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NASA's Space Launch System: Deep Space Access for CubeSats

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 https://ntrs.nasa.gov/search.jsp?R=20190033309 2020-03-03T20:01:26+00:00Z

70th International Astronautical Congress (IAC), Washington D.C., United States, 21-25 October 2019.

IAC-19,B4,5,5,x51284
NASA’s Space Launch System: Deep Space Access for CubeSats

Stephen D. Creecha, Dr. Kimberly F. Robinson b, Renée Cox c

a
Spacecraft/Payload Integration & Evolution Office, NASA’s Space Launch System, Marshall Space Flight Center,
Huntsville, AL 35812 U. S. A., steve.creech@nasa.gov
b
Spacecraft/Payload Integration & Evolution Office, Space Launch System, Marshall Space Flight Center,
Alabama, 35812, AL, USA, kimberly.f.robinson@nasa.gov
c
Spacecraft/Payload Integration & Evolution Office, Space Launch System, Marshall Space Flight Center,
Alabama, 35812, AL, USA, renee.cox@nasa.gov

Abstract
NASA is embarking on a new generation of missions to the Moon, known as the Artemis program. The Agency’s
new super heavy-lift launch vehicle, the Space Launch System (SLS), is a critical enabling capability for these
efforts, which will serve as a proving ground for future crewed expeditions to Mars. SLS is designed to return
astronauts to the Moon in the Orion spacecraft and to launch more mass and provide more volume for critical
payloads than commercially available vehicles, giving NASA a unique asset for deep space exploration. When
performance margin and volume is available, as it is on the first flight, Artemis I (previously Exploration Mission-1),
SLS can offer CubeSats access to deep space, beyond Earth’s orbit. The Artemis I flight has 13 6U (14 kg) CubeSats
manifested, and the Program is currently accepting proposals for 6U and 12U payloads for the Artemis II flight
through the agency’s CubeSat Launch Initiative (CSLI) program. Proposals from U.S.-based payload developers to
fly on Artemis II will be accepted through CSLI until November 4, 2019. When ridesharing on SLS deep space
missions, CubeSats must demonstrate they will not interfere with primary mission objectives. The 13 Artemis I
CubeSats that hail from industry, academia, NASA and its international partners represent an array of exciting deep
space science investigations and technology demonstrations that may help inform future Artemis missions. The
initial SLS Block 1 vehicle for the Artemis I flight is fully manufactured; several elements are complete and have
been delivered to the Exploration Ground Systems (EGS) Program at Kennedy Space Center (KSC), which has
responsibility for integrating and launching the SLS and Orion stack. Completed elements of the Artemis I vehicle
include the Orion Stage Adapter (OSA), which houses the 13 Artemis I CubeSats. With the Artemis I flight hardware
and software nearing completion, work is in progress for the second Block 1 launcher, designated for the crewed
Artemis II flight. Hardware is being manufactured for every element of the Artemis II vehicle. In this paper, the
author will review the status of the Artemis I vehicle and the payloads manifested for the initial flight. Information
on the Secondary Payload Deployment System (SPDS) that the SLS Program provides to payload developers will
also be included.
Keywords: NASA, Space Launch System, heavy-lift, CubeSats, Artemis I, Artemis II

Acronyms/Abbreviations Mobile Launcher (ML), Secondary Payload

Space Launch System (SLS), CubeSat Launch Deployment System (SPDS), Stennis Space Center
Initiative (CSLI), Exploration Ground Systems (EGS), (SSC), commercial-off-the-shelf (COTS). thrust vector
Orion Stage Adapter (OSA), Evolved Expendable control (TVC), Marshall Space Flight Center (MSFC),
Launch Vehicle (EELV) Secondary Payload Adapter Ames Research Center (ARC), Strategic Knowledge
(ESPA), Space Shuttle Main Engines (SSMEs), Gaps (SKGs), Foreign Object Debris (FOD), Deep
Exploration Upper Stage (EUS), Interim Cryogenic Space Network (DSN), radio frequency (RF), avionics
Propulsion Stage (ICPS), Delta Cryogenic Second Stage unit (AU).
(DCSS), United Launch Alliance (ULA) trans-lunar
injection (TLI), Universal Stage Adapter (USA), 1. Introduction

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NASA is executing an ambitious timetable for

returning to the Moon [1], known as the Artemis
program. The agency remains committed to human
exploration of Mars, and returning NASA’s human
exploration program to the Moon in the 21st century will
serve as a proving ground for numerous new
technologies needed to enable human exploration of the
Red Planet. The super heavy-lift Space Launch System
(SLS), with unrivalled capability to lift more mass and
provide more volume for strategic payloads is the
backbone for NASA’s Moon to Mars exploration
missions (see Figure 2). The vehicle has a planned
upgrade path that will enable human exploration of
Mars and game-changing science missions to be
launched deep into the solar system. The Gateway lunar
outpost and the Orion spacecraft will also play a crucial Figure 2. NASA's deep space exploration system,
role in returning NASA’s human spaceflight program to the Space Launch System (SLS) and Orion,
the Moon. Orion will enable astronauts to stay in deep launching from Kennedy Space Center, can provide
space up to 21 days at a time in the spacecraft; it can rideshare opportunities for CubeSats.
stay docked to Gateway up to six months. Gateway will successful, may inform future Artemis missions.
give NASA and its partners a platform from which to
stage lunar sorties and science missions. Upgraded 2. SLS: Evolvable Launch Capabilities for Artemis
ground processing and launch facilities at Kennedy and Beyond
Space Center (KSC) are preparing to integrate and Designed for a new generation of exploration, SLS
launch SLS and Orion to deep space. will safely send crews in Orion to the Moon and reliably
CubeSats have a key role to play in the Artemis launch NASA’s flagship science payloads deep into the
Program by identifying resources that can be exploited solar system. Available in crew and cargo
in situ, demonstrating new technologies and testing configurations, the vehicle’s planned upgrade path will
communication. Several CubeSats flying on Artemis I culminate in a launcher of unrivalled lift and payload
[see Table 1] will be returning valuable data that, if capacity compared to commercial vehicles (see Figure

Figure 1. NASA's plan to return astronauts to the lunar surface by 2024 includes three SLS/Orion
missions, which can include CubeSats.

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3). The Artemis II crew will surpass the crew of the Apollo
SLS is built on a proven, well-understood and 13 flight and become record-holders for traveling
extensively tested propulsion system. SLS leverages the farthest from Earth.
space shuttle solid rocket boosters and RS-25 liquid All SLS flights will be processed by EGS at KSC,
hydrogen (LH2) and liquid oxygen (LOX) engines with the vehicle integrated on the Mobile Launcher
(formerly the Space Shuttle Main Engines [SSMEs]). (ML), which has been upgraded and renovated to
These elements have been modified to provide more service SLS Block 1 in both crew and cargo
thrust; the RS-25s have also been adapted to operate in configurations. Similar to the space shuttle and the
more extreme environments of SLS compared to the Saturn V vehicles, the SLS stack will be assembled on
shuttle. the ML in the iconic Vehicle Assembly Building (VAB)
A new development, the SLS core stage, includes at KSC (see Figure 1). The vehicle will launch from
the LH2 and LOX propellant tanks, avionics and launch complex 39B at KSC.
housing for the four RS-25 engines. The Interim Following the Block 1 flights, the vehicle will
Cryogenic Propulsion Stage (ICPS) provides in-space evolve to Block 1B and incorporate a more powerful

Figure 3. SLS will evolve to progressively more powerful variants, providing NASA with a unique space
asset for the most demanding human and robotic deep space missions.

