DocumentCode
3550547
Title
Design of a missile autopilot using adaptive nonlinear dynamic inversion
Author
Hindman, Rick ; Shell, William M.
Author_Institution
Raytheon Missile Syst., Tucson, AZ, USA
fYear
2005
fDate
June 8-10, 2005
Firstpage
327
Lastpage
332
Keywords
aerodynamics; feedback; interpolation; inverse problems; missile guidance; model reference adaptive control systems; nonlinear dynamical systems; robust control; ANDI autopilot; adaptive element; adaptive nonlinear dynamic inversion; aerodynamic modeling; gain table; gain values; interpolation; missile autopilot; missile flight condition; missile flight envelope; parameter variation; reference model; robustness; stability; three loop feedback topology; Actuators; Aerodynamics; Artificial neural networks; Error correction; Feedback loop; Interpolation; Missiles; Performance gain; Robust stability; Topology;
fLanguage
English
Publisher
ieee
Conference_Titel
American Control Conference, 2005. Proceedings of the 2005
ISSN
0743-1619
Print_ISBN
0-7803-9098-9
Electronic_ISBN
0743-1619
Type
conf
DOI
10.1109/ACC.2005.1469954
Filename
1469954
Link To Document