ヒンジレス・ロータ・ヘリコプタに対する安定性及び操縦性増大装置に関するフライト・シミュレータ実験について

Abstract

A stability and control augmentation system designed analytically in Reference (1) was evaluated on the NASA Ames Flight Simulator for Advanced Aircraft. Linear optimal control theory was applied to determine appropriate feedback gains for the stability augmentation system. A least square design method was then applied to determine partial crossfeed gains for the control augmentation system. The augmentation system thus designed was evaluated experimentally in the piloted simulation tests. Handling qualities of the augmented as well as the unaugmented helicopter were investigated in the following flight tasks involving both visual and instrument flights: NOE (nap-of-the-earth) maneuvers, VOR approaches and a set of basic maneuvers. Experimental data show that handling qualities of the augmented helicopter were substantially improved as compared with those of the basic helicopter.