Co-cured UV-resistant fiberglass-coated composite material for aircraft wing fuel tank assembly

Abstract

To provide a composite material for use in a vehicle fuel tank assembly excellent in resistance to UV / visible light.SOLUTION: A co-curable composite material comprises: a co-curable composite material substrate; and a co-curable UV / visible light-resistant fiberglass-containing coating layer in direct contact with the co-curable composite material substrate to form a co-curable UV / visible light-resistant fiberglass-containing layer-coated composite material substrate assembly.SELECTED DRAWING: None

Description

Technical Field

[0001] The present disclosure relates broadly to the field of composite materials, and more particularly to the field of composite materials used for large structural components. In particular, the present disclosure relates to the field of composite materials used as structural materials for the inner and outer surfaces of large structural aircraft components.

Background Art

[0002] The use of composite materials in the manufacture of various structural component parts has been increasing. At least because of the strength-to-weight ratio, composite materials offer advantages as alternatives to high-density materials such as metals and metal alloys. The overall weight of a finished structure (or the weight of the component parts of a finished structure) is an important consideration in the selection of materials used in the manufacture of such a finished structure or the manufacture of the component parts of a finished structure.

[0003] A coating layer added to a composite material is less durable and has a shorter lifespan than the composite material to which such a coating layer is added. A composite material assembly may also include external or internal layers, which may include, for example, protective coatings or other coating layers. For example, when a composite material is used in the manufacture of a vehicle, such as an aircraft, the exterior paint coating, known as the "livery" of an aircraft, may require modification, rework, and changes to logos, designs, and color schemes over the lifespan of the vehicle. Such modifications to the livery may involve, for example, the removal of one or more decorative coating layers added to the composite material, including one or more paint layers. However, removing one layer or type of layer (paint, primer, adhesion promoter, adhesive layer, etc.) from the material laminated on top of the composite material may necessitate the removal of further layers or types of layers, followed by construction for backup or other reconstruction. In addition, modifications to the livery that require paint removal via the use of paint removal techniques may damage the underlying layers or even the composite material itself if the composite material is subjected to excessive mechanical paint removal techniques.

[0004] Unless otherwise explicitly stated, the descriptions herein shall not be considered prior art simply because they are included in the "technical and / or background art." [Overview of the Initiative]

[0005] According to this embodiment, a co-curable composite material is disclosed, comprising a co-curable composite structural material substrate and a co-curable UV / visible light resistant fiberglass-containing coating layer. To form a composite material substrate coated with a co-curable / co-cured UV / visible light resistant fiberglass-containing layer, the co-curable UV / visible light resistant fiberglass-containing coating layer is in direct contact with the co-curable composite structural material substrate. The composite material substrate significantly influences the manufacture of the composite material, improves the performance of the composite structural material substrate, and reduces its weight. This eliminates the need for a separate UV / visible light resistant coating previously added to the composite structural material substrate, at least in the preparation of composite material systems used in structural assemblies for large components, including, for example, the inner and outer surfaces of vehicles, including aircraft, and further including, for example, vehicle fuel tanks (e.g., aircraft fuel tanks) that may be located within an aircraft wing assembly.

[0006] According to this embodiment, in a co-cured state, a composite material substrate coated with a co-cured UV / visible light resistant fiberglass layer may be further configured to form a vehicle fuel tank. The vehicle fuel tank includes a vehicle fuel tank interior and a vehicle fuel tank cavity. The vehicle fuel tank cavity is defined and otherwise surrounded by the vehicle fuel tank interior, which exclusively contains a co-curable UV / visible light resistant fiberglass-containing layer. The co-curable UV / visible light resistant fiberglass-containing layer has a UV / visible light transmittance value of 0% to about 20% for UV / visible light wavelengths in the range of about 200 nm to about 800 nm, when the co-curable UV / visible light resistant fiberglass-containing layer has an average thickness in the range of about 2 mil to about 6 mil. The co-curable UV / visible light resistant fiberglass-containing coating layer is configured to completely cover the co-curable composite material substrate.

[0007] In another embodiment, a co-curable composite material substrate is co-curable with a co-curable UV / visible light resistant fiberglass-containing coating layer at temperatures ranging from approximately 250°F to approximately 370°F.

[0008] In another embodiment, the co-curable composite material substrate includes an epoxy resin matrix.

[0009] In a further embodiment, the co-curable composite material substrate includes a fiber-reinforced epoxy resin matrix comprising at least one of carbon fibers, boron fibers, aramid fibers, fiberglass fibers, polyester fibers, and combinations thereof.

[0010] In another embodiment, the co-curable composite material substrate includes a carbon fiber reinforced polymer composite material.

[0011] In another embodiment, the co-curable composite material substrate comprises at least one carbon fiber reinforced polymer prepreg.

[0012] In another present embodiment, a vehicle fuel tank is disclosed. The vehicle fuel tank includes a vehicle fuel tank assembly comprising a co-cured composite material. The vehicle fuel tank assembly includes a vehicle fuel tank interior. The vehicle fuel tank interior includes a co-cured composite material substrate and a co-cured UV / visible light resistant fiberglass-containing coating layer in direct contact with the co-cured composite material substrate. The co-cured UV / visible light resistant fiberglass-containing layer is configured to completely cover the co-cured composite material substrate. The vehicle fuel tank further includes a vehicle fuel tank cavity. The vehicle fuel tank cavity is defined by the vehicle fuel tank cavity interior. To form the vehicle fuel tank assembly, the co-cured composite material substrate and the co-cured UV / visible light resistant fiberglass-containing coating layer are co-cured in a co-curing regimen. The co-curing regimen includes a co-curing temperature in the range of about 250 degrees Fahrenheit to about 370 degrees Fahrenheit. The co-cured UV / visible light resistant fiberglass-containing layer has a UV / visible light transmittance value of 0% to approximately 20% for UV / visible light wavelengths in the range of approximately 200 nm to approximately 800 nm, when the co-curable and co-cured UV / visible light resistant fiberglass-containing coating layer has an average thickness in the range of approximately 2 mil to approximately 6 mil.

[0013] In another embodiment, the co-cured composite material substrate includes an epoxy resin matrix.

[0014] In another embodiment, the co-cured composite substrate includes a fiber-reinforced epoxy resin matrix comprising at least one of carbon fibers, boron fibers, aramid fibers, fiberglass fibers, polyester fibers, and combinations thereof.

[0015] In a further embodiment, the co-cured composite material substrate includes a carbon fiber reinforced polymer composite material.

[0016] In another embodiment, the co-cured composite material substrate comprises at least one carbon fiber reinforced polymer prepreg.

[0017] In a further embodiment, a co-cured UV / visible light resistant fiberglass coating layer is configured to form the inner surface of a vehicle fuel tank cavity.

