This paper describes a method to confirm stiffness requirements of deployable satellite antennas in the deployed configuration. Deployable satellite antennas are modeled as a reflector (an elastic body) supported by a mechanism or support structure (a coil spring). The equation of motion is obtained assuming that the displacement of the antenna is expressed as the sum of the elastic displacement and the rigid-body displacement due to spring rotation. Reflector modes, selected by using a parameter that is calculated using elastic and rigid-body modes of the reflector, are considered in antenna frequency prediction. A procedure is presented to confirm that the deployable antennas meet the frequency requirements. Numerical examples show that the modal test of the reflectors is not necessarily effective to confirm the frequency requirement.

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This paper describes a method to predict dynamic characteristics of large space structures. Structure is divided into several components. In the method, each component with a boundary mass is subjected to modal tests to measure frequencies and modes. Modes of the structure are estimated by using measured component modes and natural frequencies, and are applied to mode synthesis. The method is applied to a cantilever beam. Numerical results show the effectiveness of the method.

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The flows around the reentry body were analyzed by DSMC method for flow conditions of OREX reentry object. Gas particle of the flow was modeled by VSS with three energy modes, i. e. translational, rotational and vibrational modes. Four kinds of chemical reactions (dissociation, exchange, ionization, and recombination) were taken into account for Oxygen and Nitrogen-based species. To obtain the rotational collision numbers, Lumpkin's theory was applied. For vibrational collision numbers, Landau and Teller's equation was used with Park's high temperature correction. Two surface models are applied such as Maxwell and CLL model to compare the effects. The results clearly showed the basic features of non-equilibrium rarefied gas flow.

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This paper reviews recent applications of trajectory-based analysis to the aerodynamic heating environment for some entry capsules, specifically MUSES-C, Stardust, and Pioneer-Venus probes. In order to explain unexpected problems observed during the entry flight of Pioneer-Venus and Galileo probe, this analysis method solves thermochemical nonequilibrium flowfield by the computational fluid dynamics code that is coupled loosely with the ablation module and radiation module along the entry trajectory. The effect of early transition of boundary layer due to ablation products gas is also considered in this approach. The assessment of this analysis method and the difficulty of reproducing thermal response of ablator are reviewed.

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We report a numerical study of vibration-dissociation coupling which is one of the most important thermochemical relaxation phenomena in hypersonic flows around a reentry capsule. A full set of vibrational master equations was numerically solved to obtain time-resolved population distribution of the vibrational states as well as bulk properties during the relaxation process. State-resolved rate coefficients were determined using the information theoretical approach. Our results show that a quasi-steady state (QSS) exists during the relaxation process, and that the bulk dissociation mostly proceeds during the QSS. It is also shown that the high-lying vibrational energy levels are depleted during the QSS and that the severe depletion of high-lying levels strongly affects the average dissociation rate coefficient and the average vibrational energy loss due to dissociation.

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Aerodynamics of the MUSES-C type reentry capsule has been studied in the rarefied flight environment, from the free-molecular to the transition regime, using the DASH reentry trajectory as an example. The three-dimensional rarefied flow around the reentry capsule is computed by the DSMC method, in which the nonequilibrium thermal and chemical kinetics are taken into consideration, and the aerodynamic coefficients are finally obtained. The results show excellent agreement with those determined by the empirical formula in the rarefied flight regime. Finally, the dynamic stability of the DASH capsule is assured in the rarefied flight regime.

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The concept of re-entry vehicles with flexible aeroshells made from elastic material is proposed. The advantages of utilizing membrane aeroshell for reusable launch vehicle are discussed. The results show that the use of membrane aeroshells can achieve very low ballistic coefficients and make surface temperature less than the maximum temperature of metal TPS and ZYRON fiber for the main body and membrane aeroshell, respectively. Furthermore, this type of vehicle is expected to have the advantage of allowing the reduction in TPS mass. The results of numerical and experimental studies on the characteristics of membrane aeroshells in supersonic flows are also presented.

