The Future of Mro/Hirise
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Mars Reconnaissance Orbiter
Chapter 6 Mars Reconnaissance Orbiter Jim Taylor, Dennis K. Lee, and Shervin Shambayati 6.1 Mission Overview The Mars Reconnaissance Orbiter (MRO) [1, 2] has a suite of instruments making observations at Mars, and it provides data-relay services for Mars landers and rovers. MRO was launched on August 12, 2005. The orbiter successfully went into orbit around Mars on March 10, 2006 and began reducing its orbit altitude and circularizing the orbit in preparation for the science mission. The orbit changing was accomplished through a process called aerobraking, in preparation for the “science mission” starting in November 2006, followed by the “relay mission” starting in November 2008. MRO participated in the Mars Science Laboratory touchdown and surface mission that began in August 2012 (Chapter 7). MRO communications has operated in three different frequency bands: 1) Most telecom in both directions has been with the Deep Space Network (DSN) at X-band (~8 GHz), and this band will continue to provide operational commanding, telemetry transmission, and radiometric tracking. 2) During cruise, the functional characteristics of a separate Ka-band (~32 GHz) downlink system were verified in preparation for an operational demonstration during orbit operations. After a Ka-band hardware anomaly in cruise, the project has elected not to initiate the originally planned operational demonstration (with yet-to-be used redundant Ka-band hardware). 201 202 Chapter 6 3) A new-generation ultra-high frequency (UHF) (~400 MHz) system was verified with the Mars Exploration Rovers in preparation for the successful relay communications with the Phoenix lander in 2008 and the later Mars Science Laboratory relay operations. -
Mars Exploration: an Overview of Indian and International Mars Missions Nayamavalsa Scariah1, Dr
Taurian Innovative Journal/Volume 1/ Issue 1 Mars exploration: An overview of Indian and International Mars Missions NayamaValsa Scariah1, Dr. Mili Ghosh2, Dr.A.P.Krishna3 Birla Institute of Technology, Mesra, Ranchi Abstract- Mars is the fourth planet from the sun. It is 1. Introduction also known as red planet because of its iron oxide content. There are lots of missions have been launched to Mars is also known as red planet, because of the mars for better understanding of our neighboring planet. reddish iron oxide prevalent on its surface gives it a There are lots of unmanned spacecraft including reddish appearance. It is the fourth planet from sun. orbiters, landers and rovers have been launched into mars since early 1960. Sputnik was the first satellite The term sol is used to define duration of solar day on launched in 1957 by Soviet Union. After seven failure Mars. A mean Martian solar day or sol is 24 hours 39 missions to Mars, Mariner 4 was the first satellite which minutes and 34.244 seconds. Many space missions to reached the Martian orbiter successfully. The Viking 1 Mars have been planned and launched for Mars was the first lander reached on Mars on 1975. India exploration (Table:1) but most of them failed without successfully launched a spacecraft, Mangalyan (Mars completing the task specially in early attempts th Orbiter Mission) on 5 November, 2013, with five whereas some NASA missions were very payloads to Mars. India was the first nation to successful(such as the twin Mars Exploration Rovers, successfully reach Mars on its first attempt. -
Mro High Resolution Imaging Science Experiment (Hirise)
