CN102982220B - Aircraft muscle class 1 grade of component parameter design method of part - Google Patents
Aircraft muscle class 1 grade of component parameter design method of part Download PDFInfo
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Abstract
Aircraft muscle class 1 grade of component parameter design method of part：With the muscle class part in parametrization component statement aircaft configuration, the 1 grade of component parameterization statement of aircraft muscle class part is specifically related to following 4 partial contents：1）" base attribute " is specifically included：Component name, version number, creation 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 correspondence decomposing scheme；4）" two-dimensional section figure " is used for the physical significance when component is instantiated for each parameter of user's correct understanding component.The present invention helps to set up the component library system of aircraft, it is that airplane design standardization and simulation analysis provide function, performance model data basis with optimization, data is harmonious between guarantee geometry model machine, function model machine/performance prototype, improves the designing quality of aircraft, shortens the lead time.
Description
Technical field
The present invention relates to technical field of aircraft structure design, a kind of 1 grade of component parameter of aircraft muscle class part is specifically provided
Change design method.
Background technology
In the prior art, with the application that deepens continuously of cad technique, as cad technique increasingly becomes airplane design portion
The essential instrument of door.Parameter before designer needs to solve to complete product three-dimensional entity model using CAD determines to ask
Topic --- design.If cad technique can not participate in the determination of product parameters, then the application of cad technique in the design is only
The description of design result, is not design truly.CAD system will participate in the design process of product, design process
Construction of A Model just turns into key.This model should be able to be adapted to the data demand of the systems such as CAD/CAE, meet Specialty Design flow
Description.Therefore, CAE technologies are incorporated into by external major famous CAD systems one after another on the basis of CAD basic functions are realized
Respective CAD system, or to each CAE systems with data interface, expect to realize that CAD's and CAE is integrated, meet work
Journey design needs, and this is the usual way of existing main flow CAD system.At present in terms of the entity analysis of part, CAD and CAE
Technology can be realized seamless integrated, but how to solve the Seamless integration- of aviation thin-wall construction, that is, solve the geometry class of CAE models
The problem of type and uncoordinated CAE model geometric types, the key as influence CAD with CAE seamless connections, prior art can not also
Solve.
Aircraft muscle class 1 grade of component of part is the important component in the aeroplane structure design based on parametrization component, because
This, people are highly desirable to obtain a kind of excellent aircraft muscle class 1 grade of component parameter design method of part of technique effect.
The content of the invention
It is an object of the invention to provide a kind of aircraft used in the aeroplane structure design method based on parametrization component
1 grade of component parameter design method of muscle class part.
Its technical foundation is the aeroplane structure design method based on parametrization component, is now described below：
The key innovations of aeroplane structure design method based on parametrization component are to fly using parametrization component statement
The geological information and non-geometry information of structure are included in typical part in machine structure, component；The parametrization component is to flying
Machine is commonly used in designing formed by parts progress induction-arrangement, the 3-dimensional digital comprising geometry and non-geometric attribute data information
Change model.In the application, multiple structural members are generated using component instantiation.By model simplification, the attribute in structural member is refined
Information, automatically generates structural finite element model.
The requirement that the parametrization component is divided by the aircraft digital design phase, is divided into 4 ranks, scheme is corresponded to respectively
Design, preliminary design, trim designs and detailed design；Wherein：
1 grade of component is used for the schematic design phase, is the model of Full Parameterized；2nd, 3,4 grades of components are on the basis of 1 grade of component
On, according to the requirement of different design stage, gradually supplement, improve and ripe, finally give the Products Digital available for manufacture
Model；2nd, 3,4 grades of components reflect Products Digital and define gradually ripe process, are mainly used in designer to design process
Understanding and study, will for meet new design objective while can be modified on the basis of component example to it
Ask.The knowledge related to 2-4 grades of components is more enriched, and is integrated with the conventional design tool of engineering, helps designer to carry out
Preliminary design analysis.
