CN106441841A - Helicopter tail decelerator case fatigue test device - Google Patents
Helicopter tail decelerator case fatigue test device Download PDFInfo
- Publication number
- CN106441841A CN106441841A CN201610819303.5A CN201610819303A CN106441841A CN 106441841 A CN106441841 A CN 106441841A CN 201610819303 A CN201610819303 A CN 201610819303A CN 106441841 A CN106441841 A CN 106441841A
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- Prior art keywords
- casing
- tail
- helicopter
- fatigue test
- joint
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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
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- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention provides a helicopter tail decelerator case fatigue test device, and aims at solving the problem of the research gap. The helicopter tail decelerator case fatigue test device comprises a fatigue test stand and a multi-point coordinated loading system. The multi-point coordinated loading system connects and controls the fatigue test stand through an electric signal wire. The fatigue test stand comprises a rack, a simulation load driving device, a driving and fixing member, a case fixing device and a helicopter tail decelerator case is provided with a tail rotor shaft and a booster shaft. A first connector is fixed on the tail rotor shaft. A second connector is fixedly connected on the booster shaft. The simulation load driving device is fixed on the rack through the driving and fixing member. The simulation load driving device is connected with the helicopter tail decelerator case through the first connector and the second connector. All the load force commands can be accurately issued by the device so that the process can be monitored and all the information can be accurately recorded and the case fatigue test can be greatly performed.
Description
Technical field
The present invention relates to Helicopter Technology field, particularly relates to a kind of tail reducer of helicopter casing fatigue experimental device.
Background technology
Tail reducer of helicopter is located in the duct of tail end, its major function be using tail transmission shaft pass over dynamic
Power, is driven tail-rotor after deceleration by the spiral bevel gear that a pair of crossed axis angle is 90 degree, and is adjusted by control lever shaft and stick
Tail-rotor pitch, balances the moment of torsion of main rotor, to ensure the normal flight of helicopter.In duct, the rear end of tail reducer leads to
Cross two fixing ears that tail subtracts on casing to be fixed on tail boom, front end is fixed on by being fixed on tail and subtracting the connecting bushing on casing
On aircraft.It is primarily subjected to the effect of tail hub load and tail booster axial force, and failure mode mostly is fatigue rupture.For preventing
There is fatigue failure destruction in tail reducer casing, reduce casing failure probability, should carry out the casing fatigue longevity in the development and design stage
Life assessment, most efficient method is exactly to be carried out by fatigue test.At present, both at home and abroad with regard to helicopter reducer casing fatigue
The report of test is little.
Content of the invention
In order to solve problem above, the present invention proposes a kind of tail reducer of helicopter casing fatigue experimental device.
The technical scheme is that and be achieved in that：A kind of tail reducer of helicopter casing fatigue experimental device, including
Fatigue test board, coordinated multi-point loading system, the coordinated multi-point loading system is connected by electrical signal line and controls described tired
Labor testing stand；
The fatigue test board includes
Frame, is fixed on test indoor；
Simulation load driving means, implement loading force to tail reducer of helicopter casing；
Fixture is driven, is fixed on the end of the simulation load driving means；
Casing fixing device, for fixing tail reducer of helicopter casing, the casing fixing device is fixed on test
On the floor of room；
Tail reducer of helicopter casing is provided with tail-rotor axle, booster axle, is fixed with the first joint, institute on the tail-rotor axle
State and on booster axle, be fixedly connected with the second joint；
The simulation load driving means are fixed in the frame by the driving fixture,
The simulation load driving means are by first joint, the second joint and tail reducer of helicopter casing even
Connect.
Preferably, the simulation load driving means by simulate tail-rotor load force mechanisms, simulation booster axial force machine
Structure is constituted；
Simulation tail-rotor load force mechanisms are comprising eight hydraulic jacks for being located at top, the head of eight hydraulic jacks
It is connected with tail reducer of helicopter casing by first joint；
Simulation booster axial force mechanism includes a lower hydraulic jack for being located at bottom, a lower hydraulic jack
Head is connected with tail reducer of helicopter casing by second joint, implements downward loading force to casing.
