Hello team,
The apogee contact was nominal, and the inertial maneuver was successful.
Results from the inertial maneuver:
Q1 -0.06813790
Q2 -0.57560500
Q3 -0.59274000
Q4 0.55919200
GPS sec 1406340155
UTC time 07/30/2024 02:02:21
MPS Diff 0.698
MPS Cmd Vector X -0.56968600
MPS Cmd Vector Y 0.75786900
MPS Cmd Vector Z 0.31795000
CSS Angle TLM 0.714911
CSS Sun-Pointing Angle 1.429822
25 Jul 24 @22:00:000
CSS Angle TLM 0.190774
CSS Sun-Pointing Angle 0.381548
30 Jul 24 @02:00:00
Pre-Burn
Thruster 1 2736 25 Jul 24 @22:00:000
Thruster 2 2672
Thruster 3 2848
Thruster 4 2912
Post-Burn
Thruster 1 3008 30 Jul 24 @02:00:00
Thruster 2 2944
Thruster 3 3120
Thruster 4 3184
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
Best,
Andrea Coca Gonzales | Associate
Engineer Satellite Systems | MEV | ICESat-2 | TESS | IBEX
Northrop Grumman Corporation | Space Systems