Coating system for composite material protection

Abstract

The invention relates to a coating system for composite protection. A coating system for a composite component is presented. The coating system includes: a first layer including a chemical barrier configured to prevent transmission of at least one of ultraviolet light or visible light within a desired wavelength; and a second layer on and in contact with the first layer and configured to reflect an infrared component of daylight. The second layer includes a colorant configured to reflect the infrared component of daylight, where the first layer is positioned between the second layer and the composite component.

Description

TECHNICAL FIELD

[0001] The present disclosure relates generally to coatings, and more particularly to a coating system for a composite material. BACKGROUND

[0002] Fiber-reinforced composites can be used in platforms including buildings or large vehicles such as aircraft, watercraft, automobiles, trains, and other modes of transportation. The operating environment of vehicles including fiber-reinforced composites can cause degradation of the fiber-reinforced composites if the fiber-reinforced composites are exposed to the operating environment.

[0003] Accordingly, it would be desirable to have a method and apparatus that takes into account at least some of the issues discussed above, as well as possibly other issues. In particular, it would be desirable to provide a coating system for protecting fiber-reinforced composites from operating conditions. SUMMARY

[0004] One embodiment of the present disclosure provides a coating system for a composite part. The coating system includes a first layer and a second layer on and in contact with the first layer. The first layer includes a chemical barrier configured to prevent transmission of at least one of ultraviolet light or visible light within a desired wavelength. The second layer is configured to reflect an infrared component of sunlight. The second layer includes a colorant configured to reflect the infrared component of sunlight, wherein the first layer is positioned between the second layer and the composite part.

[0005] Another embodiment of the present disclosure provides an aircraft. The aircraft includes a composite part and a coating system on the composite part. The coating system includes a first layer including a chemical barrier configured to prevent transmission of at least one of ultraviolet light or visible light within a desired wavelength and a second layer configured to reflect an infrared component of sunlight. The second layer includes a colorant configured to reflect the infrared component of sunlight, wherein the first layer is positioned between the second layer and the composite part.

[0006] Another embodiment of the present disclosure provides a coating system for a composite part. The coating system includes a first layer configured to prevent transmission of at least one of ultraviolet light or visible light within a desired wavelength and including a chemical barrier including at least one of a benzotriazole, a triazine, or a benzophenone and a second layer configured to provide a desired degree of solar absorption and including between 16 wt% and 41 wt% titanium dioxide. The second layer is in contact with the first layer, wherein the first layer is positioned between the second layer and the composite part.

[0007] These features and functionalities can be implemented independently of one another or in various combinations thereof in various embodiments of the present disclosure, as will be apparent upon reference to the following descriptions and attached drawings. BRIEF DESCRIPTION OF DRAWINGS

[0008] The features of the example embodiments that are believed to be novel are set forth with particularity in the appended claims. The example embodiments, however, together with its preferred methods of use, further objects and advantages thereof, will be best understood by reference to the following detailed description of the example embodiments of the present disclosure, taken in conjunction with the accompanying drawings, where:

[0009] Figure 1 is an example of an aircraft in accordance with an example embodiment;

[0010] Figure 2 is an example of a block diagram of a platform with a coating system in an operating environment in accordance with an example embodiment;

[0011] Figure 3 is an example of a cross-sectional view of a coating system on a composite material in accordance with an example embodiment;

[0012] Figure 4 is an example of a method of aircraft manufacturing and service at a block diagram in accordance with an example embodiment; and

[0013] Figure 5 is an example of an aircraft in block diagram form in which example embodiments can be implemented. DETAILED DESCRIPTION

[0014] The example embodiments recognize and take into account that a part made of fiber reinforced composite material can easily degrade when exposed to a combination of electromagnetic radiation, moisture, and heat. The example embodiments recognize and take into account that it can be desirable to protect the fiber reinforced composite material from the components of sunlight.

[0015] The example embodiments recognize and take into account that it can be desirable to protect the fiber reinforced composite material without causing undesirable effects on other material properties or operating standards of the corresponding platform. The example embodiments recognize and take into account that an aircraft has several operating standards set by regulatory agencies. In addition, the example embodiments also recognize and take into account that it can be undesirable to increase the weight of the aircraft. The example embodiments recognize and take into account that significantly increasing the thickness of the coating can increase the risk of cracking, will increase the weight, and can not satisfy the electromagnetic effects (EME) standards of the aircraft.

