CN104697754A - Blade root section fatigue test device - Google Patents
Blade root section fatigue test device Download PDFInfo
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- CN104697754A CN104697754A CN201310646285.1A CN201310646285A CN104697754A CN 104697754 A CN104697754 A CN 104697754A CN 201310646285 A CN201310646285 A CN 201310646285A CN 104697754 A CN104697754 A CN 104697754A
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Abstract
The invention provides a blade root section fatigue test device which is convenient to use, simple to operate and high in test load accuracy. According to the technical scheme of the invention, the device comprises a fixed supporting mechanism, an excitation loading mechanism, position limiting mechanisms, a swing actuating mechanism, a centrifugal force actuating mechanism, and a steel cable, wherein the fixed supporting mechanism is connected with a blade root end of a test piece, the left end of the excitation loading mechanism is connected with a process connector end of the test piece, the right end of the excitation loading mechanism is connected with the centrifugal force actuating mechanism, the upper end of the excitation loading mechanism is connected with the swing actuating mechanism, the joint between the fixed supporting mechanism and the blade root end of the test piece can rotate around the axis, the joint between the left end of the excitation loading mechanism and the process connector end of the test piece can rotate around the axis, and the position limiting mechanisms are respectively arranged at the front and rear sides of the excitation loading mechanism.
Description
Technical field
The invention belongs to helicopter blade experimental technique, relate 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 vitals of rotor system, determines the fatigue properties of propeller shank section, for blade Fatigue Life Assessment provides reliable foundation.When carrying out torture test, needing the centrifugal force of Control experiment part, waving dynamical bending moment and pendular oscillation moment of flexure.Main propeller shank section torture test is in the past all complete on main blade section fatigue test board, and except the cause influence test progress of shared test resource, the setup time that changes the outfit of testing table is long, and workload is large, and Loading Control precision is relatively poor.
Summary of the invention
The technical problem to be solved in the present invention: a kind of propeller shank section fatigue experimental device is provided, easy to use, simple to operate, test load precision is high.
Technical scheme of the present invention: a kind of propeller shank section fatigue experimental device, is characterized in that, comprising:
Clamped mechanism, exciting load maintainer, position-limit mechanism, Hui Bai topworks, centrifugal force topworks, 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, and exciting load maintainer right-hand member is connected with centrifugal force topworks by cable wire, and exciting load maintainer upper end is connected with Hui Bai topworks;
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 both sides before and after exciting load maintainer.
Beneficial effect of the present invention: wave moment of flexure and shimmy moment of flexure and loaded in the mode of synthesis by exciting load maintainer by shimmy topworks, exciting load maintainer position-limit mechanism carries out spacing, ensures that exciting load maintainer can only have up and down and the motion of left and right directions.Centrifugal force puts on testpieces by centrifugal force topworks by cable wire and exciting load maintainer, due to flexibly connecting by cable wire, can reduce centrifugal force to the impact of waving moment of flexure and shimmy moment of flexure.Conveniently adjusted to the test load needed for testpieces by the stroke of Adjustment Tests part established angle and Hui Bai topworks.In a word, the present invention can meet the boundary condition requirement of testpieces, easy to use, simple to operate, improves Loading Control precision, has been successfully applied to torture test and the residual intensity test of Helicopter Main propeller shank section.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 is exciting load maintainer 2 structural representation of the present invention.
Fig. 3 is the enforcement illustration of the clamped mechanism 1 of the present invention.
Fig. 4 is the embodiment of exciting load maintainer 2 of the present invention.
Embodiment
Below the present invention is described in further details.See Fig. 1 ~ 2, a kind of propeller shank section fatigue experimental device, comprises clamped mechanism 1, exciting load maintainer 2, position-limit mechanism 3, Hui Bai topworks 4, centrifugal force topworks 5, cable wire 6 and root section testpieces 7.The blade root end of testpieces 7 is connected with clamped mechanism 1, and the process connection end of testpieces 7 is connected with exciting load maintainer 2; Centrifugal force puts on testpieces 7 by centrifugal force topworks 5 by cable wire 6 and exciting load maintainer 2; Wave moment of flexure and shimmy moment of flexure to be loaded in the mode of synthesis by exciting load maintainer 2 by shimmy topworks 4; Testpieces 7 can around the axis in its centrifugal force direction with arbitrarily angled installation.
