All,

    The apogee contact was nominal. The inertial maneuver was successful.

The current star percent valid is at 77%.

Q1          0.28607200       ActNor.EstInrToBdy[0]

Q2          -0.72959600      ActNor.EstInrToBdy[1]

Q3          0.11823400       ActNor.EstInrToBdy[2]

Q4          0.60981400       ActNor.EstInrToBdy[3]

GPS sec 1382819770      ActNor.EstTime

UTC time              10/31/2023 20:35:56    

J2000    Spin Axis

ECI X      -0.822189

ECI Y      -0.521428

ECI Z      -0.228295

Precession Maneuver                    

MPS Diff               0.545    deg

*MPS Diff should be < 1.5*        

Right Ascension - RA       212.383               deg

Declination - DEC              -13.197 deg

IBEX Spin Axis vs. Sun Vector                      

IBEX Sun Angle  -3.482  deg

CSS Angle TLM   1.64746              

CSS Sun-Pointing Angle  3.29492              

                                26 Oct 23@11:15:00

CSS Angle TLM   1.82553              

CSS Sun-Pointing Angle  3.65106              

                                31 Oct 23@20:00:00

Pre-Burn                            

Thruster 1           13632   26 Oct 23@11:15:00

Thruster 2           13216  

Thruster 3           17760  

Thruster 4           18176  

Post-Burn                           

Thruster 1           13760   31 Oct 23@20:00:00

Thruster 2           13344  

Thruster 3           17920  

Thruster 4           18336  

Number of Pulses                            

Thruster 1           128       

Thruster 2           128       

Thruster 3           160       

Thruster 4           160       

Thruster Pairs                   

Thruster 1 & 2   256       

Thruster 3 & 4   320       

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