All,

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

Results from the Inertial Maneuver:

Q1          -0.05167100        ActNor.EstInrToBdy[0]

Q2          0.55766000          ActNor.EstInrToBdy[1]

Q3          0.72798700          ActNor.EstInrToBdy[2]

Q4          0.39544900          ActNor.EstInrToBdy[3]

GPS sec                1306591485         ActNor.EstTime

UTC time             06/01/2021 14:04:31        output

MPS Cmd Vector X          0.357707000

MPS Cmd Vector Y          0.860733000

MPS Cmd Vector Z          0.362194000

MPS Diff              0.885     deg

*MPS Diff should be < 1.5*        

CSS Angle TLM  0.383084             

CSS Sun-Pointing Angle 0.766168             

                                28 May 21 @ 19:00:00

CSS Angle TLM  0.209357             

CSS Sun-Pointing Angle 0.418714             

                                01 June 21 @ 14:00:00

Pre-Burn                            

Thruster 1           1952       28 May 21 @ 19:00:00

Thruster 2           1920      

Thruster 3           2096      

Thruster 4           2128      

Post-Burn                           

Thruster 1           2224       01 June 21 @ 14:00:00

Thruster 2           2192      

Thruster 3           2368      

Thruster 4           2400      

Number of Pulses                           

Thruster 1           272        

Thruster 2           272        

Thruster 3           272        

Thruster 4           272        

Thruster Pairs                   

Thruster 1 & 2    544        

Thruster 3 & 4    544        

Sheral Wesley  | Sr Principal Engineer, Satellite Systems

Northrop Grumman Corporation  |  Space Systems

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