姿态气动耦合的高超声速飞行器分块建模及鲁棒控制

Focus on the inherent characteristics of attitude and aerodynamic coupling, nonlinear, and fast time-variation of the hypersonic aircraft, based on the aerodynamic characteristics and kinematics, facing to a class of hypersonic aircraft with symmetry, highly lift to drag ratio, and strong disturbance, we find a kind of hybrid modularized modeling method. As the foundation for controller design, the stability and coupling mechanism of the system is analyzed firstly. And the controller design scheme for blocks is studied based on the model we built, by the modular controller design idea. Then, considering the feature of attitude and aerodynamic coupling of the hypersonic aircraft, the pseudo-decoupling and compensation method is used to reduce the coupling and the Active Disturbance Rejection Control (ADRC) method is provided to achieve the disturbance suppression, and finally to achieve the robust attitude control of the aircraft. Thirdly, aim to the performance index of each model block, a reference model based robust attitude control method is studied. By the advantage of the modularization, we can reduce the complexity of controller design inside each block, while guarantee the control performance of each block and the aircraft as well. Finally, we build the digital simulation platform on the real-time simulator and PC, respectively, and demonstrate the robust control algorithm on each platform to test the validity of above theoretical research.

针对高超声速飞行器飞行姿态和气动力存在的多通道耦合、非线性、快时变等问题，在对飞行器气动特性和运动学原理的基础上，对一类面对称、高升阻比、强扰动的高超声速飞行器，寻找一种面向控制的混合分块建模方法；作为控制器设计的基础，首先对系统进行稳定性和耦合机理分析,并在所建立模型的基础上，根据模块化控制系统设计的思路，研究分块控制器设计方案；其次针对高超声速飞行器的姿态和气动力强耦合的特点，通过伪解耦和补偿降低耦合，再利用自抗扰控制方法实现对干扰的抑制，进而实现飞行器鲁棒姿态控制；而后针对各模块需要满足的性能指标，研究基于参考模型的鲁棒姿态控制方法，利用模块化的优势，降低模块内控制器设计复杂程度，同时保证各模块的控制性能指标，进而保证飞行器控制性能指标；最后分别在飞行器实时仿真机和数字计算机上建立数字仿真平台，并分别对所研究的飞行器鲁棒控制算法进行仿真验证，以检验理论研究的正确性。

本项目围绕近空间高超声速飞行器未来发展目标，针对具有复杂外形的跨大气层飞行的高超声速飞行器姿态/气动力存在的多通道耦合以及非线性、快时变、不确定等问题，在分析高超声速飞行流动机理的基础上，进行稳定性、耦合机理分析，获得考虑气动耦合、惯性耦合及运动耦合的飞行器的安全飞行边界判据；根据耦合分析的结果，采用前馈、状态反馈以及前馈与状态反馈结合的方法对系统进行耦合补偿降耦；针对高超声速飞行器的特性，基于灰色系统理论，提出灰色自抗扰控制方法，应用于高超声速飞行器的控制系统设计，并建立数字仿真系统进行实验，验证理论研究的正确性。本项目的研究成果将丰富高超声速飞行器的特性分析和控制方法，支撑我国近空间飞行器技术的可持续发展。