Method for Rapid Interplanetary Trajectory Analysis Using Δv Maps with Flyby Options
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Machine Learning Regression for Estimating Characteristics of Low-Thrust Transfers
MACHINE LEARNING REGRESSION FOR ESTIMATING CHARACTERISTICS OF LOW-THRUST TRANSFERS A Thesis Presented to The Academic Faculty By Gene L. Chen In Partial Fulfillment of the Requirements for the Degree Master of Science in the School of Aerospace Engineering Georgia Institute of Technology May 2019 Copyright c Gene L. Chen 2019 MACHINE LEARNING REGRESSION FOR ESTIMATING CHARACTERISTICS OF LOW-THRUST TRANSFERS Approved by: Dr. Dimitri Mavris, Advisor Guggenheim School of Aerospace Engineering Georgia Institute of Technology Dr. Alicia Sudol Guggenheim School of Aerospace Engineering Georgia Institute of Technology Dr. Michael Steffens Guggenheim School of Aerospace Engineering Georgia Institute of Technology Date Approved: April 15, 2019 To my parents, thanks for the support. ACKNOWLEDGEMENTS Firstly, I would like to thank Dr. Dimitri Mavris for giving me the opportunity to pursue a Master’s degree at the Aerospace Systems Design Laboratory. It has been quite the experience. Also, many thanks to my committee members — Dr. Alicia Sudol and Dr. Michael Steffens — for taking the time to review my work and give suggestions on how to improve - it means a lot to me. Additionally, thanks to Dr. Patel and Dr. Antony for helping me understand their work in trajectory optimization. iv TABLE OF CONTENTS Acknowledgments . iv List of Tables . vii List of Figures . viii Chapter 1: Introduction and Motivation . 1 1.1 Thesis Overview . 4 Chapter 2: Background . 5 Chapter 3: Approach . 17 3.1 Scenario Definition . 17 3.2 Spacecraft Dynamics . 18 3.3 Choice Between Direct and Indirect Method . 19 3.3.1 Chebyshev polynomial method . 20 3.3.2 Sims-Flanagan method . -
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 -
Stardust Comet Flyby
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Stardust Comet Flyby Press Kit January 2004 Contacts Don Savage Policy/Program Management 202/358-1727 NASA Headquarters, Washington DC Agle Stardust Mission 818/393-9011 Jet Propulsion Laboratory, Pasadena, Calif. Vince Stricherz Science Investigation 206/543-2580 University of Washington, Seattle, WA Contents General Release ……………………………………......………….......................…...…… 3 Media Services Information ……………………….................…………….................……. 5 Quick Facts …………………………………………..................………....…........…....….. 6 Why Stardust?..................…………………………..................………….....………......... 7 Other Comet Missions ....................................................................................... 10 NASA's Discovery Program ............................................................................... 12 Mission Overview …………………………………….................……….....……........…… 15 Spacecraft ………………………………………………..................…..……........……… 25 Science Objectives …………………………………..................……………...…........….. 34 Program/Project Management …………………………...................…..…..………...... 37 1 2 GENERAL RELEASE: NASA COMET HUNTER CLOSING ON QUARRY Having trekked 3.2 billion kilometers (2 billion miles) across cold, radiation-charged and interstellar-dust-swept space in just under five years, NASA's Stardust spacecraft is closing in on the main target of its mission -- a comet flyby. "As the saying goes, 'We are good to go,'" said project manager Tom Duxbury at NASA's Jet -
+ 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 -
Giant Planet / Kuiper Belt Flyby
Giant Planet / Kuiper Belt Flyby Amanda Zangari (SwRI) Tiffany Finley (SwRI) with Cecilia Leung (LPL/SwRI) Simon Porter (SwRI) OPAG: February 23, 2017 Take Away • New Horizons provided scientifically valuable exploration of the Kuiper Belt in the New Frontiers cost cap. • The Kuiper Belt is full of objects with a diverse range of stories that go beyond what we learned from Pluto. • Giant Planet flybys add scientific value to a Kuiper Belt mission • Found preliminary trajectory examples for high interest KBOs-- Haumea, Varuna, 2015 RR245 can be reached via Jupiter AND Saturn, Uranus or Neptune flyby in the 2030s. • To be a candidate New Frontiers