CN113836638B - Layout method for determining flat plate structure under pure bending load - Google Patents
Layout method for determining flat plate structure under pure bending load Download PDFInfo
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- CN113836638B CN113836638B CN202111097794.4A CN202111097794A CN113836638B CN 113836638 B CN113836638 B CN 113836638B CN 202111097794 A CN202111097794 A CN 202111097794A CN 113836638 B CN113836638 B CN 113836638B
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- G06F30/15—Vehicle, aircraft or watercraft design
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Abstract
The invention discloses a layout method for determining a flat plate structure under the action of pure bending load. The method overcomes the defects of the prior commonly used finite element method, so that the calculation is simpler and more convenient; in addition, the method can be used for rapidly obtaining the layout of the flat plate structure in the initial stage of design, so that the design work progress is greatly advanced.
Description
Technical Field
The invention relates to the technical field of aircraft structural design, in particular to a layout method for determining a flat plate structure under the action of pure bending load.
Background
In aircraft structural design, the fuselage often has a relatively large number of flat panel structures arranged therein due to structural assembly, docking, or functional (e.g., cargo handling, etc.) requirements. For the design of the flat plate type structure, the traditional design method is that a designer completes preliminary layout design according to own experience, builds a finite element model, then calculates stress distribution of the structure according to severe load, adjusts the structure size according to the stress distribution, and iterates step by step to obtain a final structure form. The conventional design method limits the effect of the latter dimension design due to the fact that the initial layout design is related to the experience of a designer, the final result tends to be heavy in structure weight, small in rigidity and large in stress, and the design period is seriously affected due to inefficiency caused by uncertainty of the layout design.
Therefore, a new layout design method is researched to reduce the weight of the structure, improve the structural performance and shorten the design period aiming at the defects of the traditional design method and the prior art level, and has very important significance.
Disclosure of Invention
The invention provides a layout method for determining a flat plate structure under the action of pure bending load.
The technical scheme of the invention is as follows: the realization provides a layout method for determining a flat plate structure under the action of pure bending load, which comprises the following steps:
Step 1: calculating the maximum working stress of the panel according to the pure bending load of the panel;
Step 2: obtaining a flange bar axle load expression according to the maximum working stress of the panel;
step 3: obtaining a rim moment of inertia expression according to a rim Euler formula and a rim axle pressure load expression;
step 4: obtaining a rim cross section length expression according to the rim moment of inertia expression;
Step 5: obtaining a pure bending allowable stress expression of the panel according to the length, width, thickness and material properties of the panel;
Step 6: obtaining the number of panel segments according to the maximum working stress and the pure bending allowable stress expression of the panel;
Step 7: the number of the plate edge strip segments, the section size and the panel segments, namely the layout of the plate structure, can be obtained by combining the expressions.
The method calculates the maximum working stress sigma c of the panel by the formula (1):
Wherein:
m is the pure bending load of the plate structure, a is the plate width, and t is the plate thickness.
The method calculates the axle load N 1 of the flange through a formula (2):
N1＝σcb2 (2)
Wherein:
b is the cross-sectional length of the rim.
The method calculates the moment of inertia I of the rim strip through a formula (3):
Wherein:
n 1 is the number of rim segments, E is the elastic modulus of the material.
Calculating the rim cross-sectional length b by formula (4):
calculating the pure bending allowable stress sigma cr of the flat plate through the formula (5):
Wherein:
mu is the elastic Poisson ratio of the material, and n 2 is the number of panel segments of the flat panel. K C is the critical stress coefficient of pure bending, the value and the length-width ratio of the flat plate Related to the following. According to the numerical curve, when l/n 1＝a/n2, K C =25, the numerical value is small.
Calculating the number n 2 of the panel segments through a formula (6):
σc＝σcr (6)
the number of the plate edge strip segments, the section size and the number of the panel segments, namely the layout of the plate structure, can be obtained through the formulas.
The invention has the advantages that: the invention provides a layout method for determining a flat plate structure under the action of pure bending load. The method overcomes the defects of the prior commonly used finite element method, so that the calculation is simpler and more convenient; in addition, the method can be used for rapidly obtaining the layout of the flat plate structure in the initial stage of design, so that the design work progress is greatly advanced.
Drawings
FIG. 1 is a flow chart of a method;
FIG. 2 is a schematic view of a flat panel construction;
FIG. 3 is a cross-sectional view of a ribbon;
FIG. 4 is a layout of a panel;
the numbering in the figures illustrates: 1-flat panel, 2-flat rim.
