Aircraft flaperon movement mechanism

A technology of motion mechanism and flaperon, which is applied in the field of aircraft structure design, can solve the problems of large number of parts, low reliability, complex motion relationship, etc., and achieve the effect of improving take-off and landing performance, enhancing flexibility, and large lift-to-drag ratio

Active Publication Date: 2018-05-18
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] At present, most of the flaperon motion mechanisms of aircraft are driven by connecting rods, with a large number of parts, complex motion relationships, and relatively low reliability.

Method used

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  • Aircraft flaperon movement mechanism
  • Aircraft flaperon movement mechanism
  • Aircraft flaperon movement mechanism

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Embodiment Construction

[0019] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0020] The aircraft flaperon motion mechanism of the present inventio...

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Abstract

The invention provides an aircraft flaperon movement mechanism. The aircraft flaperon movement mechanism comprises a control plane, a control plane joint, a linkage joint, an aileron driving rod, an aileron auxiliary joint, a wing hanging joint, a flap driving rod and a flap auxiliary joint, wherein the control plane joint, the linkage joint and the wing hanging joint are all triangular members. The control plane is connected with one side edge of the control plane joint; the center of the control plane joint is hinged to the first vertex of the linkage joint, the second vertex of the linkagejoint is hinged to one vertex of the wing hanging joint arranged at the trailing edge of a wing, and the third vertex of the linkage joint is hinged to the end of the aileron driving rod sleeved withthe aileron auxiliary joint; and the vertex, opposite to the side edge, connected with the control plane, of the control plane joint is hinged to the end of the aileron driving rod sleeved with the aileron auxiliary joint. The aircraft flaperon movement mechanism is small in part number, easy and rapid to mount, clear in movement relation, high in reliability and low in cost.

Description

technical field [0001] The invention belongs to the field of aircraft structure design, in particular to an aircraft flaperon motion mechanism. Background technique [0002] At present, most of the flaperon motion mechanisms of aircraft are driven by connecting rods, which have a large number of parts, complex motion relationships, and relatively low reliability. Contents of the invention [0003] The object of the present invention is to provide an efficient and simple aircraft flaperon motion mechanism, which overcomes or alleviates at least one of the above-mentioned defects in the prior art. [0004] The purpose of the present invention is achieved through the following technical scheme: a kind of aircraft flaperon kinematic mechanism, comprises rudder surface, rudder surface joint, linkage joint, aileron drive lever, aileron auxiliary joint, wing suspension joint, flap drive lever, Flap auxiliary joint, wherein the rudder surface joint, linkage joint and wing suspens...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C9/02B64C9/14
CPCB64C9/02B64C9/14B64C2009/005
Inventor 李云鹏王少童黎欣
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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