FR753

Looking at the Restart states from Rev 754 we have the following results for FR753.
FR753		NoBurn	Plan	OD	Plan-NoBurn	OD-NoBurn	Plan-OD	SMA error	PC Error	
MMS	Epoch of Plan Apogee	A(km)	A (km)	A (km)	A (km)	A (km)	A (km)			
MMS1	May 20 2017 07:14:39.097	83882.421	83905.707	83905.758	23.287	23.337	-0.05060	-0.217%	0.139%	
MMS2	May 20 2017 07:13:18.867	83882.184	83878.725	83878.569	-3.459	-3.615	0.15627	-4.518%	0.258%	
MMS3	May 20 2017 07:12:42.164	83882.413	83882.413	83882.357	0.000	-0.056	0.05576			
MMS4	May 20 2017 07:10:29.342	83882.355	83852.065	83851.967	-30.290	-30.388	0.09816	-0.324%	-0.049%	
 
MMS1 was 1.31 m/s (net delta-v) and 84.23% axial, MMS2 was 1.25 m/s and 26.39% axial, and MMS4 was 1.17 m/s and 62.27% 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 in most components except for DVY and MMS4 on DVX.
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_FR753	2017_138/10:01:12 to 2017_138/10:03:02	1.1878	0.1763	-0.3679	
		0.011878	0.01	0.01	
		-0.004889	0.01323	0.001684	
MMS1_FR753	2017_138/11:36:12 to 2017_138/11:41:02	-0.0613	0.6745	0.011158	
		0.01	0.01	-1.1158	
		-0.008245	0.01136	0.001198	
MMS4_FR753	2017_138/15:06:12 to 2017_138/15:09:42	0.4618	-0.0327	-1.0778	
		0.01	0.01	0.010778	
		-0.01774	0.02246	0.002426