Butt joint positioning device and method for large components in closed space in aircraft assembly process

Abstract

The invention provides a butt joint positioning device and method for large components in a closed space in the aircraft assembling process. The butt-joint positioning assembly of the large component is completed by adopting a conical positioning pin and a fastening pin for fixing the large component. The conical positioning pin comprises a positioning pin, a large gasket, a large nut, a small gasket, a small nut and a guide sleeve; the fastening pin for fixing the large component is composed of a connecting pin, a fastening pin body, two kinds of gaskets with different sizes and a fixing device. Firstly, before a large component is positioned, a conical positioning pin and a part of assemblies for fixing a large component fastening pin are fixed to the upper end face of a closed area at a large component butt joint hole position of a closed area, and butt joint and initial positioning of the large component are completed under the guidance of the conical design of the positioning pin and the gravity of the large component in the butt joint process; and then the conical positioning pin and the other part of assembly for fixing the large component fastening pin are installed in a matched mode, and finally butt joint positioning of the large component in the closed space is achieved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft manufacturing, and particularly relates to a docking and positioning device and method for large components in a closed space during aircraft assembly. Background Art

[0002] During aircraft assembly, the docking and positioning of large components is the basis of aircraft assembly, and all processes of aircraft assembly rely on the precise and efficient completion of the docking and positioning of large components.

[0003] Currently, the main methods for docking and positioning large components include methods such as using numerical control measurement and positioning equipment or using tooling to hoist large components and finally achieve the consistency matching of installation elements.

[0004] The main drawbacks of the above methods are as follows: (1) For large components with specific structures, using numerical control measurement and positioning equipment for docking requires designing a dedicated docking system and learning to apply dedicated measurement and docking software, with a long cycle and high cost; (2) The main docking and positioning parts of large components are relatively open and accessible to operators, while for closed and narrow spaces, operators cannot reach them, and it is impossible to fix positioning devices such as positioning pins for large components, resulting in the inability to perform the docking and positioning of large components. Summary of the Invention

[0005] Aiming at the deficiencies of the current docking and positioning technology for large components in a closed space during aircraft assembly, the present invention proposes a docking and positioning device and method for large components in a closed space during aircraft assembly.

[0006] The first aspect of the present invention provides a docking and positioning device for large components in a closed space during aircraft assembly, including: a conical positioning pin 4 and a fixing large component fastening pin 5;

[0007] The conical positioning pin 4 includes: a positioning pin 6, a large washer 7, a large nut 8, a small washer 9, a small nut 10, and a guide sleeve 11;

[0008] The positioning pin 6 is fixed on the upper layer connected part 2 through the large washer 7 and the large nut 8. Before docking and positioning, the guide sleeve 11 is sleeved on the positioning pin 6. After docking and positioning, the positioning pin 6 is fixed on the lower layer connected part 3 through the small washer 9 and the small nut 10; an operation hole is provided on the upper layer connected part 2;

[0009] The fixing large component fastening pin 5 includes: a fastening pin 12, a gasket 13, a fixing device 14, a connecting pin 15, a gasket 16; the fixing device 14 includes: a nut and a handle; a threaded hole is provided at the end of the fastening pin 12;

[0010] The fastening pin 12 is fixed on the upper layer connected part 2 through the gasket 13 and the fixing device 14,

[0011] After docking and positioning, the connecting pin 15 is threadedly inserted into the end of the fastening pin 12, and the gasket 16 is connected to the connecting pin 15 for fixing the connecting pin 15 to the lower-layer connected part 3.

[0012] Optionally, when the guide sleeve 11 is sleeved on the positioning pin 6, the total length of the guide sleeve 11 and the positioning pin 6 is greater than the total length of the fastening pin 12.

[0013] Optionally, the nut of the fixing device 14 is threadedly connected to the fastening pin 12; one end of the handle is sleeved outside the nut of the fixing device 14 for driving the nut of the fixing device 14 to rotate.

[0014] Optionally, the outer ring of the nut of the fixing device 14 and the inner ring of one end of the handle are hexagonal.

[0015] Optionally, the guide sleeve 11 is made of copper material.

[0016] Optionally, the guide sleeve 11 is conical.

[0017] Optionally, the guide sleeve 11 is threadedly connected to the positioning pin 6.

