Method for accurate drilling of holes in aircraft door skin

Abstract

The application discloses a kind of methods for accurate drilling of aircraft cabin door skin hole position, belong to the technical field of drilling.The method comprises the following steps: A, the product is closely attached to the auxiliary support plate (4), and is positioned by the hinge on the product assembly and the framework (2);B, the drill template (1) is positioned and fastened by threaded pin (11), and the product is fastened using the compression assembly (5);C, drill bit is inserted into the bushing hole (16) in drill template (1) and drilled, until all drilling is completed;D, remove the product, and drill the final hole on the product.This method realizes the standardization of hole drilling, reduces the dependence on the personal ability of the operator, and greatly improves the drilling efficiency.Solve the problem that the fastener hole position of the skin of the existing front cabin door is difficult to operate manually, has low production efficiency and poor stability.

Description

Technical Field

[0001] This invention discloses a method for precisely drilling holes in aircraft cabin door skin, belonging to the field of drilling technology. Background Technology

[0002] In the aircraft manufacturing industry, especially in the production of domestically produced large aircraft, the complex shape and intricate technological requirements of aircraft, coupled with the increasing production volume of domestically produced large aircraft, place higher demands on stable and efficient assembly production. Currently, the ARJ nose section involves 230 fastener holes per aircraft for the nose landing door skin, which amounts to 23,000 fastener holes for 100 aircraft. Currently, all fastener holes for the nose landing door skin are manually marked, a method that is difficult to operate, inefficient, prone to errors, results in poor product uniformity and stability, and requires highly skilled workers. The existing solution relies entirely on operators manually marking and drilling the holes. The solution involves operators reviewing the hole size requirements in the engineering documents, using a marking pen and steel ruler to mark the center lines of the 230 fastener holes according to the dimensions provided in the engineering documents, and then using an air drill to drill the holes according to the marked center lines.

[0003] Disadvantages of existing technology:

[0004] 1. It relies entirely on the operator's operating skills, which requires a high level of technical ability from the operator;

[0005] 2. Low work efficiency, time-consuming and labor-intensive, and long cycle time. Drilling 230 fastener holes in a single operation takes 8 hours.

[0006] 3. Poor stability, low standardization of manual marking and hole arrangement, and poor product appearance uniformity. Summary of the Invention

[0007] The technical problem to be solved by the present invention is that the fastener holes of the existing front hatch skin are difficult to make by manually scribing, resulting in low production efficiency and poor stability.

[0008] The technical solution adopted by this invention to solve its technical problem is: a method for accurately drilling holes in aircraft cabin door skin, comprising the following steps:

[0009] A. Place the product close to the auxiliary support plate and position it using the hinges and frame on the product components;

[0010] B. Secure the drill template by positioning it with threaded pins and fasten the product with clamping components;

[0011] C. Insert the drill bit into the bushing hole in the drill template and drill the hole until all holes are drilled;

[0012] D. Remove the product and drill the final hole in the product.

[0013] In step A of the above method, a hinge positioning component is provided on the skeleton.

[0014] In step B of the above method, a support base is provided on the skeleton component, and the support base is provided with a threaded hole for connection with the threaded pin.

[0015] Furthermore, the support base described in the above method includes a body and ribs. The body has a Z-shaped structure, with threaded holes on one end face and the other end face detachably connected to the frame. The ribs are located on the bent inner wall near the connection point of the frame assembly.

[0016] The method described above also includes a handle drill sleeve, which includes a handle and a drill sleeve. The drill sleeve is located at one end of the handle and can be inserted into the bushing hole in the drill template, so that the drill bit extends into the drill sleeve and drills a hole in step C.

[0017] Furthermore, the drill bushing and handle described in the above method are detachably connected.

[0018] In the above method, the auxiliary support plate is set on the side wall of the skeleton, and the bushing holes are set at intervals on the drilling template and correspond to the through holes on the product.

[0019] The clamping assembly described in the above method includes a fixed base, a locking rod assembly, and a fixing screw. The fixed base is set on the lower side wall of the frame. The locking rod assembly can control the height of the fixing screw. The fixing screw passes through the locking rod assembly and is provided with positioning rings on both sides. A rubber part is provided at the insertion end. Moving the locking rod assembly can make the rubber part pass through the drilling template and contact the lower side wall of the product.

