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STARDUSTBringing a Comet Home

Discovery 4 Mission

PI Don Brownlee@ Univ of Wash

ManagingAgency

IndustrialPartner

Lockheed Martin Space SystemsCivil Space

Space Exploration Systems

Joe VellingaProject Management Challenge 2007

February 6, 2007

PM Challenge 2007

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STARDUST

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Wild-2 Encounter

01/02/04 Vinf=6.1 km/s Rsun=1.9 AU

REarth=2.6 AU

Earth Orbit

1

2

A

B

3

Interstellar Particle Stream

Interstellar Particle Collection A-B: Feb-May 00, Aug-Dec 02

Comet Wild-2 Orbit

Loop 1

Loops 2 & 3

X Ecliptic J2000

Launch 02/07/99*

Earth Gravity Assist 01/15/01

Earth Return 01/15/06

Heliocentric Loops 1, 2 and 3 Feb 99-Jan 01, -Jul 03, -Jan 06

Deep Space Maneuvers 1: Jan 2000, 2: Jan 2002 3: Jun 2003, 4: Feb 2004

4

* second day of launch period

Annefrank 11/02/02

Vinf=7.2 km/s Rsun=2.3 AU

REarth=2.3 AU

Trajectory Overview

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Wild 2 Encounter

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Spacecraft Overview - at EncounterLaunch Mass: 385 kg (848 lb)-Bus: 254 kg (560 lb)-SRC: 46 kg (101 lb)-Fuel: 85 kg (187 lb)

Thrusters

Dust Flux MonitorInstrument

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Cometary Dust Collection

Navigation Camera Mirror

AerogelCollection

Grid

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Interstellar Particle Collection

AerogelCollection

Grid

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Aerogel Sample Collector

Part

icle

Car

rot T

rack

1 cm Interstellar Grid

3 cm Comet Grid

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Stardust Structure

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Whipple Shield

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1 cm

2 cm

5 cm

11 cm

Whipple Shield Does Its Job

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Dust Flux Monitor

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DFM on Whipple Shield BumperMass Simulator

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Cometary & Interstellar Dust Analyzer (CIDA)

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Navigation Camera (Nav Cam)

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Stardust Assembled

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On Delta II (7426)

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Launch, 7 February 1999

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Fairing Separation

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AnneFrank Encounter 2 Nov 2002

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NucleusTracking

Control

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Mirror Angle

NavCam CCD

Default TrajectoryLocked On

Navigation put it inField of View

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81P/Wild 2

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Orbital Evolution of Wild 2

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Wild 2 Trail

M. Ishiguro, et al, The Astrophysical Journal, 589:L101–L104, 2003 June 1, DISCOVERY OF THE DUST TRAIL OF THE STARDUST COMET SAMPLE RETURN MISSION TARGET: 81P/WILD 2

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Wild-2 Flyby Geometry

V = 6.12 km/s Approach Phase Angle 73 deg

• 230 km Flyby on Sunside

nucleus radius ~ 2.7 km coma radius ~100,000 km

Sun 1.86 AU

Earth 2.60 AU

SPE angle 17 deg

S/C Attitude +x // Vinf +y = ToEarth X Vinf +z = +x X +y +z is “rolled” 1.9 deg above the flyby plane for Earth point

XS

YS

Flyby plane coordinates (xs,ys,zs) defined by Vinf and Sun Vector

Wild-2 Encounter Geometry closest approach: 01/02/2004 19:22:59.1 UTC

Earth is 16.7 degrees from XS and 1.9 degrees above the flyby plane Vinf points 2.8 degrees below the eclipitic Wild-2 heliocentric speed is 26.4 km, s/c is 21.7 km/s

73 deg

Wild 2 V=26.4 km/sec

SD V=21.7 km/sec

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Wild 2 17 November 2003

• Windowed frame • Wild 2 in a 15 sec exposure

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Optical Navigation Image @ E - 14 Hours

