A compression release device for stacked flat-panel satellite and a method of using the same

Abstract

The present invention proposes a compression and release device for a stacked flat-panel satellite and a method of using the same, and belongs to the field of satellite launch technology. The invention solves the problem that the compression and release device of a stacked flat-panel satellite cannot meet the demand. The invention comprises four spiral unlocking compression and release mechanisms, and the four spiral unlocking compression and release mechanisms are all arranged on a carrier adapter. The four spiral unlocking compression and release mechanisms are respectively connected to the outer side of the satellite body, and each spiral unlocking compression and release mechanism comprises a stacking column, a release screw and a drive motor. The stacking column comprises a plurality of middle stacking columns, a top stacking column and a bottom stacking column. The plurality of middle stacking columns are arranged in sequence along the axial direction, and a top stacking column is arranged at the upper end of the middle stacking column located at the top, and a bottom stacking column is arranged at the lower end of the middle stacking column located at the bottom, and the bottom stacking column is connected to the carrier adapter. The invention is mainly used for the compression and release of stacked flat-panel satellites.

Description

Technical Field

[0001] The invention belongs to the technical field of satellite launch, and in particular relates to a compression and release device for 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. Stacked flat-panel satellites have become a solution to meet the requirements of low-orbit communication constellations. Their advantages are: First, flat-panel satellites minimize the size and weight of the entire satellite while ensuring that the size of the installation surface meets the payload requirements; second, flat-panel satellites can achieve multiple satellite launches with one rocket through stacking, which significantly improves the transportation efficiency and thus reduces the launch cost.

[0003] The compression and release device is the key to the stacking and on-orbit release of flat-panel satellites. The main functions of the compression and release device are: 1. To realize the compression and unlocking release of satellite stacking; 2. To provide the interface between the multi-satellite assembly and the carrier installation to ensure the connection strength and rigidity; 3. To provide the main load-bearing structure of the multi-satellite assembly to withstand various dynamic and static loads during the assembly launch process to ensure rigidity and strength.

[0004] There are two types of stacked flat-panel satellite compression and release devices currently in use, namely, a one-by-one unlocking and releasing type and a one-time unlocking and releasing type, but both existing methods have defects.

[0005] The defects of the one-by-one unlocking and releasing type include: First, each satellite needs to have a separate unlocking signal, so the demand for the electrical interface resources of the carrier is large, and the pressure on the information flow design is increased. Second, each satellite in the one-by-one unlocking and releasing type requires a complete set of separation unlocking devices. The use of pyrotechnics or separation mechanisms in each set of unlocking devices will increase the transportation cost and ground test cost. Third, compared with traditional multi-satellite distributors, stacked flat-panel satellites do not have structures such as central load-bearing cylinders that run through the upper and lower parts. It is difficult to find a fixed position for the unlocking signal cable, and the cable routing is difficult; Fourth, compression and unlocking and releasing are independent mechanisms, which increases the complexity of the mechanism design and the development cost, and multiple mechanisms will reduce the reliability of compression, unlocking and releasing.

[0006] In comparison, the one-time unlocking and release method uses a one-time unlocking and separation of all satellites at the same time, which avoids the above problems, but also introduces new defects, including: First, the satellites are separated at the same time, and the stacked satellites may be at risk of colliding with each other after separation; Second, in order to meet the stiffness of the stacked assembly, the pre-tightening force of the compression release device is often large, and a one-time unlocking and release may produce a large impact, affecting the satellite. Summary of the invention

[0007] In view of this, the present invention aims to provide a compression and release device for a stacked flat-panel satellite and a method of using the same, so as to solve the problem that the compression and release device of the stacked flat-panel satellite cannot meet the demand.

[0008] To achieve the above-mentioned purpose, the present invention adopts the following technical scheme: a compression and release device for a stacked flat-panel satellite, which includes four spiral unlocking compression and release mechanisms, which are all arranged on a carrier adapter, and the four spiral unlocking compression and release mechanisms are respectively connected to the outer side of the satellite body, and each spiral unlocking compression and release mechanism includes a stacking column, a release screw and a drive motor, and the stacking column includes a plurality of middle stacking columns, a top stacking column and a bottom stacking column, and the plurality of middle stacking columns are arranged in sequence along the axial direction, and a top stacking column is arranged at the upper end of the middle stacking column located at the top, and a bottom stacking column is arranged at the upper end of the middle stacking column located at the top. A bottom stacking column is arranged at the lower end of the lowest middle stacking column, and the bottom stacking column is connected to the carrying adapter. The outer sides of each middle stacking column and the top stacking column are connected to the star body. A slide groove is arranged axially inside the middle stacking column, and the slide grooves are respectively a clearance slide groove, an interference slide groove and a limit groove along the axial direction from bottom to top. A release seat is slidably connected in the clearance slide groove, and a top release seat is connected to the top of the top stacking column. A driving motor is arranged inside the bottom stacking column, and the output end of the driving motor is connected to a release screw, and the release screw is screwed to the release seat and the top release seat.

