A spray coating system and method for abrasion-resistant coating on aircraft cockpit windshields.

Abstract

This invention relates to a field application system and method for applying a wear-resistant coating to aircraft cockpit windshields, belonging to the field of aircraft maintenance technology. The invention includes a mobile cleanroom, an environmental control system, and a platform operating component. The bottom of the mobile cleanroom is supported and driven by an AGV (Automated Guided Vehicle). The main body of the mobile cleanroom is a hexahedral shell constructed from multiple cleanroom panels and multiple anti-static acrylic panels. Openings for aircraft passage are provided on the front and rear sides, and front and rear face shields are sealed and connected to them respectively. The environmental control system includes at least one fresh air FFU (Fan-Full Unit) air purifier and multiple return air FFUs installed on the inner side of the top of the mobile cleanroom. The operating platform component includes multiple heavy-duty slide rails laid on the inner bottom surface of the mobile cleanroom, and a telescopic worktable slidably mounted on the heavy-duty slide rails. This invention enables direct and efficient strengthening treatment of windshield surfaces under field conditions.

Description

Technical Field

[0001] This invention belongs to the field of aircraft maintenance technology, and specifically relates to a field aircraft cockpit windshield wear-resistant coating spraying system and spraying method. Background Technology

[0002] When military and some civilian aircraft perform missions in areas with severe sandstorms, the surface of their cockpit windshields is subjected to continuous impact and abrasion from high-speed sand particles. This abrasion causes dense micro-scratches to form on the glass surface in a short period of time, resulting in fogging or frosted glass appearance. This severely reduces light transmittance and increases light scattering, directly affecting the pilot's visual clarity and situational awareness, thus posing a flight safety hazard.

[0003] Currently, the conventional solutions to this problem are localized polishing repair or complete windshield replacement. However, the former offers only temporary relief and may alter the glass's optical properties, while the latter is costly, requires prolonged grounding, and does not enhance the glass substrate's resistance to abrasion, leading to recurring issues. Therefore, there is an urgent need for a technology that can directly and efficiently strengthen the windshield surface under outdoor conditions to fundamentally improve its service life and reliability. Summary of the Invention

[0004] This invention addresses the aforementioned problems and overcomes the shortcomings of existing technologies by providing a field-grade aircraft cockpit windshield wear-resistant coating coating system and method. This invention enables direct and efficient strengthening of the windshield surface under field conditions, fundamentally improving its service life and reliability.

[0005] To achieve the above objectives, the present invention adopts the following technical solution.

[0006] This invention provides a field application system for abrasion-resistant coating on aircraft cockpit windshields, comprising a mobile cleanroom, an environmental control system, and a work platform assembly. The bottom of the mobile cleanroom is supported and driven by an AGV (Automated Guided Vehicle). The main body of the mobile cleanroom is a hexahedral shell constructed from multiple cleanroom panels and multiple antistatic acrylic panels. The left, right, top, and bottom sides are composed of cleanroom panels, while the front and rear sides are composed of antistatic acrylic panels. The front and rear sides have openings for aircraft to pass through, each sealed with a front and rear shielding mask. The environmental control system includes components installed on the mobile cleanroom... The cleanroom includes at least one fresh air FFU air purifier and multiple return air FFU air purifiers on the inner side of the top, as well as an air conditioner, infrared radiation panel, temperature control box, and constant humidity humidifier installed inside the mobile cleanroom; the work platform assembly includes multiple heavy-duty slide rails laid on the bottom surface inside the mobile cleanroom, and a telescopic worktable slidably mounted on the heavy-duty slide rails; wherein, the front and rear face shields are configured for sealing and bonding with the aircraft fuselage, and the telescopic worktable is configured to move along the slide rails to avoid or approach the aircraft, thereby jointly achieving rapid docking and sealing between the mobile cleanroom and the aircraft.

[0007] Furthermore, the environmental control system also includes a return air vent that is connected to the air inlet of the return air FFU air purifier through a duct. An electrostatic dust collector is installed at the return air vent. The environmental control system also includes a dust particle counter installed on the outer wall of the mobile clean room and an environmental monitoring dashboard for displaying environmental parameters.

[0008] Furthermore, the telescopic worktable in the work platform assembly is equipped with feet for positioning and securing it on heavy-duty slide rails.

[0009] Furthermore, it also includes auxiliary facilities, including a protective cage ladder fixed to the outside of the side wall of the mobile cleanroom, a maintenance access cover opened on the top of the mobile cleanroom, an air shower and emergency exit opened on the side wall of the mobile cleanroom, a power distribution box and air compressor interface installed on the side wall of the mobile cleanroom, and a cleanroom light installed on the inner ceiling wall of the mobile cleanroom.

[0010] Furthermore, the cleanroom panel is a composite panel with color-coated steel plate, stainless steel or aluminum alloy as the face material, and anti-static acrylic plate as the polymethyl methacrylate plate with an anti-static film coated on the surface. The front and rear face masks are made of polypropylene material.

[0011] Furthermore, it also includes adhesive preparation equipment and cleaning equipment installed outside the mobile cleanroom. The adhesive preparation equipment is used to mix J-484 protective coating, and the cleaning equipment is used to clean the construction area floor, aircraft fuselage, and mobile cleanroom.

[0012] The present invention also provides a method for applying a wear-resistant coating to an aircraft cockpit windshield using the above-mentioned coating system, and the method includes the following steps:

[0013] S1. Equipment docking and environment construction: Operate the AGV unmanned transport vehicle to move the mobile clean room to dock with the aircraft. After the aircraft passes through, seal and bond the front and rear face shields to the fuselage. Then start the environmental control system to construct and maintain a closed working environment with a temperature of 23℃~28℃, humidity ≤50%, and cleanliness level of 100,000.

[0014] S2. Process verification test: In the clean room, near the windshield, the test panel is coated with a spray coating; after the test panel is coated, it is placed for 24 hours and checked to confirm that the coating appearance is smooth, the number of dust and particles on the surface is less than or equal to 2, and the light transmittance is ≥90% and the haze is <3.

[0015] S3. Aircraft fuselage and windshield edge protection: The aircraft fuselage is covered with a polytetrafluoroethylene film. For the leading edge of the windshield, the protective film is sealed with masking tape and high-viscosity hot melt adhesive. Rubber strips are pasted on both sides of the windshield to form airflow channels, and tape, polyethylene film and high-viscosity hot melt adhesive are used for airflow guidance and sealing. For the rear arc of the windshield at the edge of the cockpit frame, tape is pasted on the glass surface and gaps are left. Primer is applied to the gaps.

[0016] S4. Windshield surface pretreatment: The windshield glass is polished to ensure that its surface is free of defects. Then the glass surface is cleaned and dust and static electricity are removed using an electrostatic blower.

[0017] S5. Adhesive preparation and pouring / coating: Prepare the J-484 protective coating to a viscosity of 1300cps to 5300cps. Using the side of the windshield with the larger area as the main viewing surface, start pouring and coating from the lowest points on both sides of the rear arc of the windshield upwards simultaneously. Control the coating speed of the auxiliary viewing surface to be slightly faster than that of the main viewing surface. After the coating on both sides flows through the center line of the windshield, fill in the uncovered areas. Then change the coating direction to move from the rear arc of the windshield to the front edge of the windshield. By controlling the pouring path, the coating is made to be continuously and evenly distributed on the glass surface by gravity.

[0018] S6. Coating Curing and Final Treatment: After coating, place the windshield at 23℃~28℃ for 48 hours, then cure it at 45℃~55℃ for 48 hours using an infrared radiation plate and a temperature control chamber. Remove all protective materials, clean the high-viscosity hot melt adhesive, and fill the gap between the edge of the windshield and the edge of the aircraft cockpit frame with the original aircraft sealant. Finally, the coating coverage area of ​​the windshield is complete. Visual inspection shows that there are no bubbles, impurities, or flow marks on the windshield surface, and the windshield transmittance is ≥90% and the haze is <3. The coating work is then complete.

[0019] Furthermore, in step S3, the height of the rubber strips pasted on both sides of the windshield is 50mm, and a waste bag is placed at the bottom of its guide groove. When protecting the rear arc of the windshield, the reserved gap width is 1mm to 3mm.

