[특허]Dual rack and pinion rotational inerter system and method for damping movement of a flight control surface of an aircraft

The Boeing Company

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특허 상세정보

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Dual rack and pinion rotational inerter system and method for damping movement of a flight control surface of an aircraft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-005/10 F16F-007/10 B64C-013/34 F16F-015/02 F16H-019/04 B64C-009/02 F16H-025/20 F16H-025/22
출원번호	US-0867988 (2018-01-11)
등록번호	US-10107347 (2018-10-23)
발명자 / 주소	Fox, Michael T. Roach, Jeffrey M. Howell, Eric A.
출원인 / 주소	The Boeing Company
인용정보	피인용 횟수 : 0 인용 특허 : 48

초록
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There is provided a dual rack and pinion rotational inerter system for damping movement of a flight control surface of an aircraft. The system has a flexible holding structure disposed between the flight control surface and a support structure of the aircraft. The system has a dual rack and pinion assembly held by and between the flexible holding structure. The dual rack and pinion assembly has a first rack, a second rack, and a pinion engaged to and between the racks. The system has a first terminal coupled to the first rack and coupled to the flight control surface, via a pivot element, and a second terminal coupled to the second rack, and coupled to the support structure. The system has a pair of inertia wheels adjacent the flexible holding structure. The system has an axle element inserted through the inertial wheels, the flexible holding structure, and the pinion.

