Two Rovers to the Same Site on Mars, 2018: Possibilities for Cooperative Science
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Mars Science Laboratory Entry Capsule Aerothermodynamics and Thermal Protection System
Mars Science Laboratory Entry Capsule Aerothermodynamics and Thermal Protection System Karl T. Edquist ([email protected], 757-864-4566) Brian R. Hollis ([email protected], 757-864-5247) NASA Langley Research Center, Hampton, VA 23681 Artem A. Dyakonov ([email protected], 757-864-4121) National Institute of Aerospace, Hampton, VA 23666 Bernard Laub ([email protected], 650-604-5017) Michael J. Wright ([email protected], 650-604-4210) NASA Ames Research Center, Moffett Field, CA 94035 Tomasso P. Rivellini ([email protected], 818-354-5919) Eric M. Slimko ([email protected], 818-354-5940) Jet Propulsion Laboratory, Pasadena, CA 91109 William H. Willcockson ([email protected], 303-977-5094) Lockheed Martin Space Systems Company, Littleton, CO 80125 Abstract—The Mars Science Laboratory (MSL) spacecraft TABLE OF CONTENTS is being designed to carry a large rover (> 800 kg) to the 1. INTRODUCTION ..................................................... 1 surface of Mars using a blunt-body entry capsule as the 2. COMPUTATIONAL RESULTS ................................. 2 primary decelerator. The spacecraft is being designed for 3. EXPERIMENTAL RESULTS .................................... 5 launch in 2009 and arrival at Mars in 2010. The 4. TPS TESTING AND MODEL DEVELOPMENT.......... 7 combination of large mass and diameter with non-zero 5. SUMMARY ........................................................... 11 angle-of-attack for MSL will result in unprecedented REFERENCES........................................................... 11 convective heating environments caused by turbulence prior BIOGRAPHY ............................................................ 12 to peak heating. Navier-Stokes computations predict a large turbulent heating augmentation for which there are no supporting flight data1 and little ground data for validation. -
Rtg Impact Response to Hard Landing During Mars Environmental Survey (Mesur) Mission
RTG IMPACT RESPONSE TO HARD LANDING DURING MARS ENVIRONMENTAL SURVEY (MESUR) MISSION A. Schock M. Mukunda Space ABSTRACT Since the simultaneous operation of large number of landers over a long period of time is required, the landers The National Aeronautics and Space Administration must be capable of long life. They must be simple so that (NASA) is studying a seven-year robotic mission (MESUR, a large number can be sent at affordable cost, and yet Mars Environmental Survey) for the seismic, meteorological, rugged and robust In order to survive a wide range of and geochemical exploration of the Martian surface by means landing and environmental conditions, of a network of -16 small, inexpensive landers spread from pole to pole. To permit operation at high Martian latitudes, NASA has basellned the use of Radioisotope NASA has tentatively decided to power the landers with small Thermoelectric Generators (RTGs) to power the probe, RTGs (Radioisotope Thermoelectric Generators). To support lander, and scientific Instruments. Considerations favoring the NASA mission study, the Department of Energy's Office of the use of RTGs are their applicability at both low and high Special Applications commissioned Fairchild to perform Martian latitudes, their ability to operate during and after specialized RTG design studies. Those studies indicated that Martian sandstorms, and their ability to withstand Martian the cost and complexity of the mission could be significantly ground impacts at high velocities and g-loads. reduced if the RTGs had sufficient impact resistance to survive ground impact of the landers without retrorockets. High Impact resistance of the RTGs can be of critical Fairchild designs of RTGs configured for high impact importance In reducing the complexity and cost of the resistance were reported previously. -
EJSM Origins White Document Recommendations by the Origins Working Group for EJSM Mission – JGO and JEO Spacecrafts
