Maneuver Estimation Model for Relative Orbit Determination
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Orbit Determination Methods and Techniques
PROJECTE FINAL DE CARRERA (PFC) GEOSAR Mission: Orbit Determination Methods and Techniques Marc Fernàndez Uson PFC Advisor: Prof. Antoni Broquetas Ibars May 2016 PROJECTE FINAL DE CARRERA (PFC) GEOSAR Mission: Orbit Determination Methods and Techniques Marc Fernàndez Uson ABSTRACT ABSTRACT Multiple applications such as land stability control, natural risks prevention or accurate numerical weather prediction models from water vapour atmospheric mapping would substantially benefit from permanent radar monitoring given their fast evolution is not observable with present Low Earth Orbit based systems. In order to overcome this drawback, GEOstationary Synthetic Aperture Radar missions (GEOSAR) are presently being studied. GEOSAR missions are based on operating a radar payload hosted by a communication satellite in a geostationary orbit. Due to orbital perturbations, the satellite does not follow a perfectly circular orbit, but has a slight eccentricity and inclination that can be used to form the synthetic aperture required to obtain images. Several sources affect the along-track phase history in GEOSAR missions causing unwanted fluctuations which may result in image defocusing. The main expected contributors to azimuth phase noise are orbit determination errors, radar carrier frequency drifts, the Atmospheric Phase Screen (APS), and satellite attitude instabilities and structural vibration. In order to obtain an accurate image of the scene after SAR processing, the range history of every point of the scene must be known. This fact requires a high precision orbit modeling and the use of suitable techniques for atmospheric phase screen compensation, which are well beyond the usual orbit determination requirement of satellites in GEO orbits. The other influencing factors like oscillator drift and attitude instability, vibration, etc., must be controlled or compensated. -
Stark Broadening of Spectral Lines in Plasmas
atoms Stark Broadening of Spectral Lines in Plasmas Edited by Eugene Oks Printed Edition of the Special Issue Published in Atoms www.mdpi.com/journal/atoms Stark Broadening of Spectral Lines in Plasmas Stark Broadening of Spectral Lines in Plasmas Special Issue Editor Eugene Oks MDPI • Basel • Beijing • Wuhan • Barcelona • Belgrade Special Issue Editor Eugene Oks Auburn University USA Editorial Office MDPI St. Alban-Anlage 66 4052 Basel, Switzerland This is a reprint of articles from the Special Issue published online in the open access journal Atoms (ISSN 2218-2004) in 2018 (available at: https://www.mdpi.com/journal/atoms/special issues/ stark broadening plasmas) For citation purposes, cite each article independently as indicated on the article page online and as indicated below: LastName, A.A.; LastName, B.B.; LastName, C.C. Article Title. Journal Name Year, Article Number, Page Range. ISBN 978-3-03897-455-0 (Pbk) ISBN 978-3-03897-456-7 (PDF) Cover image courtesy of Eugene Oks. c 2018 by the authors. Articles in this book are Open Access and distributed under the Creative Commons Attribution (CC BY) license, which allows users to download, copy and build upon published articles, as long as the author and publisher are properly credited, which ensures maximum dissemination and a wider impact of our publications. The book as a whole is distributed by MDPI under the terms and conditions of the Creative Commons license CC BY-NC-ND. Contents About the Special Issue Editor ...................................... vii Preface to ”Stark Broadening of Spectral Lines in Plasmas” ..................... ix Eugene Oks Review of Recent Advances in the Analytical Theory of Stark Broadening of Hydrogenic Spectral Lines in Plasmas: Applications to Laboratory Discharges and Astrophysical Objects Reprinted from: Atoms 2018, 6, 50, doi:10.3390/atoms6030050 ................... -
Orbit Determination Using Modern Filters/Smoothers and Continuous Thrust Modeling
