Test engine for testing solid rocket propellant

A solid rocket and propellant technology, which is applied to rocket engine devices, machines/engines, jet propulsion devices, etc., can solve problems that affect test accuracy, large propellant dose, and unstable burning surface, and achieve convenient operation and constant burning surface , cost-saving effect

Inactive Publication Date: 2020-03-17
HUBEI SANJIANG AEROSPACE JIANGHE CHEM TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The currently used test engines usually have a large diameter. Since the propellant is obtained by wall-mounted casting, the required propellant dose is relatively large, and the combustion surface is not constant during the combustion process, which affects the test accuracy.

Method used

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  • Test engine for testing solid rocket propellant
  • Test engine for testing solid rocket propellant
  • Test engine for testing solid rocket propellant

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0028] Such as Figure 1-3 As shown, a test engine for testing solid rocket propellants includes a combustion chamber casing 1, one end of which is provided with a top cover 2, and the other end is connected with a nozzle assembly 3; The two ends of the inside of the chamber are provided with hollow-out grain support 4, and the two grain supports are arranged opposite to each other, with a propellant grain 5 installed between them, and an ignition powder pack 6 is arranged in the grain support 4 at one end of the top cover; The propellant grain is cylindrical, and the central axis is provided with an inner hole; the end face of the propellant grain is in contact with the grain bracket and is clamped tightly, and there is a gap between the outer wall of the propellant grain and the inner wall of the combustion chamber shell.

[0029] The drug column support includes a base 4-1, which is annular, and a plurality of arc-shaped support pieces 4-2 are installed on one end of the ba...

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PUM

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Abstract

The invention discloses a test engine for testing a solid rocket propellant. The test engine comprises a combustion chamber shell body, one end of the combustion chamber shell is provided with a top cover, and the other end of the combustion chamber shell is connected with a nozzle assembly; the inner part of the combustion chamber shell is provided with a propellant loading combustion chamber, the two ends of the inner part of the combustion chamber shell are each provided with a propellant column support of a hollowed-out structure, the two propellant column supports are oppositely arranged,propellant columns are installed between the two propellant column supports, and a gunpowder bag is arranged at the end, close to the top cover of each propellant column support; the propellant columns are cylindrical, and a central shaft is provided with an inner hole; and the end face of each propellant column is in contact clamping with the corresponding propellant column support, and a gap exists between the outer side wall of each propellant column and the inner wall of the combustion chamber shell. The propellant columns are stable in combustion, small in ablation and accurate in measurement, and the test engine is simple in structure, convenient to assemble and reusable.

Description

technical field [0001] The invention relates to the research field of rocket motor propellants, in particular to a test engine for testing solid rocket propellants. Background technique [0002] During the development of solid rocket propellants, in order to test the dynamic burning rate of the propellant, it is necessary to use a test engine to conduct a ground test to measure the burning rate. When measuring the existing propellant burning rate, the GJB96A-2001 standard test engine type and size is generally used The experimental engine disclosed in was tested. The currently used test engines usually have a large diameter. Since the propellant is obtained by wall-mounted casting, the required propellant dose is relatively large, and the burning surface is not constant during the combustion process, which affects the test accuracy. Contents of the invention [0003] The invention provides a test engine for testing solid rocket propellants. The propellant powder column ha...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/96F02K9/08F02K9/34F02K9/36
CPCF02K9/08F02K9/34F02K9/36F02K9/96
Inventor 曹本钊余永春吴刚吴斌陈曦
Owner HUBEI SANJIANG AEROSPACE JIANGHE CHEM TECH
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