propulsion for the Block 1 vehicle. The ICPS is a upper stage. The four-engine LH2/LOX Exploration
modified Delta Cryogenic Second Stage (DCSS), built Upper Stage (EUS) will enable Block 1B to lift at least
by United Launch Alliance (ULA) and Boeing. With the 34 t to TLI in its crew configuration and at least 37 t in
ICPS, SLS Block 1 in the crew configuration will lift at the cargo configuration. The Block 1B cargo
least 26 metric tons (t) to trans-lunar injection (TLI). configuration can accommodate large-diameter
For Block 1 flights, CubeSats are stowed in the Orion payloads in an 8.4 m-diameter cargo shroud in varying
Stage Adapter (OSA), which connects SLS to Orion’s lengths to provide unprecedented volume. For CubeSat
spacecraft adapter. The SLS program supplies a payloads, Block 1B will have volume available in the
Secondary Payload Deployment System (SPDS) in the Universal Stage Adapter (USA), which connects the
OSA for CubeSat deployment. upper stage to Orion on the Block 1B crew variant (see
NASA plans to fly the Block 1 crew variant for the Figure 3).
Artemis I uncrewed test flight and the Artemis II For Mars-enabling capabilities, the ultimate SLS
crewed mission. For Artemis II, four crew members in variant, Block 2, will incorporate upgraded boosters to
Orion will embark on a lunar flyby free-return mission. lift at least 45 t to TLI. Engineers are studying larger-

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diameter fairings in longer lengths for this vehicle, interference, possible ascent hazards, debris
which can launch habitat modules, landers, rovers and characteristics for input to unique range safety data,
other infrastructure for emplacement in Martian orbit or joint loads and environments, payload re-contact
on the surface prior to the arrival of crew. analysis (nominal mission scenarios) and more.
CubeSats in 6U and 12U form factors, as well as In addition, payload developers are responsible for
accommodations for other small payloads, such as securing RFs and arranging any ground communication
Evolved Expendable Launch Vehicle (EELV) services (i.e. amateur radio, near-Earth network, Deep
Secondary Payload Adapter (ESPA)-class, are currently Space Network (DSN), etc.). Once mission managers
being evaluated for the Block 1B and Block 2 vehicles. establish frequencies that SLS and Orion will use,
payload developers must verify their frequencies do not
3. Artemis I CubeSats overview interfere with vehicle frequencies.
For the first flight of SLS and Orion, NASA allotted
13 of 17 possible slots for 6U form factor payloads, 4. CubeSat deployments on SLS Block 1
weighing no more than 14 kg, to ride along on the test Artemis I is planned as an approximately 25-day
flight and be deployed to deep space. In addition to the mission that will include an extended stay in high-Earth
opportunity to reach deep space, SLS offers CubeSat orbit for a thorough systems checkout before
payload developers the opportunity to include
propulsion systems on their payloads.
Several Artemis I CubeSats are performing exciting
research in deep space that can contribute to future
robotic and human lunar missions. BioSentinel, a
payload from NASA’s Ames Research Center (ARC),
aims to develop a biosensor that will evaluate the
impact of deep space radiation on living organisms over
long durations beyond low-Earth Orbit (LEO).
BioSentinel uses yeast to carry out this study, which
requires a deep space environment.
LunaH-Map, developed by Arizona State
University, will map hydrogen in permanently shaded
craters near the lunar South Pole. NASA has identified
Shackleton Crater, near the South Pole, as its preferred
lunar landing site partially because of the discovery of
water ice in its permanently shadowed crater [2]. Areas
such as this are considered high-priority influences for
future surface activities; data returned by LunaH-Map
could be prove beneficial. Similarly, Morehead State
University’s Lunar IceCube payload will search for
water in solid, liquid and vapor states from an orbit
about 100 km over the lunar surface. Human or robotic
explorers may be able to exploit water ice identified by
Lunar IceCube for any number of needs, including life
support and propellant production. Lockheed Martin’s
LunIR payload will use a miniature high-temperature
Mid-Wave Infrared (MWIR) sensor to characterize the
lunar surface, which could assist in future lander site
selection.
CubeSats flying on SLS missions must not interfere
with the primary mission, which is a thorough systems
check of ground processing and launch facilities, as
well as testing of SLS and Orion in a flight
environment. To prepare for flight, payload developers
work with NASA through a series of payload safety
reviews to ensure CubeSats cause no harm to the
primary mission or the vehicles. Payload safety reviews
are phased over time and cover payload handling and Figure 4. Elements of the SLS Block 1 crew
physical processing hazards, radio frequency (RF) vehicle.

