[특허]Systems and methods for controlling a magnitude of a sonic boom

Gulfstream Aerospace Corporation

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Systems and methods for controlling a magnitude of a sonic boom

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-023/00 B64C-030/00 B64D-037/00 B64C-003/38 B64C-003/42 B64C-009/00 B64C-003/18 B64C-003/20 B64C-017/10
출원번호	US-0176843 (2014-02-10)
등록번호	US-9446839 (2016-09-20)
발명자 / 주소	Freund, Donald
출원인 / 주소	Gulfstream Aerospace Corporation
대리인 / 주소	Lorenz & Kopf, LLP (LKGlobal)
인용정보	피인용 횟수 : 0 인용 특허 : 12

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Methods and systems for controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds are disclosed herein. The method includes, but is not limited to, monitoring, with a processor, a weight of the supersonic aircraft and a distribution of fuel onboard the supersonic aircraft. The method further includes, but is not limited to, determining, with the processor, that there is a deviation of the weight of the supersonic aircraft from a design-condition weight. The method still further includes, but is not limited to, controlling, with the processor, a redistribution of the fuel onboard the supersonic aircraft to adjust an amount of fuel stored within a wing to minimize a twist in the wing caused by the deviation. Such redistribution will reduce the magnitude of the sonic boom caused by the deviation.

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1. A method of controlling a magnitude of a sonic boom caused by operation of a supersonic aircraft at supersonic speeds, the method comprising the steps of: monitoring, with a processor, a weight of the supersonic aircraft and a distribution of fuel onboard the supersonic aircraft;determining, with the processor, that there is a deviation of the weight of the supersonic aircraft from a design-condition weight;controlling, with the processor, a redistribution of the fuel onboard the supersonic aircraft to adjust an amount of fuel stored within a wing to minimize a twist in the wing caused by the deviation, the fuel being redistributed to the wing when the supersonic aircraft is above a design-condition weight and the fuel being redistributed from the wing when the supersonic aircraft is below the design weight. 2. The method of claim 1, wherein the monitoring step, the determining step, and the controlling step are repeated throughout a supersonic portion of a flight of the supersonic aircraft. 3. The method of claim 2, wherein the monitoring step, the determining step, and the controlling step are repeated substantially continuously throughout the supersonic portion of the flight of the supersonic aircraft. 4. A method of controlling a magnitude of a sonic boom caused by operation of a supersonic aircraft at supersonic speeds, the method comprising the steps of: monitoring, with a processor, a weight of the supersonic aircraft and a distribution of fuel within a plurality of wing fuel tanks mounted within a wing of the supersonic aircraft;determining, with the processor, that there is a deviation of the weight of the supersonic aircraft from a design-condition weight;controlling, with the processor, a redistribution of the fuel to adjust an amount of fuel stored within the plurality of wing fuel tanks to minimize a twist in the wing caused by the deviation, the fuel being redistributed from an inboard wing fuel tank to an outboard wing fuel tank when the supersonic aircraft is above a design-condition weight and the fuel being redistributed from the outboard wing fuel tank to the inboard wing fuel tank when the supersonic aircraft is below a design condition weight. 5. The method of claim 4, wherein the controlling step comprises redistributing the fuel between the plurality of wing fuel tanks and a fuel tank disposed elsewhere on the supersonic aircraft. 6. The method of claim 5, wherein the controlling step comprises redistributing the fuel to the plurality of wing fuel tanks from the fuel tank disposed elsewhere on the supersonic aircraft when the supersonic aircraft is above the design-condition weight. 7. The method of claim 5, wherein the controlling step comprises redistributing the fuel from the plurality of wing fuel tanks to the fuel tank disposed elsewhere on the supersonic aircraft when the supersonic aircraft is below the design-condition weight. 8. The method of claim 4, wherein the controlling step comprises redistributing the fuel among the plurality of wing fuel tanks. 9. The method of claim 4, wherein the monitoring step, the determining step, and the controlling step are repeated throughout a supersonic portion of a flight of the supersonic aircraft. 10. The method of claim 9, wherein the monitoring step, the determining step, and the controlling step are repeated substantially continuously throughout the supersonic portion of the flight of the supersonic aircraft. 11. A system for controlling a magnitude of a sonic boom caused by operation of a supersonic aircraft at supersonic speeds, the system comprising: a plurality of fuel tanks fluidly coupled to one another and mounted onboard the supersonic aircraft, the plurality of fuel tanks including an inboard wing fuel tank and an outboard wing fuel tank disposed within a wing of the supersonic aircraft;a plurality of fuel sensors configured to detect a fuel state of the plurality of fuel tanks;a plurality of fuel pumps arranged to redistribute fuel between the plurality of fuel tanks; anda processor communicatively coupled with the plurality of fuel sensors and operatively coupled with the plurality of fuel pumps, the processor configured to: receive information from the plurality of fuel sensors indicative of a distribution of fuel onboard the supersonic aircraft,calculate a weight of the supersonic aircraft based, at least in part, on the distribution of the fuel onboard the supersonic aircraft,determine a deviation of the weight of the supersonic aircraft from a design-condition weight of the supersonic aircraft, andcontrol the fuel pumps to redistribute a portion of the fuel from the inboard wing fuel tank to the outboard wing fuel tank when the aircraft is above a design-condition weight and from the outboard wing fuel tank to the inboard wing fuel tank when the aircraft is below the design-condition weight when the deviation is detected to reduce an amount of wing twist caused by the deviation. 12. The system of claim 11, wherein the processor is configured to receive information, calculate a weight, determine a deviation, and control the fuel pumps repeatedly throughout a supersonic portion of the flight. 13. The system of claim 12, wherein the processor is configured to receive information, calculate a weight, determine a deviation, and control the fuel pumps substantially continuously throughout the supersonic portion of the flight. 14. The system of claim 11, wherein the processor is configured to control the fuel pumps to redistribute the portion of the fuel repeatedly throughout a supersonic portion of the flight of the supersonic aircraft.

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Systems and methods for controlling a magnitude of a sonic boom

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Systems and methods for controlling a magnitude of a sonic boom

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