Coning.Angle.Hover

# Coning.Angle.Hover - Coning Angle Because the blades of a...

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Coning Angle Because the blades of a helicopter rotor are hinged near the root with a flap hinge, the blades are free to flap up or down. The lift forces will tend to flap the blades up, while the centrifugal forces will tend to push the blades down. A static equilibrium is achieved in hover, where the blades come to rest at an equilibrium “coning” angle, called β 0 . In forward flight, the airloads tend to vary in a sinusoidal form, and a static equilibrium is not feasible. Rather, the blades undergo a limit cycle oscillation of the form: ( 29 ( 29 ( 29 ( 29 ( 29 ( 29 ( 29 ( 29 ( 29 ... 2 cos 2 sin cos sin ... 2 cos 2 sin cos sin 2 2 1 1 0 2 2 1 1 0 + + + + + = + + + + + = ψ β c s c s c s c s t t t t t We will study the forward flight flapping motion in detail later in this course. In this section, we study a technique for estimating the coning angle when the blade is in hover. For simplicity, we will assume that the hinge point is at the origin, r=0. β

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## This note was uploaded on 01/05/2011 for the course DU 3 taught by Professor Frando during the Spring '10 term at University of Dundee.

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Coning.Angle.Hover - Coning Angle Because the blades of a...

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