Coating Systems for Composite Protection

Abstract

A coating system for protecting fiber reinforced composite materials from operating conditions is provided. A coating system for a composite part is presented. The coating system includes a first layer including a metal additive and a second layer over and in contact with the first layer, configured to reflect the infrared component of sunlight. The first layer is configured to prevent transmission of at least one of ultraviolet light or visible light within a desired wavelength range. The second layer includes polyurethane and titanium dioxide, and the first layer is disposed between the second layer and the composite part.

Description

[Technical Field]

[0001]

[0001] This disclosure relates generally to coatings, and more particularly to two-layer coatings for composite materials. [Background technology]

[0002]

[0002] Fiber-reinforced composite materials can be used in structures or platforms, including large vehicles such as aircraft, ships, cars, trains, and other means of transportation. The operating environment of vehicles containing fiber-reinforced composite materials can cause degradation of the fiber-reinforced composite materials when exposed to the operating environment.

[0003]

[0003] It would therefore be desirable to have a method and apparatus that takes into account at least some of the above-mentioned problems, as well as other problems that may arise. In particular, it would be desirable to provide a coating system for protecting fiber-reinforced composite materials from operating conditions. Summary of the Invention

[0004]

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

[0005] Another embodiment of the present disclosure provides an aircraft. The aircraft includes a composite component and a coating system on the composite component. 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 range 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 metal additive. The first layer is disposed between the second layer and the composite component.

[0006] Another embodiment of the present disclosure provides a coating system for a composite part. The coating system includes: a first layer including a metal additive including at least one of aluminum, copper, silver, gold, nickel, or stainless steel configured to prevent transmission of at least one of ultraviolet light or visible light within a desired wavelength range; and a second layer including 16 wt% to 41 wt% of a colorant configured to provide a desired solar absorptance and to reflect the infrared component of sunlight. The second layer is in contact with the first layer, and the first layer is disposed between the second layer and the composite part.

[0007]

[0007] These features and functions may be realized individually in various embodiments of the present disclosure or may be combined in other embodiments, further details of which can be found in the following description and with reference to the drawings. [Brief explanation of the drawings]

[0008] The novel features believed characteristic of the exemplary embodiments are set forth in the appended claims. However, the exemplary embodiments, together with their preferred modes of use, further objects and features, will best be understood by reading the following detailed description of exemplary embodiments of the present disclosure in conjunction with the accompanying drawings.

[0009] [Figure 1] 1 is an illustration of an aircraft in accordance with an illustrative embodiment. [Figure 2]

[0010] FIG. 1 is a block diagram of a platform having a dual layer coating in an operating environment in accordance with an illustrative embodiment; [Figure 3]

[0011] 1 is a cross-sectional view of a two-layer coating on a composite material according to an exemplary embodiment; [Figure 4]

[0012] 1 is an illustration of an aircraft manufacturing and service method in block diagram form in accordance with an illustrative embodiment; [Figure 5]

[0013] 1 illustrates an aircraft in block diagram form in which an illustrative embodiment may be implemented. DETAILED DESCRIPTION OF THE INVENTION

[0010]

[0014] The examples recognize and take into account several considerations: The exemplary embodiments recognize and take into account that components made from fiber-reinforced composite materials can be susceptible to degradation when exposed to a combination of electromagnetic radiation, moisture, and heat, and that it is desirable to protect fiber-reinforced composite materials from the components of sunlight.

[0011]

[0015] The illustrative embodiments recognize and take into account that it is desirable to protect fiber-reinforced composite materials without undesirably affecting other material properties or operational criteria of the respective platform. The illustrative embodiments recognize and take into account that aircraft have multiple operational criteria set by regulatory agencies. Additionally, the illustrative embodiments 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 may increase the risk of cracking, result in increased weight, and may not meet the aircraft's electromagnetic effects (EME) criteria.

