Coating system for composite material protection

Abstract

The invention relates to a coating system for composite protection. A coating system for a composite part is presented herein. The coating system includes a first layer including a metal additive; and a second layer on and in contact with the first layer, and configured to reflect an infrared component of the sunlight. The first layer is configured to block transmission of at least one of ultraviolet light or visible light within a desired wavelength. The second layer includes polyurethane and titanium dioxide, wherein the first layer is located between the second layer and the composite component.

Description

TECHNICAL FIELD

[0001] The present disclosure relates generally to coatings, and more particularly to a two-layer coating of a composite material. BACKGROUND

[0002] Fiber reinforced composites can be used in platforms, including buildings or large vehicles, such as airplanes, ships, cars, trains, and other forms of transportation. If the fiber reinforced composites are exposed to operating environments, including operating environments of vehicles that include fiber reinforced composites, the operating environments can cause degradation of the fiber reinforced composites.

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

[0004] An embodiment of the present disclosure provides a coating system for a composite part. The coating system includes a first layer including a metallic additive; and a second layer on and in contact with the first layer and configured to reflect an infrared component of sunlight. The first layer is configured to block transmission of at least one of ultraviolet light or visible light within a desired wavelength. The second layer includes a colorant configured to reflect the infrared component of sunlight, wherein the first layer is 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 configured to block 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 including a colorant configured to reflect the infrared component of sunlight. The first layer includes a metallic additive. The first layer is 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 block transmission of at least one of ultraviolet light or visible light within a desired wavelength and including a metallic additive including at least one of aluminum, copper, silver, gold, nickel, or stainless steel; and a second layer configured to provide a desired solar absorptance and including between 16 wt% - 41 wt% of a colorant configured to reflect an infrared component of sunlight. The second layer is in contact with the first layer, wherein the first layer is between the second layer and the composite part.

[0007] The features and functionalities can be implemented independently in various embodiments of the present disclosure or can be combined in still other embodiments, in which further details can be seen with reference to the following description and drawings. BRIEF DESCRIPTION OF DRAWINGS

[0008] The novel features described herein are set forth with particularity in the claims that follow. These descriptive examples, together with the drawings, are meant to provide further description of the illustrative embodiments and are not meant to limit the scope of the illustrative embodiments or the patent rights therein.

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

[0010] Figure 2 is an illustration of a block diagram of a platform with a dual-layer coating in an operating environment in accordance with an illustrative embodiment;

[0011] Figure 3 is an illustration of a cross-sectional view of a dual-layer coating on a composite material in accordance with an illustrative embodiment;

[0012] Figure 4 is an illustration of an aircraft manufacturing and service method in the form of a block diagram in accordance with an illustrative embodiment; and

[0013] Figure 5 is an illustration of an aircraft in the form of a block diagram in illustrative embodiments that can be implemented. DETAILED DESCRIPTION

[0014] The illustrative examples recognize and take into account several considerations. The illustrative embodiments recognize and take into account that components made of fiber-reinforced composites can degrade easily when exposed to a combination of electromagnetic radiation, moisture, and heat. The illustrative embodiments recognize and take into account that it is desirable to protect the fiber-reinforced composites from the components of sunlight.

[0015] The illustrative embodiments recognize and take into account that it is desirable to protect the fiber-reinforced composites without causing unwanted effects on other material properties or operating standards of the respective platforms. The illustrative examples recognize and take into account that aircraft have multiple operating standards set by regulatory agencies. Further, the illustrative examples recognize and take into account that it is undesirable to increase the weight of the aircraft. The illustrative embodiments recognize and take into account that substantially increasing the thickness of the coating increases the risk of cracking, increases the weight, and can not comply with electromagnetic effects (EME) standards for the aircraft.

[0016] The coatings described herein have the ability to block UV-visible light penetration at the composite surface (internal) while meeting the requirements for visible color and solar absorptance (external) without requiring overly thick coating layers, thereby avoiding issues such as cracking, weight, EME, etc.

