Force control system design for aerodynamic load simulator

摘要

A dynamic load simulator which can reproduce on-ground the aerodynamic hinge moment of control surface is an essential rig for the performance and stability test of an aircraft actuation system. The hinge moment varies widely over the flight envelope depending on the 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 verified through the experiment. The efficacy of QFT force controller is verified by a numerical simulation, in which combined aircraft dynamics, flight control law and hydraulic actuation system dynamics of aircraft control surface are considered.