Towards Star Tracker Only Attitude Estimation
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
Deep Space Craft an Overview of Interplanetary Flight Dave Doody Deep Space Craft an Overview of Interplanetary Flight
Deep Space Craft An Overview of Interplanetary Flight Dave Doody Deep Space Craft An Overview of Interplanetary Flight Published in association with PPraxisraxis PPublishiublishingng Chichester, UK Dave Doody NASA Jet Propulsion Laboratory (Caltech) Pasadena California USA Front cover illustrations: (Upper) Artist's rendition of the Dawn spacecraft operating its ion propulsion system upon arrival at the main-belt asteroid Vesta in 2011. Image courtesy McRel, Mid-continent Research for Education and Learning. (Next lower) Artist's concept of the Phoenix lander operating in the Martian Arctic, as it did from May to November 2008. Image courtesy University of Arizona. (Lower left) Artist's concept of the Cassini spacecraft as it operates in Saturn orbit July 2004 through the present day. Back cover illustrations: (Left) A near-duplicate of the Mars Phoenix lander used in developing command sequences before being sent to the spacecraft. Here, members of the Robotic Arm Engineering Team test the arm's motorized raft in the Payload Interoperability Testbed at the University of Arizona, Tucson in July 2008. Image courtesy University of Arizona. (Right) Rob Manning, Chief Engineer of NASA's Mars Exploration Program, cheers along with other team members as the ®rst images from rover Spirit come back from Mars. Courtesy NASA/Bill Ingalls. SPRINGER±PRAXIS BOOKS IN ASTRONAUTICAL ENGINEERING SUBJECT ADVISORY EDITOR: John Mason M.B.E., B.Sc., M.Sc., Ph.D. ISBN 978-3-540-89509-1 Springer Berlin Heidelberg New York Springer is part of Springer-Science + Business Media (springer.com) Library of Congress Control Number: 2008943657 Apart from any fair dealing for the purposes of research or private study, or criticism or review, as permitted under the Copyright, Designs and Patents Act 1988, this publication may only be reproduced, stored or transmitted, in any form or by any means, with the prior permission in writing of the publishers, or in the case of reprographic reproduction in accordance with the terms of licences issued by the Copyright Licensing Agency. -
Mp-Avt-171-09
UNCLASSIFIED/UNLIMITED Attitude Determination and Control of Future Small Satellites H. Ersin Soken, A. Rustem Aslan and Chingiz Hajiyev Aeronautics and Astronautics Faculty Istanbul Technical University Istanbul, TURKEY [email protected]/[email protected]/[email protected] ABSTRACT As well as other subsystems, Attitude Determination and Control System (ADCS) development is a challenging process for small satellites because of design limitations, such as size, weight and the power consumption. Besides, if they are thought in a concept with military missions, then the requirement for a high attitude pointing accuracy is something certain. Works on the effective attitude determination and control methods for small satellites can be accepted as a part of this struggle. In this paper, problems that are met during ADCS development phase for future small satellites are stated and possible solutions are suggested. 1.0 INTRODUCTION Since their first appearance, small satellites have begun to play a more and more important role in space researches and today, they have a certain share in astronautic applications, especially about new technology demonstration. Because of many advantages such as low investment and operational costs, enabling COTS (commercial of the shell) technology in space, short system development periods etc. they have been highly preferred to their larger competitors. More than 400 micro satellites launched in the last 20 years is a good proof for that [1]. Mini Satellite 100-500 kg Micro Satellite 10-100 kg Nano Satellite 1-10 kg Pico Satellite 0.1-1 kg Table 1: Small satellite classification. Although they have been investigated in depth, there are still many steps to be taken in the development phase of these types of satellites and an important field to be examined is their attitude determination and control systems (ADCS). -
Small Satellite Platform Imaging X-Ray Polarimetry Explorer (IXPE
