An aircraft fuselage skin forming apparatus and method of use thereof

Abstract

An aircraft fuselage skin forming device and its method of use, belonging to the field of skin forming equipment. It includes a support frame, a lower mold, and an upper mold; the support frame includes a base plate, support rods, and a top plate; the upper end of the base plate is fixedly connected to the support rods, and the top end of the support rods is fixedly connected to the top plate; the lower end of the top plate is fixedly connected to a hydraulic cylinder on the upper mold, and the lower end of the hydraulic cylinder is fixedly connected to a pressure block; the lower mold is rotatably connected between two support rods via a rotating shaft, and a motor is fixedly connected to the outside of the support rods via a support frame, with the motor's output shaft passing through the support rods and fixedly connected to the corresponding rotating shaft. This invention not only allows for the rotation of the outer frame, facilitating demolding and improving processing efficiency, but also limits the rotation angle of the outer frame, preventing the rotation angle from exceeding or falling below 180°, which could lead to processing failure.

Description

Technical Field

[0001] This invention relates to an aircraft fuselage skin forming equipment and its usage method, belonging to the field of skin forming equipment. Background Technology

[0002] Simple skins are commonly used in the cross-sectional sections of aircraft such as wings and fuselages. These parts have curvature in only one direction. The deformation is a simple bending, and they are generally formed using press bending and roll bending methods. The press bending method currently used usually employs upper and lower molds, placing the skin in the middle, and then applying pressure to shape it. However, after forming, the skin is often pressed into the lower mold, making demolding difficult. Therefore, it is necessary to improve this method. Summary of the Invention

[0003] The purpose of this invention is to solve the above-mentioned problems in the background art by providing an aircraft fuselage skin forming device and its usage method.

[0004] The present invention achieves the above objectives by adopting the following technical solution:

[0005] An aircraft fuselage skin forming device includes a support frame, a lower mold, and an upper mold. The support frame includes a base plate, a support rod, and a top plate. The upper end of the base plate is fixedly connected to the support rod, and the top end of the support rod is fixedly connected to the top plate. The lower end of the top plate is fixedly connected to a hydraulic cylinder on the upper mold, and the lower end of the hydraulic cylinder is fixedly connected to a pressure block. The lower mold is rotatably connected between two support rods via a rotating shaft, and a motor is fixedly connected to the outside of the support rod via a motor bracket. The output shaft of the motor passes through the support rod and is fixedly connected to the corresponding rotating shaft.

[0006] A method of using an aircraft fuselage skin forming equipment, the method comprising the following steps:

[0007] Step 1: Place the skin inside the outer frame from the top;

[0008] Step 2: Start the hydraulic cylinder to press the skin to the preset curvature with the pressure block and multiple sliders I and II, then start the hydraulic cylinder in the reverse direction;

[0009] Step 3: After the pressure block detaches from the outer frame, start the motor. The motor will drive the outer frame to rotate 180°.

[0010] Step 4: Slider II moves downward under the action of gravity, which in turn moves slider I downward, causing the stamped skin to detach from the outer frame;

[0011] Step 5: Repeat steps 1 through 4.

[0012] Compared with the prior art, the beneficial effects of the present invention are: the present invention can not only rotate the outer frame to facilitate demolding and improve processing efficiency, but also limit the rotation angle of the outer frame to avoid the outer frame rotation angle being greater than or less than 180°, which would prevent normal processing. Attached Figure Description

[0013] Figure 1 This is a front view of an aircraft fuselage skin forming device according to the present invention;

[0014] Figure 2 This is a front view of a bracket for an aircraft fuselage skin forming device according to the present invention;

[0015] Figure 3 This is a front view of the lower mold of an aircraft fuselage skin forming device according to the present invention;

[0016] Figure 4 This is a side view of the rotating block of an aircraft fuselage skin forming device according to the present invention;

[0017] Figure 5 This is a schematic diagram of the structure of the upper mold of an aircraft fuselage skin forming device according to the present invention;

[0018] Figure 6 This is a schematic diagram of the structure of a limiting device for an aircraft fuselage skin forming equipment according to the present invention. Detailed Implementation

[0019] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the invention, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0020] Specific implementation method one: as follows Figure 1-6 As shown, this embodiment describes an aircraft fuselage skin forming device, including a support 1, a lower mold 2, and an upper mold 3; the support 1 includes a base plate 11, a support rod 12, and a top plate 14; the upper end of the base plate 11 is fixedly connected to the support rod 12, and the top end of the support rod 12 is fixedly connected to the top plate 14; the lower end of the top plate 14 is fixedly connected to a hydraulic cylinder 31 on the upper mold 3, and the lower end of the hydraulic cylinder 31 is fixedly connected to a pressure block 32; the lower mold 2 is rotatably connected between two support rods 12 via a rotating shaft 23, and a motor 21 is fixedly connected to the outside of the support rod 12 via a motor bracket 22, and the output shaft of the motor 21 passes through the support rod 12 and is fixedly connected to the corresponding rotating shaft 23.

