FM830

Looking at the Restart states from Rev 831 we have the following results for FM830.
FM830		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 22 2017 09:47:12.409	84266.530	84266.530	84266.561	0.000	0.031	-0.03065			
MMS2	Dec 22 2017 09:47:09.116	84266.552	84269.049	84269.141	2.497	2.589	-0.09241	-3.701%	0.837%	
MMS3	Dec 22 2017 09:47:10.603	84266.502	84266.744	84266.862	0.242	0.360	-0.11777	-48.585%	0.684%	
MMS4	Dec 22 2017 09:47:26.299	84266.568	84268.733	84268.862	2.165	2.294	-0.12965	-5.989%	0.631%	
 
MMS2 was 0.28 m/s (net delta-v) and 52.77% axial, MMS3 was 0.24 m/s and 68.05% axial, and MMS4 was 0.26 m/s and 51.44% axial.
The plane change error is more representative of actual maneuver error due to the large axial component of the maneuvers. Also see DV errors below.   

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 DVX, MMS3 DVX and MM3 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_FM830	2017_354/13:46:12 to 2017_354/13:47:02	-0.1594	0.0289	-0.2257	
		0.01	0.01	0.01	
		0.003	0.007	0.0005	
MMS4_FM830	2017_354/16:46:12 to 2017_354/16:46:52	-0.1454	-0.0024	-0.2159	
		0.01	0.01	0.01	
		0.008	0.011	0.0006	
MMS3_FM830	2017_354/18:21:12 to 2017_354/18:22:02	0.058	0.0477	-0.2266	
		0.01	0.01	0.01	
		0.015	0.0175	0.001