CN103900811A - Rotation load applying device for tail rotor shaft fatigue test - Google Patents
Rotation load applying device for tail rotor shaft fatigue test Download PDFInfo
- Publication number
- CN103900811A CN103900811A CN201210571482.7A CN201210571482A CN103900811A CN 103900811 A CN103900811 A CN 103900811A CN 201210571482 A CN201210571482 A CN 201210571482A CN 103900811 A CN103900811 A CN 103900811A
- Authority
- CN
- China
- Prior art keywords
- hydraulic actuator
- tail rotor
- rotor shaft
- tail
- loading disc
- 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.)
- Pending
Links
Images
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention provides a rotation load applying device for a tail rotor shaft fatigue test so as to determine fatigue performance and weak parts of a tail rotor shaft and provide a basis for determining service life of the tail rotor shaft. The technical scheme of the invention is as follows: first, second, third and fourth hydraulic actuators are connected with a loading disc through rotation moment loading joints and are perpendicular to the disc surface of the loading disc; the first, second, third and fourth hydraulic actuators are symmetrically arranged around a tail rotor shaft test member with the same arm of force; a fifth hydraulic actuator and a sixth hydraulic actuator are connected through two support arms of a rotation shear loading joint and the loading disc which are 90 degrees from each other, and are parallel to the disc surface of the loading disc; the tail rotor shaft test member is secured to a test bed through an upper support bearing fake piece and a lower support bearing fake piece; the upper part of the tail rotor shaft test member is connected with the lower part of a tail decelerated output flange plate; and the upper part of the tail decelerated output plate is connected with the loading disc.
Description
Technical field
The invention belongs to helicopter tail rotor axle torture test technology, relate to a kind of tail rotor axle torture test rotation load applying device.
Background technology
Single rotor band tail-rotor formula is the form that helicopter the most extensively adopts in the world at present, the reactive torque of balance main rotor and the directional control of helicopter is rotarily driven to tail-rotor rotation realization by tail rotor axle.Tail rotor axle is the typical complex dynamic component in Helicopter Tail Drive System system, bear the compound action of the multiple load such as rotation moment of flexure, moment of torsion, tail-rotor thrust awing, its stressing conditions complexity, fatigure failure is main failure mode, and its functional reliability directly affects the flight safety of helicopter.For ensureing performance that it is good and the reliability of use, should simulate its load and design feature and carry out torture test examination, provide foundation its serviceable life for determining.In the time of definite tail rotor axle fatigue properties and Calculation of Fatigue Life, rotation moment of flexure is the sign load with the meaning of representing adopting, and truly reflects that its load is connected feature with border particularly important in torture test process.
Existing like product test unit adopts single armed to load separately, can not simulate the load that the rotary part cycle changes.
Summary of the invention
The technical problem to be solved in the present invention: a kind of tail rotor axle torture test rotation load applying device is provided, to determine fatigue behaviour and the weak part of tail rotor axle, provides foundation its serviceable life for determining.
Technical scheme of the present invention: a kind of tail rotor axle torture test rotation load applying device, the first hydraulic actuator, the second hydraulic actuator, the 3rd hydraulic actuator, the 4th hydraulic actuator loads joint by rotation moment of flexure and is connected with loading disc, and perpendicular to the card of loading disc, the first hydraulic actuator, the second hydraulic actuator, the 3rd hydraulic actuator, the 4th hydraulic actuator is symmetrical in tail rotor shaft experiment part with the identical arm of force and arranges, the 5th hydraulic actuator, the 6th hydraulic actuator loads two support arms that differ 90 ° of joint and loading disc by rotary shear and is connected, and be parallel to the card of loading disc, tail rotor shaft experiment part is by upper spring bearing bogusware, and lower supporting bearing bogusware and test-bed are fixed, and tail rotor shaft experiment part top and tail subtract output flange bottom and be linked and packed, and tail subtracts output flange top and is connected with loading disc, the first hydraulic actuator, the second hydraulic actuator, the 3rd hydraulic actuator, the 4th hydraulic actuator bottom are fixed with test-bed.
Beneficial effect of the present invention: the present invention has realized the examination of helicopter tail rotor axle torture test rotation load applying, design a set of complete test unit, ensure carrying out smoothly of test, for determining that tail rotor axle fatigue lifetime, product design loss of weight, architecture advances provide test basis.By the evidence of many covers: use the load that this test unit can real simulation testpieces to the examination of helicopter tail rotor axle torture test, test findings true and accurate.This load applying device also can be promoted the checking for other like product fatigue behaviour simultaneously, is with a wide range of applications.
