DOCSLIB.ORG

Biosentinel - a Deep Space Radiation Biosensor Mission

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text

Load more

BioSentinel - A Deep Space Radiation BioSensor Mission Bob Hanel – Project Manager James Chartres – Mission Systems Engineer Hugo Sanchez – Spacecraft Bus Systems Engineer CubeSat Developers Workshop 2017 Cal Poly, San Luis Obispo, CA 4/26/17 Authors Affiliated with NASA Ames Research Center, Moffett Field, CA BioSentinel Project Objectives • Advanced Exploration Systems (AES) selected BioSentinel to fly on the Space Launch System (SLS) Exploration Mission (EM-1) as a secondary payload • Payload selected to help fill HEOMD Strategic Knowledge Gaps in Radiation effects on Biology • Delivery to Dispenser Integrator, Tyvak, by 4/30/18 • Current EM-1 Launch Readiness Date (LRD): 9/30/18 • Key BioSentinel Project Objectives • Develop a deep space nanosat capability • Develop a radiation biosensor useful for other missions • Define & validate SLS secondary payload interfaces and accommodations for a biological payload • Collaborate with two other AES selected missions(non-biological) for EM-1 • Near Earth Asteroid (NEA) Scout (MSFC) • Lunar Flashlight (JPL) CubeSat Developers Workshop 2107 – April 26, 2017 2 BioSentinel Science Concept • Quantify DNA damage from space radiation environment – Space environment cannot be reproduced on earth – Omnidirectional, continuous, low flux with varying particle types – Health risk for humans spending long durations beyond LEO – Radiation flux can spike 1000x during a Solar Particle Event (SPE) • Correlate biologic response with LET Spectometer data – BioSensor payload uses engineered S. cerevisiae yeast – Measures rate of Double Strand Breaks (DSB) in DNA – Linear Energy Transfer (LET) Spectrometer measures particle energy and count • Yeast assay uses microfluidic arrays to monitor for DSBs – Three strains of S. cerevisae, two controls and engineered strain – Wet and activate multiple banks of micro-wells over mission lifetime – DSB and associated repair enable cell growth and division – Activate reserve wells in event of a Solar Particle Event (SPE) CubeSat Developers Workshop 2107 – April 26, 2017 3 Secondary Payload Location on SLS EM-1 6U Dispenser Orion Multi-Purpose Crew Vehicle (MPCV) MPCV Stage Adapter (MSA) Interim Cryogenic Space Propulsion Stage Launch (ICPS) Bracket & System Shelf (SLS) Launch Vehicle Adapter (LVSA) Core Stage • 13 - dispenser locations that each support a 6U (14 kg) secondary payload • 1 - bracket location allocated to a sequencer • EM-1 only accommodates 6U payloads; EM-2 may accommodate 12U payloads CubeSat Developers Workshop 2107 – April 26, 2017 4 BioSentinel EM-1 Mission Lunar Transfer & BioSentinel: Escape Launch into Heliocentric Orbit Fly-by Mission Orbit Lunar Transit 3-7 days Launch Secondary P/L Deployment (L+4-5 hrs) ArKst’s rendering • Up to 13 secondary payloads deployed and • Final orbit of secondary's to be determined of the Space powered within the same 2 hour window • Will likely be Earth-interior, heliocentric orbit Launch System • Low relave velocity between secondary payloads • Far outside the LEOs typically occupied by • BioSennel will not perform a delta-V maneuver, CubeSats will follow ICPS into disposal orbit – Range to Earth of 0.73 AU at 18 months – Far outside the protecKve shield of Earth’s magnetosphere CubeSat Developers Workshop 2107 – April 26, 2017 5 BioSentinel FreeFlyer Spacecraft: Physical Overview Low-Gain Antenna Avionics, Power, and Solar Array Gimbal Transponder Stack Solar Arrays BioSensor Payload Propulsion Radiaon Sensor Payloads: System TID + LET spectrometer (CF3)2CH2 Baeries Integrated Guidance Navigaon & Control Unit Medium-Gain Antenna Only showing 2-Panel Gimbaled Solar Array CubeSat Developers Workshop 2107 – April 26, 2017 BioSensor – Optical Measurement of Yeast in Fluidic Card Well 6U Spacecraft ~4U BioSensor Payload Microfluidic cards (x18) Fluidic Card with Optical Detection System Fluidic Card cross section of a single well Fluidic Card Detector & LED Boards CubeSat Developers Workshop 2107 – April 26, 2017 7 BioSensor Payload Hardware 9-Card Manifold with Bubble Traps & Desiccant Nutrient Supply Manifold with Electronics BioSensor 9-Card Manifold Assembly CubeSat Developers Workshop 2107 – April 26, 2017 8 BioSentinel – LET Spectrometer Radiation LET spectrometer supplied by JSC RadWorks • Both LET EDUs have been delivered to ARC • LET EDU#1 will be used to support a EDU spacecraft bus level vibe and thermal test. • LET EDU#2 used in Flatsat testing • First Flight Unit delivery to Ames scheduled for 5/31/17. C&DH Processor LET Spectrometer Simulator RS-422 Interface EDU CubeSat Developers Workshop 2107 – April 26, 2017 9 Solar Array: 2-Panel Gimbal, Adding 2-Panels BioSentinel 2-Panel Gimballed Solar Array EDU 1-Panel deployment test 2-Panel gimbal