Clamping device for aircraft parts

Abstract

According to the clamping device for the aircraft parts, in the device, a fixed head is connected to the top of a hoisting top plate, and a rotating head is rotationally connected to the top of the fixed head; in the elastic clamping adjustable mechanism, two guide rods of an assembling component symmetrically penetrate through the two ends of the hoisting top plate in a sliding mode and are fixedly connected with the top of the hoisting bottom plate so as to adjust the distance between the hoisting bottom plate and the hoisting top plate; assembling grooves are formed in the tops of the two supporting tables symmetrically installed at the two ends of the hoisting bottom plate so as to install the multiple elastic supporting assemblies; the two groups of positioning assemblies are symmetrically mounted at the two ends of the hoisting bottom plate and are used for limiting the aircraft parts in the hoisting bottom plate in the horizontal direction; the limiting mechanism is installed at the bottom of the hoisting top plate and used for limiting the aircraft parts between the hoisting bottom plate and the hoisting top plate in the vertical direction. The clamping device provided by the invention has high flexibility and adaptability, and can ensure the safety of a structural part in the transfer process of a machined part.

Description

Technical Field

[0001] The present invention relates to but is not limited to the technical field of parts clamping, and in particular to a clamping device for aircraft parts. Background Art

[0002] In the modern aviation industry, the production of small aircraft structural parts is a highly precise and technically demanding process. These small structural parts usually have complex geometric shapes and strict performance requirements. Traditional clamping tools are usually based on standardized designs. Such clamping tools can well adapt to structural parts with relatively simple geometric shapes. However, for multi-variety, small and special-shaped structural parts, such traditional clamping tools face significant challenges.

[0003] When clamping and transferring parts, especially for the clamping and transfer of multi-variety, small-shaped structural parts, traditional clamping tools often need to frequently replace the clamps or adjust the clamping method. This is because the design of standardized clamps is difficult to adapt to structural parts of different shapes and sizes. Especially when faced with complex geometric shapes, standard clamps may not provide sufficient support and stability. Frequent clamp replacement or adjustment of clamping methods not only increases the complexity of operation, but also leads to the extension of processing cycle, which in turn affects production efficiency. Summary of the invention

[0004] Purpose of the present invention: In order to solve the above-mentioned technical problems, an embodiment of the present invention provides a clamping device for aircraft parts to solve the problem that when using existing clamping tools to clamp and transport aircraft parts, the clamps need to be frequently replaced or the clamping method needs to be adjusted, thereby increasing the complexity of the operation, extending the processing cycle, and affecting the production efficiency.

[0005] Technical solution of the present invention: The embodiment of the present invention provides a clamping device for aircraft parts, comprising: a hoisting top plate 1, a fixed head 2, a rotating head 3, an elastic clamping adjustable mechanism 4 and a limiting mechanism 5;

[0006] Wherein, the fixed head 2 is fixedly connected to the top of the hanging top plate 1, and the rotating head 3 is rotatably connected to the top of the fixed head 2;

[0007] The elastic clamping adjustable mechanism 4 includes: an assembly component 41, two support platforms 42, a plurality of elastic support components 43 and two groups of positioning components 44; wherein the assembly component 41 includes two guide rods 411 and a hoisting base plate 412, the two guide rods 411 symmetrically slide through the two ends of the hoisting top plate 1, and are fixedly connected to the top of the hoisting base plate 412 located below the hoisting top plate 1, so as to adjust the distance between the hoisting base plate 412 and the hoisting top plate 1 through the two guide rods 411; the two support platforms 42 are symmetrically installed at the two ends of the hoisting base plate 412, and the top of each support platform 42 is provided with an assembly groove 421 vertically arranged with the hoisting top plate 1, which is used to install a plurality of elastic support components 43 at equal intervals through the assembly groove 421; the two groups of positioning components 44 are symmetrically installed at the two ends of the hoisting base plate 412, and are used to limit the aircraft parts placed in the hoisting base plate 412 in the horizontal direction;

[0008] The limiting mechanism 5 is installed at the bottom of the hoisting top plate 1 and is used to limit the aircraft parts placed between the hoisting bottom plate 412 and the hoisting top plate 1 in the vertical direction.

[0009] Optionally, in the clamping device for aircraft parts as described above, each elastic support assembly 43 includes a clamping bottom plate 431, a support sleeve 432, a support rod 433, a support top plate 434 and a support spring 435;

[0010] The upper end surface of the clamping bottom plate 431 is fixedly connected to the support sleeve 432, the lower end surface of the support top plate 434 is fixedly connected to the support rod 433, the support spring 435 is embedded in the support sleeve 432, and its lower end contacts the upper end surface of the clamping bottom plate 431, the bottom end of the support rod 433 is nested in the support sleeve 432, and its bottom end surface contacts the upper end of the support spring 435, and the support spring 435 is compressed by the support rod 433 to move axially in the support sleeve 432;

[0011] The bottom profile of the snap-on bottom plate 431 matches the groove profile of the assembly groove 421, and the bottom ends of the hanging top plate 1 are provided with snap-on grooves corresponding to the positions of the assembly grooves 421 at both ends, and the top profile of the supporting top plate 434 matches the groove profile of the snap-on groove, so as to embed each elastic support component 43 into the assembly groove 421 through the snap-on bottom plate 431 and into the snap-on groove at the same side of the hanging top plate 1 through the supporting top plate 434.

[0012] Optionally, in the clamping device for aircraft parts as described above, each support platform 42 is provided with a plurality of elastic support components 43 at equal intervals through its assembly slot 421 and the slot on the same side of the hoisting top plate 1;

[0013] Furthermore, the tensions of the support springs 435 in the multiple elastic support assemblies 43 are all different; the tensions of the support springs 435 are determined according to the structure of the parts to be clamped.

[0014] Optionally, in the clamping device for aircraft parts as described above, a guide groove 4121 is provided in the middle of the top end surface of the hoisting bottom plate 412, and bosses are formed at both ends of the guide groove 4121; each of the positioning components 44 includes: an adjusting screw rod 441 and a clamping plate 442;

[0015] The clamping plate 442 is slidably engaged in the guide groove 4121, and one end of the adjusting screw rod 441 is threadedly penetrated through the boss on one side of the hoisting base plate 412, and is rotatably connected to the end face of one side of the clamping plate 442 through its end, and the position of the clamping plate 442 in the guide groove 4121 is adjusted by rotating the adjusting screw rod 441 in the boss;

[0016] The two clamping plates 442 of the two positioning assemblies 44 located in the guide groove 4121 limit the position of the aircraft parts placed in the guide groove 4121 in the horizontal direction.