Brief description of the drawings
Fig. 1 is structural representation of the present invention.
Fig. 2 is section plan of the present invention.
Embodiment
Below the present invention is described in further details.
As shown in Figure 1, 2, the present invention is specially: the first hydraulic actuator 1, the second hydraulic actuator 2, the 3rd hydraulic actuator 3, the 4th hydraulic actuator 4 load joint 8 by rotation moment of flexure and be connected with loading disc 9, and perpendicular to the card of loading disc 9, the first hydraulic actuator 1, the second hydraulic actuator 2, the 3rd hydraulic actuator 3, the 4th hydraulic actuator 4 are symmetrical in tail rotor shaft experiment part 11 with the identical arm of force and arrange.The 5th hydraulic actuator 5, the 6th hydraulic actuator 6 load 9 two support arms that differ 90 ° of joint 7 and loading disc by rotary shear and are connected, and are parallel to the card of loading disc 9.Tail rotor shaft experiment part 11 is by upper spring bearing bogusware 12, lower supporting bearing bogusware 13 is fixed with test-bed, simulation tail subtracts casing to two of tail rotor axle bearings conditions, tail rotor shaft experiment part 11 tops subtract output flange 10 bottoms by installation requirement and tail and are linked and packed, and tail subtracts output flange 10 tops and is connected with loading disc 9 bottoms.All actuator two ends adopt oscillating bearing design, motor coordination when warranty test loads, and the first hydraulic actuator 1, the second hydraulic actuator 2, the 3rd hydraulic actuator 3, the 4th hydraulic actuator 4 bottoms and test-bed are fixed.
When test, 4 actuator the first hydraulic actuators 1, the second hydraulic actuator 2, the 3rd hydraulic actuator 3, the 4th hydraulic actuator 4 phase coordinations in 90 ° load and produce around tail rotor axle axis rotation moment of flexure.Other 2 actuator the 5th hydraulic actuator 5, the 6th hydraulic actuator 6 phase coordination in 90 ° load and produce around tail rotor axle axis rotary shear.Realize in the situation that tail rotor axle is fixing, moment of flexure (MY) and shearing (FX) are around the axis rotation of tail rotor axle, the transmission of real simulation load and distribution.
The load that the one or four hydraulic actuator applies:
i=1 ~ 4
F1, F2, F3, F4 are respectively the load that the first hydraulic actuator 1, the second hydraulic actuator 2, the 3rd hydraulic actuator 3, the 4th hydraulic actuator 4 apply, and L is for loading the arm of force.
Synthetic effect: moment of flexure size is M
y, direction is around tail rotor axle axis rotation moment of flexure.
The load that the 5th hydraulic actuator applies: F
5=F
x× sin (ω t+90 °)
The load that the 6th hydraulic actuator applies: F
6=F
x× sin (ω t+180 °)
Synthetic effect: shearing size is F
x, direction is around tail rotor axle axis rotary shear.
