Aeronautical and Space Sciences Japan
Online ISSN : 2424-1369
Print ISSN : 0021-4663
ISSN-L : 0021-4663
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Volume 36, Issue 410
Displaying 1-8 of 8 articles from this issue
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  • Readying for the Development of Space Station
    Summary of the 3rd Space Station Symposium
    [in Japanese]
    1988 Volume 36 Issue 410 Pages 103-111
    Published: March 05, 1988
    Released on J-STAGE: December 16, 2010
    DOIhttps://doi.org/10.2322/jjsass1969.36.103
    JOURNAL FREE ACCESS
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  • Liquefied Air Cycle Engine (LACE)
    Hiroyuki HIRAKOSO, Takahiro SUZUKI, Atsutaro WATANABE
    1988 Volume 36 Issue 410 Pages 111-118
    Published: March 05, 1988
    Released on J-STAGE: December 16, 2010
    DOIhttps://doi.org/10.2322/jjsass1969.36.111
    JOURNAL FREE ACCESS
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  • Report on Joint USA/Japan Seminar on “Mathematical Modelling in Combustion Science”
    Tadao TAKENO
    1988 Volume 36 Issue 410 Pages 119-122
    Published: March 05, 1988
    Released on J-STAGE: December 16, 2010
    DOIhttps://doi.org/10.2322/jjsass1969.36.119
    JOURNAL FREE ACCESS
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  • Reliability Evaluation on On-board Satellite Antenna Deployment Mechanism
    Masayoshi MISAWA, Shojiro MIYAKE, Tetsuo YASAKA
    1988 Volume 36 Issue 410 Pages 125-130
    Published: March 05, 1988
    Released on J-STAGE: December 16, 2010
    DOIhttps://doi.org/10.2322/jjsass1969.36.125
    JOURNAL FREE ACCESS
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    A procedure is proposed to evaluate the reliability of antenna deployment mechanism (ADM) which is a key technology in large satellite antenna development. Because of lack in basic reliability data on space mechanical components, a realistic evaluation procedure needs careful selection of test items for cost and time saving. The Failure Mode and Effects Analysis (FMEA) is conducted to identify all possible failure modes, among which the critical modes are selected for further investigations. The bearing performance and friction are found to be critical, and detailed tests are performed. The test results show that the deployment and friction torque distributions can be assumed as normal distributions. The deployment reliability of the ADM was calculated based on these distributions. This paper also describes the method to prevent the failure derived from the reduction in bearing clearance.
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  • Thermal Analysis Method of Heat Pipe Embedded Equipment Panel of Communications Satellite
    Hiroaki TSUNODA
    1988 Volume 36 Issue 410 Pages 131-138
    Published: March 05, 1988
    Released on J-STAGE: December 16, 2010
    DOIhttps://doi.org/10.2322/jjsass1969.36.131
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    The thermal analysis method for the heat pipe embedded equipment panel of communications satellite is presented. The analytical model of the honeycomb sandwich panel embedded with heat pipes is developed and evaluated by the experiments. The new method to predict temperature distribution of the entire communications equipment panel precisely without the increase of computer CPU memory size is proposed. It works even when the large number of communications transponders are put on the panel. The correctness of the method is also confirmed by the experiment.
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  • A Study on Flaw Detection Method for CFRP Composite Laminates (1st Report)
    The Measurement of Crack Extension in CFRP Composites by Electrical Potential Method
    Kazumasa MORIYA, Takashi ENDO
    1988 Volume 36 Issue 410 Pages 139-146
    Published: March 05, 1988
    Released on J-STAGE: December 16, 2010
    DOIhttps://doi.org/10.2322/jjsass1969.36.139
    JOURNAL FREE ACCESS
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    An in-service flaw detection and estimation method for CFRP composites using electrical potential drop is developed. It involves passing a constant current through composites and measuring the electrical potential, which changes as the crack advances. The resister network analysis of the random lattice model of CFRP composites shows that even in the plane normal to the fiber direction, CFRP composites can be considered as electrically homogeneous on a gross scale, i. e., on a scale of dimensions dozens of times large compared with the fibre radius. The analysis also shows that the method can detect the small increment of crack growth in CFRP composites with only a fraction of current that is required for metals. The relation between the amount of the crack growth and the potential change is expressed by a broken line composed of two straight lines. The method is applied to the delamination test of the DCB composite laminate specimen and the results are compared with the FEM solutions. The present method can provide accurate and inexpensive means for flaw detection and crack growth measurement in CFRP composite structures.
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  • Numerical Computation of Dynamic Stress Intensity Factor for Impact Fracture Toughness Test
    Motohiro NAKANO, Keizo KISHIDA
    1988 Volume 36 Issue 410 Pages 147-154
    Published: March 05, 1988
    Released on J-STAGE: December 16, 2010
    DOIhttps://doi.org/10.2322/jjsass1969.36.147
    JOURNAL FREE ACCESS
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    Consideration of inertia effect is important to estimate the stress intensity factor for impact fracture toughness test. In the present paper the dynamic stress intensity factor K(t) is calculated from K(t)=α(t)·Kstat, where α(t) is the impact response function and Kstat is the corresponding static value. The α(t) is computed by superimposing the step response function h(t). The h(t) for the crack, subjected to step load, is evaluated using the finite element method. The numerical computation of K(t) is carried out for the experiment introduced by Costin et al. The results indicate the good applicability of this method for the determination of the impact fracture toughness K1d.
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  • [title in Japanese]
    [in Japanese]
    1988 Volume 36 Issue 410 Pages 155-158
    Published: March 05, 1988
    Released on J-STAGE: December 16, 2010
    DOIhttps://doi.org/10.2322/jjsass1969.36.155
    JOURNAL FREE ACCESS
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