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Patent Analysis of

Lox-compatible composite tank for aerospace applications

Updated Time 15 March 2019

Patent Registration Data

Publication Number

US6837464

Application Number

US10/316131

Application Date

10 December 2002

Publication Date

04 January 2005

Current Assignee

LOCKHEED MARTIN CORPORATION

Original Assignee (Applicant)

LOCKHEED MARTIN CORPORATION

International Classification

B64G1/22,B64G1/40,C08J5/04,F17C13/00,F17C1/06

Cooperative Classification

B64G1/402,F17C1/06,F17C1/16,F17C13/008,F17C13/088

Inventor

KIRN, ELIZABETH PAIGE,GRAF, NEIL ANTHONY,ELY, KEVIN WILBUR

Patent Images

This patent contains figures and images illustrating the invention and its embodiment.

Lox-compatible composite tank for aerospace applications Lox-compatible composite tank for aerospace applications Lox-compatible composite tank for aerospace applications
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Abstract

Composite tanks are desirable for aerospace applications since they are much lighter than comparable metal tanks. Various polymeric compositions satisfy the requirements to make a Lox compatible tank.

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Claims

1. A method of using a composite tank to hold LOX, comprising the steps of: a) providing a composite tank apparatus, the composite tank apparatus comprising a structural tank body having an interior for containing a LOX cryogenic material that has a temperature as low as around minus 300 degrees F; b) the tank body having a tank wall that has a mechanical impact of at least ten (10) foot pounds at about minus 300 degrees F. and the wall having an inner surface for contacting LOX, the tank wall having a composite construction that includes a fiber-reinforced resin portion but that does not have multiple foam layers; and c) putting LOX in the composite tank apparatus.

2. The method of claim 1, wherein the fiber-reinforced resin portion directly contacts LOX when LOX is put into the composite tank apparatus.

3. The method of claim 1, wherein the fiber-reinforced resin portion is made of at least one from the following group: fiber-reinforced cyanate ester; fiber-reinforced halogenated resin; fiber-reinforced toughened epoxy resin; fiber-reinforced polyimide resin; and PEAR.

4. The method of claim 1, wherein the tank has a primary component wall system and an interior component wall system, the primary component wall system being made of a first resin reinforced with a first fiber, and the interior component wall system including more LOX compatible fiber, more LOX compatible form of fiber, more LOX compatible resin, a more LOX compatible lay-up pattern, a more LOX compatible treatment of the resin, and/or a resin-rich surface.

5. The method of claim 1, wherein the interior is lined or coated with a material which is more LOX-compatible than the fiber-reinforced resin.

6. Apparatus for holding LOX comprising: a) a structural tank body having an interior for containing a LOX cryogenic material that has a temperature as low as around minus 300 degrees F., the tank body having a tank wall with an inner surface for contacting LOX; b) the tank wall that has a mechanical impact of at least ten (10) foot pounds at about minus 300 degrees F., the wall having a composite construction that includes a fiber-reinforced resin portion made of at least one from the following group: fiber-reinforced cyanate ester; fiber-reinforced halogenated resin; fiber-reinforced toughened epoxy resin; fiber-reinforced polyimide resin; and PEAR; and c) the wall does not have multiple foam layers.

7. The apparatus of claim 6, wherein the fiber-reinforced resin portion directly contacts LOX when LOX is put into the composite tank apparatus.

8. The invention of claim 6, further comprising oxygen in the tank.

9. The invention of claim 6, wherein the mechanical impact threshold is at least 25 foot-pounds.

10. The invention of claim 6, wherein the mechanical impact threshold is at least 36 foot-pounds.

11. The invention of claim 6, wherein the mechanical impact threshold is at least 72 foot-pounds.

12. An aerospace launch vehicle including the apparatus of claim.6.

13. Apparatus for transporting LOX comprising: a composite feedline having means for transporting LOX, the feedline having an interior for transporting a cryogenic material that has a temperature as low as around minus 300 degrees F., the feedline having a feedline wall that has a mechanical impact of at least 10 foot pounds at about minus 300 degrees F. the wall having an inner surface for contacting LOX, the feedline wall having a composite construction that includes a fiber-reinforced resin portion made of at least one from the following group: fiber-reinforced cyanate ester; fiber-reinforced halogenated resin; fiber-reinforced toughened epoxy resin; fiber-reinforced polyimide resin; and PEAR; and wherein the wall does not have multiple foam layers.

14. The apparatus of claim 13, wherein the fiber-reinforced resin portion directly contacts LOX when LOX is put into the apparatus.

