FM645

Looking at the Restart states from Rev 646 we have the following results for FM645.
FM645		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 15 2016 10:40:55.074	42105.314	42105.314	42105.350	-0.00001	0.03598	-0.03599			
MMS2	Dec 15 2016 10:40:57.985	42105.285	42105.182	42105.214	-0.10329	-0.07168	-0.03161	30.60%	0.96%	
MMS3	Dec 15 2016 10:40:56.952	42105.294	42105.654	42105.664	0.35955	0.36990	-0.01035	-2.88%	1.61%	
MMS4	Dec 15 2016 10:40:53.236	42105.300	42105.348	42105.368	0.04792	0.06755	-0.01962	-40.95%	0.82%	
MMS2 was 0.230 m/s and 36.6% axial, MMS3 was 0.079 m/s and 42.74% axial, MMS4 was 0.090 m/s and 50.2% axial. The small SMA changes above produce larger percentage error values in SMA error.  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	Timespan0	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_FM645	2016_349/13:41:11 to 2016_349/13:41:31	0.1616	-0.0682	-0.1546	
		0.01	0.01	0.01	
		0.0006	-0.0031	-0.0008	
MMS3_FM645	2016_349/15:11:11 to 2016_349/15:11:21	-0.0312	0.0691	-0.0212	
		0.01	0.01	0.01	
		0.0015	-0.0037	-0.001	
MMS4_FM645	2016_349/16:36:11 to 2016_349/16:36:21	0.0654	0.0156	-0.0585	
		0.01	0.01	0.01	
		0.002	-0.0045	-0.0013