CN111914351B - Method for calculating overall stability of reinforced wallboard of fuselage structure - Google Patents
Method for calculating overall stability of reinforced wallboard of fuselage structure Download PDFInfo
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- CN111914351B CN111914351B CN202010644350.7A CN202010644350A CN111914351B CN 111914351 B CN111914351 B CN 111914351B CN 202010644350 A CN202010644350 A CN 202010644350A CN 111914351 B CN111914351 B CN 111914351B
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- 238000000034 method Methods 0.000 title claims abstract description 34
- 238000004364 calculation method Methods 0.000 claims abstract description 34
- 230000001687 destabilization Effects 0.000 claims description 13
- 238000004458 analytical method Methods 0.000 claims description 11
- 230000000368 destabilizing effect Effects 0.000 claims description 4
- 230000002787 reinforcement Effects 0.000 claims description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 239000000806 elastomer Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
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- G—PHYSICS
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- 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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- 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
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Abstract
A method for calculating the overall stability of the reinforced wallboard of a fuselage structure includes such steps as creating a finite element model of the reinforced wallboard of a fuselage structure, forming calculation units by rod units and adjacent half-width plate units, obtaining the stress calculation results of each calculation unit of the reinforced wallboard of the fuselage according to boundary conditions and load conditions, calculating the calculated stress and critical instability stress of the effective wide column of the reinforced wallboard of the fuselage structure by using the geometric parameters and instability processes of the minimum stress corresponding calculation units, and finally obtaining the overall stability residual strength of the reinforced wallboard of the fuselage structure by using the ratio of the critical instability stress and the calculated stress of the effective wide column of the minimum stress corresponding calculation units.
Description
Technical Field
The application belongs to the field of aircraft structural strength design, and particularly relates to a method for calculating overall stability of a reinforced wallboard of a fuselage structure.
Background
The application relates to a method for calculating stability of a reinforced wallboard of a fuselage structure when the reinforced wallboard is mainly pressed.
In the current strength check, a checking method is generally adopted for the compression of the fuselage panel, a stringer unit and a left skin unit and a right skin unit under severe working conditions are taken as research objects, axial force of the stringer rod unit is directly extracted from an overall stress analysis model, stress is calculated by the skin unit, the overall stability of the integral panel is calculated by calculating the critical instability stress of the skin unit and the critical pressure loss stress of an effective wide column, and the principle of rigidity distribution in the force transmission process is not considered during calculation.
For the airframe, on one hand, because the airframe structure belongs to an elastomer, the airframe structure can be distributed according to the rigidity principle when the load is transmitted; on the other hand, the overall stability of the reinforced wallboard of the fuselage structure is checked by directly adopting the stress analysis result of the overall stress analysis model, and the obtained result has lower precision. Therefore, a new calculation method is needed to be explored, and the overall stability calculation of the reinforced wallboard of the fuselage structure is conveniently, rapidly and accurately carried out.
Disclosure of Invention
The application provides a method for calculating the overall stability of a reinforced wallboard of a fuselage structure, which is used for calculating static strength based on a finite element analysis method and aims to improve the calculation accuracy of the overall stability of the reinforced wallboard of the fuselage structure when the fuselage structure is mainly pressed.
The application provides a method for calculating the overall stability of a reinforced wallboard of a fuselage structure, wherein the skin is an equal-thickness and equidistant common metal skin, and the stringer is an L-shaped stringer, and the method is characterized by comprising the following steps of:
a method for calculating the overall stability of a reinforced wallboard of a fuselage structure, which comprises a stringer, a skin and a fuselage frame, wherein the design digital model of the reinforced wallboard of the fuselage structure is known; 2) The frame simple support constraint of the fuselage at the end of the reinforced wallboard is used as the boundary condition of the overall stress analysis model of the fuselage wallboard; 3) According to the boundary conditions and the load working conditions, stress calculation results of all calculation units of the reinforcement wallboard of the fuselage are obtained; 4) Comparing and analyzing the stress calculation results of all calculation units under different load 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 wallboard of the fuselage structure by utilizing the geometric parameters and the instability process of the minimum stress corresponding calculating unit kz And critical buckling stress sigma cf The method comprises the steps of carrying out a first treatment on the surface of the 6) Effective wide column critical instability stress sigma of corresponding calculation unit of minimum stress cf And calculating stress sigma kz And the overall stability residual strength of the fuselage structure stiffened panel is obtained.
The destabilization 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 skins of the non-effective width areas on one side of the computing unit are in a destabilization state, and in the third stage, the skins of the non-effective width areas on two sides of the computing unit are all in a destabilization state.
