NASA Armstrong X-Press March 2021
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Industry at the Edge of Space Other Springer-Praxis Books of Related Interest by Erik Seedhouse
IndustryIndustry atat thethe EdgeEdge ofof SpaceSpace ERIK SEEDHOUSE S u b o r b i t a l Industry at the Edge of Space Other Springer-Praxis books of related interest by Erik Seedhouse Tourists in Space: A Practical Guide 2008 ISBN: 978-0-387-74643-2 Lunar Outpost: The Challenges of Establishing a Human Settlement on the Moon 2008 ISBN: 978-0-387-09746-6 Martian Outpost: The Challenges of Establishing a Human Settlement on Mars 2009 ISBN: 978-0-387-98190-1 The New Space Race: China vs. the United States 2009 ISBN: 978-1-4419-0879-7 Prepare for Launch: The Astronaut Training Process 2010 ISBN: 978-1-4419-1349-4 Ocean Outpost: The Future of Humans Living Underwater 2010 ISBN: 978-1-4419-6356-7 Trailblazing Medicine: Sustaining Explorers During Interplanetary Missions 2011 ISBN: 978-1-4419-7828-8 Interplanetary Outpost: The Human and Technological Challenges of Exploring the Outer Planets 2012 ISBN: 978-1-4419-9747-0 Astronauts for Hire: The Emergence of a Commercial Astronaut Corps 2012 ISBN: 978-1-4614-0519-1 Pulling G: Human Responses to High and Low Gravity 2013 ISBN: 978-1-4614-3029-2 SpaceX: Making Commercial Spacefl ight a Reality 2013 ISBN: 978-1-4614-5513-4 E r i k S e e d h o u s e Suborbital Industry at the Edge of Space Dr Erik Seedhouse, M.Med.Sc., Ph.D., FBIS Milton Ontario Canada SPRINGER-PRAXIS BOOKS IN SPACE EXPLORATION ISBN 978-3-319-03484-3 ISBN 978-3-319-03485-0 (eBook) DOI 10.1007/978-3-319-03485-0 Springer Cham Heidelberg New York Dordrecht London Library of Congress Control Number: 2013956603 © Springer International Publishing Switzerland 2014 This work is subject to copyright. -
Atlas Launch System Mission Planner's Guide, Atlas V Addendum
ATLAS Atlas Launch System Mission Planner’s Guide, Atlas V Addendum FOREWORD This Atlas V Addendum supplements the current version of the Atlas Launch System Mission Plan- ner’s Guide (AMPG) and presents the initial vehicle capabilities for the newly available Atlas V launch system. Atlas V’s multiple vehicle configurations and performance levels can provide the optimum match for a range of customer requirements at the lowest cost. The performance data are presented in sufficient detail for preliminary assessment of the Atlas V vehicle family for your missions. This guide, in combination with the AMPG, includes essential technical and programmatic data for preliminary mission planning and spacecraft design. Interface data are in sufficient detail to assess a first-order compatibility. This guide contains current information on Lockheed Martin’s plans for Atlas V launch services. It is subject to change as Atlas V development progresses, and will be revised peri- odically. Potential users of Atlas V launch service are encouraged to contact the offices listed below to obtain the latest technical and program status information for the Atlas V development. For technical and business development inquiries, contact: COMMERCIAL BUSINESS U.S. GOVERNMENT INQUIRIES BUSINESS INQUIRIES Telephone: (691) 645-6400 Telephone: (303) 977-5250 Fax: (619) 645-6500 Fax: (303) 971-2472 Postal Address: Postal Address: International Launch Services, Inc. Commercial Launch Services, Inc. P.O. Box 124670 P.O. Box 179 San Diego, CA 92112-4670 Denver, CO 80201 Street Address: Street Address: International Launch Services, Inc. Commercial Launch Services, Inc. 101 West Broadway P.O. Box 179 Suite 2000 MS DC1400 San Diego, CA 92101 12999 Deer Creek Canyon Road Littleton, CO 80127-5146 A current version of this document can be found, in electronic form, on the Internet at: http://www.ilslaunch.com ii ATLAS LAUNCH SYSTEM MISSION PLANNER’S GUIDE ATLAS V ADDENDUM (AVMPG) REVISIONS Revision Date Rev No. -
Orion Capsule Launch Abort System Analysis
Orion Capsule Launch Abort System Analysis Assignment 2 AE 4802 Spring 2016 – Digital Design and Manufacturing Georgia Institute of Technology Authors: Tyler Scogin Michel Lacerda Jordan Marshall Table of Contents 1. Introduction ......................................................................................................................................... 4 1.1 Mission Profile ............................................................................................................................. 7 1.2 Literature Review ........................................................................................................................ 8 2. Conceptual Design ............................................................................................................................. 13 2.1 Design Process ........................................................................................................................... 13 2.2 Vehicle Performance Characteristics ......................................................................................... 15 2.3 Vehicle/Sub-Component Sizing ................................................................................................. 15 3. Vehicle 3D Model in CATIA ................................................................................................................ 22 3.1 3D Modeling Roles and Responsibilities: .................................................................................. 22 3.2 Design Parameters and Relations:............................................................................................ -
19700031865.Pdf
1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA TM X-2075 4. Title and Subtitle 5. Report Date EFFECTOFRETROROCKETCANTANGLEON October 1970 6. Performing Organization Code GROUND EROSION - A SCALED VIKING STUDY 7. Author(s) 8. Performing Organization Report No. Leonard V. Clark L-7376 IO. Work Unit No. 9. Performing Organization Name and Address 124-08-29-01 NASA Langley Research Center 11. Contract or Grant No. Hampton, Va. 23365 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address Technical Memorandum National Aeronautics and Space Administration 14. Sponsoring Agency Code Washington, D.C. 20546 ~ 16. Abstract An experimental study was conducted at the Langley Research Center to evaluate the relative merits of canting the Viking lander retrorockets toward the spacecraft center line as a means of reducing rocket-exhaust disturbance of the surface of Mars. This paper describes the experimental study, outlines the scaling scheme of the tests, and briefly dis- cusses significant data trends. The results of this exploratory study indicate that canting of the retrorockets toward the center of the spacecraft does reduce ground erosion of the landing site from that produced by a lander configuration with downward-directed retro- rockets. Obviously, before canting the Viking lander retrorockets, it would be necessary to weigh this reduction in surface disturbance against the attendant loss of thrust due to canting. 17. Key Words (Suggested by Author(s) ) 18. Distribution Statement Jet impingement Unclassified - Unlimited Rocket-exhaust effects 19. Security Classif. (of this report) 20. Security Classif. (of this page) 21. No. -
Reusable Rocket Upper Stage Development of a Multidisciplinary Design Optimisation Tool to Determine the Feasibility of Upper Stage Reusability L
Reusable Rocket Upper Stage Development of a Multidisciplinary Design Optimisation Tool to Determine the Feasibility of Upper Stage Reusability L. Pepermans Technische Universiteit Delft Reusable Rocket Upper Stage Development of a Multidisciplinary Design Optimisation Tool to Determine the Feasibility of Upper Stage Reusability by L. Pepermans to obtain the degree of Master of Science at the Delft University of Technology, to be defended publicly on Wednesday October 30, 2019 at 14:30 AM. Student number: 4144538 Project duration: September 1, 2018 – October 30, 2019 Thesis committee: Ir. B.T.C Zandbergen , TU Delft, supervisor Prof. E.K.A Gill, TU Delft Dr.ir. D. Dirkx, TU Delft This thesis is confidential and cannot be made public until October 30, 2019. An electronic version of this thesis is available at http://repository.tudelft.nl/. Cover image: S-IVB upper stage of Skylab 3 mission in orbit [23] Preface Before you lies my thesis to graduate from Delft University of Technology on the feasibility and cost-effectiveness of reusable upper stages. During the accompanying literature study, it was determined that the technology readiness level is sufficiently high for upper stage reusability. However, it was unsure whether a cost-effective system could be build. I have been interested in the field of Entry, Descent, and Landing ever since I joined the Capsule Team of Delft Aerospace Rocket Engineering (DARE). During my time within the team, it split up in the Structures Team and Recovery Team. In September 2016, I became Chief Recovery for the Stratos III student-built sounding rocket. During this time, I realised that there was a lack of fundamental knowledge in aerodynamic decelerators within DARE. -
Reusable Stage Concepts Design Tool
DOI: 10.13009/EUCASS2019-421 8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND AEROSPACE SCIENCES (EUCASS) DOI: ADD DOINUMBER HERE Reusable stage concepts design tool Lars Pepermans?, Barry Zandbergeny ?Delft University of Technology Kluyverweg 1, 2629 HS Delft [email protected] yDelft University of Technology Kluyverweg 1, 2629 HS Delft Abstract Reusable launch vehicles hold the promise of substantially reducing the cost of access to space. Many different approaches towards realising a reusable rocket exist or are being proposed. This work focuses on the use of an optimisation method for conceptual design of non-winged reusable upper stages, thereby allowing it to take into account landing on land, sea or mid-air retrieval as well as landing the full stage or the engine only. As the optimisation criterion, the ratio of the specific launch cost of the reusable to the expendable version is used. The tool also provides for a Monte Carlo analysis, which allows for investigating the ruggedness of the design solution(s) found. The article will describe the methods implemented in the Conceptual Reusability Design Tool (CRDT) together with the modifications made to ParSim v3, a simulation tool by Delft Aerospace Rocket Engi- neering. Furthermore, it will present the steps taken to verify and validate CRDT. Finally, several example cases are presented based on the Atlas V-Centaur launch vehicle. The cases demonstrate the tools capa- bility of finding optimum and the sensitivity of the found optimum. However, it also shows the optimum when the user disables some Entry Descent and Landing (EDL) options. 1. Introduction To make space more accessible, one can reduce the cost of an orbital launch. -
A Multipurpose Reusable Reentry Satellite
I I RRS - A MULTIPURPOSE REUSABLE REENTRY SATELLITE I John J. Givens· I and Richard W. Schaupp NASA Ames Research Center I ABSTRACT . This paper descr ibes a low-cost, mul tipurpose Reus able Reentry Satellite (RRS) which can carry a variety of I experiments into space, remain in orbit for up to 60 days, return autonomously to Earth and be refurbished for reuse. Potential user applications include life science, commer I cial, and others. As presently conceived, the vehicle is a blunt ballis I tic entry vehicle with an internal cavity for accommodat ing user payloads, including those utilizing the STS Get Away Special (GAS) canister. The spacecraft provides payload power, transmits payload data, receives payload I commands, and controls payload cavi ty thermal conditions. A variety of vehicle sizes with base diameters within I the range 38 to 100 in. have been investigated. Based on these investigations, a 64-in. -diameter vehicle has been selected as a baseline for conceptual design studies. This I vehicle weighs 1900 lb and has an overall length of 76 in. It can accommo~ate a payload whioh weighs 450 lb and ocoupies 21 ft . Up to 30 kWhr of lithium battery power is I available for payload use. The results of the studies to date have been very promising. Efforts are oontinuing at NASA Ames Researoh I Center to define system capabilities and requirements while contraoted vehiole study efforts are being initiated. I INTRODUCTION I In recent years user acoess to space has been seriously oonstrained by the lack of low-cost spaceoraft and the availability of launch opportunities. -
Global Indians
NEW YORK • WASHINGTON D.C. • CHICAGO • ATLANTA • CALIFORNIA VOL 26, No. 1377 February 26, 2021 50¢ Periodical Postage GLOBAL INDIANS 32 million worldwide, over 200 Indian-origin people occupy leadership positions in 15 countries Neera Tanden nomination in Antonio Guterres jeopardy UN chief Details on page 6 'extremely grateful' to India Communities unite to combat Details on page 6 Anti-Asian Violence Congress Details on page 17 government in Puducherry falls Rishi requests intervention of Details on page 10 Governor Newsom CONTENTS Details on page 20 picture courtesy NASA An illustration of NASA's Perseverance rover landing safely on Mars. (inset) Indian-American scientist Swati Bollywood -------------------------- 30 Mohan, who led the guidance, navigation, and control operations of the Mars 2020 mission Classifieds ------------------------ 31 CAPT KRISHAN SHARMA AND AGENCIES Community Post -------------- 17-24 Cover/Top Stories --------------- 5-8 The PIOs, include leaders like Mahatma Gandhi, the guidance, navigation, and control operations of Edit Page --------------------------- 33 Horoscope --------------------------- 9 This week’s question Netaji Subash Chandra Bose, mathematician S the Mars 2020 mission. Mohan's family emigrated Chandrasekhar and Bio-chemist Hargobind Khorana, from India to the US when she was only a year old. Immigration Post ------------12-13 Do you think Biden will have a Life Style ------------------------ 14-15 better deal with Iran? who continue to make India proud and with contri- Raised in Northern Virginia and Washington DC OP-ED------------------------------- 32 butions to India's freedom struggle and excellence in metro area, she completed her bachelor's degree Last week’s result Info/Highlights ---------------------- 4 scientific fields. from Cornell University in Mechanical & Aerospace Will Indo-US relations improve Real Estate -------------------- 25-27 under Biden? As the world witnessed the historic landing of Engineering, and her M.S. -
Exhumed Rocks Reveal Mars Water Ran Deep 28 June 2012
Exhumed rocks reveal Mars water ran deep 28 June 2012 In a new study, ESA's Mars Express and NASA's Mars Reconnaissance Orbiter zoomed in on craters in a 1000 x 2000 km region of the ancient southern highlands, called Tyrrhena Terra, to learn more about the history of water in this region. Focusing on the chemistry of rocks embedded in the crater walls, rims and central uplifts, as well as the surrounding exhumed material, scientists identified 175 sites bearing minerals formed in the presence of water. "The large range of crater sizes studied, from less than 1 km to 84 km wide, indicates that these The large 25 km-diameter crater in the foreground of this hydrated silicates were excavated from depths of High Resolution Stereo Camera (HRSC) perspective tens of metres to kilometres," says Damien view has excavated rocks which have been altered by Loizeau, lead author of the study. groundwater in the crust before the impact occurred. Using OMEGA (Visible and Infrared Mineralogical "The composition of the rocks is such that Mapping Spectrometer) on ESA’s Mars Express and underground water must have been present here CRISM (Compact Reconnaissance Imaging for a long period of time in order to have altered Spectrometer for Mars) on NASA’s Mars Reconnaissance Orbiter (MRO), scientists have their chemistry." identified hydrated minerals in the central mound of the crater, on the crater walls and on the large ejecta blanket around the crater. Hydrated minerals were found in 175 locations associated with other nearby craters in the Tyrrhena Terra region of Mars. -
March 2021 Universe
Featured Stories This is the first image Perseverance sent back after touching down on Mars on Feb. 18, 2021. The view, from one of Perseverance's Hazard Cameras, is partially obscured by a dust cover. Image Credit: NASA/JPL-Caltech Perseverance Lands on Mars! By Taylor Hill It’s confirmed: Jezero Crater will be the proving ground for the Perseverance rover to further our search for ancient Martian life. After seven minutes screaming through the Martian atmosphere, the Perseverance rover and its helicopter stowaway Ingenuity touched down safely on Mars. Perseverance mission commentator and guidance, navigation, and controls operations Lead Swati Mohan made the call at 12:55 p.m.; "Touchdown confirmed, Perseverance safely on the surface of Mars, ready to begin seeking