MISSION PLAN - PDS Small Bodies Node

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Capture of cometary and interstellar dust particles is performed using the Aerogel Dust Collector. The aerogel collector allows collection from both sides. Figure 2.2-3.a shows the aerogel collector fully deployed from the SRC canister. In the figure, the visible side of the collector is used for cometary dust collection while the hidden side is used for interstellar dust collection. The total collection area per side is required to be greater than 1000 cm 2 . Stowing of the collector is achieved by first folding the collector grid onto the boom via the wrist joint and then folding the boom/collector into the SRC canister via the shoulder joint as shown in Figure 2.2-3.b Interstellar collection Aerogel collector Cometary collection wrist joint shoulder joint a. deployed b. stowed Figure 2.2-3 Aerogel Collector This deployment mechanism is the key in maximizing the amount of time available for the capture of interstellar dust particles. The mechanism allows the collector to be steered via the wrist joint about the spacecraft y-axis toward the -z-axis. The collector field-of-view remains unobstructed by the SRC backshield for 51° of this motion, half the grid is in shadow at 63°, and all of the grid is in shadow at 75°. This deployment geometry is illustrated in Figure 2.2-3.c. Note that for the shadow definition, the ISP stream is assumed to be incoming perpendicular to the aerogel grid. It is worth noting that the collector field-of-view would remain completely unobstructed for 65° of the motion should the shoulder joint be used during interstellar dust particle collection. However, usage of the shoulder joint with the collector fully deployed is considered to be an unnecessary risk. A description of the ISP collection strategy is provided in Section 4.2.1 Interstellar Particle Collection Subphases. 2.2.2.3 Imaging Camera 8
The STARDUST camera is necessary to perform the optical navigation (OPNAV) that is required to achieve a flyby accurate enough to assure adequate comet dust collection. This camera also provides the capability to obtain high-resolution images of the comet coma and comet nucleus during the close encounter. The imaging camera is Milstar/CASSINI-inherited with the following characteristics: CCD: 1024 x 1024 pixels, 12 bits/pixel Focal ratio: f/3.5 Pixel Size: 12 µmeters Shutter speeds: 5ms - 10s, 5ms steps FOV: 3.5° Readout time: ~3 sec Pixel FOV: 60 µradians Number of Filters: 8 Focal length: 200 mm Spectral range: 380 - 1100 nm start shadow half shadow fully shadowed no shadow grid fully deployed 75.1° 62.6° 50.9° 75.1° - 75° 62.6° - 63° 50.9° - 51° +z +x SRC backshell Figure 2.2-3.c Aerogel Grid Deployment Geometry The camera, shown in Figure 2.2-4, is equipped with a one-axis movable mirror which allows for image smear compensation during cometary encounter. In addition, a periscope is introduced into the optical path while imaging through the dust shields to protect the camera optics in the cometary dust environment. 9
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: propulsive maneuvers. To avoid pote
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 76 and 77:
180 Off-SEP & ORBIT normal angle (d
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2/6 launch Events Attitude 74 days
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yaw, while continuing to meet solar
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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
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the installation of the HGA. The su
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Date Sept-03 Oct-03 Nov-03 Dec-03 J
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Coma images will be acquired primar
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mirror via a simple one dimension t
Page 96 and 97:
The cross track error corresponds t
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14 12 10 24 km 3 sigma distance 1 s
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All 34-m HEF except selective 70-m
Page 102 and 103:
SRC Entry / Descent Atmospheric Ent
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Two TCM’s are planned within this
Page 106 and 107:
It is important to note that, other
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8.0 Planetary Protection The object
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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
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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
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
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
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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
Page 158 and 159:
Table 12-2 ISP #2 Collection Period
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Table 12-4 ISP #2 Spacecraft Attitu
Page 162 and 163:
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
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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