Application of H2/H∞ and dynamic inversion techniques to aircraft landing control

The paper focuses on the aircraft automatic control in longitudinal plane, during landing, taking into account the sensor errors and disturbances. Aircraft auto-landing is achieved by combining the mixed H2/H∞ and the dynamic inversion control techniques and by using an optimal observer, the geometry of landing, and two reference models. The general control law will consist of a guidance component for the commanded landing trajectory (calculated by using the dynamic inversion approach) and an optimal component which will be designed by means of a mixed H2/H∞ technique for the cancel of the sensor errors and other disturbances in the system. The theoretical results are validated by numerical simulations for the landing of a Boeing 747; the simulation results are very good, Federal Aviation Administration accuracy requirements for best category being met.