Following requirements are also met for 1 grade of component：
" component " is the parametrization set up in strict accordance with three-dimensional objects digitization modeling specification, include each attribute of part
A certain quasi-representative part；After attribute, the parameter definition of component are completed under CATIA environment, then it can belong to according to component
Property and parameter definition one component of generation example, i.e. Products Digital defines result and is placed under PDM comprehensive management；
" attribute of component " includes geometry and non-geometric attribute；Wherein：Geometric attribute is all parametrization, for forming three
Example is tieed up, geometric attribute is specifically divided into two classes, and a class is the positional parameter of component, such as external form curved surface, component positioning plane, separately
One class is the cross sectional shape parameter of component, such as thickness, width；The non-geometric attribute of component is mainly used in describing the function of component
And attribute of performance, set up function, performance prototype for Unified Model interconnected system and master data is provided；The definition of non-geometric attribute with
The continuous maturation of component, its content is gradually perfect.
Structure attribute data are pre-defined component data, including the location data of component, cross section geometric data, component
Weight coefficient, component can simplified element., it is necessary to geometry location parameter, component to component in component uniform data
Cross section property (geometry, cross section parameter), the weight characteristic of component, the component optional characteristic that simplifies in CAE analysis are carried out
Specific definition, forms member function, the maximum collection of attribute of performance description.The complete definition of structure attribute is model simplification system pair
The foundation that component is simplified, is the input data source that component used and simplified module.On the other hand, by setting up structure attribute
Definition, the simplification process of specification component realizes automatically generating for FEM model.At structure attribute definition and component geometry entity
In binding state, if the component entity in component base does not have corresponding attribute definition, after component instantiation, component simplifies
Module will be unable to recognize the example；If delete a certain component entity in component base part, the corresponding attribute of the component is determined
Justice should be deleted together.
The application of aeroplane structure design method based on parametrization component, is quickly to set up product Preliminary design mould first
Type.Using the definition for parameterizing component and quickly carrying out component, preliminary digital prototype is built.When component is called, modeling base is used
Geometry benchmark defined in standard, defines the positional parameter of component, completes the sterically defined instantiation of component；Utilize component geometric parameters
Number definition interfaces, complete the instantiation definition of member section characteristic parameter.By two above process, complete gemel is called
And instantiation, so as to realize the quick purpose for setting up product Preliminary design model.In the invoked procedure of component, can use with
The knowledge and Engineering Algorithm of component association, according to preliminary design requirement, determine the parameters such as the sectional dimension of component.
Next to that setting up Math data (non-geometric data definition).On the basis of component example, component is defined
The function of non-geometry information, i.e. component, attribute of performance, will define result and are saved in Products Digital model (CATIA models).
The definition of model simplification information is the process of gradual perfection, and all properties being stored in product data constitute unified model number
According to basis, not only contain design for manufacture data, and contain the analyze data of Design-Oriented.Use unified mould
Type interconnected system is extracted and processed to these data, then function, the performance that can be set up needed for each secondary flow journey of airplane design are imitated
True analysis model, realizes the linking of the major-minor flow of airplane design.
It is that 1 grade of component of schematic design phase service is expired in the aeroplane structure design method based on parametrization component
Foot states requirement：Using the digital prototype formed after 1 grade of component instantiation, determined tentatively by CAE analysis and optimization design
Parameter of structure design, basis is provided for weight estimation, and the aircaft configuration scheme that proof of concept is proposed is carried out clearly and embodied,
Finally provide complete aircaft configuration overall plan；1 grade of component specifically includes interior appearance curved surface, positioning datum plane, cutd open
Face parameter, non-geometry information.
It is that 2 grades of components of schematic design phase service are expired in the aeroplane structure design method based on parametrization component
Foot states requirement：
2 grades of components were serviced for the concept phase；The digital prototype formed by 2 grades of components, be aircraft accessibility,
Compatibility that maintainable, enough reliability, human engineering and supports are equipped etc. carries out coordinate design as far as possible；Zero
Part basic size provides the detailed decomposition base of weight indicator on the basis of all having determined, but not yet carries out detailed assembling
And mounting design；
2 grades of components are not the components of Full Parameterized, are on 1 grade of component instantiation and the basis after analysis of optimizing design
On, some sub-assembly/parts are integrated/be divided into component, annexation, production breakdown interface, design separation between structure is determined
Face, the preliminary reconciling spatial scale design of progress；Specifically include following design contents：
(certain intersection point between such as clear and definite wing and fuselage docks for level to be connect the design of connection concrete form between big part
Head/auricle connection)；(such as beam is continuous, rib segmentation for frame member segmentation in length and breadth；Not yet specifically connected between frame member in length and breadth
Form design is connect, does not have the joint, angle box, cornual plate of connection between frame member in length and breadth such as)；Determine single member segments shape
Formula, position are (such as vertical wall internal and external section docking, fit；Frame member not yet carries out detailed design, such as beam, wall, rib only have edge strip and
Web, without middle rib)；Coordination positioning between structural member (such as beam edge strip moves down laminating covering inner surface)；Lid position
Put, openings of sizes is designed；Structural member is the preliminary perforate of each system pass (perforate is to dig a hole, and strengthens designing without flange etc.).
