组合式高超声速飞行器布局设计与优化分析

针对高超声速飞行器气动布局设计难点，文章提出了基于多个基准流场的多部件组合设计方法.以锥导乘波体为基准，采用分段接序、多片组合的高超声速可调参数的气动布局设计，将飞行器分解为前体、机翼和中心体设计.前体和机翼以乘波体为设计思路，中心体构型根据装载需求设计，从而达到飞行器在边缘能够满足压力封闭，有效容积集中在中心体附近的总体布局思路，使得飞行器各部件功能清晰化.最终实现具有"乘波特性"的高超声速巡航飞行器参数可调的布局设计.文中对比了组合布局与传统乘波体的差异，在前体不变的情况下，研究了中心体长度、长宽比和长厚比对飞行器气动性能的影响.采用自由变形技术（free-form deformation，FFD）实现了高超声速飞行器的参数化和优化设计流程.结果表明组合布局具有更高的容积效率，可实现多参数化调节，具有良好的乘波特性，可为未来提高高超声速飞行器升阻比和满足应用要求提供方案参考. 

Layout Design and Optimization Analysis of Combined Hypersonic Vehicle

Aerodynamic layout is critical for hypersonic aircraft. In this paper, a multi-component combined design method based on multiple reference flow fields was proposed. Based on the cone-derived waverider, the aerodynamic layout design of the hypersonic vehicle with adjustable parameters was achieved by segmented sequence and multi-piece combination method. The vehicle was decomposed into three components, including forebody, wing and centerbody. The forebody and the wing were designed with the cone-derived waverider. The centerbody configuration was designed according to the volume requirements, so that the aircraft can meet the pressure closure at the edge, and the effective volume was concentrated in the vicinity of the centerbody. Therefore, the function of different components became clear. Finally, the layout design of the hypersonic cruise vehicle with "waverider characteristics" was realized, meanwhile, the design parameters were adjustable. In this paper, the difference between the combined layout and the traditional waverider was compared. The influence on the aerodynamic performance of the length, length-to-width ratio and length-to-thickness ratio of the centerbody was studied. The free-form deformation(FFD) technology was used to realize the parameterization and optimization design process of the hypersonic vehicle. The results show that the combined layout has higher volumetric efficiency, adjustable parameters and good waverider characteristics. The new method can provide a reference for improving the lift-to-drag ratio of hypersonic vehicle and meeting the requirements of engineering applications in the future.