[0020] In the above method, adjustable foot pads are provided at intervals at the lower end of the frame.

[0021] The drilling template mentioned in the above method includes a left drilling template and a right drilling template, and a handle is provided in the middle of the left drilling template and the right drilling template.

[0022] The beneficial effects of this invention are as follows: This method integrates a drill template assembly, a hinge positioning assembly, an auxiliary support assembly, and a clamping assembly into the tooling. The aircraft door assembly is positioned and secured to the tooling via the hinge positioning assembly, auxiliary support assembly, and clamping assembly. The precise drilling of the skin holes in the aircraft door assembly can be achieved through the cooperation of the handle drill jig and the drill template. This standardizes hole drilling, reducing reliance on individual operator skills; it achieves high efficiency in hole drilling, reducing the time required to drill 230 holes per flight to 1 hour; and it ensures stable and high-quality product output, guaranteeing drilling quality. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the structure of the present invention.

[0024] Figure 2 This is a schematic diagram of the connection structure of the left drill template of the present invention.

[0025] Figure 3 This is a schematic diagram of the connection structure of the right drill template of the present invention.

[0026] Figure 4 For the present invention Figure 1 Enlarged schematic diagram of the structure at point I.

[0027] Figure 5 This is a schematic diagram of the support base of the present invention.

[0028] Figure 6 This is a schematic diagram of the clamping assembly of the present invention.

[0029] Figure 7 This is a schematic diagram of the structure of the handle drill sleeve of the present invention.

[0030] The markings in the diagram are as follows: 1 is the drill template, 2 is the frame, 3 is the hinge positioning assembly, 4 is the auxiliary support plate, 5 is the clamping assembly, 51 is the locking rod assembly, 52 is the base, 53 is the fixing screw, 54 is the rubber part, 55 is the positioning ring, 10 is the handle, 11 is the threaded pin, 12 is the handle drill sleeve, 121 is the handle, 122 is the drill sleeve, 13 is the right drill template, 14 is the left drill template, 15 is the support base, 151 is the rib plate, 152 is the threaded hole, 153 is the body, and 16 is the bushing hole. Detailed Implementation

[0031] The invention will be further described below with reference to the accompanying drawings.

[0032] like Figures 1 to 7 As shown, the present invention provides a method for precisely drilling holes in an aircraft cabin door skin, comprising the following steps:

[0033] A. Place the product tightly against the auxiliary support plate 4 and position it using the hinges on the product components and the frame 2.

[0034] B. Position and secure the drill template 1 using threaded pin 11, and secure the product using clamping assembly 5;

[0035] C. Insert the drill bit into the bushing hole 16 in the drill template 1 and drill the hole until all holes are drilled;

[0036] D. Remove the product and drill the final hole in the product. Those skilled in the art will understand that the auxiliary support plate 4 is used to support the inner side of the product, but is actually set on the outer wall of the frame 2. The frame 2 is a supporting structural component, which can actually be formed by welding square tubes to form a frame structure. The drilling template 1 is a plate material with the same hole position as the product. Step A of this method mainly fixes the product to the frame 2, specifically by tightly attaching the product to the auxiliary support plate 4. Since one end of the product has a hinge, this method positions it to the frame 2 through the hinge, that is, the upper end is hinged and fixed to the frame 2. Step B involves tightly attaching the drilling template 1 to the outer side of the product, and connecting and fixing the drilling template 1 to the support seat 15 on the frame 2 through threaded pins 11. The product is positioned between the auxiliary support plate 4 and the drilling template 1, thus fixing the product. Step C mainly involves marking the drilling positions on the product and drilling guide holes to facilitate the later drilling of the final holes. For ease of positioning, this method preferably inserts the handle drill jig 12 into the bushing hole 16 in the drill template 1 and drills the hole. After completing one hole, the handle drill jig 12 is moved to continue drilling the next bushing hole 16 until all holes are drilled. Step D is the drilling of the final hole, so in practice, the product can be removed and a suitable drill bit can be selected to complete the reaming.

[0037] Preferably, in step A of the above method, a hinge positioning component 3 is provided on the frame 2. Those skilled in the art will understand that, in order to facilitate the hinged fixing of the frame 2 and the upper end of the product, this method preferably provides a hinge positioning component 3 on the frame 2. The hinge positioning component 3, in existing products, actually includes a U-shaped part and a pin. Through holes are provided on both sides of the opening of the U-shaped part. The hinge component of the product is inserted into the opening and the pin is inserted to hinge the product to the frame 2.

