Composite cryogenic tank apparatus

• US 5,419,139 A
• Filed: 12/13/1993
• Issued: 05/30/1995
• Est. Priority Date: 12/13/1993
• Status: Expired due to Term

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Martin Marietta Corporation
• Inventors: Kirn, Elizabeth P., Blum, Celia M., Seal, Ellis C.
• Primary Examiner(s): Capossela, Ronald C.
• Application Number:
  US08/166,535
• Time in Patent Office: 533 Days
• Field of Search: 62/45.1, 220/454, 220/456
• US Class Current: 62/45.1
• CPC Class Codes: B32B 1/00 Layered products having a non-planar shape
• CPC Class Codes: B32B 2255/205 Metallic coating
• CPC Class Codes: B32B 2260/021 Fibrous or filamentary layer
• CPC Class Codes: B32B 2260/046 Synthetic resin
• CPC Class Codes: B32B 2262/0269 Aromatic polyamide fibres
• CPC Class Codes: B32B 2262/101 Glass fibres
• CPC Class Codes: B32B 2262/106 Carbon fibres, e.g. graphite fibres
• CPC Class Codes: B32B 2307/7242 Non-permeable
• CPC Class Codes: B32B 2367/00 Polyesters, e.g. PET, i.e. polyethylene terephthalate
• CPC Class Codes: B32B 27/08 of synthetic resin
• CPC Class Codes: B32B 7/12 using interposed adhesives or interposed materials with bonding properties
• CPC Class Codes: B64G 1/402 Propellant tanks; Feeding propellants
• CPC Class Codes: B64G 1/4021 Tank construction; Details thereof
• CPC Class Codes: F17C 1/16 constructed of plastics materials shaping of plastics B29C
• CPC Class Codes: F17C 2201/0109 with exteriorly curved end-piece
• CPC Class Codes: F17C 2203/032 Multi-sheet layers
• CPC Class Codes: F17C 2203/0604 Liners
• CPC Class Codes: F17C 2203/0607 Coatings
• CPC Class Codes: F17C 2203/0619 with two layers
• CPC Class Codes: F17C 2209/227 by adhesive means
• CPC Class Codes: F17C 2221/011 : Oxygen
• CPC Class Codes: F17C 2221/012 : Hydrogen
• CPC Class Codes: F17C 2221/014 : Nitrogen
• CPC Class Codes: F17C 2221/017 : Helium
• CPC Class Codes: F17C 2223/0161 : cryogenic, e.g. LNG, GNL, PLNG
• CPC Class Codes: F17C 2223/036 : Very high pressure (>80 bar)
• CPC Class Codes: F17C 2260/012 : Reducing weight
• CPC Class Codes: F17C 2270/0197 : Rockets
• CPC Class Codes: F17C 3/06 : on the inner surface, i.e. in contact with the stored fluid
• CPC Class Codes: Y02E 60/32 : Hydrogen storage

Abstract

An aerospace vehicle fuel pressure, or cryogen tank apparatus includes a tank load bearing wall of composite laminate construction that is lined with a film laminate liner that includes at least two metalized layers bonded with adhesive with the metalized coatings facing each other. The liner is bonded to the load bearing wall with an adhesive. The improved tank apparatus is able to withstand extreme pressure and extreme temperature conditions, and while containing cryogens such as liquid helium and liquid hydrogen.

Claims

1. An aerospace vehicle composite cryogen tank apparatus, comprising:

a) a space structural tank body having means for containing a cryogenic material;

b) a tank body having an interior for containing a cryogenic material that has a temperature of as low as minus 400 degrees F.;

c) the tank body having a tank wall with an inner surface, the tank wall having a composite construction that includes a fiber reinforced portion;

d) liner means for lining the interior of the tank, said liner means having low permeability to gases and comprising;

i) a laminate of film layers including at least two film layers, each having a vacuum deposited metalized coating thereon, and a first layer of adhesive bonding the two metalized surfaces together;

ii) a second layer of adhesive for bonding the liner means to the composite tank inner surface; and

e) wherein the liner means has a thickness of about 0.5-2.0 mils.

2. The apparatus of claim 1 wherein the layer of adhesive is of a polyester adhesive material.

3. The apparatus of claim 1 wherein the layer of adhesive that bonds the liner means to the tank wall is a polyester adhesive material.

