The invention refers to a VTOL aircraft of the type that uses certain aerodynamic phenomena to increase the lifting force and to reduce the thrust/weight ratio. An aircraft 1 uses a propulsion system 2 consisting of four thrust producing elements, two in front 3 and two in rear 4. Each front thrust producing element 3 contains at least one front rotor 5 operated by at least one front electric motor, fixed on a fuselage 10. Each rear thrust producing element 4 contains at least one rear rotor 7 driven by at least a rear electric motor 8, fixed on the fuselage 10. On the fuselage 10 is attached symmetrically a front wing 12. On the fuselage 10 is attached symmetrically a rear wing 13. The wing 12 and 13 are used also in static conditions respectively in take-off and landing.

A method includes determining a threshold capacity associated with at least a first unmanned aerial vehicle (UAV) and a second UAV. The method includes initially setting a target charge voltage of a first battery of the first UAV to less than a full charge voltage to limit a state of charge of the first battery based on the threshold capacity. The method includes, over a lifetime of the first battery of the first UAV, periodically comparing a full charge capacity of the first battery to the threshold capacity. The method includes, based on the comparing, periodically adjusting the target charge voltage of the first battery, such that, as the full charge capacity of the first battery decreases with age, the target charge voltage increases towards the full charge voltage of the first battery.

A fire suppression system has a unique combination of components that includes interoperable electric-powered vehicles, facilities, hardware and software along with their range of specifications, standards, processes, capabilities and concepts of operations that comprise a concerted, multi-modal, system for delivering fire-retardant onto fires by uniquely-capable, ultra-quiet, electrically-powered, autonomous robotic aircraft (“SkyQarts”) that fly precise trajectories and perform extremely short take-offs and landings (ESTOL) at a highly-distributed network of small facilities (“SkyNests”) that have standardized compatible facilities, as defined herein, that interoperate with SkyQarts as well as with versatile, autonomous robotic electric-powered payload carts and electric-powered autonomous robotic delivery carts to provide safe, fast, on-demand, community-acceptable, environmentally friendly, high-capacity, sustained, affordable, day or night delivery of fire-retardant, even in smokey, IFR conditions to wildfires or controlled burns in urban, suburban, wildlands and rural settings in both developed and undeveloped countries across the globe.

A fire suppression system has a unique combination of components that includes interoperable electric-powered vehicles, facilities, hardware and software along with their range of specifications, standards, processes, capabilities and concepts of operations that comprise a concerted, multi-modal, system for delivering fire-retardant onto fires by uniquely-capable, ultra-quiet, electrically-powered, autonomous robotic aircraft (“SkyQarts”) that fly precise trajectories and perform extremely short take-offs and landings (ESTOL) at a highly-distributed network of small facilities (“SkyNests”) that have standardized compatible facilities, as defined herein, that interoperate with SkyQarts as well as with versatile, autonomous robotic electric-powered payload carts and electric-powered autonomous robotic delivery carts to provide safe, fast, on-demand, community-acceptable, environmentally friendly, high-capacity, sustained, affordable, day or night delivery of fire-retardant, even in smokey, IFR conditions to wildfires or controlled burns in urban, suburban, wildlands and rural settings in both developed and undeveloped countries across the globe.

An air vehicle has an airframe, aerodynamic lift-generating wings, and a propulsion system. The propulsion system provides propulsion to the air vehicle in powered aerodynamic flight mode and in vectored flight mode, and stability and control in vectored flight mode. The propulsion system includes a first set of non-pivotable first propulsion units, arranged in polygonal arrangement with respect to the airframe, enclosing the air vehicle center of gravity, providing a fixed vertical thrust vector and an aggregate vertical thrust sufficient for enabling vectored flight mode. The propulsion system includes a second set of pivotable second propulsion units, arranged in spaced relationship with respect to the center of gravity, and provide vectored control moments to the air vehicle in three rotational degrees of freedom. The second propulsion units enable angular displacement of the respective thrust vectors at least between a respective vertical position and a respective horizontal position, and provide at least an aggregate horizontal thrust sufficient for providing powered aerodynamic flight mode.

An air vehicle has an airframe, aerodynamic lift-generating wings, and a propulsion system. The propulsion system provides propulsion to the air vehicle in powered aerodynamic flight mode and in vectored flight mode, and stability and control in vectored flight mode. The propulsion system includes a first set of non-pivotable first propulsion units, arranged in polygonal arrangement with respect to the airframe, enclosing the air vehicle center of gravity, providing a fixed vertical thrust vector and an aggregate vertical thrust sufficient for enabling vectored flight mode. The propulsion system includes a second set of pivotable second propulsion units, arranged in spaced relationship with respect to the center of gravity, and provide vectored control moments to the air vehicle in three rotational degrees of freedom. The second propulsion units enable angular displacement of the respective thrust vectors at least between a respective vertical position and a respective horizontal position, and provide at least an aggregate horizontal thrust sufficient for providing powered aerodynamic flight mode.

The present disclosure relates to a reconfigurable battery system and method of operating the same. An example apparatus includes at least one memory, instructions in the apparatus, and processor circuitry to execute the instructions to determine a state of charge of a battery, determine a closed circuit voltage of the battery, determine a value of a parameter based on a ratio of the state of charge and the closed circuit voltage, and control a switch coupled to the battery based on the value of the parameter, the controlling of the switch to either cause the battery to be coupled to a battery string or cause the battery to be disconnected from the battery string.

Embodiments of a system and method for carrying an aeronautical or launch vehicle to altitude for release to flight are disclosed. The system may comprise a multiplicity of mounting elements configured to be affixed to a carrier aircraft in distributed fashion along a mounting axis. Each mounting element may include a cradle and a retention strap. Each retention strap may be suspendedly attached to a respective said cradle, and actuatable from a retention configuration to a release configuration. The retention configuration may enable the retention straps to clampingly secure the vehicle to the respective cradles. The actuation of the retention straps from the retention configuration to the release configuration may disable the clamping securement and thereby release the vehicle to drop away from the cradles. For one or more of the retention straps, the actuation may be by way of detonating at least one corresponding pyrotechnic fastener.

A long-distance drone is disclosed having a canard wing configuration with a cabin attached to a left main wing and a right main wing. There is a left forewing and a right forewing connected together to form a single-piece forewing. There is a left linear support connecting the left forewing to the left main wing, and a right linear support connecting the right forewing to the right main wing. A plurality of propellers is disposed on the left and the right linear supports.

A long-distance drone is disclosed having a canard wing configuration with a cabin attached to a left main wing and a right main wing. There is a left forewing and a right forewing connected together to form a single-piece forewing. There is a left linear support connecting the left forewing to the left main wing, and a right linear support connecting the right forewing to the right main wing. A plurality of propellers is disposed on the left and the right linear supports.