+++ DISCLAIMER +++

Nothing you see here is real, even though the conversion or the presented background story might be based historical facts. BEWARE!

Some Background:

On 23 January 1992, the Lithuanian Minister of Defense signed an order establishing the staff for the Aviation Base of the Aviation Service. But an actual base in the Šiauliai airport territory (Barysiai airfield) was not established until March, when according to the ordinance of the Government of Lithuanian Republic, all the infrastructure, buildings, territory and 24 An-2 aircraft were passed from ”Lithuanian Airlines" to the Aviation Service of the Ministry of Defense in January 1992.

Anyway, the Globėjas' airframes sooner or later reached their flying hour limits, and will be phased out towards 2020. As a replacement Lithuania will begin taking delivery of its first batch of ex-Portuguese F-16s in 2016, while the Baltic States are considering in the near future to protect their airspace on their own.

General characteristics:

Crew: 1

Length: 14.5 [126] m (47 ft 7 in)

Wingspan: 7.154 m (23 ft 6 in)

Height: 4 m (13 ft 6 in)

Wing area: 23.0 m² (247.3 ft²)

Empty weight: 5,846 kg (12,880 lb)

Gross weight: 8,825 kg (19,425 lb)

Powerplant:

1× Tumansky R25-300, rated at 40.21 kN (9,040 lbf) thrust dry

and 69.62 kN (15,650 lbf) with afterburner

Performance:

Maximum speed: 2,175 km/h (1,351.48 mph)

Maximum speed: Mach 2.0

Landing speed: 350 km/h (190 kts)

Range: (internal fuel) 1,210 km (751 miles)

Service ceiling: 17,800 m (58,400 ft)

Rate of climb: 225 m/s (44,280 ft/min)

Armament:

1x internal 23 mm GSh-23 cannon

5x hardpoints for a wide range of guided and unguided ordnance of up to 3.310 lb (1.500 kg).

In QRA configuration the Lithuanian MiG-21 typically carry two or four Rafal Python III short

range air-to-air missiles and an 800l drop tank on the centerline pylon.

Against ground targets, unguided bombs of up to 1.100 lb (500kg) caliber or unguided rockets

can be carried; alternatively, a Rafael LITENING laser designation pod and three

Griffin Mk. 82 LGBs or a single Mk. 84 LGB can be carried, or optically guided weapons like up

to four AGM-65 Maverick or a single GBU-8.

The kit and its assembly:

This kit is the entry for the 2016 "One Week Group Build" at whatifmodelers.com, which ran from 29th of April until 8th May (so, actually nine days...). I had this project earmarked for the recent "Cold War" GB, but it fell outside of the build's time horizon. But despite the dubious kit as basis, I tackled the build since I had anything else already at hand.

The basis is the MiG-21-93 demonstrator kit from Ukrainian manufacturer Condor, one of the many reincarnations of the venerable KP MiG-21bis, but with some updates. You get, for instance, engraved, very fine panel lines, some typical details were added like the wraparound windscreen (wrong shape, though) and the radar warning fairing on the fin as well as an extra sprue with modern Russian ordnance – apparently from some other kit!

On the downside, there's overall mediocre fit due to the molds' age, some dubious details (anything appears softened or blurred…) or the simple lack thereof (e. g. there’s no ventral gun fairing at all). But there’s nothing that could not be mended, and after all this is just a whiffy version.

Since there was only one week time to build the thing and make beauty pics, the whole project remained close to OOB status, even though a lot of detail changes or additions were made in order to convert the Russian MiG-21-93 into an earlier but similar Israeli MiG-21 2000 derivative.

These mods include:

- A Martin Baker ejection seat, with wire trigger handles

- HUD made from clear styrene

- Lowered flaps

- An added jet pipe/interior for the otherwise bleak exhaust (parts from a Kangnam Yak-38)

- Hydraulic pipes on the landing gear, made from very thin wire

- Some more/different blade antennae

- Measuring vanes on the pitot boom

- Different GSh-23 gun fairing, from an Academy MiG-23

- Thinner blast deflector plates under the anti-surge doors

- A pair of Python III AAMs, plus respective launch rails

- Different centerline drop tank, from an F-5E

- Scratched chaff/flare dispensers under the rear fuselage (as carried by the MiG-21 2000 demonstrator)

Building the model went straightforward, but it took some putty work to fill some seams, dents and holes all around the kit. Biggest issue was a hole in front of the cockpit screen, where simply not enough styrene had been injected into the mould!

Painting and markings:

The Lithuanian Air Force as operator for this build was chosen because it would not only fit into the real world timeline (even though I doubt that there would have been any budget for this aircraft at that time, even if MiG-21s had not been upgraded at all...) and because the potential livery would be very simple: contemporary L-39 trainers, C-27L Spartan as well as some L-410 and Mi-8 transporters carry a uniform, dull grey livery. Why not apply it on an air superiority fighter, too?

Finding an appropriate tone was not easy, though. Some sources claim the grey tone to be FS 36306, others refer to FS 36270 or "close to Blue/Grey FS35237", but IMHO none of the cited Federal Standard tones works well. Real world Lithuanian aircraft appear pretty dark and dull, and the color also features a greenish, slate grey hue - it's a unique color indeed.

After some trials (and also wishing to avoid mixing) I settled for Humbrol 111 (German Field Grey, a.k.a. Uniform Grey) as basic tone. It's a rather dark choice, but I wanted some good contrast to the national markings. A full wraparound livery appeared a little too dark and boring, so I added light blue wing undersurfaces (Humbrol 115). The kit received a light black in wash and some panel shading, primarily in order to add some life to the otherwise uniform surface.

