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?
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pitch link load 1
- Thread starter bernie007
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Chapter 21 of Ray Prouty booklet 'Even More Helicopter Aerodynamics' is entitled "Pitch-Link Loads'. It is totally non-technical, but it does give an overview of the subject.
Dave Jackson
Dave Jackson
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