[0017] Optionally, in the clamping device for aircraft parts as described above, the limiting mechanism 5 includes a plurality of position-adjustable components 51 and fixed components 52;

[0018] A slide groove 11 is provided at the bottom of the hanging top plate 1 , and the plurality of position-adjustable components 51 are slidably engaged in the slide groove 11 , and the fixing component 52 is installed at the bottom of all or part of the position-adjustable components 51 .

[0019] Optionally, in the clamping device for aircraft parts as described above, each of the position-adjustable components 51 includes a slider 511 and a threaded sleeve 512;

[0020] The position-adjustable component 51 is slidably engaged in the bottom slide groove 11 of the hoisting top plate 1 through a slider 511 , one end of the threaded sleeve 512 is fixedly connected to the bottom of the slider 511 , and the other end is used to install the fixed component 52 .

[0021] Optionally, in the clamping device for aircraft parts as described above, the fixing assembly 52 includes: a limiting sleeve 521, a limiting rod 522, a limiting spring 523, a fixing plate 524 and a resisting pad 525;

[0022] One end of the limiting sleeve 521 is threadedly fixedly connected to the bottom end of the threaded sleeve 512 at the corresponding position, the limiting rod 522 is threadedly connected to the top surface of the fixing plate 524, and after the limiting spring 523 is nested in the limiting sleeve 521, the top end of the limiting rod 522 is embedded in the limiting sleeve 521, so that the limiting spring 523 is located between the bottom end of the threaded sleeve 512 and the top end of the limiting rod 522; and the bottom end of the fixing plate 524 is fixedly connected to the abutment pad 525;

[0023] Multiple limiting mechanisms 5 are located between the lifting top plate 1 and the aircraft parts placed in the guide groove 4121 of the lifting bottom plate 412, and contact the top of the aircraft parts through the resistance pad 525. The aircraft parts apply an upward force to the limiting spring 523 through the fixing plate 524 and the limiting rod 522.

[0024] Optionally, in the clamping device for aircraft parts as described above, the limiting mechanism 5 further comprises: a small part clamping assembly 53; the small part clamping assembly 53 is installed at the bottom of the fully or partially position-adjustable assembly 51; the small part clamping assembly 53 comprises: a disassembly head 531, a drive motor 532, a rotating arm 533, a positioning plate 534, a clamping sleeve 535, a pull rod 536, a clamping plate 537 and a tension spring 538;

[0025] The top of the disassembly head 531 is screwed and fixed to the bottom of the threaded sleeve 512, the drive motor 532 is installed at the bottom of the disassembly head 531, the top of the rotating arm 533 is fixedly connected to the output end of the drive motor 532, the bottom of the rotating arm 533 is fixedly connected to the top surface of the positioning plate 534, and the positioning plate 534 is symmetrically screwed with a connecting joint 5341 to be fixedly connected to the clamping sleeve 535 located below it through the connecting joint;

[0026] The clamping sleeve 535 includes a top plate and two side plates located at the bottom of both ends of the top plate, and is threadedly connected to the bottom of each connecting joint 5342 through its top plate. Two pull rods 536 are symmetrically arranged and correspondingly slide through the two side plates of the clamping sleeve 535. Each pull rod 536 passes through the inner end of the side plate at the corresponding position and is threadedly connected to a clamping plate 537. The tension spring 538 is sleeved on the pull rod 536, and the two ends of the tension spring 538 are respectively fixedly connected to the outer wall of the side plate on the same side and the inner wall of the pull rod 536; the clamping sleeve 535 is driven to rotate by the driving motor 532, and the pull rod 536 is pulled to clamp the other two sides of the aircraft part in the horizontal direction using two clamping plates 537.

[0027] Optionally, the clamping device for aircraft parts as described above further comprises: an auxiliary sleeve plate 6;

[0028] For the hoisting base plate 412 whose length exceeds the preset threshold, the auxiliary sleeve plate 6 is fixedly connected to the bottom of the hoisting base plate 412 to enhance the rigidity of the hoisting base plate 412 .

[0029] Optionally, in the clamping device for aircraft parts as described above, the elastic clamping adjustable mechanism 4 further includes: a connecting arm 422, a supporting platform 423, a limiting plate 424 and a limiting bolt 425;

[0030] The two ends of the bottom of each support platform 42 are connected to the support platform 423 through fixed connecting arms 422, and the same side ends of the two support platforms 42 are connected to the same support platform 423 through one connecting arm 422 respectively;

[0031] The two side walls of the bosses at both ends of the lifting base plate 412 are respectively fixedly connected to the limiting plates 424, and each limiting plate 424 is located at the bottom of the support platform 42 at the same end, and the bottom of the limiting plate 424 is threadedly installed with a limiting bolt 425; the bottom of the support platform 42 is provided with a plurality of screw holes at equal intervals, which are used to screw and fix the limiting bolts 425 to the screw holes at the corresponding positions of the bottom of the support platform 42 after adjusting the position of the support platform 42, thereby fixing the position of the support platform 42.

[0032] Beneficial effects of the invention: The embodiment of the invention provides a clamping device for aircraft parts, which has the following beneficial effects:

[0033] First, in the present invention, two groups of positioning components are provided and installed at the end of the assembly component, and the limiting mechanism is installed at the bottom of the lifting top plate. Then, according to different structural parts, the position of the support platform in the assembly component can be adjusted, thereby the adaptive elastic support component and the lifting top plate can be connected to each other, and the limiting mechanism and the positioning component can ensure stable clamping of the structural parts, and can also be replaced accordingly according to the different structural parts that need to be clamped. Therefore, it has a high degree of flexibility and adaptability, and can ensure the safety of the structural parts and avoid any form of damage to them during the transportation of processed parts.

[0034] Second, the tensions of the multiple support springs in the present invention are all different, and thus, through the sliding support platform, different support top plates can be clamped on the inner wall of the slot at the bottom of the lifting top plate. Before the support top plate is clamped in the slot, it is necessary to pull the support top plate upward so that it is on the same horizontal line as the slot. After the support top plate is clamped in the slot, the lifting top plate can be driven downward under the action of the support springs, thereby avoiding the difficulty in accurately controlling the elastic clamping force. If the clamping force is too large, it is easy to cause damage to structural parts with brittle materials or delicate designs, such as surface scratches or microcracks caused by internal stress concentration.

