FM831

Looking at the Restart states from Rev 832 we have the following results for FM831.
FM831		NoBurn	Plan	OD	Plan-NoBurn	OD-NoBurn	Plan-OD	SMA error	Plane change error	
MMS	Epoch of Plan Apogee	A(km)	A (km)	A (km)	A (km)	A (km)	A (km)			
MMS1	Dec 25 2017 05:24:36.869	84222.900	84222.860	84222.825	-0.041	-0.075	0.03433			
MMS2	Dec 25 2017 05:24:28.841	84225.477	84222.863	84222.764	-2.614	-2.714	0.09935	-3.800%	-0.583%	
MMS3	Dec 25 2017 05:24:32.869	84223.198	84222.907	84222.766	-0.291	-0.432	0.14072	-48.334%	-0.989%	
MMS4	Dec 25 2017 05:24:45.125	84225.193	84222.945	84222.788	-2.248	-2.405	0.15724	-6.996%	1.033%	
 
MMS2 was 0.14 m/s (net delta-v) and 37.09% axial, MMS3 was 0.13 m/s and 51.02% axial, and MMS4 was 0.12 m/s and 33.0% axial.
The plane change error is more representative of actual maneuver error due to the large axial component of the maneuvers. The errors were of roughly equal magnitude of FM830 and so cancelled each other.   

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 requirements.
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)	
MMS3_FM831	2017_355/17:34:17 to 2017_355/17:34:37	0.0222	0.0184	0.1146	
		0.002	0.002	0.002	
		0.00025	0.00175	0.00075	
MMS2_FM831	2017_355/19:24:27 to 2017_355/19:24:37	-0.1199	-0.0179	0.0779	
		0.002	0.002	0.002	
		0.00025	0.0015	0.0005	
MMS4_FM831	2017_355/23:04:27 to 2017_355/23:04:37	-0.0857	0.0266	0.0772	
		0.002	0.002	0.002	
		0.0001	0.002	0.0005