Granted Patent B2

US 8,951,375 · App. 13/238,841 · Granted Feb 10, 2015

Abstract

Claims (109)

1. A method of fabricating a composite part with integrated stiffeners, the method comprising:

triggering a shape memory polymer (SMP) apparatus to a malleable state;

shaping an SMP apparatus in the malleable state to correspond with a desired configuration of a first surface of the composite part to be fabricated, including one or more cavities configured for placement of stiffeners therein;

triggering the SMP apparatus to a rigid state;

placing the stiffeners into the cavities;

applying composite material onto the SMP apparatus and exposed surfaces of the stiffeners resting within the cavities; and

co-curing or co-bonding the stiffeners with the composite material on the SMP apparatus via pressure and heat to fabricate the composite part,

wherein the co-curing or co-bonding of the stiffeners with the composite material comprises:

heating the composite material to a composite material cure temperature;

triggering a change in modulus of the SMP apparatus from the rigid state to the malleable state; and

inducing a pressure differential sufficient to drive the SMP apparatus, in the malleable state, toward a mold surface corresponding to a desired configuration of a second surface of the composite part, thereby compressing the composite material against the mold surface during cure and compressing the stiffeners into the composite material during cure, thus co-curing or co-bonding the internal stiffeners to the composite material.

2. The method of claim 1 , wherein the stiffeners are internal stiffeners.

3. The method of claim 1 , wherein the stiffeners include at least one of frames, stringers, core, and additional layers of composite material.

4. The method of claim 1 , wherein the composite part is an aircraft monolithic fuselage, a wing, a nacelle, an aircraft panel, an aircraft duct, aircraft structural supports, an aircraft component made from solid laminates, integrally stiffened laminates, or core stiffened sandwich structure, or internal stiffeners for an aircraft component.

5. The method of claim 1 , wherein the stiffeners are pre-cured prior to placement in the cavities.

6. The method of claim 1 , wherein the stiffeners are uncured prior to placement in the cavities.

7. The method of claim 6 , wherein the stiffeners are uncured composite material placed on or wrapped around reinforcement inserts composed of shape memory polymer (SMP).

8. The method of claim 7 , wherein the SMP apparatus is triggered to the malleable state while the reinforcement inserts remain rigid during co-curing or co-bonding while.

9. The method of claim 1 , further comprising:

equalizing the induced pressure differential after the composite material is cured or inducing a pressure differential sufficient to urge the SMP apparatus away from the cured composite material; and

removing the SMP apparatus from within the composite part.

10. The method of claim 1 , wherein the SMP apparatus is configured to begin to change to the malleable state when heated above a temperature T g , wherein the composite material cure temperature is equal to or greater than T g , such that heating the composite material to the composite material cure temperature simultaneously heats and triggers a change in modulus of the SMP apparatus from the rigid state to the malleable state.

11. The method of claim 10 , wherein forming the SMP apparatus to correspond with the first surface of the composite part to be formed thereon comprises:

placing the SMP apparatus over an inner mandrel tool;

sealing ends of the SMP apparatus to the inner mandrel tool;

placing the SMP apparatus and inner mandrel tool into an outer mold;

heating the SMP apparatus above T g and inflating the SMP apparatus toward the outer mold;

cooling the SMP apparatus below T g ; and

removing the SMP apparatus in its rigid state from the outer mandrel tool.

12. The method of claim 1 , further comprising placing rigid reinforcement inserts into the cavities between the SMP apparatus and the stiffeners, wherein the cavities are sized and shaped to allow both the rigid reinforcement inserts and the internal stiffeners to rest therein.

13. A method of fabricating a composite part, the method comprising:

forming a shape memory polymer (SMP) apparatus to correspond with a first surface of the composite part to be formed thereon, including one or more channels or cavities configured for placement of internal stiffeners therein;

placing internal stiffeners within the channels or cavities of the SMP apparatus;

applying composite material onto the SMP apparatus and exposed surfaces of the internal stiffeners while the SMP apparatus is in a rigid state;

heating the composite material to a composite material cure temperature;

triggering a change in modulus of the SMP apparatus from the rigid state to a malleable state; and

inducing a pressure differential sufficient to drive the SMP apparatus, in the malleable state, toward a mold surface corresponding to a desired shape of a second surface of the composite part, thereby compressing the composite material against the mold surface during cure and compressing the internal stiffeners into the composite material during cure, thus co-curing or co-bonding the internal stiffeners to the composite material.

