CN104344955A - Static load simulation test method of airplane wheel bearing - Google Patents
Static load simulation test method of airplane wheel bearing Download PDFInfo
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- CN104344955A CN104344955A CN201410593872.3A CN201410593872A CN104344955A CN 104344955 A CN104344955 A CN 104344955A CN 201410593872 A CN201410593872 A CN 201410593872A CN 104344955 A CN104344955 A CN 104344955A
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Abstract
The invention relates to a static load simulation test method of an airplane wheel bearing. A test machine comprises a dragging system and a loading system, wherein a tested bearing is enabled by the dragging system to rotate according to a stipulated rotation speed, the loading system is used for providing a test load to the tested bearing, the tested bearing is enabled to simulate the use working conditions such as the stress working condition and the test condition of the airplane wheel bearing in the flying, high-speed sliding, instantaneous impacting when in landing, laterodeviation landing and stopping processes of an airplane, the working condition of the airplane wheel bearing can be comprehensively reflected, the strength and service life of the airplane wheel bearing can be accurately evaluated, the loading force distribution, which is practically applied by the airplane load, on the airplane wheel bearing and the deviation stress working condition of the airplane wheel bearing when the airplane is stopped in a deviation manner can be simulated, and the fault can be efficiently and reliably stimulated. The credible test evidence can be provided for researching the airplane wheel bearing at a higher rotation speed and a heavier load, and the research period can be shortened.
Description
Technical field
The present invention relates to a kind of airplane wheel bearing load testing machine, specifically a kind of simulated aircraft wheel bearing bears the test method of load condition when aircraft stationary state.
Background technology
Along with the development of aircraft, take off and increase gradually with land hourly velocity and weight, in taking-off and landing process, security issues become increasingly urgent, requires also more and more higher to the performance and reliability of wheel bearing, and the ability on airport is maked a return voyage, continues fight capability and adapted to the safety that it is related to aircraft.
Wheel bearing is not only used for supporting wheel, guides the sense of rotation of wheel, reduces the friction in rotation process, and bears the various load between wheel and wheel shaft.And bearing all has a significant impact the serviceability of aircraft, life-span, each economic target and reliability, also can cause flight safety accident even in some cases.
As the wheel bearing of consumable accessory, because the accident that wheel bearing fails normally to work accounts for certain ratio, therefore security during aircraft landing how is effectively improved, improve aircraft to the adaptive faculty of various load situation, runway condition, weather conditions, become the main goal in research of airplane wheel bearing.
The mode of motion of major part bearing is that outer ring is fixed, inner ring rotates.Airplane wheel bearing has its unique distinction, and being different from the maximum feature of other bearings is the mode of motion that outer ring rotates, inner ring is fixing, and its operating mode in use.
Due to geometrical feature and the design feature of the conical bearing of aircraft employing, it can bear radial and axial combined load.Outer raceway and bearing axis angle larger, the axial thrust that can bear and the ratio of radial thrust larger, the osculatory of roller and raceway is longer, and so the ability of bearing load is stronger.Aircraft is in different duties, and the stressing conditions of bearing is different.
1, aircraft remains static, and bearing mainly bears dead load.The shutdown load p that the gravity of aircraft produces passes to outer raceway by the roller of bearing, i.e. wheel hub.P can be decomposed into axial force N and the power F perpendicular to outer raceway vertically.
2, aircraft is when ground taxi, mainly also bears vertical load.Definitely not smooth due to ground, the amplitude of the vertical tremor of aircraft is greater than the gravity of aircraft.
When 3, landing, the moment of wheel ground connection is first mainly subject to huge static vertical shock load, and wheel accelerates to reach the speed same with aircraft in ground roll-out with very high acceleration then.Heavily land if aircraft creates, the harm that bearing bears this shock load under the state do not operated is very large.If band sideslip ground connection, time as larger in crosswind, wheel also will receive larger side load, when wheel is subject to side-friction force, due to inertia effect, and the trend of the oriented lopsidedness of aircraft.Therefore act on vertical load on outboard bearing and side load larger than inner side.
In several failure modes that bearing is common, airplane wheel bearing is threatened maximum for wheel bearing is after bearing larger shock load, make surface of contact generation plastic yielding because overload comprises local overload, be called that plastic yield was lost efficacy.
Along with the demand of current countries in the world to large transport airplane is increasing, the wheel bearing developing high rotating speed heavy load is also more and more urgent, and people also more and more recognize the importance of wheel bearing test.Bearing test is an indispensable important proof procedure in design bearing and manufacture process, according to the actual installation operating mode of bearing, actual motion state on bearing tester, namely the rotating speed of bearing, axial load, radial load and environment temperature, lubricating status etc. operate according to actual condition is given, reach predetermined age or to bearing failure.
Bearing tester is of a great variety both at home and abroad at present, the bearing testers such as railway bearing, wind power bearing and machine bearing can be, structure is roughly and uses electro spindle to drive the inner ring of the test bearing be arranged in bearing seat to rotate, high-speed bearing testing machine disclosed in Chinese patent CN201210103079, bearing shaft to opposite side utilize axial loading device to realize axial load to load, the radial side of bearing utilizes radial loading device to realize radial load and loads.
