OPTIMAL ACTUATION RESEARCH AND STUDY
Final rept. 1 Mar 1966-1 Feb 1967
DOUGLAS AIRCRAFT CO INC SANTA MONICA CA MISSILE AND SPACE SYSTEMS DIV
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The servo actuating and corresponding energy distribution subsystem comprise approximately 80 of an aircrafts flight control system weight. Consequently, whenever subsystem tradeoff studies are conducted it is desirable to select the optimum design with respect to weight and other similar parameters. This study investigates and develops such an optimal design process. A sample problem was selected and an optimal technique formulated and applied to the problem. The sample problem was a fixed-configuration hydraulic actuation and power system. The study objectives were to optimize weight, dollar cost, size, dynamic performance, and reliability as a function of the systems independent design parameters. The parameters included pressure, actuator area, actuator torque arm, and plumbing tube sizes. Parameter optimization was accomplished by fixed grid and random searching techniques. Within the framework of parameter optimization, a design philosophy was formulated which allowed dissimilar terms e. g., weight in pounds and dollar cost in dollars to be combined to form a total performance criterion for the system.