National Aeronautics and Space AdministrationJet Propulsion LaboratoryCalifornia Institute of TechnologyN
ASA
Exop
lane
t Sci
ence
Insti
tute
Design-a-MissionGroup Projects
July 21, 2014
2014 Sagan Summer Workshop“Imaging Planets and Disks”
National Aeronautics and Space AdministrationJet Propulsion LaboratoryCalifornia Institute of TechnologyN
ASA
Exop
lane
t Sci
ence
Insti
tute
NASA Keck MOWG - D. Gelino 2
What is this group project about?
February 26, 2013
Design your own mission to detect exoplanets
Three different mission classes: Probe, Medium-scale, Flagship
Two different high-contrast instruments: Coronagraph and Starshade
Each class and hardware setup combination has a cost cap and set of science goals
Two groups for each type of mission: see who can observe the most planets!
You will sign up for a group on the sheets provided, and start working towards your 7-10 min presentation to be given on Friday afternoon.
National Aeronautics and Space AdministrationJet Propulsion LaboratoryCalifornia Institute of TechnologyN
ASA
Exop
lane
t Sci
ence
Insti
tute
NASA Keck MOWG - D. Gelino 3
Which group should I choose?
February 26, 2013
Groups 1 & 2: Probe-scale mission with CoronagraphCost requirement: Under $1.5 BillionPrimary science goal: Maximize observations of cold JupitersSecondary science goal: Estimate potential capability of
detecting other types of planets
Groups 3 & 4: Probe-scale mission with StarshadeCost requirement: Under $1.5 BillionPrimary science goal: Maximize observations of cold JupitersSecondary science goal: Estimate potential capability of
detecting other types of planets
Groups 5 & 6: Medium-scale mission with CoronagraphCost requirement: Under $4 BillionPrimary science goal: Maximize observations of exoEarth
candidatesSecondary science goal: Estimate potential capability of
detecting other types of planets
National Aeronautics and Space AdministrationJet Propulsion LaboratoryCalifornia Institute of TechnologyN
ASA
Exop
lane
t Sci
ence
Insti
tute
NASA Keck MOWG - D. Gelino 4
Which group should I choose?
February 26, 2013
Groups 7 & 8: Medium-scale mission with StarshadeCost requirement: Under $4 BillionPrimary science goal: Maximize observations of exoEarth
candidatesSecondary science goal: Estimate potential capability of detecting
other types of planets
Groups 9 & 10: Flagship-scale mission with CoronagraphCost requirement: Under $12 BillionPrimary science goal: Maximize observations of exoEarth
candidatesSecondary science goal: Estimate potential capability of detecting
other types of planets
Groups 11 & 12: Flagship-scale mission with StarshadeCost requirement: Under $12 BillionPrimary science goal: Maximize observations of exoEarth
candidatesSecondary science goal: Estimate potential capability of detecting
other types of planets
National Aeronautics and Space AdministrationJet Propulsion LaboratoryCalifornia Institute of TechnologyN
ASA
Exop
lane
t Sci
ence
Insti
tute
NASA Keck MOWG - D. Gelino 5
What Questions Do I need to Answer?
February 26, 2013
1. What is the name of your mission and its primary goals?
a. Have fun with an acronym and logo if you like!