[0038] Preferably, in step B of the above method, the skeleton 2 assembly is provided with a support base 15, and the support base 15 is provided with a threaded hole 152 for connecting to the threaded pin 11. Those skilled in the art will understand that, in order to facilitate the detachable connection between the drill template 1 and the skeleton 2, it is actually preferred to provide a support base 15 on the skeleton 2 assembly, and the support base 15 is provided with a threaded hole 152 for connecting to the threaded pin 11. In practice, a through hole is provided on the drill template 1, and the threaded pin 11 passes through the drill template 1 and is threadedly connected to the support base 15 to fix the drill template 1 to the skeleton 2, thereby achieving the requirement of pressing the product.

[0039] Preferably, the support base 15 in the above method includes a body 153 and a rib plate 151. The body 153 has a Z-shaped structure, with a threaded hole 152 on one end face of the body 153, and the other end face can be detachably connected to the frame 2 assembly. The rib plate 151 is located on the bent inner wall near the connection point of the frame 2 assembly. Those skilled in the art will understand that this method specifically prefers the structure of the support base 15 to ensure the structural strength of the connection point. The preferred support base 15 includes a body 153 and a rib plate 151. The body 153 has a Z-shaped structure, and the bent edge is actually vertically positioned. The threaded hole 152 is located on one end face of the body 153, and the other end face can be detachably connected to the frame 2 assembly, which can be fixed by bolts. The rib plate 151 is located on the bent inner wall near the connection point of the frame 2 assembly to ensure that the threaded pre-tightened support base 15 does not deform.

[0040] Preferably, the above method further includes a handle drill sleeve 12, which includes a handle 121 and a drill sleeve 122. The drill sleeve 122 is disposed at one end of the handle 121 and can be inserted into the bushing hole 16 in the drill template 1, so that the drill bit extends into the drill sleeve 122 and drills a hole in step C. Those skilled in the art will understand that this method uses the handle drill sleeve 12 to adjust the size of the positioning hole. Preferably, the handle drill sleeve 12 includes a handle 121 and a drill sleeve 122, with the drill sleeve 122 disposed at one end of the handle 121. The drill sleeve 122 can be inserted into the bushing hole 16 in the drill template 1 through the handle 121, so that the drill bit extends into the drill sleeve 122 and drills a hole in step C. This structure also prevents the drill bit from contacting the inner wall of the drill template 1, protecting the hole wall in the drill template; and the handle drill sleeve is easy to replace and maintain, resulting in lower replacement costs.

[0041] Preferably, the drill sleeve 122 and the handle 121 described in the above method are detachably connected. Those skilled in the art will understand that, in order to facilitate drilling positioning holes of different sizes, this device preferably allows for a detachable connection between the drill sleeve 122 and the handle 121. This facilitates smoother drilling of the drill sleeve, meaning the hole diameter can be flexibly selected. The required hole diameter can be adjusted according to the actual situation later. For example, if the required hole diameter is currently 2.6mm, and later it needs to be changed to a 3mm hole, only the handle drill sleeve 12 needs to be replaced; there is no need to replace the drill template 1. Furthermore, different specifications of handle drill sleeves 12 can be randomly selected according to the actual situation to obtain different hole diameters. Later, the final hole can be obtained by directly enlarging the guide hole.

[0042] Preferably, in the above method, the auxiliary support plate 4 is disposed on the side wall of the frame 2, and the bushing holes 16 are spaced apart on the drilling template 1 and correspond to the through holes on the product. Those skilled in the art will understand that, to ensure good contact on the inner side of the product, it is actually preferable to provide the auxiliary support plate 4 on the side wall of the frame 2, and the shape of the auxiliary support plate 4 can be similar to the shape of the inner side of the product. The bushing holes 16 are actually for positioning the pre-drilled holes in the product, so they should actually be spaced apart on the drilling template 1 and correspond to the through holes on the product.

