CN102999677A - First-level construction member parametrization design method for airplane frame-type parts - Google Patents
First-level construction member parametrization design method for airplane frame-type parts Download PDFInfo
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Abstract
A first-level construction member parametrization design method for airplane frame-type parts comprises that the frame-type parts in an airplane structure is described by parametrization construction members. First-level construction member parametrization description of the airplane frame-type parts particularly relates to contents as the following four parts: (1) essential attributes comprise construction member names, version numbers, creating time, construction member description, manufacture technology and remarks; (2) geometric attributes comprise location parameters and section parameter; (3) non-geometric attributes particularly relate to decomposion schemes and non-geometric attribute information; and (4) a two-dimensional sectional view is used for enabling a user to correctly understand physical significances of each parameter of the construction member when construction member instantiation is carried out. The first-level construction member parametrization design method contributes to building a component base system of an airplane, provides function and performance model data basis for airplane design standardization, simulated analysis and optimizing, guarantees consistency of data between a geometric model machine a d a functional model machine/performance model machine, improves design quality of the airplane, and shortens development period.
Description
Technical field:
The present invention relates to the aeroplane structure design technical field, provide especially a kind of Airplane frame class part 1 grade of member parameterization design method.
Background technology:
In the 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 finish product three-dimensional entity model parameter problem identificatioin before---design.If cad technique can not participate in the definite of product parameters, the application of cad technique in design only is 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 realization 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 Airplane frame class part is based on the important component part in the aeroplane structure design of parametrization member, and therefore, people expect to obtain 1 grade of member parameterization design method of a kind of Airplane frame class part.
Summary of the invention:
The objective of the invention is is providing a kind of 1 grade of member parameterization design method of Airplane frame 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 the 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 the member; Described parametrization member carries out induction-arrangement to parts commonly used in the 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 the 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 gradually process of maturation of Products Digital definition, are mainly used in the designer to understanding and the study of design process, can on the basis of member example it be made amendment simultaneously, are used for satisfying the requirement of new design objective.The knowledge relevant with 2-4 level member is abundanter, and integrated engineering design tool commonly used, helps the designer to carry out preliminary design analysis.
For 1 grade of member, also satisfy following requirement:
" 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 finishing member under the software environments such as CATIA, parameter-definition, then can be according to the example that the definition of structure attribute and parameter is generated a member, namely Products Digital defines the result and places under the general management of PDM;
" attribute of member " comprises how much and non-geometric attribute; Wherein: geometric attribute all is 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 such as external form curved surface, member plane of orientation etc., another kind of is the cross sectional shape parameter of member, such 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 the component base does not have corresponding attribute definition, then after this member instantiation, member is simplified module with this example of None-identified; If during a certain member entity in the deletion component base spare, the attribute definition that then this member is corresponding should together be deleted.
Based on the application of the aeroplane structure design method of parametrization member, it at first is 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 finished the sterically defined instantiation of member; Utilize member geometric parameter definition interfaces, finish the instantiation definition of member section characteristic parameter.By above two processes, finish 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 the 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 the 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, then 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 the 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 is proposed is carried out clear and definite and is specialized, and finally provides 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 the 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 as much as possible coordinate design; The basis of all having determined in parts basic size provides the detailed decomposition base of weight indicator, but not yet carries 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 the analysis of optimizing design, member is integrated/be divided into some subassembly/parts, determine annexation between the structure, production breakdown interface, initial breakdown interface, carry out preliminary reconciling spatial scale design; Specifically comprise following design content:
Connect concrete form design (be horizontal open joint/auricle be connected with certain intersection point fuselage between such as clear and definite wing) between the large parts; In length and breadth frame member segmentation (, rib segmentation continuous such as beam; Not yet carry out in length and breadth the design of concrete type of attachment between the frame member, such as the joint that not have in length and breadth connection between the frame member, angle box, gusset plate etc.); Determine that single member segments form, position are (such as vertical wall internal and external section docking, fit; Frame member not yet carries out detailed design, such as frame etc. edge strip and web is only arranged, the rib in the middle of not having); Coordination location (moving down applying covering inside surface such as the beam edge strip) between the 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 does not have the reinforcement designs such as flange).
