CN110450978A - The full electricity of Universal, modular pushes away satellite platform - Google Patents
The full electricity of Universal, modular pushes away satellite platform Download PDFInfo
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- CN110450978A CN110450978A CN201910749345.XA CN201910749345A CN110450978A CN 110450978 A CN110450978 A CN 110450978A CN 201910749345 A CN201910749345 A CN 201910749345A CN 110450978 A CN110450978 A CN 110450978A
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- pushes away
- satellite platform
- full electricity
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- 230000005611 electricity Effects 0.000 title claims abstract description 37
- 238000012545 processing Methods 0.000 claims abstract description 20
- 238000004891 communication Methods 0.000 claims abstract description 19
- 238000009434 installation Methods 0.000 claims abstract description 14
- 238000005485 electric heating Methods 0.000 claims abstract description 3
- 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
- 241000274582 Pycnanthus angolensis Species 0.000 claims description 5
- 230000007246 mechanism Effects 0.000 claims description 5
- 239000011087 paperboard Substances 0.000 claims description 5
- 238000003491 array Methods 0.000 claims description 3
- 238000013461 design Methods 0.000 abstract description 13
- 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
- 238000005516 engineering process Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 7
- 238000001228 spectrum Methods 0.000 description 6
- 108010066057 cabin-1 Proteins 0.000 description 4
- 230000008859 change Effects 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000010276 construction Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 3
- 108010066114 cabin-2 Proteins 0.000 description 2
- 108010066278 cabin-4 Proteins 0.000 description 2
- HBBGRARXTFLTSG-UHFFFAOYSA-N Lithium ion Chemical compound [Li+] HBBGRARXTFLTSG-UHFFFAOYSA-N 0.000 description 1
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 238000013500 data storage Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 229910001416 lithium ion Inorganic materials 0.000 description 1
- 239000013307 optical fiber Substances 0.000 description 1
- 238000011112 process operation Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 210000000352 storage cell Anatomy 0.000 description 1
Classifications
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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
-
- 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
-
- 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
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Radio Relay Systems (AREA)
- Photovoltaic Devices (AREA)
Abstract
The present invention relates to the full electricity of a kind of Universal, modular in space technology field to push away satellite platform, including electric propulsion cabin, energy resource supply cabin, communications and data processing cabin, attitude control cabin and load install cabin；The mode that the electric propulsion cabin, the energy resource supply cabin, communications and data processing cabin, the attitude control cabin and load installation cabin pass sequentially through linear storehouse serially assembles, and the electric propulsion freight space is in starting point；The electric propulsion cabin, the energy resource supply cabin, communications and data processing cabin, the attitude control cabin and load installation cabin are connect by Standard Machine electric heating interface with adjacent compartment.The full electricity of the present invention pushes away satellite platform using modularized design, reduces the coupling between each subsystem of platform, simplifies the complexity of whole star AIT, shorten the lead time.
Description
Technical field
The present invention relates to space industries, specifically, being related to a kind of full electricity of Universal, modular pushes away satellite platform.
Background technique
Full electric propulsion platform relies on its high-mechanic ratio, long-life advantage, in track holding, a wide range of change rail and deep space exploration
It has a clear superiority in task.In addition, to adapt to different mission requirements, while satellite development cost and period are significantly reduced,
The modularized design that full electricity pushes away Utility Satellite platform becomes inexorable trend.
Domestic and international main full electricity is bulldozed the BSS-702SP of Tai You Boeing Co., Orbital Sciences Corporation, the U.S. at present
GEOstar-3 platform, the DFH-4SP of the Eurostar 3000EOR of European Space Agency and China, these platforms design in configuration
When all use modular design concept, it is main or separate platform and load, although terrace part is set using subdivision
Meter, but being spatially separated interface is not to be apparent, each bay section still falls within Open architecture.
Thus, it would be highly desirable to develop a kind of full electricity and push away satellite platform, meet the multitask adaptability of Future Satellite, simplify and develop
Process shortens the full duty cycle of satellite and improves the technical problems such as commercial value.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of full electricity of Universal, modular to push away satellite platform.
