Simulation machine body tool for verifying wiring harness laying process

Abstract

The utility model belongs to the technical field of aviation, and discloses a simulation fuselage tool for verifying a wiring harness laying process. Openings are formed in the two ends of the simulation machine body tool so that a robot can enter and exit, the simulation machine body tool comprises a floor assembly, a plurality of machine body frame assemblies and a plurality of machine body stringers, the machine body frame assemblies are arranged at intervals in the length direction of the floor assembly, the machine body frame assemblies are of an arc-shaped structure, and the machine body stringers are arranged at intervals in the circumferential direction of the machine body frame assemblies. The fuselage stringers extend in the length direction of the floor assembly, and one fuselage stringer is connected with the multiple fuselage frame assemblies. Through the design of the floor assembly, the plurality of fuselage frame assemblies and the plurality of fuselage stringers, the actual working environment of the middle fuselage barrel section structure is simulated, the accuracy and reliability of a verification result can be ensured, and a conclusion obtained from the simulation fuselage tool can be well applied to the actual aircraft assembly process.

Description

Technical Field

[0001] The utility model relates to the field of aviation technology, in particular to a simulated fuselage tooling for verifying the wiring harness laying process. Background Art

[0002] Civil aircraft assembly manufacturing has the characteristics of many installed parts, many types of parts, many installation forms, high installation requirements, and narrow installation space. For example, the wiring harness installation in the aircraft has 400 wires, nearly 4,000 applicable connectors, and more than 40,000 termination points; the operating space is dark and narrow; the installation requirements are strict, and the wiring requirements such as wiring harness spacing, bending radius, slackness, and connector assembly requirements must be met. It takes a long time and is inefficient to use manual labor to lay and inspect the entire aircraft wiring harness.

[0003] Therefore, it is proposed to use robots and operators to share the working space, give full play to their respective strengths, divide the work and work together to ensure the quality of aircraft assembly and improve assembly efficiency. Human-machine collaboration is a new process for wiring harness laying. In order to improve the maturity of technology and evaluate economic efficiency and quality efficiency, it is necessary to make robots and operators actually perform a series of operations for wiring harness laying to evaluate the feasibility of human-machine collaboration for wiring harness laying. However, using aircraft for verification is very costly and inconvenient.

[0004] Therefore, it is necessary to provide a simulated fuselage tooling for wire harness laying process verification to evaluate the feasibility of this new process of wire harness laying by human-machine collaboration. Utility Model Content

[0005] The purpose of the utility model is to provide a simulated fuselage tooling for wire harness laying process verification, so as to simulate the actual working environment of the mid-fuselage barrel section structure, help to ensure the accuracy and reliability of the verification results, so that the conclusions drawn from this simulated fuselage tooling can be better applied to the actual aircraft assembly process.

[0006] To achieve this purpose, the utility model adopts the following technical solutions:

[0007] A simulated fuselage tooling for harness laying process verification, the simulated fuselage tooling is used to simulate the structure of the middle fuselage barrel section, and openings are provided at both ends of the simulated fuselage tooling for robots to enter and exit, and the simulated fuselage tooling includes:

[0008] Floor assemblies;

[0009] A plurality of fuselage frame assemblies are arranged at intervals along the length direction of the floor assembly, and the fuselage frame assemblies are in an arc-shaped structure;

[0010] A plurality of fuselage long stringers are arranged at intervals along the circumference of the fuselage frame assembly, and the fuselage long stringers extend along the length direction of the floor assembly. One fuselage long stringer is connected to a plurality of fuselage frame assemblies.

[0011] Preferably, the floor assembly comprises:

[0012] A base frame, on which a plurality of base plates are fixedly arranged, and the plurality of base plates are spliced ​​to form the surface of the floor assembly;

[0013] A plurality of universal wheels are arranged at the bottom of the base frame.

[0014] Preferably, the universal wheel comprises a wheel body and a buckle, and the buckle can limit the rotation of the wheel body.

[0015] Preferably, the floor assembly further comprises:

[0016] A plurality of adjusting feet are arranged at the bottom of the base frame, and the height of the adjusting feet is adjustable.

[0017] Preferably, the fuselage frame assembly comprises:

[0018] A plurality of segmented frames, each segmented frame comprising a web and edge strips arranged around the web, and portions of the edge strips of two adjacent segmented frames are directly opposite;

[0019] The locking piece is used to fix and connect two adjacent segment frames.

