The report presents the results of a study program to apply linear optimal control theory to the problems of control blending (phasing) and attitude stabilization and control for VTOL aircraft. The Bell X-22A was used as the application vehicle. Optimal control blending, the phasing of the controls required at hover into those required in conventional flight in such a way as to minimize the cost of control, was solved in general. The stabilization and control problem was approached by applying three different design techniques based on linear optimal control theory: model in the performance index technique, root locus technique, pilot control task technique. These designs were practicalized and evaluated with a piloted simulation which included nonlinear aerodynamic and control characteristics. The different techniques considered showed varying degrees of success in yielding good designs from a handling qualities standpoint. The model in the performance index technique was found to be the most immediately useful, and was treated in the greatest detail. (Author)


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