ll, 

The perigee contacts for Orbit # 562 were nominal for command/telemetry and the inertial maneuver successful. 

The following objectives were accomplished: 

  1. Reset_master_timer 
  2. CAR# 1235 Dump Orbit# 561 remaining Blks 
  3. CAR# 1237 Upload Orbit# 564 ATS 

IBEX_2022_102_o0564a_v001.scr (93 cmds)

  1. Dump Back Orbit (from start,0,0,0,0)

  2. SetDownlink 320k
  3. Results from PERIGEE inertial maneuver 

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