Device and method for restoring and manufacturing intersection point hole in aircraft skin repair area

Abstract

The invention belongs to an aircraft riveting assembly technology, and relates to an aircraft skin repair area intersection point hole recovery manufacturing device and method. A skin repair area conformal structure is adopted for shaping an aircraft skin repair area, and the skin repair conformal structure can comprise a supporting and adjusting assembly, a skin connecting frame positioning assembly, a system and finished product mounting support positioning and drilling assembly and a fuselage structure supporting bracket assembly. The skin connecting frame positioning assembly and the system and finished product mounting support positioning and drilling assembly are sequentially and accurately mounted and debugged on the basis of the supporting and adjusting assembly and then are connected and fixed; the relative position between the skin connecting frame positioning assembly and the system and finished product mounting support positioning and drilling assembly is fixed and is not adjusted; foundation feet for supporting the adjusting assembly can be adjusted, the adjusting structure can be matched with a single screw and double nuts, the height of the skin connecting frame positioning assembly is adjusted through the adjusting nuts, and the shape-preserving structure is connected with an aircraft structure in a positioning mode within a short time. According to the invention, accurate re-manufacturing on the new skin according to the original intersection position of the original skin can be realized. Compared with a method for reversely drilling the original aircraft structure intersection hole to the new skin, damage to the original aircraft structure intersection hole in the reverse drilling process is avoided, the drilling precision is improved, and the quality of the original aircraft structure intersection hole is guaranteed.

Description

Technical Field

[0001] The invention belongs to aircraft riveting assembly technology, and relates to a device and method for restoring and preparing intersection holes in an aircraft skin repair area. Background Art

[0002] When the aircraft skin is damaged, cracks, debonding and wrinkles will occur, which will damage the strength and stiffness of the aircraft skin, seriously affecting the service life of the aircraft skin and the aerodynamic characteristics of the aircraft. Repairing the damaged aircraft skin is of great significance to ensure the service life of the aircraft skin and its aerodynamic characteristics.

[0003] At present, there are two main ways to repair damaged aircraft skin: repairing on the basis of the original skin and cutting the damaged skin, and replacing it with a new skin. In the process of repairing the aircraft skin based on these two methods, the fuselage structure near the repair area needs to be conformal to avoid deformation of the fuselage structure frame and beam during the repair process. However, in some cases, such as during the service of the aircraft, the phenomenon of skin burns caused by the combustion of residual oil in the engine occasionally occurs. The damaged aircraft skin is located at the connection frame between the fuselage and the tail section. When cutting the damaged area and replacing the new skin, the tail section of the aircraft needs to be disconnected. At this time, the connection frame is detached from the constraints of the tail section connection bolts and the rivets connecting to the fuselage skin. The structural rigidity is seriously insufficient, and a stable conformal device is inevitably required for conformal maintenance. On the other hand, after replacing the new skin, if there are support mounting holes for installing the finished system products on the skin at this point in the original aircraft state, they need to be re-made, and the position coordination requirements are high. Under normal circumstances, the aircraft will be considered to be restored to the original manufacturing jig for conformal preservation and intersection hole making. However, since the aircraft is loaded with many finished products and equipment in the service stage, its volume and weight are also large. It is extremely difficult to achieve the prototype frame reset and hole making, or even impossible to achieve. Summary of the invention

[0004] The main purpose of the present invention is to provide a conformal structure for skin repair and a method for restoring the intersection holes in the repair area to overcome or alleviate the technical defects existing in the above background.

[0005] Technical solution: To achieve the above-mentioned purpose, the present invention provides a device for restoring and making intersection holes in an aircraft skin repair area, which uses a skin repair area conformal structure to shape the aircraft skin repair area. The skin repair conformal structure may include a support adjustment component, a skin connection frame positioning component, a system and finished product installation support positioning and hole making component, and a fuselage structure support bracket component;

[0006] Among them, the skin connection frame positioning component, the system and the finished product installation support positioning and hole making component are connected and fixed after being accurately installed and debugged in sequence on the basis of the support adjustment component; the connection form can be screws, pins, etc.; the relative position between the skin connection frame positioning component and the system and the finished product installation support positioning and hole making component is fixed and does not need to be adjusted; the foot of the support adjustment component is adjustable, and the adjustment structure can adopt a single screw and a double nut to adjust the height of the skin connection frame positioning component by adjusting the nut, so as to realize the positioning connection of the conformal structure with the aircraft structure in a short time.

