Curved surface compensation mounting clamp for aircraft fixture

Abstract

The utility model discloses a curved surface compensation mounting fixture for an aircraft fixture, which relates to the technical field of aircraft manufacturing, and comprises a bottom plate, the left end and the right end of the top of the bottom plate are fixedly connected with clamping components, the top of the bottom plate is fixedly connected with a plurality of groups of first hydraulic cylinders, and the telescopic ends of the first hydraulic cylinders are rotatably provided with rotating frames; a first rotating shaft is movably connected to the surface of the rotating frame, an adjusting block is fixedly connected to the inner side of the first rotating shaft, a connecting plate is fixedly connected to the top of the adjusting block, a second hydraulic cylinder is fixedly connected to the middle end of the top of the connecting plate, and an inner supporting block is fixedly connected to the telescopic end of the second hydraulic cylinder; a plurality of annularly-distributed supporting columns are fixedly connected to the outer side of the top of the connecting plate. The multi-degree-of-freedom adjusting device can be adjusted in a multi-degree-of-freedom mode, corresponding adjustment of the position and the posture of the aircraft fixture is achieved through stretching and retracting of the first hydraulic cylinder, horizontal rotation of the rotating frame and free deflection of the adjusting block, and the aircraft fixture can be rapidly supported.

Description

Technical Field

[0001] This utility model relates to the field of aircraft manufacturing technology, specifically to a curved surface compensation mounting fixture for aircraft jigs. Background Technology

[0002] Aircraft jigs are key process equipment used to position and fix aircraft components in the aircraft manufacturing process. The accuracy and stability of the mounting fixtures directly affect the assembly quality of aircraft components. During aircraft assembly, jigs are needed to fix the corresponding mounting panels. Due to the special structure and complex shape of aircraft jigs, they generally have high-precision, irregular, and complex curved surfaces with extremely high surface quality requirements. However, existing jigs cannot effectively support aircraft jigs with different curvatures, thus reducing the support effect on the aircraft jigs. Furthermore, they lack shock absorption mechanisms, which prevents the weakening and buffering of vibrations generated during subsequent processing. In severe cases, this can cause the aircraft jigs to shift, affecting the final processing quality. Therefore, we propose a curved surface compensation mounting jig for aircraft jigs. Utility Model Content

[0003] The purpose of this invention is to provide a curved surface compensation mounting fixture for aircraft jigs to solve the problems mentioned in the background art.

[0004] To achieve the above objectives, this utility model provides the following technical solution: a curved surface compensation mounting fixture for an aircraft frame, comprising a base plate, with clamping assemblies fixedly connected to both the left and right ends of the top of the base plate, multiple sets of first hydraulic cylinders fixedly connected to the top of the base plate, and a rotating frame rotatably mounted on the telescopic end of each first hydraulic cylinder, a first rotating shaft movably connected to the surface of the rotating frame, an adjusting block fixedly connected to the inner side of the first rotating shaft, and a connecting plate fixedly connected to the top of the adjusting block, a second hydraulic cylinder fixedly connected to the middle of the top of the connecting plate, and an inner support block fixedly connected to the telescopic end of the second hydraulic cylinder, multiple annularly distributed support columns fixedly connected to the outer side of the top of the connecting plate, and an arc-shaped rod movably connected to the top of each support column via the second rotating shaft, a magnetorheological damper corresponding to the arc-shaped rod fixedly connected to the outer side of the bottom of the connecting plate, and a sleeve fixedly connected to the telescopic end of the magnetorheological damper, the sleeve being movably connected to the outer surface of the second rotating shaft.

[0005] Preferably, a spring rod is fixedly connected to the outer side of the first rotating shaft on the surface of the adjusting block, and a weight is fixedly connected to the outer side of the spring rod.

[0006] Preferably, the top of the inner support block and the arc-shaped rod are both arc-shaped structures, the two ends of the arc-shaped rod are hemispherical structures, the entire surface of the arc-shaped rod is smooth, each two adjacent arc-shaped rods are connected by an elastic band, and the outer surfaces of the arc-shaped rod and the inner support block are covered with a fluorocarbon rubber layer.

