Design and Optimization of Navigation and Guidance Techniques for Mars Pinpoint Landing: Review and Prospect Zhengshi Yu1,2, Pingyuan Cui*1,2, John L
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MARS SCIENCE LABORATORY ORBIT DETERMINATION Gerhard L. Kruizinga(1)
MARS SCIENCE LABORATORY ORBIT DETERMINATION Gerhard L. Kruizinga(1), Eric D. Gustafson(2), Paul F. Thompson(3), David C. Jefferson(4), Tomas J. Martin-Mur(5), Neil A. Mottinger(6), Frederic J. Pelletier(7), and Mark S. Ryne(8) (1-8)Jet Propulsion Laboratory, California Institute of Technology, 4800 Oak Grove Drive, Pasadena, California 91109, +1-818-354-7060, fGerhard.L.Kruizinga, edg, Paul.F.Thompson, David.C.Jefferson, tmur, Neil.A.Mottinger, Fred.Pelletier, [email protected] Abstract: This paper describes the orbit determination process, results and filter strategies used by the Mars Science Laboratory Navigation Team during cruise from Earth to Mars. The new atmospheric entry guidance system resulted in an orbit determination paradigm shift during final approach when compared to previous Mars lander missions. The evolving orbit determination filter strategies during cruise are presented. Furthermore, results of calibration activities of dynamical models are presented. The atmospheric entry interface trajectory knowledge was significantly better than the original requirements, which enabled the very precise landing in Gale Crater. Keywords: Mars Science Laboratory, Curiosity, Mars, Navigation, Orbit Determination 1. Introduction On August 6, 2012, the Mars Science Laboratory (MSL) and the Curiosity rover successful performed a precision landing in Gale Crater on Mars. A crucial part of the success was orbit determination (OD) during the cruise from Earth to Mars. The OD process involves determining the spacecraft state, predicting the future trajectory and characterizing the uncertainty associated with the predicted trajectory. This paper describes the orbit determination process, results, and unique challenges during the final approach phase. -
MARS an Overview of the 1985–2006 Mars Orbiter Camera Science
MARS MARS INFORMATICS The International Journal of Mars Science and Exploration Open Access Journals Science An overview of the 1985–2006 Mars Orbiter Camera science investigation Michael C. Malin1, Kenneth S. Edgett1, Bruce A. Cantor1, Michael A. Caplinger1, G. Edward Danielson2, Elsa H. Jensen1, Michael A. Ravine1, Jennifer L. Sandoval1, and Kimberley D. Supulver1 1Malin Space Science Systems, P.O. Box 910148, San Diego, CA, 92191-0148, USA; 2Deceased, 10 December 2005 Citation: Mars 5, 1-60, 2010; doi:10.1555/mars.2010.0001 History: Submitted: August 5, 2009; Reviewed: October 18, 2009; Accepted: November 15, 2009; Published: January 6, 2010 Editor: Jeffrey B. Plescia, Applied Physics Laboratory, Johns Hopkins University Reviewers: Jeffrey B. Plescia, Applied Physics Laboratory, Johns Hopkins University; R. Aileen Yingst, University of Wisconsin Green Bay Open Access: Copyright 2010 Malin Space Science Systems. This is an open-access paper distributed under the terms of a Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. Abstract Background: NASA selected the Mars Orbiter Camera (MOC) investigation in 1986 for the Mars Observer mission. The MOC consisted of three elements which shared a common package: a narrow angle camera designed to obtain images with a spatial resolution as high as 1.4 m per pixel from orbit, and two wide angle cameras (one with a red filter, the other blue) for daily global imaging to observe meteorological events, geodesy, and provide context for the narrow angle images. Following the loss of Mars Observer in August 1993, a second MOC was built from flight spare hardware and launched aboard Mars Global Surveyor (MGS) in November 1996. -
Gulick, V CV2008.PDF
