Method and structure for damage embedded additive repair of large curvature aircraft canopy transparencies

Abstract

The application discloses a large-curvature aircraft canopy cover transparent piece damage inlay type additive repair method and structure, relates to a kind of quick repair method of aircraft canopy cover damage, specifically includes the following steps: removing damaged area on organic glass canopy cover, and polishing hole, hole is polished into inlay type groove inward;Flexible inner baffle is pasted on the inside of organic glass canopy cover and shields hole, and repair filler is filled in hole, flexible outer baffle is pasted on the outside of organic glass canopy cover and shields hole;The hole area filled with repair filler is heated, after heating, cooling, so that repair filler is cooled and solidified into shape.Large-curvature aircraft canopy cover transparent piece damage inlay type additive repair structure is repaired and formed using a kind of large-curvature aircraft canopy cover transparent piece damage inlay type additive repair method.The application solves the problems of repair adaptability of large-curvature canopy cover complex damage shape, limited view after repair canopy cover and local strength reduction.

Description

Technical Field

[0001] This invention relates to a rapid repair method for damage to an aircraft cockpit canopy, and more specifically to a rapid additive repair method and structure for in-situ embedded repair of damage to transparent parts of a large-curvature aircraft cockpit canopy. Background Technology

[0002] The aircraft canopy is mainly composed of a canopy frame and a transparent acrylic glass component. When in service in the field, it is highly susceptible to external impacts, resulting in various types of damage such as holes and scratches, which can lead to cockpit leakage and endanger flight safety and mission support. In order to effectively ensure the continuous generation of combat power, temporary and rapid field repairs are required for canopy damage, enabling the aircraft to relocate or continue operations.

[0003] The invention patent application with publication number CN114851603A discloses a method for repairing broken holes in the acrylic glass of an aircraft canopy. The method uses acrylic glass patches combined with reinforcing patches to repair the canopy damage. The acrylic glass patches are bonded to the original canopy with adhesive and cured by in-situ heating. This method of repair takes several hours.

[0004] In the 2014 Academic Symposium on Aviation Safety and Equipment Maintenance Technology, Wang Dingjiang et al. disclosed a rapid repair process for damage to transparent parts of aircraft cockpit canopies on pages 809-813. This method removes damage by using a special hole-breaking milling tool and manufactures corresponding insert patches. A special adhesive was developed to bond the insert patches. The repair time is 50 minutes.

[0005] Both of the above methods involve the fabrication of patches of specific shapes, which have limited adaptability to the shape of the puncture damage. They also rely on repair adhesives for bonding, making it difficult to achieve the original canopy performance after repair, and the canopy's visibility is affected to some extent.

[0006] Therefore, in order to meet the repair requirements of complex damage to large-curvature canopies, improve the performance of canopies after repair, restore the visibility of the damaged area of ​​the canopy, shorten the repair time of the field structure, simplify the operation process, and improve the support capability, it is necessary to develop a new method for repairing damage to transparent parts of large-curvature aircraft canopies. 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 aircraft cockpit canopies with large curvature, aiming to solve the above-mentioned technical problems.

[0008] To achieve the above objectives, the present invention adopts the following technical solution:

[0009] An embedded additive repair method for damaged transparent parts of aircraft cockpit canopies with large curvature includes the following steps:

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

[0011] A flexible inner baffle is attached to the inside of the plexiglass canopy to cover the holes, and repair filler is filled into the holes. A flexible outer baffle is attached to the outside of the plexiglass canopy to cover the holes.

[0012] The pore areas filled with the repair filler are heated, and then cooled to allow the repair filler to cool and solidify.

[0013] Through the above technical solution, the present invention provides an in-situ rapid additive repair method for damaged transparent parts of aircraft canopies with large curvature. In-situ rapid additive repair is achieved through repair fillers, enabling repair of damage of any shape. Flexible inner and outer baffles are used to adhere to the canopy surface, achieving both fit with the large curvature canopy surface and enhancing operational convenience. Embedded repair holes are used to form a fitted structure between the repaired part and the damaged canopy, improving the mechanical properties of the repair structure. This solves the problems of adaptability to repairing complex damage shapes of large curvature canopies, limited visibility after repair, and reduced local strength.

[0014] Preferably, in the above-mentioned method for repairing damage to a transparent part of a large curvature aircraft canopy using an embedded additive manufacturing method, 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 method for embedded additive repair of damage to a transparent part of a large curvature aircraft canopy, during the process of grinding the hole, a dust leak-proof bag is made around the inside and outside of the damaged area on the acrylic canopy using sealant and vacuum bag film.

[0016] Preferably, in the above-mentioned method for embedded additive repair of damage to transparent parts of large curvature aircraft canopy, during the process of bonding the flexible inner baffle and the flexible outer baffle, the flexible inner baffle and the flexible outer baffle are squeezed to control the gap between the flexible inner baffle and the inner and outer surfaces of the plexiglass canopy to be between 0.2mm and 0.5mm.

