A scheme for simplified trajectory design in aero-gravity assist using singular orbits

Naoko Ogawa, Kazuhisa Fujita, Jun'ichiro Kawaguchi

研究成果: Conference article査読

抄録

This paper proposes a novel strategy for simplified trajectory design in aero-gravity assist missions. In aero-gravity assists, the extent of deceleration and the periapsis altitude are coupled and dependent to each other, which makes it difficult to obtain desired outgoing trajectory. We insert a one-revolution orbit as a trajectory leg just after the aero-gravity assist so that we can utilize degrees of freedom in design for connecting two trajectory before and after the swing-by. After one-revolution interplanetary cruise, the S/C re-encounters the planet and thus has a chance to go to new destination by a usual gravity assist, or to experience aero-gravity assist again, which allows us various interplanetary missions afterward. This paper describes the difficulty in design of aero-gravity assists, outline of our novel approach and its detailed procedures. A case study for Earth aero-gravity assist design is also shown.

本文言語English
ページ(範囲)3211-3227
ページ数17
ジャーナルAdvances in the Astronautical Sciences
148
出版ステータスPublished - 2013
外部発表はい
イベント23rd AAS/AIAA Space Flight Mechanics Meeting, Spaceflight Mechanics 2013 - Kauai, HI, United States
継続期間: 2013 2 102013 2 14

ASJC Scopus subject areas

  • 航空宇宙工学
  • 宇宙惑星科学

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