A LUNAR LASER RANGING RETRO-REFLECTOR ARRAY
21st CENTURY
Professor Douglas Currie
for the
University of Maryland, College Park, MD, USA
NASA Lunar Science Institute, Moffett Field, CA
INFN – LNF, Laboratori Nazionali di Frascati, Italy
& The LLRRA-21 Teams with the
Lunar University Network for Astrophysics Research
Jack Burns, Director
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OUTLINE
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Introduction of Structure
Outline of Talk
Consideration of Apollo Results
Science Areas
Lunar Physics
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Different Accuracies
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Mission – Flights
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Expected Science
• Lunar
• Relativity
Google Lunar X Prize
Lunette
LGN
Acknowledgements
Solution – Single CCR
LLRRA-21
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Planetary - Astronomy Panel
Astronomical -
Problem Due to Librations
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Inertial Properties of Gravitational Energy
Temporal Change of G
Spatial Change of G
General Review
Decadal Remarks
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Relativity Physics
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Lunar Core
Other
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Why a Solution
Design
Signal Performance
Emplacement Issues
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23 February 2011
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OVERVIEW
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Science Heritage – The Apollo Arrays
Current Status and Science Objectives of LLR
Objectives and Method for the Next Generation Retroreflector
Challenges and Solutions
Robotic Emplacement on Lunar Surface
Will it Work – Heritage
Will it Work – Computer Simulation of Optical/Thermal Performance
Will It Work – Thermal Vacuum Testing of Package
Will it Work – Science Objectives
Critical Vendors
Flight Opportunities
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Why Laser Ranging
• Exquisitely Precise Range
• Range is Sensitive to Many Parameters
– Relativity
– Geo-Physics (Earth Satellites)
– Seleno-Physics (Lunar Observations)
• Satellite Ranging
– Esp. LAGEOS, but also Other Satellites
– Gravity Field, Crustal Properties, etc, etc.
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What do I Mean by Precise
• The APOLLO Station is Currently Ranging
– At a Level of 2.4 parts in 1,000,000,000,000
• If My Eyes were This Good, I Could
– Read a License Plate on the Moon
– Inspect Someone’s DNA Amino Acid
• In San Francisco from Washington
• Detect Tiny General Reletivity Effects
• Detect the Sloshing of the Liquid Lunar Core
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But Why the Moon ??
• Second Brightest Object in the Sky
• Basis of Time Keeping – Lunar Calendar
– Jewish and Muslim Religious Holidays
– First light of moon to Start Ramadan
– Results Holidays Moving About Solar Seasons
• Solar calendar
– Better for Planting of Crops
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23 February 2011
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Why Laser Ranging to the Moon
• Ideally Want to Track an Object
– Which Travels on a Geodesic
• Problems
– Solar Photons Push Satellite to New Orbit
– Heated Surface of Satellite Emits IR Photons
• Moon has Much Better Mass/Surface Ratio
• Besides, We Learn of the Lunar Interior
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Background
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Retroreflector Array to moon on Apollo 11 1969
How do we do laser ranging?
Send a very short laser pulse toward the moon
Time the interval between transmission & reflection
But reflection from the Lunar Surface is too weak
Need to send the light back to the Transmitter
Enter the Cube Corner Reflector
Sends the Light Back to the Source
“Strong” i.e. Usable Signal Level
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What have the Apollo Arrays Done
• The Earth-Moon System Provides an Ideal System
– To Evaluate Relativity and Einstein’s Theory
– To Understand the Interior of the Moon
• Moon is Massive enough to Resist Drag/Pressure
• Moon is Far Enough to be in a Solar Orbit (Weakly Bound)
• LLR Currently Provides our Tests of:
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The Weak Equivalence Principle (WEP)*:  a / a < 1.310-13
The Strong Equivalence Principle (SEP): 
< 4104
Time-Rate-of-Change of G to < 710  13 per year
Inverse Square Law to 3 10 11 at 10 8 m scales
Geodetic Precession to 0.6 %
Gravitomagnetism to 0.1 %
Initial Definition of Liquid Lunar Core
Love Numbers of the Crust
Free Librations and Q of the Moon
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ASTRO2010 DECADAL SURVEY
Gravitational and Particle Physics Panel
Much is unknown about fundamental theory: Modifications of
general relativity on accessible scales are not ruled out by today’s
fundamental theories and observations. It makes sense to look for
them by testing general relativity as accurately as possible. Costeffective experiments that increase the precision of measurement of
PPN parameters, and test the strong and weak equivalence
principles, should be carried out. For example, improvements in
Lunar Laser Ranging promise to advance this area.
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ASTRO2010 DECADAL SURVEY
Gravitational and Particle Physics Panel
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The direct detection of gravitomagnetic effects (the Lense-Thirring
precession) from Lageos/Grace, Gravity Probe B, and lunar laser ranging.
The lunar laser ranging verification of the strong equivalence principle to 104, meaning that the triple graviton vertex is now known to a better accuracy
than the triple gluon vertex.
Limits on the fractional rate of change of the gravitational constant
G (< 10-12) Limits on the fractional rate of change of the gravitational
constant G (< 10-12/yr) from lunar laser ranging. Atomic experiments
limiting time variation of the fine structure constant to 10-16/yr over periods
of several years.
Experiments that are in progress include the Microscope equivalence
principle experiment, the APOLLO lunar laser ranging observations, and
tests of general relativity using torsion balances and atom interferometry.
Improved strong and weak equivalence principle limits. Better determination
of PPN parameters and and Ġ/G from next generation Lunar laser ranging
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ASTRO2010 DECADAL SURVEY
Gravitational and Particle Physics Panel
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A new Lunar Laser Ranging (LLR) program, if conducted as a low cost robotic
mission or an add-on to a manned mission to the Moon, offers a promising and costeffective way to test general relativity and other theories of gravity (Figure 8.12). So
far, LLR has provided the most accurate tests of the weak equivalence principle, the
strong equivalence principle and the constancy in time of Newton’s gravitational
constant. These are tests of the core foundational principles of general relativity. Any
detected violation would require a major revision of current theoretical understanding.
As of yet, there are no reliable predictions of violations. However, because of their
importance, the panel favors pushing the limits on these principles when it can be
done at a reasonable cost. The installation of new LLR retroreflectors to replace the
40 year old ones might provide such an opportunity. The panel emphasizes again
that its opinion that experiments improving the measurements of basic parameters of
gravitation theory are justified only if they are of moderate cost. Therefore, it
recommends that NASA’s existing program of small- and medium-scale astrophysics
missions address this science area by considering, through peer review, experiments
to test general relativity and other theories of gravity. The panel notes that a robotic
placement of improved reflectors for LLR is likely to be consistent with the
constraints of such a program. It returns to this recommendation below in the context
of a recommendation to augment the Explorer program.
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ASTRO2010 DECADAL SURVEY
Cosmology and Fundamental Physics Panel
These complex spin-induced orbital effects are the consequences of “frame
dragging,” a fundamental prediction of Einstein’s theory that has been probed in the
Solar System using Gravity Probe B, LAGEOS satellites, and Lunar laser ranging,
and has been hinted at in observations of accretion onto neutron stars and black
holes.