mission, a 2 Giant planet+KBO mission must be endorsed by a decadal survey according to current rules. New Horizons Heritage NH Jupiter Encounter planned around Pluto flyby timing, which was dominated by achieving quadruple occultations, “interesting” side up. New Horizons Heritage Pluto flyby took advantage of Ecliptic crossing, enabling access to the cold classical belt (where 2014 MU69 is located). New Horizons Heritage 2014 MU69 discovered while in flight. Targeting was from spacecraft propulsion and took advantage of cold classical population density. Object is small, reddish ~40 km diameter. Saturn’s moons show incredible diversity NASA/JPL As do Uranus and Neptune Some Kuiper Belt Geography Where do we want to go? Getting there- JGA “anytime” New Horizons model: Fast Launch, Jupiter Flyby, Launch window every 11 years McGranaghan et al 2011 Can we go to more than just Jupiter? If so, where, what? New Horizons 2 • 2008 launch using New Horizons flight spares • Proposed Jupiter flyby, equinox flyby of Uranus, and flyby of (47171) 1999 TC36 (now know to be trinary). -
NASA's MESSENGER Sends Flyby Data to Earth Using
Press Release For immediate release Special Delivery: NASA’s MESSENGER Sends Flyby Data to Earth Using CCSDS File Delivery Protocol Developed for Deep Space by International Team WASHINGTON, Aug. 10 (CCSDS) – NASA’s MESSENGER team is using the CCSDS File Delivery Protocol (CFDP), a highly specialized protocol designed to overcome space operations communications challenges, to download data captured during a successful flyby of Earth last week. A team of international space data communications experts, collaborating through the Consultative Committee for Space Data Systems (CCSDS), developed CFDP to reliably and efficiently downlink files from a spacecraft even in the strenuous environment of deep space. Since the MESSENGER spacecraft’s launch a year ago, it has successfully used CFDP to enable mission communications and will use it throughout its 7.9-billion kilometer journey to Mercury. In using CFDP, MESSENGER communications represents a change in the standard method of storing science and housekeeping data on spacecraft built by the Johns Hopkins University Applied Physics Laboratory (JHU/APL). MESSENGER is also the first U.S. space flight mission to use CFDP in mission operations. Prior to MESSENGER, JHU/APL missions used a raw storage model of storing data, but new mission and operational requirements meant that MESSENGER would have to incorporate a file system of data storage into its spacecraft software architecture. A reliable method of downlinking files to the ground had to be found and CFDP was chosen by mission planners to do the job. CFDP is included in the MESSENGER software architecture through a reuse of a NASA Jet Propulsion Lab (NASA JPL) implementation on the ground and a JHU/APL “CFDP-lite” implementation on the flight side. -
Mariner to Mercury, Venus and Mars
NASA Facts National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Pasadena, CA 91109 Mariner to Mercury, Venus and Mars Between 1962 and late 1973, NASA’s Jet carry a host of scientific instruments. Some of the Propulsion Laboratory designed and built 10 space- instruments, such as cameras, would need to be point- craft named Mariner to explore the inner solar system ed at the target body it was studying. Other instru- -- visiting the planets Venus, Mars and Mercury for ments were non-directional and studied phenomena the first time, and returning to Venus and Mars for such as magnetic fields and charged particles. JPL additional close observations. The final mission in the engineers proposed to make the Mariners “three-axis- series, Mariner 10, flew past Venus before going on to stabilized,” meaning that unlike other space probes encounter Mercury, after which it returned to Mercury they would not spin. for a total of three flybys. The next-to-last, Mariner Each of the Mariner projects was designed to have 9, became the first ever to orbit another planet when two spacecraft launched on separate rockets, in case it rached Mars for about a year of mapping and mea- of difficulties with the nearly untried launch vehicles. surement. Mariner 1, Mariner 3, and Mariner 8 were in fact lost The Mariners were all relatively small robotic during launch, but their backups were successful. No explorers, each launched on an Atlas rocket with Mariners were lost in later flight to their destination either an Agena or Centaur upper-stage booster, and planets or before completing their scientific missions. -
