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 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 method for performing a cleaning cycle on a turbine engine mounted to an airframe includes conducting a cleaning agent from a cleaning agent supply into the gas turbine engine. The method further includes conducting compressed air from a cleaning air supply into the gas turbine engine to dry motor the gas turbine engine while the cleaning agent is conducted from the cleaning agent supply into the gas turbine engine.

The disclosure relates to a nozzle (12) for cooling a jet engine (2) for maintenance, wherein the jet engine (2) comprises an exhaust channel (21) for the exit of exhaust gases of the jet engine (2), the nozzle (12) comprises a suction adapter (121) having a round shape adapted to be connected in sealed manner to the exhaust channel (21) for sucking air from the exhaust channel (21), and a suction channel (122) in fluid connection with the suction adapter (121) for sucking air from the suction adapter (121), wherein the suction channel (122) is arranged to be connected to an air suction device (13).

The disclosure relates also to an apparatus (1) for cooling a jet engine (2) for maintenance and a method for maintenance of a jet engine (2).

This disclosure details exemplary moonroof systems for vehicles. An exemplary moonroof system may include a pod assembly that may be received within an opening of a headliner. The pod assembly may be utilized to dock, deploy, and land an unmanned aerial vehicle relative to the moonroof system. The pod assembly may include a charging and cooling system for charging and cooling the unmanned aerial vehicle when it is docked within the pod assembly.

An aircraft assist system described herein includes an aircraft coupling counterpart attached to a strut of a landing gear of an aircraft, and an assist vehicle. The assist vehicle includes a frame, ground-engaging wheels mounted to the frame, a power source for driving one or more of the ground-engaging wheels, and a vehicle coupling counterpart for engagement with the aircraft coupling counterpart. The aircraft coupling counterpart and the vehicle coupling counterpart define a swivel connection for transferring a propulsive force from the takeoff assist vehicle to the aircraft. The aircraft coupling counterpart is disengageable from the vehicle coupling counterpart by upward movement of the aircraft coupling counterpart relative to the vehicle coupling counterpart.

An unmanned aircraft such as a tethered drone has an electrical power connection for receiving electrical power from a remote source, and a power delivery system for delivering electrical power to onboard applications equipment such as radio transmitters. To ensure that ground staff are not exposed to high levels of radiation from the transmitters, power is only delivered to the communications equipment after the aircraft has left the ground. A sensor associated with the aircraft's undercarriage may be used to detect when the aircraft is airborne. The applications equipment is powered from an accumulator which is only charged up from the power supply after launch. In the event of a failure of the power supply when airborne, the output of the accumulator is diverted to control propulsion and flight control systems, which are normally powered directly from the power supply, to allow a controlled descent, and thus shutting off the applications equipment before the aircraft returns to proximity to personnel on the ground.

Example implementations may relate to using an unmanned aerial vehicle (UAV) dedicated to deployment of operational infrastructure, with such deployment enabling charging of a battery of a UAV from a group of UAVs. More specifically, the group of UAVs may include at least (i) a first UAV of a first type configured to deploy operational infrastructure and (ii) a second UAV of a second type configured to carry out a task other than deployment of operational infrastructure. With this arrangement, a control system may determine an operational location at which to deploy operational infrastructure, and may cause the first UAV to deploy operational infrastructure at the operational location. Then, the control system may cause the second UAV to charge a battery of the second UAV using the operational infrastructure deployed by the first UAV at the operational location.

Exemplary embodiments described in this disclosure are generally directed to a collaborative relationship between a UAV and an automobile. In a first exemplary method, a data capture system is provided in a UAV. The data capture system may be used to capture data when the UAV is in flight. A first computer in the UAV determines one or more limitations associated with wirelessly transmitting some or all of the data from the UAV to an automobile. The first computer may be further used to withhold wireless transmission of a portion of the data to the automobile due to the one or more limitations. The portion of data is transferred to a second computer in the automobile after landing the UAV on the automobile. In a second exemplary method, the UAV includes a communication relay system for relaying to an automobile, signals received from a satellite or a cellular base station.

A self-insulating air delivery system maintains a desired air temperature of the conditioned air supplied thereinto for delivery to an aircraft. The system uses insulating airflow layers; a parallel layer and a counterflow layer. A starting section connects to a PCA unit and delivers conditioned air therefrom to an interior supply hose. The starting section also either creates bleed conditioned air or accepts conditioned insulating air and supplies it to an interior insulating hose that is annularly outward of the supply hose and in which air flows parallel to airflow in the supply hose. A reversing connector indirectly connects the supply hose to the aircraft and reverses the flow of air from the interior insulating hose to flow back toward the PCA unit in an exterior counterflow hose that is annularly outward of the interior insulating hose.