面向机动飞行的变进气道高超声速飞行器协调控制策略

With the development of hypersonic technology, the requirements for the wider velocity range and maneuvering flight have been increasingly emerging, which have become one of the urgent problems to be solved for hypersonic vehicle (HSV). Studies at home and abroad show that the control methods for HSV based on fixed geometry inlet cannot deal with the requirement of maneuvering flight. That results in the narrow control range of flight velocity and angle of attack and restricts the ability of the aircraft to maneuvering flight. Therefore, based on the coordinated control of hypersonic vehicle for maneuverable flight, a novel flight control and coordinated optimization strategy for hypersonic vehicle with variable inlet is proposed in this project that achieves maneuvering flight with wider Maher range for HSV. Through the analysis of the characteristics of hypersonic vehicle with variable inlet, a control-oriented model is established in this project. Considering the coupling effect of variable inlet control and flight control, the coordinated control strategy is studied to improve the maneuverability under steady condition. For the emergencies (such as missile interception and other unexpected situations), the collaborative strategy of trajectory and control is discussed, which can improve the maneuverability and achieve fast and high precision tracking of the trajectory simultaneously. The research breakthroughs the limitation that the flight control under the structure of fixed geometry inlet cannot meet the requirements of maneuvering flight, which also provides a new way to solve the wide velocity range and flexible flight control for HSV.

随着高超声速技术的发展，宽速域和机动飞行需求日益凸显，成为高超声速飞行器亟待解决的问题之一。国内外研究表明，基于定进气道的控制技术无法有效满足飞行机动性的要求，飞行器速度和攻角的控制范围较窄，限制了飞行器灵活机动地飞行能力。为此，本申请课题以提高机动性为目的，提出研究高超声速飞行器变进气道控制与飞行控制协调优化策略来实现宽马赫数范围内机动飞行。课题通过对变进气道飞行器特性分析，建立了面向控制模型；综合考虑变进气道控制与飞行控制耦合影响，研究协调控制策略，实现稳定条件下机动性的提高；针对突发事件（例如导弹拦截等突发情况）研究轨迹与控制协同策略，在提高机动性同时，实现对轨迹的快速高精度跟踪。课题研究突破了定进气道结构下飞行控制不能满足机动性飞行的局限，为解决高超声速飞行器宽速域、灵活机动的飞行控制提供新的途径。

课题针对高超声速飞行器机动飞行的需求，提出高超声速飞行器变进气道控制与飞行器控制协调优化策略，建立变进气道高超声速飞行器协调控制理论和优化方法。实现在可移动进气罩调节情况下，高超声速飞行器对高度、速度的跟踪，跟踪收敛时间在60秒以内；实现在超燃冲压发动机工作范围内，拓宽飞行器速域、速域范围扩宽10%；提高攻角的变化范围，为解决高超声速飞行器宽速域、灵活、机动的飞行提供新的途径。最后，建立了实时仿真平台，实现了在虚拟仿真环境下对设计算法有效性的验证。研究工作主要从以下四个方面展开：（1）变进气道高超声速飞行器面向控制建模，通过模型分析与简化获得变进气道高超声速飞行器面向控制模型；（2）变进气道高超声速飞行器协调控制策略，研究变进气道高超声速飞行器分级步进控制与多模型鲁棒控制协调策略方法，研究连续调节控制与非线性自适应控制协调策略，并使用李雅普诺夫方法进行稳定分析，实现更好的控制性能；（3）变进气道高超声速飞行器快速轨迹与控制协同策略，研究有限时间自适应观测器-控制器综合方法，实现对给定轨迹指令的高精度快速跟踪；（4）变进气道高超声速飞行器协调控制仿真系统构建及测试, 同时开发了实时仿真与视景仿真功能，实现了对算法的有效性验证。