Panel satellite mixed stacking layout structure and releasing method

Abstract

The invention provides a flat plate satellite mixed stacking layout structure and a releasing method, and the layout structure comprises a large flat plate satellite and a small flat plate satellite; the small flat satellites are stacked and placed in a supporting cabin of the rocket to form a first vertical layer; each layer of the first vertical layer comprises two small-sized plate satellites which are laid flatly; the large flat plate satellites are stacked at the top end of the first vertical layer to form a second vertical layer; the two side faces, away from each other in the tiling direction, of the two small flat plate satellites of each layer of the first vertical layer are aligned with the two corresponding side faces of the large flat plate satellite respectively. By means of the layout structure, efficient utilization of the space of the fairing can be achieved.

Description

Technical Field

[0001] This invention relates to the field of satellites, and more specifically to a hybrid stacked layout structure for flat-panel satellites. 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 achieve high-density accommodation of satellites of different sizes within the fairing, designing a hybrid stacking layout structure for flat-panel satellites is particularly important. Summary of the Invention

[0004] The purpose of this invention is to overcome the shortcomings of the prior art and provide a flat-panel satellite hybrid stacking layout structure and release method.

[0005] This invention provides a hybrid stacked layout structure for flat-panel satellites, comprising: a large flat-panel satellite and a small flat-panel satellite; the small flat-panel satellites are stacked in the support compartment of a rocket to form a first vertical stage; each layer of the first vertical stage includes two small flat-panel satellites laid flat; the large flat-panel satellites are stacked at the top of the first vertical stage to form a second vertical stage; the two sides of the two small flat-panel satellites in each layer of the first vertical stage that are far apart from each other along their laying direction are respectively aligned with the corresponding two sides of the large flat-panel satellite.

[0006] According to one embodiment of the present invention, the small flat-panel satellites in each layer of the first vertical layer are stacked at intervals; the large flat-panel satellites in each layer of the second vertical layer are stacked at intervals; and the large flat-panel satellites are stacked at intervals with the small flat-panel satellites.

[0007] According to one embodiment of the present invention, a clamping release device is further included; the clamping release device includes a full-pressure clamping release device and a half-pressure clamping release device; the full-pressure clamping release device includes a full-height stacking column base, a full-height stacking column, and a long clamping rod; the half-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 half-height stacking column base are disposed in the support compartment of the rocket; at least one full-height stacking column is respectively disposed on the two mutually distant sides of the two small flat-panel satellites in each layer of the first vertical stage, and at least one full-height stacking column is disposed on each of the large flat-panel satellites in each layer of the second vertical stage; the full-height stacking columns of the bottom layer of small flat-panel satellites are respectively placed on one full-height stacking column base, and the full-height stacking columns of the upper layer of small flat-panel satellites or large flat-panel satellites are respectively placed on one full-height stacking column base. The full-height stacking columns are sequentially placed on the full-height stacking columns of the lower-level small or large flat-panel satellites; one end of the long clamping rod is rotatably connected to the base of the full-height stacking column; the long clamping rod swings toward the large flat-panel satellite to press the full-height stacking column; a half-height stacking column is respectively provided on the side of each of the two small flat-panel satellites in each of the first vertical layers adjacent to their docking surfaces; the half-height stacking columns of the bottom-level small flat-panel satellites are respectively placed on a half-height stacking column base, and the half-height stacking columns of the upper-level small flat-panel satellites are sequentially placed on the half-height stacking columns of the lower-level small flat-panel satellites; one end of the short clamping rod is rotatably connected to the base of the half-height stacking column; the short clamping rod swings toward the small flat-panel satellite to press the half-height stacking column.

[0008] According to one embodiment of the present invention, a long clamping block is provided at the end of the long clamping rod away from the full-height stacking column base to press the large flat-panel satellite at the top downward; a short clamping block is provided at the end of the short clamping rod away from the half-height stacking column base to press the small flat-panel satellite at the top downward.

[0009] According to one embodiment of the present invention, the full-height stacking column and the half-height stacking column are provided with grooves on the end face away from their corresponding large or small flat-panel satellite to accommodate the long or short clamping rod.

[0010] According to one embodiment of the present invention, the half-height stacking columns of two small flat-panel satellites arranged on the same side of each layer of the first vertical level along the stacking direction are staggered; when two small flat-panel satellites are laid flat, the half-height stacking column of one small flat-panel satellite is placed on the half-height stacking column on the same side of the other small flat-panel satellite.