In the 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, finish 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 the 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, finish each function system and structure, structure and interstructural final connection interface design, it specifically comprises following content request: the annexation design between the member (adds angle box, gusset plate etc. such as beam, rib connection; Key position securing member connecting portion design is such 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 the system (structure is that the system pass perforate is determined).
In the 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, the design of technological datum hole.
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; Typical structural elements can be summarized as 11 classes in the aircraft: 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 Airplane frame class part: with the frame class part in the parametrization member statement aircaft configuration, 1 grade of member parametrization statement of Airplane frame 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: frame plane, upper surface, lower surface, interior profile 1, interior profile 2, interface 1, interface 2; Cross section parameter be specially the length, width in cross section, highly, thickness information;
" non-geometric attribute " is specifically related to again following two parts content: " non-geometric attribute " information of decomposing scheme, corresponding decomposing scheme; Wherein: decomposing scheme is carrying out need to resolving into several parts when finite element is simplified in order to explain this member; " non-geometric attribute " information of corresponding decomposing scheme satisfies following requirement: corresponding decomposing scheme, describe each in detail and decompose all " non-geometric attribute " information that part need to comprise when simplifying processing, be specifically related to following content: the simplified element type that this decomposition part can adopt, the computation attribute of corresponding the type finite element unit and related computing formula;
" two-dimensional section figure ": the physical significance that is used for when the member instantiation, supplying each parameter of user's correct understanding member.
1 grade of member parameterization design method of described Airplane frame class part is characterized in that: for L-type combo box class A of geometric unitA, the cross section parameter in its " geometric attribute " specifically comprises following content of parameter (referring to table 1):
L: architrave bar width, t1: architrave bar thickness, t2: frame web thickness.
Table 1 cross section parameter is described
1 grade of member parameterization design method of described Airplane frame class part, it is characterized in that: be the combination beam wall class A of geometric unitA of T shape extrudate for edge strip up and down, the decomposing scheme in its " non-geometric attribute " is that it is decomposed into upper architrave, lower architrave, left inside architrave, right inside architrave and frame web five parts; Wherein:
For upper architrave, lower architrave, left inside architrave, right inside architrave, its simplified element, computation attribute and incidence formula are referring to table 2:
Table 2 can be reduced to member computation attribute and the incidence formula of bar, beam class unit
For lower edge strip, its simplified element is identical with upper edge strip with computation attribute, and difference only is that the concrete value of the parameter of incidence formula is different;
For the frame web, but simplified element and computation attribute see Table 3:
Table 3 can be reduced to member computation attribute and the incidence formula of all kinds of plate classes unit
All kinds of simplified elements in the table 3 and computation attribute thereof are corresponding respectively, jointly consist of " non-geometric attribute " content of frame web.
1 grade of member parameterization design method of described Airplane frame class part is characterized in that: 1 grade of member parametrization statement of Airplane frame 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 all are curved surfaces, therefore can produce multiple different combination, and specifically referring to table 4, various cross sectional shape also has different combinations.
The combination that the different location of table 4 frame class A of geometric unitA are how much
The present invention specifically provides Airplane frame class part 1 grade of member parameterization design method for the technical matters described in the 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 basis, data is harmonious between how much model machines of assurance, function model machine/performance prototype, 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 that 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 is after after a while, and it is also very difficult to want to review modeling process.
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 not having available member in the component base, by the application that proposes to set up new structural member, after finishing the examinations such as design to newly-built member, technique, manufacturing, in component base, increase required member.By such regulation, thoroughly the digital definition process of normative model guarantees 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, the Specification Design process, also having an advantage is by comprising in the 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, major-minor flow process is integrated in the realization 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 finish 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 frame class A of geometric unitA positional parameter principle schematic;
Fig. 2 is L-type architrave member section synoptic diagram.