[0009] Furthermore, satellite brackets are provided on the outer sides of the middle stacking column and the top stacking column, and the satellite brackets are connected to the star body. Two cylindrical pins are provided on the satellite bracket, and the two cylindrical pins are positioned and connected to the star body.

[0010] Furthermore, the upper parts of the middle stacking columns and the bottom stacking columns are provided with docking inner edges, and the lower parts of the middle stacking columns and the top stacking columns are provided with docking outer edges. The multiple middle stacking columns, the middle stacking columns and the bottom stacking columns, and the middle stacking columns and the top stacking columns are connected by the nested cooperation of the docking inner edges and the docking outer edges.

[0011] Furthermore, the driving motor is a brake motor, the output end of the driving motor is a rotating flange, the rotating flange is connected to the release screw through a motor clamp, the number of the motor clamps is two, and the two motor clamps are butt-connected.

[0012] Furthermore, the release screw is provided with an external thread, the release seat and the top release seat are provided with internal threads, the internal threads are threadedly matched with the external threads, a guide structure is provided at the top of the release screw, a fixing pin is provided at the bottom, a pin hole is provided on the motor clamp, and the fixing pin is inserted into the pin hole.

[0013] Furthermore, the motor clamp includes a connected screw end fixing sleeve and a motor end fixing flange, the pin hole is opened on the screw end fixing sleeve, the motor end fixing flange is connected to the rotating flange, the screw end fixing sleeve is provided with a mounting ear, and the mounting ears on the two motor clamps are butt-connected.

[0014] Furthermore, four sliding blocks are evenly distributed along the circumferential direction on the outer side of the release seat, four sliding grooves are evenly distributed along the circumferential direction in the middle stacking column, and the four sliding blocks are respectively arranged in the four sliding grooves.

[0015] Furthermore, the top release seat includes a fixing ring and a center body, the fixing ring and the center body are connected by a plurality of reinforcing ribs evenly distributed along the circumference, a fixing platform is arranged on the top of the top stacking column, and the fixing ring is connected to the fixing platform.

[0016] Furthermore, the driving motor is provided with a plurality of fixed ears evenly distributed along the circumference, and the bottom stacking column is provided with a plurality of bracket ears evenly distributed along the circumference, and the fixed ears and the bracket ears are both connected to the carrying adapter.

[0017] The present invention also provides a method for using a compression release device for a stacked flat-panel satellite, the method comprising an assembly process and a release process;

[0018] The assembly process includes the following steps:

[0019] Step 1: Install the four bottom stacking columns and the drive motor concentrically on the carrier adapter set position;

[0020] Step 2: Connect the release screw to the output end of the drive motor;

[0021] Step 3: Install the middle stacking columns and the top stacking columns with the star body, wherein the outer side of the star body at the top is connected to four top stacking columns, and the outer side of the remaining star bodies is connected to four middle stacking columns;

[0022] Step 4: Install the star body at the bottom layer, screw the release seat onto the release screw through threads, so that the release seat is located at the bottom end of the release screw, and pass the middle stacking column through the release screw by hoisting, so that the middle stacking column is pre-fixed on the bottom stacking column, and the release seat is embedded in the gap slide groove, and the top of the release seat is away from the limit groove;

[0023] Step 5: Install the star body on the upper layer, screw the release seat onto the release screw through threads, make the distance between adjacent release seats equal to the sum of the height of the middle stacking column and the release safety height, pass the middle stacking column through the release screw by hoisting, pre-fix the middle stacking column on the middle stacking column below, embed the release seat into the gap slide groove, and keep the top of the release seat away from the limit groove;

[0024] Step 6: Repeat step 5 to complete the installation of the remaining star bodies except the top star body;

[0025] Step 7: Pre-fix the top stacking column of the topmost star body on the middle stacking column below through the release screw, screw the top release seat onto the release screw, tighten the top release seat onto the top stacking column, and connect the top release seat to the top stacking column through the connector;

[0026] Step 8: Power on the four drive motors synchronously in the reverse direction to compress all the stacking columns. When the compression force reaches the set value, stop powering on, lock the drive motors, and complete the assembly.

[0027] The release process is: the four drive motors are energized in the forward direction synchronously, the drive motors drive the release screws to rotate, the release screws drive the release seat and the top release seat to move away from the carrier adapter, and the release and pushing away of all the star bodies are completed from top to bottom.

[0028] Compared with the prior art, the beneficial effects of the present invention are as follows: the present invention provides a compression and release device for stacked flat-panel satellites and a method of using the same, which, under the premise of realizing a simplified design in which a set of mechanisms can be used for both compression and separation and release, meets the needs of releasing and separating satellites one by one, thereby avoiding collisions between satellites during the separation process; in addition, it can also achieve the effects of reducing separation shock and controlling the separation timing.

