CN100447550C - Externally swing joint-bearing fatigue experimental apparatus of automatic rotor oblique device for helicopter - Google Patents
Externally swing joint-bearing fatigue experimental apparatus of automatic rotor oblique device for helicopter Download PDFInfo
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- CN100447550C CN100447550C CNB2006100124423A CN200610012442A CN100447550C CN 100447550 C CN100447550 C CN 100447550C CN B2006100124423 A CNB2006100124423 A CN B2006100124423A CN 200610012442 A CN200610012442 A CN 200610012442A CN 100447550 C CN100447550 C CN 100447550C
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Abstract
The present invention discloses an external-swing type fatigue tester for oscillating bearings of automatic tilters of rotary wings of a helicopter, which is characterized in that the present invention is provided with a sleeve barrel (8) fixed with a machine frame (3), and an inner ring (9) of an oscillating bearing of an automatic tilter is fixedly connected with the sleeve barrel; an annular frame (11) is fixedly connected with an outer ring (10) of the oscillating bearing of the automatic tilter, and is connected with piston rods of four loading hydraulic cylinders (1, 2, 16, 17) by four ball hinges; cylinder blocks of the loading hydraulic cylinders (1, 2, 16, 17) are respectively connected with the machine frame (3) by four ball hinges; the annular frame (11) is connected with three connecting rods (4, 15, 18) by three ball hinges; the three connecting rods (4, 15, 18) are respectively connected with three slide blocks (5, 14, 19) with three ball nuts by three ball hinges; the three slide blocks (5, 14, 19) with three ball nuts are engaged with three ballscrews (6, 13, 20) connected with three servo motors (7, 12, 21) fixed on the machine frame (3). The present invention not only can simulate the real stressed and motion conditions of the oscillating bearing of the automatic tilter in the process of flight and replace a rotary wing of a helicopter in a fatigue test, but also can reduce the cost of the fatigue test for oscillating bearings of automatic tilters of rotary wings of a helicopter greatly.
Description
Technical field
The present invention relates to a kind of apparatus of automatic rotor oblique device for helicopter externally swing joint-bearing fatigue experimental.
Background technology
Helicopter is a kind of of rotor craft, is with the vertical take off and landing aircraft of rotor as its main lift source.Rotation produces the required power of helicopter flight by rotor, and rotor shaft approaches vertical, produces pulling force upwards to overcome helicopter weight; Simultaneously, rotor can be handled by catanator again, produce forward, backward, left, horizontal component to the right, therefore, go straight up to function vertical take off and landing, hovering, left and right sides all directions flight forwards, backwards.
Apparatus of automatic rotor oblique device for helicopter is the critical piece of helicopter control system, just by the skyborne attitude adjustment of apparatus of automatic rotor oblique device realize lifting airscrew forward, backward, left, be tilted to the right, and produce forward, backward, left, horizontal component to the right, thereby make helicopter left and right sides all directions flight forwards, backwards.The quality of apparatus of automatic rotor oblique device performance all has decisive influence to flight safety, maneuverability, reliability, dirigibility and the length of military service phase of helicopter.And the oscillating bearing of auto-bank unit is one of topmost support accessory in the auto-bank unit system.So the science of auto-bank unit oscillating bearing fatigue lifetime is estimated accurately helicopter design, use, maintenance etc. are all had material impact, desire to the fatigue lifetime of auto-bank unit oscillating bearing the science of carrying out just estimate accurately and must carry out a large amount of torture tests.
Past is paid attention to not enough to the apparatus of automatic rotor oblique device oscillating bearing fatigue lifetime, its fatigue experiment is mostly done by Bearing Factory, and Bearing Factory adopts the fatigue test method of plain bearing to do the torture test of apparatus of automatic rotor oblique device, data reliability fatigue lifetime that provides is on the low side, the data that have are too conservative, cause a lot of apparatus of automatic rotor oblique device oscillating bearings when arriving the rated life time, its quality is still fine, still can continue to use, but because the rated life time arrives, have to change, and cause very big waste.
Along with the expansion in helicopter range of application, field and the increase of helicopter military service quantity, it is a reality and urgent task that development can be simulated apparatus of automatic rotor oblique device for helicopter oscillating bearing real stressed special-purpose fatigue experiment platform with motion in flight course.
Summary of the invention
For to the fatigue lifetime of apparatus of automatic rotor oblique device for helicopter oscillating bearing the science of carrying out estimate accurately, the invention provides a kind of apparatus of automatic rotor oblique device for helicopter externally swing joint-bearing fatigue experimental, this testing machine can not only be simulated auto-bank unit oscillating bearing real stressed and moving situation in flight course, replace the lifting airscrew in the torture test, and can reduce the cost of apparatus of automatic rotor oblique device for helicopter oscillating bearing torture test widely.
The technical solution adopted for the present invention to solve the technical problems is: it has a sleeve that is fixed together with frame, connecting firmly the inner ring of auto-bank unit oscillating bearing on it, the outer ring of annular frame and auto-bank unit oscillating bearing connects firmly, annular frame links to each other with the piston rod of four loading hydraulic cylinders by four ball pivots, the cylinder body of loading hydraulic cylinder links to each other with frame by four ball pivots respectively, four loading hydraulic cylinders are in the even branch of being arranged as of space, be that four ball pivots that loading hydraulic cylinder is connected with annular frame are positioned on the same circumference of annular frame upper surface, and apart from one another by 90 °.Connecting three connecting rods by three ball pivots on annular frame, these three connecting rods link to each other with three slide blocks that have ball nut by three ball pivots respectively.Three ball pivots that annular frame is connected with connecting rod are installed on the same circumference of annular frame lower surface, and 120 ° of spaces, and three systems that three connecting rods and slide block, ball-screw and servomotor are formed also are 120 ° of distributions in the space.
Description of drawings
Fig. 1 is a helicopter auto-bank unit externally swing joint-bearing fatigue experimental structural representation;
Fig. 2 is the A-A cut-open view of helicopter auto-bank unit externally swing joint-bearing fatigue experimental.
In Fig. 1, Fig. 2,1. first loading hydraulic cylinder, 2. second loading hydraulic cylinder, 3. frame, 4. first connecting rod, 5. first slide block, 6. first ball-screw, 7. first servomotor, 8. sleeve, 9. inner ring, 10. outer ring, 11. annular frames, 12. second servomotor, 13. second ball-screws, 14. second slide blocks, 15. second connecting rods, 16. the 3rd loading hydraulic cylinder, 17. the 4th loading hydraulic cylinders, 18. third connecting rods, 19. the 3rd slide block, 20. the 3rd ball-screws, 21. the 3rd servomotors.
Embodiment
Fig. 1 is an embodiment disclosed by the invention, is connecting firmly the inner ring 9 of auto-bank unit oscillating bearing on the sleeve 8 that is fixed together with frame 3, and annular frame 11 connects firmly with the outer ring 10 of auto-bank unit oscillating bearing.Annular frame 11 links to each other with the piston rod of first loading hydraulic cylinder 1, second loading hydraulic cylinder 2, the 3rd loading hydraulic cylinder 16, the 4th loading hydraulic cylinder 17 by four ball pivots, and the cylinder body of first loading hydraulic cylinder 1, second loading hydraulic cylinder 2, the 3rd loading hydraulic cylinder 16, the 4th loading hydraulic cylinder 17 links to each other with frame 3 by four ball pivots respectively.First loading hydraulic cylinder 1, second loading hydraulic cylinder 2, the 3rd loading hydraulic cylinder 16, the 4th loading hydraulic cylinder 17 are in the even branch of being arranged as of space, promptly four ball pivots being connected with annular frame 11 of first loading hydraulic cylinder 1, second loading hydraulic cylinder 2, the 3rd loading hydraulic cylinder 16, the 4th loading hydraulic cylinder 17 are positioned on the same circumference of annular frame 11 upper surfaces, and apart from one another by 90 °.On annular frame 11, connecting first connecting rod 4, second connecting rod 15, third connecting rod 18 by three ball pivots, first connecting rod 4, second connecting rod 15, third connecting rod 18 link to each other with first slide block 5, second slide block 14, the 3rd slide block 19 that have ball nut by three ball pivots respectively, and first ball-screw 6, second ball-screw 13, the 3rd ball-screw 20 are to connect firmly mutually with the output shaft of first servomotor 7, second servomotor 12, the 3rd servomotor 21 respectively.Three ball pivots that annular frame 11 is connected with first connecting rod 4, second connecting rod 15, third connecting rod 18 are installed on the same circumference of annular frame 11 lower surfaces, and 120 ° of spaces, the system that first connecting rod 4, first slide block 5, first ball-screw 6, first servomotor 7 are formed, the system that third connecting rod 18, the 3rd slide block 19, the 3rd ball-screw 20, the 3rd servomotor 21 are formed, the system that second connecting rod 15, second slide block 14, second ball-screw 13, second servomotor 12 are formed also is 120 ° of distributions in the space.
Science is estimated the fatigue lifetime of helicopter auto-bank unit oscillating bearing accurately, and the operating mode in the time of must guaranteeing to carry out the torture test of auto-bank unit oscillating bearing, motion, stressed etc. and this bearing truth when work are coincide.In the helicopter flight process, the variation of its heading is to realize by the attitude that changes auto-bank unit, even the upper surface of annular frame 11 and vertical axis (axis of sleeve 8) constitute different angles in the space, with realize helicopter before fly, after fly, various flight attitudes such as a left side flies, the right side flies.Auto-bank unit must bear the load from four rotors in the attitude adjustment process, when individual rotor was in diverse location and different angles, it was to each rotor.
In the present invention, by to first servomotor 7, second servomotor 12, the rate curve of the 3rd servomotor 21 and the different set of displacement curve, can simulate helicopter in flight course, parameters such as the amplitude that the various attitudes of auto-bank unit are adjusted, frequency, speed, acceleration (comprise forward, backward, left, attitude adjustment to the right).First loading hydraulic cylinder 1, second loading hydraulic cylinder 2, the 3rd loading hydraulic cylinder 16, the 4th loading hydraulic cylinder 17 can be simulated in apparatus of automatic rotor oblique device attitude adjustment process exactly by HYDRAULIC CONTROL SYSTEM, and four rotors impose on the load of auto-bank unit.
Claims (4)
1. apparatus of automatic rotor oblique device for helicopter externally swing joint-bearing fatigue experimental, comprise first loading hydraulic cylinder (1), second loading hydraulic cylinder (2), the 3rd loading hydraulic cylinder (16), the 4th loading hydraulic cylinder (17), first connecting rod (4), second connecting rod (15), third connecting rod (18), first slide block (5), second slide block (14), the 3rd slide block (19), first ball-screw (6), second ball-screw (13), the 3rd ball-screw (20), first servomotor (7), second servomotor (12) and the 3rd servomotor (21), it is characterized in that: it has a sleeve (8) that is fixed together with frame (3), connecting firmly the inner ring (9) of auto-bank unit oscillating bearing on the sleeve (8), annular frame (11) connects firmly with the outer ring (10) of auto-bank unit oscillating bearing, annular frame (11) is by four ball pivots and first loading hydraulic cylinder (1), second loading hydraulic cylinder (2), the 3rd loading hydraulic cylinder (16), the piston rod of the 4th loading hydraulic cylinder (17) links to each other, first loading hydraulic cylinder (1), second loading hydraulic cylinder (2), the 3rd loading hydraulic cylinder (16), the cylinder body of the 4th loading hydraulic cylinder (17) links to each other with frame (3) by ball pivot respectively; Annular frame (11) is connecting first connecting rod (4) by three ball pivots, second connecting rod (15), third connecting rod (18), first connecting rod (4), second connecting rod (15), third connecting rod (18) is respectively by ball pivot and first slide block (5) that has ball nut, second slide block (14) links to each other with the 3rd slide block (19), first slide block (5) that has ball nut, the 3rd slide block (19) that has second slide block (14) of ball nut and have a ball nut respectively with first ball-screw (6), second ball-screw (13) and the 3rd ball-screw (20) are meshed, described first ball-screw (6), second ball-screw (13) and the 3rd ball-screw (20) respectively with first servomotor (7) that is fixed on the frame (3), second servomotor (12) is connected with the 3rd servomotor (21).
