NASA's Space Launch System
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Vulcan Centaur
VULCAN CENTAUR The Vulcan Centaur rocket design leverages the flight-proven success of the Delta IV and Atlas V launch vehicles while introducing new technologies and innovative features to ensure a reliable and aordable space launch service. Vulcan Centaur will service a diverse range of markets including 225 ft commercial, civil, science, cargo and national security space customers. 1 The spacecraft is encapsulated in a 5.4-m- (17.7-ft-) diameter payload fairing (PLF), a sandwich composite structure made with a vented aluminum-honeycomb core and graphite-epoxy face sheets. The bisector (two-piece shell) PLF encapsulates the spacecraft. The payload attach fitting (PAF) is a similar sandwich composite structure creating the mating interface from spacecraft to second stage. The PLF separates using a debris-free horizontal and vertical separation system with 2 200 ft spring packs and frangible joint assembly. The payload fairing is available in the 15.5-m (51-ft) standard and 21.3-m (70-ft) 1 long configurations. The Centaur upper stage is 5.4 m (17.7 ft) in diameter and 3 11.7 m (38.5 ft) long with a 120,000-lb propellant capacity. Its propellant tanks are constructed of pressure-stabilized, corrosion-resistant stainless steel. Centaur is a liquid hydrogen/liquid oxygen-fueled vehicle, with two RL10C 4 engines. The Vulcan Centaur Heavy vehicle, flies the upgraded 2 Centaur using RL10CX engines with nozzle extensions. The 5 175 ft cryogenic tanks are insulated with spray-on foam insulation (SOFI) to manage boil o of cryogens during flight. An aft equipment shelf provides the structural mountings for vehicle electronics. -
Mission to Jupiter
This book attempts to convey the creativity, Project A History of the Galileo Jupiter: To Mission The Galileo mission to Jupiter explored leadership, and vision that were necessary for the an exciting new frontier, had a major impact mission’s success. It is a book about dedicated people on planetary science, and provided invaluable and their scientific and engineering achievements. lessons for the design of spacecraft. This The Galileo mission faced many significant problems. mission amassed so many scientific firsts and Some of the most brilliant accomplishments and key discoveries that it can truly be called one of “work-arounds” of the Galileo staff occurred the most impressive feats of exploration of the precisely when these challenges arose. Throughout 20th century. In the words of John Casani, the the mission, engineers and scientists found ways to original project manager of the mission, “Galileo keep the spacecraft operational from a distance of was a way of demonstrating . just what U.S. nearly half a billion miles, enabling one of the most technology was capable of doing.” An engineer impressive voyages of scientific discovery. on the Galileo team expressed more personal * * * * * sentiments when she said, “I had never been a Michael Meltzer is an environmental part of something with such great scope . To scientist who has been writing about science know that the whole world was watching and and technology for nearly 30 years. His books hoping with us that this would work. We were and articles have investigated topics that include doing something for all mankind.” designing solar houses, preventing pollution in When Galileo lifted off from Kennedy electroplating shops, catching salmon with sonar and Space Center on 18 October 1989, it began an radar, and developing a sensor for examining Space interplanetary voyage that took it to Venus, to Michael Meltzer Michael Shuttle engines. -
Preparation of Papers for AIAA Journals
