A triangular prism - type modular microsatellite configuration

Abstract

The present invention discloses a triangular prism - type modular micro - satellite configuration. It adopts a modular symmetric design, which is convenient for overall installation, can balance the center of gravity of the satellite, and is beneficial to attitude control. Based on the triangular prism structure design, it provides good stability. It adopts a multi - functional structural board design, integrating functional components with the structure, reducing the overall weight of the satellite and lowering costs. The PMI foam - filled battery pack design can reduce weight and keep the battery warm. Through the cooperation and connection of the connecting pin plates, positioning pin slots and chutes on the modules, it can be conveniently assembled and installed as well as interconnected with multiple satellites. The mutual cooperation of the movable phased - array antenna and the fixed phased - array antenna can increase the antenna coverage and maneuverability. After the solar panels are deployed, they can cover the satellite payloads to facilitate heat dissipation. Multiple satellites are interconnected to form a satellite array to meet the coverage of a larger area. Through connection around the cylindrical satellite distribution device, multi - satellite stacked launch can be achieved, reducing the satellite launch cost.

Description

Technical Field

[0001] The present invention belongs to the technical field of microsatellites, and particularly relates to a triangular prism - type modular micro - satellite configuration. Background Technique

[0002] With the development of commercial space technology, domestic commercial space companies have grown rapidly like bamboo shoots after a spring rain. Commercial spacecraft are mainly micro - satellites, which are characterized by light weight, small volume, low cost, high functional density, etc. With the development of industrial technology and the application of some new devices, new materials and new processes, satellite instrumentation has a trend of miniaturization, integration and light - weight. The application of micro - satellites is becoming more and more extensive, and the annual launch volume is growing rapidly. The development of commercial satellites is market - oriented, aiming to maximize profits. Therefore, the development cost of satellites is a key factor restricting the commercialization of micro - satellites. Then, how to significantly reduce the launch cost of small satellites has become a research trend.

[0003] Generally, the configurations of medium - large satellites generally use load - bearing cylinders as the main structure, and micro - satellites generally use truss box - plate configurations, both of which have problems such as high production cost, long assembly time, and difficulty in establishing mass - production lines. With the large - scale deployment of satellite constellations by commercial space enterprises represented by SpaceX and OneWeb, domestic commercial space companies have also followed suit and carried out the research and development of low - cost and rapidly deployable micro - satellites. Due to the limited low - earth - orbit frequency resources and orbital position resources, according to the principle of "first come, first served", a large number of satellites need to be launched as soon as possible to seize low - earth - orbit resources. This has put forward new requirements for satellite design, production, manufacturing, etc., such as low cost, rapid assembly, modular mass production, etc. To effectively address the challenges brought by rapidly mass - producing satellites, it is necessary to optimize the configuration design of satellites from first - principles, break the traditional satellite design ideas, and focus on aspects such as low cost, rapid assembly and modular design.

[0004] Currently, medium - large satellites generally adopt a configuration with a load - bearing cylinder as the main structure, and micro - satellites generally adopt a truss box - plate configuration, both of which have problems such as high production cost, long assembly time, and difficulty in establishing a mass - production line. Summary of the Invention

[0005] The purpose of the present invention is to provide a triangular prism - type modular micro - satellite configuration to solve the problems raised in the above - mentioned background technique.

[0006] To achieve the above - mentioned purpose, the present invention provides the following technical solution: A triangular prism - type modular micro - satellite configuration, including an energy module, a sub - platform module and a payload module. Sub - platform modules are fixedly installed at both ends of the energy module. Payload modules are fixedly installed at the outer ends of the sub - platform modules. A solar panel module is hinged to the upper end of the energy module through a hinge. The cross - sections of the energy module, the sub - platform module and the payload module are all triangular and have the same shape.

[0007] Preferably, the energy module includes a first frame. An MPPT functional structure board and a battery management functional structure board are embedded in the front inclined surface of the first frame. A distributor functional structure board and a power supply computer functional structure board are embedded in the rear inclined surface of the first frame. A lithium-ion battery module is radially inserted into the first frame. The lithium-ion battery module is composed of lithium-ion battery cores assembled. PMI foam is filled in the gap between the lithium-ion battery module and the first frame.

