All,
The Apogee support was nominal for Cmd and TLM. The Inertial maneuver was successful.
Tim
J2000
Spin Axis
ECI X
-0.581401
ECI Y
0.746530
ECI Z
0.323521
Q1 -0.49560700 ActNor.EstInrToBdy[0]
Q2 -0.30432400 ActNor.EstInrToBdy[1]
Q3 0.09011300 ActNor.EstInrToBdy[2]
Q4 0.80848000 ActNor.EstInrToBdy[3]
GPS sec
1217070082.000 ActNor.EstTime
MPS Diff
0.645 deg
MPS Cmd Vector X -0.585219000
MPS Cmd Vector Y 0.747996000
MPS Cmd Vector Z 0.313081000
CSS Angle TLM 0.5028
CSS Sun-Pointing Angle 1.0056
27 July 18 @0630
CSS Angle TLM 0.310274
CSS Sun-Pointing Angle 0.620548
31 July 18 @1100
Pre-Burn
Thruster 1 2560 27 July 18 @0630
Thruster 2 2496
Thruster 3 2880
Thruster 4 2944
Post-Burn
Thruster 1 2720 31 July 18 @1100
Thruster 2 2656
Thruster 3 3040
Thruster 4 3104
Number of Pulses
Thruster 1 160
Thruster 2 160
Thruster 3 160
Thruster 4 160
Thruster Pairs
Thruster 1 & 2 320
Thruster 3 & 4 320
Timothy E. Perry
CRS, IBEX, OCO-2 & TESS
Mission Operations
Tim.perry@ngc.com
Office (703) 406-5976
Cell (301) 606-1430
Corp Cell (571) 447-8977
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