Claims (1)
1. a tail rotor axle torture test rotation load applying device, is characterized in that,
The first hydraulic actuator, the second hydraulic actuator, the 3rd hydraulic actuator, the 4th hydraulic actuator load joint by rotation moment of flexure and are connected with loading disc, and perpendicular to the card of loading disc, the first hydraulic actuator, the second hydraulic actuator, the 3rd hydraulic actuator, the 4th hydraulic actuator are symmetrical in tail rotor shaft experiment part with the identical arm of force and arrange, the 5th hydraulic actuator, the 6th hydraulic actuator load two support arms that differ 90 ° of joint and loading disc by rotary shear and are connected, and are parallel to the card of loading disc; Tail rotor shaft experiment part is by upper spring bearing bogusware, and lower supporting bearing bogusware and test-bed are fixed, and tail rotor shaft experiment part top and tail subtract output flange bottom and be linked and packed, and tail subtracts output flange top and is connected with loading disc; The first hydraulic actuator, the second hydraulic actuator, the 3rd hydraulic actuator, the 4th hydraulic actuator bottom are fixed with test-bed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210571482.7A CN103900811A (en) | 2012-12-25 | 2012-12-25 | Rotation load applying device for tail rotor shaft fatigue test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210571482.7A CN103900811A (en) | 2012-12-25 | 2012-12-25 | Rotation load applying device for tail rotor shaft fatigue test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103900811A true CN103900811A (en) | 2014-07-02 |
Family
ID=50992275
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210571482.7A Pending CN103900811A (en) | 2012-12-25 | 2012-12-25 | Rotation load applying device for tail rotor shaft fatigue test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103900811A (en) |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104280241A (en) * | 2014-10-14 | 2015-01-14 | 合肥工业大学 | Helicopter rotor system elastic bearing load measuring device |
| CN104457449A (en) * | 2014-12-12 | 2015-03-25 | 晋西工业集团有限责任公司 | Rotational flexibility detector for rotatable stabilizer |
| CN104502093A (en) * | 2014-12-19 | 2015-04-08 | 湖南科技大学 | Fault simulation experiment device for helicopter tail transmission system |
| CN104833493A (en) * | 2015-04-07 | 2015-08-12 | 中国直升机设计研究所 | Fatigue test loading device for tail rotor hub central component |
| CN105067263A (en) * | 2015-08-18 | 2015-11-18 | 鹰领航空高端装备技术秦皇岛有限公司 | Endurance tester for combined joint bearing matching with tail rotor of tail rotor type helicopter |
| CN105136459A (en) * | 2015-08-18 | 2015-12-09 | 燕山大学 | Testing machine for joint bearings combined and matched with swing cylinder type helicopter tail rotor system |
| CN105352732A (en) * | 2015-12-08 | 2016-02-24 | 中国飞机强度研究所 | Aeroengine fan shaft composite static force and fatigue tester |
| CN105445023A (en) * | 2015-11-23 | 2016-03-30 | 西安交通大学 | Static index testing platform and method for industrial robot joint decelerator |
| CN105738086A (en) * | 2014-12-10 | 2016-07-06 | 中国飞机强度研究所 | Aero-engine fan shaft rotation bending moment loading method |
| CN104280241B (en) * | 2014-10-14 | 2017-01-04 | 合肥工业大学 | A kind of helicopter rotor system resilient bearing loads measurement equipment |
| CN106767651A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of measuring method of helicopter blade established angle |
| CN107436237A (en) * | 2017-06-05 | 2017-12-05 | 上海交通大学 | A kind of helicopter hub center non-torque loading simulator |
| CN107727375A (en) * | 2017-08-30 | 2018-02-23 | 江西昌河航空工业有限公司 | Motion loading device and method is used in a kind of propeller hub detection |
| 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 |
| CN110426211A (en) * | 2019-07-24 | 2019-11-08 | 中国电力科学研究院有限公司 | A kind of Wind turbines loading device |
| CN110589025A (en) * | 2019-09-29 | 2019-12-20 | 中国直升机设计研究所 | Rotor transition shaft fixing device |
| CN110712763A (en) * | 2019-10-12 | 2020-01-21 | 哈尔滨飞机工业集团有限责任公司 | Single-spar crack propagation test device and test method |
| CN111079329A (en) * | 2019-12-04 | 2020-04-28 | 中国直升机设计研究所 | Fatigue life assessment method based on similar structure test |
| CN112880993A (en) * | 2021-01-18 | 2021-06-01 | 中国航发沈阳发动机研究所 | Loading device and method for static force and fatigue test load of main shaft of aircraft engine |
