A split flexible drill jig kit and method for hole making of aircraft joint parts

Abstract

The present invention provides a split flexible drill jig kit and method for hole-making of aircraft joint parts, belonging to the field of aircraft assembly and manufacturing. The split flexible drill jig kit includes a lower drill template and an upper drill template, which are clamped on the vertical surface of the joint parts from both sides. A depression is made in the middle of the upper end of the lower drill template, and a threaded hole is made in the middle of the depression, which is matched with a central positioning pin. The positioning and fixing of the joint parts are realized through the circular hole of the bushing on the vertical surface. The upper drill template is provided with threaded holes in the vertical direction, and the joint parts are pressed on the lower drill template through pressing bolts. Both the upper and lower drill templates are provided with through holes in the horizontal direction, with quick-release drill sleeves built in, and threaded holes are made beside the through holes, and the locking and limiting of the limiting bolts are realized through the limiting bolts. During use, the joint parts fixed on the aircraft structure are positioned, the lower template and the upper template are installed in sequence, and finally the hole-making is completed. The present invention improves the hole-making quality and efficiency and solves the problem that holes cannot be made in the joint under closed conditions.

Description

Technical Field

[0001] The present invention belongs to the field of aircraft assembly manufacturing, and relates to a split flexible drill jig kit and method for drilling holes in aircraft joint parts. Background Art

[0002] In the process of modern aircraft assembly manufacturing, joint parts are widely used in the docking assembly of intersection components. The installation quality of the joints affects the coordination and interchangeability of the docking assembly, as well as the flight safety and service life of the aircraft. Therefore, the installation quality of the fasteners that fixedly connect the joints and the structure is an important quality index. How to ensure the perpendicularity of the hole drilling between the joints and the structure is an important research content in the field of aircraft assembly. At present, it is mainly difficult to control the perpendicularity of the hole drilling between aircraft joint parts and the structure in the following two aspects:

[0003] 1. The hole drilling space of the stiffener structure is not open

[0004] The overall shape of the joint part is T-shaped, including a bottom surface and a vertical surface in the middle. The vertical surface is provided with a bushing round hole, and holes need to be drilled on the bottom surface. It is usually installed at an important position on the aircraft design separation surface and is a key part for the damage tolerance design of the aircraft structure. Usually, stiffeners will be set on the joint part during the design process. Due to the small overall shape of the joint part itself, the presence of stiffening ribs causes the structure to be not open, and a general-purpose vertical drill cannot be applied, and the drill jig cannot be fixed either.

[0005] In addition, due to the influence of multiple vertical ribs on the joint structure, the aperture of the joint web hole is small, and it is difficult to clamp and fix with a general drill jig, and the accuracy of hole drilling cannot be guaranteed.

[0006] 2. The accumulated error of analog coordinate positioning is large

[0007] Aircraft joint parts generally involve the coordinated positioning of multiple joints, and generally adopt the analog coordinate positioning method, that is, the dimensional relationship is transmitted through an analog gauge and the final positioning position of the joint is determined. The advantage of analog coordinate positioning is that it can ensure the coordination of subsequent joint positioning and installation. However, this method is greatly affected by the accumulated errors of actual aircraft assembly, resulting in different position states of the joints of each product, and it is impossible to directly add a hole drilling drill jig in the aircraft final assembly positioning jig for direct hole drilling.

[0008] At present, in order to obtain better assembly processability, it is usually necessary to adopt a separate joint hole making scheme during actual assembly to strictly ensure the position of the hole connecting the joint with other parts. In the actual operation process, it is generally necessary to first use analog measurement to locate the joint, use adhesive technology to fix the joint to the aircraft structure during the positioning process, remove the positioning tooling, use the line drawing method to draw the hole making point, and then the operator needs to use a handheld air drill to make holes. However, there are many holes on the joint. Using a steel ruler to draw lines not only requires attention to the hole margins and spacing, but also the risk of the operator drawing lines incorrectly. Moreover, due to the thick thickness of the hole making interlayer of the joint parts and the narrow space, it is difficult for the operator to control the verticality of the hole during the drilling process, and the problem of non-vertical holes is prone to occur. This operation process is mainly controlled by the operator, and there are phenomena of inaccurate hole position and easy to exceed the quality of hole making. In addition, there are many holes, and the efficiency of drawing lines and making holes on the rack is not high. Summary of the invention

