Cable fixing device for flat satellite and assembling and working method thereof

Abstract

The invention provides a cable fixing device for a flat satellite and an assembling and working method of the cable fixing device, and belongs to the technical field of spacecraft product general assembly. The problem that the cable cannot be fixed after the panel satellite is closed is solved. The cable fixing device comprises a traction fixing seat, a magnetic attraction fixing lower seat, a magnetic attraction fixing upper seat, a take-up device and a fixing clip, a first rotating shaft is arranged on the traction fixing seat, the traction fixing seat is connected to a bottom plate of the flat satellite, the traction fixing seat is connected with a cable, and a second rotating shaft is arranged on the traction fixing seat. The tail end of the cable is connected with a top plate of the flat satellite through the fixing clip, the magnetic attraction fixing lower seats and the magnetic attraction fixing upper seats are arranged in pairs and attract each other, the multiple magnetic attraction fixing lower seats and the multiple magnetic attraction fixing upper seats are connected with a bottom plate of the flat satellite, and the magnetic attraction fixing lower seats are connected with the bottom plate of the flat satellite. And the plurality of magnetic fixed upper seats are connected with a cable. The cable fixing device is mainly used for fixing cables after a panel satellite is closed.

Description

Technical Field

[0001] The invention belongs to the technical field of space vehicle product assembly, and in particular relates to a cable fixing device for a flat-panel satellite and an assembly and working method thereof. Background Art

[0002] The various devices on the satellite need to be interconnected through cables to achieve power supply or signal transmission. The cables need to be properly routed and fixed in the satellite cabin to play the following roles: first, prevent the cables from shaking during launch to avoid damage to the equipment or itself; second, protect the electrical connector at the cable end and reduce the load at the root of the electrical connector.

[0003] Since satellites are often closed cabins, when the last cabin panel of the satellite is closed, the electrical connectors of the equipment on the inner surface of the cabin panel need to be plugged in. Therefore, a certain length margin needs to be reserved for the relevant cables, and the electrical connectors should be plugged in first before the cabin is closed. The defect of this operation is that the cable part with the reserved length margin is in a free state after the cabin is closed, so there is a risk of shaking in the cabin, causing damage to the cables or equipment. The current commonly used solution is to open an operation hole on the surface of the cabin panel, and after the satellite is closed first, reach into the satellite through the cabin hole to complete the plugging of the electrical connector and the fixation of the cable. However, the operation hole will reduce the utilization rate of the cabin panel and increase the difficulty of thermal control design.

[0004] For flat-panel satellites, this problem is more severe for the following reasons: First, the two-dimensional flat-panel satellite equipment layout space is concentrated on the upper and lower cabin panels. Compared with traditional satellites, more and thicker cables are required to interconnect across cabins during cabin merging, so the risk of damage is also greater; second, flat-panel satellites are often assembled by top-plate hoisting, which is difficult to assemble and the cables are difficult to plug and fix. Therefore, more cable length margin needs to be reserved to ensure safe operation; third, it is difficult for the two cabin panels to have enough space for opening operating holes while meeting the requirements of payload, solar wing and platform equipment layout. Summary of the invention

[0005] In view of this, the present invention aims to provide a cable fixing device for a flat-panel satellite and an assembly and working method thereof, so as to solve the problem that the cables cannot be fixed after the flat-panel satellite is assembled.

[0006] To achieve the above-mentioned purpose, the present invention adopts the following technical scheme: a cable fixing device for a flat-panel satellite, comprising a traction fixing seat, a magnetic fixing lower seat, a magnetic fixing upper seat, a wire take-up device and a fixing clip, wherein the traction fixing seat is provided with a first rotating shaft, the traction fixing seat is connected to the bottom plate of the flat-panel satellite, the traction fixing seat is connected to the cable, the end of the cable is connected to the top plate of the flat-panel satellite through a fixing clip, the magnetic fixing lower seat and the magnetic fixing upper seat are arranged in pairs and attract each other, the number of the magnetic fixing lower seat and the number of the magnetic fixing upper seat are both several, several magnetic fixing lower seats are connected to the bottom plate of the flat-panel satellite, several magnetic fixing upper seats are connected to the cable, the magnetic fixing lower seat is provided with a lower threading hole, the upper part of the magnetic fixing lower seat and the lower part of the magnetic fixing upper seat are An upper threading hole is provided, and after the magnetic fixed lower seat and the magnetic fixed upper seat are attracted to each other, the upper threading holes on the magnetic fixed lower seat and the magnetic fixed upper seat are relative to each other, the wire take-up device comprises a wire take-up wheel, a wire take-up bracket, a vortex spring and a second rotating shaft, the wire take-up bracket is connected to the bottom plate of the flat-panel satellite, the wire take-up wheel and the second rotating shaft are both connected to the wire take-up bracket, vortex springs are provided at both ends of the wire take-up wheel, a vortex spring shell is provided outside the vortex spring, the vortex spring shell is connected to the wire take-up bracket, one end of the vortex spring is connected to the wire take-up wheel, and the other end is connected to the vortex spring shell, a traction line is connected to the wire take-up wheel, the traction line passes through all the lower threading holes of the magnetic fixed lower seat in turn, then bypasses the first rotating shaft, and then passes through the upper threading holes of the magnetic fixed lower seat and the magnetic fixed upper seat in turn, and finally the end of the traction line is fixed on the second rotating shaft.