[0012]

[0016] Described herein is a coating that has the ability to block transmission of ultraviolet and visible light at the composite surface (inside) while meeting the requirements for visible color and solar absorptance (outside) without an excessively thick paint layer, thereby avoiding issues such as cracking, weight, and EME.

[0013]

[0017] Referring now to Figure 1, an aircraft is shown in accordance with an illustrative embodiment. Aircraft 100 has wings 102 and 104 attached to fuselage body 106. Aircraft 100 includes engines 108 and 110 attached to wing 102 and wing 104, respectively.

[0014]

[0018] The fuselage 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 fuselage body 106.

[0015]

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

[0016]

[0020] 2, a block diagram of an operating environment is shown in accordance with an illustrative embodiment. Platform 202 resides within operating environment 200 and is exposed to sunlight 216. Platform 202 may take any desired form.

[0017]

[0021] Coating system 210 provides protection for composite component 206 of platform 202. Coating system 210 protects composite component 206 from sunlight 216. Coating system 210 includes first layer 212, which includes metal additive 224 and is configured to prevent transmission of at least one of ultraviolet light 217 or visible light 218 within a desired wavelength 234, and second layer 214, in contact with first layer 212 and configured to reflect infrared component 220 of sunlight 216. First layer 212 can be applied onto composite component 206 as one of a coating, a film, or an ink.

[0018]

[0022] A coating can be, for example, a thin layer or covering of a given volume, which can be, for example, a liquid, fluid, continuous, or free-flowing material. Examples of coatings for purposes of this description include paints, primers, topcoats, and the like, as well as combinations thereof.

[0019]

[0023] A film can be, for example, a thin coating of material that can be in a solid or semi-solid state, and in some embodiments, flexible. Examples of films for purposes of this description include decals, stickers, wraps, and the like.

[0020]

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

[0021]

[0025] The second layer 214 is exposed to the operating environment 200. As a result, sunlight 216 strikes the second layer 214. The second layer 214 is disposed above the first layer 212 and covers the first layer 212.

[0022]

[0026] Second layer 214 includes colorant 239 configured to reflect infrared component 220 of sunlight 216. Colorant 239 can include any desired colorant configured to reflect infrared component 220 of sunlight 216. In some embodiments, colorant 239 includes titanium dioxide 240. Colorant 239 can be present in any desired polymeric material within second layer 214. In some embodiments, 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 embodiments, second layer 214 includes polyurethane 238. In some embodiments, second layer 214 includes polyurethane 238 with titanium dioxide 240. First layer 212 is disposed between second layer 214 and composite component 206. Second layer 214 can be applied onto composite component 206 as one of a coating, a film, or an ink.

[0023]

[0027] Composite part 206 includes a fiber-reinforced matrix material. In some embodiments, the fiber-reinforced material includes at least one of carbon fiber, boron fiber, glass fiber, polyester fiber, aramid fiber (e.g., Kevlar®), polymer fiber, or other desired reinforcing fiber. In some embodiments, composite part 206 includes at least one of polyester, vinyl ester, cyanate ester, bismaleimide, polyetherimide, polyphenylene sulfide, polyaryletherketone (including PEEK and PEKK), a thermoset material, such as an epoxy material, or nylon. In some embodiments, the epoxy composite material includes at least one of novolac epoxy, aromatic epoxy, aliphatic epoxy, or cyclic epoxy. In some embodiments, composite part 206 includes a thermoset resin.

[0024]

[0028] Currently, epoxy resin systems can incorporate both multifunctional and difunctional epoxy systems to achieve polymer matrices with improved tensile strength and compression after impact (CAI). Difunctional epoxy resins can be saturated, unsaturated, cycloaliphatic, aromatic, cycloaliphatic, or heterocyclic. Examples of difunctional epoxy resins can be based on diglycidyl ethers or glycidyl ethers of 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 imidines and amides, glycidyl ethers, or any combination thereof. Preferred difunctional epoxy resins can be derived from diglycidyl ethers of bisphenol F, diglycidyl ethers of bisphenol A, diglycidyl dihydroxynaphthalene, or any combination thereof.