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In order to improve the performance and usefulness of an expansion tube, a new trial of controlled diaphragm rupture has been examined. An 80 mm x 80 mm square duct is used as the driven section of a shock tube. The ambient air acts as the driver gas, and is separated with a single or a few layers of diaphragm made either of Mylar, cellophane or polyethylene. The diaphragm is ruptured by irradiating a single pulse laser beam of 380 J energy on to it. The results of the experiments are reported here.

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OREX (Orbital Re-entry experiment) was the first atmospheric re-entry flight experiment. It was launched by the first H-II rocket in February, 1994 from Tanegashima Space Center in Japan. Various precious flight data on hypersonic aerothermodynamics were acquired during the flight. In this paper, outline of OREX flight are described and the some characteristics of the flow around OREX are mentioned. It is shown that the flow is both in strong chemically and thermally non-equilibrium in high altitude and in chemically non-equilibrium but thermally equilibrium in lower altitude. For the precise estimation of aerodynamic heat, the effects of the finite rate catalysis should be considered and CFD results with catalytic models are compared with flight data.

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Reentry and entry vehicles flying through the earth's atmosphere or other planet's atmosphere confront severe aerodynamic heating. The severe heat flux, the complicated functional requirements due to small weight budget often impose several engineering challenges on designing of the thermal protection system (TPS) of the capsule. The key technologies related to designing of TPS of reentry capsules are summarized introducing design results of the MUSES-C reentry capsule in this paper. The chief points of these challenges are estimation of the aerodynamic heating environment and a prediction of the behavior of the thermal protection material in the flight environment. Ablation analysis code has been developed taking account of the pyrolysis gas effect and verified on the basis of heating test data in the arc wind tunnel. For slow descending by the means of parachute deployment, the sealing between components to be separated needs to be considered as a part of TPS.

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This paper reports about CORAL that is one of CanSat developed at SokaUniversity in 2002. CanSat is a small satellite developed by students and it size is 350ml can size. The mission of CORAL is to develop TNC (Terminal Node Controler) and do an experiment our TNC. We will use this TNC on our CubeSat. CubeSat is low-earth orbit satellite. It size is 10×10×10cm and mass is under 1kg. Our TNC is developed by only FPGA (Field Programmable Gate Array). We will launch this satellite on Aug. 2-3. 2002 in BlackRock desert. Nevada. US.

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We will participate in CanSat project for ARLISS (A Rocket Launched for International Student Satellites) project in 2002. CanSat is small size satellite project by students in USA and Japan. CanSat climb to 12,000-ft (40,000m) height by amateur rocket, then CanSat is released. This time, we will launch two CanSats name of PEARL (Practical Experiments Apparatus of Radiophotos for Long-distance) and CORAL (COmmunication Related Acquirement Laboratory). This paper is report on satellite system of PEARL. Missions of PEARL are acquisition of digital image by CMOS camera, transmission by 2.4GHz, 1Mbps, operation by one FPGA, and vehicle of various sensors and GPS Receiver.

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We participate in "A Rocket Launch for International Student Satellites" (ARLISS). Many Japanese and United States universities are joining in the project to design and develop small satellites called CanSat, which is called after 350ml can. The amateur rockets fly at about 12,000 feet altitude and then eject three CanSats into a 10-15 minute descent flight with each parachute. We operate the CanSats during the time of descent. We are now developing one CanSat, sized of 350ml can, and one OpenClass, sized of φ 150mm×250mm. Using CanSat, we will conduct turning flight experiment using shape memory alloy mechanism. Using OpenClass, we have two experiments. First, we will conduct a comeback experiment and control its flight direction with GPS navigation autonomously. Second, we will conduct a data relay experiment and a tracking experiment using Rover. In this paper, we will describe these three missions and subsystem designs of the CanSat and the OpenClass, and we will show the results of sub-orbit flight experiments.

