A methodology is presented for the design of flight control systems that exhibit stability and performance-robustness in the presence of actuator failures. The design is based upon two elements. The first element consists of a control law that will ensure at least stability in the presence of a class of actuator failures. This law is created by inner-loop, reduced-order, linear dynamic inversion, and outer-loop compensation based upon Quantitative Feedback Theory. The second element consists of adaptive compensators obtained from simple and approximate time-domain identification of the dynamics of the 'effective vehicle' with failed actuator(s). An example involving the lateral-directional control of a fighter aircraft is employed both to introduce the proposed methodology and to demonstrate its effectiveness and limitations.
Development of a Design Methodology for Reconfigurable Flight Control Systems
Aerospace Sciences ; 2000 ; Reno, NV, United States
2000-01-01
Preprint
No indication
English
DEVELOPMENT OF A DESIGN METHODOLOGY FOR RECONFIGURABLE FLIGHT CONTROL SYSTEMS
British Library Conference Proceedings | 2000
|Reconfigurable flight control systems design
British Library Online Contents | 1998
|Reconfigurable flight control systems
Tema Archive | 1991
|Online Contents | 2005
|