[0025]

[0029] In some embodiments, composite component 206 includes one of a thermoset resin, an epoxy resin, or a thermoplastic resin. In some embodiments, composite component 206 includes a carbon fiber reinforced composite material 254. In some embodiments, composite component 206 includes a glass fiber reinforced composite material 252. Composite component 206 can be formed using any desired method. In some embodiments, composite component 206 can be formed through resin infusion, wet lamination, or resin sweep.

[0026]

[0030] Surface 208 is an exterior surface of composite component 206. In some embodiments, first layer 212 contacts surface 208 of composite component 206. In some embodiments, a surface film or primer is present between surface 208 and first layer 212.

[0027]

[0031] In some embodiments, second layer 214 is the exterior surface of platform 202. In some embodiments, second layer 214 has a desired exterior color 242 for performance. In some embodiments, second layer 214 is white 244 or gray 246. In some embodiments, second layer 214 provides thermal control 236 for coating system 210 through controlled solar absorptance 248. Solar absorptance 248 can be evaluated using any desired standard established by a materials society or regulatory body, such as the American Society for Testing and Materials. In some embodiments, solar absorptance 248 can be evaluated using ASTM E903-20.

[0028]

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

[0029]

[0033] First layer 212 includes metal additive 224. Metal additive 224 is present in first layer 212 including at least one of epoxy, acrylic, polyurethane, polyamide, modified rosin, hydrocarbon resin, or modified cellulose. In some embodiments, the amount and specific metal additive 224 is configured to block transmission of at least one of ultraviolet light 217 or visible light 218 within a desired wavelength 234 range. In some embodiments, first layer 212 includes metal additive 224 that prevents transmission of at least one of ultraviolet light 217 or visible light 218, and metal additive 224 is present in first layer 212 in a range of 1.7 to 26.4 wt %. Weight percentages herein are calculated as dry weight percentages.

[0030]

[0034] Metal additive 224 may include any desired metal or alloy. Metal additive 224 may be selected such that metal additive 224 does not have undesirable interactions with the composite material of composite component 206. In some embodiments, metal additive 224 may include at least one of aluminum 226, copper 227, silver 228, gold 229, nickel 230, or stainless steel 231. By including one of these metals, metal additive 224 may include a metal or any desired alloy. For example, when metal additive 224 includes aluminum 226, metal additive 224 may include at least one of aluminum or at least one alloy of aluminum. As another example, when metal additive 224 includes copper 227, metal additive 224 may include at least one of brass or bronze.

[0031]

[0035] In some embodiments, first layer 212 includes metal additive 224 in a range of 1.7-26 wt%. In some embodiments, first layer 212 includes metal additive 224 in a range of 1.7-8.6 wt%. In some embodiments, first layer 212 includes metal additive 224 in a range of 6.6-13.2 wt%. In some embodiments, first layer 212 includes metal additive 224 in a range of 12.8-25.7 wt%. In some embodiments, first layer 212 includes metal additive 224 in a range of 19.8-26.4 wt%. By way of example, metal additive 224 can be aluminum 226 in the amount referenced above.

[0032]

[0036] In some embodiments, first layer 212 blocks the transmission of at least one of ultraviolet light 217 or visible light 218 through at least one of reflection or scattering. In some embodiments, desired wavelength 234 is in the range of 300-500 nm. In some embodiments, desired wavelength 234 is in the range of 300-550 nm. In some embodiments, desired wavelength 234 is in the range of 300-800 nm.

