Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
  • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
  • B64C1/066—Interior liners
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B27/00—Layered products comprising a layer of synthetic resin
  • B32B27/06—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material
  • B32B27/08—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B27/00—Layered products comprising a layer of synthetic resin
  • B32B27/28—Layered products comprising a layer of synthetic resin comprising synthetic resins not wholly covered by any one of the sub-groups B32B27/30 - B32B27/42
  • B32B27/286—Layered products comprising a layer of synthetic resin comprising synthetic resins not wholly covered by any one of the sub-groups B32B27/30 - B32B27/42 comprising polysulphones; polysulfides
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B27/00—Layered products comprising a layer of synthetic resin
  • B32B27/30—Layered products comprising a layer of synthetic resin comprising vinyl (co)polymers; comprising acrylic (co)polymers
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B27/00—Layered products comprising a layer of synthetic resin
  • B32B27/30—Layered products comprising a layer of synthetic resin comprising vinyl (co)polymers; comprising acrylic (co)polymers
  • B32B27/308—Layered products comprising a layer of synthetic resin comprising vinyl (co)polymers; comprising acrylic (co)polymers comprising acrylic (co)polymers
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B27/00—Layered products comprising a layer of synthetic resin
  • B32B27/36—Layered products comprising a layer of synthetic resin comprising polyesters
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B27/00—Layered products comprising a layer of synthetic resin
  • B32B27/36—Layered products comprising a layer of synthetic resin comprising polyesters
  • B32B27/365—Layered products comprising a layer of synthetic resin comprising polyesters comprising polycarbonates
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B27/00—Layered products comprising a layer of synthetic resin
  • B32B27/42—Layered products comprising a layer of synthetic resin comprising condensation resins of aldehydes, e.g. with phenols, ureas or melamines
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
  • B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
  • B64C1/1476—Canopies; Windscreens or similar transparent elements
  • B64C1/1492—Structure and mounting of the transparent elements in the window or windscreen
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B2250/00—Layers arrangement
  • B32B2250/03—3 layers
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B2250/00—Layers arrangement
  • B32B2250/24—All layers being polymeric
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B2250/00—Layers arrangement
  • B32B2250/40—Symmetrical or sandwich layers, e.g. ABA, ABCBA, ABCCBA
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B2307/00—Properties of the layers or laminate
  • B32B2307/30—Properties of the layers or laminate having particular thermal properties
  • B32B2307/306—Resistant to heat
  • B32B2307/3065—Flame resistant or retardant, fire resistant or retardant
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B2307/00—Properties of the layers or laminate
  • B32B2307/40—Properties of the layers or laminate having particular optical properties
  • B32B2307/412—Transparent
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B2307/00—Properties of the layers or laminate
  • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
  • B32B2307/584—Scratch resistance
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B2307/00—Properties of the layers or laminate
  • B32B2307/70—Other properties
  • B32B2307/704—Crystalline
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B2307/00—Properties of the layers or laminate
  • B32B2307/70—Other properties
  • B32B2307/714—Inert, i.e. inert to chemical degradation, corrosion
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B2605/00—Vehicles
  • B32B2605/003—Interior finishings
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B2605/00—Vehicles
  • B32B2605/18—Aircraft
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
  • B64D2011/0038—Illumination systems for cabins as a whole
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
  • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
  • B64D2013/0603—Environmental Control Systems
  • B64D2013/0625—Environmental Control Systems comprising means for distribution effusion of conditioned air in the cabin
• • 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
  • Y10T428/31504—Composite [nonstructural laminate]
• • 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
  • Y10T428/31504—Composite [nonstructural laminate]
  • Y10T428/31507—Of polycarbonate

Definitions

• the present invention generally relates to layered materials and more specifically to layered, transparent thermoplastic materials having flame resistant properties.
• Transparent windows used today on commercial aircraft are typically formed of a transparent polycarbonate material having a scratch-resistant polysiloxane coating. Because these polycarbonate windows do not meet the FAA requirements for OSU heat release, exemptions have been provided by the FAA to allow their use. For airplane windows, however, the FAA exemption has limited the size of the windows so as not to impose more than the historic vertical burn flammability requirement.
• the present invention provides a layered material is formed by having a thin, flammable and heat resistant outer polymeric material coupled to the exterior of a thicker, transparent polymeric inner material.
