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Rotorcraft Flying Menu >General
Aerodynamics >Airfoil >
Blade Pitch Angle
The pitch angle of a rotor blade is the angle
between its chord line and the reference plane containing the
rotor hub. [Figure 2-4] You control the pitch angle of the blades
with the flight controls. The collective pitch changes each
rotor blade an equal amount of pitch no matter where it is located
in the plane of rotation (rotor disc) and is used to change
rotor thrust. The cyclic pitch control changes the pitch of
each blade as a function of where it is in the plane of rotation.
This allows for trimming the helicopter in pitch and roll during
forward flight and for maneuvering in all flight conditions.
Figure 2-4. Do not confuse the axis
of rotation with the rotor mast. The only time they coincide
is when the tip-path plane is perpendicular to the rotor mast.
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