Method of making fire resistant sustainable aircraft interior panels

Patent metadata

Field	Value
Publication number	US-9925728-B2
Application number	US-201514591875-A
Country	US
Kind code	B2
Filing date	Jan 7, 2015
Priority date	Jan 8, 2014
Publication date	Mar 27, 2018
Grant date	Mar 27, 2018

Abstract

The present invention relates to method of manufacturing an aircraft interior panel comprising a core sandwiched between first and second skins, wherein both of the first and second skins are formed from natural fibers containing non-halogenated fire-retardant and set within an inorganic thermoset resin, thereby forming a fire-resistant sustainable aircraft interior panel. The method comprises impregnating the natural fibers with non-halogenated fire retardant and an inorganic thermoset resin, and laying up the resin-impregnated natural fibers to sandwich the core. This stack is then cured by raising the temperature of the stack sufficient to initiate curing but without reaching the boiling point of water in the stack, holding the stack at that first temperature before raising the temperature again to reach the boiling point of water in the stack, before cooling the stack.

First claim

We claim:

1. A method of manufacturing an aircraft interior panel comprising a core sandwiched between first and second skins, wherein both of the first and the second skins are formed from natural fibres containing a fire-retardant and set within an inorganic thermoset resin, thereby forming a fire-resistant sustainable aircraft interior panel, the method comprising:
(a) impregnating the natural fibres with the fire retardant to form fire-resistant natural fibres;
(b) impregnating the fire-resistant natural fibres with the inorganic thermoset resin to produce resin-impregnated natural fibres;
(c) laying up the resin-impregnated natural fibres to sandwich the core, thereby forming a stack of the core sandwiched between the resin-impregnated natural fibres; and
(d) curing the stack to form the fire-resistant sustainable aircraft interior panel that comprises the core sandwiched between the first and the second skins, wherein the curing comprises:
(d1) raising the temperature of the stack to a first temperature that is equal to or greater than a minimum activation temperature of the inorganic thermoset resin that initiates a curing reaction and less than a boiling point of water in the stack;
(d2) holding the stack at the first temperature;
(d3) raising a temperature of the stack to a second temperature that is equal to or greater than the boiling point of water in the stack; and
(d4) cooling the stack to reduce a temperature of the stack from the second temperature.

2. The method of claim 1 , further comprising between steps (b) and (c):
(b1) storing the resin-impregnated natural fibres as prepregs; and
(b2) retrieving from storage the prepregs of the resin-impregnated natural fibres.

3. The method of claim 1 , wherein the first temperature is between 75° C. and 90° C.

4. The method of claim 1 , wherein step (d2) further comprises:
holding the stack at the first temperature for between 5 minutes and 60 minutes.

5. The method of claim 1 , wherein the second temperature is between 100° C. and 130° C.

6. The method of claim 1 , wherein step (d3) further comprises:
raising the temperature of the stack to the second temperature at a rate of between 1° C. per minute and 10° C. per minute.

7. The method of claim 1 , wherein step (d4) further comprises:
cooling the stack to reduce the temperature of the stack from the second temperature as soon as a temperature of the stack is measured to have reached the second temperature.

8. The method of claim 1 , wherein step (d4) further comprises:
cooling the stack to allow it to reach ambient temperature.

9. The method of claim 1 , further comprising curing the stack in a press and wherein steps (c) and (d) further comprise:
raising a temperature of dies of the press to the first temperature and holding the dies at the first temperature, then performing step (c) by laying up the stack within the press, closing the press such that the dies sandwich the stack, thereby raising the temperature of the stack to the first temperature; and
cooling the stack, to reduce a temperature of the stack, by no longer heating the dies and allowing the stack to cool within the press.

10. The method of claim 2 , wherein step (b1) further comprises storing the composite prepregs for over 1 day.

11. The method of claim 10 , wherein step (b1) further comprises storing the composite prepregs at a temperature below −10° C.

