NASA Deep Space Network
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Mission to Jupiter
This book attempts to convey the creativity, Project A History of the Galileo Jupiter: To Mission The Galileo mission to Jupiter explored leadership, and vision that were necessary for the an exciting new frontier, had a major impact mission’s success. It is a book about dedicated people on planetary science, and provided invaluable and their scientific and engineering achievements. lessons for the design of spacecraft. This The Galileo mission faced many significant problems. mission amassed so many scientific firsts and Some of the most brilliant accomplishments and key discoveries that it can truly be called one of “work-arounds” of the Galileo staff occurred the most impressive feats of exploration of the precisely when these challenges arose. Throughout 20th century. In the words of John Casani, the the mission, engineers and scientists found ways to original project manager of the mission, “Galileo keep the spacecraft operational from a distance of was a way of demonstrating . just what U.S. nearly half a billion miles, enabling one of the most technology was capable of doing.” An engineer impressive voyages of scientific discovery. on the Galileo team expressed more personal * * * * * sentiments when she said, “I had never been a Michael Meltzer is an environmental part of something with such great scope . To scientist who has been writing about science know that the whole world was watching and and technology for nearly 30 years. His books hoping with us that this would work. We were and articles have investigated topics that include doing something for all mankind.” designing solar houses, preventing pollution in When Galileo lifted off from Kennedy electroplating shops, catching salmon with sonar and Space Center on 18 October 1989, it began an radar, and developing a sensor for examining Space interplanetary voyage that took it to Venus, to Michael Meltzer Michael Shuttle engines. -
NASA's Lunar Atmosphere and Dust Environment Explorer (LADEE)
Geophysical Research Abstracts Vol. 13, EGU2011-5107-2, 2011 EGU General Assembly 2011 © Author(s) 2011 NASA’s Lunar Atmosphere and Dust Environment Explorer (LADEE) Richard Elphic (1), Gregory Delory (1,2), Anthony Colaprete (1), Mihaly Horanyi (3), Paul Mahaffy (4), Butler Hine (1), Steven McClard (5), Joan Salute (6), Edwin Grayzeck (6), and Don Boroson (7) (1) NASA Ames Research Center, Moffett Field, CA USA ([email protected]), (2) Space Sciences Laboratory, University of California, Berkeley, CA USA, (3) Laboratory for Atmospheric and Space Physics, University of Colorado, Boulder, CO USA, (4) NASA Goddard Space Flight Center, Greenbelt, MD USA, (5) LunarQuest Program Office, NASA Marshall Space Flight Center, Huntsville, AL USA, (6) Planetary Science Division, Science Mission Directorate, NASA, Washington, DC USA, (7) Lincoln Laboratory, Massachusetts Institute of Technology, Lexington MA USA Nearly 40 years have passed since the last Apollo missions investigated the mysteries of the lunar atmosphere and the question of levitated lunar dust. The most important questions remain: what is the composition, structure and variability of the tenuous lunar exosphere? What are its origins, transport mechanisms, and loss processes? Is lofted lunar dust the cause of the horizon glow observed by the Surveyor missions and Apollo astronauts? How does such levitated dust arise and move, what is its density, and what is its ultimate fate? The US National Academy of Sciences/National Research Council decadal surveys and the recent “Scientific Context for Exploration of the Moon” (SCEM) reports have identified studies of the pristine state of the lunar atmosphere and dust environment as among the leading priorities for future lunar science missions. -
LADEE PDS Mission Description Center Document Document No: DES-12.LADEE.LPMD Rev.: 1.5 Effective Date: 05-13-2014
