US20060024483A1 - Transparent composite panel - Google Patents
Transparent composite panel Download PDFInfo
- Publication number
- US20060024483A1 US20060024483A1 US10/901,808 US90180804A US2006024483A1 US 20060024483 A1 US20060024483 A1 US 20060024483A1 US 90180804 A US90180804 A US 90180804A US 2006024483 A1 US2006024483 A1 US 2006024483A1
- Authority
- US
- United States
- Prior art keywords
- transparent
- nanofibers
- panel
- matrix
- approximately
- 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
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
- C08K7/00—Use of ingredients characterised by shape
- C08K7/02—Fibres or whiskers
-
- 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
- B29C45/00—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
- B29C45/0005—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor using fibre reinforcements
-
- 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
- B29C45/00—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
- B29C45/14—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
- B29C45/14065—Positioning or centering articles in the mould
- B29C45/14073—Positioning or centering articles in the mould using means being retractable during injection
-
- 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
- B29C45/00—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
- B29C45/14—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
- B29C45/14778—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles the article consisting of a material with particular properties, e.g. porous, brittle
- B29C45/14786—Fibrous material or fibre containing material, e.g. fibre mats or fibre reinforced material
-
- 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
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/12—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of short length, e.g. in the form of a mat
-
- 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
- B29C70/58—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising fillers only, e.g. particles, powder, beads, flakes, spheres
-
- 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
- B64C1/1484—Windows
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B82—NANOTECHNOLOGY
- B82Y—SPECIFIC USES OR APPLICATIONS OF NANOSTRUCTURES; MEASUREMENT OR ANALYSIS OF NANOSTRUCTURES; MANUFACTURE OR TREATMENT OF NANOSTRUCTURES
- B82Y30/00—Nanotechnology for materials or surface science, e.g. nanocomposites
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
- C08K7/00—Use of ingredients characterised by shape
- C08K7/02—Fibres or whiskers
- C08K7/04—Fibres or whiskers inorganic
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
- C08K7/00—Use of ingredients characterised by shape
- C08K7/02—Fibres or whiskers
- C08K7/04—Fibres or whiskers inorganic
- C08K7/14—Glass
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
- C08K2201/00—Specific properties of additives
- C08K2201/011—Nanostructured additives
-
- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
-
- 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
- a transparent nanofiber composite panel 10 constructed according to the principles of the present invention is shown in operative association with a mobile platform 12 .
- the transparent nanofiber composite panel 10 is an optical quality fiber reinforced transparency having high structural strength properties.
- the mobile platform 12 is shown as an aircraft, the mobile platform 12 could also be represented in the form of other mobile platforms, such as a ship, a train, a bus or an automobile.
- the present invention will be described below as particularly applicable for use in association with mobile platforms, the invention should not be so limited in application. It is envisioned that the invention is equally applicable to aircraft, trains, buses, tanks, ships, buildings, or any application where a composite transparency having high strength and lightweight construction is of paramount importance.
Abstract
A transparent nanofiber composite panel that includes a plurality of transparent nanofibers integrated in random orientations within a transparent matrix is provided. The transparent nanofibers have a diameter that is less than the wavelength of visible light. The extremely small diameter of the transparent nanofibers allows the transparent panel to be substantially insensitive to an RI ‘mismatch’ between the transparent nanofibers and the transparent matrix. Additionally, due to random orientation of the transparent nanofibers within the transparent matrix the transparent nanofiber composite panel possesses substantially isotropic material properties such that the transparent nanofiber composite panel can be incorporated as a structural, load bearing, component of a larger structure.
Description
- The present invention relates to composite transparencies and more particularly to transparent composites utilized to provide transparent structural panels that can be incorporated into the structure of a mobile platform.
- Composite transparencies have many applications in many devices and structures. For example, composite transparencies can be utilized in eyeglasses, high security display cases, high-rise building windows and fighter jet cockpit canopies. In a particular instance, composite transparencies can be utilized to construct windows of a mobile platform such as an aircraft, train, bus, tank or ship. Generally, mobile platform windows formed of known transparent materials are not suitable for use as structural component of the mobile platform. In many instances, windows in many commercial mobile platforms are relatively small in size, due, at least in part, to the limited capabilities of current transparent window materials to carry a load and also due to the heavy and complex support structure needed to carry mobile platform fuselage loads around the window cutout in the absence of a load bearing transparency.
- Typically, these transparent window materials consist of a transparent polymer that exhibits such useful qualities as good transparency and easy formation of complex shapes. However, these polymer windows typically have a limited strength capability, tend to be notch sensitive, and craze, i.e. form nuisance cracks, over time at very low stress levels. Moreover, these windows generally require a heavy support structure in order to support the window within the fuselage structure of the mobile platform. Each component of such a support structure is designed to strengthen panels of the fuselage that surround and support each window. However, each component increases the cost and weight of the completed window assembly, thereby providing an incentive to keep some mobile platform windows relatively small.
