This disclosure is generally directed to an Unmanned Aerial Device (UAV) that uses a removable computing device for command and control. The UAV may include an airframe with rotors and an adjustable cradle to attach a computing device. The computing device, such as a smart phone, tablet, MP3 player, or the like, may provide the necessary avionics and computing equipment to control the UAV autonomously. For example, the adjustable cradle may be extended to fit a tablet or other large computing device, or retracted to fit a smart phone or other small computing device. Thus, the adjustable cradle may provide for the attachment and use of a plurality of different computing devices in conjunction with a single airframe. Additionally the UAV may comprise adjustable arms to assist in balancing the load of the different computing devices and/or additional equipment attached to the airframe.

Control system for aircraft having laterally offset rotors

Unmanned aerial vehicle with detachable computing device

This disclosure is generally directed to a High Speed vertical takeoff and landing (VTOL) aircraft that includes fixed wing flight capabilities. The High Speed VTOL aircraft may include at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a main wing, and at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a vertical wing. The rotors may be driven by electric motors. However, other power sources may be used such as combustion or hybrid engines. By adjusting the speed and/or the pitch of the rotors, the aircraft can transition from a vertical flight configuration to a horizontal flight configuration and back.

High speed multi-rotor vertical takeoff and landing aircraft

A method and apparatus provide for automatically controlling the flight of a tiltrotor aircraft while the aircraft is in flight that is at least partially rotor-borne. The method and apparatus provide for automatically tilting nacelles in response to a longitudinal-velocity control signal so as to produce a longitudinal thrust-vector component for controlling longitudinal velocity of the aircraft. Simultaneously, cyclic swashplate controls are automatically actuated so as to maintain the fuselage in a desired pitch attitude. The method and apparatus also provide for automatically actuating the cyclic swashplate controls for each rotor in response to a lateral-velocity control signal so as to produce a lateral thrust-vector component for controlling lateral velocity of the aircraft. Simultaneously, collective swashplate controls for each rotor are automatically actuated so as to maintain the fuselage in a desired roll attitude. The method and apparatus provide for yaw control through differential longitudinal thrust produced by tilting the nacelles.

Method and apparatus for flight control of tiltrotor aircraft

A twin-rotor side-by-side compound rotorcraft has a fuselage and variable incident wing assembly that pivots relative to fuselage. The aircraft also has landing gear assembly and a tail fin assembly. The variable incident wing assembly is pivotally attached to the fuselage, and includes wing members, engines fixedly mounted to the wing members or another area of the rotorcraft, and a mast attached at a fixed angle relative to the wing members. Then engines may also be located near the fuselage or another area of the rotorcraft. The variable incident wing assembly is capable of pivoting about a pivot axis, thereby allowing mast orientation in at least a hover mast position and a forward flight mast position. The rotors provide additional forward thrust and the wings provide additional lift, when the mast is in the forward flight mast position.

Rotorcraft with Variable Incident Wing

A control lever assembly for a tilt-rotor aircraft, comprises at least one control lever which is movable relative to a control lever support. The control lever support has a rotational position that varies in correspondence with the tilt of the rotor of the aircraft. For example, the control lever support is movable by an actuator between a first position, in the airplane mode of the aircraft, in which the control lever moves substantially horizontally and a second position, in the helicopter mode of the aircraft, in which the control lever moves substantially vertically.

Control system for aircraft having laterally offset rotors

Citations

Unmanned aerial vehicle with detachable computing device

High speed multi-rotor vertical takeoff and landing aircraft

Method and apparatus for flight control of tiltrotor aircraft

Rotorcraft with Variable Incident Wing

Control lever assembly for a tilt-rotor aircraft

References

Attitude control system for vtol aircraft

Convertiplane with control mechanism

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