Quick-release type wing body butt joint pin shaft assembly and design method

Abstract

The invention belongs to the field of aircraft structure design, and particularly relates to a quick-release wing body butt joint pin shaft assembly and a design method. According to the assembly, a first lining and a second lining are installed in a lug hole of a single-lug connector; a third bushing and a fourth bushing are mounted in lug holes of the double-lug joint; a hollow pin shaft is inserted into the single-lug connector and the lug hole lining of the double-lug connector, a pin shaft gasket is arranged between the head end face of the hollow pin shaft and the lug end face of the double-lug connector, and a compensation gasket is arranged on the tail end face of the hollow pin shaft; the blanking cap is inserted into the tail part of the hollow pin shaft; the safety bolt is inserted into the hollow pin shaft through the head of the hollow pin shaft and fixedly connected with the nut in cooperation with the hollow pin shaft, and a bolt gasket is arranged between the end face of the blanking cap and the end face of the nut. The cotter pin is connected with the safety bolt and the nut. On the basis of ensuring reliable butt-joint bearing of the wings, the empennage and the fuselage pair, the requirement of quick disassembly and assembly can be met, and the maintainability of the structure is improved.

Description

Technical Field

[0001] This application belongs to the field of aircraft structural design, and specifically relates to a quick-release wing-body docking pin assembly and its design method. Background Technology

[0002] For the land transportation of large and medium-sized aircraft, considering the convenience of relocation, it is often necessary to separate the wings from the fuselage to reduce the size of the transported components. Due to the characteristics of large loads, complex stress conditions, numerous structural details, and high installation precision requirements, traditional wing-fuselage docking structures for large and medium-sized aircraft often lack the characteristics for frequent and rapid disassembly. Once docked, they are either permanently non-removable or extremely costly to disassemble and reassemble, requiring a large number of complex specialized tools and site support. This is extremely unfavorable for the off-site disassembly and assembly of aircraft wing-fuselage structures.

[0003] Traditional wing-fuselage docking primarily employs two methods: distributed and centralized. Distributed docking uses bolted group connections, which are often non-removable and designed for the same lifespan as the airframe; once the wing and fuselage are docked, replacement is not considered. Centralized docking also uses a lug and pin connection, but this method often uses a custom-made bolt for the pin, making it difficult to disassemble. Furthermore, to ensure ease of wing-fuselage docking, the bushings press-fitted into the lug holes are precision-reamed during docking to address misalignment issues caused by accumulated manufacturing tolerances. However, this method leads to bushing eccentricity, increasing the difficulty of bushing replacement in the field. These factors all contribute to the difficulty in assembling and disassembling centralized wing-fuselage docking.

[0004] With changing design and usage requirements, existing aircraft wing-body joints often require detachable designs, rendering traditional methods no longer entirely applicable. To meet the need for quick-release wing-body joints in aircraft structures, several solutions have been proposed domestically.

[0005] Option 1: This option involves designing box-shaped docking structures for the fuselage and wings. The docking structure body 1 has an interface, and the docking structure body 2 has docking components that fit the shape of the interface. Through electrically driven rotation and extension, after the wing and fuselage are docked, the docking components are inserted into docking structure body 1 to complete the wing-fuselage docking. During disassembly, the docking components retract electrically, disconnecting the wing-fuselage connection. The advantage of this option is convenient docking; however, this method results in a significant weight sacrifice in the docking structure, requires a dedicated electric drive mechanism, and is extremely difficult to implement for medium and large aircraft, as docking accuracy is hard to control.

[0006] Option 2: This option designs a quick-release mechanism for wing-body docking, employing a centralized docking joint with single and double lugs for force transmission. The pin is combined with a movable mechanism fixed to the fuselage wing surface to form a movable quick-release mechanism, allowing the pin to be inserted and removed between the single and double lugs via a push-pull mechanism. The advantages of this option are rapid assembly and disassembly capabilities and relatively high docking load reliability. However, fixing the pin to the fuselage structure increases structural cross-linking, potentially leading to cross-linking of structural failure modes. The load on the pin can easily affect the reliability of the movable mechanism, and jamming of the movable mechanism can prevent the pin from retracting or extending, affecting wing-body docking. Furthermore, this option also presents the challenge of ensuring the precision of the pin's assembly and disassembly with the docking structure.

[0007] Therefore, there is an urgent need for a technical solution to overcome or mitigate at least one of the aforementioned defects in the existing technology. Summary of the Invention

[0008] The purpose of this application is to provide a quick-release wing-body docking pin assembly and design method to solve at least one problem existing in the prior art.