- In at least some known instances, fiber reinforced transparent composites have been utilized in constructing mobile platform windows that are lighter and stronger than the transparent polymer windows typically used. Such composite windows typically include a transparent fiber integrated within a transparent polymer matrix, e.g. an epoxy resin. To provide high quality transparent properties of such composites, the refraction index (RI) of the transparent fiber must substantially match that of the polymer matrix to a third decimal place. While such RI matching is straightforward, problems arise due to a ‘mismatch’ in the RI's as a function of temperature change. That is, as the environmental temperature to which the transparent composite is exposed changes, the RI of the polymer matrix and/or the RI of the fiber will change such that there is a ‘mismatch’ between the RI's of the matrix and the fiber. Typically, the RI changes significantly for the polymer matrix but is relatively constant for the fiber. Therefore, changes in the environmental temperature, either increases and/or decreases, can cause a ‘mismatch’ of RI's of the matrix and the fiber. A significant ‘mismatch’, e.g. greater than 0.01, between the RI of the matrix and the RI of the fiber causes clouding of the transparent composite.
- Accordingly, the present invention seeks to provide the art with a strong composite transparency that can provide excellent structural strength and does not suffer from opacity at extreme temperatures. The present invention is focused on use with an aircraft window, however it is applicable to any transparency where high strength and lightweight construction are of paramount importance.
- A transparent nanofiber composite panel is provided in accordance with a preferred embodiment of the present invention. The transparent nanofiber composite panel includes a plurality of transparent nanofibers integrated in random orientations within a transparent matrix. The transparent nanofibers have a diameter that is less than the wavelength of visible light. In a preferred exemplary embodiment, the transparent nanofibers are constructed of glass. Alternatively, the transparent nanofibers can be constructed of any other suitable transparent material having high strength properties, for example, silicon dioxide, graphite or a transparent polymer such as nylon or polycarbonate.
- In a preferred form, the transparent matrix is formed from a transparent epoxy resin. The high transmittance of the transparent nanofibers resulting from having a diameter less than the wavelength of visible light permits variations in the refraction index (RI) of the matrix that may occur due to extreme temperatures, without affecting the translucency of the transparent nanofiber composite panel. More specifically, the extremely small diameter of the transparent nanofibers allows the transparent panel to be substantially insensitive to an RI ‘mismatch’ between the transparent nanofibers and the transparent matrix.
- Due to the random orientation of the transparent nanofibers within the transparent matrix, the transparent nanofiber composite panel comprises substantially isotropic material properties. For example, the transparent nanofiber composite panel possesses approximately equal strength in all directions. Therefore, the transparent nanofiber composite panel can be incorporated as a structural, load bearing, component of a larger structure, e.g. a mobile platform fuselage.
- The features, functions, and advantages can be achieved independently in various embodiments of the present inventions or may be combined in yet other embodiments.
- The present invention will become more fully understood from the detailed description and the accompanying drawings, wherein:
-
FIG. 1 is an illustration of an exemplary mobile platform including a transparent nanofiber composite panel according to the principles of the present invention; -
FIG. 2 is a sectional view of the transparent nanofiber composite panel shown inFIG. 1 ; -
FIG. 3 is an exemplary schematic view of a method of forming transparent nanofibers for use with the transparent nanofiber composite panel shown inFIG. 1 ; -
FIG. 4A is a schematic view of an injection mold used to construct the transparent nanofiber composite panel, shown inFIG. 1 , in accordance with a preferred embodiment of the present invention; and -
FIG. 4B is a schematic view of a nanofiber pre-impregnated tape used to construct the transparent nanofiber composite panel, shown inFIG. 1 , in accordance with another preferred embodiment of the present invention - The following description of the preferred embodiment(s) is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses.
