Machine body posture adjusting tool

Abstract

The utility model discloses a fuselage posture adjusting tool, which relates to the technical field of aircraft manufacturing and assembling and comprises two fixing devices which are arranged front and back and are respectively used for fixing the front end and the rear end of a fuselage. Each fixing device comprises two adjusting mechanisms, each adjusting mechanism comprises a frame and a supporting column arranged on the frame, and each adjusting mechanism further comprises a transverse moving assembly, a longitudinal moving assembly and a vertical moving assembly which are arranged on the frame so as to drive the supporting column to move transversely, longitudinally and vertically. Each fixing device further comprises a connecting frame. The brackets can be transversely, longitudinally and vertically moved and adjusted, so that each bracket has a three-degree-of-freedom adjusting function, a fuselage and wings are conveniently positioned and butted, and the construction requirements of butting precision, safety, stability and proper height of the fuselage and wing structure are met; and a worker can conveniently mount other equipment such as a nose landing gear on the fuselage.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft manufacturing and assembly, in particular to a fuselage posture adjustment tool. Background Art

[0002] Unmanned aerial vehicle (UAV), also known as "drone", is an unmanned aircraft that is controlled by radio remote control equipment and self-contained program control devices, or is operated completely or intermittently autonomously by an onboard computer.

[0003] During the drone manufacturing and assembly process, the fuselage typically needs to be lifted manually or by an overhead crane to adjust its position and align it with other components, such as the wings. This method makes the fuselage's position susceptible to operator habits, reducing the accuracy of the fuselage-wing structure docking, reducing assembly safety, and making it difficult to install onboard equipment, cables, and other accessories. Utility Model Content

[0004] The purpose of the utility model is to solve the problems in the prior art and to propose a posture adjustment tooling that is convenient for stably supporting the fuselage, facilitating adjustment and positioning, and facilitating the installation of airborne equipment, cables and other accessories on the fuselage.

[0005] In order to achieve the above purpose, the present invention adopts the following technical solutions:

[0006] Fuselage posture adjustment tooling, including:

[0007] Two fixing devices, which are arranged front and back and are used to fix the front and rear ends of the fuselage respectively;

[0008] Each fixing device includes two adjustment mechanisms, each adjustment mechanism includes a frame and a support provided on the frame, and each adjustment mechanism also includes a lateral movement component, a longitudinal movement component and a vertical movement component provided on the frame to drive the support to move laterally, longitudinally and vertically respectively;

[0009] Each fixing device also includes a connecting frame, the two ends of which are fixedly connected to the two frames respectively, and the connecting frame is located on the sides of the two frames to form a working space between the two frames;

[0010] Two brackets, each bracket is arranged on two pillars of a fixing device.

[0011] Furthermore, a crossbeam is provided between the two connecting frames, and the crossbeam is connected to the connecting frames via pins.

[0012] Furthermore, a connecting rod is provided in the middle of one of the brackets, and both the connecting bracket and the connecting rod are U-shaped.

[0013] Furthermore, the transverse movement assembly includes a transverse adjustment handwheel, a transverse threaded rod, a transverse slide rail and a transverse movement plate. The transverse threaded rod and the transverse slide rail are both arranged on the frame. The transverse adjustment handwheel is fixedly connected to one end of the transverse threaded rod. The transverse movement plate is slidingly connected to the frame through the transverse slide rail, and a first threaded sleeve is provided at the bottom of the transverse movement plate, which is threadedly connected to the transverse threaded rod.

[0014] Furthermore, the longitudinal moving assembly includes a longitudinal adjustment handwheel, a longitudinal threaded rod, a longitudinal slide rail and a longitudinal moving plate. The longitudinal threaded rod and the longitudinal slide rail are both arranged on the transverse moving plate. The longitudinal adjustment handwheel is fixedly connected to one end of the longitudinal threaded rod. The longitudinal moving plate is slidingly connected to the transverse moving plate through the longitudinal slide rail, and a third threaded sleeve is provided at the bottom of the longitudinal moving plate, which is threadedly connected to the longitudinal threaded rod.