[0008] Preferably, the sub-platform module includes a second frame. Data acquisition functional structure boards are embedded in both the front inclined surface and the rear inclined surface of the second frame. An attitude control functional structure board is fixedly installed on the inner wall of the second frame. Positioning pin slots are opened at three vertex corners of the second frame. Connecting pin plates are embedded in the positioning pin slots. Three groups of screw holes are opened on the connecting pin plates, and the middle screw hole is installed in the positioning pin slot through a bolt.

[0009] Preferably, the payload module includes a third frame. A high-performance computing unit is fixedly installed in the third frame. Shielding structure boards are embedded in both the front inclined surface and the rear inclined surface of the third frame. Active phased array antennas are hinged to both bottom edges on both sides of the third frame through movable hinges. The active phased array antennas are stored in the front inclined surface and the rear inclined surface of the third frame. A fixed phased array antenna is embedded in the bottom surface of the third frame.

[0010] Preferably, first chutes are opened at three vertex corners of the first frame. The cross-sectional structure of the first chutes is the same as that of the positioning pin slots. Fixed mounting screw holes are opened in the first chutes of the first frame.

[0011] Preferably, second chutes are opened at three vertex corners of the third frame. The cross-sectional structure of the second chutes is the same as that of the positioning pin slots. Fixed mounting screw holes are opened in the second chutes of the third frame.

[0012] Preferably, the first frame, the second frame and the third frame are all made of aluminum alloy material or manufactured by metal foam printing.

[0013] Preferably, the solar panel module consists of two pieces, namely the south wing and the north wing. The transverse width of each wing plate is the distance between the outer end faces of the two payload modules. One-sided wing plate of the solar panel module is hinged by a number of sub-unit modules. The extended length of one-sided wing plate of the solar panel module is greater than the perimeter of the energy module.

[0014] Preferably, the coverage direction of the fixed phased array antenna is changed by the change of the orientation through the satellite body, and the orientation of the active phased array antenna is adjusted through the connection of the hinge.

[0015] Preferably, the load module can be interconnected through a connecting pin plate and a second sliding groove.

[0016] Preferably, the first frame, the second frame, and the third frame all have a regular triangular cross-section structure.

[0017] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0018] 1. By adopting a symmetric design, the center of gravity of the satellite can be balanced, making the mass distribution of the satellite more uniform, which is beneficial to the attitude control of the satellite.

[0019] 2. Based on the triangular cross-section structure of the first frame, the second frame, and the third frame, good stability is provided. Moreover, it is made of aluminum alloy processing or metal foam printing, which reduces the weight, lowers the processing cost, and cooperates with the internal structure to strengthen the overall structure.

[0020] 3. By using lithium-ion batteries, the storage density is increased, and the PMI foam has the advantages of light weight, easy processing, and low cost.

[0021] 4. Based on the materials of the first frame, the second frame, and the third frame and in cooperation with each functional structural board, the heat dissipation effect of the device can be guaranteed to meet the heat dissipation requirements of high-power circuits.

[0022] 5. Through the cooperation of the connecting pin plate with the positioning pin groove, the first sliding groove, and the second sliding groove, an overall connection structure is formed, which is convenient for combination.

[0023] 6. By adopting the distribution mode of the movable phased array antenna and the fixed phased array antenna, it can be deployed in orbit according to instructions and the antenna direction can be changed through the movable hinge, so as to achieve beam coverage of a specific area without performing a whole-satellite maneuver.

[0024] 7. Through the deployment and coverage of the solar panel, it can effectively shield the satellite body and the deployable antenna, which is beneficial to the heat dissipation of the satellite thermal control system.

[0025] 8. It is convenient to combine two or more to form a satellite array to meet the coverage of a larger area.

[0026] 9. It is convenient to launch multiple satellites in one rocket, which can greatly reduce the launch cost and launch cycle of a single satellite. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 is a three-dimensional structural schematic diagram of the present invention;

[0028] Figure 2 is a three-dimensional structural schematic diagram of the energy module of the present invention;

[0029] Figure 3 is a three-dimensional structural schematic diagram of the sub-platform module of the present invention;

[0030] Figure 4 Schematic three-dimensional structure diagram of the payload module of the present invention;

[0031] Figure 5 Schematic top view of multi-satellite interconnection in orbit of the present invention;

[0032] Figure 6 Schematic bottom view of multi-satellite interconnection in orbit of the present invention;

[0033] Figure 7 Schematic layout diagram of multi-satellite launch of the present invention.

