GENERALIZED DYNAMIC INVERSION CONTROL OF F-16 FIGHTER-JET LATERAL MANEUVERING

摘要

The generalized dynamic inversion control designrnparadigm is applied to lateral control of an F-16 jet fighterrnmodel. The purpose of the control system is to perform arndirectional maneuver while holding speed of the vehiclernconstant. The model of the vehicle is decomposed intorntwo parts by partitioning the state vector into outer andrninner parts. A quadratic scalar function in the attitude andrnspeed states is defined, resembling the deviation of thernouter state vector from its desired value. A second orderrnlinear stable dynamics in the outer state deviation functionrnis specified and evaluated along solution trajectories ofrnthe vehicle’s equations of motion, resulting in a linearrnalgebraic relation in the control vector. The control designrnis made by generalized inversion of the relation using thernGreville formula, and the resulting control law consists ofrnparticular and auxiliary parts. The particular part works torndrive the outer states to their desired values by nullifyingrnthe outer state deviation function. The auxiliary part of therncontrol law acts on the nullspace of the controls coefficientrnin the algebraic relation, and it provides the vehicle’srninternal stability with the aid of the null-control vector.