[0021] The lower mold 2 also includes an outer frame 24, multiple sliders I 27, multiple limiting blocks 26, and slider II 210; the side of the outer frame 24 is fixedly connected to the rotating shaft 23; the multiple sliders I 27 and slider II 210 are vertically arranged inside the outer frame 24, and the multiple sliders I 27 are symmetrically arranged on both sides of slider II 210. The inner wall of the outer frame 24 and the side of sliders I 27 are provided with limiting grooves 25. The side of slider II 210 and multiple sliders I 27 are fixedly connected with limiting blocks 26, and each limiting block 26 slides with the corresponding limiting groove 25; the upper and lower ends of the multiple sliders I 27 and slider II 210 are provided with arc surfaces 28.

[0022] The inner walls of slider II 210, slider I 27 and outer frame 24 are all smooth, and the weight of slider II 210 is greater than the weight of slider I 27.

[0023] When the plurality of limiting blocks 26 move to the lowest end of the corresponding limiting groove 25, the upper arc surfaces 28 of the plurality of sliders I 27 and slider II 210 form a concave surface that is downwardly recessed and equal to the preset curvature of the skin.

[0024] It also includes a limiting device 4; the limiting device 4 includes a housing 41, a movable block 42, a T-shaped slider 43, a spring 45, a connecting rod 46, and a round rod 47; the housing 41 is fixedly connected to the side of the support rod 12, and the upper end of the inner wall of the housing 41 is provided with a T-shaped groove 44; the upper end of the movable block 42 is fixedly connected to a T-shaped slider 43 that slides in cooperation with the T-shaped groove 44; one end of the connecting rod 46 is fixedly connected to the side of the T-shaped slider 43, and the other end of the connecting rod 46 passes through the housing 41 and protrudes from the outer end of the housing 41; the round rod 47 is vertically and fixedly connected to the side of the end of the connecting rod 46 that protrudes from the outer end of the housing 41; a spring 45 is fixedly connected between the T-shaped slider 43 and the inner wall of the housing 41.

[0025] The rotating shaft 23, which is close to the outer shell 41, passes through the support rod 12 and is located inside the outer shell 41. A rotating block 29 is fixedly connected to one end of the rotating shaft 23 inside the outer shell 41.

[0026] The rotating block 29 is in the shape of a quadrangular frustum, and the lower end face of the movable block 42 is set as an inclined surface, and the inclined surface of the lower end of the movable block 42 has the same inclination angle as the inclined surface of the side of the rotating block 29.

[0027] The support rod 12 connected to the outer shell 41 is also provided with a sliding groove 13; the side of the pressure block 32 is fixedly connected with a crossbar 33 that slides in cooperation with the sliding groove 13; the lower end of the crossbar 33 is fixedly connected with two limiting rods 34; each limiting rod 34 is provided with an inclined groove 35 and a vertical groove 36 communicating with the inclined groove 35; the connecting rod 46 is located between the two limiting rods 34, and the round rod 47 slides in cooperation with the inclined groove 35 and the vertical groove 36.

[0028] A method of using an aircraft fuselage skin forming equipment, the method comprising the following steps:

[0029] Step 1: Place the skin inside the outer frame 24 from the top of the outer frame 24;

[0030] Step 2: Start the hydraulic cylinder 31 to make the pressure block 32 and multiple sliders I 27 and II 210 press the skin to the preset curvature, and then start the hydraulic cylinder 31 in the reverse direction;

[0031] Step 3: After the pressure block 32 is separated from the outer frame 24, the motor 21 is started, and the motor 21 drives the outer frame 24 to rotate 180°;

[0032] Step 4: Slider II 210 moves downward under the action of gravity, which drives slider I 27 to move downward, causing the stamped skin to detach from the outer frame 24;

[0033] Step 5: Repeat steps 1 through 4.