- With reference to
FIG. 1 , a transparentnanofiber composite panel 10 constructed according to the principles of the present invention is shown in operative association with amobile platform 12. More particularly, the transparentnanofiber composite panel 10 is an optical quality fiber reinforced transparency having high structural strength properties. Although themobile platform 12 is shown as an aircraft, themobile platform 12 could also be represented in the form of other mobile platforms, such as a ship, a train, a bus or an automobile. Additionally, although the present invention will be described below as particularly applicable for use in association with mobile platforms, the invention should not be so limited in application. It is envisioned that the invention is equally applicable to aircraft, trains, buses, tanks, ships, buildings, or any application where a composite transparency having high strength and lightweight construction is of paramount importance. - In the particular example provided, the transparent
nanofiber composite panel 10 is shown as a window of themobile platform 12. It should be appreciated, however, that the transparentnanofiber composite panel 10 may be used in any portion of themobile platform 12 and may include the cockpit window or a door window. Moreover, the transparentnanofiber composite panel 10 may be used in any number of environments not strictly limited to conventional “windows”. For example, skylights, running light covers, satellite dome covers, view ports on undersea watercraft, and various other environments may employ the transparentnanofiber composite panel 10 of the present invention. - The
mobile platform 12 generally includes afuselage 14 that surrounds the transparentnanofiber composite panel 10. A traditional prior art side window is shown inFIG. 1 in phantom lines and is generally indicated byreference numeral 16. As is apparent, the transparentnanofiber composite panel 10 has a larger field of view than the traditional priorart side window 16. This is due, in part, to the greater strength and load carrying capability of the transparentnanofiber composite panel 10, as further described below. - Turning to
FIG. 2 , a portion of the transparentnanofiber composite panel 10 is illustrated. The transparentnanofiber composite panel 10 generally includes a plurality oftransparent nanofibers 18 integrated within atransparent matrix 20. Thetransparent nanofibers 18 have a diameter, “d”. In a preferred embodiment the diameter d of thetransparent nanofibers 18 is less than the wavelength of visible light, i.e., less than approximately 400 to 600 nm. Preferably, thetransparent nanofibers 18 have a diameter d of between approximately 10 to 400 nm. In the particular example provided, thetransparent nanofibers 18 are constructed of glass. However, thetransparent nanofibers 18 can be constructed of any other suitable transparent material having high strength properties as described herein; for example, silicon dioxide, graphite or a transparent polymer such as nylon or polycarbonate. - In a preferred form, the
matrix 20 is formed from a transparent epoxy resin. The epoxy resin is selected based on transparency, strength, and refractive index (RI). Preferably, the RI of thematrix 20 is substantially similar to the RI of thetransparent nanofibers 18. However, the high transmittance of thetransparent nanofibers 18 of the present invention, as described below, permits variations in the RI of thematrix 20 that may occur due to extreme temperatures, without affecting the translucency of the transparent nanofibercomposite panel 10. - In accordance with a preferred implementation of the present invention, due to the diameter d being less than the wavelength of visible light, the
transparent nanofibers 18 permit transmittance of light on the order of 90%. Moreover, because the transmittance of thetransparent nanofibers 18 is very high, it is possible to allow dissimilar RIs between thetransparent nanofibers 18 and thetransparent matrix 20 without the transparent nanofibercomposite panel 10 becoming opaque. Additionally, as the diameter of thetransparent nanofibers 18 decreases, fiber strength increases due to a reduction in surface defects. This is especially true of glass nanofibers, which have been shown to exhibit linearly increasing tensile strength up to 1×106 PSI for fiber diameters of approximately 1000 nm. - Preferably the
transparent nanofibers 18 are distributed within thematrix 20 at approximately 10% to 60% by volume. Due to the high tensile strength of thetransparent nanofibers 18, as the diameter of thetransparent nanofibers 18 decreases, the concentration oftransparent nanofibers 18 integrated with thetransparent matrix 20 can decrease without sacrificing the structural strength properties of the transparent nanofibercomposite panel 10. - Moreover, due to the high tensile strength of the
transparent nanofibers 18, thetransparent nanofibers 18 can be distributed within thematrix 20 at random orientations without sacrificing the structural strength properties of the transparent nanofibercomposite panel 10. That is, due to the high tensile strength of the small diametertransparent nanofibers 18 sufficient strength will remain in the transparent nanofibercomposite panel 10 without integrating thetransparent nanofibers 18 within thetransparent matrix 20 in a particular orientation. Furthermore, the random orientation of thetransparent nanofibers 18 within thetransparent matrix 20 provides the transparent nanofibercomposite panel 10 with quasi-isotropic material properties, e.g. approximately equal strength in all directions. Therefore, the transparent nanofibercomposite panel 10 can be incorporated as a structural, load bearing, component of themobile platform fuselage 14. - With reference to
FIG. 3 , thetransparent nanofibers 18 are preferably produced by spinning the material through a powerful electric field, known in the art as “electrospinning”, though various other methods may be employed. Apolymer melt 22, glass in the particular example provided, is pumped from asource 24 through afeed line 26 to aspinneret 28. Thespinneret 28 extends between atop plate 30 and abottom plate 32. Thetop plate 30 is charged via apower source 34. An electric field is thereby formed that in turn electrostatically charges themelt 22 as it leaves thespinneret 28. As thepolymer melt 22 is spun out from thespinneret 28, the electric field draws out themelt 22 into nanofibers that may then be collected on thebottom plate 32. - In a preferred implementation, the
transparent nanofibers 18 are integrated with thetransparent matrix 20 utilizing an injection molding process as illustrated inFIG. 4A . Amold 38 generally includes mold halves 40 that combine to form a designated shape, such as, for example, a window shape.Epoxy resin 42 andtransparent nanofibers 18 are then injected into themold 38. Once theepoxy resin 42 has set or cured, the transparent nanofibercomposite panel 10 may then be removed from themold 38. Since thetransparent nanofibers 18 may be randomly oriented within themold 38, it is possible for themold 38 to take on any shape desired, thereby allowing windows that have complex surfaces. - Turning to
FIG. 4B , in an alternative preferred embodiment, thetransparent nanofibers 18 are used to form a reinforcedpre-impregnated tape 36. For example, thetransparent nanofibers 18 may be arranged in a resin that, after solidification, forms thetransparent matrix 20 in the form of strips ofpre-impregnated tape 36. Successive layers of thepre-impregnated tape 36 may then be laminated to form the transparent nanofibercomposite panel 10. Due to the random orientation of thetransparent nanofibers 18 on thepre-impregnated tape 36, thepre-impregnated tape 36 need not be aligned in any particular manner when laminated with layers of otherpre-impregnated tape 36 to form the transparent nanofibercomposite panel 10. - In yet another preferred embodiment, the
transparent nanofibers 18 are woven into a ‘cloth’. The transparent nanofiber ‘cloth’ is then exposed to thetransparent matrix 20, such that thetransparent matrix 20 penetrates the transparent nanofiber ‘cloth’. - By employing transparent nanofibers integrated within a transparent matrix, the transparent nanofiber
composite panel 10 is substantially insensitive to RI ‘mismatch’, e.g. ‘mismatch’ caused by changes in the environmental temperature. That is, the transparent nanofibercomposite panel 10 will maintain a high level of transparency, e.g. 90%, over a wide range of temperature. In an exemplary embodiment the transparent nanofibercomposite panel 10 will maintain a high level of transparency at temperatures ranging between approximately (−60)° F. and approximately 400° F. Moreover, the transparent nanofibercomposite panel 10 is substantially stronger and is capable of use as a load bearing structural component of themobile platform 12. For example, in the case where the transparent nanofibercomposite panel 10 is a window in a mobile platform fuselage, a load can be transferred across the window so that additional fuselage structure does not need to be incorporated around the window. Preferably, thetransparent nanofibers 18 are constructed of glass to thereby provide significant tensile strength and allow lower concentration of thetransparent nanofibers 18 within thetransparent matrix 20. The lower concentration provides further increases in transmittance and decreases in optical distortion of light through the transparent nanofibercomposite panel 10. If polymer material is used to construct thetransparent nanofibers 18, it is preferable to select a polymer material with a RI and an index variation substantially similar to the RI and index variation of thetransparent matrix 20. - Furthermore, the transparent nanofiber
composite panel 10 constructed with thetransparent nanofibers 18 randomly oriented within thetransparent matrix 20, as described above, is not limited to unidirectional strength. Thus, the transparent nanofibercomposite panel 10 will have quasi-isotropic material properties. - While various preferred embodiments have been described, those skilled in the art will recognize modifications or variations, which might be made without departing from the inventive concept. The examples illustrate the invention and are not intended to limit it. Therefore, the description and claims should be interpreted liberally with only such limitation as is necessary in view of the pertinent prior art.
Claims (40)
1. A transparent panel comprising:
a transparent matrix; and
a plurality of transparent nanofibers integrated within the transparent matrix, the transparent nanofibers having a diameter less than the wavelength of visible light.
2. The transparent panel of claim 1 , wherein the transparent nanofibers have a diameter between approximately 10 nm and 400 nm.
3. The transparent panel of claim 1 , wherein the transparent nanofibers comprise glass transparent nanofibers.
4. The transparent panel of claim 1 , wherein the transparent nanofibers comprise approximately 10% to 60% of the transparent panel by volume.
5. The transparent panel of claim 1 , wherein an index of refraction of the transparent nanofibers approximately equals an index of refraction (RI) of the transparent matrix.
6. The transparent panel of claim 1 , wherein the transparent nanofibers are integrated within the transparent matrix to form a non-woven transparent nanofiber mat tape used to construct the transparent panel.
7. The transparent panel of claim 1 , wherein the transparent nanofibers form a mat cloth that is integrated within the transparent matrix to form the transparent panel.
8. The transparent panel of claim 1 , wherein the transparent nanofibers and the transparent matrix are injected into a mold to form the transparent panel.
9. The transparent panel of claim 1 , wherein the transparent matrix comprises an epoxy resin.
10. The transparent panel of claim 1 , wherein the transparent nanofibers comprise a polymer.
11. The transparent panel of claim 1 , wherein the transparent nanofibers are integrated within the transparent matrix in a random orientation to provide a structural load bearing transparent panel comprising substantially isotropic strength such that a load can be transferred across the transparent panel in any direction.
