Integrated flight/propulsion control system design based on a decentralized, hierarchical approachA sample integrated flight/propulsion control system design is presented for the piloted longitiudinal 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.
Document ID
19890065930
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mattern, Duane (NASA Lewis Research Center Cleveland, OH, United States)
Garg, Sanjay (NASA Lewis Research Center; Sverdrup Technology, Inc. Cleveland, OH, United States)
Bullard, Randy (NASA Lewis Research Center Cleveland, OH, United States)