Exomars 2020 – AMELIA: the EDL Science Experiment for the Entry and Descent Module of the Exomars 2020 Mission Conference Or Workshop Item
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Mars Reconnaissance Orbiter Navigation Strategy for the Exomars Schiaparelli EDM Lander Mission
Jet Propulsion Laboratory California Institute of Technology Mars Reconnaissance Orbiter Navigation Strategy for the ExoMars Schiaparelli EDM Lander Mission Premkumar R. Menon Sean V. Wagner, David C. Jefferson, Eric J. Graat, Kyong J. Lee, and William B. Schulze AAS/AIAA Astrodynamics Specialist Conference San Antonio, Texas February 5–9, 2017 AAS Paper 17-337 © 2017 California Institute of Technology. Government Sponsorship Acknowledged. Mars Reconnaissance Orbiter Project Mars Reconnaissance Orbiter (Mission, Spacecraft and PSO) The Mars Reconnaissance Orbiter mission launched in August 2005 from the Cape Canaveral Air Force Station arriving at Mars in March 2006 started science operations in November 2006. MRO has completed 10 years since launch (50,000 orbits by Mar 2017) and to date has returned nearly 300 Terabytes of data. MRO Primary Science Orbit (PSO): • Sun-synchronous orbit ascending node at 3:00 PM ± 15 minutes Local Mean Solar Time (LMST) (daylight equatorial crossing) • Periapsis is frozen about the Mars South Pole • Near-repeat ground track walk (GTW) every 17-day, 211 orbit (short-term repeat) MRO targeting cycle, exact repeat after 4602 orbits. The nominal GTW is 32.45811 km West each 211 orbit cycle (maintained with periodic maneuvers). MRO Spacecraft: • Spacecraft Bus: 3-axis stabilized ACS system; 3-meter diameter High Gain Antenna; hydrazine propulsion system • Instrument Suite: HiRISE Camera, CRISM Imaging spectrometer, Mars Climate Sounder, Mars Color Imager, Context Camera, Shallow Subsurface Radar, Electra engineering payload (among other instrument payloads) 2/07/17 MRO support of ExoMars Schiaparelli Lander Overflight Relay PRM-3 4. MRO shall have good overflight pass geometry within the first 2 Sols after landing. -
Matematikken Viser Vej Til Mars
S •Matematikken The viser vej til Mars Kim Plauborg © The Terma Group 2016 THE BEGINNING Terma has been in Space since man walked on the Moon! © The Terma Group 2016 FROM ESRO TO EXOMARS Terma powered the first comet landing ever! BREAKING NEWS The mission ends today when the Rosetta satellite will set down on the surface In 2014 the Rosetta satellite deployed the small lander Philae, which landed on the cometof 67P morethe than 10 comet years after Rosetta was launched. © The Terma Group 2016 FROM ESRO TO EXOMARS Rosetta Mars Express Technology Venus Express evolution and Galileo enhancement Small GEO BepiColombo ExoMars © The Terma Group 2016 Why go Mars? Getting to and landing on Mars is difficult ! © The Terma Group 2016 THE EXOMARS PROGRAMME Two ESA missions to Mars in cooperation with Roscosmos with the main objective to search for evidence of life 2016 Mission Trace Gas Orbiter Schiaparelli 2020 Mission Rover Surface platform © The Terma Group 2016 EXOMARS 2016 14th March 2016 Launched from Baikonur cosmodrome, Kazakhstan © The Terma Group 2016 EXOMARS 2016 16th October 2016 Separation of Schiaparelli from the orbiter © The Terma Group 2016 SCHIAPARELLI Schiaparelli (EDM) - an entry, descent and landing demonstrator module © The Terma Group 2016 EXOMARS 2016 19th October 2016 Landing of Schiaparelli the surface of Mars © The Terma Group 2016 EXOMARS 2016 19th October 2016 Landing of Schiaparelli the surface of Mars © The Terma Group 2016 EXOMARS 2020 © The Terma Group 2016 TERMA AND EXOMARS Terma deliveries to the ExoMars 2016 mission • Remote Terminal Power Unit for Schiaparelli • Mission Control System • Spacecraft Simulator • Support for the Launch and Early Orbit Phase © The Terma Group 2016 ExoMars RTPU The RTPU is a central unit in the Schiaparelli lander. -
Lessons from Insight for Future Planetary Seismology
Open Archive Toulouse Archive Ouverte (OATAO ) OATAO is an open access repository that collects the wor of some Toulouse researchers and ma es it freely available over the web where possible. This is a publisher's version published in: https://oatao.univ-toulouse.fr/26931 Official URL : https://doi.org/10.1029/2019JE006353 To cite this version : Panning, M. P. and Pike, W. T. and Lognonné, Philippe,... [et al.]On͈Deck Seismology: Lessons from InSight for Future Planetary Seismology. (2020) Journal of Geophysical Research: Planets, 125 (4). ISSN 2169-9097 Any correspondence concerning this service should be sent to the repository administrator: [email protected] RESEARCH ARTICLE On-Deck Seismology: Lessons from InSight for Future 10.1029/2019JE006353 Planetary Seismology Special Section: 1 2 3 1 4 5 InSightatMars M. P. Panning , W. T. Pike , P. Lognonné , W. B. Banerdt , N. Murdoch , D. Banfield , C. Charalambous2 , S. Kedar1, R. D. Lorenz6 , A. G. Marusiak7 , J. B. McClean2,8 ,C. 1 9 2 10 Key Points: Nunn , S. C. Stähler ,A.E.Stott , and T. Warren • Based on InSight recordings, 1 2 atmospheric noise is amplified for Jet Propulsion Laboratory, California Institute of Technology, Pasadena, CA, USA, Department of Electrical and seismic sensors on deck, consistent Electronic Engineering, Imperial College London, London, UK, 3Planetology and Space Science Team, Université de with Viking observations Paris, Institut de Physique du Globe, CNRS, Paris, France, 4Department of Electronics, Optronics and Signal Processing, • -
Exomars 2016
University of California, Davis Department of Mechanical and Aerospace Engineering ExoMars 2016 Critical Design Review Final Report David Bartolo Shazib Elahi Aaron Tun Junyi Zhang EAE 198: Intro to Space Vehicles Professor S. K. Robinson 3/23/2019 Contents 1. Introduction 4 1.1 ExoMars 2016 Overview 4 1.1.1 ExoMars Program Vision 4 1.1.2 Timeline of Events 6 1.1.3 Spacecraft and Launch Vehicle Specifications 6 1.2 ExoMars 2016 Mission Stakeholders and Requirements 7 1.3 Mission Objectives 7 1.3.1 Trace Gas Orbiter 7 1.3.2 Schiaparelli EDM 7 1.4 Concept of Operations 8 1.4.1 Space Segment 8 1.4.2 Ground Segment 9 1.5 Subsystems 10 1.5.1 Trace Gas Orbiter 10 1.5.2 Schiaparelli EDM 11 2. Background 12 2.1 Similar Spacecraft 13 2.1.1 Trace Gas Orbiter 13 2.1.2 Schiaparelli EDM 13 2.2 ExoMars 2016 Innovations 13 3. Modifications to Design 14 3.1 Functional Hierarchy Diagram, Analysis/Modification Requirements 14 3.2 Rationale for Chosen Requirements, Potential Benefits and Downsides 15 3.3 Modified Subsystem Requirements 16 4. Analyses 17 4.1 Major Analysis: Power 17 4.1.1 Goals of Analysis 17 4.1.2 Assumptions, Principles, and Methods 17 4.1.2.1 Power Generation and Sources 17 4.1.2.3 Power Regulation and Control 18 4.1.2.4 Power Regulators 19 4.1.2.5 Power Distribution and Heat Dissipation 19 4.1.3 Math, Models, and Code 19 4.1.3.1 Power Generation and Sources 19 2 4.1.3.2 Power Energy Storage 21 4.1.3.3 Power Regulation and Control 21 4.1.3.5 Power Distribution and Heat Dissipation 22 4.1.4 Results 22 4.1.5 Discussion of Importance of Results 26 4.2 Minor Analysis I: Deployable Array Design 26 4.2.1 Goals of Analysis 26 4.2.2 Assumptions, Principles, and Methods 26 4.2.3 Math, Models, and Code 29 4.2.4 Results 32 4.2.5 Discussion of Importance of Results 35 4.3 Minor Analysis II: Influence of Adding Solar Array on Lander 36 4.3.1 Goals of Analysis 36 4.3.2 Assumptions, Principles, and Methods 37 4.3.3 Math, Models, and Code 38 4.3.4 Results 42 4.3.5 Discussion 43 5. -
EDL – Lessons Learned and Recommendations
."#!(*"# 0 1(%"##" !)"#!(*"#* 0 1"!#"("#"#(-$" ."!##("""*#!#$*#( "" !#!#0 1%"#"! /!##"*!###"#" #"#!$#!##!("""-"!"##&!%%!%&# $!!# %"##"*!%#'##(#!"##"#!$$# /25-!&""$!)# %"##!""*&""#!$#$! !$# $##"##%#(# ! "#"-! *#"!,021 ""# !"$!+031 !" )!%+041 #!( !"!# #$!"+051 # #$! !%#-" $##"!#""#$#$! %"##"#!#(- IPPW Enabled International Collaborations in EDL – Lessons Learned and Recommendations: Ethiraj Venkatapathy1, Chief Technologist, Entry Systems and Technology Division, NASA ARC, 2 Ali Gülhan , Department Head, Supersonic and Hypersonic Technologies Department, DLR, Cologne, and Michelle Munk3, Principal Technologist, EDL, Space Technology Mission Directorate, NASA. 1 NASA Ames Research Center, Moffett Field, CA [email protected]. 2 Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), German Aerospace Center, [email protected] 3 NASA Langley Research Center, Hampron, VA. [email protected] Abstract of the Proposed Talk: One of the goals of IPPW has been to bring about international collaboration. Establishing collaboration, especially in the area of EDL, can present numerous frustrating challenges. IPPW presents opportunities to present advances in various technology areas. It allows for opportunity for general discussion. Evaluating collaboration potential requires open dialogue as to the needs of the parties and what critical capabilities each party possesses. Understanding opportunities for collaboration as well as the rules and regulations that govern collaboration are essential. The authors of this proposed talk have explored and established collaboration in multiple areas of interest to IPPW community. The authors will present examples that illustrate the motivations for the partnership, our common goals, and the unique capabilities of each party. The first example involves earth entry of a large asteroid and break-up. NASA Ames is leading an effort for the agency to assess and estimate the threat posed by large asteroids under the Asteroid Threat Assessment Project (ATAP). -
Sanjay Limaye US Lead-Investigator Ludmila Zasova Russian Lead-Investigator Steering Committee K
Answer to the Call for a Medium-size mission opportunity in ESA’s Science Programme for a launch in 2022 (Cosmic Vision 2015-2025) EuropEan VEnus ExplorEr An in-situ mission to Venus Eric chassEfièrE EVE Principal Investigator IDES, Univ. Paris-Sud Orsay & CNRS Universite Paris-Sud, Orsay colin Wilson Co-Principal Investigator Dept Atm. Ocean. Planet. Phys. Oxford University, Oxford Takeshi imamura Japanese Lead-Investigator sanjay Limaye US Lead-Investigator LudmiLa Zasova Russian Lead-Investigator Steering Committee K. Aplin (UK) S. Lebonnois (France) K. Baines (USA) J. Leitner (Austria) T. Balint (USA) S. Limaye (USA) J. Blamont (France) J. Lopez-Moreno (Spain) E. Chassefière(F rance) B. Marty (France) C. Cochrane (UK) M. Moreira (France) Cs. Ferencz (Hungary) S. Pogrebenko (The Neth.) F. Ferri (Italy) A. Rodin (Russia) M. Gerasimov (Russia) J. Whiteway (Canada) T. Imamura (Japan) C. Wilson (UK) O. Korablev (Russia) L. Zasova (Russia) Sanjay Limaye Ludmilla Zasova Eric Chassefière Takeshi Imamura Colin Wilson University of IKI IDES ISAS/JAXA University of Oxford Wisconsin-Madison Laboratory of Planetary Space Science and Spectroscopy Univ. Paris-Sud Orsay & Engineering Center Space Research Institute CNRS 3-1-1, Yoshinodai, 1225 West Dayton Street Russian Academy of Sciences Universite Paris-Sud, Bat. 504. Sagamihara Dept of Physics Madison, Wisconsin, Profsoyusnaya 84/32 91405 ORSAY Cedex Kanagawa 229-8510 Parks Road 53706, USA Moscow 117997, Russia FRANCE Japan Oxford OX1 3PU Tel +1 608 262 9541 Tel +7-495-333-3466 Tel 33 1 69 15 67 48 Tel +81-42-759-8179 Tel 44 (0)1-865-272-086 Fax +1 608 235 4302 Fax +7-495-333-4455 Fax 33 1 69 15 49 11 Fax +81-42-759-8575 Fax 44 (0)1-865-272-923 [email protected] [email protected] [email protected] [email protected] [email protected] European Venus Explorer – Cosmic Vision 2015 – 2025 List of EVE Co-Investigators NAME AFFILIATION NAME AFFILIATION NAME AFFILIATION AUSTRIA Migliorini, A. -
PSS Mars Oct 08
Planetary Sciences Subcommittee October 2-3, 2008 Doug McCuistion Director, Mars Exploration Program 2 Memorable Scenes Phoenix Meteorology is Changing from Phoenix Spacecraft thruster expose water-ice in permafrost SSI camera images water- ice particles clouds and Top: Robotic Arm delivers their movement soil+ice dug from trench to the Thermal Evolved Gas Analyzer (TEGA) Bottom: TEGA CELL #0 after receiving ice-bearing sample Phoenix images early morning water- Dust Devil frost. Lasts longer every morning as winter approaches Robotic Arm digs trench and discovers water ice. SSI camera documents H2O SSI camera images multiple sublimation. dust devils TEGA’s mass spectrometer confirms presence of water- ice on Mars. 3 4 Phoenix Meteorology is Changing A White Christmas on Mars? Atmospheric pressure and temperature data have been recorded at the Phoenix landing site every Virga, in the 2 seconds since landing. from of water- snow, has been detected in the atmosphere, getting nearer Dust cloud to the ground approaching daily. Morning wind is up to about 9 mph; enough to rattle the solar arrays but not to damage the spacecraft. 5 6 The End is in Sight Available power (measurement based) WCL Cells Utilized power (modeled) Command Moratorium Command a Conjunction MECA’s Wet Chemistry Lab (WCL) MECA’s Optical Microscope: highest resolution (4 microns/pixel) b discovers perchlorates in soil! optical images delivered from any planetary surface other than earth c AFM Tip Perchlorates: Powerful, but d stable oxidant. Very hydroscopic. Survival heater -
GEP-Exomars: a Geophysics And
Lunar and Planetary Science XXXVII (2006) 1982.pdf GEP-ExoMars: a Geophysics and Environment observatory on Mars : Philippe Lognonné1, Tilman Spohn2, David Mimoun1,*, Stephan Ulamec3, Jens Biele3, the ML2SP team and the Aurora Environment team 1IPGP, St. Maur des Fossés, France 2DLR, Institute for Planetary Research, D-12489 Berlin, Germany 3DLR, Institute for Space Simulation, D-51170 Köln, Germany , *E-mail: [email protected] Mass / average Network Instrument Heritage Description Comments kg power, W science Scientific objective: Seismic suite: 2 VBB oblique seismometers Needs soil contact, plus one Short period horizontal MEMS wind and sun SEIS Netlander (Phase B) 1,615 0,28 (Micro-Electro Mechanical System) sensor x protection and The goal of the Long-Lived Geoscience Observatory completing the trihedron. Target sensitivity < decoupling from Meteo suite: wind, temperature, pressure, partly to be replaced humidity, OD, UV spectra, dust impact. by similar Pasteur ATM Beagle-2 (flown) 0,685 0,095 x on Mars, GEP (Geophysics Package) is to initiate the Modes: low/nominal/campaign/dust devil instruments, see rates below Atmospheric electricity probe to measure setup of a permanent network of fixed stations on the electric conductivity, quasi DC electric field AEP Netlander (Phase B) 0,147 0,105 CORE (up to 300 V/m), ELF/VLF radio-electric x emissions (10 Hz to 4 kHz) planet, with the objective to operate for several years. Heat flow and physical properties package. Deployed by a mole up to 5 m deep in Martian regolith: TEM, a thermal These stations will monitor with high resolution the HP3 Beagle-2 (flown) 1,195 0,003 measurement suite (thermal conductivity, heat capacity, thermal gradient [heat flux]); DACTIL, a set of accelerometers (orientation, seismic activity and the rotation of the planet, the depth, so Tri-axial vector magnetic field sensor Champ, Astrid-2 satellites including t and attitude sensors. -
