与进气道相容的飞行器乘波-楔形前体气动特性及重构研究

The integration of hypersonic vehicle forebody and inlet is very important to achieve hypersonic flying. Based on the waverider and liftbody concept, a coupling design method of the hypersonic waverider - wedge-shaped forebody that with flow patterns of waverider and configuration characteristics of liftbody is researched, the forebody and hypersonic inlet with rectangular section integration design is done also. The shock wave structure and coupling flow characteristics of hypersonic waverider - wedge-shaped forebody and inlet with rectangular section was analyzed with three-dimensional numerical analyzer. The geometry parameter which affects flow characteristics of forebody and inlet is investigated. The coupling design principle and method of hypersonic waverider - wedge-shaped forebody and inlet with rectangular section is presented. An integration of hypersonic forebody/inlet case is designed, the performance and flow characteristics of forebody/inlet at different inflow Mach number is presented with three-dimensional numerical analyzer. The preliminary test verification would conducted on the hypersonic waverider - wedge-shaped forebody with inlet in a hypersonic tunnel.

飞行器进气道/前体的一体化设计是实现高超声速飞行的关键。本项目拟将乘波体气动性能优势与升力体结构特征优势相结合，对一种兼顾乘波体气动特性和升力体结构特征、与进气道相容的高超声速飞行器乘波-楔形前体设计方法开展研究。通过数值模拟细致刻画其三维波系结构及流动特征，凝炼影响气动性能的几何描述参数，分析和揭示其耦合流动机理。并据此开展此类前体/进气道流场的气动重构原则与方法研究。最终获得综合考虑前体升阻力特性、有效容积及进气道内流性能的乘波-楔形前体/进气道一体化气动布局方案。在此基础上，针对设计和非设计工况，对此一体化布局方案开展三维数值模拟分析与风洞试验研究，验证并掌握此类一体化构型的总体性能、流动特征与工作特性，为我国近空间飞行器相关技术的研究提供技术储备。

飞行器进气道/前体的一体化设计是实现高超声速飞行的关键。本项目将乘波体气动性能优势与升力体结构特征优势相结合，对一种兼顾乘波体气动特性和升力体结构特征、与进气道相容的高超声速飞行器乘波-楔形前体设计方法开展了研究。对影响乘波体“乘波”的因素进行了研究，给出了前缘激波的不脱体的限制条件及具体的判定方法。分析了乘波体几何特征参数对前缘激波不脱体的影响，给出了前体激波不脱体限制条件，并进行了数值模拟验证。结果表明：通过该方法设计的乘波前体的流动特征与预期的结果相吻合，说明给出的激波不脱体限制条件及影响规律可信，设计方法可行。研究了乘波前体/矩形截面高超声速进气道的匹配设计技术，提出了一种乘波前体/矩形截面高超声速进气道匹配设计方法，数值仿真结果表明：该匹配设计方法可以有效地对前体激波进行控制，保证前体激波与进气道唇口匹配，可据此开展此类前体/进气道流场的气动重构研究。给出了基于圆锥截线、流线追踪和乘波-楔形组合的三种前体/进气道设计方法及流程，分析了典型几何参数对气动性能的影响变化规律。将前体/进气道风洞试验与数值仿真结果进行了对比，实验获得的数据点与仿真获得的曲线吻合较好，说明采用的数值模拟方法可以较为准确地模拟高超声速前体/进气道内的流动，所得相关规律及结果可信。本项目研究可为我国近空间飞行器相关技术的研究提供技术储备。