A Numerical Study on the Effect of the Umbilical Plate on Longitudinal Controllability of a Low Aspect Ratio Launch Vehicle
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The Korea Aerospace Research Institute (KARI) is developing the Korea space launch vehicle (KSLV)-II for a flight test in 2021, and it has already produced the test launch vehicle (TLV) for a performance test of the 75 tonf liquid engine that will be used in the KSLV-II for the first time. The TLV utilizes, with slight changes, the same parts of the KSLV-II to avoid development delays and reduce development costs. In this study, the aerodynamic coefficients are predicted through a CFD analysis of the TLV with the umbilical plate used at the beginning of its development, and the flow characteristics around the umbilical plate are analyzed. In addition, we calculate the control ratio, which is the design requirement of the control system, using the predicted aerodynamic coefficients and investigated the effect of the umbilical plate mounted on the aft body of the TLV on its longitudinal stability. This study presents the aspects to be considered in the design of the umbilical plate and control system of a low aspect ratio launch vehicle.
KeywordsLaunch vehicle Umbilical plate Aerodynamic characteristics Low aspect ratio
This work was partly supported by the Korea Space Launch Vehicle II Program sponsored by the Ministry of Science and ICT and the National Research Foundation of Korea (NRF) grant funded by the Ministry of Science and ICT (NRF-2017R1A5A1015311).
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