A Low-Cost Mission for LISA Markus Landgraf, Florian Renk, Pierre Joachim, Rüdiger Jehn HSO-GFA
|
|
- Rosemary Florence Blake
- 6 years ago
- Views:
Transcription
1 A Low-Cost Mission for LISA Markus Landgraf, Florian Renk, Pierre Joachim, Rüdiger Jehn HSO-GFA LISA Internal Final Presentation July 8 th, 2011 CDF HSO-GFA Page 1
2 Overview Basic working assumptions Operational orbit: heliocentric slow drift-away Soyuz launch from Kourou Transfer scenarios Total delta-v budgets Conclusion LISA Internal Final Presentation July 8 th, 2011 CDF HSO-GFA Page 2
3 Basic assumptions V-config L=10 6 km basic angle 90deg, no difference in delta-v for 60deg LISA Internal Final Presentation July 8 th, 2011 CDF HSO-GFA Page 3
4 Circular Heliocentric Trailing For slow drift (15deg over 5 years) Stop manoeuvre is required Initial trailing angle 10deg to avoid disturbance of the formation Third body perturbation by the Earth is compensated by drift in the HCW frame Full numerical simulation and minimisation of breathing performed LISA Kick-Off June 15 th, 2011 CDF HSO-GFA Page 4
5 Drifting LISA Internal Final Presentation July 8 th, 2011 CDF HSO-GFA Page 5
6 Constellation Breathing LISA Internal Final Presentation July 8 th, 2011 CDF HSO-GFA Page 6
7 Constellation Arm Length LISA Internal Final Presentation July 8 th, 2011 CDF HSO-GFA Page 7
8 Constellation Range Rate LISA Internal Final Presentation July 8 th, 2011 CDF HSO-GFA Page 8
9 Interplanetary Transfer vinf [m/s] decl [deg] rasc [deg] Δv arr [m/s] mother daugther daughter LISA Internal Final Presentation July 8 th, 2011 CDF HSO-GFA Page 9
10 Soyuz Launch from Kourou LISA Internal Final Presentation July 8 th, 2011 CDF HSO-GFA Page 10
11 Soyuz Launcher Performance LISA Internal Final Presentation July 8 th, 2011 CDF HSO-GFA Page 11
12 Transfer Scenarios Baseline: Double launch lunar fly-by 1. Soyuz launches 2 Daughters into HEO at 15deg inclination Daughters perform lunar fly-by to reach escape condition 2. Soyuz launches Mother directly into i=65deg departure hyperbola Option 1: Double launch direct: same launch scenario as in baseline, but without lunar fly-by, but split manoeuvres are performed after leaving the Earth s sphere of influence Option 2: Single launch direct: launch all spacecraft on one launcher, all three perform a split manoeuvre after leaving the Earth s sphere of influence LISA Internal Final Presentation July 8 th, 2011 CDF HSO-GFA Page 12
13 Lunar Fly-by transfer Example transfer: Injection of S/Cs into HEO with rapo = 400,000 km - Orbital plane is equivalent to lunar orbital plane (LOP) (accessibility from Kourou TBD, see next slide) At apogee both S/C change the inclination with respect to the LOP by 10.5 DEG (both planes are then 21 DEG apart) At next perigee pass the apogee must be raised to reach the required v after the fly-by - Apogee raising ΔV = 40 m/s Lunar fly-by approaching the moon from different hemispheres leads to required v vectors LISA Internal Final Study Presentation July 8 th, 2011 CDF HSO-GFA Page 13
14 Lunar Fly-by transfer Insertion in lunar orbital plane (LOP) not always possible Restrictions on the launcher inclination due to walking impact point of 3 rd stage GAIA launcher scenario with 15 DEG parking orbit Unbalanced ΔV for rotation of orbital planes - Required rotation now 3 DEG and 24 DEG Manoeuvre 11 and 80 m/s, respectively Declination of the moon is 50 % of the time below 15 deg and can then be reached from a 15-deg inclination HEO Lunar flyby time slot from MJD= to Example case: flyby on 8 Aug 2019 ( ) with v =731 m/s at an altitude of 200 km LISA Internal Final Study Presentation July 8 th, 2011 CDF HSO-GFA Page 14
15 Delta-v budget LGA transfer, double launch mother daughter 1 daughter 2 launcher disp 36m/s 5m/s 5m/s perigee raise - 40m/s 40m/s plane change - 11m/s 80m/s apogee raise - 40m/s 40m/s arrival 154m/s 130m/s 104m/s navigation 20m/s 20m/s 20m/s launch window reserve, gravity loss (20%) 42m/s 46m/s 50m/s total 252m/s 272m/s 299m/s LISA Internal Final Presentation July 8 th, 2011 CDF HSO-GFA Page 15