Small Satellite Platform Imaging X-Ray Polarimetry Explorer (IXPE) Mission Concept and Implementation (SSC18-V-XX) 32nd Annual Small Satellite Conference, Logan, UT, USA 4-9 August 2018 7 August: 14:00 – 14:15 Presented by: Dr. William Deininger Ball Aerospace This work was authored by employees of Ball Aerospace under Contract No.NNM16581489R with the National Aeronautics and Space Administration. The United States Government retains and the publisher, by accepting the article for publication, acknowledges that the United States Government retains a non-exclusive, paid-up, irrevocable, worldwide license to reproduce, prepare derivative works, distribute copies to the public, and perform publicly and display publicly, or allow others 1 to do so, for United States Government purposes. All other rights are reserved by the copyright owner. CO-AUTHORS . William Kalinowski – IXPE Spacecraft Lead and . Scott Mitchell – IXPE Mission Design Lead, Ball C&DH Lead, Ball . Sarah Schindhelm – IXPE Structural Design . Jeff Bladt – IXPE ADCS Lead, Ball Lead, Ball . Zach Allen – IXPE EPDS and Electrical Systems . Janice Houston – IXPE Lead Systems Engineer, Lead, Ball MSFC . Kyle Bygott – IXPE Spacecraft FSW Lead, Ball . Brian Ramsey – IXPE Deputy Principal . Brian Smith – IXPE AI&T Manager, Ball Investigator (DPI), MSFC . Colin Peterson – IXPE Mission Operations . Stephen O’Dell – IXPE Project Scientist, MSFC Manager, Ball . Michele Foster – IXPE V&V Engineer, MSFC . Spencer Antoniak – IXPE Launch Services, Ball . Ettore Del Monte – IXPE Instrument Systems . Jim Masciarelli – IXPE Metrology and Payload Engineering Lead, IAPS/INAF Systems Lead, Ball . Francesco Santoli – IXPE Instrument Systems . Jennifer Erickson – IXPE Requirement Lead, Ball Engineering, IAPS/INAF . Sandra Johnson – IXPE Telecommunications . -
JPL Has Once Again Closed out the Year in Style. Less Than a Month
Jet DECEMBER Propulsion 2006 Laboratory VOLUME 36 NUMBER 17 2006 INREVIEW By Mark Whalen JPL has once again closed out the year in style. Less than a month after the announcement that Mars Global Surveyor has likely finished its operat- ing career, the most productive Mars mission in history came through with the explosive news in December that its photographs have revealed bright new deposits in two gullies on Mars that suggest water carried sediment A gully as imaged by Mars Global Surveyor liquid water was involved in its genesis. through them sometime during the is shown at left in August 1999 and at right However, this observation and a similar in September 2005. The images show the light-toned flow in Terra Sirenum to- past seven years. southeast wall of an unnamed crater in the gether show that some gully sites are Centauri Montes region. No light-toned indeed changing today, providing tanta- In the meantime, the Laboratory con- deposit was present in August 1999, but lizing evidence there might be sources of appeared by February 2004. The new light- liquid water beneath the surface of Mars tinues its studies of the solar system toned flow, by itself, does not prove that right now. and beyond, with 15 spacecraft, two rovers, seven science instruments and three Earth observatories all meeting or exceeding their require- ments. Following are some highlights, chronologically, from 2006. Continued on page 2 2 niverse CONT'D U 2006INREVIEW A new image from the Galaxy Evolution Explorer completed MARCH a multi-wavelength, neon-col- Cassini found what may be evidence ored portrait of the enormous of liquid water reservoirs that erupt in Cartwheel galaxy after a smaller Yellowstone-like geysers on Saturn’s galaxy plunged through it, trigger- moon Enceladus. -
CONSTELLATION an Official Publication of the Bucks-Mont Astronomical Association, Inc
CONSTELLATION An Official Publication of the Bucks-Mont Astronomical Association, Inc. April/May/June Chris Sommers and VOLUME 23, Issue No. 2 2008 Scott Petersen, Editors © BMAA, Inc. 2008 BMAA News BMAA has had a busy spring, despite almost all of our StarWatches being clouded out. In April we attended an open house at Montgomery County Community College’s Observatory, and Dwight Dulsky and Lou Vittorio made presentations at Upper Moreland Middle School. In May we had our Astronomy Day exhibit set up in Peddler’s Village in New Hope and Dwight Dulsky led the effort at the Bucks County Science Teachers Association’s semi- annual meeting in Doylestown. We have a lot to look forward to this summer, including the summer triangle, summer