Details were painted according to real world MiG-21 pics: the cockpit became classic teal with light grey instrument panels, plus OOB decals for the dashboard and side consoles. The landing gear struts were painted in a light, metallic grey (Humbrol 127 + 56) while the wells were painted in an odd primer color, a mix of Aluminum, Sand and Olive Drab. Parts of the covers were painted with Humbrol 144 (Blue Grey), seen on a modernized real world MiG-21. The wheel discs became bright green.

IAI's MiG-21 2000 demonstrator from 1993 had a black radome (as well as later Romanian LanceR Cs), so I adapted this detail for my build. Other typical di-electric fairings on a MiG-21's hull were painted in slightly darker camouflage colors, while the fin's leading edge became dark grey.

The blast deflector plates received yellow and black warning stripes, and some potentially dangerous parts for the ground crews like the pointed anti-flutter booms were painted red. The Python IIIs were simply painted all-white, mounted on grey launch rails - a harsh contrast to the dull rest of the aircraft.

Main markings come from a Blue Rider Publishing aftermarket sheet for modern Lithuanian aircraft. This set also includes the small Air Force crests, which I put on the nose, as well as the typical, blue tactical codes.

The stencils come from the scrap box, the small Lithuanian flag stripes on the tail rudder were created from single decal stripes, a personal addition inspired by Lithuanian C-27J transporters. They add some more color to the otherwise murky Baltic MiG fighter.

The silver ring around the air intake as well as the stripes at the flaps and the rudder were created with simple decal stripes instead of paint.

Finally, after I added some graphite soot around the jet exhaust and some panle lines with a pencil (e .g. the blow-in doors and airbrake outlines), the kit was sealed with hardly thinned Revell matt acrylic varnish, trying to create a really dull finish.

A tough build, despite being mostly OOB, but the details took their toll. This Baltic MiG does not look flashy, but, with IAI's real world MiG-21 2000 as well as the LanceR conversion for Romania in the Nineties, this one is pretty plausible. And with the simple paint scheme, the MiG-21 looks even pretty chic!

A fish-eye series at the botanical garden green houses, Parc de la Tete d'Or, Lyon, France, on February 3, 2023.

I own this Minolta lens MD 1:2.8 f=16mm Fish-Eye since April 2014 (flic.kr/s/aHsjYBkn5J) but I only used adapted to one of my two Sony A7 bodies and I never did a film with it. The 180° view-angle is obtained in the image diagonal. The lens includes a build-in filter rotatory system with a yellow "Y52", a red "R60" and a blue "B12" filter on addition to the normal non-filtered position.

For this film, the lens is mounted on one of my two Minolta X-700, the "China" version (assembled in China 1993-1999). The camera was also equipped with its motor drive MD1 and the Minolta multi-function back. The X-700 was loaded with a B&W super-panchromatic Rollei Retro 400S (Agfa Aviphot 400) 36-exposure film.

The Agfa Aviphot film used for aerial photography is specially sensitized in the red, up to 780nm in the near IR instead of the regular 650-680 nm limit of a normal panchromatic film. The film provides usually high-definition and high-contrast negative views. What is more, the Agfa Aviphot is coated on a thin and flat polyester base without any base color increasing the contrast as well. However to prevent the halation possible the Agfa Aviphot is coated on the backside with a black and blue anti-halation pigment to inhibit the light back diffusion (halation). The printing from a data back was tested here to print the hour on the two-first frames setting the intensity to the medium value available (3 diamonds) on the Minolta multi-function back (there are 6 levels of intensity available).

The red R60 filter was used for most of the views. Exposures were determined using the TTL system of the Minolta X-700 in the manual mode, privileging the shadow areas.

February 3, 2023

Parc de la Tête d'Or

69006 Lyon

France

After exposures the film was processed using Adox Adonal (strictly equivalent to Agfa Rodinal "R09") developer at dilution 1+50, 20°C for 22min. The film was then digitalized using a Sony A7 body fitted to a Minolta Slide Duplicator installed on a Minolta Auto Bellows III with a lens Minolta Bellow Macro Rokkor 50mm f/3.5. The RAW files obtained were then processed in LR and finally edited to the final jpeg pictures.

All views of the film are presented in the dedicated album either in the printed framed versions and unframed full-size jpeg accompanied by some documentary smartphone Vivio Y76 color pictures.

WWII Military Vehicles...Compressor Truck, this particular vehicle was salvaged from Belgium where it was probably used in the Battle of the Bulge. I’m told it’s the only, completely operational vehicle of this type in existence. It has functioning chain saw, large drill, Jack hammer and operational machine gun and siren among other goodies. A truly multi functioning work platform.

This clone of the English Sinclair ZX Spectrum by Clive Sinclair was my first computer. By the size of a book, it had a Z80 processor, 16k of RAM, no hard disk, used a B&W 14" TV as monitor, a cassette recorder as data storage unit that could eventually work and an external font. The case is made of molded ABS plastic and the multifunction keys are probably made of rubbery polyurethane. Made in Brazil by Microdigital, 1984.

It measures 23 x 14,5 x 4 cm.

To learn more about personal computer design in Britain in early 1980s, try this:

blog.modernmechanix.com/2008/05/19/microcomputing-british...

+++ DISCLAIMER +++

Nothing you see here is real, even though the model, the conversion or the presented background story might be based on historical facts. BEWARE!

Some background:

Operated by the Islamic Revolutionary Guards Corps, Iran's small Bell AH-1J fleet has seen a fair share of indigenous modernization in recent years. In 1971, Iran purchased 202 examples of an improved AH-1J, named "AH-1J International", from the United States. This improved Cobra featured an uprated P&WC T400-WV-402 engine and a stronger drivetrain, so that it would have a better performance under “hot & high” conditions. Recoil damping gear was fitted to the 20 mm M197 gun turret, and the gunner was given a stabilized sight and a stabilized seat, too. Of the AH-1Js delivered to the Shah's Imperial Iranian Army Aviation, 62 were TOW-capable.

