MISSION PLAN - PDS Small Bodies Node

More documents

Recommendations

Info

Stage II ignition t=277.5 s h=66.4 nmi v=18,315 fps MECO t=264.0 s h=61.8 nmi v=18,314 fps Fairing Jettison t=284.0 s h=68.5 nmi v=18,383 fps SECO 1 t=597.3 s h=102.0 nmi v=25,568 fps SRM Burnout t=63.1 s h=10.9 nmi v=3,480 fps SRM Jettison: Set 1 Set 2 t (s)= 66.0 67.0 h (nmi)= 11.8 12.2 v (fps)= 3,520 3,538 Orbit 100.0 nmi circular 28.44 deg inclination Data shown corresponds to DTO profile for 2/06/96, but is typical for other launch dates. Liftoff - 1.36 g's SRM impact Figure 3.2-1.a Launch Vehicle Boost Profile SECO 2 t=1,414.0 s h=96.3 nmi v=29,703 fps Stage II/III separation t=1,467.0 s Stage III ignition t=1,504.0 s h=102.2 nmi v=29,666 fps Stage II restart t=1,309.8 s h=99.1 nmi v=25,581 fps Data shown corresponds to DTO profile for 2/06/96, but is typical for other launch dates. Stage III burnout t=1,569.3 s h=120.9 nmi v=39,745 fps C3=26.0 km 2 /s 2 DEC=-19.695 deg RA=234.89337 deg Spacecraft separation t=1,639.0 s h=175.5 nmi v=39,497 fps Figure 3.2-1.b Spacecraft Orbit Injection Profile 3.3 Activation and Checkout Subphase 48
After completion of the initial acquisition subphase, the spacecraft is essentially at a known attitude with communications having been established. At this point the flight team begins a characterization and calibration period of the majority of the spacecraft subsystems. In addition, attitude control maneuvers will commence to maintain the desired attitude. Communication during this period is near continuous. Key subsystem performance tests will be conducted early in the checkout phase. Table 3.3-1 provides a summary of the subsystem checkout plan. Again it is noted that specific numbers are provided for illustrative purposes only and are subject to change. Table 3.3-1 Subsystem Checkout Plan Subsystem Activity Time Risk / Impact Data Return ACS Determine if Star Camera performance can maintain 15° deadband L to L+14 d Reliance on IMU for attitude knowledge. Impacts power at Star Camera images, attitude knowledge information aphelion Telecom Verify HGA L to Less data return thru use Nominal telemetry Navigation Camera (see below) CIDA DFMI SRC performance Perform series of calibrations, includes Scan Mirror Verify CIDA is functional Verify DFMI is operational Verify SRC latches are operational L+90 d L+4 d to L+18 d of MGA. Unable to obtain calibrated optical navigation data L+5 d Unable to collect CIDA data L+18 d Unable to collect DFMI data L+90 d Minimal probability SRC fails to open at first ISP collection Nav Camera images (window & compress) CIDA data DFMI data Latch telemetry indicating open The first trajectory correction maneuver (TCM-1) is performed at L+15 days to correct injection errors. At completion of this maneuver, the spacecraft will be ready for the long cruise period that lies ahead. Within the Activation and Checkout subphase, it is desirable to verify the performance of the Navigation Camera, the Star Cameras, the pointing mirror, the periscope, the Attitude Control System (ACS) and the navigation flight software algorithms of centroiding, windowing and compression, all of which will be heavily used during encounter operations. Table 3.3-2 provides a summary of the current imaging plans for the launch phase. Table 3.3-2 Launch Phase Imaging Plan Time L+4 days L+18 days Image Description no. of images bits per pixel no. of filters Comments Moon Color 3 16 4 PIO-windowed, best efforts basis depending on launch activities Mirror pointing, alignment 20 16 1 Pattern matched, windowed & sensitivity calibration (nav) (10x10), nominal attitude, tight deadband 49
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 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 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
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
Page 132 and 133:
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
Page 146 and 147:
Table 10.2-6 Communications Schedul
Page 148 and 149:
031228 19180 0 031229 19180 0 03123
Page 150 and 151:
TRAJECTORY CORRECTION MANEUVERS EVE
Page 152 and 153:
2453509.10737773 50518. 143437. 229
Page 154 and 155:
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
Page 166 and 167:
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
show all

MISSION PLAN - PDS Small Bodies Node

Create successful ePaper yourself

Delete template?

Save as template?