[0020] Preferably, a plurality of reinforcing ribs are arranged in the segment frame, and the plurality of reinforcing ribs are arranged at intervals along the length direction of the segment frame.

[0021] Preferably, a plurality of slots are provided on one side of the segment frame, the plurality of slots are spaced apart along the length direction of the segment frame, and the plurality of fuselage long stringers are correspondingly mounted in the plurality of slots.

[0022] Preferably, the simulated fuselage tooling further comprises:

[0023] The fuselage skin is covered and fixed on the plurality of fuselage frame components, and the fuselage skin is an arc-shaped structure.

[0024] Preferably, the simulated fuselage tooling further comprises:

[0025] A plurality of support components, one end of each support component is fixed to the floor component, and the other end of each support component is fixed to the fuselage frame component.

[0026] Preferably, an entrance is provided on the side of the simulated fuselage tooling.

[0027] Beneficial effects of the utility model:

[0028] This simulated fuselage tooling is provided with openings at both ends for the robot to enter and exit. The simulated fuselage tooling includes a floor assembly, multiple fuselage frame assemblies and multiple fuselage long stringers. The multiple fuselage frame assemblies are arranged at intervals along the length direction of the floor assembly. The fuselage frame assembly is an arc-shaped structure. The multiple fuselage long stringers are arranged at intervals along the circumference of the fuselage frame assembly. The fuselage long stringers extend along the length direction of the floor assembly. One fuselage long stringer is connected to multiple fuselage frame assemblies.

[0029] Compared with directly using the real aircraft fuselage to verify the wiring harness laying process, the simulated fuselage tooling greatly reduces the cost. The manufacturing cost of the real aircraft fuselage is high, and once used for verification experiments, it may cause irreversible damage. The simulated fuselage tooling provides a cost-effective alternative. The design of the simulated fuselage tooling allows easy assembly and disassembly in a laboratory or factory environment, facilitating multiple iterations of verification to optimize the wiring harness laying process for human-machine collaboration. Verification on the simulated fuselage tooling can avoid potential safety hazards to the real aircraft. At the same time, for operators and robots, working in the simulated fuselage tooling is also safer and more controllable, reducing the risk of accidents. By designing floor components, multiple fuselage frame components and multiple fuselage long spars to simulate the actual working environment of the mid-fuselage barrel section structure, it helps to ensure the accuracy and reliability of the verification results, so that the conclusions drawn from this simulated fuselage tooling can be better applied to the actual aircraft assembly process. Openings are set at both ends of the simulated fuselage tooling to facilitate the robot's entry and exit, providing conditions for the robot and the operator to share the working space. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a structural schematic diagram of the simulated fuselage tooling provided by the utility model;

[0031] Figure 2 It is a structural schematic diagram of the simulated fuselage tooling (excluding the fuselage skin) provided by the utility model;

[0032] Figure 3 It is a structural schematic diagram of the floor assembly provided by the utility model;

[0033] Figure 4 It is a partial structural schematic diagram of the fuselage frame assembly provided by the utility model;

[0034] Figure 5 It is a partial structural schematic diagram of the fuselage long stringer provided by the utility model;

[0035] Figure 6 It is a structural schematic diagram of the support assembly provided by the utility model.

[0036] In the figure:

[0037] 1. Floor assembly; 11. Base frame; 12. Bottom plate; 13. Universal wheels; 14. Adjustable feet;

[0038] 2. Fuselage frame assembly; 21. Segmented frame; 211. Web; 212. Edge strip; 22. Reinforcement rib; 23. Slot;

[0039] 3. Fuselage long stringer;

[0040] 4. Fuselage skin;

[0041] 5. Passenger observation window;

[0042] 6. Support assembly; 61. Carbon fiber tube; 62. Pipe joint;

[0043] 7. Entrance. DETAILED DESCRIPTION

[0044] The present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only the parts related to the present invention, rather than all structures, are shown in the accompanying drawings.

[0045] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0046] In the present utility model, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0047] In the description of this embodiment, the terms "upper", "lower", "right", etc., are based on the directions or positions shown in the drawings, and are only for the convenience of description and simplified operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation of the present invention. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0048] Manual work for wiring harness laying and inspection of the entire aircraft takes a long time and is inefficient. Therefore, it is proposed to use robots to share the working space with operators, give full play to their respective strengths, divide the work and work together to ensure the quality of aircraft assembly and improve assembly efficiency. Human-machine collaboration for wiring harness laying is a new process. In order to improve the maturity of the technology, evaluate economic efficiency and improve quality efficiency, it is necessary to enable robots and operators to actually perform a series of operations for wiring harness laying to evaluate the feasibility of human-machine collaboration for wiring harness laying. However, using real aircraft for verification is very costly and inconvenient.