[0007] Furthermore, the system and finished product mounting support positioning and hole-making assembly comprises two parts, a positioning assembly and a hole-making assembly. The connecting holes on the positioning assembly are made according to the theoretical coordinate position based on the product digital model during the conformal structure manufacturing, and the adjustment is completed; a certain gap is reserved at the connection between the positioning assembly and the main body, and after the connecting hole of the positioning assembly is connected with the connecting hole of the system or finished product mounting support near the damaged area of ​​the aircraft skin, epoxy resin is poured into the gap, and a stable structure is formed after curing, which plays a conformal and positioning role for the aircraft structure; the connecting holes on the hole-making assembly can be made into initial holes or no holes during manufacturing, and are poured and made on site according to the positions of the original system or finished product mounting holes on the damaged skin to form a hole-making drill template for restoring the intersection holes in the skin repair area.

[0008] Furthermore, the skin connecting frame positioning assembly includes: a connecting frame, a conformal connecting plate, the conformal connecting plate is fixed on the connecting frame, a bushing is connected in the middle of the conformal connecting plate, the bushing is concentrically fixed to the connecting hole on the tail section connecting frame, and finally a bolt pin is inserted to position and tighten the aircraft skin repair area.

[0009] Furthermore, the fuselage structure support bracket assembly acts on the positions of the main load-bearing support frames of the aircraft to support and fix the aircraft.

[0010] Furthermore, there is a conformal connecting plate on the skin connecting frame positioning assembly, which can be connected to the aircraft frame plane through a number of stepped bolts to play a positioning and conformal role.

[0011] On the other hand, the present invention also provides a method for restoring and obtaining intersection holes in a repair area. The method is based on the above-designed device for restoring and obtaining intersection holes in a repair area of ​​an aircraft skin, and comprises the following steps:

[0012] The first step is to remove the relevant systems or finished products on the aircraft from the mounting bracket before repairing the aircraft skin;

[0013] In the second step, the connection system and finished product mounting bracket positioning assembly is conformed and positioned with the system or finished product mounting bracket near the damaged skin;

[0014] The third step is to test the installation system and the finished product installation support hole-making assembly on the conformal structure, and adjust the installation position of the hole-making assembly so that there is a certain gap between the hole-making assembly and the damaged skin profile;

[0015] The fourth step is to use the damaged skin profile and the system or finished product mounting support connection holes on the damaged skin as the filling reference, first stick the demoulding cloth on the damaged skin, pour the epoxy resin on the plane, and determine the number and position of the filling holes on site, and then use the pin and drill sleeve to pour the drill sleeve holes according to the damaged skin system or finished product mounting support connection holes;

[0016] Step 5: After the epoxy resin is cured, remove the demoulding cloth and excess epoxy resin between the system and finished product mounting bracket positioning components and the damaged skin, and pull out the pin from the drill sleeve to form a final usable hole-making component; remove the system and finished product mounting bracket hole-making components from the conformal structure;

[0017] In the sixth step, after the damaged skin is replaced, the system and the finished product installation support hole-making assembly are reinstalled on the conformal structure, and the hole-making assembly obtained in the fifth step is used to make holes in the new skin.

[0018] Furthermore, the gap value between the hole making assembly and the damaged skin profile is in the range of 2-3 mm.

[0019] Furthermore, the release cloth is used to prevent the epoxy resin from adhering to the skin and being difficult to clean.

[0020] Beneficial technical effects: The structure designed by the present invention for maintaining the shape of an aircraft skin during repair can be operated in situ on the aircraft and is easy to implement. The structure solves the problem that it is difficult or impossible to restore the aircraft to the original manufacturing jig for shape maintenance and hole making. The structure can accurately connect and fix the skin connection frame positioning component to the aircraft frame that needs to be kept in shape in a short time by adjusting the support adjustment component, thereby playing a reliable shape-keeping role. Compared with the conformal method of restoring the aircraft to the original manufacturing jig and hoisting the aircraft to a fixed conformal structure for positioning, the maintenance efficiency is improved and the operating cost is reduced.

