IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0736156
(2013-01-08)
|
등록번호 |
US-8812177
(2014-08-19)
|
발명자
/ 주소 |
- Yates, Travis L.
- Linton, Bradley D.
|
출원인 / 주소 |
- Bell Helicopter Textron Inc.
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
11 |
초록
▼
According to one embodiment, an integrated aircraft trim assembly features a shaft, a mechanical stop, a trim motor, a clutch, and a measurement device. The mechanical stop device is operable to at least partially prevent rotation of the shaft outside of an allowable range of motion. The trim motor
According to one embodiment, an integrated aircraft trim assembly features a shaft, a mechanical stop, a trim motor, a clutch, and a measurement device. The mechanical stop device is operable to at least partially prevent rotation of the shaft outside of an allowable range of motion. The trim motor has an output component in mechanical communication with the shaft. The clutch separates the trim motor from the shaft. The measurement device is proximate to the shaft and operable to measure a position of the shaft and communicate the measured position to a flight control computer operable to change a position of a flight control device.
대표청구항
▼
1. A rotorcraft, comprising: a body;a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;a rotor system coupled to the power train and comprising a plurality of rotor blades;a flight control assembly operable to receive one or more pilot comma
1. A rotorcraft, comprising: a body;a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;a rotor system coupled to the power train and comprising a plurality of rotor blades;a flight control assembly operable to receive one or more pilot commands from a pilot;one or more linkages coupled between the flight control assembly and an integrated trim assembly;the integrated trim assembly comprising: a housing;a shaft at least partially disposed within the housing and coupled to the one or more linkages;a mechanical stop device disposed proximate to the housing and operable to at least partially prevent rotation of the shaft outside of an allowable range of motion; anda trim motor at least partially disposed within the housing and having an output component in mechanical communication with the shaft;a trim computer operable to send one or more trim signals to the trim motor instructing the trim motor to change a position of the output component; anda flight control computer operable to receive one or more measurements from the integrated trim assembly and instruct the rotor system to change a position of at least one of the plurality of rotor blades based on the received one or more measurements. 2. The rotorcraft of claim 1, wherein the flight control assembly comprises a cyclic flight control assembly operable to receive one or more cyclic commands from the pilot. 3. The rotorcraft of claim 1, wherein the flight control assembly comprises a collective flight control assembly operable to receive a one or more collective commands from the pilot. 4. The rotorcraft of claim 1, further comprising a clutch disposed within the housing and coupling the trim motor to the shaft. 5. The rotorcraft of claim 4, wherein the clutch is configured such that disengaging the clutch prevents the trim motor from restricting movement of the shaft. 6. The rotorcraft of claim 1, wherein the trim computer is operable to drive the flight control assembly by sending a trim signal instructing the trim motor to move the output component such that the trim motor causes the flight control assembly to move. 7. The rotorcraft of claim 1, wherein the trim computer is operable to send a trim signal instructing the trim motor to maintain the output component at a fixed position such that the output component establishes a trim position for the shaft. 8. The rotorcraft of claim 1, the integrated trim assembly further comprising a run-down damper coupled to the shaft and operable to assist the shaft in moving to a trim position established by the output component. 9. The rotorcraft of claim 1, the integrated trim assembly further comprising a shear device coupled to the shaft and configured to separate the trim motor from a portion of the shaft such that portion of the shaft may move freely in response to pilot inputs received through the flight control assembly. 10. The rotorcraft of claim 1, the integrated trim assembly further comprising at least one measurement device disposed within the housing proximate to the shaft and operable to provide the one or more measurements to the flight control computer. 11. The rotorcraft of claim 1, the integrated trim assembly further comprising a gradient spring coupled to the shaft and operable to allow the shaft to move relative to the output component. 12. The rotorcraft of claim 11, the integrated trim assembly further comprising: a first measurement device positioned between the gradient spring and the trim motor; anda second measurement device positioned proximate to the shaft opposite the gradient spring from the first measurement device, wherein the flight control computer is operable to receive instruct the rotor system to change a position of at least one of the plurality of rotor blades based a difference between a measurement from the first measurement device and a measurement from the second measurement device. 13. An integrated aircraft trim assembly, comprising: a shaft;a mechanical stop device operable to at least partially prevent rotation of the shaft outside of an allowable range of motion;a trim motor having an output component in mechanical communication with the shaft;a clutch separating the trim motor from the shaft; anda measurement device proximate to the shaft and operable to measure a position of the shaft and communicate the measured position to a flight control computer operable to change a position of a flight control device. 14. The integrated aircraft trim assembly of claim 13, further comprising a housing, wherein the shaft, the mechanical stop device, the trim motor, the clutch, and the measurement device are each at least partially disposed within the housing. 15. The integrated aircraft trim assembly of claim 13, wherein the flight control device is a rotorcraft blade. 16. The integrated aircraft trim assembly of claim 13, wherein the flight control device is an aircraft flight control surface. 17. The integrated aircraft trim assembly of claim 13, wherein the shaft is configured to mechanically communicate with a pilot control device. 18. The integrated aircraft trim assembly of claim 17, wherein the pilot control device is a pilot control stick. 19. The integrated aircraft trim assembly of claim 17, wherein the pilot control device is a set of foot pedals. 20. The integrated aircraft trim assembly of claim 17, wherein the trim motor is operable to drive the pilot control device by moving the output component such that rotation of the shaft causes the pilot control device to move. 21. The integrated aircraft trim assembly of claim 13, wherein the clutch is configured such that disengaging the clutch prevents the trim motor from restricting movement of the shaft. 22. The integrated aircraft trim assembly of claim 13, wherein the trim motor is operable to maintain the output component at a fixed position such that the output component establishes a trim position for the shaft. 23. An integrated cyclic trim assembly, comprising: a shaft;a mechanical stop device operable to at least partially prevent rotation of the shaft outside of an allowable range of motion;a measurement device proximate to the shaft and operable to measure a position of the shaft and communicate the measured position to a flight control computer operable to change a position of at least one rotor blade of a rotor system;a shear device coupled to the shaft and configured to separate the trim motor from a portion of the shaft such that portion of the shaft may move freely in response to pilot inputs received through the flight control assembly; anda damper coupled to the shaft and operable to reduce oscillations in the shaft. 24. The integrated cyclic trim assembly of claim 23, further comprising a housing, wherein the shaft, the mechanical stop device, the measurement device, the shear device, and the damper are each at least partially disposed within the housing.
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