It is that 3 grades of components of schematic design phase service are expired in the aeroplane structure design method based on parametrization component
Foot states requirement：3 grades of components are the services of Design for assembly stage；The digital prototype formed by 3 grades of components, carries out each function series
System and structure, structure and interstructural trim designs, by checking that feelings are docked at various states, interference and the interface of integrated design
Condition, completes the interference checking of whole airplane, forms final system/structural interface definition and checks basis there is provided weight；This stage
The digital prototype of formation is developed model machine in flow equivalent to conventional airplane and acted on；
3 grades of components are not the components of Full Parameterized, are, according to trim designs needs, 2 grades of components to be carried out with continuation refinement, is repaiied
Change and improve and increase and decrease corresponding spare part, complete each function system and designed with structure, structure and interstructural final connection interface,
It is specifically comprising the description below requirement：Annexation design (such as connection of beam, rib plus angle box, cornual plate between component；Crucial portion
Position fastener connection section position design, the connection localized design for the component that such as bearing pin larger with certain stress is connected；Lid mouthful frame is set
Meter)；Mounting design between component and system (as determined installation of the fuel pump on structural member)；Interference between component and system is set
Meter (structure determines for system pass perforate).
It is that 4 grades of components of schematic design phase service are expired in the aeroplane structure design method based on parametrization component
Foot states requirement：4 grades of components are serviced for detailed design phase；The final full machine digital prototype formed by 4 grades of components is met
Final design load, determines parts final weight state, while meeting manufacturability requirement；
4 grades of components are not the components of Full Parameterized, are on the basis of 3 grades of components, to correct, improve three-dimensional part model
Local detail, meets what all design requirements of component were obtained, and it is specifically comprising the description below requirement：To the local tool of component connection
Shape design, local strengthening design；Component joint detail designs (standard component code name, spread pattern, gap, back gauge, related structure
Part may be changed locally)；Component chamfering, rounding, lightening core, mitigation hole, mitigation groove, oil-through-hole, the design of technological datum hole.
The aeroplane structure design method based on parametrization component, it is characterised in that：" component " strictly presses three-dimensional objects
Digitization modeling specification is set up, and by component and its is resulted in relative design, technique, manufacture with knowledge base and is known
Know, Computer Aided Design personnel complete design works during component use；Typical structural elements can be summarized as 11 classes in aircraft：
1) beam, wall；2) rib；3) muscle；4) skinpiston；5) frame；6) longitudinal baffle；7) joint, angle box；8) lid, mouth frame；9) band plate；
10) hinge；11) it is other.
The innovation main points of the present invention and claimed emphasis are related to a kind of 1 grade of component parameterization design of aircraft muscle class part
Method, it is characterised in that：With the muscle class part in parametrization component statement aircaft configuration, aircraft muscle class 1 grade of component parameter of 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 " is specifically included：Component name, version number, creation time, component description, manufacturing process, remarks；
" geometric attribute " is specifically divided into positional parameter, cross section parameter two parts, wherein, positional parameter includes：Where rib
Frame plane, the external surface of rib end points 1, the locating surface of rib end points 1, the external surface of rib end points 2, the locating surface of rib end points 2；Join in section
Number is specially height, the thickness information in section；
" non-geometric attribute "：Specifically related to following two parts contents：" the non-geometric category of decomposing scheme, correspondence decomposing scheme
Property " information；Wherein：Muscle class part need not be decomposed, and be overall plan；" non-geometric attribute " information of correspondence decomposing scheme is specific
Including：The simplified element type that can be used, the computation attribute of correspondence the type finite element unit and the calculation formula of association；
" two-dimensional section figure "：For when component is instantiated for the physical significance of each parameter of user's correct understanding component.
