A transportation system and method serve passenger-conveying VTOL air vehicles (AVs) at a vertiport. The vertiport has a flight deck including at least one landing pad, a passenger terminal, and a dynamic partition arrangement that defines a capsule for receiving one of the AVs at a time. The dynamic partition arrangement assumes a first open state in which it is open to the flight deck and closed to the passenger terminal and a second open state in which it is closed to the flight deck and open to the passenger terminal. A robotic system includes a handling robot that automatically approaches and docks with the AV after landing, and conveys the AV between the landing pad and the capsule via an opening provided by the first open state of the dynamic partition.

A charging system may comprise: a first battery array; a bi-directional direct current (DC)/DC converter in electrical communication with the first battery array; and a charging interface in electrical communication with the bi-directional DC/DC converter, the charging interface configured to electrically couple to a second battery array of an electric vehicle.

A charging ecosystem may comprise: an interconnected battery module; a first battery system comprising a first plurality of the interconnected battery modules; and a second battery system comprising a second plurality of the interconnected battery module. The first battery system may be configured for charging the second battery system. The second battery system may be configured for powering an electric vehicle. The interconnected battery module is adaptable to various interfaces with the first system and the second system.

A mobile microgrid charging system may comprise a first battery array that is configured to be transported from location to location and facilitate fast charging of electric aircrafts. The mobile microgrid charging system is mobile and configured to charge multiple electric aircraft prior to re-charging.

A mobile charging system for electric vehicles may include a fluid management system. The fluid management system may be configured to be fluidly coupled to the electric vehicle. The fluid management system may be configured to provide heating or cooling to a vehicle battery system during charging of the vehicle battery system of the electric vehicle.

In one aspect, a system for charging an aircraft can include a robotic charging device, and a computing system configured to obtain data associated with a transportation itinerary and energy parameter(s) of the aircraft. The data associated with the transportation itinerary can be indicative of an aircraft landing facility at which the aircraft is to be located. The computing system can determine (e.g., select) a robotic charging device from among a plurality of robotic charging devices for charging the aircraft based on the transportation itinerary data and energy parameter(s) of the aircraft; determine charging parameter(s) for the robotic charging device based on the transportation itinerary data; and communicate command instruction(s) for the robotic charging device to charge the aircraft according to the charging parameter(s). The robotic charging device can be configured to automatically connect with a charging area of the aircraft for charging a battery onboard the aircraft.

A system for an aircraft includes an electric energy module and a connector module operatively connected to the electric energy module. The connector module is: structured to attach the electric energy module to the aircraft when the connector module is in an engaged mode while in use, and operable between the engaged mode and a disengaged mode. The connector module in the disengaged mode while in use disengages the electric energy module from the aircraft.

A driverless ground vehicle for coupling to an aircraft has a vehicle base, a chassis with wheels that is arranged on the vehicle base, a control unit, a drive, an electrical energy store, and a coupling unit. The drive is coupled to the chassis for moving the wheels. The coupling unit is arranged on the vehicle base and carries an electrical line to be connected to the electrical energy store and has a first electrical connector at a distal end. The coupling unit is designed to move the first electrical connector for coupling to a second electrical connector. The control unit is connected to the drive and the coupling unit to control the drive to move the ground vehicle to the aircraft and to control the coupling unit to move the first connector into a predefinable position on the aircraft to establish an electrical connection to the second electrical connector.

In an embodiment, an integrated ground support system for an aircraft is described herein, the system including a frame on which the system is arranged as a singular assembly. An engine, drive train, alternator, bleed air unit, one or more electrical components, and air cycle machine are mounted on the frame. The engine operates at a first operational state associated with a first rotational speed that is independent of a frequency associated with electrical power, if only the electrical power is to be used by the aircraft, and the engine operates at a second operational state associated with a second rotational speed, different from the first rotational speed, that is a function of a pressure associated with bleed air or the conditioned air, if the electrical power and one of the bleed air or the conditioned air are to be used simultaneously by the aircraft.

A system for an aircraft, comprises an electric energy module; and a connector module operatively connected to the electric energy module. The connector module is: structured to attach the electric energy module to the aircraft when the connector module in an engaged mode while in use, and operable between the engaged mode and a disengaged mode, the connector module in the disengaged mode while in use disengaging the electric energy module from the aircraft.