Panel satellite pressing and releasing device and panel satellite

Abstract

The utility model provides a flat satellite compressing and releasing device and a flat satellite, and the compressing and releasing device comprises a stacking column pedestal, a stacking column and a compressing rod. The stacking column base is arranged in a supporting cabin of the rocket; the stacking columns are used for being fixedly connected with the side faces of the stacked flat satellites. The stacking columns arranged on the bottommost flat plate satellite are placed on the stacking column bases, and the stacking columns arranged on the upper flat plate satellite are sequentially placed on the stacking columns of the lower flat plate satellite; one end of the pressing rod is rotatably connected with the stacking column base; and the pressing rod swings towards the panel satellite so as to press the stacking column. According to the pressing and releasing device, reliable stacking and safe releasing of the flat satellites in the fairing can be achieved.

Description

Technical Field

[0001] This utility model relates to the field of satellites, specifically to a flat-panel satellite compression and release device and a flat-panel satellite. Background Technology

[0002] With the rapid development of commercial spaceflight and low-Earth orbit (LEO) internet satellite constellations, multi-satellite launch technology has gradually become an important method for space launches. LEO internet satellite constellation construction is characterized by large scale, numerous satellites, uniform satellite shapes, and mass production. LEO internet satellites typically adopt a modular flat-panel structure configuration, maximizing fairing space utilization through stacked multi-satellite assembly technology.

[0003] To ensure reliable stacking and release of satellites within the fairing, designing a flat-panel satellite clamping and release device is of paramount importance. Utility Model Content

[0004] The purpose of this invention is to overcome the shortcomings of the existing technology and provide a flat satellite compression and release device.

[0005] This utility model provides a flat-panel satellite clamping and release device, comprising: a stacking column base, stacking columns, and a clamping rod; the stacking column base is disposed in the support compartment of a rocket; the stacking columns are used for fixed connection to the sides of stacked flat-panel satellites; the stacking columns of the bottom-level flat-panel satellites are placed on the stacking column base, and the stacking columns of the upper-level flat-panel satellites are sequentially placed on the stacking columns of their lower-level flat-panel satellites; one end of the clamping rod is rotatably connected to the stacking column base; the clamping rod swings toward the flat-panel satellites to clamp the stacking columns.

[0006] According to one embodiment of the present invention, a clamping block is provided at the end of the clamping rod away from the stacking column base to press the top flat satellite downward.

[0007] According to one embodiment of the present invention, the stacking column has a clamping groove on the end face away from its corresponding flat satellite to accommodate the clamping rod.

[0008] According to one embodiment of the present invention, the two ends of the stacking column along the stacking direction protrude toward the two sides of the flat satellite opposite to it, so as to support the flat satellite.

[0009] According to one embodiment of the present invention, the stacking column base is provided with an unfolding drive mechanism; the unfolding drive mechanism includes a mounting base, a connecting rod, a torsion spring, and a separation connection device; one end of the connecting rod is rotatably connected to the mounting base, and the other end is rotatably connected to the clamping rod; the torsion spring is disposed at the connection between the connecting rod and the clamping rod; the separation connection device is disposed on the mounting base and is detachably connected to the end of the clamping rod near the mounting base; when the clamping rod clamps the flat satellite, the flat satellite is fixedly connected to the clamping rod through the separation connection device; after the separation connection device separates from the clamping rod, the torsion spring drives the connecting rod to rotate relative to the mounting base, thereby pushing the clamping rod to swing away from the flat satellite to release the flat satellite.

[0010] According to one embodiment of the present invention, the separating connection device is an explosive bolt.

[0011] According to one embodiment of the present invention, two cylindrical grooves are provided at the top of the stacking column of the top-layer flat satellite; springs are provided in the cylindrical grooves; the clamping block presses the springs into the cylindrical grooves from the top of the stacking column, and the springs are used to provide an upward driving force for the clamping rod.

