Double layer coating system for composite protection

Abstract

The title of the application is a two-layer coating system for composite protection. The present application shows a two-layer coating system for an epoxy composite component. The two-layer 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 a second layer in contact with the first layer and configured to reflect an infrared component of sunlight. The first layer comprises polyurethane and carbon black. And the second layer comprises polyurethane and titanium dioxide. The first layer is between the second layer and the epoxy composite component.

Description

Technical Field

[0001] This disclosure generally relates to coatings, and more specifically to two-layer coatings of composite materials. Background Technology

[0002] Fiber-reinforced composite materials can be used in platforms, including buildings or large vehicles such as aircraft, ships, automobiles, trains, and other modes of transportation. The operating environment of vehicles containing fiber-reinforced composite materials can lead to their degradation—if the materials are exposed to the operating environment.

[0003] Therefore, it is desirable to have a method and apparatus that take into account at least some of the aforementioned problems, as well as other potential issues. Specifically, it is desirable to provide a coating system to protect fiber-reinforced composite materials from the effects of operating conditions. Summary of the Invention

[0004] One embodiment of this disclosure provides a two-layer coating system for an epoxy composite component. The two-layer coating system includes a first layer and a second layer, the first layer being configured to prevent transmission of at least one of ultraviolet or visible light within a desired wavelength, and the second layer being in contact with the first layer and configured to reflect the infrared component of sunlight. The first layer comprises polyurethane with carbon black. The second layer comprises polyurethane with titanium dioxide. The first layer is located between the second layer and the epoxy composite component.

[0005] Another embodiment of this disclosure provides an aircraft. The aircraft includes an epoxy compound component and a dual-coating system on the epoxy compound component. The dual-coating system includes a first layer and a second layer, the first layer being configured to prevent transmission of at least one of ultraviolet or visible light within a desired wavelength, and the second layer being configured to reflect the infrared component of sunlight. The first layer comprises polyurethane and carbon black. The second layer comprises polyurethane and titanium dioxide. The first layer is located between the second layer and the epoxy compound component.

[0006] Another embodiment of this disclosure provides a two-layer coating system for epoxy composite components. The two-layer coating system includes a first layer and a second layer. The first layer is configured to prevent transmission of at least one of ultraviolet or visible light within a desired wavelength and contains 0.8-4.5 wt% carbon black. The second layer is configured to provide desired solar absorptivity and contains 16-41 wt% titanium dioxide. The second layer is in contact with the first layer, and the first layer is located between the second layer and the epoxy composite component.

[0007] These features and functions may be implemented independently in various embodiments of this disclosure, or may be combined in other embodiments, in which further details can be seen with reference to the following description and drawings. Attached Figure Description

[0008] Novel features considered characteristic of exemplary embodiments are set forth in the appended claims. However, exemplary embodiments, their preferred modes of use, further objects and features will be best understood upon reading in conjunction with the accompanying drawings, with reference to the following detailed description of exemplary embodiments of this disclosure, wherein: Figure 1 This is an example of an aircraft according to an exemplary implementation; Figure 2 This is a block diagram example of a platform having a double-layer coating in an operating environment according to an exemplary embodiment; Figure 3 This is an example of a cross-sectional view of a double-layer coating on an epoxy compound material according to an exemplary embodiment; Figure 4 These are examples of aircraft manufacturing and servicing methods in the form of block diagrams according to exemplary embodiments; and Figure 5 It is an example of an aircraft in block diagram form, in which exemplary embodiments can be implemented. Detailed Implementation

[0009] The exemplary embodiments recognize and incorporate several considerations. The exemplary embodiments recognize and consider that components made of fiber-reinforced composite materials are prone to degradation when exposed to a combination of electromagnetic radiation, moisture, and heat. The exemplary embodiments recognize and consider that protecting the fiber-reinforced composite materials from the effects of solar components is desirable.

[0010] Exemplary embodiments recognize and consider that protecting the fiber-reinforced composite material without undesirably affecting other material properties or the operational standards of the corresponding platform is desirable. Exemplary examples recognize and consider that the aircraft has several operational standards established by regulatory agencies. Furthermore, exemplary examples recognize and consider that increasing the aircraft's weight is undesirable. Exemplary embodiments recognize and consider that significantly increasing the coating thickness may increase the risk of cracking, increase weight, and potentially fail to meet the aircraft's electromagnetic effects (EME) standards.

