US20060093804A1 - Blast resistant liner for use in limited access enclosures - Google Patents
Blast resistant liner for use in limited access enclosures Download PDFInfo
- Publication number
- US20060093804A1 US20060093804A1 US10/979,580 US97958004A US2006093804A1 US 20060093804 A1 US20060093804 A1 US 20060093804A1 US 97958004 A US97958004 A US 97958004A US 2006093804 A1 US2006093804 A1 US 2006093804A1
- Authority
- US
- United States
- Prior art keywords
- liner
- cargo hold
- pressure vessel
- hold
- fiber reinforcement
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
- B65D—CONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
- B65D90/00—Component parts, details or accessories for large containers
- B65D90/22—Safety features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/0015—Devices specially adapted for the protection against criminal attack, e.g. anti-hijacking systems
- B64D45/0061—Devices specially adapted for the protection against criminal attack, e.g. anti-hijacking systems by protecting cabin or cargo hold from bombs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
- B65D—CONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
- B65D90/00—Component parts, details or accessories for large containers
- B65D90/22—Safety features
- B65D90/32—Arrangements for preventing, or minimising the effect of, excessive or insufficient pressure
- B65D90/325—Arrangements for preventing, or minimising the effect of, excessive or insufficient pressure due to explosion, e.g. inside the container
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
- F41H5/00—Armour; Armour plates
- F41H5/013—Mounting or securing armour plates
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
- F41H5/00—Armour; Armour plates
- F41H5/02—Plate construction
- F41H5/04—Plate construction composed of more than one layer
- F41H5/0471—Layered armour containing fibre- or fabric-reinforced layers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42D—BLASTING
- F42D5/00—Safety arrangements
- F42D5/04—Rendering explosive charges harmless, e.g. destroying ammunition; Rendering detonation of explosive charges harmless
- F42D5/045—Detonation-wave absorbing or damping means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2995/00—Properties of moulding materials, reinforcements, fillers, preformed parts or moulds
- B29K2995/0037—Other properties
- B29K2995/0089—Impact strength or toughness
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S428/00—Stock material or miscellaneous articles
- Y10S428/911—Penetration resistant layer
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49616—Structural member making
- Y10T29/49618—Restoring existing member, e.g., reinforcing, repairing
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49616—Structural member making
- Y10T29/49623—Static structure, e.g., a building component
- Y10T29/49629—Panel
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49826—Assembling or joining
- Y10T29/49947—Assembling or joining by applying separate fastener
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49826—Assembling or joining
- Y10T29/49947—Assembling or joining by applying separate fastener
- Y10T29/49948—Multipart cooperating fastener [e.g., bolt and nut]
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
- Y10T428/24058—Structurally defined web or sheet [e.g., overall dimension, etc.] including grain, strips, or filamentary elements in respective layers or components in angular relation
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/249921—Web or sheet containing structurally defined element or component
- Y10T428/249924—Noninterengaged fiber-containing paper-free web or sheet which is not of specified porosity
Definitions
- This invention relates to explosion resistant interior space liners capable of mitigating the shock, overpressure, fragmentation and fire effects of an explosion within the interior space without catastrophic structural or critical systems failure to the building, aircraft or vehicle where the liner is installed.
- the invention particularly relates to aircraft, specifically installation and operation within cargo holds of commercial air transport category aircraft.
- Aircraft are considered to be a likely target for terrorists, based on historical events such as the Pan Am Lockerbie incident, 9/11, and other unexplained in-flight disasters that may have been due to terrorist activity. Therefore, it is a major goal of the US Federal Aviation Administration (FAA) and the US Transportation Safety Authority (TSA) to improve the resistance of aircraft to improvised explosive devices (IED's), particularly explosives placed in checked luggage or cargo, as items placed in the cargo hold are harder to screen than carry-on items.
- FAA Federal Aviation Administration
- TSA US Transportation Safety Authority
- ULD's Unit Load Devices
- a co-pending application by the same inventor addresses the issue of explosives within ULD's.
- Smaller aircraft such as Boeing 737's or regional jets, have open cargo holds where items are placed directly into the hold.
- an explosive device detonated in an aircraft cargo hold has only to puncture the thin aluminum skin or disrupt the sensitive electronic and hydraulic control lines. Even a small explosive detonated in the cargo hold during flight will likely destroy the aircraft. Therefore it is an object of this invention to provide a system that makes the cargo hold of aircraft highly resistant to explosives.
- the invention also applies to many other enclosed spaces besides aircraft which may require resistance to explosives, so other benefits of the invention will be described accordingly.
- the invention is a liner for an enclosed space, and the liner is constructed of a blast resistant composite material.
- the composite material is preferably a polymer resin matrix with a fiber reinforcement.
