DOCSLIB.ORG

Challenges and Solutions for Lunar Icecube Birches- First Generation Cubesat Lunar Orbiter Science Payloads

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Challenges and Solutions for Lunar Icecube Birches- First Generation Cubesat Lunar Orbiter Science Payloads CHALLENGES AND SOLUTIONS FOR LUNAR ICECUBE BIRCHES- FIRST GENERATION CUBESAT LUNAR ORBITER SCIENCE PAYLOADS Pamela Clark (JPL) Ben Malphrus (Morehead State) Cliff Brambora, Terry Hurford, Dave Folta, Paul Mason, Matt Grubb (GSFC) Kris Angkasa (JPL) Mike Tsay (Busek) Lunar IceCube Selected for Launch on EM-1 in 2020 Currently Under Development at Morehead State NASA GSFC JPL Busek NASA IV&V Clark etal ISmallSat 2015 IceCube 2 Lunar IceCube Project Team The Team consists of university, NASA, and private sector partners: • Morehead State University Space Science Center Ben Malphrus (PI), Jeff Kruth, Kevin Brown, Michael Combs, Jose Garcia, Graduate and Undergraduate students • The Busek Company Mike Tsay, John Frongillo, Josh Model • NASA Goddard Spaceflight Center BIRCHESTeam: Pamela Clark, Dennis Reuter, Robert MacDowall, Clifford Brambora, Deepak Patel, Navigation and Tracking: David Folta Ian Banks, and Terry Hurford • NASA IV&V FSW: Matt Grubb, Scott Zemerick, Justin Morris • JPL Pamela Clark (Science PI), Kris Angkasa 8/9/2018 FY17 - AES Mid-Year 3 Lunar IceCube Objectives & Technical Approach •A 6U CubeSat mission to prospect for water in ice, liquid, and vapor forms and other lunar volatiles from a low-perigee, highly inclined lunar orbit using a compact IR spectrometer in attempt to lend insight into the transport physics from mid-latitudes to PSRs Lunar IceCube 6U will: •Be deployed during lunar trajectory by the SLS on EM-1 •use an innovative RF Ion engine to achieve lunar capture and a science orbit of 100 km perilune IAA 2016 Lunar IceCube 3/1/2016 4 NextSTEP - Lunar IceCube Status Mission Description and Objectives Lunar IceCube is a 6U small satellite whose mission is to prospect for water in ice, liquid, and vapor forms and other lunar volatiles from a low-perigee, inclined lunar orbit using a compact IR spectrometer. 1.) Lunar IceCube will be deployed by the SLS on EM-1 and 2.) use an innovative RF Ion engine combined with a low energy trajectory to achieve lunar capture and a science orbit of 100 km perilune. Strategic Knowledge Gaps 1-D Polar Resources 7: Temporal Variability and Movement Dynamics of Surface- Correlated OH and H2O deposits toward PSR retention 1-D Polar Resources 6: Composition, Form and Distribution of Polar Volatiles 1-C Regolith 2: Quality/quantity/distribution/form of H species and other volatiles in mare and highlands regolith (depending on the final inclination of the Lunar IceCube orbit) Technology Demonstrations Current Status • Busek BIT 3 - High isp RF Ion Engine Team is preparing for acceptance and • NASA GSFC - BIRCHES Miniaturized IR Spectrometer - characterize water integration of Flight Hardware and other volatiles with high spectral resolution (5 nm) and wavelength FlatSat with non rad-hard subsystems and range (1 to 4 μm) emulators is in development • Space Micro C&DH- Inexpensive Radiation-tolerant Subsystem • JPL Iris v. 2.1 Ranging Transceiver Trajectory, navigation, and thermal models • BCT- XACT ADCS w/ Star Tracker and Reaction Wheels along with communications links, mass, Critical• Custom MilestonesPumpkin- High Power (120W) CubeSat Solar Array