Jam tolerant electromechanical actuation systems and methods of operation
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-005/10
B64C-005/00
출원번호
US-0469531
(2006-09-01)
등록번호
US-7410132
(2008-08-12)
발명자
/ 주소
Flatt,James E.
출원인 / 주소
Parker Hannifin Corporation
대리인 / 주소
Renner, Otto, Boisselle & Sklar
인용정보
피인용 횟수 :
4인용 특허 :
21
초록▼
In a vehicle, having a fixed supporting structure and a load movable relative thereto, a jam tolerant actuating system, a method for controlling this system including: Locating a physical coupling/decoupling mechanism between the load and an actuator assembly as close a practicable to the load; cons
In a vehicle, having a fixed supporting structure and a load movable relative thereto, a jam tolerant actuating system, a method for controlling this system including: Locating a physical coupling/decoupling mechanism between the load and an actuator assembly as close a practicable to the load; constructing the coupling/uncoupling mechanism to be reversible, and hence testable; and controlling the connection/disconnection via decision making electronics which will detect any system failure by monitoring, at a minimum: actuator main motor load and speed, and actuator output load. Also set forth are specific embodiments of pivotable rotary geared actuators as well as linear ball screw type actuators embodying the coupling/uncoupling mechanisms of this invention.
대표청구항▼
What is claimed is: 1. In an aircraft, having a fixed supporting structure and a control surface movable relative thereto, a jam tolerant actuating system including a computer, control means and at least two electromechanical actuator assemblies, each of said actuator assemblies further including a
What is claimed is: 1. In an aircraft, having a fixed supporting structure and a control surface movable relative thereto, a jam tolerant actuating system including a computer, control means and at least two electromechanical actuator assemblies, each of said actuator assemblies further including a main motor for providing motion force therefore; a load sensor and a position sensor on said actuator assembly; a coupling/decoupling mechanism, positioned at the output member of said actuator assembly, for severing the load path between said actuator assembly and said movable surface; and a disconnect actuator for providing motive force for said coupling/decoupling mechanism, a method for controlling said actuating system, comprising the steps of: a. operating said movable control surface by said actuator assembly via said main motor, as directed by said computer via Command and Power inputs through said control means; b. relaying, from said control means to said computer, a plurality of the following inputs; i. main motor speed from a main motor commutator; ii. main motor current; iii. actuator assembly output load from said load sensor; and iv. actuator assembly output position, processed to determine speed, from said position sensor; and c. completely severing, via decoupling, the load path between said actuator assembly and said movable surface, via driving said coupling/decoupling mechanism in one direction, upon the detection of a malfunction, as determined by said control means, based on at least three of the above i., ii., iii., and iv. inputs; wherein the coupling/decoupling mechanism comprises a gear train which, and wherein said completely severing step comprises driving this gear train in the one direction, upon detection of the malfunction. 2. A method as set forth in claim 1, wherein said actuator assemblies include rotary actuators. 3. A method as set forth in claim 2, wherein the rotary actuators comprise of geared rotary actuators. 4. A method as set forth in claim 1, wherein the actuator assemblies comprise linear actuators. 5. A method as set forth in claim 4, wherein the linear actuators are comprised of ball screw actuators. 6. A method as set forth in claim 5, wherein the ball screw actuator each comprises: a bidirectionally rotatable power driven ball screw; and a reciprocable ball nut having peripherally-spaced outward first surface engagement portions, driven by the ball screw. 7. A method as set forth in claim 6, wherein the ball nut is operatively connected to an output member attached to the movable surface and wherein the coupling/decoupling mechanism decouples this operative connection. 8. A method as set forth in claim 1, wherein the control surface is a primary control surface of the aircraft. 9. A method as set forth in claim 1, wherein the control surface is a secondary control surface of the aircraft. 10. A method of controlling an electromechanical actuator assembly in an aircraft having a control surface movable by the actuator assembly; said method comprising the steps of: operating the movable control surface by the actuator assembly via a main motor, and completely severing, via decoupling, a load path between the actuator assembly and the movable surface upon detection of a malfunction; wherein said completely severing step comprises driving a coupling/decoupling mechanism positioned at the output of the actuator assembly; wherein the coupling/decoupling mechanism comprises a gear train, and wherein said completely severing step comprises driving this gear train in one direction, upon detection of the malfunction. 11. A method as set forth in claim 10, wherein said gear-train-driving step comprises using a rotary motor to drive the gear train in the one direction. 12. A method as set forth in claim 11, further including the step of reversing the previous decoupling step thereby reestablishing the load path, between the actuator assembly and the movable control surface, by the rotary motor driving the coupling/decoupling mechanism in a reverse direction. 13. A method as set forth in claim 10, further including the step of reversing the previous decoupling step to reestablish the load path between the actuator assembly and the movable control surface. 14. A method as set forth in claim 10, wherein the control surface is a primary control surface of the aircraft. 15. A method as set forth in claim 10, wherein the control surface is a secondary control surface of the aircraft. 16. A method of controlling an electromechanical actuator assembly in an aircraft having a control surface movable by the actuator assembly; said method comprising the steps of: operating the movable control surface by the actuator assembly via a main motor, and completely severing, via decoupling, a load path between the actuator assembly and the movable surface upon detection of a malfunction; wherein said completely severing step comprises driving a coupling/decoupling mechanism positioned at the output of the actuator assembly; further comprising the step of testing the actuator assembly prior to the operating step. 17. A method as set forth in claim 16, wherein the testing step comprises decoupling the coupling/decoupling mechanism and then recoupling the coupling/decoupling mechanism. 18. A method as set forth in claim 17, wherein the coupling/decoupling mechanism comprises a gear train which, and wherein said completely severing step comprises driving this gear train in the one direction, upon detection of the malfunction. 19. A method as set forth in claim 18, wherein said test-decoupling step comprises driving the gear train in the one direction and said test-recoupling step comprises driving the gear train in reverse direction. 20. A method as set forth in claim 18, wherein said gear-train-driving steps comprise using a reversible rotary motor to drive the gear train in the one direction and the reverse direction. 21. A method as set forth in claim 16, wherein the control surface is a primary control surface of the aircraft. 22. A method as set forth in claim 16, wherein the control surface is a secondary control surface of the aircraft.
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