Orbit Determination Using Modern Filters/Smoothers and Continuous Thrust Modeling by Zachary James Folcik B.S. Computer Science Michigan Technological University, 2000 SUBMITTED TO THE DEPARTMENT OF AERONAUTICS AND ASTRONAUTICS IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF MASTER OF SCIENCE IN AERONAUTICS AND ASTRONAUTICS AT THE MASSACHUSETTS INSTITUTE OF TECHNOLOGY JUNE 2008 © 2008 Massachusetts Institute of Technology. All rights reserved. Signature of Author:_______________________________________________________ Department of Aeronautics and Astronautics May 23, 2008 Certified by:_____________________________________________________________ Dr. Paul J. Cefola Lecturer, Department of Aeronautics and Astronautics Thesis Supervisor Certified by:_____________________________________________________________ Professor Jonathan P. How Professor, Department of Aeronautics and Astronautics Thesis Advisor Accepted by:_____________________________________________________________ Professor David L. Darmofal Associate Department Head Chair, Committee on Graduate Students 1 [This page intentionally left blank.] 2 Orbit Determination Using Modern Filters/Smoothers and Continuous Thrust Modeling by Zachary James Folcik Submitted to the Department of Aeronautics and Astronautics on May 23, 2008 in Partial Fulfillment of the Requirements for the Degree of Master of Science in Aeronautics and Astronautics ABSTRACT The development of electric propulsion technology for spacecraft has led to reduced costs and longer lifespans for certain -
A Basic Requirement for Studying the Heavens Is Determining Where In
Abasic requirement for studying the heavens is determining where in the sky things are. To specify sky positions, astronomers have developed several coordinate systems. Each uses a coordinate grid projected on to the celestial sphere, in analogy to the geographic coordinate system used on the surface of the Earth. The coordinate systems differ only in their choice of the fundamental plane, which divides the sky into two equal hemispheres along a great circle (the fundamental plane of the geographic system is the Earth's equator) . Each coordinate system is named for its choice of fundamental plane. The equatorial coordinate system is probably the most widely used celestial coordinate system. It is also the one most closely related to the geographic coordinate system, because they use the same fun damental plane and the same poles. The projection of the Earth's equator onto the celestial sphere is called the celestial equator. Similarly, projecting the geographic poles on to the celest ial sphere defines the north and south celestial poles. However, there is an important difference between the equatorial and geographic coordinate systems: the geographic system is fixed to the Earth; it rotates as the Earth does . The equatorial system is fixed to the stars, so it appears to rotate across the sky with the stars, but of course it's really the Earth rotating under the fixed sky. The latitudinal (latitude-like) angle of the equatorial system is called declination (Dec for short) . It measures the angle of an object above or below the celestial equator. The longitud inal angle is called the right ascension (RA for short). -
Statistical Orbit Determination
Preface The modem field of orbit determination (OD) originated with Kepler's inter pretations of the observations made by Tycho Brahe of the planetary motions. Based on the work of Kepler, Newton was able to establish the mathematical foundation of celestial mechanics. During the ensuing centuries, the efforts to im prove the understanding of the motion of celestial bodies and artificial satellites in the modem era have been a major stimulus in areas of mathematics, astronomy, computational methodology and physics. Based on Newton's foundations, early efforts to determine the orbit were focused on a deterministic approach in which a few observations, distributed across the sky during a single arc, were used to find the position and velocity vector of a celestial body at some epoch. This uniquely categorized the orbit. Such problems are deterministic in the sense that they use the same number of independent observations as there are unknowns. With the advent of daily observing programs and the realization that the or bits evolve continuously, the foundation of modem precision orbit determination evolved from the attempts to use a large number of observations to determine the orbit. Such problems are over-determined in that they utilize far more observa tions than the number required by the deterministic approach. The development of the digital computer in the decade of the 1960s allowed numerical approaches to supplement the essentially analytical basis for describing the satellite motion and allowed a far more rigorous representation of the force models that affect the motion. This book is based on four decades of classroom instmction and graduate- level research. -