The full electricity of a kind of Universal, modular provided according to the present invention pushes away satellite platform, including electric propulsion cabin, energy resource supply cabin,
Communications and data handles cabin, attitude control cabin and load and installs cabin；
The electric propulsion cabin, the energy resource supply cabin, communications and data processing cabin, the attitude control cabin and the load
The mode that installation cabin passes sequentially through linear storehouse serially assembles, and the electric propulsion freight space is in starting point；
The electric propulsion cabin, the energy resource supply cabin, communications and data processing cabin, the attitude control cabin and the load
Lotus installation cabin is connect by Standard Machine electric heating interface with adjacent compartment.
The full electricity of the present invention push away satellite platform using can linear storehouse modularized design scheme, the degree of modularity is high, each mould
Interface is clear between block, is only connected by several standard interfaces, reduces the coupling between each subsystem of platform, simplifies whole star
The complexity of AIT, shortens the lead time.
The full electricity of the present invention pushes away satellite platform and uses modularized design simultaneously, so that the extended capability of platform and inheritance are more
By force, towards different type task, without doing a wide range of change, major design work, which will focus in seriation single machine type spectrum, to be carried out
The selection of different type spectrums.
In some embodiments, the electric propulsion cabin uses load barrel structure, the energy resource supply cabin, the communication and number
Boxboard typed structure is used according to processing cabin, the attitude control cabin and load installation cabin.
It include at least four loaded cylinder in the electric propulsion cabin, the loaded cylinder is with tiling side in parallel in some embodiments
Formula is laid out in the electric propulsion cabin.
In some embodiments, standardization xenon cabin, institute can be added between the electric propulsion cabin and the energy resource supply cabin
Standardization xenon cabin is stated equipped with the load barrel structure and xenon bottle with electric propulsion cabin same size.
The full electricity of the present invention pushes away satellite platform and is formed on the basis of standard type by increasing modular standardization xenon cabin 6
Extended pattern further enhances the controllability of Satellite orbital maneuver ability so that Satellite orbital maneuver ability enhances, can root
Propulsion die is cut and extended according to demand, and process operation is very simple.
In some embodiments, the attitude control cabin includes the attitude control executing agency based on momentum-exchange, and the attitude control executes
Mechanism is configured with flywheel group or control-moment gyro group.
In some embodiments, when the attitude control executing agency configures wheel group, flywheel group described in every group includes that at least four flies
It takes turns, at least one flywheel is installed using angled manner in the flywheel group.
In some embodiments, communications and data processing cabin includes at least On board computer, storage unit, described logical
Portion is equipped with number biography antenna over the ground to letter out of my cabin with data processing.
In some embodiments, load installation cabin is equipped with multiple omnidirectional's TT&C antennas, and load installation cabin can pacify
Fill different loads.Respective loads can be installed according to task difference, so that the present invention can be suitable for high rail remote sensing satellite, high rail simultaneously
Telecommunication satellite, deep space exploration aircraft, space junk remove the polymorphic types tasks such as aircraft, in-orbit service aircraft.
In some embodiments, the energy resource supply cabin includes at least more secondary solar arrays, battery group, windsurfing driving machine
Structure, power-supply controller of electric, supply convertor, the solar array realize one-dimensional rotation by driving mechanism.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, the full electricity of the present invention pushes away satellite platform using modularized design, reduces the coupling between each subsystem of platform, simplifies
The complexity of whole star AIT, shortens the lead time.
2, the full electricity of the present invention pushes away satellite platform towards different type task, and platform inheritance is strong, without doing a wide range of change,
Major design work will focus on the selection that different type spectrums are carried out in seriation single machine type spectrum.
3, the Satellite orbital maneuver ability controllability that the full electricity of the present invention pushes away satellite platform is strong, according to demand can be to propulsion module
Block is cut and is extended, and the process is easy to operate.
4, the full electricity of the present invention pushes away satellite platform can be suitable for high rail remote sensing satellite, high rail telecommunication satellite, deep space exploration simultaneously
Aircraft, space junk remove the polymorphic types tasks such as aircraft, in-orbit service aircraft.
5, design scheme of the invention can save full electricity and push away satellite platform development cost, be highly suitable for commercial satellite and answer
With.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is satellite platform extended pattern overall configuration figure of the present invention；
Fig. 2 is standard type of the present invention to extended pattern conversion process figure；
Fig. 3 is electric propulsion cabin modular configuration figure of the present invention；
Fig. 4 is energy resource supply modular configuration figure of the present invention；
Fig. 5 is communications and data processing module configuration picture of the present invention；
Fig. 6 is attitude control modular configuration figure of the present invention；
Fig. 7 is the expansible xenon modular configuration figure of the present invention；
Fig. 8 is loaded cylinder of the present invention and boxboard typed mixing load-carrying construction figure.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection scope.
