曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
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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PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL4(6)
