Engine servo mechanism with heat proof and heat radiation integrated thermal control

Abstract

The invention provides an engine servo mechanism with heat proof and heat radiation integrated thermal control; the engine servo mechanism comprises a thermal control coating, a multilayer, heaters and thermistors; one side, far away from the engine, of a servo mechanism is a heat radiation surface, and the heat radiation surface employs the thermal control coating; one side, facing the engine, ofthe servo mechanism is wrapped by the multilayer so as to provide heat leak and thermal protection functions; a main heater and a backup heater are bonded on the surface of the servo mechanism so asto make temperature compensating control, and a main thermistor and a backup thermistor are bonded to serve as temperature measurement and control points; the servo mechanism and the engine mounting surface are installed in a heat insulation manner. The engine servo mechanism thermal protection and heat radiation integrated thermal control can be realized, thus providing temperature compensating control in on-orbit long term storage, realizing massive heat diffusion in short term working, providing high temperature thermal protection in engine working, and solving the multiple difficult thermal control problems that the servo mechanism faces under different work modes and thermal environments, such as long term standby, short time working and engine high temperature influences.

Description

technical field [0001] The invention relates to an engine servomechanism, in particular to a thermal control for an engine servomechanism in orbital storage, work and heat protection. Background technique [0002] In order to realize the ability of multi-orbit deployment, an aircraft is equipped with a high-thrust two-way swing orbital control engine, and the two-way swing capability of the engine is realized through two high-power servo mechanisms. This type of servo mechanism has high requirements for on-orbit temperature control (-35~+70°C), long single working time (120s), many times of work during on-orbit deployment (two times per orbit), and high short-term power consumption during operation ( 64W / set), and its installation position is relatively close to the engine. In view of these tasks and environmental characteristics, this kind of servo mechanism is faced with the influence of on-orbit thermal environment changes, bottom engine plume and heat radiation, etc., a...

AI Technical Summary

Problems solved by technology

This type of servo mechanism has high requirements for on-orbit temperature control (-35~+70°C), long single working time (120s), many times of work during on-orbit deployment (two times per orbit), and high short-term power consumption during operation ( 64W / set), and its installation position is relatively close to the engine

In view of these tasks and environmental characteristics, this kind of servo mechanism is faced with the influence of on-orbit thermal environment changes, bottom engine plume and heat radiation, etc., and it is necessary to solve thermal control difficulties such as long-term standby, short-time work, and high-temperature effects of the engine. Design brings great difficulty

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