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 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 component for an aircraft includes at least one connection interface, wherein the connection interface is configured to simultaneously establish an electrical connection and a mechanical connection. An electrical system for an aircraft and a method for connecting components for an aircraft are disclosed.

Abstract: The disclosure herein relates to a measuring system for determining damage to components including at least one fiber-reinforced plastics material, comprising sensors that can be or are arranged on a component to be mutually spaced, the sensors distributed over a curved surface of the component in the use position. In order provide a measuring system by which it is possible to obtain fiber-reinforced plastics components economically and with reasonable outlay, and by which process parameters and/or state variables can be reliably obtained during production and operation of the component, it is proposed to provide the component with a substrate that is different from the component and on which the sensors can be or are arranged, the substrate being flexible, and for the sensors arranged on the flexible substrate to form a measuring device.

Abstract: The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, which comprises a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, a marker substance device configured to dispense a volatile marker gas to the environment when in contact with the surrounding air and being hermetically sealed from the surrounding air by the first component element, the second component element, and/or the bonding if the bonding is not damaged, and a detector device configured to detect the marker gas dispensed by the marker substance device.

Abstract: A measurement arrangement for detecting damage to components that are made of at least one fiber-reinforced plastic material, has a plurality of temperature sensors that are arrangeable or arranged on a component at a spacing from one another. In order to provide a measurement arrangement, by means of which temperature data can be cost-effectively obtained during the production and operation of a component and for it to thus be possible for damage to the component to be recorded and monitored, the plurality of temperature sensors on the component form a sensor array and a change in the thermal material properties of the component is detected by means of the sensor array.

Abstract: The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, the component device having a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, and a detector device having at least one interior space sensor device configured to measure a change in a pressure and/or a concentration of a gas surrounding the interior space sensor device. The first component element, the second component element, and the bonding confine an interior space. The interior space sensor device is arranged in the interior space.

Abstract: A method for joining structural elements to a component made of at least one fiber-reinforced plastics material, includes providing at least two structural elements made of at least one fiber-reinforced plastics material having a particular matrix; providing at least one film element made of a thermoplastic heavy-duty material; arranging the at least one film element on a surface of one of the structural elements or between surfaces to be joined of the at least two structural elements to be joined; and producing the component to be joined in a curing process.

Abstract: A method for joining structural elements to a component made of at least one fiber-reinforced plastics material, includes providing at least two structural elements made of at least one fiber-reinforced plastics material having a particular matrix; providing at least one film element made of a thermoplastic heavy-duty material; arranging the at least one film element on a surface of one of the structural elements or between surfaces to be joined of the at least two structural elements to be joined; and producing the component to be joined in a curing process.

Abstract: A measurement arrangement for detecting damage to components that are made of at least one fiber-reinforced plastic material, has a plurality of temperature sensors that are arrangeable or arranged on a component at a spacing from one another. In order to provide a measurement arrangement, by means of which temperature data can be cost-effectively obtained during the production and operation of a component and for it to thus be possible for damage to the component to be recorded and monitored, the plurality of temperature sensors on the component form a sensor array and a change in the thermal material properties of the component is detected by means of the sensor array.

Abstract: The disclosure herein relates to a measuring system for determining damage to components including at least one fiber-reinforced plastics material, comprising sensors that can be or are arranged on a component to be mutually spaced, the sensors distributed over a curved surface of the component in the use position. In order provide a measuring system by which it is possible to obtain fiber-reinforced plastics components economically and with reasonable outlay, and by which process parameters and/or state variables can be reliably obtained during production and operation of the component, it is proposed to provide the component with a substrate that is different from the component and on which the sensors can be or are arranged, the substrate being flexible, and for the sensors arranged on the flexible substrate to form a measuring device.

Abstract: A device and method for testing a fiber-composite component, which is to be processed by means of bonding, for the presence of at least one substance out of a selection of possible contaminants. A surface heating device for regional heating of a part-zone of the fiber-composite component to be bonded is performed for desorption of contaminants. A sensor array with a plurality of sensors detects contaminants in the gas phase, and a control device ascertains and signals contaminations which are found. An extractor device can be employed to extract machining dust from the fiber-composite component to a desorption device.

