A large aircraft wing-body joint hole drilling jig device

Abstract

The utility model belongs to the technical field of aircraft assembly, a kind of large aircraft wing-body joint's trepanning jig device.The device contains two parts of female die and male die.The female die is in the form of plate, contains several hole positions A, and each hole position is equipped with drill sleeve A;The male die is in the form of plate, contains several hole positions B, and each hole position is equipped with drill sleeve B, the film surface of female die and the film surface of male die are completely matched, the several hole positions A and several hole positions B are respectively one-to-one alignment, and drill sleeve A and drill sleeve B are aligned;The female die is used to drill hole on Fy joint, and the male die is used to drill hole on fuselage skin and reinforcing frame, and the Fy joint after drilling hole and fuselage skin and reinforcing frame are connected using fastener.Lifting wing is avoided, wing-body docking efficiency is improved, worker operating environment is improved, and drilling rate is accelerated.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft assembly technology, and is a drilling jig device for drilling holes in large aircraft wing-body joints. Background Technology

[0002] The fuselage and wings of a large amphibious aircraft are connected by multiple sets of linkages, with titanium alloy joints attached to the fuselage and wings respectively at both ends. During wing-fuselage docking, the original process involved using the initial hole on the titanium alloy Fy joint as a reference, and then drilling connection holes between the joint and the fuselage skin and frame. However, during the development and batch manufacturing process, the small distance between the wing and fuselage, coupled with the impact of the single lug of the Fy joint on the work space, made drilling some holes difficult, requiring the wing to be raised to ensure successful drilling. Raising the wing, however, affected the processing of the remaining joints, ultimately impacting the overall wing-fuselage docking efficiency. To improve wing-fuselage docking efficiency, a drilling jig needs to be designed to replace the Fy joint, allowing for separate drilling of the fuselage and Fy joint, avoiding unnecessary wing raising, and improving the worker's operating environment and posture. Utility Model Content

[0003] The purpose of this utility model is: To address the aforementioned problems in the existing technology, this utility model provides a drilling jig device for drilling holes in large aircraft wing-body joints.

[0004] The present invention adopts the following technical solution: A drilling jig apparatus for drilling holes in a large aircraft wing-body joint comprises a female mold and a male mold. The female mold is plate-shaped and includes several hole positions A, each equipped with a drill sleeve A. The male mold is plate-shaped and includes several hole positions B, each equipped with a drill sleeve B. The film-coated surfaces of the female mold and the male mold are completely adhered to each other. The hole positions A and B are aligned one-to-one, and the drill sleeves A and B are aligned. The female mold is used to drill holes in the wing-body joint, and the male mold is used to drill holes in the fuselage skin and reinforcing frame. The drilled wing-body joint is connected to the fuselage skin and reinforcing frame using fasteners.

[0005] Furthermore, it also includes a matching pin, which is used to check the consistency between hole position A and hole position B.

[0006] Furthermore, the aforementioned holes A are arranged in two rows, symmetrically on both sides of the female mold.

[0007] Furthermore, the aforementioned holes B are arranged in two rows, symmetrically on both sides of the male mold.

[0008] Furthermore, the female mold is fastened to the Fy connector using bolts, nuts, and a bolt.

[0009] Furthermore, the male mold is fastened to the machine body skin and reinforcing frame using bolts and nuts.

[0010] Furthermore, gaskets are provided between the male mold and hole A, and between the female mold and hole B.

[0011] Technical effects: The male mold and corresponding drill bushing in this device can be used to make holes in the fuselage skin and frame, and the female mold and corresponding drill bushing can be used to make holes in the Fy joint. After making the holes, the hole positions and diameters on the Fy joint are completely coordinated with the hole positions and diameters on the fuselage. This avoids lifting the wing, improves the wing-fuselage docking efficiency, improves the worker's operating environment, and speeds up the hole making rate. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of a positive mold; Figure 2 This is a schematic diagram of a female mold; Figure 3 This is a schematic diagram showing the alignment of the female mold and the male mold; Figure 4 This is a schematic diagram of an example of a female mold; Figure 5 This is a schematic diagram of a positive mold embodiment. Detailed Implementation

[0013] 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 in conjunction with the embodiments of this utility model. 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 protection scope of this utility model.

