A method includes providing a structure having a surface, treating a portion of the surface to modify a wettability of the portion of the structure, and forming at least one liquid flow path on the surface through said treating.

An environmental aspect control assembly is configured to control one more environmental aspects. The environmental aspect control assembly may include at least one aspect-controlling portion formed of one or more environmental aspect-controlling materials, and at least one shape-changing actuator operatively connected to the aspect-controlling structure(s). The shape-changing actuator(s) is configured to have a first actuator shape at a first temperature and a second actuator shape at a second temperature that differs from the first temperature. The first actuator shape causes the aspect-controlling structure(s) to form a first structural shape. The second actuator shape causes the aspect-controlling structure(s) to form a second structural shape that differs from the first structural shape.

An aircraft insulation system comprising a foil extending at a distance from an inner surface of an aircraft outer shell. An air gap is defined between the foil and the aircraft outer shell. A cabin exhaust air duct is arranged adjacent to an inner surface of the foil and being adapted to have cabin exhaust air flow through the duct.

A panel assembly (such as for an internal cabin of an aircraft) includes at least one liquid flow path formed on at least one surface through surface treatment. The at least one liquid flow path is formed in relation to at least one bank on the at least one surface. The at least one liquid flow path is configured to divert liquid to a desired location.

A water and ice detection and quantitative assessment system (WIDQAS) for moisture detection and assessment of water accumulation on an aircraft having an airframe that has at least one enclosed space within the airframe is described. The WIDQAS may include a plurality of sensors and a data measurement device. The plurality of sensors may be arranged in the at least one enclosed space within the airframe and each sensor of the plurality of sensors may be configured to detect a presence of moisture in the at least one enclosed space and generate a data measurement that is responsive to the detection of moisture in the at least one enclosed space. The data measurement device is in signal communication with the plurality of sensors and may be configured to record the data measurement for each sensor and record identifying information about the measurement during a flight of the aircraft.

The embodiments relate to reducing condensate precipitate on inner surfaces of an outer skin of an aircraft and adjacent components. The condensate precipitate is reduced by supplying dry air to an upper region of an air gap which extends between the upper region and a lower region and is disposed between the outer skin of an aircraft and an insulation arranged between a cabin wall and the outer skin of an aircraft. The dry air may be obtained with low effort and at low cost by sucking it off from the lower region of the air gap and conducted in one or more lines to the upper region of the air gap, where it is allowed to re-enter the air gap. The lines are connected to fans which create a pressure difference in the lines, which moves the dry air from the inlet opening or openings to the outlet openings.

A cargo lining assembly for an aircraft, and an aircraft section and aircraft having the same. The cargo lining assembly has a ventilation inlet and outlet arranged at different sidewalls of the cargo lining assembly, and independent therefrom an air recirculation system. Also, an aircraft section and an aircraft with such a cargo lining assembly.

An aircraft cabin portion having a cabin device module which has an upper face, a fluid-guiding element located on the upper face of the cabin device module, and a fluid collector located at a lower end of the fluid-guiding element. The fluid collector may consist substantially of a flexible material which forms a lumen for draining a fluid, wherein the lumen has an entry opening located at the lower end of the fluid-guiding element so that the fluid flows from the at least one fluid-guiding element into the lumen. Also an aircraft having such an aircraft cabin portion.

A thermal and acoustic insulation system for an aircraft, to be received between an inner surface of an aircraft primary structure, such as an aircraft fuselage structure, and a surface of a panel arrangement delimiting an aircraft cabin, the surface facing away from the aircraft cabin, comprises an insulation package and at least one sensor adapted to measure a level of humidity present in the insulation package. The insulation package comprises a core layer having a thermal and acoustic damping performance, and a packing layer enclosing the core layer. The packing layer is provided with a plurality of normally closed and selectively openable drainage openings which are actuatable to change between their normally closed state and an open state.