- 著者
- Naoko OGAWA Yuichi TSUDA Yuto TAKEI Hiroka INOUE Shota TAKAHASHI Yasuhiro KAWAKATSU
- 出版者
- THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
- 雑誌
- TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
- 巻号頁・発行日
- vol.17, no.3, pp.398-403, 2019 (Released:2019-05-04)
- 参考文献数
- 3
- 被引用文献数
- 3 4
The Martian Moons eXploration (MMX) mission is now under study by the Japan Aerospace Exploration Agency (JAXA). Its scope includes the world's first landing on one of the Martian moons, collecting samples from the surface, and returning to Earth. This paper describes the orbit design for MMX. Nominal and backup trajectories for launch in 2024 and 2026 are discussed. The Mars orbit insertion (MOI) sequence using 3-impulse maneuvers is introduced. A new scheme, the robust MOI, is also proposed as a contingency to enhance the robustness of the mission sequence. A method to design a robust MOI trajectory and examples are presented.
- 著者
- Shota TAKAHASHI Naoko OGAWA Yasuhiro KAWAKATSU
- 出版者
- THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
- 雑誌
- TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
- 巻号頁・発行日
- vol.17, no.3, pp.404-411, 2019 (Released:2019-05-04)
- 参考文献数
- 9
- 被引用文献数
- 1 2
Failure of the orbit insertion maneuver has a significant impact on the entire mission, for the trajectory of a spacecraft is largely deflected by swing-by. The risk can be reduced by targeting a point on the B-plane where the spacecraft reaches the free-return (FR) trajectory with the target body in the case of insertion failure. The backup orbit must also satisfy conditions suitable for the mission. We investigated the type of orbit insertion that is both robust to failure and reasonable for the mission requirements. We call this method FR ensured orbit insertion. Among various failure modes of the orbit insertion maneuver, we focus on the complete maneuver failure. The impact parameters on the B-plane to achieve the orbit insertion are formulated based on the geometry of velocity vectors at swing-by. The necessary deflection angle αFR at swing-by must be smaller than the possible maximum deflection angle αmax for the target body. When we introduce proper scaling factors, the relation of αmax and αFR is characterized by a single parameter λ. Using polar orbit insertion as an example, maps which show the reachability of FR trajectory after the insertion failure for each approaching condition are presented. The derived maps can be used as a tool to assess the applicability of the method in the mission design. Finally, as an application to practical mission design, we demonstrate the use of FR ensured orbit insertion in JAXA's MMX mission.
- 著者
- Sho SASAKI Masaki FUJIMOTO Hajime YANO Takeshi TAKASHIMA Yasumasa KASABA Yukihiro TAKAHASHI Jun KIMURA Yuichi TSUDA Ryu FUNASE Osamu MORI Stefano CAMPAGNOLA Yasuhiro KAWAKATSU
- 出版者
- THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
- 雑誌
- TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
- 巻号頁・発行日
- vol.10, no.ists28, pp.Tk_37-Tk_40, 2012 (Released:2013-06-07)
EJSM (Europa Jupiter System Mission) is an international Jovian system mission with three spacecraft. Coordinated observation of Jovian magnetosphere is one of the important targets of the mission in addition to icy satellites, atmosphere, and the interior of Jupiter. JAXA will take a role on the magnetosphere spinner JMO (Jupiter Magnetospheric Orbiter), whereas ESA will launch JGO (Jupiter Ganymede Orbiter) and NASA will be responsible for JEO (Jupiter Europa Orbiter). One possibility is to combine JMO with a proposed solar sail mission of JAXA for Jupiter and one of Trojan asteroids. Since Trojan asteroids could be representing raw solid materials of Jupiter or at least outer solar system bodies,involvement of Trojan observation should enlarge the scope and enhance the quality of EJSM.
- 著者
- Osamu MORI Hirotaka SAWADA Ryu FUNASE Mutsuko MORIMOTO Tatsuya ENDO Takayuki YAMAMOTO Yuichi TSUDA Yasuhiro KAWAKATSU Jun'ichiro KAWAGUCHI Yasuyuki MIYAZAKI Yoji SHIRASAWA IKAROS Demonstration Team and Solar Sail Working Group
- 出版者
- THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
- 雑誌
- TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)
- 巻号頁・発行日
- vol.8, no.ists27, pp.To_4_25-To_4_31, 2010 (Released:2011-06-14)
- 参考文献数
- 1
- 被引用文献数
- 19 40
The Japan Aerospace Exploration Agency (JAXA) will make the world's first solar power sail craft demonstration of photon propulsion and thin film solar power generation during its interplanetary cruise by IKAROS (Interplanetary Kite-craft Accelerated by Radiation Of the Sun). The spacecraft deploys and spans a membrane of 20 meters in diameter taking the advantage of the spin centrifugal force. The spacecraft weighs approximately 310kg, launched together with the agency's Venus Climate Orbiter, AKATSUKI in May 2010. This will be the first actual solar sail flying an interplanetary voyage.