The longitudinal dynamics of the aircraft is defined by: x = Ax+ Bu, A = 0 0 0 -0.05 0 0 0 0.05 0 -0.3 B =B₁ = [ 0 B=B₂ =[ 0 1 -0.2 0 0 0 0 0 1 -1 1 -1 0.1 0 -1 -0.7 0.001 0 0 0 0 1² 0 0 -2 -0.11² " With the thrust only input or the elevator only input, the corresponding B matrices are: y = Cx For measurements of either the altitude, speed or pitch angle, the corresponding C matrices are: C=Ca=[1 0 0 0 o], C=C₁ = [0 1 0 0 0], C=C₂ = [0 0 1 0 0]
The longitudinal dynamics of the aircraft is defined by: x = Ax+ Bu, A = 0 0 0 -0.05 0 0 0 0.05 0 -0.3 B =B₁ = [ 0 B=B₂ =[ 0 1 -0.2 0 0 0 0 0 1 -1 1 -1 0.1 0 -1 -0.7 0.001 0 0 0 0 1² 0 0 -2 -0.11² " With the thrust only input or the elevator only input, the corresponding B matrices are: y = Cx For measurements of either the altitude, speed or pitch angle, the corresponding C matrices are: C=Ca=[1 0 0 0 o], C=C₁ = [0 1 0 0 0], C=C₂ = [0 0 1 0 0]
Introductory Circuit Analysis (13th Edition)
13th Edition
ISBN:9780133923605
Author:Robert L. Boylestad
Publisher:Robert L. Boylestad
Chapter1: Introduction
Section: Chapter Questions
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Question
Is the uncontrolled, open loop system?
a.unstable
b.not asymptotically stable
c.asymptotically stable
d.unstable
![The longitudinal dynamics of the aircraft is defined by:
x = Ax+Bu, A=
B=B₁ = [0
B = BE = [0
For measurements
C=C₁ = [1
Ca
C=C₁ = [0
O a.
0
0
0
0
0
0
-0.05
0
0.05
-0.3
With the thrust only input or the elevator only input, the corresponding B matrices are:
unstable
1 0 0 0],
0 1 0 0]
0.001 0001
0 0 -2 -0.1]
C=C₂ = [0
Is the uncontrolled, open loop system?
d. unstable
1
-0.2
0
0
0
0
0
1
−1
1
of either the altitude, speed or pitch angle, the corresponding C matrices are:
0 0 0 0],
O b. not asymptotically stable
O c. asymptotically stable
-1
0.1
0
-1
-0.7
"
y = Cx](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2Fdf6bbd7c-5d08-4329-80df-c691787490e9%2F70ab3cc4-87ba-4b72-baa2-82fe83f652b6%2Fn0abt7q_processed.png&w=3840&q=75)
Transcribed Image Text:The longitudinal dynamics of the aircraft is defined by:
x = Ax+Bu, A=
B=B₁ = [0
B = BE = [0
For measurements
C=C₁ = [1
Ca
C=C₁ = [0
O a.
0
0
0
0
0
0
-0.05
0
0.05
-0.3
With the thrust only input or the elevator only input, the corresponding B matrices are:
unstable
1 0 0 0],
0 1 0 0]
0.001 0001
0 0 -2 -0.1]
C=C₂ = [0
Is the uncontrolled, open loop system?
d. unstable
1
-0.2
0
0
0
0
0
1
−1
1
of either the altitude, speed or pitch angle, the corresponding C matrices are:
0 0 0 0],
O b. not asymptotically stable
O c. asymptotically stable
-1
0.1
0
-1
-0.7
"
y = Cx
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