Takehiko Satoh

第49回月・惑星シンポジウム (2016年7月20-21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 49th ISAS Lunar and Planetary Symposium (July 20-21, 2016. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan 著者人数: 17名 資料番号: SA6000059023

第15回宇宙科学シンポジウム (2015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 15th Space Science Symposium (January 6-7, 2015. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)Sagamihara Campus), Sagamihara, Kanagawa Japan 資料番号: SA6000034333 レポート番号: S4-011

第58回宇宙科学技術連合講演会（2014年11月12日-14日. 長崎ブリックホール), 長崎市, 長崎県 "Preliminary thermal design and analysis of a Mars surface exploration spacecraft has been conducted. The sensitivities of thermal mass, envelope size and allowable temperature range of the component for heater power are presented based on preliminary EXCEL thermal calculation, and it is shown that allowable temperature range of external component is a critical parameter, and that heat leaks though electrical wire and coaxial cable for telecommunication is not negligible. These results suggest significant importance of expanding allowable temperature range of component,instead of accepting the current specification as-is." 資料番号: AC1500054000 レポート番号: JSASS-2014-4162

第58回宇宙科学技術連合講演会（2014年11月12日-14日. 長崎ブリックホール), 長崎市, 長崎県 Study on Mars entry-descent-landing and surface exploration technologies demonstrators has been undertaken with due consideration of potential scientific measurement proposals. As a result, the most outstanding candidates for the next Martian exploration mission have been selected through a local screening panel among four high-level engineering scopes, four high-level scientific scopes, and eleven proposals of scientific measurement. In this article, an overview of comparative study on engineering as well as scientific scopes is presented. 資料番号: AC1500052000 レポート番号: JSASS-2014-4157

第47回月・惑星シンポジウム (2014年8月4日-6日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県 47th ISAS Lunar and Planetary Symposium (August 4-6, 2014. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan 形態: カラー図版あり 資料番号: SA6000033001

Since 2008, a new plan for next Mars exploration program has been proposed and discussed by scientists and engineers in Japan. This exploration program is named MELOS, or Mars Exploration with Lander and Orbiter Synergy, a long-awaited program in the planetary science community in Japan after unsuccessful end of Nozomi Mars orbiter and ongoing challenge of Akatsuki Venus orbiter. The goal of the whole program is to understand Mars as a system, by elucidation of Martian climate, atmospheric escape, internal structure, surface environment and interaction by them. A series of missions has been planned, and several spacecraft including orbiters and landers are under discussion to be launched in early 2020's. In this paper, we investigate launch opportunities during early 2020's and estimate the payload mass in each case. Feasible interplanetary transfer trajectories from Earth to Mars are proposed. Preliminary design of insertion sequence into the Mars orbit and some orbit candidates derived from mission requirements are also shown together with numerical simulation results.

Japanese Venus Climate Orbiter "AKATSUKI" (PLANET-C) was successfully launched at 06:58:22JST on May 21st by H-IIA F17. It has 5 camers as mission instruments to study the venusian climate. Details of the instruments are described in this paper. Ultraviolet Imager (UVI 0.365μm),1μm Camera (IR1: 0.9μm),Longwave IR Camera (LIR: 8-12μm) were initialized at 20:50JST and took snapshots of the earth. Distance from the earth was 250,000km, and the apparent diameter was 2.8 degrees. UVI and IR1 detected the scattered sun light, while LIR detected the IR emission from the earth's body and can take the picture of the whole planet.