基于等离子体合成射流激励的高超声速飞行器控制机理及控制方法研究

Long endurance and high maneuver are surly the tendency in the future of the hypersonic vehicle technology development. But the present flight control system based on the aerodynamic rudders cannot solve the problem in the application of an extending envelope flight mission for the lack of the control ability. The plasma synthetic jet actuator is a novel active flow field control method that can provide extra operating forces and moments by changing the flow field characteristics around the vehicle. But the plasma synthetic jet actuator has not been applied in the hypersonic vehicles flight control while only been implemented in some low speed and subsonic aerial vehicles. The object of this project is to investigate the wide envelope flight control based on the plasma synthetic jet actuator by building the plasma synthetic jet actuator modeling, hypersonic flow field mechanism analyzing, performance optimization and control law deriving. The effort mainly focused on the following two points: 1) Influencing mechanism of the plasma synthetic jet actuator on the hypersonic vehicle aerodynamic characteristics; 2) Wide envelope robust flight control law design for the plasma synthetic jet actuated hypersonic vehicle. It is the goal to achieve a promotion for the hypersonic vehicle flying ability, and to advance the domestic development of the hypersonic control theory and control technology, which is of significant theoretical meaning and great practical value.

长航时、大机动飞行是高超声速飞行器未来的发展趋势，但目前仅依靠舵面的飞控系统无法解决大包络飞行所引起的控制能力不足问题。而等离子体合成射流激励作为一种新型的主动流场控制方式，通过改变飞行器的流场特性，能够提供额外的控制力和力矩，已应用于低速/亚音速飞行器飞行控制，但在高超声速飞行器飞行控制方面的研究尚未开展。本项目从高超声速飞行器控制系统设计的角度出发，通过激励器建模、高超声速流场作用机制分析、飞行器控制特性优化和飞行控制律设计，解决高超声速飞行器大包络机动飞行控制问题。重点研究等离子合成射流激励对高超声速飞行器气动特性的影响机制和基于等离子合成射流激励的高超声速飞行器大包络强鲁棒控制器设计，实现高超声速飞行器飞行能力的提升，从而推动我国高超声速飞行器控制理论的发展和控制技术的进步，具有重要的理论意义与应用价值。

本项目以等离子流动控制作为气动控制的途径，以高超声速巡航飞行器实现长航时稳定控制和大机动飞行控制为目标，重点研究了等离子气动激励对高超声速飞行器气动特性的作用规律和基于等离子激励的高超声速飞行器大包络强鲁棒的自主飞行控制方法。.在等离子射流激励特性方面，建立了等离子射流激励的物理模型，通过数值分析与实验研究探索了等离子体合成射流激励特性随激励参数的变化规律，揭示主导射流强度、重复频率的物理机制。.在等离子射流激励对飞行器流场的作用机理方面，通过对两类等离子射流的风洞实验，验证了等离子射流能够有效减小飞行器的头部与翼面前缘的激波阻力，同时纳秒级等离子射流激励能够增加飞行器12%的升力系数，同时将失速攻角由20°增加至27°，明确了等离子体合成射流激励产生高超声速飞行控制力及力矩的机理和规律。.在基于等离子射流激励/舵系统的复合飞行控制系统设计方法方面，建立了飞行器的多模控制模型，将等离子射流激励等效为附加的控制力与力矩，基于复合灵敏度进行了飞行器的控制系统设计与优化，保证了系统的稳定性和鲁棒性。