高超声速飞行器构型的数值模拟、试验研究与优化设计

Numerical Simulation,Experiment and Optimization of Hypersonic Vehicle Configuration

综合升力体和乘波构型的气动性能优势,发展了一种高超声速飞行器前体气动构型的设计方法。运用该方法参考某高超声速飞行器气动布局方案,设计了一种高超声速飞行器气动布局。对该类高超声速气动布局进行了数值模拟、优化设计和试验研究;并研究了该类气动布局在高空飞行时,稀薄气体效应对气动性能的影响。数值模拟结果表明：构型前体预压缩面能够将高压气体封闭在构型下表面,实现了乘波构型的设计概念;优化设计结果表明,对于该构型宽展比应在0.4-0.6之间,通过优化升阻比至少有3%-5%的提高余地。对DSMC算法的碰撞模型和有效碰撞次数进行了改进,发展了临近空间飞行器气动性能模拟软件。研究结果表明,在临近空间区域,该类气动布局的升阻比特性略有下降,但仍旧保持了高升阻比的气动优势。

A new design method of the hypersonic forebody is present based on the waverider and tiftbody concept. By means of this method and taking as reference the configuration of a certain hypersonic vehicle, the configuration of a new hypersonic vehicle is designed. Numerical simulation, optimization,and experiment are conducted on this vehicle, and the impact of thin gas on hypersonic vehicle configuration aerodynamics is also studied. Simulation investigation shows that the pre-compressed surface of the forebody can confine the highpressure air into the bottom surface, so the waverider design objective is realized. The optimization results show that the ratio of width-to-span should be limited to 0. 4-0.6, and that the lift-to-drag ratio have the in crease space of 3 %-5 %. DSMC program is developed to investigate the aerodynamic pcrformance of hypersonic vehicles in near space. With the method, flows in transitional regions around the waverider are simulated in the near space region. Investigation shows that the lift-to-drag ratio is slightly decreased in near space but also in the region of high value.