Satellite fixing structure based on vertical staggered stacking mode and mounting method

Abstract

The invention provides a satellite fixing structure based on a vertical staggered stacking mode and an installation method, and belongs to the technical field of satellites, and the fixing structure is composed of six rectangular structural plates, two inner partition plates and four force bearing columns. Wherein the six rectangular structural plates correspond to the six structural plates on the periphery of the satellite main frame, so that six surfaces of the satellite cuboid body are jointly formed; the first inner partition plate and the second inner partition plate are installed in the satellite body in a symmetrical state, and the internal space of the satellite body is divided into three areas. The first force bearing column, the second force bearing column, the third force bearing column and the fourth force bearing column are installed at four corners of the cuboid body. According to the scheme, all the devices can be reasonably installed while the form types of the devices carried by the networking satellite are improved, the space inside and outside the fixing structure is fully utilized, staggered stacking of the satellites on the upper layer and the lower layer is achieved through the fixing structure, and then the utilization rate of the space inside the fairing of the carrier rocket is effectively improved.

Description

Technical Field

[0001] This invention discloses a satellite fixing structure and installation method based on vertical staggered stacking, which is used for satellites launched in a multi-satellite launch mode. It promotes the realization of staggered stacking of satellites by using a simplified multi-plate splicing load-bearing structure and equipment layout method, thereby shortening the mass production cycle of satellites and significantly improving the space utilization rate inside the launch vehicle fairing. It belongs to the field of spacecraft structural design. Background Technology

[0002] To meet the construction requirements of satellite constellation networking, efficient mass production of satellites is necessary, followed by rapid deployment through multi-satellite launches. Currently, the launch methods for mass-produced satellites both domestically and internationally generally employ either a "parallel launch method with satellites mounted sideways around a central support tube" or a "tandem launch method with satellites stacked vertically without a central support tube." However, with the surge in demand for networking satellites and the increasing size of the launch vehicle fairing envelope, the "parallel launch method with satellites mounted sideways around a central support tube" suffers from limitations in terms of wasted space and mass. In contrast, the "tandem launch method with satellites stacked vertically without a central support tube" overcomes these shortcomings and is gradually becoming the mainstream launch method for large-scale networking satellites.

[0003] The current design of domestic stacked satellites mainly draws on the design concept of "Starlink satellites". Each satellite adopts a design scheme of three load-bearing columns distributed in an isosceles triangle and a flat plate with solar panels installed on one side. Each batch of satellites adopts a stacking method of "two satellites in the same layer rotated 180° and installed back to back, with the upper and lower layers of satellites maintaining a parallel and consistent state".

[0004] From an overall morphological perspective, a single satellite adopts a flat rectangular configuration with two large planes: one plane is the ground-facing plane, where the satellite's main equipment, including antennas for ground communication, is installed; the other plane is the celestial-facing plane, where the satellite's solar panels employ a single-wing, multi-fold design, folding and retracting into this plane during launch. The satellite's main structure uses an open design without sealed panels, with three load-bearing columns connecting to the main structure. Two of these columns are located at the ends of one long side of the satellite, and the third is located in the center of the other long side. The axes of the three columns are parallel to each other and perpendicular to the largest set of planes on the satellite, and the direction of these axes also corresponds to the stacking direction of the upper and lower satellite layers. During the stacking of multiple satellites, the upper and lower layers are stacked in the same direction, and their projections in the stacking direction completely overlap. Therefore, all equipment carried by the satellite must be flat, and the retracted solar panels must also lie within the stacking planes. The upper and lower satellites transfer forces to each other through their respective three load-bearing columns. Therefore, in order to improve the rigidity of a single satellite, as well as the overall rigidity of the multi-satellite assembly, high-rigidity reinforcing ribs need to be designed between each pair of the three load-bearing columns. These reinforcing ribs form an isosceles triangle, dividing the original rectangular space inside the satellite into three triangular regions: one large and two small. Some equipment on the satellite needs to be installed at an angle to accommodate the acute angles in these triangular regions.

[0005] However, existing stacking technologies have the following drawbacks:

[0006] (1) The solar array is retracted and installed on the satellite stacking plane, which increases the height of the satellite assembly in the stacking direction, but does not make good use of the space around the satellite assembly.

[0007] (2) In order to improve the rigidity of the satellite with a three-column design, a high reinforcing rib is often designed between any two columns, which is parallel to the axis of the column. The reinforcing ribs connected between the three columns form a triangular area, which is not conducive to the installation of the equipment and causes a waste of space.

[0008] (3) If the upper and lower satellites are stacked in a completely parallel manner, the equipment installed on the satellites must adopt a flat design or a "folded up at launch and deployed after entering orbit" form. The former will limit the installation of many types of equipment, such as helical antennas and rod antennas; the latter will increase the deployment mechanism, thereby increasing the weight of the satellite and reducing the overall reliability of the satellite.

[0009] (4) The solar array adopts a single-wing multi-fold design. After it is deployed into orbit, it will form a large flexible component on one side of the rigid body of the satellite, which will make it difficult to control the satellite's attitude.

[0010] (5) The satellite adopts an open design without a sealed structural panel, which exposes the onboard equipment directly to the space environment, increasing the intensity of radiation and reducing the service life of the equipment. Summary of the Invention

[0011] This invention discloses a satellite fixing structure and installation method based on a vertical staggered stacking method, including the composition and connection of the main load-bearing structure of the satellite, the layout and assembly sequence of the main equipment, and the stacking method of the upper and lower satellites.

