CN107991044A - A kind of dynamometer check method studied perpendicular curved and lateral bending vibration damping and compare the influence of Bridge Flutter derivative - Google Patents
A kind of dynamometer check method studied perpendicular curved and lateral bending vibration damping and compare the influence of Bridge Flutter derivative Download PDFInfo
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- CN107991044A CN107991044A CN201711018593.4A CN201711018593A CN107991044A CN 107991044 A CN107991044 A CN 107991044A CN 201711018593 A CN201711018593 A CN 201711018593A CN 107991044 A CN107991044 A CN 107991044A
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
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- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
Abstract
The present invention provides a kind of dynamometer check method for studying perpendicular curved and lateral bending vibration damping and comparing Bridge Flutter derivative and influencing, belong to non-constant amplitude simple harmonic quantity forced vibration tests technical field.Inertia force is calculated according to the model quality moments of inertia and vibration acceleration, aerodynamic balance measuring signal is cut inertia force obtains aerodynamic force, i.e., quiet wind-force and self excitation force, and its average is cut acquisition self excitation force.Then according to existing theoretical identification different damping than the Bridge Flutter derivative under the conditions of non-continuous vibration, and then the influence of amplitude and damping ratio to flutter derivatives can be analyzed.This test method realizes that the non-constant amplitude under the conditions of the different damping ratio of bridge main beam Segment Model erects the vibration of curved and lateral bending, can study the influence of damping ratio and amplitude to Bridge Flutter derivative, reliable calculating parameter foundation is provided for bridge charming appearance and behaviour Response Analysis.
Description
Technical field
The invention belongs to it is a kind of can study that perpendicular curved and lateral bending vibration damping compares that Bridge Flutter derivative influences force and shake
Dynamic dynamometer check method, and in particular to the servomotor controlled using special procedure, pass through pitch wheel and tooth plate
Transmission effect driving bridge main beam Segment Model realize that the non-constant amplitude harmonic wave of band damping (diverging decays) forces perpendicular curved or side
Bending vibration is moved, using the synchronously tested model of the force balance of rigid support model by the gentle power signal of inertia force, according to bridge
The inertia force that model (including binary end plate) the quality moments of inertia and vibration acceleration are calculated, cuts model by balance actual measurement power and is used to
Property power, obtains aerodynamic force, then cuts pneumostatic power (i.e. its average value), obtain pneumatic self excitation force, binding model actual vibration
Displacement and speed time-histories, based on correlation theory, identify different damping than the flutter derivatives under the conditions of, non-continuous vibration, from
And the influence of damping ratio and amplitude to Bridge Flutter derivative can be analyzed, the final calculating for bridge wind-induced vibration response is analyzed
Reliable parameter foundation is provided.
Background technology
As bridge develops towards large span and super-span direction so that sensitiveness increase of the bridge structure to wind, pneumatically
Non-linear component increase in self excitation force, especially when the rapid diverging of vibration or decay, bridge main beam surface pressing and surrounding flow
It is different with the result under the conditions of constant amplitude simple harmonic oscillation, therefore Bridge Sections self excitation force and reflect quivering for section self-excitation characteristic
The derivative that shakes can also change correspondingly.For a long time, when identifying flutter derivatives using forced vibration tests method both at home and abroad, without exception
Ground is all based on constant amplitude simple harmonic oscillation, and traditional constant amplitude forced vibration method can not study influence of the damping ratio to flutter derivatives.It is aobvious
So, constant amplitude simple harmonic oscillation is applicable only for a specific flutter critical condition.However, actual Bridge Sections charming appearance and behaviour is erected
Curved, lateral bending and twisting vibration are typically all the non-continuous vibration with damping, it is therefore necessary to propose that a kind of new test method is come
Study influence of the vibration with damping to Bridge Flutter derivative.
The content of the invention
The technical problem to be solved by the present invention is to provide one kind to realize the non-constant amplitude harmonic wave of bridge main beam Segment Model single-degree-of-freedom
Perpendicular curved and lateral bending forced vibration, and then the Bridge Flutter Derivative Characteristics under the conditions of the different perpendicular curved and lateral bending vibration damping ratios of research
Test method.The test method that erecting curved and lateral bending forced vibration with damping simple harmonic quantity influences Bridge Flutter derivative includes：Bridge mould
Type, force balance, rigid strut, binary end plate, guide rail, sliding block, tooth plate, gear, servomotor and base.
