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Chinese Journal of Space Science ›› 2016, Vol. 36 ›› Issue (3): 380-385.doi: 10.11728/cjss2016.03.380

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A Balanced Satellite Thermal Control Optimization Method for Different Orbit and Attitude

ZHOU Yangeng   

  1. Shanghai Institute of Satellite Engineering, Shanghai 201109
  • Received:2015-11-12 Revised:2016-03-02 Online:2016-05-15 Published:2016-06-06

Abstract:

Based on analysis of the thermal control design of traditional satellites,an optimization method for satellite thermal design which is applicable to both Sun-synchronous orbit and lowinclination orbit is presented.Using this optimization method,thermal simulation analysis is made for a satellite under both orbit conditions,and the satellite thermal balance test and in-orbit validation are conducted for the Sun-synchronous orbit.Combined with thermal simulation results,it is shown that the thermal design of low-inclination orbit satellite conditions can reduce the ground test verification,shorten the satellite development cycle and save the costs significantly.This research work can provide reference for the design optimization of satellite thermal control.

Key words: Thermal control design, Optimization methods, Thermal simulation, Development cycle

CLC Number: