CN109507040B - Honeycomb sandwich structure panel compression stress assessment method - Google Patents

Honeycomb sandwich structure panel compression stress assessment method Download PDF

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CN109507040B
CN109507040B CN201811518552.6A CN201811518552A CN109507040B CN 109507040 B CN109507040 B CN 109507040B CN 201811518552 A CN201811518552 A CN 201811518552A CN 109507040 B CN109507040 B CN 109507040B
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panel
sandwich structure
stress
sandwich
thickness
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CN109507040A (en
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杜正兴
刘洪权
殷黎
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Xian Aircraft Design and Research Institute of AVIC
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Xian Aircraft Design and Research Institute of AVIC
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/20—Investigating strength properties of solid materials by application of mechanical stress by applying steady bending forces
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N2203/0014—Type of force applied
    • G01N2203/0023—Bending
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N2203/0058—Kind of property studied
    • G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
    • G01N2203/0075—Strain-stress relations or elastic constants
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N2203/02—Details not specific for a particular testing method
    • G01N2203/06—Indicating or recording means; Sensing means
    • G01N2203/067—Parameter measured for estimating the property
    • G01N2203/0676—Force, weight, load, energy, speed or acceleration

Abstract

The invention belongs to the field of material mechanics, and relates to a method for evaluating the compressive stress of a honeycomb sandwich structure panel. According to the method, the axial force and the bending moment of the sandwich structure unit are extracted through a finite element calculation result; calculating the inertia moment of the section and the area of the panel section according to the geometric parameters of the section of the sandwich structure; calculating the axial stress according to the ratio of the axial force to the cross-sectional area, calculating the bending stress generated by the bending moment of the sandwich structure according to a bending formula, and superposing the axial stress and the bending stress at the panel of the sandwich structure so as to calculate the maximum compressive stress of the panel. The method can calculate the working stress of the sandwich structure panel to reach the maximum value of the panel stress, and can more accurately predict the damage of the sandwich structure panel.

Description

Honeycomb sandwich structure panel compression stress assessment method
Technical Field
The invention belongs to the technical field of material mechanics, and relates to a method for evaluating the compressive stress of a honeycomb sandwich structure panel.
Background
For the honeycomb sandwich structure used on the current airplane, the compressive stress of the panel under the action of load is needed when the buckling of the cells of the panel, the crinkling of the panel and the shearing and crinkling of the panel are carried out. At present, NASTRAN finite element software is generally adopted to calculate the compressive stress of the panel at home and abroad, and then the compressive stress sigma of the panel is calculated to be E epsilon (E is the equivalent elastic modulus of the panel) by selecting the strain value epsilon on the panel; or the stress value on the panel is directly selected as the working stress of the panel, and the methods have a problem that the calculated panel stress is the mean stress of the panel, the stress of the actual panel section in the gradient direction is uneven, and the local stress of the panel is larger than that of the currently adopted calculation method, so that the calculation of the panel is more dangerous, and the risk is brought to model development.
In the strength calculation of the honeycomb sandwich structure, the calculation of cell buckling, panel wrinkle damage and shear wrinkle of the honeycomb sandwich structure panel needs to extract the working stress of the panel, the strain of the panel is generally extracted in the calculation of the working stress of the panel in the prior art, and then the strain is multiplied by the equivalent elastic modulus of the panel to obtain the working stress of the panel.
Disclosure of Invention
The purpose of the invention is: a method for evaluating the compressive stress of a honeycomb sandwich structure panel is designed to solve the technical problem that the calculation result in the existing method is deviated from danger and the structure is possibly damaged in advance.
In order to solve the technical problem, the technical scheme of the invention is as follows:
a honeycomb sandwich structure panel compressive stress assessment method extracts axial force and bending moment of a sandwich structure unit through a finite element calculation result; calculating the inertia moment of the section and the area of the panel section according to the geometric parameters of the section of the sandwich structure; calculating the axial stress according to the ratio of the axial force to the cross-sectional area, calculating the bending stress generated by the bending moment of the sandwich structure according to a bending formula, and superposing the axial stress and the bending stress at the panel of the sandwich structure so as to calculate the maximum compressive stress of the panel.
The method for evaluating the compressive stress of the honeycomb sandwich structure panel comprises the following steps:
step one, extracting the axial force F of the sandwich structure unit according to the finite element calculation resultNBending moment Mx；
Step two, determining the inertia moment I on the section of the honeycomb sandwich structure by utilizing a calculation method of the plane graph inertia moment in material mechanicsz；
Step three, according to the axial force F of the sandwich structure unitNCalculating the axial stress sigma of the sandwich panel1；
Step four, according to the sandwich structure unitBending moment MxCalculating the maximum bending stress sigma of the sandwich panel2；
Step five, according to the axial stress sigma of the sandwich structure panel1And maximum bending stress sigma2The maximum compressive stress σ of the sandwich panel was calculated.
In the second step, the moment of inertia I is determinedzThe formula (2) is specifically as follows:
Figure BDA0001902659710000021
wherein t is1Thickness of the panel one of the sandwich structure, t2Thickness of the second panel of the sandwich structure, tcIs the thickness of the sandwich core and b is the length of the loading edge of the sandwich unit.
Axial stress sigma in the step three1The calculation formula of (2) is as follows:
Figure BDA0001902659710000022
wherein A is the area of the sandwich cross-section panel.
The maximum bending stress sigma in the fourth step2The calculation formula of (2) is as follows:
Figure BDA0001902659710000023
wherein y ismaxThe maximum distance from the sandwich panel to the centroid of the sandwich cross-section.
The calculation formula of the maximum compressive stress sigma in the step five is as follows:
Figure BDA0001902659710000031
the invention has the beneficial effects that: by adopting the method for evaluating the compressive stress of the honeycomb sandwich structure panel, the maximum value of the compressive stress of the honeycomb sandwich structure panel can be obtained, and the state that the strength of the conventional honeycomb sandwich structure panel is dangerous to calculate is changed.
Drawings
FIG. 1 is a schematic view of the geometry of a honeycomb sandwich structure;
FIG. 2 is a flow chart of the steps of a method for evaluating compressive stress of a honeycomb sandwich panel;
fig. 3 is a schematic diagram illustrating calculation and derivation of a compressive stress evaluation method for a honeycomb sandwich structure panel.
Detailed Description
The invention is further illustrated with reference to the following figures and examples:
taking an aircraft sandwich structure wallboard as an example, the method for evaluating the compressive stress of the honeycomb sandwich structure panel is calculated, evaluated and verified as follows.
1. Extracting the axial force F of the sandwich structure unit according to the finite element calculation resultNBending moment Mx；
2. Referring to the sandwich structure cross section shown in fig. 1, the moment of inertia I on the honeycomb sandwich structure cross section can be determined by using the calculation method of the plane figure moment of inertia in material mechanicszComprises the following steps:
Figure BDA0001902659710000032
wherein t is1Thickness of the panel one of the sandwich structure, t2Thickness of the second panel of the sandwich structure, tcIs the thickness of the sandwich core and b is the length of the loading edge of the sandwich unit.
3. Axial force F according to the sandwich structural unitNCalculating the axial stress sigma of the sandwich panel1
Figure BDA0001902659710000033
Wherein A is the area of the sandwich cross-section panel.
4. Bending moment M according to sandwich structure unitxMeter for measuringCalculating the maximum bending stress sigma of a sandwich panel2
Figure BDA0001902659710000034
Wherein y ismaxThe maximum distance from the sandwich panel to the centroid of the sandwich cross-section.
5. Axial stress σ according to sandwich construction panel1And maximum bending stress sigma2Calculating the maximum compressive stress sigma of a sandwich panel
Figure BDA0001902659710000041
The whole calculation flow is shown in fig. 2, and the specific settlement results are as follows.
(1) Selecting axial force F of certain unit of sandwich structureN-83.2 and bending moment Mx＝7620.9；
(2) The section parameter of the sandwich structural unit is t1＝t2＝0.432，tcCalculating the section inertia moment I of the sandwich structure as 10 and b as 114z＝12181.3；
(3) Calculating sandwich structure panel axial force FNStress sigma generated1，
Figure BDA0001902659710000042
(4) Calculating the bending moment M of the sandwich panelxStress sigma generated2；
Figure BDA0001902659710000043
(5) Calculating the Panel stress σ
σ＝σ1-σ2＝-37.78
The equivalent modulus of elasticity of the panel is E30400 and the compression strain value of the panel is ε -420, the original calculation is madeThe compressive stress of the panel calculated by the method is σ' ═ E ∈ -30400 × 420 × 10-6＝-12.77。
Therefore, the stress of the panel measured by the evaluation method is larger than that of the original measurement method, and the strength evaluation of the structure by the evaluation method is safer than that of the original measurement method. The first step to the fourth step in the technical scheme of the evaluation method of the present invention do not have a necessary sequence, and referring to the schematic calculation derivation diagram of the evaluation method of the present invention in fig. 3, the derivation sequence in fig. 3 is satisfied, and the compressive stress of the honeycomb sandwich structure panel can be obtained.