4. The apparatus of claim 1 wherein the liner means has low permeability to hydrogen.

5. The apparatus of claim 1 wherein the vacuum deposited metalized coating is about one thousand angstroms in thickness.

6. The apparatus of claim 1 wherein the tank wall is of a graphite/epoxy material.

7. The apparatus of claim 1 wherein the tank wall is of a Kevlar/epoxy material.

8. The apparatus of claim 1 wherein the apparatus contains liquid helium at a temperature of about minus 423 degrees F.

9. An aerospace vehicle composite cryogen tank apparatus, comprising:

a) a space vehicle having structural means for containing a cryogenic material;

b) a tank body having an interior for containing a cryogenic material that has a temperature of as low as minus 400 degrees F.;

c) the tank body having a tank wall with an inner surface, the tank wall having a composite construction that includes a fiber reinforced portion;

d) liner means for lining the interior of the tank, said liner means having low permeability to gases and comprising;

i) a laminate of bonded layers and including at least two film layers, each film layer having a vacuum deposited metalized coating thereon, and a first layer of adhesive bonding the two metalized surfaces together;

ii) a second layer of adhesive for bonding the liner means to the composite tank inner surface; and

e) wherein the liner means has a thickness of about 0.5-1.0 mils, and the two film layers are of substantially equal thickness.

10. The apparatus of claim 9 wherein the metalized surfaces are aluminized surfaces.

11. An aerospace vehicle composite cryogen tank apparatus, comprising:

a) a tank body for containing cryogenic material during use;

b) the tank body having an interior for containing a cryogenic material that has a temperature of as low as minus 450 degrees F.;

c) a load bearing wall including an inner surface, the tank wall having a composite construction that includes a fiber portion embedded in a matrix material;

d) liner means for lining the inner surface of the load bearing wall, said liner means having low permeability to gases and comprising;

i) a laminate of layers including at least two film layers, each film layer having a metalized surface with a vacuum deposited metalized thereon, and a first layer of adhesive bonding the two metalized surfaces of the two film layers together;

ii) a second layer of adhesive for bonding the liner means to the load bearing wall inner surface; and

e) wherein the liner means has a thickness of about 0.5-2.0 mils.

12. The apparatus of claim 11 wherein the first layer of adhesive is of a thermoset resin adhesive material.

13. The apparatus of claim 11 wherein the second layer of adhesive, bonding the liner means to the load bearing wall, is a thermoset resin adhesive material.

14. The apparatus of claim 11 wherein the first layer of adhesive is a polyester resin.

15. The apparatus of claim 11 wherein the second layer of adhesive is a polyester resin.

16. The apparatus of claim 11 wherein the liner means has means for lowering permeability to hydrogen.

17. The apparatus of claim 11 wherein the metalized surfaces are aluminized surfaces.

18. The apparatus of claim 11 wherein the vacuum deposited metalized coating on each film layer is about one thousand angstroms in thickness.

19. The apparatus of claim 11 wherein the load bearing wall is of a graphite and epoxy composite laminate.

20. The apparatus of claim 11 wherein the load bearing wall is of a Kevlar and epoxy composite laminate.

21. The apparatus of claim 11 wherein the apparatus contains liquid hydrogen at a temperature of about minus 423 degrees F.

22. An aerospace vehicle tank apparatus, comprising:

a) a tank body having structural means for containing a cryogenic material;

b) the tank body having an interior for containing a cryogenic material that has a temperature of as low as minus 400 degrees F.;

c) the tank body having a tank wall comprising laminate composite construction that includes a fiber reinforced portion;

d) liner means for lining the interior of the tank, said liner means having low permeability to gases and comprising;

i) a laminate of bonded layers and including at least two film layers, each film layer having at least one outer surface with a vacuum deposited metalized coating thereon, and a first layer of adhesive bonding the two metalized surfaces together of each film layer;

ii) a second layer of adhesive for bonding the liner means to the tank wall; and

e) wherein the liner means has a thickness of about 0.5-2.0 mils, and the two film layers are of substantially equal thickness.

23. The apparatus of claim 22 wherein the tank wall is a fiber reinforced composite laminate that includes epoxy.

24. The apparatus of claim 22 wherein the tank wall is a composite laminate that includes graphite.

25. The apparatus of claim 22 wherein the tank wall is a fiber reinforced composite laminate that includes polyester.

26. The apparatus of claim 22 wherein the fibers are glass fibers.

27. The apparatus of claim 22 wherein the fibers are aramid fibers.

28. The apparatus of claim 22 wherein the tank wall is a fiber reinforced composite laminate with fibers embedded in a matrix material.

29. The apparatus of claim 28 wherein the fibers are glass fibers.

30. The apparatus of claim 28 wherein the fibers are aramid fibers.

31. The apparatus of claim 22 wherein the metalized surfaces are aluminized surfaces.