A satellite cabin panel clamping mechanism for a satellite assembly line

Abstract

The present invention provides a satellite cabin panel clamping mechanism for a satellite assembly line, which belongs to the field of satellite manufacturing technology. It solves the problem of how to improve the quality of satellite production while improving the efficiency of satellite assembly. The satellite cabin panel clamping mechanism for a satellite assembly line includes a clamping member 1 for clamping the satellite cabin panel. The satellite cabin panel clamping mechanism also includes a clamping member 2. The clamping member 2 has two clamping plates that can slide relative to each other in the same direction. The clamping plates are provided with a clamping positioning structure, and the clamping member 1 can be clamped and fixed between the two clamping plates through the clamping positioning structure. The clamping mechanism adopts a dual-component design of clamping member 1 and clamping member 2, so that the satellite cabin panel body does not need to be repeatedly clamped, and a quick clamping design is made between clamping member 1 and the satellite cabin panel, and between clamping member 1 and clamping member 2, thereby greatly improving the satellite assembly efficiency while improving the quality of satellite production.

Description

Technical Field

[0001] The invention belongs to the technical field of satellite manufacturing and relates to a satellite cabin plate clamping mechanism used in a satellite assembly line. Background Art

[0002] With the further development of space technology and on-orbit launch missions, the on-orbit launch of microsatellites will become a trend, and the model of a primary satellite carrying multiple small satellites will become the mainstream. When the primary satellite reaches the predetermined orbit, the side hatch opens, and the embedded microsatellites are ejected into orbit by a special mechanism, thus completing the launch mission of sending satellites into space.

[0003] At present, most microsatellites adopt a cabin-type structure, such as the cabin-type satellite configuration disclosed in Chinese patent [Application No.: 201811352223.9]. This type of satellite structure has a small operating space, and it is easy for components to block each other in the small space. Many parts of the connection between the cabin panels are also located inside the cabin, making it difficult to use automated equipment such as robotic arms to enter the cabin for assembly. Usually, manual installation of various equipment in the satellite cabin is required.

[0004] To improve manufacturing efficiency, existing technologies often pre-install various devices on the deck before assembling the cabin. However, due to the large variety of devices installed on the deck, the deck must pass through multiple workstations to complete the assembly of each device. During this process, the deck is typically placed at the workstation corresponding to the assembly process, then clamped and fixed with fixtures at the workstation for assembly. After completing one process, it is moved to the next. This means that during the assembly of the deck equipment, the deck needs to be repeatedly clamped at different workstations, which can easily cause wear and even damage to the deck, affecting the production quality of the satellite. Furthermore, repeated clamping wastes assembly time and reduces satellite assembly efficiency. Summary of the Invention

[0005] The purpose of the present invention is to address the above-mentioned problems in the existing technology and propose a satellite cabin panel clamping mechanism for a satellite assembly line. The technical problem to be solved by the present invention is how to improve the quality of satellite production while improving the efficiency of satellite assembly.

[0006] The objectives of the present invention can be achieved through the following technical solutions: a satellite cabin panel clamping mechanism for a satellite assembly line, comprising a clamping member 1 for clamping a satellite cabin panel, characterized in that the satellite cabin panel clamping mechanism also includes a clamping member 2, the clamping member 2 having two clamping plates that can slide relative to each other in the same direction, and a clamping positioning structure is provided on the clamping plate, through which the clamping member 1 can be clamped and fixed between the two clamping plates.

