All Tables

Table 1: Initial orbital elements and evolution of case-study objects. Notes: Columns are, from left: Object designation; initial orbital elements (epoch is JD 2 452 120.5); number of approaches within the Hill spheres of Mercury and Venus; time until achievement of Venus crossing orbit; time until first Venus close approach; lifetime; note ("CO'' means collision). Data from integration 4.
Table 2: Examples of temporary capture orbits. Columns are, from left: Object and capture event designation; group membership; period between first and last entry of Hill sphere ( $t_{\rm orb}$ ); orbital elements a, e, and i 100 days prior to (first) entry of Hill sphere; change in orbital elements a, e, and i (values at 100 days prior to (first) entry of Hill sphere minus values at 100 days post (last) exit of Hill sphere; mean anomaly at capture ( $M_{\rm cap}$ , first entry of Hill sphere) and escape ( $M_{\rm esc}$ , last exit of Hill sphere); number of complete revolutions in same sense between (first) entry and (last) escape of Hill sphere, relative to initial mean anomaly in hermeocentric orbit ( $N_{\rm orb}$ ); rotational sense (retrograde or prograde) of each initiated revolution (temporally from left to right) relative to initial mean anomaly in hermeocentric orbit and to plane of orbit in the Mercury centered reference frame; average period of revolution ( $<P_{\rm orb}>$ ); minimum distance to Mercury ( $R_{\rm min}$ , Mercury radii); and minimal energy of elleptic orbit relative to Mercury ( $E_{\rm min}$ ). Data from integration 3.
Table 3: Orbital parameters in the short-term hermeocentric integration. Columns are, from left: Object designation; initial hermeocentric a ( $a_{\rm ini}$ ) and e ( $e_{\rm ini}$ ); average a and e during hermeocentric orbit, with extreme ranges; average orbital period; minimal and maximal periods (relative to initial M of hermeocentric orbit); duration of hermeocentric orbit (<P>); number of revolutions relative to initial M of hermeocentric orbit ( $N_{\rm orb}$ ); rotational sense (prograde/retrograde); mean anomaly of Mercury at time of escape from hermeocentric orbit ( $L_{\rm esc}$ ); identity of Lagrangian point traversed at escape from hermeocentric orbit ( $T_{\rm CO}$ ); and time of collision with Mercury. Data from integration 5 (100 day duration). Object 93r is the originally identified satellite. For object 75-75p, close approaches with Venus are initiated after 1.78 Myr.
Table 4: Orbital parameters in the long-term hermeocentric integration. Notes: Columns are, from left: Object designation; initial hermeocentric a and e; average a with extreme range; duration of hermeocentric orbit; rotational sense (prograde/retrograde); notes or end fate ("CO'' indicates collision with Mercury). Data from integration 5 for situation at t=4.54 Myr. Values of <a> are for the initial 75 kyr of the integration, unless otherwise indicated in the "Note'' column. Object 93r is the originally identified satellite.