Abstract: The embodiments are a zoom method and apparatus, an unmanned aerial vehicle, an unmanned aircraft system and a storage medium. The zoom method is applied to an unmanned aerial vehicle including an image capturing apparatus and the method includes: controlling the image capturing apparatus to capture an initial image, where a resolution of the initial image is W0*H0 and an area of the initial image is S0; obtaining a cropped image according to the initial image, where the cropped image is an image with an area of S cropped from a preset region in the initial image, S0/S=C and C is a digital zoom factor of the image capturing apparatus; and obtaining a zoom image according to the cropped image, where the zoom image is an image obtained by zooming the cropped image by C/A times, a resolution of the zoom image is W1*H1, A=W0/W1 and C?A.

Abstract: Embodiments of the present application provide an image fusion method and a bifocal camera. The method includes: acquiring a thermal image captured by the thermal imaging lens and a visible light image captured by the visible light lens; determining a first focal length when the thermal imaging lens captures the thermal image and a second focal length when the visible light lens captures the visible light image; determining a size calibration parameter and a position calibration parameter of the thermal image according to the first focal length and the second focal length; adjusting a size of the thermal image according to the size calibration parameter, and moving an adjusted thermal image to the visible light image according to the position calibration parameter for registration with the visible light image, to obtain to-be-fused images; and fusing the to-be-fused images to generate a bifocal fused image.

Abstract: A propeller, a propeller kit, a power assembly, a power kit and an unmanned aerial vehicle (UAV). The propeller includes a hub and at least two blades connected to the hub. The hub is detachably mounted on a corresponding drive apparatus by a mounting member corresponding to the hub, so that the propeller is mounted on the corresponding drive apparatus. A surface, facing the mounting member, of the hub is provided with a first fitting portion. A surface, facing the hub, of the mounting member is provided with a second fitting portion corresponding to the first fitting portion. The first fitting portion matches the second fitting portion. In the foregoing manner, a user can be prevented from incorrectly mounting a forward propeller and a counter-rotating propeller during the use of a quick-detachable propeller in the embodiments of the present application.

Abstract: The present disclosure provides a dual-band external antenna for an unmanned aerial vehicle (UAV) and a UAV. The dual-band external antenna for the UAV includes a substrate, a low-frequency oscillator region, a high-frequency oscillator region, a feed coaxial line and ground terminals. Two ground terminals are respectively electrically connected to a feed terminal of the feed coaxial line. An avoidance region for arranging the feed coaxial line is disposed in the low-frequency oscillator region or the high-frequency oscillator region. The low-frequency oscillator region includes a first low-frequency oscillator region and a second low-frequency oscillator region. The high-frequency oscillator region includes a first high-frequency oscillator region and a second high-frequency oscillator region that are vertically asymmetrically disposed on the front and back sides of the substrate.

Abstract: An unmanned aerial vehicle (UAV) includes a fuselage, a power driving unit, and an UAV arm. The UAV arm includes a cantilever, a mounting base, and a connecting portion. The mounting base is connected to a first end of the cantilever. The mounting base is configured for a power driving unit of the UAV to be mounted. The connecting portion is connected to a second end of the cantilever. The connecting portion is configured to be connected to the fuselage of the UAV. An upper end of a cross section of the cantilever is arc-shaped, and a lower end of the cross section of the cantilever is pointed. The cross section of the cantilever is a section perpendicular to a direction from the first end of the cantilever toward the second end of the cantilever.

Abstract: Embodiments of the present invention provide a method, an apparatus, a terminal, and a storage medium for elevation surrounding flight control. The method includes: obtaining surrounding parameter information of an unmanned aerial vehicle; determining, according to the surrounding parameter information, an elevation surrounding trajectory to be surrounded, where the elevation surrounding trajectory includes a plane with the point of interest as a center and the surrounding radius as a radius, and the plane where the elevation surrounding trajectory is located is perpendicular to a horizontal plane; controlling the unmanned aerial vehicle to fly along the elevation surrounding trajectory.

