Aeroelastic response, loads, and stability of a composite rotor in forward flight

Edward C. Smith, Inderjit Chopra

Research output: Contribution to journalArticle

51 Scopus citations

Abstract

The aeroelastic response, blade and hub loads, and shaft-fixed aeroelastic stability are investigated for a helicopter with elastically tailored composite rotor blades. A new finite element-based structural analysis including nonclassical effects such as transverse shear, torsion related warping, and in-plane elasticity is integrated with the University of Maryland Advanced Rotorcraft Code (UMARC). The structural dynamics analysis is correlated against both experimental data and detailed finite element results. Correlation of rotating natural frequencies of coupled composite box-beams is generally within 5-10%. The analysis is applied to a soft-in-plane hingeless rotor helicopter in free flight propulsive trim. Changes in blade loads are relatively small; however, aeroelastic stability can be significantly improved by the use of elastic pitch-lag coupling. For example, lag mode damping can be increased 300% over a range of thrust conditions and forward speeds. The influence of attached flow unsteady aerodynamics on the blade response and vibratory hub loads is also investigated. The magnitude and phase of the flap response is substantially altered by the unsteady aerodynamic effects. Vibratory hub loads increase up to 30% due to unsteady aerodynamic effects.

Original languageEnglish (US)
Pages (from-to)1265-1273
Number of pages9
JournalAIAA journal
Volume31
Issue number7
DOIs
StatePublished - Jul 1993

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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