CN104596697B - Undercarriage wheel brake kinetic moment measuring method - Google Patents
Undercarriage wheel brake kinetic moment measuring method Download PDFInfo
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- CN104596697B CN104596697B CN201410696644.9A CN201410696644A CN104596697B CN 104596697 B CN104596697 B CN 104596697B CN 201410696644 A CN201410696644 A CN 201410696644A CN 104596697 B CN104596697 B CN 104596697B
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Abstract
An undercarriage wheel brake kinetic moment measuring method measures a brake kinetic moment in a loading state or an undercarriage wheel in a braking test of a large inertia dynamic test bed, solves the problems that a dynamic braking moment of a brake device cannot be directly measured as a torque/force sensor cannot be mounted on an undercarriage and the dynamic test brake moment of the undercarriage is measured, meets kinetic moment measuring requirements of a brake test of undercarriages with different structural sizes and is used for measuring the brake moment of a plane brake device in the loading state. The undercarriage can serve as an onboard device of a plane and has a huge use value. The measuring method has the advantages that the measuring method is simple in structure, convenient to mount, fine in universality and safety, can be widely used for undercarriage brake tests of various military aircrafts and civil aircrafts and other wheel power tests of an automobile and the like, and has important social significance and application prospects, and time and labor are saved.
Description
Technical field
The invention belongs to aircraft brake experimental technique is and in particular to a kind of take up with other for airplane wheel installation state
The method of the brake torque measurement in the frame braking effort that falls test.
Background technology
Brake torque, also known as braking moment, is the moment of the prevention wheel rolling being produced by brake gear during wheel braking,
In opposite direction with reference to moment.It is one of key parameter of brake machine wheel design, is not only to determine brake device structure parameter
Foundation, and directly affect the structural strength of undercarriage, tire, wheel hub, be also calculate aircraft sliding run performance, decelerability,
The major parameter of ground run distance, sliding race time, energy absorption etc..Quiet brake torque can be divided into by the kinestate of wheel in use
With two kinds of dynamic brake torque.Quiet brake torque:Between wheel and ground no relative motion when brake gear provide brake torque.Dynamic
Brake torque:The brake torque that during sliding race, wheel brake provides.
With the development of aircraft, take off and be gradually increased with speed when landing and weight, during taking-off and landing
Security issues become increasingly urgent, requires also more and more higher to the performance and reliability of brake system, the safety that it is related to aircraft is returned
Boat, the ability continuing fight capability and adapting to airport.Therefore, wheel braking test is to ensure that the sliding race of aircraft, the weight of safety of landing
Want one of dynamic test project, its purpose is to examine wheel brake system can meet aircraft braking distance under different loads
Requirement it is ensured that aircraft is sliding runs and landing safety.
Domestic at present for aircraft brake system brake torque measurement be all dispatch from the factory before in large-scale brake inertial test table
On carry out, and do not have unfeasible measuring method for the brake gear being arranged on undercarriage, once becoming undercarriage machine
One technological difficulties of wheel brake test.
Chinese patent 201310652766 five-degree-of-freedom follow-up brake moment measurement device has been spoken approvingly of one kind and has been risen and fallen for band
The brake torque measurement apparatus of frame wheel braking test, its principle is using torque sensor direct measurement brake torque, its torsion
Square sensor one end is coaxially connected with brake gear by terminal pad, and the other end connects load expansion link, and load expansion link passes through
In hold-down support fixation and test-bed.The measurement of brake torque cannot be realized through analyzing this device.As described in this patent, connect
Disk is installed together with brake gear, does not but speak approvingly of terminal pad and is specifically partly connected with what of brake gear.Brake gear
Two kinds of brake disc transfer disk and quiet disk, Moving plate takes turns rotation at random, and such as terminal pad is connected with the Moving plate of brake gear, then make machine
Wheel is non-rotatable;Quiet disk and wheel shaft geo-stationary, if terminal pad is connected with the quiet disk of brake gear, and quiet disk is and runs through machine
The wheel shaft phase of wheel is fixed, and wheel shaft is connected with the opposite side undercarriage of wheel, a load machine of undercarriage inherently wheel
Structure, is power rather than counteracting force in the same direction with the power suffered by the bearing rod described in this device, and the torque sensor of therefore installation is surveyed
The brake torque measuring is the moment of components that actual brake moment is with respect to bearing rod.
