[특허]Methods of controlling thrust in a rocket motor

Alliant Techsystems Inc.

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Methods of controlling thrust in a rocket motor

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B63H-011/00
미국특허분류(USC)	060/204; 060/228; 239/265.25
출원번호	US-0760069 (2010-04-14)
등록번호	US-8539751 (2013-09-24)
발명자 / 주소	Cover, Cary Lee Stroud, Sean Scott Piovoso, Michael Joseph Kelly, Timothy James
출원인 / 주소	Alliant Techsystems Inc.
대리인 / 주소	Traskbritt
인용정보	피인용 횟수 : 1 인용 특허 : 8

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A propulsion thrust control system and method for controlling thrust in a rocket motor includes configuring valves of an energized rocket motor to an initial total valve area according to a total thrust command. The total thrust command is converted into a commanded propellant mass flow discharge rate. A varying total valve area is computed from an error between the commanded propellant mass flow discharge rate and a calculated propellant mass flow discharge rate. The valves are reconfigured according to a distribution of the varying total valve area. Th...

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1. A method of controlling thrust in a rocket motor, comprising: configuring axial and maneuver control valves of an energized rocket motor to achieve an initial total valve area corresponding to a total thrust command;determining a commanded discharged propellant mass flow discharge rate that corresponds to the total thrust command;calculating a compensated total valve area corresponding to an error between the commanded propellant mass flow discharge rate and at least one of a calculated propellant mass flow discharge rate and a measured propellant mass flow discharge rate; andreconfiguring at least one of the axial and maneuver control valves to achieve the compensated total valve area. 2. The method of claim 1, further comprising calculating the total thrust command from at least one of a sum of all net thrust commands from each of the axial and maneuver control valves of the energized rocket motor and a maximum net thrust command. 3. The method of claim 1, further comprising: measuring a pressure within a gas generator of the energized rocket motor; andreconfiguring one or more of the axial and maneuver control valves when the pressure exceeds a pressure limit of the gas generator. 4. The method of claim 1, wherein reconfiguring at least one of the axial and maneuver control valves further comprises configuring at least one of the axial and maneuver control valves to one of a substantially maximally open position and a substantially maximally closed position in response to the error between the commanded propellant mass flow discharge rate and the at least one of the calculated propellant mass flow discharge rate and the measured propellant mass flow discharge rate. 5. The method of claim 4, further comprising reconfiguring at least one of the valves incrementally to approach the intial total valve area when a measured pressure within a gas generator of the energized rocket motor is within a threshold corresponding to the total thrust command. 6. The method of claim 1, wherein reconfiguring at least one of the axial and maneuver control valves further comprises incrementally adjusting at least one of the axial and maneuver control valves. 7. The method of claim 1, further comprising reconfiguring at least one of the axial and maneuver control values according to a priority command when the total thrust command exceeds available thrust of the energized rocket motor. 8. The method of claim 1, further comprising: calculating a burn rate from a measured pressure within a gas generator of the energized rocket motor and the compensated total valve area; andestimating the burn rate utilizing a comparison between the measured pressure and an estimated pressure. 9. A method for controlling thrust in a rocket motor, comprising: receiving net thrust commands comprising at least one thrust command for orienting a rocket motor propelled vehicle;calculating a minimum total thrust command for a gas generator of a rocket motor to meet the net thrust commands;configuring axial and maneuver control valves of the rocket motor according to the minimum total thrust command; andreconfiguring at least one of the axial and maneuver control valves to change a valve area of the axial and maneuver control valves in response to a comparison of a commanded propellant mass flow discharge rate and a calculated propellant mass flow discharge rate. 10. The method of claim 9, wherein calculating the minimum total thrust comprises calculating at least one of a sum of the net thrust commands and a sum of worst case net thrusts. 11. The method of claim 9, wherein reconfiguring at least one of the axial and maneuver control valves comprises configuring at least one of the axial and maneuver control valves to one of a substantially maximally open and a substantially maximally closed position. 12. The method of claim 9, wherein reconfiguring at least one of the axial and maneuver control valves comprises incrementally adjusting at least one of the axial and maneuver control valves in response to the minimum total thrust command. 13. The method of claim 9, further comprising calculating the commanded propellant mass flow discharge rate from the minimum total thrust command. 14. The method of claim 9, further comprising reconfiguring at least one of the axial and maneuver control valves according to a priority command when the minimum total thrust command exceeds available thrust of the rocket motor. 15. The method of claim 9, further comprising: calculating a burn rate from a measured pressure within a gas generator of the rocket motor and a total valve area; andrecalculating the burn rate utlizing a comparison between the measured pressure and an estimated pressure.

이 특허에 인용된 특허 (8)

이 특허를 인용한 특허 피인용횟수: 1

Stroud, Sean S.; Piovoso, Michael J.. Rockets, methods of rocket control and methods of rocket evaluation utilizing pressure compensation. USP2017069677504.

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Methods of controlling thrust in a rocket motor

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Methods of controlling thrust in a rocket motor

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이 특허에 인용된 특허 (8)

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