[0043] Preferably, the clamping assembly 5 in the above method includes a fixed base 52, a locking rod assembly 51, and a fixing screw 53. The fixed base 52 is disposed on the lower side wall of the frame 2. The locking rod assembly 51 can control the height of the fixing screw 53. The fixing screw 53 passes through the locking rod assembly 51 and is provided with positioning rings 55 on both sides. A rubber part 54 is provided at the insertion end. Moving the locking rod assembly 51 can make the rubber part 54 pass through the drilling template 1 and contact the lower side wall of the product. Those skilled in the art will understand that the clamping assembly 5 is prior art. In fact, its structure and connection relationship are briefly described. The clamping assembly 5 includes a fixed base 52, a locking rod assembly 51 and a fixing screw 53. The fixed base 52 is set on the lower side wall of the frame 2. The locking rod assembly 51 can control the height of the fixing screw 53. The fixing screw 53 passes through the locking rod assembly 51 and is provided with positioning rings 55 on both sides. A rubber part 54 is provided at the insertion end. Moving the locking rod assembly 51 can make the rubber part 54 pass through the drilling template 1 and contact and connect with the lower side wall of the product.

[0044] Preferably, the lower end of the frame 2 in the above method is provided with adjustable foot pads at intervals. Those skilled in the art will understand that, in order to ensure the stability of the device's support force, this method preferably provides adjustable foot pads at intervals at the lower end of the frame 2, and the height of the foot pads is adjusted according to the bottom surface to meet the support requirements.

[0045] Preferably, the drill template 1 in the above method includes a left drill template 14 and a right drill template 13, and a handle 10 is provided in the middle of the left drill template 14 and the right drill template 13. Those skilled in the art will understand that, due to the large size of the product and the similarity in structure between the drill template 1 and the product, in order to reduce costs and facilitate handling, this method preferably divides the drill template 1 into two parts, actually including a left drill template 14 and a right drill template 13, and a handle 10 is provided in the middle of the left drill template 14 and the right drill template 13. The handle 10 is mainly provided for convenient handling.

Claims

1. A method for precisely drilling holes in an aircraft cabin door skin, characterized in that... Includes the following steps: A. Place the product close to the auxiliary support plate (4) and position it using the hinges on the product components and the frame (2); B. Position and secure the drill template (1) using the threaded pin (11), and secure the product with the clamping assembly (5); C. Insert the drill bit into the bushing hole (16) in the drill template (1) and drill until all holes are drilled; D. Remove the product and drill the final hole in the product; The frame (2) is provided with a hinge positioning component (3), which includes a U-shaped part and a pin. The U-shaped part has through holes on both sides of the opening. The hinge of the product can be hinged to the frame (2) by inserting the hinge part through the opening and inserting the pin. The auxiliary support plate (4) is provided on the side wall of the frame (2). The shape of the auxiliary support plate (4) is similar to the inner shape of the product. The bushing holes (16) are spaced on the drilling template (1) and correspond to the through holes on the product. In step B, the frame (2) component is provided with a support base (1). 5), and the support base (15) is provided with a threaded hole (152) for connection with the threaded pin (11); the support base (15) includes a body (153) and a rib plate (151). The body (153) has a Z-shaped structure. The threaded hole (152) is provided on one end face of the body (153), and the other end face can be detachably connected to the skeleton (2) assembly. The rib plate (151) is provided on the bent inner wall near the connection of the skeleton (2) assembly; it also includes a handle drill sleeve (12). The handle drill sleeve (12) includes a hand drill. The handle (121) and drill sleeve (122) are provided at one end of the handle (121) and the drill sleeve (122) can be inserted into the bushing hole (16) in the drill template (1) so that the drill bit can be inserted into the drill sleeve (122) and drill a hole in step C; the drill sleeve (122) and the handle (121) are detachably connected; the clamping assembly (5) includes a fixed base (52), a locking rod assembly (51) and a fixing screw (53), the fixed base (52) is provided on the lower side wall of the frame (2) and the locking rod is fixed. The tensioning rod assembly (51) can control the height of the fixing screw (53). The fixing screw (53) passes through the locking rod assembly (51) and is provided with positioning rings (55) on both sides. A rubber part (54) is provided at the insertion end. Moving the locking rod assembly (51) can make the rubber part (54) pass through the drill template (1) and contact the lower side wall of the product. The drill template (1) includes a left drill template (14) and a right drill template (13), and a handle (10) is provided in the middle of the left drill template (14) and the right drill template (13).

2. The method for precisely drilling holes in aircraft cabin door skin as described in claim 1, characterized in that: The lower end of the frame (2) is provided with adjustable foot pads at intervals.

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