CN104019968B - A kind of pilot system testing screw blade fatigue property - Google Patents
A kind of pilot system testing screw blade fatigue property Download PDFInfo
- Publication number
- CN104019968B CN104019968B CN201410212074.1A CN201410212074A CN104019968B CN 104019968 B CN104019968 B CN 104019968B CN 201410212074 A CN201410212074 A CN 201410212074A CN 104019968 B CN104019968 B CN 104019968B
- Authority
- CN
- China
- Prior art keywords
- screw blade
- test specimen
- blade test
- fixture
- screw
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
Testing a pilot system for screw blade fatigue property, it is added mounted mechanism, shaking table, foil gauge and dynamic strain meter formed by screw blade test specimen, fixture, static load; Position between them connects relation: the root of 4 propeller blade test specimens is connected with fixture by bolt, and left and right respectively arranges 2 screw blade test specimens; In the punching of screw blade test specimen apical location, adding mounted mechanism to install static load, 2 screw blade test specimens on every limit add mounted mechanism by the static load of tip and link together; Whole screw blade test specimen and fixture one are connected on the moving-coil of shaking table by the leading screw of shaking table; Foil gauge is pasted in the corresponding position of screw blade test specimen; Dynamic strain meter is connected with foil gauge. Present configuration is simple, easy to operate, efficiency height, and for the test of screw blade labor performance test, test result has important engineer applied for structure fatigue life evaluation and is worth.
Description
Technical field
The present invention relates to a kind of pilot system testing screw blade fatigue property, belong to experimental test technical field.
Background technology
Engineering structure in use, all subjects repeated load, and fatigure failure can occur, and for ensureing its security, it is necessary to test its fatigue property, through technical development for many years, has already formed perfect fatigue property test standard, but, properller leaf is complicated by load in practical work process, in high speed rotating, blade subjects very big centrifugal force and aerodynamic drag force, awing, cause alternation moment and vibration load to act on blade because of blade plane of rotation and flight direction non-vertical, therefore, water screw complex load condition must be simulated, test its fatigue property, for assessment of fatigue lifetime, but, conventional protracted test machine can only carry out axial tension/compression or the rotary bending fatigue test of simple sample, existing axial centrifugal force is had again to the screw blade structural part of alternation transverse load, still lack effective experiment on fatigue properties system. for this reason, screw blade test specimen, fixture, static load are added the pilot system that mounted mechanism, shaking table, foil gauge and dynamic strain meter are integrated into test screw blade fatigue property by the present invention, and test result has important engineer applied for structure fatigue life evaluation and is worth.
Summary of the invention
1, object: it is an object of the invention to provide a kind of pilot system testing screw blade fatigue property, for the fatigue property test of properller structure.
2, technical scheme: a kind of pilot system testing screw blade fatigue property of the present invention, is added mounted mechanism, shaking table, foil gauge and dynamic strain meter formed by screw blade test specimen, fixture, static load. It is as follows that position between them connects relation: the root of 4 screw blade test specimens is connected with fixture by bolt, and left and right respectively arranges 2 screw blade test specimens;In the punching of screw blade test specimen tip, adding mounted mechanism to install static load, 2 screw blade test specimens on every limit add mounted mechanism by the static load of tip and link together; Whole screw blade test specimen and fixture one are connected on the moving-coil of shaking table by the leading screw of shaking table; Foil gauge is pasted in the corresponding position of screw blade test specimen; Dynamic strain meter is connected with foil gauge.
Described screw blade test specimen is screw blade fatigue sample, and the concrete shape and size of this test specimen design according to the properller of reality, and the retaining part at two ends has hole, is connected with fixture by bolt.
Described fixture combines by cylinder and the clamping plate that have a hole, and in order to install and clamping screw blade test specimen, distortion amount when need to load according to the shape and size of screw blade specimen holder end and screw blade test specimen carry out Design and manufacture.
Described static load adds mounted mechanism and is made up of 4 block-type face clamping plate, loading screw rod and corresponding bolt, nut, and so that screw blade test specimen is applied static load, wherein the one side of profile clamping plate is plane, and another side should fit tightly the surface of screw blade test specimen.
Described shaking table is the vibrostand in order to screw blade test specimen to apply vibration load, it is possible to load size and frequency to applying control, it is possible to be conventional electric and magnetic oscillation platform or self-control shaking table.
