CN103093031A - Parametrization design method for aircraft skin wall panel part primary components - Google Patents
Parametrization design method for aircraft skin wall panel part primary components Download PDFInfo
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Abstract
A parametrization design method for aircraft skin wall panel part primary components includes that parametrization components are used for expression of skin wall panel parts in an aircraft structure, and the parametrization expression of the aircraft skin wall panel part primary components particularly relates to the following four parts of the content: 1), 'essential attribute' which particularly includes component name, version number, creation time, component description, manufacturing technique and remarks, 2), 'geometric attribute' which particularly falls into location parameters and section parameters, 3), 'non-geometric attribute' which particularly relates to scheme decomposition and 'non-geometric attribute' information corresponding to the scheme decomposition, and 4), a 'two-dimension sectional drawing' which is used for correct understanding on the physical significance of each parameter of the components by users in component instantiation. The parametrization design method for the aircraft skin wall panel part primary components facilitates the establishing of an aircraft component base system, provides function and performance model data base for aircraft design standardization and simulated analysis and optimization, guarantees the coordination and consistency of data among geometric prototypes and function prototypes/performance prototypes, improves the aircraft design quality, and shortens the aircraft development cycle.
Description
Technical field
The present invention relates to the aeroplane structure design technical field, provide especially a kind of aircraft skin wallboard class part 1 grade of member parameterization design method.
Background technology
In prior art, along with the application that deepens continuously of cad technique, along with cad technique more and more becomes the requisite instrument of aircraft design unit.The designer need to solve and use CAD to complete product three-dimensional entity model parameter problem identificatioin before---design.If cad technique can not participate in determining of product parameters, the application of cad technique in design is only the description of design result so, is not design truly.CAD system will participate in the design process of product, and the Construction of A Model of design process just becomes key.This model should be able to be fit to the data demand of the systems such as CAD/CAE, meets the description of Specialty Design flow process.For this reason, external each large famous CAD system is on the basis of realizing the CAD basic function, one after another the CAE technology is incorporated into CAD system separately, perhaps provide data-interface to each CAE system, expectation realizes that CAD and CAE's is integrated, satisfy the engineering design needs, this is the common way of existing main flow CAD system.At present aspect the entity analysis of part, CAD and CAE technology can realize seamless integrated, but how to solve the seamless integrated of aviation thin-wall construction, namely solve geometric type and the inharmonic problem of CAE model geometric type of CAE model, become the key that affects CAD and CAE seamless connection, prior art also can't solve.
1 grade of member of aircraft skin wallboard class part is based on the important component part in the aeroplane structure design of parametrization member, and therefore, people urgently wish to obtain the good 1 grade of member parameterization design method of aircraft skin wallboard class part of a kind of technique effect.
Summary of the invention
The purpose of this invention is to provide a kind of 1 grade of member parameterization design method of aircraft skin wallboard class part that uses in the aeroplane structure design method based on the parametrization member.
Its technical foundation is the aeroplane structure design method based on the parametrization member, now is described below:
Be typical part in operation parameter member statement aircaft configuration based on the crucial innovative point of the aeroplane structure design method of parametrization member, comprise geological information and the non-geological information of structure in member; Described parametrization member carries out induction-arrangement to parts commonly used in airplane design and forms, comprises how much and the three-dimensional digitalization model of non-geometric attribute data message.In application, utilize the member instantiation to generate a plurality of structural members.By model simplification, refine the attribute information in structural member, automatically the generating structure finite element model.
The requirement that described parametrization member was divided by the airplane digital design phase is divided into 4 ranks, respectively corresponding conceptual design, the design of drawing a design, trim designs and detailed design; Wherein:
1 grade of member is used for the schematic design phase, is the model of Full Parameterized; 2,3,4 grades of members are on the basis of 1 grade of member, and are additional, perfect and ripe gradually according to the requirement of different design stage, finally obtain the Products Digital model that can be used for making; 2,3,4 grades of members have reflected the Products Digital definition process of maturation gradually, are mainly used in the designer to understanding and the study of design process, can on the basis of member example, it be modified simultaneously, are used for satisfying the requirement of new design objective.The knowledge relevant to 2-4 level member is abundanter, and integrated engineering design tool commonly used, helps the designer to carry out preliminary design analysis.
