Structural Dynamics of a Helicopter Rotor Blade.
Abstract
In the investigation of the structural dynamic problems associated with a helicopter rotor blade, a fully articulated rotor blade is considered in the analysis of the aeroelastic model. Therefore, there are three degrees of freedom considered; flapping, torsion, and lead-lag. The flapping and torsional motions are coupled inertially and the lead-lag motion is uncoupled from the other motions. The study is concerned with developing an aeroelastic model which takes into consideration the effects of the shearing force and rotary inertia upon the fundamental frequencies and mode shapes of the rotor blade. Also, the effect of inertial coupling between flapping and torsion on the fundamental frequencies and mode shapes is considered. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1973
- Accession Number
- AD0763934
Entities
People
- Michael D. Rudy
Organizations
- Pennsylvania State University