Hybrid metal composite structures, rocket cases, and related methods

Patent metadata

Field	Value
Publication number	US-10603873-B2
Application number	US-201615250404-A
Country	US
Kind code	B2
Filing date	Aug 29, 2016
Priority date	Aug 29, 2016
Publication date	Mar 31, 2020
Grant date	Mar 31, 2020

Abstract

A method of forming a hybrid metal composite structure including at least one metal ply. The method includes forming at least one metal ply, forming the at least one metal ply comprising forming at least one perforation in the at least one metal ply, abrasively blasting at least one surface of the at least one metal ply to coarsen the at least one surface of the metal ply, and exposing the at least one metal ply to at least one of an acid or a base. The method further includes disposing at least one fiber composite material structure adjacent the at least one metal ply. Related methods of forming a portion of a rocket case and related hybrid metal composite structures are also disclosed.

First claim

What is claimed is:

1. A method of forming a hybrid metal composite structure, the method comprising:
providing metal plies between layers of a fiber composite material structure, the metal plies each comprising:
perforations extending therethrough;
at least a portion of inside surfaces of the perforations having a surface roughness from about 0.5 μm R a and about 4.0 μm R a ;
a first coating consisting of a silane coupling agent chemically bonded to a surface of the metal ply; and
a second coating comprising a polymeric material chemically bonded to the first coating; and

disposing each metal ply of the metal plies between layers of a fiber composite material structure to form alternating first layers of the metal plies and second layers of the fiber composite material, each layer of the fiber composite material structure including a fiber material dispersed within a matrix material comprising an epoxy, the second coating chemically bonded to the epoxy.

2. The method of claim 1 , further comprising selecting the fiber composite material structure to comprise a carbon fiber composite material.

3. The method of claim 1 , further comprising exposing the metal plies to one of sulfuric acid, nitric acid, hydrochloric acid, hydrofluoric acid, or combinations thereof.

4. The method of claim 1 , further comprising selecting at least one metal ply to comprise titanium.

5. The method of claim 1 , wherein providing metal plies comprises providing metal plies having a first coating comprising at least one of aminopropyl trimethoxysilane (H 2 N(CH 2 ) 3 Si (OCH 3 ) 3 ), aminopropyl triethoxysilane (H 2 N(CH 2 ) 3 Si (OC 2 H 5 ) 3 ), glycidyloxypropyl trimethoxysilane (C 9 H 20 O 5 Si), glycidyloxypropyl methyldimethoxysilane (C 9 H 20 O 4 Si), or glycidyloxypropyl triethoxysilane (C 12 H 26 O 5 Si).

6. The method of claim 1 , wherein disposing each metal ply of the metal plies comprises disposing each metal ply of the metal plies proximate a lateral edge of the hybrid metal composite structure.

7. The method of claim 1 , further comprising forming a bolt hole through the each metal ply of the metal plies and the at least one fiber composite material structure.

8. A method of forming a portion of a rocket case, the method comprising:
forming at least one hybrid metal composite structure, forming the at least one hybrid metal composite structure comprising:
forming perforations in each metal ply of a plurality of metal plies;
abrasively blasting at least one surface of each metal ply of the plurality of metal plies to coarsen at least a portion of inside surfaces of the perforations of each metal ply of the plurality of metal plies to have a surface roughness from about 0.5 μm R a and about 4.0 μm R a ;
forming a first coating consisting of a silane coupling agent chemically bonded to at least one surface of each metal ply of the plurality of metal plies; and
forming a second coating comprising a polymeric material chemically bonded to the first coating of each metal ply of the plurality of metal plies; and
incorporating the metal plies of the plurality of metal plies between a plurality of layers of a fiber composite material structure, each layer of the plurality of layers of the fiber composite material structure comprising a fiber material dispersed within a matrix material comprising an epoxy, wherein incorporating the metal plies of the plurality of metal plies between the plurality of layers of the fiber composite material structure comprises chemically bonding the second coating to the epoxy; and

operably coupling the at least one hybrid metal composite structure to at least another hybrid metal composite structure, the at least another hybrid metal composite structure comprising at least another metal ply.

