Environmental Engineering Reference
In-Depth Information
Carrying out the integration of Equation (11-30) by parts gives the following
expressions for the flap accelerations of an independent blade:
sM
= -
sK
B
-
s
W
2
K
W
+ 2W
s
q
p
sK
C
-
c
y
gK
g
(
Bending
)
(
Tension Stiffening
)
-
c
q
p
W
2
+ 2Wf
c
y + f
s
y
M
R
(
-
Rigid
Body Motion
)
+
s
W
2
s
q
p
K
q
(
Inertia Moment Stiffening
)
(11-31)
+ W
2
s
q
p
c
q
p
M
B
+
F
a
(
C.G. Imbalance
)
(
Aero Forace
)
+
s
W
2
s
q
p
M
(
Inertia Force Stiffening
)
+
g
(- c
c
q
p
+
s
q
p
s
y + b
0
c
q
p
c
y)
M
g
(
Gravity
)
The various coefficients in this acceleration equation are given by the integrals in Equations
(11-32) which are evaluated numerically. A
trim
solution of the equation of motion is then
found by forward integration in time (or, equivalently, in azimuth y) until the following
convergence criteria
are met:
s
[2(
n
+ 1)p /W] =
s
[2
n
p W] ± e
1
s
[2(
n
+ 1)p /W] =
s
[2
n
p /W] ± e
2
/
where
n
=
number of rotor rotations
e
1
, e
2
= convergence tolerances (m, m/s)
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