MISSION PLAN - PDS Small Bodies Node
MISSION PLAN - PDS Small Bodies Node
MISSION PLAN - PDS Small Bodies Node
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Special ‘coming-off-theperiscope’<br />
calibration<br />
10 16 1<br />
(nav)<br />
- same as previous -<br />
3.4 Mission Operations<br />
STARDUST mission operations during the launch phase is comprised mainly of the<br />
checkout and activation of spacecraft subsystems, as well as the first orbit determination<br />
of the spacecraft trajectory in preparation for TCM-1.<br />
Initial tracking of the launch vehicle through spacecraft separation will be handled by<br />
various ground tracking stations operated by the Air Force as well as by Advanced Range<br />
Instrumentation Aircraft (ARIA). A NASA requirement calls for tracking of all powered<br />
launch vehicle flight activities, so ARIA tracking is required through out the injection<br />
burns. Within 30 minutes of separation, Boeing will supply JPL with an injection state<br />
based on tracking and telemetered data from the launch vehicle during the launch<br />
sequence. After separation, tracking will be taken over by the Deep Space Network’s<br />
34M HEF net. Table 3.4-1 summarizes the general mission operations requirements and<br />
activities.<br />
Table 3.4-1 Launch Phase Mission Operations<br />
Mission Operation Description<br />
Communications L+0 to 16 d: 24 hr/d, antenna: LGA<br />
L+16 to 30 d: 8 hr/d, antenna: LGA<br />
Navigation L+15 d: TCM 1<br />
Spacecraft Attitude Time Description angz (°) angy (°) db (°)<br />
L+0 to 30 d constant off-sun -45 180 15<br />
DSN Profile<br />
All 34-m<br />
L+0 to +16 d: 24 h/d<br />
L+16 to +30 d: 2*4 h/d<br />
1. See section 10 for attitude mode definitions.<br />
2. DSN Coverage should alternate between Northern Hemisphere and Southern Hemisphere DSN sites.<br />
3. A*B = A number of tracks at B frequency<br />
50