[0018] The second aspect of the present invention provides a docking and positioning method using the large-component docking and positioning device in the aircraft assembly process as described in any one of the first aspect, including:

[0019] Install the conical positioning pin on the upper end face of the upper-layer connected part 2 in a manner similar to bolt installation with the help of a large nut and a large washer, and fix the upper part of the positioning pin on the upper end face of the upper-layer connected part 2 with the help of the self-handle of the fixed large-component fastening pin and a universal open-end wrench;

[0020] Lift the upper-layer connected part 2 to the upper end face of the lower-layer connected part 3. At a distance of 10 mm from the upper end face of the lower-layer connected part 3, use a crane and a traction device to complete the alignment of the basic position of the large component. After the position of the large component is basically stable, use the guide sleeve of the conical positioning pin and the gravity of the large component itself to complete the alignment and docking of the docking positioning holes of the large component;

[0021] Disassemble the guide sleeve of the conical positioning pin and replace it with a connecting small nut and a small washer. At this time, the preliminary docking and positioning of the large component are completed;

[0022] According to the upper half of the fixed large-component fastening pin installed on the large component on the ground, insert the lower half of the fixed large-component fastening pin through the corresponding hole of the component docked with the large component to connect it with the fixed large-component fastening pin, and finally complete the docking and positioning of the large component.

[0023] The beneficial effects of this application are as follows:

[0024] 1) Before the docking and positioning of large components, install the conical positioning pins and the fastening pins for fixing large components on the upper end surface of the cavity structure at the upper end of the docking holes in the closed area of the large components. This assembly avoids the inaccessibility of the closed space during the docking of large components and the inability to install the positioning pins in real time according to the docking state, realizing the pre-installation of the positioning pins and fastening pins for large components in the closed space.

[0025] 2) During the docking process of large components, rely on the guide sleeves of the already installed conical fixing pins and the gravity of the large components themselves to complete the preliminary positioning of the large components, creating a new method for the docking of large components in a closed space. Design the special positioning pins and the fastening pins for fixing large components according to the structural characteristics of the large components themselves and the docking area, making the separation surface of the tooling design of the positioning pins and the fastening pins for fixing large components coincide with the docking structure form of the large components. Using this docking and positioning method does not require designing and purchasing software for large component docking and positioning equipment, reducing costs, while meeting the docking requirements of large components and improving the safety of personnel and products.

[0026] 3) The design concept of the present invention is novel, easy to implement, and widely applicable, providing a technical solution for the docking and positioning problem of large components in a closed space during the assembly process in the aerospace field, and having extremely high application value and wide popularization. Description of the Drawings

[0027] Figure 1 It is a schematic diagram of the large component structure;

[0028] Figure 2 It is a schematic diagram of the upper connected structure;

[0029] Figure 3 It is a schematic diagram of the lower connected structure;

[0030] Figure 4 It is a schematic diagram of the conical positioning pin structure;

[0031] Figure 5 It is a schematic diagram of the fastening pin for fixing large components;

[0032] Description of the Reference Numerals:

[0033] 1 Large component structure, 2 Upper connected part, 3 Lower connected part, 4 Conical positioning pin, 5 Fastening pin for fixing large components, 6 Positioning pin, 7 Large washer, 8 Large nut, 9 Small washer, 10 Small nut, 11 Guide sleeve, 12 Fastening pin, 13 Gasket, 14 Fixing device, 15 Connecting pin, 16 Gasket. Detailed Implementation Modes

[0034] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts fall within the scope of protection of the present invention.

[0035] The features and exemplary embodiments of various aspects of the present invention will be described in detail below. In the following detailed description, many specific details are set forth in order to provide a comprehensive understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be practiced without some of these specific details. The following description of the embodiments is only intended to provide a better understanding of the present invention by showing examples of the present invention. The present invention is in no way limited to any specific arrangements and methods set forth below, but covers any improvements, substitutions, and modifications of structures, methods, and devices without departing from the spirit of the present invention. In the drawings and the following description, well-known structures and technologies are not shown to avoid unnecessarily obscuring the present invention.

[0036] In the description of the present invention, it should be noted that the directions or positional relationships indicated by terms such as "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, and should not be construed as limiting the present invention. In addition, the use of ordinal numbers (for example, "first and second", etc.) is to distinguish objects and is not limited to this order, and should not be construed as indicating or implying relative importance.