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committing to TLI. The ICPS will provide the burn to and an avionics unit (AU). The AU is activated after the
send Orion to TLI. After separation from Orion, the TLI burn and near the completion of the disposal
stage will perform a series of maneuvers to insert itself maneuvers. The AU receives simple discrete signals
into a heliocentric disposal trajectory. The ICPS will be from the ICPS to start a pre-coordinated, pre-loaded,
pointed at a 55-degree beta angle to the sun to give the autonomous deployment sequence; it has a battery life
payloads the best thermal conditions possible. The of 10 days after on-orbit activation. For 6U CubeSats, a
stage will put itself into a 1 revolution per minute (rpm) vibration isolation/mitigation system is also provided.
barbecue roll. The stage will vent any remaining Payload dispensers are commercial-off-the-shelf
hydrazine, take a final set of readings, downlink them (COTS) models. The SPDS mounting bracket design
and shut down. Prior to final shutdown, the stage will includes connector mounting and dispenser interfaces.
send an activation signal to the SPDS, initiating the The 6U brackets are designed to hold up to 60 lbs.; most
CubeSat deployment process. payloads with the COTS dispenser are expected to
The deployment window for the CubeSats is near weigh about 47 lbs. Based on the maximum allowable
the completion of ICPS disposal maneuvers to about 10 payload mass for a 6U dispenser, an ejection rate of 3.9
days post-launch. To give payload developers an idea of +/ -0.2 feet/sec (1.2 +/- 0.06 m/sec) is anticipated.
the timelines involved and some deployment windows Technicians at MSFC installed the SPDS in the OSA
that could be beneficial for missions, SLS engineers and tested the avionics prior to shipping to EGS. Once
identified several “bus stops” from which payload payloads are mounted in the OSA, payload batteries can
developers can choose to release payloads. be charged. Once batteries are charged and the OSA
Thermal conditions are one of several factors each with the payloads installed moves to the VAB for
payload developer considered when determining which stacking, no additional access to the payloads is
bus stop to use for payload deployment. In addition to possible.
thermal environments, payload developers considered
flight time to the Moon, which affects propellant usage; 5. Artemis I Payload Manifest
radiation conditions (see Figure 6), mission goals, ICPS Payload developers from industry, government,
attitude stability and more. After considering these academia and international partners have 6U CubeSats
factors, each payload developer selected its final bus manifested on Artemis I. Three payloads are competing
stop, or deployment location. for prize money in the CubeQuest Challenge, part of
For both Artemis I and II Block 1 flights, the SLS NASA’s Centennial Challenges. Outside of the three
Program supplies mounting brackets, cable harnesses CubeQuest missions, which earned slots based on their
performances in qualifying ground
tournaments, the remaining ten
CubeSats were selected based on the
possibilities of returning data to address
identified Strategic Knowledge Gaps
(SKGs) [3]. Mission planners will use a
more focused set of criteria to evaluate
proposals for CubeSats to fly on
Artemis II, choosing payloads that will
support the Artemis program by
addressing lunar or Martian SKGs that
will support returning humans to the
Moon and exploring onward to Mars.
See Table 1 for a complete listing of
CubeSat missions manifested on
Artemis I.

Figure 5. The SLS Secondary Payload Deployment System (SPDS) includes mounting brackets, a
vibration isolation system and a commercial-off-the-shelf (COTS) dispenser.

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Table 1. Artemis I SLS Payload Manifest.

