flapping
CRAN , (and others)
Flapping , in a teetering rotor, causes the rotor tip-path plane to tilt away(flap back) from the spin axis and is the result of differing airspeeds on adv/retreating blades.
I am having trouble seeing how "flapping loads" increase in a sideslip.
In sideways flight, the helicopter will roll, just as it will pitch in forward flight, but corrective cyclic is not needed in the "other" direction.
Actually, more cyclic has to added in the direction you are going, or you will slow down. The cg of the aircraft swings out behind and the rotor thrust then remains aligned with the cg, otherwise it would continue to roll.
In any case, the relationship of the rotor tilt to the fuselage has nothing to do with flapping. The ratio of forward speed to rotor speed is the only factor I am aware of that controls flapping angle for a given g loading.
What am I missing?