[0009] In order to solve the above-mentioned problems existing in the prior art, the present invention provides a split flexible drilling jig kit and method for making holes in aircraft joint parts, which utilizes the bushing circular holes on the vertical surfaces of multi-reinforcement rib joint parts as a reference for flexible positioning and fixing of the drilling jig, and fixes the drilling jig by spindle positioning bolts and auxiliary positioning bolts, thereby ultimately ensuring the verticality of the holes on the joint parts.

[0010] In order to achieve the above object, the technical solution adopted by the present invention is as follows:

[0011] A split flexible drilling jig set for drilling holes in aircraft joint parts, the split flexible drilling jig set comprising a lower drilling template 1, an upper drilling template 2, a center locating pin 3, a conical locating pin 4, a quick-release drill sleeve 5, a limit bolt 6, a fixing bolt 7 and a clamping bolt 8.

[0012] The described drilling template 1 is generally rectangular in shape. There are multiple recesses on its rear side to avoid the vertical ribs of joint parts. A depression is made in the middle of its upper surface. A threaded hole is made in the middle of the bottom surface of the depression area, which cooperates with the center positioning pin 3 to pass through the bushing round hole on the vertical surface of the joint part and serves as the positioning and fixing reference for the joint part. Taking the vertical surface of the joint part as the reference surface, during positioning and installation, the center positioning pin 3 passes through the bushing round hole on the vertical surface of the joint part and is screwed into the drilling template 1, so that the vertical surface is completely fitted with the bottom surface of the depression area of the drilling template 1 without clearance. At this time, the bottom surface of the joint part is in contact with the rear side of the drilling template 1, and the bottom surface is the surface where holes need to be drilled. After positioning and installation, the height of the top end face of the center positioning pin 3 is less than the depth of the depression area to avoid interference when the upper and lower drilling templates are aligned; at both ends outside the depression area on the upper surface of the drilling template 1, a threaded hole and a round hole in the vertical direction are made, and the threaded hole and the round hole are arranged diagonally respectively. A tapered positioning pin 4 is installed in the round hole, which cooperates with the reserved hole position of the upper drilling template 2 for the quick positioning of the upper and lower drilling templates and ensures concentricity of the cooperation; multiple through holes in the horizontal direction are provided on the front end face of the drilling template 1, and quick-change drill sleeves 5 are installed in the through holes for drilling the bottom surface of the joint part. The number and position of the through holes correspond to the hole positions to be drilled, and a through groove in the vertical direction is made at the end face of the through hole for cleaning metal chips after drilling; a threaded hole is made beside the through hole on the front end face of the drilling template 1 for installing a limit bolt 6. The limit bolt 6 presses the head shoulder of the quick-change drill sleeve 5 to achieve quick locking and limiting of the quick-change drill sleeve 5 and prevent it from falling off after long-term use.

