FI748

Looking at the Restart states from Rev 749 we have the following results for FI748.
FI748		NoBurn	Plan	OD	Plan-NoBurn	OD-NoBurn	Plan-OD	SMA error	
MMS	Epoch of Plan Apogee	A(km)	A (km)	A (km)	A (km)	A (km)	A (km)		
MMS1	May 06 2017 07:10:39.247	83748.262	83891.081	83891.038	142.818	142.775	0.04293	0.030%	
MMS2	May 06 2017 07:10:00.537	83820.920	83891.026	83890.796	70.106	69.876	0.23025	0.328%	
MMS3	May 06 2017 07:09:25.029			83891.008					
MMS4	May 06 2017 07:08:16.999	83863.971	83891.069	83890.975	27.098	27.004	0.09467	0.349%	
 
MMS1 was 4.68 m/s (net delta-v) and 11.8% axial, MMS2 was 4.53 m/s and 35.4% axial, and MMS4 was 3.96 m/s and 32.2% axial.   

The Table below provides the following information:
•	First row for each maneuver: planned maneuver total delta-V values based on the associated DVTABLEs  
•	Second row for each maneuver: associated final maneuver planning requirements 
•	Third row for each maneuver: predicted velocity error at the time of the maneuver computed by differencing the predicted velocity at the maneuver time (starting with the post-perigee GEONS state prior to the maneuver) vs the definitive GEONS state at the time of the maneuver.
As shown in the table below, all maneuvering spacecraft meet the requirement.
Maneuver ID	Timespan	DVX (m/s)/ 
Req. (m/s)/
DiffVX(m/s)	DVY (m/s)/
Req. (m/s)/
DiffVY(m/s)	DVZ (m/s)/
Req. (m/s)/
DiffVZ(m/s)	
MMS2_FI748	2017_122/19:37:37 to 2017_122/19:44:37	-1.4452	-2.976	-3.1032	
		0.014452	0.02976	0.031032	
		0.000325	0.0003966	0.0004887	
MMS1_FI748	2017_122/21:52:27 to 2017_122/21:59:37	2.3563	-3.5256	-1.9888	
		0.023563	0.035256	0.019888	
		0.0000899	-0.0006557	0.000505	
MMS4_FI748	2017_123/1:23:57 to 2017_123/1:29:37	-0.9429	-2.8409	-2.5947	
		0.009429	0.028409	0.025947	
		0.0003542	0.002807	0.0007156