Radomes, aircraft and spacecraft including such radomes, and methods of forming radomes
Radomes include an outer wall having a first average thickness and an inner wall having a second average thickness that is different from the first average thickness. At least a major portion of the inner wall is separated from at least a major portion of the outer wall by a space therebetween. The outer wall may comprise a layer of ceramic matrix composite (CMC) material. Aircraft and spacecraft include such radomes. Methods of forming radomes include forming an outer wall having a first average thickness, forming an inner wall having a different second average thickness, and coupling together the inner wall and the outer wall in such a manner as to provide a space between at least a major portion of the outer wall and at least a major portion of the inner wall.
1. A radome comprising:
an outer wall comprising a layer of ceramic matrix composite (CMC) material having a first average physical thickness; and
an inner wall comprising a layer of material having a second average physical thickness differing from the first average physical thickness, the inner wall having a shape similar to a shape of the outer wall, at least a major portion of the inner wall separated from at least a major portion of the outer wall by a space between the inner wall and the outer wall.
2. The radome of claim 1 , wherein each of the outer wall and the inner wall comprises a dome, and wherein at least a portion of the inner wall is disposed within the dome of the outer wall.
3. The radome of claim 2 , wherein the space between the outer wall and the inner wall is at least substantially uniform.
4. The radome of claim 3 , wherein a physical thickness of the outer wall is at least substantially uniform.
5. The radome of claim 4 , wherein a physical thickness of the inner wall is at least substantially uniform.
6. The radome of claim 1 , wherein the second average physical thickness of the inner wall is about one-fourth (¼) or less of the first average physical thickness of the outer wall.
7. The radome of claim 6 , wherein the space has an average physical thickness about two-thirds (⅔) or less of the first average physical thickness of the outer wall.
8. The radome of claim 1 , further comprising a frit coating on at least a portion of an exterior surface of the outer wall.
9. The radome of claim 1 , wherein the ceramic matrix composite material comprises:
a ceramic matrix phase; and
a reinforcement phase comprising at least one of a plurality of fibers, a plurality of whiskers, and a plurality of particles dispersed throughout the ceramic matrix phase.
10. The radome of claim 9 , wherein the ceramic matrix composite material comprises a plurality of fibers arranged in a fabric, the fabric disposed within the ceramic matrix phase.
11. The radome of claim 9 , wherein the ceramic matrix phase comprises at least one of an oxide material, aluminum silicate, and mullite.
12. The radome of claim 11 , wherein the ceramic matrix phase comprises an oxide material selected from the group consisting of magnesium oxide (MgO), aluminum oxide (Al 2 O 3 ), silicon oxide (SiO 2 ), zirconium oxide (ZrO 2 ), titanium oxide (TiO 2 ), and yttrium oxide (Y 2 O 3 ).
13. The radome of claim 12 , wherein the reinforcement phase comprises a ceramic material.
14. The radome of claim 13 , wherein the ceramic material comprises aluminum silicate.
15. The radome of claim 1 , wherein the inner wall comprises a layer of ceramic matrix composite (CMC) material having a material composition at least substantially similar to a material composition of the ceramic matrix composite material of the outer wall.
16. The radome of claim 1 , wherein the inner wall comprises a layer of organic matrix composite material comprising:
a polymer matrix phase; and
a reinforcement phase comprising at least one of a plurality of fibers, a plurality of whiskers, and a plurality of particles dispersed throughout the polymer matrix phase.
17. The radome of claim 16 , wherein the polymer matrix phase exhibits a glass transition temperature greater than about 850° F. (454° C.).
18. The radome of claim 1 , further comprising at least one of air, nitrogen, and an inert gas within the space.
19. The radome of claim 18 , wherein the space is hermetically sealed.
20. The radome of claim 1 , wherein the radome exhibits an average insertion loss of less than about −1.5 dB for scan angles between about 15° and about 45° over a range of frequencies of electromagnetic radiation extending from a first frequency to a second frequency when the electromagnetic radiation is emitted from an antenna disposed within the radome, the second frequency being about 1.4 times the first frequency.
21. The radome of claim 1 , wherein a first average electrical thickness of the outer wall is equal to about one-half (½) of an integer multiple of a wavelength of electromagnetic radiation in the outer wall at a center of a desired range of operating wavelengths, a second average electrical thickness of the inner wall is equal to about one-eighth (⅛) of a wavelength of electromagnetic radiation in the inner wall at the center of the desired range of operating wavelengths, and an average electrical thickness of the space between the outer wall and the inner wall is between about one-fifth (⅕) and about one-tenth ( 1/10) of a wavelength of electromagnetic radiation in the space at the center of the desired range of operating wavelengths.