Abstract: The present disclosure provides an antenna, a wireless signal processing device, and an unmanned aerial vehicle. The antenna includes: a substrate having a first surface and a second surface opposite the first surface; a first radiator and a second radiator disposed on the first surface, the first radiator and the second radiator facing opposite each other, the first radiator being located at one end near a head of the substrate, and the second radiator being located at one end near a root of the substrate; a third radiator disposed on the second surface, the third radiator being mirror symmetric with a portion of a structure of the first radiator and conducting with the second radiator, so that the first radiator, the second radiator and the third radiator form a coupled resonance point; and a feed line connected with the first radiator, the second radiator and the third radiator.

Abstract: The embodiments are an aircraft time synchronization system and method. The system comprises: a first communication module and a second communication module, wherein data transmission is performed between the first communication module and the second communication module via a communication line, and an I/O interface of the first communication module is connected to the I/O interface of the second communication module via an interruption signal line; the first communication module sends the data information to the second communication module via the communication line, and at the same time sends the triggered interruption signal to the second communication module via the interruption signal line; the second communication module performs time synchronization with the first communication module based on the communication time difference and system time difference with the first communication module determined according to the receiving time of the data information and interruption signal and the sending time.

Abstract: An unmanned aerial vehicle (UAV) assembly includes an UAV and an UAV docking station. The UAV docking station includes a housing, an extension piece, and a door. The housing is provided with an accommodation cavity and a hatch communicating with the accommodation cavity. The extension piece comprises an extension cavity and is connected to the housing. The extension piece is disposed on a side portion of a housing end which is near the hatch, and the extension cavity communicates with the accommodation cavity. The door is connected to the housing and disposed at the hatch, and the door is configured to open or close the hatch. A cross-sectional area where the extension cavity communicates with the accommodation cavity is greater than a cross-sectional area of the accommodation cavity. The UAV can be accommodated in the accommodation cavity of the UAV docking station.

Abstract: An automatic obstacle avoidance method is applied to an unmanned aerial vehicle (UAV). The UAV includes at least one radar. The method includes: acquiring detected data of the radar; calculating theoretical state information of the detection target based on motion information of the UAV; excluding invalid data from the detected data using a Kalman filtering algorithm to obtain corrected data by combining the detected data with the theoretical state information; determining the height information of the UAV by correcting the detected data; and triggering an obstacle avoidance warning when the height information of the UAV is less than a pre-set height threshold value.

Abstract: A radar ranging method and a ranging radar are applied to an unmanned aerial vehicle. A first range to an obstacle is obtained using a first radar waveform. range. A second range to the obstacle are obtained using a second radar waveform if the first range is less than a preset switching threshold. the maximum detection range of the first radar waveform is greater than that of the second radar waveform; and a detection range resolution of the second radar waveform is higher than that of the first radar waveform.

Abstract: A module upgrade method and a module to be upgraded in an unmanned aerial vehicle (UAV) system are disclosed in embodiments of the present invention. The method includes: acquiring an upgrade file of the module to be upgraded; upgrading the module to be upgraded according to the upgrade file; judging whether the module to be upgraded is successfully upgraded; and if no, reacquiring an upgrade file of the module to be upgraded, and upgrading the module to be upgraded according to the re-acquired upgrade file until finishing upgrading the module to be upgraded. In this way, the upgrade success rate of the module to be upgraded can be improved by multiple upgrades, and the upgrade method is simple, convenient, easy to implement and high in reliability.

Abstract: Embodiments of the present application are a UAV foot stand and a UAV. The UAV foot stand includes a main body, a mounting board, and a support structure, where one end of the main body is provided with a lightening cavity, one end of the main body that is provided with the lightening cavity extends outward to form the mounting board, the support structure is fixed to the main body, and the support structure at least partially extends into the lightening cavity and is connected to an inner wall of the lightening cavity, so as to increase rigidity of the main body.