| CN113533085A (en) * | 2021-07-01 | 2021-10-22 | 中国航发湖南动力机械研究所 | Helicopter main reducer rotor shaft load loading simulation device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4089211A (en) * | 1976-11-01 | 1978-05-16 | United Technologies Corporation | Elastomeric bearing test machine |
| RU2065145C1 (en) * | 1993-11-11 | 1996-08-10 | Московский вертолетный завод им.М.Л.Миля | Method of detection of structural damages in multistream toothed driving mechanisms |
| EP0729883A1 (en) * | 1995-02-28 | 1996-09-04 | Advanced Technology Institute of Commuter-Helicopter, Ltd. | Higher harmonic control apparatus for a helicopter |
| CN101788392A (en) * | 2010-03-11 | 2010-07-28 | 齐齐哈尔轨道交通装备有限责任公司 | Fatigue and vibration experiment table and system |
| CN202153183U (en) * | 2011-06-15 | 2012-02-29 | 中国航空动力机械研究所 | Load applying and torque balance device |
| CN102401764A (en) * | 2011-11-17 | 2012-04-04 | 中国航空动力机械研究所 | Model loading device |
-
2012
- 2012-12-25 CN CN201210571482.7A patent/CN103900811A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4089211A (en) * | 1976-11-01 | 1978-05-16 | United Technologies Corporation | Elastomeric bearing test machine |
| RU2065145C1 (en) * | 1993-11-11 | 1996-08-10 | Московский вертолетный завод им.М.Л.Миля | Method of detection of structural damages in multistream toothed driving mechanisms |
| EP0729883A1 (en) * | 1995-02-28 | 1996-09-04 | Advanced Technology Institute of Commuter-Helicopter, Ltd. | Higher harmonic control apparatus for a helicopter |
| CN101788392A (en) * | 2010-03-11 | 2010-07-28 | 齐齐哈尔轨道交通装备有限责任公司 | Fatigue and vibration experiment table and system |
| CN202153183U (en) * | 2011-06-15 | 2012-02-29 | 中国航空动力机械研究所 | Load applying and torque balance device |
| CN102401764A (en) * | 2011-11-17 | 2012-04-04 | 中国航空动力机械研究所 | Model loading device |
Non-Patent Citations (1)
| Title |
|---|
| 李清蓉 等: "《直升机尾桨轴疲劳试验技术研究》", 《直升机技术》, no. 3, 15 September 2009 (2009-09-15) * |
Cited By (29)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104280241A (en) * | 2014-10-14 | 2015-01-14 | 合肥工业大学 | Helicopter rotor system elastic bearing load measuring device |
| CN104280241B (en) * | 2014-10-14 | 2017-01-04 | 合肥工业大学 | A kind of helicopter rotor system resilient bearing loads measurement equipment |
| CN105738086A (en) * | 2014-12-10 | 2016-07-06 | 中国飞机强度研究所 | Aero-engine fan shaft rotation bending moment loading method |
| CN104457449A (en) * | 2014-12-12 | 2015-03-25 | 晋西工业集团有限责任公司 | Rotational flexibility detector for rotatable stabilizer |
| CN104457449B (en) * | 2014-12-12 | 2017-03-08 | 晋西工业集团有限责任公司 | A kind of rotatable stabilising arrangement rotates device for detecting flexibility |
| CN104502093A (en) * | 2014-12-19 | 2015-04-08 | 湖南科技大学 | Fault simulation experiment device for helicopter tail transmission system |
| CN104833493A (en) * | 2015-04-07 | 2015-08-12 | 中国直升机设计研究所 | Fatigue test loading device for tail rotor hub central component |
| CN104833493B (en) * | 2015-04-07 | 2017-07-07 | 中国直升机设计研究所 | A kind of tail-rotor hub center piece fatigue test loading device |
| CN105067263A (en) * | 2015-08-18 | 2015-11-18 | 鹰领航空高端装备技术秦皇岛有限公司 | Endurance tester for combined joint bearing matching with tail rotor of tail rotor type helicopter |
| CN105067263B (en) * | 2015-08-18 | 2017-06-30 | 鹰领航空高端装备技术秦皇岛有限公司 | Tail-rotor formula helicopter tail rotor forms a complete set of joint bearing life testing machine |
| CN105136459A (en) * | 2015-08-18 | 2015-12-09 | 燕山大学 | Testing machine for joint bearings combined and matched with swing cylinder type helicopter tail rotor system |
| CN105136459B (en) * | 2015-08-18 | 2017-12-08 | 燕山大学 | Joint bearing testing machine is combined in the system support of oscillating oil cylinder formula helicopter tail rotor |
| CN105445023A (en) * | 2015-11-23 | 2016-03-30 | 西安交通大学 | Static index testing platform and method for industrial robot joint decelerator |
| CN105445023B (en) * | 2015-11-23 | 2017-12-15 | 西安交通大学 | A kind of industrial robot joint decelerator Static State Index test platform and method of testing |
| CN105352732A (en) * | 2015-12-08 | 2016-02-24 | 中国飞机强度研究所 | Aeroengine fan shaft composite static force and fatigue tester |
| CN105352732B (en) * | 2015-12-08 | 2018-11-13 | 中国飞机强度研究所 | A kind of compound static(al) and fatigue tester of aerial engine fan axis |
