Abstract: A system for autonomous aircraft towing includes a tow vehicle with a turntable lifting unit for engaging an aircraft's nose landing gear, a sensor system, and an Offline Intelligence Advanced Driver Assistance System (OI-ADAS) integrated with the tow vehicle. The OI-ADAS includes a local processing unit that processes sensor data in volatile memory without persistent storage and a controller that analyzes visual cues to determine position and orientation, generates control commands, controls the turntable lifting unit, and maneuvers the tow vehicle. The OI-ADAS operates without preexisting knowledge of the environment, processing all data exclusively in volatile memory and discarding visual frames after processing. The system detects visual cues on ground surfaces for navigation without relying on pre-existing maps or GPS data. A collision avoidance module detects obstacles and generates avoidance maneuvers in autonomous mode while providing warnings and intervention in operator-controlled mode.

Abstract: A system for autonomous aircraft towing includes a tow vehicle with a turntable lifting unit configured to engage an aircraft's nose landing gear, a sensor system, and a controller. The controller receives real-time communications over a dedicated network from tow vehicles, ground service vehicles, control towers, centralized workstations, or stationary sensors, autonomously generates control commands based on received communications, controls the turntable lifting unit to capture and lift the nose landing gear, and maneuvers the tow vehicle to tow the aircraft. A method for autonomous aircraft towing includes engaging an aircraft's nose landing gear with a turntable lifting unit, receiving real-time communications over a dedicated network, autonomously generating control commands, controlling the turntable lifting unit, and maneuvering the tow vehicle.

Abstract: A system for autonomous aircraft towing with steering control includes a tow vehicle with a turntable lifting unit configured to engage an aircraft's nose landing gear, a sensor system including steering angle sensors to monitor angular position of the tow vehicle's steering system, a wheelbase sensor to detect distance between main landing gear and nose wheel, and a controller. The controller calculates an inertia factor based on detected distance, determines permissible driving parameters based on the inertia factor, towing speed, and steering angle measurements, autonomously generates control commands based on permissible driving parameters, and controls the turntable lifting unit and tow vehicle steering to maintain safe operational limits during aircraft towing operations. A method for autonomous aircraft towing with steering control is also provided.

Abstract: An aircraft tow vehicle comprises a vehicle body, a turntable lifting unit coupled to the vehicle body configured to engage with an aircraft nose landing gear, and a modular high-current battery management system. The system includes at least one removable battery pack module housed within the vehicle body, comprising a battery frame housing a plurality of lithium iron phosphate (LiFePO4) batteries, a controller to monitor and control the batteries, a high-current DC power relay for managing current flow, at least one supercapacitor to manage rapid changes in current flow, and at least one semiconductor device to regulate voltage and current levels. The system is capable of providing a peak current output of at least 1000 amperes. This configuration enables the tow vehicle to perform efficient aircraft towing operations with enhanced energy management and operational flexibility.

Abstract: The present disclosure provides a multi-vehicle omnidirectional aircraft maneuvering system comprising a plurality of tow vehicles, each tow vehicle comprising a turntable lifting unit (TLU) configured to capture and secure a portion of an aircraft's landing gear, a control unit configured to communicate with and coordinate the movements of the plurality of tow vehicles, and wherein each TLU comprises an automated turntable, a gate configured to open and close to receive landing gear, and a moving floor configured to support the landing gear. The system enables precise positioning and omnidirectional movement of aircraft through coordinated operation of multiple tow vehicles that simultaneously engage with different landing gear components. Each tow vehicle includes sensors for detecting landing gear position and environmental conditions, while the control unit establishes wireless communication to synchronize lifting operations and coordinate simultaneous movement patterns.

Abstract: A system for autonomous aircraft towing includes a tow vehicle with a turntable lifting unit for engaging an aircraft's nose landing gear, a sensor system, and an Offline Intelligence Advanced Driver Assistance System (OI-ADAS) integrated with the tow vehicle. The OI-ADAS includes a local processing unit that processes sensor data in volatile memory without persistent storage and a controller that analyzes visual cues to determine position and orientation, generates control commands, controls the turntable lifting unit, and maneuvers the tow vehicle. The OI-ADAS operates without preexisting knowledge of the environment, processing all data exclusively in volatile memory and discarding visual frames after processing. The system detects visual cues on ground surfaces for navigation without relying on pre-existing maps or GPS data. A collision avoidance module detects obstacles and generates avoidance maneuvers in autonomous mode while providing warnings and intervention in operator-controlled mode.

