CN103439096B - A kind of helicopter tail rotor booster fatigue test system - Google Patents
A kind of helicopter tail rotor booster fatigue test system Download PDFInfo
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- CN103439096B CN103439096B CN201310360457.9A CN201310360457A CN103439096B CN 103439096 B CN103439096 B CN 103439096B CN 201310360457 A CN201310360457 A CN 201310360457A CN 103439096 B CN103439096 B CN 103439096B
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- tail rotor
- helicopter tail
- rotor booster
- booster
- direct drive
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Abstract
A kind of helicopter tail rotor booster fatigue test system, it is made up of fatigue tester, Hydraulic Station, rotation direct drive valve, actuator exerciser, digital storage oscilloscope, X-over, upper and lower fixture and helicopter tail rotor booster; Upper and lower fixture is arranged on fatigue tester, helicopter tail rotor booster two ends are arranged on upper and lower fixture, Hydraulic Station is connected with rotation direct drive valve by oil pipe, rotate direct drive valve to be connected with helicopter tail rotor booster again, actuator exerciser is connected with rotation direct drive valve by circuit, and digital storage oscilloscope is connected with actuator exerciser the relevant information showing helicopter tail rotor booster.The present invention can not only simulate external air loads effect, can also simulate the effect of actuator hydraulic pressure, and experimental test result determine the longevity for helicopter tail rotor booster fatigue and is had important engineer applied value.
Description
Technical field
The present invention relates to a kind of helicopter tail rotor booster fatigue test system, belong to experimental test technical field.
Background technology
Helicopter tail rotor booster in the course of the work, constantly bears alternate load, must examine its fatigue lifetime when design and devdlop.Helicopter tail rotor booster works under hydraulic-driven usually used as a subsystem of helicopter, not only bear the hydraulic pressure of self actuator, but also bear aerodynamic loading effect, conventional fatigue tester only can simulate external air loads effect, and the effect of actuator hydraulic pressure can not be simulated, at present, the effectively test macro of the helicopter tail rotor booster fatigue of practicality is still lacked.For this reason, plain fatigue testing machine, Hydraulic Station, rotation direct drive valve, actuator exerciser, digital storage oscilloscope, X-over, fixture and helicopter tail rotor booster are integrated into helicopter tail rotor booster fatigue test system by the present invention, external air loads effect can not only be simulated, can also simulate the effect of actuator hydraulic pressure, experimental test result determine the longevity for helicopter tail rotor booster fatigue and is had important engineer applied value.
Summary of the invention
1, object: the object of the invention is to provide a kind of helicopter tail rotor booster fatigue test system, it can the effect of Reality simulation duty load, and have simple, practical, feature efficiently, system operation cost is also lower.
2, technical scheme: a kind of helicopter tail rotor booster fatigue test system of the present invention, is made up of fatigue tester, Hydraulic Station, rotation direct drive valve, actuator exerciser, digital storage oscilloscope, X-over, upper and lower fixture and helicopter tail rotor booster.Position annexation between them is as follows: upper and lower fixture is arranged on fatigue tester, helicopter tail rotor booster two ends are arranged on upper and lower fixture, Hydraulic Station is connected with rotation direct drive valve by oil pipe, rotate direct drive valve to be connected with helicopter tail rotor booster again, actuator exerciser is connected with rotation direct drive valve by circuit, and digital storage oscilloscope is connected with actuator exerciser the relevant information showing helicopter tail rotor booster.Wherein, the order of connection of fatigue tester, upper and lower fixture and helicopter tail rotor booster is from top to bottom:
Fatigue tester → upper fixture → helicopter tail rotor booster → lower clamp → fatigue tester
Described fatigue tester is conventional low-frequency fatigue test machine, and in order to apply fatigue load to helicopter tail rotor booster piston, the load range of testing machine need be greater than the test load of helicopter tail rotor booster.
Described Hydraulic Station is conventional hydraulic station, oil transportation mouth and oil return opening need be had, oil transportation mouth is used for rotation direct drive valve conveying liquid force feed, and oil return opening is used for hydraulic oil to pass back into Hydraulic Station, and the oil pressure that Hydraulic Station can provide need be greater than the test oil pressure of helicopter tail rotor booster and can keep stable.
