This paper describes an experimental study to compute the normal modes of vibrations of helicopters. The work presented herein details the normal modes characteristics between 5Hz and 50Hz of a developed helicopter. The Lynx helicopter airframe was used as the test aircraft. Each mode shape was recorded at 121 monitoring points on the airframe in the vertical, lateral and fore-and-aft directions. Complex response plots were obtained for each mode shape and the modal damping factors were estimated. The results of the experimental investigations were compared with a theoretical finite element modelling analysis. Good agreement between the finite element analysis and the experimental natural frequencies and mode shapes were obtained.
SELMY, A. (1985). AN INVESTIGATION OF HELICOPTER FUSELAGE NORMAL MODES OF VIBRATION. International Conference on Aerospace Sciences and Aviation Technology, 1(A.S.A.T. CONFERENCE 14-16 May 1985 r CAIRO), 559-568. doi: 10.21608/asat.1985.26533
MLA
A. I. SELMY. "AN INVESTIGATION OF HELICOPTER FUSELAGE NORMAL MODES OF VIBRATION", International Conference on Aerospace Sciences and Aviation Technology, 1, A.S.A.T. CONFERENCE 14-16 May 1985 r CAIRO, 1985, 559-568. doi: 10.21608/asat.1985.26533
HARVARD
SELMY, A. (1985). 'AN INVESTIGATION OF HELICOPTER FUSELAGE NORMAL MODES OF VIBRATION', International Conference on Aerospace Sciences and Aviation Technology, 1(A.S.A.T. CONFERENCE 14-16 May 1985 r CAIRO), pp. 559-568. doi: 10.21608/asat.1985.26533
VANCOUVER
SELMY, A. AN INVESTIGATION OF HELICOPTER FUSELAGE NORMAL MODES OF VIBRATION. International Conference on Aerospace Sciences and Aviation Technology, 1985; 1(A.S.A.T. CONFERENCE 14-16 May 1985 r CAIRO): 559-568. doi: 10.21608/asat.1985.26533
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