[0013] The described upper drilling template 2 is a rectangular parallelepiped with overall dimensions basically the same as those of the lower drilling template 1. The two are used in combination. Multiple recesses are made at the positions on its rear side in contact with the joint part to avoid the vertical rib area of the joint part and ensure that there is no clearance between the joint part and the drilling template when the upper and lower drilling templates are used in combination; reserved holes and through holes in the vertical direction are made at both ends of the upper drilling template 2, and the reserved holes and the through holes are arranged diagonally respectively. Among them, the reserved holes are used to cooperate with the tapered positioning pins 4 installed on the lower drilling template 1 to achieve quick positioning. Fixed bolts 7 are installed in the through holes. The heads of the fixed bolts 7 adopt the structure of internal hexagon bolts, and their tails cooperate with the threaded holes at both ends of the lower drilling template 1 to fix the positions of the upper and lower drilling templates and screw and lock them to prevent displacement during the drilling process; through holes and threaded holes in the horizontal direction are also made on the front end face of the upper drilling template 2, which are used to install quick-change drill sleeves 5 and limit bolts 6 respectively. Among them, the number and position of the through holes, that is, the quick-change drill sleeves 5, correspond to the holes to be drilled. Similarly, a through groove is made at the end face of the through hole for cleaning metal chips after drilling; multiple threaded holes in the vertical direction are made in the middle of the upper surface of the upper drilling template 2. The positions of the threaded holes avoid the quick-change drill sleeves 5 and the limit bolts 6 and are used to install pressing bolts 8. After the pressing bolts 8 are screwed into the threaded holes, their bottom ends abut against the vertical surface of the joint part after positioning and installation, pressing the joint part against the lower drilling template 1 to ensure firm pressing during the drilling process and avoid hole position errors.

[0014] Further, the quick-release drill bushing 5 and the through holes on the front end faces of the upper and lower drill templates adopt a form of small clearance fit for inserting holes. The inner bushing holes have various specifications and are replaced according to the actual feed requirement of drilling, and finally the final holes on the joint are made, solving the difficulty of making holes by disassembling the drill template multiple times.

[0015] Further, the split flexible drill die kit includes three specifications according to the structure of the joint parts and the number of holes to be drilled. The specifications are different, but the principle and structure are basically the same, and they are adaptively selected according to the types of joint parts.

[0016] A method for drilling holes in aircraft joint parts, the drilling method comprising the following steps:

[0017] The first step: pre-positioning, using an analog gauge to coordinately position the joint parts. During the positioning process, the bottom surface of the coordinately positioned joint parts is bonded and fixed to the aircraft structure by using a liquid gasket or other bonding technologies.

[0018] The second step: removing the analog gauge to prepare space and site for installing the split flexible drill die kit.

[0019] The third step: connecting the lower drill template 1 to the bushing round hole on the vertical surface of the joint parts through the center positioning pin 3, so that the lower drill template 1 is completely fitted with no gap to the bottom surface and the vertical surface of the joint parts.

[0020] The fourth step: quickly positioning the lower drill template 1 and the upper drill template 2 through the conical positioning pin 4.

[0021] The fifth step: screwing the fixing bolts 7 and the pressing bolts 8 into the bolt holes of the upper and lower drill templates to realize the fixing and locking of the upper and lower drill templates, and ensuring that the lower drill template 1 is completely fitted with no gap to the upper drill template 2 and the bottom surface of the joint parts.

[0022] The sixth step: selecting the quick-release drill bushing 5 according to the diameter of the hole to be drilled and installing it on the upper and lower drill templates, installing the limit bolt 6 to lock the quick-release drill bushing 5, and drilling holes in the joint parts respectively.

[0023] The beneficial effects of the present invention:

[0024] The split-type quick-change drill die for aircraft joint parts of the present invention can realize quick hole drilling for joint parts, improve the hole drilling quality and efficiency, solve the problem that holes cannot be drilled for joints under closed conditions, ensure the accuracy and stability of hole drilling, and simplify the operation. Description of the Drawings

[0025] Figure 1 It is a schematic structural diagram of the split flexible drill die kit.

[0026] Figure 2(a) is a schematic diagram of the assembly structure of the upper drilling template.

[0027] Figure 2(b) is a schematic diagram of the assembly structure of the lower drilling template.

[0028] Figure 3(a) is a schematic diagram of the positioning of joint parts on the lower drilling template.

[0029] Figure 3(b) is a schematic diagram of the positioning of joint parts on the upper drilling template.

[0030] Figure 4 is a schematic diagram of the installation of the split flexible drill jig kit.

