@techreport{oai:jaxa.repo.nii.ac.jp:00043989,
 author = {永安, 正彦 and 山崎, 昭司 and 森田, 一雄 and NAGAYASU, Masahiko and YAMAZAKI, SHOJI and MORITA, KAZUO},
 month = {Feb},
 note = {This paper describes an application of the steady state decoupling control to the experimental STOL airplane,which has been developed by the National Aerospace Laboratory.Firstly,the design procedures of the decoupled control system using state-feedback or output-feedback are presented.Then the design procedures are applied to the flight control system of the STOL airplane.The linearized longitudinal equation of motion is dealt with.Engine thrust,elevator and/or USB flap are to be available as controls,and airspeed,flight path angle and/or pitch angle are controled in decoupled fasion.The case that angle of attack and air speed are not measurable is studied as output-feed back control.Simulation results show good performance for both state-and output-feedback control systems., 資料番号: NALTM0406000, レポート番号: NAL TM-406},
 title = {定常非干渉制御のSTOL機縦制御への応用},
 year = {1980}
}