Design Review Improvements Product Overview

DTIC Science & Technology

2015-05-07

Boeing Anne Ramsey, Harris Corporation Ronald H. Mandel, Lockheed Martin Mark King, Micropac Industries Melanie Berg, NASA Cindy Kohlmiller...Northrop Grumman craig.wesser@ngc.com Richard Fink NRO finkrich@nro.mil Marvin LeBlanc NOAA Marvin.LeBlanc@noaa.gov Robert Adkisson Boeing...Dennis.Boiter@intelsatgeneral.com Silva Bouchard Northrop Grumman Silvia.Bouchard@ngc.com Mark Braun Raytheon mark.j.braun@raytheon.com Marvin Candee

A case study in pollution prevention at the Northrop Grumman B-2 division

DOE Office of Scientific and Technical Information (OSTI.GOV)

Haltmeyer, T.

1995-12-31

In 1990, Northrop Grumman Corporation outlined a pollution prevention program to be jointly chartered by all operating elements. This concept was expanded by the B-2 Division, to become a comprehensive industrial multimedia program known as Zero 2000. The Zero 2000 program mandates the elimination of releases of hazardous materials to air, land and water by 2000. Northrop Grumman B-2 Division has effectively identified and defined environmental needs associated with the operations and is meeting or exceeding pollution prevention goals to affect measurable improvements to the quality of air, land and water. Through the Zero 2000 program, they have achieved amore » reduction of over 85% in hazardous waste generated and a reduction of ozone-depleting chemical emissions by 90%. In addition, they have reduced mobile air pollution by approximately 280 tons per year; reduced water usage by an average of 34%; and, have reduced solid waste disposal by 55%. Their environmental needs were defined through a grass roots assessment by environmental staff members and other professionals. This evaluation emerged from a basic Northrop Grumman philosophy to find innovative solutions to technological problems.« less

Northrop Grumman HEC flight coaxial cryocoolers performance

NASA Astrophysics Data System (ADS)

Nguyen, T.; Russo, J.; Basel, G.; Chi, D.; Abelson, L.

2018-05-01

The Northrop Grumman Aerospace Systems (NGAS) has expanded the cryocooler product line to include a single stage High Efficiency Cryocooler (HEC) cooler with a coaxial pulse tube cold head that operates at temperatures down to 45K. The HEC coaxial pulse tube cooler has been adopted by several customers, and has completed acceptance testing to meet program flight requirements. The NGAS TRL 9 HEC is a pulse tube cryocooler with a flexure bearing compressor which has been delivered for a number of flight payloads that are currently operating in space. To date, NGAS has delivered space cryocoolers in several configurations including single stage with a linear cold head and two stage with both linear and coaxial cold heads. The new HEC coaxial cooler uses the same TRL9 HEC compressor with a passive pulse tube cold head, to maintain the flight heritage of the HEC linear cooler. In this paper, we present the flight acceptance test data of the HEC coaxial cryocooler, which includes thermal performance, launch vibration and thermal cycling. The HEC coaxial cooler has demonstrated excellent performance in family with the flight qualified HEC linear cooler. The HEC coaxial cooler provides users with additional flexibility in selecting the cold head configuration to meet their particular applications.

Northrop Grumman Corporation's modified U.S. Navy F-5E Shaped Sonic Boom Demonstration (SSBD) aircraft flies over Lake Isabella, Calif., on Aug. 4, 2003

NASA Image and Video Library

2003-08-04

Northrop Grumman Corporation's modified U.S. Navy F-5E Shaped Sonic Boom Demonstration (SSBD) aircraft flies over Lake Isabella, California on Aug. 4, 2003. NASA Dryden provided range, air and ground data-gathering support for the SSBD project, which is part of DARPA's Quiet Supersonic Platform (QSP) program.

Why and Whither Hypersonics Research in the US Air Force

DTIC Science & Technology

2000-12-01

of strong interest in high supersonic and hypersonic flight. Actual flight achievements—notably the first supersonic flight by the XS - 1 on 14...Air Force is sponsoring Future Strike Aircraft studies with Boeing, Lockheed Martin, and Northrop Grumman . Under these studies, subsonic, supersonic...SMC/XRD) MSE Technology Applications, Inc. Northrop Grumman Air Combat Systems Orbital Sciences Corporation Boeing Phantom Works 18 May 2000

Leadership Behaviors of Management for Complex Adaptive Systems

DTIC Science & Technology

2010-04-01

arson • The Five Dysfunctions of a Team - Patrick M. Lencioni Agile Development Practices • Agile Project Management with Scrum – Ken Schwaber...and down to the individual and team level – Relationships are not defined hierarchically, but rather through interactions across References: Mike...n – Consisting of parts intricately combined © Copyright 2009 Northrop GrummanCopyright 2010 Northrop Grumman 5 Predictable or Adaptive Software/IT

Northrop Grumman Corporation's modified U.S. Navy F-5E Shaped Sonic Boom Demonstration (SSBD) aircraft flies over the company's Palmdale, Calif. facilities on Aug. 2, 2003

NASA Image and Video Library

2003-08-02

Northrop Grumman Corporation's modified U.S. Navy F-5E Shaped Sonic Boom Demonstration (SSBD) aircraft flies over the company's Palmdale, California facilities on Aug. 2, 2003. NASA Dryden provided range, air and ground data-gathering support for the SSBD project, which is part of DARPA's Quiet Supersonic Platform (QSP) program.

Alternatives for Modernizing U.S. Fighter Forces

DTIC Science & Technology

2009-05-01

Plans for Modernizing Fighter Forces xS -2. The Possible Role of the F-22 Program in Mitigating the Air Force’s Projected Inventory Shortfall xvi1- 1 ... Northrop Grumman won that competition with its proposal for an aircraft based on the RQ-4 Global Hawk. 38 ALTERNATIVES FOR MODERNIZING U.S. FIGHTER...flyable demonstrator for exploring technologies that could lead to an operational UCAV-N, was rolled out by Northrop Grumman in December 2008. Its

The Global Hawk Unmanned Aerial Vehicle Acquisition Process: A Summary of Phase I Experience,

DTIC Science & Technology

1997-01-01

8217 ]p ßSTEIM ■ nvrmim ü f ATX » LJ^P^ iiaiiiiiiaJ Mm MM» .. VHP The research described in this report was sponsored by the Defense Advanced...Flight Sciences, Northrop Grumman, Boeing, Raytheon, Westinghouse, Scaled Composites , Teledyne Ryan Aeronautical, and E-Systems, without whose...Corporation, Westinghouse, Northrop Grumman, Scaled Composites , Raytheon, Boeing, Teledyne Ryan, E-Systems, and Aurora Flight Sciences. It should be noted

Starlight suppression from the starshade testbed at NGAS

NASA Astrophysics Data System (ADS)

Samuele, Rocco; Glassman, Tiffany; Johnson, Adam M. J.; Varshneya, Rupal; Shipley, Ann

2009-08-01

We report on progress at the Northrop Grumman Aerospace Systems (NGAS) starshade testbed. The starshade testbed is a 42.8 m, vacuum chamber designed to replicate the Fresnel number of an equivalent full-scale starshade mission, namely the flagship New Worlds Observer (NWO) configuration. Subscale starshades manufactured by the NGAS foundry have shown 10-7 starlight suppression at an equivalent full-mission inner working angle of 85 milliarseconds. In this paper, we present an overview of the experimental set up, scaling relationships to an equivalent full-scale mission, and preliminary results from the testbed. We also discuss potential limitations of the current generation of starshades and improvements for the future.

Webb Telescope Passes Important Optical Test on This Week @NASA – May 5, 2017

NASA Image and Video Library

2017-05-05

NASA’s James Webb Space Telescope (JWST) has successfully passed the center of curvature test at Goddard Space Flight Center, in Greenbelt, Md. This important optical measurement of Webb’s fully assembled primary mirror was the final test held at Goddard before the telescope is shipped off for end-to-end cryogenic testing at Johnson Space Center in Houston. When that’s complete, the world’s most advanced observatory goes to Northrop Grumman Aerospace Systems in Redondo Beach, California, for final assembly and testing. Webb is targeted for launch in 2018 on a mission to help unravel some of the greatest mysteries of the universe. Also, Cassini Update, NASA Visits Midwest Company Helping Build Orion, Orion’s Launch Abort System Motor Tested, Wind Tunnel Tests Continue with SLS, and Community College Aerospace Scholars!

The Mechanical Property Data Base from an Air Force/Industry Cooperative Test Program on Advanced Aluminum Alloys

DTIC Science & Technology

1993-12-01

Longitudinal) E3 Fatigue Crack Growth Rate Data for Alcan 8090-T8 160 1 " x 4" Extrusion ( L-T Orientation). Grumman E4 Fatigue Crack Growth Rate...Data for Alcan 8090-T8 161 1 " x 4" Extrusion (T-L Orientation). Grumman E5 Fatigue Crack Growth Rate Data for Alcan 8090-T651 162 1 "x 4" Extrusion (L-T...Orientation). Northrop E6 Fatigue Crack Growth Rate for Alcan 8090-T651 163 1 " x 4" Extrusion (T-L Orientation). Northrop E7 Fatigue Crack Growth Rate

Modular Open Network ARCHitecture (MONARCH): Transitioning plug-and-play to aerospace

NASA Astrophysics Data System (ADS)

Martin, M.; Lyke, J.

The Air Force Research Laboratory (AFRL) developed an initial plug-and-play (PnP) capability for spacecraft, similar to USB on personal computers, which better defines hardware and software interfaces and incorporates self-discovery and auto-configuration in order to simplify spacecraft development and reduce cost and schedule. PnP technology was matured through a suborbital PnP flight experiment in September 2007 and a secondary Spacecraft Avionics Experiment (SAE) payload on the TacSat-3 satellite, which launched in May 2009. AFRL developed and submitted a complete set of PnP standards through the American Institute of Aeronautics and Astronautics (AIAA) in 2011. Space electronics to adapt existing satellite components and implement full PnP on satellites in accordance with these AFRL standards was independently developed in alternate hardware implementations by Goodrich Corp under AFRL and by Northrop Grumman under Operationally Responsive Space (ORS). In 2011, AFRL conducted a cost-benefit analysis of PnP and assembled a collaborative review board (CRB) in Sept 2011 to evaluate PnP. This CRB was comprised of representatives from Space and Missiles Center (SMC), National Reconnaissance Organization (NRO), Naval Research Laboratory (NRL), John Hopkins University (JHU) Applied Physics Laboratory (APL), The Aerospace Corporation, and several large commercial and DOD satellite developers. This CRB laid out a transition path to develop and implement PnP standards for implementation in large (> 1000 kg) DOD and commercial satellites. Transition of PnP technology into operational systems continues in PnP architecture studies for SMC, PnP products from multiple space industry vendors, commercial implementations of PnP, and the Northrop Grumman ORS-2 spacecraft currently project to fly in 2014-2015. This paper provides details related to development of PnP technology, AFRL's cost-benefit analysis of PnP, recommendations of the PnP CRB, and on-going efforts to mature - nd fly PnP technology.

Status of the Northrop Grumman Compact Infrared Free-Electron Laser

DOE Office of Scientific and Technical Information (OSTI.GOV)

Lehrman, I.S.; Krishnaswamy, J.; Hartley, R.A.

1995-12-31

The Compact Infrared Free Electron Laser (CIRFEL) was built as part of a joint collaboration between the Northrop Grumman Corporation and Princeton University to develop FEL`s for use by researchers in the materials, medical and physical sciences. The CIRFEL was designed to lase in the Mid-IR and Far-IR regimes with picosecond pulses, megawatt level peak powers and an average power of a few watts. The micropulse separation is 7 nsec which allows a number of relaxation phenomenon to be observed. The CIRFEL utilizes an RF photocathode gun to produce high-brightness time synchronized electron bunches. The operational status and experimental resultsmore » of the CERFEL will be presented.« less

New York Film Academy Students on Webb Telescope Tour

NASA Image and Video Library

2017-12-08

Students and teachers from the New York Film Academy visited Northrop Grumman’s Space Park facility in December 2014 for a tour of the James Webb Space Telescope, and got an up-close look at the tennis-court-sized sunshield that will keep the telescope cool in deep space. Photo courtesy of Northrop Grumman Corporation

Northrop Grumman TR202 LOX/LH2 Deep Throttling Engine Technology Project Status

NASA Technical Reports Server (NTRS)

Gromski, Jason; Majamaki, Annik; Chianese, Silvio; Weinstock, Vladimir; Kim, Tony S.

2010-01-01

NASA's Propulsion and Cryogenic Advanced Development (PCAD) project is currently developing enabling propulsion technologies in support of future lander missions. To meet lander requirements, several technical challenges need to be overcome, one of which is the ability for the descent engine(s) to operate over a deep throttle range with cryogenic propellants. To address this need, PCAD has enlisted Northrop Grumman Aerospace Systems (NGAS) in a technology development effort associated with the TR202 engine. The TR202 is a LOX/LH2 expander cycle engine driven by independent turbopump assemblies and featuring a variable area pintle injector similar to the injector used on the TR200 Apollo Lunar Module Descent Engine (LMDE). Since the Apollo missions, NGAS has continued to mature deep throttling pintle injector technology. The TR202 program has completed two series of pintle injector testing. The first series of testing used ablative thrust chambers and demonstrated igniter operation as well as stable performance at discrete points throughout the designed 10:1 throttle range. The second series was conducted with calorimeter chambers and demonstrated injector performance at discrete points throughout the throttle range as well as chamber heat flow adequate to power an expander cycle design across the throttle range. This paper provides an overview of the TR202 program, describing the different phases and key milestones. It describes how test data was correlated to the engine conceptual design. The test data obtained has created a valuable database for deep throttling cryogenic pintle technology, a technology that is readily scalable in thrust level.

Environmentally Responsible Aviation N plus 2 Advanced Vehicle Study

NASA Technical Reports Server (NTRS)

Drake, Aaron; Harris, Christopher A.; Komadina, Steven C.; Wang, Donny P.; Bender, Anne M.

2013-01-01

This is the Northrop Grumman final report for the Environmentally Responsible Aviation (ERA) N+2 Advanced Vehicle Study performed for the National Aeronautics and Space Administration (NASA). Northrop Grumman developed advanced vehicle concepts and associated enabling technologies with a high potential for simultaneously achieving significant reductions in emissions, airport area noise, and fuel consumption for transport aircraft entering service in 2025. A Preferred System Concept (PSC) conceptual design has been completed showing a 42% reduction in fuel burn compared to 1998 technology, and noise 75dB below Stage 4 for a 224- passenger, 8,000 nm cruise transport aircraft. Roadmaps have been developed for the necessary technology maturation to support the PSC. A conceptual design for a 55%-scale demonstrator aircraft to reduce development risk for the PSC has been completed.

High beta and second stability region transport and stability analysis. Final report

DOE Office of Scientific and Technical Information (OSTI.GOV)

Hughes, M.H.; Phillips, M.W.

1996-01-01

This report describes MHD equilibrium and stability studies carried out at Northrop Grumman`s Advanced Technology and Development Center during the period March 1 to December 31, 1995. Significant progress is reported in both ideal and resistive MHD modeling of TFTR plasmas. Specifically, attention is concentrated on analysis of Advanced Tokamak experiments at TFTR involving plasmas in which the q-profiles were non-monotonic.

High beta and second stability region transport and stability analysis: Technical progress report

DOE Office of Scientific and Technical Information (OSTI.GOV)

Hughes, M.H.; Phillips, M.W.

1995-03-01

This report summarizes MHD equilibrium and stability studies carried out at Northrop Grumman`s Advanced Technology and Development Center during the 12 month period starting March 1, 1994. Progress is reported in both ideal and resistive MHD modeling of TFTR plasmas. The development of codes to calculate the significant effects of highly anisotropic pressure distributions is discussed along with results from this model.

78 FR 29808 - Petition for Exemption; Summary of Petition Received

Federal Register 2010, 2011, 2012, 2013, 2014

2013-05-21

... signing the comment for an association, business, labor union, etc.). You may review DOT's complete... would allow Northrop Grumman Systems Corporation to operate a BE-1900 (a type rated aircraft requiring...

KSC-2010-5709

NASA Image and Video Library

2010-11-16

CAPE CANAVERAL, Fla. -- Japan Aerospace Exploration Agency and International Space Station Program Manager Tetsuro Yokoyama addresses attendees of the American Astronautical Society's 2010 National Conference held at the Radisson Resort at the Port in Cape Canaveral, Fla. The panel of speakers seated from left to right are, International Space Services President James Zimmerman; International Space Station Program Manager Michael Suffredini; Canadian Space Agency Director of Space Exploration Operations and Infrastructure Pierre Jean; European Space Agency Directorate of Human Spaceflight and International Space Station Programme Department Bernado Patti and Roskosmos Piloted Space Programs Department Director Alexey Krasnov. This year's conference was titled: International Space Station: The Next Decade - Utilization and Research. The conference was organized with the support of Kennedy and sponsored by The Boeing Company, Honeywell International Inc., Northrop Grumman Corp., Space Florida and the Universities Space Research Association (USRA). Photo credit: NASA/Jim Grossmann

Pin bearing evaluation of LTM25 composite materials

NASA Technical Reports Server (NTRS)

Shah, C. H.; Postyn, A. S.

1996-01-01

This report summarizes pin bearing evaluations of LTM25 composite materials. Northrop Grumman Corporation conducted pin bearing testing and fabricate two panels from composite materials that cure at low temperatures. These materials are being incorporated into Unmanned Aerial Vehicles (UAVS) to reduce manufacturing costs since they allow the use of low-cost tooling and facilities. Two composite prepreg product forms were evaluated; MR50/LTM25 unidirectional tape, batch 2881vd and CFS003/LTM25 woven cloth, batch 2216. Northrop Grumman fabricated, machined, and tested specimens to determine the bearing strength in accordance with MIL-HDBK-17D, Volume 1, Section 7.2.4. Quasi-isotropic laminates from the two product forms were fabricated for these tests. In addition, 2 quasi-isotropic panels of dimensions 12 in. x 28 in. were fabricated (one each from the two product forms), inspected, and shipped to NASA Langley for further evaluation.

Three-dimensional simulation of helix traveling-wave tube cold-test characteristics using MAFIA

DOE Office of Scientific and Technical Information (OSTI.GOV)

Kory, C.L.

1996-12-31

A critically important step in the traveling-wave tube (TWT) design process is the cold-testing of the slow-wave circuit for dispersion, beam interaction impedance and RF losses. Experimental cold-tests can be very time-consuming and expensive, thus limiting the freedom to examine numerous variations to the test circuit. This makes the need for computational methods crucial as they can lower cost, reduce tube development time and allow the freedom to introduce novel and improved designs. The cold-test parameters have been calculated for a C-Band Northrop-Grumman helix TWT slow-wave circuit using MAFIA, the three-dimensional electromagnetic finite-integration computer code. Measured and simulated cold-test datamore » for the Northrop-Grumman helix TWT including dispersion, impedance and attenuation will be presented. Close agreement between simulated and measured values of the dispersion, impedance and attenuation has been obtained.« less

Acquisition and Competition Strategy Options for the DD(X): The U.S. Navy’s 21st Century Destroyer

DTIC Science & Technology

2006-01-01

5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Rand Corporation,National Defense Research Institute,1776...In April 2002, one of those teams, led by Nor- throp Grumman Ship Systems ( NGSS ), was selected winner of the competition and awarded a $2.9 billion...Northrop Grumman Ship Systems ( NGSS ) and including Raytheon Systems Co. was selected as winner of that competition and placed under contract to

Light UAV Support Ship (ASW) (LUSSA)

DTIC Science & Technology

2011-08-01

35 9.5 TriSWACH Model Test Data...7 Figure 8: TriSWACH Model ...Innovation in Ship Design (CISD) used the Northrop Grumman Bat UAV (formally known as the Swift Engineering Killer Bee KB4) to model launch, recovery, and

A Moderated Discussion about Interesting Careers in Aerospace and Mission Operations

NASA Astrophysics Data System (ADS)

Grant, Jeffrey

2013-01-01

Astronomers have one of the lowest unemployment rates in the US, yet many do not work in the field of astronomy because of few permanent traditional options relative to the number of PhDs produced each year. Where do so many astronomers find employment? Learn more at this session. Astronomical training provides the background for many interesting careers. As appropriate to the location of this meeting, this session provides a perspective on what those opportunities may be among aerospace industry-related careers. They are more diverse than you might think. In this session, two speakers with wide ranging experience in the field and a high level view of staffing large projects offer their thoughts. Kathy Flanagan is Deputy Director of the Space Telescope Science Institute, which will conduct the science and mission operations for the James Webb Space Telescope. This project has involved staffing at many levels of hardware, software, data analysis, science, operations, and outreach. Jeff Grant is sector vice president and general manager of the Space Systems Division at Northrop Grumman Aerospace Systems, and leads the design, build, launch and operations of major systems in space. We invite early career scientists and their mentors to hear their thoughts and ask questions at this session.

Shuttle Mission STS-50: Orbital Processing of High-Quality CdTe Compound Semiconductors Experiment: Final Flight Sample Characterization Report

NASA Technical Reports Server (NTRS)

Larson, David J.; Casagrande, Luis G.; DiMarzio, Don; Alexander, J. Iwan D.; Carlson, Fred; Lee, Taipo; Dudley, Michael; Raghathamachar, Balaji

1998-01-01

The Orbital Processing of High-Quality Doped and Alloyed CdTe Compound Semiconductors program was initiated to investigate, quantitatively, the influences of gravitationally dependent phenomena on the growth and quality of bulk compound semiconductors. The objective was to improve crystal quality (both structural and compositional) and to better understand and control the variables within the crystal growth production process. The empirical effort entailed the development of a terrestrial (one-g) experiment baseline for quantitative comparison with microgravity (mu-g) results. This effort was supported by the development of high-fidelity process models of heat transfer, fluid flow and solute redistribution, and thermo-mechanical stress occurring in the furnace, safety cartridge, ampoule, and crystal throughout the melting, seeding, crystal growth, and post-solidification processing. In addition, the sensitivity of the orbital experiments was analyzed with respect to the residual microgravity (mu-g) environment, both steady state and g-jitter. CdZnTe crystals were grown in one-g and in mu-g. Crystals processed terrestrially were grown at the NASA Ground Control Experiments Laboratory (GCEL) and at Grumman Aerospace Corporation (now Northrop Grumman Corporation). Two mu-g crystals were grown in the Crystal Growth Furnace (CGF) during the First United States Microgravity Laboratory Mission (USML-1), STS-50, June 24 - July 9, 1992.

Electro-Optic Identification (EOID) Research Program

DTIC Science & Technology

2001-09-30

1 Electro - Optic Identification (EOID) Research Program Gene M. Cumm Northrop Grumman Oceanic and Naval Systems P.O. Box 1488 Annapolis...control number. 1. REPORT DATE 30 SEP 2001 2. REPORT TYPE 3. DATES COVERED 00-00-2001 to 00-00-2001 4. TITLE AND SUBTITLE Electro - Optic Identification

Schools Enlisting Defense Industry to Boost STEM

ERIC Educational Resources Information Center

Trotter, Andrew

2008-01-01

Defense contractors Northrop Grumman Corp. and Lockheed Martin Corp. are joining forces in an innovative partnership to develop high-tech simulations to boost STEM--or science, technology, engineering, and mathematics--education in the Baltimore County schools. The Baltimore County partnership includes the local operations of two major military…

NASA's Webb Sunshield Gives an "Open Wide" for Inspection

NASA Image and Video Library

2017-12-08

The sunshield on NASA's James Webb Space Telescope is the largest part of the observatory—five layers of thin, silvery membrane that must unfurl reliably in space. The precision in which the tennis-court sized sunshield has to open must be no more than a few centimeters different from its planned position. In this photo, engineers and scientists examine the sunshield layers on this full-sized test unit. Because there's a layer of the shiny silver material on the base under the five layers of the sunshield, it appears as if the sunshield has a mouth that is "open wide" while engineers take a look. The photo was taken in a clean room at Northrop Grumman Corporation, Redondo Beach, California. The sunshield separates the observatory into a warm sun-facing side and a cold side where the sunshine is blocked from interfering with the sensitive infrared instruments. The infrared instruments need to be kept very cold (under 50 K or -370 degrees Fahrenheit) to operate. The sunshield protects these sensitive instruments with an effective sun protection factor, or SPF, of 1,000,000. Sunscreen generally has an SPF of 8 to 50. In addition to providing a cold environment, the sunshield provides a thermally stable environment. This stability is essential to maintaining proper alignment of the primary mirror segments as the telescope changes its orientation to the sun. Earlier this year, the first flight layer of the sunshield was delivered to Northrop Grumman. Northrop Grumman is designing the Webb Telescope’s sunshield for NASA’s Goddard Space Flight Center, in Greenbelt, Maryland. Innovative sunshield membranes are being designed and manufactured by NeXolve Corporation of Huntsville, Alabama. The James Webb Space Telescope is the successor to NASA's Hubble Space Telescope. It will be the most powerful space telescope ever built. Webb is an international project led by NASA with its partners, the European Space Agency and the Canadian Space Agency. For more information about the Webb telescope, visit: www.jwst.nasa.gov or www.nasa.gov/webb For more information on the Webb Sunshield, visit: jwst.nasa.gov/sunshield.html Photo credit: Alex Evers/Northrop Grumman Corporation NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

Integrating Technology and Engineering with a Marine Design Contest and 3-D Modeling

ERIC Educational Resources Information Center

Hammons, John

2011-01-01

The Northrop Grumman (now Huntington Ingalls Industries, Incorporated) Apprentice School, in cooperation with several area businesses, sponsors an annual boat-design competition for high school students to increase awareness of the naval architecture profession and the shipbuilding industry. The competition engages students' math, science,…

77 FR 3007 - Notice Pursuant to the National Cooperative Research and Production Act of 1993-National...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-01-20

... Production Act of 1993--National Shipbuilding Research Program Notice is hereby given that, on December 20....C. 4301 et seq. (``the Act''), National Shipbuilding Research Program (``NSRP'') has filed written..., the following members have changed their names: Northrop Grumman Shipbuilding, Inc.--Gulf Coast...

