Small combined spring type quick unfolding mechanism

A technology combining springs and deployment mechanisms, which is applied to self-propelled bombs, weapon types, projectiles, etc., can solve the problems of high cost and large structural space requirements, and achieve the effects of low cost, short processing cycle and strong interchangeability

Active Publication Date: 2013-09-25
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Abstract
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Problems solved by technology

In the existing technology, the folding mechanism adopts the form of torsion bar, which requires a large structural space. The material of the torsion bar needs to have ex

Method used

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  • Small combined spring type quick unfolding mechanism

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Embodiment Construction

[0015] The present invention will be further elaborated below by describing a preferred specific embodiment in detail in conjunction with the accompanying drawings.

[0016] Such as figure 1 As shown, a small combined spring-type rapid deployment mechanism includes a rudder surface 1 and a compression spring 2 arranged on the rudder surface 1, a rudder seat 3 and a rotating unit; the rudder surface 1 is a right-angled trapezoid; The lower bottom is sequentially provided with a compression spring 2, a rudder seat 3 and a rotating unit from bottom to top. A locking pin 21 is respectively arranged on both sides of the compression spring 2 . Arrange two locking pins 21 and a compression spring 2 into the installation hole of the rudder seat 3 according to the diagram, use tooling to make the two locking pins 21 move toward each other, compress them in place, and snap them into the limiting taper hole of the rudder surface 1; The rudder surface 1 and the rudder seat 3 are connect...

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Abstract

The invention discloses a small combined spring type unfolding mechanism which comprises a rudder surface, a compression spring, a rudder seat and a rotating unit. The compression spring is arranged on the rudder surface, the rudder surface is in the shape of a right trapezoid, and the compression spring, the rudder seat and the rotating unit are sequentially arranged at the trapezoidal bottom of the rudder surface from bottom to top. The rotating unit comprises a rotary shaft, a rudder surface cylindrical pin, a first torsion spring, a second torsion spring, a screw pin and a spring seat, the middle of the rotary shaft is fixed to the rudder surface by the aid of the rudder surface cylindrical pin, the first torsion spring and the second torsion spring are respectively arranged on two sides of the rudder surface cylindrical pin and are disposed in the rotary shaft, the other side of the first torsion spring is connected with the rudder seat, and the other side of the second torsion spring is connected with the spring seat. The small combined spring type unfolding mechanism has the advantages that a combined spring mode is adopted, the maximum thickness of the integral mechanism is only 10mm, accordingly, the small combined spring type unfolding mechanism can be applied to mechanisms with small space, and is low in cost.

Description

technical field [0001] The invention relates to a rudder surface deployment mechanism in the field of missile launching, in particular to a small combined spring type rapid deployment mechanism. Background technique [0002] When the missile is in the barrel, the rudder surface is pressed against the inner wall of the launch tube under the action of external force. When the missile is released from the barrel, the rudder surface automatically opens and locks itself. The rudder surface deflects within the range of -18o ~ 18o through mechanical limit. In the existing technology, the folding mechanism adopts the form of torsion bar, which requires a large structural space. The material of the torsion bar needs to have extremely strong toughness and high hardness. After mechanical tests, only imported steel (NL-2) To meet the use requirements, the cost of procurement is relatively high. Contents of the invention [0003] The purpose of the present invention is to provide a s...

Claims

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Application Information

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IPC IPC(8): F42B15/00F42B10/64
Inventor 韩子晨王杜林武晓峰
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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