CN102935897A - Hollow beam for high-speed flutter model with high aspect ratio and production method thereof - Google Patents
Hollow beam for high-speed flutter model with high aspect ratio and production method thereof Download PDFInfo
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- CN102935897A CN102935897A CN2011102327033A CN201110232703A CN102935897A CN 102935897 A CN102935897 A CN 102935897A CN 2011102327033 A CN2011102327033 A CN 2011102327033A CN 201110232703 A CN201110232703 A CN 201110232703A CN 102935897 A CN102935897 A CN 102935897A
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Abstract
The invention relates to a hollow beam for a high-speed flutter model with a high aspect ratio and a production method thereof. The hollow beam is in a rectangular hollow structure, and lug pieces are arranged on two sides of the rectangle. By using the hollow beam provided with the lug pieces, the weight can be reduced while the requirement for three-way rigidity is satisfied, and the overweight problem of transonic velocity flutter models is solved. During production, two symmetrical hat type alloy components are processed firstly, then subjected to high temperature adhesion bond, and connected through rivets, therefore the problem that the rectangular hollow beam structure with variable cross-sections and lug pieces is difficult to process is solved, and the strength requirement can be guaranteed. The hollow beam is simple in design and easy to produce and assemble.
Description
Technical field
The invention belongs to the theory of structure field, relate to a kind of thin-walled beam main force support structure for high aspect ratio wing high speed flutter model.
Background technology
For the airplane flutter pattern layout of high aspect ratio wing, the version of single-beam model is widely used in the structures such as wing, fuselage, empennage.And the high speed flutter model can be used for obtaining the Transonic Flutter characteristic of aircraft and parts thereof.For the design feature of high speed flutter model, usually needing very, girder frame quality provides very large aerofoil rigidity.
The defectives such as method in the past often exists stiffness simulation uncertain, and processing and manufacturing is difficult, and is overweight.It is light how can to design and process a kind of quality, the variable section main force support structure that rigidity is large, and it is particularly important to seem concerning the flutter model designer.
For the main force support structure of high speed flutter model, often exist the problem of the difficult and difficult processing of design: difficult being mainly reflected in of design will be satisfied rigidity greatly and the light designing requirement of quality simultaneously, and rigidity need satisfy the three-dimensional requirement, namely vertically to cross sectional moment of inertia I
x, lateral cross moment of inertia I
y, second polar moment of area J; And for the band auricle thin-walled beam of processing variable section, take Boring machine processing before, very difficult, and the extremely difficult acceptable product that meet design requirement; In addition, under the high speed wind tunnel condition, strength problem is very outstanding, adopts conventional cementing model as easy as rolling off a log by the high velocity air impact failure in test, will be denied at the design initial stage.
Summary of the invention
Be difficult to the deficiencies such as design, processing for solving quality variable section main force support structure light, that rigidity is large, the invention provides a kind of beam with variable cross-section, and can satisfy the three-way rigidity requirement, be difficult for by the box girder of the high speed flutter model of high velocity air impact failure with and preparation method thereof.
A kind of box girder for high aspect ratio wing high speed flutter model has two symmetrical carnival hat type alloy components, adopts riveted joint and the cementing form of high temperature to be fixed into the variable section structure of hollow band auricle between the two.
A kind of method for making of the box girder for high aspect ratio wing high speed flutter model may further comprise the steps:
Step 1: determine to treat the simulated aircraft wing vertically to cross sectional moment of inertia I
Ax, lateral cross moment of inertia I
Ay, second polar moment of area J
a
Step 2: obtain the some cross section property design objectives of model vertically to cross sectional moment of inertia I according to the rigidity scale-relation
x, lateral cross moment of inertia I
y, second polar moment of area J;
Step 3: draw the sectional dimension that satisfies each cross section three-way rigidity requirement in the step 2 by try and cut method and pre-determined box girder walled thickness t and auricle thickness t, comprise the width W of box girder, height H and with the width L of auricle;
Step 4: process carnival hat type alloy components, each cross section relative dimensions of carnival hat type alloy components is: width W, and height H/2, the brim of a hat thickness is t/2, is L with the width of the brim of a hat, and processes rivet hole at the brim of a hat of carnival hat type alloy components;
Step 5: it is cementing that two carnival hat type alloy components are carried out high temperature;
Step 6: two carnival hat type alloy components are connected by rivet.
