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

discuss the design of a pitch stabilization system to make the aircraft closed-loop
stable in pitch.
    In Fig. 6.31a, the schematic diagram of a typical pitch stabilization system is
shown and, in Fig. 6.31b, its block diagram implementation is presented. The
 elevator servo is approxirnated as a first-order lag with a break frequency a -. 10
rad/s. We have an inner loop with angle of attack feedback and an outer loop with
pitch rate feedback. The putpose of the inner-loop alpha feedback is to make the
aircraft statically stable. The outer-loop pitch rate feedback enables us to select
a suitable value of the damping ratio so that the aircraft has the desired level of
longitudinal handling qua7ities in the closed-loop sense.
    To illustrate the design procedure, we consider the statically unstable version
of the general aviation airplane. Here, we consider the transfer function of the
complete (fourth-order) system because the short-period approximation is not
a) Schematic diagram
                                                                                                                                   
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