globular clusters (see Orum Stringer’s List in this Issue) including M56 as described by Alan Pasicznyk, jovial Jupiter and its parade of double shadow transits, and multiple occultations of Antares by the Moon. Happy observing BMAAers!!! Summer Planetary Jewel: Jovial Jupiter Courtesy of Steve Olson BMAA Gophers Position Name President Dwight Dulsky Vice President Bernie Kosher Treasurer Ed Radomski Secretary Herb Borteck Star Watch Coordinator George Reagan Constellation Editors Chris Sommers and Scott Petersen Webmaster Jim Moyer For More Information About BMAA Go to www.bma2.org. 1 ****** Alan's Collection of Excellent Deep Sky Objects Through a 4.5 Inch Newtonian. Raisins in a Pie", M56 ¾ Alan Pasicznyk When I finally located the dim glow of M56 for the first time on July 15, 1991, I was expecting to find nothing more than "just another globular cluster" to log into my list of Messier objects. -
FY 2002 Performance and Accountability Report FY 2002 Was the Second Year of Continuous, Permanent Human Habitation of the International Space Station
National Aeronautics and Space Administration Fiscal Year 2002 Performance and Accountability Report Contents NASAVision and Mission Part I: Management’s Discussion and Analysis Transmittal Letter 6Message From the Administrator 8Reliability and Completeness of Financial and Performance Data 9Federal Managers’ Financial Integrity Act Statement of Assurance Overview 13Mission 13Organizational Structure 15Highlights of Performance Goals and Results 53Actions Planned to Achieve Key Unmet Goals 53Looking Forward 55Analysis of Financial Statements 55Systems, Controls, and Legal Compliance 56Integrity Act Material Weaknesses and Non-Conformances 58Additional Key Management Information 58The President’s Management Agenda 71Management Challenges and High-Risk Areas Part II: Performance 84Summary of Annual Performance by Strategic Goals Performance Discussion 87Space Science 99Earth Science 109Biological and Physical Research 117Human Exploration and Development of Space 123Aerospace Technology Supporting Data 133Space Science 145Earth Science 173Biological and Physical Research 185Human Exploration and Development of Space 193Aerospace Technology 209Manage Strategically Crosscutting Process 219Provide Aerospace Products and Capabilities Crosscutting Process 223Generate Knowledge Crosscutting Process 225Communicate Knowledge Crosscutting Process Part III: Financial 233Letter From the Chief Financial Officer Financial Statements and Related Auditor’s Reports 236Financial Overview 238Financial Statements 267Auditor’s Reports NASA Office of Inspector -
Mars Earth Return Vehicle (MERV) Propulsion Options
Mars Earth Return Vehicle (MERV) Propulsion Options Steven R. Oleson,1 Melissa L. McGuire,2 Laura Burke,3 James Fincannon,4 Joe Warner,5 Glenn Williams,6 and Thomas Parkey7 NASA Glenn Research Center, Cleveland, Ohio 44135 Tony Colozza,8 Jim Fittje,9 Mike Martini,10 and Tom Packard11 Analex Corporation, Cleveland, Ohio 44135 Joseph Hemminger12 N&R Engineering, Cleveland, Ohio 44135 John Gyekenyesi13 ASRC Engineering, Cleveland, Ohio 44135 The COMPASS Team was tasked with the design of a Mars Sample Return Vehicle. The current Mars sample return mission is a joint National Aeronautics and Space Administration (NASA) and European Space Agency (ESA) mission, with ESA contributing the launch vehicle for the Mars Sample Return Vehicle. The COMPASS Team ran a series of design trades for this Mars sample return vehicle. Four design options were investigated: Chemical Return /solar electric propulsion (SEP) stage outbound, all-SEP, all chemical and chemical with aerobraking. The all-SEP and Chemical with aerobraking were deemed the best choices for comparison. SEP can eliminate both the Earth flyby and the aerobraking maneuver (both considered high risk by the Mars Sample Return Project) required by the chemical propulsion option but also require long low thrust spiral times. However this is offset somewhat by the chemical/aerobrake missions use of an Earth flyby and aerobraking which also take many months. Cost and risk analyses are used to further differentiate the all-SEP and Chemical/Aerobrake options. 1COMPASS Lead, DSB0, 21000 Brookpark Road, and AIAA Senior Member. 2COMPASS Integration Lead, DSB0, 21000 Brookpark Road, non-member. 3Mission Designer, DSB0, 21000 Brookpark Road, and Non-Member. -
Status of Solar Sail Propulsion: Moving Toward an Interstellar Probe
https://ntrs.nasa.gov/search.jsp?R=20070037462 2019-08-30T01:59:41+00:00Z Status of Solar Sail Propulsion: Moving Toward an Interstellar Probe Les Johnson, Roy M. Young, and Edward E. Montgomery IV NASA George C. Marshall Space Flight Center, Huntsville. AL 35812 Abstract. NASA's In-Space Propulsion Technology Program has developed the first- generation of solar sail propulsion systems sufficient to accomplish inner solar system science and exploration missions. These first-generation solar sails, when operational, will range in size from 40 meters to well over 100 meters in diameter and have an areal density of less than 13 grams-per-square meter. A rigorous, multiyear technology development effort culminated last year in the testing of two different 20-meter solar sail systems under thermal vacuum conditions. This effort provided a number of significant insights into the optimal design and expected performance of solar sails as well as an understanding of the methods and costs of building and using them. In a separate effort, solar sail orbital analysis tools for mission design were developed and tested. Laboratory simulations of the effects of long-term space radiation exposure were also conducted on two candidate solar sail materials. Detailed radia- tion and charging environments were defined for mission trajectories outside the protection of the earth's magnetosphere, in the solar wind environment. These were used in other analytical tools to prove the adequacy of sail design features for accommodating the harsh space environment. Preceding, and in conjunction with these technology efforts, NASA sponsored several mission application studies for solar sails, including one that would use an evolved sail capa- bility to support humanity's first mission into nearby interstellar space. -
Development and Implementation of Star Tracker Electronics
DEGREE PROJECT, IN SYSTEMS, CONTROL & ROBOTICS , SECOND LEVEL STOCKHOLM, SWEDEN 2014 Development and Implementation of Star Tracker Electronics MARCUS LINDH KTH ROYAL INSTITUTE OF TECHNOLOGY ELECTRICAL ENGINEERING, SPACE AND PLASMA PHYSICS DEPARTMENT Development and Implementation of Star Tracker Electronics MARCUS LINDH, [email protected] Stockholm 2014 Space and Plasma Physics School of Electrical Engineering Kungliga Tekniska Hogskolan¨ XR-EE-SPP 2014:001 i Development and Implementation of Star Tracker Electronics Abstract Star trackers are essential instruments commonly used on satellites. They pro- vide precise measurement of the orientation of a satellite and are part of the at- titude control system. For cubesats star trackers need to be small, consume low power and preferably cheap to manufacture. In this thesis work the electronics for a miniature star tracker has been developed. A star detection algorithm has been implemented in hardware logic, tested and verified. A platform for continued work is presented and future improvements of the current implementation are discussed. Utveckling och implementering av elektronik for¨ en stjarnkamera¨ Sammanfattning Stjarnkameror¨ ar¨ vanligt forekommande¨ instrument på satelliter. De tillhan- dahåller information om satellitens orientering med mycket hog¨ precision och ar¨ en viktig del i satellitens reglersystem. For¨ kubsatelliter måste dessa vara små, stromsnåla¨ och helst billiga att tillverka. I detta examensarbete har elektroniken for¨ en sådan stjarnkamera¨ utvecklats. En algoritm som detekterar stjarnor¨ har im- plementerats i hårdvara, testats och verifierats. En hårdvaruplattform som fortsatt arbete kan utgå ifrån har skapats och forslag¨ på forb¨ attringar¨ diskuteras. keywords miniature star tracker, cubesat, real-time blob detection, FPGA image processing, CMOS image sensor, smartfusion2 SoC, attitude control, hardware development ii Acknowledgements During frustrating and seemingly impossible problems, my super- visors Nicola Schlatter and Nickolay Ivchenko have been of great support. -
Volume 134Preliminary3.Indd
