CN103558019A - Three-slideway wing flap test method for simulating deformation of wings - Google Patents
Three-slideway wing flap test method for simulating deformation of wings Download PDFInfo
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- CN103558019A CN103558019A CN201310544844.8A CN201310544844A CN103558019A CN 103558019 A CN103558019 A CN 103558019A CN 201310544844 A CN201310544844 A CN 201310544844A CN 103558019 A CN103558019 A CN 103558019A
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Abstract
The invention belongs to the technical field of strength tests, and relates to a three-slideway wing flap test method of the strength test under the condition that the wings deform. By utilizing the relative displacement theory, the three-slideway wing flap test method largely reduces the design scale of the experiment, reduces test risks, largely improves the accuracy of the experiment design through the method that forced displacement and pneumatic loads are simultaneously loaded stage by stage, and fully tests the structures like 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 exhibition that causes at wing flap aerofoil of the distortion of wing accounts for whole wing flap stress to ess-strain is larger, if ignore these impacts, can not fully examine flap configurations.Present stage analog machine wing-warp line conventional method all adopts the mode of box section simulation, needs box section to apply independent load in process of the test, and experimental scale and cost are all larger, and process of the test risk is larger.
Summary of the invention
The object of the invention is to propose all three slide rail wing flap test methods of smaller simulation wing distortion of a kind of experimental scale and cost.
Technical solution of the present invention is,
Step 1: according to flap-track pitch arrangement test-bed;
Step 2: wing flap, according to installation requirement, is arranged on test-bed;
Step 3: Wings distortion, show that three slide rails are at wing tie point top offset, obtain three slide rail tie point positions after distortion, obtain wing flexure line;
Step 4: utilize the method for relative displacement, in the middle of solving, slide rail needs the displacement that forces applying in process of the test, simulate with step 3 in the wing flexure line that obtains;
Step 5: the stand in the middle of utilizing or the stand of both sides, apply and force displacement and the thriving face of Chinese-style jacket with buttons down the front to apply aerodynamic loading flap-track simultaneously; The aerodynamic loading providing according to design objective, the 5% thriving face loading of Chinese-style jacket with buttons down the front step by step with aerodynamic loading total amount, simultaneously according to the flap-track obtaining in step 4, apply 5% step by step flap-track being loaded of total amount of forcing displacement, until be loaded into flap-track that aerodynamic loading that design objective provides and step 4 obtain, apply and force displacement, obtain the real load of three slide rail wing flaps under wing deformation condition and distribute and stress distribution.
Stand in the middle of described utilization applies while forcing displacement flap-track, 2 lines of the slide rail tie point of wing flap both sides are to apply the zero point of forcing displacement, the stand that utilizes both sides applies while forcing displacement flap-track, and middle slide rail tie point is to apply the zero point of forcing displacement.
The good effect that the present invention produces: the present invention adopts relative displacement theory greatly to reduce experimental design scale, the method of forcing displacement and aerodynamic loading simultaneously to load step by step by employing, the precision of test design is improved greatly, the structures such as wing flap have been carried out to abundant examination.
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- beds 6,7,8;
Step 2: wing flap 15, according to installation requirement, is arranged on test- bed 6,7,8;
Step 3: Wings distortion, show that three slide rails, at wing tie point 1,2,3 top offsets, obtain three slide rail tie point positions after distortion, obtain wing flexure line, as Fig. 1;
Step 4: utilize the method for relative displacement, in the middle of solving, slide rail needs to apply in process of the test forces displacement 4, simulate with step 3 in the wing flexure line 5 that obtains;
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 and force displacement and the thriving face 15 of Chinese-style jacket with buttons down the front to apply aerodynamic loading, the aerodynamic loading providing according to design objective, the 5% thriving face loading of Chinese-style jacket with buttons down the front step by step with aerodynamic loading total amount, according to the flap-track calculating, apply 5% step by step flap-track being loaded of total amount of forcing displacement, until be loaded into the aerodynamic loading that design objective provides and the flap-track calculating, apply and force displacement, obtaining the real load of three slide rail wing flaps under wing deformation condition distributes and stress distribution.
Embodiment mono-
With certain large transport airplane wing flap force-transfer characteristic test cruising condition test, carry out method explanation.
1) installation requirement on wing according to wing flap cruising condition, is arranged on wing flap on three stand bearings.
2) according to wing, distortion draws the displacement under cruising condition at wing tie point of three slide rails, obtains three slide rail wing tie points position after distortion under full machine coordinate system;
3) utilize the method for relative displacement solve in the middle of slide rail in process of the test, need the displacement that forces applying, see Fig. 1;
4) add displacement pressurized strut 10 in stand 7 in selecting as required and apply and force displacement, see 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 bis-
With certain large transport airplane wing flap force-transfer characteristic test landing state test, carry out method explanation.
1) installation requirement on wing according to wing flap landing state, is arranged on wing flap on three stand bearings.
