CN105486494A - Load applying method of shielded wing surface - Google Patents
Load applying method of shielded wing surface Download PDFInfo
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- CN105486494A CN105486494A CN201410535667.1A CN201410535667A CN105486494A CN 105486494 A CN105486494 A CN 105486494A CN 201410535667 A CN201410535667 A CN 201410535667A CN 105486494 A CN105486494 A CN 105486494A
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Abstract
The invention belongs to the technical field of strength tests, and relates to a load applying method of a shielded wing surface. The method comprises: according to wing surface load distribution, giving load F3 and F4 of pulling pressure pads of a lower wing surface, a distance b between the pulling pressure pads, a distance a between a rear steel cable and the rear pulling pressure pad, and a distance c between a front steel cable and the front pulling pressure pad, etc.
Description
Technical field
The invention belongs to strength test technical field, relate to a kind of load applying method of crested aerofoil.
Background technology
Aerofoil crested, loading system was true by only can ensure the power transmission of aerofoil pressure heart forward part aerofoil at the non-obstructing district prestowage adjustment pressure heart in the past, whole aerofoil can not be examined, and prestowage aerofoil imposed load is greater than real load, load applying regional testing has a big risk, another kind of mode covers face by removal, loads at top airfoil, and the crested aerofoil that test can not obtain loading procedure is interfered.
Summary of the invention
The object of the invention is the load loading method proposing a kind of crested aerofoil.
Technical solution of the present invention is,
Step 1: according to aerofoil load diatibution, provide the load F4 of the load F3 on lower aerofoil rear portion tension and compression pad 10, anterior tension and compression pad 11, distance b between rear portion tension and compression pad 10 and anterior tension and compression pad 11, the distance a of rear portion cable wire 8 and rear portion tension and compression pad 10, the distance c of anterior cable wire 12 and anterior tension and compression pad 11.Determining can the region of perforate.
Step 2: by separating linear equation in two unknowns group
Obtain F1, F2.
Step 3: F1, F2 of calculating according to step 2, utilizes lever principle solving equations
Obtain distance d, the e of front and rear part cable wire and upper steel load beam application point.
Step 4: the distance a provided according to step 2, b, c, paste lower aerofoil by tension and compression pad, select suitable cable wire according to the magnitude of the load of F2,
Step 5: be connected to by tension and compression pad on the girder steel of bottom, bottom girder steel is connected with top girder steel by cable wire, top girder steel load(ing) point is connected by loading lever with top airfoil rubberized tape, realizes load and loads.
Advantage of the present invention is: the present invention is combined by lever system by the non-perforate in examination district and the rubberized tape of top airfoil by lower aerofoil tension and compression pad, makes aerofoil load applying truer; Remain the shaded areas of the overwhelming majority, ensure that the integrality of testpieces, and aerofoil interference situation can be monitored in experimentation; Improve the accuracy of load applying, increase work efficiency, shorten the test period
Accompanying drawing explanation
Fig. 1 is loading theory design diagram of the present invention;
Fig. 2 is load applying schematic diagram of the present invention.
Wherein: 1 covers aerofoil 2 covers the anterior tension and compression pad 12 anterior cable wire 13 top airfoil rubberized tape 14 of non-examination district 3 crested aerofoil 4 top, face cable wire 6 lever 7 rubberized tape cable wire 8 rear portion, girder steel 5 top cable wire 9 bottom girder steel 10 rear portion tension and compression pad 11 and load girder steel rear portion, cable wire a bottom cable wire 8 and rear portion tension and compression pad 10 on the distance b bottom girder steel of rear portion tension and compression pad 10 and the distance c bottom girder steel upper forepart tension and compression pad 11 of anterior tension and compression pad 11 and girder steel rear portion, the distance d top cable wire 8 of anterior cable wire 12 and the anterior cable wire 12 of the distance e top girder steel of load applying cable wire and load F3 rear portion tension and compression pad 10 load F4 anterior tension and compression pad 11 load F upper steel load beam on the anterior cable wire 12 of load F2 on the distance F1 rear portion cable wire 8 of load applying cable wire
Embodiment
Below in conjunction with accompanying drawing, the present invention is elaborated.
Step 1: according to aerofoil load diatibution, provide the load F4 of the load F3 on lower aerofoil rear portion tension and compression pad 10, anterior tension and compression pad 11, distance b between rear portion tension and compression pad 10 and anterior tension and compression pad 11, the distance a of rear portion cable wire 8 and rear portion tension and compression pad 10, the distance c of anterior cable wire 12 and anterior tension and compression pad 11.Determining can the region of perforate.
Step 2: by separating linear equation in two unknowns group
Obtain load F1, the F2 on rear portion cable wire 8, anterior cable wire 12.
Step 3: F1, F2 of calculating according to step 2, utilizes lever principle solving equations
Distance d, the e of rear portion cable wire 8, anterior cable wire 12 tie point and top girder steel 4 load applying point.
Step 4: the distance a provided according to step 2, b, c, paste lower aerofoil 3 by rear portion tension and compression pad 10, anterior tension and compression pad 11, select suitable anterior cable wire 12, select suitable opening diameter according to the magnitude of the load of F2.
Step 5: rear portion tension and compression pad 10, anterior tension and compression pad 11 are connected on bottom girder steel 9, bottom girder steel 9 is connected with top girder steel 4 by rear portion cable wire 8, anterior cable wire 12, top girder steel 4 load(ing) point is connected by rubberized tape cable wire 7 by loading lever 6 with top airfoil rubberized tape 13, realizes load and loads.
Claims (1)
1. a load applying method for crested aerofoil, is characterized in that, comprise the following steps:
Step 1: according to aerofoil load diatibution, provides lower aerofoil tension and compression pad load F3, F4, the distance b between tension and compression pad, the distance a of rear portion cable wire and rear portion tension and compression pad, the distance c of anterior cable wire and anterior tension and compression pad;
Step 2: by separating linear equation in two unknowns group
Obtain F1, F2;
Step 3: F1, F2 of calculating according to step 2, utilizes lever principle solving equations
Obtain distance d, the e of front and rear part cable wire and upper steel load beam application point;
Step 4: the distance a provided according to step 2, b, c, paste lower aerofoil by tension and compression pad, select suitable cable wire according to the magnitude of the load of F2, select suitable opening diameter according to the diameter of cable wire;
Step 5: be connected on girder steel by tension and compression pad, girder steel is connected with top girder steel by cable wire, and top girder steel load(ing) point is connected by loading lever with top airfoil rubberized tape, realizes load and loads.
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 true CN105486494A (en) | 2016-04-13 |
| CN105486494B 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) |
Cited By (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 |
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| 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 |
Cited By (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 |
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| Publication number | Publication date |
|---|---|
| CN105486494B (en) | 2018-07-24 |
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