[0007] Furthermore, the traction fixing seat and the fixing clip both include a cable fixing surface, a mounting support and a support column, the cable fixing surface is connected to the mounting support through four support columns, the cable fixing surface is connected to the cable, a rotating shaft hole is opened on the support column of the traction fixing seat, the first rotating shaft passes through the rotating shaft hole and is connected to the nut, the mounting support of the traction fixing seat is connected to the bottom plate of the flat-panel satellite, and the mounting support of the fixing clip is connected to the top plate of the flat-panel satellite.

[0008] Furthermore, the magnetic fixed lower seat includes a lower armature, a magnet, a lower shell and a lower bottom plate, magnetic recesses are arranged at both ends of the lower armature, a magnetic steel groove is opened on the lower armature, a magnet is arranged in the magnetic steel groove, a magnetic steel pad is arranged on the outside of the magnetic steel, the lower armature is sleeved in the lower shell, the lower shell is connected to the lower bottom plate, the lower bottom plate is connected to the bottom plate of the flat-panel satellite, the lower threading hole passes through the lower armature and the lower shell, and upper threading holes are opened at both ends of the upper part of the lower shell.

[0009] Furthermore, the magnetically fixed upper seat includes an upper armature, an upper shell and an upper base plate, magnetic protrusions are provided at both ends of the upper armature, upper wire threading holes are provided on the magnetic protrusions, the upper armature and the upper base plate are both sleeved in the upper shell, the upper shell is connected to the upper base plate, nylon tie grooves are provided on the upper shell and the upper base plate, nylon tie grooves are passed through the nylon tie, and the magnetically fixed upper seat is connected to the cable via the nylon tie.

[0010] Furthermore, the magnetic steel is made of neodymium iron boron, the lower armature and the upper armature are made of electromagnetic pure iron, the magnetic steel pad is made of silicone rubber, and the lower shell, lower base plate, upper shell and upper base plate are made of aluminum alloy.

[0011] Furthermore, the take-up wheel includes a wheel body and a shaft body, the shaft body is arranged at both ends of the wheel body, a vortex spring groove is opened on the shaft body, a vortex spring buckle is arranged at the bottom of the shell of the vortex spring housing, the vortex spring is provided with an inner fixed arm and an outer fixed arm, the inner fixed arm is embedded in the vortex spring groove, and the outer fixed arm is embedded in the vortex spring buckle.

[0012] Furthermore, the wire taking-up bracket includes a mounting ear and a wheel mounting surface, the mounting ear is vertically arranged to the wheel mounting surface, the mounting ear is connected to the bottom plate of the flat-panel satellite, the wheel mounting surface and the shell of the vortex spring housing are both provided with wheel through holes, the shaft body passes through the wheel through hole, a rotating shaft through hole is provided on the wheel mounting surface, the second rotating shaft passes through the rotating shaft through hole, a mounting threaded hole is provided on the wheel mounting surface, a mounting through hole is provided on the shell of the vortex spring housing, and the vortex spring housing is connected to the wheel mounting surface through the cooperation of the mounting through hole, the mounting threaded hole and screws.

[0013] Furthermore, a threading hole is provided on the wheel body, the traction wire passes through the threading hole and has a nail head at one end, the vortex spring housing is made of aluminum alloy, the vortex spring is made of spring steel, the traction wire is a Kevlar rope, and the surface of the shaft and the wheel through hole are coated with molybdenum disulfide.

[0014] The present invention also provides an assembly method for a cable fixing device for a flat-panel satellite, which comprises the following steps: Step 1: Complete the installation of the equipment in the flat-panel satellite cabin in advance, complete the installation and fixation of the bottom plate and frame of the flat-panel satellite, and complete the plugging of the cables involved in the cabin with the electrical connectors of the corresponding equipment on the bottom plate; Step 2: Install the traction fixing seat and several magnetic fixing lower seats on the surface of the base plate according to the cable outlet position, diameter and routing requirements of the flat-panel satellite assembly; Step 3: Use nylon cable ties to fix the cable to the surface of the traction fixing seat. According to the spacing of several magnetic fixing lower seats, use nylon cable ties to fix the same number of magnetic fixing upper seats to the surface of the cable; Step 4: Install two wire-taking brackets on both sides of the wire-taking wheel, install the two wire-taking brackets on the surface of the bottom plate, and install the second rotating shaft on the wire-taking brackets; Step 5: Connect one end of the traction line to the take-up wheel, and then pass the other end of the traction line through the lower threading holes of all the magnetic fixed lower seats in turn, then go around the first rotating shaft, and then pass through the upper threading holes of the magnetic fixed lower seat and the magnetic fixed upper seat in turn. Finally, fix the end of the traction line on the second rotating shaft; Step 6: Lift the top plate above the frame of the flat-panel satellite, leave space for operation, use the fixing clips to fix the cables on the surface of the top plate, and plug the ends of the cables into the electrical connectors of the corresponding devices on the top plate; Step 7: Connect one end of the vortex spring to the take-up wheel and the other end to the vortex spring housing. Rotate the vortex spring housing to tighten the vortex spring inward, and then use screws to connect the vortex spring housing to the take-up bracket. The vortex spring completes the storage of elastic potential energy.

