Flag-lag stability of helicopter rotor blads in hover and forward flight

Balasubramanian, TS (1982) Flag-lag stability of helicopter rotor blads in hover and forward flight. Technical Report. National Aeronautical Laboratory, Bangalore, India.

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The aerodynamic damping in the lead lag direction for a13; helicopter rotor is very 104,. This makes the blade susceptible for aeroelastic instabilities in that direction.has gone in for dampers in that direction.13; The industry Still the gndustry is trying to solve the problem from the root., by studying basic mechanism of instability in lead lag directions.This has produced enormous lfterature. In the flap-lag stability of helicopter rotors. Various authors have dealt with this problem in detail evolving various methods of solutions, particularly axticdated rotors. For hingeless rotors' the literature available is some-what limited, for the procedure is quite cumbersome to even generate the basic equations.At NAL the articulated rotor flap-lag stability has been studied with the NAL Floquet transitton13; method to reduce computer time. The hingeless rotor equations of motion has been studied in detail and solutions have been obtained using Galerkints principle and HAL floquet transition method.

Item Type: Monograph (Technical Report)
Uncontrolled Keywords: Hingeless rotor hoverstability;Helicopter rotor blades
Subjects: AERONAUTICS > Aerodynamics
Depositing User: M/S ICAST NAL
Date Deposited: 27 Oct 2006
Last Modified: 24 May 2010 04:22
URI: http://nal-ir.nal.res.in/id/eprint/3192

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