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       +   -b,C,r ddt + qt,(lzi - /).l) - Ixz,dd )Al  = C18r A8r + C/8a A8a
         - Cm"U -  (Cmd CI dd  + C, .) Aa + dd  (ly, dd  _ Cnq.,) AO
        - C,n~e A8e + Cm8t A8t
  (-Cnp - b,Cn~ dd )Ap + (_b,Cnpdd + qo(ly, - /xi) - Ixz, dd  )A4
          + (-b,Cnr dd  + Ixz,qo + Ixz, dd  )A /, = C"8r A8r + Cn8a A8a
    Now let us evaluate the forces and moments acting on the airplane following a
small disturbance during the pull-out. Referring to Fig. 4.18, we have
      Fxo - -D - W sin0o + T -O
Fzo = ~L+ W cosO,, - (V~) (UR ) = 0
                Mo -O
         Fvo = Lo(RM) = No = 0
'y
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PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
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_/_h _
Fig.4.18    Forces acting on an airplane during a pull-out maneuver.
For the disturbed flight,
                 Fx -. Fxo + AFx -. -(Do + AD) - W sin(0o + AO) + T
                                                                                                                                                                      \ U)?-
   Fz -- Fzo + AFz = -(Lo + AL) + W cos(0o + AO) - ( v~   [(Uo +RAf/
so that
                                                 AFx -. -AD - W cos 0o AO
                        AFz = -AL - W sinOoAO - (V;~) [2URAU ]
 Proceedingin a similar way as we did for the small disturbance equations ofmotion
for a steady flight in a vertical plane, we obtain
                                    Cxu - -2CD - CDu
                                    xcr : -CDa
                                                           Cx0 - -CL COS 0o
                                        Cxct - -CDd - 0
                                         Cxq = -CDq - 0
                                 Czu = -2CL - CLu - 2tTl,iqo
                                    zct : -Cln
                                      zd - -CLdt
　
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