Radome with ceramic matrix composite

Patent metadata

Field	Value
Publication number	US-12407091-B2
Application number	US-202318545743-A
Country	US
Kind code	B2
Filing date	Dec 19, 2023
Priority date	Dec 16, 2021
Publication date	Sep 2, 2025
Grant date	Sep 2, 2025

Abstract

In a first example, a radome includes a shell including a ceramic matrix composite, the shell forming a first hole at a forward end of the shell and a second hole at an aft end of the shell. The radome also includes a fluid impervious coating on the shell. In a second example, a vehicle includes a main body, the radome, and an attachment assembly that couples the radome to the main body. In a third example, a method includes forming a shell comprising a ceramic matrix composite using a wet layup process, applying a fluid impervious coating onto the shell, and curing the shell and the fluid impervious coating.

First claim

What is claimed is:

1. A method of forming a radome, the method comprising:
forming a shell comprising a ceramic matrix composite using a wet layup process;
applying a fluid impervious coating onto the shell;
curing the shell and the fluid impervious coating; and
coupling the shell to a vehicle by:
attaching an annular component to the vehicle; and
attaching a bipod component to the shell at a joint of the bipod component, the joint forward of the annular component, wherein a first leg of the bipod component is adjoined to the annular component aft from the joint, and a second leg of the bipod component is adjoined to the annular component aft from the joint.

2. The method of claim 1 , further comprising machining the fluid impervious coating to reduce a thickness of the fluid impervious coating.

3. The method of claim 1 , wherein forming the shell comprises forming the shell such that the shell comprises an inner surface and an outer surface, and wherein applying the fluid impervious coating comprises applying the fluid impervious coating such that the fluid impervious coating covers an entirety of the outer surface.

4. The method of claim 1 , wherein forming the shell comprises forming the shell such that the shell forms a first hole at a forward end of the shell and a second hole at an aft end of the shell.

5. The method of claim 4 , wherein the first hole is smaller than the second hole.

6. The method of claim 4 , further comprising positioning a tip such that the tip forms a fluid tight seal with the shell over the first hole.

7. The method of claim 6 , wherein the tip comprises a ceramic material.

8. The method of claim 6 , further comprising using a fastening assembly to mechanically fasten the tip to the shell.

9. The method of claim 8 , wherein using the fastening assembly comprises:
positioning a bushing such that the bushing conforms to an inner surface of the shell and receives an aft end of the tip; and
mating a fastener with the aft end of the tip to hold the tip against the shell over the first hole.

10. The method of claim 9 , further comprising positioning a spring element between the fastener and the bushing such that the spring element receives the aft end of the tip.

11. The method of claim 10 , wherein the spring element maintains a preload on the tip during thermal expansion of the shell.

12. The method of claim 10 , wherein the spring element maintains a preload on the tip during thermal contraction of the shell.

13. The method of claim 1 , wherein the annular component forms a hole configured to receive a fastener.

14. The method of claim 1 , wherein the bipod component forms a hole configured to receive a fastener.

15. The method of claim 1 , wherein the bipod component comprises:
a joint that forms a hole configured to receive a fastener, wherein
the first leg couples the joint to a first attachment point on the annular component; and
the second leg couples the joint to a second attachment point on the annular component.

16. The method of claim 4 , wherein the first hole and the second hole are aligned on an axis, and wherein the bipod component is more flexible along a first direction that is perpendicular to the axis than a second direction that is parallel to the axis.

17. The method of claim 1 , further comprising using a fastening assembly comprising a spring element that is configured to maintain a preload on the shell during thermal expansion of the shell or during thermal contraction of the shell.

18. The method of claim 1 , further comprising using a fastening assembly comprising a spring element that is configured to maintain a preload on the bipod component during thermal expansion of the shell or during thermal contraction of the shell.

19. The method of claim 1 , wherein the first and second legs converge at the joint.

20. The method of claim 1 , wherein the first and second legs are machined and are attached to the annular component at first and second at first and second machine joints, respectively.

Assignees

• Boeing Co

Inventors

• Best Michael J
• Dichiara Robert A
• Muench Brian L
• Heng Vann
• Embler Jonathan D
• Pinney Thomas R
• O'Brien Holly M

Classifications

• H01Q1/281

  Nose antennas · CPC title

• H01Q1/42 Primary

  Housings not intimately mechanically associated with radiating elements, e.g. radome · CPC title