CN104217048A - Method for managing complex spacecraft three-dimensional model - Google Patents
Method for managing complex spacecraft three-dimensional model Download PDFInfo
- Publication number
- CN104217048A CN104217048A CN201310220927.1A CN201310220927A CN104217048A CN 104217048 A CN104217048 A CN 104217048A CN 201310220927 A CN201310220927 A CN 201310220927A CN 104217048 A CN104217048 A CN 104217048A
- Authority
- CN
- China
- Prior art keywords
- coordinate system
- skeleton pattern
- layout
- spacecraft
- dimensional model
- 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.)
- Pending
Links
Abstract
The invention relates to a method for managing a complex spacecraft three-dimensional model. Framework models of the complex spacecraft three-dimensional model are divided into a configuration-layer framework model and a layout-layer framework model from top to bottom. The configuration-layer framework model is a first-layer framework model and is composed of top layer coordinate systems for expressing a spacecraft, large system interfaces, complete machine configuration and cabin interfaces. The layout-layer framework model is a second-layer framework model and is used for expressing layout information of single equipment, loads and structural mechanisms of all subsystems in the spacecraft on the basis of receiving configuration layer information, a single equipment coordinate system is built, transmission from top to bottom is carried out through the uniform coordinate system of the whole spacecraft three-dimensional model, the uniform data transmission and assembling standard is built, three-dimensional model information is managed, the changeability and accuracy of the spacecraft three-dimensional model are improved, cooperation and integration between designers are achieved, and therefore fast derivation and deformation of serialization products are achieved.
Description
Technical field
The invention belongs to manned spacecraft field, relate to a kind of management method of Complex Spacecraft three-dimensional model.
Background technology
Spacecraft three-dimensional modeling is a complicated systems engineering, by common collaborative designs of a plurality of research institutes such as structure collectivity, structure subsystem and unit research institutes, completed, whole Process in Cooperative Design be one from being abstracted into concrete progressive process, can be divided into Configuration Design stage, general assembly topological design stage, unit layout stage, detailed design phase, general assembly stage and support stage in-orbit.
In the cooperative surroundings of spacecraft Life cycle, take top-down method for designing, the general arrangement of each subsystem will be by totally completing, within overall minute, task each subsystem footprint, subsystem is distributed interior spatial structure according to overall institute to footprint, then under pass to parts and components and carry out detailed design.
Three-dimensional model need to carry out data transmission and model modification between these different departments, in the process of every data transfer and model modification, can completing technology state confirmation between each department and model modification confirm operation, for making three-dimensional model there is associated modification effect, revising, in change, automatically safeguard the consistance of three-dimensional modeling data, from the layer of structure of spacecraft, start with, by the general structure layout of spacecraft, design constraint, basis of reference and layout etc. thereof are out abstract, and with the point in space, line, face and parameter sketch etc. construct skeleton pattern, the space layout of reflection product, locus shape between parts, the space line framework structure of the main framework that topological relation and assembling conjunction relation etc. require, and take skeleton pattern as transmitting carrier, in general assembly topological design, when unit layout and detailed design, the design basis that upstream is set up, geometric properties, coherent references etc. are with reference to being delivered in the design of downstream, become the positioning datum of downstream design, design basis and fixed reference feature.
Spacecraft skeleton pattern is conventionally by reference point, the reference characteristic such as datum line and reference field forms, and using these benchmark and determine each parts size and mutual referring-to relation as the positioning datum of Assembly of the parts in assembling process, downstream designer carries out reference by skeleton pattern and receives, and carry out further transmitting downstream after refinement according to the designing requirement of this level, thereby realize the transmission for the second time of reference relation, the rest may be inferred until bottom designer is arrived in design reference, the method that this reference is successively transmitted according to this, relevance between model is very complicated, for issuing, can not there is deletion by associated geometry, cut apart, merge, intersect and wait the operation that affects geometric element ID, and there will be the circulation reference between part, must make the very big redundancy of data, cause reference relation chaotic, be not easy to management.