[0012] According to one embodiment of the present invention, a full-pressure clamping release device and a semi-pressure clamping release device are included. The full-pressure clamping release device includes a full-height stacking column base, a full-height stacking column, and a long clamping rod. The semi-pressure clamping release device includes a half-height stacking column base, a half-height stacking column, and a short clamping rod. The full-height stacking column base and the semi-height stacking column base are disposed in the support compartment of the rocket. Each layer of the stack includes two flat-panel satellites laid flat. At least one of the full-height stacking columns is disposed on each of the two flat-panel satellites in each layer, on the two sides of the two flat-panel satellites that are far apart from each other. The full-height stacking columns of the bottom flat-panel satellites are placed on a full-height stacking column base, and the full-height stacking columns of the upper flat-panel satellites are placed sequentially on the full-height stacking columns of the flat-panel satellites below them. One end of the long clamping rod is connected to the full-height stacking column base. The stacked column base is rotatably connected; the long clamping rod swings toward the flat satellite to press the full-height stacked column; each of the two flat satellites in each layer has a half-height stacked column on its side adjacent to its docking surface; the half-height stacked columns on the same side of the two flat satellites in each layer are staggered; when two flat satellites are laid flat, the half-height stacked column of one flat satellite is placed on the half-height stacked column of the other flat satellite on the same side; the bottom half-height stacked columns are placed on a half-height stacked column base, and the half-height stacked columns of the upper flat satellites are placed on the half-height stacked columns of the flat satellites below them; one end of the short clamping rod is rotatably connected to the half-height stacked column base; the short clamping rod swings toward the flat satellite to press the half-height stacked column.

[0013] According to one embodiment of the present invention, in the stacking direction, one end of the half-height stacking column corresponding to the two flat satellites in each layer protrudes to the side of the flat satellite to support the flat satellite.

[0014] On the other hand, this utility model provides a flat-panel satellite, including the stacked columns in the above-mentioned compression and release device.

[0015] According to the flat-panel satellite clamping and releasing device of this utility model, the stacking column set on the side of the flat-panel satellite is clamped or released by the clamping rod, so as to realize reliable clamping and safe release of the stacked flat-panel satellite.

[0016] It should be understood that the above general description and the following specific embodiments are merely exemplary and illustrative, and do not limit the scope of the present invention. Attached Figure Description

[0017] The accompanying drawings are part of the specification of this utility model and illustrate exemplary embodiments of the utility model. The drawings, together with the description in the specification, are used to illustrate the principles of the utility model.

[0018] Figure 1 This is a schematic diagram of the flat satellite pressing and releasing device in one embodiment of the present invention, showing the pressing state of the flat satellite;

[0019] Figure 2 This is a schematic diagram of the flat satellite compression and release device releasing the flat satellite in one embodiment of the present invention;

[0020] Figure 3 This is a schematic diagram of a stacked column according to an embodiment of the present invention;

[0021] Figure 4 This is a schematic diagram of the unfolding drive mechanism according to an embodiment of the present invention;

[0022] Figure 5 yes Figure 4 A front view of the compressed state;

[0023] Figure 6 yes Figure 4 A front view of the unfolded state;

[0024] Figure 7 This is a schematic diagram of a compression release device according to another embodiment of the present invention;

[0025] Figure 8 This is a cross-sectional view of a full-height stacked column according to an embodiment of the present invention;

[0026] Figure 9This is a schematic diagram of the flat satellite compression and release device releasing the flat satellite in another embodiment of the present invention;

[0027] Figure 10 This is a schematic diagram of a half-height stacked column of a full-height stacked column according to an embodiment of the present invention;

[0028] Figure 11 This is a schematic diagram of the flat satellite pressing and releasing device in another embodiment of the present invention, showing the pressing state of the flat satellite;

[0029] Figure 12 yes Figure 11 The front view;

[0030] Figure 13 This is a schematic diagram of the flat satellite clamping and releasing device releasing the flat satellite in another embodiment of the present invention;

[0031] Figure 14 This is a schematic diagram of releasing a large flat-panel satellite according to one embodiment of the present invention;

[0032] Figure 15 This is a schematic diagram of releasing a small flat-panel satellite according to one embodiment of the present invention.

[0033] Explanation of reference numerals in the attached figures:

[0034] 200-Flat Panel Satellite; 300-Stacking Column Base; 400-Stacking Column; 500-Clamping Rod; 600-Clamping Block; 1-Large Flat Panel Satellite; 2-Small Flat Panel Satellite; 3-Short Clamping Block; 4-Long Clamping Block; 5-Long Clamping Rod; 6-Short Clamping Rod; 7-Full Height Stacking Column; 8-Full Height Stacking Column Base; 9-Half Height Stacking Column Base; 10-Half Height Stacking Column; 11-Explosion Bolt; 12-Mounting Base; 13-Connecting Rod; 14-Torsion Spring; 15-Unlocking Spindle; 16-Unfolding Spindle; 17-Spring. Detailed Implementation

[0035] The features and exemplary embodiments of various aspects of this utility model will be described in detail below. To make the objectives, technical solutions, and advantages of this utility model clearer, the following detailed description is provided in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain this utility model and to exemplarily illustrate the principles of this utility model, and are not configured to limit this utility model. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the dimensions of some structural components or regions in the drawings may be enlarged for other structural components or regions to aid in the understanding of the embodiments of this utility model.