[0037] In the description of the present invention, it should be noted that unless otherwise clearly specified and limited, the terms "installation", "connection", and "coupling" should be understood in a broad sense, and can be directly connected or indirectly connected through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0038] It should be noted that, without conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other, and the various embodiments can be referenced and cited from each other. The following will describe the present invention in detail with reference to the drawings and in combination with the embodiments.

[0039] The following further describes the present invention in detail with reference to the embodiments and the drawings, but the embodiments of the present invention are not limited thereto.

[0040] Such as Figures 1-5As shown in the figure, the present invention provides a method for docking and positioning large components in a closed space during aircraft assembly. According to the self-requirements of the large component structure 1 during docking in the closed space, a conical positioning pin 4 and a design separation surface for fixing the large component fastening pin 5 are designed, and the installation of the conical positioning pin and the fastening pin is completed during the ground placement stage of the large component.

[0041] The method includes: installing the conical positioning pin 4 in a manner similar to bolt installation with the help of a nut and a washer on the upper connected part 2 in the closed area of the large component, and fixing the upper part of the positioning pin on the upper connected part 2 in the closed area of the large component with the help of its own handle and a universal open-end wrench for the fixed large component fastening pin 5. Hoist the large component to the upper end face of the docking component, and at a distance of 10 mm from the upper end face of the large component docking component, complete the alignment of the basic position of the large component with the help of a crane and a traction device. After the position of the large component is basically stable, complete the alignment and docking of the docking positioning hole of the large component with the help of the guide sleeve of the conical positioning pin and the gravity of the large component itself. Then disassemble the guide sleeve of the conical positioning pin and replace it with a connecting nut and a washer. At this time, the preliminary docking and positioning of the upper connected part 2 and the lower connected part 3 of the large component are completed; subsequently, according to the upper half of the fixed large component fastening pin installed on the large component on the ground, insert the lower half of the fixed large component fastening pin through the corresponding hole of the component docked with the large component to connect it with the fixed large component fastening pin, and finally complete the docking and positioning of the large component.

[0042] This docking and positioning method is simple to operate, has a low manufacturing cost, and is safe and reliable in operation. According to the self-structural characteristics of the closed area of the large component and the components at the docking part, a conical positioning pin and a design separation surface for fixing the fastening pin are designed, and partial installation of the conical positioning pin and the fixed fastening pin is completed during the ground placement stage of the large component, effectively solving the problem of docking and positioning large components in a closed space during aircraft assembly. This positioning method is applied to the docking and positioning of large components in a closed space in the aircraft assembly field for the first time.

[0043] To achieve the above object, the present invention proposes the following technical solutions:

[0044] A method and device for docking and positioning large components in a closed space during aircraft assembly are composed of a conical positioning pin and a fixed large component fastening pin. The conical positioning pin is composed of 6 parts: a positioning pin, a large washer, a large nut, a small washer, a small nut, and a guide sleeve; the fixed large component fastening pin is composed of 5 parts: a connecting pin, a fastening pin, two types of gaskets with different sizes, and a fixing device.

[0045] Since the large component is relatively large in both volume and weight, before docking the large component, it is placed on a ground placement rack. The operator enters the docking area inside the large component through a specially made step ladder. First, insert the tapered positioning pin through the opening on the upper end face of the hole of the large component docking bolt, and fix the positioning pin to the upper end face of the docking positioning hole of the large component through a large washer and a large nut, so as to ensure that the large component can use the positioning pin for large component docking positioning guidance during docking, and complete the initial docking positioning of the large component.

[0046] During the ground placement stage of the large component, it is also necessary to complete the installation of the fixed large component fastening pin. With the help of an open-end wrench and a fixed fastening pin handle, complete the installation of the fixed fastening pin on the upper end face of the docking positioning hole of the large component, so as to ensure the final positioning after the large component completes the initial positioning.

[0047] After the positioning pin and the fixed large component fastening pin are installed on the ground, hoist the large component. After hoisting the large component to 10 mm above the upper end face of the docking component, use a traction tool to basically align the hole positions of the large component. Then, with the guiding function of the positioning pin guide sleeve and the gravity of the large component itself, make the large component slowly descend, and finally achieve the initial positioning of the large component.