[0031] In the figure: 1 lower drilling template; 2 upper drilling template; 3 center positioning pin; 4 conical positioning pin; 5 quick-release drill bushing; 6 limit bolt; 7 fixing bolt; 8 pressing bolt. Specific implementation mode

[0032] In order to make the purpose, technical solution and advantages of the present invention clearer, the present invention will be described in detail below with reference to the accompanying drawings.

[0033] The technical problem solved by the present invention is to provide a method and tooling for accurately drilling holes in joint parts under the condition of a closed area formed during the assembly of a detachable disassembly structure drill jig. The specific technical solution is as follows:

[0034] A split flexible drill jig kit for drilling holes in aircraft joint parts, the split flexible drill jig kit includes a lower drilling template 1, an upper drilling template 2, a center positioning pin 3, a conical positioning pin 4, a quick-release drill bushing 5, a limit bolt 6, a fixing bolt 7 and a pressing bolt 8, as Figure 1 shown.

[0035] As shown in Fig. 2(b), the under-reaming template 1 is generally in the shape of a cuboid. Multiple recesses are provided on its rear side to avoid the vertical ribs of the joint parts. A depression is made in the middle of its upper surface, and a threaded hole is made in the middle of the bottom surface of the depression area, which is matched with the center positioning pin 3. It is used to pass through the bushing round hole on the vertical surface of the joint part and serve as the positioning and fixing reference for the joint part. Taking the vertical surface of the joint part as the reference surface, during positioning and installation, the center positioning pin 3 passes through the bushing round hole on the vertical surface of the joint part and is screwed into the under-reaming template 1, so that the vertical surface is completely fitted with the bottom surface of the depression area of the under-reaming template 1 without gaps. At this time, the bottom surface of the joint part is in contact with the rear side surface of the under-reaming template 1, and the bottom surface is the surface where holes need to be drilled. After positioning and installation, the height of the top end surface of the center positioning pin 3 is less than the depth of the depression area to avoid interference when the upper and lower reaming templates are aligned, as shown in Fig. 3(a); at both ends outside the depression area on the upper surface of the under-reaming template 1, threaded holes and round holes in the vertical direction are made, and the threaded holes and round holes are arranged diagonally respectively. A tapered positioning pin 4 is installed in the round hole, which is matched with the reserved hole position of the upper reaming template 2 for the quick positioning of the upper and lower reaming templates and to ensure concentricity of the matching; three through holes in the horizontal direction are provided on the front end surface of the under-reaming template 1, and quick-release drill sleeves 5 are installed in the through holes. The two adopt a small clearance fit in the form of inserting holes for drilling holes in the bottom surface of the joint part. The positions of the through holes correspond to the hole positions to be drilled, and a through groove in the vertical direction is made at the end surface of the through hole for cleaning metal chips after hole drilling; a threaded hole is made beside the through hole on the front end surface of the under-reaming template 1 for installing a limit bolt 6. The limit bolt 6 presses the head shoulder of the quick-release drill sleeve 5 to achieve quick locking and limiting of the quick-release drill sleeve 5 and prevent it from falling off after long-term use.

