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2020 Vol.39, Issue 4 Preview Page

Research Article

Design of launch pad for mitigating acoustic loads on launch vehicle at liftoff

우주발사체 발사 시 음향하중 저감을 위한 발사대 설계

Seiji Tsutsumi1∗
1Japan Aerospace Exploration Agency
∗Corresponding Author
31 July 2020. pp. 331-341
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Abstract

At liftoff, launch vehicles are subject to harmful acoustic loads due to the intense acoustic waves generated by propulsion systems. Because these waves can cause electronic and mechanical components of launch vehicles and payloads to fail, predicting and mitigating acoustic loads is an important design issue. This article presents the latest information about the generation of acoustic waves and the acoustic design methods applicable to the launch pad. The development of the Japanese Epsilon solid launcher is given as an example of the new methodology for launch pad design. Computational fluid dynamics together with 1/42 scale model testing were performed for this development. Effectiveness of the launch pad design to reduce acoustic loads was confirmed by the post-flight analysis.

Keywords
Launch vehicle
Aeroacoustics
Computational fluid dynamics
Computational aeroacoustics

우주발사체는 발사 시 추진장치에서 발생하는 고강도 소음에 의한 음향하중의 영향을 받는다. 로켓소음은 발사체와 페이로드 내 전자 및 기계 부품의 손상 및 오작동을 유발할 수 있기 때문에 음향하중의 예측 및 저감은 설계에 있어 중요한 고려사항이다. 본 논문에서는 로켓 소음의 생성 및 발사대의 음향설계 기법에 대한 최신 연구동향을 논하였다. 특히, 새로운 발사대 설계 방법론의 예로서 일본 Epsilon 로켓 발사대의 개발과정을 기술하였다. 전산유체역학 모사 및 1/42 축소모형 실험을 통하여 설계된 발사대의 음향하중 저감 효과를 Epsilon 로켓의 실제 비행 데이터 분석을 통하여 검증하였다.

키워드
우주발사체
공력음향학
전산유체역학
전산공력음향학
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Information
  • Publisher :The Acoustical Society of Korea
  • Publisher(Ko) :한국음향학회
  • Journal Title :The Journal of the Acoustical Society of Korea
  • Journal Title(Ko) :한국음향학회지
  • Volume : 39
  • No :4
  • Pages :331-341
  • Received Date : 2020-06-17
  • Accepted Date : 2020-07-18
  • DOI :https://doi.org/10.7776/ASK.2020.39.4.331
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