- the preferred polymer resin matrix includes, but is not limited to a vinyl ester resin.
- the fiber reinforcement is an aramid material.
- the fiber reinforcement is S-2®Glass.
- the fiber reinforcement is a carbon or graphite fiber.
- the liner is fabricated inside the enclosed space.
- the liner is constructed as a segmented three piece self-contained pressure vessel with an end cap at each end.
- the pieces are laid up and cured on a collapsible tool.
- the liner is fabricated using the Vacuum Infusion Process.
- the pieces are assembled to create a pressure vessel inside the interior space such that in the event of an explosion, dilation of the liner is allowed.
- the enclosed space is an aircraft cargo hold.
- the composite thickness is 6-12 plies (4-8 mm) and the weight is 1.5 to 3.0 pounds per square foot.
- a doorway is left in the liner and including an oversized internal door constructed of blast resistant liner material.
- the enclosed space is a room where explosives are stored or processed.
- the enclosed space is the interior of an existing shipping container.
- the enclosed space is a cargo hold on a vehicle or ship.
- the invention is a method of lining a cargo hold with a blast resistant composite material,
- the method includes first fabricating forward and aft bulkheads (i.e. pressure vessel end caps) in-situ and attaching to the cargo hold floor.
- the next step is fabricating the hold floor in-situ and attaching to the end caps as well as the cargo hold floor, then fabricating all left hand side cargo hold segments, starting at the forward end cap and proceeding to the aft end cap such that each segment is bolted to a neighboring flange associated with the adjacent segment.
- the final step is fabricating the right hand side segments, alternating between fore and aft until all segments converge at the main cargo door(s) where doorway cutouts are incorporated, such that an oversized inside door is attached to the cargo hold which becomes self sealing upon pressurization of the cargo hold.
- FIG. 1 illustrates the improved blast resistance of the composite material compared to conventional metal materials.
- FIG. 2 shows the invention assembled inside the cargo hold of a typical aircraft.
- FIG. 3 shows the invention in cross-section installed in a typical aircraft cargo hold.
- FIG. 4 shows the in-situ fabrication of the invention using a collapsible tool.
- FIG. 5 identifies the space claim of the invention relative to a typical aircraft fuselage.
- the inventor has produced a completely new concept for blast protection, enabled in part by employing very different materials than currently used for aircraft, vehicle or building construction.
- Conventional materials such as thin aluminum or steel provide little or no blast protection.
- Conventional materials exhibit relatively low specific strength and/or specific modulus. Consequently, blast resistant containers constructed using conventional materials do not offer a weight efficient solution.
- a new class of materials enables a different approach. Such materials are similar to fiberglass in that they utilize a reinforcing fiber architecture, which is infused with a polymer resin matrix.
- the most effective version of composite construction utilizes materials which exhibit high compressive and tensile specific strengths and high compressive and tensile specific moduli. Specific strength is defined as the ultimate compressive (or tensile) strength of the material divided by its density.
- Specific modulus is the elastic compressive (or tensile) modulus of the material divided by its density.
- the polymer resin matrix is resistant to galvanic corrosion, solvents and chemical agents.
- the inventor has developed a particularly suitable version of the material, described in a co-pending application.
- the fiber reinforcement is treated with a special resin compatible sizing which develops a high specific laminate strength, high specific laminate modulus, high laminate strain to failure and high laminate fracture toughness. These materials have much higher resistance to blast per unit volume than metals.
- FIG. 1 shows the results of a test of the blast resistant composite compared to aluminum, particularly relevant for aircraft, whose skins are aluminum.
- the aluminum plate 1 ruptures when exposed to blast from 2.7 kg of C-4 at a standoff distance of 152 mm.
- the composite plate 2 does not rupture when exposed to a blast from 4.6 kg of C-4 at the same distance.
- the novel invention is a composite liner 5 , shown in FIG. 2 as a Cargo Hold Liner (CHL) installed in a typical aircraft.
- FIG. 3 shows a cross-section of the aircraft cargo hold 3 and the three segmented pieces 4 of the composite liner installed within the aircraft cargo hold.
- the segments of the Cargo Hold Liner will be fabricated inside the aircraft's cargo hold 3 by laying up successive plies of 60 inch wide overlapping woven fabric broadgoods to the required wall thickness.
- the plies will be laid-up and bagged on a collapsible tool surface 7 as shown in FIG. 4 and cured inside the cargo hold 3 using the Vacuum Infusion Process (VIP).
- VIP Vacuum Infusion Process
- VOC's volatile organic compounds
- cured segments 4 of the composite Cargo Hold Liner 5 are removed from the collapsible tool and assembled inside the aircraft's cargo hold 3 as shown in FIG. 2 .
