CN107356404A - A kind of plate member formula wing aerodynamic elasticity model in wind tunnel - Google Patents
A kind of plate member formula wing aerodynamic elasticity model in wind tunnel Download PDFInfo
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- CN107356404A CN107356404A CN201710569515.7A CN201710569515A CN107356404A CN 107356404 A CN107356404 A CN 107356404A CN 201710569515 A CN201710569515 A CN 201710569515A CN 107356404 A CN107356404 A CN 107356404A
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- wing
- aileron
- aerofoil
- stiffness
- stiffness simulation
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a kind of plate member formula wing aerodynamic elasticity model in wind tunnel, it includes wing-body, stiffness simulation flat board, aileron simulated block and aileron stiffness simulation block, in wing-body plane, according to the structural form and resemblance of aerofoil, aerofoil bending, torsional rigidity distribution are calculated；Then whole main plane is divided into some small aerofoils according to profile, in order to ensure to calculate the accurate of analysis, it is divided into 30 40 parts, the thickness of each small aerofoil is set to adjust by obtained bending, torsional rigidity distribution, final realize is distributed by characterizing the stiffness simulation flat board of each small aerofoil rigidity to simulate the bending stiffness of whole wing structure and torsional rigidity, the stiffness simulation flat board of different-thickness is manufactured on same casting and is process, wing-body is obtained, aileron simulated block is connected with wing-body with aileron stiffness simulation block.The Elasticity test model constructed using the method can effectively simulate wing rigidity, ensure the precision needs of elasticity test, and significantly reduced-order models design and process time.
Description
Technical field
The present invention relates to a kind of test model, more particularly to a kind of plate member formula wing aerodynamic elasticity model in wind tunnel.
Background technology
Aircraft aeroelasticity wind tunnel test is for research aircraft aeroelastic effect and the flutter experiment that a situation arises, science
Effective simulation aircraft wing Stiffness Distribution is to research and analyse the necessary condition of aircraft aeroelastic characteristic.In wind tunnel test,
The Stiffness Distribution of actual airplane is simulated with elasticity analog model.Traditional elastic similar test model is typically by the true of aircraft
Structure carries out contracting ratio, and this structure design form is extremely complex, and the mould processing cycle is very long, constrains wind tunnel test progress.
Accordingly, it is desirable to provide a kind of new technical scheme solves the above problems.
The content of the invention
The technical problem to be solved in the invention is to provide a kind of plate member formula wing aerodynamic elasticity model in wind tunnel.
To solve the technical problem of the present invention, the present invention provides a kind of plate member formula wing aerodynamic elasticity model in wind tunnel,
It includes wing-body, stiffness simulation flat board, aileron simulated block and aileron stiffness simulation block,
In wing-body plane, according to the structural form and resemblance of aerofoil, aerofoil bending, torsional rigidity distribution are calculated；
Then whole main plane is divided into some small aerofoils according to profile, in order to ensure to calculate the accurate of analysis and conveniently be divided into
30-40 parts, the thickness of each small aerofoil is set to adjust by obtained bending, torsional rigidity distribution, final realization passes through table
The stiffness simulation flat board for levying each small aerofoil rigidity is distributed to simulate the bending stiffness of whole wing structure and torsional rigidity, different thick
The stiffness simulation flat board of degree is manufactured on same casting and is process, and obtains wing-body, and aileron simulated block is used with wing-body
Aileron stiffness simulation block connects.
Total is using same material part according to each small aerofoil（Stiffness simulation flat board, aileron simulated block, aileron rigidity mould
Intend block）Thickness directly mill out, all parts is are rigidly connected, and the thickness of each several part shows the size of its coupling stiffness.
Beneficial effects of the present invention：The Elasticity test model constructed using the method can effectively simulate wing rigidity, ensure
The precision of elasticity test needs, and significantly reduced-order models design and process time.
Brief description of the drawings
Fig. 1 is the front view of the flat layout Elasticity test model of the present invention.
Fig. 2 is plate layout's formula Elasticity test model stereogram of the present invention.
1st, wing-body, 2, stiffness simulation flat board, 3, aileron simulated block, 4, aileron stiffness simulation block.
Embodiment
The invention will be further described with specific embodiment below in conjunction with the accompanying drawings.Following examples are merely to illustrate this hair
It is bright, it is not limited to protection scope of the present invention.
As illustrated in fig. 1 and 2, a kind of plate member formula wing aerodynamic elasticity model in wind tunnel of the invention, it includes wing master
Body 1, stiffness simulation flat board 2, aileron simulated block 3 and aileron stiffness simulation block 4,
In the plane of wing-body 1, according to the structural form and resemblance of aerofoil, aerofoil bending, torsional rigidity distribution are calculated；
Then whole main plane is divided into some small aerofoils according to profile, in order to ensure to calculate the accurate of analysis and conveniently be divided into
30-40 parts, the thickness of each small aerofoil is set to adjust by obtained bending, torsional rigidity distribution, final realization passes through table
The stiffness simulation flat board for levying each small aerofoil rigidity is distributed to simulate the bending stiffness of whole wing structure and torsional rigidity, different thick
The stiffness simulation flat board of degree is manufactured on same casting and is process, and obtains wing-body 1, aileron simulated block 3 and wing-body 1
Connected with aileron stiffness simulation block 4.