[0036] As shown in Fig. 2(a), the upper drill template 2 is a cuboid with overall dimensions basically the same as those of the lower drill template 1. The two are used in combination. Multiple recesses are provided at the position where the rear side contacts the joint - type part to avoid the rib area of the joint - type part, ensuring that there is no gap between the joint - type part and the drill template when the upper and lower drill templates are used in combination, as shown in Fig. 3(b). Both ends of the upper drill template 2 are provided with reserved holes and through - holes in the vertical direction, and the reserved holes and through - holes are arranged diagonally respectively. Among them, the reserved holes are used to cooperate with the conical positioning pins 4 installed on the lower drill template 1 to achieve rapid positioning. Fixed bolts 7 are installed in the through - holes. The heads of the fixed bolts 7 adopt the structure of internal hexagon bolts, and their tails cooperate with the threaded holes at both ends of the lower drill template 1 to fix the positions of the upper and lower drill templates and be screwed and locked to prevent displacement during the hole - making process. Three through - holes and threaded holes in the horizontal direction are also provided on the front end face of the upper drill template 2, which are used to install quick - release drill sleeves 5 and limit bolts 6 respectively. The number and positions of the through - holes, that is, the quick - release drill sleeves 5, correspond to the holes to be drilled. Similarly, through - grooves are provided on the end faces of the through - hole ends to clean metal chips after hole - making. Multiple threaded holes are provided in the vertical direction in the middle of the upper surface of the upper drill template 2. The positions of the threaded holes avoid the quick - release drill sleeves 5 and limit bolts 6 and are used to install pressing bolts 8. After the pressing bolts 8 are screwed into the threaded holes, their bottoms abut against the vertical faces of the joint - type parts after positioning and installation, pressing the joint - type parts onto the lower drill template 1 to ensure firm pressing during the hole - making process and avoid hole - position errors.

[0037] The structural reference of the split flexible drill jig kit Figure 1 。

[0038] A method for hole - making of aircraft joint - type parts, the hole - making method comprising the following steps:

[0039] The first step: pre - positioning. Use an analog gauge to coordinate and position the joint - type part, and use a liquid gasket to bond and fix the bottom surface of the coordinated and positioned joint - type part to the aircraft structure.

[0040] The second step: Remove the analog gauge to prepare space and site for installing the split flexible drill jig kit.

[0041] The third step: Select a suitable split flexible drill jig kit according to the specifications of the joint - type part. Connect the lower drill template 1 to the bushing round hole on the vertical face of the joint - type part through the center positioning pin 3, so that the bottom surface and vertical face of the lower drill template 1 are completely fitted without gaps.

[0042] The fourth step: Rapidly position the lower drill template 1 and the upper drill template 2 through the conical positioning pin 4.

[0043] The fifth step: Screw the fixed bolts 7 and pressing bolts 8 into the bolt holes of the upper and lower drill templates to achieve the fixation and locking of the upper and lower drill templates, ensuring that the bottom surface of the lower drill template 1 is completely fitted without gaps with the upper drill template 2 and the joint - type part.

[0044] Step 6: Select the quick-release drill bushing 5 according to the diameter of the hole to be drilled and install it on the upper and lower drill templates. Install the limit bolt 6 to lock the quick-release drill bushing 5. As Figure 4 shown, drill holes for the connector parts respectively.

[0045] The above embodiments only represent the implementation modes of the present invention, but should not be construed as limiting the scope of the patent of the present invention. It should be noted that for those skilled in the art, without departing from the concept of the present invention, several deformations and improvements can still be made, and these all belong to the protection scope of the present invention.

