Table 6: JPL solution 102. The orbital elements are ecliptic heliocentric and error bars correspond to 1 σ formal uncertainties. Epoch TDB 2014 Jul 18.0 Eccentricity 1 . 0008169 ± 0 . 0000016 Perihelion distance 1 . 39866662 ± 0 . 00000071 au Time of perihelion TDB 2014 Oct 25 . 318385 ± 0 . 000096 d Longitude of node 300 . 977577 ◦ ± 0 . 000026 ◦ Argument of perihelion 2 . 438202 ◦ ± 0 . 000060 ◦ Inclination 129 . 027337 ± 0 . 000031 ◦ RA of spin pole 62 . 8 ◦ ± 7 . 0 ◦ DEC of spin pole 14 ◦ ± 14 ◦ Strength of jet 1 (86 . 5 ± 5 . 2) × 10 − 9 au/d 2 Strength of jet 2 (153 ± 67) × 10 − 9 au/d 2 Thrust angle of jet 1 60 . 2 ◦ ± 3 . 1 ◦ Thrust angle of jet 2 152 . 4 ◦ ± 4 . 8 ◦ Diurnal lag angle 9 . 4 ◦ ± 1 . 6 ◦ Mars encounter distance 140496 . 6 ± 4 . 0 km Epoch of closest approach to Mars TDB 2014 Oct 19 18:28:33.99 ± 0 . 85 s 28