[0018] In a further embodiment, the inner surface of the vehicle fuel tank further includes a fuel tank primer layer positioned to cover a co-cured UV / visible light resistant fiberglass layer. The inner surface of the fuel tank cavity is defined by the fuel tank primer layer.

[0019] In another embodiment, including the co-cured UV / visible light resistant fiberglass-containing layer within a co-cured composite material assembly eliminates the need for at least one of the fuel tank primer layer and the UV-absorbing paint layer within the vehicle fuel tank assembly.

[0020] Further embodiments disclose an aircraft wing assembly including a vehicle fuel tank, which includes a vehicle fuel tank assembly comprising a co-cured composite material. The vehicle fuel tank assembly includes a vehicle fuel tank interior. The vehicle fuel tank interior includes a co-cured composite material substrate and a co-cured UV / visible light resistant fiberglass-containing coating layer in direct contact with the co-cured composite material substrate. The co-cured UV / visible light resistant fiberglass-containing coating layer is configured to completely cover the co-cured composite material substrate. The vehicle fuel tank further includes a vehicle fuel tank cavity. The vehicle fuel tank cavity is defined by the vehicle fuel tank interior. To form the vehicle fuel tank assembly, the co-cured composite material substrate and the co-cured UV / visible light resistant fiberglass-containing coating layer are co-cured in a co-curing regimen. The co-curing regimen includes a co-curing temperature in the range of approximately 250 degrees Fahrenheit to approximately 370 degrees Fahrenheit. The co-cured UV / visible light resistant fiberglass-containing layer has a UV / visible light transmittance value of 0% to approximately 20% for UV / visible light wavelengths in the range of approximately 200 nm to approximately 800 nm, when the co-cured UV / visible light resistant fiberglass-containing layer has an average thickness in the range of approximately 2 mil to approximately 6 mil.

[0021] In another embodiment, the vehicle includes a vehicle fuel tank which includes a vehicle fuel tank assembly comprising a co-cured composite material. The vehicle fuel tank assembly includes a vehicle fuel tank interior. The vehicle fuel tank interior includes a co-cured composite material substrate and a co-cured UV / visible light resistant fiberglass-containing layer in direct contact with the co-cured composite material substrate. The co-cured UV / visible light resistant fiberglass-containing layer is configured to completely cover the co-cured composite material substrate. The vehicle fuel tank further includes a vehicle fuel tank cavity. The vehicle fuel tank cavity is defined by the vehicle fuel tank interior. To form the vehicle fuel tank assembly, the co-cured composite material substrate and the co-cured UV / visible light resistant fiberglass layer are co-cured in a co-curing regimen. The co-curing regimen includes a co-curing temperature in the range of about 250 to about 370 degrees Fahrenheit. The co-cured UV / visible light resistant fiberglass-containing layer has a UV / visible light transmittance value of 0% to approximately 20% for UV / visible light wavelengths in the range of approximately 200 nm to approximately 800 nm, when the co-cured UV / visible light resistant fiberglass-containing layer has an average thickness in the range of approximately 2 mil to approximately 6 mil. The vehicle is selected from the group consisting of manned aircraft, unmanned aircraft, manned spacecraft, unmanned spacecraft, manned rotary-wing aircraft, unmanned rotary-wing aircraft, manned ground vehicles, unmanned ground vehicles, manned water vehicles, unmanned water vehicles, manned underwater vehicles, unmanned underwater vehicles, satellites, and combinations thereof.

[0022] A further embodiment of this invention discloses a method comprising providing a co-curable composite substrate. The composite substrate includes a first side surface of the co-curable composite substrate and a second side surface of the co-curable composite substrate. The method further comprises adding a co-curable UV / visible light resistant fiberglass-containing layer on the second side surface of the co-curable composite. The co-curable UV / visible light resistant fiberglass-containing layer added on the second side surface of the co-curable composite has an average thickness ranging from about 2 mils to about 6 mils. The method further comprises co-curing the co-curable composite substrate with the co-curable UV / visible light resistant fiberglass-containing layer to form a co-cured composite vehicle fuel tank assembly. The co-cured composite vehicle fuel tank assembly includes a co-cured inner surface of the vehicle fuel tank assembly. The inner surface of a co-cured composite vehicle fuel tank assembly includes a co-cured UV / visible light resistant fiberglass-containing layer, which has a UV / visible light transmittance value of 0% to about 20% for UV / visible light wavelengths in the range of about 200 nm to about 800 nm when the co-cured UV / visible light resistant fiberglass-containing layer has an average thickness in the range of about 2 mil to about 6 mil. The co-cured UV / visible light resistant fiberglass-containing layer is configured to define the vehicle fuel tank cavity. According to the disclosed method, including a co-cured UV / visible light resistant fiberglass-containing layer within a co-cured composite vehicle fuel tank assembly eliminates the need for at least one of a UV / visible light absorbing detail primer layer and a UV / visible light absorbing paint layer within the co-cured composite vehicle fuel tank assembly.

[0023] In another embodiment, the co-cured composite substrate includes a fiber-reinforced epoxy resin matrix comprising at least one of carbon fibers, boron fibers, aramid fibers, fiberglass fibers, polyester fibers, and combinations thereof.

[0024] In a further embodiment, the co-cured composite material substrate includes a carbon fiber reinforced polymer composite material.

[0025] In another aspect, the method further includes depositing a fuel tank primer layer on the UV / visible light resistant fiber glass containing layer.

[0026] The above features, functions, and advantages can be realized alone in various aspects or combined in yet another aspect, the details of which can be confirmed by referring to the following description and the accompanying drawings.

[0027] Although the variations of the present disclosure have been described in general terms, the accompanying drawings will now be referred to. These are not necessarily drawn to scale.

Brief Description of the Drawings

[0028] [Figure 1A] It is a view of a vehicle in the form of an aircraft according to this aspect. [Figure 1B] It is a cross-sectional side view of a vehicle fuel tank in the form of an aircraft main wing assembly fuel tank. [Figure 2A] It is an enlarged cross-sectional representative side view of a co-curable UV / visible light resistant composite material according to this aspect. [Figure 2B] It is an enlarged cross-sectional representative side view of a co-cured UV / visible light resistant composite material according to this aspect. [Figure 2C] It is an enlarged cross-sectional representative side view of a co-cured UV / visible light resistant composite material system according to this aspect. [Figure 3] It is a flowchart outlining the method according to this aspect. [Figure 4] It is a flowchart outlining the method according to this aspect.

