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                                                                     -(5.25 s + 3.15)
                                              Go(s) =  s~2 25 s2 + 3. .15 s + 6.53)
                   -(0.04s2+4s) .
                               Gcr(s): s~2 25s2+3 15s+6 53~
Design (a) a pitch displacement autopilot to give level I handling qualities and (b)
an altitude-hold autopilot for acceptable handling qualities.
6.4   A light airplane has the following longitudinal transfer functions:
                                                                -(0.2 S3 + lOS2 +  S + 1.5)
                                 G",(s) : ~4+4 3+2  2+0~5 s _ O.l)
                                                                       -(10 S2 + 20 s + 1.5)
                  N
                                        Go(s) :  ~S4+4 S3+2 s2+0~5 s - O-l)
Determine the longitudinal eigenvalues,ls the airplane longitudinally stable? If not,
design a suitable pitch augmentation system so that the airplane has conventional
short-period and phugoid modes in the closed-loop sense.
AIRPLANE RESPONSE AND CLOSED-LOOP CONTROL          625
6.5     The transfer function of an airplane for yaw rate to rudder deflection is given
by'
                                                        rls)          =(4.5 s + 0.75)
                         A8r(S) = ~S2+ ls+4.2)
Design a yaw damper to give levell Dutch-roll flying qualities.
6.6    The         itudinal dynamics of an anrplane                      ce form is
 .050

                    2.5  1.0  -0.
                     5-0 -3.5  O.C
                    10
            ~
     A
 Design a full  state feedback controller to give a frequency of5.0 racVs and damping
 ratio of 0.8 for the short-period mode and a frequency of 0.15 rad/s and damping
 ratio of 0.15 for the phugoid mode.
6.7   The lateral-directional dynamics of an airplane in state-space form is given
　
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