In calculating the calculated stress sigma of the effective wide column kz When the method is used, firstly, the total force of the critical point of the computing unit in each stage is calculated by utilizing the geometric parameters of the computing unit and three stages of the destabilization process, the total force of the critical point of each stage of the computing unit is distributed to the skin of the non-effective width area and the effective wide column according to the rigidity distribution principle, the force on the effective wide column in each stage is overlapped to form the total force of the effective wide column, and the calculated stress sigma of the effective wide column is calculated according to the total force of the effective wide column and the area of the effective wide column kz 。
In the first stage, calculating the total force of the critical point of the calculation unit according to the rigidity distribution principle, and respectively calculating the skin of the non-effective width area and the bearing load of 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 computing unit increased in the second stage is overlapped on the skin of the non-effective width area on the side where the instability occurs and the effective wide column according to the rigidity distribution principle; in the third stage, the stress of the skins of the non-effective width areas on the two sides of the computing unit is not increased any more, and the total force of the critical points of the computing unit increased in the third stage is fully overlapped on the effective wide column.
The application has the beneficial effects that: when the method is used for calculating the overall stability of the reinforced wallboard of the fuselage structure, the destabilization process of the calculating unit is divided into three stages to be calculated respectively, the principle that load transmission is distributed according to rigidity is fully considered, and the overall stability calculating precision of the reinforced wallboard of the fuselage structure when the stiffened wallboard of the fuselage structure is mainly stressed can be improved.
The application is described in further detail below with reference to the drawings of embodiments.
Drawings
FIG. 1 is a schematic view of a typical fuselage structure stiffened panel;
FIG. 2 is a schematic diagram 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 broad column.
The numbering in the figures illustrates: 1 skin, 2 stringers, 3 fuselage frames, 4 computation units, 5 non-effective width zone skin, 6 effective wide columns, 7 effective width skin.
Detailed Description
Referring to the drawings, a typical fuselage structure stiffened panel contains 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 wallboard comprises the following specific steps:
the application carries out static strength calculation based on a finite element analysis method, and aims to improve the calculation accuracy of the overall stability of the reinforced wallboard of the fuselage structure when the fuselage structure is mainly pressed.
According to the design digital model of the reinforced wallboard of the fuselage structure, taking the intersection point of the stringer 2 and the fuselage frame 3 as a reference, a finite element model of the reinforced wallboard of the fuselage structure is established, 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 units form a calculating unit 4, and each calculating unit comprises an effective wide column 6 in the middle position and non-effective width area skins 7 at two sides of the effective wide column 6, as shown in fig. 3 and 4.
During analysis, the frame 3 simple support constraint at the end of the reinforced wallboard is used as the boundary condition of the overall stress analysis model of the wallboard.
And obtaining the stress calculation result of each calculation unit of the reinforcement wallboard of the fuselage 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, and carrying out calculation analysis, wherein the geometric parameters of the calculation unit 4, including the stringer area, the skin thickness and the skin width, are extracted from the design digital model.
Then the geometric parameter and the destabilization process of the minimum stress corresponding calculating unit 4 are utilized to calculate the calculated stress sigma of the effective wide column 6 of the reinforced wallboard of the fuselage structure kz And critical buckling stress sigma cf 。
According to the stability formula of the section bar of chapter 21 and the stability formula of the reinforced flat plate of chapter 24 of the book 9 of the aircraft design manual, the geometric parameters of the calculating unit 4 are utilized to calculate the calculating unit 4Effective wide column 6 critical instability stress sigma cf Skin 1 critical instability stress sigma cr Effective width W of skin 1 eff 。
Then according to the geometric parameter and instability process of the minimum stress corresponding calculating unit 4, calculating the calculated stress sigma of the effective wide column 6 of the reinforced wallboard of the fuselage structure kz . Calculation stress sigma of effective broad column 6 kz During calculation, the destabilization process of the calculating unit 4 is divided into three stages, wherein in the first stage, the calculating unit 4 has complete bearing capacity, in the second stage, the non-effective width area skins 5 on one side of the calculating unit 4 are in a destabilization state, and in the third stage, the non-effective width area skins 5 on two sides of the calculating unit are in a destabilization state.