2. apparatus of automatic rotor oblique device for helicopter externally swing joint-bearing fatigue experimental according to claim 1, it is characterized in that: first loading hydraulic cylinder (1), second loading hydraulic cylinder (2), the 3rd loading hydraulic cylinder (16), the 4th loading hydraulic cylinder (17) are in the even distribution of being arranged as of space, promptly four ball pivots being connected with annular frame (11) of first loading hydraulic cylinder (1), second loading hydraulic cylinder (2), the 3rd loading hydraulic cylinder (16), the 4th loading hydraulic cylinder (17) are positioned on the same circumference of annular frame (11) upper surface, and apart from one another by 90 °.
3. apparatus of automatic rotor oblique device for helicopter externally swing joint-bearing fatigue experimental according to claim 1 and 2, it is characterized in that: annular frame (11) is installed on the same circumference of annular frame (11) lower surface with three ball pivots that first connecting rod (4), second connecting rod (15), third connecting rod (18) are connected, and 120 ° of spaces.
4. apparatus of automatic rotor oblique device for helicopter externally swing joint-bearing fatigue experimental according to claim 3, it is characterized in that: the system that first connecting rod (4), first slide block (5), first ball-screw (6), first servomotor (7) are formed, the system that third connecting rod (18), the 3rd slide block (19), the 3rd ball-screw (20), the 3rd servomotor (21) are formed, they also are to be 120 ° of distributions in the space for the systems that second connecting rod (15), second slide block (14), second ball-screw (13), second servomotor (12) are formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100124423A CN100447550C (en) | 2006-03-17 | 2006-03-17 | Externally swing joint-bearing fatigue experimental apparatus of automatic rotor oblique device for helicopter |
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| Application Number | Priority Date | Filing Date | Title |
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| CNB2006100124423A CN100447550C (en) | 2006-03-17 | 2006-03-17 | Externally swing joint-bearing fatigue experimental apparatus of automatic rotor oblique device for helicopter |
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| CN1818598A CN1818598A (en) | 2006-08-16 |
| CN100447550C true CN100447550C (en) | 2008-12-31 |
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| CN101363770B (en) * | 2008-10-08 | 2010-06-16 | 燕山大学 | Fatigue-tesing machine for ball socket bearing of helicopter main rotor |
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| 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 |
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| CN105710805B (en) * | 2016-03-25 | 2017-07-25 | 哈尔滨飞机工业集团有限责任公司 | A kind of helicopter auto-bank unit stop instrument |
| CN105865780B (en) * | 2016-05-30 | 2018-02-23 | 吉林大学 | Electronic activity of force closed loop monodentate roller box hydraulic exciting tilting low-temperature test platform |
| CN106644458B (en) * | 2016-09-12 | 2019-04-12 | 中国人民解放军海军航空工程学院青岛校区 | A kind of tail reducer of helicopter casing fatigue test method |
| CN106644477B (en) * | 2016-12-19 | 2019-11-05 | 兰州空间技术物理研究所 | A kind of radial direction oscillating bearing running in machine |
| CN106644482B (en) * | 2016-12-30 | 2020-09-08 | 北京金风科创风电设备有限公司 | Load loading device and method |
| CN109707842B (en) * | 2017-03-31 | 2021-11-16 | 法可赛(太仓)汽车配件有限公司 | Gear shifting driver |
| CN108760309B (en) * | 2018-06-29 | 2019-08-02 | 燕山大学 | A kind of Helicopter Main rotor system forms a complete set of bearing tester |
| CN109187019B (en) * | 2018-10-31 | 2019-07-26 | 燕山大学 | Oscillating oil cylinder loaded type main rotor ball socket bearing comprehensive test machine |
| 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 |
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Patent Citations (5)
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| US4089211A (en) * | 1976-11-01 | 1978-05-16 | United Technologies Corporation | Elastomeric bearing test machine |
| US4623300A (en) * | 1985-09-19 | 1986-11-18 | United Technologies Corporation | Helicopter rotor blade securement device |
| US5381692A (en) * | 1992-12-09 | 1995-01-17 | United Technologies Corporation | Bearing assembly monitoring system |
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| CN1818598A (en) | 2006-08-16 |
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