Optically clear structural laminate

• US 6,818,306 B2
• Filed: 09/27/2002
• Issued: 11/16/2004
• Est. Priority Date: 09/27/2002
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Miller, Michael C., Bridges, Donald J., Melquist, James L., Krey, Timothy J.
• Primary Examiner(s): Buttner, David J.
• Assistant Examiner(s): Keehan, Christopher
• Application Number:
  US10/259,702
• Publication Number:
  US 20040062934A1
• Time in Patent Office: 781 Days
• Field of Search: 428/413, 428/417, 428/297.4, 428/298.1, 428/298.7, 428/298.4, 428/299.4, 428/300.1, 428/497, 428/391, 523/06, 244/121, 244/129.3
• US Class Current: 428/413
• CPC Class Codes: B29C 70/58 comprising fillers only , e.g. particles, powder, beads, flakes, spheres B29C70/025 takes precedence, agglomerating hollow spheres to produce synthetic foam B29C70/66; compounding ingredients per se C08K
• CPC Class Codes: B29K 2995/0026 Transparent
• CPC Class Codes: B32B 2260/021 Fibrous or filamentary layer
• CPC Class Codes: B32B 2260/046 Synthetic resin
• CPC Class Codes: B32B 2262/101 Glass fibres
• CPC Class Codes: B32B 27/00 Layered products comprising a layer of synthetic resin fibrous or filamentary layer made of a synthetic resin B32B5/02; particulate layer made of a synthetic resin B32B5/16; foamed layer made of a synthetic resin B32B5/18
• CPC Class Codes: B32B 27/06 as the main or only constituent of a layer, which is next to another layer of the same or of a different material next to a layer of a particular substance B32B9/045; next to a bituminous or tarry layer B32B11/046; next to a water setting substance layer B32B13/12; next to a metal layer B32B15/08; next to a glass layer B32B17/10; next to a layer formed of natural mineral fibres or particles B32B19/045; next to a wood layer B32B21/08; next to a cellulosic plastic layer B32B23/08; next to a natural or synthetic rubber layer B32B25/08
• CPC Class Codes: B32B 27/38 comprising epoxy resins
• CPC Class Codes: B64C 1/1484 Windows B64C1/1492 takes precedence
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y10T 428/24994 Fiber embedded in or on the surface of a polymeric matrix
• CPC Class Codes: Y10T 428/2971 Impregnation
• CPC Class Codes: Y10T 428/31511 Of epoxy ether
• CPC Class Codes: Y10T 428/31525 Next to glass or quartz

Abstract

An optically clear structural laminate includes a thermosetting resin, a silane coupling agent and a filler. The laminate has a high weight to strength ratio and is capable of optical transmission over a wide range of temperatures.The laminate has increased tensile strength and is capable of being easily formed into complex shaped components. The structural properties of the laminate make it useful as aircraft canopies and windows.

Claims

1. An aircraft window comprising an optically transmissive laminate for structural support, that comprises:

an optically clear epoxy resin;

a filler embedded in said epoxy resin, wherein the volume percent of said filler is between about 45% to 65% and a refractive index of said filler is within about 0.010 of a refractive index of said epoxy resin for a wavelength between about 400 nm and about 750 nm; and

a silane coupling agent in contact with said filler.

2. The aircraft window of claim 1, wherein said epoxy resin is selected from the group consisting of Bisphenol A and Bisphenol F families.

3. The aircraft window of claim 1, wherein said filler is selected from the group consisting of glass and quartz.

4. The aircraft window of claim 1, wherein the optical transmission of said laminate varies by less than about 25% over a temperature range from about −

10°

F. to about 180°

F.

5. The aircraft window of claim 1, wherein said filler is a fabric filler having a thickness between about 0.002″

and about 0.020″

.

6. The aircraft window of claim 1, wherein said filler is a fabric filler having a thickness between about 0.002″

and about 0.010″

.

7. An aircraft window comprising a structural aircraft laminate capable of optical transmission for student support comprising:

an optically clear thermosetting resin;

a filler embedded in said thermosetting resin, wherein the refractive index of said filler is within about 0.005 of the refractive index of said thermosetting resin for a wavelength between about 400 nm and about 750 nm; and

a silane coupling agent in contact with said filler, such that said optical transmission varies by less than about 25% over a temperature range from about −

10°

F. to about 180°

F.

8. An aircraft window of claim 7, wherein said silane coupling agent is selected from the group consisting of 3-glycidoxypropyltrimethoxysilane, gamma-aminopropyltriethoxysilane, and aminoethylaminopropyltrimethoxysilane.

9. An aircraft window of claim 7, wherein said thermosetting resin is an epoxy resin.

10. An aircraft window of claim 9, wherein said epoxy resin is selected from the group consisting of Bisphenol A and Bisphenol F families.

11. An aircraft window of claim 7, wherein said filler is a fabric filler having a thickness between about 0.002″

and about 0.020″

.

12. An aircraft window of claim 7, wherein said filler is a fabric filler having a thickness between about 0.002″

and about 0.010″

.

13. An aircraft window of claim 7, wherein said structural aircraft laminate is an aircraft canopy.

14. An aircraft window of claim 7, wherein said structural aircraft laminate is an aircraft window.

15. An aircraft window comprising an optically transmissive laminate, for structural support that comprises:

an optically transmissive epoxy resin selected from the group consisting of Bisphenol A and Bisphenol F families;

a fabric filler embedded in said epoxy resin, wherein the volume percent of said fabric filler is between about 45% and about 65% and a refractive index of said fabric filler is within about 0.005 of a refractive index of said epoxy resin for a wavelength between about 400 nm and about 750 nm; and

a silane coupling agent selected from the group consisting of 3-glycidoxypropyltrimethoxysilane, gamma-aminopropyltriethoxysilane, and aminoethylaminopropyltrimethoxysilane, said silane coupling agent in contact with said fabric filler, such that the optical transmission of said laminate varies by less than about 25% over a temperature range from about −

10°

F. to about 180°

F.

16. An aircraft window of claim 15 wherein said laminate is a unidirectional laminate having a tensile strength of at least about 50 kpsi.

17. An aircraft window of claim 15 wherein the optical transmission of said laminate is at least about 80% in the visible spectrum at 75°

F.

18. An aircraft window of claim 15 wherein said fabric filler comprises woven fiber strands and said fabric filler has a thickness between about 0.002″

and about 0.020″

.