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The word autumn comes from the Old French word autompne (automne in modern French), and was later normalized to the original Latin word autumnus.[2] There are rare examples of its use as early as the 14th century, but it became common only in the 16th, around the same time as fall, and the two words appear to have been used interchangeably.
Before the 16th century harvest was the term usually used to refer to the season. However as more people gradually moved from working the land to living in towns (especially those who could read and write, the only people whose use of language we now know), the word harvest lost its reference to the time of year and came to refer only to the actual activity of reaping, and fall and autumn began to replace it as a reference to the season.
The alternative word fall is now mostly a North American English word for the season. It traces its origins to old Germanic languages. The exact derivation is unclear, the Old English fiæll or feallan and the Old Norse fall all being possible candidates. However, these words all have the meaning "to fall from a height" and are clearly derived either from a common root or from each other. The term only came to denote the season in the 16th century, a contraction of Middle English expressions like "fall of the leaf" and "fall of the year".
During the 17th century, English immigration to the colonies in North America was at its peak and the new settlers took their language with them. While the term fall gradually obsolesced in Britain, it became the more common term in North America, where autumn is nonetheless preferred in scientific and, often, literary contexts.
(from wikipedia)
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.
Weight loss is important for reducing the risk of diabetes in individuals with obesity and impaired glucose homeostasis and reducing blood pressure.Neither a large amount of weight loss nor weight normalization are required to achieve these effects.Most dietary weight-loss strategies lead to reasonable weight loss of 8–10% of initial body weight, but the real challenge of treatment for
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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.
UPDATE: The event received a lot of press coverage and similar images were published in the local media so I'll share the link and allow you to draw your own conclusions.
www.sarajevo-x.com/bih/clanak/110323055#23
My thoughts: The intentions were good, bring kids and police officers together. Unfortunately, I feel that this event served to do two things that are fundamentally problematic in a country like Bosnia. First, it reinforced the message that guns are cool. In a country like Bosnia and Herzegovina where the average person will tell you that war is normal, addressing the normalization of weapons on a cultural level must be a priority or yes, there will be a war every fifty-years. Second, it reinforces the image of the police as an adversarial unit. This is problematic when one considers that this event coincides with ongoing efforts to implement community-based policing in Sarajevo.
The 2020 EPI ecosystem services issue category includes the following indicators: tree cover loss, grassland loss, and wetland loss. All indicators and composite indices in the EPI are normalized as a 0–100 proximity-to-target score, with 100 representing "at target" and 0 being furthest from the target.
Reframing the Pap Smear – Opening Reception
Monday, January 9, 2012
Venue: Art Bar
Visual Arts
Don’t fear the smear! Women’s health doctor demystifies the speculum as a tool to embrace, not avoid.
Reframe the Pap – the creation of women’s health doctor Sheila Wijayasinghe – looks at images of the speculum, the medical tool used in Pap tests to normalize the instrument by placing it in various familiar surroundings – with the view that women should be equally comfortable with regular pap testing as they would be with everyday objects.
“Pap testing is a women’s best defense against cervical cancer. Women should embrace the speculum as a tool of positivity and not fear the smear,” says Dr. Wijayasinghe.
Every year in Canada over 1,300 women are diagnosed with cervical cancer and almost 400 women will die annually of this disease. While the Pap Test itself is a short procedure, it can invoke a great deal of anxiety in women. Some women are afraid of the speculum, the plastic or metal tool used for the Pap Test, and avoid seeing their doctor.
“Art and social media are some the best tools to promote healthy life choices. By starting a conversation about rarely discussed health topics we can increase awareness and help women make active choices to support their well-being,” added Dr. Wijayasinghe.
All proceeds raised from Reframe the Pap will go towards the Immigrant Women’s Health Center (IWHC) in Toronto, a sexual health clinic serving immigrant, refugee and marginalized women across the City of Toronto.
More About Reframing the Pap Smear Here
Art Bar: The Art Bar (named after a weekly figure drawing class ongoing since 1957) is our storefront room with large windows facing Queen Street West. It is an intimate space for parties, meetings, conferences or exhibitions.