[0015] The present invention also provides a working method of a cable fixing device for a flat-panel satellite, specifically: the top plate is hoisted downward and closed with the frame, the cable falls under the action of its own gravity, the elastic potential energy of the vortex spring is released, and the take-up wheel is driven to rotate and retract the traction line. Under the action of the traction line, each magnetically fixed upper seat gradually approaches the corresponding magnetically fixed lower seat until the magnetically fixed upper seat and the magnetically fixed lower seat are attracted and locked, and the reserved cable is fixed after the cabin is closed.

[0016] Compared with the prior art, the present invention has the following beneficial effects: (1) The present invention provides a cable fixing device for a flat-panel satellite and its assembly and working method, which can fix the cable after the satellite cabin is assembled without adding a cabin penetration operation hole, thereby avoiding the risk of damage to the cable or equipment.

[0017] (2) The present invention can achieve locking under the action of traction and guidance while the bottom plate is hoisted and closed, without the need for additional operations during the closing process, thereby reducing the difficulty of operation.

[0018] (3) The present invention only plays a traction and guiding role in the process of winding the line. The fixation is achieved by the attraction of the magnetic fixed lower seat and the magnetic fixed upper seat. Therefore, each component will not be subjected to excessive stress. While the whole device realizes a lightweight design, its reliability is still not affected.

[0019] (4) After the magnetic fixed lower seat and the magnetic fixed upper seat described in the present invention are attracted to each other, the attracted parts of the magnetic protrusion and the magnetic concave block are in a tightly fitted state, and the lower armature and the upper armature form a closed magnetic circuit. Under the synergistic magnetic shielding effect of the aluminum alloy shell, there is very little magnetic leakage, which will not affect the normal operation of the satellite magnetic equipment.

[0020] (5) The present invention is flexible in design. The number, installation route, spacing, etc. of the magnetically fixed upper seat and the magnetically fixed lower seat can be changed according to the outlet position, diameter, and routing requirements of the cables involved in the flat-panel satellite assembly, thereby adapting to the fixing requirements in different situations.

[0021] (6) The present invention has a simple structure, small size and light weight, and will not cause excessive layout and weight burdens on the satellite. The precision requirements of each component are low, which can reduce the processing cost, shorten the processing cycle, and have a low cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings: Figure 1 This is a schematic diagram of the structure of a cable fixing device for a flat-panel satellite according to the present invention; Figure 2 This is a schematic diagram of the structure of the traction fixing seat of the present invention; Figure 3 This is a schematic diagram of the structure of the magnetic fixed lower seat of the present invention; Figure 4 This is a schematic diagram of the cross-sectional structure of the magnetically fixed lower seat of the present invention; Figure 5 This is a schematic diagram of the structure of the magnetically fixed upper seat of the present invention; Figure 6 This is a schematic diagram of the cross-sectional structure of the magnetically fixed upper seat of the present invention; Figure 7 It is a schematic diagram of the attraction structure of the magnetically fixed upper seat and the magnetically fixed lower seat of the present invention; Figure 8 It is a schematic diagram of the structure of the wire take-up device of the present invention; Fig. 9 It is a schematic diagram of the cross-sectional structure of the wire take-up device of the present invention; Fig.10 It is a schematic diagram of the structure of the take-up wheel of the present invention; Fig.11 This is a schematic diagram of the structure of the wire take-up bracket according to the present invention; Fig.12 It is a schematic diagram of the structure of the vortex spring housing according to the present invention; Fig.13 It is a schematic diagram of the vortex spring structure of the present invention; Fig.14 The present invention is a schematic diagram of a cable fixing device for a flat-panel satellite assembly method. Figure 1 ; Fig.15The present invention is a schematic diagram of a cable fixing device for a flat-panel satellite assembly method. Figure 2 ; Fig.16 The present invention is a schematic diagram of a cable fixing device for a flat-panel satellite assembly method. Figure 3 ; Fig.17 The present invention is a schematic diagram of a cable fixing device for a flat-panel satellite assembly method. Figure 4 ; Fig.18 The present invention is a schematic diagram of a cable fixing device for a flat-panel satellite assembly method. Figure 5 ; Fig.19 The present invention is a schematic diagram of a cable fixing device for a flat-panel satellite assembly method. Figure 6 ; Fig. 20 This is a schematic diagram of a cable fixing device for a flat-panel satellite according to the present invention after assembly; Fig.21 The working method of the cable fixing device for flat-panel satellite according to the present invention is schematically shown. Figure 1 ; Fig. 22 The working method of the cable fixing device for flat-panel satellite according to the present invention is schematically shown. Figure 2 ; Fig.23 The working method of the cable fixing device for flat-panel satellite according to the present invention is schematically shown. Figure 3 .