[0012] The technical solution of this invention is as follows:

[0013] A satellite fixing structure based on a vertical staggered stacking method consists of six rectangular structural plates, two inner partitions and four load-bearing columns. The six rectangular structural plates include the six structural plates on the periphery of the satellite's main frame: +X plate, -X plate, +Y plate, -Y plate, +Z plate and -Z plate, which together constitute the six faces of the satellite's cuboid body.

[0014] The first and second inner partitions are installed symmetrically inside the satellite body and are fixedly connected to the +X plate, -X plate, +Z plate, and -Z plate respectively, dividing the internal space of the satellite body into three regions.

[0015] The first load-bearing column is fixedly connected to both the +X and +Y plates; the second load-bearing column is fixedly connected to both the -X and +Y plates; the third load-bearing column is fixedly connected to both the -X and -Y plates; and the fourth load-bearing column is fixedly connected to both the +X and -Y plates.

[0016] Wherein, +X direction is the satellite's on-orbit flight direction, +Z direction is the satellite's on-orbit direction relative to the Earth, and +Y direction, +X direction, and +Z direction satisfy the Cartesian coordinate system; Satellite body coordinate system: point O is located at the center of the surface of the -Z plate facing the +Z direction, Xb direction passes through point O and is parallel to the +X direction, Yb direction passes through point O and is parallel to the +Y direction, and Zb direction passes through point O and is parallel to the +Z direction.

[0017] An installation method, implemented based on the aforementioned satellite fixing structure with a vertical staggered stacking method, is used to achieve a symmetrical layout of satellite equipment and a vertical staggered stacking of multiple satellites. The installation method includes:

[0018] S110, the first phase of satellite assembly, includes: completing the installation of equipment inside the satellite on the -Z board, including a propulsion system, an integrated electronics unit, two laser communication payloads, two fiber optic gyroscopes, two flywheels, a data transmission unit, and a battery pack;

[0019] S120, the second phase of satellite assembly, includes: sequentially completing the installation of the first inner partition, the second inner partition, the +X plate, the -X plate, the +Y plate, the -Y plate, and the equipment inside the satellite on these structural plates, including two flywheels, two Earth remote sensing cameras, two magnetic rods, one microwave network, two GNSS filters, two magnetometers, and two solar panel drive mechanisms.

[0020] S130, the third phase of satellite assembly, includes: completing the installation of equipment on the +Z board, including one array antenna integrated processor, one helical transmitting antenna, one data transmission antenna, one rod antenna, one remote sensing data compression and processing unit, one ferrite rod, two feed transmitting antennas, two feed receiving antennas, and one telemetry and control antenna;

[0021] S140 completes the integration of the satellite + Z-plate assembly with the rest of the satellite, and then completes the installation of the remaining external equipment, including two folded solar panels, two GNSS antennas, two star sensors, one telemetry and control antenna, and one sun sensor.

[0022] S150: After the external equipment of the satellite is installed, install the first to fourth load-bearing columns;

[0023] S160, two satellites stacked, one above the other: the second satellite orbits Z. b After the shaft rotates 90° counterclockwise, it docks with the first satellite through the four supporting columns. The two satellites are offset from each other by the protruding parts on both sides of their ±Y directions, and the equipment in the overlapping areas maintains a suitable installation distance.

[0024] Beneficial effects:

[0025] This invention provides a satellite load-bearing structure based on a vertical staggered stacking method and the installation method of corresponding equipment. A single satellite adopts a design scheme with four load-bearing columns distributed in a square and solar panels installed on both sides. Two solar panels of the same area are folded together and hung on both sides of the far end of the satellite body, so that the satellite presents an overall shape of "flat in the middle and convex on both sides". Under the premise of maintaining the same or similar design form, the upper and lower satellites are docked according to the arrangement of the "protruding parts" on the satellites, which are rotated 90° around the central axis of the satellite stacking surface and staggered from each other. The mechanical docking and force transmission between the two satellites are completed through the load-bearing columns at the four corners of the satellite body, making the maximum use of the internal space of the fairing. The satellite's main structure comprises four pairs of identical structural plates assembled into a flat cuboid configuration. One pair of plates is larger in both dimensions, and most of the satellite's equipment is directly mounted on this pair. The other pair houses a smaller number of devices or equipment capable of independent testing. This third pair is designed as the final sealing plate for the entire satellite, ensuring that its removal allows operators to access any area inside the satellite. This improves the overall assembly and testing efficiency and maintainability of the satellite, and helps shorten the mass production cycle. Compared to satellites stacked in a similar "Starlink" configuration, this invention offers the following seven advantages:

[0026] (1) Compared with the triangular distribution of load-bearing columns, the quadrilateral distribution of load-bearing columns can reduce the number of diagonal braces in the main load-bearing structure, thereby reducing the triangular area in the internal space of the satellite, making the internal space of the satellite more square, which is conducive to the layout of internal equipment.

[0027] (2) By using a vertically staggered stacking method, "protrusions" on the satellite can be reasonably avoided, so that a single satellite does not need to be "flat" in all areas. This is conducive to the installation of "non-flat" equipment on the outside of the satellite, such as helical antennas, rod antennas, star sensors, etc., so that the satellite can carry more types of equipment.

