Nonlinear Receding Horizon Control of an F-16 Aircraft

In this paper the application of receding horizon control (RHC) with the linear, parameter varying (LPV) design methodology to a high delity, nonlinear F-16 aircraft model is demonstrated. The highlights of the paper are i)Use of RHC to improve upon the performance of a LPV regulator. ii)Discussion on details of implementation such as control space formulation, tuning of RHC parameters, computation time and numerical properties of the algorithms. iii)Simulated response of nonlinear RHC and LPV regulator Nomenclature npos = North position (ft) T = Thrust (lb) epos = East position (ft) e = Elevator (deg) h = Altitude (ft) a = Aileron (deg) = Bank angle (deg) r = Rudder (deg) = Pitch angle (deg) = Yaw angle (deg) V t = Velocity(ft/s) = Angle of attack (deg) = Side slip angle (deg) p = Roll rate (deg/s) q = Pitch rate (deg/s) r = Yaw rate (deg/s) 1