Abstract
A key issue in interplanetary missions is the attempt to reduce as much as possible the on board propellant, which has a direct inpact on the payload weight and eventually on the cost of the mission. Then in the mission analysis one tries to to minimize the variation of velocity ΔV f needed for the spacecraft orbit insertion, and it is of interest to look for arrival conditions close to (temporary) ballistic capture of the spacecraft by the target planet (ΔV f ~ 0).
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Circi, C., Teofilatto, P. (2002). Low ΔV Orbit Insertion in Interplanetary Missions. In: Celletti, A., Ferraz-Mello, S., Henrard, J. (eds) Modern Celestial Mechanics: From Theory to Applications. Springer, Dordrecht. https://doi.org/10.1007/978-94-017-2304-6_25
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DOI: https://doi.org/10.1007/978-94-017-2304-6_25
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