CN103017891A - Noise testing method under heat noise combination environment - Google Patents
Noise testing method under heat noise combination environment Download PDFInfo
- Publication number
- CN103017891A CN103017891A CN201210531682XA CN201210531682A CN103017891A CN 103017891 A CN103017891 A CN 103017891A CN 201210531682X A CN201210531682X A CN 201210531682XA CN 201210531682 A CN201210531682 A CN 201210531682A CN 103017891 A CN103017891 A CN 103017891A
- Authority
- CN
- China
- Prior art keywords
- travelling
- temperature
- positions
- wave tube
- probe
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Landscapes
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
Abstract
The invention belongs to the field of aviation strength tests and particularly relates to a noise testing method under heat noise combination environment. The noise testing method includes a test preparation step, a probe microphone frequency response modification step and a probe sensor position modification step. The testing method is used in strong noise high temperature combination environment with noise as 165 dB and temperature as 1000 DEG C. Noise sound pressure value can be obtained under the heat noise combination loading environment. Compared with a heat insulation box method, environment temperature for measuring sound pressure is improved, and measurement accuracy is improved. The method can be applied to the fields of aviation and aerospace. Devices adopted in the method are simple and reliable in structure. An adopted calculation method is small in calculation quantity and capable of being well applied to tests under heat noise combination environment. The method provides a reliable measurement way for heat noise tests.
Description
Technical field
The invention belongs to aviation strength test field, particularly relate to noise testing method under a kind of thermonoise federated environment.
Background technology
Along with the development of space shuttle and High Speed Civil aircraft, the environmental baseline that aircraft is carried out aerial mission is more complicated and changeable, and aeroplane structure design faces huge challenge.Influence factor mainly comprises propulsion system noise, boundary layer noise, boundary layer aerothermal load, local vibration etc.Structure dynamic response and dynamic fatigue that these adverse factors cause are difficult to calculate, need to verify the reliability of design by demonstration test.Combined simulation for vibration, high very noisy, thermal environment load can be realized by the progressive wave test device.
High very noisy, thermal environment Combined Trials can be called for short the thermonoise test.Along with the increase of thermonoise test demand, the test capability of the existing travelling-wave tube in laboratory has obtained expansion.After the progressive wave test capacity expansion, its maximum operating temperature need to measure and guide sound load under hot environment, and laboratory existing noise measurement sensor maximum operating temperature only has 700 ℃ about 1000 ℃.Thereby need oneself to develop the measurement mechanism of replacement.
Summary of the invention
Goal of the invention: noise testing method under a kind of thermonoise federated environment is provided, and the apparatus structure that this method adopts is simple and reliable, calculated amount is less, can be applied to preferably the test under the thermonoise federated environment.
Technical scheme: noise testing method under a kind of thermonoise federated environment, also namely the acoustic pressure in the travelling-wave tube 7 is measured, may further comprise the steps:
The step of step 2, test: directly measure the acoustic pressure of travelling-wave tube in the time of below 700 ℃ with 4128 probe microphones, its formula is as follows:
P=P
L+P
H+P
T（1）
Wherein:
P is the travelling-wave tube sound pressure level
P
LBe travelling-wave tube stage casing probe microphone measurement result
P
HBe probe microphone frequency response correction
P
TBe the correction of probe microphone temperature
The probe microphone at travelling-wave tube middle part can not continue to use in the time of more than 700 ℃, only has the sound pressure level at the measurement result estimation travelling-wave tube middle part of the probe microphone by front and rear, and its formula is as follows:
P
G=P
GL+P
GH+P
GT+P
GP（2）
Wherein:
P
GBe the test section sound pressure level
P
GLFor cold-zone probe microphone measurement result average
P
GHBe probe microphone frequency response correction
P
GTBe the correction of probe microphone temperature
P
GPBe the probe microphone position correction
P
GTValue is provided by microphone producer; For obtaining P
GHAnd P
GPValue need to be done the specific determination test step, and is suddenly as follows:
Step 2.1:P
GHMeasure
Use 5,6 positions, all the other positions block with plug;
2.1.1: arrange respectively the 2510M4A microphone in 5,6 positions, measurement result is designated as Mic5, Mic6, loads sound field by test spectrum shape and magnitude, measures the each point sound pressure level;
2.1.2:Mic5 be arranged in 6 positions, Mic6 is arranged in 5 positions, measurement result is designated as Mic5-6, Mic6-5, loads sound field by test spectrum shape and magnitude, measures the each point sound pressure level;
2.1.3:Mic6 install back the origin-location, measurement result is designated as Mic6p, probe microphone is installed in 5 positions, and measurement result is designated as Mic5p, loads sound field by test magnitude and spectrum shape, makes a little 6 position temperature stabilizations at 100 ℃, measurement each point sound pressure level; Then obtain:
P
GH=Mic6p－Mic5p+(Mic6－Mic5+Mic6-5－Mic5-6)/2（3）
Step 2.2:P
GpMeasure
2.2.1: at 1,3,5 location arrangements probe microphones, measurement result is designated as respectively Mic1p, Mic3p, Mic5p, all the other positions block with plug, add air-flow, make loudspeaker reach supply gas pressure, open the heating lamp box, temperature gradually raises, monitor the temperature of 3 positions, 6 positions, guarantee that 3 position temperature can not be above 600 ℃;
2.2.2: take the temperature of 3 positions as reference temperature, under following temperature, measure respectively: 100 ℃, 200 ℃, 300 ℃, 400 ℃, 500 ℃, 600 ℃; Load sound field by test spectrum shape and magnitude, record acoustic pressure and the temperature of each position, each measurement result is revised according to formula (1), then the P under certain temperature
GpFor:
P
Gp=Mic3p－(Mic1p+Mic5p)/2（4）
2.2.3: to the P under the different temperatures
GpDo linear fit, be extrapolated to 1000 ℃, obtain the P under 1000 ℃
GpValue.
Beneficial effect: the present invention be at noise up to 165dB, temperature up to the method for testing under the high temperature combined loading environment of 1000 ℃ very noisy, can obtain the heat noise sound pressure level under the combination loading environment of making an uproar.Existing method adopts the heat insulation box method to research and develop high-temperature test device, can be 650 ℃ of lower acoustic pressures of measuring.The present invention and heat insulation box method compare, and the environment temperature of measuring acoustic pressure is improved, and measuring accuracy also improves.The present invention not only can be applicable to aviation field, also can be applicable to space industry.For example: engine nozzle, space shuttle thermal protection system, deliver fiery tank, all need to test under the thermonoise federated environment, this measuring technology just can be applied.The apparatus structure that this method of testing adopts computing method calculated amount simple and reliable, that adopt is less, can be applied to preferably the test under the thermonoise federated environment, for the thermonoise test provides reliable measurement means.
Description of drawings
Fig. 1 is that the present invention tests set-up procedure probe microphone layout schematic diagram.
Embodiment
Below in conjunction with accompanying drawing the present invention is done to describe in further detail, see also Fig. 1.Noise testing method under a kind of thermonoise federated environment is also namely measured the acoustic pressure in the travelling-wave tube 7, may further comprise the steps:
The step of step 2, test: directly measure the acoustic pressure of travelling-wave tube in the time of below 700 ℃ with 4128 probe microphones, its formula is as follows:
P=P
L+P
H+P
T（1）
Wherein:
P is the travelling-wave tube sound pressure level
P
LBe travelling-wave tube stage casing probe microphone measurement result
P
HBe probe microphone frequency response correction
P
TBe the correction of probe microphone temperature
The probe microphone at travelling-wave tube middle part can not continue to use in the time of more than 700 ℃, only has the sound pressure level at the measurement result estimation travelling-wave tube middle part of the probe microphone by front and rear, and its formula is as follows:
P
G=P
GL+P
GH+P
GT+P
GP（2）
Wherein:
P
GBe the test section sound pressure level
P
GLFor cold-zone probe microphone measurement result average
P
GHBe probe microphone frequency response correction
P
GTBe the correction of probe microphone temperature
P
GPBe the probe microphone position correction
P
GTValue is provided by microphone producer; For obtaining P
GHAnd P
GPValue need to be done the specific determination test step, and is suddenly as follows:
Step 2.1:P
GHMeasure
Use 5,6 positions, all the other positions block with plug;
2.1.1: arrange respectively the 2510M4A microphone in 5,6 positions, measurement result is designated as Mic5, Mic6, loads sound field by test spectrum shape and magnitude, measures the each point sound pressure level;
2.1.2:Mic5 be arranged in 6 positions, Mic6 is arranged in 5 positions, measurement result is designated as Mic5-6, Mic6-5, loads sound field by test spectrum shape and magnitude, measures the each point sound pressure level;
2.1.3:Mic6 install back the origin-location, measurement result is designated as Mic6p, probe microphone is installed in 5 positions, and measurement result is designated as Mic5p, loads sound field by test magnitude and spectrum shape, makes a little 6 position temperature stabilizations at 100 ℃, measurement each point sound pressure level; Then obtain:
P
GH=Mic6p－Mic5p+(Mic6－Mic5+Mic6-5－Mic5-6)/2（3）
Step 2.2:P
GpMeasure
2.2.1: at 1,3,5 location arrangements probe microphones, measurement result is designated as respectively Mic1p, Mic3p, Mic5p, all the other positions block with plug, add air-flow, make loudspeaker reach supply gas pressure, open the heating lamp box, temperature gradually raises, monitor the temperature of 3 positions, 6 positions, guarantee that 3 position temperature can not be above 600 ℃;
2.2.2: take the temperature of 3 positions as reference temperature, under following temperature, measure respectively: 100 ℃, 200 ℃, 300 ℃, 400 ℃, 500 ℃, 600 ℃; Load sound field by test spectrum shape and magnitude, record acoustic pressure and the temperature of each position, each measurement result is revised according to formula (1), then the P under certain temperature
GpFor:
P
Gp=Mic3p－(Mic1p+Mic5p)/2（4）
2.2.3: to the P under the different temperatures
GpDo linear fit, be extrapolated to 1000 ℃, obtain the P under 1000 ℃
GpValue.
The inventive method problem to be solved is, under 1000 ℃ of conditions how to travelling-wave tube in acoustic pressure measure.Existing microphone probe is the highest can only to tolerate 700 ℃, how to improve the upper temperature limit of microphone work? 1,5 position (see photo) temperature of travelling-wave tube are lower, available microphone is directly measured acoustic pressure, can not directly measure acoustic pressure with microphone and 3 position temperature are high.If can find the relation of 3 position acoustic pressures and 1,5 position acoustic pressures (is the P that preamble is mentioned
GP), and obtain that this concerns P below 700 ℃
GPTemperature variant rule is extrapolated to 1000 ℃, just can calculate 3 acoustic pressure by 1,5 sound pressure meters.It more than is the content of mentioning in the step 2.2.Content in the step 2.1 is to measure P in addition
GH, be exactly the frequency response of measuring probe microphone in fact, because the frequency response of probe microphone generally need to be revised.Step 1 is prepared for test is front.
Example: below by example, the present invention is described in further details.Acoustic pressure in the example represents with the third-octave form.The acoustic pressure occurrence is referenced as 20 μ Pa with decibel (dB) expression.
Step 1: for testing front preparation, installation gets final product on request
Step 2: the front is definition and the explanation of formula
Step 2.1P
GHMeasure.Test in 155dB, carry out during 100 ℃ of 6 positions.Detailed test figure and the results are shown in following table 1.
Table 1
Step 2.2P
GPMeasure.Test is carried out under 700 ℃, 500 ℃, 300 ℃ conditions of 3 position temperature respectively at 1 position acoustic pressure 155dB.Detailed test figure and the results are shown in following table 2-table 4.
Test findings during table 2300 ℃.
Test findings during table 3500 ℃.
Test findings during table 4700 ℃.
To the P under the different temperatures
GPCarry out linear fit.Under 300 ℃, 500 ℃, 700 ℃, measured P
GP, be designated as respectively: P
GP-300, P
GP-500, P
GP-700P under 1000 ℃ of the fitting results
GPBe designated as: P
GP-1000The detailed fit data see the following form 5.
Table 5
| Frequency (Hz) | P GP-300(dB) | P GP-500(dB) | P GP-700(dB) | P GP-1000(dB) |
| 31.5 | -5.3 | -6.9 | -10.7 | -15.1 |
| 40 | -4.6 | -8.9 | -12.1 | -15.0 |
| 50 | -6.6 | -10.8 | -12.8 | -17.8 |
| 63 | -8.4 | -12.6 | -15.2 | -20.6 |
| 80 | -5.9 | -13.4 | -16.3 | -24.9 |
| 100 | -1.8 | -17.1 | -20.2 | -36.0 |
| 125 | -4.8 | -20.1 | -22.1 | -37.2 |
| 160 | -10.4 | -20.2 | -22.6 | -28.0 |
| 200 | -14.0 | -16.4 | -19.2 | -23.0 |
| 250 | -15.6 | -16.4 | -18.7 | -20.8 |
| 315 | -12.9 | -23.5 | -26.3 | -37.8 |
| 400 | -16.9 | -21.2 | -22.1 | -26.6 |
| 500 | -18.9 | -21.9 | -22.9 | -26.2 |
| 630 | -19.4 | -23.2 | -23.9 | -27.8 |
| 800 | -17.0 | -24.8 | -25.1 | -32.4 |
| 1000 | 0.8 | -2.8 | -26.2 | -37.0 |
| 1250 | -2.4 | -2.0 | -2.0 | -1.6 |
| 1600 | 0.1 | 0.6 | 0.8 | 1.3 |
| 2000 | -0.6 | 0.1 | 0.1 | 0.8 |
| 2500 | -0.3 | 3.3 | 3.1 | 6.3 |
| 3150 | -0.6 | 1.0 | 1.7 | 3.6 |
| 4000 | -0.4 | -1.9 | -1.7 | -3.0 |
| 5000 | -1.0 | 1.0 | 0.7 | 2.4 |
| 6300 | -0.5 | 1.3 | 1.0 | 2.5 |
| 8000 | -0.8 | 0.5 | 0.0 | 0.9 |
| 10000 | -0.9 | 1.5 | 0.9 | 2.8 |
So far measured the position correction amount P when temperature is 1000 ℃
GPBe 155dB for 1 position acoustic pressure, when the temperature of 3 positions was 1000 ℃, the sound pressure level of 3 positions can be by acoustic pressure and the position correction amount P of 1,5 positions
GPEstimate.
The present invention be at noise up to 165dB, temperature up to the method for testing under the high temperature combined loading environment of 1000 ℃ very noisy, can obtain the heat noise sound pressure level under the combination loading environment of making an uproar.Existing method adopts the heat insulation box method to research and develop high-temperature test device, can be 650 ℃ of lower acoustic pressures of measuring.The present invention and heat insulation box method compare, and the environment temperature of measuring acoustic pressure is improved, and measuring accuracy also improves.The present invention not only can be applicable to aviation field, also can be applicable to space industry.For example: engine nozzle, space shuttle thermal protection system, deliver fiery tank, all need to test under the thermonoise federated environment, this measuring technology just can be applied.The apparatus structure that this method of testing adopts computing method calculated amount simple and reliable, that adopt is less, can be applied to preferably the test under the thermonoise federated environment, for the thermonoise test provides reliable measurement means.
Claims (1)
1. noise testing method under the thermonoise federated environment is also namely measured the acoustic pressures in the travelling-wave tube 7, it is characterized in that, may further comprise the steps:
Step 1, test are prepared: at travelling-wave tube leading portion, stage casing and back segment, each installs a plurality of Denmark B﹠amp; 4182 probe microphones that K company produces, former and later two microphones are in low-temperature space, also be 1,5 positions of travelling-wave tube, at two 4182 probe microphones of the anterior layout of travelling-wave tube, also be 5,6 positions of travelling-wave tube, arranging three 4182 probe microphones at the travelling-wave tube middle part, also is 2,3,4 positions of travelling-wave tube, arranges 4182 probe microphones at the rear portion of travelling-wave tube; It also is 1 position of travelling-wave tube;
The step of step 2, test: directly measure the acoustic pressure of travelling-wave tube in the time of below 700 ℃ with 4128 probe microphones, its formula is as follows:
P=P
L+P
H+P
T（1）
Wherein:
P is the travelling-wave tube sound pressure level
P
LBe travelling-wave tube stage casing probe microphone measurement result
P
HBe probe microphone frequency response correction
P
TBe the correction of probe microphone temperature
The probe microphone at travelling-wave tube middle part can not continue to use in the time of more than 700 ℃, only has the sound pressure level at the measurement result estimation travelling-wave tube middle part of the probe microphone by front and rear, and its formula is as follows:
P
G=P
GL+P
GH+P
GT+P
GP（2）
Wherein:
P
GBe the test section sound pressure level
P
GLFor cold-zone probe microphone measurement result average
P
GHBe probe microphone frequency response correction
P
GTBe the correction of probe microphone temperature
P
GPBe the probe microphone position correction
P
GTValue is provided by microphone producer; For obtaining P
GHAnd P
GPValue need to be done the specific determination test step, and is suddenly as follows:
Step 2.1:P
GHMeasure
Use 5,6 positions, all the other positions block with plug;
2.1.1: arrange respectively the 2510M4A microphone in 5,6 positions, measurement result is designated as Mic5, Mic6, loads sound field by test spectrum shape and magnitude, measures the each point sound pressure level;
2.1.2:Mic5 be arranged in 6 positions, Mic6 is arranged in 5 positions, measurement result is designated as Mic5-6, Mic6-5, loads sound field by test spectrum shape and magnitude, measures the each point sound pressure level;
2.1.3:Mic6 install back the origin-location, measurement result is designated as Mic6p, probe microphone is installed in 5 positions, and measurement result is designated as Mic5p, loads sound field by test magnitude and spectrum shape, makes a little 6 position temperature stabilizations at 100 ℃, measurement each point sound pressure level; Then obtain:
P
GH=Mic6p－Mic5p+(Mic6－Mic5+Mic6-5－Mic5-6)/2（3）
Step 2.2:P
GpMeasure
2.2.1: at 1,3,5 location arrangements probe microphones, measurement result is designated as respectively Mic1p, Mic3p, Mic5p, all the other positions block with plug, add air-flow, make loudspeaker reach supply gas pressure, open the heating lamp box, temperature gradually raises, monitor the temperature of 3 positions, 6 positions, guarantee that 3 position temperature can not be above 600 ℃;
2.2.2: take the temperature of 3 positions as reference temperature, under following temperature, measure respectively: 100 ℃, 200 ℃, 300 ℃, 400 ℃, 500 ℃, 600 ℃; Load sound field by test spectrum shape and magnitude, record acoustic pressure and the temperature of each position, each measurement result is revised according to formula (1), then the P under certain temperature
GpFor:
P
Gp=Mic3p－(Mic1p+Mic5p)/2（4）
2.2.3: to the P under the different temperatures
GpDo linear fit, be extrapolated to 1000 ℃, obtain the P under 1000 ℃
GpValue.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210531682.XA CN103017891B (en) | 2012-12-11 | 2012-12-11 | Noise testing method under heat noise combination environment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210531682.XA CN103017891B (en) | 2012-12-11 | 2012-12-11 | Noise testing method under heat noise combination environment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103017891A true CN103017891A (en) | 2013-04-03 |
| CN103017891B CN103017891B (en) | 2014-10-22 |
Family
ID=47966753
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210531682.XA Active CN103017891B (en) | 2012-12-11 | 2012-12-11 | Noise testing method under heat noise combination environment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103017891B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104596781A (en) * | 2013-10-30 | 2015-05-06 | 北京强度环境研究所 | Flame heating type thermal noise combined environment testing device |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101614584A (en) * | 2009-07-17 | 2009-12-30 | 深圳大学 | A kind of noise measurement system and method based on digital signal processing |
| CN102426035A (en) * | 2011-11-21 | 2012-04-25 | 上海工程技术大学 | Method for testing static flow resistivity and tortuosity of porous sound-absorbing material |
-
2012
- 2012-12-11 CN CN201210531682.XA patent/CN103017891B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101614584A (en) * | 2009-07-17 | 2009-12-30 | 深圳大学 | A kind of noise measurement system and method based on digital signal processing |
| CN102426035A (en) * | 2011-11-21 | 2012-04-25 | 上海工程技术大学 | Method for testing static flow resistivity and tortuosity of porous sound-absorbing material |
Non-Patent Citations (1)
| Title |
|---|
| 潘凯: "基于VA One的飞行舱内噪声预计方法研究", 《测控技术》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104596781A (en) * | 2013-10-30 | 2015-05-06 | 北京强度环境研究所 | Flame heating type thermal noise combined environment testing device |
| CN104596781B (en) * | 2013-10-30 | 2017-07-14 | 北京强度环境研究所 | A kind of flame heating hot noise compound environmental tester |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103017891B (en) | 2014-10-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110717219B (en) | Method and device for acquiring inlet flow of air compressor in complete machine state of aero-engine | |
| CN104713731A (en) | Aero-turbine active clearance control cartridge receiver model confirmatory experiment table | |
| CN104964790B (en) | The modification method of dynamic pressure in combustion chamber is measured using pressure guiding pipe | |
| CN105758460A (en) | Thermal bending deformation and vibration test bench for disk rod fastening rotor | |
| CN103335902B (en) | True pipe bending fatigue test system and method | |
| CN105424369B (en) | A kind of aero-engine aerodynamic model exerciser | |
| Kuo et al. | Effects of jet noise source distribution on acoustic far-field measurements | |
| Zhang et al. | Analysis on acoustic performance and flow field in the split-stream rushing muffler unit | |
| US20120078567A1 (en) | Combustion reference temperature estimation | |
| US10706189B2 (en) | Systems and method for dynamic combustion tests | |
| CN105445031A (en) | Small aero-engine test run stand thrust calibrating system | |
| CN103017891B (en) | Noise testing method under heat noise combination environment | |
| Li et al. | Study on aerodynamic noise numerical simulation and characteristics of safety valve based on dipole and quadrupole | |
| CN111222277B (en) | Vibration evaluation method for inlet and outlet pipelines of booster pump of gas transmission station | |
| CN105095583A (en) | Modal analysis method of static pressure main spindle at micro scale | |
| CN203743033U (en) | Nuclear reactor top draught fan performance testing device | |
| Schuster et al. | Dynamic temperature and pressure measurements in the core of a propulsion engine | |
| CN104742895A (en) | Passenger car air brake system fault detection method based on analytic model | |
| CN203929717U (en) | Porosint becomes gradient high temperature Acoustic performance testing device | |
| CN106338407B (en) | A kind of detection method of traction electric machine cooling system parameter | |
| CN207366195U (en) | In the air by the experimental rig of oily feeler lever damper | |
| CN110489825A (en) | A kind of Compensation Design method of big orifice class air pipe line | |
| KR101109249B1 (en) | Apparatus for Regulating Concentricity of Pipe and System having the Same | |
| Su et al. | Indirect measurement method for high frequency response of complex structure based on statistical energy analysis | |
| Serrano et al. | Effect of Airfoil Clocking on Noise of LP Turbines: Part II—Modal Structure Analysis |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |