[특허]Solid propellant gas control system and method

Honeywell International Inc.

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Solid propellant gas control system and method

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-009/80 F02K-009/84 F02K-009/26 F02K-009/86
미국특허분류(USC)	060/204; 060/256; 060/233; 701/013; 701/531; 244/003.2; 244/003.22; 244/171
출원번호	US-0429003 (2009-04-23)
등록번호	US-8528316 (2013-09-10)
발명자 / 주소	Baker, Mark H. Abel, Steve Woessner, George
출원인 / 주소	Honeywell International Inc.
대리인 / 주소	Ingrassia Fisher & Lorenz, P.C.
인용정보	피인용 횟수 : 5 인용 특허 : 15

초록
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Systems and methods of controlling solid propellant gas pressure and vehicle thrust are provided. Propellant gas pressure and a vehicle inertial characteristic are sensed. Propellant gas pressure commands and vehicle thrust commands are generated. A propellant gas pressure error is determined based on the propellant gas pressure commands and the sensed propellant gas pressure, and vehicle thrust error is determined based on the vehicle thrust commands and the sensed vehicle inertial characteristic. Reaction control valves are moved between closed and full-open positions based on the determined propellant gas pressure error and on the determined vehicle thrust error. The system and method allow the reaction control valves to operate at variable frequencies or at fixed frequencies. The system and method also allows propellant pressure to be commanded to follow a predetermined pressure profile or commanded to vary “on-the-fly.”

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1. A solid propellant gas control system, comprising: a solid propellant gas generator configured to generate and supply a propellant gas;a propellant state sensor configured to sense a parameter representative of propellant gas pressure and to supply pressure feedback signals representative of the sensed propellant gas pressure;a vehicle inertial motion sensor configured to sense a vehicle inertial characteristic and to supply vehicle inertial response signals representative of the sensed vehicle inertial characteristic;a plurality of reaction control valves in fluid communication with the propellant gas generator, each reaction control valve coupled to receive reaction control signals and responsive thereto to selectively move between a closed position and a full-open position; anda controller coupled to receive propellant gas pressure commands, vehicle thrust commands, the pressure feedback signals, and the vehicle inertial response signals, and configured, in response to these signals, to: (i) determine a propellant gas pressure error based on the propellant gas pressure commands and the pressure feedback signals,(ii) determine a thrust error based on the vehicle thrust commands and the vehicle inertial response signals,(iii) determine the reaction control signals based on the determined propellant gas pressure error and the determined thrust error, and(iv) supply the reaction control signals to the reaction control valves. 2. The system of claim 1, wherein the controller is further configured to apply a priority weighting factor to the determined propellant gas pressure error. 3. The system of claim 1, further comprising: a flight computer operable to supply the propellant gas pressure commands and the vehicle thrust commands. 4. The system of claim 1, wherein the solid propellant gas pressure generator comprises: a vessel defining a combustion chamber; anda solid propellant disposed within the combustion chamber, the solid propellant configured to generate the propellant gas upon being ignited. 5. The system of claim 4, wherein: the solid propellant gas generator further comprises an igniter coupled to receive an initiation signal and configured, in response thereto, to ignite the solid propellant; andthe controller is further configured to selectively supply the initiation signal. 6. The system of claim 1, further comprising: a plurality of reaction control thrust nozzles, each reaction control thrust nozzle disposed downstream of, and in fluid communication with, one of the reaction control valves, each reaction control thrust nozzle configured to generate a thrust when propellant gas flows there-through. 7. The system of claim 1, further comprising: a main thrust nozzle in fluid communication with the solid propellant gas generator to at least selectively receive propellant gas therefrom. 8. The system of claim 7, wherein the main thrust nozzle is disposed downstream of, and in fluid communication with, one of the reaction control valves. 9. The system of claim 1, further comprising: a manifold in fluid communication with the solid propellant gas generator and each reaction control valve. 10. The system of claim 1, wherein the propellant state sensor includes one or more of a propellant gas temperature sensor and a propellant gas pressure sensor. 11. A solid propellant gas control system, comprising: a vessel defining a combustion chamber; anda solid propellant disposed within the combustion chamber, the solid propellant configured to generate the propellant gas upon being ignited;a propellant state sensor configured to sense a parameter representative of propellant gas pressure and to supply pressure feedback signals representative of the sensed propellant gas pressure;a vehicle inertial sensor configured to sense a vehicle inertial characteristic and to supply vehicle inertial response signals representative of the sensed vehicle inertial characteristic;a plurality of reaction control valves in fluid communication with the combustion chamber, each reaction control valve coupled to receive reaction control signals and responsive thereto to selectively move between a closed position and a full-open position; anda controller coupled to receive propellant gas pressure commands, vehicle thrust commands, the pressure feedback signals, and the vehicle inertial response signals, and configured, in response to these signals, to: (i) determine a propellant gas pressure error based on the propellant gas pressure commands and the pressure feedback signals,(ii) determine a thrust error based on the vehicle thrust commands and the vehicle inertial response signals,(iii) apply a priority weighting factor to the determined propellant gas pressure error, to thereby generate a priority-weighted propellant gas pressure error,(iv) determine the reaction control signals based on the priority-weighted propellant gas pressure error and the determined thrust error, and(v) supply the reaction control signals to the reaction control valves. 12. The system of claim 11, further comprising: a flight computer operable to supply the propellant gas pressure commands and the vehicle thrust commands. 13. The system of claim 11, further comprising: a plurality of reaction control thrust nozzles, each reaction control thrust nozzle disposed downstream of, and in fluid communication with, one of the reaction control valves, each reaction control thrust nozzle configured to generate a thrust when propellant gas flows there-through. 14. The system of claim 11, further comprising: a main thrust nozzle in fluid communication with the combustion chamber to at least selectively receive propellant gas therefrom. 15. The system of claim 14, wherein the main thrust nozzle is disposed downstream of, and in fluid communication with, one of the reaction control valves. 16. The system of claim 11, further comprising: a manifold in fluid communication with the combustion chamber and each reaction control valve. 17. The system of claim 11, wherein the propellant state sensor includes one or more of a propellant gas temperature sensor and a propellant gas pressure sensor. 18. A method of controlling a propellant gas generation system, comprising the steps of: generating propellant gas;coupling a plurality of reaction control valves to receive the propellant gas, each of the reaction control valves movable between a closed position and a full-open position;sensing propellant gas pressure;sensing a vehicle inertial characteristic;generating propellant gas pressure commands;generating vehicle thrust commands;determining a propellant gas pressure error based on the propellant gas pressure commands and the sensed propellant gas pressure;determining a vehicle thrust error based on the vehicle thrust commands and the sensed vehicle inertial characteristic;selectively moving one or more of the reaction control valves between the closed and full-open positions based on the determined propellant gas pressure error and on the determined vehicle thrust error.

이 특허에 인용된 특허 (15)

이 특허를 인용한 특허 피인용횟수: 5

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Solid propellant gas control system and method

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Solid propellant gas control system and method

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이 특허에 인용된 특허 (15)

이 특허를 인용한 특허 피인용횟수: 5

IPC 상위 출원인

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