CN103020375B - 1 grade of component parameter method for designing of aircraft stringer class part - Google Patents
1 grade of component parameter method for designing of aircraft stringer class part Download PDFInfo
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Abstract
1 grade of component parameter method for designing of aircraft stringer class part: state the stringer class part in aircaft configuration with parametrization component, 1 grade of component parameterization of aircraft stringer class part is stated and is specifically related to following 4 partial contents: 1) " base attribute " specifically includes: component name, version number, establishment time, component description, manufacturing process, remarks；2) " geometric attribute " is specifically divided into positional parameter, cross section parameter two parts；3) " non-geometric attribute " is specifically related to decomposing scheme, " non-geometric attribute " information of corresponding decomposing scheme；4) " two-dimensional section figure " for supplying the physical significance of user's each parameter of correct understanding component when component instantiation.The present invention contributes to setting up the component library system of aircraft, function, performance model data basis is provided with optimizing for airplane design standardization and simulation analysis, ensure data harmonious between geometry model machine, function model machine/performance prototype, improve the designing quality of aircraft, shorten the lead time.
Description
Technical field
The present invention relates to technical field of aircraft structure design, specifically provide a kind of aircraft stringer class part 1
Level component parameter method for designing.
Background technology
In prior art, along with the application that deepens continuously of cad technique, along with cad technique increasingly becomes
For the requisite instrument of aircraft design unit.Designer needs to solve to use CAD to complete product three
Parameter determination problem design before dimension physical model.If cad technique can not participate in product ginseng
The determination of number, then cad technique application in the design is only the description of design result, is not
Design truly.The design process of CAD system product to be participated in, the model construction of design process
Just become crucial.This model should be able to be suitable for the data demand of the systems such as CAD/CAE, meets specialty and sets
The description of meter flow process.To this end, external the most famous each CAD system is at the base realizing CAD basic function
On plinth, one after another CAE technology is incorporated into respective CAD system, or to each CAE system
Thering is provided data-interface, it is desirable to realize the integrated of CAD with CAE, meet engineering design needs, this is existing
The usual way of some main flow CAD system.At present in terms of the entity analysis of part, CAD Yu CAE skill
Art can realize seamless integrated, but how to solve the Seamless integration-of aviation thin-wall construction, i.e. solves CAE
The geometric type of model and the CAE inharmonic problem of model geometric type, become and affect CAD and CAE
The key of seamless connection, prior art also cannot solve.
1 grade of component of aircraft stringer class part is important in aeroplane structure design based on parametrization component
Ingredient, therefore, the aircraft stringer class part 1 that a kind of technique effect of the highly desirable acquisition of people is excellent
Level component parameter method for designing.
Summary of the invention
It is an object of the invention to provide and a kind of make in aeroplane structure design method based on parametrization component
1 grade of component parameter method for designing of aircraft stringer class part.
Its technical foundation is aeroplane structure design method based on parametrization component, is now described below:
The key innovations of aeroplane structure design method based on parametrization component is to use parametrization structure
Typical part in part statement aircaft configuration, comprises geological information and the non-geometry information of structure in component；
Described parametrization component carries out induction-arrangement to parts conventional in airplane design and is formed, comprises
Geometry and the three-dimensional digitalization model of non-geometric attribute data information.In the application, component example is utilized
Metaplasia becomes multiple structural member.By model simplification, refine the attribute information in structural member, automatically generate
Structural finite element model.
The requirement that described parametrization component was divided by the aircraft digital design phase, is divided into 4 ranks,
The most corresponding conceptual design, preliminary design, trim designs and detailed design；Wherein:
1 grade of component, for the schematic design phase, is the model of Full Parameterized；2,3,4 grades of components be
On the basis of 1 grade of component, according to the requirement of different design stage, gradually supplement, improve and ripe,
Obtain the Products Digital model that can be used for manufacturing eventually；2,3,4 grades of components reflect Products Digital calmly
The process that justice is gradually ripe, is mainly used in designer to the understanding of design process and study, simultaneously can
On the basis of component example, it is modified, be used for meeting the requirement of new design objective.With
The knowledge that 2-4 level component is relevant is abundanter, and is integrated with the design tool that engineering is conventional, helps design
Personnel carry out preliminary design analysis.
Following requirement is also met: " component " is in strict accordance with three-dimensional objects number for 1 grade of component
Wordization modeling specification is set up, the parameterized a certain quasi-representative part of each attribute that comprises part；When
After completing the attribute of component, parameter definition under CATIA environment, then can according to structure attribute and
The definition of parameter generates the example of a component, i.e. Products Digital definition result is placed in the complete of PDM
Under facial canal reason；
" attribute of component " comprises geometry and non-geometric attribute；Wherein: geometric attribute is all parametrization
, it being used for being formed three dimensional example, geometric attribute is specifically divided into two classes, and a class is the positional parameter of component,
Such as external form curved surface, component location plane etc., another kind of is the cross sectional shape parameter of component, as thickness,
Width etc.；The non-geometric attribute of component is mainly used in describing function and the attribute of performance of component, for model
Unified interconnected system sets up function, performance prototype provides master data；The definition of non-geometric attribute along with
The continuous maturation of component, its content is the most perfect.
Structure attribute data are predefined component data, and location data, cross section including component are several
What data, the weight coefficient of component, component can simplified element.In component uniform data, need
To the geometry location parameter of component, the cross section property (geometry, cross section parameter) of component, component
Weight characteristic, component optional characteristic that simplifies in cae analysis be defined in detail, form component
The maximum collection that function, attribute of performance describe.The complete definition of structure attribute is that model simplification system is to structure
Part carries out the foundation simplified, and is that component uses and simplifies the input data source of module.On the other hand, logical
Cross and set up structure attribute definition, the simplification process of specification component, it is achieved automatically generating of FEM (finite element) model.
Structure attribute definition is in binding state, if the component entity in component base does not has with component geometry entity
Have the attribute definition of correspondence, then, after this component instantiation, component simplifies module and will be unable to identify this example；
If during a certain component entity deleted in component base part, then the attribute definition that this component is corresponding should be by one
With deleting.
The application of aeroplane structure design method based on parametrization component, is first quickly to set up at the beginning of product
Step designs a model.Utilize parametrization component quickly to carry out the definition of component, build preliminary digital prototype.
When component calls, use modeling geometry benchmark defined in benchmark, define the positional parameter of component, complete
Become the sterically defined instantiation of component；Utilize component geometric parameter definition interfaces, complete member section special
Levy the instantiation definition of parameter.By two above process, calling and instantiation of complete gemel,
Thus realize quickly setting up the purpose of product Preliminary design model.In the invoked procedure of component, permissible
Use the knowledge and Engineering Algorithm associated with component, according to preliminary design requirement, determine cutting of component
The parameters such as face size.
Next to that set up Math data (definition of non-geometric data).On the basis of component example,
The non-geometry information of definition component, i.e. the function of component, attribute of performance, definition result is saved in product
In product digital model (CATIA model).The definition of model simplification information is the process of gradual perfection,
The all properties being saved in product data constitutes the basis of unified model data, not only contains face
To the design data manufactured, and contain the analytical data of Design-Oriented.Use unified model associates
These data are extracted and are processed by system, then can set up the function needed for airplane design each secondary flow journey,
Performance Analysis model, it is achieved the linking of the major-minor flow process of airplane design.
In described aeroplane structure design method based on parametrization component, for the 1 of schematic design phase service
Level component meets following requirement:
The digital prototype formed after utilizing 1 grade of component instantiation, true by cae analysis and optimization design
Fixed preliminary parameter of structure design, provides basis for weight estimation, the aircraft knot proposing proof of concept
Structure scheme carries out clearly and embodies, and finally provides complete aircaft configuration overall plan；Described 1 grade
Component specifically comprises interior appearance curved surface, positioning datum plane, sectional parameter, non-geometry information.
