DOCSLIB.ORG

'.';King Navigation

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
'.';King Navigation 1980012912 -' JPL PUBLICATION 78-38 '.';king Navigation W. J. O'Neil, R. P. Rudd, D. L. Farless, C. E. Hildebrand, R. T. Mitchell, K. H. Rourke, et al. Jet Propulsion Laboratory E. A. Euler Martin Marietta Aerospace (N,%SA-C[_-l_,2517) VIklt_G ._AVIGA'IION (Jet t, u0-213_-_ : Pcopulsio[, L,_c.) 322 p _lC Alq/MF A01 _:d[,U CSCL Z2.t; hd0-_|4dj •_ [J_;c ]. a_ GJ/15 l,t7 5 'JJ ± November 15, 1979 _',r:.'> ;Y/l&_',,/I_cC7.'/',_/, : < X* ",t ,'" t National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Pasadena, California # 1980012912-002 JPL PUBLICATION 78-38 Viking Navigation W. J. O'Neil, R. P. Rudd, D. L. Farless, C. E. Hildebrand, R. T. Mitchell, K. H. Rourke, et al. Jet Propulsion Laboratory E. A. Euler Martin Marietta Aerospace November 15, 1979 National Aeronautics and Space Administration Jet Propulsion Laboratory : California Institute of Technology Pasadena, California 1980012912-003 The research descnbed bnth_s pubhcat_onwas camed out by the Jet Propulsion Laboratory, Cahforn_aInstitute of Technology, under NASA Contract No NAS7-100 i 1980012912-004 Abstract NASA soft-landed two Viking spacecraft on Mars in the summer t,f 1976. These were the free world's first landings on another planet. This report provides a final, comprehensive description of the navigation of the Viking spacecraft throughout their flight from Earth launch to Mars landing. The flight path design, actual int]lght control, and postflight reconstruction ale discussed in detail. The report Is comprised of an introductory chapter followed by five Olapters which essenually correspond to the organization of the Viking navigation operations, namely, Trajectory Descriptton, Interplanetary Orbit Determination, Satellite Orbit Determination, ._haneuver Analysis, and Lander Flight Path Analysis. To tile extent appropriate, each chapter describes the preflight analyses upon which the operational strategies and performance predictions we,e based. The inflight results are then discussed and compared with the preflight predictions and, finally, the results of any postflight analyses are presented. Ill 1980012912-005 Contents Introduction.................................... 1 W. J. O'Neil and R. P. Rudd I. Flight Path Design .............................. 5 II. Viking 1 Inflight Synopsis .......................... 16 II1. Viking 2 Inflight Synopsis .......................... 20 References .................................... 27 Appendix.Definitionsof Terminology ..................... 28 Figures la. FPAG personnel .............................. 3 lb. FPAG functional organization ....................... 4 2. Viking flight team functional orgamzation ................. 9 3. SPFPAD operations schedule ....................... 11 4. Lander descent .............................. 13 5. Accessible area constraints ........................ 13 6. Accessible area fixed to orbit ....................... 14 7. Inertial landing point ........................... 14 8. Orbit plane design ............................ 14 9. Viking 1 orbit insertion design ...................... 15 10. Viking 1 B-plane delivery requirements ................. 15 11. Timing offset ............................... 15 12. Orbital operations plan .......................... 16 13. Viking 1 heliocentric trajectory ................... 17 14. Viking 1 launch accuracy ......................... 17 15. Viking 1 Earth departure control ..................... 17 16. Viking 1 interplanetary delivery ..................... 18 17. Viking 1 Mars approach control ..................... 19 18. Viking 1 Mars orbit insertion ....................... 20 19. Viking 1 actual site acquisitions ..................... 20 20. Descent sequence ............................ 21 21. Landing accuracy ............................. 21 22. Viking 2 heliocentric trajectory ..................... 21 23. Viking 2 launch accuracy ......................... 22 24. Viking 2 midcourse aimpoints ...................... 22 V _R_t_D_G PAGE BLANK NOT FILMED 1980012912-006 "_ 25. Viking 2 unbiased near-Earth mldcourse maneuver ........... 23 26. Viking 2 Earth departure control .................... 24 27. Viking 2 rmdcour_u tdrgeL_dand dch_uvedaimpomts ........... 25 28. VO 1 and ',10 2 ground tracks ..................... 26 29. Viking 2 landing region .......................... 26 Trajectory Description ............................ 30 D. L. Farless, L. H. Dicken, and R. E. D_ehl I. Launch Phase ............................... 30 II. Interplanetary Phase ............................. 31 A. Heliocentnc Orbit Descnpt,on ...................... 31 B. Near-Earth MIdcourse Maneuver Effects ................. 33 C. Solar Pressure Effects .......................... 