[0011] According to one embodiment of the present invention, in the stacking direction, one end of the half-height stacking column, which is provided corresponding to the two small flat-panel satellites of each layer of the first vertical level, protrudes toward the side of the small flat-panel satellite to support the small flat-panel satellite.

[0012] According to one embodiment of the present invention, the two ends of the full-height stacking column along the stacking direction protrude toward the two sides of the small or large flat-panel satellite opposite to it, so as to support the small or large flat-panel satellite.

[0013] According to one embodiment of the present invention, both the full-height stacking column base and the half-height stacking column base are provided with a deployment drive mechanism; the deployment 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 long clamping rod or the short clamping rod; the torsion spring is disposed at the connection between the connecting rod and the long clamping rod or the short clamping rod; the separation connection device is disposed on the mounting base and is detachably connected to the end of the long clamping rod or the short clamping rod near the mounting base; when the long clamping rod or the short clamping rod presses against the large flat-panel satellite or the small flat-panel satellite, the large flat-panel satellite or the small flat-panel satellite is fixedly pressed against the long clamping rod or the short clamping rod through the separation connection device; after the separation connection device is separated from the long clamping rod or the short clamping rod, the torsion spring drives the connecting rod to rotate relative to the mounting base, so as to push the long clamping rod or the short clamping rod to swing away from the flat-panel satellite to release the large flat-panel satellite or the small flat-panel satellite.

[0014] On the other hand, the present invention provides a method for releasing a flat-panel satellite. The satellite adopts the layout structure described above, including: after the rocket reaches the orbital insertion point, it starts to rotate; after reaching a certain angular velocity, it sends an unlocking signal for the large flat-panel satellite; after receiving the unlocking signal from the rocket, the separation and connection device separates from the long clamping rod; the long 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 long clamping rod rotates relative to the connecting rod and swings to its maximum angle; the large flat-panel satellite separates from the small flat-panel satellite, and under the action of the rocket's rotational angular velocity... The rocket gradually increases the inter-satellite distance to complete the separation and release of the large flat-panel satellite. After the large flat-panel satellite has separated, the rocket sends an unlocking signal to the small flat-panel satellite. Upon 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 under the action of the rocket's rotational angular velocity, the inter-satellite distance gradually increases, completing the separation and release of the small flat-panel satellite.

[0015] According to the planar satellite hybrid stacking layout structure of the present invention, the fairing space is efficiently utilized through the single and double row planar satellite hybrid stacking structure.

[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 invention. Attached Figure Description

[0017] The accompanying drawings, which are part of the specification of this invention, illustrate exemplary embodiments of the invention. The drawings, together with the description in the specification, serve to illustrate the principles of the invention.

[0018] Figure 1 This is a perspective view of a flat-panel satellite hybrid stacking layout structure according to an embodiment of the present invention; Figure 2 This is a front view of a flat-panel satellite hybrid stacking layout structure according to an embodiment of the present invention; Figure 3 This is a schematic diagram of the unfolded state of the long clamping rod and the short clamping rod according to an embodiment of the present invention; Figure 4 This is a schematic diagram illustrating the release of a large flat-panel satellite according to an embodiment of the present invention; Figure 5 This is a schematic diagram illustrating the release of a small flat-panel satellite according to an embodiment of the present invention; Figure 6 This is a perspective view of a compression release device according to an embodiment of the present invention; Figure 7 yes Figure 6 A front view of the compressed state; Figure 8 yes Figure 6 A front view of the unfolded state; Figure 9 This is a schematic diagram of a compression release device according to another embodiment of the present invention; Figure 10 This is a cross-sectional view of a full-height stacked column according to an embodiment of the present invention.

[0019] Explanation of reference numerals in the attached figures: 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 hinge; 16-Unfolding hinge; 17-Spring. Detailed Implementation

[0020] The features and exemplary embodiments of various aspects of the present invention will now be described in detail. To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present invention and to exemplify the principles of the present invention, and are not configured to limit the present invention. 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 the present invention.

[0021] 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 the present invention. In the description of the present invention, 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 the present invention according to the specific circumstances.

[0022] 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.

[0023] 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.

