CN103870613A - Calculation method of bearing capacity of reinforced wall plate - Google Patents
Calculation method of bearing capacity of reinforced wall plate Download PDFInfo
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- CN103870613A CN103870613A CN201210528288.0A CN201210528288A CN103870613A CN 103870613 A CN103870613 A CN 103870613A CN 201210528288 A CN201210528288 A CN 201210528288A CN 103870613 A CN103870613 A CN 103870613A
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Abstract
The invention provides a calculation method of the bearing capacity of a reinforced wall plate and belongs to the field of strength analysis of aircraft structures. According to the technical scheme, the calculation method is an axial compression loading action based calculation method of the effective width of buckling of a skin. Stiffness reduction is performed through modification of the cross section area and the moment of inertia of a stringer in a finite element model which is formed by plate beam units after the buckling of the skin is produced, stress analysis of a structure is performed by a linear iteration solution method of load loading steps, comparison is performed on the working stress of the stringer in a calculation result and the allowable limiting stress of a stringer and skin combined structure, the allowable limiting stress serves as a damage standard and is solved based on an engineering method, and accordingly the bearing capacity of the structure is obtained. Compared with the traditional full housing model, a calculation method model is a plate beam unit model, the geometric nonlinearity and contact problem solution which is large in time consumption and difficult to converge is replaced by the linear solution, and accordingly the modeling time consumption is small, the calculation speed is high, and the requirements for the professional quality of the computer hardware and analysis staff are low.
Description
Technical field
A kind of Material Stiffened Panel load-bearing capacity of the present invention computing method belong to aeronautic structure intensive analysis field.
Background technology
Document [A numerical assessment of the buckling/ultimate strength characteristicsof stiffened aluminium plates with fixed/floating transverse frames[J] .Thin-Walled Structures, 2009,47:1373 – 1386.] more typically represent the method for current calculating Material Stiffened Panel post-buckling.The method is calculated by setting up finite element model method.Specific practice is:
1) carry out model construction in conjunction with Material Stiffened Panel structure composition and geometric properties.Covering and rib adopt plate shell unit (Shellelement) simulation, and web member adopts spring element (Spring element) simulation;
2) each part material mechanical property and load boundary condition are according to applying with batch material mechanical performance test figure and concrete load condition;
3) determine the initial disturbance (Initial imperfections) of Post-Buckling Analysis according to Material Stiffened Panel structure linear buckling mode (linear buckling mode);
4) carry out the Post-Buckling Analysis of Material Stiffened Panel based on nonlinear iteration solution technique, and then definite load-bearing capacity.
But make to exist in this way following shortcoming:
1) owing to will carrying out Post-Buckling Analysis, Material Stiffened Panel need to be created as the details finite element model that can reflect details position stiffness variation, and modeling workload is large, and easily makes mistakes;
2) in Material Stiffened Panel model construction web member performance parameter choose with practical set process in performance difference very large, affected the credibility of result of calculation;
3) finite element model of setting up according to the method, need to consider geometrical non-linearity simultaneously and the nonlinear problem such as contact, and causes numerical convergence difficulty, calculates and is difficult for successfully.
Summary of the invention
The object of this invention is to provide and a kind ofly can truly reflect that rigidity of structure Changing Pattern in loading procedure, modeling are convenient, the fast metal Material Stiffened Panel post-buckling computing method of computing velocity.
Technical scheme of the present invention, a kind of Material Stiffened Panel load-bearing capacity computing method, comprise the following steps 1: set up finite element model according to Material Stiffened Panel structure;
Step 2: the finite element numerical of buckling structure solves, utilizes in step 1 finite element model to carry out buckling structure in conjunction with imposed load and solves;
Step 3: determine post-buckling initial disturbance according to buckling structure mode, carry out the Post-Buckling Analysis of Material Stiffened Panel based on nonlinear iteration solution technique, and then definite load-bearing capacity;
It is characterized in that,
In step 2, during the finite element numerical of buckling structure solves, be that the engineering method of utilization based on test figure is to the buckling stress of covering and solving that the ultimate stress allowable of long purlin covering unitized construction is carried out;
In finite element analysis, in conjunction with current load condition, structure is carried out calculating based on the Stiffness degradation of effective width method, and utilize the area of section of long purlin and the mode of moment of inertia modification to carry out rigidity reduction;
Introduce the analytical model after stiffness reduction by calculating, until when in calculating by substep load applying, arbitrarily the working stress of long purlin reaches the ultimate stress allowable that the above-mentioned long purlin covering calculating combines, it is critical that structure has reached destruction, adds up current load step and be Material Stiffened Panel load-bearing capacity.
