Abstract
The concept of an equivalent lime constant and a model expansion method is introduced to design a synthetic stabilization acceleration autopilot. In the autopilot control loop, an extended Kalman filter is incorporated to estimate the time–varying airframe parameters. The relations between the characteristics of the autopilot and the estimation errors of the extended Kalman filter are investigated through computer simulations. It is Found that the model expansion method can specify the gains of the autopilot control loop efficiently. The results also show that, if the characteristics of the autopilot are specified properly, an acceptable estimation error for the extended Kalman fliter can be obtained.
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