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Unfolding driving device and method for missile folding rudder or folding wing

A technology of driving device and driving method, which is applied in the direction of projectiles, offensive equipment, weapon types, etc., can solve the problems of large impact force, large volume and weight, and poor reliability, and achieve the effect of improving reliability and reducing volume and weight

Active Publication Date: 2021-09-07
AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

There are generally disadvantages such as large impact force, poor reliability, or the need to provide air and hydraulic sources, and large volume and weight.

Method used

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  • Unfolding driving device and method for missile folding rudder or folding wing
  • Unfolding driving device and method for missile folding rudder or folding wing
  • Unfolding driving device and method for missile folding rudder or folding wing

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Embodiment Construction

[0027] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0028] An embodiment of the invention provides a device for deploying a missile folding rudder or folding wings. A base 200 is included. Exemplary, such as figure 1 As shown, the number of the base 200 is not less than two groups, and one end of the base 200 is used to connect with the missile body 100, and the other end is use...

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PUM

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Abstract

The invention relates to the technical field of missile driving, in particular to an unfolding driving device and method for a missile folding rudder or folding wing. The device comprises a base, a deflection body, a shape memory alloy hyperelastic pipe and a locking mechanism; a deflection groove is formed in one side wall of the base; one end of the deflection body is located in the deflection groove, the shape memory alloy hyperelastic pipe is installed in the deflection body, and the two ends of the shape memory alloy hyperelastic pipe extend into the base; a locking rod groove is formed at one end of the shape memory alloy hyperelastic pipe, and the locking mechanism is arranged in the locking rod groove; and the locking mechanism comprises a ratchet locking rod, one end of the ratchet locking rod is rotationally connected with the shape memory alloy hyperelastic pipe, and the ratchet locking rod is sleeved with a shape memory alloy driving spring. Through the device, the reliability of the folding rudder or the folding wing can be improved, and the size and the weight of the driving device are reduced.

Description

technical field [0001] The invention belongs to the technical field of missile driving, and in particular relates to a device and a driving method for unfolding a missile folding rudder or folding wings. Background technique [0002] The wings folding technology has the advantages of saving airborne space, increasing bomb loading, and being convenient for transportation and storage, and has broad application prospects. During the unfolding process of the folding wings, the driving mode is an important factor affecting whether the wings can be deployed normally, the speed of deployment, the impact force of deployment, and the reliability of deployment. At present, the commonly used driving methods include fire control, pneumatic, hydraulic, electric and so on. There are generally disadvantages such as large impact force, poor reliability, or the need to provide air and hydraulic sources, and large volume and weight. Contents of the invention [0003] In view of the above ...

Claims

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Application Information

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IPC IPC(8): F42B10/16
CPCF42B10/16
Inventor 牛涛陈福龙王耀奇曲海涛王文博张纪春
Owner AVIC BEIJING AERONAUTICAL MFG TECH RES INST