[0015] Furthermore, the transverse moving assembly and the longitudinal moving assembly are arranged perpendicular to each other.

[0016] Furthermore, the vertical moving assembly includes a shell, a worm gear, a worm and a vertical adjustment handwheel. The shell is arranged on the longitudinal moving plate, the worm gear is rotatably connected to the interior of the shell, the inner ring of the worm gear is provided with a second threaded sleeve, the pillar passes through the worm gear and is threadedly connected to the second threaded sleeve, one end of the worm gear horizontally penetrates into the interior of the shell and engages with the worm gear, the other end of the worm gear is fixedly connected to the vertical adjustment handwheel, a vertical slide groove is provided on the outside of the pillar, and a slider is provided on the shell, and the slider is located inside the vertical slide groove.

[0017] Furthermore, the upper ends of the two pillars are provided with fixing rods, the upper ends of the fixing rods are spherical, and movable seats are provided on both sides of the bottom of the bracket. The bottom of the movable seat is provided with a spherical groove, and the spherical upper end of each fixing rod is located inside a spherical groove.

[0018] Furthermore, a pad is provided on the top of the bracket, and the top of the pad is arc-shaped to fit the lower surface of the fuselage, and a strap is provided on the top of the bracket.

[0019] Furthermore, a universal wheel is provided at the bottom of the frame, a fixing plate is provided at the bottom of the frame, a threaded hole is opened on the fixing plate, a fixing threaded rod is provided inside the threaded hole, and a fixing seat is provided at the lower end of the fixing threaded rod.

[0020] The beneficial effects of the utility model are:

[0021] In the utility model, the fuselage attitude adjustment tooling can be adjusted laterally by rotating the lateral adjustment hand wheel, longitudinally by rotating the longitudinal adjustment hand wheel, and vertically by rotating the vertical adjustment hand wheel, so that each bracket has adjustment functions in three directions: lateral, longitudinal, and vertical, which facilitates the positioning and docking of the fuselage and the wing, and meets the construction requirements of accurate docking, safety, stability, and appropriate height between the fuselage and wing structures. In addition, the working space left between the two frames facilitates the installation of other equipment such as the front landing gear on the fuselage by workers.

[0022] The crossbeam can be connected to the two connecting frames through pins, so that the tooling is combined into a whole, which can effectively prevent the tooling from tipping over and displacement. When not in use, the crossbeam can be disassembled, making it easier for the two fixing devices to be separated into a single unit and evacuated, thereby improving the flexibility of the tooling. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 This is a schematic diagram of the three-dimensional structure of the fuselage posture adjustment tooling proposed in the utility model;

[0024] Figure 2 This is a schematic diagram of the three-dimensional structure of the horizontal moving component and the vertical moving component of the fuselage posture adjustment tooling proposed in the present invention;

[0025] Figure 3 This is a schematic cross-sectional view of the vertical adjustment assembly, fixing rod and movable seat of the fuselage posture adjustment tooling proposed in the present invention;

[0026] Figure 4 This is a schematic cross-sectional structural diagram of the first threaded sleeve of the fuselage posture adjustment tooling proposed by the utility model.

[0027] In the figure: 1 frame, 101 universal wheel, 2 horizontal movement assembly, 201 horizontal adjustment handwheel, 202 horizontal threaded rod, 203 horizontal slide rail, 204 horizontal movement plate, 205 first threaded sleeve, 3 longitudinal movement assembly, 301 longitudinal adjustment handwheel, 302 longitudinal threaded rod, 303 longitudinal slide rail, 304 third threaded sleeve, 305 longitudinal movement plate, 4 vertical movement assembly, 401 housing, 402 worm gear, 403 worm, 404 vertical adjustment handwheel, 405 second threaded sleeve, 5 pillar, 501 vertical slide groove, slider 502, 6 bracket, 7 beam, 8 connecting frame, 9 connecting rod, 10 fixed rod, 11 movable seat. DETAILED DESCRIPTION

[0028] The technical solution of the present application will be further described in detail below in conjunction with specific implementation methods.

