A control law for decoupling roll rate, angle of attack and sideslip in rapid, nonlinear airplane maneuvers is derived. For simplicity, only moments caused by ailerons, rudder and elevator are considered, and control forces are neglected. Simulated responses of the closed loop system, including the control forces, show that the neglected forces have no significant effects and that large, simultaneous lateral and longitudinal maneuvers can be precisely performed. The violent divergences which occur in open-loop maneuvers of this type are eliminated by the decoupling. The control law showed little sensitivity to 20 percent perturbation in three important stability derivatives.
Nonlinear decoupled control synthesis for maneuvering aircraft
1978 Conference on Decision and Control ; 1979 ; San Diego, CA
1979-01-01
Miscellaneous
No indication
English
Nonlinear dynamic inversion control for super-maneuvering aircraft
British Library Online Contents | 1998
|Nonlinear Design Loads for Maneuvering Elastic Aircraft
AIAA | 2000
|European Patent Office | 2021
|