15. An aerospace launch vehicle including the apparatus of claim 13.

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Claim Tree

  • 1
    1. A method of using a composite tank to hold LOX, comprising the steps of:
    • a) providing a composite tank apparatus, the composite tank apparatus comprising a structural tank body having an interior for containing a LOX cryogenic material that has a temperature as low as around minus 300 degrees F;
    • b) the tank body having a tank wall that has a mechanical impact of at least ten (10) foot pounds at about minus 300 degrees F. and the wall having an inner surface for contacting LOX, the tank wall having a composite construction that includes a fiber-reinforced resin portion but that does not have multiple foam layers; and
    • c) putting LOX in the composite tank apparatus.
    • 2. The method of claim 1, wherein
      • the fiber-reinforced resin portion directly contacts LOX when LOX is put into the composite tank apparatus.
    • 3. The method of claim 1, wherein
      • the fiber-reinforced resin portion is made of at least one from the following group: fiber-reinforced cyanate ester; fiber-reinforced halogenated resin; fiber-reinforced toughened epoxy resin; fiber-reinforced polyimide resin; and PEAR.
    • 4. The method of claim 1, wherein
      • the tank has a primary component wall system and an interior component wall system, the primary component wall system being made of a first resin reinforced with a first fiber, and the interior component wall system including
    • 5. The method of claim 1, wherein
      • the interior is lined or coated with a material which is more LOX-compatible than the fiber-reinforced resin.
  • 6
    6. Apparatus for holding LOX comprising:
    • a) a structural tank body having an interior for containing a LOX cryogenic material that has a temperature as low as around minus 300 degrees F., the tank body having a tank wall with an inner surface for contacting LOX;
    • b) the tank wall that has a mechanical impact of at least ten (10) foot pounds at about minus 300 degrees F., the wall having a composite construction that includes a fiber-reinforced resin portion made of at least one from the following group: fiber-reinforced cyanate ester; fiber-reinforced halogenated resin; fiber-reinforced toughened epoxy resin; fiber-reinforced polyimide resin; and PEAR; and
    • c) the wall does not have multiple foam layers.
    • 7. The apparatus of claim 6, wherein
      • the fiber-reinforced resin portion directly contacts LOX when LOX is put into the composite tank apparatus.
    • 8. The invention of claim 6, further comprising
      • oxygen in the tank.
    • 9. The invention of claim 6, wherein
      • the mechanical impact threshold is at least 25 foot-pounds.
    • 10. The invention of claim 6, wherein
      • the mechanical impact threshold is at least 36 foot-pounds.
    • 11. The invention of claim 6, wherein
      • the mechanical impact threshold is at least 72 foot-pounds.
  • 12
    12. An aerospace launch vehicle including
    • the apparatus of claim.6.
  • 13
    13. Apparatus for transporting LOX comprising:
    • a composite feedline having means for transporting LOX, the feedline having an interior for transporting a cryogenic material that has a temperature as low as around minus 300 degrees F., the feedline having a feedline wall that has a mechanical impact of at least 10 foot pounds at about minus 300 degrees F. the wall having an inner surface for contacting LOX, the feedline wall having a composite construction that includes a fiber-reinforced resin portion made of at least one from the following group: fiber-reinforced cyanate ester
    • fiber-reinforced halogenated resin
    • fiber-reinforced toughened epoxy resin
    • fiber-reinforced polyimide resin
    • and PEAR
    • and wherein the wall does not have multiple foam layers.
    • 14. The apparatus of claim 13, wherein
      • the fiber-reinforced resin portion directly contacts LOX when LOX is put into the apparatus.
  • 15
    15. An aerospace launch vehicle including
    • the apparatus of claim 13.
See all 5 independent claims

Description

STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT

The inventions described herein were made in the performance of work under one or more of the following: Lockheed Martin Michoud Space Systems IRAD M-21D, IRAD M-24D, IRAD M-28D, Cooperative Agreement No. NCC8-115 dated 1 Jul. 1996, General Dynamics RD-1 No. 611-5588-453 and reported in GDSS-ERR-90-600.

REFERENCE TO A “MICROFICHE APPENDIX”

Not applicable

BACKGROUND OF THE INVENTION

1. Field of the Invention

The present invention relates to tanks for liquid oxygen. More particularly, the present invention relates to composite tanks for liquid oxygen.

2. General Background of the Invention

The following U.S. Patents are incorporated herein by reference: U.S. Pat. No. 5,056,367; 5,251,487; 5,380,768; 5,403,537; 5,419,139; and all references cited in those patents.

The following international applications published under the PCT are incorporated herein by reference: International Publication Nos. WO 97/18081 and WO 97/28401 and all references cited in those publications.

A fiber-reinforced composite is defined as a material consisting of fibers of high strength and modulus embedded in or bonded to a matrix with distinct interfaces or boundaries between them. In this form, both fibers and matrix retain their physical and chemical identities, yet they produce a combination of properties that cannot be produced by either constituent alone. In general, fibers are the principal load carrying members, while the surrounding matrix keeps them in desired location and orientation, transfers loads between fibers, and protects the fibers. The matrix material may be a polymer, a metal, or a ceramic. This disclosure focuses on polymer matrix composites.

The fibers can be made from a variety of materials. These materials include glass, graphite or carbon, polymers, boron, ceramics, or metals. Glass fibers include E-glass (electrical) and S-glass (structural) types. Carbon fibers include those made from different precursors, such as polyacrylonitrile (PAN) or pitch. Polymer fibers include, but are not limited to, aramid (Kevlar®), polyethylene (Spectra®), or PBO (Zylon®). Ceramic fibers may include silicon carbide (SiC) or aluminum oxide (Al2O3).

