CN107860565A - A kind of loading device of helicopter simulating blade stress - Google Patents
A kind of loading device of helicopter simulating blade stress Download PDFInfo
- Publication number
- CN107860565A CN107860565A CN201710941329.1A CN201710941329A CN107860565A CN 107860565 A CN107860565 A CN 107860565A CN 201710941329 A CN201710941329 A CN 201710941329A CN 107860565 A CN107860565 A CN 107860565A
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- China
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- steel wire
- wire rope
- joint
- test specimen
- testpieces
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The present invention relates to a kind of loading device of helicopter simulating blade stress, including support (1) technique for fixing beam (2) one end, technique beam (2) another end is connected with testpieces (3), testpieces (3) is connected with joint (4), steel wire rope (5) is attached joint (4), there is buffer (6) among steel wire rope (5), steel wire rope (5) is connected with puller system (7), and steel wire rope (5) and puller system (7) hinge are on support bar (10).By the ingehious design of exciting device, the simulation of air and testpieces power is realized；By puller system ingehious design, the simulation of testpieces centrifugal force is realized.Centrifugal force can be realized at the test condition, wave and shimmy power while load, and loading procedure is reliable and stable, loading procedure distortion when having avoided the longevity part from being tested.
Description
Technical field
The invention belongs to experiment loading unit, is related to and anti-interference loading is carried out to testpieces.
Background technology
According to navigation mark HB5935 (6.2.3) articles and national military standard GJB720.4 (4.2.1) article mandatory provisions, AC311
And AC313 type machines blade need to carry out customary fatigue test, some items being related in the experiment including main blade and tail-rotor leaf
Experiment.
To realize the experiment, each position stressing conditions when need to design a set of helicopter simulating blade work.To blade stress
Analyzed, the stress of blade relates generally to three key elements：Wave, shimmy and centrifugal force.
It is due to that blade is rotated and produced to wave with the shimmy result for being due to blade with air interaction, centrifugal force；
In helicopter live flying, because various components interfere, it is difficult to monitored in time of day, it is necessary in experimental enviroment
Simulated.
Therefore, it is very notable to design a kind of " loading device of helicopter simulating blade stress " necessity.
The content of the invention
The purpose of the present invention is：Design a kind of loading device of helicopter simulating blade stress, make testpieces in experiment shape
Centrifugal force can be realized under state, waves and shimmy power while loads, and loading procedure is reliable and stable, has avoided longevity part from being tested
When loading procedure distortion.
The technical scheme is that a kind of loading device of helicopter simulating blade stress, including support (1) regular worker
Skill beam (2) one end, technique beam (2) another end are connected with testpieces (3), and testpieces (3) is connected with joint (4), steel wire rope (5)
Joint (4) is attached, and has buffer (6) among steel wire rope (5), steel wire rope (5) is connected with puller system (7), steel wire rope (5)
With puller system (7) hinge on support bar (10)；
Exciting device (8) is connected with motor (9), and exciting device (8) couples with joint (4) rigidity.
Support (1) lower end is fixed, upper end hinge technique beam (2), and when test specimen (3) vibrates, technique beam (2) can be around hinge
Point rotates.Joint (4) is linked to be an entirety with test specimen (3), exciting device (8) and steel wire rope (5), and steel wire rope (5) is to test specimen (3)
Pulling force is provided to simulate centrifugal force, the size of centrifugal force is realized by puller system (7)；Exciting device (8) carries to test specimen (3)
Waved and shimmy for exciting force, wave and shimmy difference can be adjusted by the angle of joint (4), the size of exciting force
Changed by the rotating speed of motor (9) to realize.
It is an advantage of the invention that：By the ingehious design of exciting device, the simulation of air and testpieces power is realized；Pass through
Puller system ingehious design, realize the simulation of testpieces centrifugal force.Centrifugal force can be realized at the test condition, wave
And shimmy power loads simultaneously, and loading procedure is reliable and stable, loading procedure distortion when having avoided the longevity part from being tested.
Brief description of the drawings
Fig. 1, it is structural representation of the invention, support (1), technique beam (2), testpieces (3) are connected, test specimen (3), joint
(4), steel wire rope (5), buffer (6), puller system (7), exciting device (8), motor (9), connection support bar (10).