The clamped joint 1b that clamped mechanism 1 comprises heavy frame 1a and is connected with the blade root end of testpieces 7.Clamped joint 1b can be fixed on heavy frame 1a with unspecified angle around the axis of testpieces 7, and fixed form can compress mode for ring flange, also can be other types of attachment such as circumferential waist-shaped hole docking.
The loading joint 2f that exciting load maintainer 2 comprises excitation head 2a, waves pendulum loading head 2b, waves pendulum bearing pin 2c, centrifugal force loading head 2d, centrifugal force bearing pin 2e and be connected with the process connection end of testpieces 7.Waving pendulum loading head 2b one end is articulated with on excitation head 2a by waving pendulum bearing pin 2c, and other one end is connected with Hui Bai topworks 4.Centrifugal force loading head 2d one end is articulated with on excitation head 2a by waving pendulum bearing pin 2e, and other one end is connected with centrifugal force topworks 5 by cable wire 6.Loading joint 2f can be fixed on excitation head 2a with unspecified angle around the axis of testpieces, and fixed form can be being spirally connected of locking nut anti-looseness, also can be that ring flange compresses other type of attachment such as mode or circumferential waist-shaped hole docking.
Wave pendulum bearing pin 2c and centrifugal force bearing pin 2e can concentrate on a shaft, now wave pendulum loading head 2b and centrifugal force loading head 2d and be articulated with on common axis 2ce simultaneously.Wave pendulum loading head 2b, centrifugal force loading head 2d and excitation head 2a tri-all any at the position relationship of fore-and-aft direction, if excitation head 2a is not in outermost, then need install limited piece of 2g additional at the two ends of common axis 2ce.
It is shimmy that position-limit mechanism 3 is used for preventing exciting load maintainer 2 at fore-and-aft direction, two all between only allow up and down and the relative motion of left and right directions.Position-limit mechanism 3 can select the scheme in ZL201020701291.4.
Hui Bai topworks 4 can be that various gas (liquid) pressure or electromagnetism perform actuator, also can be eccentric mechanism or electromagnetic exciting mechanism; Centrifugal force is generally static load, and centrifugal force topworks 5 can be that various gas (liquid) pressure or electromagnetism perform actuator.
Principle of work of the present invention is: be installed on this test unit with certain angle by testpieces 7, control centrifugal force topworks 5 pairs of testpieces 7 and apply required centrifugal force, control Nian Huibai topworks 4 pairs of testpieces 7 apply certain displacement alternation value, if now wave the demand that moment of flexure and shimmy moment of flexure can not reach test load simultaneously, then need to unclamp the clamped joint 1b that is connected with testpieces 7 two ends and load joint 2f, rotate testpieces with after adjusting setting angle, then carry out above-mentioned load applying.So repeatedly, until wave the demand that moment of flexure and shimmy moment of flexure reach test load simultaneously, then load debugging terminates, and can formally test.
Embodiment:
Embodiment 1, the fixed form of clamped joint 1b is that ring flange compresses mode.As shown in Figure 3, by ring flange 1d and bolt and nut group 1c, clamped joint 1b is fixed on load and adds on 1a, unclamp bolt and nut group 1c, clamped joint 1b can around the rotation of 360 °, its axis.
Embodiment 2, the fixed form loading joint 2f is being spirally connected of locking nut anti-looseness.As shown in Figure 2 and Figure 4, load joint 2f and docked with excitation head 2a by screw thread, and by set nut, both are locked.
Embodiment 3, wave pendulum bearing pin 2c and centrifugal force bearing pin 2e and concentrate on an axle---on common axis 2ce.As shown in Figure 4, because centrifugal force loading head 2d is positioned at outside excitation head 2a, limited piece of 2g is installed additional at the two ends of common axis 2ce.
Claims (4)
1. a propeller shank section fatigue experimental device, is characterized in that, comprising:
Clamped mechanism, exciting load maintainer, position-limit mechanism, Hui Bai topworks, centrifugal force topworks, 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, and exciting load maintainer right-hand member is connected with centrifugal force topworks by cable wire, and exciting load maintainer upper end is connected with Hui Bai topworks;
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 both sides before and after exciting load maintainer.
2. the propeller shank section fatigue experimental device according to right 1, is characterized in that, the clamped joint that clamped mechanism comprises heavy frame and is connected with the blade root end of testpieces, and clamped joint can be fixed on heavy frame with unspecified angle around the axis of testpieces.
3. the propeller shank section fatigue experimental device according to right 1, is characterized in that, the loading joint that exciting load maintainer comprises excitation head, waves pendulum loading head, waves pendulum bearing pin, centrifugal force loading head, centrifugal force bearing pin and be connected with the process connection end of testpieces; Wave pendulum loading head one end by waving pendulum hinge on excitation head, other one end is connected with Hui Bai topworks; Centrifugal force loading head one end is by waving pendulum hinge on excitation head, and other one end is connected with centrifugal force topworks by cable wire; Load joint to be fixed on excitation head with unspecified angle around the axis of testpieces.
4. the propeller shank section fatigue experimental device according to right 3, is characterized in that, wave pendulum bearing pin and centrifugal force bearing pin can concentrate on a shaft, now wave pendulum loading head and centrifugal force loading head be articulated with on this axle simultaneously.
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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| Publication Number | Publication Date |
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| CN104697754A true CN104697754A (en) | 2015-06-10 |
| CN104697754B CN104697754B (en) | 2017-08-29 |
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| CN201310646285.1A Active CN104697754B (en) | 2013-12-04 | 2013-12-04 | A kind of propeller shank section fatigue experimental device |
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Cited By (12)
| 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 |
| CN106370370A (en) * | 2016-08-17 | 2017-02-01 | 中国航空工业集团公司西安飞行自动控制研究所 | Rapidly changeable actuator vibration test clamp |
| 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 |
| CN109506911A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Load testing machine |
| CN109506908A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Endpiece testpieces fatigue test horizontal tail load charger |
| 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 |
| CN110884683A (en) * | 2019-12-04 | 2020-03-17 | 中国直升机设计研究所 | Helicopter blade pin flight load testing method |
| CN110901949A (en) * | 2019-10-15 | 2020-03-24 | 中国直升机设计研究所 | Helicopter blade strength test method |
| CN111645877A (en) * | 2020-05-07 | 2020-09-11 | 南京华航翼飞行器技术有限公司 | Seesaw type rotor wing fatigue test device and working method thereof |
| CN112504589A (en) * | 2020-10-30 | 2021-03-16 | 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 |
| CN113670739A (en) * | 2021-08-17 | 2021-11-19 | 无锡瑞来检测科技有限公司 | Helicopter main rotating blade fatigue test device |
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Cited By (17)
| 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 |
| CN106370370A (en) * | 2016-08-17 | 2017-02-01 | 中国航空工业集团公司西安飞行自动控制研究所 | Rapidly changeable actuator vibration test clamp |
| 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 |
| 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 |
| CN109506911A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Load testing machine |
| CN109506908A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Endpiece testpieces fatigue test horizontal tail load charger |
| CN110901949B (en) * | 2019-10-15 | 2022-06-03 | 中国直升机设计研究所 | Helicopter blade strength test method |
| CN110901949A (en) * | 2019-10-15 | 2020-03-24 | 中国直升机设计研究所 | Helicopter blade strength test method |
| CN110884683A (en) * | 2019-12-04 | 2020-03-17 | 中国直升机设计研究所 | Helicopter blade pin flight load testing method |
| 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 |
| 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 |
| CN111645877A (en) * | 2020-05-07 | 2020-09-11 | 南京华航翼飞行器技术有限公司 | Seesaw type rotor wing fatigue test device and working method thereof |
| CN112504589A (en) * | 2020-10-30 | 2021-03-16 | 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 |
| CN113670739A (en) * | 2021-08-17 | 2021-11-19 | 无锡瑞来检测科技有限公司 | Helicopter main rotating blade fatigue test device |
| 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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| CN104697754B (en) | 2017-08-29 |
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