[0017] Turning now to Figure 1 a diagram of an aircraft is depicted in accordance with the illustrative implementations. The aircraft 100 has a wing 102 and a wing 104 attached to a fuselage 106. The aircraft 100 includes an engine 108 attached to the wing 102 and an engine 110 attached to the wing 104.

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

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

[0020] Turning now to Figure 2 a diagram of a block diagram of an operating environment is depicted in accordance with the illustrative implementations. 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 component 206 of the platform 202. The coating system 210 protects the composite component 206 from the sunlight 216. The coating system 210 includes a first layer 212 that includes a metallic additive 224 and is configured to block 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 to the composite component 206 as one of a coating, a film, or an ink.

[0022] A coating can be, for example, a thin layer or covering that can be, for example, a liquid, a fluid, a continuous or free-flowing, and a volumetrically constant material. Examples of coatings of the present specification include paints, primers, topcoats, and the like, and combinations thereof.

[0023] A film can be, for example, a thin covering of material that can be in a solid or semi-solid state, and in some implementations can be flexible. Examples of films of the present specification include decals, stickers, wraps, and the like.

[0024] Ink is a colored liquid or fluid used for writing, drawing, printing, etc. Examples include solids, liquids, mixtures, and ink analogues and combinations thereof.

[0025] The second layer 214 is exposed to the operating environment 200. Therefore, sunlight 216 shines on the second layer 214. The second layer 214 is located above and covers the first layer 212.

[0026] The second layer 214 includes a colorant 239 configured to reflect infrared component 220 of sunlight 216. The colorant 239 includes any desired colorant configured to reflect infrared component 220 of sunlight 216. In some illustrative examples, the colorant 239 includes titanium dioxide 240. The colorant 239 may be present in any desired polymeric material in the second layer 214. In some illustrative examples, the second layer 214 includes at least one of epoxy resin, acrylic resin, polyurethane 238, polyamide, modified rosin, hydrocarbon resin, or modified cellulose. In some illustrative examples, the second layer 214 includes polyurethane 238. In some illustrative examples, the second layer 214 includes polyurethane 238 having titanium dioxide 240. A first layer 212 is located between the second layer 214 and the composite component 206. The second layer 214 may be applied to the composite component 206 as a coating, film, or ink.

[0027] Composite component 206 includes a fiber-reinforced matrix material. In some illustrative examples, the fiber reinforcement material includes carbon fiber, boron fiber, glass fiber, polyester fiber, aramid fiber (e.g., for example, ...). The composite component 206 comprises at least one of polyester, vinyl ester, cyanate ester, bismaleimide, polyetherimide, polyphenylene sulfide, polyaryl ether ketone (including PEEK and PEKK), thermosetting material (such as epoxy resin material), or nylon. In some illustrative examples, the epoxy composite comprises at least one of phenolic epoxy resin, aromatic epoxy resin, aliphatic epoxy resin, or cyclic epoxy resin. In some illustrative examples, the composite component 206 comprises a thermosetting resin.

[0028] Currently, epoxy systems can combine a multifunctional epoxy system with a difunctional epoxy system to achieve a polymer matrix with improved tensile strength and compression after impact (CAI). The difunctional epoxy resin can be saturated, unsaturated, cycloaliphatic, aromatic, alicyclic, or heterocyclic. Examples of difunctional epoxy resins can be those based on diglycidyl ethers or bisphenol F, bisphenol A, phenol and cresol epoxy novolac resins, glycidyl ethers of phenol-formaldehyde 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 imidines and amides, glycidyl ethers, or any combination thereof. Preferred difunctional epoxy resins can be from diglycidyl ethers of bisphenol F, diglycidyl ethers of bisphenol A, diglycidyl dihydroxynaphthalene, or any combination thereof.

[0029] In some illustrative examples, the composite part 206 includes one of a thermoset resin, an epoxy resin, or a thermoplastic resin. In some illustrative examples, the composite part 206 includes a carbon fiber reinforced composite 254. In some illustrative examples, the composite part 206 includes a glass fiber reinforced composite 252. The composite part 206 can be formed using any desired method. In some illustrative examples, 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 illustrative examples, the first layer 212 is in contact with the surface 208 of the composite part 206. In some illustrative examples, a surfacing film or primer is present between the surface 208 and the first layer 212.

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

[0032] In some illustrative examples, the second layer 214 provides a solar energy absorption 248 between 0.20-0.67. In some illustrative examples, the second layer 214 provides a solar energy absorption 248 ranging from 0.20 to 0.67, or from 0.23 to 0.67, or from 0.23 to 0.53. In some illustrative examples, the second layer 214 provides a solar energy absorption 248 ranging from 0.21-0.23. In some illustrative examples, the second layer 214 provides a solar energy absorption 248 ranging from 0.58-0.67.

[0033] The first layer 212 includes a metal additive 224. The metal additive 224 is present in the first layer 212 with at least one of an epoxy resin, an acrylic resin, a polyurethane, a polyamide, a modified rosin, a hydrocarbon resin, or a modified cellulose. In some illustrative examples, the metal additive 224 is used in an amount and a particular metal additive 224 is configured to block transmission of at least one of ultraviolet light 217 or visible light 218 in a desired wavelength 234. In some illustrative examples, the first layer 212 includes the metal additive 224 to block transmission of at least one of ultraviolet light 217 or visible light 218, where the metal additive 224 is present in the first layer 212 in a range of 1.7-26.4 wt.%. The weight percentages given herein are calculated as a percentage of dry weight.

[0034] The metal additive 224 includes any desired metal or metal alloy. The metal additive 224 is selected such that the metal additive 224 does not have an unwanted interaction with the composite material of the composite part 206. In some illustrative examples, the metal additive 224 includes at least one of aluminum 226, copper 227, silver 228, gold 229, nickel 230, or stainless steel 231. By including one of these metals, the metal additive 224 includes that metal or any desired alloy of that metal. For example, when the metal additive 224 includes aluminum 226, the metal additive 224 includes at least one of aluminum or at least one aluminum alloy. As another example, when the metal additive 224 includes copper 227, the metal additive 224 can include at least one of brass or bronze.

[0035] In some illustrative examples, the first layer 212 includes a metal additive 224 ranging from 1.7-26 wt%. In some illustrative examples, the first layer 212 includes a metal additive 224 ranging from 1.7-8.6 wt%. In some illustrative examples, the first layer 212 includes a metal additive 224 ranging from 6.6-13.2 wt%. In some illustrative examples, the first layer 212 includes a metal additive 224 ranging from 12.8-25.7%. In some illustrative examples, the first layer 212 includes a metal additive 224 ranging from 19.8-26.4%. In examples, the metal additive 224 can be aluminum 226 in the above amounts.

[0036] In some illustrative examples, the first layer 212 blocks transmission of at least one of ultraviolet light 217 or visible light 218 by at least one of reflection or scattering. In some illustrative examples, the desired wavelength 234 ranges from 300-500 nm. In some illustrative examples, the desired wavelength 234 ranges from 300-550 nm. In some illustrative examples, the desired wavelength 234 ranges from 300-800 nm.

[0037] In some illustrative examples, the first layer 212 is a darker color than a desired exterior color 242 of the second layer 214. In some illustrative examples, the second layer 214 is a lighter color, such as white, and has a low solar absorptance characteristic. The second layer 214 includes a white colorant, such as titanium dioxide 240 in rutile or anatase form (aka titanium white or TiO2), antimony white, zinc white, silica, and the like, ranging from 16 wt% - 41 wt%. In some illustrative examples, the second layer 214 includes titanium dioxide 240 ranging from 20-41 wt%. In some illustrative examples, the second layer 214 includes titanium dioxide 240 ranging from 16 wt% - 21 wt%.

[0038] The thickness 232 of the first layer 212 is selected to provide a desired amount of blocking of 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 performance of the coating system 210. In some illustrative examples, 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.

[0039] Thickness can be measured using any desired standard put forth by a materials or regulatory association, such as the American Society for Testing and Materials. In some illustrative examples, the thickness 232 and the thickness 250 can be evaluated using ASTM D4138-22.