When the critical point of the first stage of the destabilizing process is reached, the total force of the computing unit 4 is marked as delta P1, the covering 5 of the non-effective width area and the effective wide column 6 have complete bearing capacity, the total force delta P1 of the computing unit 4 is distributed according to the rigidity distribution principle, and the force of the effective wide column 6 in the first stage is marked as P1 according to the rigidity distribution principle;
when the critical point of the second stage of the destabilizing process is reached, the total force of the computing unit 4 is delta P1+ delta P2, the total force increment of the second stage relative to the first stage is recorded as delta P2, at the moment, the non-effective width area skin 5 at one side of the stringer 2 loses bearing capacity, the non-effective width area skin 5 and the effective wide column 6 at the other side have bearing capacity, the increment delta P2 of the total force of the computing unit 4 at the critical point of the second stage is distributed according to the rigidity distribution principle, and the force of the effective wide column 6 at the second stage is recorded as P2 according to the rigidity distribution principle;
when the critical point of the third stage of the destabilizing process is reached, the total force of the computing unit 4 is delta p1+delta p2+delta p3, the total force increment of the third stage relative to the second stage is recorded as delta P3, at the moment, the skins 5 of the non-effective width areas on the two sides of the stringer 2 lose bearing capacity, the increased total force is borne by the effective wide columns 6, and the force of the effective wide columns 6 of the third stage is recorded as P3 according to the rigidity distribution principle;
the forces P1, P2 and P3 of the effective wide column 6 in three stages of the destabilization process are overlapped to obtain the total force of the effective wide column 6, and the calculated stress sigma of the effective wide column 6 can be calculated by the area of the effective wide column 6 kz ；
Finally, the critical instability stress sigma of the effective wide column 6 of the calculation unit 4 is calculated according to the minimum stress cf And calculating stress sigma kz And the overall stability residual strength of the fuselage structure stiffened panel is obtained.
Claims (2)
1. A method for calculating the overall stability of a reinforced wallboard of a fuselage structure, which comprises a stringer, a skin and a fuselage frame, wherein the design digital model of the reinforced wallboard of the fuselage structure is known; 2) The frame simple support constraint of the fuselage at the end of the reinforced wallboard is used as the boundary condition of the overall stress analysis model of the fuselage wallboard; 3) According to the boundary conditions and the load working conditions, stress calculation results of all calculation units of the reinforcement wallboard of the fuselage are obtained; 4) Comparing and analyzing the stress calculation results of all calculation units under different load 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 wallboard of the fuselage structure by utilizing the geometric parameters and the instability process of the minimum stress corresponding calculating unit kz And critical buckling stress sigma cf The method comprises the steps of carrying out a first treatment on the surface of the The method for calculating the overall stability of the reinforced wallboard of the fuselage structure is characterized in that the destabilization process of the calculating unit in the step 5) is divided into three stages, wherein the calculating unit has complete bearing capacity in the first stage, the skin of the non-effective width area on one side of the calculating unit is in a destabilization state in the second stage, and the skins of the non-effective width areas on two sides of the calculating unit are in a destabilization state in the third stage; calculating the total force of the calculating unit at the critical point of each stage by using the geometric parameters of the calculating unit and three stages of the destabilizing process, and distributing the total force of the critical point of each stage of the calculating unit to a non-effective width according to the rigidity distribution principleThe force on the effective wide column at each stage is overlapped on the degree area skin and the effective wide column to form the total force of the effective wide column, and the calculated stress sigma of the effective wide column is calculated according to the total force of the effective wide column and the area of the effective wide column kz The method comprises the steps of carrying out a first treatment on the surface of the 6) Effective wide column critical instability stress sigma of corresponding calculation unit of minimum stress cf And calculating stress sigma kz And the overall stability residual strength of the fuselage structure stiffened panel is obtained.
2. The method for calculating the overall stability of the reinforced wallboard of the fuselage structure according to claim 1, wherein in the first stage, the total force of the critical point of the calculating unit is calculated according to the rigidity distribution principle, and the skin of the non-effective width area and the bearing load of the effective wide column are calculated respectively; 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 computing unit increased in the second stage is overlapped on the skin of the non-effective width area on the side where the instability occurs and the effective wide column according to the rigidity distribution principle; in the third stage, the stress of the skins of the non-effective width areas on the two sides of the computing unit is not increased any more, and the total force of the critical points of the computing unit increased in the third stage is fully overlapped on the effective wide column.
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| 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 |
| CN114055090B (en) * | 2021-11-19 | 2023-03-24 | 北京星航机电装备有限公司 | Pre-hollowed weight-reducing skin panel and forming method thereof |
| CN115031590B (en) * | 2022-05-19 | 2023-06-27 | 上海交通大学 | Structural stability optimization method for reinforced wallboard bearing joint load |
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| 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 |
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