CN109507040A - A kind of honeycomb sandwich construction panel compression stress appraisal procedure - Google Patents

A kind of honeycomb sandwich construction panel compression stress appraisal procedure Download PDF

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Publication number
CN109507040A
CN109507040A CN201811518552.6A CN201811518552A CN109507040A CN 109507040 A CN109507040 A CN 109507040A CN 201811518552 A CN201811518552 A CN 201811518552A CN 109507040 A CN109507040 A CN 109507040A
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sandwich
panel
stress
appraisal procedure
moment
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CN109507040B (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

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  • Physics & Mathematics (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Chemical & Material Sciences (AREA)
  • Analytical Chemistry (AREA)
  • Biochemistry (AREA)
  • General Health & Medical Sciences (AREA)
  • General Physics & Mathematics (AREA)
  • Immunology (AREA)
  • Pathology (AREA)
  • Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)

Abstract

The invention belongs to mechanics of materials fields, are related to a kind of honeycomb sandwich construction panel compression stress appraisal procedure.Method of the invention extracts axle power, the moment of flexure of sandwich unit by result of finite element；Further according to the geometric parameter in sandwich section, the moment of inertia in section, the area in panel section are calculated；According to the ratio calculation axial stress of axle power and area of section, according to bending formula, calculate the bending stress of sandwich moment of flexure generation, at sandwich panel axial stress and bending stress be overlapped and then calculate the maximal compressed stress of panel.The method of the present invention can reach the maximum value of panel stress to the calculating of sandwich panel working stress, can more accurately predict the destruction of sandwich panel.

Description

A kind of honeycomb sandwich construction panel compression stress appraisal procedure
Technical field
The invention belongs to mechanics of materials technical fields, are related to a kind of honeycomb sandwich construction panel compression stress appraisal procedure.
Background technique
For the honeycomb sandwich construction used on current aircraft, in the compartment buckling, panel wrinkle damage and face for carrying out panel When the shearing fold of plate, require to use compression stress of the panel under load effect.Currently, both at home and abroad to panel compression stress Calculating generally use NASTRAN finite element software to be calculated, then by choose panel on strain value ε, calculate panel The stress in compression sigma=E ε equivalent elastic modulus of panel (E be)；Or work of the stress value directly on selection panel as panel Make stress, these methods have a problem that, the panel stress being calculated in this way is the mean value stress of panel, and actual panel Stress of the section on gradient direction be it is non-uniform, the local stress of panel can be greater than answering for currently used calculation method Power, the calculating that will cause panel in this way are partial to danger, bring risk to Project R&D.
In the Strength co-mputation of honeycomb sandwich construction, compartment buckling, the panel wrinkle of honeycomb sandwich construction panel are damaged and are cut The calculating for cutting fold requires to extract the working stress of panel, generally using extraction in the calculating of the working stress of previous panel The strain of panel obtains the working stress of panel then multiplied by the equivalent elastic modulus of panel, the panel that this method calculates Working stress is the mean stress of panel, and honeycomb sandwich construction is when bearing bending load, and the stress on panel is simultaneously uneven, The outermost stress of panel is maximum, in this way to the Strength co-mputation of honeycomb sandwich construction when can relatively danger, make structure premature degradation.
Summary of the invention
The purpose of the present invention is: a kind of honeycomb sandwich construction panel compression stress appraisal procedure is designed, to solve side at present The technical issues of calculated result present in method can be relatively dangerous, may result in structure premature degradation.
To solve this technical problem, the technical scheme is that
A kind of honeycomb sandwich construction panel compression stress appraisal procedure, the honeycomb sandwich construction panel compression stress are commented Method is estimated by result of finite element, extracts axle power, the moment of flexure of sandwich unit；Further according to the several of sandwich section What parameter, calculates the moment of inertia in section, the area in panel section；According to the ratio calculation axial stress of axle power and area of section, According to bending formula, the bending stress of sandwich moment of flexure generation is calculated, to axial stress at sandwich panel and curved Transverse stress is overlapped and then calculates the maximal compressed stress of panel.
Steps are as follows for the honeycomb sandwich construction panel compression stress appraisal procedure:
Step 1: extracting the axle power F of sandwich unit according to result of finite elementN, moment Mx；
Step 2: being determined on honeycomb sandwich construction section using the calculation method of planar graph the moment of inertia in the mechanics of materials The moment of inertia Iz；
Step 3: according to the axle power F of sandwich unitN, calculate the axial stress σ of sandwich panel1；
Step 4: according to the moment M of sandwich unitx, calculate the maximum stress in bend σ of sandwich panel2；
Step 5: according to the axial stress σ of sandwich panel1And maximum stress in bend σ2Calculate sandwich panel Maximal compressed stress σ.
The moment of inertia I is determined in the step twozFormula it is specific as follows:
Wherein t1For the thickness of sandwich panel one, t2For the thickness of sandwich panel two, tcFor sandwich fuse Thickness, b be sandwich unit load edge lengths.
Axial stress σ in the step three1Calculation formula are as follows:
Wherein A is the area of sandwich section panel.
Maximum stress in bend σ in the step four2Calculation formula are as follows:
Wherein ymaxFor sandwich panel to the maximum distance of sandwich cross-section centroid.
The calculation formula of maximal compressed stress σ in the step five are as follows:
It, can be with the beneficial effects of the present invention are: using honeycomb sandwich construction panel compression stress appraisal procedure of the invention The maximum value for obtaining honeycomb sandwich construction panel compression stress changes previous honeycomb sandwich construction slab strength and calculates danger partially State.
Detailed description of the invention
Fig. 1 is honeycomb sandwich construction geometric parameter schematic diagram；
Fig. 2 is honeycomb sandwich construction panel compression stress appraisal procedure flow chart of steps；
Fig. 3 is that honeycomb sandwich construction panel compression stress appraisal procedure calculates derivation schematic diagram.
Specific embodiment
The present invention will be further described with reference to the accompanying drawings and examples:
By taking certain aircraft sandwich siding as an example, to honeycomb sandwich construction panel compression stress appraisal procedure of the invention into It is as follows that row calculates assessment verifying.
1, according to result of finite element, the axle power F of sandwich unit is extractedN, moment Mx；
2, the sandwich section with reference to shown in Fig. 1, using the calculation method in the mechanics of materials about planar graph the moment of inertia, It can determine the moment of inertia I on honeycomb sandwich construction sectionzAre as follows:
Wherein t1For the thickness of sandwich panel one, t2For the thickness of sandwich panel two, tcFor sandwich fuse Thickness, b be sandwich unit load edge lengths.
3, according to the axle power F of sandwich unitN, calculate the axial stress σ of sandwich panel1
Wherein A is the area of sandwich section panel.
4, according to the moment M of sandwich unitx, calculate the maximum stress in bend σ of sandwich panel2
Wherein ymaxFor sandwich panel to the maximum distance of sandwich cross-section centroid.
5, according to the axial stress σ of sandwich panel1And maximum stress in bend σ2Calculate the maximum pressure of sandwich panel Stress under compression σ
Entire calculation process is as shown in Fig. 2, specific checkout result is as follows.
(1) the axle power F of sandwich unit is chosenN=-83.2 and moment Mx=7620.9；
(2) cross section parameter of sandwich unit is t1=t2=0.432, tc=10, b=114 calculate sandwich and cut Face the moment of inertia Iz=12181.3；
(3) sandwich panel axle power F is calculatedNThe stress σ of generation1,
(4) sandwich panel moment M is calculatedxThe stress σ of generation2；
(5) panel stress σ is calculated
σ=σ1-σ2=-37.78
The equivalent elastic modulus of panel is E=30400, and the compression strain value of panel is ε=- 420, then original calculating side The compression stress of the calculated panel of method is σ '=ε=- 30400 × 420 × 10 E-6=-12.77.
As it can be seen that the stress for the panel that appraisal procedure of the invention calculates is greater than original measuring method, using this hair Bright appraisal procedure can be than original measuring method safety to the strength assessment of structure.Using the technical side of appraisal procedure of the invention The step 1 sequencing uninevitable to step 4 in case derives schematic diagram referring to the calculating of the appraisal procedure of the present invention of Fig. 3, Meet the derivation sequencing of Fig. 3, the compression stress of you can get it honeycomb sandwich construction panel.

