深宇宙追跡技術グループ

冨木 淳史

トミキ アツシ  (TOMIKI ATSUSHI)

基本情報

所属
国立研究開発法人宇宙航空研究開発機構 宇宙科学研究所 准教授
学位
博士(工学)(2007年3月 東京電機大学)

J-GLOBAL ID
200901094498520904
researchmap会員ID
6000005907

外部リンク

論文

 42
  • Tatsuaki Hashimoto, Junji Kikuchi, Ryo Hirasawa, Kota Miyoshi, Wataru Torii, Naoki Morishita, Nobutaka Bando, Atsushi Tomiki, Shintaro Nakajima, Masatsugu Otsuki, Hiroyuki Toyota, Kakeru Tokunaga, Chikako Hirose, Tetsuo Yoshimitsu, Hiroshi Takeuchi
    Proceedings of the International Astronautical Congress, IAC 2023-October 2023年  
    A 6U CubeSat “OMOTENASHI” was developed to be the world's smallest moon lander. It was launched by NASA's SLS Artemis-1 on November 16, 2022. However, because of the spacecraft anomaly, the battery was depleted and the communication with the spacecraft had been lost. After we gave up the moon landing experiment, we have been conducting a search and rescue operation till September 2023. But it was unsuccessful, unfortunately. In this article, the mission objective, the spacecraft design, the planed mission scenario, and the in-orbit operation results are presented. Additionally, lessons learned from the development and the in-orbit operation are presented.
  • Timothy Pham, Hiroshi Takeuchi, Atsushi Tomiki, Kathleen Harmon, Sami Asmar, Yoshihide Sugimoto, Taniguchi Sho, Tsutomu Ichikawa
    Proceedings of the International Astronautical Congress, IAC 2023-October 2023年  
    This paper presents a collaborative effort between NASA and JAXA to make 3-way Doppler data from JAXA tracking stations available to the Artemis 1 navigation team to improve orbit determination. The paper describes the system configuration and concept of operation of this capability. Testing effort at the three JAXA's ground stations - the Uchinoura's 20-m and 34-m antennas and Usuda's 64-m antenna - are discussed. Both aspects of system testing are highlighted, first on the use of Artemis 1 recorded signal to ensure compatibility between ground and flight systems, and second on the tracking with the Lunar Reconnaissance Orbiter, as a substitute for Artemis before launch, to validate other key operational functions such as ephemeris processing, spacecraft tracking capability, data delivery, and interactions among multiple operational teams in different organizations. Results from actual support to Artemis 1's Orion spacecraft in November-December 2022 are also presented.
  • Timothy Pham, Hiroshi Takeuchi, Atsushi Tomiki
    ADVANCES IN COMMUNICATIONS SATELLITE SYSTEMS 2 95 235-242 2020年  
    This chapter presents an ongoing effort in preparing JAXA Uchinoura station support to the Artemis 1 mission, scheduled for launch in late 2020. The system involves three key participants: JAXA ground station at Uchinoura, the Deep Space Network (DSN) components at the Jet Propulsion Laboratory, California, and the Artemis 1 mission navigation at the NASA Johnson Space Center, Texas.Demonstration of Uchinoura station support to the future Artemis signal relies on the use of a low-cost, highly-portable software-defined radio (SDR) test equipment as well as the tracking of the Lunar Reconnaissance Orbiter (LRO) spacecraft. Using the SDR equipment, we validated the compatibility of signal format between the Artemis flight radio and the Uchinoura ground station without having to send the flight equipment to the station. By tracking an ongoing operational spacecraft such as LRO, we were able to calibrate the performance of the system in real operational conditions. The measured Doppler noise of 0.03 Hz (1-sigma), or 0.002 m/s range rate at S-band, for Uchinoura station is deemed suitable to the Artemis 1 mission navigation needs.This chapter also discusses the test equipment capability and its performance. In addition to being low cost, the equipment offers many advantages compared to the traditional full-scaled test signal simulator. Chief among them is portability making system easy to set up and transport, and the fidelity of the test signal that it captures from spacecraft flight equipment. Some of the lessons learned, such as internal frequency stability of the test signal, are also reflected.
  • Tatsuaki Hashimoto, Junji Kikuchi, Ryo Hirasawa, Naoki Morishita, Nobutaka Bando, Atsushi Tomiki, Wataru Torii, Yuta Kobayashi, Shintaro Nakajima, Masatsugu Otsuki, Tetsuo Yoshimitsu, Tetsuya Yamada, Kota Miyoshi, Hiroyuki Toyota, Kakeru Tokunaga, Chikako Hirose, Toshinori Ikenaga, Aiko Nagamatsu, Hitoshi Morimoto
    Proceedings of the International Astronautical Congress, IAC 2020-October 2020年  
    Copyright © 2020 by the International Astronautical Federation (IAF). All rights reserved. A 6U CubeSat “OMOTENASHI” will be the world's smallest moon lander which is launched by NASA SLS Artemis-1. Because of its severe mass and size limitation, it will adopt semi-hard landing scheme. That is, OMOTENASHI is decelerated from orbital velocity to less than 50 m/s by a small solid rocket motor and shock absorption mechanism has been developed to withstand the high-speed impact. Ultra small communication system (X-band and P-band) is also developed. It observes radiation environment of Earth and moon region with portable dosimeters. This paper shows the mission outline, the design, and the development results of OMOTENASHI.
  • 五十 里哲, 伊藤 琢博, 小栗 健士朗, 稲守 孝哉, 坂井 信一郎, 川勝 康弘, 冨木 淳史, 船瀬 龍
    日本航空宇宙学会論文集 68(2) 89-95 2020年  
    <p>A Fault Detection, Isolation, and Recovery (FDIR) algorithm for attitude control systems is a key technology to increasing the reliability and survivability of spacecraft. Micro/nano interplanetary spacecraft, which are rapidly evolving in recent years, also require robust FDIR algorithms. However, the implementation of FDIR algorithms to these micro/nano spacecraft is difficult because of the limitations of their resources (power, mass, cost, and so on). This paper shows a strategy of how to construct a FDIR algorithm in the limited resources, taking examples from micro deep space probe PROCYON. The strategy focuses on function redundancies and multi-layer FDIR. These ideas are integrated to suit the situation of micro/nano interplanetary spacecraft and demonstrated in orbit by the PROCYON mission. The in-orbit results are discussed in detail to emphasize the effectiveness of the FDIR algorithm. </p>

MISC

 151
  • 森下直樹, 平澤遼, 徳永翔, 菊池隼仁, 鳥居航, 冨木淳史, 三好航太, 中塚潤一, 坂東信尚, 橋本樹明
    宇宙科学技術連合講演会講演集(CD-ROM) 67th 2023年  
  • 橋本樹明, 平澤遼, 菊池隼仁, 徳永翔, 森下直樹, 鳥居航, 冨木淳史, 三好航太, 坂東信尚, 廣瀬史子, 中島晋太郎, 竹内央
    宇宙科学技術連合講演会講演集(CD-ROM) 67th 2023年  
  • 村田泰宏, 沼田健二, 内村孝志, 大西徹, 木村公洋, 田渕豪, 坪井昌人, 戸田知朗, 冨木淳史, 中原聡美, 湯地恒次, 吉永昌志, 長谷川豊, 長谷川豊
    日本天文学会年会講演予稿集 2021 2021年  
  • 吉光徹雄, 大槻真嗣, 前田孝雄, 吉川健人, 國井康晴, 冨木淳史, 宇佐美尚人, 澤田弘崇, 平野大地, 須藤真琢
    宇宙科学技術連合講演会講演集(CD-ROM) 65th 2021年  
  • 前田孝雄, 吉川健人, 大槻真嗣, 吉光徹雄, 國井康晴, 冨木淳史, 澤田弘崇, 平野大地, 須藤真琢, 久保田孝
    宇宙科学技術連合講演会講演集(CD-ROM) 64th 2020年  

所属学協会

 1

共同研究・競争的資金等の研究課題

 4

産業財産権

 10