[0024] In the following description of the present invention, 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 of the present invention includes both space launch vehicles or launch vehicles used to launch satellites, spacecraft, or other probes, and various missiles, rockets, and other weapons used to carry payloads, as well as 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 one of launch vehicles or missiles based on the specific terms used in the description, thereby narrowing the scope of protection of the present invention.

[0025] It will be apparent to those skilled in the art that the present invention can be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention.

[0026] Figure 1 This is a perspective view of a flat-panel satellite hybrid stacking layout structure according to an embodiment of the present invention; Figure 2 This is a front view of a flat-panel satellite hybrid stacking layout structure according to an embodiment of the present invention; Figure 3 This is a schematic diagram of the unfolded state of the long clamping rod and the short clamping rod according to an embodiment of the present invention; Figure 4 This is a schematic diagram illustrating the release of a large flat-panel satellite according to an embodiment of the present invention; Figure 5 This is a schematic diagram illustrating the release of a small flat-panel satellite according to an embodiment of the present invention; Figure 6 This is a perspective view of a compression release device according to an embodiment of the present invention; Figure 7 yes Figure 6 A front view of the compressed state; Figure 8 yes Figure 6 A front view of the unfolded state; Figure 9 This is a schematic diagram of a compression release device according to another embodiment of the present invention; Figure 10This is a cross-sectional view of a full-height stacked column according to an embodiment of the present invention.

[0027] like Figure 1 and 2 As shown, this invention provides a hybrid stacked layout structure for flat-panel satellites, comprising: 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 a rocket, forming 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, forming a second vertical stage. The two sides of the two small flat-panel satellites 2 in each layer of the first vertical stage, which are spaced apart from each other along their tiling direction, are aligned with the corresponding two sides of the large flat-panel satellite 1.

[0028] The layout structure provided in this embodiment, through a hybrid stacking structure of single and double-row flat-panel satellites, achieves high-density storage of flat-panel satellites of different sizes within the fairing. This fully utilizes the fairing space, improves the flexibility of launching multiple satellites with a single rocket and maximizes the use of rocket capacity, reduces waste of rocket capacity, improves rocket efficiency, and can meet the needs of launching flat-panel satellites of different sizes in a group.

[0029] like Figure 1 As shown, taking a stack of 12 flat-panel satellites as an example, the smaller flat-panel satellites are stacked in the bottom layer (the first vertical layer), with two smaller flat-panel satellites in each layer, for a total of five layers. The two larger flat-panel satellites are stacked in the top layer (the second vertical layer), with one larger flat-panel satellite in each layer, for a total of two layers.

[0030] like Figure 1 and 2 As shown, according to one embodiment of the present invention, small flat-panel satellites 2 are stacked at intervals in each layer of the first vertical layer. Large flat-panel satellites 1 are stacked at intervals in each layer of the second vertical layer. Large flat-panel satellites 1 and small flat-panel satellites 2 are stacked at intervals.

[0031] In this embodiment, the staggered stacking of large flat-panel satellite 1 and small flat-panel satellite 2 can effectively avoid the risk of collision between satellites of different sizes during satellite-rocket separation, thereby improving the safety and reliability of satellite-rocket separation.

[0032] like Figures 3-5As shown, according to one embodiment of the present invention, in addition to the large flat-panel satellite 1 and the small flat-panel satellite 2, the layout structure also includes a clamping and release device. The clamping and release device includes a full-pressure clamping and release device and a half-pressure clamping and release device. The full-pressure clamping and 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 and 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 support compartment of the rocket. At least one full-height stacking column 7 is disposed on each of the two small flat-panel satellites 2 in each layer of the first vertical stage, which are located on opposite sides. A corresponding full-height stacking column 7 is disposed on each of the large flat-panel satellites 1 in each layer of the second vertical stage. The full-height stacking columns 7 of the bottommost small flat-panel satellite 2 are placed on a full-height stacking column base 8, and the full-height stacking columns 7 of the upper-layer small flat-panel satellite 2 or large flat-panel satellite 1 are placed sequentially on the full-height stacking columns 7 of the lower-layer small flat-panel satellite 2 or large flat-panel satellite 1. One end of the long clamping rod 5 is rotatably connected to the full-height stacking column base 8. A long clamping rod 5 swings toward the large flat-panel satellite 1 to clamp the full-height stacking column 7. A half-height stacking column 10 is respectively installed on the side adjacent to the docking surface of each of the two smaller flat-panel satellites 2 in the first vertical layer. The half-height stacking columns 10 of the bottom-level smaller flat-panel satellite 2 are placed on a half-height stacking column base 9, and the half-height stacking columns 10 of the upper-level smaller flat-panel satellites 2 are placed sequentially on the half-height stacking columns 10 of the smaller flat-panel satellites 2 below them. One end of a short clamping rod 6 is rotatably connected to the half-height stacking column base 9. The short clamping rod 6 swings toward the smaller flat-panel satellites to clamp the half-height stacking columns 10.