• the total thickness of the layered material is between about between about 0.03 and 0.20 inches, more preferably between about 0.04 and 0.12 inches, and most preferably approximately 0.10 inches.
• the layered material meets the current Federal Aviation Administration (“FAA”) requirements in terms of flammability resistance properties (FAR 25.853 and Appendix F), including heat release, vertical burn, smoke emissions tests, and toxic fume emissions tests.
• FAR 25.853 and Appendix F flammability resistance properties
• the layered material also passes the Ohio State University (“OSU”) heat release test as found in FAR 25.853-Part IV.
• the layered material is also durable and scratch resistant and has the desired mechanical properties in terms of strength and flex modulus.
• the layered material is also transparent at thicknesses useful for a wide variety of application.
• One such application is in the cabin interior of commercial aircraft, including, preferably, for use as a transparent dust cover for commercial airplane windows.
• Other applications for the layered material within the cabin interior of commercial aircraft include, but are not limited to, use on back-lit signs or other lighting possibilities, class dividers, bins which do not restrict the view of flight attendants and other safety features such as instrument panels.
• the polymeric inner material is one having the desired transparency and mechanical properties at the desired thickness but alone does not meet the current FAA flammability resistance properties or pass the OSU heat release test.
• the polymeric outer material meets the FAA flammability and OSU heat resistant requirements, but does not possess the requisite transparency at the desired thickness (over about 5 mils).
• the present invention also provides two preferred methods for forming the layered material.
• preformed films of a polymeric outer material are laminated to a preformed inner polymeric material under heat and pressure and subsequently cooled under controlled conditions to form the layered material.
• the polymeric inner material is extruded between preformed film layers of the polymeric outer material and cooled under controlled conditions to form the layered material.
• Figure 1 illustrates a aircraft window assembly formed in accordance with a preferred embodiment of the present invention
• Figure 2 is a section view of a portion of Figure 1 taken along line 2-2;
• Figure 3 is a schematic view of a extrusion assembly line used to make the layered material of Figure 2;
• Figure 4 is a schematic view of a lamination assembly line used to make the layered material of Figure 2;
• Figure 5 is an interior view of an aircraft cabin having a plurality of components utilizing the layered material of Figure 2.
• the present invention discloses a layered material that meets the current Federal
• the layered material also passes the Ohio State University (“OSU”) heat release test as found in FAR 25.853-Part IV.
• the layered material is also durable and scratch resistant and has a thickness between about between about 0.03 and 0.20 inches, more preferably between about 0.04 and 0.12 inches, and most preferably approximately 0.10 inches.
• the layered material in the range of thicknesses above, achieves sufficient transparency and mechanical properties for use in a wide variety of potential applications, including, for example, as a dust cover used in a commercial aircraft window assembly.
• an aircraft window assembly 10 is shown having a multi-piece window assembly 12 that is sealed between and within the outer structure 14 of the fuselage 16 and an inner cabin liner 38.
• the multi-piece window assembly 12 includes a structural window 20 fixedly coupled around an opening 22 in the outer structure 14 using a plurality of screws or rivets 28.
• the window assembly 12 also includes a fail-safe pane 30 and an electronic shade with dust cover 32.
• the multi-piece window assembly 12 is sealed around an opening 34 in an inner fairing 36 of the inner cabin liner 38 and the structural window 20 using a seal 40.
• the dust cover 32 passes current Federal Aviation Administration (FAA) requirements in terms of flammability resistance properties (FAR 25.853 and Appendix F), including heat release, vertical burn, smoke emissions tests, and toxic fume emissions tests.
• FAA Federal Aviation Administration
• the dust cover 32 also passes the Ohio State University heat release test as found in FAR 25.853-Part IV.
• the dust cover 32 is also sufficiently transparent and has acceptable color, and possesses the necessary physical and mechanical properties for use in commercial aircraft, including but not limited to meeting or exceeding below for ultimate tensile strength and modulus, flexural strength and modulus, durability (in terms of ultraviolet light exposure and weather exposure (as described in the Experimental Section), specific gravity and density and impact and scratch resistance at the desired thickness (between about 0.03 and 0.20 inches, more preferably between about 0.04 and 0.12 inches, and most preferably approximately 0.10 inches).
