DOCSLIB.ORG

AERO -1 Room 14-0551 77 Massachusetts Avenue Cambridge, MA 02139 Ph: 617.253.2800 Milbraries Email: [email protected] Document Services

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
AERO -1 Room 14-0551 77 Massachusetts Avenue Cambridge, MA 02139 Ph: 617.253.2800 Milbraries Email: Docs@Mit.Edu Document Services Coverage Optimization Using a Single Satellite Orbital Figure-of-Merit by John L. Young III B.S. Aerospace Engineering United States Naval Academy, 2001 SUBMITTED TO THE DEPARTMENT OF AERONAUTICS AND ASTRONAUTICS IN PARTIAL FULFILLMENT OF THE REQUIREMENTS OF THE DEGREE OF MASTER OF SCIENCE IN AERONAUTICS AND ASTRONAUTICS AT THE MASSACHUSETTS INSTITUTE MASSACHUSETTS INSTITUTE OF TECHNOLOGY OF TECHNOLOGY June 2003 NL 0 52 J @ 2003 John L. Young III. All Rights Reserved LIBRARIES The author hereby grants to MIT permission to reproduce and distribute publicly paper and electronic copies of this thesis document in whole or in part. Signature of Author Department of Aeronautics and Astronautics May 23, 2003 Certified by David W. Carter Technical Staff, The Charles Stark Draper Laboratory Thesis Supervisor Certified by_ John E. Draim Captain, USN (ret) Thesis Advisor Certified by Paul J. Cefola Technicistaff, The MIT Lincoln Laboratory Lecturer, Department of Aeronautics and Astronautics Thesis Advisor Accepted by E H.N. Slater Professor of Aeronautics and Astronautics Chair, Committee on Graduate Students AERO -1 Room 14-0551 77 Massachusetts Avenue Cambridge, MA 02139 Ph: 617.253.2800 MILbraries Email: [email protected] Document Services http://libraries.mit.edu/docs DISCLAIMER NOTICE The accompanying media item for this thesis is available in the MIT Libraries or Institute Archives. Thank you. Coverage Optimization Using a Single Satellite Orbital Figure-of-Merit By John L. Young III Submitted to the Department of Aeronautics and Astronautics on May 23, 2003, in partial fulfillment of the requirements for the Degree of Master of Science In Aeronautics and Astronautics Abstract A figure-of-merit for measuring the cost-effectiveness of satellite orbits is introduced and applied to various critically inclined daily repeat ground track orbits. The figure-of-merit measures orbit performance through the coverage time provided over a specified point or region on the ground. This thesis primarily focuses on coverage to a ground station, however coverage to a region is briefly examined. The selected repeat ground track orbits are optimized to maximize the coverage provided by varying the orbit's argument of perigee and longitude of ascending node. Several known orbits were reproduced as a result of this coverage optimization. The figure-of-merit measures the cost of the orbit by the launch cost in AV to attain the mission orbit. The launch AV is calculated using a series of analytic formulas. Trends in the figure-of-merit are investigated with respect to repeat ground track pattern, ground station location, orbit eccentricity, and minimum elevation angle. Using the proposed figure-of-merit, various repeat ground track orbits are examined and compared to draw conclusions on the cost-effectiveness of each orbit. This figure-of-merit has potential for use by satellite system designers to compare the cost-effectiveness of different orbits to determine the optimal orbit for a single satellite and by extension, a constellation of satellites. Technical Supervisor: Dr. David W. Carter Title: Member of the Technical Staff, C.S. Draper Laboratory, Inc. Thesis Advisor: Dr. Paul J. Cefola Title: Member of the Technical Staff, MIT Lincoln Laboratory Thesis Advisor: Captain John E. Draim, USN (ret) Title: Aerospace Consultant 3 [This page intentionally left blank] 4 ACKNOWLEDGEMENTS May 23, 2003 I would first like to thank the Charles Stark Draper Laboratory for the opportunity and funding to pursue my Masters Degree these past two years. I would also like to thank my thesis advisor, Dr. David Carter, for taking me on as a student. If it were not for him, I would probably still be searching for a research topic. I gained a wealth of knowledge from our numerous meetings and discussions. It was also a pleasure working with Dr. Paul Cefola, from whom I have learned a great deal. He was right when he told me that I was going to be playing with the 'big dogs,' and I am happy that I had to opportunity to do so. The insight from Captain John Draim, USN (ret) was also instrumental in this thesis. It is always great working with another Annapolis grad. Hopefully I will be able accomplish some of the great things that he has done in his career, both in and out of the Navy. This thesis would not have been possible without the help from all three of my advisors. Countless hours were spent on the phone with them reviewing both my work and my writing. I am also grateful for their support in writing the AAS Paper this past February. It was an extremely valuable experience and I can't complain about Puerto