基于局部偏转吻切方法的背部进气高超飞行器一体化设计研究  

Research on the integration design of hypersonic vehicles with dorsal inlets based on the local-turning osculating cones method

作　　者：郑晓刚 林德寿 方啸雷 尤延铖 朱呈祥 Zheng Xiaogang;Lin Deshou;Fang Xiaolei;You Yancheng;Zhu Chengxiang(School of Aerospace Engineering,Xiamen University,Xiamen 361005,China)

机构地区：[1]厦门大学航空航天学院,厦门361005

出　　处：《空天技术》2023年第5期1-10,共10页Aerospace Technology

基　　金：国家自然科学基金(U21B6003,U20A2069,12202372);博士后科学基金(2022M712653)。

摘　　要：背部进气式布局利用内/外流压缩方向的不同将进气道置于背部,避免了内/外流激波间的相互干涉,已成为未来高超声速一体化设计发展的重要方向之一。为进一步拓展此类气动布局的设计思路,提出了一种基于局部偏转吻切方法的背部进气内/外流一体化设计方法,实现了三维内转进气道与基于复杂三维弯曲激波乘波体的“无干涉”一体化设计。该方法通过Bezier曲面定义的三维激波面巧妙地将三维内转进气道布置于全三维乘波体背部。在此基础上,分别采用吻切流场乘波原理与局部偏转吻切方法设计进气道与乘波体的气动型面。研究结果表明,基于该方法设计的背部进气式一体化构型在设计状态下展现出了极佳的整体气动特性,整个下表面完全“骑乘”于外流复杂三维弯曲激波之上,背部进气道产生的内流准三维激波也基本封口。不考虑空气黏性的影响,该一体化构型的升阻比为4.947,进气道的增压比为14.988,总压恢复系数可达0.847,流量捕获系数为0.9996,基本实现全流量捕获。By mounting the hypersonic inlet on the upper side of the fuselage,the dorsal-inlet layout can effectively decouple the mutual interference between the internal and external shock waves.It has become one of the research hotspots in the aerospace industry.To further expand this design idea,an integration design method of hypersonic vehicles with dorsal inlets based on the local-turning osculating cones method is proposed,which realizes the"non-interference"integration design for the inward-turning inlet and the waverider based on the complex three-dimensional shock wave.This method skillfully arranges the inwardturning inlet on the dorsal of the waverider by utilizing a three-dimensional shock wave defined by the Bezier surface.On this basis,the osculating flowfield method and the local-turning osculating cones method are used to generate the aerodynamic surfaces of the inlet and waverider,respectively.Research results demonstrate that the proposed dorsal inlet integrated configuration exhibits excellent overall aerodynamic characteristics under the design condition.The entire lower surface completely"rides"above the assigned shock wave and the dorsal inlet is basically sealed by the incident shock wave.Regardless of the influence of air viscosity,the lift-to-drag ratio of this integrated configuration is 4.947,the pressure ratio is 14.988,the total pressure recovery coefficient is 0.847,and the mass flow capture coefficient is 0.9996,which means the dorsal inlet basically realizes the full flow capture.

关 键 词：高超声速飞行器 背部进气 局部偏转吻切方法 乘波 升阻特性 

分 类 号：V211.5[航空宇航科学与技术—航空宇航推进理论与工程]