[0040] In some demonstrative examples, the first layer 212 comprises a thickness 232 between 0.5-2.0 mil. In some demonstrative examples, the first layer 212 comprises a thickness 232 between 0.8-1.5 mil. In some demonstrative examples, the first layer 212 comprises a thickness 232 between 0.8-1.2 mil. In some demonstrative examples, the first layer 212 comprises a thickness 232 between 1.0-1.5 mil. In some demonstrative examples, the first layer 212 comprises a thickness 232 between 1.0-2.0 mil.

[0041] In some demonstrative examples, the thickness 232 is selected based on a location of the coating system 210 on the platform 202. In some demonstrative examples, the thickness 232 can be selected according to the operating environment 200.

[0042] The thickness 250 of the second layer 214 and the specific colorant 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 of the coating system 210. In some demonstrative examples, 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.

[0043] In some demonstrative examples, the second layer 214 comprises a thickness 250 between 2.0-4.0 mil. In some demonstrative examples, the second layer 214 comprises a thickness 250 between 2.4-4.0 mil. In some demonstrative examples, the second layer 214 comprises a thickness 250 between 2.4-3.2 mil. In some demonstrative examples, the second layer 214 comprises a thickness 250 between 2.0-3.6 mil.

[0044] In some demonstrative examples, the first layer 212 comprises a thickness 232 between 0.8-1.5 mil, and the second layer 214 comprises a thickness 250 between 2.0-3.6 mil. In some demonstrative examples, the first layer 212 comprises a thickness between 0.8-1.2 mil or 1.0-1.5 mil, and wherein the second layer comprises a thickness between 2.0-3.6 mil.

[0045] In some illustrative examples, the platform 202 takes the form of an aircraft 204. In these illustrative examples, the aircraft 204 includes a composite part 206 and a coating system 210 on the composite part 206. The coating system 210 includes a first layer 212 configured to block 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 sunlight 216. The first layer 212 includes a metallic additive 224. The second layer 214 includes a colorant 239 configured to reflect the infrared component 220 of sunlight 216. The first layer 212 is positioned between the second layer 214 and the composite part 206. In some illustrative examples, the first layer 212 further includes at least one of an epoxy resin, an acrylic resin, a polyurethane, a polyamide, a modified rosin, a hydrocarbon resin, or a modified cellulose. In some illustrative examples, the second layer 214 includes a polyurethane 238 having titanium dioxide 240.

[0046] The composite part 206 can take the form of any desired part or portion of a part of the platform 202. In some illustrative examples, the composite part 206 is a piece of a tail 256 of the aircraft 204. In some illustrative examples, the composite part 206 is a horizontal stabilizer 260. In some illustrative examples, the composite part 206 is an elevator 258 of the tail 256 of the aircraft 204. In some illustrative examples, the elevator 258 can take the form of a horizontal stabilizer 116. In some illustrative examples, the composite part 206 is a wing 262 of the aircraft 204. In some illustrative examples, the composite part 206 is a fuselage 264 of the aircraft 204. Figure 1

[0047] In some illustrative examples, an outer clearcoat 215 is present in the coating system 210. The outer clearcoat 215 is in contact with the second layer 214. The outer clearcoat 215 is an optional layer that is not present in some illustrative examples. The outer clearcoat 215 can provide additional protection to the second layer 214 and the first layer 212 from unwanted abrasion.

[0048] Figure 2 The coating system 210 in the composite part 206 can be applied by at least one of spraying, inkjet printing, wiping, 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 illustrative examples, the first layer 212 can be applied and cured prior to the application of the second layer 214. In some illustrative examples, the first layer 212 can be co-cured with the composite part 206.

[0049] Figure 2 ​The illustration of the operating environment 200 is not meant to imply physical or architectural limitations to the methodology that can be implemented in illustrative implementations. Other components can be used in addition to or instead of the components illustrated. Some components can be unnecessary. Additionally, the illustration provides an overview of some functional components. When implemented in an illustrative implementation, one or more of these components can be combined, divided, or combined and divided into different components. For example, a surface treatment film or primer can exist between the surface 208 and the first layer 212.