[0033]

[0037] In some embodiments, the color of first layer 212 is darker than the desired exterior color 242 of second layer 214. In some embodiments, second layer 214 is lighter in color, such as white, and has low solar absorptance. Second layer 214 includes a white colorant, such as rutile or anatase titanium dioxide 240 (also known as titania or TiO), antimony white, zinc white, or silicon dioxide, in the range of 16 wt% to 41 wt%. In some embodiments, second layer 214 includes titanium dioxide 240 in the range of 20 wt% to 41 wt%. In some embodiments, second layer 214 includes titanium dioxide 240 in the range of 16 wt% to 21 wt%.

[0034]

[0038] The thickness 232 of the first layer 212 is selected to block a desired amount of at least one of ultraviolet light 217 or visible light 218. The thickness 232 of the first layer 212 is selected to provide desired material properties for the coating system 210. In some 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.

[0035]

[0039] The thickness can be measured using any desired standard established by a materials society or regulatory body, such as the American Society for Testing and Materials. In some embodiments, thickness 232 and thickness 250 can be evaluated using ASTM D4138-22.

[0036]

[0040] In some embodiments, first layer 212 has a thickness 232 between 0.5 and 2.0 mils. In some embodiments, first layer 212 has a thickness 232 between 0.8 and 1.5 mils. In some embodiments, first layer 212 has a thickness 232 between 0.8 and 1.2 mils. In some embodiments, first layer 212 has a thickness 232 between 1.0 and 1.5 mils. In some embodiments, first layer 212 has a thickness 232 between 1.0 and 2.0 mils.

[0037]

[0041] In some embodiments, thickness 232 is selected based on the location of coating system 210 on platform 202. In some embodiments, thickness 232 can be selected depending on operating environment 200.

[0038]

[0042] The thickness 250 and specific colorant of the second layer 214 are selected to provide reflection of the infrared component 220 of sunlight 216. The thickness 250 of the second layer 214 is selected to provide desired material properties for the coating system 210. In some embodiments, 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.

[0039]

[0043] In some embodiments, second layer 214 has a thickness 250 between 2.0 and 4.0 mils. In some embodiments, second layer 214 has a thickness 250 between 2.4 and 4.0 mils. In some embodiments, second layer 214 has a thickness 250 between 2.4 and 3.2 mils. In some embodiments, second layer 214 has a thickness 250 between 2.0 and 3.6 mils.

[0040]

[0044] In some embodiments, first layer 212 has a thickness 232 between 0.8 and 1.5 mils, and second layer 214 has a thickness 250 between 2.0 and 3.6 mils. In some embodiments, first layer 212 has a thickness between 0.8 and 1.2 mils or 1.0 and 1.5 mils, and second layer 214 has a thickness between 2.0 and 3.6 mils.

[0041]

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

[0042]

[0046] Composite component 206 may take the form of any desired component or portion of a component of platform 202. In some examples, composite component 206 is a portion of tail section 256 of aircraft 204. In some examples, composite component 206 is horizontal stabilizer 260. In some examples, composite component 206 is elevator 258 in tail section 256 of aircraft 204. In some examples, elevator 258 may take the form of horizontal stabilizer 116 in Figure 1 . In some examples, composite component 206 is wing 262 of aircraft 204. In some examples, composite component 206 is fuselage 264 of aircraft 204.

[0043]

[0047] In some embodiments, an outer clear coat 215 is present in coating system 210. Outer clear coat 215 is in contact with second layer 214. Outer clear coat 215 is an optional layer that is not present in some embodiments. Outer clear coat 215 can provide additional protection for second layer 214 and first layer 212 against unwanted wear.

[0044]

[0048] 2 can be applied by at least one of spraying, inkjet printing, wiping, roller application, or any other desired application method. First layer 212 and second layer 214 can be applied to composite component 206 in liquid form. In some embodiments, first layer 212 can be applied and cured before applying second layer 214. In some embodiments, first layer 212 can be co-cured with composite component 206.

