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Finite Element Stability Analysis for Coupled Rotor and Support Systems

NASA NTRS · Contractor Report (CR) · 19770019135 · Published 2019-06-20 · Legacy CDMS · 2 authors

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Abstract and citation only, verbatim from NASA NTRS; full text lives there. All credit to the authors and Legacy CDMS.

Abstract

The effects of fuselage motions on stability and random response were analytically assessed. The feasibility of adequate perturbation models from non-linear trim conditions was studied by computer and hardware experiments. Rotor wake-blade interactions were assessed by using a 4-bladed rotor model with the capability of progressing and regressing blade pitch excitation (cyclic pitch stirring), by using a 4-bladed rotor model with hub tilt stirring, and by testing rotor models in sinusoidal up or side flow.

Authors

  • Hohenemser, K. H. Washington Univ.
  • Yin, S. K. Washington Univ.

Citation

Hohenemser, K. H., Yin, S. K. (2019). Finite Element Stability Analysis for Coupled Rotor and Support Systems. Legacy CDMS. NASA NTRS ID 19770019135. https://ntrs.nasa.gov/citations/19770019135 ↗