FM462

Looking at the Restart states from Rev 463 we have the following results for FM462.
FM462		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	Jun 16 2016 07:53:23.004	42107.075	42106.118	42106.105	-0.95690	-0.96983	0.01293	-1.35%	0.75%	
MMS2	Jun 16 2016 07:53:20.750	42107.069	42109.955	42109.968	2.88676	2.89911	-0.01235	-0.43%	0.22%	
MMS3	Jun 16 2016 07:52:52.418	42107.043	42108.251	42108.273	1.20776	1.22933	-0.02157	-1.79%	2.05%	
MMS4	Jun 16 2016 07:52:56.414	42107.043	42107.043	42107.043	0.00000	-0.00011	0.00011			

MMS3 maneuver was only ~ 8 cm/sec and so had a larger % error.  MMS1 was highly axial, while MMS2 was more radial.
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_FM462	2016_167/12:01:11 to 2016_167/12:01:31	0.2254	0.0379	0.1432	
		0.01	0.01	0.01	
		0.00025	-0.0015	-0.0005	
MMS3_FM462	2016_167/13:36:11 to 2016_167/13:36:11	0.0703	0.0351	0.0404	
		0.01	0.01	0.01	
		0.0005	-0.0012	-0.0003	
MMS1_FM462	2016_167/15:11:11 to 2016_167/15:11:31	-0.0762	0.0445	-0.1265	
		0.01	0.01	0.01	
		0.001	-0.0012	-0.00025