All,

 

The apogee contact was nominal for CMD and TLM. The Inertial Maneuver was successful.

 

Results from the Inertial Maneuver:

Q1 -0.31261800 ActNor.EstInrToBdy[0]

Q2 0.58067800  ActNor.EstInrToBdy[1]

Q3 -0.14056000 ActNor.EstInrToBdy[2]

Q4 0.73846200  ActNor.EstInrToBdy[3]

GPS sec 1239026552.000 ActNor.EstTime

MPS Diff 0.626 deg

MPS Cmd Vector X           0.945101000

MPS Cmd Vector Y           0.303730000

MPS Cmd Vector Z            0.120553000

CSS Angle TLM   1.53468

CSS Sun-Pointing Angle   3.06936

                              6 Apr 19 @22:30

CSS Angle TLM   0.437455            

CSS Sun-Pointing Angle   0.87491

                              11 Apr 19 @ 14:00

Pre-Burn                          

Thruster 1            8832      6 Apr 19 @22:30

Thruster 2            8608     

Thruster 3            10880   

Thruster 4            11104   

Post-Burn                         

Thruster 1            9088      11 Apr 19 @ 14:00

Thruster 2            8864     

Thruster 3            11184   

Thruster 4            11408   

Number of Pulses                          

Thruster 1            256       

Thruster 2            256       

Thruster 3            304       

Thruster 4            304       

Thruster Pairs                  

Thruster 1 & 2    512       

Thruster 3 & 4    608       

 

 

 

Eric Chubin
Mission Operations Engineer - OCO2, IBEX
Northrop Grumman Innovation Systems

OCO2 MOC#: (703) 429 - 7015

Mobile#: (240) 328 - 2098

Eric.Chubin@ngc.com

 
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