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Breakthrough Propulsion Study Assessing Interstellar Flight Challenges and Prospects
Breakthrough Propulsion Study Assessing Interstellar Flight Challenges and Prospects NASA Grant No. NNX17AE81G First Year Report Prepared by: Marc G. Millis, Jeff Greason, Rhonda Stevenson Tau Zero Foundation Business Office: 1053 East Third Avenue Broomfield, CO 80020 Prepared for: NASA Headquarters, Space Technology Mission Directorate (STMD) and NASA Innovative Advanced Concepts (NIAC) Washington, DC 20546 June 2018 Millis 2018 Grant NNX17AE81G_for_CR.docx pg 1 of 69 ABSTRACT Progress toward developing an evaluation process for interstellar propulsion and power options is described. The goal is to contrast the challenges, mission choices, and emerging prospects for propulsion and power, to identify which prospects might be more advantageous and under what circumstances, and to identify which technology details might have greater impacts. Unlike prior studies, the infrastructure expenses and prospects for breakthrough advances are included. This first year's focus is on determining the key questions to enable the analysis. Accordingly, a work breakdown structure to organize the information and associated list of variables is offered. A flow diagram of the basic analysis is presented, as well as more detailed methods to convert the performance measures of disparate propulsion methods into common measures of energy, mass, time, and power. Other methods for equitable comparisons include evaluating the prospects under the same assumptions of payload, mission trajectory, and available energy. Missions are divided into three eras of readiness (precursors, era of infrastructure, and era of breakthroughs) as a first step before proceeding to include comparisons of technology advancement rates. Final evaluation "figures of merit" are offered. Preliminary lists of mission architectures and propulsion prospects are provided. -
Cislunar Tether Transport System
FINAL REPORT on NIAC Phase I Contract 07600-011 with NASA Institute for Advanced Concepts, Universities Space Research Association CISLUNAR TETHER TRANSPORT SYSTEM Report submitted by: TETHERS UNLIMITED, INC. 8114 Pebble Ct., Clinton WA 98236-9240 Phone: (206) 306-0400 Fax: -0537 email: [email protected] www.tethers.com Report dated: May 30, 1999 Period of Performance: November 1, 1998 to April 30, 1999 PROJECT SUMMARY PHASE I CONTRACT NUMBER NIAC-07600-011 TITLE OF PROJECT CISLUNAR TETHER TRANSPORT SYSTEM NAME AND ADDRESS OF PERFORMING ORGANIZATION (Firm Name, Mail Address, City/State/Zip Tethers Unlimited, Inc. 8114 Pebble Ct., Clinton WA 98236-9240 [email protected] PRINCIPAL INVESTIGATOR Robert P. Hoyt, Ph.D. ABSTRACT The Phase I effort developed a design for a space systems architecture for repeatedly transporting payloads between low Earth orbit and the surface of the moon without significant use of propellant. This architecture consists of one rotating tether in elliptical, equatorial Earth orbit and a second rotating tether in a circular low lunar orbit. The Earth-orbit tether picks up a payload from a circular low Earth orbit and tosses it into a minimal-energy lunar transfer orbit. When the payload arrives at the Moon, the lunar tether catches it and deposits it on the surface of the Moon. Simultaneously, the lunar tether picks up a lunar payload to be sent down to the Earth orbit tether. By transporting equal masses to and from the Moon, the orbital energy and momentum of the system can be conserved, eliminating the need for transfer propellant. Using currently available high-strength tether materials, this system could be built with a total mass of less than 28 times the mass of the payloads it can transport. -
9Th Annual & Final Report 2006 2007
