A clamping tool for fuselage assembly in light aircraft maintenance operations

Abstract

The application discloses a clamping tool for fuselage assembly in light aircraft maintenance operation, and relates to a fuselage assembly device of light aircraft, which comprises a rack and a fuselage clamping mechanism. A plurality of roller assemblies are arranged on the rack, the fuselage clamping mechanism is provided with a plurality of rolling rings and a plurality of fuselage clamping assemblies connected in series with the rolling rings. Each rolling ring is located on each group of roller assemblies in one-to-one correspondence, and adjacent two rolling rings are connected as a whole through a plurality of supporting rods. Each group of fuselage clamping assemblies is detachably fixed to the inner ring of the rolling ring, and each group of fuselage clamping assemblies connects the rolling rings in series. The fuselage to be assembled is detachably connected with each group of fuselage clamping assemblies and is detachably fixed in each rolling ring by each group of fuselage clamping assemblies, and each rolling ring can rotate circumferentially on the roller assembly. The application can provide stable support for the fuselage and realize the overturning function, can adjust the angle according to the working condition, realize multi-angle operation on the fuselage, and improve the flexibility and convenience.

Description

Technical Field

[0001] This invention relates to assembly equipment for light aircraft fuselages, specifically, to a clamping fixture for fuselage assembly in light aircraft maintenance operations. Background Technology

[0002] Light aircraft typically have a fuselage length of 6–8 meters, a height of 2.3–2.8 meters, a wingspan of 8–11 meters, an empty weight of 350–500 kg, and 2–6 seats. They are common private and training aircraft, such as the Cecessa 172 or PA-44-180. During their service life, repairs of these aircraft do not require the specialized docking stations of larger aircraft like Boeing and Airbus, resulting in lower technical requirements for maintenance facilities and spaces.

[0003] The applicant previously disclosed a work platform applicable to the maintenance of small general aviation aircraft fuselages. Please refer to the Chinese patent document entitled "A Work Platform for the Maintenance of Small General Aviation Aircraft Fuselage," publication number CN219705077U, published on September 19, 2023. In this technology, a height-adjustable and relatively displaceable base frame serves as the supporting foundation for the fuselage to be maintained. The fuselage is clamped and fixed to a corresponding, slidable clamping mechanism on top of the base frame to facilitate maintenance. However, during the assembly and maintenance process, the clamping mechanism can only achieve lateral displacement and cannot be rotated. When working on different parts of the fuselage, operators need to frequently relocate, and sometimes even climb ladders to ascend the fuselage. This demonstrates poor flexibility and convenience during operation, resulting in low maintenance efficiency and increased technical difficulty. Summary of the Invention

[0004] This invention provides an assembly and maintenance device for light aircraft fuselages, in order to solve the technical problem that the existing fuselage assembly and maintenance work platforms have poor flexibility and convenience.

[0005] The technical solution adopted in this invention is as follows: A clamping fixture for fuselage assembly in light aircraft maintenance operations includes a frame and a fuselage clamping mechanism mounted on the frame. On the frame, corresponding to the longitudinal direction of the fuselage, multiple sets of roller assemblies are arranged at intervals along a front-to-back sequence, with each set consisting of two roller assemblies arranged horizontally. The fuselage clamping mechanism, corresponding to the multiple sets of roller assemblies on the frame, has multiple rolling rings and multiple sets of fuselage clamping assemblies connected in series with each rolling ring. Each rolling ring of the fuselage clamping mechanism is located one-to-one on each set of roller assemblies on the frame, adjacent to each other. The two rolling rings are connected as a whole by multiple support rods arranged around the circumference; each set of body clamping components of the body clamping mechanism is detachably fixed to the inner ring of the rolling ring in a circumferential distribution, and each set of body clamping components connects the rolling rings together; the body to be assembled is detachably connected to each set of body clamping components of the body clamping mechanism, and is detachably fixed in each rolling ring of the body clamping mechanism by each set of body clamping components, and each rolling ring of the body clamping mechanism can rotate circumferentially on the roller assembly of the frame.