[0007] Preferably, the top of the support column has two inclined surfaces, and a reserved groove is provided on the inclined surface of the support column. A spring is fixedly connected to the bottom of the cavity of the reserved groove, and the top of the spring is fixedly connected to the bottom of the arc-shaped rod.

[0008] Preferably, auxiliary support plates are fixedly connected to both sides of the support column, and the bottom of the auxiliary support plates is fixedly connected to the top of the connecting plate.

[0009] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0010] This utility model allows for multi-degree-of-freedom adjustment: through the extension and retraction of the first hydraulic cylinder, the horizontal rotation of the rotating frame, and the free deflection of the adjusting block, corresponding adjustments to the position and attitude of the aircraft frame are achieved, enabling rapid support for the aircraft frame.

[0011] Local fine fit: Through the circular distribution of arc-shaped rods that can swing independently around the second pivot, and with the cooperation of springs and reserved grooves, a flexible micro-support structure is formed. When the second hydraulic cylinder drives the inner support block to rise and contact the bottom of the aircraft frame, each arc-shaped rod can adaptively swing at different angles according to the local curvature difference of the aircraft frame surface, so that the support surface changes from "point and line contact" to "surface contact", realizing high-precision and stress-free fit of curved surfaces;

[0012] Multiple damping combinations improve processing results: the magnetorheological damper, sleeve, and second rotating shaft form the first damping mechanism, while the elastic rod and weight form the second damping mechanism. The magnetorheological damper changes in advance according to the detection signal to complete surface compensation and vibration compensation, and the elastic rod and weight alleviate vibration after vibration to achieve compensation. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the structure of this utility model;

[0014] Figure 2 This is a schematic diagram of the structure of this utility model after removing the clamping components;

[0015] Figure 3 This utility model Figure 2 Enlarged structural diagram at point A in the middle.

[0016] In the figure: base plate 1, first hydraulic cylinder 2, second hydraulic cylinder 3, inner support block 4, arc rod 5, connecting plate 6, rotating frame 7, elastic band 8, elastic rod 9, weight 10, adjusting block 11, magnetorheological damper 12, spring 13, reserved groove 14, auxiliary support plate 15, support column 16, sleeve 17, second rotating shaft 18, first rotating shaft 19, clamping assembly 20. Detailed Implementation

[0017] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0018] Please see Figures 1-3 A curved surface compensation mounting fixture for an aircraft frame includes a base plate 1. Clamping assemblies 20 are fixedly connected to both the left and right ends of the top of the base plate 1. Multiple sets of first hydraulic cylinders 2 are fixedly connected to the top of the base plate 1, and a rotating frame 7 is rotatably mounted on the telescopic end of the first hydraulic cylinder 2. A first rotating shaft 19 is movably connected to the surface of the rotating frame 7. An adjusting block 11 is fixedly connected to the inner side of the first rotating shaft 19, and a connecting plate 6 is fixedly connected to the top of the adjusting block 11. A second hydraulic cylinder 3 is fixedly connected to the middle of the top of the connecting plate 6, and an inner support block 4 is fixedly connected to the telescopic end of the second hydraulic cylinder 3. Multiple annularly distributed support columns 16 are fixedly connected to the outer side of the top of the connecting plate 6, and an arc-shaped rod 5 is movably connected to the top of the support column 16 through a second rotating shaft 18. A magnetorheological damper 12 corresponding to the arc-shaped rod 5 is fixedly connected to the outer side of the bottom of the connecting plate 6. A sleeve 17 is fixedly connected to the telescopic end of the magnetorheological damper 12, and the sleeve 17 is movably connected to the outer surface of the second rotating shaft 18.

[0019] The clamping assembly 20 includes a vertical plate with two vertical slides on the inner side of the vertical plate. An adjustable clamping structure is provided on the slides. The clamping structure is used to clamp and fix the end of the aircraft frame. It can move along the slides and can deflect. It is suitable for clamping curved workpieces. The size of the clamping structure can be changed according to different needs.

[0020] The first hydraulic cylinder 2 is provided with at least three sets: left, center, and right, and each set has at least two cylinders to ensure effective support for the aircraft frame.

