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

Abstract Results are presented on the implementation aspects of the design of an integrated flight and propulsion control (IFPC) system for an experimental short take-off and vertical landing aircraft configuration. A centralised IFPC system, designed using the method of H ∞ loop-shaping, is partitioned into separate airframe and engine sub-controllers which are connected by a specified coupling structure. Performance and robustness properties of partitioned IFPC systems designed according to two alternative partitioning 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 partitioned IFPC system and validated in non-linear simulations.

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