All,

The apogee contact was nominal for command/telemetry and the inertial maneuver was successful.

Q1          -0.25316200      ActNor.EstInrToBdy[0]

Q2          -0.55943200      ActNor.EstInrToBdy[1]

Q3          -0.15866100      ActNor.EstInrToBdy[2]

Q4          0.77315700       ActNor.EstInrToBdy[3]

GPS sec 1407981524      ActNor.EstTime

UTC time              08/18/2024 01:58:30    

Precession Maneuver                    

Cmd Diff               141.269               deg

MPS Diff               0.624    deg

                MPS Diff should be < 1.5              

MPS Cmd Vector X           -0.78845000

MPS Cmd Vector Y           0.56814700

MPS Cmd Vector Z           0.23570200

CSS Angle TLM   0.20842              

CSS Sun-Pointing Angle  0.41684              

                                12 Aug 24 @12:00:00

CSS Angle TLM   0.724157           

CSS Sun-Pointing Angle  1.448314           

                                18 Aug 24 @02:00:00

Pre-Burn                            

Thruster 1           3824     12 Aug 24 @12:00:00

Thruster 2           3760    

Thruster 3           3984    

Thruster 4           4048    

Post-Burn                           

Thruster 1           4096     18 Aug 24 @02:00:00

Thruster 2           4032    

Thruster 3           4272    

Thruster 4           4336    

Number of Pulses                            

Thruster 1           272       

Thruster 2           272       

Thruster 3           288       

Thruster 4           288       

Thruster Pairs                   

Thruster 1 & 2   544       

Thruster 3 & 4   576       

Best Regards,

Sheral Wesley  | Sr Principal Engineer, Satellite Systems

Northrop Grumman Corporation  |  Space Systems

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