FR695

Looking at the Restart states from Rev 696 we have the following results for FR695.
FR695		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	Feb 03 2017 04:57:06.540	42098.403	42107.061	42107.066	8.65747	8.66310	-0.00563	-0.07%	0.15%	
MMS2	Feb 03 2017 04:56:38.959	42107.107	42107.085	42107.086	-0.02228	-0.02042	-0.00187			
MMS3	Feb 03 2017 04:56:25.988	42112.776	42107.090	42107.092	-5.68577	-5.68445	-0.00132	0.02%	0.08%	
MMS4	Feb 03 2017 04:57:01.085	42098.401	42107.056	42107.070	8.65551	8.66912	-0.01361	-0.16%	-0.07%	
 
MMS1 was 2.77 m/s and 32.4% axial, MMS3 was 2.11 m/s and 76.8% axial, MMS4 was 2.64 m/s 52.9% 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 p lanning 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_FR695	2017_33/01:41:07 to 2017_33/01:44:37	-0.0793	-1.8287	-2.0769	
		0.002	0.018287	0.020769	
		-0.0001235	-0.0003947	-0.0001345	
MMS4_FR695	2017_33/03:13:57 to 2017_33/03:19:37	1.5301	-0.1727	-2.1459	
		0.015301	0.002	0.021459	
		0.00006101	0.0002332	0.0001399	
MMS3_FR695	2017_33/04:48:27 to 2017_33/04:54:37	-0.1319	1.4044	-1.4598	
		0.002	0.014044	0.014598	
		0.00005971	0.0002381	0.0001972