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1. A dual rack and pinion rotational inerter system for damping movement of a flight control surface of an aircraft, the dual rack and pinion rotational inerter system comprising: a flexible holding structure disposed between the flight control surface and a support structure of the aircraft;a dual rack and pinion assembly held by and between the flexible holding structure, the dual rack and pinion assembly comprising a first rack, a second rack, and a pinion engaged to and between the first rack and the second rack;a first terminal coupled to the first rack and coupled to the flight control surface, via a pivot element, and a second terminal coupled to the second rack, and coupled to the support structure;a pair of inertia wheels comprising a first inertia wheel adjacent to a first side of the flexible holding structure, and a second inertial wheel adjacent to a second side of the flexible holding structure; andan axle element inserted through the first inertial wheel, the flexible holding structure, the pinion, and the second inertial wheel, coupling a rotational movement of the pair of inertia wheels and the pinion,wherein rotation of the flight control surface causes translational movement, via the pivot element, of the first rack relative to the second rack, along a longitudinal inerter axis, which causes the rotational movement of the pinion and the pair of inertia wheels, such that the rotational movement of the pinion is resisted by the pair of inertia wheels, resulting in the dual rack and pinion rotational inerter system damping movement of the flight control surface. 2. The system of claim 1 further comprising a plurality of rod bearings inserted into interior corners of the flexible holding structure. 3. The system of claim 1 further comprising a sleeve element surrounding a central rectangular portion of the axle element. 4. The system of claim 1 wherein the flexible holding structure comprises one of a clamping holding structure, and a thin section flexure holding structure. 5. The system of claim 1 wherein the flexible holding structure comprises a two-piece flexible holding structure comprised of a first piece attached to a second piece, wherein the first piece is a mirror image of the second piece. 6. The system of claim 1 wherein the first rack has a first plurality of teeth, the second rack has a second plurality of teeth, and the pinion has a plurality of gear teeth, such that the plurality of gear teeth engage to and between the first plurality of teeth and the second plurality of teeth. 7. The system of claim 1 wherein the first terminal comprises a first spherical bearing having a first end coupled to the first rack, and having a second end coupled to the flight control surface, via the pivot element, and further wherein the second terminal comprises a second spherical bearing having a first end coupled to the second rack, and having a second end coupled to the support structure. 8. The system of claim 1 wherein the axle element comprises a central rectangular portion, a cylindrical portion attached to each end of the central rectangular portion, a square portion attached to each end of each cylindrical portion, and a cylindrical threaded end portion attached to each end of each square portion. 9. The system of claim 1 wherein the pinion has a through opening having a square shaped cross-section, and each of the pair of inertia wheels has a through opening having a square shaped cross-section. 10. An aircraft, comprising: a flight control surface pivotably coupled to a support structure;one or more actuators configured to actuate the flight control surface; andat least one dual rack and pinion rotational inerter system for damping movement of the flight control surface of the aircraft, the at least one dual rack and pinion rotational inerter system comprising: a flexible holding structure disposed between the flight control surface and the support structure of the aircraft;a plurality of rod bearings inserted into interior corners of the flexible holding structure;a dual rack and pinion assembly clamped by and between the flexible holding structure, the dual rack and pinion assembly comprising a first rack, a second rack, and a pinion engaged to and between the first rack and the second rack;a first terminal coupled to the first rack and coupled to the flight control surface, via a pivot element, and a second terminal coupled to the second rack, and coupled to the support structure;a pair of inertia wheels comprising a first inertia wheel adjacent to a first side of the flexible holding structure, and a second inertial wheel adjacent to a second side of the flexible holding structure; andan axle element inserted through the first inertial wheel, the flexible holding structure, the pinion, and the second inertial wheel, coupling a rotational movement of the pair of inertia wheels and the pinion,wherein rotation of the flight control surface causes translational movement, via the pivot element, of the first rack relative to the second rack, along a longitudinal inerter axis, which causes the rotational movement of the pinion and the pair of inertia wheels, such that the rotational movement of the pinion is resisted by the pair of inertia wheels, resulting in the dual rack and pinion rotational inerter system damping movement of the flight control surface. 11. The aircraft of claim 10 wherein the at least one dual rack and pinion rotational inerter system further comprises a sleeve element surrounding a central rectangular portion of the axle element. 12. The aircraft of claim 10 wherein the flexible holding structure comprises a two-piece flexible holding structure comprised of mirror image plates, each mirror image plate comprising one of, a forged plate, or an extruded plate. 13. The aircraft of claim 10 wherein the first terminal comprises a first spherical bearing having a first end coupled to the first rack, and having a second end coupled to the flight control surface, via the pivot element, and further wherein the second terminal comprises a second spherical bearing having a first end coupled to the second rack, and having a second end coupled to the support structure. 14. The aircraft of claim 10 wherein the flight control surface comprises an aileron, and the support structure comprises a wing, a wing portion support structure, or a wing spar. 15. A method for damping movement of a flight control surface of an aircraft, the method comprising the steps of: installing at least one dual rack and pinion rotational inerter system between the flight control surface and a support structure of the aircraft; the at least one dual rack and pinion rotational inerter system comprising: a flexible holding structure having a plurality of rod bearings inserted into interior corners of the flexible holding structure;a dual rack and pinion assembly clamped by and between the flexible holding structure, the dual rack and pinion assembly comprising a first rack, a second rack, and a pinion engaged to and between the first rack and the second rack;a first terminal coupled to the first rack and coupled to the flight control surface, via a pivot element, and a second terminal coupled to the second rack, and coupled to the support structure;a pair of inertia wheels comprising a first inertia wheel adjacent to a first side of the flexible holding structure, and a second inertial wheel adjacent to a second side of the flexible holding structure; andan axle element inserted through the first inertial wheel, the flexible holding structure, the pinion, and the second inertial wheel, and the axle element coupling a rotational movement of the pair of inertia wheels and the pinion,rotating the flight control surface using one or more actuators;using the at least one dual rack and pinion rotational inerter to axially accelerate and pull in a translational movement along a longitudinal inerter axis, the first rack relative to the second rack, and to cause the rotational movement of the pinion and the pair of inertia wheels, such that the rotational movement of the pinion is resisted by the pair of inertia wheels and there is no incidental motion; anddamping movement of the flight control surface, using the at least one dual rack and pinion rotational inerter. 16. The method of claim 15 wherein installing comprises installing the at least one dual rack and pinion rotational inerter system, further comprising a sleeve element surrounding a central rectangular portion of the axle element. 17. The method of claim 15 wherein installing comprises installing the at least one dual rack and pinion rotational inerter system, where the first terminal comprises a first spherical bearing having a first end coupled to the first rack, and having a second end coupled to the flight control surface, via the pivot element, and where the second terminal comprises a second spherical bearing having a first end coupled to the second rack, and having a second end coupled to the support structure. 18. The method of claim 15 wherein installing comprises installing the at least one dual rack and pinion rotational inerter system, where the flexible holding structure comprises a two-piece flexible holding structure comprised of mirror image plates, each mirror image plate comprising one of, a forged plate, or an extruded plate. 19. The method of claim 15 wherein using the at least one dual rack and pinion rotational inerter to axially accelerate and pull the first rack relative to the second rack, further comprises controlling with the axle element a clamping force of the flexible holding structure. 20. The method of claim 15 wherein damping movement of the flight control surface further comprises damping movement of the flight control surface to provide increased flutter suppression of the flight control surface, resulting in an improved hydraulic application stability and an increased efficient flight control actuation.

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Dual rack and pinion rotational inerter system and method for damping movement of a flight control surface of an aircraft

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Dual rack and pinion rotational inerter system and method for damping movement of a flight control surface of an aircraft

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