Payload Developer(s) Sponsor Destination Mission

ArgoMoon Argotec Agenzia Spaziale Geocentric orbit with Photograph the ICPS,
Italiana (ASI) high eccentricity and CubeSat deployment, the
apogee close to the Earth and Moon using
Moon HD cameras and
advanced imaging
software
Biosentinel NASA Ames, NASA NASA Advanced Heliocentric orbit via Use yeast as a biosensor
Johnson, Loma Linda Exploration Systems lunar flyby to evaluate the effects of
University Medical (AES) ambient space radiation
Center, University of on DNA
Saskatchewan
Cislunar Cornell University NASA Cube Quest Lunar orbit Demonstrate use of an
Explorers Challenge, sponsored by inert water-based
NASA’s Science propulsion system for
Technology Mission lunar gravity assists and
Directorate capture in lunar orbit;
(STMD) Centennial compete in NASA’s
Challenges Deep Space Derby
CubeSat to Study Southwest Research NASA Science Mission Deep space Study the sources and
Solar Particles Institute, NASA Directorate (SMD) acceleration mechanisms
(CuSP) Goddard of solar and
interplanetary particles in
near-Earth orbit
EQUilibriUm University of Tokyo Japanese Aerospace Earth-Moon L2 point Demonstrate trajectory
Lunar-Earth point Exploration Agency control techniques within
6U Spacecraft (JAXA) the Sun-Earth-Moon
(EQUULEUS) region and image Earth’s
plasmasphere
Lunar IceCube Morehead State NASA Next Space Lunar orbit Search for water (and
University, NASA Technologies for other volatiles) in ice,
JPL, NASA Goddard, Exploration liquid and vapor states
BUSEK Partnerships using infrared
(NextSTEP) spectrometer
Lunar Flashlight NASA JPL NASA AES Lunar orbit Search for ice deposits
using near-infrared band
lasers
Lunar-Polar Arizona State NASA SMD Lunar orbit Perform neutron
Hydrogen University spectroscopy to
Mapper (LunaH- characterize abundance of
Map) hydrogen in permanently
shaded craters
LunIR Lockheed Martin NASA NextSTEP Heliocentric orbit via Use a miniature high-
Space Systems lunar flyby temperature Mid-Wave
Infrared (MWIR) sensor
to characterize the lunar
surface
Near Earth NASA Marshall NASA AES NEA within ~1.0 AU Detect target NEA,
Asteroid (NEA) of Earth perform reconnaissance
Scout and close proximity
imaging
Outstanding Institute of Space and JAXA Lunar surface Develop world’s smallest
MOon Astronautical Science lunar lander and observe
exploration (ISAS)/JAXA lunar radiation
Technologies environment

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demonstrated by
Nano Semi-Hard
Impactor
(OMOTENASHI)
Team Miles Miles Space, LLC NASA Cube Quest Deep space Demonstrate propulsion
Challenge using plasma thrusters;
compete in NASA’s
Deep Space Derby
University of University of NASA Cube Quest Deep space Demonstrate use of solar
Colorado-Earth Colorado in Boulder Challenge radiation pressure for
Escape Explorer propulsion; compete in
(CU-E3) NASA’s Deep Space
Derby
5.1 Vicinity of bus stop one developer of the smallest lunar lander to date and the
Payloads are deployed in one-minute intervals to fourth country to successfully land on the Moon.
reduce likelihood of contact. The first bus stop, about Lunar Flashlight, BioSentinel, ArgoMoon, Cislunar
four hours post-launch, is between Earth’s two Van Explorers and Lunar IceCube also plan to deploy at bus
Allen Belts. Two missions from JAXA, stop 1. About 90 minutes after the ICPS clears the first
OMOTENASHI and EQUULEUS, will deploy at this Van Allen Belt, Near Earth Asteroid (NEA) Scout, a
time. The OMOTENASHI CubeSat will use a solid NASA Marshall Space Flight Center (MSFC) mission
rocket motor to attempt a lunar landing. If successful, equipped with a solar sail to rendezvous with an
OMOTENASHI will provide JAXA with two firsts: asteroid, will deploy.

