All,
The perigee contacts were nominal for command and tlm. The inertial maneuver was successful.
The SSR was dumped via APL.
The following objectives were accomplished:
1.
CAR# 1174 Upload Orbit# 531 ATS
IBEX_2021_166_o0531a_v001.scr (758 – 845)
2.
DumpBackorbit (from start,0,0,0,0)pre-maneuver
3.
Reset_master_timer
4.
Set_Downlink (40k)
5.
DumpBackorbit (from start,0,0,0,0) post maneuver
Results from the Inertial Maneuver:
Q1 -0.19378000 ActNor.EstInrToBdy[0]
Q2 -0.52086800 ActNor.EstInrToBdy[1]
Q3 -0.83083200 ActNor.EstInrToBdy[2]
Q4 0.02937150 ActNor.EstInrToBdy[3]
GPS sec 1307061133 ActNor.EstTime
UTC time 06/07/2021 00:31:59 output
MPS Cmd Vector X 0.283804000
MPS Cmd Vector Y 0.883311000
MPS Cmd Vector Z 0.373117000
MPS Diff 0.777 deg
*MPS Diff should be < 1.5*
CSS Angle TLM 0.209357
CSS Sun-Pointing Angle 0.418714
01 June 21 @ 14:00:00
CSS Angle TLM 0.362077
CSS Sun-Pointing Angle 0.724154
07 June 21 @ 00:30:00
Pre-Burn
Thruster 1 2224 01 June 21 @ 14:00:00
Thruster 2 2192
Thruster 3 2368
Thruster 4 2400
Post-Burn
Thruster 1 2512 07 June 21 @ 00:30:00
Thruster 2 2480
Thruster 3 2672
Thruster 4 2704
Number of Pulses
Thruster 1 288
Thruster 2 288
Thruster 3 304
Thruster 4 304
Thruster Pairs
Thruster 1 & 2 576
Thruster 3 & 4 608
Sheral Wesley |
Sr Principal Engineer, Satellite Systems
Northrop Grumman Corporation | Space Systems
O: 703-406-5641 | C: 202-236-0802 |
sheral.wesley@ngc.com