CN103558019B - A kind of three slide rail wing flap test methods simulating wing distortion - Google Patents
A kind of three slide rail wing flap test methods simulating wing distortion Download PDFInfo
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- CN103558019B CN103558019B CN201310544844.8A CN201310544844A CN103558019B CN 103558019 B CN103558019 B CN 103558019B CN 201310544844 A CN201310544844 A CN 201310544844A CN 103558019 B CN103558019 B CN 103558019B
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Abstract
The invention belongs to strength test technical field, relate to a kind of three slide rail wing flap test methods for the strength test under wing deformation of three slide rail wing flaps.The present invention adopts relative displacement theory to substantially reduce experimental design scale, reduce empirical risk, the while of forcing displacement and aerodynamic loading by adopting, the method for multistage loadings, makes the precision of test design greatly improve, has carried out abundant examination to structures such as wing flaps.
Description
Technical field
The invention belongs to strength test technical field, relate to a kind of three slide rail wing flap test methods for the strength test under wing deformation of three slide rail wing flaps.
Background technology
Three slide rail wing flaps are under wing deformation, load can be redistributed between three slide rails, and the proportion that the distortion of wing accounts for whole wing flap stress in the exhibition that wing flap aerofoil causes to ess-strain is comparatively large, if ignore these impacts, fully can not examine flap configurations.The mode that present stage analog machine wing-warp line conventional method all adopts box section to simulate, needs in process of the test to apply independent load to box section, and experimental scale is all larger with cost, and process of the test risk is larger.
Summary of the invention
The object of the invention is the three slide rail wing flap test methods proposing a kind of experimental scale and spend all smaller simulation wing distortion.
Technical solution of the present invention is,
Step 1: according to flap-track pitch arrangement test-bed;
Step 2: by wing flap according to installation requirement, be arranged on test-bed;
Step 3: Wings is out of shape, and show that three slide rails are at wing tie point top offset, obtains three slide rail tie point positions after deformation, obtain wing flexure line;
Step 4: the method utilizing relative displacement, what solve that middle slide rail needs to apply in process of the test forces displacement, simulates and the wing flexure line that obtains in step 3;
Step 5: the stand in the middle of utilizing or the stand of both sides, applies to force displacement and the thriving face of Chinese-style jacket with buttons down the front to apply aerodynamic loading to flap-track simultaneously; According to the aerodynamic loading that design objective provides, with 5% of aerodynamic loading total amount Chinese-style jacket with buttons down the front thriving face loading step by step, apply to force 5% of the total amount of displacement to load flap-track step by step according to the flap-track obtained in step 4 simultaneously, until be loaded into aerodynamic loading that design objective provides and the flap-track that step 4 obtains applies to force displacement, obtain the real load of three slide rail wing flaps under wing deformation condition and distribute and stress distribution.
When stand in the middle of described utilization applies to force displacement to flap-track, 2 lines of the slide rail tie point of wing flap both sides are the zero point applying to force displacement, when utilizing the stand of both sides to apply to force displacement to flap-track, middle slide rail tie point is the zero point applying to force displacement.
The good effect that the present invention produces: the present invention adopts relative displacement theory to substantially reduce experimental design scale, the method of multistage loadings while of forcing displacement and aerodynamic loading by adopting, the precision of test design is improved greatly, abundant examination has been carried out to structures such as wing flaps.
Accompanying drawing explanation
Fig. 1 is that the present invention forces displacement to solve wing flexure line schematic diagram;
Fig. 2 is the schematic diagram that the present invention forces displacement to apply.
Embodiment
Below in conjunction with Figure of description, the present invention is described in further detail.
Below in conjunction with accompanying drawing, the present invention is elaborated.
Step 1: according to wing flap 15 slide rail pitch arrangement test-bed 6,7,8;
Step 2: by wing flap 15 according to installation requirement, be arranged on test-bed 6,7,8;
Step 3: Wings is out of shape, and show that three slide rails are at wing tie point 1,2,3 top offset, obtain three slide rail tie point positions after deformation, obtain wing flexure line, as Fig. 1;
Step 4: the method utilizing relative displacement, what solve that middle slide rail needs to apply in process of the test forces displacement 4, simulates and the wing flexure line 5 that obtains in step 3;
Step 5: the displacement pressurized strut 10 of stand in the middle of utilizing or the displacement pressurized strut 9 of the stand of both sides, 11, simultaneously to flap-track 13 or 12, 14 apply to force displacement and the thriving face 15 of Chinese-style jacket with buttons down the front to apply aerodynamic loading, according to the aerodynamic loading that design objective provides, with 5% of aerodynamic loading total amount Chinese-style jacket with buttons down the front thriving face loading step by step, apply to force 5% of the total amount of displacement to load flap-track step by step according to the flap-track calculated, apply to force displacement until be loaded into the design objective aerodynamic loading provided and the flap-track calculated, obtain the real load of three slide rail wing flaps under wing deformation condition to distribute and stress distribution.
Embodiment one
With the test of certain large transport airplane wing flap force-transfer characteristic test cruising condition, carry out method explanation.
1) according to the installation requirement of wing flap cruising condition on wing, wing flap is arranged on three stand bearings.
