AN INVESTIGATION OF HELICOPTER FUSELAGE NORMAL MODES OF VIBRATION | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Article 47, Volume 1, A.S.A.T. CONFERENCE 14-16 May 1985 r CAIRO, May 1985, Page 559-568 PDF (2.13 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/asat.1985.26533 | ||||
 View on SCiNiTO | ||||
| Author | ||||
| A. I. SELMY | ||||
| Doctor Engineer, Research and Development Sector, Arab British, Helicopter Company, Arab Organization for Industrialization. | ||||
| Abstract | ||||
| 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. | ||||
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