| 摘要 |
A compound aircraft features variable incidence wings, a thruster, a rotor and a clutch connecting the engines to the rotor. Upon reaching a suitable forward speed, the control system of the compound aircraft unloads the rotor and disengages the clutch, disconnecting the rotor from the engines. The control system configures the cyclic and collective pitch effectors to cause the rotor to autorotate. The control system selects an autorotation rotational speed that is adequately rapid to prevent excessive deformation of the rotor blades due to aerodynamic forces acting on the blade and that is adequately slow to prevent excessive compressibility effects. |
