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Atmospheric gravity waves play important roles in couplings in the terrestrial atmosphere and ionosphere, i.e. in the whole atmosphere, by transporting momentum and energy in vertical and horizontal directions. One of the hotspots, i.e. active source region of such gravity waves, is the area of the Andes and the Antarctic peninsula. In order to study gravity wave activity generated at this hotspot and propagating up to the MLT region,we installed an all-sky airglow camera in November 2017 at Rio Gallegos station (51.6S, 69.3W), Patagonia, Argentina. The imager at Rio Gallegos is equipped with an InGaAs array sensor, sensitive to the near-infrared (900-1700 nm), and can observe OH Meinel band airglow (~87 km altitude), obtaining an OH airglow image every 5 sec with an exposure time of 2 sec. This system has a similar specification with the five imagers of the ANtarctic Gravity Wave Instrument Network (ANGWIN) at Davis, McMurdo, Halley, Syowa and the south pole. In this presentation, we will report the results from Rio Gallegos station, by means of M-transform analysis, which quantitatively derives distributions of short-period gravity wave energy in the horizontal phase velocity domain. Also, comparison with the results from Syowa station in the Antarctic (69.0S, 39.6E) will be presented., The 28th IUGG General Assembly (IUGG2023) (Berlin 2023)

A user-on-demand power source based on renewable energy requires storage devices to balance power sources and power demands because of the fluctuation of power sources like solar cells or wind power generators. The role of the control system is defined as two different tasks: allowing a power-flow imbalance between demand and power sources; and balancing the power flow inside the system. Since this control is complicated, many control methods using precise calculation of the power balance have been proposed. An analogue-like distributed control method - named “modified DC-bus signalling” - for controlling a renewable-energy power source without the need for a central processing unit is proposed. The modified DC bus signalling method discussed in this paper is composed of a DC-bus line connected with a battery, water-splitting electrochemical cell, and a fuel cell for hydrogen-energy storage via converters. The proposed control method was demonstrated to be able to control step-like and random changes in input and output power. The battery compensated high-frequency fluctuations in power demand, and the electrochemical cell and fuel cell handled the remaining low-frequency ones, which were matched to their response speeds.

令和二年度宇宙輸送シンポジウム（2021年1月14日-15日. オンライン開催), Space Transportation Symposium FY2020 (January 14-15, 2021. Online Meeting), 資料番号: SA6000160047, レポート番号: STEP-2020-009

第21回宇宙科学シンポジウム (2021年1月6日-7日. オンライン開催), 21st Space Science Symposium (January 6-7, 2021. Online Meeting), 資料番号: SA6000163042, レポート番号: g01-10

第21回宇宙科学シンポジウム (2021年1月6日-7日. オンライン開催), 21st Space Science Symposium (January 6-7, 2021. Online Meeting), 著者人数: 44名ほか, 資料番号: SA6000163022, レポート番号: S5-004

第20回宇宙科学シンポジウム (2020年1月8日-9日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)相模原キャンパス), 相模原市, 神奈川県, 20th Space Science Symposium (January 8-9, 2020. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)Sagamihara Campus), Sagamihara, Kanagawa Japan, 著者人数: 20名, 資料番号: SA6000152173, レポート番号: P2.67

第18回宇宙科学シンポジウム (2018年1月9日-10日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)相模原キャンパス), 相模原市, 神奈川県, 18th Space Science Symposium (January 9-10, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)Sagamihara Campus), Sagamihara, Kanagawa Japan, 資料番号: SA6000118160, レポート番号: P-127

第8回極域科学シンポジウム/特別セッション：[S] 先端的技術で切り開く極域科学 －極域観測における計測、分析、解析の最前線－12月7日（木）国立極地研究所 2階大会議室The Eighth Symposium on Polar Science/Special session: [S] Polar science developed by leading-edge technology - on the frontiers of measurement and analysis in polar science -Thu. 7 Dec./2F Auditorium, National Institute of Polar Research

第17回宇宙科学シンポジウム (2017年1月5日-6日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)相模原キャンパス), 相模原市, 神奈川県, 17th Space Science Symposium (January 5-6, 2017. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)Sagamihara Campus), Sagamihara, Kanagawa Japan, 資料番号: SA6000060127, レポート番号: P-085

第7回極域科学シンポジウム:[OS]宙空圏11月29日（火）国立極地究所 1階 交流アトリウム

第16回宇宙科学シンポジウム (2016年1月6日-7日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)相模原キャンパス), 相模原市, 神奈川県, 16th Space Science Symposium (January 6-7, 2016. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)Sagamihara Campus), Sagamihara, Kanagawa Japan, 資料番号: SA6000046214, レポート番号: P-215

