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Chinese Journal of Space Science ›› 2017, Vol. 37 ›› Issue (6): 748-751.doi: 10.11728/cjss2017.06.748

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An Optimization Design Method for Thermal Control of Satellite Propulsion Subsystem

ZHOU Yangeng1, ZHOU Xiujuan2, ZHANG Yu1, ZHAO Jizhe1, WU Zishuai1, GUI Lijia1, HU Xiaokang1   

  1. 1. Shanghai Institute of Satellite Engineering, Shanghai 201109;
    2. Shanghai Aerospace Electronic Technology Institute, Shanghai 201109
  • Received:2016-06-08 Revised:2017-09-06 Online:2017-11-15 Published:2017-11-10

Abstract:

The conventional thermal control requirements of satellite propulsion subsystem are that the pipings and parts of hydrazine tank need tropical winding and multilayer coating. In this paper, an optimization design for thermal control of propulsion subsystem under a new type of propellant is proposed, in which the propulsion module controlled heat treatment measures are cancelled, the propulsion module outer plate is coated with multiplayer insulation components, and compensation heating for electromagnetic valve is adopted. Thermal balance testing and in-orbit validation are conducted for thermal control propulsion subsystem with optimized design. The results show that the level of propulsion subsystem temperatures and power requirements can meet the requirements of current range of domestic thermal control of satellites. Optimized design of the propulsion subsystem thermal control have the advantages of low power consumption, light weight and easiness of assembly. By combining with the satellite configuration, the subdivision operation can be achieved.

Key words: Satellite propulsion subsystem, Thermal control, Optimization design, Operation subdivision

CLC Number: