Here are images from my recent visit to the Cambo (www.cambo.com) factory in the Netherlands while I was visiting Amsterdam. Rene Rook of Cambo was nice enough to guide me through the entire production process as well as show me some vintage cameras from the companies history and show me their current product line (which was just recently updated at Photokina 2012)

for a full review of the products and a discussion of the images you see here (especially the vintage products) you can read the full article on my website www.brianhirschfeldphotography.com

Stemedica Cell Technologies manufacturing is focused on producing best-in-class stem cell lines for research and clinical studies and trials.

John Allison is William F. Hosford Professor of Materials Science and Engineering at the University of Michigan and a National Academy of Engineering member.

His major research interest is in understanding the inter-relationships between processing, alloying, microstructure and properties in metallic materials – and in incorporating this knowledge into computational tools for use in research, education and engineering. An important part of his research is development of Integrated Computational Materials Engineering (ICME) tools – and thus collaborations with other computational and experimental groups are an essential element of my work. Central to my research are investigations on the evolution of microstructures - current examples include precipitate evolution, recrystallization and grain growth and texture development in magnesium, aluminum and titanium alloys. He is also interested in mechanical behavior of these materials, with an emphasis on development of mechanistic and phenomenological understanding of the influence of microstructure on properties such as strength, ductility and fatigue resistance.

Allison comes to the University from Ford Motor Company, where he was a senior technical leader in the Research and Advanced Engineering organization. Over the twenty seven years of his tenure at Ford, he led teams developing integrated computational materials engineering, or ICME, methods. He helped develop advanced computer software that simulates manufacturing processes and predicts the influence of the manufacturing process on material properties. The output of these models is then coupled with product performance models to predict how manufactured components will behave during service.

July 11, 2023.

Photo by Marcin Szczepanski/Lead Multimedia Storyteller, Michigan Engineering

(En) Founded in 1906, the Coking Plant of Anderlues was specialized in the production of coke for industrial use.

Coke was obtained by distillation of coal in furnaces and, thanks to its superior fuel coal properties, it was used afterwards to feed the blast furnaces in the steel manufacturing process.

Closed and abandoned since 2002, the site has since undergone many losses and damages, not including an important pollution. While some buildings have now been demolished, there are however still some important parts of the former coking plant.

Among them, the former coal tower, next to the imposing "battery" of 38 furnaces, where the coke was produced. Besides them, we still can see the administrative buildings, the power station with its cooling tower, and buildings for the by-products, which were obtained by recovering the tar and coal gas. There are also a gasometer north side, the coal tip east side and a settling basin south side.

-----------

(Fr) Fondées en 1906, les Cokeries d'Anderlues étaient spécialisées dans la fabrication de coke à usage industriel.

Le coke était obtenu par distillation de la houille dans des fours et, grâce à ses propriétés combustibles supérieures au charbon, il servait par après à alimenter les hauts-fourneaux dans le processus de fabrication de l'acier.

Fermé et laissé à l'abandon depuis 2002, le site a depuis lors subi de nombreuses pertes et dégradations, sans compter la pollution qui y règne. Si certains bâtiments (comme l'ancien lavoir à charbon) ont aujourd'hui été démolis, on retrouve encore toutefois certaines parties importantes de cette ancienne cokerie.

Parmi celles-ci, l'ancienne tour à charbon suivie de près par l'imposante "batterie" de 38 fours, où était produit le coke. A côté d'eux, on découvre également les bâtiments administratifs, la centrale électrique avec sa tour de refroidissement, ainsi que les bâtiments des sous-produits, lesquels étaient obtenus par récupération du goudron et du gaz de houille. Et en périphérie, on retrouve un gazomètre côté nord, le terril à l'est et un bassin de décantation côté sud.

Io Aircraft - www.ioaircraft.com

Drew Blair

www.linkedin.com/in/drew-b-25485312/

io aircraft, phantom express, phantom works, boeing phantom works, lockheed skunk works, hypersonic weapon, hypersonic missile, scramjet missile, scramjet engineering, scramjet physics, boost glide, tactical glide vehicle, Boeing XS-1, htv, Air-Launched Rapid Response Weapon, (ARRW), hypersonic tactical vehicle, hypersonic plane, hypersonic aircraft, space plane, scramjet, turbine based combined cycle, ramjet, dual mode ramjet, darpa, onr, navair, afrl, air force research lab, defense science, missile defense agency, aerospike,

Advanced Additive Manufacturing for Hypersonic Aircraft

Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.

Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.

*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.

What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.

Unified Turbine Based Combined Cycle (U-TBCC)

To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5

However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.

Enhanced Dynamic Cavitation

Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.

Dynamic Scramjet Ignition Processes

For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.

Hydrogen vs Kerosene Fuel Sources

Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.

Conforming High Pressure Tank Technology for CNG and H2.

As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.

As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).

Enhanced Fuel Mixture During Shock Train Interaction

Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.

Improved Bow Shock Interaction

Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.

6,000+ Fahrenheit Thermal Resistance

To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.

*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope

Scramjet Propulsion Side Wall Cooling

With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.

Lower Threshold for Hypersonic Ignition

Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.

Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities

Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.

Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)

To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.

A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.

BlueEdge - Mach 8-10 Hypersonic Commercial Aircraft, 210 Passenger Hypersonic Plane - Iteration 2

Seating: 210 | Crew 2+4

Length: 195ft | Span: 93ft

Engines: 4 U-TBCC (Unified Turbine Based Combined Cycle) +1 Aerospike for sustained 2G acceleration to Mach 10.

Fuel: H2 (Compressed Hydrogen)

Cruising Altitude: 100,000-125,000ft

Airframe: 75% Proprietary Composites

Operating Costs, Similar to a 737. $7,000-$15,000hr, including averaged maintenence costs

Iteration 2

IO Aircraft www.ioaircraft.com

Drew Blair www.linkedin.com/in/drew-b-25485312/

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

hypersonic plane, hypersonic aircraft, hypersonic commercial plane, hypersonic commercial aircraft, hypersonic airline, tbcc, glide breaker, fighter plane, hyperonic fighter, boeing phantom express, phantom works, boeing phantom works, lockheed skunk works, hypersonic weapon, hypersonic missile, scramjet missile, scramjet engineering, scramjet physics, boost glide, tactical glide vehicle, Boeing XS-1, htv, Air Launched Rapid Response Weapon, (ARRW), hypersonic tactical vehicle, space plane, scramjet, turbine based combined cycle, ramjet, dual mode ramjet, darpa, onr, navair, afrl, air force research lab, office of naval research, defense advanced research project agency, defense science, missile defense agency, aerospike, hydrogen, hydrogen storage, hydrogen fueled, hydrogen aircraft

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

Unified Turbine Based Combined Cycle. Current technologies and what Lockheed is trying to force on the Dept of Defense, for that low speed Mach 5 plane DOD gave them $1 billion to build and would disintegrate above Mach 5, is TBCC. 2 separate propulsion systems in the same airframe, which requires TWICE the airframe space to use.

Unified Turbine Based Combined Cycle is 1 propulsion system cutting that airframe deficit in half, and also able to operate above Mach 10 up to Mach 15 in atmosphere, and a simple nozzle modification allows for outside atmosphere rocket mode, ie orbital capable.

Additionally, Reaction Engines maximum air breather mode is Mach 4.5, above that it will explode in flight from internal pressures are too high to operate. Thus, must switch to non air breather rocket mode to operate in atmosphere in hypersonic velocities. Which as a result, makes it not feasible for anything practical. It also takes an immense amount of fuel to function.

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

Advanced Additive Manufacturing for Hypersonic Aircraft

Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.

Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.

*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.

What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.

Unified Turbine Based Combined Cycle (U-TBCC)

To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5

However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.

Enhanced Dynamic Cavitation

Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.

Dynamic Scramjet Ignition Processes

For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.

Hydrogen vs Kerosene Fuel Sources

Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.

Conforming High Pressure Tank Technology for CNG and H2.

As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.

As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).

Enhanced Fuel Mixture During Shock Train Interaction

Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.

Improved Bow Shock Interaction

Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.

6,000+ Fahrenheit Thermal Resistance

To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.

*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope

Scramjet Propulsion Side Wall Cooling

With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.

Lower Threshold for Hypersonic Ignition

Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.

Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities

Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.

Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)

To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.

A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.