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Image 2022

Distance=6793 km

Time=E-1113 sec

Mirror=1.9 deg

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Image 2034

Distance=4599 km

Time=E-753 sec

Mirror=2.7 deg

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Image 2041

Distance=3321 km

Time=E-543 sec

Mirror=3.8 deg

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Image 2044

Distance=2773 km

Time=E-453 sec

Mirror=4.3 deg

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Image 2046

Distance=2409 km

Time=E-393 sec

Mirror=5.7 deg

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Image 2048

Distance=2045 km

Time=E-333 sec

Mirror=6.6 deg

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Image 2050

Distance=1742 km

Time=E-283 sec

Mirror=7.9 deg

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Image 2052

Distance=1320 km

Time=E-213 sec

Mirror=10.2 deg

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Image 2053

Distance=1260 km

Time=E-203 sec

Mirror=10.8 deg

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Image 2054

Distance=1201 km

Time=E-193 sec

Mirror=11 deg

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Image 2056

Distance=1082 km

Time=E-173 sec

Mirror=12.6 deg

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Image 2058

Distance=963 km

Time=E-153 sec

Mirror=14.2 deg

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Image 2059

Distance=903 km

Time=E-143 sec

Mirror=15 deg

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Image 2060

Distance=845 km

Time=E-133 sec

Mirror=16 deg

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Image 2061

Distance=787 km

Time=E-123 sec

Mirror=17.5 deg

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Image 2062

Distance=729 km

Time=E-113 sec

Mirror=19 deg

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Image 2063

Distance=671 km

Time=E-103 sec

Mirror=20 deg

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Image 2064

Distance=915 km

Time=E-93 sec

Mirror=23 deg

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Image 2065

Distance=559 km

Time=E-83 sec

Mirror=25 deg

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Image 2066

Distance=504 km

Time=E-73 sec

Mirror=28 deg

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Image 2067

Distance=452 km

Time=E-63 sec

Mirror=32 deg

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Image 2069

Distance=352 km

Time=E-43 sec

Mirror=42 deg

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Image 2071

Distance=274 km

Time=E-23 sec

Mirror=59 deg

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Image 2073

Distance=236 km

Time=E-3 sec

Mirror=85 deg

Closest Approach Image

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Image 2075

Distance=257 km

Time=E+17 sec

Mirror=113 deg

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Image 2077

Distance=326 km

Time=E+37 sec

Mirror=133 deg

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Image 2079

Distance=421 km

Time=E+57 sec

Mirror=145 deg

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Image 2080

Distance=472 km

Time=E+67 sec

Mirror=150 deg

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Image 2081

Distance=526 km

Time=E+77 sec

Mirror=153 deg

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Image 2083

Distance=637 km

Time=E+97 sec

Mirror=158 deg

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Image 2084

Distance=694 km

Time=E+107 sec

Mirror=160 deg

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Image 2085

Distance=752 km

Time=E+117 sec

Mirror=161 deg

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Image 2086

Distance=810 km

Time=E+127 sec

Mirror=163 deg

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Image 2087

Distance=869 km

Time=E+137 sec

Mirror=164 deg

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Image 2088

Distance=927 km

Time=E+147 sec

Mirror=165 deg

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Image 2091

Distance=1105 km

Time=E+177 sec

Mirror=167.6 deg

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Image 2092

Distance=1165 km

Time=E+187 sec

Mirror=168.4 deg

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Image 2094

Distance=1285 km

Time=E+207 sec

Mirror=169.4 deg

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Image 2096

Distance=1405 km

Time=E+227 sec

Mirror=170.3 deg

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Image 2098

Distance=1525 km

Time=E+247 sec

Mirror=171.1 deg

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Image 2100

Distance=1646 km

Time=E+267 sec

Mirror=171.8 deg

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Image 2104

Distance=1888 km

Time=E+307 sec

Mirror=172.9 deg

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Image 2108

Distance=2130 km

Time=E+347 sec

Mirror=173.7 deg

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Image 2112

Distance=2373 km

Time=E+387 sec

Mirror=174.3 deg

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Image 2115

Distance=3467 km

Time=E+567 sec

Mirror=176.1 deg

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First Image Released• Many Flat Bottomed

Craters• Jets May be Coming

From Walls of ‘Sublimation Craters’

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Flight Pointing Errors from Enc_Abs Attitude

-0.25

0.00

0.25

0.50

0.75

1.00

1.25

1.50

1.75

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2.25

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4.25

-30.00 -20.00 -10.00 0.00 10.00 20.00 30.00

Time from Closest Approach (minutes)

Rot

atio

n ab

out e

ach

Axi

s(de

gree

s)

X Rotat.Y Rotat.Z Rotat.