[0028] (3) The symmetrical layout of the solar array is beneficial to the attitude control of the entire satellite;

[0029] (4) The solar wings are folded up on the two sides of the far end of the star, rather than on the surface used for stacking, which can further reduce the overall stacking height of the multi-stars and make full use of the space around the multi-star stacked assembly.

[0030] (5) The thrusters are positioned in the forward and backward directions of the satellite flight, so the satellite does not need to adjust its attitude when performing orbit control operations, thus reducing the impact on satellite service operations;

[0031] (6) The satellite retains traditional cover components, which prevents the internal equipment of the satellite from being directly exposed to the space environment, improves the radiation resistance of the entire satellite, and further enhances the lifespan of the entire satellite;

[0032] (7) The satellite structure adopts a “multi-plate splicing” form, which can reduce the cost of structural manufacturing, improve the replaceability and maintainability of the structure, and further improve the overall assembly efficiency of the satellite. Attached Figure Description

[0033] Figure 1 This is a schematic diagram of a satellite fixing structure based on a vertically staggered stacking method;

[0034] Figure 2 An exploded view of the satellite fixing structure based on a vertically staggered stacking method;

[0035] Figure 3 This is a schematic diagram showing the relative positions of the load-bearing columns;

[0036] Figure 4 A schematic diagram of the first stage of equipment installation;

[0037] Figure 5 Diagram showing the second phase of equipment installation;

[0038] Figure 6 This is a schematic diagram of the +Z board assembly installation.

[0039] Figure 7 Provide an overall layout diagram of the equipment installation;

[0040] Figure 8 A schematic diagram of the third stage of equipment installation (view 1);

[0041] Figure 9 A schematic diagram of the third stage of equipment installation (viewpoint 2);

[0042] Figure 10 This is a schematic diagram of the satellite's on-orbit status.

[0043] Figure 11 Slanted view of two stars stacked together Figure 1 ;

[0044] Figure 12 Top view of the two stars stacked together;

[0045] Figure 13 Slanted view of two stars stacked together Figure 2 ;

[0046] Figure 14 This is a schematic diagram of a multi-star stacked state. Detailed Implementation

[0047] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

[0048] This invention provides a satellite fixing structure based on a vertically staggered stacking method. Figure 1 This is a schematic diagram of a satellite fixing structure based on a vertically staggered stacking method; Figure 2 This is an exploded view of the satellite's fixed structure based on a vertically staggered stacking method. The coordinate system in the diagram is as follows: +X direction represents the satellite's orbital flight direction, +Z direction represents the satellite's orbital direction relative to the Earth, and +Y direction, +X direction, and +Z direction satisfy a Cartesian coordinate system; Satellite body coordinate system: Point O is located at the center of -Z plate 1-6 (the surface facing the +Z direction), X... b The direction passes through point O and is parallel to the +X direction, Y b The direction passes through point O and is parallel to the +Y direction, Z b The direction passes through point O and is parallel to the +Z direction.

[0049] like Figure 1 and Figure 2As shown, the satellite fixing structure based on the vertical staggered stacking method consists of six rectangular structural plates, two inner partitions, and four load-bearing columns. The six rectangular structural plates include the six structural plates surrounding the satellite's main frame: +X plate 1-1, -X plate 1-2, +Y plate 1-3, -Y plate 1-4, +Z plate 1-5, and -Z plate 1-6. Among them, +X plate 1-1 and -X plate 1-2 have the same length and width, +Y plate 1-3 and -Y plate 1-4 have the same length and width, and +Z plate 1-5 and -Z plate 1-6 have the same length and width. Furthermore, +X plate 1-1, -Y plate 1-4, -X plate 1-2, and +Y plate 1-3 have the same width and are fixedly connected to each other in the order of 1-1, 1-4, 1-2, and 1-3 in the width direction. +Z plate 1-5 and -Z plate 1-6 are connected to +X plate 1-1 and -X plate 1-2 through their length edges and to +Y plate 1-3 and -Y plate 1-4 through their width edges, thus forming the six faces of the satellite's cuboid body. The first inner partition 1-7 and the second inner partition 1-8 are installed symmetrically inside the satellite body, and are respectively fixedly connected to the +X plate 1-1, -X plate 1-2, +Z plate 1-5, and -Z plate 1-6, dividing the internal space of the satellite body into three regions. The first load-bearing column 1-9 is fixedly connected to both the +X plate 1-1 and the +Y plate 1-3, the second load-bearing column 1-10 is fixedly connected to both the -X plate 1-2 and the +Y plate 1-3, the third load-bearing column 1-11 is fixedly connected to both the -X plate 1-2 and the -Y plate 1-4, and the fourth load-bearing column 1-12 is fixedly connected to both the +X plate 1-1 and the -Y plate 1-4.

[0050] Among all the structural plates, +Z plate 1-5 and -Z plate 1-6 have the largest areas and are used to install the main equipment on the satellite. +Z plate 1-5 has multiple open interfaces for installing ground pointing equipment, including the main payload located at the center. The widths of +X plate 1-1, -X plate 1-2, +Y plate 1-3, and -Y plate 1-4 determine the height of the satellite's internal space. They are all designed with a large length-to-width ratio to keep the satellite body flat. The side of +X plate 1-1 near the fourth support column 1-12 and the side of -X plate 1-2 near the second support column 1-10 both have large rectangular notches to avoid inter-satellite communication laser communication payloads.

