The dynamic system which expresses lateral-directional motion of an airplane constructs a typical multivariable system, so-called P-canonical structure in which each of the outputs is expressed as explicitly and wholly dependent upon all of the inputs.
In this study, an reference model was introduced to the dynamic system and the method of variational calculus was applied under condition such as the accumulated quantity of error signal between the model and the practical airplane dynamics would be restricted.
The control actions were based on the error signals and their derivatives, so that the optimal control system was synthesized. And further, it was shown that the realization of such a control would be possible under condition of comparatively small acceleration without making increment of the settling time.
At the end of this study, a numerical example was shown, in which the difference of responses was illustrated between the cases that the dynamic system would be carried out an ordinary feedback control and such as the optimal control.