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Derailment of No. 13 - SUMAN, IND. Aug. 27, 1923
Suman, Indiana
Date: August 27, 1923
Source Type: Photograph
Publisher, Printer, Photographer: Unknown
Postmark: Not applicable
Collection: Steven R. Shook
Remark: The following information concerning this train derailment was published in The Chesterton Tribune:
ENGINEER KILLED IN WRECK CAUSED BY WASHOUT
A washout on the B. &. O. railroad about half a mile east of Suman station on the B. & O., caused by the heavy rains of Sunday night, resulted in a serious wreck in which one man, George Novenger, the engineer lost his life; and four others received injuries. The train, No. 13, an express train of six express cars went down a twenty-foot embankment, the engine turning over and pinning the engineer underneath.
The dead:
George Novenger, 58 years old, engineer on the express; lives in Garrett.
The injured:
A. M. Farquhason, 30 years old, express messenger; lives at Deshler, O.
J. M. Sattenstein, 30 years old, special service officer for the American Railway Express; lives in Chicago.
H. A. Houtzer, 28 years old, train agent; lives in Lima, O.
N. E. Miller, 27 years old, fireman; lives in Garrett.
The train was going west. When within a mile of the fatal spot Novenger noticed a danger signal. He stopped the train and phoned for instructions, it is said. His train was then given clear passage.
When the wheels on the train began to grind the engineer began applying the brakes. It was too late, however. The road bed caved in, causing the engine and the first coach to go down the embankment. Miller, who was riding in the cab with Novenger, leaped out of the door. A heavy flow of water washed him more than two rods. He stopped when he struck a telephone pole. Novenger was entrapped in the cab. When found his head was buried downward in sand and water. The throttle of the engine had him pinioned. It was more than four hours after the wreck before Novenger's body was extricated. It was taken to Wellsboro and was to have been removed to Garrett this afternoon.
Miller suffered body bruises when he leaped from the engine. He was first to reach the engine after it overturned and made a futile attempt to rescue Novenger.
Farquhason, Sattenstein and Houtzer were riding in the second coach. This coach turned partly over. The three men were thrown against the side of the car causing minor injuries. Sattenstein stated it all happened so quickly that he or his fellow workmen did not have time to leap to safety.
"I felt that something was going to happen," Sattenstein declared. "And the first thing I knew I heard the wheels grinding. It seemed but a minute later that we felt our coach overturning. We certainly were lucky that it did not go all the way down. We suffered but minor injuries."
The wreck occurred about 12:25 o'clock. Word was immediately flashed to the nearby towns and help was sent to the scene of the accident. Early this morning a wrecker was in operation. It will probably take a few days to hoist the engine back on the right of way, officials of the railroad company stated.
Novenger has been in the employ of the Baltimore & Ohio System for more than thirty-five years. He was known as one of the most cautious engineers on the road an official of the company said this morning.
[Note: It is very likely that George Novenger's surname is misspelled in this article and should be written as Novinger.]
Source:
The Chesterton Tribune, Chesterton, Porter County, Indiana, on August 30, 1923; Volume 40, Number 25, Page 1, Column 6.
Copyright 2010. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
Date: March 1879
Source Type: Photograph, Carte de Visite
Publisher, Printer, Photographer: Zephaniah Pinkerton "Z. P." McMillen
Postmark: Not Applicable
Collection: Steven R. Shook
Remark: This carte de visite was included in a photograph album owned by Louise DeMotte Letherman.
Written in ink on the reverse of this carte de visite is the following:
Yours truly
Carrie A. Parker,
Mar. 1879.
On the reverse of the carte de visite is printed the following information:
Z. P. McMILLEN,
ARTIST.
12 AND 14
EAST MAIN STREET,
GALESBURG, ILLINOIS.
DUPLICATES SUPPLIED AT ANY TIME.
The photograph was taken by Zephaniah Pinkerton "Z. P." McMillen who operated a photograph studio in Galesburg, Knox County, Illinois in the 1860s and 1870s. McMillen was born March 4, 1833, and died on November 1, 1903, in Omaha, Douglas County, Nebraska.
Research has been unable to positively identify Carrie A. Parker, but this may be Carrie A. (Parker) Magers who appears in the 1900 Federal Census for Galesburg, Knox County, Illinois. This Carrie was born in December 1858, the daughter of Henry Ellsworth Parker and Cornelia F. (Roberts) Parker. She would marry Robert Magers in 1891.
Louise (DeMotte) Letherman was born August 21, 1859, in Valparaiso, Porter County, Indiana, the daughter of Mark L. DeMotte and Elizabeth (Christy) DeMotte. She married Lawrence Letherman on May 3, 1883, in Valparaiso. Louise died at Malden, Middlesex County, Massachusetts, on September 24, 1905. Louise is buried in Valparaiso's Maplewood Cemetery.
Mark Lindsey DeMotte was born in Rockville, Parke County, Indiana, on December 28, 1832, the son of Daniel DeMotte and Mary (Brewer) DeMotte. He graduated from Asbury University (now DePauw University) in Greencastle, Putnam County, Indiana, with an A.B. degree in 1853 and immediately began studying law at this institution, earning his law degree (LL.B.) in 1855. DeMotte was soon admitted to the Indiana bar and began his practice of law at Valparaiso, Porter County, Indiana.
In December 1856, Elizabeth Christy wedded DeMotte in Valparaiso, a union that resulted in two children, Louise and Mary.
DeMotte would serve in the Civil War rising to the rank of captain under the command of General Robert H. Milroy. At the conclusion of the war, DeMotte moved to Lexington, Lafayette County, Missouri, to resume his practice of law. He was an unsuccessful Republican candidate for Congress in the 1872 and 1876 elections.
DeMotte returned to Valparaiso in 1877 to practice law and would organize the Northern Indiana Law School in 1879, which later became known as the Valparaiso University School of Law (which went defunct in 2020).
DeMotte would again be a Republican candidate for Congress, winning the election of 1880, but would lose as an incumbent in the 1882 election. He would then serve in the Indiana State Senate between 1886 and 1890. He was appointed the postmaster of Valparaiso serving from March 24, 1890, to March 20, 1894. He would also serve as dean of the Northern Indiana Law School from 1890 to 1908.
DeMotte passed away on September 23, 1908, in Valparaiso and was interred in Maplewood Cemetery in that community.
Copyright 2020. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
PACK TRAIN WITH "GRUB" READY TO START FOR THE MINES
Date: Circa 1908
Source Type: Photograph Booklet
Publisher, Printer, Photographer: Augusta Anderson, Inland Printing Company
Postmark: Not Applicable
Remark: The St. Joe River was located immediately behind the photographer of this image. To the immediate right in this image, but not visible, was the St. Joe Mercantile Company - flag hanging from the mercantile is barely visible at upper right of image.
Libraries holding copies of The Shadowy St. Joe indicate that this souvenir book was published circa 1910. After researching the life of Augusta Anderson, however, it is much more likely that the book was published in 1908 or perhaps 1907. In addition, it is very likely that Augusta Anderson was neither the author of the book nor the photographer of the images contained within the book.
Augusta Anderson was born circa 1885. On February 13, 1908, in Spokane, Spokane County, Washington, Augusta married Fred D. Straffin. Straffin was a fairly well-known photographer who operated from a Spokane photography studio. Straffin published a souvenir book of the Potlatch lumber mill located in Potlatch, Latah County, Idaho, in 1907 that is very similar in design to The Shadowy St. Joe. Straffin also published a souvenir book of St. Maries, Benewah County, Idaho, which is located along the St. Joe River, that is also of nearly the same design as The Shadowy St. Joe.
Straffin was somewhat under duress when he married Augusta Anderson. According to a news item published in the Spokane Daily Chronicle on February 8, 1908, Straffin had been “charged with the seduction of Augusta Anderson, 23 years of age…. Straffin claimed that the girl yielded readily to his request that she live with him, and denied that, except in a joking way, that he had ever promised to marry her. The girl denies these statements emphatically, alleging that she took the matter seriously. She broke down several times in court.”
It is learned from a June 18, 1908, news item also published in the Spokane Daily Chronicle that Straffin and Anderson had married on February 13, 1908, so that Straffin could avoid jail and have the seduction case dismissed in superior court. This same news item mentions that Augusta was now seeking a divorce after four months of marriage because Fred had “been drunk much of the time since their marriage and has not contributed to her support.” It also notes that before the marriage that Augusta had been a waitress and specifically states that “The groom was a photographer. He offered to teach the girl the art of the offer was accepted. Before the girl had mastered her trade, however, Straffin was arrested for intimate relations with her, and was bound over to the superior court to answer to the charge.”
The 1908 divorce case apparently was dismissed since there appears in the October 11, 1910, issue of The Press, published in Spokane, a notice of a pending divorce suit between Augusta and Fred D. Straffin. The Spokane Daily Chronicle’s January 19, 1911, issue reports that the divorce was granted and states that “She [August Straffin] charged that she was deserted on the day of her wedding, which occurred in Spokane in 1908, and that her husband had never contributed to her support. She was permitted to resume her maiden name, Augusta Anderson.”
Augusta Straffin appears in the 1908 city directory for Spokane with Fred as the proprietor of the Rembrandt Studio, while later directories do not tie Augusta to any photography business. Collectively, this information suggests that Augusta Anderson had neither taken the photographs appearing in The Shadowy St. Joe – there is no evidence that she was fully trained as a photographer – nor had she compiled the book as an author. Rather, evidence strongly suggests that Fred D. Straffin was responsible for the development and publication of The Shadowy St. Joe and perhaps had August listed as author as an inducement to initiate or maintain an intimate relationship with her. It is possible the Augusta had taken the photographs and authored the book while Fred was occupied with drinking and desertion of his wife, but this calls into question as to how Augusta was fully trained as a photographer.
Fred D. Straffin was born in 1869 and died April 23, 1917, in Salt Lake City, Salt Lake County, Utah; he is buried at the Salt Lake City Cemetery in an unmarked grave. His death certificate indicates that he was a widow at the time of his death, suggesting that he may have remarried after being divorced from Augusta.
Little is known concerning August Anderson after her divorce from Fred. A notice of marriage licenses granted in Spokane County published in The Spokesman-Review on February 11, 1914, mentions that an Adam Noble or Spokane was granted a license to marry Augusta Anderson, also of Spokane. It is assumed that this is likely the same Augusta Anderson that married and divorced Fred D. Straffin.
Sources:
Anderson, Augusta. Circa 1908. The Shadowy St. Joe. Spokane, Washington: The Inland Printing Company. 54 p.
The Press, Spokane, Spokane County, Washington; October 11, 1910; Volume 8, Number 312, Page 7, Column 5. Column titled “Three Divorce Suits.”
Spokane Daily Chronicle, Spokane, Spokane County, Washington; February 8, 1908; Volume 22, Number 139, Page 3, Column 5. Column titled “He Wronged a Woman.”
Spokane Daily Chronicle, Spokane, Spokane County, Washington; June 18, 1908; Volume 22, Number 251, Page 4, Column 5. Column titled “Wedded to Dodge Jail; Divorce.”
Spokane Daily Chronicle, Spokane, Spokane County, Washington; January 19, 1911; Volume 25, Number 124, Page 7, Column 6. Column titled “Deserted Bride is Given Divorce.”
The Spokesman-Review, Spokane, Spokane County, Washington; December 10, 1907; Volume 25, Number 178, Page 18, Column 3. Column titled “Takes Pictures of Potlatch Mill.”
The Spokesman-Review, Spokane, Spokane County, Washington; February 11, 1914; Volume 31, Number 241, Page 7, Column 2. Column titled “City and County Records. Marriage Licenses.”
Copyright 2022. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
Copyright © John G. Lidstone, all rights reserved.
You are warned: DO NOT STEAL or RE-POST THIS PHOTO.
It is an offence under law if you remove my copyright marking, or post this image anywhere else without my express written permission.
If you do, and I find out, you WILL be reported for copyright infringement action to the host platform and/or group applicable.
The same applies to all of my images.
My copyright is also embedded in the image metadata.
Goal: To communicate the identity of the church to the people of Tulsa, OK. The brand had to be applicable to both campuses, traditional and contemporary worship. It had to be simple enough to be used alone, but with an emphasis on a meaningful symbolism.
Audience: People in Tulsa, OK. Since there are 2 locations, the demographic was different for each campus. One more focused on young families with children, and the other representing a much wider demographic.
Project: Church branding - Logo design
Direction:This concept is based on their tagline - "one church, two locations". The two locations are linked together like a chain and represented by triangles (a symbol for God) arranged in a K monogram.
Other important info: This concept was not used, but I wanted to share this anyway for inspiration and because I liked these concepts. So I guess it is a finished piece.
You can find herbal supplements to treat piles at www.herbalproductsreview.com/hemorrhoids-treatment-review...
Dear friend, in this video we are going to discuss about the herbal supplements to treat piles. Herbs are always close to nature and so they are safe to use and this is applicable to treating piles as well.
If you liked this video, then please subscribe to our YouTube Channel to get updates of other useful health video tutorials.
Herbal Supplements To Treat Piles
BARTHOLOMEW & McCLELLAND
DRY GOODS BOOTS SHOES
&C
IND.
VALPARAISO.
THE FLAG OF OUR UNION
1863
Date: 1863
Source Type: Civil War token
Publisher, Printer, Photographer: Bartholomew & McClelland; token manufactured by Henry Darius Higgins of Mishawaka, Indiana
Postmark: Not applicable
Collection: Steven R. Shook
Remark: During the American Civil War, coins issued by the government began to experience a severe decrease in circulation as citizens hoarded coins containing gold, silver, and copper. As a result, transacting business became increasingly difficult as the war progressed. Many merchants therefore contracted to have private minters produce tokens as a proxy for government issued coinage. Today, these tokens are referred to as "store cards."
H. A. Ratterman, of Cincinnati, Ohio, was the first merchant to circulate privately minted tokens during the fall of 1862. The United States Congress, however, banned the usage of non-government issued coins on June 8, 1864, when it enacted 18 U.S.C. § 486; this law made the minting and usage of privately minted coins illegal and punishable by a prison term of up to five years, a fine of up to $2,000, or both.
In Valparaiso, the dry goods merchants Bartholomew & McClelland issued two types of copper tokens. Both types have one side that is nearly identical, reading "BARTHOLOMEW & McCLELLAND - DRY GOODS - VALPARAISO, IND. - BOOTS SHOES &c." One version of the token has a reverse side reading "UNITED STATES CAPITAL 1863" and includes an image of the capitol building in Washington, D.C. and eight stars; note that this misspells Valparaiso as Valpariso.
The other version of the token, which is the rarer of the two, has a reverse side reading "THE FLAG OF OUR UNION 1863" and includes an image of the American flag with a Liberty cap atop the flag pole and thirteen stars.
The capital and flag designs are attributed to Henry Darius Higgins, an optician from Mishawaka, St. Joseph County, Indiana. Higgins was apparently a craftsman. Besides eyeglasses, he produced sinking dies for tokens, barometers, false teeth, and guns. Due to his tokens' homemade appearance, they are commonly referred to today as "Indiana Primitives." Higgins produced tokens for merchants located in northern Indiana and southern Michigan, and they were produced in very limited quantities. As a result, most of Higgins' token are quite scarce.
Artillus V. Bartholomew and Marquis L. McClelland formed a partnership in the dry goods business in Valparaiso in 1862, a partnership that continued for four years when McClelland left the partnership to become the cashier of the First National Bank of Valparaiso. Bartholomew continued in the dry goods business for many years after the dissolution of the partnership, forming a business partnership with Valparaiso residents Stephen Finney and Claus Specht.
This token appears in tokencatalog.com, the premier source for token information.
⦿ Fuld No. IN915A-1a; rarity R7 (10 to 20 examples known to exist)
⦿ Unlisted in Wagaman
⦿ Token Catalog No. 457085
Sources:
Blickensderfer, Scott. 2008. Bartholomew & McClelland, Valparaiso, Indiana. The Civil War Token Journal 42(1):11-33.
Fuld, George, and Melvin Fuld. 1975. U.S. Civil War Store Card. Second Edition. Lawrence, Massachusetts: Quarterman Publications, Inc. 615 p.
Wagaman, Lloyd E. 1981. Indiana Trade Tokens. Fairfield, Ohio: Indiana-Kentucky-Ohio Token and Medal Society. 302 p.
TokenCatalog.com
Copyright 2023. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
The Extinct Nilgiri Tahr, Nilgiritragus hylocrius, known locally as the Nilgiri Ibex or simply Ibex - Eravikulam National Park - Kerala, India.
______________________________________________________________________ _______________
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The Nilgiri Tahr, Nilgiritragus hylocrius, known locally as the Nilgiri Ibex or simply Ibex, is an ungulate that is endemic to the Nilgiri Hills and the southern portion of the Western Ghats in the states of Tamil Nadu and Kerala in Southern India. It is the state animal of Tamil Nadu. Despite its local name, it is more closely related to the sheep of the Ovis genus than the Ibex and wild goats of the Capra genus.
In the Tamil Language it is called varaiaadu, the term being composed of two Tamil words, wurrai a precipice, and aadu, a goat. It is also the state animal of Tamil Nadu. The ancient word in classical Tamil was "varudai" (வருடை: Natrinai, 359; Ainkurunuru, 287; Pattinappalai, 139). It was previously named Capra warryato by Gray.
The Nilgiri Tahrs are stocky goats with short, coarse fur and a bristly mane. Males are larger than the females, and have a darker color when mature. Both sexes have curved horns, which are larger in the males, reaching up to 40 centimetres (16 in) for males and 30 centimetres (12 in) for females. Adult males weigh 80 to 100 kilograms (180 to 220 lb) and stand about 100 centimetres (39 in) tall at the shoulder. Adult males develop a light grey area on their backs and are thus called "saddlebacks".
These Tahrs inhabit the open montane grassland habitat of the South Western Ghats montane rain forests ecoregion. At elevations from 1,200 to 2,600 metres (3,900 to 8,500 ft), the forests open into grasslands interspersed with pockets of stunted forests, locally known as sholas. These grassland habitats are surrounded by dense forests at the lower elevations. The Nilgiri tahrs formerly ranged over these grasslands in large herds, but hunting and poaching in the nineteenth century reduced their population to as few as 100 animals by the early 20th century. Since that time their populations have increased somewhat, and presently number about 2000 individuals. Their range extends over 400 kilometres (250 mi) from north to south, and Eravikulam National Park is home to the largest population. The other significant concentration is in the Nilgiri Hills, with smaller populations in the Anamalai Hills, Periyar National Park, Palni Hills and other pockets in the Western Ghats south of Eravikulam, almost to India's southern tip. A small populations of Tahr numbering around 200 are known to inhabit the Boothapandi, Azhakiyapandipuram, Velimalai, Kulasekaram and Kaliyal Ranges in the Kanyakumari district of Tamil Nadu and another small herd of less than 30 animals is known to inhibit Ponmudi hills in Trivandrum district of Kerala.
Source : en.wikipedia.org/wiki/Nilgiri_tahr
© 2008 2025 Lloyd Thrap Photography for Halo Media Group
All works subject to applicable copyright laws. This intellectual property MAY NOT BE DOWNLOADED except by normal viewing process of the browser. The intellectual property may not be copied to another computer, transmitted , published, reproduced, stored, manipulated, projected, or altered in any way, including without limitation any digitization or synthesizing of the images, alone or with any other material, by use of computer or other electronic means or any other method or means now or hereafter known, without the written permission of Lloyd Thrap and payment of a fee or arrangement thereof.
No images are within Public Domain. Use of any image as the basis for another photographic concept or illustration is a violation of copyright.
BARTHOLOMEW & McCLELLAND
DRY GOODS BOOTS SHOES
&C
IND.
VALPARISO.
UNITED STATES
CAPITAL
1863
Date: 1863
Source Type: Civil War token
Publisher, Printer, Photographer: Bartholomew & McClelland; token manufactured by Henry Darius Higgins of Mishawaka, Indiana
Postmark: Not applicable
Collection: Steven R. Shook
Remark: Note that Valparaiso is incorrectly spelled as Valpariso on this token.
During the American Civil War, coins issued by the government began to experience a severe decrease in circulation as citizens hoarded coins containing gold, silver, and copper. As a result, transacting business became increasingly difficult as the war progressed. Many merchants therefore contracted to have private minters produce tokens as a proxy for government issued coinage. Today, these tokens are referred to as "store cards."
H. A. Ratterman, of Cincinnati, Ohio, was the first merchant to circulate privately minted tokens during the fall of 1862. The United States Congress, however, banned the usage of non-government issued coins on June 8, 1864, when it enacted 18 U.S.C. § 486; this law made the minting and usage of privately minted coins illegal and punishable by a prison term of up to five years, a fine of up to $2,000, or both.
In Valparaiso, the dry goods merchants Bartholomew & McClelland issued two types of copper tokens. Both types have one side that is nearly identical, reading "BARTHOLOMEW & McCLELLAND - DRY GOODS - VALPARAISO, IND. - BOOTS SHOES &c." One version of the token has a reverse side reading "UNITED STATES CAPITAL 1863" and includes an image of the capitol building in Washington, D.C. and eight stars; note that this misspells Valparaiso as Valpariso.
The other version of the token, which is the rarer of the two, has a reverse side reading "THE FLAG OF OUR UNION 1863" and includes an image of the American flag with a Liberty cap atop the flag pole and thirteen stars.
The capital and flag designs are attributed to Henry Darius Higgins, an optician from Mishawaka, St. Joseph County, Indiana. Higgins was apparently a craftsman. Besides eyeglasses, he produced sinking dies for tokens, barometers, false teeth, and guns. Due to his tokens' homemade appearance, they are commonly referred to today as "Indiana Primitives." Higgins produced tokens for merchants located in northern Indiana and southern Michigan, and they were produced in very limited quantities. As a result, most of Higgins' token are quite scarce.
Artillus V. Bartholomew and Marquis L. McClelland formed a partnership in the dry goods business in Valparaiso in 1862, a partnership that continued for four years when McClelland left the partnership to become the cashier of the First National Bank of Valparaiso. Bartholomew continued in the dry goods business for many years after the dissolution of the partnership, forming a business partnership with Valparaiso residents Stephen Finney and Claus Specht.
This token appears in tokencatalog.com, the premier source for token information.
⦿ Fuld No. IN915A-2a; rarity R6 (20 to 75 examples known to exist)
⦿ Unlisted in Wagaman
⦿ Token Catalog No. 390064
Sources:
Blickensderfer, Scott. 2008. Bartholomew & McClelland, Valparaiso, Indiana. The Civil War Token Journal 42(1):11-33.
Fuld, George, and Melvin Fuld. 1975. U.S. Civil War Store Card. Second Edition. Lawrence, Massachusetts: Quarterman Publications, Inc. 615 p.
Wagaman, Lloyd E. 1981. Indiana Trade Tokens. Fairfield, Ohio: Indiana-Kentucky-Ohio Token and Medal Society. 302 p.
TokenCatalog.com
Copyright 2018. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
Date: 1920
Source Type: Photograph
Publisher, Printer, Photographer: Will Voss
Postmark: Not Applicable
Collection: Steven R. Shook
Remark: This photograph is labeled "Grand Trunk Valpo." Given its label, it is assumed that this photograph was taken near the Grand Trunk Railroad depot in Valparaiso. It appears that this locomotive is numbered 472, which suggests that it may have instead been owned and operated by the Pennsylvania Railroad since the Grand Trunk Railroad generally used a four digit numbering system for its locomotives.
This photograph was included in an album of photographs that appear to have been taken by Will Voss between 1919 and 1921. Most of the photographs in the album are labeled and dated. The bulk of the photographs in the album were taken in Illinois, Indiana, and Wisconsin.
It is apparent from the photographs taken in and around Valparaiso, Porter County, Indiana, that Will Voss was a student at Polk's School of Piano Tuning in Valparaiso.