Summary of the invention
It is to overcome the problem that traditional spacecraft three-dimensional model management exists that the technology that the present invention solves is dealt with problems, and proposes a kind of management method of the Complex Spacecraft three-dimensional model based on coordinate system skeleton pattern, comprises the steps:
1) by top-down configuration layer skeleton pattern and the layout layer skeleton pattern of being divided into of Complex Spacecraft three-dimensional model skeleton pattern, wherein, configuration layer skeleton pattern is ground floor skeleton pattern, by expressing spacecraft, forms with large system interface, whole device configuration, the interfacial top layer coordinate system of cabin section; Layout layer skeleton pattern is skeleton pattern for the second time, receiving on the basis of configuration layer information, for expressing stand-alone device, the load of each subsystem of spacecraft, the layout information of structural mechanism;
2) carry out described configuration layer skeleton pattern design, comprise: set up whole device coordinate system, cabin section coordinate system and interphase coordinate system, the coordinate system of setting up is respectively as the frame of reference of whole device and the corresponding frame of reference, and transmit downstream with the form of issue geometry according to designing requirement, as the input of layout layer design;
3) set up described layout layer skeleton pattern, by the mode directly copying, receive and resolve the dependency basis conventional coordinates in configuration layer skeleton pattern, the superior and the subordinate Model Mountings adopts subordinate's skeleton pattern to set coordinate system and higher level's skeleton pattern and sets the coordinate system assembling of aliging, and carries out the establishment of follow-up equipment installation coordinate system in layout layer as reference;
4), in described layout layer skeleton pattern, each stand-alone device installation requirement providing according to each subsystem is set up whole stand-alone device layout coordinate systems;
5) in stand-alone device when assembling,, apparatus for establishing coordinate system on equipment, carries out coordinate system according to the mode of coordinate system constraint and unit layout coordinate system corresponding in layout layer skeleton pattern and aligns and set up assembly relation.
The present invention has realized whole spacecraft three-dimensional model and has carried out top-down transmission by unified coordinate system, unified data transmission and the reference for assembling set up, realized the management of three-dimensional model information, the assembling of the superior and the subordinate's model, assembled at the corresponding levels, stand-alone device is installed and is realized by unified coordinate system, overcome in the past monoskeleton model with reference to the limitation of transmitting, effectively solved design with reference to the contradiction between transmitting and reusing, thereby effectively evaded the confusion of reference relation and unordered, can effectively manage reference relation, and can solve flexibly the functional module elements of " seriation " and " differentiation ", promote the alterability of spacecraft three-dimensional model, improve the accuracy of three-dimensional model, realize collaborative fusion between deviser, thereby realize the derivative and distortion fast of tandem product.
Embodiment
The management of spacecraft three-dimensional model under Pro/E of being comprised of three cabin sections of take is below example, and the present invention is further illustrated:
1) in three cabin section spacecraft configuation layer skeleton pattern design phase, in the geometric center of spacecraft and rocket interface, set up whole device coordinate system CS_0-0, in three cabin sections (section-1, cabin, section-2, cabin and section-3, cabin), along the geometric center of the bottom surface of transmit direction, set up cabin section coordinate system CS_1-0, CS_2-0 and CS_3-0 separately, the frame of reference and the corresponding frame of reference as whole device, and transmit downstream with the form of issue geometry according to designing requirement, as the input of layout layer;
2), during topological design Shi Jianli layout layer skeleton pattern, first by the mode directly copying, receive and resolve the dependency basis conventional coordinates (CS_0-0, CS_1-0, CS_2-0 and CS_3-0) in configuration layer skeleton pattern;
3) assembling of the layout layer skeleton pattern of section-1, cabin adopts setting coordinate system CS_Z-1-0 and the fundamental coordinate system CS_1-0 coordinate system corresponding to configuration layer skeleton pattern of layout layer skeleton pattern to align to realize;
4) assembling of the layout layer skeleton pattern of section-2, cabin adopts setting coordinate system CS_Z-2-0 and the fundamental coordinate system CS_2-0 coordinate system corresponding to configuration layer skeleton pattern of layout layer skeleton pattern to align to realize;
5) assembling of the layout layer skeleton pattern of section-3, cabin adopts setting coordinate system CS_Z-3-0 and the fundamental coordinate system CS_3-0 coordinate system corresponding to configuration layer skeleton pattern of layout layer skeleton pattern to align to realize;
6), in the layout layer skeleton pattern of section-1, cabin, section-2, cabin and section-3, cabin, according to the installation site requirement of certain stand-alone device TGk430, set up this stand-alone device layout coordinate system CS_TGk430_SKEL;
7) repeating step 6), set up the layout coordinate system of whole stand-alone device;
8) when stand-alone device is assembled, first on equipment, then apparatus for establishing coordinate system assembles according to coordinate system the way of restraint, for example: for stand-alone device TGk430, first at the geometric center apparatus for establishing coordinate system CS_TGk430 of equipment TGk430, then according to installation relation, device coordinate system CS_TGk430 and layout layer skeleton pattern unit layout coordinate system CS_TGk430_SKEL are assembled according to the mode of coordinate system constraint, wherein, for the equipment of installing on cylinder class sidewall, generally adopt cylindrical-coordinate system to install;
9) repeating step 8) complete the assembling of whole stand-alone device.
