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.

Sounds are generated by an aerial vehicle during operation. For example, the motors and propellers of an aerial vehicle generate sounds during operation. Systems, methods, and apparatus may actively adjust the position and/or configuration of one or more propeller blades of a propulsion mechanism to generate different sounds and/or lifting forces from the propulsion mechanism.

The present invention relates to the technical field of UAV (unmanned aerial vehicle), and more particularly to a UAV with linkage foldable arms, which includes a linkage mechanism, a fuselage body and multiple aircraft arms. The multiple aircraft arms are connected with each other through the linkage mechanism and are connected with the fuselage body; a locating part is located in a middle of the fuselage body; the locating part comprises a positioning structure, a fixed structure which plays a limit role is located on one of the multiple aircraft arms, the fixed structure is buckled with the positioning structure. When the aircraft arms are unfolded or folded, only one aircraft arm needs to be operated to drive other aircraft arms to move under the action of the linkage mechanism, so that multiple folding steps are simplified into a folding process, which is convenient in operation and strong in practicability.

A foldable multi-rotor UAV includes: a fuselage; and a plurality of arms, wherein a first end of each of the arms is connected to a side face of the fuselage through a rotating mechanism; a motor and foldable blades connected to the motor are provided on a second end of each of the arms; each of the arms rotate relatively to the fuselage through the rotating mechanism; wherein the arms comprises a front arm and a rear arm; during a folded state, the rear arm upwardly rotates towards the fuselage for folding, in such a manner that the rear arm is contained at a lower portion of the side face of the fuselage; then the front arm upwardly rotates towards the fuselage for folding, in such a manner that the front arm is contained at an upper portion of the side face of the fuselage.

An autonomous flight vehicle capable of both rotary wing flight and fixed wing flight may include a pair of rotary wing flight thrusters used during rotary wing flight and a smaller pair of hybrid flight thrusters used during both rotary wing flight and fixed wing flight. The larger rotary wing flight thrusters are skewed at an angle to reduce an apparent torque and improve the controllability of the autonomous flight vehicle, while using smaller, and so more efficient, thrusters during fixed wing flight.

The present invention relates to an unmanned helicopter. The unmanned helicopter comprises a fuselage. Two arms are respectively disposed on each of two sides of the fuselage. One end of each arm is connected to the fuselage, and the other end of each arm is provided with a rotor having a motor. The unmanned helicopter is characterized in that: the four arms are grouped into a front group and a rear group, two arms in each group are disposed symmetrically along the axis of the fuselage, the fuselage is movably connected to each arm, an angle between a length direction of any one of the two arms in each group and a corresponding rotation axis is an angle r, an angle between the rotation axis and a horizontal surface of the fuselage is an angle a, and an angle between a projection line of the rotation axis on the horizontal surface of the fuselage and the axis direction that extends outward the fuselage is an angle b. By ingeniously selecting values of the angle a, the angle r and the angle b, the structure of the unmanned helicopter in a folded state is very compact, thereby effectively saving space.

An unmanned aerial vehicle comprises a housing, a plurality of first arms, a plurality of second arms, and a landing gear. The housing includes a gimbal attachment to couple a gimbal with a camera. Each of the plurality of first arms and the plurality of second arms rotatably couple with the housing at one end and has a motor coupled with a propeller on the other end. The landing gear includes a plurality of foldable legs and releasably couples with an underside of the housing. The aerial vehicle may be programmed with aerial flight path data that corresponds with a prior traced route.

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

A flight device includes a device body with a surface, a plurality of arm structures disposed in the device body and a plurality of rotor modules disposed to the arm structures respectively. Each arm structure includes a fixing base, a second screw element, a connecting unit, a rod body and a position-limiting element. The fixing base is disposed in the device body and includes a first screw element having a first screw part. The second screw element has a second screw part matched with the first screw part. The connecting unit drills through the second screw element. The connecting unit is locked to the fixing base by screwing the first and second screw parts with each other. The rod body drills through the connecting unit. The position-limiting element is disposed between the second screw element and the connecting unit. The position-limiting element abuts against the second screw element.

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.