Abstract:
A new reusable launch vehicle (RLV) concept FL-T1 is proposed via biconic cross section design method and the parametric geometry representation method CST based on class function and shape function. On the basis of aerodynamic force analysis regarding this configuration and matching design for the control surfaces, the aerodynamic characteristics and the control efficiency are studied for the vehicle. By the concept of multi-objective optimization, the integrated aerodynamics and aerothermodynamics optimization is conducted. It has been indicated that the proposed RLV concept FL-T1 has a high hypersonic trimming lift to drag ratio, effective deceleration ability, and acceptable heating environment. It can be considered as potential concept for future RLV. The overall performance of optimized concepts is significantly improved, compared with the original one. These optimized concepts can be considered as potential choices for future design.