RLV reentry mathematical modeling

A reusable launch vehicle (RLV) reentry conceptual design and control modeling research were presented for scheme analysis in the preliminary design stage. The RLV aerodynamic configuration was a wing-body combination with two elevons at the wing trailing edge, a rudder on the vertical tail and a flap at the end of the body. The RCS/Aerosurfaces compound control mathematical model was developed for attitude control. In order to rapidly accomplish the preliminary aerodynamic databases, the engineering prediction method was applied to calculate the aerodynamic forces and moments. The aerodynamic regions implemented was rarefied flow, transitional flow, and hypersonic continuum flow. The control analysis supported the evolution of the design to provide an optimal design. A six degrees of freedom reentry simulation shows that the RLV aerodynamic and control model has the same flight performances as the space shuttle orbiter.