[0035] Third, in the present invention, one end of the limit sleeve is fixedly connected to the bottom of the slider, one end of the limit rod slides through the other end of the limit sleeve through the limit spring, the fixing plate is threadedly sleeved on the other end of the limit rod, and the resistance pad is fixedly connected to the bottom of the fixing plate, so that the hoisting top plate moves downward under the action of the supporting spring, thereby driving the resistance pad to resist and clamp on the top of the structural member, and under the action of the limit spring, auxiliary clamping can be performed, thereby ensuring that the structural member is more stable during the transportation of processed parts.

[0036] Fourthly, the present invention drives the clamping sleeve to rotate by driving the motor, thereby realizing the function of rotational clamping. Meanwhile, the clamping directions of the two clamping plates are perpendicular to each other. When the pull rod is released, the clamping plates will clamp the small structural parts under the action of the tension spring. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] The accompanying drawings are used to provide a further understanding of the technical solution of the present invention and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the technical solution of the present invention and do not constitute a limitation on the technical solution of the present invention.

[0038] Figure 1 A schematic diagram of a clamping device for aircraft parts provided by an embodiment of the present invention Figure 1 ;

[0039] Figure 2 A schematic diagram of a clamping device for aircraft parts provided by an embodiment of the present invention Figure 2 ;

[0040] Figure 3 A schematic diagram of a clamping device for aircraft parts provided by an embodiment of the present invention Figure 3 ;

[0041] Figure 4 A schematic diagram of a clamping device for aircraft parts provided by an embodiment of the present invention Figure 4 ;

[0042] Figure 5 A schematic diagram of a clamping device for aircraft parts provided by an embodiment of the present invention Figure 5 ;

[0043] Figure 6 for Figure 5 A schematic diagram of a partially enlarged structure of region A in a clamping device for aircraft parts provided by the illustrated embodiment;

[0044] Figure 7 for Figure 5 A schematic diagram of a partially enlarged structure of region B in a clamping device for aircraft parts provided by the illustrated embodiment;

[0045] Figure 8for Figure 1 A schematic structural diagram of some components of a clamping device for aircraft parts provided by the illustrated embodiment;

[0046] Fig. 9 A schematic structural diagram of a small-sized part clamping assembly in a clamping device for aircraft parts provided in an embodiment of the present invention.

[0047] Description of reference numerals:

[0048] 1. Lifting top plate; 11. Slide; 2. Fixed head; 3. Rotating head; 4. Elastic clamping adjustable mechanism; 41. Assembly component; 411. Guide rod; 412. Lifting bottom plate; 4121. Guide groove; 42. Support platform; 421. Assembly groove; 422. Connecting arm; 423. Support platform; 424. Limit plate; 425. Limit bolt; 43. Elastic support component; 431. Clamping bottom plate; 432. Support sleeve; 433. Support rod; 434. Support top plate; 435. Support spring; 44. Positioning component; 441. Adjustment wire Rod; 442, clamping plate; 5, limiting mechanism; 51, position adjustable component; 511, slider; 512, threaded sleeve; 52, fixed component; 521, limiting sleeve; 522, limiting rod; 523, limiting spring; 524, fixed plate; 525, contact pad; 53, small parts clamping component; 531, disassembly head; 532, drive motor; 533, rotating arm; 534, positioning plate; 5341, connecting joint; 535, clamping sleeve; 536, pull rod; 537, splint; 538, tension spring; 6, auxiliary sleeve. DETAILED DESCRIPTION

[0049] In order to make the purpose, technical solution and advantages of the present invention more clear, the embodiments of the present invention will be described in detail with reference to the accompanying drawings. It should be noted that the embodiments and features in the embodiments of the present application can be combined with each other arbitrarily without conflict.

[0050] As described in the above background technology, small structural parts usually have complex geometric shapes and strict performance requirements. The clamping and transportation of various small and special-shaped structural parts require frequent replacement of clamps or adjustment of clamping methods due to the use of traditional clamping tools, which increases the complexity of operation, prolongs the processing cycle, and thus affects production efficiency.

[0051] In addition, usually, the clamping tools used to clamp structural parts have a single elastic force. For structural parts with brittle materials or delicate designs, the fixed clamping force may cause damage to these sensitive structural parts, such as indentations, cracks or deformations, thereby affecting the integrity and function of the structural parts.

[0052] In view of the above problems, an embodiment of the present invention provides a clamping device for aircraft parts. The clamping device for aircraft parts provided by the embodiment of the present invention can solve the problem that the clamping device for clamping large aircraft structural parts has a single elastic force, which means that the clamping force is fixed. Although this design simplifies the structure of the clamping device, it is not suitable for all types of structural parts, especially for structural parts with brittle materials or delicate designs. The fixed clamping force may cause damage to these sensitive parts, such as indentations, cracks or deformations, thereby affecting the integrity and function of the structural parts.

[0053] The present invention provides the following specific embodiments which can be combined with each other. The same or similar concepts or processes may not be described in detail in some embodiments.

[0054] like Figure 1-Figure 9 As shown, the clamping device for aircraft parts according to the embodiment of the present invention may include a hoisting top plate 1, a fixed head 2, a rotating head 3, an elastic clamping adjustable mechanism 4 and a limiting mechanism 5.

[0055] The fixed head 2 is fixedly connected to the top of the hanging top plate 1 , and the rotating head 3 is rotatably connected to the top of the fixed head 2 .

[0056] In a specific embodiment, the method for realizing the rotational connection of the rotating head 3 can be: a threaded groove is opened on the inner wall of the rotating head 3, and a threaded rod is fixedly connected to the output end through an external driving structure, and one end of the threaded rod is threadedly installed on the inner wall of the rotating head 3, thereby the rotating head 3 can be driven to rotate through the driving structure, thereby driving the clamping mechanism to rotate.

