Rapid clamping tool for spacecraft structural component

Abstract

The invention relates to the technical field of spacecraft structural part machining, in particular to a spacecraft structural part rapid clamping tool which comprises a bearing component, a clamping component and a material supporting component, the bearing component comprises a bearing disc, a sliding groove is formed in the inner side of the bearing disc, a supporting seat is arranged on the inner side of the bearing disc, and a clamping groove is formed in the clamping component; the clamping component comprises a first supporting strip, a clamping component is arranged on the upper side of the first supporting strip, a first mounting plate is arranged at one end of the outer side of the first supporting strip, and a second mounting plate is arranged at the other end of the outer side of the first supporting strip; and a screw rod is mounted on the side, corresponding to the first mounting plate, of the second mounting plate. According to the clamping device, the clamping component rotates on the inner side of the bearing disc, the fixing angle of the clamping component is adjusted, clamping operation of spacecraft structural parts of different shapes can be adapted, the stability of the clamping operation is improved, the clamping component is driven by the lead screw to slide on the upper side of the first supporting strip for clamping operation, and the clamping speed is increased.

Description

Technical Field

[0001] The invention relates to the technical field of spacecraft structural component processing, in particular to a quick clamping tool for spacecraft structural components. Background Art

[0002] The spacecraft structure is the assembly of all the force-bearing and supporting components of the spacecraft, which is generally divided into satellite structure, space probe structure, manned spacecraft structure and space shuttle structure. The spacecraft structural parts are the components of the spacecraft structure. Among them, the spacecraft structural parts clamping fixture is the positioning structure in the production of spacecraft structural parts, which ensures the stability of spacecraft structural parts during processing.

[0003] A Chinese patent discloses a fast milling clamping tool for aviation structural parts (authorization announcement number CN217914041U). In this patented technology, one end of the first slide bar and the second slide bar are both in contact with the hourglass-shaped slider, and the other ends of the first slide bar and the second slide bar are respectively inserted into the first mounting hole and the second mounting hole and extend outside the base. The other end of the first slide bar is connected to a first limit plate, and a second limit block is slidably provided on the surface of the base away from the end of the first limit block, thereby realizing fast clamping and fixing of aviation structural parts. However, the angle of the clamping plate of the above-mentioned clamping tool is fixed, and it can only complete the clamping operation of square parts. The adaptability to special-shaped spacecraft structural parts is low, which is not conducive to the stability of the clamping operation, and the flexibility of use is low. Manual clamping operation is adopted, and the convenience of operation is low, which affects the clamping speed. Therefore, those skilled in the art provide a fast clamping tool for spacecraft structural parts to solve the problems raised in the above-mentioned background technology. Summary of the invention

[0004] The purpose of the present invention is to provide a quick clamping fixture for a spacecraft structural component to solve the problems raised in the above-mentioned background technology.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a rapid clamping tool for a spacecraft structural part, comprising a load-bearing member, a clamping member and a supporting member, the clamping member is located at the inner side position of the load-bearing member, the supporting member is located at the inner side position of the load-bearing member, the load-bearing member includes a load-bearing plate, a sliding groove is opened on the inner side of the load-bearing plate, and a support seat is arranged on the inner side of the load-bearing plate, the clamping member includes a first support bar, a clamping member is arranged on the upper side of the first support bar, a first mounting plate is arranged at the outer side end position of the first support bar, a second mounting plate is arranged at the outer side end position of the first support bar, a screw rod is installed at the corresponding side position of the second mounting plate and the first mounting plate, a motor is installed at the outer side of the second mounting plate at the position corresponding to the screw rod, a first sliding block is arranged at one end position of the first support bar, a first rotating hole is opened at the upper side of the load-bearing plate adjacent to the support seat, and a first rotating column is arranged at the lower side position of the other end of the first support bar.

