An aircraft that closely integrates thrust and aerodynamics to achieve VTOL flight, forward flight, and smooth transitions from VTOL to forward flight. The invention combines a Box wing, Ducted Rotors and movable Flaperons for VTOL and sustained forward flight of an aircraft. In forward flight, the concept uses a plurality of fixed Ducted Rotors to not only provide thrust, but also enhance dynamic lift and controllability by interacting closely with the two fixed primary lifting bodies of each ducted wing section. In VTOL flight and transitioning to forward flight, the Ducted Rotors direct air through movable Flaperons attached to the trailing end of the ducted wings, providing smooth power, controllability, and aircraft orientation throughout transition. Throughout all phases of flight, differential actuation of Ducted Rotors and Flaperons provide control.

UAV configurations and battery augmentation for UAV internal combustion engines, and associated systems and methods are disclosed. A representative configuration includes a fuselage, first and second wings coupled to and pivotable relative to the fuselage, and a plurality of lift rotors carried by the fuselage. A representative battery augmentation arrangement includes a DC-powered motor, an electronic speed controller, and a genset subsystem coupled to the electronic speed controller. The genset subsystem can include a battery set, an alternator, and a motor-gen controller having a phase control circuit configurable to rectify multiphase AC output from the alternator to produce rectified DC feed to the DC-powered motor. The motor-gen controller is configurable to draw DC power from the battery set to produce the rectified DC feed.

UAV configurations and battery augmentation for UAV internal combustion engines, and associated systems and methods are disclosed. A representative configuration includes a fuselage, first and second wings coupled to and pivotable relative to the fuselage, and a plurality of lift rotors carried by the fuselage. A representative battery augmentation arrangement includes a DC-powered motor, an electronic speed controller, and a genset subsystem coupled to the electronic speed controller. The genset subsystem can include a battery set, an alternator, and a motor-gen controller having a phase control circuit configurable to rectify multiphase AC output from the alternator to produce rectified DC feed to the DC-powered motor. The motor-gen controller is configurable to draw DC power from the battery set to produce the rectified DC feed.

A stowable lift rotor is coupled to an airframe of a VTOL aircraft. The VTOL aircraft is convertible between a VTOL flight mode and a forward flight mode. The stowable lift rotor includes a lift arm. The proximal end of the lift arm is coupled to the airframe of the VTOL aircraft. The stowable lift rotor also includes a rotor assembly including rotor blades coupled to the distal end of the lift arm. The lift arm is movable between various positions including an extended position in the VTOL flight mode, a stowed position in the forward flight mode and intermediate positions therebetween such that the distance between the rotor assembly and the airframe is greater in the extended position than in the stowed position.

A stowable lift rotor is coupled to an airframe of a VTOL aircraft. The VTOL aircraft is convertible between a VTOL flight mode and a forward flight mode. The stowable lift rotor includes a lift arm. The proximal end of the lift arm is coupled to the airframe of the VTOL aircraft. The stowable lift rotor also includes a rotor assembly including rotor blades coupled to the distal end of the lift arm. The lift arm is movable between various positions including an extended position in the VTOL flight mode, a stowed position in the forward flight mode and intermediate positions therebetween such that the distance between the rotor assembly and the airframe is greater in the extended position than in the stowed position.

A system for the prioritization of flight controls in an electric aircraft is illustrated. The system includes a plurality of flight components, a sensor, and a computing device. The plurality of flight components are coupled to the electric aircraft. The sensor is coupled to each flight component of the plurality of flight components. Each sensor of the plurality of sensors is configured to detect a failure event of a flight component of the plurality of flight components and generate a failure datum associated to the flight component of the plurality of flight components. The computing device is communicatively connected to the sensor and is configured to receive the failure datum associated to the flight component of the plurality of flight component from the sensor, determine a prioritization element as a function of the failure datum, and restrict at least a flight element as a function of the prioritization element.

A solar powered airship includes a cabin, at least one fuselage having an interior volume filled with a volume of a lighter-than-air gas such as helium, and a wing affixed to the fuselage. A plurality of solar panels are affixed to the wing and to the fuselage. A plurality of rotors are affixed to the wing, wherein each rotor is powered via an electric motor having a battery that is operably connected to the plurality of solar panels, thereby allowing for continuous flight. The solar powered airship may further include propellors, which may also be powered via the solar panels, or which may include gasoline powered motors. The solar powered airship can include various configurations and numbers of fuselages, wings, rotors, and propellors.

A solar powered airship includes a cabin, at least one fuselage having an interior volume filled with a volume of a lighter-than-air gas such as helium, and a wing affixed to the fuselage. A plurality of solar panels are affixed to the wing and to the fuselage. A plurality of rotors are affixed to the wing, wherein each rotor is powered via an electric motor having a battery that is operably connected to the plurality of solar panels, thereby allowing for continuous flight. The solar powered airship may further include propellors, which may also be powered via the solar panels, or which may include gasoline powered motors. The solar powered airship can include various configurations and numbers of fuselages, wings, rotors, and propellors.

One embodiment is an aircraft including first and second fuselages; a wing assembly connecting the first and second fuselages, wherein the first and second fuselages are parallel to one another; first and second forward propulsion systems tiltably attached to forward ends of the first and second fuselages; and first and second aft propulsion systems fixedly attached proximate aft ends of the first and second fuselages.

One embodiment is an aircraft including first and second fuselages; a wing assembly connecting the first and second fuselages, wherein the first and second fuselages are parallel to one another; first and second forward propulsion systems tiltably attached to forward ends of the first and second fuselages; and first and second aft propulsion systems fixedly attached proximate aft ends of the first and second fuselages.