[0016] Coatings are described herein that have the ability to block the penetration of ultraviolet-visible light at the surface (interior) of a composite material while meeting the requirements of visible color and degree of solar absorption (exterior) without an over-thick paint layer, thereby avoiding problems such as cracking, weight, EME, etc.

[0017] Turning now to Figure 1 , an example of an aircraft is depicted in accordance with an example embodiment. The aircraft 100 has a wing 102 and a wing 104 that are attached to a body 106. The aircraft 100 includes an engine 108 attached to the wing 102 and an engine 110 attached to the wing 104.

[0018] The body 106 has a tail section 112. A horizontal stabilizer 114, a horizontal stabilizer 116, and a vertical stabilizer 118 are attached to the tail section 112 of the body 106.

[0019] The aircraft 100 is one example of an aircraft that can have a coating configured to protect a composite material from ultraviolet or visible light degradation. The coating of the example example can be present on at least one of the wing 102, the wing 104, the body 106, or the tail section 112.

[0020] Turning now to Figure 2 , an example of a block diagram of an operating environment is depicted in accordance with an example embodiment. A platform 202 is present in the operating environment 200 and is exposed to sunlight 216. The platform 202 can take any desired form.

[0021] A coating system 210 provides protection for a composite material component 206 of the platform 202. The coating system 210 protects the composite material component 206 from the sunlight 216. The coating system 210 includes a first layer 212 that includes a chemical barrier 224 configured to prevent transmission of at least one of ultraviolet light 217 or visible light 218 within a desired wavelength 234 and a second layer 214 that is in contact with the first layer 212 and is configured to reflect an infrared component 220 of the sunlight 216. The first layer 212 can be applied on the composite material component 206 as one of a coating, a film, or an ink (layer).

[0022] The second layer 214 is exposed to the operating environment 200. Thus, the sunlight 216 impinges on the second layer 214. The second layer 214 is positioned on top of and covers the first layer 212.

[0023] The second layer 214 includes a colorant 239 configured to reflect the infrared component 220 of the sunlight 216. The colorant 239 includes any desired colorant configured to reflect the infrared component 220 of the sunlight 216. In some example instances, the colorant 239 includes titanium dioxide 240. The colorant 239 can be present in any desired polymeric material in the second layer 214. In some example instances, the second layer 214 includes at least one of an epoxy, an acrylic, a polyurethane 238, a polyamide, a modified rosin, a hydrocarbon resin, or a modified cellulose. In some example instances, the second layer 214 includes a polyurethane 238. The first layer 212 is positioned between the second layer 214 and the composite part 206. The second layer 214 can be applied to the composite part 206 as one of a coating, a film, or an ink (layer).

[0024] A coating can be, for example, a thin layer or covering, which can be, for example, a liquid, a fluid, a continuum, or can be a material that is free-flowing and has a constant volume. Examples of coatings described herein include paints, primers, topcoats, and the like, and combinations thereof.

[0025] A film can be, for example, a thin material covering in a solid or semi-solid state, and in some embodiments can be flexible. Examples of films described herein include decals, stickers, wraps, and the like.

[0026] An ink is a colored liquid or fluid used for writing, drawing, printing, and the like. Examples include solid, liquid, hybrid, and similar inks, and combinations thereof. The composite part 206 includes a fiber-reinforced matrix material. In some example instances, the fiber-reinforced material includes at least one of carbon fibers, boron fibers, glass fibers, polyester fibers, aramid fibers (such as, for example ), polymeric fibers, or other desired reinforcing fibers. In some example instances, the composite part 206 includes at least one of a polyester, a vinyl ester, a cyanate ester, a bismaleimide, a polyetherimide, a polyphenylene sulfide, a polyaryletherketone (including PEEK and PEKK), a thermoset material (such as an epoxy material), or a nylon. In some example instances, the epoxy composite includes at least one of a phenol novolac epoxy, an aromatic epoxy, an aliphatic epoxy, or a cyclic epoxy. In some example instances, the composite part 206 includes a thermoset resin.

