DOCSLIB.ORG

What Is the Cube Quest Challenge

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
What Is the Cube Quest Challenge What’s the Cube Quest Challenge? Jim Cockrell Cube Quest Challenge Administrator Small Satellite Conference – August 6, 2016 • What are Challenges? • What is NASA’s Centennial Challenges? • Why a Cube Quest Challenge? • What is Cube Quest? Who is Eligible? • What is EM-1? • How do they get on EM-1? • What is the current status? 06Aug2016 CubeQuest for SmallSat Conference 2 In 1761, John In 1809, Nicolas Appert In 1901, Alberto I n 1 9 1 0 , G e o r g e s H a r r i s o n ( c l o c k (baker) solved the Santos-Dumont Chavez (pilot) won the maker) solved the Napoleon challenge for (coffee plantation Milan Committee British maritime food preservation heir) won the French challenge being the first navigation challenge airship challenge to fly over the Alps In 1977 & 1979, Paul In 2004, Burt Rutan I n 1 9 2 7 , C h a r l e s MacCready (aerospace engineer) won In 2007, Peter Homer Lindbergh (mail pilot) (aeronautic engineer) the X-Prize Ansari (unemployed engineer) won the Orteig Prize w o n t h e K r e m e r challenge being the first won the NASA Astronaut being the first to fly Prizes for human- private entity to enter Glove challenge by making across the Atlantic powered flight space twice within two a better glove Ocean challenges weeks 06Aug2016 CubeQuest for SmallSat Conference 3 • NASA STMD’s Centennial Challenges Program, iniJated in 2005, named aer Wright Brothers’ KiOy Hawk flight • Engages public in advanced technology development • Prizes for solving problems of interest to NASA and the naon • CompeJtors based in US; not supported by government funding. Current • Since 2005, there have been eight Centennial Challenges: challenge categories, resulJng in more • than 20 challenge events to date. Sample Return Robot • More than $6 million in prize money • 3-D Printed Habitat has been awarded to more than 17 different teams • Mars Ascent Vehicle • Summer 2013, work began on Cube • Cube Quest Quest Challenge 06Aug2016 CubeQuest for SmallSat Conference 4 • CubeSats are smaller in: cost, mass, volume, risk • Constellaons of cooperave, liOle satellites > single, convenJonal satellites • Cube Quest incenJvizes progress of CubeSats for deep space: • Long distance, high bandwidth comm • Navigaon and poinJng - without GPS or Earth’s magneJc reference • Thermal management outside Earth’s albedo • Survival in radiaon beyond LEO 06Aug2016 CubeQuest for SmallSat Conference 5 • Astrophysics: – Distributed RF and OpJcal Arrays on affordable satellite constellaon – Affordable, Jme-correlated (simultaneous) mulJ-point observaons of NEOs (mass density, albedo, etc) • Planetary Exploraons: – Distributed measurements (Ex: surface seismographic; Mars “weather systems”, mulJ-site impactors to detect lunar subsurface volales, etc.) – Co-ordinated assets (Ex: landers paired with orbiJng relays) Impactor Concept • Heliophysics: – Global coverage – MulJple observaons of transient events (Ex: radio occultaon) – Geographically distributed Jme-correlated “space weather” measurements Heliophysics, MulJpoint Science • Earth Science – Global coverage (mulJple) – Time correlated weather, oceanic observaons • DoD – Global coverage – Rapid response – System-level redundancy; high reliability 06Aug2016 CubeQuest for SmallSat Conference 6 Get your CubeSat to the Moon – or far beyond – Work the best. Survive the longest. Win prizes. Goal: to foster innovation in small spacecraft navigation, CubeSat limited to operations, and communications techniques for deep space 6U and 14 kg Qualify for EM-1 Lunar Derby Deep Space Derby Ground Tournaments (GT) launch While in lunar orbit While range ≥4M km - or – get your own ride 4 Rounds Achieve Lunar Orbit- Farthest Distance $1.5M/shared, $1M max per team $225k/25k Approx every 6 months Error-free Error-free Communication Communication Top 5 teams receive Burst Rate- $225k/25k Burst Rate- $225k/25k Total Volume- $675k/75k incremental funding Total Volume- $675k/75k (max $100k per team) Longevity Longevity Top 3 teams launch $450k/50k $225k/25k free on EM-1 More info: 06Aug2016 CubeQuest for SmallSat Conference 7 hp://www.nasa.gov/cubequest/details SLS Safety and Interface Requirements • SLS Payload Safety Reviews (to fly on EM-1) • Or equivalent, for 3rd-party launches CCP-CQ-OPSRUL-001 National Aeronautics and Space Administration EFFECTIVE DATE: December 4, 2014 NASA Centennial Challenges in Collaboration with Ames Research Center Marshall Space Flight Center, Alabama 35812 Any allowable part of the spectrum Cube Quest Challenge Ground Tournaments, Deep Space Derby, • subject to FCC public freq. alloc. and licensing regs and Lunar Derby Operations and Rules December 4, 2014 Comm data eligible for prizes • May use NASA DSN – at your cost • DSN tracks all trajectories; checks lunar orbit, 4M km range • Comm data format per Rules, to qualify CHECK THE MASTER LIST — VERIFY THAT THIS IS THE CORRECT VERSION BEFORE USE Comply with Orbital Debris and Planetary ProtecJon laws and regs hp://www.nasa.gov/cubequest/reference 06Aug2016 CubeQuest for SmallSat Conference 8 • US ciJzens, permanent residents, and US-based enJJes • No federal employees, within their employment scope • Register per rules • Compete in any, or all, Ground Tournaments • Your team can enter and win! hp://www.nasa.gov/cubequest/howtoenter 06Aug2016 CubeQuest for SmallSat Conference 9 • NASA’s first non-crewed lunar flyby mission of Orion from SLS – Launch in late 2018 • Capacity for thirteen 6U-sized CubeSats • Secondary Payloads deploy aer Orion departure into lunar flyby trajectory 06Aug2016 CubeQuest for SmallSat Conference 10 SLS Configuration Orion: Carries astronauts into deep space Stage Adapter: The Orion MPCV Stage Adapter will be the Interim Cryogenic Propulsion Stage: first new SLS hardware to fly. Based on the Delta IV Heavy upper stage; the power to leave Earth Core Stage: Newly developed for SLS, the Core Stage towers more than 200 feet tall Solid Rocket Boosters: Built on Space ShuOle hardware; more powerful for a new era of exploraon RS-25 Engines: Space ShuOle engines for the first four flights are already in inventory 06Aug2016 CubeQuest for SmallSat Conference 11 What is EM-1? 06Aug2016 CubeQuest for SmallSat Conference 12 ! Eleven 6U/12U payload locaons 6U volume/mass is the current standard (14 kg payload mass) Payloads will be “powered off” from turnover through Orion separaon and payload deployment Payload Deployment System Sequencer; ~Ø156” payload deployment will begin with pre- loaded sequence following MPCV separaon and ICPS disposal burn ~21° ~22° Payload requirements captured in Interface DefiniJon and Requirements ~56° Document ~8° 06Aug2016 CubeQuest for SmallSat Conference 13 Top 3 qualified GT-4 Winners offered free EM-1 launch – Declare intent to fly EM-1 – Be a top five winner in GT-1 and/or GT-2 – Pass SLS payload safety reviews – Compete and win in GT-4 • Four Ground Tournaments (GTs) – GT-1 - Aug 2015 - $20k - winners announced! – GT-2 - Mar 2016 - $30k – winners announced! – GT-3 - Oct 2016 - $30k – GT-4 - Mar 2017 - $20k and chance to launch on EM-1 • Teams may compete in any or all four GTs – they get harder as they go! 06Aug2016 CubeQuest for SmallSat Conference 14 5 Judge Panel • 2 NASA • 3 Non-NASA leaders Teams submit GT • Industry documents • Academic • DoD Top 5 Teams Scoring > 3.0/5.0 40% CCP-CQ-OPSRUL-001 National Aeronautics and Space Administration EFFECTIVE DATE: December 4, 2014 NASA Centennial Challenges in Collaboration with Ames Research Center Marshall Space Flight Center, Alabama 35812 Likelihood Cube Quest Challenge Ground Tournaments, Deep Space Derby, and Lunar Derby of Mission Operations and Rules CCP-CQ-OPSRUL-001 National Aeronautics and Space Administration EFFECTIVE DATE: December 4, 2014 December 4, 2014 NASA Centennial Challenges in Collaboration with Ames Research Center Marshall Space Flight Center, Alabama 35812 Success Cube Quest Challenge Ground Tournaments, Deep Space Derby, and Lunar Derby Operations and Rules CHECK THE