CN219524245U - General assembly type frame for small-sized parts of airplane - Google Patents

Abstract

The utility model discloses a general assembly type frame for small parts of an airplane, which comprises a supporting component, a bracket component and a turnover component, wherein the three components are connected with each other in a detachable mode, so that the working difficulty of maintaining the assembly type frame is reduced; the support assembly is used for clamping and positioning small-sized parts of different types of aircrafts, the overturning assembly can directly meet the angle requirement of part assembly in the assembly process, and the supporting assembly can greatly expand the application range of the assembly type frame due to the adjustable height.

Description

General assembly type frame for small-sized parts of airplane

Technical Field

The utility model relates to the field of aircraft assembly equipment, in particular to a general assembly type frame for small parts of an aircraft.

Background

In the current aircraft assembly field, the assembly of the components is an important ring in the whole machine assembly, and the component products are characterized by larger weight, various sizes, wide hole position distribution needing to coordinate assembly and high interchangeability requirement. However, the existing aircraft structure assembly type frames are almost all assembly type frames for large-sized parts, and for small-sized parts of an aircraft, too many types of assembly type frames are needed, and based on the requirement of high cost performance of aircraft assembly, assembly work of the small-sized parts of the aircraft is mainly completed by a plurality of operators. And only the assembly of small parts of the aircraft is completed manually, so that the defect of insufficient assembly precision of the parts is easily caused. Therefore, how to meet the high cost performance of aircraft assembly and solve the problem of insufficient assembly precision in manual operation is needed to be solved.

Disclosure of Invention

The utility model aims to overcome the defect that the high cost performance cannot be met when the assembly precision is improved by adopting an assembly type frame in the assembly process of the small-sized parts of the airplane due to the excessive types of the needed type frame in the assembly process of the small-sized parts of the airplane in the prior art, and provides the general assembly type frame for the small-sized parts of the airplane.

The aim of the utility model is mainly realized by the following technical scheme:

the utility model provides a general assembly type frame of small-size spare part of aircraft, includes the support subassembly, the support subassembly includes first locating plate and second locating plate, first locating plate connects the second locating plate is the inside casing, first locating plate with the detachable connection of second locating plate; the second positioning plate is provided with a plurality of rotary openings, and the rotary openings are provided with clamping positioners in a rotary way: the clamping positioner is used for positioning and clamping the small-sized parts of the airplane on the second positioning plate.

At present, the assembly of the small parts of the airplane is finished in a manual mode, but the assembly of the small parts of the airplane is not a simple working process, and the problem of lower assembly precision is easy to occur only by manual operation; in order to ensure the service life of the aircraft, the precision requirement of each part installation in the aircraft assembly process needs to be met. For the assembly of an aircraft, once the positioning reference between the aircraft parts and the assembly fixture deviates, an uncoordinated phenomenon can occur, so that the problems of reduced performance and reduced structural stability of the aircraft occur; however, as the small-sized parts of the airplane have the characteristics of multiple sizes and multiple types, the assembly fixture matched with the small-sized parts of various types of airplanes is required to be designed according to the traditional assembly frame to meet the assembly of the small-sized parts of the airplane, so that the cost in the assembly process of the airplane is greatly increased, and the assembly requirement of the airplane with high cost performance cannot be met.

In the embodiment of the utility model, under the condition that the assembly type frame is adopted to improve the assembly precision, in order to meet the requirement of high cost performance of the assembly of small parts of an airplane, the assembly type frame comprises a bracket component, the bracket component comprises a second positioning plate, and the second positioning plate is provided with a plurality of rotating ports which are used for clamping a positioner in a rotating way; therefore, the positioning and clamping device can be arranged in different forms according to the types of small parts of the airplane, so that the clamping, positioning and assembling work requirements of the small parts of the airplane of multiple types are met; in addition, for the assembly of the small-sized parts of the same type of aircraft, the assembly type frame can enable the errors of the parts of the same type to be smaller and the precision to be more accurate in the assembly process. The bracket assembly further comprises a first positioning plate, and the first positioning plate is fixedly connected with the second positioning plate, so that the first positioning plate can support the second positioning plate; therefore, the probability of deformation of the second positioning plate caused by overweight of small parts of the aircraft in the assembly process can be reduced; in the embodiment of the utility model, the second positioning plate is screwed and clamped with the positioner in a mode of arranging the screwed ports, the screwed ports formed in the second positioning plate are limited, and in order to improve the application range of the assembly type frame, the first positioning plate and the second positioning plate are connected in a detachable mode; therefore, when more parts of different types are required to be assembled, the assembly can be realized by directly replacing the second positioning plate, and the manufacturing cost of the aircraft is greatly reduced; and as the important part that presss from both sides tight location to small-size spare part of aircraft, the second locating plate is heavier in assembly process degree of wear, first locating plate with detachable the connection between the second locating plate can simplify the periodic maintenance work of second locating plate, thereby improves the life of assembly type frame.