[0021] The rotating frame 7 can be operated manually to rotate, or a motor can be installed inside the output end of the first hydraulic cylinder 2. The rotating frame 7 is connected to the output shaft of the motor, and the rotation of the rotating frame 7 can be controlled by the motor.

[0022] The aircraft frame is placed on top of the arc-shaped rod 5, and strain gauges or vibration sensors are installed at the support. The operation of each first hydraulic cylinder 2 is controlled to adjust the height, which drives the corresponding arc-shaped rod 5 to rise and fall. At the same time, the rotating frame 7 rotates and the adjusting block 11 deflects, so that the arc-shaped rod 5 fits against the lower surface of the aircraft frame.

[0023] Then, control the extension and retraction of the second hydraulic cylinder 3 to make the inner support block 4 fit against the bottom of the aircraft frame. The height of the inner support block 4 can be adjusted. It can be raised for concave curved surfaces to provide auxiliary support, and lowered for convex curved surfaces to provide auxiliary support.

[0024] Once the device has positioned and supported the aircraft frame, the clamping structure on the upright plate is adjusted to clamp and fix the ends of the aircraft frame, thus completing the installation of the aircraft frame.

[0025] Both the magnetorheological damper 12 and the detection equipment are electrically connected to the processor. After the signal detected by the detection equipment such as strain gauges or vibration sensors is transmitted to the processor, the processor controls the magnetorheological damper 12 to adjust the current according to different signal conditions, thereby making the magnetorheological fluid reach different viscosities, and achieving different damping effects on the arc rod 5 with the cooperation of the second rotating shaft 18 and the sleeve 17.

[0026] The first rotating shaft 19 on the surface of the adjusting block 11 has a spring rod 9 fixedly connected to its outer side, and a weight 10 is fixedly connected to the outer side of the spring rod 9.

[0027] The elastic rod 9 and the weight 10 form the second shock absorption mechanism. After being vibrated, the vibration force is released by swinging, and the vibration is relieved and compensated after it occurs.

[0028] The tops of the inner support block 4 and the arc-shaped rod 5 are both arc-shaped structures, and the two ends of the arc-shaped rod 5 are hemispherical structures. The entire surface of the arc-shaped rod 5 is smooth. Each pair of adjacent arc-shaped rods 5 is connected by an elastic band 8, and the outer surfaces of the arc-shaped rod 5 and the inner support block 4 are covered with a layer of fluorocarbon rubber.

[0029] The elastic band 8 can restore the tilted arc rod 5 to a horizontal state after the aircraft frame is removed, and work together to make the support force distribution more even.

[0030] The fluorocarbon rubber layer provides a certain degree of cushioning and increases friction, improving the support effect. Together with the support structure, it prevents the aircraft frame from shifting due to vibration.

[0031] The top of the support column 16 has two sloping sides. A reserved groove 14 is provided on the sloping side of the support column 16. A spring 13 is fixedly connected to the bottom of the cavity of the reserved groove 14, and the top of the spring 13 is fixedly connected to the bottom of the arc rod 5.

[0032] The deflection of the arc rod 5 on the support column 16 is mainly related to the aircraft frame. After the aircraft frame is placed on the arc rod 5, the shape of the aircraft frame will cause the arc rod 5 to deflect freely along the inclined surface of the support column 16, so that the arc rod 5, which is distributed in a ring, can swing at different angles adaptively according to the local curvature difference of the aircraft frame surface. The reset of the arc rod 5 is achieved by the cooperation of the elastic band 8 and the spring 13, and the spring 13 can also play the role of buffering vibration.

[0033] Auxiliary support plates 15 are fixedly connected to both sides of the support column 16, and the bottom of the auxiliary support plates 15 is fixedly connected to the top of the connecting plate 6.

[0034] The auxiliary support plate 15 can improve the overall strength of the support column 16, thereby further improving the support effect on the aircraft frame.