[0011] Now transferred to Figure 1 An example of an aircraft is depicted according to an exemplary embodiment. The aircraft 100 has wings 102 and 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.

[0012] The fuselage 106 has a tail 112. Horizontal stabilizers 114, 116 and vertical stabilizers 118 are attached to the tail 112 of the fuselage 106.

[0013] Aircraft 100 is an example of an aircraft that may have a coating configured to protect the composite material from degradation by ultraviolet or visible light. In exemplary embodiments, the coating may be present on at least one of the wings 102, 104, fuselage 106, or tail 112. In some exemplary embodiments, a dual-coating system as described may be present on horizontal stabilizer 114 or horizontal stabilizer 116.

[0014] Now transferred to Figure 2 A block diagram example of an operating environment is depicted according to an exemplary embodiment. Platform 202 exists in operating environment 200 and is exposed to sunlight 216. Platform 202 can take any desired form.

[0015] A dual-coating system 210 provides protection for the epoxy compound component 206 of platform 202. The dual-coating system 210 protects the epoxy compound component 206 from sunlight 216. The dual-coating system 210 includes a first layer 212 and a second layer 214. The first layer 212 is configured to prevent the transmission of at least one of ultraviolet light 217 or visible light 218 within a desired wavelength 234. The second layer 214 is in contact with the first layer 212 and is configured to reflect the infrared component 220 of sunlight 216. The first layer 212 comprises polyurethane 222 and carbon black 224.

[0016] 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 on top of and covers the first layer 212.

[0017] The second layer 214 comprises polyurethane 238 and titanium dioxide 240. The first layer 212 is located between the second layer 214 and the epoxy compound component 206.

[0018] Epoxy composite component 206 includes a fiber-reinforced matrix material. In some exemplary embodiments, the fiber reinforcement material includes at least one of carbon fiber, boron fiber, glass fiber, aramid fiber, polymer fiber, or other desired reinforcing fibers. In some exemplary embodiments, the epoxy composite material includes at least one of phenolic epoxy, aromatic epoxy, aliphatic epoxy, or cyclic epoxy. Currently, epoxy resin systems can combine multifunctional epoxy systems with bifunctional epoxy systems to achieve a polymer matrix with improved tensile strength and compressive strength after impact (CAI). Bifunctional epoxy resins can be saturated, unsaturated, cyclic aliphatic, aromatic, alicyclic, or heterocyclic. Examples of bifunctional epoxy resins can be based on the following: diglycidyl ethers or bisphenol F, bisphenol A, phenol and cresol epoxy phenolic varnishes (novolacs), glycidyl ethers of phenol-aldehyde adducts, glycidyl esters of aliphatic diols, diglycidyl ethers, diethylene glycol diglycidyl ethers, aromatic epoxy resins, aliphatic polyglycidyl ethers, epoxidized olefins, aromatic glycidyl amines, heterocyclic glycidylimides and amides, glycidyl ethers, or any combination thereof. Preferred bifunctional epoxy resins may be derived from diglycidyl ethers of bisphenol F, diglycidyl ethers of bisphenol A, diglycidyl dihydroxynaphthalene, or any combination thereof.

[0019] In some exemplary embodiments, epoxy composite component 206 includes carbon fiber reinforced epoxy composite material 254. In some exemplary embodiments, epoxy composite component 206 includes glass fiber reinforced epoxy composite material 252.

[0020] Surface 208 is the outer surface of epoxy compound component 206. In some exemplary embodiments, a first layer 212 contacts surface 208 of epoxy compound component 206. In some exemplary embodiments, a surface film or primer layer is present between surface 208 and the first layer 212.

[0021] In some exemplary instances, the second layer 214 is the outer surface of the platform 202. In some exemplary instances, the second layer 214 has a desired external color 242 for performance. In some exemplary instances, the second layer 214 is white 244 or gray 246. In some exemplary instances, the second layer 214 provides thermal control 236 of the double-coated system 210 through controlled solar absorptivity 248. Solar absorptivity 248 can be evaluated using any desired standard proposed by materials or regulatory associations such as the American Society for Testing and Materials. In some exemplary instances, solar absorptivity 248 can be evaluated using ASTM E903-20.

[0022] In some exemplary instances, the second layer 214 provides a solar absorptivity 248 in the range of 0.21–0.23. In some exemplary instances, the second layer 214 provides a solar absorptivity 248 in the range of 0.58–0.67.