040

Friday, December 8th, 2017

Fortune Global Forum 2017

Guangzhou, China

8:00 AMâ9:20 AM

SMART MANUFACTURING AND THE INTERNET OF THINGS

Around the world, factory floors and assembly lines are becoming highly automated, combining human ingenuity with data and technology to revolutionize product and productivity outcomes. As the notion of a âfactory of the futureâ continues to evolve, how are companies incorporating âsmartâ and connected products into their manufacturing process? From sensors and robots to 3D printing and green technology, global companies are experimenting with a variety of methods to streamline, scale, and sustain their business. Here in China, manufacturers have been asked to deliver on the nationâs âMade in China 2025â strategy and are aggressively pursuing their own strategies to become smarter, greener, and more efficient. As these changes take hold, what are the implications for those doing business in China and for supply chains worldwide? And how are companies redeploying and reeducating their workforces as traditional factory jobs become automated and the need for technically proficient talent increases?

Hosted by The City of Guangzhou

Börje Ekholm, President and CEO, Ericsson Group

Till Reuter, Chief Executive Officer, KUKA

Tony Tan, Partner, Shanghai Office, McKinsey & Company

Wang Wenyin, Chairman, Amer International Group

Shoei Yamana, President and CEO, Konica Minolta

Zhang Jing, Founder and Chairman, Cedar Holdings Group

Moderator: Adam Lashinsky, Fortune

Photograph by Vivek Prakash/Fortune

HOBO U14 data loggers display, record, and provide alarm notifications of temperature and humidity conditions. Receive out-of-range alarms notifications with the optional Auto Dialer or Remote Audible Alarm. These loggers are well-suited for use in manufacturing, processing, and storage environments where reliable monitoring and documentation of temperature and relative humidity conditions is critical.

www.onsetcomp.com/products/data-loggers/u14-001

These tiled tanks once were filled with bleach used in the tiolet paper manufacturing process back when Georgia Pacific operated a paper mill on this site. They're located next to Kulshan Brewing's Trackside Beer Garden in Bellingham, Washington.

I used a KITE to fly the camera.

Io Aircraft - www.ioaircraft.com

Drew Blair

www.linkedin.com/in/drew-b-25485312/

io aircraft, phantom express, phantom works, boeing phantom works, lockheed skunk works, hypersonic weapon, hypersonic missile, scramjet missile, scramjet engineering, scramjet physics, boost glide, tactical glide vehicle, Boeing XS-1, htv, Air-Launched Rapid Response Weapon, (ARRW), hypersonic tactical vehicle, hypersonic plane, hypersonic aircraft, space plane, scramjet, turbine based combined cycle, ramjet, dual mode ramjet, darpa, onr, navair, afrl, air force research lab, defense science, missile defense agency, aerospike,

Advanced Additive Manufacturing for Hypersonic Aircraft

Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.

Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.

*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.

What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.

Unified Turbine Based Combined Cycle (U-TBCC)

To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5

However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.

Enhanced Dynamic Cavitation

Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.

Dynamic Scramjet Ignition Processes

For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.

Hydrogen vs Kerosene Fuel Sources

Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.

Conforming High Pressure Tank Technology for CNG and H2.

As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.

As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).

Enhanced Fuel Mixture During Shock Train Interaction

Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.

Improved Bow Shock Interaction

Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.

6,000+ Fahrenheit Thermal Resistance

To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.

*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope

Scramjet Propulsion Side Wall Cooling

With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.

Lower Threshold for Hypersonic Ignition

Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.

Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities

Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.

Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)

To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.

A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.

Io Aircraft - www.ioaircraft.com

Drew Blair

www.linkedin.com/in/drew-b-25485312/

io aircraft, phantom express, phantom works, boeing phantom works, lockheed skunk works, hypersonic weapon, hypersonic missile, scramjet missile, scramjet engineering, scramjet physics, boost glide, tactical glide vehicle, Boeing XS-1, htv, Air-Launched Rapid Response Weapon, (ARRW), hypersonic tactical vehicle, hypersonic plane, hypersonic aircraft, space plane, scramjet, turbine based combined cycle, ramjet, dual mode ramjet, darpa, onr, navair, afrl, air force research lab, defense science, missile defense agency, aerospike,

Advanced Additive Manufacturing for Hypersonic Aircraft

Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.

Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.

*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.

What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.

Unified Turbine Based Combined Cycle (U-TBCC)

To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5

However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.

Enhanced Dynamic Cavitation

Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.

Dynamic Scramjet Ignition Processes

For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.

Hydrogen vs Kerosene Fuel Sources

Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.

Conforming High Pressure Tank Technology for CNG and H2.

As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.

As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).

Enhanced Fuel Mixture During Shock Train Interaction

Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.

Improved Bow Shock Interaction

Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.

6,000+ Fahrenheit Thermal Resistance

To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.

*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope

Scramjet Propulsion Side Wall Cooling

With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.

Lower Threshold for Hypersonic Ignition

Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.

Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities

Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.

Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)

To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.

A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.

Graham Harwood (UK), Matsuko Yokokoji (JP).

A coal-fired boiler powers a network of computers exploring the relationships between power and media. Coal Fired Computers explores the ecologies that have created and maintained power, and the subsequent health residues and crisis of fuelling that power. The work responds to the displacement of coal production to distant India, China or Vietnam and our industrial heritage, in particular the work of Charles Parsons whose steam turbine is used to produce 40% of today’s electricity. In many countries this rate is much higher (more than 70% in India and China).

According to the World Health Organization, 318.000 deaths occur annually from chronic bronchitis and emphysema caused by exposure to coal dust. The common perception is that wealthy countries have put this all behind them, displacing coal dust into the lungs of unrecorded, unknown miners in distant lands, coal returning in our lives in the form of cheap and apparently clean goods we consume.

Coal fired energy not only powers our computers here in Europe, but is integral to the production of the 300.000.000 computers made each year. 81% of the energy used in a computer’s life cycle is expended in the manufacturing process, now taking place in countries with high levels of coal consumption.

yoha.co.uk/cfc

www.artefact-festival.be/2011/

Here are images from my recent visit to the Cambo (www.cambo.com) factory in the Netherlands while I was visiting Amsterdam. Rene Rook of Cambo was nice enough to guide me through the entire production process as well as show me some vintage cameras from the companies history and show me their current product line (which was just recently updated at Photokina 2012)

for a full review of the products and a discussion of the images you see here (especially the vintage products) you can read the full article on my website www.brianhirschfeldphotography.com

As part of the required course knowledge pupils need to be able to outline the process involved in taking a square wooden blank and preparing it for turning between centres. These pictures depict that process chronologically.

Stage 1 * Preparation of wooden blank. Cut to size. Sand square. Mark across diagonals. Centre punch the centre point. Use spring dividers to mark circumference. Repeat on other end.

Stage 2 * Plane off corners down to circumference line. This takes cross section from square to octagon. This reduces force on cutting toll in initial prep of blank. Mount between fork [driven] centre and dead [or live ] centre at tailstock end. Apply grease a dead centre end. apply force from tailstock end to force fork into material at driven end. Adjust toolstock height to suit. Check for clearance.

Stage 3 * Roughout using scraper to diameter. Use combination of gouges and skew chisels to add beads and other decorative detailing as required. Ensure spindle speed is appropriate for material and cross section under consideration. Obey all safety instructions.

040

Friday, December 8th, 2017

Fortune Global Forum 2017

Guangzhou, China

8:00 AM–9:20 AM

SMART MANUFACTURING AND THE INTERNET OF THINGS

Around the world, factory floors and assembly lines are becoming highly automated, combining human ingenuity with data and technology to revolutionize product and productivity outcomes. As the notion of a “factory of the future” continues to evolve, how are companies incorporating “smart” and connected products into their manufacturing process? From sensors and robots to 3D printing and green technology, global companies are experimenting with a variety of methods to streamline, scale, and sustain their business. Here in China, manufacturers have been asked to deliver on the nation’s “Made in China 2025” strategy and are aggressively pursuing their own strategies to become smarter, greener, and more efficient. As these changes take hold, what are the implications for those doing business in China and for supply chains worldwide? And how are companies redeploying and reeducating their workforces as traditional factory jobs become automated and the need for technically proficient talent increases?

Hosted by The City of Guangzhou

Börje Ekholm, President and CEO, Ericsson Group

Till Reuter, Chief Executive Officer, KUKA

Tony Tan, Partner, Shanghai Office, McKinsey & Company

Wang Wenyin, Chairman, Amer International Group

Shoei Yamana, President and CEO, Konica Minolta

Zhang Jing, Founder and Chairman, Cedar Holdings Group

Moderator: Adam Lashinsky, Fortune

Photograph by Vivek Prakash/Fortune

Graham Harwood (UK), Matsuko Yokokoji (JP).