[0057] In the embodiment of the present invention, the elastic clamping adjustable mechanism 4 includes an assembly component 41, two support platforms 42, a plurality of elastic support components 43 and two groups of positioning components 44. Among them, the assembly component 41 includes two guide rods 411 and a hoisting base plate 412. The two guide rods 411 slide symmetrically through the two ends of the hoisting top plate 1 and are fixedly connected to the top of the hoisting base plate 412 located below the hoisting top plate 1, so as to adjust the distance between the hoisting base plate 412 and the hoisting top plate 1 through the two guide rods 411; the two support platforms 42 are symmetrically installed at the two ends of the hoisting base plate 412, and the top of each support platform 42 is provided with an assembly groove 421 vertically arranged with the hoisting top plate 1, which is used to install a plurality of elastic support components 43 at equal intervals through the assembly groove 421; the two groups of positioning components 44 are symmetrically installed at the two ends of the hoisting base plate 412, and are used to limit the aircraft parts placed in the hoisting base plate 412 in the horizontal direction.

[0058] It should be noted that the support platform 42 described in this embodiment is vertically arranged with respect to the assembly component 41. In addition, the clamping end of the positioning component 44 described in this embodiment can be slidably mounted on the assembly component 41, and the stability of the structural component during the transportation of the processed parts can be ensured by two sets of positioning components 44.

[0059] It should be noted that, in the embodiment described, a limiting head is fixedly connected to the top of the guide rod 411, and a concave groove is provided on the top of the lifting base plate 412, and a structural member can be placed in the groove and limited.

[0060] The limiting mechanism 5 in the embodiment of the present invention is installed at the bottom of the hoisting top plate 1, and is used to limit the aircraft parts placed between the hoisting bottom plate 412 and the hoisting top plate 1 in the vertical direction. It can be understood that the limiting mechanism 5 in the embodiment of the present invention provides auxiliary clamping, and the main clamping force of the structural parts comes from the elastic support assembly 43.

[0061] In one implementation of the embodiment of the present invention, Figure 6 As shown, each elastic support assembly 43 includes a clamping bottom plate 431 , a support sleeve 432 , a support rod 433 , a support top plate 434 and a support spring 435 .

[0062] In this implementation, the upper end surface of the clamping base plate 431 is fixedly connected to the support sleeve 432, the lower end surface of the support top plate 434 is fixedly connected to the support rod 433, the support spring 435 is embedded in the support sleeve 432, and its lower end contacts the upper end surface of the clamping base plate 431, the bottom end of the support rod 433 is nested in the support sleeve 432, and its bottom end surface contacts the upper end of the support spring 435, and the support spring 435 is compressed by the support rod 433 to move axially in the support sleeve 432.

[0063] It should be noted that the guide plates are symmetrically fixedly connected to the two sides of the support top plate 434 in this implementation, and the inner wall of the card slot is symmetrically provided with card slots matching the guide plates. In addition, the guide plates are symmetrically fixedly connected to the two sides of the support top plate 434, and the inner wall of the card slot is symmetrically provided with card slots matching the guide plates.

[0064] In this implementation, the bottom profile of the snap-on bottom plate 431 matches the groove profile of the assembly groove 421, and the two ends of the bottom of the hanging top plate 1 are provided with snap-on grooves corresponding to the positions of the assembly grooves 421 at both ends, and the top profile of the supporting top plate 434 matches the groove profile of the snap-on groove, so as to embed each elastic support component 43 into the assembly groove 421 through the snap-on bottom plate 431 and into the snap-on groove at the same side of the hanging top plate 1 through the supporting top plate 434.

[0065] Furthermore, each support platform 42 is provided with a plurality of elastic support components 43 at equal intervals through its assembly groove 421 and the slot on the same side of the hanging top plate 1 .

[0066] It should be noted that the tension of the support spring 435 in the multiple elastic support assemblies 43 in this implementation is different, so that the different elastic support assemblies 43 can be adjusted to be connected to the hanging top plate 1 through the sliding support platform 42, so that the clamping force can be adjusted, and then the different elastic support assemblies 43 can be adjusted according to the different structural parts. In the specific implementation, the tension of the support spring 435 is determined according to the structure of the part to be clamped. For parts to be clamped with different structures, the parts are clamped by using support springs with corresponding tensions to meet the needs of stable and reliable clamping of different parts.

[0067] In one implementation of the embodiment of the present invention, a guide groove 4121 is provided in the middle of the top surface of the hoisting bottom plate 412, and bosses are formed at both ends of the guide groove 4121; each positioning assembly 44 includes: an adjusting screw rod 441 and a clamping plate 442; Figure 1 and Figure 2 shown.

[0068] In the implementation method, the clamping plate 442 is slidably clamped in the guide groove 4121, and after one end of the adjusting screw rod 441 is threaded through the boss on one side of the lifting base plate 412, its end is rotatably connected to the end face of one side of the clamping plate 442, and the position of the clamping plate 442 in the guide groove 4121 is adjusted by rotating the adjusting screw rod 441 in the boss.

[0069] It should be noted that in this implementation, the two clamping plates 442 of the two positioning components 44 are located in the guide groove 4121 to limit the position of the aircraft parts placed in the guide groove 4121 in the horizontal direction. In addition, the bottom of the clamping plate 442 in this implementation is fixedly connected with a guide block, the inner wall of the guide block is in contact with the inner wall of the guide groove 4121, and the other end of the adjusting screw rod 441 is fixedly connected with an adjusting head, and the outer wall of the adjusting head is provided with anti-slip patterns.

[0070] As a possible situation, the end of the clamping plate 442 is an arc-shaped structure, and the inner wall of the clamping plate 442 is fixedly connected with a soft clamping pad.

[0071] The limiting mechanism 5 in the embodiment of the present invention is installed at the bottom of the hanging top plate 1. The limiting mechanism 5 provides a downward clamping force on the hanging top plate 1, thereby cooperating with the two sets of positioning components 44 to further ensure the stability of the clamping.

[0072] In one embodiment of the present invention, Figure 1-Figure 9As shown, the limiting mechanism 5 includes a plurality of position adjustable components 51 and a fixed component 52. In this implementation, a slide groove 11 is provided at the bottom of the hanging top plate 1, and the plurality of position adjustable components 51 are slidably engaged in the slide groove 11, and the fixed component 52 is installed at the bottom of all or part of the position adjustable components 51.

[0073] In one embodiment of the present invention, Figure 1-Figure 9 As shown, the position adjustable component 51 includes a slider 511 and a threaded sleeve 512. The position adjustable component 51 is slidably engaged in the bottom slide groove 11 of the hanging top plate 1 through the slider 511, one end of the threaded sleeve 512 is fixedly connected to the bottom of the slider 511, and the other end is used to install the fixed component 52.

