NationalNational Aeronautics Aeronautics and Space and Administration Space Administration

KPLO, ISECG, et al…

Ben Bussey Chief Exploration Scientist Human Exploration & Operations Mission Directorate, NASA HQ

1 Strategic Knowledge Gaps

• SKGs define information that is useful/mandatory for designing human spaceflight architecture • Perception is that SKGs HAVE to be closed before we can go to a destination, i.e. they represent Requirements • In reality, there is very little information that is a MUST HAVE before we go somewhere with humans. What SKGs do is buy down risk, allowing you to design simpler/cheaper systems. • There are three flavors of SKGs 1. Have to have – Requirements 2. Buys down risk – LM foot pads 3. Mission enhancing – Resources • Four sets of SKGs – Moon, Phobos & Deimos, Mars, NEOs www.nasa.gov/exploration/library/skg.html

2 EM-1 Secondary Payloads

13 CUBESATS SELECTED TO FLY ON INTERIM EM-1 CRYOGENIC PROPULSION • Lunar Flashlight STAGE • Near Earth Asteroid Scout • Bio Sentinel • LunaH-MAP • CuSPP • Lunar IceCube • LunIR • EQUULEUS (JAXA) • OMOTENASHI (JAXA) • ArgoMoon (ESA) • STMD Centennial Challenge Winners

3 3 3 Lunar Flashlight Overview

Looking for surface ice deposits and identifying favorable locations for in-situ utilization in lunar south pole cold traps

Measurement Approach:

• Lasers in 4 different near-IR bands illuminate the lunar surface with a 3° beam (1 km spot). Orbit: • Light reflected off the lunar • Elliptical: 20-9,000 km surface enters the spectrometer to • Orbit Period: 12 hrs distinguish water ices from • Sci Pass: ~10min regolith.

Phases Teaming: • Launch: SLS EM1  JPL-MSFC • LOI: Launch +6 months  S/C (6U - 14 kg): JPL • Design Review: July, 2016  Mission Design & Nav: JPL • Phase E: >1 year

 Propulsion: Green Prop (MSFC)  Payload: 1-2 micron Spectrometer  I&T: JPL 4 4 Lunar IceCube

Mission Description and Objectives Lunar IceCube is a 6U small satellite whose mission is to prospect for water in ice, liquid, and vapor forms and other lunar volatiles from a low-perigee, inclined lunar orbit using a compact IR spectrometer. 1.) Lunar IceCube will be deployed by the SLS on EM-1 and 2.) use an innovative RF Ion engine combined with a low energy trajectory to achieve lunar capture and a science orbit of 100 km perilune. Strategic Knowledge Gaps 1-D Polar Resources 7: Temporal Variability and Movement Dynamics of Surface- Correlated OH and H2O deposits toward PSR retention

1-D Polar Resources 6: Composition, Form and Distribution of Polar Volatiles

1-C Regolith 2: Quality/quantity/distribution/form of H species and other volatiles in mare and highlands regolith (depending on the final inclination of the Lunar IceCube orbit)

Technology Demonstrations Current Status • Busek BIT 3 - High isp RF Ion Engine Team is preparing for CDR. All critical / long- • NASA GSFC BIRCHES - Miniaturized IR Spectrometer - characterize water lead Flight hardware has been ordered. and other volatiles with high spectral resolution (5 nm) and wavelength FlatSat with non rad-hard subsystems and range (1 to 4 μm) emulators is in development • Space Micro C&DH - Inexpensive Radiation-tolerant Subsystem • JPL Iris v. 2.1 - Ranging Transceiver Trajectory, navigation, and thermal models • BCT- XACT - ADCS w/ Star Tracker and Reaction Wheels along with communications links, mass, Critical• Custom MilestonesPumpkin - High Power (120W) CubeSat Solar Array volume and power budgets evolving

5 5 Korea Pathfinder Lunar Orbiter (KPLO)

• KPLO is KARI’s (Korea Aerospace Research Institute) first lunar mission

• KARI has offered NASA a payload opportunity on KPLO, and participation in joint Science teams – NASA planning a PS program – Call for PS expected in FY18 ROSES

• HEOMD is flying ShadowCam to acquire data that help address SKGs

• Complements KARI instruments – LUTI, PolCam, KGRS, KMAG

6 Korea Pathfinder Lunar Orbiter (KPLO)

• From a 100 km altitude, ShadowCam will provide a pixel scale of 1.7 m over a ~5 km wide swath

• ShadowCam is derived from the LROC NAC – 500 times for sensitive – TDI

• Science significance: NASA SKGs addressed: – Spatial and temporal distribution of volatiles – Monitor movement of volatiles within PSRs – Reveal the geomorphology, accessibility, and geotechnical characteristics of cold traps