[0014] 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 setup and method set forth below, but covers any improvements, substitutions, and modifications to the structure, method, and device without departing from the spirit of this utility model. In the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring this utility model.

[0015] In the description of this utility model, it should be noted that the directions or positional relationships indicated by terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" are based on these directions or positional relationships and are only used for the convenience of describing this utility model and simplifying the description. They should not be construed as limiting this utility model. In addition, the use of ordinal numbers (e.g., "first and second," etc.) is for distinguishing objects and is not limited to this order, and should not be construed as indicating or implying relative importance.

[0016] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly, encompassing both direct connection and indirect connection via an intermediate medium. Those skilled in the art can understand the specific meaning of these terms in this utility model based on the specific circumstances.

[0017] 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 and in conjunction with the embodiments.

[0018] like Figure 3 and Figure 4 As shown, a titanium alloy Fy connector (13) of a large amphibious aircraft is connected to the fuselage skin and reinforcing frame (14) by 10 sets of fasteners. The upper end of the Fy connector is connected to the wing by bearings and connecting rods. When configuring the connection holes between the Fy connector (13) and the fuselage skin and reinforcing frame (14), due to the small distance between the wing and the fuselage, and the influence of the single ear on the Fy connector (13) on the construction space, it is difficult to drill some holes. The wing must be raised to ensure smooth hole drilling, which affects the drilling efficiency and drilling quality.

[0019] like Figures 1 to 4As shown: This utility model embodiment provides a drilling jig device for drilling holes in a large aircraft wing-body joint. The device comprises two parts: a female mold (1) and a male mold (2). The female mold (1) is plate-shaped and contains several holes (3). Each hole is equipped with several drill bushings (4) and several bolts, washers, and nuts (5). The male mold (2) is plate-shaped and contains several holes (6). Each hole is equipped with several drill bushings (7) and several bolts, washers, and nuts (8). The film-coating surface (9) of the female mold (1) and the film-coating surface (10) of the male mold (2) are completely fitted together. The holes (3) in the female mold (1) and the holes (6) in the male mold (2) are drilled integrally during the manufacturing of the drilling jig, and are coordinated with each other. The consistency of the holes can be checked by using the fitting pin (11). The drill bushings (4) and (7) are composed of various inner diameter specifications and are used to realize step-by-step drilling on the aircraft. The female mold (1) and the male mold (2) are positioned and connected to the aircraft product by bolts, washers and nuts respectively. The film-coating surface (9) of the female mold (1) and the film-coating surface (10) of the male mold (2) are completely fitted to the shape of the aircraft product to be installed. The hole (12) is a process hole for manufacturing the drilling jig.

[0020] The aircraft's wings and fuselage employ a multi-link connection scheme, with 6 links symmetrically arranged on each side, for a total of 12 links.

[0021] Taking the left side as an example, the links are: front Fz link (longitudinal), front Fy link (span), front Fxz link (diagonal / longitudinal), rear Fz link (longitudinal), rear Fy link (span), and rear Fxz link (diagonal / longitudinal). Each link has a double-eared connector at both ends, which connects to a single-eared connector on the wing or fuselage, respectively.

[0022] The single ear of the Fy connector on the body and the double ears of the Fy lever are connected, and the base is connected to the body by 10 sets of fasteners.

[0023] The female mold and the male mold are completely fitted together. The holes in the female mold and the male mold are drilled integrally during the manufacturing of the drilling jig and are coordinated with each other. The consistency of the holes can be checked by using the fitting pins. The female mold and the male mold are positioned and connected to the aircraft product by bolts, washers and nuts respectively. The drill bushing is composed of various inner diameter specifications and is used to achieve step-by-step drilling on aircraft; The female mold film surface and the male mold film surface are completely fitted to the shape of the aircraft product to be installed.

