DOCSLIB.ORG

Overview of the Esa Jovian Technology Reference Studies

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Overview of the Esa Jovian Technology Reference Studies DOCUMENT OVERVIEW OF THE ESA JOVIAN TECHNOLOGY REFERENCE STUDIES prepared by/préparé par Alessandro Atzei, Arno Wielders, Anamarija Stankov, Peter Falkner reference/réference SCI-AP/2004/TN-085/AA issue/édition 3 revision/révision 0 date of issue/date d’édition 30/03/07 status/état Final Document type/type de document Technical Note SCI-AP a ESTEC Jovian Studies Overview Keplerlaan 1 - 2201 AZ Noordwijk - The Netherlands April_2_04_07 .doc Tel. (31) 71 5656565 - Fax (31) 71 5656040 Overview of the ESA Jovian Technology Reference Studies issue 3 revision 0 - 30/03/07 page 2 of 148 APPROVAL Title Overview of the ESA Jovian Technology Reference Studies issue 3 revision 0 titre issue revision author Alessandro Atzei, Arno Wielders, Anamarija Stankov, Peter date 30/03/07 auteur Falkner date approved by date approuvé by date Overview of the ESA Jovian Technology Reference Studies issue 3 revision 0 - 30/03/07 page 3 of 148 T ABLE O F C ONTENTS INTRODUCTION .....................................................................................................................................................7 Technology reference Studies....................................................................................................................7 Purpose of this document...........................................................................................................................7 STUDYING THE JOVIAN SYSTEM ..........................................................................................................................9 PREVIOUS MISSIONS ............................................................................................................................................11 RADIATION ENVIRONMENT OF JUPITER: MODELS AND MEASUREMENTS.................................................13 THE JOVIAN MINISAT EXPLORER – EXPLORING EUROPA .............................................................................17 JME-1 THE SCIENTIFIC INTEREST IN EUROPA ..............................................................................19 JME-1.1 Looking for a subsurface ocean...............................................................................................................19 JME-1.2 Global topography ...................................................................................................................................20 JME-1.3 Composition of the (sub)surface..............................................................................................................20 JME-2 THE JOVIAN MINISAT EXPLORER TRS................................................................................21 JME-3 THE STRAWMAN PAYLOAD ..................................................................................................23 JME-3.1 The JEO HIPS .........................................................................................................................................24 JME-3.2 The JRS HIPS..........................................................................................................................................26 JME-3.3 Impactors .................................................................................................................................................27 JME-3.3.1 JEO Microprobe Analysis (JEOMA).......................................................................................................27 JME-3.3.2 The Europa Microprobe In-Situ Explorer (EMPIE) ................................................................................32 JME-3.3.3 General comments on impactors..............................................................................................................36 JME-4 MISSION ANALYSIS ................................................................................................................38 JME-4.1 Launch .....................................................................................................................................................38 JME-4.2 The Transfer Phase ..................................................................................................................................38 JME-4.3 The Jovian Tour.......................................................................................................................................41 JME-4.3.1 Orbit insertion and initial orbit capture ....................................................................................................42 JME-4.3.2 The JRS tour.............................................................................................................................................45 JME-4.3.3 THE JEO TOUR ......................................................................................................................................50 JME-4.4 The Operational Phase.............................................................................................................................56 JME-4.5 Europa Coverage .....................................................................................................................................57 JME-4.6 Decommissioning ....................................................................................................................................58 JME-4.7 Radiation environment and electrostatic discharge .................................................................................60 Overview of the ESA Jovian Technology Reference Studies issue 3 revision 0 - 30/03/07 page 4 of 148 JME-5 THE SPACECRAFT..................................................................................................................63 JME-5.1 The composite..........................................................................................................................................63 JME-5.2 The Jovian Europa Orbiter.......................................................................................................................64 JME-5.3 The Jupiter Relay Satellite.......................................................................................................................67 JME-5.4 Overall mass budget ................................................................................................................................70 JME-5.5 Power budgets..........................................................................................................................................71 JME-5.6 Data transfer