Rapid repairing method for assembled composite material

Abstract

The invention relates to a quick repair method for an assembled composite material. The quick repair method comprises the following steps: S1, manufacturing a composite material laminated plate; s2, cutting the composite material laminated plate; s3, holes are formed in the hexagonal composite material patch units; s4, obtaining a large number of hexagonal composite material patch units; s5, adhering the alkali-free glass fiber cloth; s6, holes are formed in the aluminum alloy plate; s7, the aluminum alloy plate is cut; s8, a large number of aluminum alloy connecting units are obtained; s9, repairing and patch assembling; s10, adjusting the appearance of the curved surface of the assembly structure; s11, the assembly structure is installed; through prefabrication and splicing of a large number of hexagonal composite material patch units and aluminum alloy connecting units, the repairing and manufacturing time of large composite materials is shortened, and the repairing speed is increased; by changing the using number of the hexagonal composite material patch units and the aluminum alloy connecting units, rapid repair of different damage areas can be effectively achieved; by changing the bending shape of the aluminum alloy connecting unit, the damage of the composite materials with different curvatures can be effectively and rapidly repaired.

Description

Technical Field

[0001] The invention relates to the field of composite material repair, in particular to a method for quickly repairing assembled composite materials. Background Art

[0002] Composite material repair is an important means to reduce the cost of composite materials in the fields of aerospace, shipbuilding, etc. The preparation of composite material patches takes up a lot of time in composite material repair, and it is difficult to quickly improve the repair efficiency. Under field support conditions, the lack of corresponding composite material manufacturing equipment and tooling makes it difficult to manufacture composite material patches. At the same time, since composite materials usually have a certain curvature, the damage area produced under different conditions is different, which makes it difficult to pre-manufacture repair patches. Therefore, for field support or emergency tasks, it is necessary to propose a method for quickly repairing large-area composite material damage. At present, there are many patents related to composite material repair methods. For example, Chinese patent CN202210535318.4, which was published on September 23, 2022, proposes a method for quickly repairing aircraft structure damage with composite materials using rapid light curing. Chinese patent CN201410617517.5, which was published on January 25, 2019, proposes a method for rapid bonding and repair based on ultraviolet light-curing composite materials. Chinese patent CN202310283702.4, published on July 14, 2023, proposes a method for quickly repairing complex surface structural damage based on silicone rubber molds. However, these methods require special repair conditions or tooling under field conditions, have high repair environment requirements, are complex to operate, and are difficult to ensure repair quality and to deal with large-area multi-curvature structural damage. Therefore, it is very necessary to propose a fast and simple method that can effectively carry out repairs on composite material damage of different areas and different curvatures. Summary of the invention

[0003] In order to solve the above problems, the present invention provides a method for quickly repairing assembled composite materials.

[0004] A method for rapid repair of assembled composite materials, the specific steps of which are as follows:

[0005] S1. Production of composite laminates: using prepreg cutting equipment to cut the preferred composite prepreg, completing prepreg paving, and using vacuum bags to package the prepreg composite panels on a flat metal mold;

[0006] S2. Cutting of composite laminates: placing the prepared composite laminates into a processing grinder, cutting the composite laminates into hexagonal composite patch units, and grinding out overlapping areas around the patches;

[0007] S3. Making holes for hexagonal composite patch units: using composite drilling equipment to drill fastener holes in the overlap area to complete the preparation of the hexagonal composite patch units;

[0008] S4, obtaining a large number of hexagonal composite patch units;

[0009] S5. Pasting the alkali-free glass fiber cloth: using the preferred adhesive to paste the preferred alkali-free glass fiber cloth on one surface of the preferred aluminum alloy plate, and completing the heating and curing of the adhesive;

[0010] S6. Aluminum alloy plate hole making: Use an automated mechanical drilling lathe to drill fastener holes on the aluminum alloy plate with alkali-free glass fiber cloth attached;

[0011] S7. Cutting of aluminum alloy plates: using a machining lathe to cut the aluminum alloy plates with holes into rectangular aluminum alloy connection units;

[0012] S8. Obtain a large number of aluminum alloy connection units;

[0013] S9. Repair patch assembly: according to the area of ​​the damaged area, select a corresponding number of hexagonal composite material patch units and aluminum alloy connection units;

[0014] S10. Adjustment of the curved surface shape of the assembled structure: During the splicing process of the hexagonal composite patch, the aluminum alloy connection unit is shaped according to the shape of the damaged structural surface;

[0015] S11. Installation of the assembly structure: Grind the edges of the spliced ​​repair patches according to the geometric morphology of the damaged area.

