MISSION PLAN - PDS Small Bodies Node

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Launch Initial Acquisition TCM-1 Activation and Checkout 0 - 30 0 - 1 15 1 - 30 30 1 - 29 3.2 Initial Acquisition Subphase The initial acquisition subphase includes all activities from launch vehicle liftoff to completion of Deep Space Network (DSN) acquisition. Although one complete day is allocated for this activity, selection of the short coast launch option allows these activities to be completed within three hours of launch. Prior to liftoff (L/O), the spacecraft is powered on via launch vehicle umbilical power at L/O-240 minutes. The spacecraft is transferred to internal battery power at L/O-4 minutes. At this time the spacecraft is electrically configured for initial cruise mode with the exception that solar panels are not deployed and the solid-state power amplifier (SSPA) is off. The activities from liftoff to spacecraft separation are summarized in Table 3.2-1 and illustrated in Figure 3.2-1. It should be noted that the numbers presented are specific to a February 6 launch date, but are typical of other launch dates. However, the specific numbers are provided for illustrative purposes only and are subject to change as mission plans mature. Table 3.2-1 Injection Activities Event L/O+(sec) (min) Comments PRE-LAUNCH 1 Spacecraft power ON -86400.0 -1440.0 Latch Valves Closed & System Wet; EPS, C&DH, Rcvr, & DST powered 2 Switch to internal power –240.0 -4.0 On batteries 3 Liftoff 0.0 0.0 PRE-SEPARATION 4 Power on Prop Heaters 241.0 4.0 1 lb thrusters, valve, line, tank 5 Main engine cutoff (MECO) 264.0 4.4 6 Stage II ignition 277.7 4.6 7 9.5 ft fairing separation 284.0 4.8 8 First Stage II cutoff (SECO 1) 597.3 10.0 9 Enter Solar Eclipse 902.0 15.0 02/06/99 launch 10 Restart Stage II 1309.8 21.8 11 SECO 2 1414.0 23.6 12 Stage II separation 1467.0 24.5 13 Power on IMU 1485.0 24.8 sep - 2 min, earliest across LP 14 Stage III ignition 1504.0 25.1 15 Stage III burnout 1569.3 26.2 16 Spacecraft separation 1639.0 27.3 Assumes 69.7 seconds coast 17 Open Latch Valves 1640.0 27.3 sep + 1 sec 18 Deploy LV Stage III Yo 1642.0 27.4 DESPIN 46
19 Start S/C despin 1643.0 27.4 delayed to gain sep distance 20 Complete despin 1764.0 29.4 rates < 0.2 deg/s 21 Power on Star Camera 1764.0 29.4 22 Begin attitude acquisition 1764.0 29.4 23 Primary string to 1 lb thrusters 1883.0 31.4 24 Disarm thrusters 1884.0 31.4 No torques during SA deploy Table 3.2-1 Injection Activities (cont.) Event L/O+ (sec) (min) Comments SOLAR ARRAY DEPLOY 25 Start Solar Array Deploy 1885.0 31.4 26 End Solar Eclipse 2231.0 37.2 02/06/99 launch 27 Complete Solar Array Deploy 2785.0 46.4 15 min alloc,
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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
Page 13 and 14: Table 10.1-3 Spacecraft Attitude Pr
Page 15 and 16: kg km L L/O Kilogram Kilometer Laun
Page 17 and 18: Change Log Change Letter Date Affec
Page 19 and 20: 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 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 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
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14.00 MOON-PROBE RANGE Launch Phase
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180.00 SUN-EARTH-PROBE ANGLE EGA Ph
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180.00 SUN-PROBE-MOON ANGLE EGA Pha
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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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MISSION PLAN - PDS Small Bodies Node

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