Mars Sample Return (4+1 Architecture)
Status of ESA’s Mars Activities MEPAG meeting Silver Spring, 2 March 2016 • Rolf de Groot, Head of Exploration Coordination Office, ESA Science Directorate • Hakan Svedhem, ExoMars 2016 Project Scientist, ESA Science Directorate • Bernardo Patti, Head of ISS Programme and Exploration Department, ESA Human Spaceflight and Robotic Exploration Directorate • Sanjay Vijendran, Future Mars Projects, ESA Human Spaceflight and Robotic Exploration Directorate NOTE ADDED BY JPL WEBMASTER: This content has not been approved or adopted by, NASA, JPL, or the California Institute of Technology. This document is being made available for information purposes only, and any views and opinions expressed herein do not necessarily state or reflect those of NASA, JPL, or the California Institute of Technology. 1 Mars Exploration at ESA TGO and EDM ExoMars Mars Express MSR elements Rover + Platform Mission studies 2 2003 2030+ Mars Express Status: Launched in 2003 Spacecraft and payload status: very good Fuel and batteries estimates OK for ≥ 2021 Mission extension until end of 2018 Recent events and activities Coordinated measurements with the NASA MAVEN mission. Scientific objective: study of the plasma environment and atmospheric escape 12 March 2015: Close Phobos flyby (61 km from center) 14 June 2015: Mars Solar Conjunction 14 January 2016 – Close Phobos flyby (52 km) October 2016: Mars Express relays data from the ExoMars entry and descent module 3 ExoMars Programme in cooperation with Roscosmos: ESA’s flagship mission in Robotic Exploration -
CONCEPTS and APPROACHES for MARS EXPLORATION Lunar and Planetary Institute, Houston, TX July 18–20, 2000 Using the Handtool Of
CONCEPTS AND APPROACHES FOR MARS EXPLORATION Lunar and Planetary Institute, Houston, TX July 18–20, 2000 Using the handtool of the Reader, click on the title to view a particular abstract that you’re interested in. (Abstracts are listed alphabetically by first author. Abstract numbers are listed in brackets and bold at the end of each title.) Phoning Home from Mars in 2025 [6212] J. Adams Proposed Science Requirements and Acquisition Priorities for the First Mars Sample Return [6237] C. B. Agee, D. D. Bogard, D. S. Draper, J. H. Jones, C. Meyer Jr., and D. W. Mittlefehldt Clean and Cold Sample Curation [6197] C. C. Allen, C. B. Agee, R. Beer, and B. L. Cooper IPSE: Italian Package for Scientific Experiments [6084] F. Angrilli, E. Flamini, and S. Espinasse Vision 2020: A Proposed Program of Mars Exploration [6019] R. E. Arvidson FIDO Field Trials in Preparation for Mars Rover Exploration and Discovery and Sample Return Missions [6018] R. E. Arvidson, E. T. Baumgartner, P. Schenker, and S. W. Squyres MOD: An Instrument for the 2005 Mars Explorer Program HEDS Payload [6050] J. L. Bada, D. L. Blaney, F. J. Grunthaner, G. D. McDonald, C. R. Webster, M. Duke, R. A. Mathies, C. P. McKay, D. A. Paige, S. K. Ride, and M. Wadhwa A Network Mission: Completing the Scientific Foundation for the Exploration of Mars [6087] W. B. Banerdt “Following the Water” on Mars: Where Is It, How Much Is There, and How Can We Access It? [6013] N. G. Barlow Strategic Planning for Exploration of the Martian Subsurface [6233] D. -
Detection and Characterization of Martian Volatile-Rich Reservoirs: the Netlander Approach
Concepts and Approaches for Mars Exploration 6125.pdf DETECTION AND CHARACTERIZATION OF MARTIAN VOLATILE-RICH RESERVOIRS: THE NETLANDER APPROACH. F. Costard1, J.J. Berthelier2, and the GPR team, G. Musmann3, M. Menvielle2, and the MAGNET team, P. Lognonné4, D. Giardini5, B. Banerdt6, and the NL-SEIS team, A-M Harri7, F. Forget8, and the ATMIS team. 1UMR 8616, CNRS, Orsay, France, [email protected], 2C.E.T.P., UMR 8639, Saint-Maur, France, 3TUBS-IMG, Braunschweig, Germany, 4IPGP, Saint Maur, France, 5ETH, Zurich, Switzerland, 6JPL, Pasadena, USA, 7FMI, Helsinki, Finland, 8 LMD, Paris 6, Jussieu, France, Introduction: Geological and theoretical modeling do them has its own advantages and limitations and the choice indicate that, most probably, a significant part of the vola- is mostly guided by the range of depths to be explored, the tiles present in the past is presently stocked within the needed spatial resolution and the horizontal extent to be Martian subsurface as ground ice, and as clay minerals covered. We therefore propose to fly on each of the 4 (water constitution). The detection of liquid water is of landers of the NETLANDER mission a set of geophysical in- prime interest and should have deep implications in the struments to explore the first few kilometers of the subsur- understanding of the Martian hydrological cycle and also in face with, as major objectives, the detection of possible exobiology. In the frame of the 2005 joint CNES-NASA water rich layers and the characterization of the main fea- mission to Mars, a set of 4 NETLANDERs developed by an tures of the geological structures of the superficial planetary European consortium is expected to be launched between crust. -
The Mars Astrobiology Explorer-Cacher (MAX-C): a Potential Rover Mission for 2018
ASTROBIOLOGY Volume 10, Number 2, 2010 News & Views ª Mary Ann Liebert, Inc. DOI: 10.1089=ast.2010.0462 The Mars Astrobiology Explorer-Cacher (MAX-C): A Potential Rover Mission for 2018 Final Report of the Mars Mid-Range Rover Science Analysis Group (MRR-SAG) October 14, 2009 Table of Contents 1. Executive Summary 127 2. Introduction 129 3. Scientific Priorities for a Possible Late-Decade Rover Mission 130 4. Development of a Spectrum of Possible Mission Concepts 131 5. Evaluation, Prioritization of Candidate Mission Concepts 132 6. Strategy to Achieve Primary In Situ Objectives 136 7. Relationship to a Potential Sample Return Campaign 141 8. Consensus Mission Vision 146 9. Considerations Related to Landing Site Selection 147 10. Some Engineering Considerations Related to the Consensus Mission Vision 152 11. Acknowledgments 156 12. Abbreviations 156 13. References 156 1. Executive Summary use the Mars Science Laboratory (MSL) sky-crane landing system and include a single solar-powered rover. The mis- his report documents the work of the Mid-Range Ro- sion would also have a targeting accuracy of *7km Tver Science Analysis Group (MRR-SAG), which was (semimajor axis landing ellipse), a mobility range of at least assigned to formulate a concept for a potential rover mission 10 km, and a lifetime on the martian surface of at least 1 that could be launched to Mars in 2018. Based on pro- Earth year. An additional key consideration, given recently grammatic and engineering considerations as of April 2009, declining budgets and cost growth issues with MSL, is that our deliberations assumed that the potential mission would the proposed rover must have lower cost and cost risk than Members: Lisa M.