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Aileron cabin sealing structure

A sealing structure and aileron technology, which can be used in heat-reducing structures, wings, unmanned aerial vehicles, etc., can solve the problems of low rigidity and poor sealing performance of the sealing structure of the aileron cabin, so as to improve the efficiency of aerodynamic sealing and avoid the Twist, optimize the effect of the seal form

Active Publication Date: 2016-11-09
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide an aileron cabin sealing structure, which solves the problems of low rigidity and poor sealing performance of the aircraft aileron cabin sealing structure

Method used

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  • Aileron cabin sealing structure
  • Aileron cabin sealing structure
  • Aileron cabin sealing structure

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Embodiment Construction

[0021] To make the objectives, technical solutions, and advantages of the implementation 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 accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals indicate the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. The embodiments described below with reference to the accompanying drawings are exemplary, and are intended to explain the present invention, but should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative work shall fall within the protection scope of the present invention.

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Abstract

The invention provides an aileron cabin sealing structure used for connecting a fixed rear edge skin (21) and an aileron skin (22). A first shell (3) and a second shell (4) are fixedly connected to the two ends of the same side of the fixed rear edge skin (21). A first rotary bearing (5) and a first torsion spring (7) are installed in the first shell (3). A second rotary bearing (6) and a second torsion spring (8) are installed in the second shell (4). One end of a rotary shaft (1) sequentially penetrates the first rotary bearing (5) and the first torsion spring (7), and the other end of the rotary shaft (1) sequentially penetrates the second rotary bearing (6) and the second torsion spring (8), and the rotary shaft (1) is arranged between the first shell (3) and the second shell (4). One side of a steel film is fixedly connected with the rotary shaft (1), and the other side of the steel film is connected to the position between a pressing sheet (9) and the aileron skin (22) through a fastener. By the adoption of the aileron cabin sealing structure, a sealing form of an aileron cabin is optimized, a rubber sealing profile is prevented from being distorted and torn apart, the pneumatic sealing efficiency is improved, and the maintenance cost is reduced.

Description

Technical field [0001] The invention belongs to the field of aircraft structure design, and specifically relates to an aileron cabin sealing structure. Background technique [0002] In order to ensure the flight quality, a rubber strip is installed on the fixed rear edge of the wing and pressed against the leading edge of the aileron to prevent airflow from entering the aileron cabin. There is a certain amount of interference between the rubber strip and the leading edge of the aileron. After the aileron is deflected many times, the rubber strip is prone to twist and tear, which affects the sealing effect. In the actual design, in order to avoid interference with the aileron suspension arm and actuator when the aileron rotates, a number of openings are designed on the leading edge of the aileron. When the aileron deflects down around the axis of rotation, the edge of the aileron opening exceeds the fixed trailing edge. The boundary of the rubber strip, and when the aileron is de...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C9/00B64C3/26B64C3/36
CPCB64C3/26B64C3/36B64C9/00B64C2009/005B64U30/10
Inventor 李嘉玺周正光徐方舟赵洁
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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