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Low temperature and small flow precooling system and precooling method for liquid rocket engine test

A liquid rocket, small flow technology, used in engine testing, machine/structural component testing, measuring devices, etc., can solve problems such as large liquid oxygen consumption, achieve high thermal insulation effect, ensure pre-cooling effect, and improve flow rate The effect of controlling precision

Active Publication Date: 2019-07-16
XIAN AEROSPACE PROPULSION TESTING TECHN INST
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Problems solved by technology

[0007] In order to solve the problem that the existing pre-cooling system in the background technology is only applicable to a single engine and the liquid oxygen consumption in the pre-cooling process is large, the present invention provides a low-temperature and small-flow pre-cooling system and a pre-cooling method for liquid rocket engine tests

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  • Low temperature and small flow precooling system and precooling method for liquid rocket engine test

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Embodiment Construction

[0044] The invention relates to a low-temperature and small-flow precooling system and a precooling method for liquid rocket engine tests, which are suitable for liquid rocket engine tests using low-temperature media as propellants, such as liquid oxygen kerosene engines, liquid hydrogen liquid oxygen engines, and liquid oxygen methane engines. .

[0045] The system includes a precooling main pipeline, a symmetrical pipeline unit, a flow temperature measurement unit, a temperature pressure measurement unit and a state switching unit, which constitute an engine precooling system.

[0046] The symmetrical pipeline unit includes at least 2N extension pre-cooling pipes; each extension pre-cooling pipe corresponds to an engine; every two extension pre-cooling pipes form a group, one end of which is respectively connected to the two engine pre-cooling outlets, and the other end is merged Then connect to the entrance of the pre-cooling main pipeline; N≥2; the flow temperature measuri...

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Abstract

The invention relates to a low temperature and small flow precooling system for a liquid rocket engine test and a precooling method. The system comprises a precooling general pipeline, a symmetric pipeline unit, a flow measurement unit, a temperature and pressure measurement unit and a state switching unit, wherein the symmetric pipeline unit comprises at least 2N branch precooling pipelines, eachbranch precooling pipeline is corresponding to one engine, each two branch precooling pipelines forms a group, one ends are in butt joint with precooling exhaust ports of two engines respectively, the other ends are merged to be connected to the inlet of the precooling general pipeline, and N is no smaller than 2; and the flow temperature measurement unit, the temperature and pressure measurementunit and the state switching unit are sequentially and serially connected from the inlet of the precooling general pipeline to the outlet of the precooling general pipeline. The system precooling method comprises steps of 1) pipeline precooling, 2) exhaust, 3) small flow exhaust, 4) temperature judgment and 5) large flow exhaust. The system and the method of the invention solve the problems thatthe existing precooling system is only suitable for a single engine and the liquid oxygen consumption amount during the precooling process is large can be solved.

Description

technical field [0001] The invention belongs to the technical field of aerospace engine tests, and in particular relates to a low-temperature and small-flow precooling system and a precooling method for liquid rocket engine tests. Background technique [0002] A certain type of launch vehicle is equipped with four liquid oxygen / kerosene engines, and the four engines are connected in parallel. According to rocket flight requirements, it is necessary to implement asynchronous shutdown of parallel engines. In order to avoid the temperature recovery of the engine after shutting down, which will cause the temperature of the oxidant inlet of the working engine to rise and affect the work, it is necessary to pre-cool the shut down engine. Since the oxidizer carried by the rocket itself is limited, in order to save the oxidant, it is necessary to select the optimal pre-cooling discharge flow. In order to simulate this state on the ground, it is necessary to establish a liquid rock...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M15/02
CPCG01M15/02
Inventor 高强孙乐向民肖彬唐斌运
Owner XIAN AEROSPACE PROPULSION TESTING TECHN INST
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