CONTENTS Page FOREWORD vii PREFACE ix Part I SESSION 1: ORBIT DETERMINATION 1 1 Algorithm of Automatic Detection and Analysis of Non-Evolutionary Changes in Orbital Motion of Geocentric Objects (AAS 09-103) Sergey Kamensky, Andrey Tuchin, Victor Stepanyants and Kyle T. Alfriend . 3 Deriving Density Estimates Using CHAMP Precision Orbit Data for Periods of High Solar Activity (AAS 09-104) Andrew Hiatt, Craig A. McLaughlin and Travis Lechtenberg ......23 Geosat Follow-on Precision Orbit Improvement through Drag Model Update (AAS 09-105) Stephen R. Mance, Craig A. McLaughlin, Frank G. Lemoine, David D. Rowlands, and Paul J. Cefola ............43 On Preliminary Orbit Determination: A New Approach (AAS 09-106) Reza Raymond Karimi and Daniele Mortari...........63 Comparision of Different Methods of LEO Satellite Orbit Determination for a Single Pass Through a Radar (AAS 09-107) Zakhary N. Khutorovsky, Sergey Yu. Kamensky, Nickolay N. Sbytov and Kyle T. Alfriend .................71 Passive Multi-Target Tracking with Application to Orbit Determination for Geosynchronous Objects (AAS 09-108) Kyle J. DeMars and Moriba Jah ..............89 SESSION 2: RENDEZVOUS, RELATIVE MOTION, FORMATION FLIGHT AND SATELLITE CONSTELLATIONS 1 101 A Cooperative Egalitarian Peer-to-Peer Strategy for Refueling Satellites in Circular Constellations (AAS 09-109) Atri Dutta and Panagiotis Tsiotras .............103 An Investigation of Teardrop Relative Orbits for Circular and Elliptical Chief Satellites (AAS 09-110) David J. Irvin Jr., Richard G. Cobb and T. Alan Lovell .......121 xiii Page Control System Design and Simulation of Spacecraft Formations Via Leader-Follower Approach (AAS 09-111) Mahmut Reyhanoglu.................141 Decentralized Optimization for Control of Satellite Imaging Formations in Complex Regimes (AAS 09-112) Lindsay D. -
General Disclaimer One Or More of the Following Statements May Affect This Document
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) • I MARINER LIARS 1949 NAVIGATION. C;UMANC E, A..ND CON'rizoi.e John It. Scull Manager. Ottidanc a and Control Division Jet Propulsion Laboratory. California Institute of Technology Ydsadena. California ^v 3 VO %!T q4taus 4.6 N69 -41014 ^TM^W sAA YMK^ I^ ,.,,.sue 1<ATtNAr1 ^ A N Y Ir n: This paper presents the results of one phase of research carried out at the Jet Propulsion Laboratory, California Institute of Technology. under Contract No. NAS 7- 100, sponsored by the National Aero- nautics and Space Administration. I r 7 • } Design, mcchanirAtioit. snd flight test result% of th: • Mariner Ma rr &'969 navigation, guidance. and control systems are %umma rized. A trajectory deaign section describ4• -+ near-rarth launch trajectory, planetary targeting, and constraints, as well as the trad.-off's made on the traj ectory selection. -
Aas 03-003 the Inertial Stellar Compass: a Multifunction
AAS 03-003 THE INERTIAL STELLAR COMPASS: A MULTIFUNCTION, LOW POWER, ATTITUDE DETERMINATION TECHNOLOGY BREAKTHROUGH T. Brady, S. Buckley Charles Stark Draper Laboratory, Inc. Systems Engineering and Evaluation Directorate Cambridge, MA 02139 C. J. Dennehy, J. Gambino, A. Maynard NASA Goddard Space Flight Center (GSFC) Guidance, Navigation, and Control Division Greenbelt, MD 20771 The Inertial Stellar Compass (ISC) is a miniature, low power, stellar inertial attitude determination system with an accuracy of better than 0.1º (1 sigma) in three axes. The ISC consumes only 3.5 Watts of power and is contained in a 2.5 kg package. With its embedded on- board processor, the ISC provides attitude quaternion information and has Lost-in-Space (LIS) initialization capability. The attitude accuracy and LIS capability are provided by combining a wide field of view Active Pixel Sensor (APS) star camera and Micro- ElectroMechanical System (MEMS) inertial sensor information in an integrated sensor system. The performance and small form factor make the ISC a useful sensor for a wide range of missions. In particular, the ISC represents an enabling, fully integrated, micro- satellite attitude determination system. Other applications include using the ISC as a “single sensor” solution for attitude determination on medium performance spacecraft and as a “bolt on” independent safe-hold sensor or coarse acquisition sensor for many other spacecraft. NASA's New Millennium Program (NMP) has selected the ISC technology for a Space Technology 6 (ST6) flight validation experiment scheduled for 2004. NMP missions, such as ST6, are intended to validate advanced technologies that have not flown in space in order to reduce the risk associated with their infusion into future NASA missions.