Iris V2 Peer Review

Total Page:16

File Type:pdf, Size:1020Kb

Iris V2 Peer Review Development of Telecommunication Systems for EM-1 Interplanetary CubeSat Missions 2017 Interplanetary Small Satellite Conf. San Jose, California, USA 1-2 May 2017 K. Angkasa, A. Babuscia, J. Baker, N. Chahat, M. Chase, F. Davarian, C. Duncan, T. Dobreva, S. Holmes, M. Kobayashi, C. Lau, D. Lewis, A. Yarlagadda Jet Propulsion Laboratory at the California Institute of Technology Copyright ©2017 California Institute of Technology. Government Sponsorship Acknowledged. CL#TBD Outline Development of Telecommunication Systems for EM-1 Interplanetary CubeSat Missions • Introduction to EM-1 CubeSat Missions • 6 EM-1 CubeSats Using Iris Lunar IceCube LunaH-Map Lunar Flashlight CuSP NEAS BioSentinel – Telecom Systems End-to-End – Telecom Architecture & Development Challenges for Each Mission – Telecom Architecture Summary – Telecom Parameters Summary • Closing Remarks Copyright ©2017 California Institute of Technology. Government Sponsorship Acknowledged. 2 8 2 / 1 . ) 5 . f e n R ( o i t t a c a S e e r m . b o s e u c s k . i C e l s n y s r U s n a 3 y o h r i . d t a r g n t a a n e c i d r n o i n l a l l a w . t p a desig s s e c i e h t e t i z i r h t s n c i cost cost t h t U l t a i w 2 u . h w o s 1 a t l f . e e g d l e u a l n n b q c i e i s a t r i r . and and t h a o s t s e U e p e r l v 6 e o e m b , c s . h h o a t n U h c c rapid rapid d f a c 3 n m i . a o b g n u r u s r o n s n l u s a o l i a u l f e y a t n a n l v w a s e o i n s e o . p g i c h l d e l t s t t n t t ace i e a f D e n r n u o a h t t z e t u a S o i S s d s h C e e o d m t m t i e i b u d n y t inter n U w u h q n a i a o l t . l 3 e a C s s p a m n r d. p l e cal cal d p o o e i d e e e i t o n h r n t t v n n d c d o r T a a a . a a e o r . d e f i e y p ) ha l o r n r r g n l t i r 3 c b e e p u a b t t seco t a . e a s l l l f n e n Remo s t i i m l i o b e loci in in a c o -me s n en a i d d e v l R c a ( h r n v n e a e y h e o a a k d t nels nels t i B e v a l . t o r s a r ng ng . t v s d w h s a e Benefi e Pa m n u e r e e resets resets c r e . t electro g l s o s u t l a n R a i s m , t r n . b t t a e e u c n e s c a e 7 of o n m ess ess h d n a l u v g t i l y e e c 6 e i o r l c j o t e t spensi o 3 s c h i c l r d e a m s a m m e 2 t c ing ing p d n t e A n s s d 0 r n i g i d n e a u d o D i . 0 a n n r n d C o n y d i i th th g d A t 2 nd nd d . a a i 1 h i a v n interfa e d . n a i i r a n e h C i g f n l n . s w t . e a i o o lf a g c u l l j u l c e y o g s d 3 o i b i e n e d y p l n n d o o i t T n e n 1 h r i e y a t a p d a n m nc r r w a m 0 E e h its i a p l f c n t g a i v 2 . nderst E s g s p e f a o e ca l i n e n s n i n u e f c h n H ectrical ectrical i c h p i P ge ge e b r i e ermal i c Sho d c o r s S e g y r t a u e t r el cupa ructures a t n n m