12. The transparent panel of claim 11 , wherein the structural load bearing transparent panel is adapted to be incorporated as a transparent structural, load bearing member within a fuselage of a mobile platform.
13. The transparent panel of claim 1 , wherein the transparent panel comprises an optical quality transparent panel adapted to permit approximately 90% transmittance of light.
14. The transparent panel of claim 1 , wherein the transparent panel is adapted to maintain an approximately constant level of transparency at temperatures ranging between approximately (−60)° F. and approximately 400° F.
15. The transparent panel of claim 1 , wherein the transparent panel is adapted to be substantially insensitive to an RI ‘mismatch’ between the transparent nanofibers and the transparent matrix
16. A method for providing a structural load bearing transparent panel having substantially isotropic material properties over a wide range of temperatures, the method comprising:
providing a transparent matrix;
providing a plurality of transparent nanofibers having a diameter less than the wavelength of visible light;
integrating the transparent nanofibers within a transparent matrix to form the transparent panel comprising substantially isotropic strength such that a load can be transferred across the transparent panel in any direction and adapted to be substantially insensitive to a difference between a refractive index (RI) of the transparent matrix and a RI of the transparent nanofibers.
17. The method of claim 16 , wherein integrating the transparent nanofibers within a transparent matrix comprises integrating the transparent nanofibers within a transparent matrix in a random orientation such that the transparent panel comprises substantially isotropic material properties.
18. The method of claim 16 , wherein providing the plurality of transparent nanofibers comprises providing the transparent nanofibers having a diameter between approximately 10 nm and 400 nm.
19. The method of claim 16 , wherein providing the plurality of transparent nanofibers comprises providing glass nanofibers.
20. The method of claim 16 , wherein integrating the transparent nanofibers within a transparent matrix comprises integrating the transparent nanofibers such that the transparent nanofibers comprise approximately 10% to 60% of the transparent panel by volume.
21. The method of claim 16 , wherein providing the plurality of transparent nanofibers comprises providing the nanofibers having a RI approximately equal to RI of the transparent matrix.
22. The method of claim 16 , wherein integrating the transparent nanofibers within a transparent matrix comprises:
integrating the transparent nanofibers within the transparent matrix to form a non-woven transparent nanofiber mat tape; and
bonding together a plurality of pieces of the transparent nanofiber mat tape to construct the transparent panel.
23. The method of claim 16 , wherein integrating the transparent nanofibers within a transparent matrix comprises:
forming a mat cloth from the transparent nanofibers; and
integrating within the transparent matrix with the mat cloth to form the transparent panel.
24. The method of claim 16 , wherein integrating the transparent nanofibers within a transparent matrix comprises injecting the transparent nanofibers and the transparent matrix into a mold to form the transparent panel.
25. The method of claim 16 , wherein providing the transparent matrix comprises providing an epoxy resin to be integrated with the transparent nanofibers.
26. The transparent panel of claim 16 , wherein providing the transparent nanofibers comprises providing a polymer to be integrated with the transparent matrix.
27. The method of claim 16 , wherein the method further comprises incorporating the transparent panel within a fuselage of a mobile platform as a transparent structural, load bearing member.
28. The method of claim 16 , wherein integrating the transparent nanofibers within a transparent matrix comprises integrating the transparent nanofibers within the transparent matrix such that the transparent panel permits approximately 90% transmittance of light.
29. The method of claim 16 , wherein integrating the transparent nanofibers within a transparent matrix comprises integrating the transparent nanofibers within the transparent matrix such that such that the transparent panel is maintains an approximately constant level of transparency at temperatures ranging between approximately (−60)° F. and approximately 400° F.
30. A nanofiber composite panel for use in the structure of a mobile platform, said panel comprising:
a transparent epoxy resin; and
a plurality of transparent nanofibers integrated within the transparent epoxy resin in a random orientation to provide a transparent panel having substantially isotropic strength such that a load can be transferred across the transparent panel in any direction; wherein the transparent nanofibers comprise:
a diameter having a length less than the wavelength of visible light such that the transparent panel is substantially insensitive to a difference between a refractive index (RI) of the transparent epoxy resin and a RI of the transparent nanofibers.
31. The panel of claim 30 , wherein the length of the diameter of the transparent nanofibers is between approximately 10 nm and 400 nm.
32. The panel of claim 30 , wherein the transparent nanofibers comprise glass nanofibers.
33. The panel of claim 30 , wherein the transparent nanofibers comprise polymer nanofibers.
34. The panel of claim 30 , wherein the transparent nanofibers comprise approximately 10% to 60% of the transparent panel by volume.
35. The panel of claim 30 , wherein an index of refraction of the transparent nanofibers approximately equals an index of refraction (RI) of the transparent epoxy resin.
