Nonlinear reconfiguration for asymmetric failures in a six degree-of-freedom F-16

In this paper we consider an F-1 6 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. First, we outline an automated procedure to assemble symbolic and simulation models of complex aircraft. The symbolic model can be manipulated in various ways and used for both linear and nonlinear control system design. In the event of actuator failures, the failed surfaces not only cease to function as viable inputs but also impose persistent disturbances on the system. As previously shown, the problem of designing a reconfigured controller can be formulated as a nonlinear disturbance rejection problem. We apply this method to design a controller for the F-16.