n t th p f u s y n c i d e t t w t u r l a t m A ge e s t o l a e e 6U 6U oc l l u d d t a e r y a p T mass t l e l o ea t e t margi e d a h r s i da e a b d d n t i l . s f n i n , an i m P i e t e e r d t d tho l d d DA o g s a nd nd i b u a e oa e l n m a b ) a n e herit l rc t a s s y l i w c i e mplexi t t o d an a y i o a l i D u t y CSDs. CSDs. l b g v r cos f a v o d t e u r e e S u a e s h t ation c n r oa c pa c t n a U U e c l nsit li r C t l o w r e i i ( h y l exit e br s a flight flight m c o o i s ith existing s existing ith r 12 c l e tan nd nd i d de c l e t jiggl v R t erate c pa a t a ate, ate, m w a d d n th th y t t g g t E s men e l i s o mpl n e ng. l n r y y s y o S e y op st st t to to n’ % o y missio a w and and d t a i P l o s cons a o N c l a n a m e ock, ock, . 9 9 a r n c c 15 a agin E e , e b P y n ed ed l u t oor oor e, e, c o 6U p i P i e sh st, st, o c o h s o v d , , t e n t t i v depl chargi S c o i o t a I the the m d a a a oad oad TRL TRL c c w c te te e e D l n pack 3U h h wh D access access i i me me m t e y d c S rapidl e e n o s s s l s o b E e 4 Reduc e 1: 1: C ces ces posi u d e e e e the the b C e n 1 T pa t i w rfac r compatibilit i n I M u z a t s e 0 a m u w u T a a e o L a s r extr t e h l 2 Indica ili s t s c t t r h p e L m Ensures Ensures lo y l t s n b ces ces r red u A s o s u a E n m u E u e s ts ts s g y J c T o P w o l s Figure Figure h n nds n n t n sta Increases Increases t c o i n A 1 s a e l m E a r l red 2 s E s e v S e e a w i A r e y e t o D l m D l t D g G b a Pre a d oads E n l e S l i Al r e a Z r e Withsta y r I C o p e C l R G e e h S e Pa r c E h w n a P T T f o r r i S t I o e t c o N n n e j I D o i l E t t t CA a c n n LITY: e c e o i a n n s c t r r n s d e g o e d o i i l e F s B o a t n r e D s b m t e 7 h a F u m n P e S a u r c - n t 3 c l d u t o y l a a y s e D C 3 e o ATIBI e f n t s o o s i p o r 2 e l c a r m e V d R M s i e t V u s 0 p C n l r a h u e e s l l t a y t 0 S e e S t g c c a l l c i l n o a t e e a 2 l s i o n l D c b d s a o n i r P r a d e e m e r t i w a e D c A l s d r e o n i C a w e a t e t o r r R S a b D e t o r l y COMP , t s ur o s l c t p n e m l r l x y a n a I t r V c h t e r i e L e a t t a o u i a m t T e E t x e a P a d t r n l A g i i a o s r v F o / t h P t E u n t d n E n e t e S s e g D I C s o S i a Fe f e e e c l g e l t R n e r o a L v C d n u l l F a e i w o r l a l t l S o e y b l t u o p c L C a v f a a u P n i S - L f t u c - r i m P F a t n d D r O P D o s t - u n d M S c u r p C o o e i e b C o l d t T C M o a E o x R o w i l M o S e r L P Solid Rocket Boosters Rocket Solid Core Stage Core Launch Vehicle Stage Adapter Stage Vehicle Launch Secondary Payload Secondary Propulsion Stage (ICPS) Stage Propulsion Interim Cryogenic Interim Orion Launch Abort System Abort Launch Copyright ©2017 California Institute of Technology.
