Kazuhide Kodeki
Mitsubishi Electric
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Publication
Featured researches published by Kazuhide Kodeki.
Proceedings of SPIE | 2004
Toshifumi Shimizu; Shin'ichi Nagata; Chris Edwards; Theodore D. Tarbell; Yasuhiro Kashiwagi; Kazuhide Kodeki; Osamu Ito; Hiroyuki Miyagawa; Masayuki Nagase; Syunsaku Inoue; Kazumasa Kaneko; Yasushi Sakamoto; Kiyoshi Ichimoto; Saku Tsuneta; Shiro Miki; Makoto Endo; Masaki Tabata; Toshitaka Nakaoji; Keiichi Matsuzaki; Ken Kobayashi; Masashi Otsubo; Yoshinori Suematsu; K. Kumagai; Motokazu Noguchi; Tomonori Tamura; Masao Nakagiri
Extremely stable pointing of the telescope is required for images on the CCD cameras to accurately measure the nature of magnetic field on the sun. An image stabilization system is installed to the Solar Optical Telescope onboard SOLAR-B, which stabilizes images on the focal plane CCD detectors in the frequency range lower than about 20Hz. The system consists of a correlation tracker and a piezo-based tip-tilt mirror with servo control electronics. The correlation tracker is a high speed CCD camera with a correlation algorithm on the flight computer, producing a pointing error from series of solar granule images. Servo control electronics drives three piezo actuators in the tip-tilt mirror. A unique function in the servo control electronics can put sine wave form signals in the servo loop, allowing us to diagnose the transfer function of the servo loop even on orbit. The image stabilization system has been jointly developed by collaboration of National Astronomical Observatory of Japan/Mitsubishi Electronic Corp. and Lockheed Martin Advanced Technology Center Solar and Astrophysics Laboratory. Flight model was fabricated in summer 2003, and we measured the system performance of the flight model on a laboratory environment in September 2003, confirming that the servo stability within 0-20 Hz bandwidth is 0.001-0.002 arcsec rms level on the sun.
2011 International Conference on Space Optical Systems and Applications (ICSOS) | 2011
Katsumasa Miyatake; Yuta Fujii; Masaki Haruna; Kazuhide Kodeki; Shiro Yamakawa; Tatsuyuki Hanada
Laser-based optical inter-satellite communication equipment enables large capacity communication, which is essential for future observation satellites that handle huge amounts of data. One of the key technologies for optical inter-satellite communication equipment is the rapid, highly accurate acquisition and tracking of the corresponding satellite. Therefore we are developing a prototype of an acquisition and tracking system. Key specifications and experimental results of the sensor for the system are described in this paper.
Journal of Spacecraft and Rockets | 2004
Kazuhide Kodeki; Kazuhiko Fukushima; Masao Inoue; Toshio Kashiwase; Toshifumi Shimizu; Taro Sakao; Ryouhei Kano; Hirohisa Hara; Shin'ichi Nagata; Tsuyoshi Yoshida; Saku Tsuneta
The tip-tilt mirror (TTM) system was developed for the extreme ultraviolet (XUV) Cassegrain telescope aboard the Institute of Space and Astronautical Science sounding rocket. The spatial resolution of the telescope is about 5 arcsec, whereas the rocket pointing is only controlled to be within ±0.5 deg of the target (sun) without additional stability control. To stabilize the XUV image within about 5 arcsec on the focal plane, the TTM system controls the tilt of the secondary mirror with two-axis fixed-coil magnetic actuators. The TTM system has a wide tilt angle and can drive the large secondary mirror at high frequency. The two position-sensitive detectors, one placed in the telescope and the other in the TTM mechanical structure, are used for closed-loop control of the TTM. The closed-loop control system, which has command and telemetry, is executed by the flight software on the digital signal processor. The TTM has a launch-lock mechanism to protect against launch vibrations up to about 16G. The sounding rocket was launched from the Kagoshima Space Center on 31 January 1998. The TTM worked perfectly during the flight and achieved better than the expected 5-arcsec stability on the focal plane during CCD charge-coupled device exposures.
Proceedings of SPIE | 2015
Masaki Haruna; Kazuhide Kodeki; Seiichi Shimizu; Kazuhiko Fukushima; Osamu Takahara; Toshiyuki Ando; Eisuke Haraguchi
Micro vibrations generated from some internal disturbance sources such as a reaction wheel degrades the pointing stability of an observation satellite. To suppress the pointing error, we have been developing an inertial stabilization unit. A prototype mechanism is designed based on concepts that it has non-contact actuators and sensors, and rotational leaf springs are applied to support a stabilized platform in order to meet two requirements which are precise drive and tolerance for launch load. Two kind of inertial sensors are installed on the platform to measure the attitude directly. Each of these two inertial sensors covers low or high bandwidth signal respectively. These signals will be able to be combined as one wideband signal to stabilize the platform in inertial space. In this paper, the developing prototype mechanism and control equipment are described and the basic evaluation results are reported. Less than 0.3urad as a drive precision and more than 100Hz as a local sensor control bandwidth are verified. The development of the system has not completely finished yet, but the basic performance is certified to meet the design specification. From now on, we continue to develop the unit. These future results can be applied to inter-satellite laser communication system.
IFAC Proceedings Volumes | 2013
Norimasa Yoshida; Osamu Takahara; Kazuhide Kodeki
Abstract Technical issues associated with spacecraft with very high pointing stability requirement for short to medium term (typically, sub-micro radians for 1-100 seconds) are reviewed. Specifically, microvibration and pointing jitter, that are induced by various internal disturbance sources, is a major issue for this class of satellite. The experiences and lessons learned through the development of several satellites are presented. In particular, some basic concepts on attitude and pointing, new evaluation techniques of pointing stability, influence of high frequency microvibration on pointing and attitude, and dynamic interface between payload and bus are described in this context.
Astronomical Telescopes and Instrumentation | 1998
Kazuhide Kodeki; Kazuhiko Fukushima; Toshio Kashiwase; Masao Inoue; Toshifumi Shimizu; Tsuyoshi Yoshida; Taro Sakao; Hirohisa Hara; Shin'ichi Nagata; Ryouhei Kano; Saku Tsuneta
This paper describes the design and prelaunch performance of the tip-tilt mirror (TTM) system developed for the XUV Cassegrain telescope aboard the ISAS sounding rocket experiment. The spatial resolution of the telescope is about 5 arcsec, whereas the rocket pointing is only controlled to be within +/- 0.5 degree around the target without stability control. The TTM is utilized to stabilize the XUV image on the focal planes by tilting the secondary mirror with two-axes fixed-coil type actuators. The two position- sensitive detectors in the telescope optics and in the TTM mechanical structure from the normal and local closed-loop modes. The TTM has four grain modes with automatic transition among the modes. The low gain mode is used in the initial acquisition, and in case the TTM loses the tracking. The high gain mode is used in the normal tracking mode. This arrangement provides us with the wide initial acquisition angle with single TTM system as well as the high pointing accuracy once the tracking is established. The TTM has a launch-lock mechanism against the launch vibration of 16G. The closed-loop control with command and telemetry interface is done by the flight software against the launch vibration of 16G. The closed-loop control with command and telemetry interface is done by the flight software on the DSP processor. The use of the fast processor brings in the significant reduction in the weight and size of the control- electronics, more flexible control system, and shorter design and testing period.
Solar Physics | 2008
Toshifumi Shimizu; Shin’ichi Nagata; S. Tsuneta; Theodore D. Tarbell; C. Edwards; R. A. Shine; C. Hoffmann; E. Thomas; S. Sour; R. Rehse; Osamu Ito; Yasuhiro Kashiwagi; Masaki Tabata; Kazuhide Kodeki; M. Nagase; Keiichi Matsuzaki; Ken Kobayashi; Kiyoshi Ichimoto; Yoshinori Suematsu
Journal of The Japan Society for Aeronautical and Space Sciences | 2007
Kazuhide Kodeki; Yasuhiro Kashiwagi; Shiro Miki; Makoto Endoh; Osamu Itoh; Toshihumi Shimizu; Keiichi Matsuzaki; Shin'ichi Nagata; Kiyoshi Ichimoto; Saku Tsuneta
Archive | 2013
Kazuhide Kodeki; Seiichi Shimizu; Osamu Takahara
Journal of The Japan Society for Aeronautical and Space Sciences | 1999
Kazuhide Kodeki; Toshio Kashiwase; Yoshinori Arimoto; Kenichi Araki