Optimal Circle-to-Ellipse Orbit Transfer for Sun-Facing E-Sail
Optimal Circle-to-Ellipse Orbit Transfer for Sun-Facing E-Sail
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Publisher
Basel: MDPI AG
Journal title
Language
English
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Publisher
Basel: MDPI AG
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Scope and Contents
Contents
The transfer between two coplanar Keplerian orbits of a spacecraft with a continuous-thrust propulsion system is a classical problem of astrodynamics, in which a numerical procedure is usually employed to find the transfer trajectory that optimizes (i.e., maximizes or minimizes) a given performance index such as, for example, the delivered payload...
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Full title
Optimal Circle-to-Ellipse Orbit Transfer for Sun-Facing E-Sail
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TN_cdi_doaj_primary_oai_doaj_org_article_f7439de402ce4f9c817fc1fc33a93433
Permalink
https://devfeature-collection.sl.nsw.gov.au/record/TN_cdi_doaj_primary_oai_doaj_org_article_f7439de402ce4f9c817fc1fc33a93433
Other Identifiers
ISSN
2226-4310
E-ISSN
2226-4310
DOI
10.3390/aerospace9110671