Further, the clamping positioner comprises an end face spiral clamping device, a frame appearance positioning pressing device and a frame appearance positioning device, wherein the frame appearance positioning device is used for clamping and positioning small-sized parts of the airplane on the first positioning plate, the frame appearance positioning pressing device is used for propping against the small-sized parts of the airplane to be fixed on the first positioning plate, and the end face spiral clamping device is used for screwing the small-sized parts of the airplane to be tightly attached to the first positioning plate.

In the embodiment of the utility model, in order to ensure that the clamping and positioning of the bracket assembly to the small-sized parts of the aircraft reach the precision meeting the assembly work, the clamping and positioning device comprises a frame shape positioning device; the frame shape positioner has the function of clamping and fixing the small-sized parts of the airplane; therefore, the small parts of the airplane can be quickly and accurately fixed on the inner frame. Because the frame appearance positioner can only ensure that the small-sized parts of the airplane cannot slip from the inner frame in the assembly process, a plurality of end face spiral clamping devices are further arranged on the inner frame in order to ensure the assembly precision; the end face spiral clamp penetrates through the inner frame and is provided with an adjustable bolt, and the compression and the positioning of the small-sized parts of the airplane on the inner frame can be adjusted by rotating the adjustable bolt. The clamping positioner further comprises a plurality of frame shape positioning compactors, wherein adjustable fastening bolts and clamping grooves are arranged on the frame shape positioning compactors, and the adjustable fastening bolts are used for propping against edges of parts. The outer edge of the small-sized aircraft part is clamped through the clamping groove, and then the adjustable fastening bolt is rotated to abut against the small-sized aircraft part; in this way, the aircraft small parts can be brought into close contact with the inner frame, and the degree of deformation during assembly can be controlled within a prescribed tolerance range. Thus, by matching the clamping positioners, the precision of the small parts of the airplane in the assembly process is ensured.

Further, an outer frame is arranged on the outer side of the inner frame, and the outer frame is fixedly connected with the inner frame.

In the embodiment of the utility model, in order to further ensure the precision of the clamping and positioning work of the bracket component on the small-sized parts of the airplane, the outer side of the inner frame is also provided with the outer frame, and the outer frame is used as a fixing component to be connected with the inner frame, so that the stability of the inner frame on the clamping and positioning work of the small-sized parts of the airplane with larger weight is further improved; therefore, the application range of the assembly type rack is improved.

Further, the assembly type frame further comprises a turnover assembly, wherein the turnover assembly is provided with a plurality of turnover side faces, and any one of the turnover side faces is connected with the outer side face of the outer frame.

In the embodiment of the utility model, the assembly type frame can adapt to the assembly of small parts of various types of airplanes, and in the installation process, the angle of the assembly type frame needs to be adjusted in order to ensure the assembly precision of the small parts of the airplanes during the assembly. Because the assembly work of the small-sized parts of the airplane cannot be completed quickly, the assembly work of the small-sized parts of the airplane is completed manually in the traditional assembly mode, so that the assembly difficulty of the small-sized parts of the airplane is increased. In the embodiment of the utility model, the assembly type frame further comprises a turnover assembly, the turnover assembly can drive the bracket assembly to turn over, and when the angle is adjusted, the turnover assembly is only required to be fixed, so that the fixed maintenance of the assembly angle can be realized, the work flow of the assembly of small parts of the aircraft is simplified, and the assembly precision is ensured.

Further, the overturning assembly comprises a worm gear device, and a connecting rod is arranged on an output shaft of the worm gear device; the connecting rod is provided with a locating plate, and the locating plate is fixedly connected with the outer frame through bolts.

After the angle of the assembly type frame is adjusted, the probability of occurrence of the problem of reduced assembly precision of small parts of the aircraft in the assembly process is reduced in order to reduce the change of the angle of the assembly type frame caused by false collision; in the embodiment of the utility model, the overturning assembly comprises a worm gear device with a self-locking function, a connecting rod is arranged on an output shaft of the worm gear device, and a positioning plate is arranged on the connecting rod. When the embodiment of the utility model is applied, the positioning plate is connected with the outer frame, and the bracket component rotates along with the overturning component; when the rotating angle enables the assembly type rack to meet the assembly requirement of the small-sized parts of the airplane, the assembly angle is kept through the self-locking function of the worm gear device, and the assembly precision of the small-sized parts of the airplane is ensured.

