Abstract
The booster and orbiter stages of two-stage-to-orbit (TSTO) launch vehicles are separated at supersonic or hypersonic speed regimes under non-negligible dynamic pressure. An aerodynamic interaction exists between the vehicles during the aforementioned separation phase owing to the presence of complicated flow fields with shock wave (SW) interactions. Therefore, the separation operation and attitude control considering such interactions are crucial. In this study, the construction of a database comprising aerodynamic characteristics based on the results obtained using computational fluid dynamics (CFD) analysis is discussed. Based on the results obtained through CFD analysis, the pitch-up and pitch-down moments act on the orbiter and booster stages, respectively when two vehicles are located close. This makes the two vehicles move away from each other. By contrast, the pitch-down and pitch-up moments act on the orbiter and booster stages, respectively, when the two vehicles are located far. The aerodynamic interaction affects the pitching moment may reverse during the separation.
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© 2023 The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.
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Otsuki, T., Fujikawa, T., Yonemoto, K. (2023). Separation Characteristics of a Two-Stage-To-Orbit Winged Rocket by Aerodynamic Interaction Analysis. In: Lee, S., Han, C., Choi, JY., Kim, S., Kim, J.H. (eds) The Proceedings of the 2021 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2021), Volume 1. APISAT 2021. Lecture Notes in Electrical Engineering, vol 912. Springer, Singapore. https://doi.org/10.1007/978-981-19-2689-1_42
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DOI: https://doi.org/10.1007/978-981-19-2689-1_42
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