9. The method of claim 8 , further comprising exposing each metal ply of the plurality of metal plies to at least one of an acid or a base.

10. The method of claim 8 , further comprising exposing each metal ply of the plurality of metal plies to one of an acid or a base after exposing each metal ply of the plurality of metal plies to another of the acid or the base.

11. The method of claim 8 , wherein operably coupling the at least one hybrid metal composite structure to at least another hybrid metal composite structure comprises bolting the at least one hybrid metal composite structure to the at least another hybrid metal composite structure.

12. The method of claim 8 , further comprising forming one or more bolt holes in each of the at least one hybrid metal composite structure and the at least another hybrid metal composite structure.

13. The method of claim 12 , wherein forming one or more bolt holes in the at least one hybrid metal composite structure comprises forming the one or more bolt holes in a portion of the at least one hybrid metal composite structure located or to be located proximate the at least another hybrid metal composite structure for the operable coupling by extending bolts through aligned bolt holes of the at least one hybrid metal composite structure and the at least another hybrid metal composite structure.

14. A hybrid metal composite structure, comprising:
a plurality of alternating first layers and second layers, wherein:
the first layers comprise a fiber composite material structure including a fiber material dispersed within a matrix material, the matrix material comprising an epoxy; and
the second layers each comprise the fiber composite material structure and at least one metal ply, the at least one metal ply comprising perforations extending therethrough, at least a portion of inside surfaces of the perforations having a surface roughness from about 0.5 μm R a and about 4.0 μm R a and comprising a first coating consisting of a silane coupling agent chemically bonded to a surface of the at least one metal ply and a second coating comprising a polymeric material chemically bonded to the first coating and to the epoxy.

15. The hybrid metal composite structure of claim 14 , wherein the at least one metal ply comprises titanium.

16. The hybrid metal composite structure of claim 14 , wherein the fiber composite material structure comprises carbon fiber.

17. The hybrid metal composite structure of claim 14 , wherein a surface of the at least one metal ply comprises a plurality of peaks and a plurality of valleys.

18. The hybrid metal composite structure of claim 14 , wherein the silane coupling agent comprises at least one of aminopropyl trimethoxysilane, aminopropyl triethoxysilane, glycidyloxypropyl methyldimethoxysilane, or glycidyloxypropyl triethoxysilane.

19. The hybrid metal composite structure of claim 14 , wherein the hybrid metal composite structure exhibits a uniform thickness.

20. The hybrid metal composite structure of claim 14 , wherein the polymeric material comprises a phenolic material, an epoxy material, or a combination thereof.

21. The hybrid metal composite structure of claim 14 , wherein the polymeric material comprises a phenol formaldehyde resin, a phenolic primer, a bisphenol F epoxy, or a phenolic novolac epoxy.

22. The hybrid metal composite structure of claim 14 , wherein the first coating has a thickness from about one monolayer to about 500 nm.

23. The hybrid metal composite structure of claim 14 , wherein the second coating has a thickness from about 1 μm to about 15 μm.

24. The hybrid metal composite structure of claim 14 , further comprising one or more fasteners ex

Assignees

• Northrop Grumman Innovation Systems Inc

Inventors

• Garcia Benjamin W C
• Bonderson Elizabeth
• Christensen Brian
• Nelson David R

Classifications

• B32B19/06

  next to a fibrous or filamentary layer · CPC title

• B32B2250/04

  4 layers · CPC title

• C04B2237/365

  Silicon carbide · CPC title

• C04B2237/704

  of one or more of the ceramic layers or articles · CPC title

• B32B15/20

  comprising aluminium or copper {(B32B15/016 and B32B15/017 take precedence)} · CPC title