CN111914351A - Method for calculating overall stability of reinforced wall plate of fuselage structure - Google Patents
Method for calculating overall stability of reinforced wall plate of fuselage structure Download PDFInfo
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- CN111914351A CN111914351A CN202010644350.7A CN202010644350A CN111914351A CN 111914351 A CN111914351 A CN 111914351A CN 202010644350 A CN202010644350 A CN 202010644350A CN 111914351 A CN111914351 A CN 111914351A
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- 238000000034 method Methods 0.000 title claims abstract description 27
- 238000004364 calculation method Methods 0.000 claims abstract description 59
- 230000001687 destabilization Effects 0.000 claims abstract description 8
- 238000004458 analytical method Methods 0.000 claims description 11
- 230000000368 destabilizing effect Effects 0.000 claims description 5
- 230000005540 biological transmission Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/28—Fuselage, exterior or interior
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Abstract
A method for calculating the overall stability of a reinforced wall plate of a fuselage structure includes such steps as creating a finite element model of the reinforced wall plate, forming a calculation unit by rod units and adjacent half-width plate units, calculating the stress calculation results of each calculation unit according to boundary conditions and load conditions, calculating the calculated stress and critical destabilization stress of the effective wide column of the reinforced wall plate of fuselage structure by the geometric parameters and destabilization process of the minimum stress corresponding calculation unit, and calculating the ratio of the critical destabilization stress and calculated stress of the effective wide column of the minimum stress corresponding calculation unit to obtain the residual overall stability of the reinforced wall plate.
Description
Technical Field
The invention belongs to the field of design of structural strength of airplanes, and particularly relates to a method for calculating the overall stability of a reinforced wall plate of a fuselage structure.
Background
The invention mainly researches a stability calculation method when a stiffened wall plate of the fuselage structure is mainly pressed.
In the existing strength check, the fuselage wallboard compression generally adopts the following check method, a stringer unit and left and right skin units under severe working conditions are taken as research objects, the stringer unit axial force is directly extracted from an overall stress analysis model, the skin units calculate stress, the overall stability of the integral wallboard is calculated by calculating the skin unit adjacent unstable pressure stress and the effective wide column adjacent pressure loss stress, and the principle of rigidity distribution in the force transmission process is not considered in the calculation.
For the fuselage, on one hand, because the fuselage structure belongs to an elastic body, the load can be distributed according to the rigidity principle during load transmission; on the other hand, the stress analysis result of the overall stress analysis model is directly adopted to check the overall stability of the reinforced wall plate of the machine body structure, and the obtained result precision is lower. Therefore, a new calculation method needs to be explored, and the overall stability of the reinforced wall plate of the fuselage structure can be conveniently, quickly and accurately calculated.
Disclosure of Invention
The invention provides a method for calculating the overall stability of a reinforced wall plate of a fuselage structure, which is used for calculating static strength based on a finite element analysis method and aims to improve the calculation precision of the overall stability of the reinforced wall plate of the fuselage structure when the reinforced wall plate is mainly pressed.
The invention provides a method for calculating the overall stability of a reinforced wallboard of a fuselage structure, wherein the skin is common metal skin with equal thickness and equal spacing, and the stringer is an L-shaped stringer, which is characterized by comprising the following steps:
a fuselage structure adds the whole stability calculation method of the ribbed wallboard, should add the ribbed wallboard and include stringer, covering, fuselage frame, know the design digifax of the ribbed wallboard of this fuselage structure, characterized by including the following steps, 1) according to the design digifax of the ribbed wallboard of fuselage structure, regard stringer and fuselage frame intersect as the benchmark, set up the finite element model of the ribbed wallboard of fuselage structure, wherein simplify the covering as the board unit, simplify the stringer as the pole unit, simplify the fuselage frame as the roof beam unit, make up the calculation unit by pole unit and adjacent half-width board unit, every calculation unit includes the effective wide column of the median position and the non-effective width area covering of both sides of effective wide column; 2) simply supporting and constraining a fuselage frame at the end of the reinforced wall plate to serve as a boundary condition of a fuselage wall plate overall stress analysis model; 3) root of herbaceous plantObtaining stress calculation results of each calculation unit of the fuselage stiffened wall panel according to the boundary conditions and the load working conditions; 4) Comparing and analyzing the stress calculation results of each calculation unit under different load working conditions, and extracting a calculation unit corresponding to the minimum stress; 5) calculating the calculated stress sigma of the effective wide column of the reinforced wall plate of the fuselage structure by using the geometric parameters and the instability process of the minimum stress corresponding calculation unitkzAnd critical destabilizing stress σcf(ii) a 6) Calculating the effective wide column critical instability stress sigma of the unit according to the minimum stresscfAnd calculating the stress σkzAnd obtaining the total stability residual strength of the reinforced wall plate of the fuselage structure.
