A sample integrated flight/propulsion control system design is presented for the piloted longitudinal landing task with a modern, statistically unstable fighter aircraft. The design procedure is summarized. The vehicle model used in the sample study is described, and the procedure for partitioning the integrated system is presented along with a description of the subsystems. The high-level airframe performance specifications and control design are presented and the control performance is evaluated. The generation of the low-level (engine) subsystem specifications from the airframe requirements are discussed, and the engine performance specifications are presented along with the subsystem control design. A compensator to accommodate the influence of airframe outputs on the engine subsystem is also considered. Finally, the entire closed loop system performance and stability characteristics are examined.
Integrated flight/propulsion control system design based on a decentralized, hierarchical approach
Guidance, Navigation and Control Conference ; 1989 ; Boston, MA, United States
1989-01-01
Conference paper
No indication
English
Decentralized Design for Integrated Flight/Propulsion Control of Aircraft
British Library Conference Proceedings | 1998
|