FR758

Looking at the Restart states from Rev 759 we have the following results for FR758.
FR758		NoBurn	Plan	OD	Plan-NoBurn	OD-NoBurn	Plan-OD	SMA error	PC Error	
MMS	Epoch of Plan Apogee	A(km)	A (km)	A (km)	A (km)	A (km)	A (km)			
MMS1	Jun 03 2017 07:15:40.548	83895.259	83907.004	83907.018	11.745	11.760	-0.01444	-0.123%	0.082%	
MMS2	Jun 03 2017 07:15:12.323	83895.069	83901.139	83901.102	6.070	6.033	0.03660	0.603%	0.743%	
MMS3	Jun 03 2017 07:14:32.070	83895.145	83895.145	83895.119	0.000	-0.026	0.02552			
MMS4	Jun 03 2017 07:14:14.661	83895.079	83893.338	83893.327	-1.740	-1.752	0.01146	-0.658%	-0.060%	
 
MMS1 was 0.32 m/s (net delta-v) and 60.03% axial, MMS2 was 0.297 m/s and 21.97% axial, and MMS4 was 0.36 m/s and 66.67% 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 in most components except for DVX on MMS4, DVY on MMS1 and MMS4.
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_FR758	2017_152/10:06:12 to 2017_152/10:06:42	0.3806	0.0426	-0.0217	
		0.01	0.01	0.01	
		-0.004318	0.008588	0.001329	
MMS1_FR758	2017_152/11:41:12 to 2017_152/11:42:12	0.0199	0.2296	-0.2068	
		0.01	0.01	0.01	
		-0.006233	0.01092	0.001524	
MMS4_FR758	2017_152/13:16:12 to 2017_152/13:17:12	0.1396	0.0516	-0.2983	
		0.01	0.01	0.01	
		-0.01105	0.01639	0.001573