Photos by: Laynna Meyler
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 goal of "SlutWalk" is to bring together people of all genders, ages, professions, religions, ethnicities, sexual orientations, and economic statuses to create a dialogue and bring an end to attitudes that normalize victim blaming and slut shaming and to ultimately put an end to rape culture.
Licensing information: Due to the nature of this event and its goal to protect victims of violence everywhere, all photos are copyrighted and may not be used without explicit permission.
If you would like to use this photo to protect survivors of sexual assault and prevent violence, feel free to send me a request. for more information see www.slutwalkdc.com
Any other use, including embedding, is a violation of the license. Thank you and thanks for promoting the health of people and the communities they bring health to.
Taking its point of departure from this year's AV Festival theme As Slow As Possible (after John Cage), this symposium seeks to investigate how we might activate temporal concepts which are resistant to those normalized in mainstream commercially driven cultural forms.
How are artists, composers or musicians exploring time in ways that often utilize the latest digital technologies but also challenge their conventional deployment? The subject of 'Slowness', albeit in its most varied manifestations embracing multiple non-linear 'speeds' and rhythms (and thus refusing any simplistic polarization with 'speed' as such), will provide a central theme for the panel discussion, and ideas relating to how time can be multiplied, diversified, folded and suspended in contemporary art and culture will also be examined.
Eminent French philosopher Eric Alliez, cultural and music critic Paul Morley, performance art specialist and writer Laura Cull, and film theorist and philosopher John Mullarkey will draw on their unique intellectual and personal engagements with time in the history of ideas, popular culture and contemporary art in this afternoon symposium, an 'overture' of sorts to the 24 hour opening of the AV Festival. A selection of artists participating in AV Festival will present short surveys of their working practice to kick-start the proceedings. Moderated by Katherine Waugh.
Biographies
Eric Alliez is a French philosopher and Professor of Philosophy at the Centre for Research in Modern European Philosophy at Kingston University, UK. His research areas include philosophy and contemporary art, history of time and studies on Deleuze and Guattari. Publications include Capital Times: Tales from the Conquest of Time (1996), La Pensee-Matisse: portrait de l'artiste en hyperfauve (2005), L'Oeil-Cerveau: Nouvelles histories de la peinture moderne (with Jean-Clet Martin 2007)
Laura Cull is a lecturer in Performing Arts at Northumbria University in Newcastle. She is editor of Deleuze & Performance (Edinburgh University Press) and chair of the Performance & Philosophy Working Group within Performance Studies International. Her PhD develops the concept of ‘differential presence’ in performance through the philosophy of Gilles Deleuze.
Paul Morley is a cultural critic and author, he wrote for the New Musical Express from 1977 to 1983 and was the first presenter of BBC2's The Late Show. He still regularly appears on BBC2’s Newsnight Review programme. For the short-lived Channel 4 arts strand Without Walls he wrote and presented a documentary on boredom. Morley is the author of Words and Music: the history of pop in the shape of a city, Ask: The Chatter of Pop and the biographical book Nothing.
Katherine Waugh is a writer and filmmaker based in Galway. She is co-director, with Fergus Daly, of The Art of Time (2010), a film that explores philosophies of temporality in contemporary art, film and architecture. The Art of Time screens as part of the Festival at Tyneside Cinema in Newcastle on Sat 3 March.
John Mullarkey is Professor of Film and Television Studies at Kingston University, London. He has also taught philosophy and film theory at the University of Sunderland, England (1994-2004) and the University of Dundee, Scotland (2004 to 2010). He has published Bergson and Philosophy (1999), Post-Continental Philosophy: An Outline (2006), Philosophy and the Moving Image: Refractions of Reality (2010), and edited, with Beth Lord, The Continuum Companion to Continental Philosophy (2009). He is an editor of the journal Film-Philosophy, and chair of the Society for European Philosophy.
Juno's raw images were transformed, equalized and normalized, then - composed as RGB image. Resulting picture was also insignificantly tuned (contrast, sharping, color correction). Software used: GIMP 2.8.3. Raw image source: www.missionjuno.swri.edu/junocam/processing?id=633
Reframing the Pap Smear – Opening Reception
Monday, January 9, 2012
Venue: Art Bar
Visual Arts
Don’t fear the smear! Women’s health doctor demystifies the speculum as a tool to embrace, not avoid.