[0034] In the figure: 1. Energy module, 1-1. First frame, 1-2. MPPT functional structure board, 1-3. Battery management functional structure board, 1-4. Lithium-ion battery module, 1-5. Lithium-ion battery cell, 1-6. PMI foam; 1-7. Distributor functional structure board; 18. Power supply computer functional structure board, 2. Sub-platform module, 2-1. Connecting pin board, 2-2. Second frame, 2-3. Attitude control functional structure board, 2-4. Positioning pin slot, 2-5. Data acquisition functional structure board, 2-6. Bolt, 3. Payload module, 3-1. Third frame; 3-2. Shielding structure board, 3-3. High-performance computing unit, 3-4. Fixed phased array antenna, 3-5. Movable hinge, 3-6. Movable phased array antenna, 4. Solar panel module. Detailed implementation manners

[0035] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention. Embodiment

[0036] Please refer to Figure 1-7 , the present invention provides a technical solution: a triangular prism-shaped modular micro-satellite configuration, including an energy module 1, a sub-platform module 2 and a payload module 3. The sub-platform modules 2 are fixedly installed at both ends of the energy module 1, the payload module 3 is fixedly installed at the outer end of the sub-platform module 2, the solar panel module 4 is hinged to the upper end of the energy module 1 through a hinge, and the cross-sections of the energy module 1, the sub-platform module 2 and the payload module 3 are all triangular and have the same shape.

[0037] The energy module 1 stores the surplus electric energy obtained by the solar panel module 4 under illumination. The sub-platform module 2 connects and combines the energy module 1 with the payload module 3 through itself, and at the same time controls the orbit and attitude of the satellite through the built-in functional components. The payload module 3 is the main auxiliary structure for satellite functions.

[0038] Specifically, the energy module 1 includes a first frame 1-1. The front inclined surface of the first frame 1-1 is embedded with an MPPT functional structure board 1-2 and a battery management functional structure board 1-3. The rear inclined surface of the first frame 1-1 is embedded with a distributor functional structure board 1-7 and a power supply computer functional structure board 1-8. A lithium-ion battery module 1-4 is radially inserted into the first frame 1-1. The lithium-ion battery module 1-4 is assembled by lithium-ion battery cores 1-5. A PMI foam 1-6 is filled in the gap between the lithium-ion battery module 1-4 and the first frame 1-1.

[0039] The first frame 1-1 is the basic frame installation structure of the energy module 1. The MPPT functional structure board 1-2, the battery management functional structure board 1-3, the distributor functional structure board 1-7, and the power supply computer functional structure board 1-8 are all multi-functional structure boards that are respectively composed of an MPPT module, battery management, a distributor, and a power supply computer. The required functions are realized based on the MPPT module, battery management, distributor, and power supply computer. The lithium-ion battery module 1-4 stores the surplus electric energy. The filling of the PMI foam 1-6 can effectively saturate the internal gap and avoid the influence of the gap.

[0040] Specifically, the sub-platform module 2 includes a second frame 2-2. The front inclined surface and the rear inclined surface of the second frame 2-2 are both embedded with data acquisition functional structure boards 2-5. An attitude control functional structure board 2-3 is fixedly installed on the inner wall of the second frame 2-2. Positioning pin slots 2-4 are opened at three vertex corners of the second frame 2-2. Connecting pin plates 2-1 are embedded in the positioning pin slots 2-4. The connecting pin plates 2-1 are provided with three groups of screw holes. The middle screw hole is installed in the positioning pin slot 2-4 through a bolt 2-6.

[0041] The second frame 2-2 is the installation foundation of the sub-platform module 2. The data acquisition functional structure board 2-5 and the attitude control functional structure board 2-3 are both composed of a data acquisition module and an attitude control module respectively installed on a multi-functional structure board. The data acquisition module collects the current orbit and attitude data of the satellite. The attitude control module compares the data collected by the data acquisition module with the set parameters, so as to adjust the orbit and attitude of the satellite.