36. The panel of claim 30 , wherein the transparent nanofibers are integrated within the transparent epoxy resin to form a non-woven transparent nanofiber mat tape used to construct the transparent panel.
37. The panel of claim 30 , wherein the transparent nanofibers form a mat cloth that is integrated within the transparent epoxy resin to form the transparent panel.
38. The panel of claim 30 , wherein the transparent nanofibers and the transparent epoxy resin are injected into a mold to form the transparent panel.
39. The panel of claim 11 , wherein the transparent panel is adapted to be incorporated as a transparent structural, load bearing member within a fuselage of a mobile platform.
40. The panel of claim 30 , wherein the transparent panel comprises an optical quality transparent panel adapted to permit approximately 90% transmittance of light.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/901,808 US20060024483A1 (en) | 2004-07-29 | 2004-07-29 | Transparent composite panel |
PCT/US2005/026501 WO2006014961A1 (en) | 2004-07-29 | 2005-07-27 | Transparent composite panel |
GB0703374A GB2434770A (en) | 2004-07-29 | 2007-02-21 | Transparent composite panel |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/901,808 US20060024483A1 (en) | 2004-07-29 | 2004-07-29 | Transparent composite panel |
Publications (1)
Publication Number | Publication Date |
---|---|
US20060024483A1 true US20060024483A1 (en) | 2006-02-02 |
Family
ID=35033711
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/901,808 Abandoned US20060024483A1 (en) | 2004-07-29 | 2004-07-29 | Transparent composite panel |
Country Status (3)
Country | Link |
---|---|
US (1) | US20060024483A1 (en) |
GB (1) | GB2434770A (en) |
WO (1) | WO2006014961A1 (en) |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20080145655A1 (en) * | 2006-12-14 | 2008-06-19 | Ppg Industries Ohio, Inc. | Electrospinning Process |
US20080145638A1 (en) * | 2006-12-14 | 2008-06-19 | Ppg Industries Ohio, Inc. | Transparent Composite Articles |
US20080207798A1 (en) * | 2007-02-27 | 2008-08-28 | Ppg Industries Ohio, Inc. | Organic-inorganic electrospun fibers |
US20090244070A1 (en) * | 2008-03-31 | 2009-10-01 | The Boeing Company | System and method for forming optimized perimeter surveillance |
US20100106420A1 (en) * | 2008-03-31 | 2010-04-29 | The Boeing Company | System and method for forming optimized perimeter surveillance |
EP2674294A1 (en) * | 2012-06-14 | 2013-12-18 | The Boeing Company | Bicomponent Fibers Containing Nano-Filaments For Use In Optically Transparent Composites |
US8672258B1 (en) * | 2009-08-21 | 2014-03-18 | The Boeing Company | Power transmission for aircraft flight testing |
FR3021294A1 (en) * | 2014-05-23 | 2015-11-27 | Airbus Operations Sas | SHUTTER DEVICE CAPABLE OF SHUTTING OFF OPENING IN AN AIRCRAFT FUSELAGE |
US20190352819A1 (en) * | 2018-05-16 | 2019-11-21 | Lintec Of America, Inc. | Nanofiber fabric |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102005061507A1 (en) * | 2005-12-22 | 2007-07-05 | Audi Ag | Vehicle component is formed at least in part of fibre-reinforced plastics with integrated light-permeable area to form part of light unit such as brake light |
DE102008056702B4 (en) | 2008-11-11 | 2014-04-03 | Airbus Operations Gmbh | airplane window |
Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2293656A (en) * | 1942-01-03 | 1942-08-18 | Lockheed Aircraft Corp | Transparent closure and mounting |
US2834998A (en) * | 1954-01-25 | 1958-05-20 | Douglas Aircraft Co Inc | Means for mounting a frangible expanse to a vibratile support |
US3061490A (en) * | 1959-09-23 | 1962-10-30 | Libbey Owens Ford Glass Co | Laminated safety glass |
US3928708A (en) * | 1974-01-29 | 1975-12-23 | Nasa | Transparent fire resistant polymeric structures |
US4081581A (en) * | 1974-04-01 | 1978-03-28 | Ppg Industries, Inc. | Laminated aircraft windshield |
US5039566A (en) * | 1988-06-27 | 1991-08-13 | Mcdonnell Douglas Corporation | Transparent composite material |
US5665450A (en) * | 1992-08-21 | 1997-09-09 | The Curators Of The University Of Missouri | Optically transparent composite material and process for preparing same |
US6382526B1 (en) * | 1998-10-01 | 2002-05-07 | The University Of Akron | Process and apparatus for the production of nanofibers |
