A fine-adjustable aircraft component docking and orientation jig
By designing an adjustable aircraft component docking and attitude adjustment bracket, the stress docking problem was solved, precise docking was achieved, assembly efficiency was improved, and costs were reduced.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- ZHEJIANG XIZI AVIATION IND
- Filing Date
- 2025-09-23
- Publication Date
- 2026-07-21
AI Technical Summary
The existing aircraft component docking and attitude adjustment brackets lack fine-tuning functions, which leads to stress docking or the docking ball head not being able to fully enter the docking cup, affecting docking quality and safety.
Design a finely adjustable aircraft component docking and attitude adjustment bracket that includes a frame, a ground positioning component, a first docking ball joint component, a second docking ball joint component, and a third docking ball joint component. The position of the third ball joint is adjusted by a horizontal clamping component and a height adjustment component to achieve precise docking.
It improved docking quality, reduced assembly docking requirements, reduced design and manufacturing difficulty, improved component transfer efficiency, and reduced costs.
Smart Images
Figure CN224528997U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of aviation assembly tooling technology, and in particular to a finely adjustable aircraft component docking and attitude adjustment bracket. Background Technology
[0002] Aircraft components are characterized by their large size and weight. Currently, more advanced aircraft assembly lines employ automated attitude adjustment (AAP) positioning systems instead of traditional rigid tooling. On AAP assembly lines, different components first dock with their respective conformal tooling, which then docks with the positioner. The positioner calculates the drive input for each axis based on measured values from the attitude adjustment points obtained by a laser tracker, thus completing the attitude adjustment and positioning process for its current station. The product and conformal tooling are then transferred together to the next station.
[0003] Because the assembly of large components is complex and involves a huge amount of work, multiple different stations are usually set up to carry out the assembly work of large components. The structural stability of the products assembled at different stations varies, and the structural stability of the products assembled at earlier stations is usually poor.
[0004] To prevent deformation during transfer between stations, conformal fixtures for the corresponding components are used to transfer them to the next station for attitude adjustment and positioning. However, due to manufacturing errors in the components, the relative positions of the mating point groups on different conformal fixtures differ before and after attitude adjustment. If the corresponding mating and attitude adjustment brackets do not have fine-tuning capabilities, stress may occur during mating, or all mating ball heads may not fully engage with the mating cups for locking. This makes it difficult to guarantee the mating quality of the components and the safety during transport and subsequent attitude adjustment. Utility Model Content
[0005] The main purpose of this utility model is to propose a finely adjustable aircraft component docking and attitude adjustment bracket, which aims to solve the technical problem that if the docking and attitude adjustment bracket does not have a fine-adjustment function, there will be stress docking or all docking ball heads cannot be fully inserted into the docking ball cup to complete the locking during docking.
[0006] To achieve the above objectives, the adjustable aircraft component docking and attitude adjustment bracket proposed in this utility model includes a frame and further includes: Multiple ground positioning components are respectively disposed at the bottom of the frame, each including a positioning block and a first pad, for aligning with the ground positioning mark of the component assembly station so that the bracket enters the target position; Multiple first docking ball head assemblies are respectively disposed in the middle of the skeleton, each including a first ball head and a ball head seat, for matching with the ball cup on the attitude adjustment positioner of the component assembly station; Multiple second docking ball head assemblies are respectively disposed on the top of the frame, each including a second ball head and a second pad, for matching with the ball cup on the conformal tooling of the aircraft component; Multiple third docking ball head assemblies are respectively disposed on the top of the frame. Each assembly includes a third ball head, a horizontal clamping assembly, and a height adjustment assembly, which are used to manually align the position of the ball cup on the conformal tooling of the aircraft component during the docking of the third ball head.
[0007] Optionally, the ground positioning assembly further includes a first bolt for connecting the cylindrical positioning block and the first pad to the frame.
[0008] Optionally, the first mating ball head assembly further includes a second bolt for connecting the downward-facing first ball head and ball head seat to the frame.
[0009] Optionally, the second mating ball head assembly further includes a third bolt for connecting the upward-facing second ball head and the second pad to the frame.
