CN105138750B - A kind of expansible multiple intersection fuselage wire-frame model construction method - Google Patents
A kind of expansible multiple intersection fuselage wire-frame model construction method Download PDFInfo
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Abstract
A kind of expansible multiple intersection fuselage wire-frame model construction method, is related to Design of Mechanical Structure technical field, including：S1, the definition of the infrastructure elements parameterized according to fuselage general shape, and determine the erect-position of infrastructure elements；S2, extracts quantity as circulation distinguishing rule according to existing infrastructure elements, quickly generates wire-frame model node；S3, according to node elements coding rule, carries out multiple intersection point identification, determines to establish the border of wire-frame model and cell type；S4, computing is carried out using CATIA intrinsic functions；S5, addition association attributes quickly generate wire-frame model.Expansible multiple intersection fuselage wire-frame model construction method provided by the invention, airframe structure can quickly be established wire-frame model, the drawbacks of avoiding manually input, modification, a large amount of manpowers of adjustment consuming and time, not only manpower, time resource had been saved, but also can rapidly and accurately establish fuselage wire-frame model.
Description
Technical field
The present invention relates to Design of Mechanical Structure technical field, in particular to a kind of expansible multiple intersection fuselage line
Frame model building method.
Background technology
Skeleton pattern describes topology layout definition.For analysis, it is necessary to which topology layout is converted to characterization power transmission
The wire frame of route, here it is wire-frame model.Based on wire-frame model, relatively coarse structural parameters can be defined, such as covering
Thickness, the sectional area of stringer etc..This definition is relatively coarse, such as the thickness of single-piece skin is all uniform, but energy
Reduce the setting workload in follow-up work.Wire-frame model is established for airframe structure, currently without quick instrument, is leaned on completely
Manually enter, change, adjustment is time-consuming and laborious.Model construction is a process changed repeatedly again, operation by hand.Model is repaiied
It is big to change the amount of getting up to work, renewal not in time, is unfavorable for setting and alternate below.How the technical barrier of urgent need to resolve is at this stage
A kind of model building method is designed to realize the foundation of airframe structure wire-frame model, reduces the work during model foundation modification
Amount.
The content of the invention
It is an object of the invention to solve above-mentioned deficiency of the prior art, there is provided a kind of expansible multi-thread friendship of light aerocraft
Pitch fuselage wire-frame model construction method.
The purpose of the present invention is achieved through the following technical solutions：A kind of expansible multiple intersection fuselage wire-frame model structure side
Method, it is characterised in that include the following steps：
S1, the definition of the infrastructure elements parameterized according to fuselage general shape, and determine the erect-position of infrastructure elements；
S2, extracts quantity as circulation distinguishing rule according to existing infrastructure elements, quickly generates wire-frame model node；
S3, according to node elements coding rule, carries out multiple intersection point identification, determine to establish the border of wire-frame model and
Cell type；
S4, computing is carried out using CATIA intrinsic functions；
S5, quickly generates wire-frame model, specifically includes,
According to wait straight section stringer arrangement and it is non-wait straight section specific rapport, generation long joist axial line；
According to floor level and longitudinal framework quantity, floor crossmember axis and floor longitudinal framework axis are generated.
In such scheme preferably, in S1, the infrastructure elements of parametrization include feature frame, feature stringer, floor level.
In any of the above-described scheme preferably, in S2, the erect-position of the feature frame in S1, by the frame for inputting each subregion
Spacing parameter, the frame position of whole frame sections is calculated, and generates wire-frame model node.
In any of the above-described scheme preferably, in S4, in calculating process is carried out using CATIA intrinsic functions, by defeated
Enter the stringer quantity of each subregion, and coordinated to related floor level, the straight section fuselage cross-section such as utilize to calculate stringer position, it is raw
Into stringer plane and long joist axial line.
