Post on 24-Apr-2022
Brigham Young UniversityBYU ScholarsArchive
All Faculty Publications
1999-8
Nonlinear Robust Missile Autopilot Design UsingSuccessive Galerkin ApproximationTimothy McLainMechanical Engineering Department, Brigham Young University, mclain@byu.edu
Randal W. BeardDepartment of Electrical and Computer Engineering, Brigham Young University, beard@ee.byu.edu
Follow this and additional works at: https://scholarsarchive.byu.edu/facpubPart of the Mechanical Engineering Commons
Original Publication CitationMcLain, T. and Beard, R. Nonlinear Robust Missile Autopilot Design Using Successive GalerkinApproximation, Proceedings of the AIAA Guidance, Navigation, and Control Conference,AIAA-1999-3997, August 1999, Portland, Oregon.
This Conference Paper is brought to you for free and open access by BYU ScholarsArchive. It has been accepted for inclusion in All Faculty Publicationsby an authorized administrator of BYU ScholarsArchive. For more information, please contact scholarsarchive@byu.edu, ellen_amatangelo@byu.edu.
BYU ScholarsArchive CitationMcLain, Timothy and Beard, Randal W., "Nonlinear Robust Missile Autopilot Design Using Successive Galerkin Approximation"(1999). All Faculty Publications. 1935.https://scholarsarchive.byu.edu/facpub/1935
Fz
My
V
α
δ
z
0 0.2 0.4 0.6 0.8 1−50
0
50
100
150Pitch Rate
time (s)
q (d
eg/s
)
0 0.2 0.4 0.6 0.8 10
5
10
15
20Angle of Attack
time (s)
α (d
eg)
µ=0, ν=0µ=3, ν=3µ=.25, ν=.25µ=.25, ν=3µ=3, ν=.25
0 0.2 0.4 0.6 0.8 1−600
−400
−200
0
200
400Fin Deflection Rate
time (s)
dδ/d
t (de
g/s)
0 0.2 0.4 0.6 0.8 1−20
−15
−10
−5
0
5Fin Deflection
time (s)
δ (d
eg)
0 0.2 0.4 0.6 0.8 10
20
40
60
80
100
120
140Pitch Rate
time (s)
q (d
eg/s
)
0 0.2 0.4 0.6 0.8 10
5
10
15
20Angle of Attack
time (s)
α (d
eg)
0 0.2 0.4 0.6 0.8 1−20
−15
−10
−5
0
5Fin Deflection
time (s)
δ (d
eg)
0 0.2 0.4 0.6 0.8 1−0.4
−0.2
0
0.2
0.4
0.6Worst−case Parameter Variations
time (s)
µ &
ν
µν