[0034] The working principle of this invention is as follows: When using this device, the skin is placed from the upper end of the outer frame 24 at the upper ends of slider I 27 and slider II 210 inside the outer frame 24;

[0035] Start the hydraulic cylinder 31 to make the pressure block 32 and multiple sliders I 27 and II 210 press the skin to the preset curvature, and then start the hydraulic cylinder 31 in the opposite direction;

[0036] After the hydraulic cylinder 31 drives the pressure block 32 to detach from the outer frame 24, the motor 21 is started. The motor 21 drives the rotating shaft 23 to rotate, which in turn drives the outer frame 24 to rotate 180°. After rotating 180°, the skin is located at the lower end of slider I 27 and slider II 210. Slider II 210 and slider I 27 move downward under the action of gravity. At the same time, the hydraulic cylinder 31 is started again, driving the pressure block 32 to move downward. After the pressure block 32 moves into the outer frame 24, it pushes slider I 27 and slider II 210 downward (accelerating the downward movement of slider I 27 and slider II 210). Under the action of gravity and the thrust of the pressure block 32, the limiting block 26 slides to the other end in the limiting groove 25. It also causes the upper end of slider I 27 and slider II 210 to recombine into the preset arc required for the skin. Then the pressure block 32 is moved back to its original position, and the lowest point of the lower arc surface 28 of slider I 27 and slider II 210 is on the same horizontal plane (e.g., Figure 3As shown in the state, since the lower ends of slider I 27 and slider II 210 are both curved surfaces, and the formed skin is pushed out of the outer frame 24, the contact area between the lowest point of the lower end of slider I 27 and slider II 210 and the skin is reduced. Under the action of the skin's gravity, the skin automatically detaches from slider I 27 and slider II 210. At the same time, after the pressure block 32 detaches from the outer frame 24, the unprocessed skin can be placed again on the upper end of the outer frame 24 for processing, which greatly shortens the time required for the formed skin to be demolded and improves processing efficiency.

[0037] Each time the pressure block 32 moves downward, it drives the limiting rod 34 downward via the crossbar 33, causing the round rod 47 to move from the vertical groove 36 into the inclined groove 35. The lower end of the inclined groove 35 is inclined towards the outer shell 41. Therefore, when the limiting rod 34 moves downward, the round rod 47 moves along the inclined groove 35 away from the outer shell 41, thereby driving the connecting rod 46 and the movable block 42 to move. This causes the inclined surface at the lower end of the movable block 42 to disengage from the inclined surface on the side of the rotating block 29. As the pressure block 32 moves downward, the limiting rod 32 moves downward. 2. After the stamping is completed, the pressure block 32 moves upward and separates from the outer frame 24. Then, the motor 21 is started to drive the outer frame 24 to rotate. When the round rod 47 moves to the middle position of the inclined groove 35, the motor 21 drives the outer frame 24 to complete a 180° rotation. As the pressure block 32 gradually moves upward, the round rod 47 drives the connecting rod 46 and the movable block 42 to move in the direction of the outer frame 24. The inclined surface at the lower end of the movable block 42 is pressed against the inclined surface of the side of the rotating block 29, which is shaped like a truncated pyramid. The two are in close contact. Therefore, the movable block 42 restricts the rotation of the rotating block 29 by means of the inclined surface, thereby restricting the rotation of the outer frame 24. At the same time, the inclined surface at the lower end of the movable block 42 ensures that the outer frame 24 is in a horizontal state, preventing the outer frame 24 from being tilted if the rotation angle is greater than or less than 180° after rotation. This would cause the pressure block 32 to press against the tilted outer frame 24 when it moves downward, resulting in damage to the parts. Meanwhile, when the movable block 42 and the inclined surface of the rotating block 29 are in contact, the round rod 47 is located in the vertical groove 36. If the rotation angle of the outer frame 24 is too large or too small, the rotating block 29 cannot fully fit with the movable block 42, causing the movable block 42 to be unable to move to its original position. Consequently, the connecting rod 46 will prevent the round rod 47 from moving to the same vertical plane as the vertical groove 36, preventing the round rod 47 from moving into the vertical groove 36. When the pressure block 32 moves upward, it will be blocked by the round rod 47 and the inclined groove 35, indicating that the outer frame 24 has not rotated to the working position, further ensuring the safety of the operation.