33 D. Interplanetary Trajectory Data ...................... 33 III. Encounter Phase .............................. 33 IV. Mars Orbit Phase ............................... 37 Tables 1. Viking 1 launch trajectory mark event list ................. 30 2. Viking 2 launch trajectory mark event list ................ 31 3. Orbital data .............................. 31 4. Heliocentric orbit elements ........................ 32 5, Areocentric orbit elements ........................ 37 6. VO-1 Mars orbit elements ........................ 38 7. VO-2 Mars orbit elements ........................ 44 8. Mars orbit trim maneuver execution times ................ 47 Figures 1. Targeted and achieved injection aimpoints for Viking launches ..... 31 ?. Viking 1 heliocentric trajectory ..................... 32 3. Viking 2 heliocentric trajectory ..................... 32 4. Targeted and achieved midcourse maneuver aimpoints for Viking .... 33 5. Viking 1 geocentric range ........................ 34 _' 6. Viking 1 geocentric range rate ...................... 34 7. Viking 1 geocentric declination ..................... 34 8. Viking 1 geocentric right ascension .................... 34 9. Viking 1 heliocentric range ........................ 35 10. Viking 1 areocentric range ........................ 35 vi 1980012912-007 11. Viking 2geocentric range ........................ 35 12. Viking 2 geocentric range rate ...................... 35 13. Vikiqg 2 geocentric declination ................... 36 14. Viking 2 geocentric right ascension .................... 36 15. Viking 2 hehocentric range ....................... 36 16. Viking 2 areocentric _ange ....................... 36 Interplanetary Orbit Determination .................. 48 K. H. Rourke, N. Jerath, C. H. Acton, W. G. Breckenrldge, J. K. Campbell, C.S. Chrlstensen, A.J. Donegan, H.M. Koble, N.A. Mottinger, G.C. Rinker, and F. B. Winn I. Introduction .................................. 48 I1. Mission Description .......................... 49 II1. Orbit Determination System Fundamentals ............... 49 A. Trajectory Models ............................ 50 B. Observation Models ........................... 50 C. Radio Data Models ............................ 50 D. Optical Data Models ........................... 51 E. Filter Models ............................... 51 F, Orbit Determination Process ....................... 52 G. Critical Orbit Determination Inputs ................... 53 H. Orbit Determination Errors ....................... 54 IV. Orbit Determination SoftwareSystem .................. 54 V. Orbit DeterminationStrategy ....................... 55 A. Radio and Optical Orbit Determination ................. 55 B. Approach Observation Schedulas ..................... 58 C. Orbit Estimation Strategies ........................ 58 VI. Orbit I_termination Results ........................ 60 A. Launch/Earth Departure Phase ...................... 60 B. Cruise Phase ............................... 60 VII. Long-Arc RadioData Processing ..................... 62 A. Inflight Processing ............................ 62 B. Postflight Processing .......................... 64 VIII. Solar Pressure ModelImprovement ................... 68 -_ vii 1980012912-008 IX. Optical Measurements Processing .................... 73 A. Optical Measurement System ....................... 73 B. Optical Observables ........................... 73 C. SequencP.Data and Polntlng Optimization ................ 74 D. Data Flow and Management ...................... 74 E. Telemetry Data Processing ........................ 74 F. Picture _)ata Processing .......................... 74 G. Optical Obse,vables Generation ................... 75 H. Processing Results ............................ 75 X. Approach Orbit Determination Evaluation ................ 75 XI. Infilght Orbit Determlnatlon Solution Compllatlon ........... 79 XlI. DSN Station Locatlon Evaluatlon ..................... 80 A. Theoretical Background ......................... 81 B. Data Coverage and Calibrations ..................... 82 C. Preliminary Solutions .......................... 83 D. Final Solutions .............................. 83 XlII. Satellite Ephemeris Evaluation ..................... 101 A. Wilkins' Angles ............................. 101 B. Analysis of Approach Optical Data for Ephemeris Determination . 102 C. Satehite Ephemeris from VO-1 and VO-2 ............... 104 XlV. Conclusions ................................ 106 References .................................... 108 Tables 1. Mission events ............................. 49 2. Optical observables ............................ 51 3. Orbit determination system error model ................. 54 4. OD software inputs ............................ 55 5. OD software outputs ........................... 56 6. OD software glossary ..........................
Load more

Recommended publications
  • Analysis of Planetary and Solar-Induced Perturbations on Trans-Martian Trajectory of Mars Missions Before and After Mars Orbit Insertion
    Analysis of planetary and solar-induced perturbations on trans-Martian trajectory of Mars missions before and after Mars orbit insertion V U J Nwankwo1 and S K Chakrabarti1,2* 1S N Bose National Centre for Basic Sciences, Kolkata 700 098, West Bengal, India 2Indian Center for Space Physics, Kolkata 700 084, West Bengal, India Abstract: Interplanetary missions are susceptible to gravitational and nongravitational perturbing forces at every tra- jectory phase, assuming, of course, that the man made rockets and thrusters work as expected. These forces are mainly due to planetary and solar-forcing-induced perturbations during geocentric, heliocentric and Martian trajectories, and before orbit insertion. In this study, we review and/or analyze Mars orbiters mission associated perturbing forces and their possible impacts before Mars Orbit Insertion viz Earth’s oblateness, Third body (solar and lunar), solar radiation pressure, solar energetic radiation environment and atmospheric drag forces. We also model the significance of atmospheric drag force on Mangalyaan Mars orbiter mission, as a function of appropriate space environmental parameters during its 28 days in Earth’s orbit (around and during perigee passage), 300 days of heliocentric and 100 days of Martian trajectory. We have found that for a total perigee height boost of about 250 km, the cumulative orbit decay can be approximately 720 m. The approximate altitude variation could be up to 158 m with respect to the sun during 300 days of interplanetary journey toward Mars. After Mars orbit insertion, the total decay experienced by the spacecraft could be up to 701 m with decay rate of up to 9 m/day during 100 days of Martian trajectory, based on Mars–Earth atmosphere density ratio.
    [Show full text]
  • Theoretical and Experimental Investigation of Hall Thruster Miniaturization by Noah Zachary Warner
    Theoretical and Experimental Investigation of Hall Thruster Miniaturization by Noah Zachary Warner S.B., Aeronautics and Astronautics, Massachusetts Institute of Technology, 2001 S.M., Aeronautics and Astronautics, Massachusetts Institute of Technology, 2003 SUBMITTED TO THE DEPARTMENT OF AERONAUTICS AND ASTRONAUTICS IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF DOCTOR OF PHILOSOPHY AT THE MASSACHUSETTS INSTITUTE OF TECHNOLOGY JUNE 2007 © 2007 Massachusetts Institute of Technology. All rights reserved. Signature of Author . Department of Aeronautics and Astronautics May 25, 2007 Certified by . Manuel Martínez-Sánchez Professor of Aeronautics and Astronautics Thesis Supervisor Certified by . Jack Kerrebrock Professor Emeritus of Aeronautics and Astronautics Certified by . Oleg Batishchev Principal Research Scientist in Aeronautics and Astronautics Certified by . Vladimir Hruby President, Busek Company, Inc. Accepted by . Jaime Peraire Professor of Aeronautics and Astronautics Chair, Committee on Graduate Students 2 Theoretical and Experimental Investigation of Hall Thruster Miniaturization by Noah Zachary Warner Submitted to the Department of Aeronautics and Astronautics on May 25, 2007 in partial fulfillment of the requirements for the degree of Doctor of Philosophy in Aeronautics and Astronautics in the field of Space Propulsion ABSTRACT Interest in small-scale space propulsion continues to grow with the increasing number of small satellite missions, particularly in the area of formation flight. Miniaturized Hall thrusters have been identified as a candidate for lightweight, high specific impulse propul- sion systems that can extend mission lifetime and payload capability. A set of scaling laws was developed that allows the dimensions and operating parameters of a miniaturized Hall thruster to be determined from an existing, technologically mature baseline design.
    [Show full text]
  • Earth to Mars Areostationary Mission Optimization Analysis
    Earth to Mars areostationary mission optimization analysis M. M. Sánchez-García, G. Barderas and P. Romero Instituto de Matemática Interdisciplinar. U. D. Astronomía y Geodesia, Facultad de Ciencias Matemáticas, Universidad Complutense de Madrid, Madrid, Spain ([email protected], [email protected], [email protected]) Abstract Mars has become one of the priorities in the planetary exploration programs. The analysis of space mission costs has become a key factor in mission planning. The determination of optimal trajectories aiming to lower costs in terms of impulses allows for more massive payloads to be transported at a minimum energy cost. Areostationary satellites are considered the most efficient and robust candidates to satisfy the control needs of the missions to Mars. Mars Areostationary Relay Satellites providing continuous coverage of a specific region of Mars are being considered for a near future. In this work, we analyze the optimization of an areostationary mission. We first determine the launch and arrival dates for an optimal minimum energy Earth-Mars transfer trajectory. Then, the minimum thrust maneuvers to capture the spacecraft from the hyperbolic arrival trajectory to Mars and place it in the areostationary orbit are analyzed. XIV.0 Reunión Científica 13-15 julio 2020 Context of the research: Previous studies The number of missions to Mars has increased over the last years, particularly robotic missions which need to be tele- commanded from the Earth. The need to control the different missions in Mars in almost real time with a relay system that provides continuous coverage of a specific region has been proposed by several authors such as Edwards et al.
    [Show full text]
  • The Minor Planet Bulletin
    THE MINOR PLANET BULLETIN OF THE MINOR PLANETS SECTION OF THE BULLETIN ASSOCIATION OF LUNAR AND PLANETARY OBSERVERS VOLUME 35, NUMBER 3, A.D. 2008 JULY-SEPTEMBER 95. ASTEROID LIGHTCURVE ANALYSIS AT SCT/ST-9E, or 0.35m SCT/STL-1001E. Depending on the THE PALMER DIVIDE OBSERVATORY: binning used, the scale for the images ranged from 1.2-2.5 DECEMBER 2007 – MARCH 2008 arcseconds/pixel. Exposure times were 90–240 s. Most observations were made with no filter. On occasion, e.g., when a Brian D. Warner nearly full moon was present, an R filter was used to decrease the Palmer Divide Observatory/Space Science Institute sky background noise. Guiding was used in almost all cases. 17995 Bakers Farm Rd., Colorado Springs, CO 80908 [email protected] All images were measured using MPO Canopus, which employs differential aperture photometry to determine the values used for (Received: 6 March) analysis. Period analysis was also done using MPO Canopus, which incorporates the Fourier analysis algorithm developed by Harris (1989). Lightcurves for 17 asteroids were obtained at the Palmer Divide Observatory from December 2007 to early The results are summarized in the table below, as are individual March 2008: 793 Arizona, 1092 Lilium, 2093 plots. The data and curves are presented without comment except Genichesk, 3086 Kalbaugh, 4859 Fraknoi, 5806 when warranted. Column 3 gives the full range of dates of Archieroy, 6296 Cleveland, 6310 Jankonke, 6384 observations; column 4 gives the number of data points used in the Kervin, (7283) 1989 TX15, 7560 Spudis, (7579) 1990 analysis. Column 5 gives the range of phase angles.
    [Show full text]
  • An Access-Dictionary of Internationalist High Tech Latinate English
    An Access-Dictionary of Internationalist High Tech Latinate English Excerpted from Word Power, Public Speaking Confidence, and Dictionary-Based Learning, Copyright © 2007 by Robert Oliphant, columnist, Education News Author of The Latin-Old English Glossary in British Museum MS 3376 (Mouton, 1966) and A Piano for Mrs. Cimino (Prentice Hall, 1980) INTRODUCTION Strictly speaking, this is simply a list of technical terms: 30,680 of them presented in an alphabetical sequence of 52 professional subject fields ranging from Aeronautics to Zoology. Practically considered, though, every item on the list can be quickly accessed in the Random House Webster’s Unabridged Dictionary (RHU), updated second edition of 2007, or in its CD – ROM WordGenius® version. So what’s here is actually an in-depth learning tool for mastering the basic vocabularies of what today can fairly be called American-Pronunciation Internationalist High Tech Latinate English. Dictionary authority. This list, by virtue of its dictionary link, has far more authority than a conventional professional-subject glossary, even the one offered online by the University of Maryland Medical Center. American dictionaries, after all, have always assigned their technical terms to professional experts in specific fields, identified those experts in print, and in effect held them responsible for the accuracy and comprehensiveness of each entry. Even more important, the entries themselves offer learners a complete sketch of each target word (headword). Memorization. For professionals, memorization is a basic career requirement. Any physician will tell you how much of it is called for in medical school and how hard it is, thanks to thousands of strange, exotic shapes like <myocardium> that have to be taken apart in the mind and reassembled like pieces of an unpronounceable jigsaw puzzle.
    [Show full text]
  • Metaphorizing Dialogue to Enact a Flow Culture Transcending Divisiveness by Systematic Embodiment of Metaphor in Discourse -- /
    Alternative view of segmented documents via Kairos 6 May 2019 | Draft Metaphorizing Dialogue to Enact a Flow Culture Transcending divisiveness by systematic embodiment of metaphor in discourse -- / -- Introduction Metaphorizing -- beyond one-off usage Sustaining dialogue through metaphor? Indicative precedents of metaphorizing skills Discourse and debate reframed as cognitive combat through metaphor? Integrity of metaphorizing framed by complementarity between alternatives Imagining a relevant philosophers' game -- and beyond Requisite metaphoric "circumlocution" avoiding disruptive disagreement Sustainable discourse framed metaphorically as "orbiting" Metaphorizing as artful indulgence in misplaced concreteness? Re-imagining: metaphorizing, metamorphizing and cognitive shapeshifting Sustainable discourse: longest conflict versus longest conversation? References Introduction There is no difficulty in recognizing the extent to which discourse has become problematic, whether in national assemblies, parliaments, or the media (social media or otherwise). The current scene has been described as poisonously divisive. Each faction is adamant that the facts and principles it presents are beyond question. Each is necessarily right, with any in disagreement being by definition wrong. Discourse between nations, between religions, between political parties, and between disciplines currently offers little hope for a more fruitful modality. Curiously efforts towards transcending this situation -- if they are more than tokenistic -- seem to be readily entrapped by the same dynamic. Each is necessarily right or better, with others essentially misguided, misinformed or behind the times. The following is an exploration of a distinctive mode which does not rely on facts and truth as commonly understood, or on the deprecation of fake news and pretence. The focus is not on being right or wrong or the attribution of blame.
    [Show full text]
  • Astronomy and Astrophysics
    A Problem book in Astronomy and Astrophysics Compilation of problems from International Olympiad in Astronomy and Astrophysics (2007-2012) Edited by: Aniket Sule on behalf of IOAA international board July 23, 2013 ii Copyright ©2007-2012 International Olympiad on Astronomy and Astrophysics (IOAA). All rights reserved. This compilation can be redistributed or translated freely for educational purpose in a non-commercial manner, with customary acknowledgement of IOAA. Original Problems by: academic committees of IOAAs held at: – Thailand (2007) – Indonesia (2008) – Iran (2009) – China (2010) – Poland (2011) – Brazil (2012) Compiled and Edited by: Aniket Sule Homi Bhabha Centre for Science Education Tata Institute of Fundamental Research V. N. Purav Road, Mankhurd, Mumbai, 400088, INDIA Contact: [email protected] Thank you! Editor would like to thank International Board of International Olympiad on Astronomy and Astrophysics (IOAA) and particularly, president of the board, Prof. Chatief Kunjaya, and general secretary, Prof. Gregorz Stachowaski, for entrusting this task to him. We acknowledge the hard work done by respec- tive year’s problem setters drawn from the host countries in designing the problems and fact that all the host countries of IOAA graciously agreed to permit use of the problems, for this book. All the members of the interna- tional board IOAA are thanked for their support and suggestions. All IOAA participants are thanked for their ingenious solutions for the problems some of which you will see in this book. iv Thank you! A Note about Problems You will find a code in bracket after each problem e.g. (I07 - T20 - C). The first number simply gives the year in which this problem was posed I07 means IOAA2007.
    [Show full text]
  • Assessing Time Scales of Atmospheric Turbulence at Observatory Sites Aglae Kellerer
    Assessing time scales of atmospheric turbulence at observatory sites Aglae Kellerer To cite this version: Aglae Kellerer. Assessing time scales of atmospheric turbulence at observatory sites. Astrophysics [astro-ph]. Université Paris-Diderot - Paris VII, 2007. English. tel-00171277 HAL Id: tel-00171277 https://tel.archives-ouvertes.fr/tel-00171277 Submitted on 12 Sep 2007 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. U´ D D P 7 ` pr´esent´ee pour obtenir le grade de Docteur de l’Universit´eParis VII Specialit´ e:´ Astrophysique et Instrumentations Associ´ees A´ K Assessing time scales of atmospheric turbulence at observatory sites Soutenue le 7 Septembre 2007 devant la Commission d’examen : Pr´esident : Pr. G´erard Rousset Directeurs de th`ese : Dr. Vincent Coud´edu Foresto Dr. Monika Petr-Gotzens Rapporteurs : Dr. Tony Travouillon Dr. Jean Vernin Examinateurs : Dr. Thierry Fusco Dr. Marc Sarazin 2 The worst moment for the atheist is when he is really thankful and has nobody to thank. Dante Gabriel Rossetti (1828-1882) For me – as a really thankful atheist – it is a pleasure to have many people to thank, and first of all, my family.
    [Show full text]
  • Interferometric Observations of the Multiple Stellar System Delta Velorum
    Astronomy & Astrophysics manuscript no. Kellerer c ESO 2018 October 4, 2018 Interferometric observations of the multiple stellar system δ Velorum (Research Note) A. Kellerer1, M. G. Petr-Gotzens1, P. Kervella2, and V. Coud´edu Foresto2 1 European Southern Observatory, Karl-Schwarzschild-Str. 2, D-85748 Garching, Germany e-mail: [email protected], [email protected] 2 LESIA, Paris observatory e-mail: [email protected], [email protected] Received –; accepted — ABSTRACT Context. δ Velorum is a nearby ( 24 pc) triple stellar system, containing a close, eclipsing binary (Aa, Ab) discovered in 2000. Aims. Multiple systems provide∼ an opportunity to determine the set of fundamental parameters (mass, luminosity, size and chem- ical composition) of coeval stars. These parameters can be obtained with particular precision in the case of eclipsing binaries; for δ Velorum’s components (Aa, Ab) this potential has however not yet been exploited. Methods. We have analyzed interferometric observations of the close binary (Aa, Ab), obtained with the VINCI instrument and two VLTI siderostats. The measurements, which resolve the two components for the first time, are fitted onto the simple model of two uniformly bright, spherical stars. Results. The observations suggest that Aa and Ab have larger diameters than expected if they were on the main sequence, and that they are, thus, in a later evolutionary state. Key words. multiple stars – interferometry – stellar evolutionary state 1. Introduction of C and D. Finally, the most luminous component, A, was re- cently recognized to be a close eclipsing binary with a period δ Velorum (HD74956) is one of the fifty brightest stars on the T = 45.15days (Otero et al.
    [Show full text]
  • On March 16 , 2019 Fifteen Years of the Faulkes Telescope Project
    On March 16th, 2019 fifteen years of the Faulkes Telescope Project Our participation in this great adventure Andre Debackere March 2019 We started observations with the Faulkes Telescopes in January 2010. We studied different types of astronomical objects as part of - scientific workshop called “ASAM” at College Le Monteil, Monistrol sur Loire, France - European Comenius project, 6 schools in 5 countries - educational activities, 3 teachers and 2 schools - personal research, hunting binaries, measurements and discoveries 1) Scientific workshop from January 2010 to June 2016 with a dozen college students (12-16 years old) a) Our first subject of study : Trans-Neptunians and dwarf planets, astrometry and animations Learn how to use the Faulkes Telescope interface and the tools as “target visibility” and “exposure time calculator”. To be able to recognize the target in the stellar field by using ALADIN, CDS, Strasbourg, France and ASTROMETRICA, Herbert Raab, Austria. Make animations showing the motion of the asteroid against the starry sky background (with SALSAJ, EUHOU or ASTROMETRICA). How to locate an object in the sky, celestial coordinates (right ascension and declination), their measurements with ASTOMETRICA. The 2m telescopes (FTN & FTS) are powerful instruments so we started by studying the trans- Neptunians, very distant asteroids some of which are candidates for the rank of dwarf planets as for example Varuna and Orcus. (20000) Varuna discovered in 2000 and (90482) Orcus discovered in 2004 are both trans- Neptunian object from
    [Show full text]
  • Performance Testing and Internal Probe Measurements of a High Specific Impulse Hall Thruster
    Performance Testing and Internal Probe Measurements of a High Specific Impulse Hall Thruster by Noah Zachary Warner S.B., Aeronautics and Astronautics Massachusetts Institute of Technology, 2001 Submitted to the Department of Aeronautics and Astronautics in partial fulfillment of the requirements for the degree of Master of Science in Aeronautics and Astronautics at the MASSACHUSETTS INSTITUTE OF TECHNOLOGY September 2003 © 2003 Massachusetts Institute of Technology. All rights reserved. Signature of Author . Department of Aeronautics and Astronautics August 5, 2003 Certified by . Manuel Martinez-Sanchez Professor of Aeronautics and Astronautics Thesis Supervisor Accepted by . Edward M. Greitzer H.N. Slater Professor of Aeronautics and Astronautics Chair, Committee on Graduate Students 2 Performance Testing and Internal Probe Measurements of a High Specific Impulse Hall Thruster by Noah Zachary Warner Submitted to the Department of Aeronautics and Astronautics on August 5, 2003 in partial fulfillment of the requirements for the degree of Master of Science in Aeronautics and Astronautics ABSTRACT The BHT-1000 high specific impulse Hall thruster was used for performance testing and internal plasma measurements to support the ongoing development of computational mod- els. The thruster was performance tested in both single and two stage anode configura- tions. In the single stage configuration, the specific impulse exceeded 3000s at a discharge voltage of 1000V while maintaining a thrust efficiency of 50 percent. Two stage operation produced higher thrust, specific impulse and thrust efficiency than the single stage configuration at most discharge voltages. The thruster thermal warmup was charac- terized using a thermocouple embedded in the outer exit ring, and the magnetic field topology was investigated using a Gaussmeter.
    [Show full text]
  • Evolved Stars
    Evolved Stars Planets orbiting the other stellar systems: Giant Stars White Dwarfs??? No. 1, 2010 RETIRED A STARS AND THEIR COMPANIONS. III. 397 Table 1 Planetary-Mass Companions to Evolved Intermediate-Mass Stars with M > 1.5 M ∗ " Star M SpT R MP sin i aeReference ∗ ∗ (M )(R )(MJup)(AU) " " HD 13189 2–6 K2 II 8–20 1.5–2.2 0.27 (0.06) 1, 2 ··· ! Tau 2.7(0.1) K0III 13.7(0.6) 7.6(0.2) 1.93(0.03) 0.151(0.023) 3 NGC 2423 No. 3 2.4 (0.2) 10.6 2.10 0.21 (0.07) 4 ··· ··· 81 Cet 2.4 (2.0–2.5) G5 III: 11 (10–13) 5.3 2.5 0.206 (0.029) 5 HD 104985 2.3 G9 III 11 8.3 0.95 0.090 (0.009) 6, 7 18 Del 2.3 G6 III 8.5 10.3 2.6 0.08 (0.01) 6 HD 17092 2.3 (0.3) K0 III 10.9 (2.8) 4.6 (0.3) 1.29 (0.05) 0.166 (0.052) 8 ξ Aql 2.2 K0 III 12 2.8 0.68 0.0 (fixed) 6 14 And 2.2 (2.0–2.3) K0 III 11 (10–12) 4.8 0.83 0.0 (fixed) 5 HD 81688 2.1 K0III-IV 13 2.7 0.81 0.0 (fixed) 6 HD 173416 2.0 (0.3) G8 III 13.5 (0.9) 2.7 (0.3) 1.16 (0.06) 0.21 (0.04) 9 HD 11977 1.91 (0.21) G5 III 10.09 (0.32) 6.54 1.93 0.40 (0.07) 10, 11 HD 102272 1.9 (0.3) K0 III 10.1 (4.6) 5.9 (0.2) 0.614 (0.001) 0.05 (0.04) 12 ””””2.6(0.4)1.57(0.05)0.68(0.06)12 β Gem 1.86, 1.7 (0.4) K0 III 8.8 (0.1) 2.9 (0.3) 1.69 (0.03) 0.06 (0.04) 13, 14, 15, 16 HD 89744 1.86 (0.18) F7 IV 2.08 (0.06) 7.2 0.88 0.70 (0.02) 17, 18 HD 210702 1.85 (0.13) K1 IV 4.45 (0.07) 1.97 (0.11,0.18) 1.20 (0.02,0.03) 0.036 (<0.106) 19, 20 κ CrB 1.84 (0.13) K0 IV 4.71 (0.08) 2.01 (0.11,0.17) 2.80 (0.07,0.08) 0.044 (<0.123) 21, 20 6Lyn 1.82(0.13) K0IV 5.2(4.9–5.6) 2.21(0.11,0.16) 2.18(0.05,0.06) 0.059(<0.125) 20, 5 HD 167042 1.72 (0.12) K1 IV 4.30 (0.07) 1.70 (0.09,0.12) 1.32 (0.03,0.04) 0.089 (0.028,0.065) 21, 20, 5 HD 192699 1.69 (0.12) G8 IV 3.90 (0.06) 2.40 (0.15,0.21) 1.15 (0.02,0.03) 0.129 (0.029,0.060) 19, 20 HD 175541 1.65 (0.12) G8 IV 3.80 (0.09) 0.70 (0.06,0.08) 1.03 (0.02,0.03) 0.083 (<0.283) 19 HD 5319 1.59 (0.18) G5 IV 3.26 (0.50,0.41) 1.94 1.75 0.12 (0.08) 22 Notes.
    [Show full text]