Operational cooling tower model (CTTOOL V1.0)

DOE Office of Scientific and Technical Information (OSTI.GOV)

Aleman, S.; LocalDomainServers, L.; Garrett, A.

2015-01-01

Mechanical draft cooling towers (MDCT’s) are widely used to remove waste heat from industrial processes, including suspected proliferators of weapons of mass destruction (WMD). The temperature of the air being exhausted from the MDCT is proportional to the amount of thermal energy being removed from the process cooling water, although ambient weather conditions and cooling water flow rate must be known or estimated to calculate the rate of thermal energy dissipation (Q). It is theoretically possible to derive MDCT air exhaust temperatures from thermal images taken from a remote sensor. A numerical model of a MDCT is required to translatemore » the air exhaust temperature to a Q. This report describes the MDCT model developed by the Problem Centered Integrated Analysis (PCIA) program that was designed to perform those computational tasks. The PCIA program is a collaborative effort between the Savannah River National Laboratory (SRNL), the Northrop-Grumman Corporation (NG) and the Aerospace Corporation (AERO).« less

The Space Infrared Interferometric Telescope (SPIRIT): Recent Study Results and Plans

NASA Astrophysics Data System (ADS)

Leisawitz, David; SPIRIT Mission Study Team

2007-12-01

SPIRIT was recommended in the 2002 "Community Plan for Far-IR/Submillimeter Space Astronomy.” A structurally connected interferometer, SPIRIT provides sensitive sub-arcsecond angular resolution images and integral field spectroscopy in the 25 to 400 micron wavelength range. SPIRIT was designed to revolutionize our understanding of planetary system formation, reveal otherwise-undetectable planets through the disk perturbations they induce, spectroscopically probe the atmospheres of extrasolar giant planets in orbits typical of most of the planets in our solar system, and yield significant new insight into the processes associated with galaxy formation and development. This paper updates previously presented study results and describes future study plans. Our SPIRIT mission concept study proposal was peer reviewed and selected by NASA for support under the Origins Probe Mission Concept Study program. NASA's Goddard Space Flight Center and four industry partners - Ball Aerospace, Boeing, Lockheed-Martin, and Northrop-Grumman - contributed generously the study. The Origins Probe study results were reviewed by an Advisory Review Panel.

OMPS Sensor Performance and Algorithm Description

NASA Astrophysics Data System (ADS)

Branham, M. S.; Farrow, S. V.; Novicki, M.; Bhaswar, S.; Baker, B.

2009-12-01

The Ozone Mapping and Profiler Suite (OMPS), built by Ball Aerospace, is the next-generation U.S. ozone monitoring sensor suite, designed and built for the National Polar-orbiting Operational Environmental Satellite System (NPOESS), under contract to the Integrated Program Office, administered by the Air Force, National Oceanic and Atmospheric Administration (NOAA), and National Aeronautics and Space Administration (NASA) under contract to Northrop Grumman. The first flight of an OMPS is scheduled for early 2011 on the NPOESS Preparatory Project (NPP) satellite. The OMPS sensor data will be used to generate the ozone calibrated sensor data and environmental data record (EDR) products. The final OMPS sensor performance and algorithms for NPP will be presented, now that the FM1 flight sensor suite has completed sell off and is integrated on the NPP spacecraft. Challenges requiring future development, and during intensive calibration/validation on orbit will be described. Also, an overview of the sensor suite, the FM1 measurement performance, and details of the retrieval algorithms will be provided in this presentation.

Characterization of a Two-Stage Pulse Tube Cooler for Space Applications

NASA Astrophysics Data System (ADS)

Orsini, R.; Nguyen, T.; Colbert, R.; Raab, J.

2010-04-01

A two-stage long-life, low mass and efficient pulse tube cooler for space applications has been developed and acceptance tested for flight applications. This paper presents the data collected on four flight coolers during acceptance testing. Flight acceptance test of these cryocoolers includes thermal performance mapping over a range of reject temperatures, launch vibration testing and thermal cycling testing. Designed conservatively for a 10-year life, the coolers are required to provide simultaneous cooling powers at 95 K and 180 K while rejecting to 300 K with less than 187 W input power to the electronics. The total mass of each cooler and electronics system is 8.7 kg. The radiation-hardened and software driven control electronics provides cooler control functions which are fully re-configurable in orbit. These functions include precision temperature control to better than 100 mK p-p. This 2 stage cooler has heritage to the 12 Northrop Grumman Aerospace Systems (NGAS) coolers currently on orbit with 2 operating for more than 11.5 years.

CRIS Cyber Range Lexicon Version 1.0 (Report 59 0001)

DTIC Science & Technology

2015-11-27

Evaluation (T&E) Support Cell, TRMC/ Northrop Grumman ) Dr. David “Fuzzy” Wells (USPACOM) Mr. Bennett Wilson (NAVSEA GOV – CDSA, Damneck...9 Figure 4: Planes and Teams...Communities supported by the CRIS WG include, but are not limited to, Science & Technology (S&T) experimentation , Developmental and Operational Test and

Advances in integrated system heath management system technologies : overview of NASA and industry collaborative activities

NASA Technical Reports Server (NTRS)

Dixit, Sunil; Brown, Steve; Fijany, Amir; Park, Han; Mackey, Ryan; James, Mark; Baroth, Ed

2005-01-01

This paper will describe recent advances in ISHM technologies made through collaboration between NASA and industry. In particular, the paper will focus on past, present, and future technology development and maturation efforts at the Jet Propulsion Laboratory (JPL) and its industry partner, Northrop Grumman lntegrated Systems (NGIS).

Improving Naval Shipbuilding Project Efficiency through Rework Reduction

DTIC Science & Technology

2007-09-01

National Steel and Shipbuilding Company Kvaerner Masa (Finland) Swan Hunter Northrop Grumman Ship Systems Royal Schelde (The Netherlands) Vosper...72 10% T-AKE 9 $ 380 $9 2% $39 10% T-AKE Subtotal $3,354 $29 1% $370 11% Grand Total 49,287 5,645 11% 5,934 12% Table 8. Change Cost Analysis

Applying Gaming and Simulation Techniques to the Design of Online Instruction

ERIC Educational Resources Information Center

Rude-Parkins, Carolyn; Miller, Karen Hughes; Ferguson, Karen; Bauer, Robert

2006-01-01

Critical in virtually all educational arenas, gaming and simulation techniques and distance learning are major areas of interest in today's U.S. Army training. The U.S. Army Armor School at Ft. Knox, KY contracted with the University of Louisville and Northrop Grumman Mission Systems in 2003 to develop online training for Army Captains. They…

Coast Guard Deepwater Program: Background, Oversight Issues, and Options for Congress

DTIC Science & Technology

2007-10-10

PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES...112 Appendix E. NGSS Testimony...Lockheed Martin and Northrop Grumman Ship Systems ( NGSS ). ICGS was awarded an indefinite delivery, indefinite quantity (ID/IQ) contract for the Deepwater

Joint Light Tactical Vehicle (JLTV): Background and Issues for Congress

DTIC Science & Technology

2016-09-09

5 Lockheed Martin Files Protest with the Government Accountability Office (GAO...12, 2008, protests were filed with the Government Accountability Office (GAO) against the TD contract awards by the Northrop Grumman-Oshkosh team...Quantities and Program Costs13 According to the Government Accountability Agency’s (GAO’s) March 2016 Assessments of Major Weapons Programs, for a JLTV

Northrop Grumman TR202 LOX/LH2 Deep Throttling Engine Project Status

NASA Technical Reports Server (NTRS)

Gromski, J.; Majamaki, A. N.; Chianese, S. G.; Weinstock, V. D.; Kim, T.

2010-01-01

NASA's Propulsion and Cryogenic Advanced Development (PCAD) project is currently developing enabling propulsion technologies in support of the Exploration Initiative, with a particular focus on the needs of the Altair Project. To meet Altair requirements, several technical challenges need to be overcome, one of which is the ability for the lunar descent engine(s) to operate over a deep throttle range with cryogenic propellants. To address this need, PCAD has enlisted Northrop Grumman Aerospace Systems (NGAS) in a technology development effort associated with the TR202, a LOX/LH2 expander cycle engine driven by independent turbopump assemblies and featuring a variable area pintle injector similar to the injector used on the TR200 Apollo Lunar Module Descent Engine (LMDE). Since the Apollo missions, NGAS has continued to mature deep throttling pintle injector technology. The TR202 program has completed two phases of pintle injector testing. The first phase of testing used ablative thrust chambers and demonstrated igniter operation as well as stable performance at several power levels across the designed 10:1 throttle range. The second phase of testing was performed on a calorimeter chamber and demonstrated injector performance at various power levels (75%, 50%, 25%, 10%, and 7.5%) across the throttle range as well as chamber heat flux to show that the engine can close an expander cycle design across the throttle range. This paper provides an overview of the TR202 program. It describes the different phases of the program with the key milestones of each phase. It then shows when those milestones were met. Next, it describes how the test data was used to update the conceptual design and how the test data has created a database for deep throttling cryogenic pintle technology that is readily scaleable and can be used to again update the design once the Altair program's requirements are firm. The final section of the paper describes the path forward, which includes demonstrating continuously throttling with an actuator and pursuing a path towards integrated engine sea-level test-bed testing.

The Retention of Digital Skills Following Distributed and Traditional Training

DTIC Science & Technology

2011-04-01

shows that discrete procedural tasks, like digital skills, are more perishable than continuous procedures (e.g., riding a bicycle ) or declarative...BLACK, Ph.D. MICHELLE SAMS, Ph.D. Research Program Manager Director Training and Leader Development Division Research...especially due to Nancy Riffe and Diadra Swinson of Northrop Grumman who compiled numerous FBCB2 system screen shots, developed detailed graphics and

Aircraft

DTIC Science & Technology

2002-01-01

electronics, systems integration and information technology company.39 Northrop Grumman no longer seeks a position as a prime contractor/integrator of fixed...of the spares procurement and distribution processes. Finally, they recognize that excellence in Information Technology (IT) is a strategic advantage...business in export dollars, the industry has been forced to look for new markets as worldwide aircraft sales have dropped. Because the U.S. national

CRIS Cyber Range Lexicon Version 1.0

DTIC Science & Technology

2015-10-30

Zachary Weber (MIT Lincoln Laboratory) Mr. Mike Wee (Cyber Test & Evaluation (T&E) Support Cell, TRMC/ Northrop Grumman ) Dr. David “Fuzzy” Wells (USPACOM) Mr. Bennett Wilson (NAVSEA GOV – CDSA, Damneck) ...11 Figure 4: Planes and Teams...the CRIS WG include, but are not limited to, Science & Technology (S&T) experimentation , Developmental and Operational Test and Evaluation (DT&E, OT

Coast Guard Deepwater Program: Background, Oversight Issues, and Options for Congress

DTIC Science & Technology

2007-04-30

NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Congressional Research...Northrop Grumman Ship Systems ( NGSS ). On April 18, 2007, it was reported that the Justice Department is conducting an investigation of the Deepwater...59 Appendix E. NGSS Testimony . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66 February 14, 2007

James Webb Space Telescope Sunshield Test Unfolds Seamlessly

NASA Image and Video Library

2017-12-08

A major test of the sunshield for NASA’s James Webb Space Telescope was conducted recently by Northrop Grumman in Redondo Beach, California. For the first time, the five sunshield test layers were unfolded and separated; unveiling important insights for the engineers and technicians as to how the deployment will take place when the telescope launches into space. “These tests are critical and allow us to see how our modeling works and learn about any modifications we may need to make in our design as we move into sunshield flight production,” said Jim Flynn, Webb sunshield manager. The three-day test took place in July, taking seven engineers and six technicians about 20 hours to complete. On orbit, the sunshield will take several days to unfold. Read more here: 1.usa.gov/1vykZbk Credit: Northrop Grumman/Alex Evers NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

SCORPION II persistent surveillance system update

NASA Astrophysics Data System (ADS)

Coster, Michael; Chambers, Jon

2010-04-01

This paper updates the improvements and benefits demonstrated in the next generation Northrop Grumman SCORPION II family of persistent surveillance and target recognition systems produced by the Xetron Campus in Cincinnati, Ohio. SCORPION II reduces the size, weight, and cost of all SCORPION components in a flexible, field programmable system that is easier to conceal and enables integration of over fifty different Unattended Ground Sensor (UGS) and camera types from a variety of manufacturers, with a modular approach to supporting multiple Line of Sight (LOS) and Beyond Line of Sight (BLOS) communications interfaces. Since 1998 Northrop Grumman has been integrating best in class sensors with its proven universal modular Gateway to provide encrypted data exfiltration to Common Operational Picture (COP) systems and remote sensor command and control. In addition to feeding COP systems, SCORPION and SCORPION II data can be directly processed using a common sensor status graphical user interface (GUI) that allows for viewing and analysis of images and sensor data from up to seven hundred SCORPION system gateways on single or multiple displays. This GUI enables a large amount of sensor data and imagery to be used for actionable intelligence as well as remote sensor command and control by a minimum number of analysts.

NPOESS Preparatory Project Validation Program for the Cross-track Infrared Sounder

NASA Astrophysics Data System (ADS)

Barnet, C.; Gu, D.; Nalli, N. R.

2009-12-01

The National Polar-orbiting Operational Environmental Satellite System (NPOESS) Program, in partnership with National Aeronautical Space Administration (NASA), will launch the NPOESS Preparatory Project (NPP), a risk reduction and data continuity mission, prior to the first operational NPOESS launch. The NPOESS Program, in partnership with Northrop Grumman Aerospace Systems, will execute the NPP Calibration and Validation (Cal/Val) program to ensure the data products comply with the requirements of the sponsoring agencies. The Cross-track Infrared Sounder (CrIS) and the Advanced Technology Microwave Sounder (ATMS) are two of the instruments that make up the suite of sensors on NPP. Together, CrIS and ATMS will produce three Environmental Data Records (EDRs) including the Atmospheric Vertical Temperature Profile (AVTP), Atmospheric Vertical Moisture Profile (AVMP), and the Atmospheric Vertical Pressure Profile (AVPP). The AVTP and the AVMP are both NPOESS Key Performance Parameters (KPPs). The validation plans establish science and user community leadership and participation, and demonstrated, cost-effective Cal/Val approaches. This presentation will provide an overview of the collaborative data, techniques, and schedule for the validation of the NPP CrIS and ATMS environmental data products.

Proposal to Accomplish Phase B Space Shuttle Program

NASA Technical Reports Server (NTRS)

Mead, Lawrence M.; Gavin, Joseph G., Jr.

1970-01-01

This proposal has been prepared in response to National Aeronautics and Space Administration Request for Proposal No. 10-8423, dated February 20, 1970, and Amendments No.1, 2, 3, & 4 thereto. It is firm for a period of not less than one hundred twenty (120) days from March 30, 1970. The executed certifications requested in Enclosures 5 and 6 of the Request for Proposal are appended at the end of this proposal. Grumman Aerospace Corporation, along with its associates -- the General Electric Company, Eastern Airlines, the Northrop Corporation, and the Aerojet-General Corporation -- are pleased to submit this proposal. This study must prove that technical challenges can be met at a cost commensurate with realistic national funding levels at an early date, (perferably prior to the late 1977 initial operating capability (IOC) indicated in the Statement of Work). We have assembled a team of extremely competent associates. Together, we are fully qualified to study all facets of the proposed Phase B study, and to develop and build the product. We believe we have already made a promising start toward defining the concept of the space shuttle system.

Multistage Pulse Tube Refrigeration Characterization of the Northrop Grumman High Capacity Cooler - An Update

DTIC Science & Technology

2008-01-01

Additional information on AIP Conf. Proc. Journal Homepage: http://proceedings.aip.org/ Journal Information: http://proceedings.aip.org/about...coolers would make comparing temperature and load data virtually meaningless. One solution as presented by Razani [4] is to compare exergy vs...P Q ,=η (2) Where exercoolingQ , is the total exergy delivered to all refrigerated reservoirs and

Coast Guard Deepwater Program: Background, Oversight Issues, and Options for Congress

DTIC Science & Technology

2007-06-22

PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES...had been performed by Integrated Coast Guard Systems (ICGS) — an industry team led by Lockheed Martin and Northrop Grumman Ship Systems ( NGSS ). On...98 Appendix E. NGSS Testimony . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 107 May 17, 2007, Testimony

Cognitive Works Aids for C2 Planning: Actionable Information to Support Operational Decision Making

DTIC Science & Technology

2005-06-01

Information to Support Operational Decision Making Topic: Decisionmaking and Cognitive Science Jeffrey Wampler†*, Randall Whitaker§, Emilie...channeled through this state-of- the- art mobility C2 hub. It is a global AOC with several hundred people planning and executing around 350 missions...2005 Topical Area: Decisionmaking and Cognitive Science CONFERENCE PRESENTATION BY: RANDALL WHITAKER, PH.D. NORTHROP GRUMMAN INFORMATION TECHNOLOGY

Tier 1 and Tier 3 eAdjudication Business Rule Validation

DTIC Science & Technology

2018-04-01

Approved for Public Distribution Defense Personnel and Security Research Center Office of People Analytics OPA-2018-038 PERSEREC-TR-18-06 April...Northrop Grumman Technology Services Leissa C. Nelson, Ph.D. Susan C. Reed Defense Personnel and Security Research Center Office of People Analytics...Defense Personnel and Security Research Center Office of People Analytics 400 Gigling Road, Seaside, CA 93955 OPA-2018-038 PERSEREC-TR-06 April

2002 Industry Studies: Aircraft

DTIC Science & Technology

2002-01-01

aircraft to a defense electronics, systems integration and information technology company.39 Northrop Grumman no longer seeks a position as a prime...between the military and civil market . Though also upgrading the H-1 helicopter series for the USMC, Bell has mortgaged its future on tiltrotor technology ...business in export dollars, the industry has been forced to look for new markets as worldwide aircraft sales have dropped. Because the U.S. national

Standardized Verification, Validation, and Accreditation (VV&A) Documentation Schema Description Document

DTIC Science & Technology

2008-10-31

SSC Charleston; Mr. David Broyles, SSC Charleston; Dr. Richard Daehler-Wilking, SSC Charleston; Ms. Marcy Stutzman, Northrop Grumman ; and Tammie...PAGE Form Approved OMB No. 0704-0188 Public reporting burden for this collection of information is estimated to average 1 hour per response, including...1204, Arlington, VA 22202-4302, and to the Office of Management and Budget, Paperwork Reduction Project (0704-0188) Washington DC 20503. 1 . AGENCY

Modeling of the Electric Ship

DTIC Science & Technology

2010-06-01

2009, Northrop Grumman and American Superconductor, under an Office of Naval Research contract, successfully tested a HTS AC synchronous motor (HTS ACSM...BLANK i REPORT DOCUMENTATION PAGE Form Approved OMB No. 0704-0188 Public reporting burden for this collection of information is estimated to average 1 ...Washington DC 20503. 1 . AGENCY USE ONLY (Leave blank) 2. REPORT DATE June 2010 3. REPORT TYPE AND DATES COVERED Master’s Thesis 4. TITLE AND

Coast Guard Deepwater Acquisition Programs: Background, Oversight Issues, and Options for Congress

DTIC Science & Technology

2011-03-18

NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Congressional Research Service,Library Of Congress,101...Deepwater Acquisition into asset-based Acquisition Program Baselines, the proposed changes align projects that were formerly grouped under...Integrated Coast Guard Systems (ICGS)—an industry team led by Lockheed Martin and Northrop Grumman Ship Systems ( NGSS ). ICGS was awarded an indefinite

Coast Guard Deepwater Acquisition Programs: Background, Oversight Issues, and Options for Congress

DTIC Science & Technology

2009-12-23

NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Congressional Research Service,Library of Congress...Northrop Grumman Ship Systems ( NGSS ). ICGS was awarded an indefinite delivery, indefinite quantity (ID/IQ) contract for the Deepwater program that...sustainment is not a Deepwater program but is displayed to align with the FY2009 Consolidated Security, Disaster Assistance, and Continuing Appropriations

Coast Guard Deepwater Acquisition Programs: Background, Oversight Issues, and Options for Congress

DTIC Science & Technology

2011-01-14

NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Congressional Research Service,Library Of Congress...Martin and Northrop Grumman Ship Systems ( NGSS ). ICGS was awarded an indefinite delivery, indefinite quantity (ID/IQ) contract for the Deepwater...Deepwater assets. The Coast Guard’s own management policies are generally aligned with DHS directives, although operational testing policies are still

Coast Guard Deepwater Acquisition Programs: Background, Oversight Issues, and Options for Congress

DTIC Science & Technology

2011-04-14

NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Congressional Research Service,The Library of Congress...disaggregation of the Deepwater Acquisition into asset-based Acquisition Program Baselines, the proposed changes align projects that were formerly grouped...industry team led by Lockheed Martin and Northrop Grumman Ship Systems ( NGSS ). ICGS was awarded an indefinite delivery, indefinite quantity (ID/IQ

Sensing, Navigation and Reasoning Technologies for the DARPA Urban Challenge

DTIC Science & Technology

2007-12-31

from the Applanix hardware and processed the data to account for state jumps. It then broadcast the world and local frame coordinate for the vehicle...contiguous series of control tactics, as requested by the Control. 22 Team Caltech Sensing and Mapping Subsystem Health Monitor Applanix (GPS and IMU...California Institute of Technology, Big Dog Ventures, Northrop Grumman Corporation, Mohr Davidow Ventures and Applanix Inc. The authors would also

Agile-Lean Software Engineering (ALSE) Evaluating Kanban in Systems Engineering

DTIC Science & Technology

2013-03-06

Boeing)  Garry Roedler (Lockheed Martin)  Karl Scotland (Rally Software, UK)  Alan Shalloway (NetObjectives)  Neil Shirk (Lockheed Martin... Neil Siegel (Northrop Grumman)  James Sutton (Jubata Group) Thanks are also due to the members of the SERC Research Council, particularly Barry...Incremental Commitment Model to Brownfield Systems Development, Proceedings, CSER 2009, April 2009. 16. Heath , B. et al. (2009). A survey of agent-based

Agile and Lean Systems Engineering: Kanban in Systems Engineering

DTIC Science & Technology

2011-12-31

Rico (Boeing)  Garry Roedler (Lockheed Martin)  Karl Scotland (Rally Software, UK)  Alan Shalloway (NetObjectives)  Neil Shirk (Lockheed Martin... Neil Siegel (Northrop Grumman)  James Sutton (Jubata Group) Thanks are also due to the members of the SERC Research Council, particularly Barry...Commitment Model to Brownfield Systems Development, Proceedings, CSER 2009, April 2009. 14. Heath , B. et al. (2009). A survey of agent-based modeling

Task Order Final Report for the Period 20 January 2003 to 19 January 2005 (Northrop Grumman)

DTIC Science & Technology

2005-04-01

34Nonlinear optical characterization of retinal molecules," Laser and Noncoherent Light Ocular Effects: Epidemiology, Prevention, and Treatment III, Bruce E...BIOEFFECTS DIVISION OPTICAL RADIATION BRANCH 2624 LOUIS BAUER DRIVE BROOKS CITY-BASE TX 78235 April2005 Approved for public release, distribution...SPONSORIMONITOR’S ACRONYM(S) Air Force Research Laboratory AFRL/HE Human Effectiveness Directorate, Directed Energy Bioeffects Division Optical Radiation

Can Profit Policy and Contract Incentives Improve Defense Contract Outcomes?