For cryogenic tanks, the preferred matrix material is a polymer. The preferred fiber is carbon fiber, more preferably PAN-based fibers, more preferably high strength (over 500 ksi) and high modulus (over 30 Msi) fibers. The most preferred fibers are ultra high modulus fibers (over 60 Msi), specifically M55J fiber by Toray.

The development of polymer matrix composite liquid oxygen tanks is a critical step in creating the next generation of launch vehicles. Future reusable launch vehicles need to minimize the gross liftoff weight (GLOW) by reducing the dry mass fraction. The (dry) mass fraction is the weight of the launch vehicle without fuel divided by the weight of the vehicle with fuel. FIG. 1 is graph showing the effect of mass fraction on GLOW. Indicated on the graph is the RLV mass fraction target region as well as the mass fraction of the RLV without the weight reduction that composites could provide. It is clear that composite tanks are critical to enable future launch vehicles to meet required mass fractions.

The required mass fraction is possible due to the reduction of weight that composite materials can provide. Traditional oxygen tanks are usually made from metals. The space shuttle external tank (ET) has historically been made from 2219 aluminum and more recently 2195 aluminum/lithium alloy. FIG. 2 shows a comparison between these two aluminum alloys and a typical composite material for a liquid oxygen tank for a launch vehicle. The chart shows that a composite tank provides up to 41% and 28% weight savings when compared to 2219 and 2195 aluminum tanks, respectively.

In addition to meeting the required mass fraction, a liquid oxygen tank must be compatible with oxygen. The ASTM definition for oxygen compatibility is the “ability of a substance to coexist with both oxygen and a potential source(s) of ignition within the acceptable risk parameter of the user.” It is imperative that materials are selected that will resist any type of detrimental, combustible reaction when exposed to usage environments. Typically, non-metallic materials are not used in these applications because most are easily ignited in the presence of oxygen. However, there are some polymeric materials with inert chemistries that may be used for this application and resist ignition. These chemistries were evaluated by fabricating coupons and testing them with various ignition mechanisms in the presence of liquid and gaseous oxygen. The testing performed reflected situations in launch vehicles that could be potential sources of ignition in composite. These tests included pressurized mechanical impact, particle impact, puncture, puncture of damaged, oxygen-soaked samples, electrostatic discharge, friction, and pyrotechnic shock.

Applications include liquid oxygen for future launch vehicles, such as the Lockheed Martin Reusable Launch Vehicle (RLV). They could also potentially be used in other aerospace applications, including but not limited to, RFP (rocket fuel propellant) tanks and crew vehicle cabins. Other industries that may be interested in composite oxygen tanks include the air handling and medical industries. The ability to resist ignition may also be useful in chemical storage tanks and NGV (natural gas vehicle) tanks.

BRIEF SUMMARY OF THE INVENTION

The apparatus of the present invention solves the problems confionted in the art in a simple and straightforward manner. What is provided are composite tanks for liquid oxygen.

The composite tanks can be made in accordance with any of the methods disclosed in any reference incorporated herein by reference. The invention could be made, for example, using the method of U.S. Pat. No. 5,403,537.

The interior of the tanks disclosed herein typically have a volume of at least 1 liter, more often at least one gallon, and usually have a volume sufficient to allow their use to contain liquid oxygen for typical aerospace applications.

A mechanical impact of at least 10+ft-lbs at around −300 degrees F. (at around −350 degrees F. when densified oxygen (slush oxygen) is contained in the lank) is preferred, but is not a requirement. Historically materials have been required to pass the Lox mechanical impact test at 72 ft-lbs or otherwise be shown to be safe for use in application. Lox compatible composite materials have demonstrated the ability to resist combustion when subjected to any potential ignition source. For a composite tank, realistic potential ignition sources were determined to include, but are not limited to mechanisms such as pyrotechnic shock, friction, puncture, electrostatic discharge, and particle impact. These tests are taken to extreme levels. For example, in the puncture test, a sharpened serrated spike pierced a composite material while submerged in Lox without igniting the composite. This same puncture test has ignited Titanium, a material that is not oxygen compatible, and does not ignite aluminum. The pyrotechnic shock test was also an extreme test in that composites were placed in Lox and subjected to shock loads equivalent to existing metallic Lox tanks such as that on the External Tank. The friction test was extreme in that the composites were abraded to dust with a drill bit in pure oxygen without ignition. In the electrostatic discharge test, composites were subjected to energies that could far exceed any instrumentation or static build up; specifically, these composites do not ignite when subjected to 112.5 Joules from 5000 Volts.

The apparatus of the present invention includes composite tanks for liquid oxygen. The unique, nontraditional concept explored in one embodiment herein is to use fiber-reinforced PEAR composites to create liquid oxygen tanks. A PEAR material is one that is characterized by multiple ether and amide groups or linkages. An amide group is an organic group of atoms that is derived from a carboxylic acid and an amine. Ether is defined as any of a class of organic compounds structurally related to water in which hydrogen atoms have been replaced by organic groups. See FIG. 3 for a reaction that produces ether and amide linkages.

Generally, there are two types of PEAR resins: hot melt and solution.

