曝光臺 注意防騙
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,
2m
mi - --. (4,421)
p UoS
Iy
Iyl = ;-p U 2S~ (4,422)
380 PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
L
T, Uo
a
zo
a) Airplane in steady flight
\ ~--- &,
┏━━━━┳━━━━━━━━━━━┓
┃ ┃ ┃
┣━━━━╋━━━━━━━━━━━┫
┃ ┃ ┃
┣━━━━╋━━━━━━━━━━━┫
┃jr . ┃r\l, Horizonta ┃
┗━━━━┻━━━━━━━━━━━┛
zo
b) Airplane disturbed ui angle of attack
\-~ A +
c) Airplane disturbed in bank angle
Fig.4.17 Airplanein steady and disUnrbed flight condiOons.
EQUATIONS OF MOTION AND ESTIMATION OF STABILITY DERIVATIVES 381
axis or the zero-lift line, whereas 0o is the angle between the local horizontal and
the velocit)t vector or the flight path.
Now let us evaluate various derrvatives like Cxu, Czu, etc., appearing in Eqs.
(4.417-4.419).
The forces acting on the airplane are lift L, drag D, thrust T, and weight W as
shown. For steady equilibrium flight,
Fxo = T ~ Do - W sin0o = o (4.423)
and, for disturbed flight,
Fx - Fxo + AF.r (4.424)
- T - D - W sin(0o + AO) (4.425)
= T - (Do + A/:5) - W sin(0o + AO) (4.426)
so that
AFx = -AD - W cos OoAO (4.427)
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