In typical aircraft, longitudinal flight linearization can be modelled using a second- order system as in Figure Q3(a)(i). Figure Q3(a)(i) shows pole zero map on s- plane for the second-order system of the unit step. By referring to the pole-zero location, Determine the type of second-order response and sketch the nature of step response of the system. Solve for the damping ratio, Cand natural frequency, h. H) Find the values of percent overshoot, %OS and peak time, Tp in) Find the closed loop transfer function and calculate the unknown gains, K, and K. 0.2 K. Co) s(s+ 1) s+1 Figure Q3(a)(i) 5.44 2 4.41 5.44
In typical aircraft, longitudinal flight linearization can be modelled using a second- order system as in Figure Q3(a)(i). Figure Q3(a)(i) shows pole zero map on s- plane for the second-order system of the unit step. By referring to the pole-zero location, Determine the type of second-order response and sketch the nature of step response of the system. Solve for the damping ratio, Cand natural frequency, h. H) Find the values of percent overshoot, %OS and peak time, Tp in) Find the closed loop transfer function and calculate the unknown gains, K, and K. 0.2 K. Co) s(s+ 1) s+1 Figure Q3(a)(i) 5.44 2 4.41 5.44
Introductory Circuit Analysis (13th Edition)
13th Edition
ISBN:9780133923605
Author:Robert L. Boylestad
Publisher:Robert L. Boylestad
Chapter1: Introduction
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Transcribed Image Text:In typical aircraft, longitudinal flight linearization can be modelled using a second-
order system as in Figure Q3(a)(i). Figure Q3(a)(ii) shows pole zero map on s-
plane for the second-order system of the unit step. By referring to the pole-zero
location,
Determine the type of second-order response and sketch the nature of step
response of the system.
Solve for the damping ratio, Çand natural frequency, wn.
i) Find the values of percent overshoot, %0S and peak time, Tp
iv)
Find the closed loop transfer function and calculate the unknown gains, K.
and K.
RIs).
0.2
Co)
K,
s(s + 1)
Ks
Figure Q3(a(i)
Pt Me
+,5.44
4.415
5.44
-6
A
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