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 an output end, the output end is provided with at least two gas channels, one end of each gas channel communicates with the combustion chamber of the testengine unit, and the other end communicates with the external environment of the test engine unit. Each spray pipe unit is detachably connected into the corresponding gas channel. Each spray pipe unitis used for correspondingly bearing different types of throat liner test pieces. The combustion chamber is used for generating the same real gas environment for simulating a rocket engine and testingdifferent types of throat liner test pieces. 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 atthe 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 technical field of solid rocket motor testing, in particular, the present application relates to a testing device for a nozzle throat liner of a rocket motor. Background technique [0002] The nozzle of the solid rocket motor plays a role in controlling the pressure of the combustion chamber, maintaining the normal combustion of the charge, and accelerating the expansion of the gas to generate thrust. Under the scouring and ablation of high-temperature, high-velocity, two-phase flow (containing condensed phase alumina particles) gas inside the solid rocket motor, the throat diameter of the nozzle will increase, and the throat lining in the nozzle will undergo structural changes accordingly. The increase of the throat diameter of the nozzle will affect the internal ballistic characteristics of the engine, which will lead to ablation abnormalities such as broken throat liner, throat liner flying out, or excessive th...

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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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