[0007] Different from the prior art, the present invention has redesigned the clamping method of the satellite cabin panel. Specifically, the present invention designs the satellite cabin panel clamping mechanism to be composed of two components, namely clamping part 1 and clamping part 2, wherein clamping part 1 is used for clamping the satellite cabin panel. After being clamped by clamping part 1, clamping part 1 is clamped and fixed by clamping part 2. This design makes it possible for the satellite cabin panel to be clamped only once, that is, when it enters the next assembly process, it does not need to be removed from clamping part 1, but clamping part 1 is removed from clamping part 2 of the previous assembly process, and then installed in clamping part 2 of the next assembly process to complete the clamping of the satellite cabin panel in the next process. That is to say, during the assembly and transfer process of the satellite cabin panel in different processes, the satellite cabin panel does not need to be repeatedly clamped and disassembled, thereby avoiding possible wear of the satellite cabin panel and improving the survival rate of the satellite. Production quality; at the same time, by designing the clamping part 2, that is, the clamping part 2 is designed with two clamping plates that can slide relative to each other in the same direction, and each clamping plate is provided with a clamping and positioning structure for clamping and fixing the clamping part 1, through the adjustment of the spacing between the above two clamping plates, the clamping part 2 in each process can be adapted to the clamping part 1 of satellite cabin panels of different sizes, so that the satellite assembly line can be used to assemble satellite cabin panels of various sizes without changing the clamps. Since a satellite has multiple cabin panels, the size may be difficult. Therefore, the above design saves the time required for the existing assembly line to replace the clamps; and, compared with the existing clamps that need to be careful each time they clamp the cabin panel, the present invention is the disassembly and assembly of the clamping part 1 and the clamping part 2 during the process transition process, and there is no need to worry about the disassembly and assembly between the two, which greatly improves the disassembly and assembly speed, thereby helping to improve the efficiency of satellite assembly.

[0008] In the aforementioned satellite panel clamping mechanism for a satellite assembly line, the first clamping member is frame-shaped and capable of enclosing the satellite panel. This design of the first clamping member protects the panel during the process of transferring the panel, further ensuring satellite production quality.

[0009] In the satellite cabin panel clamping mechanism used in the satellite assembly line, the clamping and positioning structure includes a fixed seat, a pressure rod, and a driving member. The fixed seat is fixed to a clamping plate, and the fixed seat is provided with a first connecting rod and a second connecting rod. One end of the first connecting rod is hinged to the fixed seat, and the other end is fixedly connected to the pressure rod. The second connecting rod is hinged to the fixed seat, and a linkage is provided between the first and second connecting rods. The two ends of the linkage are respectively hinged to the first and second connecting rods. The driving member is fixed to the clamping plate and can drive the free end of the second connecting rod to swing so that the pressure rod presses against the first clamping member. When the first clamping member needs to be clamped and fixed, the main working process of the clamping and positioning structure is to drive the second connecting rod to swing through the driving member. The swinging of the second connecting rod drives the linkage member to swing. At this time, the first connecting rod can, driven by the linkage member, press the pressure rod downward to achieve the clamping and fixing of the first clamping member. The entire process is fully automatic. The first clamping member only needs to be placed in place for rapid clamping, which is beneficial to improving the efficiency of satellite assembly.

[0010] In the satellite cabin panel clamping mechanism used in the satellite assembly line, the fixed seat, pressure rod, connecting rod 1, connecting rod 2, and linkage member form a clamping and positioning assembly. There are two groups of clamping and positioning assemblies, with a lifting plate disposed between the two groups. Cranks are hinged at each end of the lifting plate, and the free ends of the cranks are hinged to the free end of the corresponding connecting rod 2. The lifting plate can be moved by a driving member to cause the two pressure rods to synchronously clamp clamping member 1. This design not only ensures that clamping member 1 can be effectively clamped, but also enables the clamping and positioning assemblies to be clamped synchronously at one time, eliminating the need for step-by-step operations. This greatly improves clamping efficiency, thereby further improving satellite assembly efficiency.

[0011] In the satellite cabin panel clamping mechanism used in the satellite assembly line, the pressure rod slides along the length of connecting rod one and is fixedly connected to connecting rod one via a locking structure. The locking structure includes sliding buckles slidably disposed on the upper and lower sides of connecting rod one. The pressure rod is inserted into the buckles, and locking nuts are provided on the outer sides of both buckles. The locking nuts are threadedly connected to the pressure rod and can lock the buckles and pressure rod to connecting rod one. By loosening the locking nuts, the buckles can slide on connecting rod one, thus allowing the pressure rod's clamping position to be adjusted. This allows the assembly line to adapt to the clamping requirements of cabin panels of different sizes without changing the clamps, thereby improving the overall efficiency of satellite assembly.