Referring to the attached drawing for showing the embodiment of the present invention, the present invention is described in more detail.The present invention can be with many
Different form is realized, and should not be construed as being limited by the embodiment herein proposed.
The satellite platform example generally cuboid that the present invention provides, but it is not limited to cuboid.With reference to the accompanying drawing
The present invention is described in detail for 1-8 and specific embodiment.
As shown in Fig. 1, it includes electric propulsion cabin 1, energy that the full electricity of Universal, modular of the invention, which pushes away satellite platform maximum composition,
Source supplies cabin 2, communication and data processing cabin 3, attitude control cabin 4, load installation cabin 5, standardization xenon cabin 6, and each module is using linear
The assembly method of storehouse.The full electricity of Universal, modular of the invention, which pushes away satellite platform, two kinds of forms of standard type and extended pattern, full electricity
Pushing away satellite platform to have standard type includes electric propulsion cabin 1, energy resource supply cabin 2, communication and data processing cabin 3, attitude control cabin 4, load peace
Stowage 5.As shown in Fig. 2, full electricity pushes away satellite platform extended pattern by increasing modular standardization xenon cabin 6 in standard type
It is formed, to enhance Satellite orbital maneuver ability.
As shown in fig. 7, passing through the electromechanical hot interface public affairs mouth 28 positioned at 4 standards of 4 corner points above cabin between each cabin
It is connect with the electromechanical hot interface mother mouth 29 for being located at 4 standards of 4 corner points below cabin with adjacent compartment, electric propulsion cabin 1 is
Beginning module, it is to terminate module that load, which installs cabin 5, and standardization xenon cabin 6 is adjacent with electric propulsion cabin 1.
As shown in figure 3, electric propulsion cabin of the invention, which includes at least 48,1, xenon bottle pressure of loaded cylinder 7,4, adjusts mould
The power processing unit of flow controlling unit 12,2 of thrust vectoring regulating device 11,4 of hall thruster 10,4 of block 9,4
13。
As shown in figure 4, energy resource supply cabin of the invention includes at least 2 secondary solar arrays 14, see that attached drawing Isosorbide-5-Nitrae group lithium ion stores
15,2 solar array driving mechanisms 16 of battery pack, can one dimensional driving, 1 power-supply controller of electric, 17,2 power processing units 18.
As shown in figure 5, communication and data processing cabin of the invention include at least On board computer 19, data storage cell
20, the mountable number over the ground in portion passes antenna out of my cabin for communication and data processing.
As shown in fig. 6, attitude control cabin of the invention includes at least 4 flywheels 21, using three formal dress and 1 angle mount, 3 are not
With the attitude control computer 24 of optical fibre gyro 23,1 of star sensor 22,2 being directed toward, can be needed according to attitude control task by flywheel group more
It is changed to other attitude control executing agencies such as control-moment gyro group.
As shown in Figure 1, load installation cabin 5 can install respective loads according to task difference, enable the satellite platform same
When be suitable for high rail remote sensing satellite, high rail telecommunication satellite, deep space exploration aircraft, space junk remove aircraft, in-orbit service
The polymorphic types task such as aircraft, while load installation cabin 5 includes at least 2 omnidirectional's TT&C antennas 25.
As shown in fig. 7, standardization xenon cabin 6 includes at least 4 loaded cylinders 26, and it is identical as the diameter of loaded cylinder 7 shown in Fig. 2,4
A xenon bottle 27 is identical as 8 diameter of xenon bottle shown in Fig. 2.
As shown in figure 8, the load-carrying construction that full electricity pushes away satellite platform is that loaded cylinder 7 adds the mixing of boxboard 30 to hold in the present invention
Power structure is laid in electric propulsion cabin using 7 parallel connection of loaded cylinder of 4 same sizes, standardizes loaded cylinder configuration in xenon cabin
Identical as electric propulsion cabin, remaining all cabin is all made of the load-carrying construction of boxboard 30.