Embodiment:
Embodiment 1
A kind of 1 grade of member parameterization design method of Airplane frame class part that in the aeroplane structure design method based on the parametrization member, uses.
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 the instructions.
The emphasis of present embodiment relates to 1 grade of member parameterization design method of a kind of Airplane frame class part: with the frame class part in the parametrization member statement aircaft configuration, 1 grade of member parametrization statement of Airplane frame 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: frame plane, upper surface, lower surface, interior profile 1, interior profile 2, interface 1, interface 2; Cross section parameter be specially the length, width in cross section, highly, thickness information;
" non-geometric attribute " is specifically related to again following two parts content: " non-geometric attribute " information of decomposing scheme, corresponding decomposing scheme; Wherein: decomposing scheme is carrying out need to resolving into several parts when finite element is simplified in order to explain this member; " non-geometric attribute " information of corresponding decomposing scheme satisfies following requirement: corresponding decomposing scheme, describe each in detail and decompose all " non-geometric attribute " information that part need to comprise when simplifying processing, be specifically related to following content: the simplified element type that this decomposition part can adopt, the computation attribute of corresponding the type finite element unit and related computing formula;
" two-dimensional section figure ": the physical significance that is used for when the member instantiation, supplying each parameter of user's correct understanding member.
1 grade of member parameterization design method of described Airplane frame class part, for L-type combo box class A of geometric unitA, the cross section parameter in its " geometric attribute " specifically comprises following content of parameter (referring to table 1):
L: architrave bar width, t1: architrave bar thickness, t2: frame web thickness.
Table 1 cross section parameter is described
1 grade of member parameterization design method of described Airplane frame class part, be the combination beam wall class A of geometric unitA of T shape extrudate for edge strip up and down, the decomposing scheme in its " non-geometric attribute " is that it is decomposed into upper architrave, lower architrave, left inside architrave, right inside architrave and frame web five parts; Wherein:
For upper architrave, lower architrave, left inside architrave, right inside architrave, its simplified element, computation attribute and incidence formula are referring to table 2:
Table 2 is reduced to member computation attribute and the incidence formula of bar, beam class unit
For lower edge strip, its simplified element is identical with upper edge strip with computation attribute, and difference only is that the concrete value of the parameter of incidence formula is different;
For the frame web, but simplified element and computation attribute see Table 3:
Table 3 can be reduced to member computation attribute and the incidence formula of all kinds of plate classes unit
All kinds of simplified elements in the table 3 and computation attribute thereof are corresponding respectively, jointly consist of " non-geometric attribute " content of frame web.
1 grade of member parameterization design method of described Airplane frame class part, 1 grade of member parametrization statement of Airplane frame 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 all are curved surfaces, therefore can produce multiple different combination, and specifically referring to table 4, various cross sectional shape also has different combinations.
The combination that the different location of table 4 frame class A of geometric unitA are how much
Present embodiment specifically provides Airplane frame class part 1 grade of member parametrization expression method and application mode for the technical matters described in the 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 basis, data is harmonious between how much model machines of assurance, function model machine/performance prototype, final designing quality, the purpose of shortening lead time that realizes improving aircraft.
The application mode of 1 grade of member of the described Airplane frame class of present embodiment part mainly is 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 finished the sterically defined instantiation of member;
2) utilize member geometric parameter definition interfaces, finish the instantiation definition of member section characteristic parameter.By above two processes, finish 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 the 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 the 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, then 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 Airplane frame class part is mainly used:
A) mode one: (generating the member example)
1) starts 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, finds the digital-to-analogue that is generated by the member instantiation on the structure tree
2) double-click this digital-to-analogue, eject and revise window
3) revising window, revise geological information, non-geological information
4) finish the modification of member example after confirming.