16 Delta-v budget direct transfer, double launch mother daughter 1 daughter 2 launcher disp 36m/s 5m/s 5m/s perigee raise - 10m/s 10m/s apogee raise - 773m/s 773m/s split - 148m/s 148m/s arrival 154m/s 130m/s 104m/s navigation 20m/s 20m/s 20m/s launch window reserve, gravity loss (20%) 42m/s 218m/s 212m/s total 252m/s 1304m/s 1272m/s LISA Internal Final Presentation July 8 th, 2011 CDF HSO-GFA Page 16
17 Delta-v budget direct transfer, single launch mother daughter 1 daughter 2 launcher disp 5m/s 5m/s 5m/s perigee raise 10m/s 10m/s 10m/s apogee raise 773m/s 773m/s 773m/s split 167m/s 167m/s 167m/s arrival 154m/s 130m/s 104m/s navigation 20m/s 20m/s 20m/s launch window reserve, gravity loss (20%) 226m/s 218m/s 212m/s total 1355m/s 1304m/s 1272m/s LISA Internal Final Presentation July 8 th, 2011 CDF HSO-GFA Page 17
18 Consequences of Longer Arms Cost is 100m/s per 1 million km in arrival delta-v, distribution between individual S/C is TBD LISA Internal Final Presentation July 8 th, 2011 CDF HSO-GFA Page 18
19 Conclusion (1/2) The heliocentric drift-away formation has the potential to minimise the LISA propulsion system (in size, minimum thrust, and cost) other options do not provide the required formation stability, require significant stationkeeping or large distances in the Earth Increasing the arm length costs approximately 100m/s per 1 million km Soyuz provides 1,933kg for the mother launch (i=65deg escape), 2,210kg (15deg HEO with apogee at 400,000km, 2,277kg minus 3% margin due to unconfirmed launcher optimisation) LISA Internal Final Presentation July 8 th, 2011 CDF HSO-GFA Page 19
20 Conclusion (2/2) Delta-v budget provided for three transfer scearios double-launch with daughters performing lunar fly-by double-launch with direct transfer single launch with direct transfer LISA Internal Final Presentation July 8 th, 2011 CDF HSO-GFA Page 20
IMPACT OF SPACE DEBRIS MITIGATION REQUIREMENTS ON THE MISSION DESIGN OF ESA SPACECRAFT
IMPACT OF SPACE DEBRIS MITIGATION REQUIREMENTS ON THE MISSION DESIGN OF ESA SPACECRAFT Rüdiger Jehn (1), Florian Renk (1) (1 ) European Space Operations Centre, Robert-Bosch-Str. 5, 64293 Darmstadt, Germany,
More informationarxiv:gr-qc/ v1 15 Nov 2004
Mission design for LISA Pathfinder arxiv:gr-qc/0411071v1 15 Nov 2004 M Landgraf, M Hechler, and S Kemble ESA/ESOC, Robert-Bosch-Straße 5, D-64293 Darmstadt, Germany E-mail: Markus.Landgraf@esa.int EADS
More informationEnd-Of-Life Disposal Concepts for Lagrange-Point and Highly Elliptical Orbit Missions
End-Of-Life Disposal Concepts for Lagrange-Point and Highly Elliptical Orbit Missions Executive summary of the main study and the study extension Version 1.0 12 February 2015 ESA/ESOC contract No. 4000107624/13/F/MOS
More informationESMO Mission Analysis
Changing the economics of space ESMO Mission Analysis SRR Workshop Alison Gibbings 22 nd 26 th March 2010 Review of the existing baseline Sensitivity analysis Contents At lunar Injection Along the WSB-Moon
More informationBepiColombo Launch Window Design Based on a Phasing Loop Strategy
BepiColombo Launch Window Design Based on a Phasing Loop Strategy Carlos Corral van Damme * GMV, Tres Cantos, Madrid, 28760, Spain Rüdiger Jehn and Stefano Campagnola European Space Operations Centre,
More informationASEN 5050 SPACEFLIGHT DYNAMICS Interplanetary
ASEN 5050 SPACEFLIGHT DYNAMICS Interplanetary Prof. Jeffrey S. Parker University of Colorado Boulder Lecture 29: Interplanetary 1 HW 8 is out Due Wednesday, Nov 12. J2 effect Using VOPs Announcements Reading:
More informationAstrodynamics (AERO0024)
Astrodynamics (AERO0024) 10. Interplanetary Trajectories Gaëtan Kerschen Space Structures & Systems Lab (S3L) Motivation 2 6. Interplanetary Trajectories 6.1 Patched conic method 6.2 Lambert s problem
More informationASTRIUM. Interplanetary Path Early Design Tools at ASTRIUM Space Transportation. Nathalie DELATTRE ASTRIUM Space Transportation.