Reframe the Pap – the creation of women’s health doctor Sheila Wijayasinghe – looks at images of the speculum, the medical tool used in Pap tests to normalize the instrument by placing it in various familiar surroundings – with the view that women should be equally comfortable with regular pap testing as they would be with everyday objects.
“Pap testing is a women’s best defense against cervical cancer. Women should embrace the speculum as a tool of positivity and not fear the smear,” says Dr. Wijayasinghe.
Every year in Canada over 1,300 women are diagnosed with cervical cancer and almost 400 women will die annually of this disease. While the Pap Test itself is a short procedure, it can invoke a great deal of anxiety in women. Some women are afraid of the speculum, the plastic or metal tool used for the Pap Test, and avoid seeing their doctor.
“Art and social media are some the best tools to promote healthy life choices. By starting a conversation about rarely discussed health topics we can increase awareness and help women make active choices to support their well-being,” added Dr. Wijayasinghe.
All proceeds raised from Reframe the Pap will go towards the Immigrant Women’s Health Center (IWHC) in Toronto, a sexual health clinic serving immigrant, refugee and marginalized women across the City of Toronto.
More About Reframing the Pap Smear Here
Art Bar: The Art Bar (named after a weekly figure drawing class ongoing since 1957) is our storefront room with large windows facing Queen Street West. It is an intimate space for parties, meetings, conferences or exhibitions.
Photos by: Laynna Meyler
Reframing the Pap Smear – Opening Reception
Monday, January 9, 2012
Venue: Art Bar
Visual Arts
Don’t fear the smear! Women’s health doctor demystifies the speculum as a tool to embrace, not avoid.
Reframe the Pap – the creation of women’s health doctor Sheila Wijayasinghe – looks at images of the speculum, the medical tool used in Pap tests to normalize the instrument by placing it in various familiar surroundings – with the view that women should be equally comfortable with regular pap testing as they would be with everyday objects.
“Pap testing is a women’s best defense against cervical cancer. Women should embrace the speculum as a tool of positivity and not fear the smear,” says Dr. Wijayasinghe.
Every year in Canada over 1,300 women are diagnosed with cervical cancer and almost 400 women will die annually of this disease. While the Pap Test itself is a short procedure, it can invoke a great deal of anxiety in women. Some women are afraid of the speculum, the plastic or metal tool used for the Pap Test, and avoid seeing their doctor.
“Art and social media are some the best tools to promote healthy life choices. By starting a conversation about rarely discussed health topics we can increase awareness and help women make active choices to support their well-being,” added Dr. Wijayasinghe.
All proceeds raised from Reframe the Pap will go towards the Immigrant Women’s Health Center (IWHC) in Toronto, a sexual health clinic serving immigrant, refugee and marginalized women across the City of Toronto.
More About Reframing the Pap Smear Here
Art Bar: The Art Bar (named after a weekly figure drawing class ongoing since 1957) is our storefront room with large windows facing Queen Street West. It is an intimate space for parties, meetings, conferences or exhibitions.
Photos by: Laynna Meyler
April 19, 2015 - New York City - Governor Andrew M. Cuomo has dinner at the Intercontinental Hotel in New York City Sunday April 19, 2015 with leaders from business and higher education that will be joining New York's trade mission to Cuba. This is the first Governor-led state trade mission to Cuba since President Obama began the process to normalize diplomatic relations between the United States and Cuba. (Office of the Governor - Kevin P. Coughlin)
On July 20th, the Israeli-Palestinian Band, HEARTBEAT: Amplifying Youth Voices, performed at the RED Berlin Skylounge of the Institute for Cultural Diplomacy. As a positive alternative to the normalization of segregation, violence, and racism, Heartbeat creates spaces and opportunities for Palestinian and Israeli youth musicians to build critical awareness, respect, and trust while harnessing creative nonviolent tools for self-expression and social change.
Engaging in a sustained music, dialogue, and empowerment process, Heartbeat youth musicians become agents of change; harnessing the tools of creativity to imagine possibilities, ask questions, and publicly address systemic problems such as violence, oppression, and inequality-partnering to create a safe, equitable future for all.
