CN204495552U - A kind of aerofoil profile clamping device for measuring blade twist rigidity - Google Patents
A kind of aerofoil profile clamping device for measuring blade twist rigidity Download PDFInfo
- Publication number
- CN204495552U CN204495552U CN201520204319.6U CN201520204319U CN204495552U CN 204495552 U CN204495552 U CN 204495552U CN 201520204319 U CN201520204319 U CN 201520204319U CN 204495552 U CN204495552 U CN 204495552U
- Authority
- CN
- China
- Prior art keywords
- grip block
- testpieces
- aerofoil profile
- clamping device
- aperture
- 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
Abstract
The utility model provides a kind of aerofoil profile clamping device for measuring blade twist rigidity, comprise a grip block, described grip block is rectangular parallelepiped, be vertical relation with the testpieces of parallel placement, the centre position of described grip block has match test part size, is the clamping hole of parallel relation with described testpieces, described grip block upper surface has two and reverses apertures centered by displacement axis near lateral edge position, described torsion aperture is perpendicular to testpieces, penetrate the lower surface of whole grip block to grip block from described grip block upper surface.Measure twisting resistance by direct perforate on this clamping device and wave power, avoiding groove aluminium of transferring in aerofoil profile, eliminate and load brought error on groove aluminium, decrease unnecessary workload.
Description
Technical field
The utility model relates to helicopter stiffness test field, is specifically related to a kind of stiffness test of blade.
Background technology
Helicopter blade torsional rigidity is by applying appropriate torque load to tested propeller-blade section by measuring the change of front and rear edges displacement between this cross-sectional area, to reach the test of torsional rigidity.When surveying torsional rigidity, designing airfoil fixture is needed to clamp mutually with blade, for ensureing with bending moment axis as the centre of twist, two kinds of methods are had to implement at present: one, to transfer one section of groove aluminium at the other end of aerofoil profile fixture, test by applying a pair couple on aerofoil profile fixture and groove aluminium, two, wrapped by whole aerofoil profile fixture with groove aluminium, test by applying a pair couple at groove aluminium two ends, load is delivered to change blade being carried out blade displacement by fixture.
By being loaded with following deficiency on groove aluminium:
1, groove aluminium is connected with aerofoil profile and does not belong to rigid connection, and in the process of load applying, groove aluminium can absorb the load of a part, thus can not ensure that 100% dynamic changes process is on testpieces, affects test accuracy;
2, add many workloads, groove aluminium need be cut out according to corresponding size, then also need on groove aluminium distribution, delay test progress when personnel and task abnormity anxiety;
If 3 load applied are comparatively large, easily cause groove aluminium to be out of shape, thus cause test to carry out.
Utility model content
For the above technical matters existed, the utility model proposes a kind of aerofoil profile clamping device for measuring blade twist rigidity, directly aerofoil profile is extended corresponding length according to loading demands, centered by displacement axis, two holes are joined in aerofoil profile two ends symmetry, apply a pair couple in the position in two holes and come short form test and installation thereof, improve test accuracy simultaneously.
A kind of aerofoil profile clamping device for measuring blade twist rigidity, comprise a grip block, described grip block is rectangular parallelepiped, be vertical relation with the testpieces of parallel placement, the centre position of described grip block has match test part size, is the clamping hole of parallel relation with described testpieces, described grip block upper surface has two and reverses apertures centered by displacement axis near lateral edge position, described torsion aperture is perpendicular to testpieces, penetrate the lower surface of whole grip block to grip block from described grip block upper surface.
Preferably, have above and below described clamping hole one be parallel to testpieces wave aperture, described in wave aperture and clamping hole distance be 1/4 of testpieces width, the width that described grip block is forward and backward is greater than clamping hole width.
Key point of the present utility model is that of avoiding groove aluminium of transferring in aerofoil profile, eliminates and load brought error on groove aluminium, decrease unnecessary workload.Following benefit is had when doing blade twist rigidity:
1, improve test accuracy, when applying couple, ensure that load is all applied on testpieces;
2, reduce labour intensity, improve work efficiency;
3, fixture is simple and practical, can simultaneously for waving rigidity, the test request of shimmy rigidity;
4, no matter magnitude of load can apply with this fixture, does not worry that fixture distortion causes test to carry out
Accompanying drawing explanation
Fig. 1 is for measuring the structural representation of a preferred embodiment of the aerofoil profile clamping device of blade twist rigidity according to the utility model.
Fig. 2 is the vertical view of grip block embodiment illustrated in fig. 1.
Fig. 3 is the front elevation of grip block embodiment illustrated in fig. 1.
Wherein, 1 is aerofoil profile fixture, and 2 is laser displacement sensor, and 3 is blade, and 4 is stationary fixture, and 5 is laser displacement sensor measurement point, and 6 is tested section, and 7 for reversing aperture, and 8 for waving aperture.
