FR980

Looking at the Restart states from Rev 981 we have the following results for FR980
FR980		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	Feb 21 2019 01:36:57.418	97431.513	97431.513	97431.519	0.000	0.006	-0.00577		
MMS2	Feb 21 2019 01:34:33.799	97431.344	97425.946	97425.891	-5.399	-5.454	0.05494	-1.018%	
MMS3	Feb 21 2019 01:41:24.104	97431.936	97424.896	97424.891	-7.041	-7.045	0.00432	-0.061%	
MMS4	Feb 21 2019 01:39:27.308	97433.564	97444.782	97444.786	11.218	11.223	-0.00483	-0.043%	
 
MMS2 was 0.116 m/s (net delta-v) and 13.37% axial, MMS3 was 0.129 m/s and 16.42% axial, and MMS4 was 0.495 m/s and 7.18% axial.

No plane change error included since these maneuver had very little plane change.
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)	
MMS4_FR980	2019_49/18:51:12 to 2019_49/18:52:02	-0.4734	-0.1258	0.072	
		0.01	0.01	0.01	
		0.001271	-0.001713	-0.0008081	
MMS42_FR980	2019_49/20:46:12 to 2019_49/20:46:22	0.1155	0.0038	-0.0096	
		0.01	0.01	0.01	
		-0.002904	0.001238	0.0003193	
MMS3_FR980	2019_49/22:51:12 to 2019_49/22:51:22	0.1259	0.0062	-0.0023	
		0.01	0.01	0.01	
		-0.003467	0.001255	0.0004371