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Pin connection structure for metal shell of solid rocket engine

A technology of pin connection and metal casing, which is applied to rocket motor devices, machines/engines, mechanical equipment, etc., and can solve the problems of reducing the structural quality of solid rocket motor casings

Inactive Publication Date: 2016-06-01
中国航天科工集团第六研究院四十一所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The technical problem to be solved by the present invention is to provide a pin connection structure for the metal casing of the solid rocket motor to solve the problem of connecting the metal casing of the solid rocket motor and reducing the structural quality of the solid rocket motor casing

Method used

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  • Pin connection structure for metal shell of solid rocket engine
  • Pin connection structure for metal shell of solid rocket engine
  • Pin connection structure for metal shell of solid rocket engine

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Embodiment Construction

[0022] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0023] Such as figure 1 As shown, the pin connection structure of the solid rocket motor metal casing mainly includes the casing joint 1, the top cover 2, the pin 3 and the sealing ring 4.

[0024] Such as figure 2 As shown, the shell joint 1 is provided with an axial positioning surface 5 , a circumferential positioning groove 6 , a shell joint connecting surface 7 , a shell joint pin hole 8 , a transition surface 9 , and a sealing surface 10 . The axial positioning surface 5 is arranged on the end surface of the shell joint 1 for the axial positioning of the top cover 2; the circumferential positioning groove 6 is set on the end surface of the shell joint 1 for realizing the circumferential positioning of the top cover 2; the connecting surface of the shell joint 7 The radial thickness must meet the requirements of tensile load, shear load and extr...

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Abstract

The invention relates to a pin connection structure for a metal shell of a solid rocket engine. The pin connection structure comprises shell connectors, a top cover, pins and a sealing ring. Each shell connector is provided with an axial locating face, a circumferential locating groove, a shell connector connection face, pin holes, a transition face and a sealing face. The top cover is provided with an axial locating boss, a circumferential locating boss, a top cover connection face, top cover pin holes and a sealing groove. Each pin is composed of a pin cap, a polished rod and a screw. The sealing ring is installed in the sealing groove in the top cover. According to the pin connection structure, assembly and disassembly are simple, and the structural reliability is high. The opening radial dimension of the front shell connector and the rear shell connector can be effectively increased, the structural mass of the shell of the solid rocket engine can be decreased, the structural mass of the top cover is decreased, the axial dimension of the engine is shortened, and the mass ratio of the solid rocket engine to a missile is effectively increased.

Description

technical field [0001] The invention relates to a connection structure of a solid rocket motor, in particular to a pin connection structure of a metal shell of a solid rocket motor. Background technique [0002] The solid rocket motor free-loading grain can easily replace the grain, avoids the problem of bonding and debonding between the grain and the heat insulation layer, facilitates engine maintenance, reduces development costs, and is widely used. In order to increase the mass ratio of the free-loading grain engine, reduce the negative mass, and reduce the thickness of the heat insulation layer, one end of the engine is required to have a large opening structure. After the grain is filled, a top cover is installed at the large opening end. The ingenuity, manufacturability, operability, mass size, and space occupied by the connection structure of the engine’s large opening end directly affect the thickness of the engine’s combustion chamber insulation layer, the outer dia...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/34
CPCF02K9/343
Inventor 李静
Owner 中国航天科工集团第六研究院四十一所
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