ANTI-FROST GLAZING HAVING HEATING POWER DIFFERENTIATED OVER THE ENTIRE SURFACE THERE-OF

Abstract

An anti-icing glazing or portion thereof, is entirely located, in the fitted position, on one side of the plane of symmetry of the body of an airborne, water-borne or terrestrial vehicle, wherein the heating power is differentiated over the whole of the surface thereof, so as to apply the maximum power to the portion of the surface where the heat loss is maximum.

Claims

1. An anti-icing glazing or portion thereof, entirely located, in a fitted position, on one side of a plane of symmetry of the a of an airborne, water-borne or terrestrial vehicle, wherein a heating power is differentiated over the whole of a surface thereof, so as to apply a maximum power to the portion of the surface where a heat loss is maximum.

2. The anti-icing glazing or portion thereof as claimed in claim 1, wherein said portion of the surface where the heat loss is maximum is a bottom portion of the glazing which is subjected to greater collection of water than the rest of the glazing.

3. The anti-icing glazing or portion thereof as claimed in claim 1, an envelope of which is defined by a quadrilateral ABCD, AB being a tangent to a middle of an upper post of the glazing or the portion thereof, BC a tangent to a middle of a rear post thereof, CD a tangent to a middle of a lower post thereof and DA a tangent to a middle of a front post thereof, optionally included in the plane of symmetry of the body of the vehicle, E and G being the middles of the segments DA, respectively BC, F being any point on the segment EG, wherein a mean specific heating powers are 7, respectively 4, respectively 4, each to within ±1 kW/m.sup.2, in the surface areas delimited by the points CDEF, respectively ABGE, respectively CFG.

4. The anti-icing glazing or portion thereof as claimed in claim 1, wherein a differentiated heating power is obtained by a deposition of a transparent electrically conductive layer of heterogeneous thickness to adjust a power dissipated.

5. The anti-icing glazing or portion thereof as claimed in claim 1, further comprising a transparent electrically conductive layer from which fine flow-separating lines have been removed by ablation, so as to help to control a distribution of differentiated heating power.

6. The anti-icing glazing or portion thereof as claimed in claim 5, wherein the transparent electrically conductive layer comprises at least one transparent conductive oxide and/or at least one metal.

7. The anti-icing glazing or portion thereof as claimed in claim 1, wherein the anti-icing glazing is a laminated glazing including a laminated structure, of which a face inside the laminated structure of the glass sheet of the laminated glazing which, in the fitted position, is in contact with the outside atmosphere, bears resistive electrically conductive elements.

8. A method comprising utilizing an anti-icing glazing or portion thereof as claimed in claim 1 in an airborne, water-borne or terrestrial vehicle.

9. The anti-icing glazing or portion thereof as claimed in claim 6, wherein the at least one transparent conductive oxide is tin-doped indium oxide (Indium Tin Oxide—ITO) or fluorine-doped tin oxide SnO.sub.2:F.

10. The anti-icing glazing or portion thereof as claimed in claim 6, wherein the at least one metal is silver.

Description

[0016] The invention will be better understood in light of the following description of the appended drawings, in which:

[0017] FIG. 1 represents the quadrilateral characteristic of one half of anti-icing glazing, and the delimitation of zones in accordance with one particular embodiment of the invention, and

[0018] FIG. 2 represents a quadrilateral analogous to that of FIG. 1, superposed on which are zones of different mean specific heating powers.

[0019] With reference to FIG. 1, a frontal glazing of an aircraft cockpit is centered with respect to the cabin of the aircraft, i.e. with respect to the plane of symmetry thereof. For reasons of symmetry, it is sufficient here to represent only the right half, as front view of the aircraft in the fitted position, of the frontal windshield, which half is positioned on a single right-hand side of the plane of symmetry of the cabin. This cockpit may furthermore comprise two lateral windshields on either side of the frontal windshield.

[0020] The frontal windshield has an anti-icing function by means of a transparent electrically conductive layer borne by the face oriented toward the inside of the laminated structure of the glass sheet in contact with the outside atmosphere.

[0021] The envelope of this right half of the frontal windshield is defined by the quadrilateral ABCD, AB being the tangent to the middle of the upper post of the right half of the glazing, BC the tangent to the middle of the rear post thereof, CD the tangent to the middle of the lower post thereof and DA the tangent to the middle of the front post thereof, which is included here in the plane of symmetry of the cabin. E and G are the middles of the segments DA, respectively BC, and F is any point on the segment EG.

[0022] With reference to FIG. 2, in accordance with the invention, mean specific heating powers are indeed 7, respectively 4, respectively 4, each to within ±1 kW/m.sup.2, in the surface areas delimited by the points CDEF, respectively ABGE, respectively CFG.