Spatio-Temporal Characteristics for Moon-Based Earth Observations
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Multi-Body Trajectory Design Strategies Based on Periapsis Poincaré Maps
MULTI-BODY TRAJECTORY DESIGN STRATEGIES BASED ON PERIAPSIS POINCARÉ MAPS A Dissertation Submitted to the Faculty of Purdue University by Diane Elizabeth Craig Davis In Partial Fulfillment of the Requirements for the Degree of Doctor of Philosophy August 2011 Purdue University West Lafayette, Indiana ii To my husband and children iii ACKNOWLEDGMENTS I would like to thank my advisor, Professor Kathleen Howell, for her support and guidance. She has been an invaluable source of knowledge and ideas throughout my studies at Purdue, and I have truly enjoyed our collaborations. She is an inspiration to me. I appreciate the insight and support from my committee members, Professor James Longuski, Professor Martin Corless, and Professor Daniel DeLaurentis. I would like to thank the members of my research group, past and present, for their friendship and collaboration, including Geoff Wawrzyniak, Chris Patterson, Lindsay Millard, Dan Grebow, Marty Ozimek, Lucia Irrgang, Masaki Kakoi, Raoul Rausch, Matt Vavrina, Todd Brown, Amanda Haapala, Cody Short, Mar Vaquero, Tom Pavlak, Wayne Schlei, Aurelie Heritier, Amanda Knutson, and Jeff Stuart. I thank my parents, David and Jeanne Craig, for their encouragement and love throughout my academic career. They have cheered me on through many years of studies. I am grateful for the love and encouragement of my husband, Jonathan. His never-ending patience and friendship have been a constant source of support. Finally, I owe thanks to the organizations that have provided the funding opportunities that have supported me through my studies, including the Clare Booth Luce Foundation, Zonta International, and Purdue University and the School of Aeronautics and Astronautics through the Graduate Assistance in Areas of National Need and the Purdue Forever Fellowships. -
Perturbation Theory in Celestial Mechanics
Perturbation Theory in Celestial Mechanics Alessandra Celletti Dipartimento di Matematica Universit`adi Roma Tor Vergata Via della Ricerca Scientifica 1, I-00133 Roma (Italy) ([email protected]) December 8, 2007 Contents 1 Glossary 2 2 Definition 2 3 Introduction 2 4 Classical perturbation theory 4 4.1 The classical theory . 4 4.2 The precession of the perihelion of Mercury . 6 4.2.1 Delaunay action–angle variables . 6 4.2.2 The restricted, planar, circular, three–body problem . 7 4.2.3 Expansion of the perturbing function . 7 4.2.4 Computation of the precession of the perihelion . 8 5 Resonant perturbation theory 9 5.1 The resonant theory . 9 5.2 Three–body resonance . 10 5.3 Degenerate perturbation theory . 11 5.4 The precession of the equinoxes . 12 6 Invariant tori 14 6.1 Invariant KAM surfaces . 14 6.2 Rotational tori for the spin–orbit problem . 15 6.3 Librational tori for the spin–orbit problem . 16 6.4 Rotational tori for the restricted three–body problem . 17 6.5 Planetary problem . 18 7 Periodic orbits 18 7.1 Construction of periodic orbits . 18 7.2 The libration in longitude of the Moon . 20 1 8 Future directions 20 9 Bibliography 21 9.1 Books and Reviews . 21 9.2 Primary Literature . 22 1 Glossary KAM theory: it provides the persistence of quasi–periodic motions under a small perturbation of an integrable system. KAM theory can be applied under quite general assumptions, i.e. a non– degeneracy of the integrable system and a diophantine condition of the frequency of motion. -
On Optimal Two-Impulse Earth–Moon Transfers in a Four-Body Model
Noname manuscript No. (will be inserted by the editor) On Optimal Two-Impulse Earth–Moon Transfers in a Four-Body Model F. Topputo Received: date / Accepted: date Abstract In this paper two-impulse Earth–Moon transfers are treated in the restricted four-body problem with the Sun, the Earth, and the Moon as primaries. The problem is formulated with mathematical means and solved through direct transcription and multiple shooting strategy. Thousands of solutions are found, which make it possible to frame known cases as special points of a more general picture. Families of solutions are defined and characterized, and their features are discussed. The methodology described in this paper is useful to perform trade-off analyses, where many solutions have to be produced and assessed. Keywords Earth–Moon transfer low-energy transfer ballistic capture trajectory optimization · · · · restricted three-body problem restricted four-body problem · 1 Introduction The search for trajectories to transfer a spacecraft from the Earth to the Moon has been the subject of countless works. The Hohmann transfer represents the easiest way to perform an Earth–Moon transfer. This requires placing the spacecraft on an ellipse having the perigee on the Earth parking orbit and the apogee on the Moon orbit. By properly switching the gravitational attractions along the orbit, the spacecraft’s motion is governed by only the Earth for most of the transfer, and by only the Moon in the final part. More generally, the patched-conics approximation relies on a Keplerian decomposition of the solar system dynamics (Battin 1987). Although from a practical point of view it is desirable to deal with analytical solutions, the two-body problem being integrable, the patched-conics approximation inherently involves hyperbolic approaches upon arrival. -