Rico. Thanks also goes to Jeff Cipolloni of Draper Laboratory for his time with all of my computer questions and problems. I would also like to thank the Draper Fellows I have worked with my time here. Eric, we first met as roommates 2/c year in Annapolis. Who would have thought that we'd end up working down the hall from each other two years later? Thanks for all your help these past two years and I wish you and Emily the best of luck in the future. Andrew, what can I say? We've had a lot of fun here, both in the office and out of it. Thanks (I think) for introducing me to the addicting habit we call golf. We've had some good times on the course- in the snow, pouring rain, and sweltering heat. It's a good thing there was another crazy person to go play when no one else would. Good luck at Power School and I'm sorry I won't be down there to enjoy it with you. Stephen, what are we going to do without the great state of Massachusetts? I know you thought I was crazy and didn't think I'd be able to go NFO, but thanks for humoring me for over a year. It is too bad I won't be able to hang out with both you and Andrew down in Charleston. To the rest of the Fellows, Chris G., Hon-Fai, Stuart, Ed, Barry, Luke, Corbin, Chris J., Daryl, and Keith, thanks for all of the interesting lunch time discussions. Ed, I'll see you down in Pensacola in a year. Finally I would like to thank my family for their support throughout the years. Without it, I would have never gotten this far. Thank you. This thesis was prepared at The Charles Stark Draper Laboratory, Inc., under internal Independent Research and Development Project 0305043. Publication of this thesis does not constitute approval by Draper or the sponsoring agency of the findings or conclusions contained herein. It is publikhed for the exchange and stimulation of ideas. L. Young III 5 [This page intentionally left blank] 6 Table of Contents 1 Introdu ction ................................................................................................. 15 1.1 Thesis Objective ........................................................................................................ 15 1.2 Figure-of-M erit..............................................................................................................15 1.3 Thesis Sum mary ........................................................................................................ 17 2 B ackground ................................................................................................ 19 2.1 Chapter Overview ....................................................................................................... 19 2.2 Cost-Effectiveness Metrics......................................................................................... 19 2.2.1 Cost Per Billable M inute.................................................................................... 19 2.2.2 Cost Per Billable TI M inute................................................................................ 20 2.3 Satellite Constellation Perform ance ........................................................................... 21 2.3.1 Revisit Tim e ...................................................................................................... 21 2.3.2 Coverage Tim e .................................................................................................... 22 2.4 Constellation D esign.................................................................................................. 22 2.4.1 R .D. LU ders...................................................................................................... 22 2.4.2 R . L. Easton and R. Brescia................................................................................ 23 2.4.3 John W alker............................................................................................................24 2.4.4 D avid Beste.............................................................................................................24 2.4.5 A rthur Ballard.................................................................................................... 25 2.4.6 John Draim ........................................................................................................ 27 2.4.7 Thom as Lang ...................................................................................................... 30 2.4.8 John H anson ...................................................................................................... 30 3 M ethodology .............................................................................................. 31 3.1 Chapter Overview .......................................................................................................... 31 3.2 Repeat Ground Track Orbits ....................................................................................... 31 3.3 Repeat Ground Track Orbit Calculation ...................................................................
