CN111572814A - Configuration and assembly method of ultra-large type assembled satellite platform of static orbit - Google Patents
Configuration and assembly method of ultra-large type assembled satellite platform of static orbit Download PDFInfo
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Abstract
The invention provides a static orbit ultra-large type assembled satellite platform configuration, which comprises the following components: the mother platform comprehensively controls the whole satellite; the first module cabin and the second module cabin are connected with the mother platform and provide installation platforms for the single machine modules of the ultra-large platform; the first function cabin and the second function cabin are respectively connected with the first module cabin and the second module cabin and are used for carrying a working load; the energy source system comprises a first connecting truss, a second connecting truss, a first energy module and a second energy module, wherein the first connecting truss and the second connecting truss are respectively arranged on the first energy module and the second energy module; the first mechanical arm and the second mechanical arm are respectively arranged on the east and the west of the mother platform. The invention can be used for an ultra-large comprehensive satellite platform, is convenient for the satellite platform to carry out on-orbit maintenance, and has the advantages of low development cost, open platform configuration space and high energy utilization efficiency.
Description
Technical Field
The invention relates to satellite technology, in particular to a configuration of an ultra-large type assembled satellite platform.
Background
In recent years, the investment of the aerospace industry in main aerospace countries is continuously increased, and the number of satellites launched is gradually increased year by year. Geostationary orbit satellites are the key development in the satellite field of communications, relays, weather, earth observation and the like because of the advantages of fixed-point continuous observation. However, the geostationary orbit has very scarce orbit resources, and the high-orbit satellite faces the increasingly tense orbit resources, so that the development of an ultra-large satellite platform with larger bearing capacity is urgently needed. The existing large-scale high-orbit satellite has high launching cost due to the carrying envelope and launching capability, and the satellite platform capable of being assembled in orbit becomes an effective solution. The on-orbit assembled satellite platform can decompose a large-scale platform into a plurality of modularized small-scale platforms or functional cabin sections, and the large-scale satellite platform meeting the task requirements is formed through multiple times of launching and on-orbit assembling, so that the problem of insufficient carrying capacity in the prior art is solved. On the other hand, in order to meet the requirements of on-orbit maintenance and on-orbit upgrading of a high-orbit satellite, the single-machine modular design becomes a necessary trend, convenient replacement of a fault single machine and updating and upgrading of critical loads can be realized through the modular design, and in addition, the requirements of different loads can be met through selection and combination of modules. Therefore, for a high-orbit ultra-large satellite platform, a multi-stage modular design is necessary to break through the transportation limitation and meet the requirement of on-orbit maintenance.
On-track assembly is extended from the concept of on-track services, which is defined as: different components are connected together in space to construct a structure, subsystem, unit body of subsystems, and other space facilities, or one or more structures are separated for recombination. A2010 German space navigation center provides an intelligent building block iBOSS project for satellite on-orbit service, a traditional satellite platform is decomposed into standardized intelligent building blocks, and a new space system is formed through on-orbit assembly, so that modularization and reconstruction of a satellite are realized. 2011 in the united states, the phoenix project proposed the concept of a cell satellite, and in space, antennas of waste satellites and the cell satellite are assembled in an in-orbit manner through a mechanical arm to form a new spacecraft system; in 2015, the united states started a dragonfly project, aiming to complete on-orbit assembly and reconstruction of a large-scale solid radio frequency reflector and a satellite platform. In contrast to europe and the united states, our country is still beginning to study on in-orbit assembly techniques. In the Liu megacrystal of Harbin industry university, an expandable parabolic antenna support mechanism is taken as a research object in a Master academic paper (design and development of a modularized expandable parabolic antenna support mechanism), and an antenna support mechanism scheme consisting of hexagonal frustum modules is provided; the league of the university of the west ampere electronics science and technology and the like research the modular design technology of the unit spliced antenna and the on-orbit assembly technical scheme (the on-orbit assembly technology of the large-scale space antenna). The above research mainly aims at the modular design and on-orbit assembly of large antenna structures, and does not relate to satellite platforms. The Huang Pang Feng of the northwest industry university and the like put forward a reconfigurable cell satellite key technology oriented to an on-orbit assembly task in research papers (the reconfigurable cell satellite key technology and prospect oriented to on-orbit service) of the Huang Pang Feng and the like, and some development suggestions are provided aiming at the cell satellite technology research of China, but the research of the cell satellite key technology and the cell satellite technology mainly is technology combing on a macroscopic level, and the research of specific technologies is not deeply developed.
