A system-on-module (SOM) for controlling an unmanned vehicle (UV) is provided. The SOM comprises a circuit board, a first processing system in operative communication with the circuit board, and a second processing system in operative communication with the circuit board. The first processing system includes one or more first processing units and a volatile programmable logic array. The first processing system is configured to execute a first process for the UV. The second processing system includes one or more second processing units and a non-volatile programmable logic array. The second processing system is configured to monitor execution of the first process by the first processing system.

A mobile electronic device according to an aspect is connected to a flight device. The mobile electronic device includes a communication unit that communicates with the flight device, and a controller that executes a predetermined function. When connected to the flight device, the controller changes the predetermined function when a predetermined condition is satisfied.

Unmanned aerial vehicle (UAV) mount with a base station, also known as Flying Base Station (FBS) has garnered considerable attention for 5G and beyond communication. This invention provides a method and system for deploying a swarm of FBSs over a geographical region autonomously. The proposed 3-D deployment technique exhibit how to place a minimum number of FBSs energy efficiently over a region to offer guaranteed QoS without inter-UAV interference and UAV capacity limit violations. A Master-Slave coordination technique is revealed to maintain inter-FBS synchronization to avoid collisions during the transition. The technique for selecting intermediate hop coordinates is proclaimed under path planning.

Unmanned aerial vehicle (UAV) mount with a base station, also known as Flying Base Station (FBS) has garnered considerable attention for 5G and beyond communication. This invention provides a method and system for deploying a swarm of FBSs over a geographical region autonomously. The proposed 3-D deployment technique exhibit how to place a minimum number of FBSs energy efficiently over a region to offer guaranteed QoS without inter-UAV interference and UAV capacity limit violations. A Master-Slave coordination technique is revealed to maintain inter-FBS synchronization to avoid collisions during the transition. The technique for selecting intermediate hop coordinates is proclaimed under path planning.

A flying vehicle with a fuselage having a longitudinal axis, a cockpit extending substantially from the center of the fuselage, a left front wing extending from the fuselage, a right front wing extending from the fuselage, a left rear wing extending from the fuselage, a right rear wing extending from the fuselage. Each wing contains a rotor rotatably mounted and a direct drive brushless motor providing directional control of the vehicle. A centrally located ducted fan encompasses the cockpit and provides VTOL capabilities. The central location of the cockpit and central ducted fan aid in balance and stability. The central ducted fan is itself a brushless motor with the stator windings encapsulated in the ducted fan housing and rotor magnets within the fan. All motors and rotatable mounts are controlled by a fly-by-wire system integrated into a central computer with avionics allowing for autonomous flight.

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.

Disclosed is an aerial vehicle. The aerial vehicle may include a removable battery. Various embodiments of removable battery assemblies include a pull-bar battery assembly, a latch battery assembly, and a lever battery assembly. The aerial vehicle may also include a propeller locking mechanism to which propellers may be removably coupled. The propeller locking mechanism may obviate the need for tools for coupling or decoupling propellers to the aerial vehicle. Vents in the arm of the aerial vehicle may provide an air pathway, providing convective cooling for the electronics aerial vehicle.

A system-on-module (SOM) for controlling an unmanned vehicle (UV) is provided. The SOM comprises a circuit board, a first processing system in operative communication with the circuit board, and a second processing system in operative communication with the circuit board. The first processing system includes one or more first processing units and a volatile programmable logic array. The first processing system is configured to execute a first process for the UV. The second processing system includes one or more second processing units and a non-volatile programmable logic array. The second processing system is configured to monitor execution of the first process by the first processing system.

A collapsible flying device is provided having a housing including first and second housing sections forming an enclosure, and a motorized assembly that includes a drive motor and a drive shaft driven by the drive motor. The drive shaft matingly receives the first housing section and is coupled to the second housing section, wherein operation of the drive motor drives the drive shaft to move the first housing section from a closed position adjacent the second housing section to an open position spaced from the second housing section. A rotor hub is rotatingly driven by the drive motor. At least two rotor blades are coupled thereto and positioned within the enclosure in a collapsed position when the first housing section is in the closed position, and extend beyond the enclosure in an expanded position when the first housing section is in the open position.

Aerial vehicles may be outfitted with one or more ultrasonic anemometers, each having ultrasonic transducers embedded into external surfaces. The transducers may be aligned and configured to transmit acoustic signals to one another, and receive acoustic signals from one another, along one or more paths or axes. Elapsed times of signals transmitted and received by pairs of transducers may be used to determine air speeds along the paths or axes. Where two or more pairs of transducers are provided, a net vector may be derived based on air speeds determined along the paths or axes between the pairs of the transducers, and used to generate control signals for maintaining the aerial vehicle on a desired course, at a desired speed or altitude, or in a desired orientation. The transducers may be dedicated for use in an anemometer, or may serve multiple purposes, and may be reoriented or reconfigured as necessary.