[0029] The specific advantages are as follows:

[0030] (1) The present invention can be applied to the stacking of flat-panel satellites, thereby improving the utilization rate of the transport space and the utilization rate of the transport capacity.

[0031] (2) The present invention adopts a simplified mechanism design concept. A set of devices can be compressed and separated for release, avoiding the waste of electrical interface resources caused by providing a separate unlocking signal to a single satellite, and also solving the layout problem of complex unlocking signal cables for stacked satellites.

[0032] (3) The present invention adopts a method of separating satellites one by one. After the previous satellite has moved away from the satellite cluster, the next satellite is separated and unlocked, thereby avoiding collision between adjacent released satellites during the separation process.

[0033] (4) The present invention completes the compression and release of all satellites through the release screw and the release seat, avoiding the use of any pyrotechnics or unlockers, thereby reducing the transportation cost and ground test cost caused by unlocking.

[0034] (5) The present invention can control the release and separation of all satellites throughout the entire process, and the separation strategy can be manually intervened in special circumstances.

[0035] (6) The present invention releases and separates all satellites gently, reducing the impact of separation shock on the satellites.

[0036] (7) The present invention can adjust the release rate of the satellite by adjusting the thread pitch of the release screw and the release seat or adjusting the rotation speed of the drive motor, and the design is flexible and changeable.

[0037] (8) The present invention can be unlocked repeatedly, 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, and the device has strong adaptability. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] 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:

[0039] Figure 1 It is a schematic diagram of the three-dimensional structure of a compression and release device for a stacked flat-panel satellite according to the present invention;

[0040] Figure 2 It is a schematic cross-sectional structure diagram of a compression and release device for a stacked flat-panel satellite according to the present invention;

[0041] Figure 3 This is a schematic diagram of the three-dimensional structure of the middle stacked column of the present invention;

[0042] Figure 4 This is a schematic diagram of the cross-sectional structure of the middle stacked column of the present invention;

[0043] Figure 5 This is a schematic diagram of the three-dimensional structure of the top stacked column of the present invention;

[0044] Figure 6 This is a schematic diagram of the cross-sectional structure of the top stacked column of the present invention;

[0045] Figure 7 This is a schematic diagram of the three-dimensional structure of the bottom stacked column according to the present invention;

[0046] Figure 8 This is a schematic diagram of the release screw structure of the present invention;

[0047] Fig. 9 It is a schematic diagram of the release seat structure of the present invention;

[0048] Fig.10 It is a schematic diagram of the structure of the top release seat of the present invention;

[0049] Fig.11 This is a schematic diagram of the structure of the driving motor according to the present invention;

[0050] Fig.12 This is a schematic diagram of the motor clamp structure of the present invention;

[0051] Fig.13 The present invention is a schematic diagram of the assembly process of a compression release device for a stacked flat-panel satellite. Figure 1 ;

[0052] Fig.14 The present invention is a schematic diagram of the assembly process of a compression release device for a stacked flat-panel satellite. Figure 2 ;

[0053] Fig.15 The present invention is a schematic diagram of the assembly process of a compression release device for a stacked flat-panel satellite. Figure 3 ;

[0054] Fig.16 The present invention is a schematic diagram of the assembly process of a compression release device for a stacked flat-panel satellite. Figure 4 ;

[0055] Fig.17 The present invention is a schematic diagram of the assembly process of a compression release device for a stacked flat-panel satellite. Figure 5 ;

[0056] Fig.18 The present invention is a schematic diagram of the assembly process of a compression release device for a stacked flat-panel satellite. Figure 6 ;

[0057] Fig.19 The present invention is a schematic diagram of the assembly process of a compression release device for a stacked flat-panel satellite. Figure 7 ;

[0058] Fig. 20 The present invention is a schematic diagram of the assembly process of a compression release device for a stacked flat-panel satellite. Figure 8 ;

[0059] Fig.21The present invention is a schematic diagram of the assembly process of a compression release device for a stacked flat-panel satellite. Figure 9 ;

[0060] Fig. 22 This is a schematic diagram of the assembly of a compression and release device for a stacked flat-panel satellite according to the present invention;

[0061] Fig.23 Schematic diagram of the release process of a compression release device for a stacked flat-panel satellite according to the present invention Figure 1 ;

[0062] Fig.24 Schematic diagram of the release process of a compression release device for a stacked flat-panel satellite according to the present invention Figure 2 ;

[0063] Fig.25 Schematic diagram of the release process of a compression release device for a stacked flat-panel satellite according to the present invention Figure 3 ;

[0064] Fig.26 Schematic diagram of the release process of a compression release device for a stacked flat-panel satellite according to the present invention Figure 4 .

