1

National Aeronautics and Space Administration National Aeronautics and Space Administration

KPLO, ISECG, et al…

Ben Bussey

Chief Exploration Scientist

Human Exploration & Operations Mission Directorate,

NASA HQ

2

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

3

EM-1 Secondary Payloads

3

INTERIM

CRYOGENIC

PROPULSION

STAGE

13 CUBESATS

SELECTED TO FLY ON

EM-1 • Lunar Flashlight

• Near Earth Asteroid Scout

• Bio Sentinel

• LunaH-MAP

• CuSPP

• Lunar IceCube

• LunIR

• EQUULEUS (JAXA)

• OMOTENASHI (JAXA)

• ArgoMoon (ESA)

• STMD Centennial Challenge Winners

3

4 4

Orbit: • Elliptical: 20-9,000 km

• Orbit Period: 12 hrs

• Sci Pass: ~10min

Lunar Flashlight Overview

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

Phases • Launch: SLS EM1

• LOI: Launch +6 months

• Design Review: July, 2016

• Phase E: >1 year

Measurement Approach:

• Lasers in 4 different near-IR bands illuminate the lunar surface with a 3° beam (1 km spot).

• Light reflected off the lunar surface enters the spectrometer to distinguish water ices from regolith.

Teaming:

JPL-MSFC

S/C (6U - 14 kg): JPL

Mission Design & Nav: JPL

Propulsion: Green Prop (MSFC)

Payload: 1-2 micron Spectrometer

I&T: JPL

5

Lunar IceCube

5

Critical Milestones

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 • Busek BIT 3 - High isp RF Ion Engine

• NASA GSFC BIRCHES - Miniaturized IR Spectrometer - characterize water

and other volatiles with high spectral resolution (5 nm) and wavelength

range (1 to 4 μm)

• Space Micro C&DH - Inexpensive Radiation-tolerant Subsystem

• JPL Iris v. 2.1 - Ranging Transceiver

• BCT- XACT - ADCS w/ Star Tracker and Reaction Wheels

• Custom Pumpkin - High Power (120W) CubeSat Solar Array

Current Status Team is preparing for CDR. All critical / long-

lead Flight hardware has been ordered.

FlatSat with non rad-hard subsystems and

emulators is in development

Trajectory, navigation, and thermal models

along with communications links, mass,

volume and power budgets evolving

6

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

7

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

8

LROC Imaging Permanently Shadowed Regions (PSR)

Reflection

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

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

Sunlight nearly a point source Diffuse reflected light illuminates PSR

8

9

• 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

• Equity and debt financing

• Transportation service customer agreements

• 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

• Software

• Technical and financial milestones

• Partners:

• Astrobotic Technology

• Masten Space Systems

• Moon Express

• http://www.nasa.gov/lunarcatalyst

Close Technical Collaboration

Leveraging NASA expertise (Above: NASA Mighty Eagle &

Morpheus vehicles)

Technology and System

Development and Testing 9

Through Lunar CATALYST,

NASA is helping partners

lower risks, conduct tests,

and accelerate vehicle

development to launch

Overview

10

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

11

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

12

• 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.

ISECG Science White Paper

13

• 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

Science Enabled by Human Exploration

14

• 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

Deep Space Gateway (DSG) Science Study

15

• 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

Workshop Steering Committee

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)

16

Two Parallel Activities

1. Provide initial documentation of potential scientific resource needs

to DSG engineers

2. Plan early-2018 DSG instrument workshop

Next Steps

17

• 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)

Next Steps

1. DSG Resources Provide first-order end member numbers of potential instrument resources to

DSG engineers

18

DSG Orbits

Orbit Type Orbit Period Lunar (or L-Point)

Amplitude Range

Earth-Moon

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

19

• 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

Next Steps

2. DSG Instrument Workshop

Plan early-2018 DSG instrument workshop

20

• 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

Workshop Format

21

Thank you!

22

Resource Prospector – The Tool Box

Neutron Spectrometer System (NSS) • Water-equivalent hydrogen > 0.5 wt%

down to 1 meter depth with 2 m spatial

sampling

NIR Volatiles Spectrometer System

(NIRVSS) • Surface H2O/OH identification (1.6-3.4

mm)

• 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)

Sensor Module (HVPS and Front-End

Electronics)

Thermal neutron

detector

Epithermal neutron

detector Data Processing

Module

23

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

24

Resource Prospector – The Tool Box

Oxygen & Volatile Extraction

Node (OVEN) • Volatile Content/Oxygen Extraction

by step-wise sample heating (150 to

450C)

• Total sample volume & mass

Lunar Advanced Volatile

Analysis (LAVA) • Analytical volatile identification and

quantification in delivered sample

with GC/MS

• Measure water content of regolith at

0.5% (weight) or greater

• Characterize volatiles of interest

below 70 AMU

0

500

1000

1500

2000

2500

3000

3500

4000

0 1000 2000 3000

INT

EN

SIT

Y (

CO

UN

TS

)

CHANNEL

Mass spectrum of air measured using TRL5

mass spectrometer system.

Processing & Analysis

Nitrogen

LAVA MS ETU

OVEN RP15 ETU