DTIC Science & Technology

2009-02-01

required by investors. The weighted average cost of capital ( WACC ) is the standard financial statistic that weights the returns demanded by investors that...hold equity and investors that hold debt.6 Like FCFROIC, WACC is expressed as a percentage. Consequently, it is possible to compare these two...contractors include Lockheed, Raytheon, Northrop Grumman, and General Dynamics. 6 Mathematically, WACC = Debt/(Debt + Equity) × Debt Cost × (1-Tax Rate

Can Profit Policy and Contract Incentives Improve Defense Contract Outcomes?

DTIC Science & Technology

2008-10-01

a metric that estimates the returns required by investors. The weighted average cost of capital ( WACC ) is the standard financial statistic that...weights the returns demanded by investors that hold equity and investors that hold debt.6 Like FCFROIC, WACC is expressed as a percentage. Consequently...previous year. 5 These defense prime contractors include Lockheed, Raytheon, Northrop Grumman, and General Dynamics. 6 Mathematically, WACC = Debt/(Debt

SCORPION II persistent surveillance system with universal gateway

NASA Astrophysics Data System (ADS)

Coster, Michael; Chambers, Jonathan; Brunck, Albert

2009-05-01

This paper addresses improvements and benefits derived from the next generation Northrop Grumman SCORPION II family of persistent surveillance and target recognition systems produced by the Xetron campus in Cincinnati, Ohio. SCORPION II reduces the size, weight, and cost of all SCORPION components in a flexible, field programmable system that is easier to conceal, backward compatible, and enables integration of over forty Unattended Ground Sensor (UGS) and camera types from a variety of manufacturers, with a modular approach to supporting multiple Line of Sight (LOS) and Beyond Line of Sight (BLOS) communications interfaces. Since 1998 Northrop Grumman has been integrating best in class sensors with its proven universal modular Gateway to provide encrypted data exfiltration to Common Operational Picture (COP) systems and remote sensor command and control. In addition to being fed to COP systems, SCORPION and SCORPION II data can be directly processed using a common sensor status graphical user interface (GUI) that allows for viewing and analysis of images and sensor data from up to seven hundred SCORPION system Gateways on single or multiple displays. This GUI enables a large amount of sensor data and imagery to be used for actionable intelligence as well as remote sensor command and control by a minimum number of analysts.

SEI Approach to Harmonization

DTIC Science & Technology

2008-07-18

PAs and PLA ISO 15504 and ISO 12207 COBIT EFQM ISO 9001 Improvement Method Elements Change management techniques: IDEAL and Six Sigma...Multimodel Improvement in Practice 12 SEI Webinar Series Northrop Grumman Mission Systems • CMMI, Six Sigma, ISO , KM • ―.. accelerate achievement of Levels...CMMI, ITIL, ISO 9001, P-CMM  ―Integrated Quality Mgmt System‖ • ―…development center…reduce[d]...in-process failure costs...5 to 1%...‖ Wipro • ISO

Effective Acquisition Strategies for Systems Engineering and Technical Assistance (SETA)

DTIC Science & Technology

2012-07-01

Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to a penalty for failing to comply with a collection...environment will consist of various distributed data sources, or nodes, that are fused together in order to enhance battlefield awareness . In the event that...Northrop Grumman sold its advisory services business, TASC, to private- equity investors (see the Appedix). In August 2010, CSC announced the sale of

Navy LPD-17 Amphibious Ship Procurement: Background, Issues, and Options for Congress

DTIC Science & Technology

2009-04-07

and Options for Congress 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e . TASK NUMBER 5f...disrupting the optimal construction sequence and application of lessons learned for follow-on vessels in these programs...statements among others, although not necessarily in the order shown below: • “I am deeply concerned about Northrop Grumman Ship Systems’ ( NGSS

Coast Guard Deepwater Acquisition Programs: Background, Oversight Issues, and Options for Congress

DTIC Science & Technology

2009-10-23

NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Congressional Research Service,The Library of...role to Integrated Coast Guard Systems (ICGS)—an industry team led by Lockheed Martin and Northrop Grumman Ship Systems ( NGSS ). ICGS was awarded an...icebreaker sustainment is not a Deepwater program but is displayed to align with the FY2009 Consolidated Security, Disaster Assistance, and

Coast Guard Deepwater Acquisition Programs: Background, Oversight Issues, and Options for Congress

DTIC Science & Technology

2010-10-22

NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Congressional Research Service,The Library of...Coast Guard Systems (ICGS)—an industry team led by Lockheed Martin and Northrop Grumman Ship Systems ( NGSS ). ICGS was awarded an indefinite delivery...The Coast Guard’s own management policies are generally aligned with DHS directives, although operational testing policies are still being revised

Navy LPD-17 Amphibious Ship Procurement: Background, Issues, and Options for Congress

DTIC Science & Technology

2010-07-01

Background, Issues, and Options for Congress 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e . TASK...performed out of sequence and significant rework has been required, disrupting the optimal construction sequence and application of lessons learned...deeply concerned about Northrop Grumman Ship Systems’ ( NGSS ) ability to recover in the aftermath of Hurricane Katrina, particularly in regard to

Navy LPD-17 Amphibious Ship Procurement: Background, Issues, and Options for Congress

DTIC Science & Technology

2010-06-10

Background, Issues, and Options for Congress 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e . TASK...out of sequence and significant rework has been required, disrupting the optimal construction sequence and application of lessons learned for...concerned about Northrop Grumman Ship Systems’ ( NGSS ) ability to recover in the aftermath of Hurricane Katrina, particularly in regard to construction

Coast Guard Deepwater Acquisition Programs: Background, Oversight Issues, and Options for Congress

DTIC Science & Technology

2009-07-22

NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Congressional Research Service,Library of Congress,101...an industry team led by Lockheed Martin and Northrop Grumman Ship Systems ( NGSS ). ICGS was awarded an indefinite delivery, indefinite quantity (ID...program but is displayed to align with the FY2009 Consolidated Security, Disaster Assistance, and Continuing Appropriations Act, P.L. 110-329.” b

Coast Guard Deepwater Acquisition Programs: Background, Oversight Issues, and Options for Congress

DTIC Science & Technology

2010-09-29

NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Congressional Research Service,The Library of...the role to Integrated Coast Guard Systems (ICGS)—an industry team led by Lockheed Martin and Northrop Grumman Ship Systems ( NGSS ). ICGS was...of individual Deepwater assets. The Coast Guard’s own management policies are generally aligned with DHS directives, although operational testing

Navy LPD-17 Amphibious Ship Procurement: Background, Issues, and Options for Congress

DTIC Science & Technology

2010-03-29

and Options for Congress 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e . TASK NUMBER 5f...performed out of sequence and significant rework has been required, disrupting the optimal construction sequence and application of lessons learned...deeply concerned about Northrop Grumman Ship Systems’ ( NGSS ) ability to recover in the aftermath of Hurricane Katrina, particularly in regard to

InP Heterojunction Bipolar Transistor Amplifiers to 255 GHz

NASA Technical Reports Server (NTRS)

Radisic, Vesna; Sawdai, Donald; Scott, Dennis; Deal, William; Dang, Linh; Li, Danny; Cavus, Abdullah; To, Richard; Lai, Richard

2009-01-01

Two single-stage InP heterojunction bipolar transistor (HBT) amplifiers operate at 184 and 255 GHz, using Northrop Grumman Corporation s InP HBT MMIC (monolithic microwave integrated circuit) technology. At the time of this reporting, these are reported to be the highest HBT amplifiers ever created. The purpose of the amplifier design is to evaluate the technology capability for high-frequency designs and verify the model for future development work.

Yes, the James Webb Space Telescope Mirrors 'Can'

NASA Image and Video Library

2017-12-08

The powerful primary mirrors of the James Webb Space Telescope will be able to detect the light from distant galaxies. The manufacturer of those mirrors, Ball Aerospace & Technologies Corp. of Boulder, Colo., recently celebrated their successful efforts as mirror segments were packed up in special shipping canisters (cans) for shipping to NASA. The Webb telescope has 21 mirrors, with 18 primary mirror segments working together as one large 21.3-foot (6.5-meter) primary mirror. The mirror segments are made of beryllium, which was selected for its stiffness, light weight and stability at cryogenic temperatures. Bare beryllium is not very reflective of near-infrared light, so each mirror is coated with about 0.12 ounce of gold. Northrop Grumman Corp. Aerospace Systems is the principal contractor on the telescope and commissioned Ball for the optics system's development, design, manufacturing, integration and testing. The Webb telescope is the world's next-generation space observatory and successor to the Hubble Space Telescope. The most powerful space telescope ever built, the Webb telescope will provide images of the first galaxies ever formed, and explore planets around distant stars. It is a joint project of NASA, the European Space Agency and the Canadian Space Agency. For more information about the James Webb Space Telescope, visit: www.jwst.nasa.gov Credit: Ball Aerospace NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

Cross-Track Infrared Sounder Science Data Record Pre-launch Calibration and On-Orbit Validation Plans

NASA Astrophysics Data System (ADS)

Hagan, D. E.; Bingham, G. E.; Predina, J.; Gu, D.; Sabet-Peyman, F.; Wang, C.; de Amici, G.; Plonski, M.; Farrow, S. V.; Hohn, J.; Esplin, M.; Zavyalov, V.; Fish, C. S.; Glumb, R.; Wells, S.; Suwinski, L.; Strong, J.; Behrens, C.; Kilcoyne, H.; Feeley, J.; Kratz, G.; Tremblay, D. A.

2009-12-01

The Cross-Track Infrared Sounder (CrIS) together with the Advanced Technology Microwave Sounder will provide retrievals of atmospheric moisture and temperature profiles for the National Polar-orbiting Operational Environmental Satellite System (NPOESS). The NPOESS is the next generation of low Earth orbiting weather and climate satellites managed by the tri-agency Integrated Program Office, which includes the Department of Commerce, Department of Defense and the National Aeronautics and Space Administration. The CrIS is a Fourier-transform Michelson interferometer covering the spectral range of 3.9 to 15.4 microns (650 to 2550 wavenumbers) developed by ITT under contract to Northrop Grumman Aerospace Systems. The first deployment of the CrIS (Flight Model 1) is scheduled for 2010 on the NPOESS Preparatory Project (NPP) satellite, an early instrument risk reduction component of the NPOESS mission. The analysis and data results from comprehensive TVAC testing of the CrIS FM1 sensor demonstrate a very accurate radiometric and spectral calibration system. We describe instrument performance parameters, and the end-to-end plans and analysis tools for on-orbit verification of sensor characteristics and validation of the SDR radiance products.

TRIAD Annual Spring Meeting (49th) Held in Huntsville, Alabama on May 27, 2010

DTIC Science & Technology

2010-05-27

Northrop Grumman Mission Systems Ms. Mitzi Whittenburg BAE Systems Presentations from the Spring TRIAD will be available to download 1-2 weeks...Ms. Mitzi Whittenburg, C.P.M., BAE Systems, Land & Armaments U.S. Combat Systems (USCS) u Ms. Chireda Gaither, CSC 2:50 pm - 3:00 pm CLOSING...REMARKS u Ms. Diane Dempsey, NDIA TRIAD Co-Chair, Meeting Chair Ms. Mitzi Whittenburg, CPM BAE Systems, Land & Armaments U.S. Combat Systems

The Value of Harmonizing Multiple Improvement Technologies: A Process Improvement Professional’s View

DTIC Science & Technology

2008-03-01

maturity models and ISO standards, specifically CMMI, CMMI-ACQ and ISO 12207 . Also, the improvement group supplemented their selection of these...compliant with the technologies and standards that are important to the business. Lockheed Martin IS&GS has integrated CMMI, EIA 632, ISO 12207 , and Six...geographically dispersed organization. [Siviy 07-1] Northrop Grumman Mission Systems has integrated CMMI, ISO 9001, AS9100, and Six Sigma, as well as a

Controlling the Cost of C4I Upgrades on Naval Ships

DTIC Science & Technology

2009-01-01

Dynamics Electric Boat and Northrop Grumman Newport News. To analyze cost drivers, variability within costs, and the accuracy of the Navy’s cost...design also features a zonal electricity grid that allows power to be directed throughout the ship where and when it is needed. C4I-Upgrade Issues...class for hull, mechanical, and electrical equip- ment and systems. However, because C4I technologies can change one or two times during the three

Implementing Filters to Identify and Prioritize Industrial Base Risk: Rules of Thumb to Reduce Cognitive Overload

DTIC Science & Technology

2015-04-30

Thumb to Reduce Cognitive Overload Sally Sleeper, ODASD[M&IBP] John F. Starns, Northrop Grumman Published April 30, 2015 Disclaimer: The views...Prioritize Industrial Base Risk: Rules of Thumb to Reduce Cognitive Overload 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6... Cognitive Overload Sally Sleeper—joined the Office of the Deputy Assistant Secretary of Defense for Manufacturing and Industrial Base Policy as Senior

Coast Guard Deepwater Acquisition Programs: Background, Oversight Issues, and Options for Congress

DTIC Science & Technology

2009-05-29

NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Congressional Research Service,Library of Congress,101...Guard awarded the role to Integrated Coast Guard Systems (ICGS)—an industry team led by Lockheed Martin and Northrop Grumman Ship Systems ( NGSS ...states that “Polar icebreaker sustainment is not a Deepwater program but is displayed to align with the FY2009 Consolidated Security, Disaster

Coast Guard Deepwater Acquisition Programs: Background, Oversight Issues, and Options for Congress

DTIC Science & Technology

2010-03-30

NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Congressional Research Service,Library of Congress,101...awarded the role to Integrated Coast Guard Systems (ICGS)—an industry team led by Lockheed Martin and Northrop Grumman Ship Systems ( NGSS ). ICGS was...Systems Command] and in April 2009. We continue to build on lessons learned and are making some significant improvements to the Stratton, including

NATO Independent Cost Estimating and the Role of Life Cycle Cost Analysis in Managing the Defence Enterprise (Estimation independante des couts de l’OTAN et role de l’analyse des couts globaux de possesssion au sen de l’OTAN)

DTIC Science & Technology

2012-08-01

Command NBCD Nuclear, Biological, and Chemical Defence NCCA U.S. Naval Center for Cost Analysis NGISSI Northrop Grumman Integrated Systems...analysis (CPA) in the United States which investigated how costs, capabilities, and risks could be examined together in an attempt to engen - der more

The Air Force Needs to Improve Cost-Effectiveness and Availability of the Joint Surveillance Target Attack Radar System (Redacted)

DTIC Science & Technology

2016-11-01

Target Attack Radar System Objective We determined whether the Air Force made cost-effective purchases on the performance-based logistics contract to... contract to Northrop Grumman Corporation to provide Total System Support Responsibility services to sustain 16 E-8C JSTARS aircraft. These services...customer support. The Total System Support Responsibility contract is valued at $7 billion, with a 6-year base period and 16 annual contract option

KSC-2010-5717

NASA Image and Video Library

2010-11-17

CAPE CANAVERAL, Fla. -- Kennedy Space Center Deputy Director Janet Petro addresses attendees of the American Astronautical Society's 2010 National Conference held at the Radisson Resort at the Port in Cape Canaveral, Fla. This year's conference was titled: International Space Station: The Next Decade - Utilization and Research. The conference was organized with the support of Kennedy and sponsored by The Boeing Company, Honeywell International Inc., Northrop Grumman Corp., Space Florida and the Universities Space Research Association (USRA). Photo credit: NASA/Jim Grossmann

KSC-2010-5716

NASA Image and Video Library

2010-11-17

CAPE CANAVERAL, Fla. -- Kennedy Space Center Deputy Director Janet Petro addresses attendees of the American Astronautical Society's 2010 National Conference held at the Radisson Resort at the Port in Cape Canaveral, Fla. This year's conference was titled: International Space Station: The Next Decade - Utilization and Research. The conference was organized with the support of Kennedy and sponsored by The Boeing Company, Honeywell International Inc., Northrop Grumman Corp., Space Florida and the Universities Space Research Association (USRA). Photo credit: NASA/Jim Grossmann

Research pilot Fred Haise

NASA Image and Video Library

1966-04-07

Fred W. Haise Jr. was a research pilot and an astronaut for the National Aeronautics and Space Administration from 1959 to 1979. He began flying at the Lewis Research Center in Cleveland, Ohio (today the Glenn Research Center), in 1959. He became a research pilot at the NASA Flight Research Center (FRC), Edwards, Calif., in 1963, serving NASA in that position for three years until being selected to be an astronaut in 1966 His best-known assignment at the FRC (later redesignated the Dryden Flight Research Center) was as a lifting body pilot. Shortly after flying the M2-F1 on a car tow to about 25 feet on April 22, 1966, he was assigned as an astronaut to the Johnson Space Center in Houston, Texas. While at the FRC he had also flown a variety of other research and support aircraft, including the variable-stability T-33A to simulate the M2-F2 heavyweight lifting body, some light aircraft including the Piper PA-30 to evaluate their handling qualities, the Apache helicopter, the Aero Commander, the Cessna 310, the Douglas F5D, the Lockheed F-104 and T-33, the Cessna T-37, and the Douglas C-47. After becoming an astronaut, Haise served as a backup crewmember for the Apollo 8, 11, and 16 missions. He flew on the aborted Apollo 13 lunar mission in 1970, spending 142 hours and 54 minutes in space before returning safely to Earth. In 1977, he was the commander of three free flights of the Space Shuttle prototype Enterprise when it flew its Approach and Landing Tests at Edwards Air Force Base, Calif. Meanwhile, from April 1973 to January 1976, Haise served as the Technical Assistant to the Manager of the Space Shuttle Orbiter Project. In 1979, he left NASA to become the Vice President for Space Programs with the Grumman Aerospace Corporation. He then served as President of Grumman Technical Services, an operating division of Northrop Grumman Corporation, from January 1992 until his retirement. Haise was born in Biloxi, Miss., on November 14, 1933. He underwent flight traini

NPOESS C3S Expandability: SafetyNetTM and McMurdo Improvements

NASA Astrophysics Data System (ADS)

Jamilkowski, M. L.; Paciaroni, J.; Pela, F.

2010-12-01

The National Oceanic & Atmospheric Administration (NOAA), Department of Defense (DoD), and National Aeronautics & Space Administration (NASA) are jointly acquiring the next-generation weather & environmental satellite system; the National Polar-orbiting Operational Environmental Satellite System (NPOESS). NPOESS replaces the current NOAA Polar-orbiting Operational Environmental Satellites (POES) and Dod's Defense Meteorological Satellite Program (DMSP). The NPOESS satellites carry a suite of sensors that collect meteorological, oceanographic, climatological, and solar-geophysical observations of the earth, atmosphere, and space. The command & telemetry portion of NPOESS is the Command, Control and Communications Segment (C3S), developed by Raytheon Intelligence & Information Systems. C3S is responsible for managing the overall NPOESS mission from control and status of the space and ground assets to ensuring delivery of timely, high quality data from the Space Segment (SS) to the Interface Data Processing Segment (IDPS) for processing. In addition, the C3S provides the globally distributed ground assets necessary to collect and transport mission, telemetry, and command data between the satellites and the processing locations. The C3S provides all functions required for day-to-day commanding & state-of-health monitoring of the NPP & NPOESS satellites, and delivery of Stored Mission Data (SMD) to each US Weather Central Interface Data Processor (IDP) for data products development and transfer to System subscribers. The C3S also monitors and reports system-wide health and status & data communications with external systems and between NPOESS segments. Two crucial elements of NPOESS C3S expandability are SafetyNetTM and communications improvements to McMurdo Station, Antarctica. SafetyNetTM is a key feature of NPOESS and a vital element of the C3S and Northrop Grumman Aerospace Systems patented data collection architecture. The centerpiece of SafetyNetTM is the system of fifteen globally-distributed ground receptors developed by Raytheon Company. These antennae will collect up to five times as much environmental data approximately four times faster than current polar-orbiting weather satellites. Once collected, these data will be forwarded near-instantaneously to US weather centrals via the global fiber optic network for processing in environmental prediction models. In January 2008, Raytheon Company achieved a significant milestone for the NPOESS program by successfully completing the first phase of a major communications upgrade for Antarctica. The upgrade of the off-continent satellite communications link at McMurdo Station more than tripled the bandwidth available for scientific research, weather prediction, and health & safety of those stationed at McMurdo. The project is part of the company’s C3S under development for NPOESS. This upgrade paves the way for a second major communications upgrade planned for 2012 in preparation for the use of McMurdo Station as one of the 15 NPOESS ground stations worldwide that will be receiving environmental data collected by the NPOESS satellites. SafetyNet is a trademark of Northrop Grumman Aerospace Systems.

