Output tracking for a non-minimum phase dynamic CTOL aircraft model
Tomlin, C.
Lygeros, J.
Benvenuti, L.
Sastry, S.
Dept. of Electr. Eng. & Comput. Sci., California Univ., Berkeley, CA;
This paper appears in: Decision and Control, 1995., Proceedings of the 34th IEEE Conference on
Publication Date: 13-15 Dec 1995
Volume: 2,
On page(s): 1867-1872 vol.2
Meeting Date: 12/13/1995 - 12/15/1995
Location: New Orleans, LA, USA
ISBN: 0-7803-2685-7
References Cited: 11
INSPEC Accession Number: 5177580
Digital Object Identifier: 10.1109/CDC.1995.480615
Current Version Published: 2002-08-06
Abstract
A dynamic model for the longitudinal axis of a conventional
takeoff and landing (CTOL) aircraft is presented. Non-minimum phase
characteristics in this model result from the fact that the process of
generating an upward pitch moment produces a small downward force,
causing the aircraft to lose altitude. The model is not full state
linearizable and the internal dynamics which remain after input-output
linearization using the coordinates of the center of mass as outputs are
unstable. The CTOL model is not flat with respect to fixed points on the
aircraft body. The nonlinear inversion technique produces stable
trajectories for the states of the internal dynamics, but the
corresponding feedforward force inputs required to track these
trajectories are large. Approximate linearization techniques which
ignore the coupling between the pitch moment and the vertical and
horizontal aircraft dynamics, may be used to calculate inputs of smaller
magnitude
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