[0012] In the satellite cabin panel clamping mechanism used in the satellite assembly line, the clamping plate has a positioning post on its upper surface, the first clamping member has a positioning seat, and the seat has a positioning hole that mates with the post. The pressure rod can press against the seat. This design of the positioning post and the positioning hole improves the clamping speed of the first clamping member, thereby enhancing satellite assembly efficiency.

[0013] In the aforementioned satellite panel clamping mechanism for a satellite assembly line, the second clamping member comprises a base, two elongated clamping plates slidably connected to the base, and locking pins provided on each clamping plate, which lock and securely connect the clamping plates to the base. This design allows for adjustment of the spacing between the two clamping plates in a single direction, making the second clamping member adaptable to various panel sizes.

[0014] In the aforementioned satellite cabin panel clamping mechanism for a satellite assembly line, the base is provided with several sets of mounting holes spaced along the sliding direction of the clamping plate. An adjustment block is positioned between the clamping plate and the base. The adjustment block is mounted via fasteners to one of the sets of mounting holes. The adjustment block has a locking hole, and a locking pin is threadedly connected to the clamping plate and can extend into the locking hole. This design of mounting holes and adjustment blocks allows for quick locking after adjusting the spacing between the clamping plates to accommodate different clamping sizes, thereby improving satellite assembly efficiency.

[0015] In the satellite cabin panel clamping mechanism for a satellite assembly line, the clamping member 1 includes two oppositely arranged side frames, a transmission rod and a positioning rod for clamping the satellite cabin panel slidably disposed within the side frames, the transmission rod being arranged along the length of the side frames and having one end extending out of the side frames, the positioning rod being arranged along the width of the side frames and extending inwardly from the side frames and extending out of the side frames, the outer circumference of the transmission rod having a notch arranged along the length of the transmission rod, the ends of the notch being transmission parts, a connecting rod being hingedly connected to the positioning rod, a sliding post being fixed to the free end of the connecting rod, the sliding post extending into the notch and being located between the two transmission parts, the transmission part being able to drive the connecting rod to cause the positioning rod to perform telescopic movement. By simply operating the extended end of the transmission rod to move along the length direction, the sliding post, driven by the transmission part, can drive the connecting rod to swing, and the positioning rod, driven by the connecting rod, can now perform telescopic movement. In other words, through the above design, the satellite cabin panel can be quickly clamped, thereby facilitating improved satellite assembly efficiency.

[0016] In the satellite cabin panel clamping mechanism used in the satellite assembly line, a connecting frame is provided on the side frame. One end of the connecting frame is hingedly connected to the side frame, and the other end is hingedly connected to a control frame. The control frame includes a control lever and an articulated lever. The articulated lever is articulated to a transmission rod extending from the side frame. With this design, simply moving the control lever rotates the control frame, thereby moving the transmission rod and achieving rapid clamping of the satellite cabin panel.

[0017] Compared with the existing technology, the satellite cabin panel clamping mechanism for satellite assembly line has the following advantages:

[0018] 1. This clamping mechanism adopts a dual-component design of clamping part 1 and clamping part 2, so that the satellite cabin panel body does not need to be repeatedly clamped. In addition, a quick clamping design is made between clamping part 1 and the satellite cabin panel, and between clamping part 1 and clamping part 2, thereby greatly improving the satellite production quality and the assembly efficiency of the satellite.

[0019] 2. When this clamping mechanism is applied to a satellite assembly line, one satellite assembly line can meet the assembly needs of satellite cabin panels of different sizes, greatly improving the adaptability and versatility of the satellite assembly line. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the overall structure of the satellite cabin panel clamping mechanism.

[0021] Figure 2 This is a structural diagram of the clamping member 2 in the satellite cabin panel clamping mechanism.

[0022] Figure 3 yes Figure 2 A magnified view of the local structure at point A.

[0023] Figure 4 This is a schematic diagram of the structure of the clamping member 1 in the satellite cabin panel clamping mechanism. Figure 1 .

