TY - JOUR
A2 - Prado, Antonio F. Bertachini A.
AU - da Silva Fernandes, Sandro
AU - MaranhÃ£o Porto Marinho, Cleverson
PY - 2012
DA - 2011/11/24
TI - Optimal Two-Impulse Trajectories with Moderate Flight Time for Earth-Moon Missions
SP - 971983
VL - 2012
AB - 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.
SN - 1024-123X
UR - https://doi.org/10.1155/2012/971983
DO - 10.1155/2012/971983
JF - Mathematical Problems in Engineering
PB - Hindawi Publishing Corporation
KW -
ER -