CN106697328A - Same-material model experimental design method for load transfer characteristic of aircraft thin-wall structure - Google Patents
Same-material model experimental design method for load transfer characteristic of aircraft thin-wall structure Download PDFInfo
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- CN106697328A CN106697328A CN201611160306.9A CN201611160306A CN106697328A CN 106697328 A CN106697328 A CN 106697328A CN 201611160306 A CN201611160306 A CN 201611160306A CN 106697328 A CN106697328 A CN 106697328A
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Abstract
The invention belongs to the technical field of structure/strength experiments and relates to a same-material model experimental design method for the load transfer characteristic of an aircraft thin-wall structure. By adoption of the same-material model experimental design method for the load transfer characteristic of the aircraft thin-wall structure, the scaling of the structure thickness can be adjusted to eliminate difficulties in engineering manufacture when it is ensured that the structure is within a plane stress state range; and the experiment period can be exponentially shortened through model experiments, the experiment scale can be exponentially decreased through the model experiments, the cost is saved, and the design risk of an aircraft in a project demonstration stage is lowered.
Description
Technical field
The invention belongs to structure/strength test technical field, it is related to a kind of same material of aircraft thin-wall construction posting characteristic
Model test method for designing.
Background technology
For specific Aircraft structural design scheme, it is necessary to by Static Model test, structure efficiency is carried out accurately,
Rapid evaluation, verifies Numerical results.All external applied loads that aircraft thin-wall construction bears are main by loads in plane balance, example
As above the tension and compression of lower wall panels and the common bending for resisting wing of the shearing of web, covering, rib web, the shearing resistance of web
The torsion of wing.
When Static Model experiment is designed come the posting characteristic for verifying structure, if scaling is larger, the thickness of thin-wall construction
Degree uses identical scaling with face inside dimension, can there is the difficulty for being difficult to overcome in Practical Project manufacturing process.Therefore,
Need to seek the Static Model test design method of aircraft thin-wall construction.
The content of the invention
The purpose of the present invention：A kind of aircraft thin-wall construction posting characteristic is provided with material model test design method, pin
Engineering manufacture is eliminated to larger scaling difficult.
Technical scheme：A kind of aircraft thin-wall construction posting characteristic with material model test design method, its
It is characterised by, described method comprises the following steps：
StepOne, determine the appearance and size and thickness scaling of prototype：LPrototype/LModel=CL、tPrototype/tModel=Ct；And select
Select and prototype identical material, elastic modelling quantity CE=EPrototype/EModel=1, Poisson's ratio Cμ=μPrototype/μModel=1；
Wherein, the scaling of thin-wall construction thickness is adjusted, it is ensured that the thickness t of thin-wall construction and length or width b'sThan meeting
t/b≤1/80；
Set the likelihood ratio of other physical quantitys, stress similitude ratio：Cσ=σPrototype/σModel；The strain likelihood ratio：Cε=εPrototype/εModel；
The displacement likelihood ratio：Cδ=δPrototype/δModel；The area power likelihood ratio：Cq=qPrototype/qModel；
Step 2, following similar index is derived according to the theory of similarity and equational analysis
Geometric equation：
Physical equation：
Force boundary condition：
Above-mentioned similar index is only limited to stress, the components of strain in face, and q here is the load acted on unit area,
Corresponding similar index is if load is concentrated force or concentrated moment：
Concentrated force：
Concentrated moment：
Step 3, it is ensured that prototype is constant with ess-strain in model, i.e. Cε=1, Cσ=1.According to similar finger in step 2
The load and the relation of measured displacement and prototype applied in mark computation model experiment
In model test, it is ensured that with prototype there is identical to constrain, and apply following load
The load series of applying is adjusted by model test measured displacement, strain on the basis of linearity range, and by mould
The linearity range physical quantity measured in type experiment, according to the anti-physical quantity for pushing away prototype of following relational expression：
Displacement：δPrototype=δModelCL
Strain：εPrototype=εModel
Stress：σPrototype=σModel。
Beneficial effects of the present invention：The present invention provides a kind of aircraft thin-wall construction posting characteristic and is set with material model experiment
Meter method, can eliminate engineering in the scaling for ensureing structure adjustment structural thickness in the range of plane stress state
Manufacture is difficult.Test period and scale can exponentially be shortened by model test, it is cost-effective, and reduce aircraft scheme opinion
The design risk in card stage.