volume and power budgets evolving PDR Phase 1 CDR/∆CDR Phase 2 Phase 3 FRR/ORR Launch Mission Ops Mission Duration Project Closure 05/16/17 05/19/2016 06/20/2016 04/26/2018 11/28/2018 04/15/2019 2020 2020-2022 2 years incl. ext. 2022-23 3/14/18 8/9/2018 FY17 - AES Mid-Year 5 EM-1 Space Launch System: SLS + Orion ISS, Moon, NEAs and Beyond… EM-1 Scheduled for 2020 Uses an Innovative Propulsion Sytem and Low Energy Trajectory 7 Design and Development Challenges •Many Aspects of Interplanetary CubeSat Missions Do Not Scale- •Require Complex Subsystems, Complex Ops, Complex FSW •Significant ∆V Requirement Dictates Complex Low Energy Manifold Trajectory •Mass and Volume Constrained •Few COTS Radiation-Tolerant Components/Subsystems Exist for CubeSats •COTS Systems at Low TRL and without Flight Heritage •Thermal Management is a Challenge- BIRCHES requires cooling to cryogenic temperatures, spacecraft has limited Radiating Surfaces •Complex Attitude Control Requirements •Power Budget Requires nearly 100 W prime power •COTS Systems Produce 72 W •Complex Ground Data Systems Required to Communicate with DSN and Process Science Data •Constrained Resources •Highly Compressed Development Timeline B. Malphrus IAA 2016 Lunar IceCube 3/1/2016 8 Lunar IceCube- Requires Complex Subsystems Pumpkin Solar Arrays Cryocooler Electronics Box GNC: BCT XACT Solar Arrays Gimbals Proton 400K Lite (Under Transponder) X-Band Transponder Pumpkin EPS UHF Deep Space Beacon UHF Dipole Antenna Busek Bit-3 RF Ion Thruster Iodine Tank BIRCHES IR Spectrometer Battery Module Cryocooler X-Band LNA X-Band SSPA 8/9/2018 FY17 - AES Mid-Year 9 Morehead State 6U CubeSat Bus B. Malphrus IAA 2016 Lunar IceCube 3/1/2016 10 Lunar IceCube Subsystems MEL v. 4.26.2016 System Mass Volume (in Us) Power Use CAD Model Source Structures, Thermal 0.85 kg 6U Exterior & Rings N/A MSU- M. MSU Management 239 x 366 x 116mm Combs C&DH: Proton 400K 0. 15 kg 0.2 U 9.3 W Space Micro Space Micro BCT XACT for ACS Control BCT XACT Harnesses, cables, coatings… 0.34 kg (est.) Conformal w/in structure 0.1 U N/A Estimated MSU Solar panels & Gimbals 1.8 kg Deployable panels intrude 10 mm N/A Pumpkin MSU + Custom Pumpkin 120W Array into structure (each) Pumpkin Solar Panel Drive Articulators Included above 120 x 88 x 20 mm (0.2U) 5 W Requested Pumpkin + Custom Pumpkin w/ Faulhaber from MMA Faulhaber Stepper motors EPS + Batteries 0.6 kg (est.) 0.25 U Quiescent Draw = EPS and MSU Pumpkin 10 mW Batteries BIT-3 Busek RF Ion Iodine 1.5027 kg <2U 65 W Busek Draft Busek 180 x 102 x 88 mm CAD model Propellant 1.2 kg Contained within Above N/A Busek CAD Busek ACS/GNC: BCT XACT + Two 50 0.92 kg 0.5 U 6.3W Cont. BCT- XACT and BCT mN RWAs 100 x 100 x 50mm (3RW@ Max) NST Comms: JPL Iris 0.90 kg 100.5 x 101.0 x 56.0 mm 27.7 W X-Band Tx Iris 2.1 JPL Power Amplifier (SSPA) 0.150 kg 86.6 x 42.7 x 17.8 mm 11.6 W- Rx LNA, LGAs 0.08 kg 0.1kg 69.4 x 47.5 x 13 mm 31.8 W Transpond UHF Beacon- AstroDev Li 0.25 kg 0.1 U 6 W Tx AstroDev MSU Quad Array 0.25 W Rx BIRCHES- Spectrometer 0.8 kg 80.33 mm x 104.87 mm x 79.38 50 mW Draft CAD GSFC Optical Box mm from GSFC BIRCHES DRE 1.02 kg 35.925 x 150 x 88 mm 25W GSFC GSFC Cryocooler 0.75 kg 80.33 mm x 68.05 mm x 79.38 mm 12W Needed GSFC Vendor Cryocooler Electronics 0.75 kg 30.48 mm x 91.44 mm x 91.44 mm TOTALS: 14.00 kg 6U: Envelope 239 x 366 x 116mm Varies by Mode 0.00 kg margin Clark etal ISmallSat 2015 IceCube 11 Significant ∆V Requirement- BIT-3 RF Ion Engine • Busek BIT-3 cm RF Ion Engine • Radiation Tolerant PPU Design • Mini-RF Cathode Innovation • Test Fired with Xenon, Iodine • Solid Iodine Propellant • Projected Performance on Lunar IceCube: ISP: 1906 sec BIT-3 Thruster Firing at the Busek Facilities Thrust: > 0.8 mN 0.90 3600 ∆v = 1.2 km/s Thrust System Isp 0.80 3200 0.70 2800 RF cathode operating together with the BIT-3 0.60 thruster, both on xenon propellant 2400 0.50 2000 0.40 1600 Thrust, mN Thrust, 0.30 1200 System Isp, sec 0.20 800 0.10 400 0.00 0 40 45 50 55 60 65 Power Input to Propulsion PPU, W Estimated Performance of a New, Scaled-Down Iodine BIT-3 12 Lunar IceCube BIT-3 Final Design Thruster; Isp Includes Neutralizer Flow Significant ∆V Requirement Dictates Use of Interplanetary Superhighway (IPS) Developed by M. Lo and S. Ross at JPL, the IPS uses low energy manifold trajectories based on stable and unstable manifolds and ballistic capture. Manifolds are created by Lagrange points through n-body effects and can now be modeled for realistic interplanetary trajectories Interplanetary Superhighway Makes Space Travel Simpler // NASA 07.17.02: "Lo conceived the theory of the Interplanetary Superhighway. Lo and his colleagues have turned the underlying mathematics of the Interplanetary Superhighway into a tool for mission design called "LTool," ... The new LTool was used by JPL engineers to redesign the flight path for the Genesis mission" Malphrus 2015 IceCube 13 Significant ∆V Requirement Dictates Complex Low Energy Manifold Trajectory L3 IceCube utilizes a minimal DV transfer trajectory harnessing expertise of GSFC flight dynamics. B. Malphrus IAA 2016 Lunar IceCube 3/1/2016 14 Complex Science Orbit Transition • Capture into a long-term weakly-stable lunar orbit (based on energy and dynamics) • Sequentially lowering apoapsis to achieve inclined science orbit with equatorial periapsis o Spiral; Spiral then apoapsis lowering; or Capture then Periapsis/Apoapsis reduction • Spiral transfer orbit shown with ~6 month decreasing periapsis altitude over 80 days – dependent on thrust / mass ratio, on-time, shadows, and efficiency • Orbit design goal to minimize shadows, achieve stable orbit, minimize fuel Shadow Transfer to Science in blue Shadow Transfer to Science in blue Capture in red Capture in red 15 Science Orbit • 100 km Periapsis Altitude at Equatorial Crossing o Drives Argument of Periapsis at Ascending Node • High Inclination (70-90) • Overlap of groundtracks for calibration o Drives semimajor axis (period of 7 hrs) o Yields a candidate orbit with a 100 km periapsis and 5000 km apoapsis altitude • Maximize Lifetime with no stationkeeping maneuvers o Dependent on inclination, placement of ascending node wrt Earth, Initial periapsis altitude, and eccentricity Three 1-month orbits Groundtrack Overlap 11/19/15 L-IC Science Orbit Dictates Complex ACS 17 Lunar IceCube BIRCHES Instrument Description and Objectives • Broadband InfraRed Compact High Resolution
Load more

Recommended publications
  • New Moon Explorer Mission Concept
