heedm
An apology;
>
"The very small roll to the left can be also explained aerodynamically....." <
Please disregard the above portion of that sentence.
I forgot that there are no aerodynamics involved in your two examples. The pitch referred to in that sentence is helicopter pitch not blade pitch.
______
While on the soapbox;
>"
Another effect starts happening immediately. In the hover, lift and weight were aligned. When the helicopter rolled left, the lift vector is no longer in line with the center of mass............. This means that with the helicopter rolled left, the lift vector creates a moment that, if the rotor weren't turning, would roll the helicopter left. Since the helicopter already has angular momentum, the result of the lift vector not acting through the center of mass is the vector sum of all the angular momenta. The helicopter continues to roll left because of the cyclic position, but also starts to pitch forward due to the lift vector's alignment."<
Both the longitudinal and the lateral component of the lift vector will not be in line with the mass while an upward vertical motion is taking place on the tail. When this motion stops both lift vectors will realign with the mast
The sketches on web page
http://www.synchrolite.com/0906.html and
http://www.synchrolite.com/0907.html show examples of the thrust vector for rotors with absolute rigidity. The first is hover and the second is an intermeshing configuration with lateral cyclic.
[ 26 November 2001: Message edited by: Dave Jackson ]