Market Dominance, Efficiency, Innovation, and Globalization: A Case Study of the Tanker Competition Between Boeing and Northrop Grumman/EADS

DTIC Science & Technology

2008-04-23

corporate practices in the post- Enron world, to more up-to- date and open government procurement practices. These trends have resulted in the coalescence of...significant risks to the global community • Shift toward more transparent processes both in corporate practices in the post- Enron world and in government ...is losing its traditional edge; and (d) the desire to have an open and fair government procurement process in which all parties are able to

Navy-Marine Corps Amphibious and Maritime Prepositioning Ship Programs: Background and Oversight Issues for Congress

DTIC Science & Technology

2007-06-12

up Northrop Grumman Ship Systems ( NGSS ). Table 2. FY2008-FY2013 Amphibious and MPF(F) Ship Procurement Plan (Ships fully funded in FY2006 shown for... Plan . . 13 Navy-Marine Corps Amphibious and Maritime Prepositioning Ship Programs: Background and Oversight Issues for Congress Introduction The...is whether to approve, modify, or reject the Navy’s plans for procuring amphibious and MPF(F) ships. Decisions that Congress makes on this CRS-2 1 The

Navy LPD-17 Amphibious Ship Procurement: Background, Issues, and Options for Congress

DTIC Science & Technology

2008-11-21

PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES...optimal construction sequence and application of lessons learned for follow-on vessels in these programs. In the LPD 17 program, the Navy’s reliance on an...I am deeply concerned about Northrop Grumman Ship Systems’ ( NGSS ) ability to recover in the aftermath of Hurricane Katrina, particularly in regard to

Navy LPD-17 Amphibious Ship Procurement: Background, Issues, and Options for Congress

DTIC Science & Technology

2010-10-15

Issues, And Options For Congress 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e . TASK NUMBER 5f...19 has been required, disrupting the optimal construction sequence and application of lessons learned for follow-on vessels in these programs. In...although not necessarily in the order shown below: • “I am deeply concerned about Northrop Grumman Ship Systems’ ( NGSS ) ability to recover in the

Navy MANTECH Fiscal Year 2003 Annual Report

DTIC Science & Technology

2004-03-01

CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING...at five Northrop Grumman Ship Systems ( NGSS ) suppliers Suppliers comprise up to 80% of the cost for the LPD 17. Phase I of this effort received...systems and a " lessons learned" overview. Procurement specialists will have knowledge and experience necessary to be a "smart buyer" of fiber optic

Navy LPD-17 Amphibious Ship Procurement: Background, Issues, and Options for Congress

DTIC Science & Technology

2011-04-20

and Options for Congress 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e . TASK NUMBER 5f...construction sequence and application of lessons learned for follow-on vessels in these programs. In the LPD 17 program, the Navy’s reliance on an immature...deeply concerned about Northrop Grumman Ship Systems’ ( NGSS ) ability to recover in the aftermath of Hurricane Katrina, particularly in regard to

Military Interoperable Digital Hospital Testbed (MIDHT)

DTIC Science & Technology

2013-10-01

activities are selected highlights completed by Northrop Grumman during the year. Cycle 4 development: - Increased the max_allowed_packet size in MySQL ...deployment with the Java install that is required by CONNECT v3.3.1.3. - Updated the MIDHT code base to work with the CONNECT v.3.3.1.3 Core Libraries...Provided TATRC the CONNECTUniversalClientGUI binaries for use with CONNECT v3.3.1.3 − Created and deployed a common Java library for the CONNECT

White Paper on Multicarrier Excitation of Multipactor Breakdown: A Survey of Current Methods and Research Opportunities

DTIC Science & Technology

2015-06-18

CLASSIFICATION TOR-2015-02548 July 31, 2015 UNCLASSIFIED Craig Wesser Northrop Grumman craig.wesser@ngc.com Richard Fink NRO finkrich@nro.mil Marvin LeBlanc...Mark Braun Raytheon mark.j.braun@raytheon.com Marvin Candee Lockheed Martin marvin.candee@lmco.com Larry Capots Lockheed Martin larry.capots@lmco.com...m Debbie Schreiber Lockheed Martin debbie.schreiber@lmco.com C. J. Land Harris cland@harris.com Jim Larosa BAE Systems james.larosa@baesystems.co m

Blinding the Eagle: Potential Loss of Strategic ISR in the 21st Century

DTIC Science & Technology

2016-03-08

being seen by non- 12 radar IMINT sensors. Even thermal crossover can make collection ineffective at times. For an ISR collector icing or severe...allow RQ-4 to utilize the BAE AN/ALQ-221 defensive suite. On the permissive front weather, namely icing , will continue to present a pervasive...2015. http://www.raytheon.com/news/feature/eyes_in_the_sky.html RQ-4 Block 30/40 Global Hawk DataSheet . Northrop Grumman. 29 Senate, An Act

Trends in Retinal Damage Thresholds from 100-Millisecond Near-Infrared Laser Radiation Exposures: A Study at 1,110, 1,130, 1,150, and 1,319 nm

DTIC Science & Technology

2009-01-01

Ste B-100 Directed Energy Bioeffects Division San Antonio, TX 78228 Optical Radiation Branch 2624 Louis Bauer Dr. Brooks City-Base, TX...S) Air Force Research Laboratory Human Effectiveness Directorate Directed Energy Bioeffects Division Optical Radiation Branch 2624 Louis Bauer Dr...Research Laboratory, 711th HPW, Optical Radiation Branch, 2624 Louis Bauer Dr., Brooks City-Base, Texas 78231 3Northrop Grumman, 4241 Woodcock Dr. Ste. B

Historical Remembrances of the Chandra X-ray Observatory: How Partnerships Created Success

NASA Astrophysics Data System (ADS)

Burke, Robert

2009-09-01

As the astronomy community plans for new ventures in space, we're forced to find creative solutions to operate within the ever increasing fiscal constraints of the current economic environment. The Chandra X-ray Observatory program offers an example of how missions can be successfully developed within manageable budget constraints. The ten year anniversary offers us the chance to look back at the Chandra team's special partnership between scientists, managers, and industry that led to our success.Chandra experienced many of the challenges common to major observatories: state-of-the-art technical requirements, budget-induced slips, and restructurings. Yet the Chandra team achieved excellent performance for dramatically lower cost. In fact, Chandra completed its prime mission for billions of dollars less than originally planned. In 1992, NASA MSFC and Northrop Grumman (then TRW) together led a major restructure that saved approximately 3.4B in program cost, while we improved the imaging capability and observing efficiency of Chandra. This was accomplished by a combination of team-work, systems engineering, advanced technology insertion, and effective approaches for program implementation, combined with a high performance culture that aligned goals and focused on mission success. Northrop Grumman is proud of our role in supporting the NASA Marshall Space Flight Center and our academic partners in advancing the frontiers of x-ray astronomy and scientific discovery with Chandra. As Chandra continues its extended mission, the observatory continues to provide superb scientific performance.

Cryogenic optical testing results of JWST aspheric test plate lens

NASA Astrophysics Data System (ADS)

Smith, Koby Z.; Towell, Timothy C.

2011-09-01

The James Webb Space Telescope (JWST) Secondary Mirror Assembly (SMA) is a circular 740mm diameter beryllium convex hyperboloid that has a 23.5nm-RMS (λ/27 RMS) on-orbit surface figure error requirement. The radius of curvature of the SMA is 1778.913mm+/-0.45mm and has a conic constant of -1.6598+/-0.0005. The on-orbit operating temperature of the JWST SMA is 22.5K. Ball Aerospace & Technologies Corp. (BATC) is under contract to Northrop Grumman Aerospace Systems (NGAS) to fabricate, assemble, and test the JWST SMA to its on-orbit requirements including the optical testing of the SMA at its cryogenic operating temperature. BATC has fabricated and tested an Aspheric Test Plate Lens (ATPL) that is an 870mm diameter fused silica lens used as the Fizeau optical reference in the ambient and cryogenic optical testing of the JWST Secondary Mirror Assembly (SMA). As the optical reference for the SMA optical test, the concave optical surface of the ATPL is required to be verified at the same 20K temperature range required for the SMA. In order to meet this objective, a state-of-the-art helium cryogenic testing facility was developed to support the optical testing requirements of a number of the JWST optical testing needs, including the ATPL and SMA. With the implementation of this cryogenic testing facility, the ATPL was successfully cryogenically tested and performed to less than 10nm-RMS (λ/63 RMS) surface figure uncertainty levels for proper reference backout during the SMA optical testing program.

Overview of the James Webb Space Telescope observatory

NASA Astrophysics Data System (ADS)

Clampin, Mark

2011-09-01

The James Webb Space Telescope (JWST) is a large aperture, space telescope designed to provide imaging and spectroscopy over the near and mid-infrared from 1.0 μm to 28 μm. JWST is a passively cooled infrared telescope, employing a five layer sunshield to achieve an operating temperature of ~40 K. JWST will be launched to an orbit at L2 aboard an Ariane 5 launcher in 2013. The Goddard Space Flight Center (GSFC) is the lead center for the JWST program and manages the project for NASA. The prime contractor for JWST is Northrop Grumman Aerospace Systems (NGST). JWST is an international partnership with the European Space Agency (ESA), and the Canadian Space Agency (CSA). ESA will contribute the Ariane 5 launch, and a multi-object infrared spectrograph. CSA will contribute the Fine Guidance Sensor (FGS), which includes the Tunable Filter Imager (TFI). A European consortium, in collaboration with the Jet Propulsion Laboratory (JPL), builds the mid-infrared imager (MIRI). In this paper we present an overview of the JWST science program, and discuss recent progress in the development of the observatory. In this paper we will discuss the scientific motivations for JWST, and discuss recent progress in the construction of the observatory, focusing on the telescope and its optics, which have recently completed polishing.

Grumman and SDI-related technology

DOE Office of Scientific and Technical Information (OSTI.GOV)

Lewis, B.

1985-01-01

The application of Grumman Corporation's aerospace and nuclear fusion technology to the Strategic Defense Initiative (SDI) program has taken place in at least five major areas. These include infrared boost surveillance and tracking to detect intercontinental ballistic missiles just after launch, space-based radar, neutral particle beam platforms, nuclear electric power and propulsion units in space, and battle management systems. The author summarizes developments in each of these areas to illustrate how Grumman has responded to the request that the scientific and industrial communities pursue innovative, high-risk concepts involving materials, structures, space power, space physics, and kinetic energy weapon concepts. 3more » figures.« less

X-ray Cryogenic Facility (XRCF) Handbook

NASA Technical Reports Server (NTRS)

Kegley, Jeffrey R.

2016-01-01

The X-ray & Cryogenic Facility (XRCF) Handbook is a guide for planning operations at the facility. A summary of the capabilities, policies, and procedures is provided to enhance project coordination between the facility user and XRCF personnel. This handbook includes basic information that will enable the XRCF to effectively plan and support test activities. In addition, this handbook describes the facilities and systems available at the XRCF for supporting test operations. 1.2 General Facility Description The XRCF was built in 1989 to meet the stringent requirements associated with calibration of X-ray optics, instruments, and telescopes and was subsequently modified in 1999 & 2005 to perform the challenging cryogenic verification of Ultraviolet, Optical, and Infrared mirrors. These unique and premier specialty capabilities, coupled with its ability to meet multiple generic thermal vacuum test requirements for large payloads, make the XRCF the most versatile and adaptable space environmental test facility in the Agency. XRCF is also recognized as the newest, most cost effective, most highly utilized facility in the portfolio and as one of only five NASA facilities having unique capabilities. The XRCF is capable of supporting and has supported missions during all phases from technology development to flight verification. Programs/projects that have benefited from XRCF include Chandra, Solar X-ray Imager, Hinode, and James Webb Space Telescope. All test programs have been completed on-schedule and within budget and have experienced no delays due to facility readiness or failures. XRCF is currently supporting Strategic Astrophysics Technology Development for Cosmic Origins. Throughout the years, XRCF has partnered with and continues to maintain positive working relationships with organizations such as ATK, Ball Aerospace, Northrop Grumman Aerospace, Excelis (formerly Kodak/ITT), Smithsonian Astrophysical Observatory, Goddard Space Flight Center, University of Alabama Huntsville, and more.

Suomi NPP VIIRS spectral characterization: understanding multiple RSR releases

NASA Astrophysics Data System (ADS)

Moeller, Chris; McIntire, Jeff; Schwarting, Tom; Moyer, Dave; Costa, Juliette

2012-09-01

The Suomi National Polar-orbiting Partnership (S-NPP) satellite was successfully launched on October 28, 2011, beginning the on-orbit era of the Visible Infrared Imager Radiometer Suite (VIIRS). In support of atlaunch readiness, VIIRS underwent a rigorous pre-launch test program to characterize its spatial, radiometric, and spectral performance. Spectral measurements, the subject of this paper, were collected during instrument level testing at Raytheon Corp. (summer 2009), and then again in a special spectral test for VisNIR bands during spacecraft level testing at Ball Aerospace and Technologies Corp. (spring 2010). These spectral performance measurements were analyzed by industry (Northrop Grumman, NG) and by the Relative Spectral Response (RSR) subgroup of the Government team, (NASA, Aerospace Corp., MIT/Lincoln Lab, Univ. Wisconsin) leading to releases of the S-NPP VIIRS RSR characterization by both NG and the Government team. The NG RSR analysis was planned to populate the Look-Up-Tables (LUTs) that support the various VIIRS operational products, while the Government team analysis was initially intended as a verification of the NG RSR product as well as an early release RSR characterization for the science community's pre-launch application. While the Government team deemed the NG December 2010 RSR release as acceptable for the "at-launch" RSR characterization during the pre-launch phase, the Government team has now (post-launch checkout phase) recommended for using the NG October 2011 RSR release as an update for the LUTs used in VIIRS SDR and EDR operational processing. Meanwhile the Government team RSR releases remain available to the community for their investigative interests, and may evolve if new understanding of VIIRS spectral performance is revealed in the S-NPP post-launch era.

Beyond G-band : a 235 GHz InP MMIC amplifier

NASA Technical Reports Server (NTRS)

Dawson, Douglas; Samoska, Lorene; Fung, A. K.; Lee, Karen; Lai, Richard; Grundbacher, Ronald; Liu, Po-Hsin; Raja, Rohit

2005-01-01

We present results on an InP monolithic millimeter- wave integrated circuit (MMIC) amplifier having 10-dB gain at 235 GHz. We designed this circuit and fabricated the chip in Northrop Grumman Space Technology's (NGST) 0.07- m InP high electron mobility transistor (HEMT) process. Using a WR3 (220-325 GHz) waveguide vector network analyzer system interfaced to waveguide wafer probes, we measured this chip on-wafer for -parameters. To our knowledge, this is the first time a WR3 waveguide on-wafer measurement system has been used to measure gain in a MMIC amplifier above 230 GHz.

The triumph and decline of the "squares": Grumman Aerospace engineers and production workers in the Apollo era, 1957--1973

NASA Astrophysics Data System (ADS)

Onkst, David Hugh

This dissertation is a social, cultural, and economic history of the men and women of the Grumman Aerospace Company of Bethpage, New York from 1957 through 1973. These "Grummanites" were the engineers and production workers who designed and built the Apollo Lunar Modules that allowed humans to land on the Moon. This study provides unique insights into the impact that the Apollo Program---a large state-initiated and -supported program---had on those "squares," people whom many contemporaries saw as a vital part of mainstream 1960s American society. By the beginning of the Space Age in 1957, Grumman, Long Island's single largest employer, had firmly established a workplace culture of paternalism that Grummanites largely embraced. Company officials believed strongly in worker retention and had established a policy of providing every sort of benefit their employees seemingly desired, including a highly personal and participatory form of management. Many Grummanites had joined the firm during the early years of the Apollo Program because they believed in the promise of permanent employment on exciting projects that would explore the endless frontier of space. But, as many of these mainly self-reliant, individualistic "squares" would bitterly discover, their dedication to Grumman did little to secure their livelihoods during the aerospace industry's early 1970s downsizing; their individual successes were too largely tied to federal spending and declined when Americans grew disenchanted with space exploration. This dissertation demonstrates how the cultural bond of paternalism between aerospace workers and their company unraveled in the 1960s, and then ended in the early 1970s, because of forces within the company, the economy, and the American state. The word "triumph" in this study's title not only applies to Grummanites' triumphs with the Lunar Modules, but also their individual socioeconomic victories. The term "decline" refers to the early 1970s downsizing of more than a third of the Apollo workforce that had made that program a reality. By relying on a wide-range of archival research (including corporate records) and extensive surveys and interviews with Grummanites, this dissertation provides an overview of how Apollo era aerospace workers interacted with the Cold War American state.

Design Review Improvement Recommendations

DTIC Science & Technology

2015-06-18

Anne Ramsey, Harris Corporation Ronald H. Mandel, Lockheed Martin Mark King, Micropac Industries Melanie Berg, NASA Cindy Kohlmiller, Northrop...Donna Potter , SSL ii Executive Summary The aerospace industry continues to experience design escapes that significantly impact program

Development of Advanced High Lift Leading Edge Technology for Laminar Flow Wings

NASA Technical Reports Server (NTRS)

Bright, Michelle M.; Korntheuer, Andrea; Komadina, Steve; Lin, John C.

2013-01-01

This paper describes the Advanced High Lift Leading Edge (AHLLE) task performed by Northrop Grumman Systems Corporation, Aerospace Systems (NGAS) for the NASA Subsonic Fixed Wing project in an effort to develop enabling high-lift technology for laminar flow wings. Based on a known laminar cruise airfoil that incorporated an NGAS-developed integrated slot design, this effort involved using Computational Fluid Dynamics (CFD) analysis and quality function deployment (QFD) analysis on several leading edge concepts, and subsequently down-selected to two blown leading-edge concepts for testing. A 7-foot-span AHLLE airfoil model was designed and fabricated at NGAS and then tested at the NGAS 7 x 10 Low Speed Wind Tunnel in Hawthorne, CA. The model configurations tested included: baseline, deflected trailing edge, blown deflected trailing edge, blown leading edge, morphed leading edge, and blown/morphed leading edge. A successful demonstration of high lift leading edge technology was achieved, and the target goals for improved lift were exceeded by 30% with a maximum section lift coefficient (Cl) of 5.2. Maximum incremental section lift coefficients ( Cl) of 3.5 and 3.1 were achieved for a blown drooped (morphed) leading edge concept and a non-drooped leading edge blowing concept, respectively. The most effective AHLLE design yielded an estimated 94% lift improvement over the conventional high lift Krueger flap configurations while providing laminar flow capability on the cruise configuration.

NPOESS Preparatory Project Validation Program for Ocean Data Products from VIIRS

NASA Astrophysics Data System (ADS)

Arnone, R.; Jackson, J. M.

2009-12-01

The National Polar-orbiting Operational Environmental Satellite Suite (NPOESS) Program, in partnership with National Aeronautical Space Administration (NASA), will launch the NPOESS Preparatory Project (NPP), a risk reduction and data continuity mission, prior to the first operational NPOESS launch. The NPOESS Program, in partnership with Northrop Grumman Aerospace Systems (NGAS), will execute the NPP Validation program to ensure the data products comply with the requirements of the sponsoring agencies. Data from the NPP Visible/Infrared Imager/Radiometer Suite (VIIRS) will be used to produce Environmental Data Records (EDR's) of Ocean Color/Chlorophyll and Sea Surface Temperature. The ocean Cal/Val program is designed to address an “end to end” capability from sensor to end product and is developed based on existing ongoing government satellite ocean remote sensing capabilities that are currently in use with NASA research and Navy and NOAA operational products. Therefore, the plan focuses on the extension of known reliable methods and capabilities currently used with the heritage sensors that will be extended to the NPP and NPOESS ocean product Cal/Val effort. This is not a fully “new” approach but it is designed to be the most reliable and cost effective approach to developing an automated Cal/Val system for VIIRS while retaining highly accurate procedures and protocols. This presentation will provide an overview of the approaches, data and schedule for the validation of the NPP VIIRS Ocean environmental data products.

Navy Tactical Ocean Optical Products from the National Polar-orbiting Operational Environmental Satellite System (NPOESS)

NASA Astrophysics Data System (ADS)

Lyon, P. E.; Arnone, R.

2006-12-01

The Naval Research Laboratory at Stennis Space Center (NRLSSC) is preparing to produce optical products for Naval operations support from the National Polar-orbiting Operational Environmental Satellite System (NPOESS). This effort will leverage existing hardware and software systems in place at NRLSSC which are currently used to produce optical products from current sensors SeaWiFS and MODIS Aqua/Terra. This effort is part of an inter agency collaboration between NASA, NOAA, IPO, NRL and the prime contractor for NPOESS, Northrop Grumman / Raytheon. This poster presents an outline of the NRLSSC's plan for achieving the best possible optical products from NPOESS.

KSC-2010-5721

NASA Image and Video Library

2010-11-17

CAPE CANAVERAL, Fla. -- Senior Vice President and Deputy General Manager of Orbital Sciences Corp. Frank Culbertson Jr. addresses attendees of the American Astronautical Society's 2010 National Conference held at the Radisson Resort at the Port in Cape Canaveral, Fla. as NASA Deputy Associate Administrator of Space Operations Mission Directorate Lynn Cline and Lockheed Martin Information Systems & Global Services Program Director, Therese Thrift look on. This year's conference was titled: International Space Station: The Next Decade - Utilization and Research. The conference was organized with the support of Kennedy and sponsored by The Boeing Company, Honeywell International Inc., Northrop Grumman Corp., Space Florida and the Universities Space Research Association (USRA). Photo credit: NASA/Jim Grossmann

NPOESS Preparatory Project Validation Program for Atmsophere Data Products from VIIRS

NASA Astrophysics Data System (ADS)

Starr, D.; Wong, E.

2009-12-01

The National Polar-orbiting Operational Environmental Satellite Suite (NPOESS) Program, in partnership with National Aeronautical Space Administration (NASA), will launch the NPOESS Preparatory Project (NPP), a risk reduction and data continuity mission, prior to the first operational NPOESS launch. The NPOESS Program, in partnership with Northrop Grumman Aerospace Systems (NGAS), will execute the NPP Validation program to ensure the data products comply with the requirements of the sponsoring agencies. Data from the NPP Visible/Infrared Imager/Radiometer Suite (VIIRS) will be used to produce Environmental Data Records (EDR's) for aerosol and clouds, specifically Aerosol Optical Thickness (AOT), Aerosol Particle Size Parameter (APSP), and Suspended Matter (SM); and Cloud Optical Thickness (COT), Cloud Effective Particle Size (CEPS), Cloud Top Temperature (CTT), Height (CTH) and Pressure (CTP), and Cloud Base Height (CBH). The Aerosol and Cloud EDR Validation Program is a multifaceted effort to characterize and validate these data products. The program involves systematic comparison to heritage data products, e.g., MODIS, and ground-based correlative data, such as AERONET and ARM data products, and potentially airborne field measurements. To the extent possible, the domain is global. The program leverages various investments that have and are continuing to be made by national funding agencies in such resources, as well as the operational user community and the broad Earth science user community. This presentation will provide an overview of the approaches, data and schedule for the validation of the NPP VIIRS Aerosol and Cloud environmental data products.

NASA's F-15B from the Dryden Flight Research Center flew in the supersonic shockwave of a modified U.S. Navy F-5E jet in support of the Shaped Sonic Boom Demonstration (SSBD) project. On Aug. 27, 2003, the F-5 SSBD aircraft demonstrated a method to reduce

NASA Image and Video Library

2003-08-25

NASA's F-15B research testbed jet from NASA's Dryden Flight Research Center flew in the supersonic shockwave of a Northrop Grumman Corp. modified U.S. Navy F-5E jet in support of the Shaped Sonic Boom Demonstration (SSBD) project, which is part of the DARPA's Quiet Supersonic Platform (QSP) program. On Aug. 27, 2003, the F-5 SSBD aircraft demonstrated a method to reduce the intensity of sonic booms.

JWST Full-Scale Model on Display in Germany

NASA Image and Video Library

2010-03-10

JWST Full-Scale Model on Display. A full-scale model of the James Webb Space Telescope was built by the prime contractor, Northrop Grumman, to provide a better understanding of the size, scale and complexity of this satellite. The model is constructed mainly of aluminum and steel, weighs 12,000 lb., and is approximately 80 feet long, 40 feet wide and 40 feet tall. The model requires 2 trucks to ship it and assembly takes a crew of 12 approximately four days. This model has travelled to a few sites since 2005. The photographs below were taken at some of its destinations. The model is pictured here in Munich, Germany Credit: EADS Astrium

JWST Full-Scale Model on Display in Germany

NASA Image and Video Library

2017-12-08

JWST Full-Scale Model on Display. A full-scale model of the James Webb Space Telescope was built by the prime contractor, Northrop Grumman, to provide a better understanding of the size, scale and complexity of this satellite. The model is constructed mainly of aluminum and steel, weighs 12,000 lb., and is approximately 80 feet long, 40 feet wide and 40 feet tall. The model requires 2 trucks to ship it and assembly takes a crew of 12 approximately four days. This model has travelled to a few sites since 2005. The photographs below were taken at some of its destinations. The model is pictured here in Munich, Germany Credit: EADS Astrium

An Overview of the James Webb Space Telescope (JWST) Project

NASA Technical Reports Server (NTRS)

Sabelhaus, Phillip A.

2004-01-01

The JWST project at the GSFC is responsible for the development, launch, operations and science data processing for the James Webb Space Telescope. The JWST project is currently in phase B with its launch scheduled for August 2011. The project is a partnership between NASA, ESA and CSA. The U.S. JWST team is now fully in place with the recent selection of Northrop Grumman Space Technology (NGST) as the prime contractor for the telescope and the Space Telescope Science Institute (STScI) as the mission operations and science data processing lead. This paper will provide an overview of the current JWST architecture and mission status including technology developments and risks.

An Overview of the James Webb Space Telescope (JWST) Project

NASA Technical Reports Server (NTRS)

Sabelhaus, Phillip A.; Campbell, Doug; Clampin, Mark; Decker, John; Greenhouse, Matt; Johns, Alan; Menzel, Mike; Smith, Robert; Sullivan, Pam

2005-01-01

The JWST project at the GSFC is responsible for the development, launch, operations and science data processing for the James Webb Space Telescope. The JWST project is currently in phase B with its launch scheduled for August 2011. The project is a partnership between NASA, ESA and CSA. The U.S. JWST team is now fully in place with the selection of Northrop Grumman Space Technology (NGST) as the prime contractor for the telescope and the Space Telescope Science Institute (STScI) as the mission operations and science data processing lead. This paper will provide an overview of the current JWST architecture and mission status including technology developments and risks.

Nex-Gen Space Observatory

NASA Image and Video Library

2011-10-26

NASA, space science industry and government officials are seen in front of a full-size model of NASA's James Webb Space Telescope at the Maryland Science Center in Baltimore, Wednesday, Oct. 26, 2011. From left, back row are: Dr. John Grunsfeld, former astronaut and Deputy Director, Space Telescope Science Institute (STScI), Baltimore; Jeffrey Grant, VP and General Manager of the Space Systems Division, Northrop Grumman; Van Reiner, President and CEO of the Maryland Science Center, Baltimore and Adam Reiss, recipient of the 2011 Nobel Prize in Physics and professor of astronomy and physics at Johns Hopkins University. In the front row are NASA Deputy Administrator Lori Garver, left, and U.S. Senator Barbara Mikulski (D-Md.). Photo Credit: (NASA/Carla Cioffi)

Common aperture multispectral sensor flight test program

DOE Office of Scientific and Technical Information (OSTI.GOV)

Bird, R.S.; Kaufman, C.S.