[0021] The present invention also proposes a method for restoring the intersection holes in the skin repair area, which can realize accurate re-production at the original intersection position of the original skin on the new skin. Compared with the method of drilling holes in the original aircraft structure intersection holes on the new skin, the damage to the original aircraft structure intersection holes during the drilling process is avoided, the hole making accuracy is improved, and the quality of the original aircraft structure intersection holes is guaranteed. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 A schematic diagram of the restoration of the intersection hole in the aircraft skin repair area of ​​the present invention;

[0023] Figure 2This is a schematic diagram of the structure of the aircraft skin repair area;

[0024] Figure 3 It is a schematic diagram of the structure of the adjustable support assembly;

[0025] Figure 4 It is a schematic diagram of the structure of the positioning component of the skin connection frame;

[0026] Figure 5 Schematic diagram of the support positioning and hole making components for system and finished product installation;

[0027] Figure 6 It is a schematic diagram of the structure of the fuselage structure support bracket assembly;

[0028] Among them, there are damaged skin 100, damaged part 101, tail section connecting frame 200, aircraft main load-bearing frame 10, support adjustment assembly 01, skin connecting frame positioning assembly 02, system and finished product installation support positioning and hole making assembly 03, fuselage structure support bracket assembly 04, adjustable support 01-01, screw 01-01-01, nut 01-01-02, conformal connecting plate 02-01, connecting bushing 02-01-01, system and finished product installation support positioning assembly 03-01, hole making assembly 03-02, bracket 04-01, screw elevator 04-02, and pallet 04-03. DETAILED DESCRIPTION

[0029] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. 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.

[0030] Figure 1 It is a schematic diagram of the shape preservation and restoration of the intersection hole in the repair area when repairing the skin damage at the aircraft tail section connection frame according to a non-limiting embodiment of the present invention.

[0031] The top of the aircraft skin 100 is close to the engine and is a part that is prone to burns. When the composite skin is burned, it will debond and wrinkle, which will damage the skin strength and stiffness, seriously affecting the aerodynamic characteristics of the aircraft and the service life of the aircraft skin. In order to repair the damaged skin, the damaged area of ​​the skin must be cut off, replaced with a new skin and reinforced with a patch. The cut-off part of the skin contains a 4-φ5.2 finished product mounting bracket connection hole. After replacing the new skin, the hole must be re-made and the original coordination must be ensured so that the finished product installed at this position can be reinstalled in coordination with the finished product near the damaged skin.

[0032] Before repairing the aircraft skin, remove the relevant systems or finished products from the mounting brackets and disconnect the tail boom from the fuselage.

[0033] like Figure 1 As shown and as a non-limiting embodiment, the aircraft is first lifted up using a jack, and the fuselage structure support bracket assembly 04 is installed at the position of the aircraft main load-bearing frame 10 for supporting and fixing the aircraft. According to the support position, a transverse support bracket assembly or a longitudinal support bracket assembly can be selected. As a non-limiting embodiment, the fuselage structure support bracket assembly 04 can mainly include a bracket 04-01, a screw elevator 04-02 and a support plate 04-03; Figure 6 It is a schematic diagram of a fuselage structure support bracket assembly 04 with a conformal structure for skin repair according to the present invention; bracket 04-01 adopts a triangular bracket structure, the bottom of the bracket is a flat structure, a spiral elevator 04-02 is provided on the upper end of bracket 04-01, and a pallet 04-03 is installed on the upper end of the spiral elevator 04-02, and the height of the pallet 04-03 is adjusted by adjusting the spiral elevator 04-02; during implementation, multiple people cooperate to adjust the spiral elevators 04-02 of each fuselage structure support bracket assembly 04 at the same time, and the aircraft is adjusted to a suitable height with the skin connection frame positioning assembly 02 by raising or lowering the pallet 04-03, so as to facilitate the smooth connection of the conformal connection plate 02-01 and the tail section connection frame 200.