Curriculum Vitae: Dr. Virginia C. Gulick Nr\SA Amcs RcsearchCenter, lVfail Stop 239-20,Moffetl Field, Califoniia94035 (650) 604-0781 (office), Vireinia.C.GuUckr7lnase-gav IIDUCATION PhD (Geosciences);University of Arizona Ph.D. Thesis: Magnmtic Intrusiorts ancl l{ydrotlrcrmal Systents:Implicatiotts for the Fornmtion of Small Msrtian Valleys MS. (Geosciencr:s),Minor in Hydrology,The University of Arizona,Tucson Master Thesis: Origin ad Ev'olutionoJ'I'alle1's on the Martian Volcanoes:T'he Hatvaiittn.4nalog. B.A. (Geoscicnces),Rutgers University (Rutgers College) New Brunswick, New Jersey Senior Thesis:TIte Coral SeaSedinettt Study. I'[t.ft]SENTPOStrTION 1996-prres.:ResearchScientist (SETI InstitutePrincipal Investigator)& Adjunct Professor,Astronomy Dept.,NM StateUniv. u Mars ScienceLab 2009landing site selcction steering group nrembcr. r MRO'05 IIiRISE instrumentsciencc ternr nrcnibcr(200)-2009): Lead on flrn,ial & hydrothernral processes, E/PO & r'r,eb technologies. I-IiRl:iE E/PO website (http://nrarsox,eb.nas.uasa. gov/I{iRISE) presentation Planctary l)ata in E,ducational ' Invited to AGU's Scssion Using Settings. Presentationtitle: "MRO's High Re.solutionImaging ScienceExperirncnt ([iiRISE): EdLrcation And PubiicOutr each Plans",. r Invitedpanelist fot NASA's Leamingfiom the Frontier:Getting Planetary l)ata into the Herndsof EducatorsWorkshop at LPi, March 14,2004. ' Co-convcuerof thc Volcano/iceInteraction on Earthand Mars Conf-.,P.eykjavik, Iceland, August 2000. " Projectscicnce lead on Marsorveb:the Mars l,anding Site Studies& Global Visualizationweb cnvironmentr:ffort (hItpJ4UDSIylb.nas.liUagq1llandinqsites).1998-present. o ScienceCoI for the Clickworkersl'roject; NASA's Experimeutin distributeddata analysis by the p ubl i c w eb si tc (liltd&lekfi g*9t$.3l9.qag4.gev ) 20 0 0-p resent. -
IMU/MCAV Integrated Navigation for the Powered Descent Phase Of
Overview of Chinese Current Efforts for Mars Probe Design Xiuqiang Jiang1,2, Ting Tao1,2 and Shuang Li1,2 1. College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China 2. Space New Technology Laboratory, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China Email: [email protected], [email protected] Abstract Mars exploration activities have gathered scientific data and deepened the current understanding about the Martian evolution process and living environment. As a terrestrial planet, Mars is also an excellent proving ground of some innovative special-purpose aerospace technologies. In the U.S., Soviet Union (Russia), Europe, and India, missions sending spacecraft to explore Mars currently exist, and the first three have landed their spacecrafts on the surface of Mars. China has programmed five Mars landing missions in next 20 years, and some critical technologies for Mars landing mission have been studied beforehand. In this paper, we will report Chinese Mars exploration mission scenario and the latest progress in dynamics study and guidance navigation and control (GNC) system design for Chinese first Mars probe. Some elementary design rules and index will be described according to simulation experiments, analysis and survey. Several new coping strategies will be proposed to be competent for the challenges of the Mars entry descent and landing (EDL) dynamics process. Details of the work, the supporting data and preliminary conclusions of the investigation will be presented. Based on our current efforts, one candidate system configuration architecture of Chinese first Mars probe will be shown and elaborated in the end. United States launched the “Mars Pathfinder (MPF)” 1. -
Solarhub Maxar’S Lunar Vertical Solar Array Technology
SolarHub Maxar’s Lunar Vertical Solar Array Technology Presented to the Lunar Surface Innovation Consortium (LSIC) 2021-05-27 Approved for External Release MAXAR AND LUNAR EXPLORATION Solar Power Use or disclosure of the data contained on this sheet © 2021 Maxar Technologies 2 is subject to the restrictions on the cover page A MISSION PARTNER WITH PROVEN HERITAGE With more than 60 years of experience, Maxar is a trusted partner for government and commercial missions. Our renowned Space Infrastructure capabilities date back to the Apollo Moon landing and continue to serve the most demanding missions: ▪ Communications and Earth observation ▪ Space exploration ▪ Solar electric propulsion ▪ On-orbit servicing and assembly 285+ 2,750 80+ 2.4+ Maxar-built spacecraft Combined Communication Billion people rely on launched years on orbit satellites on orbit broadcasting services powered by Maxar-built satellites Use or disclosure of the data contained on this sheet © 2021 Maxar Technologies is subject to the restrictions on the cover page 3 MAXAR IS A GLOBALLY TRUSTED LEADER DELIVERING SPACE INFRASTRUCTURE AND EARTH INTELLIGENCE SPACE INFRASTRUCTURE EARTH INTELLIGENCE Use or disclosure of the data contained on this sheet © 2021 Maxar Technologies 4 is subject to the restrictions on the cover page Psyche spacecraft chassis, power & MAXAR SPACE INFRASTRUCTURE propulsion ▪ 60+ years building high reliability spacecraft ▪ Launched 285+ LEO & GEO satellites ▪ Leader in Solar Electric Propulsion (SEP) ▪ High heritage in: − power management and distribution -