[0036] The directional terms used in the following description refer to the directions shown in the figures and are not intended to limit the specific structure of the embodiments of this utility model. In the description of this utility model, it should be noted that, unless otherwise stated, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0037] Furthermore, the terms "comprising," "including," "having," or any other variations thereof are intended to cover non-exclusive inclusion, such that a structure or component that includes a list of elements includes not only those elements but also other structural elements that are not expressly listed or inherent to the structure or component. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of other identical elements in the article or apparatus that includes the element.

[0038] Spatial relation terms such as "below," "under," "under," "low," "above," "on," and "high" are used for descriptive convenience to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device, in addition to those different from those shown in the figure. Furthermore, phrases such as "one element on / below another element" can indicate that two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first" and "second" are also used to describe individual elements, areas, parts, etc., without specifically indicating order or sequence, and should not be considered restrictive. Similar terms are used throughout the description to represent similar elements.

[0039] In the following description of this utility model, the terms "rocket," "launch vehicle," "spacecraft," "space launch vehicle," or "missile" may be used in certain scenarios for ease of description only, and their connotations are not limited to the specific terms used. Generally, the rocket in this utility model includes space launch vehicles or launch vehicles used to launch satellites, spacecraft, or other probes, as well as various missiles, rockets, and other weapons used to carry payloads, and similar products capable of sending payloads into the air. Those skilled in the art, when interpreting the above specific terms, should not limit the rocket to only launch vehicles or missiles based on the specific terms used in the description, thereby narrowing the scope of protection of this utility model.

[0040] For those skilled in the art, this invention can be implemented without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by illustrating examples.

[0041] Figure 1 This is a schematic diagram of the flat satellite pressing and releasing device in one embodiment of the present invention, showing the pressing state of the flat satellite; Figure 2 This is a schematic diagram of the flat satellite compression and release device releasing the flat satellite in one embodiment of the present invention; Figure 3 This is a schematic diagram of a stacked column according to an embodiment of the present invention; Figure 4 This is a schematic diagram of the unfolding drive mechanism according to an embodiment of the present invention; Figure 5 yes Figure 4 A front view of the compressed state; Figure 6 yes Figure 4 A front view of the unfolded state; Figure 7 This is a schematic diagram of a compression release device according to another embodiment of the present invention; Figure 8 This is a cross-sectional view of a full-height stacked column according to an embodiment of the present invention; Figure 9 This is a schematic diagram of the flat satellite compression and release device releasing the flat satellite in another embodiment of the present invention; Figure 10 This is a schematic diagram of a half-height stacked column of a full-height stacked column according to an embodiment of the present invention; Figure 11 This is a schematic diagram of the flat satellite pressing and releasing device in another embodiment of the present invention, showing the pressing state of the flat satellite; Figure 12 yes Figure 11 The front view; Figure 13 This is a schematic diagram of the flat satellite clamping and releasing device releasing the flat satellite in another embodiment of the present invention; Figure 14 This is a schematic diagram of releasing a large flat-panel satellite according to one embodiment of the present invention; Figure 15 This is a schematic diagram of releasing a small flat-panel satellite according to one embodiment of the present invention.

[0042] like Figure 1 and 2 As shown, this utility model provides a flat-panel satellite clamping and release device, including: a stacking column base 300, stacking columns 400, and a clamping rod 500. The stacking column base 300 is disposed in the support compartment of a rocket. The stacking columns 400 are used for fixed connection to the sides of stacked flat-panel satellites 200. The stacking columns 400 of the bottom flat-panel satellite 200 are placed on the stacking column base 300, and the stacking columns 400 of the upper flat-panel satellites 200 are placed sequentially on the stacking columns 400 of the lower flat-panel satellites 200. One end of the clamping rod 500 is rotatably connected to the stacking column base 300. The clamping rod 500 swings toward the flat-panel satellite 200 to clamp the stacking columns 400.

[0043] The clamping and releasing device provided in this embodiment can reliably clamp and safely release the stacked flat satellites 200 by rotating the clamping rod 500 relative to the stacking column base 300 toward or away from the flat satellites 200.

[0044] like Figure 1 and Figure 2 As shown, according to one embodiment of the present invention, a clamping block 600 is provided at the end of the clamping rod 500 away from the stacking column base 300 to press the top flat satellite 200 downward.

