FR816

Looking at the Restart states from Rev 816 we have the following results for FR816.
FR816		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 12 2017 23:17:03.276	84218.763	84226.765	84226.819	8.002	8.056	-0.05447	-0.681%	
MMS2	Nov 12 2017 23:16:55.384	84217.107	84226.776	84226.843	9.669	9.737	-0.06775	-0.701%	
MMS3	Nov 12 2017 23:17:02.735	84217.334	84226.747	84226.802	9.413	9.468	-0.05430	-0.577%	
MMS4	Nov 12 2017 23:17:12.515	84226.853	84226.851	84226.859	-0.002	0.006	-0.00806		
 
MMS1 was 0.26 m/s (net delta-v) and 8.06% axial, MMS2 was 0.46 m/s and 22.57% axial, and MMS3 was 0.34 m/s and 34.08% 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)	
MMS1_FR816	2017_313/13:39:17 to 2017_313/13:39:37	0.1287	-0.2116	-0.0778	
		0.002	0.002116	0.002	
		-0.000298	-0.00141	-0.0005823	
MMS3_FR816	2017_313/15:29:07 to 2017_313/15:29:37	0.147	-0.3046	0.0168	
		0.002	0.003046	0.0002	
		-0.0004815	-0.002029	-0.0006508	
MMS2_FR816	2017_313/17:18:57 to 2017_313/17:19:37	0.1522	-0.4253	-0.074	
		0.002	0.004253	0.002	
		-0.0002722	-0.002003	-0.0004144