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Longitudinal unfolding mechanism for direct-connected folding wing

A technology of unfolding mechanism and folding wings, which is applied in the direction of projectiles, self-propelled missiles, offensive equipment, etc. It can solve the problems of large interference of projectile attitude, unable to lock and position the wings, and large impact of unfolding and locking, etc., to achieve the expansion area The effect of maximization, accurate deployment, and small body interference

Inactive Publication Date: 2013-10-16
ZHEJIANG SCI-TECH UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, the folding wings of domestic missiles have a one-time unfolding and locking function. The unfolding time is very short, and the impact of unfolding and locking is relatively large, which greatly interferes with the attitude of the missile body. The impact of unfolding and locking may even cause the locking pin to be cut off, making the wings unable to lock. catastrophic accident

Method used

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  • Longitudinal unfolding mechanism for direct-connected folding wing
  • Longitudinal unfolding mechanism for direct-connected folding wing

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Embodiment Construction

[0013] The present invention will be further described below in conjunction with accompanying drawing.

[0014] The direct-connected folding wing longitudinal expansion mechanism includes a gas actuator 1 (providing power source); elastic wings 2, 16; locking pin holes 3, 15 in the inner channel of the cam (cooperating with the slider locking pin, for elastic wing positioning and locking at the end position of deployment); cam 4; wing rotation shafts 5, 14; cam grooves 6, 13 (in contact with the driven slider); cam locking pin hole 7 (cooperating with the guide rail locking pin, used positioning and locking of the cam); wing driven sliders 8 and 12 (to drive the wing to rotate); slider locking pins 9 and 11 (embedded in the slider); locking pin 10 (fixed on the guide rail ); guide rail 17; push rod 18 (promoting the cam to move along the guide rail). The slider in the gas actuator 1 is fixedly connected to one end of the push rod 18, and the other end of the push rod 18 is fi...

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Abstract

The invention relates to a longitudinal unfolding mechanism for a direct-connected folding wing. At present, folding wings of all missiles have functions of one time unfolding and locking, and the unfolding time of the folding wings of all the missiles is very short, the unfolding and locking impact is higher, and the interference on the posture of a flying missile is higher. By adoption of a direct-connected cam mechanism design idea, the reliable locking of folding wings of the missiles can be realized at a time. Power is supplied by a gas actuator cylinder and directly drives a cam to movealong a guide rail; and a driven sliding block on the missile wing is contacted with a chute of the cam and moves in the chute of the cam to realize unfolding of the folding wing. By the longitudinalunfolding mechanism, the minimization of a wrapping space of the folding wing is realized, the mechanism is compact, and high-precision and high-reliability folding, unfolding and locking can be realized easily.

Description

technical field [0001] The invention relates to a folding wing unfolding mechanism with self-locking function, which can be applied to the unfolding and locking of the folding wings of tactical missiles. Background technique [0002] The missile wing is an important part of the missile body. In order to make the missile launching device miniaturized and the transportation and storage simple and convenient, tactical missiles widely use folding wings. After launching, the folding wings are unfolded to reach the flight state. The folding wing unfolding mechanism is used to realize the folding and unfolding function of the missile wing. At present, the folding wings of domestic missiles have a one-time unfolding and locking function. The unfolding time is very short, and the impact of unfolding and locking is relatively large, which greatly interferes with the attitude of the missile body. The impact of unfolding and locking may even cause the locking pin to be cut off, making t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F42B15/00F42B10/64
Inventor 胡明张苗苗陈文华金永平周健钱萍潘骏张尧邓国兵张利绍
Owner ZHEJIANG SCI-TECH UNIV
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