Embedded additive repairing method and structure for damage of transparent part of large-curvature aircraft canopy

Abstract

The invention discloses an embedded additional material repairing method and structure for damage of a transparent part of a large-curvature aircraft canopy, and relates to a rapid repairing method for damage of an aircraft canopy. The method specifically comprises the following steps that a damaged area on an organic glass canopy is removed, a hole is polished, and the hole is inwards polished to form an embedded groove; a flexible inner baffle is attached to the inner side of the organic glass canopy to shield the hole, the hole is filled with repairing filler, and a flexible outer baffle is attached to the outer side of the organic glass canopy to shield the hole; and the hole area filled with the repairing filler is heated, cooling is conducted after heating, and the repairing filler is cooled, cured and formed. The large-curvature aircraft canopy transparent part damage embedded type additive repairing structure is repaired and formed through the large-curvature aircraft canopy transparent part damage embedded type additive repairing method. According to the method, the problems that the complex damage shape repairing adaptability of the large-curvature canopy is poor, the view field of the repaired rear seat canopy is limited, and the local strength is reduced are solved.

Description

Technical Field

[0001] The invention relates to a rapid repair method for damaged aircraft canopy, and more particularly to an in-situ embedded rapid material addition repair method and structure for damaged transparent parts of a large-curvature aircraft canopy. Background Art

[0002] The aircraft canopy is mainly composed of a canopy frame and transparent plexiglass parts. It is very vulnerable to external attacks when serving in the field, causing holes, scratches and other damage, causing the cabin to be leaked, endangering flight safety and mission support. In order to effectively ensure the continuous generation of combat effectiveness, it is necessary to perform temporary and rapid repairs on the canopy damage in the field, so that the aircraft has the ability to transfer or continue to fight.

[0003] The invention patent application with publication number CN114851603A discloses a method for repairing a damaged plexiglass hole in a canopy of an outdoor aircraft. The method uses a plexiglass patch combined with a reinforced patch to repair the damaged canopy. The plexiglass patch is bonded to the original canopy with an adhesive and cured by in-situ heating. The repair process takes several hours.

[0004] Wang Dingjiang et al. disclosed a rapid repair process for damaged transparent parts of aircraft canopies in the 2014 "Proceedings of the Academic Seminar on Aviation Safety and Equipment Maintenance Technology" on pages 809-813. This method uses a special hole-breaking milling tool to remove damage and manufacture corresponding inlay patches. A special adhesive is developed to bond the inlay patches. This method takes 50 minutes to repair damage.

[0005] Both of the above methods involve the production of patches of specific shapes, have limited adaptability to the shape of hole damage, and rely on repair adhesives for bonding. It is difficult to achieve the original cockpit cover performance after repair, and the cockpit cover field of view is affected to a certain extent.

[0006] Therefore, in order to meet the repair requirements of complex damage of large curvature canopy, improve the performance of the canopy after repair, restore the field of view of the damaged area of ​​the canopy, shorten the field structure repair time, simplify the operation process, and improve the support capability, it is necessary to develop a new type of damage repair method for transparent parts of large curvature aircraft canopy. Summary of the invention

[0007] In view of this, the present invention provides an embedded additive repair method and structure for damaged transparent parts of a large-curvature aircraft canopy, aiming to solve the above-mentioned technical problems.

[0008] In order to achieve the above object, the present invention adopts the following technical solution:

[0009] A method for repairing damaged transparent parts of a large-curvature aircraft canopy by embedded additive methods specifically comprises the following steps:

[0010] Remove damaged areas on the plexiglass canopy and grind holes inward to create recessed grooves;

[0011] A flexible inner baffle is attached to the inner side of the plexiglass canopy to cover the hole, a repair filler is filled into the hole, and a flexible outer baffle is attached to the outer side of the plexiglass canopy to cover the hole;

[0012] The hole area filled with the repair filler is heated, and then cooled, so that the repair filler is cooled and solidified into shape.

[0013] Through the above technical scheme, the present invention provides an in-situ rapid additive repair method suitable for damaged transparent parts of a canopy of an aircraft with large curvature. The in-situ rapid additive repair is performed by repair fillers, and damage repair of any shape can be achieved. A flexible inner baffle and a flexible outer baffle are used to fit the surface of the canopy, which can not only achieve fitting with the surface of the canopy with large curvature, but also enhance the convenience of operation. An embedded repair hole is used to form a mosaic structure between the repaired part and the damaged canopy, thereby improving the mechanical properties of the repair structure and solving the problems of adaptability to repair of complex damage shapes of canopies with large curvature, limited field of view of the canopy after repair, and reduced local strength.

[0014] Preferably, in the above-mentioned embedded additive repair method for damaged transparent parts of a large-curvature aircraft canopy, the ratio of the depth of the embedded groove to the thickness of the plexiglass canopy is between 1:1 and 1:2.

[0015] Preferably, in the above-mentioned embedded additive repair method for damaged transparent parts of a large-curvature aircraft canopy, during the process of grinding the holes, a dust leak-proof bag is made around the inner side of the damaged area on the plexiglass canopy using sealant and vacuum bag film.

[0016] Preferably, in the above-mentioned embedded additive repair method for damaged transparent parts of a large-curvature aircraft canopy, in the process of bonding the flexible inner baffle plate and the flexible outer baffle plate, the flexible inner baffle plate and the flexible outer baffle plate are squeezed so that the gap between the inner and outer surfaces of the flexible inner baffle plate and the plexiglass canopy is controlled between 0.2 mm and 0.5 mm.

[0017] Preferably, in the above-mentioned embedded additive repair method for damaged transparent parts of a large-curvature aircraft canopy, a heat repair device is used to heat the hole area filled with plexiglass powder on the inner side of the plexiglass canopy.

[0018] Preferably, in the above-mentioned embedded additive repair method for damaged transparent parts of a large-curvature aircraft canopy, before the hot patching device works, a vacuum bag is made in the action area of ​​the hot patching device and on the outside of the flexible outer baffle, and the inner and outer vacuum bags are evacuated at the same time before hot patching is performed.

[0019] Preferably, in the above-mentioned embedded additive repair method for damaged transparent parts of a large-curvature aircraft canopy, the inner and outer vacuum bags are evacuated to -0.9 Bar.

[0020] Preferably, in the above-mentioned embedded additive repair method for damaged transparent parts of a large-curvature aircraft canopy, the flexible inner baffle plate and the flexible outer baffle plate are both made of silicone rubber, and the repair filler is organic glass powder.

[0021] Preferably, in the above-mentioned embedded additive repair method for damaged transparent parts of a large-curvature aircraft canopy, a heat repair device is used to heat the plexiglass powder, firstly raising the temperature to 100°C and maintaining it for 1 hour, and then cooling it to 60°C and maintaining it for half an hour.

[0022] Preferably, in the above-mentioned embedded additive repair method for damaged transparent parts of a large-curvature aircraft canopy, the vacuum bag, the heat repair instrument, the flexible inner baffle and the flexible outer baffle are removed, and the organic glass powder repair filler is polished and solidified.

[0023] Preferably, in the above-mentioned embedded additive repair method for damaged transparent parts of a large-curvature aircraft canopy, the sealing condition of the repaired canopy is detected by nitrogen pressurization, and the recovery of the optical performance of the cabin is detected by silver streaks.

[0024] The present invention also provides a structure for repairing a damaged transparent part of a large-curvature aircraft canopy by using an embedded additive material repairing method for repairing a damaged transparent part of a large-curvature aircraft canopy.

[0025] It can be seen from the above technical solutions that, compared with the prior art, the present invention discloses a method and structure for repairing damaged transparent parts of a large-curvature aircraft canopy by embedded additive methods, which have the following beneficial effects:

[0026] 1. Adaptability: This method is suitable for repairing damage to transparent parts of large-curvature aircraft canopies and can adapt to the repair requirements of complex damage shapes.

[0027] 2. Improve performance: After repair, the performance of the canopy can be restored, including mechanical and optical properties, solving the problems of limited field of view and reduced local strength of the canopy after repair.

[0028] 3. Shorten repair time: It provides a quick repair method, simplifies the operation process, and improves the efficiency of field structure repair.

[0029] 4. Convenience of operation: The flexible inner baffle and the flexible outer baffle are used to fit the surface of the canopy, which enhances the convenience of operation and achieves the fit with the surface of the canopy with large curvature.

[0030] 5. Repair of damage of any shape: Using plexiglass powder as a repair filler for in-situ rapid additive repair can achieve repair of damage of any shape.

[0031] 6. Improving the mechanical properties of the repair structure: It is proposed to use embedded repair holes to form a mosaic structure between the repaired part and the damaged cockpit cover, thereby improving the mechanical properties of the repair structure.

[0032] 7. Reduce the impact on vision: The repair method can solve the problem of affecting the transmittance and vision of the canopy after repair, and restore the vision of the damaged area of ​​the canopy.

[0033] 8. Improve support capabilities: Through fast and effective repair methods, the aircraft's combat power continuous generation and support capabilities are improved.

[0034] 9. Restoration of optical performance: The repair filler is repaired by grinding and polishing the solidified plexiglass powder to improve the transparency and optical quality of the repair area of ​​the plexiglass canopy.

[0035] 10. Sealing and optical performance testing: The sealing condition of the cockpit cover after repair is tested by nitrogen pressurization, and the recovery of the optical performance of the cockpit is tested by silver streaks to ensure the quality of the repair. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0037] Figure 1 The accompanying drawing is a flow chart of the embedded additive repair method for damaged transparent parts of a large-curvature aircraft canopy provided by the present invention;

[0038] Figure 2 The accompanying drawing is a schematic diagram of the embedded additive repair structure for damaged transparent parts of a large-curvature aircraft canopy provided by the present invention.

[0039] in:

[0040] 1-Plexiglas canopy; 2-Flexible outer baffle; 3-Built-in groove; 4-Repair filler; 5-Flexible inner baffle; 6-Hot repair instrument. DETAILED DESCRIPTION

[0041] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0042] See attached Figure 1 and attached Figure 2 The embodiment of the present invention discloses an embedded additive repair method for a damaged transparent part of a large curvature aircraft canopy, which specifically comprises the following steps:

[0043] Remove the damaged area on the plexiglass canopy 1, grind the hole, and grind the hole inward to form an embedded groove 3;

[0044] A flexible inner baffle plate 5 is attached to the inner side of the organic glass canopy 1 to cover the hole, a repair filler 4 is filled into the hole, and a flexible outer baffle plate 2 is attached to the outer side of the organic glass canopy 1 to cover the hole;

[0045] The hole area filled with the repair filler 4 is heated, and then cooled, so that the repair filler 4 is cooled and solidified into a shape.

[0046] Embodiment 1:

[0047] The embedded additive repair method for damaged transparent parts of a large curvature aircraft canopy provided in this embodiment specifically comprises the following steps:

[0048] (I) Detecting the damaged area: Determine the damaged area of ​​the plexiglass canopy 1 through silver streak detection, and mark the damaged repair area with a marking pen.

[0049] (ii) A dust-proof bag is made around the inside of the damaged area of ​​the plexiglass canopy 1 using sealant and vacuum bag film to prevent debris from entering the cabin when removing the damage.

[0050] (III) Removing damage: The damage of the plexiglass canopy 1 is removed by a grinding method, and the damaged area of ​​the plexiglass canopy 1 is ground into circular, elliptical or other shaped holes according to the shape characteristics of the damage.

[0051] (iv) On the hole wall of the organic glass canopy 1 after the damage is removed, the embedded groove 3 is further polished inwardly, and the ratio of the depth of the embedded groove 3 to the thickness of the organic glass canopy 1 is between 1:1 and 1:2, so as to form an embedded repair hole.

[0052] (V) Clean the dust generated by grinding, and then remove the dust leak-proof bag on the inner side of the plexiglass cockpit cover 1.

[0053] (VI) The flexible inner baffle plate 5 is attached to the inner side of the embedded repair hole of the organic glass cockpit cover 1, and the flexible inner baffle plate 5 made of silicone rubber is appropriately squeezed so that the gap between the flexible inner baffle plate 5 and the inner surface of the organic glass cockpit cover 1 is controlled between 0.2 mm and 0.5 mm.

[0054] (VII) The heat patching device 6 is attached to the flexible inner baffle plate 5, and then a vacuum bag is made in the action area of ​​the heat patching device 6.

[0055] (VIII) Fill the PMMA organic glass powder repair filler into the embedded repair hole, and after filling, make the filler higher than the surface of the embedded repair hole by 1 mm to 2 mm.

[0056] (IX) The flexible outer baffle plate 2 made of silicone rubber is fitted to the outside of the embedded repair hole, and the flexible outer baffle plate 2 is appropriately squeezed so that the gap between the flexible outer baffle plate 2 and the outer surface of the organic glass cockpit cover 1 is controlled between 0.2 mm and 0.5 mm, and then a vacuum bag is made on the outside of the flexible outer baffle plate 2.

[0057] (10) Evacuate the inner and outer vacuum bags simultaneously to -0.9 Bar.

[0058] (XI) Use the hot repair device 6 to heat the flexible inner baffle 5 and the organic glass powder repair filler, first raise the temperature to 100°C and maintain it for 1 hour, so that the organic glass powder repair filler is embedded in the repair hole and integrated with the organic glass cockpit cover 1. Then cool it to 60°C and maintain it for half an hour to solidify the organic glass powder repair filler.

[0059] (XII) Remove the vacuum bag, hot-fix device 6, flexible inner baffle 5 and flexible outer baffle 2, grind and polish the solidified organic glass powder repair filler, and improve the transparency and optical quality of the repair area of ​​the organic glass cockpit cover 1.

[0060] (XIII) The sealing condition of the cockpit cover after repair shall be tested by nitrogen pressurization, and the recovery of the optical performance of the cockpit shall be tested by silver streaks.

[0061] The in-situ embedded rapid additive repair method for damaged transparent parts of large-curvature aircraft canopy provided in this embodiment is different from the existing aircraft canopy repair method in that:

[0062] 1. Using organic glass powder as a repair filler for in-situ rapid additive repair can achieve damage repair of any shape, solving the problem of repairing complex damage shapes of large-curvature canopies, and at the same time solving the problem of affecting the light transmittance and field of view of the canopy after repair.

[0063] 2. The silicone rubber flexible inner baffle and the silicone rubber flexible outer baffle are used to fit the surface of the canopy, which can not only achieve fitting with the surface of the canopy with large curvature, but also enhance the convenience of operation.

[0064] 3. It is proposed to use embedded repair holes to form a mosaic structure between the repaired part and the damaged cockpit cover, thereby improving the mechanical properties of the repair structure.

[0065] Embodiment 2:

[0066] This embodiment provides a structure for repairing a damaged transparent part of a large-curvature aircraft canopy by using an embedded additive material repair method for repairing a damaged transparent part of a large-curvature aircraft canopy according to Embodiment 1. Figure 2 As shown, the structure is formed after the flexible outer baffle 2, the flexible inner baffle 5 and the thermal patching device 6 are removed.

[0067] In this specification, each embodiment is described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other. For the device disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant parts can be referred to the method part.

[0068] The above description of the disclosed embodiments enables one skilled in the art to implement or use the present invention. Various modifications to these embodiments will be apparent to one skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but rather to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A method for repairing damaged transparent parts of a large curvature aircraft canopy by embedded additive method, characterized in that: The specific steps include: Remove damaged areas on the plexiglass canopy and grind holes inward to create recessed grooves; A flexible inner baffle is attached to the inner side of the plexiglass canopy to cover the hole, a repair filler is filled into the hole, and a flexible outer baffle is attached to the outer side of the plexiglass canopy to cover the hole; The hole area filled with the repair filler is heated, and then cooled, so that the repair filler is cooled and solidified into shape.

2. The method for repairing damaged transparent parts of a large curvature aircraft canopy by embedded additive method according to claim 1, characterized in that: The ratio of the depth of the embedded groove to the thickness of the plexiglass cockpit cover is between 1:1 and 1:

2.

3. The method for repairing damaged transparent parts of a large curvature aircraft canopy by embedded additive method according to claim 1, characterized in that: While the hole was being sanded, a dust-proof bag was made on the plexiglass canopy using sealant and vacuum bagging film around the inside of the damaged area.

4. The method for repairing damaged transparent parts of a large curvature aircraft canopy by embedded additive method according to claim 1, characterized in that: During the process of laminating the flexible inner baffle and the flexible outer baffle, the flexible inner baffle and the flexible outer baffle are squeezed so that the gap between the inner and outer surfaces of the flexible inner baffle and the organic glass cockpit cover is controlled between 0.2 mm and 0.5 mm.

5. The method for repairing damaged transparent parts of a large curvature aircraft canopy by embedded additive method according to claim 1, characterized in that: A heat patching device is used to heat the hole area filled with plexiglass powder on the inner side of the plexiglass cockpit cover.

6. The method for repairing damaged transparent parts of a large curvature aircraft canopy by embedded additive method according to claim 5, characterized in that: Before the hot patching device is put into operation, a vacuum bag is made in the active area of ​​the hot patching device and on the outside of the flexible outer baffle, and the inner and outer vacuum bags are evacuated simultaneously before hot patching.

7. The method for repairing damaged transparent parts of a large curvature aircraft canopy by embedded additive method according to claim 6, characterized in that: The inner and outer vacuum bags are evacuated to -0.9 Bar.

8. The method for repairing damaged transparent parts of a large curvature aircraft canopy by embedded additive method according to claim 7, characterized in that: The flexible inner baffle plate and the flexible outer baffle plate are both made of silicone rubber, and the repair filler is organic glass powder.

9. The method for repairing damaged transparent parts of a large curvature aircraft canopy by embedded additive method according to claim 8, characterized in that: Use a heat repair device to heat the plexiglass powder, first raise the temperature to 100°C, maintain for 1 hour, then cool to 60°C, and maintain for half an hour.

10. A damaged embedded additive repair structure for transparent parts of a large curvature aircraft canopy, characterized in that: The damaged transparent part of a large-curvature aircraft canopy is repaired and formed by using an embedded additive repair method according to any one of claims 1 to 9.

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