Abstract: A multi-rotor UAV (unmanned aerial vehicle) includes a fuselage, four aircraft wings and a landing stand, wherein the landing stand comprises four landing support legs, every landing support leg is installed below an outermost end of a corresponding aircraft wing to form a landing support structure of the UAV, every landing support leg comprises a main pole and a base soft rubber, wherein the base soft rubber enwraps a base of the main pole for buffering. The multi-rotor UAV of the present invention is stable while taking off or landing, and is light in weight.

Abstract: A transport drone includes: a drone body; a transport unit for carrying an object to be transported; a balancing unit comprising a balancing frame and a swinging device, wherein the balancing frame is connected to the transport unit; the swinging device is respectively connected to the balancing frame and the drone body; the swinging device has rotational freedom; a sensor placed on the balancing frame for detecting a tilt angle of the balancing frame; and a controller electrically connected to both the sensor and the swinging device, wherein the controller controls rotation of the swinging device according to the tilt angle detected by the sensor, so as to adjust the tilt angle of the balancing frame and keep the transport unit in a horizontal state. The transport drone ensures that the items to be transported are in a horizontal state, effectively preventing dumping or damage of the items.

Abstract: A method for controlling an attitude of a rotor UAV (unmanned aerial vehicle) includes judging whether the rotor UAV is in a first attitude on a support base; and starting a first thrust generating device which is offset from a first side of a center of gravity of the rotor UAV, the first thrust generating device generating a thrust that faces away from the support base while working, the first side moving away from the support base, flipping the rotor UAV and switching the rotor UAV from the first attitude to a second attitude. Also, a system for controlling the attitude of the rotor UAV is provided. According to the method and the system, the rotor UAV can be switched between different attitudes without artificially assisting in adjusting a current attitude of the rotor UAV, so that the convenience in use and the satisfaction of experience are improved.

Abstract: An electrical connection structure includes a first connection device and a second connection device. The first connection device includes a first outer tube and a first base; multiple rolling parts are disposed in a tube wall of the first outer tube; the second connection device includes a second outer tube, a casing tube and a second base; the second outer tube has a recess on an outer wall thereof; a gap space is provided between the casing tube and the second outer tube; when the first connection device is docked with the second connection device, the first outer tube is inserted into the gap space, the rolling parts are inserted into the recess; the casing tube forces the rolling parts to remain in the recess for locking up the first and second connection devices. A UAV includes a tail rod quick release structure which includes the electrical connection structure.

Abstract: An anti-wring component, a gimbal and a flying machine are disclosed in the present invention. The anti-wring component comprises a wire spool and a supporting locating piece, wherein the wire spool is fixed on the supporting locating piece; the wire spool comprises an anti-wring cylinder; a cord hole is set on the anti-wring cylinder for a multi-wire planar cable to go inside; wire lead-out holes are set on the anti-wring cylinder for the multi-wire planar cable to pass through; a limiting boss is set on the anti-wring cylinder for limiting the multi-wire planar cable. The gimbal comprises a roll axis U-shape arm and the anti-wring component; wherein the supporting locating piece is fixed on the roll axis U-shape arm. The flying vehicle comprises the gimbal. The present invention prevents the multi-wire planar cable from wring and ensures a normal transmission of data and image signals.

Abstract: 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.

Abstract: 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.

Abstract: A method for calibrating aircraft tri-axial balance include steps of: receiving a first indicator signal; tumbling an aircraft by 360 degrees by specified times according to the first indicator signal; collecting and recording first geomagnetic data; receiving a second indicator signal; rotating the aircraft laterally by 360 degrees by the specified times according to the second indicator signal; collecting and recording second geomagnetic data; receiving a third indicator signal; rotating the aircraft horizontally by 360 degrees by the specified times according to the third indicator signal; collecting and recording third geomagnetic data; and obtaining a calibrated geomagnetic curve according to the first geomagnetic data, the second geomagnetic data and the third geomagnetic data.

Abstract: A gimbal control method, a gimbal control system and a gimbal device are provided. The method includes steps of: obtaining simulation position information, measurement position information and simulation angular velocity information of a Pitch axis of a gimbal in real-time; calculating a first position error between the simulation position information of the Pitch axis and the measurement position information of the Pitch axis; processing the first position error with proportional-derivative calculation, wherein the first position error is compensated with the simulation angular velocity information during the proportional-derivative calculation; and, according to a result of the proportional-derivative calculation after compensating, generating a first torque control instruction for controlling a torque of a Pitch axis motor, so as to enable the Pitch axis to reach a position corresponding to the simulation position information of the Pitch axis. According to the present invention, a brush motor is adopted.

Abstract: A photographing method and a photographing device of an unmanned aerial vehicle, the unmanned aerial vehicle, and a ground control device are provided. The method includes steps of: receiving a photographing instruction of the unmanned aerial vehicle; selecting a photographing model of the unmanned aerial vehicle, wherein the photographing model includes a photographing object and a photographing mode of the unmanned aerial vehicle which are correlated with each other; when the photographing object corresponding to the photographing model of the unmanned aerial vehicle is identified to exist in a captured image, adopting the photographing mode correlated to the photographing object of the unmanned aerial vehicle, for adjusting a flight condition of the unmanned aerial vehicle and for photographing the photographing object of the unmanned aerial vehicle. The present invention enables the unmanned aerial vehicle to automatically capture image data of ideal effect.

