Space truss structure on-orbit manufacturing device and method

Abstract

The invention discloses an on-orbit manufacturing device and method for a space truss structure. The device is composed of a rack, a feeding disc, a discharging disc, an upper feeding roller, a lower feeding roller, an upper guiding die, a lower guiding die, a forming die assembly, a front joint nailing device assembly, a rear joint nailing device assembly, a truss cutting device and a strip-shaped material. A strip-shaped material is wound on the upper material disc and the lower material disc respectively and conveyed forwards through the upper feeding roller and the lower feeding roller respectively, and a beam blank of a longitudinal beam is formed under the combined action of the forming core mold assembly, the forming upper mold assembly and the forming lower mold assembly. The overlapping part of the front material and the rear material of the beam blank of the longitudinal beam can emit suturing nails in different shapes with certain kinetic energy through the front seam nailing device assembly and the rear seam nailing device assembly, so that the longitudinal beam is formed; and when the generated length reaches the target length, the beam cutting device is used for cutting off. The forming efficiency is high, the structural performance is more stable, and limitation of ground processing and transportation is avoided, so that a larger and more complex space structure can be manufactured.

Description

Technical Field

[0001] The present invention relates to the field of truss structures, and more particularly to a device for on-orbit manufacturing of large-scale space truss structures. Background Art

[0002] With the continuous deepening of space exploration activities, the human demand for space facilities is also continuously increasing. To meet these demands, it is necessary to develop larger and more complex space truss structures. Currently, the manufacturing of traditional space truss structures mainly relies on first manufacturing beam materials and then completing the process through welding and assembly. This method has complex processes, long cycles, difficult quality assurance, and cannot form a complete space structure at one time. Given that large-scale and lightweight are the development directions of spacecraft and their affiliated facilities, the existing technologies are difficult to meet the space application requirements of large-size, high-performance, and complex structural components, especially considering the limitations of ground-to-space transportation capabilities and costs.

[0003] Currently, the on-orbit manufacturing technology of space truss structures is being actively researched and developed. The main research directions include on-orbit 3D printing and on-orbit assembly technologies based on modules or cable materials. Although 3D printing technology has manufacturing flexibility, its on-orbit construction efficiency for ultra-large space structures is not high, limited by its process method. For the on-orbit assembly technology based on modules or cable materials, due to the need to handle numerous assembly interfaces and complex unmanned autonomous assembly operations, the structural construction efficiency and stiffness are not satisfactory. Summary of the Invention

[0004] The purpose of the present invention is to provide a device for on-orbit manufacturing of a space truss structure. By continuously inputting upper and lower strip materials, pipe forming can be completed after passing through a forming die, and then the working station can be adjusted to generate a cross structure of horizontal and vertical beams, with good forming effect and high forming efficiency.

[0005] To achieve the above purpose, the present invention adopts the following technical solutions: A device for on-orbit manufacturing of a space truss structure, characterized by comprising a frame, a feeding tray, a discharging tray, an upper feeding roller, a lower feeding roller, an upper guiding die, a lower guiding die, a forming die assembly, a front joint nailing device assembly, a rear joint nailing device assembly, a truss cutting device, and strip materials.

[0006] For a device for on-orbit manufacturing of a space truss structure according to the present invention, both the upper feeding roller and the lower feeding roller are respectively composed of a passive roller, an active roller, an active roller driving device, a gap adjusting device, and a positioning device. The passive roller and the active roller are arranged in parallel, and a gap is formed between the roller surfaces of the passive roller and the active roller. The gap adjusting device is connected to the passive roller or the active roller, the active roller driving device is connected to the active roller, and the positioning device is arranged before or after the gap.

[0007] The invention discloses an on-track manufacturing device for a space truss structure. The upper guide die and the lower guide die both have a slit-shaped space special-shaped curved structure. The curved shape of the slit is a transitional shape between the flat sheet fixed shapes and the openings of the two curved slits are opposite to each other.