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Nihon University is developing micro satellite "CubeSat" proposed by USSS and we aim at the launch in 2003. Participating in this project means that we can earn the basic know how of developing a satellite and buildup a foundation to do a simple experiment in space. We suggest the mission of our "CubeSat" as attitude estimation by measuring temperature using platinum resistance element. In this presentation, we will introduce the subsystem of our CubeSat, current status of the mission analysis, and report the result of the operation experiment in ARLISS.

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This paper describes the current status of the University of Tokyo's super-small satellite called "CubeSat". CubeSat project is the international joint program, which aims for developing and actually launching 10cm cubic satellites weighing less than 1kg to Low-Earth Orbit. University of Tokyo's CubeSat is a technology demonstration satellite to validate the pico-satellite bus system and the commercial-off-the shelf components in space as well as the Earth imaging mission. This paper shows the final design and current status of the satellite.

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Tokyo Institute of Technology (TITech) is participating in the CubeSat Project which is an international, educational, and practical project. "CubeSat" means S^3-SAT (Student, Space, Study Satellite), and the shape of the satellite is cubic. In this project, over ten universities are developing the small satellites of 100mm cubic and less than 1kg in weight which might be developed in a very short period. Eighteen CubeSats will be launched together in Spring 2003 by a Russian rocket called "DNEPR". TITech CubeSat project is called the "CUTE" (CUbical TITech Engineering satellite) project. Within this project, we are developing one CubeSat called CUTE-I, and have conducted various tests and experiments. In this paper, we explain the detail of design and development of CUTE-I, then, we report the result of final ground test.

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University of Tokyo has been developing small satellites since 1999 for educational purposes as well as technology development. So far, several types of pico-satellites including CanSats and CubeSat are designed and constructed. This paper reports history of CanSat project, Fly Back competition using CanSats, conceptual design of CubeSat II which is currently being developed and future perspective of UT's small satellite project.

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Laboratory for Space Systems (LSS), Department of Mechanical and Aerospace Engineering, Tokyo Institute of Technology (Tokyo Tech), is dedicated to promoting a Small Satellite development Program (SSP) since 1998. We succeeded in manufacturing total 10 sub-orbital CanSats (1999-2001) in the program. Moreover we started to develop a CubeSat as an orbital satellite since 2000. We have completed the first CubeSat flight model named CUTE-I and are waiting for launching it. SSP is now an educational and practical program, however, we attempt to make the program a more advanced one in future. In this report, we explain the present status and future aspect of Tokyo Tech SSP.

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This paper describes the Ground Station network (GSN) Project. The objectives of GSN are to connect ground stations that worldwide universities possess via Internet, to remote-control them to enlarge visible duration, and to share telemetry data and so on. Several Universities in Japan anticipate the GSN project and discuss about GSN protocol in USSS, UNISAT (UNISEC). We proposed adopting SOAP (Simple Object Access Protocol) for GSN transmission protocol. SOAP is an XML/HTTP-based protocol for accessing services and objects in a platform-independent manner. Up to now, we made a draft of GSN protocol for remote-control, and did fundamental remote-control experiment on the GSN protocol. In this paper, we present about GSN protocol and the result of the experiment.

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The feasibility study has been conducted to build a small satellite (so called 'nano-satellite'), which has 3-kg mass and less than 30-W power, since October in 1998. A 3-axes attitude control experiment of the nano-satellite under micro-gravity field was carried out at Japan Micro-gravity Center (JAMIC) in 2001. The small reaction wheel was used as an actuator for the attitude control developed by Hokkaido Institute of Technology as one of the important key technologies of the nanosatellite. The 3-axes attitude control by using wireless CCD camera (VHF wave) and image processing was demonstrated under micro-gravity.

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Microthrusters for nano satellites using liquid propellant are under development by MEMS technology. In order to observe the flow in vaporizing chamber, a new vaporizing microthruster is build and tested, which consists of silicon wafer and Pyrex glass with transparent ITO film resistor. The size of this thruster is 30mm×40mm and the weight is less than 4g. Obtained maximum thrust is 0.37mN with 4.8W and flow rate 5.5mg/s. Dry-out starts on thin film heater at first and appears on the opposite channel wall later. These complex phase change phenomena effect in thrust fluctuating. Several self-reactive-type monopropellant thrusters are fabricated similarly using Pt deposited on silicon wafer as a catalyst. The flow difference due to channel geometry is being explored.

