Flight dynamic modeling of bearingless helicopters

V. Jambunathan, V. R. Murthy

Research output: Contribution to conferencePaper

Abstract

Flight Dynamic equations of the helicopter including the rotor and inflow degrees of freedom are developed. A six degree of freedom, rigid helicopter airframe model is coupled with the elastic rotor and dynamic inflow models. The rotor is represented by the generalized blade equations based on the rotating elastic modes, while a first harmonic model is used for the inflow perturbation dynamics. Floquet Theory is applied to the periodic flight dynamic stability problem in forward flight. Results are presented in the form of eigenvalues and eigenvectors. Quasi-Static rotor assumption is investigated in Multiblade Coordinates and is found to be unsatisfactory. Time invariant analysis is found to be acceptable in near hover flight conditions but not at high forward speeds. Effects of rotor inertial loads are found to be significant.

Original languageEnglish (US)
Pages216-225
Number of pages10
DOIs
StatePublished - Jan 1 1995
Event20th Atmospheric Flight Mechanics Conference, 1995 - Baltimore, United States
Duration: Aug 7 1995Aug 10 1995

Other

Other20th Atmospheric Flight Mechanics Conference, 1995
CountryUnited States
CityBaltimore
Period8/7/958/10/95

ASJC Scopus subject areas

  • Mechanical Engineering
  • Computer Science Applications
  • Energy Engineering and Power Technology
  • Aerospace Engineering

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    Jambunathan, V., & Murthy, V. R. (1995). Flight dynamic modeling of bearingless helicopters. 216-225. Paper presented at 20th Atmospheric Flight Mechanics Conference, 1995, Baltimore, United States. https://doi.org/10.2514/6.1995-3450