Certain aspects relate to a ground support cart for charging an electric aircraft. An exemplary ground support cart includes a frame, at least a wheel operatively coupled to the frame and configured to facilitate rolling translation of the ground support cart, a cart battery mounted to the frame and configured to provide a first electrical charging current, a conductor in electric communication with the at least a cart battery, a coolant source mounted to the frame and configured to provide a coolant flow, a hose in fluidic communication with the coolant source, and a controller configured to control the first electrical charging current within the conductor and the coolant flow within the hose.

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.

An HVAC system has a duct with an inlet and an outlet. A first supercharger is disposed in the duct. A second supercharger is disposed in the duct in parallel with the first supercharger. A gearbox has a first output shaft coupled to the first supercharger and a second output shaft of the gearbox coupled to the second supercharger. A first evaporation coil is disposed in the duct between the supercharger and inlet. A second evaporation coil is disposed in the duct between the supercharger and outlet. A heater is disposed in the duct between the supercharger and outlet.

An unmanned aerial vehicle according to certain embodiments generally includes a chassis, a power supply mounted to the chassis, a control system operable to receive power from the power supply, at least one rotor operable to generate lift under control of the control system, a line having one end coupled to the chassis and an opposite free end, wherein the free end is positioned below the chassis, and a severing mechanism operable to sever the line under control of the control system.

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.

This specification describes an electrically powered modular platform comprising a power module comprising a common power bus, the power module electrically connected to a power source; one or more service modules that provide a service; a termination module that is configured to cover an opening in the one or more service modules, wherein the power module, each of the one or more service modules, and the termination module are modular and stackable, and wherein the power module and each of the one or more service modules are electrically connected using the common power bus to provide power to each of the one or more service modules.

Electric aircraft charging system including charging cable configured to carry electricity and energy source, wherein the energy source is electrically connected to the charging cable. The system also including a cable reel module, the cable reel module including a reel, wherein the reel is rotatably mounted to the cable reel module, wherein the reel is configured to rotate in a forward direction and a reverse direction, and the charging cable, in a stowed configuration, is wound around the reel. The cable reel module further including a rotation mechanism configured to rotate the reel in reverse, and a cable reel module door having a closed position and an open position, wherein the closed position prevents access to the reel and the open position allows access to the reel. The system additionally including a controller communicatively connected to the rotation mechanism and configured to send a retraction signal to the rotation mechanism.

An air start unit for starting and servicing jet engines in aircraft and other flying machines, wherein at least one compressor is provided for generating air and a power supply for supplying electrical power consumers. The air start unit drives the compressor with at least one electric motor, with the electric motor drawing the electrical energy for operation from a high-voltage battery. The electric motors then in turn drive the compressor, which generates compressed air from ambient air for the purpose of starting and servicing the jet engines in aircraft and other flying machines. With an appropriate battery capacity, the air start unit can also supply power consumer of these aircraft and other flying machines via the power supply.

Example implementations may relate to self-deployment of operational infrastructure by an unmanned aerial vehicle (UAV). Specifically, a control system may determine operational location(s) from which a group of UAVs is to provide aerial transport services in a geographic area. For at least a first of the operational location(s), the system may cause a first UAV from the group to perform an infrastructure deployment task that includes (i) a flight from a source location to the first operational location and (ii) installation of operational infrastructure at the first operational location by the first UAV. In turn, this may enable the first UAV to operate from the first operational location, as the first UAV can charge a battery of the first UAV using the operational infrastructure installed at the first operational location and/or can carry out item transport task(s) at location(s) that are in the vicinity of the first operational location.

A system is provided for multi-engine coordination of gas turbine engine motoring in an aircraft. The system includes a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode.