Unfolding mechanism for foldable double wing boards of aircraft

A technology of deployment mechanism and aircraft, applied in directions such as wing adjustment, can solve problems such as unfavorable wing plate deployment in place, reduction of driving torque conversion coefficient, etc., and achieve the effect of improving driving capacity and driving torque.

Active Publication Date: 2011-02-16
中国航天科工集团第二研究院二一〇所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although the structure is relatively simple, in the second half of the wing plate deployment, the conversion coefficient of the driving torque decreases, which is not conducive to the wing plate being fully deployed at the end position.

Method used

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  • Unfolding mechanism for foldable double wing boards of aircraft
  • Unfolding mechanism for foldable double wing boards of aircraft
  • Unfolding mechanism for foldable double wing boards of aircraft

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Embodiment Construction

[0020] When the foldable wings of the aircraft are unfolded, the drag moment value generated by the aerodynamic lift increases with the increase of the expansion angle of the wings. According to the characteristics of its changing law, a double rocker slider is designed to adapt to its changing law Wing expansion mechanism. The working characteristics of this mechanism are: in the initial stage of wing plate expansion, the drive torque conversion coefficient K3 of the wing plate is slightly small, and with the increase of the wing plate expansion angle, the torque conversion coefficient K3 gradually increases, especially when the wing plate rotation angle is increased. In the last third area, the torque conversion coefficient K3 shows a rapid increase trend, and at this time the angular velocity of the wing plate gradually decreases. Near the end area, the wing plate unfolding mechanism forms a working characteristic of low speed and high torque. It is very beneficial to avoid...

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PUM

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Abstract

The invention discloses an unfolding mechanism for a foldable double wing boards of an aircraft, comprising a fuel gas action device, a linear guiderail, a slider, connection rods and rockers. The linear guiderail is located on a perpendicular bisector of a rotation shaft connecting line of two wing boards and fixed on the aircraft body through a lower bracket; the slider is articulated with one ends of two connection rods; the fuel gas action device drives the slider to move linearly along the linear guiderail; the other ends of the two connection rods are respectively articulated with one end of one rocker; the other end of each rocker is articulated with a wing board rotation shaft fixed on a wing board bracket; under the push of the connection rods, the rockers rotate around the wing board rotation shaft fixed on the wing board bracket; one rocker is fixedly connected with a wing board shaft sleeve; and the rockers drive the wing board to rotate when rotating around the wing boardrotation shaft. The unfolding mechanism of the invention greatly improves the unfolding driving capability of the wing board and does not generate impact to the wing board bracket.

Description

technical field [0001] The invention relates to a propulsion mechanism, in particular to a propulsion mechanism for transforming a foldable double-wing panel of an aircraft from a folded state during storage to an unfolded state during normal operation. Background technique [0002] At present, the foldable double-wing panel deployment mechanism of aircraft mainly includes a rack and pinion deployment mechanism and a double crank slider deployment mechanism. Due to the limitations of the structural characteristics of existing products, there are obvious deficiencies in the prior art in the process of wing plate deployment, which are mainly manifested in the following aspects: [0003] 1) Rack and pinion deployment mechanism, the basic structure is to install a rack that can move in a straight line at the axis of symmetry, and drive the gear that is fixedly connected with the wing to rotate around the axis of the wing, so as to realize the rotation and deployment of the wing....

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/56
Inventor 钟世宏
Owner 中国航天科工集团第二研究院二一〇所
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