[0045] In this embodiment, the clamping block presses down on the topmost flat satellite stack from above, pre-compressing the flat satellites and evenly transmitting the pre-compression force to the stacking column, avoiding pressure eccentricity. For example, the clamping block 600 can be made of metal.

[0046] According to one embodiment of the present invention, the stacking column 400 has a clamping groove on the end face away from its corresponding flat satellite 200 to accommodate the clamping rod 500.

[0047] like Figure 3 As shown, according to one embodiment of the present invention, the two ends of the stacking column 400 along the stacking direction protrude toward the two sides of the flat satellite 200 opposite to it, so as to support the flat satellite 200.

[0048] The compression release device provided in this embodiment, with the two ends of the stacking column 400 protruding, enables the flat satellites to be stacked at intervals, effectively avoiding the risk of satellites colliding with each other during satellite-rocket separation, and improving the safety and reliability of satellite-rocket separation.

[0049] like Figures 4-7 As shown, according to one embodiment of the present invention, the stacking column base 300 is provided with an unfolding drive mechanism. The unfolding drive mechanism includes a mounting base 12, a connecting rod 13, a torsion spring 14, and a separation connection device. One end of the connecting rod 13 is rotatably connected to the mounting base 12, and the other end is rotatably connected to the clamping rod 500. The torsion spring 14 is disposed at the connection between the connecting rod 13 and the clamping rod 500. The separation connection device is disposed on the mounting base 12 and is detachably connected to the end of the clamping rod 500 near the mounting base 12. When the clamping rod 500 clamps the flat satellite 200, the flat satellite 200 is fixedly connected to the clamping rod 500 and clamped by the separation connection device. After the separation connection device is separated from the clamping rod 500, the torsion spring 14 drives the connecting rod 13 to rotate relative to the mounting base 12, thereby pushing the clamping rod 500 to swing away from the flat satellite 200 and release the flat satellite 200.

[0050] like Figures 4-7 As shown, according to one embodiment of the present invention, one end of the connecting rod 13 is rotatably connected to the mounting base 12 via an unlocking pivot 15, and the other end is rotatably connected to the connecting rod 13 via an unfolding pivot 16. A torsion spring 14 is mounted on the unfolding pivot 16, and the torsion spring 14 is used to provide an unfolding driving torque to the clamping rod 500.

[0051] According to one embodiment of the present invention, the separation connection device is an explosion bolt 11.

[0052] In this embodiment, the separation connection device can be an explosion bolt 11, a separation nut, or a shape memory alloy puller.

[0053] like Figure 8 As shown, according to one embodiment of the present invention, the top of the stacking column 400 of the top-layer flat satellite 200 is provided with two cylindrical grooves, and springs 17 are provided in the cylindrical grooves. The clamping block 600 presses the springs 17 into the cylindrical grooves from the top of the stacking column 400. The springs 17 are used to provide an upward driving force for the clamping rod 500, that is, to cooperate with the unfolding drive mechanism to assist the clamping rod 500 in separating from the flat satellite 200.

[0054] In this embodiment, when the clamping release device locks the flat-panel satellite 200, one end of the spring 17 is fixedly connected to the stacking column 400, and the other end contacts the clamping block 600, providing an upward elastic force to the clamping block 600. After unlocking, the clamping block 600, pushed by the spring 17, drives the clamping rod 500 to move upward.

[0055] like Figure 9 As shown, according to one embodiment of the present invention, a full-pressure clamping release device and a half-pressure clamping release device are included. The full-pressure clamping release device includes a full-height stacking column base 8, a full-height stacking column 7, and a long clamping rod 5. The half-pressure clamping release device includes a half-height stacking column base 9, a half-height stacking column 10, and a short clamping rod 6. The full-height stacking column base 8 and the half-height stacking column base 9 are disposed in the rocket's support compartment.

[0056] Each layer of the stack consists of two flat-panel satellites 200 laid flat. At least one full-height stacking column 7 is provided on each of the two mutually distant sides of the two flat-panel satellites 200 in each layer. The full-height stacking column 7 of the bottom-layer flat-panel satellite 200 rests on a full-height stacking column base 8, and the full-height stacking columns 7 of the upper-layer flat-panel satellites 200 are placed sequentially on the full-height stacking columns 7 of the flat-panel satellites 200 below them. One end of a long clamping rod 5 is rotatably connected to the full-height stacking column base 8. The long clamping rod 5 swings toward the flat-panel satellite 200 to clamp the full-height stacking column 7.