In described aeroplane structure design method based on parametrization component, for the 2 of schematic design phase service
Level component meets following requirement:
2 grades of components serviced for the concept phase；The digital prototype formed by 2 grades of components, for flying
The accessibility of machine, maintainability, enough reliabilities, human engineering and the compatibility of support equipment
Etc. carrying out coordinate design as far as possible；Parts basic size all it has been determined that on the basis of provide weight
The detailed decomposition base of figureofmerit, but not yet carry out detailed assembling and mounting design；
2 grades of components are not the components of Full Parameterized, are 1 grade of component instantiation and through optimizing design point
On the basis of after analysis, component is integrated/is divided into some molectron/parts, determine to connect between structure and close
System, production breakdown interface, initial breakdown interface, carry out preliminary reconciling spatial scale design；Specifically comprise following setting
Meter content:
Connect concrete form between big parts to design (if certain intersection point between clear and definite wing and fuselage is water
Flat banjo fixing butt jointing/auricle connects)；(as continuous in beam, the rib segmentation of frame member segmentation in length and breadth；Skeleton in length and breadth
Concrete type of attachment design is not yet carried out, such as connecing of not connecting between frame member in length and breadth between component
Head, angle box, gusset plate etc.)；Determine single member segments form, position (as vertical wall internal and external section docking,
Fit；Frame member not yet carries out detailed design, as beam, wall, rib etc. only have edge strip and web, does not has
There is the rib of centre)；Coordination location (as beam edge strip moves down laminating eyelid covering inner surface) between structural member；
Lid position, openings of sizes design；Structural member be the preliminary perforate of each system pass (perforate is simply dug a hole,
Flange etc. is not had to strengthen design).
In described aeroplane structure design method based on parametrization component, for the 3 of schematic design phase service
Level component meets following requirement:
3 grades of components are the services of Design for assembly stage；The digital prototype formed by 3 grades of components, is carried out
Each function system and structure, structure and interstructural trim designs, by checking the various of integrated design
State, interference and interface docking situation, complete the interference checking of whole airplane, formed final system/
Structural interface defines, it is provided that weight checks basis；The digital prototype that this stage is formed is equivalent to tradition and flies
Model machine effect in kind in flow process developed by machine；
3 grades of components are not the components of Full Parameterized, are according to trim designs needs, carry out 2 grades of components
Continue refinement, revise and improve and increase and decrease corresponding spare part, complete each function system and structure, structure
Designing with interstructural final connection interface, it specifically comprises the description below and requires: the company between component
Connect relational design (as beam, rib connection add angle box, gusset plate etc.；Key position fastener connection section position sets
Meter, such as the connection localized design of the component that the bearing pin bigger with certain stress is connected；Lid mouth frame designs)；
Mounting design (as determined fuel pump installation on structural member) between component and system；Component and system it
Between interference design (structure is that system pass perforate determines).
In described aeroplane structure design method based on parametrization component, for the 4 of schematic design phase service
Level component meets following requirement:
4 grades of components service for detailed design phase；The final full machine numeral sample formed by 4 grades of components
Machine meets final design load, determines parts final weight state, meets manufacturability simultaneously and wants
Ask；
4 grades of components are not the components of Full Parameterized, are on the basis of 3 grades of components, revise, improve zero
The local detail of part threedimensional model, meets what component all of design requirement obtained, under it specifically comprises
State content to require: component connects local concrete shape design, local strengthening design；Component connects thin
Joint design (standard component code name, spread pattern, gap, back gauge, associated components may locally be changed)；
Component chamfering, rounding, lightening core, alleviate hole, alleviate groove, oil through, technological datum hole design.
Described aeroplane structure design method based on parametrization component, it is characterised in that: " component " is strict
Set up by three-dimensional objects digitization modeling specification, be obtained in that and it by component and with knowledge base
Relevant design, technique, manufacturing knowledge, Aided Design personnel's complete design during component uses
Work；In aircraft, typical structural elements can be summarized as 11 classes: 1) beam, wall；2) rib；3) long
Purlin；4) skinpiston；5) frame；6) longitudinal baffle；7) joint, angle box；8) lid, mouth frame；
9) band plate；10) hinge；11) other.
The innovation main points of the present invention and claimed emphasis relate to a kind of 1 grade of structure of aircraft stringer class part
Part parameterization design method, it is characterised in that: by the stringer class in parametrization component statement aircaft configuration
Part, the statement of 1 grade of component parameterization of aircraft stringer class part is specifically related to following 4 partial contents: " base
This attribute ", " geometric attribute ", " non-geometric attribute ", " two-dimensional section figure "；Wherein:
" base attribute " specifically includes: component name, version number, the establishment time, component description,
Manufacturing process, remarks；
" geometric attribute " is specifically divided into positional parameter, cross section parameter two parts, wherein, positional parameter
Including: external surface, axial plane, prelocalization face, rear-locating face；Cross section parameter is specially the length in cross section
Degree, width, highly, thickness information；1 grade of component positional parameter schematic diagram ginseng of aircraft stringer class part
See Fig. 1.