A coal-fired boiler powers a network of computers exploring the relationships between power and media. Coal Fired Computers explores the ecologies that have created and maintained power, and the subsequent health residues and crisis of fuelling that power. The work responds to the displacement of coal production to distant India, China or Vietnam and our industrial heritage, in particular the work of Charles Parsons whose steam turbine is used to produce 40% of today’s electricity. In many countries this rate is much higher (more than 70% in India and China).

According to the World Health Organization, 318.000 deaths occur annually from chronic bronchitis and emphysema caused by exposure to coal dust. The common perception is that wealthy countries have put this all behind them, displacing coal dust into the lungs of unrecorded, unknown miners in distant lands, coal returning in our lives in the form of cheap and apparently clean goods we consume.

Coal fired energy not only powers our computers here in Europe, but is integral to the production of the 300.000.000 computers made each year. 81% of the energy used in a computer’s life cycle is expended in the manufacturing process, now taking place in countries with high levels of coal consumption.

yoha.co.uk/cfc

www.artefact-festival.be/2011/

Jelly Belly Candy Company, formerly known as Herman Goelitz Candy Company and Goelitz Confectionery Company, manufactures Jelly Belly jelly beans and other candy. It is based in Fairfield, California, with a second manufacturing facility in North Chicago, Illinois and a distribution center in Pleasant Prairie, Wisconsin. In October 2008, the company opened a 50,000 sq ft (4,645 m2) manufacturing plant in Rayong, Thailand where it produces confectionery for the international market.

The company's signature product, the Jelly Belly jelly bean, comes in more than 50 varieties, ranging from traditional flavors like orange, lemon, lime, and cherry, to more exotic ones like cinnamon, pomegranate, cappuccino, buttered popcorn, and chili-mango.

Jelly Belly Candy Company manufactures numerous specialty Jelly Belly jelly beans with licensed products like Tabasco sauce and uncommon candy tastes like egg nog and pancakes with maple syrup. A few flavors, like lychee and green tea, are sold only in markets outside the United States.

Several flavors have been based on popular alcoholic beverages, beginning with Mai Tai in 1977. Over the years, new additions have included blackberry brandy (now discontinued), strawberry daiquiri, margarita, mojito, and piña colada. Draft beer, a flavor inspired by Hefeweizen ale, was introduced in 2014. All such flavors are entirely alcohol-free.

"Bertie Bott's Every Flavour Beans" were inspired by the Harry Potter book series and featured intentionally gruesome flavors such as "Vomit", "Earwax", "Skunk Spray", and "Rotten Egg". A similar product pairs lookalike "normal" jelly beans with weird flavors in a product dubbed "BeanBoozled" which has gone through several editions.

"Sport Beans" are jelly beans designed to provide physical energy and enhance athletic performance. They contain carbohydrates, electrolytes (in the form of sodium and potassium), and vitamins B1, B2, B3 and C. "Extreme Sport Beans" include the additional boost of caffeine.

The company makes over 100 different confections, including chocolates, licorice, gummis, and candy corn.

The company operates three manufacturing plants in Fairfield, California; North Chicago, Illinois; and Rayong, Thailand. A fourth facility in Pleasant Prairie, Wisconsin, is for distribution.

The Fairfield and Pleasant Prairie locations offer free daily tours. The 1⁄4 mi-long (400 m) self-guided Fairfield tour features interactive exhibits, Jelly Belly bean art, and videos featuring the candy manufacturing process. It was named one of the best factory tours for children by FamilyFun Magazine in 2014.

en.wikipedia.org/wiki/Jelly_Belly

en.wikipedia.org/wiki/Wikipedia:Text_of_Creative_Commons_...

Io Aircraft - www.ioaircraft.com

Drew Blair

www.linkedin.com/in/drew-b-25485312/

io aircraft, phantom express, phantom works, boeing phantom works, lockheed skunk works, hypersonic weapon, hypersonic missile, scramjet missile, scramjet engineering, scramjet physics, boost glide, tactical glide vehicle, Boeing XS-1, htv, Air-Launched Rapid Response Weapon, (ARRW), hypersonic tactical vehicle, hypersonic plane, hypersonic aircraft, space plane, scramjet, turbine based combined cycle, ramjet, dual mode ramjet, darpa, onr, navair, afrl, air force research lab, defense science, missile defense agency, aerospike,

Advanced Additive Manufacturing for Hypersonic Aircraft

Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.

Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.

*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.

What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.

Unified Turbine Based Combined Cycle (U-TBCC)

To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5

However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.

Enhanced Dynamic Cavitation

Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.

Dynamic Scramjet Ignition Processes

For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.

Hydrogen vs Kerosene Fuel Sources

Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.

Conforming High Pressure Tank Technology for CNG and H2.

As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.

As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).

Enhanced Fuel Mixture During Shock Train Interaction

Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.

Improved Bow Shock Interaction

Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.

6,000+ Fahrenheit Thermal Resistance

To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.

*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope

Scramjet Propulsion Side Wall Cooling

With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.

Lower Threshold for Hypersonic Ignition

Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.

Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities

Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.

Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)

To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.

A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.

Here are images from my recent visit to the Cambo (www.cambo.com) factory in the Netherlands while I was visiting Amsterdam. Rene Rook of Cambo was nice enough to guide me through the entire production process as well as show me some vintage cameras from the companies history and show me their current product line (which was just recently updated at Photokina 2012)

for a full review of the products and a discussion of the images you see here (especially the vintage products) you can read the full article on my website www.brianhirschfeldphotography.com

As part of the required course knowledge pupils need to be able to outline the process involved in taking a square wooden blank and preparing it for turning between centres. These pictures depict that process chronologically.

Stage 1 * Preparation of wooden blank. Cut to size. Sand square. Mark across diagonals. Centre punch the centre point. Use spring dividers to mark circumference. Repeat on other end.

Stage 2 * Plane off corners down to circumference line. This takes cross section from square to octagon. This reduces force on cutting toll in initial prep of blank. Mount between fork [driven] centre and dead [or live ] centre at tailstock end. Apply grease a dead centre end. apply force from tailstock end to force fork into material at driven end. Adjust toolstock height to suit. Check for clearance.

Stage 3 * Roughout using scraper to diameter. Use combination of gouges and skew chisels to add beads and other decorative detailing as required. Ensure spindle speed is appropriate for material and cross section under consideration. Obey all safety instructions.

GL Mustang series. I added the convertible to this piece. Notice that big ass scratch across the windshield that sucks. Must have happen during the manufacturing process.

Grey Eagle - Hypersonic Bomber Mach 8 - 10, IO Aircraft www.ioaircraft.com

Length: 150'

Span: 71'

Engines: 4 U-TBCC (Unified Turbine Based Combined Cycle)

1 Air Breathing Aerospike

Fuel: Kero / Hydrogen

Payload: Up 36 2,000 LBS JDAM's, or 80,000 LBS

Range: 10,000nm + Aerial Refueling Capable

www.ioaircraft.com/hypersonic.php

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

hypersonic bomber, hypersonic commercial aircraft, hypersonic commercial plane, hypersonic aircraft, hypersonic plane, hypersonic airline, tbcc, glide breaker, fighter plane, hypersonic fighter, boeing phantom express, phantom works, boeing phantom works, lockheed skunk works, hypersonic weapon, hypersonic missile, scramjet engineering, scramjet physics, boost glide, tactical glide vehicle, space plane, scramjet, turbine based combined cycle, ramjet, dual mode ramjetdefense science, missile defense agency, aerospike, hydrogen aircraft, airlines, military, physics, airline, aerion supersonic, aerion, spike aerospace, boom supersonic, , darpa, onr, navair, afrl, air force research lab, office of naval research, defense advanced research project agency, afosr, socom, arl, army future command, mda, missile defense agenci, dia, defense intelligence agency, air force of science and research,

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

Unified Turbine Based Combined Cycle. Current technologies and what Lockheed is trying to force on the Dept of Defense, for that low speed Mach 5 plane DOD gave them $1 billion to build and would disintegrate above Mach 5, is TBCC. 2 separate propulsion systems in the same airframe, which requires TWICE the airframe space to use.

Unified Turbine Based Combined Cycle is 1 propulsion system cutting that airframe deficit in half, and also able to operate above Mach 10 up to Mach 15 in atmosphere, and a simple nozzle modification allows for outside atmosphere rocket mode, ie orbital capable.

Additionally, Reaction Engines maximum air breather mode is Mach 4.5, above that it will explode in flight from internal pressures are too high to operate. Thus, must switch to non air breather rocket mode to operate in atmosphere in hypersonic velocities. Which as a result, makes it not feasible for anything practical. It also takes an immense amount of fuel to function.

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

Advanced Additive Manufacturing for Hypersonic Aircraft

Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.

Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.

*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.

What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.