[0029] The following describes in detail embodiments of the present application. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present application and are not to be construed as limiting the present application.

[0030] In the description of this application, it should be understood that the terms "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0031] In the description of this application, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "connected," "connected," and "disposed" should be understood in a broad sense. For example, they may refer to fixed connection or disposition, detachable connection or disposition, or integral connection or disposition. Those skilled in the art will understand the specific meanings of the above terms in this application based on specific circumstances.

[0032] Example 1

[0033] Reference Figure 1-4 The fuselage posture adjustment tooling is used for fuselage positioning and assembly to improve the stability of the fuselage during assembly, facilitate the adjustment and positioning of the fuselage posture, and facilitate the installation of other accessories on the fuselage.

[0034] The fuselage posture adjustment tool comprises two fixing devices, which are arranged front and back and are used to fix the front end and the rear end of the fuselage respectively.

[0035] Each fixing device includes two adjustment mechanisms and a connecting frame 8. Each adjustment mechanism includes a frame 1. The two ends of the connecting frame 8 are fixedly connected to the two frames 1 respectively, and the connecting frame 8 is located on the sides of the two frames 1 to form a working space between the two frames 1. The working space between the two frames 1 can free up the space under the fuselage, thereby facilitating the staff to install the front landing gear on the fuselage.

[0036] A crossbeam 7 is provided between the two connecting frames 8 in the two fixing devices. The crossbeam 7 is connected to the connecting frame 8 by pins. The crossbeam 7 connected by the pins is convenient for disassembly from the two fixing devices, so that the tooling is connected as one during use, thereby improving stability. When evacuating the site, it can be divided into two units, which is convenient for moving to the parking area, thereby improving work flexibility.

[0037] Each adjustment mechanism includes a transverse movement component 2 arranged on the frame 1, and the transverse movement component 2 includes a transverse adjustment handwheel 201, a transverse threaded rod 202, a transverse slide rail 203 and a transverse movement plate 204. The transverse threaded rod 202 and the transverse slide rail 203 are both arranged on the frame 1. The transverse adjustment handwheel 201 is fixedly connected to one end of the transverse threaded rod 202, and the transverse movement plate 204 is slidingly connected to the frame 1 through the transverse slide rail 203, and a first threaded sleeve 205 is provided at the bottom of the transverse movement plate 204. The first threaded sleeve 205 is threadedly connected to the transverse threaded rod 202. By rotating the transverse adjustment handwheel 201, the transverse threaded rod 202 can be driven to rotate, and the transverse threaded rod 202 rotates inside the first threaded sleeve 205, so that the first threaded sleeve 205 drives the transverse movement plate 204 to move along the transverse slide rail 203 for transverse adjustment.

[0038] Each adjustment mechanism also includes a longitudinal movement component 3 arranged on the transverse movement plate 204, and the longitudinal movement component 3 includes a longitudinal adjustment handwheel 301, a longitudinal threaded rod 302, a longitudinal slide rail 303 and a longitudinal movement plate 305. The longitudinal threaded rod 302 and the longitudinal slide rail 303 are both arranged on the transverse movement plate 204, and the longitudinal adjustment handwheel 301 is fixedly connected to one end of the longitudinal threaded rod 302, and the longitudinal movement plate 305 is slidingly connected to the transverse movement plate 204 through the longitudinal slide rail 303, and a third threaded sleeve 304 is provided at the bottom of the longitudinal movement plate 305, and the third threaded sleeve 304 is threadedly connected to the longitudinal threaded rod 302. By rotating the longitudinal adjustment handwheel 301, the longitudinal threaded rod 302 can be driven to rotate, and the longitudinal threaded rod 302 rotates inside the third threaded sleeve 304, so that the third threaded sleeve 304 drives the longitudinal movement plate 305 to move along the longitudinal slide rail 303 for longitudinal adjustment.

[0039] The transverse moving assembly 2 and the longitudinal moving assembly 3 are arranged perpendicular to each other, so that the tooling can be adjusted transversely and longitudinally on a horizontal plane.

