MISSION PLAN - PDS Small Bodies Node

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Special ‘coming-off-theperiscope’ calibration 10 16 1 (nav) - same as previous - 3.4 Mission Operations STARDUST mission operations during the launch phase is comprised mainly of the checkout and activation of spacecraft subsystems, as well as the first orbit determination of the spacecraft trajectory in preparation for TCM-1. Initial tracking of the launch vehicle through spacecraft separation will be handled by various ground tracking stations operated by the Air Force as well as by Advanced Range Instrumentation Aircraft (ARIA). A NASA requirement calls for tracking of all powered launch vehicle flight activities, so ARIA tracking is required through out the injection burns. Within 30 minutes of separation, Boeing will supply JPL with an injection state based on tracking and telemetered data from the launch vehicle during the launch sequence. After separation, tracking will be taken over by the Deep Space Network’s 34M HEF net. Table 3.4-1 summarizes the general mission operations requirements and activities. Table 3.4-1 Launch Phase Mission Operations Mission Operation Description Communications L+0 to 16 d: 24 hr/d, antenna: LGA L+16 to 30 d: 8 hr/d, antenna: LGA Navigation L+15 d: TCM 1 Spacecraft Attitude Time Description angz (°) angy (°) db (°) L+0 to 30 d constant off-sun -45 180 15 DSN Profile All 34-m L+0 to +16 d: 24 h/d L+16 to +30 d: 2*4 h/d 1. See section 10 for attitude mode definitions. 2. DSN Coverage should alternate between Northern Hemisphere and Southern Hemisphere DSN sites. 3. A*B = A number of tracks at B frequency 50
4.0 Cruise Phases 4.1 Overview The STARDUST mission has nearly six years of relatively low activity cruise. The cruise phases are subdivided into Cruise 1 (Earth-Earth), Cruise 2 (Earth-Wild-2), and Cruise 3 (Wild-2-Earth). Within these phase are embedded the following subphases: ISP collection, Deep Space Maneuvers (DSM), and Trajectory Correction Maneuvers (TCM). Other activities that occur during the cruise phases but do not have specific subphases associated with them are the CIDA and DFMI experiments. The spacecraft trajectory for this phase is the same as shown in Figure 2.3-1. Cruise phases and subphases are defined in Table 4.1-1. The Cruise phase data set is considered the same as the Mission data set and can be found in Section 9.1. Table 4.1-1 Cruise Phase Subphase Definition Cruise Phase Sub-Phases Time (L+days) Cruise 1 (Earth-Earth) 30 - 649 DSM-1 (TCM 2) 398 - 402 ISP Collection 403 - 469 TCM 3 (DSM-1 + 30 d) 432 Cruise 2 (Earth-Wild-2) Cruise 3 (Wild-2-Earth) ISP Collection DSM-2 (TCM 7) DSM-3 (TCM 8) TCM 9 (DSM-3 + 7 d) TCM 16 (3rd aphelion) 739 - 1691 1267 - 1402 1130 1609 - 1611 1618 1841 - 2445 2063 Duration (days) 619 5 66 - 952 135 1 3 - 604 - 4.2 Interstellar Dust Science Interstellar dust collection is concentrated in the part of the trajectory where the Interstellar dust impact velocity is relatively low (inbound trajectory legs). Collection is performed only during the first two loops resulting in 201 days of total collection time. Collection is not performed on the third loop to avoid contamination of the cometary samples collected during the encounter with Wild-2. CIDA and DFMI operations are nearly continuous, essentially whenever there is sufficient power to turn the instruments on. However, prime CIDA periods can be defined as those during which the interstellar dust stream is made to fall within the field-of-view of the CIDA instrument, while not violating power availability or conflicting with other important mission activities. With passive experiments and without the need for stringent attitude control (the uncertainty in the radiant direction of the interstellar dust could be as large as 30°), these 51
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STARDUST MISSION PLAN February 1, 1
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STARDUST MISSION PLAN Edward A. Hir
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Table of Contents Table of Contents
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10.1.1 Spacecraft Attitude History
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Figure 6.2-1.a Wild-2 Encounter Com
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Table 10.1-3 Spacecraft Attitude Pr
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kg km L L/O Kilogram Kilometer Laun
Page 17 and 18: Change Log Change Letter Date Affec
Page 19 and 20: 1.0 Introduction 1.1 Purpose The pu
Page 21 and 22: 2.0 Mission Overview 2.1 Mission Ob
Page 23 and 24: Fairing STARDUST Second Stage Star3
Page 25 and 26: propulsive maneuvers. To avoid pote
Page 27 and 28: The STARDUST camera is necessary to
Page 29 and 30: of-view is smaller, as described in
Page 31 and 32: Backshell Avionics Deck Parachute C
Page 33 and 34: Earth Gravity Assist 01/15/01 Earth
Page 35 and 36: Cruise 2 (Earth-Wild-2) ISP Collect
Page 37 and 38: 2.3.2 Launch Period Strategy 2.3.2.
Page 39 and 40: Table 2.3-2 Baseline Mission Parame
Page 41 and 42: Table 2.3-2 Baseline Mission Parame
Page 43 and 44: *B plane angle (deg) -41.051 -40.96
Page 45 and 46: 2.3.2.2 ∆V Budget The total ∆V
Page 47 and 48: Accumulation of Radiation with Time
Page 49: Table 2.3-4 STARDUST Alternate-2 Mi
Page 52 and 53: calculations will require more deta
Page 54 and 55: 10 17 10 16 10 15 10 14 10 13 Fluen
Page 56 and 57: 8 10 flare, no shielding 6 10 4 10
Page 58 and 59: The orbit of comet Wild-2 was drast
Page 60 and 61: • Dust density = Nucleus density
Page 62 and 63: 2.4.4 Interstellar Dust Science Pla
Page 64 and 65: Launch Initial Acquisition TCM-1 Ac
Page 66 and 67: Stage II ignition t=277.5 s h=66.4
Page 70 and 71: phases are very similar to the stan
Page 72 and 73: presented in tables contained in Ap
Page 74 and 75: Figure 4.2-4.b. Beta Meteoriod Impa
Page 76 and 77: 180 Off-SEP & ORBIT normal angle (d
Page 78 and 79: 2/6 launch Events Attitude 74 days
Page 80 and 81: yaw, while continuing to meet solar
Page 82 and 83: Time Image Description images pixel
Page 84 and 85: (EGA-60d to +30d) TCM 4 (EGA-60 d)
Page 86 and 87: 6.0 Wild-2 Encounter Phase (E-100 t
Page 88 and 89: the installation of the HGA. The su
Page 90 and 91: Date Sept-03 Oct-03 Nov-03 Dec-03 J
Page 92 and 93: Coma images will be acquired primar
Page 94 and 95: mirror via a simple one dimension t
Page 96 and 97: The cross track error corresponds t
Page 98 and 99: 14 12 10 24 km 3 sigma distance 1 s
Page 100 and 101: All 34-m HEF except selective 70-m
Page 102 and 103: SRC Entry / Descent Atmospheric Ent
Page 104 and 105: Two TCM’s are planned within this
Page 106 and 107: It is important to note that, other
Page 108 and 109: 8.0 Planetary Protection The object
Page 110 and 111: Earth-Probe Range Sun-Earth-Probe A
Page 112 and 113: 9.1 Mission Data Set (cont) 14.00 E
Page 114 and 115: 14.00 MOON-PROBE RANGE Launch Phase
Page 116 and 117: 180.00 SUN-EARTH-PROBE ANGLE EGA Ph
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180.00 SUN-PROBE-MOON ANGLE EGA Pha
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180.00 SUN- WILD-2 -PROBE ANGLE Enc
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Cone & Clock Angles of Wild-2 Cone
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180 Cone & Clock Angles of Sun 180
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9.4 Wild-2 Encounter Data Set (cont
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16.00 MOON-PROBE RANGE Return Phase
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10.0 Appendix B: Unbalanced Attitud
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spacecraft attitude when the spacec
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Time From Launch Off-sun Angle (deg
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Acceleration (1E-11 km/s/s) 12 10 8
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+z, yaw +y, pitch +x, roll Figure 1
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** vectors evaluated at the time of
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Rgt Ascen (deg) [eme'2000] 360 300
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Table 10.2-6 Communications Schedul
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Table 10.2-6 Communications Schedul
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031228 19180 0 031229 19180 0 03123
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TRAJECTORY CORRECTION MANEUVERS EVE
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2453509.10737773 50518. 143437. 229
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50204. 3437. 2189.12 outb SEP = 3 d
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Table 12-1 ISP #1 Collection Period
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Table 12-2 ISP #2 Collection Period
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Table 12-4 ISP #2 Spacecraft Attitu
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Table 12-5 CIDA #1 Collection Perio
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Table 12-6 CIDA #2 Collection Perio
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908.000 41.659 20.000 9.272 175.100
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Table 12-8 CIDA #1 Spacecraft Attit
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Table 12-9 CIDA #2 Spacecraft Attit
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Table 12-11 CIDA #3 Solar Conjuncti
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13.0 Appendix E: PRD Traceability M
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