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Optimization Design of Space Launch Vehicle Using Genetic Algorithm

유전 알고리즘을 이용한 우주 발사체 통합 최적 설계

  • Lee, Kangkyu (Department of Aerospace Engineering, Inha University) ;
  • Cha, Seung-won (Department of Aerospace Engineering, Inha University) ;
  • Yang, Sungmin (Department of Aerospace Engineering, Inha University) ;
  • Kim, Yong-chan (Department of Aerospace Engineering, Inha University) ;
  • Oh, Seok-Hwan (Department of Aerospace Engineering, Inha University) ;
  • Lee, Sangbok (Department of Aerospace Engineering, Inha University) ;
  • Roh, Tae-Seong (Department of Aerospace Engineering, Inha University)
  • Received : 2017.09.11
  • Accepted : 2017.12.18
  • Published : 2018.08.01

Abstract

A system design and integrated design process for a space launch vehicle were established based on system engineering. With the mission design results for a given payload weight and trajectory, it is possible to perform optimal design by integrating each unit such as propulsion, weight estimation, and aerodynamic force after analysis, during in the system design process. The program is finally configured to verify that the designed vehicle can perform its mission through 3-DOF trajectory optimization simulation. Genetic algorithms are used as the optimization method, and the optimal design results of the variables and parameters to be considered during design are presented.

본 논문에서는 시스템 엔지니어링을 기반으로 우주 발사체의 시스템 설계를 정립하여 통합 설계할 수 있는 프로세스를 정립하였다. 주어진 페이로드 중량과 궤적에 대한 임무 설계 결과를 바탕으로, 시스템 설계 단계에서는 추진, 무게 추정, 공력 등의 각 단위별 해석을 진행한 후 통합하여 최적 설계를 수행될 수 있도록 하였다. 최종 단계에서는 설계된 발사체를 3-자유도 궤적 최적화 시뮬레이션을 통해 임무를 수행할 수 있는지 확인하도록 프로그램을 구성하였다. 최적 설계 기법으로는 유전 알고리즘을 이용하였으며, 이를 이용하여 설계 시 고려해야 할 변수와 파라미터들의 최적 설계 결과를 제시하였다.

Keywords

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