[0051] like Figure 2 and Figure 3As shown, the first to fourth load-bearing columns all adopt a "cylindrical tube + L-shaped corner piece" design. The upper and lower surfaces of the "cylindrical tube sections" of the four load-bearing columns are coplanar, and their axes are parallel. Let L1 be the distance between the first load-bearing column 1-9 and the second load-bearing column 1-10, and the distance between the third load-bearing column 1-11 and the fourth load-bearing column 1-12; and L2 be the distance between the second load-bearing column 1-10 and the third load-bearing column 1-11, and the fourth load-bearing column 1-12 and the first load-bearing column 1-9. Then, the distances between them satisfy L1 = L2.

[0052] This invention provides an installation method based on the aforementioned satellite fixing structure, used to achieve a symmetrical layout of satellite equipment and a vertically staggered stacking of multiple satellites. The installation method includes the following steps:

[0053] S110, such as Figure 4 As shown, the first phase of satellite assembly includes: completing the installation of equipment inside the satellite on the Z-board 1-6, including a propulsion system 2-1 (mainly composed of two thrusters 2-1-1 and two tanks 2-1-2, etc.), an integrated electronics unit 2-2, two laser communication payloads 2-3, two fiber optic gyroscopes 2-4, two flywheels 2-5, a data transmission unit 2-6, and a battery pack 2-7.

[0054] The axes of both thrusters 2-1-1 are located on the satellite's plane of symmetry (X). b OZ b Within the plane, they point to the ±X directions, i.e., the satellite's flight direction and the opposite direction, and the thruster axis passes through the satellite's center of mass in the initial state; the two sets of tanks 2-1-2 surround the Z-axis. b The axes are symmetrically distributed, and the propellant is consumed in opposite directions, causing the satellite's center of mass to be centered on the X-axis. b Direction and Y b The direction remains constant; the two laser communication payloads 2-3 orbit around Z. b The optical path is symmetrically distributed along the axis, with the front-end optical receiving and transmitting modules pointing to the ±X directions respectively, i.e., the satellite's flight direction and the opposite direction, facilitating inter-satellite laser communication; two fiber optic gyroscopes 2-4 orbit around the Z-axis. b The axes are symmetrically distributed around the center, with the three axes parallel to the satellite's X, Y, and Z directions, respectively; two flywheels 2-5 revolve around the Z-axis. bThe axes are approximately centrally symmetrically distributed. One flywheel 2-5 is directly mounted on the -Z plate 1-6, with its axis pointing in the +Z direction. The other flywheel 2-5 is obliquely mounted on the -Z plate 1-6 via a bracket, with its axis pointing in the direction of the sum of the unit vectors in the +X, +Y, and +Z directions. Among the equipment without special installation requirements, the heaviest integrated electronics 2-2 is mounted on one corner of the -Z plate 1-6 in the +X / +Y direction, while the relatively heavy data transmission unit 2-6 and battery pack 2-7 are mounted on the other corner of the -Z plate 1-6 in the -X / -Y direction.

[0055] S120, such as Figure 5 As shown, the second stage of satellite assembly includes: sequentially completing the installation of the first inner partition 1-7, the second inner partition 1-8, the +X plate 1-1, the -X plate 1-2, the +Y plate 1-3, the -Y plate 1-4, and the equipment located inside the satellite on these structural plates, including two flywheels 2-5, two Earth remote sensing cameras 2-8, two magnetic rods 2-9, one microwave network 2-10, two GNSS filters 2-11, two magnetometers 2-12, and two solar panel drive mechanisms 2-13.

[0056] Two flywheels 2-5 orbit around Z b The axes are approximately centrally symmetrically distributed. One flywheel 2-5 is directly mounted on the +X plate 1-1, with its axis pointing in the -X direction. The other flywheel 2-5 is directly mounted on the second inner partition 1-8, with its axis pointing in the Y direction. Two Earth-sensing cameras 2-8 are arranged around the Z-axis. b The axes are symmetrically distributed and installed on the first inner partition 1-7 and the second inner partition 1-8 respectively, with both axes pointing in the +Z direction; two magnetic rods 2-9 are installed on the first inner partition 1-7 and the second inner partition 1-8 respectively, one of which points axially in the +X direction and the other in the +Z direction; two magnetometers 2-12 are arranged around the Z-axis. b The axes are symmetrically distributed and installed on the +X plate 1-1 and -X plate 1-2 respectively (one of the magnetometers is located on...). Figure 5 The middle is obscured, in Figure 7 (As can be seen in the image), the three axes are parallel to the satellite's X, Y, and Z directions, respectively; the two solar panel drive mechanisms 2-13 are along the satellite's X... b OZ b The solar panels are symmetrically distributed and installed on the +Y plate 1-3 and -Y plate 1-4 respectively, with the axes of the two solar panel drive mechanisms 2-13 being coaxial and both located in the Y direction. b OZ b In-plane; two GNSS filters 2-11 surround Z. b The axes are symmetrically distributed and installed on the +X plate 1-1 and -X plate 1-2 respectively; the microwave network 2-10 is installed on the second inner partition 1-8.

[0057] S130, such as Figure 6 As shown, the third stage of satellite assembly includes: completing the installation of equipment on +Z board 1-5, including one array antenna integrated processor 2-15, one spiral transmitting antenna 2-16, one data transmission antenna 2-17, one rod antenna 2-18, one remote sensing data compression and processing unit 2-19, one ferrite rod 2-20, two fed transmitting antennas 2-21, two fed receiving antennas 2-22, and one telemetry and control antenna 2-23.