MASTER LIST — VERIFY THAT THIS IS THE CORRECT VERSION BEFORE USE Total December 4, 2014 GT CHECK THE MASTER LIST — VERIFY THAT THIS IS THE CORRECT VERSION BEFORE USE Team of 60% Score • Rules technical SMEs Compliance with Rules, • GT Workbook SLS IDRD, • SLS IDRD SLS Saey • SLS Safety Rqts (or equiv. launch provider rqts) Rqts 06Aug2016 CubeQuest for SmallSat Conference 15 Fall 2014 2018 EM-1 L+365 Days Competition EM-1 Competition Registration Launch End Today 365 Days GT1 GT2 GT3 GT4 $200kGT-1 GT-2 GT-3 GT-4 $300k $300k $200k Down Select (if more Teams than 28 days Team A launch spaces Team B (Not Selected) 28 days Team C 28 days Team D Team X 365 Days End 3rd-Party Launch 28 days Team X 365 Days Team Y Team Z End End 28 days < 365 Days Team Y 3rd-Party Launch < 28 Team Z 3rd-Party Launch days 06Aug2016 CubeQuest for SmallSat Conference 16 * - indicates EM-1 Qualifier Industry Academia Alpha CubeSat Xtraordinary *Cislunar EXplorers Innovave Space Partnerships, Cornell University Inc. * MIT KitCube MassachuseOs InsJtute of Technology *Heimdallr * SEDS UC San Diego Ragnarok Industries, Inc University of California- San Diego G.O.A.T.S. Worchester Polytechnic InsJtute *Team Miles Fluid & Reason LLC * CU-E3 University of Colorado – Boulder 06Aug2016 Lunar Derby Deep Space Derby Lunar & Deep Space Derby 17 • Registra]on is Open for GT-3 – September 21, 2016 • Registraon Deadline and SubmiOals due date – Winners announced in October 2016 • Final Ground Tournament – In-Person at Ames Research Center in March 2017 hp://www.nasa.gov/cubequest/howtoenter 06Aug2016 CubeQuest for SmallSat Conference
Load more

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]
  • Solar Sail Propulsion for Deep Space Exploration
    Solar Sail Propulsion for Deep Space Exploration Les Johnson NASA George C. Marshall Space Flight Center NASA Image We tend to think of space as being big and empty… NASA Image Space Is NOT Empty. We can use the environments of space to our advantage NASA Image Solar Sails Derive Propulsion By Reflecting Photons Solar sails use photon “pressure” or force on thin, lightweight, reflective sheets to produce thrust. 4 NASA Image Real Solar Sails Are Not “Ideal” Billowed Quadrant Diffuse Reflection 4 Thrust Vector Components 4 Solar Sail Trajectory Control Solar Radiation Pressure allows inward or outward Spiral Original orbit Sail Force Force Sail Shrinking orbit Expanding orbit Solar Sails Experience VERY Small Forces NASA Image 8 Solar Sail Missions Flown Image courtesy of Univ. Surrey NASA Image Image courtesy of JAXA Image courtesy of The Planetary Society NanoSail-D (2010) IKAROS (2010) LightSail-1 & 2 CanX-7 (2016) InflateSail (2017) NASA JAXA (2015/2019) Canada EU/Univ. of Surrey The Planetary Society Earth Orbit Interplanetary Earth Orbit Earth Orbit Deployment Only Full Flight Earth Orbit Deployment Only Deployment Only Deployment / Flight 3U CubeSat 315 kg Smallsat 3U CubeSat 3U CubeSat 10 m2 196 m2 3U CubeSat <10 m2 10 m2 32 m2 9 Planned Solar Sail Missions NASA Image NASA Image NASA Image Near Earth Asteroid Scout Advanced Composite Solar Solar Cruiser (2025) NASA (2021) NASA Sail System (TBD) NASA Interplanetary Interplanetary Earth Orbit Full Flight Full Flight Full Flight 100 kg spacecraft 6U CubeSat 12U CubeSat 1653 m2 86
    [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]
  • Cornell University
    Advanced CubeSat Technologies for Affordable Deep Space Science and Exploration Missions Ground Tournaments, the Moon, and Beyond Jim Cockrell Cube Quest Challenge Administrator iCubeSat - 30 May 2017 • What is Cube Quest? – Why a Cube Quest? – Rules and Prize Structure • Today’s Status Get your CubeSat to the moon, work the best – GT4 Competitors survive the longest win big prizes! – Emerging Technologies • Next Steps – GT4 winners – In-space Competition 30 May 2017 CubeQuest Challenge - iCubeSat 2 • SmallSats/CubeSats > conventional spacecraft – easier to launch – lower in cost • Unique missions with ensembles – planetary seismographs – array of Mars weather stations – distributed, correlated measurements – redundancy at the system level; robust system of systems – nodes for antenna arrays or telescope arrays – Augments traditional probes 30 May 2017 CubeQuest Challenge - iCubeSat 3 To-date, CubeSats don’t venture beyond LEO: Limitation SoA Deep Space Missions Need Limited comm range Low-gain dipoles or patches high gain directional antennas mainly used needed Limited comm data Low power, amateur band High-power, high frequency, wide rate transmitters mainly used bandwidth transmitters needed Lacking radiation COTS, low-cost parts used; more Radiation shielding, fault detection, tolerance benign environment of LEO fault tolerance Lacking in-space Not demonstrated (except solar High thrust, high ISP needed; propulsion sails); chemical fuel/pressurized chemical, electrical, solar containers prohibited Depend on Earth- Passive magnetorquers
    [Show full text]
  • Space Launch System Program March 1, 2018
    https://ntrs.nasa.gov/search.jsp?R=20180003498 2019-08-31T15:55:45+00:00Z National Aeronautics and Space Administration 5 . 4 . 3 .SPACE . 2 . 1 . LAUNCH SYSTEM CubeSats - To The Moon & Beyond Scott Spearing CubeSat Subject Matter Expert Space Launch System Program March 1, 2018 www.nasa.gov/sls www.nasa.gov/sls SLS BLOCK 1 EXPLORATION MISSION-1 (EM-1) Forward Ring Launch Abort System Secondary Payloads Electrical Panels Cabling Orion Avionics Box (2 places) Interim Cryogenic Propulsion Stage Launch Vehicle Stage Adapter OSA Diaphragm Core Stage Secondary Payload Brackets (13) Boosters Isogrid Barrel Panels Access Cover Aft Ring (2 places) Orion Stage Adapter (OSA) www.nasa.gov/sls 0418 EM-1 OSA SECONDARY PAYLOAD ACCOMMODATIONS Secondary Payload Avionics Box Cabling 6U CubeSat Payload 6U CubeSat Secondary Payload Dispenser Brackets (13) (PSC) Secondary Payload Mounting Bracket LEGEND: SLS Provided PD Provided www.nasa.gov/sls 0418 EM-1 SYSTEM DESCRIPTION AND PURPOSE Expand and fully utilize the SLS capabilities for exploration purposes without causing harm or inconvenience to SLS or its primary payload. • Thirteen (max capability 17) 6U payload locations • 6U volume/mass is the current standard OSA (14 kg payload mass) Diaphragm • Payloads will be “powered off” from turnover through Orion separation and ~Ø156” (13’) payload deployment • Payload Deployment System Avionics Unit; payload deployment will begin with pre-loaded OSA ~21° sequence following Orion separation and ~22° ICPS disposal burn • Payload requirements captured in Interface
    [Show full text]
  • From Ground Tournaments to Lunar and Deep Space Derby
    NASA’s CubeQuest Challenge – From Ground Tournaments to Lunar and Deep Space Derby Liz Hyde1 Millennium Engineering and Integration, Moffett Field, CA, 94035 and Jim Cockrell2 NASA Ames Research Center, Moffett Field, CA, 94035 The First Flight of NASA’s Space Launch System will feature 13 CubeSats that will launch into cis-lunar space. Three of these CubeSats are winners of the CubeQuest Challenge, part of NASA’s Space Technology Mission Directorate (STMD) Centennial Challenge Program. In order to qualify for launch on EM-1, the winning teams needed to win a series of Ground Tournaments, periodically held since 2015. The final Ground Tournament, GT-4, was held in May 2017, and resulted in the Top 3 selection for the EM-1 launch opportunity. The Challenge now proceeds to the in-space Derbies, where teams must build and test their spacecraft before launch on EM-1. Once in space, they will compete for a variety of Communications and Propulsion-based challenges. This is the first Centennial Challenge to compete in space and is a springboard for future in-space Challenges. In addition, the technologies gained from this challenge will also propel development of deep space CubeSats. Nomenclature ARC = Ames Research Center BCT = Blue Canyon Technologies CDR = Critical Design Review ConOps = Concept of Operations COTS = Commercial Off-The-Shelf CU-E3 = University of Colorado Earth Escape Explorer DSN = Deep Space Network EDU = Engineering Development Unit EM-1 = Exploration Mission 1 GRC = Glenn Research Center GT = Ground Tournament Isp = Specific Impulse LEO = Low-Earth Orbit MCR = Mission Concept Review mN = milinewtons MSFC = Marshall Space Flight Center PDR = Preliminary Design Review RACP = Resilient Affordable CubeSat Processor SAR = System Acceptance Review SDR = Software Defined Radio SLS = Space Launch System SRR = System Requirements Review 1 Mechanical Engineer, MEI, MS 213-6, Moffett Field, CA, AIAA Member.
