A moisture control assembly for use with a support beam extending through an insulation layer is provided. The insulation layer is positioned between an outer wall and an inner wall. The assembly includes: a moisture path close-out structure coupled to the insulation layer at an aperture defined through the insulation layer, the moisture path close-out structure including an opening substantially aligned with the aperture and configured to receive the support beam therethrough; and a coupling mechanism configured to secure the moisture path close-out structure to the support beam such that the moisture path close-out structure is partially pulled away from the insulation layer, the coupling mechanism and the moisture path close-out structure configured to direct liquid flow down and away from the support beam and along the insulation layer.

Devices, systems, and methods for remote deicing/anti-icing of an aircraft are described herein. One remote operator deicing/anti-icing station located in a remote location from a deicing/anti-icing rig includes a number of remote rig control components for actuation by a remote operator, wherein the remote rig control components include a remote operator user interface, located outside of a rig being at least partially controlled by the remote operator deicing/anti-icing station, the rig including a truck and a deicing/anti-icing control cabin that controls disbursement of substances to deice/anti-ice an aircraft, and a communication device that communicates instructions from the remote operator user interface and the number of remote rig control components to the rig to control at least one of the truck and the deicing/anti-icing control cabin.

Devices, systems, and methods for remote deicing/anti-icing of an aircraft are described herein. One remote operator deicing/anti-icing station located in a remote location from a deicing/anti-icing rig includes a number of remote rig control components for actuation by a remote operator, wherein the remote rig control components include a remote operator user interface, located outside of a rig being at least partially controlled by the remote operator deicing/anti-icing station, the rig including a truck and a deicing/anti-icing control cabin that controls disbursement of substances to deice/anti-ice an aircraft, and a communication device that communicates instructions from the remote operator user interface and the number of remote rig control components to the rig to control at least one of the truck and the deicing/anti-icing control cabin.

The present disclosure provides an airplane ground deicing installation that minimizes the impact of deicing operations on the airport during icing conditions. The installation does not require alteration of a normal taxi pattern and can be performed as quickly as the average separation time between take-offs. The installation allows modification of its shape to adapt to the contour of almost all types of commercial passengers airplanes operating from major airports, and simultaneously deices large surfaces of the airplane. Deicing and anti-icing fluids are applied to airplane surfaces from nozzles positioned in close proximity to the airplane's surface. Speed and adaptability to different types of airplanes, combined with a design that allows rapid relocation of the installation, are key features that make it possible to place the installation on the taxiway, close to the head of the runway it serves, such that the taxi pattern and the separation in between takeoffs are not altered as compared to the normal operations of the airport.

The present disclosure provides for informed de-icing by identifying a travel time range for an aircraft from a de-icing station to a runway; identifying a holdover window based on predicted weather conditions during the travel time range; estimating a takeoff time for the aircraft based on a takeoff queue for the runway and the travel time range; and in response to the holdover window expiring before the estimated takeoff time, delaying the aircraft from de-icing. In some aspects, informed de-icing includes, in response to identifying an aircraft scheduled for de-icing within a caution threshold of a scheduled takeoff time and to determining that a push time cannot be delayed: evaluating an effect of repeating a de-icing operation for the aircraft on flight operations; and in response to the effect exceeding an impact threshold: rescheduling the de-icing operation for the aircraft based on a new takeoff time.

An aircraft heating assembly including an internal combustion engine having a liquid coolant system distinct from any fuel and lubricating system of the engine and including cooling passages in the internal combustion engine for circulating a liquid coolant from a coolant inlet to a coolant outlet, a coolant circulation path outside of the internal combustion engine and in fluid communication with the coolant inlet and the coolant outlet, and a heating element in heat exchange relationship with a portion of the aircraft to be heated. The coolant circulation path extends through a heat exchanger configured to remove a portion of a waste heat from the liquid coolant. The heating element is in heat exchange relationship with the coolant circulation path to receive another portion of the waste heat therefrom. A method of heating a portion of an aircraft is also discussed.

The disclosure relates to the methods and devices for wind turbine blade mechanical de-icing. The proposed method for de-icing of a wind turbine blade, includes the steps of positioning a wind turbine blade in a substantially horizontal position; pulling a line one over the wind turbine blade; and pulling both ends of the line one sideways parallel to the wind turbine blade. The line one can be provided with a line two attached to it and the method may further include the step of pulling up a joint connecting the lines one and two to the leading edge and using the line one to slide the joint position over the leading edge of the blade. According to an embodiment an elastic sliding plate configured to prevent line entanglement may be attached at the line one and two joint position.

There are provided methods and systems for a towbar-less aircraft tow. The towbar-less aircraft tow includes a chassis configured to receive thereon at least a portion of an aircraft main landing gear assembly. The towbar-less aircraft tow further includes a lifting mechanism coupled to the chassis, configured to raise the aircraft main landing gear assembly by a variable amount. The towbar-less aircraft tow further includes a propulsion system coupled to the chassis, configured to move the towbar-less aircraft tow in a direction along a trajectory. The towbar-less aircraft tow further includes an electrical storage system coupled to the chassis. The towbar-less aircraft tow further includes a power connector mounted to said electrical storage system, configured to connect with an aircraft de-icing system for communicating electrical power from the towbar-less aircraft tow to the aircraft de-icing system during aircraft de-icing.

There are provided methods and systems for a towbar-less aircraft tow. The towbar-less aircraft tow includes a chassis configured to receive thereon at least a portion of an aircraft main landing gear assembly. The towbar-less aircraft tow further includes a lifting mechanism coupled to the chassis, configured to raise the aircraft main landing gear assembly by a variable amount. The towbar-less aircraft tow further includes a propulsion system coupled to the chassis, configured to move the towbar-less aircraft tow in a direction along a trajectory. The towbar-less aircraft tow further includes an electrical storage system coupled to the chassis. The towbar-less aircraft tow further includes a power connector mounted to said electrical storage system, configured to connect with an aircraft de-icing system for communicating electrical power from the towbar-less aircraft tow to the aircraft de-icing system during aircraft de-icing.

The disclosure relates to the methods and devices for wind turbine blade mechanical de-icing. The proposed method for de-icing of a wind turbine blade, includes the steps of positioning a wind turbine blade in a substantially horizontal position; pulling a line one over the wind turbine blade; and pulling both ends of the line one sideways parallel to the wind turbine blade. The line one can be provided with a line two attached to it and the method may further include the step of pulling up a joint connecting the lines one and two to the leading edge and using the line one to slide the joint position over the leading edge of the blade. According to an embodiment an elastic sliding plate configured to prevent line entanglement may be attached at the line one and two joint position.