The present disclosure relates to a multifunction battery switch and method of connecting a battery pack to an external bus via the multifunction battery switch. The multifunction battery switch having a multifunctional controller, a plurality of switches, an inductor, and a resistor. Each of the plurality of switches is independently controllable via switch commands from the multifunctional controller. The inductor, the resistor, and the plurality of switches are arranged to define a buck-boost converter to selectively regulate power transfer between the battery pack and the external bus as a function of the switch commands from the multifunctional controller.

A public transportation system combines a unique combination of components that includes interoperable electric-powered vehicles, facilities, hardware and software having specifications, standards, processes, capabilities, nomenclature, and concepts of operations that together include a concerted, comprehensive, multi-modal, future system for moving people and goods that is herein named Quiet Urban Air Delivery (QUAD) and in which uniquely-capable, ultra-quiet, one to six-seat, electrically-powered, autonomous aircraft (SkyQarts) fly sub-193 kilometer trips on precise trajectories with negligible control latency and perform extremely short take-offs and landings (ESTOL) with curved traffic patterns at a highly-distributed network of very small, airports (“SkyNests”) that themselves have standardized compatible facilities that interoperate with SkyQarts as well as with versatile, autonomous electric-powered payload carts (EPCs) and robotic delivery carts (RDCs) to provide safe, fast, on-demand, community-acceptable, environmentally friendly, high-capacity, affordable door-to-door delivery of both passengers and cargo across urban, suburban and rural settings across the globe.

A public transportation system combines a unique combination of components that includes interoperable electric-powered vehicles, facilities, hardware and software having specifications, standards, processes, capabilities, nomenclature, and concepts of operations that together include a concerted, comprehensive, multi-modal, future system for moving people and goods that is herein named Quiet Urban Air Delivery (QUAD) and in which uniquely-capable, ultra-quiet, one to six-seat, electrically-powered, autonomous aircraft (SkyQarts) fly sub-193 kilometer trips on precise trajectories with negligible control latency and perform extremely short take-offs and landings (ESTOL) with curved traffic patterns at a highly-distributed network of very small, airports (“SkyNests”) that themselves have standardized compatible facilities that interoperate with SkyQarts as well as with versatile, autonomous electric-powered payload carts (EPCs) and robotic delivery carts (RDCs) to provide safe, fast, on-demand, community-acceptable, environmentally friendly, high-capacity, affordable door-to-door delivery of both passengers and cargo across urban, suburban and rural settings across the globe.

A system of fall back flight control configured for use in electric aircraft includes an input control configured to receive a pilot input and generate a control datum. System includes a flight controller communicatively coupled to the input control and configured to receive the control datum and generate an output datum. The system includes the actuator having a primary mode in which the actuator is configured to move the at least a portion of the electric aircraft as a function of the output datum and a fall back mode in which the actuator is configured to move the at least a portion of the aircraft as a function of the control datum. The actuator configured to receive the control datum, receive the output datum, detect a loss of communication with the flight controller, and select the fall back mode as a function of the detection.

A solar unmanned aircraft is disclosed. The aircraft includes a first body, a second body, a main wing, a tail wing and at least four vertical control wings. The at least four control wings are all located below the main wing and the tail wing so that an upper surface of the main wing and tail wing can massively be installed with solar panels. Each of the vertical control wings has a fixed wing and a rudder. The rudder can rotate with respect to the fixed wing to control the attitude and motion of the solar unmanned aircraft.

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.

An aircraft comprising at least one propulsion unit configured to propel the aircraft in a first direction and at least one further propulsion unit configured to propel the aircraft in a second direction substantially opposite to the first direction. The aircraft also includes at least one wing, wherein the at least one propulsion unit is mounted in front of the leading edge of the at least one wing, such that the air downstream of the at least one propulsion unit flows around the at least one wing to provide lift and a longitudinal thrust in the first direction. The at least one further propulsion unit is configured to provide a longitudinal thrust in the second direction.

An aircraft comprising at least one propulsion unit configured to propel the aircraft in a first direction and at least one further propulsion unit configured to propel the aircraft in a second direction substantially opposite to the first direction. The aircraft also includes at least one wing, wherein the at least one propulsion unit is mounted in front of the leading edge of the at least one wing, such that the air downstream of the at least one propulsion unit flows around the at least one wing to provide lift and a longitudinal thrust in the first direction. The at least one further propulsion unit is configured to provide a longitudinal thrust in the second direction.

An aircraft has a fuselage, a wing assembly coupleable to the fuselage, and an empennage including a pair of tail booms configured to be removably coupled to the wing assembly. The wing assembly includes a pair of boom interfaces located on laterally opposite sides of the fuselage. Each tail boom has a boom forward end configured to be mechanically attached to one of the boom interfaces using an externally-accessible mechanical fastener.