Table 3 The Earth-centered modified classical orbital elements computed by the retrograde semi-analytical model at TLI epoch
From: Reachable set analysis of practical trans-lunar orbit via a retrograde semi-analytic model
\(\kappa_{{{\text{EJ2}}}}\)/m | \(e_{{{\text{EJ2}}}}\) | \(i_{{{\text{EJ2}}}}\)/deg | \({\Omega }_{{{\text{EJ2}}}}\)/deg | \(\omega_{{{\text{EJ2}}}}\)/deg | \(f_{{{\text{EJ2}}}}\)/deg | \(\Delta t\)/day |
|---|---|---|---|---|---|---|
7462500 | 0.96192 | 25.0860 | 22.5152 | 94.6927 | 0.00000 | 4.90386 |