FM617

Looking at the Restart states from Rev 618 we have the following results for FM617.
FM617		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 17 2016 13:55:59.008	42105.322	42105.387	42105.405	0.06446	0.08308	-0.01862	-28.89%	0.70%	
MMS2	Nov 17 2016 13:56:02.868	42105.327	42105.338	42105.321	0.01077	-0.00590	0.01667	154.80%	0.90%	
MMS3	Nov 17 2016 13:56:03.396	42105.304	42106.434	42106.426	1.13027	1.12243	0.00783	0.69%	1.35%	
MMS4	Nov 17 2016 13:55:56.468	42105.315	42105.315	42105.312	0.00000	-0.00259	0.00259			
MMS1 was 0.0995 m/s and 89.31% axial, MMS2 was 0.090 m/s and 63.55% axial, MMS3 was 0.11 m/s and 31.5% axial. These small DV values and the very small SMA changes for MMS1 and MMS2 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)	
MMS3_FM617	2016_321/17:51:11 to 2016_321/17:51:11	0.0835	0.0267	0.0618	
		0.01	0.01	0.01	
		-0.0008732	0.002094	0.0007389	
MMS2_FM617	2016_321/20:11:11 to 2016_321/20:11:21	-0.0341	0.046	-0.0668	
		0.01	0.01	0.01	
		-0.0022990	0.004483	0.0011310	
MMS1_FM617	2016_321/21:46:11 to 2016_321/21:46:31	0.0159	0.0429	-0.0898	
		0.01	0.01	0.01	
		-0.0030030	0.004344	-0.0006156