- the CHL becomes a self contained pressure boundary (i.e. vessel) with its own pressure activated door.
- the CHL is attached to the floor of the cargo hold whereby dilation of the vessel is permitted during explosive detonation. Such dilation allows the CHL to expand (approx.
- soft shell (i.e. blanket type) liners are more compliant (i.e. flexible) and permit excessive deformation which results in greater load transfer to the aircraft fuselage, thereby increasing the risk of impaired air-worthiness
- All composite solutions preferably incorporate, but are not necessarily limited to, a vinyl ester, epoxy or phenolic resin matrix, in conjunction with one of three different types of fiber reinforcements.
- the composite laminate which utilizes a vinyl ester resin, that is resistant to chemical agents and solvents, is ideally suited as a liner within aircraft cargo holds, where spillage or leakage of unwanted or unanticipated caustic cargo could potentially cause significant damage to the aircraft.
- the novel CHL has three preferred reinforcing fibers, namely, an aramid (i.e. Kevlar) fiber solution, an S-2®Glass fiber solution and a carbon (or graphite) fiber solution.
- the acquisition cost for the aramid solution is higher but also offers a lighter weight solution relative to the S-2®Glass solution.
- the aramid solution exhibits a higher repair, maintenance and life cycle cost relative to the S-2®Glass solution by virtue of the significantly reduced compressive strength exhibited by aramid laminates.
- the carbon (or graphite) fiber solution offers improved space efficiency at slightly reduced blast efficiency relative to aramid or S-2®Glass.
- the novel cargo hold liner will be fabricated inside the cargo hold as three cured (i.e. rigid) laminate segments 4 as shown in the cross-sectional view of FIG. 3 , using portable collapsible tooling 7 as shown in FIG. 4 .
- the cured parts i.e. pressure vessel segments
- the flanges of mating segments 6 FIG. 3
- the attachment of the CHL to the cargo hold floor accommodates dilation of the liner floor such that no loads are transferred to the fuselage in the direction transverse to the aircraft.
- the novel liner concept for a CHL creates a structure within a structure, i.e. a pressure vessel within the aircraft cargo hold as shown in FIG. 2 .
- Some interior volume will be lost, as shown in FIG. 5 , based on the maximum thickness and dilational space claim of 12 mm and 13 mm, respectively (or roughly a 1 inch zone around the top and sides and a half inch zone along the floor) as measured inward from the fuselage stringers as for a Boeing 737 aircraft 8 .
- the invention is particularly applicable to aircraft cargo holds, as in addition to extremely effective blast protection, the invention can be installed quickly without otherwise affecting the aircraft. Moreover compared to any other proposed blast protection schemes the invention is much lighter. However, the invention applies equally well to many other applications where it is desirable to blast proof the interior of an enclosed space where the enclosure has small doors thereby limiting access to its interior.
Abstract
The invention is an explosive resistant liner, located inside an enclosed space, and made from a blast resistant material. The liner is preferably constructed inside the enclosed space, consisting of lay-up, curing and assembly steps utilizing a collapsible tool. The invention is particularly applicable to blast protection for aircraft cargo holds.
Description
- Not Applicable
- Not Applicable
- Not Applicable
- This invention relates to explosion resistant interior space liners capable of mitigating the shock, overpressure, fragmentation and fire effects of an explosion within the interior space without catastrophic structural or critical systems failure to the building, aircraft or vehicle where the liner is installed. The invention particularly relates to aircraft, specifically installation and operation within cargo holds of commercial air transport category aircraft.
- Aircraft are considered to be a likely target for terrorists, based on historical events such as the Pan Am Lockerbie incident, 9/11, and other unexplained in-flight disasters that may have been due to terrorist activity. Therefore, it is a major goal of the US Federal Aviation Administration (FAA) and the US Transportation Safety Authority (TSA) to improve the resistance of aircraft to improvised explosive devices (IED's), particularly explosives placed in checked luggage or cargo, as items placed in the cargo hold are harder to screen than carry-on items.
- Wide body aircraft store cargo in containers called Unit Load Devices, (ULD's), which are loaded with cargo and luggage before being placed in the aircraft. A co-pending application by the same inventor addresses the issue of explosives within ULD's. Smaller aircraft, such as Boeing 737's or regional jets, have open cargo holds where items are placed directly into the hold. To cause an aircraft to become non-airworthy, an explosive device detonated in an aircraft cargo hold has only to puncture the thin aluminum skin or disrupt the sensitive electronic and hydraulic control lines. Even a small explosive detonated in the cargo hold during flight will likely destroy the aircraft. Therefore it is an object of this invention to provide a system that makes the cargo hold of aircraft highly resistant to explosives. The invention also applies to many other enclosed spaces besides aircraft which may require resistance to explosives, so other benefits of the invention will be described accordingly.