Iranian AH-1Js participated in the Iran–Iraq War—which saw the most intensive use of helicopters in any conventional war. Iranian AH-1Js (particularly the TOW-capable ones) were "exceptionally effective" in anti-armor warfare, inflicting heavy losses on Iraqi armored and vehicle formations. In operations over the barren terrain in Khuzestan and later in southern Iraq, beside the standard tactics, Iranian pilots developed special, effective tactics, often in the same manner as the Soviets did with their Mi-24s. Due to the post-Revolution weapons sanctions, Iranians had to make do with what was at hand: lacking other guided ordnance they equipped the AH-1Js with AGM-65 Maverick missiles and used them with some success in several operations. About half of the AH-1Js were lost during the conflict to combat, accidents, and simple wear and tear –the rest of the fleet was kept operational and busy during the following years.

The most notable use of the AH-1Js in combat by the IRGC took place in spring and summer 2008 when two AH-1Js stationed in Zahedan were extensively used in close-air-support missions during a counter-terrorism operation by IRGC Ground Forces against the Jondollah group (later to be rebranded as Jaish ul-Adl after being listed as a terrorist organization by the US State Department). After the arrest and execution of its leader, Abdolmalek Reigi by Iran, the group stopped its activities in 2009. It resumed again a few years later resulting in the launch of new anti-terror operations involving the AH-1Js in 2013, which continued periodically until 2020.

General characteristics:

Crew: 2

Length: 53 ft 5 in (16.28 m) with both rotors turning

45 ft 9 in (14 m) for fuselage only

Width: 10 ft 9 in (3.28 m) for stub wings only

Height: 13 ft 5 in (4.09 m)

Main rotor diameter: 43 ft 11 in (13.39 m)

Main rotor area: 1,514.97 sq ft (140.745 m²)

Empty weight: 2,802 kg (6,177 lb)

Max takeoff weight: 4,530 kg (9,987 lb)

Powerplant:

2× P&W Canada T400-CP-400 (PT6T-3 Twin-Pac) turboshaft engines, coupled to produce 1,530 shp

(1,140 kW; de-rated from 1,800 shp (1,342 kW) for drivetrain limitations)

Performance:

Maximum speed: 236 km/h (147 mph, 127 kn)

Range: 600 km (370 mi, 320 nmi)

Service ceiling: 10,500 ft (3,200 m)

Rate of climb: 1,090 ft/min (5.5 m/s)

Armament:

1× 20 mm (0.787 in) M197 3-barreled Gatling cannon in M97 chin turret with 750 rounds

4× hardpoints under the sub wings for 2.75” (70 mm) Mk 40 or Hydra 70 rockets in 7 or 19 rounds

pods; up to 16 5” (127 mm) Zuni rockets in 4-round LAU-10D/A launchers, up to eight Toophan

ATGM in a dual or quad launcher on each wing, AIM-9 Sidewinder or Misagh-2 anti-aircraft

missiles (1 mounted on each hardpoint)

The kit and its assembly:

This is the counterpart to another modified Fujimi AH-1 model, actually a kit bashing of the AH-1S and the AH-1J model to produce something that comes close to the real IAMI HESA-2091 helicopter, an upgraded/re-built AH-1J International of the Iranian Army Air Force. The “leftover” parts were used to create an (Indonesian) AH-1G – even though the HESA-2091 was the “core project”.

To create this Iranian variant, the AH-1J was taken as the basis and the nose as well as the flat-window canopy from the AH-1S were transplanted. While the nose with the TOW sensor turret was just an optional part that fits naturally on the fuselage (even though not without some PSR), the clear parts was more challenging, because the flat canopy is shorter than the original. In this case I had to fill some triangular gaps between the hood and the engine section, and this was done with 1.5 mm styrene sheet wedges and some more PSR to blend the parts that were not meant to be combined into each other.

The cockpit was taken OOB, together with the pilot figures that come with the kit. I also retained the original all-metal main rotor because the Iranian Cobras AFAIK were never upgraded with composite material blades?

To set the HESA-2091 further apart from the original AH-1J I changed the sensor turret in the nose and scratched a ball-shaped fairing that resembles the indigenous RU-290 thermal camera – it’s actually the ball joint from a classic clear Matchbox kit display, with a base scratched from 0.5mm styrene sheet. The “ball” turned out to be a bit too large, but the overall look is O.K., since I wanted a non-TOW AH-1J. For a “different-than-a-stock-AH-1J” look A small radome for a missile guidance antenna was added to the nose above the sensor turret, too. Another personal addition are the small end plates on the stabilizers – inspired by similar installations on Bell’s early twin-engine AH-1s, even though these later disappeared and were technically replaced by a ventral fin extension and a longer fuselage; the Iranian AH-1Js retained the short, original fuselage of the single-engine Cobra variants, though. The end plates were cut from leftover rotor blades from the scrap box, IIRC they belong to a Matchbox Dauphin 2.

Being part of the historical Zahedan fire support team I gave the Cobra an armament consisting of a nineteen round 70mm Hydra unguided missile pods (OOB), a pair of AGM-65 Maverick missiles (an ordnance actually deployed by Iranian Cobras), together with their respective launch rails, and I added launch tubes for indigenous Misagh-2 anti-aircraft missiles (which are actually MANPADS) to the stub wings’ tips as a self-defense measure. These were scratched from 2mm styrene rods.

Painting and markings:

Finding a suitable paint scheme was not easy. A conservative choice would have been an early mid-stone/earth scheme or a tri-color scheme consisting of sand, earth and dark green. However, while doing WWW research I came across some more exotic and contemporary specimen, carrying a kind of leopard-esque mottle scheme or even a “high resolution” fractal/digital cammo consisting of three shades of beige/brown/grey – even though I am not certain if the latter was a “real” camouflage for operational helicopters or just a “show and shine” propaganda livery?