[0027] Currently, epoxy systems can incorporate multifunctional epoxy systems with difunctional epoxy systems to obtain a polymer matrix with both improved tensile strength and compression-after-impact (CAI) after impact. The difunctional epoxy resin can be saturated, unsaturated, cycloaliphatic, aromatic, alicyclic, or heterocyclic. Examples of difunctional epoxy resins can be those based on diglycidyl ether or bisphenol F, bisphenol A, phenol and cresol epoxy novolacs, glycidyl ethers of phenol-aldehyde adducts, glycidyl ethers of aliphatic diols, diglycidyl ethers, diethylene glycol diglycidyl ether, aromatic epoxy resins, aliphatic polyglycidyl ethers, epoxidized olefins, aromatic glycidyl amines, heterocyclic glycidyl imines and amides, glycidyl ethers, or any combination thereof. Preferred difunctional epoxy resins can be from diglycidyl ether of bisphenol F, diglycidyl ether of bisphenol A, diglycidyl dihydroxynaphthalene, or any combination thereof.

[0028] In some example embodiments, the composite part 206 includes one of a thermoset resin, an epoxy resin, or a thermoplastic resin. In some example embodiments, the composite part 206 includes a carbon fiber reinforced composite 254. In some example embodiments, the composite part 206 includes a glass fiber reinforced composite 252.

[0029] The composite part 206 can be formed using any desired method. In some example embodiments, the composite part 206 can be formed by resin infusion, wet layup, or resin sweep.

[0030] The surface 208 is an outer surface of the composite part 206. In some example embodiments, the first layer 212 is in contact with the surface 208 of the composite part 206. In some example embodiments, a surface film or primer layer is present between the surface 208 and the first layer 212.

[0031] In some example instances, the second layer 214 is an outer surface of the platform 202. In some example instances, the second layer 214 has a desired exterior color 242 of performance. In some example instances, the second layer 214 is white 244 or gray 246. In some example instances, the second layer 214 provides thermal control 236 to the coating system 210 through a controlled solar absorptance 248. The solar absorptance 248 can be evaluated using any desired standard put forth by a materials or governing association, such as the American Society for Testing and Materials. In some example instances, the solar absorptance 248 can be evaluated using ASTM E903-20.

[0032] In some example instances, the second layer 214 provides a solar absorptance 248 in the range of 0.20-0.67. In some example instances, the second layer 214 provides a solar absorptance 248 in the range of 0.20 to 0.67, or 0.23 to 0.67, or 0.23 to 0.53. In some example instances, the second layer 214 provides a solar absorptance 248 in the range of 0.21-0.23. In some example instances, the second layer 214 provides a solar absorptance 248 in the range of 0.58-0.67.

[0033] The first layer 212 includes a chemical barrier 224. In some example instances, the first layer 212 further includes at least one of a polyurethane 222 or an epoxy 223 and the chemical barrier 224. In some example instances, the chemical barrier 224 is present in the first layer 212 with at least one of an epoxy 223, an acrylic, a polyurethane 222, a polyamide, a modified rosin, a hydrocarbon resin, or a modified cellulose. In some example instances, the chemical barrier 224 includes at least one of a benzotriazole, a triazine, or a benzophenone. In some example instances, the chemical barrier 224 is configured in content and specific type to block transmission of at least one of ultraviolet light 217 or visible light 218 within a desired wavelength 234. The chemical barrier 224 is present in the first layer 212 in any desired range of weight to prevent transmission of at least one of ultraviolet light 217 or visible light 218. The weight percentages demonstrated herein are calculated as a percentage of dry weight.

[0034] In some example instances, the first layer 212 blocks transmission of at least one of ultraviolet light 217 or visible light 218 through absorption. In some example instances, the desired wavelength 234 is in the range of 300-550 nm. In some example instances, the desired wavelength 234 is in the range of 300-500 nm. In some example instances, the desired wavelength 234 is in the range of 300-800 nm.