Wobbling Stars and Planets in This Activity, You
Activity: Wobbling Stars and Planets In this activity, you will investigate the effect of the relative masses and distances of objects that are in orbit around a star or planet. The most common understanding of how the planets orbit around the Sun is that the Sun is stationary while the planets revolve around the Sun. That is not quite true and is a little more complicated. PBS An important parameter when considering orbits is the center of mass. The concept of the center of mass is that of an average of the masses factored by their distances from one another. This is also commonly referred to as the center of gravity. For example, the balancing of a ETIC seesaw about a pivot point demonstrates the center of mass of two objects of different masses. Another important parameter to consider is the barycenter. The barycenter is the center of mass of two or more bodies that are orbiting each other, and is the point around which both of them orbit. When the two bodies have similar masses, the barycenter may be located between NASA the two bodies (outside of either of bodies) and both objects will follow an orbit around the center of mass. This is the case for a system such as the Sun and Jupiter. In the case where the two objects have very different masses, the center of mass and barycenter may be located within the more massive body. This is the case for the Earth-Moon system. scienceprojectideasforkids.com Classroom Activity Part 1 Materials • Wooden skewers 1. -
Applications of Solar Wind Particle Impact Simulations at Lunar Magnetic Anomalies to the Study of Lunar Swirls
47th Lunar and Planetary Science Conference (2016) 2648.pdf APPLICATIONS OF SOLAR WIND PARTICLE IMPACT SIMULATIONS AT LUNAR MAGNETIC ANOMALIES TO THE STUDY OF LUNAR SWIRLS. C. J. Tai Udovicic1, G. Y. Kramer2, and E. M. Harnett3, 1Dept of Earth Sciences, University of Toronto, 22 Russell St, Toronto, ON, Canada, ([email protected]), 2Lunar and Planetary Institute, 3600 Bay Area Bvld, Houston, TX, ([email protected]), 3University of Washington, Earth and Space Sciences, Seattle, WA ([email protected]). Introduction: Lunar swirls are high albedo features highlands often appear to have swirl-like anomalies due that exhibit low spectral maturity. They have been to their complicated topography. To mitigate this, we identified at various sites on the Moon, and all coincide generated a slope map from the WAC GLD100 (SLP), with a lunar magnetic anomaly (magnomaly) [1], which we overlayed with the WAC 643 nm normalized although not all magnomalies have an identifiable swirl. reflectance image to distinguish high albedo swirls from The leading hypothesis for lunar swirl origin is high albedo slopes. Even so, after one pass of the region, presented in [2] as magnetic field standoff of the solar only about half of the swirls could be detected with this wind which causes uneven space weathering at the swirl method alone. The remaining half were found after surface. This hypothesis fails to explain why lunar using particle simulations as a guide. swirls are observed at some but not all of the magnetic Solar wind particle tracking simulations: We anomalies present on the Moon. To investigate the solar used the 2D solar wind particle tracking simulation wind standoff hypothesis further and to improve swirl presented in [2]. -
Apollo 17 Index: 70 Mm, 35 Mm, and 16 Mm Photographs
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) Preparation, Scanning, Editing, and Conversion to Adobe Portable Document Format (PDF) by: Ronald A. Wells University of California Berkeley, CA 94720 May 2000 A P O L L O 1 7 I N D E X 7 0 m m, 3 5 m m, A N D 1 6 m m P H O T O G R A P H S M a p p i n g S c i e n c e s B r a n c h N a t i o n a l A e r o n a u t i c s a n d S p a c e A d m i n i s t r a t i o n J o h n s o n S p a c e C e n t e r H o u s t o n, T e x a s APPROVED: Michael C . -
THE BINARY COLLISION APPROXIMATION: Iliiilms BACKGROUND and INTRODUCTION Mark T