[0040] Each adjustment mechanism also includes a vertical movement component 4 and a support 5 arranged on the longitudinal movement plate 305. The vertical movement component 4 includes a housing 401, a worm gear 402, a worm 403 and a vertical adjustment hand wheel 404. The housing 401 is arranged on the longitudinal movement plate 305. The worm gear 402 is rotatably connected to the interior of the housing 401. The inner ring of the worm gear 402 is provided with a second threaded sleeve 405. The support 5 passes through the worm gear 402 and is threadedly connected to the second threaded sleeve 405. One end of the worm 403 is horizontally inserted into the housing. The inside of the body 401 is engaged with the worm gear 402, and the other end of the worm 403 is fixedly connected to the vertical adjustment hand wheel 404. A vertical slide groove 501 is provided on the outside of the pillar 5, and a slider 502 is provided on the shell 401. The slider 502 is located inside the vertical slide groove 501. By rotating the vertical adjustment hand wheel 404, the worm 403 can be driven to rotate, thereby driving the worm gear 402 to rotate, and the second threaded sleeve 405 on the inner ring of the worm gear 402 rotates, thereby driving the pillar 5 to move vertically along the vertical slide groove.

[0041] Each bracket 6 is arranged on two pillars 5 of a fixing device, and a connecting rod 9 is provided in the middle of one of the brackets 6. The connecting frame 8 and the connecting rod 9 are both U-shaped, thereby leaving the middle of the fixing device empty to form a working space, which is convenient for installing accessories on the fuselage.

[0042] Each fixing device is provided with two adjustment mechanisms, so that the height of the left and right ends of the bracket 6 can be fine-tuned respectively to adjust the tilt angle of the fuselage on the bracket 6, so that the tooling can adapt to uneven ground and facilitate the positioning and docking of the fuselage and the wing. In addition, a fixing rod 10 is provided at the upper end of each of the two pillars 5. The upper end of the fixing rod 10 is spherical. Both sides of the bottom of the bracket 6 are provided with a movable seat 11. The bottom of the movable seat 11 is provided with a spherical groove. The spherical upper end of each fixing rod 10 is located inside a spherical groove. When one of the pillars When individual adjustments are made using the vertical adjustment hand wheel 404, the spherical upper end of the fixing rod 10 can move within the spherical groove, thereby facilitating rotation between the bracket 6 and the support 5. Furthermore, since there is a certain assembly clearance between the spherical upper end of the fixing rod 10 and the spherical groove, the heights of the two support columns 5 can be fine-tuned within a certain range, allowing the tooling to adapt to uneven ground and ensuring the levelness of the fuselage on the bracket 6. Furthermore, a bubble-shaped level is installed on the bracket 6 to facilitate visual inspection of whether the tooling is level.

[0043] A pad is provided on the top of the bracket 6, and the top of the pad is arc-shaped to fit the lower surface of the fuselage. The pad is made of high-strength, corrosion-resistant, and high-temperature resistant nylon pad or other non-wood-like lightweight materials. The contact part with the lower surface of the fuselage is made of soft material to protect the lower surface of the fuselage. A strap is provided on the top of the bracket 6, and the fuselage can be fixed to the bracket 6 by the strap to improve the stability of the fuselage when it is fixed.

[0044] Example 2

[0045] In order to improve the flexibility and stability of the fuselage posture adjustment tooling, a universal wheel 101 is provided at the bottom of the frame 1, and a fixing plate is provided at the bottom of the frame 1. A threaded hole is opened on the fixing plate, and a fixed threaded rod is provided inside the threaded hole. A fixed seat is provided at the lower end of the fixed threaded rod. The tooling can be moved by the universal wheel 101, thereby improving the flexibility of the tooling. When fixing the fuselage, the fixed threaded rod can be rotated to lower the fixed seat and contact the ground, so that the tooling is fixed by the fixed seat, thereby improving the stability of the tooling.

