Journal of Aerospace System Engineering (항공우주시스템공학회지)

The Society for Aerospace System Engineering (항공우주시스템공학회)
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Optimal Design of a Composite Solar Panel for Vibration Suppression

진동 저감을 위한 복합재료 태양전지판의 최적설계

  • Kim, Yongha (Graduate School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Kim, Hiyeop (Graduate School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Park, Jungsun (Department of Aerospace and Mechanical Engineering, Korea Aerospace University)
  • 김용하 (한국항공대학교 일반대학원 항공우주 및 기계공학과) ;
  • 김휘엽 (한국항공대학교 일반대학원 항공우주 및 기계공학과) ;
  • 박정선 (한국항공대학교 항공우주 및 기계공학부)
  • Received : 2018.09.27
  • Accepted : 2018.11.17
  • Published : 2018.12.31
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Abstract

This paper proposes the use of supports as passive vibration absorber to a composite solar panel for a high-agility satellite. We further defined the dynamic model of the composite solar panel with the help of the Ritz method and verified vibration suppression performance of the support by performing vibration analysis. Finally, this research ensures optimal design of the composite solar panel with the support for maximizing vibration suppression performance in limited mass. The proposed results of the optimal design can be applied in actual structural design of satellites.

본 논문에서는 고기동 위성의 진동 저감을 위해 지지대를 복합재료 태양전지판에 적용하였다. 또한 리츠 법을 이용하여 지지대를 포함한 복합재료 태양전지판의 동역학적 모델을 정의하였으며, 지지대가 포함되지 않은 복합재료 태양전지판과 비교하여 지지대의 진동 흡수 성능을 확인하였다. 제한된 질량 내에서 진동 흡수 성능을 최대화하기 위해 정의된 동역학적 모델을 이용하여 지지대를 포함한 복합재료 태양전지판의 설계변수에 대한 최적설계를 수행하였으며, 최적화된 전개 고정형 복합재료 태양전지판의 설계안을 도출하였다.

Keywords

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Fig. 1 Deployable Solar Panel

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Fig. 2 Schematic of a composite solar panel with a support

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Fig. 3 Objective Function History

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Fig. 4 Result of the Frequency Response Analysis

Table 2 Dimensions of the Composite Solar Panel

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Table 3 Material Properties of CFRP (HEXCEL)

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Table 4 Optimization Results

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