FR379

Looking at the Restart states from Rev 380 we have the following results for FR379.

FR379		NoBurn	Plan	OD	Plan-NoBurn	OD-NoBurn	Plan-OD	error	
MMS	Epoch of Plan Apogee	A(km)	A (km)	A (km)	A (km)	A (km)	A (km)		
MMS1	Mar 25 2016 17:23:43.135	42098.227	42101.889	42101.913	3.66255	3.68668	-0.02413	-0.66%	
MMS2	Mar 25 2016 17:23:38.300	42104.783	42101.907	42101.920	-2.87549	-2.86237	-0.01312	0.46%	
MMS3	Mar 25 2016 17:23:24.342	42104.152	42101.902	42101.913	-2.24993	-2.23917	-0.01075	0.48%	

All three DVs were highly axial and had plan change errors of 0.21%, 0.11% and 0.32% respectively.
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_FR379	2016_84/13:52:36 to 2016_84/13:54:36	0.0757	-0.0243	0.6875	
		0.002	0.002	0.006875	
		-0.0002	-0.0002	-0.00025	
MMS1_FR379	2016_84/15:28:26 to 2016_84/15:29:36	0.1569	-0.5268	0.1976	
		0.002	0.005268	0.002	
		-0.0008	-0.001	-0.00075	
MMS2_FR379	2016_84/17:03:36 to 2016_84/17:04:36	-0.3387	-0.0835	0.361	
		0.003387	0.002	0.00361	
		-0.0011	-0.0019	-0.001