[특허]Flight control laws for constant vector flat turns

Textron Innovations Inc.

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Flight control laws for constant vector flat turns

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G05D-001/08 G06F-007/00
미국특허분류(USC)	701/003; 701/004; 701/014; 244/180; 340/979
출원번호	US-0391522 (2011-03-30)
등록번호	US-8332082 (2012-12-11)
국제출원번호	PCT/US2011/030498 (2011-03-30)
§371/§102 date	20120221 (20120221)
발명자 / 주소	Christensen, Kevin Thomas Shue, Shyhpyng Jack Caudill, Troy Sheldon
출원인 / 주소	Textron Innovations Inc.
대리인 / 주소	Walton, James E.
인용정보	피인용 횟수 : 4 인용 특허 : 0

초록
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An aircraft and method to control flat yawing turns of the aircraft while maintaining a constant vector across a ground surface. The aircraft includes a control system in data communication with control actuators, a lateral control architecture, a longitudinal control architecture, and an initialization command logic. The lateral control architecture controls the aircraft in the lateral direction, while the longitudinal control architecture controls the aircraft in the longitudinal direction. The initialization command logic automatically activates the l...

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1. An aircraft, comprising: a sensor carried by the aircraft, the sensor being adapted to sense a directional movement of the aircraft;an actuator carried by the aircraft, the actuator being utilized to control the directional movement of the aircraft; anda control system in data communication with the aircraft sensor and operably associated with the actuator, the control system having: a model adapted to decouple the directional movement of the aircraft into a lateral equation of motion and a longitudinal equation of motion;a lateral control architecture in data communication with the model, the lateral control architecture being adapted to utilize the lateral equation of motion to control the lateral motion of the aircraft;a longitudinal control architecture in data communication with the model, the longitudinal control architecture adapted to utilize the longitudinal equation of motion to control the longitudinal motion of the aircraft; andan initialization command logic in data communication with the lateral control architecture and in data communication with the longitudinal control architecture;wherein the initialization command logic selectively activates the lateral control architecture for controlling the lateral motion of the aircraft and selectively activates the longitudinal control architecture for controlling the longitudinal motion of the aircraft; andwherein the control system utilizes the lateral control architecture and the longitudinal control architecture to control speed variations of the aircraft while the aircraft maintains a constant vector heading across a ground surface. 2. The aircraft of claim 1, the aircraft further comprising: a directional controller, the directional controller being manipulated by a pilot controlling the aircraft, the directional controller being in data communication with the control system. 3. The aircraft of claim 2, the directional control architecture comprising: a directional heading control loop;a directional turn coordination control loop; anda directional yaw rate control loop. 4. The aircraft of claim 2, further comprising: a directional control latch in data communication with the directional control architecture;wherein, as the directional controller is moved out of a detent position, the directional control latch activates a constant vector flat turn motion. 5. The aircraft of claim 1, the lateral control architecture comprising: a lateral sideward groundspeed control loop;a lateral roll attitude control loop; anda lateral roll rate control loop. 6. The aircraft of claim 5, further comprising: a lateral controller carried by the aircraft, the lateral controller being manipulated by a pilot controlling the aircraft, the lateral controller creating a lateral command in data communication with the lateral sideward groundspeed control loop, the lateral roll attitude control loop, and the lateral roll rate control loop. 7. The aircraft of claim 6, further comprising: a lateral control latch in data communication with the control system;wherein, as the lateral controller is moved out of a detent position, the lateral control latch resets a lateral speed hold. 8. The aircraft of claim 1, the longitudinal control architecture comprising: a longitudinal forward speed control loop;a longitudinal pitch angle control loop; anda longitudinal pitch rate control loop. 9. The aircraft of claim 8, the longitudinal control architecture further comprising: a longitudinal controller carried by the aircraft, the longitudinal controller being manipulated by a pilot controlling the aircraft, the longitudinal controller creating a longitudinal command in data communication with the longitudinal forward speed control loop, the longitudinal pitch angle control loop, and the longitudinal pitch rate control loop. 10. The aircraft of claim 9, further comprising: a longitudinal control latch in data communication with the control system;wherein, as the longitudinal controller is moved out of a detent position, the longitudinal control latch resets a longitudinal speed hold. 11. A method to control flat yawing turns of an aircraft while maintaining a constant vector heading across a ground surface, the method comprising: sensing the speed variation of the aircraft with a sensor carried by the aircraft, the speed variation having: a longitudinal direction of motion; anda lateral direction of motion;controlling the speed variation of the aircraft with actuators operably associated with the aircraft;providing a control system in data communication with the aircraft sensor and operably associated with the actuators, the control system having: a model;a lateral control architecture;a longitudinal control architecture; andan initialization command logic in data communication with the lateral control architecture and in data communication with the longitudinal control architecture;decoupling the directional movement of the aircraft into the lateral equation of motion and the longitudinal equation of motion with the model;controlling the lateral direction of motion with a lateral control architecture, the lateral control architecture utilizing the lateral equation of motion;controlling the longitudinal direction of motion with a longitudinal control architecture, the longitudinal control architecture utilizing the longitudinal equation of motion; andselectively activating the lateral control architecture and the longitudinal control architecture with the initialization command logic;wherein the control system receives sensed speed variation data from the sensor and operably controls the actuators, thus providing selective control of the yawing turns of the aircraft while maintaining a constant vector across a ground surface. 12. The method of claim 11, the method further comprising: commanding the flat yawing turns with a directional controller manipulated by a pilot controlling the aircraft, the directional controller being operably associated with a directional control architecture, the directional control architecture being in data communication with the control system. 13. The method of claim 12, wherein the commanding of the flat yawing turns with the directional control architecture comprises: communicating data through a directional heading control loop;communicating data through a directional turn coordination control loop; andcommunicating data through a directional yaw rate control loop. 14. The method of claim 12, further comprising: activating the constant vector flat turn with a directional control latch as the directional controller is moved out of a detent position, the directional control latch being operably associated with the directional control architecture. 15. The method of claim 11, wherein controlling the lateral direction of motion with the lateral control architecture comprises: communicating lateral motion data through a lateral sideward groundspeed control loop;communicating lateral motion data through a lateral roll attitude control loop; andcommunicating lateral motion data through a lateral roll rate control loop. 16. The method of claim 11, further comprising: controlling the lateral direction of motion with a lateral controller manipulated by a pilot controlling the aircraft, the lateral controller being operably associated with the lateral control architecture. 17. The aircraft of claim 16, further comprising: resetting a lateral speed hold with a lateral control latch as the lateral controller is moved out of a detent position, the lateral control latch being in data communication with the lateral control architecture. 18. The method of claim 17, wherein controlling the longitudinal direction of motion with the longitudinal control architecture comprises: communicating longitudinal motion data through a longitudinal forward speed control loop;communicating longitudinal motion data through a longitudinal pitch angle control loop; andcommunicating longitudinal motion data through a longitudinal pitch rate control loop. 19. The aircraft of claim 11, the longitudinal control architecture further comprising: controlling the longitudinal direction of motion with a longitudinal controller manipulated by a pilot controlling the aircraft, the longitudinal controller being operably associated with the longitudinal control architecture. 20. The aircraft of claim 19, further comprising: resetting a longitudinal speed hold with a longitudinal control latch as the longitudinal controller is moved out of a detent position, the longitudinal control latch being in data communication with the longitudinal control architecture.

이 특허를 인용한 특허 피인용횟수: 4

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Flight control laws for constant vector flat turns

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Flight control laws for constant vector flat turns

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