Helicopter flight control system design and evaluation for NOE operations using controller inversion techniques

Abstract

A flight control system design technique is described that allows rapid evaluation of candidate control laws using computer simulated trajectories. The two-step technique first computes the optimum trajectory for the basic aircraft, and then reconstructs the pilot's control displacements necessary to fly this trajectory, given a particular control system architecture. Since the flight control system itself does not add to the acceleration potential of the helicopter, one may evaluate several proposed control laws in terms of the resulting stick inputs for the same maneuver. The method is illustrated through application to implicit and explicit model-following control laws designed for a battlefield helicopter with and without an auxiliary propulsor. It is shown that the technique is a valuable aid for selection of promising control laws for further simulator studies and flight investigations.