DOCSLIB.ORG

Advances in Spacecraft Attitude Control

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Advances in Spacecraft Attitude Control Edited by Timothy Sands Advances in Spacecraft AttitudeControl Spacecraft attitude maneuvers comply with Euler’s moment equations, a set of three nonlinear, coupled differential equations. Nonlinearities complicate the mathematical treatment of the seemingly simple action of rotating, and these complications lead Advances in Spacecraft to a robust lineage of research. This book is meant for basic scientifically inclined readers, and commences with a chapter on the basics of spaceflight and leverages this remediation to reveal very advanced topics to new spaceflight enthusiasts. The Attitude Control topics learned from reading this text will prepare students and faculties to investigate interesting spaceflight problems in an era where cube satellites have made such investigations attainable by even small universities. It is the fondest hope of the editor Edited by Timothy Sands and authors that readers enjoy this book. ISBN 978-1-78984-802-1 Published in London, UK © 2020 IntechOpen © vjanez / iStock Advances in Spacecraft Attitude Control Edited by Timothy Sands Published in London, United Kingdom Supporting open minds since 2005 Advances in Spacecraft Attitude Control http://dx.doi.org/10.5772/intechopen.77574 Edited by Timothy Sands Contributors Brendon Smeresky, Alexa Rizzo, Matthew Cooper, Jonathan Lang, Henry Travis, Zachary A Lewis, Kyle Baker, Joshua Ten Eyck, Ranjan Vepa, Eryn Culton, Emanuele Calabrò, Elisa Capello, Matteo Dentis, Renato Bruni, Fabio Celani, Elżbieta Jarzębowska, Marcin Kłak, Peter Waswa, Sangram Redkar © The Editor(s) and the Author(s) 2020 The rights of the editor(s) and the author(s) have been asserted in accordance with the Copyright, Designs and Patents Act 1988. All rights to the book as a whole are reserved by INTECHOPEN LIMITED. The book as a whole (compilation) cannot be reproduced, distributed or used for commercial or non-commercial purposes without INTECHOPEN LIMITED’s written permission. Enquiries concerning the use of the book should be directed to INTECHOPEN LIMITED rights and permissions department ([email protected]). Violations are liable to prosecution under the governing Copyright Law. Individual chapters of this publication are distributed under the terms of the Creative Commons Attribution - NonCommercial 4.0 International which permits use, distribution and reproduction of the individual chapters for non-commercial purposes, provided the original author(s) and source publication are appropriately acknowledged. More details and guidelines concerning content reuse and adaptation can be found at http://www.intechopen.com/copyright-policy.html. Notice Statements and opinions expressed in the chapters are these of the individual contributors and not necessarily those of the editors or publisher. No responsibility is accepted for the accuracy of information contained in the published chapters. The publisher assumes no responsibility for any damage or injury to persons or property arising out of the use of any materials, instructions, methods or ideas contained in the book. First published in London, United Kingdom, 2020 by IntechOpen IntechOpen is the global imprint of INTECHOPEN LIMITED, registered in England and Wales, registration number: 11086078, 7th floor, 10 Lower Thames Street, London, EC3R 6AF, United Kingdom Printed in Croatia British Library Cataloguing-in-Publication Data A catalogue record for this book is available from the British Library Additional hard and PDF copies can be obtained from [email protected] Advances in Spacecraft Attitude Control Edited by Timothy Sands p. cm. Print ISBN 978-1-78984-802-1 Online ISBN 978-1-78984-803-8 eBook (PDF) ISBN 978-1-83968-516-3 An electronic version of this book is freely available, thanks to the support of libraries working with Knowledge Unlatched. KU is a collaborative initiative designed to make high quality books Open Access for the public good. More information about the initiative and links to the Open Access version can be found at www.knowledgeunlatched.org We are IntechOpen, the world’s leading publisher of Open Access books Built by scientists, for scientists 4,500+ 119,000+ 135M+ Open access