Multidirectional Filament Reinforced Tape and Method of Manufacture

Abstract

The apparatus is a laminar shear resistant pre-impregnated resin tape for use in die forming pultrusuion processes, with the tape formed by integrating three distinguishable layers, each with integrated parallel reinforcing filaments. The layers are arranged within the tape so that the filaments of adjacent layers are oriented at angles to each other. The tape of the preferred embodiment of the invention is constructed with the filaments of the center layer at 90 degrees to the length of the tape and the filaments of the two outer layers aligned with the length of the tape. The center layer can be more heavily loaded with filaments than conventional tapes, and the outer two layers have less than the amount of filament load of the center layer.

Description

BACKGROUND OF THE INVENTION[0001]This invention deals generally with filament reinforced thermoplastic pre-impregnated tape, and more specifically with a multiple directional and multiple layer filament reinforced thermoplastic tape for use in pultrusion processes.[0002]Mixtures of various filaments and plastic resins are used to produce composites that have unique properties compared to the traditional engineering materials like metals and non-reinforced plastics. The filaments in the resin matrix increase the strength of the composites so much that they far exceed even the strongest metals, although composites are much lighter than their metal counterparts.[0003]Thermoplastic resins are often used to make these composites. Thermoplastic resins are solid at room temperature, and they soften and ultimately melt at elevated temperatures turning into a very viscous liquid. Reinforced thermoplastic composites are typically produced by intermingling finely ground resin particles with bu...

AI Technical Summary

Benefits of technology

[0017]The tape of the present invention can be substituted for the prior art two layer tape and eliminate the previously described shortcomings of the prior art products. The prepreg tape of the present invention eliminates the spot welding attachment process and the problems and limitations inherent in that type of construction. Moreover, the ratio of transverse to axial filament placements can easily be increased from the prior art 1:1 to almost any greater proportion. Such a higher ratio greatly increases the efficiency of filament usage in the composite and makes the final part stronger. Of course, the angle between the transverse filaments and the length dimension of the tape can also be varied.

[0018]The prepreg tape of the invention also has a balanced design so that any layer in the feed to the pultruder can be turned over without altering the filament stack up configuration of the finished part. Using the prepreg tape of this invention eliminates the possibility of the operator error in the pultrusion process in which two 0 degree and two transverse filament layers are adjacent in the finished product.

[0019]The prepreg tape of the invention has a 0 degree filament layer on both its surfaces, and therefore no extra layer of 0 degree prepreg is required as a cover for an otherwise exposed outer layer of 90 degree filaments before feeding the pultruder. The tape of this invention also allows the first transverse load bearing layer of filaments to be much closer to the outer surface, thereby increasing the strength of the final product.

[0020]Using tape of this invention also permits the filament loading of the transverse filament layer to be increased to a very high level with low resin content. Low resin content has normally promoted shear failure in prior art prepreg, however, since the amount of filament used in the 0 degree layers can be kept low, the outer 0 degree layers can be richly loaded with resin. These 0 degree layers then bond well to the resin lean transverse filament layer, and they also bond well to each other when processed in the pultruder. Therefore, the end products are not prone to the same degree of laminar shear failure as prior art products even though most of the filament is in a resin lean environment.

[0021]Several alternate embodiments of the invention are also available. The two outer layers can be produced so they are not identical. The prepreg tape from this embodiment can include solid lubricants mixed with the resin used in one or both of the 0 degree outer layers. Solid lubricants typically have a deleterious affect on the mechanical properties of a composite as the concentrations are increased. If used throughout the entire composite, the amount must be kept quite low to prevent serious degradation of strength. However, with this embodiment one thin outer layer can be heavily loaded with a solid lubricant while keeping the two other layers in the tape at a low, safe, level of lubricant, or even without any lubricant. This prepreg tape can then be used as the outer layer of the pultruded part, with the lubricated surface facing outward. The finished pultruded part is mechanically sound while still being highly self lubricated on the outer surface. A variation of this embodiment uses only the two unidirectional plies, one heavily loaded with solid lubricant and the other at a very low level or lubricant free.

Problems solved by technology

This process is labor intensive and less than ideal.

If a piece is absent in the composite, the finished product is defective.

The resulting composite is inefficient because the 50% of the filament oriented in the lengthwise direction is not used to carry the bending load across the width direction.

Another problem is that the alternating layers of 0 and 90 degree filaments must be arranged to achieve a balanced design.

However, using the two layer tapes, an operator error is easily possible.

This results in a product flaw.

Components made using a 0 and 90 degree prepreg orientation can also exhibit shear failures when subjected to bending.

This failure mode is most prevalent in products made from prepreg that has high filament loading and low resin content.

These failures typically occur at the interface between the 0 and 90 degree layers at the center of the bending plane; but usually never within a composite layer itself.

This shear failure condition can limit the ultimate strength of the part.

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