The beneficial effect of expansible multiple intersection fuselage wire-frame model construction method provided by the present invention be that it is possible to by
Airframe structure quickly establishes wire-frame model, avoids manually input, modification, adjusts the drawbacks of expending a large amount of manpowers and time,
The wire-frame model for establishing airframe structure using expansible multiple intersection fuselage wire-frame model construction method provided by the invention can reach
To the purpose of rapid modeling, it can in time adjust during model foundation, quickly be fed back, both save manpower, time money
Source, and can rapidly and accurately establish fuselage wire-frame model.
Brief description of the drawings
Fig. 1 is the stream of the preferred embodiment 1 of expansible multiple intersection fuselage wire-frame model construction method according to the invention
Journey schematic diagram；
Fig. 2 is the embodiment illustrated in fig. 1 of expansible multiple intersection fuselage wire-frame model construction method according to the invention
Wire-frame model schematic diagram.
Embodiment
In order to better understand according to the expansible multiple intersection fuselage wire-frame model construction method of the present invention program, below
One preferred embodiment of the expansible multiple intersection fuselage wire-frame model construction method of the present invention is further elaborated with reference to attached drawing
Explanation.
As shown in Figure 1, expansible multiple intersection fuselage wire-frame model construction method provided by the invention includes the following steps：
S1, the definition of the infrastructure elements parameterized according to fuselage general shape, and determine the erect-position of infrastructure elements；
S2, extracts quantity as circulation distinguishing rule according to existing infrastructure elements, quickly generates wire-frame model node；
S3, according to node elements coding rule, carries out multiple intersection point identification, determine to establish the border of wire-frame model and
Cell type；
S4, computing is carried out using CATIA intrinsic functions；
S5, quickly generates wire-frame model, specifically includes,
According to wait straight section stringer arrangement and it is non-wait straight section specific rapport, generation long joist axial line；
According to floor level and longitudinal framework quantity, floor crossmember axis and floor longitudinal framework axis are generated.
In S1, the infrastructure elements of parametrization include feature frame, feature stringer, floor level.According to existing feature frame station
Position, by inputting the frame spacing parameter of each subregion, the frame position of whole frame sections is calculated, the framed plane of generation institute.It is logical
The stringer quantity for inputting each subregion is crossed, and is coordinated to related floor level, the straight section fuselage cross-section such as utilizes to calculate stringer position
Put, generate stringer plane and long joist axial line.According to wait straight section stringer arrangement and it is non-wait straight section specific rapport, generate
Long joist axial line.According to floor level and longitudinal framework quantity, floor crossmember axis and floor longitudinal framework axis are generated.
One structural bone is quickly established using expansible multiple intersection fuselage wire-frame model construction method provided by the invention
Frame model, the model include frame erect-position plane, Fuselage liner part stringer plane, fuselage long joist axial line, floor crossmember, floor longitudinal direction
The elements such as skeleton, it is desirable to which tree-like brevity and lucidity, readable strong, key element is issued automatically., can be with for the structure of skeleton pattern
Its process is subjected to general curing.
Wire-frame model is established for airframe structure, currently without quick instrument, inputs, change by hand completely, adjustment,
It is time-consuming and laborious.Model construction is a process changed repeatedly again, operation by hand.The model modification amount of getting up to work is big.Using
The expansible multiple intersection fuselage wire-frame model construction method of the present invention, can adjust model in time, quickly be fed back, under being conducive to
The development of one step design work.
During specific use, using expansible multiple intersection fuselage wire-frame model construction method provided by the invention
Establish fuselage wire-frame model.First, the quick wire-frame model generation coordinate system of fuselage is defined according to global coordinate system as desired.
Then, DMU (digital prototype) fuselage general shape data are imported.Under this section of shape, Parametric Definition feature frame 19, feature
Stringer 22, floor level 1, complete the Parametric Definition of airframe structure arrangement, as shown in the table.
DMU is the abbreviation of DATA MANAGEMENT UNIT, is Airbus Aircraft integrated data system AIDS (AIRCRAFT
INTEGRATED DATA SYSTEM) core computer, its function is：1st, collect, handle, recording various aircraft parameters,
The mandatory parameter provided including FDIU, is recorded in DMU internal storages and choosing to install referred to as digital AIDS loggers
External recorder (DAR).2nd, various reports are produced according to working status, be stored in nonvolatile memory.
