FM958

Looking at the Restart states from Rev 959 we have the following results for FM958
FM958		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 17 2018 22:11:11.470	84204.437	84209.197	84209.220	4.760	4.783	-0.02272	-0.477%	1.630%	
MMS2	Dec 17 2018 22:11:03.896	84209.209	84209.187	84209.236	-0.023	0.027	-0.04980			
MMS3	Dec 17 2018 22:11:09.835	84204.197	84209.242	84209.252	5.045	5.055	-0.01027	-0.204%	-0.816%	
MMS4	Dec 17 2018 22:11:21.877	84206.566	84209.226	84209.223	2.660	2.657	0.00271	0.102%	-10.056%	
 
MMS1 was 0.30 m/s (net delta-v) and 23.10% axial, MMS3 was 0.286 m/s and 23.47% axial, and MMS4 was 0.185 m/s and 4.45% axial.
The plane change for MMS4 was a factor of 10 smaller than the other spacecraft and mostly radial, which is why the error percentage was so large.  

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)	
MMS3_FM958	2018_348/22:14:17 to 2018_348/22:14:37	0.2674	0.0149	0.0878	
		0.002674	0.002	0.002	
		-0.0001375	-0.00004706	-0.00008525	
MMS1_FM958	2018_349/00:19:07 to 2018_349/00:19:37	0.2888	-0.0134	-0.0926	
		0.002888	0.002	0.002	
		-0.00009268	0.000148	0.00002019	
MMS4_FM958	2018_349/02:09:17 to 2018_349/02:09:37	0.183	-0.0024	0.0061	
		0.002	0.002	0.002	
		-0.00002716	-0.00000554	-0.00003705