CN104697754B - A kind of propeller shank section fatigue experimental device - Google Patents
A kind of propeller shank section fatigue experimental device Download PDFInfo
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- CN104697754B CN104697754B CN201310646285.1A CN201310646285A CN104697754B CN 104697754 B CN104697754 B CN 104697754B CN 201310646285 A CN201310646285 A CN 201310646285A CN 104697754 B CN104697754 B CN 104697754B
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Abstract
The present invention provides a kind of propeller shank section fatigue experimental device, and easy to use, simple to operate, test load precision is high.Technical scheme includes：Clamped mechanism, exciting load maintainer, position-limit mechanism, Hui Bai executing agencies, centrifugal force executing agency, cable wire, clamped mechanism is connected with the blade root end of testpieces, exciting load maintainer left end is connected with the process connection end of testpieces, exciting load maintainer right-hand member is connected by cable wire with centrifugal force executing agency, and exciting load maintainer upper end is connected with Hui Bai executing agencies；The blade root end junction of clamped mechanism and testpieces can be rotated about axis；The process connection end junction of exciting load maintainer left end and testpieces can be rotated about axis；Limited location mechanism is located at exciting load maintainer front and rear sides.
Description
Technical field
The invention belongs to helicopter blade experimental technique, it is related to a kind of propeller shank section fatigue experimental device.
Background technology
Rotor system is the important guarantee of helicopter lift system, and blade is the important component of rotor system, determines oar
The fatigue properties of blade root section, reliable foundation is provided for blade Fatigue Life Assessment.When carrying out fatigue test, it is necessary to control
The centrifugal force of testpieces, wave dynamical bending moment and shimmy dynamical bending moment.Main propeller shank section fatigue test in the past is all in main blade
Completed on airfoil section fatigue test board, influence is tested into being outside one's consideration the reason for except shared experiment resource, testing stand change the outfit preparation when
Between it is long, workload is big, and Loading Control precision is relatively poor.
The content of the invention
The technical problem to be solved in the present invention：A kind of propeller shank section fatigue experimental device, easy to use, operation letter are provided
Single, test load precision is high.
Technical scheme：A kind of propeller shank section fatigue experimental device, it is characterised in that including：
Clamped mechanism, exciting load maintainer, position-limit mechanism, Hui Bai executing agencies, centrifugal force executing agency, cable wire,
Clamped mechanism is connected with the blade root end of testpieces, the process connection end phase of exciting load maintainer left end and testpieces
Even, exciting load maintainer right-hand member is connected by cable wire with centrifugal force executing agency, and exciting load maintainer upper end is with waving pendulum execution machine
Structure is connected；
The blade root end junction of clamped mechanism and testpieces can be rotated about axis；Exciting load maintainer left end and testpieces
Process connection end junction can be rotated about axis；
Limited location mechanism is located at exciting load maintainer front and rear sides.
Beneficial effects of the present invention：Wave moment of flexure and shimmy moment of flexure by shimmy executing agency by exciting load maintainer to close
Into mode load, exciting load maintainer position-limit mechanism carry out it is spacing, it is ensured that above and below exciting load maintainer can only have and right and left
To motion.Centrifugal force is put on testpieces by centrifugal force executing agency by cable wire and exciting load maintainer, due to passing through
The flexible connection of cable wire, can reduce centrifugal force to waving the influence of moment of flexure and shimmy moment of flexure.By Adjustment Tests part established angle and
The conveniently adjusted test load to needed for testpieces of stroke of Hui Bai executing agencies.In a word, the present invention can meet testpieces
Boundary condition requirement, it is easy to use, simple to operate, Loading Control precision is improved, Helicopter Main blade root has been successfully applied to
The fatigue test of section and residual intensity test.
Brief description of the drawings
Fig. 1 is the structural representation of the present invention.
Fig. 2 is the structural representation of exciting load maintainer 2 of the present invention.
Fig. 3 is the implementation illustration of clamped mechanism 1 of the invention.
Fig. 4 is the embodiment of exciting load maintainer 2 of the present invention.