[0009] The technical solution of this application is:

[0010] A quick-release wing-body docking pin assembly, installed at the wing-body docking point, includes:

[0011] A single-ear connector, wherein a first bushing and a second bushing are installed in the ear hole of the single-ear connector;

[0012] A double-ear connector, wherein a third bushing and a fourth bushing are installed in the ear holes of the double-ear connector;

[0013] A hollow pin is inserted into the ear hole bushing of the single-ear connector and the double-ear connector. A pin washer is provided between the head end face of the hollow pin and the ear plate end face of the double-ear connector, and a compensation washer is provided at the tail end face of the hollow pin.

[0014] A plug, which is inserted into the tail of the hollow pin;

[0015] A safety bolt, wherein the head of the safety bolt is inserted into the hollow pin and fixedly connected with a nut, and a bolt washer is provided between the end face of the plug and the end face of the nut;

[0016] A cotter pin connects the safety bolt and the nut.

[0017] Preferably, the hollow pin is manufactured by machining ultra-high strength steel after heat treatment, with chrome plating on the mating surfaces and cadmium-titanium plating on the remaining surfaces.

[0018] Preferably, the hollow pin's inner hole is stepped, comprising a first-level step and a second-level step;

[0019] There is a first transition section between the first-level step and the second-level step, and the first transition section has chamfered and rounded corner structural features.

[0020] There is a 3mm height difference between the first-level step and the second-level step;

[0021] There is a second transition section between the first step and the head end face of the hollow pin, and the second transition section has a chamfered structure feature.

[0022] There is a third transition section between the secondary step and the end face of the hollow pin shaft, and the third transition section has a chamfered structure.

[0023] Preferably, the diameter of the head end face of the hollow pin is 10 mm or more larger than the inner diameter of the ear piece of the double-ear connector.

[0024] Preferably, the hollow pin extends 3-5mm beyond the end face of the double-ear connector.

[0025] Preferably, the plug is made of heat-treated stainless steel and has a passivated surface.

[0026] Preferably, the diameter of the end face of the plug is 10 mm or more larger than the inner diameter of the ear piece of the double-ear connector.

[0027] Preferably, the plug is inserted into the hollow pin 5-10mm.

[0028] Preferably, the pin washer is made of heat-treated stainless steel and has a passivated surface.

[0029] Preferably, the pin washer has a thickness of 3mm or more, the inner diameter of the pin washer is larger than the outer diameter of the hollow pin, and the outer diameter of the pin washer is greater than or equal to the diameter of the head end face of the hollow pin.

[0030] Preferably, the compensation shim is manufactured from heat-treated stainless steel and has a passivated surface.

[0031] Preferably, after the compensation gasket is fitted to the end face of the double-ear connector, a gap of at least 0.5 mm is maintained between it and the end face of the plug. The inner diameter of the compensation gasket is 0.5 mm or more larger than the outer diameter of the hollow pin, and the compensation gasket is 10 mm or more larger than the inner diameter of the double-ear connector.

[0032] Preferably, the bolt washer is made of heat-treated stainless steel and has a passivated surface.

[0033] Preferably, the bolt washer has a thickness of 3mm or more, the inner diameter of the bolt washer is 0.5mm or more larger than the outer diameter of the hollow pin, and the bolt washer is 5mm or more larger than the maximum diameter of the safety bolt head.

[0034] Preferably, if the wing-body docking point does not transmit directional loads, the gap between the lugs of the single-ear connector and the double-ear connector is not less than the relative displacement between the lugs.

[0035] Preferably, if the wing-body docking point transmits directional loads, then an assembly shim is provided between the third bushing end face and the first bushing end face, and between the second bushing end face and the fourth bushing end face.

[0036] Preferably, the thickness of the assembly shim is greater than or equal to the gap between the bushings, the outer diameter of the assembly shim is greater than or equal to the outer diameter of the bushing end face, and the inner diameter of the assembly shim is 0.5 mm or more greater than the outer diameter of the hollow pin.

[0037] The second aspect of this application provides a design method for a quick-release wing-body docking pin assembly, used to design the quick-release wing-body docking pin assembly as described above, the design method comprising:

[0038] Step S1: Based on the load size at the wing-body docking point and the assembly and cross-linking relationship of each part, complete the detailed design of the hollow pin shaft;

[0039] Step S2: Based on the design dimensions of the hollow pin and the actual load-bearing requirements, complete the selection and design of the bolt assembly, which includes safety bolts, nuts, and cotter pins.

[0040] Step S3: Based on the design dimensions of the hollow pin, and considering the functionality of the plug structure, complete the detailed design of the plug.