Sixth International Conference on Mars (2003) 3287.pdf MROHIGHRESOLUTIONIMAGINGSCIENCEEXPERIMENT(HIRISE): INSTRUMENTDEVELOPMENT.AlanDelamere,IraBecker,JimBergstrom,JonBurkepile,Joe Day,DavidDorn,DennisGallagher,CharlieHamp,JeffreyLasco,BillMeiers,AndrewSievers,Scott StreetmanStevenTarr,MarkTommeraasen,PaulVolmer.BallAerospaceandTechnologyCorp.,PO Box1062,Boulder,CO80306 Focus Introduction:Theprimaryfunctionalre- Mechanism PrimaryMirror quirementoftheHiRISEimager,figure1isto PrimaryMirrorBaffle 2nd Fold allowidentificationofbothpredictedandun- Mirror knownfeaturesonthesurfaceofMarstoa muchfinerresolutionandcontrastthanprevi- ouslypossible[1],[2].Thisresultsinacam- 1st Fold erawithaverywideswathwidth,6kmat Mirror 300kmaltitude,andahighsignaltonoise ratio,>100:1.Generationofterrainmaps,30 Filters cmverticalresolution,fromstereoimages Focal requiresveryaccurategeometriccalibration. Plane Theprojectlimitationsofmass,costand schedulemakethedevelopmentchallenging. FocalPlane SecondaryMirror Inaddition,thespacecraftstability[3]must Electronics TertiaryMirror SecondaryMirrorBaffle notbeamajorlimitationtoimagequality. Thenominalorbitforthesciencephaseofthe missionisa3pmorbitof255by320kmwith Figure1Cameraopticalpathoptimizedforlowmass periapsislockedtothesouthpole.Thetrack Integration(TDI)tocreateveryhigh(100:1)signalnoise velocityisapproximately3,400m/s. ratioimages. HiRISEFeatures:TheHiRISEinstrumentperformance Theimagerdesignisanall-reflectivethreemirrorastig- goalsarelistedinTable1.Thedesignfeaturesa50cm matictelescopewithlight-weightedZeroduropticsanda -
LAURA KERBER Jet Propulsion Laboratory [email protected] 4800 Oak Grove Dr
LAURA KERBER Jet Propulsion Laboratory [email protected] 4800 Oak Grove Dr. Pasadena, CA __________________________________________________________________________________________ Education September 2006-May 2011 Brown University, Providence, RI PhD, Geological Sciences (May 2011) MS, Engineering, Fluid Mechanics (May 2011) MS, Geological Sciences (May 2008) August 2002-May 2006 Pomona College, Claremont, CA Major: Planetary Geology/Space Science Minor: Mathematics May 2002 Graduated Cherry Creek High School, Greenwood Village, Colorado, highest honors Research Experience and Roles September 2014- Present Jet Propulsion Laboratory, Research Scientist PI of Discovery Mission Concept Moon Diver Deputy Project Scientist, 2001 Mars Odyssey Yardang formation and distribution on Mars and Earth Ongoing development of end-to-end Martian sulfur cycle model, including microphysical processes, photochemistry, and interaction with the surface Measurement of wind over complex surfaces Microscale wind and erosion processes in cold polar deserts Science liaison to the Mars Program Office, Next Mars Orbiter (NeMO) Member of 2015 NeMO SAG Member of 2015 ICE-WG (In-situ resource utilization and civil engineering HEOMD working group) Science lead on several internal formulation studies, including a “Many MERs to Mars” concept study; “RSL Exploration with the Axel Extreme Terrain Robot” strategic initiative; “Autonomous Recognition of Signs of Life” spontaneous RTD; Moon Diver Instrument Trade Study; etc. Lead of Citizen Scientist “Planet Four: -
MEPAG Report to PSS 03-2016
Lisa Pratt, MEPAG Chair Report to PSS March 10-11, 2016 Mission Status Highlights • Curiosity is moving on from its several-month investigation of the Namib (part of Bagnold dunes) • MRO and ODY are stepping up observations as data rates increase – Both orbiters have started observing candidate sites (exploration zones) for humans on Mars • MER-B has survived winter and is exploring area where orbital data indicate clays • MAVEN has finished prime mission; special issue out with 59 papers reporting results • Foreign collaborations with ESA Mars Express and ExoMars MOMA continuing • 2020 Mars rover passed PDR review but has not gone through the Directorate or Agency Program Management Councils MEPAG Face-to-Face Meeting held March 2–3 • New MEPAG Chair: Jeff Johnson (JHU-APL) – Lisa Pratt moves to MEPAG Executive Committee – Nominations invited to fill vacancies on Goals Committee • Wide-Ranging Presentations and Discussion – Reports from PSD, MEP, and several space agencies • Including report from IMEWG iMARS coordination study – Overview of joint HEO-SMD activities • Successful first workshop for landing sites (Exploration Zones) for humans on Mars held October 2015 – MEPAG accepted two reports from its Science Analysis Groups • Science Objectives for Human Explorers on Mars (HSO-SAG) • Next Mars Orbiter (NEX-SAG) Next Mars Orbiter (1 of 3) MEPAG endorsed the NEX-SAG report which concluded: o z M’rs Prflitere utilizing Solar Electric Propulsion (SEP) and advanced telecom in a 5‑year mission in low Mars orbit, could provide exciting new science and resource identification A mission with SEP could have the capability for return of a cache of Mars samples to Earth vicinity as well as payload elements addressing high-priority resource and other science objectives o Return capability addresses the need to make progress on sample return, which is the Decadal Survey’s highest priority for flagship missions. -
An Implementation Concept for the ASPIRE Mission
An Implementation Concept for the ASPIRE Mission. W. D. Deininger* ([email protected]), W. Purcell,* P. Atcheson,*G. Mills,* S. A Sandford,** R. P. Hanel,** M. McKelvey,** and R. McMurray** *Ball Aerospace & Technologies Corp. (BATC) P. O. Box 1062 Boulder, CO, USA 80306-1062 **NASA Ames Research Center Moffett Field, CA, USA 94035 Abstract—The Astrobiology Space Infrared Explorer complex and tied to the cyclic process whereby these (ASPIRE) is a Probe-class mission concept developed as elements are ejected into the diffuse interstellar medium part of NASA’s Astrophysics Strategic Mission Concept (ISM) by dying stars, gathered into dense clouds and studies. 1 2 ASPIRE uses infrared spectroscopy to explore formed into the next generation of stars and planetary the identity, abundance, and distribution of molecules, systems (Figure 1). Each stage in this cycle entails chemical particularly those of astrobiological importance throughout alteration of gas- and solid-state species by a diverse set of the Universe. ASPIRE’s observational program is focused astrophysical processes: hocks, stellar winds, radiation on investigating the evolution of ices and organics in all processing by photons and particles, gas-phase neutral and phases of the lifecycle of carbon in the universe, from ion chemistry, accretion, and grain surface reactions. These stellar birth through stellar death while also addressing the processes create new species, destroy old ones, cause role of silicates and gas-phase materials in interstellar isotopic enrichments, shuffle elements between chemical organic chemistry. ASPIRE achieves these goals using a compounds, and drive the universe to greater molecular Spitzer-derived, cryogenically-cooled, 1-m-class telescope complexity. -
Gordon Woodcock Space Architecture Award 2020 Candidate: a Scott Howe
Gordon Woodcock Space Architecture Award 2020 Candidate: A Scott Howe To the AIAA Space Architecture Technical Committee, thank you very much for nominating me for this award. I feel humbled, and I’m sure there are many worthy candidates. I feel as though I have been busy in some distant corner of the field, but I am very pleased that Space Architecture has grown to what it is today. The following are my statements and comments as requested – please let me know if further information is needed. 1. Statement confirming you’ve been involved in the field for at least 10 years: I was at the impressionable age of 9 years old when Neil and Buzz walked on the moon and was interested in space ever since. However, the idea of working for NASA seemed way beyond my reach, and didn’t seem compatible with my desire to become an architect so I went straight into architecture. I worked in terrestrial architecture since 1978. A turning point came when I began working in Japan in 1988, and got involved with the folks doing robotic construction. I began considering the issue of large-scale construction using entirely autonomous, mechanized means, and in the late 1990’s was introduced to early AIAA Design Engineering Space Architecture WG efforts by Marc Cohen and Ted Hall. I submitted my first Space Architecture paper, discussing a robotic outpost construction system in 2000 and increased my involvement in AIAA after that. I became a full-time Space Architect in 2007 when I joined the NASA Jet Propulsion Laboratory and have been working on robotic construction for planetary surfaces, the design of outposts and habitats, and pressurized vehicles ever since that time. -
PUBLIC OPEN EVENING Outreach — 17 January 2017 — A