- The invention is a liner for an enclosed space, and the liner is constructed of a blast resistant composite material. In the preferred embodiment, the composite material is preferably a polymer resin matrix with a fiber reinforcement. The preferred polymer resin matrix includes, but is not limited to a vinyl ester resin. In one version, the fiber reinforcement is an aramid material. In another version, the fiber reinforcement is S-2®Glass. In another version, the fiber reinforcement is a carbon or graphite fiber.
- In one embodiment, the liner is fabricated inside the enclosed space. In one version the liner is constructed as a segmented three piece self-contained pressure vessel with an end cap at each end. In another aspect, the pieces are laid up and cured on a collapsible tool.
- In another embodiment the liner is fabricated using the Vacuum Infusion Process. In one version, the pieces are assembled to create a pressure vessel inside the interior space such that in the event of an explosion, dilation of the liner is allowed.
- In one version, of the liner, the enclosed space is an aircraft cargo hold. In one aspect of this version, the composite thickness is 6-12 plies (4-8 mm) and the weight is 1.5 to 3.0 pounds per square foot. In one version, a doorway is left in the liner and including an oversized internal door constructed of blast resistant liner material.
- In one embodiment, the enclosed space is a room where explosives are stored or processed. In another, the enclosed space is the interior of an existing shipping container. In a further embodiment the enclosed space is a cargo hold on a vehicle or ship.
- In another embodiment, the invention is a method of lining a cargo hold with a blast resistant composite material, The method includes first fabricating forward and aft bulkheads (i.e. pressure vessel end caps) in-situ and attaching to the cargo hold floor. The next step is fabricating the hold floor in-situ and attaching to the end caps as well as the cargo hold floor, then fabricating all left hand side cargo hold segments, starting at the forward end cap and proceeding to the aft end cap such that each segment is bolted to a neighboring flange associated with the adjacent segment. The final step is fabricating the right hand side segments, alternating between fore and aft until all segments converge at the main cargo door(s) where doorway cutouts are incorporated, such that an oversized inside door is attached to the cargo hold which becomes self sealing upon pressurization of the cargo hold.
- The invention will be better understood by referring to the following illustrations.
-
FIG. 1 illustrates the improved blast resistance of the composite material compared to conventional metal materials. -
FIG. 2 shows the invention assembled inside the cargo hold of a typical aircraft. -
FIG. 3 shows the invention in cross-section installed in a typical aircraft cargo hold. -
FIG. 4 shows the in-situ fabrication of the invention using a collapsible tool. -
FIG. 5 identifies the space claim of the invention relative to a typical aircraft fuselage. - The inventor has produced a completely new concept for blast protection, enabled in part by employing very different materials than currently used for aircraft, vehicle or building construction. Conventional materials such as thin aluminum or steel provide little or no blast protection. Conventional materials exhibit relatively low specific strength and/or specific modulus. Consequently, blast resistant containers constructed using conventional materials do not offer a weight efficient solution. A new class of materials enables a different approach. Such materials are similar to fiberglass in that they utilize a reinforcing fiber architecture, which is infused with a polymer resin matrix. The most effective version of composite construction utilizes materials which exhibit high compressive and tensile specific strengths and high compressive and tensile specific moduli. Specific strength is defined as the ultimate compressive (or tensile) strength of the material divided by its density. Specific modulus is the elastic compressive (or tensile) modulus of the material divided by its density. The polymer resin matrix is resistant to galvanic corrosion, solvents and chemical agents. The inventor has developed a particularly suitable version of the material, described in a co-pending application. In this version, the fiber reinforcement is treated with a special resin compatible sizing which develops a high specific laminate strength, high specific laminate modulus, high laminate strain to failure and high laminate fracture toughness. These materials have much higher resistance to blast per unit volume than metals.
