基于控制分配的推力矢量短距起飞垂直降落飞机减速过渡控制

Deceleration transition controller design of thrust-vectored short takeoff and vertical landing aircraft based on control allocation

针对推力矢量型短距起飞垂直降落飞机由平飞到悬停的减速过渡过程中面临非线性、控制量冗余且耦合等问题,本文建立了含执行器约束的推力矢量短距起飞垂直降落飞机六自由度非线性数学模型,提出一种基于智能控制分配的减速过渡过程控制方法:以非线性增量动态逆方法设计控制律,获得虚拟控制指令。考虑执行器执行能力和过渡过程期望指标设计优化函数,使用改进的粒子群算法在线解算实际控制量。仿真实验验证了该方法在过渡过程中具有指令跟踪精度高,对气动参数摄动与外界风干扰鲁棒性强等优点。

The thrust vectoring short takeoff and vertical landing(STOVL)aircraft is faced with nonlinearity,control redundancy,and control coupling during the deceleration transition from flat flight to hover.In this paper,a six degrees of freedom(6DOF)nonlinear mathematical model of the thrust vector STOVL aircraft with actuator constraints is established to solve the above problems.A deceleration transition process control method based on intelligent control distribution is proposed,which uses nonlinear incremental dynamic inversion as the control law to obtain the virtual control input.Taking the execution capability of the actuator and the transition process expectation index design optimization function into account,the improved particle swarm algorithm is used to calculate the actual control amount online.Simulation experiments verify that the method has high command tracking accuracy during the transition process and strong robustness against aerodynamic parameter perturbation and external wind interference.