Interplanetary Mission Designs by Multiple Earth-Venus-Jupiter Swingbys

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概要

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• This paper presents a possible usage of a multiple swingby technique which makes use of at most three gravity-assist planets (Earth, Venus, and Jupiter). Various combinations are considered (e.g., a multiple Venus swingby, a multiple Earth-Venus swingby, etc.), and each of te energy exchange mechanisms between a spacecraft and planet (s) is investigated as well as the angular momentum exchange mechanisms. Focusing on attainable orbital elements, the capability of each swingby technique is also investigated. The major purpose of this technique is to reduce the launch velocity increment while maintaining a reasonable flight time. When only one planet is involved, a forward dynamic programming approach is successfully applied to determine the optimal swingby sequence. However, when more than two planets are used, computations become quite time consuming so that a simplified control strategy is proposed. This strategy is built up with several subsequences, in which a forward dynamic programming approach is partially applied. Four specific interplanetary mission designs (M1 through M4) are presented : M1 : escaping from the solar system; M2 : falling into the sun; M3 : out-of-the-ecliptic mission; and M4 : retrograde mission; by using a multiple Earth-Venus swingby and a multiple Earth-Venus-Jupiter swingby with as small as 3.0km/sec launch velocity increment. Results are compared with a conventional direct launch technique in terms of the Earth launch velocity increment, flight time, and available launch window. Computations are based on a patched conics method, and orbits of Earth, Venus, and Jupiter are assumed to be circular and coplanar unless otherwise specified.

• 宇宙航空研究開発機構の論文

著者

• Tanabe Toru

  Department Of Aeronautics University Of Tokyo

• Yokota Hiroki

  Departments Of Biomedical Engineering And Anatomy & Cell Biology Indiana University-purdue Unive

• Yokota Hiroki

  Department Of Aeronautics University Of Tokyo

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