1996-11-01

This paper will provide an overview of the Common Aperture Multispectral Sensor (CAMS) Hardware Demonstrator. CAMS is a linescanning sensor that simultaneously collected digital imagery over the Far-IR (8 to 12 {mu}m) and visible spectral (0.55 to 1.1 PM) spectral bands, correlated at the pixel level. CAMS was initially sponsored by the U.S. Naval Air System Commands F/A-18 program office (PMA-265). The current CAMS field tests are under the direction of Northrop-Grumman for the Defense Nuclear Agency (DNA) in support of the Follow-On Open Skies Sensor Evaluation Program (FOSEP) and are scheduled to be conducted in April 1996. 8 figs.,more » 4 tabs.« less

Polymer/Silicate Nanocomposites Used to Manufacture Gas Storage Tanks With Reduced Permeability

NASA Technical Reports Server (NTRS)

Campbell, Sandi G.; Johnston, Chris

2004-01-01

Over the past decade, there has been considerable research in the area of polymer-layered silicate nanocomposites. This research has shown that the dispersion of small amounts of an organically modified layered silicate improves the polymer strength, modulus, thermal stability, and barrier properties. There have been several reports on the dispersion of layered silicates in an epoxy matrix. Potential enhancements to the barrier properties of epoxy/silicate nanocomposites make this material attractive for low permeability tankage. Polymer matrix composites (PMCs) have several advantages for cryogenic storage tanks. They are lightweight, strong, and stiff; therefore, a smaller fraction of a vehicle's potential payload capacity is used for propellant storage. Unfortunately, the resins typically used to make PMC tanks have higher gas permeability than metals. This can lead to hydrogen loss through the body of the tank instead of just at welds and fittings. One approach to eliminate this problem is to build composite tanks with thin metal liners. However, although these tanks provide good permeability performance, they suffer from a substantial mismatch in the coefficient of thermal expansion, which can lead to failure of the bond between the liner and the body of the tank. Both problems could be addressed with polymersilicate nanocomposites, which exhibit reduced hydrogen permeability, making them potential candidates for linerless PMC tanks. Through collaboration with Northrop Grumman and Michigan State University, nanocomposite test tanks were manufactured for the NASA Glenn Research Center, and the helium permeability was measured. An organically modified silicate was prepared at Michigan State University and dispersed in an epoxy matrix (EPON 826/JeffamineD230). The epoxy/silicate nanocomposites contained either 0 or 5 wt% of the organically modified silicate. The tanks were made by filament winding carbon fibers with the nanocomposite resin. Helium permeability was measured by Northrop Grumman, showing that the leak rate/day of the nanocomposite matrix tank was approximately 80-percent less than that of the neat epoxy matrix tank.

Development of the Tropospheric Water Vapor and Cloud ICE (TWICE) Millimeter- and Sub-millimeter Wave Radiometer Instrument for 6U-Class Nanosatellites

NASA Astrophysics Data System (ADS)

Reising, S. C.; Kangaslahti, P.; Schlecht, E.; Bosch-Lluis, X.; Ogut, M.; Padmanabhan, S.; Cofield, R.; Chahat, N.; Brown, S. T.; Jiang, J. H.; Deal, W.; Zamora, A.; Leong, K.; Shih, S.; Mei, G.

2015-12-01

Measurements of upper-tropospheric water vapor and cloud ice at a variety of local times are critically needed to provide information not currently available from microwave sensors in sun-synchronous orbits. Such global measurements would enable increasingly accurate cloud and moisture simulations in global circulation models, improving both climate predictions and knowledge of their uncertainty. In addition, this capability would address the need for measurements of cloud ice particle size distribution and water content in both clean and polluted environments. Complementary measurements of aerosol pollution would allow investigation of its effects on cloud properties and climate. This is particularly important since the uncertainty in the aerosol effect on climate is at least four times as great as the uncertainty in greenhouse gas effects. To address this unmet need, a collaborative team among Colorado State University, Caltech Jet Propulsion Laboratory and Northrop Grumman Corporation is developing and fabricating the Tropospheric Water and Cloud ICE (TWICE) radiometer instrument. TWICE is designed with size, mass, power consumption and downlink data rate compatible with deployment aboard a 6U-Class nanosatellite. TWICE is advancing the state of the art of spaceborne millimeter- and submillimeter-wave radiometers by transitioning from Schottky mixer-based front ends to InP HEMT MMIC low-noise amplifier front ends, substantially reducing the radiometer's mass, volume and power consumption. New low-noise amplifiers and related front-end components are being designed and fabricated by JPL and Northrop Grumman based on InP HEMT MMIC technology up to 670 GHz. The TWICE instrument will provide 16 radiometer channels, including window frequencies near 240, 310 and 670 GHz to perform ice particle sizing and determine total ice water content, as well as four sounding channels each near 118 GHz for temperature sounding and near 183 GHz and 380 GHz for water vapor sounding during nearly all weather conditions, particularly useful in the upper troposphere in the presence of ice clouds.

EC97-43950-2

NASA Image and Video Library

1997-02-25

Bob Cummings, a technician at NASA's Dryden Flight Research Center, Edwards, California, checks out a new "Smart Skin" antenna mounted on the tip of the right vertical fin of Dryden's F/A-18 Systems Research Aircraft. Flight tests of the antenna system demonstrated a five-fold increase in voice communications range and a substantial improvement in the pattern of radiation and quality of transmission compared to the standard dorsal blade antenna on the aircraft. The Smart Skin antenna system was electrically as well as physically connected to the airframe, making the aircraft skin operate as an antenna along with the antenna itself. The concept was developed by TRW Avionics Systems Division and integrated into the F/A-18's vertical fin by Northrop-Grumman Corporation.

Cusp-Gun Sixth-Harmonic Slotted Gyrotron

NASA Astrophysics Data System (ADS)

Stutzman, R. C.; McDermott, D. B.; Hirata Luhmann, Y., Jr.; Gallagher, D. A.; Spencer, T. A.

2000-10-01

A high-harmonic slotted gyrotron has been constructed at UC Davis to be driven by a 70 kV, 3.5 A, axis-encircling electron beam from a Northrop Grumman Cusp gun. The 94 GHz, slotted sixth-harmonic gyrotron is predicted to generate 50 kW with an efficiency of 20%. Using the profile of the adiabatic field reversal from the UC Davis superconducting test-magnet, EGUN simulations predict that an axis-encircling electron beam will be generated with an axial velocity spread of Δ v_z/v_z=10% for the desired velocity ratio of α =v_z/v_z=1.5. The design will also be presented for an 8th-harmonic W-band gyrotron whose magnetic field can be supplied by a lightweight permanent magnet.

JWST Full-Scale Model on Display at GSFC

NASA Image and Video Library

2010-02-26

JWST Full-Scale Model on Display. A full-scale model of the James Webb Space Telescope was built by the prime contractor, Northrop Grumman, to provide a better understanding of the size, scale and complexity of this satellite. The model is constructed mainly of aluminum and steel, weighs 12,000 lb., and is approximately 80 feet long, 40 feet wide and 40 feet tall. The model requires 2 trucks to ship it and assembly takes a crew of 12 approximately four days. This model has travelled to a few sites since 2005. The photographs below were taken at some of its destinations. The model is pictured here in Greenbelt, MD at the NASA Goddard Space Flight Center. Credit: NASA/Goddard Space Flight Center/Pat Izzo

Nex-Gen Space Observatory

NASA Image and Video Library

2011-10-26

U.S. Senator Barbara Mikulski (D-Md.), third from right, cuts the yellow ribbon presenting the James Webb Space Telescope permanent exhibit at the Maryland Science Center on Wednesday, Oct. 26, 2011 in Baltimore. Mikulski is joined by NASA Deputy Administrator Lori Garver, far left; Adam Reiss, recipient of the 2011 Nobel Prize in Physics and professor of astronomy and physics at Johns Hopkins University; Jeffrey Grant, VP and General Manager of the Space Systems Division, Northrop Grumman; Van Reiner, President and CEO of the Maryland Science Center, Baltimore and Dr. John Grunsfeld, former astronaut and Deputy Director, Space Telescope Science Institute (STScI), Baltimore. The Webb telescope will provide images of the first galaxies ever formed and explore planets around distant stars. Photo Credit: (NASA/Carla Cioffi)

The $2000 electric powertrain TRP Project. Baseline program final report, June 22, 1994--January 21, 1996

DOE Office of Scientific and Technical Information (OSTI.GOV)

NONE

1997-01-01

The program objective was to develop and test technologies which improve the Northrop Grumman electric powertrain and lead to the volume production of an electric powertrain with the power, smoothness, and cost of an internal combustion engine. Accomplishments for this program are summarized in the following six topic areas and selected figures are shown: (1) The 100 hp powertrain was commercialized; (2) The Chrysler EPIC minivan was commercialized; (3) The 230 hp powertrain was commercialized; (4) The Blue Bird electric school and commercial buses were commercialized; (5) Related developments were initiated for DoD and energy systems applications; and (6) Severalmore » key powertrain technologies were researched and advanced.« less

Industrial production of RHIC magnets

DOE Office of Scientific and Technical Information (OSTI.GOV)

Anerella, M.D.; Fisher, D.H.; Sheedy, E.

1996-07-01

RHIC 8 cm aperture dipole magnets and quadrupole cold masses are being built for Brookhaven National Laboratory (BNL) by Northrop Grumman Corporation at a production rate of one dipole magnet and two quadrupole cold masses per day. This work was preceded by a lengthy Technology Transfer effort which is described elsewhere. This paper describes the tooling which is being used for the construction effort, the production operations at each workstation, and also the use of trend plots of critical construction parameters as a tool for monitoring performance in production. A report on the improvements to production labor since the startmore » of the programs is also provided. The magnet and cold mass designs, and magnetic test results are described in more detail in a separate paper.« less

Parametric cost estimation for space science missions

NASA Astrophysics Data System (ADS)

Lillie, Charles F.; Thompson, Bruce E.

2008-07-01

Cost estimation for space science missions is critically important in budgeting for successful missions. The process requires consideration of a number of parameters, where many of the values are only known to a limited accuracy. The results of cost estimation are not perfect, but must be calculated and compared with the estimates that the government uses for budgeting purposes. Uncertainties in the input parameters result from evolving requirements for missions that are typically the "first of a kind" with "state-of-the-art" instruments and new spacecraft and payload technologies that make it difficult to base estimates on the cost histories of previous missions. Even the cost of heritage avionics is uncertain due to parts obsolescence and the resulting redesign work. Through experience and use of industry best practices developed in participation with the Aerospace Industries Association (AIA), Northrop Grumman has developed a parametric modeling approach that can provide a reasonably accurate cost range and most probable cost for future space missions. During the initial mission phases, the approach uses mass- and powerbased cost estimating relationships (CER)'s developed with historical data from previous missions. In later mission phases, when the mission requirements are better defined, these estimates are updated with vendor's bids and "bottoms- up", "grass-roots" material and labor cost estimates based on detailed schedules and assigned tasks. In this paper we describe how we develop our CER's for parametric cost estimation and how they can be applied to estimate the costs for future space science missions like those presented to the Astronomy & Astrophysics Decadal Survey Study Committees.

Mass and Performance Estimates for 5 to 1000 kW(e) Nuclear Reactor Power Systems for Space Applications

DTIC Science & Technology

1990-12-01

Albany Street Cambridge, MA 02139 Dave Berwald Grumman Aerospace Corporation MS B20-05 Bethpage, NY 11714 F. Best Assistant Professor Texas A&M... Zielinski U. S. Department of Energy SAN-ACR Division 13333 Broadway Oakland, CA 94612 G. L. Zigler Science & Engineering Associates 6301

JWST Full-Scale Model on Display at Goddard Space Flight Center

NASA Image and Video Library

2010-02-26

JWST Full-Scale Model on Display. A full-scale model of the James Webb Space Telescope was built by the prime contractor, Northrop Grumman, to provide a better understanding of the size, scale and complexity of this satellite. The model is constructed mainly of aluminum and steel, weighs 12,000 lb., and is approximately 80 feet long, 40 feet wide and 40 feet tall. The model requires 2 trucks to ship it and assembly takes a crew of 12 approximately four days. This model has travelled to a few sites since 2005. The photographs below were taken at some of its destinations. The model is pictured here in Greenbelt, MD at the NASA Goddard Space Flight Center. Credit: NASA/Goddard Space Flight Center/Pat Izzo

KSC-2010-5720

NASA Image and Video Library

2010-11-17

CAPE CANAVERAL, Fla. -- SpaceX Vice President of Mission Assurance and Astronaut Safety Ken Bowersox addresses attendees of the American Astronautical Society's 2010 National Conference held at the Radisson Resort at the Port in Cape Canaveral, Fla. Also on stage (left to right) are, NASA Deputy Associate Administrator of Space Operations Mission Directorate Lynn Cline; NASA Program Integration Manager at Johnson Space Center, Jeff Arend; Lockheed Martin Information Systems & Global Services Program Director Therese Thrift and NASA Commercial Resupply Program Deputy Manager at Johnson Space Center Ford Dillon. This year's conference was titled: International Space Station: The Next Decade - Utilization and Research. The conference was organized with the support of Kennedy and sponsored by The Boeing Company, Honeywell International Inc., Northrop Grumman Corp., Space Florida and the Universities Space Research Association (USRA). Photo credit: NASA/Jim Grossmann

A High-Average-Power Free Electron Laser for Microfabrication and Surface Applications

NASA Technical Reports Server (NTRS)

Dylla, H. F.; Benson, S.; Bisognano, J.; Bohn, C. L.; Cardman, L.; Engwall, D.; Fugitt, J.; Jordan, K.; Kehne, D.; Li, Z.;

Editorial Conference Comments by the General Chair

NASA Astrophysics Data System (ADS)

Reed, Robert A.

2017-01-01

The 53rd IEEE Nuclear and Space Radiation Effects Conference (NSREC) was held July 11-15, 2016, at the Oregon Convention Center in Portland; the conference hotel was the Portland Doubletree. The NSREC is recognized as one of the premier international conferences on radiation effects in electronic materials, devices, and systems. The 2016 conference continued this tradition with a strong technical program, a one-day tutorial short course, radiation effects data workshop, industrial exhibit, and meetings for the IEEE Women in Engineering and Young Professionals organizations. The conference was sponsored by the Radiation Effects Committee of the IEEE Nuclear and Plasma Sciences Society (NPSS), and supported by Atmel, BAE Systems, Boeing, Cobham Semiconductor Solutions, Freebird Semiconductor, Honeywell, International Rectifier, Intersil Corporation, Jet Propulsion Laboratory, Northrop Grumman, Southwest Research Institute, and VPT Rad.

Nuclear Magnetic Resonance Used to Quantify the Effect of Pyrolysis Conditions on the Oxidative Stability of Silicon Oxycarbide Ceramics

NASA Technical Reports Server (NTRS)

1996-01-01

This work was undertaken in support of the Low Cost Ceramic Composite Virtual Company, (LC^3), whose members include Northrop Grumman Corporation, AlliedSignal Inc., and Allison Advanced Development Company. LC^3 is a cost-shared effort funded by the Advanced Research Projects Agency (ARPA) and the LC^3 participants to develop a low-cost fabrication methodology for manufacturing ceramic matrix composite structural components. The program, which is being administered by the U.S. Air Force Wright Laboratory Materials Directorate, is focused on demonstrating a ceramic matrix composite turbine seal for a regional aircraft engine. This part is to be fabricated by resin transfer molding of a siloxane polymer into a fiber preform that will be transformed into a ceramic by pyrolytic conversion.

James Webb Space Telescope Status

NASA Technical Reports Server (NTRS)

Mather, John C.

2005-01-01

The James Webb Space Telescope (JWST) is the first deployable infrared to millimeter wave space telescopes. We will describe the progress on JWST and introduce other speakers in the session. The JWST will operate at the Sun-Earth Lagrange point L2, where radiative cooling lowers the telescope and instrument temperatures to about 35 K. It will have an 18-segment beryllium primary mirror with a 25 m2 area fitting inside a 6.6m circumscribed circle, and will provide spectroscopy and imaging over the wavelength range from 0.6 to 28 microns. It is planned for launch in 2011 on an Ariane 5 rocket. The project is a partnership of NASA, ESA, and CSA, and the prime contractor is Northrop Grumman. See http://www.jwst.nasa.gov for more details on JWST.

Science FEST: Preservice Teachers link Math and Science in Astronomy Lessons

NASA Astrophysics Data System (ADS)

DeMuth, N. H.; Kasabian, J.; Hacking, P. B.

2005-12-01

Funded by the National Science Foundation and corporate sponsored by Northrop Grumman, Science FEST (Science for Future Elementary School Teachers) aims to develop the science content and pedagogy for project participants by connecting their college coursework to the science they will eventually teach. Working individually and in pairs, future elementary and secondary school teachers design a comprehensive module in astronomy that is inquiry-based and reflects national and state science standards. Project participants then teach their module in local elementary or middle school classrooms. Science FEST project participants report gaining a deep understanding of the science they are teaching, learning to engage all students to explore science concepts, and reflecting on their teaching and how it can be improved. The project's website can be found at www.science-fest.org.

Wake-up transceivers for structural health monitoring of bridges

NASA Astrophysics Data System (ADS)

Kumberg, T.; Kokert, J.; Younesi, V.; Koenig, S.; Reindl, L. M.

2016-04-01

In this article we present a wireless sensor network to monitor the structural health of a large-scale highway bridge in Germany. The wireless sensor network consists of several sensor nodes that use wake-up receivers to realize latency free and low-power communication. The sensor nodes are either equipped with very accurate tilt sensor developed by Northrop Grumman LITEF GmbH or with a Novatel OEM615 GNSS receiver. Relay nodes are required to forward measurement data to a base station located on the bridge. The base station is a gateway that transmits the local measurement data to a remote server where it can be further analyzed and processed. Further on, we present an energy harvesting system to supply the energy demanding GNSS sensor nodes to realize long term monitoring.

A high-average-power FEL for industrial applications

DOE Office of Scientific and Technical Information (OSTI.GOV)

Dylla, H.F.; Benson, S.; Bisognano, J.

1995-12-31

CEBAF has developed a comprehensive conceptual design of an industrial user facility based on a kilowatt UV (150-1000 nm) and IR (2-25 micron) FEL driven by a recirculating, energy-recovering 200 MeV superconducting radio-frequency (SRF) accelerator. FEL users{endash}CEBAF`s partners in the Laser Processing Consortium, including AT&T, DuPont, IBM, Northrop-Grumman, 3M, and Xerox{endash}plan to develop applications such as polymer surface processing, metals and ceramics micromachining, and metal surface processing, with the overall effort leading to later scale-up to industrial systems at 50-100 kW. Representative applications are described. The proposed high-average-power FEL overcomes limitations of conventional laser sources in available power, cost-effectiveness, tunabilitymore » and pulse structure. 4 refs., 3 figs., 2 tabs.« less

Defining the next generation munitions handler

DOE Office of Scientific and Technical Information (OSTI.GOV)

Cassiday, B.K.; Koury, G.J.; Pin, F.G.

1995-07-01

RHIC 8 cm aperture dipole magnets and quadrupole cold masses are being built for Brookhaven National Laboratory (BNL) by Northrop-Grumman Corporation at a production rate of one dipole magnet and two quadrupole cold masses per day. This work was preceded by a lengthy Technology Transfer effort which is described elsewhere. This paper describes the tooling which is being used for the construction effort, the production operations at each workstation, and also the use of trend plots of critical construction parameters as a tool for monitoring performance in production. A report on the improvements to production labor since the start ofmore » the programs is also provided. The magnet and cold mass designs, and magnetic test results are described in more detail in a separate paper.« less

Proceedings of the IDA (Institute for Defense Analyses) Workshop on Formal Specification and Verification of Ada (Trade Name) (2nd) Held in Alexandria, Virginia on July 23-25, 1985.

DTIC Science & Technology

1985-11-01

2% -N X Mailing Directory U Bernard Abrams ABRAMS@USC-ECLB Grumman Aerospace Corporation Mail Station 001-31T Bethpage, NY 11714 (516) 575-9487 Omar...Aerospace & Comm. Corp. 10440 State Highway 83 Colorado Springs, Colorado 80908 Mark R. Cornwell CORNWELL @NRL-CSS Code 7590 Naval Research Lab Washington...5) Role of the Formal Definition of Ada Bernard Lang, INRIA, no date, 10 pages [6) The Users of a Formal Definition for Ada Bernd Krieg-Brdckner 2

Silver and Gold

NASA Image and Video Library

2017-12-08

Inside NASA's Goddard Space Flight Center's giant clean room in Greenbelt, Md., JWST Optical Engineer Larkin Carey from Ball Aerospace, examines two test mirror segments recently placed on a black composite structure. This black composite structure is called the James Webb Space Telescope's “Pathfinder” and acts as a spine supporting the telescope's primary mirror segments. The Pathfinder is a non-flight prototype. The mirrors were placed on Pathfinder using a robotic arm move that involved highly trained engineers and technicians from Exelis, Northrop Grumman and NASA. "Getting this right is critical to proving we are ready to start assembling the flight mirrors onto the flight structure next summer," said Lee Feinberg, NASA's Optical Telescope Element Manager at NASA Goddard. "This is the first space telescope that has ever been built with a light-weighted segmented primary mirror, so learning how to do this is a groundbreaking capability for not only the Webb telescope but for potential future space telescopes." The James Webb Space Telescope is the successor to NASA's Hubble Space Telescope. It will be the most powerful space telescope ever built. Webb is an international project led by NASA with its partners, the European Space Agency and the Canadian Space Agency. For more information about the Webb telescope, visit: www.jwst.nasa.gov or www.nasa.gov/webb Credit: NASA/Chris Gunn NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

Broadband Characterization of a 100 to 180 GHz Amplifier

NASA Technical Reports Server (NTRS)

Kangaslahti, Pekka; Deal, W. R.; Mei, X. B.; Lai, R.

2007-01-01

Atmospheric science and weather forecasting require measurements of the temperature and humidity vs. altitude. These sounding measurements are obtained at frequencies close to the resonance frequencies of oxygen (118 GHz) and water (183 GHz) molecules. We have characterized a broadband amplifier that will increase the sensitivity of sounding and other instruments at these frequencies. This study demonstrated for the first t1me continuous low noise amplification from 100 to 180 GHz. The measured InP monolithic millimeter-wave Integrated circuit (MMIC) amplifier had more than 18 dB of gain from 100 to 180 GHz and 15 dB of gain up to 220 GHz. This is the widest bandwidth low noise amplifier result at these frequencies to date. The circuit was fabricated in Northrop Grumman Corporation 35 nm InP high electron mobility transistor (HEMT).

First NASA/Industry High-Speed Research Configuration Aerodynamics Workshop

NASA Technical Reports Server (NTRS)

Wood, Richard M. (Editor)

1999-01-01

This publication is a compilation of documents presented at the First NASA/Industry High Speed Research Configuration Aerodynamics Workshop held on February 27-29, 1996 at NASA Langley Research Center. The purpose of the workshop was to bring together the broad spectrum of aerodynamicists, engineers, and scientists working within the Configuration Aerodynamics element of the HSR Program to collectively evaluate the technology status and to define the needs within Computational Fluid Dynamics (CFD) Analysis Methodology, Aerodynamic Shape Design, Propulsion/Airframe Integration (PAI), Aerodynamic Performance, and Stability and Control (S&C) to support the development of an economically viable High Speed Civil Transport (HSCT) aircraft. To meet these objectives, papers were presented by representative from NASA Langley, Ames, and Lewis Research Centers; Boeing, McDonnell Douglas, Northrop-Grumman, Lockheed-Martin, Vigyan, Analytical Services, Dynacs, and RIACS.

Effects of Random Circuit Fabrication Errors on Small Signal Gain and on Output Phase In a Traveling Wave Tube

NASA Astrophysics Data System (ADS)

Rittersdorf, I. M.; Antonsen, T. M., Jr.; Chernin, D.; Lau, Y. Y.

2011-10-01

Random fabrication errors may have detrimental effects on the performance of traveling-wave tubes (TWTs) of all types. A new scaling law for the modification in the average small signal gain and in the output phase is derived from the third order ordinary differential equation that governs the forward wave interaction in a TWT in the presence of random error that is distributed along the axis of the tube. Analytical results compare favorably with numerical results, in both gain and phase modifications as a result of random error in the phase velocity of the slow wave circuit. Results on the effect of the reverse-propagating circuit mode will be reported. This work supported by AFOSR, ONR, L-3 Communications Electron Devices, and Northrop Grumman Corporation.

