Foldable grid control plane

A folding and rudder surface technology, applied in aircraft parts, aircraft control, transportation and packaging, etc., can solve the problems of non-starting efficiency, reduction, and difficulty in folding, and achieve the effect of simplifying the folding mechanism, high control efficiency, and reduced size

Active Publication Date: 2016-07-06
JIANGXI HONGDU AVIATION IND GRP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, grid rudders also have problems such as large size and weight, difficulty in folding, failure to start or reduced efficiency in large speed ranges, etc. These problems seriously limit the scope of use of grid rudders, especially those that require the rudder surface to have the ability to fold Supersonic missiles cannot use such high-efficiency, low-moment control rudder surfaces

Method used

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  • Foldable grid control plane
  • Foldable grid control plane

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Embodiment Construction

[0013] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments. The following examples are only used to illustrate the present invention, and are not intended to limit the protection scope of the present invention.

[0014] like figure 1 and 2 As shown, a foldable grid rudder surface of the present invention includes a grid-like rudder surface 3, a rotating shaft 2, a locking mechanism 4 and an integrated torsion spring 5, and the grid junction of the rudder surface 3 passes through The hinge 1 is connected, and a hinge 1 is arranged between the two side edges of the rudder surface 3 adjacent to the hinge 1. The middle and lower part of the rudder surface 3 is fixed on the ground through the rotating shaft 2, and the top of the rotating shaft 2 is locked on the rudder surface 3 through the locking mechanism 4. The rotating shaft 2. A pair of integrated torsion springs 5 ​​are provided at the intersection of...

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Abstract

The invention discloses a foldable grid control plane which comprises a control plane body composed of lattices, a rotary shaft, a locking mechanism and integrated torsion springs. The lattice joint positions of the control plane body are connected through hinges. The position between every two adjacent hinges on the edges of the two sides of the control plane body is provided with a hinge. The middle lower portion of the control plane body is fixed to the ground through the rotary shaft. The top of the rotary shaft is locked to the control plane body through the locking mechanism. The lattice joint positions on the two sides of the rotary shaft are provided with the pair of integrated torsion springs. By the adoption of the foldable grid control plane, a folding mechanism of the grid control plane can be greatly simplified, the size of the control plane in a folded state is reduced, the foldable grid control plane is suitable for various aircrafts with the high requirement for the size of the control plane in a non-working state, and the unfolded control plane has the high operation efficiency and the low hinging moment.

Description

technical field [0001] The invention relates to a foldable grid rudder surface. Background technique [0002] Lattice rudders have the advantages of high control efficiency and small hinge moment, especially for large subsonic or supersonic aircraft, which can improve the maneuverability of the aircraft and greatly reduce the torque requirements of the control mechanism. However, the grid rudder actually has problems such as large size and weight, is not easy to fold, and does not start or reduces efficiency in a large speed range. These problems seriously limit the scope of use of the grid rudder, especially those that require the rudder surface to have the ability to fold. Supersonic missiles cannot use such high-efficiency, low-moment control rudder surfaces. [0003] Therefore, it is necessary to provide a new technical solution to solve the above problems. Contents of the invention [0004] The technical problem to be solved by the present invention is to provide a ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C5/18
CPCB64C5/18
Inventor 韩宝瑞刘涛张邦楚杨会林雷军政高辉张炜翔普睿铁程一周盛
Owner JIANGXI HONGDU AVIATION IND GRP
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