2) according to wing distortion show that three slide rails are in the displacement of wing tie point under cruising condition, obtain three slide rail wing tie points be out of shape under full machine coordinate system after position;
3) utilize the method for relative displacement solve middle slide rail need in process of the test apply force displacement, see Fig. 1;
4) the displacement pressurized strut 10 added in selecting as required in stand 7 applies to force displacement, sees Fig. 2;
5) displacement pressurized strut 10 apply force displacement and aerodynamic loading as requested 5% grade load 65% simultaneously, displacement pressurized strut 10 apply force displacement and aerodynamic loading as requested 2% grade load 67% simultaneously, obtain experimental data.
Embodiment two
With certain large transport airplane wing flap force-transfer characteristic test landing condition test, carry out method explanation.
1) according to the installation requirement of wing flap landing state on wing, wing flap is arranged on three stand bearings.
2) according to wing distortion solve three slide rails in the displacement of wing tie point under landing state, obtain three slide rail wing tie points be out of shape under full machine coordinate system after position;
3) utilize the method for relative displacement solve middle slide rail need in process of the test apply force displacement, see Fig. 1;
4) the displacement pressurized strut 9,11 added in selecting as required in stand 6,8 applies to force displacement, sees Fig. 2;
5) displacement pressurized strut 10 apply force displacement and aerodynamic loading as requested 5% grade load 65% simultaneously, displacement pressurized strut 10 apply force displacement and aerodynamic loading as requested 2% grade load 67% simultaneously, obtain experimental data.
Technique effect:
The wing flap test method of simulation wing distortion, the method for multistage loadings while of by applying to force displacement and aerodynamic loading, reduce wing flap experimental design scale, reduce empirical risk, test accuracy improves greatly, has carried out abundant examination to structures such as wing flaps.
Claims (2)
1. simulate three slide rail wing flap test methods of wing distortion, it is characterized in that,
Step 1: according to flap-track pitch arrangement test-bed;
Step 2: by wing flap according to installation requirement, be arranged on test-bed;
Step 3: Wings is out of shape, and show that three slide rails are at wing tie point top offset, obtains three slide rail tie point positions after deformation, obtain wing flexure line;
Step 4: the method utilizing relative displacement, what solve that middle slide rail needs to apply in process of the test forces displacement, simulates and the wing flexure line that obtains in step 3;
Step 5: the stand in the middle of utilizing or the stand of both sides, applies to force displacement and the thriving face of Chinese-style jacket with buttons down the front to apply aerodynamic loading to flap-track simultaneously; According to the aerodynamic loading that design objective provides, with 5% of aerodynamic loading total amount Chinese-style jacket with buttons down the front thriving face loading step by step, apply to force 5% of the total amount of displacement to load flap-track step by step according to the flap-track obtained in step 4 simultaneously, until be loaded into aerodynamic loading that design objective provides and the flap-track that step 4 obtains applies to force displacement, obtain the real load of three slide rail wing flaps under wing deformation condition and distribute and stress distribution.
2. a kind of three slide rail wing flap test methods simulating wing distortion according to claim 1, it is characterized in that, when stand in the middle of described utilization applies to force displacement to flap-track, 2 lines of the slide rail tie point of wing flap both sides are the zero point applying to force displacement, when utilizing the stand of both sides to apply to force displacement to flap-track, middle slide rail tie point is the zero point applying to force displacement.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310544844.8A CN103558019B (en) | 2013-11-05 | 2013-11-05 | A kind of three slide rail wing flap test methods simulating wing distortion |
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| CN201310544844.8A CN103558019B (en) | 2013-11-05 | 2013-11-05 | A kind of three slide rail wing flap test methods simulating wing distortion |
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| CN103558019A CN103558019A (en) | 2014-02-05 |
| CN103558019B true CN103558019B (en) | 2016-03-09 |
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| CN103808505B (en) * | 2014-03-06 | 2016-04-13 | 哈尔滨工业大学 | Wing static loading experiment device |
| CN105716835B (en) * | 2014-12-03 | 2018-04-10 | 中国飞机强度研究所 | A kind of chuck type wing loading device |
| CN104931250B (en) * | 2015-06-29 | 2018-04-13 | 中国航空工业集团公司西安飞机设计研究所 | A kind of full machine loading dynamic test method of high-lift system |
| CN105775163B (en) * | 2016-05-06 | 2017-10-13 | 江西昌河航空工业有限公司 | A kind of test simulator of aircraft flap motion |
| RU182921U1 (en) * | 2017-12-06 | 2018-09-05 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Loading device for bench testing of the steering surface |
| CN109342037B (en) * | 2018-10-17 | 2021-03-26 | 中国特种飞行器研究所 | Pneumatic load loading system and loading method for frame type airfoil structure |
| CN109490114B (en) * | 2018-12-12 | 2021-05-07 | 中国航空工业集团公司西安飞机设计研究所 | Full-size fatigue test flap load loading method |
| CN110823506B (en) * | 2019-10-30 | 2021-03-26 | 上海理工大学 | Wing simulation test bed driven by linear motor |
| CN113071704B (en) * | 2021-03-30 | 2023-02-10 | 中国商用飞机有限责任公司 | Test method and system for simulating wing deformation |
| CN115649479B (en) * | 2022-12-08 | 2023-04-25 | 四川腾盾科技有限公司 | Low-cost test device and test method for unmanned aerial vehicle flap system |
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