[0074] Specifically, in order to limit the top of the structural member and ensure the stability of the processing, a slide groove 11 is opened at the bottom of the lifting top plate 1, and multiple position-adjustable components 51 are slidably engaged on the inner wall of the slide groove 11, and multiple fixed components 52 are installed on the corresponding position-adjustable components 51. Then, according to the size of the structural member, the corresponding fixed component 52 can be installed on the position-adjustable component 51, and then by adjusting the position of the fixed component 52, the corresponding fixed component 52 can be made to contact the top of the frame member, thereby further improving the stability of the structural member.

[0075] It should be noted that the two sides of the sliding block 511 described in this embodiment are symmetrically fixedly connected with guide bars, and the inner wall of the sliding groove 11 is provided with a clamping groove matching the guide bar.

[0076] Specifically, in order to conveniently adjust the clamping position of structural members of different sizes, the slider 511 is slidably engaged with the inner wall of the slide groove 11, and one end of the threaded sleeve 512 is fixedly connected to the bottom of the slider 511. Then, by adjusting the position of the slider 511 in the slide groove 11, after the adjustment is completed, the corresponding fixing component 52 can be threadedly installed in the threaded sleeve 512, thereby enabling the same horizontal position on the structural member to be clamped.

[0077] In one embodiment of the present invention, Figure 1-Figure 9 As shown, the fixing assembly 52 includes: a limiting sleeve 521, a limiting rod 522, a limiting spring 523, a fixing plate 524 and a contact pad 525. Among them, one end of the limiting sleeve 521 is threadedly fixedly connected to the bottom end of the threaded sleeve 512 at the corresponding position, the limiting rod 522 is threadedly connected to the top surface of the fixing plate 524, and after the limiting spring 523 is nested in the limiting sleeve 521, the top end of the limiting rod 522 is embedded in the limiting sleeve 521, so that the limiting spring 523 is located between the bottom end of the threaded sleeve 512 and the top end of the limiting rod 522; and the bottom end of the fixing plate 524 is fixedly connected to the contact pad 525.

[0078] Specifically, in order to limit and clamp the structural parts accordingly, one end of the limit sleeve 521 is threadedly connected to the other end of the threaded sleeve 512, one end of the limit rod 522 slides through the other end of the limit sleeve 521 through the limit spring 523, the fixed plate 524 is threadedly sleeved on the other end of the limit rod 522, and the resistance pad 525 is fixedly connected to the bottom of the fixed plate 524, and then the lifting top plate 1 moves downward under the action of the support spring 435, thereby driving the resistance pad 525 to resist and clamp on the top of the structural parts, and under the action of the limit spring 523, auxiliary clamping can be performed, thereby ensuring that the structural parts are more stable during the transportation of processed parts.

[0079] In a specific implementation, a plurality of limiting mechanisms 5 are located between the lifting top plate 1 and the aircraft parts placed in the guide groove 4121 of the lifting bottom plate 412, and contact the top of the aircraft parts through the resistance pad 525, and the aircraft parts apply an upward force to the limiting spring 523 through the fixing plate 524 and the limiting rod 522.

[0080] In the embodiment of the present invention, in order to ensure the clamping stability of the structural member, one end of the adjusting screw rod 441 is threadedly penetrated through the side wall of the lifting base plate 412 and is rotatably connected to one side of the clamping plate 442. A guide groove 4121 is opened on the top of the lifting base plate 412, and the clamping plate 442 is slidably engaged in the guide groove 4121. Then, by rotating the adjusting screw rod 441, the position of the clamping plate 442 on the guide groove 4121 can be adjusted, so that the two sides of the structural member can be clamped by the two clamping plates 442, thereby ensuring the stability of the structural member, thereby ensuring that the structural member is not easy to shake during the processing.

[0081] In one embodiment of the present invention, Figure 1-Figure 9 As shown, the limiting mechanism 5 may further include: a small parts clamping assembly 53. It should be noted that the small parts clamping assembly 53 is installed at the bottom of all or part of the position adjustable assembly 51; the small parts clamping assembly 53 includes: a disassembly head 531, a drive motor 532, a rotating arm 533, a positioning plate 534, a clamping sleeve 535, a pull rod 536, a clamping plate 537 and a tension spring 538.

[0082] In this implementation, the top of the disassembly head 531 is screwed and fixed to the bottom end of the threaded sleeve 512, the drive motor 532 is installed at the bottom end of the disassembly head 531, the top of the rotating arm 533 is fixedly connected to the output end of the drive motor 532, the bottom end of the rotating arm 533 is fixedly connected to the top surface of the positioning plate 534, and the positioning plate 534 is symmetrically screwed with a connecting joint 5341 to fix the clamping sleeve 535 located therebelow through the connecting joint.

[0083] The clamping sleeve 535 includes a top plate and two side plates located at the bottom of both ends of the top plate, and is threadedly connected to the bottom of each connecting joint 5342 through its top plate. Two pull rods 536 are symmetrically arranged and correspondingly slide through the two side plates of the clamping sleeve 535. Each pull rod 536 passes through the inner end of the side plate at the corresponding position and is threadedly connected to a clamping plate 537. The tension spring 538 is sleeved on the pull rod 536, and the two ends of the tension spring 538 are respectively fixedly connected to the outer wall of the side plate on the same side and the inner wall of the pull rod 536; the clamping sleeve 535 is driven to rotate by the driving motor 532, and the pull rod 536 is pulled to clamp the other two sides of the aircraft part in the horizontal direction using two clamping plates 537.

[0084] In a specific implementation, a connection joint 5341 is symmetrically threaded through the top of the positioning plate 534 , and a screw hole matching the end of the connection joint 5341 is opened on the top of the clamping sleeve 535 .

[0085] In a specific implementation, the limiting mechanism 5 can be combined with a fixing component 52 and a small part clamping component 53. For example, for an area where the upper end surface of the part to be clamped is flat, the fixing component 52 is used for upper and lower limiting. For an area where the top of the part to be clamped has a protrusion, the small part clamping component 53 is used for multi-directional clamping.

[0086] In an implementation of the embodiment of the present invention, the clamping device for aircraft parts may further include: an auxiliary sleeve plate 6 .