Described X-over is multiple stage rank axial workpieces, is two of the Hydraulic Station joint between hydraulic fluid port and oil pipe, in order to two hydraulic fluid ports of connected pipes and Hydraulic Station.
Described rotation direct drive valve is the accessory be connected with helicopter tail rotor booster, and its inside has the aperture of motor control valve.Rotate direct drive valve and hydraulic oil is sent to helicopter tail rotor booster, driven plunger moves axially, the motor of the aperture of its operation valve drives by actuator exerciser, to change piston movement direction and speed, form closed-loop control, piston in helicopter tail rotor booster can be maintained equilibrium position effectively.
Described actuator exerciser is drive the electronic installation rotating direct drive valve motor, exports control signal, and receive the piston position signal of helicopter tail rotor booster feedback to the motor rotating direct drive valve.
Described digital storage oscilloscope is conventional oscillograph, in order to observe control and the feedback signal of helicopter tail rotor booster.
Described helicopter tail rotor booster is a kind of hydraulic servo driving of two-chamber single-piston rod, and it is made up of piston rod assembly, front end cylindrical shell, rear end cylindrical shell, ring flange and coupling bolt, and whole system is connected by coupling bolt and fixes.Under the control of actuator exerciser, tail-rotor booster provides the servo-actuated equilibrant of tail-rotor leaf aerodynamic force, and lower maintenance balances and stablize in working order to make tail-rotor, and its working hydraulic pressure pressure is 6MPa, and the maximum working load of piston rod is 8kN.
Described upper fixture is the part that Step Shaft and hexahedron are combined into, and its two ends are connected with fatigue tester and helicopter tail rotor booster respectively.
Described lower clamp is heart portion hexahedron part with holes, and its two ends are connected with fatigue tester and helicopter tail rotor booster respectively.
3, advantage and effect: the invention has the beneficial effects as follows and can carry out torture test test to helicopter tail rotor booster separately, can be the design of helicopter tail rotor booster, exploitation and checking and provide effect technique support, in addition, the present invention has simply, the advantage of practical, efficient, low cost, effectively can complete helicopter tail rotor booster fatigue test.
Accompanying drawing explanation
Below in conjunction with drawings and Examples, the present invention is further described.
Fig. 1 is X-over schematic diagram.
Fig. 2 is upper fixture schematic diagram.
Fig. 3 is connecting link schematic diagram.
Fig. 4 is lower clamp schematic diagram.
Fig. 5 is tail-rotor rotor booster fatigue test system structural drawing.
In Fig. 5: 1. fatigue tester, 2. go up fixture, 3. helicopter tail rotor booster, 4. rotate direct drive valve, 5. X-over, 6. Hydraulic Station, 7. digital storage oscilloscope, 8. actuator exerciser, 9. lower clamp.
Embodiment
Below in conjunction with drawings and Examples, the present invention is further described.
Embodiment one: composition graphs 1 to Fig. 5 illustrates the specific embodiment of the present invention.