[0006] The aforementioned technical measures fix the machine body onto the machine body clamping mechanism through a machine body clamping assembly that is detachably connected to the machine body and the rolling ring. By generating a circumferentially rotating rolling ring on the roller assembly of the frame, a flipping function is achieved while providing stable support for the machine body. The angle can be adjusted according to different working conditions, enabling multi-angle inspection and operation of the machine body, improving flexibility, convenience, and work efficiency.

[0007] Furthermore, the inner ring of each rolling ring of the body clamping mechanism has a radially convex limiting ring, and the circumferential spacing of the limiting ring is provided with several limiting holes. The body clamping assembly of the body clamping mechanism has a slide rod, and multiple sets of limiting sliders are slidably mounted on the outer side of the slide rod. Each set of limiting sliders has an annular groove through which the limiting ring can be inserted, and the limiting slider has at least one hole that passes through the annular groove and matches the limiting hole of the limiting ring. Multiple sets of body connecting pins are slidably mounted on the inner side of the slide rod. The fuselage clamping assembly is detachably connected to the fuselage to be assembled via a set of fuselage connecting pins on the inner side. The fuselage clamping assembly is detachably connected to the limiting ring of the corresponding inner ring of the rolling ring via each set of limiting sliders on the outer side.

[0008] The above-mentioned technical measures achieve detachable connection through the cooperation of limit slider and limit ring, which improves flexibility and convenience. The machine body connecting pin is detachably connected to the machine body to be assembled, which enables the machine body and the machine body clamping component to be quickly connected and separated, improving the flexibility and convenience of the clamping mechanism.

[0009] Furthermore, the inner side of the slide rod of the body clamping assembly is provided with a recessed groove, and each set of body connecting pins is slidably assembled in the groove on the inner side of the slide rod; and a number of limiting holes connecting the inner and outer sides are provided at intervals in the groove of the slide rod, and the body connecting pin and / or the limiting slider at the current connection position is blocked and limited by the limiting pin connected in the corresponding limiting hole on the slide rod.

[0010] The above-mentioned technical measures, by setting a sliding groove on the inner side of the slide bar, allow the body connecting pin to move flexibly within the sliding groove, thereby achieving flexible position adjustment and improving flexibility. At the same time, by setting a limiting hole and a limiting pin, the movement of the body connecting pin and the limiting slider is restricted, thereby improving stability.

[0011] Furthermore, the clamping fixture also includes a rolling drive mechanism, which is used to generate a driving force for the circumferential rotation of the rolling ring of the machine body clamping mechanism; The rolling drive mechanism includes a motor, a drive shaft, multiple sets of sprockets, and multiple sets of chains; Each set of chains is circumferentially assembled corresponding to each rolling ring of the fuselage clamping mechanism; The motor is fixed on the frame, and the output shaft of the motor is connected to the transmission shaft; The drive shaft is supported longitudinally on the frame by multiple sets of bearings arranged at intervals; Each set of sprockets corresponds to the chain fitted to each rolling ring of the body clamping mechanism and is connected in series on the drive shaft.

[0012] The above-mentioned technical measures, by setting up a rolling drive mechanism, enable the circumferential rotation drive of the rolling ring through the coordinated work of the motor, drive shaft, sprocket and chain. Through motor control, the effect of saving labor is achieved and the level of automation is improved.

[0013] Furthermore, the body clamping mechanism also has multiple drive rings, each drive ring forming a one-to-one pairing relationship with each rolling ring, and the one-to-one pairing drive rings are axially connected to the side of the rolling rings. Correspondingly, each set of chains of the rolling drive mechanism is circumferentially assembled in the corresponding drive ring.

[0014] The above-mentioned technical measures, through the cooperation of each drive ring and rolling ring, reduce the complexity and possibility of errors in the operation process, and help improve accuracy and production efficiency.

