Referenced Items are not available for this document.
A flight controller is designed for a twin rotor helicopter model, and the property is examined by experiments. The model has a simlar structure to that of VTOL aircraft. It is not linearizable by static state feedback but linearizable by dynamic state feedback. The design method accomplishes partial linearization by applying static feedback linearization to the main and the lower subsystems hierarchically. The controller has the same structure as the structure previously derived by back stepping. Experiments show the effectiveness
Published in:
Control Applications, 1999. Proceedings of the 1999 IEEE International Conference on
(Volume:1
)
Date of Conference: 1999
- Page(s):
- 146 - 151 vol. 1
- Meeting Date :
- 22 Aug 1999-27 Aug 1999
- Print ISBN:
- 0-7803-5446-X
- INSPEC Accession Number:
- 6468216
- Conference Location :
- Kohala Coast, HI
- Digital Object Identifier :
- 10.1109/CCA.1999.806166
- Product Type:
- Conference Publications
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