DOCSLIB.ORG

A Low-Thrust Transfer Strategy to Earth-Moon Collinear Libration Point Orbits

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
A Low-Thrust Transfer Strategy to Earth-Moon Collinear Libration Point Orbits A LOW-THRUST TRANSFER STRATEGY TO EARTH-MOON COLLINEAR LIBRATION POINT ORBITS A Thesis Submitted to the Faculty of Purdue University by Martin T. Ozimek In Partial Fulfillment of the Requirements for the Degree of Master of Science December 2006 Purdue University West Lafayette, IN ii For Mom, Dad, Sarah, and Bops iii ACKNOWLEDGMENTS I would like to thank my parents for their seemingly never ending support and confidence that I would persevere in my personal quest for an advanced degree. The decision to commit to a higher degree has been an adventure that I hope to continue along, and I can’t begin to explain the importance of that priceless feeling of simply knowing that someone is there when needed. Professor Kathleen Howell, my advisor, is also owed a great deal of gratitude, not only for posing the fateful words “low-thrust” one day in her office during a discussion about NASA’s potential Jupiter Icy Moons missions, but also for her personal standard for excellence that she instills in each of her many successful graduate students. I’ve always felt that Purdue University reached out to me and offered me that “extra” indefinable something from the moment I began seriously considering a graduate institution. In no other person is this ambiguous something “extra” exemplified than in Professor Howell, who has sought to ensure that my research efforts are guided and ultimately shared with others in the best possible way. This notion has also been exemplified by Professor James Longuski, whose door has always been open to me from day one, and whom I must also credit in heavily influencing my decision to attend Purdue University. On more than one occasion, Professor William Crossley has also had his door open to help along my path of solving what turned out to be a difficult optimization problem. I also owe many thanks to Daniel Grebow. Dan has been a close friend, colleague, and even roommate throughout my stay at Purdue, and this work is the direct continuation of a mission analysis that we worked on together. Often, many of the new ideas I have for current and future research are a result of simple dialogs that we frequently engage in. iv The idea to study mission applications toward lunar south pole coverage would never have originated had I not fortuitously been privileged to work at the NASA Goddard Spaceflight Center during the summers of 2005 (as a member of the NASA Academy by way of the Indiana Space Grant Consortium) and 2006. There, I benefited from the knowledge of some of the greatest libration point mission experts in the world, and owe particular thanks to my mentor David Folta. Support from NASA under contract numbers NNG05GM76G and NNX06AC22G is greatly appreciated. Finally, I would like to thank Purdue University for financial support, including the Andrews Fellowship, for the entirety of my M.S. program. v TABLE OF CONTENTS Page LIST OF TABLES............................................................................................................ vii LIST OF FIGURES ......................................................................................................... viii ABSTRACT........................................................................................................................ x 1 INTRODUCTION ............................................................................................................1 1.1 Historical Overview of the Three-Body Problem.......................................................3 1.2 Developments in Low-Thrust Transfer Trajectories ..................................................5 1.2.1 Optimal Control .................................................................................................. 5 1.2.2 Application to Orbit Problems ............................................................................ 6 1.3 Focus of this Work .....................................................................................................7 2 BACKGROUND ............................................................................................................10 2.1 The Circular Restricted Three-Body Problem..........................................................10 2.1.1 Assumptions...................................................................................................... 11 2.1.2 Geometry........................................................................................................... 11 2.1.3 Equations of Motion.......................................................................................... 12 2.1.4 Libration Points................................................................................................. 15 2.1.5 Formulation Relative to P2 in the CR3BP......................................................... 17 2.2 Natural Periodic Orbits in the CR3BP......................................................................18 2.2.1 First-Order Variational Equations Relative to the Collinear Points.................. 19 2.2.2 The State Transition Matrix .............................................................................. 23 2.2.3 The Fundamental Targeting Relationships ....................................................... 25 2.2.4 Periodic Orbits .................................................................................................. 28 2.3 Invariant Manifolds ..................................................................................................31 2.3.1 Stable and Unstable Manifolds Associated with the Collinear Points.............. 