CN110450978B - General modular full-electric push satellite platform - Google Patents
General modular full-electric push satellite platform Download PDFInfo
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- CN110450978B CN110450978B CN201910749345.XA CN201910749345A CN110450978B CN 110450978 B CN110450978 B CN 110450978B CN 201910749345 A CN201910749345 A CN 201910749345A CN 110450978 B CN110450978 B CN 110450978B
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- 238000004891 communication Methods 0.000 claims abstract description 24
- 238000012545 processing Methods 0.000 claims abstract description 22
- 238000009434 installation Methods 0.000 claims abstract description 19
- 229910052724 xenon Inorganic materials 0.000 claims description 16
- FHNFHKCVQCLJFQ-UHFFFAOYSA-N xenon atom Chemical compound [Xe] FHNFHKCVQCLJFQ-UHFFFAOYSA-N 0.000 claims description 16
- 230000007246 mechanism Effects 0.000 claims description 6
- 230000005540 biological transmission Effects 0.000 claims description 3
- 239000002775 capsule Substances 0.000 claims description 3
- 238000005259 measurement Methods 0.000 claims description 3
- 238000013461 design Methods 0.000 abstract description 13
- 238000011161 development Methods 0.000 abstract description 8
- 230000008878 coupling Effects 0.000 abstract description 4
- 238000010168 coupling process Methods 0.000 abstract description 4
- 238000005859 coupling reaction Methods 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 7
- 238000000034 method Methods 0.000 description 6
- 238000001228 spectrum Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 5
- 230000008859 change Effects 0.000 description 3
- 108010066057 cabin-1 Proteins 0.000 description 2
- 108010066114 cabin-2 Proteins 0.000 description 2
- 108010066278 cabin-4 Proteins 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- HBBGRARXTFLTSG-UHFFFAOYSA-N Lithium ion Chemical compound [Li+] HBBGRARXTFLTSG-UHFFFAOYSA-N 0.000 description 1
- 241000274582 Pycnanthus angolensis Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000013500 data storage Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 229910001416 lithium ion Inorganic materials 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000011087 paperboard Substances 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
Abstract
The invention relates to a universal modularized full-electric-propulsion satellite platform in the technical field of spaceflight, which comprises an electric propulsion cabin, an energy supply cabin, a communication and data processing cabin, an attitude control cabin and a load installation cabin, wherein the electric propulsion cabin is connected with the energy supply cabin; the electric propulsion cabin, the energy supply cabin, the communication and data processing cabin, the attitude control cabin and the load installation cabin are sequentially assembled in series in a linear stack mode, and the electric propulsion cabin is positioned at a starting end; the electric propulsion cabin, the energy supply cabin, the communication and data processing cabin, the attitude control cabin and the load installation cabin are connected with adjacent cabins through standard electromechanical and thermal interfaces. The full-electric push satellite platform adopts a modular design, reduces the coupling among subsystems of the platform, simplifies the complexity of the AIT of the whole satellite and shortens the development period.
Description
Technical Field
The invention relates to the field of spaceflight, in particular to a universal modular full-electric-push satellite platform.
Background
The full electric propulsion platform has obvious advantages in track maintenance, large-range track change and deep space exploration tasks by virtue of the advantages of high bearing ratio and long service life. In addition, in order to meet different task requirements and simultaneously significantly reduce the satellite development cost and period, the modular design of the full-electric general satellite platform becomes a necessary trend.
At present, the main full-electric push platforms at home and abroad comprise BSS-702SP of the American Boeing company, GEOstar-3 platform of the American Rail science company, Eurostat 3000EOR of the European Bureau and DFH-4SP of China, the platforms adopt a modular design concept in configuration design, but the platforms are mainly separated from loads, although the platform part adopts a cabin design, the separation interface is not clear in space, and all cabin sections still belong to an open structure.
Therefore, a full-electric-push satellite platform is urgently needed to be developed, and the technical problems of meeting the multi-task adaptability of future satellites, simplifying the development process, shortening the full task cycle of the satellites, improving the commercial value and the like are solved.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a universal modular full-electric-push satellite platform.
The invention provides a universal modularized full-electric-propulsion satellite platform which comprises an electric propulsion cabin, an energy supply cabin, a communication and data processing cabin, an attitude control cabin and a load installation cabin, wherein the electric propulsion cabin is connected with the energy supply cabin;
the electric propulsion cabin, the energy supply cabin, the communication and data processing cabin, the attitude control cabin and the load installation cabin are sequentially assembled in series in a linear stack mode, and the electric propulsion cabin is positioned at a starting end;
the electric propulsion cabin, the energy supply cabin, the communication and data processing cabin, the attitude control cabin and the load installation cabin are connected with adjacent cabins through standard electromechanical and thermal interfaces.
