Table 6 The Earth-centered modified classical orbital elements computed with the high-precision 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 |
|---|---|---|---|---|---|---|
6564074 | 0.96691 | 28.5008 | 61.4684 | 60.2577 | 359.7095 | 5.0708 |