The apogee tracking contact was nominal and the sun maneuver successful.

Results from the Sun  Maneuver:

Q1          -0.06173700        ActNor.EstInrToBdy[0]

Q2          -0.78924800        ActNor.EstInrToBdy[1]

Q3          0.40991700          ActNor.EstInrToBdy[2]

Q4          0.45303900          ActNor.EstInrToBdy[3]

GPS sec 1351654110         ActNor.EstTime

UTC time             11/05/2022 03:28:16       output

CSS Angle TLM   0.218503             

CSS Sun-Pointing Angle 0.437006             

                                28 Oct 22 @18:32:00

CSS Angle TLM   1.96394                

CSS Sun-Pointing Angle 3.92788                

                                05 Nov 22@03:30:00

Pre-Burn

Thruster 1            8064       28 Oct 22 @18:32:00

Thruster 2            7824      

Thruster 3            10224   

Thruster 4            10464   

Post-Burn

Thruster 1            8400       05 Nov 22@03:30:00

Thruster 2            8160      

Thruster 3            10864   

Thruster 4            11104   

Number of Pulses

Thruster 1            336        

Thruster 2            336        

Thruster 3            640        

Thruster 4            640        

Thruster Pairs   

Thruster 1 & 2    672        

Thruster 3 & 4    1280      

Sheral Wesley  | Sr Principal Engineer, Satellite Systems

Northrop Grumman Corporation  |  Space Systems

O: 703-406-5641  |  C: 202-236-0802  |  sheral.wesley@ngc.com