[0058] The array antenna integrated processor 2-15, serving as the satellite's main payload, integrates the traditional array receiving antenna and data processing lower-level unit into a single, flat design. It can be approximated as a sealing panel for the satellite, mounted precisely in the center of the +Z plate 1-5. The central axis of its array antenna section is aligned with the satellite's +Z plate. b The axes coincide and point towards the satellite's +Z direction; the helical transmitting antenna 2-16 is installed at one corner in the satellite's -X / +Y direction, while the rod antenna 2-18 is installed at the other corner in the satellite's +X / -Y direction, with the two arranged in an approximately symmetrical manner, and their axes both pointing towards the satellite's +Z direction; the data transmission antenna 2-17, the remote sensing data compression processing unit 2-19, and the ferrite rod 2-20 are concentrated in the region in the satellite's -X / -Y direction, with the data transmission antenna 2-17 also designed to be flat, and its installation method is the same as that of the array antenna integrated processor 2-15. The remote sensing data compression processing unit 2-19 and the ferrite rod 2-20 are both installed on the side of the +Z plate facing the satellite's interior, with the ferrite rod 2-20 maintaining its axial direction towards the satellite's +Y direction; since the height of the feed transmitting antenna 2-21, feed receiving antenna 2-22, and telemetry and control antenna 2-23 is relatively low, their installation restrictions are fewer. While meeting the requirements of the axis pointing towards the satellite's +Z direction and the overall electromagnetic compatibility of the satellite, their deployment positions are as follows: Figure 6 As shown, two fed transmitting antennas 2-21 and two fed receiving antennas 2-22 are symmetrically installed in the middle area of ​​the long side (edge ​​in the ±X direction) of the +Z plate 1-5, and the telemetry and control antenna 2-23 is installed on the edge in the +Y direction to reduce its obstruction by other satellites in the satellite stacking state, with its axis pointing towards the +Z direction of the satellite. The assembly of the +Z plate 1-5 assembly can be carried out simultaneously with the first and second phases of the above equipment installation.

[0059] Combination Figure 6 and Figure 7 It can be seen that the satellite's interior consists of a first inner partition 1-7, a second inner partition 1-8, and X... b OZ b Face and Y b OZ b The surface is divided into eight regions, and the total mass of the equipment in each region revolves around the satellite Z. bThe axes are approximately centrally symmetric. The total mass of region ① (mainly integrated electronics 2-2) and region ⑧ (mainly data transmission unit 2-6, battery pack 2-7, data transmission antenna 2-17, and remote sensing data compression processing unit 2-19) is similar. The total mass of region ② (mainly two upright flywheels 2-5) and region ⑦ (mainly one upright and one oblique flywheel 2-5) is similar. The total mass of region ③ (mainly one storage tank 2-1-2, one GNSS filter 2-11, and one magnetometer 2-12) and region ⑥ (mainly one storage tank 2-1-2, one GNSS filter 2-11, and one magnetometer 2-12) is similar. The total mass of region ④ (mainly one laser communication payload 2-3, one fiber optic gyroscope 2-4, and one Earth remote sensing camera 2-8) and region ⑤ (mainly one laser communication payload 2-3, one fiber optic gyroscope 2-4, and one Earth remote sensing camera 2-8) is similar. By arranging the main equipment as described above, and adjusting the positions of equipment without special installation requirements, the satellite's center of mass is positioned at Z. b On the axis.

[0060] S140, such as Figure 8 and Figure 9 As shown, after the +Z board assembly is combined with the satellite body, the remaining external equipment of the satellite is installed, including two folded solar panels 2-14, two GNSS antennas 2-24, two star sensors 2-25, one telemetry and control antenna 2-23 and one sun sensor 2-26.

[0061] Two of the folded solar panels, 2-14, are positioned along satellite X. b OZ b The antennas are symmetrically distributed and installed on the outer sides of the +Y plate 1-3 and -Y plate 1-4, respectively; the two GNSS antennas 2-24 are along the satellite Z-axis. b The antennas are symmetrically distributed along their axis and obliquely mounted on the outer sides of the +X plate 1-1 and -X plate 1-2 via brackets, with the antennas pointing towards the satellite X. b OZ b The planes are parallel, maintaining an angle of less than 90° with the satellite's Z-axis; the two star sensors 2-25 are along the satellite's Z-axis. b The axes are approximately centrally symmetrically distributed and obliquely mounted on the +X and +Y sides of the -Z plate 1-6 via supports, respectively, at the junction angles of the +X and -Y sides, maintaining alignment with the satellite X-axis. b OZ b The plane is parallel and maintains an angle of less than 90° with the satellite's -Z direction; the telemetry and control antenna 2-23 is installed on the edge of the +Y direction of the -Z plate 1-6 to reduce its obstruction by other satellites in the satellite stacking state, and its axis points towards the satellite's -Z direction; the sun sensor 2-26 is installed in the middle area of ​​the -Z plate 1-6 to provide a wider field of view when the satellite is working in orbit, and its axis points towards the satellite's -Z direction.

