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Novel image analysis for trajectory of microtubules gliding on kinesins with Tip detection

Journal of Biomechanical Science and engineering 2009年第3期4卷 404-414页

作者： Sugita, Shukei Sakamoto, Naoya Ohashi, Toshiro Sato, Masaaki Department of Biomedical Engineering Graduate School of Biomedical Engineering Tohoku University 6-6-01 Aramaki-aza-Aoba Aoba Sendai 980-8579 Japan VCAD System Research Program RIKEN 2-1 Hirosawa Wako 351-0198 Japan Department of Bioengineering and Robotics Graduate School of Engineering Tohoku University 6-6-01 Aramaki-aza-Aoba Aoba Sendai 980-8579 Japan Division of Human Mechanical Systems and Design Graduate School of Engineering Hokkaido University N13 W8 Kita Sapporo 060-8628 Japan

Control of the gliding directions of kinesin-driven microtubules (MTs) in vitro has good feasibility for the development of nano-scale transport systems. A requirement for the control of transporters in these systems includes detecting the positions of gliding MTs;however, no studies have reported on the monitoring of the positions of gliding MTs. Here, we suggest an algorithm to detect tip coordinates of gliding MTs by binarization, skeletonization, and filtration of fluorescent images of MTs. The algorithm was first applied to artificially drawn segments with given lengths (10-80 pixels), widths (1-10 pixels), and curvature radii (20-120 pixels) to verify the effect of the sizes of MTs on accuracy of tip coordinates extracted by the algorithm, and error was estimated by referring to the true coordinates. The estimated errors were as small as 2 pixels in the width and were not affected by the length and the curvature radius, indicating that our algorithm is useful to extract the tips of MTs. The algorithm was subsequently applied to images of gliding MTs. Since distances from the trajectories of the MTs to the centers of gravity of the MTs (3.7 ± 2.1 pixels) were significantly larger than those to the tips (1.9 ± 0.5 pixels), the use of the tips as representative points of gliding MTs was verified. A detection method using tips of MTs, as suggested in this study, may be a useful technique for monitoring each MT in nanoscale transport systems.

关键词： Pixels

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RESPONSIVENESS IMPROVEMENT OF IDLING SPEED CONTROL FOR AUTOMOTIVE

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38th International Conference on Computers and Industrial engineering

作者： Zhang, Yang Koorikawa, Takashi Kurihara, Nobuo Science Program in Mechanical System Engineering Hachinohe Institute of Technology School of Engineering Japan Hachinohe Institute of Technology School of Engineering Japan

ISBN: (纸本)9787121074370

Fuel economy is an important issue in the modern automotive industry. So fuel economy technologies are a research emphasis. Improving engine efficiency as a core of fuel saving technologies is under extensive study. Idle speed is the minimum operating speed of a combustion engine. The period of the idling operation occupies thirty percent of driving time for. urban traffic. Therefore significant fuel economy and emissions improvements can be gained by lowering the idle speed of an engine. In order to achieve a lower idle speed it is necessary to maintain a stable idle speed in the presence of known disturbances (e.g. air conditioning) and unknown disturbances. In this paper, idling speed was studied based on a four-cylinder gasoline engine model by three kinds of robust control methods, or PID control, Smith predictor and sliding mode control. A sliding mode controller was proposed, and accordingly a speed sliding surface was designed From the result of simulation, it was confirmed that control performance with load disturbance could be improved.

关键词： Idle speed control Robust control Sliding mode control Smith predictor Smith plus Compensation

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Wind tunnel testing of JSAE standard Low-aerodynamic-drag vehicle body using 1/5 scale model

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Review of Automotive engineering 2009年第1期30卷 51-60页