Further, the turnover assembly further comprises a rotating handle, and the rotating handle is installed on a worm of the worm gear and worm device: the rotating handle is used for driving the worm to rotate.

In order to reduce the operation difficulty of rotating the overturning assembly, a rotating handle is arranged on the worm; because the worm is a rod piece, the grip of the rotary handle can provide better force application effect and larger operation space than the worm in the rotating process; therefore, when the turnover assembly is applied, the worm can be directly driven to rotate by directly applying force to the rotating handle, so that the operation difficulty of rotation of the turnover assembly is greatly reduced.

Further, the assembly type rack further comprises a supporting component, wherein the supporting component comprises a supporting column, and the supporting column is detachably connected with the bracket component.

In the embodiment of the utility model, in order to improve the application range of the assembly type frame and simplify the assembly work of small parts of the high aircraft, the assembly type frame for the small parts of the aircraft further comprises a support component which is detachably connected with the bracket component; thus, when the small parts of the high-altitude airplane are required to be assembled, the supporting components with different heights can be directly replaced.

Further, the device also comprises a support assembly, wherein the support assembly comprises a support column; the overturning assembly is provided with a base which is used for fixedly supporting the worm gear device; the support column detachably connects in the base, the upset subassembly with the support subassembly is detachable connection.

In the assembly process, as the turnover assembly is required to be continuously coordinated with the bracket assembly to finish the work, in order to avoid the reduction of the service life of the assembly type rack caused by excessive abrasion of the turnover assembly, the turnover assembly is required to be maintained regularly, and the turnover assembly is detachably connected with the bracket assembly, so that the maintenance and repair work of the turnover assembly can be simplified.

Further, the support assembly further comprises a flange plate, and the flange plate is installed at the bottom of the support column; the flange plate is fixedly connected with the support column through a threaded rod piece; the threaded rod piece is provided with a nut, and the nut is tightly attached to the supporting column: the nut is used for adjusting the distance between the flange plate and the support column.

In order to improve the support stability of the support column, a flange plate is arranged at the bottom of the support column and is connected with the support column through a threaded rod piece, so that the stability of the support column is further improved through the flange plate. In the embodiment of the utility model, in order to improve the stability of the threaded rod piece on the connection of the support column and the flange, the threaded rod piece is also provided with a nut, and the nut can be screwed in and screwed out to adjust the height between the support rod and the flange, so that the height of the support component is adjustable, and the application range of the assembly type frame is enlarged.

Further, a plurality of tool balls are arranged on the outer frame.

In order to accurately position the assembly position of the small-sized parts of the airplane, so that errors generated in the assembly process are reduced, and the outer frame is provided with a tool ball; the tool spheroidization is matched with the auxiliary of the computer to carry out data processing on the assembly information of the small-sized parts of the airplane, so that the assembly position of the small-sized parts of the airplane is accurately positioned.

In summary, compared with the prior art, the utility model has the following beneficial effects: the small-size spare part assembly type frame of aircraft, including supporting component, bracket component and upset subassembly triplex, triplex are detachable connection each other, when the part damages, can realize in time changing, maintenance each spare part's purpose, have improved the utilization ratio of each part of assembly type frame has avoided the waste of assembly resource. The height of the supporting component can be adjusted through the flange plate arranged on the supporting component, so that the application range of the assembly type rack is increased; in addition, the bracket component comprises a replaceable second positioning plate, and the second positioning plate can meet the spin-mounting of different types and numbers of clamping positioners through the arrangement of different spin ports; the overturning assembly has a self-locking function, can stably maintain the assembly angle of the assembly type frame, and improves the assembly precision of the assembly type frame to small parts of the aircraft.

Drawings

The accompanying drawings, which are included to provide a further understanding of embodiments of the utility model and are incorporated in and constitute a part of this specification, illustrate embodiments of the utility model and together with the description serve to explain the principles of the utility model. In the drawings:

FIG. 1 is a schematic view of the overall structure of an assembled rack according to the present utility model;

FIG. 2 is a schematic view of a bracket assembly according to the present utility model;

FIG. 3 is a left side view of the fabricated bracket of the present utility model;

fig. 4 is an overall top view of the fabricated bracket of the present utility model.

