An indirect procedure to optimize the deployment of a two-spacecraft formation into a highly elliptic orbit is presented. The necessary conditions for the optimality are fully derived; a peculiar shooting technique, based on the Newton method, is described. An exhaustive numerical analysis is carried out considering the two-body keplerian model; some results, taking the Lunisolar perturbation and the Earth Asphericity into account, are also presented.
Optimal cooperative deployment of a two-satellite formation into a highly elliptic orbit / Zavoli, Alessandro; F., Simeoni; L., Casalino; Colasurdo, Guido. - STAMPA. - 142(2012), pp. 3647-3663.
Optimal cooperative deployment of a two-satellite formation into a highly elliptic orbit
ZAVOLI, ALESSANDRO;COLASURDO, Guido
2012
Abstract
An indirect procedure to optimize the deployment of a two-spacecraft formation into a highly elliptic orbit is presented. The necessary conditions for the optimality are fully derived; a peculiar shooting technique, based on the Newton method, is described. An exhaustive numerical analysis is carried out considering the two-body keplerian model; some results, taking the Lunisolar perturbation and the Earth Asphericity into account, are also presented.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
