CN101710360B - Optimization design method of skeleton structure of airplane assembly tool - Google Patents

Optimization design method of skeleton structure of airplane assembly tool Download PDF

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CN101710360B
CN101710360B CN2009102544659A CN200910254465A CN101710360B CN 101710360 B CN101710360 B CN 101710360B CN 2009102544659 A CN2009102544659 A CN 2009102544659A CN 200910254465 A CN200910254465 A CN 200910254465A CN 101710360 B CN101710360 B CN 101710360B
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section bar
finite element
design
file
skeleton
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CN101710360A (en
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张卫红
王振培
刘虎
王丹
朱继宏
罗小桃
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Haian Lianke Automobile Parts Co., Ltd.
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Northwestern Polytechnical University
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Abstract

The invention discloses an optimization design method of a skeleton structure of an airplane assembly tool, which is used for the optimization design of a skeleton structure of an airplane assembly tool. The method comprises the following steps of: building a profile specification library file; then building a finite element model of a tool skeleton in MSC.PATRAN; generating a BDF file of the finite element model in finite element software; setting an input parameter of a genetic algorithm; transferring MSC.NASTRAN to analyze the BDF file by adopting the genetic algorithm; generating a new variable sequence according to an analysis result; meanwhile, selecting a corresponding profile in the profile library by utilizing other external programs according the new variable sequence; writing the size information of the profile into the BDF file; and then repeating the steps until optimized calculation ends. Due to the adoption of the genetic algorithm, the method solves the optimization problem of discrete variables, lightens the weight of a tool structure under the condition of meeting the rigidity requirement of the tool, shortens the design period of the skeleton structure of the airplane assembly tool and reduces the production cost.