[0023] In the figure: 1-traction fixing seat, 2-magnetic fixing lower seat, 3-magnetic fixing upper seat, 4-receiving device, 5-fixing clip, 6-first rotating shaft, 7-cable fixing surface, 8-mounting support, 9-support column, 10-rotating shaft hole, 11-lower armature, 12-magnetic steel, 13-magnetic steel pad, 14-lower shell, 15-lower bottom plate, 16-magnetic steel groove, 17-magnetic concave block, 18-lower threading hole, 19-upper threading hole, 20-upper armature, 21-upper shell, 22-upper bottom plate, 23-magnetic protrusion, 24-nylon Cable tie groove, 25-receiving wheel, 26-receiving bracket, 27-vortex spring housing, 28-vortex spring, 29-traction line, 30-wheel body, 31-threading hole, 32-axle body, 33-vortex spring groove, 34-mounting ear, 35-wheel mounting surface, 36-wheel through hole, 37-rotating shaft through hole, 38-mounting threaded hole, 39-mounting through hole, 40-housing, 41-vortex spring buckle, 42-inner fixed arm, 43-outer fixed arm, 44-cable, 45-second rotating shaft, 46-bottom plate, 47-frame, 48-top plate. DETAILED DESCRIPTION

[0024] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely explain the technical solutions in the embodiments of the present invention. It should be noted that the embodiments of the present invention and the features in the embodiments can be combined with each other without conflict, and the described embodiments are only part of the embodiments of the present invention, not all of the embodiments.

[0025] See also Figure 1-13 The present embodiment is described, a cable fixing device for a flat-panel satellite, comprising a traction fixing seat 1, a magnetic fixing lower seat 2, a magnetic fixing upper seat 3, a wire take-up device 4 and a fixing clip 5, the traction fixing seat 1 is provided with a first rotating shaft 6, the traction fixing seat 1 is connected to the bottom plate 46 of the flat-panel satellite, the traction fixing seat 1 is connected to the cable 44, the end of the cable 44 is connected to the top plate 48 of the flat-panel satellite through the fixing clip 5, the magnetic fixing lower seat 2 and the magnetic fixing upper seat 3 are arranged in pairs and attract each other, the number of the magnetic fixing lower seat 2 and the number of the magnetic fixing upper seat 3 are both several, several magnetic fixing lower seats 2 are connected to the bottom plate 46 of the flat-panel satellite, several magnetic fixing upper seats 3 are connected to the cable 44, the magnetic fixing lower seat 2 is provided with a lower threading hole 18, the upper part of the magnetic fixing lower seat 2 and the lower part of the magnetic fixing upper seat 3 are provided with an upper threading hole 19, the magnetic fixing lower seat 2 and the magnetic fixing upper seat 3 are connected to each other, and the magnetic fixing lower seat 2 is provided with a lower threading hole 19. After the suction fixed upper seat 3 is mutually attracted, the upper threading holes 19 on the magnetic fixed lower seat 2 and the magnetic fixed upper seat 3 are positioned relative to each other, and the wire take-up device 4 includes a wire take-up wheel 25, a wire take-up bracket 26, a vortex spring 28 and a second rotating shaft 45. The wire take-up bracket 26 is connected to the bottom plate 46 of the flat-panel satellite, and the wire take-up wheel 25 and the second rotating shaft 45 are both connected to the wire take-up bracket 26. Both ends of the wire take-up wheel 25 are provided with vortex springs 28, and the outer side of the vortex spring 28 is provided with a vortex spring. Shell 27, the vortex spring shell 27 is connected to the wire taking-up bracket 26, one end of the vortex spring 28 is connected to the wire taking-up wheel 25, and the other end is connected to the vortex spring shell 27, the wire taking-up wheel 25 is connected with a traction line 29, the traction line 29 passes through the lower threading holes 18 of all the magnetic fixed lower seats 2 in sequence, then bypasses the first rotating shaft 6, and then passes through the upper threading holes 19 of the magnetic fixed lower seat 2 and the magnetic fixed upper seat 3 in sequence, and finally the end of the traction line 29 is fixed on the second rotating shaft 45.

[0026] like Figure 2As shown, the basic structures of the traction fixing seat 1 and the fixing clip 5 are the same, both of which include a cable fixing surface 7, a mounting support 8 and a support column 9. The cable fixing surface 7 is connected to the mounting support 8 through four support columns 9, and the cable fixing surface 7 is connected to the cable 44. The cable fixing surface 7, the mounting support 8 and the support column 9 are connected to form a fixing clip 5. On the basis of the fixing clip 5, the traction fixing seat 1 is additionally provided with a rotating shaft hole 10 on the support column 9. The first rotating shaft 6 passes through the rotating shaft hole 10 and is connected to a nut. The mounting support 8 of the traction fixing seat 1 is connected to the bottom plate 46 of the flat-panel satellite, and the mounting support 8 of the fixing clip 5 is connected to the top plate 48 of the flat-panel satellite.

[0027] like Figure 3 and Figure 4 As shown, the magnetic fixed lower seat 2 includes a lower armature 11, a magnetic steel 12, a lower shell 14 and a lower bottom plate 15, and magnetic concave blocks 17 are arranged at both ends of the lower armature 11. A magnetic steel groove 16 is opened on the lower armature 11, and the magnetic steel 12 is arranged in the magnetic steel groove 16. A magnetic steel pad 13 is arranged on the outer side of the magnetic steel 12. The lower armature 11 is sleeved in the lower shell 14, and the lower shell 14 is connected to the lower bottom plate 15. The lower bottom plate 15 is connected to the bottom plate 46 of the flat satellite, and the lower threading hole 18 runs through the lower armature 11 and the lower shell 14. Both ends of the upper part of the lower shell 14 are provided with upper threading holes 19.

[0028] The installation method of the magnetic fixed lower seat 2 is: insert the magnet 12 into the magnet groove 16, and then use the magnetic steel pad 13 to be placed on the outside of the magnet 12 for compression, and finally the lower shell 14 and the lower bottom plate 15 are buckled together to complete the installation of the magnetic fixed lower seat 2, and the contact parts of the lower armature 11, the lower shell 14, and the lower bottom plate 15 are glued to complete the fixation. After fixation, the lower armature 11 coincides with the lower threading hole 18 of the lower shell 14.

[0029] like Figure 5 and Figure 6 As shown, the magnetic fixed upper seat 3 includes an upper armature 20, an upper shell 21 and an upper base plate 22, magnetic protrusions 23 are provided at both ends of the upper armature 20, and an upper threading hole 19 is provided on the magnetic protrusion 23. The upper armature 20 and the upper base plate 22 are both sleeved in the upper shell 21, and the upper shell 21 is connected to the upper base plate 22. Nylon tie grooves 24 are provided on the upper shell 21 and the upper base plate 22, and nylon tie grooves 24 are passed through the nylon tie grooves 24. The magnetic fixed upper seat 3 is connected to the cable 44 through the nylon tie.

[0030] The installation method of the magnetically fixed upper seat 3 is: the upper shell 21 and the upper base plate 22 are buckled together to cover the upper armature 20, and the contact parts of the upper armature 20, the upper shell 21 and the upper base plate 22 are glued to complete the fixation. After fixation, the nylon tie groove 24 of the upper shell 21 and the upper base plate 22 overlap.

[0031] The magnetic steel 12 is preferably made of neodymium iron boron, which has a large magnetic energy product and can realize a miniaturized design of the magnetically fixed lower seat 2. The magnetic steel material has a wide range of extreme temperature, which can avoid demagnetization of the magnetic steel caused by high and low temperature environments in space. The lower armature 11 and the upper armature 20 are preferably made of electromagnetic pure iron, the magnetic steel pad 13 is preferably made of high tear-resistant silicone rubber, and the lower shell 14, the lower bottom plate 15, the upper shell 21 and the upper bottom plate 22 are preferably made of aluminum alloy, which can be formed by stamping sheet metal to reduce processing costs.

[0032] When the magnetically fixed upper seat 3 is close to the magnetically fixed lower seat 2, under the action of the magnetic steel 12, the magnetic protrusion 23 and the magnetic concave block 17 are attracted, and the magnetic protrusion 23 and the magnetic concave block 17 are designed to cooperate with each other. The inclined surface plays a guiding role in the attraction process. After the attraction is completed, the attraction parts of the magnetic protrusion 23 and the magnetic concave block 17 are in a tightly fitted state, and the lower armature 11 and the upper armature 20 form a closed magnetic circuit, such as Figure 7 As shown, under the synergistic magnetic shielding effect of the aluminum alloy casing, magnetic leakage is very small and will not affect the normal operation of the satellite magnetic equipment.

[0033] like Figure 8-Figure 13 As shown, the take-up wheel 25 includes a wheel body 30 and a shaft body 32, the shaft body 32 is arranged at both ends of the wheel body 30, a vortex spring groove 33 is provided on the shaft body 32, a vortex spring buckle 41 is provided at the bottom of the shell 40 of the vortex spring housing 27, and the vortex spring 28 is provided with an inner fixing arm 42 and an outer fixing arm 43, the inner fixing arm 42 is embedded in the vortex spring groove 33, and the outer fixing arm 43 is embedded in the vortex spring buckle 41. A threading hole 31 is provided on the wheel body 30 for passing and fixing the traction line 29, and the traction line 29 passes through the threading hole 31 and has a nail head at one end.

[0034] The wire take-up bracket 26 includes a mounting lug 34 and a wheel mounting surface 35, wherein the mounting lug 34 is arranged vertically with the wheel mounting surface 35, and the mounting lug 34 is connected to the bottom plate 46 of the flat satellite, and the wheel mounting surface 35 and the shell 40 of the spiral spring housing 27 are both provided with a wheel through hole 36, and the shaft body 32 passes through the wheel through hole 36, and the wheel mounting surface 35 is provided with a shaft through hole 37, and the second shaft 45 passes through the shaft through hole 37, and the wheel mounting surface 35 is provided with a mounting threaded hole 38, and the shell 40 of the spiral spring housing 27 is provided with a mounting through hole 39, and the spiral spring housing 27 is connected to the wheel mounting surface 35 through the mounting through hole 39, the mounting threaded hole 38 and the screw. The wire take-up device 4 is synchronously assembled during the cable fixing device, and is not installed separately.

