CN112249360A - Method for assembling spacecraft structural plate - Google Patents
Method for assembling spacecraft structural plate Download PDFInfo
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- CN112249360A CN112249360A CN202011171526.8A CN202011171526A CN112249360A CN 112249360 A CN112249360 A CN 112249360A CN 202011171526 A CN202011171526 A CN 202011171526A CN 112249360 A CN112249360 A CN 112249360A
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- 238000000034 method Methods 0.000 title claims abstract description 30
- 238000003825 pressing Methods 0.000 claims abstract description 24
- 238000009434 installation Methods 0.000 description 15
- 238000012544 monitoring process Methods 0.000 description 5
- 239000011120 plywood Substances 0.000 description 5
- 239000000463 material Substances 0.000 description 4
- 238000011900 installation process Methods 0.000 description 3
- 238000012827 research and development Methods 0.000 description 3
- 238000007790 scraping Methods 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Installation Of Indoor Wiring (AREA)
Abstract
The invention discloses an assembly method of a spacecraft structural slab, which comprises the steps of firstly, installing a cable support on a structure, unfolding the cable support at a specified angle to enable a cross-slab cable to cross the cable support to avoid pressing the cable, then adjusting the structural slab to be in a vertical state and to be close to a satellite main structure, fixing the cross-slab cable after reaching a specified position, folding and disassembling the cable support, and finally, completing the structural slab.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to an assembly method of a spacecraft structural plate.
Background
The aerospace technology is developed rapidly, and how to shorten the development and production period of the spacecraft is of great importance on the premise of ensuring the quality. Because the spacecraft has extremely high requirements on assembly precision and quality, a large number of monitoring post personnel are required to be arranged besides operators in the assembly process of the spacecraft at present, and the labor cost is greatly increased.
Taking the assembly of the satellite structure plate as an example, in the process of assembling the plate, when the distance between the satellite structure plate and the satellite main body can generate the risk of pressing the cable line of the cross plate, the assembly speed needs to be slowed down, and operators and monitoring posts concentrate on the butt joint surface, even need to pause the assembly frequently, so as to coat and bundle the suspicious line pressing part until the distance gradually approaches zero. In actual operation, the net time of each structural slab is about 4-10 hours. In the assembling process, a plurality of operators are arranged on the site, and different numbers of monitoring posts are required to be set according to the risks related to the products and the main structure on the structural plate.
Although the operation process of the plywood is not complicated, the requirements on experience and matching of operators are high, attention needs to be paid to precise operation with high concentration to ensure that other structures are not rubbed or the cross-board cable is not pressed, so that a large amount of manpower resources and time are consumed, and the manufacturing cost of the satellite is increased. And the monitoring post personnel are generally research and development personnel of related components, and the time for inputting and assembling is too long, which means that the research and development time is reduced, and the whole research and development progress of the spacecraft is influenced to a certain extent.
Disclosure of Invention
Aiming at solving part or all problems in the prior art, the invention provides an assembly method of a spacecraft structural plate, which comprises the following steps:
installing a single machine and wiring:
horizontally mounting the structural plate on a side plate mounting vehicle;
a single machine and a cable support are arranged on the structural plate, wherein a bottom plate of the cable support is fixed on one side of the structural plate close to the satellite main structure;
unfolding the cable support to enable a cable mounting plate of the cable support and the bottom plate to form a specified angle and be fixed; and
carrying out cable layout wiring, wherein a cross-board cable is connected to a single machine on one side of the satellite main structure through a cable mounting plate of the cable support;
adjusting the position of the structural plate:
adjusting a side plate mounting vehicle, and gradually turning the structural plate 90 degrees from a flat state to an upright state;
adjusting a side plate mounting vehicle, and pushing the structural plate to a satellite main structure until the distance between the structural plate and the satellite main structure reaches a preset value; and
and (3) disassembling the cable support:
fixing the cross-plate cable at a specified position on one side of the satellite main structure, so that the cross-plate cable is in a tensioned state; and
the cable support is folded and detached; and
and adjusting the side plate mounting vehicle, and continuously pushing the structural plate to the satellite main structure until the mounting position is preset.
Further, the tail end of the bottom plate of the cable support is bent, and during installation, the tail end of the bottom plate is attached to the side face of the structural plate and is fixed to the side face of the structural plate through the tail end.
Further, the unfolding angle of the cable bracket is determined according to the installation process of the cross-plate cable.
Further, the cable holder is fixed to the structural plate by a screw.
