A reinforcement mechanism for stacked flat-panel satellite and its use method

Abstract

The present invention proposes a reinforcement mechanism and a method of using the same for stacked flat-panel satellites, and belongs to the field of space product structure and mechanism design. The problem of poor mechanical properties of existing flat-panel satellite assemblies is solved. It includes a first reinforcement mechanism and a second reinforcement mechanism, and the first reinforcement mechanism and the second reinforcement mechanism are alternately arranged around the outside of the satellite assembly. The first reinforcement mechanism includes a first recovery rod, a first steel belt fixing seat and an elastic steel belt. A plurality of first steel belt fixing seats are arranged axially at intervals on the first recovery rod, and two elastic steel belts are connected to both sides of each first steel belt fixing seat, respectively. A plurality of second steel belt fixing seats are arranged axially at intervals on the second recovery rod, and the first steel belt fixing seat and the second steel belt fixing seat are alternately arranged in the vertical direction. One end of the elastic steel belt is connected to the first steel belt fixing seat, and the other end is connected to the second steel belt fixing seat through a fixing rope. It is mainly used for the reinforcement of stacked flat-panel satellites.

Description

Technical Field

[0001] The invention belongs to the field of reinforced structure design of flat-panel satellites, and in particular relates to a reinforcing mechanism applied to a stacked flat-panel satellite and a use method thereof. Background Art

[0002] In recent years, with the continuous development of low-orbit communication technology, the construction of low-orbit communication constellation systems has gradually become a research focus in the aerospace field. Low-orbit communication constellations have two characteristics: first, the communication satellite payload size is large, so the satellite needs to have a large installation surface; second, low-orbit communication constellations often require hundreds, or even thousands or tens of thousands of satellites to achieve global coverage. In this case, stacked flat-panel satellites have become the mainstream solution. The advantages of stacked flat-panel satellites are: first, flat-panel satellites minimize the volume and weight of the entire satellite while ensuring that the installation surface size meets the payload requirements; second, flat-panel satellites can achieve multiple satellite launches in one rocket through stacking, which significantly improves the transportation efficiency and thus reduces the launch cost.

[0003] During the final assembly and launch phase, the stacked flat-panel satellite is assembled by installing stacking columns on the outside of the satellite body, and then stacking and pressing the stacking columns together. In the assembled satellite assembly, there is no direct connection between the satellite bodies, the stacking columns are stacked and pressed together in the longitudinal direction, and there is no direct connection between the stacking columns in the transverse direction. The defect of this combination method is that after the assembly is completed, any stacking column combination is similar to a cantilever beam structure. Due to the amplification effect of the longer force arm, the closer to the top, the greater the bending moment, the greater the vibration response, and the worse the mechanical environment. Therefore, the requirements for the mechanical environment resistance of the satellite body and each on-board equipment are also higher. Since the networking satellite needs to meet the worst mechanical environment conditions, this defect causes unnecessary design margins for the mechanical properties of a large number of satellites near the bottom and on-board equipment. This defect also leads to a limit on the number of stacking layers.

[0004] At present, the solutions to this problem include: 1. Strengthening the stiffness and strength of each stacked column to improve the mechanical properties of the entire satellite assembly; 2. Increasing the compression force of the stacked columns to improve the mechanical properties of the entire satellite assembly; 3. In addition to overall compression, increasing the fixation between the stacked columns to improve the mechanical properties of the entire satellite assembly. However, all of the above schemes have obvious defects, including: First, the enhancement of the stiffness and strength of each stacking column is not proportional to the improvement of the overall mechanical properties. Taking this measure to improve the overall mechanical properties often requires excessive weight and design costs. Since each stacking column is fixedly connected to the outside of the satellite, it is always a component of the satellite during the entire life cycle from the satellite's release into orbit to its deorbit. Therefore, the excessive weight of the stacking column will not only occupy additional carrying capacity, but will also affect the satellite's configuration layout, attitude control, orbit control, etc.; second, there is a theoretical upper limit to increasing the clamping force of the stacking column, and the premise of increasing the clamping force is also to increase the strength of the stacking column; third, increasing the fixation between the stacking columns can effectively improve the mechanical properties of the entire satellite, but if the stacking columns are directly fixed, the complexity of the mechanism design and the development cost will increase significantly, and the unlocking of the stacking columns before the satellite is released in orbit will reduce the reliability of the satellite release. Summary of the invention

[0005] In view of this, the present invention aims to propose a reinforcement mechanism for stacked flat-panel satellites and a method of using the same, so as to solve the problem of poor mechanical properties of existing flat-panel satellite assemblies.