[0006] As a further solution of the present invention: an adjustment groove is provided at the upper outer end of the supporting plate, an adjustment screw is provided on the upper side of the first sliding block, a fixing nut is installed on the outer side of the adjusting screw, a guide groove is provided on the upper side of the first support bar, the clamping member includes a clamping plate, second sliding blocks are provided at both ends of the lower side of the clamping plate, an installation groove is provided on the lower side of the clamping plate, and a rotating wheel is installed on the inner side of the installation groove.

[0007] As a further solution of the present invention: a second rotating hole is opened on the upper side of the carrying plate near the first rotating hole, the supporting member includes a second support bar, a second rotating column is arranged at the lower side of one end of the second support bar, a sliding rod is arranged at the other end of the second support bar, a baffle is arranged at the front end of the sliding rod, a third sliding block is arranged on the front side of the baffle, and a spring is installed on the outer side of the sliding rod at the corresponding side position of the second support bar and the baffle.

[0008] As a further solution of the present invention: the first sliding block slides at an inner position of the sliding groove, and the first rotating column rotates at an inner position of the first rotating hole.

[0009] As a further solution of the present invention: the screw rod is rotated at the corresponding side positions of the first mounting plate and the second mounting plate by a motor, the screw rod is rotated at the lower end position of the clamping member, and the clamping member slides at the upper side position of the first support bar.

[0010] As a further solution of the present invention: the position of the adjusting screw corresponds to that of the adjusting slot, the adjusting screw slides at the inner position of the adjusting slot, and the adjusting screw is fixed at the inner position of the adjusting slot by a fixing nut.

[0011] As a further solution of the present invention: the rotating wheel rotates at the inner side of the installation groove, the rotating wheel rotates at the inner side of the guide groove, and the screw rod rotates at the lower end of the second sliding block.

[0012] As a further solution of the present invention: the second rotating column rotates at the inner position of the second rotating hole, the rear end of the sliding rod slides at the front end position of the second supporting bar, and the third sliding block slides at the inner position of the sliding groove.

[0013] Compared with the prior art, the present invention has the following beneficial effects: 1. The invention discloses a spacecraft structural component rapid clamping tool, which can adapt to the clamping operation of spacecraft structural components of different shapes by rotating the clamping component on the inner side of the carrier plate, adjusting the fixing angle of the clamping component, and has a high degree of adaptability to special-shaped spacecraft structural components, thereby improving the stability of the clamping operation and the flexibility of use; 2. The clamping member is driven by the screw rod to slide on the upper side of the first support bar to perform the clamping operation, thereby improving the convenience of operation and the clamping speed. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of the structure of a rapid clamping tool for a spacecraft structural component; Figure 2 It is a schematic diagram of the structure of a load-bearing component in a rapid clamping fixture for a spacecraft structure; Figure 3 It is a structural schematic diagram of a clamping component in a rapid clamping tool for a spacecraft structural component; Figure 4 A fast clamping tool for a spacecraft structure Figure 1 The structural diagram of part A in the figure; Figure 5 It is a structural schematic diagram of a clamping component in a rapid clamping tool for a spacecraft structural component; Figure 6 The figure is a schematic diagram of the structure of a material supporting component in a rapid clamping fixture for a spacecraft structure.

[0015] In the figure: 1. load-bearing member; 2. clamping member; 3. supporting member; 4. load-bearing plate; 5. slide groove; 6. support seat; 7. first support bar; 8. clamping member; 9. first mounting plate; 10. second mounting plate; 11. screw rod; 12. motor; 13. first slider; 14. first rotating hole; 15. first rotating column; 16. adjusting groove; 17. adjusting screw; 18. fixing nut; 19. guide groove; 20. clamping plate; 21. second slider; 22. mounting groove; 23. rotating wheel; 24. second rotating hole; 25. second support bar; 26. second rotating column; 27. slide rod; 28. baffle; 29. ​​third slider; 30. spring. DETAILED DESCRIPTION