22. An aircraft or spacecraft comprising:
an antenna for emitting electromagnetic radiation over a range of frequencies of electromagnetic radiation extending from a first frequency to a second frequency; and
a radome at least partially covering the antenna, the radome comprising:
an outer wall comprising a layer of ceramic matrix composite (CMC) material having a first average physical thickness; and
an inner wall comprising a layer of material having a second average physical thickness differing from the first average physical thickness, the inner wall having a shape similar to a shape of the outer wall, at least a major portion of the inner wall separated from at least a major portion of the outer wall by a space between the inner wall and the outer wall.
23. The aircraft or spacecraft of claim 22 , wherein the aircraft or spacecraft comprises at least one of a missile and an aircraft.
24. The aircraft or spacecraft of claim 22 , wherein the second frequency is about 1.4 times the first frequency.
25. The aircraft or spacecraft of claim 22 , wherein the radome exhibits an average power insertion loss of less than about −1.5 dB for scan angles between about 15° and about 45° over the range of frequencies when the electromagnetic radiation is emitted by the antenna.
26. A method of forming a radome, comprising:
forming a dome-shaped outer wall having a first average physical thickness and comprising a ceramic matrix composite (CMC) material;
forming a dome-shaped inner wall having a second average physical thickness differing from the first average physical thickness;
inserting the inner wall at least partially into an area enclosed by the outer wall; and
coupling the inner wall to the outer wall and providing a space between at least a major portion of the outer wall and at least a major portion of the inner wall.
27. The method of claim 26 , further comprising configuring the outer wall and the inner wall to provide an at least substantially uniform distance between the inner wall and the outer wall when the inner wall is coupled to the outer wall.
28. The method of claim 27 , further comprising forming the outer wall to have an at least substantially uniform physical thickness.
29. The method of claim 28 , further comprising forming the inner wall to have an at least substantially uniform physical thickness.
30. The method of claim 26 , further comprising selecting the second average physical thickness of the inner wall to be about one-fourth (¼) or less of the first average physical thickness of the outer wall.
31. The method of claim 30 , further comprising configuring the outer wall and the inner wall to cause the average distance between the outer wall and the inner wall to be about two-thirds (⅔) or less of the first average physical thickness of the outer wall.
32. The method of claim 26 , further comprising forming a frit coating on at least a portion of an exterior surface of the outer wall.
33. The method of claim 26 , wherein forming the dome-shaped outer wall comprising the ceramic matrix composite material comprises dispersing a reinforcement phase comprising at least one of a plurality of fibers, a plurality of whiskers, and a plurality of particles throughout a ceramic matrix phase to form the ceramic matrix composite material.
34. The method of claim 33 , wherein dispersing the reinforcement phase throughout the ceramic matrix phase comprises embedding a fabric comprising a plurality of fibers within the ceramic matrix phase.
35. The method of claim 34 , further comprising selecting the ceramic matrix phase to comprise at least one of an oxide material, aluminum silicate, and mullite.
36. The method of claim 35 , further comprising selecting the ceramic matrix phase to comprise an oxide material selected from the group consisting of magnesium oxide (MgO), aluminum oxide (Al 2 O 3 ), silicon oxide (SiO 2 ), zirconium oxide (ZrO 2 ), titanium oxide (TiO 2 ), and yttrium oxide (Y 2 O 3 ).
37. The method of claim 35 , further comprising selecting the reinforcement phase to comprise a ceramic material.
38. The method of claim 37 , further comprising selecting the reinforcement phase to comprise aluminum silicate.
39. The method of claim 26 , wherein forming a dome-shaped inner wall comprises forming the inner wall to comprise a layer of ceramic matrix composite (CMC) material.
40. The method of claim 39 , further comprising selecting the ceramic matrix composite material of the inner wall to have a material composition at least substantially similar to a material composition of the ceramic matrix composite material of the outer wall.
41. The method of claim 26 , wherein forming the dome-shaped inner wall comprises dispersing a reinforcement phase comprising at least one of a plurality of fibers, a plurality of whiskers, and a plurality of particles throughout a polymer matrix phase to form an organic matrix composite material of the inner wall.
42. The method of claim 41 , further comprising selecting the polymer matrix phase to comprise a polymer material exhibiting a glass transition temperature greater than about 850° F. (454° C.).
43. The method of claim 26 , further comprising providing at least one of air, nitrogen, and an inert gas within the space.
44. The method of claim 43 , further comprising hermetically sealing the space.
45. The method of claim 26 , further comprising configuring the radome to exhibit an average insertion loss of less than about −1.5 dB for scan angles between about 15° and about 45° over a range of frequencies of electromagnetic radiation extending from a first frequency to a second frequency when the electromagnetic radiation is emitted from an antenna disposed within the radome, the second frequency being about 1.4 times the first frequency.