The instability process of the computing unit is divided into three stages, wherein in the first stage, the computing unit has complete bearing capacity, in the second stage, the skin of the non-effective width area on one side of the computing unit is in an instability state, and in the third stage, the skins of the non-effective width areas on two sides of the computing unit are in instability states.
At the calculation of the calculated stress σ of the effective wide columnkzFirstly, respectively calculating the total force of a calculation unit at each stage critical point by using the geometric parameters of the calculation unit and three stages of a destabilization process, distributing the total force of each stage critical point of the calculation unit to a skin of a non-effective width area and an effective wide column according to a rigidity distribution principle, superposing the forces on the effective wide columns at each stage to form the total force of the effective wide columns, and calculating the calculated stress sigma of the effective wide columns according to the total force of the effective wide columns and the area of the effective wide columnskz。
In the first stage, respectively calculating the total force of the critical point of the calculation unit according to a rigidity distribution principle to respectively calculate the load borne by the skin of the non-effective width area and the effective wide column; in the second stage, the stress of the skin of the non-effective width area on the side where the instability occurs is not increased any more, and the total force of the critical point of the calculation unit increased in the second stage is superposed on the skin of the non-effective width area on the side where the instability does not occur and the effective wide column according to the rigidity distribution principle; in the third stage, the stress of the skins in the non-effective width areas on the two sides of the computing unit is not increased any more, and the total force of the computing unit critical points increased in the third stage is completely superposed on the effective wide column.
The beneficial effect of this application lies in: when the overall stability of the reinforced wall panel of the fuselage structure is calculated, the instability process of the calculating unit is divided into three stages to be calculated respectively, the load transfer is fully considered according to the rigidity distribution principle, and the overall stability calculation precision of the reinforced wall panel of the fuselage structure when the reinforced wall panel is mainly pressed can be improved.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
FIG. 1 is a schematic view of a typical fuselage structure stiffened panel;
FIG. 2 is a schematic view of a finite element analysis model of a typical fuselage structure stiffened panel;
FIG. 3 is a schematic diagram of a computing unit;
FIG. 4 is a schematic view of an effective wide column.
The numbering in the figures illustrates: the method comprises the following steps of 1 covering, 2 stringers, 3 fuselage frames, 4 computing units, 5 covering of an ineffective width area, 6 covering of an effective wide column and 7 covering of an effective width.
Detailed Description
Referring to the drawings, a typical stiffened panel of a fuselage structure comprises an integral skin 1, a plurality of longitudinal stringers 2 and a plurality of transverse fuselage frames. The method for calculating the overall stability of the reinforced wall plate comprises the following specific steps:
the static strength calculation method is based on a finite element analysis method, and aims to improve the calculation precision of the overall stability of the reinforced wall plate of the fuselage structure when the reinforced wall plate is mainly pressed.
According to the design digifax of the fuselage structure stiffened wall panel, a finite element model of the fuselage structure stiffened wall panel is established by taking the intersection point of the stringer 2 and the fuselage frame 3 as a reference, wherein the skin 1 is simplified into a plate unit, the stringer 2 is simplified into a rod unit, the fuselage frame 3 is simplified into a beam unit, the rod unit and the adjacent half-width plate unit form a calculation unit 4, and each calculation unit comprises an effective wide column 6 at the middle position and an ineffective width area skin 7 at two sides of the effective wide column 6, as shown in fig. 3 and 4.
During analysis, the fuselage frame 3 at the end of the stiffened wall panel is simply supported and constrained to serve as a boundary condition of the fuselage wall panel overall stress analysis model.
And obtaining the stress calculation results of each calculation unit of the fuselage stiffened wall panel according to the boundary conditions and the load working conditions.
And comparing and analyzing the stress calculation results of the calculation units under different load working conditions, extracting the calculation unit 4 corresponding to the minimum stress for calculation and analysis, and extracting the geometric parameters of the calculation unit 4 from a design digital-to-analog, wherein the geometric parameters comprise the stringer area, the skin thickness and the skin width.