" non-geometric attribute ": be specifically related to following two parts content: decomposing scheme, corresponding decomposing scheme
" non-geometric attribute " information；Wherein: stringer class part need not decompose, for overall plan；Right
" non-geometric attribute " information answering decomposing scheme specifically includes: the simplified element type that can use,
The computation attribute of corresponding the type finite element unit and the computing formula of association；
" two-dimensional section figure ": for supplying the thing of user's each parameter of correct understanding component when component instantiation
Reason meaning.
Described 1 grade of component parameter method for designing of aircraft stringer class part, it is characterised in that: for L
In " geometric attribute " of type 1 grade of component of stringer part, cross section parameter specifically includes following three: cut
Edge strip T profile overall width, upper edge strip T profile right side width, lower edge strip T profile overall width on face.
Fig. 2 is shown in by cross section parameter schematic diagram, and parameter describes and is shown in Table 1.
Table 1 cross section parameter describes
Described 1 grade of component parameter method for designing of aircraft stringer class part, it is characterised in that: for L
1 grade of component of aircraft stringer class part of shape extrudate, its simplified element, computation attribute and association are public
Formula sees table 2；In table 2: H1 is the special case of upper edge strip T profile right side width H；T1 is lower edge strip
The special case of T profile overall width t；L1 is the special case of upper edge strip T profile overall width L；
Table 2 can be reduced to bar, the component computation attribute of beam class unit and incidence formula
Described 1 grade of component parameter method for designing of aircraft stringer class part, it is characterised in that: aircraft is long
Class part 1 grade of component parameterization in purlin is stated and is further related to following 3 partial contents: " association knowledge ", " importing
Report ", " explanation "；Wherein:
" association knowledge " is when component calls, and provides a user with the relevant design knowledge of this component；
" Import Reports " is for the modeling process of recording member；
" illustrating ": for geometry location parameter, axle, front and back to position be all curved surface, therefore can produce many
Planting different combinations, referring specifically to table 3, various different cross sectional shapes also have different combinations.
The combination of table 3 stringer class A of geometric unitA difference location geometry
The present invention is that the technical problem described in background technology provides a kind of feasible solution, tool
Body provides 1 grade of component parameter method for designing of aircraft stringer class part.Set up aircraft based on this
Component library system, Airplane Digital Product Definition process specification can be made, each auxiliary for airplane design
The simulation analysis of flow process and optimization provide function, performance model data basis, it is ensured that geometry model machine, merit
Between energy model machine/performance prototype, data is harmonious, and final realization improves the designing quality of aircraft, shortening
The purpose of lead time.
Compared with prior art, advantage for present invention and effect:
1) present invention contributes to modular product digital definition process
CAD system is that designer provides abundant modelling means, and same problem can be by not
Same approach is solved, and therefore, the digital definition of product exists for nonstandard problem.Several years
The Design of digital come experience have shown that, the meeting lack of standardization of digital definition process brings following two main
Problem:
First is to design a model to understand difficulty: designing a model of designer's foundation, other designers
It is clear that member is difficult to deciphering, if needing to be modified model, designer often thinks that research is clear
Chu's model is set up process and might as well again be set up once by model；Even model designer is through one section
After time, want to review modeling process the most difficult.
Next to that existing experience and resource can not be made full use of: design is the accumulation of experience, successfully
Design experienced by test and the checking used, it is ensured that design result meets design requirement, has good
Technique well, manufacturing.If not using for reference existing Element Design experience, use the design knot of maturation
Really, the reliability of Element Design, the designing quality of part are required for again verifying, the system of part
Make technique to be also required to again examine, have influence on the utilization of tooling device, certainly will cause and have experience
With the waste of resource, it is unfavorable for the accumulation of experience, is unfavorable for realizing the quick design of product.
By to the analysis of current version part form, conclusion, the regulation following strictly modeling specification is built
Vertical parametrization, modular component, provide condition for realizing the definition of normalized Products Digital.
