| dc.description |
A novel procedure for the optimization of aircraft
autostabilizer systems is presented. The procedure is
straightforward, and its application does not result in
demands for autostabilizer systems of prohibitive complexity.
Many important non-linear effects may be included with only
slight extra complication in the required calculations. The
procedure is applicable, in the first place, to piloted aircraft,
- the essence of the procedure being the assumption that the
purpose of thy: autostabilizer is to reduce the effort demanded
of the pilot in executing a given manoeuvre or attaining a
given response. Although the presence of the pilot is
explicitly taken into account in the calculations no form
of pilot's transfer function need be specified.
It is shown how the procedure may be modified to form
an approximate procedure for the optimization of autostabilizers
for pilotless aircraft having linear autostabilizer characteristics
and linear aircraft dynamics. The results of some
calculations presented herein support a suggestion that this
approximate optimization procedure may also be frequently
applied with success to pilotless aircraft having certain
non-linearities, either in the autostabilizer system or in
the aircraft dynamics. |
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