Abstract: An antenna arrangement for an aircraft includes an antenna unit, a radome structure covering the antenna unit, and a mounting device for mounting the antenna arrangement to an outer surface of an aircraft component. The antenna unit is mounted to or integrally formed with the radome structure and the radome structure is mounted to or integrally formed with the mounting device.

Abstract: An opening completely arranged in a skin panel of a structural portion of the aircraft is formed in the outer skin of the skin panel, and for each of the skin panels with one of the openings, an associated structural element of an electronic arrangement is separately provided. The structural element is designed and detachably fastened by a frame thereof to the outer skin in the corresponding skin panel on the side of the outer skin opposite the outer surface, such that it seals the corresponding opening such that the skin panel has at least the same pressure-tightness and at least the same strength relative to tension, pressure and shear forces which act in the skin panel in the extension direction of the outer skin as the same skin panel without the corresponding opening.

Abstract: An aircraft comprising a skin, a multiplicity of antenna arrangements, each of which is arranged in a different region of a corresponding multiplicity of mutually spaced regions of the skin and comprises an antenna element that is arranged and configured to emit radio waves into a surrounding area of the aircraft, and a multiplicity of visual indicators, each of which is assigned to a different antenna arrangement of the antenna arrangements. Each of the visual indicators is arranged on the skin or on the antenna arrangement in the region of the skin in which the assigned antenna arrangement is situated in such a manner that it is visible from outside the aircraft and emits light during operation in an on state.

Abstract: An antenna arrangement for an aircraftincludes an antenna unit, a radome structure covering the antenna unit, and a mounting device for mounting the antenna arrangement to an outer surface of an aircraft component. The antenna unit is mounted to or integrally formed with the radome structure and the radome structure is mounted to or integrally formed with the mounting device.

Abstract: An opening completely arranged in a skin panel of a structural portion of the aircraft is formed in the outer skin of the skin panel, and for each of the skin panels with one of the openings, an associated structural element of an electronic arrangement is separately provided. The structural element is designed and detachably fastened by a frame thereof to the outer skin in the corresponding skin panel on the side of the outer skin opposite the outer surface, such that it seals the corresponding opening such that the skin panel has at least the same pressure-tightness and at least the same strength relative to tension, pressure and shear forces which act in the skin panel in the extension direction of the outer skin as the same skin panel without the corresponding opening.

Abstract: An antenna arrangement for an aircraft for fastening to an outer side of an exterior skin of the aircraft has a body and side wall sections and a connecting section. The body is U-shaped or H-shaped if viewed from a predefined direction and can be flowed through with a low aerodynamic drag by a flow along the predefined direction. The antenna arrangement has one or more antennas in the form of a printed circuit board and of which each is fastened to the body and is fastenable directly to the outer side of the aircraft exterior skin at two first edges of the side wall sections which form two free ends of the U-shape or H-shape on a first side of the connecting section or, for the U-shape, on the connecting section and/or regions of the side wall sections, which regions adjoin the connecting section directly as the predefined direction is parallel to the flow direction during flight.

Abstract: A supervision system for an aircraft for monitoring a safe charging of portable electrical devices of a passenger who may be in an attentive or an inattentive state, comprising a passenger seat, a power supply station assigned to the seat and used to supply electrical power to the portable electrical device, the portable electrical device being connected to the power supply station, a camera, which detects the state of the passenger situated on the seat, and an arrangement to distinguish whether the passenger is in an attentive or inattentive state. A method for safe charging of portable electrical devices is also presented and described, comprising the steps of detecting a passenger with a camera, analyzing whether the passenger is in an attentive state or in an inattentive state, and, if the passenger is in an attentive state, supplying a power supply station with electrical power to be provided to a portable electrical device connected to the power supply station.

Abstract: An aircraft comprising a skin, a multiplicity of antenna arrangements, each of which is arranged in a different region of a corresponding multiplicity of mutually spaced regions of the skin and comprises an antenna element that is arranged and configured to emit radio waves into a surrounding area of the aircraft, and a multiplicity of visual indicators, each of which is assigned to a different antenna arrangement of the antenna arrangements. Each of the visual indicators is arranged on the skin or on the antenna arrangement in the region of the skin in which the assigned antenna arrangement is situated in such a manner that it is visible from outside the aircraft and emits light during operation in an on state.

Abstract: An antenna arrangement for an aircraft for fastening to an outer side of an exterior skin of the aircraft has a body and side wall sections and a connecting section. The body is U-shaped or H-shaped if viewed from a predefined direction and can be flowed through with a low aerodynamic drag by a flow along the predefined direction. The antenna arrangement has one or more antennas in the form of a printed circuit board and of which each is fastened to the body and is fastenable directly to the outer side of the aircraft exterior skin at two first edges of the side wall sections which form two free ends of the U-shape or H-shape on a first side of the connecting section or, for the U-shape, on the connecting section and/or regions of the side wall sections, which regions adjoin the connecting section directly as the predefined direction is parallel to the flow direction during flight.

Abstract: A mobile satellite communication gateway includes an aircraft communication interface and a satellite communication interface. The aircraft communication interface is designed to make a bidirectional data connection between the satellite communication gateway and a data network of an aircraft, while the satellite communication interface is designed to make a bidirectional data connection between the satellite communication gateway and a satellite communication network. The satellite communication gateway includes a signal processing device, which is coupled to the aircraft communication interface and the satellite communication interface and which is designed to interchange data between the data network of the aircraft and the satellite communication network.

