International Journal of Aeronautical and Space Sciences

  • 제17권4호
  • /
  • Pages.526-534
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  • 2016
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  • 2093-274X(pISSN)
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  • 2093-2480(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
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Thermo-mechanical Design for On-orbit Verification of MEMS based Solid Propellant Thruster Array through STEP Cube Lab Mission

  • Oh, Hyun-Ung (Space Technology Synthesis Laboratory, Department of Aerospace Engineering, Chosun University) ;
  • Ha, Heon-Woo (Space Technology Synthesis Laboratory, Department of Aerospace Engineering, Chosun University) ;
  • Kim, Taegyu (Space Technology Synthesis Laboratory, Department of Aerospace Engineering, Chosun University) ;
  • Lee, Jong-Kwang (Micro Systems Laboratory, Department of Mechanical Engineering, Hanbat National University)
  • 투고 : 2015.10.05
  • 심사 : 2016.12.03
  • 발행 : 2016.12.30
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초록

A MEMS solid propellant thruster array shall be operated within an allowable range of operating temperatures to avoid ignition failure by incomplete combustion due to a time delay in ignition. The structural safety of the MEMS thruster array under severe on-orbit thermal conditions can also be guaranteed by a suitable thermal control. In this study, we propose a thermal control strategy to perform on-orbit verification of a MEMS thruster module, which is expected to be the primary payload of the STEP Cube Lab mission. The strategy involves, the use of micro-igniters as heaters and temperature sensors for active thermal control because an additional heater cannot be implemented in the current design. In addition, we made efforts to reduce the launch loads transmitted to the MEMS thruster module at the system level structural design. The effectiveness of the proposed thermo-mechanical design strategy has been demonstrated by numerical analysis.

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참고문헌

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