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

[0018] Preferably, in the above-mentioned method for embedded additive repair of damage to transparent parts of a large curvature aircraft cockpit canopy, before the heat repair instrument is used, vacuum bags are made in the working area of ​​the heat repair instrument and on the outside of the flexible outer baffle. The inner and outer vacuum bags are simultaneously evacuated before heat repair is performed.

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

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

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

[0022] Preferably, in the above-mentioned method for embedded additive repair of damage to transparent parts of large curvature aircraft cockpit canopies, the vacuum bag, heat repair instrument, flexible inner baffle and flexible outer baffle are removed, and the cured organic glass powder repair filler is ground, polished and cured.

[0023] Preferably, in the above-mentioned method for embedded additive repair of damage to the transparent part of a large curvature aircraft cockpit canopy, the sealing condition of the cockpit canopy after repair is detected by nitrogen pressurization, and the recovery of the cockpit's optical performance is detected by silver ripple testing.

[0024] The present invention also provides an embedded additive repair structure for damage to transparent parts of large-curvature aircraft cockpit canopies, which is repaired and formed using the aforementioned embedded additive repair method for damage to transparent parts of large-curvature aircraft cockpit canopies.

[0025] As can be seen from the above technical solution, compared with the prior art, the present invention discloses a method and structure for embedded additive repair of damage to transparent parts of large-curvature aircraft cockpit canopies, which has the following beneficial effects:

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

[0027] 2. Improved performance: The repair can restore the performance of the canopy, including its mechanical and optical properties, and solves the problems of limited visibility and reduced local strength of the canopy after repair.

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

[0029] 4. Ease of operation: Flexible inner and outer baffles are used to fit the surface of the canopy, which enhances the ease of operation and achieves a good fit with the surface of the canopy with large curvature.

[0030] 5. Repair of damage of any shape: In-situ rapid additive repair can be achieved by using plexiglass powder as a repair filler, which can realize the repair of damage of any shape.

[0031] 6. Improve the mechanical properties of the repair structure: The use of embedded repair holes is proposed to form a fitting structure between the repair part and the damaged canopy, thereby improving the mechanical properties of the repair structure.

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

[0033] 8. Enhanced support capabilities: Through rapid and effective repair methods, the continuous generation and support capabilities of aircraft combat effectiveness have been improved.

[0034] 9. Optical performance restoration: By grinding, polishing and curing the cured acrylic powder to repair the filler, the transparency and optical quality of the acrylic canopy repair area are improved.

[0035] 10. Sealing and Optical Performance Testing: The sealing condition of the canopy after repair is tested by nitrogen pressurization, and the recovery of the cockpit's optical performance is tested by silver ripple testing to ensure the quality of the repair. Attached Figure Description

[0036] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0037] Figure 1 The attached figure is a flowchart of the embedded additive repair method for damaged transparent parts of large curvature aircraft cockpit canopies provided by the present invention.

[0038] Figure 2 The attached figure is a schematic diagram of the embedded additive repair structure for damage to the transparent part of a large curvature aircraft cockpit canopy provided by the present invention.

[0039] in:

[0040] 1- Acrylic glass canopy; 2- Flexible outer baffle; 3- Embedded groove; 4- Repair filler; 5- Flexible inner baffle; 6- Heat repair device. Detailed Implementation

[0041] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0042] See appendix Figure 1 and attached Figure 2 This invention discloses an embedded additive repair method for damaged transparent parts of aircraft cockpit canopies with large curvature, specifically including the following steps:

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

[0044] A flexible inner baffle 5 is attached to the inside of the plexiglass canopy 1 to cover the holes, and a repair filler 4 is filled into the holes. A flexible outer baffle 2 is attached to the outside of the plexiglass canopy 1 to cover the holes.

[0045] The pore areas of the filling and repair filler 4 are heated and then cooled to allow the filling and repair filler 4 to cool and solidify.

[0046] Example 1:

[0047] The embedded additive repair method for damaged transparent parts of large-curvature aircraft cockpit canopies provided in this embodiment specifically includes the following steps:

[0048] (a) Damage detection: The damaged area of ​​the plexiglass canopy 1 is determined by silver line detection, and the damaged repair area is marked with a marker pen.

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

[0050] (III) Damage removal: The damage to the acrylic canopy 1 is removed by grinding. The damaged area of ​​the acrylic canopy 1 is ground into a circular, elliptical or other shaped hole according to the shape characteristics of the damage.

[0051] (iv) On the hole wall after the damage of the plexiglass canopy 1 is removed, continue to grind inward to form an embedded groove 3. The ratio of the depth of the embedded groove 3 to the thickness of the plexiglass canopy 1 is between 1:1 and 1:2, forming an embedded repair hole.

[0052] (v) Clean up the dust generated during polishing, and then remove the dust leak-proof bag inside the plexiglass cockpit cover 1.

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

[0054] (vii) The heat repair instrument 6 is attached to the flexible inner baffle 5, and then a vacuum bag is made in the working area of ​​the heat repair instrument 6.