Orbital Fueling Architectures Leveraging Commercial Launch Vehicles for More Affordable Human Exploration
ORBITAL FUELING ARCHITECTURES LEVERAGING COMMERCIAL LAUNCH VEHICLES FOR MORE AFFORDABLE HUMAN EXPLORATION by DANIEL J TIFFIN Submitted in partial fulfillment of the requirements for the degree of: Master of Science Department of Mechanical and Aerospace Engineering CASE WESTERN RESERVE UNIVERSITY January, 2020 CASE WESTERN RESERVE UNIVERSITY SCHOOL OF GRADUATE STUDIES We hereby approve the thesis of DANIEL JOSEPH TIFFIN Candidate for the degree of Master of Science*. Committee Chair Paul Barnhart, PhD Committee Member Sunniva Collins, PhD Committee Member Yasuhiro Kamotani, PhD Date of Defense 21 November, 2019 *We also certify that written approval has been obtained for any proprietary material contained therein. 2 Table of Contents List of Tables................................................................................................................... 5 List of Figures ................................................................................................................. 6 List of Abbreviations ....................................................................................................... 8 1. Introduction and Background.................................................................................. 14 1.1 Human Exploration Campaigns ....................................................................... 21 1.1.1. Previous Mars Architectures ..................................................................... 21 1.1.2. Latest Mars Architecture ......................................................................... -
EPOXI COMET ENCOUNTER FACT SHEET Nov
EPOXI COMET ENCOUNTER FACT SHEET Nov. 2, 2010 Quick Facts Flyby Spacecraft Dimensions: 3.3 meters (10.8 feet) long, 1.7 meters (5.6 feet) wide, and 2.3 meters (7.5 feet) high Weight: 601 kilograms (1,325 pounds) at launch, consisting of 517 kilograms (1,140 pounds) spacecraft and 84 kilograms (185 pounds) fuel. On 10/25/10 there was 4 kilograms (8.8 pounds) of fuel remaining. Power: 2.8-meter-by-2.8-meter (9-foot-by-9 foot) solar panel providing up to 750 watts, depending on distance from sun. Power storage via small, 16-amp- hourrechargeable nickel hydrogen battery Comet Hartley 2 Nucleus shape: Elongated Nucleus size (estimated): About 2.2 kilometers (1.4 miles) long Nucleus mass: Roughly 280 million metric tons Nucleus rotation period: About 18 hours Nucleus composition: Water ice, carbon dioxide ice, silicate dust Mission Launch: Jan. 12, 2005 Launch site: Cape Canaveral Air Force Station, Florida Launch vehicle: Delta II 7925 with Star 48 upper stage Impact with Tempel 1: 10:52 p.m. PDT July 3, 2005 (1:52 a.m. EDT July 4, 2005) Earth-comet distance at time of impact: 133.6 million kilometers (83 million miles) Total distance traveled by spacecraft from Earth to Tempel 1: 431 million kilometers (268 million miles) Flyby of Hartley 2: About 10 a.m. EDT or 7 a.m. PDT Nov. 4, 2010 Additional distance traveled by spacecraft to Hartley 2: About 4.6 billion kilometers (2.9 billion miles) Program Cost of Deep Impact: $267 million total (not including launch vehicle), consisting of $252 million spacecraft development and $15 million mission operations Cost of EPOXI extended mission: $42 million, for operations from 2007 to end of project at the end of fiscal year 2011. -
A Manned Flyby Mission to Eros