[0045]

[0049] The illustration of manufacturing environment 200 in FIG. 2 is not meant to impose physical or architectural limitations on the manner in which an example embodiment may be implemented. Other components in addition to or in place of the illustrated components may be used. Some components may be unnecessary. Also, blocks are presented to illustrate some functional components. When implemented in an example embodiment, one or more of these blocks may be combined, separated, or combined and separated into different blocks. For example, a surface film or primer may be present between surface 208 and first layer 212.

[0046]

[0050] Referring now to Figure 3, a cross-sectional view of a two-layer coating on a composite material is shown in accordance with an illustrative embodiment. Composite part 302 is a physical embodiment of composite part 206 from Figure 2. Coating system 304 resides on composite part 302. Coating system 304 protects composite part 302 from degradation due to exposure to sunlight. Coating system 304 is a physical embodiment of coating system 210 from Figure 2. View 300 is a cross-sectional view of two-layer coating system 304 on composite part 302.

[0047]

[0051] Coating system 304 includes a first layer 306 and a second layer 308. In this example, first layer 306 is in contact with composite component 302. In some not shown examples, a surface film or primer may be present between composite component 302 and first layer 306.

[0048]

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

[0049]

[0053] First layer 306 prevents or significantly reduces the transmission of at least one of ultraviolet or visible light within a desired wavelength range. First layer 306 absorbs, reflects, or both absorbs and reflects at least one of ultraviolet or visible light within a desired wavelength range. First layer 306 provides desirable blocking properties for the desired wavelengths. In some embodiments, first layer 306 provides protection for composite component 302 through at least one of reflection or scattering.

[0050]

[0054] Second layer 308 is in contact with first layer 306. Second layer 308 provides thermal protection for composite component 302, and first layer 306 provides protection against at least one of ultraviolet or visible light. In some embodiments, second layer 308 uses solar radiation absorption to provide protection against the infrared component of sunlight.

[0051]

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

[0052]

[0056] Composite component 302 with coating system 304 is resistant to degradation due to cyclic exposure to at least one of ultraviolet or visible light and moisture. Composite component 302 with coating system 304 meets desired criteria for solar absorptance, color, and crack resistance. First layer 306 and second layer 308 are arranged in a specific order and have thicknesses 310 and 312 configured to selectively absorb or reflect specific wavelengths of solar radiation and meet other desired coating properties. In some embodiments, coating system 304 meets desired criteria for corrosion resistance.

[0053]

[0057] In this 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. The outer clear coat 314 is optional in some examples. The outer clear coat 314 can provide additional protection for the second layer 308 and the first layer 306 against unwanted wear.

[0054]

[0058] The phrase "at least one of" used in conjunction with enumerated items herein means that different combinations of one or more of the enumerated items can be used, and that only one of the enumerated items may be required. For example, "at least one of item A, item B, and item C" may include, but is not limited to, item A, item A and item B, or item B. This example may also include item A, item B, and item C, or item B and item C. Of course, any combination of these items may be present. In other examples, "at least one of" may be, but is not limited to, two item A, one item B, ten item C, four item B, and seven item C, or other suitable combinations. An item may be a specific object, thing, or category. In other words, "at least one of" means that any combination of items and multiple items from the list can be used, but not all of the listed items are required.

[0055]

[0059] As used herein, the term "a number of," when used in connection with items, means one or more items.

[0056]

[0060] The flow diagrams and block diagrams in the different illustrated embodiments illustrate the structure, functionality, and operation of some possible implementations of apparatuses and methods in the example embodiments. In this regard, each block in the flow diagrams or block diagrams may represent at least one of a module, a segment, a function, or a portion of an operation or step.

[0057]

[0061] In some alternative implementations of the exemplary embodiments, one or more functions described in a block may occur out of the order described in the figures. For example, in some cases, two blocks shown in succession may be executed substantially concurrently, or the blocks may sometimes be performed in the reverse order, depending on the functionality involved. Also, other blocks may be added in addition to the blocks shown in a flow diagram or block diagram. Some blocks may be optional.