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The authors have developed the practical prototype of a micro-solid propellant rocket array thruster for attitude control of a 10kg class micro-spacecraft. a target of this activity is to build the array thruster with 10000 of solid propellant micro-rockets arrayed on a 100×100mm substrate. The prototype with the Φ0.8 micro-rockets arrayed at a pitch of 1.2mm on a 20×30mm substrate has built and tested so far. Boron/potassium nitrate (NAB) propellant is used with/without initiator of lead rhodanide/potassium chlorate/nitrocellulose (RK). Impulse thrust was measured by means of a pendulum method. The experimental results show that the prototype has proper ignition characteristics and further experimental studies are needed to evaluate and to control the impulse thrust with accuracy. We are planning to conduct the thrust measurement test under vacuum condition.

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The launching project of a hybrid rocket from Taiki Multi-purpose Aerospace Park has been conducted by the research stuffs in the universities in Hokkaido. In this plan, after the flight in outer space, the rocket is taken back using a parafoil-glider with of GPS (Grobal Positioning System). The present study deals with the development of the winged vehicle to obtain the basic materials of the parafoil-glider system.

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In this study we propose a novel laser-assisted plasma thruster, in which plasma is induced through a laser beam irradiation onto a target, or a laser-assisted process, and then accelerated by electrical means instead of a direct acceleration only by using a laser beam. Inducing the short-duration conductive plasma between electrodes with a certain voltage, a short-duration switching, or a discharge is achieved, in the laser-assisted PPT. Also, reductions of energy losses to electrodes, electrodes erosion, and improvement of specific impulse through the intense current caused by the short duration discharge can be expected. Here, a fundamental study of a newly developed coaxial laser-assisted pulsed plasma thruster is conducted. Its anode consists of a cupper tube and a cathode, or a solid propellant, of a carbon rod. A DC power supply was used as the power source, and an Nd : AYG laser (wave length : 1.06μm, maximum pulse energy : 1.4J/pulse, pulse width : 10 nsec) was utilized, With this system, the peak current of about 80A with its duration of 15 nsec (FWHM) was observed in a typical case. Also, similar current with similar pulse duration was observed without the power source applied between electrodes.

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The basic experiments have been conducted to develop the staged combustion hybrid-rocket engine with two combustion chambers. In the present study, in order to understand the characteristics of the oxidizer (N_2O), the dependency on temperature was measured and the self-pressurizing supply system was tested. Moreover the combustion test was carried out. The results reveal that N_2O is useful as oxidizer of the hybrid-rocket engine.

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A joint research team of universities has been organized to develop small-scale reusable launch systems based on new type of hybrid rockets. This paper describes the project outline, development study of a new type of hybrid rocket engine, and the result of a ballistic test launch using this engine. The key design of the new type hybrid rocket engine, designated as Jet Impinging type Hybrid Rocket, is that the gas flow collides with the solid fuel surface to accelerate the heat transfer to the fuel, resulting in improved thrust level. Static firing tests with an engineering model engine with a LOX cooling system showed sufficiently prompt ignition and stable combustion. Based on these results, a flight model engine was developed to conduct a ballistic test launch. The engine worked excellently in the test launch and the result was successful, showing that te engine showed expected performance in the flight condition.

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The successful launch of a hybrid rocket with a swirling-oxidizer-type engine on march 2001 demonstrated the advantages of this type of engine and a maturity level of the propulsion. In this paper, two possible missions using this type of engine are discussed ; launching a sounding hybrid rocket to the altitude of 60 [km] and placing a micro satellite into LEO with a 3-stage hybrid rocket. To evaluate the missions, the trajectories of the vehicles were calculated and the frames of the hybrid rockets were preliminarily designed. The results show that the hybrid rockets with a swirling-oxidizer-type engine can achieve the missions with smaller frames than hose of solid rockets.

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To develop the thermal protection technologies for atmospheric re-entry vehicles, the researches have been performed on the erosion mechanism of the Carbon/Carbon (C/C) materials. The erosion and oxidation phenomena of the CVD (Chemical Vapor Deposition)-SiC thermal protection coatings are important factors in this respect. The high purity CVD-SiC samples were selected to evaluate the phenomena by comparing with those of the C/C materials. The outcomes of the previous researches indicated that the phenomena should be investigated more precisely by improving the experimental methods. This paper describes latest outcomes.

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As a preliminary step of the test by Scirocco Plasma wind tunnel using partial structure models representative of the real nose cap of the reentry vehicle, on heating rate and pressure of which the effect to the material erosion seemed to be big, by using CFD the pre-analysis was carried out. From this results the validity of this CFD code was confirmed, and there was the qualitative coincidence on the heat flux in real flight condition and heat flux in plasma wind tunnel condition. Those results suggest effectiveness of the wind tunnel test using partial structure models of the real nose cap.

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Amorphous borosilicon carbonitride stable at 1880℃ was prepared by pyrolysis of polyorganoborosilazane as the precursor for Si-N-B-C ceramics. The prepared ceramics is not only thermally stable, but the oxidation resistance is also excellent at 1700℃ in dry air. The carbon fiber reinforced borosilicon carbonitride of ceramics matrix composites (CMC) was prepared by the polymer infiltration and pyrolysis (PIP) method using polyorganoborosilazane. The CMC had good oxidation resistance up to 1200℃ in day air, which was able to be explained in relation to the properties of the ceramics.

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The paper presents experimental results for tensile creep behavior of orthogonal 3-D woven Tyranno^<TM> fiber/Si-Ti-C-O ceramic matrix composites at 1300-1450℃ in air. The composites exhibited excellent tensile properties at elevated temperature in air. For creep stresses between 60 and 140 MPa, the creep rate decreased continuously with time, with no apparent steady-state regime observed at 1300-1450℃. Under the test conditions, the microstructure of Tyranno fiber and Si-Ti-C-O matrix was unstable, resulting in weight loss and SiC grain growth. As a result, the viscosity of the fiber and matrix increased because of increase in viscosity caused a continuously decreasing creep rate, which made steady-state creep impossible under these conditions.

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The purpose of our study is to understand the shear performance of layered CFRP laminates at wide temperature range changed from room temperature to cryogenic temperature. Analytical evaluations of the v-notched specimens (Iosipescu shear test) to determine the in plane and out-of-plane (interlaminar) shear properties (modulus and strength) of layered CFRP laminates have been conducted through the finite element modeling. Analytical results were utilized to examine how closely the test would meet the requirement of an ideal shear test that there should be pure and uniform stress and strain distributions in the test region. Different correction factors of the v-notch shear specimens for in plane and out-of-plane shear property determinations are obtained respectively and will be used to modify the experimental results in the coming study.

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To realize the practically Reusable Launch Vehicle (RLV), one of the most significant technologies is drastic weight reduction of airframe weight. Instead of the conventional aluminum tank, utilization of carbon fiber reinforced plastics (CFRP) for cryogenic propellant tanks is essential to reduce the tank weight. We built a small CFRP tank by filament winding, and performed pressure test and LN2 storage demonstration. After the test, there were various amount of leakage from the various area of the tank. In this study, microscopic analyses were conducted to find the mechanism of material damage and leak path formulation. The large void in the cross section is the most predominant factor of the leakage from this tank.

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Tension and in-plane shear tests have been carried out to measure the in-plane mechanical properties of T800H/3633 CFRP woven laminates at room temperature, liquid nitrogen temperature (77 K) and liquid helium temperature (4 K). Tensile and shear tests were conducted according to the following JIS standard procedures : JIS K 7073 for tensile tests, and JIS K 7079 for shear tests. The specimen geometry utilized in the determination of the fiber-aligned strength included a dog-boned shape and wedge tabs. A two-dimensional finite element analysis was also used to study the stress distributions within the dog-bone shaped specimens and to interpret the experimental measurements.

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As a part of the present investigation has already been reported in the former information, there are a number of unclarified points regarding use of the Y-type lumbers of the excavations in Sakuramachi-Site (Oyabe City, Toyama). On the assumption that the Y-type lumbers can be used as sledges, in the present report describe on a conclusion reached by comparing simpler experiments regarding tribology of the Y-type lumbers with the results of calculation.

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Authors have performed field survey on origin of a statue of "Lions and Buddhism Wheel(法輪)" as the Indian National Emblem in Republic of India. There are many small projections between spokes on inner side of a rim of a Buddhism Wheel. Origin of projections has not been known yet for long times. In Archaeological Museum of Sanchi near Great Sanchi Stupas at third century B. C., the original form of Buddhism Wheel statue was surveyed. A spoke is tenon-jointed in a rim with a wedge. It is found that the wedges of tenon joints are the prototype of small projections of Buddhism Wheel.

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There are many factories where manufacture the material of the glaze of the pottery in Gifu Prefecture Mizunami City. The machine called toronmeru is used to make material soil the small powder there. The water wheel was spent on the power of the machine before. However, now the water wheel power is only one factory. This report studied the power transmission system of this water wheel.

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Subsequent to investigating the siewing rim mechanisme used in the revoiving stages of the Konpira-Kanamaruza theatre, we investigated the rotating mechanism of the Kurehaza theatre, constructed during Japan's Meiji Era (1868-1912) After measuring the rotational resistance of the Kurehaza theatre, stage under various conditions, we determined there was a significant difference between resistance at rotational startup and during rotation.

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The first flight in Japan is being done by Mr. Yoshitoshi TOKUGAWA and Mr. Kumazou HINO in the 43rd year of Meiji. Mr. HINO who did the first flight grappled with the development of the flight technology after that as well. He assembled that airplane at Tokyo Technical High School attached to Nippon Institute of Technology in the 44rd year of Meiji. And. He tried flight at AOYAMA and YOYOGI drill ground. As for the details of this airplane, it isn't clear. It is explained that this report was investigated about the airplane which Hino made. And, this report explains that the technology related to the airplane in those days by drawing the draft of this airplane was examined.

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Franz Reuleaux, left his name in Kinematics and Theory of Machines, collected mechanical models personally and also asked Gustav Voigt Co., German company, to make them. The 19models that were imported in Meiji era are preserved in Kyoto University. And a copy of the purchase slip is also preserved, but the contents were obscure because the original German explanation was written in "Katakana" that are Japanese characters. The collation of the purchase slip with the catalog in Cornell University made clear the contents of the purchase slip.

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Isambard Kingdom Brunel (IKB) applied the atmospheric railway, which had been used in Ireland since 1844,to the new line from Exeter to Teignmouth of the South Devon Railway (SDR) in 1847. In the atmospheric railway, the power was supplied to the trains by the suction of a piston in a huge tube laid along rails. In order to the suction power is supplied from the engine house, trains could run quietly, cleanly and cheaply, and suit to the steep gradient truck, but there were some mechanical defects : the airtight valve made of metal and leather was frozen and deterioration of the leather, and corrosion of the metal. The SDR had to pay to operate and maintain the railway systems and decided to replace them by a locomotive-hauled railway in 1849.

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The Royal Albert Bridge is Isambard Kingdom Brunel's spectacular solution to bridging the river Tamar at Saltash near Plymouth. The bridge has two spans of 139m(455ft) and a central pier was built on the rock, 24m(80ft) above the high water mark. Each of the two main spans was formed of a curved wrought iron elliptical tube. The foundations of piers were erected by the method of the pneumatic caisson. He raised the span to its position using hydraulic jacks. It was officially opened on 2th May 1859 by Prince Albert, the year of Brunel's death. The Royal Albert Bridge still carries all the rail traffic to Penzance.

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Although the vehicular diesel engine was initially introduced by both Daimler Benz and MAN in 1924,commercial activities on automotive diesel engine were began on 1930's in European country. It was very interested that these competitive situation for newly developed vehicular diesel engine was quite same in Japan in 1930's simultaneously. Although only 2 engines made in 1940 was existed in Japan already, luckily a very unique engine made by Gas-den (predecessor of Hino Motors) made in 1937 was discovered recently. This is report on this engine.

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Mr. Hiroshi HIRAOKA (1856-1934 is a famous Japanese railway engineer and he founded HIRAOKA WORKS in 1889. This WORKS is well known as passenger car and freight car builder in the Meiji period of Japan. These rolling stock supplied for not only Imperial Government Railway of Japan (IGRJ) but also many other private railways as Nippon Railway, Sangu Raiway, Tobu Railway, and so on. In this report, 1) His life, 2) Course of railway engineer, 3) Outline and short history of HIRAOKA WORKS, are described.

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In the "Mechanical Engineering Experiment", the revision of experiment themes as well as the improvement of materials and facilities has been made by the instructors in order for the students to have a better understanding of the class. One such example is the installation of an access point of wireless LAN in some laboratories and that was made the most use of in the Electric Circuit classes. Thanks to the wireless LAN, the students can bring their own lap top computers without worrying about the wiring on their desks which already have lots of experiment devices, making it possible to easily access internet sites for references. The instructors opened an Internet homepage in advance for Electric Circuit and the homepage includes A) pictures and movies for the experiments, B) related pieces of information and C) bulletin boards for students follow-ups, all of which played an important role in the class.

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Faculty of Engineering of Tamagawa University provides the recycling education as a part of Zenjin education. The project was launched five years ago for students enrolled in the Faculty of Engineering, but was extended to include the environmental education for all students two years ago, as Tamagawa Gakuen acquired a certificate of ISO14001. In this paper, we report the experiences and results of our educational activities. Specifically, the activities include 1) recycling of bicycles with legal transfer procedures and repair; 2) recycling of umbrellas with repair and reuse for the local community; 3) reuse of books with recovery and donation to foreign countries with poor educational environment; 4) practical educations for the environmental problems such as acid rain, global warming, and air pollution by document research, information retrieval and practical measurement.

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It was thought that the take-tonbo (dragonfly-shaped flying toy made of bamboo) has been originated by Gennai Hiraga (Japanese naturalist) at Edo era in Japan and it is a toy which could be made comparatively simply. Therefore many people had their experiences to make it at the times of elementary school or junior high school. In this paper, under the considerations about the principle of its flying from the measurement of lift by making use of an electric scale, the rotating stability from three moments of inertia and the balance of the masses of wing and shaft, the results of lesson practice for making the take-tonbo to junior high school students is reported.

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The study about a magnet or magnetism is contents treated in science subject at school education in Japan. In the present industry, a variety of products which used the magnet are developed, and it is necessary to learn about its practical use as application of a principle in Industry Arts and Homemaking course. Then, the teaching tools for learning the mechanism of an eddy current experiementally were developed as an example of practical use of magnet improvement, and the study effect was investigated by lesson practice. As a results og these, the work of an eddy current could be learned in experience and the concern about a magnet or science was able to be raised.

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The rapid progress of semiconductor technology promotes the digitalization of a product, and also the digitalization of infrastructure of product design by using a computer a CAD software and so on. This paper describes the progress of mechanical design technology and the importance of the education by using 3dimensional computer aided design (3DCAD) system at multimedia age.

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I is important to consider measures of the mechanical engineering of the skeleton for understanding the curriculum of design drawing by the student more, if the future image of school subject is considered. As guidance nethod of the drawing education education, the design drawing of Fukushima National College of Technology does not remain for the preparation drawing account, and the solid work which is suitable for the drawing is produced and submitted. The two or three-dimensional wind tunnel in application design drawing is designed, and the workis to complete the drawing, account and specification.

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