Interplanetary Path Early Design Tools at Space Transportation Nathalie DELATTRE Space Transportation Page 1 Interplanetary missions Prime approach: -ST has developed tools for all phases Launch from Earth
More informationESA activities towards the Gravitation Waves Space Observatory
ESA activities towards the Gravitation Waves Space Observatory Frédéric Safa ESA Science Directorate, Future Missions LISA Symposium, Zurich 2016 The Gravitation Wave Observatory in ESA Science Programme
More informationInterplanetary Mission Opportunities
Interplanetary Mission Opportunities Introduction The quest for unravelling the mysteries of the universe is as old as human history. With the advent of new space technologies, exploration of space became
More informationEUROSTAR 3000 INCLINED ORBIT MISSION : LIFETIME OPTIMISATION IN CASE OF INJECTION WITH A LOW INCLINATION
EUROSTAR 3000 INCLINED ORBIT MISSION : LIFETIME OPTIMISATION IN CASE OF INJECTION WITH A LOW INCLINATION Franck Raballand (1), Julie De Lamarzelle (2), François Bonaventure (3), Anne-Hélène Gicquel (4)
More informationMission Design Options for Solar-C Plan-A
Solar-C Science Definition Meeting Nov. 18, 2008, ISAS Mission Design Options for Solar-C Plan-A Y. Kawakatsu (JAXA) M. Morimoto (JAXA) J. A. Atchison (Cornell U.) J. Kawaguchi (JAXA) 1 Introduction 2
More informationSatellite Orbital Maneuvers and Transfers. Dr Ugur GUVEN
Satellite Orbital Maneuvers and Transfers Dr Ugur GUVEN Orbit Maneuvers At some point during the lifetime of most space vehicles or satellites, we must change one or more of the orbital elements. For example,
More informationSolar Orbiter Ballistic Transfer Mission Analysis Synthesis
European Space Agency Agence Spatiale Européenne directorate of operations and infrastructure ground systems engineering department mission analysis office MAO Working Paper No. 483 Issue 1, Rev. 0 Solar
More informationAstrodynamics (AERO0024)
Astrodynamics (AERO0024) L06: Interplanetary Trajectories Gaëtan Kerschen Space Structures & Systems Lab (S3L) Motivation 2 Problem Statement? Hint #1: design the Earth-Mars transfer using known concepts
More informationSIMBOL-X: A FORMATION FLYING MISSION ON HEO FOR EXPLORING THE UNIVERSE
SIMBOL-X: A FORMATION FLYING MISSION ON HEO FOR EXPLORING THE UNIVERSE P. Gamet, R. Epenoy, C. Salcedo Centre National D Etudes Spatiales (CNES) 18 avenue Edouard Belin, 31401 TOULOUSE Cedex 9, France
More informationChapter 8. Precise Lunar Gravity Assist Trajectories. to Geo-stationary Orbits
Chapter 8 Precise Lunar Gravity Assist Trajectories to Geo-stationary Orbits Abstract A numerical search technique for designing a trajectory that transfers a spacecraft from a high inclination Earth orbit
More informationCAS-ESA Call for small mission proposals - Technical annex
CAS-ESA Call for small mission proposals - Technical annex Copenhagen workshop 23/09/2014 Table of contents 1. General considerations Mass & power Schedule Work breakdown and share Technology readiness
More informationOptElec: an Optimisation Software for Low-Thrust Orbit Transfer Including Satellite and Operation Constraints
OptElec: an Optimisation Software for Low-Thrust Orbit Transfer Including Satellite and Operation Constraints 7th International Conference on Astrodynamics Tools and Techniques, DLR, Oberpfaffenhofen Nov
More informationRELATIVE MISSION ANALYSIS FOR PROBA 3: SAFE ORBITS AND CAM
5TH INTERNATIONAL CONFERENCE ON SPACECRAFT FORMATION FLYING MISSIONS AND TECHNOLOGIES RELATIVE MISSION ANALYSIS FOR PROBA 3: SAFE ORBITS AND CAM Munich, 31 st May 2013 T. V. Peters D. Escorial Presented
More informationNew Worlds Observer Final Report Appendix J. Appendix J: Trajectory Design and Orbit Determination Lead Author: Karen Richon
Appendix J: Trajectory Design and Orbit Determination Lead Author: Karen Richon The two NWO spacecraft will orbit about the libration point created by the Sun and Earth/Moon barycenter at the far side
More informationPLANETARY MISSIONS FROM GTO USING EARTH AND MOON GRAVITY ASSISTS*
. AIAA-98-4393 PLANETARY MISSIONS FROM GTO USING EARTH AND MOON GRAVITY ASSISTS* Paul A. Penzo, Associate Fellow AIAA+ Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Dr. Pasadena,
More informationInterplanetary Travel
Interplanetary Travel Interplanetary Travel Concept Patched Conic Hypothesis Departure & Arrival Manoeuvres Interplanetary Travel Concept Interplanetary travel is concerned with motion of manmade objects
More informationInterplanetary Mission Analysis
Interplanetary Mission Analysis Stephen Kemble Senior Expert EADS Astrium stephen.kemble@astrium.eads.net Page 1 Contents 1. Conventional mission design. Advanced mission design options Page 1. Conventional
More informationLAUNCHES AND LAUNCH VEHICLES. Dr. Marwah Ahmed
LAUNCHES AND LAUNCH VEHICLES Dr. Marwah Ahmed Outlines 2 Video (5:06 min) : https://youtu.be/8t2eyedy7p4 Introduction Expendable Launch Vehicles (ELVs) Placing Satellite into GEO Orbit Introduction 3 Introduction
More informationM5 Call - Technical Annex
M5 Call - Technical Annex Prepared by SCI-F Reference ESA-SCI-F-ESTEC-TN-2016-002 Issue 1 Revision 0 Date of Issue 25/04/2016 Status Issued Document Type Distribution Table of contents: 1 Introduction...
More informationASEN 6008: Interplanetary Mission Design Lab Spring, 2015
ASEN 6008: Interplanetary Mission Design Lab Spring, 2015 Lab 4: Targeting Mars using the B-Plane Name: I d like to give credit to Scott Mitchell who developed this lab exercise. He is the lead Astrodynamicist
More informationPowered Space Flight
Powered Space Flight KOIZUMI Hiroyuki ( 小泉宏之 ) Graduate School of Frontier Sciences, Department of Advanced Energy & Department of Aeronautics and Astronautics ( 基盤科学研究系先端エネルギー工学専攻, 工学系航空宇宙工学専攻兼担 ) Scope
More informationSpace Travel on a Shoestring: CubeSat Beyond LEO
Space Travel on a Shoestring: CubeSat Beyond LEO Massimiliano Vasile, Willem van der Weg, Marilena Di Carlo Department of Mechanical and Aerospace Engineering University of Strathclyde, Glasgow 5th Interplanetary
More informationSpace-Based Polar Remote Sensing
in co- opera+on with Space-Based Polar Remote Sensing Malcolm Macdonald working with Pamela C Anderson, Carl Warren & Ben Dobke www.strath.ac.uk/mae 12 October 2012 View of Earth at 1200hrs UTC, 12 Slide
More informationPrevious Lecture. Orbital maneuvers: general framework. Single-impulse maneuver: compatibility conditions
2 / 48 Previous Lecture Orbital maneuvers: general framework Single-impulse maneuver: compatibility conditions closed form expression for the impulsive velocity vector magnitude interpretation coplanar
More informationOPTIMAL DESIGN OF LOW-ENERGY TRANSFERS TO HIGHLY ECCENTRIC FROZEN ORBITS AROUND THE MOON
IAC-010-B4-8 OPTIMAL DESIGN OF LOW-ENERGY TRANSFERS TO HIGHLY ECCENTRIC FROZEN ORBITS AROUND THE MOON Author: Ms. Alison Gibbings, agibbing@eng.gla.ac.uk Glasgow University, Space Advanced Research Team,
More informationList of Tables. Table 3.1 Determination efficiency for circular orbits - Sample problem 1 41
List of Tables Table 3.1 Determination efficiency for circular orbits - Sample problem 1 41 Table 3.2 Determination efficiency for elliptical orbits Sample problem 2 42 Table 3.3 Determination efficiency
More informationThe Interstellar Boundary Explorer (IBEX) Mission Design: A Pegasus Class Mission to a High Energy Orbit
The Interstellar Boundary Explorer (IBEX) Mission Design: A Pegasus Class Mission to a High Energy Orbit Ryan Tyler, D.J. McComas, Howard Runge, John Scherrer, Mark Tapley 1 IBEX Science Requirements IBEX
More informationLibration Orbit Mission Design: Applications Of Numerical And Dynamical Methods
Libration Orbit Mission Design: Applications Of Numerical And Dynamical Methods David Folta and Mark Beckman NASA - Goddard Space Flight Center Libration Point Orbits and Applications June 1-14, 22, Girona,
More informationLOTNAV. A Low-Thrust Interplanetary Navigation Tool: The Trajectory Reconstruction Module
LOTNAV A Low-Thrust Interplanetary Navigation Tool: The Trajectory Reconstruction Module Juan Luis Cano González Mission Analysis Division Deimos Space S.L. -1- The LOTNAV Tool The Low-Thrust Interplanetary
More informationHYPER Industrial Feasibility Study Final Presentation Orbit Selection
Industrial Feasibility Study Final Presentation Orbit Selection Steve Kemble Astrium Ltd. 6 March 2003 Mission Analysis Lense Thiring effect and orbit requirements Orbital environment Gravity Atmospheric
More informationLOW EARTH ORBIT CONSTELLATION DESIGN USING THE EARTH-MOON L1 POINT
LOW EARTH ORBIT CONSTELLATION DESIGN USING THE EARTH-MOON L1 POINT Naomi Chow and Erica Gralla, Princeton University James Chase, Jet Propulsion Laboratory N. J. Kasdin, + Princeton University AAS 04-248
More informationInterplanetary Trajectory design for Rosetta and Solar Orbiter
Jose Rodriguez-Canabal Memorial Interplanetary Trajectory design for Rosetta and Solar Orbiter Johannes Schoenmaekers H / Mission Analysis Section (HSO-GFA) Senior Adviser ESA / ESOC Email: johannes.schoenmaekers@esa.int
More information(2015) ISSN
Colombo, Camilla and Alessi, Elisa Maria and van der Weg, Willem Johan and Soldini, Stefania and Letizia, Francesca and Vetrisano, Massimo and Vasile, Massimiliano and Rossi, Alessandro and Landgraf, Markus
More informationFormation Flying and Rendezvous and Docking Simulator for Exploration Missions (FAMOS-V2)
Formation Flying and Rendezvous and Docking Simulator for Exploration Missions (FAMOS-V2) Galder Bengoa, F. Alonso, D. García, M. Graziano (GMV S.A.) Dr. Guillermo Ortega (ESA/ESTEC) 2nd ESA Workshop on
More informationFlight and Orbital Mechanics
Flight and Orbital Mechanics Lecture slides Challenge the future 1 Flight and Orbital Mechanics AE-104, lecture hours 1-4: Interplanetary flight Ron Noomen October 5, 01 AE104 Flight and Orbital Mechanics
More informationDISPOSAL OF LIBRATION POINT ORBITS ON A HELIOCENTRIC GRAVEYARD ORBIT: THE GAIA MISSION
DISPOSAL OF LIBRATION POINT ORBITS ON A HELIOCENTRIC GRAVEYARD ORBIT: THE GAIA MISSION Camilla Colombo (1), Francesca Letizia (), Stefania Soldini (3) and Florian Renk (4) (1)()(3) Aeronautics, Astronautics
More informationOrbit Design Marcelo Suárez. 6th Science Meeting; Seattle, WA, USA July 2010
Orbit Design Marcelo Suárez Orbit Design Requirements The following Science Requirements provided drivers for Orbit Design: Global Coverage: the entire extent (100%) of the ice-free ocean surface to at
More informationGALILEO CONSTELLATION: EVALUATION OF STATION KEEPING STRATEGIES.
