FI986

Looking at the Restart states from Rev 987 we have the following results for FI986
FI986		NoBurn	Plan	OD	Plan-NoBurn	OD-NoBurn	Plan-OD	SMA error	
MMS	Epoch of Plan Apogee	A(km)	A (km)	A (km)	A (km)	A (km)	A (km)		
MMS1	Mar 14 2019 02:04:22.693	97408.112	97382.147	97382.134	-25.965	-25.978	-0.01287	0.050%	
MMS2	Mar 14 2019 02:01:34.073	97408.108	97354.859	97354.661	-53.250	-53.448	-0.19794	0.372%	
MMS3	Mar 14 2019 02:11:27.171	97408.285	97447.894	97447.891	39.609	39.606	-0.00320	-0.008%	
MMS4	Mar 14 2019 02:06:20.369	97408.196	97408.196	97408.252	0.000	0.056	0.05594		
 
MMS1 was 0.506 m/s (net delta-v) and 17.96% axial, MMS2 was 1.513 m/s and 17.23% axial, and MMS3 was 1.661 m/s and 9.02% axial.

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_FI986	2019_70/20:51:12 to 2019_70/20:53:52	-1.6198	-0.4693	0.3305	
		0.016198	0.01	0.01	
		-0.0008609	-0.00006921	0.0002393	
MMS2_FI986	2019_70/22:26:12 to 2019_70/22:28:22	1.3577	0.4112	-0.0269	
		0.013577	0.01	0.01	
		0.004416	-0.003555	-0.0001373	
MMS1_FI986	2019_71/00:01:12 to 2019_71/00:02:12	0.5946	0.241	0.0372	
		0.01	0.01	0.01	
		0.00155	-0.002389	0.0004481