32 vi Page 2.3.2 Invariant Manifolds Relative to a Fixed Point .................................................. 35 2.3.3 Computation of Manifolds Corresponding to Fixed Points Along an Orbit..... 37 2.4 Optimal Control Theory ...........................................................................................39 2.4.1 Summary of the First Necessary Conditions for Optimal Control.................... 40 2.4.2 Tests for a Local Minimum Value of the Performance Index .......................... 43 3 LOW-THRUST TRANSFER ALGORITHM ................................................................45 3.1 Engine Model ...........................................................................................................46 3.2 Control Law Derivation............................................................................................48 3.3 Adjoint Control Transformation...............................................................................55 3.4 Numerical Solution via Direct Shooting: A Local Approach...................................59 3.5 Shotgun Method for Initial Conditions: A Global Approach...................................63 4 MISSION APPLICATIONS...........................................................................................66 4.1 Orbits for Line-of-Sight Lunar South Pole Coverage (CR3BP) ..............................67 4.1.1 Three-Dimensional Periodic Orbits in the CR3BP ........................................... 67 4.1.2 Families of Orbits for Lunar South Pole Coverage ........................................ 68 4.1.3 Mission Orbit Selection Criteria ....................................................................... 73 4.2 Optimal Transfers to the Earth-Moon Stable Manifold............................................75 4.2.1 Transfers to a 12-Day L1 Halo Orbit ................................................................. 78 4.2.2 Transfer to a 14-Day L1 Vertical Orbit ............................................................. 87 4.2.3 Transfer to a 14-Day L2 Butterfly Orbit............................................................ 91 5 SUMMARY AND RECOMMENDATIONS.................................................................96 5.1 Summary...................................................................................................................96 5.2 Recommendations for Future Work .........................................................................98 LIST OF REFERENCES...................................................................................................99 vii LIST OF TABLES Table Page Table 4.1 Dynamical and Propulsion Constants................................................................77 Table 4.2 12-Day L1 Halo Orbit Transfer Data Summary .................................................82 Table 4.3 12-Day L1 Halo Orbit Long Transfer Data Summary........................................86 Table 4.4 14-Day L1 Vertical Orbit Transfer Data Summary............................................91 Table 4.5 14-Day L2 Butterfly Orbit Transfer Data Summary ..........................................95 viii LIST OF FIGURES Figure Page Figure 2.1 Geometry in the Restricted Three-Body Problem............................................12 Figure 2.2 Equilibrium Point Locations for the CR3BP....................................................16 Figure 2.3 Geometry of P2-Centered Rotating Frame .......................................................18 Figure 2.4 Linearized L1 Periodic Orbit.............................................................................23 Figure 2.5 Basic Diagram for a Free Final Time Targeting Scheme.................................27 Figure 2.6 Targeting a Perpendicular X-axis Crossing in the CR3BP ..............................30 Figure 2.7 Several L1 Lyapunov Orbits Obtained Via Continuation.................................31 Figure 2.8 Stable and Unstable Manifold at X eq ...............................................................34 Figure 2.9 Global
Load more

Recommended publications
  • PROJECT PENGUIN Robotic Lunar Crater Resource Prospecting VIRGINIA POLYTECHNIC INSTITUTE & STATE UNIVERSITY Kevin T
    PROJECT PENGUIN Robotic Lunar Crater Resource Prospecting VIRGINIA POLYTECHNIC INSTITUTE & STATE UNIVERSITY Kevin T. Crofton Department of Aerospace & Ocean Engineering TEAM LEAD Allison Quinn STUDENT MEMBERS Ethan LeBoeuf Brian McLemore Peter Bradley Smith Amanda Swanson Michael Valosin III Vidya Vishwanathan FACULTY SUPERVISOR AIAA 2018 Undergraduate Spacecraft Design Dr. Kevin Shinpaugh Competition Submission i AIAA Member Numbers and Signatures Ethan LeBoeuf Brian McLemore Member Number: 918782 Member Number: 908372 Allison Quinn Peter Bradley Smith Member Number: 920552 Member Number: 530342 Amanda Swanson Michael Valosin III Member Number: 920793 Member Number: 908465 Vidya Vishwanathan Dr. Kevin Shinpaugh Member Number: 608701 Member Number: 25807 ii Table of Contents List of Figures ................................................................................................................................................................ v List of Tables ................................................................................................................................................................vi List of Symbols ........................................................................................................................................................... vii I. Team Structure ........................................................................................................................................................... 1 II. Introduction ..............................................................................................................................................................