In Figure 5, a kind of helicopter tail rotor booster fatigue test system of the present invention, is made up of fatigue tester 1, Hydraulic Station 6, rotation direct drive valve 4, actuator exerciser 8, digital storage oscilloscope 7, X-over 5, upper and lower fixture 2,9 and helicopter tail rotor booster 3.Position annexation between them is as follows: upper and lower fixture 2,9 is arranged on fatigue tester 1, helicopter tail rotor booster 3 two ends are arranged on upper and lower fixture 2,9, Hydraulic Station 6 is connected with rotation direct drive valve 4 by oil pipe, rotate direct drive valve 4 to be connected with helicopter tail rotor booster 3 again, actuator exerciser 8 is connected with rotation direct drive valve 4 by circuit, and digital storage oscilloscope 7 is connected with actuator exerciser 8 relevant information showing helicopter tail rotor booster 3.Fatigue tester 1 selection MTS in this embodiment, fatigue load is applied to the piston of helicopter tail rotor booster 3, the hydraulic oil of set pressure is sent to and rotates direct drive valve 4 by Hydraulic Station 6, rotate direct drive valve 4 and again hydraulic oil is sent to helicopter tail rotor booster 3, driven plunger moves axially; The piston position signal of helicopter tail rotor booster 3 feeds back to the actuator exerciser 8 be connected with digital storage oscilloscope 7, actuator exerciser 8 drives the motor rotating direct drive valve 4, change the direction of hydraulic oil and the aperture of valve in valve, to change piston movement direction and speed, form closed-loop control, piston in helicopter tail rotor booster 3 can be maintained equilibrium position effectively.Because actuator exerciser 8 does not have screen, therefore, it is connected to digital storage oscilloscope 7, the current signal of actuator exerciser 8 and valve break-make H passage provide signal to 1 passage of digital storage oscilloscope 7, to show the aperture and running of hydraulic power oil direction signal that rotate direct drive valve 4, the demodulation of actuator exerciser 8 and Open-closed-loop H passage provide signal to 2 passages of digital storage oscilloscope 7, to show the piston displacement of helicopter tail rotor booster 3, like this, by digital storage oscilloscope 7 can observe rotate direct drive valve 4 aperture and hydraulic oil flows to and the piston displacement of helicopter tail rotor booster 3.Digital storage oscilloscope 7 can also calculate and show 1 passage peak-to-peak value and 2 passage peak-to-peak values, and the signal of yellow high frequency is 1 channel signal, and the signal of green low frequency is 2 channel signals, and 1 passage peak-to-peak value is shown in the oscillograph screen lower left corner.Actuator exerciser 8 gathers piston displacement signal from helicopter tail rotor booster 3, by calculating, send instructions to the motor rotating direct drive valve 4, and digital storage oscilloscope 7 is responsible for display.The electric wire one of being drawn by actuator exerciser 8 is divided into 2, and a road connects helicopter tail rotor booster 3, tunnel and connects rotation direct drive valve 4.
Helicopter tail rotor booster 3 cylinder body there are 4 Ф 6.4 hard-covers for the connection of M6 × 40 bolt join through hole, but the joint that MTS fatigue tester 1 provides is threaded connector (M27 × 2), both do not mate, in addition, the piston of helicopter tail rotor booster 3 is hollow, not joint, for this reason, design and machined fixture (as shown in Figures 2 to 4), by upper and lower fixture (2 and 9), helicopter tail rotor booster 3 being connected on MTS fatigue tester 1.Helicopter tail rotor booster 3 hydraulic pipeline joint is the female joint of M12 × 1, and Hydraulic Station 6 is the threaded hole of M14 × 1.5 × 12, for this reason, designs and machined the adapter coupling 5 (as shown in Figure 1) between 1 pair of fluid pressure line and Hydraulic Station 6.
Like this, this cover system by designing above just can complete helicopter tail rotor booster fatigue test.
Embodiment two: the difference of present embodiment and embodiment one is the selection of fatigue tester 1, can be fatigue tester or the self-control fatigue testers such as conventional MTS, INSTRON, other design philosophy of helicopter tail rotor booster fatigue test system be identical with embodiment one with connected mode.