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LLR LUNAR SCIENCE
OVERVIEW
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Elastic Tides of the Moon
Tidal Dissipation
Size and Oblateness of Liquid Core
Dissipation at Liquid-Core/Solid-Mantle Interface
Lunar Moment of Inertia
Fluid Core Moment of Inertia
Evolution and Heating
Existence of a Smaller Solid Inner Core
Selenodetic Site Positions
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LLR RELATIVITY SCIENCE
OVERVIEW
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Strong Equivalence Principle
Weak Equivalence Principle
Time Variation of Gravitational Constant
GravitoMagnetic Effects
Deviation of 1/r2 –
– MOND Theories of Gravitation
• Fundamental Inconsistency of
– General Relativity and Quantum Mechanics
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LLRRA-21 Science Motivations
• Astrophysical Science Motivations
– Fundamental Incompatibility Between
• Quantum Mechanics and General Relativity
– Dark Energy may be Aspect of Large-Scale Gravity
• Dvali Idea Replaces Normal GR with “Leaky” Gravity
• Can be Seen in Precession of Lunar Orbit
– Dark Matter inspires Alternative Gravity Models (MOND)
• Further Tests of Inverse Square Law could Confirm or Deny
• Lunar Science Motivations
– Liquid Core –
Dimensions, Shape, Rotation
– Inner Solid Core –
Existence, Size, Rotation
– Rotational Dynamics – Q, External Impacts
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SHORT HISTORY
• Apollo Lunar Laser Ranging Arrays 1969
– Thermal and Optical Analysis and Testing
– McDonald LLR Station
• 2006
– Return to the Moon
– Could Address Accuracy Limit
• 2007
– LSSO for 100 mm CCR
– Lunar Science Sortie Opportunities
• 2009
– NLSI > LUNAR at University of Colorado
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LIBRATION PROBLEMS
• Why is there a Problem with the Apollo Arrays
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Libration in Both Axis of 8 degrees
Apollo Arrays are Tilted by the Lunar Librations
CCR in Corner is Further Away by Several Centimeters
Even Short Laser Pulse is Spread
Results in a Range Uncertainty by ~2 cm
APOLLO Station of Tom Murphy UCSD
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Thousands of Returns per Normal Point
Root N to Get Range to 1 – 2 millimeters
Needs Large Telescope
Hard to get Daily Coverage
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APOLLO Data from Tom Murphy
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LLRRA-21 PROGRAM
• Solid 100 mm Cube Corner Reflector
– 42 Year Heritage on the Moon
– Hundreds on Satellites
– Technology Readiness Level (TRL) = 6.5
• Lunar Deployment Program
– Phase I
• Surface Emplacement
• Supports Sub Millimeter Single PhotoElectron Ranging
• 2013 - 2014
– Phase II
• Anchored Emplacement
• Supports SPE Ranging at less than 100 microns
• 2016 or Later
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LLRRA-21 Teams
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LSSO Team – NASA
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Douglas Currie Principal Investigator
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University of Maryland, College Park, College Park m MD, USA•
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NLSI, Moffett Field, CA, USA &
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INFN-LNF Frascati, Italy
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Bradford Behr
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University of Maryland, College Park, MD, USA
Tom Murphy
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University of California at San Diego, San Diego, CA , USA
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Simone Dell’Agnello
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INFN/LNF Frascati, Italy
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Giovanni Delle Monache
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INFN/LNF Frascati, Italy
W. David Carrier
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Lunar Geotechnical Institute, Lakeland, FL, USA
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Roberto Vittori
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Italian Air Force, ESA Astronaut Corps
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Ken Nordtveldt
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Northwest Analysis, Bozeman, MT, USA
Gia Dvali
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New York University, New York, NY and CERN, Geneva, CH
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David Rubincam
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GSFC/NASA, Greenbelt, MD, USA