Copyright 2023. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
JIM'S
SUPER
MARKETS
FOOD STAMP CREDIT
50¢
IN ELIGIBLE FOODS
Date: Circa 1970s
Source Type: Token
Publisher, Printer, Photographer: Plasco Company
Postmark: Not Applicable
Collection: Steven R. Shook
Remark: Jim's Super Markets, known as the Fiesta Villa Supermarket chain, operated in Michigan City, LaPorte County, Indiana, at 1002 North Karwick Road, the intersection of Ohio Street and Earl Road, and the intersection of Woodlawn Avenue and U.S. Route 20 during the 1970s and 1980s. These retail establishments were owned by James Agemy.
On August 3, 1984, Agemy would plead guilty in federal court to two charges of mail fraud in a scheme whereby his employees would redeem at face value coupons for products that they had not purchased (i.e., coupon fraud). Agemy would then issue "credit slips" to his participating employees that could be used to purchase products at his chain of stores at a discount. The fraudulent scheme resulted in the redemption of coupons in excess of $100,000 and operated over a five year period from January 1978 November 1982.
U.S. District Court Judge Allen Sharp sentenced Agemy to a suspended five year sentence of each of the two charges, imposed a fine of $1,000 on each count ($2,000 in total), and required Agemy to establish a $100,000 fund for restitution to the defrauded companies.
Beginning in the 1930s, the federal government issued coupons to families and individuals whose income level was below a certain threshold. The purpose of the coupons was to assist in the purchase of food. Today, SNAP cards are issued by the federal government for the same purpose.
During the 1970s, the lowest denomination of federally issued "food stamps" was one dollar and federal law prohibited the exchange of food stamps for money. Hence, to solve the issue of providing change to customers, companies issued credit tokens in lieu of money. These tokens could then be used to purchase "eligible food" items.
The federal law changed in January 1979 and retailers were allowed to provide change to customers as long as the coins amounted to less than one dollar. This new law essentially eliminated the use of food stamp credit tokens in the United States.
⦿ Wagaman No. m-4010; rarity modern
Sources:
Chicago Tribune, Chicago, Cook County, Illinois; August 4, 1984; Volume 136, Number 217, Page 10, Columns 1-4. Column titled "Restitution Offered in $100,000 Coupon Fraud."
South Bend Tribune, South Bend, St. Joseph County, Indiana; August 4, 1984; Volume 112, Number 148, Page 3, Column 4. Column titled "Grocer Pleads Guilty in Fraud."
South Bend Tribune, South Bend, St. Joseph County, Indiana; September 8, 1984; Volume 182, Number 148, Page 10, Columns 4-5. Column titled "Restitution Part of Sentence."
Wagaman, Lloyd E. 1981. Indiana Trade Tokens. Fairfield, Ohio: Indiana-Kentucky-Ohio Token and Medal Society. 302 p.
Copyright 2019. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
While I still intend to do a Volvo B7TL version of the Nottinghamshire repaints pack I made for the Spectra, containing a few liveries applicable to low floor vehicles, I'm sitting on it right now as I'm just not in the mood right now. In the meantime I had an idea one night of doing a livery from all the Wellglade companies on the E200 MMC, which I guess I could release on FF, perhaps... I'm torn between doing that or going all out and doing different route branded Kinchbus liveries, TM Travel 'Line 30' and all those kinds of things. The more I'm thinking the more ideas I'm getting for stuff to make - such as TM Travel liveried Spectras!
Anyway, I'm getting ahead of myself there, as right now each of the four main Wellglade Group companies are represented with one repaint each and they look pretty nice if I do say so myself (although a couple of bits still need cleaning up or adding). Up front is Kinchbus and since it's the basic livery with no route branding there's not a lot to say about it really - maybe one day in the future when the MMCs are replaced on Skylink we'll see this in real life?
Second in line is Notts and Derby, for which I had originally intended on doing their typical blue, white and lime green livery, but it didn't sit right on the MMC so instead I've had a go at their extremely new livery that features numerous arrows pointing diagonally up the side. It sits on the bus much better than the old livery did and since it's so new I've taken a generous scoop of artistic licence so that as well as being slapped onto a single decker it has a couple more arrows on the back that I doubt are there in real life, plus a blue front panel.
Back there in third is TM Travel with the livery that I initially thought of putting on the MMC and put the idea into m head of doing all four. When they came out with their 'new' livery a few years back (essentially TrentBarton 'red spare' but it says TM Travel instead) it featured a large "TM" graphic at the rear made out of a chequer pattern. It must've been a fiddly feature as they abandoned it for later repaints but I wanted to replicate it in OMSI.
Bringing up the rear is TrentBarton, which you could consider to be the least important here since TB repaints for the E200 MMC aren't exactly a new or rare phenomenon. The only thing about this one is rather than going for the yellow/Mango style as per the real MMC spares I wanted to see what they would have looked like in the version of the 'red spare' livery that, for a short time, was applied to a Versa. It's actually a shame we'll never get to see it in real life; much the same as it's a shame we'll never see a Stagecoach 'beachball' MMC with a blue front panel.
© 2018 2024 Photo by Lloyd Thrap Photography
for Halo Media Group
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#AbFav_BRIDGES_ 🌉
From building to building!
A bridge is a structure built to span a physical obstacle (such as a body of water, valley, road, or rail) without blocking the way underneath.
It is constructed for the purpose of providing passage over the obstacle, which is usually something that is otherwise difficult or impossible to cross.
There are many different designs of bridges, each serving a particular purpose and applicable to different situations.
Designs of bridges vary depending on factors such as the function of the bridge, the nature of the terrain where the bridge is constructed and anchored, and the material used to make it, and the funds available to build it.
The earliest bridges were likely made with fallen trees and stepping stones.
The Neolithic people built boardwalk bridges across marshland.
The Arkadiko Bridge (dating from the 13th century BC, in the Peloponnese) is one of the oldest arch bridges still in existence and use.
So many beauties around today, here are some we travelled over...
THANK you for ALL your comments and visits, so appreciated, have a good day, M, (*_*)
For more: www.indigo2photography.com
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bridge, high, buildings, impressive, concrete, design, colour, horizontal, NikonD7000, "Magda indigo", landscape, road, pillars, travel, pedestrian
Photos taken at The Black Country Museum 1940's Weekend, 2016. Please be respectful to the people in the photograph, (where applicable).
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Date: 1907
Source Type: Photograph
Publisher, Printer, Photographer: Kouts Centennial Book (1965)
Postmark: Not Applicable
Collection: Steven R. Shook
Remark: Morrison baseball team, 1907.
Front: Eleazer E. (Tad) Starkey, Manager
Second row, from left: Amos Mockler, Harry Mockler, Gust Lippert, Jack Wandry.
Third row, from left: Louis Wandry, Emil Lippert, Steve Mockler, Eldridge Mockler, Charles Mockler.
Morrison was a small populated area located in the east one-half of Section 23, Township 36 North, Range 6 West of Pleasant Township, Porter County, Indiana. The intersection of present day County Road 950 South and Baum's Bridge Road was in the approximate center of this community.
Source:
Centennial Committee. 1965. Kouts Centennial, 1865-1965. Kouts, Indiana: Centennial Committee. 181 p.
Copyright 2021. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
X Western Bank Note Co. Cincinnati, O. Woodruff, Tucker & Co. X
FORMED UNDER THE LIMITED PARTNERSHIP ACT
No. 189
THE INDIANA
TRUST & EXCHANGE CO.
Will pay TEN DOLLARS in current
bills on demand, value received
REAL ESTATE DEEDED IN TRUST BY
THE SPECIAL PARTNERS TO
DOUBLE THE
AMOUNT OF CAPITAL STOCK
Valparaiso Laporte Jan 1 1838
TEN E. Brown Bishop Gen.l Partner. TEN
Date: January 1, 1838
Source Type: Obsolete Scrip
Publisher, Printer, Photographer: Western Bank Note Company, Woodruff, Tucker & Company
Postmark: Not Applicable
Collection: Steven R. Shook
Remark: The $10 bank note is a bit mysterious like so many notes from this period, and other denominations are known to exist that are similar with LaPorte being overwritten with "Valparaiso." This suggests that a Valparaiso branch existed for this company or that it may have changed of location of operation.
Porter County, Indiana, was authorized into existence by the Indiana State Legislature on February 5, 1836, and organized in 1837, with Valparaiso serving as the county seat; Porter County was cleaved off from LaPorte County. At the time that this note was issued on January 1, 1838, the county was approaching its second year of existence.
Published in the January 18, 1839, issue of Der Vaterslandfreund und Geist der Zeit of Canton, Ohio, is the following information about the Indiana Trust & Exchange Company [translated from German]:
"Shinplaster. – The Hamilton Intelligencer of January 15 [1839] reported that a company of persons had smothered some parts of the county with paper money certified: The Indiana Trust $ Exchange Co. Payable cash in Laporte, Indiana and signed E. Brown Bishop, Gen’l Partner. The notes are set to one, five and ten dollars. The State of Indiana has never authorized the issuance of such paper, and does not permit anyone to see the same in circulation. More than $50,000 found their way into Preble County [Ohio]."
Published in the February 2, 1839, issue of the Richmond Palladium of Richmond, Indiana, is the following information about the Indiana Trust & Exchange Company:
Swindlers of the Shinplaster Stamp – A gang of Swindlers in Hamilton co. Ohio, have flooded some portions of that county with paper money, bearing as its title “The Indiana Trust and Exchange Co.” made payable at Laporte, Ia., and signed E. Brown Bishop, General Partner. The notes are of the denominations of ones, fives and tens. The state of Indiana has never authorized the issuing of such paper, neither does justice license any man to circulate it. More than Fifty Thousand Dollars have made their way into Preble county. – N., Y. Star.
E. Brown Bishop may be a fictitious name used to sign the Indiana Trust & Exchange Company notes given the information above. However, the 1840 and 1850 Federal Census enumerations for LaPorte County, Indiana, list Elijah Bishop; the 1850 enumeration indicating that Elijah was a farmer residing in Galena Township. Elijah is buried at Lambs Chapel Cemetery in LaPorte, LaPorte County, Indiana. His burial information indicates that he was born June 23, 1811, in Ohio, and died on December 22, 1892, in Indiana.
Furthermore, E. D. Daniels’ history of LaPorte County, published in 1904, includes a rather long biographical sketch of Henry Robertson Bishop, which includes considerable information about his father, Elijah Bishop. Elijah’s father is mentioned as being the son of Benjamin Bishop, a sailor who joined the army in the fight for independence during the Revolutionary War. Benjamin later learned the blacksmith’s trade and then turned to farming in Preble County, Ohio, before removing to Wayne County, Indiana. It is rather interesting that Elijah was likely familiar with Preble County, where these notes were circulated, and was raised in Wayne County, Indiana, the county where the Richmond Palladium was published. Elijah was a pioneer of LaPorte County, Indiana, having settled there in 1833.
Source Information:
Daniels, E. D. 1904. A Twentieth Century History and Biographical Record of LaPorte County, Indiana. Chicago, Illinois: The Lewis Publishing Company. 813 p. [see pp. 711-712]
Der Vaterslandfreund und Geist der Zeit, Canton, Stark County, Ohio; January 18, 1839; Volume 10, Number 27, Page 3, Column 2-3.
The Ohio State Journal, Columbus, Franklin County, Ohio; July 25, 1843; Volume 7, Number 7, Page 4, Column 1.
Richmond Palladium, Richmond, Wayne County, Indiana; February 2, 1839; Volume 9, Number 4, Page 1, Column 6.
Wolka, Wendell. 2018. A History of Indiana Obsolete Bank Notes and Scrip. Sun City Center, Florida: Wendell Wolka. 900 p. [see p9. 791-792]
Wolka, Wendell A., Jack M. Vorhies, and Donald A. Schramm. 1978. Indiana Obsolete Notes and Scrip. Iola, Wisconsin: Krause Publications. 306 p. [see p. 256]
Copyright 2022. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
CHAS. W. MANN
WANATAH, IND.
GOOD FOR
5¢
IN TRADE
Date: Circa 1910s
Source Type: Token
Publisher, Printer, Photographer: Unknown
Postmark: Not Applicable
Collection: Steven R. Shook
Remark: Charles W. Mann was the proprietor of a saloon located in Wanatah, LaPorte County, Indiana, during the early 1900s. Charles' death certificate notes that he was born April 21, 1869, in Indiana and died February 14, 1934, at the Logansport State Hospital located in Logansport, Cass County, Indiana. Note that Charles' place of death conflicts with the place of death mentioned in his death announcement.
In 1891, Charles W. Mann married Johanna Pauline Lawrence. Mann is buried in Sacred Heart Cemetery in Clinton Township, Cass County, Indiana.
The following news item concerning Charles W. Mann's saloon appeared in the May 21, 1910, issue of The Fort Wayne Sentinel:
CALLS HIS GIN-MILL A BANK.
Auditor of State Will Go After a Wanatah Saloonist.
Indianapolis, May 21. -- Charles W. Mann, a saloonkeeper in Wanatah, is attracting the attention of the banking department of the state because he insists in using the word "bank" in the name of his saloon, making the name as it appears on one of the windows ""The Northside Bank." The proprietor of the place believes that since the attorney general said a few days ago that the word bank could be used in the name of an establishment when it would not deceive the public he can use the word in the name of his saloon if he desires. However, his attempt to use it will be followed by prosecution, according to the auditor of the state.
Mann's death notice below appeared in the February 16, 1934, issue of The Vidette-Messenger:
HOLD RITES FOR CHARLES MANN
Funeral services for Charles Mann, age 70, a former resident of Wanatah, who died at his home in South Bend Wednesday, were held this morning at 10 o'clock at the Sacred Heart cemetery with H. A. Boelke in charge. Mr. Mann is survived by his widow, three sons, three daughters, three brothers and one sister.
⦿ Wagaman No. W-1600c.
⦿ Token Catalog No. TC-50874
Sources:
The Fort Wayne Sentinel, Fort Wayne, Allen County, Indiana; May 21, 1910; Page 7, Column 4. Column titled "Calls His Gin-Mill a Bank."
TokenCatalog.com
The Vidette-Messenger, Valparaiso, Porter County, Indiana' February 16, 1934; Volume 7, Page 6, Column 8. Column titled "Hold Rites for Charles Mann."
Wagaman, Lloyd E. 1981. Indiana Trade Tokens. Fairfield, Ohio: Indiana-Kentucky-Ohio Token and Medal Society. 302 p.
Copyright 2023. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
Crew / Passengers Rank - if applicable Position e.g. Pilot Status
Anthony Arthur Clifford Flying Officer RCAF Pilot Killed
Kenneth McIvor Flying Officer RCAF Flight Engineer Killed
David Fehrman Flying Officer RCAF Bomb Aimer Killed
Michael Cecil Cameron Warrant Officer RCAF Wireless Operator Killed
Clarence Halvorson Flight Sergeant RCAF Air Gunner Killed
Leslie Claude Hellekson Flight Sergeant RCAF Air Gunner Killed
The aircraft was flying from RAF Linton-on-Ouse and had earlier been carrying out bumps and circuits but the crew became tired of this and decided to fly around the local area. As it became dark the crew became disorientated and eventually ended up circling Glossop. The aircraft was observed flying into the hillside at 10:10pm.
The demise of KB993 in May 18th 1945 was one of the first post World War 2 crashes on high ground, ten days after the end of hostilities.
There was no navigator on board because the crew should have been carrying out only circuits, a task which he would have had no part in.
Text by kind permission of Alan L Clark www.peakdistrictaircrashes.co.uk
30th ANNUAL CONVENTION
LAPORTE DISTRICT LUTHER LEAGUE
PORTER, IND., JUNE 23-24, 1928
Date: June 23, 1928
Source Type: Photograph
Publisher, Printer, Photographer: Olsen Studio
Postmark: Not Applicable
Collection: Steven R. Shook
Remark: This panoramic group photograph of the attendees of the 30th Annual Convention of the LaPorte District Luther League was taken along the south side of the Augsburg Evangelical Lutheran Church. This church no longer stands and was replaced by a more modern and larger church. The church stood at the southeast corner of the present day intersection of Beam Street and Mineral Springs Road in Porter, Porter County, Indiana.
The congregation's cemetery was located immediately south of the church building and a few tombstones are visible to the far left and right sides of this photograph.
The following news item concerning this meeting appeared in the June 28, 1928, issue of The Vidette-Messenger:
LUTHER LEAGUE MEET CLOSES
With 52 registered delegates the climax of the thirtieth annual convention of the LaPorte district Luther League was reached at services in the Porter Lutheran church Tuesday afternoon when between 400 and 500 persons heard Rev. Joseph A. Parkander, of Chicago, deliver a stirring sermon in "The Three-Fold Challenge to the Youth of Our Church."
Officers named were: Rev. Frank Bonander, East Chicago, president; Paul Crlson, Miller, vice-president; Viola Lindstrom, Miller, recording secretary; Margaret Johnson, Gary, corresponding secretary; Franklin Lindborg, Hobart, treasurer; Vernon Carlson, Porter, delegate to the Long Lake, Ill., conference Jul 16 to 22. The next meeting will be held in Gary on June 22 and 23, 1929.
Source:
The Vidette-Messenger, Valparaiso, Porter County, Indiana; June 28, 1928; Volume 1, Page 4, Column 3.
Copyright 2023. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
The Golden Temple - Amritsar, Punjab, India.
An old photo, reposted for those who have not seen earlier. One of my favourite photo.
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The Harmandir Sahib (Punjabi: ਹਰਿਮੰਦਰ ਸਾਹਿਬ), also Darbar Sahib (Punjabi: ਦਰਬਾਰ ਸਾਹਿਬ, Punjabi pronunciation: [dəɾbɑɾ sɑhɪb]) and informally referred to as the "Golden Temple", is a prominent Sikh Gurdwara located in the city of Amritsar, Punjab, India. It was built by the fifth Sikh guru, Guru Arjun, in the 16th Century. In 1604, Guru Arjun completed the Adi Granth, the holy scripture of Sikhism, and installed it in the Gurudwara.
There are four doors to get into the Harmandir Sahib, which symbolize the openness of the Sikhs towards all people and religions. The present day Gurdwara was rebuilt in 1764 by Jassa Singh Ahluwalia with the help of other Sikh Misls. In the early nineteenth century, Maharaja Ranjit Singh secured the Punjab region from outside attack and covered the upper floors of the Gurdwara with gold, which gives it its distinctive appearance and its English name.
The Harimandir Sahib is considered holy by Sikhs. The holiest text of Sikhism, the Guru Granth Sahib, is always present inside the Gurdwara. Its construction was mainly intended to build a place of worship for men and women from all walks of life and all religions to come and worship God equally. Over 100,000 people visit the holy shrine daily for worship.
The Harmandir Sahib literally means The Temple of God. The fourth guru of Sikhism, Guru Ram Das, excavated a tank in 1577 CE which subsequently became known as Amritsar (meaning "Pool of the Nectar of Immortality"), giving its name to the city that grew around it. In due course, a Sikh edifice, Sri Harmandir Sahib (meaning "the abode of God"), rose in the middle of this tank and became the supreme centre of Sikhism. Its sanctum came to house the Adi Granth comprising compositions of Sikh Gurus and other saints considered to have Sikh values and philosophies, e.g., Baba Farid, and Kabir. The compilation of The Adi Granth was started by the fifth guru of Sikhism, Guru Arjan Dev Ji.
Chesterton-Porter Ice Co.
Chesterton, Indiana
Date: Circa 1900
Source Type: Photograph
Publisher, Printer, Photographer: Unknown
Postmark: Not Applicable
Collection: Steven R. Shook
Remark: This photograph was taken at the present day T-intersection of Calumet Road and Broadway Avenue, facing the east side of Calumet Avenue. The building to the left in the photograph was the Chesterton Town Hall and fire station. Both buildings shown in the photograph still stand [2014]. Anton G. Gustafson owned a one-half interest in the Chesterton-Porter Ice Company. Gustafson was born in Westchester Township, Porter County, Indiana, on February 19, 1861, the son of Adolph and Clara (Swanson) Gustafson, natives of Sweden. Anton married Rose Thomas on December 31, 1894, and they had four children: Raymond Thomas, Mildred G., Mary C., and Lois. Anton served as recorder of Porter County, a trustee of Westchester Township, and postmaster of Chesterton.
The sign in the window above the horse's neck states: "MILES ORTON'S 25 CENT SHOWS." The round sign behind the delivery wagon states: "PABST MILWAUKEE, POOL & BILLIARDS." Miles Orton was a circus performer and one of the foremost bareback horse trick riders of his day.
The storefront sign of SARATOGA, J. A. KREIGER was a saloon and billiard hall and saloon. J. A. KREIGER refers to John A. Krieger (notice difference in spelling of surname), owner of the structure. Krieger would later rename his establishment The Klondike Saloon.
Interestingly, John A. Krieger was president of the Chesterton Cemetery Association, while Anton G. Gustafson served as that association's secretary in the early 1900s.
---------------
The following news item appeared in the November 7, 1902, issue of The Chesterton Tribune:
Chesterton Chips.
The "Saratoga" is the name of the swellest drinking resort in Chesterton. It is J. A. Krieger's new place on Valparaiso street. The building is heated by hot water, has its own water works run by gasoline engine, and a splendid system of lighting. The upper floor, 28x70, is to be used as a ball room, and has one of the finest hardwood floors in this part of the state. In one corner is a toilet room, equipped with all the modern conveniences of city buildings. The furniture of the bar room is birchwood with mahogany finish, and the billiard room is equipped with two pool and one billiard tables. The proprietor has spared neither pains nor expense to make the "Saratoga" the finest pleasure resort in this part of the county, and in fact Valparaiso has no place that can compare with it.
---------------
The following news item appeared in the May 17, 1906, issue of The Chesterton Tribune:
LOCAL NEWS OF THE WEEK
Gustafson & Kreiger, the ice-dealers, are setting a very bad example to the ice-trust of the country. They announce that they will furnish ice as long as their ice-houses hold out to their customers for the same rate paid last year. There will be no raise of rates here until the local supply is exhausted, and then if the supply does not hold out, which may not be likely, the users will pay for what they get at actual cost rate, plus cost of delivering.
Sources:
The Chesterton Tribune, Chesterton, Porter County, Indiana; November 7, 1902; Volume 19, Number 31, Page 5, Column 5. Column titled "Chesterton Chips."
The Chesterton Tribune, Chesterton, Porter County, Indiana; May 17, 1906; Volume 23, Number 7, Page 5, Column 4. Column titled "Local News of the Week."
Copyright 2014. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
The Kid -
At the Chamera Lake - near Dalhousie, Chamba District, Himachal Pradesh, India.
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Copyright © learning.photography.
All rights reserved. All images contained in this Photostream remain the property of learning.photography and is protected by applicable Copyright Law. Any images from this Photostream may not be reproduced, copied, or used in any way without my written permission.
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The Chamera Dam impounds the River Ravi and supports the hydroelectricity project in the region. It is located near the town of Dalhousie, in the Chamba district in the state of Himachal Pradesh in India The reservoir of the dam is the Chamera Lake.
After completion of the first phase, the Chamera-I generates 540 MW (3x180 MW) of electricity. The second stage i.e. Chamera-II Dam generates 300 MW (3X100 MW) of electricity. From year 2012, the 3rd stage i.e. Chamera III generates 231 MW (3x77) of electricity.
The unique feature of the region is the fluctuating day and night temperature. The temperature during the day near the dam rises up to 35 degrees Celsius and drops to a minimum of 18 to 20 °C at night.
The water level in the Chamera Lake rises to a maximum of 763 meters while the minimum water level is 747 meters.
The absence of aquatic life in the lake has made it an ideal location for water sports. According to the plan developed by the tourism department, the lake shares the scope of sports activities like rowing, motor boating, paddle boating, sailing, canoeing, angling and kayaking. House boats and shikaras are also available. The government attempts to provide all these facilities to the tourists.
