| Compared with the conventional helicopter, helicopter with electrically controlled rotor (ECR helicopter)replaces swashplate with trailing-edge flap for primary rotor controls, the advancements of the former have simple structure, light weight, improved safety, convenient for maintenance and so on. The unique way of controlling determines the specificity on the flight dynamics of ECR helicopter. This paper researches on flight dynamics of ECR helicopter.At first, the unsteady aerodynamics models of the electrically controlled rotor (ECR) is established, the basic airfoil is introduced by Leishman and Beddoes based on indicial method for the unsteady subsonic compressible flow case in time domain. Flap aerodynamic model is proposed by Hariharan and Leishman also based on indicial method for unsteady flow case. On its basis, ECR helicopter flight dynamics model is established. Reference helicopter as a sample is improved to ECR helicopter for calculating on the trim, stability and handling quality and analysis the result.A numerical systematic investigation into the effects of ECR design parameter such as pitch index and blade torsional stiffness. Coming to a conclusion: By increasing the pitch index or reducing torsional stiffness, Pitch bandwidth is increased and Required power is decreased. |