[0015] Furthermore, the chain of the rolling drive mechanism is composed of a chain body and screw joints at both ends; Correspondingly, two fixed end plates are arranged at intervals inside the drive ring, and each fixed end plate has a through hole for the screw connector to pass through. The chain, which is circumferentially assembled in the corresponding drive ring, is fitted onto the fixed end plate in the drive ring by screw joints at both ends, and is adjusted and locked by nuts.

[0016] The above-mentioned technical measures are implemented by threading the screw joint onto the fixed end plate and adjusting the chain tension with a nut. The nut allows for easy adjustment of the chain tension, ensuring proper fit between the chain and the drive ring. This reduces errors caused by chain slack or over-tightness, improves connection stability, and reduces the possibility of chain loosening during use.

[0017] Furthermore, between the paired drive ring and the rolling ring, a limiting ring is used to connect the radially inwardly convex ring.

[0018] The above-mentioned technical measures enhance structural stability by connecting a limiting ring between the drive ring and the rolling ring.

[0019] Furthermore, the frame has two longitudinal beams and two end beams. The two longitudinal beams are arranged along the longitudinal direction of the fuselage, and the two end beams connect the two longitudinal beams into a whole at both ends. The frame has a frame structure. The roller assemblies on the frame are arranged on the top side of the two longitudinal beams, with the two roller assemblies of each group arranged symmetrically on the two longitudinal beams. The frame structure of the above-mentioned technical measures is simple. The connection between the end beams and the longitudinal beams enhances the stability of the frame. The roller assembly is arranged symmetrically on the two longitudinal beams, which helps to maintain the balance of the frame during use and reduces stress concentration caused by asymmetry.

[0020] Furthermore, the roller assembly includes a roller support and a roller body, the roller support being connected to the longitudinal beam with an upwardly protruding structure, and the top of the roller support having an inwardly sloping structure; The roller body is detachably connected to the top of the corresponding roller support, and each roller body is arranged obliquely inward on the frame structure of the machine frame.

[0021] The roller assembly described above has a simple structure, which, while meeting structural strength requirements, helps to reduce weight and material usage. Each roller body is arranged obliquely inwards on the frame structure, which enhances stability.

[0022] Furthermore, the frame has protruding support bases around its perimeter, and each support base is connected to anchor bolts.

[0023] The support base in the above technical measures has a simple structure, which helps to reduce weight and material usage while meeting structural strength requirements.

[0024] One or more technical solutions provided by this invention have at least the following technical effects or advantages: This invention uses a body clamping assembly that is detachably connected to the body and the rolling ring to fix the body onto the body clamping mechanism. By generating a circumferentially rotating rolling ring on the roller assembly, it provides stable support for the body while achieving a flipping function. The angle can be adjusted according to different working conditions, enabling multi-angle inspection and operation of the body, improving flexibility, convenience, and work efficiency. Attached Figure Description

[0025] The accompanying drawings, which are provided to further illustrate embodiments of the invention and constitute a part of this invention, are not intended to limit the scope of the invention. Figure 1 This is a schematic diagram of the structure of the present invention in use; Figure 2 This is a schematic diagram of the frame structure of the present invention (with the roller body removed). Figure 3 This is a schematic diagram of the fuselage clamping mechanism and roller body structure of the present invention (with the fuselage clamping components removed). Figure 4 This is a schematic diagram of the rolling drive mechanism of the present invention; Figure 5 This is a schematic diagram of the fuselage clamping assembly structure of the present invention; Figure 6 This is a partially enlarged structural diagram of the fuselage clamping assembly of the present invention; Figure 7 This is a schematic diagram of the structure of the fuselage clamping assembly of the present invention when connected to the fuselage; Among them, 1-frame; 11-support base; 12-longitudinal beam; 13-end beam; 14-roller support; 15-roller body; 16-roller assembly; 17-anchor bolt; 2-rolling drive mechanism; 21-motor; 22-drive shaft; 23-sprocket; 24-screw joint; 25-chain; 3-body clamping mechanism; 31-rolling ring; 32-limiting ring; 33-support rod; 34-fixed end plate; 35-drive ring; 36-slide rod; 37-limiting slider; 38-body connecting pin; 39-slide groove; 310-limiting pin; 4-body. Detailed Implementation

[0026] To better understand the above-mentioned objectives, features, and advantages of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that, where there is no conflict, the embodiments of the present invention and the features thereof can be combined with each other.