[0087] In this implementation, for the hoisting base plate 412 whose length exceeds the preset threshold, the auxiliary sleeve plate 6 is fixedly connected at the bottom thereof to enhance the rigidity of the hoisting base plate 412, thereby ensuring the stability of clamping the long parts.

[0088] Specifically, an auxiliary supporting structure is slidably connected to the inner wall of the lifting base plate 412. Since the supporting platform 423 is adjusted synchronously with the position of the supporting platform 42, when the length of the structural member is long and the end position of the supporting platform 42 is far away from the position of the lifting top plate 1, the auxiliary supporting structure can be used to support the bottom of the structural member on the other side of the lifting top plate 1, thereby ensuring that the processing of the structural member is more stable.

[0089] In one implementation of the embodiment of the present invention, Figure 5 As shown, the elastic clamping adjustable mechanism 4 further includes: a connecting arm 422 , a supporting platform 423 , a limiting plate 424 and a limiting bolt 425 .

[0090] In this implementation, the two ends of the bottom of each support platform 42 are connected to the support platform 423 through fixedly connected connecting arms 422, and the same side ends of the two support platforms 42 are connected to the same support platform 423 through one connecting arm 422. It should be noted that the top of the support platform 423 in this implementation is covered with a soft rubber pad, and the support platform 423 can provide corresponding support for the longer structural parts.

[0091] In addition, the two side walls of the bosses at both ends of the lifting base plate 412 are respectively fixedly connected with the limiting plates 424, and each limiting plate 424 is located at the bottom of the support platform 42 at the same end, and the bottom of the limiting plate 424 is threadedly installed with a limiting bolt 425; the bottom of the support platform 42 is provided with a plurality of screw holes at equal intervals, which are used to fix the position of the support platform 42 by screwing the limiting bolts 425 to the screw holes at the corresponding positions of the bottom of the support platform 42 after adjusting the position of the support platform 42, thereby fixing the position of the support platform 42.

[0092] Specifically, after the position adjustment of the support platform 42 is completed, the limiting bolt 425 is screwed to the screw hole at the bottom of the support platform 42, thereby ensuring that the position of the support platform 42 is fixed, thereby ensuring that the overall clamping mechanism is more stable.

[0093] The following describes some specific implementations of the present invention:

[0094] Specifically, in aircraft manufacturing, when it is necessary to process aircraft structural parts, in order to ensure the clamping stability of the parts, the assembly component 41 is installed on the lifting top plate 1, the support platform 42 is symmetrically installed on the assembly component 41, and an assembly groove 421 is opened on the top of the support platform 42. There are multiple groups of elastic support components 43, which are evenly spaced and installed on the inner wall of the assembly groove 421. There are two groups of positioning components 44, which are symmetrically installed at the end of the assembly component 41. The limiting mechanism 5 is installed at the bottom of the lifting top plate 1, and then the position of the support platform 42 on the assembly component 41 can be adjusted according to the different structural parts. The adapted elastic support component 43 and the lifting top plate 1 can be connected to each other, and the limiting mechanism 5 and the positioning component 44 can ensure the stable clamping of the structural parts, and can also be replaced accordingly according to the different structural parts that need to be clamped. It has a high degree of flexibility and adaptability, and can ensure that the safety of the structural parts is guaranteed during the transportation of the processed parts, and avoid any form of damage to them.

[0095] Specifically, in order to conveniently process aircraft parts, the guide rod 411 slides symmetrically through the two ends of the lifting top plate 1 and is fixedly connected to the top of the lifting bottom plate 412, so that the structural member is placed in the top groove of the lifting bottom plate 412, and then the two sides of the structural member can be clamped by the positioning component 44, and then under the action of the elastic support component 43, the limiting mechanism 5 can be driven to assist in clamping the top of the structural member.

[0096] Specifically, in order to clamp the parts with appropriate clamping force, multiple clamping bottom plates 431 are fixedly connected to the inner wall of the assembly groove 421 at equal intervals, one end of the support sleeve 432 is fixedly connected to the top of the clamping bottom plate 431, one end of the support rod 433 slides through the other end of the support sleeve 432 through the support spring 435, and the support top plate 434 is fixedly connected to the other end of the support rod 433. A clamping groove matching the support top plate 434 is opened at the bottom of the hanging top plate 1, and the tensions of the multiple support springs 435 are different, so that the sliding support platform 42 , thereby different support top plates 434 can be clamped on the inner wall of the slot at the bottom of the lifting top plate 1. Before the support top plate 434 is clamped in the slot, it is necessary to pull the support top plate 434 upward so that it is on the same horizontal line as the slot. After the support top plate 434 is clamped in the slot, the lifting top plate 1 can be driven downward under the action of the support spring 435, thereby avoiding the difficulty in accurately controlling the elastic clamping force. If the clamping force is too large, it is easy to cause damage to structural parts with brittle materials or delicate designs, such as surface scratches or microcracks caused by internal stress concentration.

[0097] Specifically, when it is necessary to clamp small parts with various structures, firstly, the shapes of small structural parts are mostly irregular. Direct clamping by the clamping device will lead to unstable clamping, which is easy to fall off later. Therefore, when clamping small irregular parts, firstly, two clamping plates 442 are used to clamp the two sides of the structural part, so that the small irregular structural part can be put in a straightened state, and then different disassembly heads 531 are replaced according to the shape and size of the small structural part and installed on the threaded sleeve 512. After the installation is completed, by twisting the disassembly head 531 and pulling the pull rod 536, the clamping surfaces of the two clamping plates 537 can be located on both sides of the small structural part; before clamping, for example For example, by driving the motor 532, the clamping sleeve 535 is driven to rotate, thereby realizing the function of rotational clamping. At the same time, the clamping directions of the two clamping plates 537 and the two clamping plates 442 are perpendicular to each other. When the pull rod 536 is loosened, the clamping plate 537 will clamp the small structural parts under the action of the tension spring 538. At the same time, since one side of the clamping plate 537 is threadedly connected to the end of the pull rod 536, the whole process is easy to operate, and the replacement of the clamping plate 537 can be completed in a short time, which greatly improves the work efficiency of the production line. At the same time, since a section of the thread of the disassembly head 531 passes through the other end of the threaded sleeve 512, the clamping method can be quickly changed, further improving the production efficiency.

