Process for preparing moulded articles from fibre-reinforced composite materials—I

Patent metadata

Field	Value
Publication number	US-10507596-B2
Application number	US-201615164366-A
Country	US
Kind code	B2
Filing date	May 25, 2016
Priority date	May 29, 2015
Publication date	Dec 17, 2019
Grant date	Dec 17, 2019

Abstract

The present invention relates to low or zero-tack composite materials such as pre-pregs and their use in automated manufacturing, particularly robotic pick and place. The present invention further relates to an automated process for preparing an article, particularly a molded article, from a fiber-reinforced composition material.
The molded articles prepared by the process described herein are particularly suitable as components for transport applications, and particularly the automotive industry. The automotive components prepared by the present invention are particularly suitable as mid- or high-volume automotive parts, in which cost and speed of production are paramount. The present invention provides a process in which the cutting and handling of pre-preg materials is greatly simplified, providing advantages of efficiency and economy. The lay-up time according to the present invention is significantly reduced, allowing a reduction in the unit cost per component and/or allowing the high volume of component production desired in the automotive industry.

First claim

The invention claimed is:

1. An automated process for preparing a moulded article from a plurality of pre-pregs comprising the steps of:
(a) providing a mould;
(b) disposing a laminar pre-preg into or onto said mould by an automated conveying member which applies a prehensile force to said pre-preg to convey said pre-preg from a starting position to a finishing position in or on said mould;
(c) repeating step (b) at least once to dispose one or more further pre-pregs into or onto said mould;
wherein said laminar pre-preg is a fibre-reinforced curable composite material, wherein said pre-preg comprises a core layer having a first surface and a second surface and further comprises a surface layer disposed directly on at least one surface of said core layer,
wherein said core layer comprises one or more layer(s) of reinforcing fibres impregnated with a first curable resin, which exhibits a viscosity at 21° C. of less than 500,000 Pa·s and/or an uncured glass transition temperature (Tg) of less than 8° C. as measured by differential scanning calorimetry (DSC) at a heating rate of 10° C. per minute, and wherein said surface layer comprises a second curable resin, which exhibits a viscosity at 21° C. of at least 500,000 Pa·s and/or an uncured glass transition temperature (Tg) of at least 8° C. as measured by DSC at a heating rate of 10° C. per minute; and
wherein the prehensile force is applied by said automated conveying member directly to the external surface of said surface layer of said pre-preg.

2. The automated process of claim 1 wherein said prehensile force is selected from vacuum, magneto-adhesion and electro-adhesion.

3. The automated process of claim 2 wherein said automated conveying member comprises an astrictive end effector to convey said prepreg from said starting position to said finishing position in or on said mould, optionally wherein said pre-preg is conveyed from said starting position to an intermediate position between said starting and finishing positions, wherein said intermediate position is a stacking position where said pre-preg is stacked or wherein said intermediate position is a position where said pre-preg is deposited in or on a release film or lay-up mould or mould loading device, and wherein said pre-preg is then conveyed from the intermediate position to said finishing position in or on said mould.

4. The automated process of claim 3 , wherein steps (b) and (c) are conducted in an environment at ambient temperature in the range of 18° C. to 23° C.

5. The automated process of claim 4 wherein said process further comprises the step of thermally curing said plurality of pre-pregs while the pre-pregs are in or on the mould to form the moulded article, wherein thermal curing is conducted at a cure temperature of greater than 120° C., and wherein the surface layer remains part of the fibre-reinforced composite material during and after curing.

6. The automated process of claim 1 wherein the surface layer does not contain any reinforcing fibres.

7. The automated process of claim 6 wherein at least one of the pre-preg of the plurality of pre-preg is not associated with a protective removable interleave disposed on an external surface of the pre-preg and wherein the automated process does not comprise a step of removing said protective removable interleave.

8. The automated process of claim 1 wherein the first curable resin comprises one or more curable thermosetting resin(s) selected from the group consisting of epoxy resins, bismaleimides, vinyl ester resins, cyanate ester resins, isocyanate-modified epoxy resins, phenolic resins, benzoxazine, formaldehyde condensate resins, polyesters, acrylics, and combinations thereof.

9. The automated process of claim 1 wherein each of the first and second curable resins comprises at least one selected from multi-functional epoxy resin, wherein said multifunctional epoxy resin is selected from diglycidyl ether of bisphenol F (DGEBF), diglycidyl ether of bisphenol A (DGEBA), diglycidyl dihydroxy naphthalene, resin based on phenol and cresol epoxy novolacs, glycidyl ethers of phenol-aldehyde adducts, aromatic epoxy resins, aliphatic triglycidyl ethers, dialiphatic triglycidyl ethers, aliphatic polyglycidyl ethers, epoxidised olefins, triglycidyl aminophenols, aromatic glycidyl amines, heterocyclic glycidyl imidines and amides, glycidyl ethers, fluorinated epoxy resins, N,N,N′,N′-tetraglycidyl diamino diphenylmethane (TGDDM) and N,N,N′,N′-tetraglycidyl-m-xylenediamine.

10. The automated process of claim 9 wherein the first and second curable resins are independently selected from curable resins which comprise:
a first difunctional epoxy resin component selected from bisphenol A epoxy resins; and/or
(ii) a second difunctional epoxy resin component selected from bisphenol F epoxy resins;
optionally in combination with one or more of the epoxy resin(s) selected from:
(iii) an epoxy phenol novolac (EPN) resin;
(iv) an epoxy cresol novolac (ECN) resin;
(v) triglycidyl aminophenol; and
(vi) tetraglycidyl diamino diphenyl methane (TGDDM).

11. The automated process of claim 1 wherein the second curable resin exhibits a viscosity at 21° C. of at least 1,000,000 Pa·s, and/or an uncured Tg of from about 12 to 30° C. and wherein the first curable resin exhibits a viscosity at 21° C. of no more than 300,000 Pa·s, and/or an uncured Tg of no more than 6° C.

12. The automated process of claim 5 , wherein curing is performed at a temperature in the range of from 130° C. to 150° C. for a period of no more than 10 minutes.

13. The automated process of claim 6 wherein a surface layer is disposed on both surfaces of said core layer and the surface layer exhibits an areal weight of from about 5 to about 100 g/m 2 .

14. The automated process of claim 1 wherein the core layer exhibits an areal weight of from about 200 to about 1500 g/m 2 .

15. The automated process of claim 5 wherein the surface layer of the prepreg is tack-free prior to curing.

16. The automated process of claim 1 wherein the pre-preg exhibits a permeability to air such that a 100×100 mm sample of the pre-preg is retained for at least 60 seconds by a silicone suction cup of external diameter 22 mm and working internal diameter 20 mm exerting a vacuum level defined by an open flow-rate of 20 liters/min prior to contact with the surface of the pre-preg.

17. The automated process of claim 16 wherein the pre-preg exhibits an air permeability:
such that the flow rate through the pre-preg is no more than 18 liters/min, measured when the pre-preg has been retained for 60 seconds by a silicone suction cup of external diameter 22 mm and working internal diameter 20 mm exerting a vacuum level defined by an open flow-rate of 20 liters/min prior to contact with the surface of the pre-preg; and/or
(ii) of no more than 4 cm 3 /s/cm 2 , as measured according to ASTM D737-04.

18. The automated process of claim 1 wherein said pre-preg is flexible at 20° C.

Assignees

• Cytec Ind Inc

Inventors

• Steele Mark Raymond
• Gibbs Andrew Steven

Classifications

• B29B11/16 Primary

  comprising fillers or reinforcement {(non-woven fabrics per se D04H1/00, D04H3/00)} · CPC title

• B29K2995/0063

  Density · CPC title

• B29K2063/00

  Use of {EP, i.e.} epoxy resins {or derivatives thereof}, as moulding material · CPC title

• B29K2307/04

  Carbon · CPC title

• B29K2105/089

  fabric · CPC title