Further, a rubber pad is arranged on one side of the cable support, which is in contact with the structural plate, and the rubber pad comprises a step-shaped structure, is arranged in the mounting hole of the bottom plate of the cable support and is in interference fit with the bottom plate.
Further, the preset value of the distance between the structural plate and the main satellite structure is the minimum operating space allowing the cable support to be detached.
Further, appointed angle between cable mounting panel and the bottom plate sets up through spacing hole cooperation on spacing backup pad and the cable mounting panel and forms, wherein, spacing backup pad arrange in on the bottom plate, just the spacing backup pad can be followed installation axle 0 ~ 180 degree rotation, spacing hole has a plurality ofly, spacing backup pad inserts different spacing holes, can form different angles.
Further, the specified angle between the cable mounting plate and the base plate is not more than 90 °, preferably less than 45 °.
Further, drawing the cable holder apart includes:
lifting the cable mounting plate to enable the limiting support plate to be separated from the limiting hole;
folding the limiting support plate to be attached to the bottom plate;
folding the cable mounting plate to be attached to the bottom plate; and
and the cable mounting plate is pressed onto the bottom plate through a pressing sliding block.
According to the method for assembling the spacecraft structural slab, the cable support is used for wiring the cross-slab cables, so that the risk of pressing the line when the structural slab plywood is installed is effectively avoided, meanwhile, the number of monitoring posts can be reduced, the time for plywood combination is reduced, and the final assembly efficiency is improved. The present invention is based on the unique insight of the inventors: the inventor finds through research and practice that under the traditional structural slab installation mode, the wire pressing risk is easily generated, therefore, operators and watch posts need to be equipped at the same time, and highly centralized fine operation is carried out. The cable support is detached when used up, and the weight of the spacecraft and/or the satellite cannot be additionally increased: when the cable mounting plate is used, the angle of the limiting support plate is adjusted or the limiting plates with different lengths are selected according to different assembly requirements, so that the angle between the cable mounting plate and the structural plate can be flexibly adjusted, and different cable routing requirements are met; after the cable support is used, the cable support can be folded to be in a minimum enveloping state, the cable support is convenient to disassemble, the cable support can be prevented from being rubbed with a satellite product or a satellite structure, and in order to further reduce the risk of scraping the surface of a satellite structure plate, a rubber pad is arranged on a bottom plate of the cable support; and the disassembled cable support can be repeatedly used, occupies small space and is easy to store. In addition, the cable support is flexible in structure, different structural forms can be selected according to the structural design of the spacecraft/satellite or the assembly process requirement, and the overall volume of the cable support is further reduced.
Drawings
To further clarify the above and other advantages and features of embodiments of the present invention, a more particular description of embodiments of the present invention will be rendered by reference to the appended drawings. It is appreciated that these drawings depict only typical embodiments of the invention and are therefore not to be considered limiting of its scope. In the drawings, the same or corresponding parts will be denoted by the same or similar reference numerals for clarity.
Fig. 1 shows a schematic flow diagram of a method of assembling a spacecraft structural panel in accordance with an embodiment of the invention;
FIGS. 2a-2f show an assembly schematic of a spacecraft structural panel in accordance with an embodiment of the invention;
FIG. 3 shows a schematic structural view of a cable support according to an embodiment of the invention;
FIG. 4 is a schematic structural view showing a closed state of a cable holder according to an embodiment of the present invention;
FIG. 5 shows a schematic structural view of a base plate of a cable support according to an embodiment of the invention;
FIG. 6 shows a schematic view of the installation of rubber pads of the cable tray base plate according to one embodiment of the present invention;
FIG. 7 is a schematic view of the pressing slider of the cable holder according to one embodiment of the present invention;
FIG. 8 is a schematic view of the compression slide of one embodiment of the present invention shown in a deployed position on a cable support;
FIG. 9 is a schematic view of the compression slide of one embodiment of the present invention shown in a collapsed condition; and
fig. 10a-10b show schematic views of a cable holder according to an embodiment of the invention deployed at different angles.
Detailed Description
In the following description, the present invention is described with reference to examples. One skilled in the relevant art will recognize, however, that the embodiments may be practiced without one or more of the specific details, or with other alternative and/or additional methods, materials, or components. In other instances, well-known structures, materials, or operations are not shown or described in detail to avoid obscuring aspects of the invention. Similarly, for purposes of explanation, specific numbers, materials and configurations are set forth in order to provide a thorough understanding of the embodiments of the invention. However, the invention is not limited to these specific details. Further, it should be understood that the embodiments shown in the figures are illustrative representations and are not necessarily drawn to scale.
