Design for aerodynamic configuration of a hypersonic axisymmetric maneuverable reentry vehicle

The problems of aerodynamic configuration design for a hypersonic axisymmetric maneuverable reentry vehicle is studied. In order to design such a maneuverable reentry vehicle which is capable of wide-range endoatmosphere maneuvering, turning off and pushing downward at a high speed, and adjustable for terminal flight parameters, and to meet the engineered requirements of integrated design or control system, the normal acceleration, maneuvering balancing ability, and influence factors of maneuvering distance are analyzed, aerodynamic characteristics of assemblies of cone and rudders are calculated by inviscid numerical calculated method corrected by past data of wind tunnel tests. The result shows that slender biconic shape with four rudders is the best aerodynamic configuration to bridge the gap between the aerodynamic requirements, i.e. higher lift, lift-drag ratio, higher rudder control efficiency, and appropriate static margin together with less load-torque. Using orthogonal design method, the impact tendency and range of different configuration parameters are obtained. Wind tunnel tests are carried out on this basis, and best shape satisfying the general technical specification is proposed . The difference between the cruciform rudders and bifurcate rudders for the chosen shape is compared, draws the conclusion that the bifurcate configuration has better aerodynamic performance no matter in lift, lift-drag ratio, rudder control efficiency, or static margin. However its engineering implementation is relatively difficult.