GS1595

Looking at the Restart states from Rev 1597 we have the following results for GS1595.
GS1595		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	Jan 21 2025 13:15:08.916	97530.930	97559.567	97559.609	28.637	28.679	-0.04206	-0.147%	
MMS2	Jan 21 2025 13:34:06.532	97534.287	97534.287	97534.291	0.000	0.004	-0.00442		
MMS3	Jan 21 2025 13:30:31.374	97533.020	97538.174	97538.202	5.154	5.182	-0.02786	-0.541%	
MMS4	Jan 21 2025 15:49:15.107	97535.463	97535.463	97535.471	0.000	0.008	-0.00848		
 
MMS1 was 1.239 m/s and 40.61% axial, MMS3 was 0.227 m/s and 37.12%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)	
MMS1_GS1595	2025_14/10:39:17 to 2025_14/10:41:37	0.5235	0.5755	0.9603	
		0.01	0.01	0.01	
		0.00194	0.001267	0.001021	
MMS3_GS1595	2025_14/16:26:17 to 2025_14/16:26:37		0.095	0.104	0.1735	
		0.01	0.01	0.01	
		0.001391	0.00118	-0.0006112