Load more

Recommended publications
  • Analysis of Perturbations and Station-Keeping Requirements in Highly-Inclined Geosynchronous Orbits
    ANALYSIS OF PERTURBATIONS AND STATION-KEEPING REQUIREMENTS IN HIGHLY-INCLINED GEOSYNCHRONOUS ORBITS Elena Fantino(1), Roberto Flores(2), Alessio Di Salvo(3), and Marilena Di Carlo(4) (1)Space Studies Institute of Catalonia (IEEC), Polytechnic University of Catalonia (UPC), E.T.S.E.I.A.T., Colom 11, 08222 Terrassa (Spain), [email protected] (2)International Center for Numerical Methods in Engineering (CIMNE), Polytechnic University of Catalonia (UPC), Building C1, Campus Norte, UPC, Gran Capitan,´ s/n, 08034 Barcelona (Spain) (3)NEXT Ingegneria dei Sistemi S.p.A., Space Innovation System Unit, Via A. Noale 345/b, 00155 Roma (Italy), [email protected] (4)Department of Mechanical and Aerospace Engineering, University of Strathclyde, 75 Montrose Street, Glasgow G1 1XJ (United Kingdom), [email protected] Abstract: There is a demand for communications services at high latitudes that is not well served by conventional geostationary satellites. Alternatives using low-altitude orbits require too large constellations. Other options are the Molniya and Tundra families (critically-inclined, eccentric orbits with the apogee at high latitudes). In this work we have considered derivatives of the Tundra type with different inclinations and eccentricities. By means of a high-precision model of the terrestrial gravity field and the most relevant environmental perturbations, we have studied the evolution of these orbits during a period of two years. The effects of the different perturbations on the constellation ground track (which is more important for coverage than the orbital elements themselves) have been identified. We show that, in order to maintain the ground track unchanged, the most important parameters are the orbital period and the argument of the perigee.
    [Show full text]
  • Astrodynamics
    Politecnico di Torino SEEDS SpacE Exploration and Development Systems Astrodynamics II Edition 2006 - 07 - Ver. 2.0.1 Author: Guido Colasurdo Dipartimento di Energetica Teacher: Giulio Avanzini Dipartimento di Ingegneria Aeronautica e Spaziale e-mail: [email protected] Contents 1 Two–Body Orbital Mechanics 1 1.1 BirthofAstrodynamics: Kepler’sLaws. ......... 1 1.2 Newton’sLawsofMotion ............................ ... 2 1.3 Newton’s Law of Universal Gravitation . ......... 3 1.4 The n–BodyProblem ................................. 4 1.5 Equation of Motion in the Two-Body Problem . ....... 5 1.6 PotentialEnergy ................................. ... 6 1.7 ConstantsoftheMotion . .. .. .. .. .. .. .. .. .... 7 1.8 TrajectoryEquation .............................. .... 8 1.9 ConicSections ................................... 8 1.10 Relating Energy and Semi-major Axis . ........ 9 2 Two-Dimensional Analysis of Motion 11 2.1 ReferenceFrames................................. 11 2.2 Velocity and acceleration components . ......... 12 2.3 First-Order Scalar Equations of Motion . ......... 12 2.4 PerifocalReferenceFrame . ...... 13 2.5 FlightPathAngle ................................. 14 2.6 EllipticalOrbits................................ ..... 15 2.6.1 Geometry of an Elliptical Orbit . ..... 15 2.6.2 Period of an Elliptical Orbit . ..... 16 2.7 Time–of–Flight on the Elliptical Orbit . .......... 16 2.8 Extensiontohyperbolaandparabola. ........ 18 2.9 Circular and Escape Velocity, Hyperbolic Excess Speed . .............. 18 2.10 CosmicVelocities
    [Show full text]
  • Handbook of Satellite Orbits from Kepler to GPS Michel Capderou
    Handbook of Satellite Orbits From Kepler to GPS Michel Capderou Handbook of Satellite Orbits From Kepler to GPS Translated by Stephen Lyle Foreword by Charles Elachi, Director, NASA Jet Propulsion Laboratory, California Institute of Technology, Pasadena, California, USA 123 Michel Capderou Universite´ Pierre et Marie Curie Paris, France ISBN 978-3-319-03415-7 ISBN 978-3-319-03416-4 (eBook) DOI 10.1007/978-3-319-03416-4 Springer Cham Heidelberg New York Dordrecht London Library of Congress Control Number: 2014930341 © Springer International Publishing Switzerland 2014 This work is subject to copyright. All rights are reserved by the Publisher, whether the whole or part of the material is concerned, specifically the rights of translation, reprinting, reuse of illustrations, recitation, broadcasting, reproduction on microfilms or in any other physical way, and transmission or information storage and retrieval, electronic adaptation, computer software, or by similar or dissimilar methodology now known or hereafter developed. Exempted from this legal reservation are brief excerpts in connection with reviews or scholarly analysis or material supplied specifically for the purpose of being entered and executed on a computer system, for exclusive use by the purchaser of the work. Duplication of this pub- lication or parts thereof is permitted only under the provisions of the Copyright Law of the Publisher’s location, in its current version, and permission for use must always be obtained from Springer. Permis- sions for use may be obtained through RightsLink at the Copyright Clearance Center. Violations are liable to prosecution under the respective Copyright Law. The use of general descriptive names, registered names, trademarks, service marks, etc.