    New Moon Explorer Mission Concept Les JOHNSONa,*, John CARRa,Jared Jared DERVANa, Alexander FEWa, Andy HEATONa, Benjamin Malphrusd, Leslie MCNUTTa, Joe NUTHb, Dana Tursec, and Aaron Zuchermand aNASA MSFC, Huntsville, AL USA bNASA GSFC, Huntsville, AL USA cRoccor, Longmont, CO USA dMorehead State University, Morehead, KY USA Abstract New Moon Explorer (NME) is a smallsat reconnaissance mission concept to explore Earth’s ‘New Moon’, the recently discovered Earth orbital companion asteroid 469219 Kamoʻoalewa (formerly 2016HO3), using solar sail propulsion. NME would determine Kamoʻoalewa’s spin rate, pole position, shape, structure, mass, density, chemical composition, temperature, thermal inertia, regolith characteristics, and spectral type using onboard instrumentation. If flown, NME would demonstrate multiple enabling technologies, including solar sail propulsion, large-area thin film power generation, and small spacecraft technology tailored for interplanetary space missions. Leveraging the solar sail technology and mission expertise developed by NASA for the Near Earth Asteroid (NEA) Scout mission, affordably learning more about our newest near neighbor is now a possibility. The mission is not yet planned for flight. Keywords: Kamoʻoalewa, solar sail, moon, Apollo asteroid 1. Introduction The emerging capabilities of extremely small spacecraft, coupled with solar sail propulsion, offers an opportunity for low-cost reconnaissance of the recently- discovered asteroid 469219 Kamoʻoalewa (formerly 2016HO3). While Kamoʻoalewa is not strictly a new moon, it is, for all practical purposes, an orbital companion of the Earth as the planet circles the sun. Kamoʻoalewa’s orbit relative to the Earth can be seen in Figure 1. Using the technologies developed for the NASA Fig. 1 The orbit of Earth’s companion, Kamoʻoalewa Near Earth Asteroid (NEA) Scout mission, a 6U as both it and the Earth orbit the Sun.
    [Show full text]
  • 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]
  • KPLO, ISECG, Et Al…
    NationalNational Aeronautics Aeronautics and Space and Administration Space Administration KPLO, ISECG, et al… Ben Bussey Chief Exploration Scientist Human Exploration & Operations Mission Directorate, NASA HQ 1 Strategic Knowledge Gaps • SKGs define information that is useful/mandatory for designing human spaceflight architecture • Perception is that SKGs HAVE to be closed before we can go to a destination, i.e. they represent Requirements • In reality, there is very little information that is a MUST HAVE before we go somewhere with humans. What SKGs do is buy down risk, allowing you to design simpler/cheaper systems. • There are three flavors of SKGs 1. Have to have – Requirements 2. Buys down risk – LM foot pads 3. Mission enhancing – Resources • Four sets of SKGs – Moon, Phobos & Deimos, Mars, NEOs www.nasa.gov/exploration/library/skg.html 2 EM-1 Secondary Payloads 13 CUBESATS SELECTED TO FLY ON INTERIM EM-1 CRYOGENIC PROPULSION • Lunar Flashlight STAGE • Near Earth Asteroid Scout • Bio Sentinel • LunaH-MAP • CuSPP • Lunar IceCube • LunIR • EQUULEUS (JAXA) • OMOTENASHI (JAXA) • ArgoMoon (ESA) • STMD Centennial Challenge Winners 3 3 3 Lunar Flashlight Overview Looking for surface ice deposits and identifying favorable locations for in-situ utilization in lunar south pole cold traps Measurement Approach: • Lasers in 4 different near-IR bands illuminate the lunar surface with a 3° beam (1 km spot). Orbit: • Light reflected off the lunar • Elliptical: 20-9,000 km surface enters the spectrometer to • Orbit Period: 12 hrs distinguish water
    [Show full text]
  • Payload Design for the Lunar Flashlight Mission
    Lunar and Planetary Science XLVIII (2017) 1709.pdf Payload Design For The Lunar Flashlight Mission. B. A. Cohen1, P. O. Hayne2, B. T. Greenhagen3, D. A. Paige4, J. M. Camacho2, K. Crabtree5, C. Paine2, R. G. Sellar5; 1NASA Marshall Space Flight Center, Huntsville AL 35812 ([email protected]), 2Jet Propulsion Laboratory, Pasadena CA 91109, 3Applied Physics Laboratory, Johns Hopkins University, Laurel MD 20723, 4UCLA, Los Angeles, CA 90095, 5 Photon Engineering, Tucson AZ 85711. Introduction: Recent reflectance data from LRO lengths in rapid sequence, while a receiver system de- instruments suggest water ice and other volatiles may tects the reflected light. Derived reflectance and water be present on the surface in lunar permanently- ice band depths will be mapped onto the lunar surface shadowed regions, though the detection is not yet de- in order to identify locations where H2O ice is present finitive [1-3]. Understanding the composition, quanti- at or above 0.5 wt% concentration. ty, distribution, and form of water and other volatiles In the past year, we have advanced the design for associated with lunar permanently shadowed regions the Lunar Flashlight payload to meet our measurement (PSRs) is identified as a Strategic Knowledge Gap requirement within the limited mass and power availa- (SKG) for NASA’s human exploration program. These ble for the instrument system. We optimized the laser polar volatile deposits are also scientifically interest- wavelengths for maximum sensitivity to water ice ab- ing, having potential to reveal important information sorption bands. The selected wavelengths are 1.064 (- about the delivery of water to the Earth-Moon system.
    [Show full text]
  • Lunar and Lagrangian Point L1/L2 Cubesat Communication and Navigation Considerations
    SSC17-V-02 Lunar and Lagrangian Point L1/L2 CubeSat Communication and Navigation Considerations Scott Schaire, Yen F Wong, Serhat Altunc, George Bussey, Marta Shelton, Dave Folta, Cheryl Gramling NASA Goddard Space Flight Center, Greenbelt, MD 20771 (757) 824-1120, [email protected] Peter Celeste, Mike Anderson, Trish Perrotto Booz Allen Hamilton, Annapolis Junction, MD 20701 Ben Malphrus, Jeff Kruth Morehead State University, Morehead, KY 40351 ABSTRACT CubeSats have grown in sophistication to the point that relatively low-cost mission solutions could be undertaken for planetary exploration. There are unique considerations for lunar and L1/L2 CubeSat communication and navigation compared with low earth orbit CubeSats. This paper explores those considerations as they relate to the Lunar IceCube Mission. The Lunar IceCube is a CubeSat mission led by Morehead State University with participation from NASA Goddard Space Flight Center, Jet Propulsion Laboratory, the Busek Company and Vermont Tech. It will search for surface water ice and other resources from a high inclination lunar orbit. Lunar IceCube is one of a select group of CubeSats designed to explore beyond low-earth orbit that will fly on NASA’s Space Launch System (SLS) as secondary payloads for Exploration Mission (EM) 1. Lunar IceCube and the EM-1 CubeSats will lay the groundwork for future lunar and L1/L2 CubeSat missions. This paper discusses communication and navigation needs for the Lunar IceCube mission and navigation and radiation tolerance requirements related to lunar and L1/L2 orbits. Potential CubeSat radios and antennas for such missions are investigated and compared. Ground station coverage, link analysis, and ground station solutions are also discussed.
