A moisture control apparatus for use with a structure within an aircraft, the structure including an upper surface, the moisture control apparatus comprising: a moisture absorbing layer including a moisture absorbing material, the layer including a leading edge, a trailing edge, side edges, an upper surface, and, a lower surface; and, a reverse-bevel defined along the leading edge of the layer, wherein the reverse-bevel and the upper surface of the structure define a gutter configured to retain moisture flowing along the upper surface of the structure.

The present disclosure provides a method of allocating shared radio resources in a spectrum shared system (SSS), the method including: obtaining, by a system controller of the SSS, identification information from at least one radio service device of the SSS and a node unit of a distributed antenna system (DAS); determining, by the system controller of the SSS, whether the at least one radio service device interoperates with the DAS based on the identification information; and allocating, by the system controller of the SSS, the shared radio resources to the at least one radio service device and the DAS, respectively, based on a result of the determining of interoperating.

The present disclosure provides a method of allocating shared radio resources in a spectrum shared system (SSS), the method including: obtaining, by a system controller of the SSS, identification information from at least one radio service device of the SSS and a node unit of a distributed antenna system (DAS); determining, by the system controller of the SSS, whether the at least one radio service device interoperates with the DAS based on the identification information; and allocating, by the system controller of the SSS, the shared radio resources to the at least one radio service device and the DAS, respectively, based on a result of the determining of interoperating.

A cabin module for an aircraft comprises a section which has an upward-facing surface in an installed state of the cabin module, wherein the upward-facing surface of the section comprises an integrated drainage channel. An aircraft furthermore comprises at least one such cabin module.

A honeycomb thermal insulation structure may comprise a first facesheet, a second facesheet, and a honeycomb core between the first facesheet and the second facesheet. The honeycomb core may include a plurality of honeycomb unit cells each composed of walls having a height and spaced by a distance. The walls of the honeycomb cells may have perforations. The honeycomb thermal insulation structure may further comprise a non-convective gas loaded in the honeycomb unit cells between the walls. A flow of the gas through the perforations may be substantially absent.

An aircraft may include a fuselage, and a moisture accumulation prevention system that prevents moisture from accumulating on at least one structure within the fuselage. The moisture accumulation prevention system includes at least one ultrasonic element coupled to the structure(s). The ultrasonic element(s) operates at a frequency that prevents moisture particles from adhering to a surface of the structure(s).

Systems and methods are provided for insulation and moisture drainage. One exemplary embodiment is a bay blanket configured to insulate an aircraft. The bay blanket includes insulation, and a first trough running along a length of a leftward face of the insulation and adapted to receive water draining from an outboard side of the insulation. The first trough includes sidewalls that meet at an inboard side of the insulation and extend from the inboard side to the outboard side. The bay blanket also includes a second trough running along a length of a rightward face of the insulation and adapted to receive water draining from the outboard side. The second trough includes sidewalls that meet at the inboard side and extend from the inboard side to the outboard side.

A moisture wicking heat shrink sleeve for aircraft cabin moisture control incorporates a heat shrinkable tube of predetermined length receivable over a structural member. A moisture absorbing layer is adhered to a surface of the heat shrinkable tube with the heat shrinkable tube and adhered moisture absorbing layer configured for radial contraction from a first expanded condition to a second contracted condition upon application of heat.

An insulation component to be attached to a fuselage structure of an aircraft. The insulation component extends in a planar manner, and at least one peripheral recess, running transversely to the at least one longitudinal recess, is formed in a first surface of the insulation component configured to receive a respective associated peripheral support of the fuselage structure.

Systems and methods are provided for insulation and moisture drainage. One exemplary embodiment is an apparatus comprising a bay blanket configured to insulate an aircraft. The bay blanket includes insulation, and a first waterproof lip that protrudes from the insulation in an outboard direction towards a frame of the aircraft and extends along a length of a leftward side of the bay blanket. The bay blanket also includes a second waterproof lip that protrudes from the insulation in an outboard direction towards the frame of the aircraft along a length of a rightward side of the bay blanket.