Space Vehicle Conceptual Design Blue Team March 20, 2021
Hephaestus: Space Vehicle Conceptual Design Blue team March 20, 2021 Connor Cruickshank, Joel Lundahl, Birgir Steinn Hermannsson, Greta Tartaglia M.Sc. students, KTH Royal Institute of Technology, Stockholm, Sweden Abstract—A hypothetical contest has been issued to summit ms Structural mass Olympus Mons. This report details a conceptual design of a space P Power vehicle intended for that purpose. Functional requirements of the p Combustion chamber pressure vehicle were defined, and the primary subsystems identified. The 02 SpaceX Starship was chosen to serve as a design baseline and pe Exhaust gas exit pressure a comparison of suitable launch vehicles was made. Subsystems S Drag surface such as propulsion, reaction control, power generation, thermal T Thrust management and radiation shielding were considered, as well as ue Exhaust gas exit velocity interior design of the space vehicle and its protection measures W Weight for Mars entry and activities. The consequences of an engine-out scenario were studied. t Metric tonne The Starship launch system was deemed the most suitable launch vehicle candidate. Six Raptor engines were selected for the spacecraft main propulsion system, with 8 smaller thrusters I. INTRODUCTION for reaction control. A radiator mass of 890 kg was estimated In the year 2038 a challenge was issued for a team of for the thermal management system, and lithium metal hydride was determined an adequate radiation shielding material for the pioneers to be the first to reach the peak of Olympus Mons, the crew quarters. A radiation shelter was integrated into the pantry, highest mountain in the solar system. The reward for the first to and layouts of the crew quarters and cargo bay were prepared. -
The Mars Surveyor Program - Planned Orbiter and Lander for 2001
Lunar and Planetary Science XXXI 1776.pdf THE MARS SURVEYOR PROGRAM - PLANNED ORBITER AND LANDER FOR 2001. R. S. Saunders, Jet Propulsion Laboratory, 180-701, 4800 Oak Grove Drive, Pasadena, CA 91109, [email protected]. Introduction: Following the loss of the Mars Cli- An additional experiment, the Martian Radiation mate Orbiter and the Mars Polar Lander, the Mars Environment Experiment (MARIE) is an energetic Surveyor Program is undergoing a replanning effort. particle spectrometer designed to measure the near There is currently no anticipated change to the 2001 space radiation environment as related to the radiation orbiter science payload, which is scheduled for launch hazard to human explorers. This is one of the Human on March 30, 2001. If launched on schedule, the or- Exploration and Development of Space Enterprise biter will arrive at Mars on Oct. 20, 2001. The 2001 (HEDS) experiments that was selected for the 2001 orbiter carries the Gamma Ray Spectrometer (GRS) mission to acquire data needed before planning human (based on science objectives lost with Mars Observer) missions to Mars. MARIE will determine the radia- and the Thermal Emission Imaging System tion energy spectrum, separate the contribution from (THEMIS). The Mars Surveyor 2001 Lander is sched- various particles, and measure the accumulated ab- uled to launch on April 10, 2001 and will land on sorbed dose and dose rate that would occur in human Mars on January 22, 2002, about three months after tissue. the orbiter arrives and about two weeks after the or- Lander Site Selection: During the past year, the biter achieves its mapping orbit following a 76 day planetary science community was engaged in selecting aerobraking sequence. -
Development of Supersonic Retropropulsion for Future Mars Entry, Descent, and Landing Systems
JOURNAL OF SPACECRAFT AND ROCKETS Vol. 51, No. 3, May–June 2014 Development of Supersonic Retropropulsion for Future Mars Entry, Descent, and Landing Systems Karl T. Edquist∗ and Ashley M. Korzun† NASA Langley Research Center, Hampton, Virginia 23681 Artem A. Dyakonov‡ Blue Origin, LLC, Kent, Washington 98032 Joseph W. Studak§ NASA Johnson Space Center, Houston, Texas 77058 Devin M. Kipp¶ Jet Propulsion Laboratory, California Institute of Technology, Pasadena, California, 91109 and Ian C. Dupzyk** Lunexa, LLC, San Francisco, California 94105 DOI: 10.2514/1.A32715 Recent studies have concluded that Viking-era entry system deceleration technologies are extremely difficult to scale for progressively larger payloads (tens of metric tons) required for human Mars exploration. Supersonic retropropulsion is one of a few developing technologies that may enable future human-scale Mars entry systems. However, in order to be considered as a viable technology for future missions, supersonic retropropulsion will require significant maturation beyond its current state. This paper proposes major milestones for advancing the component technologies of supersonic retropropulsion such that it can be reliably used on Mars technology demonstration missions to land larger payloads than are currently possible using Viking-based systems. The development roadmap includes technology gates that are achieved through ground-based testing and high-fidelity analysis, culminating with subscale flight testing in Earth’s atmosphere that demonstrates stable and controlled flight. The component technologies requiring advancement include large engines (100s of kilonewtons of thrust) capable of throttling and gimbaling, entry vehicle aerodynamics and aerothermodynamics modeling, entry vehicle stability and control methods, reference vehicle systems engineering and analyses, and high-fidelity models for entry trajectory simulations. -
Co-Optimization of Mid Lift to Drag Vehicle Concepts for Mars Atmospheric Entry
10th AIAA/ASME Joint Thermophysics and Heat Transfer Conference AIAA 2010-5052 28 June - 1 July 2010, Chicago, Illinois Co-Optimization of Mid Lift to Drag Vehicle Concepts for Mars Atmospheric Entry Joseph A. Garcia1 , James L. Brown2 , David J. Kinney1 and Jeffrey V. Bowles1 NASA Ames Research Center, Moffett Field, CA 94035, USA and Loc C. Huynh3. Xun J. Jiang3, Eric Lau3, and Ian C. Dupzyk4 ELORET Corporation, Moffett Field, CA 94035, USA As NASA continues to make plans for future robotic precursor and eventual human missions to Mars, the need to characterize and develop designs for entry vehicles capable of delivering large masses to the surface of Mars will persist. In combination with this, NASA has recognized that the current heritage technology for Mars’ Entry Decent and Landing (EDL) does not have the capability to land the required payload masses. Both the Thermal Protection System (TPS) and the Descent/Landing systems require new design approaches. Because of these needs, NASA has performed an Entry, Descent and Landing Systems Analysis (EDL-SA) study for high mass exploration and science missions to identify key enabling technology areas for further investment. One key technology area identified includes rigid aeroshell shapes for aerodynamic performance and controllability. In this investigation, a system optimization study of alternative aeroshell shapes for Mars exploration class payloads of approximately 40 metric tons has been conducted. This system optimization is accomplished using a Multi-disciplinary Design Optimization (MDO) framework which accounts for the aeroshell shape, trajectory, thermal protection system, and vehicle subsystem closure along with a Multi Objective Genetic Algorithm (MOGA) for the initial shape exploration. -
Mars Exploration Entry, Descent and Landing Challenges1,2
Mars Exploration Entry, Descent and Landing Challenges1,2 Robert D. Braun Robert M. Manning Georgia Institute of Technology Jet Propulsion Laboratory Atlanta, GA 30332-0150 California Institute of Technology (404) 385-6171 Pasadena, CA 91109 [email protected] (818) 393-7815 [email protected] Abstract—The United States has successfully landed five interesting locations within close proximity (10’s of m) of robotic systems on the surface of Mars. These systems all pre-positioned robotic assets. These plans require a had landed mass below 0.6 metric tons (t), had landed simultaneous two order of magnitude increase in landed footprints on the order of hundreds of km and landed at sites mass capability, four order of magnitude increase in landed below -1 km MOLA elevation due the need to