Several types of resins and composites have been subjected to an extensive battery of tests for their sensitivity to reaction in the presence of oxygen. Historically, the approach was to test the material in the standard mechanical impact test in liquid oxygen (LOX). If the material had an impact threshold of 72 foot-pounds, it was acceptable for use in oxygen environments, such as launch vehicle LOX tanks. If the material's threshold was less than 72 foot-pounds, it typically was not used. Due to limitations in the testing as well as differences in the material structures between metals and composites, standard high strength composite materials have not been able to pass at this level at typical RLV tank wall thicknesses. The approach taken here, which was developed in conjunction with NASA, was to use the standard mechanical impact test to rank composites with respect to each other. Furthermore, an evaluation of the compatibility of composites in oxygen environments would only be determined after testing composite materials with respect to specific ignition mechanisms while in the presence of oxygen. The ignition mechanisms tested included pressurized mechanical impact, particle impact, puncture, puncture of damaged, oxygen-soaked samples, electrostatic discharge, friction, and pyrotechnic shock. If the material could withstand ignition in these environments, it could possibly be considered oxygen compatible.

Several PEAR materials are undergoing evaluation in the standard mechanical impact test. It is expected to do well in liquid oxygen testing due to its high flammability resistance. See FIG. 4 for a comparison of PEAR resin to a typical epoxy.

Another critical parameter for a composite tank is the ability to withstand repeated temperature changes (thermal cycles) without microcracking. One factor that contributes to microcrack resistance is toughness. PEAR resin is tougher than most standard epoxies. See FIG. 5. One effect of thermal cycling is a loss of mechanical properties. FIG. 6 shows how thermal cycling does not effect performance of PEAR materials.

The composite feedline of the present invention preferably has an inner diameter of around 1″ to 36″.

As used herein, “form of fiber” means unidirectional tape, slit tape, tow, fabric, woven fabric, chopped fiber, or felt.

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWNGS

For a further understanding of the nature, objects, and advantages of the present invention, reference should be had to the following detailed description, read in conjunction with the drawings, wherein time is in seconds and mechanical impact is in foot-pounds:

FIG. 1 is a graphical representation of the effect of mass fraction on gross lift off weight;

FIG. 2 is a graphical representation of material weight comparison;

FIG. 3 is a graphical representation of a reaction that produces ether and amide linkages;

FIG. 4 is a graphical representation of flammability of PEAR vs. epoxy;

FIG. 5 is a graphical representation of toughness of PEAR vs. epoxy;

FIG. 6 is a graphical representation showing modulus data after thermal cycling;

FIG. 7 is a schematic diagram of a halogenated prepreg autoclave vacuum bag;

FIG. 8 is a side view of the preferred embodiment of the apparatus of the present invention shown in a cylindrical tank general configuration;

FIG. 9 is an end view of the tank of FIG. 8;

FIG. 10 is a perspective view of the preferred embodiment of the apparatus of the present invention showing a spherical tank;

FIG. 11 is a perspective view of the preferred embodiment of the apparatus of the present invention showing an ogived tank;

FIG. 12 is plan view of the preferred embodiment of the apparatus of the present invention showing a multi-lobe tank, general configuration;

FIG. 13 is an end view of the tank of FIG. 12;

FIG. 14 is a side view of the tank of FIGS. 12 and 13;

FIG. 15 is a side view of the preferred embodiment of the apparatus of the present invention showing a semi-conformal tank, general configuration;

FIG. 16 is a plan view of the tank of FIG. 15;

FIG. 17 is a perspective of the preferred embodiment of the apparatus of the present invention showing a lifting body;

FIG. 18 is a perspective of the preferred embodiment of the apparatus of the present invention showing a winged body, and

FIG. 19 is a perspective of the preferred embodiment of the apparatus of the present invention showing a cylindrical stage, external tank type.

DETAILED DESCRIPTION OF THE INVENTION

FIGS. 8-9 show the preferred embodiment of the apparatus of the present invention designated generally by the numeral 10. The shape of a composite LO2 tank is not limited to, but may be any of the following: cylindrical, spherical, ogived, multi-lobe, or conformal. Composite LO2 tanks may be part of but are not limited to any of the following launch vehicles types: lifting body or winged body. A composite tank may also be part of a separate stage such as the External tank of the spare shuttle.

A spherical tank 24 is simply a sphere as shown in FIG. 10. Tank 24 can have a diameter of between about 1-150 feet.

An ogived tank 25 is a tank with an ogive shape along its sides. The sides can measure between about 1 and 150 feet wide or about 3 and 150 feet high. An example of an ogive tank 25 is the external Tank LO2 tank. FIG. 11 depicts a sketch of this concept.

Any of the tanks of FIGS. 8-16 may also be part of a winged body vehicle 27 or a cylindrical stage 28 as shown in FIGS. 18 and 19, respectively. Winged body vehicles 27 can be generally cylindrically shaped, with wings on the sides.

A composite LO2 may be part of a single stage to orbit vehicle or a multiple stage to orbit vehicle where a multiple stage to orbit vehicle is composed of at least 2 stages.

A cylindrical tank is one that has a basic body as a cylinder 11 as shown in FIGS. 8-9. Domes 12, 13 may be facing outward as shown in FIG. 10, but may also be internal or flat bulkheads capping off a cylinder. In FIGS. 8 and 9, a cylindrical tank 10 is shown having a general configuration that includes a cylindrically shaped side wall 11 and conically shaped dome end portions 12, 13.