First NASA/Industry High-Speed Research Configuration Aerodynamics Workshop. Pt. 2

NASA Technical Reports Server (NTRS)

Wood, Richard M. (Editor)

1999-01-01

This publication is a compilation of documents presented at the First NASA Industry High Speed Research Configuration Aerodynamics Workshop held on February 27-29, 1996 at NASA Langley Research Center. The purpose of the workshop was to bring together the broad spectrum of aerodynamicists, engineers, and scientists working within the Configuration Aerodynamics element of the HSR Program to collectively evaluate the technology status and to define the needs within Computational Fluid Dynamics (CFD) Analysis Methodology, Aerodynamic Shape Design, Propulsion/Airframe Integration (PAI), Aerodynamic Performance, and Stability and Control (S&C) to support the development of an economically viable High Speed Civil Transport (HSCT) aircraft. To meet these objectives, papers were presented by representatives from NASA Langley, Ames, and Lewis Research Centers; Boeing, McDonnell Douglas, Northrop-Grumman, Lockheed-Martin, Vigyan, Analytical Services, Dynacs, and RIACS.

First NASA/Industry High-Speed Research Configuration Aerodynamics Workshop. Part 1

NASA Technical Reports Server (NTRS)

Wood, Richard M. (Editor)

1999-01-01

This publication is a compilation of documents presented at the First NASA/Industry High Speed Research Configuration Aerodynamics Workshop held on February 27-29, 1996 at NASA Langley Research Center. The purpose of the workshop was to bring together the broad spectrum of aerodynamicists, engineers, and scientists working within the Configuration Aerodynamics element of the HSR Program to collectively evaluate the technology status and to define the needs within Computational Fluid Dynamics (CFD) Analysis Methodology, Aerodynamic Shape Design, Propulsion/Airframe Integration (PAI), Aerodynamic Performance, and Stability and Control (S&C) to support the development of an economically viable High Speed Civil Transport (HSCT) aircraft. To meet these objectives, papers were presented by representative from NASA Langley, Ames, and Lewis Research Centers; Boeing, McDonnell Douglas, Northrop-Grumman, Lockheed-Martin, Vigyan, Analytical Services, Dynacs, and RIACS.

The magnet system of the Relativistic Heavy Ion Collider (RHIC)

DOE Office of Scientific and Technical Information (OSTI.GOV)

Greene, A.; Anerella, M.; Cozzolino, J.

1995-07-01

The Relativistic Heavy Ion Collider now under construction at Brookhaven National Laboratory (BNL) is a colliding ring accelerator to be completed in 1999. Through collisions of heavy ions it is hoped to observe the creation of matter at extremely high temperatures and densities, similar to what may have occurred in the original ``Big Bang.`` The collider rings will consist of 1740 superconducting magnet elements. Some of elements are being manufactured by industrial partners (Northrop Grumman and Everson Electric). Others are being constructed or assembled at BNL. A description is given of the magnet designs, the plan for manufacturing and testmore » results. In the manufacturing of the magnets, emphasis has been placed on uniformity of their performance and on quality. Results so far indicate that this emphasis has been very successful.« less

The magnet system of the Relativistic Heavy Ion Collider (RHIC)

DOE Office of Scientific and Technical Information (OSTI.GOV)

Greene, A.; Anerella, M.; Cozzolino, J.

1996-07-01

The Relativistic Heavy Ion Collider now under construction at Brookhaven National Laboratory (BNL) is a colliding ring accelerator to be completed in 1999. Through collisions of heavy ions it is hoped to observe the creation of matter at extremely high temperatures and densities, similar to what may have occurred in the original ``Big Bang``. The collider rings will consist of 1,740 superconducting magnet elements. Some of these elements are being manufactured by industrial partners (Northrop Grumman and Everson Electric). Others are being constructed or assembled at BNL. A description is given of the magnet designs, the plan for manufacturing andmore » test results. In the manufacturing of the magnets, emphasis has been placed on uniformity of their performance and on quality. Results so far indicate that this emphasis has been very successful.« less

Preserving Perishables (Dormavac)

NASA Technical Reports Server (NTRS)

1979-01-01

A new commercial product that can preserve perishable commodities for weeks without freezing, so that they can be shipped fresh without the cost of air freight, has been developed by Grumman Corporation, Bethpage, Long Island, New York. The development benefited from the company's experience in developing the environmental control system for the Lunar Module, which delivered Apollo astronauts to the surface of the moon. Called Dormavac, the system provides a commodity-preserving environment within an aluminum container that can be transported by truck, rail or ship. Dormavac creates a cold-but above freezing-environment with high relative humidity and very low air pressure. The saturated air minimizes commodity weight loss and the air is automatically changed several times an hour to flush away odors and harmful gases released by the commodities. According to company literature, Dormavac significantly extends the transportation life of perishables. For example, pork has a normal cold storage life of about seven days, beef two weeks and tomatoes three weeks; with Dormavac, pork remains fresh for three weeks, beef more than six weeks and tomatoes seven weeks or more. Dormavac is manufactured and marketed by Grumman Allied Industries, Woodbury, New York. In developing the system, Grumman Allied drew upon the technological resources of another company subsidiary, Grumman Aerospace. Engineers who had earlier worked on Lunar Module environmental control brought their know-how and experience to the Dormavac development.

Design development of graphite primary structures enables SSTO success

NASA Astrophysics Data System (ADS)

Biagiotti, V. A.; Yahiro, J. S.; Suh, Daniel E.; Hodges, Eric R.; Prior, Donald J.

1997-01-01

This paper describes the development of a graphite composite wing and a graphite composite intertank primary structure for application toward Single-Stage to Orbit space vehicles such as those under development in NASA's X-33/Reusable Launch Vehicle (RLV) Program. The trade study and designs are based on a Rockwell vertical take-off and horizontal landing (VTHL) wing-body RLV vehicle. Northrop Grumman's approach using a building block development technique is described. Composite Graphite/Bismaleimide (Gr/BMI) material characterization test results are presented. Unique intertank and wing composite subcomponent test article designs are described and test results to date are presented. Wing and intertank Full Scale Section Test Article (FSTA) objectives and designs are outlined. Trade studies, supporting building block testing, and FSTA demonstrations combine to develop graphite primary structure composite technology that enables developing X-33/RLV design programs to meet critical SSTO structural weight and operations performance criteria.

[Activities of Goddard Earth Sciences and Technology Center, Maryland University

NASA Technical Reports Server (NTRS)

2003-01-01

The Goddard Space Flight Center (GSFC) is recognized as a world leader in the application of remote sensing and modeling aimed at improving knowledge of the Earth system. The Goddard Earth Sciences Directorate plays a central role in NASA's Earth Observing System and the U.S. Global Change Research Program. Goddard Earth Sciences and Technology (GEST) is organized as a cooperative agreement with the GSFC to promote excellence in the Earth sciences, and is a consortium of universities and corporations (University of Maryland Baltimore County, Howard University, Hampton University, Caelum Research Corporation and Northrop Grumman Corporation). The aim of this new program is to attract and introduce promising students in their first or second year of graduate studies to Oceanography and Earth system science career options through hands-on instrumentation research experiences on coastal processes at NASA's Wallops Flight Facility on the Eastern Shore of Virginia.

Advanced Space Transportation Program (ASTP)

NASA Image and Video Library

2002-10-01

NASA's Marshall Space Flight Center in Huntsville, Alabama, manages the Space Launch Initiative (SLI), NASA's priority developmental program focused on empowering America's leadership in space. SLI includes commercial, higher education, and defense partnerships and contracts to offer widespread participation in both the risk and success of developing our nation's next-generation reusable launch vehicle. This photo depicts an artist's concept of a future second-generation launch vehicle. For the SLI, architecture definition includes all components of the next-generation reusable launch system: Earth-to-orbit vehicles (the Space Shuttle is the first generation earth-to-orbit vehicle), crew transfer vehicles, transfer stages, ground processing systems, flight operations systems, and development of business case strategies. Three contractor teams have each been funded to develop potential second- generation reusable launch system architectures: The Boeing Company of Seal Beach, California; Lockheed Martin Corporation of Denver, Colorado along with a team including Northrop Grumman of El Segundo, California; and Orbital Sciences Corporation of Dulles, Virginia.

Advanced Space Transportation Program (ASTP)

NASA Image and Video Library

2002-10-01

NASA's Marshall Space Flight Center in Huntsville, Alabama, manages the Space Launch Initiative (SLI), NASA's priority developmental program focused on empowering America's leadership in space. SLI includes commercial, higher education and defense partnerships and contracts to offer widespread participation in both the risk and success of developing our nation's next-generation reusable launch vehicle. This photo depicts an artist's concept of a future second-generation launch vehicle during separation of stages. For SLI, architecture definition includes all components of the next-generation reusable launch system: Earth-to-orbit vehicles (the Space Shuttle is the first-generation earth-to-orbit vehicle), crew transfer vehicles, transfer stages, ground processing systems, flight operations systems, and development of business case strategies. Three contractor teams have each been funded to develop potential second generation reusable launch system architectures: The Boeing Company of Seal Beach, California; Lockheed Martin Corporation of Denver, Colorado; a team including Northrop Grumman of El Segundo, California; and Orbital Sciences Corporation of Dulles, Virginia.

The NASA Dryden Flight Research Center Unmanned Aircraft System Service Capabilities

NASA Technical Reports Server (NTRS)

Bauer, Jeff

2007-01-01

Over 60 years of Unmanned Aircraft System (UAS) expertise at the NASA Dryden Flight Research Center are being leveraged to provide capability and expertise to the international UAS community. The DFRC brings together technical experts, UAS, and an operational environment to provide government and industry a broad capability to conduct research, perform operations, and mature systems, sensors, and regulation. The cornerstone of this effort is the acquisition of both a Global Hawk (Northrop Grumman Corporation, Los Angeles, California) and Predator B (General Atomics Aeronautical Systems, Inc., San Diego, California) unmanned aircraft system (UAS). In addition, a test range for small UAS will allow developers to conduct research and development flights without the need to obtain approval from civil authorities. Finally, experts are available to government and industry to provide safety assessments in support of operations in civil airspace. These services will allow developers to utilize limited resources to their maximum capability in a highly competitive environment.

Fluids and Combustion Facility Acoustic Emissions Controlled by Aggressive Low-Noise Design Process

NASA Technical Reports Server (NTRS)

Cooper, Beth A.; Young, Judith A.

2004-01-01

The Fluids and Combustion Facility (FCF) is a dual-rack microgravity research facility that is being developed by Northrop Grumman Information Technology (NGIT) for the International Space Station (ISS) at the NASA Glenn Research Center. As an on-orbit test bed, FCF will host a succession of experiments in fluid and combustion physics. The Fluids Integrated Rack (FIR) and the Combustion Integrated Rack (CIR) must meet ISS acoustic emission requirements (ref. 1), which support speech communication and hearing-loss-prevention goals for ISS crew. To meet these requirements, the NGIT acoustics team implemented an aggressive low-noise design effort that incorporated frequent acoustic emission testing for all internal noise sources, larger-scale systems, and fully integrated racks (ref. 2). Glenn's Acoustical Testing Laboratory (ref. 3) provided acoustical testing services (see the following photograph) as well as specialized acoustical engineering support as part of the low-noise design process (ref. 4).

Adaptive smart wing design for military aircraft: requirements, concepts, and payoffs

NASA Astrophysics Data System (ADS)

Kudva, Jayanth N.; Appa, Kari; Van Way, Craig B.; Lockyer, Allen J.

1995-05-01

New developments in smart structures and materials have made it possible to revisit earlier work in adaptive and flexible wing technology, and remove some of the limitations for technology transition to next-generation aircraft. Research performed by Northrop Grumman, under internal funding, has led to a new program sponsored by ARPA to investigate the application of smart structures and materials technologies to twist and adapt and aircraft wing. Conceptual designs are presented based on state-of-the-art materials, including shape memory alloys, piezoelectrics, and fiber optic sensors for incorporation in a proposed smart wing design. Plans are described to demonstrate proof-of-concept on a prototype 1/10 scale -18 model that will be tested in a wind tunnel for final validation. Highlights of the proposed program are summarized with respect to program objectives, requirements, key concept design features, demonstration testing, and smart wing technology payoffs and risks.

Deformation Measurements of Smart Aerodynamic Surfaces

NASA Technical Reports Server (NTRS)

Fleming, Gary A.; Burner, Alpheus

2005-01-01

Video Model Deformation (VMD) and Projection Moire Interferometry (PMI) were used to acquire wind tunnel model deformation measurements of the Northrop Grumman-built Smart Wing tested in the NASA Langley Transonic Dynamics Tunnel. The F18-E/F planform Smart Wing was outfitted with embedded shape memory alloys to actuate a seamless trailing edge aileron and flap, and an embedded torque tube to generate wing twist. The VMD system was used to obtain highly accurate deformation measurements at three spanwise locations along the main body of the wing, and at spanwise locations on the flap and aileron. The PMI system was used to obtain full-field wing shape and deformation measurements over the entire wing lower surface. Although less accurate than the VMD system, the PMI system revealed deformations occurring between VMD target rows indistinguishable by VMD. This paper presents the VMD and PMI techniques and discusses their application in the Smart Wing test.

SLI Artist's Concept

NASA Technical Reports Server (NTRS)

2002-01-01

NASA's Marshall Space Flight Center in Huntsville, Alabama, manages the Space Launch Initiative (SLI), NASA's priority developmental program focused on empowering America's leadership in space. SLI includes commercial, higher education, and defense partnerships and contracts to offer widespread participation in both the risk and success of developing our nation's next-generation reusable launch vehicle. This photo depicts an artist's concept of a future second-generation launch vehicle. For the SLI, architecture definition includes all components of the next-generation reusable launch system: Earth-to-orbit vehicles (the Space Shuttle is the first generation earth-to-orbit vehicle), crew transfer vehicles, transfer stages, ground processing systems, flight operations systems, and development of business case strategies. Three contractor teams have each been funded to develop potential second- generation reusable launch system architectures: The Boeing Company of Seal Beach, California; Lockheed Martin Corporation of Denver, Colorado along with a team including Northrop Grumman of El Segundo, California; and Orbital Sciences Corporation of Dulles, Virginia.

SLI Artist `s Launch Concept

NASA Technical Reports Server (NTRS)

2002-01-01

NASA's Marshall Space Flight Center in Huntsville, Alabama, manages the Space Launch Initiative (SLI), NASA's priority developmental program focused on empowering America's leadership in space. SLI includes commercial, higher education and defense partnerships and contracts to offer widespread participation in both the risk and success of developing our nation's next-generation reusable launch vehicle. This photo depicts an artist's concept of a future second-generation launch vehicle during launch. For SLI, architecture definition includes all components of the next-generation reusable launch system: Earth-to-orbit vehicles (the Space Shuttle is the first generation earth-to-orbit vehicle), crew transfer vehicles, transfer stages, ground processing systems, flight operations systems, and development of business case strategies. Three contractor teams have each been funded to develop potential second generation reusable launch system architectures: The Boeing Company of Seal Beach, California; Lockheed Martin Corporation of Denver, Colorado along with a team including Northrop Grumman of El Segundo, California; and Orbital Sciences Corporation of Dulles, Virginia.

SLI Artist's Concept-Stage Separation

NASA Technical Reports Server (NTRS)

2002-01-01

NASA's Marshall Space Flight Center in Huntsville, Alabama, manages the Space Launch Initiative (SLI), NASA's priority developmental program focused on empowering America's leadership in space. SLI includes commercial, higher education and defense partnerships and contracts to offer widespread participation in both the risk and success of developing our nation's next-generation reusable launch vehicle. This photo depicts an artist's concept of a future second-generation launch vehicle during separation of stages. For SLI, architecture definition includes all components of the next-generation reusable launch system: Earth-to-orbit vehicles (the Space Shuttle is the first-generation earth-to-orbit vehicle), crew transfer vehicles, transfer stages, ground processing systems, flight operations systems, and development of business case strategies. Three contractor teams have each been funded to develop potential second generation reusable launch system architectures: The Boeing Company of Seal Beach, California; Lockheed Martin Corporation of Denver, Colorado; a team including Northrop Grumman of El Segundo, California; and Orbital Sciences Corporation of Dulles, Virginia.

COMSAC: Computational Methods for Stability and Control. Part 1

NASA Technical Reports Server (NTRS)

Fremaux, C. Michael (Compiler); Hall, Robert M. (Compiler)

2004-01-01

Work on stability and control included the following reports:Introductory Remarks; Introduction to Computational Methods for Stability and Control (COMSAC); Stability & Control Challenges for COMSAC: a NASA Langley Perspective; Emerging CFD Capabilities and Outlook A NASA Langley Perspective; The Role for Computational Fluid Dynamics for Stability and Control:Is it Time?; Northrop Grumman Perspective on COMSAC; Boeing Integrated Defense Systems Perspective on COMSAC; Computational Methods in Stability and Control:WPAFB Perspective; Perspective: Raytheon Aircraft Company; A Greybeard's View of the State of Aerodynamic Prediction; Computational Methods for Stability and Control: A Perspective; Boeing TacAir Stability and Control Issues for Computational Fluid Dynamics; NAVAIR S&C Issues for CFD; An S&C Perspective on CFD; Issues, Challenges & Payoffs: A Boeing User s Perspective on CFD for S&C; and Stability and Control in Computational Simulations for Conceptual and Preliminary Design: the Past, Today, and Future?

Miniature Packaging Concept for LNAs in the 200-300 GHz Range

NASA Technical Reports Server (NTRS)

Samoska, Lorene; Fung, Andy; Varonen, Mikko; Lin, Robert; Peralta, Alejandro; Soria, Mary; Lee, Choonsup; Padmanabhan, Sharmila; Sarkozy, Stephen; Lai, Richard

2016-01-01

In this work, we describe new miniaturized low noise amplifier modules which we developed for incorporation in small-scale satellites or Cubesats, and which exhibit similar or better performance compared to previously reported LNAs in the literature. We have targeted the WR4 (170-260 GHz) and WR3 (220-325 GHz) waveguide bands for the module development. The modules include two different methods of E-plane probes which have been developed for low loss, and stability at high frequencies. MMIC LNAs were also developed for these frequency ranges and fabricated in Northrop Grumman Corporation's 35 nm InP HEMT technology, and we have experimentally verified that noise performance is lower than reported in prior work. The best results include a miniature LNA module with 550K noise at 224 GHz, and a wideband LNA module with 15 dB gain from 230-280 GHz.

Application of smart materials for improved flight performance of military aircraft

DOE Office of Scientific and Technical Information (OSTI.GOV)

Kudva, J.; Appa, K.; Martin, C.

1995-12-31

This paper discusses on-going work under an ARPA/WL contract to Northrop Grumman entitled {open_quotes}Smart Structures and Materials Development - Smart Wing.{close_quotes} The contract addresses the application of smart materials and smart Structures concepts to enhance the aerodynamic and maneuver performance of military aircraft. Various concepts for adaptive wing and control surfaces are being studied. Specifically, (a) wing span-wise twist control using built-in shape- memory alloy torquing mechanism and (b) cambered leading edge and trailing edge control surfaces using hybrid piezoelectric and SMA actuation, are being evaluated for a 20% model of a modem day fighter aircraft. The potential benefits ofmore » the designs include increased lift for short take-offs, improved high-speed maneuverability, and enhanced control surface effectiveness. These benefits will be quantified by testing the sub-scale model in a transonic wind tunnel next year.« less

European agreement on James Webb Space Telescope's Mid-Infrared Instrument (MIRI) signed

NASA Astrophysics Data System (ADS)

2004-06-01

Artist's impression of the JWST hi-res Size hi-res: 1601 kb Credits: ESA Artist's impression of the JWST An artist's impression of the selected design for the JWST spacecraft. Northrop Grumman and Ball Aerospace are the prime contractors for JWST. Artist's impression of the JWST Credits: ESA Artist's impression of the JWST An artist's impression of the selected design for the JWST spacecraft. Northrop Grumman and Ball Aerospace are the prime contractors for JWST. Observing the first light, the James Webb Space Telescope (JWST) will help to solve outstanding questions about our place in the evolving Universe. MIRI, the Mid-Infrared Instrument, is one of the four instruments on board the JWST, the mission scheduled to follow on the heritage of Hubble in 2011. MIRI will be built in cooperation between Europe and the United States (NASA), both equally contributing to its funding. MIRI’s optics, core of the instrument, will be provided by a consortium of European institutes. According to this formal agreement, ESA will manage and co-ordinate the whole development of the European part of MIRI and act as the sole interface with NASA, which is leading the JWST project. This marks a difference with respect to the previous ESA scientific missions. In the past the funding and the development of the scientific instruments was agreed by the participating ESA Member States on the basis of purely informal arrangements with ESA. In this case, the Member States involved in MIRI have agreed on formally guaranteeing the required level of funding on the basis of a multi-lateral international agreement, which still keeps scientists in key roles. Over the past years, missions have become more complex and demanding, and more costly within an ever tighter budget. They also require a more and more specific expertise which is spread throughout the vast European scientific community. As a result, a new management procedure for co-ordination of payload development has become a necessity to secure the successful and timely completion of scientific space projects. ESA’s co-ordination of the MIRI European consortium represents the first time such an approach has been used, which will be applied to the future missions of the ESA long-term Science Programme - the ‘Cosmic Vision’. The technology package for LISA (LTP), an ESA/NASA mission to detect gravitational waves, is already being prepared under the same scheme. Sergio Volonte, ESA Co-ordinator for Astrophysics and Fundamental Physics Missions, comments: “I’m delighted for such an achievement between ESA and its Member States. With MIRI we will start an even more effective co-ordination on developing our scientific instruments, setting a new framework to further enhance their excellence.” Note to Editors The James Webb Space Telescope (JWST), is a partnership between ESA, NASA and the Canadian Space Agency. Formerly known as the Next Generation Space Telescope (NGST), it is due to be launched in August 2011, and it is considered the successor of the NASA/ESA Hubble Space Telescope. It is three times larger and more powerful than its predecessor and it is expected to shed light on the 'Dark Ages of the Universe' by studying the very distant Universe, observing infrared light from the first stars and galaxies that ever emerged. MIRI (Mid-Infrared Camera-Spectrograph) is essential for the study of the old and distant stellar population; regions of obscured star formation; hydrogen emission from previously unthinkable distances; the physics of protostars; and the sizes of ‘Kuiper belt’ objects and faint comets. Further to the contribution to MIRI, Europe through ESA is contributing to JWST with the NIRSPEC (Near-Infrared multi-object Spectrograph) instrument (fully funded and managed by ESA) and, as agreed in principle with NASA, with the Ariane 5 launcher. The ESA financial contribution to JWST will be about 300 million Euros, including the launcher. The European institutions involved in MIRI will contribute about 70 million Euros overall. The European institutions who signed the MIRI agreement with ESA are: the Centre Nationale des Etudes Spatiales (CNES), the Danish Space Research Institute (DSRI), the German Aerospace Centre (DLR), the Spanish Ministerio de Educación y Ciencia (MEC), the Nederlandse Onderzoekschool voor Astronomie (NOVA), the UK Particle Physics and Astronomy Research Council (PPARC) and the Swedish National Space Board (SNSB). Four European countries, Belgium, Denmark, Ireland and Switzerland contribute to MIRI through their participation into ESA’s Scientific Experiment Development programme (PRODEX). This is an optional programme, mainly used by smaller countries, by which they delegate to ESA the management of funding to develop scientific instruments. The delivery to NASA of the MIRI instrument is due for March 2009.