[0006] To achieve the above-mentioned purpose, the present invention adopts the following technical scheme: a reinforcement mechanism applied to a stacked flat-panel satellite, comprising a first reinforcement mechanism and a second reinforcement mechanism, wherein the first reinforcement mechanism and the second reinforcement mechanism are alternately arranged around the outside of the satellite assembly, wherein the first reinforcement mechanism and the second reinforcement mechanism both comprise a recovery rod and a steel belt fixing seat, wherein the recovery rod is divided into a first recovery rod and a second recovery rod, wherein the steel belt fixing seat is divided into a first steel belt fixing seat and a second steel belt fixing seat, wherein the first reinforcement mechanism comprises a first recovery rod, a first steel belt fixing seat and an elastic steel belt, wherein a plurality of first steel belt fixing seats are arranged axially at intervals on the first recovery rod, wherein two elastic steel belts are respectively connected on both sides of each first steel belt fixing seat, wherein the elastic steel belt is an elongated thin sheet structure having a shape memory function, wherein the elastic steel belt has a straightened, curled and any-point bending state, and wherein the cross section is an arch in the straightened state. The cross-section is rectangular in the curled state, the cross-section at the bending point is rectangular in the bent state at any point, and the cross-section of the remaining part is arched. The second reinforcing mechanism includes a second recovery rod, a second steel belt fixing seat, a fixing rope and a hot knife. A plurality of second steel belt fixing seats are arranged at intervals along the axial direction on the second recovery rod. The first steel belt fixing seat and the second steel belt fixing seat are alternately arranged in the vertical direction. One end of the elastic steel belt is connected to the first steel belt fixing seat, and the other end is connected to the second steel belt fixing seat through a fixing rope. The end of the elastic steel belt is in a curled state, and two adjacent elastic steel belts form a spatial triangular structure with the recovery rod. A hot knife is arranged on the second steel belt fixing seat, and the hot knife is fitted on both sides of the fixing rope. The lower end of the recovery rod is rotatably connected to the recovery fixing seat, and a recovery torsion spring is arranged at the connection between the recovery rod and the recovery fixing seat, and the recovery fixing seat is connected to the transport adapter.

[0007] Furthermore, the first steel belt fixing seat includes a first recovery square groove and a first steel belt fixing arm, the first recovery square groove is a square tube structure, the first recovery square groove is sleeved on the first recovery rod, the number of the first steel belt fixing arms is four, the four first steel belt fixing arms are symmetrically arranged in pairs on both sides of the first recovery square groove, there is an angle between the two first steel belt fixing arms on the same side, and one end of the elastic steel belt is connected to the first steel belt fixing arm.

[0008] Furthermore, the second steel belt fixing seat includes a second recovery square groove and a second steel belt fixing arm, the second recovery square groove is a square tube structure, the second recovery square groove is sleeved on the second recovery rod, there are two second steel belt fixing arms, the two second steel belt fixing arms are symmetrically arranged on both sides of the second recovery square groove, the elastic steel belt is provided with a row of first fixing rope holes arranged at equal intervals at the connecting end with the second steel belt fixing seat, and the upper and lower parts of the second steel belt fixing arms are respectively provided with second fixing rope holes, and the fixing rope passes through the first fixing rope hole and the second fixing rope hole and is tied tightly.

[0009] Furthermore, a hot knife wire hole is provided on the side of the second recovery square groove, and a hot knife fixing groove and a fixing rope groove are provided on the second steel belt fixing arm. The fixing rope after being tightened is embedded in the fixing rope groove, and the hot knife is installed in the hot knife fixing groove. The wire of the hot knife passes through the hot knife wire hole and is led into the second recovery square groove.

[0010] Furthermore, the recovery fixing seat includes mounting ears, a fixed rear wall and a fixed side wall. There are two fixed side walls, and the two fixed side walls are connected to both sides of the fixed rear wall. The two fixed side walls are rotatably connected to the recovery rod. The bottom of the fixed rear wall and the fixed side wall are both provided with mounting ears, and the mounting ears are connected to the carrying adapter.

[0011] Furthermore, the recovery torsion spring includes a first torsion spring arm and a second torsion spring arm, a torsion spring groove is opened on the fixed rear wall, the first torsion spring arm is installed in the torsion spring groove, and the second torsion spring arm is installed in the recovery rod.

[0012] Furthermore, the two fixed side walls are each provided with a shaft hole, the lower portion of the recovery rod is provided with a shaft through hole, the shaft passes through the shaft hole, the shaft through hole and the recovery torsion spring and is connected to the nut.

[0013] Furthermore, the satellite assembly includes a plurality of flat-panel satellites, and the plurality of flat-panel satellites are stacked and installed along the axial direction.

[0014] Furthermore, the flat-panel satellite includes a satellite body and stacking columns, the number of the stacking columns is four, and the four stacking columns are respectively connected to the four corners of the satellite body.

[0015] The present invention also provides a method for using a reinforcement mechanism applied to a stacked flat-panel satellite, the method comprising an assembly process and a release process;

[0016] The assembly process is as follows: install the first steel belt fixing seat on the first recovery rod, connect the two sides of the recovery torsion spring to the recovery fixing seat and the first recovery rod respectively, then rotate the first recovery rod and the recovery fixing seat, bend the elastic steel belt to make it in a straight state, fix the elastic steel belt on the first steel belt fixing seat, and complete the assembly of the first reinforcement mechanism; install the second steel belt fixing seat on the second recovery rod, connect the two sides of the recovery torsion spring to the recovery fixing seat and the second recovery rod respectively, then rotate the second recovery rod and the recovery fixing seat, install the hot knife on the second steel belt fixing seat, and complete the assembly of the second reinforcement mechanism; alternately arrange the first reinforcement mechanism and the second reinforcement mechanism around the outside of the satellite assembly, install the recovery fixing seat on the surface of the carrier adapter, rotate the first reinforcement mechanism and the second reinforcement mechanism inward until each recovery rod is in a vertical state, bend the elastic steel belt to make it bend at the edge of the satellite assembly, connect the elastic steel belt to the second steel belt fixing seat through a fixing rope, then bend the end of the elastic steel belt to make the end of the elastic steel belt in a curled state, and the assembly is completed;

[0017] The release process is as follows: the hot knife is energized, the hot knife melts the fixing rope, the elastic steel belt begins to curl and retract under the triggering of the curling part at the end, the recovery rod loses the fixation of the elastic steel belt, and rotates outward under the action of the recovery torsion spring until all the elastic steel belts are completely curled and retracted. After the recovery rod fits the surface of the carrier adapter, the release is completed.

