Electric Propulsion: Systems Analysis and Potential Application in Space Exploration
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The Solar Cruiser Mission: Demonstrating Large Solar Sails for Deep Space Missions
The Solar Cruiser Mission: Demonstrating Large Solar Sails for Deep Space Missions Les Johnson*, Frank M. Curran**, Richard W. Dissly***, and Andrew F. Heaton* * NASA Marshall Space Flight Center ** MZBlue Aerospace NASA Image *** Ball Aerospace Solar Sails Derive Propulsion By Reflecting Photons Solar sails use photon “pressure” or force on thin, lightweight, reflective sheets to produce thrust. NASA Image 2 Solar Sail Missions Flown (as of October 2019) NanoSail-D (2010) IKAROS (2010) LightSail-1 (2015) CanX-7 (2016) InflateSail (2017) NASA JAXA The Planetary Society Canada EU/Univ. of Surrey Earth Orbit Interplanetary Earth Orbit Earth Orbit Earth Orbit Deployment Only Full Flight Deployment Only Deployment Only Deployment Only 3U CubeSat 315 kg Smallsat 3U CubeSat 3U CubeSat 3U CubeSat 10 m2 196 m2 32 m2 <10 m2 10 m2 3 Current and Planned Solar Sail Missions CU Aerospace (2018) LightSail-2 (2019) Near Earth Asteroid Solar Cruiser (2024) Univ. Illinois / NASA The Planetary Society Scout (2020) NASA NASA Earth Orbit Earth Orbit Interplanetary L-1 Full Flight Full Flight Full Flight Full Flight In Orbit; Not yet In Orbit; Successful deployed 6U CubeSat 90 Kg Spacecraft 3U CubeSat 86 m2 >1200 m2 3U CubeSat 32 m2 20 m2 4 Near Earth Asteroid Scout The Near Earth Asteroid Scout Will • Image/characterize a NEA during a slow flyby • Demonstrate a low cost asteroid reconnaissance capability Key Spacecraft & Mission Parameters • 6U cubesat (20cm X 10cm X 30 cm) • ~86 m2 solar sail propulsion system • Manifested for launch on the Space Launch System (Artemis 1 / 2020) • 1 AU maximum distance from Earth Leverages: combined experiences of MSFC and JPL Close Proximity Imaging Local scale morphology, with support from GSFC, JSC, & LaRC terrain properties, landing site survey Target Reconnaissance with medium field imaging Shape, spin, and local environment NEA Scout Full Scale EDU Sail Deployment 6 Solar Cruiser Mission Concept Mission Profile Solar Cruiser may launch as a secondary payload on the NASA IMAP mission in October, 2024. -
Theory of Space Magnetic Sail Some Common Mistakes and Electrostatic Magsail
1 Article MagSail after Cath for J 10 1 6 06 AIAA -2006 -8148 Theory of Space Magnetic Sail Some Common Mistakes and Electrostatic MagSail * Alexander Bolonkin C&R, 1310 Avenue R, #F -6, Brooklyn, NY 11229, USA T/F 718 -339 -4563, [email protected], http://Bolonki n.narod.ru Abstract The first reports on the “Space Magnetic Sail” concept appeared more 30 years ago. During the period since some hundreds of research and scientific works have been published, including hundreds of research report by professors at major famous universities. The author herein shows that all these works related to Space Magnetic Sail concept are technically incorrect because their authors did not take into consideration that solar wind impinging a MagSail magnetic field creates a particle m agnetic field opposed to the MagSail field. In the incorrect works, the particle magnetic field is hundreds times stronger than a MagSail magnetic field. That means all the laborious and costly computations in revealed in such technology discussions are us eless: the impractical findings on sail thrust (drag), time of flight within the Solar System and speed of interstellar trips are essentially worthless working data! The author reveals the correct equations for any estimated performance of a Magnetic Sail as well as a new type of Magnetic Sail (without a matter ring). Key words: magnetic sail, theory of MagSail, space magnetic sail, Electrostatic MagSail *Presented to 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference , 6 - 9 Nov 2006 National Convention Centre, Canberra, Australia. Introduction The idea of utilizing the magnetic field to aggregate matter in space, harnessing a drag from solar wind or receiving a thrust from an Earth - charged particle beam is old. -
9.0 BACKGROUND “What Do I Do First?” You Need to Research a Card (Thruster Or 9.1 DESIGNER’S NOTES Robonaut) with a Low Fuel Consumption
9.2 TIPS FOR INEXPERIENCED ROCKET CADETS 9.0 BACKGROUND “What do I do first?” You need to research a card (thruster or 9.1 DESIGNER’S NOTES robonaut) with a low fuel consumption. A “1” is great, a “4” The original concept for this game was a “Lords of the Sierra Madre” in is marginal. The PRC player*** can consider an dash to space. With mines, ranches, smelters, and rail lines all purchased and claim Hellas Basin on Mars, using just his crew card. He controlled by different players, who have to negotiate between them- needs 19 fuel steps (6 WT) along the red route to do this. selves to expand. But space does not work this way. “What does my rocket need?” Your rocket needs 4 things: Suppose you have a smelter on one main-belt asteroid, powered by a • A card with a thruster triangle (2.4D) to act as a thruster. • A card with an ISRU rating, if its mission is to prospect. beam-station on another asteroid, and you discover platinum on a third • A refinery, if its mission is to build a factory. nearby asteroid. Unfortunately for long-term operations, next year these • Enough fuel to get to the destination. asteroids will be separated by 2 to 6 AUs.* Furthermore, main belt Decide between a small rocket able to make multiple claims, Hohmann transfers are about 2 years long, with optimal transfer opportu- or a big rocket including a refinery and robonaut able to nities about 7 years apart. Jerry Pournelle in his book “A Step Farther industrialize the first successful claim. -
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. -
E-Sail for Fast Interplanetary Travel. M
Planetary Science Vision 2050 Workshop 2017 (LPI Contrib. No. 1989) 8056.pdf E-SAIL FOR FAST INTERPLANETARY TRAVEL. M. Aru1, P. Janhunen2, 1University of Tartu, Estonia, 2Finnish Meteorological Institute, Finland Introduction: Propulsion is a significant factor for areas of scientific research and new types of missions our access to the Solar System and the time con- could be imagined and created, improving our unders- sumption of the missions. We propose to use the elect- tanding of the Solar System. ric solar wind sail (E-sail), which can provide remar- Manned presence on Mars. A spacecraft equipped kable low thrust propulsion without needing propellant with a large E-sail, that provides 1 N of thrust at 1 au [1, 2]. from Sun, can travel from Earth to the asteroid belt in a The E-sail is a propellantless propulsion concept year. One such spacecraft can bring back three tonnes that uses centrifugally stretched, charged tethers to of water in three years, and repeat the journey multiple extract momentum from the solar wind to produce times within its estimated lifetime of at least ten years thrust. Over periods of months, this small but conti- [9, 12]. The water can be converted to synthetic cryo- nuous thrust can accelerate the spacecraft to great genic rocket fuel in orbital fuelling stations where speeds of approximately 20 to 30 au/year. For examp- manned vehicles travelling between Earth and Mars le, distances of 100 au could be reached in <10 years, can be fuelled. This dramatically reduces the overall which is groundbreaking [1]. mission fuel ratio at launch, and opens up possibilities The principles of operation: A full-scale E-sail for affordable continuous manned presence on Mars includes up to 100 thin, many kilometers long tethers, [13]. -
Future Space Transportation Technology: Prospects and Priorities
Future Space Transportation Technology: Prospects and Priorities David Harris Projects Integration Manager Matt Bille and Lisa Reed In-Space Propulsion Technology Projects Office Booz Allen Hamilton Marshall Space Flight Center 12 1 S. Tejon, Suite 900 MSFC, AL 35812 Colorado Springs, CO 80903 [email protected] [email protected] / [email protected] ABSTRACT. The Transportation Working Group (TWG) was chartered by the NASA Exploration Team (NEXT) to conceptualize, define, and advocate within NASA the space transportation architectures and technologies required to enable the human and robotic exploration and development of‘ space envisioned by the NEXT. In 2002, the NEXT tasked the TWG to assess exploration space transportation requirements versus current and prospective Earth-to-Orbit (ETO) and in-space transportation systems, technologies, and rcsearch, in order to identify investment gaps and recommend priorities. The result was a study nom’ being incorporatcd into future planning by the NASA Space Architect and supporting organizations. This papcr documents the process used to identify exploration space transportation investment gaps ;IS well as tlie group’s recommendations for closing these gaps and prioritizing areas of future investment for NASA work on advanced propulsion systems. Introduction investments needed to close gaps before the point of flight demonstration or test. The NASA Exploration Team (NEXT) was chartered to: Achieving robotic, and eventually, human presence beyond low Earth orbit (LEO) will Create and maintain a long-term require an agency-wide commitment of NASA strategic vision lor science-driven centers working together as “one NASA.” humanhobotic exploration Propulsion technology advancements are vital if NASA is to extend a human presence beyond the Conduct advanced concepts analym Earth’s neighhorhood. -
IAF Space Propulsion Symposium 2019
IAF Space Propulsion Symposium 2019 Held at the 70th International Astronautical Congress (IAC 2019) Washington, DC, USA 21 -25 October 2019 Volume 1 of 2 ISBN: 978-1-7138-1491-7 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© (2019) by International Astronautical Federation All rights reserved. Printed with permission by Curran Associates, Inc. (2020) For permission requests, please contact International Astronautical Federation at the address below. International Astronautical Federation 100 Avenue de Suffren 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 PROPULSION SYSTEM (1) BLUE WHALE 1: A NEW DESIGN APPROACH FOR TURBOPUMPS AND FEED SYSTEM ELEMENTS ON SOUTH KOREAN MICRO LAUNCHERS ............................................................................ 1 Dongyoon Shin KEYNOTE: PROMETHEUS: PRECURSOR OF LOW-COST ROCKET ENGINE ......................................... 2 Jérôme Breteau ASSESSMENT OF MON-25/MMH PROPELLANT SYSTEM FOR DEEP-SPACE ENGINES ...................... 3 Huu Trinh 60 YEARS DLR LAMPOLDSHAUSEN – THE EUROPEAN RESEARCH AND TEST SITE FOR CHEMICAL SPACE PROPULSION SYSTEMS ....................................................................................... 9 Anja Frank, Marius Wilhelm, Stefan Schlechtriem FIRING TESTS OF LE-9 DEVELOPMENT ENGINE FOR H3 LAUNCH VEHICLE ................................... 24 Takenori Maeda, Takashi Tamura, Tadaoki Onga, Teiu Kobayashi, Koichi Okita DEVELOPMENT STATUS OF BOOSTER STAGE LIQUID ROCKET ENGINE OF KSLV-II PROGRAM ....................................................................................................................................................... -
Title Study on Propulsive Characteristics of Magnetic Sail And
Study on Propulsive Characteristics of Magnetic Sail and Title Magneto Plasma Sail by Plasma Particle Simulations( Dissertation_全文 ) Author(s) Ashida, Yasumasa Citation 京都大学 Issue Date 2014-01-23 URL https://doi.org/10.14989/doctor.k17984 Right Type Thesis or Dissertation Textversion ETD Kyoto University Acknowledgment I would like to acknowledge many people supporting my doctorate study. My supervisor, Professor Hiroshi Yamakawa of Research Institute for Sustainable Humanosphere (RISH) of Kyoto University, supported my research throughout my master’s and doctor’s course. His valuable suggestions and advises indicated the guideline of my study, and especially, I learned the attitude toward researches. In addition, his work as the member of Strategic Headquarters for Space Policy has aroused my enthusiasm about the further evolution of the space exploration industry and a desire to contribute to it. I am deeply grateful for him. I am most grateful to Associate Professor Ikkoh Funaki of The Institute of Space and Astro- nautical Science (ISAS) of Japan Aerospace Exploration Agency (JAXA) for his advice. I am thankful for giving me a chance to start the study on the propulsion system making use of the solar wind. He had helped me since the beginning of my study. I would like to express my deep gratitude to him. I want to thank Associate Professor Hirotsugu Kojima of RISH/Kyoto University. He taught me various knowledge about plasma physics, the experimental studies and so on. I greatly appreciate Professor Tetsuji Matsuo of Kyoto University for our fruitful discussions and for reviewing this thesis. I also sincerely thank him for his many helpful comments and astute suggestions. -
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. -
Solar Electric Propulsion Sail
IOSR Journal of Electronics and Communication Engineering (IOSR-JECE) e-ISSN: 2278-2834,p- ISSN: 2278-8735.Volume 13, Issue 5, Ver. I (Sep.-Oct. 2018), PP 18-22 www.iosrjournals.org Solar Electric Propulsion Sail Dr. S.S. Subashka Ramesh [1] Sri Haripriya Nutulapti [2], Yashraj Sharma [3], Pratyush Kumar [4] [1], [2], [3], [4] Department of Computer Science and Engineering, SRM institute of science & technology Ramapuram Campus, Chennai-89, India. Corresponding Author: Dr. S.S. Subashka Ramesh Abstract: The solar expedition missions have been minimized mainly due to the performance of the space capsules, also because of the planned amount of fuel a space shuttle must carry without discharging in order to advance to an unfamiliar region. Traditionally, a solar electric propulsion sail is extremely deformable to drive a space rocket through outer space. Photon or electric sails are propounding medium of propulsion by utilizing the cosmic radiation endeavored because of sun’s rays on massive mirrors. It is a fusion of photo-voltaic cells and ions for the propelling and is also capable of enabling very fine maneuvering of the spacecraft by means of large sail-surface deformations. Solar electric propulsion sailutilizes the natural beams of sunlight to advancethe vehicles into and out of space, just the way wind helps to propel the sailboats over the water. NASA team claimed working on the start ofgrowth of technology on the assignment recognized as the solar sail demonstrator which proved thatmaking use of giant, weightless and unfurling objects float in universe would enhance the abilities of travelling deeper in space. -
Electric Sail Technology Demonstration Mission Spacecraft
https://ntrs.nasa.gov/search.jsp?R=20170001821 2019-06-22T08:27:43+00:00Z The Conceptual Design of an Electric Sail Technology Demonstration Mission Spacecraft Presentation at: 40th Annual AAS Guidance and Control Conference Breckenridge, CO, USA February 3-8, 2017 Bruce M. Wiegmann NASA-MSFC-ED04 [email protected] Presentation Agenda • HERTS/Electric Sail background information • Findings from the Phase I NIAC • This propulsion technology enables trip times to the Heliopause in 10 – 12 years • Fastest transportation method to reach Heliopause of near term propulsion technologies • Current Phase II NIAC tasks • Plasma chamber testing • Particle-in-cell (PIC) space plasma to spacecraft modeling • Tether material investigation • Conceptual design of a TDM spacecraft • Mission capture Image shown is copyright by: Alexandre Szames, Antigravite, Paris, and is used with permission National Aeronautics and Space Administration 2 Solar Wind Basics-> Solar Sail • The relative velocity of the Solar Wind through the decades The solar wind ions traveling at 400-500 km/sec are the naturally occurring (free) energy source that propels an E-Sail National Aeronautics and Space Administration 3 Electric Sail Origins The electric solar wind sail, or electric sail for short, is a propulsion invention made in 2006 at the Kumpula Space Centre by Dr. Pekka Janhunen. Image courtesy of: Dr. Pekka Janhunen Phase I Findings • Electric-Sail propulsion systems are the fastest method to get spacecraft to deep space destinations as compared to: • Solar sails, • All chemical propulsions, • Electric (ion) propulsion systems • Technology appears to be viable . • Technology Assessment – Most subsystems at high state of readiness except: • Wire-plasma interaction modeling, • Wire deployment, and • Dynamic control of E–Sail spacecraft… • These are the three areas of focus for the current Phase II NIAC National Aeronautics and Space Administration 5 Electric Sail – Concept of Operations • The E-sail consists of 10 to 20 conducting, positively charged, bare wires, each 1–20 km in length. -
Orbit Transfer Problems and the Results You Obtained
MS&E 315 and CME 304 Solar sailing between Earth and Mars 1 Overview In this project, you will use your knowledge of nonlinear optimization to help a space agency design a cargo mission. The mission consists of making a cargo spacecraft perform interplanetary orbit transfers between Earth and Mars, and the agency is considering using a solar sail to propel the spacecraft. They need you to determine how the spacecraft should be operated to perform these orbit transfers in the shortest possible time for different solar sail technologies. 2 Mission information 2.1 Simplifications The agency has determined that the following simplifications are acceptable for your analysis: 1. Orbits are heliocentric, circular and co-planar. 2. Gravitational effects due to celestial bodies other than the Sun are ignored. 3. The Sun and spacecraft are modeled as point masses. 4. The Sun has spherically symmetric gravitational and radiation fields. 2.2 Problem description The problem you have to solve consists of determining how the solar sail of the spacecraft should be oriented to make the spacecraft perform each of the interplanetary orbit transfers Earth-Mars and Mars-Earth in the shortest possible time. You have to perform this analysis for some, say three, of the available solar sail technologies so that the agency can choose the most appropriate one in terms of cost and performance. Each solar sail technology is identified by a characteristic acceleration, as described in the next subsection. Figure1 shows a diagram of the orbits of interest, where rE and !E denote the radius and angular velocity, respectively, of Earth's orbit around the Sun, and rM and !M denote the radius and angular velocity, respectively, of Mars's orbit around the Sun.