-
FIG. 1 shows the results of a test of the blast resistant composite compared to aluminum, particularly relevant for aircraft, whose skins are aluminum. As shown inFIG. 1 thealuminum plate 1 ruptures when exposed to blast from 2.7 kg of C-4 at a standoff distance of 152 mm. Thecomposite plate 2 does not rupture when exposed to a blast from 4.6 kg of C-4 at the same distance. - In order to simultaneously defeat blast and fragmentation threats at minimum weight, the novel invention is a
composite liner 5, shown inFIG. 2 as a Cargo Hold Liner (CHL) installed in a typical aircraft.FIG. 3 shows a cross-section of the aircraft cargo hold 3 and the three segmentedpieces 4 of the composite liner installed within the aircraft cargo hold. The segments of the Cargo Hold Liner will be fabricated inside the aircraft'scargo hold 3 by laying up successive plies of 60 inch wide overlapping woven fabric broadgoods to the required wall thickness. The plies will be laid-up and bagged on acollapsible tool surface 7 as shown inFIG. 4 and cured inside thecargo hold 3 using the Vacuum Infusion Process (VIP). This is a closed cell curing process by which the release of volatile organic compounds (VOC's) is negligible and maintained well below EPA exposure limits. After the in-situ curing of parts is completed, curedsegments 4 of the compositeCargo Hold Liner 5 are removed from the collapsible tool and assembled inside the aircraft'scargo hold 3 as shown inFIG. 2 . After assembly of the segments, the CHL becomes a self contained pressure boundary (i.e. vessel) with its own pressure activated door. The CHL is attached to the floor of the cargo hold whereby dilation of the vessel is permitted during explosive detonation. Such dilation allows the CHL to expand (approx. 12 mm on each side) without contacting the fuselage of the aircraft's cargo hold while simultaneously preventing fragmentation threats from penetrating. Alternatively, soft shell (i.e. blanket type) liners are more compliant (i.e. flexible) and permit excessive deformation which results in greater load transfer to the aircraft fuselage, thereby increasing the risk of impaired air-worthiness - Three preferred composite laminate solutions are contemplated, each offering slightly different costs and benefits. All composite solutions preferably incorporate, but are not necessarily limited to, a vinyl ester, epoxy or phenolic resin matrix, in conjunction with one of three different types of fiber reinforcements. The composite laminate which utilizes a vinyl ester resin, that is resistant to chemical agents and solvents, is ideally suited as a liner within aircraft cargo holds, where spillage or leakage of unwanted or unanticipated caustic cargo could potentially cause significant damage to the aircraft.
- With regard to fiber reinforcement, the novel CHL has three preferred reinforcing fibers, namely, an aramid (i.e. Kevlar) fiber solution, an S-2®Glass fiber solution and a carbon (or graphite) fiber solution. The acquisition cost for the aramid solution is higher but also offers a lighter weight solution relative to the S-2®Glass solution. On the other hand, the aramid solution exhibits a higher repair, maintenance and life cycle cost relative to the S-2®Glass solution by virtue of the significantly reduced compressive strength exhibited by aramid laminates. The carbon (or graphite) fiber solution offers improved space efficiency at slightly reduced blast efficiency relative to aramid or S-2®Glass.
- The following wall thicknesses and weights are applicable to the novel CHL design:
-
- Thickness: ranging from 6 to 12 plies of laminate (4 mm to 8 mm) depending on location on the CHL surface; and
- Weight: ranging from 1.5 to 3.0 pounds per square foot depending on location
- As previously mentioned, the novel cargo hold liner will be fabricated inside the cargo hold as three cured (i.e. rigid)
laminate segments 4 as shown in the cross-sectional view ofFIG. 3 , using portablecollapsible tooling 7 as shown inFIG. 4 . After tooling 7 is collapsed to facilitate removal of the part from the tool, as well as removal of the tool through the cargo hold door, the cured parts (i.e. pressure vessel segments) will be assembled inside the aircraft as shown inFIG. 2 and attached to the floor of the cargo hold. The flanges ofmating segments 6,FIG. 3 , will be mechanically fastened using through bolts which are all accessed from inside the CHL. The attachment of the CHL to the cargo hold floor accommodates dilation of the liner floor such that no loads are transferred to the fuselage in the direction transverse to the aircraft. The order of part fabrication and assembly is described as follows: -
- 1. Forward and aft (CHL) bulkheads (i.e. pressure vessel end caps) will first be fabricated in-situ and attached to the aircraft cargo hold floor.
- 2. Next the CHL floor will be fabricated in-situ and attached to the end caps as well as the cargo hold floor.
- 3. Next to be fabricated are all left hand side CHL segments starting at the forward end cap and proceeding to the aft end cap. Each segment is to be bolted to a neighboring flange associated with the adjacent segment.
Finally, the right hand side segments are to be fabricated alternating between fore and aft until all segments converge at the main cargo door(s) where doorway cutouts are to be incorporated. An oversized inside door is attached to the CHL which becomes self sealing upon pressurization of the cargo hold.
- The novel liner concept for a CHL creates a structure within a structure, i.e. a pressure vessel within the aircraft cargo hold as shown in
FIG. 2 . Some interior volume will be lost, as shown inFIG. 5 , based on the maximum thickness and dilational space claim of 12 mm and 13 mm, respectively (or roughly a 1 inch zone around the top and sides and a half inch zone along the floor) as measured inward from the fuselage stringers as for aBoeing 737 aircraft 8. - The invention is particularly applicable to aircraft cargo holds, as in addition to extremely effective blast protection, the invention can be installed quickly without otherwise affecting the aircraft. Moreover compared to any other proposed blast protection schemes the invention is much lighter. However, the invention applies equally well to many other applications where it is desirable to blast proof the interior of an enclosed space where the enclosure has small doors thereby limiting access to its interior.