Claims

1. A split flexible drill jig kit for hole making of aircraft joint parts, characterized in that, The described aircraft joint - type part is overall T - shaped, including a bottom surface and a vertical surface in the middle. The split flexible drill jig kit includes a lower drill template (1), an upper drill template (2), a center positioning pin (3), a conical positioning pin (4), a quick - release drill bushing (5), a limit bolt (6), and a fixing bolt (7). The lower drill template (1) is overall cuboid - shaped. There are multiple recesses on its rear side for avoiding the vertical ribs of the joint - type part. There is a depression in the middle of its upper surface. There is a threaded hole in the middle of the bottom surface of the depression area, which cooperates with the center positioning pin (3) to position and fix the joint - type part through the bushing round hole on the vertical surface of the joint - type part. After positioning and installation, the height of the top end face of the center positioning pin (3) is less than the depth of the depression area. The vertical surface fits perfectly with the bottom surface of the depression area of the lower drill template (1) without gaps. At this time, the bottom surface of the aircraft joint - type part fits with the rear side of the lower drill template (1). At both ends of the upper surface of the lower drill template (1) outside the depression area, there is a threaded hole and a round hole in the vertical direction, and the threaded hole and the round hole are arranged diagonally respectively. The conical positioning pin (4) is installed in the round hole. There are multiple through - holes in the horizontal direction on the front end face of the lower drill template (1), and the quick - release drill bushing (5) is installed in the through - holes for drilling holes in the bottom surface of the joint - type part. The number and position of the through - holes correspond to the hole positions to be drilled. There is a threaded hole beside the through - holes on the front end face of the lower drill template (1) for installing the limit bolt (6). The limit bolt (6) presses the head shoulder of the quick - release drill bushing (5) to achieve quick locking and limiting of the quick - release drill bushing (5). The upper drill template (2) is a cuboid with overall dimensions basically the same as those of the lower drill template (1). The two are used in combination. There are multiple recesses at the position where its rear side contacts the joint - type part to avoid the vertical rib area of the joint - type part. At both ends of the upper drill template (2), there are reserved holes and through - holes in the vertical direction, and the reserved holes and the through - holes are arranged diagonally respectively. Among them, the reserved holes are used to cooperate with the conical positioning pins (4) installed on the lower drill template (1) to achieve quick positioning. The fixing bolts (7) are installed in the through - holes, and their tails cooperate with the threaded holes at both ends of the lower drill template (1) to fix the positions of the upper and lower drill templates and lock them. There are also through - holes and threaded holes in the horizontal direction on the front end face of the upper drill template (2), which are used to install the quick - release drill bushing (5) and the limit bolt (6) respectively. Among them, the number and position of the through - holes, that is, the quick - release drill bushings (5), correspond to the holes to be drilled.

2. The split flexible drill jig kit for hole making of aircraft joint parts according to claim 1, characterized in that At the end faces of the through - holes on the front end faces of the lower drill template (1) and the upper drill template (2), there are through - grooves in the vertical direction for cleaning metal chips after drilling.

3. A split flexible drill jig kit for hole making of aircraft joint parts according to claim 1, characterized in that, The split flexible drill jig kit also includes a pressing bolt (8). There are multiple threaded holes in the vertical direction in the middle of the upper surface of the upper drill template (2). The positions of the threaded holes avoid the quick - release drill bushings (5) and the limit bolts (6) and are used to install the pressing bolts (8). After the pressing bolts (8) are screwed into the threaded holes, their bottom ends press against the vertical surface of the joint - type part after positioning and installation, pressing the joint - type part onto the lower drill template (1).

4. A split flexible drill jig kit for hole-making of aircraft joint parts according to claim 1, characterized in that The quick-release drill bushing (5) mentioned above is in a small clearance fit in the through holes on the front faces of the upper and lower drill templates. The inner bushing holes have various specifications and can be replaced according to the actual feed requirement of drilling.

5. A method for drilling holes in aircraft joint parts, which is realized based on the split flexible drill jig kit according to any one of claims 1-4. The hole drilling method includes the following steps: The first step: pre-positioning. Use an analog gauge to coordinate and position the joint parts. By using the bonding technology, bond and fix the bottom surface of the coordinated and positioned joint parts on the aircraft structure. The second step: Remove the analog gauge. The third step: Connect the lower drill template (1) to the bushing round hole on the vertical surface of the joint parts through the center positioning pin (3), so that the lower drill template (1) is completely fitted with no clearance to the bottom surface and the vertical surface of the joint parts. The fourth step: Quickly position the lower drill template (1) and the upper drill template (2) through the conical positioning pin (4). The fifth step: Screw the fixing bolts (7) and the pressing bolts (8) into the bolt holes of the upper and lower drill templates to fix and lock the upper and lower drill templates, and ensure that the lower drill template (1) is completely fitted with no clearance to the upper drill template (2) and the bottom surface of the joint parts. The sixth step: Select the quick-release drill bushing (5) according to the required drilled hole diameter and install it on the upper and lower drill templates. Install the limit bolts (6) to lock the quick-release drill bushing (5), and drill holes in the joint parts respectively.

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