According to 19 feature frames, 22 Gents sign stringer, 1 floor level infrastructure elements extraction quantity as circulation differentiate according to
According to quickly generating wire-frame model node.Intersect computing of the long joist axial line with frame intersection is realized in CATIA first, generates covering
Upper node, then extracts the coordinate information of node by survey tool, and covering node serial number takes 6 digits by modeling regulation
CK1K2PS1S2 is represented.By frame axis using frame height as basic parameter, outer frame edge is respectively obtained in frame plane bias internal certain distance
Bar and interior edge strip axis, then will correspond to frame node in outer frame edge strip and interior edge strip upslide shadow, generation frame plane node on covering.
Floor is highly obtained into floor crossmember lower plane for parameter shift with floor crossmember, is generated respectively in floor crossmember lower planes
Axis.Then floor crossmember upper-lower axis is intersected with edge strip in longitudinal floor beam plane and frame, obtains ground plate node.Frame is put down
Node of the face interior nodes near floor level needs to consider the coordination with floor location, by corresponding frame plane interior nodes land used
Plate node is replaced.
According to certain node elements coding rule, multiple intersection point is known between progress stringer, floor level and frame axis
Not (such as：Stringer intersects with floor boundary line, stringer and frame axis intersect, and stringer, floor boundary and frame are given a bit altogether
Deng), determined to establish the border of wire-frame model according to the cross feature of identification point, and correspond to and distribute its unit class for wanting component units
Type.
Operation CATIA intrinsic functions are calculated, and establish covering set of node, frame plane outer rim set of node, frame plane inner edge
5 bar set of node, floor upper limb set of node, floor lower edge set of node point set arrays.5 node sets can describe whole machine
Body structure network node, each structure wire frame member is all to realize structure by connecting these network nodes.
OGridInFuslage_out (k1, k2) --- fuselage surface stringer-frame intersection point set
OGridInFuslage_out1 (k1, k2) --- outer frame edge strip intersection point set
OGridInFuslage_out2 (k1, k2) --- edge strip intersection point set in frame
OPointFloorFrameout1 (k1, k2) --- floor crossmember upper surface intersection point set
OPointFloorFrameout2 (k1, k2) --- floor crossmember lower surface intersection point set
Establish node coordinate array：The coordinate of each node is made of the numerical value in tri- directions of X, Y, Z.
OGridPosition_out (k1, k2,3) --- fuselage surface stringer-frame intersecting point coordinate
OGridPosition_out1 (k1, k2,3) --- outer frame edge strip intersecting point coordinate
OGridPosition_out2 (k1, k2,3) --- edge strip intersecting point coordinate in frame
OGridFloorPosition_out1 (k1, k2,3) --- floor crossmember upper surface intersecting point coordinate
OGridFloorPosition_out2 (k1, k2,3) --- floor crossmember lower surface intersecting point coordinate
Establish node serial number array：The numbering of each node is made of the character string of one 6.
OGridNumber_out (k1, k2) --- fuselage surface stringer-frame intersection point numbering
OGridNumber_out1 (k1, k2) --- outer frame edge strip intersection point is numbered
OGridNumber_out2 (k1, k2) --- edge strip intersection point is numbered in frame
OGridFloorNumber_out1 (k1, k2) --- floor crossmember upper surface intersection point is numbered
OGridFloorNumber_out2 (k1, k2) --- floor crossmember lower surface intersection point is numbered
Such as Fig. 2, the foundation of fuselage wire-frame model is completed by the matching of node array based on numbering, especially by acquisition corresponding two
A node, respectively along the ROD members of course generation stringer, around the BAR members of fuselage cross-section direction generation bulkhead, transversely generates floor
Crossbeam BAR members, along the ROD members of longitudinal direction generation longitudinal floor beam；Then, by obtaining corresponding four nodes, covering is generated respectively
QUAD4 members, the QUAD4 members etc. on floor.ROD is bar, and BAR is beam, and QUAD4 is node.