The present invention, according to wing model Stiffness Distribution situation, the contracting of true wing rigidity is compared into model wing rigidity；According to
Wing profile is divided into some trapezoidal, and piecemeal is more in theory, and stiffness simulation is more accurate, to common engineering problem, 30-40 blocks
Meet rigidity requirement；For each segmented areas, bent in itself according to aerofoil, each trapezoidal small airfoil thickness of torsional rigidity trim makes it
Mutually fitted with corresponding region bending, torsional rigidity；According to Stiffness Distribution, the flat layout elastic model side of thickness change is obtained
Case, this scheme can be with the whole wing Stiffness Distributions of accurate simulation.
In order to preferably ensure the accuracy of rigidity of model, for the region for being difficult to coordinate the distribution of bending rigidity, Ke Yi
Partial enlargement subdivision is further continued on the basis of existing small aerofoil.
The Elasticity test model constructed using the method can effectively simulate wing rigidity, ensure the precision of elasticity test and need
Will, and significantly reduced-order models design and process time.
Claims (1)
- A kind of 1. plate member formula wing aerodynamic elasticity model in wind tunnel, it is characterised in that：It includes wing-body, stiffness simulation is put down Plate, aileron simulated block and aileron stiffness simulation block,In wing-body plane, according to the structural form and resemblance of aerofoil, aerofoil bending, torsional rigidity distribution are calculated；Then whole main plane is divided into some small aerofoils according to profile, in order to ensure to calculate the accurate of analysis, is divided into 30- 40 parts, the thickness of each small aerofoil is set to adjust by obtained bending, torsional rigidity distribution, it is final to realize by characterizing respectively The stiffness simulation flat board of small aerofoil rigidity is distributed to simulate the bending stiffness of whole wing structure and torsional rigidity, different-thickness Stiffness simulation flat board is manufactured on same casting and is process, and obtains wing-body, aileron simulated block and wing-body aileron Stiffness simulation block connects.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201710569515.7A CN107356404B (en) | 2017-07-13 | 2017-07-13 | A kind of plate member formula wing aerodynamic elasticity model in wind tunnel |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710569515.7A CN107356404B (en) | 2017-07-13 | 2017-07-13 | A kind of plate member formula wing aerodynamic elasticity model in wind tunnel |
Publications (2)
| Publication Number | Publication Date |
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| CN107356404A true CN107356404A (en) | 2017-11-17 |
| CN107356404B CN107356404B (en) | 2019-11-12 |
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| CN201710569515.7A Active CN107356404B (en) | 2017-07-13 | 2017-07-13 | A kind of plate member formula wing aerodynamic elasticity model in wind tunnel |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110887633A (en) * | 2019-12-25 | 2020-03-17 | 中国航空工业集团公司西安飞机设计研究所 | Elastic gust response wind tunnel test device |
| CN111428399A (en) * | 2020-03-06 | 2020-07-17 | 中国航天空气动力技术研究院 | Design method of wing rudder surface full-elasticity model with unknown rigidity distribution |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0727665A (en) * | 1993-07-08 | 1995-01-31 | Mitsubishi Heavy Ind Ltd | Model for testing aeroelasticity |
| CN103678762A (en) * | 2013-09-29 | 2014-03-26 | 北京航空航天大学 | Optimal scaling modeling method of aeroelasticity wind-tunnel model of composite material wing |
| CN104933250A (en) * | 2015-06-23 | 2015-09-23 | 中国航空工业集团公司西安飞机设计研究所 | Wing aerodynamics modeling method |
| 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 |
| CN105975706A (en) * | 2016-05-16 | 2016-09-28 | 中国航空工业集团公司西安飞机设计研究所 | Scheme stage wing parameter estimation method |
-
2017
- 2017-07-13 CN CN201710569515.7A patent/CN107356404B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0727665A (en) * | 1993-07-08 | 1995-01-31 | Mitsubishi Heavy Ind Ltd | Model for testing aeroelasticity |
| CN103678762A (en) * | 2013-09-29 | 2014-03-26 | 北京航空航天大学 | Optimal scaling modeling method of aeroelasticity wind-tunnel model of composite material wing |
| CN104933250A (en) * | 2015-06-23 | 2015-09-23 | 中国航空工业集团公司西安飞机设计研究所 | Wing aerodynamics modeling method |
| 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 |
| CN105975706A (en) * | 2016-05-16 | 2016-09-28 | 中国航空工业集团公司西安飞机设计研究所 | Scheme stage wing parameter estimation method |
Non-Patent Citations (2)
| Title |
|---|
| 吴强等: "考虑结构动力学与颤振约束的颤振缩比模型优化设计", 《航空学报》 * |
| 成志清等: "机翼颤振模型的结构动力学设计", 《振动工程学报》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110887633A (en) * | 2019-12-25 | 2020-03-17 | 中国航空工业集团公司西安飞机设计研究所 | Elastic gust response wind tunnel test device |
| CN111428399A (en) * | 2020-03-06 | 2020-07-17 | 中国航天空气动力技术研究院 | Design method of wing rudder surface full-elasticity model with unknown rigidity distribution |
| CN111428399B (en) * | 2020-03-06 | 2022-10-28 | 中国航天空气动力技术研究院 | Design method of wing rudder surface full-elasticity model with unknown rigidity distribution |
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| CN107356404B (en) | 2019-11-12 |
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