Drones convertible into personal computers are disclosed, A disclosed unmanned aerial vehicle (UAV) includes a body and rotors carried by the body. The rotors move relative to the body from a first position when the UAV is in a drone mode to a second position when the UAV is in a computer mode.

The present disclosure presents various embodiments of a system for retrieving a fixed-wing aircraft from free flight using a flexible capture member. The system includes a GPS reference sensor and a communication link to guide the fixed-wing aircraft to intercept the flexible capture member.

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 operably coupled to the battery supervisory circuit to selectively switch, for each of the plurality of switchable battery modules, the battery switch between the first position and the second position based at least in part on the one or more parameters of the battery and in accordance with a predetermined switching routine.

A system comprising an unmanned aerial vehicle (UAV) configured to transition from a terminal homing mode to a target search mode, responsive to an uplink signal and/or an autonomous determination of scene change.

A vehicle can be configured to include a body having a body bottom conjoined with a body sidewall and a body top forming a body cavity. The body top includes a body top opening and the body sidewall includes a body sidewall opening. The vehicle can include a payload housing having a payload bottom conjoined with a payload housing sidewall and a payload housing top forming a payload housing cavity, wherein the payload housing cavity is configured to hold at least one operating module for the vehicle. The vehicle can include at least one arm. The vehicle can include at least one interlocking arrangement of the body top opening or body side wall configured to removably secure the payload housing and the at least one arm to the body. Each of the body, the payload housing, and the at least one arm can be structured with additive manufactured material.

Devices and systems of the inventive concept provide a durable, all-weather manned or unmanned aircraft that is capable of vertical flight and provides improved stability upon payload launch or delivery. The payload bay is positioned along the central axis of the aircraft and proximal to the aircraft's center of gravity. Control and fuel systems are positioned fore and aft of the payload bay, respectively. The payload bay is configured to store and deliver a wide variety of payload types. The aircraft also includes features that reduce vibration, prolong the interval between necessary maintenance, and permit all-weather operation.

Embodiments of the present disclosure relate to a UAV comprising a fuselage, a rotor, and a patch antenna element. The patch antenna element, which is provided from a patch antenna stack-up, is conformally disposed on an outer surface of the UAV's fuselage. The patch antenna comprises a first substrate, patch conductor, intermediate substrate, bottom substrate, and ground plane. The patch conductor is disposed on a top surface of the first substrate. A first surface of the intermediate substrate, which is a magneto-dielectric material, is disposed on a bottom surface of the first substrate. A top surface of the bottom substrate is disposed on a second surface of the intermediate substrate. A ground plane conductor is disposed on a bottom surface of the bottom substrate.

An electronic speed controller includes an output circuit and one or more processors. The output circuit is configured to control currents to a plurality of motors of an unmanned aerial vehicle (UAV). The motors are configured to drive the UAV. The one or more processors are configured to, individually or collectively, determine an operating state of a first motor of the plurality of motors, collect power from the first motor in response to the operating state of the first motor is a decelerating state, and distribute at least a portion of the power collected from the first motor to a second motor of the plurality of motors.

A method for controlling an unmanned aerial vehicle within a flight operating space. The unmanned aerial vehicle includes one or more sensor arrays on each spar. The method includes determining, using a plurality of sensor arrays, a flight path for the unmanned aerial vehicle. The method also includes receiving, by at least one sensor array of the plurality of sensor arrays, sensor data identifying at least one object in the operating space. The sensor data is transmitted over a communications bus connecting components of the UAV. The method further includes determining, by one or more processors onboard the unmanned aerial vehicle, a flight path around the at least one object. The method also includes generating, by the one or more onboard processors, a first signal to cause the unmanned aerial vehicle to navigate within the operating space around the at least one object.

Systems, devices, and methods for a vertical take-off and landing (VTOL) aerial vehicle having a first GPS antenna and a second GPS antenna, where the second GPS antenna is disposed distal from the first GPS antenna; and an aerial vehicle flight controller, where the flight controller is configured to: utilize a GPS antenna signal via the GPS antenna switch from the first GPS antenna or the second GPS antenna; receive a pitch level of the aerial vehicle from the one or more aerial vehicle sensors in vertical flight or horizontal flight; determine if the received pitch level is at a set rotation from vertical or horizontal; and utilize the GPS signal not being utilized via the GPS antenna switch if the determined pitch level is at or above the set rotation.