The full-electric push satellite platform adopts a modular design scheme capable of linear stacking, has high modularization degree, has clear interfaces among all modules, is connected only through a plurality of standard interfaces, reduces the coupling among all subsystems of the platform, simplifies the complexity of the AIT of the whole satellite and shortens the development period.
Meanwhile, the full-electric-drive satellite platform adopts a modular design, so that the platform has stronger expansion capability and inheritance, is oriented to different types of tasks, does not need to be changed in a large range, and is mainly designed by concentrating on selecting different types of spectrums in a serialized single-machine type spectrum.
In some embodiments, the electric propulsion cabin adopts a bearing cylinder structure, and the energy supply cabin, the communication and data processing cabin, the attitude control cabin and the load installation cabin adopt a box plate type structure.
In some embodiments, the electric propulsion cabin comprises at least 4 force bearing cylinders, and the force bearing cylinders are arranged in the electric propulsion cabin in a parallel and flat way.
In some embodiments, a standardized xenon cabin can be additionally arranged between the electric propulsion cabin and the energy source supply cabin, and the standardized xenon cabin is provided with a force bearing cylinder structure and a xenon bottle which have the same specification as the electric propulsion cabin.
The full-electric-drive satellite platform is formed into an expanded type by adding the modularized standardized xenon cabin 6 on the basis of a standard type, so that the satellite orbit maneuvering capability is enhanced, the adjustability of the satellite orbit maneuvering capability is further enhanced, a propulsion module can be cut and expanded according to requirements, and the process is very simple to operate.
In some embodiments, the attitude control cabin comprises an attitude control actuator based on momentum exchange, and the attitude control actuator is configured with a flywheel set or a control moment gyro group.
In some embodiments, when the attitude control actuator is configured with wheel sets, each of the flywheel sets includes at least 4 flywheels, and at least one flywheel in the flywheel set is installed in an inclined manner.
In some embodiments, the communication and data processing cabin at least comprises an on-board computer and a storage unit, and an earth data transmission antenna is installed outside the communication and data processing cabin.
In some embodiments, the load installation cabin is provided with a plurality of omnidirectional measurement and control antennas, and the load installation cabin can be used for installing different loads. Corresponding loads can be installed according to different tasks, so that the method can be simultaneously suitable for various tasks such as a high-orbit remote sensing satellite, a high-orbit communication satellite, a deep space exploration aircraft, a space debris removal aircraft, an in-orbit service aircraft and the like.
In some embodiments, the energy supply cabin at least comprises a plurality of pairs of solar sailboards, a storage battery pack, a sailboard driving mechanism, a power controller and a power converter, wherein the solar sailboards are rotated in one dimension by the driving mechanism.
Compared with the prior art, the invention has the following beneficial effects:
1. the full-electric push satellite platform adopts a modular design, reduces the coupling among subsystems of the platform, simplifies the complexity of the AIT of the whole satellite and shortens the development period.
2. The full-electric-push satellite platform is oriented to different types of tasks, the platform inheritance is strong, large-scale change is not needed, and main design work is focused on selecting different types of spectrums from a series of single-machine spectrums.
3. The full-electric push satellite platform has strong adjustability of satellite orbit maneuvering capability, can cut and expand the push module according to requirements, and is simple to operate in the process.
4. The full-electric-drive satellite platform can be simultaneously suitable for various tasks such as a high-orbit remote sensing satellite, a high-orbit communication satellite, a deep space exploration aircraft, a space debris removal aircraft, an on-orbit service aircraft and the like.
5. The design scheme of the invention can save the development cost of the full-electric push satellite platform and is very suitable for commercial satellite application.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a diagram of an extended overall configuration of a satellite platform according to the present invention;
FIG. 2 is a diagram of the standard to extended conversion process of the present invention;
FIG. 3 is a schematic view of a modular configuration of the electric propulsion compartment of the present invention;
FIG. 4 is a structural diagram of an energy supply module according to the present invention;
FIG. 5 is a block diagram of a communication and data processing module configuration according to the present invention;
FIG. 6 is a configuration diagram of an attitude control module according to the present invention;
FIG. 7 is a schematic diagram of an expandable xenon module configuration according to the present invention;
fig. 8 is a structure diagram of the bearing cylinder and the boxboard type mixed bearing structure of the invention.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
The present invention will be described in more detail below with reference to the accompanying drawings, which illustrate embodiments of the invention. This invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein.
The satellite platform provided by the invention is a cuboid as a whole, but is not limited to the cuboid. The present invention will be described in detail with reference to the accompanying drawings 1 to 8 and the embodiments.
