ISU Internship Project - Barcelona Moon Team Mission Design
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Transcript of ISU Internship Project - Barcelona Moon Team Mission Design
Mike Safyan – ISU/CTAE 1
Preliminary Mission Analysis for the Barcelona Moon Team Rover
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Mike Safyan – ISU/CTAE 2
Project Goals
Primary Goals• Define an initial set of mission requirements• Create a set of design spreadsheetsSecondary Goals• Provide some initial design recommendations
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Google Lunar X-Prize
• International competition for private teams• Safely land and operate a robot on the lunar surface• Must be 90% privately funded (10% government)• 21 teams participating (and 2 withdrawn)• $30K registration, $30M prize purse
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Barcelona Moon Team• First Spain-based team• Headed by Galactic Suite Moonrace• Want to bring together Catalan (and Spanish)
entrepreneurial, industrial and academic capabilities• Want as much of the project as possible to come
from local industry• Want to be creative and fun
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Previous Work Conducted
Boris Maitre, UPC Master’s Thesis:• Transfer trajectory – Hohmann• Landing site – Luna 17/Lunokhod 1• Mass at launch:– 0.5 to 8.5 tons (LEO)– 0.3 to 3 tons (GTO)
• Launch Vehicle – Ariane 5
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Cost Estimate
10 20 30 40 50 60 70 80 90 1000
25
50
75
100
125
150
175
200
NASA Lunar Rover Cost Estimate
Difficulty/Complexity: Very HighDifficulty/Complexity: Low
Rover Mass (kg)
Cost
in M
illio
ns (2
010€
)
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Difficulty/ Complexity
Cost/kg (NASA)
Cost/kg (GLXP)
very high 1 800 000 € 180 000 €
low 470 000 € 47 000 €
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GLXP Rules for the Rover
• Travel a minimum of 500 meters from initial landing site.
• Transmit from the surface an “Arrival Mooncast” and a “Mission Complete Mooncast”.– Contains a set of defined images, video, and data– Approximately 500Mb
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Bonus Prizes
$4M Prize PurseHeritage - imagery and video of a historical
artifact from a previous mission• Water Detection – prove the presence of water
on the surface• Range – travel 5 km• Survival – operate for at least two lunar daysDiversity – promote diversity in the field of
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GLXP Preferred Partners
• Space X – 10% off launch costs• SETI – Free use of ATA for data downlink for 7
days• Universal Space Network – 50% discount for
TT&C services for 30 days• Space Florida - $2M bonus if launch from
FloridaAGI – Free STK package
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Lunar Terrain - General
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Lunar Mare relatively flat and smoothLunar Highlands relatively rough, heavily cratered
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Lunar Terrain – Rock Distribution
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Rock size and distribution is greater near “fresh” craters
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Lunar Terrain – Lighting
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Assuming minimum 20° sun angle is needed for the Solar Arrays, that only gives 10 Earth days of lunar operation per lunar day
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Summary of Rover Requirements
• Rover mass no greater than 80 kg.• Traverse obstacles up to 20 cm in height.• Maintain a ground contact pressure less than 7
to 10 kPa at all times.• Traverse slopes, both up and down, of a
minimum 20°.• Minimum roving speed of 10 cm/s• Complete the surface GLXP mission
requirements within 10 Earth days.8/26/2010
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Rover Design
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Rover Subsystems
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Process
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Analysis Trade-offs Recommendations
Discussion Future Work
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Rover Mobility
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Power System Architecture
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Rover Power
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Communication System Architecture
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Ground Station
RoverLander
High rate, UHF
High rate, X-
band
Low
rate
, S-
band
Low
rate
, S-
band
Low rate, S-band
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Rover Communications
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Rover Mass and Power Budgets
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System Mass (kg) % Total
Navigation 6 13%
C&DH 2 4%
Power 10,5 22%
Thermal 2,5 5%
Mobility 7 15%
Structures 11 23%
Communications 8 17%
Total 47
System Peak (W)
Nominal (W)
Standby (W)
Sensors 4 4 4Thermal 25 15 5Articulation 3 0 0C&DH 10 5 2Lander Comms 1 1 1Earth Comms 20 10 0Mobility 20 10 0Camera Systems 25 10 0Margin 15% 15% 15%Total 100 51 13
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Rover Link Budget
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MtoE High Rate
MtoE Low Rate
EtoM Low Rate
MtoM Crosslink
Transmitter Transmit power [W] 20.00 10.00 10.00 0.10Frequency [GHz] 8.45 2.29 2.12 0.30Parabolic Antenna Diameter [m] 0.30 N/A 6.00 N/ATransmitter Gain [dB] 25.89 5.00 39.90 1.80Range [km] 384403 384403 384403 2
Losses Free space Loss [dB] 222.68 211.34 210.67 88.01Atmospheric Loss [dB] 0.06 0.03 0.03 0.00Other Losses [dB] 2.00 1.00 1.00 1.00
Receiver Parabolic Antenna Diameter [m] 6.10 12.00 N/A N/AReceiver Gain, Gr [dB] 52.05 46.59 5.00 1.80System noise temperature [K] 45 300 500 500Receiver figure of merit [dB/K] 35.52 21.82 -21.99 -25.19Bit rate [kbps] 1000.00 8.00 1.00 1000.00Required Eb/N0 [dB] 10.00 10.00 10.00 10.00Link Margin [dB] 8.28 4.02 4.81 36.20
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Summary of Recommendations
• Design for low mass, cost and complexity– rover design, landing site, path selection
• Choose mission unique aspects with minimal impact on rover design
• Use GLXP preferred partners where feasible• Put any complex payloads on the lander• Sell acquired data, such as mobility
performance results
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Moonbase Alpha/GLXP Proposal
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Summary
• Initial set of mission requirements created• Gained a better understanding of lunar
conditions for mobile robotics• Created spreadsheets for evaluating mission
design options/feasibility• Provided initial values for rover mass, power
and link budgets
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Questions?
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