[0050] Turning now to Figure 3 , an illustration of a cross-sectional view of a dual layer coating on a composite material is depicted in accordance with an illustrative implementation. The composite component 302 is Figure 2 a physical implementation of the composite component 206 in Figure 2 . The coating system 304 protects the composite component 302 from degradation due to exposure to sunlight. The coating system 304 is

[0051] The coating system 304 includes a first layer 306 and a second layer 308. In this illustrative example, the first layer 306 is in contact with the composite component 302. In some unillustrated examples, a surface treatment film or primer can exist between the composite component 302 and the first layer 306.

[0052] The first layer 306 protects the composite component 302 from at least one of ultraviolet light or visible light within a desired wavelength. The first layer 306 includes a metal additive. The metal additive is configured to block transmission of at least one of ultraviolet light or visible light within a desired wavelength. In some illustrative examples, the metal additive includes at least one of aluminum, copper, silver, gold, nickel, or stainless steel.

[0053] The first layer 306 blocks or significantly reduces transmission of at least one of ultraviolet light or visible light within a desired wavelength. The first layer 306 at least absorbs or reflects at least one of ultraviolet light or visible light within a desired wavelength. The first layer 306 provides a desired blocking characteristic to a desired wavelength. In some illustrative examples, the first layer 306 provides protection to the composite component 302 by at least one of reflecting or scattering.

[0054] The second layer 308 is in contact with the first layer 306. The second layer 308 provides thermal protection to the composite component 302 while the first layer 306 provides protection against at least one of ultraviolet light or visible light. In some illustrative examples, the second layer 308 provides protection to an infrared component of sunlight with a solar absorptivity.

[0055] In some illustrative examples, the first layer 306 is darker in color than the second layer 308. In some illustrative examples, the second layer 308 is white. In some other illustrative examples, the second layer 308 is gray. In some illustrative examples, the second layer 308 has a desired outer color for performance, which can be selected from white, gray, beige, off-white, or any other desired color.

[0056] The composite component 302 with the coating system 304 is resistant to degradation due to cyclic exposure to at least one of ultraviolet light or visible light and moisture. The composite component 302 with the coating system 304 meets desired standards for solar absorptance, color, and resistance to cracking. The first layer 306 and the second layer 308 are arranged in a particular order, with the thickness 310 and the thickness 312 configured to selectively absorb or reflect at least one of particular wavelengths of solar radiation while meeting other desired coating characteristics. In some illustrative examples, the coating system 304 meets desired standards for corrosion resistance.

[0057] In the present illustrative example, an outer clear coat 314 is present in the coating system 304. The outer clear coat 314 is in contact with the second layer 308. In some illustrative examples, the outer clear coat 314 is optional. The outer clear coat 314 can provide additional protection to the second layer 308 and the first layer 306 from unwanted abrasion.

[0058] As used herein, the phrase “at least one of,” when used with a list of items, means that a variety of one or more of the listed items can be used and only one item in the list can be needed. For example, “at least one of A, B, or C” can include, but is not limited to, A, A and B, or B. This example also can include A, B, and C, or B and C. Of course, any combination of these items can be present. In other examples, “at least one” can be, for example, but not limited to, two of A; one of B; ten of C; four of B and seven of C; or other suitable combinations. The items can be specific objects, things, or categories. In other words, “at least one of’ a combination of items in a list can be used, but not every item in the list has to be present.

[0059] As used herein, “a number of” when used in reference to items means one or more items.

[0060] The flowcharts and block diagrams depicting different embodiments illustrate the architecture, functionality, and operation of some possible implementations of the apparatus and methods in the illustrative embodiments. In this respect, each block in the flowchart or block diagram may represent at least one of a module, segment, function, or part of an operation or step.

