Optimal Control of a Compound Rotorcraft for Engine Performance Enhancement

Abstract Demands for rotorcraft with increased flight speed, improved operational performance and reduced environmental impact have led to a drive in research development of alternative concepts. Compound overcome the speed limitations conventional helicopters additional lifting propulsive components. Further benefits, these augmentations provide control parameters, resulting redundancy. This work aims investigate optimal strategies generic coaxial compound rotorcraft, equipped turboshaft engines, targeting minimization mission fuel burn gaseous emissions. The direct redundant controls considered are: (a) main rotor (b) propeller (c) fuselage pitch attitude. A simulation tool analysis has been developed coupled zero-dimensional engine model stirred-reactor combustor model. First, experimental test data were used extensive validation models. parametric was then carried out gain insight into effect controls. followed by derivation generalized set allocations using surrogate-assisted genetic algorithm. Application during realistic scenarios demonstrated reductions NOx up 6.93% 8.74%, respectively. method constitutes rigorous approach guide design systems future advanced rotorcraft.