基于类咽式进气道的高超声速飞行器一体化设计

Integrative Design of Airbreathing Hypersonic Vehicle Based on Sim-Jaws Inlet

针对吸气式高超声速飞行器高空巡航飞行时净推力和升力不足的难题,探索了一种基于类咽式进气道的高超声速飞行器一体化设计方法。该方法耦合了具有高升阻比特性的乘波机体和气流压缩性能优异的三维内收缩进气道,获得了一种气动性能较优的高超声速飞行器一体化构型。在设计过程中,对一种咽式进气道的几何外形和激波系结构进行了适当改变,得到了能与楔形乘波前体进行一体化设计的类咽式进气道构型,并采用遗传算法对进气道参数进行了优化;以所得到的进气道和乘波体为基础对飞行器整体构型进行了飞行器内外流一体化设计。无黏计算所得流场与理论设计吻合良好,有黏计算结果表明该飞行器在马赫数7时最大升阻比达到3.4,具有良好的气动性能。

A method for designing an airbreathing hypersonic vehicle based on a sim-jaws inlet was introduced for the purpose of improving the net thrust and lift force of hypersonic cruise vehicle. The high lift-to-drag ratio characteristic of waveriders and excellent intake capability of 3D inward-turning inlet were combined in the hypersonic integrative configuration. Based on the shock wave structures and geometric configuration of a Jaws inlet, a new inlet （ denoted ＂Sim- Jaws inlet＂ ） was redesigned which could be integrated with wedge waverider, and was optimized by genetic algorithm. According to the research on the Sim-Jaws inlet and waverider forebody, an entire vehicle configuration with integrated airframe and engine had been presented. Theoretical study and numerical simulation showed that this vehicle had good aerodynamic performance at Mach number 7.