FR815

Looking at the Restart states from Rev 816 we have the following results for FR815.
FR815		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	Nov 10 2017 03:40:57.926	84247.136	84239.323	84239.291	-7.813	-7.845	0.03177	-0.407%	
MMS2	Nov 10 2017 03:40:35.738	84247.229	84237.641	84237.636	-9.588	-9.593	0.00475	-0.050%	
MMS3	Nov 10 2017 03:40:51.393	84247.229	84237.908	84237.863	-9.320	-9.366	0.04592	-0.493%	
MMS4	Nov 10 2017 03:41:29.652	84247.340	84247.341	84247.391	0.000	0.051	-0.05090		
 
MMS1 was 0.41 m/s (net delta-v) and 35.56% axial, MMS2 was 0.19 m/s and 30.44% axial, and MMS3 was 0.33 m/s and 10.44% 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 except MMS2 DVX, and all MMS DVY. 
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)	
MMS1_FR815	2017_312/06:51:12 to 2017_312/06:51:52	0.3543	-0.0917	0.1738	
		0.01	0.01	0.01	
		0.008747	-0.01435	-0.001253	
MMS3_FR815	2017_312/08:26:12 to 2017_312/08:26:42	0.3158	-0.0532	-0.0527	
		0.01	0.01	0.01	
		0.008189	-0.01235	-0.00105	
MMS2_FR815	2017_312/10:01:12 to 2017_312/10:01:32	0.1589	-0.0921	0.0497	
		0.01	0.01	0.01	
		0.01592	-0.0186	-0.0005325