Embodiment
Below in conjunction with accompanying drawing to being described in further details for the aerofoil profile clamping device measuring blade twist rigidity involved by the utility model.
A kind of aerofoil profile clamping device for measuring blade twist rigidity, comprise a grip block, described grip block is rectangular parallelepiped, be vertical relation with the testpieces of parallel placement, the centre position of described grip block has match test part size, is the clamping hole of parallel relation with described testpieces, as shown in Figure 2, described grip block upper surface has two and reverses apertures centered by displacement axis near lateral edge position, described torsion aperture is perpendicular to testpieces, penetrate the lower surface of whole grip block to grip block from described grip block upper surface.
As shown in Figure 3, have above and below described clamping hole one be parallel to testpieces wave aperture, described in wave aperture and clamping hole distance be 1/4 of testpieces width, the width that described grip block is forward and backward is greater than clamping hole width.
As a kind of clamping device of tail-rotor, grip block adds and grows to 300mm, width is 100mm, thickness 40mm, at the marginal position of upper surface (300*40), centered by displacement axis, 30mm place, distance edge has two and reverses aperture, during test, first blade 3 one end is clamped by stationary fixture 4, the other end stretches in the clamping hole of aerofoil profile fixture 1, the laser displacement sensor measurement point 5 of tested section 6 surrounding installs laser displacement sensor 2, afterwards couple is applied to aerofoil profile fixture 1, namely on the torsion aperture of grip block, twisting resistance is applied, as shown in Figure 1, make two force directions contrary by pulley.
For another example a kind of clamping device of main oar, grip block adds and grows to 1000mm, width is 200mm, thickness 40mm, at the marginal position of upper surface (1000*40), centered by displacement axis, 60mm place, distance edge has two and reverses aperture, during test, the same with tail-rotor, first blade 3 one end is clamped by stationary fixture 4, the other end stretches in the clamping hole of aerofoil profile fixture 1, the laser displacement sensor measurement point 5 of tested section 6 surrounding installs laser displacement sensor 2, afterwards couple is applied to aerofoil profile fixture 1, namely on the torsion aperture of grip block, twisting resistance is applied, as shown in Figure 1, make two force directions contrary by pulley.
This fixture has following benefit when doing blade twist rigidity:
1, improve test accuracy.When applying couple, ensure that load is all applied on testpieces;
2, reduce labour intensity, improve work efficiency;
3, fixture is simple and practical, can simultaneously for waving rigidity, the test request of shimmy rigidity;
4, no matter magnitude of load can apply with this fixture, does not worry that fixture distortion causes test to carry out.
It should be noted that; the utility model comprises any one and combination in any thereof in above-described embodiment for the aerofoil profile clamping device measuring blade twist rigidity; but embodiment recited above is only be described preferred implementation of the present utility model; not the utility model scope is limited; do not departing under the utility model designs spiritual prerequisite; the various distortion that the common engineering technical personnel in this area make the technical solution of the utility model and improvement, all should fall in protection domain that claims of the present utility model determine.
Claims (2)
1. one kind for measuring the aerofoil profile clamping device of blade twist rigidity, it is characterized in that: comprise a grip block, described grip block is rectangular parallelepiped, be vertical relation with the testpieces of parallel placement, the centre position of described grip block has match test part size and is the clamping hole of parallel relation with described testpieces, described grip block upper surface has two and reverses aperture centered by displacement axis near lateral edge position, described torsion aperture perpendicular to testpieces, and passes the lower surface of whole grip block to grip block from described grip block upper surface.