Unified Turbine Based Combined Cycle (U-TBCC)

To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5

However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.

Enhanced Dynamic Cavitation

Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.

Dynamic Scramjet Ignition Processes

For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.

Hydrogen vs Kerosene Fuel Sources

Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.

Conforming High Pressure Tank Technology for CNG and H2.

As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.

As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).

Enhanced Fuel Mixture During Shock Train Interaction

Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.

Improved Bow Shock Interaction

Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.

6,000+ Fahrenheit Thermal Resistance

To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.

*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope

Scramjet Propulsion Side Wall Cooling

With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.

Lower Threshold for Hypersonic Ignition

Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.

Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities

Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.

Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)

To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.

A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.

Here are images from my recent visit to the Cambo (www.cambo.com) factory in the Netherlands while I was visiting Amsterdam. Rene Rook of Cambo was nice enough to guide me through the entire production process as well as show me some vintage cameras from the companies history and show me their current product line (which was just recently updated at Photokina 2012)

for a full review of the products and a discussion of the images you see here (especially the vintage products) you can read the full article on my website www.brianhirschfeldphotography.com

Here are images from my recent visit to the Cambo (www.cambo.com) factory in the Netherlands while I was visiting Amsterdam. Rene Rook of Cambo was nice enough to guide me through the entire production process as well as show me some vintage cameras from the companies history and show me their current product line (which was just recently updated at Photokina 2012)

for a full review of the products and a discussion of the images you see here (especially the vintage products) you can read the full article on my website www.brianhirschfeldphotography.com

Each skein has about 30-45 yards of silk pieces of fabric attached to each other. The silk strips are about .75 inches wide. There is some variance due to the way this yarn is created. It's created by the collection of silk remnants of clothing (mainly saris) in the truing and trimming of fabric during the manufacturing process. Then the strips are attached together to make this great yarn by sewing the ends together.

There are brocade pieces of material in this yarn so if you have any kind of allergies to metal by example I would choose another yarn! But if you have no allergies, this yarn has such cool colors and textures even if you don't knit with it, you can use it on plenty of projects and even wrapping gifts (my personal favorite).

Also, please note, that this yarn is from Nepal and I worked with women's co-ops to ensure proper and fair wages were provided to the women who made this yarn. That's important because we all need to

RETHINK YOUR CRAFTING! Only from Darn Good Yarn purveyors of Fine Recycled Silk Yarn, Free Knitting and Crochet Patterns and more!

Graham Harwood (UK), Matsuko Yokokoji (JP).

A coal-fired boiler powers a network of computers exploring the relationships between power and media. Coal Fired Computers explores the ecologies that have created and maintained power, and the subsequent health residues and crisis of fuelling that power. The work responds to the displacement of coal production to distant India, China or Vietnam and our industrial heritage, in particular the work of Charles Parsons whose steam turbine is used to produce 40% of today’s electricity. In many countries this rate is much higher (more than 70% in India and China).

According to the World Health Organization, 318.000 deaths occur annually from chronic bronchitis and emphysema caused by exposure to coal dust. The common perception is that wealthy countries have put this all behind them, displacing coal dust into the lungs of unrecorded, unknown miners in distant lands, coal returning in our lives in the form of cheap and apparently clean goods we consume.

Coal fired energy not only powers our computers here in Europe, but is integral to the production of the 300.000.000 computers made each year. 81% of the energy used in a computer’s life cycle is expended in the manufacturing process, now taking place in countries with high levels of coal consumption.

yoha.co.uk/cfc

www.artefact-festival.be/2011/

Hella Jongerius (1963) - Coloured Vases, 2010

Porselein, 300 zelfgemaakte kleuren, resulterend uit het mengen van oude en nieuwe glazuren; sommige vazen: glazuren en verf. Unica

Porcelain, 300 selfmade colours through a mix of old and new glazes; some vases: glazes + spray lacquer. One-offs

Op de vloer staan ook 300 vazen opgesteld in uiteenlopende kleurschakeringen: de nieuwe serie Coloured Vases (serie 3). Deze serie is afgelopen zomer ontwikkeld in nauwe samenwerking met Koninklijke Tichelaar Makkum. De Coloured Vases laten kleurexperimenten zien, waarbij telkens een bestaande vaas is gebruikt als ‘canvas’. De kleuren bestaan uit een mix van oude glazuren en nieuwe synthetische glazuren. Sommige vazen zijn voorzien van een extra laag industriële verf. Kleur is een belangrijk element in de ontwerppraktijk van Hella Jongerius en dat ziet u overal in de tentoonstelling terugkomen.

Hella Jongerius (1963) geldt internationaal als een van de belangrijkste ontwerpers van haar generatie. In 1993 start zij in Rotterdam haar studio Jongeriuslab, waar zij zowel in eigen beheer als in opdracht van nationale en internationale bedrijven producten ontwerpt. Jongerius introduceert in de jaren negentig ambachtelijke imperfecties en individualiteit in industriële productiemethodes. Ambachtelijke kwaliteiten zijn volgens Jongerius niet afleesbaar aan de perfectie waarmee dingen zijn gemaakt, maar aan de afwijkingen, ‘misfits’, de zichtbare sporen van de hand van de maker.

Standing on the floor are 300 vases, arranged in a variety of colour schemes: the new series of Coloured Vases (series 3). Jongerius developed this series during the summer in close collaboration with Royal Tichelaar Makkum. The Coloured Vases are experiments with colour, using an existing vase as a ‘canvas’. The colours consist of a mix of historical mineral glaze recipes and modern chemical glaze recipes. Some vases have an extra layer of industrial paint. Colour is an important element in Hella Jongerius’s design practice, as you will see throughout the exhibition.

Hella Jongerius (1963) is internationally regarded as one of the most important designers of her generation. She began her own studio Jongeriuslab in Rotterdam in 1993, designing products for international clients and also self-initiated projects. In the 1990s she introduced imperfections and individuality into the industrial manufacturing process. Jongerius believes that the quality of craftsmanship is not legible in perfect products but only in the ‘misfits’ that betray the process and the hand of the maker.

en.wikipedia.org/wiki/De_Havilland_Dove#Variants

en.wikipedia.org/wiki/Yorkshire_Air_Museum#Collection

The de Havilland DH.104 Dove is a British short-haul airliner developed and manufactured by de Havilland. The design, which was a monoplane successor to the pre-war Dragon Rapide biplane, came about from the Brabazon Committee report which, amongst other aircraft types, called for a British-designed short-haul feeder for airlines.

The Dove was a popular aircraft and is considered to be one of Britain's most successful postwar civil designs, with over 500 aircraft manufactured between 1946 and 1967. Several military variants were operated, such as the Devon by the Royal Air Force and the Sea Devon by the Royal Navy, and the type also saw service with a number of overseas military forces.

A longer four-engined development of the Dove, intended for use in the less developed areas of the world, was the Heron. A considerably re-designed three-engined variant of the Dove was built in Australia as the de Havilland Australia DHA-3 Drover.

The development team for the Dove was headed by Ronald Bishop, the creator of the de Havilland Mosquito, a wartime fighter-bomber, and the de Havilland Comet, the first commercial jet aircraft in the world. It had been developed to meet the Type VB requirement issued by the Brabazon Committee. In concept, the Dove was developed to be the replacement of the pre-war Dragon Rapide. It was also required to be competitive with the large numbers of surplus military transports in the aftermath of the Second World War, such as the Douglas DC-3. Unlike the Dragon Rapide, the Dove's structure was entirely metal. It featured innovations including constant-speed propellers, flaps, and a retractable tricycle undercarriage.

In 1946, aviation magazine Flight praised the qualities of the newly developed Dove, noting its "modernity" as well as the aircraft's load-carrying capacity, safe engine-failure performance, and positive maintenance features. Considerable attention was paid to aspects of maintainability, many of the components being designed to be interchangeable and easy to remove or replace, such as the rudder, elevator, and power units; other areas include the mounting of the engines upon four quick-release pickup points, the routing of cables and piping, and the detachable wings and tail cone. The extensive use of special Redux metal-bonding adhesives reduced the need for riveting during the manufacturing process, reducing overall weight and air-skin friction.

While standard passenger versions of the Dove would carry between eight and eleven passengers, the cabin was designed to allow operators to convert between higher and lower density seating configurations. Features such as a single aircraft lavatory and an aft luggage compartment could be removed to provide increased seating. Various specialised models were produced for other roles, such as aerial survey, air ambulance, and flying classroom. A strengthened cabin floor structure was used to enable concentrated freight loads to be carried as well. The Dove could also serve as an executive transport, and in such a configuration it was capable of seating five passengers; the executive model proved to be popular with various overseas customers, particularly those in the United States.

