Aerodynamic characteristic study of space launch vehicle in ground tests = 지상시험을 통한 우주발사체의 공력특성 연구

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The experimental research on a high-altitude environment experiment of space launch vehicle is important for securing independent technologies with launching space vehicles and completing missions. In the ground test facility, scaled down test models should be used and this is accompanied by various similarities. In addition, free-stream is maintained along the flow direction in a real space launch vehicle having a large length to diameter ratio, but an artificial free-stream recovery is required in the case of the afterbody of the scaled down model in which free-stream is difficult to retain. In this study, high-altitude environment experiment and shock-free technique for free-stream recovery were developed and verified. The effect of the shape of the support for fixing the test model on the flow interference was compared by applying shock-free technique. And, a study was carried out to apply the shock-free technique and the thruster module to confirm the flow interference between the free-stream and exhaust plumes on the base plane, which is the most complicated part of high-altitude environment experiment study. From the results of the flow verification tests, it was confirmed that the flow was replicated with the error of about $\pm 3%$. The error between the slope angle of inclined shockwave of the scaled down transition section model using the shock-free shape and the slope angle of the horizontal plate model, and between the theoretical and the experimental value of the static pressure of the model were confirmed to be 2% and 1%, respectively. As a result, the efficiency of the shockwave cancellation technique has been verified. From the thruster test, not only a shockwave pattern, but a flow-field pattern from the mutual interaction between the exhaust plume and the free-stream undisturbed flow, was experimentally observed.
Advisors
Park, Gisuresearcher박기수researcher
Description
한국과학기술원 :항공우주공학과,
Publisher
한국과학기술원
Issue Date
2018
Identifier
325007
Language
eng
Description

학위논문(박사) - 한국과학기술원 : 항공우주공학과, 2018.8,[vi, 104 p. :]

Keywords

high-altitude environment experiment▼aflow verification▼aflow interference▼athruster module; 고공환경모사실험▼a유동검증▼a충격파 상쇄 기법▼a유동교란▼a추력기 모듈

URI
http://hdl.handle.net/10203/265400
Link
http://library.kaist.ac.kr/search/detail/view.do?bibCtrlNo=828282&flag=dissertation
Appears in Collection
AE-Theses_Ph.D.(박사논문)
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