2010 Stellar Awards EARLY CAREER
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Nasa Engineering & Safety Center
National Aeronautics and Space Administration NASA ENGINEERING & SAFETY CENTER 2008 TECHNICAL UPDATE www.nasa.gov 1 It gives me a lot of pleasure to recognize the 5th anniversary of the establishment of the NASA Engineering and Safety Center. It also offers, for me, a valuable reminder that it is important always to be open to new ideas and new approaches to solving problems. When the NESC was established, I was more than a bit pessimistic that it could work, that it could provide value for the Agency over and above that offered by our various center engineering directorates. I was wrong. The synergy that has been achieved by the NESC and its cross-agency approach to solving difficult technical problems has been truly impressive. It is, in my mind, a useful model for future endeavors and a great example that it is actually possible for us to “be NASA”, to rise above some of the parochial geographic concerns which have plagued NASA for five decades. These days, when someone tells me that the NESC is looking at a particular issue, I am reassured, because I know that if a solution can be found, this group will find it. – Dr. Michael D. Griffin, NASA Administrator 2 Table of Contents Stakeholder Messages ........................................................................................ 2 NESC Leadership ................................................................................................ 3 Overview: How the NESC Works .......................................................................... 4 NESC Academy: Learning from the Past ............................................................... 8 Technical Highlights Collecting Flight Force Measurements to Improve Coupled Loads Analysis ... 11 Analysis of Constellation Program Mass Properties ....................................... 11 Prediction and Reduction of Ares SRB Thrust Oscillation ............................... 12 Review of the Launch Abort System Motor Qualification Plan ....................... -
PCEC V2.3 (For Real This Time)
PCEC v2.3 (For Real This Time) 2021 NASA Cost & Schedule Symposium 14 Apr 2021 Brian Alford Mark Jacobs Booz Allen Hamilton TGS Consultants Shawn Hayes Richard Webb TGS Consultants KAR Enterprises NASA MSFC Victory MIPSSSolutions Team SB Diversity Outline • PCEC Overview • Robotic SC Updates • CASTS Updates • PCEC v2.3 Interface Updates • Closing Victory Solutions MIPSS Team 2 What is PCEC? • The Project Cost Estimating Capability (PCEC) is the primary NASA in-house developed parametric tool for estimating the cost of robotic missions, launch vehicles, crewed vehicles, etc. – Overarching tool for creating an estimate that spans the full NASA WBS – CERs included out-of-the-box for estimating the costs of a flight system (e.g., thermal) and support functions (e.g., project management) – Connects to other NASA-sponsored specialized tools to cover the complete NASA WBS (e.g., NICM, MOCET) – Excel-based (presented as add-in in the Ribbon) with completely visible calculations and code – Consists of the PCEC Interface (the Ribbon and supporting code) and the PCEC Library (the artifacts used to estimate cost) – Available to the General Public Victory Solutions MIPSS Team 3 What is PCEC? Cont’d • PCEC comprises two primary ‘models’, offered seamlessly to the user under a single, integrated tool – Robotic Spacecraft (Robotic SC) – Crewed and Space Transportation Systems (CASTS) • These models have separate data normalizations, collections of CERs, core WBSs, modeling approaches, estimating template worksheets, and scope – Estimating artifacts constitute -
Los Motores Aeroespaciales, A-Z
Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 < aeroteca.com > Depósito Legal B 9066-2016 Título: Los Motores Aeroespaciales A-Z. © Parte/Vers: 1/12 Página: 1 Autor: Ricardo Miguel Vidal Edición 2018-V12 = Rev. 01 Los Motores Aeroespaciales, A-Z (The Aerospace En- gines, A-Z) Versión 12 2018 por Ricardo Miguel Vidal * * * -MOTOR: Máquina que transforma en movimiento la energía que recibe. (sea química, eléctrica, vapor...) Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 Este facsímil es < aeroteca.com > Depósito Legal B 9066-2016 ORIGINAL si la Título: Los Motores Aeroespaciales A-Z. © página anterior tiene Parte/Vers: 1/12 Página: 2 el sello con tinta Autor: Ricardo Miguel Vidal VERDE Edición: 2018-V12 = Rev. 01 Presentación de la edición 2018-V12 (Incluye todas las anteriores versiones y sus Apéndices) La edición 2003 era una publicación en partes que se archiva en Binders por el propio lector (2,3,4 anillas, etc), anchos o estrechos y del color que desease durante el acopio parcial de la edición. Se entregaba por grupos de hojas impresas a una cara (edición 2003), a incluir en los Binders (archivadores). Cada hoja era sustituíble en el futuro si aparecía una nueva misma hoja ampliada o corregida. Este sistema de anillas admitia nuevas páginas con información adicional. Una hoja con adhesivos para portada y lomo identifi caba cada volumen provisional. Las tapas defi nitivas fueron metálicas, y se entregaraban con el 4 º volumen. O con la publicación completa desde el año 2005 en adelante. -Las Publicaciones -parcial y completa- están protegidas legalmente y mediante un sello de tinta especial color VERDE se identifi can los originales. -
THE MAX LAUNCH ABORT SYSTEM – CONCEPT, FLIGHT TEST, and EVOLUTION Michael G
THE MAX LAUNCH ABORT SYSTEM – CONCEPT, FLIGHT TEST, AND EVOLUTION Michael G. Gilbert(1), PhD (1) Principal Engineer, NASA Engineering and Safety Center 11 Langley Blvd., MS 116,Hampton VA 23681 USA Email:[email protected] Abstract escape system Maxime Faget [1]. The effort was intended to provide The NASA Engineering and Safety Center programmatic risk-reduction for the (NESC) is an independent engineering Constellation Program (CxP) Orion Crew analysis and test organization providing Exploration Vehicle (CEV) project. support across the range of NASA programs. In 2007 NASA was developing The CEV project baseline Launch Abort the launch escape system for the Orion System (LAS) development is an evolution spacecraft that was evolved from the of the Apollo towered-rocket design, Fig. traditional tower-configuration escape 2. Unlike the Apollo LAS, the CEV LAS systems used for the historic Mercury and incorporated an attitude control motor to Apollo spacecraft. The NESC was tasked, ensure stable flight following the escape as a programmatic risk-reduction effort to motor burn. At the time the MLAS project develop and flight test an alternative to the was initiated, the CEV LAS was Orion baseline escape system concept. experiencing development delays related This project became known as the Max to the LAS attitude control motor. Launch Abort System (MLAS), named in Therefore, the MLAS project was to honor of Maxime Faget, the developer of consider escape system concepts that the original Mercury escape system. Over would not require active attitude control or the course of approximately two years the stabilization following escape motor NESC performed conceptual and tradeoff burnout. -
Testing Strategies and Methodologies for the Max Launch Abort System Dawn M
Testing Strategies and Methodologies for the Max Launch Abort System Dawn M. Schaible Daniel E. Yuchnovicz NASA Engineering and Safety Center Hampton, Virginia ABSTRACT The National Aeronautics and Space Administration (NASA) Engineering and Safety Center (NESC) was tasked to develop an alternate, tower-less launch abort system (LAS) as risk mitigation for the Orion Project. The successful pad abort flight demonstration test in July 2009 of the “Max” launch abort system (MLAS) provided data critical to the design of future LASs, while demonstrating the Agency’s ability to rapidly design, build and fly full-scale hardware at minimal cost in a “virtual” work environment. Limited funding and an aggressive schedule presented a challenge for testing of the complex MLAS system. The successful pad abort flight demonstration test was attributed to the project’s systems engineering and integration process, which included: a concise definition of, and an adherence to, flight test objectives; a solid operational concept; well defined performance requirements, and a test program tailored to reducing the highest flight test risks. The testing ranged from wind tunnel validation of computational fluid dynamic simulations to component ground tests of the highest risk subsystems. This paper provides an overview of the testing/risk management approach and methodologies used to understand and reduce the areas of highest risk — resulting in a successful flight demonstration test. KEY WORDS: Testing, risk management, flight test, launch abort systems MLAS PROJECT OVERVIEW NASA’s next generation crewed spacecraft, named Orion, is a part of the overall Constellation Program. The baseline Orion design includes a launch abort system (LAS) with tower, derived from the Apollo design. -