NASA Institute for Advanced Concepts 9th Annual & 2006 Final Report 2007 Performance Period July 12, 2006 - August 31, 2007 NASA Institute for Advanced Concepts 75 5th Street NW, Suite 318 Atlanta, GA 30308 404-347-9633 www.niac.usra.edu USRA is a non-profit corpora- ANSER is a not-for-profit pub- tion under the auspices of the lic service research corpora- National Academy of Sciences, tion, serving the national inter- with an institutional membership est since 1958.To learn more of 100. For more information about ANSER, see its website about USRA, see its website at at www.ANSER.org. www.usra.edu. NASA Institute for Advanced Concepts 9 t h A N N U A L & F I N A L R E P O R T Performance Period July 12, 2006 - August 31, 2007 T A B L E O F C O N T E N T S 7 7 MESSAGE FROM THE DIRECTOR 8 NIAC STAFF 9 NIAC EXECUTIVE SUMMARY 10 THE LEGACY OF NIAC 14 ACCOMPLISHMENTS 14 Summary 14 Call for Proposals CP 05-02 (Phase II) 15 Call for Proposals CP 06-01 (Phase I) 17 Call for Proposals CP 06-02 (Phase II) 18 Call for Proposals CP 07-01 (Phase I) 18 Call for Proposals CP 07-02 (Phase II) 18 Financial Performance 18 NIAC Student Fellows Prize Call for Proposals 2006-2007 19 NIAC Student Fellows Prize Call for Proposals 2007-2008 20 Release and Publicity of Calls for Proposals 20 Peer Reviewer Recruitment 21 NIAC Eighth Annual Meeting 22 NIAC Fellows Meeting 24 NIAC Science Council Meetings 24 Coordination With NASA 27 Publicity, Inspiration and Outreach 29 Survey of Technologies to Enable NIAC Concepts 32 DESCRIPTION OF THE NIAC 32 NIAC Mission 33 Organization 34 Facilities 35 Virtual Institute 36 The NIAC Process 37 Grand Visions 37 Solicitation 38 NIAC Calls for Proposals 39 Peer Review 40 NASA Concurrence 40 Awards 40 Management of Awards 41 Infusion of Advanced Concepts 4 T A B L E O F C O N T E N T S 7 LIST OF TABLES 14 Table 1. -
The Lunar Economy - Years 1-25 Dec 1986 - Nov 2011
MMM Theme Issues: The Lunar Economy - Years 1-25 Dec 1986 - Nov 2011 The Moon Would Seem to be a Tough Nut to Crack Until we look Closer At first we may not be able to produce “first choice” alloys and other building and manufacturing materials, but what we can produce early on will be adequate to substitute for enough products that the gross tonnage of imports from Earth can be cut to a fraction. Power Generation is essential. Better, as we point out in Foundation 2 above, the Moon has the real estate advantage of “location, location, location.” As a result, anything produced on the Moon could be shipped to space facilities in Low Earth Orbit (LEO) and Geosynchronous Orbit (GEO) at a cost advantage of equivalent products manufactured on Earth. Thus the cost of importing to the Moon those things that cannot yet be manufactured there, could be ofset by exports of Lunar manufactured goods and materials to markets in LEO and GEO. Production of consumer goods will be important and enterprise will be a key factor. It will take time, but financial break-even is possible in time. The obstacles are great. But once you look closely at the options, these obstacles fall in the ranks of those that faced MMM Theme Issues: The Lunar Economy - Years 1-25 Dec 1986 - Nov 2011 pioneers of other frontiers on Earth in eras gone by. Establishing and then elaborating the roots and possibilities of a lunar economy sufcient to support permanent pioneer frontier settlements are there, and treating them one by one has been a major theme of Moon Miners’ Manifesto through the years. -
Copyrighted Material
k Trim Size: 6.125in x 9.25in Sutton c01.tex V2 - 06/03/2020 7:55pm Page 1 CHAPTER 1 CLASSIFICATION In general terms, propulsion is the act of changing the motion of a body with respect to an inertial reference frame. Propulsion systems provide forces that either move k bodies initially at rest or change their velocity or that overcome retarding forces when k bodies are propelled through a viscous medium. The word propulsion comes from the Latin propulsus, which is the past participle of the verb propellere, meaning “to drive away.” Jet propulsion is a type of motion whereby a reaction force is imparted to a vehicle by the momentum of ejected matter. Rocket propulsion is a class of jet propulsion that produces thrust by ejecting matter, called the working fluid or propellant, stored entirely in the flying vehicle. Duct propulsion is another class of jet propulsion and it includes turbojets and ram- jets; these engines are more commonly called air-breathing engines. Duct propulsion devices mostly utilize their surrounding medium as the propellant, energized by its combustion with the vehicle’s stored fuel. Combinations of rockets and duct propul- sion devices have been attractive for some applications, and one is briefly described in this chapter. The energy source most commonly used in rocket propulsion is chemical com- bustion. EnergyCOPYRIGHTED can also be supplied by solar radiation MATERIALand by a nuclear reactor. Accordingly, the various propulsion devices in use can be divided into chemical propulsion, nuclear propulsion, and solar propulsion. Table 1–1 lists many important propulsion concepts according to their energy source and type of propellant. -
Motorised Momentum Exchange Space Tethers: the Dynamics of Asymmetrical Tethers, and Some Recent New Applications
MATEC Web of Conferences 148, 01001 (2018) https://doi.org/10.1051/matecconf/201814801001 ICoEV 2017 Motorised momentum exchange space tethers: the dynamics of asymmetrical tethers, and some recent new applications Matthew Cartmell1,2,*, Olga Ganilova1,2, Eoin Lennon1, and Gavin Shuttleworth1 1Department of Mechanical & Aerospace Engineering, University of Strathclyde, Glasgow, G1 1XJ, Scotland, UK 2Strathclyde Space Institute, University of Strathclyde, Glasgow, G1 1XJ, Scotland, UK Abstract. This paper reports on a first attempt to model the dynamics of an asymmetrical motorised momentum exchange tether for spacecraft payload propulsion, and it also provides some interesting summary results for two novel applications for motorised momentum exchange tethers. The asymmetrical tether analysis is very important because it represents the problematic scenario when payload mass unbalance intrudes, due to unexpected payload loss or failure to retrieve. Mass symmetry is highly desirable both dynamically and logistically, but it is shown in this paper that there is still realistic potential for mission rescue should an asymmetry condition arise. Conceptual designs for tethered payload release from LEO and lunar tether delivery and retrieval are also presented as options for future development. 1 Introduction Momentum exchange tether dynamics have been extensively studied in recent years, and are of current considerable interest internationally as a technology for cost effective and environmentally clean propulsion of payload mass from Low Earth Orbit (LEO). A conceptual design for a motorised momentum exchange tether is given in Figure 1 where the central facility motor drive shaft attaches to the propulsion sub-spans by mean of a gantry, mounted so that it can be rotated by the shaft. -
Design of Spacecraft Missions to Remove Multiple Orbital Debris Objects
AAS 12-017 Design of Spacecraft Missions to Remove Multiple Orbital Debris Objects Brent W. Barbee*, Salvatore Alfano†, Elfego Piñon‡, Kenn Gold‡, and David Gaylor‡ *NASA-GSFC, †CSSI, ‡Emergent Space Technologies, Inc. 35th ANNUAL AAS GUIDANCE AND CONTROL CONFERENCE February 3 - February 8, 2012 Sponsored by Breckenridge, Colorado Rocky Mountain Section AAS Publications Office, P.O. Box 28130 - San Diego, California 92198 AAS 12-017 DESIGN OF SPACECRAFT MISSIONS TO REMOVE MULTIPLE ORBITAL DEBRIS OBJECTS Brent W. Barbee,∗ Salvatore Alfano,y Elfego Pinon˜ ,z Kenn Gold,x and David Gaylor{ The amount of hazardous debris in Earth orbit has been increasing, posing an ever- greater danger to space assets and human missions. In January of 2007, a Chinese ASAT test produced approximately 2600 pieces of orbital debris. In February of 2009, Iridium 33 collided with an inactive Russian satellite, yielding approx- imately 1300 pieces of debris. These recent disastrous events and the sheer size of the Earth orbiting population make clear the necessity of removing orbital de- bris. In fact, experts from both NASA and ESA have stated that 10 to 20 pieces of orbital debris need to be removed per year to stabilize the orbital debris environ- ment. However, no spacecraft trajectories have yet been designed for removing multiple debris objects and the size of the debris population makes the design of such trajectories a daunting task. Designing an efficient spacecraft trajectory to rendezvous with each of a large number of orbital debris pieces is akin to the fa- mous Traveling Salesman problem, an NP-complete combinatorial optimization problem in which a number of cities are to be visited in turn. -
To Orbit and Back Again: How the Space Shuttle Flew in Space Free Download
TO ORBIT AND BACK AGAIN: HOW THE SPACE SHUTTLE FLEW IN SPACE FREE DOWNLOAD Davide Sivolella | 524 pages | 09 Sep 2013 | Springer-Verlag New York Inc. | 9781461409823 | English | New York, NY, United States To Orbit and Back Again: How the Space Shuttle Flew in Space (Springer… Details of how anomalous events were dealt with on individual missions are also provided, as are the recollections of those who built and flew the Shuttle. He involves here few in photographers on: electoral antitrust exceptionalism; teriparatide and significant experience; concept and matters; and s Futurism. Orbiting skyhooks Skyhook Momentum exchange tether. Soviet X-planes. This passion for astronautics led to bacheklor's and master's degrees in Aerospace Engineering from the Polytechnic of Turin Italy. Archived from the original on 26 June Technical material has been obtained from NASA as well as from other forums and specialists. The Rockwell X National Aero-Space Plane NASPbegun in the s, was an attempt to build a scramjet vehicle capable of operating like an aircraft and achieving orbit like the shuttle. InNASA originally planned to have the Gemini spacecraft land on a runway [18] with a Rogallo wing airfoilrather than an ocean landing under parachutes. Namespaces Article Talk. The spaceplane was also intended to carry cargo, with both upmass and downmass capacity. Search icon An illustration of a magnifying glass. Orbital spaceplanes are more like spacecraft, while sub-orbital spaceplanes are more like fixed-wing aircraft. Our configurations are tall Bodies and genotypes on which to See your new nationality. Space Policy. Details of how anomalous events were dealt with on individual missions are also provided, as are the recollections of those who built and flew the Shuttle. -
Moon-Tracking Orbits Using Motorized Tethers for Continuous Earth–Moon Payload Exchanges
Murray, C., and Cartmell, M.P. (2013) Moon-tracking orbits using motorized tethers for continuous earth–moon payload exchanges. Journal of Guidance, Control and Dynamics, 36 (2). pp. 567-576. ISSN 0731-5090 Copyright © 2012 American Institute of Aeronautics and Astronautics A copy can be downloaded for personal non-commercial research or study, without prior permission or charge The content must not be changed in any way or reproduced in any format or medium without the formal permission of the copyright holder(s) When referring to this work, full bibliographic details must be given http://eprints.gla.ac.uk/79980/ Deposited on: 17 May 2013 Enlighten – Research publications by members of the University of Glasgow http://eprints.gla.ac.uk Moon-Tracking Orbits using Motorized Tethers for Continuous Earth-Moon Payload Exchanges Christopher Murray 1 and Matthew P. Cartmell 2 School of Engineering, University of Glasgow 3 For human colonization of the Moon to become reality an efficient and regular means of exchanging resources between the Earth and Moon must be established. One possibility is to pass and receive payloads at regular intervals between a symmetrically laden motorized momentum exchange tether orbiting about Earth and a second or- biting about the Moon. There are significant challenges associated with this method; amongst the greatest of which is the development of a system which incorporates the complex motion of the Moon into its operational architecture in addition to having the capability of conducting these exchanges on a per-lunar-orbit basis. One way of achieving this is a method by which a motorized tether orbiting Earth can track the nodes of the Moon’s orbit and allow payload exchanges to be undertaken periodically with the arrival of the Moon at either of these nodes. -
NASA's New Emphasis on In-Space Propulsion Technology Research
NASA’s New Emphasis on In-Space Propulsion Technology Research Les Johnson Advanced Space Transportation Program/TD15 NASA Marshall Space Flight Center Marshall Space Flight Center, Alabama 35812 USA Phone: 256–544–0614 E-Mail: [email protected] IEPC-01-001 ABSTRACT NASA’s Advanced Space Transportation Program (ASTP) is investing in technologies to achieve a factor of 10 reduction in the cost of Earth orbital transportation and a factor of 2 reduction in propulsion system mass and travel time for planetary missions within the next 15 yr. Since more than 70% of projected launches over the next 10 yr will require propulsion systems capable of attaining destinations beyond low-Earth orbit (LEO), investment in in-space tech- nologies will benefit a large percentage of future missions. The ASTP technology portfolio includes many advanced