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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 -
2019 Nano/Microsatellite Market Forecast, 9Th Edition
2019 NANO/MICROSATELLITE MARKET FORECAST, 9TH EDITION Copyright 2018, SpaceWorks Enterprises, Inc. (SEI) APPROVED FOR PUBLIC RELEASE. SPACEWORKS ENTERPRISES, INC., COPYRIGHT 2018. 1 Since 2008, SpaceWorks has actively monitored companies and economic activity across both the satellite and launch sectors 0 - 50 kg 50 - 250kg 250 - 1000kg 1000 - 2000kg 2000kg+ Custom market assessments are available for all mass classes NANO/MICROSATELLITE DEFINITION Picosatellite Nanosatellite Microsatellite Small/Medium Satellite (0.1 – 0.99 kg) (1 – 10 kg) (10 – 100 kg) (100 – 1000 kg) 0 kg 1 kg 10 kg 100 kg 1000 kg This report bounds the upper range of interest in microsatellites at 50 kg given the relatively large amount of satellite development activity in the 1 – 50 kg range FORECASTING METHODOLOGY SpaceWorks’ proprietary Launch Demand Database (LDDB) Downstream serves as the data source for all satellite market Demand assessments ▪ Planned The LDDB is a catalogue of over 10,000+ historical and Constellations future satellites containing both public and non-public (LDDB) satellite programs Launch Supply SpaceWorks newly updated Probabilistic Forecast Model (PFM) is used to generate future market potential SpaceWorks PFM Model ▪ The PFM considers down-stream demand, announced/planed satellite constellations, and supply-side dynamics, among other relevant factors Expert Analysis The team of expert industry analysts at SpaceWorks SpaceWorks further interprets and refines the PFM results to create Forecast accurate market forecasts Methodology at a Glance 2018 SpaceWorks forecasted 2018 nano/microsatellite launches with unprecedented accuracy – actual satellites launched amounted to just 5% below our analysts’ predictions. In line with SpaceWorks’ expectations, the industry corrected after a record launch year in 2017, sending 20% less nano/microsatellites to orbit than in 2018. -
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 ......................................................................... -
Method for Rapid Interplanetary Trajectory Analysis Using Δv Maps with Flyby Options
View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by DSpace@MIT METHOD FOR RAPID INTERPLANETARY TRAJECTORY ANALYSIS USING ΔV MAPS WITH FLYBY OPTIONS TAKUTO ISHIMATSU*, JEFFREY HOFFMAN†, AND OLIVIER DE WECK‡ Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, 77 Massachusetts Avenue, Cambridge, MA 02139, USA. Email: [email protected]*, [email protected]†, [email protected]‡ This paper develops a convenient tool which is capable of calculating ballistic interplanetary trajectories with planetary flyby options to create exhaustive ΔV contour plots for both direct trajectories without flybys and flyby trajectories in a single chart. The contours of ΔV for a range of departure dates (x-axis) and times of flight (y-axis) serve as a “visual calendar” of launch windows, which are useful for the creation of a long-term transportation schedule for mission planning purposes. For planetary flybys, a simple powered flyby maneuver with a reasonably small velocity impulse at periapsis is allowed to expand the flyby mission windows. The procedure of creating a ΔV contour plot for direct trajectories is a straightforward full-factorial computation with two input variables of departure and arrival dates solving Lambert’s problem for each combination. For flyby trajectories, a “pseudo full-factorial” computation is conducted by decomposing the problem into two separate full-factorial computations. Mars missions including Venus flyby opportunities are used to illustrate the application of this model for the 2020-2040 time frame. The “competitiveness” of launch windows is defined and determined for each launch opportunity. Keywords: Interplanetary trajectory, C3, delta-V, pork-chop plot, launch window, Mars, Venus flyby 1. -
Dino Lorenzini Spaace Talk / Issue #1 2 Message from the Ceo
SPAACE TALK Issue #1 MESSAGE FROM THE CEO THE BIG IDEA COMPANY HIGHLIGHTS 5 MINUTES WITH... DINO LORENZINI SPAACE TALK / ISSUE #1 2 MESSAGE FROM THE CEO MESSAGE FROM THE CEO WELCOME TO THE FIRST EVER ISSUE OF SPAACE TALK. This is where we take a closer look at what’s going on across the Group and hear from colleagues and industry experts on the most exciting themes in New Space. Our vision at AAC is to deliver high-quality, timely data from space for a better life on Earth. To that end, in the last year we have welcomed three fascinating businesses to the Group and expanded our talented team to over 150 people across the world – from Washington to Uppsala. As we continue to grow and accomplish great things together, I hope that SPAACE TALK will help us to stay connected and focused, by sharing stories from all corners of our global business and putting them into a broader context: how do they help to make our vision a reality? In this issue, we are shining a light on Space Data as a Service. This will be AAC’s top growth engine over the coming years and it’s an area I’m hugely excited to develop. We’ve already made great progress: our acquisition of SpaceQuest in 2020 was a gamechanger and we’ll be speaking to SpaceQuest founder Dino Lorenzini in this issue. We’ve also got an exciting round-up of news from across the business, including a very special guest visit to our Glasgow facility – so read on, I hope you enjoy it. -