1 grade of component positional parameter schematic diagram of aircraft muscle class part is referring to Fig. 1.
Described 1 grade of component parameter design method of aircraft muscle class part, it is characterised in that：For 1 grade of component of L-type muscle part
" geometric attribute " in, cross section parameter specifically include it is following the two：Rib height H, rib thickness t.Cross section parameter schematic diagram is shown in
Fig. 2, parameter description is shown in Table 1.
The cross section parameter of table 1 is described
Described 1 grade of component parameter design method of aircraft muscle class part, it is characterised in that：For 1 grade of aircraft muscle class part
Component, its simplified element, computation attribute and incidence formula are referring to table 2；In table 2：H1 is the spy of rib height H on member section
Example；T1 is the special case of rib thickness t on member section；
Table 2 can be reduced to the component computation attribute and incidence formula of bar, beam class unit
Described 1 grade of component parameter design method of aircraft muscle class part, it is characterised in that：Aircraft muscle class 1 grade of component of part
Parametrization statement further relates to following 3 partial contents：" association knowledge ", " Import Reports ", " explanation "；Wherein：
" association knowledge " is the relevant design knowledge that the component is provided a user when component is called；
" Import Reports " are used for the modeling process of recording member；
" explanation "：For geometry location parameter, axle, front and rear positioning are curved surfaces, therefore can produce a variety of different combinations,
Referring specifically to table 3, a variety of cross sectional shapes also have different combinations.
The present invention provides a kind of feasible solution for the technical problem described in background technology, specifically provides winged
Machine muscle class 1 grade of component parameter design method of part.The component library system of aircraft is set up based on this, can make aircraft product
Digital definition process specification, simulation analysis and optimization for each secondary flow journey of airplane design provide function, performance model data
Basis, it is ensured that data is harmonious between geometry model machine, function model machine/performance prototype, it is final to realize the design matter for improving aircraft
Amount, the purpose for shortening the lead time.
The combination of the muscle class component of table 3 difference positioning geometry
Compared with prior art, advantage for present invention and effect:
1) present invention contributes to modular product digital definition process
CAD system provides abundant modelling meanses for designer, can be added the problem of same by different approach
To solve, therefore, the digital definition of product there is nonstandard problem.Design of digital in the past few years experience have shown that, number
The lack of standardization of word definition procedure can bring following two subject matters：
First is the deciphering hardly possible that designs a model：What one designer set up designs a model, and other designers are difficult to understand
Clear, if necessary to be modified to model, designer often thinks that research understands that model sets up process not as good as again
Model is set up once；Even model designer after a period of time has passed, wants to review modeling process also very difficult.
Next to that existing experience and resource can not be made full use of：Design is the accumulation of experience, and successfully design experienced
The checking tested and used, it is ensured that design result meets design requirement, with good technique, manufacturing.If do not borrowed
Reflect existing Element Design experience, using ripe design result, the reliability of Element Design, the designing quality of part are required for
Again verified, the manufacturing process of part is also required to be examined again, has influence on the utilization of tooling device, certainly will cause
There is the waste of experience and resource, be unfavorable for the accumulation of experience, be unfavorable for realizing the quick design of product.
By the analysis to current version part form, conclude, the regulation for following strictly modeling specification sets up parametrization, mould
The component of block, to realize that the Products Digital definition of standardization provides condition.Designer in the design process, from component
Component is chosen in storehouse, Preliminary design and the definition of product is carried out.When there is no available component in component base, by proposing to set up
The application of new structural member, after completing to examine design, technique, manufacture of newly-built component etc., increases required structure in component base
Part.By such regulation, can thorough normative model digital definition process, it is ensured that designing quality and anufacturability.
