推力矢量飞机过失速机动状态非定常气动力表征及鲁棒控制方法研究

Due to the nonlinear unsteady aerodynamics and the use of thrust vector control, the flight control system of aircraft for post-stall maneuvering is a nonlinear system including complex characteristics such as multi-input multi-output (MIMO), fast time variance, strong coupling and with heterogeneous actuators. To realize robust control of thrust vectored aircraft under post-stall maneuvering, this project will establish the dynamics of thrust vectored aircraft under post-stall maneuvering condition with high fidelity, through exploring of the representing method of the nonlinear unsteady aerodynamics and the mechanism of coupling between aircraft and thruster vector. After that, the dynamic control allocating method based on aircraft/thruste-vector coupled model database and the compound dynamic inversion control law based on angular acceleration feedback are proposed to realize robust control of thrust vectored aircraft in post-stall maneuvering. In this project, both of dynamical difference between thrust vector and aerodynamical actuator surface, and the error and bandwidth of sensors are considered sufficiently. The controller will be validated by hardware-in-the-loop simulation including three-axes swivel table and test platform of thrust vector. The proposed control method will also be tested on a scaled thrust-vectored aircraft.

飞机在过失速机动状态气动力非线性非定常特征显著，需要采用推力矢量增强其控制能力，因此是一个具有多变量、快时变、强耦合的异类多执行器非线性系统。为了实现推力矢量飞机过失速机动状态鲁棒控制，本项目探索过失速机动状态非线性非定常气动力模型表征方法，飞机/推力矢量耦合机理，建立过失速机动状态推力矢量飞机高置信度动力学模型。在此基础上，提出基于飞机/推力矢量耦合模型数据库的动态控制分配方法和基于角加速度信号反馈的复合动态逆控制方法，实现过失速机动状态推力矢量飞机鲁棒控制。本项目明确考虑推力矢量执行器与气动舵面的动态差异，以及机载传感器误差及频带特性，采用包含三轴转台及推力矢量测力平台的半物理仿真实验系统验证控制方法，在缩比推力矢量飞机上验证所研究控制理论。

摘要：飞机在过失速机动状态气动力非线性非定常特征显著，需要采用推力矢量增强其控制能力，因此是一个具有多变量、快时变、强耦合的异类多执行器非线性系统。为了实现推力矢量飞机过失速机动状态鲁棒控制，本项目开展了动力学建模和飞行控制方法研究，取得的主要成果包括：.（1）针对战斗机突破常规迎角进行过失速机动时，飞机绕流的分离使气动力呈现非线性非定常特征，过失速机动运动本身具有非常复杂的特性，包括运动学耦合和惯性耦合等问题，可能导致偏离、翼摇、失速尾旋等复杂的非指令运动。本项目提出了非定常气动力表征方法和基于气动参数辨识方法，过失速机动状态非线性非定常气动力模型表征方法，建立了过失速机动状态推力矢量飞机高置信度动力学模型。.（2）针对飞机进行大迎角过失速机动时，系统呈现严重的非线性，导致模型的精确度不高的问题，提出角加速度反馈的复合动态逆控制方法。采用传感器信息结合模型信息互补滤波的方式，获得高品质角加速度信号，基于角加速度反馈消除系统中模型不确定性和外部扰动等问题的影响，该方法既可保证系统动态响应性能，又可提高系统稳态性能和鲁棒性。.本课题采用包含三轴转台及推力矢量测力平台的半物理仿真实验系统验证了控制方法，在缩比推力矢量飞机上验证了所研究控制理论。