The invention discloses a modularized reconfigurable micro-nano satellite structure with the publication number of CN104290920A, which is named as a modularized reconfigurable micro-nano satellite structure and provides the modularized reconfigurable micro-nano satellite structure. None of the existing studies in China at present relate to the modular design and on-orbit assembly of a high-orbit ultra-large satellite platform. Therefore, in order to adapt to the development trend of the high-orbit satellite platform and develop the general technical research of the high-orbit ultra-large integrated satellite platform, it is urgently needed to provide a configuration of an ultra-large modular assemblable satellite platform oriented to the application of the stationary orbit.
Disclosure of Invention
In view of the defects in the prior art, the invention aims to provide a static orbit ultra-large type assembled satellite platform configuration, which comprises the following steps: the system comprises a mother platform, a satellite and a satellite positioning system, wherein the mother platform comprehensively controls the whole satellite; the first module cabin and the second module cabin are connected with the mother platform and provide installation platforms for the single machine modules of the ultra-large platform; the first function cabin and the second function cabin are respectively connected with the first module cabin and the second module cabin and are used for carrying a working load and executing a specific working task; the satellite platform comprises a first connecting truss, a second connecting truss, a first energy module and a second energy module, wherein the first connecting truss and the second connecting truss are respectively installed on the first energy module and the second energy module, and the first energy module and the second energy module are used for supplying power for the satellite platform in a centralized manner; the first mechanical arm and the second mechanical arm are respectively arranged on the east surface and the west surface of the mother platform and are used for executing an on-orbit assembly task.
Optionally or preferably, the mother platform, the first energy module and the second energy module are symmetrically arranged in a double-solar-wing configuration and are driven by a single shaft.
Alternatively or preferably, the first and second modules are in the configuration of a plate-type enclosure open to north and south sides, and capable of storing standard modules of various sizes.
Optionally or preferably, the first and second connecting trusses are in a collapsed state when launched and are deployed one by one after rail assembly.
Optionally or preferably, the system further comprises a universal docking mechanism, and the mother platform, the first module cabin and the second module cabin, the first function cabin and the second function cabin, and the first connecting truss and the second connecting truss are assembled and connected through the universal docking mechanism.
Optionally or preferably, the universal docking mechanism includes a universal docking machine driving end and a universal docking mechanism passive end, the universal docking machine driving end and the universal docking mechanism passive end are respectively installed on the installation surfaces of the two satellite components, and the two satellite components can be connected through the universal docking machine driving end and the universal docking mechanism passive end.
Optionally or preferably, a group of universal docking mechanism passive ends are arranged on two mounting surfaces of the primary platform, a group of universal docking mechanism driving ends and a group of universal docking mechanism passive ends are respectively arranged on two mounting surfaces of the first module cabin, the second module cabin, the first function cabin and the second function cabin, and a group of universal docking mechanism driving ends are arranged on mounting surfaces of the first connection truss and the second connection truss.
Optionally or preferably, a group of universal docking mechanism passive ends is reserved on the outer end faces of the first energy module and the second energy module, so that the satellite platform can be continuously expanded in the east-west direction.
Alternatively or preferably, the first module cabin and the second module cabin are symmetrically installed in the east-west direction of the mother platform, the first function cabin and the second function cabin are symmetrically installed in the east-west direction of the mother platform, the first connection truss and the second connection truss are symmetrically installed in the east-west direction of the mother platform, and the first energy module and the second energy module are symmetrically installed in the east-west direction of the mother platform.
