| 摘要 |
A tiltrotor (100) comprises a fuselage (110), a couple of wings (120) connected to the fuselage (110) and having a longitudinal axis x, each wing (120) arranged to rotate about longitudinal axis x with respect to the fuselage (110), a couple of rotors (130), each rotor (130) being connected to a wing (120) and arranged to rotate about longitudinal axis x, each rotor (130) comprising at least one blade (131) arranged to rotate about a rotation axis y substantially orthogonal to the longitudinal axis x. The tiltrotor (100) further comprises a rotation means which is configured to cause the rotation of the couple of rotors (130) and/or the couple of wings (120) about longitudinal axis x, in order to pass at least between a first configuration, where the rotation axis y is substantially vertical and a second configuration, where the rotation axis y is substantially horizontal. The rotation means comprises a first elongated transmission element (141), which is located within the couple of wings (120) and arranged to rotate about longitudinal axis x for setting in rotation the couple of wings (120), and a second elongated transmission element (142), which is located within the first elongated transmission element (141) and arranged to rotate about longitudinal axis x for setting in rotation the couple of rotors (130). The first and the second elongated transmission element (141,142) are adapted to rotate about longitudinal axis x independently of one another, so that the couple of rotors (130) and the couple of wings (120) can rotate independently of each other. |
