Since international standard ISO2394 " General principles on reliability for structures " has been established, design guidelines, codes and standards based on limit state method are being enacted in many countries in the world. This paper explains the fundamental concept of limit state design method first. Then, one view in the case of applying it to construction machinery etc. is described. Some calculation and investigation cases on the design method for materials handling carrying systems besides mobile crane which is a typical construction machinery are shown. When applying this method to a machine or its system, unlike the case where it applies to an architectural structure etc., it is important to make clear the dynamic limit state based on dynamic analyses. Finally, related outlook in the near future is discussed.

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Bogie mechanism etc. have become to be used for running equipment of crawler-type construction machine to improve the comforts. However, in the running equipment, there are many unclear points in the behavior and loads due to the complicacy. This paper shows a method for modeling of crawler-type running equipment with a bogie mechanism as a multibody system. And the treatment of the contact between grousers and rigid ground like steel plate, etc. is shown. The dynamic behavior of running equipment such as the suspension forces in traveling on horizontal and stepped ground is calculated by the traveling simulation using this model. It is possible to obtain the data required in the limit state design for running equipment by this method.

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Fatigue design codes of steel structures for cranes which have been proposed by ISO, EN and JIS were reviewed. In particular, two general approaches, limit state stress method and allowable stress method, were compared. The limit state stress method, where partial load factors are used to amplify loads before they are combined and compared with limit state imposed by yielding or cyclic loading. The allowable stress method, where the design stresses induced by combined loads are compared with allowable stresses established for the type of member or condition being examined.

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ISO standards about cranes are deliberated by ISO/TC96. In recent years, the movement which takes in the limit state method design is in the method of designing a crane, for this reason about eighty ISO standards having deliberated by ISO/TC96 were classified, and the description about a limit state method was considered. IS08686 is the sole standard mentions about the limit state method. This shows the loads and load combination but the standard about strength is incomplete at present. In addition, the standard of IS012482 which determines the time of the following overhaul from periodical record is also created.

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Residual life assessment system of cranes with risk-based maintenance technique has been generated. Risk is defined as a multiplication of likelihood by consequence of a failure with semi-qualitative method. This is based on engineering judgment with inspection data and operating conditions and fatigue damage assessment and so on. Ranking of likelihood and consequence could be defined with the assessment of damage function and others. Risk-based maintenance technique is expected as a new technique to optimize the inspection and maintenance plan.

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When we evaluate the man-machine systems, it is very important to consider not only the performance of the machine system but also the Mental Work Load (MWL) for the operator. Therefore, we construct a model using the Heart Rate Variability to analyze the relationship between the driver's MWL and the factor of the MWL. In this analysis, we construct two kinds of model. One is Multiple regression modeling for the linear analysis, and the other is Neural network modeling for the non-linear analysis. Finally, we propose the possibility that an analytical method of the model can be used to assessment of the man-machine systems.

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Cornering stiffness is usually treated as an equivalent term which presents characteristics of tire-suspension-steering system in developing the lateral force at a given tire slip angle. However, influence of suspension and steering characteristics on the value of cornering stiffness and vehicle dynamics characteristics are not separately considered and analyzed. Therefore, the relation of each suspension, steering and tire with vehicle dynamics characteristics is not obviously known. An analytical compliance model in suspension system is proposed here as a linear bush model attach with single A-arm. And relation of it with cornering stiffness and vehicle dynamics characteristics base on bicycle model are theoretically derived in this paper.

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This paper is concerned with the running stability of tractor-semitrailer combination at braking. Firstly, we construct nonlinear equations of motion for the articulated vehicles, which have 9 degrees of freedom. Secondly, simulation study is carried out to show the vehicle performance in realistic situation. Jack-knifing on the straight road section was recreated by the simulation in consideration of road gradient not only longitudinal direction but also lateral direction . By using the concept of load rate of each tire, we confirmed that the model shows the mechanism of the jack-knifing on straight road section, and the motion of limit performance conditions. Finally, the relationship between limit performance, road gradient condition, and vehicle parameters is shown. These results emphasize the importance of observation of the tire load rate. Especially, rear axle of tractor should be considered when we discuss the limit performance of jack-knifing.