[0018] Compared with the prior art, the beneficial effects of the present invention are as follows: the present invention provides a reinforcing mechanism for stacked flat-panel satellites and a method of using the same, which can improve the mechanical properties of the entire satellite assembly without increasing the weight of the stacking columns and the satellite body, while decoupling the reinforcing mechanism from the stacking column compression and release mechanism, thereby not affecting the reliability of satellite release.

[0019] The specific advantages are as follows:

[0020] (1) The reinforcing mechanism for stacked flat-panel satellites described in the present invention can wrap the flat-panel satellite assembly to make each independent stacking column become a whole, thereby reducing the cantilever beam effect of the independent stacking column and improving the mechanical properties of the flat-panel satellite assembly.

[0021] (2) The reinforcing mechanism for stacked flat-panel satellites described in the present invention forms a spatial triangle locally through two adjacent elastic steel strips and a recovery rod, thereby improving the stability of the structure, thereby suppressing the pulling of any stacked column on the whole due to the lateral swing, and further improving the reinforcing effect of the structural rigidity and strength.

[0022] (3) The reinforcing mechanism for stacked flat-panel satellites described in the present invention is decoupled from the stacking column design. The stacking column is wrapped with a mesh structure and has no direct fixed connection with the stacking column, thereby avoiding reliability problems caused by mutual coupling of the mechanisms.

[0023] (4) The reinforcing mechanism for stacked flat-panel satellites described in the present invention improves the mechanical properties of the flat-panel satellite assembly only through the mechanism itself, without adding other means, thereby reducing the design pressure on the satellite itself, the stacking column, etc.

[0024] (5) The reinforcing mechanism for stacked flat-panel satellites described in the present invention uses a hot knife to fuse the fixing rope to unlock, which has low cost and small release impact, and has little impact on the satellite and on-board equipment.

[0025] (6) The elastic steel belt in the reinforcement mechanism for stacked flat-panel satellites described in the present invention has an arched cross-section in the straightened state and has strong mechanical resistance, which can further improve the overall mechanical properties of the satellite assembly.

[0026] (7) In the reinforcing mechanism for a stacked flat-panel satellite described in the present invention, the elastic steel belt can be curled and folded by its own elasticity, thereby avoiding the need for adding a recovery structure or components and reducing the complexity of the mechanism.

[0027] (8) The components of the reinforcement mechanism for stacked flat-panel satellites described in the present invention are simple in structure, small in size, and light in weight, and the additional burden on the carrying capacity is small. The design is simple, the precision requirement is low, and the processing cost and processing cycle can be reduced.

[0028] (10) The reinforcing mechanism for stacked flat-panel satellites described in the present invention can be repeatedly fixed and released, thereby reducing the cost of ground tests. Each component is independent of each other and can be redesigned / selected according to the specific needs of the satellite, with strong adaptability. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] 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:

[0030] Figure 1 This is a schematic diagram of the structure of a reinforcement mechanism applied to a stacked flat-panel satellite according to the present invention;

[0031] Figure 2 It is a schematic diagram of the overall structure of the first reinforcing mechanism of the present invention;

[0032] Figure 3 It is a schematic diagram of the partial structure of the first reinforcing mechanism of the present invention;

[0033] Figure 4 This is a schematic diagram of the structure of the first recovery rod according to the present invention;

[0034] Figure 5 This is a schematic structural diagram of the first steel belt fixing seat of the present invention;

[0035] Figure 6 This is a schematic diagram of the structure of the elastic steel belt in a curled state according to the present invention;

[0036] Figure 7 This is a schematic structural diagram of the elastic steel belt of the present invention in a straightened state;

[0037] Figure 8 It is a schematic diagram of the curling and gathering process of the elastic steel belt according to the present invention;

[0038] Fig. 9 This is a schematic diagram of the structure of the recovery fixing seat of the present invention;

[0039] Fig.10 This is a schematic diagram of the structure of the recovery torsion spring of the present invention;

[0040] Fig.11 It is a schematic diagram of the overall structure of the second reinforcing mechanism of the present invention;

[0041] Fig.12 It is a schematic diagram of the partial structure of the second reinforcing mechanism of the present invention;

[0042] Fig.13 This is a schematic diagram of the structure of the second recovery rod according to the present invention;

[0043] Fig.14 This is a schematic structural diagram of the second steel belt fixing seat of the present invention;

[0044] Fig.15 Schematic diagram of the assembly process of the first reinforcement mechanism of the present invention Figure 1 ;

[0045] Fig.16 Schematic diagram of the assembly process of the first reinforcement mechanism of the present invention Figure 2 ;

[0046] Fig.17 Schematic diagram of the assembly process of the first reinforcement mechanism of the present invention Figure 3 ;

[0047] Fig.18 Schematic diagram of the assembly process of the second reinforcement mechanism of the present invention Figure 1 ;

[0048] Fig.19 Schematic diagram of the assembly process of the second reinforcement mechanism of the present invention Figure 2 ;