Multiple Solutions for Asteroid Orbits: Computational Procedure and Applications
A&A 431, 729–746 (2005) Astronomy DOI: 10.1051/0004-6361:20041737 & c ESO 2005 Astrophysics Multiple solutions for asteroid orbits: Computational procedure and applications A. Milani1,M.E.Sansaturio2,G.Tommei1, O. Arratia2, and S. R. Chesley3 1 Dipartimento di Matematica, Università di Pisa, via Buonarroti 2, 56127 Pisa, Italy e-mail: [milani;tommei]@mail.dm.unipi.it 2 E.T.S. de Ingenieros Industriales, University of Valladolid Paseo del Cauce 47011 Valladolid, Spain e-mail: [meusan;oscarr]@eis.uva.es 3 Jet Propulsion Laboratory, 4800 Oak Grove Drive, CA-91109 Pasadena, USA e-mail: [email protected] Received 27 July 2004 / Accepted 20 October 2004 Abstract. We describe the Multiple Solutions Method, a one-dimensional sampling of the six-dimensional orbital confidence region that is widely applicable in the field of asteroid orbit determination. In many situations there is one predominant direction of uncertainty in an orbit determination or orbital prediction, i.e., a “weak” direction. The idea is to record Multiple Solutions by following this, typically curved, weak direction, or Line Of Variations (LOV). In this paper we describe the method and give new insights into the mathematics behind this tool. We pay particular attention to the problem of how to ensure that the coordinate systems are properly scaled so that the weak direction really reflects the intrinsic direction of greatest uncertainty. We also describe how the multiple solutions can be used even in the absence of a nominal orbit solution, which substantially broadens the realm of applications. There are numerous applications for multiple solutions; we discuss a few problems in asteroid orbit determination and prediction where we have had good success with the method. -
Astrodynamic Fundamentals for Deflecting Hazardous Near-Earth Objects
IAC-09-C1.3.1 Astrodynamic Fundamentals for Deflecting Hazardous Near-Earth Objects∗ Bong Wie† Asteroid Deflection Research Center Iowa State University, Ames, IA 50011, United States [email protected] Abstract mate change caused by this asteroid impact may have caused the dinosaur extinction. On June 30, 1908, an The John V. Breakwell Memorial Lecture for the As- asteroid or comet estimated at 30 to 50 m in diameter trodynamics Symposium of the 60th International As- exploded in the skies above Tunguska, Siberia. Known tronautical Congress (IAC) presents a tutorial overview as the Tunguska Event, the explosion flattened trees and of the astrodynamical problem of deflecting a near-Earth killed other vegetation over a 500,000-acre area with an object (NEO) that is on a collision course toward Earth. energy level equivalent to about 500 Hiroshima nuclear This lecture focuses on the astrodynamic fundamentals bombs. of such a technically challenging, complex engineering In the early 1990s, scientists around the world initi- problem. Although various deflection technologies have ated studies to prevent NEOs from striking Earth [1]. been proposed during the past two decades, there is no However, it is now 2009, and there is no consensus on consensus on how to reliably deflect them in a timely how to reliably deflect them in a timely manner even manner. Consequently, now is the time to develop prac- though various mitigation approaches have been inves- tically viable technologies that can be used to mitigate tigated during the past two decades [1-8]. Consequently, threats from NEOs while also advancing space explo- now is the time for initiating a concerted R&D effort for ration. -
Readingsample