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In the conventoinal driving simulator with 6 degree-of-freedom parallel link mechanism, the acceleration simulation algorithm separates and reproduces the taranslational acceleration and the continuance acceleration. Such an algorithm provides the quick driving sense simulation with respect to the operation of the driver during the deceleration. Then, the design of the driving sense simulation algorithm that gives priority to jerk simulation of the translational motion operation component is examined. During the deceleration by sudden brake, the effect of pitch motion is also considerable as well as longitudinal motion. In this study, acceleration sense presentation algorithm considering the pitch motion of suspension of car body by load transfers is proposed. This paper develops acceleration sense presentation algorithm which mainly aims at the reduction of jerk during brake release maneuver. Finally, its effect during braking maneuver is examined.

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The recent increases in the container crane size and in the speed of operation has made the handling of container cranes increasingly more difficult. Furthermore, the need of reducing manpower costs has led to a demand for automatic container cranes. Mitsui Engineering & Shipbuilding Co., Ltd. has developed a target scanning system, utilizing a laser sensor, for the automatic operation of container cranes. The system is installed below the girder of the ship to shore crane and it can accurately detect the container or chassis position (within +/- 60mm) with three dimensional shape recognition technology. This paper describes the system of tests that were conducted to confirm the accuracy and operation of the target scanning system for the container crane during automatic operation.

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Since the static wheel load imbalance may fail the running performance of railway vehicle, the static wheel load balance should not be neglected. The causes of wheel load imbalance are as follows; unequalness of the height of primary suspentions which causes the imbalance in bogie, and unequalness of the height of secondary suspentions or mass eccentricity of the car body, which cause the imbalance in car body. Considering the background of the imbalances, authors tried tests to estimate static wheel load imbalance caused by imbalance in car body. Regarding the results of them, we developed a equipment to estimate the static wheel load imbalance.

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Car dynamics of railway is originally influenced by the interaction between wheel and rail. So with observing these interactual forces, car dynamic behaviors and conditions of the car are able to be evaluated. In this paper the method of observing wheel-rail interaction forces and these results are presented. And in another research, the technics of controlling friction between wheel and rail have been developed and practically used with injecting friction modifier to the top of low rail by the authors. For practical application case of observing these interactual forces, correlation between car dynamics behavior and wheel-rail interaction friction has been evaluated.

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Development of durable and efficient thermal protection systems against the reentry heating environments is one of the most important issues to realize the practical reusable launch vehicles in future. In order to prepare the heat shield material development, research on evaluation methods regarding the erosion rate and aerodynamic heating characteristics are being conducted using the special ground facilities. Some of the recent activities and future research directions are discussed in this report.

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One of the key technologies of Reusable Launch Vehicle (RLV) is thermal structures. This paper describes on advanced thermal structures studied by Mitsubishi Heavy Industries, Ltd. (MHI) for future application. Carbon fiber reinforced Silicone Carbide (C/SiC) hot structure is a candidate for control surfaces of RLV. MHI has developed C/SiC samples by combining Japanese 3-D woven fiber technology with French Chemical Vapor Infiltration (CVI) matrix technology.

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Advanced Thermal Protection System (TPS) is expected to be developed as one of the key technologies of Reusable Launch Vehicles (RLVs). TPS for RLV should be lighter weight, more durability to the flight environments and lower cost than conventional TPSs like a Space Shuttle. To satisfy those requirements, an advanced Flexible External Insulation (AFEI) has been improved in thermal conductivity and weight. This AFEI has been also applied as internal insulation to Surface Protected Flexible Insulation (SPFI) developed by Astrium-Space Infrastructure. This advanced SPFI (ASPFI) is aimed at protecting the windward side of reentry vehicles. This paper describes the development of advanced TPSs such as AFEI and ASPFI.