SOURCE : en.wikipedia.org/wiki/Chamera_Dam
Copyright © John G. Lidstone, all rights reserved.
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OUR
CARD
J. M. NEUBURGER
CLOTHIER
BALL'S
CORNER
LAPORTE, IND,
Date: Circa 1861-1864
Source Type: Civil War token
Publisher, Printer, Photographer: Unknown
Postmark: Not Applicable
Collection: Steven R. Shook
Remark: During the American Civil War, coins issued by the government began to experience a severe decrease in circulation as citizens hoarded coins containing gold, silver, and copper. As a result, transacting business became increasingly difficult as the war progressed. Many merchants therefore contracted to have private minters produce tokens as a proxy for government issued coinage. Today, these tokens are referred to as "store cards."
H. A. Ratterman, of Cincinnati, Ohio, was the first merchant to circulate privately minted tokens during the fall of 1862. The United States Congress, however, banned the usage of non-government issued coins on June 8, 1864, when it enacted 18 U.S.C. § 486; this law made the minting and usage of privately minted coins illegal and punishable by a prison term of up to five years, a fine of up to $2,000, or both.
Jacob M. Neuburger was an early Jewish businessman in the community of LaPorte, LaPorte County, Indiana. He was born July 4, 1840, in St. Louis, Missouri, and educated in the common schools of Cincinnati.
Jacob's initial occupation was serving as a clerk in a dry goods store. It is believed that he then entered the retail clothing business in LaPorte. Jacob married Rebecca Hamburger on January 2, 1867, and their union resulted in three children.
In 1870, Neuburger entered the insurance business in LaPorte and served as a district agent for the Imperial Insurance Company from 1871 to 1873. From October 1873 to August 1891, he was serving as a special agent for the German-American Insurance Company. He was then appointed the manager of the Atlas Insurance Company of London.
Jacob died on September 18, 1910, in Chicago, Cook County, Illinois, and was interred in B'Nae Zion Jewish Cemetery in LaPorte.
⦿ Fuld No. IN530D-1a; rarity R6 (20 to 75 examples known to exist)
⦿ Unlisted in Wagaman
⦿ Unlisted in Token Catalog
Sources:
Chas. T. Rothermel & Co. 1895. Portraits and Biographies of the Fire Underwriters of the City of Chicago. Chicago, Illinois: Chas. T. Rothermel & Co. 384 p. [see p. 72]
Find A Grave Memorial No. 18550247
Fuld, George, and Melvin Fuld. 1975. U.S. Civil War Store Card. Second Edition. Lawrence, Massachusetts: Quarterman Publications, Inc. 615 p.
Wagaman, Lloyd E. 1981. Indiana Trade Tokens. Fairfield, Ohio: Indiana-Kentucky-Ohio Token and Medal Society. 302 p.
TokenCatalog.com
Copyright 2019. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
This booklet describes the properties and scientific research applicable to the "Blaydon foundry coke" manufactured by the Priestman Collieries at Blaydon-on-Tyne, a little upstream from Newcastle. Coal is not 'just' coal but different types and seams have differing properties and some, such as for metallurgical foundry coke, are better than others depending on factors such as structure, ash and sulphur content and calorific value.
It shows the details of this specific coke as well as showing some of the laboratory and testing processes that Priestman, obviously a very organised and scientific concern, undertook to ensure the product supplied was consistant. It includes a copy of a letter, dated 1929, from a 'satisfied customer' for Blaydon Burn Coke - this being one Sir W G Armstrong, Whitworth & Co Ltd. They also mention that this specific foundry coke is manufactured in by-product (or bye-products) ovens and that they also produce a coke manufactured for those foundries that preferred the older Beehive Coke, the Priestman Garsfield Beehive Foundry Coke.
le corbusier. modulor: a harmonious measure to the human scale universally applicable to architecture and mechanics. 1954. faber and faber. london
In a debate with Council and the Commission on the October European Council, MEPs urged leaders to not waste any more time and take urgent action to tackle the energy crisis.
Read more: www.europarl.europa.eu/news/en/press-room/20221014IPR4321...
This photo is free to use under Creative Commons license CC-BY-4.0 and must be credited: "CC-BY-4.0: © European Union 2022– Source: EP". (creativecommons.org/licenses/by/4.0/) No model release form if applicable. For bigger HR files please contact: webcom-flickr(AT)europarl.europa.eu
My Card.
© 2009 2014 Photo by Lloyd Thrap Photography for Halo Media Group
All works subject to applicable copyright laws. This intellectual property MAY NOT BE DOWNLOADED except by normal viewing process of the browser. The intellectual property may not be copied to another computer, transmitted , published, reproduced, stored, manipulated, projected, or altered in any way, including without limitation any digitization or synthesizing of the images, alone or with any other material, by use of computer or other electronic means or any other method or means now or hereafter known, without the written permission of Lloyd Thrap and payment of a fee or arrangement thereof.
No images are within Public Domain. Use of any image as the basis for another photographic concept or illustration is a violation of copyright.
On Highest Hill
Date: 1928
Source Type: Photograph
Publisher, Printer, Photographer: Unknown
Postmark: Not applicable
Collection: Steven R. Shook
Remark: The fire tower on Mount Jackson is believed to have been erected during the early 1920s and removed at some time in the 1930s. The photograph indicates that the tower was located on the "highest hill," which would be Mount Tom. This is incorrect since it is known that the fire tower was located on the crest of Mount Jackson. This photograph was part a group of photographs taken on a family's vacation to the Indiana Dunes State Park in 1928.
Copyright 2015. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
Derailment of No. 13 - SUMAN, IND, - Aug. 27, 1923
Suman, Indiana
Date: August 27, 1923
Source Type: Photograph
Publisher, Printer, Photographer: Unknown
Postmark: Not applicable
Collection: Steven R. Shook
Remark: The following information concerning this train derailment was published in The Chesterton Tribune:
ENGINEER KILLED IN WRECK CAUSED BY WASHOUT
A washout on the B. &. O. railroad about half a mile east of Suman station on the B. & O., caused by the heavy rains of Sunday night, resulted in a serious wreck in which one man, George Novenger, the engineer lost his life; and four others received injuries. The train, No. 13, an express train of six express cars went down a twenty-foot embankment, the engine turning over and pinning the engineer underneath.
The dead:
George Novenger, 58 years old, engineer on the express; lives in Garrett.
The injured:
A. M. Farquhason, 30 years old, express messenger; lives at Deshler, O.
J. M. Sattenstein, 30 years old, special service officer for the American Railway Express; lives in Chicago.
H. A. Houtzer, 28 years old, train agent; lives in Lima, O.
N. E. Miller, 27 years old, fireman; lives in Garrett.
The train was going west. When within a mile of the fatal spot Novenger noticed a danger signal. He stopped the train and phoned for instructions, it is said. His train was then given clear passage.
When the wheels on the train began to grind the engineer began applying the brakes. It was too late, however. The road bed caved in, causing the engine and the first coach to go down the embankment. Miller, who was riding in the cab with Novenger, leaped out of the door. A heavy flow of water washed him more than two rods. He stopped when he struck a telephone pole. Novenger was entrapped in the cab. When found his head was buried downward in sand and water. The throttle of the engine had him pinioned. It was more than four hours after the wreck before Novenger's body was extricated. It was taken to Wellsboro and was to have been removed to Garrett this afternoon.
Miller suffered body bruises when he leaped from the engine. He was first to reach the engine after it overturned and made a futile attempt to rescue Novenger.
Farquhason, Sattenstein and Houtzer were riding in the second coach. This coach turned partly over. The three men were thrown against the side of the car causing minor injuries. Sattenstein stated it all happened so quickly that he or his fellow workmen did not have time to leap to safety.
"I felt that something was going to happen," Sattenstein declared. "And the first thing I knew I heard the wheels grinding. It seemed but a minute later that we felt our coach overturning. We certainly were lucky that it did not go all the way down. We suffered but minor injuries."
The wreck occurred about 12:25 o'clock. Word was immediately flashed to the nearby towns and help was sent to the scene of the accident. Early this morning a wrecker was in operation. It will probably take a few days to hoist the engine back on the right of way, officials of the railroad company stated.
Novenger has been in the employ of the Baltimore & Ohio System for more than thirty-five years. He was known as one of the most cautious engineers on the road an official of the company said this morning.
[Note: It is very likely that George Novenger's surname is misspelled in this article and should be written as Novinger.]
Source:
The Chesterton Tribune, Chesterton, Porter County, Indiana, on August 30, 1923; Volume 40, Number 25, Page 1, Column 6.
Copyright 2010. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
Date: 1972-1995
Source Type: Patch
Publisher, Printer, Photographer: Unknown
Postmark: Not Applicable
Collection: Steven R. Shook
Remark: The beekeeping merit badge was initiated by the Boy Scouts in 1914; at that time the merit badge included a four-legged black bee. The design of the badge was changed in 1939 to a six-legged black honey bee. In 1952, the design was again changed with a six-legged wasp-like bee on a blue background. The design of the badge above was implemented in 1956 with minor modifications in following years.
The beekeeping merit badge project was discontinued by the Boy Scouts in 1996.
Copyright 2016. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
COLLEGE BANK,
VALPARAISO, IND.
ONE CENT.
RECEIVABLE AT THE
COMMERCIAL COLLEGE
C. W. BOUCHER, Cashier.
H. B. BROWN, President.
Date: Circa 1875-1900
Source Type: Obsolete Scrip
Publisher, Printer, Photographer: Unknown
Postmark: Not Applicable
Collection: Steven R. Shook
Remark: The Northern Indiana Normal School and Business Institute, which operated from 1873 through 1900, later to be renamed Valparaiso College in 1900, and then renamed again as Valparaiso University in 1906, issued scrip as a form of trade. The Institute's Commercial College is known to have issued scrip in denominations of 1¢, 2¢, 5¢, 10¢, 25¢, 50¢, $1, $2, $10, $20, $50, $100, $500, $1,000, and $5,000, which was fictitiously backed by its deposits held in the First National Bank located in Chicago, Cook County, Illinois, or the Merchants Commercial Bank of Cleveland, Cuyahoga County, Ohio. This represents an example of an uncirculated 1¢ scrip note.
This example is not listed in Schingoethe and Schingoethe and therefore is believed to have a rarity of R7 (only one to four known examples exist).
Source Information:
Schingoethe, Herb, and Martha Schingoethe. 1993. College Currency: Money for Business Training. Port Clinton, Ohio: BNR Press. 463 p.
Wolka, Wendell. 2018. A History of Indiana Obsolete Bank Notes and Scrip. Sun City Center, Florida: Wendell Wolka. 900 p. [see p. 865]
Wolka, Wendell A., Jack M. Vorhies, and Donald A. Schramm. 1978. Indiana: Obsolete Notes and Scrip. Iola, Wisconsin, Krause Publications. 306 p. [see p.299]
Copyright 2023. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
Date: Circa 1880
Source Type: Photograph, Carte de Visite
Publisher, Printer, Photographer: Thomas D. Saunders
Postmark: Not Applicable
Collection: Steven R. Shook
Remark: This carte de visite was included in a photograph album owned by Louise DeMotte Letherman.
Written in pencil on the reverse of this carte de visite is the following:
Mrs. Annie Zeiler.
Anna "Annie" B. (Carpenter) Zeiler was born August 1860 in Missouri. She married James E. Zeiler in Lafayette County, Missouri, on December 19, 1877. Annie died on June 6, 1905, in Kansas City, Jackson County, Missouri, and was buried at Mount Washington Cemetery in Independence, Jackson County, Missouri.
On the reverse of the carte de visite is printed the following information:
FROM
SAUNDERS'
NEW STUDIO.
LEXINGTON, MISSOURI.
One Door East of Old Stand.
OPPOSITE COURT HOUSE.
This photograph was taken by Thomas D. Saunders, a well-known photographer of Lexington, Lafayette County, Missouri. Saunders was born in Kansas City, Jackson County, Missouri, on August 16, 1831, and passed away in Lexington on July 31, 1898.
Louise (DeMotte) Letherman was born August 21, 1859, in Valparaiso, Porter County, Indiana, the daughter of Mark L. DeMotte and Elizabeth (Christy) DeMotte. She married Lawrence Letherman on May 3, 1883, in Valparaiso. Louise died at Malden, Middlesex County, Massachusetts, on September 24, 1905. Louise is buried in Valparaiso's Maplewood Cemetery.
Mark Lindsey DeMotte was born in Rockville, Parke County, Indiana, on December 28, 1832, the son of Daniel DeMotte and Mary (Brewer) DeMotte. He graduated from Asbury University (now DePauw University) in Greencastle, Putnam County, Indiana, with an A.B. degree in 1853 and immediately began studying law at this institution, earning his law degree (LL.B.) in 1855. DeMotte was soon admitted to the Indiana bar and began his practice of law at Valparaiso, Porter County, Indiana.
In December 1856, Elizabeth Christy wedded DeMotte in Valparaiso, a union that resulted in two children, Louise and Mary.
DeMotte would serve in the Civil War rising to the rank of captain under the command of General Robert H. Milroy. At the conclusion of the war, DeMotte moved to Lexington, Lafayette County, Missouri, to resume his practice of law. He was an unsuccessful Republican candidate for Congress in the 1872 and 1876 elections.
DeMotte returned to Valparaiso in 1877 to practice law and would organize the Northern Indiana Law School in 1879, which later became known as the Valparaiso University School of Law (which went defunct in 2020).
DeMotte would again be a Republican candidate for Congress, winning the election of 1880, but would lose as an incumbent in the 1882 election. He would then serve in the Indiana State Senate between 1886 and 1890. He was appointed the postmaster of Valparaiso serving from March 24, 1890, to March 20, 1894. He would also serve as dean of the Northern Indiana Law School from 1890 to 1908.
DeMotte passed away on September 23, 1908, in Valparaiso and was interred in Maplewood Cemetery in that community.
Copyright 2020. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
Snapped at the Palace Lawn of erstwhile Maharaja of Patiala - now a Himachal Pradesh Tourism Hotel - at Chail - Himachal Pradesh, India.
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When Bhupinder Singh, Maharaja of Patiala was expelled from Shimla - The Summer Capital of the British India, he decided to create his own capital for the warm months. The little village of Chail was perfect. It lay surrounded by magnificent deodar forests, Shimla was in direct vision and most importantly, Chail at 2226 m was somewhat higher than British controlled Shimla. Today, the Maharaja's creation can be experienced by everyone. And for Himachal Tourism, now owner of the gracious mansion, every visitor is a Royalty. Here is a resort in the true sense of the word. A beautiful Palace with ornate furniture, charming cottages, delightful log huts, thick forests, quiet walks, a 'lovers hill', an orchard of its own, elegant lawns, badminton and lawn tennis court, billiards and even a children's park. Each regally appointed room, each quaint cottage and every warm log hut offers a memorable holiday. Whether you are on a honeymoon and in search of seclusion or wish to organize a conference, Chail offers it all. Then, there are good sightseeing places and possibility of some fishing and trekking. Chail also has the world's highest cricket pitch and polo ground. After accession to the Indian Union, Maharaja of Patiala donated most of his buildings to Chail Military School and Government of India.
Chail is connected by road. From Shimla via Kufri the distance is 45 km and via Kandaghat is 61 km. Kalka is 86 km away. Regular buses for Chail leave from Shimla, Chandigarh and Delhi. The closest airports are at Chandigarh (120 km) and Shimla (63 km).
In winter, the temperature can drop below freezing point when heavy woolens are required. In summer the climate is mild and light woolens / cottons are recommended.
Source : www.hptdc.nic.in/cir0104.htm
Photographed at Destination Star Trek Europe (NEC Birmingham) 2016.
Please respect the people, (where applicable), in the photo
Enchanted Forest
The Playland of the Indiana Dunes
Date: Circa 1979
Source Type: Brochure
Publisher, Printer, Photographer: Unknown
Postmark: Not Applicable
Collection: Steven R. Shook
Remark: Enchanted Forest began operations in 1956. It was located on a 35 acre tract of land on the north side of U.S. Route 20 west of Indiana State Road 49. Ted Kruse of Beverly Shores, Indiana, Joseph Karras of Michigan City, Indiana, and James Marzano of Chicago were developers of the amusement park. Initially, the park included thirty deer, elk, mountain goats, buffalo, and guanacos.
The grounds also included a amusement park, concessions, restaurant, picnic area, Santa Claus Workshop, and Story Book Lane, which used animals to portray nursery rhymes.
As a result of poor weather conditions and a heavy debt load, the park filed for Chapter 11 bankruptcy reorganization in April 1990, but soon filed for Chapter 7 bankruptcy dissolution in December 1990. The real estate and all assets on the property were sold at public auction on Saturday, October 19, 1991, by Norton Auctioneers of Michigan, Inc.
Information Sources:
The Vidette-Messenger, Valparaiso, Porter County, Indiana; February 20, 1956; Volume 29, Number 194, Page 7, Column 2. Column titled "Deer, Elk, Other Animals Featured At U. S. 20 Woods."
The Vidette-Messenger, Valparaiso, Porter County, Indiana; March 18, 1991; Volume 64, Number 249, Page 3A, Columns 1-4. Column titled "Enchanted Forest is Closed for Good," by William Thompson.
Copyright 2021. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
Interior of Truss-Roof Stock Shed Chicago Hydraulic Pressed Brock Co.'s Plant
Date: 1906
Source Type: Photograph
Publisher, Printer, Photographer: The Clay-Worker, March 1906
Postmark: Not Applicable
Collection: Steven R. Shook
Remark: In 1890, the Chicago Hydraulic Pressed Brick Company established a large production facility at Porter. Two additional facilities were erected in Porter over the next decade. On October 21, 1904, the plant was destroyed by fire, with the exception of the barns, clay sheds, and some minor buildings. The fire resulted in a loss reported to be $50,000. Early in the spring of 1905 the plant was rebuilt, and the buildings were made to be more fire proof. The image shows the brick manufacturing facility in 1906 after it was rebuilt. The facility ceased operations in 1924 when clay was becoming scarce, and thereby too expensive, to make brick manufacturing profitable in the area.
This image was obtained from the following article published in the March 1906 issue in The Clay-Worker:
A MODEL PRESSED BRICK PLANT.
A MODEL PLANT, unique in more than one detail, is that put into commission by the Chicago Hydraulic Pressed Brick Co., at the beginning of the season just closed. Located at Porter, Ind., it has risen, Phoenix-like, (with apologies for that thread-bare phrase) from the ashes of the company's first plant, which was destroyed by fire October, 1904.
A device for using the waste heat from the cooling kilns in a dryer into which the brick are run on rack cars directly from the presses and again directly to the kilns, a truss roof stock shed absolutely without center supports to interfere with handling, and a movable shelter shed under which the clay is dug out from the rich clay bank, are among the features which make the Hydraulic's plant at Porter, remarkable among the other pressed brick plants in the country.
The Chicago Pressed Brick Company was incorporated February, 1890. It is controlled by the Hydraulic Pressed Brick Company of St. Louis, which, prior to 1890, had furnished practically ninety per cent. of the face brick of all colors used in Chicago. Operating at Porter, Ind., prior to 1890 were the Purington-Kimbell Brick Company, the Thomas Moulding Company, and the Hinchcliff and Owen Brick Company.
The Chicago Hydraulic Pressed Brick Company purchased the yards from the parties last named, and other acreage comprising a total of 420 acres. This area contains the only deposits of clay burning a deep red, within 150 miles of Chicago. As Porter is only 45 miles from Chicago, and with an unlimited supply of clay, the object of the Chicago Hydraulic Pressed Brick Company in securing this property is self-evident.
The plant up to October 1904 had a capacity of 20,000,000 brick a year. Then came the fire, entirely destroying this valuable and productive plant, at the close of a season when it had been worked to its limit. The Company was not long in preparing the recoup this loss and rebuild the plant. Rebuilding operations commenced March 2, 1905, were completed the following May, and the plant is now the most modern pressed brick plant owned by any company, according to Chicago experts. No expense was spared in rebuilding, and every advantage given be recent patents in handling the product in an up-to-date manner, was eagerly seized by the alert management. E. C. Kimbell himself, had immediate oversight of almost every detail, and spent the greater part of his time down at Porter during the building of the new plant.
The output of the plant during its first year was practically 18,000,000. Being located on the Michigan Central, the Lake Shore and Michigan Southern railways, with switch connections with the Pere Marquette and the Elgin, Joliet and Eastern, the shipping facilities are perfect. The plant is equipped to run winter and summer, and since rebuilding, has been run continually to its full capacity.
The officers of the company are: E. C. Eliot, president, St. Louis; F. G. Middlekauff, first vice-president, St. Louis; F. L. Joy, second vice-president and secretary, St. Louis; G. F. Baker, treasurer, St. Louis; and E. C. Kimbell, assistant secretary and general manager, Chicago.
At the Hydraulic's new plant it has been demonstrated for the first time that a pressed brick manufactured by the hydraulic process can be successfully passed through a dryer in which the waste heat from the cooling kilns is used, and this process in addition to turning out a superior product of brick, lessens the cost considerably, as the brick have only one handling from machine to kiln, ready to set. Reference to the cut will show the position of the rack car as bricks are being loaded onto the pallets direct from the machine. This will make it clear to any one interested in the manufacture of pressed brick wherein the advantage of handling brick in this manner lies.
A 50,000 per day Potts machine for the manufacture of sand molded brick, which are also handled through the dryer, is another feature of the plant, and the cut shows also the sand mold clay pit with the track cars are drawn up the incline by cable direct to the disintegrating hopper.
One of the prize features of the plant, however, is the temporary shelter shed which has been installed. This follows along the clay bank as the clay is dug out, enabling the shovelers to work in any kind of weather. This shed is thirty-two feet square. The corner supports are six by eight timbers. The "bank side" of the shelter is seven feet high and runs along the top of the bank on a grooved wheel which rides a track set on a plank. The low side is sixteen feet high and also rides along on grooved wheels set at the two lower corners, these also running on a track bent to a plank. This shed keeps twelve feet of the clay bank under operation. Two tracks run through it and the cars carry the clay away as it is "mined." A volcano stove rests on a platform which is hung from a truss in the roof by rods. The mean leave their dinner pails around this stove and have hot dinners, while on an ordinary winter day the temperature is so hot that the men work with their coats off. The shelter is equally good against the heat of summer, however. The shed is so strong that it has been found possible to explode a two-pound charge of dynamite under it without effecting [sic] it at all, and one man with a crowbar can "pinch," the whole structure along by working at the front wheel.
Another cut shows the main passageway into the kilns, and the track used to bring brick from the dryers direct to the kiln. Three transfer tracks run from the main kiln track, and each car on these tracks is a double transfer car. These double cars run on a four-foot guage [sic]. The pallet or rack cars are on a two-foot guage [sic]. These run out from the dryers to the double transfer cars, aboard the double transfer cars, down the movable tracks, running into the kilns. These movable tracks are also two-foot guage [sic], and the cars are run off the transfer car direct to the kilns.
The interior of the stock shed is also shown in a cut. It is 290 feet long and sixty-four feet wide. Its truss roof and absence of center posts make it absolutely unique. A loading track runs through the center of the shed. It is the first stock shed of its kind used for this purpose.
This model plant is in charge of W. J. Soper, the superintendent, who, with the exception of three years has been with the company since its organization.
Source:
Anonymous. 1906. A Model Pressed Brick Plant. The Clay-Worker 45(3):475-476.
Copyright 2021. Some rights reserved. The associated text may not be reproduced or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of Steven R. Shook.
Anyway, a pheasant on my wall.
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LOGIE-BUCHAN, a parish, in the district of Ellon, county of Aberdeen, 2 miles (E. by S.) from Ellon; containing 713 inhabitants.
The word Logie, expressive of a low-lying spot, was given to this place on account of its applicability to the tract in which the church is situated; while the affix is descriptive of the position of the parish in that part of the county called Buchan.
Logie-Buchan is separated on the east from the German Ocean by the parish of Slains, and is intersected by the river Ythan.