Detailed Description
As shown in fig. 1-4, the layout method for determining the flat plate structure under the pure bending load by adopting the invention comprises the following steps:
It is known that: the elastic modulus of the material is E=70000 MPa, the elastic poisson ratio of the material is mu=0.33, the plate thickness is t=2mm, the plate width is a=500 mm, the plate length is l=600 mm, and the pure bending load of the plate panel is M=2500 N.m 2.
Step 1: calculating the maximum working stress of the panel according to the pure bending load of the panel;
Step 2: obtaining a flange bar axle load expression according to the maximum working stress of the panel;
N1＝σcb2＝300b2N
step 3: obtaining a rim moment of inertia expression according to a rim Euler formula and a rim axle pressure load expression;
step 4: obtaining a rim cross section length expression according to the rim moment of inertia expression;
Step 5: obtaining a pure bending allowable stress expression of the panel according to the length, width, thickness and material properties of the panel;
When l/n 1＝a/n2, K C =25. At this time:
Step 6: obtaining the number of panel segments according to the maximum working stress and the pure bending allowable stress expression of the panel;
σc＝σcr
Namely:
The method can obtain: n 2 =3.4, the number of segments is rounded, and n 2 =4.
N 2 =5 is obtainable according to l/n 1＝a/n2 in step 4.
Step 7: the above expressions can be used for obtaining the plate edge strip segments, the section size and the panel segments, namely the layout of the plate structure:
the method can obtain: b=10.59 mm.
The final layout is shown in fig. 2 and 3.
Claims (1)
1. A method for determining the layout of a flat panel structure under pure bending load, given the pure bending load of the flat panel structure, the length, width and thickness of the flat panel, comprising the steps of:
Step 1: calculating the maximum working stress of the flat panel according to the pure bending load of the flat panel:
The maximum working stress sigma c of the panel is obtained according to the following formula
Wherein: m is the pure bending load of the plate structure, a is the width of the plate, and t is the thickness of the plate;
Step 2: obtaining a flange bar axle load expression according to the maximum working stress of the panel plate:
The cap axle load expression N 1 is obtained by the following formula:
N1＝σcb2
wherein: b is the cross-sectional length of the rim;
step 3: obtaining a rim moment of inertia expression according to a rim Euler formula and a rim axle pressure load:
The moment of inertia expression I of the rim is obtained by the following formula:
Wherein: n 1 is the number of edge strip segments, E is the elastic modulus of the material;
step 4: obtaining a rim cross section length expression according to the rim moment of inertia expression:
the edge strip cross-section length expression b is obtained by the following formula
Step 5: and obtaining a pure bending allowable stress expression of the panel according to the length, width, thickness and material properties of the panel:
The expression sigma cr of the pure bending allowable stress of the flat plate is obtained by the following formula:
Wherein:
Mu is the elastic Poisson ratio of the material, n 2 is the number of panel segments of the flat plate, K C is the pure bending critical stress coefficient, and the value and the length-width ratio of the flat plate In relation, according to the numerical curve, when ln 1＝an2, K C =25, the numerical value is small;
Step 6: the number of the panel segments is obtained according to the maximum working stress and the pure bending allowable stress expression of the panel, wherein the number of the panel segments n 2 is obtained through the following formula:
σc＝σcr；
step 7: the simultaneous expression can obtain the number of the plate edge strip segments, the section size and the panel segments, namely the layout of the plate structure,
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| CN114912188A (en) * | 2022-04-18 | 2022-08-16 | 中航西安飞机工业集团股份有限公司 | Layout method for determining upper edge strip of flat plate structure under shearing load |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JP2015114114A (en) * | 2013-12-09 | 2015-06-22 | 日立化成株式会社 | Method for evaluating mechanical characteristic of thin-plate material, method for selecting thin-plate material using the same, and selected thin-plate material |
| CN112699474A (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 | Layout method for determining flat plate structure under axial compression load |
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| FR2911202B1 (en) * | 2007-01-05 | 2009-02-13 | Airbus France Sas | METHOD OF OPTIMIZING RAIDIS PANELS UNDER CONSTRAINTS |
| CN108090265B (en) * | 2017-12-08 | 2021-05-25 | 中国航空工业集团公司西安飞机设计研究所 | A stress calculation method for ordinary frame of aircraft fuselage under bending load |
| CN112711804B (en) * | 2020-12-29 | 2022-11-22 | 中国航空工业集团公司西安飞机设计研究所 | A method for analyzing the wave-isolation strength of the wall plate of the high-lift device |
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| JP2015114114A (en) * | 2013-12-09 | 2015-06-22 | 日立化成株式会社 | Method for evaluating mechanical characteristic of thin-plate material, method for selecting thin-plate material using the same, and selected thin-plate material |
| CN112699474A (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 | Layout method for determining flat plate structure under axial compression load |
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