[0010] Optionally, the horizontal clamping assembly includes a ball sleeve fitted around the outer periphery of the third ball head and a plurality of push rods threaded to the ball sleeve, each push rod being used to adjust the horizontal position of the third ball head.
[0011] Optionally, the push rod includes a knurled nut and a first screw connected to each other.
[0012] Optionally, the height adjustment assembly includes a second screw and a screw seat connected to each other, the top end of the second screw is connected to a horizontally arranged mounting plate, the horizontal clamping assembly is disposed on the mounting plate and the third ball head is arranged facing upward.
[0013] Optionally, the height adjustment assembly further includes a handle nut connected to the second screw for driving the second screw to rotate, thereby causing the horizontal clamping assembly to rise or fall.
[0014] Optionally, the third docking ball head assembly further includes a guide assembly, which includes a guide post connected to the mounting plate and a guide sleeve fitted around the outer periphery of the guide post to guide the mounting plate to rise or fall.
[0015] Optionally, it also includes multiple lifting ring assemblies, each disposed on the upper part of the frame, for lifting the bracket.
[0016] Due to manufacturing and assembly tolerances among multiple aircraft components, after individual attitude adjustment by their respective positioners and fastener installation, the positions of the docking points between the aircraft components deviate from the theoretical points. In the technical solution of this utility model, after the lower first ball head and the upper second ball head are docked with the ball cup respectively, the position of the third ball head is adjusted by the horizontal clamping component and the height adjustment component to complete the precise docking with the conformal tooling of the aircraft component. This reduces stress docking and ensures docking quality, thereby reducing the assembly docking requirements of the aircraft components and reducing the design and manufacturing difficulty of the docking bracket. At the same time, it also improves the efficiency of transferring multiple aircraft components to the next station and adjusting their attitude at the next station after attitude adjustment and positioning installation, thus reducing manufacturing and assembly costs. Attached Figure Description
[0017] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.
[0018] Figure 1 This is a three-dimensional structural diagram of an embodiment of the adjustable aircraft component docking and attitude adjustment bracket provided by this utility model; Figure 2 yes Figure 1 A 3D view of the ground positioning component; Figure 3 yes Figure 1 A three-dimensional view of the first docking ball joint assembly; Figure 4 yes Figure 1 A perspective view of the second docking ball joint assembly; Figure 5 yes Figure 1 A three-dimensional view of the third docking ball joint assembly; Figure 6 yes Figure 5 Top view; Figure 7 yes Figure 6 A sectional view of section AA in the middle; Figure 8 This is a diagram showing the docking status of the attitude adjustment bracket at its position. Figure 9 This is a diagram showing the docking status of the attitude adjustment bracket at the next station. Figure 10 yes Figure 9 Enlarged view of point B in the middle.
[0019] Labeling Explanation: Adjustment Bracket - 100, Frame - 1, Square Rod - 11, Ground Positioning Assembly - 2, Positioning Block - 21, First Pad - 22, First Bolt - 23, First Connecting Ball Head Assembly - 3, First Ball Head - 31, Ball Head Seat - 32, Second Bolt - 33, Second Connecting Ball Head Assembly - 4, Second Ball Head - 41, Second Pad - 42, Third Bolt - 43, Third Connecting Ball Head Assembly - 5, Third Ball Head - 51 Horizontal clamping assembly-52, ball sleeve-521, top rod-522, knurled nut-5221, first screw-5222, height adjustment assembly-53, second screw-531, screw seat-532, mounting plate-533, handle nut-534, guide assembly-54, guide post-541, guide sleeve-542, lifting eye assembly-6, cylindrical pin-7, attitude adjustment positioner-8, ball cup-81, AGV-9.
[0020] The realization of the purpose, functional features and advantages of this utility model will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation
[0021] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.
[0022] To better describe and illustrate the embodiments of this application, reference may be made to one or more accompanying drawings, but the additional details or examples used to describe the drawings should not be considered as limiting the scope of any of the utility model creation, the embodiments or preferred embodiments of this application, or the preferred methods described herein.
[0023] In the description of this utility model, it should be noted that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", and "outer" indicate the orientation or positional relationship based on the positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and do not indicate that the device referred to must have a specific orientation or operate in a specific orientation. Therefore, they should not be construed as limitations on this utility model.