[0023] In some exemplary embodiments, the first layer 212 is black 228 or gray 230. In some exemplary embodiments, the first layer 212 blocks the transmission of at least one of ultraviolet light 217 or visible light 218 by scattering. In some exemplary embodiments, the wavelength 234 is desired to be in the range of 300-500 nm. In some exemplary embodiments, the wavelength 234 is desired to be in the range of 300-800 nm.

[0024] In some exemplary embodiments, the first layer 212 includes a black additive or colorant, such as carbon black 224, graphite, etc. In some exemplary embodiments, the first layer 212 includes carbon black 224. In these exemplary embodiments, the amount of carbon black 224 is configured to block the transmission of at least one of ultraviolet light 217 or visible light 218 of a desired wavelength 234. In some exemplary embodiments, the first layer 212 includes carbon black 224 in the range of 0.8-4.5% by weight. In some exemplary embodiments, the first layer 212 includes carbon black 224 in the range of 1-4% by weight. In some exemplary embodiments, the first layer 212 includes carbon black 224 in the range of 1-3% by weight. In some exemplary embodiments, the color 226 of the first layer 212 is darker than the outer color 242 of the second layer 214.

[0025] In some exemplary embodiments, the second layer 214 is a lighter color, such as white, and has low solar energy absorption properties. The second layer 214 comprises a white colorant, such as titanium dioxide 240 in the form of rutile or anatase (also known as titanium oxide or TiO2), antimony white, zinc white, silicon dioxide, etc. In some exemplary embodiments, the second layer 214 comprises titanium dioxide 240 in the range of 16 wt% to 41 wt%. In some exemplary embodiments, the second layer 214 comprises titanium dioxide 240 in the range of 20 wt% to 41 wt%. In some exemplary embodiments, the second layer 214 comprises titanium dioxide 240 in the range of 16 wt% to 21 wt%.

[0026] The thickness 232 of the first layer 212 is selected to provide a desired amount of blocking for 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 of the dual-layer coating system 210. In some exemplary instances, the thickness 232 is selected based on at least one of the desired weight, desired EME performance, and desired flexibility performance of the dual-layer coating system 210.

[0027] In some exemplary embodiments, the first layer 212 includes a thickness 232 between 1.0 and 2.5 mils.

[0028] The thickness 250 of the second layer 214 is selected to provide reflection of the infrared component 220 of sunlight 216. The thickness 250 of the second layer 214 is selected to provide the desired material properties of the double-layer coating system 210. In some exemplary instances, the thickness 250 is selected based on at least one of the desired weight, desired electromagnetic effect (EME) performance, and desired flexibility performance of the double-layer coating system 210.

[0029] Thickness can be measured using any desired standard proposed by a materials or regulatory association, such as the American Society for Testing and Materials (ASTM). In some exemplary instances, thicknesses 232 and 250 can be evaluated using ASTM D4138-07a (2022). In some exemplary instances, the second layer 214 comprises a thickness 250 between 2.0 and 3.6 mils. In some exemplary instances, the second layer 214 comprises a thickness 250 between 2.4 and 3.2 mils.

[0030] In some exemplary instances, the first layer 212 includes a thickness 232 between 1.0 and 2.5 mils, and the second layer 214 includes a thickness 232 between 2.0 and 3.6 mils. In some exemplary instances, the first layer 212 includes a thickness between 1.0 and 2.0 mils, and the second layer includes a thickness between 2.4 and 3.2 mils.

[0031] In some exemplary instances, platform 202 takes the form of aircraft 204. In these exemplary instances, aircraft 204 includes an epoxy compound component 206 and a dual-coating system 210 on the epoxy compound component 206. The dual-coating system 210 includes a first layer 212 and a second layer 214. The first layer 212 is configured to prevent transmission of at least one of ultraviolet light 217 or visible light 218 within a desired wavelength 234, and the second layer 214 is configured to reflect the infrared component 220 of sunlight 216. The first layer 212 includes polyurethane 222 and carbon black 224. The second layer 214 includes polyurethane 238 and titanium dioxide 240. The first layer 212 is located between the second layer 214 and the epoxy compound component 206.

[0032] The epoxy compound component 206 may take the form of any desired component or part of a component of platform 202. In some exemplary instances, the epoxy compound component 206 is part of the tail 256 of aircraft 204. In some exemplary instances, the epoxy compound component 206 is a level stabilizer 260. In some exemplary instances, the epoxy compound component 206 is an elevator 258 in the tail 256 of aircraft 204.