The working method of testing machine determines the test method of measured piece, and therefore, bearing test methods of the prior art is all similar, and its method and principle, as Inspection Aircraft Wheels bearing test, just seem unable to do what one wishes.
One, in driving bearing rotation, the inner ring of what the testing machine applied in art methods used electro spindle driven rotary is bearing, this runs counter to the rotation mode that Inspection Aircraft Wheels bearing outer ring rotates, and thus this type of testing machine principle cannot be simulated the actual applying working condition of Inspection Aircraft Wheels.The domestic at present rolling bearing simulation experiment method also having " outer ring temperature of inner ring during rotation is fixed ", the rolling bearing simulation experiment method that outer ring temperature of inner ring during rotation is fixing disclosed in Chinese patent CN201010254885, these class methods are be connected with the outer ring of test bearing by shaft coupling by motor.There is many defects in the method, such as, drive motor directly drives outer ring synchronous rotary, as need axial loading be carried out, axial application of force acts directly on rotor by test bearing outer ring, and rotor can not bear the axial thrust of up to a hundred thousand Ns, therefore these class methods can not realize axial loading.
Its two, the loaded load of prior art test machine loader value is limited, does not far reach the high load capacity testing requirements of current wheel bearing.The typical bearing tester of prior art, the mode that its driving bearing rotates is the inner ring synchronous rotary using electro spindle directly to drive the test bearing be arranged in bearing seat, as need axial loading be carried out, axial force finally acts on the rotor of electro spindle, and the rotor of electro spindle can not bear the axial thrust of up to a hundred thousand Ns, because which limit the axial loaded load of the bearing tester of this type.
They are three years old, the typical testing machine of prior art carrys out the mode of Direct driver bearing inner race with motor drive shaft, make the side-play amount requirement of the radial direction to bearing inner race, axis very high, once side-play amount is excessive, the centrifugal imbalance that High Rotation Speed brings will threaten whole testing machine, therefore this type of testing machine load capability is limited, and high speed and heavy load can not get both.Which results in this type of testing machine and use limitation, and then cause existing test method can only complete load test or the speed test of wheel bearing respectively, the simulation test that but cannot complete wheel bearing carrys out the actual applying working condition of analog machine wheel bearing.
Its four, all kinds of bearing testers of prior art, all need to accompany examination bearing accordingly at the trial, accompany examination bearing, coaxial rotation synchronous with test bearing, and bear the reacting force of test bearing radial direction, axial load.Therefore, testing machine is when testing high-speed bearing, and needs can bear more high-revolvingly accompanies examination bearing; During the bearing of test high load capacity, what need to bear more high load capacity accompanies examination bearing; When carrying out bearing life test, often test once, need to reach a pair life-span longer accompany examination bearing.This makes the ultimative function of testing machine be limited to and accompanies examination bearing on the one hand, as then infeasible in developed more high performance bearing.On the other hand, extra increase accompany examination bearing for a pair, and the main shaft rotated, all be in test bearing in a frock, be all heater when rotated, friction force causes bulk temperature sharply to increase, and test is increased the measurement of loaded load, the measuring error of bearing temperature, and greatly reduce the safety coefficient of testing machine, easily because the softening of bearing causes security incident.The exploitativeness of this existing test method is limited, also reduces the confidence level of its test figure.
Its five, in art methods, when carrying out Equivalent static load and loading, be axial load and radial load loads respectively.This type of theoretical method, as being applied in Inspection Aircraft Wheels bearing simulation test, principle is the lateral deviation force status of the analog machine wheel bearing of making a concerted effort to come by axial force and radial force.But comparative analysis airplane wheel bearing actual condition and this type of test method, find when realizing wheel bearing lateral deviation loading force, make a concerted effort to simulate lateral deviation power as loaded formation respectively from axis and radial direction, this makes the stressed of two wheel bearings be average, and the large and stress equalization of the stressed breadth of each wheel bearing, especially axially loading makes wheel bearing when bearing axial force, lifting surface area is its whole side breadth, axial force is also balancedly distributed in its whole side breadth, thus on each roll body putting in test bearing making axial force average; ; the airplane wheel of actual lateral deviation; because wheel surface of tyre is circular arc; load makes the side surface of wheel tire form a plane of constraint; its power conducts to wheel bearing, and in wheel, two cover shaft strengths are uneven, and lateral deviation power is partial to that cover wheel bearing in lateral deviation direction; and the stressed breadth often overlapping bearing is little and and unbalanced, each roll body is stressed different in bearing.
Along with improving constantly of present generation aircraft performance requirement, the performance of airplane wheel is had higher requirement, wheel should have lightweight, load-bearing capacity is large, the life-span is high, and can bear large shock load, therefore, higher requirement is also proposed to the bearing of selecting of wheel.Wheel bearing is by heavy duty, shock load and life test results, and selecting for wheel is inexorable trend.