[0016] The step S1 requires placing the composite laminate into an autoclave and using the autoclave to evacuate the vacuum bag.

[0017] The vacuum degree of the composite material is not less than -0.95 MPa, and the temperature-time curve and the pressure-time curve adopt the manufacturing process requirements of the prepreg composite material laminate.

[0018] The preferred thickness of the aluminum alloy plate in step S5 is consistent with the grinding depth of the hexagonal composite material patch unit.

[0019] The diameter of the fastener hole made in step S6 is consistent with the diameter of the fastener hole of the hexagonal composite material patch unit.

[0020] Specifically, the spacing between the fastener holes in the same row is consistent with the spacing between the fasteners of the hexagonal composite patch unit, and the spacing between the fastener holes in each column is consistent with the width of the overlapping area of ​​the hexagonal composite patch unit.

[0021] The length of the aluminum alloy connection unit in step S7 is consistent with the length of the short side of the hexagonal composite patch unit overlap area, the width of the aluminum alloy connection unit is twice the width of the hexagonal composite patch unit overlap area, and the fastener holes of the aluminum alloy connection unit are consistent in position with the fastener holes of the hexagonal composite patch unit overlap area.

[0022] The estimation formula for the number of hexagonal composite patch units and aluminum alloy connection units required for step S9 is: n≥Adam / Acom, where Adam represents the area of ​​the damaged area and Acom represents the area of ​​the hexagonal composite patch unit.

[0023] The step S11 requires drilling holes in the area where the assembly structure and the damaged structure overlap, and using preferred bolts to fix the assembly patch to the damaged area to complete the repair of the damaged area.

[0024] The beneficial effects of the present invention are as follows: by prefabrication and splicing of a large number of hexagonal composite patch units and aluminum alloy connection units, the time for repairing and manufacturing large composite materials is shortened and the repair speed is improved; by changing the number of hexagonal composite patch units and aluminum alloy connection units used, rapid repair of different damaged areas can be effectively achieved; by changing the bending shape of the aluminum alloy connection unit, rapid repair of composite material damage with different curvatures can be effectively achieved, and the entire repair process is simple and fast to operate, and does not require special tools and tooling. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0026] Figure 1 is a flow chart of the method of the present invention;

[0027] Figure 2 It is a schematic diagram of cutting the composite laminate of the present invention;

[0028] Figure 3 It is a front view of the hexagonal composite material patch of the present invention;

[0029] Figure 4 It is a schematic diagram of cutting the aluminum alloy plate of the present invention;

[0030] Figure 5 is an isometric view of an aluminum alloy connection unit of the present invention;

[0031] Figure 6 It is an isometric view of the composite material assembly structure of the present invention;

[0032] Figure 7 It is a schematic diagram of the composite material assembly structure repair of the present invention.

[0033] In the figure: 1. Composite laminate; 2. Hexagonal composite patch unit; 3. Composite bolt hole; 4. Overlap area; 5. Aluminum alloy plate; 6. Aluminum alloy connection unit; 7. Aluminum alloy connection plate bolt hole; 8. Alkali-free glass fiber cloth; 9. Bolt; 10. Assembly structure; 11. Damaged area; 12. Damaged structure. DETAILED DESCRIPTION

[0034] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention is further described below.

[0035] like Figures 1 to 7 As shown, a method for rapid repair of assembled composite materials, the specific steps are as follows:

[0036] S1. Preparation of composite laminate 1: using prepreg cutting equipment to cut the preferred composite prepreg, based on the composite laminate 1 manufacturing process, completing the prepreg paving, and using a vacuum bag to package the prepreg composite board assembly on a flat metal mold, the prepreg is CCF300 / QY8911;

[0037] S2, cutting of composite material laminate 1: placing the prepared composite material laminate 1 into a processing grinder, cutting the composite material laminate 1 into hexagonal composite material patch units 2, and grinding the overlap area 4 around the patch;

[0038] S3, making holes in the hexagonal composite patch unit 2: using a composite drilling device to drill fastener holes in the overlap area 4 to complete the preparation of the hexagonal composite patch unit 2;

