PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL3(108)

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               -(CmaCIS + Cma)        s(l),is - CmqCI)
(6.131)
Let Na.sy, and Aspo denote the determinantsin the numerator and the denominator
ofEq. (6.131). Expanding these determinants, we obtain
                                      Na.spo = Aa.syosZ + BujpoS + Ca.spo               .       (6.132)
where
                                   Aa,.*spo = Cza.lyl                         (6.133)
                                      Bu,spo = Cm&(mi + CzqCI) - Cz8t Cmq Cl                      (6.134)
                                    Ca,.spo = CmB,Cz0                          (6.135)
and
       SOTIl-Czcr)-Czcr -[S(ITIl+Czqc")+)Cz0]1 (6.136)
                    Aspo =   -(CmaCIS + qrurr)          s(l),is - Cmqd
                                                                      J
                                         = OIS3 + a2s2 + a3S + a4                                                             (6.137)
where
                                  ai - (mi - CzaCl)l).l                        (6.138)
                  a2 = -[Czalyl + Cmqci(mi - CzdtCl) + (nii + CzqCI)CmdlCI]    (6.139)
                               a3 = Cza Cmq CI  - [(ttl I + Czq CI)Cma + Cz0C",dicl ]              (6.140)
                                   a4 = -CZOCma                          (6.141)
    The transfer function for pitch angle is given by
                      S(ITZI - CZd,CI) - Czcr
        AO(s)       -(C,nu + C,,,acis)
A8e =
Aspo(s)
(6.142)
AlRPLANE RESPONSE AND CLOSED-LOOP CONTROL         561
Expanding the numerator in Eq. (6.142), we get
　
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