[0058]

[0062] An exemplary embodiment of the disclosure may be described in the context of aircraft manufacturing and service method 400 shown in Figure 4 and aircraft 500 shown in Figure 5. Turning now to Figure 4, an aircraft manufacturing and service method is illustrated in the form of a block diagram, according to an exemplary embodiment. During the pre-production stage, aircraft manufacturing and service method 400 may include specification and design 402 of aircraft 500 in Figure 5 and material procurement 404.

[0059]

[0063] During production, component and subassembly manufacturing 406 and system integration 408 of the aircraft 500 occurs. The aircraft 500 then undergoes certification and delivery 410 and is placed into service 412. While in customer service 412, the aircraft 500 is scheduled for routine maintenance and service 414, which may include modification, reconfiguration, refurbishment, or other maintenance and upkeep.

[0060]

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

[0061]

[0065] Referring now to Figure 5, an aircraft is illustrated in block diagram form in which an illustrative embodiment may be implemented. In this example, aircraft 500 is produced by aircraft manufacturing and service method 400 in Figure 4 and may include airframe 502 having multiple systems 504 and interior 506. Example systems 504 include one or more of propulsion system 508, electrical system 510, hydraulic system 512, and environmental system 514. Any number of other systems may also be included.

[0062]

[0066] Apparatus and methods embodied herein may be used during at least one of the stages of aircraft manufacturing and service method 400. One or more illustrative embodiments may be manufactured or used during at least one of component and subassembly manufacturing 406, system integration 408, service 412, or maintenance and service 414 in FIG. 4 .

[0063]

[0067] The examples present coating systems for protecting composite parts. The coating systems protect the composite parts from degradation due to cyclic exposure to at least one of ultraviolet or visible light and moisture while meeting criteria for solar absorptance, color, and crack resistance. Layers are arranged in a specific order and at specific thicknesses within the coating system to selectively absorb and / or reflect specific wavelengths of solar radiation while meeting other criteria suitable for the purpose.

[0064]

[0068] The description of various exemplary embodiments has been presented for purposes of illustration and description and is not intended to be exhaustive or to limit the embodiments to the precise form disclosed. Many modifications and variations will be apparent to those skilled in the art. Furthermore, various exemplary embodiments may offer different features as compared to other exemplary embodiments. The selected embodiment or embodiments have been chosen and described in order to best explain the principles and practical applications of the embodiments and to facilitate others skilled in the art in understanding the disclosure of the various embodiments and various modifications suitable for the particular application contemplated.

Claims

1. A coating system (210, 304) for a composite component (206, 302), comprising: a first layer (212, 306) including a metal additive (224), the 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 a second layer (214, 308) on the first layer 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), the first layer (212, 306) being disposed between the second layer (214, 308) and the composite part (206, 302); A coating system (210, 304) comprising:

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

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

4. 2. The coating system (210, 304) of claim 1, wherein the metal additive (224) comprises 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) comprises aluminum (226) in the range of 1.7 to 26.4 wt %.

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

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

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

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

10. 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) through at least one of reflection or scattering.

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

12. The coating system (210, 304) of claim 1, wherein the second layer (214, 308) provides a solar absorptance (248) in the range of 0.20 to 0.

67.

13. The coating system (210, 304) of claim 1, wherein the desired wavelength (234) is in the range of 300 to 550 nm.

14. an outer clear coat (215, 314) in contact with said second layer (214, 308); The coating system (210, 304) of claim 1, further comprising:

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

16. a composite part (206, 302); and a coating system (210, 304) on said composite component (206, 302); 1. An aircraft (100, 204) 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), the first layer (212, 306) including a metal additive (224); and 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 of the sunlight (216), the first layer (212, 306) being disposed between the second layer (214, 308) and the composite component (206, 302); an aircraft (100, 204) including:

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

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

19. 17. The aircraft (100, 204) of claim 16, wherein the composite component (206, 302) is a wing (102, 104, 262).