Claims

1. An aircraft fuselage skin forming equipment, characterized in that: The system includes a support (1), a lower mold (2), and an upper mold (3); the support (1) includes a base plate (11), a support rod (12), and a top plate (14); the upper end of the base plate (11) is fixedly connected to the support rod (12), and the top end of the support rod (12) is fixedly connected to the top plate (14); the lower end of the top plate (14) is fixedly connected to the hydraulic cylinder (31) on the upper mold (3), and the lower end of the hydraulic cylinder (31) is fixedly connected to the pressure block (32); the lower mold (2) is rotatably connected between the two support rods (12) through a rotating shaft (23), and a motor (21) is fixedly connected to the outside of the support rod (12) through a motor bracket (22), and the output shaft of the motor (21) passes through the support rod (12) and is fixedly connected to the corresponding rotating shaft (23); The lower mold (2) also includes an outer frame (24), multiple sliders I (27), multiple limiting blocks (26), and slider II (210); the side of the outer frame (24) is fixedly connected to the rotating shaft (23); the multiple sliders I (27) and slider II (210) are vertically arranged inside the outer frame (24), and the multiple sliders I (27) are symmetrically arranged on both sides of slider II (210). The inner wall of the outer frame (24) and the side of sliders I (27) are provided with limiting grooves (25). The side of slider II (210) and multiple sliders I (27) are fixedly connected with limiting blocks (26), and each limiting block (26) slides with the corresponding limiting groove (25); the upper and lower ends of the multiple sliders I (27) and slider II (210) are provided with arc surfaces (28). When the multiple limiting blocks (26) move to the lowest end of the corresponding limiting groove (25), the upper arc surfaces (28) of the multiple sliders I (27) and II (210) form a concave surface that is recessed downward and equal to the preset curvature of the skin.

2. The aircraft fuselage skin forming equipment according to claim 1, characterized in that: The inner walls of slider II (210), slider I (27) and outer frame (24) are all smooth, and the weight of slider II (210) is greater than the weight of slider I (27).

3. The aircraft fuselage skin forming equipment according to claim 2, characterized in that: It also includes a limiting device (4); the limiting device (4) includes a housing (41), a movable block (42), a T-shaped slider (43), a spring (45), a connecting rod (46), and a round rod (47); the housing (41) is fixedly connected to the side of the support rod (12), and the upper end of the inner wall of the housing (41) is provided with a T-shaped groove (44); the upper end of the movable block (42) is fixedly connected to a T-shaped slider (43) that slides in cooperation with the T-shaped groove (44); one end of the connecting rod (46) is fixedly connected to the side of the T-shaped slider (43), and the other end of the connecting rod (46) passes through the housing (41) and protrudes from the outer end of the housing (41); the round rod (47) is vertical and fixedly connected to the side of the connecting rod (46) protruding from the outer end of the housing (41); a spring (45) is fixedly connected between the T-shaped slider (43) and the inner wall of the housing (41).

4. The aircraft fuselage skin forming equipment according to claim 3, characterized in that: A pivot (23) near the outer shell (41) passes through the support rod (12) and is located inside the outer shell (41), and a rotating block (29) is fixedly connected to one end of the pivot (23) inside the outer shell (41).

5. The aircraft fuselage skin forming equipment according to claim 4, characterized in that: The rotating block (29) is a truncated quadrangular shape, and the lower end face of the movable block (42) is set as an inclined surface. The inclined surface at the lower end of the movable block (42) has the same inclination angle as the inclined surface on the side of the rotating block (29).

6. The aircraft fuselage skin forming equipment according to claim 5, characterized in that: The support rod (12) connected to the outer shell (41) is also provided with a sliding groove (13); the side of the pressure block (32) is fixedly connected with a crossbar (33) that slides with the sliding groove (13); the lower end of the crossbar (33) is fixedly connected with two limiting rods (34); each limiting rod (34) is provided with an inclined groove (35) and a vertical groove (36) that communicates with the inclined groove (35); the connecting rod (46) is located between the two limiting rods (34), and the round rod (47) slides with the inclined groove (35) and the vertical groove (36).

7. The method of using the aircraft fuselage skin forming equipment according to claim 6, characterized in that: The method of use includes the following steps: Step 1: Place the skin inside the outer frame (24) from the top of the outer frame (24); Step 2: Start the hydraulic cylinder (31) to make the pressure block (32) and multiple sliders I (27) and II (210) press the skin to the preset arc, and then start the hydraulic cylinder (31) in the opposite direction. Step 3: After the pressure block (32) is separated from the outer frame (24), start the motor (21). The motor (21) drives the outer frame (24) to rotate 180°. Step 4: Slider II (210) moves downward under the action of gravity, which drives slider I (27) to move downward, so that the stamped skin is separated from the outer frame (24). Step 5: Repeat steps 1 through 4.

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