Dynamic characteristic analysis and force loop design for the aerodynamic load simulator

A dynamic load simulator which can reproduce, on-ground, the aerodynamic hi nge moment of control surface, is an essential rig for performance and stab ility 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 withi n some accuracy bounds, a force controller is designed based on the Quantit ative Feedback Theory (QFT). A dynamic model of load actuation system is de rived, and compared with the experimental results. Through this comparison, a nominal plant model of load actuation system with some uncertainty bound s is developed. The efficacy of QFT force controller is verified by numeric al simulation, in which hydraulic actuation system dynamics of aircraft con trol surface is considered.