Beneficial effect of the present invention, utilize the engineering method based on test figure to carry out the calculating of the ultimate stress of covering buckling stress and covering rib unitized construction, replace traditional computation process of utilizing plate shell details finite element model, can pass through programming direct solution, convenient and swift.And because this finite element model is the simple global finite element model that only comprises plate beam element, than the complicated details finite element model of traditional full plate shell unit, model construction is consuming time few, and less dependency analysis personnel engineering structure modeling experience, is not easy to make mistakes.In calculating, it is all on the basis of finite element model connecting at large-scale complex that traditional Material Stiffened Panel load-bearing capacity solves, consider that geometrical non-linearity, material nonlinearity and the post-buckling of nonlinear problems such as contacting solve, numerical convergence difficulty, calculate and be difficult for successfully, and successfully solve the Specialized Quality and the experience that depend on to a great extent engineering analysis personnel; And utilization in this method on a small scale the linear iteration of the limited number of times of naive model solve and replaced traditional extensive, non-linear solving, calculate small scale, consuming time few, easily convergence, and low to computer hardware and the requirement of analyst's Specialized Quality, greatly accelerate the design analysis process of reinforced structure.
Accompanying drawing explanation
Fig. 1 is the calculation flow chart of the inventive method.
Embodiment
Inventive principle:
In the reinforced structure that is subject to axial compression is analyzed, for the Material Stiffened Panel that bears longitudinal compression, when after the covering flexing between muscle, it also has certain continuation load-bearing capacity, be converted into the lath with certain width and invest contiguous rib, and carry together with rib until wallboard total failure, this analytical approach is exactly effective width method, the concept of effective width method is applied to finite element analysis, has just formed the stiffness reduction method based on effective width in Material Stiffened Panel load-bearing capacity analysis.Adopt the simulation of plate shell unit at covering, rib adopts in the holistic approach model of beam unit simulation, apply given substep load, calculate covering stress and long purlin stress by linearity, after each calculating, read the working stress of every covering and the buckling stress of covering compares, and carry out the calculating of covering effective width to there is flexing covering, and before next load step is analyzed, remove accordingly the covering of this piece flexing, area of section and the moment of inertia of revising corresponding long purlin complete the reduction of one-piece construction rigidity.To utilize the engineering method based on test figure to calculate as the ultimate stress of the long purlin covering unitized construction of structural failure criterion.Then for the global finite element model after rigidity reduction, utilize linear iteration method for solving to carry out the stress analysis of Material Stiffened Panel, along with the increase of load, flexing covering is more and more, the long purlin quantity of revising cross section face attribute is also more, until when in result of calculation, arbitrarily the working stress of long purlin reaches the ultimate stress of long purlin covering unitized construction, structure reached destroy critical, the load-bearing capacity of adding up current load step and be Material Stiffened Panel.
Describe the present invention below in conjunction with Fig. 1:
Step 1: the finite element model of structure is set up
Carry out the structure of holistic approach model in conjunction with Material Stiffened Panel structure composition and geometric properties.Wherein covering adopts plate shell unit (Shell element) simulation, and rib adopts beam unit (Beam element) simulation, and web member is not considered;
Step 2: the ultimate stress allowable of the buckling stress of covering and the covering combination of long purlin
Calculation procedure based on program language programming carries out the calculating of the buckling stress of covering and the ultimate stress allowable of long purlin covering combination.Wherein the buckling stress of covering adopts Euler (Eular) formula based on test figure to solve, and long purlin covering unitized construction ultimate stress allowable adopts " plate unit method " to solve;
Step 3: apply given substep load, carry out the judgement of covering flexing in conjunction with result of calculation
Utilize the finite element model of setting up, apply given substep load based on program, calculate covering stress and long purlin stress by linearity.The load wherein applying from gross load 1%, load increment step is 1%, reads the working stress of every covering and the buckling stress of covering compares after having calculated at every turn, judge whether covering occurs, proceed to step 4 if there is flexing, otherwise increase load step, repeat solving of this step;
Step 4: rigidity of model reduction
First carry out the calculating of covering effective width to there is flexing covering, then in model by corresponding covering element deletion, according to the effective width of the flexing covering calculating, the covering of effective width size is amounted to area of section and the moment of inertia growing on purlin in the both sides adjacent with covering and calculate this unitized construction, carried out rigidity reduction by area of section and the moment of inertia of revising long purlin;
Step 5: structural failure judgement and load-bearing capacity are determined
Calculate for the analytical model of introducing after stiffness reduction, apply given substep load, the integrated stress that carries out reinforced structure solves, and reads the working stress of each long purlin in analysis result, and compares with the ultimate stress of the long purlin covering unitized construction as structural failure criterion.If a certain long purlin working stress reaches criterion, represent that structure is critical in destroying, the distributed load now applying is the load-bearing capacity of structure, if arbitrary long purlin working stress does not all reach criterion, the covering stress in repeating step 3, step 4 solves, flexing judges, effective width is calculated and rigidity of model reduction, and then model stress in carry out step 5 solves, long purlin working stress reads with structural failure and judges, until a certain long purlin is critical in destroying in structure, and then obtain the load-bearing capacity of structure.
