Quickly-spliced subminiature satellite platform
Through the three-stage sub-cabin design and unified interface ultra-small satellite platform, the problem of the lack of rapid adaptation and upgrade of the existing ultra-small satellite design is solved, and the lightweight and modular design is achieved, which improves task flexibility and adaptability.
Patent Information
- Application Number
- CN202510245125.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-04
- Publication Date
- 2025-06-20
AI Technical Summary
The existing ultra-small satellite design lacks the ability to quickly adapt and adjust, and is difficult to quickly replace and upgrade, and is difficult to achieve the lightweight goal of less than 5kg. The lack of modular design leads to poor task flexibility and low adaptability.
It adopts a three-stage sub-cabin design, including GNC cabin section, propulsion cabin section and electronic cabin section, and achieves rapid assembly and functional upgrade through unified mechanical and electrical interfaces. The propulsion cabin section adopts an integrated design of storage box thrust, and the electronic cabin section includes a star computer, a battery, a GNSS antenna and an inter-star communication antenna.
It improves the modularity of the satellite, reduces the integration and interface complexity of a single machine, realizes rapid assembly and function upgrades of small satellites, reduces the quality to less than 4kg, and improves applicability and production efficiency.
Smart Images
Figure CN120171786A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the field of satellite aerospace technology, and particularly relates to an ultra-small satellite platform with rapid splicing.
Background Art
[0002] Due to the pursuit of high integration and lightweight in small satellites, the layout design features systematic integrity, with each subsystem deeply coupled. Different single units are compactly arranged according to requirements such as thermal control, mass, and energy. Once the system design is formed, it is difficult to make major changes. Similarly, for the miniaturization of satellites, due to the overall design of the highly integrated system, it is difficult to carry out a high degree of modular design, resulting in poor mission flexibility, low adaptability, slow response speed to different mission requirements, and a lack of a relatively fast self-reconfiguration and upgrade ability. Specifically, the existing small satellites have the following problems:
[0003] 1. The layout design of satellites is usually highly integrated, and modular design is mostly reflected in the combination of some single units or the whole satellite, lacking the ability to quickly adapt and adjust the composition at the subsystem level of a single satellite.
[0004] 2. For existing small satellites with complete systems, due to the high integration brought about by miniaturization, it is difficult to quickly replace and upgrade them.
[0005] 3. Currently, it is very difficult to miniaturize satellites with complete guidance, navigation, attitude control, orbit control, and payload capabilities to less than 5 kg.
[0006] 4. The integrated modular design of subsystems in small satellites is difficult and relatively scarce.
[0007] 5. Currently, it is difficult for small satellites to quickly achieve capacity upgrades and payload replacements, and it is difficult to mass-produce them.
[0008] In view of the technical problems of the existing ultra-small satellite design lacking the ability to quickly adapt and adjust and being difficult to quickly replace and upgrade, the present invention has made technical improvements to the ultra-small satellite platform.
Summary of the Invention
[0009] The object of the present invention is to propose an ultra-small satellite platform with the ability to quickly adapt and adjust and being easy to quickly replace and upgrade.
[0010] To achieve the above object, the technical solution adopted by the present invention is a super-small satellite platform with quick splicing, which includes three parts: a GNC section, a propulsion section, and an electronics section that are connected in sequence and have functional single machines assembled inside; the GNC section is used for guidance, navigation, and control functions, including momentum wheels, gyro / MEMS inertial resistors, star sensors / imaging star sensors; the propulsion section adopts an integrated design of a storage tank and thrusters, and directly integrates the thrusters onto the storage tank; the electronics section includes an on-board computer, a storage battery, a GNSS antenna, and an inter-satellite communication antenna.
[0011] Preferably, a unified mechanical interface is adopted between the GNC section and the propulsion section, and between the propulsion section and the electronics section.
[0012] Preferably, the unified mechanical interface is four M5 mounting lugs located on the four sides of the interface between the sections. The mounting lugs are smaller than the overall dimension envelope of the entire satellite platform. The sealing performance of the cabin is ensured through the flatness and parallelism of the interface between the sections, and rapid assembly and docking between the sections are realized.
[0013] Preferably, a unified communication electrical interface is adopted between the GNC section and the propulsion section, and between the propulsion section and the electronics section to realize information flow communication between the GNC section and the electronics section.
[0014] Preferably, the unified communication electrical interface is divided into a power supply interface and a data interface, and a plug-in type seat charging system is adopted. The internal power supply and signal paths are realized by reed pieces / pressure blocks and connecting cables.
[0015] Preferably, a unified mounting interface is reserved at the top of the GNC section of the satellite platform for carrying lightweight and small-sized payload single machines with a standardized spectrum.
[0016] The super-small satellite platform with quick splicing of the present invention has the following beneficial effects:
[0017] 1. The three-section sub-cabin design of the present invention disassembles the satellite at the system level, greatly improving the modularity of the satellite, and effectively reducing the single machine integration degree and interface complexity;
[0018] 2. The three-section sub-cabin design of the present invention adopts unified mechanical and electrical interfaces, significantly improving the rapid assembly and functional upgrade between modules;
[0019] 3. The present invention adopts a lightweight design, and the minimum mass of the small satellite can be reduced to less than 4 kg, greatly improving the high applicability of the satellite and helping to realize the rapid deployment of mass production;
[0020] 4. The small satellite of the present invention has a general-purpose payload interface and has the ability to carry a payload of 200 - 400 g, and can realize long-distance payload delivery tasks;
[0021] 5. The small satellite platform of the present invention has functions such as guidance, navigation, attitude control, orbit control, and payload carrying, and has the ability to independently execute tasks.
