CN105486494B - A kind of load applying method of shielded aerofoil - Google Patents
A kind of load applying method of shielded aerofoil Download PDFInfo
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- CN105486494B CN105486494B CN201410535667.1A CN201410535667A CN105486494B CN 105486494 B CN105486494 B CN 105486494B CN 201410535667 A CN201410535667 A CN 201410535667A CN 105486494 B CN105486494 B CN 105486494B
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- load
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- compression pad
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Abstract
The invention belongs to strength test technical fields, it is related to a kind of load applying method of shielded aerofoil, including being distributed according to airfoil load, provide lower aerofoil tension and compression pad load F3, F4, the distance between tension and compression pad b, rear portion cable wire and rear portion tension and compression pad distance a, front cable wire and front tension and compression pad distance c.
Description
Technical field
The invention belongs to strength test technical fields, are related to a kind of load applying method of shielded aerofoil.
Background technology
Aerofoil is shielded, and previous loading system only can guarantee that aerofoil presses heart front by adjusting the pressure heart in non-obstructing area's prestowage
Divide aerofoil power transmission true, whole aerofoils cannot be examined, and prestowage aerofoil applies load and is more than real load, the examination of load applying zone
It is big to test risk, another way loads, experiment cannot obtain the shielded wing of loading procedure by removing masking face in top airfoil
Interfere in face.
Invention content
The purpose of the present invention is to propose to a kind of load loading methods of shielded aerofoil.
Technical solution of the invention is,
Step 1:It is distributed according to airfoil load, provides load F3, the front tension and compression pad 11 on lower aerofoil rear portion tension and compression pad 10
Load F4, the distance between rear portion tension and compression pad 10 and front tension and compression pad 11 b, rear portion cable wire 8 is at a distance from rear portion tension and compression pad 10
A, front cable wire 12 and 11 distance c of front tension and compression pad.Determination can be with the region of trepanning.
Step 4:Tension and compression pad is pasted lower aerofoil, according to the amount of the load of F2 by distance a, b, the c provided according to step 2
Grade selects suitable cable wire,
Step 5:Tension and compression pad is connected on the girder steel of lower part, lower part girder steel is connect by cable wire with top girder steel, upper steel
Beam load(ing) point is connect with top airfoil rubberized tape by loading lever, realizes load load.
It is an advantage of the invention that：The present invention passes through the adhesive plaster of the trepanning and top airfoil in non-examination area by lower aerofoil tension and compression pad
Band is combined together by lever system so that airfoil load applies truer；The shaded areas of the overwhelming majority is remained, is protected
The integrality of testpieces has been demonstrate,proved, and can monitor that aerofoil interferes situation during the experiment；Improve the accurate of load application
Property, working efficiency is improved, the test period is shortened
Description of the drawings
Fig. 1 is loading theory design diagram of the present invention；
Fig. 2 is that load of the present invention applies schematic diagram.
Wherein：1 masking aerofoil 2 covers 5 upper steel of face 4 top girder steel of non-3 shielded aerofoil of examination area
11 front tension and compression are padded in 9 lower part girder steel of rope 6 lever, 7 rubberized tape cable wire, 8 rear portion cable wire, 10 rear portion tension and compression
12 front cable wire, the 13 top airfoil rubberized tape 14 load lower parts cable wire a girder steel rear portion cable wire 8 is padded to draw with rear portion
Rear portion tension and compression pad 10 and 11 lower parts distance c steel of front tension and compression pad on the lower parts the distance b girder steel of pressure pad 10
Beam upper forepart tension and compression pad 11 applies cable wire with 12 tops distance d girder steel rear portion cable wire 8 of front cable wire with load
The tops distance e girder steel front cable wire 12 and load apply load on cable wire distance F1 rear portions cable wire 8
10 fronts the load F4 tension and compression of the rear portions load F3 tension and compression pad are padded on 11 load F on the fronts F2 cable wire 12
Portion's girder steel load
Specific implementation mode
It elaborates below in conjunction with the accompanying drawings to the present invention.
Step 1:It is distributed according to airfoil load, provides load F3, the front tension and compression pad 11 on lower aerofoil rear portion tension and compression pad 10
Load F4, the distance between rear portion tension and compression pad 10 and front tension and compression pad 11 b, rear portion cable wire 8 is at a distance from rear portion tension and compression pad 10
A, front cable wire 12 and 11 distance c of front tension and compression pad.Determination can be with the region of trepanning.
Step 4:Rear portion tension and compression pad 10, front tension and compression pad 11 are pasted bottom wing by distance a, b, the c provided according to step 2
Face 3 selects suitable front cable wire 12 according to the magnitude of the load of F2, selects suitable opening diameter.