    [Show full text]
  • Similarity Laws of Lunar and Terrestrial Volcanic Flows*
    General Disclaimer One or more of the Following Statements may affect this Document This document has been reproduced from the best copy furnished by the organizational source. It is being released in the interest of making available as much information as possible. This document may contain data, which exceeds the sheet parameters. It was furnished in this condition by the organizational source and is the best copy available. This document may contain tone-on-tone or color graphs, charts and/or pictures, which have been reproduced in black and white. This document is paginated as submitted by the original source. Portions of this document are not fully legible due to the historical nature of some of the material. However, it is the best reproduction available from the original submission. Produced by the NASA Center for Aerospace Information (CASI) SIMILARITY LAWS OF LUNAR AND TERRESTRIAL VOLCANIC FLOWS* S. I. Pai and Y. Hsu Institute for Physical Science and Technology and Aerospace Engineering Department, University of Maryland, College Park Maryland 20742, and ^g15Z021.^,, ^.^,121319 7 ^t , John A. O'Keefe Goddard Space Flight Center, Greenbelt, Maryland 204T° JUN 1977 LP '' RECEIVED ^n NASA STI FACILITY INPUT BRANCH \c. STRACT Alt! ; \Z 1Z A mathematical model for the volcanic flow in planets is proposed.^^ This mathematical model, which is one-dimensional, steady duct flow of a mixture of a gas and small solid particles ( rock), has been analyzed. We v+ 0 apply this model to the lunar and the terrestrial volcanic flows under geo- +oN m U co metrically and dynamically similar conditions.
    [Show full text]
  • Design of Transfers from Earth-Moon L1/L2 Libration Point
    DESIGN OF TRANSFERS FROM EARTH-MOON L1/L2 LIBRATION POINT ORBITS TO A DESTINATION OBJECT A Dissertation Submitted to the Faculty of Purdue University by Masaki Kakoi In Partial Fulfillment of the Requirements for the Degree of Doctor of Philosophy May 2015 Purdue University West Lafayette, Indiana ii P.s iii ACKNOWLEDGMENTS My life has been a great journey. I cannot thank enough to my parents Masahiro and Kayoko for their continuous support. This journey wouldn’t have started without them. I would like to thank my siblings Hiroki, Mayumi, and Fukumi for their patience and kindness. This journey wouldn’t have been the same without them. I would like to thank my wife Lucia for her love and support. This journey won’t be complete without her. I would like to thank Prof. Howell for her patience and guidance. She has had a great influence on my life path. I had a great journey as her student. I would have been lost in space forever without her guidance, navigation, and control. Thank you very much for the priceless experience. Also, I would like to thank my committee members, Prof. Bajaj, Prof. Corless, and Prof. Longuski, for their support and advise. I would like to thank the past, current, and future research group members. We have such talented, diverse, and great people in this group. In addition, I would like to thank friends all over the world. I feel very lucky to have such great friends. I couldn’t have continued my graduate study without the support of the School of Aeronautics and Astronautics and the School of Engineering Education.