The river abounds with various kinds of trout, also with salmon, eels, lounders, and mussels; and pearls are still occasionally found.
It has a ferry opposite the parish church, where its breadth at low water is about sixty yards; and two boats are kept, one for general passengers, and the other, a larger boat, for the conveyance of the parishioners to church from the northern side.
A tradition has long prevailed that the largest pearl in the crown of Scotland was obtained in the Ythan; and it appears that, about the middle of the last century, £100 were paid by a London jeweller to gentleman in Aberdeen, for pearls found in the river.
Most of the inhabitants of the district are employed in agricultural pursuits, a small brick-work recently established being the only exception.
The great north road from Aberdeen passes through the parish, and the mail and other public coaches travel to and fro daily. On another road, leading to the shipping-port of Newburgh, the tenantry have a considerable traffic in grain, lime, and coal, the last procured from England, and being the chief fuel.
The river Ythan is navigable for lighters often or twelve tons' burthen at high water. The marketable produce of the parish is sent to Aberdeen. Logie- Buchan is ecclesiastically in the presbytery of Ellon, synod of Aberdeen, and in the patronage of Mr. Buchan.
The church was built in 1787, and contains 400 sittings.
Cemeteries - Presbyterian / Unitarian
Logie Buchan Parish Church, Logie-Buchan, Church of Scotland
The church of Logie-Buchan was dedicated to St Andrew.
St Andrew's Church was built in 1787 and has been much altered. It contains a 1728 bell.
Logie-Buchan (Aberdeen, Buchan). Also known as Logie Talargy, the church was granted by David II in 1361 to the common fund of the canons of Aberdeen cathedral, and this was confirmed to the uses of the canons by Alexander, bishop of Aberdeen in 1362, both parsonage and vicarage fruits being annexed while the cure was to become a vicarage pensionary.
Although possession was obtained by the dean and chapter, this was subsequently lost, and the church had to be re-annexed in 1437, the previous arrangement being adhered to, with both parsonage and vicarage remaining annexed.
St Andrew's Kirk, 1787. Undistinguished externally, porch 1891, inside original ceiling with Adam-like centrepiece and two-light Gothic windows, part of 1912 recasting, William Buxton. Pulpit was originally in the centre of the N wall with a horseshoe gallery bearing the Buchan coat of arms (George Reid, Peterhead, carver). Monuments to Thomas (d. 1819) and Robert (d. 1825) Buchan.
Bell, 1728, Robert Maxwell. Church bought by Captain David Buchan to ensure access and survival.
Kirkyard: plain ashlar gatepiers and rubble walls; some table tombs.
+++ DISCLAIMER +++
Nothing you see here is real, even though the conversion or the presented background story might be based on historical facts. BEWARE!
Some background:
During the interwar period, the U.S. Navy Command had placed considerable emphasis upon the role of armed aerial reconnaissance aircraft. To meet this interest, during 1931, the young Great Lakes Aircraft Company (founded in 1929 in Cleveland, Ohio) decided to embark on the development of a new naval combat aircraft to meet this role. The new aircraft, which was designated as the SBG, was a relatively modern all-metal design, even though some conservative traits like a fixed landing gear were kept.
The SBG was a low-wing cantilever monoplane, featuring all-metal, metal-covered construction. The crew of three consisted of a pilot, a bombardier and a rear gunner. The bombardier's combat station was situated in a gondola underneath the hull. The pilot was positioned well forward in the fuselage with an excellent field of view, within a fully enclosed, air-conditioned and heated cockpit, while the observer was seated directly behind him and could descend into the ventral gondola during applicable parts of a given mission, where he had an unobstructed field of view underneath the aircraft. A lookout station at the gondola’s front end could be outfitted with a bombsight.
The fixed undercarriage was covered with spats and comprised a pair of cantilever struts and single tail wheel, all of which were outfitted with pneumatic shock absorbers. One of the more unusual features of the SBG was the design of its three-piece low-mounted wing: In order to produce a wing that was both light and strong, the wing construction combined a revolutionary heavy-gauge corrugated duralumin center box and a multi-cellular trailing edge, along with a partially stressed exterior skin composed of duralumin. It was one of the earliest implementations of a metal sandwich structure in the field of aviation. Furthermore, the wings could, for storage on carriers, be manually folded back, just outside of the landing gear.
The fuselage of the SBG had an oval-section structure, composed of a mixture of duralumin frames and stringers, which were strengthened via several struts on the middle section. The fuselage exterior was covered with smooth duralumin sheet, which was internally reinforced in some areas by corrugated sheeting. The rear fuselage featured a semi-monocoque structure. A cantilever structure composed of ribs and spars was used for the tail unit; fin and tail plane were covered by duralumin sheeting, while the rudder and elevators had finely corrugated exterior surfaces.
The SBG’s original powerplant was a Pratt & Whitney R-1830-64 Twin Wasp radial engine of 850 hp (630 kW). The aircraft's offensive payload consisted of bombs. These were carried externally underneath the fuselage and the wings, using racks; the maximum load was a single 1,935 lb. (878 kg) Bliss-Leavitt Mark 13 aerial torpedo or 1,500 lb. (700 kg) of bombs, including a single 1,000 lb. (450 kg) bomb under the fuselage and up to 200 lb. under the outer wings.
The SBG was also armed with several machine guns, including rearward-facing defensive ventral and dorsal positions, each outfitted with a manual .30 in (7.62 mm) Browning machine gun. Another fixed machine gun fired, synchronized with the engine, forward through the propeller arc.
The first XSBG-1 prototype, which was christened “Prion” by Great Lakes, was ready in early 1934 and made its maiden flight on 2nd of April. While the aircraft handled well, esp. at low speed, thanks to generously dimensioned flaps, it soon became clear that it was seriously underpowered. Therefore, Great Lakes tried to incorporate a more powerful engine. The choice fell on the new Pratt & Whitney R-2180-A Twin Hornet. However, the bigger and heavier engine called for considerable changes to the engine mount and the cowling. The R-2180 also precluded the fixed machine gun, so it was, together with the synchronization gearbox, deleted. Instead, a pair of .30 in machine guns were added to the spats, which were deepened in order to take the weapons and the magazines.
Furthermore, the heavier engine shifted the aircraft’s center of gravity forward, so that the tail section had to be lengthened by roughly 1’ and the tail surfaces were enlarged, too. Various other alterations were made to the wings, including the adoption of more effective slotted ailerons, improved flaps and center-section slots. The latter feature served to smooth the airflow over the tail when flown at high angles of incidence. However, despite these changes, the SBG’s good handling did not suffer, and the modified XSBG-2 took to the air for the first time in late 1935, with a much better performance.
Satisfied with the changes, the US Navy's Bureau of Aeronautics (BuAer) placed an initial order for 54 SBG-2s in 1936 with the aircraft entering service during 1938, serving on USS Yorktown and Enterprise. However, faults were discovered with the Mark XIII torpedo at this point. Many were seen to hit the target yet failed to explode; there was also a tendency to run deeper than the set depth. It took over a year for the defects to be corrected. Another problem of the SBG when carrying the torpedo was the aimer’s position, which was located directly behind the weapon and obstructed the bomb aimer’s field of view forward. When deploying bombs from higher altitudes, this was not a problem at all, but as a consequence the SBG rarely carried torpedoes. Therefore, a second order of 48 aircraft (designated SBG-3) were pure bombers. These lacked any torpedo equipment, but they received a ventral displacement yoke that allowed to deploy bombs in a shallow dive and release them outside of the propeller arc. Furthermore, the bomb aimer/observer station received a more generous glazing, improving the field of view and offering the prone crewman in this position more space and comfort. Another modification was the reinforcement of the underwing hardpoints, so that these could now carry stores of up to 325 lb each or, alternatively, drop tanks. While the total payload was not changed, the SBG-3 could carry and deploy up to three depth charges against submarines, and the extended range was a welcome asset for reconnaissance missions.
In prewar use, SBG units were engaged in training and other operational activities and were gradually approaching the end of their useful service life with at least one aircraft being converted to target tug duty. By 1940, the US Navy was aware that the SBG had become outclassed by the fighters and bombers of other nations and a replacement was in the works, but it was not yet in service when the US entered World War II. By then, attrition had reduced their numbers to just over 60 aircraft, and with the arrival of the Curtiss SB2C “Helldiver” in December 1942, the obsolete SBGs were retired.
General characteristics:
Crew: 3
Length: 31 ft 9 in (9.682 m)
Wingspan: 45 ft 9 in (13.95 m)
Height: 10 ft 10 in (3.3 m)
Wing area: 288 sq ft (26.8 m²)
Empty weight: 4,251 lb. (1,928 kg)
Gross weight: 6,378 - 6,918 lb. (2,893 - 3,138 kg) for reconnaissance missions
7,705 - 7,773 lb (3,495 - 3,526 kg) for bombing missions
Fuel capacity: 200 US gal (740 l; 160 imp gal) in six wing tanks plus
7.9 US gal (30 l; 6.6 imp gal) in a gravity feed collector tank in the fuselage
18 US gal (70 l; 15 imp gal) of engine oil was also carried in a forward fuselage tank
Powerplant:
1 × Pratt & Whitney R-2180-A Twin Hornet 14 cylinder radial engine with 1,200 hp (865 kW),
driving a 3-bladed Hamilton-Standard Hydromatic, 11 ft 3 in (3.43 m) diameter constant-speed
fully-feathering propeller
Performance:
Maximum speed: 245 mph (395 km/h, 213 kn) at 3,650 m (11,980 ft)
210 mph (338 km/h, 183 kn) at sea level
Stall speed: 110 km/h (68 mph, 59 kn)
Range: 1,260 km (780 mi, 680 nmi)
Service ceiling: 7,300 m (24,000 ft)
Time to altitude: 2,000 m (6,600 ft) in 4 minutes
4,000 m (13,000 ft) in 11 minutes 10 seconds
Wing loading: 116 kg/m² (24 lb/sq ft) to 130 kg/m2 (27 lb/sq ft)
Power/mass: 6.3–6.8 kg/kW (10.4–11.2 lb/hp)
Armament:
2x fixed forward firing 0.30 “ (7.62 mm) Browning machine guns in the spats, firing forward,
plus 2x flexibly mounted 0.30 “ (7.62 mm) Browning machine guns in ventral and dorsal positions
A total of up to 1,500 lb (700 kg) of bombs on hardpoints under the fuselage (max. 1.000 lb; the SCG-2
could carry a single Mk. XIII torpedo) and under the wings (max. 325 lb per hardpoint, SCG-2 only 200 lb)
The kit and its assembly:
I had the idea to convert a PZL.23 into a carrier-borne light bomber on the agenda for a long time and also already a Heller kit stashed away – but it took the “In the Navy” group build at whatifmodelers.com in early 2020 to dig everything out from the stash and start the hardware phase.
Originally, this was inspired by a picture of a Ju 87D with USN “Yellow wings” markings which I came across while doing online research. This looked really good, but since the USN would never have accepted a liquid-cooled engine on one of its pre-WWII aircraft, the concept had IMHO some flaws. When I came across the PZL.23 in another context, I found that the aircraft, with its cockpit placed well forward and the generous window area, could also be a good carrier-based recce/light bomber/torpedo aircraft? This was the conceptual birth of the SBG.
The basis is the vintage, original Heller kit of the PZL.23: a VERY nice kit. It has been crisply molded, fit is very good, and even the interior detail is decent, e.g. with a nice fuselage structure and dashboard. Surface details are raised but very fine, and the styrene is also easy to handle.
Basically the PZL.23 was built OOB. The only changes I made are a crew of three figures (all Matchbox WWII pilots, two of them with their heads in different directions), a tail wheel instead of the original skid, an opening for an arrester hook under the fin (there’s even plausible space available!) and a new engine: the PZL.23’s bulky 9 cylinder Jupiter radial engine with its generous cowling and the two-blade propeller was completely replaced. The engine dummy is actually a matching R-2600 and comes from a Matchbox SB2C, even though its rear bulkhead was trimmed away so that it would fit into the new cowling. The latter came from an Italeri La-5FN, cut off long time ago from another conversion project, and I added a carburetor/oil cooler fairing underneath. Inside of the new engine I implanted a styrene tube which attaches the engine to the fuselage and also takes the metal axis of the new propeller, a (rather clumsy) donor from a Matchbox Douglas A-20G. The whole package works well, though, and gives the PZL.23 a more modern and different look.
A late modification is the glasshouse for the rear gunner. Since the PZL.23 offered considerable comfort for its crew, at least for pilot and observer, I thought that a closed rear position would make sense. I found an old rear gunner station glaizing from a vintage Airfix B-17G in the stash, and with some tailoring (including an opening for the OOB manual machine gun) the piece could be inserted into the fuselage opening. Small gaps were left, but these were simply filled with white glue. I think this was a good move, since it changes the PZL.23’s profile a little.
Other small cosmetic changes include the machine guns instead of the original large landing lights on the spats, an additional antenna mast and a cranked pitot, made from brass wire. Furthermore, I added small underwing bomb pylons and a ventral hardpoint with a scratched swing arm and a 500 lb iron bomb from an Academy kit.
Painting and markings:
For proper anachronism and some color in the shelf, I wanted the SBG to be a pre-WWII aircraft in the USN’s bright “Yellow Wings” markings, just like the Ju 87 mentioned above. As a slight twist, the fuselage was finished in all-over Light Gull Grey (FS 36440, Humbrol 40) instead of a NMF – some aircraft like F4Bs were finished this way, even though some fabric-covered parts were still painted with alu dope. In 1940, however, the bright colors would be replaced by a uniform light grey livery with subdued markings, anyway.
The aircraft’s individual markings were a bit tricky, because the USN has a very complicated color code system to identify not only the carrier to which an aircraft would belong, color markings would also identify the individual aircraft within a full squadron of 18 aircraft and its six sections. I won’t go into details, but I chose to depict the lead aircraft of section two of the scout bomber squadron on board of USS Enterprise.
For this carrier, the tail surfaces became blue (I used Modelmaster French Blue for the authentic “True Blue”), while the 2nd section had white aircraft markings on fuselage and wings. The lead aircraft (connected with the individual aircraft code “4”) had a full ring marking around the cowling. The fuselage band seems to be rather optional on bomber aircraft (more frequent on fighters?), but I eventually decided to add it - pictures suggest that probably only lead aircraft of a Section in the scout or torpedo squadrons carried this marking?
Like the cowling ring, it was painted with white and then black borders were added with decal strips. The wings were painted with Revell 310 (Lufthansa Yellow, RAL 1028), which is a pretty rich tone, and the section markings on top of them were fully created with decal material, a white 5mm stripe over a black 6mm stripe on each wing.
The aircraft’s tactical code was created from single US 45° numbers; the “S” had to be scratched from an “8”, since the decal sheet did not contain letters… Other decals were gathered from the scrap box and improvised.
After the free-standing exhaust pipes had been fixed, the kit received a light weathering treatment and was finally sealed with a coat of semi-matt acrylic varnish (Italeri semi-gloss with some matt varnish added).
A colorful aircraft model, and the transformation from a Polish light bomber into an American armed scout aircraft worked well – for an interesting result with that anachronistic touch that many interwar designs carried. However, even though the conversion has been conceptually successful, I am not happy with the finish. The glossy Humbrol paints I used refused to cure properly, and the decals were also not without problems (e.g. when you realize that the roundels you wanted to use had a poor opacity, so that the yellow underneath shines blatantly through). But despite a lot of improvisation, the outcome is quite O.K.
Mars landing sophisticated core technology 1. New high-speed heavy rocket technology $ 12.7 billion
2. The special material of aerospace technology special radiation $ 2.5 billion
3. Microgravity confrontation - technology, pharmaceutical space syndrome, Mars emergency medical system $ 1.5 billion, $ 4.5 billion
4. Special radiation multifunction smart Mars spacesuit medical warehouse $ 2.4 billion
5. The aeronautical emergency treatment technology life once, twice maintain security, rescue system $ 1.3 billion
6. rovers, Mars spacecraft, the Mars telescope, giant cell, Rover $ 3.8 billion
7. Life on Mars warehouse / micro base station on Mars, Martian soil nutrients $ 3.9 billion
8. Water - synthetic oxygen conversion technology for producing $ 1.2 billion
9. Mars LASH barge technology, semi-automatic / manual return flight back to Mars Technology $ 7.2 billion
10. Remote telemetry, communications technology
$ 1.5 billion
11. The other $ 5.7 billion
************************************************** *********** / special multi-purpose multi-purpose anti-radiation cosmic universe Wear - $ 1.5 billion
Aeromedical emergency cabin $ 7.5 billion
Multifunctional intelligent life support system $ 3 billion
Mars Rover $ 300 million
Aerospace / water planet Synthesis 1.2 one billion US dollars
Cutting-edge aerospace technology transfer core, a high precision and advanced technology, confidential technology, in order to avoid technical and commercial secrets leak, causing leaks and developers in major economic loss. Therefore, according to international practice, advanced security technology temporarily apply for international patents. You can later apply for an application in the relevant art decryption. It is noted. Technology transfer projects listed prices are reference price, the offer price, the specific projects where appropriate discount 15% -38%, will be agreed upon. International transfers in US dollars or other common international currency. Transfer technology transfer related technology required to sign trade agreement or contract, can be formal or electronic versions.
Contact, e-mail
banxin123 @ gmail.com, fangda337svb125 @ gmail.com, mdin.jshmith @ gmail.com,fangruid44o7@gmail.com, technology entry fee / $ 2,550,000, signed in accordance with international practice, after signing the contract, namely the delivery of technical entry fee of $ 2.55 million or international currency of payment, technology margin of 25%, after the delivery of technical drawings, the balance lump sum. Agreement or contract signed by both parties, the English, the French text, parts one and two, to take effect upon signature. Any breach will compensate the other party losses, liquidated damages of $ 1.25 million. But unforeseen exceptional circumstances In addition, the parties may agree to terminate the agreement and contract, no compensation. Peaceful Uses of Outer project uses technology, global commercial enterprises related establishments company may transferee. The transferee company Organziation enterprises according to related contracts and agreements, international patent applications, patent rights attributed to its purchase technical side, the licensor party no longer enjoys its technical invention patents. Transfer of technology patent formula category in the form of technology, drawings, text and other technical documents, assignment of patent drawings in accordance with the prevailing universal national patent drawings, English, French or other common international language. For detailed technical design diagrams, schematics, block diagrams, installation drawings transferor to the transferee not provided, only patented formula class technical drawings. Seller can provide technical advice or technical support, the transferee must be paid 3% to 15% of the technology consultancy. Transfer of technical drawings and technical drawings electronic version of a file each, contact e-mail encryption. Specific bank or bank transfer or electronic bank account and the other notified.
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Fangruida: human landing on Mars 10 cutting-edge technology
[Fangruida- human landing on Mars 10 innovative and sophisticated technologies]
Aerospace Science and space science and technology major innovation of the most critical of sophisticated technology R & D project
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Aerospace Science Space Science and Technology on behalf of the world's most cutting-edge leader in high technology, materials, mechatronics, information and communication, energy, biomedical, marine, aviation aerospace, microelectronics, computer, automation, intelligent biochips, use of nuclear energy, light mechanical and electrical integration, astrophysics, celestial chemistry, astrophysics and so a series of geological science and technology. Especially after the moon landing, the further development of mankind to Mars and other planets into the powerful offensive, the world's major powers eager to Daxian hand of God, increase investment, vigorously develop new sophisticated technology projects for space to space. Satellite, space station, the new spacecraft, the new space suits, the new radiation protection materials, intelligent materials, new manufacturing technology, communications technology, computer technology, detector technology, rover, rover technology, biomedical technology, and so one after another, is expected to greater breakthroughs and leaps. For example, rocket technology, spacecraft design, large power spacecraft, spacesuits design improvements, radiation multifunctional composite materials, life health care technology and space medicine, prevention against microgravity microgravity applicable drugs, tracking control technology, landing and return technology. Mars lander and returned safely to Earth as a top priority. Secondly, Mars, the Moon base and the use of transforming Mars, the Moon and other development will follow. Whether the former or the latter, are the modern aerospace science, space science basic research, applied basic research and applied research in the major cutting-edge technology. These major cutting-edge technology research and innovation, not only for human landing on Mars and the safe return of great significance, but for the entire space science, impact immeasurable universe sciences, earth sciences and human life. Here the most critical of the most important research projects of several sophisticated technology research and development as well as its core technology brief. Limit non-scientific techniques include non-technical limits of technology, the key lies in technology research and development of technology maturity, advanced technology, innovative, practical, reliable, practical application, business value and investment costs, and not simply like the idea mature technology achievements, difficult to put into things. This is the high-tech research and development, testing, prototype, test application testing, until the outcome of industrialization. Especially in aerospace technology, advanced, novelty, practicality, reliability, economy, maturity, commercial value and so on. For technical and research purely science fiction and the like may be irrelevant depth, but not as aerospace engineering and technology practice. Otherwise, Mars will become a dream fantasy, and even into settling crashed out of danger.
Regardless of the moon or Mars, many technical difficulties, especially a human landing on Mars and return safely to Earth, technical difficulties mainly in the following aspects. (Transformation of Mars and the Moon and other planets and detect other livable technology more complex and difficult, at this stage it is difficult to achieve and therefore not discussed in detail in this study). In fact, Mars will be the safe return of a full set of technology, space science, aerospace crucial scientific research development, its significance is not confined to Mars simply a return to scientific value, great commercial value, can not be measure.
1. Powered rocket, the spacecraft overall structural design not be too complex large, otherwise, the safety factor to reduce the risk of failure accidents. Fusion rocket engine main problem to be solved is the high-temperature materials and fuel ignition chamber (reaction chamber temperatures of up to tens of millions of supreme billion degrees), fissile class rocket engine whose essence is the miniaturization of nuclear reactors, and placed on the rocket. Nuclear rocket engine fuel as an energy source, with liquid hydrogen, liquid helium, liquid ammonia working fluid. Nuclear rocket engine mounted in the thrust chamber of the reactor, cooling nozzle, the working fluid delivery and control systems and other components. This engine due to nuclear radiation protection, exhaust pollution, reactor control and efficient heat exchanger design and other issues unresolved. Electrothermal rocket engine utilizing heat energy (resistance heating or electric arc heating) working medium (hydrogen, amines, hydrazine ), vaporized; nozzle expansion accelerated after discharged from the spout to generate thrust. Static rocket engine working fluid (mercury, cesium, hydrogen, etc.) from the tank enter the ionization chamber is formed thrust ionized into a plasma jet. Electric rocket engines with a high specific impulse (700-2500 sec), extremely long life (can be repeated thousands of times a starter, a total of up to thousands of hours of work). But the thrust of less than 100N. This engine is only available for spacecraft attitude control, station-keeping and the like. One nuclear - power rocket design is as follows: Firstly, the reactor heats water to make it into steam, and then the high-speed steam ejected, push the rocket. Nuclear rocket using hydrogen as working substance may be a better solution, it is one of the most commonly used liquid hydrogen rocket fuel rocket carrying liquid hydrogen virtually no technical difficulties. Heating hydrogen nuclear reactor, as long as it eventually reaches or exceeds current jet velocity hydrogen rocket engine jet speed, the same weight of the rocket will be able to work longer, it can accelerate the Rockets faster. Here there are only two problems: First, the final weight includes the weight of the rocket in nuclear reactors, so it must be as light as possible. Ultra-small nuclear reactor has been able to achieve. Furthermore, if used in outer space, we can not consider the problem of radioactive residues, simply to just one proton hydrogen nuclei are less likely to produce induced radioactivity, thus shielding layer can be made thinner, injected hydrogen gas can flow directly through the reactor core, it is not easy to solve, and that is how to get back at high speed heated gas is ejected.