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Arsen Hajian
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University of Waterloo, ON, Canada
INFN-LNF Frascati Team
Simone Dell’Agnello PI INFN-LNF, Frascati, Italy
Giovanni Delle Monache INFN-LNF, Frascati, Italy
Douglas Currie
U. of Maryland, College Park, MD, USA
NLSI, Moffett Field, CA, USA &
INFN-LNF, Frascati, Italy
Roberto Vittori
Italian Air Force & ESA Astronaut Corps
Claudio Cantone
INFN-LNF, Frascati, Italy
Marco Garattini
INFN-LNF, Frascati, Italy
Alessandro Boni
INFN-LNF, Frascati, Italy
Manuele Martini
INFN-LNF, Frascati, Italy
Nicola Intaglietta
INFN-LNF, Frascati, Italy
Caterina Lops
INFN-LNF, Frascati, Italy
Riccardo March
CNR-IAC & INFN-LNF, Rome, Italy
Roberto Tauraso
U. of Rome Tor Vergata & INFN-LNF
Giovanni Bellettini
U. of Rome Tor Vergata & INFN-LNF
Mauro Maiello
INFN-LNF, Frascati, Italy
Simone Berardi
INFN-LNF, Frascati, Italy
Luca Porcelli
INFN-LNF, Frascati, Italy
Giuseppe Bianco
ASI Centro di Geodesia Spaziale
“G. Colombo”, Matera,
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CHALLENGES for SOLID CCR
• Fabrication of the CCR to Required Tolerances
• Sufficient Return for Reasonable Operation
– Ideal Case for Link Equation
• Thermal Distortion of Optical Performance
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Absorption of Solar Radiation within the CCR
Mount Conductance - Between Housing and CCR Tab
Pocket Radiation
- IR Heat Exchange with Housing
Solar Breakthrough - Due to Failure of TIR
• Stability of Lunar Surface Emplacement
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Problem of Regolith Heating and Expansion
Drilling to Stable Layer for CCR Support
Thermal Blanket to Isolate Support
Housing Design to Minimize Thermal Expansion
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CCR FABRICATION CHALLENGE
• CCR Fabrication Using SupraSil 1 Completed
• Specifications / Actual
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Clear Aperture Diameter - 100 mm / 100 mm
Mechanical Configuration - Expansion of Our APOLLO
Wave Front Error - 0.25 / 0.15 [ l/6.7 ]
Offset Angles
• Specification
– 0.00”, 0.00”, 0.00” +/-0.20”
• Fabricated
– 0.18”, 0.15”, 0.07”
• Flight Qualified
– with Certification
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THERMAL ANALYSIS – THEORETICAL
Solar Absorption within CCR
• Solar Heat Deposition in Fused Silica
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Solar Spectrum – AMO-2
Absorption Data for SupraSil 1/311
Compute Decay Distance for Each Wavelength
Compute Heat Deposition at Each Point
• Beer’s Law
– Thermal Modeling Addresses:
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Internal Heat Transport and Fluxes
Radiation from CCR to Space
Radiation Exchange with Internal Pocket Surroundings
Mount Conduction into the Support Tabs
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MOUNT CONDUCTANCE
• Challenge:
– Heat flow from Housing to CCR at Tabs
– Optical Distortion due to Heat Flux
• Support of CCR with KEL-F “Rings”
– Intrinsic Low Conductivity
– Use of Wire Inserts - Only Line Contacts
• Line Contact of Support Reduces Heat Flow
– For Support in Launch Environment
• KEL-F Wire Compresses and
• Launch Support Comes from Flush on Tab
• Estimated (to be Validated in SCF) 1 Milli-W/oK
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POCKET RADIATION EXCHANGE
• Challenge:
– IR Radiation Between CCR & Housing
– SiO2 Has High IR Absorptivity/Emissivity
– Heat Flux Causes Optical Distortion
• Isolation Between CCR and Housing
– Low Emissivity Coatings – 2% Emissivity
– Successive Cans or Multiple Layers
• Simulations Show Isolation is Effective
• Thermal Vacuum Chamber Validation
– In April 2009 at SCF at INFN/LNF at Frascati
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INNER & OUTER THERMAL
SHIELDS
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THERMAL & SUNSHADE
• Role of Sun Shade
– Thermal Control and Sun Blocking
– Dust Protection
– UltraViolet Light Protection
• External Surface
– Highly Reflective in Visible
– High Emissivity in the Infrared
• Internal Surface
– Black in the Visible
– Low Emissivity in the Infrared
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LLRRA-21 PACKAGE
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ORBITAL THERMAL EVOLUTION
• Simulation Performed with
– Thermal Desktop
• C&R Technologies
– IDL
– Code V
• Initial Analysis
– “Steady State” Behavior
– Fixed Elevation of Sun
• But During Lunar Month
– Changing Illumination
• Both Intensity and Angle
– For CCR/Housing/Thermal Blanket/Regolith
• Some Time Constants are Longer than a Month
