Adjustable inclined support for aircraft fixture

Abstract

The utility model discloses an adjustable inclined support for an aircraft fixture, which relates to the technical field of aircraft manufacturing and comprises a base, hydraulic cylinders are fixedly connected to the periphery of the top of the base, a second rotating rod is movably connected to the middle end of the top of the base, and a second driven gear is fixedly connected to the upper end of the outer surface of the second rotating rod. Multi-degree-of-freedom and composite adjustment is achieved, the four hydraulic cylinders acting independently can achieve overall lifting and horizontal leveling of the support platform, stable supporting is provided for an aircraft fixture, a second motor drives a second driving gear to drive a second driven gear and a third supporting plate to rotate with a second rotating rod as the center, and the second rotating rod is driven to rotate. And a third motor drives a worm to be meshed with a deflection block with teeth, the deflection seat is driven to achieve accurate pitching angle deflection adjustment, deflection of the deflection seat can be accurately adjusted, and angle adjustment of the aircraft fixture in different directions can be completed through rotation and deflection matching.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aircraft manufacturing, specifically is a kind of adjustable inclined support for aircraft jig. BACKGROUND

[0002] In the field of aircraft manufacturing and assembly, jig is used to position and fix aircraft parts, to ensure the key process equipment of assembly accuracy and shape accuracy, and as the support and positioning reference of jig, its adjustability, stability and operation convenience directly affect assembly efficiency and product quality, traditional aircraft jig support is mostly fixed or only has simple height adjustment function, with the development of modern aircraft, especially large passenger aircraft and military aircraft to the direction of complex curved surface, high precision, modular assembly, higher requirements are put forward to the adjustment flexibility of jig support, in the assembly process, operating personnel often need to adjust the jig support according to the different positions and angles of aircraft parts, including height, horizontal position, pitch angle and rotation around vertical axis, to realize the best support and accurate positioning of parts.

[0003] At present, although some improved adjustable supports realize the adjustment of part degrees, there are still the following shortcomings:

[0004] Single adjustment function: many supports can only realize height or single angle adjustment, cannot meet the composite adjustment demand of complex space pose, often need to cooperate with multiple tools or artificial shims, operation is tedious, efficiency is low, and after aircraft jig is placed on support, support bears very large weight, at this time, adjustment is difficult, and accurate adjustment is difficult to complete.

[0005] Low degree of automation: adjustment process seriously depends on manual experience and manual operation, accurate, fast and repeatable digital control cannot be realized, which is not conducive to integration with automatic assembly system. CONTENT OF UTILITY MODEL

[0006] The utility model aims at providing a kind of adjustable inclined support for aircraft jig to solve the problems raised in the above background.

[0007] To achieve the above objectives, this utility model provides the following technical solution: an adjustable tilting support for an aircraft frame, comprising a base, hydraulic cylinders fixedly connected to all four sides of the top of the base, and a frame support mounted on the telescopic end of each hydraulic cylinder; a second rotating rod movably connected to the middle of the top of the base, and a second driven gear fixedly connected to the upper end of the outer surface of the second rotating rod; a second motor fixedly connected to the top of the base, and a second driving gear fixedly connected to the output shaft of the second motor, with the second driving gear meshing with the second driven gear; a third support plate fixedly connected to the top of the second rotating rod, and brackets fixedly connected to the left and right sides of the front end of the top of the third support plate; a deflection block movably connected to the inner side of the bracket, the surface of the deflection block being provided with teeth, and a deflection seat fixedly connected to the top of the deflection block; a third motor fixedly connected to the rear end of the top of the third support plate, and a worm gear fixedly connected to the output shaft of the third motor, the end of the worm gear movably connected to the third support plate, and the worm gear meshing with the teeth on the surface of the deflection block.

[0008] Preferably, the telescopic end of the hydraulic cylinder is fixedly connected to a first support plate, one end of the top of the first support plate is movably connected to a first rotating rod, the top of the first rotating rod is hinged to a second support plate, and the frame support is assembled on the second support plate.

[0009] Preferably, an electric push rod is fixedly connected to the outer side of the top of the second support plate, and a frame support is fixedly connected to the telescopic end of the electric push rod. The frame support has an "L" shaped structure, and a pad is fixedly connected to the top of the frame support.

[0010] Preferably, the telescopic ends of the hydraulic cylinder and the electric push rod are both fixedly connected to auxiliary rods, and the outer surface of the auxiliary rods is slidably connected to the fixed end of the hydraulic cylinder or the electric push rod.

