CN107885922A - Spacecraft modeling information management method - Google Patents
Spacecraft modeling information management method Download PDFInfo
- Publication number
- CN107885922A CN107885922A CN201711030264.1A CN201711030264A CN107885922A CN 107885922 A CN107885922 A CN 107885922A CN 201711030264 A CN201711030264 A CN 201711030264A CN 107885922 A CN107885922 A CN 107885922A
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- CN
- China
- Prior art keywords
- pattern layer
- skeleton pattern
- coordinate system
- spacecraft
- device model
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
- G06T17/00—Three dimensional [3D] modelling, e.g. data description of 3D objects
Abstract
The present invention relates to a kind of spacecraft modeling information management method, the described method comprises the following steps：S1, spacecraft model is divided into the first skeleton pattern layer and the second skeleton pattern layer；S2, establishes the first skeleton pattern layer frame of reference, and according to design requirement by the first skeleton pattern layer coordinate basis to the second skeleton pattern layer transmission；S3, the second skeleton pattern layer is according to the coordinate basis received, the trim designs of progress the second skeleton pattern layer；S4, device model mounting coordinate system is established in the second skeleton pattern layer, the device model is installed in second model layer.The present invention can effectively improve the alterability and accuracy of spacecraft model.
Description
Technical field
The present invention relates to three-dimensional digital field, more particularly to a kind of spacecraft modeling information management method.
Background technology
It will be appreciated that in the system environments of spacecraft Life cycle, using top down design method, each point is
The general arrangement of system will be completed by overall, totally be dispatched to each subsystem footprint, and subsystem accounts for according to overall give
Bit space distributes interior spatial structure, then under be transmitted to parts and designed in detail.Spacecraft model is generally by datum mark, base
The racing such as directrix and reference plane feature is formed, and determined using these benchmark as the positioning datum of component assembly in assembling process
The referring-to relation of the size of each parts and mutual part, downstream designer are carried out with reference to reception, and root by skeleton pattern
Further downstream transmitted after being refined according to the design requirement of the level, so as to realize second of reference relation transmission, according to
It is secondary to analogize until actual referring to up to bottom designer.But it is this with reference to the method successively transmitted successively, between model
Relevance is very complicated, can not have deletion, segmentation, merging, intersecting etc. to influence geometric element for the issued geometry associated
Operation, and the circulation reference of part occurs, necessarily causes data extremely redundancy, cause reference relation chaotic, be not easy to
The situation of management.
The content of the invention
It is an object of the invention to solve above-mentioned technical problem, there is provided a kind of spacecraft modeling information management method, improve
The alterability and accuracy of spacecraft model.
For achieving the above object, the present invention provides a kind of spacecraft modeling information management method, and methods described includes
Following steps：
S1, spacecraft model is divided into the first skeleton pattern layer and the second skeleton pattern layer；
S2, establishes the first skeleton pattern layer frame of reference, and according to design requirement by first skeleton pattern
Layer coordinate basis is to the second skeleton pattern layer transmission；
S3, the second skeleton pattern layer is according to the coordinate basis received, the dress of progress the second skeleton pattern layer
With design；
S4, device model mounting coordinate system is established in the second skeleton pattern layer, the device model is installed to
In second model layer.
Preferably, the frame of reference of the first skeleton pattern layer includes whole device coordinate system, bay section coordinate system and boundary
Areal coordinate system.
Preferably, the first skeleton pattern layer transmits coordinate in the form of issuing geometry to the second skeleton pattern layer
Benchmark, the second skeleton pattern layer receive the coordinate basis by way of directly replicating.
Preferably, in the step S3, according to setting coordinate system and the first skeleton pattern layer in the second skeleton pattern layer
The mode of frame of reference alignment realizes the trim designs of the second skeleton pattern layer.
Preferably, the device model is the regular geometric shapes being made up of plane.
Preferably, the installation method of the device model includes：Equipment itself is established in the geometric center of device model to sit
Mark system；And equipment local Coordinate System is alignd with the device model mounting coordinate system in the second skeleton pattern layer,
Establish assembly relation.
Preferably, the device model is the geometry being made up of curved surface or curved surface and plane.
Preferably, the device model is installed in the side wall of the spacecraft threedimensional model, and installation method includes：Setting
Device model side wall mounting coordinate system is established on standby model；And
Device model side wall mounting coordinate system and the device model mounting coordinate system in the second skeleton pattern layer are entered
Row alignment, establishes assembly relation.
