Antenna assembly with a multi-band radome and associated methods
An antenna assembly is for a fuselage of an aircraft and includes a first satellite antenna operable in a first frequency range, a second satellite antenna operable in a second frequency range, and a radome covering the first and second satellite antennas. The radome includes, in stacked relation, an inner skin having a quartz fabric and epoxy resin, an inner core having epoxy syntactic foam, a center laminate having quartz fabric and epoxy resin, an outer core having epoxy syntactic foam, and an outer skin having quartz fabric and epoxy resin. A fairing mounts the radome to the fuselage of the aircraft.
1. An antenna assembly for a fuselage of an aircraft comprising:
a first satellite antenna operable in a first frequency range;
a second satellite antenna operable in a second frequency range;
a radome covering said first and second satellite antennas and comprising, in stacked relation,
an inner skin comprising a quartz fabric and epoxy resin,
an inner core comprising epoxy syntactic foam,
a center laminate comprising quartz fabric and epoxy resin,
an outer core comprising epoxy syntactic foam, and
an outer skin comprising quartz fabric and epoxy resin; and
a fairing for mounting said radome to the fuselage of the aircraft.
2. The antenna assembly according to claim 1 wherein said inner skin has a thickness in a range of 0.005 to 0.025 inches.
3. The antenna assembly according to claim 1 wherein said inner core has a thickness in a range of 0.040 to 0.090 inches.
4. The antenna assembly according to claim 1 wherein said center laminate has a thickness in a range of 0.100 to 0.150 inches.
5. The antenna assembly according to claim 1 wherein said outer core has a thickness in a range of 0.040 to 0.090 inches.
6. The antenna assembly according to claim 1 wherein said outer skin has a thickness in a range of 0.005 to 0.025 inches.
7. The antenna assembly according to claim 1 wherein said radome further comprises an outer coating adjacent said outer skin.
8. The antenna assembly according to claim 7 wherein said outer coating has a thickness in a range of 0.002 to 0.008 inches.
9. The antenna assembly according to claim 7 wherein said outer coating comprises an aliphatic polyurethane.
10. The antenna assembly according to claim 1 further comprising at least one lightning protection trace carried by said radome.
11. The antenna assembly according to claim 1 wherein said first satellite antenna is operable in a frequency range within 12 to 27 GHz; and wherein said second satellite antenna is operable in a frequency range within 27 to 40 GHz.
12. An antenna assembly for a fuselage of an aircraft comprising:
a first satellite antenna operable in a first frequency range within 12 to 27 GHz;
a second satellite antenna operable in a second frequency range within 27 to 40 GHz;
a radome covering said first and second satellite antennas and comprising, in stacked relation,
an inner skin comprising a quartz fabric and epoxy resin,
an inner core comprising epoxy syntactic foam,
a center laminate comprising quartz fabric and epoxy resin,
an outer core comprising epoxy syntactic foam,
an outer skin comprising quartz fabric and epoxy resin, and
an outer coating comprises an aliphatic polyurethane; and
a fairing for mounting said radome to the fuselage of the aircraft.
13. The antenna assembly according to claim 12 wherein said inner skin has a thickness in a range of 0.005 to 0.025 inches.
14. The antenna assembly according to claim 12 wherein said inner core has a thickness in a range of 0.040 to 0.090 inches.
15. The antenna assembly according to claim 12 wherein said center laminate has a thickness in a range of 0.100 to 0.150 inches.
16. The antenna assembly according to claim 12 wherein said outer core has a thickness in a range of 0.040 to 0.090 inches.
17. The antenna assembly according to claim 12 wherein said outer skin has a thickness in a range of 0.005 to 0.025 inches.
18. The antenna assembly according to claim 12 wherein said outer coating has a thickness in a range of 0.002 to 0.008 inches.
19. The antenna assembly according to claim 12 further comprising at least one lightning protection trace carried by said radome.
20. An antenna assembly for a fuselage of an aircraft comprising:
at least one satellite antenna operable in at least one frequency range between 12 to 40 GHz; and
a radome covering said at least one satellite antenna and comprising, in stacked relation,
an inner skin comprising a quartz fabric and epoxy resin,
an inner core comprising epoxy syntactic foam,
a center laminate comprising quartz fabric and epoxy resin,
an outer core comprising epoxy syntactic foam, and
an outer skin comprising quartz fabric and epoxy resin.
21. The antenna assembly according to claim 20 wherein said inner skin has a thickness in a range of 0.005 to 0.025 inches; said inner core has a thickness in a range of 0.040 to 0.090 inches; said center laminate has a thickness in a range of 0.100 to 0.150 inches; said outer core has a thickness in a range of 0.040 to 0.090 inches; and said outer skin has a thickness in a range of 0.005 to 0.025 inches.
22. The antenna assembly according to claim 20 wherein said radome further comprises an outer coating adjacent said outer skin and comprising an aliphatic polyurethane.
23. The antenna assembly according to claim 22 wherein said outer coating has a thickness in a range of 0.002 to 0.008 inches.
24. The antenna assembly according to claim 20 further comprising at least one lightning protection trace carried by said radome.
25. The antenna assembly according to claim 20 wherein said at least one satellite antenna comprises a first satellite antenna operable in a first frequency range within 12 to 27 GHz; and a second satellite antenna operable in a second frequency range within 27 to 40 GHz.
26. A method for providing an antenna assembly on a fuselage of an aircraft comprising:
mounting at least one satellite antenna operable in at least one frequency range between 12 to 40 GHz on the fuselage of the aircraft;
providing a radome to cover said at least one satellite antenna and comprising, in stacked relation,
an inner skin comprising a quartz fabric and epoxy resin,
an inner core comprising epoxy syntactic foam,
a center laminate comprising quartz fabric and epoxy resin,
an outer core comprising epoxy syntactic foam, and
an outer skin comprising quartz fabric and epoxy resin; and
mounting said radome to the fuselage of the aircraft.
27. The method according to claim 26 wherein said inner skin has a thickness in a range of 0.005 to 0.025 inches; said inner core has a thickness in a range of 0.040 to 0.090 inches; said center laminate has a thickness in a range of 0.100 to 0.150 inches; said outer core has a thickness in a range of 0.040 to 0.090 inches; and said outer skin has a thickness in a range of 0.005 to 0.025 inches.
28. The method according to claim 26 wherein said radome further comprises an outer coating adjacent said outer skin and comprising an aliphatic polyurethane.
29. The method according to claim 28 wherein said outer coating has a thickness in a range of 0.002 to 0.008 inches.
30. The method according to claim 26 further comprising providing at least one lightning protection trace carried by said radome.
31. The method according to claim 26 wherein said at least one satellite antenna comprises a first satellite antenna operable in a first frequency range within 12 to 27 GHz; and a second satellite antenna operable in a second frequency range within 27 to 40 GHz.