曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
,
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)
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
动力机械和机身手册2(100)