20. The aircraft (100, 204) of claim 16, wherein the composite component (206, 302) is a portion of a tail section (112, 256) of the aircraft (100, 204).

21. 17. The aircraft (100, 204) of claim 16, wherein the composite component (206, 302) is a fuselage (106, 264).

22. 17. The aircraft (100, 204) of claim 16, wherein the composite component (206, 302) is a portion of a fuselage (106, 264), a wing (102, 104, 262), or a tail section (112, 256) of the aircraft (100, 204).

23. The aircraft (100, 204) of claim 16, wherein the first layer (212, 306) has a thickness (232, 310) of between 0.8 and 2.0 mils.

24. The aircraft (100, 204) of claim 16, wherein the second layer (214, 308) has a thickness (250, 312) of between 2.0 and 4.0 mils.

25. The aircraft (100, 204) of claim 16, wherein the first layer (212, 306) comprises aluminum (226) in the range of 1.7 to 26.4 wt%.

26. 17. The aircraft (100, 204) of claim 16, wherein the first layer (212, 306) includes the metal additive (224) that prevents transmission of at least one of the ultraviolet light (217) or visible light (218), and the metal additive (224) is present in the first layer (212, 306) in a range of 1.7 to 26.4 wt %.

27. The aircraft (100, 204) of claim 16, wherein the second layer (214, 308) comprises titanium dioxide (240) in the range of 16 wt% to 41 wt%.

28. The aircraft (100, 204) of claim 16, wherein the desired wavelength (234) is in the range of 300 to 550 nm.

29. The aircraft (100, 204) of claim 16, wherein the desired wavelength (234) is in the range of 300 to 800 nm.

30. 17. The aircraft (100, 204) of claim 16, wherein the composite component (206, 302) comprises one of a thermoset resin, an epoxy resin, or a thermoplastic resin.

31. 31. The aircraft (100, 204) of claim 30, wherein the composite component (206, 302) comprises an epoxy resin.

32. 17. The aircraft (100, 204) of claim 16, wherein the composite component (206, 302) comprises at least one of carbon fiber, boron fiber, glass fiber, polyester fiber, aramid fiber, or polymer fiber.

33. 17. The aircraft (100, 204) of claim 16, wherein the first layer (212, 306) comprises at least one of an epoxy, an acrylic, a polyurethane, a polyamide, a modified rosin, a hydrocarbon resin, or a modified cellulose.

34. an outer clear coat (215, 314) in contact with said second layer (214, 308); 17. The aircraft (100, 204) of claim 16, further comprising:

35. A coating system (210, 304) for a composite component (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), the first layer (212, 306) including a metal additive (224) comprising at least one of aluminum (226), copper (227), silver (228), gold (229), nickel (230), or stainless steel (231); and a second layer (214, 308) comprising 16 wt % to 41 wt % titanium dioxide (240) configured to provide a desired solar radiation absorption (248), the second layer (214, 308) being in contact with the first layer (212, 306), the first layer (212, 306) being disposed between the second layer (214, 308) and the composite component (206, 302); A coating system (210, 304) comprising:

36. The coating system (210, 304) of claim 35, wherein the desired wavelength (234) is in the range of 300 to 550 nm.

37. The coating system (210, 304) of claim 35, wherein the desired wavelength (234) is in the range of 300 to 800 nm.

38. 36. The coating system (210, 304) of claim 35, wherein the first layer (212, 306) has a thickness (232, 310) of between 0.5 and 2.0 mils.

39. 36. The coating system (210, 304) of claim 35, wherein the second layer (214, 308) has a thickness (250, 312) of between 2.0 and 4.0 mils.

40. an outer clear coat (215, 314) in contact with said second layer (214, 308); 36. The coating system (210, 304) of claim 35, further comprising:

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