부산대학교 도서관

To accurately solve the helicopter optimal equilibrium solution, a novel hybrid genetic algorithm for trimming the helicopter flight simulation model is presented, which solves the problem that traditional trim algorithm is easy to fall into local optimum point. Taking the parts of the body as unit, the flight simulation dynamic model of the whole helicopter including rotor, tail rotor and empennage has been established, in which the Pitt–Peters dynamic inflow model and Leishman–Beddoes unsteady dynamic stall model were integrated into the rotor model. Based on the body dynamic equation, the trim controls and constraint conditions of level flight and steady pitching flight were derived. Using two cases, the effectiveness and accuracy of the hybrid genetic algorithm were verified by comparison with the flight test data from the trim results of UH-60A helicopter. It is shown that there is a good agreement between the trim results and the flight test data. The hybrid genetic algorithm can quickly converge to the optimal solution and is suitable for trimming the simulation model of different flight conditions.