According to the assembling method of the static orbit ultra-large type assembled satellite platform configuration provided by the invention, the assembling method comprises the following steps:
step 1: launching the mother platform to enter the track;
step 2: launching the first module cabin to enter the rail, capturing the first module cabin by the mother platform through the first mechanical arm, and completing the butt joint of the first module cabin and the mother platform through the universal butt joint mechanism;
and step 3: launching the second module cabin to enter the rail, capturing the second module cabin by the mother platform through the second mechanical arm, and completing the butt joint of the second module cabin and the mother platform through the universal butt joint mechanism;
and 4, step 4: launching the first function cabin to enter the rail, capturing the first function cabin by the mother platform through the first mechanical arm, and completing the butt joint of the first function cabin and the first module cabin through the universal butt joint mechanism;
and 5: launching the second functional cabin to enter the rail, capturing the second functional cabin by the mother platform through the second mechanical arm, and completing the butt joint of the second functional cabin and the second module cabin through the universal butt joint mechanism;
step 6: launching the first energy module and the first connecting truss to enter the track, capturing the first connecting truss by the mother platform through the first mechanical arm, completing the butt joint of the first connecting truss and the first functional cabin through the universal butt joint mechanism, and then unfolding the first connecting truss in place;
and 7: launching the second energy module and the second connecting truss to enter the rail, capturing the second connecting truss by the mother platform through the second mechanical arm, completing the butt joint of the second connecting truss and the second functional cabin through the universal butt joint mechanism, and then unfolding the second connecting truss in place.
Compared with the prior art, the invention has the following beneficial effects:
the ultra-large assembled satellite platform adopts a multi-stage modular design concept, firstly, the ultra-large satellite platform is decomposed into a mother platform, a plurality of modular cabin sections and functional modules, and a scheme of multiple launching and on-orbit assembly is adopted, so that the limitation of carrying capacity is broken through; furthermore, the satellite single machine is subjected to modular design, and a special module cabin is designed to serve as a carrier of a single machine module, so that the requirement of on-orbit maintenance of a satellite platform is met. The high-degree modular design provides a new effective method for constructing the ultra-large satellite platform, and has important significance for prolonging the service life of the satellite platform and realizing the updating and upgrading of important single machines.
1. The method is suitable for a high-orbit ultra-large type assembled and maintainable comprehensive satellite platform;
2. the satellite platform adopts a universal assembly interface, can meet the requirements of quick assembly and integration of the ultra-large satellite platform, and enables the platform configuration to have the expandable capability;
3. the platform configuration adopts a multi-stage modular design, so that the requirement on carrying is reduced, the on-orbit maintenance of the satellite platform is facilitated, and the modular cabin section and a single machine are easy to produce in batch, thereby being beneficial to reducing the development cost;
4. the platform configuration space is open, the symmetry is good, the structure has no interference, the illumination condition is good, the on-orbit maintenance and the attitude control are convenient, and the energy utilization efficiency is high.
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 general configuration diagram of a configuration of a stationary orbit ultra-large type assembled satellite platform provided by the invention;
FIG. 2 is a configuration diagram of a mother platform;
FIG. 3 is a configuration diagram of a first module;
FIG. 4 is a configuration diagram of a first functional compartment;
FIG. 5 is a drawing showing the first connecting truss collapsed;
fig. 6 is a configuration diagram of the first connection truss and the first energy module in an unfolded state.
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.
Referring to fig. 1 to 6, an ultra-large type assembled satellite platform configuration in a stationary orbit according to the present invention includes: the system comprises a mother platform 1, wherein the mother platform 1 comprehensively controls the whole satellite; the system comprises a first module cabin 2 and a second module cabin 7, wherein the first module cabin 2 and the second module cabin 7 are connected with a mother platform 1 to provide an installation platform for a single machine module of an ultra-large platform; the first functional cabin 3 and the second functional cabin 8 are respectively connected with the first module cabin 2 and the second module cabin 7, and are used for carrying a working load and executing a specific working task; the system comprises a first connecting truss 5, a second connecting truss 10, a first energy module 4 and a second energy module 9, wherein the first connecting truss 5 and the second connecting truss 10 are respectively installed on the first energy module 4 and the second energy module 9, and the first energy module 4 and the second energy module 9 are used for supplying power to a satellite platform in a centralized manner; the first mechanical arm 6 and the second mechanical arm 11 are respectively arranged on the east surface and the west surface of the mother platform 1 and used for executing an on-orbit assembly task.