Technical scheme：
A kind of dynamometer check method studied perpendicular curved and lateral bending vibration damping and compare the influence of Bridge Flutter derivative, examination used
Experiment device includes bridge model 1, force balance 2, rigid strut 3, binary end plate 4, guide rail 5, sliding block 6, tooth plate 7, gear 8, watches
Take motor 9 and base 10；Bridge model 1 is placed vertically, and is fixedly supported on the force balance 2 in portion disposed within, it is ensured that bridge
1 center of beam model is overlapped with 2 center of force balance；Force balance 2 is fixed on the top of vertical rigid strut 3, rigid strut 3
Bottom be fixedly arranged on tooth plate 7,1 both ends of bridge model configuration binary end plate 4, is monolithically fabricated a rigid support system；Sliding block 6
On guide rail 5, tooth plate 7 is fixed on sliding block 6, and is slided therewith on guide rail 5；Tooth plate 7 is engaged with gear 8, is watched
The non-constant amplitude simple harmonic quantity twisting vibration that motor 9 produces different initial amplitudes and different damping ratio is taken, passes through the biography of gear 7 and tooth plate 8
Action drives bridge model 1 to do synchronous non-constant amplitude simple harmonic quantity and erects the vibration of curved or lateral bending, and perpendicular curved or lateral bending vibration conversion passes through test
System realizes with wind direction relative angle, the torsional displacement of synchronization gain bridge model 1, speed, acceleration and force balance 2
Six square phase signal；Inertia force is calculated according to the quality moments of inertia and vibration acceleration of bridge model 1, the total power measured is cut into inertia
Power obtains aerodynamic force, further cuts pneumostatic power (i.e. aerodynamic force average value) and obtains self excitation force, is then known according to correlation theory
Not Shu the different vibration dampings of curved or lateral bending than the Bridge Flutter derivative under the conditions of, various amplitude.
Beneficial effects of the present invention：The present apparatus can effectively realize bridge main beam Segment Model difference initial amplitude and not
With damping ratio non-constant amplitude vertically and lateral simple harmonic oscillation；Supporting structure ensures enough rigidity, vertical or lateral vibration displacement, speed
Degree and acceleration signal are preferable, moment of torsion, lift and the resistance that balance is surveyed, and can be respectively intended to quivering under identification different condition
Shake derivativeWherein i=1,4,5,6, accuracy of identification is high；It is easy to operate, it is time saving and energy saving.
Brief description of the drawings
Fig. 1 is to realize that curved simple harmonic quantity forced vibration tests schematic device is erected in band damping.
Fig. 2 is to realize band damping lateral bending simple harmonic quantity forced vibration tests schematic device.
In figure：Bridge 1 beam model；2 force balances；3 rigid struts；4 binary end plates；5 guide rails；6 sliding blocks；
7 tooth plates；8 gears；9 servomotors；10 bases.
Embodiment
Describe the embodiment of the present invention in detail below in conjunction with technical solution and attached drawing.
