Originally Posted by
heliman500
As I understand it, conservation of angular momentum is what explains the phenomenon of rotor blade acceleration/ deceleration during a corresponding CG change in relation to its axis of rotation. To me, this has nothing to do with Coriolis force, which as I understand it is really just a kinematics term to describe a fictitious force that results in a changing vector on moving reference frame. I am failing to see how this relates to a rotor system. Please enlighten me, am I missing part of the puzzle or are helicopter text books using incorrect terminology?
The rotor blades are often analyzed in a coordinates system that rotates with the rotor blade, has its origin in the rotor center, and a primary axis parallel to the (coned) pitch axis. In this system you get a coriolis force, propeller moment, etc.