[0062] S150, after the external equipment of the satellite is installed, install the first to fourth load-bearing columns according to the diagram. After the satellite enters orbit, the two solar panels 2-14 deploy along the ±Y direction of the satellite and rotate around the axis of their respective connected solar panel drive mechanisms 2-13, as shown in the diagram. As shown.

[0063] S160, such as Figure 11 , Figure 12 , Figure 13 and Figure 14 As shown, two satellites are stacked, one above the other: the second satellite orbits Z-2. b After the shaft rotates 90° counterclockwise, it docks with the first satellite 3-1 through the four supporting columns. The two satellites are staggered from each other on both sides of the ±Y direction, and the equipment in the overlapping area is kept at a suitable installation distance.

[0064] The helical transmitting antenna 2-16 and rod antenna 2-18 in the +Z direction of the first satellite 3-1 are spatially offset from the laser communication payload 2-3 and GNSS antenna 2-24 protruding in the ±X direction of the second satellite 3-2, respectively. Similarly, the two star sensors 2-25 in the -Z direction of the second satellite 3-2 are spatially offset from the laser communication payload 2-3 and GNSS antenna 2-24 protruding in the ±X direction of the first satellite 3-1, respectively. The solar arrays 2-14 protruding on both sides of the first satellite 3-1 and the second satellite 3-2 are also spatially offset. All telemetry and control antennas 2-23 on the first and second satellites 3-1 are located in non-overlapping areas between the upper and lower satellites, avoiding obstruction by the satellites above and below, and facilitating communication between the ground and satellites in the event of anomalies in a stacked configuration.

[0065] Multiple satellites stacked in the form of Figure 14 As shown, taking the body coordinate system of the lowest-level first satellite 3-1 as a reference, starting from the first satellite 3-1 and moving upwards sequentially, all satellites revolve around the Z-axis. b The rotation angles (counterclockwise when viewed from top to bottom) are: 0°, 90°, 0°, 90°, 0°, 90°... When the number of satellites participating in the stacking is odd, the relative rotation angle between the last satellite and the bottommost satellite 3-1 is 0°; when the number of satellites participating in the stacking is even, the relative rotation angle between the last satellite and the bottommost satellite 3-1 is 90°. Since the center of mass of each satellite is located at its respective Z... b Therefore, the center of mass of the stacked assembly is always located on the longitudinal axis of the assembly.

[0066] The solar panels 2-14 of all satellites are distributed around the perimeter of the assembly, with only the flat satellite body overlapping. This further reduces the height of the assembly while making full use of the space around the fairing.

[0067] Numerous specific details are set forth in the specification provided herein. However, it will be understood that embodiments of the invention may be practiced without these specific details. In some instances, well-known methods, structures, and techniques have not been shown in detail so as not to obscure the understanding of this specification.

[0068] Although the invention has been described with respect to a limited number of embodiments, those skilled in the art will understand from the foregoing description that other embodiments are conceivable within the scope of the invention described herein. Furthermore, it should be noted that the language used in this specification has been chosen primarily for readability and instructional purposes, and not for the purpose of explaining or limiting the subject matter of the invention.

Claims

1. A satellite fixing structure based on a vertically staggered stacking method, characterized in that, It consists of six rectangular structural plates, two inner partitions and four load-bearing columns. The six rectangular structural plates include the six structural plates on the periphery of the satellite's main frame: +X plate (1-1), -X plate (1-2), +Y plate (1-3), -Y plate (1-4), +Z plate (1-5), and -Z plate (1-6), which together form the six faces of the satellite's cuboid body. The first inner partition (1-7) and the second inner partition (1-8) are installed symmetrically inside the satellite body. They are fixedly connected to the +X plate (1-1), -X plate (1-2), +Z plate (1-5), and -Z plate (1-6) respectively, dividing the internal space of the satellite body into three regions. The first load-bearing column (1-9) is fixedly connected to both the +X plate (1-1) and the +Y plate (1-3); the second load-bearing column (1-10) is fixedly connected to both the -X plate (1-2) and the +Y plate (1-3); the third load-bearing column (1-11) is fixedly connected to both the -X plate (1-2) and the -Y plate (1-4); and the fourth load-bearing column (1-12) is fixedly connected to both the +X plate (1-1) and the -Y plate (1-4). Among them, +X direction is the satellite's on-orbit flight direction, +Z direction is the satellite's on-orbit direction relative to the ground, +Y direction, +X direction, and +Z direction satisfy the Cartesian coordinate system; Satellite body coordinate system: point O is located at the center of the surface of the -Z plate (1-6) facing the +Z direction, Xb direction passes through point O and is parallel to the +X direction, Yb direction passes through point O and is parallel to the +Y direction, and Zb direction passes through point O and is parallel to the +Z direction.

2. The satellite fixing structure based on a vertically staggered stacking method according to claim 1, characterized in that, The +X plate (1-1) and -X plate (1-2) have the same length and width dimensions; the +Y plate (1-3) and -Y plate (1-4) have the same length and width dimensions; the +Z plate (1-5) and -Z plate (1-6) have the same length and width dimensions. The +X plate (1-1), -Y plate (1-4), -X plate (1-2), and +Y plate (1-3) have the same width and are fixedly connected to each other in the width direction in the order of +X plate (1-1), -Y plate (1-4), -X plate (1-2), and +Y plate (1-3). The +Z plate (1-5) and -Z plate (1-6) are connected to the +X plate (1-1), -Y plate (1-4), -X plate (1-2), and +Y plate (1-3) through their length edges. The X-plate (1-2) is connected to the +Y-plate (1-3) and -Y-plate (1-4) through its width-direction edge. Among all the structural plates, the +Z-plate (1-5) and -Z-plate (1-6) have the largest areas and are used to install the main equipment on the satellite. The +Z-plate (1-5) is designed with multiple open interfaces for installing ground pointing equipment, including the main payload located in the center. The +X-plate (1-1) near the fourth support column (1-12) and the -X-plate (1-2) near the second support column (1-10) are both designed with large rectangular notches to avoid the laser communication payload for inter-satellite communication.