Then, the geometric parameters and the instability process of the minimum stress corresponding calculation unit 4 are utilized to calculate the calculated stress sigma of the effective wide column 6 of the reinforced wall plate of the fuselage structurekzAnd critical destabilizing stress σcf。
According to the formula of section bar stability in chapter 21 of handbook of aircraft design 9 and the formula of stiffened flat plate stability in chapter 24, the geometric parameters of the calculation unit 4 are used to calculate the critical buckling stress sigma of the effective wide column 6 of the calculation unit 4cf Skin 1 near-end destabilizing stress sigmacrEffective width W of skin 1eff。
Then, according to the geometric parameters and the instability process of the minimum stress corresponding calculation unit 4, the calculated stress sigma of the effective wide column 6 of the reinforced wall plate of the fuselage structure is calculatedkz. Calculated stress σ of the effective wide column 6kzDuring calculation, the instability process of the calculation unit 4 is divided into three stages, wherein in the first stage, the calculation unit 4 has complete bearing capacity, in the second stage, the skin 5 of the non-effective width area on one side of the calculation unit 4 is in an instability state, and in the third stage, the skins 5 of the non-effective width areas on two sides of the calculation unit are in instability states.
At a critical point of a first stage of a destabilization process, recording the total force of the computing unit 4 as delta P1, wherein the skin 5 and the effective wide column 6 in the non-effective width area have complete bearing capacity, distributing the total force delta P1 of the computing unit 4 according to a rigidity distribution principle, and recording the force of the effective wide column 6 at the first stage as P1 according to the rigidity distribution principle;
at a critical point of a second stage of a destabilization process, the total force of the calculation unit 4 is Δ P1+ Δ P2, the total force increment of the second stage relative to the first stage is Δ P2, at this time, the skin 5 of the non-effective width area at one side of the stringer 2 loses bearing capacity, the skin 5 of the non-effective width area and the effective wide column 6 at the other side have bearing capacity, the increment Δ P2 of the total force of the calculation unit 4 at the critical point of the second stage is distributed according to a rigidity distribution principle, and the force of the effective wide column 6 at the second stage according to the rigidity distribution principle is recorded as P2;
at the critical point of the third stage of the destabilization process, the total force of the computing unit 4 is Δ P1+ Δ P2+ Δ P3, the total force increment of the third stage relative to the second stage is recorded as Δ P3, at this time, the skins 5 of the non-effective width areas at the two sides of the stringer 2 lose the bearing capacity, the increased total force is all borne by the effective wide column 6, and the force of the effective wide column 6 at the third stage according to the rigidity distribution principle is recorded as P3;
the forces P1, P2 and P3 of the effective wide column 6 in the three stages of the instability process are superposed to form the total force of the effective wide column 6, and the calculated stress sigma of the effective wide column 6 can be calculated according to the area of the effective wide column 6kz；
Finally, the effective wide column 6 critical instability stress sigma of the calculation unit 4 is corresponded by the minimum stresscfAnd calculating the stress σkzAnd obtaining the total stability residual strength of the reinforced wall plate of the fuselage structure.
Claims (4)
1. A fuselage structure adds the whole stability calculation method of the ribbed wallboard, should add the ribbed wallboard and include stringer, covering, fuselage frame, know the design digifax of the ribbed wallboard of this fuselage structure, characterized by including the following steps, 1) according to the design digifax of the ribbed wallboard of fuselage structure, regard stringer and fuselage frame intersect as the benchmark, set up the finite element model of the ribbed wallboard of fuselage structure, wherein simplify the covering as the board unit, simplify the stringer as the pole unit, simplify the fuselage frame as the roof beam unit, make up the calculation unit by pole unit and adjacent half-width board unit, every calculation unit includes the effective wide column of the median position and the non-effective width area covering of both sides of effective wide column; 2) simply supporting and constraining a fuselage frame at the end of the reinforced wall plate to serve as a boundary condition of a fuselage wall plate overall stress analysis model; 3) obtaining stress calculation results of each calculation unit of the fuselage stiffened wall panel according to the boundary conditions and the load working conditions; 4) will be provided withComparing and analyzing the stress calculation results of each calculation unit under different load working conditions, and extracting the calculation unit corresponding to the minimum stress; 5) calculating the calculated stress sigma of the effective wide column of the reinforced wall plate of the fuselage structure by using the geometric parameters and the instability process of the minimum stress corresponding calculation unitkzAnd critical destabilizing stress σcf(ii) a 6) Calculating the effective wide column critical instability stress sigma of the unit according to the minimum stresscfAnd calculating the stress σkzAnd obtaining the total stability residual strength of the reinforced wall plate of the fuselage structure.
2. The method for calculating the overall stability of the fuselage structure stiffened wall panel of claim 1, wherein the destabilization process of the computing unit in step 5) is divided into three stages, wherein in the first stage, the computing unit has full carrying capacity, in the second stage, the skin of the ineffective width area on one side of the computing unit is in a destabilized state, and in the third stage, the skin of the ineffective width area on both sides of the computing unit is in a destabilized state.
