Aircraft capable of vertical takeoff and landing, hovering, and efficient forward flight are described. An aircraft includes two side mounted tiltable proprotors and a central rotor disposed above the proprotors. The proprotors are tiltable between at least a horizontal position for forward flight and a vertical position for vertical or hovering flight. The central rotor may be powered for vertical and transitional flight modes and may turn by free autorotation during forward flight. The proprotors may be differentially tilted during vertical or hovering flight to counter torque effects of the central rotor. The central rotor may be foldable and/or easily detachable from the aircraft to facilitate storage and transportation. Left and right proprotors may provide both forward thrust and attitude control. Control inputs to left and right proprotors may be connected directly to an autopilot creating closed loop actuation using motor RPM feedback.

A ganged servo flight control system for an unmanned aerial vehicle is provided. The flight control system may include a swashplate having first, second, and third connection portions; a first control assembly connected to the first connection portion of the swashplate; a second control assembly connected to the second connection portion of the swashplate; and a third control assembly connected to the third connection portion of the swashplate. The first control assembly may include two or more servo-actuators connected to operate in cooperation with each other.

Aircraft capable of vertical takeoff and landing, hovering, and efficient forward flight are described. An aircraft includes two side mounted tiltable proprotors and a central rotor disposed above the proprotors. The proprotors are tiltable between at least a horizontal position for forward flight and a vertical position for vertical or hovering flight. The central rotor may be powered for vertical and transitional flight modes and may turn by free autorotation during forward flight. The proprotors may be differentially tilted during vertical or hovering flight to counter torque effects of the central rotor. The central rotor may be foldable and/or easily detachable from the aircraft to facilitate storage and transportation. Left and right proprotors may provide both forward thrust and attitude control. Control inputs to left and right proprotors may be connected directly to an autopilot creating closed loop actuation using motor RPM feedback.

Aircraft capable of vertical takeoff and landing, hovering, and efficient forward flight are described. An aircraft includes two side mounted tiltable proprotors and a central rotor disposed above the proprotors. The proprotors are tiltable between at least a horizontal position for forward flight and a vertical position for vertical or hovering flight. The central rotor may be powered for vertical and transitional flight modes and may turn by free autorotation during forward flight. The proprotors may be differentially tilted during vertical or hovering flight to counter torque effects of the central rotor. The central rotor may be foldable and/or easily detachable from the aircraft to facilitate storage and transportation. Left and right proprotors may provide both forward thrust and attitude control. Control inputs to left and right proprotors may be connected directly to an autopilot creating closed loop actuation using motor RPM feedback.

The present invention is a winged VTOL aircraft of novel configuration that utilizes a single-axis rotor mounted at an oblique angle within a forward-facing, bifurcating duct, that is controlled by a plurality of servo driven vanes, producing a mechanically simple, redundantly controlled vehicle that can carry cargo, people, or otherwise, directly from point to point. The configuration uses sets of vanes to produce both moments and forces referenced around the vehicle's center of gravity, thereby, allowing the vehicle to translate in a level position, or stay stationary relative to the ground while at a slight pitch or roll attitude. This feature is very important for autonomous vehicles to accurately pick up and drop off payloads on unlevel terrain or in windy conditions. Other rotor vehicles require pitch or roll attitude to translate or compensate for wind. Complementing this vehicle's mechanically simple rotor system is a novel mechanism that collectively drives the pitch of the rotor blades by combining the input from three separate servos. Each servo can be controlled by redundant fight control systems.

A mechanically simple rotor system is a novel mechanism that collectively drives the pitch of the rotor blades by combining the input from three separate servos. Each servo can be controlled by redundant control systems. This configuration reduces total error caused by any one system and allows the continuation of rotor pitch control in the event of one or more servo or system failures.

A mechanically simple rotor system is a novel mechanism that collectively drives the pitch of the rotor blades by combining the input from three separate servos. Each servo can be controlled by redundant control systems. This configuration reduces total error caused by any one system and allows the continuation of rotor pitch control in the event of one or more servo or system failures.

A rotor blade control device for a helicopter, comprising a swash-ring, said swash-ring comprising a non-rotating component of the swash-ring, coupled in a non-rotatable manner to the helicopter, a rotating component of the swash-ring, at least three actuators disposed around a rotor shaft axis of the helicopter, a coupling means between the actuators and the non-rotating component of the swash-ring. The coupling means can be adjusted in terms of its pitch, for changing the position of a swash-ring coupling point on the non-rotating component of the swash-ring along the rotor shaft axis by the actuator, by means of a control shaft, in order to adjust the rotor blades. The coupling means has a pushing member, in addition to at least one lever non-rotatably connected to the control shaft, which is connected at a first end to the lever in a rotational joint, such that it can pivot about a pivotal axis, and is coupled at a second end to the non-rotating component of the swash-ring at a swash-ring coupling point, in a ball joint.

A rotor blade control device for a helicopter, comprising a swash-ring, said swash-ring comprising a non-rotating component of the swash-ring, coupled in a non-rotatable manner to the helicopter, a rotating component of the swash-ring, at least three actuators disposed around a rotor shaft axis of the helicopter, a coupling means between the actuators and the non-rotating component of the swash-ring. The coupling means can be adjusted in terms of its pitch, for changing the position of a swash-ring coupling point on the non-rotating component of the swash-ring along the rotor shaft axis by the actuator, by means of a control shaft, in order to adjust the rotor blades. The coupling means has a pushing member, in addition to at least one lever non-rotatably connected to the control shaft, which is connected at a first end to the lever in a rotational joint, such that it can pivot about a pivotal axis, and is coupled at a second end to the non-rotating component of the swash-ring at a swash-ring coupling point, in a ball joint.

A ganged servo flight control system for an unmanned aerial vehicle is provided. The flight control system may include a swashplate having first, second, and third connection portions; a first control assembly connected to the first connection portion of the swashplate; a second control assembly connected to the second connection portion of the swashplate; and a third control assembly connected to the third connection portion of the swashplate. The first control assembly may include two or more servo-actuators connected to operate in cooperation with each other.