    [Show full text]
  • Nasa's Space Launch System: Deep
    https://ntrs.nasa.gov/search.jsp?R=20180005407 2020-02-21T02:27:56+00:00Z NASA’S SPACE LAUNCH SYSTEM: DEEP-SPACE OPPORTUNITIES FOR SMALLSATS 4S Symposium Kimberly Robinson, Ph.D. Payloads Manager Carole McLemore, Ph.D. Secondary Payloads Integration Manager Space Launch System Program May 29, 2018 0496 0496 NASA’S EXPLORATION PLANS 0496 SLS – ENABLING HUMAN EXPLORATION EXPLORATION CLASS: DEEP SPACE CAPABILITIES • Five times more volume than any contemporary heavy lift vehicle VOLUME Orion 8m fairing • Only vehicle that can carry the Orion and a co- with with large manifested payload to the Moon Science aperture Missions telescope • Block 1: Can launch 60% more mass than any contemporary launch vehicle MASS • Block 2: Mars-enabling capability of greater than Contemporary SLS Block 1 SLS Block 2 Heavy Lift Exploration Exploration 45 metric tons to Trans Lunar Injection Class Class • Reduce transit times by half or greater to the outer DEPARTURE solar system ENERGY 0496 SLS BLOCK 1 CONFIGURATION FOR EM-1 Launch Abort System (LAS) Crew Module (CM) Service Module (SM) Encapsulated Service Module (ESM) Panels Spacecraft Adapter Orion Stage Adapter Orion Spacecraft Lockheed Martin 5 Segment Solid Rocket Boosters (2) Orbital ATK Interim Cryogenic Propulsion Stage (ICPS) Boeing/United Launch Alliance Launch Vehicle Stage Adapter Teledyne Brown Engineering Core Stage & Avionics Boeing RS-25 Engines (4) Aerojet Rocketdyne 0496 SOLID ROCKET BOOSTERS 0496 ENGINES 0496 CORE STAGE 0496 IN-SPACE STAGE AND ADAPTERS 0496 EXPLORATION MISSION-1 FULL SYSTEMS
    [Show full text]
  • CISLUNAR EXPLORERS: a STUDENT CUBESAT DEMONSTRATING LOW-COST TECHNOLOGIES for LUNAR EXPLORATION. Curran D. Muhlberger1, 1Cornell Ann S
    Lunar Exploration Analysis Group (2021) 5054.pdf CISLUNAR EXPLORERS: A STUDENT CUBESAT DEMONSTRATING LOW-COST TECHNOLOGIES FOR LUNAR EXPLORATION. Curran D. Muhlberger1, 1Cornell Ann S. Bowers College of Computing and Information Science, 107 Hoy Road, Ithaca, NY 14850, [email protected]. Introduction: Developed since 2014 by students in during integration have forced a delay. The spacecraft Cornell University’s Space Systems Design Studio, the are on track for completion within the next year, and Cislunar Explorers mission proposes to send a pair of the lessons learned [2] should help future small-scale 3U CubeSats to lunar orbit and demonstrate new lunar missions reduce cost and integration time. technologies for water electrolysis propulsion and Through demonstration of water electrolysis optical navigation in cislunar space. The vehicles propulsion and autonomous navigation on a small, showcase the results of a synergistic design process low-cost platform, Cislunar Explorers hopes to that reduces size and cost, paving the way for smaller broaden participation in orbital lunar science and missions to participate in lunar exploration. With encourage smaller lander concepts utilizing in situ water as the propellant, the architecture is suitable for resources for sample return. missions leveraging in situ resource utilization, while Acknowledgments: The mission team would like water’s safety and simple storage requirements lend to thank NASA’s Centennial Challenges program for themselves to the constraints of nanosatellite supporting Cislunar Explorers through the Cube Quest platforms. Challenge, our payload partners at Los Alamos A symbiosis between subsystems makes water National Laboratory, our advisors from the National electrolysis propulsion viable on such small vehicles.