The Space Congress® Proceedings 1966 (3rd) The Challenge of Space Mar 7th, 8:00 AM A Manned Flyby Mission to Eros Eugene A. Smith Northrop Space Laboratories Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Smith, Eugene A., "A Manned Flyby Mission to Eros" (1966). The Space Congress® Proceedings. 1. https://commons.erau.edu/space-congress-proceedings/proceedings-1966-3rd/session-2/1 This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. A MANNED FLYBY MISSION TO EROS Eugene A. Smith Northrop Space Laboratories Hawthorne, California Summary Are there lesser bodies, other than the moon, sufficiently interesting for an early manned Eros (433), the largest of the known close ap mission? proach asteroids, will pass within 0.15 AU of the Earth during its 1975 opposition. This close approach, Are such missions technically and economically occurring near the asteroid's descending node and feasible? perihelion, offers an early opportunity for a relatively low energy manned interplanetary mission. Such a Can such missions complement, rather than com mission could provide data important to the space pete with, the more ambitious Mars and Venus technologies, to the astro sciences, and to the utiliza flights? tion of extraterrestrial resources. Mars and Venus are the primary targets of early manned planetary This paper presents a partial answer to these questions flight, and therefore early manned planetary missions by examining the technical feasibility of a 1975 manned to other objects should support or complement the mission to the close approach asteroid Eros (433). -
Voyager 1 Encounter with the Saturnian System Author(S): E
Voyager 1 Encounter with the Saturnian System Author(s): E. C. Stone and E. D. Miner Source: Science, New Series, Vol. 212, No. 4491 (Apr. 10, 1981), pp. 159-163 Published by: American Association for the Advancement of Science Stable URL: http://www.jstor.org/stable/1685660 . Accessed: 04/02/2014 18:59 Your use of the JSTOR archive indicates your acceptance of the Terms & Conditions of Use, available at . http://www.jstor.org/page/info/about/policies/terms.jsp . JSTOR is a not-for-profit service that helps scholars, researchers, and students discover, use, and build upon a wide range of content in a trusted digital archive. We use information technology and tools to increase productivity and facilitate new forms of scholarship. For more information about JSTOR, please contact [email protected]. American Association for the Advancement of Science is collaborating with JSTOR to digitize, preserve and extend access to Science. http://www.jstor.org This content downloaded from 131.215.71.79 on Tue, 4 Feb 2014 18:59:21 PM All use subject to JSTOR Terms and Conditions was complicated by several factors. Sat- urn's greater distance necessitated a fac- tor of 3 reduction in the rate of data transmission (44,800 bits per second at Saturn compared to 115,200 bits per sec- Reports ond at Jupiter). Furthermore, Saturn's satellites and rings provided twice as many objects to be studied at Saturn as at Jupiter, and the close approaches to Voyager 1 Encounter with the Saturnian System these objects all occurred within a 24- hour period, compared to nearly 72 Abstract. -
Imp-C Orbit and Launch Time Analysis
IMP-C ORBIT AND LAUNCH TIME ANALYSIS BY STEPHEN J. PADDACK / I BARBARA E. SHUTE Nb 5 72614 I I GPO PRICE $ - IACCESSION NUMBER) (THRUI OTS PRICE(S) $ HA / ~PAoIih .(CODE1 7mx 3-TZ-P -'-so Hard copy (HC) % (NASA CR OR TMX OWAD NUMBER) (CATEOORY) 3#8 I j .. Microfiche (MF) JANUARY 1965 1 -GODDARD SPACE FLIGHT CENTER - GREENBELT, MARYLAND \ X-643 -6 5-40 IMP-c ORBIT AND LAUNCH TIME ANALYSIS Stephen J. Paddack and Barbara E. Shute Special Projects Branch Theoretical Division January 1965 Goddard Space Flight Center Greenbelt, Maryland TABLE OF CONTENTS -Page Abstract.. ........................................ vii NOMENCLATURE ................................... viii INTRODUCTION .................................... 1 I. ASSUMPTIONS .................................. 2 A. Nominal Initial Orbits ........................... 2 B. Dispersions on Initial Conditions .................... 4 C. Restraints on Launch Time ....................... 4 It. COMPUTING TECHNIQUES AND PROGRAMS ............. 7 A. ITEM ...................................... 7 B. Launch Window Program ......................... 7 C. Analog Stability Program ......................... 8 D. Program Comparison ........................... 8 E. Selection of Mean Elements ....................... 8 III. LAUNCH WINDOW MAPS.. ......................... 9 A. Yearsurvey ................................. 9 1. Lifetime Boundary ........................... 10 2. Spacecraft Restraints Boundary .................. 10 B. DetailedMap ................................. 11 IV. SPACECRAFT DATA.............................