[0049] Fig. 20 Schematic diagram of the assembly process of the second reinforcement mechanism of the present invention Figure 3 ;

[0050] Fig.21 This is a schematic diagram of the flat-panel satellite structure of the present invention;

[0051] Fig. 22 This is a schematic diagram of the structure of the satellite assembly of the present invention;

[0052] Fig.23 Schematic diagram of the assembly process of the reinforcement mechanism of the present invention Figure 1 ;

[0053] Fig.24 Schematic diagram of the assembly process of the reinforcement mechanism of the present invention Figure 2 ;

[0054] Fig.25 Schematic diagram of the assembly process of the reinforcement mechanism of the present invention Figure 3 ;

[0055] Fig.26 Schematic diagram of the assembly process of the reinforcement mechanism of the present invention Figure 4 ;

[0056] Fig. 27 It is a schematic diagram of the release process of the reinforcing mechanism of the present invention;

[0057] Fig.28 This is a schematic diagram of the completion of the release of the reinforcing mechanism described in the present invention.

[0058] In the figure:

[0059] 1-first reinforcement mechanism, 2-second reinforcement mechanism, 3-flat satellite, 4-carrying adapter, 5-first recovery rod, 6-first steel belt fixing seat, 7-elastic steel belt, 8-recovery fixing seat, 9-rotating shaft, 10-recovery torsion spring, 11-second recovery rod, 12-second steel belt fixing seat, 13-fixing rope, 14-hot knife, 15-star body, 16-stacking column, 17-rotating shaft through hole, 18-first recovery square groove, 19-first steel belt fixing arm, 20-first fixing rope hole, 21-mounting ear, 22-fixed rear wall, 23-fixed side wall, 24-torsion spring groove, 25-rotating shaft hole, 26-first torsion spring arm, 27-second torsion spring arm, 28-second recovery square groove, 29-second steel belt fixing arm, 30-hot knife wire hole, 31-second fixing rope hole, 32-hot knife fixing groove, 33-fixed rope groove. DETAILED DESCRIPTION

[0060] 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.

[0061] See also Figure 1-28 The present embodiment is described, a reinforcing mechanism applied to a stacked flat-panel satellite, comprising a first reinforcing mechanism 1 and a second reinforcing mechanism 2, wherein the first reinforcing mechanism 1 and the second reinforcing mechanism 2 are alternately arranged around the outside of the satellite assembly, the first reinforcing mechanism 1 and the second reinforcing mechanism 2 both comprise a recovery rod and a steel belt fixing seat, the recovery rod is divided into a first recovery rod 5 and a second recovery rod 11, the steel belt fixing seat is divided into a first steel belt fixing seat 6 and a second steel belt fixing seat 12, the first reinforcing mechanism 1 comprises a first recovery rod 5, a first steel belt fixing seat 6 and an elastic steel belt 7, a plurality of first steel belt fixing seats 6 are arranged axially at intervals on the first recovery rod 5, two elastic steel belts 7 are respectively connected on both sides of each first steel belt fixing seat 6, the elastic steel belt 7 is an elongated thin sheet structure, has a shape memory function, including straightening, curling and arbitrary point bending states, the cross section is arched in the straightened state, the cross section is rectangular in the curled state, and the cross section is bent at any point. The cross-section of the bending part in the intentional bending state is rectangular, and the cross-section of the remaining part is arched. The second reinforcement mechanism 2 includes a second recovery rod 11, a second steel belt fixing seat 12, a fixing rope 13 and a hot knife 14. A plurality of second steel belt fixing seats 12 are arranged on the second recovery rod 11 along the axial direction. The first steel belt fixing seat 6 and the second steel belt fixing seat 12 are alternately arranged in the vertical direction. One end of the elastic steel belt 7 is connected to the first steel belt fixing seat 6, and the other end is connected to the second steel belt fixing seat 12 through the fixing rope 13. The end of the elastic steel belt 7 is in a curled state, and the two adjacent elastic steel belts 7 form a spatial triangular structure with the recovery rod. A hot knife 14 is arranged on the second steel belt fixing seat 12, and the hot knife 14 is fitted on both sides of the fixing rope 13. The lower end of the recovery rod is rotatably connected to the recovery fixing seat 8, and a recovery torsion spring 10 is arranged at the connection between the recovery rod and the recovery fixing seat 8, and the recovery fixing seat 8 is connected to the transport adapter 4.

[0062] The assembly process of this embodiment is as follows: install the first steel belt fixing seat 6 on the first recovery rod 5, connect the two sides of the recovery torsion spring 10 to the recovery fixing seat 8 and the first recovery rod 5 respectively, then rotate the first recovery rod 5 to connect with the recovery fixing seat 8, bend the elastic steel belt 7 to make it in a straight state, and fix the elastic steel belt 7 on the first steel belt fixing seat 6 to complete the assembly of the first reinforcement mechanism 1; install the second steel belt fixing seat 12 on the second recovery rod 11, connect the two sides of the recovery torsion spring 10 to the recovery fixing seat 8 and the second recovery rod 11 respectively, and then connect the second recovery rod 11 to the recovery fixing seat 8. Rotate and connect, install the hot knife 14 on the second steel belt fixing seat 12, and complete the assembly of the second reinforcement mechanism 2; alternately arrange the first reinforcement mechanism 1 and the second reinforcement mechanism 2 around the outside of the satellite assembly, install the recovery fixing seat 8 on the surface of the carrier adapter 4, rotate the first reinforcement mechanism 1 and the second reinforcement mechanism 2 inward until each recovery rod is in a vertical state, bend the elastic steel belt 7 at the edge of the satellite assembly, connect the elastic steel belt 7 to the second steel belt fixing seat 12 through the fixing rope 13, and then bend the end of the elastic steel belt 7 to make the end of the elastic steel belt 7 in a curled state, and the assembly is completed;

[0063] The release process of this embodiment is as follows: the hot knife 14 is energized, the hot knife 14 melts the fixing rope 13, the elastic steel belt 7 begins to curl and retract under the triggering of the curling part at the end, the recovery rod loses the fixation of the elastic steel belt 7, and rotates outward under the action of the recovery torsion spring 10 until all the elastic steel belts 7 are completely curled and retracted, and the recovery rod is in contact with the surface of the carrier adapter 4, and the release is completed.

[0064] The present embodiment will be described in detail below with reference to the accompanying drawings:

[0065] like Figure 1 As shown, a reinforcement mechanism applied to a stacked flat-panel satellite includes two first reinforcement mechanisms 1 and two second reinforcement mechanisms 2. The first reinforcement mechanisms 1 and the second reinforcement mechanisms 2 are alternately arranged around the outside of the satellite assembly.

[0066] like Figure 1 and Figure 3 As shown, the first reinforcing mechanism 1 includes a first recovery rod 5, a first steel belt fixing seat 6 and an elastic steel belt 7. A plurality of first steel belt fixing seats 6 are axially spaced apart on the first recovery rod 5, and two elastic steel belts 7 are respectively connected to both sides of each first steel belt fixing seat 6.

[0067] like Figure 4 As shown, the first recovery rod 5 is made of a square tube and is provided with a mounting through hole for mounting the first steel belt fixing seat 6 .

[0068] like Figure 5As shown, the first steel belt fixing seat 6 includes a first recovery square groove 18 and a first steel belt fixing arm 19. The first recovery square groove 18 is sleeved on the first recovery rod 5. The number of the first steel belt fixing arms 19 is four. The four first steel belt fixing arms 19 are symmetrically arranged in pairs on both sides of the first recovery square groove 18. There is an angle between the two first steel belt fixing arms 19 on the same side. One end of the elastic steel belt 7 is connected to the first steel belt fixing arm 19.

[0069] The elastic steel strip 7 is a processed elastic memory steel sheet, and its principle is the same as that of the "slap ring". The elastic steel strip 7 is a thin and thin sheet structure with shape memory function, including straightening, curling and arbitrary point bending states. In the straight state, the cross section is arched, in the curled state, the cross section is rectangular, in the arbitrary point bending state, the cross section at the bending point is rectangular, and the rest of the cross section is arched. Figure 6 As shown, the elastic steel belt 7 curls and contracts in a natural state, and its cross section is rectangular; Figure 7 As shown, when an external force is applied to straighten it, its cross section is arched, and the arched structure can support the entire elastic steel belt 7 to maintain a straight effect and be in a temporary stable state; Figure 8 As shown, when an external force is applied to the curling direction of the elastic steel strip 7 to destroy the arch structure, the elastic steel strip 7 starts to curl and gather from that point, and gradually completes the curling and gathering of the entire elastic steel strip 7; when an external force is applied to the reverse curling direction of the elastic steel strip 7, the arch structure can also be destroyed and the steel strip can be bent, but the curling of the entire steel strip will not be caused. Figure 7 As shown, the two ends of the elastic steel belt 7 are respectively provided with a mounting hole for connecting with the first steel belt fixing arm 19 and a mounting hole for connecting with the fixing rope 13.

[0070] like Fig. 9 As shown, the recovery fixed seat 8 includes a mounting lug 21, a fixed rear wall 22 and a fixed side wall 23. The number of the fixed side walls 23 is two, and the two fixed side walls 23 are connected to both sides of the fixed rear wall 22. The fixed rear wall 22 is used to limit the mechanism to the inside, and the fixed side walls 23 are used to limit the two sides of the recovery rod. The bottom of the fixed rear wall 22 and the fixed side wall 23 are both provided with mounting lugs 21, and the mounting lugs 21 are connected to the carrier adapter 4. The two fixed side walls 23 are rotatably connected to the recovery rod, and the two fixed side walls 23 are both provided with a shaft hole 25. The lower part of the recovery rod is provided with a shaft through hole 17. The shaft 9 passes through the shaft hole 25, the shaft through hole 17 and the recovery torsion spring 10 and is connected to the nut.

[0071] like Fig.10As shown, the recovery torsion spring 10 includes a first torsion spring arm 26 and a second torsion spring arm 27. A torsion spring slot 24 is provided on the fixed rear wall 22. The torsion spring slot 24 is used to fix the recovery torsion spring 10. The first torsion spring arm 26 is installed in the torsion spring slot 24, and the second torsion spring arm 27 is inserted into the recovery rod for fixation. In a natural state, the angle between the first torsion spring arm 26 and the second torsion spring arm 27 is slightly greater than 90°, thereby achieving a recovery effect.

