Design of longitudinal autolanding guidance and control system in dynamic model inversion

This paper deals with a design of a nonlinear longitudinal autolanding guidance and control system using dynamic model inversion, which is applied to the problem of autolanding in ILS. It is assumed that the aircraft starts its approach at 1000 ft, -2.5 deg of flight path angle, and 250 ft/sec of velocity. In this design, altitude and velocity are selected as commands, and power level and pitch rate are designed as pseudo-control inputs for the approach. The final design is evaluated in nonlinear simulation for autolanding performance of the aircraft.