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
┃ . ┃ ┃ ┃ ┃ ┃
┃ ┃k ┃ ┃ ┃ ┃
┃ ┃ \ ┃ ┃ ┃ ┃
┃ ┃ \ ┃ ┃ ┃ ┃
┃ ┃ . ┃ ┃ ┃ ┃
┃ ┃ . ┃ ┃ ┃ ┃
┃ ┃ - ┃:- -- ┃ ┃ ┃
┃ ┃ ┃ I ┃ III ┃ . . ┃
┗━━━━━━┻━━━┻━━━┻━━━━━━━━━┻━━━━━━━━━━━━━━━━━━┛
o 0.2 Q.4 0.6 0.8 1 1.2 1.4 1.6 1.8 2
Ume, s
Fig. 5.45 Response of full-state observer of Example 5.16.
The performance of the observer for the given initial conditions of xi(0) = 5,
xz(0) = 1.5, and X3(0) = 0.25 and to the input r(t) : 25t is shown in Fig. 5.45
using MATLAB.4 We note that the observer performs as expected.
5.11 Summary
In this chapter, we have reviewed the basic principles of linear systems and
illustrated the theory with a number of solved examples. This background will be
useful in the study of aircraft dynamics and control. We will derive longitudinal
and lateral-directional transfer functions and study the free response of the aircraft.
We will also use the design methods we havelearned here for the design of stability
augmentation systems and automatic fiight control systems of the aircraft to obtain
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL3(88)
