A large aircraft wallboard pre-assembly tool capable of realizing a metal frame automatic deburring mechanism

Abstract

A large aircraft panel pre-assembly tool capable of realizing automatic deburring of metal frame belongs to the technical field of large aircraft panel assembly. Both ends of each skin support frame are connected to the fixed frame through a skin support frame connecting seat, each frame plate is connected to the corresponding skin support frame through an automatic lifting mechanism, and a panel skeleton frame is detachably installed on each frame plate. The utility model mainly is used for large aircraft panel pre-assembly, greatly improves panel frame assembly precision, avoids the process of repositioning after deburring of the frame and panel, avoids errors caused by repeated positioning. The utility model discloses a large aircraft panel pre-assembly tool capable of realizing automatic deburring of metal frame, when the panel and the frame are completed, the process of repositioning after deburring of the frame and the panel is not needed, one-stop assembly processing is realized, thereby the panel pre-assembly period is shortened, and the overall panel assembly efficiency is improved.

Description

Technical Field

[0001] This utility model belongs to the field of large aircraft panel assembly technology, specifically relating to a large aircraft panel pre-assembly fixture that can realize an automatic deburring mechanism for metal frames. Background Technology

[0002] In aircraft manufacturing, paneling, as a major structural component, is primarily composed of skin, internal frames, and frame reinforcements. During the assembly of large aircraft paneling, burr generation is a significant issue. Traditional deburring methods are inefficient, increase manual labor through repeated mounting, and introduce errors due to repetitive positioning. To address this problem in aircraft paneling assembly, an automatic frame lifting mechanism has been developed to remove burrs, greatly improving assembly efficiency and precision. Summary of the Invention

[0003] In order to solve the technical problem that traditional tooling cannot quickly remove burrs, this utility model provides an assembly tooling that can shorten the assembly cycle, improve the assembly quality, remove burrs and quickly and accurately reset the assembly.

[0004] The technical solution adopted by this utility model is: A pre-assembly fixture for large aircraft panels capable of automatically deburring metal frames includes multiple fixed frames, multiple skin support frames, multiple skin support frame connecting seats, multiple frame plates, multiple automatic lifting mechanisms, and multiple panel skeleton frames. The multiple skin support frames are arranged sequentially from front to back, and each skin support frame is connected to the fixed frames at both ends through skin support frame connecting seats. The skin support frames are used for internal positioning of the skin. Each frame plate is connected to the corresponding skin support frame through an automatic lifting mechanism, and a panel skeleton frame is detachably installed on each frame plate.

[0005] Furthermore, the main body of each of the fixed frames is made of Q235 square tubing, and a tabletop and a base plate are welded to the upper and lower ends of the square tubing, respectively.

[0006] Furthermore, each of the automatic lifting mechanisms includes an electric lifting screw, multiple guide rails, and multiple guide rail connecting plates; multiple guide rail connecting plates are installed on the surface of the frame plate, each guide rail connecting plate is slidably connected to the corresponding guide rail, the multiple guide rails are connected to the skin support frame, the housing of the electric lifting screw is installed on the surface of the skin support frame, and the nut of the electric lifting screw is connected to the surface of the frame plate.

[0007] Furthermore, each of the automatic lifting mechanisms also includes a buffer a, a buffer b, and two buffer supports; the buffer a and the buffer b are respectively connected to the frame plate through the two buffer supports, the buffer a and the buffer b are arranged opposite each other vertically, the buffer stop is connected to the skin support frame, and the buffer stop is arranged between the buffer a and the buffer b.

[0008] Furthermore, the automatic lifting mechanism also includes multiple distance sensors. Distance sensors are provided at corresponding positions of buffer a and buffer b, and the distance sensors are mounted on the frame plate.

[0009] Furthermore, the large aircraft panel pre-assembly fixture capable of realizing an automatic deburring mechanism for metal frames also includes a frame quick-insertion positioning pin and a quick-insertion pin fixing plate; the frame quick-insertion positioning pin is fixedly connected to the frame plate by screws and pins through the quick-insertion pin fixing plate.

[0010] Furthermore, the large aircraft panel pre-assembly fixture that enables the automatic deburring mechanism of the metal frame also includes multiple fixing clamps; the multiple fixing clamps are fixedly connected to the corresponding frame plates, and each frame plate is clamped and fixed to the panel frame frame by the multiple fixing clamps.

[0011] Compared with the prior art, the present invention has the following advantages: 1. This utility model is mainly used for the pre-assembly of large aircraft panels, which greatly improves the assembly accuracy of the panel frame, avoids the process of removing the frame and panel from the frame, deburring them, and then repositioning them, and avoids errors caused by repeated positioning.