[0041] Step S4: Based on the design of the hollow pin and bolt assembly, select suitable pin washers, compensation washers, and bolt washers;

[0042] Step S5: If the wing-body docking point does not transmit directional load, control the gap between the single-ear joint and the double-ear joint to prevent the lugs from contacting each other directly. If the wing-body docking point transmits directional load, compensate the gap between the single-ear joint and the double-ear joint by assembling shims.

[0043] Step S6: Complete the assembly of the quick-release wing-body docking pin assembly;

[0044] Step S7: Conduct assembly compensation design for the wing-body docking intersection.

[0045] The invention has at least the following beneficial technical effects:

[0046] The quick-release wing-body docking pin assembly of this application can ensure reliable docking and load-bearing of the wing, tail and fuselage, while meeting the requirement of quick disassembly and assembly, and improving the maintainability of the structure. Attached Figure Description

[0047] Figure 1 This is a schematic diagram of a quick-release wing-body docking pin assembly according to one embodiment of this application;

[0048] Figure 2 This is a schematic diagram of the clearance design of the quick-release wing-body docking pin assembly according to one embodiment of this application;

[0049] Figure 3 This is an axial view of a hollow pin shaft according to one embodiment of this application;

[0050] Figure 4 This is a cross-sectional view of a hollow pin shaft according to one embodiment of this application;

[0051] Figure 5 This is an angled view of a cover according to one embodiment of this application;

[0052] Figure 6 This is another angle view of the cover according to one embodiment of this application;

[0053] Figure 7 This is a flowchart illustrating a design method for a quick-release wing-body docking pin assembly according to one embodiment of this application. Detailed Implementation

[0054] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0055] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this application.

[0056] The following is in conjunction with the appendix Figures 1 to 7 This application will be described in further detail.

[0057] This application provides a quick-release wing-body docking pin assembly, installed at the wing-body docking point, including: a single-ear connector 1, a double-ear connector 2, a hollow pin 3, a plug 9, a safety bolt 11, and a cotter pin 12.

[0058] like Figure 1-2 As shown, a first bushing 6 and a second bushing 7 are installed in the ear hole of the single-ear connector 1; a third bushing 5 and a fourth bushing 8 are installed in the ear hole of the double-ear connector 2; a hollow pin 3 is inserted into the ear hole bushings of the single-ear connector 1 and the double-ear connector 2, and a pin washer 4 is provided between the head end face of the hollow pin 3 and the ear plate end face of the double-ear connector 2, and a compensation washer 14 is provided at the tail end face of the hollow pin 3; a plug 9 is inserted into the tail of the hollow pin 3; a safety bolt 11 is inserted into the hollow pin 3 by the head of the hollow pin 3 and is fixedly connected with a nut 13, and a bolt washer 10 is provided between the end face of the plug 9 and the end face of the nut 13; a cotter pin 12 connects the safety bolt 11 and the nut 13 to prevent the nut from rotating accidentally.

[0059] The wing-fuselage docking of a certain type of aircraft adopts a centralized intersection point single / double lug joint. The quick-release wing-fuselage docking pin assembly of this application is responsible for connecting the single lug joint 1 and the double lug joint 2 to realize the transfer of shear load. The single lug joint 1 and the double lug joint 2 are internally press-fitted with bushings to prevent the wear of the hollow pin 3 and the lugs from directly damaging the main structure of the fuselage. The bushings are made of Qbe2 material.

[0060] In a preferred embodiment of this application, the hollow pin 3 is used to transfer the concentrated shear load from the wing / tail to the fuselage. It is inserted into the lug hole of the single / double lug connector bushing. The appropriate material is selected according to the load size. Generally, it can be machined from ultra-high strength steel after high temperature heat treatment, such as A100 (2000Mpa grade) or GH4169 (1500Mpa grade). The surfaces with mating relationships are chrome plated, and the remaining surfaces are cadmium-titanium plated for corrosion protection.

