[특허]Rudder bias gain changer

LEARJET INC.

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특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Rudder bias gain changer

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-013/24 B64C-013/28 B64C-013/26 B64C-013/40
출원번호	US-0232408 (2011-07-26)
등록번호	US-9561846 (2017-02-07)
국제출원번호	PCT/US2011/045269 (2011-07-26)
§371/§102 date	20140113 (20140113)
국제공개번호	WO2013/015783 (2013-01-31)
발명자 / 주소	Butler, III, Harris K. Veletas, Mihalis
출원인 / 주소	LEARJET INC.
대리인 / 주소	Thomas & Karceski, PC
인용정보	피인용 횟수 : 0 인용 특허 : 5

초록
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A bias gain system for aircraft rudder comprises a pair of connector ends receiving an actuation force from a bias actuator. A rudder bar interface is positioned between the connector ends. The interface rotates about the rudder bar as a function of the actuation forces from the bias actuators. A mechanism comprises links and joints between the connector ends and the rudder bar is actuatable between a contracted configuration, in which first moment arms are defined between the connector ends and the rudder bar interface, and an expanded gain configuration, in which second moment arms have a greater dimension than the first moment arms. An actuator is connected to the mechanism to actuate the mechanism to actuate the mechanism independently from the actuation forces from the bias actuators, to move the mechanism between configurations. An aircraft and a method for controlling a torque on a rudder bar of an aircraft are also provided.

대표
청구항
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1. A bias gain system for aircraft rudder, comprising: a pair of bias actuators;a pair of connector ends, each of said connector ends receiving an actuation force from a respective one of the bias actuators;a rudder bar;a rudder bar interface positioned between the connector ends and connected to the rudder bar for rotation therewith about an axis of the rudder bar as a function of the actuation forces from the bias actuators;a mechanism comprising links and joints between the connector ends and the rudder bar for transmission of the actuation forces to the rudder bar, the mechanism being actuated between a contracted configuration in which first moment arms are defined between the connector ends and the rudder bar interface, and an expanded gain configuration in which second moment arms are defined between the connector ends and the rudder bar interface, the second moment arms having a greater dimension than the first moment arms; andat least one actuator connected to the mechanism to actuate the mechanism independently from the actuation forces from the bias actuators so as to move the mechanism between the contracted configuration and the expanded gain configuration. 2. The bias gain system according to claim 1, wherein the mechanism comprises a crank link, the rudder bar interface being at a first end of the crank link such that the crank link rotates concurrently with the rudder bar about said axis of the rudder bar. 3. The bias gain according to claim 2, further comprising first and second scissor links each being connected to a respective one of the connector ends, the first and second scissor links being rotatably connected to a second end of the crank link by at least a rotational joint so as to be displaced away from the crank link in the expanded gain configuration of the mechanism by actuation of the at least one actuator. 4. The bias gain system according to claim 3, wherein the first and second scissor links rotate about a common axis at the second end of the crank link. 5. The bias gain system according to claim 4, further comprising first and second gain links disposed between the at least one actuator and the first and second scissor links, the first and second gain links transmitting an actuation of the at least one actuator to the first and second scissor links to configure the mechanism to the contracted configuration and the expanded gain configuration. 6. The bias gain system according to claim 5, wherein the first and second gain links are connected to the at least one actuator at a junction and the first and second gain links connect to the first and second scissor links by first and second rotational joints, respectively. 7. The bias gain system according to claim 6, wherein the first and second gain links rotate about a common axis at the junction with the at least one actuator. 8. The bias gain system according to claim 3, wherein: the crank link has first and second lateral arms each extending toward a respective one of the first and second scissor links, anda sliding joint is disposed between each one of the first and second lateral arms and a respective one of the first and second scissor links. 9. The bias gain system according to claim 2, wherein the at least one actuator is a linear actuator secured to the crank link. 10. The bias gain system according to claim 1, wherein the rudder bar interface comprises: a bore with an engagement peripheral pattern operatively engaging the rudder bar for concurrent rotation. 11. The bias gain system according to claim 1, wherein each of the connector ends define a respective rotational joint with one of the bias actuators. 12. The bias gain system according to claim 1, wherein the rudder bar interface is located at a fore end of the mechanism relative to an orientation of an aircraft defined consistently with a flight direction of the aircraft. 13. A method for controlling a torque on a rudder bar of an aircraft having the bias gain system of claim 1, comprising: receiving actuation forces on opposed ends of the mechanism to cause a rotation of the rudder bar positioned between the opposed ends of the mechanism; andmodifying a configuration of the mechanism independently of the actuation forces to change moment-arm distances between the opposed ends of the mechanism and the rudder bar. 14. The method according to claim 13, wherein receiving the actuation forces comprises receiving two actuation forces in opposite directions. 15. The method according to claim 13, wherein modifying the configuration of the mechanism comprises modifying the configuration of the mechanism with a single degree of freedom. 16. The method according to claim 13, wherein the mechanism comprises a crank link, the rudder bar interface being at a first end of the crank link such that the crank link rotates concurrently with the rudder bar about said axis of the rudder bar and the bias gain system further comprises first and second scissor links each being connected to a respective one of the connector ends, the first and second scissor links being rotatably connected to a second end of the crank link by at least a rotational joint so as to be displaced away from a crank arm in the expanded gain configuration of the mechanism by actuation of the at least one actuator, and wherein modifying the configuration comprises expanding the mechanism by displacing the pair of scissor links away from one another and away from the crank link so as to increase moment-arm distances between the respective opposed ends of the mechanism and the rudder bar. 17. The method according to claim 16, wherein expanding the mechanism is performed during a takeoff phase of a flight of the aircraft. 18. The method according to claim 13, wherein the mechanism comprises a crank link, the rudder bar interface being at a first end of the crank link such that the crank link rotates concurrently with the rudder bar about said axis of the rudder bar and the bias gain system further comprises first and second scissor links each being connected to a respective one of the connector ends, the first and second scissor links being rotatably connected to a second end of the crank link by at least a rotational joint so as to be displaced away from a crank arm in the expanded gain configuration of the mechanism by actuation of the at least one actuator, and wherein modifying the configuration comprises contracting the mechanism by displacing the pair of scissor links toward the crank link so as to reduce moment-arm distances between the respective opposed ends of the mechanism and the rudder bar. 19. An aircraft comprising: a structural element;a rudder bar;a rudder rotatably mounted to the structural element by the rudder bar so as to pivot about an axis of the rudder bar;at least a pair of bias actuators connected to the structural element; anda bias gain system comprising: a pair of bias actuators;a pair of connector ends, each said connector end receiving an actuation force from a respective one of the bias actuators;a rudder bar interface positioned between the connector ends and connected to the rudder bar for rotation therewith about the axis of the rudder bar as a function of the actuation forces from the bias actuators;a mechanism comprising links and joints between the connector ends and the rudder bar for transmission of the actuation forces to the rudder bar, the mechanism being actuated between a contracted configuration in which first moment arms are defined between the connector ends and the rudder bar interface, and an expanded gain configuration in which second moment arms are defined between the connector ends and the rudder bar interface, the second moment arms having a greater dimension than the first moment arms; andat least one actuator connected to the mechanism to actuate the mechanism independently from the actuation forces from the bias actuators so as to move the mechanism between the contracted configuration and the expanded gain configuration. 20. The aircraft according to claim 19, wherein the mechanism comprises a crank link, the rudder bar interface being at a first end of the crank link such that the crank link rotates concurrently with the rudder bar about said axis of the rudder bar.

이 특허에 인용된 특허 (5)

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특허 상세정보

Rudder bias gain changer

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이 특허에 인용된 특허 (5)

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Rudder bias gain changer

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이 특허에 인용된 특허 (5)

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IPC 상세정보(version : 201201)

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