The crew typically consisted of a pilot and radio operator, although rapidly removable dual flight controls could be installed for a second flying crewmember. A combination of large windows and a transparent perspex cabin roof provided a high level of visibility from the cockpit. From a piloting perspective, the Dove was noted for possessing easy flying qualities and mild stall qualities. A TKS anti-icing system was available for the Dove, involving an alcohol-based jelly delivered via porous metal strips embedded on the leading edges of the wings and tail.

The Dove first flew on 25 September 1945. In December 1946, the Dove entered service with Central African Airways. Initial production of the Dove took place at de Havilland's Hatfield factory, but from 1951 the aircraft were built at the company's Broughton facility near Chester. The final example of the type was delivered in 1967. Production of the Dove and its variants totalled 544 aircraft, including two prototypes, 127 military-orientated Devons and 13 Sea Devons.

From 1946, large numbers were sold to scheduled and charter airlines around the world, replacing and supplementing the pre-war designed de Havilland Dragon Rapide and other older designs. The largest order for the Dove was placed by Argentina, which ultimately took delivery of 70 aircraft, the majority of which were used by the Argentine Air Force. LAN Chile took delivery of twelve examples and these were operated from 1949 onwards until the aircraft were sold to several small regional airlines in the United States in 1954.

In excess of 50 Doves were sold to various operators in the United States by Jack Riley, an overseas distributor for the type. De Havilland later assumed direct control of U.S. sales, but did not manage to match this early commercial success for the type.

An early batch of 30 Devons was delivered to the Royal Air Force and they were used as VIP and light transports for over 30 years. The Royal New Zealand Air Force acquired 30 Devons between 1948 and 1954, and these remained in service for VIP, crew-training and light transport duties into the 1970s.

The Biafran Air Force operated a single Dove during the Nigerian Civil War; the aircraft was lost, to be subsequently found in 1970 on the premises of a school in Uli. A second US-registered Riley Dove, N477PM delivered in 1967 to Port Harcourt from Switzerland, never reached Biafra because it was stopped by Algerian authorities.

A few Doves and civilianised Devons remained in use in 2011 in the United Kingdom, Canada, Germany and elsewhere with small commercial firms and with private pilot owners.

The Yorkshire Air Museum & Allied Air Forces Memorial is an aviation museum in Elvington, York on the site of the former RAF Elvington airfield, a Second World War RAF Bomber Command station. The museum was founded, and first opened to the public, in the mid 1980s.

The museum is one of the largest independent air museums in Britain. It is also the only Allied Air Forces Memorial in Europe. The museum is an accredited museum under Arts Council accreditation scheme. It is a Member of Friends of the Few (Battle of Britain Memorial), the Royal Aeronautical Society, the Museums Association and the Association of Independent Museums.

The Museum is a registered charity (No. 516766) dedicated to the history of aviation and was also set up as a Memorial to all allied air forces personnel, particularly those who served in the Royal Air Force during the Second World War.

Site

Further information: RAF Elvington

The 20-acre (81,000 m2) parkland site includes buildings and hangars, some of which are listed. It incorporates a 7-acre (28,000 m2) managed environment area and a DEFRA and Environment Agency supported self sustainability project called "Nature of Flight". The museum is situated next to a 10,000 ft runway, which is privately owned.

History

Whilst the Royal Air Force carried on using the runway for aircraft landing and take off training until 1992, the buildings and hangars had long been abandoned. In 1980 Rachel Semlyen approached the owners of "what was then an abandoned and derelict wartime site, with the idea of restoring the buildings and creating a museum". In 1983, a group started clearing the undergrowth and the site was ready to be unveiled as the Yorkshire Air Museum in 1986.

Events

The Museum undertakes several annual events each year within the general attraction / entertainment area as well as educational / academic events for specific audiences, plus several corporate events in association with companies such as Bentley, Porsche, banking, government agencies etc. The unique annual Allied Air Forces Memorial Day takes place in September.

Exhibits

The Museum has over 50 aircraft spanning the development of aviation from 1853 up to the latest GR4 Tornado. Several aircraft including Victor, Nimrod, Buccaneer, Sea Devon, SE5a, Eastchurch Kitten, DC3 Dakota are kept live and operated on special "Thunder Days" during the year. Over 20 historic vehicles and a Registered Archive containing over 500,000 historic artefacts and documents are also preserved at the Museum, which is also the Official Archive for the National Aircrew Association and National Air Gunners Association. It is nationally registered and accredited through DCMS/Arts Council England and is a registered charity.

A permanent exhibition on RAF Bomber Command was opened at the museum by life member, Sir David Jason. In 2010 a new exhibition called "Pioneers of Aviation", and funded by the Heritage Lottery Fund, was opened featuring the lives and achievements of Sir George Cayley, Sir Barnes Wallis, Robert Blackburn, Nevil Shute and Amy Johnson.

Principal on-site businesses include: Restaurant, Retail Shop, Events, Aircraft Operation Engineering Workshops, Archives and Corporate Business Suite. The museum is also a location for TV and film companies.

Building 1 – Airborne Forces Display & No. 609 Squadron RAF Room

Building 2 – Uniform Display

Building 3 – Air Gunners' Exhibition

Building 4 – Archives & Reference Library

Building 5 – Museum Shop

Building 7 – Memorial Garden

Building 8 – Museum HQ, Main Entrance

Building 9 – Against the Odds

Building 10 – Elvington Corporate Room

Building 11 – Museum NAAFI Restaurant

Building 12 – Control Tower

Building 13 – French Officers' Mess

Building 14 – Airmens Billet and Station MT Display

Building 15 – Royal Observer Corp

Building 16 – Signal Square

Building 17 – Hangar T2 Main Aircraft exhibition

Building 18 – Archive & Collections Building

Building 19 – Handley Page Aircraft Workshop

Building 20 – Pioneer of Aviation Exhibition

Collection

Aircraft on display

Pre-World War II

Avro 504K – Replica

Blackburn Mercury – Replica

Cayley Glider – Replica

Mignet HM.14 Pou-du-Ciel

Port Victoria P.V.8 Eastchurch Kitten Replica

Royal Aircraft Factory BE.2c – Replica

Royal Aircraft Factory SE.5a – Replica

Wright Flyer – Replica

World War II

Avro Anson T.21 VV901

Douglas Dakota IV KN353

Fairchild Argus II FK338

Gloster Meteor F.8 WL168

Gloster Meteor NF.14 WS788

Handley Page Halifax III LV907

Hawker Hurricane I – Replica

Messerschmitt Bf 109 G-6 – Replica

Slingsby T.7 Kirby Cadet RA854

Supermarine Spitfire I – Replica

Waco Hadrian 237123

Post World War II

Air Command Commander Elite

Beagle Terrier 2 TJ704

Canadair CT-133 Silver Star 133417

de Havilland Devon C.2 VP967

de Havilland Vampire T.11 XH278

Europa Prototype 001

Mainair Demon

Saunders-Roe Skeeter AOP.12 XM553

Westland Dragonfly HR.5 WH991

Cold War

BAC Jet Provost T.4 XP640

Blackburn Buccaneer S.2 XN974

Blackburn Buccaneer S.2B XX901

British Aerospace Harrier GR.3 XV748

British Aerospace Nimrod MR.2 XV250

Dassault Mirage IIIE 538

Dassault Mirage IVA 45/BR

English Electric Canberra T.4 WH846

English Electric Lightning F.6 XS903 which arrived during June 1988.

Fairey Gannet AEW.3 XL502

Gloster Javelin FAW.9 XH767

Handley Page Victor K.2 XL231

Hawker Hunter FGA.78 QA10

Hawker Hunter T.7 XL572

Panavia Tornado GR.1 ZA354

Panavia Tornado GR.4 XZ631

Ground vehicles

Second World War

Thompson Brothers Aircraft Refueller

1938 Ford Model E

1940 "Tilly" Standard 12 hp Mkl RAF Utility Vehicle

1941 Chevrolet 4x4 CMP

1942 Austin K2 NAAFI Wagon

1942 Thornycroft ‘Amazon’ Coles Crane

Cold War

1947 Commer one and a half deck airport coach

1949 Citroen 11BL

1948 David Brown VIG.2 Aircraft Tractor

1949 David Brown VIG.3 Aircraft Tractor

1951 David Brown GP Airfield Tractor

1953 Alvis Saracen 12ton APC

1953 Austin Champ Cargo 4x4 General Purpose Vehicle

1956 Green Goddess Self Propelled Pump

1958 Commer Q4 Bikini Fire Pump Unit

1958 Lansing Aircraft Carrier Type Tug

1959 Daimler Ferret ASC MK.2/3/7

1966 Chieftain Main Battle Tank

1970 Douglas P3 nuclear aircraft 25 tonne tug

1971 Pathfinder Fire Engine 35ton (ex. Manchester Airport)

1972 TACR2 Range Rover - 6 wheeled fast response fire unit

1974 GMC 6 wheeled fast response airfield fire truck

1976 Dennis Mercury 17.5 tonne aircraft tug

Pathfinder Fire Engine

Lisa Glover Chipboard dinosaur

Description:

The high quality of the cosmetic powder brush allows you to apply product more evenly, giving you a beautiful look. With elaborate manufacture process, the profession petal shaped multifunction cosmetic powder brush are so luxury for women. You can use them to make up relieved because of the disinfected process. Every cosmetic powder brush can make its own different affection. Using cheap powder brush in the right way, you can make yourself more and more beautiful and noble. Using the makeup brush gives you a daily massage every time you apply your makeup.

