MISSION PLAN - PDS Small Bodies Node

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The Sample Return Capsule is mounted along the -x-axis of the spacecraft. It is a key component that allows successful return of the cometary samples to Earth. Shown in Figure 2.2-6, there are four main components to the SRC: the avionics, the aeroshell (backshell and heat shield), the sample collector, and the parachute system. The avionics design includes a UHF locator beacon that will be used as an SRC location aid for the ground recovery team. The beacon is activated upon main chute deployment. It is powered by a set of primary cell lithium sulfur dioxide batteries. Lithium sulfur dioxide was selected because of its long shelf life, tolerance to wide temperature variations, and handling safety. These batteries have enough capacity to operate the beacon for 40 hours. Additional SRC tracking is provided by skin tracking from two C- band radar sites at the Utah Test and Training Range (UTTR) landing site. A mylar target mounted on the main chute provides an equivalent one square meter of radar cross section. The aeroshell is used to remove over 99 percent of the initial kinetic energy of the vehicle and protect the sample canister against the extreme aerodynamic heating of atmospheric entry. The heat shield is a 60° half angle blunt cone made of a graphite/epoxy composite covered with a thermal protection system. Ablative material is also applied to the backshell to protect the capsule from the effects of recirculation flow. During the entry and descent phases, a G-switch initiated timer with backup pressure sensors provides the required parachute deployment timing. The parachute system incorporates a drogue and main chute into a single parachute canister. The parachute canister contains a mortar tube that holds the drogue chute. A gas cartridge is housed outside the canister and is used to pressurize the mortar tube and expel the drogue chute. The drogue chute is used to stabilize the descending SRC through the transonic and subsonic atmospheric regimes. The drogue is discarded using one of two redundant cutters, extracting the main chute as it moves away from the SRC. Upon ground impact, a cutter in the riser of the main chute is commanded by a G-switch, separating the main chute from the SRC to prevent surface winds from dragging the SRC across the ground. 12
Backshell Avionics Deck Parachute Canister Aerogel Grid Sample Canister Heatshield 81 cm Diameter Figure 2.2-6 Sample Return Capsule 2.3 Mission Summary 2.3.1 Description Trajectory: The STARDUST mission is designed for a low velocity (6.1 km/s) flyby of comet Wild-2 during its active period (at a solar distance of 1.9 AU) and to have a low energy Earth returning trajectory. Figure 2.3-1 shows the Wild-2 orbit and the spacecraft trajectory for the first launch date. Deterministic Maneuvers: The first orbital loop is a two year loop with a 168 m/s deterministic ∆V near aphelion. This deep space maneuver, DSM 1, sets up the orbit for an Earth swingby that will pump the orbit up to a 2.5 year loop. The spacecraft stays on this loop twice and encounters the comet, Wild-2, approximately 163 days after the second perihelion of the mission, 98.5 days after the comet’s perihelion. A small,
Page 1 and 2: STARDUST MISSION PLAN February 1, 1
Page 4 and 5: STARDUST MISSION PLAN Edward A. Hir
Page 7 and 8: Table of Contents Table of Contents
Page 9 and 10: 10.1.1 Spacecraft Attitude History
Page 11 and 12: 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: of-view is smaller, as described in
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 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
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(EGA-60d to +30d) TCM 4 (EGA-60 d)
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6.0 Wild-2 Encounter Phase (E-100 t
Page 88 and 89:
the installation of the HGA. The su
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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
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
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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
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Table 10.2-6 Communications Schedul
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031228 19180 0 031229 19180 0 03123
Page 150 and 151:
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
Page 156 and 157:
Table 12-1 ISP #1 Collection Period
Page 158 and 159:
Table 12-2 ISP #2 Collection Period
Page 160 and 161:
Table 12-4 ISP #2 Spacecraft Attitu
Page 162 and 163:
Table 12-5 CIDA #1 Collection Perio
Page 164 and 165:
Table 12-6 CIDA #2 Collection Perio
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908.000 41.659 20.000 9.272 175.100
Page 168 and 169:
Table 12-8 CIDA #1 Spacecraft Attit
Page 170 and 171:
Table 12-9 CIDA #2 Spacecraft Attit
Page 172 and 173:
Table 12-11 CIDA #3 Solar Conjuncti
Page 174 and 175:
13.0 Appendix E: PRD Traceability M
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MISSION PLAN - PDS Small Bodies Node

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