[0072] like Fig.11 and Fig.12 As shown, the second reinforcement mechanism 2 includes a second recovery rod 11, a second steel belt fixing seat 12, a fixing rope 13 and a hot knife 14. A plurality of second steel belt fixing seats 12 are arranged on the second recovery rod 11 at intervals along the axial direction. The first steel belt fixing seat 6 and the second steel belt fixing seat 12 are alternately arranged in the vertical direction. One end of the elastic steel belt 7 is connected to the first steel belt fixing seat 6, and the other end is connected to the second steel belt fixing seat 12 through the fixing rope 13. The two adjacent elastic steel belts 7 form a spatial triangular structure with the recovery rod. A hot knife 14 is arranged on the second steel belt fixing seat 12. The hot knife 14 fits on both sides of the fixing rope 13 to ensure successful melting.

[0073] like Fig.13 As shown, the second recovery rod 11 is made of a square tube and is provided with a mounting through hole for mounting the second steel belt fixing seat 12 .

[0074] like Fig.14 As shown, the second steel belt fixing seat 12 includes a second recovery square groove 28 and a second steel belt fixing arm 29, the second recovery square groove 28 is a square tube structure, the second recovery square groove 28 is sleeved on the second recovery rod 11, the number of the second steel belt fixing arms 29 is two, and the two second steel belt fixing arms 29 are symmetrically arranged on both sides of the second recovery square groove 28, and the elastic steel belt 7 is provided with a row of first fixing rope holes 20 arranged at equal intervals at the connection end with the second steel belt fixing seat 12, and any hole position can be selected from the arm for fixing according to the required length of the elastic steel belt 7, and the upper and lower parts of the second steel belt fixing arm 29 are respectively provided with second fixing rope holes 31, the fixing rope 13 passes through the first fixing rope hole 20 and the second fixing rope hole 31 and is tied to complete the fixation of the elastic steel belt 7 on one side of the second reinforcement mechanism 2.

[0075] A hot knife wire hole 30 is provided on the side of the second recovery square groove 28, and a hot knife fixing groove 32 and a fixing rope groove 33 are provided on the second steel belt fixing arm 29. The fixing rope groove 33 is embedded with the tightened fixing rope 13, and the hot knife 14 is installed in the hot knife fixing groove 32. The wire of the hot knife 14 passes through the hot knife wire hole 30 and is led into the second recovery square groove 28.

[0076] like Fig.21 and Fig. 22 As shown, the satellite assembly includes a plurality of flat-panel satellites 3, which are stacked and installed along the axial direction. The flat-panel satellite 3 includes a satellite body 15 and stacking columns 16, and the number of the stacking columns 16 is four, and the four stacking columns 16 are respectively connected to the four corners of the star body 15.

[0077] The specific assembly process of this embodiment is as follows:

[0078] like Fig.15 As shown, all the first steel belt fixing seats 6 are mounted on the first recovery rod 5 by screws and nuts. Fig.16 As shown, the first torsion spring arm 26 of the recovery torsion spring 10 is inserted into the torsion spring groove 24 of the recovery fixing seat 8, and the second torsion spring arm 27 of the recovery torsion spring 10 is inserted into the square groove of the first recovery rod 5, and then the shaft 9 is passed through the shaft hole 25, the shaft through hole 17 and the recovery torsion spring 10 and connected with the nut. Fig.17 As shown, all the elastic steel belts 7 are bent to be in a straight state, and the elastic steel belts 7 are fixed to the first steel belt fixing arm 19 of the first steel belt fixing seat 6 to complete the assembly of the first reinforcement mechanism 1.

[0079] like Fig.18 As shown, all the second steel belt fixing seats 12 are installed on the second recovery rod 11 by screws and nuts, as shown in FIG. Fig.19 As shown, the first torsion spring arm 26 of the recovery torsion spring 10 is inserted into the torsion spring groove 24 of the recovery fixing seat 8, and the second torsion spring arm 27 of the recovery torsion spring 10 is inserted into the square groove of the second recovery rod 11, and then the shaft 9 is passed through the shaft hole 25, the shaft through hole 17 and the recovery torsion spring 10 and connected with the nut. Fig. 20 As shown, the hot knife 14 is installed in the hot knife fixing groove 32 of the second steel belt fixing seat 12, and then the wire of the hot knife 14 is led through the hot knife wire hole 30 to the second recovery square groove 28, and then led along the square groove of the second recovery square groove 28 to the bottom of the reinforcement mechanism, and connected to the controller set at the bottom of the reinforcement mechanism to complete the assembly of the second reinforcement mechanism 2.

[0080] like Fig.21 and Fig. 22 As shown, four stacking columns 16 are fixed to the four corners of the outer side of the satellite body 15 by standard parts to complete the assembly of the flat-panel satellite 3. Multiple flat-panel satellites 3 are stacked and installed on the surface of the carrier adapter 4 to form a satellite assembly.

[0081] like Fig.23 As shown, two first reinforcing mechanisms 1 and two second reinforcing mechanisms 2 are alternately arranged around the outside of the satellite assembly, the recovery fixing seat 8 is installed on the surface of the carrier adapter 4, and then the first reinforcing mechanism 1 and the second reinforcing mechanism 2 are rotated inward around the rotating shaft 9 until each recovery rod is in a vertical state.

[0082] like Fig.24 As shown, the elastic steel belt 7 is bent at the edge of the satellite assembly, and the bent elastic steel belt 7 passes around the stacking column 16. Then, the elastic steel belt 7 is connected to the second steel belt fixing arm 29 of the second steel belt fixing seat 12 through the fixing rope 13. After the fixing is completed, the end of the elastic steel belt 7 is bent to make the end of the elastic steel belt 7 in a curled state, which serves as a trigger point for curling and retracting a single elastic steel belt 7. Repeat the above operation to complete the fixing of all elastic steel belts 7, and the assembly is completed. The reinforcing mechanism after the assembly is as shown in FIG. Fig.25 and Fig.26 shown.

