In an embodiment, an airport electric vehicle charging system includes a current transducer electrically coupled with a power source; a solid state converter electrically coupleable with an aircraft at or near an airport gate and configured to provide and maintain power to the aircraft; and a controller. The system further includes a first feedback loop between the controller and the current transducer; a second feedback loop between the controller and the solid state converter; and a battery charger electrically coupled with the power source and configured to charge one or more electric vehicles. The first feedback loop provides a first feedback signal generated by the current transducer to the controller. The second feedback loop provides a second feedback signal generated by the solid state converter to the controller. The battery charger is configured to consume power from the power source in accordance with the first and second feedback signals.

An assistance vehicle designed for supplying electrical energy to an electric taxiing device of an aircraft landing gear when the aircraft is moving over the ground. The assistance vehicle includes an autonomous energy source, a connector enabling it to be coupled to the aircraft and to electrically power the electric taxiing device. When an assistance instruction comprising the aircraft position is received, the assistance vehicle moves in an autonomous manner so as to reach the position of the aircraft, is automatically connected to the electric taxiing device when the assistance vehicle reaches the position of the aircraft and switches into freewheeling mode. When the assisted move has finished, the assistance vehicle is separated from the electric taxiing device and switches back into tractor mode. Thus, the electrical power supply system of the aircraft is simplified by externalizing the electrical supply of the electric taxiing device.

Systems and methods are disclosed for vehicle integration of unmanned aircraft systems (UASs). Example methods may include coupling a landing dish of a vehicle integrated UAS to a ground station assembly; positioning the landing dish and the ground station assembly into a portion of a vehicle and a capping member of the vehicle integrated UAS; and coupling the landing dish to the capping member of the vehicle integrated UAS. In various embodiments, the vehicle integrated UAS may be configured to send and receive information (e.g., route information, power information, status information, etc.) between unmanned aerial vehicles (UAV) associated with the UAS to device(s) of a vehicle.

Disclosed herein is a magnetic ladder bracket adapted to be releasably attached to any surface having ferromagnetic properties, such as steel, iron etc. The magnetic ladder bracket comprises a base coupled to a plurality of magnets one a first side of the base and two or more brackets on a second side of the base. The plurality of magnets provide a jet blast resistant securement of the magnetic ladder bracket to the ferromagnetic surface on a tug or other vehicle. The ladder is secured to the brackets by placing a rail of the ladder in the brackets and securing the ladder using a securing mechanism, such as a pin placed across the bracket. The magnetic ladder bracket further includes one or more handles for removing the bracket from the ferromagnetic surface.

Disclosed herein is a magnetic ladder bracket adapted to be releasably attached to any surface having ferromagnetic properties, such as steel, iron etc. The magnetic ladder bracket comprises a base coupled to a plurality of magnets one a first side of the base and two or more brackets on a second side of the base. The plurality of magnets provide a jet blast resistant securement of the magnetic ladder bracket to the ferromagnetic surface on a tug or other vehicle. The ladder is secured to the brackets by placing a rail of the ladder in the brackets and securing the ladder using a securing mechanism, such as a pin placed across the bracket. The magnetic ladder bracket further includes one or more handles for removing the bracket from the ferromagnetic surface.

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 secure terminal for the aerial transport of passengers whose technical and operational infrastructure makes it possible to ensure the physical security of the building, of the aircraft, of the goods, of the passengers and of the flight, technical and administrative personnel and the confidentiality of the passengers and of their goods, noteworthy in that it comprises at least one building having a globally V-shaped horizontal section and comprising two branches extending from a mid-zone, constituting parking hangars for aircraft and determining between them an uncovered central zone.

Anti-collision airport system including a motorized mobile device to be moved close to an aircraft. The system includes a database to record structural characteristics of categories of aircraft and structural characteristics of the motorized mobile device. The controller is configured to identify a category corresponding to the aircraft and a positioning of the motorized mobile device with respect to the aircraft, search and retrieve, from the database, structural characteristics associated with the category corresponding to the aircraft and structural characteristics of the motorized device, calculate a trajectory for the movement of the motorized mobile device on the basis of the structural characteristics of the aircraft and of the motorized mobile device and of the positioning of the motorized mobile device with respect to the aircraft, and control the motorized mobile device according to the calculated trajectory.

An electric pushback vehicle includes a frame having a forward portion and a rear portion. The vehicle further includes front drive axle and a rear drive axle configured to communicate power to ground engaging members. A traction battery is housed within the electric pushback vehicle and provides electric power to an electric motor to drive an output shaft. A transmission is connected to receive mechanical power from the electric motor through a torque converter.

In order to be able to accommodate the required number of battery modules (5)specified in terms of their external dimensionsand in particular the number required by the customer, with good weight distribution, in the chassis gradations of diesel tractors, in particular of long cabs, when switching to a battery electric drive, different arrangements of the battery modules (5) at the front and in particular also at the rear in the chassis (2) are proposed according to the invention.