CN100575191C - A kind of main load-carrying structure of spacecraft - Google Patents
A kind of main load-carrying structure of spacecraft Download PDFInfo
- Publication number
- CN100575191C CN100575191C CN200810222832A CN200810222832A CN100575191C CN 100575191 C CN100575191 C CN 100575191C CN 200810222832 A CN200810222832 A CN 200810222832A CN 200810222832 A CN200810222832 A CN 200810222832A CN 100575191 C CN100575191 C CN 100575191C
- Authority
- CN
- China
- Prior art keywords
- propulsion module
- frame
- main frame
- main
- star
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Moulding By Coating Moulds (AREA)
- Photovoltaic Devices (AREA)
Abstract
The invention discloses a kind of main load-carrying structure of spacecraft, comprise propulsion module structure, star truss structure (6) and electronic cabin structure; The top of described propulsion module structure connects the electronic cabin structure, and the bottom is as whole star accuracy detection reference plane and the attachment face that the propulsion module instrument and equipment is provided; Described star truss structure (6) is a load installing frame that is supported by strut, is positioned at the electronic cabin structure, is used to install capacity weight, and the lower end of its strut is fixedly connected on the top of propulsion module structure.Because the hybrid main structure that the present invention adopts outside frame lateral plate structure and inner star truss structure to constitute inside and outside two load paths is transmitted whole spaceborne lotus, Path of Force Transfer is short and continuous, compact conformation, barycenter are low, have satisfied the high rigidity of whole satellite, little inertia requirement.
Description
Technical field
The present invention relates to a kind of spacecraft main force support structure, especially for a kind of novel small satellite main force support structure that improves small satellite platform adaptive capacity.
Background technology
The main force support structure of spacecraft is mainly used in to bear and acts on spaceborne static(al) and dynamic loading, for contained instrument and equipment provides the fixed installation interface and keeps stabilized accuracy, guarantees overall geometry.
With the satellite is example, and the radical function of satellite main force support structure is: bear the static(al) and the dynamic loading that act on the satellite, for spaceborne instrument and equipment provides the fixed installation interface and keeps stabilized accuracy, guarantee whole star geometric configuration.
What the instrument and equipment of each subsystem of satellite had is directly installed on the primary load bearing member, and most of instrument and equipments are connected on the primary load bearing member by less important members such as dividing plate and wallboards.The total arrangement of primary load bearing component form and mass property will adapt to the mechanical environment of carrier rocket.The load direction of the primary load bearing member of satellite structure system is consistent with the carrier rocket thrust direction.
Main force support structure is the spine of satellite.It bears axially, crooked, load such as shear and reverse.Satellite is owing to the form difference of selected primary load bearing member, and its configuration also has very big difference.At present main force support structure generally can be divided into four kinds of forms: box-shaped is board-like, center load cartridge type, truss-like, shell type.
The box-shaped plank frame: main force support structure is mainly the box type construction that honeycomb sandwich panel is formed.CAST968 small satellite platform, CAST2000 small satellite flat-bed main force support structure as China are exactly the box-shaped plank frame that adopts, and representative type also has the A2100 satellite platform of american lockheed LMT.If select boxboard formula main force support structure, because the capacity weight camera is comparatively huge, volume exclusion is very big, is that vertical installation or horizontal installation all are not easy to the general assembly operation.
Center loaded cylinder structure: the primary load bearing member of this type of satellite is positioned at the centre of satellite body.Dongfanghong-III satellite platform as China constitutes main force support structure by center loaded cylinder, structural slab exactly.The sun wing, antenna and instrument and equipment etc. are connected on the load-carrying member by connecting interface, support etc., and transfer loads on the main Path of Force Transfer.Be characterized in main by interior Path of Force Transfer transmitted load, framed plate structures such as satellite-rocket docking ring, dividing plate also are by interior Path of Force Transfer transmitted load.