Also satisfy following requirement for 1 grade of member:
" member " sets up, comprises the parameterized a certain quasi-representative part of the various attributes of part in strict accordance with three-dimensional objects digitization modeling standard; When after the attribute of completing member under the CATIA environment, parameter-definition, can be according to the definition of structure attribute and parameter being generated the example of a member, namely Products Digital defines result and is placed under the general management of PDM;
" attribute of member " comprises how much and non-geometric attribute; Wherein: geometric attribute is all parameterized, is used to form three dimensional example, and geometric attribute specifically is divided into two classes, and a class is the positional parameter of member, and as external form curved surface, member plane of orientation etc., another kind of is the cross sectional shape parameter of member, as thickness,
Width etc.; The non-geometric attribute of member is mainly used in describing function and the attribute of performance of member, for the Unified Model interconnected system is set up function, performance prototype provides master data; The definition of non-geometric attribute is along with the continuous maturation of member, and its content is perfect gradually.
The structure attribute data are predefined member data, but comprise the locator data, cross section geometric data, the weight coefficient of member, the simplified element of member of member.In the member uniform data, need to carry out specific definition to weight characteristic, member optional characteristic of simplifying in cae analysis of the geometry location parameter of member, the cross section property of member (geometric configuration, cross section parameter), member, form the maximum collection of member function, attribute of performance description.The complete definition of structure attribute is the foundation that the model simplification system is simplified member, is the input data source that member used and simplified module.On the other hand, by setting up the structure attribute definition, the simplification process of standard member realizes the automatic generation of finite element model.The structure attribute definition is in binding state with the member geometry entity, if the member entity in component base does not have corresponding attribute definition, after this member instantiation, member is simplified module with this example of None-identified; If during a certain member entity in deletion component base spare, the attribute definition that this member is corresponding should together be deleted.
Based on the application of the aeroplane structure design method of parametrization member, it is at first Rapid Establishment product primary design model.Utilize the parametrization member to carry out fast the definition of member, build preliminary electronics model machine.When member calls, use how much benchmark that define in the modeling benchmark, the positional parameter of definition member is completed the sterically defined instantiation of member; Utilize member geometric parameter definition interfaces, complete the instantiation definition of member section characteristic parameter.By above two processes, complete the calling and instantiation of member, thereby realize the purpose of Rapid Establishment product primary design model.In the invoked procedure of member, can use the knowledge related with member and Engineering Algorithm, according to preliminary designing requirement, determine the parameters such as sectional dimension of member.
Next is to set up From Math data (non-geometric data definition).On the basis of member example, the non-geological information of definition member, namely the function of member, attribute of performance, will define result and be saved in (CATIA model) in the Products Digital model.The model simplification information definition is the process of gradual perfection, is kept at the basis that all properties in product data has consisted of the unified model data, has not only comprised towards the design data of making, and has comprised the analysis data of Design-Oriented.Use the unified model interconnected system that these data are extracted and processed, can set up the required function of each secondary flow journey of airplane design, Performance Analysis model, realize the linking of the major-minor flow process of airplane design.
In described aeroplane structure design method based on the parametrization member, 1 grade of member of service satisfies following requirement for the schematic design phase:
Utilize the digital prototype that forms after 1 grade of member instantiation, determine preliminary parameter of structure design by cae analysis and optimal design, for weight estimation provides the basis, the aircaft configuration scheme that proof of concept proposes is carried out clear and definite and specialized, finally provide complete aircaft configuration overall plan; Described 1 grade of member specifically comprises interior appearance curved surface, positioning datum plane, sectional parameter, non-geological information.
In described aeroplane structure design method based on the parametrization member, 2 grades of members of service satisfy following requirement for the schematic design phase:
2 grades of members are the concept phase service; The digital prototype that is formed by 2 grades of members is for the accessibility of aircraft, maintainability, enough reliability, human engineering and support the compatibility etc. of equipment to carry out coordinate design as much as possible; Provide the detailed decomposition base of weight indicator on the basis that parts basic size has all been determined, but not yet carry out detailed assembling and mounting design;
2 grades of members are not the members of Full Parameterized, 1 grade of member instantiation and on through the basis after analysis of optimizing design, some subassembly/parts are integrated/be divided into to member, determine annexation between structure, production breakdown interface, initial breakdown interface, carry out preliminary reconciling spatial scale design; Specifically comprise following design content:
Connect concrete form design (being that horizontal open joint/auricle is connected with certain intersection point between fuselage as clear and definite wing) between large parts; (as continuous in beam, the rib segmentation of frame member segmentation in length and breadth; Not yet carry out in length and breadth the design of concrete type of attachment between frame member, as the joint that there is no in length and breadth connection between frame member, angle box, gusset plate etc.); Determine that single member segments form, position are (as vertical wall internal and external section docking, fit; Frame member not yet carries out detailed design, as beam, wall, rib etc., edge strip and web is only arranged, the rib in the middle of not having); Coordination location (moving down applying covering inside surface as the beam edge strip) between structural member; Lid position, openings of sizes design; Structural member is the preliminary perforate of each system pass (perforate is just dug a hole, and there is no the reinforcement designs such as flange).
In described aeroplane structure design method based on the parametrization member, 3 grades of members of service satisfy following requirement for the schematic design phase:
3 grades of members are the services of Design for assembly stage; The digital prototype that is formed by 3 grades of members, carry out each function system and structure, structure and interstructural trim designs, by various states, interference and the interface docking situation that checks integrated design, complete the interference checking of whole airplane, form final system/structural interface definition, provide weight to check the basis; The digital prototype that this stage forms is equivalent to model machine effect in kind in conventional airplane development flow process;
3 grades of members are not the members of Full Parameterized, according to the trim designs needs, 2 grades of members are continued refinement, modification and improve and increase and decrease corresponding spare part, complete each function system and structure, structure and interstructural final connection interface design, it specifically comprises following content request: the annexation design between member (connects as beam, rib and adds angle box, gusset plate etc.; Key position securing member connecting portion design is as the connection localized design of the member that is connected with certain stressed larger bearing pin; The design of lid mouth frame); Mounting design between member and system (as determining the installation of fuel pump on structural member); Interference design between member and system (structure is that the system pass perforate is determined).
In described aeroplane structure design method based on the parametrization member, 4 grades of members of service satisfy following requirement for the schematic design phase:
4 grades of members are the detailed design phase service; The final full machine digital prototype that is formed by 4 grades of members satisfies final design load, determines parts final weight state, satisfies simultaneously the manufacturability requirement;
4 grades of members are not the members of Full Parameterized, on the basis of 3 grades of members, revise, improve the local detail of three-dimensional part model, satisfy that all designing requirements of member obtain, it specifically comprises following content request: member is connected local concrete shape design, locally strengthens design; Member joint detail design (standard component code name, spread pattern, gap, back gauge, associated components may locally be changed); Member chamfering, rounding, lightening hole, alleviate the hole, alleviate groove, oil through, technological datum hole design.
Described aeroplane structure design method based on the parametrization member, it is characterized in that: " member " strictly pressed three-dimensional objects digitization modeling standard and set up, by member and follow knowledge base can obtain relative design, technique, manufacturing knowledge, Computer Aided Design personnel complete design work in the member use procedure; In aircraft, typical structural elements can be summarized as 11 classes: 1) beam, wall; 2) rib; 3) grow the purlin; 4) skinpiston; 5) frame; 6) longitudinal baffle; 7) joint, angle box; 8) lid, mouthful frame; 9) band plate; 10) hinge; 11) other.