ASCEND 10.2514/6.2020-4000 November 16-18, 2020, Virtual Event ASCEND 2020 Cryogenic Fluid Management Technologies Enabling for the Artemis Program and Beyond Hans C. Hansen* and Wesley L. Johnson† NASA Glenn Research Center, Cleveland, Ohio, 44135, USA Michael L. Meyer‡ NASA Engineering Safety Center, Cleveland, Ohio, 44135, USA Arthur H. Werkheiser§ and Jonathan R. Stephens¶ NASA Marshall Space Flight Center, Huntsville, Alabama, 35808, USA NASA is endeavoring on an ambitious return to the Moon and eventually on to Mars through the Artemis Program leveraging innovative technologies to establish sustainable exploration architectures collaborating with US commercial and international partners [1]. Future NASA architectures have baselined cryogenic propulsion systems to support lunar missions and ultimately future missions to Mars. NASA has been investing in maturing CFM active and passive storage, transfer, and gauging technologies over the last decade plus primarily focused on ground development with a few small- scale microgravity fluid experiments. Recently, NASA created a Cryogenic Fluid Management (CFM) Technology Roadmap identifying the critical gaps requiring further development to reach a technology readiness level (TRL) of 6 prior to infusion to flight applications. To address the technology gaps the Space Technology Mission Directorate (STMD) strategically plans to invest in a diversified CFM portfolio approach through ground and flight demonstrations, collaborating with international partners, and leveraging Public Private Partnerships (PPPs) opportunities with US industry through Downloaded by Michele Dominiak on December 23, 2020 | http://arc.aiaa.org DOI: 10.2514/6.2020-4000 the Tipping Point and Announcement of Collaborative Opportunities (ACO) solicitations. Once proven, these system capabilities will enable the high performing cryogenic propellant systems needed for the Artemis Program and beyond. -
JUICE Red Book
ESA/SRE(2014)1 September 2014 JUICE JUpiter ICy moons Explorer Exploring the emergence of habitable worlds around gas giants Definition Study Report European Space Agency 1 This page left intentionally blank 2 Mission Description Jupiter Icy Moons Explorer Key science goals The emergence of habitable worlds around gas giants Characterise Ganymede, Europa and Callisto as planetary objects and potential habitats Explore the Jupiter system as an archetype for gas giants Payload Ten instruments Laser Altimeter Radio Science Experiment Ice Penetrating Radar Visible-Infrared Hyperspectral Imaging Spectrometer Ultraviolet Imaging Spectrograph Imaging System Magnetometer Particle Package Submillimetre Wave Instrument Radio and Plasma Wave Instrument Overall mission profile 06/2022 - Launch by Ariane-5 ECA + EVEE Cruise 01/2030 - Jupiter orbit insertion Jupiter tour Transfer to Callisto (11 months) Europa phase: 2 Europa and 3 Callisto flybys (1 month) Jupiter High Latitude Phase: 9 Callisto flybys (9 months) Transfer to Ganymede (11 months) 09/2032 – Ganymede orbit insertion Ganymede tour Elliptical and high altitude circular phases (5 months) Low altitude (500 km) circular orbit (4 months) 06/2033 – End of nominal mission Spacecraft 3-axis stabilised Power: solar panels: ~900 W HGA: ~3 m, body fixed X and Ka bands Downlink ≥ 1.4 Gbit/day High Δv capability (2700 m/s) Radiation tolerance: 50 krad at equipment level Dry mass: ~1800 kg Ground TM stations ESTRAC network Key mission drivers Radiation tolerance and technology Power budget and solar arrays challenges Mass budget Responsibilities ESA: manufacturing, launch, operations of the spacecraft and data archiving PI Teams: science payload provision, operations, and data analysis 3 Foreword The JUICE (JUpiter ICy moon Explorer) mission, selected by ESA in May 2012 to be the first large mission within the Cosmic Vision Program 2015–2025, will provide the most comprehensive exploration to date of the Jovian system in all its complexity, with particular emphasis on Ganymede as a planetary body and potential habitat. -
Space Launch System (Sls) Motors
Propulsion Products Catalog SPACE LAUNCH SYSTEM (SLS) MOTORS For NASA’s Space Launch System (SLS), Northrop Grumman manufactures the five-segment SLS heavy- lift boosters, the booster separation motors (BSM), and the Launch Abort System’s (LAS) launch abort motor and attitude control motor. The SLS five-segment booster is the largest solid rocket motor ever built for flight. The SLS booster shares some design heritage with flight-proven four-segment space shuttle reusable solid rocket motors (RSRM), but generates 20 percent greater average thrust and 24 percent greater total impulse. While space shuttle RSRM production has ended, sustained booster production for SLS helps provide cost savings and access to