FM927

Looking at the Restart states from Rev 928 we have the following results for FM927
FM927		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	Sep 21 2018 15:12:45.243	84260.710	84258.872	84258.947	-1.838	-1.762	-0.07557	4.111%	-1.001%	
MMS2	Sep 21 2018 15:12:40.221	84260.706	84258.966	84259.041	-1.740	-1.665	-0.07462	4.289%	1.767%	
MMS3	Sep 21 2018 15:13:11.982	84260.743	84260.574	84260.616	-0.169	-0.127	-0.04256	25.136%	0.190%	
MMS4	Sep 21 2018 15:13:18.261	84260.754	84260.754	84260.784	0.000	0.030	-0.02960			
 
MMS1 was 0.22 m/s (net delta-v) and 18.19% axial, MMS2 was 0.12 m/s and 24.67% axial, and MMS3 was 0.086 m/s and 58.34% axial.
Note that the MMS3 plane change error is more reflective of the results for MMS3 due to the larger axial component.

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 MMS3 DVx and MMS1 DVz.
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)	
MMS1_FM927	2018_262/20:25:47 to 2018_262/20:28:32	0.199406	0.076625	-0.00297	
		0.01	0.01	0.01	
		-0.003576	-0.00018	0.02145	
MMS2_FM927	2018_262/23:35:47 to 2018_262/23:38:22	-0.06998	-0.07182	-0.07402	
		0.01	0.01	0.01	
		-0.003503	0.0002122	0.0052	
MMS3_FM927	2018_263/01:10:47 to 2018_263/01:13:22	0.038006	0.032109	-0.06685	
		0.01	0.01	0.01	
		0.02263	0.0002846	-0.0049643