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SYMBOLS
General
ct/_
K
qfn
R
thrust coefficient, divided by solidity
control-system stiffness matrix (inverted form)
nth fuselage dynamic mode (n = 1 to 4 are
symmetric, n = 5 to 8 are antisymmetric)
rotor radius
Control System
MO collective pitch moment, ft.lb
M1C lateral cyclic moment, ft-lb
M1S longitudinal cyclic moment, ft.lb
0 0 collective pitch measured at the blade root, rad
O1C lateral cyclic pitch, rad
01S longitudinal cyclic pitch, rad
075 collective pitch measured at 75% R, rad
Aeroelastic Modes
X+I advancing or progressive mode, for any mode X
X- 1 retreating or regressive mode
fiG rotor-gimbal mode
/3n nth blade-bending mode (flap and/or lead-lag)
On nth blade-torsion mode
_u rotor inflow
1/tE engine-speed mode
gtI interconnect-shaft-speed mode (antisymmetric)
VS rotor-speed mode (symmetric)
Note: The above notation generally follows that of
reference 5. The first collective bending and torsion
modes are labeled/30 and 00, respectively, but the
first progressive and regressive modes are labeled
/31+1, 01+I,/31- 1, and 01 -1.
PRYING PA6E BLANK NOT FILMED
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