Optimal two-impulse trajectories with moderate flight time for Earth-Moon missions
type: Item
instance of: scholarly article
title: Optimal two-impulse trajectories with moderate flight time for Earth-Moon missions
zbMATH Open document ID: 1264.70056
DOI: 10.1155/2012/971983
author: Cleverson Maranhão Porto Marinho
author: Sandro da Silva Fernandes
published in: Mathematical Problems in Engineering
publication date: 2013-06-11T00:00:00Z
review text: Summary: A study of optimal two-impulse trajectories with moderate flight time for Earth-Moon missions is presented. The optimization criterion is the total characteristic velocity. Three dynamical models are used to describe the motion of the space vehicle: the well-known patched-conic approximation and two versions of the planar circular restricted three-body problem (PCR3BP). In the patched-conic approximation model, the parameters to be optimized are two: initial phase angle of space vehicle and the first velocity impulse. In the PCR3BP models, the parameters to be optimized are four: initial phase angle of space vehicle, flight time, and the first and the second velocity impulses. In all cases, the optimization problem has one degree of freedom and can be solved by means of an algorithm based on gradient method in conjunction with Newton-Raphson method.
Mathematics Subject Classification ID: 70M20
Mathematics Subject Classification ID: 70Q05
Mathematics Subject Classification ID: 49N90
Mathematics Subject Classification ID: 70F07
zbMATH DE Number: 6173737
Wikidata QID: Q58912785
MaRDI profile type: Publication
full work available at URL: https://doi.org/10.1155/2012/971983
OpenAlex ID: W2064529553
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description: scientific article; zbMATH DE number 6173737