Deep Space Chronicle Deep Space Chronicle: a Chronology of Deep Space and Planetary Probes, 1958–2000 | Asifa
dsc_cover (Converted)-1 8/6/02 10:33 AM Page 1 Deep Space Chronicle Deep Space Chronicle: A Chronology ofDeep Space and Planetary Probes, 1958–2000 |Asif A.Siddiqi National Aeronautics and Space Administration NASA SP-2002-4524 A Chronology of Deep Space and Planetary Probes 1958–2000 Asif A. Siddiqi NASA SP-2002-4524 Monographs in Aerospace History Number 24 dsc_cover (Converted)-1 8/6/02 10:33 AM Page 2 Cover photo: A montage of planetary images taken by Mariner 10, the Mars Global Surveyor Orbiter, Voyager 1, and Voyager 2, all managed by the Jet Propulsion Laboratory in Pasadena, California. Included (from top to bottom) are images of Mercury, Venus, Earth (and Moon), Mars, Jupiter, Saturn, Uranus, and Neptune. The inner planets (Mercury, Venus, Earth and its Moon, and Mars) and the outer planets (Jupiter, Saturn, Uranus, and Neptune) are roughly to scale to each other. NASA SP-2002-4524 Deep Space Chronicle A Chronology of Deep Space and Planetary Probes 1958–2000 ASIF A. SIDDIQI Monographs in Aerospace History Number 24 June 2002 National Aeronautics and Space Administration Office of External Relations NASA History Office Washington, DC 20546-0001 Library of Congress Cataloging-in-Publication Data Siddiqi, Asif A., 1966 Deep space chronicle: a chronology of deep space and planetary probes, 1958-2000 / by Asif A. Siddiqi. p.cm. – (Monographs in aerospace history; no. 24) (NASA SP; 2002-4524) Includes bibliographical references and index. 1. Space flight—History—20th century. I. Title. II. Series. III. NASA SP; 4524 TL 790.S53 2002 629.4’1’0904—dc21 2001044012 Table of Contents Foreword by Roger D. -
Inside Wallops National Aeronautics and Space Administration Goddard Space Flight Center Wallops Flight Facility, Wallops Island, Va
Inside Wallops National Aeronautics and Space Administration Goddard Space Flight Center Wallops Flight Facility, Wallops Island, Va. Volume XX-08 Number 10 March 24, 2008 Max Launch Abort System Development Early last year, the Wallops Flight Facility enough and with enough distance Representatives from the Sounding embarked on a challenging effort to downrange to permit the CM to execute a Rockets Program Office and NASA support NASA Engineering and Safety nominal landing. Sounding Rocket Operations Contract, Center (NESC) with the development of (NSROC), have provided technical a composite crew module for the In addition to a wealth of solid rocket motor support associated with the solid rocket Exploration Orion spacecraft. knowledge and experience at Wallops, the motor systems. NSROC will play a major NESC found an engineering staff well- role in vehicle hardware and mechanical The NESC will design, develop, and test suited to rapid-response system GSE fabrication. an alternate concept launch abort system development. Personnel from many (LAS) for the Orion crew module (CM) Wallops organizations have joined the Team members from the Facilities as a risk mitigation for the Orion Project’s MLAS team. LAS development. Management Branch are responsible for procurement and construction of a custom Having an effective means for the crew The Wallops’ Guidance, Navigation & launch pad shelter and for infrastructure to escape in an emergency during launch Control and Mission Systems Engineering improvements related to transportation of is critical in establishing launch system Branch, have supported design and flight the MLAS demonstrator from the Wallops reliability and crew safety for the dynamics analysis. -
Desind Finding
NATIONAL AIR AND SPACE ARCHIVES Herbert Stephen Desind Collection Accession No. 1997-0014 NASM 9A00657 National Air and Space Museum Smithsonian Institution Washington, DC Brian D. Nicklas © Smithsonian Institution, 2003 NASM Archives Desind Collection 1997-0014 Herbert Stephen Desind Collection 109 Cubic Feet, 305 Boxes Biographical Note Herbert Stephen Desind was a Washington, DC area native born on January 15, 1945, raised in Silver Spring, Maryland and educated at the University of Maryland. He obtained his BA degree in Communications at Maryland in 1967, and began working in the local public schools as a science teacher. At the time of his death, in October 1992, he was a high school teacher and a freelance writer/lecturer on spaceflight. Desind also was an avid model rocketeer, specializing in using the Estes Cineroc, a model rocket with an 8mm movie camera mounted in the nose. To many members of the National Association of Rocketry (NAR), he was known as “Mr. Cineroc.” His extensive requests worldwide for information and photographs of rocketry programs even led to a visit from FBI agents who asked him about the nature of his activities. Mr. Desind used the collection to support his writings in NAR publications, and his building scale model rockets for NAR competitions. Desind also used the material in the classroom, and in promoting model rocket clubs to foster an interest in spaceflight among his students. Desind entered the NASA Teacher in Space program in 1985, but it is not clear how far along his submission rose in the selection process. He was not a semi-finalist, although he had a strong application. -
Changing the Shape of Launch Abort Systems
featured knowledge Changing the Shape of Launch Abort Systems n December 2014, NASA’s Orion Starting in December 2006, IMulti-Purpose Crew Vehicle they performed aerodynamic, (MPCV) Program successfully structural and controls analyses, conducted Experimental Flight as well as a number of wind tunnel Test-1 (EFT-1), the first orbital flight experiments, to obtain the data test of the Orion spacecraft. Close required to validate the concept. observers may have noted that the “We found that adding a fairing spacecraft had an updated shape improved the aerodynamic shape from the concepts included on the significantly,” said Schuster. “It previous Ares I-X and Orion Pad reduced drag during ascent, as well Abort 1 flight tests. In reality, the as weight by providing a separate Orion crew module (CM) shape has load path around the crew module.” not changed substantially since In addition to better quantifying these flights, but the Orion Launch the aerodynamic, performance, Abort System (LAS) has changed. and structural improvements, Reducing structural loads a major new focus investigated using the ALAS MBPC to reduce In September 2006, during a peer aeroacoustic loads on the Orion review of the NESC Composite CM. “Current predictions of Orion Crew Module (CCM) Assessment, acoustic loads far exceeded what an Alternate Launch Abort System was assumed in the design of the (ALAS) was conceived to reduce Orion subsystems,” said Scotti. structural loads carried by the “And the project hoped that the CCM during a flight abort. To ALAS approach would help solve further investigate the feasibility that problem and eliminate the of the ALAS concept, Dr. -
Toward a History of the Space Shuttle an Annotated Bibliography
Toward a History of the Space Shuttle An Annotated Bibliography Part 2, 1992–2011 Monographs in Aerospace History, Number 49 TOWARD A HISTORY OF THE SPACE SHUTTLE AN ANNOTATED BIBLIOGRAPHY, PART 2 (1992–2011) Compiled by Malinda K. Goodrich Alice R. Buchalter Patrick M. Miller of the Federal Research Division, Library of Congress NASA History Program Office Office of Communications NASA Headquarters Washington, DC Monographs in Aerospace History Number 49 August 2012 NASA SP-2012-4549 Library of Congress – Federal Research Division Space Shuttle Annotated Bibliography PREFACE This annotated bibliography is a continuation of Toward a History of the Space Shuttle: An Annotated Bibliography, compiled by Roger D. Launius and Aaron K. Gillette, and published by NASA as Monographs in Aerospace History, Number 1 in December 1992 (available online at http://history.nasa.gov/Shuttlebib/contents.html). The Launius/Gillette volume contains those works published between the early days of the United States’ manned spaceflight program in the 1970s through 1991. The articles included in the first volume were judged to be most essential for researchers writing on the Space Shuttle’s history. The current (second) volume is intended as a