Abstract This paper presents an overview of the analysis performed on the lunar orbit and some of the possible contingencies for the European Student Moon Orbiter (ESMO). Originally scheduled for launch in 2014 –2015 as a piggyback payload, it was the only ESA planned mission to the Moon. By way of a weak stability boundary transfer, ESMO is inserted into an orbit around the Moon. Propellant use is at a premium, so the operational orbit is selected to be highly eccentric. In addition, an optimization is presented to achieve an orbit that is stable for 6 months without requiring orbit maintenance. A parameter study is undertaken to study the sensitivity of the lunar orbit insertion. A database of transfer solutions across 2014 and 2015 is used to study the relation between the robustness of weak capture and the planetary geometry at lunar arrival. A number of example recovery scenarios, where the orbit insertion maneuver partially or completely fails, are also considered.
Highlights • An overview of arrival conditions of WSB transfers in 2014 and 2015 is presented.• A number of classification sets sort transfers based on their arrival conditions.• Classification sets link arrival conditions with the geometry of the planets.• Contingency strategies for missing the initial lunar insertion maneuver are studied.• Lunar orbit selection, optimization thereof, and sensitivity analysis is shown.
Contingency and recovery options for the European Student Moon Orbiter
Acta Astronautica ; 94 , 1 ; 168-183
2013-08-15
16 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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