# US 2019/0245264 A1 · Antenna Assembly For An Aircraft > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2019/0245264 A1 - Document ID: US20190245264A1 - Status: Published application - Kind: A1 - Application number: 16/263,360 - Filed: 2019-01-31 - Published: 2019-08-08 - Earliest claimed: 2018-02-07 - Assignees: Airbus Operations GmbH - Applicants: Airbus Operations GmbH - Inventors: Christian Schaupmann; Markus Altmann - Web page: https://patentgrep.com/patent/US20190245264A1 ## CPC - H01Q 1/286: {substantially flush mounted with the skin of the craft} - H01Q 1/02: Arrangements for de-icing; Arrangements for drying-out {; Arrangements for cooling; Arrangements for preventing corrosion} - H01Q 1/085: {Flexible aerials; Whip aerials with a resilient base} - H01Q 9/0407: {Substantially flat resonant element parallel to ground plane, e.g. patch antenna (dipole H01Q9/285; monopole H01Q9/40)} - H01Q 21/065: {Patch antenna array} - H01Q 21/08: the units being spaced along or adjacent to a rectilinear path {(waveguide fed H01Q21/0037)} - H01Q: ANTENNAS, i.e. RADIO AERIALS (radiators or antennas for microwave heating H05B6/72) ## 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. ## Claims ### Claim 1 An antenna assembly for an aircraft, comprising: a support element having a first and a second surface on opposite sides of the support element; at least one antenna element arranged on or in the support element; and a sealing device, wherein the first surface and the sealing device are configured in such a way that the antenna assembly is arranged in such a way on an outer skin section of an aircraft that the first surface faces the outer skin section, the sealing device is situated between the support element and the outer skin section, and at least one cavity is defined by the sealing device, the outer skin section and the first surface, and the support element or the sealing device for each of the cavities has at least one flow channel having a first and a second opening at opposite ends of the flow channel, the flow channel connecting the corresponding cavity and the environment of the antenna assembly to one another after the arrangement of the antenna assembly on the outer skin section and opening into the corresponding cavity at the first opening and opening into the environment at the second opening. ### Claim 2 (depends on 1) The antenna assembly according to claim 1, wherein the second opening of at least one of the flow channels is formed on a line section in which part of the flow channel extends and which projects from the support element or the sealing device into the environment after the arrangement of the antenna assembly on the outer skin section. ### Claim 3 (depends on 1) The antenna assembly according to claim 1, wherein the second opening of at least one of the flow channels is formed in the second surface or the sealing device. ### Claim 4 (depends on 1) The antenna assembly according to claim 1, wherein the support element is a sheet-like element. ### Claim 5 (depends on 1) The antenna assembly according to claim 1, wherein the support element is flexible. ### Claim 6 (depends on 1) The antenna assembly according to claim 1, wherein the first surface has at least one recess, each of which defines one of the cavities after the arrangement of the antenna assembly on the outer skin section. ### Claim 7 (depends on 5) The antenna assembly according to claim 5, wherein the support element has a rigid insert for each of the recesses, said insert defining the respective recess. ### Claim 8 (depends on 1) The antenna assembly according to claim 1, wherein each of the at least one antenna elements is a patch antenna and/or a Ku or Ka antenna. ### Claim 9 (depends on 1) The antenna assembly according to claim 1, wherein each of the at least one antenna elements is printed onto the support element or onto a part thereof. ### Claim 10 (depends on 1) The antenna assembly according to claim 1, wherein the second surface has at least one raised portion, in which at least one electric lead and/or at least one fastening element is arranged or which is formed by at least one electric lead and/or at least one fastening element, and wherein the second opening of at least one of the flow channels is arranged on the raised portion or directly adjacent to the raised portion. ### Claim 11 (depends on 1) The antenna assembly according to claim 1, wherein one or more thermally or electrically conductive elements, each of which forms part of the first surface or projects from the first surface, is/are provided on or in the support element, with the result that the thermally or electrically conductive elements are in contact with the outer skin section after the arrangement of the support element on the outer skin section. ### Claim 12 (depends on 1) The antenna assembly according to claim 1, further comprising an outer skin section of an aircraft, wherein the support element is arranged on the outer skin section in such a way 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. ### Claim 13 (depends on 12) The antenna assembly according to claim 12, wherein one or more holes, through which cables are passed or can be passed, is/are provided in the outer skin section, and wherein the holes are arranged outside that region of the outer skin section which is covered by the support element. ### Claim 14 (depends on 12) The antenna assembly according to claim 12, wherein a recess, in which the antenna assembly is arranged, is provided in the outer skin section. ### Claim 15 (depends on 1) An aircraft having an outer skin and an antenna assembly according to claim 1, wherein the support element is arranged in such a way on an outer skin section of the outer skin that the first surface faces the outer skin section, the sealing device is situated between the support element and the outer skin section, and the at least one cavity is defined by the sealing device, the outer skin section and the first surface.