[0008] The invention discloses an on-track manufacturing device for a spatial truss structure, wherein a forming die assembly comprises a forming core die assembly, a forming upper die assembly and a forming lower die assembly; the forming core die assembly comprises a forming core die and a core die driving mechanism for controlling the forward and backward movement of the forming core die, a gap of a specific width is preset on both sides of the forming core die, the gap is located at an outlet of a suturing gun, and the structure changes from deep to shallow; the forming upper die assembly comprises a forming upper die and an upper die driving mechanism for controlling the upward and downward movement of the forming upper die; the forming lower die assembly comprises a forming lower die and a lower die driving mechanism for controlling the upward and downward movement of the forming lower die; the size of a cavity formed by closing the forming upper die and the forming lower die is larger than the size of the forming core die to form a gap, and the thickness of the gap is equivalent to the wall thickness of a longitudinal beam or a transverse beam; the shape of the gap can be circular, elliptical or square, etc.

[0009] The invention discloses an on-track manufacturing device for a space truss structure, wherein the front seam nailing device assembly and the rear seam nailing device assembly are respectively composed of a nailing device and a motion driving mechanism, and the nailing device is controlled by the motion driving mechanism. The nailing device is composed of a nailing device, a nail chamber, a heating component, and a suture nail, wherein the heating component surrounds the nail chamber, and the suture nail is provided with a barb structure on the nail head, and the whole presents a flat and slender shape.

[0010] The invention discloses an on-track manufacturing device for a spatial truss structure, wherein an upper material tray and a lower material tray are arranged up and down, and then an upper feeding roller and a lower feeding roller, an upper guide die and a lower guide die, a forming upper die assembly and a forming lower die assembly are arranged correspondingly, and a forming core die is placed in a cavity formed by the forming upper die and the forming assembly.

[0011] The invention discloses an on-track manufacturing device for a space truss structure. An upper material tray and a lower material tray have a reel-shaped structure, and a tension control device can be arranged at the center of the reel.

[0012] The invention provides an on-track manufacturing device for a space truss structure. The upper guide die or the lower guide die can be an open and close two-half structure relative to the slit, or can be a closed fixed structure.

[0013] The invention discloses an on-track manufacturing device for a space truss structure, comprising a truss cutting device arranged at an outlet of a forming die assembly.

[0014] An on-orbit manufacturing method for a space truss structure, the steps are as follows:

[0015] The method for generating the longitudinal beam is as follows: The strip material is respectively wound on the loading disk and the unloading disk. After the strip material is wound down from the loading disk and the unloading disk, it is respectively conveyed forward through the upper feeding roller and the lower feeding roller. After passing through the upper guiding die and the lower guiding die respectively, the strip material is initially deformed, and then continues to move forward into the forming die assembly. At this time, the upper forming die and the lower forming die are in a closed state, and the forming core die is placed in the cavity formed by the closing of the upper forming die and the lower forming die. Specific-width gaps are preset on both sides of the forming core die to facilitate the reception of the stitching nails emitted by the nailing device. Under the combined action of the forming core die assembly, the upper forming die assembly and the lower forming die assembly, the beam blank of the longitudinal beam is formed. There is an overlapping part between the front and rear materials of the beam blank of the longitudinal beam. The overlapping part passes through the front joint nailing device assembly and the rear joint nailing device assembly, which will emit different-shaped stitching nails with a certain kinetic energy, making them directly penetrate the strip material. After penetration, they will be blocked by the gaps on both sides of the forming core die, causing the stitching nails to bend and deform, and finally tightly fit on the inner wall of the truss tube to form the longitudinal beam. When the generated length reaches the target length, it is cut off by the cross beam cutting device.

[0016] As can be seen from the above technical solutions, the present invention has the following advantages compared with the prior art:

[0017] The present invention has high in-orbit manufacturing capabilities. Most traditional space truss structures are assembled after being processed on the ground and then launched into space. This method not only has cumbersome processes and long cycles, but also has high transportation costs and it is difficult to ensure structural consistency. The new in-orbit manufacturing technology for space truss structures can directly manufacture truss structures in the space environment, significantly improving the manufacturing efficiency and reducing the transportation and assembly costs.

[0018] In the optimization of the structural performance, the present invention manufactures by continuously inputting strip materials. The pipe forming is completed through the forming die parts, and then the cross structure of the horizontal and longitudinal beams is generated through the cross nailing device assembly. This method can ensure good forming effect and high forming efficiency of the truss structure, and the structural performance is more stable. Compared with the traditional welding technology, the nailing technology improves the energy efficiency and effectively reduces the number of structural connection interfaces; compared with the traditional assembly method or punching riveting technology, this technology significantly improves the overall stiffness of the structure by streamlining the process flow and reducing the manufacturing complexity. In addition, this technology avoids the problem of difficult alignment during the traditional perforation process, thus ensuring the reliability and stability of the truss while improving the structural stability.

[0019] The present invention has a high degree of automation. This space truss structure manufacturing technology uses equipment and systems with a high degree of automation, such as automatic feeding rollers, automatic forming die assemblies, automatic nailing devices, etc. These equipment and systems can reduce human intervention and improve the automation degree of the manufacturing process, thereby ensuring the stability and consistency of the manufacturing process.

[0020] The present invention has strong adaptability. This manufacturing technology for space structure trusses is not restricted by ground processing and transportation. Therefore, larger and more complex space structures can be manufactured. This technology can meet the manufacturing requirements of space trusses with different sizes, different performances, and different structural forms, providing strong technical support for the development of future large spacecraft and their space appendages. Description of the Drawings

[0021] Figure 1 is a top view of an on-orbit manufacturing device for a space truss structure;

[0022] Figure 2 is a front view of an on-orbit manufacturing device for a space truss structure;

[0023] Figure 3 is a cross-sectional view of a forming die assembly of an on-orbit manufacturing device for a space truss structure;

[0024] Figure 4 is a structural diagram of a seam riveting device assembly of an on-orbit manufacturing device for a space truss structure;

[0025] Figure 5 is a structural diagram of a stitching nail that can be used by a riveting device of an on-orbit manufacturing device for a space truss structure;

[0026] Figure 6 is a schematic diagram of generating a longitudinal beam by an on-orbit manufacturing device for a space truss structure;

[0027] Figure 7 is a schematic diagram of the riveting process when generating a longitudinal beam by an on-orbit manufacturing device for a space truss structure. Detailed Description of the Invention

[0028] Embodiment 1

[0029] As Figure 1 Figure 2 shown, the present invention provides an on-orbit manufacturing device for a space truss structure, which is characterized by: a frame 1, a feeding tray 2, a discharging tray 3, an upper feeding roller 4, a lower feeding roller 5, an upper guiding die 6, a lower guiding die 7, a forming die assembly 8, a front seam riveting device assembly 9, a rear seam riveting device assembly 10, a truss cutting device 11, and a strip material 12.

[0030] Both the upper feeding roller 4 and the lower feeding roller 5 are respectively composed of a passive roller, a driving roller, a driving device for the driving roller, a gap adjusting device, and a positioning device. The passive roller and the driving roller are arranged in parallel, and a gap is formed between the roller surfaces of the passive roller and the driving roller. The gap adjusting device is connected to the passive roller or the driving roller, the driving device for the driving roller is connected to the driving roller, and the positioning device is arranged before or after the gap.

[0031] Both the upper guiding die 6 and the lower guiding die 7 have a slit-shaped spatially shaped bending structure, and the shape of the slit bending is a transitional shape between the flat sheet shaping shapes, and the openings of the two bending slits are opposite to each other.

