Metal encapsulated ceramic tile thermal insulation, and associated systems and methods

Patent metadata

Field	Value
Publication number	US-11667408-B2
Application number	US-201916437529-A
Country	US
Kind code	B2
Filing date	Jun 11, 2019
Priority date	Jun 12, 2018
Publication date	Jun 6, 2023
Grant date	Jun 6, 2023

Abstract

A metal encapsulated ceramic tile thermal insulation system for rockets and associated methods is disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end and includes a heat shield positioned at the second end. The heat shield includes a plurality of thermal protection apparatuses, where individual of the thermal protection apparatuses include ceramic tiles encapsulated by inner and outer metal layers, which are positioned on opposing top and bottom surfaces of the ceramic tiles. The plurality of thermal protection apparatuses includes a plurality of pins positioned within corresponding holes drilled through the ceramic tiles and are secured to the metal layers. The outer metal layer can protect the ceramic tile from tool strikes and debris and can also prevent water from reaching and being absorbed by the ceramic tile.

First claim

We claim:

1. An aerospace system, comprising:
a launch vehicle having a first end and a second end opposite the first end; and
a heat shield positioned toward the second end and comprising a plurality of thermal protection apparatuses, wherein individual thermal protection apparatuses comprise:
a rigid ceramic tile having opposing top and bottom surfaces and a plurality of holes that extend between the opposing top and bottom surfaces;
an outer metal portion positioned adjacent to and fully covering the top surface, wherein the outer metal portion defines an exterior surface of the thermal protection apparatus;
an edging positioned around a perimeter of the ceramic tile, wherein the edging has a top bent portion coupling the edging to the outer metal portion; and
a plurality of pins positioned within corresponding individual holes, wherein individual pins are coupled to the outer metal portion.

2. The aerospace system of claim 1 wherein the individual thermal protection apparatuses comprise an inner metal portion positioned adjacent to and fully covering the bottom surface.

3. The aerospace system of claim 2 wherein the edging is coupled to the inner metal portion, and wherein the edging is configured to remain coupled to the outer metal portion and the inner metal portion as the outer metal portion expands.

4. The aerospace system of claim 1 wherein the individual pins are welded to the outer metal portion.

5. The aerospace system of claim 1 , wherein the edging extends between the top and bottom surfaces.

6. The aerospace system of claim 5 , wherein—
the ceramic tile includes a notch formed in the top surface that extends around the perimeter of the ceramic tile, and
the top bent portion positioned in the notch such that the top bent portion is coplanar with the top surface and is positioned between the ceramic tile and the outer metal portion.

7. The aerospace system of claim 1 , wherein—
the plurality of thermal protection apparatuses comprises first and second thermal protection apparatuses positioned directly adjacent to each other,
the first and second thermal protection apparatuses are separated from each other by a gap,
the outer metal portion of the first thermal protection apparatus includes a lip portion that extends over the gap and is welded to the outer metal portion of the second thermal protection apparatus.

8. The aerospace system of claim 1 wherein the individual thermal protection apparatuses are coupled to the launch vehicle with the individual pins.

9. The aerospace system of claim 1 , further comprising:
an adhesive, wherein the individual thermal protection apparatuses are coupled to the launch vehicle with the adhesive.

10. The aerospace system of claim 1 wherein the outer metal portion of the individual thermal protection apparatuses is positioned to directly face an environment around the launch vehicle.

11. The aerospace system of claim 1 wherein the top bent portion is coplanar with the top surface and is positioned between the ceramic tile and the outer metal portion.

12. The aerospace system of claim 1 , further comprising an inner metal portion positioned between the bottom surface and the launch vehicle and fully covering the bottom surface.

13. The aerospace system of claim 1 wherein—
the edging includes a bottom bent portion,
the top bent portion is positioned between the top surface and the outer metal portion,
the ceramic tile includes a notch formed in the top surface and that extends around the perimeter of the ceramic tile, and
the top bent portion is positioned within the notch such that the top bent portion is coplanar with the top surface.

14. The aerospace system of claim 1 wherein the holes are larger than the corresponding ones of the pins such that the pins can bend and flex within the corresponding ones of the holes.

15. The aerospace system of claim 1 wherein the edging has a bottom bent portion.

16. An aerospace system, comprising:
a launch vehicle having a first end and a second end opposite the first end; and
a heat shield positioned toward the second end and comprising a plurality of thermal protection apparatuses, wherein individual thermal protection apparatuses comprise:
a rigid ceramic tile having opposing top and bottom surfaces and a plurality of holes that extend between the opposing top and bottom surfaces;
an outer metal portion positioned adjacent to and fully covering the top surface, wherein the outer metal portion defines an exterior surface of the thermal protection apparatus;
an inner metal portion positioned between the bottom surface and the launch vehicle and fully covering the bottom surface;
an edging positioned around a perimeter of the ceramic tile, wherein the edging has a top bent portion coupling the edging to the outer metal portion; and
a plurality of pins positioned within corresponding individual holes, wherein individual pins are coupled to the outer metal portion.

17. The aerospace system of claim 16 wherein individual ones of the pins are welded to the outer metal portion and the inner metal portion.

18. The aerospace system of claim 16 wherein the edging is formed of a corrugated metal, and wherein the edging is coupled to the outer metal portion and the inner metal portion.

19. The aerospace system 16 wherein the holes are larger than the corresponding ones of the pins such that the pins can bend and flex within the corresponding ones of the holes.

20. The aerospace system of claim 16 wherein the edging has a bottom bent portion.

Assignees

• Blue Origin Llc

Inventors

• Brendel John Paul
• Hupf Christopher Patrick
• Norman Adam Keith

Classifications

• F16L59/029

  layered · CPC title

• F02K9/974

  Nozzle- linings; Ablative coatings · CPC title

• B64G1/58 Primary

  Thermal protection, e.g. heat shields · CPC title

• B64G1/623

  Retarding devices, e.g. retrorockets · CPC title

• B64G1/002

  Launch systems · CPC title