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Lunar Reconnaissance Orbiter

Lunar Reconnaissance Orbiter. Presentation to Public Librarians at GSFC Visitors Center David Everett February 2, 2006. LRO Overview. LRO will launch by 2008 to provide critically needed data to enable and to plan future Exploration objectives

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Lunar Reconnaissance Orbiter

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  1. Lunar Reconnaissance Orbiter Presentation to Public Librarians at GSFC Visitors Center David Everett February 2, 2006

  2. LRO Overview • LRO will launch by 2008 to provide critically needed data to enable and to plan future Exploration objectives • LRO provides major exploration and scientific benefits by 2009 • Apollo provided first order information from a small region of the Moon; much more of the Moon need to be explored • LRO objectives addresses future landing sites, polar resources, safety, and lunar science goals • LRO address both science and exploration objectives • LRO instrument suite complements international lunar missions • Six instruments competitively selected • Comparison to international missions demonstrate LRO uniqueness and value David Everett--LRO Overview

  3. US Lunar Robotic and Apollo Missions David Everett--LRO Overview

  4. LRO Payload Provides Broad Benefits David Everett--LRO Overview

  5. Comparison to Foreign Systems Demonstrate Uniqueness and Value David Everett--LRO Overview

  6. Comparison to Foreign Systems Demonstrate Uniqueness and Value David Everett--LRO Overview

  7. Lunar Cold Traps • Cold traps exist near the lunar poles (Watson et al., 1961) • Low obliquity of Moon affords permanent shadow in depressions at high latitude. • Temperatures are low enough to retain volatiles for t > tMoon. David Everett--LRO Overview

  8. Volatile Content of Cold Traps • Hydrogen enhancements have been detected by Lunar Prospector Neutron Spectrometer (Feldman et al., 1998; 2000) • Spatially correlated to the regions of permanent shadow (Feldman et al., 2001) spatial resolution about 50 km (30 km orbit) orbit 150 km ( 100 km orbit) • Concentrations of H at 1670 ppm detected in upper 1 m in SP PSRs. Feldman et al., JGR David Everett--LRO Overview

  9. South Pole Permanent Shadows David Everett--LRO Overview

  10. North Pole Permanent Shadows David Everett--LRO Overview

  11. Cosmic Ray Telescope for the Effects of Radiation (CRaTER) Instrument Team David Everett--LRO Overview

  12. CRaTER Instrument Overview David Everett--LRO Overview

  13. CRaTER Telescope Configuration Five-element detector stack with volumes of TEP sandwiched between them David Everett--LRO Overview

  14. Diviner Lunar Radiometer Experiment (DLRE) Instrument Team David Everett--LRO Overview

  15. Diviner Measurement Overview Measurement Goals: • Map Global Day/Night Surface Temperatures • Characterize Thermal Environments for Habitability • Determine Rock Abundances at Landing Sites • Identify Potential Polar Ice Reservoirs • Search for Near-Surface and Exposed Ice Deposits Measurement Approach: • 9-channel radiometer (0.3 to 200 micron wavelength range) • 250m spatial resolution Diviner will make precise radiometric temperature measurements of the Lunar surface David Everett--LRO Overview

  16. Diviner Heritage Diviner is a nearly build to print copy of the Mars Reconnaissance Orbiter (MRO) Mars Climate Sounder (MCS) MCS Integrated with MRO for August 2005 Launch MCS Flight Model at JPL David Everett--LRO Overview

  17. Lyman Alpha Mapping Project (LAMP) Instrument Team David Everett--LRO Overview

  18. LAMP Science/Measurement • LAMP will provide landform mapping (from Lyman  albedos) at sub-km resolution in and around the permanently shadowed regions (PSRs) of the lunar surface. • LAMP will be used to identify and localize exposed water frost in PSRs. • LAMP will demonstrate the feasibility of using starlight and sky-glow for future surface mission applications. • LAMP will detect (or better constrain) the abundances of several atmospheric species. David Everett--LRO Overview

  19. LAMP Heritage LAMP is almost identical to New Horizons Alice LAMP: 5.0 kg, 4.3 W 0.2º×6.0º slit 1200-1800 Å bandpass <20 Åspectral resolution David Everett--LRO Overview

  20. Lunar Exploration Neutron Detector (LEND) Instrument Team David Everett--LRO Overview

  21. LEND Measurement Goals David Everett--LRO Overview

  22. LEND Instrument Concept Block Diagram E A D A – Collimated Sensors C – Sensors of Thermal Neutrons B – Sensors of Thermal D – Sensor of Epithermal Neutrons Neutrons for Doppler Filter E – Sensor of High Energy Neutrons David Everett--LRO Overview

  23. Lunar Orbiter Laser Altimeter (LOLA) Instrument Team David Everett--LRO Overview

  24. LOLA Measurements LOLA makes 3 measurements: (1) range to the surface, (2) spread of the laser pulse, (3) reflectance of the surface • LOLA Lineage • GLAS • SLA • MOLA • MLA • Clementine David Everett--LRO Overview

  25. What Does LOLA Have To Do? Measure the distance between the spacecraft and the surface which, along with the spacecraft position, will allow precise measurements of the lunar shape. Lay down a laser spot pattern that will provide altimetry measurements along- and across-track to enable the surface slope to be derived for safe landing. Measure the distribution of elevation within the laser footprint for estimation of surface roughness (rock size) Identify regions of enhanced surface reflectance that might indicate the presence of water ice on the surface. David Everett--LRO Overview

  26. Lunar Reconnaissance Orbiter Camera (LROC) Instrument Team Clementine Star Tracker Camera David Everett--LRO Overview

  27. LROC Measurement Objectives • Landing site identification and certification, with unambiguous identification of meter-scale hazards • Unambiguous mapping of permanent shadows and sunlit regions • Meter-scale mapping of polar regions with continuous illumination • Overlapping observations to enable derivation of meter-scale topography • Global multispectral imaging to map ilmenite and other minerals • Global morphology base map • Characterize regolith properties • Determine current impact hazard by re-imaging 1-2 m/pixel Apollo images David Everett--LRO Overview

  28. LROC Instrument Overview • 2 Narrow Angle Components (NACs) for Landing Site Certification • Wide Angle Component to Monitor Polar Lighting and Map Resources • Sequence and Compressor System • Straightforward modifications from previous flight instruments LROC WAC NAC1 NAC2 SCS David Everett--LRO Overview

  29. Mini RF Instrument Team David Everett--LRO Overview

  30. Mini-RF Spiral Development DoD NASA International TacSat FY 09 LRO FY 08 Chandrayaan-1 FY 07 (Forerunner) David Everett--LRO Overview

  31. LRO Possible Mini-RF Lunar Demonstrations SAR Imaging (Monostatic and Bistatic) Chandrayaan-1 Lunar Reconnaissance Orbiter (LRO) Chandrayaan-1 LRO Monostatic imaging in S-band to locate and resolve ice deposits on the Moon. Communications Demonstrations Component Qualification Monostatic imaging in S-band and X-band to validate ice deposits discoveries on the Moon X-Band Comm Demo Coordinated, bistatic imaging in S-band, to be compatible with the Chandrayaan-1 and LRO spacecraft, can unambiguously resolve ice deposits on the Moon Other Coordinated Tech Demos: e.g ranging, rendezvous, gravity Communications demonstration to Various Assets David Everett--LRO Overview

  32. 4 Days to the Moon David Everett--LRO Overview

  33. (M) Trajectory/Orbit Overview Minimum Energy Lunar Transfer: ~ 4 days 30 x 216 km Quasi-frozen Orbit: up to 60 days Lunar Orbit Insertion Sequence (4): 2-4 days 50 km Polar Mapping Orbit: at least 1 year David Everett--LRO Overview

  34. Payload Overview CRaTER Diviner LAMP LOLA LROC +X Mini-RF LEND +Z +Y David Everett--LRO Overview

  35. X Y Z LRO Deployed HGA 3 PANEL MODULAR SOLAR ARRAY Diviner ST ST PROPULSION MODULE Mini-RF LOLA LAMP THRUST INSTRUMENT MODULE Diviner LROC SUN MOON David Everett--LRO Overview

  36. X Y Z LRO Deployed CRaTER INSTRUMENT MODULE (OPTICAL BENCH) AVIONICS MODULE HGA LEND Mini-RF THRUST SUN 3 PANEL MODULAR SOLAR ARRAY MOON David Everett--LRO Overview

  37. Launch Vehicle Configuration ATLAS V , DELTA-IV Interfaces 1194 mm PAF Fairing Access – 3 Doors T-zero GN2 Purge System Two 61 Pin Umbilical Connectors Worst Case EELV Fairing Envelope (4m fairing) Add X axis view (top down) 1194 mm PAF David Everett--LRO Overview

  38. Spacecraft Electrical Overview Mini-RF Omnis LROC Low-Rate Cmds & Tlm S-Xpndr SpaceWire Network Hi-Rate Tlm HGA LAMP Ka-Xmtr LAMP Sci. & HK ATA C&DH 20MHz USO 9500 DDA LOLA HGA Gimbals Thermistors Closed Loop Htrs ST(2) LEND GIMBALCONROL IRW(4) CSS(10) Diviner Unsw. + 28V IMU MIL-STD-1553 Network CRaTER Battery Solar Array Sw. and Unsw. +28V Pwr Services PSE PDE Propulsion GIMBALCONTROL SA & HG Deploy Actuation SA Gimbals Vehicle Separation Break Wires David Everett--LRO Overview

  39. LRO Data Generation David Everett--LRO Overview

  40. (M) Narrow FOV Coverage LOLA 1-month 2-month 4-month 8-month David Everett--LRO Overview

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