[0061] like Figure 3-4As shown, in this embodiment, the inner hole of the hollow pin 3 is stepped, including a first-level step 3.5 and a second-level step 3.9. The diameter of the first-level step 3.5 is smaller and the same as the diameter of the safety bolt 11, ensuring that the safety bolt 11 does not loosen. The second-level step 3.9 is consistent with the outer diameter of the plug, ensuring that the plug 9 can be smoothly inserted into the hollow pin 3. A first transition section 3.6 is located between the first-level step 3.5 and the second-level step 3.9. This first transition section 3.6 features chamfered and rounded corners to prevent stress concentration. There is a height difference of approximately 3mm between the first-level step 3.5 and the second-level step 3.9 to prevent the hollow pin 3 from directly contacting the safety bolt 11 under load. A second transition section 3.2 is located between the first-level step 3.5 and the head end face 3.1 of the hollow pin 3. This second transition section 3.2 features chamfered corners. A third transition section 3.7 is located between the second-level step 3.9 and the tail end face of the hollow pin 3. This third transition section 3.7 features chamfered corners to prevent interference and gaps between the plug 9 and the hollow pin 3. A rounded corner structure 3.4 is provided between the head of the hollow pin 3 and the rod. The diameter of the head end face 3.1 of the hollow pin 3 is 10mm or more larger than the inner diameter of the lug of the double-ear connector 2 to ensure that the hollow pin 3 will not detach from the lug. The hollow pin 3 extends 3-5mm beyond the end face of the double-ear connector 2, leaving sufficient margin while preventing the bolt preload from acting directly on the ear piece.

[0062] In one embodiment of this application, the outer diameter 3.3 of the hollow pin 3 is consistent with the inner diameter of the bushing. The diameter of the first step 3.5 of the hollow pin 3 is smaller, with a tolerance of H7, and is the same as the diameter of the safety bolt 11 to ensure that the safety bolt 11 does not loosen. The outer diameter 9.3 of the second step 3.9 is consistent with the outer diameter 9.3 of the plug 9, with a fit tolerance of H7g6. The tolerance of the second step 3.9 is H8, and the tolerance of the outer diameter 9.3 of the plug 9 is g7. The height difference between the first step 3.5 and the second step 3.9 is 3mm. The diameter of the head end face of the hollow pin 3 is 10mm larger than the inner diameter of the lug. The tail of the hollow pin 3 extends 5mm beyond the double lug end face.

[0063] Safety bolt 11, nut 13, and cotter pin 12 constitute a bolt assembly. Safety bolt 11 is used to lock the hollow pin 3, ensuring that the components do not experience unintended relative displacement. Located inside the hollow pin 3, a high-strength bolt is preferred; in this embodiment, a YSA151N20 standard bolt is selected for safety bolt 11. Considering breakage safety design, safety bolt 11 should be able to withstand 67% of the ultimate load without failure, and safety bolt 11 should have a cotter pin hole. Nut 13 is a high-strength self-locking nut with a pull-out cotter pin 12, using a YSA516 standard nut for easy assembly and disassembly of the pin assembly; the tightening torque is in accordance with HB 6586-92 to prevent nut 13 from loosening, ensure structural fit, improve bolt fatigue performance, and enhance sealing performance. The cotter pin 12 is a GB / T91-3P2X40-0Cr18Ni9Ti standard cotter pin, used to prevent the nut 13 from rotating relative to the safety bolt 11 beyond the design and thus falling off; the cotter pin 12 can be selected according to the standard cotter pin hole of the bolt.

[0064] In a preferred embodiment of this application, the plug 9 is used to prevent the hollow pin 3 from coming out, and plays an anti-dislodgement role. It is inserted into the tail end face of the hollow pin 3. The material is stainless steel 15-5PH, which is heat-treated and then precision machined and the surface is passivated.

[0065] like Figure 5-6 As shown, in this embodiment, the inner diameter of the plug 9 is the same as the diameter of the safety bolt to ensure that the safety bolt does not wobble; the diameter of the end face 9.1 of the plug 9 is 10mm or more larger than the inner diameter of the ear piece of the double-ear connector 2 to prevent the pin from coming out; the length of the plug 9 should not be too long, and the plug 9 should be inserted into the hollow pin 35-10mm, which can simplify the assembly and manufacturing process and reduce the structural weight.

[0066] In one embodiment of this application, the outer diameter 9.3 of the plug 9 is consistent with the secondary step 3.9, the inner diameter 9.2 of the plug 9 is consistent with the diameter of the safety bolt 11, and the tolerance of the inner diameter 9.2 of the plug is H7; the diameter of the end face 9.1 of the plug is 10mm larger than the inner diameter of the lug; the plug 9 is inserted into the hollow pin shaft by 5mm.

[0067] In a preferred embodiment of this application, the pin washer 4 is located between the head end face of the hollow pin 3 and the double ears to prevent direct contact between the pin and the double ears, thus avoiding damage to the structural body during disassembly and assembly. The material is 15-5PH stainless steel, heat-treated and precision-machined, with a passivated surface. The pin washer 4 has a thickness of 3mm or more, and its inner diameter is larger than the outer diameter of the hollow pin 3 to ensure easy disassembly and assembly. The outer diameter of the pin washer 4 is greater than or equal to the 3.1mm diameter of the head end face of the hollow pin 3.