perform accuracy, and an entry, descent and landing operations entry, descent and landing operations in an environment sequence that may need to be completed in a lower density with sufficient atmospheric density. Current plans for (higher surface elevation) environment. This is a tall order human exploration of Mars call for the landing of 40-80 t that will require the space qualification of new EDL surface elements at scientifically interesting locations within approaches and technologies. close proximity (10’s of m) of pre-positioned robotic assets. This paper summarizes past successful entry, descent and Today, robotic exploration systems engineers are struggling landing systems and approaches being developed by the with the challenges of increasing landed mass capability to 1 robotic Mars exploration program to increased landed t while improving landed accuracy to 10’s of km and performance (mass, accuracy and surface elevation). -
The Mars Global Surveyor Mars Orbiter Camera: Interplanetary Cruise Through Primary Mission
p. 1 The Mars Global Surveyor Mars Orbiter Camera: Interplanetary Cruise through Primary Mission Michael C. Malin and Kenneth S. Edgett Malin Space Science Systems P.O. Box 910148 San Diego CA 92130-0148 (note to JGR: please do not publish e-mail addresses) ABSTRACT More than three years of high resolution (1.5 to 20 m/pixel) photographic observations of the surface of Mars have dramatically changed our view of that planet. Among the most important observations and interpretations derived therefrom are that much of Mars, at least to depths of several kilometers, is layered; that substantial portions of the planet have experienced burial and subsequent exhumation; that layered and massive units, many kilometers thick, appear to reflect an ancient period of large- scale erosion and deposition within what are now the ancient heavily cratered regions of Mars; and that processes previously unsuspected, including gully-forming fluid action and burial and exhumation of large tracts of land, have operated within near- contemporary times. These and many other attributes of the planet argue for a complex geology and complicated history. INTRODUCTION Successive improvements in image quality or resolution are often accompanied by new and important insights into planetary geology that would not otherwise be attained. From the variety of landforms and processes observed from previous missions to the planet Mars, it has long been anticipated that understanding of Mars would greatly benefit from increases in image spatial resolution. p. 2 The Mars Observer Camera (MOC) was initially selected for flight aboard the Mars Observer (MO) spacecraft [Malin et al., 1991, 1992]. -
Exobiology in the Solar System & the Search for Life on Mars
SP-1231 SP-1231 October 1999 Exobiology in the Solar System & The Search for Life on Mars for The Search Exobiology in the Solar System & Exobiology in the Solar System & The Search for Life on Mars Report from the ESA Exobiology Team Study 1997-1998 Contact: ESA Publications Division c/o ESTEC, PO Box 299, 2200 AG Noordwijk, The Netherlands Tel. (31) 71 565 3400 - Fax (31) 71 565 5433 SP-1231 October 1999 EXOBIOLOGY IN THE SOLAR SYSTEM AND THE SEARCH FOR LIFE ON MARS Report from the ESA Exobiology Team Study 1997-1998 Cover Fossil coccoid bacteria, 1 µm in diameter, found in sediment 3.3-3.5 Gyr old from the Early Archean of South Africa. See pages 160-161. Background: a portion of the meandering canyons of the Nanedi Valles system viewed by Mars Global Surveyor. The valley is about 2.5 km wide; the scene covers 9.8 km by 27.9 km centred on 5.1°N/48.26°W. The valley floor at top right exhibits a 200 m-wide channel covered by dunes and debris. This channel suggests that the valley might have been carved by water flowing through the system over a long period, in a manner similar to rivers on Earth. (Malin Space Science Systems/NASA) SP-1231 ‘Exobiology in the Solar System and The Search for Life on Mars’, ISBN 92-9092-520-5 Scientific Coordinators: André Brack, Brian Fitton and François Raulin Edited by: Andrew Wilson ESA Publications Division Published by: ESA Publications Division ESTEC, Noordwijk, The Netherlands Price: 70 Dutch Guilders/ EUR32 Copyright: © 1999 European Space Agency Contents Foreword 7 I An Exobiological View of the