[0024] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application.
[0025] Due to manufacturing and assembly tolerances between multiple aircraft components, after individual attitude adjustment by their respective positioners and installation of fasteners, the positions of the mating points between the various aircraft components deviate from the theoretical points.
[0026] In view of this, the present invention provides a finely adjustable aircraft component docking and attitude adjustment bracket. Figure 1-7 This is an embodiment of the adjustable aircraft component docking and attitude adjustment bracket provided by this utility model. Please refer to [link / reference]. Figure 1-7 The attitude adjustment bracket 100 includes a frame 1, four ground positioning components 2, six first docking ball joint assemblies 3, four second docking ball joint assemblies 4, and four third docking ball joint assemblies 5. It should be understood that the number of ground positioning components 2 and ball joint assemblies 3 / 4 / 5 can be other, depending on factors such as the positioning requirements of the aircraft components and the shape of the frame 1.
[0027] Specifically, please refer to Figure 1 The frame 1 is roughly rectangular and consists of several square rods 11 connected together. Four ground positioning components 2 are arranged roughly circumferentially at the four corners of the bottom of the frame 1. Each ground positioning component 2 includes a cylindrical positioning block 21 and a first pad 22. The positioning block 21 and the first pad 22 are fixed to the square rods 11 at the bottom of the frame 1 by connectors. The horizontal end face of the positioning block 21 is consistent with the diameter of the ground positioning mark circle of the component assembly station. When the bracket 100 is positioned at the target position, the alignment of the positioning block 21 with the mark circle is visually inspected to determine whether the positioning is in place.
[0028] Six first docking ball joint assemblies 3 are arranged approximately circumferentially in the middle of the frame 1, with three on each of the front and rear sides. Each first docking ball joint assembly 3 includes a first ball head 31 and a ball head seat 32. The first ball head 31 and the ball head seat 32 are fixed to the square rod 11 in the middle of the frame 1 by a connector. The first ball head 31 is set downwards, so that it can match the ball cup on the attitude adjustment positioner 8 of the component assembly position, thereby realizing the docking and locking functions. Of course, in other embodiments, the orientation of the first ball head 31 can be designed according to different attitude adjustment positioners 8.
[0029] Four second docking ball joint assemblies 4 are arranged approximately circumferentially at the four corners of the top of the frame 1. Each second docking ball joint assembly 4 includes a second ball head 41 and a second pad 42. The second ball head 41 and the second pad 42 are fixed to the square rod 11 at the top of the frame 1 by connectors. The second ball head 41 is positioned upwards, which can match the ball cup on the conformal tooling of the aircraft component, thereby realizing the docking and locking functions. Of course, in other embodiments, the orientation of the second ball head 41 can be designed according to different conformal tooling.
[0030] Four third docking ball joint assemblies 5 are arranged approximately circumferentially at the four corners of the top of the frame 1. Each third docking ball joint assembly 5 includes a third ball head 51, a horizontal clamping assembly 52, and a height adjustment assembly 53. The third ball head 51, the horizontal clamping assembly 52, and the height adjustment assembly 53 are fixed to the square rod 11 at the top of the frame 1 by connectors. When the third ball head 51 is docked, the third ball head 51 can be finely adjusted in the vertical and horizontal directions by operating the horizontal clamping assembly 52 and the height adjustment assembly 53, thereby manually aligning its position on the conformal tooling of the aircraft component. In this embodiment, the third ball head 51 is oriented upwards. In other embodiments, the orientation of the second ball head 41 can be designed differently depending on the conformal tooling.
[0031] In the technical solution of this utility model, after the lower first ball head 31 and the upper second ball head 41 are respectively docked with the ball cup, the position of the third ball head 51 is adjusted by the horizontal pressing component 52 and the height adjustment component 53 to complete the precise docking with the conformal tooling of the aircraft component. This reduces stress docking and ensures docking quality, reduces the assembly docking requirements of the aircraft component, and also reduces the design and manufacturing difficulty of the docking bracket 100. At the same time, it improves the efficiency of transferring multiple aircraft components to the next station after attitude adjustment and positioning installation, and the attitude adjustment of the next station, thus reducing manufacturing and assembly costs.