| CN106767651A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of measuring method of helicopter blade established angle |
| CN106767651B (en) * | 2016-11-29 | 2019-05-31 | 中国直升机设计研究所 | A kind of measurement method of helicopter blade established angle |
| CN107436237A (en) * | 2017-06-05 | 2017-12-05 | 上海交通大学 | A kind of helicopter hub center non-torque loading simulator |
| CN107727375A (en) * | 2017-08-30 | 2018-02-23 | 江西昌河航空工业有限公司 | Motion loading device and method is used in a kind of propeller hub detection |
| 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 |
| CN110426211A (en) * | 2019-07-24 | 2019-11-08 | 中国电力科学研究院有限公司 | A kind of Wind turbines loading device |
| CN110589025A (en) * | 2019-09-29 | 2019-12-20 | 中国直升机设计研究所 | Rotor transition shaft fixing device |
| CN110712763A (en) * | 2019-10-12 | 2020-01-21 | 哈尔滨飞机工业集团有限责任公司 | Single-spar crack propagation test device and test method |
| CN111079329A (en) * | 2019-12-04 | 2020-04-28 | 中国直升机设计研究所 | Fatigue life assessment method based on similar structure test |
| CN111079329B (en) * | 2019-12-04 | 2022-10-18 | 中国直升机设计研究所 | Fatigue life assessment method based on similar structure test |
| CN112880993A (en) * | 2021-01-18 | 2021-06-01 | 中国航发沈阳发动机研究所 | Loading device and method for static force and fatigue test load of main shaft of aircraft engine |
| CN113533085A (en) * | 2021-07-01 | 2021-10-22 | 中国航发湖南动力机械研究所 | Helicopter main reducer rotor shaft load loading simulation device |
| CN113533085B (en) * | 2021-07-01 | 2023-03-28 | 中国航发湖南动力机械研究所 | Helicopter main reducer rotor shaft load loading simulation device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103900811A (en) | Rotation load applying device for tail rotor shaft fatigue test | |
| CN100449196C (en) | Master-slave dual-parallel twelve-degree-of-freedom generalized force-compliant loading mechanism | |
| CN102156047B (en) | Loading simulation device for test bed of wind turbine | |
| CN101368874B (en) | Testing device for implementing main torque and vibrating torque to high speed rotary main shaft | |
| CN101830272B (en) | Spatial redundant drive swinging experiment table with two degrees of freedom | |
| CN201876368U (en) | Comprehensive test system for airplane cargo hold power drive unit (PDU) and rotating actuator cylinder | |
| CN102175441A (en) | Load simulator based on series-parallel mechanism | |
| CN106844838B (en) | A method for evaluating the performance of an aircraft air rudder | |
| CN105352732A (en) | Aeroengine fan shaft composite static force and fatigue tester | |
| CN102819972B (en) | Three-degree-of-freedom static load balance parallel motion simulation platform | |
| WO2011091081A1 (en) | Systems and methods for performing structural tests on wind turbine blades | |
| CN102539264A (en) | Assessing test machine for tribological properties of high polymer compound material | |
| CN101922995A (en) | Three-shaft six-motion freedom vibration test device of electric hammer type | |
| CN103353398B (en) | High-speed overload railway bearing testing table radial loaded mechanism | |
| CN104048826A (en) | Simulation testing device and method for multidirectional alternating load of wind power transmission system | |
| CN202083551U (en) | A simulation loading device for a test bench of a wind power generating set | |
| CN210555640U (en) | High-dynamic centrifugal overload simulation test device | |
| CN105045134A (en) | Double-friction-disk loading mechanism and bidirectional friction loading-type no-additional-torque electro-hydraulic load simulator employing same | |
| CN103884505B (en) | Ball socket bearing multidimensional coordination loading condition simulation experiment system | |
| CN203965149U (en) | A kind of multidirectional alternate load simulation test device of wind-powered electricity generation kinematic train | |
| CN203975239U (en) | A kind of low-gravity environment analog machine | |
| CN105987815B (en) | Universal clutch of motorcycle table apparatus | |
| CN103134682B (en) | Experiment table of wind generating set | |
| CN104729851B (en) | A kind of simulation of wind energy conversion system planetary gear complex working condition and test device | |
| San Andrés et al. | Experiments with a rotor-hybrid gas bearing system undergoing maneuver loads from its base support |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20140702 |
|
| RJ01 | Rejection of invention patent application after publication |