The Journal of Space Technology and Science
Online ISSN : 2186-4772
Print ISSN : 0911-551X
ISSN-L : 0911-551X
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Volume 6, Issue 1
Displaying 1-4 of 4 articles from this issue
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Articles
  • Results of Voyager-2 Neptune/Triton Encounter Radio Science Experiment at Usuda
    Tomonao HAYASHI, Toshimitsu NISHIMURA, Haruto HIROSAWA, Tadashi TAKANO ...
    1990 Volume 6 Issue 1 Pages 1_1-1_10
    Published: 1990
    Released on J-STAGE: August 31, 2013
    DOIhttps://doi.org/10.11230/jsts.6.1_1
    JOURNAL FREE ACCESS
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    The Voyager 2 encountered with the giant planet Neptune and its moon Triton on October 25, 1989. Plenty of brand new discoveries were made using two TV cameras and a radio science system onboard the spacecraft. At the time of the closest approach to Neptune, the US ground stations could not track the Voyager 2 because of the phase of rotation of the earth. So the Usuda Deep Space Center with 64m diameter antenna which belongs to the Institute of Space and Astronautical Science, Japan, was used as one of the ground stations to support the radio science experiment. In this paper we report the quick results of the Voyager 2 Neptune/Triton encounter radio science experiment at Usuda.
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  • In-Orbit Technology Experiments with a Small Satellite Debut
    Atsushi NAKAJIMA, Shigeru TOMOYA, Yoko NISHlO, Hisao YAHAGI
    1990 Volume 6 Issue 1 Pages 1_11-1_20
    Published: 1990
    Released on J-STAGE: August 31, 2013
    DOIhttps://doi.org/10.11230/jsts.6.1_11
    JOURNAL FREE ACCESS
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    This paper describes the results of the in-orbit performance testing of deployable and retractable umbrella (ADB : Aerodynamic brake) and boom systems, which will be used as important subsystems of Boomerang/Tether satellites. For this technology verifications, a small and inexpensive satellite, named DEBUT (Deployable Boom and Umbrella Test Satellite), was developed in a short period of 1.5 years elapsing from the start of the detailed design until the launch of the mission. The lithium primary batteries were used as the power source and supplied enough power to all subsystems during 10 days mission lifetime. ADB and Boom were repeatedly deployed and retracted and their telemetry data showed that they functioned normally and no malfunctions were observed. The attitude motion was also analyzed by evaluating the data of analog sun sensors.
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  • Fault Tolerant Computer Systems for Autonomous Spacecraft
    Norimasa YOSHIDA, Nobuo NAKAGAWA, Shunji MANABE
    1990 Volume 6 Issue 1 Pages 1_21-1_31
    Published: 1990
    Released on J-STAGE: August 31, 2013
    DOIhttps://doi.org/10.11230/jsts.6.1_21
    JOURNAL FREE ACCESS
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    The concept and test results of two types of fault tolerant space-borne computer systems are presented. One is a duplex system using two generic CPU’s, and the other is a hierarchical system with a specially developed fault tolerant CPU as a core processor and a generic CPU as an application processor. It is shown that a set of different system requirements and design constraints leads to a different fault tolerant architecture of the computer. It is also shown that the diversity of failure modes which can arise as a result of single event upset in the internal registers of the CPU is a major design factor whenever a generic CPU is applied. The fault tolerant operation of the two systems were demonstrated through laboratory experiments. The engineering model of the latter system is currently under development test.
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  • Geostationary Service Vehicle (GSV) and Its Potentiality in Space Business
    Yoshitsugu YASUI, Tetsuo YASAKA
    1990 Volume 6 Issue 1 Pages 1_32-1_39
    Published: 1990
    Released on J-STAGE: August 31, 2013
    DOIhttps://doi.org/10.11230/jsts.6.1_32
    JOURNAL FREE ACCESS
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    The geostationary service vehicle (GSV) is intended to provide a commercially viable on-orbit servicing system. By confining customers to GEO satellites and eliminating, in its introductory phase, those services which require large amount of consumables, the cost efficient service system can be achieved. GSV drifts along the GEO and visits a number of satellites on demand. It is capable to operate without retrieval or supply making more than 200 rendezvous during its own life. The primary service is to obtain visual and non-contact measurement informations by approaching the customer satellite to tens of meters. The secondary services are to assist the malfunctioned satellite recovery and in-operative satellite re-orbiting by grapple operation.
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