[0020] Furthermore, in step S2, the test plate is an acrylic plate placed at a 30° angle.

[0021] Furthermore, in step S6, after filling with the original sealant, the width of the sealant coverage area formed on the edge of the windshield is 7mm to 8mm.

[0022] The beneficial effects of this invention are:

[0023] This invention enables the application of wear-resistant coatings to aircraft windshields with large or multiple curvatures under limited outdoor conditions. The mobile cleanroom, equipped with FFU air filters, air conditioning, infrared radiation panels, temperature control boxes, and humidifiers, can adjust the temperature and humidity of the clean environment to the values ​​required for the coating process, unaffected by external or natural factors, thus improving practicality and applicability. After the wear-resistant coating is applied, the windshield's resistance to wind and sand abrasion is greatly improved, extending its service life and reducing the cost of windshield maintenance and replacement. Attached Figure Description

[0024] To make the technical problems solved, the technical solutions, and the beneficial effects of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

[0025] Figure 1 This is a schematic diagram of the external structure of the coating system of the present invention during operation.

[0026] Figure 2 This is a schematic diagram of an axial structure of the coating system of the present invention.

[0027] Figure 3 This is a schematic diagram of another axial structure of the coating system of the present invention.

[0028] Figure 4 This is a schematic diagram of the internal structure of the coating system of the present invention.

[0029] Figure 5 This is another internal structural diagram of the coating system of the present invention.

[0030] Figure 6 This is a schematic diagram of an aircraft windshield structure that has not undergone coating in the coating method of the present invention.

[0031] Figure 7 This is a schematic diagram of the aircraft windshield structure after coating in the coating method of the present invention.

[0032] Figure 8 This is a schematic diagram of the initial state of the retractable platform of the mobile cleanroom in the spray coating method of the present invention.

[0033] Figure 9 This is a schematic diagram of the working state of the extendable platform of the mobile cleanroom in the spray coating method of the present invention.

[0034] Figure 10 This is a schematic diagram of the rubber strips and waste bags on both sides of an aircraft windshield at one angle in the coating method of the present invention.

[0035] Figure 11 This is a schematic diagram of the rubber strips and waste bags on both sides of the aircraft windshield from another angle in the coating method of the present invention.

[0036] The markings in the diagram are as follows: 1 is a mobile cleanroom, 2 is adhesive preparation equipment, 3 is cleaning equipment, 4 is a maintenance access cover, 5 is an anti-static acrylic sheet, 6 is a rear-mounted mask, 7 is an AGV (Automated Guided Vehicle), 8 is a protective cage ladder, 9 is a cleanroom panel, 10 is an environmental monitoring dashboard, 11 is an air shower, 12 is an emergency exit, 13 is a power distribution box, 14 is an air compressor interface, 15 is an air duct, 16 is a front-mounted mask, 17 is a fresh air FFU (Frequency Unit) air purifier, 18 is an air conditioner, 19 is a temperature control box, and 20 is a telescopic workbench. 21 is an infrared radiation panel; 22 is a return air FFU air purifier; 23 is a dust particle counter; 24 is a constant humidity humidifier; 25 is a return air vent electrostatic dust collector; 26 is a cleanroom lamp; 27 is a rubber strip; 28 is the front edge of the windshield; 29 is the two sides of the windshield; 30 is the rear arc of the windshield; 31 is the area covered by sealant; 32 is the edge of the cockpit frame; 33 is the area covered by paint; 34 is the work surface; 35 is a heavy-duty slide rail; 36 is a foot support; 37 is a waste bag; 38 is the boundary line of the radome. Detailed Implementation

