CN2876753Y - Fatique-tester for vertical hinge bearing of rotary swing of helicopter - Google Patents
Fatique-tester for vertical hinge bearing of rotary swing of helicopter Download PDFInfo
- Publication number
- CN2876753Y CN2876753Y CNU2006200238345U CN200620023834U CN2876753Y CN 2876753 Y CN2876753 Y CN 2876753Y CN U2006200238345 U CNU2006200238345 U CN U2006200238345U CN 200620023834 U CN200620023834 U CN 200620023834U CN 2876753 Y CN2876753 Y CN 2876753Y
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- China
- Prior art keywords
- bearing
- vertical hinge
- lifting airscrew
- rotor
- holds
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Abstract
The utility model discloses a fatigue-tester for vertical hinge bearing of rotary swing of helicopter. Its characteristics include: a bearing frame (1) is fixed two bearing supports (16), (17), a shaft (12) is supported by bearing supports (16),(17) via the bearings (5), (6), the ends of the shaft (12) are installed the vertical hinge bearing of rotary swing of helicopter (4),(13); the right end of C-shaped frame (14) is supported on the lifting airscrew vertical socket bearings (4) (13)via two bearing holes connecting with it, the left end is connected with two guide bars (2) (15), which are installed inside two guide holes on the bearing frame (1). The utility model can simulate service load of lifting airscrew vertical socket bearing and true angular velocity and angular acceleration, etc of lifting airscrew through all kinds of loading means in the lifting airscrew vertical socket bearing fatigue test. On the premise of truth and reliability of lifting airscrew vertical socket bearing fatigue test, the utility model can reduce the cost greatly.
Description
Technical field
The utility model relates to the vertical hinge of a kind of lifting airscrew and holds fatigue tester.
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.
As seen rotor system is one of most important parts of helicopter, and the quality of rotor system performance all has decisive influence to flight safety, maneuverability, reliability and the length of military service phase of helicopter.The position of bearing maximum alterante stress on the rotor is the root of rotor, also is that stress is concentrated the most serious position herein.For the stress that reduces rotary-wing root section is concentrated, to improve the fatigue lifetime of rotor, general lifting airscrew root has all designed three hinges: promptly axially hinge, level are cut with scissors, are vertically cut with scissors, these three hinges of most helicopters all adopt rolling bearing, these bearings all bear very big alternate load, and each bearing is not complete cycle rotation, but makes high frequency low-angle reciprocally swinging, and it is stressed, operating mode, condition such as lubricated are very poor.It is one of topmost support accessory in the rotor system that wherein vertical hinge holds.So rotor vertical hinge holds the science of fatigue lifetime and estimates design to lifting airscrew system and whole helicopter, use, maintenance etc. accurately material impact is all arranged, and the basis that the science of the fatigue lifetime that the vertical hinge of rotor holds is accurately estimated is to carry out a large amount of torture tests.
The fatigue experiment that the vertical hinge of past lifting airscrew holds adopts the vertical hinge of rotor held more to be directly installed in the rotor system, and makes rotor system according near real helicopter flight process, does rotatablely moving under various angular velocity, the angular acceleration.In order accurately to estimate the fatigue lifetime that the vertical hinge of rotor holds, it is enough big that the sampling sample of fatigue experiment is wanted, promptly carrying out group number that the vertical hinge of torture test holds must be abundant, carries out the vertical hinge of rotor and holds the long-term work under the effect of alternate load of just having to of rotor that fatigue experiment uses; And the vertical hinge of rotor to hold the rotor that fatigue experiment uses must be the true rotor of helicopter, just can make experiment load that the vertical hinge of rotor holds near the real load in the course of work, and be certain the fatigue lifetime of lifting airscrew, so the phenomenon of the fatigure failure of rotor own often takes place in experimentation, must often change.Because the manufacturing cost of rotor is very high, this just makes and holds torture test by the vertical hinge of rotor to get cost too big.Simultaneously since the diameter dimension of lifting airscrew generally all between 20 meters to 40 meters, so that rotor vertical angle bearing fatigue is tested the required experiment place that takies is very big.Because the moment of inertia of lifting airscrew is very big,, must use the heavy-duty motor driving in addition so make its acceleration and deceleration rotation required starting and braking moment also very big, thus the vertical hinge of rotor to hold the energy consumption of fatigue experiment also very big.
