An unmanned aerial vehicle (UAV) includes a vehicle body and an arm assembly. The vehicle body includes a distribution board. The arm assembly includes an arm body, a lampshade, and an electric speed control (ESC) light control board. The arm body includes an accommodation space. The lampshade is mounted at the arm body. The ESC light control board is arranged in the accommodation space and electrically connected to the distribution board through a wire. The ESC light control board includes an illuminator corresponding to the lampshade and is configured to emit light out of the arm assembly through the lampshade.

Described are apparatus and processes for reconfiguring aerial vehicles, such as unmanned aerial vehicles (UAV) during navigation of the aerial vehicle between a maneuverability configuration and an efficiency configuration. When an aerial vehicle needs to be able to quickly maneuver in any direction (vertical, horizontal, pitch, roll, yaw) it is operating in a maneuverability configuration. When configured to operate in the maneuverability configuration, the primary function of the aerial vehicle configuration is to increase maneuverability of the aerial vehicle. When the aerial vehicle is navigating in a direction that is substantially horizontal, for example when navigating between locations, it may be configured to operate in an efficiency configuration. When configured to operate in the efficiency configuration, the primary function of the aerial vehicle configuration is to increase efficiency of the aerial vehicle and reduce power consumption.

An unmanned aerial vehicle includes a central body having a plurality of sides and a plurality of arms extendable from the central body. Each arm is configured to support one or more propulsion assemblies that provide a propulsion force while the unmanned aerial vehicle is in flight. The arms are configured to transform between a flight configuration in which the arms are extended away from the central body and a compact configuration in which free ends of a first subset of the arms collectively define a rectangular area. Free ends of a second subset of the arms are closer to a yaw-axis of the unmanned aerial vehicle than the free ends of the first subset of the arms. The yaw-axis passes through the rectangular area.

Various embodiments for a foldable quad-rotor (FQR) inspired by an origami mechanism are disclosed herein. The FQR can fold its arms during flight to enable aggressive turning maneuvers and operations in cluttered environments. A dynamic model of folding is built for this system with the collected data, and a feedback controller is designed to control the position and orientation of the FQR. Lyapunov stability analysis is conducted to show that the system is stable during arm folding and extension, and motion planning of the FQR is achieved based on a modified minimum-snap trajectory generation method.

A tiltrotor aircraft is designed to accommodate rotors of different diameters, as well as corresponding wings and fuselages with different span and length, while maintaining very high parts commonality, especially with respect to drive train and power source. This enables design and operation of a fleet of such aircraft with significantly different rotor diameters, which are nevertheless optimized for different missions. In preferred embodiments the rotors are configured to have high stiffness and low weight to reduce aero-structural dynamic issues across the fleet. Also in preferred embodiments drive systems are designed for a full range of speed, torque, and power associated with all intended rotors. Turboshaft engine speeds are restricted to a narrow RPM range, so that a single gearset can be replaced to achieve the desired rotor RPM. Also in preferred embodiments, aircraft in a fleet can differ in folded length, empty weight, payload length by up 50%.

A heavy-lift UAV frame includes a central frame portion having a symmetrical shape and forming a pocket area for receiving an avionics package. Top and bottom plates are secured to the central frame portion and include four corner members that extend diagonally outward therefrom. A plurality of boom arms are pivotally connected to the corner members and transition between an extended position for flight and a retracted position for storage and transport. Each boom arm includes a complementary dimension to one side of the central frame portion and is arranged parallel thereto when in the retracted position.

An aerial imaging aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons coupled therebetween. A two-dimensional distributed thrust array is coupled to the airframe. The thrust array includes a plurality of propulsion assemblies each operable for variable speed and omnidirectional thrust vectoring. A payload is coupled to the airframe and includes an aerial imaging module. A flight control system is operable to independently control the speed and thrust vector of each of the propulsion assemblies such that in an inclined flight attitude, the flight control system is operable to maintain the orientation of the aerial imaging module toward a target while translating the aircraft, changing aircraft altitude and/or circling the target.

An unmanned aerial vehicle includes a plurality of propellers and an airframe. The airframe includes a body having a hollow portion, and a plurality of through holes connected to the hollow portion and formed on an outer peripheral surface of the body. The airframe also includes a plurality of arms supporting the plurality of propellers, and each arm of the plurality of arms includes a base end portion disposed at a body side in a longitudinal direction of the respective arm. The base end portion is inserted in a corresponding through hole of the plurality of through holes and supported by the body. Each arm of the plurality of arms is configured to be stored in the hollow portion of the body by being retracted into the body via the through hole, and expanded out of the body by being pulled out of the body via the through hole.

The present invention relates to the field of air vehicle technologies and provides an arm, a power assembly and an unmanned aerial vehicle. The arm includes a principal arm and an auxiliary arm. The principal arm is mounted on the vehicle body and the principal arm can rotate relative to the vehicle body. One end of the auxiliary arm is connected to the principal arm. The auxiliary arm can rotate relative to the principal arm. In the foregoing manner, an unmanned aerial vehicle having the arm is compact in structure, small in volume and easy to carry after being folded.

A UAV (unmanned aerial vehicle) arm mechanism includes an arm fixed device, a control device, a limiting device, and an arm connecting device, wherein the control device is adapted for controlling an assembly and disassembly of the arm fixed device and the arm connecting device, the limiting device is adapted for relatively fixing the arm fixed device and the arm connecting device; the control device is adapted for driving the limiting device to be detached from the arm connecting device, so as to achieve that the arm fixed device and the arm connecting device switch among at least three different states through a relative rotation. The UAV and the UAV arm mechanism can be locked up through the positioning pins, and also can be folded and disassembled after pressing the controlling device.