According to the spacecraft modeling information management method of the present invention, realize whole spacecraft threedimensional model and pass through unification
Coordinate basis carries out top-down transmission, establishes unified data transfer and reference for assembling, realize modeling information has
Effect management, overcome monoskeleton model in the prior art with reference to the limitation transmitted, efficiently solve design with reference to transmit with
Contradiction between reuse, has evaded the confusing property of reference relation, lifted the alterability of spacecraft threedimensional model with
And accuracy.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to institute in embodiment
The accompanying drawing needed to use is briefly described, it should be apparent that, drawings in the following description are only some implementations of the present invention
Example, for those of ordinary skill in the art, on the premise of not paying creative work, can also be obtained according to these accompanying drawings
Obtain other accompanying drawings.
Fig. 1 is to schematically show the spacecraft modeling information management method according to the present invention.
Embodiment
The description of this specification embodiment should be combined with corresponding accompanying drawing, and accompanying drawing should be used as the one of complete specification
Part.In the accompanying drawings, the shape of embodiment or thickness can expand, and to simplify or conveniently indicate.Furthermore respectively tied in accompanying drawing
The part of structure will be to describe to illustrate respectively, it is notable that the member not illustrated not shown in figure or by word
Part, it is the form known to a person of ordinary skill in the art in art.
The description of embodiments herein, any reference about direction and orientation, is for only for ease of description, and can not manage
Solve as any restrictions to the scope of the present invention.It can be related to the combination of feature below for the explanation of preferred embodiment,
These features may be individually present or combine presence, and the present invention is not defined in preferred embodiment especially.The present invention
Scope be defined by the claims.
Fig. 1 is to schematically show the spacecraft modeling information management method according to the present invention.As shown in figure 1, according to this hair
Bright spacecraft modeling information management method comprises the following steps：S1, spacecraft model is divided into the first skeleton pattern layer and
Two skeleton pattern layers；S2, establishes the first skeleton pattern layer frame of reference, and according to design requirement by the first skeleton pattern
The coordinate basis of layer is to the second skeleton pattern layer transmission；S3, the second skeleton pattern layer are carried out according to the coordinate basis received
The trim designs of second skeleton pattern layer；S4, device model mounting coordinate system is established in the second skeleton pattern layer, by equipment mould
Type is installed in the second model layer.
Specifically, by spacecraft model is top-down be divided into the first skeleton pattern layer and the second skeleton pattern layer after, according to
The secondary design for carrying out the first skeleton pattern layer and the second skeleton pattern layer.The reference coordinate established on the first skeleton pattern layer
System, constructed as expression spacecraft with big system interface, whole device, the frame of reference of bay section interface, i.e., in the first skeleton pattern
The frame of reference established on type layer includes whole device coordinate system, bay section coordinate system and interface coordinate system.
, will after establishing big system interface, whole device configuration and bay section boundary in the first skeleton pattern layer with the frame of reference
Coordinate basis in first skeleton pattern layer (is packed geometry, the benchmark of "current" model in itself, for other with issuing geometric format
Model is integrally with reference to use) transmitted to the second skeleton pattern layer.
After second skeleton pattern layer receives the coordinate basis of the first skeleton pattern layer, building for the second skeleton pattern layer is carried out
It is vertical.Specifically, the second skeleton pattern layer received and parsed by way of directly replicating the first skeleton pattern layer transmission come seat
Benchmark is marked, the setting coordinate system of the second skeleton pattern layer is established with this coordinate basis, and set according in the second skeleton pattern layer
Position fixing system realizes the assembling of the second skeleton pattern layer with the mode that the reference coordinate in the first skeleton pattern layer is alignd, i.e., up and down
Level Model Mounting is realized using subordinate's skeleton pattern layer setting coordinate system and higher level's skeleton pattern layer setting coordinate system alignment constraint
Assembling.
Further, after the completion of the second skeleton pattern layer is equipped, step S4 is carried out.Specifically, first in the second skeleton pattern
Device model mounting coordinate system is established in type layer, then the difference of device model is installed as needed, respectively in a different manner
Installed.
When device model is the regular geometric shapes being made up of plane, such as rectangular-shape.Such device model is being pacified
During dress, equipment local Coordinate System is established in the geometric center of device model, then by coordinate system constrain in the way of with the second bone
Corresponding device model mounting coordinate system carries out coordinate system alignment and establishes assembly relation in frame model layer, realizes the peace of device model
Dress.
When device model is the geometry being made up of curved surface or curved surface and plane, such as cylindrical shape.This kind equipment
Model when mounted, is typically mounted in the side wall of spacecraft threedimensional model, specifically, by taking cylindrical device model as an example,
Cylindrical-coordinate system is first established during installation on device model, then in the way of coordinate system constrains and in the second skeleton pattern layer
Corresponding device model mounting coordinate system carries out coordinate system alignment and establishes assembly relation, realizes the installation of device model.