Designer in the design process, chooses component from component base, carries out the Preliminary design of product and determines
Justice.When component base does not has available component, set up the application of new structural member by proposition, complete
After the design of newly-built component, technique, manufacture etc. are examined, component base increases required component.
By such regulation, can the digital definition process of thorough normative model, it is ensured that designing quality and
Anufacturability.
2) it is that the realization of unified model interconnected system lays the foundation
Component base is used to carry out parallel product digital definition except realizing accelerating design schedule, Specification Design
Outside process, still yet another advantage is that the geometry by comprising in component, function, performance data are (non-several
What data), utilize unified model corresponding technology, automatically generate the function needed for each specialty of aircraft, property
Energy simulation analysis, Optimized model, it is achieved in aircraft digital design cycle, major-minor flow process is integrated.Cause
This, component library system is when being designed planning, it should the exploitation with unified model interconnected system, number
Fully coordinate according to demand etc., in each design phase of main flow, be not only completed the example of component
Change, and by model simplification system, component is simplified, extract structure for unified model interconnected system
Part geometry, non-geometric data lay the foundation.
Accompanying drawing explanation
Below in conjunction with the accompanying drawings and embodiment the present invention is further detailed explanation:
Fig. 1 is L-type stringer component positional parameter schematic diagram；
Fig. 2 is L-type stringer member section schematic diagram.
Detailed description of the invention
Embodiment 1
A kind of aircraft stringer class part used in aeroplane structure design method based on parametrization component
1 grade of component parameter method for designing.
Its technical foundation is aeroplane structure design method based on parametrization component, and related content sees
" innovation and creation content " part in bright book.
The present embodiment emphasis relates to a kind of 1 grade of component parameter method for designing of aircraft stringer class part: use
Stringer class part in parametrization component statement aircaft configuration, 1 grade of component parameter of aircraft stringer class part
Change statement and be specifically related to following 4 partial contents: " base attribute ", " geometric attribute ", " non-geometric attribute ",
" two-dimensional section figure "；Wherein:
" base attribute " specifically includes: component name, version number, the establishment time, component description,
Manufacturing process, remarks；
" geometric attribute " is specifically divided into positional parameter, cross section parameter two parts, wherein, positional parameter
Including: external surface, axial plane, prelocalization face, rear-locating face；Cross section parameter is specially the length in cross section
Degree, width, highly, thickness information；
" non-geometric attribute ": be specifically related to following two parts content: decomposing scheme, corresponding decomposing scheme
" non-geometric attribute " information；Wherein: stringer class part need not decompose, for overall plan；Right
" non-geometric attribute " information answering decomposing scheme specifically includes: the simplified element type that can use,
The computation attribute of corresponding the type finite element unit and the computing formula of association；
" two-dimensional section figure ": for supplying the thing of user's each parameter of correct understanding component when component instantiation
Reason meaning.
1 grade of component positional parameter schematic diagram of aircraft stringer class part sees Fig. 1.
Described 1 grade of component parameter method for designing of aircraft stringer class part, it is characterised in that: for L
In " geometric attribute " of type 1 grade of component of stringer part, cross section parameter specifically includes following three: cut
Edge strip T profile overall width, upper edge strip T profile right side width, lower edge strip T profile overall width on face.
Fig. 2 is shown in by cross section parameter schematic diagram, and parameter describes and is shown in Table 1.
Table 1 cross section parameter describes
Described 1 grade of component parameter method for designing of aircraft stringer class part, it is characterised in that: for L
1 grade of component of aircraft stringer class part of shape extrudate, its simplified element, computation attribute and association are public
Formula sees table 2；In table 2: H1 is the special case of upper edge strip T profile right side width H；T1 is lower edge strip
The special case of T profile overall width t；L1 is the special case of upper edge strip T profile overall width L；
Table 2 can be reduced to bar, the component computation attribute of beam class unit and incidence formula
Described 1 grade of component parameter method for designing of aircraft stringer class part, it is characterised in that: aircraft is long
Class part 1 grade of component parameterization in purlin is stated and is further related to following 3 partial contents: " association knowledge ", " importing
Report ", " explanation "；Wherein:
" association knowledge " is when component calls, and provides a user with the relevant design knowledge of this component；
" Import Reports " is for the modeling process of recording member；
" illustrating ": for geometry location parameter, axle, front and back to position be all curved surface, therefore can produce many
Planting different combinations, referring specifically to table 3, various different cross sectional shapes also have different combinations.