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Enhancing a life of a high pressure r e generatively cooled rocket combustor has been one of the essential problems to realize a reusable launch vehicle. One of the possible mechanical failure modes of copper chambers is low cycle fatigue. A compliant structure of a combustor using a FRP (Fiber Reinforced Plastic) composite outer shell is now being investigated to reduce thermal strain of an inner shell made of copper alloys. This paper gives an overview of the design concepts and the analysis results of life enhancement effect of the FRP composite outer shell.

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Ceramic Matrix Composite (CMC) is one of the candidates for thermal protection materials of space re-entry vehicles. In order to fix the fabricating process, some mechanical tests were performed on CMCs, which made by various process conditions, before and after thermal exposure simulating re-entry conditions. In comparison with the change of mechanical properties with process conditions by thermal exposure, it was confirmed that interface treatment (CVI-C/SiC) between SiC fiber and SiC matrix and several repeating of densification process (PIP) were required for CMCs using for thermal protection materials. Trial parts have also been fabricated successfully in the shape of a leading edge and TPS curved panel with the high accuracy by the fabricating process using the conditions selected above.

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Reliable methods for joining ceramics, for use at elevated temperatures, are enabling technologies for the successful utilization of ceramic components. In this study, the stress distribution of a SiC/SiC composite specimen containing a butt joint consisting of reaction-formed silicon carbide tested by the asymmetrical four-point bending test was precisely analyzed by the finite element method as a means to evaluate the applicability of analytical results. In the case without the effect of the thermal residual stresses, the shear stress distribution at the interface between the base and the joint almost agreed with the analytical theory. For the case with the residual stress, however, the shear stress near the surface was very large and the possibility of an initial crack induced by the residual stress was considered. Moreover, it was found that the residual shear stress distribution near the surface was significantly affected by the joint thickness.

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Mechanical properties of two kinds of 3-D woven SiC_f/SiC composite materials (CMCs) were investigated at elevated temperatures up to 1400℃. One is the CMC using a preform with carbon coating( Type A), and the other is that using a preform with SiC coating (Type B). Type B CMC indicated higher tensile strength and rigidity than Type A one at room temperature. Tensile strengths and Young's modulus of both CMC materials decreased with increasing temperature. At temperatures beyond 1200℃, the tensile strengths of both CMCs are almost same values regardless of the fiber/matrix interface coating.

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National Aerospace Laboratory of Japan (NAL) has conducted a joint program to develop a continuous fiber reinforced ceramic matrix composite (CMC) for aerospace applications. The composite is referred to as NUSK-CMC from the initials of the collaborators, which exhibits excellent tensile strength and creep strength up to 1200℃ in air. It has been attempted to apply NUSK-CMC to thermal protection system (IPS) of a future reusable space transportation system (space plane). For the purpose, thermal response and oxidation behavior under atmospheric re-entry condition were investigated using an arc jet facility. As a result, it was revealed that catalytic effect at the NUSK-CMC surface under plasma air stream was not significant. Furthermore, surface recession was hardly observed below 1450℃ in surface temperature and above 5 kPa in oxygen partial pressure at the stagnation point, because passive oxidation was dominant under the heating condition. Passive-to-active oxidation transition of the composites agreed with the Balat's theory for silicon carbide under the present experimental condition.

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This paper is concerned with the numerical analysis of dynamic thermal stress and deformation for moderately thick shells of revolution made of functionally graded material by using finite element method. The material properties of the shell are continuously inhomogeneous along the shell thickness and dependent on the temperature. The temperature distribution through the shell thickness is expressed with a curve of high order, and thick shell elements are utilized for the analysis. As a numerical example, a functionally graded material shell composed of SUS304 and PSZ subjected to thermal loads due to heat generation in the shell body is treated. The shell is axisymmetric and has a parabolic meridian. It is found that temperature distributions, stress distributions and deformations are significantly influenced by temperature dependent properties of the materials.

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This paper describes two rigidizable membranes for space inflatable structures. The membranes consist of carbon fiber reinforced plastics (CFRP) prepregs using thermosetting resins. The inflatable structures are rigidized by increasing the temperature after inflation in space. Medium temperature cure resin is used for two ply laminate membranes to be rigidized at 90 to 120℃. High temperature cure resin is used for one ply membrane with triaxial woven fabrics to obtain a more lightweight and flexible membrane. Rigidization experiments using two inflatable tori with diameter of 2.1 m are conducted and the feasibility of rigidizable membrane is evaluated by the completion of rigidization.

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The unsteady behavior of the non-stationary weak shock reflection over a wedge was investigated. Two kinds of flow models just behind the reflection point for regular reflection and Mach stem for Mach reflection were introduced to explain the unsteady behavior of the wave configurations. Based on these models, viscous effects caused by the boundary layer formed over the wedge surface and/or slip stream were included in the so-called von Neumann's two- and three-shock theories as the modified von Neumann's conditions. Comparing the solutions of modified von Neumann's theories with experimental results, it was found that the present models reveal the causes of unsteadiness of the weak shock reflection qualitatively.

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It is well known that some of sources of noise which radiates from an exhaust pipe of automobile engine exist in the flow field downstream of the pipe end. An unsteady jet issues periodically from the pipe end with shock wave, so that the unsteady jet interacts with the shock wave, resulting in the formation of the complicated flow pattern. To clarify the mechanism of noise generation, the flow field downstream of the pipe end is experimentally examined using a shock tube. The flow field is visualized by shadowgraph method and different types of density waves are observed. The density wave is considered to be one of the sources of noise. The relation between the flow properties and the flow pattern of the density waves are discussed.

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In order to investigate a later stage of Mach reflection and to check the non-selfsimilar and unsteady behavior, we performed experiments in a shock tube with a cross-section of 185 mm square in Karlsruhe University. The reflection configuration was visualized by means of the infinite fringe spacing interferometry, which is similar to the Schlieren method. The angle between incident and reflected waves were measured as well as the location of triple point. The results showed that these physical properties vary as the incident shock proceeds even in the later stage of shock reflection. For some case, the angles of incidence and reflection, which exhibited the so-called von Neumann paradox at an early stage, moved on the three-shock theory curve to resolve the paradox. For other cases, they varied toward the three-shock theory curve but the paradox was yet to be resolved.

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Radial underexpanded jet is a flow model of a wall jet of an axially-symmetric supersonic jet which impinges on a flat plate perpendicularly. The flow pattern of the wall jet can be considered to be one of the important factors to determine the flow characteristics of the impinging jet. A radial jet issues from a small space between a tube and a cilynder, or a slit nozzle, and shock waves are formed in it. Cell structure of the jet exists continuously in the circumferencial direction and then, these shocks are seen as 'shock rings'. In the experimental photographs, it is found that rings are locally distorted, branched and deformed. They are caused by the periodic oscillation of the shock cells and the time lag of that in each circumferential section. The spiral motion of the impinging jet is considered to be affected by these phenomena.

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The Pressure sensitive paint (PSP) technique was used to visualize the continuous surface pressure distribution around a sonic jet injected transversely into a supersonic freestream of Mach 2.4. The flow fiedls with jet-to-mainstream dynamic pressure ratios of approximately 0.3, 0.7,1.1 and 1.5 were examined. The visualized flow field showed high wall pressure region in the vicinity of the central axis.

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A pressure measurement system was developed with high spatial resolution using pressure-sensitive paint (PSP) and Cassegrain optics and applied to periodic flows which were generated by chopping underexpanding-jets. A violet diode with stable output was used to illuminate the PSP and a photomultiplier tube was used as a photo detector. It shows that the pressure data obtained from PSP agree with those from a conventional pressure transducer.

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Flow structure in a twin-fluid atomizer with a mixing chamber was visualized with a pulsed light source and a 35 mm still camera, and droplet size distributions of the spray were measured by the immersion liquid method, in order to study effects of the flow structure on the spray. The obtained pictures revealed that the flow in the mixing chamber might be divided into two regions: water rich region close to the wall and air rich region in the core. It was found that in the case where the thickness of the water rich region decreased as the flow approached the entrance of the nozzle, the resultant spray had smaller diameters of droplets.

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Pressure measurements were conducted under shock-loaded particle layers laid on the end wall of a vertical shock tube. The Mach number of the incident shock wave was 1.33. In order to reduce the uncertainty regarding the particles' arrangement, sized spherical particles were carefully set in regular array in the test section of the shock tube. The repeatability of the pressure measurements under the particle layer was much improved by using these regularly arranged particle layers. It was also found that the gas pressure transiently exceeded the pressure behind the reflected shock wave for the relatively small number of layers.

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Three-dimensional shock wave reflections from a cone with angles of attack were examined experimentally and numerically. The Mach number of the incident shock wave was 1.35. The attack angles of a cone model with a semi-apex angle of 30° were 10° , 15° , 20° and 25°. The experiments were performed using a vertical shock tube, and the wave configurations were visualized using a conventional schlieren system. Numerical simulations of the shock wave reflections were also conducted using unstructured solution adaptive grids. The triple-point distributions around the cone were reconstructed from the visualized wave configurations, and then compared with those obtained from the numerical simulations. The characteristic flow fields behind a curved Mach stem around the cone are revealed.

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In the present work, a robust explicit time-integration scheme named the rational Runge-Kutta (RRK) method is applied to steady supersonic flow simulations with unstructured solution adaptive grids. The results from the present numerical tests show that the RRK method allows larger Courant numbers than the modified Euler explicit method. Also, it is found that the maximal value of allowed Courant numbers in the simulations with the RRK method strongly depends on the size of the smallest edge length in the computational grids.

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The flow field around an axisymmetric plug nozzle is numerically simulated by the three-dimensional thin-layer Navier-Stokes equations. The multi-hole type secondary flow injection is introduced around the boat-tail region for the purpose of the boat-tail drag reduction. The computed result shows that the wall pressure downstream of the injection clearly increases and the boat-tail drag is reduced by 40%. The multi-hole type secondary flow injection is more efficient than the annular type slit injection.

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Japanese universities recently began to develop small satellites for educational purpose. These activities are primary for education; i.e. to provide students with opportunities to experience the whole cycle of space projects including mission conceptualization, design, fabrication, test, launch, operation and analysis of the results. However, they are also aiming for the "university type" contribution to the actual space development, by, for example, providing quick and cheap space demonstration opportunities with university small satellites or finding new seeds for future space technologies. This paper will present the current status and future vision of such university activities related to small satellites.

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The authors have been investigating the practical education program of space engineering based on the development of micro satellites. In this program, the college students propose the mission, design and develop the satellites by their hands, manage the project, and estimate the results by themselves as well as their teachers. In this paper, the current status of our activities is presented, and the expected result and the problem of the program are discussed.

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The mainstream of the research and development of satellites in NASDA is for over 1 ton-class satellite. But, 50kg-class Micro satellites and under 10kg-class Nano satellites are researched, too. "μ-Lab Sat" -the first Micro satellite in NASDA- is planning to launch in 2002. The orbit of this satellite is LEO (low earth orbit) and the attitude of this satellite is the spin stabilization mainly, and the three-axis stabilization in the experiment. "μ-Lab Sat 2" -the next micro satellite in NASDA, is under conceptual study. It has 50kg-class mother ship satellite and 5〜10kg-class daughter-ship satellites. The orbit of this satellite is GTO (geostationary transfer orbit) and the attitude of mother ship satellite is the three-axis stabilization. Daughter-ship satellites will be formation flying in the experiment. The formation flying is the key technique for the interferometer.

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Nihon University is wrestling with two artificial satellite development projects, which are called CanSat and CubeSat at present. CanSat is the artificial satellite model, which loaded 350ml can size structure with the subsystem composing a satellite. This satellite model is launched to altitude 4 km by the amateur rocket, and is operated while falling with the parachute. On the other hand Cubesat is the project that the student designs and manufactures 10 cm cube size satellite and it is thrown in LEO. We participate in these projects to experience and master a proposal of mission, design, manufacture, tests, launch, and data analysis. In this paper, the overview of our former activity about CanSat and CubeSat is described.

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University of Tokyo has been studying and developing nano-scale satellites for three years, including the 350 ml can-sized satellite named "CanSat" and 10cm cubicsatellite named "CubeSat," which is planned to be launched in 2002 using a Russian rocket. These activities are primary for education; i.e. to provide students with opportunities to experience the whole cycle of space projects including mission conceptualization, design, fabrication, test, launch, operation and analysis of the results. However, they are also aiming for the "university type" contribution to the actual space development, by, for example, providing quick and cheap space demonstration opportunities with university small satellites or finding new seeds for future space technologies. This paper will present the history of our small satellite research and development, lessons learned and future prospect.

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Participating the CanSat project we are now developing a CanSat (350ml, 350g) and an OpenClass (φ150, h300, 1.8kg), which will be launched at Black Rock, Nevada in this August. The CanSat project is a collaborative effort between students and faculty at several educational institutions, to build, launch, test and recover prototype satellites. Mission of our OpenClass is navigating an OpenClass to a predetermined location by itself using GPS stand alone positioning and data from an electric-compass and a pressure sensor while conducting experiments on two components of our CubeSat. These are a sun sensor module and an antenna deployment mechanism, both of which we have been developing to install in our CubeSat 'CUTE-I' scheduled to be launched in May 2002 from Baikonour Cosmodrome, Kazakhstan on a Russian rocket, DNEPR. Mission of our CanSat is acquiring images by using the sun sensor module modified to be able to output raw images taken by a CMOS camera in the module.

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CubeSat Project is an international, educational and practical program, and many universities and companies join in the project. A CubeSat is a pico-satellite sized of 10cm^*10cm^*10cm, less than 1kg in weight, and 18 CubeSats are planned to launch at May 1 of 2002 by a Russian rocket, Dnepr. We, TITech group, are now developing a CubeSat for the launch opprtunity. The objectives of TITech CubeSat Project are design/development of pico satellite equipped with bus components under the leadership of students, and reduce the total costs by using commercial off-the-shelf (COTS) components. In this paper, we explain the design and the development schedule of TITech CubeSat.

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In recent years, the development conation in the small satellite by the students is rising. The concept design of the small satellite that has missions proposed by the students became done in satellite design contest. Furthermore, the satellite proposed by Chiba institute of technology is fixed to be launched. We have done concept design of some small satellite, but have never made the satellite. So utilizing former experiences, we want to develop the small satellite with the inflatable structure.

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We have begun the feasibility study to build a small satellite in the 3kg mass range and in the power range less than 30W since October in 1998, sponsored by National Space Development Agency of Japan (NASDA). This satellite installs three reaction wheels for an attitude control and camera which will demonstrate optical navigation experiment by using image processing. Attitude control experiment under microgravity field was conducted using an experimental setup named "HITSAT" and successfully demonstrated in Japan Microgravity Center (JAMIC).

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This paper describes study and development of docking mechanism to release and retract a micro satellite. The docking mechanism which was designed this time is aimed at applying to small mothership-daughtership satellite for formation flying. The docking strategy using this docking mechanism divides two phases. The first is a phase of approaching and grasping a daughtership. The second is a retracting phase. The mechanism is required to release a daughtership stably and to retract it into the desired point on a mothership. The size of docking space is 350mm-diameter (daughtership size is 200mm-diameter) enough to permit position/attitude control error of daughtership. Furthermore it is necessary to secure enough size of docking space but to make a mechanism as small as possible. In addition, a recharging system is developed and equipped this mechanism. We report the result of design and introduce plans of ground experiment using air-floating test beds and a free-fall Microgravity experiment using free-fall tower.

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Taking Japan Soc. of Mechanical Engineers bulletin and lecture collection as an element to the previous report, the analysis was carried out. Some matters were proven as the result. As a result, that the discussion on "engineering education" was clarified came to future progress for the conclusion with the necessity. The bulletin of Japan engineering education society which was participating group, while it is long on the engineering education, should be analyzed in order to clarify the situation. The result is reported.

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Nowadays, robot contests are holding in many places. We usually make robots using all kinds of materials and machine parts. On the other hand, many people are interestrd in LEGO MINDSTOREMS. MINDSTORMS consists of 719 blocks and electric motors, touch sensors, light sensors, CPU conputer, etc. We can make various kinds of robots usuing these blocks and moters, sensors. In this paper, we compared two kinds of robot contest, and then we considered the difference. As a result, we understood many students were interested in the contest using MINDSTORMS. We analyzed the reason that MINDSTORMS could learn machine programming easily and realized idea shortly.

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The beginning of engineering practice at Meijo University in 1993, the main purpose was to touch the products and mechanisms. At present, according to study engineering practice, it was found that the students must act not only try to the theme mechanically but also study the meaning and reasoning of the movement. This report is described about the new element of study engineering practice based on the past behavior of engineering practice named HAND ENGINEERING I.

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The teaching tool utilized on learng the compression ignition engine in the class of junior high school industrial arts and homemaking course was produced, and the learning effect was examined by lesson practises. This teaching tool is the one utilizes the adiabatic compression. And it was improved upon the former one for the students to use more easily. By this teaching tool, the students can learn the principle of ignition through the experiments. Using this teaching tool, the students could do the experimental learning more well than before and the students who show the interest in learnig the expansive contents increased.

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Association of National Colleges of Technology published many reports on improvements, promotions and future of College of Technology. In this paper, criticisms on the technology and the engineer patterns (or the technologist patterns) of A N C T are discussed.

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It is very difficult to understand only by explanation with language or figure that the involute gears contact on the common tangential line of two gears' base circles which is called the line of action or the line of transmission and the cycloidal gears contact on the rolling circle which formes the cycloidal curved line. In order to make learners confirm this fact by their eyes, it is intended to make the specially large gear with transparent acryl board and to project them on the screen by an over-head projector. This large gear is difficult to make by rack cutter or hob cutter usually used. Therefore the contouring control cutting with an end-mill cutter was done by making use of a numerical control machining center. MINIAPT and FAPT languages are used as a programming language for it. This trial model is supposed to be used in teaching the students in technical course or mechanical course in university. Using of this model, the transmission of the point of contact of gears is able to be observed on the screen, and the locus of contact point of gears is confirmed by the eyes of learner's own.

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In the class of Creative Design Exercise, the instructors were always feeling that class hours were insufficient. To alleviate this problem, they initiated the use of an Internet homepage for assignments outside-of-class as a follow up for their students. When an experiment on a gas engine was conducted in the class, supplementary information and homework assignments such as writing an essay on the influence of automobile exhaust, making an analysis from the energy flow calculation and drawing a P-V diagram were posted on the homepage. Although the drawing of a P-V diagram was not a mandatory assignment because of the consumption of time, some students challenged and completed it, which surprised and pleased the instructors very much.

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