NASA-CR-181851-1989 Evaluation of analysis techniques for low frequency interior noise and vibration of commercial aircraft《商用飞机低频率内部噪声和振动的分析技术评估》.pdf
《NASA-CR-181851-1989 Evaluation of analysis techniques for low frequency interior noise and vibration of commercial aircraft《商用飞机低频率内部噪声和振动的分析技术评估》.pdf》由会员分享,可在线阅读,更多相关《NASA-CR-181851-1989 Evaluation of analysis techniques for low frequency interior noise and vibration of commercial aircraft《商用飞机低频率内部噪声和振动的分析技术评估》.pdf(78页珍藏版)》请在麦多课文档分享上搜索。
1、NASA Contractor Report 18“185“1Evaluation of Analysis Techniques for LowFrequency Interior Noise and Vibrationof Commercial AircraftA. E. Landmann, H. F. Tillema, and S. E. MarshallBoeing Commercial AirplanesRO. Box 3707Seattle, Washington 9812.4-2207Contract NASI-18027October 1989N/ .SANational Aer
2、onautics andSpace AdministrationLangley Research CenterHampton, Virginia 23665-5225(NASA-CF_-I61_,I) LVALUATION OF ANALYSISTECHNI(_UES FOR. LOW FRF_ULNCY INTEQIOR NnlStANO VI_RATIqN uF C_MMERCIAL AIRCRAFT(hoeing Commercial Airplane Co.) -/3 pCSCL 20A c3/rlNgO-I ko66uncl as0234097Provided by IHSNot f
3、or ResaleNo reproduction or networking permitted without license from IHS-,-,-H8U9ddU|HU|iiH|Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-i Af“_-“ “,1 FOREWORDmmLmmiwLu- 1|mK_mmThis report contains comparisons of predicted and measured vibration a
4、nd interior noise levels for anaircraft, with aft mounted propeller engines. Based on these comparisons, recommendations are madefor modeling and analysis techniques for evaluation of low-frequency engine noise and vibration in thepassenger cabin. This work was conducted under NASA contract NAS1-180
5、27 from January, 1987through February, 1989. Work was managed by the Acoustics Division at the NASA Langley ResearchCenter. During 1987 work, Mr. H. Morgan was the chief of the Acoustics Division and Mr. D. G. Ste-phens was the technical monitor for the contract. During the 1988 and early 1989 work,
6、 Mr. D. G. Ste-phens was chief of the Acoustics Division at NASA and Dr. K. Shepherd was the technical monitor forthe contract.All analytical work was performed under the direction of the Noise Research staff of the Boeing Com-mercial Airplanes. A number of engineering organizations and subcontracto
7、rs contributed to thesuccessful completion of the project as planned. Key contractor personnel responsible for this effortwereNoise Technolo_,L. M. ButzelL. W. CraigC. G. HocJgeA. E. LandmannS. E. MarshallG. K. OueitzschP. M. SeratiSlructures Technolo_K. H. DickensonR. L. DreisbachR. R. EnsmingerM.
8、T. HutchinsonH. J. JamshidiatE. E. MeyerH. E TillemaPropulsion Technolotw.M. A. HeidariR. L. MartinJ. L. WhiteT. E YantisWeights Technolo_D. E. CookD. J. RobertsSubcontractorsA. C. Aubert - Cambridge Collaborative, Inc.J. E. Manning - Cambridge Collaborative, Inc.L. D. PopemProvided by IHSNot for Re
9、saleNo reproduction or networking permitted without license from IHS-,-,-.Lwwimi|Hii-imdImiil !mE _iJiiR i|mRelmamIi !|n m|iProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-mMuTABLE OF CONTENTSFOREWORD . iTABLE OF CONTENTS iiiLIST OF TABLES . vLIST OF
10、 FIGURES vii1.0 SUMMARY . 12.0 INTRODUCTION . 3iWL-3.04.0APPROACH 53.1 Noise and Vibration Tests . 53.2 Analysis Model Development 73.2.1 Finite Element Model . 83.2.2 Statistical Energy Analysis Model . 93.2.3 PAIN Model . 13RESULTS4.14.24.34.44.54.64.74.84.94.104.114.12oo . o,oo ,o,ooo,ooo,oooo,oo
11、o,ooo.ooo,o ,. o. oooo 15Finite Element Analysis Results CFY 1987) . 15Finite Element Model Improvements (FY 1988) . 20Finite Element Analysis Results (FY 1988) . 22Statistical Energy Analysis Results (FY 1987) . 33Review of SEA Procedures for Low-Frequency Problems 384.5.1 Acoustic Space Modal Dens
12、ity Estimate 384.5.2 Structure Modal Density Estimates 394.5.3 Use of Finite Element Models to Verify SEA Parameters . 39SEAM TM Code Improvements 41SEA Low-Frequency Model Improvements . 434.7.1 Input Power Estimate . 434.7.2 Modal Density Estimates . 444.7.3 Strut Connection Modeling 444.7.4 Strut
