1. Bias 0.3 mm/s Per pass A.D. at 1e-13/day yields an
2. thesecondstationreceivingit. The lower plot window also shows the periods when the FLAK is `active' (i.e., higher acceleration levels) and `quiet'. The blue dashed guidelines assist the reader in seeing the start/stop times of the active/quiet periods on the upper figure. Finally, the dashed red lines indicate maneuver times beginningwith TLI, then TCMs1-4, and ending atthefarrightwithLOI.
3. The current state results illustrate that just prior to TLI the filter solution transient has settled, and then there is a spike corresponding to TLI. Post-TLI the solution doesn't settle until the 3-Way tracking between Canberra and Usudabegins. ByTCM1 thesolutionisreachingits steadystate performance at 300 mto 1km(3) for the duration of TLC. Near TCM4 the pointing accuracy of the two cameras degrades from the µrads level to the mrads with a subsequent decrease in overall position knowledge to 2-3 km (3). The maneuver analysis using the LAMBIC function provides bounds on the trajectory correction maneuvers and can be used for delta V budgeting. The result for the nominal case is shown in below in Table 8. For convenience the statistical clean up maneuver that occurs 6 hours after LOI (hence while in Iunar orbit) is included in the results in addition to the 4 TCMs that occur during
4. LOI trans-lunar cruise. The first maneuver is large due to maneuver execution errors of the TLI maneuver by the EDS engine. Parametric studies have shown that if the EDS engine execution errors can be minimized the size of TCM1 will be reduced as well. The TCMs 2-4 magnitudes are due primarily to FLAK, and can be reduced if the FLAK levels are reduced. As with TCM1, the LOI clean-up maneuver is large relative to the TCMs 2-4 because of LOI executionerrors. Table 8: UpperBounds on Trajectory Correction Maneuvers