[0034] Figure 3 It is a schematic diagram of the support adjustment component 01 according to the present invention, which can mainly include an adjustable support component 01-01, a screw rod 01-01-01, and a nut 01-01-02. The height position of the support adjustment component 01 is controlled and adjusted by rotating the nut 01-01-02, and the left and right positions of the support adjustment component 01 are controlled and adjusted by external force. After coordinated adjustment, the conformal connecting plate 02-01 of the skin connecting frame positioning component 02 is connected to the bushing 02-01-01, and then concentrically connected with the connecting hole on the tail section connecting frame 200, and then an 8-φ6.2 bolt pin is inserted for positioning and tightening.

[0035] Figure 5 It is a schematic diagram of the system and finished product mounting support positioning and hole making assembly 03 according to the present invention, which can mainly include the system and finished product mounting support positioning assembly 03-01 and the system and finished product mounting support hole making assembly 03-02. After the system and finished product mounting support positioning assembly 03-01 is connected to the system or finished product mounting support connection hole near the damaged area of ​​the aircraft skin by using a 2-φ6.2 spiral pin, an aluminum gasket is added to adjust the gap position at the connection between the positioning assembly and the body and epoxy resin is poured. After curing, a stable structure is formed, which plays a role in conforming and positioning the aircraft structure.

[0036] Test and adjust the installation position of the system and the finished product installation support hole making component 03-02, so that the gap between the hole making component 03-02 and the damaged skin profile is 1-2mm, and reserve thickness space for the subsequent demoulding cloth to ensure that the installation position of the support hole making component 03-02 is more accurate;

[0037] A connection and fixing hole is provided between the hole-making component 03-02 and the conformal structure, and a pin is used for connection and fixing.

[0038] For specific implementation, see the attached Figure 2 , Figure 2 It is a schematic diagram of a damaged skin 100 according to the present invention, including a damaged part 101. According to the original finished support connection hole position on the damaged skin 100, the connection hole position on the trial hole assembly 03-02 is compared. If the hole assembly 03-02 is not holed, the approximate position of the hole can be determined by marking. After the test, make a 4-φ14 large hole at the marked position of the hole making component 03-02. After making the hole, insert a drill sleeve (inner diameter φ5.2, outer diameter φ10) and a φ5.2 pin at the same time in the 4-φ14 large hole and the original finished product support connection hole on the damaged skin 100. After the pin is inserted and fixed, the surface of the area near the finished product mounting bracket connection hole on the damaged part 101 of the damaged skin 100 and the finished product mounting bracket connection hole are used as the filling reference. First, the demoulding cloth is attached to the damaged part 101 of the skin, and epoxy resin is poured between the drill sleeve (inner diameter φ5.2, outer diameter φ10) and the φ14 large hole and between the hole making component 03-02 and the demoulding cloth. After the epoxy resin is cured, pull out the pin.

[0039] The release cloth is used to prevent the epoxy resin from adhering to the skin and being difficult to clean. After the epoxy resin is cured, clean the release cloth and excess epoxy resin between the system and finished product mounting bracket positioning components and the damaged skin, and pull out the 4-φ5.2 pin from the drill sleeve.

[0040] Remove hole making assembly 03-02 from the conformal structure.

[0041] Cut the damaged skin 100. Repair and install new skin.

[0042] Reinstall hole making assembly 03-02 on the conformal structure.

[0043] Using hole making component 03-02 Drilling holes in new skin Finished product mounting bracket connection holes.

[0044] The above specific implementation methods or cases are only used to explain the technical solutions of the present invention, and are not intended to limit the present invention. Any parts not described in detail are regarded as conventional technical means in the art. A person of ordinary skill in the art should understand that based on the design concept of the present application, the technical solutions described in the aforementioned implementation methods should be adaptively modified, or some or all of the technical features therein should be replaced by equivalents. These modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A device for restoring intersection holes in aircraft skin repair areas, characterized in that: The skin repair area conformal structure is used to shape the aircraft skin repair area. The skin repair conformal structure includes a support adjustment component, a skin connection frame positioning component, a system and finished product installation support positioning and hole making component, and a fuselage structure support bracket component; Among them, the skin connection frame positioning assembly, the system and finished product installation support positioning and hole making assembly are connected and fixed after being precisely installed and debugged in sequence on the basis of the support adjustment assembly; the relative positions of the skin connection frame positioning assembly and the system and finished product installation support positioning and hole making assembly are fixed and not adjusted; the feet of the support adjustment assembly are adjustable, and by adjusting the height of the skin connection frame positioning assembly, the conformal structure can be positioned and connected to the aircraft structure in a short time.