[0048] After the initial positioning of the large component is completed, disassemble the guide sleeve of the fixed pin and replace it with a small nut. Insert the connecting pin of the fastening pin from the bottom up through the connecting hole of the component docked with the large component, and finally complete the docking positioning of the large component.

[0049] Using the above method for docking and positioning large components in a closed space during aircraft assembly, special positioning pins and fastening pins can be designed according to the structural form of the closed space of the large component, the size of the hole positions, and the spatial configuration of the closed area. Considering the characteristics of the closed space structure in the docking area of the large component, part of the installation of the positioning pin and the fastening pin is completed during the placement stage before the large component is positioned. Thus, with the help of the gravity of the large component itself and the guidance of the tapered sleeve of the positioning pin, the initial positioning of the large component is completed. After the initial positioning is completed, the lower half of the fastening pin is connected to complete the final docking positioning of the large component.

[0050] Referring to the attached drawings, the present invention proposes a method and device for docking and positioning large components in a closed space during aircraft assembly. The positioning device consists of two kinds of toolings, namely a tapered positioning pin and a fixed large component fastening pin.

[0051] The tapered positioning pin is composed of 6 parts: a positioning pin, a large washer, a large nut, a small washer, a small nut, and a guide sleeve. The tapered positioning pin is disassembled into 6 parts. First, during the ground placement stage of the large component, insert the positioning pin through the opening on the upper end face of the hole of the large component docking bolt, and fix the positioning pin to the upper end face of the docking positioning hole of the large component through a large washer and a large nut.

[0052] The fixed large-component fastening pin consists of a connecting pin, a fastening pin, two types of gaskets with different sizes, and a fixing device, which are decomposed into 5 parts. During the ground placement stage of the large component, the fastening pin and the fixing device are inserted through the opening on the upper end face of the hole of the large-component docking bolt, and a common tool, an open-end wrench, is used in conjunction with the fixing device to tighten the fastening pin and fix it to the upper end face of the docking positioning hole of the large component.

[0053] After the conical positioning pin and the fixed large-component fastening pin are installed on the ground, the large component is hoisted. After the large component is hoisted 10 mm above the upper end face of the docking component, the basic alignment of the large-component hole position is achieved with the help of a traction tool. Then, with the guiding effect of the positioning pin guide sleeve and the gravity of the large component itself, the large component slowly descends, and finally the preliminary positioning of the large component is achieved. The guide sleeve of the positioning pin is disassembled and replaced with a small nut and a small washer of the positioning pin. Then, the connecting pin of the fastening pin is inserted into the hole of the component docked with the large component to complete the docking and positioning of the large component.

[0054] Figure 4 It is a structural schematic diagram of the conical positioning pin. When the large component is placed on the ground, the small nut of the positioning pin is disassembled, and the positioning pin 6 is inserted into the upper end face of the closed docking area of the large component. The ground installation of the fixing pin is completed using the large washer 7 and the large nut 8. After the large component is docked and preliminarily positioned, the guide sleeve 11 is disassembled at the connection hole of another component docked with the large component, and the small washer 9 and the small nut 10 are installed.

[0055] Figure 5 It is a structural schematic diagram of the fixed large-component fastening pin. When the large component is placed on the ground, the connecting pin 15, the gasket 16, and the fixing device 14 of the fastening pin are disassembled. The fastening pin 12 and the gasket 13 are inserted into the upper-end hole of the large component and enter the closed docking area of the large component. The fixing device 14 is installed from the side end of the large component. The common tool, an open-end wrench, acts on the head of the fastening pin and cooperates with the fixing device 14 to tighten the fastening pin. After the large component is docked and preliminarily positioned, the connecting pin 15 is installed at the connection hole of another component docked with the large component and tightened in cooperation with the fastening pin 16 to complete the connection and final positioning of the large component.

[0056] Using the above method, the structural form of the large component in a closed space is used as the design separation surface of the conical positioning pin and the fixed large-component fastening pin used during the docking of the large component. The matching positioning pin and fastening pin are designed. Before hoisting the large component, a part of the positioning pin and the fastening pin is installed. During the docking process, the docking and preliminary positioning of the large component are completed under the guidance of the conical design of the positioning pin and the gravity of the large component itself. Then, the other part of the positioning pin and the fastening pin is installed, and finally, the docking and positioning of the large component in a closed space are achieved.

[0057] The above specific embodiments are detailed descriptions of the present invention. It cannot be determined that the specific embodiments of the present invention are only limited to these descriptions. For those of ordinary skill in the technical field to which the present invention pertains, without departing from the concept of the present invention, several simple deductions and substitutions can still be made, and all should be regarded as belonging to the protection scope of the present invention.

Claims

1. A large component docking and positioning device for closed spaces during aircraft assembly, characterized in that, Including: A conical locating pin (4) and a fixing large-component fastening pin (5); The conical locating pin (4) includes: a locating pin (6), a large washer (7), a large nut (8), a small washer (9), a small nut (10), and a guide sleeve (11); The locating pin (6) is fixed to the upper-layer connected part (2) through the large washer (7) and the large nut (8). Before butt joint positioning, the guide sleeve (11) is sleeved on the locating pin (6). After butt joint positioning, the locating pin (6) is fixed to the lower-layer connected part (3) through the small washer (9) and the small nut (10); an operation hole is provided on the upper-layer connected part (2); The fixing large-component fastening pin (5) includes: a fastening pin (12), a gasket (13), a fixing device (14), a connecting pin (15), a gasket (16); the fixing device (14) includes: a nut and a handle; a threaded hole is provided at the end of the fastening pin (12); The fastening pin (12) is fixed to the upper-layer connected part (2) through the gasket (13) and the fixing device (14), After butt joint positioning, the connecting pin (15) is threadedly inserted into the end of the fastening pin (12), and the gasket (16) is connected to the connecting pin (15) for fixing the connecting pin (15) to the lower-layer connected part (3).

2. The closed-space large-component docking and positioning device in the aircraft assembly process according to claim 1, characterized in that, When the guide sleeve (11) is sleeved on the locating pin (6), the total length of the guide sleeve (11) and the locating pin (6) is greater than the total length of the fastening pin (12).

3. The large component docking and positioning device for closed spaces in the aircraft assembly process according to claim 1, wherein The nut of the fixing device (14) is threadedly connected to the fastening pin (12); one end of the handle is sleeved outside the nut of the fixing device (14) for driving the nut of the fixing device (14) to rotate.

4. The closed space large component docking and positioning device in the aircraft assembly process according to claim 3, characterized in that, The outer circle of the nut of the fixing device (14) and the inner circle of one end of the handle are hexagonal.

5. The closed - space large - component docking and positioning device during aircraft assembly according to claim 1, wherein, The guide sleeve (11) is made of copper material.

6. The closed space large component docking and positioning device in the aircraft assembly process according to claim 1, characterized in that, The guide sleeve (11) is conical.

7. The closed space large component docking and positioning device in the aircraft assembly process according to claim 1, characterized in that, The guide sleeve (11) is threadedly connected to the locating pin (6).

8. A docking and positioning method using the docking and positioning device for large components in a closed space during the aircraft assembly process as described in any one of claims 1-7, characterized in that, Including: Install the conical locating pin on the upper end face of the upper-layer connected part (2) in a manner similar to bolt installation by means of a large nut and a large washer, and fix the upper part of the locating pin on the upper end face of the upper-layer connected part (2) by means of the fixing large-component fastening pin's own handle and a universal open-end wrench; Lift the upper-layer connected part (2) to the upper end face of the lower-layer connected part (3). At a position 10 mm away from the upper end face of the lower-layer connected part (3), use a crane and a traction device to complete the alignment of the basic position of the large component. After the position of the large component is basically stable, use the guide sleeve of the conical locating pin and the gravity of the large component itself to complete the alignment and butt joint of the butt joint positioning hole of the large component; Disassemble the guide sleeve of the conical locating pin and replace it with a connecting small nut and a small washer. At this time, the preliminary butt joint and positioning of the large component are completed; According to the upper half of the fixing large-component fastening pin installed on the large component on the ground, insert the lower half of the fixing large-component fastening pin through the corresponding hole of the component docked with the large component to connect it to the fixing large-component fastening pin, and finally complete the butt joint and positioning of the large component.

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