Helicopter Rotor Vibration Reliability Control Analysis

The benefits of applying multiple alternatives for mock-up and compression of helicopter harmonic motion are analyzed. Multiple mock-up approaches, along with a weighted-average mechanism, are approximated so that quicksand affiliated with only applying alone better alternate for the rotor blade vibration-reduction dilemma are bypassed. A harmonic motion external function matching to a flight circumstance in which blade-vortex collaboration drives amplitudinous levels of harmonic motion is accounted. The design variables consist of cross-sectional areas of the architectural component of the blade and non-architectural masses. The optimized considerations are matched with a baseline consideration looking like a UF-60 reference blade. The aftereffects demonstrate that at relatively insufficient additional cost matched with optimizing a single alternate, multiple alternates can be applied to connect diverse reduced-vibration concepts that would be excused if only a single mock-up method was exercised, and the most precise alternate may not control to the superior design.