A convertible multi-mode vehicle capable of motorized travel in the air, on land, on water, and under water. The multi-mode vehicle is capable of controlled aerial flight, movement on the ground in terrestrial environments, on an aquatic surface, as well as underwater by changing between the different modes. Pivoting propulsion motors enable a convertible configuration from one vehicle locomotion mode to another.

The present disclosure provides various embodiments of a multicopter-assisted launch and retrieval system generally including: (1) a multi-rotor modular multicopter attachable to (and detachable from) a fixed-wing aircraft to facilitate launch of the fixed-wing aircraft into wing-borne flight; (2) a storage and launch system usable to store the modular multicopter and to facilitate launch of the fixed-wing aircraft into wing-borne flight; and (3) an anchor system usable (along with the multicopter and a flexible capture member) to retrieve the fixed-wing aircraft from wing-borne flight.

Disclosed is a system and method for calibrating a magnetometer. The method comprises responsive to a determination that a magnetic inclination is less than a threshold, measuring first magnetic field data by detecting a magnetic field with the magnetometer through a first rotation path, measuring second magnetic field data by detecting the magnetic field with the magnetometer through a second rotation path, and determining calibration values for the magnetometer based on the measured first magnetic field data and the measured second magnetic field data.

An aspect of the present disclosure relates to automated imaging of photovoltaic devices using an aerial vehicle (20). In one aspect, there is a method (440) for automated imaging of a PV array (310) using an aerial vehicle (20), the PV array (310) corresponding to target points (350) for the aerial vehicle (20). The method (440) comprises: positioning the aerial vehicle (20) at one of the target points (350) corresponding to the PV array (310); and controlling the aerial vehicle (20) for automated manoeuvre between the target points (350) to capture visual datasets of the PV array (310). The automated manoeuvre comprises: aligning a field-of-view (225) of a camera (222) of the aerial vehicle (20) to a PV array subsection of the PV array (310); determining a scanning direction (360) for moving the aerial vehicle (20) between the target points (350); and capturing, using the camera (222), the visual datasets of the PV array (310) starting from the PV array subsection as the aerial vehicle (20) moves along the scanning direction (360) between the target points (350).

An aerial vehicle may include a fuselage; and one or more propellers coupled to the fuselage, wherein the aerial vehicle may have at least a taking off or landing state and a cruise state. In response to the aerial vehicle being in the taking off or landing state, an angle between a longitudinal axis of the fuselage and a horizontal plane may be within a first angular range and in response to the aerial vehicle being in the cruise state, an angle between the longitudinal axis of the fuselage and the horizontal plane may be within a second angular range. A maximum value of the second angular range may be less than a minimum value of the first angular range. In response to the aerial vehicle switching between the takeoff or landing state and the cruise state, the fuselage and the propellers may tilt as a whole.

Disclosed is a system and method for calibrating a magnetometer of a compass. With a global navigation satellite system receiver, a current position is determined. The determined position is used to determine a magnetic inclination (e.g., by a global magnetic field model such as the World Magnetic Model). The calibration system may perform different calibration sequences based on the magnetic inclination. In a first calibration sequence, performed responsive to a determination that a magnetic inclination (or the absolute value of the magnetic inclination) is less than a threshold, magnetic field data is measured by the magnetometer as it is rotated through horizontal rotation paths. If the magnetic inclination is greater than the threshold, magnetic field data is measured by the magnetometer as it is rotated through vertical rotation paths. The measured magnetic field data may be used to determine calibration values for the magnetometer compass.

The present disclosure discloses an unmanned aerial vehicle (UAV), comprising a housing having a top part and a bottom part, a plurality of arms arranged on the top part, a battery unit arranged within the housing, a processor arranged within the housing, a launching unit having a slide bar and a driving component, and a supporting component arranged on the housing to support the slide bar. One end the slide bar is rotatably connected to a pivot. The other end of the slide bar is slidably connected to the supporting component. The driving component is to actuate one of the slide bar and the supporting component to separate the slide bar from the supporting component. The slide bar is to rotate about the pivot after separating from the supporting component. An UAV readily configured for fishing can be provided by embodiments of the present disclosure.

A propulsor brake lock system includes an aircraft propulsor, a reduction gear assembly, a brake shaft, and a brake assembly. The aircraft propulsor includes a propeller having a propeller input shaft coupled thereto. The reduction gear assembly includes at least an input gear and an output gear. The input gear and output gear are both rotatable with the propeller input shaft. The brake shaft is coupled to, and is rotatable with, the output gear. The brake assembly is coupled to the brake shaft and is moveable between a disengaged position, in which the brake shaft may rotate whenever the output gear rotates, and an engaged position, in which the brake shaft is prevented from rotating, thereby preventing rotation of the output gear, the input gear, and the propeller input shaft.

The present invention relates to a drone having a movable propeller shaft, the drone comprising: a drone body having an opening formed thereon; a plurality of propeller shafts arranged radially on the drone body, each propeller shaft having one side portion passing through the opening of the drone body to be disposed inside the drone body and a propeller housing equipped with a propeller and a propeller motor; adjustment means disposed on the drone body, linked to the plurality of propeller shafts, respectively, and configured to adjust the respective angles and heights of the plurality of propeller shafts; a sensor for sensing a rotation angle of each of the plurality of propeller shafts; and a motor driver connected to each propeller, a current check circuit for determining whether current flow is normal, an MCU for transmitting and receiving signals in connection with the current check circuit and transmitting signals to the motor driver, and a main controller connected to the MCU through a wireless communication method.

The present invention relates to a drone having a movable propeller shaft, the drone comprising: a drone body having an opening formed thereon; a plurality of propeller shafts arranged radially on the drone body, each propeller shaft having one side portion passing through the opening of the drone body to be disposed inside the drone body and a propeller housing equipped with a propeller and a propeller motor; adjustment means disposed on the drone body, linked to the plurality of propeller shafts, respectively, and configured to adjust the respective angles and heights of the plurality of propeller shafts; a sensor for sensing a rotation angle of each of the plurality of propeller shafts; and a motor driver connected to each propeller, a current check circuit for determining whether current flow is normal, an MCU for transmitting and receiving signals in connection with the current check circuit and transmitting signals to the motor driver, and a main controller connected to the MCU through a wireless communication method.