MISSION PLAN - PDS Small Bodies Node

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Figure 4.2-4.b. Beta Meteoriod Impact Angle 4.2.2 CIDA Experiment The Cometary and Interstellar Dust Analyzer (CIDA) is planned to be operated anytime permissible. The main restrictions on CIDA experiment periods are off-sun angle constraints and other mission phases. The CIDA instrument is body fixed and its field-ofview is pointing toward the spacecraft +x-axis. The prime CIDA periods are defined as those portions of the mission during which the interstellar dust stream can be made to fall in the instrument field-of-view (refer back to Section 2.2.2.4). Similar to the ISP collection periods, the CIDA experiment periods are built from the implementation of two different strategies for tracking the spacecraft relative ISP velocity vector. The initial tracking strategy involves pointing the spacecraft +x-axis toward the incoming ISP stream. The same deadbands (15°) and maximum ‘center-ofdeadband’ off-sun angles, 0° and 20°, as the ISP collection period analysis apply. The start of the CIDA period is determined by when the ISP stream aligns itself with the +xaxis of a sunpointed spacecraft. The spacecraft off-sun angle is increased as the +x-axis is kept aligned with the drifting spacecraft relative ISP stream. This continues until the maximum ‘center-of-deadband’ off-sun angle, 20°, is achieved. At this point, the second strategy is invoked, which involves maintaining the maximum off-sun angle and allowing the ISP stream to drift through the CIDA field-of-view. The experiment is terminated when less than a quarter of the CIDA target is exposed to the ISP stream. The out-ofplane component of the ISP stream is once again tracked via a spacecraft yaw. The geometrically defined CIDA experiment periods are reduced by other mission activities. The CIDA 1 and CIDA 2 periods currently allow for some quiet time between the end of important mission phases and the start of CIDA activity (see section 4.2.3 for more detail). The CIDA 3 period is technically scheduled during the encounter phase, but is described here for convenience. The start of CIDA 3 is determined by when the spacecraft is able to establish communications upon exit of the pre-encounter solar conjunction. Options for starting CIDA 3 during solar conjunction are discussed in section 4.2.3. The end of CIDA 3 comes when the communications frequency is increased to 1 track per day in support of the first encounter trajectory correction maneuver. The CIDA experiment plan is summarized in Table 4.2-2. The experiment geometry for the first trajectory loop is illustrated in Figure 4.2-5. An illustration of the characteristics of these experiment periods are provided in Figures 4.2-6 through 4.2-7. These same characteristics are presented in tables contained in Appendix D. The spacecraft attitude consistent with the CIDA plan are also listed in Appendix D. Table 4.2-2 Interstellar Particle Related CIDA Experiment Periods Start End Duration Equivalent Full Target 56
Period (L+days) (L+days) (days) Duration (days) 1 45 144 99 52 2 769 914 145 74 3 1703 1747 44 28 Total - - 288 154 L+45 d = to sun (~15° off +z) = to Earth (~60° off +z) i = relative isp stream L+54 d = to sun (~20° off +z) = to Earth (~53° off +z) i = relative isp stream i L+144 d = to sun (~20° off +z) = to Earth (~12° off +z) i = relative isp stream (~35° off +x) i i Figure 4.2-5 Profile of CIDA Experiment - Loop 1 60 Off-sun & Off-Earth angles (deg) 40 20 +z-off-earth +z-off-sun 0 0 25 50 75 100 125 150 175 200 60 40 20 0 750 775 800 825 850 875 900 925 950 60 40 20 0 1650 1675 1700 1725 1750 1775 1800 1825 1850 Time (days from Launch) Figure 4.2-6.a. Spacecraft +z-axis Off-sun and Off-Earth Angle History 57
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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
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 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 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
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
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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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