A Mathematical Model of a Single Main Rotor Helicopter for ... - Read
A Mathematical Model of a Single Main Rotor Helicopter for ... - Read
A Mathematical Model of a Single Main Rotor Helicopter for ... - Read
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damping matrix in flapping differential equations<br />
flapping hinge <strong>of</strong>fset, m(ft)<br />
gravitational acceleration, m/sec2 (ft/sec2)<br />
rotor <strong>for</strong>ce normal to shaft, positive downwind, N (lb)<br />
incidence <strong>of</strong> vertical fin, positive <strong>for</strong> leading edge to the left, rad<br />
incidence <strong>of</strong> horizontal stabilizer, positive <strong>for</strong> leading edge up, rad<br />
<strong>for</strong>ward tilt <strong>of</strong> rotor shaft w.r.t. fuselage, positive <strong>for</strong>ward, rad<br />
rotor blade moment <strong>of</strong> inertia about flapping hinge, kg-m2 (slug-ft2)<br />
rotor moment <strong>of</strong> inertia about shaft<br />
factor to account <strong>for</strong> fraction <strong>of</strong> vertical tail in tail rotor wake<br />
flapping spring constant, N-m/rad (lb-ft/rad)<br />
pitch-flap coupling ratio, 4 tan 6,<br />
spring matrix in flapping differential equations<br />
fuselage rolling moment, n-m (f t-lb)<br />
fuselage lift, N (lb)<br />
rolling moment, pitching moment, and yawing moment, respectively, N-m (ft-lb)<br />
rotor blade mass, kg (slugs)<br />
blade weight moment about flapping hinge, N-m (lb-ft)<br />
number <strong>of</strong> blades<br />
roll, pitch, and yaw rates in the body-c.g. axes system, rad/sec<br />
roll, pitch, and yaw rates in the body-c.g. axes system relative to the air<br />
mass, rad/sec a .<br />
roll, pitch, and yaw rates in the hub-body axes system, rad/sec<br />
ratio <strong>of</strong> flapping frequency to rotor system angular velocity<br />
1<br />
dynamic pressure, - pV2, N/m2 (lb/ft2)<br />
2<br />
10
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