[0039] S4, obtaining a large number of hexagonal composite patch units 2;

[0040] S5, pasting the alkali-free glass fiber cloth 8: using a preferred adhesive to paste the preferred alkali-free glass fiber cloth 8 on one surface of the preferred aluminum alloy plate 5, and completing heating and curing of the adhesive;

[0041] S6, drilling holes in the aluminum alloy plate 5: using an automated mechanical drilling lathe to drill fastener holes in the aluminum alloy plate 5 on which the alkali-free glass fiber cloth 8 is attached;

[0042] S7, cutting the aluminum alloy sheet 5: using a machining lathe, cutting the aluminum alloy sheet 5 with holes made therein into rectangular aluminum alloy connection units 6;

[0043] S8, obtaining a large number of aluminum alloy connection units 6;

[0044] S9, repair patch assembly: according to the area of ​​the damaged area 11, select a corresponding number of hexagonal composite material patch units 2 and aluminum alloy connection units 6;

[0045] S10, adjusting the curved surface shape of the assembled structure 10: during the splicing process of the hexagonal composite patch, the aluminum alloy connection unit 6 is shaped according to the curved surface shape of the damaged structure 12, so that the shape of the assembled structure 10 after splicing meets the curved surface shape requirements of the damaged area 11;

[0046] S11 , installation of the assembly structure 10 : grinding the edges of the spliced ​​repair patches according to the geometrical morphology of the damaged area 11 .

[0047] The step S1 requires placing the composite laminate 1 into an autoclave, using the autoclave to evacuate the vacuum bag, and heating and pressurizing according to the composite material manufacturing process requirements to complete the manufacture of the composite laminate 1. The composite laminate 1 is provided with a plurality of groups of composite material bolt holes 3, and the composite material bolt holes 3 are located on the center line of the overlap area 4, and the number is evenly distributed.

[0048] The vacuum degree of the composite material is not less than -0.95 MPa, and the temperature-time curve and the pressure-time curve adopt the manufacturing process requirements of the prepreg composite material laminate 1.

[0049] The thickness of the aluminum alloy plate 5 in the step S5 is preferably consistent with the grinding depth of the hexagonal composite material patch unit 2 .

[0050] The overlapping area 4 is arranged inside the edge of the hexagonal composite material patch 2, with a width of 20 mm and a grinding depth of 2 mm.

[0051] The diameter of the fastener hole made in step S6 is consistent with the composite material bolt hole 3 .

[0052] Specifically, the spacing between the fastener holes in the same row is consistent with the spacing between the fasteners of the hexagonal composite patch unit 2, and the spacing between the fastener holes in each column is consistent with the width of the overlapping area 4 of the hexagonal composite patch unit 2.

[0053] The length of the aluminum alloy connection unit 6 in step S7 is consistent with the length of the short side of the overlap area 4 of the hexagonal composite patch unit 2, the width of the aluminum alloy connection unit 6 is twice the width of the overlap area 4 of the hexagonal composite patch unit 2, and the bolt hole 7 of the aluminum alloy connection plate is consistent with the position of the fastener hole in the overlap area 4 of the hexagonal composite patch unit 2.

[0054] The aluminum alloy connecting unit 6 is provided with a plurality of groups of aluminum alloy connecting plate bolt holes 7 .

[0055] The estimation formula for the number of hexagonal composite patch units 2 and aluminum alloy connection units 6 required for the step S9 is: n≥Adam / Acom, wherein Adam represents the area of ​​the damaged area 11, and Acom represents the area of ​​the hexagonal composite patch unit 2. According to the geometric shape of the damaged area 11, the aluminum alloy connection unit 6 and the hexagonal composite patch unit 2 are assembled using the preferred bolts 9.

[0056] The step S11 requires drilling holes in the overlapping area between the assembly structure 10 and the damaged structure 12, and using the preferred bolts 9 to fix the assembly patch to the damaged area 11, thereby completing the repair of the damaged area 11.

