1. Lunar University Network for Astrophysics Research Jack Burns, Director A LUNAR LASER RANGING RETRO-REFLECTOR ARRAY for the 21 st CENTURY Professor Douglas Currie 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 1

2. OUTLINE Introduction of Structure Outline of Talk Consideration of Apollo Results Science Areas Lunar Physics –Lunar Core –Other Relativity Physics –Inertial Properties of Gravitational Energy –Temporal Change of G –Spatial Change of G –General Review Problem Due to Librations –Solution – Single CCR LLRRA-21 –Why a Solution –Design –Signal Performance –Emplacement Issues Decadal Remarks –Planetary - Astronomy Panel –Astronomical - Different Accuracies –Expected Science Lunar Relativity Mission – Flights –Google Lunar X Prize –Lunette –LGN Acknowledgements NLSI Commerce Virtual Lecture 23 February 2011 2

3. OVERVIEW 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 3NLSI Commerce Virtual Lecture 23 February 2011

4. 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. 4NLSI Commerce Virtual Lecture 23 February 2011

5. 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 5NLSI Commerce Virtual Lecture 23 February 2011

6. 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 6NLSI Commerce Virtual Lecture 23 February 2011

7. 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 7NLSI Commerce Virtual Lecture 23 February 2011

8. Background 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 8NLSI Commerce Virtual Lecture 23 February 2011

9. 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: 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 9 NLSI Commerce Virtual Lecture 23 February 2011

10. 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. Cost- effective 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. 10NLSI Commerce Virtual Lecture 23 February 2011

11. ASTRO2010 DECADAL SURVEY Gravitational and Particle Physics Panel 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 10- 4, 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 11NLSI Commerce Virtual Lecture 23 February 2011

12. ASTRO2010 DECADAL SURVEY Gravitational and Particle Physics Panel 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 cost- effective 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. 12NLSI Commerce Virtual Lecture 23 February 2011

13. 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. 13NLSI Commerce Virtual Lecture 23 February 2011

14. LLR LUNAR SCIENCE OVERVIEW 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 14NLSI Commerce Virtual Lecture 23 February 2011

15. LLR RELATIVITY SCIENCE OVERVIEW Strong Equivalence Principle Weak Equivalence Principle Time Variation of Gravitational Constant GravitoMagnetic Effects Deviation of 1/r 2 – –MOND Theories of Gravitation Fundamental Inconsistency of –General Relativity and Quantum Mechanics 15NLSI Commerce Virtual Lecture 23 February 2011

16. 16 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 NLSI Commerce Virtual Lecture 23 February 2011

17. 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 17NLSI Commerce Virtual Lecture 23 February 2011

18. LIBRATION PROBLEMS Why is there a Problem with the Apollo Arrays –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 Thousands of Returns per Normal Point Root N to Get Range to 1 – 2 millimeters Needs Large Telescope Hard to get Daily Coverage 18NLSI Commerce Virtual Lecture 23 February 2011

19. 19 APOLLO Data from Tom Murphy

20. 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 20NLSI Commerce Virtual Lecture 23 February 2011

21. LLRRA-21 Teams LSSO Team – NASA Douglas Currie Principal Investigator – University of Maryland, College Park, College Park m MD, USA –NLSI, Moffett Field, CA, USA & –INFN-LNF Frascati, Italy Bradford Behr –University of Maryland, College Park, MD, USA Tom Murphy –University of California at San Diego, San Diego, CA, USA Simone Dell’Agnello –INFN/LNF Frascati, Italy Giovanni Delle Monache –INFN/LNF Frascati, Italy W. David Carrier –Lunar Geotechnical Institute, Lakeland, FL, USA Roberto Vittori –Italian Air Force, ESA Astronaut Corps Ken Nordtveldt –Northwest Analysis, Bozeman, MT, USA Gia Dvali –New York University, New York, NY and CERN, Geneva, CH David Rubincam –GSFC/NASA, Greenbelt, MD, USA Arsen Hajian –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, 21 NLSI Commerce Virtual Lecture 23 February 2011

22. 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 –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 –Problem of Regolith Heating and Expansion –Drilling to Stable Layer for CCR Support –Thermal Blanket to Isolate Support –Housing Design to Minimize Thermal Expansion 22 NLSI Commerce Virtual Lecture 23 February 2011

23. CCR FABRICATION CHALLENGE CCR Fabrication Using SupraSil 1 Completed Specifications / Actual –Clear Aperture Diameter - 100 mm / 100 mm –Mechanical Configuration - Expansion of Our APOLLO –Wave Front Error - 0.25 / 0.15 [ /6.7 ] –Offset Angles Specification –0.00”, 0.00”, 0.00” +/-0.20” Fabricated –0.18”, 0.15”, 0.07” Flight Qualified –with Certification 23 NLSI Commerce Virtual Lecture 23 February 2011

24. THERMAL ANALYSIS – THEORETICAL Solar Absorption within CCR Solar Heat Deposition in Fused Silica –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: Internal Heat Transport and Fluxes Radiation from CCR to Space Radiation Exchange with Internal Pocket Surroundings Mount Conduction into the Support Tabs 24 NLSI Commerce Virtual Lecture 23 February 2011

25. 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/ o K 25 NLSI Commerce Virtual Lecture 23 February 2011

26. Challenge: –IR Radiation Between CCR & Housing –SiO 2 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 POCKET RADIATION EXCHANGE 26 NLSI Commerce Virtual Lecture 23 February 2011

27. INNER & OUTER THERMAL SHIELDS 27NLSI Commerce Virtual Lecture 23 February 2011

28. 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 28NLSI Commerce Virtual Lecture 23 February 2011

29. LLRRA-21 PACKAGE 29NLSI Commerce Virtual Lecture 23 February 2011

30. 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 30 NLSI Commerce Virtual Lecture 23 February 2011

31. Simulation Procedure AutoCad Drawing of Total Package –CCR, Housing, Internal and External Support and Regolith 4-D Heat Deposition in CCR – UMd IDL Program –Through a Lunation, 1 Nanometer Wavelength Bands, –Many Thousands of Nodes, Reflection Effects of SunShade Thermal Desktop –Computes Temperature at Each Node PhaseMap – UMd IDL Program –Converts 3D Temperatures to 2D PhaseMap at Each of 400 Sun Angles Code V Optical Analysis Program –Adds Optical Errors (Reflection Phases, Offset Angles to Thermal Errors Analysis Program – UMd IDL Program –Evaluates Laser Return Intensity - Addressing Velocity Aberrations and Station Latitude Polarization Effects 31NLSI Commerce Virtual Lecture 23 February 2011

32. Thermal Simulation Comparison Effect of Multi-Layer Insulation Internal Sun Shade: X Dark Mirror Inner Conformal Can: Silver - 0.6% Emissivity External Surface: MLI & SSM Sun Shade Length: 100 mm Internal Sun Shade: X Dark Mirror Inner Conformal Can: Silver - 0.6% Emissivity External Surface: No MLI & SSM Sun Shade Length: 100 mm NLSI Commerce Virtual Lecture 23 February 2011 32

33. FULL Thermal Simulation Anchored Emplacement Regolith from Apollo HFE, Thermal Blanket Current Design Housing Temperature Distribution in CCR and Tip to Face Temperature Difference 33 NLSI Commerce Virtual Lecture 23 February 2011

34. 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 34 NLSI Commerce Virtual Lecture 23 February 2011

35. SCF Thermal Vacuum Test Infrared Imager Full Dynamic Range Heat Flow Due to Tab Supports NLSI Commerce Virtual Lecture 23 February 2011 35

36. Dust Accelerator University of Colorado Fused Silica Witness Plates NLSI Commerce Virtual Lecture 23 February 2011 36

