A partitioned integrated flight and propulsion control system with engine safety limiting

Results are presented on the implementation aspects of the design of an int egrated flight and propulsion control (IFPC) system for an experimental sho rt take-off and vertical landing aircraft configuration. A centralised IFPC system, designed using the method of H-proportional to loop-shaping, is pa rtitioned into separate airframe and engine sub-controllers which are conne cted by a specified coupling structure. Performance and robustness properti es of partitioned IFPC systems designed according to two alternative partit ioning schemes are validated via non-linear PC-based and pilot-in-the-loop simulations. A scheme to guarantee maximum limits on safety-critical engine variables is designed in order to preserve the structural integrity of the engine during extreme manoeuvres. The scheme is implemented on the partiti oned IFPC system and validated in non-linear simulations. Crown Copyright ( C) 2000 Published by Elsevier Science Ltd. Ail rights reserved.