Abstract: A power communication electrical connector is provided, comprising: a plug and a socket which are matched and plugged for connecting a power source circuit or a high-power load circuit; wherein power source connectors and the signal connectors are respectively provided on both the plug and the socket, the power source connectors are for connecting a power source of the power source circuit or a high-power load of the high-power load circuit; the signal connectors are for connecting an external chip of the power source circuit or an external chip of the high-power load circuit, wherein a power ground of the power source connectors the a signal ground of the signal connectors are separately provided. In addition, an anti-spark power communication electrical connector is further provided.

Abstract: A detachable propeller holder device includes a propeller holder module, a fixed seat and a motor module. Paddles are located the propeller holder module, a buckling component is located on the propeller holder module, the buckling component includes two elastic arms and two hooks, the two elastic arms are symmetrically located at two sides of the propeller holder module, the hooks are respectively located at an end of the two elastic arms and are respectively buckled with two limit portions which are symmetrically located at the fixed seat, so as to fix the propeller holder module to the fixed seat. In the detachable propeller holder device, only the buckling component at the side of the propeller holder module is pinched by fingers to deform inwardly till the hooks are detached from the limit portions of the fixed seat, and then the propeller holder module is pulled upwardly to be removed.

Abstract: An auxiliary control method and an auxiliary control system for an unmanned aerial vehicle (UAV) are provided. The auxiliary control method for the UAV includes steps of: based on a flight attitude and a flight speed of the UAV, predicting a flight path of the UAV in a scheduled time; and providing information about the flight path of the UAV in the scheduled time to an operator of the UAV. The auxiliary control method and system for the UAV provided by the present invention are able to provide the information about the flight path of the UAV in the scheduled time to the operator of the UAV, so as to help the operator of the UAV make a control decision for the UAV.

Abstract: A shock absorber includes an upper vibration damping sheet and a lower vibration damping sheet. Multiple first vibration dampers and a second vibration damper are located between the upper vibration damping sheet and the lower vibration damping sheet; the first vibration dampers are close to an edge of both the upper vibration damping sheet and the lower vibration damping sheet. One end of the second vibration damper is located on the lower vibration damping sheet and is far away from the edge of the lower vibration damping sheet, the other end of the second vibration damper extends towards the upper vibration damping sheet along an axial direction of the lower vibration damping sheet, whereby when a carrier moves, the shock absorber provides a damping effect for a gimbal through the first vibration dampers and the second vibration damper. An aircraft includes the shock absorber mentioned above and a gimbal.

Abstract: An aircraft control device and a remote controller aircraft are disclosed. The aircraft control device includes a first channel configured to receive first control information outputted by a remote controller and transmit the first control information to an aircraft; a second channel configured to receive second control information outputted by the remote controller and transmit the second control information to a camera and/or a gimbal; and a switch unit configured to switch that the first control information is received by the second channel and transmitted to the aircraft when the first channel is disturbed or a distance between the remote controller and the aircraft is larger than a distance threshold. The present invention is able to switch the transmission route of the first control information between the first channel and the second channel in accordance with situations of the first channel and the second channel.

Abstract: A calibration method, a calibration device and a calibration system for a handheld gimbal are provided.

Abstract: An obstacle avoidance device for detecting surroundings of an unmanned mobile device is disclosed, which includes a stabilization platform connected with the unmanned mobile device, wherein the stabilization platform includes a stabilizer for ensuring stably bearing at least one platform camera; and an obstacle avoidance module fixed with the stabilization platform, so as to reduce interferences to detecting the surroundings by the obstacle avoidance module when the unmanned mobile device acts. The obstacle avoidance device of the present invention is able to keep a stable attitude while the unmanned mobile device is unstable and changes an attitude thereof, so as to effectively avoid obstacles.

Abstract: A gimbal vibration damper for a UAV (unmanned aerial vehicle) includes an upper vibration damping sheet which is connected with a bottom surface of a fuselage of the UAV, a lower vibration damping sheet which is connected with a top of a gimbal, and a vibration damping component which is located between the upper vibration damping sheet and the lower vibration damping sheet, wherein an upper end of the vibration damping component is fixed with the upper vibration damping sheet, a lower end of the vibration damping component is fixed with the lower vibration damping sheet. The gimbal vibration damper provided by the present invention is able to achieve better gimbal damping effect.

Abstract: The present disclosure relates to the technical field of shooting and discloses a handheld stand for shooting which is more stable. The present disclosure comprises a rotatable handle mechanism, a base, a position adjusting mechanism, a connecting mechanism and a counterweight, wherein the rotatable handle mechanism is connected to a bottom of the base, the base is rotatable with respect to the rotatable handle mechanism, the position adjusting mechanism is disposed on an upper surface of the base for holding a shooting device and adjusting a position of the shooting device relative to the base, the counterweight is disposed below the rotatable handle mechanism and connected to the base via the connecting mechanism, and the counterweight is configured to adjust a center of gravity of the base. The present disclosure further discloses a method for adjusting the center of gravity of a handheld stand.