Hello team,
The apogee contact was nominal, and the inertial maneuver was successful.
Results from the inertial maneuver:
Q1 -0.49566500
Q2 0.27290700
Q3 0.69007200
Q4 0.45126400
GPS sec 1405562553
UTC time 07/21/2024 02:02:19
MPS Diff 0.699
MPS Cmd Vector X -0.43976100
MPS Cmd Vector Y 0.82783600
MPS Cmd Vector Z 0.34827800
CSS Angle TLM 0.190774
CSS Sun-Pointing Angle 0.381548
16 Jul 24 @22:40:00
CSS Angle TLM 0.322641
CSS Sun-Pointing Angle 0.645282
21 Jul 24 @02:00:00
Pre-Burn
Thruster 1 2176 16 Jul 24 @22:40:00
Thruster 2 2144
Thruster 3 2256
Thruster 4 2288
Post-Burn
Thruster 1 2432 21 Jul 24 @02:00:00
Thruster 2 2400
Thruster 3 2560
Thruster 4 2592
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
Kind regards,
Andrea Coca Gonzales | Associate
Engineer Satellite Systems | MEV | ICESat-2 | TESS | IBEX
Northrop Grumman Corporation | Space Systems