The names corresponding to the reference numerals are: 1. a support assembly; 2. a bracket assembly; 3. a flip assembly; 4. a support column; 5. an outer frame; 6. an inner frame; 7. a first positioning plate; 8. a second positioning plate; 9. a flange plate; 10. a nut; 11. a worm gear device; 12. rotating the handle; 13. a connecting rod; 14. a positioning plate; 15. a tool ball; 16. an end face screw clamp; 17. a frame profile positioning compactor; 18. a frame profile locator; 19. and (5) a base.

Detailed Description

For the purpose of making apparent the objects, technical solutions and advantages of the present utility model, the present utility model will be further described in detail with reference to the following examples and the accompanying drawings, wherein the exemplary embodiments of the present utility model and the descriptions thereof are for illustrating the present utility model only and are not to be construed as limiting the present utility model.

Examples:

as shown in fig. 1 to 4, in this embodiment, the assembly type rack includes a bracket assembly 2, the bracket assembly 2 includes a first positioning plate 7 and a second positioning plate 8, a plurality of screw openings are provided on the second positioning plate 8, and a plurality of positioning clamps are screwed on the screw openings; the first positioning plate 7 is connected with the second positioning plate 8 to form an inner frame 6, and the first positioning plate 7 is detachably connected with the second positioning plate 8. One of the application scenarios of this embodiment is the assembly of small-sized parts of an irregular aircraft, in order to meet the stability of the connection between the first positioning plate 7 and the second positioning plate 8, and avoid the difficulty in manufacturing the assembly frame from increasing, the inner frame 6 should not increase too much weight; so, first locating plate 7 with all be equipped with the bolt hole on the second locating plate 8, through the bolt run through the mode of bolt hole, first locating plate 7 with can both realize the detachable connection of stronger stability between the second locating plate 8, can simplify again the replacement work of second locating plate 8. In addition, when the second positioning plate 8 clamps and positions the small-sized parts of the aircraft, because the weight of the small-sized parts of the aircraft is large, the bracket assembly 2 further comprises a first positioning plate 7, and the second positioning plate 8 is supported by the first positioning plate 7, so that the second positioning plate 8 is not easy to deform in the assembly process, and the smooth performance of the assembly work of the small-sized parts of the aircraft is ensured. When the present embodiment is applied, since the small-sized parts of the assembled aircraft are not always regular, in order to expand the application range of the assembled frame, the inner frame 6 may be in a hollow form; so, small-size spare part of aircraft can be better with inside casing 6 laminating, the application scope greatly increased of assembly type frame.

In this embodiment, in order to avoid the small-sized aircraft component from slipping along the surface of the first positioning plate 7 during the assembly process, a plurality of screw openings are provided at the edge of the second positioning plate 8, the screw openings are screwed with the frame shape locators 18, and the frame shape locators 18 are engaged with the small-sized aircraft component, so as to achieve the purpose of preventing the small-sized aircraft component from slipping; in order to improve the assembly precision, the clamping positioner further comprises an end face spiral clamping device 16 which enables the small-sized parts of the airplane to be more attached to the inner frame 6, the end face spiral clamping device penetrates through the inner frame 6, and after the frame appearance positioner 18 is used for clamping and fixing the small-sized parts of the airplane, due to the fact that an adjustable bolt is arranged on the end face spiral clamping device 16, the purpose that the small-sized parts of the airplane are integrally attached to the inner frame 6 can be achieved through rotation of the bolt. In order to further improve the stability of the fixing of the small-sized parts of the aircraft on the inner frame 6, a frame shape positioning compactor 17 is further arranged at the edge of the inner frame 6, and the frame shape positioning compactor 17 is provided with an adjustable fastening bolt and a clamping groove; when the small-sized parts of the airplane are clamped into the clamping grooves to be clamped on the inner frame 6, the adjustable fastening bolts are rotated to enable the small-sized parts of the airplane to be abutted against the inner frame 6, so that deformation and position offset of the small-sized parts of the airplane in the assembly process can be kept within a tolerance range. Furthermore, in order to further improve the assembly precision of the assembly type frame for small parts of the aircraft, in this embodiment, a level gauge may be further disposed on the frame shape positioning presser 17; the level gauge is used for monitoring whether the rotation of the frame appearance positioning compactor 17 is correct or not, so that the probability of wrong rotation of the frame appearance positioning compactor 17 can be reduced, and the precision of the assembly type frame on the assembly of the small-sized parts of the airplane is improved.