Further, above-mentioned high temperature is cementing carries out under vacuum condition.
Further, the cementing degree of vacuum of above-mentioned high temperature requires as being higher than 10
-2Pa, temperature is controlled at 120 ℃ ± 5 ℃.
The good effect that the present invention produces: can satisfy simultaneously the large and light designing requirement of quality of rigidity with the auricle box girder, rigidity satisfies the three-dimensional requirement, and has successfully solved overweight problem; The processing of band auricle box girder is simple and easy to do, and the process-cycle is short.Satisfy the design feature that high speed flutter model main force support structure rigidity is large, quality is light, and satisfied the three-way rigidity requirement; The mode that carnival hat type alloy components high temperature is cementing and the later stage rivets is adopted in the processing of box girder, has solved the problem of difficult processing.
Description of drawings
Fig. 1 is the schematic cross-section that the present invention is used for the box girder of high speed flutter model;
Fig. 2 is the schematic perspective view that the present invention is used for the box girder of high speed flutter model;
Wherein, 1: box girder, 2: auricle, 3: rivet, 10: carnival hat type member.
The specific embodiment
Below in conjunction with Figure of description the present invention is described in further detail.
A kind of box girder for the high speed flutter model has two symmetrical carnival hat type members 10, adopts riveted joint and the cementing form of high temperature to be fixed into the variable section structure of hollow band auricle 2 between the two.
A kind of method for making of box girder of high speed flutter model may further comprise the steps:
Step 1: determine to treat the simulated aircraft wing vertically to cross sectional moment of inertia I
Ax, lateral cross moment of inertia I
Ay, second polar moment of area J
a
Step 2: obtain the some cross section property design objectives of model vertically to cross sectional moment of inertia I according to the rigidity scale-relation
x, lateral cross moment of inertia I
y, second polar moment of area J;
Step 3: gather the method calculated and pre-determined box girder 1 walled thickness t and auricle 2 thickness t by examination and draw and satisfy the sectional dimension that each cross section three-way rigidity requires in the step 2, comprise the width W of box girder 1, height H and with the width L of auricle 2;
Step 4: process carnival hat type alloy components 10, each cross section relative dimensions of alloy components is width W, highly is H/2, and the brim of a hat thickness is t/2, is L with the width of the brim of a hat, and processes rivet hole at the brim of a hat of carnival hat type alloy components;
Step 5: it is cementing that two carnival hat type alloy components 10 are carried out high temperature;
Step 6: two carnival hat type alloy components 10 are connected by rivet, with the connection of further reinforcement box girder 1 top and the bottom, finally form variable section main bearing beam structure.
Further, above-mentioned high temperature is cementing carries out under vacuum condition.
Further, the cementing degree of vacuum of above-mentioned high temperature requires to be higher than 10 for degree of vacuum
-2Pa, temperature is controlled at 120 ℃ ± 5 ℃.
Technique effect: the box girder structure with auricle can satisfy the large and light designing requirement of quality of rigidity simultaneously, and rigidity satisfies the three-dimensional requirement, and has successfully solved overweight problem, can meet design requirement, and method of designing is simple; The mode that carnival hat type alloy components high temperature is cementing and the later stage rivets is adopted in the processing of box girder, has solved the problem of difficult processing; For comparatively complicated variable section box girder structure, solved the problem that in the past is difficult to realization by Boring machine processing; And solved the problem of conventional cementing static strength poor performance.Mould processing is simple and easy to do, and the process-cycle is short.
Claims (4)
1. box girder that is used for high aspect ratio wing high speed flutter model, it is characterized in that: having two symmetrical carnival hat type members, adopt riveted joint and the cementing form of high temperature to fix between the two, is the variable section structure of a hollow band auricle.
2. the method for making of a kind of box girder for high aspect ratio wing high speed flutter model according to claim 1 may further comprise the steps:
Step 1: determine to treat the simulated aircraft wing vertically to cross sectional moment of inertia I
Ax, lateral cross moment of inertia I
Ay, second polar moment of area J
a
Step 2: obtain the some cross section property design objectives of model vertically to cross sectional moment of inertia I according to the rigidity scale-relation
x, lateral cross moment of inertia I
y, second polar moment of area J;
Step 3: draw the sectional dimension that satisfies each cross section three-way rigidity requirement in the step 2 by try and cut method and pre-determined box girder walled thickness t and auricle thickness t, comprise the width W of box girder, and with the width L of auricle;
Step 4: process carnival hat type alloy components, each cross section relative dimensions of alloy components is width W, highly is H/2, and the brim of a hat thickness is t/2, is L with the width of the brim of a hat, and processes rivet hole at the brim of a hat of carnival hat type alloy components;
Step 5: it is cementing that two carnival hat type alloy components are carried out high temperature;
Step 6: two carnival hat type alloy components are connected by rivet.
3. the method for making of the box girder of a kind of high speed flutter model according to claim 2, it is characterized in that: high temperature is cementing to carry out under vacuum condition.
4. the method for making of the box girder of a kind of high speed flutter model according to claim 3 is characterized in that: the cementing degree of vacuum of high temperature requires as being higher than 10
-2Pa, temperature is controlled at 120 ℃ ± 5 ℃.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN2011102327033A CN102935897A (en) | 2011-08-15 | 2011-08-15 | Hollow beam for high-speed flutter model with high aspect ratio and production method thereof |
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| CN2011102327033A CN102935897A (en) | 2011-08-15 | 2011-08-15 | Hollow beam for high-speed flutter model with high aspect ratio and production method thereof |
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| CN102935897A true CN102935897A (en) | 2013-02-20 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103407580A (en) * | 2013-08-19 | 2013-11-27 | 空气动力学国家重点实验室 | Manufacturing method of light aerofoil with super-high aspect ratio and high lift-drag ratio and aerofoil manufactured thereby |
| CN103406725B (en) * | 2013-08-01 | 2016-01-20 | 成都飞机设计研究所 | A kind of flutter model roof beam structure processing method |
| CN106672260A (en) * | 2015-11-11 | 2017-05-17 | 成都飞机工业（集团）有限责任公司 | High-aspect-ratio wing frame architecture design method |
| CN108216570A (en) * | 2017-12-14 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of high aspect ratio wing main plane structure |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0727665A (en) * | 1993-07-08 | 1995-01-31 | Mitsubishi Heavy Ind Ltd | Model for testing aeroelasticity |
| US20020069040A1 (en) * | 2000-12-05 | 2002-06-06 | Hideo Omotani | Flutter test model |
| CN101893504A (en) * | 2010-07-20 | 2010-11-24 | 中国航空工业集团公司西安飞机设计研究所 | Stiffening rib of flight vehicle aerofoil experimental model |
-
2011
- 2011-08-15 CN CN2011102327033A patent/CN102935897A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0727665A (en) * | 1993-07-08 | 1995-01-31 | Mitsubishi Heavy Ind Ltd | Model for testing aeroelasticity |
| US20020069040A1 (en) * | 2000-12-05 | 2002-06-06 | Hideo Omotani | Flutter test model |
| CN101893504A (en) * | 2010-07-20 | 2010-11-24 | 中国航空工业集团公司西安飞机设计研究所 | Stiffening rib of flight vehicle aerofoil experimental model |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103406725B (en) * | 2013-08-01 | 2016-01-20 | 成都飞机设计研究所 | A kind of flutter model roof beam structure processing method |
| CN103407580A (en) * | 2013-08-19 | 2013-11-27 | 空气动力学国家重点实验室 | Manufacturing method of light aerofoil with super-high aspect ratio and high lift-drag ratio and aerofoil manufactured thereby |
| CN103407580B (en) * | 2013-08-19 | 2015-04-08 | 空气动力学国家重点实验室 | Manufacturing method of light aerofoil with super-high aspect ratio and high lift-drag ratio and aerofoil manufactured thereby |
| CN106672260A (en) * | 2015-11-11 | 2017-05-17 | 成都飞机工业（集团）有限责任公司 | High-aspect-ratio wing frame architecture design method |
| CN106672260B (en) * | 2015-11-11 | 2018-11-02 | 成都飞机工业（集团）有限责任公司 | A kind of high aspect ratio wing type frame configuration designing method |
| CN108216570A (en) * | 2017-12-14 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of high aspect ratio wing main plane structure |
| CN108216570B (en) * | 2017-12-14 | 2023-08-18 | 中航(成都)无人机系统股份有限公司 | Main wing surface structure of high aspect ratio wing |
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Application publication date: 20130220 |