Influence of the finite duration on a fly-by
| Autor: | Janssens, Frank |
|---|---|
| Jazyk: | angličtina |
| Rok vydání: | 2008 |
| Předmět: |
orbital mechanics
patched conic sphere of influence 軌道 three body problem 数学的解析 円錐曲線貼り合わせ マヌーバ mathematical analysis equation of motion フライバイ 軌道力学 2体問題 flyby SOI two body problem maneuver エネルギー交換 energy exchange 影響球 運動方程式 trajectory Physics::Space Physics 軌道解析 trajectory analysis Astrophysics::Earth and Planetary Astrophysics 3体問題 |
| Zdroj: | 第17回アストロダイナミクスシンポジウム講演後刷り集 2007 = Proceedings of 17th Workshop on JAXA Astrodynamics and Flight Mechanics. :69-83 |
| Popis: | Patched conics is the standard tool for designing fly-by or gravity assist maneuvers performed by a spacecraft about a planet. In this procedure, the trajectory of the spacecraft about the planet is taken as a perfect hyperbola once the spacecraft is in the sphere of influence of the planet. All other perturbations are neglected. As a consequence the outgoing V infinity is identical to the incoming V infinity. In reality, the spacecraft spends a finite time in the sphere of influence of the planet. A typical time is a week. The small perturbations caused by the Sun will affect the ideal hyperbolic trajectory. When the fly-by planet is the Earth, the Moon and J2 cause also small changes in the hyperbola. The small changes in V infinity are the subject of this paper. The perturbation of the Sun can be modeled as a restricted three body problem or analyzed with the standard averaging technique applied to an hyperbolic orbit. We compare our results to the real data of the fly-by past the Earth on March 4, 2005 by the Rosetta spacecraft on his way to the comet Churymov-Gerasimenko (2014). 資料番号: AA0063718013 |
| Databáze: | OpenAIRE |
| Externí odkaz: |
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