摘要
空间运载工具设计阶段为分析比较不同外形高超音速各流动领域的性能,广泛应用局部方法。在其原始形式下,形状函数计算繁复,并限于简单几何外形组成的轴对称体。用边界元局部方法进行形状函数计算,可免去原局部方法面积分的繁复和藉助表格的局限。对STS-1轨道飞行器外形进行计算得到丁形状函数,并根据实验数据确定领域系数。由此计算出飞行器的法向力、轴向力和俯仰力矩系数,计算结果与实验数据相符。
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.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1992年第2期B014-B019,共6页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金
关键词
航天飞机
高超音速流动
气动力系数
Space shuttles, Hypersonic flow, Aerodynamic coefficient, Finite element method, Nu- merical calculation