[0049] In order to solve the above problems, Figure 1-Figure 6 As shown, the present embodiment provides a simulated fuselage tooling for harness laying process verification, which is used to simulate the structure of the middle fuselage barrel section. Openings are set at both ends of the simulated fuselage tooling to allow robots to enter and exit. The simulated fuselage tooling includes a floor assembly 1, multiple fuselage frame assemblies 2 and multiple fuselage long stringers 3. The multiple fuselage frame assemblies 2 are arranged at intervals along the length direction of the floor assembly 1. The fuselage frame assembly 2 is an arc-shaped structure. The multiple fuselage long stringers 3 are arranged at intervals along the circumference of the fuselage frame assembly 2. The fuselage long stringers 3 extend along the length direction of the floor assembly 1. One fuselage long stringer 3 is connected to multiple fuselage frame assemblies 2.

[0050] The wiring harness laying process includes six items: bracket installation, clamp installation, wiring harness lifting and pre-installation, wiring harness fixing, connector plugging and tightening, and quality inspection. When verifying the wiring harness laying process, the robot enters the tooling through the opening at one end of the simulated fuselage tooling. When installing the bracket, the robot fixes the bracket at the preset position on the fuselage frame assembly 2 according to the wiring harness laying path, and the operator rivets or screws it to lock the bracket at the preset position; when installing the clamp, the operator selects the clamp according to the drawing, and the robot uses tools to screw or rivet the clamp to the bracket; when lifting and pre-installing the wire harness, the robot lifts and installs the wire harness, and the operator places the wire harness in the clamp; when fixing the wire harness, the robot closes and locks the clamp; when tightening the connectors, the robot fixes the socket and plug respectively and tightens the plug into place; when performing quality inspection, the robot uses machine vision to perform three-dimensional scanning and reconstruction of the slack of the wire harness laying to check whether it meets the requirements; after the verification, the robot exits from the opening at the other end of the simulated fuselage tooling.

[0051] Compared with directly using the real aircraft fuselage to verify the wiring harness laying process, the simulated fuselage tooling greatly reduces the cost. The manufacturing cost of the real aircraft fuselage is high, and once used for verification experiments, it may cause irreversible damage, while the simulated fuselage tooling provides a cost-effective alternative. The design of the simulated fuselage tooling allows easy assembly and disassembly in a laboratory or factory environment, facilitating multiple iterations of verification to optimize the wiring harness laying process for human-machine collaboration. Verification on the simulated fuselage tooling can avoid potential safety hazards to the real aircraft. At the same time, for operators and robots, working in the simulated fuselage tooling is also safer and more controllable, reducing the risk of accidents. By designing a floor assembly 1, multiple fuselage frame assemblies 2, and multiple fuselage long girders 3 to simulate the actual working environment of the mid-fuselage barrel section structure, it helps to ensure the accuracy and reliability of the verification results, so that the conclusions drawn from this simulated fuselage tooling can be better applied to the actual aircraft assembly process. Openings are set at both ends of the simulated fuselage tooling to facilitate the robot's entry and exit, providing conditions for the robot and the operator to share the working space.

[0052] In this embodiment, slope pads (not shown) are provided at both ends of the floor assembly 1, which make the transition between the floor assembly 1 and the ground smoother, making it easier for the robot to enter and exit the simulated fuselage tooling. To ensure the robot's passage safety, its moving speed is no more than 5 km / h.

[0053] Specifically, Figure 2As shown, the floor assembly 1 includes a base frame 11, a bottom plate 12 and a plurality of universal wheels 13. A plurality of bottom plates 12 are fixedly arranged on the base frame 11. The plurality of bottom plates 12 are spliced ​​to form the surface of the floor assembly 1. The plurality of universal wheels 13 are arranged at the bottom of the base frame 11. The base frame 11, as the basic structure of the floor assembly 1, can provide stable support to ensure that the floor assembly 1 will not collapse or deform during use. The plurality of bottom plates 12 are spliced ​​to form the surface of the floor assembly 1, which is not only convenient for installation and disassembly, but also can enhance the overall strength of the floor assembly 1 to a certain extent. The plurality of universal wheels 13 are arranged at the bottom of the base frame 11, so that the floor assembly 1 has a high degree of flexibility and can be easily moved to adjust the position.