C) mode three: (setting up the From Math data)
1) in component base (CATIA) system, will be placed 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 the digital-to-analogue
3) utilize the Unified Model interconnected system, generate finite element model.
Compared with prior art, the advantage and the effect that have of present embodiment:
1) 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 that 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 is after after a while, and it is also very difficult to want to review modeling process.
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 not having available member in the component base, by the application that proposes to set up new structural member, after finishing the examinations such as design to newly-built member, technique, manufacturing, in component base, increase required member.By such regulation, thoroughly the digital definition process of normative model guarantees 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, the Specification Design process, also having an advantage is by comprising in the 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, major-minor flow process is integrated in the realization 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 finish 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 (4)
1. 1 grade of member parameterization design method of Airplane frame class part, it is characterized in that: with the frame class part in the parametrization member statement aircaft configuration, 1 grade of member parametrization statement of Airplane frame 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: frame plane, upper surface, lower surface, interior profile 1, interior profile 2, interface 1, interface 2; Cross section parameter be specially the length, width in cross section, highly, thickness information;
" non-geometric attribute " is specifically related to again following two parts content: " non-geometric attribute " information of decomposing scheme, corresponding decomposing scheme; Wherein: decomposing scheme is carrying out need to resolving into several parts when finite element is simplified in order to explain this member; " non-geometric attribute " information of corresponding decomposing scheme satisfies following requirement: corresponding decomposing scheme, describe each in detail and decompose all " non-geometric attribute " information that part need to comprise when simplifying processing, be specifically related to following content: the simplified element type that this decomposition part can adopt, the computation attribute of corresponding the type finite element unit and related computing formula;
" two-dimensional section figure ": the physical significance that is used for when the member instantiation, supplying each parameter of user's correct understanding member.
2. according to 1 grade of member parameterization design method of the described Airplane frame class of claim 1 part, it is characterized in that: for L-type combo box class A of geometric unitA, the cross section parameter in its " geometric attribute " specifically comprises following content of parameter:
L: architrave bar width, t1: architrave bar thickness, t2: frame web thickness.
3. according to 1 grade of member parameterization design method of the described Airplane frame class of claim 1 part, it is characterized in that: be the combination beam wall class A of geometric unitA of T shape extrudate for edge strip up and down, the decomposing scheme in its " non-geometric attribute " is that it is decomposed into upper architrave, lower architrave, left inside architrave, right inside architrave and frame web five parts; Wherein:
For upper architrave, lower architrave, left inside architrave, right inside architrave, its simplified element, computation attribute and incidence formula are referring to table 2:
Table 2 can be reduced to member computation attribute and the incidence formula of bar, beam class unit
For lower edge strip, its simplified element is identical with upper edge strip with computation attribute, and difference only is that the concrete value of the parameter of incidence formula is different;
For the frame web, but simplified element and computation attribute see Table 3:
Table 3 can be reduced to member computation attribute and the incidence formula of all kinds of plate classes unit
All kinds of simplified elements in the table 3 and computation attribute thereof are corresponding respectively, jointly consist of " non-geometric attribute " content of frame web.
4. according to 1 grade of member parameterization design method of one of them described Airplane frame class part of claim 1-3, it is characterized in that: 1 grade of member parametrization statement of Airplane frame 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 all are curved surfaces.
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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 |
| CN105488623A (en) * | 2015-11-26 | 2016-04-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft quality feature data processing method |
| CN105488623B (en) * | 2015-11-26 | 2019-09-24 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of Aircraft Quality performance data processing method |
| CN106326563A (en) * | 2016-08-25 | 2017-01-11 | 武汉理工大学 | Automotive interior and exterior ornament high-efficiency design method |
| CN111859571A (en) * | 2020-07-21 | 2020-10-30 | 齐鲁工业大学 | Stacking machine safety evaluation method and system based on parametric design |
| CN111859571B (en) * | 2020-07-21 | 2024-02-20 | 齐鲁工业大学 | Stacker safety evaluation method and system based on parameterized design |
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