8 marts 2009 with euroluna to the moon on board romit european lunar exploration association and...
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8 marts 2009
With Euroluna to the moon on board Romit
European Lunar Exploration Association and Euroluna Ltd.
8 marts 2009
Agenda for meeting 8.3.2009
1. Welcome
2. Introduction to the GLXP competition
3. Presentation of the Euroluna project
4. Presentation of Team members
5. Questions and Comments
6. Discussion
7. Close
8 marts 200915th December 2008
Another Way to the Moon
European Lunar Exploration Association and Euroluna Ltd.
8 marts 200915th December 2008
New Ideas
Ingenious Route Design
Using Gravity for Propulsion
Piggyback Ride to LEO
Standard but Tested Components
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Benefits
Minimal Fuel Consumption
Low Mass
Low Cost
Low Capital Requirement
.
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Team of Gifted Amateurs
Management Team of Entrepreneurs
Drive
Small Overhead
Specialists in IT, Materials, and Physics
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Euroluna Strengths
Technical expertise
Voluntary contributions
Ideas
Team size, team cohesion
8 marts 200915th December 2008
Budget breakdown:
Approx 2,8 million Euros
Hardware 30 %
Launch 30 %
Operation 30%
Various 10 %
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Euroluna
• European Lunar Exploration Association, registered in Denmark.
• Euroluna Ltd, registered in Switzerland
• Volunteer based, shoe-string budget
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• Team name: Euroluna• President: Palle Haastrup• Craft Name: ROMIT• Main web site: www.euroluna.org• Euroluna email: [email protected]• News at www.twitter.com/euroluna• Blog: on GLXP site
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Collaborators
• Clyde Space Inc.• Langtved Data• Micro Aerospace Solutions, Inc • University of Toronto• Preliminary contacts with: Jamesburg disc
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Key team members• Palle: Team leader• Tor: Software• Soeren: Mechanical design• Sten: Trajectory• Signe: Press• Erik: Software operator• Mogens: Embedded software• Jesper: Video processing chain• Tom: Revisor• Kertu: kontor• + many others
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Mission
• Put a remote operated vehicle on the moon• Participate in the GLXP challenge
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Google Lunar X prize
• 20 million $ 1st prize• 5 million $ 2nd prize
• 5 x 1 million $ prize
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To win
• Be the first team • Private funding• Get to the moon• Drive/move 500 m• Send back “video”
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GLXP mission requirementsRequirement Euroluna plan
Unspecified payload
10 MB transmitted to craft Minimum 64 MB memory
Roam 500m Drive, 1 cm/s
Colour camera with pan tilt and zoom capabilities, minimum resolution 0,3 milliradians per pixel
Multiple pinhole cameras with digital zoom, resolution of 3000*3000 pixels
Videos
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Euroluna technical solution
• One integrated craft• Small rover• Bi prob rocket motor• Solar powered
• Minimum design of space component.
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Key mission parameters
• Departure from LEO (800 km)• Trajectory: Weak Stability Boundary
• Design: no redundancy• Time planning: launch opportunity end
2009
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Romit Subsystems1. PROPULSION2. POWER3. ATTITUDE CONTROL4. ONBOARD CPU5. WHEELS AND MOTORS6. GPS7. CAMERAS8. COMMUNICATION9. STRUCTURAL CONNECTIONS
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Thermal Analysis
• Design temperature in space: -20 - +50 ° C• Design temperature on the moon: +30 - +50
° C • This leads to an acceptable α/ε of between
0.65 and 0.88• The outer coating: shade of grey and heat
conducting
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Other specs
• HAL specs (linux)• Connections: USB
• Operation (out of rocket, attitude control, burn 3100 m/s, wait 4 month, turn around, break, land..)
• Link budget: large disc needed.
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Mechanical and vibration analysis
• Mechanical issues on connection between the two tanks.
• Vibration analysis not made yet, but assumed to be no serious problem…
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Link budgetROMIT2 JamesburgFrequency (Hz) 8400000000 3400000000Wavelengt (m) 0.03 0.088235294Transmit power (W) 10 1Transmit power dBm 40 30Circuit losses db -1 -1Antenna gain dBi 0 0EIRP Equivalent isotropically radiated power 39 29
Range (m) 1000000000 1400000000Spaceloss (dB) -232.4 -226.0
Receiving station (Standford 45 m radio telescope) JamesburgAntenna Diameter (m) 45.7 29Antenna efficiency 0.6Antenna effective area 985Antenna gain 44.2 57
Receive power -149.2 -140.0
Noise Density -177 -177
Expected Pt/No 27.8 37.0
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Solar cell navigation (!)
• By measuring the solar input to the 6 solar cells, we get a rough direction/orientation of the spacecraft.
• Power measurement can handle this ?
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System Consumption/Production in Watt
Motors 10 W for normal operation, 5 w/motor for exceptions
Camera 3 W
Motor for turning camera 1 W
Computer 1.5 W
Radio Transmitter 3 W
Production with 3 layer solar cells, max
17 W
Power consumption
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Trajectory design
• Weak Stability boundary route
• Advantages: all launches can be used• Disadvantage: time to moon, precision
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Mission plan outline
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Mission planTime Action
0 Ejection from storage bay,
Health check, status of all systems. Transmit to ground control
Use GPS, navigation cameras to determine position
Calculate orbit, using position data
Calculate time to burn (T1).
Change attitude for 1st burn, initiate rotation about longitudinal axis
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Time ActionT1 First burn, constant GPS position measured for
monitoringPosition determined from GPS, Earth-Moon-Sun images. Course compliance monitored for possible corrections Calculate time till arrival in hyperbolic trajectory, T2Determine whether there is fuel enough for orbiting the Moon or if landing has to be immediate.
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Time ActionT2 Arrival in Moon Hyperbolic trajectory.
Decision is carried out; attitude corrected and thruster firedIf we obtain a circular orbit, Newtonian height and velocity are calculated and correlated with crater images. Results are transmitted to ground control
Calculate optimal landing place and time (T3)T3 Initiate landing sequence
Send confirmation of successful landing
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Moon operation mission plan
Given by GLXP requirements
Turn craft if upside down,drive 500 m
Long term survival prize for restart after lunar night.
Insulate components, other options ?
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Discussion
• Main conceptual design frozen• Mechanical design still evolving
• Offer for launch end of 2009 – but maybe Geo Transfer orbit in 2010
• We need to go commercial off the shelf, rather than custom designed.