[0024] Figure 5 This is a schematic diagram of the structure of the clamping member 1 in the satellite cabin panel clamping mechanism. Figure 2 .

[0025] Figure 6 This is a schematic diagram of the internal structure of the clamping component 1 after the side frame is hidden.

[0026] Figure 7 yes Figure 6 A magnified view of the local structure at point B in the middle.

[0027] In the figure, a, satellite cabin panel; 1, clamping part 1; 1a, side frame; 1b, positioning seat; 1b1, positioning hole; 2, clamping part 2; 21, clamping plate; 211, positioning column; 22, base; 221, mounting hole; 23, locking pin; 24, adjusting block; 3, fixing seat; 4, pressure rod; 5, driving part; 6, connecting rod 1; 7, connecting rod 2; 8, linkage part; 9, lifting plate; 10, crank; 11, slide buckle; 12, locking nut; 13, transmission rod; 131, transmission part; 14, positioning rod; 15, connecting rod; 16, sliding column; 17, connecting frame; 18, operating frame; 181, operating rod part; 182, hinged rod part. DETAILED DESCRIPTION

[0028] The following are specific embodiments of the present invention and the accompanying drawings to further describe the technical solutions of the present invention, but the present invention is not limited to these embodiments.

[0029] Specifically, if Figure 1 As shown, the satellite cabin panel clamping mechanism for a satellite assembly line includes a clamping member 1 and a clamping member 2 for clamping satellite cabin panel a. Clamping member 1 is frame-shaped and can surround satellite cabin panel a. Clamping member 2 has two clamping plates 21 that can slide relative to each other in the same direction. Clamping plates 21 are provided with a clamping and positioning structure. Through this clamping and positioning structure, clamping member 1 can be clamped and fixed between the two clamping plates 21. More specifically, as shown in FIG. Figure 2 As shown, the second clamping member 2 includes a base 22, two elongated clamping plates 21 arranged in parallel, and each slidably connected to a slide rail on the base 22 via a slider. The base 22 is provided with a plurality of mounting holes 221 spaced apart along the sliding direction of the clamping plates 21. An adjustment block 24 is provided between the clamping plates 21 and the base 22. The adjustment block 24 is mounted on one of the mounting holes 221 via fasteners. The adjustment block 24 has a locking hole. The clamping plates 21 are provided with a locking pin 23, which is threadedly connected to the clamping plates 21 and can extend into the locking hole.

[0030] For example Figure 3 As shown, in this embodiment, the clamping and positioning structure includes a fixed seat 3, a pressure rod 4, and a driving member 5. The fixed seat 3 is fixed to the clamping plate 21 and is provided with a connecting rod 1 6 and a connecting rod 2 7. One end of the connecting rod 1 6 is hinged to the fixed seat 3, and the pressure rod 4 is slidably mounted on the other end of the connecting rod 1 6 along the length direction of the connecting rod 1 6 and is fixedly connected via a locking structure. The locking structure includes sliders 11 slidably mounted on the upper and lower sides of the connecting rod 1 6. The pressure rod 4 is inserted into the sliders 11. The outer sides of the two sliders 11 are each provided with a locking nut 12. The locking nut 12 is threadedly connected to the pressure rod 4 and can lock the sliders 11 and the pressure rod 4 to the connecting rod 1 6. At the same time, the connecting rod 2 7 is hinged to the fixed seat 3. A linkage member 8 is provided between the connecting rods 1 6 and 7. The ends of the linkage member 8 are respectively hinged to the connecting rods 1 6 and 7. The fixing seat 3, the pressure rod 4, the connecting rod 1 6, the connecting rod 2 7 and the linkage 8 form a set of clamping and positioning components. In this embodiment, there are two sets of clamping and positioning components. A lifting plate 9 is set between the two sets of clamping and positioning components. The two ends of the lifting plate 9 are respectively hinged with cranks 10. The free ends of the cranks 10 are hinged with the free ends of the corresponding connecting rods 2 7. The lifting plate 9 can move under the action of the driving member 5 so that the two pressure rods 4 can synchronously press the clamping member 1. The above-mentioned driving member 5 can be a cylinder, a hydraulic cylinder or a linear motor. For example Figure 4 and Figure 5As shown, a positioning column 211 is further provided on the upper surface of the clamp 21, a positioning seat 1b is provided on the clamping member 1, and a positioning hole 1b1 is provided in the positioning seat 1b that can be positioned and matched with the positioning column 211, and the pressure rod 4 can be pressed on the positioning seat 1b.

