Missile structural wall for thermal protection fairing

Patent metadata

Field	Value
Publication number	US-9891031-B2
Application number	US-201515320064-A
Country	US
Kind code	B2
Filing date	Jun 10, 2015
Priority date	Jun 25, 2014
Publication date	Feb 13, 2018
Grant date	Feb 13, 2018

Abstract

The invention relates to a missile structural wall, in particular for a thermal protection fairing. The structural wall of a missile, in particular of a protective fairing of the missile, comprises a structural part provided with an outer surface and an inner surface, as well as comprising, at least at a front end of the structural part, an outer thermal protection layer on the outer surface and an inner thermal protection layer on the inner surface, the inner layer being made from a material having a density that is between 2 and 20 times lower than that of the material of the outer layer.

First claim

The invention claimed is:

1. A missile structuring wall, comprising:
a structural part comprising an outer surface and an inner surface; and
at least a portion of the structural part comprising:
at least one outer thermal protection layer on the outer surface of the structural part; and
at least one inner thermal protection layer on the inner surface of the structural part; and
wherein the inner layer is formed from a material having a density that is between 2 and 20 times lower than that of a density of a material of the outer layer.

2. The wall according to claim 1 , wherein the outer layer comprises:
integrated elements; and
a material that is selected from the group consisting of a silicone-based material and a graphite-based material.

3. The wall according to claim 1 , wherein the outer layer is configured to provide mechanical protection.

4. The wall according to claim 1 , wherein the inner layer comprises a fibrous material.

5. The wall according to claim 1 , wherein the structural part is formed from a material that is selected from the group consisting of a metal material, a thermostructural composite material and a ceramic material.

6. The wall according to claim 1 , further comprising:
at least two shells that are interconnected in connection regions; and
wherein said outer layer also covers said outer surface in said connection regions, and inner layer releases on said connection regions on said inner surface.

7. The wall according to claim 1 , further comprising:
at least one inner component which is connected by at least one of its ends to the structural part, said inner component being connected to the inner surface of the structural part by means of a thermal protection interface element via an opening provided in the inner layer.

8. The wall according to claim 7 , wherein the interface element is formed from a same material as the outer layer.

9. The wall according claim 1 , wherein said outer and inner layers are arranged over a whole of said structural part.

10. The wall according to claim 1 , wherein said outer and inner layers are arranged only on a portion of the structural part.

11. The wall according to claim 10 , wherein that the structural part is formed from a material that is selected from the group consisting of a thermostructural composite material and a ceramic material.

12. The wall according to claim 1 , wherein the wall forms a protective fairing configured for mounting on a front of the missile.

13. A missile, comprising:
a structuring wall, comprising:
a structural part comprising an outer surface and an inner surface; and
at least a portion of the structural part comprising:
at least one outer thermal protection layer on the outer surface of the structural part; and
at least one inner thermal protection layer on the inner surface of the structural part; and
wherein the inner layer is formed from a material having a density that is between 2 and 20 times lower than that of a density of a material of the outer layer.

14. The missile according to claim 13 , wherein the outer layer comprises:
integrated elements; and
a material that is selected from the group consisting of a silicone-based material and a graphite-based material.

15. The missile according to claim 13 , wherein the outer layer is configured to provide mechanical protection.

16. The missile according to claim 13 , wherein the inner layer comprises a fibrous material.

17. The missile according to claim 13 , wherein the structural part is formed from a material that is selected from the group consisting of a metal material, a thermostructural composite material and a ceramic material.

18. The missile according to claim 13 , further comprising:
at least two shells that are interconnected in connection regions; and
wherein said outer layer also covers said outer surface in said connection regions, and inner layer releases on said connection regions on said inner surface.

19. The missile according to claim 13 , further comprising:
at least one inner component which is connected by at least one of its ends to the structural part, said inner component being connected to the inner surface of the structural part by means of a thermal protection interface element via an opening provided in the inner layer.

20. The missile according to claim 19 , wherein the interface element is formed from a same material as the outer layer.

Assignees

• Mbda France

Inventors

• Quertelet Clement

Classifications

• B64G1/58

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

• F42B15/34 Primary

  Protection against overheating or radiation, e.g. heat shields; Additional cooling arrangements {(thermal protection fitted in or to cosmonautic vehicles B64G1/58)} · CPC title

• F42B10/46 Primary

  Streamlined nose cones; Windshields; Radomes {(F42B12/105 takes precedence)} · CPC title