14. The method of claim 13 , wherein the internal stiffeners are at least one of frames, stringers, core, and additional layers of composite material.

15. The method of claim 13 , wherein the internal stiffeners are pre-cured prior to placement in channels or cavities.

16. The method of claim 13 , wherein the internal stiffeners are uncured prior to placement in the channels or cavities.

17. The method of claim 13 , further comprising:

equalizing the induced pressure differential after the composite material is cured or inducing a pressure differential sufficient to urge the SMP apparatus away from the cured composite material; and

removing the SMP apparatus from within the composite part.

18. The method of claim 13 , wherein the SMP apparatus is configured to begin to change to the malleable state when heated above a temperature T g , wherein the composite material cure temperature is equal to or greater than T g , such that heating the composite material to the composite material cure temperature simultaneously heats and triggers a change in modulus of the SMP apparatus from the rigid state to the malleable state.

19. The method of claim 18 , wherein forming the SMP apparatus to correspond with the first surface of the composite part to be formed thereon comprises:

placing the SMP apparatus over an inner mandrel tool;

sealing ends of the SMP apparatus to the inner mandrel tool;

placing the SMP apparatus and inner mandrel tool into an outer mold;

heating the SMP apparatus above T g and inflating the SMP apparatus toward the outer mold;

cooling the SMP apparatus below T g ; and

removing the SMP apparatus in its rigid state from the outer mandrel tool.

20. The method of claim 13 , further comprising placing rigid reinforcement inserts into the channels or cavities between the SMP apparatus and the internal stiffeners, wherein the channels or cavities are sized and shaped to allow both the rigid reinforcement inserts and the internal stiffeners to rest therein.

21. The method of claim 18 , wherein T g is a temperature between 100° F. and 400° F., wherein inducing a pressure differential comprises inflating the SMP apparatus by applying a pressure in a range of 1 psig to 150 psig to an inner surface of the SMP apparatus.

22. A method of fabricating a monolithic composite part, the method comprising:

placing pre-cured internal stiffeners in a desired configuration on a dummy skin resting within an outer mandrel tool;

inserting a shape memory polymer (SMP) apparatus within the outer mandrel tool;

heating the SMP apparatus to a temperature T g at which the SMP apparatus begins to become malleable;

inflating the SMP apparatus outward toward the internal stiffeners and dummy skin, thereby forming cavities into the SMP apparatus corresponding to the internal stiffeners;

cooling the SMP apparatus to a temperature below T g ;

removing the SMP apparatus from the outer mandrel tool and the dummy skin;

applying uncured composite material onto the SMP apparatus and exposed surfaces of the pre-cured internal stiffeners nested within the cavities formed in the SMP apparatus; and

co-bonding the internal stiffeners with the composite material using heat and pressure to fabricate the monolithic composite part.

23. The method of claim 22 , wherein the step of co-bonding the internal stiffeners with the composite material comprises:

inserting the composite material, internal stiffeners, and SMP apparatus back into the outer mandrel tool, without the dummy skin;

heating the composite material and SMP apparatus to a composite material cure temperature greater than the SMP T g ;

applying pressure to inflate the SMP apparatus, thereby compressing the composite material and the internal stiffeners together between the outer mandrel tool and the SMP apparatus;

collapsing or deflating the SMP apparatus once the composite material is cured into the monolithic composite part; and

removing the SMP apparatus from the monolithic composite part.

24. The method of claim 23 , wherein the internal stiffeners are at least one of frames, stringers, core, and any pre-cured composite part.

25. The method of claim 23 , wherein the SMP apparatus is sealed to an inner mandrel tool at peripheral portions of the SMP apparatus, wherein the step of applying pressure to inflate the SMP apparatus further comprises forcing pressurized gas through inflation holes in the inner mandrel tool toward the SMP apparatus.

26. The method of claim 25 , wherein the step of collapsing or deflating the SMP apparatus comprises applying vacuum via the inflation holes of the inner mandrel tool to pull the SMP apparatus against an outer surface of the inner mandrel tool.

27. The method of claim 22 , wherein the co-bonding of the internal stiffeners with the composite material comprises:

sealing the SMP apparatus to the outer mandrel tool;

heating the composite material and SMP apparatus to a composite material cure temperature greater than T g ; and

inducing a pressure differential such that the SMP apparatus expands and compresses the composite material and internal stiffeners against the outer mandrel tool during cure.

