Antenna embedded in a radome
An aircraft-mounted mobile communicator for communicating with one or more satellites or base stations is disclosed. The aircraft-mounted mobile communicator includes a radome structure and one or more antenna elements embedded within or proximate to a shell of the radome structure that maximizes an aperture of the one or more antenna elements, wherein the one or more antenna elements are configured to operate over one or more frequency bands.
1. A mobile communicator mounted on an aircraft for communicating with one or more satellites or base stations, the mobile communicator comprising:
a radome structure that mounts externally to a substrate, the substrate being one of a fuselage, a wing, or a vertical stabilizer of the aircraft, the radome structure including a radome shell having a non-flat geometry relative to the substrate such that a space is formed between the radome shell and the substrate; and
one or more antenna elements embedded within the formed space in the radome structure and forming a gap between the one or more antenna elements and the radome shell, wherein the gap is minimized via the one or more antenna elements being contoured according to the non-flat radome shell of the radome, such that the one or more antenna elements exhibit the non-flat geometry relative to the substrate to have a substantially constant distance from the radome shell and a varying distance from the substrate, wherein the one or more antenna elements are configured to operate over one or more frequency bands.
2. The mobile communicator of claim 1 , wherein the one or more antenna elements are configured to operate as an electronically steered antenna (ESA).
3. The mobile communicator of claim 1 , wherein the one or more antenna elements are configured to operate as phased-array antenna.
4. The mobile communicator of claim 1 , wherein the one or more frequency bands comprises a K a band, a K u band, a V band, an L 1 band, or an L 2 band.
5. The mobile communicator of claim 1 , wherein the one or more frequency bands comprises (i) 849-851 MHz and 894-896 MHz or (ii) 1,980-1,995 MHz and 2,170-2,185 MHz.
6. The mobile communicator of claim 1 , wherein the one or more antenna elements comprise:
a first layer of conducting flexible textiles;
a second layer of non-conducting flexible textiles acting as a dielectric substrate, and a third layer of conducting flexible textiles acting as a ground plane.
7. The mobile communicator of claim 6 , wherein the first layer further comprises one or more electrical components providing an electrical feed to the one or more antenna elements.
8. The mobile communicator of claim 1 , wherein the radome structure includes one or more openings for receiving the one or more antenna elements.
9. The mobile communicator of claim 1 , wherein the gap between the one or more antenna elements and the radome shell of the radome structure is filled with a dielectric filler material over a top surface of the one or more antenna elements.
10. An aircraft comprising:
a fuselage;
a pair of wings attached to the fuselage;
a vertical stabilizer; and
a mobile communicator for communicating with one or more satellites or base stations, the mobile communicator comprising one or more antenna elements embedded within a radome structure,
wherein the one or more antenna elements are configured to operate over one or more frequency bands, and wherein the radome structure mounts externally to a substrate, the substrate being one of the fuselage, at least one of the wings, or the vertical stabilizer of the aircraft, the radome structure including a radome shell having a non-flat geometry relative to the substrate such that a space is formed between the radome shell and the substrate, wherein the one or more antenna elements are embedded within the formed space in the radome structure to form a gap between the one or more antenna elements and the radome shell, such that the one or more antenna elements exhibit the non-flat geometry relative to the substrate to have a substantially constant distance from the radome shell and a varying distance from the substrate, wherein the gap is minimized via the one or more antenna elements being contoured according to the non-flat radome shell of the radome structure.
11. The aircraft of claim 10 , wherein the one or more antenna elements are configured to operate as an electronically steered antenna (ESA).
12. The aircraft of claim 10 , wherein the one or more antenna elements are configured to operate as phased-array antenna.
13. The aircraft of claim 10 , wherein the one or more frequency bands comprises a K a band, a K u band, a V band, an L 1 band, or an L 2 band.
14. The aircraft of claim 10 , wherein the one or more frequency bands comprises (i) 849-851 MHz and 894-896 MHz or (ii) 1,980-1,995 MHz and 2,170-2,185 MHz.
15. The aircraft of claim 10 , wherein the one or more antenna elements comprise:
a first layer of conducting flexible textiles;
a second layer of non-conducting flexible textiles acting as a dielectric substrate, and
a third layer of conducting flexible textiles acting as a ground plane.
16. The aircraft of claim 15 , wherein the first layer further comprises one or more electrical components providing an electrical feed to the one or more antenna elements.
17. The aircraft of claim 10 , wherein the radome shell of the radome structure includes one or more openings for receiving the one or more antenna elements.
18. The aircraft of claim 10 , wherein the gap between the one or more antenna elements and the radome shell of the radome structure is filled with a dielectric filler material over a top surface of the one or more antenna elements.