Description

The Optimization Design of skeleton structure of airplane assembly tool
Technical field
The present invention relates to the Optimization Design of a kind of Optimization Design, particularly skeleton structure of airplane assembly tool.
Background technology
Existing aircraft rigger dress (claiming assembly jig, assembling jig again) is the suitable aircaft configuration that adopts in assembling process of aircraft and the technological equipment of production characteristics, is made up of frock skeleton, keeper, clamping element and other utility appliance usually.The frock skeleton is the matrix of aircraft rigger dress, in order to fixing and other elements such as support keeper, clamping element, keeps the accuracy and the stability thereof of the locus of each element, so must have enough rigidity.In addition, the design production cycle that the design cycle of reduction frock also can be reduced aircraft to a certain extent, thereby the design production cost of reduction aircraft.
The design present situation and the shortcoming of existing aircraft rigger dress skeleton are as follows:
1) designs the skeleton structure heaviness of designing based on conservative design experiences or traditional rigidity calculation formulas.
2) carry out rigidity of structure analysis based on finite element technique, and the sectional dimension of framework local section bar is adjusted, carry out Rigidity Calculation and adjusted size then again, till satisfaction according to analysis result.This method complicated operation, workload is big, and the design cycle is long, design cost is high.
Summary of the invention
In order to overcome prior art skeleton structure of airplane assembly tool heaviness, the design cycle is long, design cost is high deficiency, the invention provides a kind of Optimization Design of skeleton structure of airplane assembly tool, optimize and adopt genetic algorithm, can solve the optimization problem of discrete variable, can realize at short notice the intelligence of existing section bar specification is chosen, finish optimal design work to skeleton structure, under the situation that satisfies the frock rigidity requirement, alleviate the weight of tool structure, shorten the skeleton structure of airplane assembly tool design cycle, reduce production costs.
The technical solution adopted for the present invention to solve the technical problems is: a kind of Optimization Design of skeleton structure of airplane assembly tool is characterized in that comprising the steps:
(a) set up section bar specification library file, comprise all available section bar specifications in this specification storehouse;
(b) in MSC.PATRAN, set up the finite element model of frock skeleton, each section bar is reduced to beam element in the finite element, displacement boundary conditions and load when applying simultaneously frock work in finite element model;
(c) beam element in the skeleton is carried out grouping and classifying, the section bar of locus symmetry, the section bar that the cross section type is consistent with dimensional requirement are divided into one group;
(d) beam element on the same group is set at a design variable, the initial of variable name is as the identification character of differentiating beam type, and in addition, this variable comprises the plurality of sub variable, i.e. the sectional dimension information of beam;
(e) comprehensive displacement of selecting some reference point is as design constraint, with the general assembly (TW) of frock as design object;
(f) the BDF file of generation finite element model in finite element software;
The BDF file is the input file of MSC.NASTRAN, with all finite element model information and the parameters optimization information that this document comprises, submits to MSC.NASTRAN and can carry out analytical calculation;
(g) input parameter---genetic algebra, population scale, mutagenic factor, the intersection factor of setting genetic algorithm, adopting genetic algorithm to call MSC.NASTRAN analyzes the BDF file, generate new variable sequence according to analysis result, utilize other external program in the section bar storehouse, to select corresponding profile simultaneously according to new variable sequence, and the dimension information of section bar write the BDF file, repeat above-mentioned steps to computation optimization then and finish.
The advantage of the relative prior art of the present invention is: owing to adopt genetic algorithm, solved the optimization problem of discrete variable, can realize at short notice the intelligence of existing section bar specification is chosen, finish optimal design work to skeleton structure, under the situation that satisfies the frock rigidity requirement, alleviated the weight of tool structure, shorten the skeleton structure of airplane assembly tool design cycle, reduced production cost.
Among the embodiment 1, under the situation that satisfies the frock rigidity requirement, with respect to prior art, the tool structure that adopts the inventive method to design, weight saving 14.88%.
Among the embodiment 2, under the situation that satisfies the frock rigidity requirement, with respect to prior art, the tool structure that adopts the inventive method to design, weight saving 34.73%.
Below in conjunction with drawings and Examples the present invention is elaborated.
Description of drawings
Fig. 1 is the inventive method embodiment 1 used channel cross-section synoptic diagram.
Fig. 2 is the inventive method embodiment 2 used square steel schematic cross-sections.
Fig. 3 is the load and the constraint conditional definition synoptic diagram of the designed type shelf structure of the inventive method embodiment 2.
Embodiment
Architecture of the present invention mainly comprises three parts: the NASTRAN input file (* .BDF file), genetic algorithm and the section bar specification storehouse that comprise Optimization Model information.The section bar storehouse has determined the interval of variable, genetic algorithm compares by the value condition that the design constraint of each variable is satisfied situation and design object, the obtaining value method of variable is provided,, has finally made variable obtain an optimal results through after the iterative computation of multistep.
Embodiment 1: with reference to Fig. 1.The skeleton of design mode shelf structure is welded by channel-section steel, and the initial designs size of skeleton is: W=55mm, H=126mm, t=5.5mm.Weld keeper on the skeleton, external load mainly is passed to skeleton by keeper, and the displacement situation of keeper positioning end is the standard whether detection architecture rigidity satisfies, and the comprehensive displacement of this each keeper positioning end of frock designing requirement is in 0.35mm.
1) creates section bar specification storehouse.
Channel-section steel commonly used has 30 kinds of specifications approximately, and is as shown in table 1, and these 30 kinds of specification channel-section steel dimensional datas are write section bar specification library file according to ascending order, with each profile size sequence number as its line call-out " specification.The initial configuration size of skeleton (W=55mm, H=126mm, t=5.5mm) No. 6 section bars in the corresponding section bar specification storehouse.