    [Show full text]
  • Download Paper
    Ever Wonder What’s in Molniya? We Do. John T. McGraw J. T. McGraw and Associates, LLC and University of New Mexico Peter C. Zimmer J. T. McGraw and Associates, LLC Mark R. Ackermann J. T. McGraw and Associates, LLC ABSTRACT Molniya orbits are high inclination, high eccentricity orbits which provide the utility of long apogee dwell time over northern continents, with the additional benefit of obviating the largest orbital perturbation introduced by the Earth’s nonspherical (oblate) gravitational potential. We review the few earlier surveys of the Molniya domain and evaluate results from a new, large area unbiased survey of the northern Molniya domain. We detect 120 Molniya objects in a three hour survey of ~ 1300 square degrees of the sky to a limiting magnitude of about 16.5. Future Molniya surveys will discover a significant number of objects, including debris, and monitoring these objects might provide useful data with respect to orbital perturbations including solar radiation and Earth atmosphere drag effects. 1. SPECIALIZED ORBITS Earth Orbital Space (EOS) supports many versions of specialized satellite orbits defined by a combination of satellite mission and orbital dynamics. Surely the most well-known family of specialized orbits is the geostationary orbits proposed by science fiction author Arthur C. Clarke in 1945 [1] that lie sensibly in the plane of Earth’s equator, with orbital period that matches the Earth’s rotation period. Satellites in these orbits, and the closely related geosynchronous orbits, appear from Earth to remain constantly overhead, allowing continuous communication with the majority of the hemisphere below. Constellations of three geostationary satellites equally spaced in orbit (~ 120° separation) can maintain near-global communication and terrestrial surveillance.
    [Show full text]
  • 2008 Annual Report
    2008 Annual Report NATIONAL ACADEMY OF ENGINEERING ENGINEERING THE FUTURE 1 Letter from the President 3 In Service to the Nation 3 Mission Statement 4 Program Reports 4 Engineering Education 4 Center for the Advancement of Scholarship on Engineering Education 6 Technological Literacy 6 Public Understanding of Engineering Developing Effective Messages Media Relations Public Relations Grand Challenges for Engineering 8 Center for Engineering, Ethics, and Society 9 Diversity in the Engineering Workforce Engineer Girl! Website Engineer Your Life Project Engineering Equity Extension Service 10 Frontiers of Engineering Armstrong Endowment for Young Engineers-Gilbreth Lectures 12 Engineering and Health Care 14 Technology and Peace Building 14 Technology for a Quieter America 15 America’s Energy Future 16 Terrorism and the Electric Power-Delivery System 16 U.S.-China Cooperation on Electricity from Renewables 17 U.S.-China Symposium on Science and Technology Strategic Policy 17 Offshoring of Engineering 18 Gathering Storm Still Frames the Policy Debate 20 2008 NAE Awards Recipients 22 2008 New Members and Foreign Associates 24 2008 NAE Anniversary Members 28 2008 Private Contributions 28 Einstein Society 28 Heritage Society 29 Golden Bridge Society 29 Catalyst Society 30 Rosette Society 30 Challenge Society 30 Charter Society 31 Other Individual Donors 34 The Presidents’ Circle 34 Corporations, Foundations, and Other Organizations 35 National Academy of Engineering Fund Financial Report 37 Report of Independent Certified Public Accountants 41 Notes to Financial Statements 53 Officers 53 Councillors 54 Staff 54 NAE Publications Letter from the President Engineering is critical to meeting the fundamental challenges facing the U.S. economy in the 21st century.