Recommended publications
  • The Cubesat Mission to Study Solar Particles (Cusp) Walt Downing IEEE Life Senior Member Aerospace and Electronic Systems Society President (2020-2021)
    The CubeSat Mission to Study Solar Particles (CuSP) Walt Downing IEEE Life Senior Member Aerospace and Electronic Systems Society President (2020-2021) Acknowledgements – National Aeronautics and Space Administration (NASA) and CuSP Principal Investigator, Dr. Mihir Desai, Southwest Research Institute (SwRI) Feature Articles in SYSTEMS Magazine Three-part special series on Artemis I CubeSats - April 2019 (CuSP, IceCube, ArgoMoon, EQUULEUS/OMOTENASHI, & DSN) ▸ - September 2019 (CisLunar Explorers, OMOTENASHI & Iris Transponder) - March 2020 (BioSentinnel, Near-Earth Asteroid Scout, EQUULEUS, Lunar Flashlight, Lunar Polar Hydrogen Mapper, & Δ-Differential One-Way Range) Available in the AESS Resource Center https://resourcecenter.aess.ieee.org/ ▸Free for AESS members ▸ What are CubeSats? A class of small research spacecraft Built to standard dimensions (Units or “U”) ▸ - 1U = 10 cm x 10 cm x 11 cm (Roughly “cube-shaped”) ▸ - Modular: 1U, 2U, 3U, 6U or 12U in size - Weigh less than 1.33 kg per U NASA's CubeSats are dispensed from a deployer such as a Poly-Picosatellite Orbital Deployer (P-POD) ▸NASA’s CubeSat Launch initiative (CSLI) provides opportunities for small satellite payloads to fly on rockets ▸planned for upcoming launches. These CubeSats are flown as secondary payloads on previously planned missions. https://www.nasa.gov/directorates/heo/home/CubeSats_initiative What is CuSP? NASA Science Mission Directorate sponsored Heliospheric Science Mission selected in June 2015 to be launched on Artemis I. ▸ https://www.nasa.gov/feature/goddard/2016/heliophys ics-cubesat-to-launch-on-nasa-s-sls Support space weather research by determining proton radiation levels during solar energetic particle events and identifying suprathermal properties that could help ▸ predict geomagnetic storms.
    [Show full text]
  • Lunar Flashlight & NEA Scout
    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 Selection • 19 NASA center-led concepts were evaluated and 3 were down-selected for further refinement by AES toward a Mission Concept Review (MCR) planned for August 2014 • Primary selection criteria: - Relevance to Space Exploration Strategic Knowledge Gaps (SKGs) - Life cycle cost - Synergistic use of previously demonstrated technologies - Optimal use of available civil servant workforce Payload Strategic Knowledge Gaps Mission Concept NASA Centers Addressed BioSentinel Human health/performance in high- Study radiation-induced DNA ARC/JSC radiation space environments damage of live organisms in cis- • Fundamental effects on biological systems lunar space; correlate with of ionizing radiation in space environments measurements on ISS and Earth Lunar Flashlight Lunar resource potential Locate ice deposits in the Moon’s JPL/MSFC/MHS • Quantity and distribution of water and other permanently shadowed craters volatiles in lunar cold traps Near Earth Asteroid (NEA) NEA Characterization Slow flyby/rendezvous and Scout • NEA size, rotation state (rate/pole position) characterize one NEA in a way MSFC/JPL How to work on and interact with NEA that is relevant to human surface exploration • NEA surface mechanical properties 2 EM-1: Near Earth Asteroid (NEA) Scout concept WHY NEA Scout? – Characterize a NEA with an imager to address key Strategic
    [Show full text]
  • Lunar Life Sciences Payload Assessment
    Lunar Surface Science Workshop 2020 (LPI Contrib. No. 2241) 5077.pdf LUNAR LIFE SCIENCES PAYLOAD ASSESSMENT. S. C. Sun1, F. Karouia2, M. P. Lera3, M. P. Parra1, H. E. Ray4, A. J. Ricco1, S. M. Spremo1. 1NASA Ames Research Center, 2Blue Marble Space Institute of Science, 3KBR, 4ASRC Federal Space and Defense, Inc. Introduction: The Moon provides a unique site to ISS, including systems that integrate into EXPRESS study living organisms. The fractional gravity and (EXpedite the PRocessing of ExperimentS for Space) unique radiation environment have similarities to Mars Racks or are external space exposure research facilities. and will help us understand how life will respond to These same systems can be the basis for future payload conditions on the red planet. Martian and lunar envi- systems for experiments to be performed beyond Low ronments can be simulated on the ground but not to high Earth Orbit. Such facilities would need to be adapted to fidelity. Altered gravity and increased radiation are dif- be compatible with the new research platforms and ficult to replicate simultaneously, which makes study- function in the harsher radiation environment found out- ing their combined effect difficult. The International side the magnetosphere. If Gateway and a lunar based- Space Station, and previously, the Space Shuttle, pro- lab could provide EXPRESS-compatible interfaces, lev- vided a microgravity environment, and could simulate eraging hardware developed for ISS would be more fea- fractional-g only via an onboard centrifuge. Because sible. the ISS and Space Shuttle orbits were within the Earth’s Gaps in Capabilities: Many of the payload systems magnetosphere, experiments on those platforms have that have been developed require human tending.
