Tilt-rotor over-torque protection from asymmetric gust
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G05D-001/00
G05D-001/06
G05D-003/00
G06F-007/00
G06F-017/00
B64C-029/00
B64C-011/30
B64C-027/08
출원번호
US-0932241
(2015-11-04)
등록번호
US-10131427
(2018-11-20)
발명자
/ 주소
Blyth, Robert Matthew
Wilkinson, Paul Raymond
출원인 / 주소
Bell Helicopter Textron Inc.
대리인 / 주소
Walton, James E.
인용정보
피인용 횟수 :
0인용 특허 :
2
초록▼
A system includes a first mast torque transfer system, a second mast torque transfer system coupled to the first mast torque transfer system, and a torque limiting system. The torque limiting system includes a first sensor configured to determine a torque of the first mast torque transfer system, a
A system includes a first mast torque transfer system, a second mast torque transfer system coupled to the first mast torque transfer system, and a torque limiting system. The torque limiting system includes a first sensor configured to determine a torque of the first mast torque transfer system, a second sensor configured to determine a torque of the second mast torque transfer system, and a processor configured to determine a differential torque between the torque of the first mast torque transfer system and the torque of the second mast torque transfer system and configured to control at least one of a torque input and a torque output to at least one of the first and second mast torque transfer systems as a function of the determined differential torque.
대표청구항▼
1. A system, comprising: a first mast torque transfer system;a second mast torque transfer system coupled to the first mast torque transfer system; anda torque limiting system, comprising: a first sensor configured to determine a torque of the first mast torque transfer system;a second sensor config
1. A system, comprising: a first mast torque transfer system;a second mast torque transfer system coupled to the first mast torque transfer system; anda torque limiting system, comprising: a first sensor configured to determine a torque of the first mast torque transfer system;a second sensor configured to determine a torque of the second mast torque transfer system; anda processor configured to determine a differential torque between the torque of the first mast torque transfer system and the torque of the second mast torque transfer system and configured to control at least one of a torque input and a torque output to at least one of the first and second mast torque transfer systems as a function of the determined differential torque. 2. The system of claim 1, wherein the processor is configured to determine a differential collective pitch command as a function of the determined differential torque. 3. The system of claim 2, wherein the processor is configured to combine the differential torque with a roll rate value and a lateral stick value. 4. The system of claim 1, wherein the processor is configured to determine a symmetric collective pitch command as a function of the determined differential torque. 5. The system of claim 4, wherein the processor is configured to combine the differential torque with a power level value and a rotor governor value. 6. The system of claim 1, wherein the processor is configured to determine a power demand signal engine command as a function of the determined differential torque. 7. The system of claim 6, wherein the processor is configured to combine the differential torque with a power demand value. 8. A method, comprising: sensing a first sensor configured to determine a torque of the first mast torque transfer system;sensing a second sensor configured to determine a torque of the second mast torque transfer system;determining a differential torque between the first mast torque transfer system and the second mast torque transfer system coupled to the first mast torque transfer system; andcontrolling at least one of a torque input and a torque output to at least one of the first and second mast torque transfer systems as a function of the determined differential torque. 9. The method of claim 8, further comprising: determining a differential collective pitch command as a function of the determined differential torque. 10. The method of claim 9, further comprising: combining the differential torque with a roll rate value and a lateral stick value. 11. The method of claim 8, further comprising: determining a symmetric collective pitch command as a function of the determined differential torque. 12. The method of claim 11, further comprising: combining the differential torque with a power level value and a rotor governor value. 13. The method of claim 8, further comprising: determining a power demand signal engine command as a function of the determined differential torque. 14. The method of claim 13, further comprising: combining the differential torque with a power demand value. 15. A tiltrotor aircraft, comprising: a first mast torque transfer system;a second mast torque transfer system coupled to the first mast torque transfer system; anda torque limiting system, comprising: first sensor configured to determine a torque of the first mast torque transfer system;a second sensor configured to determine a torque of the second mast torque transfer system; anda processor configured to determine a differential torque between the torque of the first mast torque transfer system and the torque of the second mast torque transfer system and configured to control at least one of a torque input and a torque output to at least one of the first and second mast torque transfer systems as a function of the determined differential torque. 16. The tiltrotor aircraft of claim 15, wherein the differential torque is associated with a reaction to asymmetrical wind conditions acting on a first proprotor associated with the first mast torque transfer system and a second proprotor associated with the second mast torque transfer system. 17. The tiltrotor aircraft of claim 15, wherein the determined differential torque is associated with operation of the tiltrotor aircraft being operated in an airplane mode of flight. 18. The tiltrotor aircraft of claim 15, wherein the determined differential torque is associated with operation of the tiltrotor aircraft being operated in a helicopter mode of flight. 19. The tiltrotor aircraft of claim 15, wherein the processor is configured to determine at least one of a differential collective pitch command, a symmetric collective pitch command, and a power demand signal engine command as a function of the determined differential torque. 20. The tiltrotor aircraft of claim 15, wherein the processor is configured to combine the determined differential torque with at least one of a roll rate value, a lateral stick value, a power level value, a rotor governor value, and a power demand value.
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