    [Show full text]
  • Nasa's Space Launch System: Deep-Space Opportunities
    https://ntrs.nasa.gov/search.jsp?R=20180005407 2019-08-31T14:51:15+00:00Z NASA’S SPACE LAUNCH SYSTEM: DEEP-SPACE OPPORTUNITIES FOR SMALLSATS 4S Symposium Kimberly Robinson, Ph.D. Payloads Manager Carole McLemore, Ph.D. Secondary Payloads Integration Manager Space Launch System Program May 29, 2018 0496 0496 NASA’S EXPLORATION PLANS 0496 SLS – ENABLING HUMAN EXPLORATION EXPLORATION CLASS: DEEP SPACE CAPABILITIES • Five times more volume than any contemporary heavy lift vehicle VOLUME Orion 8m fairing • Only vehicle that can carry the Orion and a co- with with large manifested payload to the Moon Science aperture Missions telescope • Block 1: Can launch 60% more mass than any contemporary launch vehicle MASS • Block 2: Mars-enabling capability of greater than Contemporary SLS Block 1 SLS Block 2 Heavy Lift Exploration Exploration 45 metric tons to Trans Lunar Injection Class Class • Reduce transit times by half or greater to the outer DEPARTURE solar system ENERGY 0496 SLS BLOCK 1 CONFIGURATION FOR EM-1 Launch Abort System (LAS) Crew Module (CM) Service Module (SM) Encapsulated Service Module (ESM) Panels Spacecraft Adapter Orion Stage Adapter Orion Spacecraft Lockheed Martin 5 Segment Solid Rocket Boosters (2) Orbital ATK Interim Cryogenic Propulsion Stage (ICPS) Boeing/United Launch Alliance Launch Vehicle Stage Adapter Teledyne Brown Engineering Core Stage & Avionics Boeing RS-25 Engines (4) Aerojet Rocketdyne 0496 SOLID ROCKET BOOSTERS 0496 ENGINES 0496 CORE STAGE 0496 IN-SPACE STAGE AND ADAPTERS 0496 EXPLORATION MISSION-1 FULL SYSTEMS
    [Show full text]
  • Cislunar Explorers Mission Update Enabling Low Cost Interplanetary Smallsat Missions
    Cislunar Explorers Mission Update Enabling Low Cost Interplanetary SmallSat Missions Presented By: Aaron Zucherman Cislunar Explorers Mission Manager PhD Systems Engineering Student [email protected] CubeSat Workshop 2020 Cislunar Explorers Team Organization • Cornell University’s Space Systems Design Studio (SSDS) • Principal Investigators: Prof. Mason Peck and Dr. Curran Muhlberger • Mission Manager: Aaron Zucherman, PhD Student • Other members: ~18 Cornell Students • National Space Society • NSS Liaison: Dr. Dean Larson 2 Cislunar Explorers Mission Background • NASA’s CubeQuest Challenge SLS • 3rd place at Ground Tournament (GT) 1 in 2015 • 1st place at GT2 in 2016 • 2nd place at GT3 in 2016 • 1st place at final GT in 2019 • CubeQuest Lunar Derby ICPS • Achieve Lunar Orbit Prize • Spacecraft Longevity Prize • 1 of 13 6U CubeSats on Artemis-1 • Formally EM-1 Deployers • First Lunch of NASA’s SLS rocket Images Curtesy of NASA 3 Cislunar Explorers Design Overview • Technology Demonstrator 3UA • No science payload 3UB • Redundant spacecraft • Spin-Stabilized Attitude Control System • Water Electrolysis Propulsion System • Demonstrate potential In Situ Resource Utilization System • Optical Navigation System • Low cost position and attitude determination • Triangulation using celestial bodies • ChipSat • Rideshare on a rideshare • Self-contained Satellite Cislunar Explorers Model 4 Cislunar Explorers Mission Goals • Lower barriers to exploring cislunar and interplanetary space • Test technologies that can be leveraged by future missions
    [Show full text]
  • Attitude Control for the Lumio Cubesat in Deep Space
