Abstract

This paper discusses a method for solving the so called low-thrust Lambert’ s problem. The problem is formulated as a two-points boundary value one, where the initial and final positions are provided in terms of equinoctial variables. A first-order perturbative method is used for investigate the development of orbital elements generated by the low-thrust propulsion system, which acts as a perturbative parameter with respect to the zero-order Keplerian motion. An implicit formulation is thus obtained which allows for the determination of the low-thrust transfer trajectory driving the equinoctial parameters from the initial to their final values in a prescribed time. Furthermore the paper presents three test cases, which demonstrate the flexibility of the method for different missions: the first example is a spiral multi-revolution transfer from low Earth orbit to the International Space Station, the second is a interplanetary transfer from Earth to Mars, while the third is a geostationary transfer orbit to a geostationary orbit.

Autore Pugliese

• Avanzini Giulio

Tutti gli autori

• G. Avanzini , A. Palmas , E. Vellutini

Titolo volume/Rivista

Non Disponibile

Anno di pubblicazione

2011

ISSN

Non Disponibile

ISBN

Non Disponibile

Numero di citazioni Wos

Nessuna citazione

Ultimo Aggiornamento Citazioni

Non Disponibile

Numero di citazioni Scopus

Non Disponibile

Ultimo Aggiornamento Citazioni

Non Disponibile

Settori ERC

Non Disponibile

Codici ASJC

Non Disponibile