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.

Sounds are generated by an aerial vehicle during operation. For example, the motors and propellers of an aerial vehicle generate sounds during operation. Systems, methods, and apparatus may actively adjust the position and/or configuration of one or more propeller blades of a propulsion mechanism to generate different sounds and/or lifting forces from the propulsion mechanism.

An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has a protrusion extending upwardly from a central vertical axis. The protrusion provides an initial instability to begin a self-righting process when the aeronautical vehicle is inverted on a surface. A propulsion system, such as rotor driven by a motor can be mounted in a central void of the self-righting frame assembly and oriented to provide a lifting force. A power supply is mounted in the central void of the self-righting frame assembly and operationally connected to the at least one rotor for rotatably powering the rotor. An electronics assembly is also mounted in the central void of the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a surface.

A rotorcraft has a frame and a plurality of rotors connected to the frame. The frame has a roll axis and a pitch axis. Each of the rotors includes a rotor shaft. The rotor shaft of each of the rotors is canted with respect to at least one of the roll axis and the pitch axis. The rotor shaft of each of the rotors may be canted between 3 and 15 degrees. Each of the rotors may be a co-axial co-rotating rotor. The rotors may be oriented in opposing pairs across the frame. Both rotors in each opposing pair rotate in the same direction. The rotorcraft may include at least two additional rotors, each having a forward cant. Each of the additional rotors may be a co-axial contra-rotating rotor.

Sounds are generated by an aerial vehicle during operation. For example, the motors and propellers of an aerial vehicle generate sounds during operation. Systems, methods, and apparatus may actively adjust the position and/or configuration of one or more propeller blades of a propulsion mechanism to generate different sounds and/or lifting forces from the propulsion mechanism.

This disclosure provides a monitoring system, a base station, and a control method of drones. The drone includes a battery that supplies electric power for the drone and that connects with a charging connector. The base station includes a charging device, and the charging device includes a power supply connector, a power supply, and a power controller. The power supply connector is used for connecting to the charging connector. The power supply provides electric power. The power controller is coupled to the power supply and the power supply connector. The power controller is used to determine the battery specification of the battery and charge the battery from the power supply according to the battery specification. Thereby, the charging efficiency can be improved and the charging abnormality can be avoided.

PROBLEM: To provide a chemical spraying drone (unmanned air vehicle) in which minimizes chemical drift outside the field by a simple structure without additional equipment and complicated control.

SOLUTION: To provide a chemical spraying drone that actively uses the air flow made by rotors for spraying, comprising chemical spray nozzles and rotors (preferably two-stage rotors), wherein the chemical spray nozzles are positioned under the rotors and under a circular area with its center at a point offset by a predetermined distance rearward with respect to the flying direction from the rotor's rotation axis, its radius 90 percent of the radius of the rotor blade, on a straight line with a depression angle of about 60 degrees rearward from the horizontal line passing through the rotor's rotation axis. The position of the chemical spray nozzles may be dynamically adjusted.

A system for stabilizing a payload, comprising: a platform mount having a first end adapted to be physically connected to a supporting platform and a second end; a payload mount adapted to be physically connected to a payload, and is physically and rotatably connected via at least one pivot axis to the second end of the platform mount; at least one sensor adapted for measuring angular orientation of the payload along the at least one pivot axis; at least one propulsion device connected to the payload mount, and angled to change an angular position of the payload mount along the at least one pivot axis; and a stabilizing controller adapted for receiving outputs of the at least one sensor, calculating instructions for the at least one propulsion device, and forwarding the instructions to the at least one propulsion device.

A motor assembly including a housing, a first rotor (R1, R1) and a second rotor (R2, R2) provided in the housing. The first rotor (R1, R1) is configured to drive a first output shaft, and the second rotor is configured to drive a second output shaft.

A propulsion system (50) is disclosed. The propulsion system (50) includes a first propeller (52), a second propeller (54), and a third propeller (56). The first propeller (52), the second propeller (54), and the third propeller (56) are arranged to rotate about a common axis and the second propeller (54) is disposed between the first propeller (52) and the third propeller (56). The first and third propellers (52, 56) are configured to rotate about the common axis in a first direction (A) and the second propeller (54) is configured to rotate about the common axis in a second direction (B) opposite to the first direction (A). A first motor (60) may be coupled to the first and third propellers (52, 56) and a second motor (64) may be coupled to the second propeller (54). A first shaft (58) and second shaft (62) may be arranged along the common axis, wherein the first and third propellers (52, 56) are coupled to the first shaft (58) and the second propeller (54) is coupled to the second shaft (62).