– Analysis of Behavior of Face to Tip Temperature Difference
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Simulation Procedure
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AutoCad Drawing of Total Package
– CCR, Housing, Internal and External Support and Regolith
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4-D Heat Deposition in CCR – UMd IDL Program
– Through a Lunation, 1 Nanometer Wavelength Bands,
– Many Thousands of Nodes, Reflection Effects of SunShade
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Thermal Desktop
– Computes Temperature at Each Node
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PhaseMap – UMd IDL Program
– Converts 3D Temperatures to 2D PhaseMap at Each of 400 Sun Angles
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Code V Optical Analysis Program
– Adds Optical Errors (Reflection Phases, Offset Angles to Thermal Errors
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Analysis Program – UMd IDL Program
– Evaluates Laser Return Intensity - Addressing
• Velocity Aberrations and Station Latitude
• Polarization Effects
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Thermal Simulation Comparison
Effect
of
Multi-Layer
Insulation
Internal Sun Shade:
X Dark Mirror
Internal Sun Shade:
X Dark Mirror
Inner Conformal Can: Silver - 0.6%
Emissivity
External Surface:
No MLI & SSM
Sun Shade Length:
100 mm
Inner Conformal Can: Silver - 0.6%
Emissivity
External Surface:
MLI & SSM
Sun Shade Length:
100 mm
600
6
500
5
400
4
300
3
200
2
100
1
0
0
-100
-1
-200
-2
-2 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30
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FULL Thermal Simulation
Anchored Emplacement
Regolith from Apollo HFE,
Thermal Blanket
Current Design Housing
Temperature Distribution
in CCR and Tip to Face
Temperature Difference
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1.2
1
0.8
0.6
0.4
0.2
0
0
10
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CURRENT STATUS
• Preliminary Definition of Overall Package
• Completed Preliminary Simulations
– LSSO – Lunar Science Surface Opportunities
– Thermal (CCR, Regolith, Housing), Optical
• Completed Phase I Thermal Vacuum Tests
– Solar Absorption Effects on CCR
– CCR Time Constants –
• IR Camera – Front Face
• Thermocouples – Volume
• Preliminary Optical FFDP
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SCF Thermal Vacuum Test
Infrared Imager
Full Dynamic Range
Heat Flow Due to Tab
Supports
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Dust Accelerator
University of Colorado
Fused Silica Witness Plates
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LLRRA-21 SIGNAL STRENGTH
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88% of the Current Apollo 15 Signal Level
– At End of First Decade still about the same as Apollo 15 and
– 2.64 Stronger than Apollo 11
Simulated Pattern with Offset Angles to Correct for Velocity Aberration
Relative to Current A11
– On Axis Return is 49% of Apollo 11
– At Velocity Aberrated Latitude , the Return is ~55% of Apollo 11
– But No Dust so Stronger by a Factor of 9.6
– Overall – Stronger Than Apollo 11 by a factor of 2.64
– Overall – 90% of the return of Apollo 15
If Dust on the Apollo Array is due LEM Launch – LLRRA-21 has a Cover for Landing Dust
If Dust on the Apollo Arrays is due to Steady Deposit of Dust or High Velocity Impacts
– There would be at Least a Decade of Good Returns
– But LLRRA-21 Should Expect Better Performance
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Sun Shade
Dust Mitigator
APOLLO Station gets Many Thousands of Returns in 5 Minutes on Apollo 15 Almost Every Night
– 3.6 meter Therefore Smaller Telescopes can Work
– At 1,000 Returns on 3.6 Meter,
– One Should get 80 Returns on 1 Meter and 25 Returns on 0.6 meter Telescope
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ROBOTIC DEPLOYMENT
• Deployment Methods
– Lander Mounting
• Few Millimeters
• Thermal Expansion of Lander during Lunation
– Surface Deployment
• Sub-Millimeter
• Regolith Expansion during Lunation
– Anchored Deployment
• Tens of Microns
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ROBOTIC DEPLOYMENT
• Candidate Flight Opportunities
– Google X Prize
• Astrobotics
– David Gump
• Moon Express – Bob Richards
– Lunette – Discovery Mission Proposal
• LLRRA-21 is Backup Retroreflector Package
– ILN
• Future NASA Possibility
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ROBOTIC DEPLOYMENT
Requirements
• Orientation
– Three Angles
• Toward the Earth
– Azimuth and Elevation
– About One Degree
• :Clocking”
– Accommodation for Velocity Aberration
– About One Degree