Institute of Astronomy PUBLIC OPEN EVENING outreach — 17 January 2017 — A Clean water ice hiding just below TONIGHT’S SPEAKER the surface of Mars The talk schedule for this term can be viewed at: this term can be viewed talk schedule for The Matt Bothwell The biggest galaxy in the Universe? Our weekly welcome ELCOME to our weekly public Wopen evenings for the 2017/18 season. Each night there will be a half-hour talk which begins promptly Erosion on Mars has uncovered large, steep cross-sections of clean, subterranean ice. In this at 7.15pm: tonight Matt Bothwell will false color image captured by NASA’s HiRISE camera, one of eight recently discovered stripes be giving us his talk The biggest appears dark blue against the Martian terrain. Credit: NASA/JPL/Uni. Of Arizona/USGS galaxy in the Universe? The talk is followed by an oppor- IT’S GOOD news for future Martian scientists have discovered this in no tunity to observe if (and only if!) the www.ast.cam.ac.uk/public/public_observing/current colonists – NASA has just discovered less than eight different places across weather is clear. The IoA’s historical plenty of easy-to-access water just Mars, in both hemispheres. Northumberland and Thorrowgood under Mars’s surface. The new photographs were taken by Astronomers have known for ‘HiRISE’, a powerful camera attached telescopes, along with our modern decades that water exists on Mars, but to NASA’s Mars Reconnaissance Orbit- 16-inch telescope, will be open just how easy it is to get at (and use) er, and the purity of the hidden water for observations. -
Composition of Mars, Michelle Wenz
The Composition of Mars Michelle Wenz Curiosity Image NASA Importance of minerals . Role in transport and storage of volatiles . Ex. Water (adsorbed or structurally bound) . Control climatic behavior . Past conditions of mars . specific pressure and temperature formation conditions . Constrains formation and habitability Curiosity Rover at Mount Sharp drilling site, NASA image Missions to Mars . 44 missions to Mars (all not successful) . 21 NASA . 18 Russia . 1 ESA . 1 India . 1 Japan . 1 joint China/Russia . 1 joint ESA/Russia . First successful mission was Mariner 4 in 1964 Credit: Jason Davis / astrosaur.us, http://utprosim.com/?p=808 First Successful Mission: Mariner 4 . First image of Mars . Took 21 images . No evidence of canals . Not much can be said about composition Mariner 4, NASA image Mariner 4 first image of Mars, NASA image Viking Lander . First lander on Mars . Multispectral measurements Viking Planning, NASA image Viking Anniversary Image, NASA image Viking Lander . Measured dust particles . Believed to be global representation . Computer generated mixtures of minerals . quartz, feldspar, pyroxenes, hematite, ilmenite Toulmin III et al., 1977 Hubble Space Telescope . Better resolution than Mariner 6 and 7 . Viking limited to three bands between 450 and 590 nm . UV- near IR . Optimized for iron bearing minerals and silicates Hubble Space Telescope NASA/ESA Image featured in Astronomy Magazine Hubble Spectroscopy Results . 1994-1995 . Ferric oxide absorption band 860 nm . hematite . Pyroxene 953 nm absorption band . Looked for olivine contributions . 1042 nm band . No significant olivine contributions Hubble Space Telescope 1995, NASA Composition by Hubble . Measure of the strength of the absorption band . Ratio vs. -
Mars Reconnaissance Orbiter's High Resolution Imaging Science
JOURNAL OF GEOPHYSICAL RESEARCH, VOL. 112, E05S02, doi:10.1029/2005JE002605, 2007 Click Here for Full Article Mars Reconnaissance Orbiter’s High Resolution Imaging Science Experiment (HiRISE) Alfred S. McEwen,1 Eric M. Eliason,1 James W. Bergstrom,2 Nathan T. Bridges,3 Candice J. Hansen,3 W. Alan Delamere,4 John A. Grant,5 Virginia C. Gulick,6 Kenneth E. Herkenhoff,7 Laszlo Keszthelyi,7 Randolph L. Kirk,7 Michael T. Mellon,8 Steven W. Squyres,9 Nicolas Thomas,10 and Catherine M. Weitz,11 Received 9 October 2005; revised 22 May 2006; accepted 5 June 2006; published 17 May 2007. [1] The HiRISE camera features a 0.5 m diameter primary mirror, 12 m effective focal length, and a focal plane system that can acquire images containing up to 28 Gb (gigabits) of data in as little as 6 seconds. HiRISE will provide detailed images (0.25 to 1.3 m/pixel) covering 1% of the Martian surface during the 2-year Primary Science Phase (PSP) beginning November 2006. Most images will include color data covering 20% of the potential field of view. A top priority is to acquire 1000 stereo pairs and apply precision geometric corrections to enable topographic measurements to better than 25 cm vertical precision. We expect to return more than 12 Tb of HiRISE data during the 2-year PSP, and use pixel binning, conversion from 14 to 8 bit values, and a lossless compression system to increase coverage. HiRISE images are acquired via 14 CCD detectors, each with 2 output channels, and with multiple choices for pixel binning and number of Time Delay and Integration lines. -