2. Define the telescope and instrument
a. Size
b. Coronagraph or starshade
c. Contrast
d. Inner Working Angle
e. Mission Lifetime
f. Any other modifications to default parameters
3. Estimate total mission cost
4. Present potential yield for each type of exoplanet
a. Earths, Jupiters, Neptunes, warm mini-Neptunes
5. Present yield as a function of astrophysical uncertainty
a. exozodi level
b. eta_planet
6. Present any lessons learned (e.g. yield scaling relationships)
Designing a Mission:Calculating Science Yields
Christopher Stark (NASA GSFC, NPP)
Aki Roberge (NASA GSFC)Avi Mandell (NASA GSFC)
Tyler Robinson (U of Washington)
Designing a Mission: The Role of a Yield Calculator
1. Science goals determine a certain type of observation needed for some number of planets
2. Make a tool (aka. DRM code) that calculates approximate yields as functions of gross astrophysical and mission parameters
3. Use it to figure out what those parameters need to be to satisfy #1
4. Take those parameters to the engineers
5. Iterate until satisfied
Inputs to the DRM
DRM
Exoplanet yield
9
Depends on distance to star, planet’s orbit, radius, albedo, and phase function, and the exposure time for the required SNR
“Completeness” = the chance of observing a given planet around a given star if that planet exists
Too faint
texpose
How To Calculate Planet Yield:Completeness
Calculated via a Monte Carlo simulation with synthetic planets
IWA
10
t = (Planet SNR)2 ×(Planet count rate) + 2 × (Background count rate)
(Planet count rate)2
Background count rate =
Leaked starlight + Zodiacal light + Exozodiacal light
Image: Stefan Seip
Kalas et al. 2005
Give’on et al. (2007)
How To Calculate Planet Yield:Exposure Time
How To Calculate Planet Yield:Optimizing Exposure Time to Maximize Yield
Starting the Hands-On Exercise• Start VNC Viewer. Log in
• Open a Terminal window
– Under Applications / System Tools
• Type …
> cd Mon
> cp /ssw/Mon/* .
• This will copy the yield tool and two costing spreadsheets to your /home/Mon directory
• Begin Quick Start guide examples …
Inner Working Angle
• IWA entered into yield tool in arcseconds• For coronagraphs,
• IWA = a × λ / D• OWA = b × λ / D• λ = 0.55 μm, a > 2, b < 20• You have to calculate what a, b your choices
correspond to before using the cost calculator
• For starshades, IWA can be anything. No OWA• Small IWAs will increase the starshade / telescope
separation and the retargeting times
A Few Words About Costs
• The cost tools are Open Office spreadsheets, one for coronagraphs, one for starshades• May look complicated but are not hard to use
• These are estimates of what your missions will cost
• The point of having cost caps is to put a constraint on your design choices• So you don’t all order up the premium versions of
everything
Exoplanet Exploration Program
Click to edit Master title style
Keith Warfield (JPL)
Vritika Singh (JPL)
July 21, 2014
Keith Warfield (JPL)
Vritika Singh (JPL)
July 21, 2014
Sagan Summer WorkshopMission Group Project: Cost Estimation Tools
Sagan Summer WorkshopMission Group Project: Cost Estimation Tools
Exoplanet Exploration Program
The Mission Costing Process
1. Define the telescope, coronagraph / starshade
2. Input chosen parameters on front worksheet of spreadsheet• For some parameters, have to choose from a drop-down list
of options. Choose option closest to your design value.
3. Choose orbit
4. Sheet calculates data volume, rate and downlink
5. Sheet calculates pointing requirements
6. Select spacecraft bus
7. Sheet calculates launch mass
8. Select launch vehicle
9. Estimate total mission cost
10. … then iterate
Exoplanet Exploration Program
Coronagraph/Telescope Flight System Sizing
Exoplanet Exploration Program
Design Worksheet
• Fill in all input information as an initial starting point• Orbit choice requires telecom data volume evaluation and mission duration choice• Spacecraft and Launch Vehicle are selected from lists on other worksheets
18The technical data in this document is controlled under the U.S. Export Regulations, release to foreign persons may require an export authorization.
System Parameter Option ADiameter (m) 1.0 mOn-Axis (0) or Off-Axis (1) 0Raw Contrast (log10) -8IWA (milliarcsec) (75-200) 200 masecSpectral Bands (number) 3Bandwidth per Band (%) 10%
Detector CCD (1), CMOS (2), EMCCD (3) 2Mission Duration Lifetime (years) 5 yrsOrbit LEO (1), L2 (2), Trailing Orbit (3), or GEO (4) 2Spacecraft Spacecraft Configuration Selection Spacecraft DLaunch Vehicle Launch Vehicle Selection L/V B
Payload Driven Spacecraft Pointing Requirement 0.50 asecPayload Power Requirement 281 WData Generated per Day 691 Mb/dayPayload Mass 520 kg Coronagraph Mass 220 kg Telescope Mass 300 kgLaunch Capability 3700 kgLaunch Mass 2079 kgLaunch Margin 1621 kgCost (FY14) $725 M
Coronagraph Instrument & Telescope
Overall Mass and Cost
Inputs 1
Telescope
Coronagraph Instrument
Inputs 2
Auto Outputs
Exoplanet Exploration Program
Orbit and Telecom Sheets
19The technical data in this document is controlled under the U.S. Export Regulations, release to foreign persons may require an export authorization.
