面向全飞行包线的高超声速飞行器复杂动态建模及主动鲁棒控制

For ensuring stable and safe flight of air-breathing hypersonic vehicles (AHVs) large- maneuvering in full flight envelope, bad flight conditions and complex dynamic characteristics, all of these make the modeling and control design became one of the most important challenging problems. Since the physical constraints and time-delay dynamics are very important challenge issues which degenerate the robustness, safety, rapidity and accuracy of control system severely in full-envelope flight of AHVs, this project is focused on constraints and time-delay dynamics modeling and active robust control strategy. Therefore, the key contents needed broken through in the advanced project are shown as follows. . Firstly, the influence of the physical constraints and time-delay dynamics in full flight envelope are analyzed, and the modeling methods for those dynamics are proposed. And furthermore, model accuracy evaluation technologies are proposed based on iteration algorithm and set theory. Secondly, since complex constraints and the time-delay dynamics in different flight stages have different influences on the control performance of the vehicles, so the constraints and time-delay dynamics are analyzed and classifying strategies are presented based on varying parameter of the linear varying parameter modeling. Thirdly, in order to reduce the time-delay dynamics influence while satisfying the complex constraints, the active control method and model predictive control theories are studied, and then the active time-delay control strategies are also designed. On this basis, active robust model predictive control algorithms are proposed for full envelope flight of air-breathing hypersonic vehicles. Lastly, semi-physical simulation is carried out to validate the developed models and the proposed control design methods. The key theories and the novel technologies mentioned above will be broken through to provide new theoretical and technical support for the application of AHVs.

高超声速飞行器在全飞行包线内大跨度机动飞行时，恶劣的飞行环境和复杂的动态特性等使其建模与控制器设计面临重大挑战。针对约束与时滞等复杂动态对控制系统鲁棒性、安全性、快速性和精确性的严重影响问题，本项目拟开展约束与时滞动态建模及其主动鲁棒控制方法研究，重点解决以下关键技术：1）分析全飞行包线内的约束特性和时滞动态，基于迭代思想和集合理论，提出约束与时滞动态建模方法及模型精度评估算法。2）针对不同飞行阶段约束特性表现形式不同、时滞动态特性不同的问题，基于变参数区域划分，研究约束分类描述算法以及时滞动态分类方法。3）为满足复杂约束、降低时滞影响，基于主动控制思想和模型预测控制理论，设计主动时滞控制策略，提出面向全飞行包线的高超声速飞行器主动鲁棒预测控制算法。在此基础上，利用已有半实物仿真系统验证所提模型和方法的有效性。本项目预期的理论突破和技术创新，将为推动高超声速飞行器发展提供新理论和新方法。

临近空间高超声速飞行技术是军民用航空航天领域重要的战略发展方向之一，具有很强的前瞻性、战略性与带动性，正成为当今世界广泛关注的焦点。但是，临近空间高超声速飞行技术的难度要远远大于传统飞行技术。弹性机体、推进系统以及结构动态之间的耦合更强，模型非线性度更高，飞行高度和马赫数跨度更大，运行环境更加复杂，使得高超声速飞行器控制系统设计成为亟待解决的关键问题之一，也是飞行控制领域研究的热点问题。特别是，高超声速飞行器在全飞行包线内大跨度机动飞行时，恶劣的飞行环境和复杂的动态特性等使其建模与控制器设计面临重大挑战。.针对约束与时滞等复杂动态对控制系统鲁棒性、安全性、快速性和精确性的严重影响问题，本项目开展了约束与时滞动态建模及其主动鲁棒控制方法研究，重点解决了以下关键问题：1）分析了高超声速飞行器全飞行包线内的约束特性和时滞动态，并基于迭代思想和集合理论，提出了约束与时滞动态建模方法及模型精度评估算法，获得了全飞行包线的高超声速飞行器动力模型，以及约束与时滞动态模型。2）针对不同飞行阶段约束特性表现形式不同、时滞动态特性不同的问题，基于变参数区域划分，研究了约束分类描述算法以及时滞动态分类方法，揭示了高超声速飞行器控制系统时滞特性，从而为降低时滞特性对控制系统的影响提供了理论基础。3）为满足复杂约束、降低时滞影响，提出了非线性约束处理方法、设计了主动时滞控制策略，并研究了复杂约束下不确定非线性系统的鲁棒预测控制方法，进而提出了面向全飞行包线的高超声速飞行器主动鲁棒预测控制算法，为飞行器在全飞行包线内实施大跨度机动飞行时的精细化控制提供了新的控制方案，为推动高超声速飞行器发展提供新理论和新方法。