In specific embodiment, the workbench that calculates place is MSC.PATRAN and MSC.NASTRAN, and step is as follows:
(1) in conjunction with reinforced structure composition and geometric properties, according to aeronautic structure integrated stress method for analyzing and modeling, covering is adopted the simulation of plate shell unit, rib to adopt the simulation of beam unit and do not consider that web member sets up the holistic approach model of structure, wherein carry out as basis take each parts theoretical diagram grid division aspect, and it is area of section and moment of inertia that geometric attribute should be given respectively in unit, each long purlin;
(2) according to the concrete physical dimension of structure and material behavior, utilize Euler's formula to carry out the solving of buckling stress of covering, utilize " plate unit method " to grow the solving of ultimate stress allowable of purlin and effective width covering unitized construction, simultaneously the position annexation between given covering and long purlin is connected the element number of two long purlins (as 10 100 11 with certain piece covering, the wherein element number of 100 expression coverings, 10 representatives see from covering outside surface direction the left long purlin element number being connected with covering, and 11 represent the right long purlin element number being connected with covering);
(3) apply given substep load, revise structural finite element model file * .bdf.i(as model.bdf.1) middle load value, then calling NASTRAN carries out structure and solves, destination file * .f06.i(by reading current generation is as model.f06.1) obtain the working stress of all coverings, retain this step * .bdf.i, * .f06.i, * .xdb.i file (as model.bdf.1, model.f06.1, model.xdb.1).If total outer F that carries, loading step when complete Reality simulation physical test loads, and is undertaken: 0.05F, 0.10F, 0.15F, 0.20F, 0.25F by following loading step, 0.30F, 0.35F, 0.40F, 0.45F, 0.50F, 0.55F, 0.60F, 0.65F, 0.67F, 0.70F, 0.72F, 0.74F, 0.76F, 0.78F, 0.80F, 0.82F, 0.84F, 0.86F, 0.88F, 0.90F, 0.91F, 0.92F, 0.93F, 0.94F, 0.95F, 0.96F, 0.97F, 0.98F, 0.99F, 1.0F, 1.01F ..., until destroy;
(4) by comparing the corresponding covering buckling stress calculating in covering working stress and step (2), judge whether covering flexing occurs, if there is no covering generation flexing, carry out next step loading, jumping into the 3rd step solves, if there is covering generation flexing, enter step (5);
(5) effective width of carrying out flexing covering according to various effective width computing formula common in aeronautic structure intensity solves, here the formula that adopts Bruhn to recommend in the Analysis and Design of Flight Vehicle Structures report of 1973 calculates, calculate again area of section and the moment of inertia of closing on the unitized construction of long purlin and effective width covering formation with flexing covering, then in the model file * .bdf.i generating in step (3), carry out the rigidity reduction of model by removing flexing covering unit and modification with corresponding area of section and the moment of inertia (as carried out the area of corresponding long purlin cell attribute definition line and the modification of moment of inertia parameter in * .bdf.i file) of the connected spreading of flexing covering purlin, calling NASTRAN carries out structure and solves, obtain long purlin stress by reading the destination file * .f06.i of current step generation, retain
(6) working stress of each long purlin in the middle analysis result * .f06.i of read step (5), and compare with the ultimate stress of the long purlin covering unitized construction as structural failure criterion.If a certain long purlin working stress reaches criterion, represent that the distributed load now applying is the load-bearing capacity of structure, if arbitrary long purlin working stress does not all reach criterion, the covering stress in repeating step (3), step (4) solves with flexing and judges, and then carry out that effective width in step (5) solves, rigidity of model reduction, model stress solve, long purlin working stress reads with structural failure and judges, until a certain long purlin is critical in destroying in structure, and then obtain the load-bearing capacity of structure;
(7) add up current load step (as 0.86F), known current load step 0.86F is the load-bearing capacity of structure.
