FR768

Looking at the Restart states from Rev 769 we have the following results for FR768.
FR768		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	Jul 01 2017 07:30:48.707	83896.711	83901.458	83901.544	4.747	4.833	-0.08602	-1.812%	-0.073%	
MMS2	Jul 01 2017 07:30:33.392	83896.626	83896.626	83896.615	0.000	-0.011	0.01099			
MMS3	Jul 01 2017 07:30:28.152	83896.734	83898.165	83898.244	1.431	1.510	-0.07905	-5.522%	1.195%	
MMS4	Jul 01 2017 07:30:13.002	83896.637	83896.330	83896.436	-0.307	-0.201	-0.10612	34.553%	-0.378%	
 
MMS1 was 0.27 m/s (net delta-v) and 48.44% axial, MMS3 was 0.22 m/s and 13.81% axial, and MMS4 was 0.19 m/s and 54.50% axial. 
Larger SMA % errors due to small size of the maneuver.  Error in terms of meters is in line with FR753, but smaller maneuver.

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 except MMS4 DVX and MMS4 DVY
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_FR768	2017_180/08:46:12 to 2017_180/08:46:52	-0.1937	0.1251	-0.1556	
		0.01	0.01	0.01	
		-0.001466	0.003831	0.001029	
MMS3_FR768	2017_180/10:21:12 to 2017_180/10:21:32	-0.2183	-0.0224	-0.0526	
		0.01	0.01	0.01	
		-0.0022928	0.005956	0.001305	
MMS4_FR768	2017_180/15:26:12 to 2017_180/15:26:52	-0.104	0.0069	-0.2046	
		0.01	0.01	0.01	
		-0.01171	0.01553	0.001103