• Trading telecom needs vs. station keeping requirements vs. mission duration
• All subsystems can be impacted by the decision but Telecom is the most important
• Make sure the daily coronagraph data can fits with the orbit capability
• Select a spacecraft offering the required telecom band
Telecom Capability
L2 Earth Trailing
S 20 n/a
X 3000 300/(ops year 2̂)
Ka 13000 1300/(ops year 2̂)
Max Downlink Duration 8 hrs/day 8hrs/day
S 576 n/a
X 86,400 8640/(ops year 2̂)
Ka 374,400 37400/(ops year 2̂)
Max Downlink Rate (kbps)
Max Daily Data Volume (Mb/day)
Earth Trailing L2Typical Downlink Band X/Ka X/KaTypical Downlink Antenna
HGA MGA/HGA
Ground Stations DSN DSN
Con’sLarge link distance; higher cost launch; limited extended mission
Station keeping required; higher cost launch
Pro’sNo station keeping, extremely quiescent environment
Constant geometry; extended mission option
Exoplanet Exploration Program
Spacecraft Selection Sheet
• Select a spacecraft with:– Sufficient payload mass and power capability– Adequate pointing performance (requirement set by telescope)– Correct mission design life– Correct telecom band
20The technical data in this document is controlled under the U.S. Export Regulations, release to foreign persons may require an export authorization.
Spacecraft A Spacecraft B Spacecraft C Spacecraft DSpacecraft
ESpacecraft F
Payload Power (OAV) (EOL) W (EOL) 50 125 730 650 1000 3000
Payload Mass Limit of Bus kg 70 200 380 650 1700 2400
Bus Dry mass (w/o Payload) kg 60 125 600 500 1500 2000
Science Data Storage capability Mbit 500 20,000 134,000 200,000 51,000 102,000
Pointing Control arcsec 5 5 3 0.3 0.2 0.15
Slewrate deg/min 60 390 240 120 50 5
Mission Design Life yrs 1 2 5* 5* >5* >5*
Compatible LVs (names) L/V A only All L/V's All L/V's All L/V's All L/V's All L/V's
Downlink Band S-band S-BandS-band and X-
bandS-band and X-
bandX-band and
Ka-bandX-band and
Ka-band
Propulsion type NoneBlowdown hydrazine
Blowdown hydrazine
Blowdown hydrazine
Blowdown hydrazine
Blowdown hydrazine
Cost $ FY14 $ 26 M $ 53 M $ 90 M $ 142 M $ 174 M $ 264 M
Exoplanet Exploration Program
Launch Mass and Spacecraft Power Estimation Sheet
• Worksheet used for estimating power requirement for spacecraft selection, and launch mass for launch vehicle selection
• JPL standard mass and power margins are included
21The technical data in this document is controlled under the U.S. Export Regulations, release to foreign persons may require an export authorization.