For small satellite, if want the center loaded cylinder to play the primary load bearing effect, its diameter must be suitable with the butt joint ring size, like this space outerpace is very little, the installation space that provides is few, and the inner space is lower because of the mounting or dismounting space requirement degree of utilization of camera, and is awkward.Be the side plate form or increase the platform form erecting equipment of all having no idea, make whole star rotor inertia also be unfavorable for the overall little inertia requirement that proposes greatly even instrument and equipment is distributed in the periphery.And, therefore to so also influence the rigidity of loaded cylinder in the perforate of loaded cylinder corresponding site because the driving engine of propulsion system need stretch out the celestial body outside.
Truss structure: the truss that its primary load bearing member is made up of rod member.HS 702 satellite platforms as U.S. Hughes Electronics.Truss can have various ways, and therefore, the configuration of truss bearing satellite also is variation.Can adopt triangular truss or polygonal truss framework.The configuration of truss-like primary load bearing member is different, and the configuration of satellite is also just different.Truss structure is very high to the requirement of material and structure, and less as the example of main force support structure at home, technical risk is bigger.
Outer shell construction: as the primary load bearing member, mainly is by outer Path of Force Transfer transmitted load with the cabin body.This class satellite often is formed by connecting by a plurality of cabins, is connected by cabin body flange between cabin and the cabin, bottom load of bearing whole spacecraft with carrier rocket bonded assembly cabin.Adopt this kind structure mostly as the recoverable satellite of China, the manned spacecraft of various countries.But when there is the bigger capacity weight of quality in the satellite centre, also be not easy to only select shell as main force transferring structure.
Above-mentioned several structure all adopts mono-power transmission route, causes longitudinal axis inertia big, can not satisfy the manoevreability of capacity weight simultaneously.At present, the mono-main force support structure can not adapt to the quick power operated demand of small satellite, but the main force support structure of comprehensive multiple mode, difficult the realization do not seen the pertinent literature report on design and structure.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, provide that longitudinal axis inertia is little, capacity weight is implemented to roll easily, pitching is motor-driven, adopts a kind of main load-carrying structure of spacecraft in inside and outside pair of load path.
Technical solution of the present invention is: a kind of main load-carrying structure of spacecraft comprises propulsion module structure, star truss structure and electronic cabin structure; The top of described propulsion module structure connects the electronic cabin structure, and the bottom is as whole star accuracy detection reference plane and the attachment face that the propulsion module instrument and equipment is provided; Described star truss structure is a load installing frame that is supported by strut, is positioned at the electronic cabin structure, is used to install capacity weight, and the lower end of its strut is fixedly connected on the top of propulsion module structure.
Described propulsion module structure is the frustum shape, comprises propulsion module lower end frame, propulsion module housing, propulsion module reinforcement stringer and propulsion module upper end frame; Propulsion module is strengthened stringer and is distributed in around the propulsion module housing, two ends are captive joint propulsion module lower end frame and propulsion module upper end frame respectively, the upper surface of propulsion module upper end frame connects the electronic cabin structure, and the circular conical surface of frame bottom, propulsion module upper end is the joint face of propulsion module housing.
The strut quantity of described star truss structure is to be no less than six even numbers, the shared jointing in the top of per two struts, and last end junction is connected with the load installing frame, and following end junction is connected with the propulsion module structure.
Described propulsion module lower end frame is provided with inside flange, as whole star accuracy detection reference plane and the attachment face that the propulsion module instrument and equipment is provided.
Described electronic cabin structure comprises angle bead and reinforcement support on angle bead under the main frame, main frame column, the main frame, angle bead on angle bead and the main frame is being installed the reinforcement support near angle bead place on the main frame on the main frame column under the main frame column connection main frame.
Described electronic cabin structure also comprises T shape angle bead, supports the main frame column under main frame on angle bead and the main frame between the angle bead.
The present invention's beneficial effect compared with prior art is:
1, satellite main force support structure of the present invention docks with carrier rocket, and employing outside frame lateral plate structure and inner star truss structure constitute the hybrid main structure in inside and outside two load paths and transmit whole spaceborne lotus, and Path of Force Transfer is short and continuous.Its main Path of Force Transfer is:
In: capacity weight camera → capacity weight star lattice supporting framework → propulsion module lower end frame → delivery interface frame, mating frame;
Outward: top board and side plate → main frame structure → propulsion module upper end frame → propulsion module housing → propulsion module lower end frame → delivery interface frame, mating frame.