Preferably, the hydraulic jack on eight tops be respectively four the first hydraulic jacks, second hydraulic jack,
One the 3rd hydraulic jack, two the 4th hydraulic jacks；
Four first hydraulic jacks are respectively positioned on the top of first joint, implement loading force upwards to casing；
Second hydraulic jack is located at the right side of first joint, implements loading force to the left to casing；
3rd hydraulic jack is located at the rear side of first joint, implements loading force backward to casing；
Two the 4th hydraulic jacks are respectively positioned on the left side of first joint, implement loading force to the left to casing.
Preferably, coordinated multi-point loading system includes industrial computer, control card, driving card, data collecting card, printer；
Industrial computer connects the control card, driving card, data collecting card respectively by isa bus；
Industrial computer connects the printer by USB；
Industrial computer also includes display, mass storage.
Preferably, the working procedure of the coordinated multi-point loading system is：
Step 1：The fatigue test spectrum of industrial computer input tail reducer of helicopter casing；
Step 2：Fatigue test spectral factorization is control command to simulation load driving means by control card by industrial computer；
Step 3：Control card is by driving card control simulation load driving means；
Step 4：Simulation load drives the tail reducer of helicopter casing imposed load to testing；
Step 5：Simulation load is driven by real load feedback of status to data collecting card；
Step 6：Data collecting card sampling real load state, obtains status data, and status data is issued industrial computer；
Step 7：Industrial computer shows and recording status data, forms fatigue test report；
Step 8：Industrial computer prints fatigue test report by printer.
Preferably, fatigue test spectrum is according to helicopter practical flight task and the in-flight stress shape of reduction case
State is worked out,
The fatigue test spectrum includes loading force size, cycle, persistent period.
The present invention is primarily subjected to tail hub load and tail booster axial force according to the stress of tail reducer of helicopter casing
Effect, each loading force is simulated using the electro-hydraulic servo oil cylinder of nine passages, and can be preferable using coordinated multi-point loading system
Nine passage of control electro-hydraulic servo oil cylinder, accurately assign each loading force order, monitoring process, accurately record each letter
Breath, the fatigue test of casing preferably can be carried out, and fill up the problem of this research blank.
Description of the drawings
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
Accompanying drawing to be used needed for technology description is had to be briefly described, it should be apparent that, drawings in the following description are only this
Some embodiments of invention, for those of ordinary skill in the art, without having to pay creative labor, may be used also
To obtain other accompanying drawings according to these accompanying drawings.
Fig. 1 is coordinate system of the present invention and load diagram；
Fig. 2 is the structural representation of the present invention；
Fig. 3 is fatigue test loading scheme schematic diagram of the present invention.
In figure：1- tail reducer casing；2- drives fixture；3- casing fixing device；The first hydraulic jack of 401-；402-
Second hydraulic jack；The 3rd hydraulic jack of 403-；The 4th hydraulic jack of 404-；Hydraulic jack under 405-；The first joint of 5-；6-
Two joints.
Specific embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation is described, it is clear that described embodiment is only a part of embodiment of the present invention, rather than whole embodiments.It is based on
Embodiment in the present invention, it is every other that those of ordinary skill in the art are obtained under the premise of creative work is not made
Embodiment, belongs to the scope of protection of the invention.
As shown in figure 1, tail reducer casing is primarily subjected to 6 power of tail-rotor load element and tail booster responsive to axial force.?
Tail-rotor load Fx on tail-rotor axle is rearward-directed force, and it is axial force that Fy is vertical force, Fz, and Mx, My, Mz are corresponding torque, Fq
For booster to casing and the axial force of control lever shaft.In addition with gear mesh force Fn inside decelerator and Ft etc., belong to
Inertial forces in decelerator (all load all show direction as just with Fig. 1).The tail-rotor load of oar central point is acted on,
Casing and driving gear pair are passed to by tail-rotor axle and its support, the gear mesh force for being formed wherein in gear pair is again by tooth
The support of wheel shaft passes to casing.And axial force one end of booster directly passes to tail reducer casing by booster housing
1, the other end then passes to tail reducer casing 1 by operating linear system, tail-rotor leaf, tail-rotor, tail-rotor axle.