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Package Included:

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www.casesinthebox.com/profession-petal-shaped-multifuncti...

(En) Founded in 1906, the Coking Plant of Anderlues was specialized in the production of coke for industrial use.

Coke was obtained by distillation of coal in furnaces and, thanks to its superior fuel coal properties, it was used afterwards to feed the blast furnaces in the steel manufacturing process.

Closed and abandoned since 2002, the site has since undergone many losses and damages, not including an important pollution. While some buildings have now been demolished, there are however still some important parts of the former coking plant.

Among them, the former coal tower, next to the imposing "battery" of 38 furnaces, where the coke was produced. Besides them, we still can see the administrative buildings, the power station with its cooling tower, and buildings for the by-products, which were obtained by recovering the tar and coal gas. There are also a gasometer north side, the coal tip east side and a settling basin south side.

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(Fr) Fondées en 1906, les Cokeries d'Anderlues étaient spécialisées dans la fabrication de coke à usage industriel.

Le coke était obtenu par distillation de la houille dans des fours et, grâce à ses propriétés combustibles supérieures au charbon, il servait par après à alimenter les hauts-fourneaux dans le processus de fabrication de l'acier.

Fermé et laissé à l'abandon depuis 2002, le site a depuis lors subi de nombreuses pertes et dégradations, sans compter la pollution qui y règne. Si certains bâtiments (comme l'ancien lavoir à charbon) ont aujourd'hui été démolis, on retrouve encore toutefois certaines parties importantes de cette ancienne cokerie.

Parmi celles-ci, l'ancienne tour à charbon suivie de près par l'imposante "batterie" de 38 fours, où était produit le coke. A côté d'eux, on découvre également les bâtiments administratifs, la centrale électrique avec sa tour de refroidissement, ainsi que les bâtiments des sous-produits, lesquels étaient obtenus par récupération du goudron et du gaz de houille. Et en périphérie, on retrouve un gazomètre côté nord, le terril à l'est et un bassin de décantation côté sud.

Graham Harwood (UK), Matsuko Yokokoji (JP).

A coal-fired boiler powers a network of computers exploring the relationships between power and media. Coal Fired Computers explores the ecologies that have created and maintained power, and the subsequent health residues and crisis of fuelling that power. The work responds to the displacement of coal production to distant India, China or Vietnam and our industrial heritage, in particular the work of Charles Parsons whose steam turbine is used to produce 40% of today’s electricity. In many countries this rate is much higher (more than 70% in India and China).

According to the World Health Organization, 318.000 deaths occur annually from chronic bronchitis and emphysema caused by exposure to coal dust. The common perception is that wealthy countries have put this all behind them, displacing coal dust into the lungs of unrecorded, unknown miners in distant lands, coal returning in our lives in the form of cheap and apparently clean goods we consume.

Coal fired energy not only powers our computers here in Europe, but is integral to the production of the 300.000.000 computers made each year. 81% of the energy used in a computer’s life cycle is expended in the manufacturing process, now taking place in countries with high levels of coal consumption.

yoha.co.uk/cfc

www.artefact-festival.be/2011/

Grey Eagle - Hypersonic Bomber Mach 8 - 10, IO Aircraft www.ioaircraft.com

Length: 150'

Span: 71'

Engines: 4 U-TBCC (Unified Turbine Based Combined Cycle)

1 Air Breathing Aerospike

Fuel: Kero / Hydrogen

Payload: Up 36 2,000 LBS JDAM's, or 80,000 LBS

Range: 10,000nm + Aerial Refueling Capable

www.ioaircraft.com/hypersonic.php

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Unified Turbine Based Combined Cycle. Current technologies and what Lockheed is trying to force on the Dept of Defense, for that low speed Mach 5 plane DOD gave them $1 billion to build and would disintegrate above Mach 5, is TBCC. 2 separate propulsion systems in the same airframe, which requires TWICE the airframe space to use.

Unified Turbine Based Combined Cycle is 1 propulsion system cutting that airframe deficit in half, and also able to operate above Mach 10 up to Mach 15 in atmosphere, and a simple nozzle modification allows for outside atmosphere rocket mode, ie orbital capable.

Additionally, Reaction Engines maximum air breather mode is Mach 4.5, above that it will explode in flight from internal pressures are too high to operate. Thus, must switch to non air breather rocket mode to operate in atmosphere in hypersonic velocities. Which as a result, makes it not feasible for anything practical. It also takes an immense amount of fuel to function.

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

Advanced Additive Manufacturing for Hypersonic Aircraft

Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.

Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.

*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.

What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.

Unified Turbine Based Combined Cycle (U-TBCC)

To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5

However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.

Enhanced Dynamic Cavitation

Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.

Dynamic Scramjet Ignition Processes

For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.

Hydrogen vs Kerosene Fuel Sources

Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.

Conforming High Pressure Tank Technology for CNG and H2.

As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.

As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).

Enhanced Fuel Mixture During Shock Train Interaction

Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.

Improved Bow Shock Interaction

Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.

6,000+ Fahrenheit Thermal Resistance

To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.

*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope

Scramjet Propulsion Side Wall Cooling

With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.

Lower Threshold for Hypersonic Ignition

Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.

Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities

Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.

Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)

To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.

A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.

As part of the required course knowledge pupils need to be able to outline the process involved in taking a square wooden blank and preparing it for turning between centres. These pictures depict that process chronologically.

Stage 1 * Preparation of wooden blank. Cut to size. Sand square. Mark across diagonals. Centre punch the centre point. Use spring dividers to mark circumference. Repeat on other end.

Stage 2 * Plane off corners down to circumference line. This takes cross section from square to octagon. This reduces force on cutting toll in initial prep of blank. Mount between fork [driven] centre and dead [or live ] centre at tailstock end. Apply grease a dead centre end. apply force from tailstock end to force fork into material at driven end. Adjust toolstock height to suit. Check for clearance.

Stage 3 * Roughout using scraper to diameter. Use combination of gouges and skew chisels to add beads and other decorative detailing as required. Ensure spindle speed is appropriate for material and cross section under consideration. Obey all safety instructions.

Io Aircraft - www.ioaircraft.com

Drew Blair

www.linkedin.com/in/drew-b-25485312/

io aircraft, phantom express, phantom works, boeing phantom works, lockheed skunk works, hypersonic weapon, hypersonic missile, scramjet missile, scramjet engineering, scramjet physics, boost glide, tactical glide vehicle, Boeing XS-1, htv, Air-Launched Rapid Response Weapon, (ARRW), hypersonic tactical vehicle, hypersonic plane, hypersonic aircraft, space plane, scramjet, turbine based combined cycle, ramjet, dual mode ramjet, darpa, onr, navair, afrl, air force research lab, defense science, missile defense agency, aerospike,

Advanced Additive Manufacturing for Hypersonic Aircraft

Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.

Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.

*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.

What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.

Unified Turbine Based Combined Cycle (U-TBCC)

To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5

However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.

Enhanced Dynamic Cavitation

Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.

Dynamic Scramjet Ignition Processes

For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.

Hydrogen vs Kerosene Fuel Sources

Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.

Conforming High Pressure Tank Technology for CNG and H2.

As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.

As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).

Enhanced Fuel Mixture During Shock Train Interaction

Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.

Improved Bow Shock Interaction

Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.

6,000+ Fahrenheit Thermal Resistance

To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.

*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope

Scramjet Propulsion Side Wall Cooling

With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.

Lower Threshold for Hypersonic Ignition

Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.

Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities

Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.

Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)

To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.

A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.

A new Rider (a watch for motorcycle riders) in the display area at Prim.