Encounter Attitude Control

Roll Maneuver

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Location of Center of Brightness in CCD Frame

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Nucleus Tracking

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Closest Approach Determination

185.0

235.0

285.0

335.0

385.0

435.0

485.0

535.0

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635.0

685.0

757538632 757538652 757538672 757538692 757538712 757538732 757538752 757538772 757538792 757538812 757538832

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Closest ApproachDistance=237 km (9 km closer)Time =757538732 SCLK (87 seconds early)

Closest Approach

236.4 km

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Image 2076

Distance=2874 km

Time=E+27 sec

Mirror=124 deg

Wild 2 Jets

• “Dozens” of Jets• 107 Tons of Water /

Orbit (Lyman AphaMeasurements)

• Average Recession Rate About 0.25 m / Orbit

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Jet Source Regions (Sekanina et al., 2004)

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Wild 2 surface ≠ asteroid or satellite surfaces

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Wild 2 Map

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Pit-Spall Craters

• The pit/spall zone morphology is common for microcraterson lunar rocks (strength dominated)

• It is unknown on larger bodies (Escape vel. Wild2 ~1 m/s)

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Wild 2’s Spires(Monument Valley in dirty ice)

spirespire shadow

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White Spot

A dust jet above the surface?Transient condensates?

3 views from different angles Blow-up

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Particle FluxesFluxes (1 sec)

0.1

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100

1000

10000

-300 0 300 600 900T (sec)

Cts

PVDF-S1Acoustic 1Acoustic 2Acoustic 3

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The Importance of Sample Return Missions

• Science is done on the ground

• Instrumentation is state-of-the-art and future SOA

• Ultimate in precision & sensitivity

• Not limited by mass, power, cost or reliability

• Results can be confirmed by independent methods

• Instruments can be calibrated before and after

• Analysis strategies can be iterative

• Samples are a resource for long into the future

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Or this . . .

Try to Launch This . . .

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Approach Events

* Red or dashed = contingency or single failure anomaly

SRC ENTRY: 15 JAN 2006 09:57 UTC (02:57 MST)

125 KM

UtahTest &TrainingRange

Earth Entry Decision Mechanisms:1. SRC Release Enable (ground command)2. SRC Release Fault Protection (spacecraft

flight software) 3. SRC Release Disable (ground command)

E-10d05 Jan E-6d

09 Jan

E-29h13 Jan

TCM-19[Fixed Attitude]

TCM18,18a

S/C ~inRelease Attitude

EnableUplink (1) FP Disable (2) or

Release Disable (3)

E-5.7h-4h

-3.7h

S/C in Release Attitude

Bus Divert orBackup Orbit (4 yrs)

PACIFIC OCEAN

T19 Release/Divert

Deep Space Network (70-m/34-m)Near-continuous from E-30dDual complex/antennas for critical eventsSix antenna redundant for Release

SRC ReleaseE-12h14 Jan

TCM-19a,b[19a - Fixed Attitude]

[19b - Full Sky]

T19a,b

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SRC Entry (E=0h, 02:57 MST, 09:57 UTC)V = 12.8 km/s, FPA = -8.2°

ALT

ITU

DE

[ * =

sla

nt ra

nge

]

DOWNRANGE

TCM-19,x (E-36,12h)

SRC Separation (E-4h)[Maui: ~105,000km*, ~57° elev]

125 km Atmosphere

To MAAF

Entry, Descent and LandingSTRATCOM SSN

Earliest: ~E-8:00, [~205,000 km*]Nominal: ~E-4:00, [~105,000 km*]End: ~E-0:00, [~3,800 km*]

1

2

3

45

6

789

EDL Events Entry+min Alt (~km MSL)1. UTTR I/R & CINE Tracking +0.6 762. Peak Heating +0.9 613. Peak G-loads +1.0 534. 3-G Timer Start +1.9 365. Drogue Deploy/UTTR Skin Tracking +2.2 326. Enter UTTR Airspace +3.9 177. Main Chute/UHF Deploy +8.0 38. Arm Main Chute Cutter +8.3 39. Landing +14.6 1.2

Recovery Operations• Helos vectored via HILL AFB MCC: 2 Vertigo + UTTR On-Scene Commander• Ground vehicles available if weather does not permit flight• Recovery crew bags SRC and returns to clean room at MAAF for GN2 purge• Depart for JSC in 2 days, dedicated cargo plane• Challenges: Night time, ground fog/inversion, water/mud/snow, cold

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Utah Test and Training RangeLanding Target

40° 19’ N, 113° 27’ W

Baseline Delivery Ellipse76 x 44 km, 99%

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Cross Track Down to 20 km by 1/11/06

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Navigation Criteria DiagramYELLOW DIVOT[debris casualty]

DUGWAY PROPERTY[property hazards]

WARNING TRACK[prediction confidence]

EFPA to 99%[-8.05 to -8.35 deg]

APPROVED LANDING ZONE to 95%

DUGWAY POPULATION[intact src casualty]

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Helicopter for Recovery

IR Camera

Night Sun

UHF Antenna

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SRC Recovery Operations EnvironmentFull Moon Rise: 5:47 pm (MST) Jan 14 SRC Entry: 2:57 amSRC Lands: 3:12 amSun Rise: 7:55 amMoon Set: 9:05 amSun Set: 5:31 pm

• Average Minimum Temperature: 18.3 Deg F• Average Maximum Temperature: 34.4 Deg F• Mean Wind: 3.92 MPH (3.4 Knots)

UTTR Feb 4, 1998UTTR Jan 13, 2005

Recovery Team Prepared, Equipped

and Trained For Worst Case Recovery

Environment

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Incoming Over Nevada – from Aircraft

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Incoming Over Nevada

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SRC After Victory Roll

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Off the Helo on Way to Clean Room

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Starting Disassembly

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Delivery to Johnson Space Center

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First Inspection of Aerogel Grid

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Particle Entry Track

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Two Fluffy Particle Impacts?

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Particles Along Track

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Cutting Aerogel – Harmonic Saw

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Valentine Particle

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Particle Analysis

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Olivine (Forsterite) Particle

This particle, a type of olivine called forsterite, was brought to Earth in the Stardust sample-return capsule. The grain, encased in melted aerogel, is about 2-millionths of a meter across.

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Don Brownlee at Science Workshop

Comet Particle Composition – many built like loose dirt-clods • large strong rocks• very fine powdery materialsRemarkable Range of Minerals• Some of these particles contain minerals that form only at extremely

high temperatures – similar to "refractory" materials that formed in the hottest, innermost regions of the disk of gas and dust that formed the Sun and planets, or prior stars

• Olivine (iron - primarily magnesium) and high-temperature minerals rich in calcium, aluminum and titanium

Isotope ratios show:– Some formed around prior stars– Some formed inside the orbit of Mercury during formation of our

Solar System

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Stardust Web Site

http://stardust.jpl.nasa.gov/

Stardust is a NASA Discovery Project, managed by the Jet Propulsion Laboratory. Don Brownlee of the University of Washington is the Principal Investigator. JPL provided

the Navigation Camera and performed mission design, navigation and DSNcommunications and tracking. Images and art work used in this presentation can be

found on the JPL Stardust web site above.

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What Did We Do?, Technically:PLAN

• Launch on 2/6/99

• Go to 2.7 AU on Solar Power

• Collect Interstellar Particles for > 150 days

• Encounter Wild 2 on 1/2/04– Collect > 1000 >15µ Particles– Survive up to 1 cm Rocks

• Return to Earth @ 12.8 km/sec

ACTUAL• Launch 2/7/99 (LV Delay)

– Recovered from LV Error (312 kg instead of 366 kg)

• Self Despin (1 kg Hydrazine)• Went to 2.7 AU with no Problems

– Invented S/A Switching Unit• Collected Interstellar Particles for

195 days• Dry Run Encounter at Asteroid

Annefrank 11/2/02 (at no cost ↑)• Encounter 1/2/04

– More than Enough; Many Broke up– 7 ‘Rocks’ ≥ 0.3 cm w/o Damage

• Returned @ 12.8 km/sec– Fastest Ever Man Made Object– New Heatshield Material → Orion

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What Did We Do?, Programmatically:PLAN

