The goal of this paper is to consider problems of mathematical modelling of non-steady flight regimes of a helicopter equipped with a main rotor hingeless hub, as well as helicopter controlled motion. The technique suggested is based on numerical integration with respect to time using expansion of blade strains, and the calculation results by this technique are presented. The design loads are compared with the experimental ones. The paper also describes the results of modelling dynamics of a helicopter with a main rotor hingeless hub in flight by autopilot to improve stability and controllability.
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