Drilling clamp for copying airplane supporting rod preparation hole

Abstract

The utility model provides a drilling clamp for copying an airplane supporting rod preparation hole. The drilling clamp comprises a clamp body, a positioning check block, a V-shaped block, a pressing plate assembly, a pouring bush positioning pin and a lining. An original supporting rod is placed on the two V-shaped blocks, the end, provided with three preparation holes, of the original supporting rod is inserted into the phi AH7 through hole of the positioning check block, and the end, provided with the fork lug connector, of the original supporting rod is fixed to the clamp body through the positioning pin. And the two pressing plate assemblies are used for tightly pressing the supporting rod. The three pouring bush positioning pins are inserted into the three phi DH7 through holes in the side face of the positioning check block, the six bushings penetrate into the two ends of the three pouring bush positioning pins respectively, epoxy resin (pouring bushings) is filled between the outer cylindrical faces of the bushings and the phi DH7 inner surfaces, and after the epoxy resin is solidified, three preparation holes of an original supporting rod are copied on the clamp. And a new supporting rod is replaced, and three preparation holes are drilled through the clamp. Through the process method, the preparation hole in the original supporting rod with the scratched outer surface can be copied to a new supporting rod, so that the purpose of replacing the supporting rod with the scratched outer surface on the airplane is achieved.

Description

Technical Field

[0001] This utility model relates to the field of aircraft industrial equipment design and manufacturing technology, specifically to a drilling fixture for replicating the configuration holes of an aircraft support rod. Background Technology

[0002] Support rods are a common type of connector on aircraft, used to connect and secure small aircraft parts. For example... Figure 1 As shown, support rod 1 is a steel pipe (outer diameter φA) riveted to a fork-shaped lug connector with a semi-circular head. The fork-shaped lug connector has a pair of concentric holes and a positioning hole 3 (diameter φB). The other end of the support rod is fitted with three mounting holes 2 (diameter φC) when connecting to other components on the aircraft. Typical aircraft components require three to four support rods for connection and fixation. To coordinate installation dimensions, before installation, one end of each support rod is connected and fixed to the aircraft component through three mounting holes. These three mounting holes are precision-machined, ensuring a tight fit with the bolt rod with minimal clearance. After installation, the other end is connected to the aircraft body via the fork-shaped lug structure.

[0003] During aircraft overhauls, some support rods need to be replaced due to scratches on their exterior. Before installation, three connection holes need to be prepared on the new support rod. However, the limited space on the aircraft makes direct hole preparation impossible. Alternatively, measuring the dimensions of the three holes on the original support rod and then drilling the corresponding holes on the new rod can yield poor results; often, one or two holes will not align, preventing the bolts from being inserted. Therefore, it is necessary to accurately replicate the original support rod's holes onto the new support rod in the open space outside the aircraft to ensure successful installation. Utility Model Content

[0004] This invention provides a drilling jig for copying the configuration holes on an aircraft support rod, which can accurately copy the configuration holes on the original support rod to the new support rod, ensuring that the new support rod can be successfully installed on the aircraft.

[0005] This utility model provides a drilling fixture for replicating the configuration holes of an aircraft support rod, comprising: a fixture body 5, a positioning block 6, a V-block 7, a casting sleeve positioning pin 15, and a bushing 16.

[0006] The fixture body 5 is a cuboid. The fixture body 5 is set on the workbench. The upper surface of the fixture body 5 has a positioning through hole at the left end along the length direction, two V-shaped blocks 7 are arranged in the middle, and a positioning stop block 6 is set at the right end.

[0007] The positioning block 6 has a fixed through hole along the length of the clamp body 5; the side of the positioning block has a casting sleeve hole 14; the center line of the fixed through hole and the center line of the two V blocks are in the same plane; the diameter of the casting sleeve hole 14 is larger than the diameter of the original support rod's configuration hole; the casting sleeve hole 14 is machined according to the A-swing and C-swing angles of the original support rod's configuration hole.

[0008] Bushings 16 are provided at both ends of the gating hole 14, and the bushings 16 are bonded to the through hole with epoxy resin.

[0009] When the bushing 16 is bonded to the casting hole 14, the original support rod is placed on two V-blocks 7. One end of the original support rod with the matching hole is inserted into the fixing through hole of the positioning block 6, and the other end with the fork-ear connector is positioned in the positioning through hole by the positioning pin. The casting hole positioning pin 15 is inserted into the matching holes of the bushing 16 and the original support rod. The outer diameter of the casting hole positioning pin 15, the inner diameter of the bushing 16 and the diameter of the matching hole of the original support rod are the same.

[0010] When the drilling jig is in use, the new support rod is placed on two V-blocks 7. The end of the new support rod used for machining the hole is inserted into the fixed through hole of the positioning block 6, and the end with the fork lug is positioned in the positioning through hole by the positioning pin.

[0011] Optionally, the distance from the right end face of the positioning block 6 to the center line of the positioning through hole at the left end of the clamping body 5 is equal to the length of the support rod.

[0012] Optionally, both V-blocks 7 and the positioning stop 6 are welded to the fixture body 5.

[0013] Optionally, the drilling fixture for replicating the configuration holes of the aircraft support rod also includes: pressure plate assembly 8;

[0014] The pressure plate assembly 8 includes: a pressure plate 9, a bolt 10, and a nut 11;

[0015] The pressure plate 9 is provided with long slots;

[0016] The hexagonal head of bolt 10 is inserted into the dovetail groove of the workbench, and the bolt shank of bolt 10 passes through the long slot of pressure plate 9 and is fixed with nut 11.

[0017] Adjust the position of the pressure plate 9 by using the long slot to ensure that the end of the pressure plate 9 presses on the original support rod.

[0018] Optionally, the diameter of the gating sleeve hole 14 is at least 9 mm larger than the diameter of the original support rod's fitting hole.

[0019] Optionally, the outer diameter of bushing 16 should be at least 6 mm larger than its inner diameter.

[0020] This utility model provides a drilling jig for copying the fitting holes on an aircraft support rod. It can copy the fitting holes on the original support rod with scratches to the new support rod, thereby achieving the purpose of replacing the support rod with scratches on the aircraft. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the support rod structure;

[0022] Figure 2 This is a schematic diagram of the drilling fixture structure provided by this utility model;

[0023] Figure 3 This is a schematic diagram of the positioning pin structure provided by this utility model;

[0024] Figure 4 This is a schematic diagram of the positioning block structure provided by this utility model;

[0025] Figure 5 This is a schematic diagram of the casting sleeve structure provided by this utility model;

[0026] Figure 6 This is a schematic diagram of the bushing structure provided by this utility model;

[0027] Explanation of reference numerals in the attached figures:

[0028] 1. Support rod; 2. Fitting hole; 3. Fork lug joint positioning hole; 4. Drilling jig; 5. Jig body; 6. Positioning stop; 7. V-block; 8. Pressure plate assembly; 9. Pressure plate; 10. Bolt; 11. Nut; 12. Positioning pin; 13. Positioning through hole; 14. Sprue hole; 15. Sprue positioning pin; 16. Bushing; 17. Epoxy resin; 18. Fixing through hole; 19. Inner diameter; 20. Outer diameter. Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0030] The features and illustrative embodiments of various aspects of this utility model will now be described in detail. In the following detailed description, numerous specific details are set forth in order to provide a comprehensive understanding of this utility model. However, it will be apparent to those skilled in the art that this utility model can be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of this utility model by illustrating examples of it. This utility model is by no means limited to any specific arrangements and methods set forth below, but covers any improvements, substitutions, and modifications to the structure, method, and apparatus without departing from the spirit of this utility model. In the accompanying drawings and the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring this utility model.

[0031] It should be noted that, where there is no conflict, the embodiments of this utility model and the features therein can be combined with each other, and the various embodiments can be referenced and cited in turn. The present utility model will now be described in detail with reference to the accompanying drawings and embodiments.

[0032] The present invention will be further described in detail below with reference to the embodiments and accompanying drawings, but the implementation of the present invention is not limited thereto.

[0033] Figure 1 As a support rod, Figure 2 It is a drilling fixture. Figure 3 For positioning pins, Figure 4 For positioning stop, Figure 5 For casting sleeve, Figure 6 For bushing.

[0034] like Figure 1-6 As shown, this utility model provides a drilling jig for replicating the configuration holes of an aircraft support rod. The drilling jig 4 is composed of a jig body 5, a positioning block 6, a V-block 7, a pressure plate assembly 8, a positioning pin 12, a casting sleeve positioning pin 15, and a bushing 16.

[0035] The clamping body 5 is a cuboid. One end of it has a positioning through hole 13 with a diameter of φBH7, which is the same as the positioning hole 3 of the fork lug connector. Two V-shaped blocks 7 are arranged in the middle of the clamping body 5, and the right end of the clamping body 5 is a positioning stop block 6.

[0036] The positioning block 6 has a fixed through hole 18 with a diameter of φAH7, which is the same as the diameter of the support rod 1. The side of the positioning block 6 has three gating holes with a diameter of φDH7, which are at least 9mm larger than the diameter of the fitting hole 2.

[0037] The center line of the fixing through hole 18 (φAH7) of the positioning block 6 and the two V-blocks 7 must be in the same plane. The distance from the right end face of the positioning block 6 to the center line of the positioning through hole 13 of φBH7 at the left end of the clamp body must be equal to the length of the support rod.

[0038] The two V-shaped blocks 7 and the positioning block 6 are all welded to the clamp body 5.

[0039] The pressure plate assembly 8 consists of a pressure plate 9, bolts 10, and nuts 11. The hexagonal head of the bolt 10 is inserted into the dovetail groove of the worktable, and the other end passes through the elongated slot of the pressure plate 9 and is secured with the nut 11. The position of the pressure plate 9 is adjusted through the elongated slot to ensure that the pressure plate 9 can press against the support rod.

