Small Satellites for Space Science: a COSPAR Scientific Roadmap
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NASA’s Space Launch System: Deep-Space Delivery for Smallsats Dr. Kimberly F. Robinson1 and George Norris2 NASA Marshall Space Flight Center, Huntsville, AL, 35812 ABSTRACT Designed for human exploration missions into deep space, NASA’s Space Launch System (SLS) represents a new spaceflight infrastructure asset, enabling a wide variety of unique utilization opportunities. While primarily focused on launching the large systems needed for crewed spaceflight beyond Earth orbit, SLS also offers a game-changing capability for the deployment of small satellites to deep-space destinations, beginning with its first flight. Currently, SLS is making rapid progress toward readiness for its first launch in two years, using the initial configuration of the vehicle, which is capable of delivering 70 metric tons (t) to Low Earth Orbit (LEO). On its first flight test of the Orion spacecraft around the moon, accompanying Orion on SLS will be small-satellite secondary payloads, which will deploy in cislunar space. The deployment berths are sized for “6U” CubeSats, and on EM-1 the spacecraft will be deployed into cislunar space following Orion separate from the SLS Interim Cryogenic Propulsion Stage. Payloads in 6U class will be limited to 14 kg maximum mass. Secondary payloads on EM-1 will be launched in the Orion Stage Adapter (OSA). Payload dispensers will be mounted on specially designed brackets, each attached to the interior wall of the OSA. For the EM-1 mission, a total of fourteen brackets will be installed, allowing for thirteen payload locations. The final location will be used for mounting an avionics unit, which will include a battery and sequencer for executing the mission deployment sequence. -
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. -
University of Iowa Instruments in Space
University of Iowa Instruments in Space A-D13-089-5 Wind Van Allen Probes Cluster Mercury Earth Venus Mars Express HaloSat MMS Geotail Mars Voyager 2 Neptune Uranus Juno Pluto Jupiter Saturn Voyager 1 Spaceflight instruments designed and built at the University of Iowa in the Department of Physics & Astronomy (1958-2019) Explorer 1 1958 Feb. 1 OGO 4 1967 July 28 Juno * 2011 Aug. 5 Launch Date Launch Date Launch Date Spacecraft Spacecraft Spacecraft Explorer 3 (U1T9)58 Mar. 26 Injun 5 1(U9T68) Aug. 8 (UT) ExpEloxrpelro r1e r 4 1915985 8F eJbu.l y1 26 OEGxOpl o4rer 41 (IMP-5) 19697 Juunlye 2 281 Juno * 2011 Aug. 5 Explorer 2 (launch failure) 1958 Mar. 5 OGO 5 1968 Mar. 4 Van Allen Probe A * 2012 Aug. 30 ExpPloiorenre 3er 1 1915985 8M Oarc. t2. 611 InEjuxnp lo5rer 45 (SSS) 197618 NAouvg.. 186 Van Allen Probe B * 2012 Aug. 30 ExpPloiorenre 4er 2 1915985 8Ju Nlyo 2v.6 8 EUxpKlo 4r e(rA 4ri1el -(4IM) P-5) 197619 DJuenc.e 1 211 Magnetospheric Multiscale Mission / 1 * 2015 Mar. 12 ExpPloiorenre 5e r 3 (launch failure) 1915985 8A uDge.c 2. 46 EPxpiolonreeerr 4130 (IMP- 6) 19721 Maarr.. 313 HMEaRgCnIe CtousbpeShaetr i(cF oMxu-1ltDis scaatelell itMe)i ssion / 2 * 2021081 J5a nM. a1r2. 12 PionPeioenr e1er 4 1915985 9O cMt.a 1r.1 3 EExpxlpolorerer r4 457 ( S(IMSSP)-7) 19721 SNeopvt.. 1263 HMaalogSnaett oCsupbhee Sriact eMlluitlet i*scale Mission / 3 * 2021081 M5a My a2r1. 12 Pioneer 2 1958 Nov. 8 UK 4 (Ariel-4) 1971 Dec. 11 Magnetospheric Multiscale Mission / 4 * 2015 Mar. -
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 -
Wide-Field Infrared Survey Explorer Launch Press