• Table 1 The physical, mechanical and flammability requirements of the dust cover 32 is summarized below in Table 1:
• the dust cover 32 is formed by first coupling a thin polymeric film 42 to at least one, and more preferably both sides of a thicker inner transparent polymeric material 41. The dust cover 32 is then sized and shaped and otherwise post-processed to fit within the openings 22, 34 created within the inner and outer fairings 24, 36 of the window assembly 10.
• the inner transparent polymeric material 41 is one having the desired transparency and mechanical properties as described in Table 1 above at thickness between about 0.03 inches and 0.20 inches for use as a dust cover 32, but alone does not meet the current FAA flammability resistance properties or pass the OSU heat release test as described in the previous paragraphs.
• the thin polymeric film 42 meets the FAA flammability and OSU heat resistant requirements and is sufficiently transparent as a thin film (less than about 5 mils), but does not possess the requisite transparency at thicknesses between 0.03 and 0.20 inches necessary for use as the dust cover 32.
• the outer transparent polymeric film 42 therefore provides the necessary flammability resistance and heat release characteristics to protect the thicker inner material 41 while being thin enough not to adversely affect the transparency of the resultant dust cover 32.
• the outer transparent film 42 also provides solvent resistance, cleanability, durability, weatherability and a degree of scratch resistance to the formed layered dust cover 32.
• One preferred polymeric material used as the inner transparent material 41 is clear, uncolored (or untinted) forms of polycarbonate.
• Preferred sufficiently transparent versions of the polycarbonate have a melt temperature between about 520 and 620 degrees Fahrenheit (270-330 degrees Celsius).
• Examples of specific commercially available polycarbonates that meet the requirements of Table 1 include Lexan ML 4249, Lexan 9600-116, Lexan ML 4506- 116, Lexan ML 4248-116, Lexan ML 4249-116, and Lexan F 2104 all available from GE Plastics of Covier, Ontario Canada.
• Other clear, uncolored polycarbonates that may also be used are Hyzod F 15700 and Hyzod F 15400, both available from Sheffield Plastics of Sheffield, Massachusetts.
• polyethersulfone (“PES”) and various acrylic polymers.
• PES polyethersulfones
• acrylics such as Plexiglas® (available from AtoHaas North America of Philadelphia, Pennsylvania).
• PEKK polyetherketoneketone
• polyetheretherketone PEEK
• Parmax ® SRP a self reinforcing polymer based on homopolymers and copolymers based on a substituted poly(l,4-phenylene) structure where each phenylene ring has a substituent derived from a variety of organic groups and available from Mississippi Polymer Technologies, inc. of Bay St. Louis, Mississippi).
• the ultimate thickness of the film 41 is dependent upon a combination of the flame retardant and transparency properties of the particular polymer or copolymer within the desired thickness range (less than about 5 mils).
• the dust cover 32 is formed, in accordance with one preferred embodiment of the present invention, using a co-extrusion technique.
• the material 104 forming the inner transparent material 41 is loaded into hopper 102 of a single- or multi-screw extruder 100.
• the material 104 is then mixed and melted within the barrel 106 of the extruder 100.
• polycarbonates are melted in the extruder 100 between about 520 and 620 degrees Fahrenheit (between about 270 and 330 degrees Celsius).
• the mixed and melted material 104 exits the extruder 100 through a nozzle 108 and sheet- forming die 110 that are sized to . form a sheet 112 at the desired thickness.
• the sheet 112 exits the die 110 slightly below its melt temperature.
• a pair of outer transparent films 42 are unrolled from individual rollers 114 located above and below the sheet 112, respectively.
• the films 42 and sheet 112 are then moved along a conveyor (not shown) and introduced between a pair of heated polished rollers 116, which presses the films 42 into the extruded sheet 112 at a predetermined pressure.
• the rollers 116 are maintained at about 300 degrees Fahrenheit (about 150 degrees Celsius) and function to chill the inner hot sheet 112, therein allowing the lamination of the outer films 42 to a respective side of the sheet 112.
• the heated laminated material 31 exits the rollers 116 along a second conveyor
• cooling fans 130 located in close proximity to the heating rollers 116, direct airflow to cool the material 31 quickly.
