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A multi-gain sliding mode based controller for the pitch angle control of a civil aircraft is presented in this paper. The proposed controller is based on a novel concept of the sliding mode controllers in which multiple gains are being used to control the pitch angle of an aircraft and make it insensitive to parameter variations while reducing the chattering and guaranteeing the stability of the...
We consider an F-16 fighter aircraft subject to asymmetric actuator failures. To address non-symmetric faults, it is not possible to decouple the longitudinal and lateral dynamics. It is necessary to deal with a full six degree of freedom airframe. Firstly, we outline an automated procedure to assemble the symbolic and simulation models of complex aircraft. The symbolic model can be manipulated in...
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