FI745

Looking at the Restart states from Rev 747 we have the following results for FI745.
FI745		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	Apr 30 2017 16:49:55.099	83855.988	83779.715	83779.927	-76.272	-76.061	-0.21176	0.278%	
MMS2	Apr 30 2017 16:46:08.242	83886.936	83852.919	83852.669	-34.017	-34.267	0.25000	-0.735%	
MMS3	Apr 30 2017 16:45:02.863	83922.971	83922.971	83923.003	0.000	0.032	-0.03186		
MMS4	Apr 30 2017 16:42:06.686	83943.605	83895.892	83895.847	-47.712	-47.758	0.04547	-0.095%	
 
MMS1 was 11.8 m/s (net delta-v) and 44.2% axial, MMS2 was 4.91 m/s and 58.64% axial, and MMS4 was 2.59 m/s and 71.6% 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)	
MMS2_FI745	2017_116/02:06:12 to 2017_116/02:20:52	3.2486	-1.0073	3.6344	
		0.032486	0.010073	0.036344	
		-0.00365	0.0081	0.00115	
MMS4_FI745	2017_116/0 4:21:12 to 2017_116/04:30:02	1.2197	-0.8973	2.1871	
		0.012197	0.01	0.021871	
		-0.006109	0.009319	0.00004758	
MMS1_FI745	2017_116/06:36:12 to 2017_116/07:01:00	9.5353	1.003	6.9701	
		0.095353	0.01003	0.069701	
		-0.003161	0.005973	0.0002404