propulsion systems. From the next- generation ion propulsion system operating in the 5–10 kW range to fission-powered multikilowatt systems, substantial advances in spacecraft propulsion performance are antici- pated. Some of the most promising technologies for achieving these goals use the environment of space itself for energy and propulsion and are generically called “propellantless,” because they do not require onboard fuel to achieve thrust. An overview of state-of-the-art space pro- pulsion technologies, such as solar and plasma sails, electrodynamic and momentum transfer tethers, and aeroassist and aerocapture, will also be described. Results of recent Earth-based technology demonstrations and space tests for many of these new propulsion technologies will be discussed. THE LIMITS OF CHEMICAL PROPULSION our continued exploration of space. -
68Th International Astronautical Congress (IAC 2017)
68th International Astronautical Congress (IAC 2017) Unlocking Imagination, Fostering Innovation and Strengthening Security Adelaide, Australia 25 - 29 September 2017 Volume 1 of 19 ISBN: 978-1-5108-5537-3 Printed from e-media with permission by: Curran Associates, Inc. 57 Morehouse Lane Red Hook, NY 12571 Some format issues inherent in the e-media version may also appear in this print version. Copyright© (2017) by International Astronautical Federation All rights reserved. Printed by Curran Associates, Inc. (2018) For permission requests, please contact International Astronautical Federation at the address below. International Astronautical Federation 3 rue Mario Nikis 75015 Paris France Phone: +33 1 45 67 42 60 Fax: +33 1 42 73 21 20 www.iafastro.org Additional copies of this publication are available from: Curran Associates, Inc. 57 Morehouse Lane Red Hook, NY 12571 USA Phone: 845-758-0400 Fax: 845-758-2633 Email: [email protected] Web: www.proceedings.com TABLE OF CONTENTS VOLUME 1 A1.IP. INTERACTIVE PRESENTATIONS IAC-17.A1.IP.1 LIFE SUPPORT SYSTEMS RELATED TO GRAVITY IN SJ-10 AND TG-2 SATELLITE SPACE FLIGHT EXPERIMENTS..................................................................................................................................................................1 Hao Sun IAC-17.A1.IP.3 THE STUDY ON SPACE-FLIGHT INDUCED DNA DAMAGE IN ARABIDOPSIS THALIANA AND THE PROTECTIVE EFFECT OF HYDROGEN ................................................................................................................................2 -
9783211838624.Pdf
Martin Tajmar Advanced Space Propulsion Systems Springer-Verlag Wien GmbH Dipl. Ing. Dr. Martin Tajrnar ARC Seibersdorf Research GmBH, Seibersdorf, Austria This book was generously supported by the Austrian Research Centers This work is subject to copyright. All rights are reserved, whether the whole or part of the material is concerned, specifically those of translation, reprinting, re-use of illustrations, broadcasting, reproduction by photocopying machines or similar means, and storage in data banks. Product Liability: The publisher can give no guarantee for all the information contained in this book. This does also refer to information about drug dosage and application thereof. In every individual case the respective user must check its accuracy by consulting other pharmaceutical literature. The use of registered names, trademarks, etc. in this publication does not imply, even in the absence of a specific statement, that such names are exempt from the relevant protective laws and regulations and therefore free for general use. © 2003 Springer-Verlag Wien Originally published by Springer-Verlag Wien New York in 2003 Typesetting: Thomson Press Ltd., Chennai, India Printing: A. Holzhausen Nfg., A-1l40 Wien Printed on acid-free and chlorine-free bleached paper SPIN: 10888345 With 121 (partly coloured) Figures CIP-data applied for ISBN 978-3-211-83862-4 ISBN 978-3-7091-0547-4 (eBook) DOI 10.1007/978-3-7091-0547-4 Contents Introduction .................................................... 1 Propulsion Fundamentals . 3 1.1 History......................................................... 3 1.2 Propulsion Fundamentals .......................................... 7 1.2.1 Tsiolkovski Equation . 8 1.2.2 Delta-V Budget. 9 l.2.3 Single-staging - Multi-staging. .. 12 1.3 Trajectory and Orbits ............................................