37. LLRRA-21 SIGNAL STRENGTH 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 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 37NLSI Commerce Virtual Lecture 23 February 2011 NLSI Commerce Virtual Lecture 23 February 2011

38. 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 38NLSI Commerce Virtual Lecture 23 February 2011

39. 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 39NLSI Commerce Virtual Lecture 23 February 2011

40. ROBOTIC DEPLOYMENT Requirements Orientation –Three Angles Toward the Earth –Azimuth and Elevation –About One Degree :Clocking” –Accommodation for Velocity Aberration –About One Degree 40NLSI Commerce Virtual Lecture 23 February 2011

41. 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 41 NLSI Commerce Virtual Lecture 23 February 2011

42. 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) 42NLSI Commerce Virtual Lecture 23 February 2011

43. ROBOTIC DEPLOYMENT Surface Deployment 43NLSI Commerce Virtual Lecture 23 February 2011

44. DEPLOYMENT We have not received any detailed info Therefore have not significantly started If we are selected at a later time –Perhaps the deployment method and procedure –Could be handled by JPL –Who has developed detailed procedures 44NLSI Commerce Virtual Lecture 23 February 2011

45. 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 45NLSI Commerce Virtual Lecture 23 February 2011

46. 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 46NLSI Commerce Virtual Lecture 23 February 2011

47. ANCHORED DEPLOYMENT NLSI Commerce Virtual Lecture 23 February 2011 47

48. PNEUMATIC PROBOSCIS SYSTEM Kris Zacny – Honeybee, Inc. 48NLSI Commerce Virtual Lecture 23 February 2011

49. CRITICAL VENDORS Cube Corner Retroreflectors –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: ETS-8, QZSS Japan Naval Research Laboratory NASA U.S. Air Force 49NLSI Commerce Virtual Lecture 23 February 2011

50. 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 50NLSI Commerce Virtual Lecture 23 February 2011

51. 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 51NLSI Commerce Virtual Lecture 23 February 2011

52. 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 52NLSI Commerce Virtual Lecture 23 February 2011

53. MISSION OPPORTUNITES Possible Roles for 100 mm Solid CCR Retroreflector –NASA 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 53 NLSI Commerce Virtual Lecture 23 February 2011

54. 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 54NLSI Commerce Virtual Lecture 23 February 2011

55. Thank You! any Questions? or Comments? currie@umd.edu 55 NLSI Commerce Virtual Lecture 23 February 2011

56. Phase I – Early Deployment Objective: The objective of the Phase 1 effort is the early deployment of a “Lunar Laser Retroreflector Ranging Array for the 21 st Century” (LLRRA-21). This is currently under consideration for a Google Lunar X Prize flight before the end of 2013. Approach: Using internal funds within the LUNAR Team supported by the NASA Lunar Science Institute, the University of Maryland will complete a flight ready (certified and tested) LLRRA-21 package by the end of calendar 2012. The plan is then to interface this with the Moon Ex 1, the first Lander being built by Moon Express. Due to the short time, there will be no pointing mechanism on Moon Ex 1 to point the LLRRA-21 toward the center of the earth. For this reason, the opening angle of the Sun/Dust Shade will be increased from 8 degrees to 12 degrees. This will lead to a significant reduction in signal for a few days near lunar noon. 56NLSI Commerce Virtual Lecture 23 February 2011

57. Phase I – Early Deployment Funding: Phase 1 will require funding of the order of $2,000,000 to be paid to Moon Express as the cost of the flight plus an undefined about (estimated to be $300,000) for interfacing LLRRA-21 to the Lander. As mentioned above, the funding for this first package has been provided by internal funds. Schedule Fabrication of a set of components has been completed, with a second generation of components expected to be completed by July. A thermal vacuum test will be accomplished in the April time frame, using the SCF facility at the INFN-LNF in Frascati, Italy. Following the thermal vacuum tests, the vibration and shake tests will be accomplished in a facility in Maryland. The package will then be delivered to Moon Express for interfacing. 57NLSI Commerce Virtual Lecture 23 February 2011

58. Phase 2 - Science Deployment Science Objective: The objective of Phase 2 is to deploy at least three LLRRA-21s on the lunar surface. This is required in order to determine the orientation angle of the librating moon. As mentioned above, this is needed in order to study the interior of the moon. Since the risk for the Google Lunar X Prize (GLXP) flights is considerably above that of a normal NASA program, we address five Landers to assure that proper deployment of at least three. If all are properly deployed, then there will be considerable additional information on the local variations of the crustal deformation (Love Numbers). Approach: Five flights on Moon Express (or replacements). Need a minimum of 3 deployed for basic lunar science. These would be mounted on the top instrument platform with a pointing device. 58NLSI Commerce Virtual Lecture 23 February 2011 Phase 2 Science Objective: The objective of Phase 2 is to deploy at least three LLRRA-21s on the lunar surface. This is required in order to determine the orientation angle of the librating moon. As mentioned above, this is needed in order to study the interior of the moon. Since the risk for the Google Lunar X Prize (GLXP) flights is considerably above that of a normal NASA program, we address five Landers to assure that proper deployment of at least three. If all are properly deployed, then there will be considerable additional information on the local variations of the crustal deformation (Love Numbers). Approach:

59. Phase 3 - Anchored Deployment Science Objective: The objective of the Phase 3 effort is the deployment of three LLRRA-21 which will support ranging accuracy of less than 100 microns. HEOMD Objective: Many missions are now relying on demonstrated drilling and sampling operation on the behavior of lunar regolith simulants. In general the mechanical properties of the regolith are significantly different. The anchored deployment of LLRRA-21 using the pneumatic drilling will be the first test of modern drilling methods in time for other missions to adjust their procedures to accommodate what is learned about the actual regolith properties. 59NLSI Commerce Virtual Lecture 23 February 2011

60. Phase 3 - Anchored Deployment Approach: A pneumatic drill from Kriz Zacny of Honeybee would be carried by the Moon Express lander. The LUNAR Team of the University of Colorado has funded Honeybee to develop a design for the Astrobotics lander and is now funding Honeybee for the development of a deployment procedure for the Moon Express lander. Schedule: Optimally, this would proceed in parallel with Phase 2 Funding: Optimally this would be funded by HEOMD. 60NLSI Commerce Virtual Lecture 23 February 2011

61. Current Objectives SALMON Proposal for LLRRA-21 –Background NASA-SMD is preparing a SALMON Announcement to address support of science experiments to be carried on Google Lunar X Prize flights. –Schedule SMD has requested and now closed community input on such a SALMON and is now preparing the AO. Expected in the next few weeks. –Projected Proposal Format Joint Ames/University of Maryland Detailed Relationship TBD 61NLSI Commerce Virtual Lecture 23 February 2011

62. Proposed Personnel Principal Investigator: –Professor Douglas Currie, U. of Md, College Park Deputy PI: –Professor Chris Davis, U. of Md, College Park Co-Investigators: –Dr. Simone Dell-Agnello (INFN-LNF, Frascati, Italy) –Dr Giovanni Delle Monache (INFN-LNF, Frascati, Italy) –Dr. Chris Zacny, Honeybee Corp. –Professor Hironoda Noda, NAOJ –Professor Maria Zuber, MIT –Dr. David Smith, GSFC Project MgrTBD, Ames Research Center Project CoordinatorTBD, Ames Research Center Senior ProgrammerDr. Bradford Behr Graduate StudentTBD 62NLSI Commerce Virtual Lecture 23 February 2011

63. Possible additional Co-Investigators Professor Tom Murphy, UCSD Bob Roberts, Moon Express 63NLSI Commerce Virtual Lecture 23 February 2011