In sum, the domestic special simulation experiment method for airplane wheel bearing is still sheet weakness zone, now extremely urgent to the exploration of wheel bearing operating state data when aircraft is static, release the simulation experiment method conformed to for Inspection Aircraft Wheels bearing operating mode imperative.
Summary of the invention
For overcome exist in prior art can not simulated aircraft lateral deviation shut down opportunity wheel bearing lateral deviation force status, can not excite out of order effectively, reliably, the present invention proposes a kind of airplane wheel bearing static load simulation experiment method.
The present invention carries out described airplane wheel bearing static load simulation test by the charger of bearing tester.The charger of described bearing tester comprises hydraulic cylinder, fixed head, load transducer, column, portable plate, rubber wheel, loading head, loading axle, detent and brake disc; Charger is fixed on the upper surface of grade slab by column; Fixed head is fixed on the end face of column top; Hydraulic cylinder is arranged on the geometric center of described fixed head upper surface, and make the expansion link of this hydraulic cylinder through after fixed head the lower surface of this fixed head and portable plate upper surface; Described portable plate level is arranged on the middle part of described column, and is that guide rail moves up and down with column; Described portable plate upper surface geometric center is provided with load transducer; Described portable plate lower surface has guide-track groove, and the carried base board that adds of loading head is arranged in this guide-track groove; Load transducer is fixedly mounted between the end face and portable plate of the expansion link of hydraulic cylinder; The two ends loading axle are separately fixed on two loading arms of loading head; Test bearing is arranged on the middle part loading axle; Rubber wheel is sleeved on the outer ring of described test bearing; Brake disc is sleeved on and loads on axle, and the flange on this brake disc is fixedly connected with an end face of rubber wheel; The braking video disc of described brake disc is arranged in the braking intermediate plate of detent; The upper end of described detent is fixed in loading head the lower surface adding carried base board.
Concrete steps of the present invention are:
Step 1: static loading is tested, heavy load condition when simulated aircraft is static.The content of described static loading test comprises test bearing has flawless and distortion under rated load; In described static loading test, under wheel yield load, wheel outer race does not allow to loosen.Described wheel yield load is the maximum load of wheel; Detailed process is:
The first step: installation test bearing.
Second step: load transducer returns to zero.By promoting the height of portable plate, the rubber wheel be arranged on below this portable plate is made to be in vacant state; Adjustment load transducer is to zero-bit.
3rd step: Adjustment Tests machine is to the critical conditions loaded.Promote loading activity plate by load cylinder to move down along column with the speed of 1mm/s; Be arranged on the position of the rubber wheel on loading head by the adjustment of loading activity plate, make the peripheral surface contacts of the circumferential surface of this rubber wheel and static drum.
4th step: static load load test.
First the parameter of load test is determined.Described load test parameter comprises the working pressure of oil cylinder output and the maximum test load of test bearing.
After described each test parameters is determined, test bearing is loaded.In loading:
By strengthening the oil pressure of load cylinder inflow point, the working pressure that oil cylinder is exported is increased to 13.8MPa in 0 ~ 6s internal linear, applies radial load by drum to bearing; The described test load acting on test bearing is loaded on 850KN in 0 ~ 6s internal linear.When the test load acting on test bearing reaches 850KN, keep this load 20s.When after this load 20s of maintenance, by reducing the oil pressure of load cylinder inflow point, the working pressure that oil cylinder is exported is decreased to 0MPa in 0 ~ 6s internal linear, makes the test load acting on test bearing be offloaded to 0KN in 0 ~ 6s internal linear.
In load test process, to be ruptured by test bearing if occur or outer shroud loosen cause vibration, noise abnormal occurrence, then directly unload, and carry out the 5th step test.
5th step: the loading head that moves up after unloading makes rubber wheel leave drum.Dismounting test bearing and adopt conventional method to detect this bearing have flawless and distortion.If test bearing has crackle and distortion, off-test; Otherwise carry out step 2.
Step 2, static lateral deviation load test: described static lateral deviation load test be simulated aircraft static time lateral deviation heavy load condition lower bearing under rated load, have flawless, distortion.Under wheel yield load, wheel outer race does not allow to loosen.Described wheel yield load is the maximum load of wheel.
Process of the test is as follows:
The first step: the lateral deviation angle [alpha] determining U-shaped loading head.Described lateral deviation angle is the side drift angle of aircraft.Described side drift angle α is 0 ~ 20 °, and adjust U-shaped loading head in portable plate lowermost guide rail with the angle of vertical direction, with the side drift angle of simulated aircraft.
Second step: installation test bearing.
3rd step: load transducer returns to zero.According to the method for step 1 second step, load transducer is returned to zero.
4th step: Adjustment Tests machine is to the critical conditions loaded.Controlled loading oil cylinder pushing loading activity plate moves down along column with the speed of 1mm/s; Be arranged on the position of the rubber wheel on loading head by the adjustment of loading activity plate, make the peripheral surface contacts of the circumferential surface of this rubber wheel and static drum.
5th step: static load lateral deviation load test.
First the parameter of lateral deviation load test is determined.Described load test parameter comprises: the working pressure that oil cylinder exports, the maximum test load of test bearing, test bearing radial load and axial load.
