한국항공우주학회지 (Journal of the Korean Society for Aeronautical & Space Sciences)

  • 제30권4호
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  • Pages.106-113
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  • 2002
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  • 1225-1348(pISSN)
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  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
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연성하중해석을 이용한 위성체 구조부재의 최적화

Optimization of Spacecraft Structure by Using Coupled Load Analysis

  • 황도순 (한국항공우주연구원) ;
  • 이영신 (충남대학교 기계설계공학과) ;
  • 김인걸 (충남대학교 항공우주공학과)
  • 발행 : 2002.06.01
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초록

인공위성에서 위성 구조체의 임무는 위성체의 모든 부품을 제반 환경조건 하에서 안전하게 지지하는 것이다. 위성 구조체의 안전성은 위성체 및 발사체 모델의 결합 및 하중함수로 표현되는 발사하중을 부가한 연성하중해석을 통해 최종적으로 검증된다. 본 연구에서는 구조체 무게의 감소를 위해, 발사하중상태 하에의 위성구조에 대해 직접 최적화알고리듬을 적용하였다. 위성 구조부재의 손상여부의 판단을 위한 가속도 반응은 연성하중해석의 결과를 바탕으로 얻었다. 최적화 결과, 구조부재 중량은 약 12%의 감소를 보였으며, 하니콤 심재의 두께가 성능에 크게 기여함을 알 수 있었다.

In spacecraft system, structure subsystem has the mission of supporting all the components safely under various space environmental conditions. The safety of spacecraft structure is finally verified from the coupled load analysis, which is a branch of load analysis which combines the launch vehicle and satellite. This study introduces the optimization algorithm to reduce the weight of spacecraft structure under launch environmental conditions directly. The acceleration responses are obtained by the introduction of coupled load analysis, which lead to check the failure of spacecraft structural members. The results show a 12% saving of structural weight and this saving is mainly driven by the thickness of honeycomb core, which strongly affects the natural frequencies of platforms and panels.

키워드

참고문헌

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피인용 문헌

  1. A correlation study of satellite finite element model for coupled load analysis using transmissibility with modified correlation measures vol.33, pp.1, 2014, https://doi.org/10.1016/j.ast.2014.01.002
  2. Finite Element Model Updating and Validation of Satellites for Coupled Load Analysis vol.41, pp.8, 2013, https://doi.org/10.5139/JKSAS.2013.41.8.605