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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. -
Soviet Steps Toward Permanent Human Presence in Space
SALYUT: Soviet Steps Toward Permanent Human Presence in Space December 1983 NTIS order #PB84-181437 Recommended Citation: SALYUT: Soviet Steps Toward Permanent Human Presence in Space–A Technical Mere- orandum (Washington, D. C.: U.S. Congress, Office of Technology Assessment, OTA- TM-STI-14, December 1983). Library of Congress Catalog Card Number 83-600624 For sale by the Superintendent of Documents, U.S. Government Printing Office, Washington, D.C. 20402 Foreword As the other major spacefaring nation, the Soviet Union is a subject of interest to the American people and Congress in their deliberations concerning the future of U.S. space activities. In the course of an assessment of Civilian Space Stations, the Office of Technology Assessment (OTA) has undertaken a study of the presence of Soviets in space and their Salyut space stations, in order to provide Congress with an informed view of Soviet capabilities and intentions. The major element in this technical memorandum was a workshop held at OTA in December 1982: it was the first occasion when a significant number of experts in this area of Soviet space activities had met for extended unclassified discussion. As a result of the workshop, OTA prepared this technical memorandum, “Salyut: Soviet Steps Toward Permanent Human Presence in Space. ” It has been reviewed extensively by workshop participants and others familiar with Soviet space activities. Also in December 1982, OTA wrote to the U. S. S. R.’s Ambassador to the United States Anatoliy Dobrynin, requesting any information concerning present and future Soviet space activities that the Soviet Union judged could be of value to the OTA assess- ment of civilian space stations. -
Case Study of the Internal Growth Dynamics of NASA
University of Montana ScholarWorks at University of Montana Graduate Student Theses, Dissertations, & Professional Papers Graduate School 1971 Case study of the internal growth dynamics of NASA Bruce M. Whitehead The University of Montana Follow this and additional works at: https://scholarworks.umt.edu/etd Let us know how access to this document benefits ou.y Recommended Citation Whitehead, Bruce M., "Case study of the internal growth dynamics of NASA" (1971). Graduate Student Theses, Dissertations, & Professional Papers. 1747. https://scholarworks.umt.edu/etd/1747 This Thesis is brought to you for free and open access by the Graduate School at ScholarWorks at University of Montana. It has been accepted for inclusion in Graduate Student Theses, Dissertations, & Professional Papers by an authorized administrator of ScholarWorks at University of Montana. For more information, please contact [email protected]. CASE STUDY OF THE INTERNAL GROWTH DYNAMICS OF NASA By Bruce M. Whitehead B.A. University of Montana, 1970 Presented in partial fulfillment of the requirements for the degree of Master of Arts UNIVERSITY OF MONTANA 1971 Approved by: Chairman, Board of Examiners Dea^ Grad^txe 7/ UMI Number: EP35189 All rights reserved INFORMATION TO ALL USERS The quality of this reproduction is dependent upon the quality of the copy submitted. In the unlikely event that the author did not send a complete manuscript and there are missing pages, these will be noted. Also, if material had to be removed, a note will indicate the deletion. UMI OlM«rt*tk>n Publishing UMI EP35189 Published by ProQuest LLC (2012). Copyright in the Dissertation held by the Author. -
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. -
Hybrid Solar Sails for Active Debris Removal Final Report
HybridSail Hybrid Solar Sails for Active Debris Removal Final Report Authors: Lourens Visagie(1), Theodoros Theodorou(1) Affiliation: 1. Surrey Space Centre - University of Surrey ACT Researchers: Leopold Summerer Date: 27 June 2011 Contacts: Vaios Lappas Tel: +44 (0) 1483 873412 Fax: +44 (0) 1483 689503 e-mail: [email protected] Leopold Summerer (Technical Officer) Tel: +31 (0)71 565 4192 Fax: +31 (0)71 565 8018 e-mail: [email protected] Ariadna ID: 10-6411b Ariadna study type: Standard Contract Number: 4000101448/10/NL/CBi Available on the ACT website http://www.esa.int/act Abstract The historical practice of abandoning spacecraft and upper stages at the end of mission life has resulted in a polluted environment in some earth orbits. The amount of objects orbiting the Earth poses a threat to safe operations in space. Studies have shown that in order to have a sustainable environment in low Earth orbit, commonly adopted mitigation guidelines should be followed (the Inter-Agency Space Debris Coordination Committee has proposed a set of debris mitigation guidelines and these have since been endorsed by the United Nations) as well as Active Debris Removal (ADR). HybridSail is a proposed concept for a scalable de-orbiting spacecraft that makes use of a deployable drag sail membrane and deployable electrostatic tethers to accelerate orbital decay. The HybridSail concept consists of deployable sail and tethers, stowed into a nano-satellite package. The nano- satellite, deployed from a mothership or from a launch vehicle will home in towards the selected piece of space debris using a small thruster-propulsion firing and magnetic attitude control system to dock on the debris. -
Propulsion Systems for Interstellar Exploration
The Future of Electric Propulsion: A Young Visionary Paper Competition 35th International Electric Propulsion Conference October 8-12, 2017 Atlanta, Georgia Propulsion Systems for Interstellar Exploration Steven L. Magnusen Embry-Riddle Aeronautical University, Daytona Beach, FL, USA Alfredo D. Tuesta∗ National Research Council Postdoctoral Associate, Washington, DC, USA [email protected] August 4, 2017 Abstract The idea of manned spaceships exploring nearby star systems, although difficult and unlikely in this generation or the next, is becoming less a tale of science fiction and more a concept of rigorous scientific interest. In 2003, NASA sent two rovers to Mars and returned images and data that would change our view of the planet forever. Already, scientists and engineers are proposing concepts for manned missions to the Red Planet. As we prepare to visit the planets in our solar system, we dare to explore the possibilities and venues to travel beyond. With NASA’s count of known exoplanets now over 3,000 and growing, interest in interstellar science is being renewed as well. In this work, the authors discuss the benefits and deficiencies of current and emerging technologies in electric propulsion for outer planet and extrasolar exploration and propose innovative and daring concepts to further the limits of present engineering. The topics covered include solar and electric sails and beamed energy as propulsion systems. I. Introduction Te Puke is the name for the voyaging canoe that the Polynesians developed to sail across vast distances in the Pacific Ocean at the turn of the first millennium. This primitive yet sophisticated canoe, made of two hollowed out tree trunks and crab claw sails woven together from leaves, allowed Polynesian sailors to navigate the open ocean by studying the stars. -
Advancing Asteroid Surface Exploration Using Sublimate- Based Regenerative Micropropulsion and 3D Path Planning
Advancing Asteroid Surface Exploration Using Sublimate- Based Regenerative Micropropulsion And 3D Path Planning Item Type text; Electronic Thesis Authors Wilburn, Greg Publisher The University of Arizona. Rights Copyright © is held by the author. Digital access to this material is made possible by the University Libraries, University of Arizona. Further transmission, reproduction, presentation (such as public display or performance) of protected items is prohibited except with permission of the author. Download date 07/10/2021 15:36:40 Link to Item http://hdl.handle.net/10150/636641 ADVANCING ASTEROID SURFACE EXPLORATION USING SUBLIMATE-BASED REGENERATIVE MICROPROPULSION AND 3D PATH PLANNING by Greg Wilburn ____________________________ Copyright © Greg Wilburn 2019 A Thesis Submitted to the Faculty of the DEPARTMENT OF AEROSPACE AND MECHANICAL ENGINEERING In Partial Fulfillment of the Requirements For the Degree of MASTER OF SCIENCE In the Graduate College THE UNIVERSITY OF ARIZONA 2019 Acknowledgements The author would first like to thank his thesis committee members for their help and direction in solving some of the complex problems in this work. The author acknowledges the time and effort of his advisor, Dr. Jekan Thangavelauthum, for his guidance over the entire course of the project. Recognition is deserved for Dr. Erik Asphaug and Dr. Stephen Schwarz for their development of the AMIGO robot concept. The development of MEMS systems presented could not have been done without the coursework and guidance from Dr. Eniko Enikov. Special thanks goes to my friends and family who have supported and encouraged me through my graduate studies. I couldn’t have done it without you, Emilia! 3 Table of Contents I. -
Space Propulsion Technology for Small Spacecraft
Space Propulsion Technology for Small Spacecraft The MIT Faculty has made this article openly available. Please share how this access benefits you. Your story matters. Citation Krejci, David, and Paulo Lozano. “Space Propulsion Technology for Small Spacecraft.” Proceedings of the IEEE, vol. 106, no. 3, Mar. 2018, pp. 362–78. As Published http://dx.doi.org/10.1109/JPROC.2017.2778747 Publisher Institute of Electrical and Electronics Engineers (IEEE) Version Author's final manuscript Citable link http://hdl.handle.net/1721.1/114401 Terms of Use Creative Commons Attribution-Noncommercial-Share Alike Detailed Terms http://creativecommons.org/licenses/by-nc-sa/4.0/ PROCC. OF THE IEEE, VOL. 106, NO. 3, MARCH 2018 362 Space Propulsion Technology for Small Spacecraft David Krejci and Paulo Lozano Abstract—As small satellites become more popular and capa- While designations for different satellite classes have been ble, strategies to provide in-space propulsion increase in impor- somehow ambiguous, a system mass based characterization tance. Applications range from orbital changes and maintenance, approach will be used in this work, in which the term ’Small attitude control and desaturation of reaction wheels to drag com- satellites’ will refer to satellites with total masses below pensation and de-orbit at spacecraft end-of-life. Space propulsion 500kg, with ’Nanosatellites’ for systems ranging from 1- can be enabled by chemical or electric means, each having 10kg, ’Picosatellites’ with masses between 0.1-1kg and ’Fem- different performance and scalability properties. The purpose tosatellites’ for spacecrafts below 0.1kg. In this category, the of this review is to describe the working principles of space popular Cubesat standard [13] will therefore be characterized propulsion technologies proposed so far for small spacecraft. -
Comparison of the Solar Sail with Electric Propulsion Systems
.:- .:- &,, NASA CONTRACTOR REPORT *o Qo COMPARISON OF THE SOLAR SAIL WITH ELECTRIC PROPULSION SYSTEMS Prepared by . -... THE MACNEAL-SCHWENDLER CORPORATION Los Angeles, Calif. 90041 for . .. NATIONAL AERONAUTICS AND SPACE ADMINISTRATION. WASHINGTON, D. c. ea FEBRUARY 1972 TECH LIBRARY KAFB, NM 1. Report No. 2. Government Accession No. NASA CR-1986 I 4. Title and Subtitle 5. Report Date COMPARISON OF THE SOLAR SAIL WITH ELECTRIC February 1972 PROPULSIONSYSTEMS 6. Performing Organization Code 7. Author(s) 8. Performing Organization Report No. Richard H. MacNeal 'EMSR 13A 10. Work Unit No. 9. Performing Organization Name and Address The MacNeal-SchwendlerCorpmTtkCm ~-~ 74.42 NO. FigueroaStreet 11. Contract or Grant No. Los Angeles , California90041 NAS7-699 13. Type of Re rt and Period Covered 2. Sponsoring AgencyName and Address ContracGr NationalAeronautics and Space Administration FinalReport Washington, D. C. 20546 14. Sponsoring AgencyCade RWS 5. Supplementary Notes 6. Abstract A studyof the propulsive efficiencies of solar sails and electric propulsionsystems which shows increasing efficiency for solar sails for. launch mission durations. 7. Key- Words (Suggested by Author(s) 1 18. Distribution Statement Solar sails, electricpropulsion systems Unlimited advancedspace concepts. i ~~ "- .. 19. Security Classif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Price' Unclassified Unclassified 13 $3 .?70 For sale by the National Technical InformationService, Springfield, Virginia 22151 COMPARISON OF THE SOLAR SA1 L WITHELECTRIC PROPULSION SYSTEMS By Richard H. MacNeal The MacNeal-SchwendlerCorporation ABSTRACT The propulsiveefficiencies of the solar sail and ofelectric propul- sion systemsare compared on the basis of specificimpulse. It is shown thatthe solar sail is more efficientat onea.u. -
Beam Powered Propulsion Systems
Beam Powered Propulsion Systems Nishant Agarwal University of Colorado, Boulder, 80309 While chemical rockets have dominated space exploration, other forms of rocket propulsion based on nuclear power, electrostatic and magnetic drives, and other principles have been considered from the earliest days of the field with the goal to improve efficiency through higher exhaust velocities, in order to reduce the amount of fuel the rocket vehicle needs to carry. However, the gap between technology to reach orbit from surface and from orbit to interplanetary travel still remains open considering both economics of time and money. In addition, methods have been tested over the years to reach the orbit with single stage rocket from earth’s surface which will eventually result in drastic cost savings. Reusable SSTO vehicles offer the promise of reduced launch expenses by eliminating recurring costs associated with hardware replacement inherent in expendable launch systems. No Earth- launched SSTO launch vehicles have ever been constructed till date. Beam Powered Propulsion has emerged as a promising concept that is capable to fulfill all regimes of space travel. This paper takes a look at these concepts and studies the feasibility of Microwave Propulsion for possibility of SSTO vehicle. Nomenclature At = nozzle throat area C* = characteristic velocity Cf = Thrust Coefficient Cp = Specific heat constant Dt, Dexit = Diameter of nozzle throat, Nozzle exit diameter g = acceleration due to gravity Gamma = Specific heat ratio LOX/LH = Liquid Oxygen/Liquid Hydrogen MR = mass ratio Mi,Ms,Mp = total mass, structural mass, propellant mass, payload mass Mpayl = payload mass Mdot = flow rate Isp = Specific Impulse Ve = exhaust velocity I. -
Human Spaceflight Plans of Russia, China and India
Presentation to the Secure World Foundation November 3, 2011 by Marcia S. Smith Space and Technology Policy Group, LLC and SpacePolicyOnline.com “Civil” Space Activities in Russia “Civil” space activities Soviet Union did not distinguish between “civil” and “military” space programs until 1985 Line between the two can be quite blurry For purposes of this presentation, “civil” means Soviet/Russian activities analogous to NASA and NOAA (though no time to discuss metsats today) Roscosmos is Russian civil space agency. Headed by Army General (Ret.) Vladimir Popovkin Recent reports of $3.5 billion budget, but probably does not include money from US and others 11-03-11 2 Key Points to Take Away Space cooperation takes place in the broad context of U.S.-Russian relations Russia may not be a superpower today, but it is a global power and strategically important to the United States Complex US-Russian relationship, as New START and INKSNA demonstrate Russian space program modest by Soviet standards, but Retains key elements Leverages legacy capabilities for current activities and commercial gain Is a global launch service provider from four launch sites from Arctic to equator Proud history of many space “firsts,” but also tragedies and setbacks U.S.-Soviet/Russian civil space relationship has transitioned from primarily competition to primarily cooperation/interdependence today Cooperation not new, dates back to 1963, but much more intensive today U.S. is dependent on Russia for some things, but they also need us Bold dreams endure as Mars 500 demonstrates 11-03-11 3 Today is 54th Anniversary of First Female in Space 11-03-11 4 Just One of Many “Firsts” First satellite (Sputnik, Oct. -
High Speed AB-Solar Sail*
1 Article High Reflective Solar Sail after Cathcarth 6 3 06 AIAA-2006-4806 High Speed AB-Solar Sail* Alexander Bolonkin C&R, 1310 Avenue R, #F-6, Brooklyn, NY 11229, USA T/F 718-339-4563, [email protected], [email protected], http://Bolonkin.narod.ru Abstract The Solar sail is a large thin film used to collect solar light pressure for moving of space apparatus. Unfortunately, the solar radiation pressure is very small about 9 N/m2 at Earth's orbit. However, the light force significantly increases up to 0.2 - 0.35 N/m2 near the Sun. The author offers his research on a new revolutionary highly reflective solar sail which flyby (after special maneuver) near Sun and attains velocity up to 400 km/sec and reaching far planets of the Solar system in short time or enable flights out of Solar system. New, highly reflective sail-mirror allows avoiding the strong heating of the solar sail. It may be useful for probes close to the Sun and Mercury and Venus. Key words: AB-solar sail, highly reflective solar sail, high speed propulsion. * This work is presented as paper AIAA-2006-4806 for 42 Joint Propulsion Conference, Sacramento, USA, 9-12 July, 2006. Introduction A solar sail is a thin film reflector that uses solar energy for propulsion. The spacecraft deploys a large, lightweight sail which reflects light from the Sun (or some other source). The radiation pressure on the sail provides thrust by reflecting photons. The solar radiation pressure is very small 6.7 Newtons per gigawatt.