books available International authors and editors Downloads Our authors are among the 151 Top 1% 12.2% Countries delivered to most cited scientists Contributors from top 500 universities Selection of our books indexed in the Book Citation Index in Web of Science™ Core Collection (BKCI) Interested in publishing with us? Contact [email protected] Numbers displayed above are based on latest data collected. For more information visit www.intechopen.com Meet the editor Dr. Timothy Sands graduated from Columbia University, Stanford University, and the Naval Postgraduate School. He is an Interna- tional Scholar Laureate of the Golden Key International Honor Society, a Fellow of the Defense Advanced Research Projects Agency, panelist of the National Science Foundation Graduate Research Fellowship program, and an interviewer for undergradu- ate admissions at Stanford University. He has published prolifically in archival journals, conference proceedings, books, and book chapters, in addition to giving plenary, keynote, and invitational presentations. He holds one patent in spacecraft attitude control. He is currently the Associate Dean of the Naval Postgrad- uate School’s Graduate School of Engineering and Applied Science having previously served as a university chief academic officer, dean, and research center director. Contents Preface III Section 1 Overviews 1 Chapter 1 3 Introduction to Satellite Attitude Control by Henry Travis Chapter 2 19 Kinematics: On Direction Cosine Matrices by Brendon Smeresky and Alex Rizzo Chapter 3 35 Quaternion-Based Spacecraft Dynamic Modeling and Reorientation Control Using the Dynamically Equivalent Manipulator Approach by Elżbieta Jarzębowska and Marcin Kłak Section 2 Control Techniques 49 Chapter 4 51 An Overview of Evolutionary Algorithms toward Spacecraft Attitude Control by Matthew A. Cooper and Brendon Smeresky Chapter 5 73 Spacecraft Guidance Sensing at Relativistic Velocities by Emanuele Calabrò Chapter 6 95 Analysis and Control of Nonlinear Attitude Motion of Gravity-Gradient Stabilized Spacecraft via Lyapunov-Floquet Transformation and Normal Forms by Peter M.B. Waswa and Sangram Redkar Chapter 7 135 Optimal Trajectory Synthesis and Tracking Control for Spacecraft Large Attitude Manoeuvers by Ranjan Vepa Contents Preface XIII Section 1 Overviews 1 Chapter 1 3 Introduction to Satellite Attitude Control by Henry Travis Chapter 2 19 Kinematics: On Direction Cosine Matrices by Brendon Smeresky and Alex Rizzo Chapter 3 35 Quaternion-Based Spacecraft Dynamic Modeling and Reorientation Control Using the Dynamically Equivalent Manipulator Approach by Elżbieta Jarzębowska and Marcin Kłak Section 2 Control Techniques 49 Chapter 4 51 An Overview of Evolutionary Algorithms toward Spacecraft Attitude Control by Matthew A. Cooper and Brendon Smeresky Chapter 5 73 Spacecraft Guidance Sensing at Relativistic Velocities by Emanuele Calabrò Chapter 6 95 Analysis and Control of Nonlinear Attitude Motion of Gravity-Gradient Stabilized Spacecraft via Lyapunov-Floquet Transformation and Normal Forms by Peter M.B. Waswa and Sangram Redkar Chapter 7 135 Optimal Trajectory Synthesis and Tracking Control for Spacecraft Large Attitude Manoeuvers by Ranjan Vepa Chapter 8 155 Parameter Optimization for Spacecraft Attitude Stabilization Preface Using Magnetorquers by Renato Bruni and Fabio Celani Chapter 9 177 Precise Attitude Control Techniques: Performance Analysis From Classical to Variable Structure Control Spacecraft attitude maneuvers comply with Euler’s moment equations, a set of three by Elisa Capello and Matteo Dentis nonlinear, coupled differential equations. Nonlinearities complicate the mathe- matical treatment of the seemingly simple action of rotating, and these complica- Section 3 tions lead to a robust lineage of research. This book begins with an introduction to Control Moment Gyroscope Actuators 201 the nature of attitude control before illustrating some recent advancements in the field, including optimal trajectory synthesis, parameter optimization, modern kine- Chapter 10 203 matics (questioning ubiquitously accepted practices), analysis and control of the Investigation of Singularities in a 3/4 CMG Configuration with nonlinear motion and utilization of precision control techniques, including applica- Mixed Skew