3. The method for calculating the overall stability of the fuselage structure stiffened wall panel of claim 1 or 2, wherein the total force of the computing unit at each stage critical point is calculated by using the geometric parameters of the computing unit and three stages of the destabilizing process, respectively, the total force of the computing unit at each stage critical point is distributed to the skin of the non-effective width region and the effective wide column according to the rigidity distribution principle, the forces on the effective wide columns at each stage are superposed to form the total force of the effective wide columns, and the calculated stress σ of the effective wide columns is calculated according to the total force of the effective wide columns and the area of the effective wide columnskz。
4. The method for calculating the overall stability of the fuselage structure stiffened wall panel of claim 3, wherein in the first stage, the total force of the critical points of the calculation unit is calculated according to the rigidity distribution principle to respectively calculate the loads borne by the skin of the non-effective width area and the effective wide column; in the second stage, the stress of the skin of the non-effective width area on the side where the instability occurs is not increased any more, and the total force of the critical point of the calculation unit increased in the second stage is superposed on the skin of the non-effective width area on the side where the instability does not occur and the effective wide column according to the rigidity distribution principle; in the third stage, the stress of the skins in the non-effective width areas on the two sides of the computing unit is not increased any more, and the total force of the computing unit critical points increased in the third stage is completely superposed on the effective wide column.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113312815A (en) * | 2021-05-19 | 2021-08-27 | 中航西安飞机工业集团股份有限公司 | Calculation method for overall stability of stringer in fuselage structure |
| CN114055090A (en) * | 2021-11-19 | 2022-02-18 | 北京星航机电装备有限公司 | Pre-hollowed weight-reducing skin panel and forming method thereof |
| CN115031590A (en) * | 2022-05-19 | 2022-09-09 | 上海交通大学 | Method for optimizing structural stability of reinforced wall plate bearing joint load |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103870613A (en) * | 2012-12-10 | 2014-06-18 | 中国飞机强度研究所 | Calculation method of bearing capacity of reinforced wall plate |
| CN105184390A (en) * | 2015-08-12 | 2015-12-23 | 中国运载火箭技术研究院 | Integrated optimization method of static strength, rigidity, stability of wallboard structure |
| JP2016134174A (en) * | 2015-01-15 | 2016-07-25 | リバーモア ソフトウェア テクノロジー コーポレーション | Numerical simulation of scrap trimming operations in sheet metal forming |
| 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 |
| CN109033526A (en) * | 2018-06-27 | 2018-12-18 | 西安飞机工业（集团）有限责任公司 | A kind of rib connect load calculation method with skin rivet |
| CN109684693A (en) * | 2018-12-12 | 2019-04-26 | 中国航空工业集团公司西安飞机设计研究所 | A method of based on the estimated Material Stiffened Panel post-buckling of finite element analysis |
-
2020
- 2020-07-06 CN CN202010644350.7A patent/CN111914351B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103870613A (en) * | 2012-12-10 | 2014-06-18 | 中国飞机强度研究所 | Calculation method of bearing capacity of reinforced wall plate |
| JP2016134174A (en) * | 2015-01-15 | 2016-07-25 | リバーモア ソフトウェア テクノロジー コーポレーション | Numerical simulation of scrap trimming operations in sheet metal forming |
| CN105184390A (en) * | 2015-08-12 | 2015-12-23 | 中国运载火箭技术研究院 | Integrated optimization method of static strength, rigidity, stability of wallboard structure |
| 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 |
| CN109033526A (en) * | 2018-06-27 | 2018-12-18 | 西安飞机工业（集团）有限责任公司 | A kind of rib connect load calculation method with skin rivet |
| CN109684693A (en) * | 2018-12-12 | 2019-04-26 | 中国航空工业集团公司西安飞机设计研究所 | A method of based on the estimated Material Stiffened Panel post-buckling of finite element analysis |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113312815A (en) * | 2021-05-19 | 2021-08-27 | 中航西安飞机工业集团股份有限公司 | Calculation method for overall stability of stringer in fuselage structure |
| CN113312815B (en) * | 2021-05-19 | 2024-04-02 | 中航西安飞机工业集团股份有限公司 | Method for calculating overall stability of stringers in fuselage structure |
| CN114055090A (en) * | 2021-11-19 | 2022-02-18 | 北京星航机电装备有限公司 | Pre-hollowed weight-reducing skin panel and forming method thereof |
| CN115031590A (en) * | 2022-05-19 | 2022-09-09 | 上海交通大学 | Method for optimizing structural stability of reinforced wall plate bearing joint load |
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