Preparation of Papers for AIAA Technical Conferences
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Call for M5 Missions
ESA UNCLASSIFIED - For Official Use M5 Call - Technical Annex Prepared by SCI-F Reference ESA-SCI-F-ESTEC-TN-2016-002 Issue 1 Revision 0 Date of Issue 25/04/2016 Status Issued Document Type Distribution ESA UNCLASSIFIED - For Official Use Table of contents: 1 Introduction .......................................................................................................................... 3 1.1 Scope of document ................................................................................................................................................................ 3 1.2 Reference documents .......................................................................................................................................................... 3 1.3 List of acronyms ..................................................................................................................................................................... 3 2 General Guidelines ................................................................................................................ 6 3 Analysis of some potential mission profiles ........................................................................... 7 3.1 Introduction ............................................................................................................................................................................. 7 3.2 Current European launchers ........................................................................................................................................... -
Launch and Deployment Analysis for a Small, MEO, Technology Demonstration Satellite
46th AIAA Aerospace Sciences Meeting and Exhibit AIAA 2008-1131 7 – 10 January 20006, Reno, Nevada Launch and Deployment Analysis for a Small, MEO, Technology Demonstration Satellite Stephen A. Whitmore* and Tyson K. Smith† Utah State University, Logan, UT, 84322-4130 A trade study investigating the economics, mass budget, and concept of operations for delivery of a small technology-demonstration satellite to a medium-altitude earth orbit is presented. The mission requires payload deployment at a 19,000 km orbit altitude and an inclination of 55o. Because the payload is a technology demonstrator and not part of an operational mission, launch and deployment costs are a paramount consideration. The payload includes classified technologies; consequently a USA licensed launch system is mandated. A preliminary trade analysis is performed where all available options for FAA-licensed US launch systems are considered. The preliminary trade study selects the Orbital Sciences Minotaur V launch vehicle, derived from the decommissioned Peacekeeper missile system, as the most favorable option for payload delivery. To meet mission objectives the Minotaur V configuration is modified, replacing the baseline 5th stage ATK-37FM motor with the significantly smaller ATK Star 27. The proposed design change enables payload delivery to the required orbit without using a 6th stage kick motor. End-to-end mass budgets are calculated, and a concept of operations is presented. Monte-Carlo simulations are used to characterize the expected accuracy of the final orbit. -
Electric Propulsion System Scaling for Asteroid Capture-And-Return Missions
Electric propulsion system scaling for asteroid capture-and-return missions Justin M. Little⇤ and Edgar Y. Choueiri† Electric Propulsion and Plasma Dynamics Laboratory, Princeton University, Princeton, NJ, 08544 The requirements for an electric propulsion system needed to maximize the return mass of asteroid capture-and-return (ACR) missions are investigated in detail. An analytical model is presented for the mission time and mass balance of an ACR mission based on the propellant requirements of each mission phase. Edelbaum’s approximation is used for the Earth-escape phase. The asteroid rendezvous and return phases of the mission are modeled as a low-thrust optimal control problem with a lunar assist. The numerical solution to this problem is used to derive scaling laws for the propellant requirements based on the maneuver time, asteroid orbit, and propulsion system parameters. Constraining the rendezvous and return phases by the synodic period of the target asteroid, a semi- empirical equation is obtained for the optimum specific impulse and power supply. It was found analytically that the optimum power supply is one such that the mass of the propulsion system and power supply are approximately equal to the total mass of propellant used during the entire mission. Finally, it is shown that ACR missions, in general, are optimized using propulsion systems capable of processing 100 kW – 1 MW of power with specific impulses in the range 5,000 – 10,000 s, and have the potential to return asteroids on the order of 103 104 tons. − Nomenclature -