2) according to wing, distortion solves the displacement under landing state at wing tie point of three slide rails, obtains three slide rail wing tie points position after distortion under full machine coordinate system;
3) utilize the method for relative displacement solve in the middle of slide rail in process of the test, need the displacement that forces applying, see Fig. 1;
4) add displacement pressurized strut 9,11 in stand 6,8 in selecting as required and apply and force displacement, see 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, by apply the method for forcing displacement and aerodynamic loading to load step by step simultaneously, has reduced wing flap experimental design scale, has reduced empirical risk, and test accuracy improves greatly, and the structures such as wing flap have been carried out to abundant examination.
Claims (2)
1. three slide rail wing flap test methods of simulating wing distortion, is characterized in that,
Step 1: according to flap-track pitch arrangement test-bed;
Step 2: wing flap, according to installation requirement, is arranged on test-bed;
Step 3: Wings distortion, show that three slide rails are at wing tie point top offset, obtain three slide rail tie point positions after distortion, obtain wing flexure line;
Step 4: utilize the method for relative displacement, in the middle of solving, slide rail needs the displacement that forces applying in process of the test, simulate with step 3 in the wing flexure line that obtains;
Step 5: the stand in the middle of utilizing or the stand of both sides, apply and force displacement and the thriving face of Chinese-style jacket with buttons down the front to apply aerodynamic loading flap-track simultaneously; The aerodynamic loading providing according to design objective, the 5% thriving face loading of Chinese-style jacket with buttons down the front step by step with aerodynamic loading total amount, simultaneously according to the flap-track obtaining in step 4, apply 5% step by step flap-track being loaded of total amount of forcing displacement, until be loaded into flap-track that aerodynamic loading that design objective provides and step 4 obtain, apply and 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 of simulating wing distortion according to claim 1, it is characterized in that, stand in the middle of described utilization applies while forcing displacement flap-track, 2 lines of the slide rail tie point of wing flap both sides are to apply the zero point of forcing displacement, the stand that utilizes both sides applies while forcing displacement flap-track, and middle slide rail tie point is to apply the zero point of forcing 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 true CN103558019A (en) | 2014-02-05 |
| CN103558019B CN103558019B (en) | 2016-03-09 |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103808505A (en) * | 2014-03-06 | 2014-05-21 | 哈尔滨工业大学 | Wing static load experiment device |
| CN104931250A (en) * | 2015-06-29 | 2015-09-23 | 中国航空工业集团公司西安飞机设计研究所 | High-lift system whole-aircraft loading dynamic test method |
| CN105716835A (en) * | 2014-12-03 | 2016-06-29 | 中国飞机强度研究所 | Chuck-type wing loading device |
| CN105775163A (en) * | 2016-05-06 | 2016-07-20 | 江西昌河航空工业有限公司 | Test simulation device for airplane 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 |
| CN109342037A (en) * | 2018-10-17 | 2019-02-15 | 中国特种飞行器研究所 | A kind of frame-type airfoil structure aerodynamic loading loading system and loading method |
| CN109490114A (en) * | 2018-12-12 | 2019-03-19 | 中国航空工业集团公司西安飞机设计研究所 | A kind of full scale fatigue test wing flap load loading method |
| CN110823506A (en) * | 2019-10-30 | 2020-02-21 | 上海理工大学 | Wing simulation test bed driven by linear motor |
| CN113071704A (en) * | 2021-03-30 | 2021-07-06 | 中国商用飞机有限责任公司 | Test method and system for simulating wing deformation |
| CN115649479A (en) * | 2022-12-08 | 2023-01-31 | 四川腾盾科技有限公司 | Low-cost test device and test method for flap system of unmanned aerial vehicle |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103808505A (en) * | 2014-03-06 | 2014-05-21 | 哈尔滨工业大学 | Wing static load experiment device |
| CN105716835A (en) * | 2014-12-03 | 2016-06-29 | 中国飞机强度研究所 | Chuck-type wing loading 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 |
| CN104931250A (en) * | 2015-06-29 | 2015-09-23 | 中国航空工业集团公司西安飞机设计研究所 | High-lift system whole-aircraft loading dynamic test method |
| 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 |
| CN105775163A (en) * | 2016-05-06 | 2016-07-20 | 江西昌河航空工业有限公司 | Test simulation device for airplane 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 |
| CN109342037A (en) * | 2018-10-17 | 2019-02-15 | 中国特种飞行器研究所 | A kind of frame-type airfoil structure aerodynamic loading loading system and loading method |
| 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 |
| CN109490114A (en) * | 2018-12-12 | 2019-03-19 | 中国航空工业集团公司西安飞机设计研究所 | A kind of full scale fatigue test wing flap load loading method |
| 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 |
| CN110823506A (en) * | 2019-10-30 | 2020-02-21 | 上海理工大学 | Wing simulation test bed driven by linear motor |
| CN113071704A (en) * | 2021-03-30 | 2021-07-06 | 中国商用飞机有限责任公司 | Test method and system for simulating wing deformation |
| 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 |
| CN115649479A (en) * | 2022-12-08 | 2023-01-31 | 四川腾盾科技有限公司 | Low-cost test device and test method for flap system of unmanned aerial vehicle |
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