[0065] In the figure:

[0066] 1-middle stacking column, 2-top stacking column, 3-bottom stacking column, 4-release screw, 5-release seat, 6-top release seat, 7-drive motor, 8-motor clamp, 9-star body, 10-carrying adapter, 11-satellite bracket, 12-cylindrical pin, 13-slide, 14-clearance slide, 15-interference slide, 16-limiting groove, 17-butt inner edge, 18-butt outer edge, 19-fixed platform, 20-bracket ear, 21-external thread, 22-guide structure, 23-fixing pin, 24-internal thread, 25-slider, 26-fixing ring, 27-reinforcement rib, 28-rotating flange, 29-fixing ear, 30-screw end fixing sleeve, 31-pin hole, 32-mounting ear, 33-motor end fixing flange. DETAILED DESCRIPTION

[0067] 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.

[0068] See also Figure 1-26The present embodiment describes a compression and release device for a stacked flat-panel satellite, which includes four spiral unlocking compression and release mechanisms, which are all arranged on a carrier adapter 10, and are respectively connected to the outer side of a satellite body 9, each of which includes a stacking column, a release screw 4, and a drive motor 7, wherein the stacking column includes a plurality of middle stacking columns 1, a top stacking column 2, and a bottom stacking column 3, wherein the plurality of middle stacking columns 1 are sequentially arranged along the axial direction, wherein the top stacking column 2 is arranged at the upper end of the middle stacking column 1 located at the top, and the bottom stacking column 3 is arranged at the lower end of the middle stacking column 1 located at the bottom. The bottom stacking column 3 is connected to the carrying adapter 10, and the outer sides of each middle stacking column 1 and the top stacking column 2 are connected to the star body 9. The middle stacking column 1 is provided with a slide groove 13 along the axial direction, and the slide groove 13 is a clearance slide groove 14, an interference slide groove 15 and a limit groove 16 from bottom to top along the axial direction. A release seat 5 is slidably connected in the clearance slide groove 14, and a top release seat 6 is connected to the top of the top stacking column 2. A driving motor 7 is provided inside the bottom stacking column 3, and the output end of the driving motor 7 is connected to the release screw 4, and the release screw 4 is screwed to the release seat 5 and the top release seat 6.

[0069] The assembly process of this embodiment includes the following steps:

[0070] Step 1: Concentrically install four bottom stacking columns 3 and drive motor 7 at the set position of the carrier adapter 10;

[0071] Step 2: Connect the release screw 4 to the output end of the drive motor 7;

[0072] Step 3: Install the middle stacking column 1 and the top stacking column 2 with the star body 9, wherein the outer side of the star body 9 at the top is connected to four top stacking columns 2, and the outer side of the remaining star bodies 9 is connected to four middle stacking columns 1;

[0073] Step 4: screw the release seat 5 used by the lowest star body 9 onto the release screw 4 through a thread, the release seat 5 used by the lowest star body 9 is located at the bottom end of the release screw 4, and the middle stacking column 1 of the star body 9 is pre-fixed on the bottom stacking column 3 through the release screw 4 by hoisting, and the release seat 5 is embedded in the gap slide groove 14, and the top of the release seat 5 is away from the limit groove 16;

[0074] Step 5: screw the release seat 5 used by the upper star body 9 onto the release screw 4 through a thread, the distance between the release seat 5 used by the upper star body 9 and the release seat 5 of the lower layer is equal to the sum of the height of the middle stacking column 1 and the release safety height, and pre-fix the middle stacking column 1 of the star body 9 on the lower middle stacking column 1 through the release screw 4 by hoisting, and embed the release seat 5 into the gap slide groove 14, and the top of the release seat 5 is away from the limit groove 16;

[0075] Step 6: Repeat step 5 to complete the installation of the remaining star bodies 9 except the top star body 9;

[0076] Step 7: Pre-fix the top stacking column 2 of the topmost star body 9 on the middle stacking column 1 below through the release screw 4, screw the top release seat 6 onto the release screw 4, tighten the top release seat 6 onto the top stacking column 2, and connect the top release seat 6 to the top stacking column 2 through a connector;

[0077] Step 8: The four drive motors 7 are energized in the reverse direction synchronously to compress all the stacking columns. When the compression force reaches the set value, the power supply is stopped, the drive motors 7 are locked, and the assembly is completed.

[0078] The release process of this embodiment is: the four drive motors 7 are energized in the forward direction synchronously, the drive motors 7 drive the release screw 4 to rotate, and the release screw 4 drives the release seat 5 and the top release seat 6 to move away from the carrier adapter 10, thereby completing the release and pushing away of all star bodies 9 from top to bottom.