Abstract: A system for wireless distribution of aircraft data, avionics parameters or control commands between a standardized aircraft interface point and other systems, including a portable in-flight entertainment (IFE) server. The system comprises an aircraft data system with avionics buses for carrying at least one of aircraft data, avionics parameters or control commands. A first module is configured to directly interface with the avionics buses, in order to read/write data. A second module is configured to combine/adapt the data and generate signals of the combined/adapted data. A third module is configured to transmit the signals from the second module via wireless standard protocols towards the portable IFE server. The IFE server is configured to receive the signals from the third module.

Abstract: An aircraft antenna assembly has a support element having a first and a second surface on opposite sides, an antenna element arranged on or in the support element, and a sealing device. The first surface and the sealing device are configured such that the antenna assembly is arranged on an outer skin section of an aircraft such that the first surface faces the outer skin section, the sealing device is situated between the support element and the outer skin section, and a cavity is defined by the sealing device, the outer skin section and the first surface. The support element or the sealing device y has a flow channel having a first and a second opening at opposite ends, the flow channel connecting the cavity and the environment and opening into the cavity at the first opening and opening into the environment at the second opening.

Abstract: A system for detecting radome damage. The system comprises a sensor unit and a processing unit. The sensor unit is configured to continuously register external impacts on a radome. The processing unit is electrically connected to the sensor unit. The processing unit is configured to compare the external impacts registered by the sensor unit with reference data. The processing unit is further formed to determine, based on the comparison, whether damage to the radome has occurred due to one or more events associated with the external impacts. Furthermore, a radome comprising the system, a flying object and a corresponding method are provided.

Abstract: A mobile satellite communication gateway includes an aircraft communication interface and a satellite communication interface. The aircraft communication interface is designed to make a bidirectional data connection between the satellite communication gateway and a data network of an aircraft, while the satellite communication interface is designed to make a bidirectional data connection between the satellite communication gateway and a satellite communication network. The satellite communication gateway includes a signal processing device, which is coupled to the aircraft communication interface and the satellite communication interface and which is designed to interchange data between the data network of the aircraft and the satellite communication network.

Abstract: A supervision system for an aircraft for monitoring a safe charging of portable electrical devices of a passenger who may be in an attentive or an inattentive state, comprising a passenger seat, a power supply station assigned to the seat and used to supply electrical power to the portable electrical device, the portable electrical device being connected to the power supply station, a camera, which detects the state of the passenger situated on the seat, and an arrangement to distinguish whether the passenger is in an attentive or inattentive state. A method for safe charging of portable electrical devices is also presented and described, comprising the steps of detecting a passenger with a camera, analyzing whether the passenger is in an attentive state or in an inattentive state, and, if the passenger is in an attentive state, supplying a power supply station with electrical power to be provided to a portable electrical device connected to the power supply station.

Abstract: A system for wireless distribution of aircraft data, avionics parameters or control commands between a standardized aircraft interface point and other systems, including a portable in-flight entertainment (IFE) server. The system comprises an aircraft data system with avionics buses for carrying at least one of aircraft data, avionics parameters or control commands. A first module is configured to directly interface with the avionics buses, in order to read/write data. A second module is configured to combine/adapt the data and generate signals of the combined/adapted data. A third module is configured to transmit the signals from the second module via wireless standard protocols towards the portable IFE server. The IFE server is configured to receive the signals from the third module.

Abstract: A system for wireless distribution of aircraft data, avionics parameters or control commands between a standardized aircraft interface point and other systems, including a portable in-flight entertainment (IFE) server. The system comprises an aircraft data system with avionics buses for carrying at least one of aircraft data, avionics parameters or control commands. A first module is configured to directly interface with the avionics buses, in order to read/write data. A second module is configured to combine/adapt the data and generate signals of the combined/adapted data. A third module is configured to transmit the signals from the second module via wireless standard protocols towards the portable IFE server. The IFE server is configured to receive the signals from the third module.

Abstract: An aircraft antenna assembly has a support element having a first and a second surface on opposite sides, an antenna element arranged on or in the support element, and a sealing device. The first surface and the sealing device are configured such that the antenna assembly is arranged on an outer skin section of an aircraft such that the first surface faces the outer skin section, the sealing device is situated between the support element and the outer skin section, and a cavity is defined by the sealing device, the outer skin section and the first surface. The support element or the sealing device y has a flow channel having a first and a second opening at opposite ends, the flow channel connecting the cavity and the environment and opening into the cavity at the first opening and opening into the environment at the second opening.

Abstract: In a method for detecting damage to a component of an aircraft, having an unpressurized first area and a pressurized second area, at least one theoretical pressure parameter, characteristic of a theoretical pressure in the unpressurized first area, a theoretical pressure in the pressurized second area or a theoretical pressure difference between the unpressurized first area and the pressurized second area, is determined. At least one actual pressure parameter, characteristic of an actual pressure in the unpressurized first area, an actual pressure in the pressurized second area or an actual pressure difference between the unpressurized first area and the pressurized second area, is recorded. The theoretical pressure parameter is compared with the actual pressure parameter. Damage to a component of the aircraft causing a compression of the unpressurized first area is detected when a difference between the theoretical pressure parameter and the actual pressure parameter exceeds a threshold value.

Abstract: A method for automatically controlling a transmission mode of an aircraft while the aircraft is communicating with a satellite is presented. In method step A), a transmission signal is generated by a transmission apparatus. In method step B), the transmission signal is transmitted to the satellite via an antenna of the aircraft that is set up to communicate with the satellite. In method step C), it is detected when a person stays inside or at an edge of a safety zone around the antenna by an apparatus for receiving radiation from the person via the antenna if the person is inside or at the edge of the safety zone. In method step D), the transmission of the transmission signal is automatically stopped or the transmission power of the transmission signal is automatically reduced by the transmission apparatus.