FM406

Looking at the Restart states from Rev 407 we have the following results for FM406.
FM406		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	Apr 21 2016 14:14:38.307	42104.011	42100.072	42100.103	-3.93887	-3.90795	-0.03092	0.79%	0.01%	
MMS2	Apr 21 2016 14:14:39.061	42104.024	42103.684	42103.710	-0.34029	-0.31418	-0.02611	7.67%	-0.002%	
MMS3	Apr 21 2016 14:14:23.558	42104.012	42104.012	42104.049	0.00000	0.03720	-0.03720			
MMS4	Apr 21 2016 14:14:32.005	42104.002	42103.963	42103.972	-0.03920	-0.02976	-0.00944	24.09%	0.14%	

All three DVs were highly axial so the Plane Change errors are the relevant values.  As seen above the “SMA error” (Plan-OD) in km for the reference spacecraft is larger than that of any of the other spacecraft.
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)	
MMS2_FM406	2016_111/18:51:11 to 2016_111/18:52:31	0.0047	-0.2894	0.344	
		0.01	0.01	0.01	
		0.0006443	0.000396	0.0006143	
MMS1_FM406	2016_111/20:26:11 to 2016_111/20:27:31	-0.0067	-0.4954	0.2549	
		0.01	0.01	0.01	
		0.00233	0.00119	0.001006	
MMS4_FM406	2016_111/22:01:11 to 2016_111/22:03:21	0.033	-0.3799	0.6196	
		0.01	0.01	0.01	
		0.0003101	0.001855	0.002185