[0057] Each layer of two flat-panel satellites 200 has a half-height stacking column 10 on its adjacent side to the docking surface. The half-height stacking columns 10 on the same side of the two flat-panel satellites 200 in each layer are staggered. When two flat-panel satellites 200 are laid flat, the half-height stacking column 10 of one flat-panel satellite 200 is placed on the half-height stacking column 10 on the same side of the other flat-panel satellite 200. The bottom half-height stacking columns 10 are placed on a half-height stacking column base 9, and the half-height stacking columns 10 of the upper flat-panel satellites 200 are placed on the half-height stacking columns 10 of the flat-panel satellites 200 below them. One end of the short clamping rod 6 is rotatably connected to the half-height stacking column base 9. The short clamping rod 6 swings toward the flat-panel satellite 200 to clamp the half-height stacking columns 10.

[0058] Specifically, in order to achieve high-density stacking of flat-panel satellites 200 within the fairing, multiple flat-panel satellites 200 (e.g., small flat-panel satellites) can be laid out flat on each layer of the stack.

[0059] In this embodiment, flat-panel satellites 200 are laid flat and stacked together. Long clamping rods 5 and short clamping rods 6 respectively clamp the full-height stacking columns 7 or half-height stacking columns 10 in the same column, forming a composite structure from multiple flat-panel satellites 200. After the satellite-launch separation command is issued, the long clamping rods 5 and short clamping rods 6 open to release the flat-panel satellites 200. For example, the half-height stacking columns 10 of two small flat-panel satellites 2 in the same layer can be positioned close to their docking point. This clamping and release device effectively reduces the number of clamping and release devices and lightens the overall weight by sharing a single half-height clamping and release device at both ends of the docking point between the flat-panel satellites 200.

[0060] like Figure 10 As shown, according to one embodiment of the present invention, in the stacking direction, one end of the half-height stacking column 10 corresponding to the two flat satellites 200 in each layer protrudes to the side of the flat satellite 200 to support the flat satellite 200.

[0061] like Figures 11-15 As shown, according to one embodiment of the present invention, the stacked flat-panel satellites include a large flat-panel satellite 1 and small flat-panel satellites 2. The small flat-panel satellites 2 are stacked in the support compartment of the rocket to form a first vertical stage. Each layer of the first vertical stage includes two small flat-panel satellites 2 laid flat. The large flat-panel satellite 1 is stacked at the top of the first vertical stage to form a second vertical stage, i.e., each layer of the second vertical stage has only one large flat-panel satellite 1. The two sides of the two small flat-panel satellites 2 in each layer of the first vertical stage, which are far apart from each other along their laying direction, are respectively aligned with the corresponding two sides of the large flat-panel satellite 1.

[0062] In the first vertical layer, each of the two small flat-panel satellites 2 has at least one full-height stacking column 7 on each of their two mutually distant sides. In the second vertical layer, each of the large flat-panel satellites 1 has a corresponding full-height stacking column 7. The full-height stacking columns 7 of the bottom-level small flat-panel satellites 2 are placed on a full-height stacking column base 8, and the full-height stacking columns 7 of the upper-level small flat-panel satellites 2 or large flat-panel satellites 1 are placed sequentially on the full-height stacking columns 7 of the lower-level small flat-panel satellites 2 or large flat-panel satellites 1. A long clamping rod 5 swings toward the large flat-panel satellite 1 to clamp the full-height stacking column 7. In the first vertical layer, each of the two small flat-panel satellites 2 has a half-height stacking column 10 on its adjacent side to its docking surface. The half-height stacking columns 10 of the bottom-level small flat-panel satellites 2 are placed on a half-height stacking column base 9, and the half-height stacking columns 10 of the upper-level small flat-panel satellites 2 are placed sequentially on the half-height stacking columns 10 of the lower-level small flat-panel satellites 2. A short clamping rod 6 swings toward the small flat-panel satellites 2 to clamp the half-height stacking column 10.

[0063] Specifically, in the flat-panel satellite stacking configuration, satellites are densely stacked in the fairing. The spacing between satellites in different stacking layers is small, and the mass characteristics of satellites of different sizes are inconsistent. If released simultaneously, the different satellites will move in different ways, posing a significant risk of collision. To ensure the safe and reliable separation of satellites of different sizes in the hybrid stacking configuration, a controllable and orderly separation scheme is required.