Angles tion at relativistic velocities, and new developments in the use of control moment by Jonathan W. Lang gyroscopes as actuators. Among the key facets of the book is the first-ever compre- hensive treatment of mounting geometries of single-gimballed control moment Chapter 11 223 gyroscopes, which will encourage readers to keep the book as a future reference Control Moment Gyroscope Skew Angle Variation and Singularity text. The analysis is centered on performance and singularity-free operations. Penetration by Kyle A. Baker The text is meant for basic scientifically inclined readers, and commences with a chapter on the basics of spaceflight and leverages this remediation to reveal very Chapter 12 233 advanced topics to new spaceflight enthusiasts. The topics learned from reading this Single Axis Singularity Mapping for Mixed Skew Angle, text will prepare students and faculties to investigate interesting spaceflight prob- Non-Redundant, Single Gimbaled CMG Systems lems in an era where cube satellites have made such investigations attainable by by Eryn A. Culton
Load more

Recommended publications
  • Juno Telecommunications
    The cover The cover is an artist’s conception of Juno in orbit around Jupiter.1 The photovoltaic panels are extended and pointed within a few degrees of the Sun while the high-gain antenna is pointed at the Earth. 1 The picture is titled Juno Mission to Jupiter. See http://www.jpl.nasa.gov/spaceimages/details.php?id=PIA13087 for the cover art and an accompanying mission overview. DESCANSO Design and Performance Summary Series Article 16 Juno Telecommunications Ryan Mukai David Hansen Anthony Mittskus Jim Taylor Monika Danos Jet Propulsion Laboratory California Institute of Technology Pasadena, California National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Pasadena, California October 2012 This research was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. Reference herein to any specific commercial product, process, or service by trade name, trademark, manufacturer, or otherwise, does not constitute or imply endorsement by the United States Government or the Jet Propulsion Laboratory, California Institute of Technology. Copyright 2012 California Institute of Technology. Government sponsorship acknowledged. DESCANSO DESIGN AND PERFORMANCE SUMMARY SERIES Issued by the Deep Space Communications and Navigation Systems Center of Excellence Jet Propulsion Laboratory California Institute of Technology Joseph H. Yuen, Editor-in-Chief Published Articles in This Series Article 1—“Mars Global
    [Show full text]
  • THE ATTITUDE CONTROL and DETERMINATION SYSTEMS of the SAS-A Satellite
    THE ATTITUDE CONTROL and DETERMINATION SYSTEMS of the SAS-A SATElliTE F. F. Mobley, A high-speed wheel inside the satellite provides the basic attitude sta­ B. E. Tossman, bilization for SAS-A. Wobbling of the spin axis is removed by an G. H. Fountain ultra-sensitive nutation damper which uses a copper vane pendulum on a taut-band suspension to dissipate energy by eddy-currents. The spin axis can be oriented anywhere in space as required for the X-ray ex­ periment by a magnetic control system operated by commands from the ground station at Quito, Ecuador. Magnetic torquing is also used to maintain the satellite spin rate at 1/ 12 revolution per minute. These systems are outgrowths of APL developments for previous satellites, chosen for simplicity and maximum expectation of satisfactory performance in orbit. The in-orbit performance has been essentially flawless. Introduction HE ATTITUDE CONTROL SYSTEM is used to a simple and reliable open-loop system, using orient SAS-A so that the X-ray detectors can commands from the ground. This is very appealing Tscan the regions of the celestial sphere in an or­ since the weight and power limitations on the derly and efficient manner to detect and measure SAS-A satellite do not permit an elaborate closed­ new X-ray sources. The two X-ray collimators loop control system. are mounted perpendicular to the satellite spin In addition to detecting and analyzing new (Z) axis. As the satellite rotates slowly about its X-ray sources, the experimenter is interested in Z axis, the detectors scan a 5-degree-wide great correlating X-ray sources with known visible stars, circle path in the celestial sphere.
