CN105043696A - Device for testing rigidity and damping of aircraft engine vibration isolator - Google Patents

Device for testing rigidity and damping of aircraft engine vibration isolator Download PDF

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Publication number
CN105043696A
CN105043696A CN201510350537.5A CN201510350537A CN105043696A CN 105043696 A CN105043696 A CN 105043696A CN 201510350537 A CN201510350537 A CN 201510350537A CN 105043696 A CN105043696 A CN 105043696A
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vibration isolator
vibrator
damping
test
proving installation
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CN201510350537.5A
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吕奇峰
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Xian Aircraft Design and Research Institute of AVIC
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Xian Aircraft Design and Research Institute of AVIC
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  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
  • Testing Of Engines (AREA)

Abstract

The invention relates to the technical field of aero-engine installation system dynamics design and specifically to a device for testing the rigidity and the damping of an aircraft engine vibration isolator. According to the device, a force sensor measures initial exciting force, related to a time course, of a vibration exciter under the effect of a predetermined vibration exciting frequency band; an acceleration sensor measures initial acceleration response, related to the time course, of a mass block under the effect of the predetermined vibration exciting frequency band; a vibration measurer converts the initial exciting force and the initial acceleration response into final exciting force and final acceleration response related to vibration exciting frequency; and the rigidity and the damping of the vibration isolator in the predetermined vibration exciting frequency is computed in virtue of the final exciting force and the final acceleration response. The device is simple in structure and a testing method is simple in steps.

