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Development of Flight Simulator for Human-Powered Aircraft
Yasuhiro Inaba,Yuzo Shimada,Kenji Uchiyama,Kenichi Abe,Yoshio Ishikawa,Takao Sugimoto,Yasuyuki Miyazaki,Yuzo Koyama,Shohei Onishi,Kazuo Matubara,Chikatoshi Satoh,Takao Minejima,Kaname Hirayanagi,Michi 제어로봇시스템학회 2006 제어로봇시스템학회 국제학술대회 논문집 Vol.2006 No.10
Design of Nonlinear Attitude Control System for Spaceplane Using Disturbance-Accommodating Control
Yuta Akai,Yuzo Shimada,Kenji Uchiyama,Akio Abe 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
In this paper, we describe a design of robust attitude controller for a spaceplanc based on feedback linearization. The feedback linearization method with a timescale separation concept has attracted research interest regarding the design of attitude control systems for aircrafts including spaceplanes. The features of this technique are the elimination of the need for any approximation in the linearization of the vehicle's dynamics and the coverage of a wider flight region. However. since this technique involves the cancellation of the nonlinear dynamics, the accuracy of the cancellation cannot be guaranteed in the presence of changes in aerodynamic and other uncertainties. Therefore, we propose the application of a nonlinear control law. which deals with the feedback linearization, using disturbance-accommodating control (DAC). Unmodeled phenomena are estimated as a new state variable by a DAC observer. Furthermore, the sensitivity function and the complementary sensitivity function in the frequency domain are shaped to design the DAC observer. Finally, Monte-Carlo simulations were performed to verify the effectiveness of the proposed attitude control law.
Development of Flight Simulator for Human-Powered Aircraft (Second Report)
Yutaro Tsugawa,Yuzo Shimada,Akio Abe,Kenichi Abe 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
A special-purpose flight simulator of a human-powered aircraft (HPA) was planned and developed in 2005-2006. and installed for the first time at Nihon University in Japan in 2007 lor pilot training, the analysis of flight characteristics. and the optimal design of an HPA. Since the installation of the simulator, we have focused on improving its accuracy. However. unlike a general aircraft, an HPA generates the thrust through the pilot pedaling the propeller. Therefore, to develop a mathematical model of an objective HPA, we clarified the mathematical relationship between the torque generated by the pilot and the propeller thrust. In addition, to realize a more accurate simulation of the motion of an actual HPA, aerodynamic coefficients were evaluated using estimation equations for a conventional aircraft. The airframe data of the HPA used were those of Miiwe 22 produced by a Nihon University student team in 2004. The result of stability analysis showed that the HPA has an unstable spiral mode under lateral motion. This result coincides with the unstable behavior of another HPA (Mowe 24) flied in 2007 when subjected to lateral wind. To improve the instability of the lateral motion, we provide to a pilot with a voice command and verify whether the new method stabilizes the lateral motion using a flight simulator.