[0033] In some exemplary embodiments, a dual-coating system 210 for an epoxy composite component 206 includes a first layer 212 and a second layer 214. The first layer 212 is configured to prevent transmission of at least one of ultraviolet light 217 or visible light 218 within a desired wavelength 234 and contains 0.8-4.5 wt% carbon black 224. The second layer 214 is configured to provide a desired solar absorptivity 248 and contains 16-41 wt% titanium dioxide 240. The second layer 214 is in contact with the first layer 212. The first layer 212 is located between the second layer 214 and the epoxy composite component 206. In some exemplary embodiments, one or more additional materials may be present between the first layer 212 and the second layer 214. In some exemplary embodiments, one or more additional materials may be present between the first layer 212 and the epoxy composite component 206. In some exemplary embodiments, the second layer 214 has a desired external color 242.

[0034] Figure 2 The dual-coating system 210 can be applied by at least one of spraying, inkjet printing, wiping, roller coating, or any other desired application method. The first and second layers can be applied to the epoxy compound component 206 in liquid form. In some exemplary instances, the first layer 212 can be applied and cured prior to the application of the second layer 214.

[0035] Figure 2 The example of operating environment 200 is not intended to imply any physical or architectural limitations on the form in which the exemplary embodiments may be implemented. Other components may be used in addition to or in place of the components shown. Some components may be unnecessary. Furthermore, the boxes are shown to illustrate some functional components. One or more of these boxes, when implemented in the exemplary embodiments, may be combined, separated, or combined and separated into different boxes. For example, a surface film or primer layer may exist between surface 208 and the first layer 212. As another example, although... Figure 2 As not shown, epoxy compound component 206 may be at least a portion of the fuselage or wing. In some exemplary instances, epoxy compound component 206 is part of the fuselage, wing, or tail 256 of aircraft 204.

[0036] Now transferred to Figure 3 An example cross-sectional view of a double-layer coating on an epoxy composite material is depicted according to an exemplary embodiment. Epoxy composite component 302 is... Figure 2 The physical implementation of the epoxy compound component 206 is described below. A dual-coating system 304 is present on the epoxy compound component 206. The dual-coating system 304 protects the epoxy compound component 206 from degradation caused by sunlight exposure. The dual-coating system 304 is... Figure 2 Physical implementation of the double-coating system 210. View 300 is a cross-sectional view of the double-coating system 304 on the epoxy compound component 302.

[0037] The dual-coating system 304 includes a first layer 306 and a second layer 308. In this exemplary example, the first layer 306 is in contact with the epoxy compound component 302. In some examples not depicted, a surface film or primer layer may be present between the epoxy compound component 206 and the first layer 306.

[0038] The first layer 306 protects the epoxy compound component 302 from at least one of ultraviolet or visible light within a desired wavelength. The first layer 306 prevents or significantly reduces the transmission of at least one of ultraviolet or visible light within a desired wavelength. The first layer 306 absorbs or reflects at least one of ultraviolet or visible light within a desired wavelength. The first layer 306 provides the desired blocking properties for the desired wavelength. In some exemplary embodiments, the first layer 306 provides protection for the epoxy compound component 302 by scattering.

[0039] The second layer 308 is in contact with the first layer 306. The second layer 308 provides thermal protection for the epoxy compound component 302, while the first layer 306 provides protection against at least one of ultraviolet or visible light. In some exemplary embodiments, the first layer 306 provides protection using scattering. In some exemplary embodiments, the second layer 308 provides protection against the infrared component of sunlight using solar absorptivity.

[0040] As shown, the first layer 306 is a darker color than the second layer 308. In some exemplary instances, the second layer 308 is white. In some other exemplary instances, the second layer 308 is gray. In some exemplary instances, the first layer 306 is black. In some other exemplary instances, the first layer 306 is gray. In some exemplary instances, the second layer 308 is a lighter gray than the first layer 306.

[0041] An epoxy compound component 302 having a dual-coating system 304 resists degradation caused by cyclic exposure to at least one of ultraviolet or visible light and moisture. The epoxy compound component 302 having the dual-coating system 304 meets desired standards for solar energy absorption, color, and crack resistance. A first layer 306 and a second layer 308 are arranged in a specific order and have thicknesses 310 and 312, which are configured to selectively absorb or reflect at least one of solar radiation of a specific wavelength, while meeting other desired coating properties. In some exemplary instances, the dual-coating system 304 meets desired standards for corrosion resistance.