[0031] For example Figures 4 to 7 As shown, in this embodiment, the clamping member 1 comprises two opposing side frames 1a. A transmission rod 13 and a positioning rod 14 for clamping the satellite panel a are slidably mounted within the side frames 1a via sliding bearings. The transmission rod 13 is arranged along the length of the side frames 1a, with one end extending out of the side frames 1a. The positioning rod 14 is arranged along the width of the side frames 1a, extending inward and out of the side frames 1a. In this embodiment, there are four positioning rods 14, positioned near both ends of the side frames 1a. The outer circumference of the transmission rod 13 has notches arranged along its length, corresponding in number and position to the positioning rods 14. The two ends of the notches form transmission sections 131. A connecting rod 15 is hingedly connected to the positioning rod 14. A sliding post 16 is fixed to the free end of the connecting rod 15. The sliding post 16 extends into the notches and is located between the two transmission sections 131. A connecting frame 17 is provided on the side frame 1a. One end of the connecting frame 17 is hingedly connected to the side frame 1a, and the other end is hingedly connected to an operating frame 18. Operating frame 18 comprises an operating lever 181 and an articulated lever 182. Articulated lever 182 is hingedly connected to a transmission rod 13 extending from the side frame 1a. By moving operating frame 18, transmission rod 13 can be moved laterally. At this point, transmission portion 131 drives linkage rod 15, causing positioning rod 14 to extend and retract, thereby clamping the satellite panel a.

[0032] As an alternative, the clamping and positioning structure in this embodiment may also adopt an air clamping claw structure.

[0033] The specific embodiments described herein are merely illustrative of the spirit of the present invention. Persons skilled in the art may make various modifications, additions, or substitutions to the described specific embodiments without departing from the spirit of the present invention or exceeding the scope of the appended claims.

[0034] Although this document frequently uses terms such as satellite cabin panel a, clamping member 1, side frame 1a, positioning seat 1b, positioning hole 1b1, clamping member 2, clamping plate 21, positioning column 211, base 22, mounting hole 221, locking pin 23, adjusting block 24, fixing seat 3, pressure rod 4, driving member 5, connecting rod 1 6, connecting rod 2 7, linkage member 8, lifting plate 9, crank 10, slider 11, locking nut 12, transmission rod 13, transmission part 131, positioning rod 14, connecting rod 15, sliding column 16, connecting frame 17, operating frame 18, operating rod portion 181, and hinged rod portion 182, the use of other terms is not excluded. These terms are used only to more conveniently describe and explain the essence of the present invention; interpreting them as any additional limitations is contrary to the spirit of the present invention.

Claims

1. A satellite cabin panel clamping mechanism for a satellite assembly line, comprising a clamping member (1) for clamping a satellite cabin panel (a), characterized in that: The clamping member (1) is frame-shaped and can surround the satellite cabin panel (a). The clamping member (1) includes two side frames (1a) arranged opposite to each other. A transmission rod (13) and a positioning rod (14) for clamping the satellite cabin panel (a) are slidably provided in the side frames (1a). The transmission rod (13) is arranged along the length direction of the side frames (1a) and one end extends out of the side frames (1a). The positioning rod (14) is arranged along the width direction of the side frames (1a) and extends toward the inner side of the side frames (1a). The outer peripheral surface of the transmission rod (13) has a notch arranged along the length direction of the transmission rod (13), and the two ends of the notch are transmission parts (131). The positioning rod (14) is hinged with a connecting rod (15), and the free end of the connecting rod (15) is fixed with a sliding column (16). The sliding column (16) extends into the notch and is located between the two transmission parts (131). The transmission part (131) can drive the connecting rod (15) to make the positioning rod (14) perform telescopic movement. The satellite cabin panel clamping mechanism further comprises a clamping member 2 (2), wherein the clamping member 2 (2) comprises two clamping plates (21) capable of sliding relative to each other in the same direction, wherein the clamping plates (21) are provided with a clamping positioning structure, and the clamping member 1 (1) can be clamped and fixed between the two clamping plates (21) through the clamping positioning structure; the clamping positioning structure comprises a fixing seat (3), a pressure rod (4) and a driving member (5), wherein the fixing seat (3) is fixed on the clamping plate (21), and the fixing seat (3) is provided with a connecting rod. One (6) and the second (7); one end of the first (6) is hinged on the fixed seat (3), and the other end is fixedly connected to the pressure rod (4); the second (7) is hinged on the fixed seat (3), and a linkage member (8) is provided between the first (6) and the second (7), and the two ends of the linkage member (8) are respectively hinged to the first (6) and the second (7); the driving member (5) is fixedly connected to the clamping plate (21) and can drive the free end of the second (7) to swing so that the pressure rod (4) presses the clamping member (1).