Rocket engine with a nuclear fission reactor, based on the heating liquid hydrogen propellant, rather than igniting flammable propellant
High-speed heavy rocket is a major cutting-edge technology. After all, space flight and aircraft carriers, submarines, nuclear reactors differ greatly from the one hand, the use of traditional fuels, on the one hand can be nuclear reactor technology. From the control, for security reasons, the use of nuclear power rocket technology, safe and reliable overriding indicators. Nuclear atomic energy in line with the norms and rules of outer space. For the immature fetal abdominal hatchery technology, and resolutely reject use. This is the most significant development of nuclear-powered rocket principle.
Nuclear-powered spaceship for Use of nuclear power are three kinds:
The first method: no water or air space such media can not be used propeller must use jet approach. Reactor nuclear fission or fusion to produce a lot of heat, we will propellant (such as liquid hydrogen) injection, the rapid expansion of the propellant will be heated and then discharged from the engine speed tail thrust. This method is most readily available.
The second method: nuclear reactor will have a lot of fast-moving ions, these energetic particles moving very fast, so you can use a magnetic field to control their ejection direction. This principle ion rocket similar to the tail of the rocket ejected from the high-speed mobile ions, so that the recoil movement of a rocket. The advantage of this approach is to promote the unusually large ratio, without carrying any medium, continued strong. Ion engine, which is commonly referred to as "electric rocket", the principle is not complicated, the propellant is ionized particles,
Plasma Engine
Electromagnetic acceleration, high-speed spray. From the development trend, the US research scope covers almost all types of electric thrusters, but mainly to the development of ion engines, NASA in which to play the most active intake technology and preparedness plans. "
The third method: the use of nuclear explosions. It is a bold and crazy way, no longer is the use of a controlled nuclear reaction, but to use nuclear explosions to drive the ship, this is not an engine, and it is called a nuclear pulse rocket. This spacecraft will carry a lot of low-yield atomic bombs out one behind, and then detonated, followed by a spacecraft propulsion installation disk, absorbing the blast pushing the spacecraft forward. This was in 1955 to Orion (Project Orion) name of the project, originally planned to bring two thousand atomic bombs, Orion later fetal nuclear thermal rocket. Its principle is mounted on a small rocket reactor, the reactor utilizing thermal energy generated by the propellant is heated to a high temperature, high pressure and high temperature of the propellant from the high-speed spray nozzle, a tremendous impetus.
Common nuclear fission technologies, including nuclear pulse rocket engines, nuclear rockets, nuclear thermal rocket and nuclear stamping rockets to nuclear thermal rocket, for example, the size of its land-based nuclear power plant reactor structure than the much smaller, more uranium-235 purity requirements high, reaching more than 90%, at the request of the high specific impulse engine core temperature will reach about 3000K, require excellent high temperature properties of materials.
Research and test new IT technologies and new products and new technology and new materials, new equipment, things are difficult, design is the most important part, especially in the overall design, technical solutions, technical route, technical process, technical and economic particularly significant. The overall design is defective, technology there are loopholes in the program, will be a major technical route deviation, but also directly related to the success of research trials. so, any time, under any circumstances, a good grasp of the overall control of design, technical design, is essential. otherwise, a done deal, it is difficult save. aerospace technology research and product development is true.
3, high-performance nuclear rocket
Nuclear rocket nuclear fission and fusion energy can rocket rocket two categories. Nuclear fission and fusion produce heat, radiation and shock waves and other large amounts of energy, but here they are contemplated for use as a thermal energy rocket.
Uranium and other heavy elements, under certain conditions, will split their nuclei, called nuclear fission reaction. The atomic bomb is the result of nuclear fission reactions. Nuclear fission reaction to release energy, is a million times more chemical rocket propellant combustion energy. Therefore, nuclear fission energy is a high-performance rocket rockets. Since it requires much less propellant than chemical rockets can, so to its own weight is much lighter than chemical rockets energy. For the same quality of the rocket, the rocket payload of nuclear fission energy is much greater than the chemical energy of the rocket. Just nuclear fission energy rocket is still in the works.
Use of nuclear fission energy as the energy of the rocket, called the atomic rockets. It is to make hydrogen or other inert gas working fluid through the reactor, the hydrogen after the heating temperature quickly rose to 2000 ℃, and then into the nozzle, high-speed spray to produce thrust.
A vision plan is to use liquid hydrogen working fluid, in operation, the liquid hydrogen tank in the liquid hydrogen pump is withdrawn through the catheter and the engine cooling jacket and liquid hydrogen into hydrogen gas, hydrogen gas turbine-driven, locally expansion. Then by nuclear fission reactors, nuclear fission reactions absorb heat released, a sharp rise in temperature, and finally into the nozzle, the rapid expansion of high-speed spray. Calculations show that the amount of atomic payload rockets, rocket high chemical energy than 5-8 times.
Hydrogen and other light elements, under certain conditions, their nuclei convergent synthesis of new heavy nuclei, and release a lot of energy, called nuclear fusion reaction, also called thermonuclear reaction.
Using energy generated by the fusion reaction for energy rocket, called fusion energy rocket or nuclear thermal rockets. But it is also not only take advantage of controlled nuclear fusion reaction to manufacture hydrogen bombs, rockets and controlled nuclear fusion reaction needs still studying it.
Of course there are various research and development of rocket technology and technical solutions to try.
It is envisaged that the rocket deuterium, an isotope of hydrogen with deuterium nuclear fusion reaction of helium nuclei, protons and neutrons, and release huge amounts of energy, just polymerized ionized helium to temperatures up to 100 million degrees the plasma, and then nozzle expansion, high-speed ejection, the exhaust speed of up to 15,000 km / sec, atomic energy is 1800 times the rocket, the rocket is the chemical energy of 3700 times.
Nuclear rocket engine fuel as an energy source, with liquid hydrogen, liquid helium, liquid ammonia working fluid. Nuclear rocket engine mounted in the thrust chamber of the reactor, cooling nozzle, the working fluid delivery and control systems and other components. In a nuclear reactor, nuclear energy into heat to heat the working fluid, the working fluid is heated after expansion nozzle to accelerate to the speed of 6500 ~ 11,000 m / sec from the discharge orifice to produce thrust. Nuclear rocket engine specific impulse (250 to 1000 seconds) long life, but the technology is complex, apply only to long-term spacecraft. This engine due to nuclear radiation protection, exhaust pollution, reactor control and efficient heat exchanger design and other issues not resolved, is still in the midst of trials. Nuclear rocket technology is cutting-edge aerospace science technology, centralized many professional and technical sciences and aerospace, nuclear physics, nuclear chemistry, materials science, the long term future ___-- wide width. The United States, Russia and Europe, China, India, Japan, Britain, Brazil and other countries in this regard have studies, in particular the United States and Russia led the way, impressive. Of course, at this stage of nuclear rocket technology, technology development there are still many difficulties. Fully formed, still to be. But humanity marching to the universe, nuclear reactor applications is essential.
Outer Space Treaty (International Convention on the Peaceful Uses of Outer Space) ****
Use of Nuclear Power Sources in Outer Space Principle 15
General Assembly,
Having considered the report of its thirty-fifth session of the Committee on the Peaceful Uses of Outer Space and the Commission of 16 nuclear
It can be attached in principle on the use of nuclear power sources in outer space of the text of its report, 17
Recognize that nuclear power sources due to small size, long life and other characteristics, especially suitable for use even necessary
For some missions in outer space,
Recognizing also that the use of nuclear power sources in outer space should focus on the possible use of nuclear power sources
Those uses,
Recognizing also that the use of nuclear power sources should include or probabilistic risk analysis is complete security in outer space
Full evaluation is based, in particular, the public should focus on reducing accidental exposure to harmful radiation or radioactive material risk
risk,
Recognizing the need to a set of principles containing goals and guidelines in this regard to ensure the safety of outer space makes
With nuclear power sources,
Affirming that this set principles apply exclusively on space objects for non-power generation, which is generally characteristic
Mission systems and implementation of nuclear power sources in outer space on similar principles and used by,
Recognizing this need to refer to a new set of principles for future nuclear power applications and internationally for radiological protection
The new proposal will be revised
By the following principles on the use of nuclear power sources in outer space.
Principle 1. Applicability of international law
Involving the use of nuclear power sources in outer space activities should be carried out in accordance with international law, especially the "UN
Principles of the Charter "and" States in the Exploration and Use of Outer Space, including the Moon and Other Celestial Bodies Activities
Treaty "3
.
2. The principle terms
1. For the purpose of these principles, "launching State" and "launching State ......" two words mean, in related
Principles related to a time of nuclear power sources in space objects exercises jurisdiction and control of the country.
2. For the purpose of principle 9, wherein the definition of the term "launching State" as contained in that principle.
3. For the purposes of principle 3, the terms "foreseeable" and "all possible" two words are used to describe the actual hair
The overall likelihood of students that it is considered for safety analysis is credible possibilities for a class of things
Member or circumstances. "General concept of defense in depth" when the term applies to nuclear power sources in outer space refers to various settings
Count form and space operations replace or supplement the operation of the system in order to prevent system failures or mitigate thereafter
"Official Records of the General Assembly, Forty-seventh Session, Supplement No. 20" 16 (A / 47/20).
17 Ibid., Annex.
38
fruit. To achieve this purpose is not necessarily required for each individual member has redundant safety systems. Given space
Use and special requirements of various space missions, impossible to any particular set of systems or features can be specified as
Necessary to achieve this purpose. For the purpose of Principle 3 (d) of paragraph 2, "made critical" does not include
Including such as zero-power testing which are fundamental to ensuring system safety required.
Principle 3. Guidelines and criteria for safe use
To minimize the risk of radioactive material in space and the number involved, nuclear power sources in outer space
Use should be limited to non-nuclear power sources in space missions can not reasonably be performed
1. General goals for radiation protection and nuclear safety
(A) States launching space objects with nuclear power sources on board shall endeavor to protect individuals, populations and the biosphere
From radiation hazards. The design and use of space objects with nuclear power sources on board shall ensure that risk with confidence
Harm in the foreseeable operational or accidental circumstances, paragraph 1 (b) and (c) to define acceptable water
level.
Such design and use shall also ensure that radioactive material does not reliably significant contamination of outer space.
(B) the normal operation of nuclear power sources in space objects, including from paragraph 2 (b) as defined in foot
High enough to return to the track, shall be subject to appropriate anti-radiation recommended by the International Commission on Radiological Protection of the public
Protection goals. During such normal operation there shall be no significant radiation exposure;
(C) To limit exposure in accidents, the design and construction of nuclear power source systems shall take into account the international
Relevant and generally accepted radiological protection guidelines.
In addition to the probability of accidents with potentially serious radiological consequences is extremely low, the nuclear power source
Design systems shall be safely irradiated limited limited geographical area, for the individual radiation dose should be
Limited to no more than a year 1mSv primary dose limits. Allows the use of irradiation year for some years 5mSv deputy agent
Quantity limit, but the average over a lifetime effective dose equivalent annual dose not exceed the principal limit 1mSv
degree.
Should make these conditions occur with potentially serious radiological consequences of the probability of the system design is very
small.
Criteria mentioned in this paragraph Future modifications should be applied as soon as possible;
(D) general concept of defense in depth should be based on the design, construction and operation of systems important for safety. root
According to this concept, foreseeable safety-related failures or malfunctions must be capable of automatic action may be
Or procedures to correct or offset.
It should ensure that essential safety system reliability, inter alia, to make way for these systems
Component redundancy, physical separation, functional isolation and adequate independence.
It should also take other measures to increase the level of safety.
2. The nuclear reactor
(A) nuclear reactor can be used to:
39
(I) On interplanetary missions;
(Ii) the second high enough orbit paragraph (b) as defined;
(Iii) low-Earth orbit, with the proviso that after their mission is complete enough to be kept in a nuclear reactor
High on the track;
(B) sufficiently high orbit the orbital lifetime is long enough to make the decay of fission products to approximately actinides
Element active track. The sufficiently high orbit must be such that existing and future outer space missions of crisis
Risk and danger of collision with other space objects to a minimum. In determining the height of the sufficiently high orbit when
It should also take into account the destroyed reactor components before re-entering the Earth's atmosphere have to go through the required decay time
between.
(C) only 235 nuclear reactors with highly enriched uranium fuel. The design shall take into account the fission and
Activation of radioactive decay products.
(D) nuclear reactors have reached their operating orbit or interplanetary trajectory can not be made critical state
state.
(E) nuclear reactor design and construction shall ensure that, before reaching the operating orbit during all possible events
Can not become critical state, including rocket explosion, re-entry, impact on ground or water, submersion
In water or water intruding into the core.
(F) a significant reduction in satellites with nuclear reactors to operate on a lifetime less than in the sufficiently high orbit orbit
For the period (including during operation into the sufficiently high orbit) the possibility of failure, there should be a very
Reliable operating system, in order to ensure an effective and controlled disposal of the reactor.
3. Radioisotope generators
(A) interplanetary missions and other spacecraft out of Earth's gravitational field tasks using radioactive isotopes
Su generator. As they are stored after completion of their mission in high orbit, the Earth can also be used
track. We are required to make the final treatment under any circumstances.
(B) Radioisotope generators shall be protected closed systems, design and construction of the system should
Ensure that in the foreseeable conditions of the track to withstand the heat and aerodynamic forces of re-entry in the upper atmosphere, orbit
Conditions including highly elliptical or hyperbolic orbits when relevant. Upon impact, the containment system and the occurrence of parity
Physical morpheme shall ensure that no radioactive material is scattered into the environment so you can complete a recovery operation
Clear all radioactive impact area.
Principle 4. Safety Assessment
1. When launching State emission consistent with the principles defined in paragraphs 1, prior to the launch in applicable under the
Designed, constructed or manufactured the nuclear power sources, or will operate the space object person, or from whose territory or facility
Transmits the object will be to ensure a thorough and comprehensive safety assessment. This assessment shall cover
All relevant stages of space mission and shall deal with all systems involved, including the means of launching, the space level
Taiwan, nuclear power source and its equipment and the means of control and communication between ground and space.
2. This assessment shall respect the principle of 3 contained in the guidelines and criteria for safe use.
40
3. The principle of States in the Exploration and Use, including the Moon and Other Celestial Bodies Outer Space Activities Article
Results of about 11, this safety assessment should be published prior to each transmit simultaneously to the extent feasible
Note by the approximate intended time of launch, and shall notify the Secretary-General of the United Nations, how to be issued
This safety assessment before the shot to get the results as soon as possible.
Principle 5. Notification of re-entry
1. Any State launching a space object with nuclear power sources in space objects that failed to produce discharge
When radioactive substances dangerous to return to the earth, it shall promptly notify the country concerned. Notice shall be in the following format:
(A) System parameters:
(I) Name of launching State, including which may be contacted in the event of an accident to Request
Information or assistance to obtain the relevant authorities address;
(Ii) International title;
(Iii) Date and territory or location of launch;
(Iv) the information needed to make the best prediction of orbit lifetime, trajectory and impact region;
(V) General function of spacecraft;
(B) information on the radiological risk of nuclear power source:
(I) the type of power source: radioisotopes / reactor;
(Ii) the fuel could fall into the ground and may be affected by the physical state of contaminated and / or activated components, the number of
The amount and general radiological characteristics. The term "fuel" refers to as a source of heat or power of nuclear material.
This information shall also be sent to the Secretary-General of the United Nations.
2. Once you know the failure, the launching State shall provide information on the compliance with the above format. Information should as far as possible
To be updated frequently, and in the dense layers of the Earth's atmosphere is expected to return to a time when close to the best increase
Frequency of new data, so that the international community understand the situation and will have sufficient time to plan for any deemed necessary
National contingency measures.
3. It should also be at the same frequency of the latest information available to the Secretary-General of the United Nations.
Principle 6. consultation
5 According to the national principles provide information shall, as far as reasonably practicable, other countries
Requirements to obtain further information or consultations promptly reply.
Principle 7. Assistance to States
1. Upon receipt of expected with nuclear power sources on space objects and their components will return through the Earth's atmosphere
After know that all countries possessing space monitoring and tracking facilities, in the spirit of international cooperation, as soon as possible to
The Secretary-General of the United Nations and the countries they may have made space objects carrying nuclear power sources
A fault related information, so that the States may be affected to assess the situation and take any
It is considered to be the necessary precautions.
41
2. In carrying space objects with nuclear power sources back to the Earth's atmosphere after its components:
(A) launching State shall be requested by the affected countries to quickly provide the necessary assistance to eliminate actual
And possible effects, including nuclear power sources to assist in identifying locations hit the Earth's surface, to detect the re substance
Quality and recovery or cleanup activities.
(B) All countries with relevant technical capabilities other than the launching State, and with such technical capabilities
International organizations shall, where possible, in accordance with the requirements of the affected countries to provide the necessary co
help.
When according to the above (a) and subparagraph (b) to provide assistance, should take into account the special needs of developing countries.
Principle 8. Responsibility
In accordance with the States in the Exploration and Use of Outer Space, including the Moon and Other Celestial Bodies activities, including the principles of Article
About Article, States shall bear international responsibility for their use of nuclear power sources in outer space relates to the activities
Whether such activities are carried on by governmental agencies or non-governmental entities, and shall bear international responsibility to ensure that this
Such activities undertaken by the country in line with the principles of the Treaty and the recommendations contained therein. If it involves the use of nuclear power sources
Activities in outer space by an international organization, should be done by the international organizations and States to participate in the organization
Undertakes to comply with the principles of the Treaty and the recommendations contained in these responsibilities.
Principle 9. Liability and Compensation
1. In accordance with the principle of States in the Exploration and Use, including the Moon and Other Celestial Bodies Outer Space Activities Article
And the Convention on International Liability for Damage Caused by Space Objects covenant of Article 7
Provisions, which launches or on behalf of the State
Each State launching a space object and each State from which territory or facility a space object is launched
Kinds of space object or damage caused by components shall bear international liability. This fully applies to this
Kind of space object carrying a nuclear power source case. Two or more States jointly launch a space object,
Each launching State shall in accordance with the above Article of the Convention for any damages jointly and severally liable.
2. Such countries under the aforesaid Convention shall bear the damages shall be in accordance with international law and fair and reasonable
The principles set out in order to provide for damages to make a claim on behalf of its natural or juridical persons, national or
International organizations to restore to the state before the occurrence of the damage.
3. For the purposes of this principle, compensation should be made to include reimbursement of the duly substantiated expenses for search, recovery and clean
Cost management work, including the cost of providing assistance to third parties.
10. The principle of dispute settlement
Since the implementation of these principles will lead to any dispute in accordance with the provisions of the UN Charter, by negotiation or
Other established procedures to resolve the peaceful settlement of disputes.
Here quoted the important provisions of the United Nations concerning the use of outer space for peaceful nuclear research and international conventions, the main emphasis on the Peaceful Uses of provisions related constraints .2 the use of nuclear rockets in outer space nuclear studies, etc., can cause greater attention in nuclear power nuclear rocket ship nuclear research, manufacture, use and other aspects of the mandatory hard indicators. this scientists, engineering and technical experts are also important constraints and requirements. as IAEA supervision and management as very important.
2. radiation. Space radiation is one of the greatest threats to the safety of the astronauts, including X-rays, γ-rays, cosmic rays and high-speed solar particles. Better than aluminum protective effect of high polymer composite materials.
3. Air. Perhaps the oxygen needed to rely on oxidation-reduction reaction of hydrogen and ilmenite production of water, followed by water electrolysis to generate oxygen. Mars oxygen necessary for survival but also from the decomposition of water, electrolytically separating water molecules of oxygen and hydrogen, this oxygen equipment has been successfully used in the International Space Station. Oxygen is released into the air to sustain life, the hydrogen system into the water system.
4. The issue of food waste recycling. At present, the International Space Station on the use of dehumidifiers, sucked moisture in the air to be purified, and then changed back to drinkable water. The astronauts' urine and sweat recycling. 5. water. The spacecraft and the space station on purification system also makes urine and other liquids can be purified utilization. 6. microgravity. In microgravity or weightlessness long-term space travel, if protective measures shall not be treated, the astronauts will be muscle atrophy, bone softening health. 7. contact. 8. Insulation, 9 energy. Any space exploration are inseparable from the energy battery is a new super hybrid energy storage device, the asymmetric lead-acid batteries and supercapacitors in the same compound within the system - and the so-called inside, no additional separate electronic control unit, this is an optimal combination. The traditional lead-acid battery PbO2 monomer is a positive electrode plate and a negative electrode plate spongy Pb composition, not a super cell. : Silicon solar cells, multi-compound thin film solar cells, multi-layer polymer-modified electrode solar cells, nano-crystalline solar cells, batteries and super class. For example, the solar aircraft .10. To protect the health and life safety and security systems. Lysophosphatidic acid LPA is a growth factor-like lipid mediators, the researchers found that this substance can on apoptosis after radiation injury and animal cells was inhibited. Stable lysophosphatidic acid analogs having the hematopoietic system and gastrointestinal tract caused by acute radiation sickness protection, knockout experiments show that lysophosphatidic acid receptors is an important foundation for the protection of radiation injury. In addition to work under high pressure, the astronauts face a number of health threats, including motion sickness, bacterial infections, blindness space, as well as psychological problems, including toxic dust. In the weightless environment of space, the astronaut's body will be like in preadolescents, as the emergence of various changes.
Plantar molt
After the environment to adapt to zero gravity, the astronaut's body will be some strange changes. Weightlessness cause fluid flow around the main flow torso and head, causing the astronauts facial swelling and inflammation, such as nasal congestion. During long-term stay in space
Bone and muscle loss
Most people weightlessness caused by the impact may be known bone and muscle degeneration. In addition, the calcium bones become very fragile and prone to fracture, which is why some of the astronauts after landing need on a stretcher.
Space Blindness
Space Blindness refers astronaut decreased vision.
Solar storms and radiation is one of the biggest challenges facing the long-term space flight. Since losing the protection of Earth's magnetic field, astronauts suffer far more than normal levels of radiation. The cumulative amount of radiation exposure in low earth orbit them exceeded by workers close to nuclear reactors, thereby increasing the risk of cancer.
Prolonged space flight can cause a series of psychological problems, including depression or mood swings, vulnerability, anxiety and fear, as well as other sequelae. We are familiar with the biology of the Earth, the Earth biochemistry, biophysics, after all, the Earth is very different astrophysics, celestial chemistry, biophysics and astrophysics, biochemistry and other celestial bodies. Therefore, you must be familiar with and adapt to these differences and changes.
Osteoporosis and its complications ranked first in the space of disease risk.
Long-term health risks associated with flying Topics
The degree of influence long-term biological effects of radiation in human flight can withstand the radiation and the maximum limit of accumulated radiation on physiology, pathology and genetics.
Physiological effects of weightlessness including: long-term bone loss and a return flight after the maximum extent and severity of the continued deterioration of other pathological problems induced by the; maximum flexibility and severity of possible long-term Flight Center in vascular function.
Long-term risk of disease due to the high risk of flight stress, microbial variation, decreased immune function, leading to infections
Radiation hazards and protection
1) radiation medicine, biology and pathway effects Features
Radiation protection for interplanetary flight, since the lack of protective effect of Earth's magnetic field, and by the irradiation time is longer, the possibility of increased radiation hazard.
Analysis of space flight medical problems that may occur, loss of appetite topped the list, sleep disorders, fatigue and insomnia, in addition, space sickness, musculoskeletal system problems, eye problems, infections problems, skin problems and cardiovascular problems
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Development of diagnostic techniques in orbit, the development of the volume of power consumption, features a wide range of diagnostic techniques, such as applied research of ultrasound diagnostic techniques in the abdominal thoracic trauma, bone, ligament damage, dental / sinus infections and other complications and integrated;
Actively explore in orbit disposal of medical technology, weightlessness surgical methods, development of special surgical instruments, the role of narcotic drugs and the like.
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However, space technology itself is integrated with the use of the most advanced technology, its challenging technical reserves and periodic demanding
With the continuous development of science and technology, space agencies plan a manned landing on the moon and Mars, space exploration emergency medicine current concern.