[0042] As used herein, the phrase "at least one / kind / item" when used with an item list means that different combinations of one or more of the listed items may be used, and only one item from the list may be required. For example, "at least one / kind / item of item A, item B, or 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 exist. In other instances, "at least one / kind / item" may be, for example, but not limited to, two items A; one item B; ten items C; four items B and seven items C; or other suitable combinations. Items may be specific objects, things, or categories. In other words, "at least one / kind / item" means that any combination of items and any number of items may be used in the list, but not all items in the list are required.

[0043] As used in this article, “some” when referring to projects means one or more projects.

[0044] Weight percentage (“weight %”), when stated in the context of a specific component in the first or second layer, is calculated on a dry weight basis as follows: It should be understood that the weight percentage calculation does not include the weight of any solvent present in liquid form in the layer (e.g., before being applied to the epoxy compound component).

[0045] The flowcharts and block diagrams depicting different embodiments illustrate the architecture, functionality, and operation of some possible implementations of the devices and methods in the exemplary embodiments. In this regard, each block in the flowchart or block diagram may represent at least one of a module, segment, function, or operation or step.

[0046] In some alternative embodiments of the exemplary implementation, one or more functions marked in the boxes may not occur in the order indicated in the figures. For example, in some cases, two boxes shown successively may be executed substantially simultaneously, or the boxes may sometimes be executed in reverse order—depending on the functionality involved. Moreover, in addition to the boxes illustrated in the flowchart or block diagram, other boxes may be added. Some boxes may be optional.

[0047] Exemplary embodiments of this disclosure can be implemented in, for example, Figure 4 The aircraft manufacturing and service method 400 shown and such Figure 5 The environment of the aircraft 500 shown is described. First, turn to... Figure 4 An example of an aircraft manufacturing and servicing method in block diagram form is depicted according to an exemplary embodiment. During the pre-production process, the aircraft manufacturing and servicing method 400 may include... Figure 5 The specifications and design of the aircraft 500 in the document 402 and the material procurement 404.

[0048] During the production process, the components and sub-components of the aircraft 500 are manufactured 406 and the system is integrated 408. Subsequently, the aircraft 500 can be certified and delivered 410 for service 412. When it is used by the customer 412, the aircraft 500 is scheduled for routine maintenance and service 414, which may include modification, reconfiguration, refurbishment or other maintenance and service.

[0049] The processes described in Aircraft Manufacturing and Service Method 400 can be performed by a system integrator, a third party, and / or an operator. In these instances, the operator may be the customer. For descriptive purposes, the system integrator may include, but is not limited to, any number of aircraft manufacturers and major system subcontractors; the third party may include, but is not limited to, any number of suppliers, subcontractors, and vendors; and the operator may be an airline, leasing company, military entity, service organization, etc.

[0050] For reference Figure 5 This illustrates a block diagram example of an aircraft that can be implemented according to exemplary embodiments. In this example, aircraft 500 is... Figure 4 The aircraft manufacturing and servicing method 400 produces an airframe 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.

[0051] The equipment and methods implemented herein can be used in at least one stage of aircraft manufacturing and servicing method 400. One or more exemplary embodiments may be implemented. Figure 4 The parts and sub-components are manufactured or used in the process of at least one of manufacturing 406, system integration 408, putting into use 412, or maintenance and service 414.

[0052] An exemplary example illustrates a two-layer coating system for protecting epoxy compound components. This two-layer coating system protects the epoxy compound components from degradation caused by cyclic exposure to at least one of ultraviolet or visible light and moisture, while meeting standards for solar absorbance, color, and crack resistance. In the two-layer coating system, the layers are arranged in a specific order and with specific thicknesses to selectively absorb and / or reflect solar radiation of specific wavelengths, while also meeting other objective standards.

[0053] This disclosure also includes the following potentially asserted terms: 1. A two-layer coating system for epoxy composite components, comprising: A first layer, configured to prevent transmission of at least one of ultraviolet or visible light within a desired wavelength, comprising polyurethane and carbon black; and The second layer, which is on and in contact with the first layer and is configured to reflect the infrared components of sunlight, comprises polyurethane and titanium dioxide, wherein the first layer is located between the second layer and the epoxy composite component.

[0054] 2. The dual-coating system according to Clause 1, wherein the second layer has the desired external color for performance.

[0055] 3. The dual-coating system according to clause 1 or 2, wherein the second layer is white or gray.

[0056] 4. The dual-coating system according to any of the preceding clauses, wherein the first layer is black or gray.

[0057] 5. A two-layer coating system according to any of the preceding clauses, wherein the first layer comprises carbon black in the range of 0.8-4.5% by weight.

[0058] 6. A two-layer coating system according to any of the preceding clauses, wherein the second layer comprises titanium dioxide in the range of 16% to 41% by weight.

[0059] 7. A two-layer coating system according to any of the preceding clauses, wherein the second layer comprises titanium dioxide in the range of 20% to 41% by weight.

[0060] 8. A dual-coating system according to any one of clauses 1-6, wherein the second layer comprises titanium dioxide in the range of 16% to 21% by weight.

[0061] 9. The dual-coating system according to any of the preceding clauses, wherein the first layer comprises a thickness between 1.0 and 2.5 mils.

[0062] 10. The double-coating system according to any of the preceding clauses, wherein the second layer comprises a thickness between 2.0 and 3.6 mils.

[0063] 11. The dual-coating system according to any of the preceding clauses, wherein the first layer comprises a thickness between 1.0 and 2.0 mils.

[0064] 12. The double-coating system according to any of the preceding clauses, wherein the second layer comprises a thickness between 2.4 and 3.2 mils.

[0065] 13. The dual-layer coating system according to any of the preceding clauses, wherein the first layer blocks the transmission of at least one of ultraviolet light or visible light by scattering.

[0066] 14. The dual-coating system according to any of the preceding clauses, wherein the second layer provides thermal control of the dual-coating system through controlled solar energy absorption.

[0067] 15. The dual-coating system according to any of the preceding clauses, wherein the second layer provides a solar energy absorption in the range of 0.21-0.23.

[0068] 16. The dual-coating system according to any of the preceding clauses, wherein the second layer provides a solar energy absorption in the range of 0.58-0.67.

[0069] 17. A double-coating system according to any of the preceding clauses, wherein the desired wavelength is in the range of 300-500 nm.

[0070] 18. An aircraft comprising: Epoxy compound components; and A dual-coating system on the epoxy compound component, the dual-coating system comprising: A first layer, configured to prevent transmission of at least one of ultraviolet or visible light within a desired wavelength, comprises polyurethane and carbon black, and The second layer, configured to reflect the infrared component of sunlight, comprises polyurethane and titanium dioxide, wherein the first layer is located between the second layer and the epoxy composite component.

[0071] 19. The aircraft as described in Clause 18, wherein the epoxy composite component comprises a carbon fiber reinforced epoxy composite material.

[0072] 20. The aircraft according to clause 18 or 19, wherein the epoxy compound component comprises a glass fiber reinforced epoxy compound material.

[0073] 21. The aircraft according to any one of clauses 18-20, wherein the epoxy compound component is a level stabilizer.

[0074] 22. The aircraft according to any one of clauses 18-20, wherein the epoxy compound component is an elevator at the tail of the aircraft.

[0075] 23. The aircraft according to any one of clauses 18-20, wherein the epoxy compound component is a portion of the fuselage, wing, or tail of the aircraft.

[0076] 24. The aircraft according to any one of clauses 18-23, wherein the epoxy composite component comprises at least one of carbon fiber, boron fiber, glass fiber or aramid fiber.

[0077] 25. The aircraft according to any one of clauses 18-24, wherein the first layer comprises a thickness between 1.0 and 2.5 mils, and wherein the second layer comprises a thickness between 2.0 and 3.6 mils.

[0078] 26. The aircraft according to any one of clauses 18-25, wherein the first layer comprises a thickness between 1.0 and 2.0 mils, and wherein the second layer comprises a thickness between 2.4 and 3.2 mils.

[0079] 27. The aircraft according to any one of clauses 18-26, wherein the first layer comprises carbon black in the range of 0.8% to 4.5% by weight.

[0080] 28. The aircraft according to any one of clauses 18-27, wherein the second layer comprises titanium dioxide in the range of 16% to 41% by weight.

[0081] 29. The aircraft according to any one of clauses 18-28, wherein the desired wavelength is in the range of 300-500 nm.