2) laid the foundation for the realization of unified model interconnected system
Parallel product digital definition is carried out in addition to realizing and accelerating design schedule, Specification Design process using component base, also
Have an advantage in that it is, by the geometry included in component, function, performance data (non-geometric data), skill to be associated using unified model
Art, automatically generates aircraft each required function of specialty, Performance Analysis, Optimized model, realizes aircraft digital design stream
Major-minor flow is integrated in journey.Therefore, component library system is when being designed planning, it should with opening for unified model interconnected system
Hair, demand data etc. are fully coordinated, and in each design phase of main flow, the instantiation of component, Er Qietong are not only completed
Cross model simplification system to simplify component, be that unified model interconnected system extracts component geometry, non-geometric data and establishes base
Plinth.
Brief description of the drawings
Below in conjunction with the accompanying drawings and embodiment the present invention is further detailed explanation：
Fig. 1 is L-type rib component positional parameter schematic diagram；
Fig. 2 is L-type rib component schematic cross-section.
Embodiment
Embodiment 1
A kind of aircraft muscle class 1 grade of component parameter of part used in the aeroplane structure design method based on parametrization component
Change design method.
Its technical foundation is the aeroplane structure design method based on parametrization component, and related content is referring to " hair in specification
Bright creation content " part.
The present embodiment emphasis is related to a kind of 1 grade of component parameter design method of aircraft muscle class part：With parametrization piece table
The muscle class part in aircaft configuration is stated, the 1 grade of component parameterization statement of aircraft muscle 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 " is specifically included：Component name, version number, creation time, component description, manufacturing process, remarks；
" geometric attribute " is specifically divided into positional parameter, cross section parameter two parts, wherein, positional parameter includes：Where rib
Frame plane, the external surface of rib end points 1, the locating surface of rib end points 1, the external surface of rib end points 2, the locating surface of rib end points 2；Join in section
Number is specially height, the thickness information in section；
" non-geometric attribute "：Specifically related to following two parts contents：" the non-geometric category of decomposing scheme, correspondence decomposing scheme
Property " information；Wherein：Muscle class part need not be decomposed, and be overall plan；" non-geometric attribute " information of correspondence decomposing scheme is specific
Including：The simplified element type that can be used, the computation attribute of correspondence the type finite element unit and the calculation formula of association；
" two-dimensional section figure "：For when component is instantiated for the physical significance of each parameter of user's correct understanding component.
1 grade of component positional parameter schematic diagram of aircraft muscle class part is referring to Fig. 1.
Described 1 grade of component parameter design method of aircraft muscle class part, for " the geometry category of 1 grade of component of L-type muscle part
Property " in, cross section parameter specifically include it is following the two：Rib height H, rib thickness t.Cross section parameter schematic diagram is shown in Fig. 2, and parameter is retouched
State and be shown in Table 1.
The cross section parameter of table 1 is described
Described 1 grade of component parameter design method of aircraft muscle class part, for aircraft muscle class 1 grade of component of part, it simplifies
Unit, computation attribute and incidence formula are referring to table 2；In table 2：H1 is the special case of rib height H on member section；T1 is that component is cut
Rib thickness t special case on face；
Table 2 can be reduced to the component computation attribute and incidence formula of bar, beam class unit
Described 1 grade of component parameter design method of aircraft muscle class part, the 1 grade of component parameterization statement of aircraft muscle class part is also
It is related to following 3 partial contents：" association knowledge ", " Import Reports ", " explanation "；Wherein：
" association knowledge " is the relevant design knowledge that the component is provided a user when component is called；
" Import Reports " are used for the modeling process of recording member；
" explanation "：For geometry location parameter, axle, front and rear positioning are curved surfaces, therefore can produce a variety of different combinations,
Referring specifically to table 3, a variety of cross sectional shapes also have different combinations.
The combination of the muscle class component of table 3 difference positioning geometry
The application mode of aircraft muscle class 1 grade of component of part is mainly 2 parts：
A) quickly product Preliminary design model is set up
Module, designer are quickly designed by component needed for interactive selection from component base and startup component parameter
The definition of component can be quickly carried out, preliminary digital prototype is built.
1) when component is called, using the geometry benchmark defined in modeling benchmark, the positional parameter of component is defined, component is completed
Sterically defined instantiation；
2) component geometric parameter definition interfaces are utilized, the instantiation definition of member section characteristic parameter is completed.Pass through the above
Two processes, complete gemel calling and instantiating, so as to realize the quick purpose for setting up product Preliminary design model.
