Modal analysis of an aircraft fuselage panel using experimental and finite-element techniques

被引：5
|
作者：
Fleming, GA [1 ]
Buehrle, RD [1 ]
Storaasli, OL [1 ]
机构：
[1] NASA, Langley Res Ctr, Hampton, VA 23681 USA
来源：
THIRD INTERNATIONAL CONFERENCE ON VIBRATION MEASUREMENTS BY LASER TECHNIQUES: ADVANCES AND APPLICATIONS | 1998年 / 3411卷
关键词：
Electro-Optic Holography; EOH; aircraft; fuselage; interferogram; FEM; validation;
D O I：
10.1117/12.307740
中图分类号：
O42 [声学];
学科分类号：
070206 ; 082403 ;
摘要：
The application of Electro-Optic Holography (EOH) for measuring the center bay vibration modes of an aircraft fuselage panel under forced excitation is presented. The requirement of free-free panel boundary conditions made the acquisition of quantitative EOH data challenging since large scale rigid body motions corrupted measurements of the high frequency vibrations of interest. Image processing routines designed to minimize effects of large scale motions were applied to successfully resurrect quantitative EOH vibrational amplitude measurements from extremely noisy data. EOH and Scanning Laser Doppler Vibrometry (SLDV) results have been used to validate and update finite element models of the fuselage panel. Various modeling techniques were evaluated for characterization of the panel normal modes at frequencies up to 1000 Hz. These models are briefly described, and comparisons between computational predictions and experimental measurements are presented.
引用
收藏
页码：537 / 548
页数：12
相关论文
共 50 条
  • [1] Experimental Modal Analysis of an Aircraft Fuselage Panel
    Wyen, Travis A.
    Schoettelkotte, Joshua J.
    Perez, Ricardo A.
    Eason, Thomas G.
    [J]. SHOCK & VIBRATION, AIRCRAFT/AEROSPACE, ENERGY HARVESTING, ACOUSTICS & OPTICS, VOL 9: PROCEEDINGS OF THE 35TH IMAC, 2017, : 155 - 166
  • [2] Experimental Modal Analysis of an Aircraft Fuselage Panel: Part II
    Wyen, Travis A.
    Perez, Ricardo A.
    Knox, Jonathan
    Schoettelkotte, Joshua J.
    Eason, Thomas G.
    [J]. TOPICS IN MODAL ANALYSIS & TESTING, VOL 9, 2019, : 289 - 298
  • [3] CORRECTION OF FINITE-ELEMENT MODELS USING EXPERIMENTAL MODAL DATA
    SOHN, K
    OKUMA, M
    NAGAMATSU, A
    [J]. JSME INTERNATIONAL JOURNAL SERIES C-DYNAMICS CONTROL ROBOTICS DESIGN AND MANUFACTURING, 1993, 36 (02): : 214 - 218
  • [4] FINITE-ELEMENT ANALYSIS OF AN ULTRALIGHT AIRCRAFT
    BAUGHN, TV
    PACKMAN, PF
    [J]. JOURNAL OF AIRCRAFT, 1986, 23 (01): : 82 - 86
  • [5] Modal analysis versus finite-element analysis
    Richardson, M
    [J]. SOUND AND VIBRATION, 2005, 39 (09): : 5 - 6
  • [6] USING MODAL-ANALYSIS TO IMPROVE CONFIDENCE IN FINITE-ELEMENT ANALYSIS
    GOOD, M
    MACIOCE, D
    [J]. SOUND AND VIBRATION, 1984, 18 (01): : 18 - &
  • [7] A comparison of finite element buckling analysis predictions and experimental results for riveted aircraft fuselage panels
    Koffi, K
    Gibson, A
    Price, M
    [J]. COMPUTATIONAL METHODS AND EXPERIMENTAL MEASUREMENTS X, 2001, 3 : 291 - 300
  • [8] MODAL SYNTHESIS VIA COMBINED EXPERIMENTAL AND FINITE-ELEMENT TECHNIQUES WITH CONSIDERATION OF ROTATIONAL EFFECTS
    CHEN, WH
    CHERNG, JS
    [J]. JOURNAL OF SOUND AND VIBRATION, 1985, 103 (01) : 1 - 11
  • [9] Finite-element simulation and analysis on high velocity impact damage of aircraft panel structure
    Li, Shulin
    Hou, Manyi
    [J]. PROGRESSES IN FRACTURE AND STRENGTH OF MATERIALS AND STRUCTURES, 1-4, 2007, 353-358 : 1033 - 1036
  • [10] Update of the starship fuselage finite element model using modal data
    Hassiotis, S
    [J]. IMAC - PROCEEDINGS OF THE 17TH INTERNATIONAL MODAL ANALYSIS CONFERENCE, VOLS I AND II, 1999, 3727 : 1563 - 1569
12345