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结合高超声速远程滑翔飞行器在升阻比、容积率和容积等方面的性能需求,对锥导乘波构型底部基线方程的确定方法、构型顶点至基本流场顶点的距离等问题进行研究;采用面元法计算分析了各外形控制变量对飞行器性能的影响规律;总结得出高超声速远程滑翔飞行器各外形设计变量确定的先后顺序及准则。
Combining the performance requirements of the hypersonic long-range gliding aircraft in terms of lift-drag ratio, volumetric capacity and volume, etc., the method of determining the baseline equation of the bottom of the cone-guided multiplicative wave configuration and the distance from the apex of the configuration to the apex of the basic flow field are studied. The influence law of each control variables on the performance of the aircraft is analyzed and calculated by using the surface element method. The order and criteria for determining the design variables of the hypersonic long-range gliding aircraft are summarized.