Volume 37 Issue 6
Nov.  2017
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ZHOU Yangeng, ZHOU Xiujuan, ZHANG Yu, ZHAO Jizhe, WU Zishuai, GUI Lijia, HU Xiaokang. An Optimization Design Method for Thermal Control of Satellite Propulsion Subsystem[J]. Journal of Space Science, 2017, 37(6): 748-751. doi: 10.11728/cjss2017.06.748
Citation: ZHOU Yangeng, ZHOU Xiujuan, ZHANG Yu, ZHAO Jizhe, WU Zishuai, GUI Lijia, HU Xiaokang. An Optimization Design Method for Thermal Control of Satellite Propulsion Subsystem[J]. Journal of Space Science, 2017, 37(6): 748-751. doi: 10.11728/cjss2017.06.748

An Optimization Design Method for Thermal Control of Satellite Propulsion Subsystem

doi: 10.11728/cjss2017.06.748
  • Received Date: 2016-06-08
  • Rev Recd Date: 2017-09-06
  • Publish Date: 2017-11-15
  • 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.

     

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  • [1]
    MA Wei, XUAN Yimin, HAN Yuge. Thermal design and infrared characteristics of the satellite[J]. Spacecr. Eng., 2009, 18(2):48-54
    [2]
    MIN Guirong. Satellite Thermal Control Technology[M]. Beijing:China Astronautics Publishing House, 1991
    [3]
    CHEN Jianxin, LIU Weiqiang. Research on thermal analysis for some remote sensing satellite[J]. Aerosp. Shanghai, 2011, 28(3):46-49
    [4]
    HOU Zengqi, HU Jin'gang. Spacecraft Thermal Control Techniques——Principles and Application[M]. Beijing:China Science and Technology Press, 2007
    [5]
    LI Guoqiang. Discuss about system and robust design of spacecraft thermal control[J]. Spacecr. Eng., 2013, 22(5):52-55
    [6]
    WU Wenrui, HUANG Hai. Analysis and optimization of SSO satellite thermal control subsystem[J]. Spacecr. Eng., 2012, 21(2):44-49
    [7]
    XU Xianghua, CHENG Xuetao, LIANG Xin'gang. Ana-lysis on space thermal environment for circular sun-synchronous orbit[J]. J. Astronaut., 2012, 33(3):399-404
    [8]
    HAN Yuge, XUAN Yimin. Parameter sensitivity analysis for the satellite thermal design[J]. Chin. J. Computat. Phys., 2004, 21(5):455-460
    [9]
    MEGAHED A, EL-DIB A. Thermal design and analysis for battery module for a remote sensing satellite[J]. J. Spacecr. Rockets, 2007, 44(4):920-926
    [10]
    BALDAUFF R W, ARMIGER W J, HOANG T T. Design and analysis of the thermal control system for the TacSat-4 spacecraft COMMx payload[R]. NRL Rev., 2009, 11(3):114-124
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