Claims (1)
1. a helicopter tail rotor booster fatigue test system, is characterized in that: it is made up of fatigue tester, Hydraulic Station, rotation direct drive valve, actuator exerciser, digital storage oscilloscope, X-over, upper and lower fixture and helicopter tail rotor booster; Upper and lower fixture is arranged on fatigue tester, helicopter tail rotor booster two ends are arranged on upper and lower fixture, Hydraulic Station is connected with rotation direct drive valve by oil pipe, rotate direct drive valve to be connected with helicopter tail rotor booster again, actuator exerciser is connected with rotation direct drive valve by circuit, and digital storage oscilloscope is connected with actuator exerciser the relevant information showing helicopter tail rotor booster; Wherein, the order of connection of fatigue tester, upper and lower fixture and helicopter tail rotor booster is from top to bottom:
Fatigue tester → upper fixture → helicopter tail rotor booster → lower clamp → fatigue tester
Described fatigue tester is conventional low-frequency fatigue test machine, and in order to apply fatigue load to helicopter tail rotor booster piston, the load range of testing machine need be greater than the test load of helicopter tail rotor booster;
Described Hydraulic Station is conventional hydraulic station, oil transportation mouth and oil return opening need be had, oil transportation mouth is used for rotation direct drive valve conveying liquid force feed, and oil return opening is used for hydraulic oil to pass back into Hydraulic Station, and the oil pressure that Hydraulic Station can provide need be greater than the test oil pressure of helicopter tail rotor booster and can keep stable;
Described X-over is multiple stage rank axial workpieces, is two of the Hydraulic Station joint between hydraulic fluid port and oil pipe, in order to two hydraulic fluid ports of connected pipes and Hydraulic Station;
Described rotation direct drive valve is the accessory be connected with helicopter tail rotor booster, its inside has the aperture of motor control valve, rotate direct drive valve and hydraulic oil is sent to helicopter tail rotor booster, driven plunger moves axially, the motor of the aperture of its operation valve drives by actuator exerciser, to change piston movement direction and speed, form closed-loop control, piston in helicopter tail rotor booster is maintained equilibrium position effectively;
Described actuator exerciser is drive the electronic installation rotating direct drive valve motor, exports control signal, and receive the piston position signal of helicopter tail rotor booster feedback to the motor rotating direct drive valve;
Described digital storage oscilloscope is conventional oscillograph, in order to observe control and the feedback signal of helicopter tail rotor booster;
Described helicopter tail rotor booster is a kind of hydraulic servo driving of two-chamber single-piston rod, and it is made up of piston rod assembly, front end cylindrical shell, rear end cylindrical shell, ring flange and coupling bolt, and whole system is connected by coupling bolt and fixes; Under the control of actuator exerciser, tail-rotor booster provides the servo-actuated equilibrant of tail-rotor leaf aerodynamic force, and lower maintenance balances and stablize in working order to make tail-rotor, and its working hydraulic pressure pressure is 6MPa, and the maximum working load of piston rod is 8kN;
Described upper fixture is the part that Step Shaft and hexahedron are combined into, and its two ends are connected with fatigue tester and helicopter tail rotor booster respectively;
Described lower clamp is heart portion hexahedron part with holes, and its two ends are connected with fatigue tester and helicopter tail rotor booster respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310360457.9A CN103439096B (en) | 2013-08-19 | 2013-08-19 | A kind of helicopter tail rotor booster fatigue test system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310360457.9A CN103439096B (en) | 2013-08-19 | 2013-08-19 | A kind of helicopter tail rotor booster fatigue test system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103439096A CN103439096A (en) | 2013-12-11 |
| CN103439096B true CN103439096B (en) | 2015-10-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310360457.9A Expired - Fee Related CN103439096B (en) | 2013-08-19 | 2013-08-19 | A kind of helicopter tail rotor booster fatigue test system |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104155087A (en) * | 2014-05-20 | 2014-11-19 | 北京航空航天大学 | Fixed-wing aircraft rudder fatigue test system |
| CN104048819B (en) * | 2014-05-20 | 2016-08-24 | 北京航空航天大学 | A kind of fixed wing machine ground spoiler fatigue checking pilot system |
| CN104019969A (en) * | 2014-05-20 | 2014-09-03 | 北京航空航天大学 | Fatigue verification test system for fixed-wing aircraft's multifunctional spoiler |
| CN104215442B (en) * | 2014-08-26 | 2017-07-07 | 中国直升机设计研究所 | A kind of tail-rotor leaf oversleeve is centrifuged force loading device |
| CN108910080B (en) * | 2018-06-26 | 2021-11-02 | 中国直升机设计研究所 | Helicopter tail rotor pneumatic load environment simulation test device |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2737181B1 (en) * | 1995-07-27 | 1997-09-19 | Eurocopter France | METHOD AND DEVICE FOR REDUCING VIBRATIONS GENERATED ON THE STRUCTURE OF A HELICOPTER |
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- 2013-08-19 CN CN201310360457.9A patent/CN103439096B/en not_active Expired - Fee Related
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Granted publication date: 20151021 Termination date: 20200819 |