METHODS OF COMPUTATION OF THE HELICOPTER DEFORMATIONS FOR THE SPECIFIED FLIGHT REGIME

摘要

Mathematical models of deformed helicopters at specified flight regimes are considered. The eigenmode expansion method is used when solving dynamic problems within the framework of the finite-element method. The equilibrium of an aeromechanical scheme of a helicopter is determined by the sum of the inertial, gravitational, and aerodynamical forces. Possible deviations from the trajectory when simulating the specified flight regime under the impact of structural deformations are compensated by the equation of the stabilization and control system.