[0012] 2. This utility model utilizes a large aircraft panel pre-assembly fixture with an automatic deburring mechanism for metal frames. Once the panel and frame holes are drilled, there is no need to remove the frame and panel from the rack for deburring and then reposition them. This achieves one-stop assembly, thereby shortening the panel pre-assembly cycle and improving the overall panel assembly efficiency. Attached Figure Description

[0013] Figure 1 This is an isometric drawing of this utility model; Figure 2 This is a schematic diagram of the skin support frame and frame plate structure of this utility model; Figure 3 This is a schematic diagram of the skin support frame structure of this utility model; Figure 4 This is a schematic diagram of the automatic lifting mechanism of this utility model; Figure 5 This is an isometric view of the automatic lifting mechanism of this utility model rising to its theoretical position; Figure 6 This is an isometric view of the automatic lifting mechanism of this utility model in the lowering state; The components include: 1. Fixed frame; 2. Skin support frame; 3. Skin support frame connecting seat; 4. Frame plate; 5. Frame quick-insertion positioning pin; 6. Quick-insertion pin fixing plate; 7. Fixing clamp; 8. Automatic lifting mechanism; 801. Distance sensor; 802. Electric lifting screw; 803. Guide rail; 804. Guide rail connecting plate; 805. Buffer a; 806. Buffer b; 807. Buffer support; 808. Buffer stop; 9. Wall panel skeleton frame. Detailed Implementation

[0014] To better understand the purpose, structure, and function of this utility model, a more detailed description of this utility model will be provided below with reference to the accompanying drawings.

[0015] like Figure 1 As shown, this utility model provides a large aircraft panel pre-assembly fixture capable of realizing an automatic deburring mechanism for metal frames. It includes multiple fixed frames 1, multiple skin support frames 2, multiple skin support frame connecting seats 3, multiple frame plates 4, multiple automatic lifting mechanisms 8, and multiple panel skeleton frames 9. The multiple skin support frames 2 are arranged sequentially from front to back. Both ends of each skin support frame 2 are connected to the fixed frame 1 through the skin support frame connecting seats 3. The skin support frames 2 are used for skin inner shape positioning. Each frame plate 4 is connected to the corresponding skin support frame 2 through an automatic lifting mechanism 8. Each frame plate 4 is detachably mounted with a panel skeleton frame 9.

[0016] like Figure 1 As shown, the main body of each fixed frame 1 is made of Q235 square tube, and a table and a base plate are welded to the upper and lower ends of the square tube respectively. The fixed frame 1 is used to support the overall structure of the tooling and the aircraft panel, and serves as the reference surface for the positioning structure of the aircraft panel.

[0017] After the fixed frame 1 is welded, the table surface of the fixed frame 1 is CNC machined.

[0018] like Figure 3 , Figure 4 As shown, each of the automatic lifting mechanisms 8 includes an electric lifting screw 802, multiple guide rails 803, and multiple guide rail connecting plates 804; multiple guide rail connecting plates 804 are installed on the plate surface of the frame plate 4, and each guide rail connecting plate 804 is slidably connected to the corresponding guide rail 803. The multiple guide rails 803 are connected to the skin support frame 2. The housing of the electric lifting screw 802 is installed on the plate surface of the skin support frame 2. The upper end of the screw of the electric lifting screw 802 is connected to the skin support frame 2 through a bearing. The nut of the electric lifting screw 802 is connected to the plate surface of the frame plate 4. The frame plate 4 can be controlled to rise and fall along the direction of the guide rail 803 by the electric lifting screw 802.

[0019] like Figure 3 , Figure 4As shown, each of the automatic lifting mechanisms 8 further includes a buffer a805, a buffer b806, and two buffer supports 807. The buffers a805 and b806 are respectively connected to the frame plate 4 via the two buffer supports 807 using screws. The buffers a805 and b806 are arranged vertically opposite each other. A buffer stop 808 is connected to the skin support frame 2 using screws and is positioned between the buffers a805 and b806. When the electric lifting screw 802 controls the frame plate 4 to rise or fall, the buffers a805 or b806 collide with the buffer stop 808, achieving a buffering effect and protecting the product.

[0020] like Figure 4 As shown, the automatic lifting mechanism 8 also includes multiple distance sensors 801. Distance sensors 801 are provided at corresponding positions of buffer a805 and buffer b806, and the distance sensors 801 are mounted on the frame plate 4.

[0021] The distance sensor 801 is used to monitor the relative position of the buffer stop 808 during the up-and-down movement.

[0022] like Figure 3 As shown, the frame quick-connect positioning pin 5 is fixedly connected to the frame plate 4 by screws and pins through the quick-connect pin fixing plate 6, and is used for positioning the frame process holes.

[0023] like Figure 2 , Figure 5 , Figure 6 As shown, multiple fixing clips 7 are fixedly connected to the corresponding frame plates 4 using screws and pins. Each frame plate 4 is clamped and fixed to the wall panel frame 9 by multiple fixing clips 7. The wall panel frame 9, the frame plates 4, and the wall panel frame 9 rise or fall simultaneously.

[0024] The fixing clamp 7 can be made using existing clamping components.

[0025] The electric lifting screw 802 controls the frame plate 4 to descend, assembling the wall panel frame 9 onto the frame plate 4; Each automatic lifting mechanism 8 can be individually controlled by a PLC for lifting, or all lifting mechanisms can be lifted simultaneously.

