[특허]Actuation control system

Hamilton Sundstrand Corporation

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특허 상세정보

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Actuation control system

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-001/76 G06F-019/00
미국특허분류(USC)	701/003; 701/100; 060/228
출원번호	US-0083826 (2011-04-11)
등록번호	US-8583294 (2013-11-12)
발명자 / 주소	Villano, William E. Gibbons, Kevin Jones, Teddy L. Recck, Francis W.
출원인 / 주소	Hamilton Sundstrand Corporation
대리인 / 주소	Kinney & Lange, P.A.
인용정보	피인용 횟수 : 2 인용 특허 : 9

초록

A dual redundant actuation control system for controlling a plurality of actuators for positioning a plurality of moveable aircraft components. The actuation control system includes a component controller. The component controller includes two component control channels. Each of the plurality of actuators is electrically connected to each of the two component control channels such that either of the two component control channels may control any or all of the plurality of actuators.

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1. A dual redundant actuation control system for controlling a plurality of actuators for positioning a plurality of moveable aircraft components, the system comprising: a component controller comprising two component control channels;wherein each of the plurality of actuators is electrically connected to each of the two component control channels such that either of the two component control channels may control any or all of the plurality of actuators; anda full authority digital engine controller (FADEC) electrically connected to the component controller, the FADEC comprising two channels;wherein each of the two FADEC channels is electrically connected to each of the two control channels such that either or both of the two FADEC channels may communicate with either or both of the two control channels for providing command instructions to the component controller and for receiving status information from the component controller. 2. The system of claim 1, wherein the component controller controls each of the two actuators to drive the plurality of moveable aircraft components to failsafe positions in response to a failure to receive command instructions from the FADEC. 3. The system of claim 1, wherein each of the two FADEC channels comprise a multi-drop digital bus. 4. The system of claim 1, wherein the plurality of moveable aircraft components consist of a pair of variable area fan nozzle doors for varying the fan nozzle cross-sectional area of an aircraft engine. 5. The system of claim 1, wherein the plurality of moveable aircraft components each comprise a variable area fan nozzle door for varying the fan nozzle cross-sectional area of an aircraft engine. 6. A variable area fan nozzle actuation system for an aircraft engine comprising: a variable area fan nozzle (VAFN) for varying the fan nozzle cross-sectional area of the aircraft engine, the VAFN comprising: a first VAFN door; anda second VAFN door; anda control system for controlling the position of the VAFN doors, the control system comprising: a first actuator attached to the first VAFN door for moving the first VAFN door;a second actuator attached to a second VAFN door for moving the second VAFN door;a VAFN controller linked to each of the first actuator and the second actuator, the VAFN controller comprising: a first VAFN control channel;a second VAFN control channel; anda channel communication link;wherein the first VAFN control channel is electrically connected to each of the first actuator and the second actuator to communicate control information between the VAFN controller and the first and second actuators; and the second VAFN control channel is electrically connected to each of the first actuator and the second actuator to communicate control information between the VAFN controller and the first and second actuators;wherein at least one of the VAFN control channels controls the first actuator and the same at least one of the VAFN control channels controls the second actuator. 7. The variable area fan nozzle actuation system of claim 6, further comprising: a first proximity sensor for sensing a position of the first VAFN door; anda second proximity sensor for sensing a position of the second VAFN door;wherein the first proximity sensor is electrically connected to each of the first VAFN control channel and the second VAFN control channel for providing information on the position of the first VAFN door to the VAFN controller; and the second proximity sensor is electrically connected to each of the first VAFN control channel and the second VAFN control channel for providing information on the position of the second VAFN door to the VAFN controller;wherein at least one of the VAFN control channels controls the first actuator at least partially in response to the information on the position of the first VAFN door; and the same at least one of the VAFN control channels controls the second actuator at least partially in response to the information on the position of the second VAFN door. 8. The variable area fan nozzle actuation system of claim 6, further comprising: a full authority digital engine controller (FADEC) electrically connected to the VAFN controller, the FADEC comprising: a first engine control channel; anda second engine control channel;wherein the first engine control channel is electrically connected to each of the first VAFN control channel and the second VAFN control channel; and the second engine control channel is electrically connected to each of the first VAFN control channel and the second VAFN control channel;wherein the FADEC provides command instructions to the VAFN controller and receives status information from the VAFN controller by employing at least one of the first engine control channel and the second communication channel. 9. The variable area fan nozzle actuation system of claim 8, wherein the VAFN controller controls the first actuator to drive the first VAFN door to a failsafe position, and the VAFN controller controls the second actuator to drive the second VAFN door to a failsafe position in response to a failure to receive command instructions from the FADEC. 