In conclusion the full electricity of the present invention pushes away satellite platform using modularized design, the coupling between each subsystem of platform is reduced
It closes, simplifies the complexity of whole star AIT, shorten the lead time；The full electricity of the present invention pushes away satellite platform towards different type task,
Platform inheritance is strong, and without doing a wide range of change, major design work, which will focus in seriation single machine type spectrum, carries out different shaped
The selection of spectrum；The Satellite orbital maneuver ability controllability that the full electricity of the present invention pushes away satellite platform is strong, according to demand can be to propulsion module
Block is cut and is extended, and the process is easy to operate；The full electricity of the present invention pushes away satellite platform and can defend simultaneously suitable for high rail remote sensing
Star, high rail telecommunication satellite, deep space exploration aircraft, space junk remove the polymorphic types tasks such as aircraft, in-orbit service aircraft；
Design scheme of the invention can save full electricity and push away satellite platform development cost, be highly suitable for commercial satellite application.
It is not specified in the present invention and partly belongs to techniques known.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (9)
1. a kind of full electricity of Universal, modular pushes away satellite platform, which is characterized in that including electric propulsion cabin, energy resource supply cabin, communication with
Data processing cabin, attitude control cabin and load install cabin；
The electric propulsion cabin, the energy resource supply cabin, communications and data processing cabin, the attitude control cabin and load installation
The mode that cabin passes sequentially through linear storehouse serially assembles, and the electric propulsion freight space is in starting point；
The electric propulsion cabin, the energy resource supply cabin, communications and data processing cabin, the attitude control cabin and load peace
Stowage is connect by Standard Machine electric heating interface with adjacent compartment.
2. the full electricity of Universal, modular according to claim 1 pushes away satellite platform, which is characterized in that the electric propulsion cabin uses
Load barrel structure, the energy resource supply cabin, communications and data processing cabin, the attitude control cabin and load installation cabin use
Boxboard typed structure.
3. the full electricity of Universal, modular according to claim 2 pushes away satellite platform, which is characterized in that the electric propulsion cabin Zhong Bao
At least four loaded cylinder is included, the loaded cylinder is laid out in the electric propulsion cabin with tile mode in parallel.
4. the full electricity of Universal, modular according to claim 1 pushes away satellite platform, which is characterized in that the electric propulsion cabin and institute
It states and adds standardization xenon cabin between energy resource supply cabin, the standardization xenon cabin is equipped with and electric propulsion cabin same size
Load barrel structure and xenon bottle.
5. the full electricity of Universal, modular according to claim 1 pushes away satellite platform, which is characterized in that the attitude control cabin includes base
In the attitude control executing agency of momentum-exchange, the attitude control executing agency is configured with flywheel group or control-moment gyro group.
6. the full electricity of Universal, modular according to claim 5 pushes away satellite platform, which is characterized in that the attitude control executing agency
When configuring wheel group, flywheel group described in every group includes at least four flywheel, at least one flywheel uses angled manner in the flywheel group
Installation.
7. the full electricity of Universal, modular according to claim 1 pushes away satellite platform, which is characterized in that at the communications and data
Stowing includes at least On board computer, storage unit, and portion is equipped with number biography antenna over the ground out of my cabin for the communications and data processing.
8. the full electricity of Universal, modular according to claim 1 pushes away satellite platform, which is characterized in that load installation cabin is set
There are multiple omnidirectional's TT&C antennas, the load installs the mountable different loads in cabin.
