DEVELOPMENT OF AEROSHAPE AND INVESTIGATION OF SMALL-SIZED WINGED RE-ENTRY VEHICLE AEROTHERMODYNAMIC CHARACTERISTICS

The search for an efficient, small-sized winged re-entry vehicle aeroshape is considered. Problem solving involves an iteration process aimed at changing initial aerodynamic external aeroshape in order to realize given performance characteristics. The computation of aerodynamic characteristics at every iteration step is completed using software packages based on different engineering techniques. Estimation of descent trajectory parameters involves searching for the optimal trajectory, and realizing the maximum cross range at given equilibrium temperature limitations, for example, at stagnation points of aeroshape elements. For this reason the shape of perspective small-sized winged re-entry vehicle aeroshapes is worked out. The defining feature of the aeroshape is that its shape, size, and wing location provide not only balancing and stability, but also the necessary value of lift at all flight modes. The shape of the nose section, the airfoil, and the value of leading-edge sweep enabled realization of acceptable heat fluxes on the vehicle surface at hypersonic speeds.