(Berlin; July 20th, 2017)
A theoretical option for reconstruction the Hennepin Ave/Lyndale Ave confluence near downtown Minneapolis. MnDOT suggested a signalized traffic circle here in their 2007 downtown freeway study, but I think a more normalized (if small) city block would be more appropriate. Traffic volumes are such to where three of the four corners (excluding the northwest corner at Summit Ave) would need to be signalized, but these could be simple two-phase signals, with all three signal locations coordinated. The block (which I have dubbed "Lowry Square") would be 3 lanes on each side, as would Lyndale Ave to the north.
This proposal provides a significant amount of room for bicycle/pedestrian infrastructure, open space/parkland, and redevelopment.
The PAIS platform is a device portal that normalizes the interface between the myriad of Internet services and connected devices. PAIS is designed to handle multiple device and application types including in-vehicle telematics, MIDs, TVs, home theater, and smartphone apps. By creating a common, stable method for accessing a wide array of constantly changing Internet service APIs, PAIS reduces the impact of service and API changes.
Taken with the ng Connect LTE Connected Camera.
How to cold water douse:
1. Get two 5 gallon buckets and fill with cold water.
2. Get yourself barefoot standing on actual ground.
3. Dump the first bucket over your head, preferably slowly.
4.Dump the second bucket over your head, Normalize yourself with breathing,
5. Stay outside for a while, you may dry yourself with a towel, but avoid going inside immediately.
6. Now feel euphoric for the next couple of hours!
That is, a section of a cylinder where the planes intersecting are not parallel. The eye of the vortex appears to be one of the foci of the ellipse. Round objects added to stop the eye from normalizing the shape, as it will do, no matter how many times I've told it not to.
The translator talks about the exercise they just completed through Corporal Natasha Richards Royal Military Police.
Continuing police training is having a real result bringing the Afghanistan police up to speed showing modern methods of policing. Captain Damian Coxon aged 24 from Folkestone and Corporal Natasha Richards aged 30 from Eastbourne have helped in the process of building a better police service for Afghanistan.
The training is held at Musa Qala Camp where the focus has been at a lowe level training which involved demonstrations and reacting out some potential roles, going through discussing where things have gone wrong or just ways to improve better policing.
Date: 21st Feb 2010
Location: Musa Qala, Afghanistan
(Photo by Staff Sergeant Will Craig MOD/Crown Copyright 2010)
April 19, 2015 - New York City - Governor Andrew M. Cuomo has dinner at the Intercontinental Hotel in New York City Sunday April 19, 2015 with leaders from business and higher education that will be joining New York's trade mission to Cuba. This is the first Governor-led state trade mission to Cuba since President Obama began the process to normalize diplomatic relations between the United States and Cuba. (Office of the Governor - Kevin P. Coughlin)
The Horsehead nebula in Hydrogen-alpha
Astrophotography is a complex process combing optics, precise mechanical pointing & tracking, real-time guiding corrections, field derotation, environmental, and sequencing through multiple pieces of equipment that all need to “talk” to each other to automate the 66 exposure frames that were obtained here. Small corrections in focus need to be made as temperatures change, small errors in tracking are corrected using a second telescope and camera that counters the mechanical equipment limitations to keep it at level of seeing that the atmosphere allows.; periodic small adjustments in tracking, called dithering, are made to average out sensor issues that could later be mistaken for signal, then finally calibration frames are taken using a special light panel of perfectly uniform illumination…this is all done remotely and robotically controlled by a computer mounted with the scope communicating with my computer at home. My telescope could be in my backyard or halfway across the world.
After collecting the data frames called “light frames” those 66 44MB images are added together in a process called stacking. This registers, normalizes, calibrates, aligns and adds the data signal while keeping the noise as low as possible, it also normalizes gradients and artifacts due to the optics as well as light pollution. …the final preprocessed image is essentially a uniform blank gray single image about 250GB in size with no stars or nebula visible!
The post processing next takes this image and pulls or stretches the signal from the background noise (dark sky sensor dark current) makes two images: one with the stars removed and one with the stars. Those two are processed separately using different techniques to enhance the extremely dim nebula signal from the noise. Then eliminate more noise and enhance sharpness of the fine details. Finally the two Star field and nebula images are recombined in the single image you see.