Embodiment
The present invention is described in further details below.Referring to Fig. 1~2, a kind of propeller shank section fatigue experimental device, bag
Include clamped mechanism 1, exciting load maintainer 2, position-limit mechanism 3, Hui Bai executing agencies 4, centrifugal force executing agency 5, cable wire 6 and root
Section testpieces 7.The blade root end of testpieces 7 is connected with clamped mechanism 1, process connection end and the phase of exciting load maintainer 2 of testpieces 7
Even；Centrifugal force is put on testpieces 7 by centrifugal force executing agency 5 by cable wire 6 and exciting load maintainer 2；Wave moment of flexure and
Shimmy moment of flexure is by shimmy executing agency 4 exciting load maintainer 2 to be loaded by way of synthesizing；Testpieces 7 can be around its centrifugation
The axis of force direction is installed with any angle.
Clamped mechanism 1 includes heavy frame 1a and the clamped joint 1b being connected with the blade root end of testpieces 7.Clamped joint 1b energy
Enough axis around testpieces 7 are fixed on unspecified angle on heavy frame 1a, and fixed form can compress mode for ring flange, also may be used
Think other types of attachment such as circumferential waist-shaped hole docking.
Exciting load maintainer 2 includes excitation head 2a, waves pendulum loading head 2b, waves pendulum bearing pin 2c, centrifugal force loading head 2d, centrifugation
The power bearing pin 2e and loading joint 2f being connected with the process connection end of testpieces 7.Pendulum loading head 2b one end is waved by waving pendulum bearing pin
2c is articulated with excitation head 2a, and other one end is connected with Hui Bai executing agencies 4.Centrifugal force loading head 2d one end is by waving pendulum bearing pin 2e
It is articulated with excitation head 2a, other one end is connected by cable wire 6 with centrifugal force executing agency 5.Loading joint 2f can be around testpieces
Axis be fixed on unspecified angle on excitation head 2a, fixed form can be spirally connected for locking nut anti-looseness, or
Ring flange compresses other types of attachment such as mode or circumferential waist-shaped hole docking.
Waving pendulum bearing pin 2c and centrifugal force bearing pin 2e can concentrate on a shaft, now wave pendulum loading head 2b and centrifugal force adds
Carrier head 2d is articulated with common axis 2ce simultaneously.Pendulum loading head 2b, centrifugal force loading head 2d and excitation head 2a tri- are waved all in front and back
To position relationship it is any, if excitation head 2a need to be installed additional at common axis 2ce two ends not in outermost and be limited block 2g.
Position-limit mechanism 3 is used for preventing exciting load maintainer 2 in the shimmy of fore-and-aft direction, two all between only allow to have above and below and
The relative motion of left and right directions.The scheme that position-limit mechanism 3 can be selected in ZL201020701291.4.
Hui Bai executing agencies 4 can for various gas (liquid) pressure or electromagnetism perform actuator, or eccentric mechanism or
Electromagnetic exciting mechanism；Centrifugal force is generally static load, and centrifugal force executing agency 5 can be that various gas (liquid) pressure or electromagnetism are performed
Actuator.
The present invention operation principle be：Testpieces 7 is installed on this experimental rig at an angle, centrifugal force is controlled
Executing agency 5 applies required centrifugal force to testpieces 7, and control Nian Huibai executing agencies 4 apply certain displacement to testpieces 7
Alternation value is measured, if now waving moment of flexure and shimmy moment of flexure can not need to unclamp and experiment while reach the demand of test load
The connected clamped joint 1b in the two ends of part 7 and loading joint 2f, rotates testpieces to adjust after setting angle, then carry out above-mentioned load
Lotus applies.So repeatedly, until waving moment of flexure and shimmy moment of flexure while reaching the demand of test load, then load debugging terminates,
Can formally it be tested.
Embodiment：
Embodiment 1, clamped joint 1b fixed form compresses mode for ring flange.As shown in figure 3, by ring flange 1d and
Clamped joint 1b is fixed on load plus 1a by bolt and nut group 1c, unclamps bolt and nut group 1c, clamped joint 1b can be around it
360 ° of rotations of axis.
Embodiment 2, loading joint 2f fixed form being spirally connected for locking nut anti-looseness.As shown in Figure 2 and Figure 4, plus
Carry joint 2f to dock with excitation head 2a by screw thread, and locked both by locking nut.
Embodiment 3, waves pendulum bearing pin 2c and centrifugal force bearing pin 2e and concentrates on an axle --- on common axis 2ce.Such as Fig. 4 institutes
Show, because centrifugal force loading head 2d is located on the outside of excitation head 2a, is installed additional at common axis 2ce two ends and be limited block 2g.