Done in detail above in association with the expansible multiple intersection fuselage wire-frame model construction method specific embodiment of the present invention
Description, but be not limitation of the present invention, every technical spirit according to the present invention is to any letter made for any of the above embodiments
Single modification belongs to the technical scope of the present invention, it is also necessary to explanation, expansible multiple intersection fuselage line according to the invention
The category of frame model building method technical solution includes any combination between each part mentioned above.
Claims (4)
1. a kind of expansible multiple intersection fuselage wire-frame model construction method, it is characterised in that include the following steps：
S1, the definition of the infrastructure elements parameterized according to fuselage general shape, and determine the erect-position of infrastructure elements；
S2, extracts quantity as circulation distinguishing rule according to existing infrastructure elements, quickly generates wire-frame model node；
S3, according to node elements coding rule, carries out multiple intersection point identification, determines to establish the border of wire-frame model and unit
Type；
S4, computing is carried out using CATIA intrinsic functions；
S5, quickly generates wire-frame model, specifically includes,
According to wait straight section stringer arrangement and it is non-wait straight section specific rapport, generation long joist axial line；
According to floor level and longitudinal framework quantity, floor crossmember axis and floor longitudinal framework axis are generated.
2. expansible multiple intersection fuselage wire-frame model construction method as claimed in claim 1, it is characterised in that：In S1, ginseng
The infrastructure elements of numberization include feature frame, feature stringer, floor level.
3. the expansible multiple intersection fuselage wire-frame model construction method as described in any one in claim 1 to 2, its feature
It is：In S2, the erect-position of the feature frame in S1, by inputting the frame spacing parameter of each subregion, by the frame of whole frame sections
Position is calculated, and generates wire-frame model node.
4. expansible multiple intersection fuselage wire-frame model construction method as claimed in claim 2, it is characterised in that：In S4,
Carried out in calculating process using CATIA intrinsic functions, carried out by inputting the stringer quantity of each subregion, and to related floor level
Coordinate, the straight section fuselage cross-section such as utilize to calculate stringer position, generate stringer plane and long joist axial line.
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| CN107908837B (en) * | 2017-10-31 | 2023-09-12 | 中航通飞华南飞机工业有限公司 | Longitudinal structure arrangement and three-dimensional modeling method for large amphibious aircraft fuselage |
| CN109670197B (en) * | 2018-11-05 | 2023-05-23 | 武汉华锋惠众科技有限公司 | Creation and adjustment method of process supplement based on wire frame model |
| CN110309568B (en) * | 2019-06-21 | 2022-07-08 | 江西洪都航空工业集团有限责任公司 | Cross cross line creating method based on CATIA |
| CN112347564A (en) * | 2020-11-17 | 2021-02-09 | 中航通飞华南飞机工业有限公司 | Method and device for quickly modeling airplane stringer gap based on CATIA (computer-graphics aided three-dimensional interactive application) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101477710A (en) * | 2009-01-20 | 2009-07-08 | 北京航空航天大学 | Body propelling integrated outer appearance modeling process for supersonic aircraft |
| CN103324772A (en) * | 2012-11-09 | 2013-09-25 | 中国商用飞机有限责任公司 | Single-curved surface wind screen nose integrated design method |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2968111B1 (en) * | 2010-11-30 | 2014-08-29 | Airbus Operations Sas | METHOD AND SYSTEM FOR AIDING THE DRIVING OF AN AIRCRAFT RUNNING ON THE GROUND ON AN AIRPORT DOMAIN. |
-
2015
- 2015-08-13 CN CN201510496367.1A patent/CN105138750B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101477710A (en) * | 2009-01-20 | 2009-07-08 | 北京航空航天大学 | Body propelling integrated outer appearance modeling process for supersonic aircraft |
| CN103324772A (en) * | 2012-11-09 | 2013-09-25 | 中国商用飞机有限责任公司 | Single-curved surface wind screen nose integrated design method |
Non-Patent Citations (1)
| Title |
|---|
| 客机机翼气动/结构多学科设计优化研究;胡婕;《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》;20130215;第C031-86页 * |
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