Claims (1)
1. Material Stiffened Panel load-bearing capacity computing method,
Comprise the following steps 1: set up finite element model according to Material Stiffened Panel structure;
Step 2: the finite element numerical of buckling structure solves, utilizes in step 1 finite element model to carry out buckling structure in conjunction with imposed load and solves;
Step 3: determine post-buckling initial disturbance according to buckling structure mode, carry out the Post-Buckling Analysis of Material Stiffened Panel based on nonlinear iteration solution technique, and then definite load-bearing capacity;
It is characterized in that,
In step 2, in the numerical solution of buckling structure, be that the engineering method of utilization based on test figure is to the buckling stress of covering and solving that the ultimate stress allowable of long purlin covering unitized construction is carried out;
In finite element analysis, in conjunction with current load condition, structure is carried out calculating based on the Stiffness degradation of effective width method, and utilize the long area of section of purlin of modification and the mode of moment of inertia to carry out rigidity reduction;
Introduce the analytical model after stiffness reduction by calculating, until when in calculating by substep load applying, arbitrarily the working stress of long purlin reaches the ultimate stress allowable that the above-mentioned long purlin covering calculating combines, it is critical that structure has reached destruction, adds up current load step and be Material Stiffened Panel load-bearing capacity.
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| CN104330253A (en) * | 2014-11-28 | 2015-02-04 | 中航沈飞民用飞机有限责任公司 | Method applied to analysis of damage tolerance feature of stiffened wall panel |
| CN104484531A (en) * | 2014-12-18 | 2015-04-01 | 大连理工大学 | Stiffened plate shell structure reliability optimization method with multisource uncertainty being considered |
| CN105302994A (en) * | 2015-11-22 | 2016-02-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Finite element simulation method of beam_plate shell structure |
| CN105844033A (en) * | 2016-03-30 | 2016-08-10 | 中国舰船研究设计中心 | Simplified progressive failure analysis method for ultimate longitudinal strength of ship |
| CN106156449A (en) * | 2016-08-31 | 2016-11-23 | 中航沈飞民用飞机有限责任公司 | A kind of composite wing wallboard Optimization Design |
| CN106202693A (en) * | 2016-07-06 | 2016-12-07 | 厦门大学 | A kind of Material Stiffened Panel structure anti-vibration fatigue optimization method based on parametric modeling |
| CN106326551A (en) * | 2016-08-23 | 2017-01-11 | 中国航空工业集团公司西安飞机设计研究所 | Calculation method for effective width of skin in reinforcing-rib wallboard structure |
| CN106697328A (en) * | 2016-12-15 | 2017-05-24 | 中国航空工业集团公司西安飞机设计研究所 | Same-material model experimental design method for load transfer characteristic of aircraft thin-wall structure |
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| CN111274670A (en) * | 2019-12-31 | 2020-06-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Design method for axial compression bearing capacity test of titanium alloy section combined wall plate |
| CN111553031A (en) * | 2020-04-24 | 2020-08-18 | 中国飞机强度研究所 | Method for calculating ultimate load of integral stiffened plate |
| CN111553030A (en) * | 2020-04-24 | 2020-08-18 | 中国飞机强度研究所 | Method for calculating damage load of integral reinforced wall plate |
| CN111914351A (en) * | 2020-07-06 | 2020-11-10 | 西安飞机工业（集团）有限责任公司 | Method for calculating overall stability of reinforced wall plate of fuselage structure |
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| CN112699471A (en) * | 2020-12-29 | 2021-04-23 | 中国航空工业集团公司西安飞机设计研究所 | Method and device for calculating effective width of skin under axial compression load of fuselage wallboard |
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