Ames Research Title: LADEE PDS Mission Description Center Document Document No: DES-12.LADEE.LPMD Rev.: 1.5 Effective Date: 05-13-2014 Lunar Atmosphere and Dust Environment Explorer (LADEE) LADEE PDS Mission Description th May 13 , 2014 Ames Research Center Moffett Field, California National Aeronautics and Space Administration i Ames Research Title: LADEE PDS Mission Description Center Document Document No: DES-12.LADEE.LPMD Rev.: 1.5 Effective Date: 05-13-2014 This document is approved in accordance with LADEE Configuration Management Plan, C04.LADEE.CM, paragraph 3.6.1.1 Document Release Routing Approval Process. Page three of this document contains the approved routed release of this document. Approval Signatures _______________________________________ ___________ Butler Hine Date LADEE Project Manager _______________________________________ ___________ Gregory T. Delory Date LADEE Deputy Project Scientist _______________________________________ ___________ Date _______________________________________ ___________ Date ii Ames Research Title: LADEE PDS Mission Description Center Document Document No: DES-12.LADEE.LPMD Rev.: 1.5 Effective Date: 05-13-2014 This page is reserved for routing approval document iii Ames Research Title: LADEE PDS Mission Description Center Document Document No: DES-12.LADEE.LPMD Rev.: 1.5 Effective Date: 05-13-2014 REVISION HISTORY Rev. Description of Change Author(s) Effective Date 1.0 Initial draft G. Delory Nov 1, 2012 1.1 Resolved several TBDs G. Delory Nov 29, 2012 Updated TOC and prepared for conversion to PDF March 21, 1.2 G. Delory 2012 Baseline March 21, NC G. Delory 2012 Edited mission objective #2 as per PDS peer review 1.3 G. Delory April 4, 2013 results Updated mission timeline and orbit plots to reflect as- 1.4 G. -
NASA's STEREO Mission
NASA’s STEREO Mission J.B. Gurman STEREO Project Scientist W.T. Thompson STEREO Chief Observer Solar Physics Laboratory, Helophysics Division NASA Goddard Space Flight Center 1 The STEREO Mission • Science and technology definition team report, 1997 December: • Understand the origin and consequences of coronal mass ejections (CMEs) • Two spacecraft in earth-leading and -lagging orbits near 1 AU (Solar Terrestrial Probe line) • “Beacon” mode for near-realtime warning of potentially geoeffective events 2 Level 1 Requirements • Understand the causes and mechanisms of CME initiation • Characterize the propagation of CMEs through the heliosphere • Discover the mechanisms and sites of energetic particle acceleration in the low corona and the interplanetary medium • Develop a 3D, time-dependent model of the magnetic topology, temperature, density, and velocity structure of the ambient solar wind 3 Implementation • Two nearly identical spacecraft launched by a single ELV • Bottom spacecraft in stack has adapter ring, some strengthening • Spacecraft built at Johns Hopkins University APL • Four science investigations 4 Scientific Instruments • S/WAVES - broad frequency response RF detection of Type II, III bursts • PLASTIC - solar wind plasma and suprathermal ion composition measurements • IMPACT - energetic electrons and ions, magnetic field • SECCHI - EUV, coronagraphs and heliospheric imagers (surface to 1.5 AU) 5 Instrument Hardware • PLASTIC IMPACT boom IMPACT boom SECCHI SCIP SECCHI HI S/WAVES 6 Orbit Design • Science team selected a separation -
Nustar Observatory Guide
NuSTAR Guest Observer Program NuSTAR Observatory Guide Version 3.2 (June 2016) NuSTAR Science Operations Center, California Institute of Technology, Pasadena, CA NASA Goddard Spaceflight Center, Greenbelt, MD nustar.caltech.edu heasarc.gsfc.nasa.gov/docs/nustar/index.html i Revision History Revision Date Editor Comments D1,2,3 2014-08-01 NuSTAR SOC Initial draft 1.0 2014-08-15 NuSTAR GOF Release for AO-1 Addition of more information about CZT 2.0 2014-10-30 NuSTAR SOC detectors in section 3. 3.0 2015-09-24 NuSTAR SOC Update to section 4 for release of AO-2 Update for NuSTARDAS v1.6.0 release 3.1 2016-05-10 NuSTAR SOC (nusplitsc, Section 5) 3.2 2016-06-15 NuSTAR SOC Adjustment to section 9 ii Table of Contents Revision History ......................................................................................................................................................... ii 1. INTRODUCTION ................................................................................................................................................... 1 1.1 NuSTAR Program Organization ..................................................................................................................................................................................... 1 2. The NuSTAR observatory .................................................................................................................................... 2 2.1 NuSTAR Performance ........................................................................................................................................................................................................ -
