Optimal Two-Impulse Trajectories with Moderate Flight Time for Earth-Moon Missions

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 todescribe the motion of the space vehicle: the well-known patched-conic approximation and two...

Full description

Saved in:
Bibliographic Details
Published in:Mathematical Problems in Engineering 2012-01, Vol.2012 (2012), p.1741-1774
Main Authors: da Silva Fernandes, Sandro, Maranhão Porto Marinho, Cleverson
Format: Article
Language:English
Citations: Items that this one cites
Items that cite this one
Online Access:Get full text
Tags: Add Tag
No Tags, Be the first to tag this record!
Description
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 todescribe 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.
ISSN:1024-123X
1563-5147
DOI:10.1155/2012/971983