The present invention relates to an autonomous, multi-use, subterranean aircraft pull-through system that connects with an aircraft arriving at the ramp pick-up point and transits through the terminal building, in a unidirectional movement, where the aircraft is serviced, then disconnects from the aircraft at the ramp release point. The autonomous, subterranean aircraft pull-through system receives multiple aircraft in a row, with rows adjacent to each other, where aircraft are nose to tail, and side by side, occupying the smallest footprint in the industry. The autonomous, subterranean aircraft pull-through system is remotely controlled and operates autonomously in a subterranean manner to assist in servicing the aircraft. The system helps to speed up the aircraft handling component of airside operations, improve safety, reduce emissions, and the cost factors borne by both airports and airlines. The autonomous, subterranean aircraft pull-through system design is versatile in handling all code A-F (ICAO) aircraft.

An airplane towing system includes telescoping actuators on tow rods that react to pushing, towing, and turning forces to distribute the forces to the tow rods rather than to an airplane structure.

A tow bar fitting for towing an aircraft is disclosed. The tow bar fitting includes a mount, a pin support, and a tow pin. The mount includes an upper attachment and a lower attachment for affixing the tow bar fitting to a landing gear of the aircraft. The pin support extends from the mount away from the landing gear. The tow pin is positioned in the pin support such that a tow pin plane that horizontally bisects the tow pin is lower than a mount plane that horizontally bisects the upper attachment and the lower attachment when the aircraft is right-side-up on the ground.

A tool for adjusting an orientation of a nose landing gear of an aircraft is disclosed herein. The nose landing gear has an axle to which a wheel is mounted. The axle has an opening extending therethrough. The opening is defined by an inner surface of the axle. The tool includes, but is not limited to, a unitary member having a handle portion at a first end of the unitary member and an axle-engaging portion at a second end of the unitary member. The handle portion is configured for engagement with a hand of an operator. The axle-engaging portion is configured to be inserted into the opening and to engage with the inner surface.

To avoid the intervention of an operator on a direction control device with which an aircraft towing system is equipped, this system comprises a first towing sling comprising a front end connected to a towing vehicle, and a rear end connected to a first main landing gear, a second towing sling comprising a front end connected to the vehicle, and a rear end connected to a second main landing gear. The direction control device is connected to a front landing gear, and arranged between the first and second slings. The direction control device comprising a lateral direction control member having a first lateral end mounted on the first sling, and a second lateral end mounted on the second sling.

Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly further allows for transportation of the UAV over uneven terrain.

A universal hitch adapter system includes a universal hitch adapter with at least one force sensor operable to measure push-and-pull forces and coupled to a) one of a front end and a rear end of an aircraft tractor and b) an aircraft tow bar coupled to a nose gear of an aircraft. The system also including a memory; a user input interface operable to receive a user's selection of one of a plurality of aircrafts stored in the memory and a user's input associated with one of a shear pin; a processor operably configured to determine at least one shear pin breaking force threshold for each of the plurality of aircrafts based on the user's input; and an indicator operable to emit an alert as a result of the force sensor measuring a force that meets or exceeds the at least one shear pin breaking force threshold.

An apparatus, system, and method are disclosed for moving an aircraft. The apparatus includes an elongated support frame, at least one tug wheel and a loading platform. The elongate support frame includes a wheel receiving recess shaped to receive a wheel of an aircraft. The tug wheel(s) support the elongated support frame. The loading platform is positioned within the wheel receiving space and is configured to support the aircraft wheel. The loading platform is positioned at a height relative to the elongated support frame that is sufficient to avoid interference between a propeller on the aircraft and the elongated support frame when the aircraft wheel is positioned on the loading platform.

A towing system comprises a bar, a first attachment device arranged at a first end of the bar, the first attachment device being able to attach the towing system to a towing vehicle, a second attachment device arranged at a second end of the bar, the second attachment device being able to attach the towing system to a travelling machine to be towed, the second attachment device comprising a fork able to hold at least one wheel of the travelling machine, the fork having two longitudinal members between which at least one wheel of the travelling machine is able to be received, a separation device able to modify the spacing between the two longitudinal members and a holding device able to hold the wheel between the two longitudinal members.

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.