[0068] In a preferred embodiment of this application, the compensation shim 14 is located between the end face of the plug 9 and the end face of the double ears, adjusting the gap between the end face of the plug 9 and the double ears. The material is stainless steel 15-5PH, 2mm thick, manufactured using heat-treated stainless steel machining, with a passivated surface. After the compensation shim 14 is fitted with the end face of the double ear connector 2, a gap of at least 0.5mm is maintained between it and the end face of the plug 9 to prevent direct contact between the end face of the plug and the double ears after connector deformation, thus preventing the nut from being pried open and subjected to undesigned tensile loads. The inner diameter of the compensation shim 14 is 0.5mm or more larger than the outer diameter of the hollow pin 3 to ensure easy disassembly and assembly. The compensation shim 14 is 10mm or more larger than the inner diameter of the double ear connector 2.

[0069] In a preferred embodiment of this application, the bolt washer 10 is located on the bolt head side to prevent direct contact between the bolt head and the pin, thus avoiding damage to the structural body during disassembly and assembly. The material is medium-to-high strength stainless steel, such as 15-5PH, which is heat-treated and then precision-machined with a passivated surface. The bolt washer 10 has a thickness of 3mm or more and should not be too thin. The inner diameter of the bolt washer 10 is 0.5mm or more larger than the outer diameter of the hollow pin 3 to ensure easy disassembly and assembly. The bolt washer 10 is 5mm or more larger than the maximum diameter of the head of the safety bolt 11.

[0070] In this application's quick-release wing-body docking pin assembly, if the wing-body docking point does not transmit directional loads (the lugs bear out-of-plane loads), the gap between the single and double lug joints is controlled to prevent direct contact between the lugs. If the wing-body docking point transmits directional loads, a dedicated assembly shim 15 is designed to compensate for the gap between the single and double lugs. If there is no requirement to transmit directional loads at the wing-body docking point: [This option is omitted]. Figure 1 As shown in the assembly shim 15, the gaps A and B between the single and double lugs should be no less than the relative displacement between the single and double lugs. If the relative displacement cannot be assessed and the design does not allow for relative displacement between the single and double lugs, it is recommended that the values ​​of gaps A and B be no less than 8% of the outer diameter of the pin shaft and no less than 2 mm. If there is a requirement to transfer directional loads at the wing-body docking point: control the gaps A and B between the single and double lugs to be between 1 and 2 mm, and design the assembly shim 15 accordingly.

[0071] In a preferred embodiment of this application, the assembly shim 15 is located between the end faces of the press-fitted bushings in the single and double lugs, filling the gap between the single-lug and double-lug joints. This ensures that the directional load can be transferred between the single and double lugs after assembly through the fit of the assembly shim. The material is medium-high strength stainless steel, such as 15-5PH, which is heat-treated and then precision-machined with a passivated surface. The thickness of the assembly shim 15 is greater than or equal to the gap between the bushings, ensuring that there is no gap between the single and double lugs affecting the transfer of directional load. The outer diameter of the assembly shim 15 is greater than or equal to the outer diameter of the bushing end face, ensuring smooth load transfer. The inner diameter of the assembly shim 15 is 0.5 mm or more larger than the outer diameter of the hollow pin 3, ensuring simple assembly and disassembly.

[0072] Based on the aforementioned quick-release wing-body docking pin assembly, a second aspect of this application provides a design method for the quick-release wing-body docking pin assembly, the design method comprising:

[0073] Step S1: Based on the load size at the wing-body docking point and the assembly and cross-linking relationship of each part, complete the detailed design of the hollow pin 3;

[0074] Step S2: Based on the design dimensions of the hollow pin 3 and the actual load-bearing requirements, complete the selection and design of the bolt assembly, which includes a safety bolt 11, a nut 13, and a cotter pin 12.

[0075] Step S3: Based on the design dimensions of the hollow pin 3 and considering the structural functionality of the plug 9, complete the detailed design of the plug 9.

[0076] Step S4: Based on the design of the hollow pin 3 and bolt assembly, select suitable pin shim 4, compensation shim 14, and bolt shim 10.

[0077] Step S5: If the wing-body docking point does not transmit directional load, control the gap between the single-ear connector 1 and the double-ear connector 2 to prevent the lugs from contacting directly. If the wing-body docking point transmits directional load, compensate the gap between the single-ear connector 1 and the double-ear connector 2 by assembling the shim 15.

[0078] Step S6: Complete the assembly of the quick-release wing-body docking pin assembly;

[0079] Step S7: Conduct assembly compensation design for the wing-body docking intersection.

