[특허]System and method with adaptive angle-of-attack autopilot

Raytheon Company

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

System and method with adaptive angle-of-attack autopilot

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G01C-021/00 G06F-015/18
미국특허분류(USC)	701/006; 244/181
출원번호	US-0683518 (2003-10-10)
발명자 / 주소	Warkomski,Edward J. Myers,Keith D.
출원인 / 주소	Raytheon Company
인용정보	피인용 횟수 : 1 인용 특허 : 6

초록
▼

A control system includes a rate-damping loop that uses a calculated angle-of attack error to non-linearly scale a rate-feedback signal so that at lower angle-of attack (AOA) error values, an acceleration feedback term plays a greater role in pitch compensation, while at greater angle-of-attack error values, a rate-feedback term plays a greater role in the pitch compensation. In some embodiments, a control system and method of controlling an angle-of-attack of a moving body are provided. A signal representing an angle-of-attack error is non-linearly combined with a signal representing a rate-of-change of an estimated angle-of-attack to generate a non-linear rate-damping signal. The non-linear rate-damping signal is subtracted from the signal representing the angle-of-attack error to generate a signal to control one or more elements of the moving body.

대표
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What is claimed is: 1. A method of controlling an angle-of-attack of a moving body comprising: non-linearly combining a first signal representing an angle-of-attack error with a second signal representing a rate-of-change of an estimated angle-of-attack to generate a third signal, the third signal being a non-linear rate-damping signal; and subtracting the third signal from the first signal to generate a fourth signal for controlling one or more elements of the moving body. 2. The method of claim 1 further comprising subtracting a fifth signal representing a rate-of-change of the second signal from the fourth signal to generate a control signal for controlling the one or more elements of the moving body. 3. The method of claim 2 further comprising subtracting the estimated angle-of-attack from a desired angle-of-attack to generate the first signal to represent the angle-of-attack error. 4. The method of claim 1 wherein non-linear combining comprises raising a product of the first and second signals to an exponent to generate the third signal. 5. The method of claim 2 further comprising using the control signal to control the one or more elements of the moving body to affect pitch of the moving body. 6. The method of claim 2 further comprising applying proportional-plus-integral compensation to the control signal to control the one or more elements of the moving body. 7. The method of claim 3 wherein the desired angle-of-attack is determined from an estimated velocity of the moving body, and wherein the angle-of-attack is a difference between a flight-path angle and a body angle of the moving body. 8. The method of claim 3 wherein the desired angle-of-attack is determined using a command table which provides desired angle-of-attacks for various mach estimates, and wherein the angle-of-attack is a difference between a flight-path angle and a body angle of the moving body. 9. The method of claim 3 further comprising: multiplying the first signal by a first weighting value prior to subtracting the third signal from the first signal; multiplying the second signal by a second weighting value prior to non-linearly combining the first and second signals; and multiplying the fifth signal by a third weighted value prior to subtracting the fifth signal from the fourth signal, and wherein non-linearly combining comprises non-linearly combining an absolute value the first signal with the second signal. 10. The method of claim 9 wherein the first, second, third, fourth and fifth signals are vectors, and the first, second and third weighted values are scalars having predetermined values. 11. The method of claim 3 wherein; the third signal is generated as part of a rate-damping loop, the third signal representing a non-linearly weighted rate-of-change of the estimated angle-of-attack, the fourth signal is an error signal that includes a weighted effect of the non-linear rate-damping signal, and the fifth signal represents a second derivative of the estimated angle-of-attack and is generated as part of an acceleration-damping loop. 12. The method of claim 3 further comprising: receiving a mach estimate from an airframe-state estimator for determining the desired angle-of-attack; receiving the estimated angle-of-attack from the airframe-state estimator; receiving the second signal representing the rate-of-change of the estimated angle-of-attack from the airframe-state estimator; and receiving the fifth signal representing the rate-of-change of the second signal from the airframe-state estimator. 13. The method of claim 12 wherein the moving body is an airframe comprising one of an aircraft, spacecraft, missile or guided projectile. 14. A control system for controlling angle-of-attack for a moving body comprising: a non-linear combining circuit for non-linearly combining a first signal representing an angle-of-attack error with a second signal representing a rate-of-change of an estimated angle-of-attack to generate a third signal, the third signal being a non-linear rate-damping signal; and a subtraction circuit for subtracting the third signal from the first signal to generate a fourth signal for controlling one or more elements of the moving body. 15. The control system of claim 14 wherein the subtraction circuit is a first subtraction circuit, and wherein the control system further comprises a second subtraction circuit for subtracting a fifth signal representing a rate-of-change of the second signal from the fourth signal to generate a control signal for controlling the one or more elements of the moving body. 16. The control system of claim 15 further comprising a third subtraction circuit for subtracting the estimated angle-of-attack from a desired angle-of-attack to generate the first signal to represent the angle-of-attack error, and wherein the non-linear combining circuit raises a product of the first and second signals to an exponent to generate the third signal. 17. The control system of claim 16 further comprising multiplication circuits which: multiply the first signal by a first weighting value prior to subtracting the third signal from the first signal; multiply the second signal by a second weighting value prior to non-linearly combining the first and second signals; and multiply the fifth signal by a third weighted value prior to subtracting the fifth signal from the fourth signal, and and wherein the non-linear combining circuit non-linearly combines an absolute value of the first signal with the second signal. 18. The control system of claim 16 wherein: the third signal is a non-linear rate-damping signal and is generated as part of a rate-damping loop, the third signal representing a non-linearly weighted rate-of-change of the estimated angle-of-attack; the fourth signal is an error signal that includes a weighted effect of the non-linear rate-damping signal; and the fifth signal represents a second derivative of the estimated angle-of-attack and is generated as part of an acceleration-damping loop. 19. The control system of claim 16 wherein the control system receives from an airframe-state estimator a mach estimate, the estimated angle-of-attack, the second signal representing a rate-of-change of the estimated angle-of-attack, and the fifth signal representing a rate-of-change of the second signal, and wherein the mach estimate is used by the control system for determining the desired angle-of-attack. 20. An airframe comprising: a control system to control an angle-of-attack by non-linearly combining a first signal representing an angle-of-attack error with a second signal representing a rate-of-change of an estimated angle-of-attack to generate a third signal, the third signal being a non-linear rate-damping signal, and subtracting the third signal from the first signal to generate a fourth signal for controlling one or more elements of the airframe; and an airframe-state estimator which generates at least the second signal from sensors. 21. The airframe of claim 20 wherein the control system comprises circuitry to: subtract a fifth signal representing a rate-of-change of the second signal from the fourth signal to generate a control signal for controlling the one or more elements of the moving body; subtract the estimated angle-of-attack from a desired angle-of-attack to generate the first signal to represent the angle-of-attack error; and determine the desired angle-of-attack from a mach estimate, and wherein the airframe-state estimator generates the mach estimate, the estimated angle-of-attack, and the fifth signal. 22. The airframe of claim 20 wherein the control system comprises circuitry to, as part of non-linearly combining, raise a product of the first and second signals to an exponent to generate the third signal. 23. The airframe of claim 21 wherein the angle-of-attack is a difference between a flight-path angle and a body angle of the airframe, and wherein the control signal is used to control one or more of either fins or elevators to affect pitch of the airframe. 24. The airframe of claim 23 wherein the airframe comprises one of an aircraft, spacecraft, missile, or guided projectile.

이 특허에 인용된 특허 (6)

이 특허를 인용한 특허 피인용횟수: 1

Tournes, Christian; Shtessel, Yuri. System and method for guiding and controlling a missile using high order sliding mode control. USP2013058436283.

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System and method with adaptive angle-of-attack autopilot

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System and method with adaptive angle-of-attack autopilot

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