Alternatively or preferably, the mother platform 1, the first energy module 4 and the second energy module 9 are symmetrically arranged in a double-solar wing configuration, and are both driven by a single shaft.
Alternatively or preferably, the first module 2 and the second module 7 are in the form of open north-south panel-type enclosures capable of storing standard modules of various sizes.
Alternatively or preferably, the first and second connecting girders 5, 10 are in a collapsed state when launched and are deployed one by one after rail assembly.
Optionally or preferably, the system further comprises a universal docking mechanism, and the mother platform 1, the first module cabin 2 and the second module cabin 7, the first function cabin 3 and the second function cabin 8, and the first connecting truss 5 and the second connecting truss 10 are assembled and connected through the universal docking mechanism.
Optionally or preferably, the universal docking mechanism includes a universal docking machine driving end 13 and a universal docking mechanism passive end 12, the universal docking machine driving end 13 and the universal docking mechanism passive end 12 are respectively installed on the installation surfaces of the two satellite components, and the two satellite components may be connected through the universal docking machine driving end 13 and the universal docking mechanism passive end 12.
Optionally or preferably, a group of universal docking mechanism passive ends 12 is arranged on two mounting surfaces of the mother platform 1, a group of universal docking mechanism passive ends 12 and a group of universal docking mechanism active ends 13 are respectively arranged on two mounting surfaces of the first module cabin 2, the second module cabin 7, the first function cabin 3 and the second function cabin 8, and a group of universal docking mechanism active ends 13 is arranged on mounting surfaces of the first connection truss 5 and the second connection truss 10.
Optionally or preferably, a group of universal docking mechanism passive ends 12 is reserved on the outer end faces of the first energy module 4 and the second energy module 9, so that the satellite platform can be continuously expanded in the east-west direction.
Alternatively or preferably, the first module cabin 2 and the second module cabin 7 are symmetrically installed with respect to the east-west direction of the mother platform 1, the first function cabin 3 and the second function cabin 8 are symmetrically installed with respect to the east-west direction of the mother platform 1, the first connection truss 5 and the second connection truss 10 are symmetrically installed with respect to the east-west direction of the mother platform 1, and the first energy module 4 and the second energy module 9 are symmetrically installed with respect to the east-west direction of the mother platform 1.
According to the assembling method of the static orbit ultra-large type assembled satellite platform configuration provided by the invention, the assembling method comprises the following steps:
step 1: launching the mother platform 1 to enter the track;
step 2: launching the first module cabin 2 to enter the track, capturing the first module cabin 2 by the mother platform 1 through the first mechanical arm 6, and completing the butt joint of the first module cabin 2 and the mother platform 1 through the universal butt joint mechanism;
and step 3: launching the second module cabin 7 to enter the rail, capturing the second module cabin 7 by the mother platform 1 through the second mechanical arm 11, and completing the butt joint of the second module cabin 7 and the mother platform 1 through the universal butt joint mechanism;
and 4, step 4: launching the first functional cabin 3 to enter the track, capturing the first functional cabin 3 by the mother platform 1 through the first mechanical arm 6, and completing the butt joint of the first functional cabin 3 and the first module cabin 2 through the universal butt joint mechanism;
and 5: launching the second functional cabin 8 to enter the rail, capturing 11 the second functional cabin 8 by the mother platform 1 through the second mechanical arm, and completing the butt joint of the second functional cabin 8 and the second module cabin 7 through the universal butt joint mechanism;
step 6: launching the first energy module 4 and the first connecting truss 5 to enter the track, capturing the first connecting truss 5 by the mother platform 1 through the first mechanical arm 6, completing the butt joint of the first connecting truss 5 and the first functional cabin 3 through the universal butt joint mechanism, and then unfolding the first connecting truss 5 to be in place;
and 7: launching the second energy module 9 and the second connecting truss 10, entering the orbit, capturing the second connecting truss 10 by the mother platform 1 by using the second mechanical arm 11, completing the butt joint of the second connecting truss 10 and the second functional cabin 8 through the universal butt joint mechanism, and then unfolding the second connecting truss 10 to the position.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
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 (10)
1. A configuration for a stationary orbit ultra-large assembled satellite platform, comprising:
the system comprises a mother platform, a satellite and a satellite positioning system, wherein the mother platform comprehensively controls the whole satellite;
the first module cabin and the second module cabin are connected with the mother platform and provide installation platforms for the single machine modules of the ultra-large platform;
the first function cabin and the second function cabin are respectively connected with the first module cabin and the second module cabin and are used for carrying a working load and executing a specific working task;
the satellite platform comprises a first connecting truss, a second connecting truss, a first energy module and a second energy module, wherein the first connecting truss and the second connecting truss are respectively installed on the first energy module and the second energy module, and the first energy module and the second energy module are used for supplying power for the satellite platform in a centralized manner;
the first mechanical arm and the second mechanical arm are respectively arranged on the east surface and the west surface of the mother platform and are used for executing an on-orbit assembly task.