    [Show full text]
  • The Lunar Icecube Mission Design: Construction of Feasible Transfer Trajectories with a Constrained Departure
    AAS 16-285 THE LUNAR ICECUBE MISSION DESIGN: CONSTRUCTION OF FEASIBLE TRANSFER TRAJECTORIES WITH A CONSTRAINED DEPARTURE David C. Folta*, Natasha Bosanac†, Andrew Cox‡, and Kathleen C. Howell§ Lunar IceCube, a 6U CubeSat, will prospect for water and other volatiles from a low-periapsis, highly inclined elliptical lunar orbit. Injected from Exploration Mission-1, a lunar gravity assisted multi-body transfer trajectory will capture into a lunar science orbit. The constrained departure asymptote and value of trans-lunar energy limit transfer trajectory types that re-encounter the Moon with the necessary energy and flight duration. Purdue University and Goddard Space Flight Center’s Adaptive Trajectory Design tool and dynamical system research is applied to uncover cislunar spatial regions permitting viable transfer arcs. Numerically integrated transfer designs applying low-thrust and a design framework are described. INTRODUCTION With the increasing miniaturization of spacecraft technologies and availability of rides for secondary payloads onboard larger spacecraft supporting various missions, small spacecraft such as CubeSats offer a significantly reduced cost and development time over conventional, larger spacecraft. These benefits enable public and private entities, as well as educational institutions, to actively participate in space exploration. In fact, twelve CubeSats are intended to be launched onboard the second stage of the upcoming Exploration Mission-1 vehicle (EM-1)1. Following deployment, each secondary payload is injected into a translunar trajectory and must navigate to various destinations by leveraging the natural dynamics and any onboard propulsion. These missions will achieve various scientific and technology demonstration objectives, such as testing solar sail technology, investigating near-Earth asteroids, surveying the Moon for water ice, and measuring the effects of deep-space radiation on living organisms2.
    [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]
  • 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]
  • Smallsats Supporting Deep Space Human Exploration
    National Aeronautics and Space Administration SmallSats supporting Deep Space Human Exploration August 06, 2018 Andres Martinez, Program Executive, Advanced Exploration Systems, HEOMD, NASA HQ Background about me… 2 National Advisory Committee for Aeronautics 3 National Aeronautics and Space Administration 4 NASA 5 Small Spacecraft Technology Program 6 NASA’S DEEP SPACE EXPLORATION SYSTEM The Orion spacecraft and Space Launch System rocket, launching from a modernized Kennedy spaceport is foundational to extending human presence deeper into the solar system. 7 EM-1 Secondary Payloads 13 CUBESATS SELECTED TO FLY ON EM-1 INTERIM • Lunar Flashlight CRYOGENIC • Near Earth Asteroid Scout PROPULSION STAGE • Bio Sentinel • LunaH-MAP • CuSP • Lunar IceCube • LunIR • EQUULEUS (JAXA) • OMOTENASHI (JAXA) • ArgoMoon (ESA) • STMD Centennial Challenge Winners: CU-E3, CisLunar Explorers, & Team Miles HEOMD/AES Deep Space SmallSats: SLS EM-1 Secondary Payloads Lunar IceCube Lunar Flashlight NEA Scout LunIR AES SmallSat Missions selected to contribute to key Human Exploration Strategic Knowledge Gaps and to Advance Key Technologies BioSentinel 10 HEOMD/AES Deep Space SmallSats: Deep Space Station 17 (DSS-17) LRO Demonstrations: • Routinely Tracking LRO at S-band • Intermediate Frequency (IF) Systems and DSN Downlink Equipment (DCD, MarCO Demonstrations: DTT) Verified • Downlink Using X-Band Feed and DSN Equipment • LRO Telemetry Blocks Sent Directly • Downlink Using X-Band Feed and MarCO Receiver System Expands DSN capabilities by utilizing from DSS-17 to JPL DSOC over the • OMSPA Using X-Band Feed and Custom SDR-based NASA Mission Backbone- verifying Multiple Receiver System non-NASA assets to provide DSS-17 Signal Path communication and navigation services FirstFirst OMSPA OMSPA Demonstration Demonstration to small spacecraft missions to the withwith a a CubeSat CubeSat Moon and inner solar 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]