MISSION PLAN - PDS Small Bodies Node

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14 12 10 24 km 3 sigma distance 1 sigma 2 sigma 3 sigma 8 6 4 2 0 1000 900 800 700 600 500 400 Flyby Distance (km) 300 200 100 0 Figure 6.2-4 Roll Angle vs. Delivery Error and Flyby Distance 6.3 Mission Operations A summary of the encounter phase operations profile is given in Table 6.3-1. Mission operations, in addition to the execution of science operations, concentrates on navigating the spacecraft to a successful encounter with comet Wild-2. Both radiometric data and optical navigation (OPNAV) are initiated at E-100 days and are carried out through E-12 hours. Approach TCM’s are planned at E-30, -10 and -2 days, -18 hours, and -6 hours. The last TCM is planned to be implemented only in the event of a contingency. The round trip light time at encounter is approximately 40 minutes. This allows only about 5 hours after receipt of the last data, sent at E-12 h, to prepare and uplink the final TCM commands, if required. OPNAV images will contain the comet and background stars. To reduce their data return requirement, they will be windowed and compressed on-board resulting in the equivalent of an image 200 x 200 pixel in size at 12 bits per pixel. As encounter approaches, the OPNAV rate is increased consistent with the increase in science imaging frequency. The OPNAV plan is summarized in Table 6.3-2. The primary communications configuration during the encounter phase uses the HGA and 34-m HEF DSN stations. This configuration is changed with the use of 70-m DSN coverage at encounter and during the Post Encounter subphase to support transmission of stored data. After flyby, when the HGA link is reestablished at about E+3 min, orbit determination to pinpoint the spacecraft position and attitude during the flyby will resume. This is critical for the reconstruction of the flythrough conditions and 80
contributes to the return of potentially viable and valuable dynamic science data. Tracking time ranges from 8 hours per week over the 34-m net to a maximum of 24 hours per day over the 70-m net at encounter. The spacecraft attitude profile on approach to the comet starts with one that supports the third CIDA experiment (see section 4 for details). This attitude is abandoned at E-44 days when the communications frequency is scheduled to increase to one track per day in support of the first approach TCM (E-30 days). To minimize spacecraft slewing, the spacecraft attitude profile then becomes one where the MGA boresight tracks the Earth. This attitude continues until E-10 days when the attitude becomes one where the HGA boresight tracks the Earth. This is done to place the spacecraft in a near-Encounter attitude and to support the start of daily science and OPNAV events at E-7 days. Finally, after the E-18 h TCM, the spacecraft attitude is set for the final coma fly through. At the encounter attitude, the dust shield is oriented toward the comet-spacecraft relative velocity vector and the HGA boresight is pointed to the Earth. Attitude maintenance activity, required to maintain the HGA link as well as the dust shield protection, is expected to increase during the fly through due to disturbances caused by the comet dust. Attitude control will also include the execution of the roll maneuvers that surround the closest approach. Table 6.3-1 Wild-2 Encounter Phase Mission Operations Mission Operation Communications Description 8 hrs / wk - HGA Comm - E-100 to -7d, no s/c flip (small SEP) 8 hrs / day - HGA Comm - E-7 to E-1d 24 hrs / day - HGA Comm - E-2 to +3d, +5 to +8d, +10 to +13d 8 hrs / wk - HGA Comm - E+13 to E+50d TCMs - Two - 4 hr passes week - MGA Comm -14 to -28, +14 to +28d 4 hrs / day - MGA Comm (2) within ± 14 days Encounter - 4 hrs / day - MGA Comm within ± 30 days Navigation L+1761 d (E-30 d): TCM 10 L+1781 d (E-10 d): TCM 11 L+1789 d (E-2 d): TCM 12 L+1790 d (E-18 h): TCM 13 L+1791 d (E-6 h): TCM 14 L+1821 d (E+30 d): DSM 4 (# 15) Spacecraft Attitude Time (days) Description angz (°) angy (°) db (°) (see section 10 for L+1691 to 1703 constant off-sun 0 180 15 attitude mode L+1703 to 1747 CIDA cst. off-sun -20 0 15 definitions) L+1747 to 1780 MGA track Earth - - 15 L+1780 to 1789 HGA track Earth - - 15 L+1789 to 1792 Encounter - - 2 L+1792 to 1805 HGA track Earth - - 2 L+1805 to 1811 HGA track Earth - - 15 L+1811 to 1841 constant off-sun 0 0 15 MGA communications: 7° off +z-axis to Earth 6 HGA communications: +z-axis to Earth 2 Encounter mode 0.3 Imaging mode 0.5 DSN Profile L+1691 to +1733d: 8 h/w L+1794 to +1796d: 4 h/d 81
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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
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Earth Gravity Assist 01/15/01 Earth
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Cruise 2 (Earth-Wild-2) ISP Collect
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2.3.2 Launch Period Strategy 2.3.2.
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Table 2.3-2 Baseline Mission Parame
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Table 2.3-2 Baseline Mission Parame
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*B plane angle (deg) -41.051 -40.96
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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 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 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
Page 134 and 135: Time From Launch Off-sun Angle (deg
Page 136 and 137: Acceleration (1E-11 km/s/s) 12 10 8
Page 138 and 139: +z, yaw +y, pitch +x, roll Figure 1
Page 140 and 141: ** vectors evaluated at the time of
Page 142 and 143: Rgt Ascen (deg) [eme'2000] 360 300
Page 144 and 145: Table 10.2-6 Communications Schedul
Page 146 and 147: 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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