Takeshi Hoshino

Japan Aerospace Exploration Agency, Chōfu, Tōkyō, Japan

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Publications (19)6.38 Total impact

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    ABSTRACT: This article presents a comprehensive path-planning method for lunar and planetary exploration rovers. In this method, two new elements are introduced as evaluation indices for path planning: 1) determined by the rover design and 2) derived from a target environment. These are defined as the rover's internal and external elements, respectively. In this article, the rover's locomotion mechanism and insolation (i.e., shadow) conditions were considered to be the two elements that ensure the rover's safety and energy, and the influences of these elements on path planning were described. To examine the influence of the locomotion mechanism on path planning, experiments were performed using track and wheel mechanisms, and the motion behaviors were modeled. The planned paths of the tracked and wheeled rovers were then simulated based on their motion behaviors. The influence of the insolation condition was considered through path plan simulations conducted using various lunar latitudes and times. The simulation results showed that the internal element can be used as an evaluation index to plan a safe path that corresponds to the traveling performance of the rover's locomotion mechanism. The path derived for the tracked rover was found to be straighter than that derived for the wheeled rover. The simulation results also showed that path planning using the external element as an additional index enhances the power generated by solar panels under various insolation conditions. This path-planning method was found to have a large impact on the amount of power generated in the morning/evening and at high-latitude regions relative to in the daytime and at low-latitude regions on the moon. These simulation results suggest the effectiveness of the proposed pathplanning method.
    IEEE Robotics &amp amp amp Automation Magazine 03/2015; 22(1):22-33. DOI:10.1109/MRA.2014.2381359 · 2.32 Impact Factor
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    ABSTRACT: A lunar lander SELENE-2 has been considered. It lands on the Moon's surface and performs in situ scientific observation, environment investigation.
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    ABSTRACT: The Japan Aerospace Exploration Agency (JAXA) views the lunar lander SELENE-2 as the successor to the SELENE mission. In this presentation, the mission objectives of SELENE-2 are shown together with the present design status of the spacecraft. JAXA launched the Kaguya (SELENE) lunar orbiter in September 2007, and the spacecraft observed the Moon and a couple of small satellites using 15 instruments. As the next step in lunar exploration, the lunar lander SELENE-2 is being considered. SELENE-2 will land on the lunar surface and perform in-situ scientific observations, environmental investigations, and research for future lunar utilization including human activity. At the same time, it will demonstrate key technologies for lunar and planetary exploration such as precise and safe landing, surface mobility, and overnight survival. The lander will carry laser altimeters, image sensors, and landing radars for precise and safe landing. Landing legs and a precisely controlled propulsion system will also be developed. A rover is being designed to be able to travel over a wide area and observe featured terrain using scientific instruments. Since some of the instruments require long-term observation on the lunar surface, technology for night survival over more than 2 weeks needs to be considered. The SELENE-2 technologies are expected to be one of the stepping stones towards future Japanese human activities on the moon and to expand the possibilities for deep space science.
    Acta Astronautica 11/2014; 104(2):545-551. DOI:10.1016/j.actaastro.2014.06.031 · 0.82 Impact Factor
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    ABSTRACT: We report updated status of the SELENE-2 project and some progress of development of technological aspect of the system and instruments on board.
  • 10th International Energy Conversion Engineering Conference; 07/2012
  • Hitoshi Naito · Takeshi Hoshino · Toshihiro Tani
    10th International Energy Conversion Engineering Conference; 07/2012
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    ABSTRACT: JAXA is planning exploration missions to the moon, following upon the Kaguya (SELENE) mission., These missions aim to demonstrate some new technologies, observe the moon scientifically, investigate technical, social and political feasibility of utilizing the moon. For the first step of the missions, the phase A study of SELENE-2 has started from the summer of 2007. This mission will demonstrate the effectiveness of several technologies including precision landing, hazard avoidance, surface mobility, and night survival technologies. In situ geological and geophysical observations will be conducted to improve our knowledge on the origin and the evolution of the moon. Investigating the lunar surface conditions and its potential for in situ resource utilization will provide key information for future human exploration missions. This paper presents the current status of the SELENE-2 mission, its objectives, its design, and other important aspects of its development such as international cooperation.
