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Position and Attitude Feedback Controller of a Planar Satellite with Two Thrusters
Takashi Matsuno,Shinji Hokamoto 제어로봇시스템학회 2009 제어로봇시스템학회 국제학술대회 논문집 Vol.2009 No.8
This paper proposes a feedback control method for the in-plane motion of a satellite equipped with two thrusters, whose force directions are fixed to the satellite. The satellite’s equations of motion have second-order nonho-lonomic constraints. This paper utilizes an invariant manifold and develops a feedback controller based on the Lyapu-nov’s second method. The developed controller can control the satellite’s state composed of six components for the po-sition and attitude angle by two thruster systems. Furthermore, the controller has robustness for the system’s modeling errors. Some simulations results are shown to demonstrate the effectiveness of the developed controller.
Optimal and Robust Design of Plasma Actuator for the Control of a Cylinder Wake
Takashi Matsuno,Kentaro Ota,Takashi Kanatani,Hiromitsu Kawazoe 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
The performance of the plasma actuators for wake control and resulting drag reduction is examined and the optimization of the driving conditions of the plasma actuators were carried out by using the robust design method for wake control at high dynamic pressure conditions. The parameter design method that we used is feasible for the optimization of the control variables for flow control, under the situation that has multiple input parameters, requiring robustness, and complexity in flow phenomenon. The result of the design method gives the predicted optimal condition for reduced control parameters and that is confirmed to be robust and stable to the application test.
Guidelines for Human Interface Design of Rescue Robots
Yasuyoshi Yokokohji,Takashi Tubouchi,Akichika Tanaka,Tomoaki Yoshida,Eiji Koyangi,Fumitoshi Matsuno,Shigeo Hirose,Hiroyuki Kuwahara,Fumiaki Takemura,Takao Ino,Kensuk Takita,Naoji Shiroma,Tetsushi Kame 제어로봇시스템학회 2006 제어로봇시스템학회 국제학술대회 논문집 Vol.2006 No.10
Aggregation States of Polyamide 4 Thin Films under an Aqueous Environment
Shunta Tamura,Haruki Mokudai,Takashi Masaki,Norifumi L. Yamada,Hisao Matsuno,Keiji Tanaka 한국고분자학회 2021 한국고분자학회 학술대회 연구논문 초록집 Vol.46 No.2
Polyamide 4 (PA4) having only four carbons between neighboring amide groups exhibits enhanced biodegradability, and thus, has been studied as one of candidates for eco-friendly structural materials. However, the biodegradation mechanism for PA4 is far clear for a moment. We here examined the aggregation states of PA4 thin films coated on a hydrophobized SiOx substrate using atomic force microscopy (AFM) and neutron reflectivity (NR) analyses in air and water environments. AFM observation revealed that the outermost surface of the PA4 film was featureless and flat at a nanometer level. Once the film was immersed into water, the thickness increased by approximately 1.1 times. NR made it clear that the PA4 film was swollen due to the water sorption in the film, and that there existed multiple layers having different densities along the direction normal to the interface. Effect of annealing temperature on such the aggregation states and the degradability will be also discussed.
Unstructured-Mesh-Based Simulation for Subsonic and Supersonic Flow Control with a Plasma Actuator
Junya Yamamoto,Koji Shimoyama,Shinkyu Jeong,Shigeru Obayashi,Takashi Matsuno,Hiromitsu Kawazoe 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
A plasma actuator is a simple device that can control flow with low power supply, so this is very practical and several applications have been proposed by many researchers. In this paper, a numerical method for simulating the flow with a plasma actuator is proposed, and it is applied to supersonic flow as well as subsonic flow. This method adopts unstructured mesh so that it can be employed for complex geometries. A numerical model proposed by Suzen et al. is used for simulating the phenomena caused by a plasma actuator, and TAS-code is employed for the flow field prediction. First, this paper validated the proposed method through two test calculations for subsonic flow; the Hump model used at CFD validity workshop in NASA Langley and then the NACA0015 airfoil. According to the results of the subsonic test calculations, the present method was able to predict the effects of the plasma actuator to the flow separation correctly. Finally, a calculation with the ramp model is conducted to control the shock wave, and its capability to control the shock wave through the shift in the shock wave location was confirmed.
Low-speed Wake Analysis of Supersonic Biplane
Shuichi Ozaki,Masahito Yonezawa,Naoshi Kuratani,Toshihiro Ogawa,Shigeru Obayashi,Takashi Matsuno,Hiromitsu Kawazoe 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
This study was focused on the profile drag estimation from the wake survey of the now field with the wind tunnel testing. The experimental investigation was conducted with the low turbulence wind tunnel to estimate the profile drag coefficient of the supersonic biplane from the pressure loss in the wake of the model. The surveys were conducted behind the supersonic biplane model whose airfoil could realize the shock wave cancellation at design Mach number 1.7. The two-dimensional CFD simulations were also conducted to compare with the experimental results. The reduction of the test data by Jones equation gave the profile drag coefficients agreed with those obtained from the CFD simulations at zero lift conditions. However, at lifting conditions. the experimental results and the CFD results didn't agree. In this study, the profile drag characteristics of the supersonic biplane were discussed based on these results.