7 LROC Imaging Permanently Shadowed Regions (PSR)

Nominal NAC mosaic of Main L PSR NAC image of Main L interior Reflection

Sunlight nearly a point source Diffuse reflected light illuminates PSR

Main L (D: 14 km, 81.4°N, 22.8°E), Red = LOLA derived PSR boundaries8

8 Overview

• In 2014, NASA competitively selected U.S. private-sector partners, based on likelihood of successfully fielding a commercially-viable lunar surface cargo transportation capability • Evaluation criteria included: • Technical approach and development schedules • Technical risks and mitigation plans • Business plans and market strategies Leveraging NASA expertise • Equity and debt financing (Above: NASA Mighty Eagle & • Transportation service customer agreements Morpheus vehicles)

• Lunar CATALYST Space Act Agreement (SAA) Partnerships • Term: 3 years (2014-2017) with option to extend • No-funds-exchanged • Substantial in-kind contributions from NASA (~$10M/year) • Technical Expertise • Test Facilities • Equipment loans Close Technical Collaboration • Software Through Lunar CATALYST, • Technical and financial milestones NASA is helping partners • Partners: lower risks, conduct tests, • Astrobotic Technology and accelerate vehicle • Masten Space Systems development to launch • Moon Express Technology and System Development and Testing • http://www.nasa.gov/lunarcatalyst 9 9 Lunar Surface Payload & Transportation RFIs

• Small Lunar Surface Payload RFI (Nov 2016) • NASA RFI to assess availability of payloads that could be delivered to the Moon as early as the 2017-2020 timeframe using emerging U.S. commercial lunar cargo transportation service providers • Payloads should address NASA exploration or science strategic objectives and knowledge gaps • Indicated intent for significant cost-sharing between NASA and payload providers

• Potential Cost-Sharing with Lunar Transportation Service Providers • NASA’s issuance of the RFI stimulated public announcements on payload cost-sharing by two emerging U.S. providers of lunar transportation services:

Moon Express (cost-sharing up to $1.5M): “Will provide up to $500,000 in funding for each instrument selected by NASA to fly aboard the company’s first three commercial lunar missions of opportunity, beginning in 2017”

Astrobotic Technology (cost-sharing up to $12M): “For every payload selected by NASA to fly on Astrobotic’s first mission, Astrobotic will provide an additional flight to payload providers on the company’s second mission at no charge.”

• Lunar Surface Cargo Transportation Services RFI (May 2017) • NASA RFI to asses US commercial capabilities for delivering payloads to the lunar surface • NASA may procure payloads and related commercial payload delivery services to the Moon • Input informs potential plans to procure payloads and related lunar delivery services

10 10 Resource Prospector (RP) Overview

Mission: • Characterize the nature and distribution of water/volatiles in lunar polar sub-surface materials • Demonstrate ISRU processing of lunar regolith

2 kilometers 100-m radius landing ellipse

RP Specs: Mission Life: 6-14 earth days (extended missions being studied) Rover + Payload Mass: 300 kg Total system wet mass (on LV): 3800kg Rover Dimensions: 1.4m x 1.4m x 2m Rover Power (nom): 300W All-Wheel Steering & All-Wheel Drive Nominal speed is 10 cm/s (Prospecting) with sprint speeds of 50 cm/s Launch Vehicle: EELV or SLS

11 ISECG Science White Paper

• ISECG agencies acknowledge science communities as major stakeholders and scientific knowledge gain as an important benefit of, and justification for, human exploration activities • A Science White Paper (SWP) has recently been developed by the international science community – Describes the international view of the science enabled by human exploration after ISS, as outlined in ISECG’s Global Exploration Roadmap – Tasked with considering the three destinations outlined in the GER • DSG in the lunar vicinity, Lunar surface, Asteroids – Engaged the scientific communities in identifying these opportunities – Additional community interaction and feedback provided by presenting initial science ideas at multiple major meetings • SWP incorporated interdisciplinary scientific topics: – Encompass all relevant science communities and disciplines: planetary science, space science, life sciences, astrobiology, astronomy, physical sciences, etc.

12 Science Enabled by Human Exploration

• The places where humans explore, such as a DSG in the lunar vicinity, may not be the “ideal” locations for certain scientific investigations, yet the presence of humans and their associated infrastructure provides opportunities that can yield Decadal relevant science

• Human Exploration permits the emplacement of scientific instruments on a scale different from what scientists/engineers typically consider. – Less mass/power/volume constrained – DSG communications capabilities could relieve pressure for other orbital and surface assets

13 13 Deep Space Gateway (DSG) Science Study

• We are conducting a study to determine in more detail what high-quality science can be conducted from a DSG, and what level of resources are required – Study consists of NASA personnel from NASA centers as well as scientists from academia • Revisit the considerations addressed in the internationally developed Science White Paper from a broad NASA perspective – Consider what Decadal science can be achieved by research on a DSG – What Strategic Knowledge Gaps (SKGs) can be closed • Consider all relevant scientific disciplines – Astronomical Observations – Collecting Interplanetary Material – Heliophysics – Earth’s Atmosphere – Fundamental Physics – Life Sciences – DSG as a Communications Relay • Enable lunar cubesats – Lunar Surface Science Using Telerobotics • Roving or instrument setup • Instrument Scope – Scale of resources that instruments need? • Community Workshop Format