2. The geostationary orbit ultra-large assembled satellite platform configuration of claim 1, wherein: the mother platform, the first energy module and the second energy module are symmetrically arranged in a double-solar-wing configuration and are driven by a single shaft.
3. The geostationary orbit ultra-large assembled satellite platform configuration of claim 1, wherein: the first module cabin and the second module cabin are in a plate cabin structure with an open north-south surface and can store standard modules with various sizes.
4. The geostationary orbit ultra-large assembled satellite platform configuration of claim 1, wherein: the first connecting truss and the second connecting truss are in a furled state when being launched and are unfolded one by one after being assembled on the rails.
5. The geostationary orbit ultra-large assembled satellite platform configuration of claim 1, wherein: the first module cabin and the second module cabin are connected with the first functional cabin through the first connecting truss and the second connecting truss through the second connecting truss.
6. The geostationary orbit ultra-large assembled satellite platform configuration of claim 5, wherein: the universal docking mechanism comprises a universal docking machine driving end and a universal docking mechanism passive end, the universal docking machine driving end and the universal docking mechanism passive end are respectively installed on installation surfaces of the two satellite assemblies, and the two satellite assemblies can be connected with the universal docking mechanism passive end through the universal docking machine driving end.
7. The geostationary orbit ultra-large assembled satellite platform configuration of claim 6, wherein: the two installation surfaces of the primary platform are provided with a group of universal docking mechanism passive ends, the two installation surfaces of the first module cabin, the second module cabin, the first function cabin and the second function cabin are respectively provided with a group of universal docking mechanism active ends and a group of universal docking mechanism passive ends, and the installation surfaces of the first connection truss and the second connection truss are provided with a group of universal docking mechanism active ends.
8. The geostationary orbit ultra-large assembled satellite platform configuration of claim 6, wherein: and a group of universal butt joint mechanism passive ends are reserved on the outer end faces of the first energy module and the second energy module, so that the satellite platform can be continuously expanded in the east-west direction.
9. The geostationary orbit ultra-large assembled satellite platform configuration of claim 1, wherein: first module cabin and second module cabin about female platform east-west direction symmetry installation, first function cabin and second function cabin about female platform east-west direction symmetry installation, first connection truss with the truss is about to connected to the second female platform east-west direction symmetry installation, first energy module and second energy module about female platform east-west direction symmetry installation.
