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

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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High-Altitude Environment Simulation of Space Launch Vehicle Including a Thruster Module

추력기 모듈을 포함한 우주발사체 고공환경모사

  • Lee, Sungmin (Korea Advanced Institute of Science and Technology) ;
  • Oh, Bum-Seok (Korea Aerospace Research Institute) ;
  • Kim, YoungJun (Korea Aerospace Research Institute) ;
  • Park, Gisu (Korea Advanced Institute of Science and Technology)
  • Received : 2018.01.17
  • Accepted : 2018.09.05
  • Published : 2018.10.01
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Abstract

In this work, the high-altitude environment simulation study was carried out at an altitude of 65 km exceeding Mach number of 6 after the launch of Korean Space Launch Vehicle using a shock tunnel. To minimize the flow disturbance due to the strut support of test model as much as possible, a few different types of strut configurations were considered. Using the configuration with minimum disturbance, the high-altitude environment simulation experiment including a propulsion system with a single-plume, was conducted. From the thruster test through flow visualization, not only a shockwave pattern, but a general flow-field pattern from the mutual interaction between the exhaust plume and the free-stream undisturbed flow, was experimentally observed. The comparison with the computation fluid dynamic(CFD) results, showed a good agreement in the forebody whereas in the afterbody and the nozzle the disagreement was about ${\pm}7%$ due to unwanted shockwave formation emanated from the nozzle-exit.

본 연구에서는, 충격파 터널을 이용하여 한국형발사체의 발사 후 마하수 6을 돌파하는 고도 65 km에서의 고공환경모사 연구를 수행하였다. 시험모델을 고정하는 지지대로 인한 유동교란 최소화를 위해 여러 다른 지지대 형상을 고려하였으며, 교란이 최소화된 지지대를 적용한 추력기 시험모델을 사용하여 단발-플룸의 추진기관을 포함한 고공환경모사 실험을 수행하였다. 가시화기법을 통한 추력기 시험을 통해 충격파 패턴뿐만 아니라 배기 플룸과 자유류 유동 간의 상호작용으로 발생하는 전반적인 유동 패턴을 실험적으로 확인하였다. 전산해석결과와 실험결과와의 비교를 통해 선단에서의 충격파 위치는 동일, 후단과 노즐부에서는 불필요 충격파로 인한 ${\pm}7%$의 오차 발생이 확인되었다.

Keywords

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