Description

A kind of rigidity of aircraft engine vibration isolator and the proving installation of damping
Technical field
The present invention relates to aeromotor installation system dynamics Design technical field, be specifically related to a kind of rigidity of aircraft engine vibration isolator and the proving installation of damping.
Background technology
Engine is one of main vibration source of aircraft, and it is while providing power for aircraft, also causes the vibration & noise of housing construction.The common method reducing engine luggine level is in mounting structure, use vibration damper (isolation mounting), and the parameter such as rigidity, damping of vibration damper is the important indicator of installation system dynamics Design, the effectiveness in vibration suppression of direct influential system.Therefore, particularly important to the parameter measurement such as damper stiffness, damping, need to design corresponding proving installation and test.
Summary of the invention
The object of this invention is to provide a kind of device for testing rigidity and the damping of aircraft engine vibration isolator.
Technical scheme of the present invention is:
The rigidity of aircraft engine vibration isolator and a proving installation for damping, comprising:
Test base, is fixedly installed on bottom it on supporting surface of level, and described test base has the plate face of level;
Test-bed, is arranged on the upper surface of described test base;
Vibration isolator, is fixed on the top of described test base by described test-bed;
Mass, has a predetermined quality, and top is fixedly attached to bottom described vibration isolator, and is positioned at the vertical below of described vibration isolator;
Vibrator, is fixedly installed on the described supporting surface of the bottom of described test base, and the exciting rod of described vibrator is vertically from the bottom to top through the plate face of described test base, and the top of described exciting rod is fixedly attached to bottom described mass;
Force snesor, is arranged on described exciting rod and described mass junction, for measuring initial excitation power relevant to time history under the effect of described vibrator predetermined excited frequency section;
Acceleration transducer, is fixedly installed on described mass, for measuring the initial acceleration response relevant to time history under the effect of described predetermined excited frequency section of described mass;
Vibration-measuring device, for receiving described initial excitation power and the initial acceleration response of described force snesor and acceleration transducer transmission, and described initial excitation power is changed into the final exciting force relevant to each excited frequency in described predetermined excited frequency section and final acceleration responsive respectively with initial acceleration response;
Processor, calculates rigidity and the damping of described vibration isolator under described predetermined excited frequency for the described final exciting force under the quality according to described mass, a certain predetermined excited frequency and described final acceleration responsive.
Alternatively, described proving installation also comprises:
Adapter coupling, is fixedly installed on described test-bed, and the top of described vibration isolator is fixedly attached to bottom described adapter coupling.
Alternatively, described test-bed is framed structure, the one in its profile side of being selected from body, cylinder or centrum.
Alternatively, described test-bed in cuboid framed structure, its bottom surface level is fixedly installed on the supporting surface of described test base, described adapter coupling is positioned at the inside of described test-bed, and the top of described adapter coupling is fixedly attached to the inside top of the cuboid framework of described test-bed.
Alternatively, the top of described vibration isolator has hanger, and described vibration isolator is fixedly attached to bottom described adapter coupling by described hanger.
Alternatively, described vibration isolator comprises the inner housing of arranged stacked from the inside to the outside, damping material layers and shell body, the bottom of described inner housing has a jut, run through described damping material layers and shell body successively, described vibration isolator is fixedly connected with by the top of described jut with described mass.
Alternatively, described proving installation also comprises:
Vibrator pedestal, is arranged between described vibrator and described supporting surface, and described vibrator is fixedly installed on described supporting surface by described vibrator base level.
Alternatively, described predetermined excited frequency section comprises minimum frequency and maximum frequency, and described vibrator is used in described time history, control excited frequency and progressively increases to described maximum frequency by described minimum frequency.
Beneficial effect of the present invention:
