Guidance, Navigation, and Control 2016
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How Doc Draper Became the Father of Inertial Guidance
(Preprint) AAS 18-121 HOW DOC DRAPER BECAME THE FATHER OF INERTIAL GUIDANCE Philip D. Hattis* With Missouri roots, a Stanford Psychology degree, and a variety of MIT de- grees, Charles Stark “Doc” Draper formulated the basis for reliable and accurate gyro-based sensing technology that enabled the first and many subsequent iner- tial navigation systems. Working with colleagues and students, he created an Instrumentation Laboratory that developed bombsights that changed the balance of World War II in the Pacific. His engineering teams then went on to develop ever smaller and more accurate inertial navigation for aircraft, submarines, stra- tegic missiles, and spaceflight. The resulting inertial navigation systems enable national security, took humans to the Moon, and continue to find new applica- tions. This paper discusses the history of Draper’s path to becoming known as the “Father of Inertial Guidance.” FROM DRAPER’S MISSOURI ROOTS TO MIT ENGINEERING Charles Stark Draper was born in 1901 in Windsor Missouri. His father was a dentist and his mother (nee Stark) was a school teacher. The Stark family developed the Stark apple that was popular in the Midwest and raised the family to prominence1 including a cousin, Lloyd Stark, who became governor of Missouri in 1937. Draper was known to his family and friends as Stark (Figure 1), and later in life was known by colleagues as Doc. During his teenage years, Draper enjoyed tinkering with automobiles. He also worked as an electric linesman (Figure 2), and at age 15 began a liberal arts education at the University of Mis- souri in Rolla. -
Kinematic Modeling of a Rhex-Type Robot Using a Neural Network
Kinematic Modeling of a RHex-type Robot Using a Neural Network Mario Harpera, James Paceb, Nikhil Guptab, Camilo Ordonezb, and Emmanuel G. Collins, Jr.b aDepartment of Scientific Computing, Florida State University, Tallahassee, FL, USA bDepartment of Mechanical Engineering, Florida A&M - Florida State University, College of Engineering, Tallahassee, FL, USA ABSTRACT Motion planning for legged machines such as RHex-type robots is far less developed than motion planning for wheeled vehicles. One of the main reasons for this is the lack of kinematic and dynamic models for such platforms. Physics based models are difficult to develop for legged robots due to the difficulty of modeling the robot-terrain interaction and their overall complexity. This paper presents a data driven approach in developing a kinematic model for the X-RHex Lite (XRL) platform. The methodology utilizes a feed-forward neural network to relate gait parameters to vehicle velocities. Keywords: Legged Robots, Kinematic Modeling, Neural Network 1. INTRODUCTION The motion of a legged vehicle is governed by the gait it uses to move. Stable gaits can provide significantly different speeds and types of motion. The goal of this paper is to use a neural network to relate the parameters that define the gait an X-RHex Lite (XRL) robot uses to move to angular, forward and lateral velocities. This is a critical step in developing a motion planner for a legged robot. The approach taken in this paper is very similar to approaches taken to learn forward predictive models for skid-steered robots. For example, this approach was used to learn a forward predictive model for the Crusher UGV (Unmanned Ground Vehicle).1 RHex-type robot may be viewed as a special case of skid-steered vehicle as their rotating C-legs are always pointed in the same direction. -
New Horizons: Reconnaissance of the Pluto-Charon System and The
C.T. Russell Editor New Horizons Reconnaissance of the Pluto-Charon System and the Kuiper Belt Previously published in Space Science Reviews Volume 140, Issues 1–4, 2008 C.T. Russell Institute of Geophysics & Planetary Physics University of California Los Angeles, CA, USA Cover illustration: NASA’s New Horizons spacecraft was launched on 2006 January 19, received a grav- ity assist during a close approach to Jupiter on 2007 February 28, and is now headed for a flyby with closest approach 12,500 km from the center of Pluto on 2015 July 14. This artist’s depiction shows the spacecraft shortly after passing above Pluto’s highly variegated surface, which may have black-streaked surface deposits produced from cryogenic geyser activity, and just before passing into Pluto’s shadow when solar and earth occultation experiments will probe Pluto’s tenuous, and possibly hazy, atmosphere. Sunlit crescents of Pluto’s moons Charon, Nix, and Hydra are visible in the background. After flying through the Pluto system, the New Horizons spacecraft could be re-targeted towards other Kuiper Belt Objects in an extended mission phase. This image is based on an original painting by Dan Durda. © Dan Durda 2001 All rights reserved. Back cover illustration: The New Horizons spacecraft was launched aboard an Atlas 551 rocket from the NASA Kennedy Space Center on 2008 January 19 at 19:00 UT. Library of Congress Control Number: 2008944238 DOI: 10.1007/978-0-387-89518-5 ISBN-978-0-387-89517-8 e-ISBN-978-0-387-89518-5 Printed on acid-free paper. -
Curriculum Vitae
DANTE S. LAURETTA Lunar and Planetary Laboratory Department of Planetary Sciences University of Arizona Tucson, AZ 85721-0092 Cell: (520) 609-2088 Email: [email protected] CHRONOLOGY OF EDUCATION Washington University, St. Louis, MO Dept. of Earth and Planetary Sciences Ph.D. in Earth and Planetary Sciences, 1997 Thesis: Theoretical and Experimental Studies of Fe-Ni-S, Be, and B Cosmochemistry Advisor: Bruce Fegley, Jr. University of Arizona, Tucson, AZ Depts. of Physics, Mathematics, and East Asian Studies B.S. in Physics and Mathematics, Cum Laude, 1993 B.A. in Oriental Studies (emphasis: Japanese), Cum Laude, 1993 CHRONOLOGY OF EMPLOYMENT Professor, Lunar and Planetary Laboratory, Dept. of Planetary Sciences, University of Arizona, Tucson, AZ; 2012 – present. Principal Investigator, OSIRIS-REx Asteroid Sample Return Mission, NASA New Frontiers Program, 2011 – present. Deputy Principal Investigator, OSIRIS-REx Asteroid Sample Return Mission, NASA New Frontiers Program, 2008 – 2011. Associate Professor, Lunar and Planetary Laboratory, Dept. of Planetary Sciences, University of Arizona, Tucson, AZ; 2006 – 2012. Assistant Professor, Lunar and Planetary Laboratory, Dept. of Planetary Sciences, University of Arizona, Tucson, AZ; 2001 – 2006. Associate Research Scientist, Dept. of Chemistry & Biochemistry, Arizona State University, Tempe, AZ; 1999 – 2001. Postdoctoral Research Associate, Dept. of Geology, Arizona State University, Tempe, AZ Primary project: Transmission electron microscopy of meteoritic minerals. Supervisor: Peter R. Buseck; Dates: 1997 – 1999. Research Assistant, Dept. of Earth and Planetary Sciences, Washington Univ., St. Louis, MO Primary project: Experimental studies of sulfide formation in the solar nebula. Advisor: Bruce Fegley, Jr.; Dates: 1993 – 1997. Research Intern, NASA Undergraduate Research Program, University of Arizona, Tucson, AZ Primary project: Development of a logic-based language for S.E.T.I. -
Modelling Bennu's Crater Development
EPSC Abstracts Vol. 14, EPSC2020-442, 2020 https://doi.org/10.5194/epsc2020-442 Europlanet Science Congress 2020 © Author(s) 2021. This work is distributed under the Creative Commons Attribution 4.0 License. Modelling Bennu's Crater Development Peter Smith, Daniella DellaGiustina, Keara Burke, Dathon Golish, and Dante Lauretta University of Arizona, Planetary Sciences, Tucson, United States of America ([email protected]) Modeling Bennu’s Crater Development P.H. Smith (1), D.N. DellaGiustina (1), K.N. Burke (1), D.R. Golish (1), D. S. Lauretta (1) (1) Lunar and Planetary Laboratory, University of Arizona, USA ([email protected]) Introduction Several hundred craters have been identified and mapped on Bennu [1]. Their spectral properties have been studied using data from the MapCam instrument onboard the OSIRIS-REx spacecraft [2]. The crater frequency versus spectral slope across the wavelength range of 0.550 µm (v band) to 0.860 µm (x band) shows a skewed distribution varying from the median spectral slope of –0.17 micron–1 (x/v = 0.948) to a neutral or flat slope (x/v = 1.0). DellaGiustina et al. [2] attribute this trend to space weathering. They suggest that freshly formed craters are red, and as they age, they evolve to the bluish slope seen across the asteroidal surface. This abstract presents the results of an age model of Bennu’s craters in the size range of 1 to 10 m. Craters in this size range were selected as having likely been formed during the time that Bennu has orbited in near-Earth space. -
Go for Lunar Landing Conference Report
CONFERENCE REPORT Sponsored by: REPORT OF THE GO FOR LUNAR LANDING: FROM TERMINAL DESCENT TO TOUCHDOWN CONFERENCE March 4-5, 2008 Fiesta Inn, Tempe, AZ Sponsors: Arizona State University Lunar and Planetary Institute University of Arizona Report Editors: William Gregory Wayne Ottinger Mark Robinson Harrison Schmitt Samuel J. Lawrence, Executive Editor Organizing Committee: William Gregory, Co-Chair, Honeywell International Wayne Ottinger, Co-Chair, NASA and Bell Aerosystems, retired Roberto Fufaro, University of Arizona Kip Hodges, Arizona State University Samuel J. Lawrence, Arizona State University Wendell Mendell, NASA Lyndon B. Johnson Space Center Clive Neal, University of Notre Dame Charles Oman, Massachusetts Institute of Technology James Rice, Arizona State University Mark Robinson, Arizona State University Cindy Ryan, Arizona State University Harrison H. Schmitt, NASA, retired Rick Shangraw, Arizona State University Camelia Skiba, Arizona State University Nicolé A. Staab, Arizona State University i Table of Contents EXECUTIVE SUMMARY..................................................................................................1 INTRODUCTION...............................................................................................................2 Notes...............................................................................................................................3 THE APOLLO EXPERIENCE............................................................................................4 Panelists...........................................................................................................................4 -
By September 1976 the Charles Stark Draper Laboratory, Inc. Cambridge
P-357 THE HISTORY OF APOLLO ON-BOARD GUIDANCE, NAVIGATION, AND CONTROL by David G. Hoag September 1976 The Charles Stark Draper Laboratory, Inc. Cambridge, Massachusetts 02139 @ The Charles Stark Draper Laboratory, Inc. , 1976. the solar pressure force on adjustable sun vanes to drive the average speed of these wheels toward zero. Overall autonomous operation was managed on-board by a small general purpose digital computer configured by its designer, Dr. Raymond Alonso, for very low power drain except at the occasional times needing fast computation speed. A special feature of this computer was the pre-wired, read-only memory called a core rope, a configuration of particularly high storage density requiring only one magnetic core per word of memory. A four volume report of this work was published in July, 1959, and presented to the Air Force Sponsors. However, since the Air Force was disengaging from civilian space development, endeavors to interest NASA were undertaken. Dr. H. Guyford Stever, then an MIT professor, arranged a presentation with Dr. Hugh Dryden, NASA Deputy Administrator, which took place on September 15.* On November 10, NASA sent a letter of in- tent to contract the Instrumentation Laboratory for a $50,000 study to start immediately. The stated purpose was that this study would con- c tribute to the efforts of NASA's Jet Propulsion Laboratory in conducting unmanned space missions to Mars, Venus, and the Earth's moon scheduled in Vega and Centaur missions in the next few years. A relationship be- tween MIT and JPL did not evolve. JPL's approach to these deep space missions involved close ground base control with their large antenna tracking and telemetry systems, considerably different from the on- board self sufficiency method which the MIT group advocated and could best support. -
The Charles Stark Draper Laboratom, Inc. Cambridge
(N ASA-CF 151088) ON-ORBIT FLIGHT CONTROL N77-10135 ALGORITHM DESCRIPTION (Draper (Charles ,Stark) Lab., Inc.) 254 p HC A12/iF A01 CSCL 22A Unclas -...-. .- .. ~ _ ~G3/16 08969 R-881 ON-ORBIT FLIGHT CONTROL ALGORITHM DESCRIPTION May 1975 The Charles Stark Draper LaboratoM, Inc. Cambridge. Massaohusefs 02139 R-881 ON-ORBIT FLIGHT CO:;TROL ALGORITHM DESCRIPTION May 1975 Approved:. N. Sears The Charles Stark Draper Laboratory, Inc. Cambridge, Massachusetts 02139 ACKNOWLEDGEMENT This report was prepared by The Charles Stark Draper Laboratory, Inc., under Contract NAS913809 with the Johnson Space Center, National Aer6 nautics and Space Administration. The following authors have contributed to the report; Yoram Baram, Edwvard Bergmann, Steven Croopnick, Louis D'Amario, Ivan Johnson, Donald Keene, Alex Penchuk, Gilbert Stubbs, John Turkovich, Joseph Turnbull, and Craig Work of the Draper Laboratory; Rick Stuva of Lockheed Electronics Company, Inc.; and Henry Kaupp, Edward Kubiak, and Kenneth Lindsay of the National Aeronautics and Space Administration. Technical coordination for the report was provided by Chris Kirchwey, George Silver and Peter Weissman of the Draper Laboratory. Design coordination between the Guid ance and Control Branch and the Draper Laboratory was carried out by Steven Croopnick. The publication of this report does not constitute approval by the National Aeronautics and Space Administration of the findings therein. It is published only for the exchange and stimulation of ideas. ii ABSTRACT The objective of the On-Orbit Flight Control Module is to provide rotational and translational control of the Space Shuttle orbiter in the Orbital Mission Phases, which are external tank separation, orbit inser tion, on-orbit and de-orbit. -
GUIDANCE, NAVIGATION, and CONTROL 2020 AAS PRESIDENT Carol S
GUIDANCE, NAVIGATION, AND CONTROL 2020 AAS PRESIDENT Carol S. Lane Cynergy LLC VICE PRESIDENT – PUBLICATIONS James V. McAdams KinetX Inc. EDITOR Jastesh Sud Lockheed Martin Space SERIES EDITOR Robert H. Jacobs Univelt, Incorporated Front Cover Illustration: Image: Checkpoint-Rehearsal-Movie-1024x720.gif Caption: “OSIRIS-REx Buzzes Sample Site Nightingale” Photo and Caption Credit: NASA/Goddard/University of Arizona Public Release Approval: Per multimedia guidelines from NASA Frontispiece Illustration: Image: NASA_Orion_EarthRise.jpg Caption: “Orion Primed for Deep Space Exploration” Photo Credit: NASA Public Release Approval: Per multimedia guidelines from NASA GUIDANCE, NAVIGATION, AND CONTROL 2020 Volume 172 ADVANCES IN THE ASTRONAUTICAL SCIENCES Edited by Jastesh Sud Proceedings of the 43rd AAS Rocky Mountain Section Guidance, Navigation and Control Conference held January 30 to February 5, 2020, Breckenridge, Colorado Published for the American Astronautical Society by Univelt, Incorporated, P.O. Box 28130, San Diego, California 92198 Web Site: http://www.univelt.com Copyright 2020 by AMERICAN ASTRONAUTICAL SOCIETY AAS Publications Office P.O. Box 28130 San Diego, California 92198 Affiliated with the American Association for the Advancement of Science Member of the International Astronautical Federation First Printing 2020 Library of Congress Card No. 57-43769 ISSN 0065-3438 ISBN 978-0-87703-669-2 (Hard Cover Plus CD ROM) ISBN 978-0-87703-670-8 (Digital Version) Published for the American Astronautical Society by Univelt, Incorporated, P.O. Box 28130, San Diego, California 92198 Web Site: http://www.univelt.com Printed and Bound in the U.S.A. FOREWORD HISTORICAL SUMMARY The annual American Astronautical Society Rocky Mountain Guidance, Navigation and Control Conference began as an informal exchange of ideas and reports of achievements among local guidance and control specialists. -
Assessment of Couple Unmanned Aerial Vehicle-Portable Magnetic
International Journal of Scientific & Engineering Research Volume 11, Issue 1, January-2020 1271 ISSN 2229-5518 Assessment of Couple Unmanned Aerial Vehicle- Portable Magnetic Resonance Imaging Sensor for Precision Agriculture of Crops Balogun Wasiu A., Keshinro K.K, Momoh-Jimoh E. Salami, Adegoke A. S., Adesanya G. E., Obadare Bolatito J Abstract— This paper proposes an improved benefits of integration of Unmanned Aerial vehicle (UAV) and Portable Magnetic Resonance Imaging (PMRI) system in relation to developing Precision Agricultural (PA) that is capable of carrying out a dynamic internal quality assessment of crop developmental stages during pre-harvest period. A comprehensive review was carried out on application of UAV technology to Precision Agriculture (PA) progress and evolving research work on developing a Portable MRI system. The disadvantages of using traditional way of obtaining Precision Agricultural (PA) were shown. Proposed Model Architecture of Coupled Unmanned Aerial vehicle (UAV) and Portable Magnetic Resonance Imaging (PMRI) System were developed and the advantages of the proposed system were displayed. It is predicted that the proposed method can be useful for Precision Agriculture (PA) which will reduce the cost implication of Pre-harvest processing of farm produce based on non-destructive technique. Index Terms— Unmanned Aerial vehicle, Portable Magnetic Resonance Imaging, Precision Agricultural, Non-destructive, Pre-harvest, Crops, Imaging, Permanent magnet —————————— —————————— 1 INTRODUCTION URING agricultural processing, quality control ensure Inspection of fresh fruit bunches (FFB) for harvesting is a rig- that food products meet certain quality and safety stand- orous assignment which can be overlooked or applied physi- D ards in a developed country [FAO]. Low profits in fruit cal counting that are usually not accurate or precise (Sham- farming are subjected by pre- and post-harvest factors. -
(Preprint) AAS 16-113 ORION BURN MANAGEMENT, NOMINAL AND
(Preprint) AAS 16-113 ORION BURN MANAGEMENT, NOMINAL AND RESPONSE TO FAILURES Ryan Odegard,∗ John L. Goodman,y Charles P. Barrett,z Kara Pohlkamp,x and Shane Robinson{ An approach for managing Orion on-orbit burn execution is described for nom- inal and failure response scenarios. The burn management strategy for Orion takes into account per-burn variations in targeting, timing, and execution; crew and ground operator intervention and overrides; defined burn failure triggers and responses; and corresponding on-board software sequencing functionality. Burn- to-burn variations are managed through the identification of specific parameters that may be updated for each progressive burn. Failure triggers and automatic re- sponses during the burn timeframe are defined to provide safety for the crew in the case of vehicle failures, along with override capabilities to ensure operational control of the vehicle. On-board sequencing software provides the timeline coor- dination for performing the required activities related to targeting, burn execution, and responding to burn failures. INTRODUCTION The trend of increasing automation and autonomy of NASA’s crewed spacecraft continues with Orion. The exploration mission flight profiles, communications time delays, and a requirement for vehicle return in the event of loss of communications drive a need for a greater level of on- board automation (no human interaction with the flight computer or spacecraft) and autonomy (no Mission Control interaction with the spacecraft or crew). Management of on-board systems for burns is a major factor in the design of the Orion automation and sequencing. The design must also accommodate crew or Mission Control override of automated burn sequencing. -
The Meteoritical Society Newsletter 2001
SUPPLEMENT TO METEORITICS & PLANETARY SCIENCE, VOL. 36, 11 The Meteoritical Society Newsletter (November 2001) A report of the business carried out by the Society over the past year, edited by Edward Scott, Secretary. PRESIDENT'S EDITORIAL Nomenclature President's Editorial Gero Kurat There are some indications that SNC meteorites could originate from Mars, there are others that relate them to carbonaceous Things usually turn out somewhat different from what one expects chondrites. Among the advocates for a martian origin is also the them to be and this was exactly so also with my first few months in foremost expert on these meteorites, Hap McSween. Some colleagues office. I was positively surprised by the amount of activities initiated neglect the possibility that SNC meteorites could not come from Mars by members of our Society. The overwhelmingly constructive and call them "martian meteorites". Others prefer to call them contributions make investing time for the Society a joy. There are, "SNICs", for obvious reasons. Hap has this year been honored for however, also some unsolved problems which do not create instant his work on "martian meteorites". As the possibility for a non-martian joy but whose solution eventually could lead to improvements origin of SNC meteorites still exists, a curious conundrum emerges: beneficial for all of us. So joy is awaiting us afterwards. Us means how could Hap have done this wonderful work on something that the Council and in particular the Secretary of the Society who does possibly does not exist? Please help us to solve that riddle—the best an excellent job in spite of the bumpy communication between our three solutions will receive prizes.