In a previous work we studied the effects of (I) the J 2 and C 22 terms of the lunar potential and (II) the rotation of the primary on the critical inclination orbits of artificial satellites. Here, we show that, when 3 rd -degree gravity harmonics are taken into account, the long-term orbital behavior and stability are strongly affected, especially for a non-rotating central body, where chaotic or collision orbits dominate the phase space. In the rotating case these phenomena are strongly weakened and the motion is mostly regular. When the averaged effect of the Earth's perturbation is added, chaotic regions appear again for some inclination ranges. These are more important for higher values of semi-major axes. We compute the main families of periodic orbits (POs), which are shown to emanate from the 'frozen eccentricity' and 'critical inclination' solutions of the axisymmetric problem ('J 2 + J 3 '). Although the geometrical properties of the orbits are not preserved, we find that the variations in e, I and g can be quite small, so that they can be of practical importance to mission planning.
We study the problem of critical inclination orbits for artificial lunar satellites, when in the lunar potential we include, besides the Keplerian term, the J 2 and C 22 terms and lunar rotation. We show that, at the fixed points of the 1-D averaged Hamiltonian, the inclination and the argument of pericenter do not remain both constant at the same time, as is the case when only the J 2 term is taken into account. Instead, there exist quasi-critical solutions, for which the argument of pericenter librates around a constant value. These solutions are represented by smooth curves in phase space, which determine the dependence of the quasicritical inclination on the initial nodal phase. The amplitude of libration of both argument of pericenter and inclination would be quite large for a non-rotating Moon, but is reduced to <0 • .1 for both quantities, when a uniform rotation of the Moon is taken into account. The values of J 2 , C 22 and the rotation rate strongly affect the quasi-critical inclination and the libration amplitude of the argument of pericenter. Examples for other celestial bodies are given, showing the dependence of the results on J 2 , C 22 and rotation rate.
Η παρούσα διατριβή αφορά στη μελέτη της κίνησης τεχνητού δορυφόρου γύρω από μησυμμετρικό, περιστρεφόμενο ουράνιο σώμα, με έμφαση στη Σελήνη, το δορυφόρο του Δία,Ευρώπη και τον αστεροειδή Εστία. Σκοπός μας είναι η ανάλυση των διαταραχών της τροχιάςενός τεχνητού δορυφόρου, που προκαλούνται από την ασυμμετρία του βαρυτικού πεδίου τουκεντρικού σώματος σε συνδυασμό με την περιστροφή του και πιθανώς την επίδραση τρίτουσώματος (π.χ. της Γης, για δορυφόρους της Σελήνης). Με τη χρήση αναλυτικών καιαριθμητικών μεθόδων, «χαρτογραφούμε» το χώρο των φάσεων, υπολογίζοντας τις μεταβολέςκάθε τύπου τροχιάς, για χρονικά διαστήματα αντίστοιχα με την τυπική διάρκεια μιαςαποστολής επισκόπησης (μερικά έτη). Τα αποτελέσματά μας μπορούν να χρησιμοποιηθούν(α) για τον αποδοτικό σχεδιασμό δορυφορικών τροχιών επισκόπησης και (β) για τονακριβέστερο υπολογισμό των φυσικών χαρακτηριστικών της Σελήνης και άλλων σωμάτων.
scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citations–citations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.