[0033] Specifically, the flat-panel satellite stacking configuration involves high-density stacking of satellites on the fairing. The small spacing between satellites in different stacking layers, coupled with the inconsistent mass characteristics of satellites of different sizes, means that simultaneous release results in different satellite motion patterns, posing a significant risk of collision. This flat-panel satellite stacking configuration places high demands on the safety and reliability of satellite-launcher separation. To ensure the safe and reliable separation of satellites of different sizes in this hybrid stacking configuration, a controllable and orderly separation scheme is required.

[0034] 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 column, forming a composite structure of multiple flat-panel satellites. After the satellite-launch 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 layout structure enables the orderly and controllable batch release of large and small flat-panel satellites in a mixed-stacking configuration of flat-panel satellites of different sizes, solving the problem of safe release of high-density mixed-stacking flat-panel satellites and improving the safety and reliability of satellite-launch separation.

[0035] This layout structure effectively reduces the number of pressure release devices and lightens the overall weight by having the upper-layer large flat-panel satellite and the lower-layer small flat-panel satellite each share a full set of high-pressure pressure release devices on both sides, and the two ends of the docking points between the flat-panel satellites each share a half set of high-pressure pressure release devices.

[0036] For example, such as Figure 2 As shown, in the first vertical layer, two full-height stacking columns are respectively set on the two mutually distant sides of the two small flat-panel satellites 2. That is, the flat-panel satellite assembly is equipped with a total of four sets of full-pressure clamping release devices, including four rows of full-height stacking columns. For example, the full-height stacking columns 7 and half-height stacking columns 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 columns 7 and half-height stacking columns 10 remain fixedly connected to the large or small flat-panel satellites and do not separate.

[0037] like Figures 1-3 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 uppermost layer downwards.

[0038] 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-compressing force can be evenly transmitted to the full-height stacking column 7 and the half-height stacking column 10, avoiding pressure eccentricity. For example, the long clamping block 4 and the short clamping block 3 can be made of metal.

[0039] According to one embodiment of the present invention, the full-height stacking column 7 and the half-height stacking column 10 are provided with grooves on the end face away from their corresponding large flat satellite 1 or small flat satellite 2 to accommodate the long clamping rod 5 or the short clamping rod 6.

[0040] In this embodiment, the groove is arranged along the stacking direction. For example, a set of full-height high-pressure release devices can be provided with two parallel long clamping rods 5 to clamp the full-height stacked columns 7. A set of half-height high-pressure release devices can be provided with two parallel short clamping rods 6 to clamp the half-height stacked columns 10.

[0041] According to one embodiment of the present invention, such as Figure 4 and 5As shown, along the stacking direction, the end faces of the full-height stacking pillar 7 and the half-height stacking pillar 10 away from the large or small flat-panel satellite can be provided with two grooves, and the full-height stacking pillar 7 and the half-height stacking pillar 10 have an "E" shape. The grooves are 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.

[0042] like Figure 4 and Figure 5 As shown, according to one embodiment of the present invention, the half-height stacking columns 10 of two small flat-panel satellites 2 arranged on the same side of each layer of the first vertical level along the stacking direction are staggered. When two small flat-panel satellites 2 are laid flat, the half-height stacking column 10 of one small flat-panel satellite 2 is placed on the half-height stacking column 10 on the same side of the other small flat-panel satellite 2.

[0043] In this embodiment, for example, the half-height stacking pillars 10 of two small flat-panel satellites 2 on the same layer can be positioned close to their docking point. When laying two small flat-panel satellites 2 flat, the half-height stacking pillar 10 of one small flat-panel satellite 2 is placed on the half-height stacking pillar 10 on the same side of the other small flat-panel satellite 2, and is pressed together using a set of half-height stacking pillar bases 9 and short clamping rods 6. This method can reduce the need for a half-pressure clamping release device and reduce the overall weight of the rocket.

