Patent Application
20190210338
The present application relates to thermoplastic composite materials, and is particularly directed to a thermoplastic composite laminate with ultraviolet protection and method of forming the same.
A known way of processing a thermoplastic composite material to manufacture a thermoplastic composite laminate that can be subsequently formed into a thermoplastic composite part is to use a method of manufacture known as continuous compression molding. In this manufacturing method, a continuous process is provided for the consolidation of thermoplastic pre-preg material into a thermoplastic composite laminate. The thermoplastic composite laminate can be of a single thickness, multiple thicknesses, or variable thicknesses.
Another known way of processing a thermoplastic material to manufacture a thermoplastic composite laminate is to use a method of manufacture known as press consolidation, which can be accomplished by either a “static” process or a “shuttle” process. In the static process, a large surface area press is used in which thermoplastic pre-preg material is heated, smashed into a consolidated thermoplastic laminate, and then cooled. In the shuttle process, multiple presses with variable temperatures are used in which thermoplastic pre-preg material is converted to a consolidated thermoplastic composite laminate.
In both methods of manufacture, the cooling of the consolidated thermoplastic composite laminate is controlled to achieve desired properties. The consolidated thermoplastic composite laminate can then be thermo-formed into a final desired shape, if the laminate is not already in the final desired shape, to provide a thermoplastic composite part. The thermoplastic composite part can be exposed to ultraviolet radiation during its service life. For example, the thermoplastic composite part may comprise a part used in an aerospace application. As a result, ultraviolet degradation damage of the thermoplastic composite part may be observed during its service life.
Accordingly, those skilled in the art continue with research and development efforts in the field of processing thermoplastic composite materials and laminates for making thermoplastic composite parts for aerospace applications.
In one aspect, a consolidated thermoplastic composite laminate with ultraviolet protection is provided. The consolidated thermoplastic composite laminate with ultraviolet protection comprises at least one ply of thermoplastic pre-preg material. The consolidated thermoplastic composite laminate with ultraviolet protection also comprises a polymer film positioned on a side of the at least one ply of thermoplastic pre-preg material. The polymer film imparts ultraviolet protection to the thermoplastic pre-preg material after the polymer film and the thermoplastic pre-preg material are heated to a temperature sufficient to consolidate the polymer film and the thermoplastic pre-preg material and thereby to provide the consolidated thermoplastic composite laminate with ultraviolet protection.
In another aspect, a method of forming a consolidated thermoplastic composite laminate with ultraviolet protection is provided. The method comprises selecting at least one ply of thermoplastic pre-preg material, and applying on a side of the selected at least one ply of thermoplastic pre-preg material a polymer film that comprises a polymer component and an ultraviolet stabilizer component. The method also comprises consolidating the thermoplastic pre-preg material and the applied polymer film to provide the consolidated thermoplastic composite laminate with ultraviolet protection.
In yet another aspect, a method of forming a consolidated thermoplastic composite part with ultraviolet protection is provided. The method comprises selecting a thermoplastic pre-preg material that includes a select one of poly ether ether ketone (PEEK), poly ether ketone ketone (PEKK), poly phenylene sulfide (PPS), polyamide (PA), poly ether imide (PEI), and poly aryl ether ketone (PAEK). The method also comprises applying on a side of the selected thermoplastic pre-preg material a polymer film comprising an ultraviolet protection additive that includes a select one of carbon black, titanium dioxide, nickel compounds, and 2,2,6,6-tetramethylpiperidine derivatives. The method further comprises heating the selected thermoplastic pre-preg material and the applied polymer film to a temperature sufficient to form a thermoplastic composite laminate with ultraviolet protection and thereby to form the consolidated thermoplastic composite part.
Other aspects will become apparent from the following detailed description, the accompanying drawings and the appended claims.
The present application is directed to a thermoplastic composite laminate with ultraviolet protection and method of forming the same. The specific thermoplastic composite laminate, forming method, and the industry in which the laminate and the forming method are implemented may vary. It is to be understood that the disclosure below provides a number of embodiments or examples for implementing different features of various embodiments. Specific examples of components and arrangements are described to simplify the present disclosure. These are merely examples and are not intended to be limiting.
By way of example, the disclosure below describes a thermoplastic composite laminate with ultraviolet protection that is used to form a thermoplastic composite part for aircraft. The thermoplastic composite laminate, the method of forming the thermoplastic composite laminate, and the method of forming the thermoplastic composite part may be implemented by an original equipment manufacturer (OEM) for manufacturing thermoplastic composite laminates or thermoplastic composite parts, or both, in compliance with military and space regulations.
Referring to
Referring to
The polymer film 130 and the thermoplastic pre-preg material 110 are heated to a temperature sufficient to consolidate the polymer film 130 and the thermoplastic pre-preg material 110 (and the at least one ply of reinforcement material 120 if provided) to provide a consolidated thermoplastic composite laminate 150 with ultraviolet protection, as shown in
Compositionally, the thermoplastic pre-preg material 110, which may be single ply or multi-ply, may be formed from various materials or combinations of materials. In some embodiments, the at least one ply of thermoplastic pre-preg material 110 includes a select one of poly ether ether ketone (PEEK), poly ether ketone ketone (PEKK), poly phenylene sulfide (PPS), polyamide (PA), poly ether imide (PEI), and poly aryl ether ketone (PAEK).
In some embodiments, the at least one ply of reinforcement material 120 includes a select one of carbon fiber and glass fiber. Other reinforcement materials are possible.
In some embodiments, the polymer film 130 comprises an ultraviolet stabilizer component in combination with a polymer component that includes, as examples, at least one of poly ether ether ketone (PEEK), poly ether ketone ketone (PEKK), poly phenylene sulfide (PPS), polyamide (PA), poly ether imide (PEI), and poly aryl ether ketone (PAEK). Other polymer components are possible. In some embodiments, the ultraviolet stabilizer component includes a select one of carbon black, titanium dioxide, nickel compounds, and 2,2,6,6-tetramethylpiperidine derivatives. Other ultraviolet stabilizer components are possible.
In some embodiments, the polymer film 130 comprises an optional reinforcement component, which is schematically shown in
In some embodiments, a thickness “X” of the polymer film 130 is between about 0.1% and about 15% of the total weight of the consolidated thermoplastic composite laminate 150 with ultraviolet protection. In some embodiments, the thickness X of the polymer film 130 is between about 2% and about 4% of the total weight of the consolidated thermoplastic composite laminate 150 with ultraviolet protection.
In some embodiments, the thickness X of the polymer film 130 is between about 0.005 inches and about 0.010 inches. In some embodiments, a thickness “Y” of the at least one ply of thermoplastic pre-preg material 110 is between about 0.001 inches and about 0.014 inches.
The at least one ply of thermoplastic pre-preg material 110, the at least one ply of reinforcement material 120, and the polymer film 130 form the multi-layered hybrid stack 100 (
Those skilled in the art will appreciate that only a portion of the hybrid stack 100 that is used to form the thermoplastic composite laminate 150 is shown in
After the hybrid stack 100 of the thermoplastic pre-preg material 110, the reinforcement material 120, and the polymer film 130 has been consolidated, the thermoplastic composite laminate 150 with ultraviolet protection shown in
As another example, the reinforcement material 120 may comprise an inorganic filler material. The inorganic filler material makes the resulting thermoplastic composite laminate 150 produced less permeable to water, gas, and organic molecules. This is because the inorganic filler material provides a tortuous pathway around which water, gas, and organic molecules must travel in order to permeate the thermoplastic composite laminate 150. Moreover, the reinforcement material 120 could act as an electrical isolation layer, depending upon the particular type of inorganic filler material selected. The electrical isolation feature may be advantageous in some applications. For example, on an aircraft panel, the need for an outer fiberglass layer to prevent galvanic corrosion with contact metal parts can be eliminated by making the aircraft panel with the thermoplastic composite laminate 150 disclosed herein.
The material of the at least one ply of thermoplastic pre-preg material 110 and the material of the polymer film 130 can each be selected and tailored to reduce ultraviolet induced stress in the thermoplastic composite laminate 150 depending upon the particular application of the thermoplastic composite laminate 150.
The following example illustrates a method of thermoplastic forming a composite laminate in accordance with an embodiment. The example thermoplastic forming method is intended to illustrate, but in no way limits, the scope of the invention.
Referring to
In block 210, at least one ply of thermoplastic pre-preg material is selected. Optionally, as shown in block 215, at least one ply of reinforcement material is applied on a side of the selected at least one ply of thermoplastic pre-preg material. Then in block 220, a polymer film that comprises a polymer component and an ultraviolet stabilizer component is applied on a side of the selected at least one ply of thermoplastic pre-preg material. The process proceeds to block 230 in which the thermoplastic pre-preg material and the applied polymer film are consolidated to provide the consolidated thermoplastic composite laminate with ultraviolet protection. Due to polymer chain entanglement, there is good adhesion between the polymer film and the at least one ply of thermoplastic pre-preg material. The process then ends.
In some embodiments, the applying on a side of the at least one ply of thermoplastic pre-preg material a polymer film that comprises a polymer component and an ultraviolet stabilizer component includes selecting an ultraviolet protection additive that includes a select one of carbon black, titanium dioxide, nickel compounds, and 2,2,6,6-tetramethylpiperidine derivatives.
In some embodiments, the method further comprises applying on an opposite side of the at least one thermoplastic pre-preg material another polymer film that comprises a polymer component and an ultraviolet stabilizer component.
In some embodiments, the selecting at least one ply of thermoplastic pre-preg material includes selecting a polymer matrix that includes a select one of poly ether ether ketone (PEEK), poly ether ketone ketone (PEKK), poly phenylene sulfide (PPS), polyamide (PA), poly ether imide (PEI), and poly aryl ether ketone (PAEK).
In some embodiments, the applying on a side of the at least one ply of thermoplastic pre-preg material a polymer film that comprises a polymer component and an ultraviolet stabilizer component includes selecting an ultraviolet stabilizer component that is compatible with melting temperature of the selected polymer matrix.