Therefore, compact conformation of the present invention, barycenter are low, have satisfied the high rigidity of whole satellite, little inertia requirement.
2, the satellite body structure has broken through the boxboard formula node configuration of more employing in the past, rationally use plate and shell structure, truss structure and band to strengthen the load circular cone tube of stringer, capacity weight docks the star truss structure that is adopted and improves setting accuracy to greatest extent with platform.Form the star truss structure and add the dual path load-carrying construction that combines inside and outside the outer panel main frame, make the satellite integral rigidity obtain guaranteeing preferably.
Description of drawings
Fig. 1 is the general view of main force support structure of the present invention;
Fig. 2 is the general view of propulsion module structure of the present invention;
Fig. 3 is the general view of star truss structure of the present invention;
Fig. 4 is the general view of main frame structure of the present invention.
The specific embodiment
As shown in Figure 1, a kind of novel satellite main force support structure of the present invention comprises propulsion module structure, star truss structure and electronic cabin structure; The top of propulsion module structure connects the electronic cabin structure, and the bottom is as whole star accuracy detection reference plane and the attachment face that the propulsion module instrument and equipment is provided; The star truss structure is positioned at the electronic cabin structure, is a load installing frame that is supported by strut, is used to install capacity weight, and the lower end of its strut is fixedly connected on the top of propulsion module structure.
As shown in Figure 2, the propulsion module structure is a frustum shape, comprises propulsion module lower end frame 1, propulsion module housing 2, propulsion module reinforcement stringer 3 and propulsion module upper end frame 4; Propulsion module is strengthened stringer 3 and is distributed in around the propulsion module housing 2, its two ends are captive joint propulsion module lower end frame 1 and propulsion module upper end frame 4 respectively, the upper surface of propulsion module upper end frame 4 connects the electronic cabin structure, be the regular hexagon structure, the circular conical surface of frame 4 bottoms, propulsion module upper end is joint faces of propulsion module housing 2.
Propulsion module lower end frame 1 is provided with inside flange, as whole star accuracy detection reference plane and the attachment face that the propulsion module instrument and equipment is provided.
As shown in Figure 3, star truss structure 6 is a load installing frame that is supported by strut, is used to install capacity weight camera and associated load, and the soil rigidity of camera is provided.Totally eight of the struts of present embodiment, shared 1 jointing in the top of per two struts, last end junction is connected with the load installing frame, and following end junction is connected with the propulsion module lower end frame 1 of propulsion module structure.
As shown in Figure 4, the electronic cabin structure in the present embodiment comprises under six main frames on angle bead 5, six main frame columns 7, six main frames that angle bead 9 and six strengthen supporting 10 and form.Angle bead 9 on angle bead 5 and the main frame is being installed reinforcement support 10 near angle bead 9 places on the main frame on the main frame column 7 under the main frame column 7 connection main frames.
Under main frame, on angle bead 5 and the main frame between the angle bead 9, also have six T shape angle beads 8, be used to support main frame column 7.
Main frame structure is the central module of electronic compartment, and main effect is to make each structural slab be linked to be an integrally closed structure, and guarantees the intensity of electronic compartment and propulsion module junction.
The main setting-up procedure of this kind small satellite main force support structure is:
(1) the propulsion module lower end frame 1 of propulsion module structure, propulsion module housing 2, propulsion module are strengthened stringer 3, propulsion module upper end frame 4 mainly connects in aggregates by riveted joint, at the excessive position of local thickness, when riveted joint can not be finished,, prevent and peel off phenomenon with the replacement that is spirally connected.
(2) consider the setting accuracy of capacity weight and the comfort feature of general assembly operation, adopted star truss structure 6 to realize that capacity weight docks with flat-bed.With star truss structure 6 bottom bolted connections on the inside flange of propulsion module lower end frame 1.
(3) angle bead 5 is connected by being spirally connected or riveting to finish with propulsion module upper end frame 4 under six main frames will having riveted.