After described each test parameters is determined, test bearing is loaded.In loading:
By strengthening the oil pressure of load cylinder inflow point, the working pressure that oil cylinder is exported is increased to 13.8MPa in 0 ~ 6s internal linear, applies radial load by drum to bearing; The described test load acting on test bearing is loaded on 850KN in 0 ~ 6s internal linear.When the test load acting on test bearing reaches 850KN, keep this load 20s.When after this load 20s of maintenance, by reducing the oil pressure of load cylinder inflow point, the working pressure that oil cylinder is exported is decreased to 0MPa in 0 ~ 6s internal linear, makes the test load acting on test bearing be offloaded to 0KN in 0 ~ 6s internal linear.
In load test process, to be ruptured by test bearing if occur or outer shroud such as to loosen at vibration that reason causes, the noise abnormal occurrence, then directly unload, and carry out the 6th step test.
6th step: the loading head that moves up after unloading makes rubber wheel leave drum.Dismounting test bearing and adopt conventional method to detect this bearing have flawless and distortion.
When described static load load test and static lateral deviation load test, the working pressure P of the output of oil cylinder is all determined by formula (1):
In formula: D is hydraulic cylinder internal diameter, unit is m; F is thrust hydraulic cylinder, and unit is N; P is working pressure, and unit is MPa
The maximum test load of described test bearing is the yield load of this test bearing.
When carrying out described static lateral deviation load test, the radial load F of test bearing
rdetermined by formula (2),
F
r＝F×cosα (2)
The axial load F of test bearing
αdetermined by formula (3):
F
α＝F×sinα (3)
The present invention is intended to realize the simulation of aircraft under static state wheel shaft strength operating mode.
The present invention is based upon on a kind of basis of relative rolling type airplane wheel bearing load impact testing machine, and testing machine is primarily of dragging system and loading system composition, and dragging system provides power, and test bearing is rotated by the rotating speed of regulation; Loading system provides test load for test bearing, and warranty test bearing is by the load test of regulation.
Compared with the prior art, the present invention has following characteristics:
A) testing apparatus compares: the airplane wheel bearing load impact testing machine that the present invention relates to, relative to prior art, avoids the use of accompanying examination bearing, has broken conventional test machine by the limitation of accompanying the maximum speed restriction of examination bearing and load-bearing capacity.
B) in process of the test, imposed load compares: be applied on each stress surface of battery of tests bearing or single test bearing respectively equably by axis or radial load to the load applying of wheel bearing in prior art, or each stress surface axis and radial load being applied to respectively equably battery of tests bearing is formed to make a concerted effort to simulate bearing lateral deviation stressed, this makes one group two to overlap the equilibrium of wheel shaft strength, stress surface uniform force.The actual loading force distribution being applied to wheel bearing of loading method energy simulated aircraft load of the present invention.
C) failure effect is excited to compare: art methods makes wheel bearing a big chunk fault can not excite out.The present invention can simulation test shaft strength time the stress point of actual applying working condition and Impact direction, more unfailing test data can be provided.The present invention utilizes the charger of described testing machine to provide loaded load F, and the load be applied on wheel bearing for simulated aircraft deadweight, the direction of its power is that vertical-horizontal faces down.During quiet load test, the non-lateral deviation of wheel, load suffered by wheel bearing is pure radial load, and radial load Fr value is with equaling loaded load F.When carrying out static lateral deviation load test, wheel and surface level have certain angle, for side drift angle α, its test bearing is as shown in Figure 5 stressed, to be Aircraft Load F vertically downward, Aircraft Load F by total load be respectively axial load F suffered by test bearing along the axis of test bearing and radial component to test bearing
α, radial load F
r, its value size is respectively F
α=F*sin α, F
r=F*cos α.The present invention simulated aircraft lateral deviation can shut down wheel bearing lateral deviation force status on opportunity substantially, effectively, reliably can inspire fault.
The present invention with reference to domestic wind power bearing, high ferro bearing and aircraft engine machine bearing etc. the test method of bearing, have references to the test method of the large aircraft wheel testing table of current domestic advanced person simultaneously, reach simulated aircraft taking off, high speed slide, moment is impacted during landing, lateral deviation is landed and wheel shaft strength operating mode in stopped process, the applying working condition states such as test condition, the operating mode of wheel bearing can be reflected all sidedly, with to its intensity, life-span is assessed accurately, for the higher rotating speed of research, more the Inspection Aircraft Wheels bearing of heavy load provides believable test basis, can greatly shorten its lead time.
Accompanying drawing explanation
Fig. 1 is the structural representation of the testing machine that the present invention uses.
Fig. 2 is test bearing scheme of installation.
Fig. 3 is static loading test load spectrum.
Fig. 4 is static lateral deviation load test loading spectrum.