    [Show full text]
  • Positioning: Drift Orbit and Station Acquisition
    Orbits Supplement GEOSTATIONARY ORBIT PERTURBATIONS INFLUENCE OF ASPHERICITY OF THE EARTH: The gravitational potential of the Earth is no longer µ/r, but varies with longitude. A tangential acceleration is created, depending on the longitudinal location of the satellite, with four points of stable equilibrium: two stable equilibrium points (L 75° E, 105° W) two unstable equilibrium points ( 15° W, 162° E) This tangential acceleration causes a drift of the satellite longitude. Longitudinal drift d'/dt in terms of the longitude about a point of stable equilibrium expresses as: (d/dt)2 - k cos 2 = constant Orbits Supplement GEO PERTURBATIONS (CONT'D) INFLUENCE OF EARTH ASPHERICITY VARIATION IN THE LONGITUDINAL ACCELERATION OF A GEOSTATIONARY SATELLITE: Orbits Supplement GEO PERTURBATIONS (CONT'D) INFLUENCE OF SUN & MOON ATTRACTION Gravitational attraction by the sun and moon causes the satellite orbital inclination to change with time. The evolution of the inclination vector is mainly a combination of variations: period 13.66 days with 0.0035° amplitude period 182.65 days with 0.023° amplitude long term drift The long term drift is given by: -4 dix/dt = H = (-3.6 sin M) 10 ° /day -4 diy/dt = K = (23.4 +.2.7 cos M) 10 °/day where M is the moon ascending node longitude: M = 12.111 -0.052954 T (T: days from 1/1/1950) 2 2 2 2 cos d = H / (H + K ); i/t = (H + K ) Depending on time within the 18 year period of M d varies from 81.1° to 98.9° i/t varies from 0.75°/year to 0.95°/year Orbits Supplement GEO PERTURBATIONS (CONT'D) INFLUENCE OF SUN RADIATION PRESSURE Due to sun radiation pressure, eccentricity arises: EFFECT OF NON-ZERO ECCENTRICITY L = difference between longitude of geostationary satellite and geosynchronous satellite (24 hour period orbit with e0) With non-zero eccentricity the satellite track undergoes a periodic motion about the subsatellite point at perigee.
    [Show full text]
  • Mr. Warren Soh Magellan Aerospace, Canada, [email protected]
    Paper ID: 24743 65th International Astronautical Congress 2014 ASTRODYNAMICS SYMPOSIUM (C1) Guidance, Navigation and Control (1) (5) Author: Mr. Warren Soh Magellan Aerospace, Canada, [email protected] Ms. Jennifer Michels Magellan Aerospace, Canada, [email protected] Mr. Don Asquin Magellan Aerospace, Canada, [email protected] Mr. Adam Vigneron International Space University, Carleton University, Canada, [email protected] Dr. Anton de Ruiter Canada, [email protected] Mr. Ron Buckingham Northeast Space Company, Canada, [email protected] ONBOARD NAVIGATION FOR THE CANADIAN POLAR COMMUNICATION AND WEATHER SATELLITE IN TUNDRA ORBIT Abstract Geosynchronous communications and meteorological satellites have limited northern latitude coverage, specifically above 65 N latitude. This lack of secure, highly reliable, high capacity communication ser- vices and insufficient meteorological data over the Arctic region has prompted Canada to investigate new satellite solutions. Since 2008, the Canadian Space Agency (CSA) has spearheaded the Polar Communi- cation and Weather (PCW) mission, slated to operate in a Highly Elliptical Orbit (HEO). A 24-hour, 90 inclination, Tundra orbit is a strong candidate; able to fill the communication and weather coverage gaps and allow continuous space weather monitoring in the Northern and Southern hemispheres. This orbit however, poses an operational challenge for GPS-based satellite orbit determination since the satellite is continuously above the GPS constellation and will experience frequent signal outages, especially when passing over the poles, aggravated by the constellation's inclination of 55. Magellan Aerospace, Winnipeg in collaboration with Carleton University, has successfully developed an onboard navigation technology for PCW within a CSA-funded Space Technology Development Program.
