基于主动流动控制涡波效应的宽速域虚拟气动外形构建原理与控制特性研究

随着航空航天技术的发展和国防力量建设的需要，大空域、宽速域、大机动域飞行器将成为未来高超声速飞行器研究的一个重要方向。为增强宽速域飞行器的气动性能和飞行品质，本项目基于具有自主知识产权的合成双射流技术和等离子体高能合成射流技术，提出一种基于主动流动控制涡波效应的宽速域虚拟气动外形控制方法。该方法结合了合成双射流丰富的旋涡结构和等离子体强烈的激波特性，低速域通过旋涡效应、超/高超声速域利用旋涡激波耦合效应构建可控的虚拟气动外形。采用理论分析、数值模拟和实验研究相结合，研究合成双射流旋涡和等离子合成射流旋涡激波的演化规律，揭示基于低速域旋涡效应和超/高超声速域涡波耦合效应的虚拟气动外形构建原理，建立虚拟气动外形评价准则，研究不同速域涡波效应对虚拟气动外形的参数影响规律，分析宽速域虚拟气动外形的控制特性，实现气动性能稳定、有效控制，为宽速域飞行器提供一种“可变、可控”的新型气动外形控制技术。

With the development of aerospace technology and the requirement of national defense force construction, aircrafts with large airspace, wide-speed range, and large maneuvering domain will become an important direction for future hypersonic vehicles. In order to enhance the aerodynamic performance and flight quality of wide-speed aircrafts, a wide-speed virtual aerodynamic shaping control method of vortex and shock effects is proposed using the owned dual-synthetic-jets technology and high-performance plasma synthetic jet technology. The method combines the abundant vortex structures of dual synthetic jets and the strong shock characteristic of plasma synthetic jet. The virtual aerodynamic shaping is controlled by vortex effect in the low-speed range and the coupling vortex-shock effect in the supersonic / hypersonic range. The evolution law of vortex and shock is studied, and the construction principle of virtual aerodynamic shaping resulted from the vortex and shock effects is revealed through theoretical analysis, numerical simulation and experimental investigation. The influence law of controllable parameters on the virtual aerodynamic shaping is studied by establishing evaluation criterions in different speed ranges, and then the control characteristics of wide-speed virtual aerodynamic shaping are analyzed. The stable and effective control of aerodynamic performance is realized to provide a newly variable and controllable control technology for the aerodynamic shaping of wide-speed aircrafts.