Fig. 5 is static lateral deviation loading tester wheel bearing force diagram
Fig. 6 is process flow diagram of the present invention.In figure:
1. triphase AC variable frequency speed-regulating asynchronous machine; 2. clutch coupling; 3. bearing seat; 4. drum; 5. substrate; 6. rubber wheel; 7.U shape loading head; 8. load axle; 9. detent; 10. portable plate; 11. load transducers; 12. columns; 13. fixed heads; 14. hydraulic cylinders; 15. wheel shafts; 16. shaft couplings; 17. round nuts; 18. axle sleeves; 19. test bearings; 20. brake discs; 21. Aircraft Load F; 22. bearing radial load F
r; 23. bearing axial load F
α.
Embodiment
The present embodiment is the static load test of aircraft wheel bearing, and the airplane wheel bearing load impact testing machine of employing is disclosed in the innovation and creation of 2014102708950.Whether the content of described static load test comprises test bearing with or without distortion under rated load, and crack.
Described airplane wheel bearing load impact testing machine comprises dragging system and loading system.Dragging system is same as the prior art, comprises triphase AC variable frequency speed-regulating asynchronous machine 1, clutch coupling 2, bearing seat 3, wheel shaft 15 and drum 4.
Loading system is vertical hydraulic load mode, comprises substrate 5, rubber wheel 6, U-shaped loading head 7, loads axle 8, detent 9, portable plate 10, load transducer 11, column 12, fixed head 13, hydraulic cylinder 14, shaft coupling 16, round nut 17, axle sleeve 18, test bearing 19, brake disc 20.Wherein dragging system is positioned at foundation ditch, and substrate 5 is positioned at foundation ditch upper surface, and loading system is arranged on described substrate 5 upper surface.Drum in dragging system is arranged on wheel shaft 15, and makes the circumferential surface of this drum through the drum groove be positioned on substrate 5, coordinates with the rubber wheel 6 in loading system.Described rubber wheel is sleeved on loading system
Described rubber wheel 6 comprises steel ring and encapsulate.Even cloth four threaded holes on an end face of steel ring, for installing brake disc 20.The internal diameter size of two each and every one end faces of steel ring presses the external diameter execution of test bearing 19.Encapsulate is that vulcanized rubber encapsulate is on the outer ring of steel ring.
Drive system is relative rolling type passive matrix wheel bearing, and it is in the innovation and creation of 201410293088.0 that the architectural feature of this drive system is disclosed in application number.In this drive system, the rotor of triphase AC variable frequency speed-regulating asynchronous machine 1 is connected with an end face of clutch coupling 2, and another end face of clutch coupling 2 is connected with wheel shaft 15 by shaft coupling 16.Wheel shaft 15 is installed with on two bearing seats 3.Drum 4 is installed on wheel shaft 3.Triphase AC variable frequency speed-regulating asynchronous machine 1 drives drum 4 to rotate by clutch coupling 2, shaft coupling 16, wheel shaft 15.
Column 12 is totally four four angles being distributed in substrate 5, and as the guide rail that portable plate 10 moves up and down, axis when bearing loading and radial force.Fixed head 13 level is installed, and is fixed on above four columns 12, and its geometric center installs fixing load cylinder 14, and bears the reacting force of vertical impact loaded load.Drawing and pressing type load transducer 11 is installed, for measuring Impulsive load load value between load cylinder 14 and portable plate 10.
Described portable plate 10 comprises boss, substrate and circular groove guide rail.Substrate is tetragonal body steel plate, and respectively there is a manhole at its four angles, and clear size of opening is that the outside dimension of column 12 performs.Boss is positioned at the geometric center place of substrate upper surface, for installed load sensor 11.Circular groove guide rail is longitudinally positioned at the geometric center place, lower surface of substrate, each even cloth five threaded holes on the breadth of its both sides.Portable plate 10 level is installed, and the manhole at four angles of its substrate, is placed on four columns 12 respectively, and column 12 can be utilized to move up and down for guide rail.
Described U-shaped loading head comprises arc plate and two loading arms.The upper surface of arc plate is convex shaped arc face.Two loading arms are symmetrically located at the lower surface of arc plate.There is manhole the lower end of each loading arm, and its clear size of opening performs by loading axle 8 end face external diameter.
In enforcement, test bearing 19 1 group two cover is installed in rubber wheel 6, and the outer ring of test bearing is fixed in steel ring, and inner ring is installed on and loads on axle, and fastening by round nut 17.Load axle 8 two ends to be installed on the loading arm of U-shaped loading head 7 by axle sleeve 18.The arc plate of the upper surface of U-shaped loading head 7 is installed in the circular groove guide rail of portable plate 10 lower surface, and passes through the bolt presses of guide rail both ends of the surface.
The present embodiment is the static load simulation test of certain type wheel bearing, comprises static loading test and static lateral deviation load test.
The charger used is vertical loading device, realizes the load on of simulated aircraft load to wheel bearing by the vertical loading of charger.During static loading test, radial load 850KN.
In the present embodiment, rubber wheel φ 248mm, drum diameter phi 1200mm.Select loading hydraulic cylinder piston diameter to be 280mm, diameter of piston rod is 160mm.