[0079] The present embodiment will be described in detail below with reference to the accompanying drawings:

[0080] like Figure 1 and Figure 2 As shown, the spiral unlocking and clamping release mechanisms include stacking columns, a release screw 4 and a drive motor 7. The stacking columns include multiple middle stacking columns 1, top stacking columns 2 and bottom stacking columns 3. The multiple middle stacking columns 1 are arranged in sequence along the axial direction. The top stacking column 2 is arranged at the upper end of the middle stacking column 1 located at the top, and the bottom stacking column 3 is arranged at the lower end of the middle stacking column 1 located at the bottom. The bottom stacking column 3 is connected to the carrying adapter 10, and the outer sides of each middle stacking column 1 and the top stacking column 2 are connected to the star body 9.

[0081] like Figure 3 and Figure 4As shown, a satellite bracket 11 is arranged on the outside of the middle stacking column 1, and the satellite bracket 11 is connected to the star body 9. Two cylindrical pins 12 are arranged on the satellite bracket 11, and the two cylindrical pins 12 are positioned and connected with the star body 9. The two cylindrical pins 12 play the role of positioning and resisting longitudinal shear force. A satellite mounting hole is arranged on the satellite bracket 11, and the satellite mounting hole is used to directly connect with the star body 9. A slide groove 13 is arranged axially inside the middle stacking column 1. The number of the slide grooves 13 is four, and the four slide grooves 13 are evenly distributed along the inner circumference of the middle stacking column 1. The slide grooves 13 are clearance slide grooves 14, interference slide grooves 15 and limit grooves 16 from bottom to top along the axial direction. A release seat 5 is slidably connected in the clearance slide groove 14. A docking inner edge 17 is arranged on the upper part of the middle stacking column 1, and a docking outer edge 18 is arranged on the lower part of the middle stacking column 1. When multiple star bodies 9 are stacked, the docking inner edge 17 is nested with the docking outer edge 18 on another stacking column to achieve a pre-fixing effect.

[0082] like Figure 5 and Figure 6 As shown, a satellite bracket 11 is provided on the outside of the top stacking column 2, and the satellite bracket 11 is connected to the star body 9. Two cylindrical pins 12 are provided on the satellite bracket 11, and the two cylindrical pins 12 are connected to the star body 9 for positioning. The two cylindrical pins 12 play the role of positioning and resisting longitudinal shear force. A satellite mounting hole is provided on the satellite bracket 11, and the satellite mounting hole is used to directly connect with the star body 9. A fixing platform 19 is provided on the top of the top stacking column 2, and a top release seat 6 is connected to the top of the top stacking column 2 through the fixing platform 19. A docking outer edge 18 is provided at the lower part of the top stacking column 2. When multiple star bodies 9 are stacked, the docking outer edge 18 of the top stacking column 2 is nested with the docking inner edge 17 of the top middle stacking column 1 to achieve a pre-fixing effect.

[0083] like Figure 7 As shown, the bottom stacking column 3 is evenly distributed with a plurality of bracket ears 20 along the circumferential direction, and the bracket ears 20 are provided with through holes, which are mechanical interfaces for fixing the bottom stacking column 3 on the carrier adapter 10, and the bracket ears 20 are connected to the carrier adapter 10. The upper part of the bottom stacking column 3 is provided with a docking inner edge 17, and when multiple star bodies 9 are stacked, the docking inner edge 17 of the bottom stacking column 3 is nested with the docking outer edge 18 of the bottom middle stacking column 1, so as to achieve a pre-fixing effect.

[0084] like Figure 8 As shown, the release screw 4 is provided with an external thread 21 , the top of the release screw 4 is provided with a guide structure 22 , and the bottom is provided with a fixing pin 23 .

[0085] like Fig. 9As shown, the release seat 5 has an internal thread 24 and four sliders 25 uniformly distributed along the circumferential direction. The internal thread 24 and the external thread 21 have the same specifications and can be screwed together. The four sliders 25 are respectively arranged in four slide grooves 13. The sliders 25 are designed to cooperate with the slide grooves 13 of the middle stacking column 1. Among them, the slider 25 and the gap slide groove 14 are clearance fit, and the slider 25 can slide up and down along the gap slide groove 14. The slider 25 and the interference slide groove 15 are interference fit. The slider 25 slides into the interference slide groove 15 to have a fixing effect. The limit groove 16 has a limiting effect on the slider 25. After the slider 25 contacts the limit groove 16, it is locked with the middle stacking column 1 under the auxiliary effect of the interference slide groove 15, thereby pushing the middle stacking column 1 to slide upward synchronously.

[0086] like Fig.10 As shown, the top release seat 6 includes a fixing ring 26 and a center body, the center body is provided with an internal thread 24, the internal thread 24 and the external thread 21 have the same specifications and can be screwed together, the fixing ring 26 and the center body are connected by a plurality of reinforcing ribs 27 evenly distributed along the circumference, the fixing ring 26 has a countersunk hole, and the countersunk hole is a mechanical interface for fixing the fixing ring 26 and the top stacking column 2.