[0098] In summary, in the clamping device for aircraft parts of the embodiment of the present invention, multiple groups of elastic support components 43 are provided and are installed at equal intervals on the inner wall of the assembly groove 421, two groups of positioning components 44 are provided and are symmetrically installed at the ends of the assembly component 41, and the limiting mechanism 5 is installed at the bottom of the hanging top plate 1, and then the position of the support platform 42 on the assembly component 41 can be adjusted according to the different structural parts, thereby the adapted elastic support component 43 and the hanging top plate 1 can be connected to each other, and the limiting mechanism 5 and the positioning component 44 can ensure the stable clamping of the structural parts. It can also be replaced accordingly according to the different structural parts that need to be clamped, thereby having a high degree of flexibility and adaptability, and being able to ensure the safety of the structural parts and avoid any form of damage to them during the transportation of processed parts. By driving the motor 532, the clamping sleeve 535 is driven to rotate, thereby realizing the function of rotational clamping. At the same time, the clamping directions of the two clamping plates 537 and the two clamping plates 442 are perpendicular to each other. When the pull rod 536 is released, the clamping plate 537 will clamp the small structural parts under the action of the tension spring 538.

[0099] The clamping device for aircraft parts provided by the embodiment of the present invention has the following beneficial effects:

[0100] First, in the present invention, two groups of positioning components are provided and installed at the end of the assembly component, and the limiting mechanism is installed at the bottom of the lifting top plate. Then, according to different structural parts, the position of the support platform in the assembly component can be adjusted, thereby the adaptive elastic support component and the lifting top plate can be connected to each other, and the limiting mechanism and the positioning component can ensure stable clamping of the structural parts, and can also be replaced accordingly according to the different structural parts that need to be clamped. Therefore, it has a high degree of flexibility and adaptability, and can ensure the safety of the structural parts and avoid any form of damage to them during the transportation of processed parts.

[0101] Second, the tensions of the multiple support springs in the present invention are all different, and thus, through the sliding support platform, different support top plates can be clamped on the inner wall of the slot at the bottom of the lifting top plate. Before the support top plate is clamped in the slot, it is necessary to pull the support top plate upward so that it is on the same horizontal line as the slot. After the support top plate is clamped in the slot, the lifting top plate can be driven downward under the action of the support springs, thereby avoiding the difficulty in accurately controlling the elastic clamping force. If the clamping force is too large, it is easy to cause damage to structural parts with brittle materials or delicate designs, such as surface scratches or microcracks caused by internal stress concentration.

[0102] Third, in the present invention, one end of the limit sleeve is fixedly connected to the bottom of the slider, one end of the limit rod slides through the other end of the limit sleeve through the limit spring, the fixing plate is threadedly sleeved on the other end of the limit rod, and the resistance pad is fixedly connected to the bottom of the fixing plate, so that the hoisting top plate moves downward under the action of the supporting spring, thereby driving the resistance pad to resist and clamp on the top of the structural member, and under the action of the limit spring, auxiliary clamping can be performed, thereby ensuring that the structural member is more stable during the transportation of processed parts.

[0103] Fourthly, the present invention drives the clamping sleeve to rotate by driving the motor, thereby realizing the function of rotational clamping. Meanwhile, the clamping directions of the two clamping plates are perpendicular to each other. When the pull rod is released, the clamping plates will clamp the small structural parts under the action of the tension spring.

[0104] Although the embodiments disclosed in the present invention are as above, the contents are only embodiments adopted to facilitate understanding of the present invention and are not intended to limit the present invention. Any technician in the field to which the present invention belongs can make any modifications and changes in the form and details of implementation without departing from the spirit and scope disclosed in the present invention, but the patent protection scope of the present invention shall still be subject to the scope defined in the attached claims.

Claims

1. A clamping device for aircraft parts, characterized in that: include: A hanging top plate (1), a fixed head (2), a rotating head (3), an elastic clamping adjustable mechanism (4) and a limiting mechanism (5); Wherein, the fixed head (2) is fixedly connected to the top of the hanging top plate (1), and the rotating head (3) is rotatably connected to the top of the fixed head (2); The elastic clamping adjustable mechanism (4) comprises: an assembly component (41), two support platforms (42), a plurality of elastic support components (43) and two groups of positioning components (44); wherein the assembly component (41) comprises two guide rods (411) and a hanging base plate (412), the two guide rods (411) symmetrically slide through the two ends of the hanging top plate (1) and are fixedly connected to the top of the hanging base plate (412) located below the hanging top plate (1), so as to adjust the hanging base plate (412) through the two guide rods (411). 12) and the distance between the hoisting top plate (1); two support platforms (42) are symmetrically installed at the two ends of the hoisting bottom plate (412), and the top of each support platform (42) is provided with an assembly groove (421) arranged perpendicularly to the hoisting top plate (1), and is used to install multiple elastic support components (43) at equal intervals through the assembly groove (421); two groups of positioning components (44) are symmetrically installed at the two ends of the hoisting bottom plate (412), and are used to limit the aircraft parts placed in the hoisting bottom plate (412) in the horizontal direction; The limiting mechanism (5) is installed at the bottom of the hoisting top plate (1) and is used to limit the aircraft parts placed between the hoisting bottom plate (412) and the hoisting top plate (1) in the vertical direction.

2. The clamping device for aircraft parts according to claim 1, characterized in that: Each elastic support assembly (43) comprises a clamping bottom plate (431), a support sleeve (432), a support rod (433), a support top plate (434) and a support spring (435); The upper end surface of the clamping bottom plate (431) is fixedly connected to the support sleeve (432), the lower end surface of the support top plate (434) is fixedly connected to the support rod (433), the support spring (435) is embedded in the support sleeve (432), and its lower end is in contact with the upper end surface of the clamping bottom plate (431), the bottom end of the support rod (433) is embedded in the support sleeve (432), and its bottom end surface is in contact with the upper end of the support spring (435), and the support spring (435) is compressed by the support rod (433) to move axially in the support sleeve (432); The bottom profile of the snap-fit ​​bottom plate (431) matches the groove profile of the assembly groove (421); the bottom ends of the hanging top plate (1) are provided with snap-fit ​​grooves corresponding to the positions of the assembly grooves (421) at both ends; and the top profile of the supporting top plate (434) matches the groove profile of the snap-fit ​​groove, so as to embed each elastic support component (43) into the assembly groove (421) through the snap-fit ​​bottom plate (431) and into the snap-fit ​​groove at the same side of the hanging top plate (1) through the supporting top plate (434).