[0035] The vortex spring housing 27 is preferably made of aluminum alloy and can be formed by stamping sheet metal to reduce processing costs. The vortex spring 28 is preferably made of spring steel, which is heat-treated after winding to ensure its elasticity. The traction line 29 is preferably a Kevlar rope to avoid damage and breakage. The surfaces of the shaft 32 and the wheel through hole 36 are coated with molybdenum disulfide to achieve lubrication and prevent vacuum cold welding.

[0036] See also Figure 14-20 This embodiment is described. This embodiment is a method for assembling a cable fixing device for a flat-panel satellite, which includes the following steps: Step 1: Pre-install the equipment in the flat-panel satellite cabin, install and fix the bottom plate 46 and frame 47 of the flat-panel satellite, and plug the cables 44 involved in the cabin assembly into the corresponding equipment electrical connectors on the bottom plate 46; Step 2: If Fig.14 As shown, according to the outlet position, diameter and routing requirements of the cable 44 involved in the flat-panel satellite assembly, the traction fixing seat 1 and a plurality of magnetic fixing lower seats 2 are installed on the surface of the bottom plate 46; Step 3: If Fig.15 As shown, a nylon tie is used to fix the cable 44 on the surface of the traction fixing seat 1, and according to the spacing of a plurality of magnetic fixing lower seats 2, an equal number of magnetic fixing upper seats 3 are fixed on the surface of the cable 44 using nylon tie; Step 4: Fig.16 As shown, two wire-receiving brackets 26 are installed on both sides of the wire-receiving wheel 25, and then the two wire-receiving brackets 26 of the assembly are installed on the surface of the bottom plate 46, the assembly is close to the last magnetic fixed lower seat 2, and the second rotating shaft 45 is installed on the wire-receiving bracket 26 and connected using a nut; Step 5: Fig.17 As shown, the traction line 29 with the nail head is passed through the threading hole 31 of the take-up wheel 25, so that one end of the traction line 29 is connected to the take-up wheel 25, and then the other end of the traction line 29 is passed through the lower threading holes 18 of all the magnetic fixed lower seats 2 in sequence, and then bypasses the first rotating shaft 6, and then passes through an upper threading hole 19 on the magnetic fixed lower seat 2, and then passes through the two upper threading holes 19 on the magnetic fixed upper seat 3 in sequence, and then passes through another upper threading hole 19 on the magnetic fixed lower seat 2, and so on through all the upper threading holes 19 of the magnetic fixed lower seat 2 and the magnetic fixed upper seat 3, and finally the end of the traction line 29 is fixed on the second rotating shaft 45. The threading path is as shown in FIG. Fig.17 As indicated by the arrow; Step 6: Fig.18 As shown, a crane is used to hoist the top plate 48 to the top of the frame 47 of the flat-panel satellite, leaving space for operation, and a fixing clip 5 is used to fix the cable 44 on the surface of the top plate 48, and the end of the cable 44 is plugged into the corresponding device electrical connector on the top plate 48; Step 7: Fig.19 As shown, the inner fixing arm 42 of the vortex spring 28 is inserted into the vortex spring groove 33, so that one end of the vortex spring 28 is connected to the take-up wheel 25, and then the outer fixing arm 43 is inserted into the vortex spring buckle 41 of the vortex spring housing 27, so that the other end of the vortex spring 28 is connected to the vortex spring housing 27, and the vortex spring housing 27 is rotated to make the vortex spring 28 roll inward, and then the vortex spring housing 27 is connected to the take-up bracket 26 with screws, and the vortex spring 28 completes the storage of elastic potential energy. The cable fixing device after installation is as shown in FIG. Fig. 20 shown.

[0037] See also Figure 21-23 The present embodiment is described as a method for using a cable fixing device for a flat-panel satellite. Specifically, the top plate 48 is hoisted downward and closed with the frame 47, the cable 44 falls under the action of its own gravity, the elastic potential energy of the vortex spring 28 is released, and the take-up wheel 25 is driven to rotate and take up the traction line 29. The traction route is as follows: Fig.21 As shown. Under the action of the traction line 29, each magnetic fixed upper seat 3 gradually approaches the corresponding magnetic fixed lower seat 2. Both the magnetic fixed upper seat 3 and the magnetic fixed lower seat 2 have upper threading holes 19. Therefore, under the action of the traction line 29, the two can accurately approach each other and be tightly attracted under the guidance of the magnetic protrusion 23 and the magnetic concave block 17, as shown. Fig. 22 As shown, until the magnetically fixed upper seat 3 and the magnetically fixed lower seat 2 are attracted and locked, the reserved cable 44 completes the fixation after the cabin is closed, which can avoid the risk of damage caused by shaking, such as Fig.23 shown.

[0038] When in use, the wire take-up device 4 only guides the approach of the magnetic fixed upper seat 3 and the magnetic fixed lower seat 2. The downward movement of the magnetic fixed upper seat 3 mainly relies on the gravity of the cable 44. Therefore, the vortex spring 28 does not need too much elasticity, and the various components of the wire take-up device do not need to bear too much stress.