According to the spacecraft modeling information management method of the present invention, realize whole spacecraft threedimensional model and pass through unification
Coordinate basis carries out top-down transmission, establishes unified data transfer and reference for assembling, realize modeling information has
Effect management, overcome monoskeleton model in the prior art with reference to the limitation transmitted, efficiently solve design with reference to transmit with
Contradiction between reuse, has evaded the confusing property of reference relation, lifted the alterability of spacecraft threedimensional model with
And accuracy.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all essences in the present invention
God any modification, equivalent substitution and improvements made etc., should be included in the scope of the protection with principle.
Claims (8)
1. a kind of spacecraft modeling information management method, it is characterised in that the described method comprises the following steps：
S1, spacecraft model is divided into the first skeleton pattern layer and the second skeleton pattern layer；
S2, the first skeleton pattern layer frame of reference is established, and sat the first skeleton pattern layer according to design requirement
Benchmark is marked to the second skeleton pattern layer transmission；
S3, according to the coordinate basis received, the assembling for carrying out the second skeleton pattern layer is set the second skeleton pattern layer
Meter；
S4, device model mounting coordinate system is established in the second skeleton pattern layer, the device model is installed to described
In second model layer.
2. spacecraft modeling information management method according to claim 1, it is characterised in that the first skeleton pattern layer
The frame of reference include whole device coordinate system, bay section coordinate system and interface coordinate system.
3. spacecraft modeling information management method according to claim 1, it is characterised in that the first skeleton pattern layer
Coordinate basis is transmitted to the second skeleton pattern layer in the form of issuing geometry, the second skeleton pattern layer passes through directly multiple
The mode of system receives the coordinate basis.
4. spacecraft modeling information management method according to claim 1, it is characterised in that in the step S3, according to
Coordinate system is set in second skeleton pattern layer and realizes described second with the mode that the frame of reference of the first skeleton pattern layer is alignd
The trim designs of skeleton pattern layer.
5. spacecraft modeling information management method according to claim 1, it is characterised in that the device model is by putting down
The regular geometric shapes that face is formed.
6. spacecraft modeling information management method according to claim 5, it is characterised in that the installation of the device model
Method includes：
Equipment local Coordinate System is established in the geometric center of device model；And
Equipment local Coordinate System is alignd with the device model mounting coordinate system in the second skeleton pattern layer, establishes dress
With relation.
7. spacecraft modeling information management method according to claim 1, it is characterised in that the device model is by song
The geometry that face or curved surface and plane are formed.
8. spacecraft modeling information management method according to claim 7, it is characterised in that the device model is installed on
In the side wall of the spacecraft threedimensional model, installation method includes：
Device model side wall mounting coordinate system is established on device model；And
Device model mounting coordinate system in device model side wall mounting coordinate system and the second skeleton pattern layer is carried out pair
Together, assembly relation is established.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711030264.1A CN107885922A (en) | 2017-10-27 | 2017-10-27 | Spacecraft modeling information management method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711030264.1A CN107885922A (en) | 2017-10-27 | 2017-10-27 | Spacecraft modeling information management method |
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| Publication Number | Publication Date |
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| CN107885922A true CN107885922A (en) | 2018-04-06 |
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| CN201711030264.1A Pending CN107885922A (en) | 2017-10-27 | 2017-10-27 | Spacecraft modeling information management method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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| CN102384833A (en) * | 2011-10-28 | 2012-03-21 | 北京航空航天大学 | Device and method for testing combination control of multiple excitation sources |
| CN104217273A (en) * | 2013-05-31 | 2014-12-17 | 北京空间技术研制试验中心 | Characteristic management method for spacecraft three-dimensional digital model |
| CN104217048A (en) * | 2013-05-31 | 2014-12-17 | 北京空间技术研制试验中心 | Method for managing complex spacecraft three-dimensional model |
| CN104548617A (en) * | 2014-12-24 | 2015-04-29 | 苏州原点工业设计有限公司 | Model spaceship wing |
| CN205345360U (en) * | 2015-08-26 | 2016-06-29 | 上海宇航系统工程研究所 | Light -duty multi -functional heat accuse multilayer support of moon exploration spacecraft |
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2017
- 2017-10-27 CN CN201711030264.1A patent/CN107885922A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102384833A (en) * | 2011-10-28 | 2012-03-21 | 北京航空航天大学 | Device and method for testing combination control of multiple excitation sources |
| CN104217273A (en) * | 2013-05-31 | 2014-12-17 | 北京空间技术研制试验中心 | Characteristic management method for spacecraft three-dimensional digital model |
| CN104217048A (en) * | 2013-05-31 | 2014-12-17 | 北京空间技术研制试验中心 | Method for managing complex spacecraft three-dimensional model |
| CN104548617A (en) * | 2014-12-24 | 2015-04-29 | 苏州原点工业设计有限公司 | Model spaceship wing |
| CN205345360U (en) * | 2015-08-26 | 2016-06-29 | 上海宇航系统工程研究所 | Light -duty multi -functional heat accuse multilayer support of moon exploration spacecraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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Application publication date: 20180406 |
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