• Mid Feb 1999 Launch

• $164.6 M Phases A-E– 12% Reserve Ph C/D

• Return & Recovery Critical Event Readiness Reviews Planned

ACTUAL• Ready for Launch at Opening of

Window 2/6/99– Met All Commitment Dates to

Environmental Facilities and Arrival @ KSC

• < $164.6 M Through 2004– Consumed 11.2% of Reserve Ph C/D

• NASA Added Return & Recovery Risk Reviews in 2005 for $10 M– CAIB Report:

• Stardust Shift from Mission Success → Fail Safe

• All Risks Known & Communicated to NASA Management

– Genesis MIB Recommendations

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How Did We Do It On Time & In Cost?• KISS• Attitude• Requirements ≤ Capability• NO!!! Requirements Creep• Team Partnership• Virtual Co-Location• Good Enough• EVM +• Risk Management• Dedication of Team

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KISS• ’94 Proposal Kept to Focused Science Mission• Primary Science:

– Interstellar Dust Collection – Hence the name: Stardust– Cometary Particle Collection – Sample Return

• Secondary & Tertiary Science– In-Situ Particle Analysis with Mass Spectrometer

• Contributed Instrument from Germany– Dust Flux Monitor– Nucleus Images using Navigation Camera

Mission had been Offered as ≈$800M Program but NOT Sold. Now we Offered it at 1/4th the Cost

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Attitude• No Overrun!! → Termination (for Real!)

– Mark Saunders, NASA HQ Discovery Program Manager: • No Question or Doubt of Termination if EVM Projected >

Committed Cost • PI Had to Declare Team Couldn’t Do It

– NO!!! 15% NASA Overrun Allowance• Team Believed we Could and Would Do It In Cost

– Designed to Cost: Stayed Within Capability of Available Hardware

– Prepared to Make any Compromises Necessary to Do It –However, Never Needed to Compromise or Descope

– How We Would Do It was Up to Us– Manage Reserve to Stay in Committed Cost

You have to Believe You Can Do It.

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Requirements ≤ Capability• Phase B SRR was “Capability & Requirements

Review”– Culmination of Design to Cost– Each CAM Presented Cost Commitment – Learned of LV Capability Error During Dry Run (366 kg →

312 kg)• Short Schedule (28 month Phase C/D) = Buy

Components & Make Program Fit– Committed $7M of Major Subcontracts Before PDR

Design to ≤ Cost

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NO!!! Requirements Creep• Mantra: “Do Not Allow Requirements Creep Camel to

get his Nose Under the Tent”– PI, Don Brownlee, Gave Ken Atkins, Development Project

Manager, Toy Camel at Ken’s Retirement in Commemoration• Turned Down Improvement ‘Opportunities’

– Addition of Volatiles Capture Mechanism Pushed by Science Team

• Concept Study Done • Unknown Risks if Development Approved

– TPS Instrumentation• Pushed by ARC Up Through NASA HQ• Unknown Additional Risk in New Heatshield that was Already

Highest Risk in Program• One Improvement Incorporated: Variable Density

Aerogel @ No Additional Cost

When Cost is Committed, Requirements ARE FROZEN

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Team PartnershipPartners: NASA, PI, Agent (JPL), Industrial Partner (LM)• 4 Party Agreement Signed by All: Committed Science

to be Accomplished, Schedule & Cost• PI Participated in All Major Reviews & Meetings –

Maintained Cognizance Throughout• JPL Managed Project & Provided Camera, Navigation,

DSMS & Mission Ops with LM– Participated in LM Activity but Small Team Limited

Oversight/Insight• LM Developed Spacecraft & Capsule, Conducted

Mission with JPL, Lead Recovery– All Activity Open to JPL & PI– Operated with Independence but Full JPL Knowledge– Risks Mitigated by Investment of Excess Reserve

Partnership Works

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Virtual Co-Location• Replicating Servers Through Fire Walls• Telecons with Each End Pulling Briefing or other

Material Off Their Own Server• Periodic Face-to-Face Meetings

– Need to Know Partners

Lose Your Frequent Flyer Status!

