CN110031087B - Method for measuring noise in aircraft cabin - Google Patents
Method for measuring noise in aircraft cabin Download PDFInfo
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- CN110031087B CN110031087B CN201910168921.1A CN201910168921A CN110031087B CN 110031087 B CN110031087 B CN 110031087B CN 201910168921 A CN201910168921 A CN 201910168921A CN 110031087 B CN110031087 B CN 110031087B
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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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- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
Abstract
The invention discloses a method for measuring noise in an aircraft cabin, which comprises the following steps: the method comprises the steps of miniature model making, microphone arrangement, noise detection, data correction, data conversion and the like. The method has the characteristics of low cost, high precision and wide application range.
Description
Technical Field
The invention relates to the field of noise monitoring, in particular to a method for measuring noise in an airplane cabin.
Background
Noise in an aircraft cabin is an important index influencing the comfort of passengers, and serious noise can cause discomfort such as fatigue, accelerated heartbeat, increased blood pressure and the like of the passengers and pilots, and also can cause instability, weakened sensitivity and the like of equipment in the aircraft due to noise and vibration in the cabin. With the continuous improvement of the comfort of the commercial aircraft, the noise is also more and more emphasized by the industry. Knowing the source of the noise, collecting noise data is the basis for noise reduction studies in the development phase of the aircraft. The method is very important for measuring noise sources, transmission path identification and noise reduction level in the cabin.
Airplanes are distinguished from automobiles by having a large volume and strict conditions of use. If each experiment and measurement is actually performed by using a real machine, the cost investment is huge and limited by the cost, the number of experiments is not large, and the collected raw data is small. And once the aircraft is shaped, experimental data measurements are taken, such development work is undoubtedly delayed.
Disclosure of Invention
In view of the deficiencies in the prior art, the present invention provides a method for measuring noise in an aircraft cabin.
In order to achieve the purpose of the invention, the invention adopts the technical scheme that:
there is provided a method for measuring noise in an aircraft cabin, comprising a method for measuring noise in an aircraft cabin, characterized by the process of:
manufacturing a miniature model: making a real airplane into a scaling model;
microphone placement: arranging 6-12 microphones in the model cabin, wherein the microphones are distributed on the same spherical surface in an equidistant array manner;
noise detection: including the cabin sound pressure level SPL before modificationmWind tunnel background noise sound pressure level SPLw;
and (3) data correction: correcting the influence generated by the background noise of the wind tunnel;
data conversion: the measured model data is used to translate into final real in-flight noise data.
Further, the data correction employs
Performing a calculation in which SPLcIs the modified sound pressure level.
Further, said data conversion employs
And
and (6) performing calculation.
Compared with the prior art, the invention has the advantages that:
1. the method has the characteristics of high measurement precision and low test cost.
2. The method is characterized in that the geometric model is measured in the wind tunnel, repeated measurement can be carried out for many times, and different weather conditions are simulated for measurement.
3. The model with different proportions can be adapted according to different wind tunnel sizes, and the experiment threshold is further reduced.
Detailed Description
The following description of the embodiments of the present invention is provided to facilitate the understanding of the present invention by those skilled in the art, but it should be understood that the present invention is not limited to the scope of the embodiments, and it will be apparent to those skilled in the art that various changes may be made without departing from the spirit and scope of the invention as defined and defined in the appended claims, and all matters produced by the invention using the inventive concept are protected.
Example 1
A method for measuring noise in an aircraft cabin, comprising the steps of:
manufacturing a miniature model: the real airplane is made into a scale model, and the scale of the model is determined according to the size of the wind tunnel.
Microphone placement: 6 microphones are arranged in the model cabin, the microphones are distributed on the same spherical surface in an equidistant array mode, and the specific microphones are placed at positions in the model cabin according to positions needing noise measurement.
Microphone model: 1/2 inch microphone 46AE by g.r.a.s company; frequency: 3.15Hz (+ -2 dB); dynamic response: 14dBA re.20 mu Pa; sensitivity: 50mV/Pa (at 250 Hz).
Noise detection: including the cabin sound pressure level SPL before modificationmWind tunnel background noise sound pressure level SPLw;
and (3) data correction: by using
Correction of the effects of wind-tunnel background noise, SPLcIs the modified sound pressure level;
data conversion: use of
And
and converting the measured model data into final real noise data in the aircraft cabin.
In the formula, subscripts m and p respectively represent a model test value and a real airplane value, f is frequency, SPL is noise sound pressure level in a cabin, Ma is incoming flow Mach number, L is characteristic dimension, U is incoming flow speed, N is a Mach number ratio scaling factor, the noise sound pressure level is obtained by a variable wind speed wind tunnel test result, and Fe is an engine noise influence correction factor and is obtained according to a ground engine test result.
Example 2
A method for measuring noise in an aircraft cabin, comprising the steps of:
manufacturing a miniature model: the real airplane is made into a scale model, and the scale of the model is determined according to the size of the wind tunnel.
Microphone placement: 12 microphones are arranged in the model cabin, the microphones are distributed on the same spherical surface in an equidistant array mode, and the specific microphones are placed in the model cabin according to the positions of the noise to be measured.
Microphone model: 1/2 inch microphone 46AE by g.r.a.s company; frequency: 20kHz (± 2 dB); dynamic response: 135dBA re.20 μ Pa; sensitivity: 50mV/Pa (at 250 Hz).
Noise detection: including the cabin sound pressure level SPL before modificationmWind tunnel background noise sound pressure level SPLw;
and (3) data correction: by using
Correction of the effects of wind-tunnel background noise, SPLcIs the modified sound pressure level;
data conversion: use of
And
and converting the measured model data into final real noise data in the aircraft cabin.
Experimental example:
the table shows the noise value in the cabin of the aircraft measured in the wind tunnel and the noise value in the cabin of the aircraft in actual use under different frequencies by the technology.
| frequency/HZ | 200 | 500 | 1000 | 2000 | 5000 | 10000 |
| experiment/dB (A) | 65.4 | 73.8 | 79.4 | 76.4 | 71.8 | 61.2 |
| measured/dB (A) | 63.1 | 70.2 | 78.1 | 79.3 | 74.3 | 58.2 |
It can be seen that the data measured by the method and the actual data have an error range class of 3dB, and have extremely high reference value compared with the actual data, and the reliability of the method is laterally proved.
Claims (1)
1. A method for measuring noise in an aircraft cabin, comprising the steps of:
manufacturing a test model: making a real airplane into a scaling model;
microphone placement: arranging 6-12 microphones in the model cabin, wherein the microphones are distributed on the same spherical surface in an equidistant array manner;
noise detection: including the cabin sound pressure level SPL before modificationmWind tunnel background noise sound pressure level SPLw;
and (3) data correction: correcting the influence generated by the background noise of the wind tunnel;
data conversion: converting the measured model data into final real in-cabin noise data;
the data correction adopts
Performing a calculation in which SPLcIs the modified sound pressure level;
the data conversion adopts
And
calculating;
subscripts m and p in the formula respectively represent a model test value and a real airplane value, f is frequency, SPL is noise sound pressure level in a cabin, Ma is incoming flow Mach number, L is characteristic dimension, U is incoming flow speed, N is a Mach number ratio scaling factor, and Fe is an engine noise influence correction factor.
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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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| CN201910168921.1A CN110031087B (en) | 2019-03-06 | 2019-03-06 | Method for measuring noise in aircraft cabin |
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| CN110031087B true CN110031087B (en) | 2021-10-19 |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN112373723B (en) * | 2020-11-20 | 2022-06-21 | 中国直升机设计研究所 | Rotor noise microphone array |
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| EP2287822A2 (en) * | 2009-08-20 | 2011-02-23 | The Boeing Company | Onboard airplane community noise and emissions monitor |
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| JP2002008189A (en) * | 2000-06-22 | 2002-01-11 | Matsushita Electric Ind Co Ltd | Vehicle detector and vehicle detection method |
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| 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 |
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