Solid rocket motor end surface grain coating structure and coating method thereof

A solid rocket and cladding structure technology, which is applied in the direction of rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of engine bursting and disintegration, low yield rate, high product process cost, etc., and achieve reliable bonding and high production efficiency , fast curing effect

Pending Publication Date: 2020-06-02
西安航科等离子体科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] Aiming at the problems in the above-mentioned prior art that there are air holes and debonding in the end surface combustion charge of the solid rocket motor, which lead to high product process cost and low yield, and the air holes and debonding are easy to cause the engine to burst and disintegrate, the present invention proposes a solid rocket motor The engine grain coating structure and coating method thereof, the specific technical scheme and method steps are as follows:

Method used

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  • Solid rocket motor end surface grain coating structure and coating method thereof
  • Solid rocket motor end surface grain coating structure and coating method thereof

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Effect test

Embodiment 1

[0026] In the solid rocket motor grain covering structure of this embodiment, the average thickness of the polyurea elastomer layer is 2.0 mm.

[0027] The coating method for implementing the solid rocket motor grain coating structure of this embodiment specifically includes the following steps:

[0028] (1) The formed powder column is fixed on the polyurea spraying rotary device, and the rotating speed of the polyurea spraying rotary device is set to be 5 seconds per circle;

[0029] (2) Use two injection devices to spray the A component of polyurea and the B component of polyurea into the spray chamber of the polyurea spraying rotary device, so that the components A and B are sprayed in the spray chamber. react to generate a polyurea mixture;

[0030] (3) Adjust the nozzle of the spray chamber and the spraying surface of the powder column to 350mm, make the spray chamber move up and down at a speed of 1m / s along the vertical direction, and the spraying surface of the spray ...

Embodiment 2

[0032] In the solid rocket motor grain covering structure of this embodiment, the average thickness of the polyurea elastomer layer is 1.8mm.

[0033] The coating method for implementing the solid rocket motor grain coating structure of this embodiment specifically includes the following steps:

[0034] (1) The formed powder column is fixed on the polyurea spraying rotary device, and the rotating speed of the polyurea spraying rotary device is set to be 4 seconds per circle;

[0035] (2) Use two injection devices to spray the A component of polyurea and the B component of polyurea into the spray chamber of the polyurea spraying rotary device, so that the components A and B are sprayed in the spray chamber. react to generate a polyurea mixture;

[0036] (3) Adjust the nozzle of the injection cavity and the spraying surface of the powder column to 300mm, make the injection cavity move up and down at a speed of 1.5m / s along the vertical direction, and the spraying surface of the...

Embodiment 3

[0038] The solid rocket motor grain coating structure of this embodiment has an average thickness of the polyurea elastomer layer of 2.2 mm.

[0039] The coating method for implementing the solid rocket motor grain coating structure of this embodiment specifically includes the following steps:

[0040] (1) The formed powder column is fixed on the polyurea spraying rotary device, and the rotating speed of the polyurea spraying rotary device is set to be 6 seconds per circle;

[0041] (2) Use two injection devices to spray the A component of the polyurea and the B polyurea component into the spray chamber of the polyurea spraying rotary device, so that the A component and the B component are sprayed in the spray chamber. react to generate a polyurea mixture;

[0042] (3) Adjust the nozzle of the spray chamber and the spraying surface of the powder column to 400mm, make the spray chamber move up and down along the vertical direction at a speed of 1m / s, and the spraying surface o...

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Abstract

The invention provides a solid rocket motor grain coating structure and a coating method thereof, and belongs to the technical field of solid rocket motor manufacturing. The solid rocket motor grain coating structure comprises a coating sleeve and a grain arranged inside the coating sleeve. The coating sleeve is a polyurea elastomer layer, and the thickness of the polyurea elastomer layer is 1.8mm-2.2 mm. The solid rocket motor grain coating structure is high in yield rate, and the reliability of the grain during combustion and the stability of a motor during operation can be ensured. The solid rocket motor grain coating method is simple in operation process, sagging is not caused after spraying, the polyurea elastomer layer cures quickly, and the production efficiency of a product is high.

Description

technical field [0001] The invention belongs to the technical field of solid rocket motor manufacturing, and in particular relates to a solid rocket motor grain coating structure and a coating method thereof. Background technique [0002] Solid rocket motor is the power device of aerospace vehicles such as rockets and navigation. Its principle is to generate high-temperature gas through the combustion of solid propellant, and then spray it out through the nozzle to generate reaction force. Solid rocket motors have a variety of charge forms, among which the end-burning grain is a relatively common one. The end-burning grain is often made of double-base propellant or modified double-base propellant. into the combustion chamber. EPDM is a commonly used material for the thermal insulation coating of grains. It has good thermodynamic properties (high elongation and softness), good thermal insulation and anti-ablation performance, and ensures the side of the grains when the end f...

Claims

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Application Information

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IPC IPC(8): F02K9/24B01J19/26B05D1/02B05D3/02
CPCF02K9/24B01J19/26B05D1/02B05D3/0254
Inventor 王浩静马俊陆亚超杨利锋陈铭德樊黎君周倩倩黄微波
Owner 西安航科等离子体科技有限公司
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