关键词: 航天飞机, 高超音速流动, 气动力系数, 有限元法, 数值计算

Abstract:

In the designing stage of new space transportation vehicles, the local method is widely used to fulfill the task of analysing and comparing the performances of different shapes in differ ent flow regimes. In its orginal form of the local method, the calculation of the shape functions is complicated and confined to the axisymmetric bodies composed of simple geometric configurations. The local method incorporated with the boundary finite elements proposed by the authors in the preceding paper is applied to construct the shape functions without invoking the complexity in carrying out the surface quadratures and of numerical tables. The calculations are performed for the STS-1 orbitcr. The shape functions are obtained with the surface geometry as the input data, and the regime coefficients are determined by fitting with the measurement data. The aerodynamic coefficients such as the normal force, axial force, and the pitching moment of the ve-hide computed by the local method are in good agreement with the experimental data.

Key words: Space shuttles, Hypersonic flow, Aerodynamic coefficient, Finite element method, Nu- merical calculation