    [Show full text]
  • Developing Technologies for Biological Experiments in Deep Space
    Developing technologies for biological experiments in deep space Sergio R. Santa Maria Elizabeth Hawkins Ada Kanapskyte NASA Ames Research Center [email protected] NASA’s life science programs STS-1 (1981) STS-135 (2011) 1973 – 1974 1981 - 2011 2000 – 2006 – Space Shuttle International Skylab Bio CubeSats Program Space Station Microgravity effects - Nausea / vomit - Disorientation & sleep loss - Body fluid redistribution - Muscle & bone loss - Cardiovascular deconditioning - Increase pathogenicity in microbes Interplanetary space radiation What type of radiation are we going to encounter beyond low Earth orbit (LEO)? Galactic Cosmic Rays (GCRs): - Interplanetary, continuous, modulated by the 11-year solar cycle - High-energy protons and highly charged, energetic heavy particles (Fe-56, C-12) - Not effectively shielded; can break up into lighter, more penetrating pieces Challenges: biology effects poorly understood (but most hazardous) Interplanetary space radiation Solar Particle Events (SPEs) - Interplanetary, sporadic, transient (several min to days) - High proton fluxes (low and medium energy) - Largest doses occur during maximum solar activity Challenges: unpredictable; large doses in a short time Space radiation effects Space radiation is the # 1 risk to astronaut health on extended space exploration missions beyond the Earth’s magnetosphere • Immune system suppression, learning and memory impairment have been observed in animal models exposed to mission-relevant doses (Kennedy et al. 2011; Britten et al. 2012) • Low doses of space radiation are causative of an increased incidence and early appearance of cataracts in astronauts (Cuccinota et al. 2001) • Cardiovascular disease mortality rate among Apollo lunar astronauts is 4-5-fold higher than in non-flight and LEO astronauts (Delp et al.
    [Show full text]
  • AES-Secondaries-FS-V508b.Pdf
    National Aeronautics and Space Administration Hitchhiking Into the Solar System: Launching NASA’s First Deep-Space CubeSats Introduction NASA is pioneering space through common capability and technology developments, enabling exploration and human STRATEGIC expansion across multiple solar system destinations, including to KNOWLEDGE GAPS an asteroid and Mars. This journey into deep space has begun with exploration systems testing and demonstrations on Earth and in space. Although uncrewed, the first flight of the Orion spacecraft in December 2014 was an initial step in demonstrating its ability to safely ferry astronauts beyond Earth into deep space. Strategic Knowledge Gaps, or SKGs, The next critical demonstration of NASA’s deep space exploration represent gaps in knowledge or capabilities will be on Exploration Mission (EM)-1 in 2018. This information required to reduce risk, first flight of NASA’s Space Launch System (SLS) rocket will increase effectiveness and improve launch an uncrewed Orion spacecraft to a stable orbit beyond the facts the design of robotic and human moon and return it to Earth. In addition to demonstrating NASA’s space exploration missions. NASA new heavy-lift capability, SLS has the capacity to accommodate uses SKGs to help inform research 11 6U-sized CubeSats, which will deploy once Orion spacecraft and investment strategies, and separation is confirmed and on a specified timeline based on their prioritize technology development for mission objectives. human and robotic exploration. NASA’s Advanced Exploration Systems Division has selected three secondary payloads for further development to launch on SLS — hitchhiking into deep space. The major driver for selection of these CubeSats was the risk reduction they enable by addressing key Strategic Knowledge Gaps (SKGs).
    [Show full text]
  • Cubesat for Planetary Science and Exploration Breaking New Grounds
    CubeSat for Planetary Science and Exploration Breaking New Grounds Julie Castillo-Rogez, Research Scientist Jet Propulsion Laboratory Copyright 2015 California Institute of Technology. Government sponsorship acknowledged. Classes of Applications Technology Demos Engineering/Ops Science INSPIRE (NASA/JPL MarCO (JPL) Europa CubeSats (NASA – Concepts) Use low-cost spacecraft For example telecom CubeSats that carry for technology testing relays during critical primary science, and validation in relevant operations for lander’s reconnaissance, or environment entry, descent, and opportunistic science landing; to support a investigations; by Human crew at Mars; to themselves or as facilitate teleoperations… daughtership INSPIRE, MarCO, and EM-1 CubeSats as Stepping Stones to Deep Space LEON 3 ‘Sphinx’ X-Band Transponder ‘Iris’ 3 Outline Science Pull for Planetary CubeSats 3U and 6U Planetary CubeSat Landscape Visions for Future Voyages Parting Thoughts Outline Science Pull for Planetary CubeSats NASA Strategic Goals Planetary Science Decadal Survey Priorities Multi-Scale Exploration Fields Science Pull for Planetary CubeSats IAA Planetary CubeSat Study (2015) . Science enablers . Distributed measurements for dynamic processes . Impactor/observer architecture (cooperating assets) . Alternative low-cost architectures . Fractionated payload for system science . High-risk, high-reward observations . Access to unique vantage points . Risk assessment by sacrificial probe . Breaking new grounds . Exploration of uncharted regions Outline Science Pull
    [Show full text]
  • Biosentinel: ! DNA Damage-And-Repair Experiment ! Beyond Low Earth Orbit!
    BioSentinel: ! DNA Damage-and-Repair Experiment ! Beyond Low Earth Orbit! Tony Ricco! Chief Technologist, Small Payloads! NASA Ames Research Center! BioSentinel! Mission Goals and Objectives • Demonstrate simple model organisms as “biosentinels” o Biologically based sensors for hazards to humans Particularly for radiation, beyond low Earth orbit (LEO) Compare/correlate to physical radiation measurements st o DNA damage: 1 space demo. of biosentinel concept o Validate radiation damage models for biology o Develop “transfer standards” from biosentinels to humans o Support development of radiation protection o Inform mitigation strategies, actions • Conduct life science studies in multiple space environments relevant to human exploration o Deconvolute effects on biological systems 2" BioSentinel! Implementation • 6U autonomous nanosatellite ADCS*" o 4U payload, including radiation sensors Biosen)nel" o ≥ 2U for bus + ADCS including µ-propulsion P/L*" o ~ 14 kg total mass Bus" o ~ 23 W average power (deployable solar panels) o Mission duration: 18 months • Identical BioSentinel payload developed for ISS o similar µ-gravity but LEO radiation environment • Identical P/L for delayed-sync. ground control o 1 xg; low radiation • Radiation exposure ground studies (e.g. BNL) o 1 xg; acute, defined radiation doses BioSen2nel!spacecra?! design!concept! *ADCS!=!a)tude!determina2on4and4control!system;!P/L!=!payload! 3" BioSentinel! Launch Orbit • Launched as a secondary payload on EM-1 – Exploration Mission 1: 1st flight of NASA’s Space Launch System
    [Show full text]
  • Space Launch System
    National Aeronautics and Space Administration 5 . 4 . 3 . 2 . 1 . SPACE LAUNCH SYSTEM DEEP-SPACE DEPLOYMENT FOR SMALLSATS Andrew Schorr NASA Space Launch System May 2017 www.nasa.gov/sls SLS BLOCK 1 CONFIGURATION SLS Block 1 Overview Capability: >70 metric tons Height: 322 feet (98 meters) CubeSat • Initial configuration of vehicle Deployers optimized for near-term heavy-lift Weight: 5.75 million pounds (2.6 million kg) capability Thrust: 8.8 million pounds • Completed Critical Design Review (39.1 million Newtons) in July 2015 Available: 2019 Secondary Paylooads On Exploration Mission-1, SLS will include thirteen 6U payload locations of up to 14kg per CubeSat www.nasa.gov/sls 0146 iCubeSat.2 EM-1 CUBESAT BUS STOPS To Helio Bus Stops Distance (approx.) Flight Time (approx.) Approx. Temp. 1 26,700 km 3 Hrs. & 34 Min. 13°C (55°F) 2 64,500 km 7 Hrs. & 51 Min. -7°C (20°F) 3 192,300 km 3 Days, 6 Hrs. & 12 Min. -29°C (- 20°F) 5 4 384,500 km 6 Days, 11 Hrs. & 57 Min. -26°C (- 15°F) 5 411,900 km 7 Days, 0 Hrs. & 16 Min. -29°C (- 20°F) Estimate; depends on mission profile 4 3 2 1 Bus Stops Description 1 First opportunity for deployment, cleared 1st radiation belt 2 Clear both radiation belts plus ~ 1 hour Van Allen Belts 3 Half way to the moon 4 At the moon, closest proximity (~250 km from surface) 5 Past the moon plus ~12 hours (lunar gravitational assist) Note: All info based on a 6.5 day trip to the moon.
    [Show full text]
  • Dr Doug Boreham
    12/13/2019 1 12/13/2019 We are going 2024 Artemis – Greek Goddess of the Hunt, the Moon, and Virginity Twin of Apollo Man-made vs natural radiation Occupational Fallout Nuclear fuel cycle 0.5% 1% 1% Consumer products 6.5% Sources of Radiation Exposure Nuclear medicine/x-rays Man-made Natural 91% radiation background 52% radiation 48% Mettler 2007 Brooks 2010 2 12/13/2019 Interplanetary space radiation What are we going to encounter beyond LEO? Limits of life in space, as Ionizing radiation that studied to date: will affect biology: Galactic Cosmic 12.5 days on a lunar round trip Radiation (GCR) 1.5 years in low Earth Solar Particle Events orbit on ISS (SPEs) Galactic Cosmic Radiation - GCR 3 12/13/2019 Deep Space Radiation • Galactic cosmic rays (GCR)—highly-ionizing radiation (Linear Energy Transfer - LET) • Comprised of high-energy protons and heavy ions • Solar particle events (SPEs): primarily energetic protons (85%), helium (14%) and high-energy (E) and high-charge (Z) ions called HZE particles (1%) 8 4 12/13/2019 DNA Damage Credit: NASA 5 12/13/2019 Human missions will need: water, food, oxygen fuel avoid solar particle events (SPEs). Deep space missions will require significant countermeasures, likely both technological and biomedical, to protect the crew from the effects of chronic radiation exposure. 11 Autonomous Biosensors for Deep Space Organisms that can survive for extended periods with minimal life support technology, and must function reliably with intermittent communication with Earth. 12 6 12/13/2019 13 7 12/13/2019
    [Show full text]
  • A New Era of Planetary Exploration with Small Satellite Platforms
    A New Era of Planetary Exploration with Small Satellite Platforms 4th IAA Conference on University Satellite Missions and CubeSat Workshop December 5, 2017 Dr. Ben Malphrus Morehead State University Morehead KY USA : A New Paradigm for Deep Space Exploration CubeSats and SmallSat Form Factors • Can Achieve Targeted Science Goals Independently • Augment Monolithic Flagship Missions • Low-Cost and Essentially Expendable – Can be sent to harsh environments • Radiation Belts of Jupiter • Ring Plane of Saturn • Atmosphere of Venus • Plumes of Enceledus 4th IAA Interplanetary SmallSat 2017 : A Pandora’s Box of Interplanetary CubeSats is Opening • New Enabling Technologies will support Interplanetary Exploration with SmallSats • NASA (and ESA to some Extent) has adopted the Interplanetary CubeSat Model, supporting missions and studies – NASA Interplanetary CubeSat Missions • MarCO • EM-1 (13 Interplanetary CubeSats) – Interplanetary CubeSat Mission Studies • Planetary Science Deep Space SmallSat Studies (PSDS3) program • Research Opportunities in Earth and Space Science (ROSES-17) – Numerous White Paper Studies Underway 4th IAA Interplanetary SmallSat 2017 : A New Era- Enabling Technologies • New Enabling Technologies will support Interplanetary Exploration with SmallSats: – New Launch Vehicles and Increased Access (Secondary Payloads to Earth Escape) – Miniaturized Propulsion Systems Capable of Producing Reasonable ∆v – Small, Highly Capable Science Instruments – High Performance Comms and Ranging Systems – Radiation Hardened Subsystems – Use
    [Show full text]
  • Lunar Flashlight Mapping Lunar Surface Volatiles Using a Cubesat
    Lunar Flashlight Mapping Lunar Surface Volatiles Using a CubeSat Dr. Barbara Cohen Lunar Flashlight PI/ Measurement Lead NASA Marshall Space FISO Telecon Flight Center 4/22/15 Lunar Flashlight: a secondary payload • 19 NASA center-led concepts were evaluated and 3 were down-selected by the Advanced Exploration Systems (AES) program • Primary selection criteria: – Relevance to Space Exploration Strategic Knowledge Gaps (SKGs) – Synergistic use of previously demonstrated technologies – Life-cycle cost and optimal use of available civil servant workforce • Other secondary payloads may be added (11 total) 2 Space Launch System (SLS) EM-1 (2018) • SLS Block 1 (70 mT) • Uncrewed circumlunar flight, duration 7 days, free- return trajectory • Demonstrate integrated systems, high-speed entry (11 km/s) EM-2 (2021-2022) • SLS Block 1 (70 mT) • Crewed lunar orbit mission (?) • Mission duration 10-14 days 3 Secondary payloads on EM-1 • Room for 11 6U cubesats on standard deployer • Secondary payloads will be integrated on the MPCV stage adapter (MSA) on the SLS upper stage MPCV • Secondary payloads will MPCV Stage Adapter (MSA) MSA be deployed on a trans- Diaphragm lunar trajectory after the Launch Vehicle Adapter upper stage disposal (LVSA) LVSA maneuver Diaphragm Core Stage Block 10001 4 Near Earth Asteroid Scout GOALS Marshall Space Flight Center/Jet Propulsion Characterize one Lab/LaRC/JSC/GSFC/NASA candidate NEA with an imager to address key One of three 6U Strategic Knowledge Cubesats sponsored Gaps (SKGs) by Advanced Demonstrates low cost Exploration
    [Show full text]
  • Lunar Flashlight: Mapping Lunar Surface Volatiles Using a Cubesat
    Lunar Flashlight: Mapping Lunar Surface Volatiles Using a Cubesat Barbara Cohen, MSFC PauiHayne,BenGreenhagen,JPL David Paige, UCLA - - - - - - . ~ - -- -- ,.... - _._ ~- - -~- - ~- . - -_ --:_ - ~;:----------- - = -,--- . -_ - ,- ....,_ - --- .. ~-- - _" --~--- ~---- - --~ ~ ~--- --=-_.-- -- ---- ~---- --, • 19 NASA center-led concepts were evaluated and 3 were down-selected by the Advanced Exploration Systems (AES) program • Primary selection criteria: - Relevance to Space Exploration Strategic Knowledge Gaps (SKGs) - Synergistic use of previously demonstrated technologies - Life-cycle cost and optimal use of available civil servant workforce • Other secondary payloads will be added - NASA SMD and STMD may be interested - Possibly others- universities, research centers, etc? Payload Strategic Knowledge Gaps Mission Concept NASA Centers Addressed BioSentinel Human health/performance in high­ Study radiation-induced DNA ARC/JSC radiation space environments damage of live organisms in cis­ • Fundamental effects on biological systems lunar space; correlate with of ionizing radiation in space environments measurements on ISS and Earth Lunar Flashlight Lunar resource potential Locate ice deposits in the Moon's JPUMSFC/MHS • Quantity and distribution of water and other permanently shadowed craters volatiles in lunar cold traps Near Earth Asteroid (NEA) NEA Characterization Slow flyby/rendezvous and Scout • N EA size, rotation state (rate/pole position) characterize one NEA in a way MSFCIJPL How to work on and interact with NEA that is relevant
    [Show full text]