Proceedings of the Shipbuilding Design/Production Integration Workshop held January 18-21, 1981 in Atlanta, Georgia. Volume 1 and 2

DTIC Science & Technology

1981-01-01

Jorud Ralf Ohlin Intershipping Consultants Ltd. Roger Vaughan A&P Appledore Ltd. Paul Wiedenhaefer Grumman Aerospace, Inc. Yoshinobu Ichinose Yukinori...We have high absenteeism which disrupts the flow of production. Our turnover rates are very high , so we don’t have a large pool of experienced...support blocks, etc. Vendor Relations. Both Intershipping and IHI emphasized the impor- tance of good relationships between shipbuilders and vendors

Report on a Cooperative Programme on Active Flutter Suppression,

DTIC Science & Technology

1980-08-01

soufflerie 16 pieds au frilon de is NASA A Langley Field. La maquette et les essais 6taient sous la responsabilitg de is firma Northrop (Fig. 1). Du c...ATLANTIC TREATY ORGANIZATION ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT (ORGANISATION DU TRAITE DE L’ATLANTIQUE NORD) A(ARI) Report No.689 REPORT...power unit was added to the console to provide for start/stop and bypass control of this unit from the wind tunnel control room. THE FLUTTER DETECTOR AND

An Influence Function Method for Predicting Store Aerodynamic Characteristics during Weapon Separation,

DTIC Science & Technology

1981-05-14

8217 AO-Ail 777 GRUMMAN AEROSPACE CORP BETHPAGE NY F/G 20/4 AN INFLUENCE FUNCTION METHOD FOR PREDICTING STORE AERODYNAMIC C--ETCCU) MAY 8 1 R MEYER, A...CENKO, S YARDS UNCLASSIFIED N ’.**~~N**n I EHEEKI j~j .25 Q~4 111110 111_L 5. AN INFLUENCE FUNCTION METHOD FOR PREDICTING STORE AERODYNAMIC...extended to their logical conclusion one is led quite naturally to consideration of an " Influence Function Method" for I predicting store aerodynamic

Artist's concept of Apollo 14 crewmen on their firs traverse of lunar surface

NASA Image and Video Library

1971-01-11

S71-16101 (January 1971) --- A Grumman Aerospace Corporation artist's concept of Apollo 14 crewmen, astronauts Alan B. Shepard Jr., commander, and Edgar D. Mitchell, lunar module pilot, as they set out on their first traverse. Shepard is pulling the Modularized Equipment Transporter (MET) which contains cameras, lunar sample bags, tools and other paraphernalia. Shepard has the Laser Ranging Retro-Reflector (LR-3) in his other hand. Mitchell is carrying the Apollo Lunar Surface Experiments Package (ALSEP) barbell mode.

Furled Starshade Prototype

NASA Image and Video Library

2016-08-09

A furled first prototype starshade developed by NASA's Jet Propulsion Laboratory, shown in technology partner Astro Aerospace/Northrup Grumman's facility in Santa Barbara, California, in 2013. This design shows petals that are more extreme in shape, which properly diffracts starlight for smaller telescopes. For launch, the petals of the starshade will be wrapped around the spacecraft, then unfurled into the familiar flower-like design once in space. As shown by this 66-foot (20-meter) model, starshades can come in many shapes and sizes. http://photojournal.jpl.nasa.gov/catalog/PIA20905

Flight evaluation of advanced controls and displays for transition and landing on the NASA V/STOL systems research aircraft

NASA Technical Reports Server (NTRS)

Franklin, James A.; Stortz, Michael W.; Borchers, Paul F.; Moralez, Ernesto, III

1996-01-01

Flight experiments were conducted on Ames Research Center's V/STOL Systems Research Aircraft (VSRA) to assess the influence of advanced control modes and head-up displays (HUD's) on flying qualities for precision approach and landing operations. Evaluations were made for decelerating approaches to hover followed by a vertical landing and for slow landings for four control/display mode combinations: the basic YAV-8B stability augmentation system; attitude command for pitch, roll, and yaw; flightpath/acceleration command with translational rate command in the hover; and height-rate damping with translational-rate command. Head-up displays used in conjunction with these control modes provided flightpath tracking/pursuit guidance and deceleration commands for the decelerating approach and a mixed horizontal and vertical presentation for precision hover and landing. Flying qualities were established and control usage and bandwidth were documented for candidate control modes and displays for the approach and vertical landing. Minimally satisfactory bandwidths were determined for the translational-rate command system. Test pilot and engineer teams from the Naval Air Warfare Center, the Boeing Military Airplane Group, Lockheed Martin, McDonnell Douglas Aerospace, Northrop Grumman, Rolls-Royce, and the British Defense Research Agency participated in the program along with NASA research pilots from the Ames and Lewis Research Centers. The results, in conjunction with related ground-based simulation data, indicate that the flightpath/longitudinal acceleration command response type in conjunction with pursuit tracking and deceleration guidance on the HUD would be essential for operation to instrument minimums significantly lower than the minimums for the AV-8B. It would also be a superior mode for performing slow landings where precise control to an austere landing area such as a narrow road is demanded. The translational-rate command system would reduce pilot workload for demanding vertical landing tasks aboard ship and in confined land-based sites.

Venus Atmospheric Maneuverable Platform (VAMP) - A Low Cost Venus Exploration Concept

NASA Astrophysics Data System (ADS)

Lee, G.; Polidan, R. S.; Ross, F.

2015-12-01

The Northrop Grumman Aerospace Systems and L-Garde team has been developing an innovative mission concept: a long-lived, maneuverable platform to explore the Venus upper atmosphere. This capability is an implementation of our Lifting Entry Atmospheric Flight (LEAF) system concept, and the Venus implementation is called the Venus Atmospheric Maneuverable Platform (VAMP). The VAMP concept utilizes an ultra-low ballistic coefficient (< 50 Pa), semi-buoyant aircraft that deploys prior to entering the Venus atmosphere, enters without an aeroshell, and provides a long-lived (months to a year) maneuverable vehicle capable of carrying science instruments to explore the Venus upper atmosphere. In this presentation we provide an update on the air vehicle design and a low cost pathfinder mission concept that can be implemented in the near-term. The presentation also provides an overview of our plans for future trade studies, analyses, and prototyping to advance and refine the concept. We will discuss the air vehicle's entry concepts of operations (CONOPs) and atmospheric science operations. We will present a strawman concept of a VAMP pathfinder, including ballistic coefficient, planform area, percent buoyancy, wing span, vehicle mass, power supply, propulsion, materials considerations, structural elements, and instruments accommodation. In this context, we will discuss the following key factors impacting the design and performance of VAMP: Entry into the Venus atmosphere, including descent profile, heating rate, total heat load, stagnation, and acreage temperatures Impact of maximum altitude on air vehicle design and entry heating Candidate thermal protection system (TPS) requirements We will discuss the interdependencies of the above factors and the manner in which the VAMP pathfinder concept's characteristics affect the CONOPs and the science objectives. We will show how the these factors provide constraints as well as enable opportunities for novel long duration scientific studies of the Venus upper atmosphere that support Venus science goals. We will also discuss how the VAMP platform itself can facilitate some of these science measurements.

Active Flow Control in an Aggressive Transonic Diffuser

NASA Astrophysics Data System (ADS)

Skinner, Ryan W.; Jansen, Kenneth E.

2017-11-01

A diffuser exchanges upstream kinetic energy for higher downstream static pressure by increasing duct cross-sectional area. The resulting stream-wise and span-wise pressure gradients promote extensive separation in many diffuser configurations. The present computational work evaluates active flow control strategies for separation control in an asymmetric, aggressive diffuser of rectangular cross-section at inlet Mach 0.7 and Re 2.19M. Corner suction is used to suppress secondary flows, and steady/unsteady tangential blowing controls separation on both the single ramped face and the opposite flat face. We explore results from both Spalart-Allmaras RANS and DDES turbulence modeling frameworks; the former is found to miss key physics of the flow control mechanisms. Simulated baseline, steady, and unsteady blowing performance is validated against experimental data. Funding was provided by Northrop Grumman Corporation, and this research used resources of the Argonne Leadership Computing Facility, which is a DOE Office of Science User Facility supported under Contract DE-AC02-06CH11357.

Advanced Space Transportation Program (ASTP)

NASA Image and Video Library

2002-10-01

NASA's Marshall Space Flight Center in Huntsville, Alabama, manages the Space Launch Initiative (SLI), NASA's priority developmental program focused on empowering America's leadership in space. SLI includes commercial, higher education, and Defense partnerships and contracts to offer widespread participation in both the risk and success of developing our nation's next-generation reusable launch vehicle. This photo depicts an artist's concept of a future second-generation launch vehicle enroute to the International Space Station. For the SLI, architecture definition includes all components of the next-generation reusable launch system: Earth-to-orbit vehicles (the Space Shuttle is the first generation earth-to-orbit vehicle), crew transfer vehicles, transfer stages, ground processing systems, flight operations systems, and development of business case strategies. Three contractor teams have each been funded to develop potential second-generation reusable launch system architectures: The Boeing Company of Seal Beach, California; Lockheed Martin Corporation of Denver, Colorado along with a team including Northrop Grumman of El Segundo, California; and Orbital Sciences Corporation of Dulles, Virginia.

The NASA Dryden Flight Research Center Unmanned Aircraft System Service Capabilities

NASA Technical Reports Server (NTRS)

Bauer, Jeff

2007-01-01

Over 60 years of Unmanned Aircraft System (UAS) expertise at the National Aeronautics and Space Administration (NASA) Dryden Flight Research Center are being leveraged to provide capability and expertise to the international UAS community. The DFRC brings together technical experts, UAS, and an operational environment to provide government and industry a broad capability to conduct research, perform operations, and mature systems, sensors, and regulation. The cornerstone of this effort is the acquisition of both a Global Hawk (Northrop Grumman Corporation, Los Angeles, California) and Predator B (General Atomics Aeronautical Systems, Inc., San Diego, California) unmanned aircraft system (UAS). In addition, a test range for small UAS will allow developers to conduct research and development flights without the need to obtain approval from civil authorities. Finally, experts are available to government and industry to provide safety assessments in support of operations in civil airspace. These services will allow developers to utilize limited resources to their maximum capability in a highly competitive environment.

Stochastic Methods for Aircraft Design

NASA Technical Reports Server (NTRS)

Pelz, Richard B.; Ogot, Madara

1998-01-01

The global stochastic optimization method, simulated annealing (SA), was adapted and applied to various problems in aircraft design. The research was aimed at overcoming the problem of finding an optimal design in a space with multiple minima and roughness ubiquitous to numerically generated nonlinear objective functions. SA was modified to reduce the number of objective function evaluations for an optimal design, historically the main criticism of stochastic methods. SA was applied to many CFD/MDO problems including: low sonic-boom bodies, minimum drag on supersonic fore-bodies, minimum drag on supersonic aeroelastic fore-bodies, minimum drag on HSCT aeroelastic wings, FLOPS preliminary design code, another preliminary aircraft design study with vortex lattice aerodynamics, HSR complete aircraft aerodynamics. In every case, SA provided a simple, robust and reliable optimization method which found optimal designs in order 100 objective function evaluations. Perhaps most importantly, from this academic/industrial project, technology has been successfully transferred; this method is the method of choice for optimization problems at Northrop Grumman.

Aeroservoelastic and Structural Dynamics Research on Smart Structures Conducted at NASA Langley Research Center

NASA Technical Reports Server (NTRS)

McGowan, Anna-Maria Rivas; Wilkie, W. Keats; Moses, Robert W.; Lake, Renee C.; Florance, Jennifer Pinkerton; Wieseman, Carol D.; Reaves, Mercedes C.; Taleghani, Barmac K.; Mirick, Paul H.; Wilbur, Mathew L.

1997-01-01

An overview of smart structures research currently underway at the NASA Langley Research Center in the areas of aeroservoelasticity and structural dynamics is presented. Analytical and experimental results, plans, potential technology pay-offs, and challenges are discussed. The goal of this research is to develop the enabling technologies to actively and passively control aircraft and rotorcraft vibration and loads using smart devices. These enabling technologies and related research efforts include developing experimentally-validated finite element and aeroservoelastic modeling techniques; conducting bench experimental tests to assess feasibility and understand system trade-offs; and conducting large-scale wind tunnel tests to demonstrate system performance. The key aeroservoelastic applications of this research include: active twist control of rotor blades using interdigitated electrode piezoelectric composites and active control of flutter, and gust and buffeting responses using discrete piezoelectric patches. In addition, NASA Langley is an active participant in the DARPA/Air Force Research Laboratory/NASA/Northrop Grumman Smart Wing program which is assessing aerodynamic performance benefits using smart materials.

Acoustic emission testing on an F/A-18 E/F titanium bulkhead

NASA Astrophysics Data System (ADS)

Martin, Christopher A.; Van Way, Craig B.; Lockyer, Allen J.; Kudva, Jayanth N.; Ziola, Steve M.

1995-04-01

An important opportunity recently transpired at Northrop Grumman Corporation to instrument an F/A - 18 E/F titanium bulkhead with broad band acoustic emission sensors during a scheduled structural fatigue test. The overall intention of this effort was to investigate the potential for detecting crack propagation using acoustic transmission signals for a large structural component. Key areas of experimentation and experience included (1) acoustic noise characterization, (2) separation of crack signals from extraneous noise, (3) source location accuracy, and (4) methods of acoustic transducer attachment. Fatigue cracking was observed and monitored by strategically placed acoustic emission sensors. The outcome of the testing indicated that accurate source location still remains enigmatic for non-specialist engineering personnel especially at this level of structural complexity. However, contrary to preconceived expectations, crack events could be readily separated from extraneous noise. A further dividend from the investigation materialized in the form of close correspondence between frequency domain waveforms of the bulkhead test specimen tested and earlier work with thick plates.

LCROSS - Lunar Impactor: Pioneering Risk-Tolerant Exploration in Search for Water on the Moon

NASA Technical Reports Server (NTRS)

Andrews, Daniel R.

2010-01-01

The Lunar CRater Observation and Sensing Satellite (LCROSS) was launched with the Lunar Reconnaissance Orbiter (LRO) on June 18, 2009 to determine the presence of water-ice in a permanently shadowed crater on the south pole of the Moon. However, an equally important purpose was to pioneer low-cost, quick-turnaround NASA missions that could accept a higher-than-normal-level of technical risk. When the LCROSS mission proposal was competitively selected by the NASA Exploration Systems Mission Directorate to design, build, and launch a spacecraft in 31 months with a $79M cost-capped budget and a fixed mass allocation, NASA Ames Research Center and its industry partner, Northrop-Grumman, needed a game-changing approach to be successful. That approach was a ground-breaking combination of having a risk-tolerant NASA Class D mission status and finding the right balance point between the inflexible elements of cost and schedule and the newly-flexible element of technical capability.

SLI Artist's Concept-Vehicle Enroute to Space Station

NASA Technical Reports Server (NTRS)

2002-01-01

NASA's Marshall Space Flight Center in Huntsville, Alabama, manages the Space Launch Initiative (SLI), NASA's priority developmental program focused on empowering America's leadership in space. SLI includes commercial, higher education, and Defense partnerships and contracts to offer widespread participation in both the risk and success of developing our nation's next-generation reusable launch vehicle. This photo depicts an artist's concept of a future second-generation launch vehicle enroute to the International Space Station. For the SLI, architecture definition includes all components of the next-generation reusable launch system: Earth-to-orbit vehicles (the Space Shuttle is the first generation earth-to-orbit vehicle), crew transfer vehicles, transfer stages, ground processing systems, flight operations systems, and development of business case strategies. Three contractor teams have each been funded to develop potential second-generation reusable launch system architectures: The Boeing Company of Seal Beach, California; Lockheed Martin Corporation of Denver, Colorado along with a team including Northrop Grumman of El Segundo, California; and Orbital Sciences Corporation of Dulles, Virginia.

Reliability of high-power QCW arrays

NASA Astrophysics Data System (ADS)

Feeler, Ryan; Junghans, Jeremy; Remley, Jennifer; Schnurbusch, Don; Stephens, Ed

2010-02-01

Northrop Grumman Cutting Edge Optronics has developed a family of arrays for high-power QCW operation. These arrays are built using CTE-matched heat sinks and hard solder in order to maximize the reliability of the devices. A summary of a recent life test is presented in order to quantify the reliability of QCW arrays and associated laser gain modules. A statistical analysis of the raw lifetime data is presented in order to quantify the data in such a way that is useful for laser system designers. The life tests demonstrate the high level of reliability of these arrays in a number of operating regimes. For single-bar arrays, a MTTF of 19.8 billion shots is predicted. For four-bar samples, a MTTF of 14.6 billion shots is predicted. In addition, data representing a large pump source is analyzed and shown to have an expected lifetime of 13.5 billion shots. This corresponds to an expected operational lifetime of greater than ten thousand hours at repetition rates less than 370 Hz.

Design development of graphite primary structures enables SSTO success

DOE Office of Scientific and Technical Information (OSTI.GOV)

Biagiotti, V.A.; Yahiro, J.S.; Suh, D.E.

1997-01-01

This paper describes the development of a graphite composite wing and a graphite composite intertank primary structure for application toward Single-Stage to Orbit space vehicles such as those under development in NASA{close_quote}s X-33/Reusable Launch Vehicle (RLV) Program. The trade study and designs are based on a Rockwell vertical take-off and horizontal landing (VTHL) wing-body RLV vehicle. Northrop Grumman{close_quote}s approach using a building block development technique is described. Composite Graphite/Bismaleimide (Gr/BMI) material characterization test results are presented. Unique intertank and wing composite subcomponent test article designs are described and test results to date are presented. Wing and intertank Full Scale Sectionmore » Test Article (FSTA) objectives and designs are outlined. Trade studies, supporting building block testing, and FSTA demonstrations combine to develop graphite primary structure composite technology that enables developing X-33/RLV design programs to meet critical SSTO structural weight and operations performance criteria. {copyright} {ital 1997 American Institute of Physics.}« less

High-order space charge effects using automatic differentiation

DOE Office of Scientific and Technical Information (OSTI.GOV)

Reusch, Michael F.; Bruhwiler, David L.; Computer Accelerator Physics Conference Williamsburg, Virginia 1996

1997-02-01

The Northrop Grumman Topkark code has been upgraded to Fortran 90, making use of operator overloading, so the same code can be used to either track an array of particles or construct a Taylor map representation of the accelerator lattice. We review beam optics and beam dynamics simulations conducted with TOPKARK in the past and we present a new method for modeling space charge forces to high-order with automatic differentiation. This method generates an accurate, high-order, 6-D Taylor map of the phase space variable trajectories for a bunched, high-current beam. The spatial distribution is modeled as the product of amore » Taylor Series times a Gaussian. The variables in the argument of the Gaussian are normalized to the respective second moments of the distribution. This form allows for accurate representation of a wide range of realistic distributions, including any asymmetries, and allows for rapid calculation of the space charge fields with free space boundary conditions. An example problem is presented to illustrate our approach.« less

Proceedings of the IDA Workshop on Formal Specification and Verification of Ada (Trade Name) (1st) Held in Alexandria, Virginia on 18-20 March 1985.

DTIC Science & Technology

1985-12-01

on the third day. 5 ADA VERIFICATION WORKSHOP MARCH 18-20, 1985 LIST OF PARTICIPANTS Bernard Abrams ABRAMS@ADA20 Grumman Aerospace Corporation Mail...20301-3081 (202) 694-0211 Mark R. Cornwell CORNWELL @NRL-CSS Code 7590 Naval Research Lab Washington, D.C. 20375 (202) 767-3365 Jeff Facemire FACEMIRE...accompanied by descriptions of their purpose in English, to LUCKHAM@SAIL for annotation. - X-2 DISTRIBUTION LIST FOR M-146 Bernard Abrams ABRAMS@USC-ECLB

Two-Stage, 90-GHz, Low-Noise Amplifier

NASA Technical Reports Server (NTRS)

Samoska, Lorene A.; Gaier, Todd C.; Xenos, Stephanie; Soria, Mary M.; Kangaslahti, Pekka P.; Cleary, Kieran A.; Ferreira, Linda; Lai, Richard; Mei, Xiaobing

2010-01-01

A device has been developed for coherent detection of the polarization of the cosmic microwave background (CMB). A two-stage amplifier has been designed that covers 75-110 GHz. The device uses the emerging 35-nm InP HEMT technology recently developed at Northrop Grumman Corporation primarily for use at higher frequencies. The amplifier has more than 18 dB gain and less than 35 K noise figure across the band. These devices have noise less than 30 K at 100 GHz. The development started with design activities at JPL, as well as characterization of multichip modules using existing InP. Following processing, a test campaign was carried out using single-chip modules at 100 GHz. Successful development of the chips will lead to development of multichip modules, with simultaneous Q and U Stokes parameter detection. This MMIC (monolithic microwave integrated circuit) amplifier takes advantage of performance improvements intended for higher frequencies, but in this innovation are applied at 90 GHz. The large amount of available gain ultimately leads to lower possible noise performance at 90 GHz.

BMI Sandwich Wing Box Analysis and Test

NASA Technical Reports Server (NTRS)

Palm, Tod; Mahler, Mary; Shah, Chandu; Rouse, Marshall; Bush, Harold; Wu, Chauncey; Small, William J.

2000-01-01

A composite sandwich single bay wing box test article was developed by Northrop Grumman and tested recently at NASA Langley Research Center. The objectives for the wing box development effort were to provide a demonstration article for manufacturing scale up of structural concepts related to a high speed transport wing, and to validate the structural performance of the design. The box concept consisted of highly loaded composite sandwich wing skins, with moderately loaded composite sandwich spars. The dimensions of the box were chosen to represent a single bay of the main wing box, with a spar spacing of 30 inches, height of 20 inches constant depth, and length of 64 inches. The bismaleimide facesheet laminates and titanium honeycomb core chosen for this task are high temperature materials able to sustain a 300F service temperature. The completed test article is shown in Figure 1. The tests at NASA Langley demonstrated the structures ability to sustain axial tension and compression loads in excess of 20,000 lb/in, and to maintain integrity in the thermal environment. Test procedures, analysis failure predictions, and test results are presented.

Comparison of Angle of Attack Measurements for Wind Tunnel Testing

NASA Technical Reports Server (NTRS)

Jones, Thomas, W.; Hoppe, John C.

2001-01-01

Two optical systems capable of measuring model attitude and deformation were compared to inertial devices employed to acquire wind tunnel model angle of attack measurements during the sting mounted full span 30% geometric scale flexible configuration of the Northrop Grumman Unmanned Combat Air Vehicle (UCAV) installed in the NASA Langley Transonic Dynamics Tunnel (TDT). The overall purpose of the test at TDT was to evaluate smart materials and structures adaptive wing technology. The optical techniques that were compared to inertial devices employed to measure angle of attack for this test were: (1) an Optotrak (registered) system, an optical system consisting of two sensors, each containing a pair of orthogonally oriented linear arrays to compute spatial positions of a set of active markers; and (2) Video Model Deformation (VMD) system, providing a single view of passive targets using a constrained photogrammetric solution whose primary function was to measure wing and control surface deformations. The Optotrak system was installed for this test for the first time at TDT in order to assess the usefulness of the system for future static and dynamic deformation measurements.

Detection of dim targets in multiple environments

NASA Astrophysics Data System (ADS)

Mirsky, Grace M.; Woods, Matthew; Grasso, Robert J.

2013-10-01

The proliferation of a wide variety of weapons including Anti-Aircraft Artillery (AAA), rockets, and small arms presents a substantial threat to both military and civilian aircraft. To address this ever-present threat, Northrop Grumman has assessed unguided threat phenomenology to understand the underlying physical principles for detection. These principles, based upon threat transit through the atmosphere, exploit a simple phenomenon universal to all objects moving through an atmosphere comprised of gaseous media to detect and track the threat in the presence of background and clutter. Threat detection has rapidly become a crucial component of aircraft survivability systems that provide situational awareness to the crew. It is particularly important to platforms which may spend a majority of their time at low altitudes and within the effective range of a large variety of weapons. Detection of these threats presents a unique challenge as this class of threat typically has a dim signature coupled with a short duration. Correct identification of each of the threat components (muzzle flash and projectile) is important to determine trajectory and intent while minimizing false alarms and maintaining a high detection probability in all environments.

ALMDS laser system

NASA Astrophysics Data System (ADS)

Kushina, Mark E.; Heberle, Geoff; Hope, Michael; Hall, David; Bethel, Michael; Calmes, Lonnie K.

2003-06-01

The ALMDS (Airborne Laser Mine Detection System) has been developed utilizing a solid-state laser operating at 532nm for naval mine detection. The laser system is integrated into a pod that mounts externally on a helicopter. This laser, along with other receiver systems, enables detailed underwater bathymetry. CEO designs and manufactures the laser portion of this system. Arete Associates integrates the laser system into the complete LIDAR package that utilizes sophisticated streak tube detection technology. Northrop Grumman is responsible for final pod integration. The laser sub-system is comprised of two separate parts: the LTU (Laser Transmitter Unit) and the LEU (Laser Electronics Unit). The LTU and LEU are undergoing MIL-STD-810 testing for vibration, shock, temperature storage and operation extremes, as well as MIL-STD-704E electrical power testing and MIL-STD-461E EMI testing. The Nd:YAG MOPA laser operates at 350 Hz pulse repetition frequency at 45 Watts average 532nm power and is controlled at the system level from within the helicopter. Power monitor circuits allow real time laser health monitoring, which enables input parameter adjustments for consistent laser behavior.

