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Table 2

Results of 5 and 10 Myr integration time, considering the main regular satellites of Uranus and 6 fictitious satellites beyond Oberon (placed on LLP).

Initial conditions-mean values-si on LLP
M A U T O s1 s2 s3 s4 s5 s6
5.08 7.47 10.41 17.07 22.83 27.50 33.00 39.60 47.50 57.00 68.40
0.001 0.001 0.003 0.001 0.001 0.001 0.001 0.001 0.001 0.001 0.001
0.00/0.00 0.04 0.12 0.08 0.07 0.41/0.21 1.09/0.55 3.39/1.51 19.20/5.14 105.86/42.44 99.91/102.79
Final mean elements-without planetesimals
M1
5.08 7.47 10.41 17.06 22.83 27.50 32.99 39.57 47.23 T A
0.001 0.001 0.004 0.002 0.002 0.006 0.012 0.019 0.077 T A
0.17 0.64 0.12 0.75 1.18 1.56 2.75 3.00 1.37 T A
M2
5.08 7.47 10.40 17.07 22.83 27.50 33.00 39.60 47.48 U O
0.001 0.001 0.006 0.001 0.002 0.006 0.002 0.001 0.002 U O
0.02 0.17 0.08 0.14 0.19 0.40 1.21 4.09 22.03 U O
M3
5.08 7.47 10.41 17.07 22.82 27.50 33.00 39.62 47.38 A O
0.001 0.001 0.004 0.002 0.002 0.005 0.005 0.005 0.005 A O
0.10 0.27 0.53 0.28 0.43 0.58 4.07 4.83 6.57 A O
M4
5.08 7.46 10.41 17.08 22.84 27.47 32.93 39.22 s1 A O
0.001 0.002 0.003 0.003 0.003 0.016 0.036 0.037 s1 A O
0.13 0.95 2.52 1.23 1.93 2.54 9.51 2.82 s1 A O
M5
4.91 7.47 10.41 17.07 22.83 27.50 32.98 39.56 ej M O
0.035 0.001 0.004 0.001 0.002 0.009 0.017 0.016 ej M O
0.44 4.26 1.34 0.27 0.42 0.62 4.84 8.05 ej M O

Notes. The planets migrate following the Mi, i = 1...5, successful models, without planetesimals. Subscript i refers to initial values and note that eq is used to indicate the inclinations of the LLP with respect to the equator of Uranus (in the case of fictitious satellites). LLP (I1/I2) is calculated for aU = 11.5 AU (M1, M2, M4, and M5) or aU = 14.2 AU (M3), depending on model Mi. The notation for the satellites are M = Miranda, A = Ariel, U = Umbriel, T = Titania, O = Oberon, s1, s2, s3, s4, s5, s6. Ejected satellites are indicated by “ej”. Satellites that have experienced catastrophic collisions have in the corresponding column, the name of the impactor. Except for Miranda’s inclination, the initial conditions of the regular satellites are given at “http://ssd.jpl.nasa.gov/?sat_elem”.

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