Space sickness
In the weightless environment of space, in the weightless environment of space, surgery may be extremely difficult and risky.
Robot surgeons
Space disease in three days after entering the space started to ease, although individual astronauts might subsequently relapse. January 2015 NASA declared working on a fast, anti-nausea and nasal sprays. In addition, due to the zero-gravity environment, and anti-nausea drugs can only be administered by injection or transdermal patches manner.
Manned spaceflight in the 21st century is the era of interplanetary flight, aerospace medicine is closely watched era is the era of China's manned space flourish. Only the central issue, and grasp the opportunity to open up a new world of human survival and development.
Various emergency contingency measures in special circumstances. Invisible accident risk prevention. Enhancing drugs and other screening methods immunity aerospace medicine and tissue engineering a microgravity environment. Drug mixture of APS, ginseng polysaccharides, Ganoderma lucidum polysaccharides, polysaccharides and Lentinan, from other compounds. Drug development space syndrome drug, chemical structure modification will be an important part.
These issues are very sensitive, cutting-edge technology is a major difficulty landing on Mars. Countries in the world, especially the world's major space powers in the country strategies and technical research, the results of all kinds continue to emerge. United States, Russia, China, Europe, India, Japan and other countries is different. United States, Russia extraordinary strength. Many patented technology and health, and most belong to the top-secret technology. Especially in aerospace engineering and technological achievements is different from the general scientific literature, practical, commercial, industrial great, especially the performance of patents, know-how, technical drawings, engineering design and other aspects. Present Mars and return safely to Earth, the first manned, significance, everything is hard in the beginning, especially the first person to land on Mars This Mars for Human Sciences Research Mars, the moon, the earth, the solar system and the universe, life and other significant. Its far greater than the value of direct investments and business interests.
In addition, it is the development of new materials, suitable for deep space operations universe, life, and other detection, wider field.
Many aerospace materials, continuous research and development of materials are key areas of aerospace development, including material rocket, the spacecraft materials, the suit materials, radiation materials, materials and equipment, instruments, materials and so on biochemistry.
Temperature metal-based compound with a metal matrix composite body with a more primordial higher temperature strength, creep resistance, impact resistance, thermal fatigue and other excellent high temperature performance.
In B, C, SiC fiber reinforced Ti3Al, TiAl, Ni3Al intermetallic matrix composites, etc.
W Fiber Reinforced with nickel-based, iron-based alloys as well as SiC, TiB2, Si3N4 and BN particle reinforced metal matrix composites
High temperature service conditions require the development of ceramic and carbon-based composite materials, etc., not in this eleven Cheung said.
Fuel storage
In order to survive in space, people need many things: food, oxygen, shelter, and, perhaps most importantly, fuel. The initial quality Mars mission somewhere around 80 percent of the space launch humans will be propellant. The fuel amount of storage space is very difficult.
This difference in low Earth orbit cause liquid hydrogen and liquid oxygen - rocket fuel - vaporization.
Hydrogen is particularly likely to leak out, resulting in a loss of about 4% per month.
When you want to get people to Mars speed to minimize exposure to weightlessness and space radiation hazards
Mars
Landings on the Martian surface, they realized that they reached the limit. The rapid expansion of the thin Martian atmosphere can not be very large parachute, such as those that will need to be large enough to slow down, carry human spacecraft.
Therefore, the parachute strong mass ratio, high temperature resistance, Bing shot performance and other aspects of textile materials used have special requirements, in order to make a parachute can be used in rockets, missiles, Yu arrows spacecraft and other spacecraft recovery, it is necessary to improve the canopy heat resistance, a high melting point polymeric fiber fabric used, the metal fabric, ceramic fiber fabrics, and other devices.
Super rigid parachute to help slow the landing vehicle.
Spacecraft entered the Martian atmosphere at 24,000 km / h. Even after slowing parachute or inflatable, it will be very
Once we have the protection of the Earth magnetic field, the solar radiation will accumulate in the body, a huge explosion threw the spacecraft may potentially lethal doses of radiation astronauts.
In addition to radiation, the biggest challenge is manned trip to Mars microgravity, as previously described.
The moon is sterile. Mars is another case entirely.
With dust treatment measures.
Arid Martian environment to create a super-tiny dust particles flying around the Earth for billions of years.
Apollo moon dust encountered. Ultra-sharp and abrasive lunar dust was named something that can clog the basic functions of mechanical damage. High chloride salt, which can cause thyroid problems in people.
Mars geological structure and geological structure of the moon, water on Mars geology, geology of the Moon is very important, because he, like the Earth's geology is related to many important issues. Water, the first element of life, air, temperature, and complex geological formations are geological structure. Cosmic geology research methods, mainly through a variety of detection equipment equipped with a space probe, celestial observations of atmospheric composition, composition and distribution of temperature, pressure, wind speed, vertical structure, composition of the solar wind, the water, the surface topography and Zoning, topsoil the composition and characteristics of the component surface of the rock, type and distribution, stratigraphic sequence, structural system and the internal shell structure.
Mars internal situation only rely on its surface condition of large amounts of data and related information inferred. It is generally believed that the core radius of 1700 km of high-density material composition; outsourcing a layer of lava, it is denser than the Earth's mantle some; outermost layer is a thin crust. Compared to other terrestrial planets, the lower the density of Mars, which indicates that the Martian core of iron (magnesium and iron sulfide) with may contain more sulfur. Like Mercury and the Moon, Mars and lack active plate movement; there is no indication that the crust of Mars occurred can cause translational events like the Earth like so many of folded mountains. Since there is no lateral movement in the earth's crust under the giant hot zone relative to the ground in a stationary state. Slight stress coupled with the ground, resulting in Tharis bumps and huge volcano. For the geological structure of Mars is very important, which is why repeated explorations and studies of Martian geological reasons.
Earth's surface
Each detector component landing site soil analysis:
Element weight percent
Viking 1
Oxygen 40-45
Si 18-25
Iron 12-15
K 8
Calcium 3-5
Magnesium 3-6
S 2-5
Aluminum 2-5
Cesium 0.1-0.5
Core
Mars is about half the radius of the core radius, in addition to the primary iron further comprises 15 to 17% of the sulfur content of lighter elements is also twice the Earth, so the low melting point, so that the core portion of a liquid, such as outside the Earth nuclear.
Mantle
Nuclear outer coating silicate mantle.
Crust
The outermost layer of the crust.
Crustal thickness obtained, the original thickness of the low north 40 km south plateau 70 kilometers thick, an average of 50 kilometers, at least 80 km Tharsis plateau and the Antarctic Plateau, and in the impact basin is thin, as only about 10 kilometers Greece plains.
Canyon of Mars there are two categories: outflow channels (outflow channel) and tree valley (valley network). The former is very large, it can be 100 km wide, over 2000 km long, streamlined, mainly in the younger Northern Hemisphere, such as the plain around Tyre Chris Canyon and Canyon jam.
In addition, the volcanic activity sometimes lava formation lava channels (lava channel); crustal stress generated by fissures, faults, forming numerous parallel extending grooves (fossa), such as around the huge Tharsis volcanic plateau radially distributed numerous grooves, which can again lead to volcanic activity.
Presumably, Mars has an iron as the main component of the nucleus, and contains sulfur, magnesium and other light elements, the nuclear share of Mars, the Earth should be relatively small. The outer core is covered with a thick layer of magnesium-rich silicate mantle, the surface of rocky crust. The density of Earth-like planets Mars is the lowest, only 3.93g / cc.
Hierarchy
The crust
Lunar core
The average density of the Moon is 3.3464 g / cc, the solar system satellites second highest (after Aiou). However, there are few clues mean lunar core is small, only about 350 km radius or less [2]. The core of the moon is only about 20% the size of the moon, the moon's interior has a solid, iron-rich core diameter of about 240 kilometers (150 miles); in addition there is a liquid core, mainly composed of iron outer core, about 330 km in diameter (205 miles), and for the first time compared with the core of the Earth, considered as the earth's outer core, like sulfur and oxygen may have lighter elements [4].
Chemical elements on the lunar surface constituted in accordance with its abundance as follows: oxygen (O), silicon (Si), iron (Fe), magnesium (Mg), calcium (Ca), aluminum (Al), manganese (Mn), titanium ( Ti). The most abundant is oxygen, silicon and iron. The oxygen content is estimated to be 42% (by weight). Carbon (C) and nitrogen (N) only traces seem to exist only in trace amounts deposited in the solar wind brings.
Lunar Prospector from the measured neutron spectra, the hydrogen (H) mainly in the lunar poles [2].
Element content (%)
Oxygen 42%
Silicon 21%
Iron 13%
Calcium 8%
Aluminum 7%
Magnesium 6%
Other 3%
Lunar surface relative content of each element (% by weight)
Moon geological history is an important event in recent global magma ocean crystallization. The specific depth is not clear, but some studies have shown that at least a depth of about 500 kilometers or more.
Lunar landscape
Lunar landscape can be described as impact craters and ejecta, some volcanoes, hills, lava-filled depressions.
Regolith
TABLE bear the asteroid and comets billions of years of bombardment. Over time, the impact of these processes have already broken into fine-grained surface rock debris, called regolith. Young mare area, regolith thickness of about 2 meters, while the oldest dated land, regolith thickness of up to 20 meters. Through the analysis of lunar soil components, in particular the isotopic composition changes can determine the period of solar activity. Solar wind gases possible future lunar base is useful because oxygen, hydrogen (water), carbon and nitrogen is not only essential to life, but also may be useful for fuel production. Lunar soil constituents may also be as a future source of energy.
Here, repeatedly stressed that the geological structure and geological structure of celestial bodies, the Earth, Moon, Mars, or that this human existence and development of biological life forms is very important, especially in a series of data Martian geological structure geological structure is directly related to human landing Mars and the successful transformation of Mars or not. for example, water, liquid water, water, oxygen, synthesis, must not be taken lightly.
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Mars landing 10 Technology
Aerospace Science and space science and technology major innovation of the most critical of sophisticated technology R & D project
[
"1" rocket propulsion technology ion fusion nuclear pulse propulsion rocket powered high-speed heavy rocket technology, space nuclear reactors spacecraft] brought big problems reflected in the nuclear reaction, nuclear radiation on spacecraft launch, control, brakes and other impact.
In particular, for the future of nuclear power spacecraft, the need to solve the nuclear reactor design, manufacture, control, cooling, radiation shielding, exhaust pollution, high thermoelectric conversion efficiency and a series of technical problems.
In particular, nuclear reactors produce radiation on astronauts' health will pose a great threat, which requires the spacecraft to be nuclear radiation shielding to ensure astronaut and ship the goods from radiation and heat from the reactor influence, but this will greatly increase the weight of the detector.
Space nuclear process applications, nuclear reaction decay is not a problem, but in a vacuum, ultra-low temperature environment, the nuclear reaction materials, energy transport materials have very high demands.
Space facing the reality of a nuclear reactor cooling cooling problems. To prevent problems with the reactor, "Washington" aircraft carrier to take four heavy protective measures for the radiation enclosed in the warship. These four measures are: the fuel itself, fuel storage pressure vessel, reactor shell and the hull. US Navy fuel all metal fuel, designed to take the impact resistance of the war, does not release fission product can withstand more than 50 times the gravity of the impact load; product of nuclear fission reactor fuel will never enter loop cooling water. The third layer of protection is specially designed and manufactured the reactor shell. The fourth layer is a very strong anti-impact combat ship, the reactor is arranged in the center of the ship, very safe. Engage in a reactor can only be loaded up to the aircraft, so as to drive the motor, and then drive the propeller. That is the core advantage of the heat generated by the heated gas flow, high temperature high pressure gas discharge backward, thereby generating thrust.
.
After installation AMPS1000 type nuclear power plant, a nuclear fuel assembly: He is a core member of the nuclear fuel chain reaction. Usually made into uranium dioxide, of which only a few percent uranium-235, and most of it is not directly involved in the nuclear fission of uranium 238. The uranium dioxide sintered into cylindrical pieces, into a stainless steel or a zirconium alloy do metal tubes called fuel rods or the original, then the number of fuel rods loaded metal cylinder in an orderly composition of the fuel assembly, and finally put a lot of vertical distribution of fuel assemblies in the reactor.
Nuclear reactor pressure vessel is a housing for containing nuclear fuel and reactor internals, for producing high-quality high-strength steel is made to withstand the pressure of dozens MPa. Import and export of the coolant in the pressure vessel.
The top of the pressure vessel closure, and can be used to accommodate the fixed control rod drive mechanism, pressure vessel head has a semi-circular, flat-topped.
Roof bolt: used to connect the locking pressure vessel head, so that the cylinder to form a completely sealed container.
Neutron Source: Plug in nuclear reactors can provide sufficient neutron, nuclear fuel ignition, to start to enhance the role of nuclear reactors and nuclear power. Neutron source generally composed of radium, polonium, beryllium, antimony production. Neutron source and neutron fission reactors are fast neutron, can not cause fission of uranium 235, in order to slow down, we need to moderator ---- full of pure water in a nuclear reactor. Aircraft carriers, submarines use nuclear reactor control has proven more successful.
Rod: has a strong ability to absorb neutrons, driven by the control rod drive mechanism, can move up and down in a nuclear reactor control rods within the nuclear fuel used to start, shut down the nuclear reactor, and maintain, regulate reactor power. Hafnium control rods in general, silver, indium, cadmium and other metals production.
Control rod drive mechanism: He is the executive body of nuclear reactors operating system and security protection systems, in strict accordance with requirements of the system or its operator control rod drives do move up and down in a nuclear reactor, nuclear reactor for power control. In a crisis situation, you also can quickly control rods fully inserted into the reactor in order to achieve the purpose of the emergency shutdown
Upper and lower support plate: used to secure the fuel assembly. High temperature and pressure inside the reactor is filled with pure water (so called pressurized water reactors), on the one hand he was passing through a nuclear reactor core, cooling the nuclear fuel, to act as a coolant, on the other hand it accumulates in the pressure vessel in play moderated neutrons role, acting as moderator.
Water quality monitoring sampling system:
Adding chemical system: under normal circumstances, for adding hydrazine, hydrogen, pH control agents to the primary coolant system, the main purpose is to remove and reduce coolant oxygen, high oxygen water suppression equipment wall corrosion (usually at a high temperature oxygen with hydrogen, especially at low temperatures during startup of a nuclear reactor with added hydrazine oxygen); when the nuclear reactor control rods stuck for some reason can not shutdown time by the the system can inject the nuclear reactor neutron absorber (such as boric acid solution), emergency shutdown, in order to ensure the safety of nuclear submarines.
Water system: a loop inside the water will be reduced at work, such as water sampling and analysis, equipment leaks, because the shutdown process cooling water and reduction of thermal expansion and contraction.
Equipment cooling water system:
Pressure safety systems: pressure reactor primary coolant system may change rapidly for some reason, the need for effective control. And in severe burn nuclear fuel rods, resulting in a core melt accident, it is necessary to promptly increase the pressure. Turn the regulator measures the electric, heating and cooling water. If necessary, also temporary startup booster pump.
Residual Heat Removal System: reactor scram may be due to an accident, such as when the primary coolant system of the steam generator heat exchanger tube is damaged, it must be urgently closed reactors.
Safety Injection System: The main components of this system is the high-pressure injection pump.
Radioactive waste treatment systems:
Decontamination Systems: for the removal of radioactive deposits equipment, valves, pipes and accessories, and other surfaces.
Europe, the United States and Russia and other countries related to aircraft carriers, submarines, icebreakers, nuclear-powered research aircraft, there are lots of achievements use of nuclear energy, it is worth analysis. However, nuclear reactor technology, rocket ships and the former are very different, therefore, requires special attention and innovative research. Must adopt a new new design techniques, otherwise, fall into the stereotype, it will avail, nothing even cause harm Aerospace.
[ "2" spacecraft structure]
[ "3"] radiation technology is the use of deep-sea sedimentation fabric fabrics deepwater technology development precipitated silver metal fibers or fiber lint and other materials and micronaire value between 4.1 to 4.3 fibers made from blends. For radiation protection field, it greatly enhances the effects of radiation and service life of clothing. Radiation resistant fiber) radiation resistant fiber - fiber polyimide polyimide fibers
60 years the United States has successfully developed polyimide fibers, it has highlighted the high temperature, radiation-resistant, fire-retardant properties.
[ "4" cosmic radiation resistant clothing design multifunctional anti-aging, wear underwear] ① comfort layer: astronauts can not wash clothes in a long flight, a lot of sebum, perspiration, etc. will contaminate underwear, so use soft, absorbent and breathable cotton knitwear making.
② warm layer: at ambient temperature range is not the case, warm layer to maintain a comfortable temperature environment. Choose warm and good thermal resistance large, soft, lightweight material, such as synthetic fibers, flakes, wool and silk and so on.
③ ventilation and cooling clothes clothes
Spacesuit
In astronaut body heat is too high, water-cooled ventilation clothing and clothing to a different way of heat. If the body heat production more than 350 kcal / h (ventilated clothes can not meet the cooling requirements, then that is cooled by a water-cooled suit. Ventilating clothing and water-cooled multi-use compression clothing, durable, flexible plastic tubing, such as polyvinyl chloride pipe or nylon film.
④ airtight limiting layer:
⑤ insulation: astronaut during extravehicular activities, from hot or cold insulation protection. It multilayer aluminized polyester film or a polyimide film and sandwiched between layers of nonwoven fabric to be made.
⑥ protective cover layer: the outermost layer of the suit is to require fire, heat and anti-space radiation on various factors (micrometeorites, cosmic rays, etc.) on the human body. Most of this layer with aluminized fabric.
New space suits using a special radiation shielding material, double design.
And also supporting spacesuit helmet, gloves, boots and so on.
[ "5" space - Aerospace biomedical technology, space, special use of rescue medication Space mental health care systems in space without damage restful sleep positions - drugs, simple space emergency medical system
]
[ "6" landing control technology, alternate control technology, high-performance multi-purpose landing deceleration device (parachute)]
[ "7" Mars truck, unitary Mars spacecraft solar energy battery super multi-legged (rounds) intelligent robot] multifunction remote sensing instruments on Mars, Mars and more intelligent giant telescope
[8 <> Mars warehouse activities, automatic Mars lander - Automatic start off cabin
]
[ "9" Mars - spacecraft docking control system, return to the system design]
Space flight secondary emergency life - support system
Spacecraft a
This booklet describes the properties and scientific research applicable to the "Blaydon foundry coke" manufactured by the Priestman Collieries at Blaydon-on-Tyne, a little upstream from Newcastle. Coal is not 'just' coal but different types and seams have differing properties and some, such as for metallurgical foundry coke, are better than others depending on factors such as structure, ash and sulphur content and calorific value.
It shows the details of this specific coke as well as showing some of the laboratory and testing processes that Priestman, obviously a very organised and scientific concern, undertook to ensure the product supplied was consistant. It includes a copy of a letter, dated 1929, from a 'satisfied customer' for Blaydon Burn Coke - this being one Sir W G Armstrong, Whitworth & Co Ltd. They also mention that this specific foundry coke is manufactured in by-product (or bye-products) ovens and that they also produce a coke manufactured for those foundries that preferred the older Beehive Coke, the Priestman Garsfield Beehive Foundry Coke.
Fountains inside the premises of Chowmahalla Palace - Old Hyderabad City, Andhra Pradesh, India.
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Chowmahalla Palace or Chowmahallat (4 Palaces), was a palace belonging to the Nizams of Hyderabad state. It was the seat of the Asaf Jahi dynasty and was the official residence of the Nizam.
In Persian, Chahar means four and in Arabic Mahalat (plural of Mahal) means palaces, hence the name Chowmahallat/four palaces, or four palaces.
All ceremonial functions including the accession of the Nizams and receptions for the Governor-General were held at this palace.
The prestigious UNESCO Asia Pacific Merit award for cultural heritage conservation was presented to Chowmahalla Palace on March 15, 2010. UNESCO representative Takahiko Makino formally handed over the plaque and certificate to Princess Esra, former wife and GPA holder of Prince Mukarram Jah Bahadur.
While Salabat Jung initiated its construction in 1750, it was completed by the period of Afzal ad-Dawlah, Asaf Jah V, the V Nizam ensured its completion between 1857 and 1869.
It is believed to be modelled on Shah of Iran's palace in Tehran.
The palace is unique for its style and elegance. Building of the palace began in the late 18th century and over the decades a synthesis of many architectural styles and influences emerged.
This palace consists of two courtyards, southern courtyard and northern courtyard. They have elegant palaces, the grand Khilwat (the Durbar Hall), fountains and gardens.
The palace originally covered 45 acres (180,000 m2), but only 14 acres (57,000 m2) remain today.
The present Nizam (Barkat Ali Khan Mukarram Jah, Pretender) and his family decided to restore the Chowmahalla Palace and open it to the public in January 2005. It took over 5 years to document and restore the palaces of the first courtyard to its former glory.
Source : en.wikipedia.org/wiki/Chowmahalla_Palace
Fangruida: human landing on Mars 10 cutting-edge technology
[Fangruida- human landing on Mars 10 innovative and sophisticated technologies]
Aerospace Science and space science and technology major innovation of the most critical of sophisticated technology R & D project
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Aerospace Science Space Science and Technology on behalf of the world's most cutting-edge leader in high technology, materials, mechatronics, information and communication, energy, biomedical, marine, aviation aerospace, microelectronics, computer, automation, intelligent biochips, use of nuclear energy, light mechanical and electrical integration, astrophysics, celestial chemistry, astrophysics and so a series of geological science and technology. Especially after the moon landing, the further development of mankind to Mars and other planets into the powerful offensive, the world's major powers eager to Daxian hand of God, increase investment, vigorously develop new sophisticated technology projects for space to space. Satellite, space station, the new spacecraft, the new space suits, the new radiation protection materials, intelligent materials, new manufacturing technology, communications technology, computer technology, detector technology, rover, rover technology, biomedical technology, and so one after another, is expected to greater breakthroughs and leaps. For example, rocket technology, spacecraft design, large power spacecraft, spacesuits design improvements, radiation multifunctional composite materials, life health care technology and space medicine, prevention against microgravity microgravity applicable drugs, tracking control technology, landing and return technology. Mars lander and returned safely to Earth as a top priority. Secondly, Mars, the Moon base and the use of transforming Mars, the Moon and other development will follow. Whether the former or the latter, are the modern aerospace science, space science basic research, applied basic research and applied research in the major cutting-edge technology. These major cutting-edge technology research and innovation, not only for human landing on Mars and the safe return of great significance, but for the entire space science, impact immeasurable universe sciences, earth sciences and human life. Here the most critical of the most important research projects of several sophisticated technology research and development as well as its core technology brief. Limit non-scientific techniques include non-technical limits of technology, the key lies in technology research and development of technology maturity, advanced technology, innovative, practical, reliable, practical application, business value and investment costs, and not simply like the idea mature technology achievements, difficult to put into things. This is the high-tech research and development, testing, prototype, test application testing, until the outcome of industrialization. Especially in aerospace technology, advanced, novelty, practicality, reliability, economy, maturity, commercial value and so on. For technical and research purely science fiction and the like may be irrelevant depth, but not as aerospace engineering and technology practice. Otherwise, Mars will become a dream fantasy, and even into settling crashed out of danger.
Regardless of the moon or Mars, many technical difficulties, especially a human landing on Mars and return safely to Earth, technical difficulties mainly in the following aspects. (Transformation of Mars and the Moon and other planets and detect other livable technology more complex and difficult, at this stage it is difficult to achieve and therefore not discussed in detail in this study). In fact, Mars will be the safe return of a full set of technology, space science, aerospace crucial scientific research development, its significance is not confined to Mars simply a return to scientific value, great commercial value, can not be measure.