In FIGS. 12-14, the tank apparatus 10 is shown in a multi-lobe tank configuration. A multi-lobe tank 29 will have at least 2 lobes as shown in FIGS. 12-14. A multi-lobe tank may also have more than 2 lobes, but typically no more than 5 lobes. A multi-lobe Lox tank 29 may have one lobe with Lox and the other lobe or lobes may contain other propellants such as LH2. In FIGS. 12-14, two tank lobes 14, 15 are shown. However, it should be understood that though there are a minimum of two lobes in FIGS. 12-14, there may be more lobes for forming tank 10.

In FIGS. 15 and 16, a conformal tank 30 is shown mounted between beams including an upper pair of beams 16, 17 and a lower pair of beams 18, 19. Similarly, the tank 10 in FIGS. 15 and 16 can be braced with additional vertically extending beams 20-23. Each of the tanks 10, 24, 25, 29, 30 can have a length of for example 2-150 feet and a maximum transverse dimension of between 2 and 100 feet. In FIGS. 8 and 9, the cylindrically shaped tank provides a diameter of about 1-100 feet and an overall length of about 2-150 feet. The multi-lobe tank 29 of FIGS. 14-16 provides an overall length of between about 4 and 150 feet, a width of 3-100 feet and a height of 2-100 feet.

A conformal tank 30 is any tank which aims to conform or shape itself to the vehicle inner mold line. Therefore, the shape of a conformal tank 30 will depend upon the vehicle body shape. FIGS. 15-16 show an example of a conformal tank for a lifting body type launch vehicle 26. A lifting body type vehicle 26 is depicted in FIG. 17. The conformal tank 30 of FIGS. 15 and 16 provides an overall length of between about 4 and 150 feet, a width of between 3 and 100 feet, and a height of between about 2-50 feet.

A PEAR tank can be fabricated using either of the uncured composite systems, any appropriate placement method, and any curing process. A listing of each of these systems, placement methods, and curing methods is found below. The best system to use depends on a variety of factors including, but not limited to, tank size and shape, composite material used, and available resources. Therefore, a decision on the best fabrication process must be made on a case-related basis.

Uncured Composite Systems:

    • Prepreg Systems
    • “Wet” Resin system.

A prepreg consists of reinforcement, such as graphite, glass, or Kevlar®, which is impregnated with a resin. A wet resin system is one where liquid resin is placed on the reinforcement at the time of manufacture.

Placement Methods for Prepreg Systems:

    • Fiber Placement
    • Tape Placement
    • Filament Winding
    • Hand Lay-up

Placement Methods for Wet systems:

    • Filament Winding
    • Resin Infusion/Resin transfer molding
    • Hand Lay-up

Fiber placement is an automated process where a robotic arm with a dispensing head is used to place several pieces of prepreg tow or slit tape, typically approximately 0.125 inches wide by 0.0055 inches thick, onto a mandrel in a desired orientation. Tape placement is a similar automated process, but the placement head is attached to a gantry rather than a robotic arm, and it places prepreg tape, typically 12 or 14 inches wide, onto the tool or mandrel. Filament winding is a process in which continuous prepreg tow or continuous fiber with wet resin is wound onto a rotating mandrel in a prescribed way. Hand lay-up is when prepreg, usually tape or fabric, or dry material and wet resin is manually applied to a tool or mandrel. Resin infusion or resin transfer molding is where resin is injected or otherwise forced into a dry reinforcement fabric or preform.

Curing Processes:

    • Autoclave
    • Oven Cured (with or without vacuum bag)
    • Radiation Cure (such as electron beam)
    • In-Situ Cure

Curing of a composite material is the application of energy (heat or radiation) and possibly pressure to cause a chemical reaction and form a compact, solid part. The cure method may be any of the following: autoclave (elevated temperature and pressure), vacuum-bag oven cure (elevated temperature and vacuum pressure), oven cure (elevated temperature, ambient pressure), radiation cure (typically ambient temperature and pressure with radiation, such as electron beams or x-ray radiation), or in-situ curing in which the material is cured as it is placed (with for example, heat and mechanical pressure). FIG. 7 illustrates an example of a bagging scheme and autoclave cure, for a PEAR composite. Typical autoclave cycle is 1 hour at 177° C./350° F. at 621 kpa (90 psi) with a post cure at 218° C. (425° F.) postcure.

The foregoing detailed description is a description of Embodiment 7. Please see the patent applications incorporated herein by reference (and particularly the documents attached to the U.S. Provisional Patent Applications) for a detailed description of the other embodiments of the present invention.

One could combine features of the different embodiments to create a Lox compatible tank or feedline; e.g. one could line or coat the hybrid tank or feedline of embodiment 3.