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Good EnoughDuring Development I was Often Asked How do you

do FBC, What do you Leave Out of ProgramAnswer: Nothing Left Out, But Less Depth

• Bounding Analyses, Particularly EDL– As Built Analyses Not Done if Still ‘In Box’

• Good Enough– Entry Flight Path Angle Didn’t Use all of UTTR– One Spacecraft Test Lab

Find the Good Enough for Project Environment

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EVM +• Baselined Schedule & Resources in 3rd Month of Phase C/D

– Entire Program Through Launch– Microsoft Project for Schedule– Margin: ≥ 1 mo Delivery to ATLO; ATLO 2 mo in Denver; 1 mo

at KSC – All in Resource Baseline (Funded)– About 9000 Milestones in LM Schedule

• Earned Value Determined Each Month– CAMS at Subsystem Level– EVM Integrity = Definitive Milestones + Honesty in Assessing

Intermediate Status– Focused on Early Identification of Problems– Quickly Developed Workaround Plans

• Biggest Challenges:– Staffing Up– Late Deliveries to ATLO– Electronic Parts – Forced Five Openings of Spacecraft– Heatshield (TRL 4 to Flight in About 2 Years)

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EVM + (continued) Staffing Slower than Planned

STARDUST ENGRG STAFFING PLAN, BUDGET & ACTUALS-9/7/97

0

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140

OCT NOV DEC JAN FEB MAR APR MAY JUN JUL AUG SEP OCT NOV DEC1997

PDO Reqs-OpenProject Reqs-OpenPDO Reqs-FirmProject Reqs-FirmPDO - On BoardProject-On Board

CDR²² <<PDR

ENGRG BUDGET BASELINE REV-6/1/97

ACTUALS THRU 9/7/97

1996

CDR

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EVM + (continued) LMA Total Program Variances

($7.0)

($6.0)

($5.0)

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EVM + (continued)• Independent Milestone Count – Good Agreement with EVM

At Apr 26, 1998 Planned = 8723 Actuals = 8382 96.1%

0.5

0.7

0.9

1.1

OC

T

NO

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DEC JA

N

FEB

MAR

APR

MAY

JUN

JUL

AUG

SEP

CU

M

(Act

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0100200300400500600700800900

1000

OC

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FEB

MAR

APR

MAY JU

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JUL

AUG

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OC

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010002000300040005000600070008000900010000

CU

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VEN

TS

Baseline Plan Current Schedule CompletedCUM Baseline CUM Current Plan CUM Actuals

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EVM + (continued)• ATLO Schedule Margin Tracked Daily

ASSEMBLY & TEST SCHEDULE MARGIN PLAN

RED

YELLOW

GREEN

05

1015202530354045

Jan-

98

Feb-

98

Mar

-98

Apr

-98

May

-98

Jun-

98

Jul-9

8

Aug-

98

Sep-

98

Oct

-98

Nov

-98

MONTHS

DAY

S O

F M

ARG

IN

Pre-Ship 10/6/98

Post-Bus Functional 3/18/98

Delayed Move to MTF

*

ASSEMBLY & TEST SCHEDULE MARGIN PLAN

RED

YELLOW

GREEN

05

1015202530354045

Jan-

98

Feb-

98

Mar

-98

Apr

-98

May

-98

Jun-

98

Jul-9

8

Aug-

98

Sep-

98

Oct

-98

Nov

-98

MONTHS

DAY

S O

F M

ARG

IN

Pre-Ship 10/6/98

Post-Bus Functional 3/18/98

Delayed Move to MTF

ASSEMBLY & TEST SCHEDULE MARGIN PLAN

RED

YELLOW

GREEN

05

1015202530354045

Jan-

98

Feb-

98

Mar

-98

Apr

-98

May

-98

Jun-

98

Jul-9

8

Aug-

98

Sep-

98

Oct

-98

Nov

-98

MONTHS

DAY

S O

F M

ARG

IN

Pre-Ship 10/6/98

Post-Bus Functional 3/18/98

Delayed Move to MTF

*

EVM – Must Do BUT at Value Added Level

PM Challenge 2007

127

Risk Management• Identified Risks Early• TPMs to Track Technical Status & Identify RisksSpacecraft (3 mo to Launch):Mass 11.5 kg Wet Mass Margin including thermal liens;

Margin allows launch with full tank and ²V Margin;Actual Weight 0.4 kg < CBE

Power 19.2% at Aphelion (24 watts)Powered On Testing (~10 watt additional margin)Thermal Mods Liens TBD