In the present invention, undeclared part belongs to the known technology of this area.
Finally it should be noted that: above embodiment apply to illustrate the present invention and and unrestricted technical scheme described in the invention; Therefore, although this instructions has been described in detail the present invention with reference to each above-mentioned embodiment, those of ordinary skill in the art should be appreciated that still can be to the present invention modify or be equal to replacement; And all do not depart from technical scheme and the improvement thereof of the spirit and scope of invention, it all should be encompassed in the middle of claim scope of the present invention.
Claims (4)
1. a management method for Complex Spacecraft three-dimensional model, is characterized in that, comprises the steps:
1) by top-down configuration layer skeleton pattern and the layout layer skeleton pattern of being divided into of Complex Spacecraft three-dimensional model skeleton pattern, wherein, configuration layer skeleton pattern is ground floor skeleton pattern, by expressing spacecraft, forms with large system interface, whole device configuration, the interfacial top layer coordinate system of cabin section; Layout layer skeleton pattern is skeleton pattern for the second time, receiving on the basis of configuration layer information, for expressing stand-alone device, the load of each subsystem of spacecraft, the layout information of structural mechanism;
2) carry out described configuration layer skeleton pattern design, comprise: set up whole device coordinate system, cabin section coordinate system and interphase coordinate system, the coordinate system of setting up is respectively as the frame of reference of whole device and the corresponding frame of reference, and transmit downstream with the form of issue geometry according to designing requirement, as the input of layout layer design;
3) set up described layout layer skeleton pattern, by the mode directly copying, receive and resolve the dependency basis conventional coordinates in configuration layer skeleton pattern, the superior and the subordinate Model Mountings adopts subordinate's skeleton pattern to set coordinate system and higher level's skeleton pattern and sets the coordinate system assembling of aliging, and carries out the establishment of follow-up equipment installation coordinate system in layout layer as reference;
4), in described layout layer skeleton pattern, each stand-alone device installation requirement providing according to each subsystem is set up whole stand-alone device layout coordinate systems;
5) in stand-alone device when assembling,, apparatus for establishing coordinate system on equipment, carries out coordinate system according to the mode of coordinate system constraint and unit layout coordinate system corresponding in layout layer skeleton pattern and aligns and set up assembly relation.
2. the management method of a kind of Complex Spacecraft three-dimensional model according to claim 1, is characterized in that, in described layout layer skeleton pattern, skeleton pattern and assembled at the corresponding levels adopt the coordinate system assembling of aliging.
3. the management method of a kind of Complex Spacecraft three-dimensional model according to claim 1, it is characterized in that, in step 5) in, geometric center apparatus for establishing coordinate system at equipment, according to installation relation, device coordinate system and layout layer skeleton pattern unit layout coordinate system are assembled according to the mode of coordinate system constraint.
4. the management method of a kind of Complex Spacecraft three-dimensional model according to claim 3, is characterized in that, the equipment of installing on cylinder class sidewall adopts cylindrical-coordinate system to install.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310220927.1A CN104217048A (en) | 2013-05-31 | 2013-05-31 | Method for managing complex spacecraft three-dimensional model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310220927.1A CN104217048A (en) | 2013-05-31 | 2013-05-31 | Method for managing complex spacecraft three-dimensional model |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104217048A true CN104217048A (en) | 2014-12-17 |
Family
ID=52098535
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310220927.1A Pending CN104217048A (en) | 2013-05-31 | 2013-05-31 | Method for managing complex spacecraft three-dimensional model |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104217048A (en) |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104657552A (en) * | 2015-02-10 | 2015-05-27 | 北京宇航系统工程研究所 | Automatic rocket tank structure three-dimensional model constructing system |