In some embodiments, the consolidating the thermoplastic pre-preg material and the applied polymer film to provide the consolidated thermoplastic composite laminate with ultraviolet protection includes heating the polymer matrix to at least the melting temperature of the selected polymer matrix.
In some embodiments, the consolidating the thermoplastic pre-preg material and the applied polymer film to provide the consolidated thermoplastic composite laminate with ultraviolet protection includes selecting a consolidating process from one of continuous compression molding, press consolidation, stamp forming, autoclave consolidation, and out-of-autoclave consolidation.
The above-described example thermoplastic forming methods may be carried out using manufacturing systems or apparatus suitable for making the thermoplastic composite laminate 150. Numerous manufacturing systems or apparatus for making thermoplastic composite laminates are known and, therefore, will not be described.
Referring to
In block 310, a thermoplastic pre-preg material is selected. The selected thermoplastic pre-preg material includes a select one of poly ether ether ketone (PEEK), poly ether ketone ketone (PEKK), poly phenylene sulfide (PPS), polyamide (PA), poly ether imide (PEI), and poly aryl ether ketone (PAEK). Optionally, as shown in block 315, at least one ply of reinforcement material is applied on a side of the selected at least one ply of thermoplastic pre-preg material. Then in block 320, a polymer film is applied on a side of the selected thermoplastic pre-preg material. The polymer film comprises an ultraviolet protection additive that includes a select one of carbon black, titanium dioxide, nickel compounds, and 2,2,6,6-tetramethylpiperidine derivatives. The process then proceeds to block 330 in which the selected thermoplastic pre-preg material and the applied polymer film are heated to a temperature sufficient to form a thermoplastic composite laminate with ultraviolet protection and thereby to form the consolidated thermoplastic composite part. The process then ends.
In some embodiments, the method further comprises heating the thermoplastic composite laminate to form a desired shape of the thermoplastic composite part with ultraviolet protection.
In some embodiments, the heating the selected thermoplastic pre-preg material and the applied polymer film to a temperature sufficient to form a thermoplastic composite laminate with ultraviolet protection and thereby to form the consolidated thermoplastic composite part includes heating the selected thermoplastic pre-preg material and the applied polymer film to a temperature between about 200° C. and about 400° C. to melt the thermoplastic pre-preg material.
In some embodiments, the method further comprises adding a reinforcement material to the polymer film before applying the selected polymer film on a side of the selected thermoplastic pre-preg material. As an example, the reinforcement material can be formed as part of the polymer film.
Examples of the present disclosure may be described in the context of an aircraft manufacturing and service method 1000 as shown in
Each of the processes of illustrative method 1000 may be performed or carried out by a system integrator, a third party, and/or an operator (e.g., a customer). For the purposes of this description, a system integrator may include, without limitation, any number of aircraft manufacturers and major-system subcontractors; a third party may include, without limitation, any number of vendors, subcontractors, and suppliers; and an operator may be an airline, leasing company, military entity, service organization, and so on.
As shown in
Moreover, thermoplastic composite laminates and thermoplastic forming methods shown or described herein may be employed during any one or more of the stages of the manufacturing and service method 1000. For example, components or subassemblies corresponding to component and subassembly manufacturing (block 1008) may be fabricated or manufactured in a manner similar to components or subassemblies produced while aircraft 1002 is in service (block 1014). Also, one or more examples of thermoplastic composite laminates and thermoplastic forming methods, or combination thereof, may be utilized during production stages (blocks 1010 and 1012). Similarly, one more examples of thermoplastic composite laminates and thermoplastic forming methods, or a combination thereof, may be utilized, for example and without limitation, while aircraft 1002 is in service (block 1014) and during maintenance and service stage (block 1016).
It should be apparent that a thermoplastic composite laminate with ultraviolet protection produced in accordance with above-described example methods is suitable for any type of application. The thermoplastic composite laminate with ultraviolet protection is especially advantageous when used to manufacture an aircraft part that is exposed to ultraviolet radiation and subject to ultraviolet degradation damage over its service-life. Example aircraft parts include, but are not limited to, fuselage, wings, empennages, nacelles and the like. The ultraviolet protection reduces ultraviolet induced stress of the aircraft part. As such, the aircraft part is capable of operating at higher temperatures with reduced stress. The result is an aircraft part that does not need to be replaced as often. This lowers maintenance and service costs.
Although an aerospace example is shown, the principles disclosed herein may be applied to other industries, such as the automotive industry, the marine industry, and the construction industry. Accordingly, in addition to the aircraft 1002, the principles disclosed herein may apply to other vehicles (e.g., land vehicles, marine vehicles, space vehicles, etc.) as well as to other types of structures.
Also, although the above description describes example thermoplastic composite laminates, example methods of forming thermoplastic composite laminates, and example methods of forming thermoplastic composite parts for OEMs in accordance with military and space regulations, it is conceivable that the example thermoplastic composite laminates, the example thermoplastic composite parts, and forming methods may be implemented in any industry in accordance with the applicable industry standards.
Further, although various embodiments of the disclosed thermoplastic composite laminate and forming methods have been shown and described, modifications may occur to those skilled in the art upon reading the specification. The present application includes such modifications and is limited only by the scope of the claims.