reliable material sources. Designed to push the spent RSRMs safely away from the space shuttle, Northrop Grumman BSMs were rigorously qualified for human space flight and successfully used on the last fifteen space shuttle missions. These same motors are a critical part of NASA’s SLS. Four BSMs are installed in the forward frustum of each five-segment booster and four are installed in the aft skirt, for a total of 16 BSMs per launch. The launch abort motor is an integral part of NASA’s LAS. The LAS is designed to safely pull the Orion crew module away from the SLS launch vehicle in the event of an emergency on the launch pad or during ascent. Northrop Grumman is on contract to Lockheed Martin to build the abort motor and attitude control motor—Lockheed is the prime contractor for building the Orion Multi-Purpose Crew Vehicle designed for use on NASA’s SLS. -
Rocket Nozzles: 75 Years of Research and Development
Sådhanå Ó (2021) 46:76 Indian Academy of Sciences https://doi.org/10.1007/s12046-021-01584-6Sadhana(0123456789().,-volV)FT3](0123456789().,-volV) Rocket nozzles: 75 years of research and development SHIVANG KHARE1 and UJJWAL K SAHA2,* 1 Department of Energy and Process Engineering, Norwegian University of Science and Technology, 7491 Trondheim, Norway 2 Department of Mechanical Engineering, Indian Institute of Technology Guwahati, Guwahati 781039, India e-mail: [email protected]; [email protected] MS received 28 August 2020; revised 20 December 2020; accepted 28 January 2021 Abstract. The nozzle forms a large segment of the rocket engine structure, and as a whole, the performance of a rocket largely depends upon its aerodynamic design. The principal parameters in this context are the shape of the nozzle contour and the nozzle area expansion ratio. A careful shaping of the nozzle contour can lead to a high gain in its performance. As a consequence of intensive research, the design and the shape of rocket nozzles have undergone a series of development over the last several decades. The notable among them are conical, bell, plug, expansion-deflection and dual bell nozzles, besides the recently developed multi nozzle grid. However, to the best of authors’ knowledge, no article has reviewed the entire group of nozzles in a systematic and comprehensive manner. This paper aims to review and bring all such development in one single frame. The article mainly focuses on the aerodynamic aspects of all the rocket nozzles developed till date and summarizes the major findings covering their design, development, utilization, benefits and limitations. -
The SKYLON Spaceplane
The SKYLON Spaceplane Borg K.⇤ and Matula E.⇤ University of Colorado, Boulder, CO, 80309, USA This report outlines the major technical aspects of the SKYLON spaceplane as a final project for the ASEN 5053 class. The SKYLON spaceplane is designed as a single stage to orbit vehicle capable of lifting 15 mT to LEO from a 5.5 km runway and returning to land at the same location. It is powered by a unique engine design that combines an air- breathing and rocket mode into a single engine. This is achieved through the use of a novel lightweight heat exchanger that has been demonstrated on a reduced scale. The program has received funding from the UK government and ESA to build a full scale prototype of the engine as it’s next step. The project is technically feasible but will need to overcome some manufacturing issues and high start-up costs. This report is not intended for publication or commercial use. Nomenclature SSTO Single Stage To Orbit REL Reaction Engines Ltd UK United Kingdom LEO Low Earth Orbit SABRE Synergetic Air-Breathing Rocket Engine SOMA SKYLON Orbital Maneuvering Assembly HOTOL Horizontal Take-O↵and Landing NASP National Aerospace Program GT OW Gross Take-O↵Weight MECO Main Engine Cut-O↵ LACE Liquid Air Cooled Engine RCS Reaction Control System MLI Multi-Layer Insulation mT Tonne I. Introduction The SKYLON spaceplane is a single stage to orbit concept vehicle being developed by Reaction Engines Ltd in the United Kingdom. It is designed to take o↵and land on a runway delivering 15 mT of payload into LEO, in the current D-1 configuration. -
Paper Session IA-Shuttle-C Heavy-Lift Vehicle of the 90'S