As shown in fig. 1, the general modular full-electric-push satellite platform of the invention comprises an electric propulsion cabin 1, an energy supply cabin 2, a communication and data processing cabin 3, an attitude control cabin 4, a load installation cabin 5 and a standardized xenon cabin 6, wherein each module adopts a linear stack assembly mode. The universal modularized full-electric-push satellite platform has two forms of a standard type and an extended type, and the full-electric-push satellite platform has the standard type and comprises an electric propulsion cabin 1, an energy supply cabin 2, a communication and data processing cabin 3, an attitude control cabin 4 and a load installation cabin 5. As shown in fig. 2, the extended version of the all-electric satellite platform is formed by adding modular standardized xenon cabins 6 to the standard version, thereby enhancing the satellite orbital mobility.
As shown in fig. 7, the compartments are connected to the adjacent compartment by 4 standard electromechanical thermal interface male ports 28 at 4 corners above the compartment and 4 standard electromechanical thermal interface female ports 29 at 4 corners below the compartment, the electric propulsion compartment 1 is the starting module, the load mounting compartment 5 is the terminating module, and the standardized xenon compartment 6 is adjacent to the electric propulsion compartment 1.
As shown in fig. 3, the electric propulsion cabin of the present invention at least includes 4 force bearing cylinders 7, 4 xenon gas bottles 8, 1 pressure adjusting module 9, 4 hall thrusters 10, 4 thrust vector adjusting devices 11, 4 flow control units 12, and 2 power processing units 13.
As shown in fig. 4, the energy supply cabin of the present invention comprises at least 2 pairs of solar panels 14, see fig. 1, 4 groups of lithium ion battery packs 15, 2 solar panel driving mechanisms 16, which can be driven in one dimension, 1 power controller 17, and 2 power processing units 18.
As shown in fig. 5, the communication and data processing cabin of the present invention at least comprises an onboard computer 19 and a data storage unit 20, and an earth data transmission antenna can be installed outside the communication and data processing cabin.
As shown in fig. 6, the attitude control cabin of the present invention at least includes 4 flywheels 21, three forward-mounted and 1 oblique-mounted are adopted, 3 star sensors 22 with different directions, 2 fiber- optic gyros 23, and 1 attitude control computer 24, and the flywheel set can be replaced by other attitude control execution mechanisms such as a control moment gyro group and the like according to the requirements of the attitude control task.
As shown in fig. 1, the load installation cabin 5 can install corresponding loads according to different tasks, so that the satellite platform can be simultaneously suitable for various tasks such as a high-orbit remote sensing satellite, a high-orbit communication satellite, a deep space exploration aircraft, a space debris removal aircraft and an in-orbit service aircraft, and meanwhile, the load installation cabin 5 at least comprises 2 omnidirectional measurement and control antennas 25.
As shown in fig. 7, the standardized xenon capsule 6 comprises at least 4 force-bearing cylinders 26, having the same diameter as the force-bearing cylinder 7 shown in fig. 2, and 4 xenon cylinders 27, having the same diameter as the xenon cylinder 8 shown in fig. 2.
As shown in fig. 8, in the invention, the bearing structure of the full-electric-propulsion satellite platform is a mixed bearing structure of a bearing cylinder 7 and a box plate 30, 4 bearing cylinders 7 with the same size are parallelly and flatly paved in an electric propulsion cabin, the bearing cylinder configuration in a standardized xenon cabin is the same as that of the electric propulsion cabin, and all the other cabins adopt the bearing structure of the box plate 30.
In conclusion, the full-electric push satellite platform adopts a modular design, so that the coupling among subsystems of the platform is reduced, the complexity of the whole satellite AIT is simplified, and the development period is shortened; the full-electric push satellite platform is oriented to different types of tasks, the platform inheritance is strong, large-scale change is not needed, and main design work is concentrated on selecting different types of spectrums from a series of single-machine spectrums; the full-electric push satellite platform has strong adjustability of satellite orbit maneuvering capability, can cut and expand the push module according to requirements, and is simple to operate in the process; the full-electric-drive satellite platform can be simultaneously suitable for various tasks such as a high-orbit remote sensing satellite, a high-orbit communication satellite, a deep space exploration aircraft, a space debris removal aircraft, an on-orbit service aircraft and the like; the design scheme of the invention can save the development cost of the full-electric push satellite platform and is very suitable for commercial satellite application.
