小型QTW無人航空機の飛行制御則設計

Abstract

This paper is concerned with the design of Stability/Control Augmentation System (S/CAS) for small Quad Tilt Wing (QTW) Unmanned Aerial Vehicle (UAV) which has been developed as a test bed for guidance and control system demonstrations. We design the basic S/CAS for the aircraft using our previously proposed design method. By comparing the eigenvalues of linearized motions of the newly developed and the previously developed QTWUAVs, the effectiveness of our method for S/CAS design is illustrated. We also show the flight test results using our S/CAS.