Rocket engine thrust chamber testing method

Abstract

The invention relates to the technical field of rockets, in particular to a rocket engine thrust chamber testing method. The method comprises the steps that starting operation is conducted on an engine; a propellant channel of the engine is filled with a propellant with an initial pressure value, and the initial pressure value of the propellant is smaller than a maximum opening pressure value of apropellant valve; continuous transformation is conducted on the pressure value of the propellant in the propellant channel, the range of pressure values of the engine under different working conditions in a thrust chamber test is covered with the continuous transformation pressure value range, and data under the working conditions corresponding to the different propellant pressure values are measured; and continuous transformation is conducted on the pressure value of the propellant in the propellant channel till the pressure value of the propellant is smaller than the maximum opening pressure value of the propellant valve. Therefore, testing in different working condition ranges of the engine can be achieved by adopting a conventional propellant valve, a high-pressure valve matched witha high-pressure propellant scheme does not need to be separately designed or purchased, the testing cost is reduced, and the testing period is shortened.

Description

technical field [0001] The invention relates to the technical field of rockets, in particular to a method for testing a thrust chamber of a rocket engine. Background technique [0002] At present, in the actual work of a high-thrust liquid rocket engine, propellants such as fuel and oxidant will pass through the pipeline, pass through the valve that controls the on-off of the pipeline, and then go to the thrust chamber, and then ignite through the igniter, and the gas generated by the combustion of the oxidizer and fuel will be released in the thrust chamber. It is sprayed out to realize the propulsion function of the rocket engine. In the actual work of the liquid rocket engine, when the rocket engine supplies propellant, it will use a pump pressure supply system to supply propellant with a certain pressure, so that the liquid rocket engine can be in a better working condition and obtain better propulsion. [0003] In the prior art, during the development of different type...

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Problems solved by technology

[0005] The main purpose of the present invention is to provide a rocket engine thrust chamber test method, to solve the problem of high cost in the rocket engine thrust chamber test in the prior art while realizing the test in different working condition ranges where the rocket engine is located

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