Parts List

The following is a list of parts and materials suitable for use in the present invention:


Material
Generic Description
Trademark
Supplier
Embodiment 1 - Cyanate Ester Composites for Oxygen Containment
prepreg
any appropriate fiber
reinforced with
cyanate ester resin;
(prepreg may be
impregnated in the
form of slit tape, tow,
uni-tape, fabric,
chopped fiber, and/or
felt)
prepreg
graphite fiber-
Reinforcement fiber,
Bryte
reinforced cyanate
such as graphite like
Technologies
ester resin; (prepreg
IM7 fiber, with any
may be impregnated
of 1522, 1522-1,
in the form of slit
1510, or any
tape, tow, uni-tape,
modified version of
fabric, chopped fiber,
these
and/or felt)
prepreg
fiber-reinforced
Any reinforcement
Bryte
cyanate ester resin;
fiber which is further
Technologies
(prepreg may be
defined in a
impregnated in the
subsequent row, such
form of slit tape, tow,
as IM7, impregnated
uni-tape, fabric,
with any of 1522,
chopped fiber, and/or
1522-1, 1510, or any
felt)
modified version of
these
Prepreg
reinforced cyanate
Any reinforcement
Hexcel
ester resin; (prepreg
fiber which is further
(formerly
may be impregnated
defined in a
part of
in the form of slit
subsequent row, such
Cytec
tape, tow, uni-tape,
as IM7, impregnated
Fiberite)
fabric, chopped fiber,
with 954-3, 954-2, or
or felt)
any modified version
of these
fiber
intermediate
Examples: IM7, IM6,
Hexcel
modulus, high
IM2; Note: Preferred
strength graphite
is IM7
which may be uni-
directional tape, slit
tape, fabric, woven
fabric) chopped fiber,
or felt
fiber
intermediate
Examples: T650,
Amoco
modulus, high
T800, T300
strength graphite
which may be uni-
directional tape, slit
tape, fabric, woven
fabric, chopped fiber,
or felt
fiber
high modulus,
Example: M55J
Toray
intermediate strength
graphite
(uni-directional tape,
slit tape, fabric,
woven fabric,
chopped fiber, or
felt)
fiber
glass (E, S, or C
Fiberglas ®
Owens/
type)
Corning
fiber
Aramid
Kevlar ®
Hexcel
resin
cyanate ester
954-2A, 954-3
Hexcel
Note these are
(formerly
typically supplied in
available
as prepregs with
from
reinforcement
Fiberite)
resin
cyanate ester
1510
Bryte
Note this has
typically been
supplied as a wet
resin (as opposed to a
prepreg); however,
the inventors have
had Bryte
specifically tailor the
1510 resin and
supply it as a prepreg
form.
resin
cyanate ester
1545
Bryte
Note this has
typically been
supplied as a wet
resin
resin
cyanate ester
1522, 1522-1
Bryte
Note: these are both
supplied as prepregs;
the 1522-1 may also
be supplied as resin
only; the 1522
family is a blend of
epoxy-cyanate ester-
bromine
Embodiment 2 Halogenated Composites for Oxygen Systems
prepreg
graphite fiber-
Reinforcement fiber,
Bryte
reinforced
which is further
halogenated epoxy
defined in a
resin
subsequent row,
which is impreg-
nated with a
halogenated resin
such as 1522,
1522-1 or any
modified version of
these (the 1522
family is a blend of
epoxy-cyanate ester-
bromine)
prepreg
graphite fiber-
Reinforcement fiber,
Hexcel
reinforced
which is further
halogenated epoxy
defined in a
resin
subsequent row,
impregnated with
F155 resin
fiber
intermediate
Examples: IM7,
Hexcel
modulus; high
IM6, IM2; Note:
strength graphite,
Preferred is IM7
which may be
uni-directional tape,
slit tape, tow, fabric,
woven fabric,
chopped fiber, or felt
fiber
intermediate
Examples: T650,
Amoco
modulus, high
T800, T300
strength graphite,
which may be uni-
directional tape, slit
tape, fabric, tow,
woven fabric,
chopped fiber, or felt
fiber
high modulus,
Example: M55J
Toray
intermediate strength
graphite
(uni-directional tape,
slit tape, tow, fabric,
woven fabric,
chopped fiber, or
felt)
fiber
glass (E, S, or C
Fiberglas ®
Owen/
type)
Corning
fiber
Aramid
Kevlar ®
Hexcel
resin
halogenated epoxy
F155 resin (in which
Hexcel
the halogen is
Bromine)
resin
halogenated cyanate
EX 1522-1 (in
Bryte
ester
which the halogen
is Bromine)
resin
halogenated
Avimid N (in which
Cytec
thermoplastic (may
case the halogen is
Fiberite
be considered a
Fluorine); this
(formerly
pseudothermosetting
material is supplied
from
one)
as a prepreg
DuPont)
resin
halogenated epoxy,
Examples: EPON
Shell
wet resin
1162, 1183 (both of
these have Bromine
as a halogen)
Embodiment 3 - Hybrid Composites for Oxygen Propulsion Systems
primary fiber or
intermediate
Examples: IM7,
Hexcel
interior fiber (but not
modulus, high
IM6, IM2; Note:
both, unless resins
strength graphite,
Preferred is IM7
are different)
which may be uni-
directional tape, slit
tape, tow, fabric,
woven fabric,
chopped fiber, or felt
primary fiber
intermediate
Examples: T650,
Amoco
or interior
modulus, high
T800, T300
fiber (but
strength graphite,
not both un-
which may be uni-
less resins
directional tape, slit
are different)
tape, tow, fabric,
woven fabric,
chopped fiber, or felt
primary fiber or
high modulus,
Example: M55J
Toray
interior fiber (but not
intermediate strength
both unless resins are
graphite intermediate
different)
modulus, high
strength graphite,
which may be uni-
directional tape, slit
tape, tow, fabric,
woven fabric,
chopped fiber, or felt
primary fiber or
glass (E, S, or C type)
Fiberglas ®
Owens/
interior fiber (but not
Corning
both unless resins are
different)
primary fiber or
Aramid
Kevlar ®
Hexcel
interior fiber (but not
both unless resins are
different)
primary resin or
cyanate ester
954-2A, 954-3
Hexcel
interior resin (but not
Note these are
(formerly
both unless fibers are
typically supplied in
available
different)
as prepregs with
from
reinforcement
Fiberite)
primary resin or
cyanate ester
1510
Bryte
interior resin (but not
Note this has
both unless fibers are
typically been
different)
supplied as a wet
resin (as opposed to
