BAC 1-11 and MAW F-111 Control Surface Weight Estimation for SWIFT Study

The NASA sponsored Smart Wing Technology Implementation Feasibility and Transition (SWIFT) program investigated the potential usefulness of hingeless, spanwise deflection variable control surfaces using smart material based actuators to diverse platforms, including transport and high performance fighter aircraft. An important consideration for such a technology transition is the weight of the control surface, and the factors that affect the weight. Estimates of the weight of control surfaces for a BAC 1-11 airliner and the Advanced Fighter Technology Integration/Mission Adaptive Wing F-111 evaluation fighter aircraft were made based on the system designed in the Smart Wing program. These weight estimates were made using finite element models of the control surfaces, expected loads for the control surfaces in potential deployment patterns, and estimates of the power density of potential actuators that could be used in such a system. The effect of various parameters, including number of actuated control surfaced segments, material configurations, location of load application, and actuator power density, on the weight of the control system for both aircraft was investigated. From these calculations, insight into the relative impact of the various parameters on total system weight was obtained. “Final” weight estimates for each aircraft are also provided, though it is difficult to compare this figure with equivalent systems currently on the aircraft in a feasibility study such as this one.