Systems and methods for controlling a magnitude of a sonic boom
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-023/00
B64C-030/00
B64C-037/00
B64C-003/38
B64C-003/42
B64C-009/00
B64C-003/18
B64C-003/20
B64C-017/10
B64D-037/00
출원번호
US-0176879
(2014-02-10)
등록번호
US-9580169
(2017-02-28)
발명자
/ 주소
Freund, Donald
출원인 / 주소
Gulfstream Aerospace Corporation
대리인 / 주소
Lorenz & Kopf, LLP (LKGlobal)
인용정보
피인용 횟수 :
0인용 특허 :
13
초록▼
A system for controlling a magnitude of a sonic boom caused by off-design operation of a supersonic aircraft includes a sensor configured to detect a condition of the supersonic aircraft. The system further includes a control surface that is mounted to a wing of the supersonic aircraft. The system s
A system for controlling a magnitude of a sonic boom caused by off-design operation of a supersonic aircraft includes a sensor configured to detect a condition of the supersonic aircraft. The system further includes a control surface that is mounted to a wing of the supersonic aircraft. The system still further includes a processor communicatively coupled to the sensor and operatively coupled with the control surface. The processor is configured to (1) receive information from the sensor indicative of the condition of the supersonic aircraft, (2) determine that there is a deviation between a lift distribution and a design-condition lift distribution based on the information, and (3) control the control surface to move in a manner that reduces the deviation. The magnitude of the sonic boom is reduced when the deviation is reduced.
대표청구항▼
1. A system for controlling a magnitude of a sonic boom caused by operation of a supersonic aircraft at supersonic speeds, the system comprising: a sensor configured to detect a condition of the supersonic aircraft;a control surface mounted to a wing of the supersonic aircraft; anda processor commun
1. A system for controlling a magnitude of a sonic boom caused by operation of a supersonic aircraft at supersonic speeds, the system comprising: a sensor configured to detect a condition of the supersonic aircraft;a control surface mounted to a wing of the supersonic aircraft; anda processor communicatively coupled to the sensor and operatively coupled with the control surface, the processor configured to: receive information from the sensor indicative of the condition of the supersonic aircraft,determine that there is a deviation between a lift distribution and a design-condition lift distribution based, at least in part on the information, andcontrol the control surface to move in a manner that reduces the deviation,wherein the processor is configured to control the control surface in a manner that applies a torsion force to the wing, the torsion force causing the wing to twist in a nose-up direction when the processor determines that the condition of the supersonic aircraft will cause the wing to twist in a nose-down direction, and the torsion force causing the wing to twist in a nose-down direction when the processor determines that the condition of the supersonic aircraft will cause the wing to twist in a nose-up direction andwherein the condition comprises one of an off-design condition weight of the supersonic aircraft and an off-design condition velocity of the supersonic aircraft. 2. The method of claim 1, wherein sensing the condition comprises sensing an off-design-condition weight of the supersonic aircraft. 3. The method of claim 1, wherein sensing the condition comprises sensing an off-design-condition velocity of the supersonic aircraft. 4. The system of claim 1, wherein the control surface is associated with a trailing end of the wing. 5. The system of claim 4, wherein the control surface comprises an aileron. 6. The system of claim 1, wherein the control surface comprises an aileron and wherein the processor is configured to move the aileron to an aft-end-up position when the processor determines that the condition of the supersonic aircraft will cause the wing to twist in a nose-down direction and wherein the processor is configured to move the aileron to an aft-end-down position when the processor determines that the condition of the supersonic aircraft will cause the wing to twist in a nose-up direction. 7. The system of claim 1, wherein the processor is configured to receive the information, determine the deviation, and control the control surface repeatedly throughout a supersonic portion of a flight of the supersonic aircraft. 8. The system of claim 7, wherein the processor is configured to receive the information, determine the deviation, and control the control surface substantially continuously throughout the supersonic portion of the flight of the supersonic aircraft. 9. The system of claim 1, wherein the processor is configured to control the control surface in a manner that eliminates the deviation. 10. 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: sensing a condition of the supersonic aircraft;receiving, at a processor, information indicative of the condition;determining, with the processor, that there is a deviation between a lift distribution of the supersonic aircraft and a design-condition lift distribution based, at least in part, on the information; andcontrolling, with the processor, a control surface mounted to a wing of the supersonic aircraft in a manner that reduces the deviation,wherein controlling the control surface comprises controlling the control surface in a manner that applies a torsion force to the wing, the torsion force causing the wing to twist in a nose-up direction when the condition of the supersonic aircraft causes the wing to twist in a nose-down direction, and the torsion force causing the wing to twist in a nose-down direction when the condition of the supersonic aircraft causes the wing to twist in a nose-up direction, andwherein the condition comprises one of an off-design condition weight of the supersonic aircraft and an off-design condition velocity of the supersonic aircraft. 11. The method of claim 10, wherein sensing the condition comprises sensing an off-design-condition weight of the supersonic aircraft. 12. The method of claim 10, wherein sensing the condition comprises sensing an off-design-condition speed of the supersonic aircraft. 13. The method of claim 10, wherein controlling the control surface comprises controlling a control surface associated with a trailing end of the wing. 14. The method of claim 13, wherein controlling the control surface comprises controlling an aileron. 15. The method of claim 10, wherein controlling the control surface comprises moving an aileron to an aft-end-up position when the condition of the supersonic aircraft causes the wing to twist in a nose-down direction and moving the aileron to an aft-end-down position when condition of the supersonic aircraft causes the wing to twist in a nose-up direction. 16. The method of claim 10, wherein the sensing step, the receiving step, the determining step, and the controlling step are repeated throughout a supersonic portion of a flight of the supersonic aircraft. 17. The method of claim 16, wherein the sensing step, the receiving step, the determining step, and the controlling step are repeated substantially continuously throughout a supersonic portion of a flight of the supersonic aircraft. 18. The method of claim 10, wherein controlling the control surface comprises controlling the control surface in a manner that eliminates the deviation.
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