    [Show full text]
  • Molniya" Type Orbits
    EXAMINATION OF THE LIFETIME, EVOLUTION AND RE-ENTRY FEATURES FOR THE "MOLNIYA" TYPE ORBITS Yu.F. Kolyuka, N.M. Ivanov, T.I. Afanasieva, T.A. Gridchina Mission Control Center, 4, Pionerskaya str., Korolev, Moscow Region, 141070, Russia, [email protected] ABSTRACT Space vehicles of the "Molniya" series, launched into the special highly elliptical orbits with a period of ~ 12 hours, are intended for solution of telecommunication problems in stretched territories of the former USSR and nowadays − Russia, and also for providing the connectivity between Russia and other countries. The inclination of standard orbits of such a kind of satellites is near to the critical value i ≈ 63.4 deg and their initial minimal altitude normally has a value Hmin ~ 500 km. As a rule, the “Molniya" satellites of a concrete series form the groups with determined disposition of orbital planes on an ascending node longitude that allows to ensure requirements of the continuous link between any points in northern hemisphere. The first satellite of the "Molniya" series has been inserted into designed orbit in 1964. Up to now it is launched over 160 space vehicles of such a kind. As well as all artificial satellites, space vehicles "Molniya" undergo the action of various perturbing forces influencing a change of their orbital parameters. However in case of space vehicles "Molniya" these changes of parameters have a specific character and in many things they differ from the perturbations which are taking place for the majority of standard orbits of the artificial satellites with rather small eccentricity. In particular, to strong enough variations (first of all, at the expense of the luni-solar attraction) it is subjected the orbit perigee distance rπ that can lead to such reduction Hmin when further flight of the satellite on its orbit becomes impossible, it re-entries and falls to the Earth.
    [Show full text]
  • Creating Intelligent Machines at Deere &
    THE 2018 CT HALL OF FAME CES 2019 PREVIEW NOVEMBERDECEMBER 2018 BLOCKCHAIN NEW WAYS TO TRANSACT SMART CARS MONITORING DRIVERS TECH CONNECTING DOCTORS WITH PATIENTS SENIOR VP, INTELLIGENT SOLUTIONS GROUP John Stone Creating Intelligent Machines at Deere & Co. i3_1118_C1_COVER_layout.indd 1 10/24/18 3:50 PM MEET THE MOST IRRESISTIBLE NEW POWER COUPLE EVERYBODY’S TALKING Sharp’s all-new, modern and elegant, built-in wall oven features an edge-to-edge black glass and stainless steel design. The SWA3052DS pairs beautifully with our new SMD2480CS Microwave DrawerTM, the new power couple of style and performance. This 5.0 cu. ft. 240V. built-in wall oven uses True European Convection to cook evenly and heat effi ciently. The 8 pass upper-element provides edge-to-edge performance. Sharp’s top-of-the-line Microwave Drawer™ features Easy Wave Open for touchless operation. Hands full? Simply wave up-and-down near the motion sensor and the SMD2480CS glides open. It’s just the kind of elegant engineering, smart functionality and cutting-edge performance you’d expect from Sharp. NEW TOUCH GLASS CONTROL PANEL EDGE-TO-EDGE, BLACK GLASS & STAINLESS STEEL OPTIONAL 30" EXTENSION KIT SHOWN Simply Better Living www.SharpUSA.com © 2018 Sharp Electronics Corporation. All rights reserved. Sharp, Microwave Drawer™ Oven and all related trademarks are trademarks or regis- tered trademarks of Sharp Corporation and/or its affi liated entities. Product specifi cations and design are subject to change without notice. Internal capacity calculated by measuring maximum width,
    [Show full text]
  • Open Rosen Thesis.Pdf
    THE PENNSYLVANIA STATE UNIVERSITY SCHREYER HONORS COLLEGE DEPARTMENT OF AEROSPACE ENGINEERING END OF LIFE DISPOSAL OF SATELLITES IN HIGHLY ELLIPTICAL ORBITS MITCHELL ROSEN SPRING 2019 A thesis submitted in partial fulfillment of the requirements for a baccalaureate degree in Aerospace Engineering with honors in Aerospace Engineering Reviewed and approved* by the following: Dr. David Spencer Professor of Aerospace Engineering Thesis Supervisor Dr. Mark Maughmer Professor of Aerospace Engineering Honors Adviser * Signatures are on file in the Schreyer Honors College. i ABSTRACT Highly elliptical orbits allow for coverage of large parts of the Earth through a single satellite, simplifying communications in the globe’s northern reaches. These orbits are able to avoid drastic changes to the argument of periapse by using a critical inclination (63.4°) that cancels out the first level of the geopotential forces. However, this allows the next level of geopotential forces to take over, quickly de-orbiting satellites. Thus, a balance between the rate of change of the argument of periapse and the lifetime of the orbit is necessitated. This thesis sets out to find that balance. It is determined that an orbit with an inclination of 62.5° strikes that balance best. While this orbit is optimal off of the critical inclination, it is still near enough that to allow for potential use of inclination changes as a deorbiting method. Satellites are deorbited when the propellant remaining is enough to perform such a maneuver, and nothing more; therefore, the less change in velocity necessary for to deorbit, the better. Following the determination of an ideal highly elliptical orbit, the different methods of inclination change is tested against the usual method for deorbiting a satellite, an apoapse burn to lower the periapse, to find the most propellant- efficient method.