The parts not described in the present invention belong to the known art in the field.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (7)
1. A universal modularized full-electric-propulsion satellite platform is characterized by comprising an electric propulsion cabin, an energy supply cabin, a communication and data processing cabin, an attitude control cabin and a load installation cabin;
the electric propulsion cabin, the energy supply cabin, the communication and data processing cabin, the attitude control cabin and the load installation cabin are sequentially assembled in series in a linear stack mode, and the electric propulsion cabin is positioned at a starting end;
the electric propulsion cabin, the energy supply cabin, the communication and data processing cabin, the attitude control cabin and the load installation cabin are connected with adjacent cabins through standard electromechanical and thermal interfaces;
the electric propulsion cabin adopts a bearing cylinder structure, and the energy supply cabin, the communication and data processing cabin, the attitude control cabin and the load installation cabin adopt box plate structures;
and a standardized xenon cabin is additionally arranged between the electric propulsion cabin and the energy supply cabin, and the standardized xenon cabin is provided with a bearing cylinder structure and a xenon bottle which have the same specification as the electric propulsion cabin.
2. The universal modular full electric propulsion satellite platform according to claim 1, wherein the electric propulsion capsule comprises at least 4 outrigger cylinders, and the outrigger cylinders are laid out in parallel in the electric propulsion capsule.
3. The universal modular full-electric-push satellite platform according to claim 1, wherein the attitude control pod comprises an attitude control actuator based on momentum exchange, the attitude control actuator configured with a flywheel set or a control moment gyro set.
4. The universal modular full-electric-push satellite platform according to claim 3, wherein when the attitude control actuators are configured with flywheel sets, each of the flywheel sets comprises at least 4 flywheels, and at least one flywheel in the flywheel sets is installed in an inclined manner.
5. The universal modular full-electric-push satellite platform according to claim 1, wherein the communication and data processing cabin at least comprises an on-board computer and a storage unit, and an earth data transmission antenna is installed outside the communication and data processing cabin.
6. The universal modular full-electric-push satellite platform according to claim 1, wherein the load installation compartment is provided with a plurality of omnidirectional measurement and control antennas, and the load installation compartment can be used for installing different loads.
7. The universal modular full-electric-push satellite platform according to claim 1, wherein the energy supply cabin comprises at least a plurality of pairs of solar sailboards, a storage battery, a sailboard driving mechanism, a power controller and a power converter, wherein the solar sailboards are rotated in one dimension by the sailboard driving mechanism.
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| CN201910749345.XA CN110450978B (en) | 2019-08-14 | 2019-08-14 | General modular full-electric push satellite platform |
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| CN201910749345.XA CN110450978B (en) | 2019-08-14 | 2019-08-14 | General modular full-electric push satellite platform |
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| CN111003211B (en) * | 2019-11-28 | 2021-10-01 | 北京空间飞行器总体设计部 | Spacecraft configuration capable of being assembled and expanded in orbit |
| CN111422378B (en) * | 2020-03-10 | 2021-11-23 | 上海卫星工程研究所 | Static orbit ultra-large type assembled satellite platform configuration and in-orbit assembly method |
| CN111409878B (en) * | 2020-03-19 | 2021-08-24 | 上海卫星工程研究所 | Open type assembled module platform cabin structure |
| CN111762340B (en) * | 2020-07-01 | 2023-09-01 | 中国人民解放军63921部队 | Modularized spacecraft platform |
| CN112052540B (en) * | 2020-09-09 | 2022-07-08 | 哈尔滨工业大学 | Architecture of small satellite for supporting ultrahigh power consumption |
| CN112572840A (en) * | 2020-12-14 | 2021-03-30 | 兰州空间技术物理研究所 | Electric propulsion system storage and supply unit and manufacturing method thereof |
| CN113220011B (en) * | 2021-03-29 | 2023-02-03 | 北京控制工程研究所 | Miniature CMG assembly module and assembly module control system |
| CN113232892B (en) * | 2021-04-30 | 2023-02-03 | 中国空间技术研究院 | One-rocket-multi-satellite-launching foldable and expandable modular stacked satellite configuration |
| CN116062196A (en) * | 2021-09-06 | 2023-05-05 | 中国科学院微小卫星创新研究院 | Assembling method of cell satellite |
| CN114115305B (en) * | 2021-11-01 | 2022-10-04 | 武汉大学 | Control system design method of high-precision remote sensing small satellite with quick attitude maneuvering |
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| CN103264774A (en) * | 2013-04-24 | 2013-08-28 | 上海卫星工程研究所 | Mini probe for Mars orbits |
| US10738768B2 (en) * | 2016-06-22 | 2020-08-11 | The George Washington University | Micro-cathode arc thruster |
| CN106628253B (en) * | 2016-12-01 | 2019-04-09 | 航天东方红卫星有限公司 | A kind of vertebra pillar modularization satellite platform framework |
| CN107963242B (en) * | 2017-11-23 | 2020-04-10 | 航天东方红卫星有限公司 | Module combination body small satellite platform with adjustable quality characteristics |
| CN109747865B (en) * | 2018-12-25 | 2021-02-09 | 航天东方红卫星有限公司 | Modular primary and secondary satellite system |
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