两 级 入 轨 航 天 器 级 间 分 离 姿 态 精 确 控 制

Precise attitude control of the orbiter and the booster is particularly important for the interstage separation of the Two-Stage-to-Orbit（TSTO）vehicle. Numerical simulation can accurately predict interstage separation，which is a multi-body separation problem for aircraft. We use the unstructured overset grid technique and the dual-time method to couple the fluid control equations and the rigid body motion equations to solve the interstage separation process of the TSTO at an angle of attack of -2°，Mach number 6，and an altitude of 30 km，and develop a technique to optimise the attitude of the orbiter and the booster during the interstage separation process. The technique obtains the aerodynamic data of the orbiter and the booster without rudder deflection angle with the relaxation iteration method and，based on these data，designs the pitching moments to be provided by the aerodynamic and gas rudders to bring the kinematic attitudes of the orbiter and the booster closer to the design target. The numerical simulation results show that strong aerodynamic interference will exist between the two stages of the TSTO during the separation process，seriously affecting the attitude control of the two stages. The technology developed can provide a reference for the design of the aerodynamic rudder motion and gas rudder operating state of the orbiter and the booster during the separation process of the TSTO，so as to improve the efficiency and safety of the interstage separation of the TSTO.