Signal Reconfiguration Method for Aircraft's Pitch Angular Rate

The signal reconfiguration of pitch angular rate in the 6 degrees of freedom aircraft model is introduced. Two methods are presented.In the first method, by building an equivalent linear model of the aircraft, the linear state observer could be designed to estimate the states. In the second method, the nonlinear tracking differentiator is applied to producing the differential signal of the pitch angle, which is used to calculate the pitch angular rate. Simulation results were presented to indicate the feasibility of two algorithms.