MISSION PLAN - PDS Small Bodies Node

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180 Off-SEP & ORBIT normal angle (deg) 150 120 +y-off-SEP-normal +y-off-ORBIT-normal 90 0 25 50 75 100 125 150 175 200 180 150 120 90 750 775 800 825 850 875 900 925 950 180 150 120 90 1650 1675 1700 1725 1750 1775 1800 1825 1850 Time (days from Launch) Figure 4.2-6.b. Spacecraft +y-axis Yaw Angle History x-axis off-ISP angle (deg) 45 30 15 0 +x-off-ISP FOV exposure 0.2 0.0 0 25 50 75 100 125 150 175 200 45 1.0 0.8 30 0.6 15 0.4 0.2 0 0.0 750 775 800 825 850 875 900 925 950 45 1.0 0.8 30 0.6 15 0.4 0.2 0 0.0 1650 1675 1700 1725 1750 1775 1800 1825 1850 Time (days from Launch) Figure 4.2-7. ISP off +x-axis Angle and Field-of-View Exposure History 1.0 0.8 0.6 0.4 FOV exposure (fraction of FOV) 4.2.3 Expansion Opportunities for ISP Experiments 58
The ISP collection and CIDA experiment plans are currently defined to allow easier mission operations and pre-launch mission design. These allowances, based on rigid ground rules, result in less than optimal collection durations. If desired, these constraints may be relaxed, but doing so may add operational and mission plan complexity. ISP Collection #1 The geometrical conditions suitable for starting ISP 1 can be achieved as early as L+355 days, but DSM-1 would interfere with the collection period. A combination of spacecraft and science constraints have led to the current plan that does not start ISP 1 until after DSM 1 has been completed. The location of DSM 1 is dictated, after all trajectory design considerations, by the need to allow sufficient radiometric tracking to support the implementation of DSM 1. Radiometric tracking is affected here by a period of solar conjunction that occurs a few weeks prior to the DSM. Based on the NEAR spacecraft solar conjunction experience, DSM 1 has been placed at 14 days after the spacecraft has reached a Sun-Earth-Probe angle of 4 degrees (increasing). For the mission scenario resulting from a launch on the first day of the launch period, DSM 1 could be scheduled such that ISP 1 would start on L+395 days. However, to ease pre-launch trajectory development, DSM 1 has been scheduled to support the latest SEP=4 degree occurrence across the launch period and ISP 1 is set to start at L+403 days. The possible variation of ISP 1 as a function of launch date is illustrated in Figure 4.2-8. Notice that not only does the start of the period change, but so also does the end of the period. The end of the period is constrained by the beta meteoriod avoidance constraint. After launch, it should be possible, if required, to adjust the location of DSM 1 according to the actual launch date and flight trajectory and obtain an earlier start to ISP 1. 59
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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
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 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 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
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
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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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