Innovation main points of the present invention and claimed emphasis relate to 1 grade of member parameterization design method of a kind of aircraft skin wallboard class part, it is characterized in that:
With the skinpiston class part in parametrization member statement aircaft configuration, 1 grade of member parametrization statement of aircraft skin wallboard class part is specifically related to following 4 partial contents: " base attribute ", " geometric attribute ", " non-geometric attribute ", " two-dimensional section figure "; Wherein:
" base attribute " specifically comprises: member title, version number, creation-time, component description,
Manufacturing process, remarks;
" geometric attribute " specifically is divided into positional parameter, cross section parameter two parts, and wherein, positional parameter comprises: external surface, locating surface 1, locating surface 2, locating surface 3, locating surface 4; Cross section parameter is specially the wallboard thickness information; Parametric description sees Table 1.
Table 1 cross section parameter is described
" non-geometric attribute ": be specifically related to following two parts content: " non-geometric attribute " information of decomposing scheme, corresponding decomposing scheme; Wherein: skinpiston class part does not need to decompose, and is overall plan; " non-geometric attribute " information of corresponding decomposing scheme specifically comprises: the simplified element type that can adopt, computation attribute and the related computing formula of corresponding the type finite element unit;
" two-dimensional section figure ": the physical significance that is used for supplying each parameter of user's correct understanding member when the member instantiation.
1 grade of member positional parameter schematic diagram of aircraft skin wallboard class part is referring to Fig. 1.
1 grade of member parameterization design method of described aircraft skin wallboard class part is characterized in that: for 1 grade of member of skinpiston class A of geometric unitA, its simplified element, computation attribute are referring to table 2.
Table 2 can be reduced to the member computation attribute of all kinds of plate classes unit
1 grade of member parameterization design method of described aircraft skin wallboard class part is characterized in that: 1 grade of member parametrization statement of aircraft skin wallboard class part also relates to following 3 partial contents: " association knowledge ", " Import Reports ", " explanation "; Wherein:
" association knowledge " is when member calls, and the relevant design knowledge of this member is provided to the user;
" Import Reports " is used for the modeling process of recording member;
" illustrate ": for the geometry location parameter, axle, location, front and back are all curved surfaces, therefore can produce multiple different combination, and specifically referring to table 3, various cross sectional shape also has different combinations.
The combination that the different location of table 3 skinpiston class A of geometric unitA are how much
The present invention specifically provides aircraft skin wallboard class part 1 grade of member parameterization design method for the technical matters described in background technology provides a kind of feasible solution.Set up based on this component library system of aircraft, can make the Airplane Digital Product Definition process specification, for the simulation analysis of each secondary flow journey of airplane design and optimization provide function, performance model data bases, between how much model machines of assurance, function model machine/performance prototype, data is harmonious, final designing quality, the purpose of shortening lead time that realizes improving aircraft.
Compared with prior art, the advantage and the effect that have of the present invention:
1) the present invention helps modular product digital definition process
CAD system provides abundant modelling means for the designer, and same problem can be solved by different approach, and therefore, just there is nonstandard problem in the digital definition of product.Design of digital experience in the past few years shows, the meeting lack of standardization of digital definition process brings following two subject matters:
The firstth, designing a model, it is difficult to understand: what designer set up designs a model, other designers are difficult to understand clear, if need to change model, the designer tends to feel that research knows that model sets up process not as good as again model being set up once; Even the model designer after after a while, wants to review modeling process also very difficult.