1. Powered rocket, the spacecraft overall structural design not be too complex large, otherwise, the safety factor to reduce the risk of failure accidents. Fusion rocket engine main problem to be solved is the high-temperature materials and fuel ignition chamber (reaction chamber temperatures of up to tens of millions of supreme billion degrees), fissile class rocket engine whose essence is the miniaturization of nuclear reactors, and placed on the rocket. Nuclear rocket engine fuel as an energy source, with liquid hydrogen, liquid helium, liquid ammonia working fluid. Nuclear rocket engine mounted in the thrust chamber of the reactor, cooling nozzle, the working fluid delivery and control systems and other components. This engine due to nuclear radiation protection, exhaust pollution, reactor control and efficient heat exchanger design and other issues unresolved. Electrothermal rocket engine utilizing heat energy (resistance heating or electric arc heating) working medium (hydrogen, amines, hydrazine ), vaporized; nozzle expansion accelerated after discharged from the spout to generate thrust. Static rocket engine working fluid (mercury, cesium, hydrogen, etc.) from the tank enter the ionization chamber is formed thrust ionized into a plasma jet. Electric rocket engines with a high specific impulse (700-2500 sec), extremely long life (can be repeated thousands of times a starter, a total of up to thousands of hours of work). But the thrust of less than 100N. This engine is only available for spacecraft attitude control, station-keeping and the like. One nuclear - power rocket design is as follows: Firstly, the reactor heats water to make it into steam, and then the high-speed steam ejected, push the rocket. Nuclear rocket using hydrogen as working substance may be a better solution, it is one of the most commonly used liquid hydrogen rocket fuel rocket carrying liquid hydrogen virtually no technical difficulties. Heating hydrogen nuclear reactor, as long as it eventually reaches or exceeds current jet velocity hydrogen rocket engine jet speed, the same weight of the rocket will be able to work longer, it can accelerate the Rockets faster. Here there are only two problems: First, the final weight includes the weight of the rocket in nuclear reactors, so it must be as light as possible. Ultra-small nuclear reactor has been able to achieve. Furthermore, if used in outer space, we can not consider the problem of radioactive residues, simply to just one proton hydrogen nuclei are less likely to produce induced radioactivity, thus shielding layer can be made thinner, injected hydrogen gas can flow directly through the reactor core, it is not easy to solve, and that is how to get back at high speed heated gas is ejected.
Rocket engine with a nuclear fission reactor, based on the heating liquid hydrogen propellant, rather than igniting flammable propellant
High-speed heavy rocket is a major cutting-edge technology. After all, space flight and aircraft carriers, submarines, nuclear reactors differ greatly from the one hand, the use of traditional fuels, on the one hand can be nuclear reactor technology. From the control, for security reasons, the use of nuclear power rocket technology, safe and reliable overriding indicators. Nuclear atomic energy in line with the norms and rules of outer space. For the immature fetal abdominal hatchery technology, and resolutely reject use. This is the most significant development of nuclear-powered rocket principle.
Nuclear-powered spaceship for Use of nuclear power are three kinds:
The first method: no water or air space such media can not be used propeller must use jet approach. Reactor nuclear fission or fusion to produce a lot of heat, we will propellant (such as liquid hydrogen) injection, the rapid expansion of the propellant will be heated and then discharged from the engine speed tail thrust. This method is most readily available.
The second method: nuclear reactor will have a lot of fast-moving ions, these energetic particles moving very fast, so you can use a magnetic field to control their ejection direction. This principle ion rocket similar to the tail of the rocket ejected from the high-speed mobile ions, so that the recoil movement of a rocket. The advantage of this approach is to promote the unusually large ratio, without carrying any medium, continued strong. Ion engine, which is commonly referred to as "electric rocket", the principle is not complicated, the propellant is ionized particles,
Plasma Engine
Electromagnetic acceleration, high-speed spray. From the development trend, the US research scope covers almost all types of electric thrusters, but mainly to the development of ion engines, NASA in which to play the most active intake technology and preparedness plans. "
The third method: the use of nuclear explosions. It is a bold and crazy way, no longer is the use of a controlled nuclear reaction, but to use nuclear explosions to drive the ship, this is not an engine, and it is called a nuclear pulse rocket. This spacecraft will carry a lot of low-yield atomic bombs out one behind, and then detonated, followed by a spacecraft propulsion installation disk, absorbing the blast pushing the spacecraft forward. This was in 1955 to Orion (Project Orion) name of the project, originally planned to bring two thousand atomic bombs, Orion later fetal nuclear thermal rocket. Its principle is mounted on a small rocket reactor, the reactor utilizing thermal energy generated by the propellant is heated to a high temperature, high pressure and high temperature of the propellant from the high-speed spray nozzle, a tremendous impetus.
Common nuclear fission technologies, including nuclear pulse rocket engines, nuclear rockets, nuclear thermal rocket and nuclear stamping rockets to nuclear thermal rocket, for example, the size of its land-based nuclear power plant reactor structure than the much smaller, more uranium-235 purity requirements high, reaching more than 90%, at the request of the high specific impulse engine core temperature will reach about 3000K, require excellent high temperature properties of materials.
Research and test new IT technologies and new products and new technology and new materials, new equipment, things are difficult, design is the most important part, especially in the overall design, technical solutions, technical route, technical process, technical and economic particularly significant. The overall design is defective, technology there are loopholes in the program, will be a major technical route deviation, but also directly related to the success of research trials. so, any time, under any circumstances, a good grasp of the overall control of design, technical design, is essential. otherwise, a done deal, it is difficult save. aerospace technology research and product development is true.
3, high-performance nuclear rocket
Nuclear rocket nuclear fission and fusion energy can rocket rocket two categories. Nuclear fission and fusion produce heat, radiation and shock waves and other large amounts of energy, but here they are contemplated for use as a thermal energy rocket.
Uranium and other heavy elements, under certain conditions, will split their nuclei, called nuclear fission reaction. The atomic bomb is the result of nuclear fission reactions. Nuclear fission reaction to release energy, is a million times more chemical rocket propellant combustion energy. Therefore, nuclear fission energy is a high-performance rocket rockets. Since it requires much less propellant than chemical rockets can, so to its own weight is much lighter than chemical rockets energy. For the same quality of the rocket, the rocket payload of nuclear fission energy is much greater than the chemical energy of the rocket. Just nuclear fission energy rocket is still in the works.
Use of nuclear fission energy as the energy of the rocket, called the atomic rockets. It is to make hydrogen or other inert gas working fluid through the reactor, the hydrogen after the heating temperature quickly rose to 2000 ℃, and then into the nozzle, high-speed spray to produce thrust.
A vision plan is to use liquid hydrogen working fluid, in operation, the liquid hydrogen tank in the liquid hydrogen pump is withdrawn through the catheter and the engine cooling jacket and liquid hydrogen into hydrogen gas, hydrogen gas turbine-driven, locally expansion. Then by nuclear fission reactors, nuclear fission reactions absorb heat released, a sharp rise in temperature, and finally into the nozzle, the rapid expansion of high-speed spray. Calculations show that the amount of atomic payload rockets, rocket high chemical energy than 5-8 times.
Hydrogen and other light elements, under certain conditions, their nuclei convergent synthesis of new heavy nuclei, and release a lot of energy, called nuclear fusion reaction, also called thermonuclear reaction.
Using energy generated by the fusion reaction for energy rocket, called fusion energy rocket or nuclear thermal rockets. But it is also not only take advantage of controlled nuclear fusion reaction to manufacture hydrogen bombs, rockets and controlled nuclear fusion reaction needs still studying it.
Of course there are various research and development of rocket technology and technical solutions to try.
It is envisaged that the rocket deuterium, an isotope of hydrogen with deuterium nuclear fusion reaction of helium nuclei, protons and neutrons, and release huge amounts of energy, just polymerized ionized helium to temperatures up to 100 million degrees the plasma, and then nozzle expansion, high-speed ejection, the exhaust speed of up to 15,000 km / sec, atomic energy is 1800 times the rocket, the rocket is the chemical energy of 3700 times.
Nuclear rocket engine fuel as an energy source, with liquid hydrogen, liquid helium, liquid ammonia working fluid. Nuclear rocket engine mounted in the thrust chamber of the reactor, cooling nozzle, the working fluid delivery and control systems and other components. In a nuclear reactor, nuclear energy into heat to heat the working fluid, the working fluid is heated after expansion nozzle to accelerate to the speed of 6500 ~ 11,000 m / sec from the discharge orifice to produce thrust. Nuclear rocket engine specific impulse (250 to 1000 seconds) long life, but the technology is complex, apply only to long-term spacecraft. This engine due to nuclear radiation protection, exhaust pollution, reactor control and efficient heat exchanger design and other issues not resolved, is still in the midst of trials. Nuclear rocket technology is cutting-edge aerospace science technology, centralized many professional and technical sciences and aerospace, nuclear physics, nuclear chemistry, materials science, the long term future ___-- wide width. The United States, Russia and Europe, China, India, Japan, Britain, Brazil and other countries in this regard have studies, in particular the United States and Russia led the way, impressive. Of course, at this stage of nuclear rocket technology, technology development there are still many difficulties. Fully formed, still to be. But humanity marching to the universe, nuclear reactor applications is essential.
Outer Space Treaty (International Convention on the Peaceful Uses of Outer Space) ****
Use of Nuclear Power Sources in Outer Space Principle 15
General Assembly,
Having considered the report of its thirty-fifth session of the Committee on the Peaceful Uses of Outer Space and the Commission of 16 nuclear
It can be attached in principle on the use of nuclear power sources in outer space of the text of its report, 17
Recognize that nuclear power sources due to small size, long life and other characteristics, especially suitable for use even necessary
For some missions in outer space,
Recognizing also that the use of nuclear power sources in outer space should focus on the possible use of nuclear power sources
Those uses,
Recognizing also that the use of nuclear power sources should include or probabilistic risk analysis is complete security in outer space
Full evaluation is based, in particular, the public should focus on reducing accidental exposure to harmful radiation or radioactive material risk
risk,
Recognizing the need to a set of principles containing goals and guidelines in this regard to ensure the safety of outer space makes
With nuclear power sources,
Affirming that this set principles apply exclusively on space objects for non-power generation, which is generally characteristic
Mission systems and implementation of nuclear power sources in outer space on similar principles and used by,
Recognizing this need to refer to a new set of principles for future nuclear power applications and internationally for radiological protection
The new proposal will be revised
By the following principles on the use of nuclear power sources in outer space.
Principle 1. Applicability of international law
Involving the use of nuclear power sources in outer space activities should be carried out in accordance with international law, especially the "UN
Principles of the Charter "and" States in the Exploration and Use of Outer Space, including the Moon and Other Celestial Bodies Activities
Treaty "3
.
2. The principle terms
1. For the purpose of these principles, "launching State" and "launching State ......" two words mean, in related
Principles related to a time of nuclear power sources in space objects exercises jurisdiction and control of the country.
2. For the purpose of principle 9, wherein the definition of the term "launching State" as contained in that principle.
3. For the purposes of principle 3, the terms "foreseeable" and "all possible" two words are used to describe the actual hair
The overall likelihood of students that it is considered for safety analysis is credible possibilities for a class of things
Member or circumstances. "General concept of defense in depth" when the term applies to nuclear power sources in outer space refers to various settings
Count form and space operations replace or supplement the operation of the system in order to prevent system failures or mitigate thereafter
"Official Records of the General Assembly, Forty-seventh Session, Supplement No. 20" 16 (A / 47/20).
17 Ibid., Annex.
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fruit. To achieve this purpose is not necessarily required for each individual member has redundant safety systems. Given space
Use and special requirements of various space missions, impossible to any particular set of systems or features can be specified as
Necessary to achieve this purpose. For the purpose of Principle 3 (d) of paragraph 2, "made critical" does not include
Including such as zero-power testing which are fundamental to ensuring system safety required.
Principle 3. Guidelines and criteria for safe use
To minimize the risk of radioactive material in space and the number involved, nuclear power sources in outer space
Use should be limited to non-nuclear power sources in space missions can not reasonably be performed
1. General goals for radiation protection and nuclear safety
(A) States launching space objects with nuclear power sources on board shall endeavor to protect individuals, populations and the biosphere
From radiation hazards. The design and use of space objects with nuclear power sources on board shall ensure that risk with confidence
Harm in the foreseeable operational or accidental circumstances, paragraph 1 (b) and (c) to define acceptable water
level.
Such design and use shall also ensure that radioactive material does not reliably significant contamination of outer space.
(B) the normal operation of nuclear power sources in space objects, including from paragraph 2 (b) as defined in foot
High enough to return to the track, shall be subject to appropriate anti-radiation recommended by the International Commission on Radiological Protection of the public
Protection goals. During such normal operation there shall be no significant radiation exposure;
(C) To limit exposure in accidents, the design and construction of nuclear power source systems shall take into account the international
Relevant and generally accepted radiological protection guidelines.
In addition to the probability of accidents with potentially serious radiological consequences is extremely low, the nuclear power source
Design systems shall be safely irradiated limited limited geographical area, for the individual radiation dose should be
Limited to no more than a year 1mSv primary dose limits. Allows the use of irradiation year for some years 5mSv deputy agent
Quantity limit, but the average over a lifetime effective dose equivalent annual dose not exceed the principal limit 1mSv
degree.
Should make these conditions occur with potentially serious radiological consequences of the probability of the system design is very
small.
Criteria mentioned in this paragraph Future modifications should be applied as soon as possible;
(D) general concept of defense in depth should be based on the design, construction and operation of systems important for safety. root
According to this concept, foreseeable safety-related failures or malfunctions must be capable of automatic action may be
Or procedures to correct or offset.
It should ensure that essential safety system reliability, inter alia, to make way for these systems
Component redundancy, physical separation, functional isolation and adequate independence.
It should also take other measures to increase the level of safety.
2. The nuclear reactor
(A) nuclear reactor can be used to:
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(I) On interplanetary missions;
(Ii) the second high enough orbit paragraph (b) as defined;
(Iii) low-Earth orbit, with the proviso that after their mission is complete enough to be kept in a nuclear reactor
High on the track;
(B) sufficiently high orbit the orbital lifetime is long enough to make the decay of fission products to approximately actinides
Element active track. The sufficiently high orbit must be such that existing and future outer space missions of crisis
Risk and danger of collision with other space objects to a minimum. In determining the height of the sufficiently high orbit when
It should also take into account the destroyed reactor components before re-entering the Earth's atmosphere have to go through the required decay time
between.
(C) only 235 nuclear reactors with highly enriched uranium fuel. The design shall take into account the fission and
Activation of radioactive decay products.
(D) nuclear reactors have reached their operating orbit or interplanetary trajectory can not be made critical state
state.
(E) nuclear reactor design and construction shall ensure that, before reaching the operating orbit during all possible events
Can not become critical state, including rocket explosion, re-entry, impact on ground or water, submersion
In water or water intruding into the core.
(F) a significant reduction in satellites with nuclear reactors to operate on a lifetime less than in the sufficiently high orbit orbit
For the period (including during operation into the sufficiently high orbit) the possibility of failure, there should be a very
Reliable operating system, in order to ensure an effective and controlled disposal of the reactor.
3. Radioisotope generators
(A) interplanetary missions and other spacecraft out of Earth's gravitational field tasks using radioactive isotopes
Su generator. As they are stored after completion of their mission in high orbit, the Earth can also be used
track. We are required to make the final treatment under any circumstances.
(B) Radioisotope generators shall be protected closed systems, design and construction of the system should
Ensure that in the foreseeable conditions of the track to withstand the heat and aerodynamic forces of re-entry in the upper atmosphere, orbit
Conditions including highly elliptical or hyperbolic orbits when relevant. Upon impact, the containment system and the occurrence of parity
Physical morpheme shall ensure that no radioactive material is scattered into the environment so you can complete a recovery operation
Clear all radioactive impact area.
Principle 4. Safety Assessment
1. When launching State emission consistent with the principles defined in paragraphs 1, prior to the launch in applicable under the
Designed, constructed or manufactured the nuclear power sources, or will operate the space object person, or from whose territory or facility
Transmits the object will be to ensure a thorough and comprehensive safety assessment. This assessment shall cover
All relevant stages of space mission and shall deal with all systems involved, including the means of launching, the space level
Taiwan, nuclear power source and its equipment and the means of control and communication between ground and space.
2. This assessment shall respect the principle of 3 contained in the guidelines and criteria for safe use.
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3. The principle of States in the Exploration and Use, including the Moon and Other Celestial Bodies Outer Space Activities Article
Results of about 11, this safety assessment should be published prior to each transmit simultaneously to the extent feasible
Note by the approximate intended time of launch, and shall notify the Secretary-General of the United Nations, how to be issued
This safety assessment before the shot to get the results as soon as possible.
Principle 5. Notification of re-entry
1. Any State launching a space object with nuclear power sources in space objects that failed to produce discharge
When radioactive substances dangerous to return to the earth, it shall promptly notify the country concerned. Notice shall be in the following format:
(A) System parameters:
(I) Name of launching State, including which may be contacted in the event of an accident to Request
Information or assistance to obtain the relevant authorities address;
(Ii) International title;
(Iii) Date and territory or location of launch;
(Iv) the information needed to make the best prediction of orbit lifetime, trajectory and impact region;
(V) General function of spacecraft;
(B) information on the radiological risk of nuclear power source:
(I) the type of power source: radioisotopes / reactor;
(Ii) the fuel could fall into the ground and may be affected by the physical state of contaminated and / or activated components, the number of
The amount and general radiological characteristics. The term "fuel" refers to as a source of heat or power of nuclear material.
This information shall also be sent to the Secretary-General of the United Nations.
2. Once you know the failure, the launching State shall provide information on the compliance with the above format. Information should as far as possible
To be updated frequently, and in the dense layers of the Earth's atmosphere is expected to return to a time when close to the best increase
Frequency of new data, so that the international community understand the situation and will have sufficient time to plan for any deemed necessary
National contingency measures.
3. It should also be at the same frequency of the latest information available to the Secretary-General of the United Nations.
Principle 6. consultation
5 According to the national principles provide information shall, as far as reasonably practicable, other countries
Requirements to obtain further information or consultations promptly reply.
Principle 7. Assistance to States
1. Upon receipt of expected with nuclear power sources on space objects and their components will return through the Earth's atmosphere
After know that all countries possessing space monitoring and tracking facilities, in the spirit of international cooperation, as soon as possible to
The Secretary-General of the United Nations and the countries they may have made space objects carrying nuclear power sources
A fault related information, so that the States may be affected to assess the situation and take any
It is considered to be the necessary precautions.
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2. In carrying space objects with nuclear power sources back to the Earth's atmosphere after its components:
(A) launching State shall be requested by the affected countries to quickly provide the necessary assistance to eliminate actual
And possible effects, including nuclear power sources to assist in identifying locations hit the Earth's surface, to detect the re substance
Quality and recovery or cleanup activities.
(B) All countries with relevant technical capabilities other than the launching State, and with such technical capabilities
International organizations shall, where possible, in accordance with the requirements of the affected countries to provide the necessary co
help.
When according to the above (a) and subparagraph (b) to provide assistance, should take into account the special needs of developing countries.
Principle 8. Responsibility
In accordance with the States in the Exploration and Use of Outer Space, including the Moon and Other Celestial Bodies activities, including the principles of Article
About Article, States shall bear international responsibility for their use of nuclear power sources in outer space relates to the activities
Whether such activities are carried on by governmental agencies or non-governmental entities, and shall bear international responsibility to ensure that this
Such activities undertaken by the country in line with the principles of the Treaty and the recommendations contained therein. If it involves the use of nuclear power sources
Activities in outer space by an international organization, should be done by the international organizations and States to participate in the organization
Undertakes to comply with the principles of the Treaty and the recommendations contained in these responsibilities.
Principle 9. Liability and Compensation
1. In accordance with the principle of States in the Exploration and Use, including the Moon and Other Celestial Bodies Outer Space Activities Article
And the Convention on International Liability for Damage Caused by Space Objects covenant of Article 7
Provisions, which launches or on behalf of the State
Each State launching a space object and each State from which territory or facility a space object is launched
Kinds of space object or damage caused by components shall bear international liability. This fully applies to this
Kind of space object carrying a nuclear power source case. Two or more States jointly launch a space object,
Each launching State shall in accordance with the above Article of the Convention for any damages jointly and severally liable.
2. Such countries under the aforesaid Convention shall bear the damages shall be in accordance with international law and fair and reasonable
The principles set out in order to provide for damages to make a claim on behalf of its natural or juridical persons, national or
International organizations to restore to the state before the occurrence of the damage.
3. For the purposes of this principle, compensation should be made to include reimbursement of the duly substantiated expenses for search, recovery and clean
Cost management work, including the cost of providing assistance to third parties.
10. The principle of dispute settlement
Since the implementation of these principles will lead to any dispute in accordance with the provisions of the UN Charter, by negotiation or
Other established procedures to resolve the peaceful settlement of disputes.
Here quoted the important provisions of the United Nations concerning the use of outer space for peaceful nuclear research and international conventions, the main emphasis on the Peaceful Uses of provisions related constraints .2 the use of nuclear rockets in outer space nuclear studies, etc., can cause greater attention in nuclear power nuclear rocket ship nuclear research, manufacture, use and other aspects of the mandatory hard indicators. this scientists, engineering and technical experts are also important constraints and requirements. as IAEA supervision and management as very important.
2. radiation. Space radiation is one of the greatest threats to the safety of the astronauts, including X-rays, γ-rays, cosmic rays and high-speed solar particles. Better than aluminum protective effect of high polymer composite materials.
3. Air. Perhaps the oxygen needed to rely on oxidation-reduction reaction of hydrogen and ilmenite production of water, followed by water electrolysis to generate oxygen. Mars oxygen necessary for survival but also from the decomposition of water, electrolytically separating water molecules of oxygen and hydrogen, this oxygen equipment has been successfully used in the International Space Station. Oxygen is released into the air to sustain life, the hydrogen system into the water system.
4. The issue of food waste recycling. At present, the International Space Station on the use of dehumidifiers, sucked moisture in the air to be purified, and then changed back to drinkable water. The astronauts' urine and sweat recycling. 5. water. The spacecraft and the space station on purification system also makes urine and other liquids can be purified utilization. 6. microgravity. In microgravity or weightlessness long-term space travel, if protective measures shall not be treated, the astronauts will be muscle atrophy, bone softening health. 7. contact. 8. Insulation, 9 energy. Any space exploration are inseparable from the energy battery is a new super hybrid energy storage device, the asymmetric lead-acid batteries and supercapacitors in the same compound within the system - and the so-called inside, no additional separate electronic control unit, this is an optimal combination. The traditional lead-acid battery PbO2 monomer is a positive electrode plate and a negative electrode plate spongy Pb composition, not a super cell. : Silicon solar cells, multi-compound thin film solar cells, multi-layer polymer-modified electrode solar cells, nano-crystalline solar cells, batteries and super class. For example, the solar aircraft .10. To protect the health and life safety and security systems. Lysophosphatidic acid LPA is a growth factor-like lipid mediators, the researchers found that this substance can on apoptosis after radiation injury and animal cells was inhibited. Stable lysophosphatidic acid analogs having the hematopoietic system and gastrointestinal tract caused by acute radiation sickness protection, knockout experiments show that lysophosphatidic acid receptors is an important foundation for the protection of radiation injury. In addition to work under high pressure, the astronauts face a number of health threats, including motion sickness, bacterial infections, blindness space, as well as psychological problems, including toxic dust. In the weightless environment of space, the astronaut's body will be like in preadolescents, as the emergence of various changes.
Plantar molt
After the environment to adapt to zero gravity, the astronaut's body will be some strange changes. Weightlessness cause fluid flow around the main flow torso and head, causing the astronauts facial swelling and inflammation, such as nasal congestion. During long-term stay in space
Bone and muscle loss
Most people weightlessness caused by the impact may be known bone and muscle degeneration. In addition, the calcium bones become very fragile and prone to fracture, which is why some of the astronauts after landing need on a stretcher.
Space Blindness
Space Blindness refers astronaut decreased vision.
Solar storms and radiation is one of the biggest challenges facing the long-term space flight. Since losing the protection of Earth's magnetic field, astronauts suffer far more than normal levels of radiation. The cumulative amount of radiation exposure in low earth orbit them exceeded by workers close to nuclear reactors, thereby increasing the risk of cancer.
Prolonged space flight can cause a series of psychological problems, including depression or mood swings, vulnerability, anxiety and fear, as well as other sequelae. We are familiar with the biology of the Earth, the Earth biochemistry, biophysics, after all, the Earth is very different astrophysics, celestial chemistry, biophysics and astrophysics, biochemistry and other celestial bodies. Therefore, you must be familiar with and adapt to these differences and changes.
Osteoporosis and its complications ranked first in the space of disease risk.
Long-term health risks associated with flying Topics
The degree of influence long-term biological effects of radiation in human flight can withstand the radiation and the maximum limit of accumulated radiation on physiology, pathology and genetics.
Physiological effects of weightlessness including: long-term bone loss and a return flight after the maximum extent and severity of the continued deterioration of other pathological problems induced by the; maximum flexibility and severity of possible long-term Flight Center in vascular function.
Long-term risk of disease due to the high risk of flight stress, microbial variation, decreased immune function, leading to infections
Radiation hazards and protection
1) radiation medicine, biology and pathway effects Features
Radiation protection for interplanetary flight, since the lack of protective effect of Earth's magnetic field, and by the irradiation time is longer, the possibility of increased radiation hazard.
Analysis of space flight medical problems that may occur, loss of appetite topped the list, sleep disorders, fatigue and insomnia, in addition, space sickness, musculoskeletal system problems, eye problems, infections problems, skin problems and cardiovascular problems
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Development of diagnostic techniques in orbit, the development of the volume of power consumption, features a wide range of diagnostic techniques, such as applied research of ultrasound diagnostic techniques in the abdominal thoracic trauma, bone, ligament damage, dental / sinus infections and other complications and integrated;
Actively explore in orbit disposal of medical technology, weightlessness surgical methods, development of special surgical instruments, the role of narcotic drugs and the like.
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However, space technology itself is integrated with the use of the most advanced technology, its challenging technical reserves and periodic demanding
With the continuous development of science and technology, space agencies plan a manned landing on the moon and Mars, space exploration emergency medicine current concern.
Space sickness
In the weightless environment of space, in the weightless environment of space, surgery may be extremely difficult and risky.
Robot surgeons
Space disease in three days after entering the space started to ease, although individual astronauts might subsequently relapse. January 2015 NASA declared working on a fast, anti-nausea and nasal sprays. In addition, due to the zero-gravity environment, and anti-nausea drugs can only be administered by injection or transdermal patches manner.
Manned spaceflight in the 21st century is the era of interplanetary flight, aerospace medicine is closely watched era is the era of China's manned space flourish. Only the central issue, and grasp the opportunity to open up a new world of human survival and development.
Various emergency contingency measures in special circumstances. Invisible accident risk prevention. Enhancing drugs and other screening methods immunity aerospace medicine and tissue engineering a microgravity environment. Drug mixture of APS, ginseng polysaccharides, Ganoderma lucidum polysaccharides, polysaccharides and Lentinan, from other compounds. Drug development space syndrome drug, chemical structure modification will be an important part.
These issues are very sensitive, cutting-edge technology is a major difficulty landing on Mars. Countries in the world, especially the world's major space powers in the country strategies and technical research, the results of all kinds continue to emerge. United States, Russia, China, Europe, India, Japan and other countries is different. United States, Russia extraordinary strength. Many patented technology and health, and most belong to the top-secret technology. Especially in aerospace engineering and technological achievements is different from the general scientific literature, practical, commercial, industrial great, especially the performance of patents, know-how, technical drawings, engineering design and other aspects. Present Mars and return safely to Earth, the first manned, significance, everything is hard in the beginning, especially the first person to land on Mars This Mars for Human Sciences Research Mars, the moon, the earth, the solar system and the universe, life and other significant. Its far greater than the value of direct investments and business interests.
In addition, it is the development of new materials, suitable for deep space operations universe, life, and other detection, wider field.
Many aerospace materials, continuous research and development of materials are key areas of aerospace development, including material rocket, the spacecraft materials, the suit materials, radiation materials, materials and equipment, instruments, materials and so on biochemistry.
Temperature metal-based compound with a metal matrix composite body with a more primordial higher temperature strength, creep resistance, impact resistance, thermal fatigue and other excellent high temperature performance.
In B, C, SiC fiber reinforced Ti3Al, TiAl, Ni3Al intermetallic matrix composites, etc.
W Fiber Reinforced with nickel-based, iron-based alloys as well as SiC, TiB2, Si3N4 and BN particle reinforced metal matrix composites
High temperature service conditions require the development of ceramic and carbon-based composite materials, etc., not in this eleven Cheung said.
Fuel storage
In order to survive in space, people need many things: food, oxygen, shelter, and, perhaps most importantly, fuel. The initial quality Mars mission somewhere around 80 percent of the space launch humans will be propellant. The fuel amount of storage space is very difficult.
This difference in low Earth orbit cause liquid hydrogen and liquid oxygen - rocket fuel - vaporization.
Hydrogen is particularly likely to leak out, resulting in a loss of about 4% per month.
When you want to get people to Mars speed to minimize exposure to weightlessness and space radiation hazards
Mars
Landings on the Martian surface, they realized that they reached the limit. The rapid expansion of the thin Martian atmosphere can not be very large parachute, such as those that will need to be large enough to slow down, carry human spacecraft.
Therefore, the parachute strong mass ratio, high temperature resistance, Bing shot performance and other aspects of textile materials used have special requirements, in order to make a parachute can be used in rockets, missiles, Yu arrows spacecraft and other spacecraft recovery, it is necessary to improve the canopy heat resistance, a high melting point polymeric fiber fabric used, the metal fabric, ceramic fiber fabrics, and other devices.
Super rigid parachute to help slow the landing vehicle.
Spacecraft entered the Martian atmosphere at 24,000 km / h. Even after slowing parachute or inflatable, it will be very
Once we have the protection of the Earth magnetic field, the solar radiation will accumulate in the body, a huge explosion threw the spacecraft may potentially lethal doses of radiation astronauts.
In addition to radiation, the biggest challenge is manned trip to Mars microgravity, as previously described.
The moon is sterile. Mars is another case entirely.
With dust treatment measures.
Arid Martian environment to create a super-tiny dust particles flying around the Earth for billions of years.
Apollo moon dust encountered. Ultra-sharp and abrasive lunar dust was named something that can clog the basic functions of mechanical damage. High chloride salt, which can cause thyroid problems in people.
*** Mars geological structure and geological structure of the moon, water on Mars geology, geology of the Moon is very important, because he, like the Earth's geology is related to many important issues. Water, the first element of life, air, temperature, and complex geological formations are geological structure. Cosmic geology research methods, mainly through a variety of detection equipment equipped with a space probe, celestial observations of atmospheric composition, composition and distribution of temperature, pressure, wind speed, vertical structure, composition of the solar wind, the water, the surface topography and Zoning, topsoil the composition and characteristics of the component surface of the rock, type and distribution, stratigraphic sequence, structural system and the internal shell structure.
Mars internal situation only rely on its surface condition of large amounts of data and related information inferred. It is generally believed that the core radius of 1700 km of high-density material composition; outsourcing a layer of lava, it is denser than the Earth's mantle some; outermost layer is a thin crust. Compared to other terrestrial planets, the lower the density of Mars, which indicates that the Martian core of iron (magnesium and iron sulfide) with may contain more sulfur. Like Mercury and the Moon, Mars and lack active plate movement; there is no indication that the crust of Mars occurred can cause translational events like the Earth like so many of folded mountains. Since there is no lateral movement in the earth's crust under the giant hot zone relative to the ground in a stationary state. Slight stress coupled with the ground, resulting in Tharis bumps and huge volcano. For the geological structure of Mars is very important, which is why repeated explorations and studies of Martian geological reasons.
Earth's surface
Each detector component landing site soil analysis:
Element weight percent
Viking 1
Oxygen 40-45
Si 18-25
Iron 12-15
K 8
Calcium 3-5
Magnesium 3-6
S 2-5
Aluminum 2-5
Cesium 0.1-0.5
Core
Mars is about half the radius of the core radius, in addition to the primary iron further comprises 15 to 17% of the sulfur content of lighter elements is also twice the Earth, so the low melting point, so that the core portion of a liquid, such as outside the Earth nuclear.
Mantle
Nuclear outer coating silicate mantle.
Crust
The outermost layer of the crust.
Crustal thickness obtained, the original thickness of the low north 40 km south plateau 70 kilometers thick, an average of 50 kilometers, at least 80 km Tharsis plateau and the Antarctic Plateau, and in the impact basin is thin, as only about 10 kilometers Greece plains.
Canyon of Mars there are two categories: outflow channels (outflow channel) and tree valley (valley network). The former is very large, it can be 100 km wide, over 2000 km long, streamlined, mainly in the younger Northern Hemisphere, such as the plain around Tyre Chris Canyon and Canyon jam.
In addition, the volcanic activity sometimes lava formation lava channels (lava channel); crustal stress generated by fissures, faults, forming numerous parallel extending grooves (fossa), such as around the huge Tharsis volcanic plateau radially distributed numerous grooves, which can again lead to volcanic activity.
Presumably, Mars has an iron as the main component of the nucleus, and contains sulfur, magnesium and other light elements, the nuclear share of Mars, the Earth should be relatively small. The outer core is covered with a thick layer of magnesium-rich silicate mantle, the surface of rocky crust. The density of Earth-like planets Mars is the lowest, only 3.93g / cc.
Hierarchy
The crust
Lunar core
The average density of the Moon is 3.3464 g / cc, the solar system satellites second highest (after Aiou). However, there are few clues mean lunar core is small, only about 350 km radius or less [2]. The core of the moon is only about 20% the size of the moon, the moon's interior has a solid, iron-rich core diameter of about 240 kilometers (150 miles); in addition there is a liquid core, mainly composed of iron outer core, about 330 km in diameter (205 miles), and for the first time compared with the core of the Earth, considered as the earth's outer core, like sulfur and oxygen may have lighter elements [4].
Chemical elements on the lunar surface constituted in accordance with its abundance as follows: oxygen (O), silicon (Si), iron (Fe), magnesium (Mg), calcium (Ca), aluminum (Al), manganese (Mn), titanium ( Ti). The most abundant is oxygen, silicon and iron. The oxygen content is estimated to be 42% (by weight). Carbon (C) and nitrogen (N) only traces seem to exist only in trace amounts deposited in the solar wind brings.
Lunar Prospector from the measured neutron spectra, the hydrogen (H) mainly in the lunar poles [2].
Element content (%)
Oxygen 42%
Silicon 21%
Iron 13%
Calcium 8%
Aluminum 7%
Magnesium 6%
Other 3%
Lunar surface relative content of each element (% by weight)
Moon geological history is an important event in recent global magma ocean crystallization. The specific depth is not clear, but some studies have shown that at least a depth of about 500 kilometers or more.
Lunar landscape
Lunar landscape can be described as impact craters and ejecta, some volcanoes, hills, lava-filled depressions.
Regolith
TABLE bear the asteroid and comets billions of years of bombardment. Over time, the impact of these processes have already broken into fine-grained surface rock debris, called regolith. Young mare area, regolith thickness of about 2 meters, while the oldest dated land, regolith thickness of up to 20 meters. Through the analysis of lunar soil components, in particular the isotopic composition changes can determine the period of solar activity. Solar wind gases possible future lunar base is useful because oxygen, hydrogen (water), carbon and nitrogen is not only essential to life, but also may be useful for fuel production. Lunar soil constituents may also be as a future source of energy.
Here, repeatedly stressed that the geological structure and geological structure of celestial bodies, the Earth, Moon, Mars, or that this human existence and development of biological life forms is very important, especially in a series of data Martian geological structure geological structure is directly related to human landing Mars and the successful transformation of Mars or not. for example, water, liquid water, water, oxygen, synthesis, must not be taken lightly.
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Mars landing 10 Technology
Aerospace Science and space science and technology major innovation of the most critical of sophisticated technology R & D project
[
"1" rocket propulsion technology ion fusion nuclear pulse propulsion rocket powered high-speed heavy rocket technology, space nuclear reactors spacecraft] brought big problems reflected in the nuclear reaction, nuclear radiation on spacecraft launch, control, brakes and other impact.
In particular, for the future of nuclear power spacecraft, the need to solve the nuclear reactor design, manufacture, control, cooling, radiation shielding, exhaust pollution, high thermoelectric conversion efficiency and a series of technical problems.
In particular, nuclear reactors produce radiation on astronauts' health will pose a great threat, which requires the spacecraft to be nuclear radiation shielding to ensure astronaut and ship the goods from radiation and heat from the reactor influence, but this will greatly increase the weight of the detector.
Space nuclear process applications, nuclear reaction decay is not a problem, but in a vacuum, ultra-low temperature environment, the nuclear reaction materials, energy transport materials have very high demands.
Space facing the reality of a nuclear reactor cooling cooling problems. To prevent problems with the reactor, "Washington" aircraft carrier to take four heavy protective measures for the radiation enclosed in the warship. These four measures are: the fuel itself, fuel storage pressure vessel, reactor shell and the hull. US Navy fuel all metal fuel, designed to take the impact resistance of the war, does not release fission product can withstand more than 50 times the gravity of the impact load; product of nuclear fission reactor fuel will never enter loop cooling water. The third layer of protection is specially designed and manufactured the reactor shell. The fourth layer is a very strong anti-impact combat ship, the reactor is arranged in the center of the ship, very safe. Engage in a reactor can only be loaded up to the aircraft, so as to drive the motor, and then drive the propeller. That is the core advantage of the heat generated by the heated gas flow, high temperature high pressure gas discharge backward, thereby generating thrust.
.
After installation AMPS1000 type nuclear power plant, a nuclear fuel assembly: He is a core member of the nuclear fuel chain reaction. Usually made into uranium dioxide, of which only a few percent uranium-235, and most of it is not directly involved in the nuclear fission of uranium 238. The uranium dioxide sintered into cylindrical pieces, into a stainless steel or a zirconium alloy do metal tubes called fuel rods or the original, then the number of fuel rods loaded metal cylinder in an orderly composition of the fuel assembly, and finally put a lot of vertical distribution of fuel assemblies in the reactor.
Nuclear reactor pressure vessel is a housing for containing nuclear fuel and reactor internals, for producing high-quality high-strength steel is made to withstand the pressure of dozens MPa. Import and export of the coolant in the pressure vessel.
The top of the pressure vessel closure, and can be used to accommodate the fixed control rod drive mechanism, pressure vessel head has a semi-circular, flat-topped.
Roof bolt: used to connect the locking pressure vessel head, so that the cylinder to form a completely sealed container.
Neutron Source: Plug in nuclear reactors can provide sufficient neutron, nuclear fuel ignition, to start to enhance the role of nuclear reactors and nuclear power. Neutron source generally composed of radium, polonium, beryllium, antimony production. Neutron source and neutron fission reactors are fast neutron, can not cause fission of uranium 235, in order to slow down, we need to moderator ---- full of pure water in a nuclear reactor. Aircraft carriers, submarines use nuclear reactor control has proven more successful.
Rod: has a strong ability to absorb neutrons, driven by the control rod drive mechanism, can move up and down in a nuclear reactor control rods within the nuclear fuel used to start, shut down the nuclear reactor, and maintain, regulate reactor power. Hafnium control rods in general, silver, indium, cadmium and other metals production.
Control rod drive mechanism: He is the executive body of nuclear reactors operating system and security protection systems, in strict accordance with requirements of the system or its operator control rod drives do move up and down in a nuclear reactor, nuclear reactor for power control. In a crisis situation, you also can quickly control rods fully inserted into the reactor in order to achieve the purpose of the emergency shutdown
Upper and lower support plate: used to secure the fuel assembly. High temperature and pressure inside the reactor is filled with pure water (so called pressurized water reactors), on the one hand he was passing through a nuclear reactor core, cooling the nuclear fuel, to act as a coolant, on the other hand it accumulates in the pressure vessel in play moderated neutrons role, acting as moderator.
Water quality monitoring sampling system:
Adding chemical system: under normal circumstances, for adding hydrazine, hydrogen, pH control agents to the primary coolant system, the main purpose is to remove and reduce coolant oxygen, high oxygen water suppression equipment wall corrosion (usually at a high temperature oxygen with hydrogen, especially at low temperatures during startup of a nuclear reactor with added hydrazine oxygen); when the nuclear reactor control rods stuck for some reason can not shutdown time by the the system can inject the nuclear reactor neutron absorber (such as boric acid solution), emergency shutdown, in order to ensure the safety of nuclear submarines.
Water system: a loop inside the water will be reduced at work, such as water sampling and analysis, equipment leaks, because the shutdown process cooling water and reduction of thermal expansion and contraction.
Equipment cooling water system:
Pressure safety systems: pressure reactor primary coolant system may change rapidly for some reason, the need for effective control. And in severe burn nuclear fuel rods, resulting in a core melt accident, it is necessary to promptly increase the pressure. Turn the regulator measures the electric, heating and cooling water. If necessary, also temporary startup booster pump.
Residual Heat Removal System: reactor scram may be due to an accident, such as when the primary coolant system of the steam generator heat exchanger tube is damaged, it must be urgently closed reactors.
Safety Injection System: The main components of this system is the high-pressure injection pump.
Radioactive waste treatment systems:
Decontamination Systems: for the removal of radioactive deposits equipment, valves, pipes and accessories, and other surfaces.
Europe, the United States and Russia and other countries related to aircraft carriers, submarines, icebreakers, nuclear-powered research aircraft, there are lots of achievements use of nuclear energy, it is worth analysis. However, nuclear reactor technology, rocket ships and the former are very different, therefore, requires special attention and innovative research. Must adopt a new new design techniques, otherwise, fall into the stereotype, it will avail, nothing even cause harm Aerospace.
[ "2" spacecraft structure]
[ "3"] radiation technology is the use of deep-sea sedimentation fabric fabrics deepwater technology development precipitated silver metal fibers or fiber lint and other materials and micronaire value between 4.1 to 4.3 fibers made from blends. For radiation protection field, it greatly enhances the effects of radiation and service life of clothing. Radiation resistant fiber) radiation resistant fiber - fiber polyimide polyimide fibers
60 years the United States has successfully developed polyimide fibers, it has highlighted the high temperature, radiation-resistant, fire-retardant properties.
[ "4" cosmic radiation resistant clothing design multifunctional anti-aging, wear underwear] ① comfort layer: astronauts can not wash clothes in a long flight, a lot of sebum, perspiration, etc. will contaminate underwear, so use soft, absorbent and breathable cotton knitwear making.
② warm layer: at ambient temperature range is not the case, warm layer to maintain a comfortable temperature environment. Choose warm and good thermal resistance large, soft, lightweight material, such as synthetic fibers, flakes, wool and silk and so on.
③ ventilation and cooling clothes clothes
Spacesuit
In astronaut body heat is too high, water-cooled ventilation clothing and clothing to a different way of heat. If the body heat production more than 350 kcal / h (ventilated clothes can not meet the cooling requirements, then that is cooled by a water-cooled suit. Ventilating clothing and water-cooled multi-use compression clothing, durable, flexible plastic tubing, such as polyvinyl chloride pipe or nylon film.
④ airtight limiting layer:
⑤ insulation: astronaut during extravehicular activities, from hot or cold insulation protection. It multilayer aluminized polyester film or a polyimide film and sandwiched between layers of nonwoven fabric to be made.
⑥ protective cover layer: the outermost layer of the suit is to require fire, heat and anti-space radiation on various factors (micrometeorites, cosmic rays, etc.) on the human body. Most of this layer with aluminized fabric.
New space suits using a special radiation shielding material, double design.
And also supporting spacesuit helmet, gloves, boots and so on.
[ "5" space - Aerospace biomedical technology, space, special use of rescue medication Space mental health care systems in space without damage restful sleep positions - drugs, simple space emergency medical system
]
[ "6" landing control technology, alternate control technology, high-performance multi-purpose landing deceleration device (parachute)]
[ "7" Mars truck, unitary Mars spacecraft solar energy battery super multi-legged (rounds) intelligent robot] multifunction remote sensing instruments on Mars, Mars and more intelligent giant telescope
[8 <> Mars warehouse activities, automatic Mars lander - Automatic start off cabin
]
[ "9" Mars - spacecraft docking control system, return to the system design]
Space flight secondary emergency life - support system
Spacecraft automatic, manual, semi-automatic operation control, remote control switch system
Automatic return spacecraft systems, backup design, the spacecraft automatic control operating system modular blocks of]
[10 lunar tracking control system
Martian dust storms, pollution prevention, anti-corrosion and other special conditions thereof
Electric light aircraft, Mars lander, Mars, living spaces, living spaces Mars, Mars entry capsule, compatible utilization technology, plant cultivation techniques, nutrition space - space soil]
Aerospace technology, space technology a lot, a lot of cutting-edge technology. Human landing on Mars technology bear the brunt. The main merge the human landing on Mars 10 cutting-edge technology, in fact, these 10 cutting-edge technology, covering a wide range, focused, and is the key to key technologies. They actually shows overall trends and technology Aerospace Science and Technology space technology. Human triumph Mars and safe return of 10 cutting-edge technology is bound to innovation. Moreover, in order to explore the human Venus, Jupiter satellites and the solar system, the Milky Way and other future development of science and laid the foundation guarantee. But also for the transformation of human to Mars, the Moon and other planets livable provides strong technical support. Aerospace Science and Technology which is a major support system.
Preparation of oxygen, water, synthesis, temperature, radiation, critical force confrontation. Regardless of the moon or Mars, survive three elements bear the brunt.
Chemical formula: H₂O
Formula: H-O-H (OH bond between two angle 104.5 °).
Molecular Weight: 18.016
Chemical Experiment: water electrolysis. Formula: 2H₂O = energized = 2H₂ ↑ + O₂ ↑ (decomposition)
Molecules: a hydrogen atom, an oxygen atom.
Ionization of water: the presence of pure water ionization equilibrium following: H₂O == == H⁺ + OH⁻ reversible or irreversible H₂O + H₂O = = H₃O⁺ + OH⁻.
NOTE: "H₃O⁺" hydronium ions, for simplicity, often abbreviated as H⁺, more accurate to say the H9O4⁺, the amount of hydrogen ion concentration in pure water material is 10⁻⁷mol / L.
Electrolysis of water:
Water at DC, decomposition to produce hydrogen and oxygen, this method is industrially prepared pure hydrogen and oxygen 2H₂O = 2H₂ ↑ + O₂ ↑.
. Hydration Reaction:
Water with an alkaline active metal oxides, as well as some of the most acidic oxide hydration reaction of unsaturated hydrocarbons.
Na₂O + H₂O = 2NaOH
CaO + H₂O = Ca (OH) ₂
SO₃ + H₂O = H₂SO₄
P₂O₅ + 3H₂O = 2H₃PO₄ molecular structure
CH₂ = CH₂ + H₂O ← → C₂H₅OH
6. The diameter of the order of magnitude of 10 water molecules negative power of ten, the water is generally believed that a diameter of 2 to 3 this organization. water
7. Water ionization:
In the water, almost no water molecules ionized to generate ions.
H₂O ← → H⁺ + OH⁻
Heating potassium chlorate or potassium permanganate preparation of oxygen
Pressurized at low temperatures, the air into a liquid, and then evaporated, since the boiling point of liquid nitrogen is -196 deg.] C, lower than the boiling point of liquid oxygen (-183 ℃), so the liquid nitrogen evaporated from the first air, remaining the main liquid oxygen.
Of course, the development of research in space there is a great difference, even more special preparation harsh environments on Earth and synthetic water and oxygen, over the need for more technological breakthroughs.
The main component of air oxygen and nitrogen. The use of oxygen and nitrogen with