Figure 6. Radiation exposure to Artemis I payloads from the first deployment opportunity to the Moon.

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Figure 7. Vibration mitigation system for Artemis I 6U CubeSats.

the final three smallsats will be released: CuSP, Team

5.2 Vicinity of bus stop two Miles and CU-E3. At this time, no payload developers
After the ICPS has cleared both radiation belts, the have chosen to deploy payloads at bus stops three or
LunaH-Map payload will be released. About one hour four.
after clearing the radiation belts, at bus stop two,
6. Artemis II Opportunities for CubeSats
Lockheed Martin’s LunIR spacecraft will deploy. Using
For the second flight of SLS and Orion, Artemis II,
a miniature high-temperature Mid-Wave Infrared
mission planners expect to be able to accommodate a
(MWIR) sensor to collect spectroscopy and
limited number of 6U and 12U form factor payloads.
thermography data, LunIR will provide data related to
Similar to Artemis I, payloads selected for the Artemis
surface characterization, remote sensing and site
II flight should address SKGs. Specifically, the agency
selection for lunar future missions.
is looking for smallsat research missions that will
reduce risk on future human spaceflight missions. For
5.3 Vicinity of bus stop five
Artemis II, outbound travel to the Moon will be about
At bus stop 5, about 12 hours after the ICPS passes
five days. At closest approach to the Moon, the ICPS
the Moon and uses its gravity to enter heliocentric orbit,
will pass approximately 260 km from the lunar surface.

Figure 8. Anticipated ejection velocity of 6U payloads released from SLS SPDS on Artemis I.

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Because Artemis II is also a Block 1 flight, payloads

will be stowed in the OSA, as in the Artemis I flight.
The SPDS provided will be similar.

7. Artemis I Vehicle Status

The first SLS Block 1 vehicle is fully manufactured,
with several elements complete and delivered to EGS,
including the OSA with the SPDS for the 13 Artemis I
6U CubeSats (see Figure 10). In addition to the OSA,
the Artemis I ICPS is complete and delivered to EGS.
The SLS solid rocket boosters, based on the space
shuttle boosters but larger and more powerful, are
largely complete for the first mission. The solid-fuel
motors, with new asbestos-free insulation, have five
propellant segments compared to the shuttle’s four-
segment boosters. The extra propellant segment gives
the boosters 20 percent more thrust; each provides 3.6 Figure 9. An aft skirt for the Artemis I solid
million pounds of thrust. The motors for the Artemis I rocket boosters is nearly complete at Kennedy Space
flight are complete and will ship to KSC in the coming Center (KSC). Four booster separation motors are
months. Forward and aft sections of the boosters, visible.
including the thrust vector control (TVC) systems in the
aft skirts, are nearing completion (see Figure 9).
The four RS-25 engines designated for the Artemis I
flight are also complete. The SLS Program has 16 RS-
25s remaining from the Space Shuttle Program. The
engines have been upgraded with new controllers. A
series of hot-fire tests at Stennis Space Center (SSC) has
qualified the engines to operate in the SLS
environments. The four RS-25s for Artemis I were
delivered to Michoud Assembly Facility near New
Orleans earlier in 2019. Technicians will integrate the
RS-25 engines into the core stage in the final months of
2019.
The 212-foot core stage, comprising an engine
section and boat tail assembly where the RS-25s are Figure 10. The Orion Stage Adapter (OSA) with
housed; the LH2 tank; an intertank; the LOX tank; and a Secondary Payload Deployment System (SPDS) has
forward skirt where flight computers are installed, is not accommodations for 13 6U CubeSats on the Artemis
only a new development – it will also be the tallest I flight.
rocket stage ever to fly. Manufacturing such a massive
stage for the first time has presented several challenges
for the team to work through. Most of these first-time-
build technical difficulties have been solved and the five
major components are structurally joined (see Figure
12). Following engine installation and final checkouts,
the stage will ship to SSC for the Green Run test
campaign.
NASA’s barge Pegasus will transport the enormous
stage from Michoud to SSC, where the B-2 test stand
has been upgraded, activated and is ready for the stage.
Pegasus was lengthened and reinforced to transport the
SLS core stage. Crews removed a 115-foot section of
the barge and replaced it with a 165-foot section
specially designed to increase the weight Pegasus can Figure 11. Completed RS-25 engine ready for
ferry. Length of the barge increased from 260 feet to installation in the Artemis I core stage.
310 feet.

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Figure 12. Technicians at Michoud Assembly Facility near New Orleans have structurally joined the
SLS Core stage for the Artemis I flight.
Green Run will feature a number of “firsts” for SLS. launched on an approximately 25-day test flight.
Green Run will be the first time the propellant tanks are CubeSats will be released into deep space once Orion
filled; the first end-to-end flow test of propellants and has separated from the vehicle and the ICPS has
other fluids through the complete stage; the first performed disposal maneuvers.
operational test of stage avionics; and the first time the NASA is accepting proposals through November 4,
four RS-25 engines are fired simultaneously. 2019 for CubeSats to fly on the second flight of SLS
Green Run as currently baselined is a combination and Orion, Artemis II. This flight will send four crew
of both qualification and acceptance testing. The test members in Orion on a lunar free-return mission.
series will validate the core stage design, design models Heliocentric disposal targets are more challenging on
and workmanship and verify the stage is ready to ship to this flight and fewer CubeSats are expected to be
KSC for final processing and integration. In addition to manifested. It is possible that the program will choose
the hot-fire testing, the entire test program as currently 12U as well as 6U payloads to fly on Artemis II.
outlined involves a number of prerequisite tests, Tentatively the maximum mass of a 12U Cubesat is 20
including vibration testing, power-on, leak and kg. U.S.-based payload developers can submit a
functional checks, hydraulics and TVC, safing, proposal for a payload to fly on Artemis II through the
simulated countdown and “wet dress rehearsal” during CSLI Program [4]. The SPDS and payload safety
which propellants are flowed through the stage but not review requirements for the Artemis II flight will be
ignited. similar to the Artemis I mission. NASA will prioritize
missions that address lunar and Martian SKGs and help
8. Conclusion reduce risk for future Artemis missions.
Artemis I is the first in a series of exciting missions Although SLS will be the largest, most powerful
to the Moon. Manufacturing is complete on the initial launcher since the Saturn V and is primarily designed to
SLS Block 1 vehicle, which will carry 13 6U CubeSats lift Orion and large science missions, mission planners
along on the test flight. Several elements, including the hope to offer rideshare opportunities to smallsats
OSA where the CubeSat payloads will be mounted, are whenever performance and volume are available, as on
complete and delivered to EGS. The core stage, an all- the Artemis I mission. By riding along on SLS,
new development, will ship to SSC in 2020 for a Green CubeSats have the ability to reach deep space and
Run test of avionics, tanking and engines. Following perform exciting science and technology demonstration
Green Run, the stage will be refurbished and shipped to missions, including testing propulsion systems.
KSC where the vehicle will be stacked with Orion and

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Sep 2018, 115 (36) 8907-8912; DOI:

References 10.1073/pnas.1802345115
[1] National Aeronautics and Space Administration, [3] National Aeronautics and Space Administration,
FY2020 Budget Amendment: Strategic Knowledge Gaps:
https://www.nasa.gov/sites/default/files/atoms/files/ https://www.nasa.gov/exploration/library/skg.html
nasa_budget_amendment_fy2020.pdf [4] FedBizOpps.gov Announcement of CubeSat Launch
[2] Shuai Li, Paul G. Lucey, Ralph E. Milliken, Paul O. Initiative:
Hayne, Elizabeth Fisher, Jean-Pierre Williams, Dana https://www.fbo.gov/index?s=opportunity&mode=fo
M. Hurley, Richard C. Elphic, Direct evidence of rm&tab=core&id=53a620f9a8e18e6ec41037891505
surface exposed water ice in the lunar polar regions, bdb3
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