摘要
世界各国在空天飞机的研制过程中遇到了很多技术难题,特别是再入过程中的复杂大气环境,更是对空天飞机的研制提出了诸多要求。双椭球由于其优良的气动特性成为空天飞机头部的典型外型。美国的X-38空天飞机便是其中的代表,可将其中一个基础三维椭球视为机身,另一个相贯半球则可视为装在机身上的座舱。围绕围绕再入过程中复杂的气动特性,本文研究了以下内容：
对双椭球外形缩比建模,运用三维N-S控制方程,数值模拟超声速(Ma∞=4-5)湍流模型中双椭球绕流。数值计算得到激波结构,模型表面压力分布,对称面上压力、温度、马赫、密度分布,并与实验纹影照片对比,符合较好。描述了空间的流动特性,分析了攻角对空间激波结构、升力系数和阻力系数的的影响。
During the research process of the space plane countries all over the world encounter a lot of technology problems. Especially complex of atmospheric environment of reentry process request the research of the space plane more difficulties. For its excellent aerodynamic characteristics double ellipsoid is the typical representative of space plane'head. The space plane of USA X-38 is a good representative. One three-dimensional ellipsoid can be seen as the fuselage, and the other hemisphere can be regarded as a plane cockpit installed in the fuselage.With regard to this problem, the main research items in this dissertation are as follow:
First the model of double ellipsoid is built. By using three-dimensional N-S equations, calculate dual-flow around double ellipsoid in the supersonic (Ma∞=4-5) turbulence model. The computational results show shock wave structure, surface pressure distribution of model, pressure, temperature, Mach and density distribution of symmetrical surface, and coincidence with the experimental schlieren photos well. Describes the flow characteristics of space, analyse attack angle's influence on the space structure of shock wave, the lift coefficient and drag coefficient.
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