Aeronautical and Space Sciences Japan
Online ISSN : 2424-1369
Print ISSN : 0021-4663
ISSN-L : 0021-4663
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Volume 22, Issue 240
Displaying 1-7 of 7 articles from this issue
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  • Studies of Hypervelocity Model Launcher
    Goro KAMIMOTO, Akimasa TSUKAMOTO, Kaoru OTSUJI
    1974 Volume 22 Issue 240 Pages 1-7
    Published: 1974
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.22.1
    JOURNAL FREE ACCESS
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    A computer study for predicting the launcher performance is conducted using a one-dimensional hydrodynamics computer code which introduces an artificial dissipative term into the partial differential equations governing the motion of a compressible fluid and includes van der Waal's equation to consider the real gas effect. A two-stage launcher kinematics of the Pilot Ballistic Range at Kyoto University has been studied experimentally using mainly a microwave reflectometry system under any conditions. And experimental results of launcher performance have been compared with the computational ones. In order to maximize and optimize the performance, the launcher parameters have been investigated and discussed.
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  • Studies on the Stability and Control of Hingeless Rotors
    Part 2. Aerodynamic Design of Virtual Offset Flapping Rotors
    Tatsuya MASUE
    1974 Volume 22 Issue 240 Pages 8-16
    Published: 1974
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.22.8
    JOURNAL FREE ACCESS
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    Amethod which translate a hingeless rotor into a virtual offset flapping rotor and its application in the design criteria of stability and control are presented. The hingeless rotor is assumed to be infinitely stiff in torsional and chordwise bending, and has a flapwise flexibility with nonuniform mass and stiffness distributions. The virtual offset of the flapping hinge and the spring restraint about it are defined with the mass exciting coefficients and the rotating natural frequency, rather than with the Southwell coefficient and non-rotating natural frequency which are presented by YOUNG2) and WARD3). Therefore not only natural flapping term, but also mass excited flapping term of hingeless rotor coincide with those of the virtual offset flapping rotor, and the translating errors of aerodynamic exciting coefficients are decreased fairly in comparison with those of the straight blades of YOUNG, WARD and BRAMWELL4).
    For the stability and control design of hingeless rot r, the allowable range of blade stiffness factor, virtual offset, Losk number and deltathree angle are presented. These design parameters of hingeless rotor are specified to diminish the variation of control retardation angle with advance ratio and to decrease the gyroscopic cross coupling moment from the standpoint of flying qualities.
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  • Current Civil Transports and Future :Prospect
    Kenjiro TOKUNO
    1974 Volume 22 Issue 240 Pages 17-23
    Published: 1974
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.22.17
    JOURNAL FREE ACCESS
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  • Design Review for Space Rocket
    Tetsuji MAKINO
    1974 Volume 22 Issue 240 Pages 24-34
    Published: 1974
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.22.24
    JOURNAL FREE ACCESS
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  • Airctaft Engine Torque Meter System
    Hidemichi KIHARA
    1974 Volume 22 Issue 240 Pages 35-37
    Published: 1974
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.22.35
    JOURNAL FREE ACCESS
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  • LETTERS TO THE EDITOR
    1974 Volume 22 Issue 240 Pages 38-46
    Published: 1974
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.22.38
    JOURNAL FREE ACCESS
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  • The Way to the Development of the Japan Society for Aeronautical and Space Sciences
    Tsukumo UNO
    1974 Volume 22 Issue 240 Pages 56
    Published: 1974
    Released on J-STAGE: May 25, 2009
    DOIhttps://doi.org/10.2322/jjsass1969.22.56
    JOURNAL FREE ACCESS
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