PRess KIT/DECEMBER 2009 Wide-field Infrared Survey Explorer Launch Contents Media Services Information ................................................................................................................. 3 Quick Facts ............................................................................................................................................. 4 Mission Overview .................................................................................................................................. 5 Why Infrared? ....................................................................................................................................... 10 Science Goals and Objectives ......................................................................................................... 12 Spacecraft ............................................................................................................................................. 16 Science Instrument ............................................................................................................................. 19 Infrared Missions: Past and Present ............................................................................................... 23 NASA’s Explorer Program ................................................................................................................. 25 Program/Project Management .......................................................................................................... 27 Media Contacts J.D. Harrington -
Proceedings of Spie
PROCEEDINGS OF SPIE SPIEDigitalLibrary.org/conference-proceedings-of-spie Ground calibration of the spatial response and quantum efficiency of the CdZnTe hard x-ray detectors for NuSTAR Brian W. Grefenstette, Varun Bhalerao, W. Rick Cook, Fiona A. Harrison, Takao Kitaguchi, et al. Brian W. Grefenstette, Varun Bhalerao, W. Rick Cook, Fiona A. Harrison, Takao Kitaguchi, Kristin K. Madsen, Peter H. Mao, Hiromasa Miyasaka, Vikram Rana, "Ground calibration of the spatial response and quantum efficiency of the CdZnTe hard x-ray detectors for NuSTAR," Proc. SPIE 10392, Hard X-Ray, Gamma-Ray, and Neutron Detector Physics XIX, 1039207 (29 August 2017); doi: 10.1117/12.2271365 Event: SPIE Optical Engineering + Applications, 2017, San Diego, California, United States Downloaded From: https://www.spiedigitallibrary.org/conference-proceedings-of-spie on 1/5/2018 Terms of Use: https://www.spiedigitallibrary.org/terms-of-use Ground Calibration of the Spatial Response and Quantum Efficiency of the CdZnTe Hard X-ray Detectors for NuSTAR Brian W. Grefenstette1, Varun Bhalerao2, W. Rick Cook1, Fiona A. Harrison1, Takao Kitaguchi3, Kristin K. Madsen1, Peter H. Mao1, Hiromasa Miyasaka1, Vikram Rana1 1Space Radiation Lab, California Institute of Technology (Caltech), Pasadena, CA 2Department of Physics, Indian Institute of Technology Bombay, Powai, Mumbai, India 3RIKEN Nishina Center, 2-1 Hirosawa, Wako, Saitama 351-0198, Japan ABSTRACT Pixelated Cadmium Zinc Telluride (CdZnTe) detectors are currently flying on the Nuclear Spectroscopic Tele- scope ARray (NuSTAR) NASA Astrophysics Small Explorer. While the pixel pitch of the detectors is ≈ 605 µm, we can leverage the detector readout architecture to determine the interaction location of an individual photon to much higher spatial accuracy. -
2018: Aiaa-Space-Report
AIAA TEAM SPACE TRANSPORTATION DESIGN COMPETITION TEAM PERSEPHONE Submitted By: Chelsea Dalton Ashley Miller Ryan Decker Sahil Pathan Layne Droppers Joshua Prentice Zach Harmon Andrew Townsend Nicholas Malone Nicholas Wijaya Iowa State University Department of Aerospace Engineering May 10, 2018 TEAM PERSEPHONE Page I Iowa State University: Persephone Design Team Chelsea Dalton Ryan Decker Layne Droppers Zachary Harmon Trajectory & Propulsion Communications & Power Team Lead Thermal Systems AIAA ID #908154 AIAA ID #906791 AIAA ID #532184 AIAA ID #921129 Nicholas Malone Ashley Miller Sahil Pathan Joshua Prentice Orbit Design Science Science Science AIAA ID #921128 AIAA ID #922108 AIAA ID #761247 AIAA ID #922104 Andrew Townsend Nicholas Wijaya Structures & CAD Trajectory & Propulsion AIAA ID #820259 AIAA ID #644893 TEAM PERSEPHONE Page II Contents 1 Introduction & Problem Background2 1.1 Motivation & Background......................................2 1.2 Mission Definition..........................................3 2 Mission Overview 5 2.1 Trade Study Tools..........................................5 2.2 Mission Architecture.........................................6 2.3 Planetary Protection.........................................6 3 Science 8 3.1 Observations of Interest.......................................8 3.2 Goals.................................................9 3.3 Instrumentation............................................ 10 3.3.1 Visible and Infrared Imaging|Ralph............................ 11 3.3.2 Radio Science Subsystem................................. -
Accessing Pds Data in Pipeline Processing and Web Sites Through Pds Geosciences Orbital Data Explorer’S Web-Based Api (Rest) Interface
45th Lunar and Planetary Science Conference (2014) 1026.pdf ACCESSING PDS DATA IN PIPELINE PROCESSING AND WEB SITES THROUGH PDS GEOSCIENCES ORBITAL DATA EXPLORER’S WEB-BASED API (REST) INTERFACE. K. J. Bennett, J. Wang, D. Scholes, Washington University in St. Louis, 1 Brookings Drive, Campus Box 1169, St. Louis, Missouri, 63130, {bennett, wang, sholes}@wunder.wustl.edu. Introduction: The Orbital Data Explorer (ODE) is tem (RSS). a web-based search tool (http://ode.rsl.wustl.edu) de- High Resolution Stereo Camera (HRSC), Mars Advanced Radar for Subsurface and Iono- veloped at NASA’s Planetary Data System’s (PDS) sphere Sounding (MARSIS), OMEGA Geosciences Node (http://pds-geosciences.wustl.edu/). Mars Express (Observatoire Mineralogie, Eau, Glaces, Through ODE, users can search, browse, and download Activite) Visible and Infrared Mineralogical a wide range of PDS Mars, Moon, Mercury, and Venus Mapping Spectrometer, and Planetary Fourier Spectrometer (PFS). data ([1,2,3,4]). Mars Orbiter Laser Altimeter (MOLA), and Mars Global In the fall of 2012, the Geosciences node intro- MOC Narrow Angle (NA) and Wide Angle Surveyor (MGS) duced a simple web-based API that allows non-PDS (WA) cameras. Gamma Ray Spectrometer (GRS) and Thermal web and processing tools to search for PDS products, Odyssey Emission Imaging System (THEMIS) obtain meta-data about those products, and download Viking Orbiter Visual Imaging Subsystem Camera A/B the products stored in ODE’s meta-data database. The Gamma Ray Spectrometer (GRS), Radio Sci- first version is now used by several teams in periodic MESSENGER ence Subsystem (RSS), Neutron Spectrometer processing and web sites. -
Abstracts of the 50Th DDA Meeting (Boulder, CO)
Abstracts of the 50th DDA Meeting (Boulder, CO) American Astronomical Society June, 2019 100 — Dynamics on Asteroids break-up event around a Lagrange point. 100.01 — Simulations of a Synthetic Eurybates 100.02 — High-Fidelity Testing of Binary Asteroid Collisional Family Formation with Applications to 1999 KW4 Timothy Holt1; David Nesvorny2; Jonathan Horner1; Alex B. Davis1; Daniel Scheeres1 Rachel King1; Brad Carter1; Leigh Brookshaw1 1 Aerospace Engineering Sciences, University of Colorado Boulder 1 Centre for Astrophysics, University of Southern Queensland (Boulder, Colorado, United States) (Longmont, Colorado, United States) 2 Southwest Research Institute (Boulder, Connecticut, United The commonly accepted formation process for asym- States) metric binary asteroids is the spin up and eventual fission of rubble pile asteroids as proposed by Walsh, Of the six recognized collisional families in the Jo- Richardson and Michel (Walsh et al., Nature 2008) vian Trojan swarms, the Eurybates family is the and Scheeres (Scheeres, Icarus 2007). In this theory largest, with over 200 recognized members. Located a rubble pile asteroid is spun up by YORP until it around the Jovian L4 Lagrange point, librations of reaches a critical spin rate and experiences a mass the members make this family an interesting study shedding event forming a close, low-eccentricity in orbital dynamics. The Jovian Trojans are thought satellite. Further work by Jacobson and Scheeres to have been captured during an early period of in- used a planar, two-ellipsoid model to analyze the stability in the Solar system. The parent body of the evolutionary pathways of such a formation event family, 3548 Eurybates is one of the targets for the from the moment the bodies initially fission (Jacob- LUCY spacecraft, and our work will provide a dy- son and Scheeres, Icarus 2011). -
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 -
The Cassini Ion and Neutral Mass Spectrometer (Inms) Investigation
THE CASSINI ION AND NEUTRAL MASS SPECTROMETER (INMS) INVESTIGATION 1, 2 3 4 J. H. WAITE ∗, JR., W. S. LEWIS ,W.T. KASPRZAK ,V.G. ANICICH , B. P. BLOCK1,T.E. CRAVENS5,G.G. FLETCHER1,W.-H. IP6,J.G. LUHMANN7, R. L. MCNUTT8,H.B. NIEMANN3,J.K.PAREJKO1,J.E. RICHARDS3, R. L. THORPE2, E. M. WALTER1 and R. V. YELLE9 1University of Michigan, Ann Arbor, MI, U.S.A. 2Southwest Research Institute, San Antonio, TX, U.S.A. 3NASA Goddard Space Flight Center, Greenbelt, MD, U.S.A. 4NASA Jet Propulsion Laboratory, Pasadena, CA, U.S.A. 5University of Kansas, Lawrence, KS, U.S.A. 6National Central University, Chung-Li, Taiwan 7University of California, Berkeley, CA, U.S.A. 8Johns Hopkins University Applied Physics Laboratory, Laurel, MD, U.S.A. 9University of Arizona, Flagstaff, AZ, U.S.A. (∗Author for correspondence, E-mail: [email protected]) (Received 13 August 1998; Accepted in final form 17 February 2004) Abstract. The Cassini Ion and Neutral Mass Spectrometer (INMS) investigation will determine the mass composition and number densities of neutral species and low-energy ions in key regions of the Saturn system. The primary focus of the INMS investigation is on the composition and structure of Titan’s upper atmosphere and its interaction with Saturn’s magnetospheric plasma. Of particular interest is the high-altitude region, between 900 and 1000 km, where the methane and nitrogen photochemistry is initiated that leads to the creation of complex hydrocarbons and nitriles that may eventually precipitate onto the moon’s surface to form hydrocarbon–nitrile lakes or oceans. -
A Pictorial History of Rockets
he mighty space rockets of today are the result A Pictorial Tof more than 2,000 years of invention, experi- mentation, and discovery. First by observation and inspiration and then by methodical research, the History of foundations for modern rocketry were laid. Rockets Building upon the experience of two millennia, new rockets will expand human presence in space back to the Moon and Mars. These new rockets will be versatile. They will support Earth orbital missions, such as the International Space Station, and off- world missions millions of kilometers from home. Already, travel to the stars is possible. Robotic spacecraft are on their way into interstellar space as you read this. Someday, they will be followed by human explorers. Often lost in the shadows of time, early rocket pioneers “pushed the envelope” by creating rocket- propelled devices for land, sea, air, and space. When the scientific principles governing motion were discovered, rockets graduated from toys and novelties to serious devices for commerce, war, travel, and research. This work led to many of the most amazing discoveries of our time. The vignettes that follow provide a small sampling of stories from the history of rockets. They form a rocket time line that includes critical developments and interesting sidelines. In some cases, one story leads to another, and in others, the stories are inter- esting diversions from the path. They portray the inspirations that ultimately led to us taking our first steps into outer space. NASA’s new Space Launch System (SLS), commercial launch systems, and the rockets that follow owe much of their success to the accomplishments presented here.