High velocity aero-gravity assist applied on eccentricity to inclination conversion for reaching solar polar orbit

Tiago Monteiro Padovan, Yuki Kubo, Junichiro Kawaguchi, Kazuhiko Yamada, Roger Gutierrez Ramon

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

In order to change the inclination of an orbit around the Sun, a good option is to perform a flyby on Jupiter, where heliocentric speeds are slower than in the inner solar system. The drawback of the resulting orbit is the great orbital period associated with its large semi-major axis. In order to reduce the orbit size and increase even more the inclination, it was suggested to implement an Aero-gravity Assist maneuver at the Earth after the Jupiter flyby. This maneuver would be used within the Eccentricity to Inclination conversion scheme to increase its performance. Results show that such a maneuver could reduce the time required for reaching a short period, highly inclined orbit in lower time than by only using Gravity Assist. The objective of this study is to analyze the performance of using Aero-gravity Assist within the Eccentricity to Inclination conversion.

Original languageEnglish
Title of host publicationAIAA Scitech 2020 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Pages1-7
Number of pages7
ISBN (Print)9781624105951
DOIs
Publication statusPublished - 2020
Externally publishedYes
EventAIAA Scitech Forum, 2020 - Orlando, United States
Duration: 2020 Jan 62020 Jan 10

Publication series

NameAIAA Scitech 2020 Forum
Volume1 PartF

Conference

ConferenceAIAA Scitech Forum, 2020
Country/TerritoryUnited States
CityOrlando
Period20/1/620/1/10

ASJC Scopus subject areas

  • Aerospace Engineering

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