曝光臺 注意防騙 網(wǎng)曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費(fèi)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)
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：動力機(jī)械和機(jī)身手冊2(100)