[0057] Example:

[0058] Step 1: Use prepreg cutting equipment to cut CCF300 / QY8911 composite material prepreg, complete prepreg paving based on the composite material laminate 1 manufacturing process, and use a vacuum bag to package the prepreg composite material board combination on a flat metal mold; put the composite material laminate 1 into an autoclave, use the autoclave to evacuate the vacuum bag, and heat and pressurize according to the composite material manufacturing process requirements to manufacture a composite material laminate 1 with a thickness of 4 mm; the vacuum degree is usually not less than -0.95MPa, and the temperature-time curve and pressure-time curve adopt the manufacturing process requirements of the CCF300 / QY8911 prepreg composite material laminate 1;

[0059] Step 2: Put the prepared composite laminate 1 into a processing grinder, cut the composite laminate 1 to make a hexagonal composite patch unit 2, and grind a lap area 4 with a certain depth and width around the patch; the lap area 4 is arranged on the inner side of the edge of the hexagonal composite patch unit 2, with a width of 20 mm and a grinding depth of 2 mm;

[0060] Step 3: using a composite material drilling device to drill composite material bolt holes 3 in the overlap area 4 to complete the preparation of the hexagonal composite material patch unit 2; the composite material bolt holes 3 are located on the center line of the overlap area 4 and are evenly distributed in number;

[0061] Step 4: Through the above steps 1 to 3, the hexagonal composite material patch unit 2 can be obtained;

[0062] Step 5: Use a preferred adhesive to stick the preferred alkali-free glass fiber cloth 8 on one surface of the preferred aluminum alloy plate 5, and heat and cure the adhesive; the thickness of the preferred aluminum alloy plate 5 is consistent with the grinding depth of the hexagonal composite patch unit 2, which is 2 mm;

[0063] Step 6: Use an automated mechanical drilling lathe to drill aluminum alloy connecting plate bolt holes 7 on the aluminum alloy plate 5 with the alkali-free glass fiber cloth 8 attached thereto; the diameter of the aluminum alloy connecting plate bolt holes 7 is consistent with the composite material bolt holes 3 of the hexagonal composite material patch unit 2; the spacing between the aluminum alloy connecting plate bolt holes 7 in the same row is consistent with the spacing between the composite material bolt holes 3 of the hexagonal composite material patch unit 2; the spacing between the aluminum alloy connecting plate bolt holes 7 in each row is consistent with the width of the overlap area 4 of the hexagonal composite material patch unit 2;

[0064] Step 7: Use a machining lathe to cut the aluminum alloy plate 5 with holes into a rectangular aluminum alloy connection unit 6; the length of the aluminum alloy connection unit 6 is consistent with the length of the short side of the overlap area 4 of the hexagonal composite patch unit 2; the width of the aluminum alloy connection unit 6 is twice the width of the overlap area 4 of the hexagonal composite patch unit 2; the aluminum alloy connection plate bolt hole 7 of the aluminum alloy connection unit 6 is consistent with the composite bolt hole 3 on the overlap area 4 of the hexagonal composite patch unit 2;

[0065] Step 8: Through the above steps 5 to 7, a large number of aluminum alloy connection units 6 can be obtained;

[0066] Step 9: According to the area of ​​the damaged area 11 on the damaged structure 12, a certain number of the hexagonal composite patch units 2 and the aluminum alloy connection units 6 are selected; the estimation formula for the required number of hexagonal composite patch units 2 and aluminum alloy connection units 6 is: n≥Adam / Acom, wherein Adam represents the area of ​​the damaged area 11, and Acom represents the area of ​​the hexagonal composite patch unit 2; according to the geometric shape of the damaged area 11, the aluminum alloy connection unit 6 and the hexagonal composite patch unit 2 are assembled using the preferred bolts 9;

[0067] Step 10: During the splicing process of the hexagonal composite patch unit 2 and the aluminum alloy connection unit 6, the aluminum alloy connection unit 6 is shaped according to the curved surface shape of the damaged structure 12, so that the shape of the assembled structure 10 after splicing meets the curved surface shape requirement of the damaged structure 12;

[0068] Step 11: According to the geometric morphology of the damaged area 11, the edge of the assembled structure 10 is polished; the overlapping area 4 of the assembled structure 10 and the damaged area 11 is drilled using a drilling device, and the assembled structure 10 is fixed to the damaged structure 12 using the preferred bolts 9 to complete the repair of the damaged area 11.

[0069] The preparation of the hexagonal composite patch unit 2 and the preparation of the aluminum alloy connection unit 6 in steps 1 to 8 are completed in advance; after damage occurs to the large-scale composite structure, only steps 9 to 11 need to be carried out to complete the damage repair.

[0070] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The above embodiments and descriptions only describe the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. A method for rapid repair of assembled composite materials, characterized in that: The specific steps are as follows: S1. Preparation of composite laminate (1): using a prepreg cutting device to cut a preferred composite prepreg, completing prepreg paving, and packaging the prepreg composite board assembly on a flat metal mold using a vacuum bag; S2. Cutting the composite laminate (1): placing the prepared composite laminate (1) into a processing grinder, cutting the composite laminate (1) into hexagonal composite patch units (2), and grinding out overlapping areas (4) around the patches; S3, making holes in the hexagonal composite patch unit (2): using a composite drilling device to drill fastener holes in the overlap area (4), thereby completing the preparation of the hexagonal composite patch unit (2); S4, obtaining a large number of hexagonal composite patch units (2); S5, pasting the alkali-free glass fiber cloth (8): pasting the preferred alkali-free glass fiber cloth (8) on one surface of the preferred aluminum alloy plate (5) using a preferred adhesive, and completing heating and curing of the adhesive; S6. Drilling holes in the aluminum alloy plate (5): using an automated mechanical drilling lathe to drill fastener holes in the aluminum alloy plate (5) on which the alkali-free glass fiber cloth (8) is attached; S7, cutting the aluminum alloy plate (5): using a machining lathe to cut the aluminum alloy plate (5) with holes made thereinto into rectangular aluminum alloy connection units (6); S8, obtaining a large number of aluminum alloy connection units (6); S9, assembling the repair patch: selecting a corresponding number of hexagonal composite material patch units (2) and aluminum alloy connection units (6) according to the area of ​​the damaged area (11); S10, adjusting the curved surface shape of the assembled structure (10): during the splicing process of the hexagonal composite patch, the aluminum alloy connection unit (6) is shaped according to the curved surface shape of the damaged structure (12); S11, installation of the assembly structure (10): grinding the edges of the spliced ​​repair patch according to the geometrical morphology of the damaged area (11).

2. The method for rapid repair of assembled composite materials according to claim 1, characterized in that: The step S1 requires placing the composite material laminate (1) into an autoclave and using the autoclave to evacuate the vacuum bag.

3. The method for rapid repair of assembled composite materials according to claim 2, characterized in that: The vacuum degree of the composite material is not less than -0.95 MPa, and the temperature-time curve and the pressure-time curve adopt the manufacturing process requirements of the prepreg composite material laminate (1).

4. The method for rapid repair of assembled composite materials according to claim 1, characterized in that: The thickness of the aluminum alloy plate (5) in the step S5 is preferably consistent with the grinding depth of the hexagonal composite material patch unit (2).

5. The method for rapid repair of assembled composite materials according to claim 1, characterized in that: The diameter of the fastener hole made in step S6 is consistent with the composite material bolt hole (3).

6. The method for rapid repair of assembled composite materials according to claim 5, characterized in that: Specifically, the spacing between the fastener holes in the same row is consistent with the spacing of the fasteners in the hexagonal composite patch unit (2), and the spacing between the fastener holes in each column is consistent with the width of the overlap area (4) of the hexagonal composite patch unit (2).

7. The method for rapid repair of assembled composite materials according to claim 1, characterized in that: The length of the aluminum alloy connection unit (6) in step S7 is consistent with the length of the short side of the overlap area (4) of the hexagonal composite patch unit (2), the width of the aluminum alloy connection unit (6) is twice the width of the overlap area (4) of the hexagonal composite patch unit (2), and the bolt hole (7) of the aluminum alloy connection plate is consistent with the position of the fastener hole of the overlap area (4) of the hexagonal composite patch unit (2).

8. The method for rapid repair of assembled composite materials according to claim 1, characterized in that: The estimation formula for the number of hexagonal composite patch units (2) and aluminum alloy connection units (6) required for step S9 is: n≥Adam / Acom, where Adam represents the area of ​​the damaged area (11) and Acom represents the area of ​​the hexagonal composite patch unit (2).

9. The method for rapid repair of assembled composite materials according to claim 1, characterized in that: The step S11 requires drilling holes in the area where the assembly structure (10) and the damaged structure (12) overlap, and using bolts (9) to fix the assembly patch to the damaged area (11), thereby completing the repair of the damaged area (11).

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