Japan Aerospace Exploration Agency Institute of Space and Astronautical Science
Japan Aerospace Exploration Agency Institute of Space and Astronautical Science
Japan Aerospace Exploration Agency Institute of Space and Astronautical Science
出版者
宇宙航空研究開発機構宇宙科学研究本部
出版者（英）
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)
雑誌名
平成15年度アストロダイナミクスシンポジウム:講演後刷り集
雑誌名(英)
ISAS Proceedings of 13th Workshop on Astrodynamics and Flight Mechanics 2003: A Collection of Technical Papers
Launch feasibility of a Venus exploring mission is studied in this paper, so as to ensure the contingency of the backup launch in 2010. In the previous study of the PLANET-C Venus orbiter mission, a launch opportunity in 2008 was applied, which was one of the best conditions to transfer from Earth to Venus. On the other hand, the transfer orbit of the 2010 launch has energy disadvantage, in which larger velocity increment to encounter Venus is required than that of the 2008 launch. Thus the weight of the spacecraft turns out to be correspondingly smaller. In order to maximize the spacecraft weight, a simple injection strategy, a direct insertion method, is proposed here. In addition to the proposed launch sequence, subsequent acceleration by OME (Orbital Maneuvering bipropellant Engine) of the spacecraft propulsion system is used so as to lessen differences of the expected weight in the launch window. By applying the direct insertion method with the OME acceleration, the weight allocated to the scientific observation instruments enables to be kept same as that in the previous study, despite the energy disadvantage of the 2010 launch window.
Launch opportunities for Venus exploring missions
