Abstract: The invention provides for systems, methods, and compositions for manipulation of sequences and/or activities of target sequences. Provided are vectors and vector systems, some of which encode one or more components of a CRISPR complex, as well as methods for the design and use of such vectors. Also provided are methods of directing CRISPR complex formation in eukaryotic cells and methods for selecting specific cells by introducing precise mutations utilizing the CRISPR/Cas system.

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: 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.

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: 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 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: An aircraft and an obstacle avoidance method and system thereof. The obstacle avoidance system comprises an image capturing apparatus (11), a gimbal stability-enhancement system, and a second controller (14). The gimbal stability-enhancement system comprises a gimbal body (12) and a gimbal control system (13). The image capturing apparatus (11) is arranged on the gimbal body (12), and is used for capturing an image in a flying direction when the aircraft is flying. The gimbal control system (13) is connected to the gimbal body (12). The second controller (14) is used for determining whether an obstacle exists in the image captured by the image capturing apparatus (11), and if yes, changing the flying direction of the aircraft according to a position of the obstacle, and if not, controlling the aircraft to fly in the current flying direction.

Abstract: The present disclosure relates to an aerial shooting method and system using a drone, wherein the aerial shooting method using a drone comprises steps of presetting an aerial path and generating a first operation instruction based on the preset aerial path; controlling the drone to fly along the preset aerial path according to the first operation instruction; marking a plurality of waypoints during the flight of the drone along the preset aerial path; planning a flight path based on the plurality of waypoints and generating a flight instruction based on the flight path; making the drone automatically fly along the flight path according to the flight instruction; and controlling the drone to shoot during the automatic flight of the drone.

Abstract: An aircraft and a roll method thereof. The aircraft comprises an aircraft body and a remote control, a motor, a power supply, a controller, a six-axis inertial sensor and an H-bridge chip. The remote control is configured for a user to input a desired inclination angle of the aircraft, and transmit the desired inclination angle to the controller, the desired inclination angle being 180° or 360°. The six-axis inertial sensor is configured to detect a current real-time inclination angle of the aircraft relative to a horizontal plane, and transmit the real-time inclination angle to the controller. The controller is configured to compute a difference value between the desired inclination angle and the real-time inclination angle, and compute a roll voltage according to the difference value. The controller is further configured to control the H-bridge chip so that the roll voltage is input to the motor.

Abstract: Disclosed is an aerial vehicle, comprising: an airframe, a propeller(s), a duct(s) and a driving device, wherein the duct(s) is arranged on the airframe and adapted to increase a lifting force for the aerial vehicle, the propeller is arranged in the respective duct and is connected to the airframe, and the driving device is connected to the propeller(s) and is arranged on the airframe.

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 target tracking method for an air vehicle includes steps of: during a flight of an air vehicle main body to a position corresponding to a global positioning system (GPS) positioning signal, taking pictures of an area where a reference target is located by a camera, and obtaining a reference image; extracting reference image characteristics of the reference target and initial position information of the reference target in the reference image from the reference image; when the camera obtains a temporary image showing a temporary target, extracting temporary image characteristics of the temporary target and temporary position information of the temporary target in the temporary image from the temporary image; if the reference image characteristics are consistent with the temporary image characteristics, calculating a deviation direction according to a difference between the initial position information and the temporary position information; and tracking the temporary target in the deviation direction.

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.