Propellant 5.3% margin to ²V Budget (377mps)

CPU Throughput 62% Processor Utilization at Encounter

DRAM Memory

128 Mbytes - 28 FSW; 75 N-Cam; 13 CIDA; 2 DFM; 10 Downlink

EEPROM Memory 40% Margin (3 Mbytes Prom) Contains

Entire FSW Load

Software Maturity 61% ATP Dry Run and 40% ATP Complete

Sequence Testing SPT #1, #2, #3 CompleteFault Protection Testing In-Work

G

G

G

G

G

G

Y

& ΔV

ΔV

PM Challenge 2007

128

SRC (3 months to Launch)

Risk Management (continued)

Mass 45.7 kg weighed Vs 44 to 46 Rqmt(+0.2 kg Parachute Lid Mod)

Power 100% Margin; Redundant Batteries

Stability 6 DOF Simulations Verify Stability at Spin Rate, X/D & b; > 3 s Entries within Design Limits (99.86% Successful out of 3000 Cases)

Mass Properties X/D =.348 Vs. .351 RequirementSpin Rate 12 rpm with failed spring Vs. 12 - 18 rpm Rqmt b = 59 Vs. 60 kg/m2 Rqmt

Landing Footprint 61 km x 23 km (3 Sigma) Vs. 84 x 30 km UTTR Rqmt (6 DOF Sims)

Parachute Performance Mortar Deploy Tests by PioneerUTTR Balloon Drop Test (impact speed < 15fps)

PICA Performance 30% Thickness Margin Based on PICA to Structure Bondline T = 250°C

G

G

G

G

G

G

G

PM Challenge 2007

129

Risk Management (continued)Project Fever Summary (7 months to Launch)

DEC JAN FEB MAR APR JUNPROJECT Y Y Y Y Y Y Cost G G G G G G Reserves Look OK Key Agreements R R Y G G G NEPA-EA G G G G G G FONSI signed and published

FLIGHT SYSTEM Cost vs Budget G G G G G G Staffing G G Y Y G G Staff Rolling Off Schedule (To Atlo) Y Y Y Y G G Schedule (To Launch) G G G G Y Y 21 Days Pre-Ship margin remains Performance G G G G G G C&DH (PACI) - Interface Robustness being worked as backup Margins G G G G G G Interfaces Y Y Y Y Y G Plan Working to Gain Robustness -- R/R Buy of FPGA's Sample Return Capsule G G G G G G ACS Starcam Procure Y Y G G G G Delivered ACS IMU Procurement R R Y Y Y G Flight Software G G G G G G Pre-ATLO Testing-SMTS G G G G G G

SCIENCE: Aerogel & Collector R R R Y Y Y Flight Production & Gradient Density Qual. CIDA Y Y G G G G Dust Flux Monitor G G G G G G

MISSION G G G G G G NavCam Y Y Y G Y G Delivered & Installed Navigation G G G G G G Mission Design & Plan G G G G G G Operations Development G G G G G G Facility Operational @ JPL Launch Vehicle G G G Y Y G Boeing swap made in fab flow. Progress OK

Technical Schedule ResourcesTechnical Schedule Resources

G G G G G Y G G G

Mar Apr MayMar Apr May Mar Apr MayMar Apr May Mar Apr MayMar Apr May

PM Challenge 2007

130

Risk Management (continued)• Reviewed Weekly & Monthly

– Description & Status– Estimated Resource Required to Mitigate

PM Challenge 2007

131

Risk Management (Continued)• Invested Reserve > 10% To Go in Risk Mitigation

– Electronics Board & Box Test Sets– ATLO Test Units (C&DH and PCA)– Soft Sim

Work Risk Hard from Beginning to EndInvest Excess Reserve Wisely

PM Challenge 2007

132

Dedication of Team• People Like Working Science Programs• Fast Programs are Very Appealing• Almost No Attrition

– A Few Retirements• People Move from Development to Mission

Operation back to Development• Team Very Committed to Stardust

– Proving that it was Working Properly– Done on Time or Acceptable Work Around

Esprit de Corps is Worth a Lot

PM Challenge 2007

133

Here’s to Your Project Being

More Successful thanStardust