[0032] To secure ground positioning component 2, please refer to... Figure 2 In one embodiment of the present invention, the ground positioning component 2 further includes six first bolts 23. The first bolts 23 can pass through the cylindrical positioning block 21 and the first pad 22 in sequence and be fixedly connected to the square rod 11 of the frame 1. The number of first bolts 23 can be set to other values as needed.
[0033] Furthermore, to ensure precise connection of the positioning block 21 to the square rod 11, the ground positioning assembly 2 also includes several cylindrical pins 7 and washers. Both the positioning block 21 and the first pad 22 have corresponding identical through holes. First, the cylindrical pins 7 are passed through the through holes and positioned with the square rod 11. Then, the washers are placed in the other through holes, and the first bolt 23 is threaded through the washers and through holes to connect with the square rod 11. This structural fit allows for both precise installation and quick removal.
[0034] To secure the first mating ball head assembly 3, please refer to... Figure 3 In one embodiment of the present invention, the first docking ball head assembly 3 further includes four second bolts 33. The second bolts 33 can pass through the first ball head 31 and the ball head seat 32 in sequence and be fixedly connected to the square rod 11 of the frame 1. The number of second bolts 33 can be set to other values as needed.
[0035] Furthermore, in order to accurately connect the first ball head 31 to the square rod 11, the first mating ball head assembly 3 also includes several cylindrical pins 7 and washers. The first ball head 31 and the ball head seat 32 are respectively provided with several identical through holes. First, the cylindrical pins 7 are passed through the through holes and positioned and engaged with the square rod 11. Then, the washers are placed in other through holes. The second bolt 33 is passed through the washers and through holes and threadedly connected to the square rod 11.
[0036] To secure the second mating ball head assembly 4, please refer to... Figure 4 In one embodiment of the present invention, the second docking ball head assembly 4 further includes four third bolts 43. The second bolts 33 can pass through the second ball head 41 and the second pad 42 in sequence and be fixedly connected to the square rod 11 of the frame 1. The number of third bolts 43 can be set to other values as needed.
[0037] Furthermore, in order to ensure that the second ball head 41 is accurately connected to the square rod 11, the second mating ball head assembly 4 also includes several cylindrical pins 7 and washers. The second ball head 41 and the second pad 42 are respectively provided with several identical through holes. First, the cylindrical pins 7 are passed through the through holes and positioned and engaged with the square rod 11. Then, the washers are placed in other through holes. Finally, the third bolt 43 is passed through the washers and through holes and threadedly connected to the square rod 11.
[0038] To adjust the position of the third docking ball assembly 5, please refer to... Figure 5-7 In one embodiment of the present invention, the horizontal pressing assembly 52 includes a ball sleeve 521 sleeved on the outer periphery of the third ball head 51 and four push rods 522 threaded to the ball sleeve 521. Each push rod 522 is used to adjust the horizontal position of the third ball head 51.
[0039] In this embodiment, the outer diameter of the third ball head 51 is 80mm, and the inner diameter of the ball sleeve 521 is 94mm. The difference in their inner and outer diameters allows the third ball head 51 to be finely adjusted within a certain range on the ball sleeve 521, enabling manual alignment of the ball cup on the conformal fitting during docking. The push rod 522 includes a knurled nut 5221 and a first screw 5222. The first screw 5222 connects to the screw hole of the ball sleeve 521, with one end abutting against the surface of the third ball head 51 and the other end connected to the knurled nut 5221 and positioned by a cylindrical pin 7. When the operator manually rotates the knurled nuts 5221 of each push rod 522 clockwise or counterclockwise, the first screw 5222 drives the third ball head 51 to change its horizontal position. After changing its horizontal position, the knurled nuts 5221 are tightened to fix it in place. It should be understood that the number of push rods 522 can be other numbers, selected according to the positioning accuracy.