SYSTEMS WORKSHEET:
Subsys CBE+ Mode 1 Mode 2 Mode 3 Mode 4Mass Cont. Cont. Power Power Power Power(kg) % (kg) (W) (W) (W) (W)
Mass Fraction
Launch Science Science & Telecom
Safe
Chronograph 21% 220 43% 314.6 0 168 168 0
Telescope 29% 300.0 43% 429.0 0 113 113 0
Payload Total 50% 520.0 43% 743.6 0 281 281 0
Spacecraft Bus
Spacecraft 48% 500.0 30% 650.0 100 100 150 100
S/C-Side Adapter 2% 25.0 5% 26.3
Bus Total 525.0 29% 676.3
Spacecraft Total (Dry) 1045.0 36% 1419.9 100 381 431 100
Subsystem Heritage Contingency 374.9 36% 36%
System Contingency 74.5 7% 7% 0 121 121 0
Spacecraft with Contingency 1494 of total w/o addl pld 100 502 552 100
Propellant & Pressurant1 2% 40.0
Spacecraft Total (Wet) 2054
L/V-Side Adapter 25.0
Launch Mass 2079
Launch Vehicle Capability 3700
Launch Vehicle Margin 1620.7
JPL Design Principles Margin 57%
Spacecraft - Option 1
30% required
Exoplanet Exploration Program
Launch Vehicle Selection Sheet
• Select a launch vehicle with higher capacity than the launch mass and power worksheet
• Minimize launch cost
22The technical data in this document is controlled under the U.S. Export Regulations, release to foreign persons may require an export authorization.
600km LEO L2Earth
TrailingGEO
Cost($FY14)
L/V A 1000 kg N/A N/A N/A $ 90 M
L/V B 14500 kg 3700 kg 3650 kg 3700 kg $ 142 M
L/V C 13700 kg 4788 kg 4838 kg 5200 kg $ 274 M
L/V D 16300 kg 6150 kg 6100 kg 6750 kg $ 306 M
L/V E 21430 kg 9380 kg 9225 kg 12710 kg $ 422 M
L/V Max. Capacity
Exoplanet Exploration Program
Starshade Flight System Sizing
Exoplanet Exploration Program
Starshade Diameter Sensitivities
Starshade Dia. (m)
Mass (kg)
Cost ($M FY14)
30 635 $120
32 680 $125
34 725 $130
36 775 $140
38 825 $150
40 880 $165
42 935 $200
Exoplanet Exploration Program
Spacecraft Choices
• Select a spacecraft suitable for the mission– Can it support the payload?– Can it support the intended mission design life?– Does spacecraft choice put constraints on launch vehicle choice?
Spacecraft W
Spacecraft X
Spacecraft Y
Spacecraft Z
Payload Power (BOL) W (BOL) 730 650 1000 3000
Payload Mass Limit of Bus kg 675 850 1700 2400
Bus Dry mass (w/o Payload) kg 600 500 1500 2000
Slewrate deg/min 240 120 50 5
Mission Design Life yrs 2 3 5 >5
Compatible LVs (names)All L/V's
except L/V FAll L/V's
except L/V FAll L/V's
except L/V F All L/V's
Downlink BandS-band and X-
bandS-band and
X-bandX-band and
Ka-bandX-band and
Ka-band
Propulsion type Blowdown hydrazine
Blowdown hydrazine
Monoprop or biprop
Monoprop or biprop
Cost $ FY14$ 120 M $ 165 M $ 240 M $ 300 M
Exoplanet Exploration Program
Launch Vehicle Choices
• Add starshade mass and spacecraft dry mass. Then add 400 kg/year for propellant. This is the launch mass.
• Select a launch vehicle with adequate capacity for the intended destination
600km LEO
L2Earth
TrailingGEO
Cost($FY14)
L/V A 1000 kg N/A N/A N/A $ 90 M
L/V B 14500 kg 3700 kg 3650 kg 3700 kg $ 142 M
L/V C 13700 kg 4788 kg 4638 kg 5200 kg $ 274 M
L/V D 16300 kg 6150 kg 6100 kg 6750 kg $ 306 M
L/V E 21430 kg 9380 kg 9225 kg 12710 kg $ 422 M
L/V Max. Capacity
Exoplanet Exploration Program
Cost Estimation
WBS Elements Total
Project Cost ($ FY14) $803 M Basis of EstimateDevelopment Cost (Phases A - D) $505 M Sum
01.0 Project Management $17 M 5% of WBS 05 thru 10 and 12
02.0 Project Systems Engineering $17 M 5% of WBS 05 thru 10 and 12
03.0 Mission Assurance $14 M 4% of WBS 05 thru 10 and 12
04.0 Science $5 M
05.0 Payload System $130 M Sum
Starshade $130 M Starshade look up table
06.0 Flight System $142 M S/C look up table
07.0 Mission Operations Preparation $15 M JPL OTS Earth-orbiting Missions (flat cost input)
09.0 Ground Data Systems $20 M JPL OTS Earth-orbiting Missions (flat cost input)
10.0 ATLO $25 M JPL OTS Earth-orbiting Missions (flat cost input)
11.0 Education and Public Outreach $2 M 0.5% of WBS 05 thru 10 and 12
12.0 Mission and Navigation Design $3 M Guess
Development Reserves $115 M 30% of WBS 01 thru 12 except 08
Operations Cost (Phases E - F) $156 M
Operations $125 M $25M/year
Operations Reserves $31 M 25% of operations
8.0 Launch Vehicle $142 M L/V look up table
COST SUMMARY (FY2014 $M) - Option 1
Exoplanet Exploration Program
Backup
28The technical data in this document is controlled under the U.S. Export Regulations, release to foreign persons may require an export authorization.