The Space Congress® Proceedings 1989 (26th) Space - The New Generation Apr 25th, 2:00 PM Paper Session I-A - Shuttle-C Heavy-Lift Vehicle of the 90's Robert G. Eudy Manager, Shuttle-C Task Team, Marshall Space Flight Center Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Eudy, Robert G., "Paper Session I-A - Shuttle-C Heavy-Lift Vehicle of the 90's" (1989). The Space Congress® Proceedings. 5. https://commons.erau.edu/space-congress-proceedings/proceedings-1989-26th/april-25-1989/5 This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. SHUTTLE-C HEAVY-LIFT VEHICLE OF THE 90 ' S Mr. Robert G. Eudy, Manager Shuttle-C Task Team Marshall Space Flight Center ABSTRACT United States current and planned space activities identify the need for increased payload capacity and unmanned flight to complement the existing Shuttle. To meet this challenge the National Aeronautics and Space Administration is defining an unmanned cargo version of the Shuttle that can give the nation early heavy-lift capability. Called Shuttle-C, this unmanned vehicle is a natural, low-cost evolution of the current Space Shuttle that can be flying 100,000 to 170,000 pound payloads by late 1994. At the core of Shuttle-C design philosophy is the principle of evolvement from the United State's Space Transportation System. -
Out There Somewhere Could Be a PLANET LIKE OURS the Breakthroughs We’Ll Need to find Earth 2.0 Page 30
September 2014 Out there somewhere could be A PLANET LIKE OURS The breakthroughs we’ll need to find Earth 2.0 Page 30 Faster comms with lasers/16 Real fallout from Ukraine crisis/36 NASA Glenn chief talks tech/18 A PUBLICATION OF THE AMERICAN INSTITUTE OF AERONAUTICS AND ASTRONAUTICS Engineering the future Advanced Composites Research The Wizarding World of Harry Potter TM Bloodhound Supersonic Car Whether it’s the world’s fastest car With over 17,500 staff worldwide, and 2,800 in or the next generation of composite North America, we have the breadth and depth of capability to respond to the world’s most materials, Atkins is at the forefront of challenging engineering projects. engineering innovation. www.na.atkinsglobal.com September 2014 Page 30 DEPARTMENTS EDITOR’S NOTEBOOK 2 New strategy, new era LETTER TO THE EDITOR 3 Skeptical about the SABRE engine INTERNATIONAL BEAT 4 Now trending: passive radars IN BRIEF 8 A question mark in doomsday comms Page 12 THE VIEW FROM HERE 12 Surviving a bad day ENGINEERING NOTEBOOK 16 Demonstrating laser comms CONVERSATION 18 Optimist-in-chief TECH HISTORY 22 Reflecting on radars PROPULSION & ENERGY 2014 FORUM 26 Electric planes; additive manufacturing; best quotes Page 38 SPACE 2014 FORUM 28 Comet encounter; MILSATCOM; best quotes OUT OF THE PAST 44 CAREER OPPORTUNITIES 46 Page 16 FEATURES FINDING EARTH 2.0 30 Beaming home a photo of a planet like ours will require money, some luck and a giant telescope rich with technical advances. by Erik Schechter COLLATERAL DAMAGE 36 Page 22 The impact of the Russia-Ukrainian conflict extends beyond the here and now. -
Why NASA's Planet-Hunting Astrophysics Telescope Is an Easy Budget Target, and What Defeat Would Mean PAGE 24
Q & A 12 ASTRONAUT’S VIEW 20 SPACE LAUNCH 34 Neil deGrasse Tyson A realistic moon plan SLS versus commercial SPECIAL REPORT SPACE DARK ENERGY DILEMMA Why NASA’s planet-hunting astrophysics telescope is an easy budget target, and what defeat would mean PAGE 24 APRIL 2018 | A publication of the American Institute of Aeronautics andd Astronautics | aeroaerospaceamerica.aiaa.orgerospaceamerica.aiaa.org 9–11 JULY 2018 CINCINNATI, OH ANNOUNCING EXPANDED TECHNICAL CONTENT FOR 2018! You already know about our extensive technical paper presentations, but did you know that we are now offering an expanded educational program as part of the AIAA Propulsion and Energy Forum and Exposition? In addition to our pre-forum short courses and workshops, we’ve enhanced the technical panels and added focused technical tutorials, high level discussion groups, exciting keynotes and more. LEARN MORE AND REGISTER TODAY! For complete program details please visit: propulsionenergy.aiaa.org FEATURES | April 2018 MORE AT aerospaceamerica.aiaa.org 20 34 40 24 Returning to Launching the Laying down the What next the moon Europa Clipper rules for space Senior research scientist NASA, Congress and We asked experts in for WFIRST? and former astronaut the White House are space policy to comment Tom Jones writes about debating which rocket on proposed United NASA’s three upcoming space what it would take to should send the probe Nations guidelines deliver the funds and into orbit close to this for countries and telescopes are meant to piece together political support for the Jovian moon. companies sending some heady puzzles, but the White Lunar Orbital Outpost- satellites and other craft House’s 2019 budget proposal would Gateway. -