Design of the Trajectory of a Tether Mission to Saturn
DOI: 10.13009/EUCASS2019-510 8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND AEROSPACE SCIENCES (EUCASS) DOI: Design of the trajectory of a tether mission to Saturn ⋆ Riccardo Calaon , Elena Fantino§, Roberto Flores ‡ and Jesús Peláez† ⋆Dept. of Industrial Engineering, University of Padova Via Gradenigio G/a -35131- Padova, Italy §Dept. of Aerospace Engineering, Khalifa University Abu Dhabi, Unites Arab Emirates ‡Inter. Center for Numerical Methods in Engineering Campus Norte UPC, Gran Capitán s/n, Barcelona, Spain †Space Dynamics Group, UPM School of Aeronautical and Space Engineering, Pz. Cardenal Cisneros 3, Madrid, Spain [email protected], [email protected], rfl[email protected], [email protected] †Corresponding author Abstract This paper faces the design of the trajectory of a tether mission to Saturn. To reduce the hyperbolic excess velocity at arrival to the planet, a gravity assist at Jupiter is included. The Earth-to-Jupiter portion of the transfer is unpropelled. The Jupiter-to-Saturn trajectory has two parts: a first coasting arc followed by a second arc where a low thrust engine is switched on. An optimization process provides the law of thrust control that minimizes the velocity relative to Saturn at arrival, thus facilitating the tethered orbit insertion. 1. Introduction The outer planets are of particular interest in terms of what they can reveal about the origin and evolution of our solar system. They are also local analogues for the many extra-solar planets that have been detected over the past twenty years. The study of these planets furthers our comprehension of our neighbourhood and provides the foundations to understand distant planetary systems. -
Utilizing Deep Reinforcement Learning to Effect Autonomous Orbit Transfers and Intercepts Via Electromagnetic Propulsion
Problem Utilizing Deep Reinforcement Learning to Effect Autonomous Results The growth in space-capable entities has caused a rapid rise in Orbit Transfers and Intercepts via Electromagnetic Propulsion ➢ Analysis the number of derelict satellites and space debris in orbit Gabriel Sutherland ([email protected]), Oregon State University, Corvallis, OR, USA ❖ The data suggests spacecraft highly capable of around Earth, which pose a significant navigation hazard. Frank Soboczenski ([email protected]), King’s College London, London, UK neutralizing/capturing small to intermediate debris Athanasios Vlontzos ([email protected]), Imperial College London, London, UK ❖ In simulations, spacecraft was able to capture and/or Objectives neutralize debris ranging in mass from 1g to 100g ❖ Satellites suffered damage in some Develop a system that is capable of autonomously neutralizing simulations multiple pieces of space debris in various orbits. Software & Simulations ❖ Simulations show that damaged segments of satellite were vaporized, which means Background that no additional debris was added to orbit ➢ Dangerous amounts of space debris in orbit, estimates vary ❖ Neural Network based on Deep Deterministic Policy ➢20,000+ tracked objects larger Gradient (DDPG) effective at low-thrust orbit transfers in than 10 cm diameter 2D Hohmann transfer problem ➢Est 500,000 objects larger ❖ Using ASTOS simulation software, mission-representative than 1 cm in diameter model of spacecraft and experimental propulsion system ➢Est 100 million objects ❖ Interfaced with DRL to train the Neural smaller than 1cm in diameter ➢ Orbital speeds of these objects Network with realistic data vary from 100+ kph to 28,100 kph ➢ Future Studies ➢ Spacecraft collisions due to space ❖ Train DDPG for 3 dimensional orbit transfer problems debris have been sparse so far Tracked spacecraft in Earth orbit. -
VASIMR VX-200 Performance and Near-Term SEP Capability for Unmanned Mars Flight
