An aircraft including: a pair of wings rotatably coupled to opposing lateral sides of the fuselage and being rotatable relative to each other; a pair of servo motors, each connected to a corresponding wing and configured to rotate the corresponding wing in two rotational directions; a pair of thrust motors, each of which mounted on a corresponding wing; and a flight controller connected to the servo motors and to the thrust motors, and configured to control each servo motor and each thrust motor, such that the aircraft can be selectively operated in a cruising mode, such that the pair of wings are in a non-permanent-rotation-state about a yawing axis which extends at least substantially through the center of gravity, and a monocopter mode, in which the pair of thrust motors provide thrust in opposite directions so that the pair of wings are in a permanent-rotation-state about the yawing axis.

An aerial vehicle including a central frame electro-mechanically connected to a central frame inertial measurement unit (IMU) adapted to output central frame inertial measurements to one or more controllers. A motor frame includes a central rod mounted in perpendicular to a longitudinal axis of the central frame, and a pair of lateral arms each fixated to a different end of the central rod in parallel to the longitudinal axis of the central frame. A motor frame IMU adapted to output motor frame inertial measurements of the motor frame to the flight controller. The central frame is further electro-mechanically connected to the one or more controllers adapted to calculate control signals for rotating the central frame according to the central frame inertial measurements and the central rod inertial measurements. A stabilizing motor adapted to rotate the central frame according to the control signals.

An aerial vehicle including a central frame electro-mechanically connected to a central frame inertial measurement unit (IMU) adapted to output central frame inertial measurements to one or more controllers. A motor frame includes a central rod mounted in perpendicular to a longitudinal axis of the central frame, and a pair of lateral arms each fixated to a different end of the central rod in parallel to the longitudinal axis of the central frame. A motor frame IMU adapted to output motor frame inertial measurements of the motor frame to the flight controller. The central frame is further electro-mechanically connected to the one or more controllers adapted to calculate control signals for rotating the central frame according to the central frame inertial measurements and the central rod inertial measurements. A stabilizing motor adapted to rotate the central frame according to the control signals.

A propulsion assembly for an unmanned aerial vehicle (UAV), includes a motor, a propeller seat configured to be driven by the motor and to receive a propeller, and a sensor configured to collect sensing data useful for determining a type of the propeller disposed on the propeller seat and controlling the motor based on the type of the propeller.

A drone with extendable and rotatable wings and a multiple accessory securing panel is provided. The extendable wings help increase the lift of the drone and reduce the air drag on the drone. The multiple accessory securing panel allows various tools and objects to be temporarily and selectively secured to the drone. The multiple accessories may be secured to the drone by a ground based rotating delivery unit. The drone may have a removable front nose and legs which receive power from a power unit.

A drone with extendable and rotatable wings and a multiple accessory securing panel is provided. The extendable wings help increase the lift of the drone and reduce the air drag on the drone. The multiple accessory securing panel allows various tools and objects to be temporarily and selectively secured to the drone. The multiple accessories may be secured to the drone by a ground based rotating delivery unit. The drone may have a removable front nose and legs which receive power from a power unit.

A multicopter is disclosed including a plurality of rotor devices, where a rotor device has at least one rotor blade which is rotatable about a rotor blade axis. The rotor device further includes a first section rotatably driven about an axis of rotation and a second section which is movable relative to the first section about an axis running parallel to the axis of rotation and to which the rotor blade is attached or which includes the rotor blade. A relative position of the second section in relation to the first section depends on a torque with which the first section is driven and a mechanical coupling which couples the relative position of the first section relative to the second section to a rotational position of the rotor blade about the rotor blade axis.

A multicopter is disclosed including a plurality of rotor devices, where a rotor device has at least one rotor blade which is rotatable about a rotor blade axis. The rotor device further includes a first section rotatably driven about an axis of rotation and a second section which is movable relative to the first section about an axis running parallel to the axis of rotation and to which the rotor blade is attached or which includes the rotor blade. A relative position of the second section in relation to the first section depends on a torque with which the first section is driven and a mechanical coupling which couples the relative position of the first section relative to the second section to a rotational position of the rotor blade about the rotor blade axis.

A vertical tail of a composite-wing unmanned aerial vehicle (UAV) having a body, a rudder face section, a rotor section, shock absorbing component and a quick installation assembly of circuit. The body includes a tail body frame and a shell. The rudder face section has a rudder machine and a rudder surface. The rudder surface is connected to one end of the tail for steering the directional deflection of the UAV. The shock absorbing component is connected to the lower end plate and the shock absorbing component absorbs the shock to the body. The quick installation assembly of circuit includes a plug, a positioning sleeve and a bias piece, the positioning sleeve is located on the outer circumference of the plug and slidingly connected to the plug, the bias piece is set between the plug and the positioning sleeve, the bias piece can absorb the impact on the plug.

According to a first aspect of the invention, there is provided a volitant vehicle comprising, a body (112), a control unit being configured to compute an estimate of the orientation of a primary axis (130) of said body with respect to a predefined reference frame, wherein said primary axis is an axis about which said vehicle rotates when flying; and at least one propeller (104) attacked to the body, wherein each of said at least one propeller has an axis of rotation (110) which is fixed with respect to said body, is configured to simultaneously produce a thrust force and a torque, said thrust force having a component along the primary axis, said torque having a component along the primary axis constructively contributing to the vehicle rotating about said primary axis, said torque having a component perpendicular to the primary axis, and all of said at least one propeller rotate with the same handedness about their respective thrust forces.