Next is to take full advantage of existing experience and resource: design is the accumulation of experience, and the checking that successful design has been experienced test and used can guarantee that design result meets design requirement, and has good technique, manufacturing.If do not use for reference existing Element Design experience, use ripe design result, the reliability of Element Design, the designing quality of part all need again to verify, the manufacturing process of part also needs again to examine, have influence on the utilization of tooling device, certainly will cause the waste that experience and resource have been arranged, be unfavorable for the accumulation of experience, be unfavorable for realizing the rapid Design of product.
By analysis, the conclusion to the current version part form, strictly follow the regulation of modeling standard and set up parametrization, modular member, provide condition for realizing normalized Products Digital definition.
The designer chooses member from component base in design process, carry out primary design and the definition of product.When there is no available member in component base, set up the application of new structural member by proposition, after completing the examinations such as design to newly-built member, technique, manufacturing, increase required member in component base.
By such regulation, thoroughly the digital definition process of normative model, guarantee designing quality and anufacturability.
2) lay the foundation for the realization of unified model interconnected system
The use component base walks abreast outside Products Digital definite division realization quickening design schedule, Specification Design process, also having an advantage is by comprising in member how much, function, performance data (non-geometric data), utilize the unified model corresponding technology, automatically generate required function, Performance Analysis, the Optimized model of each specialty of aircraft, realize the integrated of major-minor flow process in the airplane digital design cycle.Therefore, component library system is when carrying out design planning, should fully coordinate with the exploitation of unified model interconnected system, demand data etc., in each design phase of main flow, not only complete the instantiation of member, and by the model simplification system, member is simplified, for the unified model interconnected system is extracted how much of members, non-geometric data lays the foundation.
Description of drawings
The present invention is further detailed explanation below in conjunction with drawings and the embodiments:
Fig. 1 is skinpiston class A of geometric unitA positional parameter schematic diagram.
Embodiment
Embodiment 1
A kind of 1 grade of member parameterization design method of aircraft skin wallboard class part that uses in the aeroplane structure design method based on the parametrization member.
Its technical foundation is the aeroplane structure design method based on the parametrization member, and related content is referring to " innovation and creation content " part in instructions.
The present embodiment emphasis relates to 1 grade of member parameterization design method of a kind of aircraft skin wallboard class part:
With the skinpiston class part in parametrization member statement aircaft configuration, 1 grade of member parametrization statement of aircraft skin wallboard class part is specifically related to following 4 partial contents: " base attribute ", " geometric attribute ", " non-geometric attribute ", " two-dimensional section figure "; Wherein:
" base attribute " specifically comprises: member title, version number, creation-time, component description, manufacturing process, remarks;
" geometric attribute " specifically is divided into positional parameter, cross section parameter two parts, and wherein, positional parameter comprises: external surface, locating surface 1, locating surface 2, locating surface 3, locating surface 4; Cross section parameter is specially the wallboard thickness information; Parametric description sees Table 1.
Table 1 cross section parameter is described
" non-geometric attribute ": be specifically related to following two parts content: " non-geometric attribute " information of decomposing scheme, corresponding decomposing scheme; Wherein: skinpiston class part does not need to decompose, and is overall plan; " non-geometric attribute " information of corresponding decomposing scheme specifically comprises: the simplified element type that can adopt, computation attribute and the related computing formula of corresponding the type finite element unit;
" two-dimensional section figure ": the physical significance that is used for supplying each parameter of user's correct understanding member when the member instantiation.
1 grade of member positional parameter schematic diagram of aircraft skin wallboard class part is referring to Fig. 1.
1 grade of member parameterization design method of described aircraft skin wallboard class part, for 1 grade of member of skinpiston class A of geometric unitA, its simplified element, computation attribute are referring to table 2:
Table 2 can be reduced to the member computation attribute of all kinds of plate classes unit
1 grade of member parameterization design method of described aircraft skin wallboard class part, 1 grade of member parametrization statement of aircraft skin wallboard class part also relates to following 3 partial contents: " association knowledge ", " Import Reports ", " explanation "; Wherein:
" association knowledge " is when member calls, and the relevant design knowledge of this member is provided to the user;
" Import Reports " is used for the modeling process of recording member;
" illustrate ": for the geometry location parameter, axle, location, front and back are all curved surfaces, therefore can produce multiple different combination, and specifically referring to table 3, various cross sectional shape also has different combinations.