Abstract: An aircraft tow vehicle comprises a turntable lifting unit configured to automatically rotate and lift for attachment to a nose landing gear of an aircraft. A gate coupled to the turntable lifting unit automatically unlocks, opens to receive the nose landing gear, closes to secure the nose landing gear, and locks. A sensor system detects the nose landing gear. A controller receives data from the sensor system, processes the data to determine a position of the nose landing gear, and controls the turntable lifting unit while automatically adjusting a position of the tow vehicle relative to the nose landing gear. A moving floor adjusts to accommodate different nose wheel sizes. A nose wheel adapter automatically positions itself to hold down the nose landing gear when weight is detected on the moving floor.

Abstract: An aircraft tow vehicle comprises a vehicle body, a turntable lifting unit coupled to the vehicle body configured to engage with an aircraft nose landing gear, and a modular high-current battery management system. The system includes at least one removable battery pack module housed within the vehicle body, comprising a battery frame housing a plurality of lithium iron phosphate (LiFePO4) batteries, a controller to monitor and control the batteries, a high-current DC power relay for managing current flow, at least one supercapacitor to manage rapid changes in current flow, and at least one semiconductor device to regulate voltage and current levels. The system is capable of providing a peak current output of at least 1000 amperes. This configuration enables the tow vehicle to perform efficient aircraft towing operations with enhanced energy management and operational flexibility.

Abstract: An aircraft tow vehicle comprises a turntable lifting unit configured to automatically rotate and lift for attachment to a nose landing gear of an aircraft. A gate coupled to the turntable lifting unit automatically unlocks, opens to receive the nose landing gear, closes to secure the nose landing gear, and locks. A sensor system detects the nose landing gear. A controller receives data from the sensor system, processes the data to determine a position of the nose landing gear, and controls the turntable lifting unit while automatically adjusting a position of the tow vehicle relative to the nose landing gear. A moving floor adjusts to accommodate different nose wheel sizes. A nose wheel adapter automatically positions itself to hold down the nose landing gear when weight is detected on the moving floor.

Abstract: The disclosure herein provides an active anti-ice coating, which is capable of releasing an anti-ice agent, which includes anti-ice agent reservoirs, which are embedded in a UV curable matrix material, for providing an effective anti-ice coating with an active anti-ice agent release over a long period of time.

Abstract: The disclosure herein provides an active anti-ice coating, which is capable of releasing an anti-ice agent, which includes anti-ice agent reservoirs, which are embedded in a UV curable matrix material, for providing an effective anti-ice coating with an active anti-ice agent release over a long period of time.

Abstract: In order to maintain a surface region of an aircraft free of ice in a particularly energy-efficient manner, a device for deicing and/or for preventing ice formation is provided on an aircraft. The device includes a heat emitting device for emitting heat at a surface region of the aircraft, the heat emitting device is designed to dissipate heat along a line in order to produce a predetermined breaking point or a predetermined breaking line or parting line in ice accumulating on the surface region.

Abstract: An actuator mounting method for mounting at least one actuator involves providing a skin structure and at least one actuator, and fixing the at least one actuator to the inner surface of the skin structure.

Abstract: The disclosure herein provides an active anti-ice coating, which is capable of releasing an anti-ice agent, which includes anti-ice agent reservoirs, which are embedded in a UV curable matrix material, for providing an effective anti-ice coating with an active anti-ice agent release over a long period of time.

Abstract: A method for manufacturing a water- and ice-repellent surface on a metallic substrate is disclosed, comprising the steps of a) providing a metallic substrate, b) polishing the metallic substrate, c) contacting of at least a part of the metallic substrate with an electrolyte solution, d) anodizing the metallic substrate of step c) for producing a nanoporous layer on the substrate surface, and e) applying a hydrophobic coating on the nanoporous layer. Thereby the accretion of ice particularly on surfaces of aircraft exposed to a flow is reduced in comparison with the prior art.

Abstract: An actuator mounting method for mounting at least one actuator involves providing a skin structure and at least one actuator, and fixing the at least one actuator to the inner surface of the skin structure.

Abstract: In order to maintain a surface region of an aircraft free of ice in a particularly energy-efficient manner, a device for deicing and/or for preventing ice formation is provided on an aircraft. The device includes a heat emitting device for emitting heat at a surface region of the aircraft, the heat emitting device is designed to dissipate heat along a line in order to produce a predetermined breaking point or a predetermined breaking line or parting line in ice accumulating on the surface region.