The combination of table 3 stringer class A of geometric unitA difference location geometry
The application mode of aircraft stringer 1 grade of component of class part is mainly 2 parts:
A) product Preliminary design model is quickly set up
By component needed for selection interactively from component base and start component parameter and quickly design mould
Block, designer can quickly carry out the definition of component, build preliminary digital prototype.
1) when component calls, modeling geometry benchmark defined in benchmark is used, the location ginseng of definition component
Number, completes the sterically defined instantiation of component；
2) utilize component geometric parameter definition interfaces, complete the instantiation definition of member section characteristic parameter.
By two above process, calling and instantiation of complete gemel, thus realize quickly setting up product
The purpose of Preliminary design model.
B) Math data (definition of non-geometric data) are set up
On the basis of component example, the non-geometry information of definition component, i.e. the function of component, performance
Attribute, is saved in (cad model) in Products Digital model by definition result.
The definition of model simplification information is the process of gradual perfection, all genus being saved in product data
Property constitutes the basis of unified model data, not only contains design for manufacture data, and wraps
Contain the analytical data of Design-Oriented.Use Unified Model interconnected system these data are carried out extract and
Processing, then can set up the function needed for airplane design each secondary flow journey, Performance Analysis model, it is achieved
The linking of the major-minor flow process of airplane design.
The step that 1 grade of component of aircraft stringer class part is mainly applied:
A) mode one: (generating component example)
1) start component base, browse component, selected member
2) in the component instantiation window ejected with CATIA platform, the geometry of interactive selection component is fixed
Position benchmark
3) definition member section parameter
4) fill in component non-geometry information, after confirmation, generate component example.
B) mode two: (amendment component example)
1) in CATIA platform, the digital-to-analogue generated on structure tree is found by component instantiation
2) double-click this digital-to-analogue, eject amendment window
3) at amendment window, geological information, non-geometry information are revised
4) amendment of component example is completed after confirming.
C) mode three: (setting up Math data)
1) in component base (CATIA) system, current work will be placed in by the digital-to-analogue after component instantiation
Make state
2) use Unified Model interconnected system, extract the geological information in digital-to-analogue and non-geometry information
3) utilize Unified Model interconnected system, generate FEM (finite element) model.
The present embodiment is that the technical problem described in background technology provides a kind of feasible solution,
Specifically provide 1 grade of component parameter method for designing of aircraft stringer class part.Set up based on this and fly
The component library system of machine, can make Airplane Digital Product Definition process specification, each for airplane design
The simulation analysis of secondary flow journey and optimization provide function, performance model data basis, it is ensured that geometry model machine,
Between function model machine/performance prototype, data is harmonious, and final realization improves the designing quality of aircraft, contracting
The purpose of short lead time.
Compared with prior art, the present embodiment have the advantage that and effect:
1) the present embodiment contributes to modular product digital definition process
CAD system is that designer provides abundant modelling means, and same problem can be by not
Same approach is solved, and therefore, the digital definition of product exists for nonstandard problem.Several years
The Design of digital come experience have shown that, the meeting lack of standardization of digital definition process brings following two main
Problem:
First is to design a model to understand difficulty: designing a model of designer's foundation, other designers
It is clear that member is difficult to deciphering, if needing to be modified model, designer often thinks that research is clear
Chu's model is set up process and might as well again be set up once by model；Even model designer is through one section
After time, want to review modeling process the most difficult.
Next to that existing experience and resource can not be made full use of: design is the accumulation of experience, successfully
Design experienced by test and the checking used, it is ensured that design result meets design requirement, has good
Technique well, manufacturing.If not using for reference existing Element Design experience, use the design knot of maturation
Really, the reliability of Element Design, the designing quality of part are required for again verifying, the system of part
Make technique to be also required to again examine, have influence on the utilization of tooling device, certainly will cause and have experience
With the waste of resource, it is unfavorable for the accumulation of experience, is unfavorable for realizing the quick design of product.