Just three decades ago équipement and processing of this level were only available in professional research grade equipment costing millions of dollars. Of late, advances in signal processing software, consumer available astronomy camera grade sensors and computing power have allowed amateur astronomers to rival the best science images of only a decade before. And the cost and relative ease of entry to excellent astrophotography just over the last couple of years has decreased immensely allowing even novice astronomers with zero knowledge to press a couple power buttons and the scope, mount and software can automagically produce images that are really pretty good…all controlled on your telephone!!!
My setup is fully robotic and fully remote controlled of high end equipment designed for wide-field targets that are large and extremely dim deep space objects like nebula, star clusters and nearby galaxy clusters. As you may be able to tell it is a complex system of different equipment and software that all must to talk to each other perfectly throughout an evening(s) of imaging. So while the equipment does it thing outside in the cold or buggy heat, I can be cozy, warm and bug free away at home or sleeping. I even get warning alarms if something goes wrong (weather, clouds, dawn light or numerous other equipment issues) so if not automatically corrected that I can correct it remotely or physically need to check on the equipment. However failures are rare. While this project only involved less than a terabyte of data, some projects can collect 4+TB of data which must be off loaded remotely from the scope side SSD drives to a remote raid server.
Equipment
Telescope: WO FLT91 @540mm & f/5.9
Fattener: WO 68III (no reduction);
Camera: ZWO ASI2600MM Pro (monochromatic cooled APS-C CMOS sensor @-10°C, 100gain, 1x1bin);
Filters: Chroma Hα @ 36mm & 5nm band;
Mount: TTS160 Panther Alt-Az
Field derotation: TTS rOTAtor
Guide scope: WO RC51
Guide camera: ZWO ASI290MM
Control Computer: PLL Eagle4
Focus: PLL SS2 robotic focuser
Environment: PLL ECCO-2
Dew control: Kendrick heater straps
Flat panel: Elumiglow custom made
Image processing Computer: MacBook Pro M1
Data storage: Samsung2x 2TB SSD scope side & local OWC Mercury 4x6TB Raid
Remote Power: custom made: with LiTime 100Ah LiFePO battery, Victron Blue remote shunt, inverter, and power supply/charger
Sequencing and Processing
Remote client communications: Parallels Client
Planetarium: Cartes du Ciel & SSPro 6
Sequencing. framing & imaging: N.I.N.A.
Guiding: PHD2
Plate-solving: ASTAP
Alignment & pointing & power up: TTS custom
Communications platform: ASCOM
Focus control: NINA
Environment control: NINA
Calibration frames: NINA
Stacking & Preprocessing: APP - AstroPixelProcessor
Post processing: Pixinsight & Affinity Photo2
Image Frames
Integration time: 1hr 6min (66x60sec) Hα
Calibrations: flats and bias only
Pallet: H-alpha only
This was a fairly simple project as it involved only one Hα filter over a single evening of imaging with relatively short 60 second exposures. I can image more data with different filters and add that to the original data at a later time…
Color images however can take multiple evenings, weeks or years to collect hundreds of 3-5 minute HOS narrowband filter (Hydrogen-alpha, oxygen-III, and Sulfur-II) exposures as well as wideband short exposures of LRGB (luminence, red, blue, and green wide band pass filters) using 6 different filters for the camera. Total integration times (total exposure time) can easily be 40+hours involving thousands of light and calibration frames and multiple terabytes of data. The processing of the final image can take hours to days. So why not just use a color camera (called an “OSC” one shot color) instead of a monochrome sensor? Easy: monochrome sensors are superior and much more sensitive than OSC color cameras that must use a Bayer filter and collect only ¼ of the photons per pixel that a monochrome sensor can over the same amount of exposure time. Color cameras introduce more noise in the signal and further complicate the tracking/guiding errors due to the need for longer exposures. Plus color cameras just plain suck with color calibration and getting star colors those jeweled and bright objects that they are from the blue giants to the deep red carbon stars to all the colors in between. Also false color images are very easy to compose with a monochrome sensor!