[0024] The operation process is as follows: When drilling the 10 sets of holes on the Fy connector (13), first use 4 sets of bolts, washers, and nuts (5) to connect the female mold (1) to the initial hole on the Fy connector (13), so that the film-coating surface (9) of the female mold (1) is completely fitted with the mating surface of the Fy connector (13). Then insert the drill bushing (4) with the smallest inner diameter into the hole (3) of the female mold (1) and use a tool with the corresponding inner diameter to drill the Fy connector (13). Then replace the drill bushing (4) with one larger inner diameter and use the same method to enlarge the hole of the Fy connector (13) until the final hole is reached. When drilling the 10 sets of holes on the fuselage skin and reinforcing frame (14), first use 4 sets of bolts, washers, and nuts (8) to connect the male mold (2) to the initial hole on the fuselage skin and reinforcing frame (14), so that the film-coating surface (10) of the male mold (2) is completely fitted with the mating surface of the fuselage skin and reinforcing frame (14). Then, the drill bushing (7) with the smallest inner diameter is inserted into the hole (6) of the male mold (2), and the fuselage skin and reinforcing frame (14) are drilled using a tool with the corresponding inner diameter. Then, the drill bushing (7) with a larger inner diameter is replaced, and the fuselage skin and reinforcing frame (14) are enlarged using the same method until the hole is completed. At this time, the hole position and diameter made on the Fy connector (13) are completely consistent with the hole position and diameter made on the fuselage skin and reinforcing frame (14), and the connection between the Fy connector (13) and the fuselage skin and reinforcing frame (14) can be completed directly using fasteners, overcoming the difficulties of the original process scheme. Before using the drill jig, the female mold (1) and the male mold (2) can be aligned, that is, the film-coating surface (9) of the female mold (1) and the film-coating surface (10) of the male mold (2) are fully aligned, and the alignment pin (11) is used to check the consistency of the hole position (3) of the female mold (1) and the hole position (6) of the male mold (2).

[0025] The above detailed embodiments are a description of the present utility model. It should not be considered that the specific embodiments of the present utility model are limited to these descriptions. For those skilled in the art, several simple deductions and substitutions can be made without departing from the concept of the present utility model, and all of these should be considered to fall within the protection scope of the present utility model.

Claims

1. A drilling jig device for drilling holes in a large aircraft wing-body joint, characterized in that, The device comprises two parts: a female mold and a male mold. The female mold is plate-shaped and includes several holes A, each equipped with a drill sleeve A. The male mold is plate-shaped and includes several holes B, each equipped with a drill sleeve B. The film-coating surface of the female mold and the film-coating surface of the male mold are completely aligned. The holes A and B are aligned one-to-one, and the drill sleeves A and B are aligned. The female mold is used to make holes in the Fy connector, and the male mold is used to make holes in the fuselage skin and reinforcing frame. The Fy connector and the fuselage skin and reinforcing frame are connected by fasteners after the holes are made.

2. The apparatus as claimed in claim 1, characterized in that, It also includes a matching pin, which is used to check the consistency of hole position A and hole position B.

3. The apparatus as described in claim 2, characterized in that, The aforementioned holes A are arranged in two rows, symmetrically on both sides of the female mold.

4. The apparatus as described in claim 3, characterized in that, The aforementioned holes B are arranged in two rows, symmetrically on both sides of the male mold.

5. The apparatus as described in claim 4, characterized in that, The female mold is fastened to the Fy connector using bolts, nuts, and a bolt.

6. The apparatus as claimed in claim 5, characterized in that, The male mold is fastened to the machine body skin and reinforcing frame using bolts and nuts.

7. The apparatus as claimed in claim 6, characterized in that, Gaskets are provided between the male mold and hole A, and between the female mold and hole B.

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