| 摘要 |
A vertically launchable and recoverable winged aircraft includes an airframe, a least one proprotor connected to the airframe through a rotatable drive shaft, and collective and cyclic pitch control systems. The airframe includes a wing having a leading edge and a trailing edge which define a forward direction of flight in an airplane mode. The proprotors each have an axis of rotation generally parallel to the forward direction of flight in airplane mode, and include at least two proprotor blades. The cyclic pitch control system is operably connected to each blade to control the pitch of each blade, so that the aircraft is capable of controlled helicopter mode flight when the wing leading edge is pointed in a generally upward direction.
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