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SUMMARY:Analysis of a Rendezvous Mission in Non-Keplerian Orbit using Elec
tric Propulsion
DTSTART;VALUE=DATE-TIME:20181108T103000Z
DTEND;VALUE=DATE-TIME:20181108T110000Z
DTSTAMP;VALUE=DATE-TIME:20220528T224357Z
UID:indico-contribution-3878@indico.esa.int
DESCRIPTION:Speakers: RubĂ©n Vega Astorga ()\, David Morante ()\, Manuel S
anjurjo-Rivo ()\, Manuel Soler ()\nThis paper presents the analysis of a l
ow-thrust rendezvous mission to a target non-Keplerian orbit of the circul
ar restricted three body problem (CR3BP) in the Earth-Moon system. The dyn
amical characteristics of this system are revisited\, and some non-Kepleri
an orbits (e.g.\, L1 halo orbits\, NRO and L2 halo orbits) have been simul
ated to study their suitability for a rendezvous mission. Starting from an
alytical approximations\, a shooting method has been used for the numerica
l\ndescription of these orbits. Afterwards\, the different monodromy matri
ces related to the integrated non-Keplerian orbits has been studied to ana
lyse their stability and to describe stable and unstable manifolds of the
orbit\, i.e.\, ballistic trajectories that can be covered by a spacecraft
without any propellant usage.\n\nThe design of a low-thrust rendezvous mis
sion in a non-keplerian orbit is approached as an optimal control problem\
, in which the solution is the thrust magnitude and direction along the pa
th. The propellant consumption has been set as the objective function to b
e minimized\, and the trajectory is subjected to a set of constraints rang
ing from thrust limitations and time requirements specified for each missi
on. The problem to be tackled is a rendezvous mission to a specific target
in a L2 Halo orbit. Hermite-Simpson collocation method has been used for
the numerical description of the dynamical constraints of the system. Then
\, the problem has been solved numerically with IPOPT (Interior Point OPTi
mizer). An unpowered trajectory integrated from the problem initial condit
ions is used for the solver initialization. The rendezvous mission impleme
ntation and the interface with that solver have been developed in Matlab.\
n\nThree different cases of rendezvous at the target L2 Halo orbit have be
en studied: 1) rendezvous from a nearby halo manifold\, 2) rendezvous from
a close halo orbit and 3) phasing manoeuvre starting from the same halo a
s the target. All the cases have shown to be feasible for being performed
with the use of an Electric Propulsion thruster. The final optimal traject
ories for those cases are presented. In addition\, it has been shown that
propellant consumption can be greatly reduced if the stability properties
of the targeted orbits are exploited.\n\nhttps://indico.esa.int/event/224/
contributions/3878/
LOCATION: Single 107
URL:https://indico.esa.int/event/224/contributions/3878/
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