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Composite device for zero correction and on-load test of guided missile steering engine

A technology of zero correction and compound device, which is applied in ammunition testing, ammunition, self-propelled ammunition, etc., can solve problems such as low debugging accuracy and complicated debugging process, and achieve simplified testing process, simple and fast replacement process, and reduced readings effect of error

Pending Publication Date: 2021-11-02
湖北航天飞行器研究所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This solves the technical problems of complex debugging process and low debugging accuracy in the existing steering gear debugging process

Method used

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  • Composite device for zero correction and on-load test of guided missile steering engine
  • Composite device for zero correction and on-load test of guided missile steering engine
  • Composite device for zero correction and on-load test of guided missile steering engine

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Effect test

Embodiment 1

[0035] like Figure 1 to Figure 6 As shown, the present invention provides a composite device for zero correction and load testing of steering gear for missiles, including installation plane, steering gear base and four groups of zero adjustment and load testing components with the same structure, wherein,

[0036]The four groups of zero-adjustment and on-load test components with the same structure are evenly distributed in the circumferential direction on the installation plane; the zero-adjustment and on-load test components include a rudder turret with a rudder turret hole, a rotating shaft bracket, a rotating shaft, and a rotating shaft Mechanism, zero pin, angle sensor assembly, telescopic arm bracket, telescopic arm, torsion bar, torsion bar seat; the shaft bracket and the telescopic arm bracket are installed on the installation plane in a straight line, and are correspondingly arranged on the shaft Both the rotating shaft on the support and the telescopic arm arranged ...

Embodiment 2

[0043] like Figure 1 to Figure 6 As shown, the present invention provides a composite device for zero correction and load testing of steering gear for missiles, including installation plane, steering gear base and four groups of zero adjustment and load testing components with the same structure, wherein,

[0044] The four groups of zero-adjustment and on-load test components with the same structure are evenly distributed in the circumferential direction on the installation plane; the zero-adjustment and on-load test components include a rudder turret with a rudder turret hole, a rotating shaft bracket, a rotating shaft, and a rotating shaft Mechanism, zero pin, angle sensor assembly, telescopic arm bracket, telescopic arm, torsion bar, torsion bar seat; the shaft bracket and the telescopic arm bracket are installed on the installation plane in a straight line, and are correspondingly arranged on the shaft Both the rotating shaft on the support and the telescopic arm arranged...

Embodiment 3

[0054] like Figure 1 to Figure 6 As shown, the present invention provides a composite device for zero correction and load testing of steering gear for missiles, including installation plane, steering gear base and four groups of zero adjustment and load testing components with the same structure, wherein,

[0055] The four groups of zero-adjustment and on-load test components with the same structure are evenly distributed in the circumferential direction on the installation plane; the zero-adjustment and on-load test components include a rudder turret with a rudder turret hole, a rotating shaft bracket, a rotating shaft, and a rotating shaft Mechanism, zero pin, angle sensor assembly, telescopic arm bracket, telescopic arm, torsion bar, torsion bar seat; the shaft bracket and the telescopic arm bracket are installed on the installation plane in a straight line, and are correspondingly arranged on the shaft Both the rotating shaft on the support and the telescopic arm arranged...

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Abstract

The invention relates to a composite device for zero correction and on-load test of a guided missile steering engine. The composite device comprises a mounting plane, a steering engine base and four groups of zero setting and on-load testing assemblies with the same structure. The four groups of zero setting and on-load testing assemblies of the same structure are evenly distributed and installed on the mounting plane in the circumferential direction, the four groups of rudder sheets are adjusted to be in a mechanical zero position state through a steering engine room control system, meanwhile, the steering engine electrical zero position is set according to the deflection angles of the four groups of rudder sheet rotary tables, and at the moment, a torsion bar is matched to complete on-load testing. Modular design is adopted, components are convenient to replace, the four groups of zero setting and on-load testing assemblies are axially and evenly distributed on a bottom plate frame, the whole steering engine room is tested at the same time, a zero correction system of the steering engine room and a steering engine system on-load testing system are integrated, the function that one machine has multiple purposes is achieved, and the testing process of the steering engine room is simplified. The composite device has the advantages of convenient steering engine replacement, simple testing process, high testing precision, high universality and the like.

Description

technical field [0001] The invention belongs to the technical field of missile steering gear testing, and more specifically relates to a composite device for zero-position correction of a steering gear rudder plate for a missile and on-load testing of the steering gear. Background technique [0002] With the development of science and technology, the precise strike of missiles has become an important direction of missile development. Among them, the rudder blade in the rudder cabin is used to generate additional air force when the missile is flying, forming a control force on the missile, and then playing the role of controlling the missile trajectory. When the missile is flying, the rudder control system will correct the flight trajectory of the missile in real time through the deflection of the rudder blade. The deflection angle accuracy of the rudder blade directly affects the control accuracy of the steering gear system. Generally speaking, when the steering gear is ass...

Claims

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Application Information

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IPC IPC(8): F42B35/00F42B15/01
Inventor 孙印锐王力刘卓段相杰刘浩陈文博李斌王芸
Owner 湖北航天飞行器研究所
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