(4) will by angle bead on six main frame columns 7, six main frame T shape angle beads 8, six main frames 9, six strengthen supporting 10 by transition angle box connect into a single-piece main frame structure with propulsion module structure bonded assembly main frame under angle bead 5 pass through bolted connection.
Claims (4)
1, a kind of main load-carrying structure of spacecraft is characterized in that comprising propulsion module structure, star truss structure (6) and electronic cabin structure; The top of described propulsion module structure connects the electronic cabin structure, and the bottom is as whole star accuracy detection reference plane and the attachment face that the propulsion module instrument and equipment is provided; Described star truss structure (6) is a load installing frame that is supported by strut, is positioned at the electronic cabin structure, is used to install capacity weight, and the lower end of its strut is fixedly connected on the top of propulsion module structure;
Described propulsion module structure is the frustum shape, comprises propulsion module lower end frame (1), propulsion module housing (2), propulsion module reinforcement stringer (3) and propulsion module upper end frame (4); Propulsion module is strengthened stringer (3) and is distributed in propulsion module housing (2) on every side, two ends are captive joint propulsion module lower end frame (1) and propulsion module upper end frame (4) respectively, the upper surface of propulsion module upper end frame (4) connects the electronic cabin structure, and the circular conical surface of frame (4) bottom, propulsion module upper end is the joint face of propulsion module housing;
The strut quantity of described star truss structure (6) is to be no less than six even numbers, shared 1 jointing in the top of per two struts, and last end junction is connected with the load installing frame, and following end junction is connected with the propulsion module structure.
2, according to a kind of main load-carrying structure of spacecraft of claim 1, it is characterized in that: described propulsion module lower end frame (1) is provided with inside flange, as whole star accuracy detection reference plane and the attachment face that the propulsion module instrument and equipment is provided.
3, according to a kind of main load-carrying structure of spacecraft of claim 1, it is characterized in that: described electronic cabin structure comprises angle bead (9) and reinforcement support (10) on angle bead under the main frame (5), main frame column (7), the main frame, angle bead (9) on angle bead (5) and the main frame upward locates to install reinforcement support (10) near angle bead (9) on the main frame at main frame column (7) under main frame column (7) the connection main frame.
4, according to a kind of main load-carrying structure of spacecraft of claim 3, it is characterized in that: described electronic cabin structure also comprises T shape angle bead (8), is positioned to support main frame column (7) on angle bead under the main frame (5) and the main frame between the angle bead (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810222832A CN100575191C (en) | 2008-09-19 | 2008-09-19 | A kind of main load-carrying structure of spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810222832A CN100575191C (en) | 2008-09-19 | 2008-09-19 | A kind of main load-carrying structure of spacecraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101381003A CN101381003A (en) | 2009-03-11 |
| CN100575191C true CN100575191C (en) | 2009-12-30 |
Family
ID=40461104
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200810222832A Active CN100575191C (en) | 2008-09-19 | 2008-09-19 | A kind of main load-carrying structure of spacecraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100575191C (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102616385A (en) * | 2012-04-11 | 2012-08-01 | 深圳航天东方红海特卫星有限公司 | Truss-type satellite structure with central capsule |
