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Lo - Mo -.No -0
U-Uo+AU V-AV W-AW
P = Ap q = Aq r - Ar
Fx - AFx Fy = AFy Fz = AFz
L -.AL M - AM N - AN
(4.372)
(4.373)
(4.374)
(4.375)
(4.376)
(4.377)
AUU <<1
AUV, ' << 1
~UW << 1 (4.378)
p << 1 q <<1 r << 1 (4.379)
With these assumptions, second-order terms such as AqA W can be ignored.
Then Eqs. (4.364-4.369) reduce to the following form:
AFx - mAU (4.380)
AFy = m(AV + r Uo) (4.381)
AFz = m(A W - qUo) (4,382)
AL = plr - rlrz
AM = q Iy
AN = r Iz - p Ixz
(4.383)
(4.384)
(4.385)
EQUATIONS OF MOTION AND ESTIMATION OF STABILITY DERIVATIVES 375
Define
AU
u= U
AV
v : --
Uo
AW
w - - (4.386)
Uo
AFx AFy AFz
ACx= pUS' ACy= US ACz=2pUS (4.387)
ACi=TAL AM AN
2~pUo2S7 ACrrt=~_pU2S ACn:- JSb (4.388)
: = ;-p U2S
so that
AW
Act ~ ~
Uo -w
Ap ~ AUV =v
Then, Eqs. (4.380-4.385) take the following form:
mUo .
ACx - ~-p U2Su
Z\Cy = pUU ScAB + r)
ACz= UUS(Ad-_q)
AC,= p+Sb(PIx -r Ixz)
l),
ACm= pU S q
AC" = pU~Sb(r Iz - plxz)
(4.389)
(4.390)
(4.391)
(4.392)
(4.393)
(4.394)
(4.395)
(4.396)
(4.397)
(4.398)
W
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动力机械和机身手册2(96)