[0040] Drilling fixture 4 is used to replicate the three matching holes 2 on the aircraft support rod. The process is as follows:

[0041] Step 2-1) Place the original support rod 1 on the two V-blocks 7. Insert one end of the three matching holes 2 of the original support rod 1 into the fixing through hole 18 (φAH7) of the positioning block 6. Use the positioning pin 12 to position the positioning hole 3 (φBH7) of the original support rod 1 on the clamp body 5, and use the pressure plate 9 to press the original support rod 1 tightly.

[0042] Step 2-2) After the original support rod 1 is positioned and fixed on the fixture, use an angle ruler to measure the A and C pendulum angles of the three matching holes 2 (φCH7) on the right end of the support rod 1 (measure the two angles separately) and mark them on the positioning block 6.

[0043] Steps 2-3) Remove the original support rod 1 and drill three casting sleeve holes 14 (φDH7) on the positioning block 6 by marking.

[0044] Step 2-4) Install the original support rod 1 according to the steps in 2-1). Insert the locating pin 15 into the three sprue holes 14 on the positioning block 6. Install bushings 16 on both sides of the three sprue holes 14 respectively. The inner diameter 19 of the bushing 16 is the same as the diameter of the matching hole 2. The outer diameter 20 of the bushing 16 is at least 6mm larger than the inner diameter 19. Cast with epoxy resin 17.

[0045] Steps 2-5) After the epoxy resin 17 has solidified, remove the positioning pin 15 of the casting sleeve, remove the original support rod 1, and install the new support rod 1 according to the steps in 2-1). Drill 3 matching holes 2 on the new support rod 1.

[0046] In summary, we used a drilling fixture to clamp and position the support rod, thereby replicating the three matching holes. This method allows us to control the error within ±0.03mm, meeting the tolerance requirements of this part and effectively completing the machining task.

[0047] The above description is only a further embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the scope disclosed by the present utility model, based on the technical solution and concept of the present utility model, shall fall within the protection scope of the present utility model.

Claims

1. A drilling fixture for replicating the holes of an aircraft support rod, characterized in that, include: The fixture body (5), the positioning block (6), the V-block (7), the positioning pin of the casting sleeve (15), and the bushing (16); The fixture (5) is a cuboid. The fixture (5) is set on the workbench. The upper surface of the fixture (5) has a positioning through hole on the left end along the length direction, two V-shaped blocks (7) are arranged in the middle, and a positioning stop block (6) is set on the right end. The positioning block (6) has a fixed through hole along the length of the clamp body (5); the side of the positioning block has a casting sleeve hole (14); the center line of the fixed through hole and the center line of the two V blocks are in the same plane; the diameter of the casting sleeve hole (14) is larger than the diameter of the original support rod's configuration hole; the casting sleeve hole (14) is processed according to the A-swing and C-swing angles of the original support rod's configuration hole; Bushings (16) are provided at both ends of the gating hole (14), and the bushings (16) are bonded to the through hole with epoxy resin. When the bushing (16) is bonded to the casting hole (14), the original support rod is placed on two V-blocks (7). One end of the original support rod with the matching hole is inserted into the fixing through hole of the positioning block (6), and the other end with the fork ear connector is positioned in the positioning through hole by the positioning pin. The casting hole positioning pin (15) is inserted into the matching holes of the bushing (16) and the original support rod. The outer diameter of the casting hole positioning pin (15), the inner diameter of the bushing (16) and the diameter of the matching hole of the original support rod are the same. When the drilling fixture is in use, the new support rod is placed on two V-blocks (7). The end of the new support rod used for machining the hole is inserted into the fixed through hole of the positioning block (6), and the end with the fork lug is positioned in the positioning through hole by the positioning pin.

2. The drilling fixture for replicating the holes of an aircraft support rod according to claim 1, characterized in that, The distance from the right end face of the positioning block (6) to the center line of the positioning through hole at the left end of the clamping body (5) is equal to the length of the support rod.

3. The drilling fixture for replicating the holes of an aircraft support rod according to claim 1, characterized in that, The two V-blocks (7) and the positioning block (6) are all welded to the fixture body (5).

4. The drilling fixture for replicating the holes of an aircraft support rod according to claim 1, characterized in that, Also includes: Pressure plate assembly (8); The pressure plate assembly (8) includes: a pressure plate (9), a bolt (10), and a nut (11); The pressure plate (9) is provided with long slots; The hexagonal head of the bolt (10) is inserted into the dovetail groove of the workbench, and the bolt (10) is fixed with a nut (11) through the long slot of the pressure plate (9). Adjust the position of the pressure plate (9) by using the long slot to ensure that the end of the pressure plate (9) presses on the original support rod.

5. The drilling fixture for replicating the holes of an aircraft support rod according to claim 1, characterized in that, The diameter of the gating sleeve hole (14) is at least 9 mm larger than the diameter of the original support rod's fitting hole.

6. The drilling fixture for replicating the holes of an aircraft support rod according to claim 5, characterized in that, The outer diameter of the bushing (16) must be at least 6 mm larger than the inner diameter.

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