Functionalized glazing
Glazing comprising, in succession: a first rigid substrate (S 1 ); a second rigid substrate (S 2 ); a third rigid substrate (S 3 ); at least one “active” system (A) that includes at least one layer and is placed between the substrates (S 1 and S 2 ), the first substrate (S 1 ) optionally being set back in relation to the other two substrates (S 2 , S 3 ); and at least one polymer film having the function of retaining glazing fragments should the glazing break, said film being placed between the substrate (S 1 ) and the substrate (S 2 ) and between the substrate (S 2 ) and the substrate (S 3 ).
1. Glazing suitable for a side or front window for an airplane or helicopter cockpit, comprising, in succession:
a first rigid substrate (S 1 ) comprising an outside face to be outside of the cockpit;
a second rigid substrate (S 2 );
a third rigid substrate (S 3 ) comprising an inside face to be inside the cockpit,
wherein the second rigid substrate (S 2 ) positioned between the first rigid substrate (S 1 ) and the third rigid substrate (S 3 ),
wherein the substrates are made of thermally semi-toughened or chemically toughened glass;
a first active system (A) that includes at least one layer and is positioned between substrates (S 1 ) and (S 2 ),
a second active system (B) that is a thin-film multilayer system comprising a heating function and positioned between the substrates (S 1 ) and (S 2 ),
wherein the first substrate (S 1 ) is set back in relation to the other two substrates (S 2 ) and (S 3 ) with a set back zone around the periphery of the first substrate (S 1 ); and
at least one polymer film (F 1 , F 2 ) functioning as an adhesive interlayer and retaining glazing fragments should the glazing break, said film positioned between substrate (S 1 ) and substrate (S 2 ) and between substrate (S 2 ) and substrate (S 3 ), and
a seal (J 3 ) that encapsulates the substrates (S 1 ), (S 2 ) and (S 3 ) and that covers the set back zone and periphery of the first rigid substrate (S 1 ).
2. The glazing as claimed in claim 1 , wherein the active system (A) is an electrically controllable system, having variable optical and/or energy properties of the electrochromic system, optical valve, viologen system, liquid-crystal system or electroluminescent system type.
3. The glazing as claimed in claim 1 , wherein the active system (A) is positioned on face 2 of substrate (S 1 ).
4. The glazing as claimed in claim 1 , wherein the active system (A) is positioned on face 3 of substrate (S 2 ).
5. The glazing as claimed in claim 1 , wherein the active system (A) is positioned in a surface portion of substrate (S 1 ) or (S 2 ).
6. The glazing as claimed in claim 1 , wherein an active system (B) is positioned on face 3 of substrate (S 2 ).
7. The glazing as claimed in claim 1 , wherein an active system (B) is positioned on face 2 of substrate (S 1 ).
8. The glazing as claimed in claim 6 , wherein the active system (B) is a thin-film multilayer system having a heating functionality.
9. The glazing as claimed in claim 1 , wherein faces 1 and 6 on the substrate (S 1 ) and the substrate (S 3 ) respectively are covered with a multilayer (C) having an antireflection functionality.
10. The glazing as claimed in claim 1 , wherein current leads run around a part of the perimeter of active system (A) and (B).
11. The glazing as claimed in claim 1 , which is triple glazing provided with an all-solid electrochromic system (A) placed on either of faces 2 and 3 of (S 1 ) or (S 2 ), respectively.
12. The glazing as claimed in claim 1 , which passes the safety test of the FAR 25/JAR 25 standards.
13. An airplane or helicopter, comprising the glazing as claimed in claim 1 , as cockpit side or front window.