Claims (2)
1. a kind of propeller shank section fatigue experimental device, it is characterised in that including：
Clamped mechanism, exciting load maintainer, position-limit mechanism, Hui Bai executing agencies, centrifugal force executing agency, cable wire,
Clamped mechanism is connected with the blade root end of testpieces, and exciting load maintainer left end is connected with the process connection end of testpieces, swashs
The load maintainer right-hand member that shakes is connected by cable wire with centrifugal force executing agency, and exciting load maintainer upper end connects with Hui Bai executing agencies
Connect；
The blade root end junction of clamped mechanism and testpieces can be rotated about axis；The work of exciting load maintainer left end and testpieces
Skill tip side junction can be rotated about axis；
Limited location mechanism is located at exciting load maintainer front and rear sides；
Clamped mechanism includes heavy frame and the clamped joint being connected with the blade root end of testpieces, and clamped joint can be around testpieces
Axis is fixed on heavy frame with unspecified angle；
Exciting load maintainer include excitation head, wave pendulum loading head, wave pendulum bearing pin, centrifugal force loading head, centrifugal force bearing pin and with examination
Test the connected loading joint in the process connection end of part；Pendulum loading head one end is waved by waving pendulum hinge on excitation head, other one
End is connected with Hui Bai executing agencies；Centrifugal force loading head one end is by waving pendulum hinge on excitation head, and other one end passes through steel
Rope is connected with centrifugal force executing agency；Loading joint can be fixed on excitation head around the axis of testpieces with unspecified angle.
2. propeller shank section fatigue experimental device according to claim 1, it is characterised in that wave pendulum bearing pin and centrifugal force pin
Axle is concentrated on a shaft, now waves pendulum loading head and centrifugal force loading head while being articulated with this axle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310646285.1A CN104697754B (en) | 2013-12-04 | 2013-12-04 | A kind of propeller shank section fatigue experimental device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310646285.1A CN104697754B (en) | 2013-12-04 | 2013-12-04 | A kind of propeller shank section fatigue experimental device |
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| CN104697754A CN104697754A (en) | 2015-06-10 |
| CN104697754B true CN104697754B (en) | 2017-08-29 |
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Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104729846A (en) * | 2015-04-07 | 2015-06-24 | 中国直升机设计研究所 | Automatic inclinator nonrotating ring fatigue test device |
| CN106370370B (en) * | 2016-08-17 | 2019-01-25 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of actuator vibration test fixture that can be quickly converted |
| CN106768920A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of fatigue experimental device |
| CN107860565A (en) * | 2017-10-11 | 2018-03-30 | 昌河飞机工业（集团）有限责任公司 | A kind of loading device of helicopter simulating blade stress |
| CN109506911B (en) * | 2018-11-09 | 2020-10-23 | 中国直升机设计研究所 | Loading test device |
| CN109506908B (en) * | 2018-11-09 | 2020-10-23 | 中国直升机设计研究所 | Tail end load loading device for fatigue test of tail section test piece |
| CN110901949B (en) * | 2019-10-15 | 2022-06-03 | 中国直升机设计研究所 | Helicopter blade strength test method |
| CN110884686A (en) * | 2019-12-04 | 2020-03-17 | 中国直升机设计研究所 | Transformation and test method of fatigue test piece of helicopter blade airfoil section |
| CN110884683B (en) * | 2019-12-04 | 2022-04-29 | 中国直升机设计研究所 | Helicopter blade pin flight load testing method |
| CN112504589B (en) * | 2020-10-30 | 2023-08-04 | 哈尔滨飞机工业集团有限责任公司 | Helicopter composite material main blade airfoil section static strength test system and method |
| CN113670739B (en) * | 2021-08-17 | 2024-04-26 | 无锡瑞来新材料科技有限公司 | Helicopter main rotor blade fatigue test device |
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| CN201974279U (en) * | 2010-12-31 | 2011-09-14 | 中国直升机设计研究所 | Excitation head limiting device for fatigue test of helicopter blades |
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| CN201974279U (en) * | 2010-12-31 | 2011-09-14 | 中国直升机设计研究所 | Excitation head limiting device for fatigue test of helicopter blades |
| EP2725337A1 (en) * | 2012-10-24 | 2014-04-30 | Eurocopter Deutschland GmbH | Fatigue management system and method of operating such a fatigue management system |
| CN103439131A (en) * | 2013-08-19 | 2013-12-11 | 北京航空航天大学 | Fatigue testing system for large-tonnage helicopter tail rotor servo actuator |
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| CN104697754A (en) | 2015-06-10 |
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