O O i, j / O0NF-9208146--1 DE92 040887 Invited paper for Proceedings of the International Conference on Computer Simulations of Radiation Effects in Solids, Hahn-Meitner Institute Berlin Berlin, Germany August 23-28 1992 The submitted manuscript has been authored by a contractor of the U.S. Government under contract No. DE-AC05-84OR214O0. Accordingly, the U S. Government retains a nonexclusive, royalty* free licc-nc to publish or reproduce the published form of uiii contribution, or allow othen to do jo, for U.S. Government purposes." THE BINARY COLLISION APPROXIMATION: IliiilMS BACKGROUND AND INTRODUCTION Mark T. Robinson >._« « " _>i 8 « g i. § 8 " E 1.2 .§ c « •o'c'lf.S8 ° °% as SOLID STATE DIVISION OAK RIDGE NATIONAL LABORATORY Managed by MARTIN MARIETTA ENERGY SYSTEMS, INC. Under Contract No. DE-AC05-84OR21400 § g With the ••g ^ U. S. DEPARTMENT OF ENERGY OAK RIDGE, TENNESSEE August 1992 'g | .11 DISTRIBUTION OP THIS COOL- ::.•:•! :•' !S Ui^l J^ THE BINARY COLLISION APPROXIMATION: BACKGROUND AND INTRODUCTION Mark T. Robinson Solid State Division, Oak Ridge National Laboratory, Oak Ridge, Tennessee 37831-6032, U. S. A. ABSTRACT The binary collision approximation (BCA) has long been used in computer simulations of the interactions of energetic atoms with solid targets, as well as being the basis of most analytical theory in this area. While mainly a high-energy approximation, the BCA retains qualitative significance at low energies and, with proper formulation, gives useful quantitative information as well. Moreover, computer simulations based on the BCA can achieve good statistics in many situations where those based on full classical dynamical models require the most advanced computer hardware or are even impracticable. -
Exploring the Orbital Evolution of Planetary Systems
Exploring the orbital evolution of planetary systems Tabar´e Gallardo∗ Instituto de F´ısica, Facultad de Ciencias, Udelar. (Dated: January 22, 2017) The aim of this paper is to encourage the use of orbital integrators in the classroom to discover and understand the long term dynamical evolution of systems of orbiting bodies. We show how to perform numerical simulations and how to handle the output data in order to reveal the dynamical mechanisms that dominate the evolution of arbitrary planetary systems in timescales of millions of years using a simple but efficient numerical integrator. Trough some examples we reveal the fundamental properties of the planetary systems: the time evolution of the orbital elements, the free and forced modes that drive the oscillations in eccentricity and inclination, the fundamental frequencies of the system, the role of the angular momenta, the invariable plane, orbital resonances and the Kozai-Lidov mechanism. To be published in European Journal of Physics. 2 I. INTRODUCTION With few exceptions astronomers cannot make experiments, they are limited to observe the universe. The laboratory for the astronomer usually takes the form of computer simulations. This is the most important instrument for the study of the dynamical behavior of gravitationally interacting bodies. A planetary system, for example, evolves mostly due to gravitation acting over very long timescales generating what is called a secular evolution. This secular evolution can be deduced analytically by means of the theory of perturbations, but can also be explored in the classroom by means of precise numerical integrators. Some facilities exist to visualize and experiment with the gravitational interactions between massive bodies1–3. -
Strategy for Optimal, Long-Term Stationkeeping of Libration Point Orbits in the Earth-Moon System
Strategy for Optimal, Long-Term Stationkeeping of Libration Point Orbits in the Earth-Moon System Thomas A. Pavlak∗ and Kathleen C. Howelly Purdue University, West Lafayette, IN, 47907-2045, USA In an effort to design low-cost maneuvers that reliably maintain unstable libration point orbits in the Earth-Moon system for long durations, an existing long-term stationkeeping strategy is augmented to compute locally optimal maneuvers that satisfy end-of-mission constraints downstream. This approach reduces stationkeeping costs for planar and three- dimensional orbits in dynamical systems of varying degrees of fidelity and demonstrates the correlation between optimal maneuver direction and the stable mode observed during ARTEMIS mission operations. An optimally-constrained multiple shooting strategy is also introduced that is capable of computing near optimal maintenance maneuvers without formal optimization software. I. Introduction Most orbits in the vicinity of collinear libration points are inherently unstable and, consequently, sta- tionkeeping strategies are a critical component of mission design and operations in these chaotic dynamical regions. Stationkeeping is particularly important for libration point missions in the Earth-Moon system since fast time scales require that orbit maintenance maneuvers be implemented approximately once per week. Assuming that acceptable orbit determination solutions require 3-4 days to obtain, stationkeeping ∆V planning activities must be quick, efficient, and effective. Furthermore, the duration of a libration point mission is often dictated by the remaining propellant so a key capability is maintenance maneuvers that are low-cost. Thus, to accommodate a likely increase in future operations in the vicinity of the Earth-Moon libration points, fast, reliable algorithms capable of rapidly computing low-cost stationkeeping maneuvers, with little or no human interaction, are critical. -
Orbital Mechanics
Orbital Mechanics Part 1 Orbital Forces Why a Sat. remains in orbit ? Bcs the centrifugal force caused by the Sat. rotation around earth is counter- balanced by the Earth's Pull. Kepler’s Laws The Satellite (Spacecraft) which orbits the earth follows the same laws that govern the motion of the planets around the sun. J. Kepler (1571-1630) was able to derive empirically three laws describing planetary motion I. Newton was able to derive Keplers laws from his own laws of mechanics [gravitation theory] Kepler’s 1st Law (Law of Orbits) The path followed by a Sat. (secondary body) orbiting around the primary body will be an ellipse. The center of mass (barycenter) of a two-body system is always centered on one of the foci (earth center). Kepler’s 1st Law (Law of Orbits) The eccentricity (abnormality) e: a 2 b2 e a b- semiminor axis , a- semimajor axis VIN: e=0 circular orbit 0<e<1 ellip. orbit Orbit Calculations Ellipse is the curve traced by a point moving in a plane such that the sum of its distances from the foci is constant. Kepler’s 2nd Law (Law of Areas) For equal time intervals, a Sat. will sweep out equal areas in its orbital plane, focused at the barycenter VIN: S1>S2 at t1=t2 V1>V2 Max(V) at Perigee & Min(V) at Apogee Kepler’s 3rd Law (Harmonic Law) The square of the periodic time of orbit is proportional to the cube of the mean distance between the two bodies. a 3 n 2 n- mean motion of Sat. -
Orbital Resonance and Solar Cycles by P.A.Semi
Orbital resonance and Solar cycles by P.A.Semi Abstract We show resonance cycles between most planets in Solar System, of differing quality. The most precise resonance - between Earth and Venus, which not only stabilizes orbits of both planets, locks planet Venus rotation in tidal locking, but also affects the Sun: This resonance group (E+V) also influences Sunspot cycles - the position of syzygy between Earth and Venus, when the barycenter of the resonance group most closely approaches the Sun and stops for some time, relative to Jupiter planet, well matches the Sunspot cycle of 11 years, not only for the last 400 years of measured Sunspot cycles, but also in 1000 years of historical record of "severe winters". We show, how cycles in angular momentum of Earth and Venus planets match with the Sunspot cycle and how the main cycle in angular momentum of the whole Solar system (854-year cycle of Jupiter/Saturn) matches with climatologic data, assumed to show connection with Solar output power and insolation. We show the possible connections between E+V events and Solar global p-Mode frequency changes. We futher show angular momentum tables and charts for individual planets, as encoded in DE405 and DE406 ephemerides. We show, that inner planets orbit on heliocentric trajectories whereas outer planets orbit on barycentric trajectories. We further TRY to show, how planet positions influence individual Sunspot groups, in SOHO and GONG data... [This work is pending...] Orbital resonance Earth and Venus The most precise orbital resonance is between Earth and Venus planets. These planets meet 5 times during 8 Earth years and during 13 Venus years. -
Simulations of Particle Impact at Lunar Magnetic Anomalies and Comparison with Spectral Observations
Simulations of Particle Impact at Lunar Magnetic Anomalies and Comparison with Spectral Observations Erika Harnett∗ Department of Earth and Space Science, University of Washington,Seattle, WA 98195-1310, USA Georgiana Kramer Lunar and Planetary Institute, 3600 Bay Area Blvd, Houston, TX 77058, USA Christian Udovicic Department of Physics, University of Toronto, 60 St George St,Toronto, ON M5S 1A7, Canada Ruth Bamford RAL Space, STFC, Rutherford Appleton Laboratory,Chilton, Didcot Ox11 0Qx, UK (Dated: November 5, 2018) Ever since the Apollo era, a question has remained as to the origin of the lunar swirls (high albedo regions coincident with the regions of surface magnetization). Different processes have been proposed for their origin. In this work we test the idea that the lunar swirls have a higher albedo relative to surrounding regions because they deflect incoming solar wind particles that would otherwise darken the surface. 3D particle tracking is used to estimate the influence of five lunar magnetic anomalies on incoming solar wind. The regions investigated include Mare Ingenii, Gerasimovich, Renier Gamma, Northwest of Apollo and Marginis. Both protons and electrons are tracked as they interact with the anomalous magnetic field and impact maps are calculated. The impact maps are then compared to optical observations and comparisons are made between the maxima and minima in surface fluxes and the albedo and optical maturity of the regions. Results show deflection of slow to typical solar wind particles on a larger scale than the fine scale optical, swirl, features. It is found that efficiency of a particular anomaly for deflection of incoming particles does not only scale directly with surface magnetic field strength, but also is a function of the coherence of the magnetic field.