DOCSLIB.ORG

SPP NEO Inactive Body Small Planetary Platforms Assessment for NEO Inactive Bodies

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
SPP NEO Inactive Body Small Planetary Platforms Assessment for NEO Inactive Bodies CDF STUDY REPORT SPP NEO Inactive Body Small Planetary Platforms Assessment for NEO Inactive Bodies CDF-178(A) January 2018 SPP NEO Inactive Body CDF Study Report: CDF-178(A) January 2018 page 1 of 209 CDF Study Report SPP NEO Inactive Body Small Planetary Platforms Assessment for NEO Inactive Bodies ESA UNCLASSIFIED – Releasable to the Public SPP NEO Inactive Body CDF Study Report: CDF-178(A) January 2018 page 2 of 209 FRONT COVER Study Logo showing satellite approaching an asteroid with a swarm of SmallSats ESA UNCLASSIFIED – Releasable to the Public SPP NEO Inactive Body CDF Study Report: CDF-178(A) January 2018 page 3 of 209 STUDY TEAM This study was performed in the ESTEC Concurrent Design Facility (CDF) by the following interdisciplinary team: TEAM LEADER AOCS PAYLOAD COMMUNICATIONS POWER CONFIGURATION PROGRAMMATICS/ AIV COST ELECTRICAL PROPULSION DATA HANDLING CHEMICAL PROPULSION GS&OPS SYSTEMS MISSION ANALYSIS THERMAL MECHANISMS Under the responsibility of: S. Bayon, SCI-FMP, Study Manager With the scientific assistance of: Study Scientist With the technical support of: Systems/APIES Smallsats Radiation The editing and compilation of this report has been provided by: Technical Author ESA UNCLASSIFIED – Releasable to the Public SPP NEO Inactive Body CDF Study Report: CDF-178(A) January 2018 page 4 of 209 This study is based on the ESA CDF Open Concurrent Design Tool (OCDT), which is a community software tool released under ESA licence. All rights reserved. Further information and/or additional copies of the report can be requested from: S. Bayon ESA/ESTEC/SCI-FMP Postbus 299 2200 AG Noordwijk The Netherlands Tel: +31-(0)71-5655502 Fax: +31-(0)71-5655985 [email protected] For further information on the Concurrent Design Facility please contact: M. Bandecchi ESA/ESTEC/TEC-SYE Postbus 299 2200 AG Noordwijk The Netherlands Tel: +31-(0)71-5653701 Fax: +31-(0)71-5656024 [email protected] ESA UNCLASSIFIED – Releasable to the Public SPP NEO Inactive Body CDF Study Report: CDF-178(A) January 2018 page 5 of 209 TABLE OF CONTENTS 1 INTRODUCTION .................................................................................. 13 1.1 Background ...........................................................................................................13 1.2 Objective ................................................................................................................13 1.3 Scope .....................................................................................................................13 1.4 Document Structure ............................................................................................. 14 2 PAYLOAD ............................................................................................ 15 2.1 Requirements and Design Drivers MC ................................................................. 15 2.2 Requirements and Design Drivers SS ................................................................... 15 2.3 Assumptions and Trade offs SS ........................................................................... 16 2.3.1 Assumptions ................................................................................................... 16 2.3.2 Trade Offs and Selection of Instruments ....................................................... 16 2.4 Baseline Design SS ............................................................................................... 19 2.5 Accommodation ................................................................................................... 19 2.6 Operational Aspects ............................................................................................. 20 2.7 Data Volume ......................................................................................................... 21 3 MISSION ANALYSIS ........................................................................... 23 3.1 Requirements and Design Drivers MC ................................................................ 23 3.1.1 Multipoint Mission ........................................................................................ 23 3.1.2 Launch Vehicle ............................................................................................... 23 3.1.3 Launch Date ................................................................................................... 23 3.1.4 Transfer Duration .......................................................................................... 23 3.1.5 Duration of Operations .................................................................................. 23 3.2 Assumptions and Trade-Offs MC ........................................................................ 24 3.2.1 Small Body Classification ............................................................................... 24 3.2.2 Launch Strategies and Trade-Offs ................................................................. 26 3.2.3 Preliminary Assessment of DIFFERENT MISSIONS ................................... 29 3.3 Baseline Design MC ..............................................................................................31 3.3.1 Target Selection...............................................................................................31 3.3.2 Apophis ...........................................................................................................31 3.3.3 Launch Scenario ............................................................................................. 35 3.3.4 Transfers to Apophis ...................................................................................... 37 3.4 Sensitivity Analysis for MC: What if? .................................................................. 