Exoplanet Exploration Program
Payload Sheet
• Coronagraph parameters are estimated for input requirements
• Telescope selected from a pick list– Telescope sets a spacecraft pointing requirement which limits spacecraft choices
29The technical data in this document is controlled under the U.S. Export Regulations, release to foreign persons may require an export authorization.
CoronagraphIWA
Raw Contrast
Spectral Bands
Bandwidth per Band
Detector Mass Power Data Rate Cost
milliarcsec Log 10 number (%) kg W Mbps FY14 $M
Option 1 200 1 3 1 2 220 168 0.008 78
Option 2 0 No Input 0 No Input 0 -10 #NUM! 0.000 #NUM!
Option 3 0 No Input 0 No Input 0 -10 #NUM! 0.000 #NUM!
Telescope Mass Power Data rate Cost
($ FY14)Visible
0.5m Telescope 30 25 n/a $ 16 M 0%
1.0m Telescope 300 113 n/a $ 42 M 0%
1.5m Telescope 600 185 n/a Pointing $ 142 M 0%
2.0m Telescope 960 263 n/a Pointing $ 316 M 20%
2.5m Telescope 1380 338 n/a Pointing $ 564 M 20%
3.0m Telescope 1860 413 n/a Pointing $ 885 M 20%
SPACECRAFT Pointing Requirement
Tech. Dev.
Off-Axis Cost Adjustment
(kg) (W) (kbps)(asec)Visible
1
0.5
0.3
0.21
0.17
0.15
- Cyan cells are inputs that have been transferred from the Design Worksheet to this worksheet. - Yellow cells are look-up table values. - This sheet is locked; cells cannot be modified.
Notes - Purple cells have automatic calculations to provide the necessary outputs.
Exoplanet Exploration Program
Cost Estimation Worksheet
• Cost estimate is for the total project cost• Require inputs:
– Coronagraph cost– Telescope cost– Spacecraft cost– Mission duration to set operations costs
30The technical data in this document is controlled under the U.S. Export Regulations, release to foreign persons may require an export authorization.
WBS Elements Total
Project Cost ($ FY14) $725 M Basis of EstimateDevelopment Cost (Phases A - D) $427 M Sum
01.0 Project Management $14 M JPL percentage02.0 Project Systems Engineering $14 M JPL percentage03.0 Mission Assurance $11 M JPL percentage04.0 Science $5 M05.0 Payload System $121 M Sum
Chronograph $78 MTelescope $42 M
06.0 Flight System $142 M07.0 Mission Operations Preparation $5 M JPL OTS Earth-orbiting Missions09.0 Ground Data Systems $5 M JPL OTS Earth-orbiting Missions10.0 ATLO $5 M JPL OTS Earth-orbiting Missions11.0 Education and Public Outreach $1 M NASA percentage12.0 Mission and Navigation Design $3 M GuessDevelopment Reserves $99 M 30% NASA Requirement
Operations Cost (Phases E - F) $156 MOperations $125 M $25M/year Earth Mission (Sci + Ops)Operations Reserves $31 M 25% NASA Requirement
8.0 Launch Vehicle $142 M Not included in AO
COST SUMMARY (FY2014 $M) - Option 1
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