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Conceptual Studies on Hypersonic Experimental Vehicles Using Optimal Design Method
Yasufumi Watanabe,Takeshi Tsuchiya,Hideyuki Taguchi,Syuziro Sawai 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
This paper describes conceptual studies on hypersonic experimental vehicles. In this research, we focus on studying the experimental system that provides flight test environment for Pre-Cooled Turbo Jet. The acquirements of engine operational data in flight need large Mach number and dynamic pressure. In order to find an optimal solution for the launch methods of the experimental vehicles, we analyzed two cases. Optimization calculations about the trajectory are carried out with the objective function maximizing the flight time at a speed of more than Mach 4, and bring the dynamic pressure close to 50kPa.The results obtained for the different launch methods are compared.
Multidisciplinary Optimization of Vehicle Performance and Interplanetary Trajectory
Tomokazu Konno,Takeshi Tsuchiya 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
A spacecraft which travels from the Earth to Mars is optimized using a Genetic Algorithm. This study considers a spacecraft with electric propulsion that explores into deep space. The vehicle design parameters are the distribution of vehicle mass and the distribution of electric power consumption. The mission plan is to fly from the earth to Mars and to carry out fly -by in Mars. The objective functions are total mass and flight time; thus this problem is a multiobjective optimization problem. Trade-on' curves are obtained from pareto sets. The plural purpose functions have a relation of the trade-off in many cases. The designer gets possible to grasp a trade-off between the purpose functions by watching the distribution of the pareto set of solutions. This research that the thrust direction is controlled. Moreover, suppose that coasting is performed by considering on-off of a thrust. The results when thrust is controlled and not controlled are compared.
TADASHI HASEGAWA,TAKESHI AKASAKA,YUTAKA MAEDA,MASAHIRO HASHIMOTO,MAKOTO KANDA,TAKAHIRO TSUCHIYA,TAKATSUGU WAKAHARA,YUHEI MIYAUCHI,SHIGEO MARUYAMA,JING LU,SHIGERU NAGASE 성균관대학교(자연과학캠퍼스) 성균나노과학기술원 2007 NANO Vol.2 No.4
Single-walled carbon nanotubes (SWNTs) synthesized by catalytic decomposition of an alcohol were purified by extraction. The purified SWNTs were characterized on the basis of visible-near infrared (vis-NIR) absorption, photoluminescence and Raman spectroscopic analyses, scanning electron microscopy (SEM) observation, and thermal analysis. Selective extraction of metallic nanotubes was also achieved by the extraction condition.
Real-time Trajectory Optimization for Reducing Helicopter Noise Impact on the Ground
Hiroshi Ikaida,Takeshi Tsuchiya,Hirokazu Ishii,Yoshinori Okuno 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
The purpose of this study is to obtain optimal landing approaches of helicopters that reduce the ground noise impact. In a previous study, we verified that the flights following the pre-calculated optimal trajectories with using our own noise source model resulted in lower noise impact on the ground than nominal approach paths. Detailed examination of these flights experiments. however, revealed that there were some results that did not show the predicted noise reduction effects because of unexpected external disturbances. We therefore refined the algorithms to realize more practical real-time optimization. To confirm the validity and effectiveness of the proposed optimization techniques, flight experiments were conducted again. The results showed that the noise levels predicted by proposed noise models show reasonable agreement with the measured noise levels. Furthermore. the experiments demonstrated that following the real-time optimized trajectories could decrease the ground noise impact.
Zhe Shen,Takeshi Tsuchiya 제어로봇시스템학회 2022 제어로봇시스템학회 국제학술대회 논문집 Vol.2022 No.11
Ryll’s tilt-rotor is a UAV with eight inputs; the four magnitudes of the thrusts as well as four tilting angles of the thrusts can be specified in need, e.g., based on a control rule. Despite of the success in simulation, conventional feedback linearization witnesses the over-intensive change in the inputs while applying to stabilize Ryll’s tilt-rotor. Our previous research thus puts the extra procedure named gait plan forward to suppress the unexpected changes in the tilting angles. Accompanying with Two Color Map Theorem, the tilting angles are planned robustly and continuously. The designed gaits are robust to the change of the attitude. However, this is not a complete theory before applying to the tracking simulation test. This paper further discusses some gaits following Two Color Map Theorem and simulates a tracking problem for a tilt-rotor. A uniform circular moving reference is designed to be tracked by the tilt-rotor equipped with the designed robust gait and the feedback linearization controller. The planned gaits satisfying Two Color Map Theorem in this research show the robustness. The results from the simulation show the success in tracking of the tiltrotor.
Koki Sato,Takeshi Tsuchiya 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
Qualitative analysis of human pilot's maneuvers is help of improving pilots' skills and autopilot technology. If a human pilot is assumed as a model system that works on the basis of the optimal control theory, the pilot should have its own objective function to satisfy the optimality conditions. In this study, the authors regard the objective function in the optimal control theory as the performance index of pilots and propose a new approach to obtain the objective function from the given maneuvering data. We formulate a method using the genetic programming (GP) to solve this problem. To evaluate the effectiveness of the proposed method, this study carries out simulation experiments in simple systems. This experiments demonstrate that the proposed method is effective for solving the dynamic inverse optimization.
Murata, Toshiaki,Kawatsu, Utaro,Tamura, Junji,Tsuchiya, Takeshi Journal of International Conference on Electrical 2012 Journal of international Conference on Electrical Vol.1 No.2
This paper presents a state space model of a two quadrant chopper and PWM inverter-fed Interior Permanent Magnet Synchronous Motor (IPMSM) drive system and its application to hybrid vehicles. The drive system has two different state equations for motoring and regenerating action. This paper presents a common state equation by using State Space Averaging method. Using this model of the IPMSM drive system, detailed simulation and controller design of the drive system, including PWM inverter switching, are given. The validity of this model and usefulness, according to a comparison among Maximum Torque/Ampere control, Maximum Torque/Flux control, and Maximum Efficiency optimization, are confirmed from simulation results.
Development and Evaluation of Avionics for System Identification of Small UAVs
Masaru Naruoka,Takuma Hino,Ryota Nakagawa,Takeshi Tsuchiya,Shinji Suzuki 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
A new avionics tor system identification of small unmanned aerial vehicles (UAVs) is proposed in this paper. The proposed avionics consists of three parts: 1) MEMS INS/GPS navigation unit, 2) air data sensor, and 3) command logger. The accuracy and error models of the components are obtained experimentally with a prototype device, and the total performance is evaluated with Monte Carlo simulations which solve the longitudinal stability derivatives of a small UAV with the obtained error model. Furthermore, a real flight log obtained by the prototype device is analyzed. The results shows that the proposed avionics is accurate enough 10 analyze the flight characteristic of small UAVs with the system identification techniques.