Optimal Variable Wing Camber Control using Incremental Nonlinear Dynamic Inversion
T.S.C. Pollack (TU Delft - Control & Simulation)
EJ van Kampen (TU Delft - Control & Simulation)
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Abstract
Flight control systems enable the improvement of natural flying qualities and airframe performance of an aircraft. In this article, an incremental optimization control scheme is proposed to optimize a given performance objective set by the designer in an online fashion using limited model information. This scheme is applied to improve the aerodynamic efficiency levels of the General Dynamics F-16 by optimizing symmetric movement of the leading edge flap (LEF) devices, based on an open-source nonlinear simulation model. Other design goals are addressed by refining the control objective, which explicitly embeds design trade-offs in the control law. A complete control architecture is arrived at through the design of a parallel INDI control law that performs the function
of angular rate control to improve natural flying qualities. A nonlinear simulation scenario shows that the proposed control framework is capable of meeting desired handling quality characteristics while simultaneously improving aerodynamic efficiency levels and control activity. In addition, a robustness assessment is performed to gain insight into the sensitivity of the design to
on-board model offsets.
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