B Math data (non-geometric data definition)) are set up
On the basis of component example, the non-geometry information of component, the i.e. function of component, attribute of performance are defined, will be defined
As a result it is saved in Products Digital model (CAD model).
The definition of model simplification information is the process of gradual perfection, and all properties being stored in product data constitute system
The basis of one model data, not only contains design for manufacture data, and contain the analyze data of Design-Oriented.Make
These data are extracted and processed with Unified Model interconnected system, then the work(that can be set up needed for each secondary flow journey of airplane design
Energy, Performance Analysis model, realize the linking of the major-minor flow of airplane design.
The step of 1 grade of component of aircraft muscle class part is mainly applied：
A) mode one：Generate component example
1) startup component storehouse, browses component, selected member
2) in the component instantiation window and CATIA platforms of ejection, the geometry location benchmark of interactive selection component
3) member section parameter is defined
4) component non-geometry information is filled in, component example is generated after confirmation.
B) mode two：Change component example
1) in CATIA platforms, the digital-to-analogue for instantiating generation on structure tree by component is found
2) digital-to-analogue, ejection modification window are double-clicked
3) in modification window, modification geological information, non-geometry information
4) modification of component example is completed after confirming.
C) mode three：Set up Math data
1) in component base (CATIA) system, the digital-to-analogue after being instantiated by component is placed in current operating state
2) Unified Model interconnected system is used, geological information and non-geometry information in digital-to-analogue is extracted
3) Unified Model interconnected system is utilized, FEM model is generated.
The present embodiment provides a kind of feasible solution for the technical problem described in background technology, specifically provides
Aircraft muscle class 1 grade of component parameter design method of part.The component library system of aircraft is set up based on this, can produce aircraft
Product digital definition process specification, simulation analysis and optimization for each secondary flow journey of airplane design provide function, performance model number
It is final to realize the design for improving aircraft according to basis, it is ensured that data is harmonious between geometry model machine, function model machine/performance prototype
Quality, the purpose for shortening the lead time.
Compared with prior art, the present embodiment has the advantage that and effect:
1) the present embodiment contributes to modular product digital definition process
CAD system provides abundant modelling meanses for designer, can be added the problem of same by different approach
To solve, therefore, the digital definition of product there is nonstandard problem.Design of digital in the past few years experience have shown that, number
The lack of standardization of word definition procedure can bring following two subject matters：
First is the deciphering hardly possible that designs a model：What one designer set up designs a model, and other designers are difficult to understand
Clear, if necessary to be modified to model, designer often thinks that research understands that model sets up process not as good as again
Model is set up once；Even model designer after a period of time has passed, wants to review modeling process also very difficult.
Next to that existing experience and resource can not be made full use of：Design is the accumulation of experience, and successfully design experienced
The checking tested and used, it is ensured that design result meets design requirement, with good technique, manufacturing.If do not borrowed
Reflect existing Element Design experience, using ripe design result, the reliability of Element Design, the designing quality of part are required for
Again verified, the manufacturing process of part is also required to be examined again, has influence on the utilization of tooling device, certainly will cause
There is the waste of experience and resource, be unfavorable for the accumulation of experience, be unfavorable for realizing the quick design of product.
By the analysis to current version part form, conclude, the regulation for following strictly modeling specification sets up parametrization, mould
The component of block, to realize that the Products Digital definition of standardization provides condition.Designer in the design process, from component
Component is chosen in storehouse, Preliminary design and the definition of product is carried out.When there is no available component in component base, by proposing to set up
The application of new structural member, after completing to examine design, technique, manufacture of newly-built component etc., increases required structure in component base
Part.By such regulation, can thorough normative model digital definition process, it is ensured that designing quality and anufacturability.
2) laid the foundation for the realization of unified model interconnected system
Parallel product digital definition is carried out in addition to realizing and accelerating design schedule, Specification Design process using component base, also
Have an advantage in that it is, by the geometry included in component, function, performance data (non-geometric data), skill to be associated using unified model
Art, automatically generates aircraft each required function of specialty, Performance Analysis, Optimized model, realizes aircraft digital design stream
Major-minor flow is integrated in journey.Therefore, component library system is when being designed planning, it should with opening for unified model interconnected system
Hair, demand data etc. are fully coordinated, and in each design phase of main flow, the instantiation of component are not only completed, and pass through
Model simplification system simplifies to component, is that unified model interconnected system is extracted component geometry, non-geometric data and laid the foundation.