The Annual Compendium of Commercial Space Transportation: 2017
Federal Aviation Administration The Annual Compendium of Commercial Space Transportation: 2017 January 2017 Annual Compendium of Commercial Space Transportation: 2017 i Contents About the FAA Office of Commercial Space Transportation The Federal Aviation Administration’s Office of Commercial Space Transportation (FAA AST) licenses and regulates U.S. commercial space launch and reentry activity, as well as the operation of non-federal launch and reentry sites, as authorized by Executive Order 12465 and Title 51 United States Code, Subtitle V, Chapter 509 (formerly the Commercial Space Launch Act). FAA AST’s mission is to ensure public health and safety and the safety of property while protecting the national security and foreign policy interests of the United States during commercial launch and reentry operations. In addition, FAA AST is directed to encourage, facilitate, and promote commercial space launches and reentries. Additional information concerning commercial space transportation can be found on FAA AST’s website: http://www.faa.gov/go/ast Cover art: Phil Smith, The Tauri Group (2017) Publication produced for FAA AST by The Tauri Group under contract. NOTICE Use of trade names or names of manufacturers in this document does not constitute an official endorsement of such products or manufacturers, either expressed or implied, by the Federal Aviation Administration. ii Annual Compendium of Commercial Space Transportation: 2017 GENERAL CONTENTS Executive Summary 1 Introduction 5 Launch Vehicles 9 Launch and Reentry Sites 21 Payloads 35 2016 Launch Events 39 2017 Annual Commercial Space Transportation Forecast 45 Space Transportation Law and Policy 83 Appendices 89 Orbital Launch Vehicle Fact Sheets 100 iii Contents DETAILED CONTENTS EXECUTIVE SUMMARY . -
A. the Proposed Program of Research and Experimentation Spacequest, Ltd
FCC Form 442 Exhibit 1 File #: 0220-EX-CN-2018 Question 7: Purpose of Experiment A. The Proposed Program of Research and Experimentation SpaceQuest, Ltd. (“SpaceQuest”), a U.S. corporation headquartered in Fairfax, Virginia, requests FCC experimental authorization to test and evaluate an advanced RF Transceiver developed by Myriota, a spin-off company from the University of South Australia. Myriota has designed a novel communications protocol that uses a Software Defined Radio (SDR) and advanced signal processing that allows very large numbers of low power signals from user terminals to be received on the same frequency channel. Myriota desires to evaluate the ability of this advanced radio to function in a space environment. If successful, this would bring a cost-effective data communication technology to a new class of users – those with operations that require direct-to-orbit access to small amounts of data from numerous low-power devices. The primary objective of the mission is to investigate, identify and resolve potential technical and implementation issues with its advanced satellite SDR radio design. Another important objective is to demonstrate the ability to upload and run new firmware that can introduce new features to the SDR Radio after it is on orbit. The results of this three-phase experiment will (1) demonstrate and validate the ability to uplink large numbers of messages to a satellite using a single channel, (2) demonstrate the ability to downlink messages to different ground devices on a single channel, and (3) implement Myriota’s advanced signal processing algorithms on board a satellite to provide highly spectrally efficient bidirectional communications. -
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............................. -
Spacecraft Conjunction Assessment and Collision Avoidance Best Practices Handbook