Abstract: The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, the component device having a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, and a detector device having at least one interior space sensor device configured to measure a change in a pressure and/or a concentration of a gas surrounding the interior space sensor device. The first component element, the second component element, and the bonding confine an interior space. The interior space sensor device is arranged in the interior space.

Abstract: The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, which comprises a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, a marker substance device configured to dispense a volatile marker gas to the environment when in contact with the surrounding air and being hermetically sealed from the surrounding air by the first component element, the second component element, and/or the bonding if the bonding is not damaged, and a detector device configured to detect the marker gas dispensed by the marker substance device.

Abstract: The invention relates to a contamination recording apparatus (12) for recording contaminations in a flowing hydraulic fluid (10) to be examined in aircraft (11a), which comprises a conveying device (14) for conveying the flowing hydraulic fluid (10), a light source (34) for exposing the hydraulic fluid (10) flowing in the conveying device (14) to light (46), and a detection device (36) for recording a fraction of the light (46) absorbed by the exposed hydraulic fluid (10), the light source (34) being formed in order to emit light (46) having a wavelength in the near-infrared range. The invention furthermore relates to a hydraulic system (11) equipped with such a contamination recording apparatus (12) and to an aircraft (11a), and also to a method for recording contaminations in a hydraulic fluid (10) flowing in a hydraulic system (11) of an aircraft (11a).

Abstract: An apparatus used for the surface examination of components. The apparatus comprises: a radiation source configured to convert at least one non-volatile substance at least partially into a gas by irradiating a sample surface of a component; and a detector unit configured to qualitatively and/or quantitatively detect the at least one substance converted into gas. A method provided for a surface examination of components. The method comprises irradiating a sample surface of a component with a radiation source configured to convert at least one non-volatile substance at least partially into a gas; and a qualitative and/or quantitative detection of the at least one substance converted into gas via a detector unit.

Abstract: A method for testing a component for contamination. The method comprises a heating of a specimen surface of the component under a measuring bell defining a measurement volume, an at least two-time measuring of a contamination of the measurement volume with at least one contaminant, and a purging of the measurement volume with gas. An apparatus for testing a component for contamination is also disclosed. The apparatus comprises a measuring bell configured to form a measurement volume about the component or contacting the component. A heating element is configured to heat at least one specimen surface of the component. A purging unit is configured to purge the measurement volume with gas. A sensor system is configured to measure a contamination of the measurement volume with at least one contaminant.

Abstract: A device used to examine layer material for contamination. The device comprises a heating device to heat a test area of the layer material and a detector device to detect at least one contaminant desorbed from the layer material. The heating device comprises at least one infra-red heating element. A method comprises heating a test area of the layer material and detecting at least one contaminant desorbed from the layer material. The heating takes place via an infra-red heating element.

Abstract: A system and method for determining the pH value of a liquid. The system and method excite the liquid molecules in the liquid by light with a predetermined wavelength and an intensity component, transmitted through the liquid in a predetermined wavelength range, of the light used for excitation is captured. This intensity component is used to produce a wavelength/intensity absorption characteristic and this absorption characteristic is related to a reference absorption characteristic associated with a specific pH value of the liquid. The system and method thus can be used to obtain drinking water from a fuel for aircraft.

Abstract: The invention relates to a contamination recording apparatus (12) for recording contaminations in a flowing hydraulic fluid (10) to be examined in aircraft (11a), which comprises a conveying device (14) for conveying the flowing hydraulic fluid (10), a light source (34) for exposing the hydraulic fluid (10) flowing in the conveying device (14) to light (46), and a detection device (36) for recording a fraction of the light (46) absorbed by the exposed hydraulic fluid (10), the light source (34) being formed in order to emit light (46) having a wavelength in the near-infrared range. The invention furthermore relates to a hydraulic system (11) equipped with such a contamination recording apparatus (12) and to an aircraft (11a), and also to a method for recording contaminations in a hydraulic fluid (10) flowing in a hydraulic system (11) of an aircraft (11a).