2) set up finite element model.
The type shelf structure is suitably simplified, and set up finite element model.Wherein the skeleton entity is reduced to the beam model of finite element, and keeper is reduced to the cylinder beam, connects reinforcement and ignores.
3) imposed load and boundary condition.
When carrying out the product assembling, the loading direction that is subjected to is the Y-axis negative direction, creates MPC (multi-point constraint) unit between the located in connection part, except that frock self gravitation load, the external load size is respectively: F1=190N, F2=190N, F3=150N, F4a=50N, F4b=50N.Apply boundary condition at the framework two ends, retrain five direction degree of freedom, discharge degree of freedom around the Z rotational axis direction.
Table 1
Figure G2009102544659D00031
4) parameters optimization is set, sets up Optimization Model.
At first according to the form of structure beam is divided into groups, the grouping situation is as shown in table 2.Every group is defined as a beam variable, and corresponding three dimension informations of each variable (W * H * t).The comprehensive displacement on each keeper summit is defined as design constraint, is design object with the weight of beam, sets up Optimization Model, and its mathematic(al) representation is:
find : Var ( i ) = [ W , H , t ] ∈ { C 1 , C 2 , C 3 , . . . , C 30 } i = ( 1,2,3,4,5 ) min : F ( Var ( i ) ) = Min ( Weight ) s . t . Displacement ( j ) ≤ D ( j ) j = ( 1,2 , . . . , 9 )
In the formula
Var (i) (i=(1,2,3,4,5)) is five variablees, and variate-value is the corresponding line call-out " specification of section bar;
The size value of [W, H, t] expression variable;
{ C 1, C 2, C 3..., C 30It is corresponding section bar storehouse;
Displacement (j) means the comprehensive displacement of each keeper positioning end;
D (j) is the design constraint value of each keeper positioning end displacement.
Be optimized when design, with 0.35mm as the design constraint upper limit.
5) adopting genetic algorithm to be optimized finds the solution.
Because the line call-out " specification of section bar is an integer, so the Var in the model (i) is adopted binary coding.The population scale of model is set at 60, and genetic algebra was set at for 50 generations, and mutagenic factor is made as 0.06, and the factor of intersecting is made as 0.9, submits to genetic algorithm to be optimized, and the optimization result who obtains each set of variables is as shown in table 3.
Can see by the result, except that the section bar of the 3rd group of variable number become big, the section bar of all the other groups number all diminishes.
Table 2
Figure G2009102544659D00041
Weight before and after optimizing and steady arm maximum displacement contrast are as shown in table 4, with respect to the structural design under the traditional design mode, after the optimization, the weight saving of this structure 14.88%.
Table 3
Figure G2009102544659D00042
Table 4
Figure G2009102544659D00043
Embodiment 2: with reference to Fig. 2.The skeleton of design mode shelf structure is welded by square steel, and the initial designs size of each section bar of skeleton sees Table 7, is: W=160mm, H=160mm, t=8mm; W=120mm, H=120mm, t=8mm.The comprehensive displacement of this each stress point of frock designing requirement is in 0.3mm.
1) creates section bar specification storehouse.
Square steel commonly used has 29 kinds of specifications approximately, and is as shown in table 5, and these 29 kinds of size square steel dimensional datas are write section bar specification library file according to ascending order, with each profile size sequence number as its line call-out " specification.The corresponding situation of the initial configuration size of used each section bar of skeleton and section bar specification storehouse medium section number sees Table 7.
2) set up finite element model.
The type shelf structure is suitably simplified, and set up finite element model, the skeleton entity is reduced to the beam model of finite element.
3) imposed load and boundary condition
Carry out product when assembling, the loading direction that is subjected to is for straight down, the load mode of outside centre-point load as shown in Figure 3, magnitude of load is respectively: F1=5500N, F2=3200N.Apply boundary condition at the D of skeleton point, E point, F point and G point, retrain 1,2,3 three direction degree of freedom.
Table 5
Figure G2009102544659D00051
Table 6
Figure G2009102544659D00052
4) parameters optimization is set, sets up Optimization Model.
At first according to the form of structure beam is divided into groups, the grouping situation is as shown in table 6.Every group is defined as a beam variable, and corresponding three dimension informations of each variable (W * H * t).The comprehensive displacement of each stress point is defined as design constraint, is design object with the weight of beam, sets up Optimization Model, and its mathematic(al) representation is:
find : Var ( i ) = [ W , H , t ] ∈ { C 1 , C 2 , C 3 , . . . , C 29 } i = ( 1,2,3,4,5 ) min : F ( Var ( i ) ) = Min ( Weight ) s . t . Displacement ( j ) ≤ D ( j ) j = ( 1,2 , 3 )
In the formula
Var (i) (i=(1,2,3,4,5)) is five variablees, and variate-value is the corresponding line call-out " specification of section bar;
The size value of [W, H, t] expression variable;
{ C 1, C 2, C 3..., C 29It is corresponding section bar storehouse;
Displacement (j) means the comprehensive displacement of each stress point;
D (j) is the design constraint value of each stress point displacement.
Be optimized when design, with 0.30mm as the design constraint upper limit.
5) adopting genetic algorithm to be optimized finds the solution.
Because the line call-out " specification of section bar is an integer, so the Var in the model (i) is adopted binary coding.The population scale of model is set at 60, and genetic algebra was set at for 50 generations, and mutagenic factor is made as 0.06, and the factor of intersecting is made as 0.9, submits to genetic algorithm to be optimized, and the optimization result who obtains each set of variables is as shown in table 7.
Can see by table 8, except that the section bar of first group of variable number become big, the section bar of all the other groups number all diminishes.
Weight before and after optimizing and stress point maximum displacement contrast are as shown in table 8, with respect to the structural design under the traditional design mode, after the optimization, the weight saving of this structure 34.73%.
Table 7
Figure G2009102544659D00062
Table 8
Above embodiment shows, is satisfying under the situation of rigidity requirement, and the inventive method has realized the light-weight design of tool structure, makes structure lighter, and material is more economized, and has shortened the skeleton structure of airplane assembly tool design cycle, has reduced production cost.

