AN INVESTIGATION OF HELICOPTER FUSELAGE NORMAL MODES OF VIBRATION

Document Type : Original Article

Author

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.