Modes for Carrying Out the Invention

[0029] For example, material layers that can be added as coatings may be added to the surface of a composite material with the aim of changing the surface properties of the composite material. For example, primers or other coating layers may be added to a composite material to improve the adhesion of subsequent coating layers, such as paint or topcoats, to a composite material surface that may already have one or more other coatings applied. Laminating coating materials onto the surface of a composite material is laborious and time-consuming and can add substantial weight to large objects or structures containing such composite materials with multiple coating layers.

[0030] In addition, the paint removal process, which removes various paint coating layers from composite materials, often damages the protective surface layer applied to the composite material. When the paint removal process is applied beneath a paint coating layer, the paint coating layer may peel off from the surface layer, potentially requiring extensive resurfacing work. For example, one or more of the composite material coating layers may each require separate surface treatment preparation steps and procedures before one or more coating layers are subsequently deposited on the composite material surface. In some cases, a portion of one or more previously deposited coatings needs to be removed or reworked before any further coating layers can be added. Such intermediate rework of the composite material surface during processing is laborious, time-consuming, and expensive.

[0031] For example, during the manufacture of composite material components, which may include epoxy resin composites or carbon fiber reinforced polymer materials, the composite material surface may begin to degrade due to exposure to ambient ultraviolet / visible light (UV / visible light) radiation. To avoid changes in the outer surface properties of the composite material that may be at least partially caused by exposure to UV / visible light radiation, the composite material surface is often coated with at least one protective layer, such as a surfacer or primer layer sprayed onto the surface. The protective layer may contain, for example, a UV "blocking" agent.

[0032] Such UV-blocking layers are typically not placed on the inner surface of an assembly where the inner mold lines may define the inner profile of the composite material. Since UV / visible light degradation of composite materials can also occur on the inner surface of the composite material substrate assembly (e.g., where the inner mold lines or IML may be present), this embodiment considers treating such "inner" surfaces of composite material assemblies, such as a vehicle fuel tank cavity housed within a vehicle fuel tank.

[0033] Adding UV mitigating or "blocking" agents as layers to the surface of composite materials often adds complexity to the manufacturing process, at least in ways that increase manufacturing time, rework time, and overall production costs. This is because the UV-blocking material cover added in this way is typically removed from the composite or chemically or mechanically reactivated before further processing of the composite assembly. In addition, primers and surface coating layers are often treated to accept subsequent paint layers or topcoats. This treatment of individual subsequent layers added to the composite system (which may be a "stack" of laminated composite materials) again increases manufacturing time, rework time, and overall production costs.

[0034] Composite materials are typically post-treated or "reworked," for example, to repaint and / or resurface the composite material. For example, primers or paint coatings containing UV mitigating or UV "blocking" agents may be applied to the composite material surface for the purpose of protecting the composite material surface from degradation and / or discoloration that may occur, for example, when the composite material is used as a construction material in the manufacture of larger structures, by exposure to UV / visible light radiation.

[0035] In addition, UV / visible light damage from UV / visible light wavelengths that affect coating layers used to coat composite materials and / or the underlying composite materials during aircraft manufacturing and operation can result in the composite materials requiring rework. Exposure to UV / visible light radiation can alter the properties of materials over time. For example, UV / visible light radiation can make coating layers or composite materials vulnerable to processing damage, for example, when they are exposed to mechanical paint removal techniques. Selecting material layers for large structures to protect against environmental damage, including UV / visible light damage, may result in the need to add a series of coating layers. Each such coating layer addition incurs a significant amount of time and expense, and adds weight to large structures, such as aircraft (and considering the weight, fuel consumption, cargo and passenger capacity, aircraft range, etc., may be further affected).

[0036] This embodiment discloses co-curable and co-cured composite materials comprising a co-curable or co-cured layer of UV / visible light-resistant fiberglass in direct contact with a composite material substrate. Incorporation of a co-cured and co-curable UV / visible light-resistant fiberglass layer into a composite material substrate can significantly impact composite material manufacturing, improve performance, and reduce the weight of structural composite materials by at least eliminating the need for a separate UV-resistant coating previously applied to the composite material substrate, for example, in the preparation of composite material systems used in structural assemblies for larger components, including the inner and outer surfaces of vehicles, including aircraft.

[0037] According to this embodiment, a method for improving UV / visible light protection and reducing UV / visible light degradation of composite materials is disclosed. Also disclosed are composite material substrates with improved UV / visible light protection without the previously required presence of typically added protective covers or layers of UV / visible light resistant primers or other layers (e.g., (one or more) UV-absorbing paints). In addition to preventing UV / visible light degradation of the surface of the underlying composite material substrate, the methods, systems, and apparatus of this disclosure eliminate the need for protective covers, protective primer layers, and UV-absorbing paint layers, resulting in a reduction in the complexity of the composite material system and the overall stack weight of the composite material system, which further shortens the processing time of the composite material. The reduction in UV / visible light degradation of the composite material also further reduces the need for rework of the composite material (which is required by such UV / visible light degradation).

[0038] Figure 1 is a diagram of a vehicle taking the form of an aircraft according to this embodiment. As shown in Figure 1, the aircraft 10 includes a wing assembly 12, a horizontal stabilizer assembly 14, and a vertical stabilizer assembly 16. The composite materials of this disclosure are configured to form, or otherwise to be, various aircraft assemblies, including those shown in Figure 1A. As further shown in Figure 1A, the aircraft wing assembly 12 includes a vehicle fuel tank taking the form of an aircraft fuel tank within the wing assembly (hereinafter referred to as the aircraft wing assembly fuel tank). Figure 1B shows a cross-sectional side view of the wing assembly 13 along line 1B-1B. As shown in Figure 1B, the aircraft wing assembly fuel tank 13 includes an outer surface 13a and an inner surface 13b. Figure 1B further shows the wing assembly fuel tank cavity 13d. The wing assembly fuel tank cavity 13d is defined (e.g., enclosed, bounded) by the inner surface 13b of the aircraft wing assembly fuel tank.

[0039] According to this embodiment, a composite material substrate is provided which may include an epoxy resin-based composite material combined with a fiber matrix that may include carbon fibers, boron fibers, aramid fibers, fiberglass fibers, polyester fibers, and combinations thereof. Carbon fibers are particularly preferred as the composite material substrate, and carbon fiber-reinforced polymer composite materials are particularly preferred.

[0040] In further embodiments of this disclosure, a composite material used in the manufacture of a composite material structure further includes a co-curable UV / visible light resistant layer (hereinafter referred to herein as a UV / visible light suppression layer). The UV / visible light resistant layer provided to the composite material exclusively takes the form of a co-curable UV / visible light resistant fiberglass layer, which may be, for example, a single co-curable UV / visible light resistant fiberglass ply (e.g., taking the form of a single ply film layer). In further embodiments, the co-curable UV / visible light resistant fiberglass layer is provided in close contact with a co-curable composite material substrate material. To form a composite material substrate coated with co-curable UV / visible light resistant fiberglass, the composite material substrate is co-curable with the co-curable UV / visible light resistant fiberglass layer.

[0041] According to this embodiment, a “co-curable” material is defined as a material that can co-cure with another material. Thereafter, two co-curable materials will co-cure when exposed to common curing conditions. For example, conditions that can be imposed by a predetermined curing regime (such as a predetermined temperature, pressure, ramp-up temperature / rate, residence time, etc.) to form a “co-cured” composition.

[0042] The composite material substrate, also referred to herein as equivalently as the "base layer," "underlayment," or "composite material substrate layer," may be an epoxy resin-based material, may include a fiber-reinforced polymer composite material having an epoxy resin-based matrix, or may include a carbon fiber-reinforced polymer composite material, and may be a co-curable composite material. In this embodiment, the co-curable composite material may be any suitable composite material that can be co-cured with a co-curable fiberglass-containing layer material at a co-curing temperature in the range of approximately 250°F to approximately 370°F.

[0043] Composite materials are often laminated into a laminate having a selected number of layers of composite material (called "prepregs"). Prepregs can be "pre-impregnated" composite fibers, where a matrix material, such as an epoxy resin-based material, is already present. The fibers often take the form of a fabric, and the matrix is ​​used to bond them together and with other components during manufacturing. Composite matrix materials are typically partially cured to allow for easy handling. Such composite matrix materials may require cooling or refrigeration to prevent further partial curing or complete curing; such composite matrix materials are called B-stage materials. Ultimately, B-stage prepregs are stored in a cooled area because ambient heat can promote complete polymerization. It is also possible to impregnate bulk quantities of fibers and then store the prepregs in a cooled area for extended periods until subsequent curing. Prepregs are typically formed on a flat, workable surface. The stack of prepreg plies can then be formed on it using a molding or forming tool, also known as a mandrel, and may be shaped into a desired form if desired. This embodiment uses, but is not limited to, a layup layer of composite material prepreg to form co-curable and co-cured composite material substrates.

[0044] According to this embodiment, the selected degree of UV / visible light resistance and UV / visible light protection can be exclusively imparted to the co-cured composite substrate by directly contacting the surface of the co-curable composite substrate with a co-curable UV / visible light resistant fiberglass layer. This forms a composite material coated with co-cured UV / visible light resistant fiberglass after the two materials have been co-cured. In other words, according to this embodiment, previously required UV / visible light resistant primers and UV-blocking paints can be eliminated, or otherwise rendered unnecessary, because their UV protection functions within the UV / visible light resistant composite material are exclusively satisfied by the addition and placement of a co-curable UV / visible light resistant fiberglass layer provided in direct contact with the co-curable composite substrate.

[0045] According to this embodiment, by co-curing a co-curable UV / visible light resistant glass fiber layer with a co-curable composite material, benefits (including UV protection) are exclusively imparted by the co-cured UV / visible light resistant fiber glass layer of this disclosure to an underlying co-cured composite material substrate, which may be at least a co-cured epoxy-based composite material and may further be a co-cured carbon fiber reinforced polymer substrate material. To impart a selected degree of complete UV protection to the composite material coated with the co-cured UV / visible light resistant fiber glass layer of this disclosure, no further UV protective layer (e.g., in the form of a UV / visible light resistant primer or UV / visible light resistant paint) is considered, or otherwise not required to be included in the co-cured composite material of this disclosure. According to this embodiment, such imparted benefits include, but are not limited to, UV / visible light protection of the “underlying” composite material substrate (which may be an epoxy resin-based composite material) and protection of the composite material from the harmful effects of mechanical paint removal techniques.

[0046] In addition, the robustness of the co-curable UV / visible fiberglass layer of the Disclosure, co-cured on a co-curable composite substrate, which may be a co-curable epoxy composite substrate, is sufficient to withstand subsequent and repeated heat treatments that may be required during subsequent and repeated repainting protocols. That is, unlike some repainting protocols currently required, the co-cured UV / visible fiberglass layer of the Disclosure does not need to be replaced, removed, or otherwise re-added during rework, paint removal, repainting, repeated heat treatments, etc. Accordingly, the Disclosure further considers the removal or readjustment of only the layers coated on the co-cured UV / visible fiberglass-containing layer of the Disclosure (e.g., topcoat layer, basecoat layer, clearcoat layer, intermediate coating layer, etc.). In this manner, the Disclosure Disclosure discloses protection of the composite material from harmful effects, which may otherwise occur when the composite material surface is exposed to UV / visible light radiation.

[0047] Through the use of the co-cured UV / visible light resistant fiberglass coated composite substrate of this disclosure, a significant number of procedural steps that would ordinarily be required during the repainting or reworking of the composite substrate, and that were previously required, are eliminated. As a result, substantial resource reductions include, for example, material costs for replacing UV / visible light damaged layers, and manpower hours previously required for individual layer addition processes (e.g., individual layer pre-surface treatment steps, layer addition steps, layer post-surface treatment steps, which include chemical addition, physical surface treatment (including sand polishing, etc.), inspection of deposited layers, etc.).

[0048] According to this embodiment, Figure 2A is an enlarged representative cross-sectional side view of a co-curable composite material assembly 20a, comprising a co-curable composite material 22a (having a first side surface 22a' of the co-curable composite material and a second side surface 22a'' of the co-curable composite material substrate) on which a co-curable UV / visible light resistant fiberglass layer 24a (having a first side surface 24a' of the co-curable UV / visible light resistant fiberglass layer and a second side surface of the co-curable UV / visible light resistant fiberglass layer 24a'' is disposed. According to this embodiment, the co-curable composite material assembly 20a can be co-cured to form a co-cured composite material assembly. The co-curable composite material assembly 20a follows a co-curing regimen. In a co-curing regimen, a co-curable UV / visible light resistant fiberglass layer 24a, placed on a co-curable composite material substrate 22a, is co-cured for an appropriate duration at a curing temperature of less than 400 degrees Fahrenheit, more preferably in the range of approximately 250 degrees Fahrenheit to approximately 370 degrees Fahrenheit, to co-cure the two components and form a co-cured UV / visible light resistant composite material assembly.

[0049] As shown in Figure 2A, the co-curable composite substrate 22a may be a co-curable epoxy resin-based composite material, and may also be a co-curable carbon fiber reinforced polymer composite substrate. The composite substrate assembly can be used to form structural composite materials for the manufacture of structural components and structural component assemblies of vehicles. The vehicle may include, for example, an aircraft wing assembly fuel tank of the type shown in Figure 1B, and an aircraft wing assembly fuel tank of the type that may be installed in the shown vehicle taking the form of an aircraft shown in Figure 1A.

[0050] Figure 2B is an enlarged, representative cross-sectional side view of a co-cured UV / visible light-resistant composite assembly 20b formed from the uncured and co-curable components shown in Figure 2A. This includes a co-cured UV / visible light-resistant fiberglass layer 24b (having a first side 24b' and a second side 24'' of the co-cured UV / visible light-resistant fiberglass layer) in the co-cured state as shown in Figure 2B. This is co-cured with a co-cured composite substrate 22b (having a first side 22b' and a second side 22b'' of the co-cured composite substrate). According to this embodiment, the co-cured UV / visible light-resistant fiberglass 24b may be a single ply or two or more plies. The co-cured UV / visible light-resistant fiberglass layer 24b can exclusively impart a selected degree of UV / visible light protection to the underlying co-cured composite substrate 22b (i.e., be responsible for essentially 100% protection). As a result, the co-cured UV / visible light resistant fiberglass layer has a UV / visible light transmittance value ranging from approximately 0% to approximately 20% for UV / visible light wavelengths ranging from approximately 200 nm to approximately 800 nm, when the co-cured UV / visible light resistant fiberglass-containing layer has an average thickness ranging from approximately 2 mil to approximately 6 mil.

[0051] According to this embodiment, a co-cured UV / visible light resistant composite material assembly 20b, as shown in Figure 2B, can be used as a structural component, for example, including the inner surface of an aircraft wing assembly fuel tank. When the composite material of this disclosure is used to form internal structures (e.g., fuel tank cavities) during the formation of a composite material substrate, it will be understood that inner mold lines (IMLs) 25a, 25b are transferred, for example, from a composite material forming tool or forming surface (e.g., a mandrel) to the co-curable and co-cured composite material substrate. Such inner mold lines are transferred onto and otherwise present on a co-cured UV / visible light resistant fiberglass layer 24b. The IMLs are located on the inner surface of a structure, for example, the inner surface 13b of an aircraft wing assembly fuel tank, as shown in Figure 1B.

[0052] According to this embodiment, the UV / visible light resistant fiberglass layer is selected to have UV / visible light resistance properties and values. Thereafter, the co-cured UV / visible light resistant fiberglass layer is solely responsible for imparting a certain degree of UV / visible light resistance and UV / visible light protection to the underlying epoxy resin composite material. That is, according to this embodiment, the UV / visible light blocking capability of the co-cured UV / visible light resistant fiberglass layer of the Disclosure eliminates the need for, redundancy, or otherwise unnecessary presence of any further UV / visible light resistant layer in the composite material system of the Disclosure, and eliminates the need to incorporate UV / visible light blocking agents into the composite material substrate. Instead, the overall UV / visible light blocking function for the co-cured composite material assembly of the Disclosure and the structure incorporating the co-cured composite material assembly of the Disclosure is completely satisfactory. This is due to the UV / visible light blocking capability introduced into the resulting co-cured composite material assembly by the UV / visible light resistant fiberglass layer, which may be, for example, a single-ply UV / visible light resistant fiberglass layer. Such redundant, unnecessary, and / or (one or more) excluded layers include, for example, UV / visible light resistant paints, UV / visible light resistant primers, and UV / visible light resistant topcoats. Again, according to this embodiment, no further UV / visible light resistant layers are present in the co-cured composite assembly of the Disclosure and are not required to achieve the desired and selected UV / visible light blocking functions present in the co-cured composite assembly of the Disclosure.

[0053] In this embodiment, as shown in Figure 2B, the co-cured composite substrate 22b may be a co-cured epoxy resin composite, and may further be a co-cured carbon fiber reinforced polymer composite substrate. The co-cured composite substrate assembly is configured to form structural composites for the manufacture of structural components and structural component assemblies of a vehicle. The vehicle may include, for example, an aircraft wing assembly fuel tank of the type shown in Figure 1B, and an aircraft wing assembly fuel tank of the type that may be installed in the shown vehicle taking the form of an aircraft shown in Figure 1A.

[0054] According to this embodiment, when configured as a structural composite material for various aircraft, the co-cured UV / visible light resistant composite material 20b of the type shown in Figure 2B may be configured to accept, or otherwise facilitate, the deposition of various primers and topcoat layers, which may be part of the formation of the interior of a vehicle fuel tank, such as the interior of a larger structural assembly, such as an aircraft wing assembly fuel tank, for example, the type shown in Figure 1B, or it may be before the formation of such an interior (e.g., the interior cavity wall or cavity boundary). The type of aircraft wing assembly fuel tank that can be installed resides within the aircraft wing assembly of an aircraft, as shown in Figure 1A.

[0055] Figure 2C is an enlarged cross-sectional representative side view of a co-cured UV / visible light resistant composite assembly 20c, which takes the form of a co-cured composite system further comprising the co-cured UV / visible light resistant composite assembly layer shown in Figure 2B (as assembly 20b). Specifically, Figure 2C shows a co-cured composite substrate 22c on which a co-cured UV / visible light resistant fiberglass layer 24c has been added and placed. As further shown in Figure 2c, according to this embodiment, the co-cured UV / visible light resistant composite assembly does not include any further UV / visible light resistant materials (e.g., taking the form of (one or more) UV / visible light resistant primer layers or (one or more) UV / visible light resistant paint layers). That is, as shown in Figure 2C, according to this embodiment, the UV / visible light resistant fiberglass layer 24c is solely responsible for imparting UV / visible light resistance to the UV / visible light resistant composite material assembly 20c (for example, by preventing UV / visible light radiation from penetrating the co-cured UV / visible light resistant fiberglass layer to the underlying co-cured composite material substrate). As shown in Figures 2B and 2C, the co-cured composite material structure may be a co-cured carbon fiber reinforced polymer composite material substrate, or further, a co-cured epoxy resin-based composite material substrate.

[0056] As shown in Figure 2C, the co-cured UV / visible light resistant composite assembly 20c further includes a fuel tank primer layer 26c covering a co-cured UV / visible light resistant fiberglass layer 24c. According to this embodiment, if desired, the average thickness of the fuel tank primer can be significantly reduced from the amount and thickness of a conventional fuel tank primer layer previously required for known composite assemblies. In particular, the co-cured UV / visible light resistant composite assembly (this) including a UV / visible light resistant fiberglass layer can facilitate the reduction or elimination of the thickness of the fuel tank primer layer. Such a reduction in thickness (collectively referred to herein as "primer coating layer thickness") or elimination of the fuel tank primer can result in significant weight reduction, cost reduction, shorter processing times, shorter rework times, reduced man-hours, and reduced material requirements. These can be seen, for example, on a large structural scale, such as in aircraft wing assembly fuel tanks.

[0057] Further embodiments of this invention consider structures comprising at least one of the following: co-curable composite materials and co-cured composite materials, assemblies comprising co-cured composite materials, subassemblies comprising co-cured composite materials, and assemblies and / or subassemblies comprising co-cured UV / visible light resistant composite materials manufactured according to the methods described herein. Such structures include, for example, manned aircraft, unmanned aircraft, manned spacecraft, unmanned spacecraft, manned rotary-wing aircraft, unmanned rotary-wing aircraft, manned ground vehicles, unmanned ground vehicles, manned water vehicles, unmanned water vehicles, manned underwater vehicles, unmanned underwater vehicles, satellites, and combinations thereof.

[0058] Figures 3 and 4 are flowcharts outlining methods for producing co-curable and co-cured composite materials of the present disclosure. As shown in Figure 3, Method 100 is outlined. Method 100 includes providing a co-curable composite material substrate (102), which may be a co-curable epoxy resin-based composite material and may further be a co-curable carbon fiber reinforced polymer material substrate. Method 100 further includes placing a co-curable UV / visible light resistant fiberglass layer on top of the co-curable composite material layer (104). The composite material substrate has an inner mold line. The composite material substrate may be a co-curable epoxy resin-based composite material and may further be a carbon fiber reinforced polymer composite material. According to this embodiment, the co-curable UV / visible light resistant fiberglass may be a single ply or may be a plurality of fiberglass layer plies. As a result, the co-curable UV / visible light resistant fiberglass layer has a UV / visible light transmittance value in the range of about 0% to about 20% for UV / visible light wavelengths in the range of about 200 nm to about 800 nm, when the UV / visible light resistant fiberglass-containing layer has an average thickness in the range of about 2 mil to about 6 mil. Co-curable UV / visible light resistant composite material assemblies including a UV / visible light resistant fiberglass-containing layer may be of at least the type shown and described in Figure 2A and described herein. Method 100 further includes co-curing a co-curable composite material substrate with a co-curable UV / visible light resistant fiberglass-containing layer at a temperature in the range of about 250°F to about 370°F to form a co-cured UV / visible light resistant composite material fuel tank assembly of the type shown in Figure 1B and described herein (106). Method 100 further considers the formation of co-cured UV / visible light resistant composite material assemblies of the type shown in at least Figures 2B and 2C and described herein.

[0059] Figure 4 is a flowchart outlining the method according to this embodiment. As shown in Figure 4, Method 200 includes providing a co-curable composite material substrate which may be a co-curable epoxy resin-based composite material substrate and may further be a co-curable carbon fiber reinforced polymer material substrate (102). Method 200 further includes adding and arranging a co-curable UV / visible light resistant fiberglass layer on top of the co-curable composite material layer (104). The composite material substrate has an inner mold line. According to this embodiment, the co-curable UV / visible light resistant fiberglass layer may be a single ply or multiple plies. Thereafter, the co-curable UV / visible light resistant fiberglass layer has a UV / visible light transmittance value in the range of about 0% to about 20% UV / visible transmittance for UV / visible light wavelengths in the range of about 200 nm to about 800 nm, when the UV / visible light resistant fiberglass-containing layer has an average thickness in the range of about 2 mil to about 6 mil. Co-curable UV / visible resistant composite material assemblies including a UV / visible resistant fiberglass-containing layer may be of at least the types shown and described in Figure 2A and further described herein. Method 200 further includes co-curing a co-curable composite material layer with a co-curable UV / visible resistant fiberglass-containing layer at a temperature ranging from about 250°F to about 370°F to form a co-cured UV / visible resistant composite material fuel tank assembly of the type shown in Figure 1B and further described herein (106). According to this embodiment, Method 200 further includes providing a fuel tank primer to the co-cured UV / visible resistant fiberglass layer to form, for example, a co-cured composite material assembly of the type shown in Figure 2C (108). The co-cured composite material assembly is configured to form, for example, an aircraft wing assembly fuel tank of the type shown in Figure 1B.

[0060] Furthermore, this disclosure includes embodiments as defined below.

[0061] Article 1. A co-curable composite material (20a), A co-curable composite material substrate (22a), A co-curable UV / visible light resistant fiberglass-containing coating layer (24a) comprising a co-curable UV / visible light resistant fiberglass-containing coating layer in direct contact with the co-curable composite substrate for forming a composite substrate assembly (20b)(20c) coated with the co-curable UV / visible light resistant fiberglass-containing layer, The composite material substrate assembly coated with the co-curable UV / visible light resistant fiberglass-containing layer is configured to form a vehicle fuel tank (13), and the vehicle fuel tank is Vehicle fuel tank inner surface (13b) and A vehicle fuel tank cavity (13d) comprising a vehicle fuel tank cavity defined by the inner surface of the vehicle fuel tank which exclusively contains the co-curable UV / visible light resistant fiberglass-containing coating layer, The co-curable UV / visible light resistant fiberglass-containing coating layer has a UV / visible light transmittance value of 0% for UV / visible light wavelengths in the range of approximately 200 nm to approximately 800 nm when the co-curable UV / visible light resistant fiberglass-containing coating layer has an average thickness in the range of approximately 2 mil to approximately 6 mil. A co-curable composite material wherein the co-curable UV / visible light resistant fiberglass-containing coating layer is configured to completely cover the co-curable composite material substrate.

[0062] Article 2. The co-curable composite material according to Clause 1, wherein the co-curable composite material substrate is co-curable with the co-curable UV / visible light resistant fiberglass-containing coating layer at a temperature in the range of approximately 250 degrees Fahrenheit to approximately 370 degrees Fahrenheit.

[0063] Article 3. The co-curable composite material substrate is the co-curable composite material according to Clause 1, comprising an epoxy resin matrix.

[0064] Article 4. The co-curable composite material according to Clause 1, wherein the co-curable composite material substrate comprises a fiber-reinforced epoxy resin matrix, and the fiber-reinforced epoxy resin matrix comprises at least one of carbon fibers, boron fibers, aramid fibers, fiberglass fibers, polyester fibers, and combinations thereof.

[0065] Article 5. The co-curable composite material substrate is the co-curable composite material according to Clause 1, comprising a carbon fiber reinforced polymer composite material.

[0066] Article 6. The co-curable composite material substrate is the co-curable composite material according to Clause 1, comprising at least one carbon fiber reinforced polymer prepreg.

[0067] Article 7. Vehicle fuel tank (13), The vehicle fuel tank assembly includes a co-cured composite material (20b)(20c), the vehicle fuel tank assembly includes a vehicle fuel tank inner surface (13b), and the vehicle fuel tank inner surface is Co-cured composite material substrates (22b)(22c), A co-cured UV / visible light resistant fiberglass-containing layer (24b)(24c) configured to be in direct contact with the co-cured composite material substrate and to completely cover the co-cured composite material substrate, Includes a vehicle fuel tank cavity (13d) defined by the inner surface of the vehicle fuel tank, To form the vehicle fuel tank assembly, the co-cured composite material substrate and the co-cured UV / visible light resistant fiberglass-containing layer are co-cured with a co-curing regimen, the co-curing regimen includes a co-curing temperature range of approximately 250°F to approximately 370°F. The co-cured UV / visible light resistant fiberglass-containing layer has a UV / visible light transmittance value of 0% for UV / visible light wavelengths in the range of approximately 200 nm to approximately 800 nm when the co-cured UV / visible light resistant fiberglass-containing layer has an average thickness in the range of approximately 2 mil to approximately 6 mil.

[0068] Article 8. The vehicle fuel tank according to Clause 7, wherein the co-cured composite material substrate comprises an epoxy resin matrix.

[0069] Article 9. The vehicle fuel tank according to Clause 7, wherein the co-cured composite material substrate comprises a fiber-reinforced epoxy resin matrix, the fiber-reinforced epoxy resin matrix comprising at least one of carbon fibers, boron fibers, aramid fibers, fiberglass fibers, polyester fibers, and combinations thereof.

[0070] Article 10. The vehicle fuel tank according to Clause 7, wherein the co-cured composite material substrate comprises a carbon fiber reinforced polymer composite material.

[0071] Article 11. The vehicle fuel tank according to Clause 7, wherein the co-cured composite material substrate comprises at least one carbon fiber reinforced polymer prepreg.

[0072] Article 12. The vehicle fuel tank according to Clause 7, wherein the co-cured UV / visible light resistant fiberglass-containing layer is configured to form the inner surface of the vehicle fuel tank.

[0073] Article 13. The vehicle fuel tank (20c) according to Clause 7, further comprising a fuel tank primer layer (26c) disposed to cover the co-cured UV / visible light resistant fiberglass-containing layer, wherein the inner surface of the vehicle fuel tank is defined by the fuel tank primer layer.

[0074] Article 14. The vehicle fuel tank according to Clause 7, wherein the co-cured UV / visible light resistant fiberglass-containing layer is included in the co-cured vehicle fuel tank assembly, thereby eliminating the need for at least one of the fuel tank primer layer and the UV-absorbing paint layer in the vehicle fuel tank assembly.

[0075] Article 15. Aircraft wing assembly (12) including the vehicle fuel tank as described in Clause 7.

[0076] Article 16. Vehicles (10) including a vehicle fuel tank as described in Clause 7.

[0077] Article 17. The aforementioned vehicle, A vehicle according to claim 16, selected from the group consisting of manned aircraft, unmanned aircraft, manned spacecraft, unmanned spacecraft, manned rotary-wing aircraft, unmanned rotary-wing aircraft, manned ground vehicles, unmanned ground vehicles, manned water vehicles, unmanned water vehicles, manned underwater vehicles, unmanned underwater vehicles, artificial satellites, and combinations thereof.

[0078] Article 18. Method (100), (102) To provide a co-curable composite material substrate, wherein the composite material substrate includes a first side surface and a second side surface of the composite material substrate. (104) Adding a co-curable UV / visible light resistant fiberglass-containing layer on a second side surface of the co-curable composite material substrate, wherein the co-curable UV / visible light resistant fiberglass-containing layer added on the second side surface of the co-curable composite material substrate has an average thickness in the range of about 2 mils to about 6 mils, and To form a co-cured composite vehicle fuel tank assembly, the co-curable composite substrate is co-cured with a co-curable UV / visible light resistant fiberglass-containing layer (106), The co-cured composite vehicle fuel tank assembly includes an inner surface of the co-cured composite vehicle fuel tank assembly, the inner surface of the co-cured composite vehicle fuel tank assembly includes a co-cured UV / visible light resistant fiberglass-containing layer, the co-cured UV / visible light resistant fiberglass-containing layer has a UV / visible light transmittance value of 0% for UV / visible light wavelengths in the range of approximately 200 nm to approximately 800 nm when the co-cured UV / visible light resistant fiberglass-containing layer has an average thickness in the range of approximately 2 mil to approximately 6 mil. The co-cured UV / visible light resistant fiberglass-containing layer is configured to define the vehicle fuel tank cavity. A method for including the UV / visible light resistant fiberglass-containing layer within the co-cured composite vehicle fuel tank assembly, thereby eliminating the need for at least one of a UV / visible light absorbing detail primer layer and a UV / visible light absorbing paint layer within the co-cured composite vehicle fuel tank assembly.

[0079] Article 19. The method according to Clause 18, wherein the co-curable composite material substrate comprises a fiber-reinforced epoxy resin matrix, and the fiber-reinforced epoxy resin matrix comprises at least one of carbon fibers, boron fibers, aramid fibers, fiberglass fibers, polyester fibers, and combinations thereof.

[0080] Article 20. The method according to Clause 18, wherein the co-curable composite material substrate includes a carbon fiber reinforced polymer composite material.

[0081] Article 21. The method according to clause 18 (200), further comprising (108) adding a fuel tank primer layer on the co-cured UV / visible light resistant fiberglass-containing layer.

[0082] These embodiments can, of course, be carried out in ways other than those specifically presented herein without departing from the essential features of the disclosure. The embodiments herein should be considered in all respects as illustrative and non-limiting, and all modifications that fall within the meaning and equivalence of the claims are intended to be encompassed within the claims.

Claims

1. A co-curable composite material (20a), A co-curable composite material substrate (22a), A co-curable UV / visible light resistant fiberglass-containing coating layer (24a) comprising a co-curable UV / visible light resistant fiberglass-containing coating layer that is in direct contact with the co-curable composite substrate to form a composite substrate assembly (20b) (20c) coated with the co-curable UV / visible light resistant fiberglass-containing layer, The composite material substrate assembly coated with the co-curable UV / visible light resistant fiberglass-containing layer is configured to form a vehicle fuel tank (13), and the vehicle fuel tank is The inner surface of the vehicle fuel tank (13b) and A vehicle fuel tank cavity (13d) comprising a vehicle fuel tank cavity defined by the inner surface of the vehicle fuel tank which exclusively contains the co-curable UV / visible light resistant fiberglass-containing coating layer, The co-curable UV / visible light resistant fiberglass-containing coating layer has a UV / visible light transmittance value of 0% for UV / visible light wavelengths in the range of approximately 200 nm to approximately 800 nm when the co-curable UV / visible light resistant fiberglass-containing coating layer has an average thickness in the range of approximately 50.8 μm (2 mils) to approximately 152.4 μm (6 mils). A co-curable composite material wherein the co-curable UV / visible light resistant fiberglass-containing coating layer is configured to completely cover the co-curable composite material substrate.