test BioSentinel with 4-Panel Solar Array. The plan is to keep the 2-panel Gimbaled Hawk array deployed from the 1x3 U sides (trifolds) and then add 2 – 2x3U panels that are also hinged to the gimbal housing CubeSat Developers Workshop 2107 – April 26, 2017 10 Propulsion System, XACT, & Battery Packs XACT ADCS unit sandwiched between 2 battery packs (top & bottom) Propulsion System CubeSat Developers Workshop 2107 – April 26, 2017 11 Spacecraft Subsystem Fit CheckFit Initial fit check of Structural Panels, Propulsion System, XACT, 2 Battery Packs, Iris Transponder Thermal Simulator, Sun Sensor, Dispenser Separation Connector CubeSat Developers Workshop 2107 – April 26, 2017 12 Thermal System Analysis Thermal challenge is to keep warm spacecraft bus subsytems isolated from BioSensor (4-6°C). Cards raised to 23°C during cell growth phase CubeSat Developers Workshop 2107 – April 26, 2017 13 BioSentinel Mission Phases Phase Entry Exit Duration Summary & Objectives Pre-Launch Loading of biology L/V Lift-off ~6 months • Configure BioSentinel for launch, then power-off Launch L/V Lift-off Launcher Deploys ~5 hours • Powered off BioSentinel • Survive launch environments and deployment Initialization BioSentinel Complete S/C ~14 days • Power-on, reduce tip-off rates, separates from checkout deploy solar arrays, transition SLS to safe mode • Ground station initial acquisition and tracking • Check-out of S/C systems • Lunar fly-by likely to occur Science Nominal Spacecraft Final BioSensor 365 days (goal • Collect data from all payloads SOH card is expired of 540) • Execute card experiments per science timeline • Respond to SPE events • Collect Spacecraft SOH Decommissioning End of Nominal Final pass with ~7 days • Ensure all data downlinked (note, not same as Science Operations decommissioning • Solar array switches open to Project Phase F) command ensure battery never recharges CubeSat Developers Workshop 2107 – April 26, 2017 BioSentinel Link Margin (dB) vs. Mission Days CubeSat Developers Workshop 2107 – April 26, 2017 15 BioSentinel Month-in-the-Life ConOps Monitor Bus Functions Transmit to DSN (Daily, 30 minute contact, ATS) 3 1 Media A: 4 weeks 1 Media B: 2 weeks 2 2 Wet new cards with Media A Wet cards with Media B (2 fluidic cards every 6 weeks, ATS) Collect science data (4 weeks after Media A, RTS) (Continuous, RTS) Major Functions Sub-functions Major Functions Sub-functions Major Sub-functions 1 2 3 Functions Select card • Determine fluidic card Readout • Determine fluidic card Align • Determine vector to • Select µ-controller BioSensor • Select u-controller spacecraft Earth • Select pump and valve (15 min cadence) • Select and power well • Slew to Earth vector set LEDs • Select and readout sensor Power Tx • Power transmitter Apply Fluids • Open inlet valve • Iterate all wells • Open plate valve • Open nutrient valves Readout TID • Apply power to sensor Broadcast data • Broadcast SOH • Activate Pump sensor • Wait for stabilization • On CFDP command, (5 min cadence) • Sample analog readouts transmit BioSensor, Configure • Apply cold set points to LET, TID data Thermal Control other cards Readout LET • Acquire binned data • Warm set points for Spectrometer • Store data in file system Deactivate Tx • Power off transmitter Media B sensor (1 hour cadence) Realign • Slew back to sun Close System • Close inlet valve spacecraft vector • Close plate valve Monitor for SPE • Sample TID readout • Close nutrient valves • Sample LET shutter info • De-activate pump • Wet new card if SPE detected CubeSat Developers Workshop 2107 – April 26, 2017 Ground System Architecture Space Communication and Mission Operations Center - ARC Navigation (SCaN) Networks NASA Deep Space Network Telemetry & Command TLM and Activity Planning (DSN) Command Sequencing X-band CMDS System Goldstone 34-m BWG (x3) System System TLM, CMD Station Status and TRK Goldstone 34-m HEF (x1) Packets Canberra 34-m BWG (x3*) Canberra 34-m HEF (x1) Stored TLM Flight Dynamics Engineering Plotting & Madrid 34-m BWG (x2) Files System Analysis System Trending System X-band Madrid 34-m HEF (x1) Tracking Files TLM, CMD Morehead St 21-m (x1) (in dev.) and TRK Ephemeris/Acq (early Simulation Monitor & Short-Term Data Files mission) NASA Near Earth Network System Alerting System Archival System (NEN) Scheduling Hawaii 13-m (x2) Files Wallops 11-m (D/L only) File & Data Management Dongara 13-m / 7-m Hartebeethok 10-m (D/L only) Productivity Tools TLM and CMDS Networking International Space Station (ISS) Infrastructure Stored TLM Mission Files and SPE Planning e HK TLM v ISS On- Science Planning Inputs Input r e Ground board HOSC Products S Dist. Payload Env. TLM o i Network TLM and and CMDS B Science Data Center - ARC CMDS Science Data Plotting & Short-Term Data Delayed Async. Ground Control Facility - ARC Calibration
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)