[0035] In some example embodiments, the first layer 212 includes a colorant 225. In some example embodiments, the first layer 212 further includes a colorant 225 having a light color. In some example embodiments, the second layer 214 has a lighter color than the first layer, such as white, and has a property of low solar absorption. In some example embodiments, the second layer 214 includes a white colorant in a range of 16wt% - 41wt% of titanium dioxide 240 (also known as titania or TiO2) in rutile or anatase form, antimony white, zinc white, silica, or the like. In some example embodiments, the second layer 214 includes titanium dioxide 240 in a range of 20wt% - 41wt%. In some example embodiments, the second layer 214 includes titanium dioxide 240 in a range of 16wt% - 21wt%.

[0036] In some example embodiments, the coating system 210 for the composite part 206 includes a first layer 212 configured to prevent transmission of at least one of ultraviolet light 217 or visible light 218 within a desired wavelength 234 and including a chemical barrier 224 including at least one of a benzotriazole 226, a triazine 228, or a benzophenone 230, and a second layer 214 configured to provide a desired solar absorption 248 and including 16wt% - 41wt% of titanium dioxide 240, the second layer in contact with the first layer, wherein the first layer is positioned between the second layer and the composite part.

[0037] The thickness 232 of the first layer 212 is selected to provide a desired amount of barrier to at least one of ultraviolet light 217 or visible light 218. The thickness 232 of the first layer 212 is selected to provide a desired material property for the coating system 210. In some example embodiments, the thickness 232 is selected based on at least one of a desired weight, a desired EME performance, and a desired flexibility performance of the coating system 210.

[0038] The thickness can be measured using any desired standard set forth by a materials or management association, such as the American Society for Testing and Materials. In some example embodiments, the thickness 232 and the thickness 250 can be evaluated using ASTM D4138-22.

[0039] In some example instances, the first layer 212 includes a thickness 232 between 0.3-2.4 mils. In some example instances, the first layer 212 includes a thickness 232 between 0.3-0.8 mils. In some example instances, the first layer 212 includes a thickness 232 between 0.6-1.6 mils. In some example instances, the first layer 212 includes a thickness 232 between 1.4-2.4 mils. In some example instances, the first layer 212 includes a thickness 232 between 1.0-2.0 mils.

[0040] In some example instances, the thickness 232 is selected based on a location of the coating system 210 on the platform 202. In some example instances, the thickness 232 can be selected according to the operating environment 200.

[0041] The thickness 250 of the second layer 214 and the particular colorant 239 are selected to provide reflection of the infrared component 220 of the sunlight 216. The thickness 250 of the second layer 214 is selected to provide desired material properties for the coating system 210. In some example instances, the thickness 250 is selected based on at least one of a desired weight, a desired EME performance, and a desired flexibility performance of the coating system 210.

[0042] In some example instances, the second layer 214 includes a thickness 250 between 2.0-4.0 mils. In some example instances, the second layer 214 includes a thickness 250 between 2.4-4.0 mils. In some example instances, the second layer 214 includes a thickness 250 between 2.4-3.2 mils. In some example instances, the second layer 214 includes a thickness 250 between 2.0-3.6 mils.

[0043] In some example instances, the platform 202 takes the form of an aircraft 204. In these example instances, the aircraft 204 includes a composite material component 206 and a coating system 210 on the composite material component 206. The coating system 210 includes a first layer 212 including a chemical barrier 224 configured to prevent transmission of at least one of ultraviolet light 217 or visible light 218 within a desired wavelength 234 and a second layer 214 configured to reflect an infrared component 220 of the sunlight 216. The second layer 214 includes a colorant 239 configured to reflect the infrared component 220 of the sunlight 216. The first layer 212 is positioned between the second layer 214 and the composite material component 206.

[0044] The composite part 206 can take the form of any desired part or portion of a part of the platform 202. In some example instances, the composite part 206 is a portion of the tail section 256 of the aircraft 204. In some example instances, the composite part 206 is a horizontal stabilizer 260. In some example instances, the horizontal stabilizer 260 can take the form of the horizontal stabilizer 116 of Figure 1

[0045] In some example instances, an outer transparent coating 215 is present in the coating system 210. The outer transparent coating 215 is in contact with the second layer 214. The outer transparent coating 215 is an optional layer, which is not present in some example instances. The outer transparent coating 215 can provide additional protection to the second layer 214 and the first layer 212 from undesirable abrasion.