| CN106649981A (en) * | 2016-11-03 | 2017-05-10 | 上海卫星工程研究所 | Method for adaptively creating and updating three-dimensional model of satellite truss structure |
| CN106815712A (en) * | 2016-12-15 | 2017-06-09 | 中国航天科工集团第四研究院第四总体设计部 | Synergistic method between a kind of enterprise based on three-dimensional framework |
| CN107255938A (en) * | 2017-05-24 | 2017-10-17 | 北京空间技术研制试验中心 | A kind of outer maintainable technology on-orbit ground quick response of spacecraft module supports method |
| CN104657552B (en) * | 2015-02-10 | 2018-02-09 | 北京宇航系统工程研究所 | A kind of Rocket tank structure three-dimensional model automatization constructing system |
| CN107748820A (en) * | 2017-10-27 | 2018-03-02 | 北京空间技术研制试验中心 | Loading device modeling method for spacecraft |
| CN107832508A (en) * | 2017-10-27 | 2018-03-23 | 北京空间技术研制试验中心 | A kind of equipment pipeline system design method of spacecraft |
| CN107885922A (en) * | 2017-10-27 | 2018-04-06 | 北京空间技术研制试验中心 | Spacecraft modeling information management method |
| CN107967373A (en) * | 2017-05-31 | 2018-04-27 | 北京空间技术研制试验中心 | Spacecraft cable system three-dimensional design system and method |
| CN109635427A (en) * | 2018-12-11 | 2019-04-16 | 上海宇航系统工程研究所 | A kind of Satellite vapour image quick design system and method |
| CN110245405A (en) * | 2019-06-04 | 2019-09-17 | 蓝箭航天空间科技股份有限公司 | The top-down modeling method of carrier rocket and rocket modeling structure based on SIEMENS NX |
| CN111080777A (en) * | 2019-12-20 | 2020-04-28 | 北京空间机电研究所 | Three-dimensional rapid modeling method for spacecraft thermal control product |
| CN111161401A (en) * | 2019-12-18 | 2020-05-15 | 沈阳透平机械股份有限公司 | Design method, device and equipment of compressor |
| CN112818489A (en) * | 2021-02-23 | 2021-05-18 | 三一重能股份有限公司 | Wind turbine generator design method and system |
| CN113886961A (en) * | 2021-09-30 | 2022-01-04 | 中国科学院国家空间科学中心 | Radiation effect calculation method, device and equipment based on spacecraft three-dimensional shielding |
| CN113919044A (en) * | 2021-12-14 | 2022-01-11 | 深圳小库科技有限公司 | Automatic generation method and device for light steel keel wall |
| CN114117994A (en) * | 2021-12-03 | 2022-03-01 | 中国电子科技集团公司第十四研究所 | Rapid layout method for radar electronic equipment structure |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7337097B2 (en) * | 2004-03-18 | 2008-02-26 | The Boeing Company | Dynamic modeling technique for the deployment of large satellite antennas |
| CN101739478A (en) * | 2008-11-17 | 2010-06-16 | 北京卫星环境工程研究所 | Spacecraft assembly simulation technique-based virtual assembly system and virtual assembly method |
| CN102456082A (en) * | 2010-10-25 | 2012-05-16 | 北京卫星环境工程研究所 | Two-dimensional three-dimensional combined satellite general assembly process planning and simulation method |
-
2013
- 2013-05-31 CN CN201310220927.1A patent/CN104217048A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7337097B2 (en) * | 2004-03-18 | 2008-02-26 | The Boeing Company | Dynamic modeling technique for the deployment of large satellite antennas |
| CN101739478A (en) * | 2008-11-17 | 2010-06-16 | 北京卫星环境工程研究所 | Spacecraft assembly simulation technique-based virtual assembly system and virtual assembly method |
| CN102456082A (en) * | 2010-10-25 | 2012-05-16 | 北京卫星环境工程研究所 | Two-dimensional three-dimensional combined satellite general assembly process planning and simulation method |
Non-Patent Citations (2)
| Title |
|---|
| 向华平等: ""基于双骨架模型的自顶向下设计方法"", 《四川兵工学报》 * |
| 李飞等: ""航天器数字化协同设计技术研究"", 《导弹与航天运载技术》 * |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104657552A (en) * | 2015-02-10 | 2015-05-27 | 北京宇航系统工程研究所 | Automatic rocket tank structure three-dimensional model constructing system |
| CN104657552B (en) * | 2015-02-10 | 2018-02-09 | 北京宇航系统工程研究所 | A kind of Rocket tank structure three-dimensional model automatization constructing system |
| CN106649981A (en) * | 2016-11-03 | 2017-05-10 | 上海卫星工程研究所 | Method for adaptively creating and updating three-dimensional model of satellite truss structure |
| CN106815712A (en) * | 2016-12-15 | 2017-06-09 | 中国航天科工集团第四研究院第四总体设计部 | Synergistic method between a kind of enterprise based on three-dimensional framework |
| CN107255938A (en) * | 2017-05-24 | 2017-10-17 | 北京空间技术研制试验中心 | A kind of outer maintainable technology on-orbit ground quick response of spacecraft module supports method |