EJSM ORIGINS WORKING GROUP EJSM Origins White Document Recommendations by the Origins Working Group for EJSM Mission – JGO and JEO spacecrafts A. Coradini, D. Gautier, T. Guillot, G. Schubert, B. Moore, D. Turrini and H. J. Waite Document Type: Scientific Report Status: Final Version Revision: 4 Issued on: 1 April 2010 Edited by: Angioletta Coradini and Diego Turrini EJSM Origins White Document EJSM Origins White Document A. Coradini, D. Gautier, T. Guillot, B. Moore, G. Schubert, D. Turrini and H. Waite In the ESA Cosmic Vision 2015-2025 program the investigation of the conditions for planetary formation and that of the evolution of the Solar System were among the leading themes. These two themes, in fact, are strictly interlinked, since a clear vision of the origins of the Solar System cannot be achieved if we cannot discern those features which are due to the secular evolution from those which are primordial legacies of the formation time. In the context of the EJSM/Laplace proposal for a mission to Jupiter and the Jovian system, the Origins working group tried to identify the measurements to be performed in the Jovian system that could hold clues to unveil the formation histories of Jupiter and the Solar System. As we anticipated, part of the aspects to be investigated is entwined with the study of the evolution of the Solar and Jovian systems. The identified measures and their scientific domains can be divided into three categories, which will be described in the next sessions. Jupiter and the origins of giant planets As concerns the origin of Jupiter, the main interest of the EJSM mission lies in the investigation of Jupiter's composition and internal structure. -
The JIRAM (Jovian Infrared Auroral Mapper) Experiment
Lunar and Planetary Science XXXVII (2006) 1564.pdf The JIRAM (Jovian InfraRed Auroral Mapper) Experiment. A. Coradini1 , A. Adriani1, G. Filacchione2, J.Lunine1,3, G. Magni2 , M. Cosi4 and L. Tommasi4, 1 INAF-IFSI, Via Fosso del Cavaliere, 100, Rome, Italy, [email protected], 2INAF-IASF, Via Fosso del Cavaliere, 100, 00133, Rome, Italy, 3Lunar and Pla- netary Lab, University of Arizona, Tucson, AZ, USA, 4 Selex-Galileo Avionica, Via Albert Einstein 35, 50013 Campi Bisenzio (FI), Italy. + Introduction: The atmosphere of Jupiter requires aurora, the H3 is optimal for study. This molecule is multiple techniques at a variety of wavelengths. The formed at the base of the exosphere through the reac- + + present Juno payload is well-suited to a study of the tion H2 + H2 → H3 + H. The main roto-vibrational magnetic field and interior structure of Jupiter, as well band is around 4 µm and it is composed of more than as its plasma environment, but it will be strongly im- 200 possible transitions in the range 3.0 to 4.5 µm [1]. + proved by adding the capability to (a) image and make The H3 auroral spectrum was observed by Cassini spectra with high contrast of the Jovian aurora and (b) VIMS from a large distance in 2000, at much lower explore the region between roughly 1-10 bars where spatial resolution and signal-to-noise than that poten- water—Jupiter’s principal condensable because of the tially available from JIRAM. Figure 1 shows the capa- relatively high interior abundance of oxygen and ap- bility of imaging spectrometers to obtain excellent data propriate conditions in the 1-10 bar region—forms on emission features from which time-variability and clouds and aids energy transport by moist convection. -
Sojourner on Mars and Lessons Learned for Future Planetary Missions
981695 Sojourneron M arsand Lessons Learned forFuturePlanetary Rovers Brian W ilcox and Tam Nguyen NASA's JetPropulsion Laboratory C opyright© 1997 SocietyofAutom otive Engineers,Inc. ABSTRACT The sitelocations w ere designated by a hum an operator using engineering datacollected during previous On July 4, 1997, the M arsPathfinder spacecraft traversals and end-of-solstereo im ages captured by the successfullylanded on M arsinthe Ares Vallislanding lander IMP (Im ager for M arsPathfinder) cam eras. site and deployed an 11.5-kilogram m icrorover nam ed During the traversalsthe rover autonom ouslyavoided Sojourner.Thismicrorover accom plished itsprimary rock,drop-off,and slope hazards. Itchanged its course mission objectives inthe first 7 days, and continued to toavoidthese hazards and turned back tow ardits goals operatefora totalof83 sols(1 sol= M ars day = 1 Earth w henever the hazards w erenolonger inits w ay. The day + ~24 m ins)untilthe landerlostcom m unication w ith rover used "dead reckoning" counting w heel turns and Earth, probably due tolander batteryfailure. The using on-boardrate sensorsestimate position. Although microrover navigated to m any sites surrounding the the rover telem etryrecorded itsresponses to hum an lander, and conducted various science and technology driver com m ands in detail,the vehicle'sactualpositions experim entsusing itson-boardinstrum ents. were not know n untilexamination of the lander stereo im ages at the end of the sol.Acollection of stereo Inthis paper,the rover navigation perform ance is im ages containing rover tracks allow s reconstruction of analyzed on the basisofreceived rovertelem etry, rover the rover physicaltraversalpaththoughoutthe m ission. uplink com m ands and stereo im ages captured by the Since the primary purpose for a robotic vehicleon lander cam eras. -
Scientific Exploration of Mars
Chapter 5 Scientific Exploration of Mars UNDERSTANDING MARS successfully inserted Mariner 9 into an orbit about Mars8 on November 13, 1971. It was the The planets have fascinated humankind ever first spacecraft to orbit another planet (box 5-A). since observers first recognized that they had For the first 2 months of the spacecraft’s stay in characteristic motions different from the stars. Mars’ orbit, the most severe Martian dust storms Astronomers in the ancient Mediterranean called ever recorded obscured Mars surface features. them the wanderers because they appear to wan- After the storms subsided and the atmosphere der among the background of the stars. Because cleared up, Mariner 9 was able to map the entire of its reddish color as seen by the naked eye, Mars Martian surface with a surface resolution of 1 9 drew attention. It has been the subject of scientif- kilometer. ic and fictiona13 interest for centuries.4 In recent Images from Mariner 9 revealed surface fea- years, planetary scientists have developed in- tures far beyond what investigators had expected creased interest in Mars, because Mars is the from the earlier flybys. The earlier spacecraft had most Earthlike of the planets. “The study of Mars by chance photographed the heavily cratered is [therefore] an essential basis for our under- southern hemisphere of the planet, which looks standing of the evolution of the Earth and the more like the Moon than like Earth. These first inner solar system.”5 closeup images of Mars gave scientists the false Planetary exploration has been one of the Na- impression that Mars was a geologically “dead” tional Aeronautics and Space Administration’s planet, in which asteroid impacts provided the (NASA) primary goals ever since the U.S. -
Abstract - MESUR Pathfinder Mission Operations Concepts $
.$’ Abstract - MESUR Pathfinder Mission Operations Concepts $. The Mars Environmental Survey (MESUR) Pathfinder Project plans a December 1996 launch of a single spacecraft. The 7-month cruise includes up to four trajectory correction maneuvers (TCMS) and two checkouts of the complete flight system, one just after launch and one just before arrival at Mars. After jettisoning a cruise stage, an entry body containing a lander and microrover will directly enter the Mars atmosphere and parachute to a hard landing near the sub-solar latitude of 15 degrees North in July 1997. Primary surface operations last for 30 days, As a Discovery mission, MESUR Pathfinder costs are capped. Cost estimates for Pathfinder ground systems development and operations are not only lower in absolute dollars, but also are a lower percentage of total project costs than in past planetary missions. Operations teams will be smaller and fewer than typical flight projects. All experiment functions, including rover technology experiments, are collected in one Experiment Team. All engineering functions (exclusive of multimission services) are collected into a single Engineering Team. Operations with two small teams is made possible by the following characteristics: Acceptance of more risk as a Class C mission. Rover operations using simple high-level behavior commands. A simple spin-stabilized flight system. Telemetry collection of engineering and experiment data packets by demand into solid state memory. ● Direct-to-Earth telemetry driven only by downlink data rate and independent of collection rate. Prioritized packet downlink determined by ground command parameters. Onboard management of computer memory. No complex navigation data types. No cruise science and limited surface experiments. -
The Origins of the Discovery Program, 1989-1993
Space Policy 30 (2014) 5e12 Contents lists available at ScienceDirect Space Policy journal homepage: www.elsevier.com/locate/spacepol Transforming solar system exploration: The origins of the Discovery Program, 1989e1993 Michael J. Neufeld National Air and Space Museum, Smithsonian Institution, United States article info abstract Article history: The Discovery Program is a rarity in the history of NASA solar system exploration: a reform program that Received 18 October 2013 has survived and continued to be influential. This article examines its emergence between 1989 and Accepted 18 October 2013 1993, largely as the result of the intervention of two people: Stamatios “Tom” Krimigis of the Johns Available online 19 April 2014 Hopkins University Applied Physics Laboratory (APL), and Wesley Huntress of NASA, who was Division Director of Solar System Exploration 1990e92 and the Associate Administrator for Space Science 1992 Keywords: e98. Krimigis drew on his leadership experience in the space physics community and his knowledge of Space history its Explorer program to propose that it was possible to create new missions to the inner solar system for a NASA Space programme organization fraction of the existing costs. He continued to push that idea for the next two years, but it took the influence of Huntress at NASA Headquarters to push it on to the agenda. Huntress explicitly decided to use APL to force change on the Jet Propulsion Laboratory and the planetary science community. He succeeded in moving the JPL Mars Pathfinder and APL Near Earth Asteroid Rendezvous (NEAR) mission proposals forward as the opening missions for Discovery. But it took Krimigis’s political skill and access to Sen. -
45. Space Robots and Systems
1031 Space45. Space Robots Robots and Systems Kazuya Yoshida, Brian Wilcox In the space community, any unmanned spacecraft can be several tens of minutes, or even hours can be called a robotic spacecraft. However, space for planetary missions. Telerobotics technology is robots are considered to be more capable devices therefore an indispensable ingredient in space that can facilitate manipulation, assembling, robotics, and the introduction of autonomy is or servicing functions in orbit as assistants to a reasonable consequence. Extreme environments astronauts, or to extend the areas and abilities of – In addition to the microgravity environment that exploration on remote planets as surrogates for affects the manipulator dynamics or the natural human explorers. and rough terrain that affects surface mobility, In this chapter, a concise digest of the histori- there are a number of issues related to extreme cal overview and technical advances of two distinct space environments that are challenging and must Part F types of space robotic systems, orbital robots and be solved in order to enable practical engineering surface robots, is provided. In particular, Sect. 45.1 applications. Such issues include extremely high or describes orbital robots, and Sect. 45.2 describes low temperatures, high vacuum or high pressure, 45 surface robots. In Sect. 45.3 , the mathematical corrosive atmospheres, ionizing radiation, and modeling of the dynamics and control using ref- very fine dust. erence equations are discussed. Finally, advanced topics for future space exploration missions are 45.1 Historical Developments and Advances addressed in Sect. 45.4 . of Orbital Robotic Systems ..................... 1032 Key issues in space robots and systems are 45.1.1 Space Shuttle Remote Manipulator characterized as follows. -
Scott Hubbard Papers SC1286
http://oac.cdlib.org/findaid/ark:/13030/c89c73tr Online items available Guide to the Scott Hubbard Papers SC1286 Jenny Johnson & Presley Hubschmitt Department of Special Collections and University Archives October 2016 Green Library 557 Escondido Mall Stanford 94305-6064 [email protected] URL: http://library.stanford.edu/spc Note This encoded finding aid is compliant with Stanford EAD Best Practice Guidelines, Version 1.0. Guide to the Scott Hubbard SC1286 1 Papers SC1286 Language of Material: English Contributing Institution: Department of Special Collections and University Archives Title: Scott Hubbard Papers creator: Hubbard, Scott, 1948- Identifier/Call Number: SC1286 Physical Description: 111 Linear Feet Physical Description: 197 gigabyte(s) Date (inclusive): 1972-2016 Language of Material: English Special Collections and University Archives materials are stored offsite and must be paged 48 hours in advance. For more information on paging collections, see the department's website: http://library.stanford.edu/spc. Conditions Governing Access The materials are open for research use. Audio-visual materials are not available in original format, and must be reformatted to a digital use copy. Conditions Governing Use All requests to reproduce, publish, quote from, or otherwise use collection materials must be submitted in writing to the Head of Special Collections and University Archives, Stanford University Libraries, Stanford, California 94305-6064. Consent is given on behalf of Special Collections as the owner of the physical items and is not intended to include or imply permission from the copyright owner. Such permission must be obtained from the copyright owner, heir(s) or assigns. See: http://library.stanford.edu/spc/using-collections/permission-publish. -
Experiments & Analysis of the Role of Solar Power in Limiting Mars Rover
Experiments & Analysis of the Role of Solar Power in Limiting Mars Rover Range David P. Miller Tim S. Hunt Matt J. Roman [email protected] [email protected] [email protected] Aerospace & Mechanical Engineering University of Oklahoma Norman, OK 73019 Abstract— A common explanation for the limited distance this is really so. The experiments and analysis presented traveled by NASA’s past and planned Mars rovers is the below are designed to answer this question definitively. limits of solar power. This paper explores this hypothe- sis and documents a series of experiments with a solar II. OVERVIEW OF THE SR1 ROVER powered rover. A detailed comparison between our rover This paper describes SR1 (see video), a solar powered and Sojourner, with regards to power usage, is presented. Experiments and analysis clearly show that other factors autonomous rover of the approximate size and mass dominate in limiting the range of NASA’s solar powered of Sojourner (see Figure 1). This robot was built in a robots when operating on Mars. couple weeks using low-cost commercial components. Its purpose is to demonstrate that one does not have to I. MOTIVATION go to extraordinary lengths in order to get speed and There are a variety of ways of powering a Mars rover: endurance performance orders of magnitude larger than battery, RTG, and solar power. The advantages of solar those demonstrated by Sojourner. power are its renewability (as compared to a primary battery), its low cost and political banality (as compared to an RTG). The only successful Mars rover so far, Sojourner, used solar power for these reasons. -
Imaging Asteroid 4 Vesta Using the Framing Camera
Submission Completed Page 1 of 4 Your abstract submission has been received Click here to print this page now. You have submitted the following abstract to 2011 GSA Annual Meeting in Minneapolis (9–12 October 2011). Receipt of this notice does not guarantee that your submission was complete, free of errors, or accepted for presentation. IMAGING ASTEROID 4 VESTA USING THE FRAMING CAMERA KELLER, H. Uwe1, NATHUES, Andreas2, CORADINI, Angioletta3, JAUMANN, Ralf4, JORDA, Laurent5, LI, Jian-Yang6, MITTLEFEHLDT, David W.7, MOTTOLA, Stefano8, RAYMOND, C.A.9, and SCHRÖDER, Stefan E.2, (1) University Braunschweig, IGEP, Mendelssohnstrasse 3, Braunschweig, 38106, Germany, [email protected], (2) Max-Planck-Institut für Sonnensystemforschung, Max- Planck-Str. 3, Katlenburg-Lindau, 37191, Germany, (3) Istituto di Astrofisica Spaziale e Fisica Cosmica, Area Ricerca - Roma 2 Tor Vergata, Via Fosso del Cavaliere, 100, Rome, 00133, Italy, (4) German Aerospace Center (DLR) Berlin, Institute of Planetary Research, Rutherfordstrasse 2, Berlin, D-12489, Germany, (5) Laboratoire d'Astrophysique de Marseille, 38 rue Frederic Joliot-Curie, Marseille, F-13013 f, France, (6) Department of Astronomy, University of Maryland at College Park, College Park, MD 20742-242, (7) NASA, Johnson Space Center, mail code KR, 2101 NASA Parkway, Houston, TX 77058, (8) Dlr, Institute of Planetary Exploration, Rutherfordstr. 2, Berlin, 12489, Germany, (9) Jet Propulsion Laboratory, Pasadena, CA 91109 The Framing Camera (FC) onboard the Dawn spacecraft serves a dual purpose. Next to its central role as a prime science instrument it is also used for the complex navigation of the ion drive spacecraft. The CCD detector with 1024 by 1024 pixels provides the stability for a multiyear mission and its high requirements of photometric accuracy over the wavelength band from 400 to 1000 nm covered by 7 band-pass filters.