Specific embodiment
By taking certain Flight Vehicle Structure posting characteristic model experimental design as an example.Appearance and size narrows down to original with structure erect-position
1/5, structural thickness narrows down to original 1/2.Model test design is carried out below：
(1) scaling of preference pattern experiment, it is ensured that thin-wall construction is in plane stress state,
Appearance and size LPrototype/LModel=CL=5
Structure erect-position coordinate xPrototype/xTouch type=yPrototype/yTouch type=zPrototype/zTouch type=CL=5
Structural thickness LPrototype/LModel=Ct=2
(2) identical material is selected
Elastic modelling quantity：CE=EPrototype/EHorizontal type=1 Poisson's ratio：Cμ=μPrototype/μHorizontal type=1
(3) likelihood ratio (being only limited to in-plane displacement, stress, the components of strain) of other physical quantitys is set
Stress similitude ratio：Cσ=σPrototype/σModel
The strain likelihood ratio：Cε=εPrototype/εModel
The displacement likelihood ratio：Cδ=δPrototype/δModel
The area power likelihood ratio：Cq=qPrototype/qModel
(4) following similar index is derived according to the theory of similarity and equational analysis
Geometric equation：
Physical equation：
Force boundary condition：
Here q is the load acted on unit area.It is corresponding similar if load is concentrated force or concentrated moment
Index is：
Concentrated force：
Concentrated moment：
(5) ensure that prototype is constant with ess-strain in model, i.e. Cε=1, Cσ=1.Calculated according to similar index in (4)
The relation of the load applied in model test and measured displacement and prototype
(6) in model test, it is ensured that with prototype there is identical to constrain, and following load is applied
The load series of applying is adjusted by model test measured displacement, strain on the basis of linearity range, is typically taken
40% limit load.And the linearity range physical quantity by being measured in model test, according to the anti-physics for pushing away prototype of following relational expression
Amount, the posting characteristic of analytical structure
Displacement：δPrototype=5 δModel
Strain：εPrototype=εModel
Stress：σPrototype=σModel。
Claims (1)
1. a kind of aircraft thin-wall construction posting characteristic is with the method for material model experimental design ten thousand, it is characterised in that described method
Comprise the following steps：
StepOne, determine the appearance and size and thickness scaling of prototype：LPrototype/LModel=CL、tPrototype/tModel=Ct；And select with
Prototype identical material, elastic modelling quantity CE=EPrototype/EModel=1, Poisson's ratio Cμ=μPrototype/μModel=1；
Wherein, the scaling of thin-wall construction thickness is adjusted, it is ensured that the thickness t of thin-wall construction and length or width b'sThan meetingt/b≤
1/80；
Set the likelihood ratio of other physical quantitys, stress similitude ratio：Cσ=σPrototype/σModel；The strain likelihood ratio：Displacement
The likelihood ratio：Cδ=δPrototype/δModel；The area power likelihood ratio：Cq=qPrototype/qModel；
Step 2, the root Ju theory of similarity derives following similar index with equational analysis
Geometric equation：
Physical equation：
Force boundary condition：
Above-mentioned similar index is only limited to stress, the components of strain in face, and q here is the load acted on unit area, if
For concentrated force or concentrated moment, then corresponding similar index is load：
Concentrated force：
Concentrated moment：
Step 3, it is ensured that prototype is constant with ess-strain in model, i.e. Cε=1, Cσ=1.According to similar index meter in step 2
Calculate the relation of load and measured displacement and the prototype applied in model test
In model test, it is ensured that with prototype there is identical to constrain, and apply following load
The load series of applying is adjusted by model test measured displacement, strain on the basis of linearity range, and is tried by model
The linearity range physical quantity measured in testing, according to the anti-physical quantity for pushing away prototype of following relational expression：
Displacement：δPrototype=δModelCL
Strain：εPrototype=εModel
Stress：σPrototype=σModel。
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107679318A (en) * | 2017-09-28 | 2018-02-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft thin-wall construction posting characteristic becomes material model test design method |
| CN111695207A (en) * | 2020-05-06 | 2020-09-22 | 东南大学 | Crane test model design method based on similarity theory |
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| CN103745066A (en) * | 2014-01-21 | 2014-04-23 | 北京航空航天大学 | Determining method for structural stiffness index of high-aspect-ratio wing |
| 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 |
| CN104182565A (en) * | 2014-06-25 | 2014-12-03 | 中国空气动力研究与发展中心超高速空气动力研究所 | Design method of secondary light-gas gun test model |
| CN105109705A (en) * | 2015-08-03 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Method for calculating rigidity of aircraft airfoil surface structure |
| CN105975704A (en) * | 2016-05-13 | 2016-09-28 | 中国航空工业集团公司西安飞机设计研究所 | Airplane suspension joint structure fatigue test design method |
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2016
- 2016-12-15 CN CN201611160306.9A patent/CN106697328B/en active Active
Patent Citations (5)
| 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 |
| CN103745066A (en) * | 2014-01-21 | 2014-04-23 | 北京航空航天大学 | Determining method for structural stiffness index of high-aspect-ratio wing |
| CN104182565A (en) * | 2014-06-25 | 2014-12-03 | 中国空气动力研究与发展中心超高速空气动力研究所 | Design method of secondary light-gas gun test model |
| CN105109705A (en) * | 2015-08-03 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Method for calculating rigidity of aircraft airfoil surface structure |
| CN105975704A (en) * | 2016-05-13 | 2016-09-28 | 中国航空工业集团公司西安飞机设计研究所 | Airplane suspension joint structure fatigue test design method |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107679318A (en) * | 2017-09-28 | 2018-02-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft thin-wall construction posting characteristic becomes material model test design method |
| CN111695207A (en) * | 2020-05-06 | 2020-09-22 | 东南大学 | Crane test model design method based on similarity theory |
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