GALILEO CONSTELLATION: EVALUATION OF STATION KEEPING STRATEGIES Daniel Navarro-Reyes (1), Anna Notarantonio (), Giacomo Taini (3) (1) ESA, ESTEC Keplerlaan 1 Noordwijk The Netherlands, +31 71 5658313,
More informationINTER-AGENCY SPACE DEBRIS COORDINATION COMMITTEE (IADC) SPACE DEBRIS ISSUES IN THE GEOSTATIONARY ORBIT AND THE GEOSTATIONARY TRANSFER ORBITS
INTER-AGENCY SPACE DEBRIS COORDINATION COMMITTEE (IADC) SPACE DEBRIS ISSUES IN THE GEOSTATIONARY ORBIT AND THE GEOSTATIONARY TRANSFER ORBITS Presented to: 37-th Session of the SCIENTIFIC AND TECHNICAL
More informationProton Launch System Mission Planner s Guide APPENDIX F. Proton Launch System Options and Enhancements
Proton Launch System Mission Planner s Guide APPENDIX F Proton Launch System Options and Enhancements F. PROTON LAUNCH SYSTEM OPTIONS AND ENHANCEMENTS The missions presented in the previous sections represent
More informationFigure 1. View of ALSAT-2A spacecraft
ALSAT-2A TRANSFER AND FIRST YEAR OPERATIONS M. Kameche (1), A.H. Gicquel (2), D. Joalland (3) (1) CTS/ASAL, 1 Avenue de la Palestine, BP 13, Arzew 31200 Oran, Algérie, email:mo_kameche@netcourrier.com
More informationEnd of Life Re-orbiting The Meteosat-5 Experience
End of Life Re-orbiting The Meteosat-5 Experience Milan EUMETSAT, Darmstadt, Germany This article illustrates the orbit maneuver sequence performed during Meteosat- 5 End of Life (EOL) re-orbiting operations
More informationMission analysis for potential threat scenarios: kinetic impactor
Mission analysis for potential threat scenarios: kinetic impactor Marco Castronuovo, Camilla Colombo, Pierluigi Di Lizia, Lorenzo Bolsi, Mathieu Petit, Giovanni Purpura, Marta Albano, Roberto Bertacin,
More informationRADIATION OPTIMUM SOLAR-ELECTRIC-PROPULSION TRANSFER FROM GTO TO GEO
RADIATION OPTIMUM SOLAR-ELECTRIC-PROPULSION TRANSFER FROM GTO TO GEO R. Jehn European Space Operations Centre, ESA/ESOC, Robert-Bosch-Str. 5, 64289Darmstadt, Germany, +49 6151 902714, ruediger.jehn@esa.int
More informationASTRIUM. Minimum-time problem resolution under constraints for low-thrust stage trajectory computation. Nathalie DELATTRE ASTRIUM Space Transportation
Minimum-time problem resolution under constraints for low-thrust stage trajectory computation Nathalie DELATTRE Space Transportation Page 1 Introduction Purpose : Taking into account new technology for
More informationMission analysis forms an integral
Artist s impression of ESA s Mars Sample Return orbiter vehicle. This mission presents many mission analysis challenges Mission Analysis Johannes Schoenmaekers, Rüdiger Jehn, Markus Landgraf & Michael
More informationISAS MERCURY ORBITER MISSION TRAJECTORY DESIGN STRATEGY. Hiroshi Yamakawa
ISAS MERCURY ORBITER MISSION TRAJECTORY DESIGN STRATEGY Hiroshi Yamakawa Institute of Space and Astronautical Science (ISAS) 3-1-1 Yoshinodai, Sagamihara, Kanagawa, 229-851 Japan E-mail:yamakawa@pub.isas.ac.jp
More informationFeasible Mission Designs for Solar Probe Plus to Launch in 2015, 2016, 2017, or November 19, 2008
Feasible Mission Designs for Solar Probe Plus to Launch in 2015, 2016, 2017, or 2018 2007 Solar Probe Study & Mission Requirements Trajectory study and mission design trades were conducted in the fall
More informationBINARY ASTEROID ORBIT MODIFICATION
2013 IAA PLANETARY DEFENSE CONFERENCE BEAST BINARY ASTEROID ORBIT MODIFICATION Property of GMV All rights reserved TABLE OF CONTENTS 1. Mission Concept 2. Asteroid Selection 3. Physical Principles 4. Space
More informationDesign of Orbits and Spacecraft Systems Engineering. Scott Schoneman 13 November 03
Design of Orbits and Spacecraft Systems Engineering Scott Schoneman 13 November 03 Introduction Why did satellites or spacecraft in the space run in this orbit, not in that orbit? How do we design the
More informationOverview of the Jovian Exploration Technology Reference Studies
Overview of the Jovian Exploration Technology Reference Studies The Challenge of Jovian System Exploration Peter Falkner & Alessandro Atzei Solar System Exploration Studies Section ESA/ESTEC Peter.Falkner@esa.int,
More informationLecture D30 - Orbit Transfers
J. Peraire 16.07 Dynamics Fall 004 Version 1.1 Lecture D30 - Orbit Transfers In this lecture, we will consider how to transfer from one orbit, or trajectory, to another. One of the assumptions that we
More informationPhobos-Grunt's Inexorable Trans-Mars Injection (TMI) Countdown Clock
Introduction Phobos-Grunt, Russia's sample return mission targeting the martian moon Phobos, was to have marked this nation's return to interplanetary spaceflight after a decades-long hiatus. Launched
More informationMARYLAND. The Design Process Regression Analysis Level I Design Example: UMd Exploration Initiative U N I V E R S I T Y O F.
Parametric Design The Design Process Regression Analysis Level I Design Example: UMd Exploration Initiative U N I V E R S I T Y O F MARYLAND 2004 David L. Akin - All rights reserved http://spacecraft.ssl.
More informationSupplemental Questions 12U
Supplemental Questions 12U Gravitational, Electric and Magnetic Fields Questions A satellite of mass 5.00x10² kg is in a circular orbit of radius 2r around Earth. Then it is moved to a circular orbit radius
More informationEscape Trajectories from Sun Earth Distant Retrograde Orbits
Trans. JSASS Aerospace Tech. Japan Vol. 4, No. ists30, pp. Pd_67-Pd_75, 06 Escape Trajectories from Sun Earth Distant Retrograde Orbits By Yusue OKI ) and Junichiro KAWAGUCHI ) ) Department of Aeronautics
More informationJUpiter Icy Moons Explorer (JUICE) Status report for OPAG. N. Altobelli (on behalf of O. Witasse) JUICE artist impression (Credits ESA, AOES)
JUpiter Icy Moons Explorer (JUICE) Status report for OPAG N. Altobelli (on behalf of O. Witasse) JUICE artist impression (Credits ESA, AOES) Message on behalf of the JUICE Science Working Team Congratulations
More informationdocument title/ titre du document
D O C U M E N T document title/ titre du document prepared by/préparé par ESOC reference/réference issue/édition 1 revision/révision 0 date of issue/date d édition 21 July 2010 status/état Final/Approved
More informationL eaving Earth and arriving at another planet or asteroid requires
Designing Interplanetary Transfers L eaving Earth and arriving at another planet or asteroid requires a spacecraft to implement a sequence of manoeuvres. These include changes of velocity needed to escape
More informationAstrodynamics (AERO0024)
Astrodynamics (AERO0024) L05: Orbital Maneuvers Gaëtan Kerschen Space Structures & Systems Lab (S3L) North Korea Launch Vehicle WorldView1 satellite (Google Earth). 0.5m resolution. 2 Course Outline THEMATIC
More informationOrbital Mechanics MARYLAND U N I V E R S I T Y O F. Orbital Mechanics. ENAE 483/788D - Principles of Space Systems Design
Discussion of 483/484 project organization Planetary launch and entry overview Energy and velocity in orbit Elliptical orbit parameters Orbital elements Coplanar orbital transfers Noncoplanar transfers
More informationOrbital Mechanics MARYLAND
Orbital Mechanics Energy and velocity in orbit Elliptical orbit parameters Orbital elements Coplanar orbital transfers Noncoplanar transfers Time in orbit Interplanetary trajectories Planetary launch and
More informationJUICE/Laplace Mission Summary & Status
JUICE/Laplace Mission Summary & Status C. Erd JUICE Instrument WS, Darmstadt 9/11/2011 Activities during the Reformulation Phase 1. Feasible JGO s/c as a starting point a. no re-design of s/c necessary
More informationMission Overview. EAGLE: Study Goals. EAGLE: Science Goals. Mission Architecture Overview
Mission Overview OPAG Meeting November 8 th, 2006 Ryan Anderson & Daniel Calvo EAGLE: Study Goals Develop a set of science goals for a flagship mission to Enceladus Investigate mission architectures that
More informationDESTINY + : Technology Demonstration and Exploration of Asteroid 3200 Phaethon. September 20, 2017 ISAS/JAXA
DESTINY + : Technology Demonstration and Exploration of Asteroid 3200 Phaethon September 20, 2017 ISAS/JAXA 1 DESTINY + Overview This mission is to acquire the compact deep space explorer technology, fly-by
More informationLaunch strategy for Indian lunar mission and precision injection to the Moon using genetic algorithm
Launch strategy for Indian lunar mission and precision injection to the Moon using genetic algorithm VAdimurthy, R V Ramanan, S R Tandon and C Ravikumar Aeronautics Entity, Vikram Sarabhai Space Centre,
More informationOrbital Mechanics MARYLAND U N I V E R S I T Y O F. Orbital Mechanics. ENAE 483/788D - Principles of Space Systems Design
Planetary launch and entry overview Energy and velocity in orbit Elliptical orbit parameters Orbital elements Coplanar orbital transfers Noncoplanar transfers Time in orbit Interplanetary trajectories
More informationORBIT DETERMINATION AND CONTROL FOR THE EUROPEAN STUDENT MOON ORBITER
IAC-2010-E2-3 ORBIT DETERMINATION AND CONTROL FOR THE EUROPEAN STUDENT MOON ORBITER Author Ms. Alison Gibbings, agibbing@eng.gla.ac.uk Glasgow University, Space Advanced Research Team, Glasgow, United
More informationMission Trajectory Design to a Nearby Asteroid
Mission Trajectory Design to a Nearby Asteroid A project present to The Faculty of the Department of Aerospace Engineering San Jose State University in partial fulfillment of the requirements for the degree
More informationSELENE TRANSLUNAR TRAJECTORY AND LUNAR ORBIT INJECTION
SELENE TRANSLUNAR TRAJECTORY AND LUNAR ORBIT INJECTION Yasuihiro Kawakatsu (*1) Ken Nakajima (*2), Masahiro Ogasawara (*3), Yutaka Kaneko (*1), Yoshisada Takizawa (*1) (*1) National Space Development Agency
More informationLOW-COST LUNAR COMMUNICATION AND NAVIGATION
LOW-COST LUNAR COMMUNICATION AND NAVIGATION Keric Hill, Jeffrey Parker, George H. Born, and Martin W. Lo Introduction Spacecraft in halo orbits near the Moon could relay communications for lunar missions
More informationLesson 11: Orbital Transfers II. 10/6/2016 Robin Wordsworth ES 160: Space Science and Engineering: Theory and ApplicaCons
Lesson 11: Orbital Transfers II 10/6/2016 Robin Wordsworth ES 160: Space Science and Engineering: Theory and ApplicaCons ObjecCves Introduce concept of sphere of influence Study the patched conics approach
More informationChapter 4. Integrated Algorithm for Impact Lunar Transfer Trajectories. using Pseudo state Technique
Chapter 4 Integrated Algorithm for Impact Lunar Transfer Trajectories using Pseudo state Technique Abstract A new integrated algorithm to generate the design of one-way direct transfer trajectory for moon
More informationOrbital Mechanics MARYLAND U N I V E R S I T Y O F. Orbital Mechanics. ENAE 483/788D - Principles of Space Systems Design
Lecture #05 September 15, 2015 Planetary launch and entry overview Energy and velocity in orbit Elliptical orbit parameters Orbital elements Coplanar orbital transfers Noncoplanar transfers Time in orbit
More informationMAE 180A: Spacecraft Guidance I, Summer 2009 Homework 4 Due Thursday, July 30.
MAE 180A: Spacecraft Guidance I, Summer 2009 Homework 4 Due Thursday, July 30. Guidelines: Please turn in a neat and clean homework that gives all the formulae that you have used as well as details that
More informationMassimiliano Vasile, Stefano Campagnola, Paolo Depascale, Stefano Pessina, Francesco Topputo
A Toolbox for Preliminary Massimiliano Vasile, Stefano Campagnola, Paolo Depascale, Stefano Pessina, Francesco Topputo Mission Analysis and Design PAMSIT IMAGO ATOM-C EPIC Massimiliano Vasile, Stefano
More informationThe B-Plane Interplanetary Mission Design
The B-Plane Interplanetary Mission Design Collin Bezrouk 2/11/2015 2/11/2015 1 Contents 1. Motivation for B-Plane Targeting 2. Deriving the B-Plane 3. Deriving Targetable B-Plane Elements 4. How to Target
More informationParametric Design MARYLAND. The Design Process Level I Design Example: Low-Cost Lunar Exploration U N I V E R S I T Y O F
Parametric Design The Design Process Level I Design Example: Low-Cost Lunar Exploration U N I V E R S I T Y O F MARYLAND 2005 David L. Akin - All rights reserved http://spacecraft.ssl.umd.edu Parametric
More informationThe Launch of Gorizont 45 on the First Proton K /Breeze M
The Launch of Gorizont 45 on the First Proton K / Fred D. Rosenberg, Ph.D. Space Control Conference 3 April 2001 FDR -01 1 This work is sponsored by the Air Force under Air Force Contract F19628-00-C-0002
More informationMitigation of Restrictions in Planetary Missions by using Interplanetary Parking Orbits and Aeroassist
Mitigation of Restrictions in Planetary Missions by using Interplanetary Parking Orbits and Aeroassist Naoko Ogawa, Yuya Mimasu, Kazuhisa Fujita, Hiroshi Takeuchi 3, Keita Tanaka 4, Shinichiro Narita and
More informationTRAJECTORY DESIGN OF SOLAR ORBITER
TRAJECTORY DESIGN OF SOLAR ORBITER José Manuel Sánchez Pérez ESA-ESOC HSO-GFA, Robert-Bosch-Str., Darmstadt, 293, Germany, 9--929, jose.manuel.sanchez.perez@esa.int Abstract: In the context of the ESA
More informationOnboard Maneuver Planning for the Autonomous Vision Approach Navigation and Target Identification (AVANTI) experiment within the DLR FireBird mission
Onboard Maneuver Planning for the Autonomous Vision Approach Navigation and Target Identification (AVANTI) experiment within the DLR FireBird mission G. Gaias, DLR/GSOC/Space Flight Technology Department
More informationOrbital Mechanics MARYLAND. Orbital Mechanics. ENAE 483/788D - Principles of Space Systems Design
Lecture #08 September 22, 2016 Planetary launch and entry overview Energy and velocity in orbit Elliptical orbit parameters Orbital elements Coplanar orbital transfers Noncoplanar transfers Time in orbit
More informationExpanding opportunities for lunar gravity capture
Expanding opportunities for lunar gravity capture Keita Tanaka 1, Mutsuko Morimoto 2, Michihiro Matsumoto 1, Junichiro Kawaguchi 3, 1 The University of Tokyo, Japan, 2 JSPEC/JAXA, Japan, 3 ISAS/JAXA, Japan,
More information10 Orbit and Constellation Design Selecting the Right Orbit
Orbit and Constellation Design Selecting the Right Orbit.7 Design of Interplanetary Orbits Faster Trajectories Ron Noomen, Delft University of Technology Using the recipe given in Table -9, one can compute
More informationCOUPLED OPTIMIZATION OF LAUNCHER AND ALL-ELECTRIC SATELLITE TRAJECTORIES
COUPLED OPTIMIZATION OF LAUNCHER AND ALL-ELECTRIC SATELLITE TRAJECTORIES M. Verlet (1), B. Slama (1), S. Reynaud (1), and M. Cerf (1) (1) Airbus Defence and Space, 66 Route de Verneuil, 78133 Les Mureaux,
More informationA Comparison of Low Cost Transfer Orbits from GEO to LLO for a Lunar CubeSat Mission
A Comparison of Low Cost Transfer Orbits from GEO to LLO for a Lunar CubeSat Mission A presentation for the New Trends in Astrodynamics conference Michael Reardon 1, Jun Yu 2, and Carl Brandon 3 1 PhD
More informationGRAIL Takes A Roundabout Route To Lunar Orbit
The Gravity Recovery and Interior Laboratory (GRAIL) mission departed Earth from Cape Canaveral Air Force Station Space Launch Complex 17B on 2011 September 10 at 13:08 UTC, carried by a Delta II Heavy
More informationA Regional Microsatellite Constellation with Electric Propulsion In Support of Tuscan Agriculture
Berlin, 20 th - 24 th 2015 University of Pisa 10 th IAA Symposium on Small Satellites for Earth Observation Student Conference A Regional Microsatellite Constellation with Electric Propulsion In Support
More informationSatellite Engineering
Satellite Engineering Universidad de Concepción November 2009 Gaëtan Kerschen Space Structures & Systems Lab University of Liège Satellite Engineering Universidad de Concepción November 2009 Day 3: Satellite
More informationThe Orbit Control of ERS-1 and ERS-2 for a Very Accurate Tandem Configuration
The Orbit Control of ERS-1 and ERS-2 for a Very Accurate Tandem Configuration Mats Rosengren European Space Operations Centre Robert Bosch Str 5 D64293 Darmstadt Germany Email: mrosengr@esoc.esa.de Abstract
More informationA SURVEY OF BALLISTIC TRANSFERS TO LOW LUNAR ORBIT
AAS 11-277 A SURVEY OF BALLISTIC TRANSFERS TO LOW LUNAR ORBIT Jeffrey S. Parker Rodney L. Anderson and Andrew Peterson A simple strategy is identified to generate ballistic transfers between the Earth
More informationDirect MOND/TEVES test with LISA Pathfinder
Direct MOND/TEVES test with LISA Pathfinder Christian Trenkel and Steve Kemble Astrium Ltd, Stevenage, UK Joao Magueijo and Neil Bevis Imperial College, London, UK Fabrizio io demarchi and Giuseppe Congedo
More information