Abstract: A method for detecting landing of an unmanned aerial vehicle includes: acquiring a current ground clearance of each supporting vertical rod; acquiring a current height above ground of the unmanned aerial vehicle when receiving a landing instruction; determining whether a fuselage of the unmanned aerial vehicle is horizontal; when the fuselage of the unmanned aerial vehicle is horizontal, adjusting a length of the supporting vertical rod according to the current ground clearance of the supporting vertical rod to keep the fuselage horizontal when the unmanned aerial vehicle lands; and controlling the unmanned aerial vehicle to descend for landing.

Abstract: Embodiments of the present invention relate to a multi-thread exit method and a mobile terminal. The method is applicable to the mobile terminal. The method includes: obtaining an exit identifier and crash determination information of a thread; and destroying the thread according to the exit identifier and the crash determination information. In the method, an exit identifier and crash determination information of a thread are obtained, both the exit identifier and the crash determination information of the thread are determined, and different destruction modes are selected according to determination results to destroy the thread, thereby avoiding crash and congestion when a multi-thread exits and improving the stability of multi-thread exit.

Abstract: A joint calibration method is implemented in an unmanned aerial vehicle. In the method, pose information of a detection radar is obtained, and the pose information includes a ground height of the detection radar and a pitch angle of the detection radar. Target calibration parameters matching the pose information in a preset calibration parameter set are obtained. The calibration parameter set includes groups of calibration parameters, and each group of calibration parameters matching a pose information interval and the pose information interval includes a height interval and a pitch angle interval. A spatial conversion relationship between the detection radar and an image acquisition device is determined based on the target calibration parameters.

Abstract: Joint calibration methods implemented by an unmanned aerial vehicle and a server are disclosed. The server receives pose information of a detection radar from the unmanned aerial vehicle. The pose information includes a ground height and a pitch angle of the detection radar. The server determines target calibration parameters matching the pose information of the detection radar, and sends the target calibration parameters to the unmanned aerial vehicle. The unmanned aerial vehicle determines a spatial conversion relationship between the detection radar and an image acquisition device based on the target calibration parameters, and performs data fusion between the detection radar and the image acquisition device according to the spatial conversion relationship.

Abstract: Embodiments of the present invention relate to a dual-light image integration method, a dual-light image integration device and an unmanned aerial vehicle (UAV). The method includes: receiving first image data from a first image device and second image data from a second image device; separately storing the first image data and the second image data; combining the first image data and the second image data to composite third image data; and transmitting the third image data. According to the present invention, dual-light images are processed by using different data processing methods depending on subsequent operations, which can maintain synchronization of the dual-light images during image transmission while avoiding information loss during image storage, thereby well satisfying user needs.

Abstract: A remote control includes a body, a first rocker device, a second rocker device, a processor, and a signal transmission device. The first rocker device and the second rocker device are installed on the body. The processor connects to the first rocker device, the second rocker device, and the signal transmission device. The first rocker device includes a joystick component. The second rocker device includes a second joystick component. When the first joystick component moves in parallel relative to the body, the processor generates a remote control instruction used to control a movable object to move in a horizontal plane. When the second joystick component moves straightly relative to the body along a first direction or a second direction, the processor generates a remote control instruction used to control the movable object to move upward or move downward in a vertical direction of the movable object.

Abstract: A propeller, a propeller kit, a power assembly, a power kit and an unmanned aerial vehicle (UAV). The propeller includes a hub and at least two blades connected to the hub. The hub is detachably mounted on a corresponding drive apparatus by a mounting member corresponding to the hub, so that the propeller is mounted on the corresponding drive apparatus. A surface, facing the mounting member, of the hub is provided with a first fitting portion. A surface, facing the hub, of the mounting member is provided with a second fitting portion corresponding to the first fitting portion. The first fitting portion matches the second fitting portion. In the foregoing manner, a user can be prevented from incorrectly mounting a forward propeller and a counter-rotating propeller during the use of a quick-detachable propeller in the embodiments of the present application.