[0083] In this embodiment, during the launch phase and the mechanical test phase of the satellite assembly, the strengthening mechanism can effectively improve the mechanical properties of the assembly. The principle is:

[0084] 1. The elastic steel belts 7 are connected end to end to form a mesh envelope, which wraps each stacked column 16 inside, so that each independent stacked column 16 becomes a whole, thereby reducing the cantilever beam effect of the independent stacked column 16.

[0085] 2. Two adjacent elastic steel strips 7 and the recovery rod form a spatial triangle, which improves the stability of the local structure, thereby suppressing the pulling of the overall structure by the lateral swing of any stacked column 16, and further improving the strengthening effect of the structural rigidity and strength.

[0086] 3. When the elastic steel belt 7 is in a straightened state, its cross section is arched, and it has strong mechanical resistance, which can also improve the mechanical properties of the satellite assembly.

[0087] 4. Since the elastic steel belts 7 are connected end to end to form a spatial network structure, the tension and pressure are directly transmitted or balanced through the recovery fixing seat 8 in the middle, avoiding excessive shear force acting on the recovery rod, so the recovery rod itself does not need too much strength and rigidity.

[0088] After being carried into the predetermined orbit, the strengthening mechanism is released in advance before the flat-panel satellite 3 is released. The specific release process of this embodiment is as follows: Fig. 27 As shown, each hot knife 14 is powered on, the hot knife 14 melts the fixing rope 13, the elastic steel belt 7 starts to curl and close under the trigger of the end curling part, the first recovery rod 5 and the second recovery rod 11 lose the fixation of the elastic steel belt 7, and rotate outward along the rotating shaft 9 under the action of the recovery torsion spring 10. Fig.28 As shown, until all the elastic steel bands 7 are completely curled and retracted, the recovery rod is in contact with the surface of the carrier adapter 4, and the release is completed. After that, the flat-panel satellite 3 can be released and separated, and the strengthening mechanism has no effect on the separation of the flat-panel satellite 3.

[0089] The embodiments of the present invention disclosed above are only used to help illustrate the present invention. The embodiments do not describe all the details in detail, nor do they limit the invention to the specific implementation methods 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 reinforcement mechanism for a stacked flat-panel satellite, characterized in that: The invention comprises a first reinforcing mechanism (1) and a second reinforcing mechanism (2), wherein the first reinforcing mechanism (1) and the second reinforcing mechanism (2) are alternately arranged around the outside of the satellite assembly, wherein the first reinforcing mechanism (1) and the second reinforcing mechanism (2) both comprise a recovery rod and a steel belt fixing seat, wherein the recovery rod is divided into a first recovery rod (5) and a second recovery rod (11), wherein the steel belt fixing seat is divided into a first steel belt fixing seat (6) and a second steel belt fixing seat (12), wherein the first reinforcing mechanism (1) comprises a first recovery rod (5), a first steel belt fixing seat (6) and an elastic steel belt (7), wherein a plurality of first steel belt fixing seats (6) are arranged at intervals along the axial direction on the first recovery rod (5), wherein two elastic steel belts (7) are respectively connected to both sides of each first steel belt fixing seat (6), wherein the elastic steel belt (7) is an elongated thin sheet structure and has a shape memory function, wherein the elastic steel belt (7) comprises a straightened state, a curled state and an arbitrary point bending state, wherein the cross section is an arch in the straightened state, a rectangular in the curled state, and a rectangular in the bending state, and the rest of the cross section is an arc in the bending state. The partial cross section is arched, the second reinforcing mechanism (2) comprises a second recovery rod (11), a second steel belt fixing seat (12), a fixing rope (13) and a hot knife (14), a plurality of second steel belt fixing seats (12) are arranged on the second recovery rod (11) at intervals along the axial direction, the first steel belt fixing seat (6) and the second steel belt fixing seat (12) are arranged alternately in the vertical direction, one end of the elastic steel belt (7) is connected to the first steel belt fixing seat (6), and the other end is connected to the second steel belt fixing seat (12) through the fixing rope (13). On the fixing seat (12), the end of the elastic steel belt (7) is in a curled state, and two adjacent elastic steel belts (7) form a spatial triangular structure with the recovery rod. A hot knife (14) is arranged on the second steel belt fixing seat (12), and the hot knife (14) is in contact with both sides of the fixing rope (13). The lower end of the recovery rod is rotatably connected to the recovery fixing seat (8), and a recovery torsion spring (10) is arranged at the connection between the recovery rod and the recovery fixing seat (8). The recovery fixing seat (8) is connected to the transport adapter (4).

2. The reinforcement mechanism for stacked flat-panel satellite according to claim 1, characterized in that: The first steel belt fixing seat (6) comprises a first recovery square groove (18) and a first steel belt fixing arm (19); the first recovery square groove (18) is a square tube structure; the first recovery square groove (18) is sleeved on the first recovery rod (5); the number of the first steel belt fixing arms (19) is four; the four first steel belt fixing arms (19) are symmetrically arranged in pairs on both sides of the first recovery square groove (18); an angle exists between the two first steel belt fixing arms (19) on the same side; one end of the elastic steel belt (7) is connected to the first steel belt fixing arm (19).

