Sie befinden Sich nicht im Netzwerk der Universität Paderborn. Der Zugriff auf elektronische Ressourcen ist gegebenenfalls nur via VPN oder Shibboleth (DFN-AAI) möglich. mehr Informationen...
The Journal of the astronautical sciences, 2022, Vol.69 (6), p.1666-1690
2022

Details

Autor(en) / Beteiligte
Titel
Dual-Based Method for Global Optimization of Impulsive Orbital Maneuvers
Ist Teil von
  • The Journal of the astronautical sciences, 2022, Vol.69 (6), p.1666-1690
Ort / Verlag
New York: Springer US
Erscheinungsjahr
2022
Link zum Volltext
Quelle
SpringerNature Journals
Beschreibungen/Notizen
  • Optimization problems involving multiple impulsive maneuvers are, in general, nonlinear and nonconvex. This implies that their resolution is prone to local optimality and convergence issues. This work proposes an optimization method to exploit a specific structure of single-constraint nonlinear programming problems. The proposed algorithm is able to transform an optimization problem with an arbitrary number of variables into a root-finding problem of a univariate algebraic equation. Moreover, it can readily overcome the aforementioned local optimality and convergence issues. This methodology has been applied to three practical application examples. The first application involves the inclination optimization for change of plane maneuvers using drifting orbits with a relative nodal precession. The second application performs the semi-major axis optimization of phasing orbits, using a two-stage approach to solve it; specifically, the dual-based method yields a solution with phasing orbits that perform a fractional number of revolutions, which is then corrected to provide the appropriate integrality condition. The third application carries out the optimization of multi-impulse Hohmann-like transfers with an inclination change, relying on a conservation law that allows to compute a multi-impulse transfer from the solution of a two-impulse transfer. Finally, two highly relevant mission scenarios are described and numerically solved: the first scenario considers a geostationary transfer orbit with a phasing optimization to locate a satellite into a prescribed slot in geostationary orbit; the second scenario considers a multi-target rendezvous of a servicing spacecraft to visit several satellites of a constellation for debris removal or refueling operations.

Weiterführende Literatur

Empfehlungen zum selben Thema automatisch vorgeschlagen von bX