Systems and methods for airspeed estimation using actuation signals
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64D-043/02
B64C-013/40
B64C-013/50
G01P-005/02
G01P-005/00
G01P-021/02
출원번호
US-0339206
(2014-07-23)
등록번호
US-9428279
(2016-08-30)
발명자
/ 주소
Ganguli, Subhabrata
Enns, Dale Frederick
Li, Xiahong Linda
출원인 / 주소
Honeywell International Inc.
대리인 / 주소
Fogg & Powers LLC
인용정보
피인용 횟수 :
1인용 특허 :
1
초록▼
Systems and methods for airspeed estimation using actuation signals are provided. In one embodiment, an on-board avionics airspeed estimation system is provided. The system comprises: a flight control surface for an aircraft; a control surface actuator coupled to the flight control surface, wherein
Systems and methods for airspeed estimation using actuation signals are provided. In one embodiment, an on-board avionics airspeed estimation system is provided. The system comprises: a flight control surface for an aircraft; a control surface actuator coupled to the flight control surface, wherein the control surface actuator receives an actuator control output signal from an actuator control system and drives the flight control surface into a position based on the actuator control output signal; a wind estimator coupled to a plurality of aircraft sensors, wherein the plurality of aircraft sensors output a set of aircraft measurements to the wind estimator and wherein the actuator control output signal is further provided to the wind estimator; wherein the wind estimator calculates a wind speed estimate by applying the actuator control output and the set of aircraft measurements to an onboard aircraft model.
대표청구항▼
1. An on-board avionics airspeed estimation system, the system comprising: a flight control surface for an aircraft;a control surface actuator coupled to the flight control surface, wherein the control surface actuator receives an actuator control output signal from an actuator control system and dr
1. An on-board avionics airspeed estimation system, the system comprising: a flight control surface for an aircraft;a control surface actuator coupled to the flight control surface, wherein the control surface actuator receives an actuator control output signal from an actuator control system and drives the flight control surface into a position based on the actuator control output signal; anda wind estimator coupled to a plurality of aircraft sensors, wherein the plurality of aircraft sensors output a set of aircraft measurements to the wind estimator and wherein the actuator control output signal is further provided to the wind estimator;wherein the wind estimator calculates a wind speed estimate by applying the actuator control output and the set of aircraft measurements to an onboard aircraft model. 2. The system of claim 1, further comprising a primary flight control system, wherein the actuator control system transmits the actuator control output to the control surface actuator, and wherein the actuator control output drives the flight control surface into a position dictated by the primary flight control system. 3. The system of claim 1, wherein the actuator control output represents either a hydraulic pressure signal or an electric servo current. 4. The system of claim 1, wherein the flight control surface comprises one of either a rudder, an elevator, or an aileron. 5. The system of claim 1, wherein the set of aircraft measurements comprise one or both of aircraft inertial measurements and attitude measurements. 6. The system of claim 1, wherein the set of aircraft measurements include x-axis, y-axis and z-axis acceleration measurements. 7. The system of claim 1, wherein the wind estimator further comprises: the onboard aircraft model; andan estimator coupled to the onboard aircraft model, wherein the onboard aircraft model outputs to the estimator a set of estimated aircraft signals and an error vector from a deviation between the set of estimated aircraft signals and the set of aircraft measurements from which the estimator generates the wind speed estimate; andwherein the estimator provides the wind speed estimate as a feedback input into the onboard aircraft model, adjusting the wind speed estimate to drive the error vector towards a minimum acceptable error. 8. The system of claim 7, wherein the estimator varies the wind speed estimate to drive the error vector toward zero. 9. The system of claim 7, wherein the wind estimator further includes selection logic that applies a selected set of weighted gains to the error vector based on a residual of the error vector. 10. The system of claim 7, wherein the onboard aircraft model comprises a mathematical model that estimates an expected output of the aircraft based on inputs applied to mathematical model. 11. The system of claim 1, wherein the on-board avionics airspeed estimation system further outputs an aircraft airspeed estimate by vectorially summing the wind speed estimate with an aircraft inertial velocity. 12. A method for obtaining airspeed estimates, the method comprising: calculating a set of estimated aircraft signals for an aircraft, the estimated aircraft signals calculated by applying an actuator control output to an onboard aircraft model;determining an error between the set of estimated aircraft signals and a set of measured aircraft signals;calculating a wind speed estimate from the set of estimated aircraft signals and the error;applying the wind speed estimate as a feedback input to the onboard aircraft model; anddriving the error towards a minimum error using the wind speed estimate. 13. The method of claim 12, wherein a control surface actuator receives the actuator control output signal from an actuator control system and drives a flight control surface into a position based on the actuator control output signal; and wherein the set of measured aircraft signals capture a response of the aircraft to the actuator control output. 14. The method of claim 13, wherein the actuator control output represents either a hydraulic pressure signal or an electric servo current. 15. The method of claim 13, wherein the flight control surface comprises one of either a rudder, an elevator, or an aileron. 16. The method of claim 12, wherein the set of measured aircraft signals comprise one or both of aircraft inertial measurements and attitude measurements. 17. The method of claim 12, wherein the onboard aircraft model calculates the set of estimated aircraft signals and the error from a difference between the set of estimated aircraft signals and the set of measured aircraft signals. 18. The method of claim 12, wherein driving the error towards a minimum error using the wind speed estimate further comprises varying the wind speed estimate to drive the error vector toward zero. 19. The method of claim 12, further comprising calculating an aircraft airspeed estimate from the wind speed estimate. 20. The method of claim 19, further comprising vectorially summing the wind speed estimate with an aircraft inertial velocity to calculate the aircraft airspeed estimate.
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이 특허에 인용된 특허 (1)
Arethens J. P. (Valence FRX) Goumier-Beraud P. (Valence FRX), Method and device for determining the speed of a helicopter with respect to the air.
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