- Other application examples are
-
- Bomb proofing rooms at police or military installations to either store, or work on, explosives.
- Bomb-proofing existing shipping containers.
- Bomb proofing cargo spaces on vehicles or ships.
Other uses within the scope of the invention will suggest themselves to those concerned with blast protection.
Claims (35)
1. A liner for an enclosed space, wherein the liner is constructed of a blast resistant composite material configured as a rigid pressure vessel structure capable of mitigating overpressure from a blast originating within the pressure vessel.
2. The liner of claim 1 wherein the composite material comprises a resin matrix with a fiber reinforcement.
3. The liner of claim 2 wherein the fiber reinforcement is an aramid material.
4. The liner of claim 2 wherein the fiber reinforcement is S-2 glass.
5. The liner of claim 2 wherein the fiber reinforcement is a graphite or carbon fiber.
6. The liner of claim 1 wherein the liner is fabricated inside the enclosed space.
7. The liner of claim 6 , wherein the liner is constructed as a segmented three piece self-contained pressure vessel with an end cap at each end.
8. The liner of claim 7 wherein the pieces are laid up and cured on a collapsible tool.
9. The liner of claim 8 wherein the laying up and curing is accomplished with a Vacuum Infusion Process.
10. The liner of claim 7 wherein the pieces are assembled into a pressure vessel within the interior space such that in the event of an explosion, dilation of the liner is allowed.
11. The liner of claim 1 wherein the enclosed space is an aircraft cargo hold, whereby the amount of liner dilation is limited in order to avoid contact with and load transfer to the aircraft fuselage.
12. The liner of claim 11 wherein the composite thickness is 6-12 plies (4-8 mm) and the weight is 1.5 to 3.0 pounds per square foot.
13. The liner of claim 11 wherein a doorway is left in the liner and including an oversized internal door constructed of blast resistant liner material.
14. The liner of claim 1 wherein the enclosed space is a room where explosives are stored or processed.
15. The liner of claim 1 wherein the enclosed space is the interior of an existing shipping container,
16. The liner of claim 1 wherein the enclosed space is a cargo hold on a vehicle or ship.
17. A method of lining a cargo hold with a blast resistant composite material, comprising;
first fabricating forward and aft hold bulkheads (i.e. pressure vessel end caps) in-situ and attaching to a cargo hold floor,
next fabricating a floor segment in-situ and attaching to the end caps as well as the cargo hold floor,
then fabricating all left hand side cargo hold segments, starting at the forward end cap and proceeding to the aft end cap such that each segment is bolted to a neighboring flange associated with the adjacent segment; and,
fabricating right hand side segments, alternating between fore and aft until all segments converge at the main cargo door(s) where doorway cutouts are incorporated, such that an oversized inside door is attached to the cargo hold which becomes self sealing upon pressurization of the cargo hold.
18. The method of claim 17 further comprising using a collapsible tool to facilitate in-situ fabrication.
19. A method for adding a blast resistant cargo hold liner to an existing cargo hold, wherein the cargo hold has a door with dimensions smaller than the dimensions of the internal space, comprising;
bringing into the hold's interior space collapsible tooling through the existing door,
laying up and curing liner sections on the collapsible tool, wherein the sections are constructed of a blast resistant composite,
collapsing and removing the tool from the hold; and,
assembling the cured sections into a pressure vessel and attaching the pressure vessel to the interior of the hold.
20. The method of claim 19 wherein the sections include mating flanges, which are mechanically fastened using through bolts which are all accessed from inside the pressure vessel.
21. The method of claim 19 wherein the segments include at least three liner segments and at least two liner endcaps.
22. The method of claim 19 wherein the composite material comprises a resin matrix with a fiber reinforcement.
23. The method of claim 22 wherein the fiber reinforcement is an aramid material.
24. The method of claim 22 wherein the fiber reinforcement is S-2 glass.
25. The method of claim 22 wherein the fiber reinforcement is a graphite or carbon fiber.
26. The method of claim 19 wherein the laying up and curing is accomplished with a Vacuum Infusion Process.
27. The method of claim 19 wherein the pieces are assembled into a pressure vessel within the interior space such that in the event of an explosion, dilation of the liner is allowed.
28. The method of claim 19 wherein the cargo hold is an aircraft cargo hold whereby the amount of liner dilation is limited in order to avoid contact with and load transfer to the aircraft fuselage.