[0064] In this embodiment, large and small flat-panel satellites of different sizes are stacked together in a mixed single- or double-row configuration. Long clamping rods 5 and short clamping rods 6 respectively compress the full-height stacking columns 7 or half-height stacking columns 10 in the same row, forming a combined structure of multiple flat-panel satellites. After the satellite-rocket separation command is issued, the long clamping rods 5 and short clamping rods 6 sequentially open to release the large and small flat-panel satellites respectively. This clamping and release device achieves high-density storage of flat-panel satellites of different sizes within the fairing, fully utilizing the fairing space, improving the flexibility of multi-satellite launches and maximizing rocket capacity, reducing rocket capacity waste, improving rocket efficiency, and meeting the needs of launching flat-panel satellites of different sizes in batches. Furthermore, it allows for the orderly and controllable release of large and small flat-panel satellites in batches, solving the problem of safe release of high-density mixed-stack flat-panel satellites and improving the safety and reliability of satellite-rocket separation.

[0065] In addition, the compression release device uses a set of full high-pressure compression release devices shared by the upper large flat-panel satellite and the lower small flat-panel satellite on both sides, and a set of half high-pressure compression release devices shared by both ends of the docking point between the flat-panel satellites, which effectively reduces the number of compression release devices and lightens the overall weight.

[0066] For example, such as Figure 11As shown, in the first vertical layer, two full-height stacking pillars are respectively set on the two opposite sides of the two small flat-panel satellites 2 on each layer. That is, the flat-panel satellite assembly is equipped with four sets of full-pressure clamping release devices, including four rows of full-height stacking pillars. For example, each small flat-panel satellite 2 in the first vertical layer has a half-height stacking pillar at each end of its docking point. For example, the full-height stacking pillar 7 and the half-height stacking pillar 10 can be metal structures that are fixedly connected to the large or small flat-panel satellites. After the satellite separates from the launch vehicle, the full-height stacking pillar 7 and the half-height stacking pillar 10 remain fixedly connected to the large or small flat-panel satellites and do not separate.

[0067] like Figure 12 and Figure 13 As shown, according to one embodiment of the present invention, a long clamping block 4 is provided at the end of the long clamping rod 5 away from the full-height stacking column base 8 to press the large flat satellite 1 at the top downwards. A short clamping block 3 is provided at the end of the short clamping rod 6 away from the half-height stacking column base 9 to press the small flat satellite 2 on the top layer downwards.

[0068] In this embodiment, the long clamping block 4 and the short clamping rod 6 are used to pre-compress the large flat-panel satellite 1 and the small flat-panel satellite 2 by pressing them from above the full-height stacking column 7 of the uppermost large flat-panel satellite 1 and the half-height stacking column 10 of the small flat-panel satellite 2. This pre-compresses the large flat-panel satellite 1 and the small flat-panel satellite 2, ensuring that the pre-compressing force is evenly transmitted to the full-height stacking column 7 and the half-height stacking column 10, thus avoiding pressure eccentricity. For example, the long clamping block 4 and the short clamping block 3 can be made of metal. For example, a full-height high-pressure clamping release device can be equipped with two parallel long clamping rods 5 to clamp the full-height stacking column 7. A set of half-height high-pressure clamping release devices can be equipped with two parallel short clamping rods 6 to clamp the half-height stacking column 10.

[0069] According to one embodiment of the present invention, along the stacking direction, both the full-height stacking column 7 and the half-height stacking column 10 are provided with two clamping grooves, and the structures of the full-height stacking column 7 and the half-height stacking column 10 are as follows: Figure 10 The "E" shape is shown. The clamping groove is used to accommodate the long clamping rod 5 or the short clamping rod 6 to bear the preload applied by the long clamping rod 5 or the short clamping rod 6. For example, the long clamping rod 5 or the short clamping rod 6 can be a cylindrical metal rod.

[0070] According to one embodiment of the present invention, both the full-height stacked column base 8 and the half-height stacked column base 9 are provided with an unfolding drive mechanism.

[0071] According to one embodiment of the present invention, two cylindrical grooves are provided at the top of the full-height stacking column 7 of the top-layer large flat-panel satellite and the half-height stacking column 10 of the top-layer small flat-panel satellite.

[0072] In this embodiment, when the clamping release device is locking the large and small flat-panel satellites, one end of the spring 17 is fixedly connected to the full-height stacking column 7 or the half-height stacking column 10, and the other end is in contact with the short clamping block 3 or the long clamping block 4, providing an upward elastic force to the short clamping block 3 or the long clamping block 4. After unlocking, the short clamping block 3 or the long clamping block 4, pushed by the spring 17, respectively drives the short clamping rod 6 and the long clamping rod 5 to move upward, thereby assisting the long and short clamping rods in releasing the flat-panel satellites.