[0037] Combined with appendix Figure 1 -Appendix Figure 11As shown, this embodiment provides a wear-resistant coating system for aircraft cockpit windshields, including a mobile cleanroom 1. The bottom of the mobile cleanroom 1 is supported and driven by an AGV (Automated Guided Vehicle) 7, enabling flexible movement and precise positioning. The main body of the mobile cleanroom 1 is a hexahedral shell, with its left, right, top, and bottom four sides constructed from cleanroom panels 9, and its front and rear sides constructed from antistatic acrylic panels 5. The cleanroom panels 9 are composite panels made of materials such as color-coated steel, stainless steel, or aluminum alloy, possessing dustproof, antistatic, fireproof, and moisture-proof properties. The antistatic acrylic panels 5 are made of PMMA (polymethyl methacrylate), with a light transmittance of over 90%. Through coating technology, they retain high light transmittance while also possessing antistatic properties, high hardness, good gloss, and excellent high-temperature performance. Openings for aircraft passage are opened in the center of the front and rear antistatic acrylic panels 5, and front and rear beam shields 16 and 6 are respectively sealed and connected. The front and rear face shields 16 and 6 are made of polypropylene (PP) material, which is non-toxic, odorless, transparent, lightweight, and has good wear resistance, antibacterial properties, and high-temperature resistance, allowing it to be used in environments above 100°C. The front and rear face shields 16 and 6 are used to tightly adhere to the aircraft fuselage after the system is docked with the aircraft, ensuring a tight seal between the mobile cleanroom 1 and the aircraft fuselage and effectively preventing external contaminants from seeping in.

[0038] The mobile cleanroom 1 integrates an environmental control system, which includes at least one fresh air FFU air purifier 17 and three return air FFU air purifiers 22 installed on the inner side of the top of the mobile cleanroom 1. The fresh air FFU air purifier 17 continuously introduces and purifies fresh air from outside the cleanroom to maintain positive pressure. The return air FFU air purifiers 22 are connected to return air vents located at the bottom of the cleanroom via air ducts 15 to circulate and purify the internal air. Return air vent electrostatic precipitators 25 are installed at the return air vents for continuous purification.

[0039] The environmental control system ensures that the air cleanliness inside the mobile cleanroom 1 reaches Class 100,000 (i.e., 0.5μm dust particle concentration ≤ 3,520,000 pc / m³). A dust particle counter 23 is installed at the outer entrance of the mobile cleanroom 1 for real-time monitoring of cleanliness, and the monitoring data is displayed in real-time on the environmental monitoring dashboard 10. The environmental control system also includes an air conditioner 18, an infrared radiation panel 21, a temperature control box 19, and a constant humidity humidifier 24 installed inside the mobile cleanroom 1 to control the ambient temperature at 23℃~28℃ and the humidity at ≤50%.

[0040] The mobile cleanroom 1 also includes a work platform assembly, comprising four heavy-duty slide rails 35 laid on the bottom surface of the mobile cleanroom 1, and a telescopic worktable 20 slidably mounted on the heavy-duty slide rails 35. The telescopic worktable 20 is made of cold-rolled steel, possessing high load-bearing capacity to ensure operator safety. During docking of the mobile cleanroom 1 with the aircraft, the telescopic worktable 20 can be moved to either side of the cleanroom, ensuring sufficient space in the center for the aircraft to pass and preventing collisions. After docking is complete, the telescopic worktable 20 is moved back towards the center, ensuring the gap between the worktable and the aircraft is no more than 10cm to prevent personnel from falling, and is secured with foot supports 36.

[0041] In addition, the mobile cleanroom 1 is equipped with complete auxiliary facilities. The side panels of the mobile cleanroom 1 are fitted with protective ladders 8, and the top is fitted with a maintenance access cover 4, facilitating personnel access for inspection and maintenance. An air shower 11 is located on the side wall of the mobile cleanroom 1 to remove dust adhering to personnel and carried items; an emergency exit 12 is also provided for rapid entry and exit in emergencies. A power distribution box 13 is installed on the side wall of the mobile cleanroom 1, which can be connected to external AC power to supply power to all internal equipment. An air compressor interface 14 is also installed on the side wall of the mobile cleanroom 1, which can be connected to an external air compressor to provide air for pneumatic tools such as electrostatic blow guns. Cleanroom lights 26 are installed on the interior ceiling of the mobile cleanroom 1 for internal lighting.

[0042] The mobile cleanroom 1 is externally equipped with adhesive preparation equipment 2 and cleaning equipment 3. Adhesive preparation equipment 2 is mainly used for precise metering, mixing, degassing, and viscosity monitoring of the J-484 protective coating, ensuring that the prepared adhesive components are accurate and uniform, and reach the viscosity range required for spray coating. Cleaning equipment 3 is mainly used for cleaning the hangar floor, aircraft fuselage surface, and mobile cleanroom 1 during the initial construction phase to remove dust, oil, and other contaminants, creating a clean substrate environment for subsequent spray coating.

[0043] This embodiment also provides a method for applying a wear-resistant coating to an aircraft cockpit windshield using the above-mentioned coating system, specifically including the following steps:

[0044] S1. Construction Preparation and Environmental Setup

[0045] First, remove the corner pieces that obstruct the windshield from the aircraft, fully exposing the windshield. Grind and polish the windshield under natural light to ensure its surface is free of dents, cracks, or other defects, preventing run marks during the coating process. Simultaneously, clean the existing sealant from the gaps between the windshield and the aircraft fuselage.

[0046] Subsequently, inside the outdoor hangar, the hangar doors and windows were closed, and cleaning equipment 3 was used to clean the construction site floor, and water was sprayed to keep the floor moist to prevent dust.

[0047] Next, the AGV (Automated Guided Vehicle) 7 is operated to align the mobile cleanroom 1 with the centerline of the aircraft until its front end is flush with the boundary line 38 of the aircraft's radome, allowing the aircraft to pass through the mobile cleanroom 1. After the mobile cleanroom 1 is docked with the aircraft, the front and rear face shields 16 and 6 are sealed and bonded to the aircraft fuselage to ensure the airtightness of the cleanroom environment.

[0048] Connect 380V AC power to distribution box 13 to power the system. In summer, turn on air conditioner 18; in winter, turn on infrared radiation panel 21 and temperature control box 19, simultaneously turning on humidifier 24, fresh air FFU air purifier 17, and return air FFU air purifier 22. Read the current ambient temperature, humidity, and cleanliness status on the environmental monitoring dashboard 10. The control system precisely controls the ambient temperature between 23℃ and 28℃, humidity to ≤50%, and ensures a cleanliness level of 100,000.

[0049] S2. Process Validation Test

[0050] Operators wearing cleanroom suits enter cleanroom 1 through air shower 11. They climb the stairs to the telescopic workbench 20, push the workbench surface 34 along the heavy-duty slide rail 35 to a position close to the aircraft fuselage, and use two foot supports 36 to fix the workbench surface in place.

[0051] To verify that the construction environment meets the requirements for spray coating, a test piece of acrylic sheet (500mm × 600mm × 7mm thick) was prepared as the test board. It was placed on the workbench surface 34 at a 30° angle, consistent with the tilt angle of the windshield. A waste tray was placed under the test board. The adhesive was prepared according to the J-484 protective coating usage specification. After the adhesive viscosity reached the range of 1300 cps to 5300 cps, the acrylic sheet was spray-coated.

[0052] After 24 hours of drying, check that the surface is smooth, with no more than 2 dust particles, and meets the optical requirements of ≥90% light transmittance and <3 haze. If the test is passed, the formal drying process can begin.

[0053] S3. Aircraft fuselage and windshield edge protection

[0054] Before the formal coating process, the aircraft must be thoroughly protected. Cleaning equipment 3 should be used to clean and wipe the aircraft fuselage and the interior of the cleanroom. Except for the windshield area, a polytetrafluoroethylene film should be used to completely cover and protect the aircraft fuselage to prevent the coating adhesive from splashing, flowing, and contaminating the fuselage.

[0055] Differentiated protection measures are implemented for different structures around the windshield:

[0056] Windshield Side Protection 29: Along both sides 29 of the windshield, use butyl tape to attach 50mm high rubber strips 27 as guide channels for the adhesive coating. Place waste bags 37 at the bottom of the guide channels to collect waste. Cut a piece of polyethylene film 200mm wide and approximately 1200mm long as the guide surface, and use tape to attach one long side of it to the windshield surface, approximately 2mm-3mm from the edge 32 of the cockpit frame. Leave a 1mm-2mm gap at the edge of the tape, apply high-viscosity hot melt adhesive to this gap and the tape, smooth it out to form a seal, preventing the adhesive coating from flowing onto the aircraft fuselage.

[0057] Windshield Rear Curve 30 Protection: Cover the cockpit frame edge 32 with transparent tape at the rear curve 30 of the windshield, extending 2mm-3mm to the glass surface. Then, apply a layer of masking tape flush with the transparent tape, and apply protective tape underneath, leaving a 1mm-3mm gap between the masking tape and the protective tape. Apply a 1:1 mixture of primer and a brush to this gap. After application, remove the masking tape and wait approximately 3 hours before removing the protective tape. Finally, wipe the glass surface with alcohol for later use.

[0058] Windshield leading edge 28 protection: At the windshield leading edge 28, use masking tape to directly stick polyethylene film to the edge 32 of the cockpit frame, then apply high-viscosity hot melt adhesive to the edge of the masking tape and smooth it out for sealing.

[0059] S4. Windshield Pretreatment

[0060] Polish the windshield to ensure a defect-free surface. Clean the windshield with purified water, then connect the electrostatic blow gun to the air compressor interface 14 to thoroughly remove dust and static electricity from the windshield surface to prevent static electricity from attracting dust and causing defects after coating.

[0061] S5. Adhesive preparation and pouring / coating

[0062] Using adhesive preparation equipment 2, prepare a sufficient amount of J-484 protective coating according to the specifications, monitor the adhesive reaction, and start the spray coating operation when the viscosity reaches the range of 1300cps to 5300cps.

[0063] To address the characteristics of the cockpit windshield with its large and multiple curvatures, a casting process is employed. The side of the windshield with the larger coating area serves as the primary viewing surface, while the other side becomes the secondary viewing surface.

[0064] During the coating process, two operators simultaneously begin coating upwards from the lowest points on both sides of the rear arc 30 of the windshield (i.e., coating from bottom to top along the rear arc). The coating speed on the secondary viewing surface is controlled to be slightly faster than that on the primary viewing surface. The coating on the secondary viewing surface is paused after it has slightly crossed the center line of the glass. Once the coating on the primary viewing surface has also flowed past the center line, the secondary operator applies coating to any areas where the coating has not yet reached. The primary viewing surface is then coated again at the center line after the secondary viewing surface has crossed it.

[0065] After reaching the centerline, the coating direction changes to move from the rear arc 30° of the windshield towards the front edge 28°. The operator must observe the flow of the adhesive on the complex curved surface and adjust the coating position accordingly. By controlling the pouring path, the coating should flow continuously and evenly across all areas of the windshield's main and secondary viewing surfaces under gravity. If there are areas on the main viewing surface that have not been coated up to the front of the windshield, additional coating is required, starting from the point where the adhesive branches off.

[0066] If obvious defects such as bubbles, impurities, or flow marks are found on the surface of the windshield during the coating process, the adhesive must be wiped off with alcohol immediately and the coating operation should be repeated.

[0067] S6. Coating Curing and Final Treatment

[0068] After the windshield is coated, maintain the ambient temperature at 23℃~28℃ and the humidity at ≤50% and let it stand for 48 hours. After 48 hours, turn on the infrared radiation plate 21 and the temperature control box 19 to control the temperature of the windshield at 45℃~55℃ and continue to cure for another 48 hours.

[0069] After curing, remove all protective PTFE films, rubber strips 27, etc. Clean up the high-viscosity hot melt adhesive used for sealing, which is easy to remove. After removal, fill the original adhesive used on the aircraft windshield in the original location (i.e., the gap between the edge of the windshield and the edge of the cockpit frame 32) to form a sealant-covered area 31.

[0070] Finally, a visual inspection of the windshield surface should reveal no obvious defects such as bubbles, impurities, or flow marks. Figure 7 As shown, the sealant-covered area 31 extends 7mm to 8mm from the edge 32 of the cockpit frame on both sides 29 and the rear arc of the windshield. The protective coating-covered area 33 completely covers the exposed part of the windshield. Visual inspection of the windshield surface should reveal no obvious defects such as bubbles, impurities, or flow marks, and it should meet the requirements of a windshield light transmittance ≥90% and a haze <3.

[0071] With this, the entire process of applying the abrasion-resistant coating to the aircraft cockpit windshield is complete. This method significantly improves the windshield's resistance to wind and sand abrasion, extending its service life.

[0072] It is understood that the above specific description of the present invention is only for illustrating the present invention and is not limited to the technical solutions described in the embodiments of the present invention. Those skilled in the art should understand that modifications or equivalent substitutions can still be made to the present invention to achieve the same technical effect; as long as the use needs are met, they are all within the protection scope of the present invention.

Claims

1. A method of applying a wear resistant coating to an outboard aircraft windshield, the method comprising: The method includes the following steps: S1. Equipment docking and environment construction: The bottom of the mobile clean room (1) is supported and driven by the AGV unmanned transport vehicle (7). The mobile clean room (1) has openings on the front and rear sides for the aircraft to pass through and is respectively sealed with a front beam mask (16) and a rear beam mask (6). The AGV unmanned transport vehicle (7) is operated to move the mobile clean room (1) to dock with the aircraft. After the aircraft passes through, the front beam mask (16) and the rear beam mask (6) are sealed and bonded to the fuselage. Then the environmental control system is started to construct and maintain a closed working environment with a temperature of 23℃~28℃, humidity ≤50%, and cleanliness level of 100,000. S2. Process verification test: The test board is coated with a spray coating near the windshield glass inside the mobile clean room (1); after the test board is coated, it is placed for 24 hours and the coating is checked to confirm that the coating is smooth, the surface dust and the number of particles are less than or equal to 2, and the light transmittance is ≥90% and the haze is <3. S3. Protection of aircraft fuselage and windshield edges: The aircraft fuselage is covered with polytetrafluoroethylene film. For the leading edge of the windshield (28), masking tape and high-viscosity hot melt adhesive are used to seal the protective film. For both sides of the windshield (29), rubber strips (27) are pasted to form a guide channel. Tape, polyethylene film and high-viscosity hot melt adhesive are used for guidance and sealing. For the rear arc of the windshield (30), tape is pasted on the glass surface at the edge (32) of the cockpit frame and a gap is reserved. The primer is applied in the gap. S4. Windshield surface pretreatment: The windshield glass is polished to ensure that its surface is free of defects. Then the glass surface is cleaned and dust and static electricity are removed using an electrostatic blower. S5. Adhesive preparation and pouring / coating: Prepare the protective coating to a viscosity of 1300cps to 5300cps. Take the side with the larger area of ​​the windshield as the main viewing surface. Start pouring and coating from the low points on both sides of the rear arc (30) of the windshield at the same time. Control the pouring speed of the auxiliary viewing surface to be slightly faster than that of the main viewing surface. After the coating on both sides flows through the center line of the windshield, they will fill in the uncovered areas. Then change the pouring direction to move from the rear arc (30) of the windshield to the front edge (28) of the windshield. By controlling the pouring path, the coating can be continuously and evenly distributed on the glass surface by gravity. S6. Coating curing and final treatment: The mobile clean room (1) is equipped with an infrared radiation plate (21) and a temperature control box (19). After coating, it is placed in an environment of 23℃~28℃ for 48 hours. Then, the temperature of the windshield is controlled at 45℃~55℃ for 48 hours through the infrared radiation plate (21) and the temperature control box (19). All protective materials are removed, the high viscosity hot melt adhesive is cleaned, and the gap between the edge of the windshield and the edge of the aircraft cabin frame (32) is filled with the original sealant of the aircraft. Finally, the coating coverage area (33) of the windshield is complete. Visual inspection shows that there are no bubbles, impurities, or flow marks on the surface of the windshield. The windshield transmittance is ≥90% and the haze is <3. Then the coating work is completed.

2. A method of applying a wear resistant coating to an outboard aircraft windshield glass according to claim 1, wherein, In step S3, the height of the rubber strip (27) pasted on both sides (29) of the windshield is 50mm, and a waste bag (37) is set at the bottom of its guide groove to protect the rear arc (30) of the windshield. The width of the reserved gap is 1mm to 3mm.

3. A method of applying a wear resistant coating to an outboard aircraft windshield glass according to claim 1, wherein, In step S2, the test plate is an acrylic plate placed at a 30° angle.

4. A method of applying a wear resistant coating to an outboard aircraft windshield glass according to claim 1, wherein, In step S6, after filling with the original sealant, the width of the sealant-covered area (31) formed on the edge of the windshield is 7mm to 8mm.

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