Described foil gauge is a kind of chip component for monitor strain, the change strained can be converted to resistance change, be usually pasted onto surface of test piece on component, it is possible to be conventional resistance-strain sheet.
Described dynamic strain meter a kind of is connected the instrument for measuring sample strain with foil gauge, it is possible to measures in real time the dynamic strain of sample, it is possible to be conventional dynamic resistance strain instrument or automatic dynamic resistance strain meter.
All devices connect according to test requirements document and after debugging, just can complete screw blade fatigue test according to concrete test requirements document. This cover system efficiently solves the experimental test problem of screw blade fatigue property.
3, advantage and effect: the invention has the beneficial effects as follows the experimental test that can complete screw blade fatigue property, and can simultaneously carry out the fatigue test of 4 screw blade test specimens, this system has easy to operate, measuring accuracy height and the high feature of efficiency.
Accompanying drawing explanation
Below in conjunction with drawings and Examples, the present invention is further described.
Fig. 1 is screw blade test specimen schematic diagram.
Fig. 2 is fixture schematic diagram.
Fig. 3 is that static load loads mechanism show intention.
Fig. 4 is shaking table schematic diagram.
In Fig. 4: 1. nut, 2. pad, 3. leading screw, 4. moving-coil, 5. shaking table base.
Fig. 5 is screw blade experiment on fatigue properties test system structure figure.
In Fig. 5: 6. foil gauge, 7. screw blade test specimen, 8. fixture, 9. static load adds mounted mechanism, 10. shaking table.
Embodiment
Embodiment one: composition graphs 5 illustrates the specific embodiment of the present invention. A kind of pilot system testing screw blade fatigue property of the present invention, is added mounted mechanism 9, shaking table 10, foil gauge 6 and dynamic strain meter formed by screw blade test specimen 7, fixture 8, static load. In Figure 5, the root of 4 screw blade test specimens 7 is arranged on fixture 8 by bolt, each 2 the screw blade test specimens 7 in left and right; The tip of two screw blade test specimens 7 up and down on every limit adds mounted mechanism 9 by static load and links together; Fixture 8 is arranged on the leading screw 3 of shaking table 10; The corresponding position of screw blade test specimen 7 is pasted foil gauge 6;Dynamic strain meter is connected with foil gauge 6. After above equipment and the integrated docking of device, just constitute properller experiment on fatigue properties test macro.
Fig. 1 show in particular a kind of test specimen testing screw blade fatigue property, and the retaining part at screw blade test specimen 7 root devises fastener hole, can play clamping and positioning action, and for installing, static load adds mounted mechanism 9 in the hole of water screw test specimen 7 tip. Fixture 8 is as shown in Figure 2, it is arranged on the leading screw 3 of shaking table 10 and root with 4 screw blade test specimens is connected, it plays clamping screw blade test specimen and transmits the effect of load, owing to properller is at work simultaneously for tensile stress another side is stress, therefore outwardly, the one side of stress is inwardly for the one side that should make tensile stress when installing screw blade test specimen. Static load adds mounted mechanism 9 as shown in Figure 3, it is made up of 4 block-type face clamping plate, loading screw rod and corresponding bolt, nut, screw blade test specimen tip is clamped by two block-type face clamping plate by bolt, load the hole of screw rod in the middle of the profile clamping plate and screw blade test specimen tip on upper and lower both sides, the size of dehiscing of the nut adjustment screw blade test specimen tip loading screw rod two ends by tightening, it is achieved screw blade test specimen is applied static load. Foil gauge 6 is pasted in corresponding position on screw blade test specimen, and dynamic strain meter is connected with foil gauge 6, to read real-time strain, according to the corresponding relation of strain with load, it is possible to calculated the size of load suffered by screw blade test specimen by strainometer. All devices connect according to test requirements document and after debugging, just can complete the test of properller fatigue property test according to concrete test requirements document. Fig. 4 is shaking table schematic diagram, this shaking table 10 be by. nut 1, pad 2, leading screw 3, moving-coil 4, shaking table base 5 forms.