VASIMR VX-200 Performance and Near-term SEP Capability for Unmanned Mars Flight Future In-Space Operations Seminar January 19, 2011 presented by Tim Glover Director of Development [email protected] Ad Astra Rocket Company www.adastrarocket.com 1 Ad Astra Rocket Company Notes and Acronyms Notes: - solar array power values are for 1 AU - a number of publications on VASIMR R&D are available on the company’s website: http://www.adastrarocket.com Acronyms: SEP solar electric propulsion NTR nuclear thermal rocket VASIMR Variable Specific Impulse Magnetoplasma Rocket TMI Trans-Mars Insertion MOI Mars Orbit Insertion SOI sphere of influence IMLEO initial mass in low Earth orbit 2 Ad Astra Rocket Company Outline 1. VASIMR Prototype Performance 2. Simplified Earth‐Mars Trajectories 3. Chemical and NTR Hohmann Transfers 4. SEP: Initial Mass‐to‐Power Ratio and Payload Fraction 5. Near‐term SEP Mars Capabilities 6. Backup slides: • Propellant and transit time variation for actual orbits of Earth and Mars •Atlas V 551 performance curve 3 Ad Astra Rocket Company My Background • B.S., Physics, New Mexico State U. • M.S., Aerospace Engineering (Orbital Mechanics), UT-Austin • M.S., Physics, University of Pittsburgh • five years teaching high school physics, Ethical Culture Schools, New York • Ph.D., Applied Physics, Rice University, 2002 − thesis research at Johnson Space Center: designed and built plasma diagnostics to measure exhaust velocity in early VASIMR prototypes • Research Scientist, MEI Technologies 2003-2005 − continued experimental work on VASIMR up to 50 kW • Director of Development, Ad Astra Rocket Company 2005 – present − business development, external relations 4 Ad Astra Rocket Company VASIMR Operating Principles Superconducting Magnets typical path of an ion Helicon coupler (30 kW) through the rocket Ion cyclotron (170 kW) coupler i gas cold accelerated plasma plasma POWER 1. -
Magnetoshell Aerocapture: Advances Toward Concept Feasibility
Magnetoshell Aerocapture: Advances Toward Concept Feasibility Charles L. Kelly A thesis submitted in partial fulfillment of the requirements for the degree of Master of Science in Aeronautics & Astronautics University of Washington 2018 Committee: Uri Shumlak, Chair Justin Little Program Authorized to Offer Degree: Aeronautics & Astronautics c Copyright 2018 Charles L. Kelly University of Washington Abstract Magnetoshell Aerocapture: Advances Toward Concept Feasibility Charles L. Kelly Chair of the Supervisory Committee: Professor Uri Shumlak Aeronautics & Astronautics Magnetoshell Aerocapture (MAC) is a novel technology that proposes to use drag on a dipole plasma in planetary atmospheres as an orbit insertion technique. It aims to augment the benefits of traditional aerocapture by trapping particles over a much larger area than physical structures can reach. This enables aerocapture at higher altitudes, greatly reducing the heat load and dynamic pressure on spacecraft surfaces. The technology is in its early stages of development, and has yet to demonstrate feasibility in an orbit-representative envi- ronment. The lack of a proof-of-concept stems mainly from the unavailability of large-scale, high-velocity test facilities that can accurately simulate the aerocapture environment. In this thesis, several avenues are identified that can bring MAC closer to a successful demonstration of concept feasibility. A custom orbit code that dynamically couples magnetoshell physics with trajectory prop- agation is developed and benchmarked. The code is used to simulate MAC maneuvers for a 60 ton payload at Mars and a 1 ton payload at Neptune, both proposed NASA mis- sions that are not possible with modern flight-ready technology. In both simulations, MAC successfully completes the maneuver and is shown to produce low dynamic pressures and continuously-variable drag characteristics. -
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 ......................................................................... -
Conceptual Design and Optimization of Hybrid Rockets
University of Calgary PRISM: University of Calgary's Digital Repository Graduate Studies The Vault: Electronic Theses and Dissertations 2021-01-14 Conceptual Design and Optimization of Hybrid Rockets Messinger, Troy Leonard Messinger, T. L. (2021). Conceptual Design and Optimization of Hybrid Rockets (Unpublished master's thesis). University of Calgary, Calgary, AB. http://hdl.handle.net/1880/113011 master thesis University of Calgary graduate students retain copyright ownership and moral rights for their thesis. You may use this material in any way that is permitted by the Copyright Act or through licensing that has been assigned to the document. For uses that are not allowable under copyright legislation or licensing, you are required to seek permission. Downloaded from PRISM: https://prism.ucalgary.ca UNIVERSITY OF CALGARY Conceptual Design and Optimization of Hybrid Rockets by Troy Leonard Messinger A THESIS SUBMITTED TO THE FACULTY OF GRADUATE STUDIES IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF MASTER OF SCIENCE GRADUATE PROGRAM IN MECHANICAL ENGINEERING CALGARY, ALBERTA JANUARY, 2021 © Troy Leonard Messinger 2021 Abstract A framework was developed to perform conceptual multi-disciplinary design parametric and optimization studies of single-stage sub-orbital flight vehicles, and two-stage-to-orbit flight vehicles, that employ hybrid rocket engines as the principal means of propulsion. The framework was written in the Python programming language and incorporates many sub- disciplines to generate vehicle designs, model the relevant physics, and analyze flight perfor- mance. The relative performance (payload fraction capability) of different vehicle masses and feed system/propellant configurations was found. The major findings include conceptually viable pressure-fed and electric pump-fed two-stage-to-orbit configurations taking advan- tage of relatively low combustion pressures in increasing overall performance. -
