ll,
The perigee contacts for Orbit # 562 were nominal for command/telemetry and the inertial maneuver successful.
The following objectives were accomplished:
IBEX_2022_102_o0564a_v001.scr (93 cmds)
Q1 0.30877400
ActNor.EstInrToBdy[0]
Q2 0.60535800
ActNor.EstInrToBdy[1]
Q3 0.44020200
ActNor.EstInrToBdy[2]
Q4 0.58687500
ActNor.EstInrToBdy[3]
GPS sec 1333011723
ActNor.EstTime
UTC time 04/03/2022 09:01:49
output
J2000 Spin Axis
ECI X 0.982385
ECI Y 0.170536
ECI Z 0.076400
Precession Maneuver
Cmd Diff 132.566
deg
MPS Diff 0.658
deg
*MPS Diff should be < 1.5*
Right Ascension - RA 9.848
deg
Declination - DEC 4.382
deg
IBEX Spin Axis vs. Sun Vector
IBEX Sun Angle -2.828
deg
MPS Generated Inertial Vectors
MPS Cmd Vector X 0.982755000
MPS Cmd Vector Y 0.173039000
MPS Cmd Vector Z 0.065194000
CSS Angle TLM 0.310274
CSS Sun-Pointing Angle 0.620548
29 Mar 22 @14:00:00
CSS Angle TLM 0.142653
CSS Sun-Pointing Angle 0.285306
03 Apr 22 @ 08:00:00
Pre-Burn
Thruster 1 18960
29 Mar 22 @14:00:00
Thruster 2 18400
Thruster 3 24064
Thruster 4 24624
Post-Burn
Thruster 1 19216
03 Apr 22 @ 08:00:00
Thruster 2 18656
Thruster 3 24416
Thruster 4 24976
Number of Pulses
Thruster 1 256
Thruster 2 256
Thruster 3 352
Thruster 4 352
Thruster Pairs
Thruster 1 & 2 512
Thruster 3 & 4 704
Sheral Wesley |
Sr Principal Engineer, Satellite
Systems
Northrop Grumman Corporation | Space Systems
O: 703-406-5641 | C: 202-236-0802 |
sheral.wesley@ngc.com