The concrete steps of the present embodiment comprise:
Step 1: static loading is tested, heavy load condition when simulated aircraft is static.The content of described static loading test comprises test bearing has flawless, distortion under rated load.According to GJB1184A-2008 " Inspection Aircraft Wheels and brake gear general specification ", under wheel yield load, wheel outer race does not allow to loosen.Described wheel yield load is the maximum load of wheel.
The first step: installation test bearing.Test bearing 19 1 group two overlaps symmetry and is arranged in rubber wheel 6, and the outer ring of test bearing is fixed in steel ring, and inner ring is arranged on and loads on axle 8, and fastening by round nut 17.Load axle 8 two ends to be arranged on the loading arm of U-shaped loading head 7 by axle sleeve 18.
Second step: load transducer returns to zero.Start-up loading system, the extension elongation of controlled loading oil cylinder expansion link, promotes the height of portable plate, makes the rubber wheel be arranged on below this portable plate be in vacant state.Because of the deadweight of portable plate and loading head, the part as vertical load puts on test bearing by the gravity of described deadweight during vertical loading, and therefore under rubber wheel is in vacant state, adjustment load transducer is to zero-bit.
3rd step: Adjustment Tests machine is to the critical conditions loaded.Controlled loading oil cylinder 14 promotes loading activity plate 10 and moves down with the speed of 1mm/s along column 12; Be arranged on the position of the rubber wheel on loading head by the adjustment of loading activity plate, make the peripheral surface contacts of the circumferential surface of this rubber wheel and static drum 4.
4th step: static load load test.
First the parameter of load test is determined.Described load test parameter comprises: the working pressure that oil cylinder exports, the maximum test load of test bearing.Wherein:
The working pressure that oil cylinder exports is determined by formula (1):
In formula: D is hydraulic cylinder internal diameter, unit is m; F is thrust hydraulic cylinder, and unit is N; P is working pressure, and unit is MPa.
In the present embodiment, hydraulic cylinder piston diameter is 280mm, and the working pressure that oil cylinder exports is 13.8MPa.
The maximum test load of test bearing: the maximum test load of test bearing is the yield load of this test bearing.In the present embodiment, the maximum test load of described test bearing is 850KN.
After described each test parameters is determined, test bearing is loaded.In loading:
By load transducer 11 monitor be applied to load on test bearing.By strengthening the oil pressure of load cylinder inflow point, the working pressure that oil cylinder is exported is increased to 13.8MPa in 0 ~ 6s internal linear, the piston rod of oil cylinder drives loading activity plate to load by load transducer, move when loading activity strip and be arranged on rubber wheel on loading head to drum 4 imposed load, then by this dynamic changes process to the bearing being positioned at drum 4; The load that bearing is subject to is radial load.The described test load acting on test bearing is loaded on 850KN in 0 ~ 6s internal linear.When the test load acting on test bearing reaches 850KN, keep this load 20s.When after this load 20s of maintenance, by reducing the oil pressure of load cylinder inflow point, the working pressure that oil cylinder is exported is decreased to 0MPa in 0 ~ 6s internal linear, makes the test load acting on test bearing be offloaded to 0KN in 0 ~ 6s internal linear.
In load test process, to be ruptured by test bearing if occur or outer shroud loosen cause vibration, noise abnormal occurrence, then directly unload, and carry out the 5th step test.
5th step: the loading head that moves up after unloading makes rubber wheel leave drum 4.Dismounting test bearing and adopt conventional method to detect this bearing have flawless and distortion.If test bearing has flawless and deformation test to terminate, otherwise carry out step 2.
Step 2, static lateral deviation load test, lateral deviation heavy load condition when simulated aircraft is static.The content of described static lateral deviation load test comprises test bearing has flawless, distortion under rated load.According to GJB1184A-2008 " Inspection Aircraft Wheels and brake gear general specification ", under wheel yield load, wheel outer race does not allow to loosen.Described wheel yield load is the maximum load of wheel.
In the present embodiment, lateral deviation angle [alpha] is 12 °.
Process of the test is as follows:
The first step: the lateral deviation angle [alpha] determining U-shaped loading head 7.Described lateral deviation angle is the side drift angle of aircraft.Described side drift angle α is 0 ~ 20 °, in the present embodiment, selects side drift angle α to be 12 °.U-shaped loading head 7 is adjusted deviation angle in portable plate lowermost guide rail, makes the angle of itself and vertical direction be adjusted to 12 ° from 0 °, and utilize the bolt presses of guide rail both ends of the surface.
Second step: installation test bearing.Being overlapped by the test bearing 19 1 group two tested through static loading is arranged in rubber wheel 6 according to the method for step 1 second step, and the outer ring of test bearing is fixed in steel ring, and inner ring is arranged on and loads on axle 8, and fastening by round nut 17.Load axle 8 two ends to be arranged on the loading arm of U-shaped loading head 7 by axle sleeve 18.
3rd step: load transducer returns to zero.According to the method for step 1 second step, load transducer is returned to zero.
4th step: Adjustment Tests machine is to the critical conditions loaded.Controlled loading oil cylinder 14 promotes loading activity plate 10 and moves down with the speed of 1mm/s along column 12; Be arranged on the position of the rubber wheel on loading head by the adjustment of loading activity plate, make the peripheral surface contacts of the circumferential surface of this rubber wheel and static drum 4.
5th step: static load lateral deviation load test.
First the parameter of lateral deviation load test is determined.Described load test parameter comprises: the working pressure that oil cylinder exports, the maximum test load of test bearing, test bearing radial load and axial load.Wherein:
The working pressure that oil cylinder exports is determined by formula (1):
In formula: D is hydraulic cylinder internal diameter, unit is m; F is thrust hydraulic cylinder, and unit is N; P is working pressure, and unit is MPa.
The radial load F of test bearing
rdetermined by formula (2):
F
r＝F×cosα (2)
The axial load F of test bearing
αdetermined by formula (3):
F
α＝F×sinα (3)
In the present embodiment, hydraulic cylinder piston diameter is 280mm, and the working pressure that oil cylinder exports is 13.8MPa, and the radial load of test bearing is 831KN, and axial load is 177KN.
The maximum test load of test bearing: the maximum test load of test bearing is the yield load of this test bearing.In the present embodiment, the maximum test load of described test bearing is 850KN.
After described each test parameters is determined, test bearing is loaded.In loading:
By load transducer 11 monitor be applied to load on test bearing.By strengthening the oil pressure of load cylinder inflow point, the working pressure that oil cylinder is exported is increased to 13.8MPa in 0 ~ 6s internal linear, the piston rod of oil cylinder drives loading activity plate to load by load transducer, move when loading activity strip and be arranged on rubber wheel on loading head to drum 4 imposed load, then by this dynamic changes process to the bearing being positioned at drum 4; The load that bearing is subject to is radial load.The described test load acting on test bearing is loaded on 850KN in 0 ~ 6s internal linear.When the test load acting on test bearing reaches 850KN, keep this load 20s.When after this load 20s of maintenance, by reducing the oil pressure of load cylinder inflow point, the working pressure that oil cylinder is exported is decreased to 0MPa in 0 ~ 6s internal linear, makes the test load acting on test bearing be offloaded to 0KN in 0 ~ 6s internal linear.
In load test process, to be ruptured by test bearing if occur or outer shroud such as to loosen at vibration that reason causes, the noise abnormal occurrence, then directly unload, and carry out the 6th step test.
6th step: the loading head that moves up after unloading makes rubber wheel leave drum 4.Dismounting test bearing and adopt conventional method to detect this bearing have flawless and distortion.
Claims (4)
1. an airplane wheel bearing static load simulation experiment method, carries out described airplane wheel bearing static load simulation test by the charger of bearing tester; The charger of described bearing tester comprises hydraulic cylinder, fixed head, load transducer, column, portable plate, rubber wheel, loading head, loading axle, detent and brake disc; Charger is fixed on the upper surface of grade slab by column; Fixed head is fixed on the end face of column top; Hydraulic cylinder is arranged on the geometric center of described fixed head upper surface, and make the expansion link of this hydraulic cylinder through after fixed head the lower surface of this fixed head and portable plate upper surface; Described portable plate level is arranged on the middle part of described column, and is that guide rail moves up and down with column; Described portable plate upper surface geometric center is provided with load transducer; Described portable plate lower surface has guide-track groove, and the carried base board that adds of loading head is arranged in this guide-track groove; Load transducer is fixedly mounted between the end face and portable plate of the expansion link of hydraulic cylinder; The two ends loading axle are separately fixed on two loading arms of loading head; Test bearing is arranged on the middle part loading axle; Rubber wheel is sleeved on the outer ring of described test bearing; Brake disc is sleeved on and loads on axle, and the flange on this brake disc is fixedly connected with an end face of rubber wheel; The braking video disc of described brake disc is arranged in the braking intermediate plate of detent; The upper end of described detent is fixed in loading head the lower surface adding carried base board;
It is characterized in that, the step of airplane wheel bearing static load simulation test is:
Step 1: static loading is tested, heavy load condition when simulated aircraft is static; The content of described static loading test comprises test bearing has flawless and distortion under rated load; In described static loading test, under wheel yield load, wheel outer race does not allow to loosen; Described wheel yield load is the maximum load of wheel; Detailed process is:
The first step: installation test bearing;
Second step: load transducer returns to zero; By promoting the height of portable plate, the rubber wheel be arranged on below this portable plate is made to be in vacant state; Adjustment load transducer is to zero-bit;
3rd step: Adjustment Tests machine is to the critical conditions loaded; Promote loading activity plate by load cylinder to move down along column with the speed of 1mm/s; Be arranged on the position of the rubber wheel on loading head by the adjustment of loading activity plate, make the peripheral surface contacts of the circumferential surface of this rubber wheel and static drum;
4th step: static load load test;
First the parameter of load test is determined; Described load test parameter comprises the working pressure of oil cylinder output and the maximum test load of test bearing;
After described each test parameters is determined, test bearing is loaded; In loading:
By strengthening the oil pressure of load cylinder inflow point, the working pressure that oil cylinder is exported is increased to 8.89MPa in 0 ~ 6s internal linear, applies radial load by drum to bearing; The described test load acting on test bearing is loaded on 850KN in 0 ~ 6s internal linear; When the test load acting on test bearing reaches 850KN, keep this load 20s; When after this load 20s of maintenance, by reducing the oil pressure of load cylinder inflow point, the working pressure that oil cylinder is exported is decreased to 0MPa in 0 ~ 6s internal linear, makes the test load acting on test bearing be offloaded to 0KN in 0 ~ 6s internal linear;
In load test process, to be ruptured by test bearing if occur or outer shroud loosen cause vibration, noise abnormal occurrence, then directly unload, and carry out the 5th step test;
5th step: the loading head that moves up after unloading makes rubber wheel leave drum; Dismounting test bearing and adopt conventional method to detect this bearing have flawless and distortion; If test bearing has crackle and distortion, off-test; Otherwise carry out step 2;
Step 2, static lateral deviation load test: described static lateral deviation load test be simulated aircraft static time lateral deviation heavy load condition lower bearing under rated load, have flawless, distortion; Under wheel yield load, wheel outer race does not allow to loosen; Described wheel yield load is the maximum load of wheel;
Process of the test is as follows:
The first step: the lateral deviation angle [alpha] determining U-shaped loading head; Described lateral deviation angle is the side drift angle of aircraft; Described side drift angle α is 0 ~ 20 °, and adjust U-shaped loading head in portable plate lowermost guide rail with the angle of vertical direction, with the side drift angle of simulated aircraft;
Second step: installation test bearing;
3rd step: load transducer returns to zero; According to the method for step 1 second step, load transducer is returned to zero;
4th step: Adjustment Tests machine is to the critical conditions loaded; Controlled loading oil cylinder pushing loading activity plate moves down along column with the speed of 1mm/s; Be arranged on the position of the rubber wheel on loading head by the adjustment of loading activity plate, make the peripheral surface contacts of the circumferential surface of this rubber wheel and static drum;
5th step: static load lateral deviation load test;
First the parameter of lateral deviation load test is determined; Described load test parameter comprises: the working pressure that oil cylinder exports, the maximum test load of test bearing, test bearing radial load and axial load;
After described each test parameters is determined, test bearing is loaded; In loading:
By strengthening the oil pressure of load cylinder inflow point, the working pressure that oil cylinder is exported is increased to 8.89MPa in 0 ~ 6s internal linear, applies radial load by drum to bearing; The described test load acting on test bearing is loaded on 850KN in 0 ~ 6s internal linear; When the test load acting on test bearing reaches 850KN, keep this load 20s; When after this load 20s of maintenance, by reducing the oil pressure of load cylinder inflow point, the working pressure that oil cylinder is exported is decreased to 0MPa in 0 ~ 6s internal linear, makes the test load acting on test bearing be offloaded to 0KN in 0 ~ 6s internal linear;
In load test process, to be ruptured by test bearing if occur or outer shroud such as to loosen at vibration that reason causes, the noise abnormal occurrence, then directly unload, and carry out the 6th step test;
6th step: the loading head that moves up after unloading makes rubber wheel leave drum; Dismounting test bearing and adopt conventional method to detect this bearing have flawless and distortion.
2. airplane wheel bearing static load simulation experiment method as claimed in claim 1, it is characterized in that, when static load load test and static lateral deviation load test, the working pressure P of the output of oil cylinder is all determined by formula (1):
In formula: D is hydraulic cylinder internal diameter, unit is m; F is thrust hydraulic cylinder, and unit is N; P is working pressure, and unit is MPa.
3. airplane wheel bearing static load simulation experiment method as claimed in claim 1, it is characterized in that, the maximum test load of described test bearing is the yield load of this test bearing.
4. airplane wheel bearing static load simulation experiment method as claimed in claim 1, is characterized in that, during static lateral deviation load test, and the radial load F of test bearing
rdetermined by formula (2),
F
r＝F×cos α (2)
The axial load F of test bearing
αdetermined by formula (3):
F
α＝F×sin α (3)。
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| CN105334056A (en) * | 2015-11-23 | 2016-02-17 | 西安航空制动科技有限公司 | Method for airplane wheel bearing side deflection load impact test |
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| CN111323197A (en) * | 2020-03-25 | 2020-06-23 | 安徽三联学院 | Airplane shafting impact vibration simulation test device and use method thereof |
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| CN112393905A (en) * | 2020-12-14 | 2021-02-23 | 大连工业大学 | Rolling bearing tester with external impact excitation |
| CN113310695B (en) * | 2021-05-28 | 2023-01-31 | 中国商用飞机有限责任公司 | Aircraft engine windmill load ground simulation method and system |
| CN113310695A (en) * | 2021-05-28 | 2021-08-27 | 中国商用飞机有限责任公司 | Aircraft engine windmill load ground simulation method and system |
| CN114112392A (en) * | 2021-11-25 | 2022-03-01 | 中船动力研究院有限公司 | Bearing load determination method, device, equipment and storage medium |
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