Claims (2)
1. aircraft muscle class 1 grade of component parameter design method of part, the muscle class part in aircaft configuration is stated with parametrization component,
The 1 grade of component parameterization statement of aircraft muscle class part is specifically related to following 4 partial contents：It is " base attribute ", " geometric attribute ", " non-
Geometric attribute ", " two-dimensional section figure "；Wherein：
" base attribute " is specifically included：Component name, version number, creation time, component description, manufacturing process, remarks；
" geometric attribute " is specifically divided into positional parameter, cross section parameter two parts, wherein, positional parameter includes：Frame is put down where rib
Face, the external surface of rib end points 1, the locating surface of rib end points 1, the external surface of rib end points 2, the locating surface of rib end points 2；Cross section parameter has
Body is height, the thickness information in section；
" non-geometric attribute "：Specifically related to following two parts contents：" non-geometric attribute " letter of decomposing scheme, correspondence decomposing scheme
Breath；Wherein：" non-geometric attribute " information of correspondence decomposing scheme is specifically included：The simplified element type that can be used, to should
The computation attribute of limited types member unit and the calculation formula of association；
" two-dimensional section figure "：For when component is instantiated for the physical significance of each parameter of user's correct understanding component；
For in " geometric attribute " of 1 grade of component of L-type muscle part, cross section parameter specifically include it is following the two：Rib height H, muscle
Bar thickness t；
It is characterized in that：For aircraft muscle class 1 grade of component of part, its simplified element, computation attribute and incidence formula referring to table 2,
In table 2：H1 is the special case of rib height H on member section；T1 is the special case of rib thickness t on member section；
Table 2 can be reduced to the component computation attribute and incidence formula of bar, beam class unit
。
2. according to 1 grade of component parameter design method of aircraft muscle class part described in claim 1, it is characterised in that：Aircraft muscle class
1 grade of component parameterization statement of part further relates to following 3 partial contents：" association knowledge ", " Import Reports ", " explanation "；Wherein：
" association knowledge " is the relevant design knowledge that the component is provided a user when component is called；
" Import Reports " are used for the modeling process of recording member；
" explanation "：For geometry location parameter, axle, front and rear positioning are curved surfaces, therefore can produce a variety of different combinations, various
Different cross sectional shapes also has different combinations.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210571167.4A CN102982220B (en) | 2012-12-25 | 2012-12-25 | Aircraft muscle class 1 grade of component parameter design method of part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210571167.4A CN102982220B (en) | 2012-12-25 | 2012-12-25 | Aircraft muscle class 1 grade of component parameter design method of part |
Publications (2)
| Publication Number | Publication Date |
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| CN112882686A (en) * | 2019-11-29 | 2021-06-01 | 中国商用飞机有限责任公司 | Method and device for establishing fastener hole feature library, computer and storage medium |
| CN116720285B (en) * | 2023-08-07 | 2024-01-02 | 上海索辰信息科技股份有限公司 | Parameterized design method for complex shell structure |
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| US6944832B2 (en) * | 2002-06-20 | 2005-09-13 | The Boeing Company | System design using part roles |
| CN101763066A (en) * | 2009-12-15 | 2010-06-30 | 沈阳飞机工业（集团）有限公司 | Management system of numerical control machining tool typical parts of complex parts of airplane and method |
| CN102722626A (en) * | 2012-06-11 | 2012-10-10 | 北京航空航天大学 | Aircraft configuration verifying and auditing data acquiring method based on module |
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| US6944832B2 (en) * | 2002-06-20 | 2005-09-13 | The Boeing Company | System design using part roles |
| CN101763066A (en) * | 2009-12-15 | 2010-06-30 | 沈阳飞机工业（集团）有限公司 | Management system of numerical control machining tool typical parts of complex parts of airplane and method |
| CN102722626A (en) * | 2012-06-11 | 2012-10-10 | 北京航空航天大学 | Aircraft configuration verifying and auditing data acquiring method based on module |
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