MISSION PLAN - PDS Small Bodies Node

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(EGA-60d to +30d) TCM 4 (EGA-60 d) TCM 5 (EGA-10 d) TCM 6 (EGA+30 d) 649 698 739 - - - 2000 50 1500 40 S 30 1000 20 S,T (1E3 km) 500 0 -500 -1000 To Sun Earth Centered RS plane = Earth Ecliptic R = Radial direction (Sun to Earth) S = Circumferential (Orthogonal to R along Earth velocity vector) T = Out-of-Plane component EGA-72 to +72 hrs T S T S,T (1E3 km) 10 0 -10 -20 -30 -40 To Sun C/A Earth Shadow T time tics 1 hr S time tics 30 min -1500 -1500 -1000 -500 0 500 1000 1500 2000 R (1E3 km) -50 -50 -40 -30 -20 -10 0 10 20 30 40 50 R (1E3 km) Figure 5.1-1 Earth Gravity Assist Phase Spacecraft Trajectory 5.2 Mission Operations Mission operations during the EGA phase is summarized in Table 5.2-1. Support requirements for the special activities of the EGA phase will be developed post-launch, if required. However, they are expected to fit within the allocated resources. As before, ground activities are increased during the TCM periods to process radiometric data and generate the TCM commands. The delivery accuracy for the -10 day TCM is expected to be 10 km (1-σ). Two other TCM’s are performed during this phase at closest approach - 60 days and +30 days. Table 5.2-1 Earth Gravity Assist Phase Mission Operations Mission Operation Description Communications EGA - 8 hrs /day, within ±14 days All MGA, except LGA: L+708-728 TCMs - Two - 4 hr passes week, -14 to -28, +14 to +28d 4 hrs / day, within ± 14 days Navigation L+649 (EGA-60 d): TCM 4 L+739 (EGA+30 d): TCM 6 L+699 (EGA-10 d): TCM 5 Spacecraft Attitude Time Description angz (°) angy (°) db (°) 66
(see section 10 for L+649 to 668 d constant off-sun 0 0 15 attitude mode L+668 to 704 d constant off-sun 0 180 15 definitions) L+704 to 708 d constant off-sun -17 180 15 L+708 to 709 d constant off-sun -45 0 15 L+709 to 728 d constant off-sun -45 180 15 L+728 to 739 d constant off-sun 20 0 15 MGA communications: 7° off +z-axis to Earth 6 DSN Profile All 34-m L+649 to +663d: 4 h/d L+663 to +685d: 2*4 h/w L+685 to +695d: 4 h/d L+695 to +723d: 8 h/d L+723 to +739d: 4 h/d 1. DSN Coverage should alternate between Northern Hemisphere and Southern Hemisphere DSN sites. 2. A*B = A number of tracks at B frequency 67
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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
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Change Log Change Letter Date Affec
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1.0 Introduction 1.1 Purpose The pu
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2.0 Mission Overview 2.1 Mission Ob
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Fairing STARDUST Second Stage Star3
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propulsive maneuvers. To avoid pote
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The STARDUST camera is necessary to
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of-view is smaller, as described in
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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 68 and 69: Special ‘coming-off-theperiscope
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 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
Page 118 and 119: 180.00 SUN-PROBE-MOON ANGLE EGA Pha
Page 120 and 121: 180.00 SUN- WILD-2 -PROBE ANGLE Enc
Page 122 and 123: Cone & Clock Angles of Wild-2 Cone
Page 124 and 125: 180 Cone & Clock Angles of Sun 180
Page 126 and 127: 9.4 Wild-2 Encounter Data Set (cont
Page 128 and 129: 16.00 MOON-PROBE RANGE Return Phase
Page 130 and 131: 10.0 Appendix B: Unbalanced Attitud
Page 132 and 133: 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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