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: 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 remote control apparatus includes: a main controller, a wireless transmission chip, a gyroscope chip and an operating device; wherein the wireless transmission chip is electrically connected with the main controller; the gyroscope chip is electrically connected with the main controller; the operating device is electrically connected with the main controller. The gyroscope chip is used for detecting an inclination angle of the remote control apparatus relative to a horizontal plane, and sending a first electric signal representing a positioning status of the remote control apparatus to the main controller. The main controller is used for detecting an input level when the operating device is operated by an operator, and sending a second electric signal representing a movement direction instructed by the operating device to the wireless transmission chip. The wireless transmission chip transmits the second electric signal to an external device.

Abstract: A fixed-wing aircraft and flight control method and system thereof are provided. The flight control method includes steps of: setting a landing site of the fixed-wing aircraft; calculating a landing runway which starts from a runway origin and ends at the landing site and is formed by alternately connecting horizontal runways with inclined runways, wherein a horizontal distance between the runway origin and the landing site is determined according to a type of the fixed-wing aircraft, and a descent rate coefficient of the inclined runways varies with a horizontal length of the inclined runways; obtaining a current location of the fixed-wing aircraft and calculating a return route which starts from the current location of the fixed-wing aircraft and ends at the runway origin; and forming a return flight line by combining the return route with the landing runway.

Abstract: Provided are a geo-location or navigation camera, and an aircraft and a navigation method therefor. The geo-location or navigation camera comprises an image capturing apparatus (15), an image capturing direction of the image capturing apparatus (15) being vertically downward. The camera further comprises a gimbal stability-enhancement system comprising a gimbal body and a gimbal control system connected to the gimbal body. The image capturing apparatus (15) is arranged on the gimbal body. By means of the balance control and shock absorption effects of the gimbal stability-enhancement system, the stability of the image capturing apparatus (15) is better, and the image capturing direction of the image capturing apparatus (15) is maintained to be always vertically downward. The aircraft can still be navigated without a GPS. The method has advantages of being highly accurate and widely applicable.

Abstract: A gimbal handheld holder includes two support legs and a control device. A transverse rod is located between the two support legs. A handle is located on the transverse rod. A gimbal connector is located at a junction of the handle with the transverse rod. The gimbal handheld holder is connected with a gimbal through the gimbal connector. The gimbal is located below the transverse rod and between the two support legs. The handle is located on the transverse rod. The control device controls the gimbal to move. The gimbal handheld holder is able to achieve force balance at two ends thereof, and steadily hold the gimbal below the transverse rod. While being connected with the gimbal, the gimbal handheld holder is able to be directly steadily placed on ground.

Abstract: A remote control device for an aircraft and an aircraft system are provided. The aircraft system includes the aircraft and the remote control device. The remote control device includes a first global positioning system (GPS) chip, a magnetometer, a gyroscope chip, a main control chip and a first signal transceiver. The first GPS chip, the magnetometer and the gyroscope chip are respectively connected with the main control chip, and the first signal transceiver is connected with the main control chip. The first GPS chip, the magnetometer and the gyroscope chip transmit three different position signals of the remote control device to the main control chip respectively; the main control chip transmits a control signal through the first signal transceiver, and the first signal transceiver receives a condition signal of the aircraft and then transmits to the main control chip.

Abstract: A gimbal includes a housing (1). A gyroscope board (4), a camera (21), and a camera main control board (22) electrically connected with the camera are disposed in the housing. A Wi-Fi circuit board (31) and a Wi-Fi antenna (33) are also disposed in the housing. The Wi-Fi circuit board is electrically connected with the camera main control board. The camera is fixed on the housing. The gimbal achieves the independent Wi-Fi transmission, so that the structure is simplified.

Abstract: An aircraft system (1) includes an aircraft apparatus (31) including an image capturing device (33) and a remote control (32). The remote control (32) includes a display (321), a first communication circuit (322) adapted for transmitting aircraft control signals to the aircraft apparatus (31), and a second communication circuit (323) adapted for receiving image signals of the image capturing device. The display (321) is adapted for displaying the image signals.

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: Provided are a geo-location or navigation camera, and an aircraft and a navigation method therefor. The geo-location or navigation camera comprises an image capturing apparatus (15), an image capturing direction of the image capturing apparatus (15) being vertically downward. The camera further comprises a gimbal stability-enhancement system comprising a gimbal body and a gimbal control system connected to the gimbal body. The image capturing apparatus (15) is arranged on the gimbal body. By means of the balance control and shock absorption effects of the gimbal stability-enhancement system, the stability of the image capturing apparatus (15) is better, and the image capturing direction of the image capturing apparatus (15) is maintained to be always vertically downward. The aircraft can still be navigated without a GPS. The method has advantages of being highly accurate and widely applicable.

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: An aircraft and a roll method thereof. The aircraft comprises 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: A battery case includes a bottom plate part and two side plate parts extending oppositely from the bottom plate part, wherein each of the side plate parts has at least one opening, in which an elastic element is arranged. An electric skateboard includes a bearing deck, wheels mounted on both ends of the bearing deck, an electric motor mounted under the bearing deck, and said battery case which is mounted under the bearing deck. The side plate parts of the battery case have openings in which elastic elements are arranged. Therefore, when pressure is exerted by the bearing deck to the battery case, the opening of the battery case is able to squeeze the elastic element so that the battery case can undergo an elastic deformation easily.