[0039] The specific embodiments of the present invention disclosed above are only used to help explain the present invention. The specific embodiments do not describe all the details in detail, nor do they limit the invention to the specific embodiments described. According to the content of this specification, many modifications and changes can be made. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can understand and use the present invention well.

Claims

1. A cable fixing device for a flat-panel satellite, characterized in that: The invention comprises a traction fixing seat (1), a magnetic fixing lower seat (2), a magnetic fixing upper seat (3), a wire take-up device (4) and a fixing clip (5); the traction fixing seat (1) is provided with a first rotating shaft (6); the traction fixing seat (1) is connected to a bottom plate (46) of a flat-panel satellite; the traction fixing seat (1) is connected to a cable (44); the end of the cable (44) is connected to a top plate (48) of the flat-panel satellite via a fixing clip (5); the magnetic fixing lower seat (2) and the magnetic fixing upper seat (3) are arranged in pairs and are mutually connected. The magnetic fixed lower seat (2) and the magnetic fixed upper seat (3) are mutually attracted, and the number of the magnetic fixed lower seat (2) and the number of the magnetic fixed upper seat (3) are both multiple, and the multiple magnetic fixed lower seats (2) are connected to the bottom plate (46) of the flat-panel satellite, and the multiple magnetic fixed upper seats (3) are connected to the cable (44). The magnetic fixed lower seat (2) is provided with a lower threading hole (18), and the upper part of the magnetic fixed lower seat (2) and the lower part of the magnetic fixed upper seat (3) are both provided with an upper threading hole (19). After the magnetic fixed lower seat (2) and the magnetic fixed upper seat (3) are mutually attracted, the magnetic fixed The upper threading holes (19) on the fixed lower seat (2) and the magnetic fixed upper seat (3) are positioned relative to each other, the wire take-up device (4) comprises a wire take-up wheel (25), a wire take-up bracket (26), a vortex spring (28) and a second rotating shaft (45), the wire take-up bracket (26) is connected to the bottom plate (46) of the flat-panel satellite, the wire take-up wheel (25) and the second rotating shaft (45) are both connected to the wire take-up bracket (26), both ends of the wire take-up wheel (25) are provided with vortex springs (28), the outer side of the vortex spring (28) is provided with a vortex spring housing (27), and the vortex spring (28) is provided with a vortex spring housing (27). The spring housing (27) is connected to the wire-receiving bracket (26); one end of the vortex spring (28) is connected to the wire-receiving wheel (25), and the other end is connected to the vortex spring housing (27); a traction line (29) is connected to the wire-receiving wheel (25); the traction line (29) passes through the lower threading holes (18) of all the magnetic fixed lower seats (2) in sequence, then bypasses the first rotating shaft (6), and then passes through the upper threading holes (19) of the magnetic fixed lower seat (2) and the magnetic fixed upper seat (3) in sequence; finally, the end of the traction line (29) is fixed on the second rotating shaft (45).

2. A cable fixing device for a flat-panel satellite according to claim 1, characterized in that: The traction fixing seat (1) and the fixing clip (5) both comprise a cable fixing surface (7), a mounting support (8) and a support column (9); the cable fixing surface (7) is connected to the mounting support (8) via four support columns (9); the cable fixing surface (7) is connected to a cable (44); a rotating shaft hole (10) is provided on the support column (9) of the traction fixing seat (1); the first rotating shaft (6) passes through the rotating shaft hole (10) and is connected to a nut; the mounting support (8) of the traction fixing seat (1) is connected to a bottom plate (46) of a flat-panel satellite; and the mounting support (8) of the fixing clip (5) is connected to a top plate (48) of the flat-panel satellite.

3. A cable fixing device for a flat-panel satellite according to claim 1, characterized in that: The magnetic fixed lower seat (2) comprises a lower armature (11), a magnetic steel (12), a lower shell (14) and a lower bottom plate (15); both ends of the lower armature (11) are provided with magnetic concave blocks (17); a magnetic steel groove (16) is provided on the lower armature (11); a magnetic steel (12) is provided in the magnetic steel groove (16); a magnetic steel pad (13) is provided outside the magnetic steel (12); the lower armature (11) is sleeved in the lower shell (14); the lower shell (14) is connected to the lower bottom plate (15); the lower bottom plate (15) is connected to the bottom plate (46) of the flat satellite; the lower threading hole (18) passes through the lower armature (11) and the lower shell (14); and upper threading holes (19) are provided at both ends of the upper part of the lower shell (14).

4. A cable fixing device for a flat-panel satellite according to claim 3, characterized in that: The magnetically fixed upper seat (3) comprises an upper armature (20), an upper shell (21) and an upper base plate (22); both ends of the upper armature (20) are provided with magnetic protrusions (23); an upper threading hole (19) is provided on the magnetic protrusions (23); the upper armature (20) and the upper base plate (22) are both sleeved in the upper shell (21); the upper shell (21) is connected to the upper base plate (22); the upper shell (21) and the upper base plate (22) are both provided with nylon tie grooves (24); a nylon tie passes through the nylon tie grooves (24); and the magnetically fixed upper seat (3) is connected to a cable (44) via the nylon tie.