Re-creating the latter from scratch would have been prohibitively complex, because the pixelized mottles were really fine, maybe just 2” wide each in real life. But I used this scheme as an inspiration for a simplified variant, also kept in three shades of brown, even though the result was a kind of compromise due to the limited material options to create it.

The base became an overall coat with Tamiya XF-57 (Buff), plus very light grey (RAL 7035; Humbrol 196) undersides. A light black ink washing was applied, and panels were post-shaded to create a more vivid surface.

Then came the pixelized mottles in two contrast colors: first came a layer in RAL 1015 (Hellelfenbein/Light Ivory) and then a second in RAL 8011 (Nussbraun/Nut Brown) in a 1:1 ratio, slightly overlapping and letting the Buff base shine through. These mottles were not painted but rather created with square bits from generic decal stripe material in various widths from TL Modellbau. While not as sophisticated as the original camouflage, effect and look are quite similar, and add to the unique look of this HESA-2091(-ish) model. And even though I was sceptical, esp. because of the reddish Nussbraun, the blurring effect of the scheme is surprisingly good – esp. when you put the model in front of a dry mountain background! I’ll keep the concept in the back of my head for further what-if models. All those single pixels were a lot of work, but the result looks really good.

Another detail from many real late Iranian Cobras was taken over, too: a black tail rotor drive shaft cover that extends up onto the fin’s leading edge – probably a measure to hide exhaust soot stains on the tail boom? A black anti-glare panel was added in front of the windscreen, too, and the rotor blades became medium grey (Humbrol 165, Medium Sea Grey) except for the main rotor blades’ undersides, which became black. The cockpit interior was uniformly painted in a very dark grey (Revell 06, Anthracite) and the pilots received khaki jumpsuits and modern grey and olive drab “bone domes”.

The decals were puzzled together from various sources. The Iranian roundels came from a Begemot MiG-29 sheet, registration numbers and fin flashes from an Iranian F-5. The IAAF abbreviation was created with single black 4 mm letters.

Graphite was used to weather the model, esp. the area on top of the tail boom, and the model was finally sealed with matt acrylic varnish overall.

An exotic model – the Iranian home-brew HESA-2091 looks familiar, but it’s a unique combination of classic Cobra elements. More spectacular is the pixelated paint scheme, and the attempt to generate it with the help of square decal bits worked (and looks) better than expected! This might also work well in grey as a winter camouflage? Hmmm….

- HTC Incredible 2

- Women's Fossil "Emory" Multifunction Leather Wallet

- Rudsak "Lola" clutch purse

- Duracell Powermat Portable Battery

- House key + suitcase key + biner + dollar store bracelet

- Burt's Bees tinted lip balm ("Caramel Daisy")

- Body Shop blotting tissues

Hier nur einige der vielen Tasten auf dem Mulifunktionslenkrad, mit denen die Kartenansicht des Navigationssystems angepasst werden kann, oder durch das Hauptmenü gescrollt werden kann.

Here are just a few of the many buttons on the multifunction steering wheel that can be used to adjust the map view of the navigation system or to scroll through the main menu.

My beloved Nikon F4. Still in use after so many years. With the MB-23 power pack and the MF-23 Multifunction back attached she is "El Monstro" Standard multi-metering finder DP-20 attached.

Sorry for the Sigma lens...

© All Rights Reserved - you may not use this image in any form without my prior permission.

OLYMPUS DIGITAL CAMERA

The MCDU (Multifunction Control Display Unit) is one of the main user interfaces and an integral part of the FMGCS (Flight Management Guidance Control System) of the A320 family

Of the thousands of American aircraft shot down during the Vietnam War, well over half were lost to antiaircraft fire—most in the close air support role for troops in contact on the ground. In the latter half of the war, when the North Vietnamese Army switched to a more conventional style of attack using tanks, both the US Air Force and the US Army found that they lacked a decent antitank aircraft. This deeply concerned both services: if a conventional war should erupt in Central Europe with the Warsaw Pact, Soviet forces would employ mass tank attacks, which the Army would be hard-pressed to stop alone, and might require use of tactical nuclear weapons.

With these factors in mind, the USAF commissioned the A-X study in 1967, issuing a requirement for a dedicated ground attack fighter with special emphasis on antitank weaponry and survivability—A-X study groups of the responding companies were asked to review specialized World War II-era antitank aircraft such as the Ilyushin Il-2 Shturmovik and the Henschel Hs 129, both of which employed heavy cannon armament and armor protection. World War II’s top aerial tank killer, German pilot Hans-Ulrich Rudel, was brought in as a consultant.

By 1972, the USAF had narrowed down its prospects to the Northrop A-9 and Fairchild-Republic A-10, both of which had first flown in May 1972. Based on its maneuverability, survivability, and Republic’s reputation for building hardy aircraft (including the P-47 Thunderbolt and F-105 Thunderchief), the A-10 was chosen as the A-X in 1973 and went into full production as the A-10A Thunderbolt II in 1976.

When it entered service a year later, it immediately turned heads. Unlike the sleek “teen fighters” such as the F-15 and F-16 entering USAF service at the same time, the A-10 seemed almost dumpy in comparison, and its slow speed and hideous appearance quickly earned it the moniker of “Warthog,” a name that stuck far more than Thunderbolt II. However, the throwback straight wing and airliner engines hid a superb combat aircraft. The A-10 was built literally around a titanic GAU-8 Avenger 30mm gatling cannon, the largest such weapon ever built in the West, capable of firing 4000 rounds a minute—with each soda-bottle sized round made of hyperdense depleted uranium capable of slicing through tank armor. Firing the GAU-8 put such forces on the aircraft that it would immediately lower the speed, to the point that pilots reported being thrown forward in their straps, while the gun gases were capable of causing compressor stalls. If that was not enough, the A-10 was provided with a dozen underwing hardpoints capable of carrying every bomb in the USAF’s inventory, along with TV-guided AGM-65 Maverick missiles. Laser guided bombs could also be carried thanks to a Pave Penny designator attached to the right side of the fuselage.

