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Shigeru Sunada,Makoto Okamoto,Hiroshi Tokutake 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
The coefficient of α². Δ₂, of drag coefficient of a wing CD(α)(?CD(CL =0)+Δ₂(α-α?)²) increases with the decrease of Re. Comparison between airfoil characteristics (two-dimensional) and wing characteristics (three-dimensional) shows this increase is mainly caused by the increase of profile drag of the airfoil. The increase Δ₂ of a wing affects the relation between a dihedral angle and stability of dutch roll mode as follows: (1) When Δ₂ is large, dutch roll mode becomes more stable with increasing a dihedral angle. (2) When Δ₂ is smaller than the value stated in (1), dutch roll mode becomes more unstable at a small dihedral angle and, conversely, it becomes more stable at a large dihedral angle.
Experimental Study on Autonomous Lifting-body Type Airplane in Osaka Prefecture University
Hiroshi Tokutake,Shuichi Okada,Shigeru Sunada 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
A lifting-body type reentry vehicle has several advantages; however, it lacks natural stability. Therefore, a high-performance night control system is required. Our research group working on an unmanned aerial vehicle in Osaka Prefecture University focused on the flight control system of a small lifting-body type airplane. The flight model was built and the night dynamics were modeled using wind tunnel testing. In addition, a small control board with functions for autonomous flight was developed. Next, a robust flight controller was designed, and the flight testing during landing verified the performance of the developed flight control system.
Disturbance Prediction and Its Application to H<SUB>∞</SUB> Flight Control
Shuichi Okada,Hiroshi Tokutake,Shigeru Sunada 제어로봇시스템학회 2009 제어로봇시스템학회 국제학술대회 논문집 Vol.2009 No.8
An output-feedback H∞ preview controller is proposed. The controller predicts disturbance responses by considering the disturbance derivatives and generates the optimal control input that minimizeste H∞ norm of the closed-loop transfer function. By assuming a disturbance response with out a future control input, a design problem is for mulated as a standard H∞ problem. The disturbance information that the controller requires is obtained by a disturbance observer. The proposed controller is combined with the disturbance observer and applied to the flight control of the lifting-body airplane dynamics. Simulation results show the effectiveness of the proposed system.
Shuichi Okada,Hiroshi Tokutake,Shigeru Sunada 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
An observer-based disturbance estimation method was developed. The polynomial approximation of disturbance was introduced, and the observer gain was optimized so that the H-infinity norm of the estimation error was minimized. In this method, the estimated disturbance was adjusted using the estimated output error at several arbitrary time points. The proposed method was applied to aircraft dynamics and verified by numerical simulation.