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Volume 42 Issue 2
Feb.  2016
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Journal of Beijing University of Aeronautics and Astronautics  > 2016  >  42(2): 391-399.
HAN Weitao, LIU Gang, SUN Jinji, et al. Thermal-structure coupling analysis and research of MSCMG[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(2): 391-399. doi: 10.13700/j.bh.1001-5965.2015.0097(in Chinese)
Citation: HAN Weitao, LIU Gang, SUN Jinji, et al. Thermal-structure coupling analysis and research of MSCMG[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(2): 391-399. doi: 10.13700/j.bh.1001-5965.2015.0097(in Chinese)
shu

Thermal-structure coupling analysis and research of MSCMG

doi: 10.13700/j.bh.1001-5965.2015.0097
  • 1.

    School of Instrumentation Science and Opto-electronics Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

  • 2. Science and Technology on Inertial Laboratory, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

  • Received Date: 15 Feb 2015
  • Publish Date: 20 Feb 2016
    Abstract
  • As a novel actuator for spacecraft attitude maneuver, magnetically suspended control moment gyroscope (MSCMG) operates in a high vacuum with high speed rotor suspended, leading to poor dissipating heat conditions and high system temperature, which result in the larger thermal stress and weaken the structure strength of MSCMG. To reduce the influence of temperature field on the strength of MSCMG components and improve the reliability of MSCMG structure, finite element method is applied to calculate the temperature field of MSCMG under the working state and analyze the stress distribution in MSCMG components based on the temperature field to understand the influence of temperature field on the mechanical properties of MSCMG components. Moreover, the thermal network model of MSCMG is established. The heat flux path and the factors influencing temperature are analyzed according to the thermal network model and the thermal network equations. And then, the optimization measurements are put forward. After optimization, the maximum temperature of stator assembly decreases from 66.5℃ to 49℃ and that of rotor assembly decreases from 91.7℃ to 76.9℃.In addition, the safety factor of stator assembly increases from 1.52 to 1.73 (increases by 13.8%) and that of rotor assembly increases from 1.32 to 1.56 (increases by 18.2%).

     

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