Pitch link loads and control system loads seems to be a black subject. If given a naca 0012 airfoil, 2 bladed rotor of 24' diameter with a tip speed of 600fps, does anyone know what the pitch load would be (approx) on a 2000 lb helicopter in a severe pull up maneuver? Or, maybe easier, are there formulas for calculating pitch link loads?
Red Flag Submitted
Thank you for helping keep Eng-Tips Forums free from inappropriate posts. The Eng-Tips staff will check this out and take appropriate action.
Reply To This Thread
Posting in the Eng-Tips forums is a member-only feature.