    [Show full text]
  • Characterization of Previously Unidentified Lunar Pyroclastic Deposits Using Lunar Reconnaissance Orbiter Camera Data J
    JOURNAL OF GEOPHYSICAL RESEARCH, VOL. 117, E00H25, doi:10.1029/2011JE003893, 2012 Characterization of previously unidentified lunar pyroclastic deposits using Lunar Reconnaissance Orbiter Camera data J. Olaf Gustafson,1 J. F. Bell III,2,3 L. R. Gaddis,4 B. R. Hawke,5 and T. A. Giguere5,6 Received 1 July 2011; revised 31 March 2012; accepted 14 April 2012; published 8 June 2012. [1] We used a Lunar Reconnaissance Orbiter Camera (LROC) global monochrome Wide-angle Camera (WAC) mosaic to conduct a survey of the Moon to search for previously unidentified pyroclastic deposits. Promising locations were examined in detail using LROC multispectral WAC mosaics, high-resolution LROC Narrow Angle Camera (NAC) images, and Clementine multispectral (ultraviolet-visible or UVVIS) data. Out of 47 potential deposits chosen for closer examination, 12 were selected as probable newly identified pyroclastic deposits. Potential pyroclastic deposits were generally found in settings similar to previously identified deposits, including areas within or near mare deposits adjacent to highlands, within floor-fractured craters, and along fissures in mare deposits. However, a significant new finding is the discovery of localized pyroclastic deposits within floor-fractured craters Anderson E and F on the lunar farside, isolated from other known similar deposits. Our search confirms that most major regional and localized low-albedo pyroclastic deposits have been identified on the Moon down to 100 m/pix resolution, and that additional newly identified deposits are likely to be either isolated small deposits or additional portions of discontinuous, patchy deposits. Citation: Gustafson, J. O., J. F. Bell III, L. R. Gaddis, B.
    [Show full text]
  • National Aeronautics and Space Administration) 111 P HC AO,6/MF A01 Unclas CSCL 03B G3/91 49797
    https://ntrs.nasa.gov/search.jsp?R=19780004017 2020-03-22T06:42:54+00:00Z NASA TECHNICAL MEMORANDUM NASA TM-75035 THE LUNAR NOMENCLATURE: THE REVERSE SIDE OF THE MOON (1961-1973) (NASA-TM-75035) THE LUNAR NOMENCLATURE: N78-11960 THE REVERSE SIDE OF TEE MOON (1961-1973) (National Aeronautics and Space Administration) 111 p HC AO,6/MF A01 Unclas CSCL 03B G3/91 49797 K. Shingareva, G. Burba Translation of "Lunnaya Nomenklatura; Obratnaya storona luny 1961-1973", Academy of Sciences USSR, Institute of Space Research, Moscow, "Nauka" Press, 1977, pp. 1-56 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION M19-rz" WASHINGTON, D. C. 20546 AUGUST 1977 A % STANDARD TITLE PAGE -A R.,ott No0... r 2. Government Accession No. 31 Recipient's Caafog No. NASA TIM-75O35 4.-"irl. and Subtitie 5. Repo;t Dote THE LUNAR NOMENCLATURE: THE REVERSE SIDE OF THE August 1977 MOON (1961-1973) 6. Performing Organization Code 7. Author(s) 8. Performing Organizotion Report No. K,.Shingareva, G'. .Burba o 10. Coit Un t No. 9. Perlform:ng Organization Nome and Address ]I. Contract or Grant .SCITRAN NASw-92791 No. Box 5456 13. T yp of Report end Period Coered Santa Barbara, CA 93108 Translation 12. Sponsoring Agiicy Noms ond Address' Natidnal Aeronautics and Space Administration 34. Sponsoring Agency Code Washington,'.D.C. 20546 15. Supplamortary No9 Translation of "Lunnaya Nomenklatura; Obratnaya storona luny 1961-1973"; Academy of Sciences USSR, Institute of Space Research, Moscow, "Nauka" Press, 1977, pp. Pp- 1-56 16. Abstroct The history of naming the details' of the relief on.the near and reverse sides 6f .
    [Show full text]
  • Our Neighbour, the Moon Spaceflight
    Modern Astronomy: Voyage to the Planets Lecture 2 Our neighbour, the Moon and Spaceflight University of Sydney Centre for Continuing Education Autumn 2005 Tonight: ● The Moon: our nearest neighbour ● Principles of spaceflight The Moon Basic data Moon Moon/Earth Mass 0.07349 x 1024 kg 0.0123 Radius 1738.1 km 0.2725 Mean density 3.350 g/cm3 0.607 Gravity 1.62 m/s2 0.165 Semi-major axis 0.3844 x 106 km Period 27.3217 d Orbital inclination (to 5.145o ecliptic) Orbital eccentricity 0.0549 Rotation period 27.3217 d Length of day 29.53 d The Moon has • 1% of the Earth’s mass • 27% of the Earth’s radius • a surface area of 38 million km2: about the size of Africa • surface gravity 1/6 of Earth The Moon is the largest satellite in relation to its primary of any moon in the Solar System, except for Pluto/Charon. The Moon completes its orbit around the Earth once every 27.3 days. However, since the Earth has moved around the Sun in that time, it takes an additional 2.2 days before the Sun reaches the same position in the sky: this is the Earth’s orbit lunar day. As a around the Sun result of this phasing, the same Moon has made New moon one complete revolution around side of the moon the Earth is always facing the Earth. Synodic month 29.5 days Sidereal month Moon’s orbit 27.3 days around Earth New moon Earth The moon always keeps the same hemisphere turned towards the Earth, so there is a side we never see: the far side.
    [Show full text]
  • Establishing a Lunar Outpost an Interactive Qualifying Project Report
    Project Number: MH1158 Establishing a Lunar Outpost An Interactive Qualifying Project Report Submitted to the faculty of the WORCESTER POLYTECHNIC INSTITUTE In partial fulfillment of the requirements for the Degree of Bachelor of Science By ___________________________________ Ian Ball ___________________________________ Joseph Bauer ___________________________________ Andrew Dawson ___________________________________ Stephen Jenkinson <Date> ___________________________________ Professor Mayer Humi <Section> ABSTRACT Our project examined the feasibility of establishing a lunar outpost. This included analysis of Earth to moon transportation, sustainability, uses for the moon, and the potential effects on humanity. We determined that the moon is a viable option for private companies to explore due to the opportunities in establishing life-supporting systems, harvesting fuel for alternative energy, and experimental studies. The lunar outpost would have its greatest effect on humanity by providing alternative energy sources and detection of near earth objects. ii | P a g e TABLE OF CONTENTS Abstract ........................................................................................................................................... ii Table of Tables ............................................................................................................................... v Executive Summary ....................................................................................................................... vi Introduction ....................................................................................................................................
    [Show full text]
  • Increasing Access and Capabilities of Cubesats for Investigation of Earth Trojan Asteroids
    Increasing Access and Capabilities of CubeSats for Investigation of Earth Trojan Asteroids Paul J Sturmer A dissertation submitted in partial fulfillment of the requirements for the degree of Doctor of Philosophy University of Washington 2020 Reading Committee: Robert Winglee, Chair Marcel den Nijs Paul Wiggins Program Authorized to Offer Degree: Physics © Copyright 2020 Paul J Sturmer University of Washington Abstract Increasing Access and Capabilities of CubeSats for Investigation of Earth Trojan Asteroids Paul J Sturmer Chair of the Supervisory Committee: Robert Winglee Earth and Space Sciences This thesis develops the requirements of a low-cost spacecraft mission to the Sun-Earth Lagrange point L4 and L5 to search for Earth Trojan asteroids, and develops and demonstrates a specialized communication system needed to facilitate such a mission. Asteroids serve as time capsules into the historical past of our solar system, and have been critical components to our understanding of the formation and evolution of our solar system. A subset of Earth co-orbital asteroids, Earth Trojans, being close to our home can help us understand things like the conditions present during Earth’s initial formation or the Moon-Earth formation impact theory. Considering there is only one identified Earth Trojan asteroid, 2010 TK7, and the fact that numerical analysis and additional searches support a population of at least one hundred Trojans, a dedicated mission is well warranted. With the Earth Trojan asteroid regions particularly difficult to view when using Earth-based telescopes, an alternative approach is described herein: send a small low-cost spacecraft, called a CubeSat, directly to these regions for in-situ imaging.
    [Show full text]
  • Dual Lunar Ice Analyzers Supporting Next-Gen Astronautics
    AIAA 2018 Undergraduate Spacecraft Design Competition Project DIANA: Dual Lunar Ice Analyzers Supporting Next-Gen Astronautics Design Proposal by ASCENSION INDUSTRIES California Polytechnic State University, Pomona Dr. Donald Edberg Will Morris Team Advisor Team Lead AIAA Member # 22972 AIAA Member # 920006 Max Feagle Thomas Fergus Samuel Kim Deputy Team Lead Lead Guidance Engineer Lead Structural Engineer AIAA Member # 922677 AIAA Member # 920792 AIAA Member # 922679 Marco Fileccia Josh Kennedy Damian Magaña Lead Component Designer Lead Thermal Analyst Lead Propulsion Engineer AIAA Member # 922643 AIAA Member # 922673 AIAA Member # 922683 ii Extended Executive Summary Lunar water is instrumental for colonization of the Earth’s nearest celestial neighbor. Due to its weight, it would be economically infeasible to lift significant quantities of this essential resource into Earth orbit and beyond. A lunar colony becomes a much more feasible endeavor if there exist resources on the Moon that can be utilized in-situ. Missions such as NASA’s Lunar Reconnaissance Orbiter (LRO) and India’s Chandrayaan-1 have provided enticing evidence of lunar water ice present in the lunar poles. The objective of Project DIANA is to seek out potential locations of this valuable resource, confirm its existence, and to do so cost-effectively, under budget and within schedule. This mission’s success would provide a crucial stepping stone in the ultimate goal of establishing a Martian colony. The driving requirements for our mission design included the accurate quantification of water in two different lunar craters, overall mission cost under $500 M (FY17), maximized science return, and mission completion by the end of 2024.
    [Show full text]
  • Dare Mission Design: Low Rfi Observations from a Low-Altitude Frozen Lunar Orbit
    (Preprint) AAS 17-333 DARE MISSION DESIGN: LOW RFI OBSERVATIONS FROM A LOW-ALTITUDE FROZEN LUNAR ORBIT Laura Plice*, Ken Galal†, and Jack O. Burns‡ The Dark Ages Radio Experiment (DARE) seeks to study the cosmic Dark Ages approximately 80 to 420 million years after the Big Bang. Observations require truly quiet radio conditions, shielded from Sun and Earth electromagnetic (EM) emissions, on the far side of the Moon. DARE’s science orbit is a frozen orbit with respect to lunar gravitational perturbations. The altitude and orientation of the orbit remain nearly fixed indefinitely, maximizing science time without the need for maintenance. DARE’s observation targets avoid the galactic center and enable investigation of the universe’s first stars and galaxies. INTRODUCTION The Dark Ages Radio Experiment (DARE), currently proposed for NASA’s 2016 Astrophys- ics Medium Explorer (MIDEX) announcement of opportunity with a launch date in August 2023, seeks to study the universe in the cosmic Dark Ages approximately 80 to 420 million years after the Big Bang.1,2 DARE’s observations require conditions truly free of radio frequency interfer- ence (RFI), shielded from Sun and Earth EM emissions, a zone which is only available on the far side of the Moon. To maximize time in the best science conditions, DARE requires a low, equa- torial lunar orbit. For DARE, diffraction effects define quiet cones in the anti-Earth and anti-Sun sides of the Moon. In the science phase, the DARE satellite passes through the Earth-quiet cone on every orbit and simultaneously through the Sun shadow for 0 to 100% of every pass (Prime Science observations).
    [Show full text]
  • Morphology and Distribution of Volcanic Vents in the Orientale Basin from Chandrayaan-1 Moon Mineralogy Mapper (M3) Data
    41st Lunar and Planetary Science Conference (2010) 1032.pdf MORPHOLOGY AND DISTRIBUTION OF VOLCANIC VENTS IN THE ORIENTALE BASIN FROM CHANDRAYAAN-1 MOON MINERALOGY MAPPER (M3) DATA. J. Head1, C. Pieters1, M. Staid2, J. Mus- tard1, L. Taylor3, T. McCord4, P. Isaacson1, R. Klima1, N. Petro5, R. Clark6, J. Nettles1, J. Whitten1 and the M3 Team. 1Brown Univ., Providence RI 02912; 2PSI, Tucson AZ; 3Univ. Tenn., Knoxville TN 37996; 4BFC, Winthrop, WA; 5NASA GSFC, Greenbelt, MD 20771; 6USGS, Denver CO 80227 ([email protected]). Introduction and Background: One of the most radial ejecta deposits (the Hevelius Formation) and a full fundamental questions in the geological and thermal range of deposits within the basin interior, including the evolution of the Moon is the nature and history of man- Montes Rook Formation (MRF), lying between the CR tle melting and its relationship to the formation and and the OR, and the Maunder Formation, lying within the evolution of lunar multi-ringed basins. Mare volcanic OR and divided into two facies, an outer corrugated facies deposits provide evidence for the nature, magnitude and occurring mostly between the OR and the edge of the in- composition of mantle melting as a function of space ner depression, and the smooth or plains facies, lying pre- and time [1]. Many argue that mantle partial melts are dominantly within the inner depression. All of these rings derived from depths well below the influence of multi- and units have been interpreted to have formed as part of ringed basin impact events [1], while others postulate the Orientale basin event, with the Hevelius and Montes that the formation of these basins can cause mantle per- Rook Formation interpreted as variants of basin ejecta, turbations that are more directly linked to the genera- and the Maunder Formation commonly interpreted as im- tion ascent and eruption of mare basalts [2,3].
    [Show full text]
  • LPSC 41-M3 Orientale-Volcanic Vents-Final(O)
    MORPHOLOGY AND DISTRIBUTION OF VOLCANIC VENTS IN THE ORIENTALE BASIN FROM CHANDRAYAAN-1 MOON MINERALOGY MAPPER (M3) DATA. J. Head1, C. Pieters1, M. Staid2, J. Mus- tard1, L. Taylor3, T. McCord4, P. Isaacson1, R. Klima1, N. Petro5, R. Clark6, J. Nettles1, J. Whitten1 and the M3 Team. 1Brown Univ., Providence RI 02912; 2PSI, Tucson AZ; 3Univ. Tenn., Knoxville TN 37996; 4BFC, Winthrop, WA; 5NASA GSFC, Greenbelt, MD 20771; 6USGS, Denver CO 80227 ([email protected]). Introduction and Background: One of the most radial ejecta deposits (the Hevelius Formation) and a full fundamental questions in the geological and thermal range of deposits within the basin interior, including the evolution of the Moon is the nature and history of man- Montes Rook Formation (MRF), lying between the CR tle melting and its relationship to the formation and and the OR, and the Maunder Formation, lying within the evolution of lunar multi-ringed basins. Mare volcanic OR and divided into two facies, an outer corrugated facies deposits provide evidence for the nature, magnitude and occurring mostly between the OR and the edge of the in- composition of mantle melting as a function of space ner depression, and the smooth or plains facies, lying pre- and time [1]. Many argue that mantle partial melts are dominantly within the inner depression. All of these rings derived from depths well below the influence of multi- and units have been interpreted to have formed as part of ringed basin impact events [1], while others postulate the Orientale basin event, with the Hevelius and Montes that the formation of these basins can cause mantle per- Rook Formation interpreted as variants of basin ejecta, turbations that are more directly linked to the genera- and the Maunder Formation commonly interpreted as im- tion ascent and eruption of mare basalts [2,3].
    [Show full text]