Upstream propellant temperature control device used after stopping of attitude and orbit control engine

Abstract

The invention discloses an upstream propellant temperature control device used after stopping of an attitude and orbit control engine, and relates to the technical field of liquid attitude and orbit control engines of the aeronautic propulsion technical field. The upstream propellant temperature control device comprises a storage box, an output pipeline, an upstream containing cavity, an engine solenoid valve, a circulation pump and a return pipeline, wherein the storage box is of a hollow spherical structure; the storage box, the output pipeline and one end of the upstream containing cavity communicate with one another in sequence; the engine solenoid valve is fixedly mounted at the top of the upstream containing cavity and communicates with the upstream containing cavity; the engine solenoid valve communicates with an external thrust chamber; one end of the return pipeline communicates with the upstream containing cavity; the other end of the return pipeline communicates with the output pipeline; and the circulation pump is arranged on the return pipeline and is close to the joint of the return pipeline and the upstream containing cavity. The situation that a propellant is overheated due to stopping heat contra-soak, aerodynamic heating and the like is effectively avoided, and the situation that the propellant is supercooled and frozen due to space cryogenic environment cooling and the like is also avoided, so that the safety and reliability of the engine are improved.

Description

technical field [0001] The invention relates to the technical field of a liquid orbit attitude control engine in the field of aerospace propulsion technology, in particular to a valve front propellant temperature control device after the orbit attitude control engine stops. Background technique [0002] Orbit attitude control engines mostly adopt compressed gas extrusion supply mode, that is, the propellant in the storage tank enters the output pipeline 2 under the action of compressed gas pressure, and is delivered to the front of the engine solenoid valve. When the solenoid valve is opened, propellant enters the thrust chamber and the engine starts to work. When the solenoid valve is closed, the engine stops. After the engine is shut down, the propellant in front of the solenoid valve stops flowing. At this time, the temperature of certain local propellants in front of the valve may rise or fall sharply due to factors such as engine shutdown heat back soaking, aerodynamic...

AI Technical Summary

Problems solved by technology

However, in some special applications (such as the temperature control of the propellant in the cooling channel of the regenerative cooling thrust chamber before the valve, and for example, the heat insulation or heat dissipation device cannot be installed due to the engine structure and weight restrictions), the traditional method cannot be used

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