13、 Loss Factor 46Midfrequency Model Improvements . 47Statistical Energy Analysis Results (FY 1988) . 49PAIN Analysis Resuts (FY 1987) 55PAIN Analysis Results (FY 1988) 57PAIN Improvements and Feasibility Studies . 62,o111PRECEDING PAGE BLANK NOT FILMEDProvided by IHSNot for ResaleNo reproduction or ne
14、tworking permitted without license from IHS-,-,-5.0eag_CONCLUSIONS AND RECOMMENDATIONS . 655.1 Finite Element Analysis . 655.2 Statistical Energy Analysis 665.3 PAIN Analysis . 66m=JZzIII|mmiII!Ei1!m,BIWIIImmtllw=IR _;l!n el -Illivwl, |w |!-=iProvided by IHSNot for ResaleNo reproduction or networkin
15、g permitted without license from IHS-,-,-LLmE JRITableLIST OF TABLESr_ag_727 Demonstrator Airplane Ground Vibration Test (GVT) Shake Conditions . 5727 Demonstrator Airplane Flight Conditions . 7Modeling Time and Cost Comparison for 727 Demonstrator Airplane FiniteElement Models 33LwluFProvided by IH
16、SNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-viwliUiiimnliimlriNI!1mIiilIii|_ JIiiRIillmilm _iEl -“Iil -Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-IwMmw12345678910111213141516171819202122232425LIST OF“ FIGU
17、RESEa_Prediction Program Comparisons and Comments . 1727 Demonstrator Airplane-General Arrangement . 6BS 1010 Microphone and Accelerometer Locations 7727 Demonstrator Airplane-Finite Element Model Finite Element Method 8GE36 Demonstrator Engine Finite Element Model . 1025-Element Low-Frequency SEAM
18、TM Model (20- to 100-Hz Range) 11100-Element Midfrequency SEAM TM Model (100-to 400-Hz Range) 12Propeller Aircraft Interior Noise Model . 14727 Demonstrator Airplane Predicted Versus Measured Frame ModeShape at BS 1010-21.5 Hz 15727 Demonstrator Airplane GVT-Roving Microphone Data 16727 Demonstrator
19、 Airplane GVT Accelerometer Data Frame VersusCeiling Panel Response at Stringer 4 17Finite Element Prediction Versus 727/GE36 Demonstrator Test;GVT-Front Mount Vertical Shake . 18Finite Element Prediction Versus 727/GE36 Demonstrator Test;GVT-A.ft Lower Mount Lateral Shake . 20Original and Revised C
20、eiling Panel Weight Distribution . 21Original and Revised Hat Rack Weight Distribution 21Acoustic Mesh Typical Cross Section . 23727 Demonstrator Airplane-Reduced Finite Element Models . 24Finite Element Prediction Versus 727/GE36 Demonstrator Test;Ground Vibration Test-Front Mount Vertical Shake .
21、25Longitudinal Variations Around BS 1010-GE Side Window SeatMicrophone Prediction 26Finite Element Prediction Versus 727/GE36 Demonstrator Test;Ground Vibration Test-Aft Lower Mount Lateral Shake . 27Finite Element Predictions Versus 727/GE36 Demonstrator Test;Ground Vibration Test-Front Mount Verti
22、cal Shake . 28Finite Element Predictions Versus 727/GE36 Demonstrator Test;Ground Vibration Test-Aft Lower Mount Fore-Aft Shake 29Finite Element Predictions Versus 727/GE36 Demonstrator Test;Ground Vibration Test-Aft Lower Mount Vertical Shake . 30Finite Element Predictions Versus 727/GE36 Demonstra
23、tor Test;Ground Vibration Test-Aft Lower Mount Lateral Shake . 32SEA2kfr,_ Predicted Levels Versus 727 Demonstrator Test Data:GVT-Forward Mount Lateral Shake . 34PRECEDING PAGEviiBLANK NOT FILMEDProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Ii2Je,2
24、62728293O313233343536373839404142434445464748495OLae, Low-Frequency SEAM TM Model Predicted Levels Versus 727 DemonstratorTest Data; GVT-Forward Mount Vertical Shake . 35Midfrequency SEAM TM Model Predicted Levels Versus 727 DemonstratorTest Data; GVT-Forward Mount Vertical Shake . 37Asymptotic Moda
- 1.请仔细阅读文档,确保文档完整性,对于不预览、不比对内容而直接下载带来的问题本站不予受理。
- 2.下载的文档,不会出现我们的网址水印。
- 3、该文档所得收入(下载+内容+预览)归上传者、原创作者;如果您是本文档原作者,请点此认领!既往收益都归您。
下载文档到电脑,查找使用更方便
10000 积分 0人已下载
下载 | 加入VIP,交流精品资源 |
- 配套讲稿:
如PPT文件的首页显示word图标,表示该PPT已包含配套word讲稿。双击word图标可打开word文档。
- 特殊限制:
部分文档作品中含有的国旗、国徽等图片,仅作为作品整体效果示例展示,禁止商用。设计者仅对作品中独创性部分享有著作权。
- 关 键 词:
- NASACR1818511989EVALUATIONOFANALYSISTECHNIQUESFORLOWFREQUENCYINTERIORNOISEANDVIBRATIONOFCOMMERCIALAIRCRAFT

链接地址:http://www.mydoc123.com/p-836654.html