[0046] Figure 2 The coating system 210 can be applied by at least one of spray coating, inkjet printing, spreading, rolling, or any other desired application method. The first layer 212 and the second layer 214 can be applied to the composite part 206 in liquid form. In some example instances, the first layer 212 can be applied and cured prior to the application of the second layer 214. In some example instances, the first layer 212 can be co-cured with the composite part 206.

[0047] Figure 2 The example of the operating environment 200 in FIG. 2 is not intended to suggest physical or architectural limitations to the manner in which example embodiments can be implemented. Additional or fewer elements can be used. Some elements can be unnecessary. Also, the division of functionality between elements can vary. For example, a surface film or primer can be present between the surface 208 and the first layer 212.

[0048] Turning now to Figure 3 FIG. 3 depicts an example of a cross-sectional view of a coating system on a composite material, in accordance with example embodiments. The composite part 302 is Figure 2 ​a physical implementation of the composite part 206. The coating system 304 is present on the composite part 302. The coating system 304 protects the composite part 302 from degradation due to sunlight exposure. The coating system 304 is Figure 2 a physical implementation of the coating system 210. The view 300 is a cross-sectional view of the coating system 304 on the composite part 302.

[0049] The coating system 304 includes a first layer 306 and a second layer 308. In this example instance, the first layer 306 is in contact with the composite part 302. In some unillustrated instances, a surface film or a primer coating can be present between the composite part 302 and the first layer 306.

[0050] The first layer 306 protects the composite part 302 from at least one of ultraviolet light or visible light within a desired wavelength. The first layer 306 includes a chemical barrier. The chemical barrier is configured to prevent transmission of at least one of ultraviolet light or visible light within a desired wavelength. In some example instances, the chemical barrier includes at least one of a benzotriazole, a triazine, or a benzophenone.

[0051] The first layer 306 prevents or significantly reduces transmission of at least one of ultraviolet light or visible light within a desired wavelength. The first layer 306 achieves at least one of absorbing or reflecting at least one of ultraviolet light or visible light within a desired wavelength. The first layer 306 provides a desired barrier property to the desired wavelength. In some example instances, the first layer 306 provides protection to the composite part 302 by absorption.

[0052] The second layer 308 is in contact with the first layer 306. The second layer 308 provides thermal protection to the composite part 302 while the first layer 306 provides protection against at least one of ultraviolet light or visible light. In some example instances, the second layer 308 provides protection against the infrared component of sunlight with solar energy absorption.

[0053] In some example instances, the first layer 306 is darker in color than the second layer 308. In some example instances, the second layer 308 is white. In some other example instances, the second layer 308 is gray. In some example instances, the second layer 308 has a desired external color of performance that can be selected from white, gray, beige, off-white, or any other desired color.

[0054] The composite part 302 with the coating system 304 resists degradation from cyclic exposure to at least one of ultraviolet light or visible light and moisture. The composite part 302 with the coating system 304 meets desired criteria for solar absorptance, color, and crack resistance. The first layer 306 and the second layer 308 are arranged in a particular order and have thicknesses 310 and 312 configured to achieve at least one of selectively absorbing or reflecting certain wavelengths of solar radiation while meeting other desired coating properties. In some example instances, the coating system 304 meets desired criteria for corrosion resistance.

[0055] In this example instance, an outer transparent coating 314 is present in the coating system 304. The outer transparent coating 314 is in contact with the second layer 308. The outer transparent coating 314 is optional in some example instances. The outer transparent coating 314 can provide additional protection to the second layer 308 and the first layer 306 from undesirable abrasion.

[0056] As used herein, the phrase "at least one of," when used with a list of items, means that one or more of the items can be used, and that the list of items can include at least one of each of the items. For example, "at least one of item A, item B, or item C" can include, but is not limited to, only item A, only item A and item B, or only item B. This example also can include only item A, only item B, and item C, or only item B and item C. Of course, any combination of these items can be included in the example. In other examples, "at least one of" can be, for example, but not limited to, two item A's; one item B; and ten item C's; four item B's and seven item C's; or other suitable combinations. The item can be a specific object, thing, or category. In other words, at least one of means that any combination of the items in the list and the number of items can be used, not requiring all of the items in the list.

