MICROCLIMATE CONTROLLED PAD FOR EFFECTIVE PAINT STRIPPING

Abstract

An assembly for removing a desired portion of one or more layers of paint or another coating from a designated area is provided including a pad soaked with a chemical paint remover and an adhesive layer arranged about the pad configured to couple the assembly to the designated area. A removable first protective layer is positioned upwardly adjacent and is coupled to the adhesive layer. A flexible support layer is positioned adjacent the adhesive layer and the pad, opposite the removable first protective layer. A heat pad is arranged downwardly adjacent the flexible support layer. The heat pad is configured to control a microclimate adjacent the assembly when activated. A removable second protective layer is coupled to a surface of the heat pad. Removal of the second protective layer activates the heat pad.

Claims

1. An assembly for removing a desired portion of one or more layers of paint or another coating from a designated area, comprising: a pad soaked with a chemical paint remover; an adhesive layer arranged about the pad configured to couple the assembly to the designated area; a removable first protective layer positioned upwardly adjacent and coupled to the adhesive layer; a flexible support layer positioned adjacent the adhesive layer and the pad, opposite the removable first protective layer; a heat pad arranged downwardly adjacent the flexible support layer, the heat pad being configured to control a microclimate adjacent the assembly when activated; and a removable second protective layer coupled to a surface of the heat pad, wherein removal of the second protective layer activates the heat pad.

2. The assembly according to claim 1, wherein the chemical paint remover has a hazardous air pollutant (HAP) free chemical composition.

3. The assembly according to claim 1, wherein at least one of a size and shape of the pad is generally complementary to the desired portion.

4. The assembly according to claim 1, wherein at least one of a size and shape of the heat pad is generally complementary to the pad soaked with chemical paint remover.

5. The assembly according to claim 1, wherein an exothermic chemical reaction in the heat pad is activated in response to contact with air.

6. The assembly according to claim 1, wherein the microclimate includes a local temperature and moisture level.

7. The assembly according to claim 1, wherein a first surface of the adhesive layer includes an adhesive material.

8. The assembly according to claim 7, wherein the adhesive material is configured to retain the first protective layer within the assembly.

9. A method of removing one or more layers of paint or another coating from a desired area of a coated metal substrate, comprising: removing a first protective layer from a stripping assembly; attaching the assembly to the coated metal substrate such that a pad of the assembly, pre-soaked with chemical paint remover, is positioned directly adjacent the desired area; activating the assembly; and removing the assembly.

10. The method of claim 9, wherein the stripping assembly is activated by removing a removable second protective layer from a surface of a heat pad.

11. The method of claim 10, wherein removal of the second protective layer causes an exothermic chemical reaction in response to exposure of a portion of the heat pad to air.

12. The method according to claim 9, wherein an adhesive material formed on a first surface of an adhesive layer is configured to couple the stripping assembly to the coated metal substrate.

13. The method according to claim 9, wherein the chemical paint remover is a hazardous air pollutant (HAP) free chemical composition.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The subject matter, which is regarded as the invention, is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:

[0019] FIG. 1 is a perspective view of an exemplary rotary wing aircraft embodiment for use with the present invention;

[0020] FIG. 2 is a cross-sectional view of an example of a fuselage including a metal substrate having one or more layers of coating or paint applied thereto;

[0021] FIG. 3 is a cross-sectional view of a paint stripping assembly according to an embodiment of the invention;

[0022] FIGS. 4a and 4b are top and bottom views of the paint stripping assembly in an active state according to an embodiment of the invention; and

[0023] FIG. 5 is method of removing one or more layers of paint or other coating from a surface of a metal substrate;

[0024] The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.

DETAILED DESCRIPTION OF THE INVENTION

[0025] FIG. 1 schematically illustrates an example of a rotary wing aircraft 10 having a main rotor assembly 12. The aircraft 10 includes an airframe 14 having an extending tail 16 which mounts a tail rotor system 18, such as an anti-torque system, a translational thrust system, a pusher propeller, a rotor propulsion system, and the like. The main rotor assembly 12 includes a plurality of rotor blade assemblies 22 mounted to a rotor hub 20. The main rotor assembly 12 is driven about an axis of rotation A through a main gearbox (illustrated schematically at T) by one or more engines E. Although a particular helicopter configuration is illustrated and described in the disclosed embodiment, other configurations and/or machines, such as high speed compound rotary wing aircrafts with supplemental translational thrust systems, dual contra-rotating, coaxial rotor system aircrafts, tilt-rotors and tilt-wing aircrafts, and fixed wing aircrafts, will also benefit from embodiments of the invention.

[0026] An example of a cross-section of a portion of the airframe 14 is illustrated in more detail in FIG. 2. In the illustrated, non-limiting embodiment, a surface treatment layer 24 is formed directly over the metal substrate 23 of the airframe 14. The airframe 14 additionally includes a layer of primer 26 and a layer of topcoat 28 configured to provide the airframe 14 with an aesthetic appearance including a desired color and finish. The cross-section of the airframe 14 illustrated and described herein is intended as an example, and other metal substrates having one or more layers of a variety of coatings or paints are within the scope of the invention.