[0044] For example, such as Figure 4 As shown, each of the small flat-panel satellites 2 in the first vertical layer has a half-height stacking column at each end of its docking point. When two small flat-panel satellites 2 are laid flat, the half-height stacking column 10 of one small flat-panel satellite 2 is placed on the half-height stacking column 10 on the same side of the other small flat-panel satellite 2, and a set of half-height stacking column bases 9 and short clamping rods 6 are respectively set at each end of the docking point. That is, the flat-panel satellite assembly has a total of two rows of half-height stacking columns.

[0045] like Figure 4 As shown, according to one embodiment of the present invention, in the stacking direction, one end of a half-height stacking column 10, which is provided corresponding to two small flat-panel satellites 2 in each layer of the first vertical level, protrudes toward the side of the small flat-panel satellite 2 to support the small flat-panel satellite 2.

[0046] In this embodiment, the layout structure allows the small flat-panel satellites in each layer to be spaced apart by one end of the half-height stacked column 10 protruding to the side of the small flat-panel satellite 2, thereby reducing the risk of collision between the small flat-panel satellites during satellite-rocket separation.

[0047] According to one embodiment of the present invention, the two ends of the full-height stacking column 7 along the stacking direction protrude to the two sides of the small flat-panel satellite 2 or the large flat-panel satellite 1 opposite to it, so as to support the small flat-panel satellite 2 or the large flat-panel satellite 1.

[0048] The layout structure of this embodiment, with the protruding ends of the semi-full-height stacked columns 7, allows small and large flat-panel satellites in each layer to be spaced apart, reducing the risk of collisions between flat-panel satellites of different sizes during satellite-rocket separation.

[0049] like Figures 6-9 As shown, according to an embodiment of the present invention, both the full-height stacking column base 8 and the half-height stacking column base 9 are provided with an deployment drive mechanism. The deployment 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 a long clamping rod 5 or a short clamping rod 6. The torsion spring 14 is disposed at the connection between the connecting rod 13 and the long clamping rod 5 or the short clamping rod 6. The separation connection device is disposed on the mounting base 12 and is detachably connected to the end of the long clamping rod 5 or the short clamping rod 6 near the mounting base 12. When the long clamping rod 5 or the short clamping rod 6 presses against the large flat-panel satellite 1 or the small flat-panel satellite 2, the large flat-panel satellite 1 or the small flat-panel satellite 2 is fixedly pressed against the long clamping rod 5 or the short clamping rod 6 by the separation connection device. After the separation connection device is separated from the long clamping rod 5 or the short clamping rod 6, the torsion spring 14 drives the connecting rod 13 to rotate relative to the mounting base 12, so as to push the long clamping rod 5 or the short clamping rod 6 to swing away from the flat plate satellite and release the large flat plate satellite 1 or the small flat plate satellite 2.

[0050] like Figures 7-9 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 long clamping rod 5 or the short clamping rod 6.

[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 10 As shown, 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. Springs 17 are installed in the cylindrical grooves. Short clamping blocks 3 and long clamping blocks 4 respectively press the springs 17 into the cylindrical grooves from the top of the full-height stacking column 7 and the half-height stacking column 10. The springs 17 provide an upward driving force for the long clamping rods 5 and 6.

[0054] 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 post 7 or the half-height stacking post 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.

[0055] 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.

[0056] like Figure 1 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 full-height stacked column 7 and the half-height stacked column 10, respectively. The spring 17 and the torsion spring 14 are in the pre-tightened state.

[0057] 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 4 As shown, after receiving the unlocking signal from the rocket, 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.

[0058] 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.

[0059] 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.

[0060] 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.

[0061] On the other hand, the present invention provides a method for releasing a flat-panel satellite, wherein the satellite adopts the above-described layout structure, including: 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. 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. S03: After the large flat-panel satellite has separated, the rocket sends an unlocking signal to the small flat-panel satellite; 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.

[0062] The above embodiments of the present invention can be combined with each other and have corresponding technical effects.

[0063] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A flat-panel satellite stacking layout structure, characterized in that, include: Large flat-panel satellites and small flat-panel satellites; the small flat-panel satellites are stacked in the rocket's support cabin to form the first vertical stage; Each layer of the first vertical level includes two small flat-panel satellites laid flat; the large flat-panel satellites are stacked at the top of the first vertical level to form a second vertical level. The two small flat-panel satellites in each of the first vertical layers have their two sides, which are far apart from each other along their tiling direction, aligned with the corresponding two sides of the large flat-panel satellite.

