【作者】 吉康；

【导师】 夏健；

【作者基本信息】 南京航空航天大学 ， 流体力学， 2007， 硕士

【摘要】 本文借鉴了国外先进的乘波机设计思想,独立编制了一套完整的高超声速密切锥乘波机的机身/推进一体化设计程序,为高超声速空天飞机的一体化设计提供了快捷有效的预设计方法。随着马赫数的升高,波阻和摩阻增加,形成升阻比“屏障”,而乘波构形飞行器是克服这一屏障的有效途径。本文在Ma∞=5.0～10.0,激波角β=9°～13°的条件下,利用密切锥方法,构造了由基于楔形流和锥形流的综合流场,生成乘波机外形。这种方法设计的乘波机前体既具有“楔导”乘波体可以为进气道提供均匀流场的优点,又具有“锥导”乘波体的高升阻比、容积效率和气动性能较好的优点。前机身和推进系统一体化设计的目的是充分利用前体对高超音速来流进行预压缩,尽可能捕获空气流量以满足发动机需要,并要求在进气道进口截面流场均匀。进气坡面转折形成的激波打在超音速冲压喷气发动机整流罩的唇口上。坡面转折的形状由乘波前体形状和发动机形状共同决定。激波前体“楔导”部分的流场通过三道进气坡面转折激波后,流入超音速冲压喷气发动机。然后经过隔离段和燃烧室,由喷口流出。飞行器的后体通过几何构造的方法完成。经过N-S方程数值计算验证,采用上述方法一体化设计的飞行器的流场符合设计要求,并取得良好的升阻比特性。更多还原

【Abstract】 An airframe/propulsion integrative hypersonic waverider design method based on osculating cones is developed in this dissertation. The design method is proved to be convenient and effective for integrative design of hypersonic vehicle.Both the wave drag and the friction drag increase as the Mach number becomes higher for hypersonic flow ; moreover , a technique difficult will appear which is called L/D barrier. The waverider aerodynamic configuration may be a way to overcome this barrier. A osculating cones hypersonic waverider is generated based on the wedge-derived and cone-derived flow field at the conditions of Ma∞=5.0～10.0 , and shock angle differed from 9°to 13°. The osculating cones method can be seen as a generic waverider design method which has the advantage both of wedge-derived waverider and cone-derived waverider, such as symmetrical flow, large L/D, good volumetric efficiency and other aerodynamics performance.The purpose of airframe/propulsion integrative design is to compress the hypersonic flow with vehicle forebody, to capture enough air flow to satisfy the combustor, and to provide symmetrical flow to the inlet. The shockwaves from the inlet ramps is cancelled at the cowl lip of the scramjet engine. The shape of the inlet ramps is determined by both the shape of vehicle forebody and scramjet engine. The air coming from the wedge-derived forebody flows though three inlet ramp shockwaves to the scramjet engine, and then flow out though divergence section and combustor. The aftbody is defined purely geometrically.The configuration has been numerically verified by solving the N-S equations. It shows that the aim of integrative design is attained and high lift-to-drag ratio is achieved.更多还原