3. The satellite fixing structure based on a vertically staggered stacking method according to claim 1, characterized in that, The first to fourth load-bearing columns all adopt the design form of "cylindrical tube + L-shaped corner piece". The upper end face and lower end face of the cylindrical tube part of the four load-bearing columns are coplanar. The axes of the cylindrical tube parts are parallel to each other. The distance between the first load-bearing column (1-9) and the second load-bearing column (1-10), and the distance between the third load-bearing column (1-11) and the fourth load-bearing column (1-12) are L1. The distance between the second load-bearing column (1-10) and the third load-bearing column (1-11), and the distance between the fourth load-bearing column (1-12) and the first load-bearing column (1-9) are L2. Then the distance between them satisfies L1=L2.

4. An installation method, characterized in that, Based on the satellite fixing structure according to any one of claims 1-3, a symmetrical layout of satellite equipment and vertical staggered stacking of multiple satellites are achieved, and the installation method includes: S110, the first phase of satellite assembly, includes: completing the installation of equipment inside the satellite on the -Z board (1-6), including a propulsion system (2-1), an integrated electronics unit (2-2), two laser communication payloads (2-3), two fiber optic gyroscopes (2-4), two flywheels (2-5), a data transmission unit (2-6), and a battery pack (2-7). S120, the second phase of satellite assembly, includes: sequentially completing the installation of the first inner partition (1-7), the second inner partition (1-8), the +X plate (1-1), the -X plate (1-2), the +Y plate (1-3), the -Y plate (1-4), and the equipment inside the satellite on these structural plates, including two flywheels (2-5), two Earth remote sensing cameras (2-8), two magnetic rods (2-9), one microwave network (2-10), two GNSS filters (2-11), two magnetometers (2-12), and two solar panel drive mechanisms (2-13). S130, the third phase of satellite assembly, includes: completing the installation of equipment on the +Z board (1-5), including one array antenna integrated processor (2-15), one helical transmitting antenna (2-16), one data transmission antenna (2-17), one rod antenna (2-18), one remote sensing data compression processing unit (2-19), one ferrite rod (2-20), two fed transmitting antennas (2-21), two fed receiving antennas (2-22), and one telemetry and control antenna (2-23). S140, complete the integration of the satellite + Z board assembly with other parts of the satellite, and then complete the installation of the remaining external equipment of the satellite, including two folded solar panels (2-14), two GNSS antennas (2-24), two star sensors (2-25), one telemetry and control antenna (2-23) and one sun sensor (2-26). S150: After the external equipment of the satellite is installed, install the first to fourth load-bearing columns; S160, stacking two satellites: the second satellite (3-2) orbits Z. b After the shaft rotates 90° counterclockwise, it docks with the first satellite (3-1) through the four supporting columns. The two satellites are offset from each other by the protruding parts on both sides of their ±Y directions, and the equipment in the overlapping areas of the upper and lower parts maintains a suitable installation distance.

5. The installation method according to claim 4, characterized in that, S110 includes: two thrusters (2-1-1) whose axes are both located on the satellite's plane of symmetry (X). b OZ b Within the plane, the thrusters point to the ±X directions, which are the satellite's flight direction and the opposite direction, respectively, and the thruster axis passes through the satellite's center of mass in the initial state; the two tanks (2-1-2) surround the Z-axis. b The axes are symmetrically distributed, and the propellant is consumed in opposite directions, causing the satellite's center of mass to be located in the X-axis during operation. b Direction and Y b The direction remains constant; the two laser communication payloads (2-3) revolve around Z. b The optical path is symmetrically distributed along the axis, with the front-end optical receiving and transmitting modules pointing to the ±X directions respectively, i.e., the satellite's flight direction and the opposite direction, facilitating inter-satellite laser communication; two fiber optic gyroscopes (2-4) revolve around the Z-axis. b The axes are symmetrically distributed around the center, with the three axes parallel to the satellite's X, Y, and Z directions, respectively; two flywheels (2-5) revolve around the Z-axis. b The axes are approximately centrally symmetrically distributed. One flywheel (2-5) is directly mounted on the -Z plate (1-6) with its axis pointing in the +Z direction. The other flywheel (2-5) is obliquely mounted on the -Z plate (1-6) via a bracket, with its axis pointing in the direction of the sum of the unit vectors in the +X, +Y, and +Z directions. Among the equipment without special installation requirements, the heaviest integrated electronics (2-2) is mounted on one corner of the -Z plate (1-6) in the +X / +Y direction, while the relatively heavy data transmission unit (2-6) and battery pack (2-7) are mounted on the other corner of the -Z plate (1-6) in the -X / -Y direction.