[0080] In a preferred embodiment of this application, in step S6, the assembly relationship between the components of the pin assembly is as follows:

[0081] a) The bottom hole of the single-ear connector 1 and the double-ear connector 2 adopts an interference fit with the bushing to prevent the bushing from rotating or falling out. The interference tolerance range is 0.01mm~0.055mm, and the standard tolerance H7 / s6 is recommended.

[0082] b) The bushing inner hole and the hollow pin 3, and the hollow pin 3 and the safety bolt 11 are all fitted with a small clearance to facilitate disassembly. The clearance tolerance range is between 0.009mm and 0.055mm. The standard tolerance H7 / g6 is recommended.

[0083] c) If assembly shim 15 exists, assembly shim 15 shall be installed first. When the thickness of the assembly shim exceeds the measured value of gap A and B, the assembly shim shall be ground and repaired. If there is no assembly shim 15, skip this step.

[0084] d) The hollow pin 3 and the pin washer 4 are assembled together and inserted into the bushing after the single and double lugs are fitted. It is recommended that the outer diameter of the hollow pin 3 be 3.3 with a tolerance of g6. The hollow pin 3 and the bushing are fitted with a clearance fit to ensure that the hollow pin 3 can be smoothly inserted or removed.

[0085] e) The compensation shim 14 mates with the pin 3;

[0086] f) Insert the plug 9 into the secondary step 3.9 of the hollow pin 3. It is recommended that the secondary step 3.9 of the hollow pin and the outer diameter 9.3 of the plug 9 adopt a clearance fit to ensure smooth disassembly and assembly. The clearance tolerance should be controlled at 0.007mm~0.065mm, and the standard tolerance H8 / g7 is recommended.

[0087] g) Check the gap between the plug 9 and the compensation gasket 14. The gap should not be less than 0.5 mm.

[0088] h) Safety bolt 11 is inserted into hollow pin 3. Safety bolt 11 is a standard aviation bolt. It fits with the first step 3.5 of hollow pin 3 and the inner diameter 9.2 of plug 9. The inner diameter 9.2 of plug 9, the first step 3.5 of hollow pin 3, safety bolt 11 and hollow pin 3 are clearance fit to facilitate disassembly and assembly. The clearance tolerance is controlled at 0.007~0.045mm. It is recommended to use standard tolerance H7 / g6.

[0089] i) The nut washer 10 mates with the safety bolt 11;

[0090] j) Tighten nut 13 to the specified torque according to HB 6586-92;

[0091] k) Insert the cotter pin 12 and connect the nut 13 and the safety bolt 11;

[0092] l) Whether the measured gaps A, B, and C meet the design requirements.

[0093] In one embodiment of this application, the inner diameter tolerance of the single-ear connector 1 and the double-ear connector 2 is controlled at H7, and the outer diameter tolerance of bushings 5, 6, 7, and 8 is controlled at s6. The bushings and the ear pieces are in an interference fit to prevent accidental rotation or dislodgement of the bushings; the inner diameter tolerance of the bushings is controlled at H7; the hollow pin 3 and the pin washer 4 are assembled and inserted into the bushing after the single and double ear fit is completed; the outer diameter 3.3 of the hollow pin 3 is controlled at g6, and the hollow pin 3 and the bushing are in a clearance fit to ensure that the hollow pin 3 can be smoothly inserted or removed; the compensation washer 14 is fitted with the pin 3; the plug 9 is inserted into the secondary step 3.9 of the hollow pin 3; the tolerance of the secondary step 3.9 of the hollow pin 3 is controlled at H8, and the outer diameter of the plug 9 is controlled at g6. The diameter 9.3 tolerance is controlled as g7. The plug 9 and the hollow pin 3 are clearance fit to ensure smooth disassembly and assembly. Check the gap between the plug 9 and the compensation shim 14. The gap should not be less than 0.5mm. If it is less than 0.5mm, the compensation shim is allowed to be ground. The safety bolt 11 is inserted into the hollow pin 3. The safety bolt 11 is a standard aviation bolt. It fits with the first step 3.5 of the hollow pin 3 and the inner diameter 9.2 of the plug 9. The tolerance of the inner diameter 9.2 of the plug 9 and the first step 3.5 of the hollow pin 3 is selected as H7 to ensure that the safety bolt 11, the plug 9 and the hollow pin 3 are clearance fit for easy disassembly and assembly. The nut washer 10 fits with the safety bolt 11. Tighten the nut 13. The tightening torque shall be in accordance with HB 6586-92. Insert the cotter pin 12 to connect the nut 13 and the safety bolt 11.