• the cooling rate is controlled by the fans 130 to assure both bond strength between the outer film material 42 and the inner material 112 while minimizing the level of crystallites in the outer film 42 to achieve the necessary transparency.
• the exact process parameters will be determined as a function of processing equipment capabilities, the thermal properties of the materials being used, and the physical dimensions of the required sheets.
• the dust cover 32 is formed, in accordance with another preferred embodiment of the present invention, using a co-lamination technique.
• a pair of outer transparent films 42 are unrolled from rollers 202 above and below a preformed inner transparent material 41 and all are introduced between a pair of heated polished rollers 204.
• the heated laminated material 31 exits the rollers 116 and is cooled to form the layered material 33.
• the predetermined pressure exerted between the rollers 116 and cooling characteristics determines the overall thickness of the layered material 33.
• cooling fans 130 located in close proximity to the heating rollers 116, direct airflow to cool the material 31 quickly.
• the cooling rate is controlled by the fans 130 to assure both bond strength between the outer film material 42 and the inner material 112 while minimizing the level of crystallites in the outer film 42 to achieve the necessary transparency.
• the exact process parameters will be determined as a function of processing equipment capabilities, the thermal properties of the materials being used, and the physical dimensions of the required sheets.
• the layered material 33 formed in accordance with either preferred method is post processed in a manner well known in the aerospace industry concerning shaping windows.
• the layered material 33 is machined or die stamped to the desired shape.
• layered material 33 is ideally suited for use as a transparent dust cover 32 for airplane windows
• a similar layered material 33 (having a thin polymer film 42 coupled to one or more sides on the inner polymer material 41) may be formed and utilized for use on other components 44 within the cabin region of the airplane fuselage.
• non-limiting examples of components 44 that are formed from the layered material of the present invention include countertops 46, cabinet enclosures 48 such as wastebaskets, tray tables 50, backlit lighted signs 52 such as emergency exit signs 54, illuminating window panels 56 having light emitting diode displays 58, window bezels 60, class dividers 62, privacy partitions 64, backlit ceiling panels 66, direct lighting ceiling panels 68, lighted doors 70, lighted door latches 72, doorway linings 74, proximity lights 76, stow bin doors 78, privacy curtains 80, door handles 82 (capable of changing from red to green, for example), amenity cabinets 84, sink decks 86 for lavatories and kitchens (with or without an appropriate undersink enclosure 88), doorway liners 90, stow bin latch handles 92, lighted phones 94, and backlit control panels 96.
• the layered material 33 may also find applications outside of the aerospace industry in components requiring similar mechanical
• test samples were prepared and evaluated for weatherability and durability.
• samples prepared using a polycarbonate inner material 42 coated on either side with a five mil thick PEKK coating 41 were subjected to a 17-day cycle of weatherability.
• This cycle hereinafter referred to as the "GAG" cycle, varies the atmospheric conditions from between -65 and 170 degrees Fahrenheit (about -50 to 75 degrees Celsius) and simulates atmospheric conditions from sea level to the upper atmosphere.
• This test is designed to determine if the materials use in laminated layers will disbond due to dissimilar thermal expansion characteristics.
• the samples made in accordance with the preferred embodiments of the present invention, using either the coextrusion or colamination technique showed no mechanical defects (delamination and durability) or transparency loss.

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• Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Mechanical Engineering (AREA)
• Laminated Bodies (AREA)
• Extrusion Moulding Of Plastics Or The Like (AREA)
• Manufacture Of Macromolecular Shaped Articles (AREA)

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Publications (2)

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• 2005
  • 2005-04-08 US US11/102,401 patent/US8043704B2/en active Active
• 2006
  • 2006-03-17 WO PCT/US2006/010066 patent/WO2006110267A2/en not_active Ceased
  • 2006-03-17 EP EP06748477.4A patent/EP1874537B1/en active Active
  • 2006-03-17 CA CA 2595449 patent/CA2595449A1/en not_active Abandoned
  • 2006-03-17 CN CNA2006800069975A patent/CN101132912A/zh active Pending
  • 2006-03-17 JP JP2008505336A patent/JP2008535691A/ja active Pending
  • 2006-03-17 RU RU2007140830/04A patent/RU2007140830A/ru not_active Application Discontinuation

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