A COMBINED SCHEME FOR CALCULATING THE AERODYNAMIC CHARACTERISTICS OF A HELICOPTER WITH A SINGLE ROTOR

Abstract

For a helicopter, interaction with the environment plays a more significant role than for an airplane, because during interaction the geometry of the helicopter changes (the change is largely related to the position of the blades relative to the main rotor hub). In turn, the movement of the blades causes a change in the forces acting on the blades. The aerodynamic forces acting on the articulated blade become dependent not only on the movement of the helicopter, but also on the movement of the blade relative to the hub. The aerodynamic characteristics of the main rotor, and therefore the helicopter in general, have a significant dependence on the position of the controls. This indicates that the determination of the aerodynamic characteristics of the helicopter without taking into account the deviations of the control levers gives approximate values. This circumstance significantly complicates the process of determining the aerodynamic characteristics of a helicopter.

An analysis of publications in the field of rotor motion dynamics and helicopter flight dynamics is performed. Theoretical and applied issues of calculating the aerodynamic characteristics of a helicopter rotor and a helicopter as a whole are considered. Existing methods of calculating the rotor in various motion conditions are presented. The possibility of jointly solving the problems of rotor aerodynamics and single-rotor helicopter flight dynamics at established flight modes, subject to balancing, is provided. In the end, such an approach to the solution will allow for a more accurate prediction of the helicopter flight characteristics, determining the loads on the structural elements of the rotor, tail rotor, stabilizer, and the joint action of these loads on the helicopter fuselage. An analysis of possible theories of determining the aerodynamic characteristics of the rotor and tail rotor is performed. A methodology for solving helicopter balancing problems while minimizing time and computer resources is proposed.