Reference in the specification to "one embodiment" or "the embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the invention. The appearances of the phrase "in one embodiment" in various places in the specification are not necessarily all referring to the same embodiment.
It should be noted that the embodiment of the present invention describes the process steps in a specific order, however, this is only for the purpose of illustrating the specific embodiment, and does not limit the sequence of the steps. Rather, in various embodiments of the present invention, the order of the steps may be adjusted according to process adjustments.
Aiming at the problem that a line pressing risk is easy to occur when a structural plate is combined with a plate in the satellite assembling process, the invention provides the method for assembling the spacecraft structural plate, which effectively solves the problem through the use of a cable support, and the scheme of the invention is further described by combining the attached drawings of the embodiment.
Fig. 3 shows a schematic structural view of a cable holder according to an embodiment of the invention. As shown in fig. 3, the cable support comprises a cable installation plate 101, a bottom plate 102 and a limiting support plate 103.
The cable mounting plate 101 is rotatably connected to the bottom plate 102, and a rotation limiting device is disposed on the side of the rotation shaft, so that the cable mounting plate 101 can rotate along the mounting shaft by 0-90 degrees. At least one limiting hole 1011 is arranged on the cable mounting plate 101.
The limiting support plate 103 is arranged on the bottom plate 102 and rotatably connected with the bottom plate 102, the limiting support plate 103 can rotate along an installation shaft by 0-180 degrees, the rotation direction of the limiting support plate 103 is opposite to that of the cable installation plate 101, the installation position of the limiting support plate 103 corresponds to the limiting hole 1011, and when the limiting support plate 103 rotates to a certain angle, the limiting support plate can be inserted into the limiting hole 1011, so that the included angle between the cable installation plate 101 and the bottom plate 102 is fixed. The angle between the cable mount plate 101 and the base plate 102 is no more than 90 ° and/or no less than 10 °, typically the angle is less than 45 °, preferably less than 42 °.
The bottom plate 102 is used for fixing the cable rack on a structural plate, and for facilitating disassembly, in an embodiment of the present invention, the tail portion of the bottom plate 102 is bent, and the bending angle is consistent with an angle formed by a mounting surface and a side surface of the structural plate, so that when the cable rack is installed, the second surface of the bottom plate 102 is attached to the mounting surface of the structural plate, and the bent tail portion of the bottom plate 102 is attached to the side surface of the structural plate. In an embodiment of the present invention, in order to avoid scraping between the cable rack and the structural plate when the cable rack is mounted or dismounted, and thereby causing damage to the structural plate, a rubber pad 1024 is further disposed on the second surface of the bottom plate 102, as shown in fig. 5, the rubber pad 1024 is a step-shaped structure, is in interference fit with the bottom plate 102, and is directly screwed into the bottom plate mounting hole 1025, as shown in fig. 6. At least one pressing mechanism is disposed on the first surface of the base plate 102, the pressing mechanism includes a pressing slider 1021, a guide groove 1022, and a limit screw 1023, and an opening is disposed at a portion of the cable mounting plate 101 opposite to the pressing slider 1021. The structure of the pressing slider 1021 is as shown in fig. 7, and includes a waist hole 0211 and a guiding ridge 0212, the pressing slider 1021 is installed in a guiding groove 1022 of the base plate 102, and when the cable mounting plate 101 and the limiting support plate 103 are folded and folded, the pressing slider 1021 is pushed, so that the guiding ridge 0212 slides along the guiding groove 1022, and after pressing the cable mounting plate 101, the limiting screw 1023 is screwed, at this time, the cable support becomes a folded and pressed state, which is a minimum envelope size state, and occupies a minimum space during moving and storing, as shown in fig. 4. The pressing slider 1021 is in a state shown in fig. 8 when the cable holder is unfolded, and in a state shown in fig. 9 when the cable holder is folded.