Further, since the braking principle of aircraft is the kinetic energy to absorb aircraft for the friction relying on brake gear, therefore brake
Disk forms high temperature heat reservoir, and as measured to signal near heat reservoir, the signal temperature drift that high temperature causes must solve
Technological difficulties.
Therefore, the wheel braking torgue measurement with undercarriage is remained as to technological difficulties of wheel braking test.
Content of the invention
For overcoming the shortcomings of to carry out wheel braking torgue measurement to the wheel with undercarriage present in prior art,
The present invention proposes a kind of wheel braking kinetic moment measuring method having undercarriage.
The detailed process of the present invention is as follows:
Step 1:Force analysis.
When aircraft brake slides, the main stress of airplane wheel wheel shaft includes:Brake gear provide brake torque, by vertical
The flexure stress that downward Aircraft Load produces, and when aircraft is affected by crosswind ,/pressure is drawn by the wind-induced axial direction in this side.
It is applied in each stress on wheel shaft, the strain maximum on accuracy of measurement impact causes for the flexure stress of wheel shaft vertical direction
Deformation, the predominantly applying of Aircraft Load, or produce because of jolting of causing of ground out-of-flatness.Caused by flexure stress should
Become the upper and lower surface into wheel shaft for the position of maximum, compressive strain is maximum in the upper surface of wheel shaft, stretching strain is for wheel shaft lower surface
Greatly, linearly reduce from 0~90 ° with vertical direction angle according to wheel shaft surface circular arc radial line, the position therefore affecting minimum is wheel shaft
The two sides in axis horizontal direction.
Step 2:Determine strain gauge adhesion position and mode.When determining the paste position of foil gauge, need to consider strain
The temperature-compensating mode of piece, eliminate Aircraft Load and be applied to bending strain on wheel wheel shaft, and the sensitivity and accurately of measurement
Degree.For this reason, determining that strain gauge adhesion position and mode are:
The described wheel shaft surface being located at for strain gauge adhesion position between undercarriage leg and wheel hub, and make first to answer
Become piece R1The centrage of length direction and the second foil gauge R2Between the axis of the centrage of length direction and described wheel wheel shaft
Angle is respectively ± 45 °, by described first foil gauge R1With the second foil gauge R2Obtain strain stress at this respectively1And ε2, according to
Generalized Hooke law, obtains principal stress σi:
In formula (1):ε i is strain value, and E is Young's moduluss, and μ is the Poisson's ratio of measured piece.
Described principal stress σiIncluding tensile stress sigma1With compressive stress-σ2, and described tensile stress sigma1With compressive stress-σ2Direction
Two are mutually perpendicular to.
And | σ1|=|-σ2| (2)
Principal stress value is equal to maximum shear stress
|σi|=τmax(3)
By the maximum shear stress that moment of torsion produces it is
In the first foil gauge R with stickup1With the second foil gauge R2The plane of symmetry on paste the 3rd foil gauge R3Should with the 4th
Become piece R4.The first described foil gauge R1With the 4th foil gauge R4Symmetrically, the second foil gauge R2With the 3rd foil gauge R3Symmetrically.
Four foil gauges are divided two groups, the first foil gauge R1With the second foil gauge R2One group, the 3rd foil gauge R3Should with the 4th
Become piece R4One group, every group of strain gauge adhesion direction is mutually perpendicular to, and is 45 ° with axis angle, is respectively symmetrically to be pasted on and is answered by curved
The wheel shaft both sides of the deformation minimum that power causes, specifically at the straight line surfaces that axis horizontal face is intersected with wheel shaft periphery.
5th step:Paste foil gauge.The strain gauge adhesion position being determined according to step 2 and mode, according to a conventional method by the
One foil gauge R1, the second foil gauge R2, the 3rd foil gauge R3With the 4th foil gauge R4It is pasted onto wheel shaft surface.
Step 3:Connect each foil gauge.By the first foil gauge R1, the second foil gauge R2, the 3rd foil gauge R3With the 4th strain
Piece R4By the series connection of full-bridge circuit connection, and access data collecting system according to a conventional method.
Step 4:Wheels-locked testing.Tested according to gear test specification, carry out data signal acquisition simultaneously and store.
Step 5:Measurement and Data Processing.
The first step:Filtering.
Second step:The strain data of wheel shaft is converted to brake torque.Described wheel axial strain conversion is realized by formula (6)
For brake torque:
Wheel wheel shaft moment of torsion
In formula, Torsion Section coefficientD is wheel shaft diameter;
By foil gauge full-bridge circuit connection, full-bridge circuit output voltage u is obtained by formula (7)0
ε in formulaiSurvey the strain value read, ε for deformeter1For the first foil gauge R1Strain value, ε2For the second foil gauge R2's
Strain value, ε3For the 3rd foil gauge R3Strain value, ε4For the 4th foil gauge R4Strain value.
Obtained by formula (7)
Brake torque is drawn by formula (6,7)
Brake torque curve is obtained by formula (8).So far, complete the wheel braking kinetic moment measurement of undercarriage.
Under static state, wheel wheel shaft institute stress is applied to the radial direction vertically downward on wheel shaft to aircraft for Aircraft Load
Power, stress is flexure stress.When aircraft is braked in sliding, wheel wheel shaft, in addition to the flexure stress being applied by Aircraft Load, is gone back
Bear the torsion of brake gear applying, be shear stress.The described brake gear in this place is to torsion power produced by wheel wheel shaft
Square, as brake torque.
For flexure stress, using axisymmetric strain gauge adhesion method, offsetting be superimposed because of the applying of Aircraft Load curved should
Power.
Under moment of torsion effect, rotating shaft surface any unit area is in pure shear stress ζ state, and it is equivalent to and is become with axis
The principal stress σ of ± 45 ° of deflections1And σ2,Wherein σ1Direction is stretching strain ε1、ε3,σ2Direction is compressive strain ε2、ε4, therefore edge and axle
Line becomes ± 45 ° of directions to paste foil gauge, can measure strain.
Averaged by the two panels foil gauge of symmetrical mounting method, being caused by tyre load straight up can be offset
Flexure stress acts on, thus obtaining the strain under the pure shear stress suffered by rotating shaft surface.
Knowledge further according to the mechanics of materials can calculate shear stress size by strain gauge, thus calculating brake twisting resistance
Square.Or brake torque is obtained by the method demarcated.
The measurement apparatus of airplane wheel axle braking effort square of the present invention, for being under installation state, or
Wheel in the large-scale inertia momentum test wheels-locked testing with undercarriage for the platform, carried out braking effort square measurement, solve due to
On undercarriage, torque/force sensor cannot be installed and measured directly asking cannot be carried out to the dynamic brake moment of brake gear
Topic.
The simple structure of the present invention meets the kinetic moment measurement requirement of different structure size undercarriage wheels-locked testing, solution
A difficult problem for undercarriage dynamic test brake torque of having determined measurement, and when being creatively used for aircraft brake system and being in installation state
The measurement of brake torque, can use as the airborne equipment of aircraft, have huge use value.The present invention has structure letter
Single, easy for installation, laborsaving save time, the advantages of versatility is good, safety is good, can be widely used for various military secret, civil aircraft undercarriage is stopped
Other wheel power experimental tests such as car test and automobile, have important social meaning and application prospect.
Because the present invention uses, change what the measurement of current brake torque was only done experiment on inertial test table in wheel
When the present situation that measures, work condition state data when actually used to brake gear can be obtained, there is provided accurately brake dress
Put intensity and life appraisal, provide test basis for research performance more preferably brake gear.
Brief description
Fig. 1 is the structural representation of the present invention.
Fig. 2 is the connection diagram of foil gauge.
Fig. 3 is paste position schematic diagram.
Fig. 4 is the stress diagram of wheel shaft, and wherein, 4a is wheel shaft positive side unit area force diagram, and 4b is wheel shaft dorsal part
Face unit area force diagram.
Fig. 5 is the flow chart of the present invention.In figure:
1. wheel;2. wheel hub and brake gear;3. wheel shaft;4. undercarriage leg;5. foil gauge;6. data collecting system.
Specific embodiment
The present embodiment carries out the brake torque measurement of wheels-locked testing for aircraft after runway slides.
Described foil gauge 5 has 4, the respectively first foil gauge R1, the second foil gauge R2, the 3rd foil gauge R3Should with the 4th
Become piece R4.Data collecting system 6 is conventional strain acquisition system.Wherein, four foil gauges are divided into two groups, the first foil gauge R1
With the second foil gauge R2One group, the 3rd foil gauge R3With the 4th foil gauge R4One group;By two groups of foil gauges be symmetrically pasted onto wheel hub and
Wheel shaft surface between undercarriage leg 4, and be on the horizontal plane residing for axle axis.Two foil gauges in described every group
Angle between the centrage of length direction is 90 degree, and the centrage of described two foil gauge length direction and axis angle
It is 45 °.
Connected by full bridge circuit between described four foil gauges, and each outfan in this bridge circuit respectively with
Each orifice of data collecting system 6.Connected by full bridge circuit between described each foil gauge, temperature-compensating each other, with
The impact of the temperature change that elimination is answered brake gear to absorb aircraft kinetic energy and produced.
In the present embodiment, when aircraft brake slides, brake torque is produced by brake gear, aircraft kinetic energy is consumed with this.
During brake, wheel 1 produces brake torque at wheel hub and brake gear 2, and the cylinder showing as on wheel shaft 3 produces by torsion
The strain that moment is brought, the present embodiment utilizes the strain on four foil gauge 5 wheel axle 3 surfaces, with indirect measurement brake torque.
The detailed process of the present invention is as follows:
Step 1:Force analysis.
When aircraft brake slides, the stressing conditions of airplane wheel wheel shaft 3 are extremely complex, the main stress bag of wheel wheel shaft 3
Include:The brake torque of brake gear offer, the flexure stress being produced by Aircraft Load vertically downward, and when aircraft is subject to crosswind shadow
When ringing ,/pressure is drawn by the wind-induced axial direction in this side.It is applied in each stress on wheel shaft, maximum on accuracy of measurement impact
Strain the deformation causing for the flexure stress of wheel shaft vertical direction, the predominantly applying of Aircraft Load, or because ground out-of-flatness is drawn
That rises jolts and produces.The position of the strain maximum being caused by flexure stress is the upper and lower surface of wheel shaft, and compressive strain is in wheel shaft
Upper surface is maximum, and stretching strain is that wheel shaft lower surface is maximum, according to wheel shaft surface circular arc radial line with vertical direction angle from 0~90 ° of line
Property reduce, therefore affect minimum position be axle axis horizontal direction two sides.
Step 2:Determine strain gauge adhesion position and mode.When determining the paste position of foil gauge, need to consider strain
The temperature-compensating mode of piece, eliminate Aircraft Load and be applied to bending strain on wheel wheel shaft, and the sensitivity and accurately of measurement
Degree.
The first step:Determine strain gauge adhesion region.Choose and be located between undercarriage leg and wheel hub on wheel wheel shaft
Wheel shaft surface be strain gauge adhesion region.
Second step:Determine strain gauge adhesion angle:Known by the mechanics of materials, for the moment of torsion producing on wheel wheel shaft, with wheel
The direction of ± 45 ° of axle axis one-tenth is principal direction of stress.Paste first on the direction that the axis with described wheel wheel shaft becomes ± 45 °
Foil gauge R1With the second foil gauge R2, by described first foil gauge R1With the second foil gauge R2Obtain strain stress at this respectively1With
ε2, according to generalized Hooke law, obtain principal stress σi:
In formula (1):εiFor strain value, E is Young's moduluss, and μ is the Poisson's ratio of measured piece.
Described principal stress σiIncluding tensile stress sigma1With compressive stress-σ2, and described tensile stress sigma1With compressive stress-σ2Direction
Two are mutually perpendicular to.
And | σ1|=|-σ2| (2)
Principal stress value is equal to maximum shear stress
|σi|=τmax(3)
By the maximum shear stress that moment of torsion produces it is
Second step:Determine the temperature-compensating mode of foil gauge.Determinand has the thermal coefficient of expansion of oneself, so can be with
The change temperature elongates or shortens.In brake, brake gear absorbs aircraft kinetic energy and changes into heat energy, wheel shaft temperature meeting wheel
Rise therewith.With the first foil gauge R1The second foil gauge R is pasted in vertical direction2.First foil gauge R1With the second foil gauge R2
It is in same temperature environment, the stroke being caused by temperature is identical, the strain facies being caused by temperature is with so drawn by temperature
The output voltage rising is zero, and therefore two panels foil gauge temperature compensates each other, and can offset the impact of tension/compressive stress.
3rd step:Determine the removing method of bending strain and the raising method of measurement sensitivity.Straining with first pasting
Piece R1With the second foil gauge R2The plane of symmetry on paste the 3rd foil gauge R3With the 4th foil gauge R4.The first described foil gauge R1With
4th foil gauge R4Symmetrically, the second foil gauge R2With the 3rd foil gauge R3Symmetrically.The strain that flexure stress is produced on wheel shaft,
In the first foil gauge R1With the 4th foil gauge R4The strain that place produces is stretching strain △ R1With △ R4, the second foil gauge R2Should with the 3rd
Become piece R3Locate as compressive strain-△ R2With-△ R3, in the strain value of the symmetrical two groups of foil gauges generations pasted under same flexure stress
Equal:
|△R1|=|-△ R2|=|-△ R3|=| △ R4| (5)
Therefore, symmetrical method of attaching eliminates the flexure stress impact being applied on wheel shaft by Aircraft Load and because ground is uneven
The reason such as whole and the flexure stress impact that causes, and make bridge output voltage increased one times, improve measurement sensitivity.
4th step:Improve accuracy of measurement.From the force analysis of step 1, it is applied in each stress on wheel shaft, right
The deformation that the maximum strain of accuracy of measurement impact causes for the flexure stress of wheel shaft vertical direction, four foil gauges are divided two
Group, R1With R2One group, R3With R4One group, every group of strain gauge adhesion direction is mutually perpendicular to, and is 45 ° with axis angle, is respectively symmetrically
It is pasted on the minimum wheel shaft both sides of the deformation being caused by flexure stress, specifically intersect with wheel shaft periphery in axis horizontal face
At straight line surfaces.
5th step:Paste foil gauge.According to a conventional method wheel shaft surface is carried out pasting foil gauge pre-treatment and wanting by above
Ask, by foil gauge R1, foil gauge R2, foil gauge R3With foil gauge R4It is pasted onto wheel shaft surface.
Step 3:By foil gauge R1, foil gauge R2, foil gauge R3With foil gauge R4By the series connection of full-bridge circuit connection, and by often
Rule method accesses data collecting system 6.
Step 4:Wheels-locked testing.Tested according to gear test specification, carry out data signal acquisition simultaneously and store.
Step 5:Measurement and Data Processing.
The first step:Filtering.Measured strain data is filtered according to a conventional method, removes the hair causing because of vibration etc.
Thorn.
Second step:The strain data of wheel shaft is converted to brake torque.Described wheel axial strain conversion is realized by formula (6)
For brake torque:
Wheel wheel shaft moment of torsion
In formula, Torsion Section coefficientD is wheel shaft diameter;
By foil gauge full-bridge circuit connection, full-bridge circuit output voltage u is obtained by formula (7)0
ε in formulaiSurvey the strain value read, ε for deformeter1For foil gauge R1Strain value, ε2For foil gauge R2Strain value, ε3
For foil gauge R3Strain value, ε4For foil gauge R4Strain value.
From formula (7)
Brake torque is drawn by formula (6,7)
The brake torque curve being drawn by formula (8), the as present invention final gained brake torque data and curves.So far,
Complete the wheel braking kinetic moment measurement of undercarriage.
Claims (1)
1. a kind of wheel braking kinetic moment measuring method having undercarriage is it is characterised in that detailed process is as follows:
Step 1:Force analysis;
When aircraft brake slides, the main stress of airplane wheel wheel shaft includes:Brake gear provide brake torque, by vertically downward
The flexure stress that produces of Aircraft Load, and when aircraft is affected by crosswind ,/pressure is drawn by the wind-induced axial direction in this side;Apply
In each stress on wheel shaft, the shape that the strain maximum on accuracy of measurement impact causes for the flexure stress of wheel shaft vertical direction
Become, the predominantly applying of Aircraft Load, or produce because of jolting of causing of ground out-of-flatness;The strain being caused by flexure stress is
Big position is the upper and lower surface of wheel shaft, and compressive strain is maximum in the upper surface of wheel shaft, and stretching strain is that wheel shaft lower surface is maximum, according to
, from 0~90 ° of linear reduction, the position therefore affecting minimum is axle axis water for wheel shaft surface circular arc radial line and vertical direction angle
Square to two sides;
Step 2:Determine strain gauge adhesion position and mode;When determining the paste position of foil gauge, need to consider foil gauge
Temperature-compensating mode, eliminate Aircraft Load and be applied to bending strain on wheel wheel shaft, and the sensitivity of measurement and accuracy;For
This, determine that strain gauge adhesion position and mode are:
The described wheel shaft surface being located at for strain gauge adhesion position between undercarriage leg and wheel hub, and make the first foil gauge
R1The centrage of length direction and the second foil gauge R2Angle between the axis of the centrage of length direction and described wheel wheel shaft
It is respectively ± 45 °, by described first foil gauge R1With the second foil gauge R2Obtain strain stress at this respectively1And ε2, according to broad sense
Hooke's law, obtains principal stress σi:
In formula (1):ε i is strain value, and E is Young's moduluss, and μ is the Poisson's ratio of measured piece;
Described principal stress σiIncluding tensile stress sigma1With compressive stress-σ2, and described tensile stress sigma1With compressive stress-σ2Two, direction
It is mutually perpendicular to;
And | σ1|=|-σ2| (2)
Principal stress value is equal to maximum shear stress
|σi|=τmax(3)
By the maximum shear stress that moment of torsion produces it is
In the first foil gauge R with stickup1With the second foil gauge R2The plane of symmetry on paste the 3rd foil gauge R3With the 4th foil gauge
R4;The first described foil gauge R1With the 4th foil gauge R4Symmetrically, the second foil gauge R2With the 3rd foil gauge R3Symmetrically;
Four foil gauges are divided two groups, the first foil gauge R1With the second foil gauge R2One group, the 3rd foil gauge R3With the 4th foil gauge
R4One group, every group of strain gauge adhesion direction is mutually perpendicular to, and is 45 ° with axis angle, is respectively symmetrically to be pasted on and is drawn by flexure stress
The wheel shaft both sides of the deformation minimum rising, specifically at the straight line surfaces that axis horizontal face is intersected with wheel shaft periphery;
5th step:Paste foil gauge;The strain gauge adhesion position being determined according to step 2 and mode, according to a conventional method should by first
Become piece R1, the second foil gauge R2, the 3rd foil gauge R3With the 4th foil gauge R4It is pasted onto wheel shaft surface;
Step 3:Connect each foil gauge;By the first foil gauge R1, the second foil gauge R2, the 3rd foil gauge R3With the 4th foil gauge R4Press
Full-bridge circuit connection is connected, and accesses data collecting system according to a conventional method;
Step 4:Wheels-locked testing;Tested according to gear test specification, carry out data signal acquisition simultaneously and store;
Step 5:Measurement and Data Processing;
The first step:Filtering;
Second step:The strain data of wheel shaft is converted to brake torque;Realize described wheel axial strain by formula (6) to be converted to and stop
Car moment:
Wheel wheel shaft moment of torsion
In formula, Torsion Section coefficientD is wheel shaft diameter;
By foil gauge full-bridge circuit connection, full-bridge circuit output voltage u is obtained by formula (7)0
ε in formulaiSurvey the strain value read, ε for deformeter1For the first foil gauge R1Strain value, ε2For the second foil gauge R2Strain
Value, ε3For the 3rd foil gauge R3Strain value, ε4For the 4th foil gauge R4Strain value;
Obtained by formula (7)
Brake torque is drawn by formula (6,7)
Brake torque curve is obtained by formula (8);So far, complete the wheel braking kinetic moment measurement of undercarriage.
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CN107416192A (en) * | 2017-05-15 | 2017-12-01 | 河北天启通宇航空器材科技发展有限公司 | The axle connection mechanism of gyroplane wheel hub |
US10598209B2 (en) | 2017-09-08 | 2020-03-24 | Goodrich Corporation | Aircraft brake torque load reaction through landing gear bogie structure |
CN110803300B (en) * | 2019-11-22 | 2021-05-25 | 航天时代飞鸿技术有限公司 | Testing method of unmanned aerial vehicle wheel braking moment testing tool |
RU204025U1 (en) * | 2020-12-21 | 2021-05-04 | Открытое акционерное общество "Опытный завод N 31 Гражданской авиации" | AERODROME BRAKE TROLLEY FOR DETERMINING BRAKING CONDITIONS OF AIRCRAFT PNEUMATIC WHEELS |
CN116558699A (en) * | 2023-03-29 | 2023-08-08 | 中国航发湖南动力机械研究所 | Helicopter rotor wing brake starting torque measurement method and system |
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CN1305925A (en) * | 2000-10-13 | 2001-08-01 | 王丽莉 | Carriage for forced landing of aircraft with landing chassis |
CN1273813C (en) * | 2002-12-31 | 2006-09-06 | 中国农业机械化科学研究院 | Full machine ground load on site calibration test method and its device |
US7489996B2 (en) * | 2004-05-06 | 2009-02-10 | Hydro-Aire, Inc. | Antiskid control unit and data collection system for vehicle braking system |
CN102582602B (en) * | 2012-03-05 | 2014-12-31 | 西安航空制动科技有限公司 | Method for controlling brake efficiency of aircraft carbon brake disc in wet state |
CN202693185U (en) * | 2012-07-13 | 2013-01-23 | 哈尔滨飞机工业集团有限责任公司 | Equipment for measuring braking torque of aircraft wheel |
US9016134B2 (en) * | 2012-12-11 | 2015-04-28 | Goodrich Corporation | Circular load cell strain sensor configuration |
CN103604555B (en) * | 2013-12-04 | 2015-12-02 | 中国飞机强度研究所 | Five-degree-of-freedom follow-up brake moment measurement device |
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