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Zero adjusting device and method of guided missile steering engine rudder wing

A zero-position adjustment and rudder-wing technology, which is applied to the zero-position adjustment of the rudder of a missile steering gear and the zero-position adjustment device of the rudder of a missile steering gear, can solve the problem of high operational skill requirements, low work efficiency, and consistency of rudder blades. and poor accuracy

Pending Publication Date: 2019-01-08
HUNAN GAOKE ELECTRONICS TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This method not only has low work efficiency and requires high operating skills, but also has poor consistency and precision of the rudder blade.

Method used

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  • Zero adjusting device and method of guided missile steering engine rudder wing
  • Zero adjusting device and method of guided missile steering engine rudder wing
  • Zero adjusting device and method of guided missile steering engine rudder wing

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Embodiment Construction

[0018] The present invention will be further described below in conjunction with accompanying drawing.

[0019] Such as Figure 1 to Figure 3 The shown zero adjustment device of the rudder wing of the missile steering gear includes a base 1, a first V-shaped positioning bracket 2 connected to the base 1 and a second V-shaped positioning bracket 3, a linear guide pair 4 connected to the base 1, and The slide plate 5 slidingly connected to the linear guide rail pair 4, the bracket 6 connected to the slide plate 5 at one end, the fixed positioning plate 7 connected to the other end of the bracket 6, the movable positioning plate 8 detachably connected to the fixed positioning plate 7 by bolts at both ends, and The compression handle bar 9 that the movable positioning plate 8 is threaded, the standard body 11 that is detachably connected with the rudder wing 10 of the missile, is slidably connected with the first V-shaped positioning bracket 2 or the second V-shaped positioning br...

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PUM

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Abstract

The invention discloses a zero adjusting device and method of a guided missile steering engine rudder wing. The zero adjusting device comprises a base (1), a first V-shaped positioning support (2), asecond V-shaped positioning support (3), a linear guideway pair (4), a sliding plate (5) which is connected with the linear guideway pair, a support (6) which is connected with the sliding plate, a fixed positioning plate (7) which is connected with the support, a movable positioning plate (8) which is detachably connected with the fixed positioning plate, a compressing handle rod (9) which is connected with the movable positioning plate, a standard body (11) which is connected with a rudder wing body (10) and a center adjusting sliding ring (12), wherein the first V-shaped positioning support(2), the second V-shaped positioning support (3) and the linear guideway pair (4) are connected with the base. The adjusting process comprises the following steps that the rudder wing body (10) is connected with a wing shaft (16), and the standard body (11) is arranged on the rudder wing body (10) in a sleeving manner; and the compressing handle rod (9) is rotated to enable the standard body (11)to be attached to the fixed positioning plate (7) and the compressing handle rod (9), the connection of the rudder wing body (10) and the wing shaft (16) is fixed, and the position is recorded in a drive program of a guided missile steering engine.

Description

technical field [0001] The invention relates to the technical field of missiles, in particular to a device for adjusting the zero position of the rudder wing of the missile steering gear; the invention also relates to a method for adjusting the zero position of the rudder wing of the missile steering gear. Background technique [0002] The rudder wing is an important part of the rocket guidance cabin, including the rudder blade and the rudder blade seat. Whether it works normally directly affects the shooting accuracy of the whole missile. The function of the rudder wing is to generate additional aerodynamic force to form the control force and control moment for the rocket, so as to control the flight of the projectile according to the predetermined trajectory. Because the missile is affected by various factors during the flight, the flight trajectory will change to a certain extent, so the deflection of the rudder wing must be used to adjust and correct the flight trajector...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B15/01F42B10/04
CPCF42B10/04F42B15/01
Inventor 刘衡湘王贤勇郜俊杰
Owner HUNAN GAOKE ELECTRONICS TECH
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