FR937

Looking at the Restart states from Rev 938 we have the following results for FR937
FR937		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	Oct 19 2018 19:01:22.445	84240.379	84240.379	84240.401	0.000	0.021	-0.02107			
MMS2	Oct 19 2018 19:01:19.820	84240.347	84241.259	84241.447	0.912	1.100	-0.18806	-20.628%	0.185%	
MMS3	Oct 19 2018 19:02:01.360	84240.409	84248.619	84248.670	8.209	8.260	-0.05108	-0.622%	0.857%	
MMS4	Oct 19 2018 19:02:06.795	84240.406	84249.236	84249.372	8.830	8.966	-0.13599	-1.540%	0.494%	
 
MMS2 was 0.31 m/s (net delta-v) and 5.33% axial, MMS3 was 0.197 m/s and 44.23% axial, and MMS4 was 0.28 m/s and 44.50% axial.
Even though MMS2 was largely radial there was not much SMA change.  Small DV angular change produced large SMA errors.

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 MMS2 DVx and MMS4 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)	
MMS2_FR937	2018_291/00:31:12 to 2018_291/00:31:42	-0.2604	-0.1322	-0.0899	
		0.01	0.01	0.01	
		0.01191	-0.007693	0.0003366	
MMS3_FR937	2018_291/02:06:12 to 2018_291/02:06:32	-0.1477	0.0343	-0.1302	
		0.01	0.01	0.01	
		0.002739	0.000963	0.0004332	
MMS4_FR937	2018_291/03:41:12 to 2018_291/03:41:42	-0.2328	-0.0588	0.1422	
		0.01	0.01	0.01	
		0.01654	-0.005311	0.0005227