曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

                          S4 + (5.0574 + k4)S3 + (13.1052 + k3)S2 + (0.3860 + k2)S
                               + (0.5918 + ki) : 0                                                             (6.328)
Comparing the coefficient of Eqs. (6.302) and (6.328), we obtain
ki -0.0417     k2 - 8.1452     k3 -17.5033     k4 -
                            X = (A - BK P)X + Br(t)
                               = AX + B [r(t) - KPX]
This gives us the desired full-state feedback control law as
                                             U -. r(t) - K PX
4.8426  (6.329)
riginal state-space.
 we obtain
(6.330)
(6.331)
(6.332)
O
 1
O
1
0
O
     Then next step is to do a reverse transformation back to the o
Substituting for Z, Ap, and Bp in Eq. (6.307) and rearranging,

-0.5544 ]
0.0132
0.0463
0.0177 J
604  .          PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
                                                                                                          Basic System
                                                    -_ Full-StateFeedback
LongitudInal Full-State Feedback Design for GA Alrplana
8
d
<
                        .                    ...l    
┏━━━━━━━━━━━━━━━━━━┳━━━━━━┓
┃                           .        ┃            ┃
┃                                 .  ┃            ┃
┣━━━━━━━━━━━━━━━━━━╋━━━━━━┫
┃37  ;-' .                           ┃        ll, ┃
┗━━━━━━━━━━━━━━━━━━┻━━━━━━┛
Fig. 635    Longitudinal response of the full-state feedback controller for the general
aviation airplane.
      To verify the design, we have performed a simulation ofthe free response [r (t) =
OJ using MATLABI  for the initial conditions Au  - 5 deg, u  - 0, 0  = q  = 0. The
results are shown in Fig. 6.35. We observe that the system with full-state feedback
law performs as expected.
　
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