In this work the solution to the 8th Global Trajectory Optimisation Competition proposed from the PoliMi-UPM team is presented. With the aim of maximizing the objective function, a two-stage strategy has been devised. First, two spacecraft target selenoflybys to significantly modify their orbital parameters, in particular increasing the semi-major axis. Later, the formation is steered with lowthrust propulsion to point radio sources within the assigned tolerance. The latter is achieved by means of a geometrical method that minimises the orbital parameters variation, and that provides boundary condition for an indirect method solution of the Two-point Boundary Value Problem. No constraints on the number of seen radio sources have been applied. On a higher level, a genetic algorithm is used to identify the optimal flyby parameters.

GTOC8: Results and Methods of POLIMI-UPM

Topputo, F.;Dei Tos, D. A.;Filippetto, D.;Massari, M.;Di Lizia, P.;Gonzalo Gomez, J. L.;Pesce, V.;Colagrossi, A.;
2016

Abstract

In this work the solution to the 8th Global Trajectory Optimisation Competition proposed from the PoliMi-UPM team is presented. With the aim of maximizing the objective function, a two-stage strategy has been devised. First, two spacecraft target selenoflybys to significantly modify their orbital parameters, in particular increasing the semi-major axis. Later, the formation is steered with lowthrust propulsion to point radio sources within the assigned tolerance. The latter is achieved by means of a geometrical method that minimises the orbital parameters variation, and that provides boundary condition for an indirect method solution of the Two-point Boundary Value Problem. No constraints on the number of seen radio sources have been applied. On a higher level, a genetic algorithm is used to identify the optimal flyby parameters.
Spaceflight Mechanics 2016
978-0-87703-633-3
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Utilizza questo identificativo per citare o creare un link a questo documento: http://hdl.handle.net/11311/979343
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