[0040] The height adjustment assembly 53 includes a second screw 531 and a screw seat 532 that are threaded together. The screw seat 532 is fixedly mounted on the square rod 11 by a flange. The second screw 531 is movably arranged in the vertical direction and its top end is connected to the mounting plate 533. The ball sleeve 521 of the horizontal pressing assembly 52 is fixed on the mounting plate 533. The third ball head 51 is arranged facing upward and is partially movably arranged in the ball sleeve 521. The third ball head 51 can move horizontally relative to the mounting plate 533.
[0041] Furthermore, to enable the third ball head 51 to be height-adjustable, in one embodiment of this invention, the height adjustment assembly 53 further includes a handle nut 534 threadedly connected to the second screw 531. The handle nut 534 is rotatably connected to the upper end of the screw seat 532 and confined to that position, for example, through a bearing connection. When the operator manually rotates the handle nut 534 clockwise or counterclockwise, the second screw 531 can be driven to rotate upwards or downwards, thereby causing the mounting plate 533 and the third ball head 51 to rise or fall.
[0042] Furthermore, to enable the third ball head 51 to rise or fall more precisely, in one embodiment of this invention, the third ball head assembly 5 further includes a guide assembly 54. The guide assembly 54 includes a guide post 541 connected to the mounting plate 533 and a guide sleeve 542 sleeved around the guide post 541. The guide sleeve 542 is fixed to the square rod 11 by means of tight fit, bolt connection, etc. The guide post 541 can slide within the guide sleeve 542, thereby guiding the mounting plate 533 connected to it to rise or fall together with the second screw 531. Two sets of guide posts 541 and guide sleeves 542 are provided, symmetrically arranged on both sides of the second screw 531, playing a guiding role during the up-and-down adjustment of the third ball head 51 and reducing the shear strength of the screw in the screw seat 532.
[0043] It should be understood that the first ball head 31, the second ball head 41, and the third ball head 51 all have a spherical structure that docks with the cup and a connecting structure that is integrated with the spherical structure. The spherical structure can be selected as any shape with a spherical surface or a hemispherical surface.
[0044] In order to transport the attitude adjustment bracket 100 by crane, in one embodiment of this utility model, four lifting ring assemblies 6 are also included. Each lifting ring assembly 6 includes a lifting ring and a lifting ring seat connected to the lifting ring. The lifting ring seat is fixed to the square rod 11 on the upper part of the frame 1 by bolts. The lifting ring assemblies 6 are roughly distributed at the four corners for lifting the bracket 100.
[0045] Please see Figure 8-10 In one embodiment of this utility model, the attitude adjustment bracket 100 is used in the docking of aircraft components as follows.
[0046] Please refer to the following before use: Figure 8By turning the handle nut 534, the four third docking ball head assemblies 5 on the attitude adjustment bracket 100 are adjusted downward as a whole to avoid interference with the conformal tooling of the aircraft parts during docking, and the top rod 522 of the horizontal clamping assembly 52 is loosened. Before docking, the attitude adjustment bracket 100 is transferred to the docking station by AGV9, and the attitude adjustment bracket 100 is placed in place by observing whether the floor positioning component under the attitude adjustment bracket 100 coincides with the ground positioning mark circle of the station. The movement adjustment of the attitude positioner 8 first connects the ball cup on the conformal fixture of the aircraft component with the second ball head 41 of the second docking ball head assembly 4 on the attitude adjustment bracket 100, and then inserts a locking pin into the ball cup of the conformal fixture to lock the ball head. Tighten the handle nut 534 to adjust the vertical height of the third docking ball head assembly 5, and obtain the range of motion of the ball head by the difference between the outer diameter of the third ball head 51 (80mm) and the inner diameter of the ball sleeve 521 (94mm). With the horizontal clamping assembly 52 in a relaxed state, place the third ball head 51 into the ball cup on the conformal fixture, and then lock the clamping assembly to complete the docking and locking of the conformal fixture and the posture adjustment bracket 100. The attitude adjuster 8 is moved and withdrawn to an area outside the component turnover path range; The AGV9 lifts the overall attitude adjustment bracket 100, and the product, conformal tooling and bracket 100 are transferred to the next assembly station together. At the same time, the ground positioning component under the attitude adjustment bracket 100 is observed to ensure that the bracket 100 is placed in place by observing whether the ground positioning mark circle of the next station coincides. Please see Figure 9 The next station's attitude adjustment locator 8 moves and adjusts to the target position of the attitude adjustment docking ball head, completing the docking of the ball cup 81 on the attitude adjustment locator 8 with the first docking ball head assembly 3 on the attitude adjustment bracket 100, and inserts the positioning pin to complete the locking operation. Finally, in the next assembly station, the product's orientation and positioning function can be achieved by directly adjusting the orientation of the orientation adjustment bracket 100 through the positioner 8.