2. The satellite cabin panel clamping mechanism for a satellite assembly line according to claim 1, characterized in that: The fixing seat (3), the pressure rod (4), the connecting rod 1 (6), the connecting rod 2 (7) and the linkage member (8) form a group of clamping and positioning components. There are two groups of clamping and positioning components. A lifting plate (9) is provided between the two groups of clamping and positioning components. The two ends of the lifting plate (9) are respectively hinged with cranks (10). The free ends of the cranks (10) are hinged with the free ends of the corresponding connecting rods 2 (7). The lifting plate (9) can move under the action of the driving member (5) so that the two pressure rods (4) can synchronously press the clamping member 1 (1).

3. The satellite cabin panel clamping mechanism for a satellite assembly line according to claim 1, characterized in that: The pressure rod (4) is slidably arranged on the connecting rod (6) along the length direction of the connecting rod (6) and is fixed to the connecting rod (6) through a locking structure. The locking structure includes sliding buckles (11) slidably arranged on the upper and lower sides of the connecting rod (6), respectively. The pressure rod (4) is inserted into the sliding buckles (11). The outer sides of the two sliding buckles (11) are provided with locking nuts (12). The locking nuts (12) are threadedly connected to the screw and can lock the sliding buckles (11) and the pressure rod (4) on the connecting rod (6).

4. The satellite cabin panel clamping mechanism for a satellite assembly line according to claim 1, characterized in that: A positioning column (211) is provided on the upper surface of the clamping plate (21), a positioning seat (1b) is provided on the clamping member (1), a positioning hole (1b1) capable of positioning and cooperating with the positioning column (211) is provided in the positioning seat (1b), and the pressure rod (4) can be pressed on the positioning seat (1b).

5. The satellite cabin panel clamping mechanism for a satellite assembly line according to claim 1, 2, 3 or 4, characterized in that: The second clamping member (2) includes a base (22), and the two clamping plates (21) are in the shape of long strips and are respectively slidably connected to the base (22). The clamping plates (21) are provided with locking pins (23), and the clamping plates (21) can be locked and fixedly connected to the base (22) through the locking pins (23).

6. The satellite cabin panel clamping mechanism for a satellite assembly line according to claim 5, characterized in that: The base (22) is provided with a plurality of groups of mounting holes (221) spaced apart along the sliding direction of the splint (21), an adjusting block (24) is provided between the splint (21) and the base (22), the adjusting block (24) being mounted on one of the groups of mounting holes (221) via a fastener, the adjusting block (24) having a locking hole, the locking pin (23) being threadedly connected to the splint (21) and being capable of extending into the locking hole.

7. The satellite cabin panel clamping mechanism for a satellite assembly line according to claim 1, characterized in that: A connecting frame (17) is provided on the side frame (1a), one end of the connecting frame (17) is hinged to the side frame (1a), and the other end is hinged to an operating frame (18), the operating frame (18) comprises an operating lever portion (181) and an articulated lever portion (182), and the articulated lever portion (182) is articulated to a transmission rod (13) extending out of the side frame (1a).

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