AERONAUTICAL LAMINATED GLAZING WITH MINIMUM DEFORMATION IN THE EVENT OF ALL OF THE GLASS SHEETS OF SAME BREAKING

Abstract

A laminated glazing for a vehicle or a building, includes an inner structural glass sheet having a surface compressive stress of between 400 and 1000 MPa with exchange depths of between 100 and 500, for example at least equal to 150 m and an outer structural glass sheet having a surface compressive stress of between 50 and 300 MPa with exchange depths of between 50 and 100 m, on condition that the product of the two is at most equal to 25 000 MPa.Math.m.

Claims

1. A laminated glazing for a vehicle or a building, comprising an inner structural glass sheet having a surface compressive stress of between 400 and 1000 MPa with exchange depths of between 100 and 500 m and an outer structural glass sheet having a surface compressive stress of between 50 and 300 MPa with exchange depths of between 50 and 100 m, on condition that the product of the two is at most equal to 25 000 MPa.Math.m.

2. The laminated glazing as claimed in claim 1, wherein the inner and outer structural glass sheets have identical or different thicknesses of between 3 and 20 mm, and wherein a sum of their thicknesses is between 10 and 20 mm.

3. The laminated glazing as claimed in claim 1, wherein the inner and outer structural glass sheets have a soda-lime or aluminosilicate composition.

4. The laminated glazing as claimed in claim 1, wherein the inner and outer structural glass sheets are chemically reinforced.

5. The laminated glazing as claimed in claim 1, wherein the inner and outer structural glass sheets are bonded to one another by means of a first adhesive interlayer having a thickness of between 0.5 and 5 mm.

6. The laminated glazing as claimed in claim 1, comprising, on a side of the outer structural glass sheet opposite the inner structural glass sheet, an outer glass sheet having a thickness between 0.5 and 5 mm.

7. The laminated glazing as claimed in claim 6, wherein the outer glass sheet has a soda-lime or aluminosilicate composition.

8. The laminated glazing as claimed in claim 6, wherein the outer glass sheet is semi-tempered or chemically reinforced.

9. The laminated glazing as claimed in claim 6, wherein the outer glass sheet is bonded to the outer structural glass sheet by means of a second adhesive interlayer having a thickness of between 3 and 12 mm.

10. The laminated glazing as claimed in claim 6, wherein a face of the outer glass sheet oriented toward the outer structural glass sheet supports a network of heating wires and/or an electrically-conductive heating layer.

11. The laminated glazing as claimed in claim 1, wherein one face of the inner or outer structural glass sheet supports a network of heating wires and/or an electrically-conductive heating layer.

12. The laminated glazing as claimed in claim 6, wherein the face of the outer glass sheet opposite the outer structural glass sheet is flush with the assembly structure.

13. The laminated glazing as claimed in claim 5, wherein an adhesive interlayer comprises a polyvinyl butyral, a polyurethane, an ethylene/vinyl acetate copolymer or the like.

14. The laminated glazing as claimed in claim 1, wherein the laminated glazing is curved.

15. The laminated glazing as claimed in claim 1, wherein a reinforcing sheet is inserted between the inner and outer structural glass sheets, over a portion at least of a peripheral zone of the laminated glazing.

16. A method comprising utilizing a laminated glazing as claimed in claim 1 in aeronautics.

17. The method as claimed in claim 16, wherein the laminated glazing is a pressurized aircraft glazing.

18. The laminated glazing as claimed in claim 1, wherein the inner structural glass sheet has a surface compressive stress of between 400 and 1000 MPa with exchange depths at least equal to 150 m.

19. The laminated glazing as claimed in claim 5, wherein the thickness of the first adhesive interlayer is between 1.8 and 3.2 mm.

Description

EXAMPLE

[0041] A laminated glazing of pressurized commercial aircraft cockpit consists, from the inside of the aircraft outward: [0042] of an 8-mm thick inner structural sheet of aluminosilicate glass with a chemical reinforcement generating a surface stress of 450 MPa for an exchange depth of 200 m; [0043] of an 8-mm thick outer structural sheet of soda-lime glass with a chemical reinforcement generating a surface stress of 250 MPa for an exchange depth of 60 m; and [0044] of a semi-tempered (surface stress of 50 MPa) 3-mm thick outer soda-lime glass sheet.

[0045] The two structural glass sheets are bonded by means of a 2-mm thick PVB adhesive interlayer.

[0046] The outer structural glass sheet and the outer glass sheet are bonded by means of a 10-mm thick PU adhesive interlayer.

[0047] The face of the outer glass sheet oriented toward the outer structural glass sheet bears a deicing heating layer of ITO. This is in particular the case for a frontal deicing glazing of an aircraft cockpit. As specified above, in the case of a demisting glazing, the heating function may be supported by any surface of the structural block in the laminate.

[0048] The outer face of the outer glass sheet lies flush with the body of the aircraft, assembly environment of the laminated glazing.

[0049] In the event of breakage of the two structural glass sheets of the laminated glazing, the large fragmentation of the outer structural glass sheet, i.e. into pieces of large dimensions, provides a minimal deformation of the glazing under the effect of the pressure.

[0050] Furthermore, this eventuality of breaking of the two structural glass sheets is minimized by the surface compressive stress characteristics thereof.