Stellar Physics 2: Stellar Evolution and Stability Bearbeitet von Gennady S. Bisnovatyi-Kogan, A.Y. Blinov, M. Romanova 1. Auflage 2011. Buch. xxii, 494 S. Hardcover ISBN 978 3 642 14733 3 Format (B x L): 15,5 x 23,5 cm Gewicht: 1024 g Weitere Fachgebiete > Physik, Astronomie > Astronomie: Allgemeines > Astrophysik Zu Inhaltsverzeichnis schnell und portofrei erhältlich bei Die Online-Fachbuchhandlung beck-shop.de ist spezialisiert auf Fachbücher, insbesondere Recht, Steuern und Wirtschaft. Im Sortiment finden Sie alle Medien (Bücher, Zeitschriften, CDs, eBooks, etc.) aller Verlage. Ergänzt wird das Programm durch Services wie Neuerscheinungsdienst oder Zusammenstellungen von Büchern zu Sonderpreisen. Der Shop führt mehr als 8 Millionen Produkte. Chapter 8 Pre-Main Sequence Evolution As can be seen from the calculations of cloud collapse described in Sect. 7.2,stars with mass M>3Mˇ appear in the optical range immediately near to the main se- quence. Objects of lower mass exist for part of the time as optical stars with radiation due to gravitational contraction energy. Consider evolution of a star from its ap- pearance in the optical region until it reaches the main sequence, and its central temperature becomes sufficiently high to initiate a nuclear reaction converting hy- drogen into helium (see review [105]). 8.1 Hayashi Phase The pre-main sequence evolution of stars takes place at not very high temperatures, when a non-full ionization of matter and large opacity cause such stars to be almost convective. This fact was first established by Hayashi [461, 462], who took into account a convection in constructing evolutionary tracks for contracting stars in the HR diagram (see Fig. -
Space Object Self-Tracker On-Board Orbit Determination Analysis Stacie M
Air Force Institute of Technology AFIT Scholar Theses and Dissertations Student Graduate Works 3-24-2016 Space Object Self-Tracker On-Board Orbit Determination Analysis Stacie M. Flamos Follow this and additional works at: https://scholar.afit.edu/etd Part of the Space Vehicles Commons Recommended Citation Flamos, Stacie M., "Space Object Self-Tracker On-Board Orbit Determination Analysis" (2016). Theses and Dissertations. 430. https://scholar.afit.edu/etd/430 This Thesis is brought to you for free and open access by the Student Graduate Works at AFIT Scholar. It has been accepted for inclusion in Theses and Dissertations by an authorized administrator of AFIT Scholar. For more information, please contact [email protected]. SPACE OBJECT SELF-TRACKER ON-BOARD ORBIT DETERMINATION ANALYSIS THESIS Stacie M. Flamos, Civilian, USAF AFIT-ENY-MS-16-M-209 DEPARTMENT OF THE AIR FORCE AIR UNIVERSITY AIR FORCE INSTITUTE OF TECHNOLOGY Wright-Patterson Air Force Base, Ohio DISTRIBUTION STATEMENT A APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLIMITED The views expressed in this document are those of the author and do not reflect the official policy or position of the United States Air Force, the United States Department of Defense or the United States Government. This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. AFIT-ENY-MS-16-M-209 SPACE OBJECT SELF-TRACKER ON-BOARD ORBIT DETERMINATION ANALYSIS THESIS Presented to the Faculty Department of Aeronatics and Astronautics Graduate School of Engineering and Management Air Force Institute of Technology Air University Air Education and Training Command in Partial Fulfillment of the Requirements for the Degree of Master of Science Stacie M. -
Brightness Profiles of Early-Type Galaxies Hosting Seyfert Nuclei
A&A 469, 75–88 (2007) Astronomy DOI: 10.1051/0004-6361:20066684 & c ESO 2007 Astrophysics The host galaxy/AGN connection Brightness profiles of early-type galaxies hosting Seyfert nuclei A. Capetti and B. Balmaverde INAF - Osservatorio Astronomico di Torino, Strada Osservatorio 20, 10025 Pino Torinese, Italy e-mail: [capetti;balmaverde]@oato.inaf.it Received 2 November 2006 / Accepted 15 March 2007 ABSTRACT We recently presented evidence of a connection between the brightness profiles of nearby early-type galaxies and the properties of the AGN they host. The radio loudness of the AGN appears to be univocally related to the host’s brightness profile: radio-loud nuclei are only hosted by “core” galaxies while radio-quiet AGN are only found in “power-law” galaxies. We extend our analysis here to a −1 sample of 42 