US20040067364A1 (en) * | 2002-10-08 | 2004-04-08 | National Aerospace Laboratory Of Japan | Carbon nanofiber-dispersed resin fiber-reinforced composite material |
US20040259996A1 (en) * | 2002-08-27 | 2004-12-23 | Georg Stoppelmann | High-viscous moulding materials with nano-scale fillers |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE19758009A1 (en) * | 1997-01-16 | 1998-07-23 | Volkswagen Ag | Vehicle roof |
EP1244730B1 (en) * | 1999-12-07 | 2007-02-28 | William Marsh Rice University | Oriented nanofibers embedded in polymer matrix |
DE10064396A1 (en) * | 2000-12-21 | 2002-07-18 | Webasto Vehicle Sys Int Gmbh | Vehicle bodywork component consists of a transparent plastic material which is reinforced by means of embedded nano fibers |
-
2004
- 2004-07-29 US US10/901,808 patent/US20060024483A1/en not_active Abandoned
-
2005
- 2005-07-27 WO PCT/US2005/026501 patent/WO2006014961A1/en active Application Filing
-
2007
- 2007-02-21 GB GB0703374A patent/GB2434770A/en not_active Withdrawn
Patent Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2293656A (en) * | 1942-01-03 | 1942-08-18 | Lockheed Aircraft Corp | Transparent closure and mounting |
US2834998A (en) * | 1954-01-25 | 1958-05-20 | Douglas Aircraft Co Inc | Means for mounting a frangible expanse to a vibratile support |
US3061490A (en) * | 1959-09-23 | 1962-10-30 | Libbey Owens Ford Glass Co | Laminated safety glass |
US3928708A (en) * | 1974-01-29 | 1975-12-23 | Nasa | Transparent fire resistant polymeric structures |
US4081581A (en) * | 1974-04-01 | 1978-03-28 | Ppg Industries, Inc. | Laminated aircraft windshield |
US5039566A (en) * | 1988-06-27 | 1991-08-13 | Mcdonnell Douglas Corporation | Transparent composite material |
US5665450A (en) * | 1992-08-21 | 1997-09-09 | The Curators Of The University Of Missouri | Optically transparent composite material and process for preparing same |
US6382526B1 (en) * | 1998-10-01 | 2002-05-07 | The University Of Akron | Process and apparatus for the production of nanofibers |
US20040259996A1 (en) * | 2002-08-27 | 2004-12-23 | Georg Stoppelmann | High-viscous moulding materials with nano-scale fillers |
US20040067364A1 (en) * | 2002-10-08 | 2004-04-08 | National Aerospace Laboratory Of Japan | Carbon nanofiber-dispersed resin fiber-reinforced composite material |
Cited By (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20080145638A1 (en) * | 2006-12-14 | 2008-06-19 | Ppg Industries Ohio, Inc. | Transparent Composite Articles |
US7632563B2 (en) | 2006-12-14 | 2009-12-15 | Ppg Industries Ohio, Inc. | Transparent composite articles |
US20080145655A1 (en) * | 2006-12-14 | 2008-06-19 | Ppg Industries Ohio, Inc. | Electrospinning Process |
US8088323B2 (en) | 2007-02-27 | 2012-01-03 | Ppg Industries Ohio, Inc. | Process of electrospinning organic-inorganic fibers |
US20080207798A1 (en) * | 2007-02-27 | 2008-08-28 | Ppg Industries Ohio, Inc. | Organic-inorganic electrospun fibers |
US8846199B2 (en) | 2007-02-27 | 2014-09-30 | Ppg Industries Ohio, Inc. | Organic-inorganic electrospun fibers |
US8686854B2 (en) | 2008-03-31 | 2014-04-01 | The Boeing Company | System and method for forming optimized perimeter surveillance |
US8370111B2 (en) | 2008-03-31 | 2013-02-05 | The Boeing Company | System and method for forming optimized perimeter surveillance |
US20090244070A1 (en) * | 2008-03-31 | 2009-10-01 | The Boeing Company | System and method for forming optimized perimeter surveillance |
US20100106420A1 (en) * | 2008-03-31 | 2010-04-29 | The Boeing Company | System and method for forming optimized perimeter surveillance |
US8672258B1 (en) * | 2009-08-21 | 2014-03-18 | The Boeing Company | Power transmission for aircraft flight testing |
US9114589B2 (en) * | 2012-06-14 | 2015-08-25 | The Boeing Company | Bicomponent fibers containing nano-filaments for use in optically transparent composites |
RU2636729C2 (en) * | 2012-06-14 | 2017-11-27 | Зе Боинг Компани | Two-component fibre containing nanowires for application in optically transparent composites |
JP2014000807A (en) * | 2012-06-14 | 2014-01-09 | Boeing Co | Bicomponent fibers containing nano-filaments for use in optically transparent composites |
KR20130140552A (en) * | 2012-06-14 | 2013-12-24 | 더 보잉 컴파니 | Bicomponent fibers containing nano-filaments for use in optically transparent composites |