On September 26, 2008 my family and I were privileged to spend the day in the beautiful town of Nové Mesto nad Metují in the east of the Czech Republic, close to the Polish border. Our host was Mr. Jan Prokop, Marketing Director (and principal designer) at the ELTON hodinárská, a.s. - the manufacturers of fine bespoke Prim wristwatches.

Mr. Prokop collected us from our hotel in Prague, drove us to Nové Mesto nad Metují and back (a round trip of three hours), presented their current product range, guided us through their interesting museum, and led us on a tour of the full manufacturing operation at Prim. This was a fantastic opportunity, and we got to see everything from the manufacturing of cases, dials, hesatite crystals and hands through to the final assembly process. We also saw great examples of their bespoke manufacturing capability as well as their top class restoration service. Mr Prokop ended a fine day with a meal and good local beer in a restaurant on the old town square.

Six weeks after our visit I sent my prized Prim Sport "Igen" 38 (produced in the 60's and early-70's) to ELTON where it is currently being restored and modernised to my specification, as well as being personalised. I can't wait to get it back - my first bespoke wristwatch and an heirloom to pass on to my son!

Although obviously sensitive about certain parts of their operation, Mr. Prokop graciously allowed me to take many photographs during our visit, and here they are for your viewing pleasure. As you will see, these are truly hand-made watches that combine both leading edge design and manufacturing processes and age-old processes and technologies. It is this progressive traditionalism and craftsmanship that gives these unique timepieces their individual character...and I love them!

Io Aircraft - www.ioaircraft.com

Drew Blair

www.linkedin.com/in/drew-b-25485312/

io aircraft, phantom express, phantom works, boeing phantom works, lockheed skunk works, hypersonic weapon, hypersonic missile, scramjet missile, scramjet engineering, scramjet physics, boost glide, tactical glide vehicle, Boeing XS-1, htv, Air-Launched Rapid Response Weapon, (ARRW), hypersonic tactical vehicle, hypersonic plane, hypersonic aircraft, space plane, scramjet, turbine based combined cycle, ramjet, dual mode ramjet, darpa, onr, navair, afrl, air force research lab, defense science, missile defense agency, aerospike,

Advanced Additive Manufacturing for Hypersonic Aircraft

Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.

Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.

*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.

What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.

Unified Turbine Based Combined Cycle (U-TBCC)

To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5

However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.

Enhanced Dynamic Cavitation

Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.

Dynamic Scramjet Ignition Processes

For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.

Hydrogen vs Kerosene Fuel Sources

Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.

Conforming High Pressure Tank Technology for CNG and H2.

As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.

As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).

Enhanced Fuel Mixture During Shock Train Interaction

Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.

Improved Bow Shock Interaction

Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.

6,000+ Fahrenheit Thermal Resistance

To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.

*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope

Scramjet Propulsion Side Wall Cooling

With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.

Lower Threshold for Hypersonic Ignition

Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.

Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities

Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.

Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)

To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.

A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.

Io Aircraft - www.ioaircraft.com

Drew Blair

www.linkedin.com/in/drew-b-25485312/

io aircraft, phantom express, phantom works, boeing phantom works, lockheed skunk works, hypersonic weapon, hypersonic missile, scramjet missile, scramjet engineering, scramjet physics, boost glide, tactical glide vehicle, Boeing XS-1, htv, Air-Launched Rapid Response Weapon, (ARRW), hypersonic tactical vehicle, hypersonic plane, hypersonic aircraft, space plane, scramjet, turbine based combined cycle, ramjet, dual mode ramjet, darpa, onr, navair, afrl, air force research lab, defense science, missile defense agency, aerospike,

Advanced Additive Manufacturing for Hypersonic Aircraft

Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.

Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.

*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.

What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.

Unified Turbine Based Combined Cycle (U-TBCC)

To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5

However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.

Enhanced Dynamic Cavitation

Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.

Dynamic Scramjet Ignition Processes

For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.

Hydrogen vs Kerosene Fuel Sources

Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.

Conforming High Pressure Tank Technology for CNG and H2.

As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.

As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).

Enhanced Fuel Mixture During Shock Train Interaction

Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.

Improved Bow Shock Interaction

Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.

6,000+ Fahrenheit Thermal Resistance

To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.

*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope

Scramjet Propulsion Side Wall Cooling

With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.

Lower Threshold for Hypersonic Ignition

Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.

Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities

Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.

Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)

To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.

A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.

The Password:JDM Dry Carbon Fiber Engine Cover for the 2013+ Subaru BRZ / Scion FR-S will clean up the look of your engine bay! Like all of our Dry Carbon parts we manufacture, this engine cover has been precision crafted for a perfect fitment every time. We have used a fade resistant resin during the manufacturing process to ensure this plug cover will always look & function as good as the day you bought it!

Includes all necessary mounting hardware.

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Map Kernow (son of Cornwall), the Giant Cornish Miner at Kapunda, South Australia.

And giant it certainly is, you can't really appreciate the scale of the thing from this photo.

The original statue stood until 1 June 2006 when it was destroyed. A local teenager poured Eranol (molecular iodine) around the statue, splashing some of the accelerant on the statue's right leg. Although his intent was to take a photo of the statue surrounded by a "ring of fire", and he did not intend to cause significant harm to the work, the resulting fire caused $95,000 worth of damage and the statue had to be demolished.

Fortunately the statue was insured for $140,000, and the original artist Ben van Zetten agreed to rebuild the work. The new statue was rededicated on the site of the old on 3 June 2007, just over a year after the original was destroyed. The replacement was said to be "much more resistant to damage" than the original, and the artist stated that the new version looked "far better than before", as the manufacturing process allowed the bronze colouring to be more apparent.

Some friends of mine live not far from Kapunda, they said the arsonist was almost lynched by the residents.

From Barfoot's series of coloured lithographs of 1840 depicting the cotton manufacturing process.

Original text written to accompany Lithograph No.12:

"When the clear, white cloth is brought from the bleaching to the Printer, it is wound upon a box like a weaver's beam. In front, is the copper roller, coloured yellow, with a pattern engraved upon it, which dips as it turns round in the box below, which is filled with a coloured liquor. To keep this colour from fixing on the whole of the cloth, a fine thin piece of steel called The Doctor, is so placed as to scrape it off the flat or smooth parts of the roller, before it touches the cloth, leaving only the engraved parts filled. The piece runs between the engraved roller, and a large iron bowl covered with a blanket, and thus receives the impression from the engraving. It then passes upwards, over hollow iron boxes, to dry it quickly, lest the liquor should spread or run; and it is then hung up in a hot room for a few days, for dying. The liquor printed on the cloth is not the proper dye, but what is called a mordant, because it fixes upon the cloth the colour in which the pieces are afterwards dyed. Sometimes the cloth is entirely soaked in a mordant liquor, and dyed of one even colour; but a pattern may be afterwards produced by printing with what is called a solvent, to loosen or discharge it, and leave white figures. These mordants and solvents consist of preparations of alum, iron and other things, according to the colour wanted. They are also slightly coloured with dye stuff, to shew the Printer how the work is done. Thus you see that the science of Chemistry is as useful in Dying as that of Mechanics is in Weaving."

© 2012 PKG Photography, all rights reserved

Clothing or jewelry worn around the neck: this is the basic dictionary definition for a necklace; yet, there used to be much more to it than a simple fashionable accessory that completes a trendy casual or elegant dress. To the ancient people, a necklace meant a lot more than a mere decorative item: first of all, the manufacturing process was a lot more difficult than it is today, and jewels as such were plainly used to suggest some form of differentiation or belonging to a group or a class. Wood, rocks, plant beads, shells, gems and so on, were all used in the design of neck jewelry.

Past symbolism has partly survived in the special nature of a certain type of necklace: many Christians now wear a cross or a crucifix as a faith epitome. Such a necklace is considered to protect and help the wearer in difficulty by its direct connection with Jesus Christ, His Love and Sacrifice for humanity. Nevertheless, there are some who wear the cross necklace out of sheer decorative pleasure, without attaching any hidden meaning to it; such cases would definitely explain the wide variety of cross-like jewelry that is presently available on the market.

The way a woman wears a necklace is completely different from the way a man does; this is basically relevant for the fact that for the latter, the necklace is a way of drawing attention to the cleavage. A necklace doesn't suggest sexuality, it only accents femininity, charm, elegance and the fine curves of a delicate neck. Men on the other hand wear some choke-type necklace models that have a mere decorative function; yet they still send a clear message about the wearer: he is interested in good looks, trendy in style and therefore, a man of his times.