Claims (1)
1. testing a pilot system for screw blade fatigue property, it is added mounted mechanism, shaking table, foil gauge and dynamic strain meter formed by screw blade test specimen, fixture, static load;
Described shaking table is the vibrostand in order to screw blade test specimen to apply vibration load, and load size and frequency to applying control, and is conventional electric and magnetic oscillation platform or self-control shaking table;
Described foil gauge is a kind of chip component for monitor strain, the change of strain on screw blade test specimen can be converted to resistance change, usually be pasted onto screw blade surface of test piece, is conventional resistance-strain sheet;
Foil gauge is pasted in the corresponding position of screw blade test specimen; Dynamic strain meter is connected with foil gauge;
It is characterized in that: the root of 4 screw blade test specimens is connected with fixture by bolt, left and right respectively arranges 2 screw blade test specimens; In the punching of screw blade test specimen tip, adding mounted mechanism to install static load, 2 screw blade test specimens on every limit add mounted mechanism by the static load of tip and link together; Whole screw blade test specimen and fixture one are connected on the moving-coil of shaking table by the leading screw of shaking table;
Described screw blade test specimen is screw blade fatigue sample, and the concrete shape and size of this fatigue sample design according to the properller of reality, and the retaining part at two ends has hole, is connected with fixture by bolt;
Described fixture combines by cylinder and the clamping plate that have a hole, and in order to install and clamping screw blade test specimen, distortion amount when need to load according to the shape and size of screw blade specimen holder end and screw blade test specimen carry out Design and manufacture;
Described static load adds mounted mechanism and is made up of 4 block-type face clamping plate, loading screw rod and corresponding bolt, nut, and so that screw blade test specimen is applied static load, wherein the one side of profile clamping plate is plane, and another side should fit tightly the surface of screw blade test specimen;
Described dynamic strain meter a kind of is connected the instrument for measuring the strain of screw blade test specimen with foil gauge, it is possible to measures in real time the dynamic strain of screw blade test specimen, is conventional dynamic resistance strain instrument or automatic dynamic resistance strain meter;
All devices connect according to test requirements document and after debugging, just can complete screw blade fatigue test according to concrete test requirements document.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410212074.1A CN104019968B (en) | 2014-05-20 | 2014-05-20 | A kind of pilot system testing screw blade fatigue property |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410212074.1A CN104019968B (en) | 2014-05-20 | 2014-05-20 | A kind of pilot system testing screw blade fatigue property |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104019968A CN104019968A (en) | 2014-09-03 |
| CN104019968B true CN104019968B (en) | 2016-06-15 |
Family
ID=51436848
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410212074.1A Active CN104019968B (en) | 2014-05-20 | 2014-05-20 | A kind of pilot system testing screw blade fatigue property |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104019968B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104596695B (en) * | 2015-01-28 | 2017-01-25 | 华东交通大学 | Loading device for accurately controlling rivet preload of riveting member |
| CN106198265B (en) * | 2016-07-05 | 2019-03-19 | 中国航空工业集团公司北京航空材料研究院 | A kind of partition part testing fatigue experimental rig and test method |
| IL247408B (en) * | 2016-08-21 | 2018-03-29 | Elbit Systems Ltd | System and method for detecting weakening of the adhesion strength between structural elements |
| CN107719696B (en) * | 2017-09-12 | 2020-02-07 | 北京航空航天大学 | Dynamic characteristic synchronous testing device of axial compact type aircraft propeller |
| CN107941636A (en) * | 2017-11-08 | 2018-04-20 | 武汉航空仪表有限责任公司 | A kind of fatigue life test system and method for helicopter blade electric heating assembly |
| CN112710448B (en) * | 2021-01-22 | 2023-02-28 | 中国人民解放军空军工程大学 | Resonance fatigue test method capable of applying combined stress load |
