Single phase toughened heat-curable resin systems exhibiting high strength after impact

Claim 2

A heat-curable resin system, comprising: (a) from 10 to about 80 weight percent of an epoxy resin component; (b) from 10 to about 50 weight percent of a prereact component; and (c) from 0.8 to about 1.6 equivalents, based upon the epoxy groups in components (a) and (b), of an aromatic diamine curing agent; wherein said prereact component (b) is the essentially phenolic hydroxyl-free reaction product of an epoxy resin and a diphenol; wherein the molecular weight of component (b) is such that phase separation does not result upon cure of the heat-curable resin system; and wherein all percents of (a) and (b) are percents by weight relative to the total weight of components (a), (b), and (c).

Claim 3

The heat-curable resin system of claim 1 wherein said resin system, when used to impregnate intermediate modulus carbon fibers to form a prepreg which is laid up into a composite, cured, and tested according to Boeing Specification Support Standard BSS 7260, retains a CAI value in excess of 275 MPa after an impact of 6.68 kJ/m.

Claim 4

The composition of claim 2 wherein said CAI value is greater than 300 MPa.

Claim 5

The composition of claim 1 wherein said prereact component (b) is prepared through the reaction of an epoxy resin with a diphenol selected from the group consisting of the bisphenols; resorcinol; hydroquinone; the dihydroxynaphthalenes; the dihydroxybiphenyls; the phenolated monomeric and oligomeric dicyclopentadienes; and mixtures thereof.

Claim 6

The composition of claim 1 wherein said epoxy resin in prereact component (b) is a glycidyl derivative of a diphenol selected from the group consisting of bisphenol A, bisphenol F, bisphenol S, the dihydroxynaphthalenes, the phenolated monomeric and oligomeric dicyclopentadienes, and the phenol terminated polyarylene oligomers containing ether, carbonyl, or sulfone groups interspersed between the arylene groups and having 10 or fewer arylene groups in the polyarylene oligomer; and mixtures thereof.

Claim 7

The composition of claim 1 wherein the epoxy resin component (a) is a glycidyl derivative of a diphenol selected from the group consisting of bisphenol A; bisphenol F; bisphenol S; the dihydroxynaphthalenes; the phenolated monomeric and oligomeric dicyclopentadienes; and the phenol terminated polyarylene oligomers containing ether, carbonyl, or sulfone groups interspersed between the arylene groups and having 10 or fewer arylene groups in the polyarylene oligomer; and mixtures thereof.

Claim 8

The composition of claim 1 wherein said curing agent (c) is selected from the group consisting of the diaminodiphenylmethanes; 2,2-bis[diaminophenyl]propanes; diaminobenzenes; diaminodiphenyloxides; diaminophenylsulfides; diaminodiphenylsulfones; and the aminophenyl terminated polyarylene oligomers having interspersed ether, carbonyl, and sulfone groups, and containing less than about five arylene groups; and mixtures thereof.

Claim 9

The composition of claim 4 wherein said epoxy resin in component (b) is a glycidyl derivative of a diphenol selected from the group consisting of bisphenol A; bisphenol F; bisphenol S; the dihydroxynaphthalenes; the phenolated monomeric and oligomeric dicyclopentadienes; and the phenol terminated polyarylene oligomers containing ether, carbonyl, or sulfone groups interspersed between the arylene groups and having 10 or fewer arylene groups in the polyarylene oligomer; and mixtures thereof.

Claim 10

The composition of claim 6 wherein said epoxy resin in component (b) is a glycidyl derivative of a diphenol selected from the group consisting of bisphenol A; bisphenol F; bisphenol S; the dihydroxynaphthalenes; the phenolated monomeric and oligomeric dicyclopentadienes; and the phenol terminated polyarylene oligomers containing ether, carbonyl, or sulfone groups interspersed between the arylene groups and having 10 or fewer arylene groups in the polyarylene oligomer; and mixtures thereof.

Claim 11

The composition of claim 2 wherein said heat-curable resin system retains a substantial part of its initial tack after ten days storage at room temperature.

Claim 12

The composition of claim 3 wherein said heat-curable resin system retains a substantial part of its initial tack after ten days storage at room temperature.

Claim 13

The composition of claim 5 wherein said heat-curable resin system retains a substantial part of its initial tack after ten days storage at room temperature.