2. the aerofoil profile clamping device for measuring blade twist rigidity according to claim 1, it is characterized in that: on described grip block directly over clamping hole and immediately below have one be parallel to testpieces wave aperture, described distance of waving aperture and clamping hole is 1/4 of testpieces width, and the width that described grip block is forward and backward is greater than clamping hole width.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520204319.6U CN204495552U (en) | 2015-04-07 | 2015-04-07 | A kind of aerofoil profile clamping device for measuring blade twist rigidity |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520204319.6U CN204495552U (en) | 2015-04-07 | 2015-04-07 | A kind of aerofoil profile clamping device for measuring blade twist rigidity |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204495552U true CN204495552U (en) | 2015-07-22 |
Family
ID=53574857
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520204319.6U Active CN204495552U (en) | 2015-04-07 | 2015-04-07 | A kind of aerofoil profile clamping device for measuring blade twist rigidity |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204495552U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105181318A (en) * | 2015-09-23 | 2015-12-23 | 华北电力大学（保定） | Wind power generator blade bending-torsional coupling vector measuring device |
| CN106802247A (en) * | 2015-11-26 | 2017-06-06 | 中国直升机设计研究所 | A kind of composite rear fatigue and defect tolerance experimental rig |
| CN108225692A (en) * | 2017-12-01 | 2018-06-29 | 中国直升机设计研究所 | A kind of measurement blade entirety torsional rigidity test of vehicular method |
| CN109506862A (en) * | 2018-11-12 | 2019-03-22 | 中国直升机设计研究所 | A kind of flexible beam tail-rotor leaf stiffness test device |
| CN109668502A (en) * | 2017-10-16 | 2019-04-23 | 上海同济检测技术有限公司 | Profile reverses measuring device |
| CN112484951A (en) * | 2020-11-24 | 2021-03-12 | 北京航空航天大学 | Portable wind tunnel test supporting device with adjustable attack angle and two-degree-of-freedom elastic support |
| CN112504873A (en) * | 2020-10-30 | 2021-03-16 | 中国直升机设计研究所 | Vertical rotor blade torsional rigidity measuring system and measuring method |
| CN114701659A (en) * | 2022-04-02 | 2022-07-05 | 航天特种材料及工艺技术研究所 | Characterization testing device and method for small-load bending and torsion deformation of composite material airfoil |
-
2015
- 2015-04-07 CN CN201520204319.6U patent/CN204495552U/en active Active
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105181318A (en) * | 2015-09-23 | 2015-12-23 | 华北电力大学（保定） | Wind power generator blade bending-torsional coupling vector measuring device |
| CN105181318B (en) * | 2015-09-23 | 2018-08-10 | 华北电力大学（保定） | A kind of blade of wind-driven generator Torsion Coupling vector measurement device |
| CN106802247A (en) * | 2015-11-26 | 2017-06-06 | 中国直升机设计研究所 | A kind of composite rear fatigue and defect tolerance experimental rig |
| CN106802247B (en) * | 2015-11-26 | 2019-03-01 | 中国直升机设计研究所 | A kind of composite material endpiece fatigue and defect tolerance experimental rig |
| CN109668502A (en) * | 2017-10-16 | 2019-04-23 | 上海同济检测技术有限公司 | Profile reverses measuring device |
| CN108225692A (en) * | 2017-12-01 | 2018-06-29 | 中国直升机设计研究所 | A kind of measurement blade entirety torsional rigidity test of vehicular method |
| CN109506862A (en) * | 2018-11-12 | 2019-03-22 | 中国直升机设计研究所 | A kind of flexible beam tail-rotor leaf stiffness test device |
| CN112504873A (en) * | 2020-10-30 | 2021-03-16 | 中国直升机设计研究所 | Vertical rotor blade torsional rigidity measuring system and measuring method |
| CN112484951A (en) * | 2020-11-24 | 2021-03-12 | 北京航空航天大学 | Portable wind tunnel test supporting device with adjustable attack angle and two-degree-of-freedom elastic support |
| CN112484951B (en) * | 2020-11-24 | 2022-02-11 | 北京航空航天大学 | Portable wind tunnel test supporting device with adjustable attack angle and two-degree-of-freedom elastic support |
| CN114701659A (en) * | 2022-04-02 | 2022-07-05 | 航天特种材料及工艺技术研究所 | Characterization testing device and method for small-load bending and torsion deformation of composite material airfoil |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204495552U (en) | A kind of aerofoil profile clamping device for measuring blade twist rigidity | |
| EP2886264A3 (en) | Device for processing a structure and spacecraft | |
| CN203929532U (en) | A kind of jointing testing device for shear strength | |
| CN104589231A (en) | Sliding type positioning clamp | |
| CN103512801B (en) | A kind of stretching force-measuring sensor | |
| CN102709845B (en) | Ground wire lifter | |
| CN202196007U (en) | Peel strength testing device | |
| CN205733938U (en) | A kind of clamping position frock for support roller hanger boring | |
| CN208681374U (en) | A kind of blade detection fixture for Quanta200 scanning electron microscope | |
| CN207650012U (en) | A kind of thin plate high-speed stretch sample line-up jig | |
| CN205941190U (en) | Integral type pushes away tensile testing machine with swivel work head | |
| CN202846081U (en) | Wedge-shaped welding fixture device | |
| CN104297075A (en) | A metal wire torsion test method for a steel wire rope | |
| CN205538300U (en) | Metallographic specimen cutting jig | |
| CN208334057U (en) | A kind of longitudinal stretching shearing test clamp | |
| CN205201368U (en) | Vibration test clamp | |
| CN205719507U (en) | The logical oil draining bolt torque tester of braking | |
| CN207106940U (en) | A kind of clamping device | |
| CN206563679U (en) | A kind of mobile phone center strength testing device | |
| CN104807696B (en) | A kind of method that testing machine and service-test machine carry out testpieces centering setting | |
| CN204985364U (en) | Thrust bearing axial interval adjusting device in pairs | |
| CN208653926U (en) | A kind of quiet, dynamic clamp of elevator operating system test | |
| CN206504943U (en) | Tensile test work piece holder | |
| CN203791880U (en) | Bucket rod A-support oil pipe locating device of excavator | |
| CN208543152U (en) | Plate-side plate welding fixation kit |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |