Characteristics of the Flank Magnetopause: THEMIS Observations
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Astrodynamics
Politecnico di Torino SEEDS SpacE Exploration and Development Systems Astrodynamics II Edition 2006 - 07 - Ver. 2.0.1 Author: Guido Colasurdo Dipartimento di Energetica Teacher: Giulio Avanzini Dipartimento di Ingegneria Aeronautica e Spaziale e-mail: [email protected] Contents 1 Two–Body Orbital Mechanics 1 1.1 BirthofAstrodynamics: Kepler’sLaws. ......... 1 1.2 Newton’sLawsofMotion ............................ ... 2 1.3 Newton’s Law of Universal Gravitation . ......... 3 1.4 The n–BodyProblem ................................. 4 1.5 Equation of Motion in the Two-Body Problem . ....... 5 1.6 PotentialEnergy ................................. ... 6 1.7 ConstantsoftheMotion . .. .. .. .. .. .. .. .. .... 7 1.8 TrajectoryEquation .............................. .... 8 1.9 ConicSections ................................... 8 1.10 Relating Energy and Semi-major Axis . ........ 9 2 Two-Dimensional Analysis of Motion 11 2.1 ReferenceFrames................................. 11 2.2 Velocity and acceleration components . ......... 12 2.3 First-Order Scalar Equations of Motion . ......... 12 2.4 PerifocalReferenceFrame . ...... 13 2.5 FlightPathAngle ................................. 14 2.6 EllipticalOrbits................................ ..... 15 2.6.1 Geometry of an Elliptical Orbit . ..... 15 2.6.2 Period of an Elliptical Orbit . ..... 16 2.7 Time–of–Flight on the Elliptical Orbit . .......... 16 2.8 Extensiontohyperbolaandparabola. ........ 18 2.9 Circular and Escape Velocity, Hyperbolic Excess Speed . .............. 18 2.10 CosmicVelocities -
Evolution of the Rendezvous-Maneuver Plan for Lunar-Landing Missions
NASA TECHNICAL NOTE NASA TN D-7388 00 00 APOLLO EXPERIENCE REPORT - EVOLUTION OF THE RENDEZVOUS-MANEUVER PLAN FOR LUNAR-LANDING MISSIONS by Jumes D. Alexunder und Robert We Becker Lyndon B, Johnson Spuce Center ffoaston, Texus 77058 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. C. AUGUST 1973 1. Report No. 2. Government Accession No, 3. Recipient's Catalog No. NASA TN D-7388 4. Title and Subtitle 5. Report Date APOLLOEXPERIENCEREPORT August 1973 EVOLUTIONOFTHERENDEZVOUS-MANEUVERPLAN 6. Performing Organizatlon Code FOR THE LUNAR-LANDING MISSIONS 7. Author(s) 8. Performing Organization Report No. James D. Alexander and Robert W. Becker, JSC JSC S-334 10. Work Unit No. 9. Performing Organization Name and Address I - 924-22-20- 00- 72 Lyndon B. Johnson Space Center 11. Contract or Grant No. Houston, Texas 77058 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address Technical Note I National Aeronautics and Space Administration 14. Sponsoring Agency Code Washington, D. C. 20546 I 15. Supplementary Notes The JSC Director waived the use of the International System of Units (SI) for this Apollo Experience I Report because, in his judgment, the use of SI units would impair the usefulness of the report or I I result in excessive cost. 16. Abstract The evolution of the nominal rendezvous-maneuver plan for the lunar landing missions is presented along with a summary of the significant developments for the lunar module abort and rescue plan. A general discussion of the rendezvous dispersion analysis that was conducted in support of both the nominal and contingency rendezvous planning is included. -
Low Earth Orbit Slotting for Space Traffic Management Using Flower
Low Earth Orbit Slotting for Space Traffic Management Using Flower Constellation Theory David Arnas∗, Miles Lifson†, and Richard Linares‡ Massachusetts Institute of Technology, Cambridge, MA, 02139, USA Martín E. Avendaño§ CUD-AGM (Zaragoza), Crtra Huesca s / n, Zaragoza, 50090, Spain This paper proposes the use of Flower Constellation (FC) theory to facilitate the design of a Low Earth Orbit (LEO) slotting system to avoid collisions between compliant satellites and optimize the available space. Specifically, it proposes the use of concentric orbital shells of admissible “slots” with stacked intersecting orbits that preserve a minimum separation distance between satellites at all times. The problem is formulated in mathematical terms and three approaches are explored: random constellations, single 2D Lattice Flower Constellations (2D-LFCs), and unions of 2D-LFCs. Each approach is evaluated in terms of several metrics including capacity, Earth coverage, orbits per shell, and symmetries. In particular, capacity is evaluated for various inclinations and other parameters. Next, a rough estimate for the capacity of LEO is generated subject to certain minimum separation and station-keeping assumptions and several trade-offs are identified to guide policy-makers interested in the adoption of a LEO slotting scheme for space traffic management. I. Introduction SpaceX, OneWeb, Telesat and other companies are currently planning mega-constellations for space-based internet connectivity and other applications that would significantly increase the number of on-orbit active satellites across a variety of altitudes [1–5]. As these and other actors seek to make more intensive use of the global space commons, there is growing need to characterize the fundamental limits to the capacity of Low Earth Orbit (LEO), particularly in high-demand orbits and altitudes, and minimize the extent to which use by one space actor hampers use by other actors. -
New Planetary Science from Dawn, Rosetta, and New Horizons
New Planetary Science from Dawn, Rosetta, and New Horizons We have many active probes exploring deep space now. Image: The Planetary Society Three of them are giving us great new science from minor planets. ●Dawn ● NASA mission ● Asteroid Vesta and asteroid and dwarf planet Ceres ● First asteroid orbiter ● First to orbit two different deep space targets ●Rosetta ● European Space Agency mission ● Comet 67P/Churyumov–Gerasimenko ● First comet orbiter and landing ● Hopes the be the first to make two landings on a comet ●New Horizons ● NASA mission ● Dwarf planet Pluto and other Kuiper belt objects beyond ● First mission to Pluto But first, a surprise guest appearance by Messenger ●Launched August 2004 by NASA. ●March 2011 arrived at Mercury. ●April 2015 crashed into Mercury. Photo: NASA Significant Science by Messenger at Mercury ●Crashed into the planet April 30 2015. ●For earlier mission highlights, see RAC program by Brenda Conway October 2011. ●Last few orbits were as low as possible. ●Highest resolution photos ever of the surface. ●Unexpected discovery that Mercury's magnetic field grows and shrinks in response to the Sun's level of activity. Significant Science by Messenger at Mercury ●Discovered unexpected hollows on the surface. ●Younger than impact craters around them (some are in or on craters - the surface collapsed some time after the impact). ●Mercury was believed to be geologically inactive. ● First evidence there are dynamic processes on the surface of Mercury today. Photo: NASA Significant Science by Messenger at Mercury ● The last image sent by Messenger before its crash. Photo: NASA Dawn ●Launched September 2007. ●February 2009 Mars flyby and gravity assist. -
Dawn/Dusk Asymmetry of the Martian Ultraviolet Terminator Observed Through Suprathermal Electron Depletions Morgane Steckiewicz, P
Dawn/dusk asymmetry of the Martian UltraViolet terminator observed through suprathermal electron depletions Morgane Steckiewicz, P. Garnier, R. Lillis, D. Toublanc, François Leblanc, D. L. Mitchell, L. Andersson, Christian Mazelle To cite this version: Morgane Steckiewicz, P. Garnier, R. Lillis, D. Toublanc, François Leblanc, et al.. Dawn/dusk asymme- try of the Martian UltraViolet terminator observed through suprathermal electron depletions. Journal of Geophysical Research Space Physics, American Geophysical Union/Wiley, 2019, 124 (8), pp.7283- 7300. 10.1029/2018JA026336. insu-02189085 HAL Id: insu-02189085 https://hal-insu.archives-ouvertes.fr/insu-02189085 Submitted on 29 Mar 2021 HAL is a multi-disciplinary open access L’archive ouverte pluridisciplinaire HAL, est archive for the deposit and dissemination of sci- destinée au dépôt et à la diffusion de documents entific research documents, whether they are pub- scientifiques de niveau recherche, publiés ou non, lished or not. The documents may come from émanant des établissements d’enseignement et de teaching and research institutions in France or recherche français ou étrangers, des laboratoires abroad, or from public or private research centers. publics ou privés. RESEARCH ARTICLE Dawn/Dusk Asymmetry of the Martian UltraViolet 10.1029/2018JA026336 Terminator Observed Through Suprathermal Key Points: • The approximate position of the Electron Depletions UltraViolet terminator can be M. Steckiewicz1 , P. Garnier1 , R. Lillis2 , D. Toublanc1, F. Leblanc3 , D. L. Mitchell2 , determined -
Lunar Orbiting Cubesat Sensor Transport System Mike Seibert, Alejandro Levi, and Mitchell Paradis Graduate Students, Colorado School of Mines
Lunar Orbiting CubeSat Sensor Transport System Mike Seibert, Alejandro Levi, and Mitchell Paradis Graduate Students, Colorado School of Mines Concept Origin Notional Mission Evaluated Carrier Spacecraft Conceptual Design The 2018 Lunar Polar Prospecting (LPP) Workshop Objective: • Structure: Based on EELV Secondary generated a series of recommendations for Deploy a constellation of 6 sensor spacecraft in single Payload Adapter (ESPA) Grande. prospecting of lunar water. Recommendation 3 was polar low lunar orbit plane. • Propulsion: Monoprop system with 2.5 km/s for swarms CubeSats overflying polar regions at delta-V capability. altitudes below 20 km. Recommendation 3 also Cruise Phase: Includes 179 m/s for 110 days of recommended “a swarm of hundreds of low cost LOCuST is released from the launch vehicle in a GTO. orbit eccentricity control impactors instrumented for volatile detection and A series of perigee maneuvers using carrier spacecraft • Earth Telecom: Optical derived from LADEE or quantification.” [1] propulsion are used to raise apogee to lunar distance. IRIS Version 2.0 radio • Relay Telecom: IRIS Version 2.0 (multiple if all RF) The graduate student team developed both mission Lunar Orbit Insertion/Optimization • Thermal control:Accounts for challenges of low and vehicle designs that address the LPP Lunar orbit capture into an initial 200km altitude orbit over lunar day side. recommendation during the Space Resources Design I polar orbit. Orbit is lowered to 10km altitude Main Propulsion course at the Colorado School of Mines in Spring perilune, 100km apolune. All capture and initial 2019. CubeSat optimization maneuvers use carrier spacecraft Deployers propulsion. The CubeSat swarm concept was interpreted to mean a constellation of small short mission duration Deployments spacecraft with sensors optimized for localizing After each deployment orbit phasing maneuvers to Solar Array surface water ice. -
Overcoming the Challenges Associated with Image-Based Mapping of Small Bodies in Preparation for the OSIRIS-Rex Mission to (101955) Bennu
Preprint of manuscript submitted to Earth and Space Science Overcoming the Challenges Associated with Image-based Mapping of Small Bodies in Preparation for the OSIRIS-REx Mission to (101955) Bennu D. N. DellaGiustina1, C. A. Bennett1, K. Becker1, D. R Golish1, L. Le Corre2, D. A. Cook3†, K. L. Edmundson3, M. Chojnacki1, S. S. Sutton1, M. P. Milazzo3, B. Carcich4, M. C. Nolan1, N. Habib1, K. N. Burke1, T. Becker1, P. H. Smith1, K. J. Walsh5, K. Getzandanner6, D. R. Wibben4, J. M. Leonard4, M. M. Westermann1, A. T. Polit1, J. N. Kidd Jr.1, C. W. Hergenrother1, W. V. Boynton1, J. Backer3, S. Sides3, J. Mapel3, K. Berry3, H. Roper1, C. Drouet d’Aubigny1, B. Rizk1, M. K. Crombie7, E. K. Kinney-Spano8, J. de León9, 10, J. L. Rizos9, 10, J. Licandro9, 10, H. C. Campins11, B. E. Clark12, H. L. Enos1, and D. S. Lauretta1 1Lunar and Planetary Laboratory, University of Arizona, Tucson, AZ, USA 2Planetary Science Institute, Tucson, AZ, USA 3U.S. Geological Survey Astrogeology Science Center, Flagstaff, AZ, USA 4KinetX Space Navigation & Flight Dynamics Practice, Simi Valley, CA, USA 5Southwest Research Institute, Boulder, CO, USA 6Goddard Spaceflight Center, Greenbelt, MD, USA 7Indigo Information Services LLC, Tucson, AZ, USA 8 MDA Systems, Ltd, Richmond, BC, Canada 9Instituto de Astrofísica de Canarias, Santa Cruz de Tenerife, Spain 10Departamento de Astrofísica, Universidad de La Laguna, Santa Cruz de Tenerife, Spain 11Department of Physics, University of Central Florida, Orlando, FL, USA 12Department of Physics and Astronomy, Ithaca College, Ithaca, NY, USA †Retired from this institution Corresponding author: Daniella N. -
Dawn Mission to Vesta and Ceres Symbiosis Between Terrestrial Observations and Robotic Exploration
Earth Moon Planet (2007) 101:65–91 DOI 10.1007/s11038-007-9151-9 Dawn Mission to Vesta and Ceres Symbiosis between Terrestrial Observations and Robotic Exploration C. T. Russell Æ F. Capaccioni Æ A. Coradini Æ M. C. De Sanctis Æ W. C. Feldman Æ R. Jaumann Æ H. U. Keller Æ T. B. McCord Æ L. A. McFadden Æ S. Mottola Æ C. M. Pieters Æ T. H. Prettyman Æ C. A. Raymond Æ M. V. Sykes Æ D. E. Smith Æ M. T. Zuber Received: 21 August 2007 / Accepted: 22 August 2007 / Published online: 14 September 2007 Ó Springer Science+Business Media B.V. 2007 Abstract The initial exploration of any planetary object requires a careful mission design guided by our knowledge of that object as gained by terrestrial observers. This process is very evident in the development of the Dawn mission to the minor planets 1 Ceres and 4 Vesta. This mission was designed to verify the basaltic nature of Vesta inferred both from its reflectance spectrum and from the composition of the howardite, eucrite and diogenite meteorites believed to have originated on Vesta. Hubble Space Telescope observations have determined Vesta’s size and shape, which, together with masses inferred from gravitational perturbations, have provided estimates of its density. These investigations have enabled the Dawn team to choose the appropriate instrumentation and to design its orbital operations at Vesta. Until recently Ceres has remained more of an enigma. Adaptive-optics and HST observations now have provided data from which we can begin C. T. Russell (&) IGPP & ESS, UCLA, Los Angeles, CA 90095-1567, USA e-mail: [email protected] F. -
Delta II Dawn Mission Booklet
Delta Launch Vehicle Programs Dawn United Launch Alliance is proud to launch the Dawn mission. Dawn will be launched aboard a Delta II 7925H launch vehicle from Cape Canaveral Air Force Station (CCAFS), Florida. The launch vehicle will deliver the Dawn spacecraft into an Earth- escape trajectory, where it will commence its journey to the solar system’s main asteroid belt to gather comparative data from dwarf planet Ceres and asteroid Vesta. United Launch Alliance provides the Delta II launch service under the NASA Launch Services (NLS) contract with the NASA Kennedy Space Center Expendable Launch Services Program. We are delighted that NASA has chosen the Delta II for this Discovery Mission. I congratulate the entire Delta team for their significant efforts that resulted in achieving this milestone and look forward to continued launches of scientific space missions aboard the Delta launch vehicle. Kristen T. Walsh Director, NASA Programs Delta Launch Vehicles 1 Dawn Mission Overview The Dawn spacecraft will make an eight-year journey to the main asteroid belt between Mars and Jupiter in an effort to significantly increase our understanding of the conditions and processes acting at the solar system’s earliest epoch by examining the geophysical properties of the asteroid Vesta and dwarf planet Ceres. Evidence shows that Vesta and Ceres have distinct characteristics and, therefore, must have followed different evolutionary paths. By observing both, with the same set of instruments, scientists hope to develop an understanding of the transition from the rocky inner regions, of which Vesta is characteristic, to the icy outer regions, of which Ceres is representative. -
Mars Science Laboratory Participating Scientists Program Proposal
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Ceres: a Prime Target for Robotic Sample Return and Future Human Exploration
50th Lunar and Planetary Science Conference 2019 (LPI Contrib. No. 2132) 3062.pdf CERES: A PRIME TARGET FOR ROBOTIC SAMPLE RETURN AND FUTURE HUMAN EXPLORATION. K. R. Fisher1 and L. D. Graham1, 1Astromaterials Research and Exploration Science (ARES) Division, NASA Johnson Space Center 2101 E NASA Pkwy, Houston Texas, 77058. [email protected] and [email protected] Introduction: NASA’s Dawn spacecraft was re- ing the systems previously developed for the OSIRIS- cently deactivated in November after spending three REx spacecraft. years orbiting Ceres gathering data through its remote A major component that could be re-used is the sensing instrument suite. The Dawn mission served as a OSIRIS-REx sampling system. OSIRIS-REx will uti- crucial step in furthering our understanding of small lize the Touch-and-Go Sample Acquisition Mechanism bodies within the Solar System and provided a wealth (TAGSAM) to acquire up to hundreds of grams of sur- of new information about Vesta and Ceres during the face material. TAGSAM includes a large collector eleven year mission. head mounted to the end of an 11 foot robotic arm. The The conclusion of Dawn should not be the conclu- collector head has multiple gas nozzles which will dis- sion of exploration at Ceres. A logical follow-on mis- pense a burst of nitrogen gas to stir up loose regolith on sion would be to return samples from the surface to the surface under the collector head [5]. A portion of provide ground truth for the orbiter data. Ceres sample this regolith will be captured in the TAGSAM collec- return is highly feasible and would benefit directly tors and stored for return [5]. -
ISTS-2017-D-110ⅠISSFD-2017-110
50,000 Laps Around Mars: Navigating the Mars Reconnaissance Orbiter Through the Extended Missions (January 2009 – March 2017) By Premkumar MENON,1) Sean WAGNER,1) Stuart DEMCAK,1) David JEFFERSON,1) Eric GRAAT,1) Kyong LEE,1) and William SCHULZE1) 1)Jet Propulsion Laboratory, California Institute of Technology, USA (Received May 25th, 2017) Orbiting Mars since March 2006, the Mars Reconnaissance Orbiter (MRO) spacecraft continues to perform valuable science observations, provide telecommunication relay for surface assets, and characterize landing sites for future missions. Previous papers reported on the navigation of MRO from interplanetary cruise through the end of the Primary Science Phase in December 2008. This paper highlights the navigation of MRO from January 2009 through March 2017, covering the Extended Science Phase, the first three extended missions, and a portion of the fourth extended mission. The MRO mission returned over 300 terabytes of data since beginning primary science operations in November 2006. Key Words: Navigation, orbit determination, propulsive maneuvers, reconstruction, phasing 1. Introduction Siding Spring at Mars in October 20144) and imaged the Exo- Mars lander Schiaparelli in October 2016.5,6) MRO plans to The Mars Reconnaissance Orbiter spacecraft launched from provide telecommunication support for the Entry, Descent, and Cape Canaveral Air Force Station on August 12, 2005. MRO Landing (EDL) phase of NASA’s InSight mission in November entered orbit around Mars on March 10, 2006 following an in- 2018 and NASA’s Mars 2020 mission in February 2021. terplanetary cruise of seven months. After five months of aer- obraking and three months of transition to the Primary Sci- 2.1.