Design and Feasibility Study of a Turboshaft equipped Two-Seat Kitcopter

摘要

The paper discusses some major design reflections for a two-seat gas turbine equipped helicopter with a main rotor designed for an AUM of 650 kg. The helicopter gross weight estimations, the engine, the main and tail rotor, the helicopter performance and the drive train are tackled. For the main rotor, a blade-element-momentum-theory program allowed the verification of a safe working domain for the helicopter main rotor in hover OGE. From this design study, some important helicopter performance characteristics have been derived. Weight is a major drive factor in the design of an aircraft and particularly on a helicopter with a small payload ratio. In a helicopter, the transmission drive system has a significant impact on the total weight of the helicopter. Therefore, an examination of the important drive train components are discussed in this paper.