By to the analysis of current version part form, conclusion, the regulation following strictly modeling specification is built
Vertical parametrization, modular component, provide condition for realizing the definition of normalized Products Digital.
Designer in the design process, chooses component from component base, carries out the Preliminary design of product and determines
Justice.When component base does not has available component, set up the application of new structural member by proposition, complete
After the design of newly-built component, technique, manufacture etc. are examined, component base increases required component.
By such regulation, can the digital definition process of thorough normative model, it is ensured that designing quality and
Anufacturability.
2) it is that the realization of unified model interconnected system lays the foundation
Component base is used to carry out parallel product digital definition except realizing accelerating design schedule, Specification Design
Outside process, still yet another advantage is that the geometry by comprising in component, function, performance data are (non-several
What data), utilize unified model corresponding technology, automatically generate the function needed for each specialty of aircraft, property
Energy simulation analysis, Optimized model, it is achieved in aircraft digital design cycle, major-minor flow process is integrated.Cause
This, component library system is when being designed planning, it should the exploitation with unified model interconnected system, number
Fully coordinate according to demand etc., in each design phase of main flow, be not only completed the example of component
Change, and by model simplification system, component is simplified, extract structure for unified model interconnected system
Part geometry, non-geometric data lay the foundation.
Claims (2)
1. 1 grade of component parameter method for designing of aircraft stringer class part, it is characterised in that: use parametrization
Stringer class part in component statement aircaft configuration, the 1 grade of component parameterization statement of aircraft stringer class part
Be specifically related to following 4 partial contents: " base attribute ", " geometric attribute ", " non-geometric attribute ", " two
Dimension sectional view "；Wherein:
" base attribute " specifically includes: component name, version number, the establishment time, component description,
Manufacturing process, remarks；
" geometric attribute " is specifically divided into positional parameter, cross section parameter two parts, wherein, positional parameter
Including: external surface, axial plane, prelocalization face, rear-locating face；Cross section parameter is specially the length in cross section
Degree, width, highly, thickness information；
" non-geometric attribute ": be specifically related to following two parts content: decomposing scheme, corresponding decomposing scheme
" non-geometric attribute " information；Wherein: stringer class part need not decompose, for overall plan；Right
" non-geometric attribute " information answering decomposing scheme specifically includes: the simplified element type that can use,
The computation attribute of corresponding the type finite element unit and the computing formula of association；
" two-dimensional section figure ": for supplying the thing of user's each parameter of correct understanding component when component instantiation
Reason meaning
In " geometric attribute " for L-type 1 grade of component of stringer part, cross section parameter specifically includes down
State three: edge strip T profile overall width on cross section, upper edge strip T profile right side width, lower edge strip are T-shaped
Material overall width；
For 1 grade of component of aircraft stringer class part of L-shaped extrudate, its simplified element, calculating belong to
Property and incidence formula see table 2:
Table 2 is to be reduced to bar, the component computation attribute of beam class unit and incidence formula
In table 2: H1 is the special case of upper edge strip T profile right side width H；T1 is that lower edge strip T profile is total
The special case of width t；L1 is the special case of upper edge strip T profile overall width L.
2. according to 1 grade of component parameter method for designing of aircraft stringer class part described in claim 1,
It is characterized in that: 1 grade of component parameterization of aircraft stringer class part is stated and further related to following 3 partial contents:
" association knowledge ", " Import Reports ", " explanation "；Wherein:
" association knowledge " is when component calls, and provides a user with the relevant design knowledge of this component；
" Import Reports " is for the modeling process of recording member；
" illustrating ": for geometry location parameter, axle, front and back to position be all curved surface, therefore can produce many
Planting different combinations, various different cross sectional shapes also have different combinations.
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| CN104298798B (en) * | 2014-04-17 | 2017-05-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Three-dimensional coordinating method for airplane product |
| CN106096092B (en) * | 2016-05-31 | 2019-04-23 | 中国航空工业集团公司西安飞机设计研究所 | A kind of design method of stringer banjo fixing butt jointing test clamping end |
| 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) |
| CN116061464A (en) * | 2022-12-26 | 2023-05-05 | 江西洪都航空工业集团有限责任公司 | Multi-stringer forming device and forming method |
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