44 3.4.1 Launch into LEO + EP Assisted Escape ........................................................ 44 3.4.2 Other NEOs Targets ....................................................................................... 45 3.4.3 Mission to Phobos .......................................................................................... 48 4 SYSTEMS ............................................................................................ 53 4.1 System Requirements and Design Drivers .......................................................... 53 4.1.1 Mission and System Requirements Tree ....................................................... 53 4.1.2 Mission Requirements Update ...................................................................... 53 4.1.3 Mission Design Drivers .................................................................................. 57 ESA UNCLASSIFIED – Releasable to the Public SPP NEO Inactive Body CDF Study Report: CDF-178(A) January 2018 page 6 of 209 4.2 System Baseline Design ....................................................................................... 58 4.2.1 Target Selection and Strawman Payload ....................................................... 58 4.2.2 Transfer, Rendezvous and Operations Overview .......................................... 59 4.2.3 Baseline MC Design Summary ....................................................................... 60 4.2.4 Baseline SS Design Summary ........................................................................ 62 4.2.5 Propellant Budget .......................................................................................... 62 4.2.6 Product Tree ................................................................................................... 63 4.2.7 Modes and Phases .......................................................................................... 65 4.2.8 Smallsat Mass Budget and Equipment List ................................................... 66 4.2.9 Mother Spacecraft Mass Budget and Equipment List ................................... 68 4.2.10 Power Budget ................................................................................................. 70 4.2.11 Structural Assumptions .................................................................................. 71 4.3 System Options ..................................................................................................... 71 5 CONFIGURATION ............................................................................... 73 5.1 Requirements and Design Drivers MC ................................................................ 73 5.2 Requirements and Design Drivers SS .................................................................. 73 5.3 Assumptions and Trade offs MC .......................................................................... 74 5.4 Assumptions and Trade offs SS ........................................................................... 74 5.5 Baseline Design MC ............................................................................................. 74 5.5.1 Description of the MC Spacecraft .................................................................. 74 5.5.2 Main Dimensions of the MC spacecraft ......................................................... 81 5.6 Baseline Design SS ............................................................................................... 82 5.6.1 Description of the SS Spacecraft .................................................................... 82 5.6.2 Main Dimensions of the SS Spacecraft .......................................................... 84 6 MECHANISMS ..................................................................................... 87 6.1 Requirements and Design Drivers MC ...............................................................
Load more

Recommended publications
  • Planetary Science Division Status Report
    Planetary Science Division Status Report Jim Green NASA, Planetary Science Division January 26, 2017 Astronomy and Astrophysics Advisory CommiBee Outline • Planetary Science ObjecFves • Missions and Events Overview • Flight Programs: – Discovery – New FronFers – Mars Programs – Outer Planets • Planetary Defense AcFviFes • R&A Overview • Educaon and Outreach AcFviFes • PSD Budget Overview New Horizons exploresPlanetary Science Pluto and the Kuiper Belt Ascertain the content, origin, and evoluFon of the Solar System and the potenFal for life elsewhere! 01/08/2016 As the highest resolution images continue to beam back from New Horizons, the mission is onto exploring Kuiper Belt Objects with the Long Range Reconnaissance Imager (LORRI) camera from unique viewing angles not visible from Earth. New Horizons is also beginning maneuvers to be able to swing close by a Kuiper Belt Object in the next year. Giant IcebergsObjecve 1.5.1 (water blocks) floatingObjecve 1.5.2 in glaciers of Objecve 1.5.3 Objecve 1.5.4 Objecve 1.5.5 hydrogen, mDemonstrate ethane, and other frozenDemonstrate progress gasses on the Demonstrate Sublimation pitsDemonstrate from the surface ofDemonstrate progress Pluto, potentially surface of Pluto.progress in in exploring and progress in showing a geologicallyprogress in improving active surface.in idenFfying and advancing the observing the objects exploring and understanding of the characterizing objects The Newunderstanding of Horizons missionin the Solar System to and the finding locaons origin and evoluFon in the Solar System explorationhow the chemical of Pluto wereunderstand how they voted the where life could of life on Earth to that pose threats to and physical formed and evolve have existed or guide the search for Earth or offer People’sprocesses in the Choice for Breakthrough of thecould exist today life elsewhere resources for human Year forSolar System 2015 by Science Magazine as exploraon operate, interact well as theand evolve top story of 2015 by Discover Magazine.