[0073] For example, to quickly separate flat-panel satellites of different sizes after the clamping release device is unlocked, a spin-jet separation method can be used. That is, the rocket spins before separation, and after reaching a certain angular velocity, the separation command is sent, providing the satellites with an initial angular velocity. Since satellites in different layers are at different distances from the center of rotation, they have different linear velocities at the same angular velocity, thus allowing them to gradually separate after separation.

[0074] like Figure 11 As shown, in the initial state, the long clamping rod 5 and the short clamping rod 6 are embedded in the grooves on the sides of the full-height stacked column 7 and the half-height stacked column 10 to clamp them. The explosion bolt 11 is fixedly connected to the lower end face of the long clamping rod 5 and the short clamping rod 6. The short clamping block 3 and the long clamping block 4 clamp them from the top of the half-height stacked column 10 and the full-height stacked column 7, respectively. The spring 17 and the torsion spring 14 are in the pre-tightened state.

[0075] After reaching its orbital insertion point, the rocket begins to rotate. Once it reaches a certain angular velocity, it sends an unlocking signal to the large flat-panel satellite. For example... Figure 14 As shown, after receiving the unlocking signal from the rocket launch, the explosive bolt separates from the long clamping rod 5. Driven by the spring 17, the long clamping block 4 moves the long clamping rod 5 upwards, simultaneously driving the connecting rod 13 to rotate relative to the mounting base 12 around the unlocking shaft 15. Under the driving torque of the torsion spring 14, the long clamping rod 5 rotates around the unfolding shaft and swings to its maximum angle. The two large flat-panel satellites separate from the ten smaller flat-panel satellites below, and under the influence of the rocket's rotational angular velocity, gradually increase the distance between them, and gradually increase the distance from the rocket, completing the separation and release of the large flat-panel satellites. At this time, because the semi-high pressure release device is in a locked state, the ten smaller flat-panel satellites below remain in a stacked assembly state and have not yet separated.

[0076] After a certain delay (e.g., after the large flat-panel satellite has safely separated), the rocket sends an unlock signal to the small flat-panel satellite. Figure 5As shown, the explosive bolt separates from the short clamping rod 6. Driven by the spring 17, the short clamping block 3 moves the short clamping rod 6 upwards, simultaneously driving the connecting rod 13 to rotate relative to the mounting base 12 around the unlocking shaft 15. Under the driving torque of the torsion spring 14, the short clamping rod 6 rotates around the unfolding shaft and swings to its maximum angle. The 10 small flat-panel satellites separate from the rocket and gradually increase the inter-satellite distance under the rocket's rotational angular velocity, thus completing the separation and release of the 10 small flat-panel satellites.

[0077] After the star separates from the rocket, the full-height stacked column base 8 and the half-height stacked column base 9 remain fixedly connected to the rocket.

[0078] For example, the swing angle of the long clamping rod 5 or the short clamping rod 6 can be mechanically limited by the mounting base 12.

[0079] The clamping and releasing process of the clamping and releasing device on the flat-panel satellite is as follows:

[0080] S01: After the rocket reaches the orbital insertion point, it begins to rotate. Once it reaches a certain angular velocity, it sends the unlocking signal for the large flat-panel satellite.

[0081] S02: After receiving the unlocking signal of the large flat-panel satellite sent by the rocket, the separation and connection device separates from the long clamping rod. The long clamping rod moves upward and drives the connecting rod to rotate relative to the mounting base. Under the driving torque of the torsion spring, the long clamping rod rotates relative to the connecting rod and swings to the maximum angle. The large flat-panel satellite separates from the small flat-panel satellite and gradually increases the inter-satellite distance under the action of the rocket's rotational angular velocity, completing the separation and release of the large flat-panel satellite.

[0082] S03: After the large flat-panel satellite has separated, the rocket sends an unlocking signal to the small flat-panel satellite;

[0083] S04: After receiving the unlocking signal from the rocket, the separation and connection device separates from the short clamping rod. The short clamping rod moves upward, simultaneously driving the connecting rod to rotate relative to the mounting base. Under the driving torque of the torsion spring, the short clamping rod rotates around the connecting rod and swings to its maximum angle. The small flat-panel satellite separates from the rocket and gradually increases the inter-satellite distance under the action of the rocket's rotational angular velocity, completing the separation and release of the small flat-panel satellite.