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

[0056] (ix) Fit the flexible outer baffle 2 made of silicone rubber to the outside of the embedded repair hole, and squeeze the flexible outer baffle 2 appropriately so that the gap between the flexible outer baffle 2 and the outer surface of the organic glass canopy 1 is controlled between 0.2mm and 0.5mm. Then make a vacuum bag on the outside of the flexible outer baffle 2.

[0057] (x) Simultaneously evacuate both the inner and outer vacuum bags to -0.9 Bar.

[0058] (xi) Use a heat repair instrument 6 to heat the flexible inner baffle 5 and the acrylic powder repair filler. First, heat the temperature to 100°C and maintain it for 1 hour to allow the acrylic powder repair filler to be embedded in the repair hole and fused with the acrylic canopy 1. Then cool it to 60°C and maintain it for half an hour to allow the acrylic powder repair filler to solidify and take shape.

[0059] (xii) Remove the vacuum bag, heat repair instrument 6, flexible inner baffle 5 and flexible outer baffle 2, grind and polish the cured organic glass powder repair filler to improve the transparency and optical quality of the repair area of ​​the organic glass canopy 1.

[0060] (xiii) Test the sealing condition of the canopy after repair by pressurizing with nitrogen, and test the recovery of the cockpit's optical performance by using silver ripples.

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

[0062] 1. In-situ rapid additive repair using plexiglass powder as a repair filler can achieve the repair of damage of any shape, solving the problem of repairing complex damage shapes of canopies with large curvature, and at the same time solving the problem of affecting the light transmittance and visibility of the canopy after repair.

[0063] 2. The use of flexible inner and outer silicone rubber baffles to fit the surface of the canopy not only achieves a good fit with the surface of the canopy with large curvature, but also enhances the ease of operation.

[0064] 3. An embedded repair hole was proposed to create a fitting structure between the repaired part and the damaged canopy, thereby improving the mechanical properties of the repair structure.

[0065] Example 2:

[0066] This embodiment provides an embedded additive repair structure for damaged transparent parts of a large-curvature aircraft cockpit canopy, which is repaired using the embedded additive repair method for damaged transparent parts of a large-curvature aircraft cockpit canopy described in Embodiment 1. That is, as... Figure 2 As shown, this is the structure formed after removing the flexible outer baffle 2, the flexible inner baffle 5, and the heat repair device 6.

[0067] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the apparatus disclosed in the embodiments, since it corresponds to the method disclosed in the embodiments, the description is relatively simple; relevant parts can be referred to the method section.

[0068] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those 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 invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A method for embedded additive repair of damage to a transparent component of an aircraft cockpit canopy with high curvature, characterized in that, Specifically, the following steps are included: Remove the damaged areas on the plexiglass canopy and grind the holes inward to create recessed grooves. A flexible inner baffle is attached to the inside of the plexiglass canopy to cover the holes, and repair filler is filled into the holes. A flexible outer baffle is attached to the outside of the plexiglass canopy to cover the holes. The pore areas of the filling material are heated, then cooled to allow the filling material to solidify and take shape. The ratio of the depth of the recessed groove to the thickness of the plexiglass canopy is between 1:1 and 1:

2. During the bonding process of the flexible inner baffle and the flexible outer baffle, the flexible inner baffle and the flexible outer baffle are squeezed to control the gap between the flexible inner baffle and the inner and outer surfaces of the plexiglass canopy to be between 0.2mm and 0.5mm. A heat-filling device is used to heat the pore area filled with plexiglass powder on the inside of the plexiglass canopy.

2. The method for embedded additive repair of damage to a transparent component of a large-curvature aircraft cockpit canopy according to claim 1, characterized in that, During the process of grinding the holes, a dust leak-proof bag is made around the inside of the damaged area on the plexiglass canopy using sealant and vacuum film.

3. The method for embedded additive repair of damage to a transparent component of a large-curvature aircraft cockpit canopy according to claim 1, characterized in that, Before the heat repair machine is put into operation, vacuum bags are made in the working area of ​​the heat repair machine and on the outside of the flexible outer baffle. The inner and outer vacuum bags are simultaneously evacuated before heat repair is performed.

4. The method for embedded additive repair of damage to a transparent component of a large-curvature aircraft cockpit canopy according to claim 3, characterized in that, Vacuum bags were used to evacuate the inner and outer layers to -0.9 Bar.

5. The method for embedded additive repair of damage to a transparent component of a large-curvature aircraft cockpit canopy according to claim 4, characterized in that, Both the flexible inner baffle and the flexible outer baffle are made of silicone rubber, and the repair filler is plexiglass powder.

6. The method for embedded additive repair of damage to a transparent component of a large-curvature aircraft cockpit canopy according to claim 5, characterized in that, The acrylic powder was heated using a heat repair device. First, the temperature was raised to 100°C and maintained for 1 hour, then cooled to 60°C and maintained for half an hour.

7. An embedded additive repair structure for damaged transparent parts of a large-curvature aircraft cockpit canopy, characterized in that, The damaged transparent part of the large curvature aircraft cockpit canopy is repaired and formed using the embedded additive repair method according to any one of claims 1-6.

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