[0061] In some alternative implementations of the illustrative embodiments, one or more functions mentioned in the boxes may not appear in the order shown in the figures. For example, in some cases, two boxes shown consecutively may actually be executed simultaneously, or these boxes may sometimes be executed in reverse order, depending on the functions involved. Furthermore, additional boxes may be added besides those mentioned in the flowchart or block diagram. Some boxes may be optional.

[0062] It is possible Figure 4 The aircraft manufacturing and service methods 400 shown are Figure 5 An illustrative embodiment of this disclosure is depicted against the background of the aircraft 500 shown. First, turn to... Figure 4 An illustration of an aircraft manufacturing and service method, represented in block diagram form, is depicted according to an illustrative embodiment. During pre-production, the aircraft manufacturing and service method 400 may include... Figure 5 Specifications and design of China Aircraft 500 402 and material procurement 404.

[0063] During the production of Aircraft 500, component and sub-component manufacturing 406 and system integration 408 are performed. Afterward, Aircraft 500 can be certified and delivered 410 for service 412. During customer service 412, Aircraft 500 is scheduled for routine maintenance and repair 414, which may include modifications, reconfigurations, refurbishments, or other maintenance and repairs.

[0064] Each process of the aircraft manufacturing and service method 400 may be implemented or performed by a systems integrator, a third party, and / or an operator. In these instances, the operator may be a customer. For the purposes of this description, a systems integrator may include, but is not limited to, any number of aircraft manufacturers and major systems subcontractors; a third party may include, but is not limited to, any number of suppliers, subcontractors, and vendors; and an operator may be an airline, leasing company, military entity, service organization, etc.

[0065] Now refer to Figure 5 An illustration of an aircraft in the form of a block diagram is depicted in an illustrative embodiment that can be implemented. In this example, aircraft 500 is composed of... Figure 4An aircraft manufacturing and service method 400 can produce and can include a fuselage 502 having a plurality of 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 can be included.

[0066] The apparatus and methods embodied herein can be used in at least one stage of the aircraft manufacturing and service method 400. In Figure 4 One or more illustrative embodiments can be manufactured or used in at least one of the processes of component and subassembly manufacturing 406, system integration 408, service 412, or maintenance and repair 414 of the aircraft manufacturing and service method 400.

[0067] Illustrative examples provide a coating system that protects a composite part. The coating system protects the composite part from degradation due to cyclic exposure to at least one of ultraviolet light or visible light and moisture, while meeting standards for solar absorptance, color, and anti-cracking. Multiple layers are arranged within the coating system in a particular order and at particular thicknesses to selectively absorb and / or reflect certain wavelengths of solar radiation, while meeting other purpose standards.

[0068] The description of the different illustrative embodiments has been 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 illustrative embodiments can provide different features to provide a variety of implementations of the disclosed embodiments. The chosen embodiments were chosen and described in order to best explain the principles of the embodiments, the practical application, and to enable others skilled in the art to understand the disclosure for various embodiments with various modifications as are suited to the particular use contemplated.

[0069] The present disclosure can specifically include the following clauses:

[0070] 1. A coating system (210, 304) for a composite part (206, 302), comprising:

[0071] a first layer (212, 306) including a metal additive (224), the first layer (212, 306) configured to block transmission of at least one of ultraviolet light (217) or visible light (218) within a desired wavelength (234); and

[0072] a second layer (214, 308) on and in contact with the first layer (212, 306) and configured to reflect an infrared component (220) of the sunlight (216), the second layer (214, 308) including a colorant (239) configured to reflect the infrared component (220) of the sunlight (216), wherein the first layer (212, 306) is between the second layer (214, 308) and the composite component (206, 302).

[0073] 2. The coating system (210, 304) of clause 1, wherein the second layer (214, 308) has a desired exterior color (242) for performance.

[0074] 3. The coating system (210, 304) of clause 1, wherein the second layer (214, 308) is white (244) or gray (246).

[0075] 4. The coating system (210, 304) of clause 1, wherein the metal additive (224) includes at least one of aluminum (226), copper (227), silver (228), gold (229), nickel (230), and stainless steel (231).

[0076] 5. The coating system (210, 304) of clause 1, wherein the first layer (212, 306) includes aluminum (226) in a range of 1.7-26.4 wt%.

[0077] 6. The coating system (210, 304) of clause 1, wherein the metal additive (224) is present in the first layer (212, 306) in a range of 1.7-26.4 wt%.

[0078] 7. The coating system (210, 304) of clause 1, wherein the second layer (214, 308) includes titanium dioxide (240) in a range of 16 wt% - 41 wt%.

[0079] 8. The coating system (210, 304) of clause 1, wherein the first layer (212, 306) includes a thickness (232, 310) between 0.8-2.0 mils.

[0080] 9. The coating system (210, 304) of clause 1, wherein the second layer (214, 308) includes a thickness (250, 312) between 2.0-4.0 mils.

[0081] 10. The coating system (210, 304) according to Clause 1, wherein the first layer (212, 306) blocks the transmission of at least one of ultraviolet light (217) or visible light (218) by reflecting or scattering at least one.

[0082] 11. The coating system (210, 304) according to Clause 1, wherein the second layer (214, 308) provides thermal control for the coating system (210, 304) by a controlled solar energy absorption rate (248).

[0083] 12. The coating system (210, 304) according to Clause 1, wherein the solar energy absorption rate (248) provided by the second layer (214, 308) is in the range of 0.20-0.67.

[0084] 13. The coating system (210, 304) according to Clause 1, wherein the desired wavelength (234) is in the range of 300-550 nm.

[0085] 14. The coating system (210, 304) according to Clause 1, further comprising:

[0086] The outer transparent coating (215, 314) is in contact with the second layer (214, 308).

[0087] 15. The coating system (210, 304) according to Clause 1, wherein the colorant (239) comprises titanium dioxide (240), and the second layer (214, 308) further comprises polyurethane (238).

[0088] 16. An aircraft (100, 204) comprising:

[0089] Composite components (206, 302); and

[0090] A coating system (210, 304) on the composite components (206, 302), the coating system (210, 304) comprising:

[0091] The first layer (212, 306) is configured to prevent ultraviolet light (217) or visible light (218) within the desired wavelength (234).

[0092] Transmission of at least one of the following, wherein the first layer (212, 306) comprises a metal additive (224), and

[0093] a second layer (214, 308) configured to reflect an infrared component of sunlight, the second layer (214, 308) including a colorant (239) configured to reflect an infrared component (220) of sunlight (216), wherein the first layer (212, 306) is positioned between the second layer (214, 308) and the composite component (206, 302).

[0094] 17. The aircraft (100, 204) of clause 16, wherein the composite component (206, 302) comprises a carbon fiber reinforced composite material (254).

[0095] 18. The aircraft (100, 204) of clause 16, wherein the composite component (206, 302) comprises a glass fiber reinforced composite material (252).

[0096] 19. The aircraft (100, 204) of clause 16, wherein the composite component (206, 302) is a wing (102, 104, 262).

[0097] 20. The aircraft (100, 204) of clause 16, wherein the composite component (206, 302) is a portion of a tail (112, 256) of the aircraft (100, 204).

[0098] 21. The aircraft (100, 204) of clause 16, wherein the composite component (206, 302) is a fuselage (106, 264).

[0099] 22. The aircraft (100, 204) of clause 16, wherein the composite component (206, 302) is one of a portion of a fuselage (106, 264), a wing (102, 104, 262), or a tail (112, 256) of the aircraft (100, 204).

[0100] 23. The aircraft (100, 204) of clause 16, wherein the first layer (212, 306) comprises a thickness (232, 310) between 0.8-2.0 mils.

[0101] 24. The aircraft (100, 204) of clause 16, wherein the second layer (214, 308) comprises a thickness (250, 312) between 2.0-4.0 mils.

[0102] 25. The aircraft (100, 204) of clause 16, wherein the first layer (212, 306) comprises aluminum (226) ranging between 1.7-26.4 wt%.