資料番号: SA1003287000

Solar-B衛星の重要な特徴の1つは、口径50cmの主鏡の回折限界である0.2秒角の空間分解能で太陽の可視光観測が可能な点である。高分解能の観測の為に厳しい姿勢制御の精度が要求され、高い位置検出精度が太陽センサーに必要となる。Solar-B衛星に搭載される超高精度太陽センサー(Ultra Fine Sun Sensor, UFSS)の角度検出性能をプロトモデル品で検証し、ランダム誤差0.15arcsec(1σ)、視野±0.5度、四方でバイアス誤差約2arcsec(p-p)の実力を実証した。, 資料番号: AA0047899126

第12回宇宙科学シンポジウム (2012年1月5日-6日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)相模原キャンパス), 相模原市, 神奈川県, 12th Space Science Symposium (January 5-6, 2012. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)Sagamihara Campus), Sagamihara, Kanagawa Japan, 資料番号: SA6000064210, レポート番号: P4-212

大気球シンポジウム 平成23年度（2011年10月6-7日. 宇宙航空研究開発機構宇宙科学研究所 (JAXA)(ISAS)）, 相模原市, 神奈川県), Balloon Symposium 2011 (October 6-7, 2011. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 著者人数: 25名ほか, 資料番号: SA6000067015, レポート番号: isas11-sbs-015

星に搭載された太陽センサーは出来るだけ精度良く太陽方向を測定し、その信号は衛星の姿勢安定化に使用される。「ひので」(SOLAR-B: Solar Physics Satellite)衛星に搭載された望遠鏡は今までにない高い角分解能で太陽を観測する装置であり、衛星には極めて高い姿勢安定化が要求された。このために、我々は、ランダム誤差1秒角(3σ)、±0.5度視野にわたりバイアス誤差2秒角(p-p)という高い位置決定精度で太陽方向を測定することができる超高精度太陽センサー「UFSS(Ultra Fine Sun Sensor)」を開発した。性能検証モデル品を用いて高精度計測を可能とする手法を確立し、フライトモデル製作に向けた性能検証を行い、フライト品設計に反映させた。また確立した計測手法を用いてフライト品の性能検証を行った。, The aim of sun sensors installed on spacecrafts is to measure the direction of the sun as precisely as possible, which signals are utilized to stabilize the spacecraft attitude. The HINODE (SOLAR-B: Solar Physics Satellite) satellite has three telescopes for high spatial resolution observations of the sun and requires extremely stabilized pointing of the spacecraft. For achieving the pointing requirements, we have developed compact sun sensors named Ultra Fine Sun Sensor (UFSS), which are required to provide pointing signals with the random noise less than 1 arcsecond (3 sigma) and the bias noise less than 2 arcseconds (p-p) for the field-of-view with +/- 0.5 degree. For verifying the performance with pre-launch measurements, we have established the methods of the measurements and have confirmed the excellent performance of the sensors., 資料番号: AA0063799000, レポート番号: JAXA-RR-07-013

第28回宇宙利用シンポジウム (2012年1月23-24日. 日本学術会議), 港区, 東京都, Space Utilization Research (January 23-24, 2012. Science Council of Japan), Minato-ku, Tokyo Japan, 資料番号: SA6000032005, レポート番号: M05

The details of the instrument of GXV boarded on the sounding rocket K-10-14 and the preliminary results of the experiment are presented. The aim of this experiment was to observe the Cygnus loop (the most promenent S.N.R.) with fine spatial resolution by two Hadamard Transform X-ray Telescopes (HTXT) and with good spectral resolution by two filter counters. The angular resolution of HTXT is about 20' x 20' with effective area about 149 cm^2 each. The pure methane is employed the counter gas in order to get the desired positional resolution. The filter counters have different windows with effective area about 20 cm^2 each. The one is equipped with standard 1 μm thick polypropylene film window while the other with 1500 Å A1 coated 1 μm thick polypropylene film. The latter filter counter reduced the X-ray efficiency in the L-band (E < 0.4 keV) energy range whereas it had almost equal X-ray efficiency to that of the former one in the M-band (E > 0.4 keV). K-10-14 was launched at 20^h 40^m on 27 in August 1980 from Kagoshima Space Center. The X-ray detectors were operated properly for more than 200 seconds. The attitude control system (ACS) started to maneuver the payload from 85 second after launch. The target, Cygnus loop, was missed due to the mulfunction of the ACS. The detailed data analysis is underway., 資料番号: SA0125934000