[0087] like Fig.11 As shown, the drive motor 7 is a DC flange motor, and the output end of the drive motor 7 is a rotating flange 28, which is a rotating part of the drive motor 7. The rotating flange 28 is connected to the release screw 4 through the motor clamp 8, and the rotating flange 28 is provided with a threaded hole for fixing the motor clamp 8. The drive motor 7 is evenly distributed with a plurality of fixing ears 29 along the circumference, and the fixing ears 29 are provided with through holes, which are the mechanical interfaces for fixing the drive motor 7 on the carrier adapter 10, and the fixing ears 29 are connected to the carrier adapter 10. The drive motor 7 can rotate in the reverse direction when reverse power is supplied.

[0088] like Fig.12 As shown, there are two motor clamps 8, and the two motor clamps 8 are butt-jointed. A pin hole 31 is provided on the motor clamp 8, and the fixing pin 23 is inserted into the pin hole 31. The motor clamp 8 includes a connected screw end fixing sleeve 30 and a motor end fixing flange 33, the pin hole 31 is provided on the screw end fixing sleeve 30, the motor end fixing flange 33 is provided with a countersunk hole, and the countersunk hole is used to connect with the rotating flange 28, and the screw end fixing sleeve 30 is provided with a mounting ear 32, and the mounting ear 32 is used for the combination of two motor clamps 8, and the mounting ears 32 on the two motor clamps 8 are butt-jointed.

[0089] In the above embodiment, the surface of the gap groove 14 of the middle stacking column 1, the external thread 21 of the release screw 4 and the surface of the column section containing the external thread 21, the internal thread 24 and the inner hole surface of the release seat 5, and the internal thread 24 and the inner hole surface of the top release seat 6 are coated with molybdenum disulfide to prevent vacuum cold welding and reduce sliding friction within the mechanism.

[0090] Taking a four-layer stacked flat-panel satellite as an example, the four-layer stacked flat-panel satellite includes four stacked satellite bodies 9, which are respectively the first satellite body, the second satellite body, the third satellite body and the fourth satellite body from bottom to top. The specific assembly process of this embodiment includes the following steps:

[0091] Step 1: Fig.13 As shown, four bottom stacking columns 3 and a drive motor 7 are concentrically mounted on a set position of a carrier adapter 10;

[0092] Step 2: If Fig.14 As shown, two motor clamps 8 are buckled with the outer side of the release screw 4 and fixed by standard parts, and then the motor clamp 8 is connected to the rotating flange 28 of the drive motor 7 to realize the connection between the release screw 4 and the output end of the drive motor 7;

[0093] Step 3: If Fig.15 As shown, the middle stacking column 1 and the top stacking column 2 are installed with the star body 9, wherein the outer side of the fourth star body is connected to four top stacking columns 2, and the outer sides of the first star body, the second star body and the third star body are respectively connected to four middle stacking columns 1;

[0094] Step 4: Fig.16 As shown, the release seat 5 used by the first star body is screwed on the release screw 4 through a thread, and the release seat 5 used by the first star body is located at the bottom end of the release screw 4. The first star body with the middle stacking column 1 installed in step 3 is installed on the bottom stacking column 3 by hoisting, so that the middle stacking column 1 of the first star body passes through the release screw 4, and the middle stacking column 1 of the first star body is stacked on the bottom stacking column 3, so that the docking inner edge 17 and the docking outer edge 18 are nested to achieve a pre-fixing effect, and the slider 25 of the release seat 5 is embedded in the gap slide groove 14, and the top of the release seat 5 is away from the limit groove 16. After installation, Fig.17 As shown;

[0095] Step 5: Fig.18As shown, the release seat 5 used by the second star body is screwed on the release screw 4 through a thread, and the distance between the release seat 5 used by the second star body and the release seat 5 used by the first star body is equal to the sum of the height of the middle stacking column 1 and the release safety height. The second star body with the middle stacking column 1 installed in step 3 is installed on the middle stacking column 1 connected to the first star body by hoisting, so that the middle stacking column 1 of the second star body passes through the release screw 4, and the middle stacking column 1 of the second star body is stacked on the middle stacking column 1 connected to the first star body, so that the docking inner edge 17 and the docking outer edge 18 are nested to achieve a pre-fixing effect, and the slider 25 of the release seat 5 is embedded in the gap slide groove 14, and the top of the release seat 5 is away from the limit groove 16;

[0096] Step 6: Fig.19 As shown, follow the process of step 5 to complete the installation of the third satellite body;

[0097] Step 7: Fig. 20 As shown, the fourth star body with the top stacking column 2 installed in step 3 is installed on the middle stacking column 1 connected to the third star body, so that the top stacking column 2 of the fourth star body passes through the release screw 4, and the top stacking column 2 of the fourth star body is stacked on the middle stacking column 1 connected to the third star body, so that the docking inner edge 17 and the docking outer edge 18 are nested to achieve a pre-fixing effect, and the top release seat 6 is screwed onto the release screw 4, so that the top release seat 6 is tightened on the top stacking column 2, and the top release seat 6 is connected to the top stacking column 2 through a connector to complete the preliminary compression of all star bodies 9;

[0098] Step 8: Fig.21 As shown, the four drive motors 7 are energized in the reverse direction synchronously to further compress all the stacking columns. When the compression force reaches the set value, the power supply is stopped, the drive motors 7 are in a locked state, and the compression assembly of the four-layer stacked flat-panel satellite is completed.