    [Show full text]
  • L-G-0015436434-0054602840.Pdf
    Position, Navigation, and Timing Technologies in the 21st Century IEEE Press 445 Hoes Lane Piscataway, NJ 08854 IEEE Press Editorial Board Ekram Hossain, Editor in Chief Jón Atli Benediktsson David Alan Grier Elya B. Joffe Xiaoou Li Peter Lian Andreas Molisch Saeid Nahavandi Jeffrey Reed Diomidis Spinellis Sarah Spurgeon Ahmet Murat Tekalp Position, Navigation, and Timing Technologies in the 21st Century Integrated Satellite Navigation, Sensor Systems, and Civil Applications Volume 1 Edited by Y. T. Jade Morton, University of Colorado Boulder Frank van Diggelen, Google James J. Spilker, Jr., Stanford University Bradford W. Parkinson, Stanford University Associate Editors: Sherman Lo, Stanford University Grace Gao, Stanford University Copyright © 2021 by The Institute of Electrical and Electronics Engineers, Inc. All rights reserved. Published by John Wiley & Sons, Inc., Hoboken, New Jersey. Published simultaneously in Canada. No part of this publication may be reproduced, stored in a retrieval system, or transmitted in any form or by any means, electronic, mechanical, photocopying, recording, scanning, or otherwise, except as permitted under Section 107 or 108 of the 1976 United States Copyright Act, without either the prior written permission of the Publisher, or authorization through payment of the appropriate per-copy fee to the Copyright Clearance Center, Inc., 222 Rosewood Drive, Danvers, MA 01923, (978) 750-8400, fax (978) 750-4470, or on the web at www.copyright.com. Requests to the Publisher for permission should be addressed to the Permissions Department, John Wiley & Sons, Inc., 111 River Street, Hoboken, NJ 07030, (201) 748-6011, fax (201) 748-6008, or online at http://www.wiley.com/go/permissions.
    [Show full text]
  • Coordinates James R
    Coordinates James R. Clynch Naval Postgraduate School, 2002 I. Coordinate Types There are two generic types of coordinates: Cartesian, and Curvilinear of Angular. Those that provide x-y-z type values in meters, kilometers or other distance units are called Cartesian. Those that provide latitude, longitude, and height are called curvilinear or angular. The Cartesian and angular coordinates are equivalent, but only after supplying some extra information. For the spherical earth model only the earth radius is needed. For the ellipsoidal earth, two parameters of the ellipsoid are needed. (These can be any of several sets. The most common is the semi-major axis, called "a", and the flattening, called "f".) II. Cartesian Coordinates A. Generic Cartesian Coordinates These are the coordinates that are used in algebra to plot functions. For a two dimensional system there are two axes, which are perpendicular to each other. The value of a point is represented by the values of the point projected onto the axes. In the figure below the point (5,2) and the standard orientation for the X and Y axes are shown. In three dimensions the same process is used. In this case there are three axis. There is some ambiguity to the orientation of the Z axis once the X and Y axes have been drawn. There 1 are two choices, leading to right and left handed systems. The standard choice, a right hand system is shown below. Rotating a standard (right hand) screw from X into Y advances along the positive Z axis. The point Q at ( -5, -5, 10) is shown.
    [Show full text]