Claims (1)

1. the Optimization Design of a skeleton structure of airplane assembly tool is characterized in that may further comprise the steps:
(a) set up section bar specification library file, comprise all available section bar specifications in this specification storehouse;
(b) in MSC.PATRAN, set up the finite element model of frock skeleton, each section bar is reduced to beam element in the finite element, displacement boundary conditions and load when applying simultaneously frock work in finite element model;
(c) beam element in the skeleton is carried out grouping and classifying, the section bar of locus symmetry, the section bar that the cross section type is consistent with dimensional requirement are divided into one group;
(d) beam element on the same group is set at a design variable, the initial of variable name is as the identification character of differentiating beam type, and in addition, this variable comprises the plurality of sub variable, i.e. the sectional dimension information of beam;
(e) comprehensive displacement of selecting some reference point is as design constraint, with the general assembly (TW) of frock as design object;
(f) the BDF file of generation finite element model in finite element software;
The BDF file is the input file of MSC.NASTRAN, with all finite element model information and the parameters optimization information that this document comprises, submits to MSC.NASTRAN and can carry out analytical calculation;
(g) input parameter---genetic algebra, population scale, mutagenic factor, the intersection factor of setting genetic algorithm, adopting genetic algorithm to call MSC.NASTRAN analyzes the BDF file, generate new variable sequence according to analysis result, utilize other external program in the section bar storehouse, to select corresponding profile simultaneously according to new variable sequence, and the dimension information of section bar write the BDF file, repeating step (a)～(g) to computation optimization finishes then.
CN2009102544659A 2009-12-23 2009-12-23 Optimization design method of skeleton structure of airplane assembly tool Expired - Fee Related CN101710360B (en)

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CN103020368B (en) * 2012-12-20 2015-09-09 唐山轨道客车有限责任公司 Row head optimized design method
CN103383752A (en) * 2013-07-15 2013-11-06 上海飞机制造有限公司 Assembly scheduling method of aircraft
CN103984803B (en) * 2014-04-17 2017-02-15 中国航空工业集团公司沈阳飞机设计研究所 Finite element load application method
CN106599345B (en) * 2016-10-26 2020-08-18 北京数设科技有限公司 Airplane structure section bar identification method and device
CN108509748B (en) * 2018-04-17 2022-05-03 江西洪都商用飞机股份有限公司 Rapid design method for inner template of airplane assembly fixture
CN111098995B (en) * 2019-12-25 2021-10-08 中国船舶工业集团公司第七0八研究所 Size optimization system for middle cross section structure of oil tanker and bulk carrier
CN113408040B (en) * 2021-07-16 2022-06-17 中南大学 Analog data correction method and system in civil engineering

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