Research Article
A Convex Approach for Trajectory Optimization of Super-Synchronous-Transfer-Orbit Large Launch Systems with Time-Position Constraints
Table 6
Deviations of terminal orbital elements.
| | Parameters | Deviations |
| | Semimajor axis, m | 1.26 | | Eccentricity | 0.0000001 | | Inclination, deg | -0.0001 | | Longitude of ascending node, deg | -0.0001 | | Argument perigee, deg | -0.0002 | | , s | 0.06 |
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