    [Show full text]
  • Venona Special Studies
    - 1 - Venona Project Special Studies Transcribed by Students of the Mercyhurst College Institute for Intelligence Studies Arranged by John Earl Haynes, Library of Congress, 2010 COVER NAMES IN NEW YORK TRAFFIC p. 2 UNIDENTIFIED COVER NAMES IN NEW YORK TRAFFIC p. 86 COVER NAMES IN SAN FRANCISCO TRAFFIC p. 92 COVER NAMES IN WASHINGTON TRAFFIC p. 123 ADDITIONAL COVERNAMES AND RELATED INFORMATION IN DIPLOMATIC TRAFFIC p. 127 REVISED TRANSLATION OF MESSAGE ON ANTENNA-LIBERAL'S WIFE ETHEL p. 135 THE COVERNAMES "ANTENNA" AND "LIBERAL" IN . MESSAGES p. 139 ESSAGES IN . INVOLVING THE COVERNAME"ENORMOZ" AND THE NAMES OF NUCLEAR PHYSICISTS, ETC. p. 147 UNDATED REPORT OF MEREDITH GARDNER p. 155 DEVELOPMENT OF THE “G--“HOMER” [“GOMER”] CASE p. 158 THE KOMAR (KRAVCHENKO) AFFAIR IN . MESSAGES p. 161 REVISED TRANSLATION OF TWO . MESSAGES ON CHANGES IN COVERNAMES p. 170 THE COVERNAME "KARAS" IN. TRAFFIC p. 178 THE COVERNAMES "TÉNOR", "BAS", AND "CHETÁ" (? IN . TRAFFIC p. 181 - 2 - Special Study Cover Names in New York Traffic - 3 - cover-name Message number Date Publication reference S/ or 3/NBF/ 19 N.Y. to M. 812 29053 JKI 06 T1022 1B-1910 0027A ABRAM N.Y. to M. 992 24063 JKR 14 T872√ 1B-7518 0005A JACK SOBLE 1086 06073 JKV 48 T873√ 2A-0011 1957 29113 NNNNNN T939√ 625 04054 JHD 48 T916√ 851 15064 JIJ 40 T10.1√ 1146 10084 JHM 41 T123√ 1251 02094 JHN 12 T301√ (to ChEKh) 0005B 1353 23094 JHO 42 T289√ 1449 12104 JIL 37 T106√ 1754 14124 JHZ 49 T6√ 48 11015 JHV 37 (NSA)T1941 AVGUR 2A-0013 1638 (AUGUR) N.Y.
    [Show full text]
  • The Hera Mission
    Dr. Patrick Michel Hera Investigation Team PI Université Côte d’Azur Observatoire de la Côte d’Azur CNRS, Lagrange Laboratory Nice, France The Hera Mission ESA UNCLASSIFIED - For Official Use Hera main aspects Role of space missions at ESA in NEO hazard mitigation • Understanding the problem (deflection modeling and simulations) 2001 • Ground versus space solutions analyses • Assessment of space component options 2002- • 6 parallel phase-0 studies (3 space telescopes, 3 rendezvous) Euneos Nero Earthguard 1 2004 • ESA’s NEO Mission Advisory Panel (NEOMAP) established • Kinetic impactor validation ranked highest importance 2004- • Don Quijote mission selected and studied up to phase-A level 2006 • SANCHO / Proba-IP orbiter up to phase A level studies, small deep-space Don Quijote Ishtar Simone 2008- mission to investigate impactor’s result 2009 • AIDA proposed by NASA: USA/impactor + ESA/impact assessment • ESA phase 0 and phase A studies on the observer spacecraft "AIM” (GSP) 2011- Proba-IP 2016 • Phase B1 study and “consolidation phase” for mission definition (GSTP) • HERA: impact observer spacecraft reformulation and optimization AIM 2017- • Phase B1 implementation + payload + technology breadboards (GSTP+SSA) Several concepts 2019 • DART phase-C kick-off on 15 May 2018 Hera iterated AIDA: An International Planetary Defense Mission U.S. National Research Council Committee “Defending Planet Earth: Near-Earth Object Surveys and Hazard Mitigation Strategies” Recommendation: “If [U.S.] Congress chooses to fund mitigation research at an appropriately high level, the first priority for a space mission in the mitigation area is an experimental test of a kinetic impactor along with a characterization, monitoring, and verification system, such as the Don Quixote mission that was previously considered, but not funded, by the European Space Agency.
    [Show full text]
  • ESA SSA and Instrumentation Required for Space Weather Activities
    ESA SSA and instrumentation required for space weather activities Piers Jiggens, Alain Hilgers (ESTEC/TEC) Juha-Pekka Luntama, Alexi Glover (ESOC/HSO) SSA Preparatory Programme Overview (2009-2012) SSA Preparatory Programme SST NEO SWE Core CO-I CO-II Data Centre (DC-xx) Database and Prototype Requirements Architectural Portal Pilot Data and design Development Centres evaluation SN-I SN-II SN-IV SN-VI Preparation of Space Weather Space Weather Space Weather Space Weather Instruments Precursor Additional Services Implementation Service Services Design Study Operations and Development SSA Preparatory Programme Architecture studies ESA Customer Product System Req. (CRD) Spec. (PSD) Req. (SRD) CO-I Also SN-II CO-II Dedicated Space Weather Hosted SSA Spacecraft Instruments Payloads Programme Implementation Architectural Astrium Design Study Design Study (GmbH) Gather Instrument Astrium Kayser-Threde Documentation (GmbH) (GmbH) 2010 - Produce shortlist of Covering all 3 Covering only one viable missions Segments: segment: 2013 Space Surveillance Space Weather Match instruments & Tracking (other 2 are to missions Near-Earth Objects covered under a Space Weather separate contract) Determine 2012-2014 2013-2014 Development Plan SN-II: Space Weather Instrument Implementation Design Study - Inputs 1. Create database of instruments (46 originally included) Astrium (GmbH) 2. AO + instrument workshop (ESTEC, November 2010) Project Manager: Norbert Pailer 3. List of all possible mission opportunities (> 200 initially) 4. Shortlist of representative instruments based on maturity at the time and the amount of data provided (Design Descriptions, ICDs) including: • Radiation Monitors: NGRM, HMRM, EPT, SREM; Plasma instruments: SW- ChaPS, AMBER, AMBER_GEO, M-NLP • Micrometeoroids: AIDA-IS, SODA; Surface Potential: SPD; Magnetometer: MRMAG; Auroral Imager: WFAI; Solar X-rays: XFM 5.
    [Show full text]
  • Landing and Operations on Comet 67P/Churyumov–Gerasimenko
    Acta Astronautica ∎ (∎∎∎∎) ∎∎∎–∎∎∎ Contents lists available at ScienceDirect Acta Astronautica journal homepage: www.elsevier.com/locate/actaastro Rosetta Lander – Landing and operations on comet 67P/Churyumov–Gerasimenko Stephan Ulamec a,n, Cinzia Fantinati a, Michael Maibaum a, Koen Geurts a, Jens Biele a, Sven Jansen a, Oliver Küchemann a, Barbara Cozzoni a, Felix Finke a, Valentina Lommatsch a, Aurelie Moussi-Soffys b, Cedric Delmas b, Laurence O´Rourke c a DLR, D-51147 Köln, Germany b CNES, F-31055 Toulouse, France c ESA/ESAC, Urb. Villafranca del Castillo, ES-28691 Madrid, Spain article info abstract Article history: The Rosetta Lander Philae is part of the ESA Rosetta Mission which reached comet 67P/ Received 2 October 2015 Churyumov–Gerasimenko after a 10 year cruise in August 2014. Since then, Rosetta has Received in revised form been studying both its nucleus and coma with instruments aboard the Orbiter. On 16 November 2015 November 12th, 2014 the Lander, Philae, was successfully delivered to the surface of the Accepted 24 November 2015 comet and operated for approximately 64 h after separation from the mother spacecraft. Since the active cold gas system aboard the Lander as well as the anchoring harpoons did Keywords: not work, Philae bounced after the first touch-down at the planned landing site “Agilkia”.At Rosetta the final landing site, “Abydos”, a modified First Scientific Sequence was performed. Due to Philae the unexpectedly low illumination conditions and a lack of anchoring the sequence had to Lander be adapted in order to minimize risk and maximize the scientific output. All ten instru- Comet Operations ments could be activated at least once, before Philae went into hibernation.
    [Show full text]
  • Determination of Optimal Earth-Mars Trajectories to Target the Moons Of
    The Pennsylvania State University The Graduate School Department of Aerospace Engineering DETERMINATION OF OPTIMAL EARTH-MARS TRAJECTORIES TO TARGET THE MOONS OF MARS A Thesis in Aerospace Engineering by Davide Conte 2014 Davide Conte Submitted in Partial Fulfillment of the Requirements for the Degree of Master of Science May 2014 ii The thesis of Davide Conte was reviewed and approved* by the following: David B. Spencer Professor of Aerospace Engineering Thesis Advisor Robert G. Melton Professor of Aerospace Engineering Director of Undergraduate Studies George A. Lesieutre Professor of Aerospace Engineering Head of the Department of Aerospace Engineering *Signatures are on file in the Graduate School iii ABSTRACT The focus of this thesis is to analyze interplanetary transfer maneuvers from Earth to Mars in order to target the Martian moons, Phobos and Deimos. Such analysis is done by solving Lambert’s Problem and investigating the necessary targeting upon Mars arrival. Additionally, the orbital parameters of the arrival trajectory as well as the relative required ΔVs and times of flights were determined in order to define the optimal departure and arrival windows for a given range of date. The first step in solving Lambert’s Problem consists in finding the positions and velocities of the departure (Earth) and arrival (Mars) planets for a given range of dates. Then, by solving Lambert’s problem for various combinations of departure and arrival dates, porkchop plots can be created and examined. Some of the key parameters that are plotted on porkchop plots and used to investigate possible transfer orbits are the departure characteristic energy, C3, and the arrival v∞.
    [Show full text]
  • WV Graded Music List 2011
    2011 WV Graded Music List, p. 1 2011 West Virginia Graded Music List Grade 1 Grade 2 Grade 3 Grade 4 Grade 5 Grade 6 Grade Artist Arranger Title Publisher 1 - Higgins, John Suo Gan HL 1 - McGinty Japanese Folk Trilogy QU 1 - McGinty, Anne Elizabethan Songbook, An KJ 1 - Navarre, Randy Ngiele, Ngiele NMP 1 - Ployhar Along the Western Trail BE 1 - Ployhar Minka BE 1 - Ployhar Volga Boat Song BE 1 - Smith, R.W. Appalachian Overture BE Variant on an Old English 1 - Smith, R.W. BE Carol 1 - Story A Jubilant Carol BE 1 - Story Classic Bits and Pieces BE 1 - Story Patriotic Bits and Pieces BE 1 - Swearingen Three Chorales for Band BE 1 - Sweeney Shenandoah HL 1 Adams Valse Petite SP 1 Akers Berkshire Hills BO 1 Akers Little Classic Suite CF 1 Aleicheim Schaffer Israeli Folk Songs PO 1 Anderson Ford Forgotten Dreams BE 1 Anderson Ford Sandpaper Ballet BE 1 Arcadelt Whiting Ave Maria EM 1 Arensky Powell The Cuckoo PO 1 Bach Gardner Little Bach Suite ST Grand Finale from Cantata 1 Bach Gordon BO #207 1 Bach Walters Celebrated Air RU 1 Bain, James L. M Wagner Brother James' Air BE 1 Balent Bold Adventure WB Drummin' With Reuben And 1 Balent BE Rachel 1 Balent Lonesome Tune WB 1 Balmages Gettysburg FJ 2011 WV Graded Music List, p. 2 1 Balmages Majestica FJ 1 Barnes Ivory Towers of Xanadu SP 1 Bartok Castle Hungarian Folk Suite AL 1 Beethoven Clark Theme From Fifth Symphony HL 1 Beethoven Foulkes Creation's Hymn PO 1 Beethoven Henderson Hymn to Joy PO 1 Beethoven Mitchell Ode To Joy CF 1 Beethoven Sebesky Three Beethoven Miniatures Al 1 Beethoven Tolmage
    [Show full text]
  • Automated Trajectory Design for Impulsive and Low Thrust Interplanetary Mission Analysis Samuel Arthur Wagner Iowa State University
    Iowa State University Capstones, Theses and Graduate Theses and Dissertations Dissertations 2014 Automated trajectory design for impulsive and low thrust interplanetary mission analysis Samuel Arthur Wagner Iowa State University Follow this and additional works at: https://lib.dr.iastate.edu/etd Part of the Aerospace Engineering Commons, and the Applied Mathematics Commons Recommended Citation Wagner, Samuel Arthur, "Automated trajectory design for impulsive and low thrust interplanetary mission analysis" (2014). Graduate Theses and Dissertations. 14238. https://lib.dr.iastate.edu/etd/14238 This Dissertation is brought to you for free and open access by the Iowa State University Capstones, Theses and Dissertations at Iowa State University Digital Repository. It has been accepted for inclusion in Graduate Theses and Dissertations by an authorized administrator of Iowa State University Digital Repository. For more information, please contact [email protected]. Automated trajectory design for impulsive and low thrust interplanetary mission analysis by Samuel Arthur Wagner A dissertation submitted to the graduate faculty in partial fulfillment of the requirements for the degree of DOCTOR OF PHILOSOPHY Major: Aerospace Engineering Program of Study Committee: Bong Wie, Major Professor John Basart Ran Dai Ping Lu Ambar Mitra Iowa State University Ames, Iowa 2014 Copyright © Samuel Arthur Wagner, 2014. All rights reserved. ii DEDICATION I would like to thank my parents and all my family and friends who have helped me through- out my time as a student. Without their support I wouldn't have been able to make it. iii TABLE OF CONTENTS DEDICATION . ii LIST OF TABLES . vii LIST OF FIGURES . x ACKNOWLEDGEMENTS . xiii CHAPTER 1.
    [Show full text]
  • IAA Situation Report on Space Debris - 2016
    IAA Situation Report on Space Debris - 2016 Editors: Christophe Bonnal Darren S. McKnight International A cadem y of A stronautics Notice: The cosmic study or position paper that is the subject of this report was approved by the Board of Trustees of the International Academy of Astronautics (IAA). Any opinions, findings, conclusions, or recommendations expressed in this report are those of the authors and do not necessarily reflect the views of the sponsoring or funding organizations. For more information about the International Academy of Astronautics, visit the IAA home page at www.iaaweb.org. Copyright 2017 by the International Academy of Astronautics. All rights reserved. The International Academy of Astronautics (IAA), an independent nongovernmental organization recognized by the United Nations, was founded in 1960. The purposes of the IAA are to foster the development of astronautics for peaceful purposes, to recognize individuals who have distinguished themselves in areas related to astronautics, and to provide a program through which the membership can contribute to international endeavours and cooperation in the advancement of aerospace activities. © International Academy of Astronautics (IAA) May 2017. This publication is protected by copyright. The information it contains cannot be reproduced without written authorization. Title: IAA Situation Report on Space Debris - 2016 Editors: Christophe Bonnal, Darren S. McKnight Printing of this Study was sponsored by CNES International Academy of Astronautics 6 rue Galilée, Po Box 1268-16, 75766 Paris Cedex 16, France www.iaaweb.org ISBN/EAN IAA : 978-2-917761-56-4 Cover Illustration: NASA IAA Situation Report on Space Debris - 2016 Editors Christophe Bonnal Darren S.
    [Show full text]
  • Grid-Search Applications for Trajectory Design in Presence of Flybys
    i “output” — 2020/1/23 — 8:24 — page 1 — #1 i i i POLITECNICO DI MILANO DEPARTMENT OF AEROSPACE SCIENCE AND TECHNOLOGY DOCTORAL PROGRAMME IN AEROSPACE ENGINEERING GRID-SEARCH APPLICATIONS FOR TRAJECTORY DESIGN IN PRESENCE OF FLYBYS Doctoral Dissertation of: Davide Menzio Supervisor: Prof. Camilla Colombo Tutor: Prof. Biggs James Douglas The Chair of the Doctoral Program: Prof. Pierangelo Masarati Academic year 2018/19 – cycle XXXII i i i i i “output” — 2020/1/23 — 8:24 — page 2 — #2 i i i i i i i i “output” — 2020/1/23 — 8:24 — page I — #3 i i i Dedicated to the love of my life, Sara, who gave me the joy of my life, Ilyas. I i i i i i “output” — 2020/1/23 — 8:24 — page II — #4 i i i i i i i i “output” — 2020/1/23 — 8:24 — page III — #5 i i i Abstract N the design process of a deep-space exploration mission, two phases can be distin- guished: an interplanetary cruise and a final phase in planetary moon-system. In I both cases the flyby manoeuvres have a positive impact on the overall mission cost and the scientific return. This doctoral dissertation focuses on methods, techniques, and tools for modeling the trajectory in presence of flybys. Depending on the gravitational model used and the mission scenario foreseen, various part of the search space can be analysed and different insights derived about the nature of the third-body interaction. The ability of one method to reveal insights on the dynamics depends on the choice of the perfor- mance parameters and control variables used to study the trajectory evolution under the effect of the dynamics.
    [Show full text]
  • Porkchop Plot
    Porkchop plot Porkchop plot (also pork-chop plot) is a chart that depicts orbital trajectories for spacecraft. It is named for the characteristically porkchop-shaped contours that display combinations of launch date and arrival date characteristics of an interplanetary flight path for a given launch opportunity to Mars or any other planet.cite web author=Goldman, Elliot url=http://ccar.colorado.edu/asen5050/projects/projects_2003/goldman/ title=Launch Window Optimization: The 2005 Mars Reconnaissance Orbiter (MRO) Mission" publisher=. Representative porkchop plot for the 2005 Mars launch opportunity. What a porkchop plot really represents, says Johnston, is a solution to some orbital mechanics equations known as Lambert's theorem, which he sums up thusly: "If I know where the Earth is and where Mars is on some given day, and I know how long I would like to take to get to Mars, then I can compute the departure conditions I. Porkchop plot (also pork-chop plot) is a chart that shows contours of equal characteristic energy (C3) against combinations of launch date and arrival date for a particular interplanetary flight.[1]. By examining the results of the porkchop plot, engineers can determine when launch opportunities exist (a launch window) that is compatible with the capabilities of a particular spacecraft.[2] A given contour, called a porkchop curve, represents constant C3, and the center of the porkchop the optimal minimum C3. A porkchop plot is a data visualization tool used in interplanetary mission design which displays contours of various quantities as a function of departure and arrival date. Example pork chop plots for 2016 Earth-Mars transfers are shown here.
    [Show full text]
  • NASA Astronauts
    PUBLISHED BY Public Affairs Divisio~l Washington. D.C. 20546 1983 IColor4-by-5 inch transpar- available free to information lead and sent to: Non-informstionmedia may obtain identical material for a fee through a photographic contractor by using the order forms in the rear of this book. These photqraphs are government publications-not subject to copyright They may not be used to state oiimply the endorsement by NASA or by any NASA employee of a commercial product piocess or service, or used in any other manner that might mislead. Accordingly, it is requested that if any photograph is used in advertising and other commercial promotion. layout and copy be submitted to NASA prior to release. Front cover: "Lift-off of the Columbia-STS-2 by artist Paul Salmon 82-HC-292 82-ti-304 r 8arnr;w u vowzn u)rorr ~ nsrvnv~~nrnno................................................ .-- Seasat .......................................................................... 197 Skylab 1 Selected Pictures .......................................................150 Skylab 2 Selected Pictures ........................................................ 151 Skylab 3 Selected Pictures ........................................................152 Skylab 4 Selected Pictures ........................................................ 153 SpacoColony ...................................................................183 Space Shuttle ...................................................................171 Space Stations ..................................................................198 \libinn 1 1f.d Apoiio 17/Earth 72-HC-928 72-H-1578 Apolb B/Earth Rise 68-HC-870 68-H-1401 Voyager ;//Saturn 81-HC-520 81-H-582 Voyager I/Ssturian System 80-HC-647 80-H-866 Voyager IN~lpiterSystem 79-HC-256 79-H-356 Viking 2 on Mars 76-HC-855 76-H-870 Apollo 11 /Aldrin 69-HC-1253 69-H-682 Apollo !I /Aldrin 69-HC-684 69-H-1255 STS-I /Young and Crippen 79-HC-206 79-H-275 STS-1- ! QTPLaunch of the Columbia" 82-HC-23 82-H-22 Major Launches NAME UUNCH VEHICLE MISSIONIREMARKS 1956 VANGUARD Dec.
    [Show full text]