28. The method of claim 22 , further comprising securing rigid reinforcement inserts to portions of the internal stiffeners prior to inflating the SMP apparatus outward toward the internal stiffeners.

29. A method of fabricating a monolithic composite part, the method comprising:

placing rigid dummy internal stiffeners in a desired configuration on a dummy skin resting within an outer mandrel tool;

inserting a shape memory polymer (SMP) apparatus within the outer mandrel tool;

heating the SMP apparatus to a temperature T g at which the SMP apparatus begins to change from a rigid state to a malleable state;

inflating the SMP apparatus outward toward the dummy internal stiffeners and dummy skin, thereby forming channels into the SMP apparatus corresponding to the dummy internal stiffeners;

cooling the SMP apparatus to a temperature below T g ;

removing the outer mandrel tool, dummy internal stiffeners, and dummy skin from the SMP apparatus in its rigid state;

placing reinforcement inserts in contact with at least one surface of one or more uncured internal stiffeners;

placing the reinforcement inserts and the uncured internal stiffeners into the channels of the SMP apparatus;

applying uncured composite material onto the SMP apparatus and exposed surfaces of the uncured internal stiffeners positioned within the channels of the SMP apparatus; and

co-curing the internal stiffeners with the composite material using heat and pressure to fabricate the monolithic composite part.

30. The method of claim 29 , wherein the step of co-curing the internal stiffeners with the composite material comprises:

inserting the composite material, internal stiffeners, reinforcement inserts, and SMP apparatus back into the outer mandrel tool;

heating the composite material and SMP apparatus to a composite material cure temperature greater than the SMP T g ;

applying pressure to inflate the SMP apparatus, thereby compressing the composite material and the internal stiffeners together between the outer mandrel tool and the SMP apparatus;

collapsing or deflating the SMP apparatus once the composite material is cured into the monolithic composite part; and

removing the SMP apparatus from the monolithic composite part.

31. The method of claim 29 , wherein the internal stiffeners are at least one of frames, stringers, core, and additional layers of composite material.

32. The method of claim 30 , wherein the SMP apparatus is sealed to an inner mandrel tool at peripheral portions of the SMP apparatus, wherein the step of applying pressure to inflate the SMP apparatus further comprises forcing pressurized gas through inflation holes in the inner mandrel tool toward the SMP apparatus.

33. The method of claim 32 , wherein the step of collapsing or deflating the SMP apparatus comprises applying vacuum via the inflation holes of the inner mandrel tool to pull the SMP apparatus against an outer surface of the inner mandrel tool.

34. The method of claim 29 , wherein the step of co-curing the internal stiffeners with the composite material comprises:

sealing the SMP apparatus to the outer mandrel tool;

heating the composite material and SMP apparatus to a composite material cure temperature greater than T g ; and

inducing a pressure differential such that the SMP apparatus expands and compresses the composite material, internal stiffeners, and reinforcement inserts against the outer mandrel tool during cure.

35. The method of claim 29 , wherein the dummy internal stiffeners are substantially the same size and shape as the uncured internal stiffeners, wherein the dummy skin is substantially the same size and shape as the composite material applied onto the SMP apparatus and exposed surfaces of the uncured internal stiffeners.

36. A method of fabricating a composite part with integrated stiffeners, the method comprising:

triggering a shape memory polymer (SMP) apparatus to a malleable state;

shaping an SMP apparatus in the malleable state to correspond with a desired configuration of a first surface of the composite part to be fabricated, including one or more cavities configured for placement of stiffeners therein;

triggering the SMP apparatus to a rigid state;

placing the stiffeners into the cavities, wherein, prior to placement in the cavities, the stiffeners are uncured composite material placed on or wrapped around reinforcement inserts composed of shape memory polymer (SMP);

applying composite material onto the SMP apparatus and exposed surfaces of the stiffeners resting within the cavities; and

co-curing or co-bonding the stiffeners with the composite material on the SMP apparatus via pressure and heat to fabricate the composite part.

37. The method of claim 36 , wherein the SMP apparatus is triggered to the malleable state while the reinforcement inserts remain rigid during co-curing or co-bonding while.

Assignments (17)