[0032] As Figure 3 shown, the forming die assembly 8 includes a forming core die assembly 8-1, a forming upper die assembly 8-2, and a forming lower die assembly 8-3; the forming core die assembly 8-1 is composed of a forming core die and a core die driving mechanism for controlling the forward and backward movement of the forming core die. Specific-width gaps are preset on both sides of the forming core die, and the gaps are located at the outlet of the stitching gun, and the structure changes from deep to shallow. By precisely controlling the injection process of the stitching nails, their close fitting on the inner wall of the truss tube is achieved. This process involves the bending deformation of the stitching nails to ensure seamless docking with the inner wall of the truss tube; the forming upper die assembly 8-2 is composed of a forming upper die and an upper die driving mechanism for controlling the up and down movement of the forming upper die; the forming lower die assembly 8-3 is composed of a forming lower die and a lower die driving mechanism for controlling the up and down movement of the forming lower die; the cavity size formed by the closing of the forming upper die and the forming lower die is larger than the size of the forming core die to form a gap, and the thickness of the gap is equivalent to the wall thickness of the longitudinal beam or the cross beam; the shape of the gap is circular.

[0033] Both the front seam nailing device assembly 9 and the rear seam nailing device assembly 10 are respectively composed of a nail shooting device 10-5 and a motion driving mechanism 10-6, and the nail shooting device is controlled by the motion driving mechanism. As Figure 4 shown, the nail shooting device is composed of a nail shooter 10-1, a nail chamber 10-2, a heating assembly 10-3, and a stitching nail 10-4. As Figure 5 shown, the stitching nail 10-4 includes two different forms, and their common feature is that barbed structures are arranged on the nail heads. Overall, the stitching nail presents a flat and slender shape.

[0034] The loading tray 2 and the unloading tray 3 are arranged up and down, and then the upper feeding roller 4 and the lower feeding roller 5, the upper guiding die 6 and the lower guiding die 7, the forming upper die assembly 8-2 and the forming lower die assembly 8-3 are respectively arranged correspondingly, and the forming core die is placed in the cavity formed by the forming upper die and the forming assembly.

[0035] The loading tray 2 and the unloading tray 3 have a scroll-like structure, and a tension control device is arranged at the center of the scroll.

[0036] The upper guiding die 6 or the lower guiding die 7 is a split structure that is openable and closable relative to the slit.

[0037] It includes a truss cutting device 11, which is arranged at the outlet of the forming die assembly.

[0038] As Figure 6 shown, a method for on-orbit manufacturing of a space structure truss is as follows:

[0039] The method for generating the longitudinal beam is as follows: The strip material 12 is respectively wound on the loading reel 2 and the unloading reel 3. After the strip material is wound down from the loading reel 2 and the unloading reel 3, it is respectively conveyed forward by the upper feeding roller 4 and the lower feeding roller 5. After passing through the upper guiding die 6 and the lower guiding die 7 respectively, the strip material is initially deformed, and then continues to move forward into the forming die assembly 8; At this time, the forming upper die 8-2 and the forming lower die 8-3 are in a closed state, and the forming core die 8-1 is placed in the cavity formed by the closing of the forming upper die 8-2 and the forming lower die 8-3; Under the combined action of the forming core die assembly 8-1, the forming upper die assembly 8-2 and the forming lower die assembly 8-3, a beam blank of the longitudinal beam is formed. There is an overlapping part between the front and rear materials of the beam blank of the longitudinal beam, such as Figure 7 shown. The overlapping part passes through the front joint nailing device assembly 9 and the rear joint nailing device assembly 10, which will launch different-shaped stitching nails with a certain kinetic energy, making them directly penetrate the strip material. After penetration, they will be blocked by the gaps on both sides of the forming core die 8-1 at the back of the material, causing the stitching nails to bend and deform, and finally closely fit on the inner wall of the truss tube to form the longitudinal beam; When the generated length reaches the target length, it is cut off by the cross beam cutting device.

