[특허]Method and system for control of upstream flowfields of vehicle in supersonic or hypersonic atmospheric flight

The United States of America as represented by the Administrator of the National Aeronautics and Space Administration

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특허 상세정보

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Method and system for control of upstream flowfields of vehicle in supersonic or hypersonic atmospheric flight

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-001/38
미국특허분류(USC)	244/130; 244/204
출원번호	US-0555988 (2009-09-09)
등록번호	US-8251312 (2012-08-28)
발명자 / 주소	Daso, Endwell O. Pritchett, II, Victor E. Wang, Ten-See Farr, Rebecca Ann
출원인 / 주소	The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
대리인 / 주소	Van Bergen, Peter J.
인용정보	피인용 횟수 : 4 인용 특허 : 16

초록
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The upstream flowfield of a vehicle traveling in supersonic or hypersonic atmospheric flight is actively controlled using attribute(s) experienced by the vehicle. Sensed attribute(s) include pressure along the vehicle's outer mold line, temperature along the vehicle's outer mold line, heat flux along the vehicle's outer mold line, and/or local acceleration response of the vehicle. A non-heated, non-plasma-producing gas is injected into an upstream flowfield of the vehicle from at least one surface location along the vehicle's outer mold line. The pressur...

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1. A method of actively controlling the upstream flowfield of a vehicle traveling in supersonic or hypersonic atmospheric flight, comprising the steps of: sensing at least one attribute being experienced by a vehicle in one of supersonic and hypersonic atmospheric flight, said at least one attribute selected from the group consisting of pressure along the vehicle's outer mold line, temperature along the vehicle's outer mold line, heat flux along the vehicle's outer mold line, and local acceleration response of the vehicle;injecting a non-heated, non-plasma-producing gas into an upstream flowfield of the vehicle from at least one surface location along the vehicle's outer mold line; andadjusting pressure of said gas so-injected based on said at least one attribute so-sensed. 2. A method according to claim 1, wherein each said surface location faces said upstream flowfield. 3. A method according to claim 2, wherein said step of sensing pressure includes the step of sensing total pressure in proximity to each said surface location. 4. A method according to claim 2, wherein said step of sensing pressure includes the step of sensing fluctuating pressure at a plurality of locations along the vehicle's outer mold line. 5. A method according to claim 2, wherein said step of sensing temperature includes the step of sensing at least one of temperature and heat flux in proximity to each said surface location. 6. A method according to claim 1, wherein the vehicle includes at least one protuberance extending from the vehicle's outer mold line, and wherein said step of sensing further includes the step of sensing at least one of temperature and heat flux on each said protuberance. 7. A method according to claim 1, wherein said step of injecting includes the step of employing ambient air as said gas. 8. A method according to claim 1, wherein said step of injecting includes the step of storing a supply of said gas onboard the vehicle. 9. A method according to claim 1, wherein said gas so-injected has a Mach number selected from the group consisting of a sonic Mach number and a supersonic Mach number. 10. A method according to claim 1, wherein said step of adjusting controls said pressure of said gas so-injected at each said surface location to be approximately equal to ambient static pressure. 11. A method according to claim 1, wherein said step of adjusting controls said pressure of said gas so-injected dynamically. 12. A system for actively controlling the upstream flowfield of a vehicle traveling in supersonic or hypersonic atmospheric flight, comprising: a plurality of sensors adapted to be coupled to a vehicle capable of at least one of supersonic and hypersonic atmospheric flight, each of said sensors capable of sensing at least one attribute selected from the group consisting of pressure along the vehicle's outer mold line, temperature along the vehicle's outer mold line, heat flux along the vehicle's outer mold line, and local acceleration response of the vehicle;at least one nozzle adapted to have its exit located at a location on the vehicle's surface facing an upstream flowfield;a cold gas supply system adapted to be mounted in the vehicle and coupled to each said nozzle for delivering a cold gas thereto, wherein a non-heated, non-plasma-producing gas is injected by each said nozzle into the upstream flowfield; anda controller coupled to said sensors and said cold gas supply system for controlling pressure of said gas so-injected by each said nozzle based on each said attribute so-sensed. 13. A system as in claim 12, wherein said sensors are selected from the group consisting of total pressure sensors, fluctuating pressure sensors, temperature sensors, heat flux sensors, and accelerometers. 14. A system as in claim 12, wherein each said nozzle includes a nozzle body defined by a standardized external configuration. 15. A system as in claim 12, wherein said cold gas supply system includes means for storing a supply of said cold gas onboard the vehicle. 16. A system as in claim 12, wherein said cold gas comprises ambient air and wherein said cold gas supply system includes means for delivering the ambient air to each said nozzle. 17. A system as in claim 12, wherein each said nozzle is selected from the group consisting of sonic and supersonic nozzles. 18. A system for actively controlling the upstream flowfield of a vehicle, comprising: a vehicle capable of at least one of supersonic and hypersonic atmospheric flight, said vehicle defined by an outer mold line;a plurality of sensors adapted to be coupled to said vehicle along an outer mold line thereof, each of said sensors capable of sensing at least one attribute selected from the group consisting of pressure along said outer mold line, temperature along said outer mold line, heat flux along said outer mold line, and local acceleration response of said vehicle;at least one nozzle mounted in said vehicle, each said nozzle having an exit located at a surface of said vehicle that faces upstream thereof;a cold gas supply system mounted in said vehicle and coupled to each said nozzle for delivering a cold gas thereto, wherein a non-heated, non-plasma-producing gas is injected by each said nozzle upstream of said vehicle; anda controller coupled to said sensors and said cold gas supply system for controlling pressure of said gas so-injected by each said nozzle based on each said attribute so-sensed. 19. A system as in claim 18, wherein said sensors for sensing pressure include at least one total pressure sensor in proximity to each said surface location. 20. A system as in claim 18, wherein said sensors for sensing pressure include at least one fluctuating pressure sensor at a location along said outer mold line aft of each said surface location. 21. A system as in claim 18, wherein said sensors for sensing temperature include at least one temperature sensor in proximity to each said surface location. 22. A system as in claim 18, wherein said vehicle includes at least one protuberance extending from said outer mold line thereof, and wherein said sensors further comprise at least one temperature sensor on each said protuberance. 23. A system as in claim 22, wherein said at least one protuberance houses a radio frequency transceiver. 24. A system as in claim 18, wherein said cold gas supply system includes means for storing a supply of said gas onboard said vehicle. 25. A system as in claim 18, wherein said cold gas comprises ambient air and wherein said cold gas supply system includes means for delivering the ambient air to each said nozzle. 26. A system as in claim 18, wherein each said nozzle is selected from the group consisting of sonic and supersonic nozzles. 27. A system as in claim 18, wherein each said nozzle includes a nozzle body defined by a standardized external configuration.

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Method and system for control of upstream flowfields of vehicle in supersonic or hypersonic atmospheric flight

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Method and system for control of upstream flowfields of vehicle in supersonic or hypersonic atmospheric flight

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