    [Show full text]
  • Accretion Flows in Nonmagnetic White Dwarf Binaries As Observed in X-Rays
    Accretion Flows in Nonmagnetic White Dwarf Binaries as Observed in X-rays Şölen Balmana,< aKadir Has University, Faculty of Engineering and Natural Sciences, Cibali 34083, Istanbul, Turkey ARTICLEINFO ABSTRACT Keywords: Cataclysmic Variables (CVs) are compact binaries with white dwarf (WD) primaries. CVs and other cataclysmic variables - accretion, accre- accreting WD binaries (AWBs) are useful laboratories for studying accretion flows, gas dynamics, tion disks - thermal emission - non-thermal outflows, transient outbursts, and explosive nuclear burning under different astrophysical plasma con- emission - white dwarfs - X-rays: bina- ditions. They have been studied over decades and are important for population studies of galactic ries X-ray sources. Recent space- and ground-based high resolution spectral and timing studies, along with recent surveys indicate that we still have observational and theoretical complexities yet to an- swer. I review accretion in nonmagnetic AWBs in the light of X-ray observations. I present X-ray diagnostics of accretion in dwarf novae and the disk outbursts, the nova-like systems, and the state of the research on the disk winds and outflows in the nonmagnetic CVs together with comparisons and relations to classical and recurrent nova systems, AM CVns and Symbiotic systems. I discuss how the advective hot accretion flows (ADAF-like) in the inner regions of accretion disks (merged with boundary layer zones) in nonmagnetic CVs explain most of the discrepancies and complexities that have been encountered in the X-ray observations. I stress how flickering variability studies from optical to X-rays can be probes to determine accretion history and disk structure together with how the temporal and spectral variability of CVs are related to that of LMXBs and AGNs.
    [Show full text]
  • Správa O Činnosti Organizácie SAV Za Rok 2017
    Astronomický ústav SAV Správa o činnosti organizácie SAV za rok 2017 Tatranská Lomnica január 2018 Obsah osnovy Správy o činnosti organizácie SAV za rok 2017 1. Základné údaje o organizácii 2. Vedecká činnosť 3. Doktorandské štúdium, iná pedagogická činnosť a budovanie ľudských zdrojov pre vedu a techniku 4. Medzinárodná vedecká spolupráca 5. Vedná politika 6. Spolupráca s VŠ a inými subjektmi v oblasti vedy a techniky 7. Spolupráca s aplikačnou a hospodárskou sférou 8. Aktivity pre Národnú radu SR, vládu SR, ústredné orgány štátnej správy SR a iné organizácie 9. Vedecko-organizačné a popularizačné aktivity 10. Činnosť knižnično-informačného pracoviska 11. Aktivity v orgánoch SAV 12. Hospodárenie organizácie 13. Nadácie a fondy pri organizácii SAV 14. Iné významné činnosti organizácie SAV 15. Vyznamenania, ocenenia a ceny udelené organizácii a pracovníkom organizácie SAV 16. Poskytovanie informácií v súlade so zákonom o slobodnom prístupe k informáciám 17. Problémy a podnety pre činnosť SAV PRÍLOHY A Zoznam zamestnancov a doktorandov organizácie k 31.12.2017 B Projekty riešené v organizácii C Publikačná činnosť organizácie D Údaje o pedagogickej činnosti organizácie E Medzinárodná mobilita organizácie F Vedecko-popularizačná činnosť pracovníkov organizácie SAV Správa o činnosti organizácie SAV 1. Základné údaje o organizácii 1.1. Kontaktné údaje Názov: Astronomický ústav SAV Riaditeľ: Mgr. Martin Vaňko, PhD. Zástupca riaditeľa: Mgr. Peter Gömöry, PhD. Vedecký tajomník: Mgr. Marián Jakubík, PhD. Predseda vedeckej rady: RNDr. Luboš Neslušan, CSc. Člen snemu SAV: Mgr. Marián Jakubík, PhD. Adresa: Astronomický ústav SAV, 059 60 Tatranská Lomnica http://www.ta3.sk Tel.: 052/7879111 Fax: 052/4467656 E-mail: [email protected] Názvy a adresy detašovaných pracovísk: Astronomický ústav - Oddelenie medziplanetárnej hmoty Dúbravská cesta 9, 845 04 Bratislava Vedúci detašovaných pracovísk: Astronomický ústav - Oddelenie medziplanetárnej hmoty prof.
