Testing device for rocket engine nozzle throat liner

Abstract

The embodiment of the invention provides a testing device for a rocket engine nozzle throat liner. The testing device comprises a test engine unit and at least two spray pipe units. The test engine unit is provided with a combustion chamber and at least two output ends, each output end is provided with a gas channel, and the two ends of each gas channel communicate with the combustion chamber of the test engine unit and the external environment of the test engine unit separately. Each spray pipe unit is detachably connected into the corresponding gas channel. Each spray pipe unit is used for correspondingly bearing different types of throat liner test pieces. The combustion chamber is used for generating a real gas environment simulating a rocket engine and testing the throat lining test pieces at the at least two output ends. According to the embodiment of the testing device for the rocket engine nozzle throat liner, different types of throat liner test pieces can be ablated at the same time in the same ablation test, the real same test environment is realized, the ablation performance comparison assessment precision of different types of throat liner test pieces can be greatly improved, and the test cost is reduced.

Description

Technical field [0001] The present application relates to the field of solid rocket engine testing, and in particular, the present application relates to a test device of a rocket engine nozzle throat. Background technique [0002] The nozzle of the solid rocket engine has a function of controlling the combustion chamber pressure, maintaining normal combustion of the drug, and accelerates the gas expansion to generate thrust. Under the internal temperature, high speed, two-phase flow (condensate-containing alumina particles) of the solid rocket engine, the throat of the nozzle increases, and the throat in the nozzle will change in the nozzle. The throat of the nozzle affects the engraving characteristics of the engine, which in turn triggers abnormal abnormality such as laryngeal disruption, laryngeal flying or excessive abnormality, etc., may cause serious consequences that the solid rocket engine cannot work properly. For example, the larynarin structure that occurs due to exce...

AI Technical Summary

Problems solved by technology

[0004] 1. The test environment is quite different from the real working environment, and the accuracy of the ablation performance parameters obtained by the test is low;

[0005] 2. A single test is limited to the ablation of a single throat liner specimen, and it is difficult to reproduce the same high-precision test environment by using divided tests for throat liner specimens of different types (for example, different types, or different batches, etc.) , that is, the accuracy of the ablation performance parameters of each throat liner specimen obtained through the batch test under the same test environment is low;

[0006] 3. A single test is limited to the ablation of a single throat liner specimen. The fuel and time consumed in each test can only obtain the ablation performance parameters of one throat liner specimen, and the test cost is high

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