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                             B8 -. trii(-l}.i Cza - Cmq Cl [r71i  - Czd CI] - mi Cm,ci)
                        - C."l),i(mi - Czctci) - CxcrCICzuA,l                    (6.113)
                          Ca;  = rni (Czrr Cmq Cl  - Ull Crmr - Czq Cmd,C~
                                     - Cxu(-Iyl Cztr - Cmq CI [mi - Czd Cl] - ITl I Cma CI)          '
                                              - Cxcit Cz" lyl  + Cx& Czu Cmq C~ -  CxdrtTi I Cmu CI
                                     - Cxq Cl (Czu Cma,CI  + C,n tmi  - Cmu Czctci)         .             (6.114)
                  D8 = -rTii Czq CI Cmcr - Cxu (Cza CmqCI  - FTII Cma, - .Czq Crru1C21)
                            + Cxa Czrr Cmq CI  - Cnrmi Cmu - Cxd C7j Cmrr Czq
                          - CxO(Czu C nCtci + Cm  ml - Cm"Czdr Cl)
                   + CxqCI(CzuCma - CzaCmu)                                       (6.115)
                           E8 = -Cxa Cm"Cz{tq - CiO(Czu Cma, - Cza Cmu)             (6.116)
The transfer function for angle of attack is given by
Aa(s)
A8e =
lTI]S - Cxu   C.rbe   -(CxqCIS + Cx0)
   -Czu       Czbt    -s(mi + CzqCl)
   -Cm"      CmSt   s(lyls - CmqCl)
Along(S)
(6.117)
                AIRPLANE RESPONSE AND CLOSED-LOOP CONTROL
                                                                                                                                                                                                 *
Expanding the determinant in the numerator, we obtain
                           Na = AarS3 + BaS2+ CaS + Da
where
                                                                   Acy  = /TI I I).l Cz8t
　
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