3. The reinforcement mechanism for stacked flat-panel satellite according to claim 1, characterized in that: The second steel belt fixing seat (12) comprises a second recovery square groove (28) and a second steel belt fixing arm (29), the second recovery square groove (28) is a square tube structure, the second recovery square groove (28) is sleeved on the second recovery rod (11), there are two second steel belt fixing arms (29), the two second steel belt fixing arms (29) are symmetrically arranged on both sides of the second recovery square groove (28), the elastic steel belt (7) is provided with a row of first fixing rope holes (20) arranged at equal intervals at the connection end with the second steel belt fixing seat (12), the upper part and the lower part of the second steel belt fixing arm (29) are respectively provided with second fixing rope holes (31), the fixing rope (13) passes through the first fixing rope hole (20) and the second fixing rope hole (31) and is fastened.

4. The reinforcement mechanism for stacked flat-panel satellite according to claim 3, characterized in that: A hot knife wire hole (30) is provided on the side of the second recovery square groove (28); a hot knife fixing groove (32) and a fixing rope groove (33) are provided on the second steel belt fixing arm (29); a tightened fixing rope (13) is embedded in the fixing rope groove (33); the hot knife (14) is installed in the hot knife fixing groove (32); and a wire of the hot knife (14) passes through the hot knife wire hole (30) and is led into the second recovery square groove (28).

5. The reinforcement mechanism for stacked flat-panel satellite according to claim 1, characterized in that: The recovery fixing seat (8) comprises a mounting lug (21), a fixed rear wall (22) and a fixed side wall (23), wherein the number of the fixed side walls (23) is two, the two fixed side walls (23) are connected to the two sides of the fixed rear wall (22), the two fixed side walls (23) are rotatably connected to the recovery rod, and the bottoms of the fixed rear wall (22) and the fixed side walls (23) are both provided with mounting lugs (21), and the mounting lugs (21) are connected to the carrying adapter (4).

6. The reinforcement mechanism for stacked flat-panel satellite according to claim 5, characterized in that: The recovery torsion spring (10) comprises a first torsion spring arm (26) and a second torsion spring arm (27); a torsion spring slot (24) is provided on the fixed rear wall (22); the first torsion spring arm (26) is installed in the torsion spring slot (24); and the second torsion spring arm (27) is installed in the recovery rod.

7. The reinforcement mechanism for stacked flat-panel satellite according to claim 6, characterized in that: The two fixed side walls (23) are each provided with a shaft hole (25), the lower portion of the recovery rod is provided with a shaft through hole (17), the shaft (9) passes through the shaft hole (25), the shaft through hole (17) and the recovery torsion spring (10) and is then connected to a nut.

8. The reinforcement mechanism for stacked flat-panel satellite according to claim 1, characterized in that: The satellite assembly comprises a plurality of flat-panel satellites (3), and the plurality of flat-panel satellites (3) are stacked and installed along the axial direction.

9. The reinforcement mechanism for stacked flat-panel satellite according to claim 8, characterized in that: The flat-panel satellite (3) comprises a satellite body (15) and stacking columns (16). The number of the stacking columns (16) is four, and the four stacking columns (16) are respectively connected to the four corners of the satellite body (15).

10. A method for using the reinforcement mechanism of a stacked flat-panel satellite as claimed in claim 1, characterized in that: The method of use includes an assembly process and a release process; The assembly process is as follows: the first steel belt fixing seat (6) is installed on the first recovery rod (5), the two sides of the recovery torsion spring (10) are respectively connected to the recovery fixing seat (8) and the first recovery rod (5), then the first recovery rod (5) is rotatably connected to the recovery fixing seat (8), the elastic steel belt (7) is bent to make it in a straight state, and the elastic steel belt (7) is fixed to the first steel belt fixing seat (6), and the assembly of the first reinforcement mechanism (1) is completed; the second steel belt fixing seat (12) is installed on the second recovery rod (11), the two sides of the recovery torsion spring (10) are respectively connected to the recovery fixing seat (8) and the second recovery rod (11), and then the second recovery rod (11) is connected to the recovery fixing seat (8). Rotate the connection, install the hot knife (14) on the second steel belt fixing seat (12), and complete the assembly of the second reinforcement mechanism (2); alternately arrange the first reinforcement mechanism (1) and the second reinforcement mechanism (2) around the outside of the satellite assembly, install the recovery fixing seat (8) on the surface of the carrier adapter (4), rotate the first reinforcement mechanism (1) and the second reinforcement mechanism (2) inward until each recovery rod is in a vertical state, bend the elastic steel belt (7) to make it bend at the edge of the satellite assembly, connect the elastic steel belt (7) to the second steel belt fixing seat (12) through the fixing rope (13), and then bend the end of the elastic steel belt (7) to make the end of the elastic steel belt (7) in a curled state, and the assembly is completed; The release process is as follows: the hot knife (14) is energized, the hot knife (14) melts the fixing rope (13), the elastic steel belt (7) starts to curl and retract under the triggering of the curling part at the end, the recovery rod loses the fixation of the elastic steel belt (7), and rotates outward under the action of the recovery torsion spring (10), until all the elastic steel belts (7) are completely curled and retracted, and the recovery rod is in contact with the surface of the carrier adapter (4), and the release is completed.

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