5. A cable fixing device for a flat-panel satellite according to claim 4, characterized in that: The magnetic steel (12) is made of neodymium iron boron, the lower armature (11) and the upper armature (20) are made of electromagnetic pure iron, the magnetic steel pad (13) is made of silicone rubber, and the lower shell (14), the lower base plate (15), the upper shell (21) and the upper base plate (22) are made of aluminum alloy.

6. A cable fixing device for a flat-panel satellite according to claim 1, characterized in that: The take-up wheel (25) comprises a wheel body (30) and a shaft body (32), wherein the shaft body (32) is arranged at two ends of the wheel body (30), a vortex spring groove (33) is provided on the shaft body (32), a vortex spring buckle (41) is provided at the bottom of the shell (40) of the vortex spring housing (27), and the vortex spring (28) is provided with an inner fixing arm (42) and an outer fixing arm (43), wherein the inner fixing arm (42) is embedded in the vortex spring groove (33), and the outer fixing arm (43) is embedded in the vortex spring buckle (41).

7. A cable fixing device for a flat-panel satellite according to claim 6, characterized in that: The wire take-up bracket (26) comprises a mounting lug (34) and a wheel mounting surface (35), wherein the mounting lug (34) is arranged vertically to the wheel mounting surface (35), and the mounting lug (34) is connected to the bottom plate (46) of the flat-panel satellite, and the wheel mounting surface (35) and the shell (40) of the volute spring housing (27) are both provided with a wheel through hole (36), and the shaft (32) passes through the wheel through hole (36), and a rotating shaft through hole (37) is provided on the wheel mounting surface (35), and the second rotating shaft (45) passes through the rotating shaft through hole (37), and a mounting threaded hole (38) is provided on the wheel mounting surface (35), and a mounting through hole (39) is provided on the shell (40) of the volute spring housing (27), and the volute spring housing (27) is connected to the wheel mounting surface (35) through the cooperation of the mounting through hole (39), the mounting threaded hole (38) and screws.

8. A cable fixing device for a flat-panel satellite according to claim 7, characterized in that: The wheel body (30) is provided with a threading hole (31), the traction line (29) passes through the threading hole (31) and has a nail head at one end, the vortex spring housing (27) is made of aluminum alloy, the vortex spring (28) is made of spring steel, the traction line (29) is a Kevlar rope, and the surfaces of the shaft body (32) and the wheel through hole (36) are coated with molybdenum disulfide.

9. A method for assembling a cable fixing device for a flat-panel satellite as claimed in claim 1, characterized in that: It includes the following steps: Step 1: Preliminarily complete the installation of the equipment in the flat-panel satellite cabin, complete the installation and fixation of the bottom plate (46) and the frame (47) of the flat-panel satellite, and complete the plugging of the cables (44) involved in the cabin assembly with the electrical connectors of the corresponding equipment on the bottom plate (46); Step 2: Install the traction fixing seat (1) and a plurality of magnetic fixing lower seats (2) on the surface of the bottom plate (46) according to the outlet position, diameter and routing requirements of the cable (44) involved in the flat-panel satellite assembly; Step 3: Use nylon cable ties to fix the cable (44) on the surface of the traction fixing seat (1), and use nylon cable ties to fix the same number of magnetic fixing upper seats (3) on the surface of the cable (44) according to the spacing between the plurality of magnetic fixing lower seats (2); Step 4: Install two wire-receiving brackets (26) on both sides of the wire-receiving wheel (25), install the two wire-receiving brackets (26) on the surface of the bottom plate (46), and install the second rotating shaft (45) on the wire-receiving brackets (26); Step 5: Connect one end of the traction line (29) to the take-up wheel (25), and then pass the other end of the traction line (29) through the lower threading holes (18) of all the magnetic fixed lower seats (2) in sequence, then pass around the first rotating shaft (6), and then pass through the upper threading holes (19) of the magnetic fixed lower seat (2) and the magnetic fixed upper seat (3) in sequence, and finally fix the end of the traction line (29) on the second rotating shaft (45); Step 6: Lift the top plate (48) above the frame (47) of the flat-panel satellite, leaving space for operation, use the fixing clip (5) to fix the cable (44) on the surface of the top plate (48), and plug the end of the cable (44) into the corresponding device electrical connector on the top plate (48); Step 7: Connect one end of the vortex spring (28) to the take-up wheel (25) and the other end to the vortex spring housing (27). Rotate the vortex spring housing (27) to tighten the vortex spring (28) inward. Then use screws to connect the vortex spring housing (27) to the take-up bracket (26). The vortex spring (28) completes the storage of elastic potential energy.

10. A method for operating a cable fixing device for a flat-panel satellite as claimed in claim 1, characterized in that: The top plate (48) is hoisted downward and closed with the frame (47), the cable (44) falls under the action of its own weight, the elastic potential energy of the vortex spring (28) is released, and the take-up wheel (25) is driven to rotate and retract the traction line (29). Under the action of the traction line (29), each magnetic fixed upper seat (3) gradually approaches the corresponding magnetic fixed lower seat (2) until the magnetic fixed upper seat (3) and the magnetic fixed lower seat (2) are attracted and locked, and the reserved cable (44) is fixed after the cabin is closed.

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