2. The layout structure according to claim 1, characterized in that, The small flat-panel satellites in each layer of the first vertical level are stacked at intervals; The large flat-panel satellites in each layer of the second vertical level are stacked at intervals; the large flat-panel satellites are stacked at intervals with the small flat-panel satellites.

3. The layout structure according to claim 1, characterized in that, It also includes a clamping release device; the clamping release device includes a full-pressure clamping release device and a semi-pressure clamping release device; 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-pressure clamping release device includes a half-height stacked column base, a half-height stacked column and a short clamping rod; The full-height stacked column base and the half-height stacked column base are installed in the rocket's support compartment; In the first vertical layer, at least one full-height stacking column is provided on each of the two small flat-panel satellites on opposite sides of each other. In the second vertical layer, each large flat-panel satellite is provided with a corresponding full-height stacking column. The full-height stacking columns of the bottom-level small flat-panel satellites are placed on a full-height stacking column base. The full-height stacking columns of the upper-level small flat-panel satellites or large flat-panel satellites are placed sequentially on the full-height stacking columns of the lower-level small flat-panel satellites or large flat-panel satellites. One end of the long clamping rod is rotatably connected to the full-height stacking column base. The long clamping rod swings toward the large flat-panel satellite to clamp the full-height stacking column. Each of the two small flat-panel satellites in each of the first vertical layers has a half-height stacking column on the side adjacent to their docking surface; the half-height stacking columns of the bottommost small flat-panel satellite are placed on a half-height stacking column base, and the half-height stacking columns of the upper-layer small flat-panel satellites are placed on the half-height stacking columns of the smaller flat-panel satellites below them; one end of the short clamping rod is rotatably connected to the half-height stacking column base; the short clamping rod swings toward the small flat-panel satellite to press the half-height stacking column.

4. The layout structure according to claim 3, characterized in that, The long clamping rod has a long clamping block at one end away from the full-height stacking column base to press the large flat-panel satellite at the top downwards; the short clamping rod has a short clamping block at one end away from the half-height stacking column base to press the small flat-panel satellite at the top downwards.

5. The layout structure according to claim 4, characterized in that, The full-height stacking column and the half-height stacking column have grooves on their end faces away from their corresponding large or small flat-panel satellites to accommodate the long or short clamping rods.

6. The layout structure according to claim 3, characterized in that, The half-height stacking columns of the two small flat-panel satellites on the same side of each layer of the first vertical level along the stacking direction are staggered; when two small flat-panel satellites are laid flat, the half-height stacking column of one small flat-panel satellite is placed on the half-height stacking column on the same side of the other small flat-panel satellite.

7. The layout structure according to claim 6, characterized in that, In the stacking direction, one end of the half-height stacking column, which is provided corresponding to the two small flat-panel satellites in each layer of the first vertical level, protrudes to the side of the small flat-panel satellite to support it.

8. The layout structure according to claim 3, characterized in that, The two ends of the full-height stacking column along the stacking direction protrude to the two sides of the small or large flat-panel satellite opposite to it, so as to support the small or large flat-panel satellite.

9. The layout structure according to claim 4, characterized in that, Both the full-height stacked column base and the half-height stacked column base are equipped 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 long clamping rod or the short clamping rod; the torsion spring is disposed at the connection between the connecting rod and the long clamping rod or the short clamping rod; the separation connection device is disposed on the mounting base and is detachably connected to the end of the long clamping rod or the short clamping rod near the mounting base; When the long clamping rod or the short clamping rod clamps the large flat-panel satellite or the small flat-panel satellite, the large flat-panel satellite or the small flat-panel satellite is clamped by the separation connection device which is fixedly connected to the long clamping rod or the short clamping rod; after the separation connection device is separated from the long clamping rod or the short clamping rod, the torsion spring drives the connecting rod to rotate relative to the mounting base, so as to push the long clamping rod or the short clamping rod to swing away from the flat-panel satellite and release the large flat-panel satellite or the small flat-panel satellite.

10. A method for releasing a flat-panel satellite, wherein the satellite adopts the layout structure as described in claim 9, characterized in that, include: 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. 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. After the large flat-panel satellite has separated, the rocket sends an unlocking signal to the small flat-panel satellite. 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.

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