the signs of past life." The first image taken by the rover's engineering camera was beamed back a mere two minutes later, providing visual evidence that the rover was truly safe on Mars' rocky red soil. Universe | March 2021 | Page 1 At JPL, select members of the Mars 2020 team, JPL Director Mike Watkins, NASA Acting Administrator Steve Jurczyk, NASA Associate Administrator for the Science Mission Directorate Thomas Zurbuchen, and NASA Science Mission Directorate’s Planetary Science Division Director Lori Glaze cheered upon touchdown from the socially-distanced Mission Support Area (MSA) in Building 230, while a majority of the Mars 2020 team and the Lab watched a livestream from their homes—a markedly different landing day experience compared to past missions due to Covid safety precautions. At the time of landing, more than 2,600 JPLers were watching the Zoom livestream, while more than 2.2 million members of the public from around the world watched the NASA.gov Youtube livestream of the landing. -
Automated Making the Map of Isidis's
AUTOMATED MAKING THE MAP OF ISIDIS’S Iluhina, J. and Rodionova, J. Sternberg State Astronomical Institute, Kashirskoe shose 57-7 kv. 514, Russia, Moscow. Tel: (7 095) 344-60-50 (home); 8 903 684-91-78 (mob.). E-mail: [email protected] ABSTRACT The plain of Isidis was chosen for landing of the spacecraft of European Space Agency (ESA) that will be this year. Mars Express is the name of ESA’s Mars mission for 2003. Mars Express is the first 'flexible' mission of ESA's long- term science exploration programmer. Launch will be from Russia by a Soyuz Fregat launcher within an 11 day launch window which opens on 1 June 2003. Arrival at Mars is planned for the following December. Mars Express comprises a number of essential components - the spacecraft and its instruments, the Lander, a network of ground and data processing stations, and the launcher itself. These are supported by an experienced team of engineers in ESA and industry and hundreds of international scientists. The radar sounder on board Mars Express, MARSIS, will map the subsurface structure from a depth of about a hundred meters to as much as a few kilometers. This is in contrast with the Mars Odyssey, which can sense surface compositions to a depth of only one meter [1]. The cameras on Mars Express will map minerals at a very high resolution, and report how they are distributed on the Martian surface. This kind of data is crucial to understand the distribution of sub-surface water. The other instruments on board Mars Express will observe the atmosphere and reveal processes by which water vapor and other atmospheric gases could have escaped into space. -
Mars Orbiter and Lander (ESA)
So much nonsense has been written about the planet … that it is easy to forget that Mars is still an object of serious scientific investigation. Canadian astronomer Peter M. Millman, in “Is There Vegetation on Mars,” The Sky, 3, 10–11 (1939) Tentative Course outline • Today: Intro to Mars, Early discoveries about Mars (Chapters 1-4) • Oct 17: Canals on Mars, Water on Mars (Chapters 5-8) • Oct 24: Lichens on Mars (Chapter 9) • Oct 31: Viking mission (Chapter 10) • Nov 7: ALH 84001 (Chapter 11) • Nov 14: Methane on Mars (Chapters 12-15) Earth and Mars Basic Facts Earth Mars • 93 million miles from • 142 million miles from sun sun • Diameter: 4,212 miles • Diameter: 7,918 miles (53% of Earth) • Orbit: 365.25 days • Mass: 10.7% of Earth • Solid surface • Orbit: 687 days • Thin atmosphere • Solid surface • Thin atmosphere • 1 big moon • 2 little moons Basic Facts about Earth and Solar System • Sun and planets formed at same time The Nebular Hypothesis Immanuel Pierre Kant Laplace 1755 1796 sun (center) and planets (in disk) form at same time out of rotating cloud that collapses under the force of gravity An ALMA image of the star HD 163296 and its protoplanetary disk as seen in dust. New observations suggested that two planets, each about the size of Saturn, are in orbit around the star. These planets, which are not yet fully formed, revealed themselves in the dual imprint they left in both the dust and the gas portions of the star's protoplanetary disk. Credit: ALMA (ESO/NAOJ/NRAO), Andrea Isella, B.