Claims

1. An on-track manufacturing device for a spatial truss structure, characterized in that: It consists of a frame, an upper material tray, a lower material tray, an upper feed roller, a lower feed roller, an upper guide die, a lower guide die, a forming die assembly, a front seam nailing device assembly and a rear seam nailing device assembly; The upper feeding roller and the lower feeding roller are respectively composed of a passive roller, an active roller, an active roller driving device, a gap adjusting device and a positioning device. The passive roller and the active roller are arranged in parallel, a gap is formed between the roller surface of the passive roller and the roller surface of the active roller, the gap adjusting device is connected to the passive roller or the active roller, the active roller driving device is connected to the active roller, and the positioning device is arranged before or after the gap; The upper guide die and the lower guide die both have a slit-shaped spatial irregular curved structure, the curved shape of the slit is a transitional shape between the flat sheet fixed shapes, and the openings of the two curved slits are opposite to each other; The forming die assembly comprises a forming core die assembly, a forming upper die assembly and a forming lower die assembly; the forming core die assembly comprises a forming core die and a core die driving mechanism for controlling the forward and backward movement of the forming core die, a gap of a specific width is preset on both sides of the forming core die, the gap is located at the outlet of the suture gun, and the structure changes from deep to shallow; the forming upper die assembly comprises a forming upper die and an upper die driving mechanism for controlling the upward and downward movement of the forming upper die; the forming lower die assembly comprises a forming lower die and a lower die driving mechanism for controlling the upward and downward movement of the forming lower die; the size of the cavity formed by closing the forming upper die and the forming lower die is larger than the size of the forming core die to form a gap, and the thickness of the gap is equivalent to the wall thickness of the longitudinal beam or the cross beam; the shape of the gap can be circular, elliptical or square, etc.; The front seam stapling device assembly and the rear seam stapling device assembly are respectively composed of a nail shooting device and a motion driving mechanism. The nail shooting device is controlled by the motion driving mechanism. The nail shooting device is composed of a nail shooting device, a nail chamber, a heating component, and a suture nail. The heating component surrounds the nail chamber. The suture nail is provided with a barb structure on the nail head, and the whole presents a flat and slender shape. The upper material tray and the lower material tray are arranged up and down, and then the upper feeding roller and the lower feeding roller, the upper guide mold and the lower guide mold, the molding upper mold assembly and the molding lower mold assembly are arranged respectively, and the molding core mold is placed in the cavity formed by the molding upper mold and the molding assembly.

2. The on-track manufacturing device for a spatial lattice structure according to claim 1, characterized in that: The upper material tray and the lower material tray have a reel-like structure, and a tension control device can be arranged at the center of the reel.

3. The on-track manufacturing device for a spatial lattice structure according to claim 1 is characterized in that: The upper guide die or the lower guide die is an open and close two-half structure relative to the slit, or a closed fixed structure.

4. The on-track manufacturing device for a space lattice structure according to claim 1 is characterized in that: It includes a truss cutting device, which is arranged at the outlet of the forming die assembly.

5. A method for manufacturing a space lattice structure on-track, using the device for manufacturing a space lattice structure on-track according to claim 1, characterized in that: The longitudinal beam generation method is as follows: the strip material is wound on the upper material tray and the lower material tray respectively. After the strip material is wound off the upper material tray and the lower material tray, it is respectively conveyed forward by the upper feeding roller and the lower feeding roller. After passing through the upper guide die and the lower guide die respectively, the strip material is initially deformed, and then continues to move forward into the forming die assembly; at this time, the forming upper die and the forming lower die are in a closed state, the forming core die is placed in the cavity formed by the closing of the forming upper die and the forming lower die, and a gap of a specific width is preset on both sides of the forming core die to facilitate the reception of the suture nails fired by the nailing device. ; The longitudinal beam blank is formed under the joint action of the forming core mold assembly, the forming upper mold assembly and the forming lower mold assembly. The front and rear materials of the longitudinal beam blank have overlapping parts. The overlapping parts are fired with different shapes of suture nails with a certain kinetic energy through the front seam nailing device assembly and the rear seam nailing device assembly, so that they directly penetrate the strip material and directly penetrate into the gap on both sides of the forming core mold, and bend and deform at the back of the material and the forming core mold, and finally fit tightly to the inner wall of the truss tube to form a longitudinal beam; when the generated length reaches the target length, it is cut off by the crossbeam cutting device.

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