29. The method of claim 19 wherein the composite thickness is 6-12 plies (4-8 mm) and the weight is 1.5 to 3.0 pounds per square foot.
30. The method of claim 19 wherein a doorway is left in the liner and includes an oversized internal door constructed of blast resistant liner material.
31. The method of claim 19 wherein the cargo hold is a room where explosives are stored or processed.
32. The method of claim 19 wherein the cargo hold is the interior of an existing shipping container,
33. The method of claim 19 wherein the cargo hold is a cargo hold on a vehicle or ship.
34. The method of claim 19 wherein the resin matrix is a vinyl ester resin.
35. The method of claim 2 wherein the resin matrix is a vinyl ester resin.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/979,580 US20060093804A1 (en) | 2004-11-01 | 2004-11-01 | Blast resistant liner for use in limited access enclosures |
PCT/US2005/039412 WO2007001437A2 (en) | 2004-11-01 | 2005-10-31 | Blast resistant liner for cargo holds |
US11/505,155 US7461453B1 (en) | 2004-11-01 | 2006-08-15 | Method for adding a blast resistant cargo hold liner |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/979,580 US20060093804A1 (en) | 2004-11-01 | 2004-11-01 | Blast resistant liner for use in limited access enclosures |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/505,155 Continuation US7461453B1 (en) | 2004-11-01 | 2006-08-15 | Method for adding a blast resistant cargo hold liner |
Publications (1)
Publication Number | Publication Date |
---|---|
US20060093804A1 true US20060093804A1 (en) | 2006-05-04 |
Family
ID=36262310
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/979,580 Abandoned US20060093804A1 (en) | 2004-11-01 | 2004-11-01 | Blast resistant liner for use in limited access enclosures |
US11/505,155 Expired - Fee Related US7461453B1 (en) | 2004-11-01 | 2006-08-15 | Method for adding a blast resistant cargo hold liner |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/505,155 Expired - Fee Related US7461453B1 (en) | 2004-11-01 | 2006-08-15 | Method for adding a blast resistant cargo hold liner |
Country Status (2)
Country | Link |
---|---|
US (2) | US20060093804A1 (en) |
WO (1) | WO2007001437A2 (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1992903A2 (en) | 2007-05-15 | 2008-11-19 | GEKE Technologie GmbH | Water vehicle with a protection device against hollow charges |
US20110185884A1 (en) * | 2008-06-13 | 2011-08-04 | Esw Gmbh | Bullet-resistant transparent laminate composite and protection arrangement having a bullet-resistant transparent laminate composite |
US20110247958A1 (en) * | 2008-10-16 | 2011-10-13 | Composite Transport Technologies ,Inc. | Lightweight unit load device |
CN110425953A (en) * | 2019-08-09 | 2019-11-08 | 余姚菲戈自动化技术有限公司 | A kind of urgent apparatus for destroying of inflammable and explosive substances |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102575846B (en) * | 2009-08-21 | 2014-08-06 | 戴纳安全国际有限公司 | Closed vessel arrangement for safe destruction of rocket motors |
US8728374B1 (en) | 2011-08-02 | 2014-05-20 | Crane Composites Inc. | Method of manufacturing a foundation wall panel |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5190802A (en) * | 1989-01-06 | 1993-03-02 | Pilato Louis A | Ballistic resistant laminate |
US5545455A (en) * | 1993-04-01 | 1996-08-13 | Alliedsignal Inc. | Constructions having improved penetration resistance |
US5591933A (en) * | 1992-06-01 | 1997-01-07 | Alliedsignal Inc. | Constructions having improved penetration resistance |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2362951A (en) * | 1941-04-08 | 1944-11-14 | Vickers Armstrongs Ltd | Pressure-tight cabin for aircraft |
US3167209A (en) * | 1957-11-20 | 1965-01-26 | Wayne W Jones | Flexible tank liner |
DE3024410C2 (en) * | 1980-06-28 | 1986-10-09 | Aluminium-Walzwerke Singen Gmbh, 7700 Singen | Freight containers, in particular for air transport |
GB8925193D0 (en) * | 1989-11-08 | 1991-01-02 | Royal Ordnance Plc | The protection of aircraft structures |
US5769257A (en) * | 1994-05-04 | 1998-06-23 | Galaxy Scientific Corporation | Method and apparatus for minimizing blast damage caused by an explosion in aircraft cargo bay |
US6341708B1 (en) * | 1995-09-25 | 2002-01-29 | Alliedsignal Inc. | Blast resistant and blast directing assemblies |
US6991124B1 (en) * | 1995-09-25 | 2006-01-31 | Alliedsignal Inc. | Blast resistant and blast directing containers and methods of making |
