Study of an Air Inlet for New Sounding Rocket with ATRIUM Engine

令和4年度宇宙輸送シンポジウム（2023年1月12日-13日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)) , 相模原市, 神奈川県
Space Transportation Symposium FY2022 (January 12-13, 2023. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan
ISAS/JAXA has been conducting research and development of a reusable sounding rocket equipped with ATRIUM engine, which combines an air-turbo engine and a rocket engine. An air inlet for the vehicle is streamline-traced Busemann inlet. It has notched cowls, but one of them will be blocked by the vehicle surface. The wind tunnel experiment showed that blockage of the cowl notch caused a 2–4 % reduction in performance such as mass capture ratio (MCR) and total pressure recovery (TPR) of the inlet. In any case, the inlet was not in a perfect starting condition because a shock wave and boundary layer separation occurred near the entrance of it regardless of the amount of back pressure. The results of the CFD simulation conducted under the same condition as the wind tunnel experiment agreed well with the experimental results and validated them.
資料番号: SA6000184014
STCP-2022-014