Abstract:

Based on 2-state nonlinear aircraft dynaminc model, a nonlinear decoupling control law which contains command static error integral loop is designed by combining nonlinear inverse dynamics theory and modern optimal control theory . This control law could minimize the performance index which contains the weighted state variables, control variables and their varying rates. Using this control law, the aircraft could capture the desired flight state more accurately and decouples the control more completely with smooth control responses and less control energy. As the control law more accurate represents the nonlinear factors that arise in aircraft dynamic model and remedies the degrading of aircraft nonlinear dynamical behavior during maneuvering flight , it offers the potential for providing high levels of handling quality and flight performance in the entire flight envelope of the aircraft.

Key words: nonlinear systems, maneuvering flight, flight control, decoupling, inverse systems