Aeronautical and Space Sciences Japan
Online ISSN : 2424-1369
Print ISSN : 0021-4663
ISSN-L : 0021-4663
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Volume 29, Issue 329
Displaying 1-6 of 6 articles from this issue
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  • An Overview of System Safety and the Safety Disciplines in the United States (Part 2)
    Naohiro YUHARA, Ted. S. FERRY
    1981 Volume 29 Issue 329 Pages 283-291
    Published: June 05, 1981
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.29.283
    JOURNAL FREE ACCESS
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  • Report on the 12th Congress of the International Council of the Aeronautical Sciences
    Nobuhiko KAMIYA
    1981 Volume 29 Issue 329 Pages 292-295
    Published: June 05, 1981
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.29.292
    JOURNAL FREE ACCESS
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  • Conversion Table of the Units of the International System (SI) in Aeroand Space-Engineerings
    Akira AZUMA
    1981 Volume 29 Issue 329 Pages 296-303
    Published: June 05, 1981
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.29.296
    JOURNAL FREE ACCESS
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  • Accuracy of Numerical Methods for Subsonic Quasi Lifting Lines
    Akio ICHIKAWA, Shigenori ANDO
    1981 Volume 29 Issue 329 Pages 304-313
    Published: June 05, 1981
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.29.304
    JOURNAL FREE ACCESS
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    In our previous papers, accuracy of numerical methods for two dimensional lifting airfoils in inviscid flow were investigated. In this paper, these works are extended to the spanwise problem, namely quasi-lifting lines. Two interpolation methods and five Vortex Lattice Methods are compared, which have cotφ/2 mode and δ mode of chordwise load distributions respectively. In addition, one hybrid method is also investigated.
    Accuracy of numerical solutions are estimated using "normalwash comparison method+relative error method." Interpolation methods need about six times larger computational time than those of Vortex Lattice Methods at the same numbers of loading points. For numerical accuracy, the Vortex Lattice Method having semi-circle spanwise division without tip-inset is best. Vortex Lattice Methods and interpolation methods converge to slightly different solutions, which result from the assumptions of dissimilar chordwise load distributions. The discrepancy between them however causes no practical problems.
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  • Plastic Large Deformation Analysis of Cylindrical Shell by Using Pseudo-Equilibrium Hybrid Element (2nd Report) Dynamic Response
    Yoshihiro TAKI, Takeo MIYAIRI, Tatsuaki KOMATSU, Toru NISHIMURA
    1981 Volume 29 Issue 329 Pages 314-320
    Published: June 05, 1981
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.29.314
    JOURNAL FREE ACCESS
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    Using the pseudo-equilibrium hybrid element, we formulate the equation of motion which the structures are subjected to the plastic large deformation. And the dynamic responses of cylindrical shell, which is simply supported at both ends and compressed in the direction of its axis, are examined. In this study it is restricted us to consider an axisymmetrical deformation. As a result, it is recognized that the amplitude of prescribed load and the deformation velocity cause the apparent differences of deformation modes compared with the static one.
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  • Shear Buckling Strengths of CFRP Laminated Panels (1st Report)
    Kiyohide SUMIHARA, Shigeo KOBAYASHI, Kazuo KOYAMA
    1981 Volume 29 Issue 329 Pages 321-332
    Published: June 05, 1981
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.29.321
    JOURNAL FREE ACCESS
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    The shear buckling strengths of twelve kinds of CFRP laminated square panels clamped on each edge were investigated experimentally and analytically. The experiments were performed by a newly designed test apparatus. Finite element method based on modified HELLINGERREISSNER principle was employed in order to analyse the post-buckling large-deflection behavior. Except unidirectional laminated panels, there is almost satisfactory agreement between the analytical and experimental results for both the buckling load and the post-buckling behavior, and the following properties are disclosed. 1) The buckled shape is three half-wave type and the failure occurs without secondary buckling phenomena. 2) Both buckling load and maximum load vary depending on the stacking sequence of twelve plies of lamination. 3) As for the panels which contain a lot of +45° plies, the effects of material nonlinearity of shear modulus appear before failure. 4) In the case of the present length-thickness ratio which is 200mm/1.4mm, the maximum load is fairly greater than the buckling load, and therefore CFRP panels can be used in the post-buckling state. However, it is noteworthy that the CFRP panel fails almost elastically, different from duralumin plates. 5) From the view point of the maximum load, the FEM analysis yields either [3(0°, 90°)/sym.] or [3(90°, 0°)/sym.] is the optimum lamination, however the experiment yields [2(90°, 0°), -45°, +45°/sym.] is optimum.
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