[0046] The working principle of the fuselage posture adjustment tool is as follows: when in use, the two fixing devices are pushed to the designated area through the universal wheels 101, and then the two ends of the crossbeam 7 are connected to the two connecting frames 8 respectively through pins, so that the two fixing devices are combined into a whole, which can effectively prevent the tooling from tipping over and displacement;

[0047] The fuselage is hoisted onto the bracket 6 by a hoisting device, with the lower surface of the fuselage fitting into contact with the upper surface of the bracket 6, and then the fuselage is fixed to the bracket 6 by tightening the straps around the left and right sides of the fuselage;

[0048] When lateral adjustment is required, the lateral threaded rod 202 is driven to rotate by rotating the lateral adjustment hand wheel 201. The lateral threaded rod 202 rotates inside the first threaded sleeve 205, so that the first threaded sleeve 205 drives the lateral movable plate 204 to move along the lateral slide rail 203 for lateral adjustment.

[0049] When longitudinal adjustment is required, the longitudinal adjustment hand wheel 301 is rotated to drive the longitudinal threaded rod 302 to rotate, and the longitudinal threaded rod 302 rotates inside the third threaded sleeve 304, so that the third threaded sleeve 304 drives the longitudinal movable plate 305 to move along the longitudinal slide rail 303 to perform longitudinal adjustment;

[0050] When vertical adjustment is required, the vertical adjustment hand wheel 404 is rotated to drive the worm 403 to rotate, thereby driving the worm wheel 402 to rotate. The second threaded sleeve 405 on the inner ring of the worm wheel 402 rotates, thereby driving the strut 5 to move vertically along the vertical slide 501. By rotating the two vertical adjustment hand wheels 404 at the same time, the two struts 5 can be raised and lowered simultaneously, and the wing can be driven to move up and down as a whole over a large range.

[0051] When one support 5 is driven to rise and fall alone, the horizontality of the bracket 6 can be finely adjusted. In the actual assembly process of various parts of the tooling, since there is an assembly gap between the two supports 5 and the bracket 6, within a certain range allowed by the height difference between the two supports 5, one support 5 can be driven to rise and fall alone to fine-tune the horizontality of the bracket 6, so that the tooling can adapt to uneven ground. It should be noted that the height difference between the two supports 5 during the fine adjustment of the bracket 6 must be controlled within 3 cm. At this time, the assembly gap between the support 5 and the bracket 6 is sufficient so that when the two supports 5 are of different heights, the bracket 6 does not affect the lifting and lowering of the two supports 5.

[0052] The fuselage and wings can be positioned and docked through horizontal, longitudinal and vertical adjustments, making assembly easier;

[0053] During assembly, the working space between the two frames 1 and in the middle of the bracket 6 facilitates the installation of other equipment such as the front landing gear on the fuselage by the workers;

[0054] After assembly is completed, the aircraft is supported by a jack to separate the tooling from the fuselage. The pins can be pulled out at this time to dismantle the crossbeam 7 and separate the two fixing devices, thereby facilitating the tooling to be separated and evacuated.

[0055] The above is only a preferred specific implementation method of the present invention, but the protection scope of the present invention is not limited to this. Any technician familiar with the technical field within the technical scope disclosed by the present invention can make equivalent replacements or changes based on the technical solution and utility model concept of the present invention, which should be covered by the protection scope of the present invention.

Claims

1. The fuselage posture adjustment tool is characterized by: include: Two fixing devices, the two fixing devices are arranged in front and back, respectively used to fix the front end and the rear end of the fuselage; Each of the fixing devices includes two adjustment mechanisms, each of the adjustment mechanisms includes a frame (1) and a support (5) arranged on the frame (1), and each of the adjustment mechanisms also includes a transverse movement component (2), a longitudinal movement component (3) and a vertical movement component (4) arranged on the frame (1) to drive the support (5) to move transversely, longitudinally and vertically respectively; Each of the fixing devices further comprises a connecting frame (8), both ends of the connecting frame (8) being fixedly connected to the two frames (1), and the connecting frame (8) being located on the sides of the two frames (1) so as to form a working space between the two frames (1); Two brackets (6), each bracket (6) is arranged on two pillars (5) of a fixing device.

