CN107679318A - A kind of aircraft thin-wall construction posting characteristic becomes material model test design method - Google Patents

A kind of aircraft thin-wall construction posting characteristic becomes material model test design method Download PDF

Info

Publication number
CN107679318A
CN107679318A CN201710901390.3A CN201710901390A CN107679318A CN 107679318 A CN107679318 A CN 107679318A CN 201710901390 A CN201710901390 A CN 201710901390A CN 107679318 A CN107679318 A CN 107679318A
Authority
CN
China
Prior art keywords
model test
prototype
model
aircraft
wall construction
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201710901390.3A
Other languages
Chinese (zh)
Inventor
柴慧
赵占文
张磊
李健
侯瑞
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Xian Aircraft Design and Research Institute of AVIC
Original Assignee
Xian Aircraft Design and Research Institute of AVIC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Xian Aircraft Design and Research Institute of AVIC filed Critical Xian Aircraft Design and Research Institute of AVIC
Priority to CN201710901390.3A priority Critical patent/CN107679318A/en
Publication of CN107679318A publication Critical patent/CN107679318A/en
Pending legal-status Critical Current

Links

Classifications

    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Theoretical Computer Science (AREA)
  • Geometry (AREA)
  • General Physics & Mathematics (AREA)
  • Evolutionary Computation (AREA)
  • General Engineering & Computer Science (AREA)
  • Computer Hardware Design (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Computational Mathematics (AREA)
  • Mathematical Analysis (AREA)
  • Mathematical Optimization (AREA)
  • Pure & Applied Mathematics (AREA)
  • Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)

Abstract

The present invention relates to a kind of aircraft thin-wall construction posting characteristic to become material model test design method, and it includes：First：Determine the scaling of the appearance and size of model test part, structure erect-position and structural thickness；Second：Determine the material of model test part；3rd：The likelihood ratio of aircraft prototype and the physical quantity of model test part under plane stress state is determined according to similar index；4th：The load of model test part is calculated according to the load of aircraft prototype and the likelihood ratio, last remaining physical quantity that model test part is measured according to the load for putting on model test part, and the result of the test of Extrapolation aircraft prototype.Aircraft thin-wall construction posting characteristic provided by the invention, which becomes material model test design method, can eliminate engineering manufacture difficulty；Change the material of model test, use the material that the stock cycle is short, cheap；Exponentially shorten test period and scale, it is cost-effective；Reduce the design risk of aircraft definition stage.

Description

A kind of aircraft thin-wall construction posting characteristic becomes material model test design method
Technical field
The invention belongs to Vehicle Structure Strength experimental technique field, more particularly to a kind of aircraft thin-wall construction posting are special Property become material model test design method.
Background technology
In Aircraft structural design definition stage, it is necessary to verify the posting of structure by designing Static Model experiment Characteristic, accurate rapid evaluation is carried out to the structure efficiency of different schemes, verifies Numerical results.
In existing Aircraft structural design method, the general design method for using model test.But in modelling If scaling is larger, the thickness of aircraft thin-wall construction is scaled with face inside dimension using identical, then in Practical Project system Can have that to be difficult to the manufacture that overcomes difficult during making, if the thickness of vehicle construction material is 2mm, scaling is 20 (mistakes Greatly), then moulded dimension thickness is 0.1mm, and for the manufacturing, technology controlling and process is difficult；If the material used in prototype The stock cycle is long, expensive, still will certainly increase experimentation cost using identical material in model test.
Therefore, seek aircraft thin-wall construction posting characteristic change material model test design method to be very important.
The content of the invention
It is an object of the invention to provide a kind of aircraft thin-wall construction posting characteristic to become material model test design method, uses In any of the above-described problem of solution.
To reach above-mentioned purpose, the technical solution adopted by the present invention is：A kind of aircraft thin-wall construction posting characteristic becomes material Expect model test design method, it includes：
First：Determine the scaling of the appearance and size of model test part, structure erect-position and structural thickness；
Second：Determine the material of model test part, the Poisson ratio error of model test part material and aircraft leiomyoma cells Not higher than 5%；
3rd：The phase of aircraft prototype and the physical quantity of model test part under plane stress state is determined according to similar index Like than；
4th：The load of model test part is calculated according to the load of aircraft prototype and the likelihood ratio, finally Load according to model test part is put on measures remaining physical quantity of model test part, and the examination of Extrapolation aircraft prototype Test result.
Further, model test design method of the invention is applied to thickness t and length when aircraft thin-wall construction Or width b ratio is under conditions of t/b≤(1/100~1/80).
Further, in first, the scaling of model test part determines that method is：
Appearance and size pantograph ratio：CL=LPrototype/LModel
The coordinate ratio of structure erect-position：CL=xPrototype/xModel=yPrototype/yModel=zPrototype/zModel
Structural thickness pantograph ratio ratio：Ct=LPrototype/LModel。
Further, in second, the material of model test part determines that method is：
Modulus of elasticity：CE=EPrototype/EModelPoisson's ratio：Cμ=μPrototype/μModel≈1。
Further, in the 3rd, the physical quantity includes load, displacement, stress and strain, and remaining described physical quantity The likelihood ratio determine that method is：
Stress similitude ratio：Cσ=σPrototype/σModel
Strain the likelihood ratio：Cε=εPrototype/εModel
The displacement likelihood ratio：Cδ=δPrototype/δModel
The area power likelihood ratio：Cq=qPrototype/qModel
In above formula：Q is the load acted on unit area.
Further, in the 3rd, similar index is：
Geometric equation：
Physical equation：
Force boundary condition：
If load is concentrated force or concentrated moment, corresponding similar index is：
Concentrated force：
Concentrated moment：
Further, in the 4th, ensure that aircraft prototype and the strain likelihood ratio in model test part are constant first, i.e. Cε =1, afterwards according to apply in similar index computation model testpieces load and measured displacement, the relation of stress and prototype It is not：
Further, in model test, ensure that model test part and aircraft prototype have identical constraint, application Load meets following relational expression：
The load series of application 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 aircraft prototype of following relational expression：
Displacement：δPrototype=CLδModel
Strain：εPrototype=εModel
Stress：σPrototype=CEσModel。
Further, 40% value on the basis of the load series of application is adjusted.
Aircraft thin-wall construction posting characteristic provided by the invention, which becomes material model test design method, can eliminate engineering Manufacture is difficult；Change the material of model test, use the material that the stock cycle is short, cheap；Exponentially shorten the test period It is cost-effective with scale；Reduce the design risk of aircraft definition stage.
Brief description of the drawings
Accompanying drawing herein is merged in specification and forms the part of this specification, shows the implementation for meeting the present invention Example, and for explaining principle of the invention together with specification.
Fig. 1 is the model test design method flow chart of the present invention.
Embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.
When the thickness of aircraft thin-wall construction is much smaller than length and width (thickness t and length or wide b ratio meet t/b≤ (1/100~1/80)), it is in plane stress (membrane stress) state, can adjust the scaling of structural thickness within the specific limits Ratio.The stress intensity and stress distribution of aircraft thin-wall construction are relevant with the Poisson's ratio of material, but work as model test institute When the Poisson's ratio of material selection is close with prototype, influence of the Poisson's ratio to model test result is smaller, and error is controllable.Therefore originally Invention provides aircraft thin-wall construction posting characteristic and becomes material model test design method, can design a kind of model test part, The related data that corresponding experiment can obtain aircraft prototype is carried out to model test part, R＆D costs are greatly decreased, improve efficiency, Therefore the present invention provides aircraft thin-wall construction posting characteristic change material model test design method and included：
First：Determine the scaling of the appearance and size of model test part, structure erect-position and structural thickness；
Second：Determine the material of model test part, the Poisson ratio error of model test part material and aircraft leiomyoma cells Not higher than 5%；
3rd：The phase of aircraft prototype and the physical quantity of model test part under plane stress state is determined according to similar index Like than；
4th：The load of model test part is calculated according to the load of aircraft prototype and the likelihood ratio, finally Load according to model test part is put on measures remaining physical quantity of model test part, and the examination of Extrapolation aircraft prototype Test result.
In order that the above method is more directly perceived specific, below the present embodiment the present invention is said with one group of specific data It is bright：By taking certain Flight Vehicle Structure posting characteristic model experimental design as an example, appearance and size and the structure erect-position of model test part reduce To the 1/5 of aircraft prototype, the structural thickness of model test part narrows down to the 1/2 of aircraft prototype, what model test part was selected Elasticity modulus of materials is the 1/30 of aircraft leiomyoma cells.
Model test design includes：
First：The scaling (ensureing that thin-wall construction is in plane stress state) of preference pattern testpieces
Appearance and size：LPrototype/LModel=CL=5
Structure erect-position coordinate：xPrototype/xModel=yPrototype/yModel=zPrototype/zModel=CL=5
Structural thickness：LPrototype/LModel=Ct=2
Second：Select suitable model test part material, the material of model test part material and the material of aircraft prototype Poisson's ratio it is as far as possible identical, in the case of it can not ensure identical, its error is not higher than 5%, in the present embodiment with Poisson's ratio about Calculated exemplified by equal to 1：
Modulus of elasticity：EPrototype/EModel=CE=30 Poisson's ratios：μPrototype/μModel=Cμ≈1
3rd：Set the likelihood ratio of other physical quantitys
Stress similitude ratio：Cσ=σPrototype/σModel
Strain the likelihood ratio：Cε=εPrototype/εModel
The displacement likelihood ratio：Cδ=δPrototype/δModel
The area power likelihood ratio：Cq=qPrototype/qModel
Q is the load acted on unit area in above formula.
4th：Following similar index is exported according to the theory of similarity and equational analysis and (stress that is only limited in face, answers variation Amount)：
Geometric equation：
Physical equation：
Force boundary condition：
Corresponding similar index is if load is concentrated force or concentrated moment：
Concentrated force：
Concentrated moment：
5th：Ensure that prototype and the strain in model are constant, i.e. Cε=1.Tested according to similar index computation model in (4) The load of middle application and the relation of measured displacement, stress and aircraft prototype are respectively
6th：In model test, ensure that there is identical constraint with prototype, and apply following load
The load series of application is adjusted by model test measured displacement, strain on the basis of linearity range, is typically taken 40%.And the linearity range physical quantity by being measured in model test, according to the anti-physical quantity for pushing away prototype of following relational expression：
Displacement：δPrototype=5 δModel
Strain：εPrototype=εModel
Stress：σPrototype=30 σModel
It is that can obtain the correlation test data of aircraft prototype by as above step.
The present invention provides a kind of aircraft thin-wall construction posting characteristic and becomes material model test design method with following excellent Point：The scaling of (guarantee structure is in plane stress state) adjustment structural thickness within the specific limits, eliminates engineering manufacture On difficulty；Stock cycle short, the cheap material that model test uses, reduces material cost；Exponentially shorten examination Test cycle and scale, cut down time cost, improve airplane design efficiency；Actual aircraft is replaced using model, reduces aircraft The design risk of definition stage；The model test method of the present invention is workable, and experimental design is convenient；Can be to aircraft The posting characteristic of design structure layout carries out rapid evaluation.
It is described above, it is only the optimal embodiment of the present invention, but protection scope of the present invention is not limited thereto, Any one skilled in the art the invention discloses technical scope in, the change or replacement that can readily occur in, It should all be included within the scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of the claim Enclose and be defined.

Claims (9)

1. a kind of aircraft thin-wall construction posting characteristic becomes material model test design method, it is characterised in that including：
First：Determine the scaling of the appearance and size of model test part, structure erect-position and structural thickness；
Second：Determine the material of model test part, the Poisson ratio error of model test part material and aircraft leiomyoma cells is not high In 5%；
3rd：Determine that aircraft prototype is similar to the physical quantity of model test part under plane stress state according to similar index Than；
4th：The load of model test part, last basis are calculated according to the load of aircraft prototype and the likelihood ratio The load for putting on model test part measures remaining physical quantity of model test part, and the experiment knot of Extrapolation aircraft prototype Fruit.
2. aircraft thin-wall construction posting characteristic according to claim 1 becomes material model test design method, its feature It is, model test design method of the invention is applied at the thickness t and length or width b ratio of aircraft thin-wall construction Under conditions of t/b≤(1/100~1/80).
3. aircraft thin-wall construction posting characteristic according to claim 2 becomes material model test design method, its feature It is, in first, the scaling of model test part determines that method is：
Appearance and size pantograph ratio：CL=LPrototype/LModel
The coordinate ratio of structure erect-position：CL=xPrototype/xModel=yPrototype/yModel=zPrototype/zModel
Structural thickness pantograph ratio ratio：Ct=LPrototype/LModel。
4. aircraft thin-wall construction posting characteristic according to claim 2 becomes material model test design method, its feature It is, in second, the material of model test part determines that method is：
Modulus of elasticity：CE=EPrototype/EModelPoisson's ratio：Cμ=μPrototype/μModel≈1。
5. aircraft thin-wall construction posting characteristic according to claim 2 becomes material model test design method, its feature It is, in the 3rd, the physical quantity includes load, displacement, stress and strain, and the likelihood ratio of remaining physical quantity determines Method is：
Stress similitude ratio：Cσ=σPrototype/σModel
Strain the likelihood ratio：Cε=εPrototype/εModel
The displacement likelihood ratio：Cδ=δPrototype/δModel
The area power likelihood ratio：Cq=qPrototype/qModel
In above formula：Q is the load acted on unit area.
6. aircraft thin-wall construction posting characteristic according to claim 2 becomes material model test design method, its feature It is, in the 3rd, similar index is：
Geometric equation：
Physical equation：
Force boundary condition：
If load is concentrated force or concentrated moment, corresponding similar index is：
Concentrated force：
Concentrated moment：
7. aircraft thin-wall construction posting characteristic according to claim 2 becomes material model test design method, its feature It is, in the 4th, ensures that aircraft prototype and the strain likelihood ratio in model test part are constant first, i.e. Cε=1, basis afterwards The load and measured displacement that applies in similar index computation model testpieces, the relation of stress and prototype are respectively：
8. aircraft thin-wall construction posting characteristic according to claim 2 becomes material model test design method, its feature It is, in model test, ensures that model test part and aircraft prototype have an identical constraint, the load of application meets as follows Relational expression：
The load series of application 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 aircraft prototype of following relational expression：
Displacement：δPrototype=CLδModel
Strain：εPrototype=εModel
Stress：σPrototype=CEσModel。
9. aircraft thin-wall construction posting characteristic according to claim 8 becomes material model test design method, its feature It is, 40% value on the basis of the load series of application is adjusted.
CN201710901390.3A 2017-09-28 2017-09-28 A kind of aircraft thin-wall construction posting characteristic becomes material model test design method Pending CN107679318A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201710901390.3A CN107679318A (en) 2017-09-28 2017-09-28 A kind of aircraft thin-wall construction posting characteristic becomes material model test design method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201710901390.3A CN107679318A (en) 2017-09-28 2017-09-28 A kind of aircraft thin-wall construction posting characteristic becomes material model test design method

Publications (1)

Publication Number Publication Date
CN107679318A true CN107679318A (en) 2018-02-09

Family

ID=61138532

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201710901390.3A Pending CN107679318A (en) 2017-09-28 2017-09-28 A kind of aircraft thin-wall construction posting characteristic becomes material model test design method

Country Status (1)

Country Link
CN (1) CN107679318A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108763605A (en) * 2018-03-08 2018-11-06 南京航空航天大学 A kind of airworthiness design method of the mars device based on the principle of similitude
CN113504025A (en) * 2021-09-13 2021-10-15 中国航天空气动力技术研究院 Dynamic load testing method for wind tunnel with large attack angle and low frequency structure

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104763001A (en) * 2015-04-21 2015-07-08 山东大学 Testing device and testing method suitable for creep property of anchor cable anchoring segment
CN104833538A (en) * 2015-02-17 2015-08-12 北京交通大学 Similarity model test method for simulating tunnel construction
CN106697328A (en) * 2016-12-15 2017-05-24 中国航空工业集团公司西安飞机设计研究所 Same-material model experimental design method for load transfer characteristic of aircraft thin-wall structure
CN106840721A (en) * 2016-12-15 2017-06-13 中国航空工业集团公司西安飞机设计研究所 A kind of Flight Vehicle Structure posting characteristic model test design method

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104833538A (en) * 2015-02-17 2015-08-12 北京交通大学 Similarity model test method for simulating tunnel construction
CN104763001A (en) * 2015-04-21 2015-07-08 山东大学 Testing device and testing method suitable for creep property of anchor cable anchoring segment
CN106697328A (en) * 2016-12-15 2017-05-24 中国航空工业集团公司西安飞机设计研究所 Same-material model experimental design method for load transfer characteristic of aircraft thin-wall structure
CN106840721A (en) * 2016-12-15 2017-06-13 中国航空工业集团公司西安飞机设计研究所 A kind of Flight Vehicle Structure posting characteristic model test design method

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108763605A (en) * 2018-03-08 2018-11-06 南京航空航天大学 A kind of airworthiness design method of the mars device based on the principle of similitude
CN108763605B (en) * 2018-03-08 2023-09-29 南京航空航天大学 Airworthiness design method of Mars aircraft based on similar principle
CN113504025A (en) * 2021-09-13 2021-10-15 中国航天空气动力技术研究院 Dynamic load testing method for wind tunnel with large attack angle and low frequency structure
CN113504025B (en) * 2021-09-13 2021-12-14 中国航天空气动力技术研究院 Dynamic load testing method for wind tunnel with large attack angle and low frequency structure

Similar Documents

Publication Publication Date Title
CN105183996B (en) Face element amendment and the advance self-adaptive computing method of grid
CN106840721B (en) A kind of Flight Vehicle Structure posting characteristic model test design method
Hariharan et al. Simulation of rotor in hover: Current state, challenges and standardized evaluation
CN104298818B (en) A kind of end mill processing surface error prediction and emulation mode
CN105022898B (en) A kind of the crack performance measurement and optimization method of adhesive bonding of composites structure
CN104149340B (en) The method obtaining metal parts performance based on 3D printing technique
CN104809273A (en) Creep deformation describing method
CN107391891A (en) A kind of high aspect ratio wing Optimization Design based on Model Fusion method
CN107679318A (en) A kind of aircraft thin-wall construction posting characteristic becomes material model test design method
Chen et al. Modelling complex geometry using solid finite element meshes with correct composite material orientations
CN100461192C (en) Simulating method for resin flow and limanite deformed in resin-base composite L-shaped laminate forming
JP5264380B2 (en) Structural analysis method
CN110188378A (en) A kind of aerodynamic data fusion method neural network based
CN103018426A (en) Soft measurement method for sizing percentage during yarn-sizing process based on Bagging
CN111859813B (en) Optimization method for selecting discrete speed coordinate points in pneumatic theory unified algorithm
CN107992709A (en) Thermal-structure model modification method based on intermediate function
CN106697328B (en) A kind of aircraft thin-wall construction posting characteristic is the same as material model test design method
US11059240B2 (en) Method of designing a plybook for a composite component
Kumar An application of Taguchi’s technique to improve the accuracy of rapid prototyped FDM parts
CN109885896A (en) A kind of nonlinear organization correction method for finite element model based on multiple change differential sensitivity
Masters et al. Kestrel Results on a 2D Cut of the High Lift Common Research Model Wing
CN108536954A (en) A kind of high-precision Lattice Boltzmann Method based on intersection point interruption gal the Liao Dynasty gold
Bohnenberger et al. Sensing material systems-novel design strategies
CN109631813A (en) A kind of scaling method of large scale articulated arm coordinate measuring machine
CN104298213A (en) Index time varying gain type iterative learning control algorithm based on reference batch

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
RJ01 Rejection of invention patent application after publication

Application publication date: 20180209

RJ01 Rejection of invention patent application after publication