FI804

Looking at the Restart states from Rev 805 we have the following results for FI804.
FI804		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	Oct 10 2017 04:16:07.128	84240.432	84221.684	84221.682	-18.748	-18.750	0.00201	-0.011%	
MMS2	Oct 10 2017 04:15:21.193	84237.836	84237.836	84237.847	0.000	0.011	-0.01123		
MMS3	Oct 10 2017 04:14:36.370	84235.087	84260.674	84260.678	25.587	25.591	-0.00372	-0.015%	
MMS4	Oct 10 2017 04:13:56.835	84232.484	84269.460	84269.619	36.976	37.135	-0.15881	-0.430%	
 
MMS1 was 1.31 m/s (net delta-v) and 29.74% axial, MMS3 was 2.55 m/s and 1.43% axial, and MMS4 was 3.80 m/s and 18.49% 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_FI804	2017_281/06:56:12 to 2017_281/06:58:02	1.2072	-0.2004	0.4633	
		0.012072	0.01	0.01	
		0.004653	-0.009738	-0.004044	
MMS3_FI804	2017_281/08:31:12 to 2017_281/08:35:12	-2.5388	-0.1788	-0.1908	
		0.025388	0.01	0.01	
		0.003044	-0.004217	-0.0003776	
MMS4_FI804	2017_281/10:06:12 to 2017_281/10:11:52	-3.615	-0.4008	-1.102	
		0.03615	0.01	0.01102	
		-0.01186	-0.0003605	0.005843