[0047] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.
[0048] The above embodiments merely illustrate several implementation methods of this application, and their descriptions are relatively specific and detailed. However, they should not be construed as limiting the scope of the utility model patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.
Claims
1. A finely adjustable aircraft component docking and attitude adjustment bracket, comprising a frame (1), characterized in that, Also includes: Multiple ground positioning components (2) are respectively disposed at the bottom of the frame (1), each including a positioning block (21) and a first pad (22) for aligning with the ground positioning mark of the component assembly station so that the bracket enters the target position; Multiple first docking ball head assemblies (3) are respectively disposed in the middle of the frame (1), each including a first ball head (31) and a ball head seat (32) for matching with the ball cup on the attitude adjustment positioner of the component assembly station; Multiple second docking ball head assemblies (4) are respectively disposed on the top of the frame (1), each including a second ball head (41) and a second pad (42) for matching with the ball cup on the conformal tooling of the aircraft component; Multiple third docking ball head assemblies (5) are respectively disposed on the top of the frame (1), each including a third ball head (51), a horizontal clamping assembly (52) and a height adjustment assembly (53), used to manually align the position of the ball cup on the conformal tooling of the aircraft component when the third ball head (51) is docked.
2. The adjustable aircraft component docking and attitude adjustment bracket as described in claim 1, characterized in that, The ground positioning component (2) also includes a first bolt (23) for connecting the cylindrical positioning block (21) and the first pad (22) to the frame.
3. The adjustable aircraft component docking and attitude adjustment bracket as described in claim 1, characterized in that, The first docking ball head assembly (3) also includes a second bolt (33) for connecting the downward-facing first ball head (31) and ball head seat (32) to the frame.
4. The adjustable aircraft component docking and attitude adjustment bracket as described in claim 1, characterized in that, The second docking ball head assembly (4) also includes a third bolt (43) for connecting the upward-facing second ball head (41) and the second pad (42) to the frame.
5. The adjustable aircraft component docking and attitude adjustment bracket as described in claim 1, characterized in that, The horizontal clamping assembly (52) includes a ball sleeve (521) sleeved on the outer periphery of the third ball head (51) and a plurality of push rods (522) threaded to the ball sleeve (521), each of the push rods (522) being used to adjust the horizontal position of the third ball head (51).
6. The adjustable aircraft component docking and attitude adjustment bracket as described in claim 5, characterized in that, The push rod (522) includes a knurled nut (5221) and a first screw (5222) connected to each other.
7. The adjustable aircraft component docking and attitude adjustment bracket as described in claim 1, characterized in that, The height adjustment assembly (53) includes a second screw (531) and a screw seat (532) connected to each other. The top end of the second screw (531) is connected to a horizontally arranged mounting plate (533). The horizontal pressing assembly (52) is located on the mounting plate (533) and the third ball head (51) is arranged facing upward.
8. The adjustable aircraft component docking and attitude adjustment bracket as described in claim 7, characterized in that, The height adjustment assembly (53) also includes a handle nut (534) connected to the second screw (531) for driving the second screw (531) to rotate so that the horizontal clamping assembly (52) rises or falls.
9. The adjustable aircraft component docking and attitude adjustment bracket as described in claim 7, characterized in that, The third docking ball head assembly (5) further includes a guide assembly (54), which includes a guide post (541) connected to the mounting plate (533) and a guide sleeve (542) sleeved on the outer periphery of the guide post (541) to guide the mounting plate (533) to rise or fall.
10. The adjustable aircraft component docking and attitude adjustment bracket as described in claim 1, characterized in that, It also includes multiple lifting ring assemblies (6), which are respectively disposed on the upper part of the frame (1) for lifting the bracket.