    [Show full text]
  • Red Giant Mass-Loss: Studying Evolved Stellar Winds with FUSE and HST/STIS
    Red Giant Mass-Loss: Studying Evolved Stellar Winds with FUSE and HST/STIS A dissertation submitted to the University of Dublin for the degree of Doctor of Philosophy Cian Crowley Supervisor: Dr. Brian R. Espey Trinity College Dublin, July 2006 School of Physics University of Dublin Trinity College Dublin ii For Mam and Dad Declaration I hereby declare that this thesis has not been submitted as an exercise for a degree at this or any other University and that it is entirely my own work. I agree that the Library may lend or copy this thesis upon request. Signed, Cian Crowley July 25, 2006. Publications Crowley, C., Espey, B. R.,. & McCandliss, S. R., 2006, In prep., ‘FUSE and HST/STIS Observations of the Eclipsing Symbiotic Binary EG Andromedae’ Acknowledgments I wish to acknowledge and thank Brian Espey, Stephan McCandliss and Peter Hauschildt for their contributions to this work. Most especially I would like to express my gratitude to my supervisor Brian Espey for his enthusiastic supervision, patience and encourage- ment. His help, support and advice is very much appreciated. In addition, the helpful and insightful comments and advice from numerous people, inlcuding, Graham Harper, Philip Bennett, Alex Brown, Gary Ferland, Tom Ake, B-G Anderson and Dugan With- erick, were invaluable and again, very much appreciated. Also, a special word of thanks for their viva comments and feedback for Alex Brown and Peter Gallagher. This work was supported by Enterprise Ireland Basic Research grant SC/2002/370 from EU funded NDP. The FUSE data were obtained under the Guest Investigator Pro- gram and supported by NASA grants NAG5-8994 and NAG5-10403 to the Johns Hopkins University (JHU).
    [Show full text]
  • Juno Spacecraft Description
    Juno Spacecraft Description By Bill Kurth 2012-06-01 Juno Spacecraft (ID=JNO) Description The majority of the text in this file was extracted from the Juno Mission Plan Document, S. Stephens, 29 March 2012. [JPL D-35556] Overview For most Juno experiments, data were collected by instruments on the spacecraft then relayed via the orbiter telemetry system to stations of the NASA Deep Space Network (DSN). Radio Science required the DSN for its data acquisition on the ground. The following sections provide an overview, first of the orbiter, then the science instruments, and finally the DSN ground system. Juno launched on 5 August 2011. The spacecraft uses a deltaV-EGA trajectory consisting of a two-part deep space maneuver on 30 August and 14 September 2012 followed by an Earth gravity assist on 9 October 2013 at an altitude of 559 km. Jupiter arrival is on 5 July 2016 using two 53.5-day capture orbits prior to commencing operations for a 1.3-(Earth) year-long prime mission comprising 32 high inclination, high eccentricity orbits of Jupiter. The orbit is polar (90 degree inclination) with a periapsis altitude of 4200-8000 km and a semi-major axis of 23.4 RJ (Jovian radius) giving an orbital period of 13.965 days. The primary science is acquired for approximately 6 hours centered on each periapsis although fields and particles data are acquired at low rates for the remaining apoapsis portion of each orbit. Juno is a spin-stabilized spacecraft equipped for 8 diverse science investigations plus a camera included for education and public outreach.
    [Show full text]
  • 19.1 Attitude Determination and Control Systems Scott R. Starin
    19.1 Attitude Determination and Control Systems Scott R. Starin, NASA Goddard Space Flight Center John Eterno, Southwest Research Institute In the year 1900, Galveston, Texas, was a bustling direct hit as Ike came ashore. Almost 200 people in the community of approximately 40,000 people. The Caribbean and the United States lost their lives; a former capital of the Republic of Texas remained a tragedy to be sure, but far less deadly than the 1900 trade center for the state and was one of the largest storm. This time, people were prepared, having cotton ports in the United States. On September 8 of received excellent warning from the GOES satellite that year, however, a powerful hurricane struck network. The Geostationary Operational Environmental Galveston island, tearing the Weather Bureau wind Satellites have been a continuous monitor of the gauge away as the winds exceeded 100 mph and world’s weather since 1975, and they have since been bringing a storm surge that flooded the entire city. The joined by other Earth-observing satellites. This weather worst natural disaster in United States’ history—even surveillance to which so many now owe their lives is today—the hurricane caused the deaths of between possible in part because of the ability to point 6000 and 8000 people. Critical in the events that led to accurately and steadily at the Earth below. The such a terrible loss of life was the lack of precise importance of accurately pointing spacecraft to our knowledge of the strength of the storm before it hit. daily lives is pervasive, yet somehow escapes the notice of most people.