Claims (5)

1. a kind of honeycomb sandwich construction panel compression stress appraisal procedure, it is characterised in that: the honeycomb sandwich construction panel Steps are as follows for compression stress appraisal procedure:
Step 1: extracting the axle power F of sandwich unit according to result of finite elementN, moment Mx；
Step 2: being determined used on honeycomb sandwich construction section using the calculation method of planar graph the moment of inertia in the mechanics of materials Property square Iz；
Step 3: according to the axle power F of sandwich unitN, calculate the axial stress σ of sandwich panel1；
Step 4: according to the moment M of sandwich unitx, calculate the maximum stress in bend σ of sandwich panel2；
Step 5: according to the axial stress σ of sandwich panel1And maximum stress in bend σ2Calculate the maximum of sandwich panel Stress in compression sigma.
2. honeycomb sandwich construction panel compression stress appraisal procedure according to claim 1, it is characterised in that: the step The moment of inertia I is determined in rapid twozFormula it is specific as follows:
Wherein t1For the thickness of sandwich panel one, t2For the thickness of sandwich panel two, tcFor the thickness of sandwich fuse Degree, b are that sandwich unit loads edge lengths.
3. honeycomb sandwich construction panel compression stress appraisal procedure according to claim 1, it is characterised in that: the step Axial stress σ in rapid three1Calculation formula are as follows:
Wherein A is the area of sandwich section panel, t1For the thickness of sandwich panel one, t2For sandwich panel two Thickness, b be sandwich unit load edge lengths.
4. honeycomb sandwich construction panel compression stress appraisal procedure according to claim 1, it is characterised in that: the step Maximum stress in bend σ in rapid four2Calculation formula are as follows:
Wherein ymaxFor sandwich panel to the maximum distance of sandwich cross-section centroid, t1For the thickness of sandwich panel one Degree, t2For the thickness of sandwich panel two, tcFor the thickness of sandwich fuse, b is that sandwich unit loads edge lengths.
5. honeycomb sandwich construction panel compression stress appraisal procedure according to claim 1, it is characterised in that: the step The calculation formula of maximal compressed stress σ in rapid five are as follows:
CN201811518552.6A 2018-12-12 2018-12-12 Honeycomb sandwich structure panel compression stress assessment method Active CN109507040B (en)

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CN112033796A (en) * 2020-07-29 2020-12-04 成都飞机工业（集团）有限责任公司 Testing tool and testing method for bending mechanical property of honeycomb sandwich structure
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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Publication number Priority date Publication date Assignee Title
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
CN112033796A (en) * 2020-07-29 2020-12-04 成都飞机工业（集团）有限责任公司 Testing tool and testing method for bending mechanical property of honeycomb sandwich structure
CN112033796B (en) * 2020-07-29 2022-04-08 成都飞机工业（集团）有限责任公司 Testing tool and testing method for bending mechanical property of honeycomb sandwich structure

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