Winged 로봇 모델 재진입 우주비행체의 공력 가열 특

초록

Winged robotic reusable launch vehicles (RLVs) are designed to return to Earth after space missions for subsequent reuse. During atmospheric reentry, these vehicles travel at hypersonic speeds, leading to the formation of strong shock waves and extreme aerodynamic heating on their surfaces. A robust Thermal Protection System (TPS) is essential to protect the vehicle in such environments. In this study, aerodynamic heating characteristics in hypersonic reentry environments were investigated using STAR-CCM+. Computational simulations were performed for high-altitude flight conditions, employing a 5-species and 17-reaction chemical kinetic model. The analysis compared the JBNU Winged RLV with the U.S. X-37B orbital test vehicle. The results indicated that the highest heat fluxes occurred at the nose, wing leading edges, and stabilizers for the RLV, and at the nose and wing leading edges for the X-37B. The physical mechanisms underlying the high heat fluxes were analyzed to propose shape-based mitigation strategies. It was confirmed that applying a curved wing leading edge and incorporating a sweep angle into the stabilizer significantly reduced the peak heat flux. The modified vehicle demonstrated longitudinal static stability, as indicated by negative slopes across angles of attack of 30°, 40°, and 50°.

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