[0035] The operational process for this application is as follows:

[0036] A. Place the aircraft frame on top of the arc rod 5, and install strain gauges or vibration sensors at the support. Control the extension and retraction of the first hydraulic cylinder 2 to drive the corresponding arc rod 5 to rise and fall. Adjust the horizontal angle of the rotating frame 7 to drive the corresponding arc rod 5 to rotate horizontally. With the cooperation of the adjusting block 11, the top of the arc rod 5 is initially attached to the bottom of the aircraft frame. After the aircraft frame is placed on the arc rod 5, the shape of the aircraft frame will drive the arc rod 5 to freely deflect along the inclined plane of the support column 16, so that the arc rod 5, which is distributed in a ring, can adaptively swing at different angles according to the local curvature difference of the aircraft frame surface.

[0037] B. Control the extension and retraction of the second hydraulic cylinder 3 to make the inner support block 4 fit against the bottom of the aircraft frame. After the device has supported and positioned the aircraft frame, adjust the clamping structure on the upright plate to clamp and fix the end of the aircraft frame to complete the installation of the aircraft frame.

[0038] C. During the processing, detection devices such as strain gauges or vibration sensors can detect the corresponding deformation or vibration signals and transmit the signals to the processor. The processor analyzes the signal content to obtain the trend of deformation or vibration, and controls the magnetorheological damper 12 to adjust the magnitude of the internal coil current for different situations, thereby making the magnetorheological fluid reach different viscosities. At the same time, with the cooperation of the second rotating shaft 18 and the sleeve 17, different damping effects are achieved on the arc rod 5 to realize advance compensation and reduce the impact of subsequent vibration. In addition, the second damping mechanism composed of the elastic rod 9 and the weight 10 alleviates the vibration and achieves compensation after the vibration occurs.

[0039] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A curved surface compensation mounting fixture for aircraft jigs, comprising a base plate (1), characterized in that: Clamping assemblies (20) are fixedly connected to both the left and right ends of the top of the base plate (1). Multiple sets of first hydraulic cylinders (2) are fixedly connected to the top of the base plate (1), and a rotating frame (7) is rotatably mounted on the telescopic end of the first hydraulic cylinder (2). A first rotating shaft (19) is movably connected to the surface of the rotating frame (7). An adjusting block (11) is fixedly connected to the inner side of the first rotating shaft (19), and a connecting plate (6) is fixedly connected to the top of the adjusting block (11). A second hydraulic cylinder (3) is fixedly connected to the middle end of the top of the connecting plate (6), and the second The telescopic end of the hydraulic cylinder (3) is fixedly connected to an inner support block (4). Multiple ring-shaped support columns (16) are fixedly connected to the outer side of the top of the connecting plate (6). The top of the support column (16) is movably connected to an arc rod (5) through a second rotating shaft (18). The outer side of the bottom of the connecting plate (6) is fixedly connected to a magnetorheological damper (12) corresponding to the arc rod (5). The telescopic end of the magnetorheological damper (12) is fixedly connected to a sleeve (17), and the sleeve (17) is movably connected to the outer surface of the second rotating shaft (18).

2. The curved surface compensation mounting fixture for aircraft frame according to claim 1, characterized in that: A spring rod (9) is fixedly connected to the outer side of the first rotating shaft (19), and a weight (10) is fixedly connected to the outer side of the spring rod (9).

3. The curved surface compensation mounting fixture for aircraft frame according to claim 1, characterized in that: The top of the inner support block (4) and the arc rod (5) are both arc-shaped structures, the two ends of the arc rod (5) are hemispherical structures, the entire surface of the arc rod (5) is smooth, and each two adjacent arc rods (5) are connected by an elastic band (8), and the outer surfaces of the arc rod (5) and the inner support block (4) are covered with a fluorocarbon rubber layer.

4. A curved surface compensation mounting fixture for an aircraft frame according to claim 1, characterized in that: The top of the support column (16) has two inclined surfaces. A reserved groove (14) is provided on the inclined surface of the support column (16). A spring (13) is fixedly connected to the bottom of the cavity of the reserved groove (14), and the top of the spring (13) is fixedly connected to the bottom of the arc rod (5).

5. A curved surface compensation mounting fixture for an aircraft frame according to claim 1, characterized in that: Both sides of the support column (16) are fixedly connected to auxiliary support plates (15), and the bottom of the auxiliary support plates (15) is fixedly connected to the top of the connecting plate (6).

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