An unmanned aerial vehicle according to certain embodiments generally includes a chassis, a power supply mounted to the chassis, a control system operable to receive power from the power supply, at least one rotor operable to generate lift under control of the control system, and a motor operable to lower a free end of a line. The free end of the line is operable to engage a parcel to be delivered by the unmanned aerial vehicle. The control system is configured to operate the motor to cause the free end of the line to accelerate toward a delivery surface as the free end of the line passes through a first portion of a distance between the unmanned aerial vehicle and the delivery surface, and to decelerate as the free end of the line passes through a lower portion of the distance.

The present disclosure relates to an aircraft. The aircraft has a primary structural element, which extends along a main axis of the aircraft, and at least one monolithic structural component, which is produced by a three-dimensional printing method. The aircraft also has an aircraft system for carrying out an aircraft-specific function. The at least one monolithic structural component is fixed on the primary structural element by a fixing device, system, means, or mechanism. The monolithic structural component is embodied to accommodate the aircraft system. The disclosure also relates to a method for producing an aircraft.

The present disclosure relates to a reconfigurable battery system and method of operating the same. The reconfigurable battery system comprising a plurality of switchable battery modules, a battery supervisory circuit, and a battery pack controller, where the plurality of switchable battery modules electrically arranged in series to define a battery string defining an output voltage. The battery pack controller operable to connect the battery string to the external bus via a pre-charge switch to perform a pre-charge cycle.

An aerial vehicle may include adjustable shrouds to selectively provide protection for propellers of the aerial vehicle. The adjustable shrouds may be moved to an extended configuration around a periphery of one or more propellers during generally vertical flight or hovering operations, when delivery a payload, and/or upon detecting objects in proximity. Likewise, the adjustable shrouds may be moved to a retracted configuration that eliminates or minimizes adverse aerodynamic effects during generally horizontal flight operations, when operating at high altitude, and/or upon detecting no objects in proximity. The adjustable shrouds may include various designs, such as fan shrouds, telescoping shrouds, folding shrouds, and deployable arm shrouds.

A fixed-wing aerial underwater vehicle includes a shell component, a flight component and a pneumatic buoyancy component. The flight component includes a fixed wing and rotors, and the fixed wing and the rotors are mounted in the shell component. The pneumatic buoyancy component includes an air bladder and an inflation and deflation portion, and the inflation and deflation portion can inflate and deflate the air bladder. The air bladder is installed on the shell component, a containing space is formed in the shell component, and the inflation and deflation portion is partially or entirely installed in the containing space. Each rotor includes a rotor supporting rod, a motor base, a motor and a propeller, which are sequentially connected. A control method for the fixed-wing aerial underwater vehicle mentioned above is further provided.

A rotor unit is disclosed. The rotor unit includes a hub and a stacked rotor blade. The hub is configured to rotate about an axis in a first rotation direction. The stacked rotor blade is rotatable about the axis and further includes a first blade element and a second blade element. The first blade element has a first leading edge and the second blade element has a second leading edge. The blade elements are arranged in a stacked configuration. A leading edge of the stacked rotor blade is formed by at least a portion of the first leading edge of the first blade element as well as at least as portion of the second leading edge of the second blade element. In some embodiments, the rotor unit is coupled to an unmanned aerial vehicle.

A paradrone includes a canopy having a parafoil, a transverse canopy frame coupled to the parafoil to support the parafoil, a longitudinal canopy frame that is coupled to the parafoil while having a bent structure such that the parafoil generates a lift, and at least one parafoil connecting portion for connecting at least one canopy frame among the transverse canopy frame and the longitudinal canopy frame to the parafoil. The paradrone also includes a servomotor portion having a servomotor body and a servomotor arm for coupling and fixing intersecting parts of the transverse canopy frame and the longitudinal canopy frame. The servomotor arm is connected to a servomotor body and rotated in a predetermined direction by driving of the servomotor body to change the angle between the travelling direction of the paradrone fuselage and the transverse and longitudinal canopy frames, thereby changing the angle of attack.

The present disclosure provides an unmanned aerial vehicle (UAV). The UAV includes a main body; an inertial measurement unit (IMU) disposed in the main body; a mounting bracket for fixing the IMU; and a circuit board fixedly disposed at the main body and integrated with a plurality of functional modules. The IMU is fixed on the circuit board through the mounting bracket.

An agricultural unmanned aerial vehicle (UAV) is provided. The UAV includes a central frame, a control circuit, a left arm group, a right arm group and a spraying system. The left and right arm groups each includes a front arm assembly including a second rotor assembly, a rear arm assembly including a third rotor assembly, and a middle arm assembly including a first rotor assembly. In an output direction of downwash flow fields of the left and right arm groups, a height of a rotation plane of the first rotor assembly is lower than heights of rotation planes of the second and third rotor assemblies. The spraying system includes nozzle assemblies. The control circuit is configured to control the left and right arm groups to adjust flight attitude of the UAV. The left and right arm groups output the downwash flow fields in a direction towards the nozzle assemblies.

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.