Hope you enjoy the beauty of the invisible evening sky as much as I enjoy revealing it!!
This image is excerpted from a U.S. GAO report: www.gao.gov/products/GAO-14-450
COAST GUARD ACQUISITIONS: Better Information on Performance and Funding Needed to Address Shortfalls
Note: In current/then-year dollars. This means that numbers have not been normalized for inflation.
The Senior Center participants playing games like they did prior to the pandemic while remaining safe with their masks on and distancing.
Taking its point of departure from this year's AV Festival theme As Slow As Possible (after John Cage), this symposium seeks to investigate how we might activate temporal concepts which are resistant to those normalized in mainstream commercially driven cultural forms.
How are artists, composers or musicians exploring time in ways that often utilize the latest digital technologies but also challenge their conventional deployment? The subject of 'Slowness', albeit in its most varied manifestations embracing multiple non-linear 'speeds' and rhythms (and thus refusing any simplistic polarization with 'speed' as such), will provide a central theme for the panel discussion, and ideas relating to how time can be multiplied, diversified, folded and suspended in contemporary art and culture will also be examined.
Eminent French philosopher Eric Alliez, cultural and music critic Paul Morley, performance art specialist and writer Laura Cull, and film theorist and philosopher John Mullarkey will draw on their unique intellectual and personal engagements with time in the history of ideas, popular culture and contemporary art in this afternoon symposium, an 'overture' of sorts to the 24 hour opening of the AV Festival. A selection of artists participating in AV Festival will present short surveys of their working practice to kick-start the proceedings. Moderated by Katherine Waugh.
Biographies
Eric Alliez is a French philosopher and Professor of Philosophy at the Centre for Research in Modern European Philosophy at Kingston University, UK. His research areas include philosophy and contemporary art, history of time and studies on Deleuze and Guattari. Publications include Capital Times: Tales from the Conquest of Time (1996), La Pensee-Matisse: portrait de l'artiste en hyperfauve (2005), L'Oeil-Cerveau: Nouvelles histories de la peinture moderne (with Jean-Clet Martin 2007)
Laura Cull is a lecturer in Performing Arts at Northumbria University in Newcastle. She is editor of Deleuze & Performance (Edinburgh University Press) and chair of the Performance & Philosophy Working Group within Performance Studies International. Her PhD develops the concept of ‘differential presence’ in performance through the philosophy of Gilles Deleuze.
Paul Morley is a cultural critic and author, he wrote for the New Musical Express from 1977 to 1983 and was the first presenter of BBC2's The Late Show. He still regularly appears on BBC2’s Newsnight Review programme. For the short-lived Channel 4 arts strand Without Walls he wrote and presented a documentary on boredom. Morley is the author of Words and Music: the history of pop in the shape of a city, Ask: The Chatter of Pop and the biographical book Nothing.
Katherine Waugh is a writer and filmmaker based in Galway. She is co-director, with Fergus Daly, of The Art of Time (2010), a film that explores philosophies of temporality in contemporary art, film and architecture. The Art of Time screens as part of the Festival at Tyneside Cinema in Newcastle on Sat 3 March.
John Mullarkey is Professor of Film and Television Studies at Kingston University, London. He has also taught philosophy and film theory at the University of Sunderland, England (1994-2004) and the University of Dundee, Scotland (2004 to 2010). He has published Bergson and Philosophy (1999), Post-Continental Philosophy: An Outline (2006), Philosophy and the Moving Image: Refractions of Reality (2010), and edited, with Beth Lord, The Continuum Companion to Continental Philosophy (2009). He is an editor of the journal Film-Philosophy, and chair of the Society for European Philosophy.
Feskekôrka (Swedish: Fiskkyrkan (normalized), English: Fish church) is an indoor fish market in Gothenburg, Sweden, which got its name from the building's resemblance to a Gothic church. It opened 1 November 1874 and was drawn by the city architect Victor von Gegerfelt. Feskekôrka is an institution in Gothenburg as well as a tourist magnet, housing one of the city's oldest trades, fishing. Apart from a fish market, there is also a fish- and seafood restaurant in the building.
Hdr, 3 exposures (+2EV, 0EV, -2EV).