Download AeroSim Blockset User`s Guide - RIT - People

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AeroSim Blockset User’s Guide
AIRCRAFT MODEL DEMOS
Heading =
Altitude =
0.02 deg
200.00 m
Lateral-directional Dynamics
-----------------------------State vector: x = [v p r phi psi]
Input vector: u = [aileron rudder]
Output vector: y = [beta p r phi psi]
State matrix: A =
-0.6373
1.5135 -22.9498
9.7967
-4.1919 -20.6283
9.9282
0
0.6798
-2.6757
-1.0377
0
0
1.0000
0.0659
-0.0000
0
0
1.0022
-0.0000
Extracting aircraft linear model...
Longitudinal Dynamics
----------------------State vector: x = [u w q theta h Omega]
Input vector: u = [elevator throttle]
Output vector: y = [Va alpha q theta h]
State matrix: A =
-0.2197
0.6002
-1.4882
-9.7967
-0.5820
-4.1204
22.4024
-0.6461
0.4823
-4.5284
-4.7512
0
0
0
1.0000
0
0.0658
-0.9978
0
22.9997
32.1012
2.1170
0
0
-0.0001
0.0009
0.0000
0
0
-0.0295
0.0108
0
-0.0084
0
0
-2.7813
Control matrix: B =
0.3246
0
-2.1520
0
-29.8216
0
0
0
0
0
0 448.5357
Observation matrix: C =
0.9978
0.0658
0
-0.0029
0.0434
0
0
0
1.0000
0
0
0
0
0
0
Control matrix: B =
-1.2510
3.1931
-109.8373
1.9763
-4.3307 -20.1754
0
0
0
0
Observation matrix: C =
0.0435
0
0
0
1.0000
0
0
0
1.0000
0
0
0
0
0
0
0
0
0
1.0000
0
0
0
0
0
1.0000
0
0
0
0
0
0
0
0
0
0
0
0
0
1.0000
0
0
0
0
0
1.0000
Eigenvalue: -19.7263
Time constant = 0.0507 s
Eigenvalue: -1.3190 +/- 5.5958 i
Damping = 0.2294, natural frequency = 5.7492 rad/s, period =
Eigenvalue: 0.0611
Time constant = -16.3757 s
1.1228 s
Eigenvalue: -4.4337 +/- 10.1009 i
Damping = 0.4019, natural frequency = 11.0311 rad/s, period =
0.6220 s
Eigenvalue: -2.8950
Time constant = 0.3454 s
Eigenvalue: -0.0549 +/- 0.5690 i
Damping = 0.0961, natural frequency = 0.5716 rad/s, period = 11.0431 s
Eigenvalue: -0.0005
Time constant = 1931.1123 s
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