Embodiment
The present invention is described in further detail with reference to Figure of description.
A kind of loading device of helicopter simulating blade stress, including support (1) technique for fixing beam (2) one end, technique beam
(2) another end is connected with testpieces (3), and testpieces (3) is connected with joint (4), and steel wire rope (5) is attached joint (4), steel
There is buffer (6) among cord (5), steel wire rope (5) is connected with puller system (7), steel wire rope (5) and puller system (7) hinge
On support bar (10)；
Exciting device (8) is connected with motor (9), and exciting device (8) couples with joint (4) rigidity.
Support (1) lower end is fixed, upper end hinge technique beam (2), and when test specimen (3) vibrates, technique beam (2) can be around hinge
Point rotates.Joint (4) is linked to be an entirety with test specimen (3), exciting device (8) and steel wire rope (5), and steel wire rope (5) is to test specimen (3)
Pulling force is provided to simulate centrifugal force, the size of centrifugal force is realized by puller system (7)；Exciting device (8) carries to test specimen (3)
Waved and shimmy for exciting force, wave and shimmy difference can be adjusted by the angle of joint (4), the size of exciting force
Changed by the rotating speed of motor (9) to realize.
In use, first rotating motor (9), exciting device (8) is driven, exciting device (8) can only be moved up and down, and it is transported
Dynamic amplitude is determined that exciting is transmitted to joint (4) by exciting device (8) by electronic rotating speed, then is transmitted to test specimen (3).Due to test specimen
(3) with technique beam (2) gun iron link and hinge under support (1), therefore test specimen (3) can shake around the hinge point of support (1)
Dynamic, the size of exciting force is changed to realize by the rotating speed of motor (9).
By puller system (7) hinge on support bar (10), support bar (10) can rotate puller system around coercive mechanism
(7) pulling force that can freely control is provided, and the power is passed into steel wire rope (5), has buffer (6) in the middle part of steel wire rope (5),
Can effectively eliminate support bar (10) around coercive mechanism rotate when influence of the displacement to centrifugal force size, the size of centrifugal force passes through drawing
Power apparatus (7) is realized.
Claims (2)
- A kind of 1. loading device of helicopter simulating blade stress, it is characterised in that：Including support (1) technique for fixing beam (2) one End, technique beam (2) another end are connected with testpieces (3), and test specimen (3) is connected with joint (4), and steel wire rope (5) connects joint (4) Connect, have buffer (6) among steel wire rope (5), steel wire rope (5) is connected with puller system (7), steel wire rope (5) and puller system (7) Hinge is on support bar (10)；Exciting device (8) is connected with motor (9), and exciting device (8) couples with joint (4) rigidity.
- A kind of 2. loading device of helicopter simulating blade stress according to claim 1, it is characterised in that：Support (1) Lower end is fixed, upper end hinge technique beam (2), and when test specimen (3) vibrates, technique beam (2) can rotate around hinge.Joint (4) with Test specimen (3), exciting device (8) and steel wire rope (5) are linked to be an entirety, steel wire rope (5) pulling force is provided test specimen (3) simulate from Mental and physical efforts, the size of centrifugal force are realized by puller system (7)；Exciting device (8) test specimen (3) is provided exciting force waving and It is shimmy, wave and shimmy difference can be adjusted by the angle of joint (4), the size of exciting force is turned by motor (9) Speed changes to realize.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710941329.1A CN107860565A (en) | 2017-10-11 | 2017-10-11 | A kind of loading device of helicopter simulating blade stress |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710941329.1A CN107860565A (en) | 2017-10-11 | 2017-10-11 | A kind of loading device of helicopter simulating blade stress |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107860565A true CN107860565A (en) | 2018-03-30 |
Family
ID=61698424
