高超声速飞行器/发动机的鲁棒协调控制方法研究

Hypersonic vehicle has the operating characteristics of large envelope and wide working conditions, which make the vehicle / engine can touch and even cross the safe working boundaries, resulting in the flight safety issues. These problems are usually caused by the airframe / engine coupling, and security is of primary importance as designing the flight / engine control systems. In the hypersonic vehicle control studies, the coordinated control technology with taking into account flight performance and flight safety is a key issue to be resolved. In addition, there are some uncertainties in the aircraft aerodynamic, propulsion, structure, elastic properties, and atmospheric disturbances, the existence of these serious uncertainties also requires the control system has strong robustness. However, for the security problem causing by the coupling characteristics of hypersonic vehicles, the existing flight control techniques give little regard to the secure borders of vehicle or engine. Their controller designs are difficult to achieve, or implement with a too complex structure and difficult to coordinately debug. Therefore, for these two design requirements, the project focuses on the key issue of hypersonic vehicle robust coordinated control. The simplification of integrated coupled model, the secure border properties and characterizations, and the integrated robust coordinated control are systematically studied, the specific design methods are then given.

高超声速飞行器具有大包线、宽工况的工作特征，其在运行中可能出现飞行器/发动机触碰甚至越过安全工作边界的情况，产生飞行安全问题。而这些问题通常是由机体/发动机耦合作用导致的，在飞行器/发动机控制系统设计时，安全性是第一重要的。同时考虑飞行性能和飞行安全的协调控制技术是高超声速飞行器控制研究一项待解决的关键问题。另外，飞行器的气动、推进、结构弹性特性以及大气扰动等存在很大的不确定性，这些严重不确定性的存在还要求控制系统具有强鲁棒性。然而，针对由于耦合特性带来的高超声速飞行器安全问题，现有的控制技术在飞行控制系统设计时很少考虑飞行器或发动机的安全边界，所设计的控制器很难实现或实现起来结构过于复杂，且很难在各设计部门间进行协调调试。故针对上述两个设计要求，本项目对高超声速飞行器鲁棒协调控制的关键问题，在一体化耦合模型简化、安全边界特性和表征、一体化鲁棒和协调控制展开具体研究，并给出具体的设计方法。

本项目以采用亚燃冲压发动机或双模态超燃冲压发动机作为推进系统的高超声速飞行器作为重点研究对象，以飞行器跨越较宽飞行马赫数范围的加速爬升飞行过程为主要研究背景，将研究要点致力于设计以飞行加速度为飞/推接口参数的一体化控制框架。为了深入高超声速飞/推一体化模型的相关工作，本项目构建并发展了两类皆包含因高反压引起进气道不起动问题的冲压发动机模型，并由此构建了高超声速飞/推一体化纵向动力学机理模型。基于一体化模型，展现了以多目标增广2-DOF无扰切换方法为理论基础而设计的包含加速度调节与进气道不起动保护切换控制策略的飞/推一体化控制系统在协调发动机不起动问题与飞行器加速性能时的相关分析与结果。基于研究可知，吸气式推进系统进气道不起动边界的存在不仅仅会限制推进系统的推力输出能力，同样会限制飞行器的加速能力。并最终通过仿真研究给出了本项目所设计的双目标切换控制策略与一体控制框架的有效性。