[0054] In this embodiment, the universal wheel 13 includes a wheel body and a buckle, and the buckle can limit the rotation of the wheel body. The buckle can lock the wheel body to prevent it from rotating, so that the simulated fuselage tooling can remain stable when it is moved to a suitable position, avoiding shaking or deviation during the subsequent verification process, which affects the wiring harness laying.

[0055] Furthermore, if Figure 3 As shown, the floor assembly 1 further includes a plurality of adjustable feet 14, which are arranged at the bottom of the base frame 11, and the height of the adjustable feet 14 is adjustable. The height adjustability of the adjustable feet 14 enables the simulated fuselage tooling to adapt to uneven ground environments. By adjusting the height of the adjustable feet 14, it is possible to ensure that the simulated fuselage tooling maintains stable contact with the ground, avoid shaking or tilting, and ensure smooth wiring harness laying.

[0056] Specifically, Figure 4 As shown, the fuselage frame assembly 2 includes a plurality of segmented frames 21 and locking pieces. The segmented frames 21 include a web 211 and edge strips 212 arranged around the web 211. Part of the edge strips 212 of two adjacent segmented frames 21 are opposite to each other. The locking piece is used to fix and connect the two adjacent segmented frames 21. The plurality of segmented frames 21 are spliced ​​so that the fuselage frame assembly 2 can disperse and bear loads from different directions, thereby improving the strength and stability of the overall structure. The design of the segmented frames 21 makes the manufacturing process of the fuselage frame assembly 2 more flexible and efficient. Segmented frames 21 of different sizes and shapes can be produced as needed, and the segmented frames 21 are assembled into a complete fuselage frame assembly 2 through locking pieces. This modular production method helps to reduce manufacturing costs and improve production efficiency. When a segmented frame 21 in the fuselage frame assembly 2 is damaged or needs to be repaired, the segmented frame 21 can be disassembled and replaced separately without disassembling the entire assembly, which helps to shorten maintenance time and reduce maintenance costs. The combination of the web 211 and the edge strip 212 enables the segment frame 21 to distribute stress more effectively when bearing a load, thereby reducing the phenomenon of stress concentration. Specifically, the segment frame 21 is made of aluminum alloy.

[0057] In this embodiment, the locking member is a bolt, and the bolt passes through the edge strips 212 of the two segment frames 21 to fix the two. This fixing method is simple, efficient and highly reliable.

[0058] Furthermore, if Figure 4 As shown, a plurality of reinforcing ribs 22 are arranged in the segment frame 21, and the plurality of reinforcing ribs 22 are arranged at intervals along the length direction of the segment frame 21. The reinforcing ribs 22 can significantly increase the strength and rigidity of the segment frame 21, avoid the occurrence of stress concentration, and improve the overall stability and durability of the structure.

[0059] For more details, see Figure 4 A plurality of slots 23 are provided on one side of the fuselage frame assembly 2, and the plurality of slots 23 are arranged at intervals along the length direction of the fuselage frame assembly 2, and the plurality of fuselage long stringers 3 are correspondingly arranged in the plurality of slots 23. The arrangement of the slots 23 helps to disperse the stress borne by the fuselage long stringers 3 to the segment frame 21, thereby improving the bearing capacity and stability of the overall structure.

[0060] In this embodiment, the fuselage long stringer 3 is made of aluminum alloy and is processed by L-shaped material.

[0061] Specifically, Figure 1 As shown, the simulated fuselage tooling also includes a fuselage skin 4, which is covered and fixed on multiple fuselage frame components 2, and the fuselage skin 4 is an arc-shaped structure. The authenticity of the verification scene is ensured by setting the fuselage skin 4. Specifically, the fuselage skin 4 is formed by bending an aluminum alloy plate.

[0062] In order to further ensure the authenticity of the verification scenario, in this embodiment, Figure 1 As shown, a mounting opening is provided on the fuselage skin 4, and a passenger observation window 5 is installed at the mounting opening. Specifically, the window frame of the passenger observation window 5 is formed by 3D printing, and the glass of the passenger observation window 5 is made of acrylic material.

[0063] Specifically, Figure 1 , Figure 6 As shown, the fuselage simulation tooling further includes a plurality of support assemblies 6, which are distributed according to preset installation positions, with one end of the support assembly 6 fixed to the floor assembly 1 and the other end fixed to the fuselage frame assembly 2. The support assembly 6 effectively distributes the weight and force of the fuselage frame assembly 2 to the floor assembly 1, avoiding local overload and stress concentration, thereby enhancing the stability of the overall structure.