a prepreg); however,
the inventors have
had Bryte
specifically tailor the
1510 resin and
supply it as a prepreg
form.
primary resin or
cyanate ester
1545
Bryte
interior resin (but not
Note this has
both unless fibers are
typically been
different)
supplied as a wet
resin
primary resin or
cyanate ester
1522, 1522-1
Bryte
interior resin (but not
Note: these are both
both unless fibers are
supplied as prepregs;
different)
the 1522-1 may also
be supplied as resin
only; the 1522
family is a blend of
epoxy-cyanate ester-
bromine
primary resin or
halogenated epoxy
F155 resin (in which
Hexcel
interior resin (but not
the halogen is
both unless fibers are
Bromine)
different)
primary resin or
halogenated cyanate
EX 1522-1 (in which
Bryte
interior resin (but not
ester
the halogen is
both unless fibers are
Bromine)
different)
primary resin or
halogenated
Avimid N (in which
Fiberite
interior resin (but not
thermoplastic (may
case the halogen is
(formerly
both unless fibers are
be considered a
Fluorine); this
from
different)
pseudothermosetting
material is supplied
DuPont)
one)
as a prepreg
primary resin or
halogenated epoxy,
Examples: EPON
Shell
interior resin (but not
wet resin
1162, 1183 (both of
both unless fibers are
these have Bromine
different)
as a halogen)
primary resin or
thermoplastically
977 resins; most
Hexcel or
interior resin (but not
toughened epoxies
preferred is 977-6
Cytec
both unless fibers are
Fiberite
different)
primary resin or
polyimide (a pseudo-
Avimid R1-16
Cytec-
interior resin (but not
thermosetting type)
Fiberite
both unless fibers are
(formerly
different)
Dupont)
primary resin or
polyimide
Avimid N
Cytec-
interior resin (but not
Fiberite
both unless fibers are
(formerly
different)
Dupont)
primary resin or
polyimide
PIXA
Cytec-
interior resin (but not
Fiberite
both unless fibers are
(formerly
different)
Dupont)
primary resin or
polyimide
Avimid K3B
Cytec-
interior resin (but not
Fiberite
both unless fibers are
(formerly
different)
Dupont)
primary resin or
polyimide
Avimid NR150
Cytec-
interior resin (but not
Fiberite
both unless fibers are
(formerly
different)
Dupont)
primary resin or
polyimide (a pseudo-
Avimid R
Cytec-
interior resin (but not
thermosetting type)
Fiberite
both unless fibers are
(formerly
different)
Dupont)
resin-rich interior
surface (fiber - IM7,
resin - epoxy such as
977-6 or cyanate
ester/bromine/epoxy
blend 1522)
Embodiment 4 - Toughened Epoxy Composites for Oxygen Systems
prepreg
fiber-reinforced
Reinforcement fiber,
Hexcel or
toughened epoxy;
such as graphite like
Cytec
(prepreg may be
IM7 fiber with
Fiberite
impregnated in the
977, specifically 977-
form of slit tape, uni-
6
tape, fabric, tow,
chopped fiber, or
felt)
prepreg
fiber-reinforced
Reinforcement fiber,
Toray or
toughened epoxy;
such as M55J fiber
Cytec
(prepreg may be
with 977-6 resin
Fiberite
impregnated in the
form of slit tape, uni-
tape, fabric, tow,
chopped fiber, or
felt)
fiber
intermediate
Examples: IM7, IM6,
Hexcel
modulus, high
IM2; Note: Preferred
strength graphite,
is IM7
which may be uni-
directional tape, slit
tape, tow, fabric,
woven fabric,
chopped fiber, or felt
fiber
intermediate
Examples: T650,
Amoco
modulus, high
T800, T300
strength graphite,
which may be uni-
directional tape, slit
tape, tow, fabric,
woven fabric,
chopped fiber, or felt
fiber
high modulus,
Example: M55J
Toray
intermediate strength
graphite
(uni-directional tape,
slit tape, fabric,
woven fabric,
chopped fiber, or
felt)
fiber
glass (E, S, or C
Fiberglas
Owens/
type)
Corning
fiber
Aramid
Kevlar ®
Hexcel
resin
thermoplastically
977 resins; most
Hexcel or
toughened epoxies
preferred is 977-6
Cytec
Fiberite
toughening material
thermoplastic
(present in 977-6
Hexcel or
material
resin, believed to be
Cytec
proprietary to the
Fiberite
supplier)
Embodiment 5 - Polyimide Composites for Oxygen Systems
prepreg
fiber-reinforced
Reinforcement fiber,
Cytec
toughened epoxy;
such as graphite like
Fiberite
(prepreg may be
IM7 fiber with an
(formerly
impregnated in the
Avimid
DuPont)
form of slit tape, uni-
tape, fabric, chopped
fiber, or felt)
fiber
intermediate
Examples: IM7,
Hexcel
modulus, high
IM6, IM2; Note:
strength graphite,
Preferred is IM7
which may be uni-
directional tape, slit
tape, fabric, tow,
woven fabric,
chopped fiber, or felt
fiber
intermediate
Examples T650,
Amoco
modulus, high
T800, T300
strength graphite,
which may be uni-
directional tape, tow,
slit tape, fabric,
woven fabric,
chopped fiber, or felt
fiber
high modulus,
Example: M55J
Toray
intermediate strength
graphite
fiber
glass (E, S, or C
Fiberglas
Owens/
type)
Corning
fiber
Aramid
Kevlar ®
Hexcel
resin
polyimide (a pseudo-
Avimid R1-16
Cytec-
thermosetting type)
Fiberite
(formerly
Dupont)
resin
polyimide
Avimid N
Cytec-
Fiberite
(formerly
Dupont)
resin
polyimide
PIXA
Cytec-
Fiberite
(formerly
Dupont)
resin
polyimide
Avimid K3B
Cytec-
Fiberite
(formerly
Dupont)
resin
polyimide
Avimid NR 150
Cytec-
Fiberite
(formerly
Dupont)
resin
polyimide (a pseudo-
Avimid R
Cytec-
thermosetting type)
Fiberite
(formerly
Dupont)
Embodiment 6 - Lined/Coated Composites for Oxygen Systems
liner
polyimide
Kapton
DuPont
liner
polyimide/
Kapton/Teflon
DuPont
fluoropolymer
liner
Metallized polyimide
metallized Kapton
Sheldahl
film
liner
Metallized
metallized FEP
Sheldahl
fluoropolymer
liner
Multilayer metallized
(the multilayer
Sheldahl
polymer
metallized polymer
liner disclosed in
U.S. Pat. No.
5,419,139 with
Kapton or FEP
being used as the
film layer)
coating
fluoropolymer
PCTFE (dispersion
General
coated)
Plastics
coating
fluoropolymer
PTFE
Plasma
Processes
fiber
graphite fiber
IM7
Hexcel
resin
epoxy resin
977-2
Hexcel or
Cytec
Fiberite