10. A method of assembling a stationary orbit very large assemblable satellite platform configuration as claimed in claim 5, comprising the steps of:
step 1: launching the mother platform to enter the track;
step 2: launching the first module cabin to enter the rail, capturing the first module cabin by the mother platform through the first mechanical arm, and completing the butt joint of the first module cabin and the mother platform through the universal butt joint mechanism;
and step 3: launching the second module cabin to enter the rail, capturing the second module cabin by the mother platform through the second mechanical arm, and completing the butt joint of the second module cabin and the mother platform through the universal butt joint mechanism;
and 4, step 4: launching the first function cabin to enter the rail, capturing the first function cabin by the mother platform through the first mechanical arm, and completing the butt joint of the first function cabin and the first module cabin through the universal butt joint mechanism;
and 5: launching the second functional cabin to enter the rail, capturing the second functional cabin by the mother platform through the second mechanical arm, and completing the butt joint of the second functional cabin and the second module cabin through the universal butt joint mechanism;
step 6: launching the first energy module and the first connecting truss to enter the track, capturing the first connecting truss by the mother platform through the first mechanical arm, completing the butt joint of the first connecting truss and the first functional cabin through the universal butt joint mechanism, and then unfolding the first connecting truss in place;
and 7: launching the second energy module and the second connecting truss to enter the rail, capturing the second connecting truss by the mother platform through the second mechanical arm, completing the butt joint of the second connecting truss and the second functional cabin through the universal butt joint mechanism, and then unfolding the second connecting truss in place.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112441261A (en) * | 2020-12-01 | 2021-03-05 | 哈尔滨工业大学 | Method for in-orbit cooperative assembly of ultra-large space telescope by multi-space robot |
| CN113581502A (en) * | 2021-08-11 | 2021-11-02 | 哈尔滨工业大学 | On-orbit assembly method of ultra-large space telescope based on multi-space robot system |
| CN113879568A (en) * | 2021-09-06 | 2022-01-04 | 中国科学院微小卫星创新研究院 | Pluggable satellite thermal control system and method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2088491C1 (en) * | 1993-08-31 | 1997-08-27 | Ракетно-космическая корпорация "Энергия" им.С.П.Королева | Long-endurance manned orbital cable complex |
| US7469864B2 (en) * | 2006-02-28 | 2008-12-30 | Bigelow Aerospace | Method for assemblying and landing a habitable structure on an extraterrestrial body |
| US20170259946A1 (en) * | 2017-05-30 | 2017-09-14 | Wayne Neville White, JR. | Interplanetary spacecraft |
| CN110182388A (en) * | 2019-05-15 | 2019-08-30 | 中国空间技术研究院 | Based on pre-integrated truss can in-orbit assembling spacecraft |
| 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 |
-
2020
- 2020-04-26 CN CN202010339765.3A patent/CN111572814A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2088491C1 (en) * | 1993-08-31 | 1997-08-27 | Ракетно-космическая корпорация "Энергия" им.С.П.Королева | Long-endurance manned orbital cable complex |
| US7469864B2 (en) * | 2006-02-28 | 2008-12-30 | Bigelow Aerospace | Method for assemblying and landing a habitable structure on an extraterrestrial body |
| US20170259946A1 (en) * | 2017-05-30 | 2017-09-14 | Wayne Neville White, JR. | Interplanetary spacecraft |
| CN110182388A (en) * | 2019-05-15 | 2019-08-30 | 中国空间技术研究院 | Based on pre-integrated truss can in-orbit assembling spacecraft |
| 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 |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112441261A (en) * | 2020-12-01 | 2021-03-05 | 哈尔滨工业大学 | Method for in-orbit cooperative assembly of ultra-large space telescope by multi-space robot |
| CN112441261B (en) * | 2020-12-01 | 2022-07-05 | 哈尔滨工业大学 | Method for on-orbit cooperative assembly of ultra-large space telescope by multi-space robot |
| CN113581502A (en) * | 2021-08-11 | 2021-11-02 | 哈尔滨工业大学 | On-orbit assembly method of ultra-large space telescope based on multi-space robot system |
| CN113581502B (en) * | 2021-08-11 | 2023-05-26 | 哈尔滨工业大学 | On-orbit assembly method of ultra-large space telescope based on multi-space robot system |
| CN113879568A (en) * | 2021-09-06 | 2022-01-04 | 中国科学院微小卫星创新研究院 | Pluggable satellite thermal control system and method |
| CN113879568B (en) * | 2021-09-06 | 2022-07-12 | 中国科学院微小卫星创新研究院 | Pluggable satellite thermal control system and method |
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Application publication date: 20200825 |