[0016] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0017] See also Figures 1 to 6 In an embodiment of the present invention, a rapid clamping tool for a spacecraft structure includes a load-bearing member 1, a clamping member 2 and a supporting member 3. The clamping member 2 is located at the inner side of the load-bearing member 1, and the supporting member 3 is located at the inner side of the load-bearing member 1. The load-bearing member 1 includes a load-bearing plate 4, a slide groove 5 is provided on the inner side of the load-bearing plate 4, and a support seat 6 is provided on the inner side of the load-bearing plate 4. The clamping member 2 includes a first support bar 7, a clamping member 8 is provided on the upper side of the first support bar 7, and a first support bar 7 is provided at one end of the outer side thereof. A mounting plate 9 is provided, a second mounting plate 10 is provided at the other end position of the outer side of the first support bar 7, a screw rod 11 is installed at the corresponding side position of the second mounting plate 10 and the first mounting plate 9, a motor 12 is installed at the position of the outer side of the second mounting plate 10 corresponding to the screw rod 11, a first slider 13 is provided at one end position of the first support bar 7, a first rotating hole 14 is opened at the upper side of the carrier plate 4 near the support seat 6, a first rotating column 15 is provided at the lower side position of the other end of the first support bar 7, and the first slider 13 slides on the slide The first rotating column 15 is rotated at the inner position of the first rotating hole 14, the screw rod 11 is rotated at the corresponding side positions of the first mounting plate 9 and the second mounting plate 10 through the motor 12, the screw rod 11 is rotated at the lower end position of the clamping member 8, and the clamping member 8 slides at the upper side position of the first support bar 7. First, a spacecraft structural component quick clamping tool is fixed to the use position through the bearing member 1, and then, according to the shape of the spacecraft structural component, the first slider 13 slides on the inner side of the slide groove 5, and the first rotating rod 11 is rotated at the corresponding side positions of the first mounting plate 9 and the second mounting plate 10. The column 15 rotates inside the first rotating hole 14 to adjust the angle of the clamping member 2. According to the position of the clamping member 2, the supporting member 3 is installed to the inner side of the carrier plate 4, and the angle of the supporting member 3 is adjusted. Finally, the spacecraft structure is placed on the upper side of the support seat 6. The first support bar 7 and the supporting member 3 support the spacecraft structure. The motor 12 drives the screw rod 11 to rotate on the corresponding sides of the first mounting plate 9 and the second mounting plate 10. The screw rod 11 rotates at the lower end of the clamping member 8, and the clamping member 8 clamps the spacecraft structure.

[0018] exist Figure 2 , 3, 4, 5: an adjusting groove 16 is provided at the upper outer end position of the carrying plate 4, an adjusting screw 17 is provided on the upper side of the first slider 13, a fixing nut 18 is installed on the outer side of the adjusting screw 17, a guide groove 19 is provided on the upper side of the first support bar 7, the clamping member 8 includes a clamping plate 20, and second sliders 21 are provided at both ends of the lower side of the clamping plate 20, a mounting groove 22 is provided on the lower side of the clamping plate 20, a rotating wheel 23 is installed on the inner side of the mounting groove 22, the adjusting screw 17 corresponds to the position of the adjusting groove 16, the adjusting screw 17 slides at the inner position of the adjusting groove 16, the adjusting screw 17 is fixed at the inner position of the adjusting groove 16 by the fixing nut 18, the rotating wheel 23 rotates at the inner position of the mounting groove 22, the rotating wheel 23 rotates at the inner position of the guiding groove 19, the screw rod 11 rotates at the lower end position of the second slider 21, and according to the shape of the spacecraft structure, the adjusting screw 17 slides on the inner side of the adjusting groove 16, the first sliding block 13 slides on the inner side of the sliding groove 5, the first rotating column 15 rotates inside the first rotating hole 14 to adjust the angle of the clamping member 2, and the fixing nut 18 rotates on the upper end of the adjusting screw 17 to fix the adjusting screw 17 to the inner side of the adjusting groove 16. According to the position of the clamping member 2, the supporting member 3 is installed on the inner side of the supporting plate 4 to adjust the angle of the supporting member 3. Finally, the spacecraft structure is placed on the upper side of the supporting seat 6, and the first supporting bar 7 and the supporting member 3 support the spacecraft structure. The operation of the motor 12 drives the screw rod 11 to rotate on the corresponding sides of the first mounting plate 9 and the second mounting plate 10. The screw rod 11 rotates at the lower end of the second sliding block 21, and drives the clamping plate 20 to slide on the upper side of the first supporting bar 7 through the second sliding block 21. The rotating wheel 23 rolls on the inner side of the guide groove 19 to guide the clamping plate 20, and the clamping plate 20 clamps the spacecraft structure.