    Acta Astronautica 04/2011; 68(7):1386-1391. DOI:10.1016/j.actaastro.2010.08.027 · 0.82 Impact Factor
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    ABSTRACT: Japanese lunar lander, 'SELENE-II' is being planned as a successor to 'Kaguya'. SELENE-II science mission team has been actively working to maximize the science gain. In this presentation we report the current status of the science instruments and scenario.
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    ABSTRACT: In this paper, a novel structure of a prototype machine is proposed for enhanced start-up characteristics in a bearingless motor. The bearingless motor has two-axis active position regulation with only one unit. Passive magnetic bearings are constructed for improved stiffness in passively regulated movements. The passive magnetic bearings have influence in active two axis movements. A serious situation occurs at a start-up process from touched down condition. An optimization of machine design has been carried out in 3D-FEM analysis and an improved structure is proposed. Based on the design, a prototype bearingless motor is developed. It is shown that a successful start-up is achieved from the touch down displacement of 0.3 mm in experiment.
    IEEE Transactions on Magnetics 12/2008; DOI:10.1109/TMAG.2008.2001845 · 1.21 Impact Factor
  • 6th International Energy Conversion Engineering Conference (IECEC); 07/2008
  • K. Asami · A. Chiba · M.A. Rahman · T. Hoshino · A. Nakajima
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    ABSTRACT: In this paper, a magnetically suspended drive is proposed with two-axis active position regulation having one unit of a bearingless motor for possible flywheel applications. For the other unit, a three-axis positioning is supported by passive magnetic bearings. Basic force and stiffness characteristics are investigated by three-dimensional (3-D) magnetic-field analysis.
    IEEE Transactions on Magnetics 11/2005; DOI:10.1109/TMAG.2005.854933 · 1.21 Impact Factor
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    ABSTRACT: A fundamental study on solar Stirling power generation system has been performed as a part of the space solar power technology program in National Aerospace Laboratory (NAL). The research work involves both a solar receiver and Stirling power generation technologies. The former work is focused on developing a high efficiency solar receiver for future space energy experiments on the Japan Experiment Module-Exposed Facility of the International Space Station. It is composed of a cavity receiver, thermal energy storage and sodium heat pipes, and aims at transporting solar heat to a bottoming system with the minimized heat loss. A ground test model of the solar receiver will be experimentally evaluated in NAL. In parallel, semi-free piston Stirling engine generators have been experimentally studied as one of the candidate converters for future space power generation. Through a series of bench tests, the thermodynamic efficiency of 32% and system efficiency of 20% was obtained. Based on these achievements, the design work for an improved Stirling generator system is underway
    Energy Conversion Engineering Conference and Exhibit, 2000. (IECEC) 35th Intersociety; 02/2000
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    ABSTRACT: A fundamental study was performed to develop a high efficiency solar heat receiver system for a solar energy experiment mission on the Japanese Experiment Module (JEM)-Exposed Facility (EF) of the International Space Station (ISS). This system is aimed to transport solar thermal energy to a bottoming system with a high efficiency. It is composed of a solar heat absorber, thermal energy storage (TES) and heat pipes (HPs). Solar light of approximately 1.8 kW is concentrated on a focal plane of the absorber aperture, and then net thermal heat of 1.3 kW is transported to the HP and supplied to a bottoming element such as a Stirling engine alternator, an AMTEC and a furnace for material processing. Uniform heating of HPs were confirmed using a secondary mirror and C/C composite receiver. One ground testing model of the solar receiver was designed and fabricated in 1998, and then experimentally evaluated at a test vacuum chamber of National Aerospace Laboratory. The receiver was heated uniformly and the good heat conduction at the interfaces (receiver-HP, and HP-TES) was confirmed. The periodic sunshine/sunshade mode occurs on the orbit JEM-EF of ISS. The thermal cycle test was performed to demonstrate sunshine/shade modes using the ground testing model. The temperatures of components changed periodically and the heat transfer rates of 100 W at sunshine mode and 75 W at sunshade mode were derived
    Energy Conversion Engineering Conference and Exhibit, 2000. (IECEC) 35th Intersociety; 02/2000
  • T Sho · Y Mukose · T Hoshino · T Suzuki · M Oikawa
    Rinsho hoshasen. Clinical radiography 06/1973; 18(5):366-9.
  • S Tarusawa · H Otake · M Watanabe · Y Tamakawa · T Hoshino
    Rinsho hoshasen. Clinical radiography 07/1970; 15(6):436-9.
  • Source
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    ABSTRACT: Since 1999, we have been developing space debris observation technologies. For this purpose, small optical observation facilities were constructed; 0.35-m Schmidt Cassegrain(SC) telescope on the X-Y mount tracking system for LEO debris observation and 35 cm Newton-type telescope on the equatorial mount for GEO debris observation. High-speed read-out CCD camera with 4K • ~ 4K elements and its cooling system have been developing for the detection of faint objects. Automatic debris detection software has been also developing for the future efficient observation. This paper describes the space debris optical observation facilities a nd detecting technologies developed by Japan Aerospace Exploration Agency (JAXA).
  • H. Otake · T. Suzuki · M. Oikawa · T. Hoshino
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    ABSTRACT: The C-G capsule (C-G), which contains 89 mg of L-cysteine and 120 mg of ; glucose in one capsule, was administered to the patients treated with ; irradiation, and protective effects of C-G on radiation injury were studied from ; the change of the leukocyte number before and a week after irradiation. Cases ; treated with irradiation were 25 cases including 10 cases of cervical uterus ; tumor. Radiation sources used in therapy were telecobalt, 10 MeV x-ray of linac, ; and 8 MeV electron beam. A dose of 4000 to 18,000 rads was delivered. In ten ; cases of cervical uterus tumor, 6690 to 7350 rads air dose was delivered to the ; lower extremities at opposing two fields. Six C-G capsules were administered ; daily from the beginning of irradiation until a week afterwards. Six cases ; except cervical uterus tumor showed change of the leukocyte number within plus ; or minus 10%, four cases of cervical uterus tumor and four cases except cervical ; uterus tumor showed a 10 to 20% decrease of the leukocyte number, and five cases ; of cervical uterus tumor and five cases except cervical uterus tumor showed a 20 ; to 50% decrease. A case of cervical uterus tumor showed a 30 to 40% increase. ; An actual leukocyte number in 1 mm³ was decreased from 4840 to 4390 in ten ; cases of cervical uterus tumor (24% reduction) and it was decreased from 6727 to ; 5520 in cases except cervical uterus tumor (18% reduction). Concerning reduction ; of the leukocyte number, C-G was suspected to act protectively. (JA);
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    ABSTRACT: Numerous post-mission launchers/satellites and the fragments generated by several explosions of themselves, called space debris, are still left in orbit. For the detection and orbit determination of space debris, ground-based optical telescopes have been used since last year in Japan. NAL has prepared high-speed tracking facility onboard 0.35 meter Schmidt Cassegrain(SC) telescope for LEO large debris/satellite observation at NAL headquarter in Tokyo. For GEO debris observation, the 0.45 meter telescope has been used at Yatsugatake in Nagano. The 1 meter telescope, which is now under construction at Bisei in Okayama will be used for smaller space debris detection. Some technological items such as development of automatic debris detecting software, small and less-vibratory refrigerator for the cooling of detecting devices, figure and attitude motion estimation and the construction of observation network system have been proceeded at NAL.