National Aeronautics and Space Administration National Aeronautics and Space Administration NASA Spacecraft Conjunction Assessment and Collision Avoidance Best Practices Handbook December 2020 NASA/SP-20205011318 The cover photo is an image from the Hubble Space Telescope showing galaxies NGC 4038 and NGC 4039, also known as the Antennae Galaxies, locked in a deadly embrace. Once normal spiral galaxies, the pair have spent the past few hundred million years sparring with one another. Image can be found at: https://images.nasa.gov/details-GSFC_20171208_Archive_e001327 ii NASA Spacecraft Conjunction Assessment and Collision Avoidance Best Practices Handbook DOCUMENT HISTORY LOG Status Document Effective Description (Baseline/Revision/ Version Date Canceled) Baseline V0 iii NASA Spacecraft Conjunction Assessment and Collision Avoidance Best Practices Handbook THIS PAGE INTENTIONALLY LEFT BLANK iv NASA Spacecraft Conjunction Assessment and Collision Avoidance Best Practices Handbook Table of Contents Preface ................................................................................................................ 1 1. Introduction ................................................................................................... 3 2. Roles and Responsibilities ............................................................................ 5 3. History ........................................................................................................... 7 USSPACECOM CA Process ............................................................. -
Launch Conjunction Assessment Handbook Version 1.0 December 2018
JFSCC, 18th Space Control Squadron Combined Space Operations Center (CSpOC) Vandenberg Air Force Base, California, USA Tel +1-805-605-3533 www.space-track.org LAUNCH CONJUNCTION ASSESSMENT HANDBOOK VERSION 1.0 DECEMBER 2018 18 SPCS Process for Launch Conjunction Assessment TABLE OF CONTENTS Contents Revision History _________________________________________________________________________________________ 1 Important Definitions ___________________________________________________________________________________ 2 18th Space Control Squadron ____________________________________________________________________________________2 Launch Conjunction Assessment _________________________________________________________________________________2 Launch Collision Avoidance ______________________________________________________________________________________2 General Pertubations _____________________________________________________________________________________________2 Special Pertubations ______________________________________________________________________________________________2 Launch Conjunction Assessment Authorities __________________________________________________________ 3 Air Force Instruction 91-217 Space Safety And Mishap Prevention Program ________________________________3 Title 14 Code of Federal Regulations (14 CFR)__________________________________________________________________3 USSTRATCOM SSA Sharing Program _____________________________________________________________________________3 Space-Track.org____________________________________________________________________________________________________4 -
Technical Constraints Impact on Mission Design to the Collinear Sun-Earth Libration Points
1 Technical Constraints Impact on Mission Design to the Collinear Sun-Earth Libration Points N. Eismont, A. Sukhanov, V. Khrapchenkov Space Research Institute, Russian Academy of Sciences ABSTRACT For the practical realization of the mission to the collinear Sun-Earth libration points technical constraints play a significant role. In the paper the influence of the constraints generated by the use of piggi-back mode of the delivering spacecraft to the vicinity of libration points are studied. High elliptical parking orbit of Molniya is taken as initial orbit for start to the L1, L2 libration points. The parameters of this orbit are supposed to be fixed and determined by the main payload demands. The duration of the passenger payload keeping on the mentioned 12 hours period orbit is limited for the case when launcher upper stage is used for the velocity impulse applying to put spacecraft onto transfer orbit to the libration point. The possibility to use one axis attitude control of the spacecraft for the executing correction maneuvers are investigated, supposing that spacecraft is spin stabilized with the spin axis directed to the Sun and maneuver impulse goes along this axis. The cost of constraints is presented in terms of characteristic velocity and time of transfer to the libration point vicinity. The goal of the paper is to understand the possibility of using regular launches of Molniya communication satellite by Soyuz-Fregat launch vehicle for sending low cost scientific spacecraft to Sun-Earth libration points. INTRODUCTION The mission to the vicinity of Sun-Earth collinear libration points are fulfilled and planned for the scientific experiments gaining big advantages from use of this region of space for optimal measurement conditions.