[0057] As used herein, "a number of," when used with respect to items, means one or more items.

[0058] The flow and block diagrams in the various drawing implementations illustrate schematically the architecture, functionality, and operations of some possible implementations of apparatus and methods in example implementations. In this regard, each block in the flow or block diagrams can represent at least one of a module, segment, function, or portion of an operation or step.

[0059] In some alternative embodiments of the exemplary implementation, one or more functions marked in the boxes may occur in a different order than those marked in the figures. For example, in some cases, two boxes shown consecutively may be executed substantially simultaneously, or these boxes may sometimes be executed in reverse order—depending on the functionality involved. Furthermore, additional boxes may be added besides the example boxes in the flowchart or block diagram. Some boxes may be optional.

[0060] Exemplary embodiments of this disclosure may be implemented in Figure 4 The aircraft manufacturing and service method 400 shown Figure 5 The environment description of the aircraft 500 shown. First, go to... Figure 4 This illustrates an example of an aircraft manufacturing and servicing method in block diagram form according to an exemplary embodiment. During pre-production, the aircraft manufacturing and servicing method 400 may include... Figure 5 The formulation and design of the 500-class aircraft 402 and the procurement of materials 404.

[0061] During production, the manufacturing of components and sub-components of the aircraft 500 is carried out 406, and system integration is performed 408. Afterward, the aircraft 500 can be certified and delivered 410 for service 412. When service 412 is provided to the customer, the aircraft 500 is scheduled for routine maintenance and servicing 414, which may include modifications, reconfigurations, refurbishments, or other maintenance and servicing.

[0062] The processes of the aircraft manufacturing and servicing method 400 may be performed or implemented by a system integrator, a third party, and / or an operator. In these instances, the operator may be the customer. For illustrative purposes, the system integrator may include, but is not limited to, any number of aircraft manufacturers and main system subcontractors; the third party may include, but is not limited to, any number of sellers, subcontractors, and suppliers; and the operator may be an airline, leasing company, military entity, service organization, etc.

[0063] For reference Figure 5 This illustrates an example of an aircraft in block diagram form, where exemplary implementations can be carried out. In this example, aircraft 500... Figure 4 The aircraft manufacturing and servicing method 400 produces and may include a fuselage 502 having multiple systems 504 and an interior 506. Examples of systems 504 include one or more of a propulsion system 508, an electrical system 510, a hydraulic system 512, and an environmental system 514. Any number of other systems may be included.

[0064] The equipment and methods implemented herein may be employed during at least one stage of the aircraft manufacturing and servicing method 400. One or more exemplary embodiments may be available. Figure 4manufactured or used during at least one of component and subassembly manufacturing 406, system integration 408, service 412, or maintenance and service 414.

[0065] These example embodiments demonstrate a coating system that protects a composite part. The coating system protects the composite part from degradation caused by cyclic exposure to at least one of ultraviolet light or visible light and moisture while meeting standards for solar absorptance, color, and crack resistance. The layers are arranged within the coating system in a particular order and with particular thicknesses to selectively absorb and / or reflect particular wavelengths of solar radiation while meeting other purpose standards.

