[특허]System and method for divert and attitude control in flight vehicles

Raytheon Company

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System and method for divert and attitude control in flight vehicles

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G01C-023/00
미국특허분류(USC)	701/003;
출원번호	US-0572138 (2009-10-01)
등록번호	US-8306674 (2012-11-06)
발명자 / 주소	Lam, Frank C.
출원인 / 주소	Raytheon Company
대리인 / 주소	Gifford, Eric A.
인용정보	피인용 횟수 : 1 인용 특허 : 4

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A system and method is provided for thruster control in a flight vehicle. The system and method uses a proportional derivative matrix control technique to determine thrust commands in a Divert and Attitude control (DAC) system. The proportional derivative matrix control system is configured to receive pitch, roll and yaw commands as inputs, and generate thrust commands as outputs. The performance of the proportional derivative matrix controller is such that the thrust commands can achieve the desired attitude angles quickly and with reduced fuel consumption. The matrix control system can efficiently control a variety of thrusters, including asymmetric thrusters having different moment arms. The matrix control system is particularly suitable to the control of DAC systems with asymmetric thrusters that are configured for attitude control.

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1. A thruster control system for a flight vehicle comprising: only four thrusters that provide pitch, yaw and roll control; anda processor configured to receive pitch, yaw and roll commands, and responsive to the pitch, yaw and roll commands generate a plurality of thruster commands in a thrust command matrix T for the four thrusters using a matrix control technique, said processor calculating T=[B]−1 M where M is a vehicle moment matrix, B is a coupling matrix that defines a relationship between a thrust provided by the thrusters and a plurality of moments generated on the flight vehicle, and [B]−1 is a pseudo inverse of the coupling matrix B. 2. The thruster control system of claim 1 further comprising: a plurality of divert thrusters to provide divert control,wherein the processor is further configured to receive data indicating center-of-gravity shift moments in the flight vehicle while the divert thrusters are firing, andwherein the processor is further configured to compensate for the center-of-gravity shift moments with the plurality of thruster commands by subtracting a divert moment matrix from the moment matrix M. 3. The thruster control system of claim 1 wherein the processor is further configured to receive line-of-sight rate commands for the flight vehicle, and wherein the processor is further configured to generate the plurality of thruster commands responsive to the line-of-sight rate commands using the matrix control technique. 4. The thruster control system of claim 1 wherein the four thrusters comprise at least one asymmetric thruster. 5. The thruster control system of claim 1 wherein the four thrusters are part of a liquid divert and attitude control system on the flight vehicle. 6. The thruster control system of claim 1 wherein the processor is configured to generate the plurality of thruster commands for the four thrusters by generating an array of thruster values for thrust command matrix T and, if any thrust command values are negative, adding a constant vector to all of the thruster values such that all of the thruster values are positive values or zero. 7. The thruster control system of claim 1 wherein the processor is configured to generate the plurality of thruster commands for the four thrusters by generating an array of thruster values and adding a constant vector to all thruster values such that at least one thruster value is shifted to zero. 8. The thruster control system of claim 7 wherein the processor is configured to generate the plurality of thruster commands for the four thrusters by further normalizing the array of thruster values by a largest thruster value in the array of thruster values if the largest thruster value exceeds a maximum value. 9. The thruster control system of claim 8 wherein the processor is configured to generate the plurality of thruster commands for the four thrusters by further normalizing the array of thruster values by the maximum value if the largest thruster value does not exceed the maximum value. 10. The thruster control system of claim 1 wherein firing any one of the thrusters creates pitch, yaw and roll moments in the flight vehicle. 11. A thruster controller system for a flight vehicle comprising a plurality of thrusters, wherein at least one of the plurality of thrusters is asymmetric to another thruster in the plurality of thrusters, the thruster controller system comprising: a processor configured to receive: pitch, yaw and roll commands for the flight vehicle;data indicating center-of-gravity shift moments in the flight vehicle; andline-of-sight rate commands for the flight vehicle;wherein the processor is further configured to generate a plurality of thruster rate commands responsive to the pitch, yaw and roll commands and the line-of-sight commands, and configured to compensate for the center-of-gravity shift moments, using a proportional derivative matrix technique, and wherein the processor is configured to generate the plurality of thruster commands for the plurality of thrusters by generating an array of thruster values and shifting the array of thruster values such that all the thruster values are positive and at least one thruster value in the array of thruster values is shifted to zero, normalizing the array of thruster values by a largest thruster value in the array of thruster values if the largest thruster value exceeds a maximum value, and normalizing the array of thruster values by the maximum value if the largest thruster value does not exceed the maximum value. 12. A method for thruster control in a flight vehicle comprising the steps of: providing the flight vehicle with only four thrusters that provide pitch, yaw and roll control;receiving pitch, yaw and roll commands; andgenerating a plurality of thruster commands in a thrust control matrix T for the four thrusters in response to the pitch, yaw and roll commands and using a matrix control technique, said technique calculating T=[B]−1 M where M is a vehicle moment matrix, B is a coupling matrix that defines a relationship between a thrust provided by the thrusters and a plurality of moments generated on the flight vehicle, and [B]−1 is a pseudo inverse of the coupling matrix B. 13. The method of claim 12 further comprising the steps of: providing the flight vehicle with a plurality of divert thrusters to provide divert control;receiving data indicating center-of-gravity shift moments in the flight vehicle while the divert thrusters are firing; andwherein the step of generating the plurality of thruster commands comprises compensating for the center-of-gravity shift moments with the plurality of thruster commands by subtracting a divert moment matrix from the moment matrix M. 14. The method of claim 12 further comprising the steps of receiving line-of-sight rate commands for the flight vehicle; andwherein the step of generating the plurality of thruster commands comprises generating the plurality of thruster commands responsive to the line-of-sight rate commands using the proportional derivative matrix technique. 15. The method of claim 12 wherein the four thrusters comprise at least one asymmetric thruster. 16. The method of claim 12 wherein the four thrusters are part of a liquid divert and attitude control system on the flight vehicle. 17. The method of claim 12 wherein the step of generating a plurality of thruster commands for the four thrusters comprises: generating an array of thruster values; andadding a constant vector to all thruster values such that all the thruster values are positive values or zero. 18. The method of claim 12 wherein the step of generating a plurality of thruster commands for the four thrusters comprises: generating an array of thruster values; andadding a constant vector to all thruster values such that at least one thruster value in the array of thruster values is shifted to zero. 19. The method of claim 18 wherein the step of generating a plurality of thruster commands for the four thrusters further comprises: normalizing the thruster values by a largest thruster value in the array of thruster values if the largest thruster value exceeds a maximum value. 20. The method of claim 18 wherein the step of generating a plurality of thruster commands for the four thrusters further comprises: normalizing the array of thruster values by the maximum value if the largest thruster value does not exceed the maximum value.

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이 특허를 인용한 특허 피인용횟수: 1

Hindman, Richard E. Air vehicle control system and method. USP2015059037315.

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System and method for divert and attitude control in flight vehicles

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System and method for divert and attitude control in flight vehicles

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