3. The clamping device for aircraft parts according to claim 2, characterized in that: Each support platform (42) is provided with a plurality of elastic support components (43) at equal intervals through its assembly groove (421) and the slot on the same side of the hanging top plate (1); Furthermore, the tensions of the support springs (435) in the multiple elastic support components (43) are all different; the tensions of the support springs (435) are determined according to the structure of the parts to be clamped.

4. The clamping device for aircraft parts according to claim 3, characterized in that: A guide groove (4121) is provided in the middle of the top end surface of the hoisting bottom plate (412), and bosses are formed at both ends of the guide groove (4121); each positioning assembly (44) comprises: an adjusting screw rod (441) and a clamping plate (442); The clamping plate (442) is slidably engaged in the guide groove (4121), and one end of the adjusting screw rod (441) is threadedly penetrated through a boss on one side of the hoisting base plate (412), and is rotatably connected to an end face of one side of the clamping plate (442) through its end portion, and the position of the clamping plate (442) in the guide groove (4121) is adjusted by rotating the adjusting screw rod (441) in the boss; The two clamping plates (442) of the two positioning assemblies (44) located in the guide groove (4121) are used to limit the position of the aircraft parts placed in the guide groove (4121) in the horizontal direction.

5. The clamping device for aircraft parts according to claim 1, characterized in that: The limiting mechanism (5) comprises a plurality of position-adjustable components (51) and a fixed component (52); The bottom of the hanging top plate (1) is provided with a slide groove (11), the plurality of position-adjustable components (51) are slidably engaged in the slide groove (11), and the fixed component (52) is installed at the bottom of all or part of the position-adjustable components (51).

6. The clamping device for aircraft parts according to claim 5, characterized in that: Each of the position-adjustable components (51) comprises a slider (511) and a threaded sleeve (512); The position-adjustable component (51) is slidably engaged in the bottom slide groove (11) of the hanging top plate (1) via a slider (511), one end of the threaded sleeve (512) is fixedly connected to the bottom of the slider (511), and the other end is used to install the fixed component (52).

7. The clamping device for aircraft parts according to claim 6, characterized in that: The fixing assembly (52) comprises: a limiting sleeve (521), a limiting rod (522), a limiting spring (523), a fixing plate (524) and a resisting pad (525); One end of the limiting sleeve (521) is threadedly fixedly connected to the bottom end of the threaded sleeve (512) at the corresponding position, the limiting rod (522) is threadedly connected to the top surface of the fixing plate (524), and after the limiting spring (523) is nested in the limiting sleeve (521), the top end of the limiting rod (522) is embedded in the limiting sleeve (521), so that the limiting spring (523) is located between the bottom end of the threaded sleeve (512) and the top end of the limiting rod (522); and the bottom end of the fixing plate (524) is fixedly connected to the contact pad (525); A plurality of limiting mechanisms (5) are located between the lifting top plate (1) and an aircraft part placed in a guide groove (4121) of the lifting bottom plate (412), and are in contact with the top of the aircraft part via a contact pad (525), and the aircraft part applies an upward force to the limiting spring (523) via a fixing plate (524) and a limiting rod (522).

8. The clamping device for aircraft parts according to claim 5, characterized in that: The limiting mechanism (5) further comprises: a small parts clamping assembly (53); the small parts clamping assembly (53) is installed at the bottom of the fully or partially position-adjustable assembly (51); the small parts clamping assembly (53) comprises: a disassembly head (531), a drive motor (532), a rotating arm (533), a positioning plate (534), a clamping sleeve (535), a pull rod (536), a clamping plate (537) and a tension spring (538); The top end of the disassembly head (531) is screwed and fixed to the bottom end of the threaded sleeve (512), the drive motor (532) is installed at the bottom end of the disassembly head (531), the top end of the rotating arm (533) is fixedly connected to the output end of the drive motor (532), the bottom end of the rotating arm (533) is fixedly connected to the top surface of the positioning plate (534), and the positioning plate (534) is symmetrically screwed with a connecting joint (5341) to be fixedly connected to the clamping sleeve (535) located below it through the connecting joint; The clamping sleeve (535) includes a top plate and two side plates located at the bottom of both ends of the top plate, and the top plate is threadedly connected to the bottom of each connecting joint (5342). Two pull rods (536) are symmetrically arranged and correspondingly slide through the two side plates of the clamping sleeve (535). Each pull rod (536) passes through the inner end of the side plate at the corresponding position and is threadedly connected to a clamping plate (537). The tension spring (538) is sleeved on the pull rod (536), and the two ends of the tension spring (538) are respectively fixedly connected to the outer wall of the side plate on the same side and the inner wall of the pull rod (536); the clamping sleeve (535) is driven to rotate by the driving motor (532), and the pull rod (536) is pulled to clamp the other two sides of the aircraft part in the horizontal direction using two clamping plates (537).

9. The clamping device for aircraft parts according to any one of claims 1 to 8, characterized in that: Also includes: Auxiliary sleeve (6); For a hoisting base plate (412) whose length exceeds a preset threshold, the auxiliary sleeve plate (6) is fixedly connected to the bottom of the hoisting base plate (412) to enhance the rigidity of the hoisting base plate (412).

10. The clamping device for aircraft parts according to any one of claims 1 to 8, characterized in that: The elastic clamping adjustable mechanism (4) further comprises: a connecting arm (422), a supporting platform (423), a limiting plate (424) and a limiting bolt (425); The two ends of the bottom of each support platform (42) are connected to the support platform (423) through fixedly connected connecting arms (422), and the same side ends of the two support platforms (42) are connected to the same support platform (423) through one connecting arm (422) respectively; The two side walls of the bosses at both ends of the hanging base plate (412) are respectively fixedly connected to the limit plates (424), and each limit plate (424) is located at the bottom of the support platform (42) at the same end, and the bottom of the limit plate (424) is threadedly installed with a limit bolt (425); a plurality of screw holes are evenly spaced at the bottom of the support platform (42), which are used to screw and fix the limit bolts (425) to the screw holes at corresponding positions on the bottom of the support platform (42) after adjusting the position of the support platform (42), thereby fixing the position of the support platform (42).

Images