Lunar Flashlight Project

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Alexia Todd
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ABSTRACT Recent observations of the Moon with the Moon Mineralogy Mapper (M3), Lunar Crater Observation and Sensing Satellite (LCROSS), the Lunar Reconnaissance Orbiter (LRO) and other evidence

1 ABSTRACT Recent observations of the Moon with the Moon Mineralogy Mapper (M3), Lunar Crater Observation and Sensing Satellite (LCROSS), the Lunar Reconnaissance Orbiter (LRO) and other evidence suggest that there are operationally useful quantities of water on the Moon. In order to address the knowledge gap about the Composition/ quantity/distribution/form of water/h species and other volatiles associated with lunar cold traps, a CubeSatbased method will be deployed as a secondary payload on the Exploration Mission-1 (EM-1) Space Launch System (SLS) flight to locate ice deposits in the Moon s permanently-shadowed craters. ANTICIPATED BENEFITS To NASA funded missions: The launch of this mission will prove the capability of 6U CubeSats as a viable capability for scientific measurements, deep-space communications, and radiation-hardened electronics. To NASA unfunded & planned missions: New low cost capability for scientific observations in deep space To other government agencies: High reliability capability for scientific observations To the commercial space industry: Solar sail manufacture High reliability CubeSat capability for scientific observations DETAILED DESCRIPTION This mission will search for and map surface volatile species and distribution (uniform or patchy) in the permanentlyshadowed craters. The Lunar Flashlight, which after its launch and delivery as a secondary payload on EM-1, will maneuver to Table of Contents. Abstract Anticipated Benefits Detailed Description Technology Maturity Management Team U.S. Work Locations and Key. Partners Technology Areas Details for.. Technology Details for.. Technology Lowest: 4 Highest: 8 Management Team Program Director: Jason Crusan Program Executive: Jitendra Joshi Continued on following page. Page 1

2 its lunar polar orbit propulsively using the solar sail, then use the same solar sail as a mirror to steer sunlight into permanentlyshaded craters while a spectrometer measures the surface compositional mix among rock/dust regolith, H2O, CH4, CO2, and possibly NH3. By Locating the potential ice deposits in the Moon s permanently-shadowed craters, this mission will address the Strategic Knowledge Gaps (SKGs) associated with the composition, quantity, distribution, form of water/h species, and other volatiles associated with lunar cold traps. The development of this Interplanetary CubeSat concept builds on: JPL's Interplanetary Nano-Spacecraft Pathfinder In Relevant Environment (INSPIRE) mission; MSFC s intimate knowledge of the SLS and EM-1 mission; Morehead State University s education-driven CubeSat program; small business development of solar-sail hardware; and JPL experience with specialized miniature sensors and deep-space exploration. U.S. WORK LOCATIONS AND KEY PARTNERS Management Team (cont.) Project Manager: John Baker Principal Investigator: Barbara Cohen Co-Investigator: Paul Hayne In-Space Propulsion Technologies (TA 2) Non-Chemical Propulsion (TA 2.2) Solar and Drag Sail Propulsion (TA 2.2.2) Solar Sail Propulsion (TA ) Robotics and Autonomous Systems (TA 4) Low Areal Density, High Strength and Stiffness Nanofiber Solar Sails (Passive) (TA ) Adaptive Nanofibers for Steerable Solar Sails (TA ) U.S. States With Work Lead Center: Jet Propulsion Laboratory Page 2

3 Supporting Centers: Marshall Space Flight Center NASA Headquarters Other Organizations Performing Work: Morehead State University DETAILS FOR TECHNOLOGY 1 Technology Title Deep Space 6U CubeSat Technology Description This technology is categorized as a hardware system for unmanned flight The 6U CubeSat will use rad-hardened avionics and miniaturized attitude control subsystems for deep space. Capabilities Provided High reliability CubeSats can be used for low cost space exploration. The components and subsystems developed for the Lunar Flashlight will enable future deep-space CubeSat missions, especially with advances in radiation-hardened electronics and communications. Potential Applications Low cost science measurements can be made in the inner solar system. Also, safety for larger science missions can be enhanced by sending probes into risky environments. Additionally, distributed fields and atmospheric measurements can now be made. Secondary Technology Area: Non-Chemical Propulsion (TA 2.2) Solar and Drag Sail Propulsion (TA 2.2.2) Other : Robotics and Autonomous Systems (TA 4) Start: 4 Current: 5 Estimated End: 8 Page 3

4 Performance Metrics Metric Unit Quantity Voulme 1 6 Liters Mass 1 14 kg DETAILS FOR TECHNOLOGY 2 Technology Title Solar Sails Technology Description This technology is categorized as a hardware subsystem for unmanned spaceflight Solar sail propulsion uses the Sun's solar radiation pressure to propel vehicles through space by reflecting solar photons from a large, mirror-like sail made of a lightweight, reflective material. The continuous photonic pressure provides propellantless thrust to hover indefinitely at points in space or to conduct orbital maneuver plane changes more efficiently than conventional chemical propulsion. Because the Sun supplies the necessary propulsive energy, solar sails require no onboard propellant, thus reducing payload mass. Capabilities Provided Propulsion, deep-space radiation hardened electronics, deepspace communications for CubeSats. Primary Technology Area: In-Space Propulsion Technologies (TA 2) Solar Sail Propulsion (TA ) Secondary Technology Area: Other : Low Areal Density, High Strength and Stiffness Nanofiber Solar Sails (Passive) (TA ) Adaptive Nanofibers for Steerable Solar Sails (TA ) Potential Applications Small Satellites for deep-space missions Propulsion technology for future robotic missions Page 4

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Lunar Flashlight & NEA Scout A NanoSat Architecture for Deep Space Exploration

National Aeronautics and Space Administration Lunar Flashlight & NEA Scout A NanoSat Architecture for Deep Space Exploration Payam Banazadeh (JPL/Caltech) Andreas Frick (JPL/Caltech) EM-1 Secondary Payload