Claim 14

The composition of claim 6 wherein said heat-curable resin system retains a substantial part of its initial tack after ten days storage at room temperature.

Claim 15

The composition of claim 7 wherein said heat-curable resin system retains a substantial part of its initial tack after ten days storage at room temperature.

Claim 16

The composition of claim 8 wherein said heat-curable resin system retains a substantial part of its initial tack after ten days storage at room temperature.

Claim 17

The composition of claim 9 wherein said heat-curable resin system retains a substantial part of its initial tack after ten days storage at room temperature.

Claim 18

A heat curable prepreg comprising: (a) a matrix resin component, comprising: i. from 10 to about 80 weight percent of an epoxy resin component; ii. from 10 to about 50 weight percent of a prereact component; and iii. from 0.8 to about 1.6 equivalents, based upon the epoxy groups in components (a) and (b), of an aromatic diamine curing agent; wherein said prereact component (ii) is essentially phenolic hydroxyl- group free wherein the molecular weight of component (ii) is such that phase separation does not result upon cure of the heat-curable resin system; and wherein all percents of (i) and (ii) are percents by weight relative to the total weight of components (i), (ii), and (iii); and (b) carbon fiber reinforcement; such that a quasiisotropic panel when prepared and impacted in accordance with Boeing standard BSS 7260 results in a compression after impact of greater than 300 MPa after being subjected to an impact of about 6.68 kJ/m, and wherein said prepreg retains a substantial part of its initial tack after ten days storage at room temperature.

Claim 19

A heat curable prepreg comprising: (a) a matrix resin component, comprising: i. from 10 to about 80 weight percent of an epoxy resin component; ii. from 10 to about 50 weight percent of a prereact component; and iii. from 0.8 to about 1.6 equivalents, based upon the epoxy groups in components (a) and (b), of an aromatic diamine curing agent; wherein said prereact component (ii) is essentially phenolic hydroxyl- group free wherein the molecular weight of component (ii) is such that phase separation does not result upon cure of the heat-curable resin system; and wherein all percents of (i) and (ii) are percents by weight relative to the total weight of components (i), (ii), and (iii); and (b) carbon fiber reinforcement; such that a quasiisotropic panel when prepared and impacted in accordance with Boeing standard BSS 7260 results in a compression after impact of greater than 300 MPa after being subjected to an impact of about 6.68 kJ/m, and wherein said prepreg retains a substantial part of its initial tack after ten days storage at room temperature.

Claim 20

A heat curable prepreg comprising: (a) a matrix resin component, comprising: i. from 10 to about 80 weight percent of an epoxy resin component; ii. from 10 to about 50 weight percent of a prereact component; and iii. from 0.8 to about 1.6 equivalents, based upon the epoxy groups in components (a) and (ii), of an aromatic diamine curing agent; wherein said prereact component (ii) is the essentially phenolic hydroxyl-free reaction product of an epoxy resin and a diphenol; wherein the molecular weight of component (ii) is such that phase separation does not result upon cure of the heat-curable resin system; and wherein all percents of (i) and (ii) are percents by weight relative to the total weight of components (i), (ii), and (iii); and (b) carbon fiber reinforcement; such that a quasiisotropic panel when prepared and impacted in accordance with Boeing standard BSS 7260 results in a compression after impact of greater than 300 MPa after being subjected to an impact of about 6.68 kJ/m, and wherein said prepreg retains a substantial part of its initial tack after ten days storage at room temperature.

Claim 21

A heat curable prepreg comprising: (a) a matrix resin component, comprising: i. from 10 to about 80 weight percent of an epoxy resin component; ii. from 10 to about 50 weight percent of a prereact component; and iii. from 0.8 to about 1.6 equivalents, based upon the epoxy groups in components (a) and (ii), of an aromatic diamine curing agent; wherein said prereact component (ii) is the essentially phenolic hydroxyl-free reaction product of an epoxy resin and a diphenol; wherein the molecular weight of component (ii) is such that phase separation does not result upon cure of the heat-curable resin system; and wherein all percents of (i) and (ii) are percents by weight relative to the total weight of components (i), (ii), and (iii); and (b) carbon fiber reinforcement; such that a quasiisotropic panel when prepared and impacted in accordance with Boeing standard BSS 7260 results in a compression after impact of greater than 300 MPa after being subjected to an impact of about 6.68 kJ/m, and wherein said prepreg retains a substantial part of its initial tack after ten days storage at room temperature.