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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
by
A ).2 0.2 O O -
)1.0
) -8.0 0
)00
)
A l*5 0 _
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