Optimal Input Design for Aircraft Parameter Estimation — Flight Test Results

In this work, optimal control methods were applied to design inputs for system identification that maximize the information content during a given maneuver time. The method relies on a dynamic programming approach and the direct method for optimal control. Optimal inputs for the identification of a linear lateral/directional model of the Remos GX general aviation aircraft were designed and injected using an actuator system in flight. For comparison, the same flight test also included orthogonal phase-optimized multisine excitations, designed over a range of relevant frequencies for the system. The two input design methods, along with the generated results from each approach, are compared to highlight their capabilities and to develop practical guidelines for aircraft flight testing.