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Experimental method and experimental device for simulating the ablation of double-pulse solid rocket motors

A rocket engine and experimental device technology, applied in jet engine testing, gas turbine engine testing, chemical analysis by combustion, etc., can solve the problem of not being able to study the influence of ablation characteristics of thermal insulation materials, and not being able to better simulate the work of double-pulse engines environment and other issues to achieve the effect of shortening the interval time

Active Publication Date: 2020-07-21
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0008] The purpose of the present invention is to provide an experimental method and experimental device for simulating the ablation of double-pulse solid rocket motors, so as to solve the problem of the inability to study the influence of pulse interval time on the ablation characteristics of thermal insulation materials in the prior art and the inability to better simulate double-pulse solid rocket motors. Problems in the working environment of pulse engines

Method used

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  • Experimental method and experimental device for simulating the ablation of double-pulse solid rocket motors
  • Experimental method and experimental device for simulating the ablation of double-pulse solid rocket motors

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Embodiment

[0075] The present invention is used for the structure of the experimental device of ground simulation dual-pulse solid rocket motor ablation:

[0076] like figure 1 As shown, it includes a first fixed experimental device and a second fixed experimental device fixedly installed on the top surface of the platform. The two fixed experimental devices have the same orientation and are set at a certain distance.

[0077] The first fixed experimental device includes a combustion section and a first pulse converging section 5 connected to each other. The combustion section includes a first top cover 1 and a first pulse combustion chamber 4 connected in sequence. Propellant 2.

[0078] The second fixed experimental device comprises a combusting section and a second pulse converging section 13 which are arranged in communication, and the combustion section includes a second top cover 17 and a second pulse combustion chamber 14 connected in sequence, and a second pulse is placed inside...

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Abstract

The present invention discloses an experimental method and an experimental device for simulating ablation of a double-pulse solid rocket engine. The experimental method comprises: performing a first ablation experiment in a first rocket engine; after the experiment is completed, separating an experimental section and a first convergence section; assembling the experimental section and a second convergence section into a second rocket engine; and after a certain time interval, performing a second ablation experiment in the second rocket engine. According to the technical scheme of the present invention, the problems of the failure to research the influence of the pulse interval time on the ablation characteristics of the thermal insulation material and the failure to better simulate the working environment of the double-pulse engine are solved.

Description

【Technical field】 [0001] The invention belongs to the technical field of thermal insulation material ablation, and in particular relates to an experimental method and an experimental device for simulating the ablation of a double-pulse solid rocket motor on the ground. 【Background technique】 [0002] In order to effectively improve the missile's survivability and combat capability, increase its range, and rationally distribute and use energy, sometimes it is necessary to start the engine multiple times. Therefore, the use of multi-pulse solid rocket motors that can be ignited multiple times is the development trend of missile power plants in the future, and the current mainstream is double-pulse solid rocket motors. The working process of the double-pulse rocket engine is divided into I pulse-interval period-II pulse, and has two independent working processes. In the environment of traditional solid rocket motors, the ablation of thermal insulation materials is a continuous...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01N31/12G01M15/14
CPCG01M15/14G01N31/12
Inventor 李江惠昆刘洋祝山
Owner NORTHWESTERN POLYTECHNICAL UNIV
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