US20130337222A1 (en) * | 2012-06-14 | 2013-12-19 | The Boeing Company | Bicomponent fibers containing nano-filaments for use in optically transparent composites |
AU2013204665B2 (en) * | 2012-06-14 | 2015-04-09 | The Boeing Company | Bicomponent fibers containing nano-filaments for use in optically transparent composites |
EP2674294A1 (en) * | 2012-06-14 | 2013-12-18 | The Boeing Company | Bicomponent Fibers Containing Nano-Filaments For Use In Optically Transparent Composites |
KR102018391B1 (en) * | 2012-06-14 | 2019-09-04 | 더 보잉 컴파니 | Bicomponent fibers containing nano-filaments for use in optically transparent composites |
US20160033237A1 (en) * | 2012-06-14 | 2016-02-04 | The Boeing Company | Macro fiber for composite articles |
CN103507274A (en) * | 2012-06-14 | 2014-01-15 | 波音公司 | Bicomponent fibers containing nano-filaments for use in optically transparent composites |
US9851182B2 (en) * | 2012-06-14 | 2017-12-26 | The Boeing Company | Macro fiber for composite articles |
FR3021294A1 (en) * | 2014-05-23 | 2015-11-27 | Airbus Operations Sas | SHUTTER DEVICE CAPABLE OF SHUTTING OFF OPENING IN AN AIRCRAFT FUSELAGE |
US20190352819A1 (en) * | 2018-05-16 | 2019-11-21 | Lintec Of America, Inc. | Nanofiber fabric |
US10724163B2 (en) * | 2018-05-16 | 2020-07-28 | Lintec Of America, Inc. | Nanofiber fabric |
JP2021524545A (en) * | 2018-05-16 | 2021-09-13 | リンテック オブ アメリカ インクLintec Of America, Inc. | Nanofiber fabric |
US11549205B2 (en) | 2018-05-16 | 2023-01-10 | Lintec Of America, Inc. | Nanofiber fabric |
JP7354153B2 (en) | 2018-05-16 | 2023-10-02 | リンテック オブ アメリカ インク | nanofiber fabric |
Also Published As
Publication number | Publication date |
---|---|
GB2434770A (en) | 2007-08-08 |
WO2006014961A1 (en) | 2006-02-09 |
GB0703374D0 (en) | 2007-03-28 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
WO2006014961A1 (en) | Transparent composite panel | |
US7651756B2 (en) | Resin infused transparent skin panel and method of making same | |
US6889938B1 (en) | Structural cockpit window and method of making same | |
EP1744950B1 (en) | Load bearing window | |
US7989057B2 (en) | Composite material | |
US9851182B2 (en) | Macro fiber for composite articles | |
WO2006093615A3 (en) | Composite polymer fibers | |
US8490348B2 (en) | Varied glass density reinforcement of composites | |
EP2439235B1 (en) | Transparent composites with organic fiber | |
US8262823B2 (en) | Window skin panel and method of making same | |
KR100256720B1 (en) | Flexible material for use in an inflatable structure | |
CN103772908A (en) | Glass fiber reinforced engineering plastic plate and simple high-damping isolating bearing | |
RU2483974C2 (en) | Carrying and damage tolerant multilayer window of aircraft | |
FR3027273A1 (en) | FACE WALL ARCHITECTURE SUCH AS A SANDWICH COMPOSITE TRAIN CAR | |
CN102555316A (en) | Fiber fabric with high buckling resistance and method for preparing fiber composite material part with high buckling resistance | |
CN217418590U (en) | Optical-grade PET (polyethylene terephthalate) protective film with high strength | |
CN211106109U (en) | Thermoplastic continuous fiber reinforced composite board | |
Demidov et al. | Hollow fibres make light and strong reinforcements | |
KR20190136784A (en) | Composite material for reinforcement and articles comprising the same | |
Richardson | Hybrid composites based on vinyl ester | |
US20170252965A1 (en) | Molded composite structure and method of molding the composite structure | |
BALL et al. | The materials/design interface in reinforced plastics(Glass fiber reinforced polyester laminates mechanical properties evaluation for structural design, considering failure criteria in terms of fiber debonding and resin and gel coat cracking) | |
Satoh et al. | Compressive behavior of thick GFRP laminates | |
BRANDT et al. | Integrally woven sandwich structures | |
Wright | A Review of the Physical Ageing of Epoxy Resins and Their Carbon Fibre Composites |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: BOEING COMPANY, THE, ILLINOIS Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:KOCH, WILLIAM J.;NORDMAN, PAUL S.;REEL/FRAME:015643/0743 Effective date: 20040719 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |