MISSION PLAN - PDS Small Bodies Node

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presented in tables contained in Appendix D. The spacecraft attitude consistent with the ISP plan are also listed in Appendix D. The attitude characteristics of these phases of the mission are summarized with respect to attitude reference planes defined in Table 4.2- 1.b. Table 4.2-1.b Reference Plane Definitions Item SPE Reference Plane Orbital Reference Plane Definition +z axis // r = unit vector from spacecraft to sun +y axis // n = unit vector of cross product of vector to sun and vector to Earth, corrected such that ecliptic-z component is positive +x axis // t = completes the triad +z axis // r = unit vector from spacecraft to sun +y axis // n = unit vector of cross product of heliocentric position and velocity vectors, i.e. orbit angular momentum vector +x axis // t = completes the triad 15 10 Impact Velocity Impact Velocity (km/s) 5 0 350 375 400 425 450 475 500 525 550 15 10 5 0 1250 1275 1300 1325 1350 1375 1400 1425 1450 Time (days from Launch) Figure 4.2-2 ISP Impact Velocity History ( β=1 particle) Off-sun & Off-Earth angles (deg) 45 30 15 +z-off-sun +z-off-earth 0 350 375 400 425 450 475 500 525 550 45 30 15 0 1250 1275 1300 1325 1350 1375 1400 1425 1450 Time (days from Launch) 54
Figure 4.2-3.a. Spacecraft +z-axis Off-sun and Off-Earth Angle History Off-SEP & ORBIT normal angle (deg) 180 150 120 +y-off-SEP-normal +y-off-ORBIT-normal 90 350 375 400 425 450 475 500 525 550 180 150 120 90 1250 1275 1300 1325 1350 1375 1400 1425 1450 Time (days from Launch) Figure 4.2-3.b. Spacecraft +y-axis Yaw Angle History Collector Depolyment Angle (deg) 180 150 120 Collector Angle Grid exposure 90 350 375 400 425 450 475 500 525 550 180 1.0 0.8 150 0.6 120 0.4 0.2 90 0.0 1250 1275 1300 1325 1350 1375 1400 1425 1450 Time (days from Launch) Figure 4.2-4.a. Collector Deployment Angle and Grid Exposure History 1.0 0.8 0.6 0.4 0.2 0.0 Fraction of Grid BETA-collector normal angle (deg) 90 60 BETA-coll-N angle 30 0 350 375 400 425 450 475 500 525 550 90 60 30 0 1250 1275 1300 1325 1350 1375 1400 1425 1450 Time (days from Launch) 55
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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
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 68 and 69: Special ‘coming-off-theperiscope
Page 70 and 71: phases are very similar to the stan
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
Page 118 and 119: 180.00 SUN-PROBE-MOON ANGLE EGA Pha
Page 120 and 121: 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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