[0011] Preferably, a first motor is fixedly connected to the other end of the top of the first support plate, a first drive gear is fixedly connected to the output shaft of the first motor, a first driven gear is meshed with the outer surface of the first drive gear, and the first driven gear is fixedly connected to the upper end of the outer surface of the first rotating rod.

[0012] Preferably, the top of the second support plate is provided with a sliding groove, and a slider is slidably connected to the inner side of the sliding groove, and the slider is fixedly connected to the bottom of the frame support.

[0013] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0014] This invention achieves multi-degree-of-freedom and composite adjustment. Four independently operating hydraulic cylinders can realize the overall lifting and leveling of the support platform, providing stable support for the aircraft frame. The second motor drives the second drive gear to drive the second driven gear and the third support plate to rotate around the second rotating rod, realizing the 360° horizontal rotation of the deflection seat. The third motor drives the worm gear to mesh with the toothed deflection block, driving the deflection seat to achieve precise pitch angle deflection adjustment, realizing precise deflection adjustment of the deflection seat. The combination of rotation and deflection can complete the angle adjustment of the aircraft frame in different directions.

[0015] When adjusting the angle of the aircraft frame, this utility model first lifts the aircraft frame using a hydraulic cylinder, and then controls the deflection seat to deflect. This effectively solves the problems of large weight, difficult adjustment, and easy damage in traditional adjustment methods. It allows the deflection seat to be adjusted without bearing weight, resulting in higher precision and no damage, thus improving safety and work efficiency.

[0016] This invention uses a hydraulic cylinder to lift the aircraft frame as a whole when adjusting its angle. Compared with the traditional method of lifting and lowering, this method is simpler and more stable. In addition, the structure at the output end of the hydraulic cylinder makes it easier and more effective to tilt and fix the aircraft frame, providing greater convenience. Attached Figure Description

[0017] Figure 1 This is a three-dimensional structural diagram of the present invention from a first-person perspective.

[0018] Figure 2 This is a three-dimensional structural diagram of the present invention from a second perspective.

[0019] Figure 3 This is a three-dimensional structural diagram of the present invention from a third-view perspective;

[0020] Figure 4 This is a schematic diagram of the slider structure of this utility model.

[0021] In the diagram: 1. Base; 2. Auxiliary rod; 3. Hydraulic cylinder; 4. Deflection seat; 5. Frame support; 6. Second motor; 7. Second driven gear; 8. Second driving gear; 9. First support plate; 10. First motor; 11. Bracket; 12. Third support plate; 13. First driving gear; 14. Second support plate; 15. Electric push rod; 16. Worm gear; 17. Deflection block; 18. First rotating rod; 19. Third motor; 20. Second rotating rod; 21. First driven gear; 22. Slider; 23. Slide groove. Detailed Implementation

[0022] 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.

[0023] Please see Figures 1-4 An adjustable tilting support for an aircraft frame includes a base 1. Hydraulic cylinders 3 are fixedly connected to all four sides of the top of the base 1, and frame supports 5 are mounted on the telescopic ends of the hydraulic cylinders 3. A second rotating rod 20 is movably connected to the middle of the top of the base 1, and a second driven gear 7 is fixedly connected to the upper end of the outer surface of the second rotating rod 20. A second motor 6 is fixedly connected to the top of the base 1, and a second driving gear 8 is fixedly connected to the output shaft of the second motor 6. The second driving gear 8 meshes with the second driven gear 7. The top of the second rotating rod 20... A third support plate 12 is fixedly connected, and brackets 11 are fixedly connected to the left and right sides of the top front end of the third support plate 12. A deflection block 17 is movably connected to the inner side of the bracket 11. The surface of the deflection block 17 is provided with teeth, and a deflection seat 4 is fixedly connected to the top of the deflection block 17. A third motor 19 is fixedly connected to the rear end of the top of the third support plate 12, and a worm gear 16 is fixedly connected to the output shaft of the third motor 19. The end of the worm gear 16 is movably connected to the third support plate 12, and the worm gear 16 meshes with the teeth on the surface of the deflection block 17.

[0024] The worm gear 16 and the deflector block 17 are coupled by a worm gear transmission, which has a self-locking characteristic and can be locked at any position, ensuring that the pitch angle can be reliably locked after adjustment. At the same time, it can realize precise angle adjustment of the deflector seat 4, improving the accuracy of aircraft frame tilt adjustment.

[0025] Pressure sensors are installed on both the frame support 5 and the deflection seat 4. The pressure feedback enables the control console (or processor) to control the operation of each hydraulic cylinder 3. The purpose is to ensure that each frame support 5 provides sufficient support for the aircraft frame, effectively supporting it and preventing damage caused by excessive force on one end.