[0066] The description of the different example embodiments is presented for purposes of illustration and description and is not intended to be exhaustive or limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. Moreover, different example embodiments can provide different features to those of other embodiments. One or more embodiments were chosen and described in order to best explain the principles of the disclosure and the practical application, and to enable others skilled in the art to best exploit the embodiments with various modifications as are suited to the particular application contemplated. Example recitations 1. A coating system (210, 304) for a composite part (206, 302), comprising: a first layer (212, 306), the first layer (212, 306) including a chemical barrier (224) configured to prevent transmission of at least one of ultraviolet light (217) or visible light (218) within a desired wavelength (234); and a second layer (214, 308) on and in contact with the first layer (212, 306) and configured to reflect an infrared component (220) of sunlight (216), the second layer (214, 308) including a colorant (239) configured to reflect the infrared component (220) of sunlight (216), wherein the first layer (212, 306) is positioned between the second layer (214, 308) and the composite part (206, 302). 2. The coating system (210, 304) of Example 1, wherein the colorant (239) includes titanium dioxide (240), and wherein the second layer (214, 308) further includes a polyurethane (238). 3. The coating system (210, 304) of Example 1, wherein the second layer (214, 308) has a desired exterior color (242) of performance. 4. The coating system (210, 304) of Example 1, wherein the second layer (214, 308) is white (244) or gray (246). 5. The coating system (210, 304) of Example 1, wherein the first layer (212, 306) includes polyurethane (222) or epoxy (223), and wherein the chemical barrier (224) includes at least one of benzotriazole (226), triazine (228), or benzophenone (230). 6. The coating system (210, 304) of Example 1, wherein the first layer (212, 306) further includes a colorant (225) having a light color. 7. The coating system (210, 304) of Example 1, wherein the first layer (212, 306) includes a thickness (232, 310) between 0.3-2.4 mils. 8. The coating system (210, 304) of Example 1, wherein the second layer (214, 308) includes a thickness (250, 312) between 2.0-4.0 mils. 9. The coating system (210, 304) of Example 1, wherein the first layer (212, 306) blocks transmission of at least one of ultraviolet light (217) or visible light (218) by absorption. 10. The coating system (210, 304) of Example 1, wherein the second layer (214, 308) provides thermal control (236) for the coating system (210, 304) by controlled solar absorption (248). 11. The coating system (210, 304) of Example 1, wherein the second layer (214, 308) provides a solar absorption (248) in a range of 0.20-0.67. 12. The coating system (210, 304) of Example 1, wherein the desired wavelength (234) is in a range of 300-550 nm. 13. The coating system (210, 304) of Example 1, further comprising: an outer clear coat (215, 314) in contact with the second layer (214, 308). 14. An aircraft (100, 204, 500) comprising: a composite component (206, 302); and A coating system (210, 304) on the composite material components (206, 302), the coating system (210, 304) comprising: The first layer (212, 306) includes a chemical barrier (224) configured to prevent ultraviolet light (217) or visible light (218) within a desired wavelength (234). Transmission of at least one of them, and The second layer (214, 308) is configured to reflect the infrared component (220) of sunlight (216), and the second layer (214, 308) includes a colorant (239) configured to reflect the infrared component (220) of sunlight (216), wherein the first layer (212, 306) is positioned between the second layer (214, 308) and the composite material component (206, 302). 15. The aircraft (100, 204, 500) according to Example 14, wherein the composite material component (206, 302) comprises carbon fiber reinforced composite material (252). 16. The aircraft (100, 204, 500) according to Example 14, wherein the composite material component (206, 302) comprises a glass fiber reinforced composite material (254). 17. The aircraft (100, 204, 500) according to Example 14, wherein the composite material component (206, 302) is a wing (102, 104, 262). 18. The aircraft (100, 204, 500) according to Example 14, wherein the composite material component (206, 302) is part of the tail section (112, 256) of the aircraft (100, 204, 500). 19. The aircraft (100, 204, 500) according to Example 14, wherein the composite material component (206, 302) is the fuselage (264). 20. The aircraft (100, 204, 500) according to Example 14, wherein the composite material component (206, 302) is one of the following: a part of the fuselage (264), wing (102, 104, 262), or tail section (112, 256) of the aircraft (100, 204, 500). 21. The coating system (210, 304) according to Example 14, wherein the first layer (212, 306) comprises a thickness (232, 310) between 0.3 and 2.4 mils. 22. The coating system (210, 304) of Example 14, wherein the second layer (214, 308) comprises a thickness (250, 312) between 2.0-4.0 mils. 23. The aircraft (100, 204, 500) of Example 14, wherein the chemical barrier (224) comprises at least one of a benzotriazole (226), a triazine (228), or a benzophenone (230). 24. The aircraft (100, 204, 500) of Example 14, wherein the second layer (214, 308) comprises titanium dioxide (240) in a range of 16wt%-41wt%. 25. The aircraft (100, 204, 500) of Example 14, wherein the desired wavelength (234) is in a range of 300-550nm. 26. The aircraft (100, 204, 500) of Example 14, wherein the desired wavelength (234) is in a range of 300-800nm. 27. The aircraft (100, 204, 500) of Example 14, wherein the composite part (206, 302) comprises one of a thermoset resin, an epoxy resin, or a thermoplastic resin. 28. The aircraft (100, 204, 500) of Example 26, wherein the composite part (206, 302) comprises an epoxy resin. 29. The aircraft (100, 204, 500) of Example 14, wherein the composite part (206, 302) comprises at least one of a carbon fiber, a boron fiber, a glass fiber, a polyester fiber, an aramid fiber, or a polymeric fiber. 30. The aircraft (100, 204, 500) of Example 14, wherein the first layer (212, 306) comprises at least one of an epoxy resin, an acrylic, a polyurethane (238), a polyamide, a modified rosin, a hydrocarbon resin, or a modified cellulose. 31. The aircraft (100, 204, 500) of Example 14, further comprising: an outer clearcoat (215, 314) in contact with the second layer (214, 308). 32. A coating system (210, 304) for a composite part (206, 302), comprising: a first layer (212, 306) configured to prevent transmission of at least one of ultraviolet light (217) or visible light (218) within a desired wavelength (234) and including a chemical barrier (224) including at least one of a benzotriazole (226), a triazine (228), or a benzophenone (230); and a second layer (214, 308) configured to provide a desired degree of solar absorption (248) and including between 16 wt% - 41 wt% titanium dioxide (240), the second layer (214, 308) in contact with the first layer (212, 306), wherein the first layer (212, 306) is positioned between the second layer (214, 308) and the composite component (206, 302). 33. The coating system (210, 304) according to Example 32, wherein the desired wavelength (234) is in the range of 300 - 550 nm. 34. The coating system (210, 304) according to Example 32, wherein the desired wavelength (234) is in the range of 300 - 800 nm. 35. The coating system (210, 304) according to Example 32, wherein the first layer (212, 306) includes a thickness (232, 310) of between 0.3 - 2.4 mils. 36. The coating system (210, 304) according to Example 32, wherein the second layer (214, 308) includes a thickness (250, 312) of between 2.0 - 4.0 mils. 37. The coating system (210, 304) according to Example 32, further comprising: an outer clear coat (215, 314) in contact with the second layer (214, 308).

Claims

1. A coating system (210, 304) for a composite part (206, 302), comprising: a first layer (212, 306), the first layer (212, 306) including a chemical barrier (224) configured to prevent transmission of at least one of ultraviolet light (217) or visible light (218) within a desired wavelength (234); and a second layer (214, 308), the second layer (214, 308) being on and in contact with the first layer (212, 306) and configured to reflect an infrared component (220) of daylight (216), the second layer (214, 308) including a colorant (239) configured to reflect the infrared component (220) of daylight (216), wherein the first layer (212, 306) is positioned between the second layer (214, 308) and the composite part (206, 302).

2. The coating system (210, 304) of claim 1, wherein the colorant (239) includes titanium dioxide (240), and wherein the second layer (214, 308) further includes polyurethane (238).

3. The coating system (210, 304) of claim 1, wherein the second layer (214, 308) has a desired external color (242) of performance.

4. The coating system (210, 304) of claim 1, wherein the second layer (214, 308) is white (244) or gray (246).

5. The coating system (210, 304) of claim 1, wherein the first layer (212, 306) includes polyurethane (222) or epoxy (223), and wherein the chemical barrier (224) includes at least one of benzotriazole (226), triazine (228), or benzophenone (230).

6. The coating system (210, 304) of claim 1, wherein the first layer (212, 306) further includes a colorant (225) having a light color.

7. The coating system (210, 304) of claim 1, wherein the first layer (212, 306) includes a thickness (232, 310) between 0.3-2.4 mils.

8. The coating system (210, 304) of claim 1, wherein the second layer (214, 308) includes a thickness (250, 312) between 2.0-4.0 mils.

9. The coating system (210, 304) of claim 1, wherein the first layer (212, 306) blocks transmission of at least one of ultraviolet light (217) or visible light (218) by absorption.

10. The coating system (210, 304) of claim 1, wherein the second layer (214, 308) provides thermal control (236) for the coating system (210, 304) through controlled solar absorption (248).

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