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Redundant locking type longitudinal expansion mechanism of folding wing

A deployment mechanism and locking technology, applied in the direction of projectiles, self-propelled projectiles, offensive equipment, etc., can solve the problems of large body posture interference, large deployment and locking impact, and expansion and locking impact, etc., to maximize the deployment area, Small body interference and reduced impact load

Inactive Publication Date: 2011-10-26
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 in flight. Failing to lock and causing catastrophic accidents

Method used

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  • Redundant locking type longitudinal expansion mechanism of folding wing
  • Redundant locking type longitudinal expansion mechanism of folding wing
  • Redundant locking type longitudinal expansion mechanism of folding wing

Examples

Experimental program
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Embodiment Construction

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

[0014] The longitudinal deployment mechanism of the redundant locking folding wing includes gas actuator 1 (providing power source); wing 2, 13; worm 3; worm gear 4, 12 (fixedly connected with the wing); wing pin holes 5, 11 ( Cooperate with the locking pin for positioning and locking of the folded and unfolded position); wing shafts 6, 10; locking pins 7, 9 (positioning and locking of the folded and unfolded position of the wings); body bracket 8; balls Nut 14; Push rod 15. The slider in the gas actuator 1 is fixedly connected with the push rod 15, the push rod 15 pushes the ball nut 14 on the worm 3 to move, the movement of the ball nut 14 drives the worm 3 to rotate, and the worm 3 is set on the side away from the ball nut 14 There is an upper worm wheel 12 and a lower worm wheel 4, and the upper worm wheel 12 and the lower worm wheel 4 are arranged symmetrically along ...

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Abstract

The invention relates to a redundant locking type longitudinal expansion mechanism of a folding wing. The existing missile folding wing has the once expansion locking function and has the defects of extremely short expansion time, great expansion locking impact and great posture interference on a missile in flight. The longitudinal expansion mechanism provided by the invention adopts the design idea that a worm mechanism and a ball nut are combined, wherein the mechanism can realize the once reliable locking of the folding wing; the power of a gas actuator cylinder drives the nut to move; a screw shaft is linked with a worm, thereby driving a worm gear to rotate around a wing shaft; and the locking of the folding wing is realized by utilizing the self-locking action of the worm. The longitudinal expansion mechanism provided by the invention realizes the minimization of the enveloping space of the folding wing, has the advantage of compact structure and is easy to realize the folding, the expansion and the locking with high accuracy and high reliability.

Description

technical field [0001] The invention relates to a folding wing unfolding mechanism with self-locking function, which is used for unfolding and locking the folding wings of tactical missiles and cruise missiles. Background technique [0002] The missile wing is an important part of the missile body. In order to make the missile launcher miniaturized and the transportation and storage simple and convenient, tactical missiles widely use folding wings. The unfolding mechanism of the folding wing is used to realize the folding and unfolding of the bomb 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 in flight. Failure to lock could result in a catastrophic accident. Contents of the invention [0003] The purpose of the present invention is to solve the one-time loc...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B15/00F42B10/64
Inventor 胡明张苗苗陈文华金永平徐国民钱萍周健潘骏刘东旭张尧
Owner ZHEJIANG SCI-TECH UNIV
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