    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.
  • Lunar Flashlight & NEA Scout

    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
  • Lunar Life Sciences Payload Assessment

    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.
  • Developing Technologies for Biological Experiments in Deep Space

    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.
  • Pre-Launch Testing of the Lunar Flashlight (LF) Cubesat GNC System David C

    Pre-Launch Testing of the Lunar Flashlight (LF) Cubesat GNC System David C

    Sternberg, D. C. et al. (2021): JoSS, Vol. 10, No. 1, pp. 959–981 (Peer-reviewed article available at www.jossonline.com) www.adeepakpublishing.com www. JoSSonline.com Pre-Launch Testing of the Lunar Flashlight (LF) CubeSat GNC System David C. Sternberg, Peter C. Lai, Aadil Rizvi, Kevin F. Ortega, Kevin D. Lo, Philippe C. Adell, and John D. Baker Jet Propulsion Laboratory California Institute of Technology Pasadena, CA, US Abstract Lunar Flashlight (LF) is a 6U, 14 kg spacecraft that will measure potential surface water ice deposits in the permanently shadowed region (PSR) of the moon. The mission described in this paper will use IR laser technology to search for volatiles in preparation for future human lunar exploration. A CubeSat’s guidance, navigation and control (GNC) system is crucial for the spacecraft to successfully reach the moon, enter a lunar orbit, and acquire scientific data. The Jet Propulsion Laboratory (JPL) has adopted a commercial-off-the-shelf (COTS) integrated GNC spacecraft system after experience from over twenty CubeSat missions. When hardware is delivered to JPL by the vendor, thorough validation testing is performed to guarantee fundamental functionality before the hard- ware is integrated into the spacecraft. Moreover, while the validation processes for the first few CubeSats relying on similar COTS-integrated GNC systems at JPL were very fluid, LF represents the first attempt JPL has made to apply large-mission, rigorous testing processes to a CubeSat, with the intent of standardizing the testing process for a rapidly growing number of CubeSats at JPL. This paper presents the rigorous testing concept applied to the GNC system, the various tests that have been performed and standardized, and the data acquired during the testing campaign to ensure that the LF GNC system will function as part of the integrated spacecraft once launched.
  • Lunar Flashlight

    Lunar Flashlight

    https://ntrs.nasa.gov/search.jsp?R=20160008001 2019-08-29T23:45:10+00:00Z Lunar Flashlight Project Manager(s)/Lead(s) John Baker (PM)/Jet Propulsion Laboratory (818) 354–5004 Barbara Cohen (PI)/ZP13 (256) 961–7901 Amy Walden (Project Lead)/FP30 (256) 961–2358 Sponsoring Program(s) Human Exploration and Operations Mission Directorate Advanced Exploration Systems Figure 1: Artist concept of the Lunar Flashlight mission over the lunar surface. Project Description The Lunar Flashlight is a Jet Propulsion Laboratory project, with NASA Marshall Space Flight Center (MSFC) serving as the principal investigator and pro- viding the solar sail propulsion system. The goal of Lunar Flashlight is to determine the presence and abun- dance of exposed lunar water ice within permanently shadowed regions (PSRs) at the lunar south pole, and to map its concentration at the 1–2 km scale to sup- port future exploration and use. After being ejected in cis-lunar space by the launch vehicle, Lunar Flashlight deploys solar panels and an 85-m2 solar sail and maneu- vers into a low-energy transfer to lunar orbit. The solar sail and attitude control system work to bring the satel- lite into an elliptical polar orbit, spiraling down over a period of 18 months to a perilune of 30–10 km above the south pole for data collection. Lunar Flashlight uses Figure 2: Reflectivity testing of the material that will be used to build the Lunar Flashlight solar sail. its solar sail to shine reflected sunlight onto the lunar surface, measuring surface reflectance with a four-filter point spectrometer.
  • Payload Design for the Lunar Flashlight Mission

    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.
  • AES-Secondaries-FS-V508b.Pdf

    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).
  • JPL's Planetary Cubesat Missions in Implementation: Marco, Lunar

    JPL's Planetary Cubesat Missions in Implementation: Marco, Lunar

    Abstract for 11th Low Cost Planetary Missions Conference June 9-11, 2015, Berlin, Germany JPL’s Planetary CubeSat Missions in Implementation: MarCO, Lunar Flashlight, and NEA Scout Frick, A., JPL; Klesh, A., JPL; Krajewski, J., JPL; Castillo-Rogez, J., JPL; Baker, J., JPL; Hartford, W., JPL; Alibay, F., JPL; Loomis, C., JPL; Imken, T., JPL; Johnson, L., NASA MSFC; Cohen, B., NASA MSFC; McNutt, L., NASA MSFC; Dervan, J.; MSFC JPL is currently developing three planetary CubeSat missions to launch in the near future to Mars, the Moon, and a Near Earth Asteroid. Mars CubeSat One (MarCO) would become the first interplanetary CubeSat, currently slated to launch with the NASA InSight Mars lander in March of 2016. MarCO is designed to provide real-time relay of Insight’s Entry, Descent, and Landing (EDL) telemetry to complement recorded and replayed data from MRO. In addition to MarCO, JPL is designing the flight systems for Lunar Flashlight and NEA Scout, developed jointly with the NASA Marshall Space Flight Center to be launched on the first uncrewed mission of the Space Launch System (SLS) in 2018. Lunar Flashlight would use a solar sail developed at the NASA Marshall Space Flight Center to achieve a lunar orbit and reflect sunlight into permanently shadowed regions of the Moon. Using the reflected photons and a simple spectrometer, Lunar Flashlight would be capable of mapping lunar volatiles, including water ice, at the lunar south pole. Lead by Marshall Space Flight Center, NEA Scout would use the same solar sail and JPL-developed deep space nano-spacecraft bus as Lunar Flashlight.
  • Cubesat for Planetary Science and Exploration Breaking New Grounds

    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
  • Biosentinel: ! DNA Damage-And-Repair Experiment ! Beyond Low Earth Orbit!

    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
  • Determining Volatile Systematics Via Lunar Orbiting Cubesat

    Determining Volatile Systematics Via Lunar Orbiting Cubesat

    EPSC Abstracts Vol. 10, EPSC2015-61, 2015 European Planetary Science Congress 2015 EEuropeaPn PlanetarSy Science CCongress c Author(s) 2015 Lunar Ice Cube: Determining Volatile Systematics Via Lunar Orbiting Cubesat P.E. Clark (1,2,3), B. Malphrus (4), R. MacDowall (2), D. Folta (2), A. Mandell (2), C. Brambora (2), D. Patel (2), S. Banks (2), K. Hohman (5), V. Hruby (5), K. Brown (4), J. Kruth (4), and R. Cox (3). (1) Institute for Astrophysics and Computational Sciences, Catholic University of America, Washington DC, [email protected]; (2) NASA/GSFC, Greenbelt, MD, USA; (3) Flexure Engineering Inc., Seattle, WA, USA; (4) Morehead State University, Morehead, KY, USA, [email protected]; (5) Busek Company, Natick, MA, USA. Abstract Earth escape to lunar capture), communication, power, thermal and radiation protection systems We have applied the CubeSat Paradigm to science providing lunar orbital operation of a cubesat bus. requirements-driven deep space exploration mission, Based on this work, we have concluded that a 6U bus Lunar Ice Cube, and are developing a compact with state of the art cubesat systems already available 'workhorse' instrument for a high priority science or now being built and tested can support a high application, which has just been selected for the priority science orbiter in cislunar space. Particular HEOMD NextSTEP program for EM1 launch. Lunar challenges for lunar cubesats are remote Ice Cube complements Lunar Flashlight, a mission communication, navigation and tracking, thermal and previously selected for EM1, by focusing on the radiation protection in a volume, power, and abundance, location and transportation physics of bandwidth constrained environment.