US6019237A (en) * | 1998-04-06 | 2000-02-01 | Northrop Grumman Corporation | Modified container using inner bag |
US6237793B1 (en) * | 1998-09-25 | 2001-05-29 | Century Aero Products International, Inc. | Explosion resistant aircraft cargo container |
US6454085B1 (en) * | 2001-01-18 | 2002-09-24 | Halliburton Energy Services, Inc. | Method and system for packaging explosive products of transportation |
US6703104B1 (en) * | 2002-01-04 | 2004-03-09 | Murray L. Neal | Panel configuration composite armor |
US8316752B2 (en) * | 2003-07-31 | 2012-11-27 | Blastgard Technologies, Inc. | Acoustic shock wave attenuating assembly |
-
2004
- 2004-11-01 US US10/979,580 patent/US20060093804A1/en not_active Abandoned
-
2005
- 2005-10-31 WO PCT/US2005/039412 patent/WO2007001437A2/en active Application Filing
-
2006
- 2006-08-15 US US11/505,155 patent/US7461453B1/en not_active Expired - Fee Related
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5190802A (en) * | 1989-01-06 | 1993-03-02 | Pilato Louis A | Ballistic resistant laminate |
US5591933A (en) * | 1992-06-01 | 1997-01-07 | Alliedsignal Inc. | Constructions having improved penetration resistance |
US5545455A (en) * | 1993-04-01 | 1996-08-13 | Alliedsignal Inc. | Constructions having improved penetration resistance |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1992903A2 (en) | 2007-05-15 | 2008-11-19 | GEKE Technologie GmbH | Water vehicle with a protection device against hollow charges |
EP1992903A3 (en) * | 2007-05-15 | 2011-08-24 | GEKE Technologie GmbH | Water vehicle with a protection device against hollow charges |
US20110185884A1 (en) * | 2008-06-13 | 2011-08-04 | Esw Gmbh | Bullet-resistant transparent laminate composite and protection arrangement having a bullet-resistant transparent laminate composite |
US8833233B2 (en) | 2008-06-13 | 2014-09-16 | Krd Sicherheitstechnik Gmbh | Bullet-resistant transparent laminate composite and protection arrangement having a bullet-resistant transparent laminate composite |
US20110247958A1 (en) * | 2008-10-16 | 2011-10-13 | Composite Transport Technologies ,Inc. | Lightweight unit load device |
CN110425953A (en) * | 2019-08-09 | 2019-11-08 | 余姚菲戈自动化技术有限公司 | A kind of urgent apparatus for destroying of inflammable and explosive substances |
Also Published As
Publication number | Publication date |
---|---|
WO2007001437A3 (en) | 2007-05-24 |
US7461453B1 (en) | 2008-12-09 |
US20080282545A1 (en) | 2008-11-20 |
WO2007001437A2 (en) | 2007-01-04 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US7461453B1 (en) | Method for adding a blast resistant cargo hold liner | |
US8777161B2 (en) | Lightweight blast mitigating composite panel | |
US4664967A (en) | Ballistic spall liner | |
US7520223B2 (en) | Explosive effect mitigated containers | |
EP2813425B1 (en) | Self-balancing pressure bulkhead | |
US5654053A (en) | High-energy-absorbing enclosure for internal explosion containment | |
US7597040B2 (en) | Composite containment of high energy debris and pressure | |
US20080308676A1 (en) | Aircraft Fuselage | |
EP0456779B1 (en) | Containers for use on aircraft for the protection of aircraft structures | |
EP2048079A2 (en) | Fuel tank assembly and associated method | |
US20140053718A1 (en) | Ballistic resistant and explosive containment systems for aircraft | |
Heimbs | Energy absorption in aircraft structures | |
CA2840077C (en) | Blast and fragment resistant wall sections used inside structures like ships | |
US9441788B2 (en) | Tank resistant to the overpressures caused by projectile impact | |
Horsfall et al. | Structural ballistic armour for transport aircraft | |
CA2845786C (en) | Structural component for armoured vehicles | |
GB2479785A (en) | Vehicle | |
RU2257537C1 (en) | Container for localization of explosion | |
Johnson et al. | Design of composite wing access cover under impact loads | |
US20230041009A1 (en) | Blast protection panel | |
CN100380092C (en) | Antiexplosion box used in civil aircraft passenger cabinet | |
Clark et al. | Armored Composite Ammunition Pressure Vessel | |
CN116164607A (en) | Non-inclusive airborne antiknock device | |
Alankaya | Success story of armored multitask vehicle design | |
Veldman et al. | Lightweight mitigating materials for structures under close-in blast loading |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: FRIEDMAN RESEARCH CORPORATION, CALIFORNIA Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:WEERTH, D. ERICH;REEL/FRAME:016486/0397 Effective date: 20050325 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |