D. Romagnoli, C. Circi

This paper deals with the realization of a Lunar Global Positioning System which uses two constellations of satellites around the L1 and L2 collinear libration points of the Earth - Moon system. Analytical solutions for periodic orbits around the collinear points have been investigated in the frame of the restricted three and four body problem. Different kinds of periodic orbits and geometry configurations for the constellations have been studied in order to minimize the amount of [delta]v needed for the station keeping maneuvers, also taking into consideration the requirements of satellite visibility from the Earth and coverage of the lunar surface. Particular attention was given to the definition of geometries of the constellations that guarantee coverage of the polar regions, due to their great importance in the renewed interest in lunar exploration. A short description of the control technique used for the station keeping on the periodic orbits is provided as well.

DGLR Symposium "To Moon and Beyond", 2008, Bremen

Conference Paper

englisch

21,6 x 27,9 cm, 10 Seiten

DGLR-Bericht, 2008, 2008-02, To Moon and Beyond; S.1-10; 2008; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

in getr. Zählung;

Bibliothek

2008