FR590

Looking at the Restart states from Rev 591 we have the following results for FR590.
FR590		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	Oct 21 2016 17:04:37.854	42105.138	42105.268	42105.268	0.12950	0.13039	-0.00089	-0.69%	-0.04%	
MMS2	Oct 21 2016 17:04:41.826	42104.667	42105.277	42105.274	0.60978	0.60689	0.00289	0.47%	-0.98%	
MMS3	Oct 21 2016 17:04:41.628	42105.261	42105.270	42105.249	0.00918	-0.01151	0.02069			
MMS4	Oct 21 2016 17:04:35.905	42105.180	42105.265	42105.262	0.08412	0.08196	0.00216	2.56%	1.71%	
 MMS1 was 0.079 m/s and 62% axial, MMS2 was 0.069 m/s and 41% axial, MMS4 was 0.077 m/s and 28% axial. These small DV values and small SMA changes produce larger percentage error values.
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 except MMS4 for DVY.
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_FR590	2016_294/14:19:36	0.0243	-0.0597	0.0145	
		0.002	0.002	0.002	
		-0.0005456	-0.001133	-0.0005521	
MMS1_FR590	2016_294/15:59:36	0.0104	0.0509	-0.0149	
		0.002	0.002	0.002	
		-0.0004910	-0.001721	-0.0006403	
MMS4_FR590	2016_294/17:34:26 to 2016_294/17:34:36	-0.0088	0.0062	0.0667	
		0.002	0.002	0.002	
		-0.0001973	-0.002368	-0.0006405