[0094] In a preferred embodiment of this application, step S7, performing intersection assembly compensation design, includes:

[0095] a) In the manufacturing process, the inner holes of the single-ear connector 1 and the double-ear connector 2 are machined using the same set of drilling templates;

[0096] b) The inner diameter of the single-ear connector 1 and the double-ear connector 2 has a 2mm margin based on the design diameter;

[0097] c) With the allowance left for single-ear joint 1 and double-ear joint 2, carry out wing-body docking and complete assembly attitude correction;

[0098] d) After confirming that the relative positions of the wing and fuselage are correct, use an automatic feed drill to fine ream the inner holes of the single-ear connector 1 and the double-ear connector 2 to ensure that the inner holes of the single-ear and double-ear connectors are completely coaxial, and finally fine ream until the inner diameter of the lugs of the single-ear connector 1 and the double-ear connector 2 is the design diameter.

[0099] e) Cold shrink fitting of concentric bushings, after fitting is completed;

[0100] f) After the bushing is pressed into place, the bushing concentric hole is reamed again until the inner hole of the bushing reaches the design diameter.

[0101] By using the above intersection compensation method, it is ensured that all the pressed bushings are concentric bushings.

[0102] This application presents a quick-release wing-fuselage docking pin assembly and its design method, addressing the rapid assembly and disassembly requirements of aircraft wing-fuselage docking. It enables rapid assembly and disassembly of wing, tail, and other docking structures with the fuselage in the field. A corresponding intersection compensation method is proposed to ensure convenient assembly and disassembly of the docking structure, ease of implementation, and reliable load-bearing capacity. This docking assembly has the characteristic of transmitting large loads while enabling rapid structural disassembly, good maintainability, and its assembly and disassembly do not affect the main structure. It has the following beneficial effects:

[0103] (1) The connection method of safety bolt + hollow pin shaft provides double protection against breakage;

[0104] (2) The assembly relationship of each component of the pin assembly is clear, and disassembly and installation are convenient;

[0105] (3) Hollow pin + plug + bolt, to avoid excessive stress at the root of the lug caused by bolt preload;

[0106] (4) Decoupling design of bending moment and heading load transmission avoids difficulties in the force transmission analysis of heading load, which may cause excessive internal forces;

[0107] (5) A margin control method is proposed, including clearance and hinge hole margin, to compensate for the attitude adjustment needs during the wing assembly process, prevent the pin jamming problem caused by bushing eccentricity, reduce the difficulty of wing-body docking and disassembly, and greatly improve the replaceability of bushing.

[0108] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A quick-release wing-body docking pin assembly, installed at the wing-body docking point, characterized in that, include: A single-ear connector (1) is provided with a first bushing (6) and a second bushing (7) installed in the ear hole of the single-ear connector (1). A double-ear connector (2), wherein a third bushing (5) and a fourth bushing (8) are installed in the ear holes of the double-ear connector (2); Hollow pin (3) is inserted into the ear hole bushing of the single ear connector (1) and the double ear connector (2). A pin washer (4) is provided between the head end face of the hollow pin (3) and the ear plate end face of the double ear connector (2). A compensation washer (14) is provided at the tail end face of the hollow pin (3). A plug (9) is inserted into the tail of the hollow pin (3); Safety bolt (11), the safety bolt (11) is inserted into the hollow pin (3) by the head of the hollow pin (3) and fixedly connected with the nut (13). A bolt washer (10) is provided between the end face of the plug (9) and the end face of the nut (13). A cotter pin (12) connects the safety bolt (11) and the nut (13).

2. The quick-release wing-body docking pin assembly according to claim 1, characterized in that, The hollow pin (3) is machined from heat-treated ultra-high strength steel. The surfaces with mating relationships are chrome-plated, and the remaining surfaces are cadmium-titanium-plated.

3. The quick-release wing-body docking pin assembly according to claim 2, characterized in that, The hollow pin (3) has a stepped inner hole, including a first-level step (3.5) and a second-level step (3.9). There is a first transition section (3.6) between the first step (3.5) and the second step (3.9), and the first transition section (3.6) has the structural features of chamfered corners and rounded corners; There is a 3mm height difference between the first step (3.5) and the second step (3.9); There is a second transition section (3.2) between the first step (3.5) and the head end face (3.1) of the hollow pin (3), and the second transition section (3.2) has a chamfered structure feature; There is a third transition section (3.7) between the second-level step (3.9) and the tail end face of the hollow pin (3), and the third transition section (3.7) has a chamfered structure.

4. The quick-release wing-body docking pin assembly according to claim 3, characterized in that, The diameter of the head end face (3.1) of the hollow pin (3) is 10 mm or more larger than the inner diameter of the ear piece of the double ear connector (2).

5. The quick-release wing-body docking pin assembly according to claim 4, characterized in that, The hollow pin (3) extends 3-5mm beyond the end face of the ear piece of the double ear connector (2).

6. The quick-release wing-body docking pin assembly according to claim 5, characterized in that, The plug (9) is made of heat-treated stainless steel and has a passivated surface.

7. The quick-release wing-body docking pin assembly according to claim 6, characterized in that, The diameter of the end face (9.1) of the plug (9) is 10 mm or more larger than the inner diameter of the ear piece of the double-ear connector (2).

8. The quick-release wing-body docking pin assembly according to claim 7, characterized in that, The plug (9) is inserted into the hollow pin (3) by 5-10 mm.

9. The quick-release wing-body docking pin assembly according to claim 8, characterized in that, The pin gasket (4) is made of heat-treated stainless steel and has a passivated surface.

10. The quick-release wing-body docking pin assembly according to claim 9, characterized in that, The thickness of the pin washer (4) is 3mm or more, the inner diameter of the pin washer (4) is greater than the outer diameter of the hollow pin (3), and the outer diameter of the pin washer (4) is greater than or equal to the diameter of the head end face (3.1) of the hollow pin (3).

11. The quick-release wing-body docking pin assembly according to claim 10, characterized in that, The compensation pad (14) is made of heat-treated stainless steel and has a passivated surface.

12. The quick-release wing-body docking pin assembly according to claim 11, characterized in that, After the compensation gasket (14) is attached to the end face of the ear piece of the double-ear connector (2), a gap of at least 0.5 mm is maintained between it and the end face of the plug (9). The inner diameter of the compensation gasket (14) is 0.5 mm or more larger than the outer diameter of the hollow pin (3), and the compensation gasket (14) is 10 mm or more larger than the inner diameter of the ear piece of the double-ear connector (2).

13. The quick-release wing-body docking pin assembly according to claim 12, characterized in that, The bolt washer (10) is made of heat-treated stainless steel and has a passivated surface.

14. The quick-release wing-body docking pin assembly according to claim 13, characterized in that, The bolt washer (10) has a thickness of 3 mm or more, the inner diameter of the bolt washer (10) is 0.5 mm or more larger than the outer diameter of the hollow pin (3), and the bolt washer (10) is 5 mm or more larger than the maximum diameter of the head of the safety bolt (11).

15. The quick-release wing-body docking pin assembly according to claim 14, characterized in that, If the wing-body docking point does not transmit directional load, the gap between the lugs of the single-ear connector (1) and the double-ear connector (2) shall not be less than the relative displacement between the lugs.

16. The quick-release wing-body docking pin assembly according to claim 15, characterized in that, If the wing-body docking point transmits the directional load, then an assembly gasket (15) is provided between the end face of the third bushing (5) and the end face of the first bushing (6), and between the end face of the second bushing (7) and the end face of the fourth bushing (8).

17. The quick-release wing-body docking pin assembly according to claim 16, characterized in that, The thickness of the assembly shim (15) is greater than or equal to the gap between the bushings, the outer diameter of the assembly shim (15) is greater than or equal to the outer diameter of the bushing end face, and the inner diameter of the assembly shim (15) is 0.5 mm or more greater than the outer diameter of the hollow pin (3).

18. A design method for a quick-release wing-body docking pin assembly, used to design the quick-release wing-body docking pin assembly as described in any one of claims 1 to 17, characterized in that, Design methods include: Step S1: Based on the load size at the wing-body docking point and the assembly cross-linking relationship of each part, complete the detailed design of the hollow pin shaft (3); Step S2: Based on the design dimensions of the hollow pin (3) and the actual load-bearing requirements, complete the selection design of the bolt assembly, which includes a safety bolt (11), a nut (13), and a cotter pin (12). Step S3: Based on the design dimensions of the hollow pin (3), and considering the structural functionality of the plug (9), complete the detailed design of the plug (9); Step S4: Based on the design of the hollow pin (3) and bolt assembly, select suitable pin washers (4), compensation washers (14), and bolt washers (10). Step S5: If the wing-body docking point does not transmit directional load, control the gap between the single-ear connector (1) and the double-ear connector (2) to prevent the lugs from contacting each other directly. If the wing-body docking point transmits directional load, compensate the gap between the single-ear connector (1) and the double-ear connector (2) by using the assembly shim (15). Step S6: Complete the assembly of the quick-release wing-body docking pin assembly; Step S7: Conduct assembly compensation design for the wing-body docking intersection.

Images