The following list describes the parts shown in FIG. 7:

  • A) BASE PLATE: Aluminum, ⅝″ thick with no deep scratches or pits. (If surface is damaged, a thin caul plate must be used to provide a smooth tool surface);
  • B) BREATHER: Airtech Super 10 or Ultraweave 1032;
  • C) SEALANT TAPE: Schnee-Moorehead 5626 or Airtech GS-213;
  • D) LAMINATE: Lay-up Orientation (example: [0,45,90,-45]2S);
  • F) RELEASE FILM: Airtech, A4000R Release Film, (1 mil);
  • G) CAUL SHEET: Torr, EL82, 50 DURO, 48″ width, 0.063″ Thick;
  • H) VACUUM COUPLING: 2 required, 1 source & 1 transducer. Minimum of two plies of breather under couplings;
  • I) VACUUM BAG: Airtech, DP1000 SHTG, 2 mil;
  • J) THERMOCOUPLE: 2 required, opposite edges of laminate, mid ply.

All measurements disclosed herein are at standard temperature and pressure, at sea level on Earth, unless indicated otherwise. All materials used or intended to be used in a human being are biocompatible, unless indicated otherwise.

The foregoing embodiments are presented by way of example only; the scope of the present invention is to be limited only by the following claims.

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Citation

Title Current Assignee Application Date Publication Date
Pressurized and/or cryogenic gas containers and conduits made with a gas impermeable polymer KURARAY CO., LTD. 05 July 1990 29 September 1992
Cryogenic insulating material ATAKA & COMPANY, LTD. 08 November 1973 15 July 1975
Production of improved preimpregnated material comprising a particulate thermosetting resin suitable for use in the formation of a substantially void-free fiber-reinforced composite article CYTEC TECHNOLOGY CORP. 03 March 1988 24 April 1990
Cryogenic insulating structure MITSUBISHI KASEI CORPORATION 12 September 1975 23 August 1977
Foam, Foam-resin composite and method of making a foam-resin composite LOCKHEED MARTIN CORPORATION 20 May 1993 10 January 1995
Title Current Assignee Application Date Publication Date
Hybrid Cryogenic Tank Construction and Method of Manufacture Therefor UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 20 July 2007 22 January 2009
Hybrid cryogenic tank construction and method of manufacture therefor UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 20 July 2007 11 January 2011
一种用于液氧容器的聚合物基复合材料及其制备方法和使用方法 哈尔滨工业大学 25 April 2012 22 August 2012
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