    [Show full text]
  • + New Horizons
    Media Contacts NASA Headquarters Policy/Program Management Dwayne Brown New Horizons Nuclear Safety (202) 358-1726 [email protected] The Johns Hopkins University Mission Management Applied Physics Laboratory Spacecraft Operations Michael Buckley (240) 228-7536 or (443) 778-7536 [email protected] Southwest Research Institute Principal Investigator Institution Maria Martinez (210) 522-3305 [email protected] NASA Kennedy Space Center Launch Operations George Diller (321) 867-2468 [email protected] Lockheed Martin Space Systems Launch Vehicle Julie Andrews (321) 853-1567 [email protected] International Launch Services Launch Vehicle Fran Slimmer (571) 633-7462 [email protected] NEW HORIZONS Table of Contents Media Services Information ................................................................................................ 2 Quick Facts .............................................................................................................................. 3 Pluto at a Glance ...................................................................................................................... 5 Why Pluto and the Kuiper Belt? The Science of New Horizons ............................... 7 NASA’s New Frontiers Program ........................................................................................14 The Spacecraft ........................................................................................................................15 Science Payload ...............................................................................................................16
    [Show full text]
  • Cubesat Attitude Control System Based on Embedded Magnetorquers in Photovoltaic Panels Mario Castro Santiago Junio De 2018
    Trabajo Fin de Grado en F´ısica Cubesat Attitude Control System based on embedded magnetorquers in photovoltaic panels Mario Castro Santiago Junio de 2018 Tutor: Andres´ Mar´ıa Roldan´ Aranda Departamento de Electr´onicay Tecnolog´ıade Computadores Universidad de Granada Abstract The use of magnetic actuation in order to stabilize and control a small 1U Cubesat is studied and analyzed, as a required step for the devel- opment of the future university satellite GranaSAT-I. This thesis gather crucial theoretical contents concerning the attitude control of a satellite in an orbit below 500 km, where the International Space Station is able to deploy nano-satellites. Moreover, these contents have been imple- mented in a MATLAB simulator. One stabilizing control law has been succesfully tested with this tool, and two different control algorithms have shown partial success when a 3-axis control has been required. In parallel, an autonomous Cubesat prototype has been manufactured in the GranaSAT Laboratory. The stabilizing algorithm has been imple- mented on the onboard computer. Telemetry data during tests reflect an adequate performance of the prototype. Resumen Se estudia el uso de actuadores magneticos´ con el objetivo de estabi- lizar y controlar un pequeno˜ Cubesat 1U, como paso necesario para el desarrollo futuro satelite´ universitario GranaSAT-I. Esta tesis recaba contenidos teoricos´ fundamentales respecto al control de orientacion´ de un satelite´ en una orbita´ por debajo de 500 km, donde la Estacion´ Espacial Internacional es capaz de lanzar nano-satelites.´ Ademas,´ esta teor´ıa ha sido implementada en un simulador en MATLAB. Con esta herramienta, se ha probado con exito´ un algoritmo de estabilizacion,´ y dos algoritmos de control han mostrado un exito´ parcial cuando un control en los tres ejes ha sido necesario.
    [Show full text]
  • Space Sector Brochure
    SPACE SPACE REVOLUTIONIZING THE WAY TO SPACE SPACECRAFT TECHNOLOGIES PROPULSION Moog provides components and subsystems for cold gas, chemical, and electric Moog is a proven leader in components, subsystems, and systems propulsion and designs, develops, and manufactures complete chemical propulsion for spacecraft of all sizes, from smallsats to GEO spacecraft. systems, including tanks, to accelerate the spacecraft for orbit-insertion, station Moog has been successfully providing spacecraft controls, in- keeping, or attitude control. Moog makes thrusters from <1N to 500N to support the space propulsion, and major subsystems for science, military, propulsion requirements for small to large spacecraft. and commercial operations for more than 60 years. AVIONICS Moog is a proven provider of high performance and reliable space-rated avionics hardware and software for command and data handling, power distribution, payload processing, memory, GPS receivers, motor controllers, and onboard computing. POWER SYSTEMS Moog leverages its proven spacecraft avionics and high-power control systems to supply hardware for telemetry, as well as solar array and battery power management and switching. Applications include bus line power to valves, motors, torque rods, and other end effectors. Moog has developed products for Power Management and Distribution (PMAD) Systems, such as high power DC converters, switching, and power stabilization. MECHANISMS Moog has produced spacecraft motion control products for more than 50 years, dating back to the historic Apollo and Pioneer programs. Today, we offer rotary, linear, and specialized mechanisms for spacecraft motion control needs. Moog is a world-class manufacturer of solar array drives, propulsion positioning gimbals, electric propulsion gimbals, antenna positioner mechanisms, docking and release mechanisms, and specialty payload positioners.