As illustrated in fig. 1 and 2, a kind of dynamometer check studied perpendicular curved and lateral bending vibration damping and compare the influence of Bridge Flutter derivative
Method, its experimental rig include bridge model 1, force balance 2, rigid strut 3, binary end plate 4, guide rail 5, sliding block 6, tooth plate 7,
Gear 8, servomotor 9 and base 10；Bridge model 1 is placed vertically, and is fixedly supported on the force balance 2 in portion disposed within
On, it is ensured that 1 center of bridge model is overlapped with 2 center of force balance；Force balance 2 is fixed on the top of vertical rigid strut 3,
The bottom of rigid strut 3 is fixedly arranged on tooth plate 7, and 1 both ends of bridge model configuration binary end plate 4, is monolithically fabricated a rigid support
System；Sliding block 6 is installed on guide rail 5, and tooth plate 7 is slided by sliding block 6 on guide rail 5；Tooth plate 7 is engaged with gear 8, servo electricity
Machine produces the non-constant amplitude simple harmonic oscillation of different initial amplitudes and different damping ratio, is driven by the gearing of gear 7 and tooth plate 8
Model 1 does synchronous non-constant amplitude harmonic wave and erects curved and lateral bending forced vibration；The torsional displacement of synchronization gain bridge model 1, speed, acceleration
The six square phase signal of degree and force balance 2；Inertia force, the total power that will be measured are calculated according to the model quality moments of inertia and vibration acceleration
Cut inertia force and obtain aerodynamic force, further cut pneumostatic power (i.e. aerodynamic force average value) and obtain self excitation force, then according to phase
The theoretical Bridge Flutter derivative identified under the conditions of different twisting vibration damping ratios is closed, it is specific as follows：
Single-degree-of-freedom is erected under the conditions of bending vibration moves, and self-excitation moment of torsion, lift and the resistance of generation are expressed as：
In formula, MT,FL,FDRespectively self-excitation moment of torsion, from induced lift force and self-excitation resistance；ρ is atmospheric density；U is incoming wind
Speed；B is bridge deck width；H andRespectively vertical displacement and vertical velocity；K=B ω/U are conversion wind speed；ω is that perpendicular bending vibration moves circle
Frequency；For with section configuration, the angle of attack and conversion the relevant flutter derivatives of wind speed K, i=1,4.
The lift directly measured by balance from induced lift force cuts inertia force and pneumostatic power obtains, due in torsion and laterally
There is no acceleration, therefore inertia force is 0, correspondingly, when self-excitation moment of torsion and resistance are the moment of torsion and resistance directly measured by balance
Journey subtracts the acquisition of pneumostatic power；
For self excitation force MTi, FLi, FDiTime-histories and vertical motion displacement and speed time-histories, hi,I=1,2 ... n, formula
(1) it is expressed as：
In formula,
Finally, calculating flutter derivatives with least square method is：
Under the conditions of single-degree-of-freedom lateral vibration, self-excitation moment of torsion, lift and the resistance of generation are expressed as：
In formula, MT,FL,FDRespectively self-excitation moment of torsion, from induced lift force and self-excitation resistance；ρ is atmospheric density；U is incoming wind
Speed；B is bridge deck width；P andRespectively lateral displacement and vertical velocity；K=B ω/U are conversion wind speed；ω justifies for lateral vibration
Frequency；For with section configuration, the angle of attack and conversion the relevant flutter derivatives of wind speed K, i=5,6.
The lift directly measured by balance from induced lift force cuts inertia force and pneumostatic power obtains, due in torsion and laterally
There is no acceleration, therefore inertia force is 0, correspondingly, when self-excitation moment of torsion and resistance are the moment of torsion and resistance directly measured by balance
Journey subtracts the acquisition of pneumostatic power；
For self excitation force MTi, FLi, FDiTime-histories and vertical motion displacement and speed time-histories, pi,I=1,2 ... n, formula
(4) it is expressed as：
In formula,
Finally, calculating flutter derivatives with least square method is：
。
Claims (3)
1. a kind of dynamometer check method studied perpendicular curved and lateral bending vibration damping and compare the influence of Bridge Flutter derivative, its feature exist
In, experimental rig used include bridge model (1), force balance (2), rigid strut (3), binary end plate (4), guide rail (5),
Sliding block (6), tooth plate (7), gear (8), servomotor (9) and base (10)；Bridge model (1) is placed vertically, and fixed support
On the force balance (2) in portion disposed within, it is ensured that bridge model (1) center is overlapped with force balance (2) center；Force balance
(2) top of vertical rigid strut (3) is fixed on, the bottom of rigid strut (3) is fixedly arranged on tooth plate (7), bridge model (1)
Both ends configuration binary end plate (4), is monolithically fabricated a rigid support system；Sliding block (6) is installed on guide rail (5), and tooth plate (7) is solid
It is scheduled on sliding block (6), and is slided therewith on guide rail (5)；Tooth plate (7) is engaged with gear (8), and servomotor (9) produces
The non-constant amplitude simple harmonic quantity twisting vibration of different initial amplitudes and different damping ratio, passes through gear (7) and the gearing band of tooth plate (8)
Dynamic bridge model (1) does synchronous non-constant amplitude simple harmonic quantity and erects the vibration of curved or lateral bending, erect curved or lateral bending vibration conversion by the system of testing with
Wind direction relative angle realizes, the torsional displacement of synchronization gain bridge model (1), speed, the six of acceleration and force balance (2)
Component force signals；Inertia force is calculated according to the quality moments of inertia of bridge model (1) and vibration acceleration, the total power measured is cut into inertia
Power obtains aerodynamic force, further cuts pneumostatic power and obtains self excitation force, then identifies that perpendicular curved or lateral bending is different according to correlation theory
Vibration damping is specific as follows than the Bridge Flutter derivative under the conditions of, various amplitude：
Single-degree-of-freedom is erected under the conditions of bending vibration moves, and self-excitation moment of torsion, lift and the resistance of generation are expressed as：
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Bridge deck width；H andRespectively vertical displacement and vertical velocity；K=B ω/U are conversion wind speed；ω is that perpendicular bending vibration moves circular frequency；For with section configuration, the angle of attack and conversion the relevant flutter derivatives of wind speed K, i=1,4；
The lift directly measured by balance from induced lift force cuts inertia force and pneumostatic power obtains, due to reversing and not having laterally
Acceleration, therefore inertia force is 0, correspondingly, the moment of torsion and resistance time-histories that self-excitation moment of torsion and resistance are directly measured by balance subtract
Pneumostatic power is gone to obtain；
For self excitation force MTi, FLi, FDiTime-histories and vertical motion displacement and speed time-histories, hi,I=1,2 ... n, formula (1) table
It is shown as：
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Finally, calculating flutter derivatives with least square method is：
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<mo>(</mo>
<mn>3</mn>
<mi>c</mi>
<mo>)</mo>
</mrow>
</mrow>
Under the conditions of single-degree-of-freedom lateral vibration, self-excitation moment of torsion, lift and the resistance of generation are expressed as：
<mrow>
<msub>
<mi>M</mi>
<mi>T</mi>
</msub>
<mo>=</mo>
<msup>
<mi>&rho;U</mi>
<mn>2</mn>
</msup>
<msup>
<mi>B</mi>
<mn>2</mn>
</msup>
<mrow>
<mo>(</mo>
<msubsup>
<mi>KA</mi>
<mn>5</mn>
<mo>*</mo>
</msubsup>
<mfrac>
<mover>
<mi>p</mi>
<mo>&CenterDot;</mo>
</mover>
<mi>U</mi>
</mfrac>
<mo>+</mo>
<msup>
<mi>K</mi>
<mn>2</mn>
</msup>
<msubsup>
<mi>A</mi>
<mn>6</mn>
<mo>*</mo>
</msubsup>
<mfrac>
<mi>p</mi>
<mi>B</mi>
</mfrac>
<mo>)</mo>
</mrow>
<mo>-</mo>
<mo>-</mo>
<mo>-</mo>
<mrow>
<mo>(</mo>
<mn>4</mn>
<mi>a</mi>
<mo>)</mo>
</mrow>
</mrow>
<mrow>
<msub>
<mi>F</mi>
<mi>D</mi>
</msub>
<mo>=</mo>
<msup>
<mi>&rho;U</mi>
<mn>2</mn>
</msup>
<mi>B</mi>
<mrow>
<mo>(</mo>
<msubsup>
<mi>KP</mi>
<mn>5</mn>
<mo>*</mo>
</msubsup>
<mfrac>
<mover>
<mi>p</mi>
<mo>&CenterDot;</mo>
</mover>
<mi>U</mi>
</mfrac>
<mo>+</mo>
<msup>
<mi>K</mi>
<mn>2</mn>
</msup>
<msubsup>
<mi>P</mi>
<mn>6</mn>
<mo>*</mo>
</msubsup>
<mfrac>
<mi>p</mi>
<mi>B</mi>
</mfrac>
<mo>)</mo>
</mrow>
<mo>-</mo>
<mo>-</mo>
<mo>-</mo>
<mrow>
<mo>(</mo>
<mn>4</mn>
<mi>b</mi>
<mo>)</mo>
</mrow>
</mrow>
<mrow>
<msub>
<mi>F</mi>
<mi>L</mi>
</msub>
<mo>=</mo>
<msup>
<mi>&rho;U</mi>
<mn>2</mn>
</msup>
<mi>B</mi>
<mrow>
<mo>(</mo>
<msubsup>
<mi>KH</mi>
<mn>5</mn>
<mo>*</mo>
</msubsup>
<mfrac>
<mover>
<mi>p</mi>
<mo>&CenterDot;</mo>
</mover>
<mi>U</mi>
</mfrac>
<mo>+</mo>
<msup>
<mi>K</mi>
<mn>2</mn>
</msup>
<msubsup>
<mi>H</mi>
<mn>6</mn>
<mo>*</mo>
</msubsup>
<mfrac>
<mi>p</mi>
<mi>B</mi>
</mfrac>
<mo>)</mo>
</mrow>
<mo>-</mo>
<mo>-</mo>
<mo>-</mo>
<mrow>
<mo>(</mo>
<mn>4</mn>
<mi>c</mi>
<mo>)</mo>
</mrow>
</mrow>
In formula, MT,FL,FDRespectively self-excitation moment of torsion, from induced lift force and self-excitation resistance；ρ is atmospheric density；U is arrives stream wind speed；B is
Bridge deck width；P andRespectively lateral displacement and vertical velocity；K=B ω/U are conversion wind speed；ω is lateral vibration circular frequency；For with section configuration, the angle of attack and conversion the relevant flutter derivatives of wind speed K, i=5,6；
The lift directly measured by balance from induced lift force cuts inertia force and pneumostatic power obtains, due to reversing and not having laterally
Acceleration, therefore inertia force is 0, correspondingly, the moment of torsion and resistance time-histories that self-excitation moment of torsion and resistance are directly measured by balance subtract
Pneumostatic power is gone to obtain；
For self excitation force MTi, FLi, FDiTime-histories and vertical motion displacement and speed time-histories, pi,I=1,2 ... n, formula (4) table
It is shown as：
<mrow>
<msub>
<mi>M</mi>
<mi>T</mi>
</msub>
<mo>=</mo>
<msup>
<mfenced open = "(" close = ")">
<mtable>
<mtr>
<mtd>
<msub>
<mi>M</mi>
<mrow>
<mi>T</mi>
<mn>1</mn>
</mrow>
</msub>
</mtd>
<mtd>
<msub>
<mi>M</mi>
<mrow>
<mi>T</mi>
<mn>2</mn>
</mrow>
</msub>
</mtd>
<mtd>
<mn>...</mn>
</mtd>
<mtd>
<msub>
<mi>M</mi>
<mrow>
<mi>T</mi>
<mi>n</mi>
</mrow>
</msub>
</mtd>
</mtr>
</mtable>
</mfenced>
<mi>T</mi>
</msup>
<mo>=</mo>
<msub>
<mi>S</mi>
<mi>T</mi>
</msub>
<mfenced open = "(" close = ")">
<mtable>
<mtr>
<mtd>
<msubsup>
<mi>A</mi>
<mn>5</mn>
<mo>*</mo>
</msubsup>
</mtd>
</mtr>
<mtr>
<mtd>
<msubsup>
<mi>A</mi>
<mn>6</mn>
<mo>*</mo>
</msubsup>
</mtd>
</mtr>
</mtable>
</mfenced>
<mo>-</mo>
<mo>-</mo>
<mo>-</mo>
<mrow>
<mo>(</mo>
<mn>5</mn>
<mi>a</mi>
<mo>)</mo>
</mrow>
</mrow>
<mrow>
<msub>
<mi>F</mi>
<mi>L</mi>
</msub>
<mo>=</mo>
<msup>
<mfenced open = "(" close = ")">
<mtable>
<mtr>
<mtd>
<msub>
<mi>F</mi>
<mrow>
<mi>L</mi>
<mn>1</mn>
</mrow>
</msub>
</mtd>
<mtd>
<msub>
<mi>F</mi>
<mrow>
<mi>L</mi>
<mn>2</mn>
</mrow>
</msub>
</mtd>
<mtd>
<mn>...</mn>
</mtd>
<mtd>
<msub>
<mi>F</mi>
<mrow>
<mi>L</mi>
<mi>n</mi>
</mrow>
</msub>
</mtd>
</mtr>
</mtable>
</mfenced>
<mi>T</mi>
</msup>
<mo>=</mo>
<msub>
<mi>S</mi>
<mi>L</mi>
</msub>
<mfenced open = "(" close = ")">
<mtable>
<mtr>
<mtd>
<msubsup>
<mi>H</mi>
<mn>5</mn>
<mo>*</mo>
</msubsup>
</mtd>
</mtr>
<mtr>
<mtd>
<msubsup>
<mi>H</mi>
<mn>6</mn>
<mo>*</mo>
</msubsup>
</mtd>
</mtr>
</mtable>
</mfenced>
<mo>-</mo>
<mo>-</mo>
<mo>-</mo>
<mrow>
<mo>(</mo>
<mn>5</mn>
<mi>b</mi>
<mo>)</mo>
</mrow>
</mrow>
<mrow>
<msub>
<mi>F</mi>
<mi>D</mi>
</msub>
<mo>=</mo>
<msup>
<mfenced open = "(" close = ")">
<mtable>
<mtr>
<mtd>
<msub>
<mi>F</mi>
<mrow>
<mi>D</mi>
<mn>1</mn>
</mrow>
</msub>
</mtd>
<mtd>
<msub>
<mi>F</mi>
<mrow>
<mi>D</mi>
<mn>2</mn>
</mrow>
</msub>
</mtd>
<mtd>
<mn>...</mn>
</mtd>
<mtd>
<msub>
<mi>F</mi>
<mrow>
<mi>D</mi>
<mi>n</mi>
</mrow>
</msub>
</mtd>
</mtr>
</mtable>
</mfenced>
<mi>T</mi>
</msup>
<mo>=</mo>
<msub>
<mi>S</mi>
<mi>D</mi>
</msub>
<mfenced open = "(" close = ")">
<mtable>
<mtr>
<mtd>
<msubsup>
<mi>P</mi>
<mn>5</mn>
<mo>*</mo>
</msubsup>
</mtd>
</mtr>
<mtr>
<mtd>
<msubsup>
<mi>P</mi>
<mn>6</mn>
<mo>*</mo>
</msubsup>
</mtd>
</mtr>
</mtable>
</mfenced>
<mo>-</mo>
<mo>-</mo>
<mo>-</mo>
<mrow>
<mo>(</mo>
<mn>5</mn>
<mi>c</mi>
<mo>)</mo>
</mrow>
</mrow>
In formula,ST=BSL；
Finally, calculating flutter derivatives with least square method is：
<mrow>
<mfenced open = "(" close = ")">
<mtable>
<mtr>
<mtd>
<msubsup>
<mi>A</mi>
<mn>5</mn>
<mo>*</mo>
</msubsup>
</mtd>
</mtr>
<mtr>
<mtd>
<msubsup>
<mi>A</mi>
<mn>6</mn>
<mo>*</mo>
</msubsup>
</mtd>
</mtr>
</mtable>
</mfenced>
<mo>=</mo>
<msup>
<mrow>
<mo>(</mo>
<msubsup>
<mi>S</mi>
<mi>T</mi>
<mi>T</mi>
</msubsup>
<msub>
<mi>S</mi>
<mi>T</mi>
</msub>
<mo>)</mo>
</mrow>
<mrow>
<mo>-</mo>
<mn>1</mn>
</mrow>
</msup>
<msubsup>
<mi>S</mi>
<mi>T</mi>
<mi>T</mi>
</msubsup>
<msub>
<mi>M</mi>
<mi>T</mi>
</msub>
<mo>-</mo>
<mo>-</mo>
<mo>-</mo>
<mrow>
<mo>(</mo>
<mn>6</mn>
<mi>a</mi>
<mo>)</mo>
</mrow>
</mrow>
<mrow>
<mfenced open = "(" close = ")">
<mtable>
<mtr>
<mtd>
<msubsup>
<mi>H</mi>
<mn>5</mn>
<mo>*</mo>
</msubsup>
</mtd>
</mtr>
<mtr>
<mtd>
<msubsup>
<mi>H</mi>
<mn>6</mn>
<mo>*</mo>
</msubsup>
</mtd>
</mtr>
</mtable>
</mfenced>
<mo>=</mo>
<msup>
<mrow>
<mo>(</mo>
<msubsup>
<mi>S</mi>
<mi>L</mi>
<mi>T</mi>
</msubsup>
<msub>
<mi>S</mi>
<mi>L</mi>
</msub>
<mo>)</mo>
</mrow>
<mrow>
<mo>-</mo>
<mn>1</mn>
</mrow>
</msup>
<msubsup>
<mi>S</mi>
<mi>L</mi>
<mi>T</mi>
</msubsup>
<msub>
<mi>F</mi>
<mi>L</mi>
</msub>
<mo>-</mo>
<mo>-</mo>
<mo>-</mo>
<mrow>
<mo>(</mo>
<mn>6</mn>
<mi>b</mi>
<mo>)</mo>
</mrow>
</mrow>
<mrow>
<mfenced open = "(" close = ")">
<mtable>
<mtr>
<mtd>
<msubsup>
<mi>P</mi>
<mn>5</mn>
<mo>*</mo>
</msubsup>
</mtd>
</mtr>
<mtr>
<mtd>
<msubsup>
<mi>P</mi>
<mn>6</mn>
<mo>*</mo>
</msubsup>
</mtd>
</mtr>
</mtable>
</mfenced>
<mo>=</mo>
<msup>
<mrow>
<mo>(</mo>
<msubsup>
<mi>S</mi>
<mi>D</mi>
<mi>T</mi>
</msubsup>
<msub>
<mi>S</mi>
<mi>D</mi>
</msub>
<mo>)</mo>
</mrow>
<mrow>
<mo>-</mo>
<mn>1</mn>
</mrow>
</msup>
<msubsup>
<mi>S</mi>
<mi>D</mi>
<mi>T</mi>
</msubsup>
<msub>
<mi>F</mi>
<mi>D</mi>
</msub>
<mo>-</mo>
<mo>-</mo>
<mo>-</mo>
<mrow>
<mo>(</mo>
<mn>6</mn>
<mi>c</mi>
<mo>)</mo>
</mrow>
<mo>.</mo>
</mrow>
2. dynamometer check method according to claim 1, it is characterised in that the binary end plate (4) and bridge model
(1) gap of 1-2mm is left between, to ensure that air-flow only has binary flowing between models.
3. dynamometer check method according to claim 1, it is characterised in that the gear (8) and tooth plate (7) are according to bridge
The perpendicular curved and lateral bending amplitude requirement of beam model (1), determines gear (8) radius, tooth pitch and tooth plate (7) length.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109682561A (en) * | 2019-02-19 | 2019-04-26 | 大连理工大学 | A kind of automatic detection high-speed railway bridge free vibration responds the method to identify mode |
| CN114370990A (en) * | 2022-01-20 | 2022-04-19 | 重庆大学 | Complex section three-dimensional buffeting force identification method based on double-balance synchronous force measurement technology |
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| CN105302998A (en) * | 2015-11-25 | 2016-02-03 | 东南大学 | Calculation method of flutter time domain of bridge |
| CN106240839A (en) * | 2015-06-04 | 2016-12-21 | 波音公司 | For analyzing the system and method for flutter test data |
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| CN106240839A (en) * | 2015-06-04 | 2016-12-21 | 波音公司 | For analyzing the system and method for flutter test data |
| CN105302998A (en) * | 2015-11-25 | 2016-02-03 | 东南大学 | Calculation method of flutter time domain of bridge |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109682561A (en) * | 2019-02-19 | 2019-04-26 | 大连理工大学 | A kind of automatic detection high-speed railway bridge free vibration responds the method to identify mode |
| CN114370990A (en) * | 2022-01-20 | 2022-04-19 | 重庆大学 | Complex section three-dimensional buffeting force identification method based on double-balance synchronous force measurement technology |
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