[0099] For stacked flat-panel satellites with other layers, it is only necessary to repeat step 6 before step 7 to complete the installation of the remaining satellite bodies 9 except the topmost satellite body 9.

[0100] The specific release process of this embodiment is as follows: the four drive motors 7 are energized in the forward direction synchronously, and the drive motors 7 drive the release screws 4 to rotate, and the compression release device is unlocked from the compression state. The drive motors 7 are continuously energized, and the release screws 4 drive the release seat 5 and the top release seat 6 to move away from the carrier adapter 10, such as Fig. 22 As shown, since the slider 25 of the release seat 5 is at a distance from the limiting groove 16 of the middle stacking column 1, it will not be pushed away by the release seat 5 at the first time, while the top release seat 6 is fixedly connected to the top stacking column 2, so it will be pushed away and released at the first time, as shown in FIG. Fig.23As shown; after the fourth satellite body is completely separated, it continues to move away from the satellite stacking assembly. At this time, the slider 25 of the release seat 5 of the third satellite body fits with the limiting groove 16 of the middle stacking column 1, pushes away from the third satellite body to start releasing, and the remaining satellites do not start releasing; until a safe distance is pulled between the third satellite body and the second satellite body, after which the slider 25 of the release seat 5 of the second satellite body fits with the limiting groove 16 of the middle stacking column 1, pushes away from the second satellite body to start releasing, as shown Fig.24 and Fig.25 According to this process, the drive motor 7 is continuously energized, and all the star bodies 9 are released and pushed away from top to bottom, as shown. Fig.26 shown.

[0101] In the above embodiment, after the slider 25 of each release seat 5 is fitted with the limit groove 16 of the middle stacking column 1, due to the effect of the interference groove 15, the release seat 5 is locked with the middle stacking column 1 and will not detach from the satellite. The release rate of the satellite can be adjusted by adjusting the thread pitch of the release screw 4, the release seat 5, and the top release seat 6 or adjusting the speed of the drive motor 7. When the satellite is separated, if there is a large transport disturbance, in order to avoid collision between adjacent satellites after separation, the separation timing can also be adjusted by intermittently turning off the drive motor 7 to achieve a further separation effect of the satellites one by one.

[0102] 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 compression release device for a stacked flat-panel satellite, characterized in that: It comprises four spiral unlocking, pressing and releasing mechanisms, which are all arranged on a transport adapter (10). The four spiral unlocking, pressing and releasing mechanisms are respectively connected to the outer side of a star body (9). Each spiral unlocking, pressing and releasing mechanism comprises a stacking column, a releasing screw (4) and a driving motor (7). The stacking column comprises a plurality of middle stacking columns (1), a top stacking column (2) and a bottom stacking column (3). The plurality of middle stacking columns (1) are arranged in sequence along the axial direction. The top stacking column (2) is arranged at the upper end of the middle stacking column (1) located at the top, and the bottom stacking column (3) is arranged at the lower end of the middle stacking column (1) located at the bottom. The bottom stacking column (3) is connected to the transport adapter (10). The outer sides of each middle stacking column (1) and the top stacking column (2) are connected to the star body (9). The middle stacking column (1) is provided with a A slide groove (13), wherein the slide groove (13) is a clearance slide groove (14), an interference slide groove (15) and a limit groove (16) in order from bottom to top along the axial direction; a release seat (5) is slidably connected in the clearance slide groove (14); the top of the top stacking column (2) is connected to the top release seat (6); a driving motor (7) is arranged inside the bottom stacking column (3); the output end of the driving motor (7) is connected to the release screw (4); the release screw (4) is screwedly connected to the release seat (5) and the top release seat (6); four sliders (25) are evenly distributed along the circumferential direction on the outer side of the release seat (5); four slide grooves (13) are evenly distributed along the circumferential direction in the middle stacking column (1); the four sliders (25) are respectively arranged in the four slide grooves (13); the distance between adjacent release seats (5) is equal to the sum of the height of the middle stacking column (1) and the release safety height.

2. A compression and release device for a stacked flat-panel satellite according to claim 1, characterized in that: Satellite brackets (11) are arranged on the outer sides of the middle stacking column (1) and the top stacking column (2); the satellite brackets (11) are connected to the star body (9); two cylindrical pins (12) are arranged on the satellite bracket (11); the two cylindrical pins (12) are positioned and connected to the star body (9).