Description of the Drawings
[0022] Figure 1 It is a schematic diagram of the modular configuration of a super-small satellite platform with quick splicing.
[0023] Figure 2 It is a single-machine layout diagram of a super-small satellite platform with quick splicing.
[0024] Figure 3 It is a schematic diagram of the mechanical interface of the cabin section of a super-small satellite platform with quick splicing.
[0025] Figure 4 It is a schematic diagram of the electrical interface of the cabin section of a super-small satellite platform with quick splicing.
[0026] Figure 5 It is a schematic diagram of the electrical interface principle of the cabin section of a super-small satellite platform with quick splicing.
Detailed Embodiment
[0027] The present invention will be further described below in conjunction with the embodiments and with reference to the drawings.
[0028] Embodiment
[0029] This embodiment realizes a super-small satellite platform with quick splicing.
[0030] Figure 1 It is a schematic diagram of the modular configuration of a super-small satellite platform with quick splicing. As shown in the figure, the overall satellite platform of this embodiment is divided into three parts according to functions: GNC (guidance, navigation, control) cabin section, propulsion cabin section, and electronics cabin section, and the GNC (guidance, navigation, control) cabin section, propulsion cabin section, and electronics cabin section are connected in sequence.
[0031] Figure 2 It is a single-machine layout diagram of a super-small satellite platform with quick splicing. As Figure 2 shown, all single machines with corresponding functions are assembled inside each cabin section of the satellite platform of this embodiment. Among them, the GNC cabin section includes momentum wheels, gyroscopes / MEMS inertial resistors, star sensors / imaging star sensors, etc., the propulsion cabin section adopts an integrated design of a storage tank and thrusters to achieve system integration, and the electronics cabin section includes an on-board computer, a storage battery, a GNSS antenna, an inter-satellite communication antenna, etc.
[0032] The propulsion cabin section adopts an integrated design of thrusters + storage tanks, directly integrating the thrusters onto the storage tanks, reducing the pipeline layout space and simplifying the assembly process, which helps to achieve the rapid assembly and deployment of the satellite platform.
[0033] Figure 3 It is a schematic diagram of the mechanical interface of a super-small satellite platform cabin section for quick splicing. As Figure 3 shown, in this embodiment, a unified mechanical interface design is adopted between the cabin sections of the satellite platform. Four M5 mounting lugs are left on each interface of the cabin sections, and the mounting lugs are smaller than the overall dimension envelope of the whole satellite, reducing the impact on the space inside the cabin and the launch vehicle space. The mechanical interface ensures the airtightness of the cabin through the flatness and parallelism of the interfaces of each cabin section, realizes the quick assembly and docking between cabin sections, and helps to achieve the quick upgrade of functions and performance.
[0034] Figure 4 It is a schematic diagram of the electrical interface of a super-small satellite platform cabin section for quick splicing. Figure 5 It is a schematic diagram of the electrical interface principle of a super-small satellite platform cabin section for quick splicing. As Figure 4 、 Figure 5 shown, in this embodiment, a unified communication electrical interface design is adopted between the cabin sections of the satellite platform to realize the information flow communication between the GNC cabin section and the electronic cabin section. The electrical interface adopts a plug-and-play seat charging system, and the internal power supply and signal paths are mainly realized by reed / block and connecting cables. The electrical interface can be divided into a power supply interface and a data interface, and the specific number of blocks can be adjusted according to actual needs.
[0035] In this embodiment, a unified mounting interface, including a mechanical interface / electrical interface, is reserved at the top of the satellite platform for carrying modularized lightweight payload single machines, improving the payload adaptability of the satellite platform.
[0036] The above are only the preferred embodiments of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the principle of the present invention, several improvements and supplements can still be made, and these improvements and supplements should also be regarded as the protection scope of the present invention.
Claims
1. A fast-joined ultra-small satellite platform, characterized in that: It includes three parts: the GNC compartment, the propulsion compartment, and the electronic compartment, which are connected in sequence and assembled internally as a single functional unit; the GNC compartment is used for guidance, navigation, and control functions, including a momentum wheel, a gyroscope / MEMS inertial resistance, and a star sensor / imaging star sensor; the propulsion compartment adopts a tank-thruster integrated design, and the thruster is directly integrated into the tank; the electronic compartment includes a satellite service computer, a battery, a GNSS antenna, and an intersatellite communication antenna.
2. The fast-joined ultra-small satellite platform according to claim 1, characterized in that: A unified mechanical interface is used between the GNC compartment and the propulsion compartment, and between the propulsion compartment and the electronic compartment.
3. The fast-joined ultra-small satellite platform according to claim 2, characterized in that: The unified mechanical interface is four M5 mounting lugs located on the four sides of the cabin interface. The mounting lugs are smaller than the overall dimensions of the satellite platform. The flatness and parallelism of the cabin interface ensure the sealing of the cabin and enable rapid assembly and docking between cabins.
4. The fast-joined ultra-small satellite platform according to claim 3, characterized in that: A unified communication electrical interface is used between the GNC compartment and the propulsion compartment, and between the propulsion compartment and the electronic compartment to realize information flow communication between the GNC compartment and the electronic compartment.
5. The fast-joined ultra-small satellite platform according to claim 4, characterized in that: The unified communication electrical interface is divided into a power supply interface and a data interface, and adopts a plug-in charging seat system. The power supply and signal paths are realized by springs / pressure blocks and connecting cables inside.
6. The fast-joined ultra-small satellite platform according to claim 4, characterized in that: A unified installation interface is reserved on the top of the GNC compartment of the satellite platform for carrying a spectrum of light and small payload units.