[0084] On the other hand, this utility model provides a flat-panel satellite, including the stacked columns in the above-mentioned compression and release device.

[0085] The above embodiments of this utility model can be combined with each other and have corresponding technical effects.

[0086] The above are merely preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. A flat-panel satellite clamping and releasing device, characterized in that, include: Stacking column base, stacking column, and clamping rod; the stacking column base is disposed in the rocket's support compartment; The stacking column is used to be fixedly connected to the side of the stacked flat-panel satellites; the stacking column of the bottom flat-panel satellite is placed on the stacking column base, and the stacking column of the upper flat-panel satellite is placed on the stacking column of the lower flat-panel satellite in sequence; one end of the clamping rod is rotatably connected to the stacking column base; the clamping rod swings toward the flat-panel satellite to clamp the stacking column.

2. The compression release device according to claim 1, characterized in that, A clamping block is provided at the end of the clamping rod away from the base of the stacking column to press the top flat satellite downwards.

3. The compression release device according to claim 1, characterized in that, The stacked column has a clamping groove on the end face away from its corresponding flat satellite to accommodate the clamping rod.

4. The compression release device according to claim 1, characterized in that, The two ends of the stacking column along the stacking direction protrude toward the two sides of the flat satellite opposite to it, so as to support the flat satellite.

5. The compression release device according to claim 2, characterized in that, The stacked column base is provided with an unfolding drive mechanism; the unfolding drive mechanism includes a mounting base, a connecting rod, a torsion spring, and a separation connection device; one end of the connecting rod is rotatably connected to the mounting base, and the other end is rotatably connected to the clamping rod; the torsion spring is disposed at the connection between the connecting rod and the clamping rod; the separation connection device is disposed on the mounting base and is detachably connected to the end of the clamping rod near the mounting base; When the clamping rod clamps the flat satellite, it is fixedly connected to the clamping rod through the separation connection device to clamp the flat satellite; after the separation connection device is separated from the clamping rod, the torsion spring drives the connecting rod to rotate relative to the mounting base, so as to push the clamping rod to swing away from the flat satellite and release the flat satellite.

6. The compression release device according to claim 5, characterized in that, The separation connection device is an explosive bolt.

7. The compression release device according to claim 5, characterized in that, The top of the stacked column of the top-level flat satellite is provided with two cylindrical grooves; springs are provided in the cylindrical grooves; the clamping block presses the springs into the cylindrical grooves from the top of the stacked column, and the springs are used to provide the clamping rod with an upward driving force.

8. The compression release device according to claim 1, characterized in that, Including full-pressure release devices and semi-pressure release devices; The full-pressure clamping release device includes a full-height stacked column base, a full-height stacked column, and a long clamping rod; The semi-high pressure release device includes a semi-high stacked column base, a semi-high stacked column, and a short pressure bar; Full-height stacked column bases and half-height stacked column bases are installed in the rocket's support compartment; Each stacked layer consists of two flat-panel satellites laid flat. At least one full-height stacking column is provided on each of the two mutually distant sides of the two flat-panel satellites in each layer; the full-height stacking column of the bottom flat-panel satellite is placed on a full-height stacking column base, and the full-height stacking columns of the upper flat-panel satellites are placed on the full-height stacking columns of the flat-panel satellites below them; one end of the long clamping rod is rotatably connected to the full-height stacking column base; the long clamping rod swings toward the flat-panel satellite to clamp the full-height stacking column. Each of the two flat satellites in each layer has a half-height stacking column on the side adjacent to its docking surface; the half-height stacking columns on the same side of the two flat satellites in each layer are staggered; when two flat satellites are laid flat, the half-height stacking column of one flat satellite is placed on the half-height stacking column of the other flat satellite on the same side. The bottom half-height stacked columns are placed on a half-height stacked column base, and the half-height stacked columns of the upper flat-panel satellite are placed on the half-height stacked columns of the lower flat-panel satellite in sequence; one end of the short clamping rod is rotatably connected to the half-height stacked column base; the short clamping rod swings toward the flat-panel satellite to clamp the half-height stacked columns.

9. The compression release device according to claim 8, characterized in that, In the stacking direction, one end of the half-height stacking column corresponding to the two flat satellites in each layer protrudes to the side of the flat satellite to support it.

10. A flat-panel satellite, characterized in that, Includes the stacked columns in the compression release device as described in any one of claims 1-9.

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