著者

矢田 達 安部 正真 岡田 達明 中村 智樹 野口 高明 岡崎 隆司 石橋 之宏 白井 慶 上椙 真之 唐牛 譲 八亀 彰吾 上野 宗孝 向井 利典 吉川 真 川口 淳一郎 藤村 彰夫

出版者

日本惑星科学会

雑誌

遊・星・人 : 日本惑星科学会誌 (ISSN:0918273X)

巻号頁・発行日

vol.22, no.2, pp.68-77, 2013-06-25

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地球外物質の採取・記載・保管および配布の目的で発足したJAXAキュレーションセンターでは,現在は小惑星イトカワにタッチダウンした探査機「はやぶさ」の試料を取り扱っている.「はやぶさ」から分離して地球帰還した再突入カプセルを受け入れ,その内部の試料コンテナを取り出してクリーンチェンバー内に導入し,開封を行った.試料コンテナ内の残留ガスから地球外起源の希ガスは検出できなかったが,キャッチャー内部からは主にケイ酸塩鉱物から成る微粒子を回収した.初期記載の結果,それらの鉱物比・鉱物組成がLL4-6コンドライト隕石に近いことが分かり,イトカワ試料と確認された.現在までに400個以上の粒子の回収・初期記載を行い,そのうち8割がイトカワ粒子だった.キュレーションセンターではこの試料を初期分析チーム,NASA,国際公募研究に対して配布し,多様な科学成果が挙がっている.

著者

唐牛 譲 石橋 之宏 上椙 真之 矢田 達 中藤 亜衣子 熊谷 和也 岡田 達明 安部 正真

出版者

一般社団法人日本地球化学会

雑誌

地球化学 (ISSN:03864073)

巻号頁・発行日

vol.48, no.4, pp.211-220, 2014-12-25 (Released:2015-01-06)

参考文献数

17

被引用文献数

1

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The Extraterrestrial Sample Curation Center of JAXA curates the Hayabusa-returned samples in conditions of minimum terrestrial contaminants, because these samples are very tiny. We evaluated the cleanliness of the handling instruments, the cleanroom environments and the sample storage chamber to improve the cleanliness of particles, organic molecules and metallic elements to a level not to affect the analyses of the Hayabusa-returned samples. In the environment of the clean chamber No. 2 where the samples have been stored, the organic molecule abundance was lower than the detection limit, furthermore, metallic elemental concentrations were the lowest among other evaluated place. A multi-stage ultrasonic cleaning by organic solvents and the ultrapure water have been applied to instruments made of stainless steel and/or aluminum alloy, and additionally, acid-alkali liquids cleaning have been performed for those made of quartz glasses. For the cleanliness of quartz glasses after the cleaning, the organic molecules abundances were blank level, and the metallic element concentrations were 1~100×109atom/cm2/24 h. It was confirmed by optical microscope that no particle of size more than 10 μm was observed on quartz glasses after the cleaning.

著者

麻生 大 星野 健 大竹 真紀子 唐牛 譲

雑誌

JpGU-AGU Joint Meeting 2020

巻号頁・発行日

2020-03-13

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Introduction:JAXA aims to conduct sustainable lunar exploration activities in the next 50 years, such as operation of lunar base with international partners and private sectors. To realize this goal, we will conduct technology demonstration step-by-step. JAXA envisions our space exploration as the extension from the Low Earth Orbit (LEO) to the Moon and Mars, with our international partners, in order to advance our contribution to intellectual assets.In October last year, the Japanese government announced its decision to officially join the international space exploration, and to proceed on coordination in the several areas including sharing of data acquired from our lunar exploration missions and technologies for lunar landing site selection.Japanese lunar exploration missions:Regarding lunar surface robotic missions, JAXA is developing Smart Lander for Investigating the Moon (SLIM), which aims to demonstrate the high-precision landing technology. The targeted launch year is 2021. Following this SLIM mission, a lunar polar exploration mission is aimed at investigating the water ice resources in the lunar polar region. This is a collaborative mission with Indian Space Research Organisation (ISRO).Objectives of the lunar polar exploration:In addition to the scientific interest about the origin and concentration mechanism of the water ice, there is strong interest in using water ice (if present) as an in-situ resources. Specifically, using water ice as a propellant will significantly affect future exploration scenarios and activities because the propellant generated from the water can be used for ascent from the lunar surface.Because of the existing limited remote-sensed data, we need to find out, by direct measurement on the lunar surface, the presence of water ice, it’s quantity, quality (pure water or contain other phases such as CO2 or CH4), and usability (how deep do we need to drill or how much energy is required to get water) in order to assess if we can use it as resources. Obtaining data to understand the principle of the water distribution and concentration is necessary to estimate the quantity and quality of water across the Moon.Status on the mission:ISRO/JAXA are jointly conducting the conceptual design (i.e. Phase-A study) under the Implementation Arrangement (IA) for the lunar polar exploration mission, in which JAXA provides a launch vehicle and a rover while ISRO provides a lander. System Requirement Review (SRR) is scheduled for this year. JAXA selected function and specification of several instruments, which will be loaded on the rover or the lander.Spacecraft configuration:The spacecraft system is based on direct communication with the Earth. The target mass of the spacecraft (incl. payload and propellant) is about 6ton and the payload mass is about 350kg. After the spacecraft reaches the Moon, it is inserted into a circular orbit having a 100km altitude via a few orbital changes. During powered-descent phase, the position of the lander is estimated by landmark navigation using shadows created by the terrain. After landing, the rover is deployed on the lunar surface using ramps. The rover then prospects water ice with its observation instruments.Landing site selection:We are down-selecting the candidates of landing site of the lunar polar region using the following parameters as constraints:- Continuous daytime: equal or more than 60days.- Continuous nighttime: equal or less than 14days.- Comm. capability: equal or more than 25%.- Land inclination: equal or less than 10deg.As a trial of the landing site selection, sunshine is simulated using digital elevation models to obtain the sunlight days per year and the number of continuous sunshine periods at each site. The maps of simulated communication visibility from the Earth and the slope are created.Conclusion:In this presentation, we will introduce current status on Japanese lunar exploration missions, focusing on a lunar polar exploration.

著者

星野 健 大竹 真紀子 唐牛 譲 白石 浩章

出版者

日本地球惑星科学連合

雑誌

日本地球惑星科学連合2019年大会

巻号頁・発行日

2019-03-14

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Introduction:Recently, it has been suggested that water ice might be present in the lunar polar region based on spectral measurements of artificial-impact-induced plumes in the permanently shadowed region, and remote sensing observation of the lunar surface using a neutron spectrometer [1], [2] and visible to infrared spectrometer [3]. In addition to the scientific interest about the origin and concentration mechanism of the water ice, there is strong interest in using water ice (if present) as an in-situ resources. Specifically, using water ice as a propellant will significantly affect future exploration scenarios and activities because the propellant generated from the water can be used for ascent from the lunar surface and can reduce the mass of the launched spacecraft of lunar landing missions.However, currently it is unclear if water ice is really present in the polar region because of the currently limited available data. Therefore, we need to learn that by directly measuring on the lunar surface. If there is water ice, we also need to know it’s quantity (how much), quality (is it pure water or does it contain other phases such as CO2 and CH4), and usability (how deep do we need to drill or how much energy is required to derive the water) for assessing if we can use it as resources. Therefore, JAXA is studying a lunar polar exploration mission that aims to gain the above information and to establish the technology for planetary surface exploration [4]. JAXA is also studying possibility of implementing it within the framework of international collaboration with Indian Space Research Organisation (ISRO).Spacecraft configuration:The spacecraft system comprises a lander system and a rover system. The system does not have a communication relay satellite but is based on direct communication with the Earth. The minimum target for the landing payload mass is several-hundred kilograms. The launch orbit is the lunar transfer orbit (LTO). After the spacecraft reaches the Moon it is inserted into a circular orbit having a 100km altitude via a few orbital changes. During powered-descent phase, the position of the lander is estimated by landmark navigation using shadows created by the terrain. After landing, the rover is deployed on the lunar surface using ramps. The rover then prospects water ice with its observation instruments..Spacecraft configuration:The spacecraft system comprises a lander system and a rover system. The system does not have a communication relay satellite but is based on direct communication with the Earth. The minimum target for the landing payload mass is several-hundred kilograms. The launch orbit is the lunar transfer orbit (LTO). After the spacecraft reaches the Moon it is inserted into a circular orbit having a 100km altitude via a few orbital changes. During powered-descent phase, the position of the lander is estimated by landmark navigation using shadows created by the terrain. After landing, the rover is deployed on the lunar surface using ramps. The rover then prospects water ice with its observation instruments..Landing site selection:Considering the mission objectives and condition of the lunar polar region, we listed the following parameters as constraints.- Presence of water- Surface topography- Communication capability- Duration of sunshineAs a first trial of the landing site selection, sunshine is simulated using digital elevation models to obtain the sunlight days per year and the number of continuous sunshine periods at each site. Also, slope and the simulated communication visibility map from the Earth are created. These conditions can be superimposed to select the landing site candidate.Current status:Recently, we finished joint mission definition review (JMDR) with ISRO, in which JAXA provide a launch rocket and a rover while ISRO provide a lander system. Related to the instruments which will be carried on the rover or the lander, JAXA selected several candidate instrument study teams for accelerating development of these instruments. In this presentation, we are going to introduce current status of the mission planning.References:[1] Feldman W. C. et al. (1998) Science, 281, 1496-1500.[2] Sanin A. B. et al. (2017) Icarus, 283, 20-30.[3] Pieters C. M. et al. (2009) Science, 326, 568-572.[4] Hoshino T. et al. (2017) 68th IAC, IAC-17-3.2B.4.

著者

大竹 真紀子 荒井 朋子 武田 弘 唐牛 譲 佐伯 和人 諸田 智克 小林 進悟 大槻 真嗣 國井 康晴

出版者

日本惑星科学会

雑誌

日本惑星科学会誌遊星人 (ISSN:0918273X)

巻号頁・発行日

vol.21, no.3, pp.217-223, 2012

参考文献数

16

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従来,月の地殻組成は月採取帰還試料や月隕石の分析値を基に推定されてきたが,最近になって,月周回衛星"かぐや"データを用いた研究などにより,既存の月採取帰還試料とは異なる組成の,より早い分化段階で形成した始原的な地殻物質が,月裏側に存在する事が指摘されている.これら未採取の月裏側地殻物質を入手し,詳細な化学組成等の情報を得る事は,月高地地殻の組成,月マグマオーシャンの固化過程や熱履歴を知ることに加え,月・地球系の形成過程を考える上でも重要な課題である.本提案では,来る10年の惑星探査計画として,月裏側の高地地域から未採取地殻物質の採取帰還を行い,詳細な組成分析,同位体分析,組織分析,既存のリモートセンシングデータと比較するための分光測定,風化度測定など,さまざまな分析を行うことにより,これら科学目標達成を目指すミッションを提案する.

著者

武田 弘 唐牛 譲 山口 亮 長岡 央 大竹 真紀子 春山 純一 矢沢 勇樹 諸田 智克 廣井 孝弘

出版者

日本惑星科学会

雑誌

日本惑星科学会秋期講演会予稿集

巻号頁・発行日

vol.2011, 2011-10-23