Abstract: A structural component for an aircraft including at least one heatable component section having a layer structure including an inner base structure, at least one heating layer having carbon allotropes embedded in a matrix material, at least one first group of consecutive layers including at least one anode layer, at least one first insulating layer, and at least one cathode layer having an electroactive coating. The first group of layers are arranged between the inner base structure and the at least one heating layer, and at least one protective layer is arranged outside the heating layer. The first group of layers constitute a structural battery. The at least one anode layer and the at least one cathode layer are electrically connectable with the heating layer.

Abstract: A multifunctional thermal and acoustic insulation system having a multilayer structure and a plurality of functional components formed integrally and non-exchangeably with the multilayer structure. The multilayer structure has a thermal and acoustic damping performance and comprises, in a stacked arrangement, a continuous first outer layer, a core layer and a continuous second outer layer. The core layer is between the outer layers so that the outer layers cover the core layer at least on opposite sides thereof. Functions of the functional components are related to at least one of the thermal and the acoustic damping performance of the multilayer structure and the functional components are provided on a first outer layer side of the core layer and/or on a second outer layer side of the core layer.

Abstract: 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.

Abstract: A system and a method for evaluating performance of a porous skin of an aircraft including the porous skin, and a boundary layer control system. The performance evaluation system includes a first sensor providing data related to the performance of the porous skin. The performance evaluation system is further configured to clean the porous skin based on the performance of the porous skin determined using the data received from the first sensor in order to ensure that the porous skin operates at its maximum capability.

Abstract: A method, comprising: providing a light source, a high contrast providing object, and an image acquisition device; emitting a light beam from the light source through the high contrast providing object, a transparent object and a surface of the transparent object toward the image acquisition device; exposing the surface of the transparent object to icing conditions such that a layer of ice is formed by ice accretion on the surface, wherein the light beam traverses the layer of ice after having traversed the transparent object; acquiring a series of images over time of the high contrast providing object using the image acquisition device; determining blur occurring in the series of images over the time; and quantifying the loss of visibility over the time through the transparent object on the basis of the determined blur.

Abstract: A system and a method for evaluating performance of a porous skin of an aircraft including the porous skin, and a boundary layer control system. The performance evaluation system includes a first sensor providing data related to the performance of the porous skin. The performance evaluation system is further configured to clean the porous skin based on the performance of the porous skin determined using the data received from the first sensor in order to ensure that the porous skin operates at its maximum capability.

Abstract: A structural component for an aircraft including at least one heatable component section having a layer structure including an inner base structure, at least one heating layer having carbon allotropes embedded in a matrix material, at least one first group of consecutive layers including at least one anode layer, at least one first insulating layer, and at least one cathode layer having an electroactive coating. The first group of layers are arranged between the inner base structure and the at least one heating layer, and at least one protective layer is arranged outside the heating layer. The first group of layers constitute a structural battery. The at least one anode layer and the at least one cathode layer are electrically connectable with the heating layer.

Abstract: A resistive heated aircraft component, comprising a fiber reinforced polymer surface and further comprising a graphene paper having first and second opposite faces, a pair of electrodes connected to the graphene paper, the graphene paper and the pair of electrodes being configured to conduct an electrical current such that the graphene paper produces heat, the second face of the graphene paper being located towards the fiber reinforced polymer surface of the aircraft, and a protective layer located on the first face of the graphene paper.

Abstract: A structural component for an aircraft includes at least one heatable component portion. The heatable component portion has a layered construction with an inner base structure, a first insulating layer arranged outside the inner base structure, a functional layer of carbon allotropes embedded in a matrix material, which is arranged outside the first insulating layer, and at least one protective layer arranged outside the functional layer. The structural component also includes an electrical connection device connected to the functional layer for selectively applying an electrical current to the functional layer to heat the functional layer.

Abstract: An analysis system for quantitative blockage analysis of a grid in icing conditions includes an optical sensor, a processor unit and a display unit. The optical sensor is configured to continuously capture a series of pictures of a grid and to submit each picture to the processor unit. The processor unit is configured to determine a color scale value for each of a number of areas in a field of each picture, to count a number of areas in a particular field of a particular picture that show a color scale value greater than an absolute reference value, to calculate a time remaining until a critical icing condition is reached based on an icing behavior model of the grid, to calculate a warning signal based on the time remaining until the critical icing condition of the grid is reached, and to display the warning signal on the display unit.