FM618

Looking at the Restart states from Rev 619 we have the following results for FM618.
FM618		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	Nov 18 2016 13:49:05.716	42105.151	42105.059	42105.048	-0.09215	-0.10295	0.01079	-11.71%	0.47%	
MMS2	Nov 18 2016 13:49:08.777	42105.067	42105.023	42105.021	-0.04352	-0.04628	0.00277	-6.35%	0.37%	
MMS3	Nov 18 2016 13:49:14.854	42106.172		42106.153		-0.01860				
MMS4	Nov 18 2016 13:49:04.518	42105.058		42105.036		-0.02118				
 MMS1 was 0.11 m/s and 40% axial, MMS2 was 0.13 m/s and 44.9% axial, MMS3 was not executed. 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)	
MMS1_FM618	2016_322/13:39:26 to 2016_322/13:39:36 	-0.0318	0.0415	0.0909	
		0.002	0.002	0.002	
		0.0007244	-0.001276	-0.0003340	
MMS2_FM618	2016_322/15:09:26 to 2016_322/15:09:36	-0.0681	0.086	0.0883	
		0.002	0.002	0.002	
		0.0000382	-8.513E-05	0.0001495