[0019] exist Figure 2 , 6Middle: A second rotating hole 24 is provided on the upper side of the carrier plate 4 near the first rotating hole 14, the supporting member 3 comprises a second supporting bar 25, a second rotating column 26 is provided at the lower side of one end of the second supporting bar 25, a sliding bar 27 is provided at the other end of the second supporting bar 25, a baffle 28 is provided at the front end of the sliding bar 27, a third sliding block 29 is provided at the front side of the baffle 28, a spring 30 is installed at the outer side of the sliding bar 27 at the corresponding side position of the second supporting bar 25 and the baffle 28, and the second rotating column 26 rotates at the inner position of the second rotating hole 24, The rear end of the slide rod 27 slides to the front end position of the second support bar 25, and the third slider 29 slides to the inner side position of the slide groove 5. According to the position of the clamping member 2, the supporting member 3 is installed to the inner side of the supporting plate 4. During the installation process, the third slider 29 slides into the inner side of the slide groove 5, and the rear end of the slide rod 27 slides at the front end of the second support bar 25. The spring 30 contracts, and the second rotating column 26 is inserted into the second rotating hole 24. The third slider 29 slides on the inner side of the slide groove 5, and the second rotating column 26 rotates inside the second rotating hole 24 to adjust the angle of the supporting member 3.

[0020] The working principle of the present invention is as follows: first, a spacecraft structural component quick clamping fixture is fixed to the use position through the bearing member 1, and then, according to the shape of the spacecraft structural component, the adjusting screw 17 slides on the inner side of the adjusting groove 16, the first slider 13 slides on the inner side of the slide groove 5, the first rotating column 15 rotates inside the first rotating hole 14 to adjust the angle of the clamping member 2, the fixing nut 18 rotates on the upper end of the adjusting screw 17, and the adjusting screw 17 is fixed to the inner side of the adjusting groove 16, and the supporting member 3 is installed to the inner side of the bearing plate 4 according to the position of the clamping member 2. During the installation process, the third slider 29 slides into the inner side of the slide groove 5, and the rear end of the sliding rod 27 slides on the front end of the second supporting bar 25. The spring 30 contracts, the second rotating column 26 is inserted into the second rotating hole 24, the third slider 29 slides on the inner side of the slide groove 5, the second rotating column 26 rotates inside the second rotating hole 24, and the angle of the supporting member 3 is adjusted. Finally, the spacecraft structure is placed on the upper side of the support seat 6, the first support bar 7 and the second support bar 25 support the spacecraft structure, the motor 12 runs to drive the screw rod 11 to rotate on the corresponding sides of the first mounting plate 9 and the second mounting plate 10, the screw rod 11 rotates at the lower end of the second slider 21, and drives the splint 20 to slide on the upper side of the first support bar 7 through the second slider 21, the rotating wheel 23 rolls on the inner side of the guide groove 19 to guide the splint 20, and the splint 20 clamps the spacecraft structure.

[0021] It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above and that the invention can be implemented in other specific forms without departing from the spirit or essential features of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations falling within the meaning and scope of the equivalent elements of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.