3. A compression and release device for a stacked flat-panel satellite according to claim 1, characterized in that: The upper parts of the middle stacking columns (1) and the bottom stacking columns (3) are both provided with butt-jointed inner edges (17), and the lower parts of the middle stacking columns (1) and the top stacking columns (2) are both provided with butt-jointed outer edges (18). The plurality of middle stacking columns (1), the middle stacking columns (1) and the bottom stacking columns (3), and the middle stacking columns (1) and the top stacking columns (2) are connected by the nested fit of the butt-jointed inner edges (17) and the butt-jointed outer edges (18).

4. A compression and release device for a stacked flat-panel satellite according to claim 1, characterized in that: The drive motor (7) is a brake motor. The output end of the drive motor (7) is a rotating flange (28). The rotating flange (28) is connected to the release screw (4) via a motor clamp (8). There are two motor clamps (8), and the two motor clamps (8) are butt-connected.

5. A compression and release device for a stacked flat-panel satellite according to claim 4, characterized in that: The release screw (4) is provided with an external thread (21), the release seat (5) and the top release seat (6) are provided with internal threads (24), the internal threads (24) are threadedly matched with the external threads (21), the top of the release screw (4) is provided with a guide structure (22), the bottom is provided with a fixing pin (23), the motor clamp (8) is provided with a pin hole (31), and the fixing pin (23) is inserted into the pin hole (31).

6. A compression and release device for a stacked flat-panel satellite according to claim 5, characterized in that: The motor clamp (8) comprises a screw end fixing sleeve (30) and a motor end fixing flange (33) connected to each other, the pin hole (31) is provided on the screw end fixing sleeve (30), the motor end fixing flange (33) is connected to the rotating flange (28), and a mounting ear (32) is provided on the screw end fixing sleeve (30), and the mounting ears (32) on the two motor clamps (8) are butt-jointed.

7. A compression and release device for a stacked flat-panel satellite according to claim 1, characterized in that: The top release seat (6) comprises a fixing ring (26) and a central body, the fixing ring (26) and the central body are connected via a plurality of reinforcing ribs (27) uniformly distributed along the circumference, a fixing platform (19) is arranged at the top of the top stacking column (2), and the fixing ring (26) is connected to the fixing platform (19).

8. The compression and release device for a stacked flat-panel satellite according to claim 1, characterized in that: The driving motor (7) is provided with a plurality of fixed ears (29) evenly distributed along the circumference, and the bottom stacking column (3) is provided with a plurality of bracket ears (20) evenly distributed along the circumference, and both the fixed ears (29) and the bracket ears (20) are connected to the carrying adapter (10).

9. A method for using the compression release device for 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 includes the following steps: Step 1: Concentrically install four bottom stacking columns (3) and a drive motor (7) at a set position of a carrier adapter (10); Step 2: Connect the release screw (4) to the output end of the drive motor (7); Step 3: Install the middle stacking columns (1) and the top stacking columns (2) with the star body (9), wherein the outer side of the star body (9) located at the top is connected to four top stacking columns (2), and the outer sides of the remaining star bodies (9) are connected to four middle stacking columns (1); Step 4: Install the star body (9) located at the bottom layer, screw the release seat (5) onto the release screw (4) through threads, so that the release seat (5) is located at the bottom end of the release screw (4), and the middle stacking column (1) is passed through the release screw (4) by hoisting, so that the middle stacking column (1) is pre-fixed on the bottom stacking column (3), and the release seat (5) is embedded in the gap slide groove (14), and the top of the release seat (5) is away from the limit groove (16); Step 5: Install the star body (9) located on the upper layer, screw the release seat (5) onto the release screw (4) through a thread, so that the distance between adjacent release seats (5) is equal to the sum of the height of the middle stacking column (1) and the release safety height, and pass the middle stacking column (1) through the release screw (4) by hoisting, so that the middle stacking column (1) is pre-fixed on the middle stacking column (1) below, and the release seat (5) is embedded in the gap slide groove (14), and the top of the release seat (5) is away from the limit groove (16); Step 6: Repeat step 5 to complete the installation of the remaining star bodies (9) except the topmost star body (9); Step 7: Pre-fix the top stacking column (2) of the topmost star body (9) on the middle stacking column (1) below through the release screw (4), screw the top release seat (6) onto the release screw (4), tighten the top release seat (6) onto the top stacking column (2), and connect the top release seat (6) to the top stacking column (2) through a connector; Step 8: The four drive motors (7) are energized in the reverse direction synchronously to compress all the stacking columns. When the compression force reaches the set value, the power supply is stopped and the drive motors (7) are locked to complete the assembly. The release process is as follows: four drive motors (7) are energized in the forward direction synchronously, the drive motors (7) drive the release screws (4) to rotate, the release screws (4) drive the release seat (5) and the top release seat (6) to move away from the carrier adapter (10), and all the star bodies (9) are released and pushed away in sequence from top to bottom.

Images