6. The installation method according to claim 4, characterized in that, S120 includes: two flywheels (2-5) surrounding Z. b The axes are approximately centrally symmetrically distributed. One flywheel (2-5) is directly mounted on the +X plate (1-1), with its axis pointing in the -X direction. The other flywheel (2-5) is directly mounted on the second inner partition (1-8), with its axis pointing in the Y direction. Two Earth remote sensing cameras (2-8) are arranged around the Z-axis. b The axes are symmetrically distributed and installed on the first inner partition (1-7) and the second inner partition (1-8), respectively, with both axes pointing in the +Z direction; two magnetic rods (2-9) are installed on the first inner partition (1-7) and the second inner partition (1-8), respectively, with one axially pointing in the +X direction and the other axially pointing in the +Z direction; two magnetometers (2-12) are arranged around the Z-axis. b The axes are symmetrically distributed and installed on the +X plate (1-1) and -X plate (1-2) respectively, with the three axes parallel to the X, Y, and Z directions of the satellite; the two solar panel drive mechanisms (2-13) are along the X direction of the satellite. b OZ b The solar panels are symmetrically distributed and mounted on the +Y plate (1-3) and -Y plate (1-4) respectively. The axes of the two solar panel drive mechanisms (2-13) are coaxial and both are located in the Y direction. b OZ b In-plane; two GNSS filters (2-11) surround Z b The axes are symmetrically distributed and installed on the +X plate (1-1) and -X plate (1-2) respectively; the microwave network (2-10) is installed on the second inner partition (1-8).

7. The installation method according to claim 4, characterized in that, S130 includes: an array antenna integrated processor (2-15) mounted as the satellite's main payload in the center of the +Z plate (1-5), with the central axis of its array antenna section aligned with the satellite's +Z plate. b The axes coincide and point towards the satellite's +Z direction; the helical transmitting antenna (2-16) is installed at the boundary angle between the satellite's -X and +Y directions, while the rod antenna (2-18) is installed at the boundary angle between the satellite's +X and -Y directions, with their axes both pointing towards the satellite's +Z direction; the data transmission antenna (2-17), remote sensing data compression processing unit (2-19), and ferrite rod (2-20) are concentrated in the boundary area between the satellite's -X and -Y directions. The data transmission antenna (2-17) is installed in the same way as the array antenna integrated processor (2-15). The sensing data compression processing unit (2-19) and the ferrite rod (2-20) are both installed on the side of the +Z plate facing the inside of the satellite, with the ferrite rod (2-20) keeping its axis facing the +Y direction of the satellite; two feed transmitting antennas (2-21) and two feed receiving antennas (2-22) are symmetrically installed in the middle area of ​​the long side of the +Z plate (1-5), with their axes pointing towards the +Z direction of the satellite; the telemetry and control antenna (2-23) is installed on the edge of the +Y direction to reduce its obstruction by other satellites in the satellite stacking state, and its axis points towards the +Z direction of the satellite.

8. The installation method according to claim 4, characterized in that, S140 includes: two folded solar panels (2-14) along the satellite X b OZ b The antennas are symmetrically distributed and installed on the outer sides of the +Y plate (1-3) and -Y plate (1-4), respectively; two GNSS antennas (2-24) are positioned along the Z-axis of the satellite. b The antennas are symmetrically distributed along their axis and obliquely mounted on the outer sides of the +X plate (1-1) and -X plate (1-2) via brackets, with the antennas pointing towards the satellite X. b OZ b The planes are parallel, maintaining an angle of less than 90° with the satellite's Z-axis; the two star sensors (2-25) are aligned along the satellite's Z-axis. b The axes are approximately centrally symmetrically distributed and obliquely mounted on the +X and +Y sides of the -Z plate (1-6) via supports at the junction angles of the +X and -Y sides, respectively, maintaining the axes aligned with the satellite's X-axis. b OZ b The plane is parallel and maintains an angle of less than 90° with the satellite's -Z direction; the telemetry and control antenna (2-23) is installed on the edge of the +Y direction of the -Z plate (1-6) to reduce its obstruction by other satellites in the satellite stacking state, and its axis points to the satellite's -Z direction; the sun sensor (2-26) is installed in the middle area of ​​the -Z plate (1-6) to provide a wider field of view when the satellite is working in orbit, and its axis points to the satellite's -Z direction.

9. The installation method according to claim 4, characterized in that, S160 includes: the helical transmitting antenna (2-16) and rod antenna (2-18) in the +Z direction of the first satellite (3-1) are spatially offset from the laser communication payload (2-3) and GNSS antenna (2-24) protruding in the ±X direction of the second satellite (3-2); the two star sensors (2-25) in the -Z direction of the second satellite (3-2) are spatially offset from the laser communication payload (2-3) and GNSS antenna (2-24) protruding in the ±X direction of the first satellite (3-1); the solar arrays (2-14) protruding on both sides of the first satellite (3-1) and the solar arrays (2-14) protruding on both sides of the second satellite (3-2) are also spatially offset from each other; all telemetry and control antennas (2-23) on the first satellite (3-1) and the second satellite (3-2) are located in the non-overlapping area of ​​the upper and lower satellites to avoid being blocked by the upper and lower satellites.

10. The installation method according to claim 4, characterized in that, Also includes: Multiple satellites stacked: Taking the body coordinate system of the bottommost first satellite (3-1) as a reference, starting from the first satellite (3-1) and moving upwards sequentially, all satellites orbit Z. b The rotation angles of the axis are: 0°, 90°, 0°, 90°, 0°, 90°, and so on.

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