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.

A power distribution system is provided for an aircraft on the ground, including a first electrical load, operably coupled to the aircraft on the ground and configured to receive at least a first portion of a predetermined maximum input power provided by a power supply; at least one second electrical load, electrically coupleable to the aircraft on the ground and configured to receive at least a second portion of the predetermined maximum input power provided by the power supply, and a controller, adapted to monitor at least one parameter of the power consumed by any one of the first and second electrical load, and control the power consumption of at least the first electrical load so that the total power consumption of the first and second electrical load does not exceed the predetermined maximum input power; wherein the predetermined maximum input power is provided via a single power line between the power supply and an input port of the first electrical load.

A taxi tug includes a chassis, a motive power source, and an auxiliary power services system. The chassis has at least one drive wheel. The motive power source is operatively connected to the at least one drive wheel. The auxiliary power services system is disposed on the chassis and is configured to provide at least one of electric power, pneumatic power, and low pressure conditioned air to an aircraft.

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.

An aircraft ground support unit (1) (GSU) for supplying a specific service according to a specific set of service parameters to an aircraft (2) on the ground and consuming a specific service energy is provided that includes: a rechargeable energy storage unit (3) (RESU) for autonomously delivering the specific service energy required for supplying the specific service in the given available service duration; an energy sensor (4) for measuring an instantaneous state of energy parameters of the RESU; and a control unit. The RESU, identifying the aircraft (2), identifying in a database the specific set of service parameters for identified aircraft, establishing a specific service energy budget estimate, determining an instantaneous charge level of the RESU, comparing the specific service energy budget estimate with the instantaneous charge level of the RESU, and generating an output signal representative of a capacity of the RESU to deliver the specific service energy budget estimate as a function of the instantancous charge level.

A lightning protection system of an aircraft when it is electrically powered on the ground by a generator set is described. Such an aircraft consequently includes a fuselage and a connecting connector to allow the connection to the generator set. The connecting connector includes a frame, male electrical contacts protruding on either side of said frame, and a lightning protection system inserted between the male electrical contacts and electrical elements of the aircraft. The protection system includes peak-clipping devices for clipping an electrical signal and a printed circuit having conductive tracks linking the male electrical contacts to the peak-clipping devices.

An aircraft ground support unit (1) for supplying a service to an aircraft (3) on the ground according to a specific servicing program is provided that includes reception means (5) suitable for identifying an aircraft (3) in motion or parked on the ground by receiving information emitted by a transponder (7) of said aircraft including an instantaneous GPS coordinates of the position of the aircraft, the identity of the aircraft, the type of aircraft, and the company of the aircraft, aircraft status data. A microprocessor is provided that is suitable for selecting and implementing a predefined servicing program stored in a database corresponding to the type and company of the thus identified aircraft (3) on the basis of the information received by the reception means. A data record device is also provided that is to store the events, aircraft status data, ground unit data for airlines operation optimization.

In one aspect, there is disclosed a taxi vehicle comprising a chassis having a coupler to connect to a coupling location of a craft and a set of wheels with at least one electric motor coupled to the set of wheels. The taxi vehicle can include a fuel cell coupled to the at least one electric motor and a battery coupled to the fuel cell. The battery can be configured to supply peak power demand to the at least one electric motor to start moving the craft. The battery can receive charging from the fuel cell when not supplying peak power demand while the fuel cell supplies power to the at least one electric motor to continue moving the craft.

A socket system for the protection against lightening of an aircraft disposed between a connection terminal of the aircraft and an end connector of a generator set powered by a power supply cable having several electrical conductors includes an extension socket connected between the end connector and the connection terminal and a safety device including in a housing made of electrically insulating material, and clipping means designed to clip an electrical signal. The installation of such a safety device prevents the propagation of an electrical overvoltage beyond the safety device.

A multi-stage, intercooled centrifugal compressor with integral power generator system for a mobile, ground-based aviation support cart is disclosed. A bootstrap-type turbo compressor module which can supply cooled air. The system may be operated in one of several modes: high pressure bleed air (e.g., 35-50 psig) for jet engine start, conditioned or cooled air (e.g., 2-5 psig) for aircraft cooling purposes, or electrical ground power. Electrical ground power and conditioned air may also be supplied simultaneously if desired.