Descent Trajectory Reconstruction and Landing Site Positioning of Changâ
ARTICLE https://doi.org/10.1038/s41467-019-12278-3 OPEN Descent trajectory reconstruction and landing site positioning of Chang’E-4 on the lunar farside Jianjun Liu1,2, Xin Ren 1, Wei Yan 1, Chunlai Li 1,2, He Zhang 3, Yang Jia3, Xingguo Zeng1, Wangli Chen1, Xingye Gao1, Dawei Liu1, Xu Tan1, Xiaoxia Zhang1, Tao Ni1,2, Hongbo Zhang1, Wei Zuo 1, Yan Su1 & Weibin Wen1 Chang’E-4 (CE-4) was the first mission to accomplish the goal of a successful soft landing on 1234567890():,; the lunar farside. The landing trajectory and the location of the landing site can be effectively reconstructed and determined using series of images obtained during descent when there were no Earth-based radio tracking and the telemetry data. Here we reconstructed the powered descent trajectory of CE-4 using photogrammetrically processed images of the CE-4 landing camera, navigation camera, and terrain data of Chang’E-2. We confirmed that the precise location of the landing site is 177.5991°E, 45.4446°S with an elevation of −5935 m. The landing location was accurately identified with lunar imagery and terrain data with spatial resolutions of 7 m/p, 5 m/p, 1 m/p, 10 cm/p and 5 cm/p. These results will provide geodetic data for the study of lunar control points, high-precision lunar mapping, and subsequent lunar exploration, such as by the Yutu-2 rover. 1 Key Laboratory of Lunar and Deep Space Exploration, National Astronomical Observatories, Chinese Academy of Sciences, Beijing 100101, China. 2 School of Astronomy and Space Science, University of Chinese Academy of Sciences, Beijing 100049, China. -
Mars-Base-Camp-2028.Pdf
Mars Base Camp An Architecture for Sending Humans to Mars by 2028 A Technical Paper Presented by: Timothy Cichan Stephen A. Bailey Lockheed Martin Space Deep Space Systems, Inc. [email protected] [email protected] Scott D. Norris Robert P. Chambers Lockheed Martin Space Lockheed Martin Space [email protected] [email protected] Robert P. Chambers Joshua W. Ehrlich Lockheed Martin Space Lockheed Martin Space [email protected] [email protected] October 2016 978-1-5090-1613-6/17/$31.00 ©2017 IEEE Abstract—Orion, the Multi-Purpose Crew Vehicle, near term Mars mission is compelling and feasible, is a key piece of the NASA human exploration and will highlight the required key systems. architecture for beyond earth orbit (BEO). Lockheed Martin was awarded the contracts for TABLE OF CONTENTS the design, development, test, and production for Orion up through the Exploration Mission 2 (EM- 1. INTRODUCTION ..................................................... 2 2). Additionally, Lockheed Martin is working on 2. ARCHITECTURE PURPOSE AND TENETS ....................... 3 defining the cis-lunar Proving Ground mission 3. MISSION CAMPAIGN, INCLUDING PROVING GROUND architecture, in partnership with NASA, and MISSIONS ................................................................ 5 exploring the definition of Mars missions as the 4. MISSION DESCRIPTION AND CONCEPT OF OPERATIONS . 7 horizon goal to provide input to the plans for 5. ELEMENT DESCRIPTIONS ....................................... 13 human exploration of the solar system. This paper 6. TRAJECTORY DESIGN ............................................ 16 describes an architecture to determine the 7. SCIENCE ............................................................. 19 feasibility of a Mars Base Camp architecture 8. MARS SURFACE ACCESS FOR CREW ......................... 14 within about a decade.