Claims (1)

1. A method for evaluating the compressive stress of a honeycomb sandwich structure panel is characterized by comprising the following steps: the method for evaluating the compressive stress of the honeycomb sandwich structure panel comprises the following steps:
step one, extracting the axial force F of the sandwich structure unit according to the finite element calculation resultNBending moment Mx；
Step two, determining the inertia moment I on the section of the honeycomb sandwich structure by utilizing a calculation method of the plane graph inertia moment in material mechanicsz；
Determination of the moment of inertia IzThe formula (2) is specifically as follows:
Figure FDA0002900608430000011
wherein t is1Thickness of the panel one of the sandwich structure, t2Thickness of the second panel of the sandwich structure, tcB is the thickness of the sandwich structure core, and b is the length of the loading edge of the sandwich structure unit;
step three, according to the axial force F of the sandwich structure unitNCalculating the axial stress sigma of the sandwich panel1；
Axial stress sigma1The calculation formula of (2) is as follows:
Figure FDA0002900608430000012
wherein A is the area of the panel with the sandwich structure section, t1Thickness of the panel one of the sandwich structure, t2B is the thickness of the sandwich structure panel II and the length of the loading edge of the sandwich structure unit;
step four, bending moment M of the sandwich structure unitxCalculating the maximum bending stress sigma of the sandwich panel2；
Maximum bending stress sigma2The calculation formula of (2) is as follows:
Figure FDA0002900608430000013
wherein y ismaxIs the maximum distance, t, from the sandwich panel to the centroid of the sandwich cross-section1Thickness of the panel one of the sandwich structure, t2Thickness of the second panel of the sandwich structure, tcB is the thickness of the sandwich structure core, and b is the length of the loading edge of the sandwich structure unit;
step five, according to the axial stress sigma of the sandwich structure panel1And maximum bending stress sigma2The maximum compressive stress sigma of the sandwich structural panel is calculated,
the maximum compressive stress σ is calculated by the formula:
Figure FDA0002900608430000021
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CN113051780A (en) * 2019-12-26 2021-06-29 中国航空工业集团公司西安飞机设计研究所 Method for judging axial compression buckling load of flat plate structure
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