14 14 Workshop Steering Committee

• Jointly sponsored by SMD and HEOMD • Co-convened by NASA HQ, JSC, MSFC, and GSFC • Steering Committee consists of the Executive Committee and a Science Advisory Group • Steering committee includes discipline experts from centers, academia, and a representative from ESA – ESA organizing a similar European-focused workshop Executive Committee Science Advisory Group Ben Bussey (HQ/HEOMD) Jake Bleacher (GSFC) Ruthan Lewis (GSFC)

Jim Garvin (GSFC) Jack Burns (U. Co.) Clive Neal (Notre Dame) Sasha Marshak (GSFC) Brad Carpenter (HQ) Debra Hurwitz Needham (MSFC) Michael New (HQ/SMD) Caleb Fassett (MSFC) Paul Neitzel (Georg. Tech.) Jim Spann (MSFC) Jennifer Fogarty (JSC) Mike Ramsey (Uni. Pitt.) Eileen Stansbery (JSC) Barbara Giles (GSFC) Julie Robinson (JSC) Executive Secretary Dana Hurley (JHU/APL) Bobbie-Gail Swan (JSC) Paul Niles (JSC) Sam Lawrence (JSC) James Carpenter (ESA)

15 Next Steps

Two Parallel Activities

1. Provide initial documentation of potential scientific resource needs to DSG engineers

2. Plan early-2018 DSG instrument workshop

16 Next Steps 1. DSG Resources Provide first-order end member numbers of potential instrument resources to DSG engineers • Initial list needed by September 2017 to potentially influence DSG design • Instruments could either go on the power/propulsion bus, the habitation module, or the logistics module – Logistics module will have heliocentric disposal orbits • Anticipated resources needed: – Mass – Power – Volume – Data – crew-time – location/preferred orbit(s) 17

DSG Orbits

Orbit Type Orbit Period Lunar (or L-Point) Earth-Moon Amplitude Range Orientation

Low Lunar Orbit (LLO) ~2 hrs 100 km Any inclination

Elliptical Lunar Orbit (ELO) ~14 hrs 100 to 10,000 km Equatorial

Near-Rectilinear Halo Orbit (NRHO) 6 to 8 days 2,000 to 75,000 km Roughly Polar

Earth-Moon L2 Halo 8 to 14 days 0 to 60,000 km (L2) Dependent on size

Distant Retrograde Orbit ~14 days 70,000 km Equatorial

18 Next Steps 2. DSG Instrument Workshop

Plan early-2018 DSG instrument workshop

• First task of the steering committee is to identify how many parallel sessions the workshop should have and what disciplines are covered in each sessions • First step is to identify ~4-5 potential session chairs – This list to be vetted by SMD division directors to ensure a breadth of experience • From this group, select ~3 session chairs per session – These people will handle abstract review, put the detailed session together, and run the session

19 Workshop Format

• Based on the successful Tempe Lunar Science Workshop held in 2007 • Attendance will be by invitation only based on an open call for presentations – Scientists, engineers, program managers, and decision/policy makers from NASA, academia, industry, and international organizations • Two types of sessions: discipline-focused splinter sessions and final plenary – The bulk of the workshop will consist of parallel discipline- focused splinter sessions, during which potential science areas enabled by exploration are presented, discussed, and eventually synthesized to instrument concepts – Final day plenary session to summarize results and discuss the next strategic steps for how workshop content will be captured and disseminated

20 Thank you!

21 Resource Prospector – The Tool Box

Epithermal neutron Data Processing Neutron Spectrometer System (NSS) detector Module • Water-equivalent hydrogen > 0.5 wt% down to 1 meter depth with 2 m spatial sampling

NIR Volatiles Spectrometer System (NIRVSS) Sensor Module Thermal neutron • Surface H2O/OH identification (1.6-3.4 (HVPS and Front-End mm) Electronics) detector • Subsurface sample characterization (with drill) • Multi-color imaging of drill cuttings/surface (eight colors between 0.4-1.1 mm) • Scene thermal radiometry (8, 10, 14 & 25 mm)

22 Resource Prospector – The Tool Box

Drill • Subsurface sample acquisition down to 1 meter in 0.1 m “bites” • Auger for fast subsurface assay with NIRVSS • Sample transfer to OVEN for detailed subsurface assay

Cuttings exit

23 Resource Prospector – The Tool Box

LAVA MS ETU Processing & Analysis

Oxygen & Volatile Extraction Node (OVEN) • Volatile Content/Oxygen Extraction by step-wise sample heating (150 to 450C) • Total sample volume & mass 4000 Lunar Advanced Volatile 3500 Nitrogen Analysis (LAVA) 3000 • Analytical volatile identification and 2500 quantification in delivered sample with GC/MS 2000 • Measure water content of regolith at 1500

0.5% (weight) or greater 1000 INTENSITY(COUNTS) • Characterize volatiles of interest 500 below 70 AMU OVEN RP15 ETU 0 0 1000 2000 3000 CHANNEL

Mass spectrum of air measured using TRL5 mass spectrometer system.

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