In this embodiment, the bracket assembly 2 further includes an outer frame 5, and the outer frame 5 is fixedly connected to the inner frame 6; when the inner frame 6 clamps and positions the small-sized parts of the airplane with larger weight, the inner frame 6 can realize more stable support on the small-sized parts of the airplane under the support action of the outer frame 5, and the deformation degree of the inner frame 6 is reduced, so that the clamping and positioning precision degree of the inner frame 6 on the small-sized parts of the airplane is improved.

In this embodiment, the assembly rack further comprises a turnover component 3, wherein the turnover component 3 has a plurality of turnover sides; the overturning assembly 3 is fixedly connected with the bracket assembly 2, and any speed overturning side surface of the overturning assembly 3 is connected with the outer frame 5; through the connection of the overturning side face and the outer frame 5, the purpose that the overturning assembly 3 drives the support assembly 2 to overturn can be achieved, and the difficulty of angle adjustment work of small parts of the airplane in assembly work is reduced.

In this embodiment, in order to meet the fixing of the angle required for assembly, the overturning assembly 3 comprises a worm gear device 11; after the assembly angle is adjusted, as the worm gear device 11 has a self-locking function, the bracket component 2 can stably maintain the angle required by the assembly of the small-sized parts of the aircraft through the self-locking function of the overturning component 3, so that the probability of error generation in the assembly work is reduced; the worm gear device 11 comprises a connecting rod 13 arranged on an output shaft, and a positioning plate 14 arranged on the connecting rod 13 is connected with the bracket assembly 2; the positioning plate 14 and the bracket assembly 2 can be detachably connected in a bolt manner, so that the difficulty in maintenance work of the turnover assembly 3 and the bracket assembly 2 can be reduced; in the assembly process, the bracket component 2 is driven to rotate through the connecting rod 13, the assembly type frame can realize accurate adjustment of different assembly angles of small parts of multiple types of airplanes, and the application range of the assembly type frame is greatly increased. In order to further reduce the operation difficulty of the overturning assembly 3 for angle adjustment, the model of the worm gear device 11 can be a worm gear reducer with an NRV50 model; because the assembly precision requirement of the small parts of the aircraft is higher, when the angle of the bracket assembly 2 is excessively changed due to normal rotation of the connecting rod 13, the adjustment work difficulty of an operator for a small angle is higher, and the error of the overturning angle of the bracket assembly 2 can be kept in a smaller range even if the angle of the connecting rod 13 is larger due to the arrangement of the worm gear reducer of the NRV50 model in the assembly process; therefore, the angle adjusting work difficulty of the assembly type rack is reduced. In addition, the worm of the worm gear and worm device 11 is sleeved with a rotary handle 12, the rotary handle 12 is simpler than the worm in operability, and the turnover assembly 3 can achieve the effect of labor-saving rotation by directly using the rotary handle 12.

In this embodiment, the assembly type stand may be used by means of manual assistance or lifting; in order to reduce the difficulty of the assembly work of the small parts of the aircraft and achieve high cost performance of the aircraft manufacture, the assembly frame also comprises a supporting component 1; the support assembly 1 is used for supporting the bracket assembly 2, and the support assembly 1 comprises a support column 4; the support columns 4 may be square tubes of 120 x 80 for the assembly work of small parts of an aircraft, to ensure the rigidity and rigidity of the support assembly 1. In order to meet the assembly precision of the small parts of the airplane, the assembly type frame is required to be adjusted in height according to the assembly requirement, and the support component 1 is detachably connected with the support component 2, so that the adjustment of the assembly type frame height can be achieved by replacing the support components 1 with different heights.

In another specific implementation of this embodiment, the assembly type rack includes a turnover component 3, a support component 1 and a bracket component 2, where the turnover component 3 is located between the support component 1 and the bracket component 2; because the overturning assembly 3 needs to be overturned to meet the requirement of the assembly angle of small parts of the aircraft, the worm gear 11 in the overturning assembly 3 can be worn due to long-term operation; thus, the turnover assembly 3 needs to be maintained regularly, and the turnover assembly 3 is detachably connected with the bracket assembly 2. In addition, the turnover assembly 3 is provided with a base 19 for fixedly supporting the worm gear device 11, and the support column 4 is detachably connected with the base 19.