    [Show full text]
  • Skylab Attitude and Pointing Control System
    I' NASA TECHNICAL NOTE SKYLAB ATTITUDE AND POINTING CONTROL SYSTEM by W. B. Chzlbb and S. M. Seltzer George C. Marshall Space Flight Center Marshall Space Flight Center, Ala. 35812 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, 0. C. FEBRUARY 1971 I I TECH LIBRARY KAFB, NM .. -, - ___.. 0132813 I. REPORT NO. 2. GOVERNMNT ACCESSION NO. j. KtLIPlbNl'b LAIALOb NO. - NASA- __ TN D-6068 I I 1 1. TITLE AND SUBTITLE 5. REPORT DATE L February 1971 Skylab Attitude and Pointing Control System 6. PERFORMING ORGANIZATION CODE __- I 7. AUTHOR(S) 8. PERFORMlNG ORGANlZATlON REPORT # - W... -B. Chubb and S. M. Seltzer I 3. PERFORMING ORGANIZATION NAME AND ADDRESS 10. WORK UNIT NO. 908 52 10 0000 M211 965 21 00 0000 George C. Marshall Space Flight Center I' 1. CONTRACT OR GRANT NO. Marshall Space Flight Center, Alabama 35812 L 13. TYPE OF REPORY & PERIOD COVERED - _-- .. .- __ 2. SPONSORING AGENCY NAME AN0 ADORES5 National Aeronautics and Space Administration Technical Note Washington, D. C. 20546 14. SPONSORING AGENCY CODE -. - - I 5. SUPPLEMENTARY NOTES Prepared by: Astrionics Laboratory Science and Engineering Directorate ~- 6. ABSTRACT NASA's Marshall Space Flight Center is developing an earth-orbiting manned space station called Skylab. The purpose of Skylab is to perform scientific experiments in solar astronomy and earth resources and to study biophysical and physical properties in a zero gravity environment. The attitude and pointing control system requirements are dictated by onboard experiments. These requirements and the resulting attitude and pointing control system are presented. 18 .- 0 1 STR inUT I ONSmTEMeNT Space station Control moment gyro Unclassified - Unlimited Attitude control -~ 9.
    [Show full text]
  • 1 the New Horizons Spacecraft Glen H. Fountain, David Y
    The New Horizons Spacecraft Glen H. Fountain, David Y. Kusnierkiewicz, Christopher B. Hersman, Timothy S. Herder, Thomas B Coughlin, William T. Gibson, Deborah A. Clancy, Christopher C. DeBoy, T. Adrian Hill, James D. Kinnison, Douglas S. Mehoke, Geffrey K. Ottman, Gabe D. Rogers, S. Alan Stern, James M. Stratton, Steven R. Vernon, Stephen P. Williams Abstract The New Horizons spacecraft was launched on January 19, 2006. The spacecraft was designed to provide a platform for the seven instruments designated by the science team to collect and return data from Pluto in 2015 that would meet the requirements established by the National Aeronautics and Space Administration (NASA) Announcement of Opportunity AO-OSS-01. The design drew on heritage from previous missions developed at The Johns Hopkins University Applied Physics Laboratory (APL) and other NASA missions such as Ulysses. The trajectory design imposed constraints on mass and structural strength to meet the high launch acceleration consistent with meeting the AO requirement of returning data prior to the year 2020. The spacecraft subsystems were designed to meet tight resource allocations (mass and power) yet provide the necessary control and data handling finesse to support data collection and return when the one way light time during the Pluto fly-by is 4.5 hours. Missions to the outer regions of the solar system (where the solar irradiance is 1/1000 of the level near the Earth) require a Radioisotope Thermoelectric Generator (RTG) to supply electrical power. One RTG was available for use by New Horizons. To accommodate this constraint, the spacecraft electronics were designed to operate on less than 200 W.
    [Show full text]