The combination that the different location of table 3 skinpiston class A of geometric unitA are how much
The application mode of 1 grade of member of aircraft skin wallboard class part is mainly 2 parts:
A) Rapid Establishment product primary design model
By the required member of interactively selection from component base and start member parameter rapid Design module, the designer can carry out the definition of member fast, builds preliminary electronics model machine.
When 1) member calls, use how much benchmark that define in the modeling benchmark, the positional parameter of definition member is completed the sterically defined instantiation of member;
2) utilize member geometric parameter definition interfaces, complete the instantiation definition of member section characteristic parameter.By above two processes, complete the calling and instantiation of member, thereby realize the purpose of Rapid Establishment product primary design model.
B) set up From Math data (non-geometric data definition)
On the basis of member example, the non-geological information of definition member, namely the function of member, attribute of performance, will define result and be saved in (cad model) in the Products Digital model.
The model simplification information definition is the process of gradual perfection, is kept at the basis that all properties in product data has consisted of the unified model data, has not only comprised towards the design data of making, and has comprised the analysis data of Design-Oriented.The unified interconnected system that uses a model is extracted and is processed these data, can set up the required function of each secondary flow journey of airplane design, Performance Analysis model, realizes the linking of the major-minor flow process of airplane design.
The step that 1 grade of member of aircraft skin wallboard class part is mainly used:
A) mode one: (generating the member example)
1) start component base, browse member, selected member
2) in the member instantiation window that ejects and CATIA platform, the geometry location benchmark of interactive selection member
3) definition member section parameter
4) fill in the non-geological information of member, generate the member example after confirming.
B) mode two: (revising the member example)
1) in the CATIA platform, find the digital-to-analogue that is generated by the member instantiation on structure tree
2) double-click this digital-to-analogue, eject and revise window
3) revising window, revise geological information, non-geological information
4) complete the modification of member example after the confirmation.
C) mode three: (setting up the From Math data)
1) in component base (CATIA) system, will be placed in by the digital-to-analogue after the member instantiation work at present state
2) the unified interconnected system that uses a model is extracted geological information and non-geological information in digital-to-analogue
3) utilize the Unified Model interconnected system, generate finite element model.
The present embodiment specifically provides aircraft skin wallboard class part 1 grade of member parameterization design method for the technical matters described in background technology provides a kind of feasible solution.Set up based on this component library system of aircraft, can make the Airplane Digital Product Definition process specification, for the simulation analysis of each secondary flow journey of airplane design and optimization provide function, performance model data bases, between how much model machines of assurance, function model machine/performance prototype, data is harmonious, final designing quality, the purpose of shortening lead time that realizes improving aircraft.
Compared with prior art, the advantage and the effect that have of the present embodiment:
1) the present embodiment helps modular product digital definition process
CAD system provides abundant modelling means for the designer, and same problem can be solved by different approach, and therefore, just there is nonstandard problem in the digital definition of product.Design of digital experience in the past few years shows, the meeting lack of standardization of digital definition process brings following two subject matters:
The firstth, designing a model, it is difficult to understand: what designer set up designs a model, other designers are difficult to understand clear, if need to change model, the designer tends to feel that research knows that model sets up process not as good as again model being set up once; Even the model designer after after a while, wants to review modeling process also very difficult.
Next is to take full advantage of existing experience and resource: design is the accumulation of experience, and the checking that successful design has been experienced test and used can guarantee that design result meets design requirement, and has good technique, manufacturing.If do not use for reference existing Element Design experience, use ripe design result, the reliability of Element Design, the designing quality of part all need again to verify, the manufacturing process of part also needs again to examine, have influence on the utilization of tooling device, certainly will cause the waste that experience and resource have been arranged, be unfavorable for the accumulation of experience, be unfavorable for realizing the rapid Design of product.
By analysis, the conclusion to the current version part form, strictly follow the regulation of modeling standard and set up parametrization, modular member, provide condition for realizing normalized Products Digital definition.The designer chooses member from component base in design process, carry out primary design and the definition of product.When there is no available member in component base, set up the application of new structural member by proposition, after completing the examinations such as design to newly-built member, technique, manufacturing, increase required member in component base.By such regulation, thoroughly the digital definition process of normative model, guarantee designing quality and anufacturability.
2) lay the foundation for the realization of unified model interconnected system
The use component base walks abreast outside Products Digital definite division realization quickening design schedule, Specification Design process, also having an advantage is by comprising in member how much, function, performance data (non-geometric data), utilize the unified model corresponding technology, automatically generate required function, Performance Analysis, the Optimized model of each specialty of aircraft, realize the integrated of major-minor flow process in the airplane digital design cycle.Therefore, component library system is when carrying out design planning, should fully coordinate with the exploitation of unified model interconnected system, demand data etc., in each design phase of main flow, not only complete the instantiation of member, and by the model simplification system, member is simplified, for the unified model interconnected system is extracted how much of members, non-geometric data lays the foundation.
Claims (3)
1. 1 grade of member parameterization design method of aircraft skin wallboard class part, it is characterized in that: with the skinpiston class part in parametrization member statement aircaft configuration, 1 grade of member parametrization statement of aircraft skin wallboard class part is specifically related to following 4 partial contents: " base attribute ", " geometric attribute ", " non-geometric attribute ", " two-dimensional section figure "; Wherein:
" base attribute " specifically comprises: member title, version number, creation-time, component description, manufacturing process, remarks;
" geometric attribute " specifically is divided into positional parameter, cross section parameter two parts, and wherein, positional parameter comprises: external surface, locating surface 1, locating surface 2, locating surface 3, locating surface 4; Cross section parameter is specially the wallboard thickness information;
" non-geometric attribute ": be specifically related to following two parts content: " non-geometric attribute " information of decomposing scheme, corresponding decomposing scheme; Wherein: skinpiston class part does not need to decompose, and is overall plan; " non-geometric attribute " information of corresponding decomposing scheme specifically comprises: the simplified element type that can adopt, computation attribute and the related computing formula of corresponding the type finite element unit;
" two-dimensional section figure ": the physical significance that is used for supplying each parameter of user's correct understanding member when the member instantiation.
2. according to 1 grade of member parameterization design method of the described aircraft skin wallboard of claim 1 class part, it is characterized in that: for 1 grade of member of skinpiston class A of geometric unitA, its simplified element, computation attribute are referring to table 2:
Table 2 can be reduced to the member computation attribute of all kinds of plate classes unit
3. according to 1 grade of member parameterization design method of the described aircraft skin wallboard of claim class part, it is characterized in that: 1 grade of member parametrization statement of aircraft skin wallboard class part also relates to following 3 partial contents: " association knowledge ", " Import Reports ", " explanation "; Wherein:
" association knowledge " is when member calls, and the relevant design knowledge of this member is provided to the user;
" Import Reports " is used for the modeling process of recording member;
" illustrate ": for the geometry location parameter, axle, location, front and back are all curved surfaces, therefore can produce multiple different combination, and various cross sectional shape also has different combinations.
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| CN106372279A (en) * | 2016-08-22 | 2017-02-01 | 中国航空工业集团公司西安飞机设计研究所 | Extruded profile mark screening method |
| CN106326563A (en) * | 2016-08-25 | 2017-01-11 | 武汉理工大学 | Automotive interior and exterior ornament high-efficiency design method |
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