曝光台 注意防骗
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at - (aw - iw + /r - €) + Acr/.r (3.192)
d~Yt ]
d~ =' (1-:1 )+2;_
Stick-fixed maneuverpoint. We have
Cm - CLXa + Cmac*rn + Cmf - a,a;Vi 77t
(3.193)
(3.194)
= CLXa + Cmac.rn + Cm f - at[aw - iw + it - € + Aat.t] Vi r7, (3.195)
Differentiating with respect to CL, we get
ar fVi r/,
~C~),=a+(tlC~_)f--..V,,7,(1-:1: : 7/ (3.196)
2)ul
The stick-fixed maneuver point Nm is that position of the center of gravity where
(dCm]dCL)m - O and is given by
Nm = a.- (:C/ ),+V 7 [(1- ~) + 2p~,] (3.197)
Hm = Nm - Xc8
For a stable airplane, Hm is positive.
(3.198)
L' -. L + AL
n=1+ \CC,
252 PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
Elevator required per g. Because ofincreased stability level during the ma-
neu'ver, the magnitude of the elevator deflection required for trim also increases.
This increase in elevator defiection is usually expressed by the parameter (d8e/dn),
which is the elevator deflection per unit increase in load factor above unity.
From Eq. (3.101), we have
d8e ( dC, )m
~ig ), =- . (3.199)
With
xcg - Nm
Cm8
(3.200)
ddC~), = dd8 ddr; (3.201)
and
dn . 1
(3.202)
. d~L = CL
we obtain
d8c . CL(Xcg - Nm)
- (3.203)
d7z -- -- CmS
Usually, for a stable airplane, Xc8 < Nm and Cm8 < 0 so that we have d8e]dn < 0-
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