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LUNAR SURFACE EMPLACEMENT
• CCR Optical Performance at Sub-Micron
– Want to Assure as Much of This as Possible
• We Have Sufficiently Strong Return
• Emplacement Issues - Diurnal Heating of Regolith
– ~ 400 Microns of Lunar Day/Night Vertical Motion
• Solutions – Dual Approach for Risk Reduction
– Drill to Stable Layer and Anchor CCR to This Level
• ~ one meter – Apollo Mission Performed Deeper Drilling
• ~ 0.03 microns of motion at this depth
– Stabilize the Temperature Surrounding the CCR
• Multi Layer Insulation Thermal Blanket – 4 meters diameter
• Support Rod Sees a Constant Temperature Environment
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SURFACE DEPLOYMENT
• Issues
– CCR Should Point Toward Earth “Center”
– Maintain Clocking Angle
• to Handle Sun Break-through
– Handle Longitudinal (toward earth) Tilt of Surface
– Handle Azimuthal Tilt of Surface
• Requirements
– Self Orienting Procedure to Keep Clocking Angle
– Longitudinal (Elevation) Self Orientation
– Azimuth Angle Adjusted by Deployment Arm
• Calibrated by Goniometer (Sun Dial)
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ROBOTIC DEPLOYMENT
Surface Deployment
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DEPLOYMENT APPROACHS
Surface Deployment
• Candidates
– Reference w.r.t. Regolith Surface
• Uneven Surface a Problem
– Reference to Local Gravity Vector
• Wire Support
• Clocking and Elevation Self Orienting
• Azimuth Correction by:
– Lander Arm
– Dedicated Motor
• Demonstration
• Frame Design and Pick-up Procedure
– Needs Info on the Capabilities of the Lander Arm
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ROBOTIC DEPLOYMENT
Anchored Deployment
• Problem with Regolith Expansion
– During a Lunation
– 300K at Surface
– ~ 400 microns
• Solution
– Anchor CCR below Thermally Active Region
– Drill to a Meter or Less
– Small Fraction of a Degree Variation
– Anchor at Base
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ANCHORED DEPLOYMENT
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PNEUMATIC PROBOSCIS SYSTEM
Kris Zacny – Honeybee, Inc.
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CRITICAL VENDORS
• Cube Corner Retroreflectors
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ITE, Inc. Laurel, Maryland, USA
Ed Aaron, President
Fabricated CCR #1 of LLRRA-21 Program
Successfully met Specifications
Fabricated Flight CCR Arrays of Apollo Design
for:
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ETS-8, QZSS Japan
Naval Research Laboratory
NASA
U.S. Air Force
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CRITICAL VENDORS
• Thermal Shields, Inner & Outer
– Epner Technologies, Inc.
– David Epner, President
– Fabricated Shields for LLRRA-21 SCF Tests
– Successful Operation in Thermal Vacuum
Test
– Epner has Fabricated LaserGold Shields for
• NOAA – GOES Satellites for 25 years
• NASA – Hubble WFPC, MOLA Laser Altimiter
– Advanced Chemical Experiment
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CRITICAL VENDORS
• Housing and Deployment Frame
– L-3. SSG, Inc. In
– Joseph Robichaud, Chief Technology Officer
– Silicon Carbide – Low Thermal Expansion
– Fabricated SiC for Space Applications for
• Jet Propulsion Laboratory
• NASA
• Naval Research Laboratory
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PREMIER STATION CHALLENGES
• Performance Requirements
– To take Advantage of LLRRA-21
– Addressing Sub-Millimeter Ranging
• Basis for Requirements
– Background on Requirements
• Commercial Sources for Components
– All Requied Elements are Available
– No “Research” Program
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MISSION OPPORTUNITES
• Possible Roles for 100 mm Solid CCR Retroreflector
– NASA
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First Manned Landing - LSSO / NASA Program
International Lunar Network (ILN) Anchor Nodes
Lunette Discovery Proposal
Lunar Express – Lockheed Martin
– Italian Space Agency & INFN
• MAGIA – ASI & INFN
– Proposed ASI Lunar Orbiter to Carry a 100 mm Solid CCR
• Italian ILN Retroreflector Instrument
– MoonLIGHT-ILN INFN Experiment
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Acknowledgements
• Primary Support at University of Maryland
– NASA via Lunar Science Surface Opportunities
– NASA via NASA Lunar Science Institute
• via LUNAR at the University of Colorado
• Primary Support for Frascati Effort
– INFN-LNF
– Italian Space Agency
• Plus Contributions by Many Individuals
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Thank You!
any
Questions?
or
Comments?
currie@umd.edu
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