2. The co-curable composite material according to claim 1, wherein the co-curable composite material substrate is co-curable with the co-curable UV / visible light resistant fiberglass-containing coating layer at a temperature in the range of about 121.1°C (about 250°F) to about 187.8°C (about 370°F).

3. The co-curable composite material according to claim 1, wherein the co-curable composite material substrate includes an epoxy resin matrix.

4. The co-curable composite material according to claim 1, wherein the co-curable composite material substrate comprises a fiber-reinforced epoxy resin matrix, and the fiber-reinforced epoxy resin matrix comprises at least one of carbon fibers, boron fibers, aramid fibers, fiberglass fibers, polyester fibers, and combinations thereof.

5. The co-curable composite material according to claim 1, wherein the co-curable composite material substrate includes a carbon fiber reinforced polymer composite material.

6. The co-curable composite material according to claim 1, wherein the co-curable composite material substrate comprises at least one carbon fiber reinforced polymer prepreg.

7. A vehicle fuel tank (13), The vehicle fuel tank assembly includes a co-cured composite material (20b) (20c), the vehicle fuel tank assembly includes a vehicle fuel tank inner surface (13b), and the vehicle fuel tank inner surface is Co-cured composite material substrates (22b) (22c), A co-cured UV / visible light resistant fiberglass-containing layer (24b) (24c) configured to be in direct contact with the co-cured composite material substrate and to completely cover the co-cured composite material substrate, This includes a vehicle fuel tank cavity (13d) defined by the inner surface of the vehicle fuel tank, To form the vehicle fuel tank assembly, the co-cured composite substrate and the co-cured UV / visible light resistant fiberglass-containing layer are co-cured with a co-curing regimen, the co-curing regimen includes a co-curing temperature range of approximately 121.1°C (approximately 250°F) to approximately 187.8°C (approximately 370°F). The co-cured UV / visible light resistant fiberglass-containing layer has a UV / visible light transmittance value of 0% for UV / visible light wavelengths in the range of approximately 200 nm to approximately 800 nm, when the co-cured UV / visible light resistant fiberglass-containing layer has an average thickness in the range of approximately 50.8 μm (2 mils) to approximately 152.4 μm (6 mils), in a vehicle fuel tank.

8. The vehicle fuel tank according to claim 7, wherein the co-cured composite material substrate comprises an epoxy resin matrix.

9. The vehicle fuel tank according to claim 7, wherein the co-cured composite material substrate comprises a fiber-reinforced epoxy resin matrix, and the fiber-reinforced epoxy resin matrix comprises at least one of carbon fibers, boron fibers, aramid fibers, fiberglass fibers, polyester fibers, and combinations thereof.

10. The vehicle fuel tank according to claim 7, wherein the co-cured composite material substrate comprises a carbon fiber reinforced polymer composite material.

11. The vehicle fuel tank according to claim 7, wherein the co-cured composite material substrate comprises at least one carbon fiber reinforced polymer prepreg.

12. The vehicle fuel tank according to claim 7, wherein the co-cured UV / visible light resistant fiberglass-containing layer is configured to form the inner surface of the vehicle fuel tank.

13. The vehicle fuel tank (20c) according to claim 7, further comprising a fuel tank primer layer (26c) disposed to cover the co-cured UV / visible light resistant fiberglass-containing layer, wherein the inner surface of the vehicle fuel tank is defined by the fuel tank primer layer.

14. The vehicle fuel tank according to claim 7, wherein the co-cured UV / visible light resistant fiberglass-containing layer is included in the co-cured vehicle fuel tank assembly, thereby eliminating the need for at least one of the fuel tank primer layer and the UV-absorbing paint layer in the vehicle fuel tank assembly.

15. An aircraft wing assembly (12) including a vehicle fuel tank as described in claim 7.

16. A vehicle (10) including the vehicle fuel tank according to claim 7.

17. The aforementioned vehicle, A vehicle according to claim 16, selected from the group consisting of manned aircraft, unmanned aircraft, manned spacecraft, unmanned spacecraft, manned rotary-wing aircraft, unmanned rotary-wing aircraft, manned ground vehicles, unmanned ground vehicles, manned water vehicles, unmanned water vehicles, manned underwater vehicles, unmanned underwater vehicles, artificial satellites, and combinations thereof.

18. Method (100), (102) To provide a co-curable composite material substrate, wherein the composite material substrate includes a first side surface and a second side surface of the composite material substrate. (104) Adding a co-curable UV / visible light resistant fiberglass-containing layer on a second side surface of the co-curable composite material substrate, wherein the co-curable UV / visible light resistant fiberglass-containing layer added on the second side surface of the co-curable composite material substrate has an average thickness in the range of about 50.8 μm (2 mil) to about 152.4 μm (6 mil), and To form a co-cured composite vehicle fuel tank assembly, the co-curable composite substrate is co-cured with a co-curable UV / visible light resistant fiberglass-containing layer (106), The co-cured composite vehicle fuel tank assembly includes an inner surface of the co-cured composite vehicle fuel tank assembly, the inner surface of the co-cured composite vehicle fuel tank assembly includes a co-cured UV / visible light resistant fiberglass-containing layer, the co-cured UV / visible light resistant fiberglass-containing layer has a UV / visible light transmittance value of 0% for UV / visible light wavelengths in the range of approximately 200 nm to approximately 800 nm when the co-cured UV / visible light resistant fiberglass-containing layer has an average thickness in the range of approximately 50.8 μm (2 mils) to approximately 152.4 μm (6 mils), The co-cured UV / visible light resistant fiberglass-containing layer is configured to define the vehicle fuel tank cavity. A method for including the UV / visible light-resistant fiberglass-containing layer within the co-cured composite vehicle fuel tank assembly, thereby eliminating the need for at least one of a UV / visible light-absorbing detail primer layer and a UV / visible light-absorbing paint layer within the co-cured composite vehicle fuel tank assembly.

19. The method according to claim 18, wherein the co-curable composite material substrate comprises a fiber-reinforced epoxy resin matrix, and the fiber-reinforced epoxy resin matrix comprises at least one of carbon fibers, boron fibers, aramid fibers, fiberglass fibers, polyester fibers, and combinations thereof.

20. The method according to claim 18, wherein the co-curable composite material substrate includes a carbon fiber reinforced polymer composite material.

21. The method according to claim 18 (200), further comprising adding a fuel tank primer layer on the co-cured UV / visible light resistant fiberglass-containing layer (108).

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