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Force synthesizing arm applied to redundant actuator system

An actuation system and redundancy technology, applied in the field of force synthesis arms, can solve the problems of redundant steering gear length, etc., and achieve the effects of improving structural reliability, convenient processing, and reducing regular maintenance costs

Inactive Publication Date: 2009-12-02
BEIHANG UNIV
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Because it is added in series, when a fault occurs, the fault transient is easily transmitted to the control surface, and when the number of redundant degrees is greater than 2, the redundant steering gear is longer, thus limiting the application

Method used

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  • Force synthesizing arm applied to redundant actuator system
  • Force synthesizing arm applied to redundant actuator system
  • Force synthesizing arm applied to redundant actuator system

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Embodiment Construction

[0032] The present invention will be further described in detail below in conjunction with the accompanying drawings.

[0033] The present invention is a force synthesis arm applied to a redundant steering gear system, such as Figure 5 As shown, the redundant steering gear system includes steering gear A1, steering gear B2, steering surface 3, and force synthesis arm 4;

[0034] Such as Figure 6 As shown, the force synthesis arm 4 includes a slider 401 , a chute 402 , a passage A403 , a passage B404 , a synthesis rod 405 , and a main arm 406 .

[0035] There is a spherical hinge groove A407 at one end of the main arm 406 front of the force synthesis arm 4, and a chute 402 is opened at the other end, and a slide block 401 is embedded in the chute 402 of the force synthesis arm 4, so that the slide block 401 can be moved in the chute 402. Swipe in. There is a spherical hinge groove B408 on the slider 401; the length of the sliding groove 402 is determined according to the m...

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Abstract

The invention provides a force synthesizing arm applied to a redundant actuator system. Aiming at characteristics of an electro-hydrostatic actuator EHA applied to the key control surface of a multi-electric aircraft, the invention designs a novel force synthesizing arm structure, which is mainly used for eliminating force-fighting phenomenon on the force synthesizing arm when the tail end of the EHA adopts a dual-redundant mechanical executing mechanism. In the design, an actuator cylinder output end of one actuator channel is fixedly connected with one end of the force synthesizing arm through a spherical hinge, an output end of the other actuator channel is fixed on a slide block through a spherical hinge, and the slide block can slide in a specific chute of the force synthesizing arm. When the actuator output of the two channels is not consistent, the sliding of the slide block can effectively eliminate the influence of the force-fighting phenomenon caused by a synchronous displacement error on the force synthesizing arm and greatly improve the structural reliability of the synthesizing arm so as to reduce the regular maintenance charge of the actuator system.

Description

technical field [0001] The invention relates to the technical field of an aircraft rudder surface actuation system, in particular to a force synthesis arm applied to a redundant actuation system. Background technique [0002] The aircraft actuation system refers to a relatively independent set of systems that can realize certain power output, mechanical action, and relative independence on the aircraft. It includes a complete set of power transmission conversion equipment from the secondary power source (hydraulic source and motor, etc.) to the mechanical action actuator, as well as the corresponding detection equipment and control system. Its control objects include various aerodynamic surfaces (control surfaces), wheel steering mechanism, landing gear retractable mechanism and other auxiliary power drive systems. The actuation system in the usual sense mainly refers to the control surface actuation system. These controlled control surfaces (rudder surfaces, wing surfaces...

Claims

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Application Information

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IPC IPC(8): B64C13/28
Inventor 朗燕齐海涛辛鹏宇李运华刘沛清
Owner BEIHANG UNIV
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