assumptions........................................................................................................................73 JME-6 SUMMARY OF THE MAIN CHALLENGES .............................................................................74 JME-RPS: THE RADIOISOTOPE POWER SOURCE OPTION .............................................................................77 RPS-1 INTRODUCTION.......................................................................................................................78 RPS-2 THE USE OF RPS.....................................................................................................................78 RPS-3 RPS TECHNOLOGY.................................................................................................................80 RPS-3.1 Current state.............................................................................................................................................80 RPS-3.2 New generation under development ........................................................................................................80 RPS-3.3 Expectations for future RPS ....................................................................................................................81 RPS-3.4 European expertise: Ulysses ....................................................................................................................82 RPS-4 IMPACT ON TRAJECTORY.....................................................................................................84 RPS-4.1 Drivers .....................................................................................................................................................84 RPS-4.2 Risks at Earth fly-bys...............................................................................................................................84 RPS-4.3 Risk mitigation by apogee raising ...........................................................................................................85 RPS-5 IMPACT ON SPACECRAFT DESIGN......................................................................................86 RPS-5.1 Configuration...........................................................................................................................................86 RPS-5.2 Thermal....................................................................................................................................................87 RPS-5.3 JME comparative budgets........................................................................................................................89 RPS-6 SAFETY IMPACT......................................................................................................................91 RPS-7 IMPACT ON THE DEVELOPMENT PLAN...............................................................................92 RPS-7.1 Drivers .....................................................................................................................................................92 RPS-7.2 RPS technology development..................................................................................................................92
Load more

Recommended publications
  • Machine Learning Regression for Estimating Characteristics of Low-Thrust Transfers
    MACHINE LEARNING REGRESSION FOR ESTIMATING CHARACTERISTICS OF LOW-THRUST TRANSFERS A Thesis Presented to The Academic Faculty By Gene L. Chen In Partial Fulfillment of the Requirements for the Degree Master of Science in the School of Aerospace Engineering Georgia Institute of Technology May 2019 Copyright c Gene L. Chen 2019 MACHINE LEARNING REGRESSION FOR ESTIMATING CHARACTERISTICS OF LOW-THRUST TRANSFERS Approved by: Dr. Dimitri Mavris, Advisor Guggenheim School of Aerospace Engineering Georgia Institute of Technology Dr. Alicia Sudol Guggenheim School of Aerospace Engineering Georgia Institute of Technology Dr. Michael Steffens Guggenheim School of Aerospace Engineering Georgia Institute of Technology Date Approved: April 15, 2019 To my parents, thanks for the support. ACKNOWLEDGEMENTS Firstly, I would like to thank Dr. Dimitri Mavris for giving me the opportunity to pursue a Master’s degree at the Aerospace Systems Design Laboratory. It has been quite the experience. Also, many thanks to my committee members — Dr. Alicia Sudol and Dr. Michael Steffens — for taking the time to review my work and give suggestions on how to improve - it means a lot to me. Additionally, thanks to Dr. Patel and Dr. Antony for helping me understand their work in trajectory optimization. iv TABLE OF CONTENTS Acknowledgments . iv List of Tables . vii List of Figures . viii Chapter 1: Introduction and Motivation . 1 1.1 Thesis Overview . 4 Chapter 2: Background . 5 Chapter 3: Approach . 17 3.1 Scenario Definition . 17 3.2 Spacecraft Dynamics . 18 3.3 Choice Between Direct and Indirect Method . 19 3.3.1 Chebyshev polynomial method . 20 3.3.2 Sims-Flanagan method .
    [Show full text]
  • 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
    [Show full text]
  • CALCEPH - Fortran 77/90/95 Language Release 3.5.0
    CALCEPH - Fortran 77/90/95 language Release 3.5.0 M. Gastineau, J. Laskar, A. Fienga, H. Manche Aug 19, 2021 CONTENTS 1 Introduction 3 2 Installation 5 2.1 Unix-like system (Linux, Mac OS X, BSD, Cygwin, ...)........................5 2.1.1 Quick instructions........................................5 2.1.2 Detailed instructions......................................5 2.2 Windows system.............................................7 2.2.1 Using the Microsoft Visual C++ compiler...........................7 2.2.2 Using the MinGW.......................................9 3 Library interface 11 3.1 A simple example program........................................ 11 3.2 Headers and Libraries.......................................... 11 3.2.1 Compilation on a Unix-like system............................... 12 3.2.2 Compilation on a Windows system............................... 12 3.3 Types................................................... 12 3.4 Constants................................................. 12 4 Multiple file access functions 15 4.1 Thread notes............................................... 15 4.2 Usage................................................... 15 4.3 Functions................................................. 15 4.3.1 calceph_open.......................................... 15 4.3.2 f90calceph_open_array..................................... 16 4.3.3 f90calceph_prefetch....................................... 17 4.3.4 f90calceph_isthreadsafe..................................... 17 4.3.5 f90calceph_compute.....................................
    [Show full text]
  • Orbital Fueling Architectures Leveraging Commercial Launch Vehicles for More Affordable Human Exploration
    ORBITAL FUELING ARCHITECTURES LEVERAGING COMMERCIAL LAUNCH VEHICLES FOR MORE AFFORDABLE HUMAN EXPLORATION by DANIEL J TIFFIN Submitted in partial fulfillment of the requirements for the degree of: Master of Science Department of Mechanical and Aerospace Engineering CASE WESTERN RESERVE UNIVERSITY January, 2020 CASE WESTERN RESERVE UNIVERSITY SCHOOL OF GRADUATE STUDIES We hereby approve the thesis of DANIEL JOSEPH TIFFIN Candidate for the degree of Master of Science*. Committee Chair Paul Barnhart, PhD Committee Member Sunniva Collins, PhD Committee Member Yasuhiro Kamotani, PhD Date of Defense 21 November, 2019 *We also certify that written approval has been obtained for any proprietary material contained therein. 2 Table of Contents List of Tables................................................................................................................... 5 List of Figures ................................................................................................................. 6 List of Abbreviations ....................................................................................................... 8 1. Introduction and Background.................................................................................. 14 1.1 Human Exploration Campaigns ....................................................................... 21 1.1.1. Previous Mars Architectures ..................................................................... 21 1.1.2. Latest Mars Architecture .........................................................................
    [Show full text]
  • Method for Rapid Interplanetary Trajectory Analysis Using Δv Maps with Flyby Options
    View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by DSpace@MIT METHOD FOR RAPID INTERPLANETARY TRAJECTORY ANALYSIS USING ΔV MAPS WITH FLYBY OPTIONS TAKUTO ISHIMATSU*, JEFFREY HOFFMAN†, AND OLIVIER DE WECK‡ Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, 77 Massachusetts Avenue, Cambridge, MA 02139, USA. Email: [email protected]*, [email protected]†, [email protected]‡ This paper develops a convenient tool which is capable of calculating ballistic interplanetary trajectories with planetary flyby options to create exhaustive ΔV contour plots for both direct trajectories without flybys and flyby trajectories in a single chart. The contours of ΔV for a range of departure dates (x-axis) and times of flight (y-axis) serve as a “visual calendar” of launch windows, which are useful for the creation of a long-term transportation schedule for mission planning purposes. For planetary flybys, a simple powered flyby maneuver with a reasonably small velocity impulse at periapsis is allowed to expand the flyby mission windows. The procedure of creating a ΔV contour plot for direct trajectories is a straightforward full-factorial computation with two input variables of departure and arrival dates solving Lambert’s problem for each combination. For flyby trajectories, a “pseudo full-factorial” computation is conducted by decomposing the problem into two separate full-factorial computations. Mars missions including Venus flyby opportunities are used to illustrate the application of this model for the 2020-2040 time frame. The “competitiveness” of launch windows is defined and determined for each launch opportunity. Keywords: Interplanetary trajectory, C3, delta-V, pork-chop plot, launch window, Mars, Venus flyby 1.
    [Show full text]
  • Imp-C Orbit and Launch Time Analysis
    IMP-C ORBIT AND LAUNCH TIME ANALYSIS BY STEPHEN J. PADDACK / I BARBARA E. SHUTE Nb 5 72614 I I GPO PRICE $ - IACCESSION NUMBER) (THRUI OTS PRICE(S) $ HA / ~PAoIih .(CODE1 7mx 3-TZ-P -'-so Hard copy (HC) % (NASA CR OR TMX OWAD NUMBER) (CATEOORY) 3#8 I j .. Microfiche (MF) JANUARY 1965 1 -GODDARD SPACE FLIGHT CENTER - GREENBELT, MARYLAND \ X-643 -6 5-40 IMP-c ORBIT AND LAUNCH TIME ANALYSIS Stephen J. Paddack and Barbara E. Shute Special Projects Branch Theoretical Division January 1965 Goddard Space Flight Center Greenbelt, Maryland TABLE OF CONTENTS -Page Abstract.. ........................................ vii NOMENCLATURE ................................... viii INTRODUCTION .................................... 1 I. ASSUMPTIONS .................................. 2 A. Nominal Initial Orbits ........................... 2 B. Dispersions on Initial Conditions .................... 4 C. Restraints on Launch Time ....................... 4 It. COMPUTING TECHNIQUES AND PROGRAMS ............. 7 A. ITEM ...................................... 7 B. Launch Window Program ......................... 7 C. Analog Stability Program ......................... 8 D. Program Comparison ........................... 8 E. Selection of Mean Elements ....................... 8 III. LAUNCH WINDOW MAPS.. ......................... 9 A. Yearsurvey ................................. 9 1. Lifetime Boundary ........................... 10 2. Spacecraft Restraints Boundary .................. 10 B. DetailedMap ................................. 11 IV. SPACECRAFT DATA.............................
    [Show full text]
  • Spacecraft Conjunction Assessment and Collision Avoidance Best Practices Handbook
    National Aeronautics and Space Administration National Aeronautics and Space Administration NASA Spacecraft Conjunction Assessment and Collision Avoidance Best Practices Handbook December 2020 NASA/SP-20205011318 The cover photo is an image from the Hubble Space Telescope showing galaxies NGC 4038 and NGC 4039, also known as the Antennae Galaxies, locked in a deadly embrace. Once normal spiral galaxies, the pair have spent the past few hundred million years sparring with one another. Image can be found at: https://images.nasa.gov/details-GSFC_20171208_Archive_e001327 ii NASA Spacecraft Conjunction Assessment and Collision Avoidance Best Practices Handbook DOCUMENT HISTORY LOG Status Document Effective Description (Baseline/Revision/ Version Date Canceled) Baseline V0 iii NASA Spacecraft Conjunction Assessment and Collision Avoidance Best Practices Handbook THIS PAGE INTENTIONALLY LEFT BLANK iv NASA Spacecraft Conjunction Assessment and Collision Avoidance Best Practices Handbook Table of Contents Preface ................................................................................................................ 1 1. Introduction ................................................................................................... 3 2. Roles and Responsibilities ............................................................................ 5 3. History ........................................................................................................... 7 USSPACECOM CA Process .............................................................
    [Show full text]
  • Launch Conjunction Assessment Handbook Version 1.0  December 2018
    JFSCC, 18th Space Control Squadron Combined Space Operations Center (CSpOC) Vandenberg Air Force Base, California, USA Tel +1-805-605-3533 www.space-track.org LAUNCH CONJUNCTION ASSESSMENT HANDBOOK VERSION 1.0 DECEMBER 2018 18 SPCS Process for Launch Conjunction Assessment TABLE OF CONTENTS Contents Revision History _________________________________________________________________________________________ 1 Important Definitions ___________________________________________________________________________________ 2 18th Space Control Squadron ____________________________________________________________________________________2 Launch Conjunction Assessment _________________________________________________________________________________2 Launch Collision Avoidance ______________________________________________________________________________________2 General Pertubations _____________________________________________________________________________________________2 Special Pertubations ______________________________________________________________________________________________2 Launch Conjunction Assessment Authorities __________________________________________________________ 3 Air Force Instruction 91-217 Space Safety And Mishap Prevention Program ________________________________3 Title 14 Code of Federal Regulations (14 CFR)__________________________________________________________________3 USSTRATCOM SSA Sharing Program _____________________________________________________________________________3 Space-Track.org____________________________________________________________________________________________________4
    [Show full text]
  • Technical Constraints Impact on Mission Design to the Collinear Sun-Earth Libration Points
    1 Technical Constraints Impact on Mission Design to the Collinear Sun-Earth Libration Points N. Eismont, A. Sukhanov, V. Khrapchenkov Space Research Institute, Russian Academy of Sciences ABSTRACT For the practical realization of the mission to the collinear Sun-Earth libration points technical constraints play a significant role. In the paper the influence of the constraints generated by the use of piggi-back mode of the delivering spacecraft to the vicinity of libration points are studied. High elliptical parking orbit of Molniya is taken as initial orbit for start to the L1, L2 libration points. The parameters of this orbit are supposed to be fixed and determined by the main payload demands. The duration of the passenger payload keeping on the mentioned 12 hours period orbit is limited for the case when launcher upper stage is used for the velocity impulse applying to put spacecraft onto transfer orbit to the libration point. The possibility to use one axis attitude control of the spacecraft for the executing correction maneuvers are investigated, supposing that spacecraft is spin stabilized with the spin axis directed to the Sun and maneuver impulse goes along this axis. The cost of constraints is presented in terms of characteristic velocity and time of transfer to the libration point vicinity. The goal of the paper is to understand the possibility of using regular launches of Molniya communication satellite by Soyuz-Fregat launch vehicle for sending low cost scientific spacecraft to Sun-Earth libration points. INTRODUCTION The mission to the vicinity of Sun-Earth collinear libration points are fulfilled and planned for the scientific experiments gaining big advantages from use of this region of space for optimal measurement conditions.
    [Show full text]
  • CALCEPH - Octave/Matlab Language Release 3.5.0
    CALCEPH - Octave/Matlab language Release 3.5.0 M. Gastineau, J. Laskar, A. Fienga, H. Manche Aug 19, 2021 CONTENTS 1 Introduction 3 2 Installation 5 2.1 Unix-like system (Linux, Mac OS X, BSD, Cygwin, ...)........................5 2.2 Windows system.............................................6 2.2.1 Using the Microsoft Visual C++ compiler...........................6 2.2.2 Using the MinGW.......................................7 3 Library interface 9 3.1 A simple example program........................................9 3.2 Package..................................................9 3.3 Types................................................... 10 3.4 Constants................................................. 10 4 Multiple file access functions 13 4.1 Thread notes............................................... 13 4.2 Usage................................................... 13 4.3 Functions................................................. 13 4.3.1 CalcephBin.open........................................ 13 4.3.2 CalcephBin.open........................................ 14 4.3.3 CalcephBin.prefetch...................................... 15 4.3.4 CalcephBin.isthreadsafe.................................... 15 4.3.5 CalcephBin.compute...................................... 15 4.3.6 CalcephBin.compute_unit................................... 17 4.3.7 CalcephBin.orient_unit..................................... 18 4.3.8 CalcephBin.rotangmom_unit.................................. 20 4.3.9 CalcephBin.compute_order................................... 21 4.3.10
    [Show full text]
  • Determination of Close Approaches for Earth-Fixed Launch Trajectories
    AAS-98-134 DETERMINATION OF CLOSE APPROACHES FOR EARTH-FIXED LAUNCH TRAJECTORIES James Woodburn= The deployment of large constellations of satellites in Low Earth Orbit increases the probability of close approaches with newly launched satellites. A new algorithm for determining launch window blackout intervals based on the avoidance of close approaches for launch trajectories which are fixed relative to the Earth Fixed coordinate system is presented. This algorithm is more robust than the technique of performing close approach analyses by sampling the launch window and significantly more efficient. The example case presented shows an improvement in efficiency by a factor of 200 while detecting blackout intervals as small as 0.3 seconds in duration. INTRODUCTION As the number of objects in orbit about the Earth increases, the determination of close approaches between objects is becoming an increasingly important aspect of satellite operations. A recent study by Jenkins and Schumacher 1 indicates the growing importance of close approach prediction for the Shuttle and the Mir space station. The basic problem is to determine when two objects will have a conjunction where the risk of collision is unacceptably large. There are many ways of defining what constitutes risk. These definitions range in complexity from the specification of a minimum allowable separation distance between the two objects to using complex probability density functions to determine the statistical probability of collision during a conjunction. Prior studies of the close approach problem have focused on the case where all objects are assumed to be in orbit about the Earth and the nominal ephemeris of the objects is known.
    [Show full text]
  • Astrogator in STK
    Astrodynamics (AERO0024) TP1: Introduction Teaching Assistant ⎯ Amandine Denis Contact details Space Structures and Systems Lab (S3L) Structural Dynamics Research Group Aerospace and Mechanical Engineering Department Room: +2/516 (B52 building) [email protected] 04 3669535 2 Today’s program Objectives Presentation of STK Exercise 1: « What does STK do, anyway? » Exercise 2: Do It Yourself! 3 Objectives of this session Discover STK and its possibilities Discover STK interface Discover basic functions and options Illustrate the first lesson 4 Objectives of this session At the end of this session, you should be able to: Create a new scenario Handle graphics windows (2D and 3D, view from/to, …) Use common options of the Properties Browser Insert a satellite in three different ways (database, Orbit Wizard, manually) Insert a facility Calculate a simple access Generate simple reports 5 Presentation of STK Design, analyze, visualize, and optimize land, sea, air, and space systems. 6 Presentation of STK – interface 7 8 9 Presentation of STK 10 11 Presentation of STK – basic elements New scenario - Model the World! Insert object - Populate the World! Properties browser - Decide everything! Animation Reports Tabs 12 Exercise 1 First contact: « What does STK do, anyway? » AGI tutorial Illustration of a Molniya orbit Notion of scenario Rules of thumb Orbit Wizard Insertion of a facility Graphics windows Calculation of a simple access 13 Exercise 1: what does STK do, anyway? Î Are Molniya orbits really a great way to spy on the USA? How many periods of access? When does the first access occur? What is the duration of the first access? Remarks/questions ? 14 Exercise 2 Do It Yourself! : Application to the satellites of the first lesson Insertion of satellites and definition of orbits: • Using Orbit Wizard • Importing from Data Base • Manually Illustration of differents satellites and orbits Options of visualization 15 Exercise 2: application to the 1st lesson >> Represent in STK all the satellites named during the first lesson.
    [Show full text]