FM463

Looking at the Restart states from Rev 464 we have the following results for FM463.
FM463		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 17 2016 07:46:36.376	42106.843	42107.779	42107.763	0.93584	0.92029	0.01555	1.66%	-1.09%	
MMS2	Jun 17 2016 07:46:30.020	42110.706	42107.762	42107.776	-2.94362	-2.92998	-0.01365	0.46%	-0.66%	
MMS3	Jun 17 2016 07:46:06.217	42109.011	42107.790	42107.798	-1.22093	-1.21300	-0.00793	0.65%	-0.39%	
MMS4	Jun 17 2016 07:46:10.643	42111.323	42107.780	42107.781	-3.54281	-3.54203	-0.00078			

MMS1 was primarily axial and about 14 cm/s, MMS2 was about evenly radial and axial, MMS3 was also about evenly radial and axial and about 18 cm/s
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_FM463	2016_168/05:38:26 to 2016_168/05:39:36	-0.1174	0.4145	-0.2553	
		0.002	0.004145	0.002553	
		-0.0005	-0.0007	-0.0004	
MMS3_FM463	2016_168/07:49:06 to 2016_168/07:49:36	-0.1104	0.1069	-0.1258	
		0.002	0.002	0.002	
		-0.0004	-0.001	-0.0004	
MMS1_FM463	2016_168/10:19:16 to 2016_168/10:19:36	0.0724	-0.0282	0.1135	
		0.002	0.002	0.002	
		-0.0001	-0.001	-0.0003