FR754

Looking at the Restart states from Rev 755 we have the following results for FR754.
FR754		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 23 2017 02:23:11.373	83909.995	83886.041	83886.663	-23.954	-23.332	-0.62224	2.598%	-2.46%	
MMS2	May 23 2017 02:22:57.943	83882.811	83886.525	83886.478	3.714	3.666	0.04764	1.283%	-2.41%	
MMS3	May 23 2017 02:22:31.893	83886.601	83886.551	83886.557	-0.051	-0.045	-0.00622			
MMS4	May 23 2017 02:22:22.923	83856.175	83886.960	83886.496	30.785	30.321	0.46377	1.507%	-1.36%	
 
MMS1 was 1.17 m/s (net delta-v) and 38.15% axial, MMS2 was 0.84 m/s and 57.55% axial, and MMS4 was 1.58 m/s and 34.56% 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_FR754	2017_139/15:57:07 to 2017_139/15:59:37	0.3716	0.1158	0.7403	
		0.003716	0.002	0.007403	
		-0.0007894	0.001464	0.001376	
MMS1_FR754	2017_139/19:37:37 to 2017_139/19:39:37	-0.6221	0.5663	0.8167	
		0.006221	0.005663	0.008167	
		0.0003069	-0.001779	0.00004313	
MMS4_FR754	2017_139/21:27:17 to 2017_139/21:29:37	0.2418	-1.5582	0.0814	
		0.002418	0.015582	0.002	
		-0.00002072	-0.002304	0.0001087