基于自适应Backstepping的飞机重心变化稳定控制律设计

Adaptive Backstepping Control for Gravity Change of Aircraft Center

飞机重心变化会影响飞机气动力从而产生较强的扰动误差,可以采用自适应Backstepping控制方法消除这种扰动误差对飞行控制的影响;首先建立飞机重心位置和重量变化的非线性模型,然后设计自适应Backstepping控制律,对模型误差进行自适应估计,针对f16飞机纵向操纵力矩不是仿射非线性的形式,采用牛顿迭代法进行求解,最后进行正常情况下、重心突变和重心渐变情况下的仿真验证,仿真结果表明设计的自适应Backstepping控制律具有很好的动态和稳态性能。

The Gravity Change of Aircraft Center has influence on the aerodynamic force of the aircraft and produce strong disturbance errors.An adaptive backstepping control method is used to eliminate the influence of the disturbance errors on flight control.Firstly,a non-linear model of aircraft gravity center position and weight change is established.Then an adaptive Backstepping control law is designed to estimate the model error adaptively.Aiming at the fact that the longitudinal control moment of F16 aircraft is not an affine non-linear form,the Newton's method is used to solve the problem.Finally,the simulation verification under normal conditions,sudden change of gravity center and gradual change of gravity center is carried out.The simulation results show that the adaptive backstepping control law designed has good dynamic and steady-state performance.