Abstract
A dynamic load simulator which can reproduce, on-ground, the aerodynamic hinge moment of control surface, is an essential rig for performance and stability test of aircraft actuation system. The hinge moment varies widely in the flight envelope depending on specific flight condition and maneuvering status. To replicate the wide spectrum of this hinge moment variation within some accuracy bounds, a force controller is designed based on the Quantitative Feedback theory (QFT). A dynamic model of load actuation system is derived, and compared with the experimental results. Through this comparison, a nominal plant model of load actuation system with some uncertainty bounds is developed. The efficacy of QFT force controller is verified by numerical simulation, in which hydraulic actuation system dynamics of aircraft control surface is considered.
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