As shown in Figure 2 and Figure 3, a kind of tail reducer of helicopter casing fatigue experimental device, including fatigue test board, multiple spot
Coordinated Loading System, coordinated multi-point loading system is connected by electrical signal line and controls fatigue test board；
Fatigue test board includes
Frame, is fixed on test indoor；
Simulation load driving means, implement loading force to tail reducer of helicopter casing 1；
Fixture 2 is driven, is fixed on the end of simulation load driving means；
Casing fixing device 3, for fixing tail reducer of helicopter casing 1, casing fixing device 3 is fixed on test chamber
On floor；
Tail reducer of helicopter casing 1 is provided with tail-rotor axle, booster axle, is fixed with the first joint 5, power-assisted on tail-rotor axle
The second joint 6 is fixedly connected with device axle；
Simulation load driving means are fixed in frame by driving fixture 2,
Simulation load driving means are connected with tail reducer of helicopter casing 1 by first joint 5, the second joint 6.
Simulation load driving means are constituted by tail-rotor load force mechanisms, simulation booster axial force mechanism are simulated；
Simulation tail-rotor load force mechanisms pass through comprising eight hydraulic jacks for being located at top, the head of eight hydraulic jacks
First joint 5 is connected with tail reducer of helicopter casing 1；
Simulation booster axial force mechanism is comprising a lower hydraulic jack 405 for being located at bottom, a lower hydraulic jack 405
Head be connected with tail reducer of helicopter casing 1 by the second joint 6, downward loading force is implemented to casing.
The hydraulic jack on eight tops is the second hydraulic jack 402, of four the first hydraulic jacks 401, respectively
3rd the 4th hydraulic jack 404 of hydraulic jack 403, two；
Four the first hydraulic jacks 401 are respectively positioned on the top of the first joint 5, implement loading force upwards to casing；
Second hydraulic jack 402 is located at the right side of the first joint 5, implements loading force to the left to casing；
3rd hydraulic jack 403 is located at the rear side of the first joint 5, implements loading force backward to casing；
Two the 4th hydraulic jacks 404 are respectively positioned on the left side of the first joint 5, implement loading force to the left to casing.
Coordinated multi-point loading system includes industrial computer, control card, driving card, data collecting card, printer；
Industrial computer connects the control card, driving card, data collecting card respectively by isa bus；
Industrial computer connects the printer by USB；
Industrial computer also includes display, mass storage.
The working procedure of coordinated multi-point loading system is：
Step 1：The fatigue test spectrum of industrial computer input tail reducer of helicopter casing 1；
Step 2：Fatigue test spectral factorization is control command to simulation load driving means by control card by industrial computer；
Step 3：Control card is by driving card control simulation load driving means；
Step 4：Simulation load drives 1 imposed load of tail reducer of helicopter casing to testing；
Step 5：Simulation load is driven by real load feedback of status to data collecting card；
Step 6：Data collecting card sampling real load state, obtains status data, and status data is issued industrial computer；
Step 7：Industrial computer shows and recording status data, forms fatigue test report；
Step 8：Industrial computer prints fatigue test report by printer.
Fatigue test spectrum is worked out according to helicopter practical flight task and the in-flight stress of reduction case,
Fatigue test spectrum includes loading force size, cycle, persistent period.
Presently preferred embodiments of the present invention is the foregoing is only, not in order to limit the present invention, all essences in the present invention
Within god and principle, any modification, equivalent substitution and improvement that is made etc., should be included within the scope of the present invention.
Claims (6)
1. a kind of tail reducer of helicopter casing fatigue experimental device, it is characterised in that
Including fatigue test board, coordinated multi-point loading system, coordinated multi-point loading system is connected by electrical signal line and controls tired
Labor testing stand；
The fatigue test board includes
Frame, is fixed on test indoor；
Simulation load driving means, implement loading force to tail reducer of helicopter casing；
Fixture is driven, is fixed on the end of the simulation load driving means；
Casing fixing device, for fixing tail reducer of helicopter casing, the casing fixing device is fixed on test chamber ground
On plate；
Tail reducer of helicopter casing is provided with tail-rotor axle, booster axle, is fixed with the first joint on the tail-rotor axle, described helps
The second joint is fixedly connected with power device axle；
The simulation load driving means are fixed in the frame by the driving fixture,
The simulation load driving means are connected with tail reducer of helicopter casing by first joint, the second joint.