In this embodiment, the support assembly 1 further includes a flange 9, where the flange 9 and the support column 4 are fixed by a threaded rod, and in this embodiment, the threaded rod may be a 45 steel member with threads; the flange 9 is installed at the bottom of the support column 4, and the flange 9 is used for further improving the stability of the support column 4. The flange 9 can be a 45 steel disc, the contact area between the disc and the ground is large, the stability is good, and the support assembly 2 can be well supported and fixed. In this embodiment, the threaded rod is provided with a nut 10, and the nut 10 is tightly attached to the support column 4. By adjusting the nut 10, a change in the distance between the flange 9 and the support column 4, i.e. an adjustability of the height of the support assembly 1, can be achieved.

In this embodiment, due to the assembly of the aircraft parts, the assembly jig also needs to accurately position the assembly position of the small aircraft parts; therefore, the tool ball 15 is arranged on the outer frame 5, and the tool ball 15 is assisted with the information data calculation of a computer, so that the accurate positioning of the assembly position of the small-sized parts of the airplane can be realized.

The foregoing description of the embodiments has been provided for the purpose of illustrating the general principles of the utility model, and is not meant to limit the scope of the utility model, but to limit the utility model to the particular embodiments, and any modifications, equivalents, improvements, etc. that fall within the spirit and principles of the utility model are intended to be included within the scope of the utility model.

Claims (10)

1. The utility model provides a general assembly type frame of small-size spare part of aircraft, includes support subassembly (2), its characterized in that, support subassembly (2) include first locating plate (7) and second locating plate (8), first locating plate (7) with second locating plate (8) fixed connection constitutes inside casing (6), first locating plate (7) with second locating plate (8) are detachable connection; the second locating plate (8) is provided with a plurality of rotary openings, and the rotary openings are provided with clamping locators in a rotary mode: the clamping positioner is used for positioning and clamping the small-sized parts of the airplane on the second positioning plate (8).

2. The universal assembly jig for small aircraft parts according to claim 1, wherein the clamping positioner comprises an end face screw clamping device (16), a frame shape positioning pressing device (17) and a frame shape positioning device (18), the frame shape positioning device (18) is used for clamping and positioning the small aircraft parts on the first positioning plate (7), the frame shape positioning pressing device (17) is used for pressing the small aircraft parts on the first positioning plate (7), and the end face screw clamping device (16) is used for screwing and pressing the small aircraft parts against the first positioning plate (7).

3. The universal assembly type frame for small parts of an aircraft according to claim 1, wherein an outer frame (5) is arranged on the outer side of the inner frame (6), and the outer frame (5) is fixedly connected with the inner frame (6).

4. A universal assembly jig for small parts of an aircraft according to claim 3, further comprising a turnover assembly (3), wherein the turnover assembly (3) has a plurality of turnover sides, any one of which is connected to an outer side of the outer frame (5).

5. The universal assembly type frame for small parts of an aircraft according to claim 4, wherein the overturning assembly (3) comprises a worm gear device (11), and a connecting rod (13) is arranged on an output shaft of the worm gear device (11); the connecting rod (13) is provided with a locating plate (14), and the locating plate (14) is fixedly connected with the outer frame (5) through bolts.

6. The universal assembly jig for small parts of an aircraft according to claim 5, wherein the turnover assembly (3) further comprises a rotating handle (12), the rotating handle (12) being mounted on a worm of the worm gear (11): the rotary handle (12) is used for driving the worm to rotate.

7. A general assembly jig for small parts of an aircraft according to any one of claims 1 to 3, further comprising a support assembly (1), wherein the support assembly (1) comprises a support column (4), and the support column (4) is detachably connected with the support assembly (2).

8. The universal assembly type frame for small parts of an aircraft according to any one of claims 5 to 6, further comprising a supporting component (1), wherein the supporting component (1) comprises a supporting column (4); a base (19) is arranged on the overturning assembly (3), and the base (19) is used for fixedly supporting the worm gear device (11); the support column (4) is detachably connected to the base (19), and the overturning assembly (3) is detachably connected with the support assembly (2).

9. The universal assembly jig for small parts of an aircraft according to claim 8, wherein the supporting assembly (1) further comprises a flange plate (9), and the flange plate (9) is mounted at the bottom of the supporting column (4); the flange plate (9) is fixedly connected with the support column (4) through a threaded rod piece; the threaded rod piece is provided with a nut (10): the nut (10) is used for adjusting the distance between the flange plate (9) and the support column (4).

10. A universal assembly jig for small parts of an aircraft according to claim 3, wherein the outer frame is provided with a plurality of tool balls (15).