[0103] 26. The aircraft (100, 204) according to Clause 16, wherein the first layer (212, 306) includes the metal additive (224) to block transmission of at least one of ultraviolet light (217) or visible light (218), wherein the metal additive (224) is present in the first layer (212, 306) in a range of 1.7-26.4 wt%.

[0104] 27. The aircraft (100, 204) according to Clause 16, wherein the second layer (214, 308) includes titanium dioxide (240) in a range of 16 wt% - 41 wt%.

[0105] 28. The aircraft (100, 204) according to Clause 16, wherein the desired wavelength (234) is in a range of 300-550 nm.

[0106] 29. The aircraft (100, 204) according to Clause 16, wherein the desired wavelength (234) is in a range of 300-800 nm.

[0107] 30. The aircraft (100, 204) according to Clause 16, wherein the composite part (206, 302) includes one of a thermoset resin, an epoxy resin, or a thermoplastic resin.

[0108] 31. The aircraft (100, 204) according to Clause 16, wherein the composite part (206, 302) includes an epoxy resin.

[0109] 32. The aircraft (100, 204) according to Clause 16, wherein the composite part (206, 302) includes at least one of carbon fiber, boron fiber, glass fiber, polyester fiber, aramid fiber, or polymeric fiber.

[0110] 33. The aircraft (100, 204) according to Clause 16, wherein the first layer (212, 306) includes at least one of an epoxy resin, an acrylic resin, a polyurethane, a polyamide, a modified rosin, a hydrocarbon resin, or a modified cellulose.

[0111] 34. The aircraft (100, 204) according to Clause 16, further comprising:

[0112] an outer clearcoat (215, 314) in contact with the second layer (214, 308).

[0113] 35. A coating system (210, 304) for a composite part (206, 302), comprising:

[0114] a first layer (212, 306) configured to block transmission of at least one of ultraviolet light (217) or visible light (218) within a desired wavelength (234) and including a metallic additive (224) including at least one of aluminum (226), copper (227), silver (228), gold (229), nickel (230), or stainless steel (231); and

[0115] a second layer (214, 308) configured to provide a desired solar absorptance (248) and including between 16wt% - 41wt% titanium dioxide (240), the second layer (214, 308) in contact with the first layer (212, 306), wherein the first layer (212, 306) is between the second layer (214, 308) and the composite component (206, 302).

[0116] 36. The coating system (210, 304) of clause 35, wherein the desired wavelength (234) is within a range of 300 - 550 nm.

[0117] 37. The coating system (210, 304) of clause 35, wherein the desired wavelength (234) is within a range of 300 - 800 nm.

[0118] 38. The coating system (210, 304) of clause 35, wherein the first layer (212, 306) includes a thickness (232, 310) of between 0.5 - 2.0 mils.

[0119] 39. The coating system (210, 304) of clause 35, wherein the second layer (214, 308) includes a thickness (250, 312) of between 2.0 - 4.0 mils.

[0120] 40. The coating system (210, 304) of clause 35, further comprising:

[0121] 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) including a metallic additive (224), the first layer (212, 306) configured to block 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 solar light (216), the second layer (214, 308) including a colorant (239) configured to reflect the infrared component (220) of the solar light (216), wherein the first layer (212, 306) is between the second layer (214, 308) and the composite part (206, 302).

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

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

4. The coating system (210, 304) of claim 1, wherein the metallic additive (224) includes at least one of aluminum (226), copper (227), silver (228), gold (229), nickel (230), and stainless steel (231).

5. The coating system (210, 304) of claim 1, wherein the first layer (212, 306) includes aluminum (226) in a range of 1.7-26.4 wt%.

6. The coating system (210, 304) of claim 1, wherein the metallic additive (224) is present in the first layer (212, 306) in a range of 1.7-26.4 wt%.

7. The coating system (210, 304) of claim 1, wherein the second layer (214, 308) includes titanium dioxide (240) in a range of 16 wt% - 41 wt%.

8. The coating system (210, 304) of claim 1, wherein the first layer (212, 306) includes a thickness (232, 310) between 0.8-2.0 mils.

9. 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.

10. 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 at least one of reflection or scattering.

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