Offering a necklace as a gift is more than common nowadays, and we often have the tendency of attaching some form of emotional value to it. People come to associate a piece of jewelry with the dear one that presented it to them, and this is how mothers leave their necklaces to their daughters and so on. Even the most common necklace could mean a fortune for someone when it is about more than mere good looks. Except for such unique cases, wearing a necklace is now part of the daily routine that requires us to look nice and trendy both for ourselves and for the others.

iPlay V1

Our design had to be cheap to manufacture, with minimal manufacture processes and a low overall cost. Keeping this in mind I sketched my basic idea and then rendered it. After exporting the DXF files I lasercut them and had my first prototype.

There is an everlasting debate amongst gamers as to which console and controller is the best. I found that the PS3 controller was the most popular second being Xbox 360. The PS3 controller is symettrical unlike the Xbox controller and is so ergonomoic you can often forget you are holding it.

I illustrated the PS3 controller outline to kickstart the CAD process. My design consists of 3 layers of 5mm acrylic creating an iphone cavity depth of 10mm (iPhone 4 has a thickness of 9.3mm) and an overall thickness of 15mm. The structure would be held together with tight fit acrylic rods. I need to carry out test pieces on 2.99+-0.1mm radii to decide what are the best dimensions to use for these slots bearing in mind the lasercutter burns away material.

The whole in the bottom layer is so the device can be pushed out from the case after use.

V2

I asked some students to test the V1 prototype. They liked the product especially its simplicity. There were points that I could develop and improve.

Not all iPhone games auto orientate, hence it was essential I adapted my design so the phone could be rotated 180 degress. This would be easy by simply duplicating the button slots.

In addition to this there was no camera hole. If I were to introduce a camera holeto the design it would have to be duplicated 180 degrees to ensure photos could be taken no matter what orientation the iPhone was.

Taking this on board I designed and manufactured iPlay V2. Although acrylic rod would create a tight fit, 4 drops of dichloromethane would chemically weld the components together for a long lasting permanent fit. After this I used a buffing wheel to create round edges making the product more ergonomic to hold.

V3

Once again I asked some students for feedback on my prototype. They were impressed with how I addressed the previous issues. The only negative point raised was that it would not fit in your pocket. This was the next challenge I faced.

I considered hinging the lower two arms and making them lock into the back of the case. However this would make the design more complex and increase cost and manufacturing processes.

I moved the top pair of holes further up to better distribute the stress. I decided to split the product in half. My V3 model has alternating layers this creates cavities that allow it to be locked together together when not in use as photographed. This would easily fit in you pocket.

The problem the alternating layers created is a less ergonomic shape. Secondly there was nothing holding the two half together when placed on the phone.

In my V4 model I introduced a rubber band which kept the two half together when on the phone. It would also prevent one half form being lost. This created a new problem; the top half of the rubber band would not always line up as there was nothing guiding it. This was my next problem to solve.

V4

My final model would be made from acrylic but I was not going to buff it as that would add a manufacture process and would siginificanty increase the manufacture time. Since I was already using the laser cutter for cutting my components I thought I may aswell engrave some sort of graphics onto the top layer. I decided to remove the gaps in between the layers to make it better to hold and to remodel the rubberband tracks.

V5

I solved the problem of the inconvenient rubber band with two more locating rods on the top. These extra rods would keep the rubber band guided along the correct track. I made a MDF prototype to test my idea and it worked successfully even with coffee stirrers replicating the acrylic rod.

Satisfied with my idea I finally created an acrylic version. This required a bit more thought than previously as I had to accomodate for the thick rubber band. I decided to use 3mm acrylic instead of 5mm to create a thinner profile. This meant I needed a total of 5 layers to accomodate an iPhone 4.

Since I was already using a lasercutter and I wanted the product to appeal to gamers I decided to engrave some patterns. I was going to use a translucent coloured acrylic for the bottom layer and adjust the design so that it covers the camera and flash. This way the case will act as a camera filter and the flash/torch will produce coloured light.

Now that the product was split into halfs the individual components were so small that cutting a single iPlay V5 uses less than an A4 sized amount of 3mm acrylic (the 2D Design screenshot has an A3 page layout). This also meant that it would fit both an iPhone 4 & 5 as the rubber can stretch to accomodate for an iPhone 5. Apart from the height of the iPhone 5 the dimensions are very similair to those of the 4.

I am very pleased with the final product and getting through to the next stage with KFDS. If I were to develop the product further I would find a way to lock the two halves together when not on the phone. This could be done like a jigsaw puzzle or by manipulating the rods into a dowel joint.

Here is the mounted Nikon F->Canon EOS adapter. Because Nikon lenses have a bigger flange-to-film distance than the EOS mount, the adapter is a strictly mechanical affair.

Flange to film distance is very critical; if the adapter is not well machined, and if it's oversized, you will lose the ability to infinity focus; if it's undersized, it will lose the ability to close focus (in a human eyeball, the same problem causes shortsightedness and far sightedness).

However, given the focusing feature of this lens (you move the camera to focus, no focusing mechanism is present) this is particular lens is probably more tolerant to manufacturing tolerances on the adapter. As such (and not wanting to wait the 6 weeks for the Nikon G-mount adapter or part with $350 yet). I bought a cheap generic Chinese made adapter off eBay.

I still checked the adapter very carefully for fit, burrs left over from manufacturing processes that can scratch the mating surfaces, and to make sure that they don't short out the EF mount's electronics communication pins before putting the whole show together.

The little floating metal tab serves as a lock to lock both the Nikkor lens to the adapter and for the locking pin from the camera to lock the bayonet mount on the EOS side.

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Strobist:

580EX II Cam left through diffusion panel M1/4

430EX Cam right through diffusion panel M1/4

Fired via PW+2/PWMM

EF100mm USM Macro

The Condé Nast Building, a 48-story office tower, is the centerpiece of the 42nd Street Master Plan prepared by the 42nd Street Development Corporation, a public/private consortium created to promote the redevelopment of this traditional heart of Manhattan.

The office tower has two orientations: on the side facing Broadway it takes on the character of Times Square and its active and dynamic environment, and on the side facing 42nd Street it takes on the more sober characteristics of the mid-town Manhattan business community. The building top reflects the principal structural support system, and it expresses in a high-technology style the project's location at the intersection of Broadway and 42nd Street-"The Crossroads of the World."

In an article in the New York Times, Herbert Muschamp wrote, "The tailoring of form to context is one of the strengths of buildings designed by Fox & Fowle. That talent gets quite a workout here, in a design that tries to relate the building to the bright lights of Broadway and the masonry cliff bordering nearby Bryant Park. It excels as a piece of urban theater, with a cluster of neon signs at the base and an eruption of high technology hardware popping out of the top."

The Condé Nast Building is an environmentally responsible building. All building systems and construction technology have been evaluated for their impact on occupant health, environmental sensitivity, and energy reduction, making Four Times Square the first project of its size to adopt state-of-the-art standards for energy conservation, indoor air quality, recycling systems, and the use of sustainable manufacturing processes. The building features environmentally efficient gas-fired absorption chillers and a state of the art curtain wall with excellent shading and insulating performance. The air delivery system will provide 50% more fresh air than industry codes, and a network of recycling chutes will serve the entire building. Stringent procedures have been followed during construction as well as in the day-to-day operation of the building in order to maintain these standards. A comprehensive set of tenant guidelines has been developed as well.

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Friday, December 8th, 2017

Fortune Global Forum 2017

Guangzhou, China

8:00 AM–9:20 AM

SMART MANUFACTURING AND THE INTERNET OF THINGS

Around the world, factory floors and assembly lines are becoming highly automated, combining human ingenuity with data and technology to revolutionize product and productivity outcomes. As the notion of a “factory of the future” continues to evolve, how are companies incorporating “smart” and connected products into their manufacturing process? From sensors and robots to 3D printing and green technology, global companies are experimenting with a variety of methods to streamline, scale, and sustain their business. Here in China, manufacturers have been asked to deliver on the nation’s “Made in China 2025” strategy and are aggressively pursuing their own strategies to become smarter, greener, and more efficient. As these changes take hold, what are the implications for those doing business in China and for supply chains worldwide? And how are companies redeploying and reeducating their workforces as traditional factory jobs become automated and the need for technically proficient talent increases?

Hosted by The City of Guangzhou

Börje Ekholm, President and CEO, Ericsson Group

Till Reuter, Chief Executive Officer, KUKA

Tony Tan, Partner, Shanghai Office, McKinsey & Company

Wang Wenyin, Chairman, Amer International Group

Shoei Yamana, President and CEO, Konica Minolta

Zhang Jing, Founder and Chairman, Cedar Holdings Group

Moderator: Adam Lashinsky, Fortune

Photograph by Vivek Prakash/Fortune