[0027] Many specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways different from those described herein, and therefore the scope of protection of the invention is not limited to the specific embodiments disclosed below.

[0028] Reference Figure 1-3 This embodiment provides a clamping fixture for fuselage assembly in light aircraft maintenance operations, including a frame 1 and a fuselage clamping mechanism 3 mounted on the frame 1; multiple sets of roller assemblies 16 are arranged in a front-to-back sequence along the longitudinal direction of the fuselage 4 on the frame 1, with each set of roller assemblies 16 consisting of two rollers arranged in a left-to-right position; the fuselage clamping mechanism 3, corresponding to the multiple sets of roller assemblies 16 on the frame 1, has multiple rolling rings 31 and multiple sets of fuselage clamping assemblies connected in series with each rolling ring 31; each rolling ring 31 of the fuselage clamping mechanism 3 is located one-to-one on each set of roller assemblies 16 on the frame 1. Two adjacent rolling rings 31 are connected as a whole by multiple support rods 33 arranged around the circumference; each set of body clamping components of the body clamping mechanism 3 is detachably fixed to the inner ring of the rolling ring 31 in a circumferential distribution, and each set of body clamping components connects each rolling ring 31 together; the body 4 to be assembled is detachably connected to each set of body clamping components of the body clamping mechanism 3, and is detachably fixed in each rolling ring 31 of the body clamping mechanism 3 by each set of body clamping components, and each rolling ring 31 of the body clamping mechanism 3 can rotate circumferentially on the roller assembly 16 of the frame 1.

[0029] In the above embodiments, the roller assembly 13 can be 3 sets, the body clamping device can be 2 sets, the rolling ring 31 can be 3, and 4 support rods 33 can be arranged between adjacent rolling rings 31; the body 4 to be assembled is fixed by the body clamping assembly, and then the fixed body is placed into each rolling ring 31, and fixed to each rolling ring again by the body clamping assembly; according to different needs, the rolling rings are rotated to adjust the body at different angles.

[0030] Reference Figure 3 , Figure 5 and Figure 6-7 In some embodiments of the present invention, the inner ring of each rolling ring 31 of the fuselage clamping mechanism 3 has a radially convex limiting ring 32, and the circumferential spacing of the limiting ring 32 is provided with a plurality of limiting holes; the fuselage clamping assembly of the fuselage clamping mechanism 3 has a slide rod 36, and a plurality of limiting sliders 37 are slidably mounted on the outer side of the slide rod 36. Each set of limiting sliders 37 has an annular groove through which the limiting ring 32 can be inserted, and the limiting slider 37 is provided with at least one through annular groove that matches the upper limiting hole of the limiting ring 32; a plurality of fuselage connecting pins 38 are slidably mounted on the inner side of the slide rod 36. The fuselage clamping assembly is detachably connected to the fuselage 4 to be assembled via the sets of fuselage connecting pins 38 on the inner side; The mounting assembly is detachably connected to the limiting ring 32 of the inner ring of the corresponding rolling ring 31 via the outer sets of limiting sliders 37.

[0031] In the above embodiments, there can be three sets of limiting sliders 37. After the limiting sliders 37 are placed in the designated position, bolts are passed through the holes of the limiting sliders 37 and the corresponding limiting holes, and then fixed with nuts. There can be two sets of body connecting pins 38, which are slidably assembled on the inner side of the slide rod 36 and aligned with the fixed connection point of the body 4 for fixation.

[0032] Reference Figure 5-7 In some embodiments of the present invention, the inner side of the slide bar 36 of the body clamping assembly is provided with a recessed groove 39, and each set of body connecting pins 38 is slidably assembled in the groove 39 on the inner side of the slide bar 36; and, a plurality of limiting holes communicating with the inner and outer sides are provided in the groove 39 of the slide bar 36 at intervals, and the body connecting pin 38 and / or the limiting slider 37 at the current connection position are blocked and limited by the limiting pin 310 connected in the corresponding limiting hole on the slide bar 36.

[0033] In the above embodiments, each set of body connecting pins 38 corresponds to two sets of limiting pins 310. When the body connecting pin 38 is slid to a designated position, the limiting pins 310 pass through the limiting holes on both sides of the body connecting pin to block and limit the body connecting pin 38.

[0034] Reference Figure 4 In some embodiments of the present invention, the clamping fixture further includes a rolling drive mechanism 2, which is used to generate a driving force for the circumferential rotation of the rolling ring 31 of the machine body clamping mechanism 3. The rolling drive mechanism 2 has a motor 21, a drive shaft 22, multiple sets of sprockets 23 and multiple sets of chains 25. Each set of chains 25 is circumferentially assembled corresponding to each rolling ring 31 of the machine body clamping mechanism 3. The motor 21 is fixed on the frame 1, and the output shaft of the motor 21 is connected to the drive shaft 22. The drive shaft 22 is supported in the longitudinal direction of the frame 1 by multiple sets of bearings arranged at intervals. Each set of sprockets 23 is connected in series on the drive shaft corresponding to the chains 25 assembled on each rolling ring 31 of the machine body clamping mechanism 3.

[0035] In the above embodiment, there are 3 sets of sprockets 23 and 3 sets of chains. The drive motor 21 drives the transmission shaft 22 to rotate, and the rotating shaft 220 drives the sprockets 23 and chains 25 to rotate, which in turn drives the rolling ring 31 to rotate.

[0036] Reference Figure 3In some embodiments of the present invention, the body clamping mechanism 3 also has a plurality of drive rings 35, each drive ring 35 forming a one-to-one pairing relationship with each rolling ring 31, and the one-to-one pairing drive rings 35 are axially connected to the side of the rolling rings 31; correspondingly, each set of chains 25 of the rolling drive mechanism 2 is circumferentially assembled in the corresponding drive ring 35.

[0037] In the above embodiment, there are three drive rings 35, which are circumferentially assembled in the corresponding drive rings 35 by the chain 25. The drive rings 35 are connected to the side of the paired rolling rings 31. When the chain 25 rotates, it drives the drive rings 35 to rotate, thereby driving the rolling rings 31 to rotate.

[0038] Reference Figure 3-4 In some embodiments of the present invention, the chain 25 of the rolling drive mechanism 2 is composed of a chain body and screw joints 24 at both ends; correspondingly, two fixed end plates 34 are arranged at intervals inside the drive ring 35, and each fixed end plate 34 has a through hole for the screw joints 24 to pass through; the chain 25 circumferentially assembled in the corresponding drive ring 35 is fitted onto the fixed end plates 34 inside the drive ring 35 by the screw joints 24 at both ends, and is adjusted and locked by nuts.

[0039] In the above embodiment, the screw connector 24 passes through the through hole on the fixed end plate 34, and is mounted on the screw connector 24 by a nut. The chain is adjusted and locked by rotating the nut.

[0040] Reference Figure 3 In some embodiments of the present invention, a radially convex limiting ring 32 is used to connect the paired drive ring 35 and rolling ring 31.

[0041] Reference Figure 2 In some embodiments of the present invention, the frame 1 has two longitudinal beams 12 and two end beams 13. The two longitudinal beams 12 are arranged along the longitudinal direction of the body 4, and the two end beams 13 connect the two longitudinal beams 12 into a whole at both ends. The frame 1 has a frame structure. Each set of roller assemblies 16 on the frame 1 is arranged on the top side of the two longitudinal beams 12, and the two roller assemblies 16 in each set are arranged symmetrically on the two longitudinal beams 12. In the above embodiment, three roller assemblies are arranged on each of the two longitudinal beams 12.

[0042] Reference Figure 1-3 In some embodiments of the present invention, the roller assembly 16 includes a roller support 14 and a roller body 15. The roller support 14 is connected to the longitudinal beam 12 with an upward protruding structure, and the top of the roller support 14 is an inwardly inclined structure. The roller body 15 is detachably connected to the top of the corresponding roller support 14, and each roller body 15 is arranged obliquely inward on the frame structure of the frame 1.

[0043] In the above embodiment, the roller support 14 and the roller body 15 are connected by four bolts and nuts located around the perimeter. The roller body 15 includes a roller and a roller support plate. The roller is mounted on the roller support plate and fixed by the bolts and nuts.

[0044] Reference Figure 2 In some embodiments of the present invention, the frame 1 has outwardly protruding support seats 11 around its perimeter, and each support seat is connected to an anchor bolt 17.

[0045] In the above embodiment, there is a support base 11 on each of the four sides of the frame 1, and two anchor bolts 17 are connected to each support base 11 by nuts.

[0046] Although preferred embodiments of the invention have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including both the preferred embodiments and all changes and modifications falling within the scope of the invention.

[0047] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this invention and their equivalents, this invention also intends to include these modifications and variations.

Claims

1. A clamping fixture for fuselage assembly in light aircraft maintenance operations, comprising a frame (1) and a fuselage clamping mechanism (3) mounted on the frame (1); Its features are: On the frame (1), corresponding to the longitudinal direction of the body (4), multiple sets of roller assemblies (16) are arranged in front-to-back sequence, with each set of roller assemblies (16) consisting of two rollers arranged in the left and right positions. The fuselage clamping mechanism (3) corresponds to the multiple sets of roller assemblies (16) on the frame (1), and has multiple rolling rings (31) and multiple sets of fuselage clamping assemblies connected in series with each rolling ring (31); Each rolling ring (31) of the fuselage clamping mechanism (3) is located on each set of roller assemblies (16) of the frame (1), and two adjacent rolling rings (31) are connected as a whole by multiple support rods (33) arranged around the circumference. Each set of fuselage clamping components of the fuselage clamping mechanism (3) is detachably fixed to the inner ring of the rolling ring (31) in a circumferential distribution manner, and each set of fuselage clamping components connects each rolling ring (31) together in series. The fuselage (4) to be assembled is detachably connected to each set of fuselage clamping components of the fuselage clamping mechanism (3), and each set of fuselage clamping components is detachably fixed in each rolling ring (31) of the fuselage clamping mechanism (3). Each rolling ring (31) of the fuselage clamping mechanism (3) can rotate circumferentially on the roller assembly (16) of the frame (1). The inner ring of each rolling ring (31) of the body clamping mechanism (3) has a radially convex limiting ring (32), and the circumferential spacing of the limiting ring (32) is provided with several limiting holes. The fuselage clamping mechanism (3) has a fuselage clamping assembly with a slide rod (36). Multiple sets of limiting sliders (37) are slidably mounted on the outer side of the slide rod (36). Each set of limiting sliders (37) has an annular groove through which the limiting ring (32) can be inserted. The limiting slider (37) has at least one hole that passes through the annular groove and matches the upper limit hole of the limiting ring (32). Multiple sets of fuselage connecting pins (38) are slidably mounted on the inner side of the slide rod (36). The fuselage clamping assembly is detachably connected to the fuselage (4) to be assembled via the sets of fuselage connecting pins (38) on the inner side; The fuselage clamping assembly is detachably connected to the limiting ring (32) of the inner ring of the corresponding rolling ring (31) via each set of limiting sliders (37) on the outer side.