Families Citing this family (42)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101848612A (en) * | 2010-05-07 | 2010-09-29 | 北京航空航天大学 | Portable electronic equipment cabin |
| CN102009746B (en) * | 2010-11-08 | 2012-11-14 | 航天东方红卫星有限公司 | Octagonal battery-equipped array upright post micro satellite configuration |
| CN102001452B (en) * | 2010-11-08 | 2013-01-23 | 航天东方红卫星有限公司 | Method for realizing integration of energy control and main force bearing plate of satellite |
| CN102303710B (en) * | 2011-06-08 | 2013-05-01 | 航天东方红卫星有限公司 | General propelling module for small satellites |
| CN102502426B (en) * | 2011-10-20 | 2014-07-23 | 中联重科股份有限公司 | Crane boom and crane |
| CN102556367B (en) * | 2011-11-15 | 2014-09-10 | 上海卫星装备研究所 | Method for assembling structures of light product platforms |
| US9180984B2 (en) | 2012-05-11 | 2015-11-10 | The Boeing Company | Methods and apparatus for performing propulsion operations using electric propulsion systems |
| US8915472B2 (en) | 2012-05-11 | 2014-12-23 | The Boeing Company | Multiple space vehicle launch system |
| CA2831309C (en) * | 2012-12-04 | 2017-05-30 | The Boeing Company | Methods and apparatus for performing propulsion operations using electric propulsion systems |
| CN103612775B (en) * | 2013-11-20 | 2016-01-06 | 西北工业大学 | The multi-functional load-carrying construction of a kind of micro-satellite |
| CN104698509A (en) * | 2013-12-10 | 2015-06-10 | 上海卫星工程研究所 | Geostationary orbit meteorological satellite |
| CN103935529B (en) * | 2014-04-29 | 2018-01-12 | 上海卫星工程研究所 | A kind of quick response satellite structure |
| CN103963998B (en) * | 2014-05-06 | 2017-03-01 | 上海卫星工程研究所 | A kind of hexagonal-shaped frame primary load bearing satellite structure |
| CN103963997A (en) * | 2014-05-06 | 2014-08-06 | 上海卫星工程研究所 | Small satellite polygonal force bearing barrel |
| CN104567681B (en) * | 2015-01-08 | 2018-04-27 | 航天东方红卫星有限公司 | A kind of accurate measurement method of satellite precise benchmark truss structure device |
| CN105083590B (en) * | 2015-09-02 | 2017-03-22 | 南京理工大学 | Multiunit cubesat main load-bearing structure |
| CN105235916B (en) * | 2015-10-27 | 2017-10-27 | 上海微小卫星工程中心 | A kind of integrated satellite of compact layout |
| CN105438503B (en) * | 2015-11-30 | 2018-02-09 | 中国空间技术研究院 | A kind of satellite-rocket docking device |
| CN106248384B (en) * | 2016-09-12 | 2018-07-03 | 西安航天动力试验技术研究所 | A kind of power for liquid propellant rocket engine test transmits Change-over frame and design method |
| CN106864773B (en) * | 2017-03-31 | 2018-05-22 | 北京蓝箭空间科技有限公司 | A kind of instrument cabin structure of vehicle |
| CN107323686B (en) * | 2017-05-16 | 2019-10-29 | 上海卫星工程研究所 | Load lays flat test with seperated open type mounting device |
| CN107505799B (en) * | 2017-09-18 | 2020-04-10 | 北京空间飞行器总体设计部 | Concentrated point type stressed load supporting structure |
| CN108045597A (en) * | 2017-10-23 | 2018-05-18 | 上海卫星工程研究所 | Modularization, sectional satellite structure |
| CN107902107B (en) * | 2017-11-17 | 2023-09-05 | 南京理工大学 | Six-unit cube star main bearing structure |
| CN107878782A (en) * | 2017-11-17 | 2018-04-06 | 南京理工大学 | Three unit cube star main force support structures |
| CN108583936A (en) * | 2018-04-04 | 2018-09-28 | 上海宇航系统工程研究所 | A kind of strong maneuverable spacecraft configuration of hollow carrying greatly |
| CN108725844B (en) * | 2018-06-26 | 2020-04-21 | 蓝箭航天空间科技股份有限公司 | Control cabin structure of space carrier |
| CN109094820B (en) * | 2018-07-11 | 2021-03-16 | 上海空间推进研究所 | Annular flat-plate stove type composite material main bearing structural member |
| CN109015510B (en) * | 2018-07-26 | 2020-02-18 | 北京卫星环境工程研究所 | Stringer installation method of instrument installation platform in sealed cabin secondary structure |
| CN109050873A (en) * | 2018-08-31 | 2018-12-21 | 上海宇航系统工程研究所 | A kind of aircraft section structure with large size opening |
| CN109496098B (en) * | 2018-09-18 | 2020-10-09 | 上海宇航系统工程研究所 | Spacecraft electronic equipment mounting structure and spacecraft |
| CN109823576B (en) * | 2019-02-20 | 2020-11-24 | 上海卫星工程研究所 | Bearing connection structure for planetary lander |
| CN110697087A (en) * | 2019-10-24 | 2020-01-17 | 北京空间飞行器总体设计部 | Satellite propulsion service cabin structure |
| CN111846290B (en) * | 2020-08-06 | 2022-03-01 | 北京中科宇航技术有限公司 | Carrier rocket and launching support tail section thereof |
| CN112298605B (en) * | 2020-09-29 | 2022-03-04 | 北京空间飞行器总体设计部 | Plate-and-bar type satellite main structure |
| CN112498742B (en) * | 2021-01-13 | 2022-07-19 | 北京工商大学 | Electronic cabin adopting food steamer type closed box structure |
| CN112758353B (en) * | 2021-01-13 | 2022-07-15 | 中国科学院高能物理研究所 | Highly integrated, modular, fully shielded payload structure for astronomical satellites |
| CN112993536B (en) * | 2021-02-07 | 2022-12-09 | 中国科学院微小卫星创新研究院 | Antenna load compartment configuration |
| CN112977882A (en) * | 2021-03-12 | 2021-06-18 | 上海卫星工程研究所 | High orbit satellite platform structure with central force bearing cylinder type storage boxes tiled in parallel |
| CN113911393A (en) * | 2021-09-29 | 2022-01-11 | 北京空间飞行器总体设计部 | Cone-prism transition type honeycomb interlayer bearing cylinder structure |
| CN114162350B (en) * | 2021-12-01 | 2023-09-29 | 上海宇航系统工程研究所 | Main structure of sun alignment orientation device suitable for space station |
| CN114408215B (en) * | 2021-12-27 | 2024-02-09 | 航天东方红卫星有限公司 | Satellite configuration suitable for rapid maneuvering ultra-stable imaging |
-
2008
- 2008-09-19 CN CN200810222832A patent/CN100575191C/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102616385A (en) * | 2012-04-11 | 2012-08-01 | 深圳航天东方红海特卫星有限公司 | Truss-type satellite structure with central capsule |
| CN102616385B (en) * | 2012-04-11 | 2015-01-14 | 深圳航天东方红海特卫星有限公司 | Truss-type satellite structure with central capsule |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101381003A (en) | 2009-03-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN100575191C (en) | A kind of main load-carrying structure of spacecraft | |
| CN107889482B (en) | Stackable satellite and stacking method thereof | |
| CN111703592B (en) | Large commercial remote sensing satellite platform configuration and assembly method | |
| CN103935529B (en) | A kind of quick response satellite structure | |
| CN103863577A (en) | Frame panel type satellite configuration and modular satellite | |
| RU2617162C1 (en) | Spacecraft, its payload module and service system module | |
| CN105235916B (en) | A kind of integrated satellite of compact layout | |
| CN109050989B (en) | Double-star point type adapter | |
| CN110697087A (en) | Satellite propulsion service cabin structure | |
| CN107745829B (en) | Lightweight spacecraft main structure | |
| CN109941459A (en) | A kind of satellite configuration and satellite | |
| CN210246650U (en) | Solar module floating system and structure thereof | |
| CN114408215B (en) | Satellite configuration suitable for rapid maneuvering ultra-stable imaging | |
| CN108045597A (en) | Modularization, sectional satellite structure | |
| CN112357118B (en) | Manned lunar surface lander based on truss structure | |
| CN111409871B (en) | Satellite platform configuration with extendable truss node pods | |
| CN214524462U (en) | Moonlet structure system and moonlet | |
| RU2617018C1 (en) | Service system module | |
| CN114435627A (en) | Satellite structure and satellite assembly method | |
| CN116513487B (en) | Multifunctional upper-level configuration and space carrier | |
| CN219192571U (en) | Compact primary and secondary star structure | |
| CN112455721B (en) | Large-bearing modular service cabin structure | |
| RU159978U1 (en) | SERVICE MODULE | |
| US3517897A (en) | Multi-module thrust mount | |
| RU2621221C1 (en) | Service system module |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |