Aeronautical and Space Sciences Japan
Online ISSN : 2424-1369
Print ISSN : 0021-4663
ISSN-L : 0021-4663
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Volume 27, Issue 302
Displaying 1-7 of 7 articles from this issue
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  • Accident Analysis Study of the System Safety Activities
    Mitsutake YANAGISAWA, Yasuhiro YAMAGUCHI
    1979 Volume 27 Issue 302 Pages 109-119
    Published: March 05, 1979
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.27.109
    JOURNAL FREE ACCESS
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  • Trends in Active Flutter Suppression
    Hidetsugu HORIKAWA
    1979 Volume 27 Issue 302 Pages 119-126
    Published: March 05, 1979
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.27.119
    JOURNAL FREE ACCESS
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  • Development of Launch Vehicles for Space Observation
    7. Development of Scientific Sounding Rockets and Progress of Scientific Satellite Program-from my note-books (Part 3)
    Shigebumi SAITO
    1979 Volume 27 Issue 302 Pages 127-135
    Published: March 05, 1979
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.27.127
    JOURNAL FREE ACCESS
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  • Report on the 11th International Council of the Aeronautical Sciences
    Ryuma KAWAMURA
    1979 Volume 27 Issue 302 Pages 136-146
    Published: March 05, 1979
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.27.136
    JOURNAL FREE ACCESS
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  • Lift on a Slender Wing with a Nonuniform Flight Velocity
    Shigenori ANDO
    1979 Volume 27 Issue 302 Pages 147-150
    Published: March 05, 1979
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.27.147
    JOURNAL FREE ACCESS
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    As an example of lifting wings in nonuniform flight speeds, slender wings are studied. The flight speeds may be subsonic, transonic, or supersonic. It is found that the lift force and lift distribution are affected explicitly by the instant acceleration, and not by the whole history of the past flight. It makes a clear contrast to usual non-slender wings. An acceleration (a deceleration) increases (decreases) the lift force, from that for a constant flight speed. The reason of this result is inferred. An important dimensionless quantity, "reduced acceleration, " is defined by UC0/UU2, where U is acceleration, C0 is maximum wing chord, and U is the instant flight speed.
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  • The Geometrical Non-Linear Analysis of a Monocoque Structure
    Tosaku TAKAMURA, Toru NISHIMURA
    1979 Volume 27 Issue 302 Pages 151-159
    Published: March 05, 1979
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.27.151
    JOURNAL FREE ACCESS
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    Monocoque structures, which are considered as an assembly of a number of rods and pannels, are generally analyzed by the usual method. But the stiffness of the thin plate element is largely changed due to effects of buckling, large deflection and others. To account for these features, some particular devices may be introduced, otherwise the use of the more refined mesh or adequate discretion becomes essential to obtain suitable results. The present paper gives a convenient representation for the stiffness matrix of the rectangular and curved panel surrounded by stiffeners. The expression is an incremental relation between some modes of membrane stresses distribution, surface pressure and deflections or deformation of the plate, where the matrix elements also depend on the total membrane stresses and deflections. Using this relation, analysis of the total structure may be easily performed by the well-known incremental load method. Several numerical examples are shown, where number of modes used is 27 in stress distribution, and 15 in deflection. Comparing these results with the exact solution, it is proved that the expression is sufficient for practical use.
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  • Estimation of Induced Rolling Moment
    Shin-ichi NAKAO, Michiyoshi NAMIKI
    1979 Volume 27 Issue 302 Pages 159-166
    Published: March 05, 1979
    Released on J-STAGE: January 13, 2010
    DOIhttps://doi.org/10.2322/jjsass1969.27.159
    JOURNAL FREE ACCESS
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    The Semi-empirical formula of estimating the induced rolling moment has been developed. This formula is based on the concept that the magnitude of induced rolling moment is ruled by the dimension and structure of vortex wake behind missile, and is represented as a function of the parameter describing the relative dimension of vortex wake to the fin span. Since the formula includes a few assumptions and experimental parameters, agreement between the theory and experiment is not always good. However, the formula is useful to get qualitative understanding of the effect of induced rolling moment on missile, and moreover will give correct quantitative results if employed under accurate underStanding of the flow field around missile.
    Presented in this paper are application of the formula to cruciform missile, comparisons between the flight data of sounding rockets and the simulation results obtained by this formula, and finally the effect of fin design on induced rolling moment.
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