作者： Shimano, Kenjiro Kumano, Takahiro Takagi, Michitoshi Ono, Kenji Horinouchi, Nariaki Tarumi, Seiji Department of Mechanical Systems Engineering Faculty of Engineering Musashi Institute of Technology 1-28-1 Tamazutsumi Setagaya Tokyo 158-8557 Japan Layout Group Automobile Platform Design Department Suzuki Motor Corporation 300 Takatsuka-cho Minami-ku Hamamatsu-shi Shizuoka 432-8611 Japan Department of Prime Mover Engineering School of Engineering Tokai University 1117 Kitakaname Hiratsuka-shi Kanagawa 259-1292 Japan VCAD System Research Program RIKEN 2-1 Hirosawa Wako Saitama 351-0198 Japan Heat Transfer and Fluid Flow Laboratory Toyota Central R and D Labs. Inc. Nagakute Aichi 480-1192 Japan CAE Testing Division Yamaha Motor Co. Ltd. 2500 Shingai Iwata-shi Shizuoka 438-8501 Japan

As computational fluid dynamics plays a crucial role in vehicle body design, the CFD committee, one of the technical committees comprising JSAE, embarked on a benchmark project in which a number of CFD codes would be tested on the same vehicle body. A wind tunnel test of the 1/5 scale model was conducted to provide reference data for the benchmark test. In this paper, details of the measurements are presented. On the body surface, smooth flow patterns were visualised by tufting. It was also found that total pressure loss in the wake of the model displayed a unique pattern similar to a mushroom cloud. © 2009 Society of Automotive Engineers of Japan, Inc. All rights reserved.

关键词： Computational fluid dynamics

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mechanical modeling and finite element analysis of porous cast products

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Seimitsu Kogaku Kaishi/Journal of the Japan Society for Precision engineering 2008年第12期74卷 1273-1277页

作者： Esmaeili, N. Alvesand, J.L. Teodosiu, C. VCAD System Research Program RIKEN Japan Department of Mechanical Engineering University of Minho Portugal

A study was conducted to develop a methodology to perform finite element (FE)-based simulations of the micromechanical response on actual three-dimensional (3D) microstructures. It was demonstrated that the methodology was applicable to other 3D image acquisition techniques, such as X-ray computed tomography. The simplifications performed in image manipulation and voxelization retained the major features of the pores, including their high angular morphology and orientation. A parallelepipedic volume of about 20 &19 &15 mm3 size and average porosity of about 0.05 were extracted from a car engine block made of an aluminum cast alloy to conduct the investigations. The 3D pore morphology was reconstructed from the stack of 3900 serial sections. The simulations were performed on 12 cubic subdomains of the parallelepipedic volume having the size of 3.31&1.77&2.98 mm3 where the porosity volume fraction varied from about 0.022% up to 25%.

关键词： Fracture

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Annual business and news: Beginning the 32nd year

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Journal of Guidance, Control, and Dynamics 2009年第1期32卷 1-7页

作者： Schmidt, George T. Akella, Maruthir Balakrishnan, S.N. Campbell, Mark E. Clarke, John-Paul Colgren, Richard D. Crassidis, John L. Doman, David B. Eke, Fidelis O. Enns, Russell J. Gawronski, Wodek Hablani, Hari B. Leitner, Jesse A. Ping, Lu MacDonald, Malcolm McFarland, Michael B. Melton, Robert G. Mitchell, James Mukhopadhyay, Vivekanand Sasiadek, Jurek Z. Schaub, Hanspeter Wise, Kevin A. United States NATO Systems and Electronics Technology Panel Lecture Series on Low Cost Navigation Sensors and Integration Technology U.S. Air Force Office of Scientific Research United States United States American Automatic Control Council United States Sibley School of Mechanical and Aerospace Engineering Cornell University United States School of Aerospace Engineering Air Transportation Laboratory Georgia Institute of Technology United States Lockheed Martin Aeronautics Company Palmdale CA United States United States Wright-Patterson Air Force Base Dayton OH United States Davis United States Apache Longbow Jet Propulsion Laboratory California Institute of Technology United States GSFC United States Department of Aerospace Engineenng Iowa State University United States Raytheon Electronic Systems United States Department of Aerospace Engineering Pennsylvania State University United States NASA Langley Research Center United States Indian Institute of Technology India Department of Aerospace Engineering Carleton University Canada International Federation of Automatic Control Robotics Technical Committee Joint Robotics and Control Systems Societies Chapter Ottawa Canada X-45 Joint-Unmanned Combat Air System Program

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Ornithopter modeling for flight simulation

Ornithopter modeling for flight simulation

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International Conference on Control, Automation and systems ( ICCAS)

作者： Jae-Hung Han Jin-Young Lee Dae-Kwan Kim Department of AeroSpace Engineering School of Mechanical AeroSpace and System Engineering KAIST Daejeon South Korea COMS Systems Department Communication Ocean & Meteorological Satellite Program Office Korea Aerospace Research Institute Daejeon South Korea

This paper presents the flight simulation of flapping-wing air vehicles (ornithopters) based on a refined flapping-wing aerodynamic model; the modified strip theory (MST). Compared with conventional types of micro air vehicles (MAVs), flapping MAVs show more complicated flight behaviors due to their complex wing motions and aerodynamics. In this paper, a flight dynamic model of an ornithopter is presented to analyze its stability and controllability. This paper focuses on the stabilization and path-following control of the ornithopter by adjusting the flapping frequency and tail-wingpsilas elevation angle. In spite of its nonlinear and complex behavior, controlling the tail-wing pitch angle can be effective for the stabilization in longitudinal motion of the ornithopter.

关键词： Aerospace simulation Aerodynamics Vehicle dynamics Unmanned aerial vehicles Force control Strips Control system synthesis Aerospace engineering Electronic mail Frequency

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Annual business and news:: Beginning the 31st year of the Journal of Guidance, Control, and Dynamics

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2008年第1期31卷 1-1页

作者： Schmidt, George T. Aeronautics and Astronautics Massachusetts Institute of Technology (MIT) AIAA Institute of Electrical and Electronics Engineers Russian Federation Academy of Navigation and Motion Control Department of Mechanical and Aerospace Engineering and Engineering Mechanics University of Missouri-Rolla(UMR) Lockheed Electronics Company Center for Space Research University of Texas Austin United States Wright Laboratory Eglin Air Force Base UMR AIAA Guidance Navigation and Control Technical Committee American Automatic Control Council Lockheed Martin Aeronautics Company Palmdale CA United States C4ISR and Unmanned Air Vehicle (UAV) Programs for Air Vehicle Sciences and Systems Accreditation Board Engineering and Technology Inc./Aeronautical National Technical Committee on Guidance Navigation and Control Department of Mechanical and Aerospace Engineering University at Buffalo State University of New York (SUNY) AIAA Technical Committee on GN and C Air Vehicles Directorate Air Force Research Laboratory (AFRL) Wright-Patterson Air Force Base Space Access and Hypersonic Vehicle Guidance and Control Group Control Science Center of Excellence AFRL AIAA Technical Committee on Guidance Navigation and Control Department of Mechanical and Aeronautical Engineering University of California (UC) Davis United States Boeing Company Modernized Flight Control System for the Apache Longbow AIAA Institute of Electrical and Electronics Engineers AHS Jet Propulsion Laboratory California Institute of Technology Boeing Company Flight Sciences and Advanced Design Group Guidance Navigation and Control (GN and C) Systems Engineer Distributed Space Systems NASA Goddard Space Flight Center (GSFC) AIAA GN and C Technical Committee Department of Aerospace Engineering and Engineering Mechanics University of Texas Austin United States Institute of Navigation American Astronautical Society AIAA Guidance Navigation (GN and C) and Control Technical Committee Department of Aerospace Engineering Iowa State University Iowa

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Numerical analysis of the unsteady cavitating flow in a 2D-cascade and a 3D-inducer

Numerical analysis of the unsteady cavitating flow in a 2D-c...

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43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference

作者： Ugajin, Hiroki Kawai, Masafumi Okita, Kohei Ohta, Takashi Kajishima, Takeo Nakano, Masataka Tomaru, Hiroshi IHI Corporation Tokyo 190-1297 Japan IHI Corporation Yokohama 235-8501 Japan RIKEN Wako Saitama 113-8656 Japan Osaka University Osaka 565-0871 Japan Space Technology Group Research and Engineering Division Aero-Engine and Space Operations 229 Tonogaya Mizuho-machi Nishitama-gun AIAA Fluid Group Research Laboratory Functionality Simulation and Information Team VCAD System Research Program Center for Intellectual Property Strategies Department of Mechanical Engineering Space Technology Group Research and Engineering Division Aero-Engine and Space Operations

ISBN: (纸本)1563479036

The unsteady cavitating flow in a turbopump inducer has been analyzed using CFD simulation results. An accurate three-dimensional detached eddy simulation (DES) code which took into account the cavitating phenomena was used. The three-dimensional code is based on the numerical method for compressible flow using low Mach number flow approximation. The cavitation is modeled by the source/sink of vapor phase in the liquid flow. The code has been applied for cavitating flows in both a 2D cascade and a 3D inducer. The computational results showed similar unsteady behaviors to experimental measurements in terms of the direction in cavity propagations and tendency in cavity developments. Mechanism for the unsteady cavitating flow such as rotating cavitation is investigated by analyzing the numerical results. One model is proposed to describe the reason why the cavity appears to propagate in the forward direction.

关键词： Unsteady flow

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Simultaneous planar measurement of size and three-component velocity of droplets in an aero-engine airblast fuel spray by stereoscopic interferometric laser imaging technique

Simultaneous planar measurement of size and three-component ...

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10th International Conference on Liquid Atomization and Spray systems, ICLASS 2006

作者： Matsuura, Kazuaki Zarogoulidis, Konstantinos Hardalupas, Yannis Taylor, Alexander M.K.P. Kawaguchi, Tatsuya Sugimoto, Daisuke Hishida, Koichi Aviation Program Group Japan Aerospace Exploration Agency Japan Department of Mechanical Engineering Imperial College London United Kingdom Department of Mechanical and Control Engineering Tokyo Institute of Technology Japan Department of System Design Engineering Keio University Japan

A new technique is proposed to simultaneously measure the size and three-component velocity of droplets, which is the extension of the interferometric laser imaging technique to the stereoscopic configuration. The optical compression concept is also utilized to avoid droplet image overlap for the application to the relatively dense region of sprays. The applicability of the technique is successfully demonstrated by using a practical aero-engine airblast fuel spray field. The results are compared with those by the phase Doppler anemometry to evaluate the performance. The results by the two techniques show good agreement. The influence of the air pressure drop through the nozzle is also studied by the present technique and the results are reasonable and consistent with those from literatures. Some important characteristics of the complicated counter-swirling airblast spray field is clearly revealed, taking advantage of the present technique, such as the droplet motions influenced by the air flow in the recirculation zone and in the attenuated circumferential counter-swirl shear-layer structure, not only by the mean velocity values, but also by the various correlations among droplet properties.

关键词： Drops

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Peristaltic PDMS pump with perfect dynamic valves for both gas and liquid

Peristaltic PDMS pump with perfect dynamic valves for both g...

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19th IEEE International Conference on Micro Electro mechanical systems

作者： Jeong, Ok Chan Morimoto, Takashi Watanabe, Yuusaku Konishi, Satoshi Center of Promotion of the COE Program Ritsumeikan University Japan Department of Mechanical Engineering Ritsumeikan University Japan Department of Micro System Technology Ritsumeikan University Japan

ISBN: (纸本)0780394755

This paper presents for the first time experimental results on the peristaltic PDMS pump with perfect dynamic valves for both gas and liquid. Micropump consists of the three peristaltic-type actuators and the micro channel connecting with chambers and the inlet/outlet port. Micropump is fabricated by SU8 mold process and the two-step curing process for the irreversible bonding of PDMS layers. The diameter and the thickness of the actuator diaphragm are 1 mm and 98 μm, respectively. The total size of micro pump is about 5 mm × 5.5 mm. The dynamic gas and liquid valve actions of the single actuator are observed to verify effect of the fluidic mass and viscosity of the working fluid. Perfect peristaltic motions and robust pumping actions of the micro pump are confirmed by the flowrate test of micropump with the air and the ink. ©2006 IEEE.

关键词： Pumps

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