Horizontal weak constraint cold flow solid rocket engine test bed and pulse triggering method

A solid rocket and engine technology, which is applied in rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of inconsistency between the sky and the ground that cannot be reproduced in high-altitude flight tests, unstable combustion of the engine, etc., and achieve light weight, high reliability, and Achievable strong effect

Active Publication Date: 2022-03-01
HARBIN ENG UNIV
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Problems solved by technology

[0005] The purpose of the present invention is to propose a horizontal weak-constraint cold flow solid rocket engine test bench and a pulse trigger method for the test method of the engine's unstable combustion in order to solve the inconsistency problem of the sky and the ground that the ground test of the engine cannot reproduce the high-altitude flight test

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  • Horizontal weak constraint cold flow solid rocket engine test bed and pulse triggering method
  • Horizontal weak constraint cold flow solid rocket engine test bed and pulse triggering method
  • Horizontal weak constraint cold flow solid rocket engine test bed and pulse triggering method

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Embodiment Construction

[0040] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0041] The test engine in this embodiment adopts conventional solid rocket motor, and carbon fiber composite material is selected as the engine casing, which has the characteristics of high strength and low mass. Engines of different diameters and lengths are available for practical testing.

[0042] Such as figure 1 As shown, the horizontal weakly constrained cold flow solid rocket motor test bench includes a support structure and a test structure. The support structure includes a base, a thrust support wall, a slide rail, a slider, a safety limit device, a head snap ring, A force hammer and a spring hook, a thrust support wall is installed on one side of the base, the thrust support wall is connected with the slide rail, the slide rail is fixed on the base, and the slide rail is provided with two sliders, on which A head snap ring...

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Abstract

According to the horizontal type weak constraint cold flow solid rocket engine test bed and the pulse triggering method, the weak constraint cold flow solid rocket engine test bed can release the tail freedom degree of an engine, and the tail freedom degree and the original resonance mode of the engine are guaranteed in the mode that one end is fixedly supported and the other end is simply supported; a test method is provided for the heaven and earth consistency of an unstable combustion test, and the real high-altitude flight working condition is better reproduced. And meanwhile, ground reproduction of air flight conditions is realized by using a method of internal ignition powder explosion and external force hammer knocking. The method has the advantages of being simple in principle, high in adaptability and weak in constraint on the projectile body, and has a good application prospect in an unstable combustion experiment.

Description

technical field [0001] The invention relates to the technical field of rocket motor testing, in particular to a horizontal weakly constrained cold flow solid rocket motor test bench and a pulse trigger method. Background technique [0002] Unstable combustion of solid rocket motors means that the pressure in the combustion chamber deviates from the law predetermined by the designer, resulting in transient pressure changes. Nowadays, the equipment of high-energy charges in solid rocket motors makes the working environment of the motors even worse. The inside of the motors is exposed to high-temperature and high-pressure environments, and small disturbances may cause abnormal ballistic pressure inside the motor, irregular vibration of the shell, and irregularities in the outer ballistic curve. Deviated or even exploded situations. In the ground test vehicle, due to the strong constraints on the shell, it is impossible to completely reproduce the flight state. Regarding the i...

Claims

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Application Information

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IPC IPC(8): F02K9/96
CPCF02K9/96
Inventor 王革周博成杨铭义蒲炜强王志邦李德坚杨海威关奔
Owner HARBIN ENG UNIV
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