[0022] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A rapid clamping fixture for a spacecraft structure, comprising a load-bearing component (1), a clamping component (2) and a supporting component (3), wherein the clamping component (2) is located at an inner side of the load-bearing component (1), and the supporting component (3) is located at an inner side of the load-bearing component (1), and wherein: The bearing member (1) comprises a bearing plate (4), a slide groove (5) is provided on the inner side of the bearing plate (4), a support seat (6) is provided on the inner side of the bearing plate (4), the clamping member (2) comprises a first support bar (7), a clamping member (8) is provided on the upper side of the first support bar (7), a first mounting plate (9) is provided at one end of the outer side of the first support bar (7), a second mounting plate (10) is provided at the other end of the outer side of the first support bar (7), a screw rod (11) is installed at the corresponding side positions of the second mounting plate (10) and the first mounting plate (9), a motor (12) is installed at the outer side of the second mounting plate (10) at the position corresponding to the screw rod (11), a first sliding block (13) is provided at one end of the first support bar (7), a first rotating hole (14) is provided on the upper side of the bearing plate (4) adjacent to the support seat (6), and a first rotating column (15) is provided at the lower side of the other end of the first support bar (7).

2. A quick clamping fixture for aerospace structural parts according to claim 1, characterized in that: An adjusting groove (16) is provided at the outer end of the upper side of the carrier plate (4); an adjusting screw (17) is provided on the upper side of the first slider (13); a fixing nut (18) is installed on the outer side of the adjusting screw (17); a guide groove (19) is provided on the upper side of the first support bar (7); the clamping member (8) comprises a clamping plate (20); second sliders (21) are provided at both ends of the lower side of the clamping plate (20); a mounting groove (22) is provided on the lower side of the clamping plate (20); a rotating wheel (23) is installed on the inner side of the mounting groove (22).

3. The rapid clamping fixture for aerospace structural parts according to claim 1, characterized in that: A second rotating hole (24) is provided on the upper side of the carrier plate (4) adjacent to the first rotating hole (14); the supporting member (3) comprises a second supporting bar (25); a second rotating column (26) is provided at the lower side of one end of the second supporting bar (25); a sliding bar (27) is provided at the other end of the second supporting bar (25); a baffle plate (28) is provided at the front end of the sliding bar (27); a third sliding block (29) is provided at the front side of the baffle plate (28); and a spring (30) is installed on the outer side of the sliding bar (27) at the corresponding side position of the second supporting bar (25) and the baffle plate (28).

4. The rapid clamping fixture for aerospace structural parts according to claim 1, characterized in that: The first sliding block (13) slides at an inner position of the sliding groove (5), and the first rotating column (15) rotates at an inner position of the first rotating hole (14).

5. The rapid clamping fixture for aerospace structural parts according to claim 1, characterized in that: The screw rod (11) is rotated at corresponding side positions of the first mounting plate (9) and the second mounting plate (10) by a motor (12), the screw rod (11) is rotated at the lower end position of the clamping member (8), and the clamping member (8) slides at the upper side position of the first support bar (7).

6. A spacecraft structural component rapid clamping tool according to claim 2, characterized in that: The adjusting screw (17) corresponds to the position of the adjusting slot (16), the adjusting screw (17) slides at the inner position of the adjusting slot (16), and the adjusting screw (17) is fixed at the inner position of the adjusting slot (16) by a fixing nut (18).

7. A quick clamping fixture for aerospace structural parts according to claim 2, characterized in that: The rotating wheel (23) rotates at an inner position of the mounting groove (22), the rotating wheel (23) rotates at an inner position of the guide groove (19), and the screw rod (11) rotates at a lower end position of the second sliding block (21).

8. The rapid clamping fixture for aerospace structural parts according to claim 3, characterized in that: The second rotating column (26) rotates at an inner position of the second rotating hole (24), the rear end of the sliding rod (27) slides at a front end position of the second supporting bar (25), and the third sliding block (29) slides at an inner position of the sliding groove (5).

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