Step 5:Rear portion tension and compression pad 10, front tension and compression pad 11 are connected on lower part girder steel 9, lower part girder steel 9 passes through rear portion
Cable wire 8, front cable wire 12 are connect with top girder steel 4, and girder steel 4 load(ing) point in top is with top airfoil rubberized tape 13 by loading lever 6
It is connected by rubberized tape cable wire 7, realizes load load.
Claims (1)
1. a kind of load applying method of shielded aerofoil, characterized in that include the following steps：
Step 1:It is distributed according to airfoil load, provides lower aerofoil tension and compression pad load F3, F4, the distance between tension and compression pad b, rear portion steel
Rope and rear portion tension and compression pad distance a, front cable wire and front tension and compression pad distance c；
Step 2:By solving linear equation in two unknowns groupF1, F2 are obtained, F1 refers to rear portion
The load of cable wire, F2 refer to the load of front cable wire；
Step 3:According to step 2 calculated F1, F2, lever principle solving equations are utilizedObtain rear portion steel
Rope applies point distance d with upper steel load beam, and front cable wire applies point distance e with upper steel load beam；
Step 4:Tension and compression pad is pasted lower aerofoil by distance a, b, the c provided according to step 2, is selected according to the magnitude of the load of F2
Suitable cable wire is selected, suitable opening diameter is selected according to the diameter of cable wire；
Step 5:Tension and compression pad is connected on girder steel, girder steel is connect by cable wire with top girder steel, top girder steel load(ing) point with it is upper
Aerofoil rubberized tape realizes load load by loading lever connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410535667.1A CN105486494B (en) | 2014-10-11 | 2014-10-11 | A kind of load applying method of shielded aerofoil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410535667.1A CN105486494B (en) | 2014-10-11 | 2014-10-11 | A kind of load applying method of shielded aerofoil |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105486494A CN105486494A (en) | 2016-04-13 |
| CN105486494B true CN105486494B (en) | 2018-07-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410535667.1A Active CN105486494B (en) | 2014-10-11 | 2014-10-11 | A kind of load applying method of shielded aerofoil |
Country Status (1)
| Country | Link |
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| CN (1) | CN105486494B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109163963A (en) * | 2018-08-24 | 2019-01-08 | 中国飞机强度研究所 | A kind of test load rubberized tape setting-out template and method |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3472799B2 (en) * | 2000-02-29 | 2003-12-02 | 防衛庁技術研究本部長 | Airfoil for blade |
| CN101685039A (en) * | 2008-09-23 | 2010-03-31 | 中国农业机械化科学研究院 | Method for testing field ground load calibration of airplane wing and calibration device thereof |
| CN102991727A (en) * | 2012-12-10 | 2013-03-27 | 中国飞机强度研究所 | Constraint system of airplane structure test |
| CN103303493A (en) * | 2013-01-05 | 2013-09-18 | 中国航空工业集团公司西安飞机设计研究所 | Wing load applying device for large aircraft strength test |
| CN103558020A (en) * | 2013-11-05 | 2014-02-05 | 中国航空工业集团公司西安飞机设计研究所 | Method for applying test load to movable wing surface of aerofoil in process of large deformation of aerofoil |
| CN103994878A (en) * | 2014-04-17 | 2014-08-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Integration test verification method of airplane movable wing surface |
| CN104075868A (en) * | 2014-05-30 | 2014-10-01 | 西北工业大学 | Aerodynamic load loading method used for reliability tests on aircraft flap and slat system |
-
2014
- 2014-10-11 CN CN201410535667.1A patent/CN105486494B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3472799B2 (en) * | 2000-02-29 | 2003-12-02 | 防衛庁技術研究本部長 | Airfoil for blade |
| CN101685039A (en) * | 2008-09-23 | 2010-03-31 | 中国农业机械化科学研究院 | Method for testing field ground load calibration of airplane wing and calibration device thereof |
| CN102991727A (en) * | 2012-12-10 | 2013-03-27 | 中国飞机强度研究所 | Constraint system of airplane structure test |
| CN103303493A (en) * | 2013-01-05 | 2013-09-18 | 中国航空工业集团公司西安飞机设计研究所 | Wing load applying device for large aircraft strength test |
| CN103558020A (en) * | 2013-11-05 | 2014-02-05 | 中国航空工业集团公司西安飞机设计研究所 | Method for applying test load to movable wing surface of aerofoil in process of large deformation of aerofoil |
| CN103994878A (en) * | 2014-04-17 | 2014-08-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Integration test verification method of airplane movable wing surface |
| CN104075868A (en) * | 2014-05-30 | 2014-10-01 | 西北工业大学 | Aerodynamic load loading method used for reliability tests on aircraft flap and slat system |
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| CN105486494A (en) | 2016-04-13 |
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