FR1610

Looking at the Restart states from Rev 1610 we have the following results for FR1611
FR1610		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	Mar 11 2025 17:56:51	97421.938	97635.108	97627.025	213.170	205.086	8.083	3.792%	-7.792%	
MMS2	Mar 11 2025 17:56:57	97718.158	97635.106	97635.247	-83.052	-82.910	-0.142	0.171%	0.941%	
MMS3	Mar 11 2025 17:56:60	97603.309	97635.108	97635.129	31.799	31.819	-0.020	-0.064%	0.106%	
MMS4	Mar 11 2025 20:12:53	97634.924	97634.898	97634.885	-0.025	-0.038	0.013	 		
 
MMS1 was 4.0099 m/s (net delta-v) and 38.46% axial, MMS2 was 1.9137 m/s and 35.27% axial, and MMS3 was 0.4321 m/s and 7.86% axial.
MMS1 stopped at approximately 96% of the maneuver due to a modefirelimit being passed on the axial thrusters.

The Table below provides the following information:
•	The start and end times and planned maneuver 
•	Total delta-V (DeltaV_X, DeltaV_Y, and DeltaV_Z) for the first maneuver extracted from the DVTABLE files, 
•	The associated predicted velocity maneuver planning requirement for 1 and 2 orbit predictions (DeltaV_X Req, DeltaV_Y Req, and DeltaV_Z Req)
•	The difference between the predicted velocity and the GEONS definitive velocity at the start time of the first maneuver (Diff_V_X, Diff_V_Y, and Diff_V_Z).Planned maneuver total delta-V values based on the associated DVTABLEs    
As shown in the table below, all meet the requirement except MMS3 DVX, MMS3 DVY, MMS3 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)	
MMS3_FR1610	2025_66/00:03:57 to 2025_66/00:04:37		0.3626	-0.2203	-0.0836	
		0.003626	0.002203	0.002	
		0.005461	-0.00303	-0.003972	
MMS1_FR1610	2025_66/02:02:27 to 2025_66/02:09:37		2.2254	-1.9166	-2.963	
		0.022254	0.019166	0.02963	
		0.002387	0.00167	0.000652	
MMS2_FR1610	2025_66/03:56:37 to 2025_66/03:59:37		-0.9894	0.9564	1.3294	
		0.009894	0.009564	0.013294	
		0.004244	-0.001805	-0.004123