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Test engine

An engine and charge technology, applied in the direction of machines/engines, rocket engine devices, mechanical equipment, etc., can solve the problems of high test cost, loss, unsatisfactory, etc., and achieve improved safety and reliability, good durability and The effect of reliability and simple structure

Active Publication Date: 2017-08-29
HUBEI SANJIANG AEROSPACE JIANGHE CHEM TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The existing test engine has many groups and parts, poor durability, serious wear and tear, high test cost and other problems, and the maximum working pressure can only reach 20MPa
With the gradual increase in the working performance requirements of solid rocket motors and composite solid propellants, their working pressure is also gradually increasing, which cannot meet the needs

Method used

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  • Test engine

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Embodiment Construction

[0015] The present invention will be further described below in conjunction with the embodiments and accompanying drawings, but the protection scope of the present invention is not limited to the range described in the embodiments.

[0016] Such as figure 1 As shown, a test engine includes a thrust seat 1, a charge combustion chamber 2, and a nozzle assembly 4 arranged in sequence, and an ignition powder pack 9 is also provided at one end of the charge combustion chamber near the thrust seat 1; it is characterized in that: the thrust seat 1 It is sealed with the charge combustion chamber 2 and between the charge combustion chamber 2 and the nozzle assembly 4 with a snap ring structure.

[0017] In a preferred solution, the thrust seat is connected to the charge combustion chamber by a first snap ring 7, and a first compensation block 8 is installed, which is fixed by screws. The thrust seat is processed with two sealing grooves, and the first sealing groove is installed in the...

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Abstract

The invention discloses a test engine. The test engine comprises a thrust block, a charging combustion chamber and a spray pipe assembly which are arranged in sequence. The end, close to the thrust block, of the charging combustion chamber is further provided with an igniter pad. The test engine is characterized in that a gap between the thrust block and the charging combustion chamber as well as a gap between the charging combustion chamber and the spray pipe assembly are sealed by adoption of a clamping ring structure. By adoption of sealing with the clamping ring structures, only radial sealing surfaces are arranged on a shell, the sealing surfaces need to be protected only in the using process, and cleaning and maintenance are convenient. If being rusted, the sealing surfaces can be ground and derusted according to the design sizes of the sealing surfaces. Based on a fatigue life estimation method, clamping rings can be reused for 50 times or above theoretically, a spray pipe shell can be reused for 30 times or above, and the shell and a spray pipe blind nut can be used for a long time.

Description

technical field [0001] The invention belongs to the technical field of testing, and in particular relates to a testing engine. Background technique [0002] Solid rocket motors and composite solid propellants are one-time products. In order to obtain their related properties, such as burning rate, pressure index and energy, etc., performance tests are carried out with test engines such as BSFΦ118 for performance tests, so as to obtain Required data, performance test engine can be reused. The existing test engine has many groups and parts, poor durability, serious wear and tear, high test cost and other problems, and the maximum working pressure can only reach 20MPa. With the gradual increase in the working performance requirements of solid rocket motors and composite solid propellants, their working pressure is also gradually increasing, which cannot meet the needs. Contents of the invention [0003] The invention provides a test engine to achieve the purposes of red...

Claims

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Application Information

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IPC IPC(8): F02K9/96
CPCF02K9/96
Inventor 吴刚史丰雨吴斌曹本钊余永春陈曦
Owner HUBEI SANJIANG AEROSPACE JIANGHE CHEM TECH
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