非线性飞机对象操纵面故障的控制律重构

Control Law Reconfiguration under Control Surface Failure for Nonlinear Aircraft Dynamic

研究以六自由度非线性方程描述的飞机在操纵面损伤或卡死故障情况下使用伪逆法进行控制律重构的方法 .通过对气动系数中的操纵导数进行合理的近似处理 ,将控制律重构问题转化为解一个线性方程组的问题 .给出了全数字实时仿真结果 ,验证了该重构算法的可行性 .

The application of pseudo-inverse method based flight control reconfiguration in the 6 degrees of freedom aircraft model was introduced. The failure considered here is the control surface effectiveness loss or lock-in-place. Via the appropriate linearization of the control coefficients, the reconfiguration problem was simplified to a problem of solving a linear equations. The real-time digital simulation results were given to indicate the validity of the algorithm.