    70th International Astronautical Congress, Washington D.C., United States, 21-25 October 2019. Copyright 2019 by the authors. Published by the IAF, with permission and released to the IAF to publish in all forms. IAC-19,C1,6,4,x50894 ATTITUDE CONTROL FOR THE LUMIO CUBESAT IN DEEP SPACE A.´ Romero-Calvo,1 J. D. Biggs, 1 F. Topputo1 The Lunar Meteoroid Impact Observer(LUMIO) is a 12U CubeSat designed to observe, quantify, and characterize the impact of meteoroids on the lunar surface. The combination of a highly demanding Concept of Operations(ConOps) and the characteristics of the deep-space environment determine the configuration of the spacecraft. This paper presents the preliminary Attitude Determination and Control System(ADCS) design of LUMIO, the reaction wheels desaturation strategy and Moon tracking control laws. The proposed solution is shown to (a) prevent the saturation of the reaction wheels, (b) minimize propellant consumption, (c) minimize the parasitic ∆V , (d) keep the pointing angle below a certain limit, and e) maximize power generation. Although no attempt is made to optimize the control parameters, the most efficient alternative in terms of propellant consumption is identified. The proposed LUMIO design could lay the foundations for a standardized minimum mass and volume ADCS system for CubeSats operating in deep-space. Nomenclature ~ns Unit vector normal to surface A Actual DCM matrix Ω Aperture angle of a regular tetrahedron Hadamard’s product Ad Desired DCM matrix P Solar constant Ae Error DCM matrix R Reaction wheels
    [Show full text]
  • Enabling a New Generation of Lunar Exploration Stephen D
    NASA’s Space Launch System: Enabling a New Generation of Lunar Exploration Stephen D. Creech NASA’s Space Launch System Program Spacecraft/Payload Integration & Evolution (SPIE) Office Mailstop XP50, Marshall Space Flight Center, AL 35812 256-544-9365 [email protected] Abstract—Following two decades of operational experience in 1. NASA’S LUNAR EXPLORATION low-Earth orbit (LEO), NASA has turned its focus once again to deep space exploration. The Agency is building the Space CAMPAIGN Launch System (SLS) to take astronauts and cargo to the Moon With the signing of Space Policy Directive 1, the U. S. and send robotic spacecraft deep into the solar system. Offering Administration has directed NASA to focus resources on unmatched performance, departure energy and payload deep space exploration. Specifically, the policy directs the capacity, SLS is designed to evolve into progressively more powerful configurations, enabling a new generation of human Agency to: exploration of the Moon in preparation for future missions to Mars. The first build of the Block 1 vehicle is nearly complete Lead an innovative and sustainable program of for Exploration Mission-1 (EM-1), the first integrated flight of exploration with commercial and international SLS and the Orion crew vehicle. EM-1 will send an uncrewed partners to enable human expansion across the Orion to a distant retrograde lunar orbit in order to test and solar system and to bring back to Earth new verify new systems, and along the way will deploy 13 6U-class knowledge and opportunities. Beginning with CubeSats in deep space along the upper stage disposal missions beyond low-Earth orbit, the United States trajectory after separation from Orion.
    [Show full text]