The proving installation of aircraft engine vibration isolator rigidity of the present invention and damping, by the initial excitation power that force sensor measuring is relevant to time history under the effect of described vibrator predetermined excited frequency section, the initial acceleration response relevant to time history under the effect of described predetermined excited frequency section of described mass is measured by acceleration transducer, by vibration-measuring device, initial excitation power is changed into the final exciting force relevant to excited frequency and final acceleration responsive with initial acceleration response again, rigidity and the damping of vibration isolator under this predetermined excited frequency is calculated finally by final exciting force and final acceleration responsive, proving installation structure is simple, method of testing step is simple.
Accompanying drawing explanation
Fig. 1 is the structural representation of the proving installation of aircraft engine vibration isolator rigidity of the present invention and damping;
Fig. 2 be in proving installation of the present invention vibration isolator be connected with adapter coupling and mass after cut-open view.
Embodiment
Here will be described exemplary embodiment in detail, its sample table shows in the accompanying drawings.When description below relates to accompanying drawing, unless otherwise indicated, the same numbers in different accompanying drawing represents same or analogous key element.
As depicted in figs. 1 and 2, the rigidity of aircraft engine vibration isolator provided by the invention and the proving installation of damping, comprise test base 1, test-bed 5, vibration isolator 3, mass 2, vibrator 8, force snesor 7, acceleration transducer 6, vibration-measuring device and processor.
Test base 1 can be multiple applicable framed structure, and the one in its profile side of being selected from body, cylinder or centrum, is fixedly installed on bottom it on supporting surface of level, and supporting surface can be ground or other supporting surfaces, and test base 1 has the plate face of level.In the present embodiment, test base 1 is cuboid framed structure
Test-bed 5 can be multiple applicable framed structure equally, and the one in its profile side of being selected from body, cylinder or centrum, is arranged on the upper surface of test base 1.In the present embodiment, test-bed 5 in cuboid framed structure, its bottom surface level is fixedly installed on the supporting surface of test base 1, and adapter coupling 4 is positioned at the inside of test-bed 5, and the top of adapter coupling 4 is fixedly attached to the inside top of the cuboid framework of test-bed 5.
Vibration isolator 3 is the one of the known aircraft engine vibration isolator needing test, is fixed on the top of test base 1 by test-bed 5.Particularly, vibration isolator 3 can comprise the inner housing 32 of arranged stacked from the inside to the outside, damping material layers 33 and shell body 34; Have a jut 35 in the bottom of inner housing 32, run through damping material layers 33 and shell body 34 successively, final vibration isolator 3 is fixedly connected with by the top of jut 35 with mass 2.
Further, all right adapter coupling 4 of proving installation of the present invention, be fixedly installed on test-bed 5, the top of vibration isolator 3 is fixedly attached to bottom adapter coupling 4.Particularly, can also have one or more hanger 21 at the top of vibration isolator 3, vibration isolator 3 is fixedly attached to bottom adapter coupling 4 by hanger 31.
Mass 2 has a predetermined quality (the aircraft engine quality simulated as required and determine), and top is fixedly attached to bottom vibration isolator 3, and is positioned at the vertical below of vibration isolator 3.
Vibrator 8 can be selected from the one in known multiple vibrator; Vibrator 8 is fixedly installed on the supporting surface of the bottom of test base 1, and the exciting rod of vibrator 8 is vertically from the bottom to top through the plate face of test base 1, and the top of exciting rod is fixedly attached to bottom mass 2.Further, can also arrange vibrator pedestal 9 between vibrator 8 and bottom support face, vibrator pedestal 9 can adopt multiple applicable planform, to strengthen the stability of installing; Vibrator 8 is fixedly installed on bottom support face by vibrator pedestal 9 level.
Force snesor 7 can adopt multiple applicable force snesor, is arranged on exciting rod and mass 2 junction, for measuring initial excitation power relevant to time history under the effect of vibrator 3 predetermined excited frequency section.Wherein, predetermined excited frequency section comprises minimum frequency and does large frequency, and in increasing progressively relation, such as predetermined excited frequency section can be 5-2000Hz, and wherein minimum is 5hz, is 2000hz to the maximum; Time history refers to vibrator 8 and becomes greatly from 5hz that (size of each change can regulate as required gradually, such as change 0.1hz or 1hz per second etc.) to the time required during 2000hz, this process is frequency sweep again, and wherein time history can set as required.
Acceleration transducer 6 can adopt multiple applicable acceleration transducer, is fixedly installed on mass 2, for the initial acceleration response that measurement quality block 2 is relevant to time history under the effect of above-mentioned predetermined excited frequency section.
Vibration-measuring device is measuring appliance known at present or measuring system, be mainly used in the initial excitation power and the initial acceleration response that receive above-mentioned force snesor 7 and acceleration transducer 6 transmission, and initial excitation power is changed into the final exciting force relevant to each excited frequency in predetermined excited frequency section and final acceleration responsive with initial acceleration response respectively by fast Fourier transform (FFT) method.
Device parts time processor can be multiple, such as, be directly chosen as a computing machine, and related data can automatic input or manual typing, is calculated by corresponding program.Rigidity and the damping of vibration isolator 3 under predetermined excited frequency is calculated for the final exciting force under the quality according to mass 2, a certain predetermined excited frequency and final acceleration responsive.
The proving installation of aircraft engine vibration isolator rigidity of the present invention and damping, by responding transform measuring the initial excitation power relevant to time history that obtains and initial acceleration, obtain and the final exciting force of frequency dependence and final acceleration responsive, last rigidity and the damping being calculated vibration isolator under this predetermined excited frequency again by final exciting force and final acceleration responsive, proving installation structure is simple, method of testing step is simple, under the condition of short form test equipment, can the rigidity of Measurement accuracy aircraft engine isolation mounting and frequency dependence and damping.
Further, in the rigidity of aircraft engine vibration isolator of the present invention and the proving installation of damping, vibrator 8 is for the applying realizing whole predetermined excited frequency section complete in above-mentioned time history.Initial acceleration response measured by the initial excitation power that force snesor 7 is measured and acceleration transducer 6 is all one group data corresponding with time history.Initial excitation power is changed into the final exciting force relevant to each excited frequency in predetermined excited frequency section and final acceleration responsive with initial acceleration response by fast Fourier transform method by vibration-measuring device respectively.Final exciting force now and final acceleration responsive are the one group data corresponding with excited frequencies all in predetermined excited frequency section.
Processor is according to the final exciting force F (ω) under the mass M of mass 2 of input, a certain predetermined excited frequency (in predetermined excited frequency section) and final acceleration responsive and the stiffness K of vibration isolator 3 and damping C calculate predetermined excited frequency as follows successively with formula under:
Step 4.1, definition T ( ω ) = x ·· ( ω ) F ( ω ) - - - ( I )
Wherein, ω is circular frequency, and ω=2 π f, f are described predetermined excited frequency;
Step 4.2, according to kinetics equation definition Complex modes:
k(ω)＝K(ω)+iC(ω)ω(Ⅱ)
Wherein, i is imaginary unit;
K with C in step 4.3, formula II is the real number relevant to frequencies omega, then obtain finally obtaining vibration isolator Complex modes formula is
k ( ω ) = ( M - 1 T ( ω ) ) ω 2 - - - ( I I I )
Step 4.4 is by the mass M of described mass 2, described predetermined excited frequency value f, described final exciting force F (ω) and described final acceleration responsive substitute into described formula I and formula III obtains vibration isolator Complex modes k (ω), then obtain stiffness K and the damping C of vibration isolator 3 under described predetermined excited frequency according to formula II.
It should be noted that, according to above-mentioned formula except the stiffness K that can obtain vibration isolator 3 under a predetermined excited frequency and damping C, stiffness K and the damping C of the vibration isolator 3 under all excited frequencies of predetermined excited frequency section can also be obtained.Therefore, the method for testing of the proving installation of aircraft engine vibration isolator rigidity of the present invention and damping can not only record aircraft engine vibration isolator in the rigidity of resonant frequency point and damping, can also reflect that vibration isolator rigidity, damping are with the variable quantity of frequency.
Further, with the citing of certain test figure 33.4Hz Frequency point data, the computation process of vibration isolator rigidity and damping is described in detail.
Mass M=the 44.7kg of mass 2, the data of sensor collection are exciting force and the acceleration responsive of time history, need to carry out fast Fourier transform (FFT) to it, the exciting force F (ω) under different frequency and acceleration responsive can be obtained
According to the circular frequency ω=2 π f=2 π × 33.4=209.7520rad/s of the known 33.4Hz of relation ω=2 π f of circular frequency ω and angular frequency f, get exciting force F (209.7520) and acceleration responsive that 33.4Hz goes out be respectively: with (data are from vibration-measuring device 6); I is imaginary unit.
Thus according to obtain:
Basis again k ( ω ) = ( M - 1 T ( ω ) ) ω 2 Obtain:
k ( 209.7520 ) = ( 44.7 - 1 - 0.0404 + 0.0047 i ) ( 209.7520 ) 2 = 3.0412 e + 006 + 1.2606 e + 005 i ;
Then at 33.4Hz Frequency point, the stiffness K=3.0412e+006N/m of this vibration isolator;
Obtain according to k (ω)=K (ω)+iC (ω) ω again: 209.7520 × C=1.2606e+005, finally obtains damping C = 1.2606 e + 005 209.7520 = 600.9955 N · ( m / S ) .
The above; be only the specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of described claim.

Claims (8)

1. the rigidity of aircraft engine vibration isolator and a proving installation for damping, is characterized in that, comprising:
Test base (1), is fixedly installed on bottom it on supporting surface of level, and described test base (1) has the plate face of level;
Test-bed (5), is arranged on the upper surface of described test base (1);
Vibration isolator (3), is fixed on the top of described test base (1) by described test-bed (5);
Mass (2), has a predetermined quality, and top is fixedly attached to described vibration isolator (3) bottom, and is positioned at the vertical below of described vibration isolator (3);
Vibrator (8), be fixedly installed on the described supporting surface of the bottom of described test base (1), the exciting rod of described vibrator (8) is vertically from the bottom to top through the plate face of described test base (1), and the top of described exciting rod is fixedly attached to described mass (2) bottom;
Force snesor (7), is arranged on described exciting rod and described mass (2) junction, for measuring initial excitation power relevant to time history under the effect of described vibrator (8) predetermined excited frequency section;
Acceleration transducer (6), is fixedly installed on described mass (2), for measuring described mass (2) initial acceleration response relevant to time history under the effect of described predetermined excited frequency section;
Vibration-measuring device, for receiving the described initial excitation power and initial acceleration response that described force snesor (7) and acceleration transducer (6) transmit, and described initial excitation power is changed into the final exciting force relevant to each excited frequency in described predetermined excited frequency section and final acceleration responsive respectively with initial acceleration response;
Processor, calculates rigidity and the damping of described vibration isolator (3) under described predetermined excited frequency for the described final exciting force under the quality according to described mass (2), a certain predetermined excited frequency and described final acceleration responsive.
2. proving installation according to claim 1, is characterized in that, also comprises:
Adapter coupling (4), is fixedly installed on described test-bed (5), and the top of described vibration isolator (3) is fixedly attached to described adapter coupling (4) bottom.
3. proving installation according to claim 1 and 2, is characterized in that, described test-bed (5) in framed structure, the one in its profile side of being selected from body, cylinder or centrum.
4. proving installation according to claim 3, it is characterized in that, described test-bed (5) in cuboid framed structure, its bottom surface level is fixedly installed on the supporting surface of described test base (1), described adapter coupling (4) is positioned at the inside of described test-bed (5), and the top of described adapter coupling (4) is fixedly attached to the inside top of the cuboid framework of described test-bed (5).
5. proving installation according to claim 2, it is characterized in that, the top of described vibration isolator (3) has hanger (31), and described vibration isolator (3) is fixedly attached to described adapter coupling (4) bottom by described hanger (31).
6. proving installation according to claim 2, it is characterized in that, described vibration isolator (3) comprises the inner housing (32) of arranged stacked from the inside to the outside, damping material layers (33) and shell body (34), the bottom of described inner housing (32) has a jut (35), run through described damping material layers (33) and shell body (34) successively, described vibration isolator (3) is fixedly connected with by the top of described jut (35) with described mass (2).
7. proving installation according to claim 1, is characterized in that, also comprises:
Vibrator pedestal (9), is arranged between described vibrator (8) and described supporting surface, and described vibrator (8) is fixedly installed on described supporting surface by described vibrator pedestal (9) level.
8. proving installation according to claim 1, it is characterized in that, described predetermined excited frequency section comprises minimum frequency and maximum frequency, and described vibrator (8) progressively increases to described maximum frequency for controlling excited frequency in described time history by described minimum frequency.
CN201510350537.5A 2015-06-23 2015-06-23 Device for testing rigidity and damping of aircraft engine vibration isolator Pending CN105043696A (en)

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Cited By (5)

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Publication number Priority date Publication date Assignee Title
CN105716973A (en) * 2016-04-14 2016-06-29 吉林大学 Vibration test device and method of vibration-absorbing material
CN106017833A (en) * 2016-05-13 2016-10-12 北京空间飞行器总体设计部 High-damping micro-amplitude vibration isolator performance test method
CN110375940A (en) * 2019-08-16 2019-10-25 西北工业大学 A kind of low frequency vibration isolation testboard and vibration detecting system
CN110470380A (en) * 2019-04-13 2019-11-19 西北工业大学 A kind of vibration isolator mechanical impedance test method for considering pedestal and influencing
CN112556957A (en) * 2020-12-04 2021-03-26 中国直升机设计研究所 Transmission characteristic test device for liquid elastic vibration isolation system

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105716973A (en) * 2016-04-14 2016-06-29 吉林大学 Vibration test device and method of vibration-absorbing material
CN106017833A (en) * 2016-05-13 2016-10-12 北京空间飞行器总体设计部 High-damping micro-amplitude vibration isolator performance test method
CN106017833B (en) * 2016-05-13 2018-07-31 北京空间飞行器总体设计部 A kind of performance test methods of high-damping micro-vibration isolation device
CN110470380A (en) * 2019-04-13 2019-11-19 西北工业大学 A kind of vibration isolator mechanical impedance test method for considering pedestal and influencing
CN110375940A (en) * 2019-08-16 2019-10-25 西北工业大学 A kind of low frequency vibration isolation testboard and vibration detecting system
CN112556957A (en) * 2020-12-04 2021-03-26 中国直升机设计研究所 Transmission characteristic test device for liquid elastic vibration isolation system

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