JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
Online ISSN : 2432-3691
Print ISSN : 1344-6460
ISSN-L : 1344-6460
Volume 55, Issue 637
Displaying 1-7 of 7 articles from this issue
Articles
  • Kazuhide Kodeki, Yasuhiro Kashiwagi, Shiro Miki, Makoto Endoh, Osamu I ...
    2007 Volume 55 Issue 637 Pages 57-64
    Published: 2007
    Released on J-STAGE: April 10, 2007
    JOURNAL FREE ACCESS
    The solar observation satellite “SOLAR-B,” which is being developed under the joint cooperation of JAXA and NAOJ with the U.S.A. (NASA) and the U.K. (PPARC), will be launched in summer 2006. SOLAR-B requires very high pointing stability for its three telescopes. In particular, the Solar Optical Telescope (SOT), which has the highest resolution and narrowest field of view among these telescopes, requires 0.06 [arcsec] of short-term (10[s]) stability to meet the observation demands. However, it is very difficult to achieve such levels of stability by only using the satellite attitude control system due to disturbance from the observation equipment. Therefore, we propose using the Correlation Tracker and tip-tilt Mirror package (CTM), which stabilizes the sun observation image. CTM consists of a correlation tracker and a piezo-based tip-tilt mirror with servo control electronics. This paper describes the mechanism and the control and determination methods of the control gain of CTM as well as the results of experiments conducted to clarify its capability.
    Download PDF (963K)
  • Akio Kato, Genyo Matsubara, Takeshi Nakamura
    2007 Volume 55 Issue 637 Pages 65-73
    Published: 2007
    Released on J-STAGE: April 10, 2007
    JOURNAL FREE ACCESS
    Motion of aircraft controlled by the pilot is decided depending on the characteristics of man-machine system. Although analysis and study using the mathematical model of the aircraft including the control system is usually done, the method for making mathematical model of pilot, which is necessary for analysis and study of man-machine system, has not been established. Although there was an example of the method for making mathematical model of pilot using transfer function (Kato, A., et al., J. Jpn. Soc. Aeronaut. Space Sci., 50 (2002), pp. 409–415), it was thought that there was a possibility that a more accurate, more flexible pilot model was obtained if neural networks (NN) was applied. Therefore, various studies were done concerning pilot model to which NN is applied. As a result, it has been understood that pilot model with better performance is obtained comparing with the case of applying the transfer function. Moreover, it has been understood also that versatile pilot model, which can deal with various conditions by one model, is obtained by applying NN and studying the control results in various conditions.
    Download PDF (520K)
  • Makoto Mizoguchi, Shigeru Aso
    2007 Volume 55 Issue 637 Pages 74-81
    Published: 2007
    Released on J-STAGE: April 10, 2007
    JOURNAL FREE ACCESS
    A numerical analysis of a piston motion in a free piston driver has been conducted including a diaphragm rupture. Quasi-one-dimensional flow is assumed in the driver. Various losses, which are generated in a compression process, are simplified. A process of the diaphragm rupture is assumed by Outa’s model. Experiments are also conducted by using a free piston shock tunnel. Calculated pressure histories show excellent agreements with experimental results. The numerical analysis shows that the piston motion is strongly affected by the diaphragm rupture. Especially, pressure histories in front of the piston change significantly with compact compression tubes. Diaphragm opening time is necessary to be considered to increase test time and to obtain soft landing conditions in compact free piston drivers.
    Download PDF (933K)
  • Masahito Hayakawa, Osamu Kobayashi
    2007 Volume 55 Issue 637 Pages 82-88
    Published: 2007
    Released on J-STAGE: April 10, 2007
    JOURNAL FREE ACCESS
    A flight simulator must exactly simulate the aircraft motion. So, engineers check if the solution of equations of motion, the calculation of flight positions and attitudes, and then, the drawn-up of visual scenery from cockpit windows according to the calculated positions and attitudes are correct. This paper proposes an additional check if the aircraft motion perceived from visual scenery by pilot is same as the calculated motion. This opinion is applied to the simulation case that just lateral-directional flying qualities are evaluated, and it is found that the pitching motion rate (q) and Euler’s pitch attitude rate (Θ) should not be perfectly neglected (i.e. q=Θ=0) but (q and Θ) should be given assuming steady level turn flight should be given. The flight simulator test showed that the pilot felt more real flight motion and controlled some harder than in the condition of q=Θ=0.
    Download PDF (933K)
  • Tianshunag Fu, Fumiaki Imado
    2007 Volume 55 Issue 637 Pages 89-97
    Published: 2007
    Released on J-STAGE: April 10, 2007
    JOURNAL FREE ACCESS
    DAS (Dive and Ascent Satellite) is a kind of satellite that can approach very close to the earth, which was designed by NAL (National Aerospace Laboratory of Japan) in later 1970’s. Now we paid attention to the function of the satellite that can descend and ascend, and proposed to use it for getting detailed information of the area which is suffered from a natural disaster. In this paper orbital control of DAS with minimum fuel consumption is discussed, where the earth is treated as an ellipsoid of revolution, the atmosphere drag and the second zonal coefficient is considered. The optimal orbital control problems are treated as nonlinear two point boundary problems, and solved by the steepest ascent method. The derivation of equations and results are shown in detail.
    Download PDF (861K)
  • Jun Osaka, Yoshitaka Uriuda, Osamu Imamura, Kiyotaka Yamashita, Shuhei ...
    2007 Volume 55 Issue 637 Pages 98-103
    Published: 2007
    Released on J-STAGE: April 10, 2007
    JOURNAL FREE ACCESS
    An experimental research on supersonic combustion of kerosene in a model scramjet combustor has been conducted. Kerosene was injected normally into a Mach 2 by three types of methods. First, liquid kerosene was directly injected. In comparison with hydrogen, combustion did not take place at low total temperature or in the fuel lean condition. Secondly, “effervescent atomization” method was used. Effervescent atomization method could control penetration height and mass flow rate independently, and improve ignition limits of liquid kerosene. Finally, gaseous kerosene was used. While only intensive combustion mode and choke mode were observed when liquid kerosene was used, existence of transition mode was observed when gaseous kerosene was used.
    Download PDF (696K)
  • Atsushi Hashimoto,, Yasuyuki Furuta,, Naoto Yagi, Yoshiaki Nakamura
    2007 Volume 55 Issue 637 Pages 104-110
    Published: 2007
    Released on J-STAGE: April 10, 2007
    JOURNAL FREE ACCESS
    The problem of low subsonic delta wing flutter was studied experimentally and numerically. Two kinds of oscillation: low- and high-amplitude oscillation modes were observed in experiment. Moreover, the transition velocity between the two modes significantly depends on angle of attack. When angle of attack is high, the transition from low- to high-amplitude mode is made more suddenly. The flutter velocity obtained in the present experiment shows good agreement with other experimental data as well as results of the present computation. In addition, the flow field around an oscillating delta wing with large deformation is made clear, where vortex motion is coupled with wing motion. It is found that aerodynamic force produced by the vortex near the wing leading edge is closely related with the large amplitude wing oscillation.
    Download PDF (614K)
feedback
Top