FR938

Looking at the Restart states from Rev 939 we have the following results for FR938
FR938		NoBurn	Plan	OD	Plan-NoBurn	OD-NoBurn	Plan-OD	SMA error	Plane change error	
MMS	Epoch of Plan Apogee	A(km)	A (km)	A (km)	A (km)	A (km)	A (km)			
MMS1	Oct 22 2018 14:35:47.127	84199.558	84199.515	84199.499	-0.043	-0.059	0.01656			
MMS2	Oct 22 2018 14:35:48.506	84200.593	84199.526	84199.451	-1.067	-1.141	0.07469	-7.002%	0.233%	
MMS3	Oct 22 2018 14:35:53.182	84207.792	84199.524	84199.445	-8.268	-8.347	0.07848	-0.949%	-0.437%	
MMS4	Oct 22 2018 14:36:03.791	84208.492	84199.520	84199.456	-8.972	-9.036	0.06399	-0.713%	0.288%	
 
MMS2 was 0.18 m/s (net delta-v) and 34.75% axial, MMS3 was 0.42 m/s and 17.41% axial, and MMS4 was 0.34 m/s and 34.16% axial.
Interestingly, the magnitude of the SMA change errors for each maneuvering MMS was quite similar.  
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 MMS2 DVx and MMS4 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)	
MMS2_FR938	2018_292/05:54:17 to 2018_292/05:54:37	-0.1077	-0.1465	0.0245	
		0.002	0.002	0.002	
		2.526e-05	6.259e-05	2.108e-05	
MMS4_FR938	2018_292/07:44:07 to 2018_292/07:44:37	-0.2394	0.2331	-0.0599	
		0.002394	0.002331	0.002	
		-9.901e-06	-0.0001399	-0.0001401	
MMS3_FR938	2018_292/09:33:57 to 2018_292/09:34:37	-0.2392	0.3357	0.0639	
		0.002392	0.003357	0.002	
		-0.0003382	-0.0001023	-0.0003217