nearby (Vrec < 7000 km s ) Seyfert galaxies hosted by early-type galaxies. From the nuclear point of view, they show a large deficit of radio emission (at a given X-ray or narrow line luminosity) with respect to radio-loud AGN, conforming with their identification as radio-quiet AGN. We used the available HST images to study their brightness profiles. Having excluded complex and highly nucleated galaxies, in the remaining 16 objects the brightness profiles can be successfully modeled with a Nuker law with a steep nuclear cusp characteristic of “power-law” galaxies (with logarithmic slope γ = 0.51−1.07). This result is what is expected for these radio-quiet AGN based on our previous findings, thus extending the validity of the connection between brightness profile and radio loudness to AGN of a far higher luminosity. -
Front Cover Image
Front Cover Image: Top Right: The Mars Science laboratory Curiosity Rover successfully landed in Gale Crater on August 6, 2012. Credit: NASA /Jet Propulsion Laboratory. Upper Middle: The Dragon spacecraft became the first commercial vehicle in history to successfully attach to the International Space Station May 25, 2012. Credit: Space Exploration Technologies (SpaceX). Lower Middle: The Dawn Spacecraft enters orbit about asteroid Vesta on July 16, 2011. Credit: Orbital Sciences Corporation and NASA/Jet Propulsion Laboratory, California Institute of Technology. Lower Right: GRAIL-A and GRAIL-B spacecraft, which entered lunar orbit on December 31, 2011 and January 1, 2012, fly in formation above the moon. Credit: Lockheed Martin and NASA/Jet Propulsion Laboratory, California Institute of Technology. Lower Left: The Dawn Spacecraft launch took place September 27, 2007. Credit: Orbital Sciences Corporation and NASA/Jet Propulsion Laboratory, California Institute of Technology. Program sponsored and provided by: Table of Contents Registration ..................................................................................................................................... 3 Schedule of Events .......................................................................................................................... 4 Conference Center Layout .............................................................................................................. 6 Special Events ................................................................................................................................ -
The Catalogue of Cometary Orbits and Their Dynamical Evolution? Małgorzata Królikowska1 and Piotr A
A&A 640, A97 (2020) Astronomy https://doi.org/10.1051/0004-6361/202038451 & c ESO 2020 Astrophysics The catalogue of cometary orbits and their dynamical evolution? Małgorzata Królikowska1 and Piotr A. Dybczynski´ 2 1 Centrum Badan´ Kosmicznych Polskiej Akademii Nauk (CBK PAN), Bartycka 18A, Warszawa 00-716, Poland e-mail: [email protected] 2 Astronomical Observatory Institute, Faculty of Physics, A.Mickiewicz University, Słoneczna 36, Poznan,´ Poland Received 19 May 2020 / Accepted 23 June 2020 ABSTRACT We present the CODE catalogue, the new cometary catalogue containing data for almost 300 long-period comets that were discovered before 2018. This is the first catalogue containing cometary orbits in the five stages of their dynamical evolution and covering three successive passages through the perihelion, with the exception of the hyperbolic comets which are treated in a different manner. Non- gravitational orbits are given for about 100 of these long-period comets, and their orbits obtained while neglecting the existence of non-gravitational acceleration are included for comparison. For many of the presented comets, different orbital solutions, based on the alternative force models or various subsets of positional data, are also provided. The preferred orbit is always clearly indicated for each comet. Key words. comets: general – Oort Cloud 1. Introduction shot 1. The method of obtaining Snapshots 2 and 3, that is orig- inal and future orbits, is described in Sect.3. The previous and The knowledge of orbits is crucial in many research areas related next orbit calculations (Snapshots 4 and 5) are sketched out in to the origin and the evolution of comets and their populations.