follow-on to the first volume. It includes key articles, books, hearings, and U.S. government publications published on the Shuttle between 1992 and the end of the Shuttle program in 2011. The material is arranged according to theme, including: general works, precursors to the Shuttle, the decision to build the Space Shuttle, its design and development, operations, and management of the Space Shuttle program. Other topics covered include: the Challenger and Columbia accidents, as well as the use of the Space Shuttle in building and servicing the Hubble Space Telescope and the International Space Station; science on the Space Shuttle; commercial and military uses of the Space Shuttle; and the Space Shuttle’s role in international relations, including its use in connection with the Soviet Mir space station. -
Acquisition Story 54 Introduction 2 Who We Were 4 194Os 8 195Os 12
table of contents Introduction 2 Who We Were 4 194Os 8 195Os 12 196Os 18 197Os 26 198Os 30 199Os 34 2OOOs 38 2O1Os 42 Historical Timeline 46 Acquisition Story 54 Who We Are Now 58 Where We Are Going 64 Vision For The Future 68 1 For nearly a century, innovation and reliability have been the hallmarks of two giant U.S. aerospace icons – Aerojet and Rocketdyne. The companies’ propulsion systems have helped to strengthen national defense, launch astronauts into space, and propel unmanned spacecraft to explore the universe. ➢ Aerojet’s diverse rocket propulsion systems have powered military vehicles for decades – from rocket-assisted takeoff for propeller airplanes during World War II – through today’s powerful intercontinental ballistic missiles (ICBMs). The systems helped land men on the moon, and maneuvered spacecraft beyond our solar system. ➢ For years, Rocketdyne engines have played a major role in national defense, beginning with powering the United States’ first ICBM to sending modern military communication satellites into orbit. Rocketdyne’s technology also helped launch manned moon missions, propelled space shuttles, and provided the main power system for the International Space Station (ISS). ➢ In 2013, these two rocket propulsion manufacturers became Aerojet Rocketydne, blending expertise and vision to increase efficiency, lower costs, and better compete in the market. Now, as an industry titan, Aerojet Rocketdyne’s talented, passionate employees collaborate to create even greater innovations that protect America and launch its celestial future. 2011 A Standard Missile-3 (SM-3) interceptor is being developed as part of the U.S. Missile Defense Agency’s sea-based Aegis Ballistic Missile Defense System. -
Launch Abort System Evolution
featured knowledge Launch Abort System Evolution critical component of crewed spacecraft, the launch Aabort system (LAS), allows for rescue of the crew in the event of a catastrophic malfunction while the spacecraft is sitting on the launch pad or on its way into orbit. For a successful rescue, however, the LAS must perform several critical maneuvers in rapid-fire succession. First, the launch abort motors must be powerful enough to fly the fairing and crew module (CM) to a safe distance away from the launch vehicle. Next, it must reorient and fly in a carefully controlled heat shield-forward attitude. Finally, it must release the CM, enabling the CM’s parachute landing system to deploy for a safe return of the crew. LAS begins with Project Mercury Since the time of Project Mercury and the Apollo Program, the LAS has maintained its traditional tower configuration. But as spacecraft design has evolved, so has the need for a new LAS. The Orion Multi-Purpose Propulsively stabilized MLAS concept. Crew Vehicle launched on December 4, 2014, featured a new Alternative Launch Abort System (ALAS) shape and structure that enhanced the aerodynamic and aeroacoustic performance of the spacecraft. But while the NESC was spearheading efforts on the ALAS design, it was also developing the Max Launch Abort System (MLAS), a follow-on to the ALAS design that incorporated the ALAS shape while fundamentally changing the LAS from a tower to a towerless design. Named in honor of Maxime Faget, developer of the original Mercury launch escape system, MLAS was a 2-year effort Left: Successful launch abort test of the passively stabilized that culminated in a full-scale flight demonstration.