综合利用涡波效应的大容量宽速域飞行器气动布局设计

Vortex-wave Comprehensive Utilization for Large Volume Capacity and Wide-speed Aerodynamic Layout Optimization Design

高超声速飞行器在亚、跨、超及高超声速等速域内的气动效率与容量问题是制约高超声速飞行器实用化的重要瓶颈问题。大容量宽速域高性能气动布局设计技术在保证高超声速巡航阶段高气动性能的同时,迫切需要在具备足够容量的前提条件下实现高的亚、跨及超声速气动效率。通过综合利用低速涡升力与高速激波压缩升力,提出了一种涡波综合利用宽速域大容量气动布局设计方法。结合计算流体力学(CFD)方法与ARI_OPT优化设计平台,设计得到一种背负式大容量气动布局,计算结果表明,该布局在跨声速与高超声速下的最大升阻比分别可达到10.3与5.9,飞行器整体性能稳定且在宽速域条件下均具有良好的气动性能,弥补了传统乘波体气动布局在亚、跨声速下的性能缺陷,可为高超声速飞行器气动布局走向工程应用提供技术支持。

The problem of sub-sonic aerodynamic efficiency and capacity of hypersonic vehicles has become a bottleneck problem that restricts the technology of hypersonic vehicles from the conceptual and theoretical exploration stage to the advanced technology development and flight demonstration test stage with clear application background.The high-capacity and wide-speed domain high-performance aerodynamic layout design technology should ensure high aerodynamic performance during the hypersonic cruise stage,and urgently needs to achieve high transonic speed aerodynamic efficiency under the premise of sufficient capacity.Through the comprehensive use of low-speed vortex lift and high-speed shock compression lift,a vortex-wave comprehensive utilization of wide-speed domain and large-capacity aerodynamic layout design method was proposed.Combining the CFD method and the ARI_OPT optimization design platform,a knapsack large-capacity aerodynamic layout was designed.The evaluation results show that the maximum lift-to-drag ratio of the layout at transonic and hypersonic speeds is 10.3 and 5.9,respectively.The overall performance of the aircraft is stable and has good aerodynamic performance under wide-speed conditions,which makes up for the performance defects of the traditional wave rider aerodynamic layout at transonic speed,and can provide technical support for hypersonic aircraft to engineering applications.