[0042] Specifically, the load module 3 includes a third frame 3-1. A high-performance computing unit 3-3 is fixedly installed inside the third frame 3-1. Shielding structure plates 3-2 are embedded on both the front inclined surface and the rear inclined surface of the third frame 3-1. The bottom edges on both sides of the third frame 3-1 are hinged with movable phased array antennas 3-6 through movable hinges 3-5. The movable phased array antennas 3-6 are received inside the front inclined surface and the rear inclined surface of the third frame 3-1. A fixed phased array antenna 3-4 is embedded on the bottom surface of the third frame 3-1.

[0043] The third frame 3-1 is the installation basic structure of the load module 3. The high-performance computing unit 3-3 is the core component for the satellite to achieve its main functions and is manufactured according to design requirements. The shielding structure plates 3-2 shield and protect the internal space of the third frame 3-1. The movable phased array antennas 3-6 hinged through the movable hinges 3-5 can be adjusted at a certain angle based on their own structural design, and the fixed phased array antenna 3-4 is adjusted along with the overall attitude. The two cooperate with each other to receive signals in different frequency bands.

[0044] Specifically, first chutes are opened at the three top corners of the first frame 1-1. The cross-sectional structure of the first chutes is the same as that of the positioning pin slots 2-4. Mounting screw holes are opened in the first chutes of the first frame 1-1.

[0045] Through the cross-sectional design of the first chutes and the positioning pin slots 2-4, the smoothness and boundary of the overall connection can be ensured.

[0046] Specifically, second chutes are opened at the three top corners of the third frame 3-1. The cross-sectional structure of the second chutes is the same as that of the positioning pin slots 2-4. Mounting screw holes are opened in the second chutes of the third frame 3-1.

[0047] Through the cross-sectional design of the second chutes and the positioning pin slots 2-4, the smoothness and boundary of the overall connection can be ensured.

[0048] Specifically, the first frame 1-1, the second frame 2-2, and the third frame 3-1 are all made of aluminum alloy material or manufactured by metal foam printing.

[0049] Through the material setting, the overall quality is ensured to be light and the strength meets the requirements, while ensuring the effect of heat conduction.

[0050] Specifically, the solar panel module 4 consists of two pieces, namely the south wing and the north wing. The transverse width of each wing plate is the distance between the outer end faces of the two load modules 3. One-sided wing plate of the solar panel module 4 is hinged by a number of sub-unit modules. The extended length of one-sided wing plate of the solar panel module 4 is greater than the perimeter of the energy module 1.

[0051] Through the articulation of several sub-modules, the entire solar panel module 4 can be freely extended. The length of the solar panel module 4 is set to effectively cover the whole satellite and provide sunshade protection between the fixed phased array antenna 3-4 and the movable phased array antenna 3-6.

[0052] Specifically, the coverage direction of the fixed phased array antenna 3-4 changes by varying its orientation through the satellite body, and the orientation of the movable phased array antenna 3-6 is adjusted through the connection of hinges.

[0053] By arranging the fixed phased array antenna 3-4 and the movable phased array antenna 3-6, the overall antenna signal can be effectively covered to ensure the reception effect.

[0054] Specifically, the payload module 3 can be interconnected through the connecting pin plate 2-1 and the second sliding groove.

[0055] The combined connection of the payload module 3 through the connecting pin plate 2-1 and the second sliding groove enables a single satellite body to be grouped in several numbers, and then to cover a larger area.

[0056] Specifically, the first frame 1-1, the second frame 2-2 and the third frame 3-1 are all of a quasi-regular triangular cross-section structure.

[0057] Through the design of the quasi-regular triangular cross-section, the single satellite bodies can be circularly combined and distributed. At the same time, based on the payload module 3, they can be connected in series, thus ensuring the convenience of multiple satellites in one launch.

[0058] Working principle: After entering the predetermined orbit, after the solar panel module 4 is deployed, it supplies electrical energy to the device and stores the remaining electrical energy between the energy modules 1 for backup. The ground remote control signal is received through the fixed phased array antenna 3-4 and the movable phased array antenna 3-6 of the payload module 3. The sub-platform module 2 adjusts the regulations and attitudes of the satellite based on the data acquisition functional structure board 2-5 and the attitude control functional structure board 2-3.