10. The variable area fan nozzle actuation system of claim 8, wherein the first engine control channel and the second engine control channel each comprise a multi-drop digital bus. 11. The variable area fan nozzle actuation system of claim 6, wherein: the first actuator comprises: a first drive motor electrically connected to the first VAFN control channel;a first brake physically connected to the first drive motor, and electrically connected to the first VAFN control channel;a second drive motor electrically connected to the second VAFN control channel;a second brake physically connected to the second drive motor, and electrically connected to the second VAFN control channel; anda first summing gearbox physically connected to each of the first drive motor and the second drive motor and physically connected to a first shaft attached to the first VAFN door;wherein at least one of the first drive motor and the second drive motor operate through the first summing gearbox to move the first VAFN door in response to control information from the VAFN controller, and the first brake and the second brake operate on their respective connected drive motor to halt movement of their respective connected drive motor in response to control information from the VAFN controller; andthe second actuator comprises: a third drive motor electrically connected to the first VAFN control channel;a third brake physically connected to the third drive motor, and electrically connected to the first VAFN control channel;a fourth drive motor electrically connected to the second VAFN control channel;a fourth brake physically connected to the fourth drive motor, and electrically connected to the second VAFN control channel; anda second summing gearbox physically connected to each of the third drive motor and the fourth drive motor and physically connected to a second shaft attached to the second VAFN door;wherein at least one of the third drive motor and the fourth drive motors operate through the second summing gearbox to move the second VAFN door in response to control information from the VAFN controller, and the third brake and the fourth brake operate on their respective connected drive motor to halt movement of their respective connected drive motor in response to control information from the VAFN controller. 12. The variable area fan nozzle actuation system of claim 11, wherein: the first drive motor comprises a first resolver for measuring rotational position of the first drive motor, wherein the rotational position is communicated to the first VAFN control channel;the second drive motor comprises a second resolver for measuring rotational position of the second drive motor, wherein the rotational position is communicated to the second VAFN control channel;the third drive motor comprises a third resolver for measuring rotational position of the third drive motor, wherein the rotational position is communicated to the first VAFN control channel; andthe fourth drive motor comprises a fourth resolver for measuring rotational position of the fourth drive motor, wherein the rotational position is communicated to the second VAFN control channel. 13. The variable area fan nozzle actuation system of claim 12, wherein the control information from the VAFN controller causing any of the first, second, third, and fourth brakes to halt movement of their respective connected drive motor is determined at least partially from the rotational position measured by the resolver for the drive motor. 14. The variable area fan nozzle actuation system of claim 11, wherein, the first actuator further comprises: a first gearbox sensor electrically connected to the first VAFN control channel and physically connected to the first summing gearbox for measuring rotational position of the first drive motor, wherein the rotational position is provided to the first VAFN control channel;a second gearbox sensor electrically connected to the second VAFN control channel and physically connected to the first summing gearbox for measuring rotational position of the second drive motor, wherein the rotational position is provided to the second VAFN control channel;the second actuator further comprises: a third gearbox sensor electrically connected to the first VAFN control channel and physically connected to the second summing gearbox for measuring rotational position of the third drive motor, wherein the rotational position is provided to the first VAFN control channel;a fourth gearbox sensor electrically connected to the second VAFN control channel and physically connected to the second summing gearbox for measuring rotational position of the fourth drive motor, wherein the rotational position is provided to the second VAFN control channel;wherein the VAFN controller controls the first actuator at least partially in response to the rotational position measurements of the first and second gearbox sensors of the first summing gearbox; and the VAFN controller controls the second actuator at least partially in response to the rotational position measurements of the third and fourth gearbox sensors of the second summing gearbox. 15. The variable area fan nozzle actuation system of claim 14, wherein the control information from the VAFN controller causing any of the first, second, third, and fourth brakes to halt movement of their respective connected drive motor is determined at least partially from the rotational position measured by the gearbox sensor for the drive motor. 16. The variable area fan nozzle actuation system of claim 15, wherein the first, second, third, and fourth gearbox sensors comprise at least one of a rotary variable differential transformer, a linear variable differential transformer, and a rotary encoder. 17. A method of controlling an actuator for positioning a moveable aircraft component, the method comprising: connecting electrically a first component channel of a component controller to an actuator attached to the moveable aircraft component;connecting electrically a second component channel of the component controller to the actuator;detecting a position of the moveable aircraft component with a first position sensor and a second position sensor; andcontrolling the actuator in response to the detected position of the moveable aircraft component, wherein controlling the actuator comprises: controlling a first portion of the actuator with the first component channel in response to the position detected by the first position sensor; andcontrolling a second portion of the actuator with the second component channel in response to the position detected by the second position sensor. 18. The method of claim 17, wherein controlling the first portion of the actuator with the first component channel comprises braking the first portion of the actuator.

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Actuation control system

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Actuation control system

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