12. The method of claim 1 , further comprising passing the resin-impregnated natural fibres through drain rollers to achieve a fibre to resin mix ratio between 25% and 50%.

13. The method of claim 1 , wherein step (b) further comprises impregnating the natural fibres with a resin mix comprising the inorganic thermoset resin in any combination with:
a hardener; and
an anti-shrinkage additive.

14. The method of claim 13 , wherein the resin mix comprises substantially 80% by weight of an aluminium silicate derivative inorganic thermoset resin, substantially 15% by weight of an aluminium/copper phosphate hardener, and substantially 5% by weight of a metakaolin anti-shrinkage additive.

15. The method of claim 1 , wherein the natural fibres comprise flax fibres.

16. The method of claim 1 , wherein step (a) further comprises impregnating the natural fibres with a non-halogenated flame retardant.

17. A method of manufacturing an aircraft interior panel comprising a core sandwiched between first and second skins, wherein both of the first and the second skins are formed from natural fibres containing a fire-retardant and set within an inorganic thermoset resin, thereby forming a fire-resistant sustainable aircraft interior panel, the method comprising:
(a) laying up resin-impregnated natural fibres to sandwich the core, thereby forming a stack of the core sandwiched between the resin-impregnated natural fibres; and
(b) curing the stack to form the fire-resistant sustainable aircraft interior panel that comprises the core sandwiched between the first and the second skins, wherein the curing comprises:
(b1) raising a temperature of the stack to a first temperature that is equal to or greater than a minimum activation temperature of the inorganic thermoset resin that initiates a curing reaction and less than a boiling point of water in the stack;
(b2) holding the stack at the first temperature;
(b3) raising a temperature of the stack to a second temperature that is equal to or greater than the boiling point of water in the stack; and
(b4) cooling the stack to reduce a temperature of the stack from the second temperature.

18. A method of manufacturing an aircraft, the method comprising:
manufacturing an aircraft interior panel comprising a core sandwiched between first and second skins, wherein both of the first and the second skins are formed from natural fibres containing a fire-retardant and set within an inorganic thermoset resin, thereby forming a fire-resistant sustainable aircraft interior panel, the method of manufacturing the aircraft interior panel comprising:
(a) impregnating the natural fibres with the fire retardant to form fire-resistant natural fibres;
(b) impregnating the fire-resistant natural fibres with the inorganic thermoset resin to produce resin-impregnated natural fibres;
(c) laying up the resin-impregnated natural fibres to sandwich the core, thereby forming a stack of the core sandwiched between the resin-impregnated natural fibres; and
(d) curing the stack to form the fire-resistant sustainable aircraft interior panel that comprises the core sandwiched between the first and the second skins, wherein the curing comprises:
(d1) raising the temperature of the stack to a first temperature that is equal to or greater than a minimum activation temperature of the inorganic thermoset resin that initiates a curing reaction and less than a boiling point of water in the stack;
(d2) holding the stack at the first temperature;
(d3) raising a temperature of the stack to a second temperature that is equal to or greater than the boiling point of water in the stack; and
(d4) cooling the stack to reduce a temperature of the stack from the second temperature; and

installing the aircraft interior panel within the aircraft.

19. The method of claim 18 , further comprising between steps (b) and (c):
(b1) storing the resin-impregnated natural fibres as prepregs; and
(b2) retrieving from storage the prepregs of the resin-impregnated natural fibres.

20. The method of claim 16 , wherein the natural fibres comprise flax fibres.

Assignees

• Boeing Co

Inventors

• Martin Pedro P
• Gonzalez-Garcia Ana
• Lapena Nieves

Classifications

• B32B2309/025

  Temperature vs time profiles · CPC title

• C04B28/005

  containing gelatineous or gel forming binders, e.g. gelatineous Al(OH)3, sol-gel binders · CPC title

• C04B2111/00982

  as construction elements for space vehicles or aeroplanes · CPC title

• C04B2111/0062

  Gypsum-paper board like materials · CPC title

• C04B2111/00896

  as prepregs · CPC title