[0059] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A triangular prism - type modular microsatellite configuration, comprising an energy module (1), a sub - platform module (2) and a payload module (3), characterized in that: Both ends of the energy module (1) are fixedly installed with sub-platform modules (2), the outer ends of the sub-platform modules (2) are fixedly installed with payload modules (3), the upper end of the energy module (1) is hinged with a solar panel module (4) through a hinge, and the cross-sections of the energy module (1), the sub-platform module (2) and the payload module (3) are all triangular and have the same shape; The energy module (1) includes a first frame (1-1), an MPPT functional structure board (1-2) and a battery management functional structure board (1-3) are embedded on the front inclined surface of the first frame (1-1), a distributor functional structure board (1-7) and a power supply computer functional structure board (1-8) are embedded on the rear inclined surface of the first frame (1-1), a lithium-ion battery module (1-4) is radially inserted into the first frame (1-1), the lithium-ion battery module (1-4) is assembled by lithium-ion battery cores (1-5), and PMI foam (1-6) is filled in the gap between the lithium-ion battery module (1-4) and the first frame (1-1); The sub-platform module (2) includes a second frame (2-2), data acquisition functional structure boards (2-5) are embedded on both the front inclined surface and the rear inclined surface of the second frame (2-2), an attitude control functional structure board (2-3) is fixedly installed on the inner wall of the second frame (2-2), positioning pin slots (2-4) are opened at the three vertex corners of the second frame (2-2), connection pin plates (2-1) are embedded in the positioning pin slots (2-4), the connection pin plates (2-1) are provided with three groups of screw holes, and the middle screw hole is installed in the positioning pin slot (2-4) through a bolt (2-6); The payload module (3) includes a third frame (3-1), a high-performance computing unit (3-3) is fixedly installed in the third frame (3-1), shielding structure boards (3-2) are embedded on both the front inclined surface and the rear inclined surface of the third frame (3-1), active phased array antennas (3-6) are hinged and movably connected to both bottom edges of the third frame (3-1) through movable hinges (3-5), the active phased array antennas (3-6) are received in the front inclined surface and the rear inclined surface of the third frame (3-1), and a fixed phased array antenna (3-4) is embedded on the bottom surface of the third frame (3-1).

2. A triangular prism type modular small satellite configuration according to claim 1, characterized in that: First chutes are opened at the three vertex corners of the first frame (1-1), and the cross-sectional structure of the first chutes is the same as that of the positioning pin slots (2-4), and fixed mounting screw holes are opened in the first chutes of the first frame (1-1).

3. A triangular prism type modular small satellite configuration according to claim 1, characterized in that: Second chutes are opened at the three vertex corners of the third frame (3-1), and the cross-sectional structure of the second chutes is the same as that of the positioning pin slots (2-4), and fixed mounting screw holes are opened in the second chutes of the third frame (3-1).

4. The triangular prism type modular small satellite configuration according to claim 1, characterized in that: The first frame (1-1), the second frame (2-2) and the third frame (3-1) are all made of aluminum alloy material or manufactured by metal foam printing.

5. A triangular prism type modular small satellite configuration according to claim 1, characterized in that: The solar panel module (4) consists of two wings, namely the south wing and the north wing. The transverse width of each wing is the distance between the outer end faces of the two payload modules (3). One side wing of the solar panel module (4) is hinged by a number of sub-unit modules, and the extended length of one side wing of the solar panel module (4) is greater than the perimeter of the energy module (1).

6. The triangular prism type modular micro-satellite configuration according to claim 1, characterized in that: The fixed phased array antenna (3-4) changes the coverage direction by changing the orientation through the satellite body, and the movable phased array antenna (3-6) adjusts the orientation through the connection of hinges.

7. The triangular prism type modular micro-satellite configuration according to claim 1, characterized in that: The payload modules (3) can be interconnected through the connecting pin plates (2-1) and the second chutes.

8. The triangular prism type modular micro-satellite configuration according to claim 4, characterized in that: The first frame (1-1), the second frame (2-2) and the third frame (3-1) all have a cross-sectional structure similar to an equilateral triangle.

Images