[0026] like Figure 5 As shown, the electric lifting screw 802 controls the frame plate 4 to descend, assembling the wall panel frame 9 onto the frame plate 4; then, the electric lifting screw 802 controls the frame plate 4 and the wall panel frame 9 installed on it to rise back to the theoretical installation position of the frame, and the fastener connection holes are made. like Figure 6 As shown, after the hole is made, the electric lifting screw 802 control frame plate 4 and the wall panel frame 9 installed on it descend simultaneously along the guide rail 803 to remove burrs and apply sealant. like Figure 5 As shown, the electric lifting screw 802 control frame plate 4 and the wall panel frame 9 mounted on it rise and reset to the theoretical installation position of the frame, and the fasteners are connected; further, the frame quick-connect positioning pin 5 is opened, the fixing clamp 7 is opened, the electric lifting screw 802 control frame plate 4 descends, and the wall panel frame 9 is removed from the frame. The aircraft wall panel assembly is completed.

[0027] This pre-assembly fixture can improve the assembly efficiency and accuracy of the panel, ensuring the demand for increased production capacity of aircraft panels. The automatic lifting mechanism 8 of this frame can realize the pre-assembly of large aircraft panels with deburred parts, shorten the aircraft panel manufacturing cycle, improve production efficiency, significantly reduce manufacturing costs, facilitate manual operation, and reduce labor costs.

[0028] It is understood that this utility model has been described through some embodiments, and those skilled in the art will recognize that various changes or equivalent substitutions can be made to these features and embodiments without departing from the spirit and scope of this utility model. Furthermore, under the teachings of this utility model, these features and embodiments can be modified to adapt to specific situations and materials without departing from the spirit and scope of this utility model. Therefore, this utility model is not limited to the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of this application are within the protection scope of this utility model.

Claims

1. A pre-assembly fixture for large aircraft panels capable of automatically deburring metal frames, characterized in that: It includes multiple fixed frames (1), multiple skin support frames (2), multiple skin support frame connecting seats (3), multiple frame plates (4), multiple automatic lifting mechanisms (8), and multiple wall panel skeleton frames (9); the multiple skin support frames (2) are arranged sequentially from front to back, and each skin support frame (2) is connected to the fixed frame (1) at both ends through the skin support frame connecting seats (3). The skin support frames (2) are used for skin inner shape positioning. Each frame plate (4) is connected to the corresponding skin support frame (2) through an automatic lifting mechanism (8). Each frame plate (4) is detachably installed with a wall panel skeleton frame (9).

2. The pre-assembly fixture for large aircraft panels capable of realizing an automatic deburring mechanism for metal frames according to claim 1, characterized in that: The main body of each fixed frame (1) is made of Q235 square tube, and the table and the base plate are welded to the upper and lower ends of the square tube respectively.

3. A large aircraft panel pre-assembly fixture capable of realizing an automatic deburring mechanism for metal frames according to claim 1, characterized in that: Each of the automatic lifting mechanisms (8) includes an electric lifting screw (802), multiple guide rails (803), and multiple guide rail connecting plates (804); multiple guide rail connecting plates (804) are installed on the plate surface of the frame plate (4), and each guide rail connecting plate (804) is slidably connected to the corresponding guide rail (803) up and down. The multiple guide rails (803) are connected to the skin support frame (2). The housing of the electric lifting screw (802) is installed on the plate surface of the skin support frame (2), and the nut of the electric lifting screw (802) is connected to the plate surface of the frame plate (4).

4. A large aircraft panel pre-assembly fixture capable of realizing an automatic deburring mechanism for metal frames according to claim 3, characterized in that: Each of the automatic lifting mechanisms (8) further includes a buffer a (805), a buffer b (806), and two buffer supports (807); the buffer a (805) and the buffer b (806) are respectively connected to the frame plate (4) through the two buffer supports (807), the buffer a (805) and the buffer b (806) are arranged opposite each other, the buffer stop (808) is connected to the skin support frame (2), and the buffer stop (808) is arranged between the buffer a (805) and the buffer b (806).

5. A large aircraft panel pre-assembly fixture capable of realizing an automatic deburring mechanism for metal frames according to claim 4, characterized in that: The automatic lifting mechanism (8) also includes multiple distance sensors (801). Distance sensors (801) are provided at corresponding positions of buffer a (805) and buffer b (806). The distance sensors (801) are mounted on the frame plate (4).

6. A pre-assembly fixture for large aircraft panels capable of automatically deburring metal frames according to claim 1, characterized in that: The large aircraft panel pre-assembly fixture that enables the automatic deburring mechanism of the metal frame also includes a frame quick-insertion positioning pin (5) and a quick-insertion pin fixing plate (6); the frame quick-insertion positioning pin (5) is fixedly connected to the frame plate (4) by screws and pins through the quick-insertion pin fixing plate (6).

7. A large aircraft panel pre-assembly fixture capable of realizing an automatic deburring mechanism for metal frames according to claim 1, characterized in that: The large aircraft panel pre-assembly fixture that enables the automatic deburring mechanism of the metal frame also includes multiple fixing clips (7); the multiple fixing clips (7) are fixedly connected to the corresponding frame plate (4), and each frame plate (4) is clamped and fixed to the panel frame frame (9) by multiple fixing clips (7).

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