9. the full electricity of Universal, modular according to claim 1 pushes away satellite platform, which is characterized in that the energy resource supply cabin is extremely
Few includes more secondary solar arrays, battery group, windsurfing driving mechanism, power-supply controller of electric, supply convertor, and the solar array is logical
Mechanism of overdriving realizes one-dimensional rotation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910749345.XA CN110450978B (en) | 2019-08-14 | 2019-08-14 | General modular full-electric push satellite platform |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910749345.XA CN110450978B (en) | 2019-08-14 | 2019-08-14 | General modular full-electric push satellite platform |
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| CN110450978A true CN110450978A (en) | 2019-11-15 |
| CN110450978B CN110450978B (en) | 2021-05-11 |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111003211A (en) * | 2019-11-28 | 2020-04-14 | 北京空间飞行器总体设计部 | Spacecraft configuration capable of being assembled and expanded in orbit |
| CN111409878A (en) * | 2020-03-19 | 2020-07-14 | 上海卫星工程研究所 | Open type assembled module platform cabin structure |
| CN111422378A (en) * | 2020-03-10 | 2020-07-17 | 上海卫星工程研究所 | Static orbit ultra-large type assembled satellite platform configuration and in-orbit assembly method |
| CN111762340A (en) * | 2020-07-01 | 2020-10-13 | 中国人民解放军63921部队 | Modularized spacecraft platform |
| CN112052540A (en) * | 2020-09-09 | 2020-12-08 | 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 |
| CN113220011A (en) * | 2021-03-29 | 2021-08-06 | 北京控制工程研究所 | Miniature CMG assembly module and assembly module control system |
| CN113232892A (en) * | 2021-04-30 | 2021-08-10 | 中国空间技术研究院 | One-rocket-multi-satellite-launching foldable and expandable modular stacked satellite configuration |
| CN113815899A (en) * | 2021-09-06 | 2021-12-21 | 中国科学院微小卫星创新研究院 | Cell satellite system capable of being assembled and reconstructed in on-orbit modularization manner |
| CN114115305A (en) * | 2021-11-01 | 2022-03-01 | 武汉大学 | Control system design method of high-precision remote sensing small satellite with fast maneuvering posture |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103264774A (en) * | 2013-04-24 | 2013-08-28 | 上海卫星工程研究所 | Mini probe for Mars orbits |
| CN106628253A (en) * | 2016-12-01 | 2017-05-10 | 航天东方红卫星有限公司 | Cone type modularization satellite platform architecture |
| US20170370353A1 (en) * | 2016-06-22 | 2017-12-28 | The George Washington University | Micro-cathode arc thruster |
| CN107963242A (en) * | 2017-11-23 | 2018-04-27 | 航天东方红卫星有限公司 | A kind of adjustable assembly small satellite platform of mass property |
| CN109747865A (en) * | 2018-12-25 | 2019-05-14 | 航天东方红卫星有限公司 | A kind of modular primary and secondary satellite system |
-
2019
- 2019-08-14 CN CN201910749345.XA patent/CN110450978B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103264774A (en) * | 2013-04-24 | 2013-08-28 | 上海卫星工程研究所 | Mini probe for Mars orbits |
| US20170370353A1 (en) * | 2016-06-22 | 2017-12-28 | The George Washington University | Micro-cathode arc thruster |
| CN106628253A (en) * | 2016-12-01 | 2017-05-10 | 航天东方红卫星有限公司 | Cone type modularization satellite platform architecture |
| CN107963242A (en) * | 2017-11-23 | 2018-04-27 | 航天东方红卫星有限公司 | A kind of adjustable assembly small satellite platform of mass property |
| CN109747865A (en) * | 2018-12-25 | 2019-05-14 | 航天东方红卫星有限公司 | A kind of modular primary and secondary satellite system |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111003211A (en) * | 2019-11-28 | 2020-04-14 | 北京空间飞行器总体设计部 | Spacecraft configuration capable of being assembled and expanded in orbit |
| 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 |
| CN111422378A (en) * | 2020-03-10 | 2020-07-17 | 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 |
| CN111409878A (en) * | 2020-03-19 | 2020-07-14 | 上海卫星工程研究所 | Open type assembled module platform cabin structure |
| CN111762340A (en) * | 2020-07-01 | 2020-10-13 | 中国人民解放军63921部队 | Modularized spacecraft platform |
| CN111762340B (en) * | 2020-07-01 | 2023-09-01 | 中国人民解放军63921部队 | Modularized spacecraft platform |
| CN112052540A (en) * | 2020-09-09 | 2020-12-08 | 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 |
| CN113220011A (en) * | 2021-03-29 | 2021-08-06 | 北京控制工程研究所 | Miniature CMG assembly module and assembly module control system |
| 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 |
| CN113232892A (en) * | 2021-04-30 | 2021-08-10 | 中国空间技术研究院 | One-rocket-multi-satellite-launching foldable and expandable modular stacked satellite configuration |
| 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 |
| CN113815899A (en) * | 2021-09-06 | 2021-12-21 | 中国科学院微小卫星创新研究院 | Cell satellite system capable of being assembled and reconstructed in on-orbit modularization manner |
| CN114115305A (en) * | 2021-11-01 | 2022-03-01 | 武汉大学 | Control system design method of high-precision remote sensing small satellite with fast maneuvering posture |
| 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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| CN110450978B (en) | 2021-05-11 |
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