Based on the cable support structure, the flow of the method for assembling the spacecraft structural panel provided by the invention is shown in fig. 1, and the method comprises the following steps:
first, in step 001, a single device and a wire are installed. As shown in fig. 2aa, first, the structural panel 201 is horizontally mounted on the side panel mounting car 202; then, installing a single machine and a cable bracket 100 on the structural plate 201, wherein the bottom plate of the cable bracket 100 is fixed on one side of the structural plate 201 close to the satellite main structure 203; unfolding the cable support 100 so that the cable installation plate of the cable support and the bottom plate form a designated angle and are fixed, wherein the unfolding angle of the cable support is determined according to the installation process of the cross-plate cable, and is generally not greater than 90 degrees, preferably less than 45 degrees; in another embodiment of the invention, a specified angle between the cable mounting plate and the bottom plate is set by matching a limiting support plate with a limiting hole on the cable mounting plate; finally, cable layout wiring is carried out, wherein a cross-board cable 204a crosses over a cable mounting plate of the cable support and is connected to a single machine on one side of the satellite main structure; for comparison, in the example, a portion of the cross-board cable 204b is routed in a conventional manner, as shown in fig. 2 ab; in one embodiment of the invention, the cable holder is fixed to the structural panel by fixing the tail end of the bottom plate of the cable holder to the side of the structural panel, and in yet another embodiment of the invention, the cable holder is fixed to the structural panel by screws;
next, at step 002, the structural plate position is adjusted. The side plate installation vehicle 202 is adjusted, the structural plate 201 is gradually turned over by 90 degrees from a flat state to an upright state, fig. 2b shows a state when the structural plate 201 is turned over to 45 degrees, it can be seen that the span plate cable 204a is supported by the cable support 100 and cannot be contacted with the plate surface, and the span plate cable 204b falls on the edge of the satellite main structure, so that a line pressing is easy to occur; next, adjusting the side plate installation vehicle 202, and pushing the structural plate 201 to a satellite main structure until the distance between the structural plate and the satellite main structure reaches a preset value; in an embodiment of the present invention, the preset value is a minimum operating space allowing the cable holder to be detached, as shown in fig. 2ca, at this time, the state of the cross-board cable 204b is as shown in fig. 2cb, the cross-board cable 204b falls on the edge of the satellite main structure, and once the board is closed, a pressing line is easily formed;
next, at step 003, the cable holder is disassembled. Fixing the cross-plate cable 204a at a designated position on one side of the satellite main structure, so that the cross-plate cable 204a is in a tensioned state and further cannot fall to the edge of the satellite main structure, thereby avoiding a wire pressing risk, then furling the cable support, as shown in fig. 2d, during the furling process of the cable support, the cross-plate cable 204a can still maintain the tensioned state, and after the cable support 100 is completely tightened, as shown in fig. 2e, in an embodiment of the present invention, furling the cable support includes:
lifting the cable mounting plate to enable the limiting support plate to be separated from the limiting hole;
folding the limiting support plate to be attached to the bottom plate;
folding the cable mounting plate to be attached to the bottom plate; and
and the cable mounting plate is pressed onto the bottom plate through a pressing sliding block.
After the cable support 100 is completely tightened, the cable support can be detached from the structural plate, as shown in fig. 2f, it can be seen that the span-plate cable 204a is always tensioned, and the span-plate cable 204b falls on the edge of the main structure of the satellite, so that a line pressing is easy to occur; because the installation surface of the cable support 100, which is in contact with the structural plate 201, is made of rubber materials, the risk of scraping the surface of the satellite structural plate does not exist during installation and disassembly; and
finally, at step 004, the board is closed. And adjusting the side plate mounting vehicle, and continuously pushing the structural plate to the satellite main structure until the mounting position is preset to finish the structural plate plywood.
Therefore, the installation of the whole structural slab is completed, in the installation process, the cross slab cable can be conveniently and quickly fixed in front of the plywood through the cable support, the pressing line is avoided, and the whole operation can be quickly completed by only one operator. The cable support is detached when used up, and the weight of the spacecraft and/or the satellite cannot be increased additionally.
While various embodiments of the present invention have been described above, it should be understood that they have been presented by way of example only, and not limitation. It will be apparent to persons skilled in the relevant art that various combinations, modifications, and changes can be made thereto without departing from the spirit and scope of the invention. Thus, the breadth and scope of the present invention disclosed herein should not be limited by any of the above-described exemplary embodiments, but should be defined only in accordance with the following claims and their equivalents.
Claims (9)
1. A method of assembling a spacecraft structural panel, comprising the steps of:
installing a single machine and wiring:
horizontally mounting the structural plate on a side plate mounting vehicle;
a single machine and a cable support are arranged on the structural plate, wherein a bottom plate of the cable support is fixed on one side of the structural plate close to the satellite main structure;
unfolding the cable support to enable a cable mounting plate of the cable support and the bottom plate to form a specified angle and be fixed; and
carrying out cable layout wiring, wherein a cross-board cable crosses over a cable mounting plate of the cable support and is connected to a single machine on one side of the satellite main structure;
adjusting the position of the structural plate:
adjusting a side plate mounting vehicle, and gradually turning the structural plate 90 degrees from a flat state to an upright state; and
adjusting a side plate mounting vehicle, and pushing the structural plate to a satellite main structure until the distance between the structural plate and the satellite main structure reaches a preset value;
and (3) disassembling the cable support:
fixing the cross-plate cable at a specified position on one side of the satellite main structure, so that the cross-plate cable is in a tensioned state; and
the cable support is folded and detached; and
and adjusting the side plate mounting vehicle, and continuously pushing the structural plate to the satellite main structure until the mounting position is preset.
2. The assembly method of claim 1, wherein the tail end of the bottom plate of the cable holder is bent, and when the cable holder is mounted, the tail end of the bottom plate is attached to the side surface of the structural plate, and the tail end is fixed to the side surface of the structural plate.
3. An assembly method according to claim 2, wherein the tail end is secured to the structural panel by screws.
4. The method of assembling of claim 1, wherein the angle between the cable mount plate of the cable mount and the base plate is determined according to the process of installing the span cable.
5. The assembling method according to claim 1, wherein the angle between the cable mounting plate and the bottom plate is set by engaging a plurality of limiting holes on the cable mounting plate with a plurality of limiting support plates disposed on the bottom plate and rotatable about the mounting shaft by 0 to 180 degrees.
6. An assembly method according to claim 1, wherein the specified angle between the cable mounting plate and the base plate is no more than 90 °, preferably less than 45 °.
7. The method of assembling of claim 1, wherein a rubber pad is disposed on a side of the cable support in contact with the structural plate, the rubber pad comprising a stepped configuration and being mounted in a mounting hole of a bottom plate of the cable support in interference fit with the bottom plate.
8. An assembly method according to claim 1, characterised in that the preset value of the distance between the structural plate and the main satellite structure after turning 90 ° is the minimum operating space allowing the detachment of the cable support.
9. The method of assembling of claim 5, wherein collapsing the cable holder comprises:
lifting the cable mounting plate to enable the limiting support plate to be separated from the limiting hole;
folding the limiting support plate to be attached to the bottom plate;
folding the cable mounting plate to be attached to the bottom plate; and
and the cable mounting plate is pressed onto the bottom plate through a pressing sliding block.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011171526.8A CN112249360B (en) | 2020-10-28 | 2020-10-28 | Method for assembling spacecraft structural plate |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011171526.8A CN112249360B (en) | 2020-10-28 | 2020-10-28 | Method for assembling spacecraft structural plate |
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| CN112249360A true CN112249360A (en) | 2021-01-22 |
| CN112249360B CN112249360B (en) | 2021-09-24 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112758355A (en) * | 2021-01-28 | 2021-05-07 | 中国科学院微小卫星创新研究院 | Satellite structural plate and mounting method thereof |
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|---|---|---|---|---|
| EP1032142A2 (en) * | 1999-02-23 | 2000-08-30 | TRW Inc. | Spacecraft module interconnection structure |
| JP2007253762A (en) * | 2006-03-22 | 2007-10-04 | Mitsubishi Electric Corp | Artificial satellite equipment panel |
| CN104047942A (en) * | 2014-05-28 | 2014-09-17 | 上海微小卫星工程中心 | Satellite side plate positioning device, satellite side plate mounting equipment and satellite side plate mounting method |
| CN109335023A (en) * | 2018-08-31 | 2019-02-15 | 南京理工大学 | A kind of no cable high density cube star and its assembly method |
| CN109878764A (en) * | 2019-02-28 | 2019-06-14 | 上海微小卫星工程中心 | A kind of mechanical, electrical and heating integrated satellite structure plate |
-
2020
- 2020-10-28 CN CN202011171526.8A patent/CN112249360B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1032142A2 (en) * | 1999-02-23 | 2000-08-30 | TRW Inc. | Spacecraft module interconnection structure |
| JP2007253762A (en) * | 2006-03-22 | 2007-10-04 | Mitsubishi Electric Corp | Artificial satellite equipment panel |
| CN104047942A (en) * | 2014-05-28 | 2014-09-17 | 上海微小卫星工程中心 | Satellite side plate positioning device, satellite side plate mounting equipment and satellite side plate mounting method |
| CN109335023A (en) * | 2018-08-31 | 2019-02-15 | 南京理工大学 | A kind of no cable high density cube star and its assembly method |
| CN109878764A (en) * | 2019-02-28 | 2019-06-14 | 上海微小卫星工程中心 | A kind of mechanical, electrical and heating integrated satellite structure plate |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112758355A (en) * | 2021-01-28 | 2021-05-07 | 中国科学院微小卫星创新研究院 | Satellite structural plate and mounting method thereof |
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