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The feedback I inearization method is appl ied to odation of aircraft failures occuring at the control effectors or the airframe. The failures are identified as parameter changes in the six-degree-offreedom nonlinear equations of motion by the recursive least square algorithm. The control parameters are updated using the latest estimated system parameters. In order to allow one to use digital computer in implementation, a discrete time servo controller is designed for the surface actuators and the engine, where the reference inputs are given by the continuous time control law. The performance of the RFCS is demonstrated through computer simulation using the nonlinear model of an aircraft which has half o f the right wing broken off.
Yoshimasa Ochi (Fri,) studied this question.
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