2. The device for restoring and producing intersection holes in the aircraft skin repair area according to claim 1, characterized in that: The system and finished product mounting support positioning and hole-making components include two parts: a positioning component and a hole-making component. The connecting holes on the positioning component are made according to the theoretical coordinate position based on the product digital model during the conformal structure manufacturing, and the adjustment is completed; a certain gap is reserved at the connection between the positioning component and the main body. After the connecting hole of the positioning component is connected with the connecting hole of the system or finished product mounting support near the damaged area of ​​the aircraft skin, epoxy resin is poured into the gap, and a stable structure is formed after curing, which plays a conformal and positioning role for the aircraft structure; the connecting holes on the hole-making component can be made into initial holes or no holes during manufacturing, and they are poured and made on site according to the positions of the original system or finished product mounting holes on the damaged skin to form a hole-making drill template for restoring the intersection holes in the skin repair area.

3. The device for restoring and producing intersection holes in the aircraft skin repair area according to claim 1, characterized in that: The skin connection frame positioning assembly includes: a connection frame, a conformal connection plate, the conformal connection plate is fixed on the connection frame, a bushing is connected in the middle of the conformal connection plate, the bushing is concentrically fixed to the connection hole on the tail section connection frame, and finally a bolt pin is inserted to position and tighten the aircraft skin repair area.

4. The device for restoring and producing intersection holes in the aircraft skin repair area as claimed in claim 3, characterized in that: There is a conformal connecting plate on the skin connecting frame positioning assembly, which is connected to the aircraft frame plane through a number of stepped bolts to play a positioning and conformal role.

5. The device for restoring and producing intersection holes in the aircraft skin repair area according to claim 1, characterized in that: The fuselage structure support bracket assembly acts on the positions of the main load-bearing support frames of the aircraft and is used to support and fix the aircraft.

6. A method for restoring intersection holes in a repair area, the method being based on the aircraft skin repair area intersection hole restoration device as claimed in any one of claims 1 to 5, characterized in that: The following steps are involved: The first step is to remove the relevant systems or finished products on the aircraft from the mounting bracket before repairing the aircraft skin; In the second step, the connection system and finished product mounting bracket positioning assembly is conformed and positioned with the system or finished product mounting bracket near the damaged skin; The third step is to test the installation system and the finished product installation support hole-making assembly on the conformal structure, and adjust the installation position of the hole-making assembly so that there is a certain gap between the hole-making assembly and the damaged skin profile; The fourth step is to use the damaged skin profile and the system or finished product mounting support connection holes on the damaged skin as the filling reference, first stick the demoulding cloth on the damaged skin, pour the epoxy resin on the plane, and determine the number and position of the filling holes on site, and then use the pin and drill sleeve to pour the drill sleeve holes according to the damaged skin system or finished product mounting support connection holes; Step 5: After the epoxy resin is cured, remove the demoulding cloth and excess epoxy resin between the system and finished product mounting bracket positioning components and the damaged skin, and pull out the pin from the drill sleeve to form a final usable hole-making component; remove the system and finished product mounting bracket hole-making components from the conformal structure; In the sixth step, after the damaged skin is replaced, the system and the finished product installation support hole-making assembly are reinstalled on the conformal structure, and the hole-making assembly obtained in the fifth step is used to make holes in the new skin.

7. A method for restoring and producing intersection holes in a repair area as claimed in claim 6, characterized in that: The gap between the hole making component and the damaged skin profile is in the range of 2-3mm.

8. A method for restoring and obtaining intersection holes in a repair area as claimed in claim 6, characterized in that: The release cloth is used to prevent the epoxy resin from adhering to the skin.

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