GS1605

Looking at the Restart states from Rev 1607 we have the following results for GS1605.
GS1605		NoBurn	Plan	OD	Plan-NoBurn	OD-NoBurn	Plan-OD	SMA error	
MMS	Epoch of Plan Apogee	A(km)	A (km)	A (km)	A (km)	A (km)	A (km)		
MMS1	Feb 25 2025 16:25:39	97610.099	97586.104	97586.096	-23.995	-24.002	0.00788	-0.033%	
MMS2	Feb 25 2025 16:28:56	97584.827	97584.827	97584.851	0.000	0.024	-0.02368		
MMS3	Feb 25 2025 16:27:45	97588.717	97584.924	97584.932	-3.793	-3.785	-0.00794	0.209%	
MMS4	Feb 25 2025 18:44:59	97591.488	97591.488	97591.512	0.000	0.024	-0.02401		
 
MMS1 was 1.173 m/s and 44.50% axial, MMS3 was 0.179 m/s and 39.57%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 except MMS3 DVX and DVZ
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_GS1605	2025_48/23:44:07 to 2025_48/23:46:37
	-0.4838	-0.4987	-0.9463	
		0.004838	0.004987	0.009463	
		0.003924	0.001729	0.003889	
MMS3_GS1605	2025_49/01:36:17 to 2025_49/01:36:37
	-0.0741	-0.0763	-0.1448	
		0.002	0.002	0.002	
		0.002476	0.000211	-0.004218