Jjmonl 1603.Pmd
alactic Observer GJohn J. McCarthy Observatory Volume 9, No. 3 March 2016 GRAIL - On the Trail of the Moon's Missing Mass GRAIL (Gravity Recovery and Interior Laboratory) was a NASA scientific mission in 2011/12 to map the surface of the moon and collect data on gravitational anomalies. The image here is an artist's impres- sion of the twin satellites (Ebb and Flow) orbiting in tandem above a gravitational image of the moon. See inside, page 4 for information on gravitational anomalies (mascons) or visit http://solarsystem. nasa.gov/grail. The John J. McCarthy Observatory Galactic Observer New Milford High School Editorial Committee 388 Danbury Road Managing Editor New Milford, CT 06776 Bill Cloutier Phone/Voice: (860) 210-4117 Production & Design Phone/Fax: (860) 354-1595 www.mccarthyobservatory.org Allan Ostergren Website Development JJMO Staff Marc Polansky It is through their efforts that the McCarthy Observatory Technical Support has established itself as a significant educational and Bob Lambert recreational resource within the western Connecticut Dr. Parker Moreland community. Steve Barone Jim Johnstone Colin Campbell Carly KleinStern Dennis Cartolano Bob Lambert Mike Chiarella Roger Moore Route Jeff Chodak Parker Moreland, PhD Bill Cloutier Allan Ostergren Cecilia Dietrich Marc Polansky Dirk Feather Joe Privitera Randy Fender Monty Robson Randy Finden Don Ross John Gebauer Gene Schilling Elaine Green Katie Shusdock Tina Hartzell Paul Woodell Tom Heydenburg Amy Ziffer In This Issue "OUT THE WINDOW ON YOUR LEFT" ............................... 4 SUNRISE AND SUNSET ...................................................... 13 MARE HUMBOLDTIANIUM AND THE NORTHEAST LIMB ......... 5 JUPITER AND ITS MOONS ................................................. 13 ONE YEAR IN SPACE ....................................................... 6 TRANSIT OF JUPITER'S RED SPOT .................................... -
+ New Horizons
Media Contacts NASA Headquarters Policy/Program Management Dwayne Brown New Horizons Nuclear Safety (202) 358-1726 [email protected] The Johns Hopkins University Mission Management Applied Physics Laboratory Spacecraft Operations Michael Buckley (240) 228-7536 or (443) 778-7536 [email protected] Southwest Research Institute Principal Investigator Institution Maria Martinez (210) 522-3305 [email protected] NASA Kennedy Space Center Launch Operations George Diller (321) 867-2468 [email protected] Lockheed Martin Space Systems Launch Vehicle Julie Andrews (321) 853-1567 [email protected] International Launch Services Launch Vehicle Fran Slimmer (571) 633-7462 [email protected] NEW HORIZONS Table of Contents Media Services Information ................................................................................................ 2 Quick Facts .............................................................................................................................. 3 Pluto at a Glance ...................................................................................................................... 5 Why Pluto and the Kuiper Belt? The Science of New Horizons ............................... 7 NASA’s New Frontiers Program ........................................................................................14 The Spacecraft ........................................................................................................................15 Science Payload ...............................................................................................................16 -
Collision Avoidance Operations in a Multi-Mission Environment
AIAA 2014-1745 SpaceOps Conferences 5-9 May 2014, Pasadena, CA Proceedings of the 2014 SpaceOps Conference, SpaceOps 2014 Conference Pasadena, CA, USA, May 5-9, 2014, Paper DRAFT ONLY AIAA 2014-1745. Collision Avoidance Operations in a Multi-Mission Environment Manfred Bester,1 Bryce Roberts,2 Mark Lewis,3 Jeremy Thorsness,4 Gregory Picard,5 Sabine Frey,6 Daniel Cosgrove,7 Jeffrey Marchese,8 Aaron Burgart,9 and William Craig10 Space Sciences Laboratory, University of California, Berkeley, CA 94720-7450 With the increasing number of manmade object orbiting Earth, the probability for close encounters or on-orbit collisions is of great concern to spacecraft operators. The presence of debris clouds from various disintegration events amplifies these concerns, especially in low- Earth orbits. The University of California, Berkeley currently operates seven NASA spacecraft in various orbit regimes around the Earth and the Moon, and actively participates in collision avoidance operations. NASA Goddard Space Flight Center and the Jet Propulsion Laboratory provide conjunction analyses. In two cases, collision avoidance operations were executed to reduce the risks of on-orbit collisions. With one of the Earth orbiting THEMIS spacecraft, a small thrust maneuver was executed to increase the miss distance for a predicted close conjunction. For the NuSTAR observatory, an attitude maneuver was executed to minimize the cross section with respect to a particular conjunction geometry. Operations for these two events are presented as case studies. A number of experiences and lessons learned are included. Nomenclature dLong = geographic longitude increment ΔV = change in velocity dZgeo = geostationary orbit crossing distance increment i = inclination Pc = probability of collision R = geostationary radius RE = Earth radius σ = standard deviation Zgeo = geostationary orbit crossing distance I. -
Spacecraft Trajectories in a Sun, Earth, and Moon Ephemeris Model
SPACECRAFT TRAJECTORIES IN A SUN, EARTH, AND MOON EPHEMERIS MODEL A Project Presented to The Faculty of the Department of Aerospace Engineering San José State University In Partial Fulfillment of the Requirements for the Degree Master of Science in Aerospace Engineering by Romalyn Mirador i ABSTRACT SPACECRAFT TRAJECTORIES IN A SUN, EARTH, AND MOON EPHEMERIS MODEL by Romalyn Mirador This project details the process of building, testing, and comparing a tool to simulate spacecraft trajectories using an ephemeris N-Body model. Different trajectory models and methods of solving are reviewed. Using the Ephemeris positions of the Earth, Moon and Sun, a code for higher-fidelity numerical modeling is built and tested using MATLAB. Resulting trajectories are compared to NASA’s GMAT for accuracy. Results reveal that the N-Body model can be used to find complex trajectories but would need to include other perturbations like gravity harmonics to model more accurate trajectories. i ACKNOWLEDGEMENTS I would like to thank my family and friends for their continuous encouragement and support throughout all these years. A special thank you to my advisor, Dr. Capdevila, and my friend, Dhathri, for mentoring me as I work on this project. The knowledge and guidance from the both of you has helped me tremendously and I appreciate everything you both have done to help me get here. ii Table of Contents List of Symbols ............................................................................................................................... v 1.0 INTRODUCTION -
Space Sector Brochure
SPACE SPACE REVOLUTIONIZING THE WAY TO SPACE SPACECRAFT TECHNOLOGIES PROPULSION Moog provides components and subsystems for cold gas, chemical, and electric Moog is a proven leader in components, subsystems, and systems propulsion and designs, develops, and manufactures complete chemical propulsion for spacecraft of all sizes, from smallsats to GEO spacecraft. systems, including tanks, to accelerate the spacecraft for orbit-insertion, station Moog has been successfully providing spacecraft controls, in- keeping, or attitude control. Moog makes thrusters from <1N to 500N to support the space propulsion, and major subsystems for science, military, propulsion requirements for small to large spacecraft. and commercial operations for more than 60 years. AVIONICS Moog is a proven provider of high performance and reliable space-rated avionics hardware and software for command and data handling, power distribution, payload processing, memory, GPS receivers, motor controllers, and onboard computing. POWER SYSTEMS Moog leverages its proven spacecraft avionics and high-power control systems to supply hardware for telemetry, as well as solar array and battery power management and switching. Applications include bus line power to valves, motors, torque rods, and other end effectors. Moog has developed products for Power Management and Distribution (PMAD) Systems, such as high power DC converters, switching, and power stabilization. MECHANISMS Moog has produced spacecraft motion control products for more than 50 years, dating back to the historic Apollo and Pioneer programs. Today, we offer rotary, linear, and specialized mechanisms for spacecraft motion control needs. Moog is a world-class manufacturer of solar array drives, propulsion positioning gimbals, electric propulsion gimbals, antenna positioner mechanisms, docking and release mechanisms, and specialty payload positioners. -
Radial Variation of the Interplanetary Magnetic Field Between 0.3 AU and 1.0 AU
|00000575|| J. Geophys. 42, 591 - 598, 1977 Journal of Geophysics Radial Variation of the Interplanetary Magnetic Field between 0.3 AU and 1.0 AU Observations by the Helios-I Spacecraft G. Musmann, F.M. Neubauer and E. Lammers Institut for Geophysik and Meteorologie, Technische Universitiit Braunschweig, Mendelssohnstr. lA, D-3300 Braunschweig, Federal Republic of Germany Abstract. We have investigated the radial dependence of the radial and azimuthal components and the magnitude of the interplanetary magnetic field obtained by the Technical University of Braunschweig magnetometer experiment on-board of Helios-1 from December 10, 1974 to first perihelion on March 15, 1975. Absolute values of daily averages of each quantity have been employed. The regression analysis based on power laws leads to 2.55 y x r- 2 · 0 , 2.26 y x r- i.o and F = 5.53 y x r- i. 6 with standard deviations of 2.5 y, 2.0 y and 3.2 y for the radial and azimuthal components and magnitude, respectively. Here r is the radial distance from the sun in astronomical units. The results are compared with results obtained for Mariners 4, 5 and 10 and Pioneers 6 and 10. The differences are probably due to different epochs in the solar cycle and the different statistical techniques used. Key words: Interplanetary magnetic field - Helios-1 results. Introduction The study of the vanat10n of the components and magnitude of the in terplanetary magnetic field with heliocentric distance is very intersting at the present time. The mission of Mariner 10 to the inner solar system to a heliocentric distance of 0.46 AU and the missions of Pioneer 10 and Pioneer 11 to the outer solar system to heliocentric distances beyond 5 AU have provided new data over a wide range of heliocentric distance. -
The Deep Space Network - a Technology Case Study and What Improvements to the Deep Space Network Are Needed to Support Crewed Missions to Mars?
The Deep Space Network - A Technology Case Study and What Improvements to the Deep Space Network are Needed to Support Crewed Missions to Mars? A Master’s Thesis Presented to Department of Telecommunications State University of New York Polytechnic Institute Utica, New York In Partial Fulfillment of the Requirements for the Master of Science Degree By Prasad Falke May 2017 Abstract The purpose of this thesis research is to find out what experts and interested people think about Deep Space Network (DSN) technology for the crewed Mars mission in the future. The research document also addresses possible limitations which need to be fix before any critical missions. The paper discusses issues such as: data rate, hardware upgrade and new install requirement and a budget required for that, propagation delay, need of dedicated antenna support for the mission and security constraints. The Technology Case Study (TCS) and focused discussion help to know the possible solutions and what everyone things about the DSN technology. The public platforms like Quora, Reddit, StackExchange, and Facebook Mars Society group assisted in gathering technical answers from the experts and individuals interested in this research. iv Acknowledgements As the thesis research was challenging and based on the output of the experts and interested people in this field, I would like to express my gratitude and appreciation to all the participants. A special thanks go to Dr. Larry Hash for his guidance, encouragement, and support during the whole time. Additionally, I also want to thank my mother, Mrs. Mangala Falke for inspiring me always. Last but not the least, I appreciate the support from Maricopa County Emergency Communications Group (MCECG) and Arizona Near Space Research (ANSR) Organization for helping me to find the experts in space and communications field.