| CN107967373A (en) * | 2017-05-31 | 2018-04-27 | 北京空间技术研制试验中心 | Spacecraft cable system three-dimensional design system and method |
| CN107832508A (en) * | 2017-10-27 | 2018-03-23 | 北京空间技术研制试验中心 | A kind of equipment pipeline system design method of spacecraft |
| CN107885922A (en) * | 2017-10-27 | 2018-04-06 | 北京空间技术研制试验中心 | Spacecraft modeling information management method |
| CN107748820A (en) * | 2017-10-27 | 2018-03-02 | 北京空间技术研制试验中心 | Loading device modeling method for spacecraft |
| CN109635427A (en) * | 2018-12-11 | 2019-04-16 | 上海宇航系统工程研究所 | A kind of Satellite vapour image quick design system and method |
| CN110245405A (en) * | 2019-06-04 | 2019-09-17 | 蓝箭航天空间科技股份有限公司 | The top-down modeling method of carrier rocket and rocket modeling structure based on SIEMENS NX |
| CN111161401A (en) * | 2019-12-18 | 2020-05-15 | 沈阳透平机械股份有限公司 | Design method, device and equipment of compressor |
| CN111161401B (en) * | 2019-12-18 | 2024-02-23 | 沈阳透平机械股份有限公司 | Method, device and equipment for designing compressor |
| CN111080777A (en) * | 2019-12-20 | 2020-04-28 | 北京空间机电研究所 | Three-dimensional rapid modeling method for spacecraft thermal control product |
| CN112818489A (en) * | 2021-02-23 | 2021-05-18 | 三一重能股份有限公司 | Wind turbine generator design method and system |
| CN112818489B (en) * | 2021-02-23 | 2023-09-22 | 三一重能股份有限公司 | Wind turbine generator design method and system |
| CN113886961A (en) * | 2021-09-30 | 2022-01-04 | 中国科学院国家空间科学中心 | Radiation effect calculation method, device and equipment based on spacecraft three-dimensional shielding |
| CN114117994A (en) * | 2021-12-03 | 2022-03-01 | 中国电子科技集团公司第十四研究所 | Rapid layout method for radar electronic equipment structure |
| CN113919044A (en) * | 2021-12-14 | 2022-01-11 | 深圳小库科技有限公司 | Automatic generation method and device for light steel keel wall |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104217048A (en) | Method for managing complex spacecraft three-dimensional model | |
| CN103870635A (en) | Rapid design, analysis and optimization system of large-scale structure based on modularization | |
| CN102893231B (en) | Configure and/or equip the method in the means of transport cabin of especially aircraft | |
| US9514434B2 (en) | Apparatus and method for automatic work instruction generation | |
| CN104573182A (en) | Designing method for multimode control system of aircraft | |
| CN104407576A (en) | Realization method for general type production and manufacturing unit and control system thereof | |
| CN104915482A (en) | Satellite data receiving simulation analysis platform | |
| CN111736994B (en) | Resource arranging method, system, storage medium and electronic equipment | |
| CN105631581A (en) | Structured process design method for discrete manufacturing industry | |
| CN106325887A (en) | Service process management method based on Activiti | |
| US8560287B2 (en) | Configuration-controlled dynamic generation of product data for complex products | |
| CN103616855A (en) | Three-dimensional simulation assembly-based cutting tool management system and management method thereof | |
| Menéndez et al. | Virtual verification of an aircraft Final Assembly Line industrialization: an industrial case | |
| CN110619470A (en) | Assembly production line simulation model and construction method thereof | |
| EP3286700B1 (en) | Templates in a multidisciplinary engineering system | |
| CN112068522A (en) | Reconfigurable production line manufacturing control system, method, and medium | |
| CN116774977A (en) | Design method of coal mine industrial Internet of things development platform based on low codes | |
| CN108734768A (en) | Three-dimensional extensive model visualization Database Systems | |
| CN104217274A (en) | Organization management method for three-dimensional model of complex spacecraft | |
| CN109426675B (en) | Stateflow-based redundancy management method for airborne electromechanical integrated management system | |
| Menéndez et al. | Virtual verification of the AIRBUS A400M final assembly line industrialization | |
| CN102750610A (en) | Transaction control method in product lifecycle phase management-enterprise resource planning (PLM-ERP) integration process | |
| CN110673553A (en) | Unit model for assembly line simulation and construction method thereof | |
| EP3206143B1 (en) | System and method for managing variations in a product structure for a product | |
| CN107885922A (en) | Spacecraft modeling information management method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20141217 |
|
| WD01 | Invention patent application deemed withdrawn after publication |