Survivability was paramount in the A-10’s design. The cockpit was surrounded by a titanium “bathtub” impervious to cannon rounds below 30 millimeter size—an important consideration given the Soviet Union’s employment of the lethal ZSU-23 self-propelled antiaircraft gun that had wreaked havoc among Israeli forces in the 1973 Yom Kippur War. The high-bypass turbofan engines were mounted high on the rear fuselage, apart from each other to better resist damage, while their placement behind the wing and forward of the twin tails both masked them from ground fire and reduced their infrared footprint. The fuel tanks are protected by foam and two small tanks are designed to keep a small reserve in the unlikely event all four interior fuel tanks were penetrated. Redundancy and simplicity are meant to keep the aircraft aloft even after heavy damage, while the semi-recessed wheels reduce the damage caused by a belly landing. The A-10 was also designed to operate from austere forward bases and be capable of quick turnarounds in combat. Finally, though the straight wing seemed a throwback to World War II, it had been proven by the A-1 Skyraider in Vietnam that a straight wing, combined with comparatively slow speed, made an aircraft very maneuverable. Pilots reported the A-10 to be easy to fly, though difficult on long missions because of the lack of an autopilot.

A-10s were quickly deployed to Central Europe, waiting for the mass Soviet tank attack that would never come. In bad weather common to Europe, it was found that if the A-10 had a weakness, it was its lack of all-weather capability, and given that the aircraft was meant to operate from very low level, this could be a real problem in wartime. There were also concerns that, even with the A-10’s durability, it was still too vulnerable to ground fire and surface-to-air missiles. With the fall of the Soviet Union and the Warsaw Pact in 1989, the USAF saw no purpose for the A-10 and prepared to retire them from service in favor of more F-16s.

The First Gulf War saved the Warthog. Employed in the desert, where weather was less of a problem, the A-10 proved to be devastating to Iraqi tank crews, breaking up attacks on Coalition forces, and inflicting catastrophic damage on the so-called “Highway of Death” north of Kuwait City. Four A-10s were lost during the conflict, none to ground fire. So valuable was the A-10’s long loiter time and massive firepower that US Army commanders informed the USAF that, if the latter service got rid of the A-10, the Army would buy them back. The A-10 would see extensive service in Bosnia, Kosovo, Afghanistan, and Iraq (again). Each time, Warthog units posted mission capable rates exceeding 85 percent. The type’s durability was also proven, with one aircraft coming back during the First Gulf War missing most of its left wing and one engine, and another in the Second Gulf War after complete loss of hydraulics.

With the realization that the only replacement for the A-10 would be another A-10, the USAF in 2008 began upgrading the A-10As in service to A-10Cs, with new wings, autopilot, GPS, “glass” multifunction cockpit, and true all-weather capability in the form of LANTIRN navigation pods. A number of A-10s are used in the forward air control role, with additional radios, as OA-10As, but functionally do not differ from regular A-10s. The type is now intended to remain in service until 2025.

78-0625's career may have been spent entirely in the Air National Guard; it was part of the 103rd Tactical Fighter Group (Connecticut ANG) at Windsor Locks in the 1980s, and was transferred to the 124th Fighter Wing (Idaho ANG) at Boise possibly around 2005. It may have seen combat over Bosnia in the mid-1990s and over Iraq. 78-0625 was upgraded to an A-10C in 2007.

The Idaho ANG has never had particularly spectacular markings on its aircraft, dating back to their days in various F-4 types; rather than the gaudy tail art of some other units, the 124th contents itself with a simple "Idaho" stripe on the tail in blue, with a few mountains. The component 190th FS' "Skull Banger" squadron marking is carried on the engines. Idaho has taken to naming its aircraft, and 78-0625 carries the name "Pride of Coeur d'Alene" on the nose. Interestingly, along with travel pods for the pilot and ground crew, this aircraft also carries a LANTIRN pod on the right wing. I got this shot on a pretty much perfect airshow day at Wings Over the Falls in Great Falls, Montana.

A fish-eye series at the botanical garden green houses, Parc de la Tete d'Or, Lyon, France, on February 3, 2023.

I own this Minolta lens MD 1:2.8 f=16mm Fish-Eye since April 2014 (flic.kr/s/aHsjYBkn5J) but I only used adapted to one of my two Sony A7 bodies and I never did a film with it. The 180° view-angle is obtained in the image diagonal. The lens includes a build-in filter rotatory system with a yellow "Y52", a red "R60" and a blue "B12" filter on addition to the normal non-filtered position.

For this film, the lens is mounted on one of my two Minolta X-700, the "China" version (assembled in China 1993-1999). The camera was also equipped with its motor drive MD1 and the Minolta multi-function back. The X-700 was loaded with a B&W super-panchromatic Rollei Retro 400S (Agfa Aviphot 400) 36-exposure film.

The Agfa Aviphot film used for aerial photography is specially sensitized in the red, up to 780nm in the near IR instead of the regular 650-680 nm limit of a normal panchromatic film. The film provides usually high-definition and high-contrast negative views. What is more, the Agfa Aviphot is coated on a thin and flat polyester base without any base color increasing the contrast as well. However to prevent the halation possible the Agfa Aviphot is coated on the backside with a black and blue anti-halation pigment to inhibit the light back diffusion (halation). The printing from a data back was tested here to print the hour on the two-first frames setting the intensity to the medium value available (3 diamonds) on the Minolta multi-function back (there are 6 levels of intensity available).

The red R60 filter was used for most of the views. Exposures were determined using the TTL system of the Minolta X-700 in the manual mode, privileging the shadow areas.

Serre aride Mexique Madagascar, February 3, 2023

Jardin Botanique de Lyon

Parc de la Tête d'Or

69006 Lyon

France

After exposures the film was processed using Adox Adonal (strictly equivalent to Agfa Rodinal "R09") developer at dilution 1+50, 20°C for 22min. The film was then digitalized using a Sony A7 body fitted to a Minolta Slide Duplicator installed on a Minolta Auto Bellows III with a lens Minolta Bellow Macro Rokkor 50mm f/3.5. The RAW files obtained were then processed in LR and finally edited to the final jpeg pictures.

All views of the film are presented in the dedicated album either in the printed framed versions and unframed full-size jpeg accompanied by some documentary smartphone Vivio Y76 color pictures.

Details: www.spera.de/products/015970

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The Gotthard project used pumpable emulsions for blasting. These materials do not become explosive until they have been loaded into the blasting holes. Here, workers prepare a section of the Faido multifunction station for blasting.

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+++ DISCLAIMER +++

Nothing you see here is real, even though the conversion or the presented background story might be based historical facts. BEWARE!

Some Background:

On 23 January 1992, the Lithuanian Minister of Defense signed an order establishing the staff for the Aviation Base of the Aviation Service. But an actual base in the Šiauliai airport territory (Barysiai airfield) was not established until March, when according to the ordinance of the Government of Lithuanian Republic, all the infrastructure, buildings, territory and 24 An-2 aircraft were passed from ”Lithuanian Airlines" to the Aviation Service of the Ministry of Defense in January 1992.

Anyway, the Globėjas' airframes sooner or later reached their flying hour limits, and will be phased out towards 2020. As a replacement Lithuania will begin taking delivery of its first batch of ex-Portuguese F-16s in 2016, while the Baltic States are considering in the near future to protect their airspace on their own.

General characteristics:

Crew: 1

Length: 14.5 [126] m (47 ft 7 in)

Wingspan: 7.154 m (23 ft 6 in)

Height: 4 m (13 ft 6 in)

Wing area: 23.0 m² (247.3 ft²)

Empty weight: 5,846 kg (12,880 lb)

Gross weight: 8,825 kg (19,425 lb)

Powerplant:

1× Tumansky R25-300, rated at 40.21 kN (9,040 lbf) thrust dry

and 69.62 kN (15,650 lbf) with afterburner

Performance:

Maximum speed: 2,175 km/h (1,351.48 mph)

Maximum speed: Mach 2.0

Landing speed: 350 km/h (190 kts)

Range: (internal fuel) 1,210 km (751 miles)

Service ceiling: 17,800 m (58,400 ft)

Rate of climb: 225 m/s (44,280 ft/min)

Armament:

1x internal 23 mm GSh-23 cannon

5x hardpoints for a wide range of guided and unguided ordnance of up to 3.310 lb (1.500 kg).

In QRA configuration the Lithuanian MiG-21 typically carry two or four Rafal Python III short

range air-to-air missiles and an 800l drop tank on the centerline pylon.

Against ground targets, unguided bombs of up to 1.100 lb (500kg) caliber or unguided rockets

can be carried; alternatively, a Rafael LITENING laser designation pod and three

Griffin Mk. 82 LGBs or a single Mk. 84 LGB can be carried, or optically guided weapons like up

to four AGM-65 Maverick or a single GBU-8.

The kit and its assembly:

This kit is the entry for the 2016 "One Week Group Build" at whatifmodelers.com, which ran from 29th of April until 8th May (so, actually nine days...). I had this project earmarked for the recent "Cold War" GB, but it fell outside of the build's time horizon. But despite the dubious kit as basis, I tackled the build since I had anything else already at hand.

The basis is the MiG-21-93 demonstrator kit from Ukrainian manufacturer Condor, one of the many reincarnations of the venerable KP MiG-21bis, but with some updates. You get, for instance, engraved, very fine panel lines, some typical details were added like the wraparound windscreen (wrong shape, though) and the radar warning fairing on the fin as well as an extra sprue with modern Russian ordnance – apparently from some other kit!

On the downside, there's overall mediocre fit due to the molds' age, some dubious details (anything appears softened or blurred…) or the simple lack thereof (e. g. there’s no ventral gun fairing at all). But there’s nothing that could not be mended, and after all this is just a whiffy version.

Since there was only one week time to build the thing and make beauty pics, the whole project remained close to OOB status, even though a lot of detail changes or additions were made in order to convert the Russian MiG-21-93 into an earlier but similar Israeli MiG-21 2000 derivative.

These mods include:

- A Martin Baker ejection seat, with wire trigger handles

- HUD made from clear styrene

- Lowered flaps

- An added jet pipe/interior for the otherwise bleak exhaust (parts from a Kangnam Yak-38)

- Hydraulic pipes on the landing gear, made from very thin wire

- Some more/different blade antennae

- Measuring vanes on the pitot boom

- Different GSh-23 gun fairing, from an Academy MiG-23

- Thinner blast deflector plates under the anti-surge doors

- A pair of Python III AAMs, plus respective launch rails

- Different centerline drop tank, from an F-5E

- Scratched chaff/flare dispensers under the rear fuselage (as carried by the MiG-21 2000 demonstrator)

Building the model went straightforward, but it took some putty work to fill some seams, dents and holes all around the kit. Biggest issue was a hole in front of the cockpit screen, where simply not enough styrene had been injected into the mould!

Painting and markings:

The Lithuanian Air Force as operator for this build was chosen because it would not only fit into the real world timeline (even though I doubt that there would have been any budget for this aircraft at that time, even if MiG-21s had not been upgraded at all...) and because the potential livery would be very simple: contemporary L-39 trainers, C-27L Spartan as well as some L-410 and Mi-8 transporters carry a uniform, dull grey livery. Why not apply it on an air superiority fighter, too?

Finding an appropriate tone was not easy, though. Some sources claim the grey tone to be FS 36306, others refer to FS 36270 or "close to Blue/Grey FS35237", but IMHO none of the cited Federal Standard tones works well. Real world Lithuanian aircraft appear pretty dark and dull, and the color also features a greenish, slate grey hue - it's a unique color indeed.

After some trials (and also wishing to avoid mixing) I settled for Humbrol 111 (German Field Grey, a.k.a. Uniform Grey) as basic tone. It's a rather dark choice, but I wanted some good contrast to the national markings. A full wraparound livery appeared a little too dark and boring, so I added light blue wing undersurfaces (Humbrol 115). The kit received a light black in wash and some panel shading, primarily in order to add some life to the otherwise uniform surface.

Details were painted according to real world MiG-21 pics: the cockpit became classic teal with light grey instrument panels, plus OOB decals for the dashboard and side consoles. The landing gear struts were painted in a light, metallic grey (Humbrol 127 + 56) while the wells were painted in an odd primer color, a mix of Aluminum, Sand and Olive Drab. Parts of the covers were painted with Humbrol 144 (Blue Grey), seen on a modernized real world MiG-21. The wheel discs became bright green.

IAI's MiG-21 2000 demonstrator from 1993 had a black radome (as well as later Romanian LanceR Cs), so I adapted this detail for my build. Other typical di-electric fairings on a MiG-21's hull were painted in slightly darker camouflage colors, while the fin's leading edge became dark grey.

The blast deflector plates received yellow and black warning stripes, and some potentially dangerous parts for the ground crews like the pointed anti-flutter booms were painted red. The Python IIIs were simply painted all-white, mounted on grey launch rails - a harsh contrast to the dull rest of the aircraft.

Main markings come from a Blue Rider Publishing aftermarket sheet for modern Lithuanian aircraft. This set also includes the small Air Force crests, which I put on the nose, as well as the typical, blue tactical codes.

The stencils come from the scrap box, the small Lithuanian flag stripes on the tail rudder were created from single decal stripes, a personal addition inspired by Lithuanian C-27J transporters. They add some more color to the otherwise murky Baltic MiG fighter.

The silver ring around the air intake as well as the stripes at the flaps and the rudder were created with simple decal stripes instead of paint.

Finally, after I added some graphite soot around the jet exhaust and some panle lines with a pencil (e .g. the blow-in doors and airbrake outlines), the kit was sealed with hardly thinned Revell matt acrylic varnish, trying to create a really dull finish.

A tough build, despite being mostly OOB, but the details took their toll. This Baltic MiG does not look flashy, but, with IAI's real world MiG-21 2000 as well as the LanceR conversion for Romania in the Nineties, this one is pretty plausible. And with the simple paint scheme, the MiG-21 looks even pretty chic!

These were originally imagined as escape ships. They became too cool for that and now are multifunction exploration ships.

Ilford B&W film HP5+ expired in 2011 but stored 10 years in the fridge.

Pictures were taken using a SLR Minolta X-500 body (1984) with the MultiFunction back set to the dating (MM/DD/YY) auto mode and a standard lens Minolta MD 50 mm f/1.4.

Place de la Croix-Rousse

69004 Lyon

France

The film was exposed for 400 ISO on Dec. 21, 2021 ("12 21 21") and processed using Ilford Ilfosol at the dilution of 1+9 at 20°C for 7min10 (normal recommended time +10%).

The pictures were then digitalized using a Sony A7 body and a Minolta Slide Duplicator with a Minolta Auto Bellows Macro Rokkor 50mm f/3.5.

The international military-technical forum ARMY 2019.

Международный военно-технический форум АРМИЯ 2019.

The KL Sandefjord Anchor Handling Tug Supply (AHTS) vessel is owned by K Line Offshore (Kawasaki Kisen Kaisha). It is a multifunction vessel designed to carry out seabed operations, ploughing / trenching and pre-lay work in ultra-deep waters and harsh environments. With a bollard pull of 390t, it the world’s strongest AHTS vessel constructed to date.

The ship was delivered to K Line on 7 January 2011 after successfully completing sea trials in December 2010. The vessel will begin operating after the installation and testing of the A-frame at Kristiansand harbour in southern Norway.

Design

KL Sandefjord is the first of two AHTS vessels of AH 12 CD design. It is 95m-long and 24m-wide with 9.8m depth to the centre of the main deck. It has a maximum draught of 7.82m and a cargo rail height of 3.10m above the deck.

The deadweight capacity is 4,800t with cargo deck area measuring about 750m². The deck can carry cargo weighing up to 3,200t. The free area on the deck can carry 10t/m² of cargo.

The A-frame is fitted on the deck for subsea construction works. It weighs 250t and has an inside width of 15,500mm between the legs at deck level. The top width is 10,500mm and inside height is 11,100mm. The outreach is 8.5m at the aft and 4.55m forward the A-frame pivot

Construction

The hull was constructed by STX Norway Offshore in Tulcea, Romania. The construction was supervised by Norway-based OSM Group.

The hull was launched in February 2010. It was towed to position alongside the tug Pegasus and then towed to STX Norway Offshore’s Langsten shipyard in Tomrefjord in Alesun County, Norway for final outfitting. Naming ceremony was held in November 2010.

Equipment

The vessel is fitted with ROV hangar and ODIM LARS system for underwater search operations and handling of anchors respectively. An ODIM Anchor Recovery Frame (ARF) is fitted on aft deck to handle Torpedo type anchors. It is flush with the main deck when in stowed position.

The two jib RRM cargo rail cranes are equipped with manipulators for safe operations of the working area on the deck.

Large chain and synthetic fibre rope of different capacities are available on the deck.

Propulsion

KL Sandefjord has a highly efficient power plant designed and built by Finland-based Wärtsilä. It consists of two 16v 32-type main engines and 2,200kW, five diesel generators with alternators connected to the main switchboard.

The engines are connected to shaft lines through reduction gears and controlled pitch propellers (CPP) which can be powered using diesel-electric, diesel-mechanical or hybrid modes. The two main CPPs have four blades that rotate at a speed of 130rpm.

The three thrusters-two tunnel thrusters forward and one tunnel thruster to the aft are fixed with fixed pitch propellers. The thrusters operate at variable speeds, regulated by frequency controlled motors.

Accommodation

The vessel can accommodate 70 people on board. There are 45 cabins of which six single berth cabins are reserved for officers. The rest are 14 single berth and 25 double berth cabins for crew members.

Facilities

Facilities on board include a conference room, lounges and internet access.

Decks A and D have a client office and a conference room while Deck C has only client office. The bridge accommodates one ship office. Deck A houses a lounge which is fully equipped with satellite TV and home theatre system. Deck B has two lounges with similar facilities.

All the cabins have local area network (LAN) connections. V-sat is provided separately for client internet and telephone lines.

Other major facilities include a gym and a hospital for officers and crew members.

Building Multifunction preview available

Visit my web-site

i-tech3design.wixsite.com/i-tech3design

* Disco-Alternative

* MESH Building

* Construction quality in a minimalist style

* This multipurpose facility designed for entertainment and "events at the disco, etc. .."

* The structure is composed of:

- Easy system of Rez (Rezbox)

- Armchairs minimal style, with a single session of animation avatar "Copy Only"

- Speakers Audio Aerodynamic "Copy"

- Console for DJs, with the animation, "Copy Only"

- Dynamic Lights controller (Environment)

- Dynamic Lights controller (light effect) controlled color

Portraits of my more or less old camera's and accessories.

Fuji HD-M with date. I bought this camera at spring 1990 at Daiei department store, 21-3, Narimasu 2-Chōme, Itabashi, Tokyo

Japan 175-0094.

"HD-M" stands for "Heavy Duty -Motor". It was designed to resist to water immersions and difficult weather or environmental conditions. I did most of my photos in Japan with it during the year 1991-1990 and used many years after. 30 years after. It still functions in full including the flash and dating back. The dating back was however limited to the year 2019.

Picture taken using a Sony A7 body on a Minolta Auto Bellows III fitted with a Minolta Auto Bellows Rokkor 100 mm f/4 lens. Artificial LED lights in a mini studio light box.

After using the Robotic Refueling Mission (RRM) Wire Cutter Tool to snip the wire that bounds the outer “tertiary” cap of the fuel valve, the Dextre robot uses the Multifunction Tool, equipped with a special adapter, to remove this cap and reveal the inner seals. Then it’s another round of wire-snipping and cap-removing before the fuel valve is accessed and the fluid can be transferred. This process is demonstrated with the actual RRM module on the International Space Station in January 2013.

Image credit: NASA

NASA image use policy.

NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission.

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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

-------------------------------------------------- -------------

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

A derivate of the Multifunction Self Protection System (MUSS) is used on the "Pitbull".

MUSS consists of three main elements: the sensors, consisting of laser warner and a missile warner using ultraviolet sensors, the computer, and the electronic or pyrotechnic countermeasures. When the sensors detect an incoming missile or a laser beam aimed at the vehicle, the computer activates the countermeasures. MUSS offers 360° protection with elevation up to 70° and can handle up to four threats at once.

(Source: Wikipedia)

Village of Scottsville, NY www.scottsvillefd.org

Ladder 4610 E-One, is a multifunction, aerial, rescue, and pumper. It has a 78 foot straight stick, foam system, hydraulic rescue tools, emergency medical equipment and carries 500 gallons of water.

On display at the 2014 Fire Expo in Harrisburg, PA

Ecco una zebra multiteste, tipo coltellino svizzero! Le zebre sono matte e divertenti!

Zebras are funny and crazy!

If you’re an only child, you’re kind of stuck relying on strangers or school teaching you about your body and sex.  Unless you’re lucky enough to have really cool and proactive parents, they often don’t approach you to talk about the “birds and the...

loveworks.com/learned-sex-in-the-city/

Pictures were taken using a SLR Minolta X-500 body (1984) with the MultiFunction back set to the dating (MM/DD/YY) auto mode and a standard lens Minolta MD 50 mm f/1.4. 35 mm Fujicolor film C200 36 exposures 200 ISO.

La Saône à l'Ile Barbe et sa passerelle, Lyon, France, New Year Day 2022.

Quai Clemenceau

69300 Caluire-et-Cuire

France

The film was developed using the C-41 process then digitalized using a Sony A7 body and a Minolta Slide Duplicator with a Minolta Auto Bellows III with a lens Minolta Bellow Macro Rokkor 50mm f/3.5.

For this frame, the artificial light produced by the LED lamp during the digital transfer was supplemented by a Wratten 80A blue filter to test the blue shift induced (conversion of tungsten light 3200 K to daylight 5500K. The light temperature was then less limited to the edge of scale available in LR.

Vendor: BTO

Type: Best Illuminated Watches

Price:

36.97

Best Illuminated Watches

Best Illuminated Watches

beyondtheoutdoors.com/wp-content/uploads/2017/01/Amono-Ou...

beyondtheoutdoors.com/best-illuminated-watches/

Niqab

The international military-technical forum ARMY 2019.

Международный военно-технический форум АРМИЯ 2019.

Practical Washbasin with Storage by Planit... Inspirational design