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710941329.1A Pending CN107860565A (en) | 2017-10-11 | 2017-10-11 | A kind of loading device of helicopter simulating blade stress |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107860565A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110901949A (en) * | 2019-10-15 | 2020-03-24 | 中国直升机设计研究所 | Helicopter blade strength test method |
| CN114414250A (en) * | 2021-12-14 | 2022-04-29 | 北京动力机械研究所 | Acceleration test simulation method of lifting lug type mounting structure |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998019909A1 (en) * | 1996-11-07 | 1998-05-14 | Zf Luftfahrttechnik Gmbh | Device and method for measuring and calibrating the control angles and control forces of a rotor blade |
| KR20020054160A (en) * | 2000-12-27 | 2002-07-06 | 장근호 | Bench for Fatigue Tests of Helicopter's Rotor Component |
| DE102011017564A1 (en) * | 2011-04-26 | 2012-10-31 | Aerospy Sense & Avoid Technology Gmbh | Method and system for inspecting a surface for material defects |
| CN104019967A (en) * | 2014-05-20 | 2014-09-03 | 北京航空航天大学 | Testing system for testing fatigue performance of helicopter main-rotor crossbeam |
| CN104062104A (en) * | 2013-03-19 | 2014-09-24 | 徐可君 | Cyclic test device for fatigue of aeroengine compressor blade |
| CN104697766A (en) * | 2014-08-26 | 2015-06-10 | 中国直升机设计研究所 | Bidirectional hinge support device |
| CN104697754A (en) * | 2013-12-04 | 2015-06-10 | 中国直升机设计研究所 | Blade root section fatigue test device |
| CN105716839A (en) * | 2014-12-03 | 2016-06-29 | 中国直升机设计研究所 | Anti-twist device for rotor hub attachment fatigue test |
| CN106018064A (en) * | 2016-05-06 | 2016-10-12 | 江西昌河航空工业有限公司 | Force application device for centrifugal force supplementation |
| CN106768920A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of fatigue experimental device |
| CN106802234A (en) * | 2015-11-26 | 2017-06-06 | 中国直升机设计研究所 | A kind of main oar center piece three-dimensional loading device of bearingless rotor |
| CN110641735A (en) * | 2019-09-29 | 2020-01-03 | 中国直升机设计研究所 | Fatigue test loading device for tail rotor hub journal shaft sleeve assembly |
-
2017
- 2017-10-11 CN CN201710941329.1A patent/CN107860565A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998019909A1 (en) * | 1996-11-07 | 1998-05-14 | Zf Luftfahrttechnik Gmbh | Device and method for measuring and calibrating the control angles and control forces of a rotor blade |
| KR20020054160A (en) * | 2000-12-27 | 2002-07-06 | 장근호 | Bench for Fatigue Tests of Helicopter's Rotor Component |
| DE102011017564A1 (en) * | 2011-04-26 | 2012-10-31 | Aerospy Sense & Avoid Technology Gmbh | Method and system for inspecting a surface for material defects |
| CN104062104A (en) * | 2013-03-19 | 2014-09-24 | 徐可君 | Cyclic test device for fatigue of aeroengine compressor blade |
| CN104697754A (en) * | 2013-12-04 | 2015-06-10 | 中国直升机设计研究所 | Blade root section fatigue test device |
| CN104019967A (en) * | 2014-05-20 | 2014-09-03 | 北京航空航天大学 | Testing system for testing fatigue performance of helicopter main-rotor crossbeam |
| CN104697766A (en) * | 2014-08-26 | 2015-06-10 | 中国直升机设计研究所 | Bidirectional hinge support device |
| CN105716839A (en) * | 2014-12-03 | 2016-06-29 | 中国直升机设计研究所 | Anti-twist device for rotor hub attachment fatigue test |
| CN106802234A (en) * | 2015-11-26 | 2017-06-06 | 中国直升机设计研究所 | A kind of main oar center piece three-dimensional loading device of bearingless rotor |
| CN106018064A (en) * | 2016-05-06 | 2016-10-12 | 江西昌河航空工业有限公司 | Force application device for centrifugal force supplementation |
| CN106768920A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of fatigue experimental device |
| CN110641735A (en) * | 2019-09-29 | 2020-01-03 | 中国直升机设计研究所 | Fatigue test loading device for tail rotor hub journal shaft sleeve assembly |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110901949A (en) * | 2019-10-15 | 2020-03-24 | 中国直升机设计研究所 | Helicopter blade strength test method |
| CN114414250A (en) * | 2021-12-14 | 2022-04-29 | 北京动力机械研究所 | Acceleration test simulation method of lifting lug type mounting structure |
| CN114414250B (en) * | 2021-12-14 | 2024-04-09 | 北京动力机械研究所 | Acceleration test simulation method for lifting lug type mounting structure |
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Application publication date: 20180330 |