FM646

Looking at the Restart states from Rev 647 we have the following results for FM646.
FM646		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	Dec 16 2016 10:34:04.188	42104.990	42105.009	42104.972	0.01894	-0.01847	0.03741			
MMS2	Dec 16 2016 10:34:08.703	42104.854	42105.004	42104.980	0.15015	0.12571	0.02444	16.28%	-0.05%	
MMS3	Dec 16 2016 10:34:09.082	42105.304	42104.984	42104.955	-0.32071	-0.34946	0.02876	-8.97%	-0.24%	
MMS4	Dec 16 2016 10:34:03.139	42105.008	42104.992	42104.979	-0.01566	-0.02896	0.01330	-84.97%	0.46%	
 MMS2 was 0.20 m/s and 69.8% axial, MMS3 was 0.175 m/s and 24.6% axial, MMS4 was 0.11 m/s 50.4% axial. These small DV values and small SMA changes produce larger percentage SMA error values. The plane change error is more representative of the actual error in these maneuvers.     
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)	
MMS4_FM646	2016_350/07:34:26 to 2016_350/07:34:36	-0.0639	-0.0748	0.0481	
		0.002	0.002	0.002	
		-0.0002	-0.0005	-0.00021	
MMS2_FM646	2016_350/10:39:06 to 2016_350/10:39:36	-0.0325	-0.145	0.1348	
		0.002	0.002	0.002	
		-0.0001	-0.0006	-0.0002	
MMS3_FM646	2016_350/11:54:26 to 2016_350/11:54:36	0.0262	-0.1697	-0.0225	
		0.002	0.002	0.002	
		-0.00001	-0.0003	-0.00003