[0027] Referring now to FIGS. 3 and 4, an assembly 30 for locally removing paint from a designated portion of the airframe 14 of the rotary wing aircraft 10 of FIG. 1 for example, is illustrated. Although the assembly 30 is illustrated and described herein with reference to removing one or more layers of coating or paint from a metal substrate 23 of the airframe 14 of a rotary wing aircraft 10, the assembly 30 may be used to remove coatings from metal surfaces of other large objects including, but not limited to, fixed wing aircrafts, freight cars, and ships for example. A first layer of the assembly 30 includes a pad 32 pre-soaked with chemical paint stripper or paint remover configured to remove one or more layers of paint or another polyurethane or epoxy based coating from a metal substrate. In one embodiment, the chemical is a hazardous air pollutant (HAP) free, such as a hydrogen peroxide based stripper for example. Although the illustrated pad 32 is generally elliptical in shape, the pad 32 may be configured to have any shape and size complementary to a desired portion of the aircraft 10 from which the paint or another coating is intended to be removed.

[0028] Surrounding at least a portion of the pad 32 is an adhesive layer 34. The adhesive layer 34 may have a thickness equal to the pad 32 such that adjacent surfaces of the pad 32 and the adhesive layer 34 are substantially flush. In one embodiment, the adhesive layer 34 includes an opening 36 having a size and shape similar to the pad 32. As shown, the pad 32 may be positioned within the opening 36 such that the adhesive layer 34 protects the periphery of the pad 32 from exposure to air, which may decrease the effectiveness of the chemical solvent or paint remover contained therein. During application of the assembly 30 to an aircraft 10, an adhesive material (not shown) arranged on a first surface 38 of the adhesive layer 34 is configured to contact and adhere to the airframe 14 of the aircraft 10 near the desired portion from which the one or more layers of paint or another coating are to be removed.

[0029] Positioned upwardly adjacent the first surface 38 of the adhesive layer 34 and the first surface 40 of the pad 32 is a removable protective layer 42. In one embodiment, the adhesive material (not shown) on the first surface 38 of the adhesive layer 34 may be used to retain the protective layer 42 in position relative to the assembly 30. The protective layer 42 may be formed from a material, such as plastic for example, that is easily removable from the adhesive material without significantly degrading the adhesion strength of the adhesive material. The protective layer 42 is intended to prevent evaporation of the chemical paint remover within the pad 32 due to exposure to air, prior to the assembly 30 being applied to a portion of an aircraft 10. In addition, the protective layer 42 similarly prevents contamination of the adhesive material configured to couple the assembly 30 to the aircraft 10 during the paint stripping process.

[0030] Positioned adjacent a second, opposite surface 44, 46 of the adhesive layer 34 and the pad 32, respectively, is a support layer 48 formed from a flexible chemical resistant material that is compatible with the chemical solvent stored within the pad 32. Coupled downwardly adjacent the support layer 48 is a heat pad 50. In the illustrated, non-limiting embodiment, the heat pad 50 has a size and shape generally complementary to the pad 32 soaked with chemical solvent or paint remover. A removable activation or protection layer 52 is disposed in contact with a surface 54 of the heat pad 50 opposite the support layer 48. The heat pad 50 is a conventional type of heat pad 50 configured to have an exothermic chemical reaction upon activation, such as by removal of the adjacent protection layer 52. In one embodiment, iron oxidation is configured to occur upon the unsealing and exposure of surface 54 of the heat pad 50 to air. However, heat pads 50 configured to have other types of chemical reactions are within the scope of the invention. Upon activation of the heat pad by removal of the protection layer 52, the heat pad 50 is configured to generate heat for a limited length of time, such as up to about eight hours for example. Inclusion of the heat pad 50 in the assembly 30 is intended to control the temperature and relative humidity of the area as the chemical solvent of pad 32 erodes the one or more layers of paint or coating applied to the metal substrate 23.

[0031] Referring now to FIG. 5, a method 100 of removing one or more layers of paint or another coating from a surface of a metal substrate 23 includes removing the protective layer 42 from the assembly 30, as shown in block 102. In block 104, the assembly 30 is attached to the airframe 14 of the aircraft 10. The exposed first surface 38 of the adhesive layer 34 is attached to a portion of the airframe 14 such that the exposed first surface 40 of the pad 32 is in contact with a desired area from which paint and/or other coatings are intended to be stripped. The assembly 30 is then activated, in block 106, by removing the protection layer 52 from the surface 54 of the heat pad 50, thereby exposing the heat pad 50 to the ambient air. Activation of the heat pad 50 allows the chemical paint remover within the pad 32 to interact with the paint at an elevated temperature. The activated assembly 30 remains attached to the aircraft 10 for a desired period of time, generally no longer than two hours.

[0032] While the activated assembly 30 is attached to the aircraft 10, the chemical solvent penetrates through the one or more layers of coating or paint applied to the metal substrate 23. Upon reaching the metal substrate, the chemical solvent breaks down the bonds extending between the metal substrate and an adjacent layer of coating or paint to dissociate the paint from the metal substrate. After sufficient time, the assembly 30 is removed from the surface of the aircraft 10, in block 108. In block 110, the swollen portion of the one or more layers of paint that were arranged in contact with the pre-soaked pad 32 are removed, such as by scraping for example, to expose the metal substrate 23 of the aircraft 10.

[0033] The assembly 30 described herein more efficiently removes one or more layers of paint or another coating from a desired portion of a metal substrate 23 by controlling the microclimate of the desired area. More specifically, the assembly 30 is configured to control the local temperature, the ambient temperature, the ambient airflow, the relative humidity, and the effective concentration of the chemical solvent. As a result, a single assembly 30 is sufficient to remove the one or more layers of paint from a metal substrate 23, and no reapplication of the chemical solvent is necessary. The improved control provided by the assembly 30 allows for easy application of the chemical solvent to the desired area while minimizing waste, such as of the chemical solvent and masking materials, and the risk of contact or exposure to the chemical solvent. In addition, the assembly 30 acts as a masking agent to prevent the chemical paint stripper from affecting adjacent areas.

[0034] While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.