Burnthrough resistant floor panels and method of manufacturing and installation

Patent metadata

Field	Value
Publication number	US-11130560-B2
Application number	US-201816044622-A
Country	US
Kind code	B2
Filing date	Jul 25, 2018
Priority date	Jul 25, 2018
Publication date	Sep 28, 2021
Grant date	Sep 28, 2021

Abstract

Aspects of the present disclosure present floor panels and floor panel assemblies that include incorporated burnthrough resistant materials and/or include burnthrough resistant layers applied to floor panels used in floor panel assemblies, along with methods for inhibiting fire penetration into compartments and methods of making and installing burnthrough resistant floor panels and floor assemblies including such apparatuses and methods as they relate to vehicles, including aircraft.

First claim

What is claimed is:

1. A burnthrough resistant floor panel comprising:
an internal support structure having an internal support structure first surface and
an internal support structure second surface;
at least one skin, said at least one skin comprising a skin thickness, said at least one skin configured to substantially cover the internal support structure first surface and said at least one skin further configured to substantially cover the internal support structure second surface to form a floor panel, said at least one skin having an exterior skin surface, said skin further comprising a fiber-containing composite material, said fiber-containing composite material comprising at least one of: a carbon fiber, a boron fiber, a glass fiber, and an aramid fiber, said fiber-containing composite material further comprising at least one of: a phenolic resin; an, epoxy resin; and an acrylamide resin;
a burnthrough resistant material impregnated throughout the skin thickness of the at least one skin, said burnthrough resistant material resisting a backside heat flux of less than about 2.0 BTU/ft 2 /sec for at least from about 4 mins to about 5 mins;
an adhesive layer disposed on at least one side of the at least one skin, said adhesive layer comprising an adhesive material, said adhesive material a fire retardant additive; and
wherein the burnthrough resistant floor panel has a floor panel density, said floor panel density ranging from about 0.4 to about 1.10 lbft 2 .

2. The burnthrough resistant floor panel of claim 1 , wherein the internal support structure comprises a honeycomb panel.

3. The burnthrough resistant floor panel of claim 1 , wherein the burnthrough resistant material comprises a ceramic paper.

4. The burnthrough resistant floor panel of claim 1 , wherein the burnthrough resistant material comprises at least one of: an inorganic polymer film material and a ceramic material.

5. The burnthrough resistant floor panel of claim 1 , wherein the internal support structure is made from a material comprising at least one of: a non-metallic core and an aluminum core.

6. The burnthrough resistant floor panel of claim 5 , wherein the non-metallic core comprises an open cell foam.

7. The burnthrough resistant floor panel of claim 1 , wherein the floor panel has a thickness ranging from about 0.25 inch to about 1 inch.

8. A fuselage comprising the burnthrough resistant floor panel of claim 1 .

9. An aircraft comprising the burnthrough resistant floor panel of claim 1 .

10. The burnthrough resistant floor panel of claim 1 , wherein the burnthrough resistant material is integrated throughout the thickness of the at least one skin.

11. The burnthrough resistant floor panel of claim 1 , wherein the burnthrough resistant material and the at least one skin are co-cured.

12. The burnthrough resistant floor panel of claim 1 , wherein the fiber-containing composite material comprises a carbon fiber reinforced plastic.

13. The burnthrough resistant floor panel of claim 1 , wherein the adhesive material comprises an adhesive material requiring no curing.

14. The burnthrough resistant floor panel of claim 1 , wherein the adhesive material comprises a pressure sensitive adhesive material.

15. The burnthrough resistant floor panel of claim 1 , wherein the adhesive material comprises at least one of: a polyester-based adhesive, a polyvinyl fluoride-based adhesive, and a silicone-based adhesive.

16. The burnthrough resistant floor panel of claim 1 , wherein the at least one skin incorporates integrally the adhesive layer.

17. A burnthrough resistant floor assembly comprising:
a floor panel, said floor panel comprising:
an internal support structure having a first internal support structure surface and a second internal support structure surface;
at least one skin configured to substantially cover the first internal support structure surface and the second internal support structure surface;
a burnthrough resistant material impregnated into the at least one skin, said at least one skin further comprising a fiber-containing composite material, said fiber-containing composite material comprising at least one of: a carbon fiber; a boron fiber; a glass fiber; and an aramid fiber, said fiber-containing composite material further comprising at least one of: a phenolic resin; an, epoxy resin; and an acrylamide resin;
an adhesive layer disposed on at least one side of the at least one skin, said adhesive layer comprising an adhesive material, said adhesive material comprising a fire retardant additive;
wherein the floor assembly resists a backside heat flux of less than about 2.0 BTU/ft 2 /sec for at least from about 4 mins to about 5 mins; and

wherein the burnthrough resistant floor panel has a floor panel density, said floor panel density ranging from about 0.4 to about 1.10 lbft 2 .

18. A fuselage comprising the burnthrough resistant floor assembly of claim 17 .

19. An aircraft comprising the burnthrough resistant floor assembly of claim 17 .

20. The burnthrough resistant floor assembly of claim 17 , wherein the burnthrough resistant material is integrated throughout the thickness of the at least one skin.

21. The burnthrough resistant floor assembly of claim 17 , wherein the burnthrough resistant material and the at least one skin are co-cured.

22. The burnthrough resistant floor assembly of claim 17 , wherein the fiber-containing composite material comprises a carbon fiber reinforced plastic.

23. A method for inhibiting fire penetration into an aircraft cabin, the method comprising:
providing a floor assembly into an aircraft fuselage interior, said floor assembly comprising:
a burnthrough resistant floor panel, said burnthrough resistant floor panel comprising:
an internal support structure having a first internal support structure surface and a second internal support structure surface;
at least one skin configured to substantially cover at least one of the first internal support structure surface and the second internal support structure surface, said at least one skin comprising a burnthrough resistant material, said burnthrough resistant material impregnated into the at least one skin, said skin further comprising a fiber-containing composite material, said fiber-containing composite material comprising at least one of: a carbon fiber; a boron fiber; a glass fiber; and an aramid fiber, said fiber-containing composite material further comprising at least one of: a phenolic resin; an, epoxy resin; and an acrylamide resin;
an adhesive layer disposed on at least one side of the at least one skin, said adhesive layer comprising an adhesive material, said adhesive material comprising a fire retardant additive;

wherein the burnthrough resistant floor panel resists a backside heat flux of less than about 2.0 BTU/ft 2 /sec for at least from about 4 mins to about 5 mins;
wherein the floor assembly obviates the presence of separate fire retardant apparatuses located in the lower half of an aircraft; and
wherein the burnthrough resistant floor panel has a floor panel density, said floor panel density ranging from about 0.4 to about 1.10 lbft 2 .

24. The method of claim 23 , wherein the burnthrough resistant material is impregnated throughout the thickness of the at least one skin.

25. A method of making a burnthrough resistant floor panel, the method comprising:
providing an internal support structure further comprising an in

Assignees

• Boeing Co

Inventors

• Slaton Daniel B

Classifications

• B64C1/00

  Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like · CPC title

• Y02T50/40

  Weight reduction · CPC title

• B64C2001/0081

  from metallic materials · CPC title

• B64C2001/0072

  from composite materials · CPC title

• B64C1/18 Primary

  Floors · CPC title