FR589

Looking at the Restart states from Rev 590 we have the following results for FR589.
FR589		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 20 2016 17:11:30.751	42105.394	42105.287	42105.295	-0.10636	-0.09862	-0.00774	7.28%	0.64%	
MMS2	Oct 20 2016 17:11:33.699	42105.392	42104.806	42104.824	-0.58592	-0.56829	-0.01763	3.01%	3.11%	
MMS3	Oct 20 2016 17:11:34.551	42105.407	42105.407	42105.417	0.00000	0.00987	-0.00988			
MMS4	Oct 20 2016 17:11:30.115	42105.407	42105.333	42105.338	-0.07381	-0.06921	-0.00460	6.23%	1.61%	
MMS1 was 0.095 m/s and 66.5% axial, MMS2 was 0.089 m/s and 0.5% axial, MMS4 was 0.55 m/s and 10.1% axial. These small DV values and the small SMA changes above 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.
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)	
MMS1_FR589	2016_293/22:06:11	0.0257	-0.0288	0.0334	
		0.01	0.01	0.01	
		-0.0008063	0.0009826	0.00048	
MMS2_FR589	2016_293/23:31:11	0.0607	-0.0497	-0.0211	
		0.01	0.01	0.01	
		-0.0009538	0.001149	0.0004297	
MMS14_FR589	2016_294/00:56:11 to 2016_294/00:56:21	0.049	0.0139	-0.0539	
		0.01	0.01	0.01	
		-0.0002094	-0.0003881	-0.0002001