[특허]Turbine powered electromechanical actuation system

Hamilton Sundstrand Corporation

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Turbine powered electromechanical actuation system

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64G-001/40
미국특허분류(USC)	244/171.2; 244/171.1; 060/228; 060/230
출원번호	US-0692269 (2010-01-22)
등록번호	US-8727284 (2014-05-20)
발명자 / 주소	Hill, David G.
출원인 / 주소	Hamilton Sundstrand Corporation
대리인 / 주소	Cantor Colburn LLP
인용정보	피인용 횟수 : 0 인용 특허 : 10

초록
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An electromechanical actuation system (10) for a space vehicle includes a propellant source (18) and at least one turbine (14) operably connected to the propellant source (18) and rotatable by a flow of propellant (16) therefrom. At least one electrical generator (20) is operably connected to the at least one turbine (14) and is configured to convert rotation of the turbine (14) into electrical energy. At least one electromechanical actuator (12) is operably connected to the at least one electrical generator (20) such that electrical energy from the at least one electrical generator (20) drives operation of the at least one electromechanical actuator (12). A method of operating a turbine powered electromechanical actuator (12) for a space vehicle includes rotating the at least one turbine (14) via a flow of propellant (16) therethrough. Electrical energy is generated in at least one electrical generator (20) operably connected to the at least one turbine (14) and the electromechanical actuator (12) is operated with the electrical energy generated therein.

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1. An electromechanical actuation system (10) for a space vehicle comprising: a propellant source (18);at least one turbine (14) in flow communication with the propellant source (18) and rotatable by a flow of propellant (16) therefrom;at least one electrical generator (20) operably connected to the at least one turbine (14) configured to convert rotation of the at least one turbine (14) into electrical energy; andat least one electromechanical actuator (12) operably connected to the at least one electrical generator (20) such that electrical energy from the at least one electrical generator (20) drives operation of the at least one electromechanical actuator (12). 2. The electromechanical actuation system (10) of claim 1 wherein the at least one electromechanical actuator (12) is at least two electromechanical actuators (12). 3. The electromechanical actuation system (10) of claim 1 wherein a discreet electrical generator (20) of the at least one electrical generator (20) is operably connected to each electromechanical actuator (12) of the at least one electromechanical actuator (12). 4. The electromechanical actuation system (10) of claim 1 wherein the flow of propellant (16) comprises one of a hydrogen gas vented from a liquid hydrogen propellant tank (18) repressurization system, compressed helium or other gas, solid propellant gas generator, or a liquid propellant. 5. The electromechanical actuation system (10) of claim 1 further comprising at least one system controller (28) operably connected to the at least one electrical generator (20) and configured to control flow of electrical energy to the at least one electromechanical actuator (12). 6. The electromechanical actuation system (10) of claim 5 wherein the at least one system controller (28) is operably connected to a vehicle flight computer (30). 7. The electromechanical actuation system (10) of claim 1 further comprising at least one governor (24) operably connected to the at least one turbine (14) to control rotation thereof. 8. The electromechanical actuation system (10) of claim 7 further comprising a propellant control valve (26) operably connected to the at least one governor (24) to control a flow rate of flow of propellant (16) into the at least one turbine (14). 9. A method of operating a turbine powered electromechanical actuator (12) for a space vehicle comprising: delivering a flow of propellant (16) to at least one turbine (14) from a propellant source (18);rotating the at least one turbine (14) via the flow of propellant (16) through the at least one turbine (14);generating electrical energy in at least one electrical generator (20) operably connected to the at least one turbine (14) via rotation of the at least one turbine (14); andoperating the electromechanical actuator (12) with the electrical energy generated in the at least one electrical generator (20). 10. The method of claim 9 further comprising controlling a flow of electrical energy to the at least one electromechanical actuator (12) via at least one system controller (28) operably connected to the at least one electrical generator (20). 11. The method of claim 10 further comprising receiving commands from a vehicle flight computer (30) to direct the flow of electrical energy via the at least one system controller (28). 12. The method of claim 9 further comprising controlling rotation of the at least one turbine (14) via at least one speed control device (24) operably connected to the at least one turbine (14). 13. The method of claim 12 further comprising controlling a flow rate of the flow of propellant (16) into the at least one turbine (14) via a propellant control valve (26) operably connected to the at least one speed control device (24). 14. A thrust vector control system for a space vehicle main engine (34) comprising: at least two electromechanical actuators (12) operably connected to the main engine (34), one or more of electromechanical actuators (12) of the at least two electromechanical actuators (12) configured to articulate the main engine (34) in a first direction (36) and one or more electromechanical actuators (12) of the at least two electromechanical actuators (12) configured to articulate the main engine (34) in a second direction (38);a propellant source (18);at least one turbine (14) operably connected to the propellant source (18) and rotatable by a flow of propellant (16) therefrom; andat least one electrical generator (20) operably connected to the at least one turbine (14) and the at least two electromechanical actuators (12), the at least one electrical generator (20) configured to convert rotation of the turbine (14) into electrical energy which drives operation of the at least two electromechanical actuators (12). 15. The thrust vector control system of claim 14 wherein the at least one turbine (14) is at least two turbines (14). 16. The thrust vector control system of claim 15 wherein the at least one electrical generator (20) is at least two electrical generators (20), each electrical generator (20) of the at least two electrical generators (20) operably connected to one or more turbines (14) of the at least two turbines (14) and to one or more electromechanical actuators (12) of the at least two electromechanical actuators (12). 17. The thrust vector control system of claim 14 wherein the flow of propellant (16) comprises one of a hydrogen gas vented from a liquid hydrogen propellant tank (18) repressurization system, compressed helium or other gas, solid propellant gas generator, or a liquid propellant. 18. The thrust vector control system of claim 14 further comprising at least one system controller (28) operably connected to the at least one electrical generator (20) configured to control flow of electrical energy to the at least two electromechanical actuators (12). 19. The thrust vector control system of claim 14 further comprising at least one speed control device (24) operably connected to the at least one turbine (14) to control rotation thereof. 20. The thrust vector control system of claim 19 further comprising a propellant control valve (26) operably connected to the at least one speed control device (24) to control a flow rate of the flow of propellant (16) into the at least one turbine (14).

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Turbine powered electromechanical actuation system

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Turbine powered electromechanical actuation system

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IPC 상위 출원인

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IPC 상세정보(version : 201201)

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