[0082] 30. A two-layer coating system for epoxy composite components, comprising: The first layer, configured to prevent transmission of at least one of ultraviolet or visible light within a desired wavelength, and comprising 0.8-4.5% by weight of carbon black; and The second layer, configured to provide desired solar energy absorption and comprising 16%-41% by weight of titanium dioxide, is in contact with the first layer, wherein the first layer is located between the second layer and the epoxy compound component.

[0083] 31. The dual-coating system according to Clause 30, wherein the second layer has the desired external color for performance.

[0084] 32. The dual-layer coating system according to clause 30 or 31, wherein the first layer comprises a thickness between 1.0 and 2.5 mils, and wherein the second layer comprises a thickness between 2.0 and 3.6 mils.

[0085] 33. A two-layer coating system according to any one of clauses 30-32, wherein the first layer comprises a thickness between 1.0 and 2.0 mils, and wherein the second layer comprises a thickness between 2.4 and 3.2 mils.

[0086] 34. The dual-layer coating system according to any one of clauses 30-33, wherein the desired wavelength is in the range of 300-500 nm.

[0087] 35. The dual-layer coating system according to any one of clauses 30-33, wherein the desired wavelength is in the range of 300-800 nm.

[0088] Specifically, this application includes the following implementation methods: 1. A two-layer coating system for epoxy composite components, comprising: A first layer, configured to prevent transmission of at least one of ultraviolet or visible light within a desired wavelength, comprising polyurethane and carbon black; and The second layer, which is on and in contact with the first layer and is configured to reflect the infrared components of sunlight, comprises polyurethane and titanium dioxide, wherein the first layer is located between the second layer and the epoxy composite component.

[0089] 2. The double-layer coating system according to embodiment 1, wherein: (a) The second layer has a desired external color for its performance, optionally wherein the second layer is white or gray; and / or (b) The first layer is black or gray.

[0090] 3. The dual-layer coating system according to embodiment 1 or 2, wherein the first layer comprises carbon black in the range of about 0.8% to 4.5% by weight.

[0091] 4. The dual-layer coating system according to any of the foregoing embodiments, wherein the second layer comprises titanium dioxide in the range of 16 wt%-41 wt%, optionally 20 wt%-41 wt%, or 16 wt%-21 wt%.

[0092] 5. The double-layer coating system according to any of the foregoing embodiments, wherein: (a) The first layer comprises a thickness between 1.0 and 2.5 mils, optionally between 1.0 and 2.0 mils; and / or (b) The second layer comprises a thickness between 2.0 and 3.6 mils, optionally between 2.4 and 3.2 mils.

[0093] 6. The double-layer coating system according to any of the foregoing embodiments, wherein: (a) The first layer blocks the transmission of at least one of ultraviolet light or visible light by scattering; (b) The second layer provides thermal control of the bilayer coating system through controlled solar absorptivity; and / or (c) The second layer provides solar energy absorption in the range of 0.21-0.23 and / or 0.58-0.67.

[0094] 7. An aircraft comprising: Epoxy compound components; and A dual-coating system on the epoxy compound component, the dual-coating system comprising: A first layer, configured to prevent transmission of at least one of ultraviolet or visible light within a desired wavelength, comprises polyurethane and carbon black, and The second layer, configured to reflect the infrared component of sunlight, comprises polyurethane and titanium dioxide, wherein the first layer is located between the second layer and the epoxy composite component.

[0095] 8. The aircraft according to embodiment 7, wherein the epoxy composite component comprises at least one of carbon fiber, boron fiber, glass fiber or aramid fiber; optionally, wherein the epoxy composite component comprises a carbon fiber reinforced epoxy composite material and / or a glass fiber reinforced epoxide composite material.

[0096] 9. The aircraft according to embodiment 7 or 8, wherein the epoxy compound component is a part of the fuselage, wing, or tail of the aircraft; optionally, wherein the epoxy compound component is a horizontal stabilizer or elevator at the tail of the aircraft.

[0097] 10. The aircraft according to any one of embodiments 7-9, wherein: (a) The first layer comprises a thickness between 1.0 and 2.5 mils, optionally between 1.0 and 2.0 mils; and / or (b) The second layer comprises a thickness between 2.0 and 3.6 mils, optionally between 2.4 and 3.2 mils.

[0098] 11. The aircraft according to any one of embodiments 7-10, wherein the first layer comprises carbon black in the range of 0.8% to 4.5% by weight.

[0099] 12. The aircraft according to any one of embodiments 7-11, wherein the second layer comprises titanium dioxide in the range of 16% to 41% by weight.