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. -
Astrox Studies and Experience with the Reusable Booster Systems and Two-Stage-To-Orbit Concepts
Astrox Studies and Experience with the Reusable Booster Systems and Two-Stage-to-Orbit Concepts Presented to: National Research Council Aeronautics and Space Engineering Board February 2012 By: Astrox Corporation Dr. Christopher Tarpley Colorado Springs, CO 80917 Dr. Ajay P. Kothari College Park, MD 20740 Distribution A: Approved for public release; distribution unlimited Acknowledgements • Dr. Mark Lewis, Ex-Chief Scientist, Air Force • Dr. Werner Dahm, Ex-Chief Scientist, Air Force • Dr. Donald Paul, Chief Scientist – Rtrd, AFRL/RB • Mr. Bruce Thieman, AFRL/RB • Mr. Barry Hellman, AFRL/RB • Mr. John Livingston, ASC/XR • Mr. Glenn Liston, AFRL/RZ • Mr. Dan Risha, AFRL/RZ • Dr. Kevin Bowcutt, Boeing Huntington Beach • Dr. Ray Moszee, SAF/AQR, Pentagon 2 Distribution A: Approved for public release; distribution unlimited Background • Astrox experience with Access-to-Space (ATS) and high Mach cruise configurations covers almost two decades of work primarily with Air Force and NASA • Astrox has been developing tools for vehicle design and quantitative analysis since 1990 • Studies have covered: – SSTO and TSTO Systems – RP, JP, Methane and LH2 Systems – Payloads from 2,000 to 60,000 lbs – Rocket, Turbine, Ram/Scramjet Engines – Air Launch, Horizontal and Vertical Takeoff Configurations 3 Distribution A: Approved for public release; distribution unlimited Relevant Studies Performed Inward Turning Inlet 1990-1992 ASC/XR Inward Turning Flowpath and Vehicles 1993-2000 NASA/LaRC HADO and HySIDE Code 1995-1997 ASC/XR Inward Turning SSTO Designs 1997-1999 NASA/MSFC Access-to-Space / FAST* 1 2004 - 2006 AFRL/VA TSTO Architectures 2005 AFRL/VA Aerial Refueling 2006 AFRL/PRS Prompt Global Strike 2006 AFRL/PRS Hybrid Launch Study 2007 AFRL/PRS TSTO Study 2007-2008 AFRL/PRS FAST* 2 2008 AFRL/RB Joint System Study 2009 AFRL/RB *FAST – Fully Reusable Access-to-Space Technology 4 Distribution A: Approved for public release; distribution unlimited Recent Relevant Publications 1. -
Aerocapture As an Enhancing Option for Ice Giants Missions
WHITE PAPER FOR THE PLANETARY SCIENCE DECADAL SURVEY, 2023 - 2032 Aerocapture as an Enhancing Option for Ice Giants Missions Primary Author: Soumyo Dutta NASA Langley Research Center Phone: 757-864-3894 E-Mail: [email protected] Co-Authors: Gonçalo Afonso1 Jay Feldman5 Zachary R. Putnam11 Samuel W. Albert2 Roberto Gardi12 Jeremy R. Rea15 Hisham K. Ali3 Athul P. Girija13 Sachin Alexander Reddy21 Gary A. Allen4 Tiago Hormigo1 Thomas Reimer22 Antonella I. Alunni5 Jeffrey P. Hill5 Sarag J. Saikia23 James O. Arnold4 Shayna Hume2 Isil Sakraker Özmen22 Alexander Austin6 Christopher Jelloian14 Kunio Sayanagi24 Gilles Bailet7 Vandana Jha5 Stephan Schuster25 Shyam Bhaskaran6 Breanna J. Johnson15 Jennifer Scully6 Alan M. Cassell5 Craig A. Kluever16 Ronald R. Sostaric15 George T. Chen6 Jean-Pierre Lebreton17 Christophe Sotin6 Ian J. Cohen8 Marcus A. Lobbia6 David A. Spencer6 James A. Cutts6 Ping Lu18 Benjamin M. Tackett4 Rohan G. Deshmukh4 Ye Lu19 Nikolas Trawny6 Robert A. Dillman9 Rafael A. Lugo9 Ethiraj Venkatapathy5 Guillermo Dominguez Daniel A. Matz15 Paul F. Wercinski5 Calabuig10 Robert W. Moses9 Michael C. Wilder5 Sarah N. D’Souza5 Michelle M. Munk9 Michael J. Wright5 Donald T. Ellerby5 Adam P. Nelessen6 Cindy L. Young9 Giusy Falcone11 Miguel Pérez-Ayúcar20 Alberto Fedele12 Richard W. Powell4 1 Spin.Works S.A. 4 Analytical Mechanics Associates 2 University of Colorado, Boulder 5 NASA Ames Research Center 3 Georgia Institute of Technology Aerocapture for Ice Giants Missions 6 Jet Propulsion Laboratory/California 16 University of Missouri Institute of Technology 17 French National Centre for Scientific 7 University of Glasgow Research 8 John Hopkins University/Applied Physics 18 San Diego State University Laboratory 19 Kent State University 9 NASA Langley Research Center 20 Aurora Technology B.V.