[0064] In this embodiment, if Figure 6 As shown, the support assembly 6 is composed of a carbon fiber tube 61 and pipe joints 62 arranged at both ends of the carbon fiber tube 61. The material of the pipe joint 62 is aluminum alloy. The pipe joint 62 is fixedly connected to the floor assembly 1 / fuselage frame assembly 2 by bolts, and the installation is simple and quick.

[0065] In this embodiment, if Figure 1 , Figure 2 As shown, an entrance 7 is provided on the side of the fuselage simulation tooling for operators to enter and exit. The opening for the robot to enter and exit is separated from the entrance 7 for the operator to enter and exit, so that the two can operate in parallel without interfering with each other.

[0066] Obviously, the above embodiments of the present invention are merely examples for the purpose of clearly illustrating the present invention, and are not intended to limit the implementation methods of the present invention. For those skilled in the art, various obvious changes, readjustments and substitutions can be made without departing from the scope of protection of the present invention. It is not necessary and impossible to list all implementation methods here. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention shall be included in the scope of protection of the claims of the present invention.

Claims

1. A simulated fuselage tooling for wire harness laying process verification, characterized in that: The simulated fuselage tooling is used to simulate the structure of the middle fuselage barrel section. Openings are provided at both ends of the simulated fuselage tooling for the robot to enter and exit. The simulated fuselage tooling includes: Floor assembly (1); A plurality of fuselage frame assemblies (2) are arranged at intervals along the length direction of the floor assembly (1), and the fuselage frame assemblies (2) are in an arc-shaped structure; A plurality of fuselage long stringers (3) are arranged at intervals along the circumference of the fuselage frame assembly (2); the fuselage long stringers (3) extend along the length direction of the floor assembly (1); and one fuselage long stringer (3) is connected to a plurality of fuselage frame assemblies (2).

2. The simulated fuselage tooling for wire harness laying process verification according to claim 1 is characterized in that: The floor assembly (1) comprises: A base frame (11), a plurality of base plates (12) being fixedly arranged on the base frame (11), and the plurality of base plates (12) being spliced ​​together to form the surface of the floor assembly (1); A plurality of universal wheels (13) are arranged at the bottom of the base frame (11).

3. The simulated fuselage tooling for wire harness laying process verification according to claim 2 is characterized in that: The universal wheel (13) comprises a wheel body and a buckle, and the buckle can limit the rotation of the wheel body.

4. The simulated fuselage tooling for wire harness laying process verification according to claim 2 is characterized in that: The floor assembly (1) further comprises: A plurality of adjustable feet (14) are arranged at the bottom of the base frame (11), and the height of the adjustable feet (14) is adjustable.

5. The simulated fuselage tooling for wire harness laying process verification according to claim 1 is characterized in that: The fuselage frame assembly (2) comprises: A plurality of segmented frames (21), wherein the segmented frames (21) include a web (211) and edge strips (212) arranged around the web (211), and portions of the edge strips (212) of two adjacent segmented frames (21) are directly opposite; The locking piece is used for fixedly connecting two adjacent segment frames (21).

6. The simulated fuselage tooling for wire harness laying process verification according to claim 5 is characterized in that: A plurality of reinforcing ribs (22) are arranged in the segment frame (21), and the plurality of reinforcing ribs (22) are arranged at intervals along the length direction of the segment frame (21).

7. The simulated fuselage tooling for wire harness laying process verification according to claim 5 is characterized in that: A plurality of slots (23) are provided on one side of the fuselage frame assembly (2), the plurality of slots (23) are arranged at intervals along the length direction of the fuselage frame assembly (2), and the plurality of fuselage long stringers (3) are correspondingly mounted in the plurality of slots (23).

8. The simulated fuselage tooling for wire harness laying process verification according to any one of claims 1 to 7, characterized in that: The simulated fuselage tooling also includes: The fuselage skin (4) is covered and fixed on the plurality of fuselage frame components (2), and the fuselage skin (4) is an arc-shaped structure.

9. The simulated fuselage tooling for wire harness laying process verification according to any one of claims 1 to 7, characterized in that: The simulated fuselage tooling also includes: A plurality of support components (6), one end of each support component (6) is fixed to the floor component (1), and the other end of each support component (6) is fixed to the fuselage frame component (2).

10. The simulated fuselage tooling for wire harness laying process verification according to any one of claims 1 to 7, characterized in that: An entrance (7) is provided on the side of the simulated fuselage tooling.

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