Materials for Liquid Propulsion Systems
https://ntrs.nasa.gov/search.jsp?R=20160008869 2019-08-29T17:47:59+00:00Z CHAPTER 12 Materials for Liquid Propulsion Systems John A. Halchak Consultant, Los Angeles, California James L. Cannon NASA Marshall Space Flight Center, Huntsville, Alabama Corey Brown Aerojet-Rocketdyne, West Palm Beach, Florida 12.1 Introduction Earth to orbit launch vehicles are propelled by rocket engines and motors, both liquid and solid. This chapter will discuss liquid engines. The heart of a launch vehicle is its engine. The remainder of the vehicle (with the notable exceptions of the payload and guidance system) is an aero structure to support the propellant tanks which provide the fuel and oxidizer to feed the engine or engines. The basic principle behind a rocket engine is straightforward. The engine is a means to convert potential thermochemical energy of one or more propellants into exhaust jet kinetic energy. Fuel and oxidizer are burned in a combustion chamber where they create hot gases under high pressure. These hot gases are allowed to expand through a nozzle. The molecules of hot gas are first constricted by the throat of the nozzle (de-Laval nozzle) which forces them to accelerate; then as the nozzle flares outwards, they expand and further accelerate. It is the mass of the combustion gases times their velocity, reacting against the walls of the combustion chamber and nozzle, which produce thrust according to Newton’s third law: for every action there is an equal and opposite reaction. [1] Solid rocket motors are cheaper to manufacture and offer good values for their cost. -
Triton: Topography and Geology of a Probable Ocean World with Comparison to Pluto and Charon
remote sensing Article Triton: Topography and Geology of a Probable Ocean World with Comparison to Pluto and Charon Paul M. Schenk 1,* , Chloe B. Beddingfield 2,3, Tanguy Bertrand 3, Carver Bierson 4 , Ross Beyer 2,3, Veronica J. Bray 5, Dale Cruikshank 3 , William M. Grundy 6, Candice Hansen 7, Jason Hofgartner 8 , Emily Martin 9, William B. McKinnon 10, Jeffrey M. Moore 3, Stuart Robbins 11 , Kirby D. Runyon 12 , Kelsi N. Singer 11 , John Spencer 11, S. Alan Stern 11 and Ted Stryk 13 1 Lunar and Planetary Institute, Houston, TX 77058, USA 2 SETI Institute, Palo Alto, CA 94020, USA; chloe.b.beddingfi[email protected] (C.B.B.); [email protected] (R.B.) 3 NASA Ames Research Center, Moffett Field, CA 94035, USA; [email protected] (T.B.); [email protected] (D.C.); [email protected] (J.M.M.) 4 School of Earth and Space Exploration, Arizona State University, Tempe, AZ 85202, USA; [email protected] 5 Lunar and Planetary Laboratory, University of Arizona, Tucson, AZ 85641, USA; [email protected] 6 Lowell Observatory, Flagstaff, AZ 86001, USA; [email protected] 7 Planetary Science Institute, Tucson, AZ 85704, USA; [email protected] 8 Jet Propulsion Laboratory, Pasadena, CA 91001, USA; [email protected] 9 National Air & Space Museum, Washington, DC 20001, USA; [email protected] 10 Department of Earth and Planetary Sciences, Washington University in Saint Louis, Saint Louis, MO 63101, USA; [email protected] 11 Southwest Research Institute, Boulder, CO 80301, USA; [email protected] (S.R.); [email protected] (K.N.S.); [email protected] (J.S.); [email protected] (S.A.S.) Citation: Schenk, P.M.; Beddingfield, 12 Johns Hopkins Applied Physics Laboratory, Laurel, MD 20707, USA; [email protected] 13 C.B.; Bertrand, T.; Bierson, C.; Beyer, Humanities Division, Roane State Community College, Harriman, TN 37748, USA; [email protected] R.; Bray, V.J.; Cruikshank, D.; Grundy, * Correspondence: [email protected] W.M.; Hansen, C.; Hofgartner, J.; et al.