2. a kind of tail reducer of helicopter casing fatigue experimental device as claimed in claim 1, it is characterised in that：
The simulation load driving means are constituted by tail-rotor load force mechanisms, simulation booster axial force mechanism are simulated；
Simulation tail-rotor load force mechanisms pass through comprising eight hydraulic jacks for being located at top, the head of eight hydraulic jacks
First joint is connected with tail reducer of helicopter casing；
Simulation booster axial force mechanism is comprising a lower hydraulic jack for being located at bottom, the head of a lower hydraulic jack
It is connected with tail reducer of helicopter casing by second joint, downward loading force is implemented to casing.
3. a kind of tail reducer of helicopter casing fatigue experimental device as claimed in claim 2, it is characterised in that：
The hydraulic jack on eight tops is four the first hydraulic jacks, the second hydraulic jack, the 3rd liquid respectively
Compressing cylinder, two the 4th hydraulic jacks；
Four first hydraulic jacks are respectively positioned on the top of first joint, implement loading force upwards to casing；
Second hydraulic jack is located at the right side of first joint, implements loading force to the left to casing；
3rd hydraulic jack is located at the rear side of first joint, implements loading force backward to casing；
Two the 4th hydraulic jacks are respectively positioned on the left side of first joint, implement loading force to the left to casing.
4. a kind of tail reducer of helicopter casing fatigue experimental device as described in claim 1 or 3, it is characterised in that
Coordinated multi-point loading system includes industrial computer, control card, driving card, data collecting card, printer；
Industrial computer connects the control card, driving card, data collecting card respectively by isa bus；
Industrial computer connects the printer by USB；
Industrial computer also includes display, mass storage.
5. a kind of tail reducer of helicopter casing fatigue experimental device as claimed in claim 4, it is characterised in that the multiple spot
The working procedure of Coordinated Loading System is：
Step 1：The fatigue test spectrum of industrial computer input tail reducer of helicopter casing；
Step 2：Fatigue test spectral factorization is control command to simulation load driving means by control card by industrial computer；
Step 3：Control card is by driving card control simulation load driving means；
Step 4：Simulation load drives the tail reducer of helicopter casing imposed load to testing；
Step 5：Simulation load is driven by real load feedback of status to data collecting card；
Step 6：Data collecting card sampling real load state, obtains status data, and status data is issued industrial computer；
Step 7：Industrial computer shows and recording status data, forms fatigue test report；
Step 8：Industrial computer prints fatigue test report by printer.
6. a kind of tail reducer of helicopter casing fatigue experimental device as claimed in claim 5, it is characterised in that：
The fatigue test spectrum is worked out according to helicopter practical flight task and the in-flight stress of reduction case,
The fatigue test spectrum includes loading force size, cycle, persistent period.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610819303.5A CN106441841A (en) | 2016-09-12 | 2016-09-12 | Helicopter tail decelerator case fatigue test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610819303.5A CN106441841A (en) | 2016-09-12 | 2016-09-12 | Helicopter tail decelerator case fatigue test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106441841A true CN106441841A (en) | 2017-02-22 |
Family
ID=58169333
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610819303.5A Pending CN106441841A (en) | 2016-09-12 | 2016-09-12 | Helicopter tail decelerator case fatigue test device |
Country Status (1)
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107345854A (en) * | 2017-06-13 | 2017-11-14 | 中国航发湖南动力机械研究所 | Decelerator full court slow test mounting and positioning device |
| CN107436237A (en) * | 2017-06-05 | 2017-12-05 | 上海交通大学 | A kind of helicopter hub center non-torque loading simulator |
| CN107764545A (en) * | 2017-09-25 | 2018-03-06 | 上海交通大学 | The Helicopter Main Reducer multi-function test stand of electric feedback |
| CN108489723A (en) * | 2018-04-23 | 2018-09-04 | 中国航发哈尔滨东安发动机有限公司 | Master subtracts casing component booster bearing fatigue experimental device |
| CN108762066A (en) * | 2018-04-24 | 2018-11-06 | 合肥工业大学 | A kind of control method of the electronic tail gearbox system of helicopter |
| CN109229366A (en) * | 2018-08-02 | 2019-01-18 | 哈尔滨飞机工业集团有限责任公司 | A kind of ducted tail rotor helicopter digital tail reducer radome fairing |
| CN110704951A (en) * | 2019-09-29 | 2020-01-17 | 中国直升机设计研究所 | Helicopter tail section fatigue test load spectrum compilation method |
| CN111537209A (en) * | 2020-04-30 | 2020-08-14 | 中国航发哈尔滨东安发动机有限公司 | Bearing seat assembly for tail reduction casing fatigue test and mounting method |
| CN111610022A (en) * | 2020-06-24 | 2020-09-01 | 中国航发中传机械有限公司 | Helicopter tail reducer control shaft and guide cylinder wear resistance test system and application method thereof |
| CN111879511A (en) * | 2020-08-14 | 2020-11-03 | 湘潭科达电工专用成套设备有限责任公司 | Helicopter middle and tail speed reducer comprehensive test bed |
| CN112630055A (en) * | 2021-03-09 | 2021-04-09 | 天津航天瑞莱科技有限公司 | Aeroengine case thermal-static coupling test system |
| CN112798437A (en) * | 2020-12-28 | 2021-05-14 | 中国航发沈阳发动机研究所 | Intermediate casing test load loading device |
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Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107436237A (en) * | 2017-06-05 | 2017-12-05 | 上海交通大学 | A kind of helicopter hub center non-torque loading simulator |
| CN107345854B (en) * | 2017-06-13 | 2019-10-25 | 中国航发湖南动力机械研究所 | Retarder full court slow test mounting and positioning device |
| CN107345854A (en) * | 2017-06-13 | 2017-11-14 | 中国航发湖南动力机械研究所 | Decelerator full court slow test mounting and positioning device |
| CN107764545A (en) * | 2017-09-25 | 2018-03-06 | 上海交通大学 | The Helicopter Main Reducer multi-function test stand of electric feedback |
| CN108489723A (en) * | 2018-04-23 | 2018-09-04 | 中国航发哈尔滨东安发动机有限公司 | Master subtracts casing component booster bearing fatigue experimental device |
| CN108762066B (en) * | 2018-04-24 | 2021-03-12 | 合肥工业大学 | Control method of helicopter electric tail reducer system |
| CN108762066A (en) * | 2018-04-24 | 2018-11-06 | 合肥工业大学 | A kind of control method of the electronic tail gearbox system of helicopter |
| CN109229366A (en) * | 2018-08-02 | 2019-01-18 | 哈尔滨飞机工业集团有限责任公司 | A kind of ducted tail rotor helicopter digital tail reducer radome fairing |
| CN109229366B (en) * | 2018-08-02 | 2021-07-16 | 哈尔滨飞机工业集团有限责任公司 | Digitized tail speed reducer fairing of ducted tail rotor helicopter |
| CN110704951A (en) * | 2019-09-29 | 2020-01-17 | 中国直升机设计研究所 | Helicopter tail section fatigue test load spectrum compilation method |
| CN110704951B (en) * | 2019-09-29 | 2021-10-15 | 中国直升机设计研究所 | Helicopter tail section fatigue test load spectrum compilation method |
| CN111537209A (en) * | 2020-04-30 | 2020-08-14 | 中国航发哈尔滨东安发动机有限公司 | Bearing seat assembly for tail reduction casing fatigue test and mounting method |
| CN111537209B (en) * | 2020-04-30 | 2022-04-01 | 中国航发哈尔滨东安发动机有限公司 | Bearing seat assembly for tail reduction casing fatigue test and mounting method |
| CN111610022A (en) * | 2020-06-24 | 2020-09-01 | 中国航发中传机械有限公司 | Helicopter tail reducer control shaft and guide cylinder wear resistance test system and application method thereof |
| CN111879511A (en) * | 2020-08-14 | 2020-11-03 | 湘潭科达电工专用成套设备有限责任公司 | Helicopter middle and tail speed reducer comprehensive test bed |
| CN111879511B (en) * | 2020-08-14 | 2024-05-28 | 湘潭科达电工专用成套设备有限责任公司 | Comprehensive test bed for tail speed reducer in helicopter |
| CN112798437A (en) * | 2020-12-28 | 2021-05-14 | 中国航发沈阳发动机研究所 | Intermediate casing test load loading device |
| CN112798437B (en) * | 2020-12-28 | 2024-01-02 | 中国航发沈阳发动机研究所 | Intermediate case test load loading device |
| CN112630055A (en) * | 2021-03-09 | 2021-04-09 | 天津航天瑞莱科技有限公司 | Aeroengine case thermal-static coupling test system |
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