dc.contributor
Escola Tècnica Superior d'Enginyeries Industrial i Aeronàutica de Terrassa
dc.contributor
Universitat Politècnica de Catalunya. L'AIRE - Laboratori Aeronàutic i Industrial de Recerca i Estudis
dc.contributor.author
Colasurdo, Guido
dc.contributor.author
Casalino, Lorenzo
dc.contributor.author
Fantino, Elena
dc.identifier
Colasurdo, G.; Casalino, L.; Fantino, E. Minimum-fuel escape from two body sun-earth system. "Journal of guidance control and dynamics", 1999, vol. 22, núm. 5, p. 632-636.
dc.identifier
https://hdl.handle.net/2117/23186
dc.identifier
10.2514/2.4446
dc.description.abstract
Escaping from the solar system by receiving
gravity assist from the Earth is considered
in this paper. A simple procedure,which
neglects the eccentricity of the Earth’s orbit and uses the two-body problem equations
and the patched-conic approximation, provides
near-optimal trajectories using either a
single or multiple Earth flybys. The analysis
shows that the amount of propellant required
to escape from the solar system decreases
with the number of flybys, but the mission
time increases. The same approach is also
used to find near-optimal trajectories that
use a single powered flyby. The eccentricity
of the Earth’s orbit can be exploited to
reduce the characteristic velocity; an
indirect optimization procedure provides
the most favorable locations where the Earth
should be intercepted.
dc.description.abstract
Peer Reviewed
dc.description.abstract
Postprint (published version)
dc.format
application/pdf
dc.rights
Restricted access - publisher's policy
dc.subject
Àrees temàtiques de la UPC::Aeronàutica i espai::Astronàutica::Navegació espacial
dc.subject
Àrees temàtiques de la UPC::Física::Astronomia i astrofísica
dc.subject
Outer space--Exploration
dc.subject
Two-body problem
dc.subject
Earth (Planet)--Orbit
dc.subject
Sistema solar -- Exploració
dc.title
Minimum-fuel escape from two body sun-earth system
