CN110031087A - A method of for survey aircraft interior noise - Google Patents
A method of for survey aircraft interior noise Download PDFInfo
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- CN110031087A CN110031087A CN201910168921.1A CN201910168921A CN110031087A CN 110031087 A CN110031087 A CN 110031087A CN 201910168921 A CN201910168921 A CN 201910168921A CN 110031087 A CN110031087 A CN 110031087A
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- noise
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- interior noise
- aircraft interior
- survey aircraft
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H17/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves, not provided for in the preceding groups
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- General Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
Abstract
The invention discloses a kind of methods for survey aircraft interior noise comprising: miniatures production, microphone arrangement, noise measuring, data correction and data conversion and etc..This method has the characteristics that at low cost, precision is high and use scope is wide.
Description
Technical field
The present invention relates to noise monitoring fields, and in particular to a method of for survey aircraft interior noise.
Background technique
Aircraft cabin noise is an important indicator for influencing passenger comfort, and serious noise may make passenger and flight
Member's generation fatigue, palpitating speed, blood pressure raising etc. are uncomfortable, can also make the equipment and instrument of interior of aircraft, because of interior noise and vibration
Phenomena such as raw unstability of movable property and sensitivity weaken.With the continuous improvement of commercial aircraft comfort, noise is also increasingly by industry
Pay attention on boundary.Understand noise source, collect the basis that noise data is aircraft development phase Research of Noise Reduction.To noise source, transmitting road
The measurement of noise abatement seems particularly significant in diameter identification, cabin.
Aircraft is different from automobile, has biggish volume and stringent use condition.If experiment and measurement all make every time
True operation is carried out with real machine, such cost input will be very huge, and be limited to cost, and the number of experiment will not be very
More, the initial data of collection is also less.And once aircraft shapes, then carries out experimental data measurement, such R&D work without
It is suspected to be lag.
Summary of the invention
Aiming at the shortcomings in the prior art, the present invention provides a kind of method for survey aircraft interior noise.
In order to achieve the above object of the invention, the technical solution adopted by the present invention are as follows:
A kind of method for survey aircraft interior noise is provided, including a kind of side for survey aircraft interior noise
Method, which is characterized in that comprise the following processes:
Miniatures production: actual airplane is made into scale model；
Microphone arrangement: 6~12 microphones are arranged in mock-up cabin, the equidistant array distribution of microphone is in the same spherical surface
On；
Noise measuring: including sound pressure level SPL in the cabin before amendmentmWith background noise of wind tunnel sound pressure level SPLw；
Data correction: the influence generated to background noise of wind tunnel is modified；
Data conversion: final actual airplane interior noise data are converted to using the model data measured.
Further, the data correction usesIt is calculated,
Wherein SPLcFor revised sound pressure level.
Further, the data conversion usesWithIt is calculated.
It is of the invention compared with prior art:
1. having, measurement accuracy is high, the low feature of testing cost.
2. equity is measured than model in wind-tunnel, measurement can be repeated several times, and simulate the progress of different weather situation
Measurement.
3. can be adapted to the model of different proportion according to different wind-tunnel sizes, further reduced experiment threshold.
Specific embodiment
A specific embodiment of the invention is described below, in order to facilitate understanding by those skilled in the art this hair
It is bright, it should be apparent that the present invention is not limited to the ranges of specific embodiment, for those skilled in the art,
As long as various change is in the spirit and scope of the present invention that the attached claims limit and determine, these variations are aobvious and easy
See, all are using the innovation and creation of present inventive concept in the column of protection.
Embodiment 1
A method of for survey aircraft interior noise, which is characterized in that comprise the following processes:
Miniatures production: actual airplane is made into scale model, the diminution ratio of model is according to depending on wind-tunnel size.
Microphone arrangement: in mock-up cabin arrange 6 microphones, the equidistant array distribution of microphone on the same spherical surface,
Position foundation of the specific microphone in mock-up cabin needs to measure the position of noise and places.
Microphone model: 1/2 inch of microphone 46AE of G.R.A.S company；Frequency: 3.15Hz (± 2dB)；Dynamic is rung
It answers: 14dBA re.20 μ Pa；Sensitivity: 50mV/Pa (at 250Hz).
Noise measuring: including sound pressure level SPL in the cabin before amendmentmWith background noise of wind tunnel sound pressure level SPLw；
Data correction: it usesBackground noise of wind tunnel is generated
Influence is modified, SPLcFor revised sound pressure level；
Data conversion: it usesWithTo survey
The model data obtained is converted to final actual airplane interior noise data.
Subscript m and p respectively indicate model test value and actual airplane value in formula, and f is frequency, and SPL is interior noise sound
It arbitrarily downgrades, Ma is free stream Mach number, and L is characterized size, and U is speed of incoming flow, and N is Mach number scale factor, specifically by change wind speed and wind
Hole test result obtains, and Fe is that engine noise influences modifying factor, is obtained according to ground engine test result.
Embodiment 2
A method of for survey aircraft interior noise, which is characterized in that comprise the following processes:
Miniatures production: actual airplane is made into scale model, the diminution ratio of model is according to depending on wind-tunnel size.
Microphone arrangement: in mock-up cabin arrange 12 microphones, the equidistant array distribution of microphone on the same spherical surface,
Position foundation of the specific microphone in mock-up cabin needs to measure the position of noise and places.
Microphone model: 1/2 inch of microphone 46AE of G.R.A.S company；Frequency: 20kHz (± 2dB)；Dynamic response:
135dBA re.20μPa；Sensitivity: 50mV/Pa (at 250Hz).
Noise measuring: including sound pressure level SPL in the cabin before amendmentmWith background noise of wind tunnel sound pressure level SPLw；
Data correction: it usesBackground noise of wind tunnel is generated
Influence is modified, SPLcFor revised sound pressure level；
Data conversion: it usesWithTo survey
The model data obtained is converted to final actual airplane interior noise data.
Experimental example:
It has been counted in table through the art of this patent at different frequencies, noise numerical value in the aircraft cabin measured in wind-tunnel
The noise numerical value in middle deck is used with the aerocraft real.
| Frequency/HZ | 200 | 500 | 1000 | 2000 | 5000 | 10000 |
| Test/dB (A) | 65.4 | 73.8 | 79.4 | 76.4 | 71.8 | 61.2 |
| Actual measurement/dB (A) | 63.1 | 70.2 | 78.1 | 79.3 | 74.3 | 58.2 |
Data measured through the invention and real data be can be seen that in the error range class of 3dB, compared with truthful data
There is high reference value, also the reliability of the technology of the present invention has been confirmed in side.
Claims (3)
1. a kind of method for survey aircraft interior noise, which is characterized in that comprise the following processes:
Miniatures production: actual airplane is made into scale model；
Microphone arrangement: 6 ~ 12 microphones are arranged in mock-up cabin, the equidistant array distribution of microphone is on the same spherical surface；
Noise measuring: including sound pressure level SPL in the cabin before amendment m With background noise of wind tunnel sound pressure level SPLw；
Data correction: the influence generated to background noise of wind tunnel is modified；
Data conversion: final actual airplane interior noise data are converted to using the model data measured.
2. the method according to claim 1 for survey aircraft interior noise, it is characterised in that: the data correction is adopted
WithIt is calculated, wherein SPL c For revised sound pressure level.
3. the method according to claim 2 for survey aircraft interior noise, it is characterised in that: the data conversion is adopted
WithWithIt is calculated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910168921.1A CN110031087B (en) | 2019-03-06 | 2019-03-06 | Method for measuring noise in aircraft cabin |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910168921.1A CN110031087B (en) | 2019-03-06 | 2019-03-06 | Method for measuring noise in aircraft cabin |
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| CN110031087A true CN110031087A (en) | 2019-07-19 |
| CN110031087B CN110031087B (en) | 2021-10-19 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111595434A (en) * | 2020-05-29 | 2020-08-28 | 中国航空工业集团公司西安飞机设计研究所 | Ground noise testing method for propeller engine |
| CN112373723A (en) * | 2020-11-20 | 2021-02-19 | 中国直升机设计研究所 | Rotor noise microphone array |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020011939A1 (en) * | 2000-06-22 | 2002-01-31 | Koichiro Mizushima | Vehicle detection apparatus and vehicle detection method |
| EP2287822A2 (en) * | 2009-08-20 | 2011-02-23 | The Boeing Company | Onboard airplane community noise and emissions monitor |
| CN103471709A (en) * | 2013-09-17 | 2013-12-25 | 吉林大学 | Method for predicting noise quality of noise inside passenger vehicle |
| CN104697622A (en) * | 2013-12-06 | 2015-06-10 | 中国飞机强度研究所 | Method for testing aircraft noise loads |
| CN104897275A (en) * | 2015-06-23 | 2015-09-09 | 武汉工程大学 | Engine noise testing method based on outfield airplane |
| CN205302715U (en) * | 2015-09-15 | 2016-06-08 | 西安杰西电子科技发展有限责任公司 | Flight simulator sound data acquisition system |
| CN106297763A (en) * | 2016-08-05 | 2017-01-04 | 中国商用飞机有限责任公司 | aircraft cabin noise suppression system and method |
| CN206223233U (en) * | 2016-12-01 | 2017-06-06 | 天津大学 | A kind of experimental system for simulating for large-scale cabin environment Comfort Evaluation |
-
2019
- 2019-03-06 CN CN201910168921.1A patent/CN110031087B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020011939A1 (en) * | 2000-06-22 | 2002-01-31 | Koichiro Mizushima | Vehicle detection apparatus and vehicle detection method |
| EP2287822A2 (en) * | 2009-08-20 | 2011-02-23 | The Boeing Company | Onboard airplane community noise and emissions monitor |
| CN103471709A (en) * | 2013-09-17 | 2013-12-25 | 吉林大学 | Method for predicting noise quality of noise inside passenger vehicle |
| CN104697622A (en) * | 2013-12-06 | 2015-06-10 | 中国飞机强度研究所 | Method for testing aircraft noise loads |
| CN104897275A (en) * | 2015-06-23 | 2015-09-09 | 武汉工程大学 | Engine noise testing method based on outfield airplane |
| CN205302715U (en) * | 2015-09-15 | 2016-06-08 | 西安杰西电子科技发展有限责任公司 | Flight simulator sound data acquisition system |
| CN106297763A (en) * | 2016-08-05 | 2017-01-04 | 中国商用飞机有限责任公司 | aircraft cabin noise suppression system and method |
| CN206223233U (en) * | 2016-12-01 | 2017-06-06 | 天津大学 | A kind of experimental system for simulating for large-scale cabin environment Comfort Evaluation |
Non-Patent Citations (1)
| Title |
|---|
| 左孔成 等: "飞机舱内噪声的研究现状", 《航空学报》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111595434A (en) * | 2020-05-29 | 2020-08-28 | 中国航空工业集团公司西安飞机设计研究所 | Ground noise testing method for propeller engine |
| CN112373723A (en) * | 2020-11-20 | 2021-02-19 | 中国直升机设计研究所 | Rotor noise microphone array |
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| CN110031087B (en) | 2021-10-19 |
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