2. The fuselage posture adjustment tool according to claim 1, characterized in that: A crossbeam (7) is provided between the two connecting frames (8), and the crossbeam (7) is connected to the connecting frames (8) via pins.

3. The fuselage posture adjustment tool according to claim 1, characterized in that: A connecting rod (9) is provided in the middle of one of the brackets (6), and both the connecting frame (8) and the connecting rod (9) are U-shaped.

4. The fuselage posture adjustment tool according to claim 1, characterized in that: The transverse movement assembly (2) comprises a transverse adjustment handwheel (201), a transverse threaded rod (202), a transverse slide rail (203) and a transverse movement plate (204), wherein the transverse threaded rod (202) and the transverse slide rail (203) are both arranged on the frame (1), the transverse adjustment handwheel (201) is fixedly connected to one end of the transverse threaded rod (202), the transverse movement plate (204) is slidably connected to the frame (1) via the transverse slide rail (203), and a first threaded sleeve (205) is provided at the bottom of the transverse movement plate (204), and the first threaded sleeve (205) is threadedly connected to the transverse threaded rod (202).

5. The fuselage posture adjustment tool according to claim 4, characterized in that: The longitudinal movement assembly (3) comprises a longitudinal adjustment hand wheel (301), a longitudinal threaded rod (302), a longitudinal slide rail (303) and a longitudinal movement plate (305), wherein the longitudinal threaded rod (302) and the longitudinal slide rail (303) are both arranged on the transverse movement plate (204), the longitudinal adjustment hand wheel (301) is fixedly connected to one end of the longitudinal threaded rod (302), the longitudinal movement plate (305) is slidably connected to the transverse movement plate (204) via the longitudinal slide rail (303), and a third threaded sleeve (304) is provided at the bottom of the longitudinal movement plate (305), and the third threaded sleeve (304) is threadedly connected to the longitudinal threaded rod (302).

6. The fuselage posture adjustment tool according to claim 5, characterized in that: The transverse moving component (2) and the longitudinal moving component (3) are arranged perpendicular to each other.

7. The fuselage posture adjustment tool according to claim 5, characterized in that: The vertical moving assembly (4) includes a housing (401), a worm wheel (402), a worm (403) and a vertical adjustment hand wheel (404), wherein the housing (401) is arranged on the longitudinal moving plate (305), the worm wheel (402) is rotatably connected to the interior of the housing (401), the inner ring of the worm wheel (402) is provided with a second threaded sleeve (405), the pillar (5) passes through the worm wheel (402) and is threadedly connected to the second threaded sleeve (405), one end of the worm (403) is horizontally penetrated into the interior of the housing (401) and meshed with the worm wheel (402), the other end of the worm (403) is fixedly connected to the vertical adjustment hand wheel (404), the outside of the pillar (5) is provided with a vertical slide groove (501), the housing (401) is provided with a slider (502), and the slider (502) is located inside the vertical slide groove (501).

8. The fuselage posture adjustment tool according to claim 1, characterized in that: The upper ends of the two pillars (5) are each provided with a fixing rod (10), the upper ends of the fixing rods (10) are spherical, and movable seats (11) are provided on both sides of the bottom of the bracket (6), and the bottom of the movable seat (11) is provided with a spherical groove, and the spherical upper end of each fixing rod (10) is located inside one of the spherical grooves.

9. The fuselage posture adjustment tool according to claim 1, characterized in that: A pad is provided on the top of the bracket (6), and the top of the pad is arc-shaped so as to fit the lower surface of the fuselage. A strap is provided on the top of the bracket (6).

10. The fuselage posture adjustment tool according to claim 1, characterized in that: A universal wheel (101) is provided at the bottom of the frame (1), and a fixing plate is provided at the bottom of the frame (1). A threaded hole is provided on the fixing plate, a fixing threaded rod is provided inside the threaded hole, and a fixing seat is provided at the lower end of the fixing threaded rod.

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