2. The clamping fixture for fuselage assembly in light aircraft maintenance operations according to claim 1, characterized in that: The inner side of the slide bar (36) of the fuselage clamping assembly is provided with a recessed groove (39), and each set of fuselage connecting pins (38) is slidably assembled in the groove (39) on the inner side of the slide bar (36); Furthermore, the slide groove (39) of the slide rod (36) is provided with a number of limiting holes that connect the inner and outer sides at intervals. The body connecting pin (38) and / or the limiting slider (37) of the current connection position are blocked and limited by the limiting pin (310) connected in the corresponding limiting hole on the slide rod (36).

3. The clamping fixture for fuselage assembly in light aircraft maintenance operations according to claim 1, characterized in that: The clamping fixture also includes a rolling drive mechanism (2), which is used to generate a driving force for the circumferential rotation of the rolling ring (31) of the body clamping mechanism (3); The rolling drive mechanism (2) has a motor (21), a drive shaft (22), multiple sets of sprockets (23) and multiple sets of chains (25); Each set of chains (25) is circumferentially assembled with respect to each rolling ring (31) of the fuselage clamping mechanism (3); The motor (21) is fixed on the frame (1), and the output shaft of the motor (21) is connected to the transmission shaft (22); The drive shaft (22) is supported longitudinally on the frame (1) by multiple sets of bearings arranged at intervals; Each set of sprockets (23) is connected in series with the chain (25) assembled on the drive shaft corresponding to each rolling ring (31) of the body clamping mechanism (3).

4. The clamping fixture for fuselage assembly in light aircraft maintenance operations according to claim 3, characterized in that: The fuselage clamping mechanism (3) also has multiple drive rings (35), each drive ring (35) and each rolling ring (31) form a one-to-one matching relationship, and the one-to-one matching drive rings (35) are axially connected to the side of the rolling rings (31). Correspondingly, each set of chains (25) of the rolling drive mechanism (2) is circumferentially assembled in the corresponding drive ring (35).

5. The clamping fixture for fuselage assembly in light aircraft maintenance operations according to claim 4, characterized in that: The chain (25) of the rolling drive mechanism (2) is composed of the chain body and the screw joints (24) at both ends; Correspondingly, two fixed end plates (34) are arranged at intervals inside the drive ring (35), and each fixed end plate (34) has a through hole for the screw connector (24) to pass through; The chain (25) circumferentially assembled in the corresponding drive ring (35) is fitted onto the fixed end plate (34) in the drive ring (35) by the screw joints (24) at both ends, and is adjusted and locked by nuts.

6. The clamping fixture for fuselage assembly in light aircraft maintenance operations according to claim 4, characterized in that: Between the paired drive ring (35) and the rolling ring (31), a limiting ring (32) is used to connect the radially inwardly protruding ring.

7. The clamping fixture for fuselage assembly in light aircraft maintenance operations according to claim 1, characterized in that: The frame (1) has two longitudinal beams (12) and two end beams (13). The two longitudinal beams (12) are arranged along the longitudinal direction of the fuselage (4). The two end beams (13) connect the two longitudinal beams (12) into a whole at both ends of the two longitudinal beams (12). The frame (1) has a frame structure. Each set of roller assemblies (16) on the frame (1) is arranged on the top side of the two longitudinal beams (12), and the two roller assemblies (16) of each set are arranged symmetrically on the two longitudinal beams (12).

8. The clamping fixture for fuselage assembly in light aircraft maintenance operations according to claim 7, characterized in that: The roller assembly (16) includes a roller support (14) and a roller body (15). The roller support (14) is connected to the longitudinal beam (12) with an upward protruding structure. The top of the roller support (14) is an inwardly inclined structure. The roller body (15) is detachably connected to the top of the corresponding roller support (14), and each roller body (15) is arranged obliquely inward on the frame structure of the frame (1).

9. The jigging tool for fuselage assembly in the maintenance work of a light aircraft according to Claim 7, wherein: The frame (1) has outwardly protruding support seats (11) around its perimeter, and each support seat is connected to an anchor bolt (17).

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