Tubular inner-hole charge structure with inner cavity partition and used for solid rocket engine, and method

An inner cavity partition, solid rocket technology, applied in rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of increasing the design thickness of the engine combustion chamber shell, increasing the passive weight of the missile, and affecting the missile range, etc. Achieve the effect of reducing draft risk, reducing negative quality and improving safety

Active Publication Date: 2019-08-20
SHANGHAI XINLI POWER EQUIP RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

As a result, the design thickness of the engine combustion chamber shell is increased, and the passive weight of the missile is increased, which affects the range of the missile.

Method used

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  • Tubular inner-hole charge structure with inner cavity partition and used for solid rocket engine, and method
  • Tubular inner-hole charge structure with inner cavity partition and used for solid rocket engine, and method
  • Tubular inner-hole charge structure with inner cavity partition and used for solid rocket engine, and method

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Embodiment Construction

[0027] The solution provided by the present invention is to provide a solid rocket motor inner hole tubular charge structure with an inner cavity partition, and an inner cavity partition is arranged in the solid rocket combustion chamber charge column, which improves the surface increase of the charge, Make the working pressure and thrust of the engine stable.

[0028] Such as figure 1 As shown, the present invention proposes a solid rocket motor inner hole tubular charge structure with an inner cavity partition, including an inner cavity partition 1, a heat insulating layer 3 and a combustion chamber casing 4;

[0029] The inner surface of the combustion chamber shell 4 is sandblasted, and the adhesive is evenly sprayed, and the heat insulation layer 3 is bonded to the combustion chamber shell 4; Put the butylated hydroxy composite propellant slurry, and when the slurry reaches the designated position, put it into the inner cavity partition 1, and then continue to inject th...

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Abstract

The invention discloses a tubular inner-hole charge structure with an inner cavity partition and used for a solid rocket engine. The inner cavity partition is arranged in the combustion chamber chargestructure of the solid engine, and the inner cavity partition is made from a polyurethane foam material. The tubular inner-hole charge structure with the inner cavity partition and used for the solidrocket engine has the beneficial effects of being capable of effectively improving the progressive performance of the solid rocket engine in a working process, reducing the maximum working pressure of the engine, reducing the design thickness of a shell body, reducing the passive mass of the missile engine, and increasing the missile range.

Description

technical field [0001] The invention relates to a solid rocket motor inner-hole tubular charge structure with an inner cavity partition, and belongs to the technical field of solid rocket motor charge structures. Background technique [0002] Combustion chamber charge is one of the important parts in the structure of solid rocket motor, which provides power for the motor and propels the missile to fly. In the charge design of the combustion chamber, the design of the charge determines the change of the combustion surface, thereby determining the change form of the thrust of the engine. The solid rocket motor with the inner hole tubular charge poured on the wall has obvious surface increase in the working process, which will make the working pressure and thrust of the engine continue to rise, and increase the maximum working pressure of the engine. As a result, the design thickness of the engine combustion chamber casing is increased, and the negative weight of the missile i...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/24F02K9/34
CPCF02K9/24F02K9/34F02K9/346
Inventor 陈俊沈铁华乐浩何鹏王蓬勃阳洁乌日娜
Owner SHANGHAI XINLI POWER EQUIP RES INST
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