[0100] 13. The dual-coating system or aircraft according to any of the foregoing embodiments, wherein the desired wavelength is in the range of 300-500 nm.

[0101] 14. A two-layer coating system for epoxy composite components, comprising: The first layer, configured to prevent transmission of at least one of ultraviolet or visible light within a desired wavelength, and comprising 0.8-4.5% by weight of carbon black; and The second layer, configured to provide desired solar energy absorption and comprising 16%-41% by weight of titanium dioxide, is in contact with the first layer, wherein the first layer is located between the second layer and the epoxy compound component.

[0102] 15. The double-layer coating system according to embodiment 14, wherein: (a) The second layer has the desired external color for performance; (b) The first layer comprises a thickness between 1.0 and 2.5 mils and the second layer comprises a thickness between 2.0 and 3.6 mils, optionally wherein the first layer comprises a thickness between 1.0 and 2.0 mils and the second layer comprises a thickness between 2.4 and 3.2 mils; and / or (c) The desired wavelength is in the range of 300-800 nm, optionally 300-500 nm.

[0103] The descriptions of various exemplary embodiments are shown for illustrative purposes and are not intended to be exhaustive or limited to the forms of the disclosure. Many modifications and variations will be apparent to those skilled in the art. Furthermore, different exemplary embodiments may provide features that differ from other exemplary embodiments. One or more selected embodiments have been chosen and described in order to best illustrate the principles of implementation, practical application, and to enable those skilled in the art to understand the disclosure of various embodiments with various modifications suitable for the specific purpose considered.

Claims

1. A dual-layer coating system for an epoxy composite part, comprising: a first layer configured to prevent transmission of at least one of ultraviolet light or visible light within a desired wavelength, the first layer comprising polyurethane with carbon black; and a second layer on and in contact with the first layer and configured to reflect an infrared component of sunlight, the second layer comprising polyurethane with titanium dioxide, wherein the first layer is positioned between the second layer and the epoxy composite part.

2. The dual-layer coating system of claim 1, wherein: (a) the second layer has a desired exterior color of performance, optionally wherein the second layer is white or gray; and / or (b) the first layer is black or gray.

3. The dual-layer coating system of claim 1 or 2, wherein the first layer comprises carbon black in a range of about 0.8 wt% - 4.5 wt%.

4. The dual-layer coating system of any preceding claim, wherein the second layer comprises titanium dioxide in a range of 16 wt% - 41 wt%, optionally 20 wt% - 41 wt%, or 16 wt% - 21 wt%.

5. The dual-layer coating system of any preceding claim, wherein: (a) the first layer comprises a thickness between 1.0 - 2.5 mils, optionally between 1.0 - 2.0 mils; and / or (b) the second layer comprises a thickness between 2.0 - 3.6 mils, optionally between 2.4 - 3.2 mils.

6. The dual-layer coating system of any preceding claim, wherein: (a) the first layer blocks transmission of at least one of ultraviolet light or visible light by scattering; (b) the second layer provides thermal control of the dual-layer coating system by controlled solar absorption; and / or (c) the second layer provides a solar absorption in a range of 0.21 - 0.23 and / or 0.58 - 0.

67.

7. An aircraft, comprising: an epoxy composite part; and a dual-layer coating system on the epoxy composite part, the dual-layer coating system comprising: a first layer configured to prevent transmission of at least one of ultraviolet light or visible light within a desired wavelength, the first layer comprising polyurethane with carbon black, and a second layer configured to reflect an infrared component of sunlight, the second layer comprising polyurethane with titanium dioxide, wherein the first layer is positioned between the second layer and the epoxy composite part.

8. The aircraft of claim 7, wherein the epoxy composite part comprises at least one of carbon fiber, boron fiber, glass fiber, or aramid fiber; optionally wherein the epoxy composite part comprises a carbon fiber reinforced epoxy composite material and / or a glass fiber reinforced epoxy composite material.

9. The aircraft of claim 7 or 8, wherein the epoxy composite part is one of a fuselage, a wing, or a portion of a tail of the aircraft; optionally wherein the epoxy composite part is a horizontal stabilizer or an elevator of the tail of the aircraft. ​ 10. The aircraft of any of claims 7-9, wherein: (a) the first layer comprises a thickness of between 1.0-2.5 mils, optionally between 1.0-2.0 mils; and / or (b) the second layer comprises a thickness of between 2.0-3.6 mils, optionally between 2.4-3.2 mils.

Images