| CN116294962B (en) * | 2023-05-18 | 2023-08-08 | 安徽羲禾航空科技有限公司 | Propeller blade airfoil type detection equipment |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02297037A (en) * | 1989-05-12 | 1990-12-07 | Hitachi Ltd | Method and device for measuring vibration of blade |
| US6085593A (en) * | 1997-09-04 | 2000-07-11 | Mtu Motoren-Und Turbinen-Union Munchen Gmbh | Vibration damping element test apparatus |
| CN102507275A (en) * | 2011-09-19 | 2012-06-20 | 哈尔滨飞机工业集团有限责任公司 | Helicopter composite material paddle fatigue test piece molding method |
| CN102539127A (en) * | 2010-12-31 | 2012-07-04 | 中国直升机设计研究所 | Device for applying standard load during blade calibration |
| CN103472741A (en) * | 2013-08-29 | 2013-12-25 | 东方电气集团东方汽轮机有限公司 | Control system for fatigue certification experimental test on blades of wind turbine |
| CN103471843A (en) * | 2013-10-15 | 2013-12-25 | 北京航空航天大学 | Bending multi-axial fatigue test mechanism |
-
2014
- 2014-05-20 CN CN201410212074.1A patent/CN104019968B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02297037A (en) * | 1989-05-12 | 1990-12-07 | Hitachi Ltd | Method and device for measuring vibration of blade |
| US6085593A (en) * | 1997-09-04 | 2000-07-11 | Mtu Motoren-Und Turbinen-Union Munchen Gmbh | Vibration damping element test apparatus |
| CN102539127A (en) * | 2010-12-31 | 2012-07-04 | 中国直升机设计研究所 | Device for applying standard load during blade calibration |
| CN102507275A (en) * | 2011-09-19 | 2012-06-20 | 哈尔滨飞机工业集团有限责任公司 | Helicopter composite material paddle fatigue test piece molding method |
| CN103472741A (en) * | 2013-08-29 | 2013-12-25 | 东方电气集团东方汽轮机有限公司 | Control system for fatigue certification experimental test on blades of wind turbine |
| CN103471843A (en) * | 2013-10-15 | 2013-12-25 | 北京航空航天大学 | Bending multi-axial fatigue test mechanism |
Non-Patent Citations (1)
| Title |
|---|
| 《风力机叶片动力特性实验台设计》;李海波等;《热能动力工程》;20120131;第27卷(第1期);第117－121、141页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104019968A (en) | 2014-09-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104019968B (en) | A kind of pilot system testing screw blade fatigue property | |
| CN104019970B (en) | A kind of pilot system of testing helicopter tail rotor fatigue behaviour | |
| CN104019967B (en) | A kind of pilot system testing Helicopter Main oar crossbeam fatigue behaviour | |
| CN104019950B (en) | A kind of pilot system of testing airplane tank vibrating fatigue performance | |
| CN105842055A (en) | Strength testing fixture using uniaxial testing machine for variable-proportion biaxial loading | |
| CN102519791B (en) | Mechanical fatigue tester for test piece | |
| CN104749031A (en) | Measurement jig and measurement method for rotary blade | |
| CN202735181U (en) | Tangential and radial recombination fretting wear test device | |
| CN108100302B (en) | Experimental excitation device of heart characteristic in helicopter tail-rotor hub | |
| CN204255765U (en) | A kind of load test device of structural member otic placode | |
| CN103163016A (en) | Auxiliary device for carrying out axial tension test on quasi brittle materials | |
| CN103196768A (en) | Fretting wear simulation test system | |
| CN104390852A (en) | Bolt shear test fixture and test machine | |
| CN103604715A (en) | Compound stress environment testing system of contact point material | |
| CN104677584A (en) | Simulative testing device and method of drilling tool thread dynamic fatigue | |
| CN104697766A (en) | Bidirectional hinge support device | |
| CN202471397U (en) | Elastic support parts flexibility tester | |
| CN205301069U (en) | Many sizes rock specimen positioner under three -dimensional rigidity loading | |
| CN204286791U (en) | Bearing fatigue simulator stand | |
| CN202362199U (en) | Component fatigue strength testing device | |
| CN107588972A (en) | A kind of Loading for actuator exerciser for simulating missile wing rudder face loading condition | |
| CN102954887B (en) | A kind of test unit measuring high-pressure turbine working blade damping | |
| CN205333412U (en) | Size adjustable pretightning force adj. tabular test piece anchor clamps of formula impact tester that drop hammer | |
| CN106018077A (en) | Test fixture for multi-axial fatigue crack propagation performance of CT samples | |
| CN105179533A (en) | Double-cylinder force measuring brake caliper |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210330 Address after: 100191 No.888, 8th floor, building 66, No.14 Huayuan North Road, Haidian District, Beijing Patentee after: Beijing tangrenxiang Technology Co.,Ltd. Address before: 100191 No. 37, Haidian District, Beijing, Xueyuan Road Patentee before: BEIHANG University |
|
| TR01 | Transfer of patent right |