Summary of the invention
The purpose of this utility model is to provide a kind of lifting airscrew special fatigue test machine that vertical hinge holds, this fatigue tester can hold the parameter such as true angular velocity, angular acceleration of the operating load that holds by the vertical hinge of various load mode real simulation rotors in the fatigue experiment and rotor at the vertical hinge of rotor, thereby can replace the lifting airscrew in the torture test, this invention is guaranteeing that the vertical hinge of rotor holds that torture test is true, under the reliable premise, is reducing the vertical hinge of rotor greatly and hold the cost of torture test.
The technical scheme that its technical matters that solves the utility model adopts is: connecting firmly two bearing seats on scaffold, axle is bearing on the bearing seat by bearing, and the two ends up and down of axle are installed the vertical hinge of lifting airscrew and held; The right-hand member of gap frame holds by being bearing in the vertical hinge of lifting airscrew with two dead eyes that it connects firmly, and left end is connecting firmly two guide poles, and guide pole is installed in two pilot holes on the scaffold; Can do between gap frame and the scaffold to move, but can not relatively rotate relative to straight line; The piston rod of load cylinder links to each other with gap frame by a ball pivot, and the cylinder body of load cylinder links to each other with scaffold by a ball pivot; Connecting firmly a rocker shaft in the centre position of axle, rocker shaft links to each other with connecting rod by hinge, and connecting rod links to each other with crank by hinge, and crank is connected on the output shaft of servomotor; The forward and reverse of servomotor rotatablely moves, and drives the vertical hinge of rotor by crank, connecting rod, rocker shaft and axle and makes reciprocal swing in high frequency; Load cylinder imposes on the vertical hinge of rotor by gap frame and holds a load that equals rotor centrifugal force.
Description of drawings
Fig. 1 holds special fatigue test machine structural representation for the vertical hinge of lifting airscrew.
In Fig. 1,1, scaffold, 2, guide pole, 3, load cylinder, 4, vertical hinge holds, 5, bearing, 6, bearing, 7, rocker shaft, 8, hinge, 9, connecting rod, 10, crank, 11, servomotor, 12, axle, 13, vertical hinge holds, 14, gap frame, 15, guide pole, 16, bearing seat, 17, bearing seat.
Embodiment
Fig. 1 is the disclosed embodiment (see figure 1) of the utility model, the vertical hinge of lifting airscrew holds on the scaffold 1 of special fatigue test machine and is connecting firmly two bearing seats 16,17, axle 12 is bearing on the bearing seat 16,17 by bearing 5,6, and the two ends up and down of axle 12 are installed the vertical hinge of lifting airscrew and held 4,13.The right-hand member of gap frame 14 holds on 4,13 by being bearing in the vertical hinge of lifting airscrew with two dead eyes that it connects firmly, and left end is connecting firmly two guide poles 2,15, and guide pole 2,15 is installed in two pilot holes on the scaffold 1.Can do to move between gap frame 14 and the scaffold 1, but can not relatively rotate relative to straight line.Axially the piston rod of load cylinder 3 links to each other with gap frame by a ball pivot, and the cylinder body of load cylinder 3 links to each other with scaffold 1 by a ball pivot.Connecting firmly a rocker shaft 7 in the centre position of axle 12, rocker shaft 7 links to each other with connecting rod 9 by hinge 8, and connecting rod 9 links to each other with crank 10 by hinge, and crank 10 is fixed on the output shaft of servomotor 11.
Science is estimated the fatigue lifetime that the vertical hinge of lifting airscrew holds accurately, must guarantee that at first the operating mode, motion, load when carrying out the vertical hinge of rotor holds torture test, condition such as lubricated and the truth of this bearing in the helicopter flight process match.In the helicopter course of work, to often take off, operation such as raising speed, deceleration, landing, all must follow this mast change in rotational speed in these operating process, simultaneously because rotor is a beam that rigidity is very low, length is very big, add change of wind velocity, rotor dither on (plane vertical with the rotor driving shaft) in the surfaces of revolution must take place.In the helicopter flight process, the vertical hinge of rotor holds also will bear the centrifugal force that the rotor high speed rotating produces.
In the utility model, the forward and reverse of servomotor 11 rotatablely moves, and drives the vertical hinge of rotor by crank 10, connecting rod 9, rocker shaft 7 with axle 12 and makes reciprocal swing in high frequency.Load cylinder 3 imposes on the vertical hinge of rotor by gap frame and holds a load that equals rotor centrifugal force.
Because the speed of servomotor can be set arbitrarily,, make the real motion rule that the vertical hinge of rotor holds in the vertical hinge of rotor holds in the torture test the characteristics of motion and the helicopter flight process consistent so can find the rate curve of a servomotor.The centrifugal force that the control of the axial tension that load cylinder 3 is applied by hydraulic system can the true reappearance rotor be produced under different rotating speeds.
Claims (3)
1. the vertical hinge of lifting airscrew holds fatigue tester, comprise bearing (5,6), vertical hinge holds (4,13), load cylinder (3) and servomotor (11), it is characterized in that: connect firmly two bearing seats (16,17) on the scaffold (1), axle (12) is by bearing (5,6) be bearing on the bearing seat (16,17), the two ends up and down of axle (12) are installed the vertical hinge of lifting airscrew and are held (4), (13); The right-hand member of gap frame (14) holds on (4,13) by being bearing in the vertical hinge of lifting airscrew with two dead eyes that it connects firmly, and left end is connecting firmly two guide poles (2,15), and guide pole (2), (15) are installed in two pilot holes on the scaffold 1.
2. hold fatigue tester according to the vertical hinge of the described lifting airscrew of claim 1, it is characterized in that: the piston rod of load cylinder (3) links to each other with gap frame (14) by a ball pivot, and the cylinder body of load cylinder (3) links to each other with scaffold (1) by a ball pivot.
3. hold fatigue tester according to claim 1 or the vertical hinge of 2 described lifting airscrews, it is characterized in that: connecting firmly a rocker shaft (7) in the centre position of axle (12), rocker shaft (7) links to each other with connecting rod (9) by hinge (8), connecting rod (9) links to each other with crank (10) by hinge, and crank (10) is fixed on the output shaft of servomotor (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2006200238345U CN2876753Y (en) | 2006-03-17 | 2006-03-17 | Fatique-tester for vertical hinge bearing of rotary swing of helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2006200238345U CN2876753Y (en) | 2006-03-17 | 2006-03-17 | Fatique-tester for vertical hinge bearing of rotary swing of helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2876753Y true CN2876753Y (en) | 2007-03-07 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2006200238345U Expired - Fee Related CN2876753Y (en) | 2006-03-17 | 2006-03-17 | Fatique-tester for vertical hinge bearing of rotary swing of helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2876753Y (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104697794A (en) * | 2013-12-04 | 2015-06-10 | 中国直升机设计研究所 | Tungsten carbide bearing performance test device |
| CN108760309A (en) * | 2018-06-29 | 2018-11-06 | 燕山大学 | A kind of Helicopter Main rotor system forms a complete set of bearing tester |
| CN109357871A (en) * | 2018-12-12 | 2019-02-19 | 中国北方发动机研究所(天津) | A kind of connecting rod small end of engine bearing certification test platform and test macro |
| CN109520736A (en) * | 2018-11-12 | 2019-03-26 | 中国直升机设计研究所 | A kind of spring bearing durability test device |
| CN113567121A (en) * | 2021-08-27 | 2021-10-29 | 中浙高铁轴承有限公司 | Helicopter engine input end shafting bearing test loading device |
-
2006
- 2006-03-17 CN CNU2006200238345U patent/CN2876753Y/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104697794A (en) * | 2013-12-04 | 2015-06-10 | 中国直升机设计研究所 | Tungsten carbide bearing performance test device |
| CN104697794B (en) * | 2013-12-04 | 2017-06-23 | 中国直升机设计研究所 | A kind of tungsten carbide bearing performance experimental rig |
| CN108760309A (en) * | 2018-06-29 | 2018-11-06 | 燕山大学 | A kind of Helicopter Main rotor system forms a complete set of bearing tester |
| 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 |
| CN109520736A (en) * | 2018-11-12 | 2019-03-26 | 中国直升机设计研究所 | A kind of spring bearing durability test device |
| CN109357871A (en) * | 2018-12-12 | 2019-02-19 | 中国北方发动机研究所(天津) | A kind of connecting rod small end of engine bearing certification test platform and test macro |
| CN109357871B (en) * | 2018-12-12 | 2020-11-06 | 中国北方发动机研究所(天津) | Engine connecting rod small-end bearing examination test bed and test system |
| CN113567121A (en) * | 2021-08-27 | 2021-10-29 | 中浙高铁轴承有限公司 | Helicopter engine input end shafting bearing test loading device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |