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An aircraft flaperon motion mechanism

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

Active Publication Date: 2021-05-25
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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  • An aircraft flaperon motion mechanism
  • An aircraft flaperon motion mechanism
  • An aircraft flaperon motion 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 motion mechanism, comprising a rudder surface, a rudder surface joint, a linkage joint, an aileron drive rod, an aileron auxiliary joint, a wing suspension joint, a flap drive rod, and a flap auxiliary joint, wherein the rudder The surface joint, the linkage joint and the wing suspension joint are all triangular components, the rudder surface is connected with one side of the rudder surface joint, and the center of the rudder surface joint is hinged with the first vertex of the linkage joint, and the second vertex of the linkage joint is It is hinged with the first vertex of the wing suspension joint arranged on the trailing edge of the wing, and the third vertex of the linkage joint is hinged with the end of the flap driving rod set in the flap auxiliary joint. The rudder surface joint is connected with a rudder The opposite vertex of the side of the surface is hinged with the end of the aileron drive rod which is sleeved in the aileron auxiliary joint. The mechanism provided by the invention has few parts, simple and convenient installation, clear motion relationship, high reliability and low 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 Patents(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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