[0026] The telescopic end of the hydraulic cylinder 3 is fixedly connected to a first support plate 9. One end of the top of the first support plate 9 is movably connected to a first rotating rod 18. The top of the first rotating rod 18 is hinged to a second support plate 14, and the frame support 5 is assembled on the second support plate 14.

[0027] An electric push rod 15 is fixedly connected to the outer side of the top of the second support plate 14. The telescopic end of the electric push rod 15 is fixedly connected to a frame support 5. The frame support 5 has an "L" shaped structure, and a pad is fixedly connected to the top of the frame support 5.

[0028] The L-shaped structure of the frame support 5 has a horizontal plate that supports the aircraft frame and a vertical plate that clamps and fixes the aircraft frame from the side.

[0029] The base plate is made of metal, which can reduce the damage of the aircraft jig to the jig support 5 and prevent the jig support 5 from damaging the aircraft jig.

[0030] The process of placing the aircraft frame is as follows: control the hydraulic cylinder 3 to raise the frame support 5, and at the same time control the electric push rod 15 to move the frame support 5 outward to place the aircraft frame. At the same time as placing it, control the frame support 5 to move inward so that its vertical plate contacts the side wall of the aircraft frame, thus completing the support and fixation of the aircraft frame. The aircraft frame does not contact the deflection seat 4, which facilitates the subsequent angle adjustment of the aircraft frame.

[0031] The third motor 19 drives the worm gear 16 to rotate, which drives the deflection block to deflect through the worm wheel and worm gear transmission, thereby realizing the deflection action of the deflection seat 4. After the adjustment is completed, the hydraulic cylinder 3 controls the frame support 5 to descend, and the aircraft frame descends accordingly and tilts after contacting the deflection seat 4. At the same time, each pressure sensor measures the pressure value borne by the frame support 5 and controls each hydraulic cylinder 3 to operate.

[0032] The operation of the hydraulic cylinder 3 described above is as follows: the hydraulic cylinder 3 at the lower end of the aircraft frame tilt controls the frame support 5 to descend, while the hydraulic cylinder 3 at the upper end controls the frame support 5 to rise, so that each frame support 5 can provide sufficient support force for the aircraft frame. At the same time, the second support plate 14 deflects under the action of the hinge device, so that the frame support 5 and the aircraft frame tilt at the same angle. Meanwhile, the electric push rod 15 operates to keep the vertical plate of the frame support 5 clamped to the aircraft frame, and finally the tilt adjustment of the aircraft frame is completed.

[0033] For heavier aircraft frames, an auxiliary rod 2 can be installed at the telescopic end of the hydraulic cylinder 3 and the electric push rod 15. The outer surface of the auxiliary rod 2 is slidably connected to the fixed end of the hydraulic cylinder 3 or the electric push rod 15. The auxiliary rod 2 enhances the bending stiffness of the telescopic end of the hydraulic cylinder 3 and the electric push rod 15, preventing the hydraulic cylinder 3 and the electric push rod 15 from being damaged by lateral pressure when the aircraft frame is tilted.

[0034] The other end of the top of the first support plate 9 is fixedly connected to the first motor 10. The output shaft of the first motor 10 is fixedly connected to the first drive gear 13. The outer surface of the first drive gear 13 is meshed with the first driven gear 21, and the first driven gear 21 is fixedly connected to the upper end of the outer surface of the first rotating rod 18.

[0035] Controlling the rotation of the second motor 6 and the first motor 10, the second driven gear 7 can be driven to rotate under the cooperation of the second driving gear 8, thereby causing the second rotating rod 20 to rotate, which can drive the deflection seat 4. At the same time, under the cooperation of the first driving gear 13, the first driven gear 21 can be driven to rotate, thereby causing the first rotating rod 18 to rotate, which can drive the frame support 5 to rotate horizontally. After that, the aircraft frame can be tilted at other angles.

[0036] For the aforementioned rotation operation, for aircraft frames with heavy loads, a ball bearing structure can be installed on the pad of the frame support 5 to allow the frame support 5 to rotate smoothly under the aircraft frame and facilitate the movement of the frame support 5 by the electric push rod 15. Only after the frame support 5 moves outward can the rotation at the corner of the aircraft frame be completed. After the rotation is completed, the electric push rod 15 will run to make the vertical plate of the frame support 5 clamp and fix the aircraft frame again.

[0037] The aforementioned rotation process must be carried out when the aircraft frame is in a horizontal position.

[0038] The top of the second support plate 14 is provided with a sliding groove 23, and a slider 22 is slidably connected to the inner side of the sliding groove 23. The slider 22 is fixedly connected to the bottom of the frame support 5. The sliding groove 23 and the slider 22 can ensure the stability of the movement of the frame support 5.

[0039] The working principle of this application is as follows: First, the aircraft frame is placed. Then, the worm gear 16 is rotated to deflect the deflector seat 4 to a set angle. After the adjustment is completed, the hydraulic cylinder 3 controls the frame support 5 to descend. The aircraft frame will contact the deflected deflector seat 4 and tilt. Under the support and tilting action of the deflector seat 4 and the cooperation of the pressure sensor and the hydraulic cylinder, the tilting and fixing of the aircraft frame is completed.

[0040] For cases requiring tilting at other angles, after placing the aircraft frame, first rotate the deflector 4 and the frame support 5 to make the deflection angles of the deflector 4 and the frame support 5 correspond, then complete the deflection work of the deflector 4 mentioned above, and complete the tilting and fixing of the aircraft frame.

[0041] When the angle needs to be adjusted again, the aircraft frame is first lifted by the hydraulic cylinder 3 and the frame support 5, so that the deflection seat 4 is no longer under heavy pressure, which facilitates its deflection. This can improve the adjustment accuracy, avoid the damage that may be caused by adjustment under heavy pressure, improve safety, and complete the angle adjustment of the aircraft frame efficiently and accurately.

[0042] 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. An adjustable tilt support for an aircraft jig, comprising a base (1), characterized in that: Hydraulic cylinders (3) are fixedly connected to the top of the base (1) around all four sides, and the telescopic ends of the hydraulic cylinders (3) are equipped with frame supports (5). A second rotating rod (20) is movably connected to the middle of the top of the base (1), and a second driven gear (7) is fixedly connected to the upper end of the outer surface of the second rotating rod (20). A second motor (6) is fixedly connected to the top of the base (1), and a second driving gear (8) is fixedly connected to the output shaft of the second motor (6). The second driving gear (8) meshes with the second driven gear (7). A third support plate (1) is fixedly connected to the top of the second rotating rod (20). 2), and brackets (11) are fixedly connected to the left and right sides of the top front end of the third support plate (12). A deflection block (17) is movably connected to the inner side of the bracket (11). The surface of the deflection block (17) is provided with teeth, and a deflection seat (4) is fixedly connected to the top of the deflection block (17). A third motor (19) is fixedly connected to the rear end of the top of the third support plate (12), and a worm (16) is fixedly connected to the output shaft of the third motor (19). The end of the worm (16) is movably connected to the third support plate (12), and the worm (16) meshes with the teeth on the surface of the deflection block (17).

2. The adjustable tilt support for aircraft jigs according to claim 1, characterized in that: The telescopic end of the hydraulic cylinder (3) is fixedly connected to a first support plate (9), and a first rotating rod (18) is movably connected to one end of the top of the first support plate (9). A second support plate (14) is hinged to the top of the first rotating rod (18), and the frame support (5) is mounted on the second support plate (14).

3. An adjustable tilt support for an aircraft frame according to claim 2, characterized in that: An electric push rod (15) is fixedly connected to the outer side of the top of the second support plate (14). The telescopic end of the electric push rod (15) is fixedly connected to a frame support (5). The frame support (5) has an "L" shaped structure, and a pad is fixedly connected to the top of the frame support (5).

4. An adjustable tilt support for an aircraft jig according to claim 3, characterized in that: The extension and retraction ends of the hydraulic cylinder (3) and the electric push rod (15) are both fixedly connected to auxiliary rods (2), and the outer surface of the auxiliary rods (2) is slidably connected to the fixed end of the hydraulic cylinder (3) or the electric push rod (15).

5. An adjustable tilt support for an aircraft jig according to claim 2, characterized in that: The other end of the top of the first support plate (9) is fixedly connected to the first motor (10), the output shaft of the first motor (10) is fixedly connected to the first driving gear (13), the outer surface of the first driving gear (13) is meshed with the first driven gear (21), and the first driven gear (21) is fixedly connected to the upper end of the outer surface of the first rotating rod (18).

6. An adjustable tilt support for an aircraft jig according to claim 3, characterized in that: The top of the second support plate (14) is provided with a sliding groove (23), and a slider (22) is slidably connected to the inner side of the sliding groove (23), and the slider (22) is fixedly connected to the bottom of the frame support (5).

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