DARPA/AFRL/NASA Smart Wing Second Wind Tunnel Test Results

NASA Technical Reports Server (NTRS)

Scherer, L. B.; Martin, C. A.; West, M.; Florance, J. P.; Wieseman, C. D.; Burner, A. W.; Fleming, G. A.

2001-01-01

To quantify the benefits of smart materials and structures adaptive wing technology, Northrop Grumman Corp. (NGC) built and tested two 16% scale wind tunnel models (a conventional and a "smart" model) of a fighter/attack aircraft under the DARPA/AFRL/NASA Smart Materials and Structures Development - Smart Wing Phase 1. Performance gains quantified included increased pitching moment (C(sub M)), increased rolling moment (C(subl)) and improved pressure distribution. The benefits were obtained for hingeless, contoured trailing edge control surfaces with embedded shape memory alloy (SMA) wires and spanwise wing twist effected by SMA torque tube mechanisms, compared to conventional hinged control surfaces. This paper presents an overview of the results from the second wind tunnel test performed at the NASA Langley Research Center s (LaRC) 16ft Transonic Dynamic Tunnel (TDT) in June 1998. Successful results obtained were: 1) 5 degrees of spanwise twist and 8-12% increase in rolling moment utilizing a single SMA torque tube, 2) 12 degrees of deflection, and 10% increase in rolling moment due to hingeless, contoured aileron, and 3) demonstration of optical techniques for measuring spanwise twist and deflected shape.

The "Very Cool" James Webb Space Telescope!

NASA Technical Reports Server (NTRS)

Teague, Peter J. B.

2018-01-01

For over twenty years, scientists, engineers, technicians, and other personnel have been working on the next generation space telescope. As a partnership between NASA (National Aeronautics and Space Administration), CSA (Canadian Space Agency), and ESA (European Space Angency), the James Webb Space Telescope will complement the previous research performed by the Hubble by utilizing a larger primary mirror, which will also be optimized for infrared wavelengths. This combination will allow JWST to collect data and take images of light having traveled over 13.7 billion light years. This presentation will focus on the mission, as well as the contamination control challenges during the integration and testing in the NASA Goddard Spacecraft Systems Development and Integration Facility (SSDIF), one of the largest cleanrooms in the world. Additional information will be presented regarding space simulation testing down to a cool 20 degrees Kelvin [-424 degrees Fahrenheit] that will occur at Johnson Space Center in Houston, TX, and more testing and integration to happen at Northrop Grumman Corp., in Redondo Beach, CA. Launch of the JWST is currently scheduled for the spring of 2019 at Ariane Spaceport in French Guiana, South America.

Coherently coupled high-power fiber arrays

NASA Astrophysics Data System (ADS)

Anderegg, Jesse; Brosnan, Stephen; Cheung, Eric; Epp, Paul; Hammons, Dennis; Komine, Hiroshi; Weber, Mark; Wickham, Michael

2006-02-01

A four-element fiber array has demonstrated 470 watts of coherently phased, linearly polarized light energy in a single far-field spot. Each element consists of a single-mode fiber-amplifier chain. Phase control of each element is achieved with a Lithium-Niobate phase modulator. A master laser provides a linearly polarized, narrow linewidth signal that is split into five channels. Four channels are individually amplified using polarization maintaining fiber power amplifiers. The fifth channel is used as a reference arm. It is frequency shifted and then combined interferometrically with a portion of each channel's signal. Detectors sense the heterodyne modulation signal, and an electronics circuit measures the relative phase for each channel. Compensating adjustments are then made to each channel's phase modulator. This effort represents the results of a multi-year effort to achieve high power from a single element fiber amplifier and to understand the important issues involved in coherently combining many individual elements to obtain sufficient optical power for directed energy weapons. Northrop Grumman Corporation and the High Energy Laser Joint Technology Office jointly sponsored this work.

Linear phase conjugation for atmospheric aberration compensation

NASA Astrophysics Data System (ADS)

Grasso, Robert J.; Stappaerts, Eddy A.

1998-01-01

Atmospheric induced aberrations can seriously degrade laser performance, greatly affecting the beam that finally reaches the target. Lasers propagated over any distance in the atmosphere suffer from a significant decrease in fluence at the target due to these aberrations. This is especially so for propagation over long distances. It is due primarily to fluctuations in the atmosphere over the propagation path, and from platform motion relative to the intended aimpoint. Also, delivery of high fluence to the target typically requires low beam divergence, thus, atmospheric turbulence, platform motion, or both results in a lack of fine aimpoint control to keep the beam directed at the target. To improve both the beam quality and amount of laser energy delivered to the target, Northrop Grumman has developed the Active Tracking System (ATS); a novel linear phase conjugation aberration compensation technique. Utilizing a silicon spatial light modulator (SLM) as a dynamic wavefront reversing element, ATS undoes aberrations induced by the atmosphere, platform motion or both. ATS continually tracks the target as well as compensates for atmospheric and platform motion induced aberrations. This results in a high fidelity, near-diffraction limited beam delivered to the target.

Smart wing wind tunnel test results

NASA Astrophysics Data System (ADS)

Scherer, Lewis B.; Martin, Christopher A.; Appa, Kari; Kudva, Jayanth N.; West, Mark N.

1997-05-01

The use of smart materials technologies can provide unique capabilities in improving aircraft aerodynamic performance. Northrop Grumman built and tested a 16% scale semi-span wind tunnel model of the F/A-18 E/F for the on-going DARPA/WL Smart Materials and Structures-Smart Wing Program. Aerodynamic performance gains to be validated included increase in the lift to drag ratio, increased pitching moment (Cm), increased rolling moment (Cl) and improved pressure distribution. These performance gains were obtained using hingeless, contoured trailing edge control surfaces with embedded shape memory alloy (SMA) wires and spanwise wing twist via a SMA torque tube and are compared to a conventional wind tunnel model with hinged control surfaces. This paper presents an overview of the results from the first wind tunnel test performed at the NASA Langley's 16 ft Transonic Dynamic Tunnel. Among the benefits demonstrated are 8 - 12% increase in rolling moment due to wing twist, a 10 - 15% increase in rolling moment due to contoured aileron, and approximately 8% increase in lift due to contoured flap, and improved pressure distribution due to trailing edge control surface contouring.

DARPA/ARFL/NASA Smart Wing second wind tunnel test results

NASA Astrophysics Data System (ADS)

Scherer, Lewis B.; Martin, Christopher A.; West, Mark N.; Florance, Jennifer P.; Wieseman, Carol D.; Burner, Alpheus W.; Fleming, Gary A.

1999-07-01

To quantify the benefits of smart materials and structures adaptive wing technology. Northrop Grumman Corp. built and tested two 16 percent scale wind tunnel models of a fighter/attach aircraft under the DARPA/AFRL/NASA Smart Materials and Structures Development - Smart Wing Phase 1. Performance gains quantified included increased pitching moment, increased rolling moment and improved pressure distribution. The benefits were obtained for hingeless, contoured trailing edge control surfaces with embedded shape memory alloy wires and spanwise wing twist effected by SMA torque tube mechanism, compared to convention hinged control surfaces. This paper presents an overview of the results from the second wind tunnel test performed at the NASA Langley Research Center's 16 ft Transonic Dynamic Tunnel in June 1998. Successful results obtained were: 1) 5 degrees of spanwise twist and 8-12 percent increase in rolling moment utilizing a single SMA torque tube, 2) 12 degrees of deflection, and 10 percent increase in rolling moment due to hingeless, contoured aileron, and 3) demonstration of optical techniques for measuring spanwise twist and deflected shape.

SCORPION persistent surveillance system with universal gateway

NASA Astrophysics Data System (ADS)

Coster, Michael; Chambers, Jon; Winters, Michael; Belesi, Joe

2008-04-01

This paper addresses benefits derived from the universal gateway utilized in Northrop Grumman Systems Corporation's (NGSC) SCORPION, a persistent surveillance and target recognition system produced by the Xetron campus in Cincinnati, Ohio. SCORPION is currently deployed in Operations Iraqi Freedom (OIF) and Enduring Freedom (OEF). The SCORPION universal gateway is a flexible, field programmable system that provides integration of over forty Unattended Ground Sensor (UGS) types from a variety of manufacturers, multiple visible and thermal electro-optical (EO) imagers, and numerous long haul satellite and terrestrial communications links, including the Army Research Lab (ARL) Blue Radio. Xetron has been integrating best in class sensors with this universal gateway to provide encrypted data exfiltration and remote sensor command and control since 1998. SCORPION data can be distributed point to point, or to multiple Common Operational Picture (COP) systems, including Command and Control Personal Computer (C2PC), Common Data Interchange Format for the Situational Awareness Display (CDIF/SAD), Force XXI Battle Command Brigade and Below (FBCB2), Defense Common Ground Systems (DCGS), and Remote Automated Position Identification System (RAPIDS).

High-order space charge effects using automatic differentiation

DOE Office of Scientific and Technical Information (OSTI.GOV)

Reusch, M.F.; Bruhwiler, D.L.

1997-02-01

The Northrop Grumman Topkark code has been upgraded to Fortran 90, making use of operator overloading, so the same code can be used to either track an array of particles or construct a Taylor map representation of the accelerator lattice. We review beam optics and beam dynamics simulations conducted with TOPKARK in the past and we present a new method for modeling space charge forces to high-order with automatic differentiation. This method generates an accurate, high-order, 6-D Taylor map of the phase space variable trajectories for a bunched, high-current beam. The spatial distribution is modeled as the product of amore » Taylor Series times a Gaussian. The variables in the argument of the Gaussian are normalized to the respective second moments of the distribution. This form allows for accurate representation of a wide range of realistic distributions, including any asymmetries, and allows for rapid calculation of the space charge fields with free space boundary conditions. An example problem is presented to illustrate our approach. {copyright} {ital 1997 American Institute of Physics.}« less

Sampling the Cloudtop Region on Venus

NASA Astrophysics Data System (ADS)

Limaye, Sanjay; Ashish, Kumar; Alam, Mofeez; Landis, Geoffrey; Widemann, Thomas; Kremic, Tibor

2014-05-01

The details of the cloud structure on Venus continue to be elusive. One of the main questions is the nature and identity of the ultraviolet absorber(s). Remote sensing observations from Venus Express have provided much more information about the ubiquitous cloud cover on Venus from both reflected and emitted radiation from Venus Monitoring Camera (VMC) and Visible InfraRed Imaging Spectrometer (VIRTIS) observations. Previously, only the Pioneer Venus Large Probe has measured the size distribution of the cloud particles, and other probes have measured the bulk optical properties of the cloud cover. However, the direct sampling of the clouds has been possible only below about 62 km, whereas the recent Venus Express observations indicate that the cloud tops extend from about 75 km in equatorial region to about 67 km in polar regions. To sample the cloud top region of Venus, other platforms are required. An unmanned aerial vehicle (UAV) has been proposed previously (Landis et al., 2002). Another that is being looked into, is a semi-buoyant aerial vehicle that can be powered using solar cells and equipped with instruments to not only sample the cloud particles, but also to make key atmospheric measurements - e.g. atmospheric composition including isotopic abundances of noble and other gases, winds and turbulence, deposition of solar and infrared radiation, electrical activity. The conceptual design of such a vehicle can carry a much more massive payload than any other platform, and can be controlled to sample different altitudes and day and night hemispheres. Thus, detailed observations of the surface using a miniature Synthetic Aperture Radar are possible. Data relay to Earth will need an orbiter, preferably in a low inclination orbit, depending on the latitude region selected for emphasis. Since the vehicle has a large surface area, thermal loads on entry are low, enabling deployment without the use of an aeroshell. Flight characteristics of such a vehicle have been studied (Alam et al., 2014; Kumar et al., 2014) Acknowledgements Mr. Ashish Kumar and Mr. Mofeez Alam were supported by the Indo US Forum for Science and Technology (IUSSTF) as S.N. Bose Scholars at the University of Wisconsin, Madison as Summer interns. We are grateful for the guidance support provided by Dr. Kristen Griffin and Dr. Daniel Sokol, Northrop Grumman Aerospace Corporation. References Alam, M., K. Ashish, and S.S. Limaye. Aerodynamic Analysis of BlimPlane- a Conceptual Hybrid UAV for Venus Exploration. Accepted for publication, 2014 IEEE Aerospace Conference, Big Sky, Montana, 1-8 March 2014. Ashish, K., M. Alam, and S.S. Limaye, Flight Analysis of a Venus Atmospheric Mobile Platform. Accepted for publication, 2014 IEEE Aerospace Conference, Big Sky, Montana, 1-8 March 2014. Landis, G.A., A. Colozza, C.M. LaMarre, Atmospheric flight on Venus. NASA/TM—2002-211467, AIAA-2001-0819, June 2002

Contributions of the NASA Langley Research Center to the DARPA/AFRL/NASA/ Northrop Grumman Smart Wing Program

NASA Technical Reports Server (NTRS)

Florance, Jennifer P.; Burner, Alpheus W.; Fleming, Gary A.; Martin, Christopher A.

2003-01-01

An overview of the contributions of the NASA Langley Research Center (LaRC) to the DARPA/AFRL/NASA/ Northrop Grumman Corporation (NGC) Smart Wing program is presented. The overall objective of the Smart Wing program was to develop smart** technologies and demonstrate near-flight-scale actuation systems to improve the aerodynamic performance of military aircraft. NASA LaRC s roles were to provide technical guidance, wind-tunnel testing time and support, and Computational Fluid Dynamics (CFD) analyses. The program was divided into two phases, with each phase having two wind-tunnel entries in the Langley Transonic Dynamics Tunnel (TDT). This paper focuses on the fourth and final wind-tunnel test: Phase 2, Test 2. During this test, a model based on the NGC Unmanned Combat Air Vehicle (UCAV) concept was tested at Mach numbers up to 0.8 and dynamic pressures up to 150 psf to determine the aerodynamic performance benefits that could be achieved using hingeless, smoothly-contoured control surfaces actuated with smart materials technologies. The UCAV-based model was a 30% geometric scale, full-span, sting-mounted model with the smart control surfaces on the starboard wing and conventional, hinged control surfaces on the port wing. Two LaRC-developed instrumentation systems were used during the test to externally measure the shapes of the smart control surface and quantify the effects of aerodynamic loading on the deflections: Videogrammetric Model Deformation (VMD) and Projection Moire Interferometry (PMI). VMD is an optical technique that uses single-camera photogrammetric tracking of discrete targets to determine deflections at specific points. PMI provides spatially continuous measurements of model deformation by computationally analyzing images of a grid projected onto the model surface. Both the VMD and PMI measurements served well to validate the use of on-board (internal) rotary potentiometers to measure the smart control surface deflection angles. Prior to the final entry, NASA LaRC also performed three-dimensional unstructured Navier Stokes CFD analyses in an attempt to predict the potential aerodynamic impact of the smart control surface on overall model forces and moments. Eight different control surface shapes were selected for study at Mach = 0.6, Reynolds number = 3.25 x 10(exp 6), and + 2 deg., 3 deg., 8 deg., and 10 deg.model angles-of-attack. For the baseline, undeflected control surface geometry, the CFD predictions and wind-tunnel results matched well. The agreement was not as good for the more complex aero-loaded control surface shapes, though, because of the inability to accurately predict those shapes. Despite these results, the NASA CFD study served as an important step in studying advanced control effectors.

Structural Design and Analysis of the Upper Pressure Shell Section of a Composite Crew Module

NASA Technical Reports Server (NTRS)

Sleight, David W.; Paddock, David; Jeans, Jim W.; Hudeck, John D.

2008-01-01

This paper presents the results of the structural design and analysis of the upper pressure shell section of a carbon composite demonstration structure for the Composite Crew Module (CCM) Project. The project is managed by the NASA Engineering and Safety Center with participants from eight NASA Centers, the Air Force Research Laboratory, and multiple aerospace contractors including ATK/Swales, Northrop Grumman, Lockheed Martin, Collier Research Corporation, Genesis Engineering, and Janicki Industries. The paper discusses details of the upper pressure shell section design of the CCM and presents the structural analysis results using the HyperSizer structural sizing software and the MSC Nastran finite element analysis software. The HyperSizer results showed that the controlling load case driving most of the sizing in the upper pressure shell section was the internal pressure load case. The regions around the cutouts were controlled by internal pressure and the main parachute load cases. The global finite element analysis results showed that the majority of the elements of the CCM had a positive margin of safety with the exception of a few hot spots around the cutouts. These hot spots are currently being investigated with a more detailed analysis. Local finite element models of the Low Impact Docking System (LIDS) interface ring and the forward bay gussets with greater mesh fidelity were created for local sizing and analysis. The sizing of the LIDS interface ring was driven by the drogue parachute loads, Trans-Lunar Insertion (TLI) loads, and internal pressure. The drogue parachute loads controlled the sizing of the gusset cap on the drogue gusset and TLI loads controlled the sizing of the other five gusset caps. The main parachute loads controlled the sizing of the lower ends of the gusset caps on the main parachute fittings. The results showed that the gusset web/pressure shell and gusset web/gusset cap interfaces bonded using Pi-preform joints had local hot spots in the Pi-preform termination regions. These regions require a detailed three-dimensional analysis, which is currently being performed, to accurately address the load distribution near the Pi-preform termination in the upper and lower gusset caps.

Titan LEAF: A Sky Rover Granting Targeted Access to Titan's Lakes and Plains

NASA Astrophysics Data System (ADS)

Ross, Floyd; Lee, Greg; Sokol, Daniel; Goldman, Benjamin; Bolisay, Linden

2016-10-01

Northrop Grumman, in collaboration with L'Garde Inc. and Global Aerospace Corporation (GAC), has been developing the Titan Lifting Entry Atmospheric Flight (T-LEAF) sky rover to roam the atmosphere and observe at close quarters the lakes and plains of Titan. T-LEAF also supports surface exploration and science by providing precision delivery of in situ instruments to the surface.T-LEAF is a maneuverable, buoyant air vehicle. Its aerodynamic shape provides its maneuverability, and its internal helium envelope reduces propulsion power requirements and also the risk of crashing. Because of these features, T-LEAF is not restricted to following prevailing wind patterns. This freedom of mobility allows it be commanded to follow the shorelines of Titan's methane lakes, for example, or to target very specific surface locations.T-LEAF utilizes a variable power propulsion system, from high power at ~200W to low power at ~50W. High power mode uses the propellers and control surfaces for additional mobility and maneuverability. It also allows the vehicle to hover over specific locations for long duration surface observations. Low power mode utilizes GAC's Titan Winged Aerobot (TWA) concept, currently being developed with NASA funding, which achieves guided flight without the use of propellers or control surfaces. Although slower than high powered flight, this mode grants increased power to science instruments while still maintaining control over direction of travel.Additionally, T-LEAF is its own entry vehicle, with its leading edges protected by flexible thermal protection system (f-TPS) materials already being tested by NASA's Hypersonic Inflatable Aerodynamic Decelerator (HIAD) group. This f-TPS technology allows T-LEAF to inflate in space, like HIAD, and then enter the atmosphere fully deployed. This approach accommodates entry velocities from as low as ~1.8 km/s if entering from Titan orbit, up to ~6 km/s if entering directly from Saturn orbit, like the Huygens probe.This presentation will discuss each of these topic areas, showing that a sky rover like T-LEAF is an ideal option for exploration of both the surface and atmosphere of Titan.

NASA Aeronautics Multidisciplinary Analysis and Design Fellowship Program

NASA Technical Reports Server (NTRS)

Grossman, B.; Gurdal, Z.; Kapania, R. K.; Mason, W. H.; Schetz, J. A.

1999-01-01

This program began as a grant from NASA Headquarters, NGT-10025, which was in effect from 10/l/93 until 10/31/96. The remaining funding for this effort was transferred from NASA Headquarters to NASA Langley and a new grant NGT-1-52155 was issued covering the period II/l/96 to 5/15/99. This report serves as the final report of NGT-1-52155. For a number of years, Virginia Tech had been on the forefront of research in the area of multidisciplinary analysis and design. In June of 1994, faculty members from aerospace and ocean engineering, engineering science and mechanics, mechanical engineering, industrial engineering, mathematics and computer sciences, at Virginia Tech joined together to form the Multidisciplinary Analysis and Design (MAD) Center for Advanced Vehicles. The center was established with the single goal: to perform research that is relevant to the needs of the US industry and to foster collaboration between the university, government and industry. In October of 1994, the center was chosen by NASA headquarters as one of the five university centers to establish a fellowship program to develop a graduate program in multidisciplinary analysis and design. The fellowship program provides full stipend and tuition support for seven U. S. students per year during their graduate studies. The grant is currently being administered by the NMO Branch of NASA Langley. To advise us regarding the problems faced by the industry, an industrial advisory board has been formed consisting of representatives from industry as well as government laboratories. The present membership includes major aerospace companies: Aurora Flight Sciences, Boeing: Philadelphia, Boeing: Long Beach, Boeing: Seattle, Boeing: St. Louis, Cessna, Ford, General Electric, Hughes, Lockheed-Martin: Palo Alto, Northrop-Grumman, Sikorsky, smaller, aerospace software companies: Aerosoft, Phoenix Integration and Proteus Engineering, along with representatives from government agencies, including: NASA Ames, Langley and Lewis. The function of the advisory board is to channel information from its member companies to faculty members concerning problems that need research attention in the general area of multidisciplinary design optimization (MDO). The faculty and their graduate students make presentations to the board on their research. The board makes recommendations on the research and suggests new areas and problems which need attention. Many students participating in the program spend 3-6 months in industry working on their research projects. We are completing the fifth year of the fellowship program and have had four advisory board meetings in Blacksburg. Ten students have spent the three month periods in industry. In addition to the research element of the MAD Center efforts we also have an academic component. We have developed a menu of design-related graduate courses and two new courses: one in Aerospace Manufacturing and another in MDO. Some of the MAD Center activities are described on the world-wide web at http://www.aoe.vt.edu/mads.html The MAD Center represents an innovative approach for joint Industry-Government-University cooperation in the development of a comprehensive program in engineering education which addresses the design needs of industry. The following charts list detail of the grant: mission of the MAD center, faculty members, purpose of the advisory board, board members, summary of the graduate and undergraduate program, history of the fellowship program, mission of the fellowship program, requirements of MAD fellows, course requirements, students supported, advisory board participants, and MAD center research papers

Artists concept of Apollo 15 crewmen performing deployment of LRV

NASA Image and Video Library

1971-06-26

S71-38188 (26 June 1971) --- An artist's concept showing the Apollo 15 mission commander and the lunar module pilot performing deployment of the Lunar Roving Vehicle (LRV) on the lunar surface. The figure on the left represents astronaut James B. Irwin, lunar module pilot, who here is maintaining a constant pull on the deployment cable to help the LRV unfold, while astronaut David R. Scott (right), commander, pulls the tapes that lower the LRV to the surface. (This is the third in a series of Grumman Aerospace Corporation artist's concepts telling the lunar surface LRV deployment story of the Apollo 15 mission).

Artists concept of Apollo 15 crewmen performing deployment of LRV

NASA Image and Video Library

1971-06-26

S71-38189 (26 June 1971) --- An artist's concept showing the final steps of readying the Apollo 15 Lunar Roving Vehicle (LRV) or Rover 1 for mobility on the lunar surface. Performing the last few LRV deployment tasks here are, left to right, astronauts James B. Irwin, lunar module pilot, and David R. Scott, commander. More specifically the tasks depicted here include the setting up of the seats and the total releasing of the LRV from the LM. (This is the fourth in a series of four Grumman Aerospace Corporation artist's concepts telling the lunar surface LRV deployment story for Apollo 15).

A low cost, high performance, 1.2m off-axis telescope built with NG-Xinetics silicon carbide

NASA Astrophysics Data System (ADS)

Rey, Justin J.; Wellman, John A.; Egan, Richard G.; Wollensak, Richard J.

2011-09-01

The search for extrasolar habitable planets is one of three major astrophysics priorities identified for the next decade. These missions demand very high performance visible-wavelength optical imaging systems. Such high performance space telescopes are typically extremely expensive and can be difficult for government agencies to afford in today's economic climate, and most lower cost systems offer little benefit because they fall short on at least one of the following three key performance parameters: imaging wavelength, total system-level wavefront error and aperture diameter. Northrop Grumman Xinetics has developed a simple, lightweight, low-cost telescope design that will address the near-term science objectives of this astrophysics theme with the required optical performance, while reducing the telescope cost by an order of magnitude. Breakthroughs in SiC mirror manufacturing, integrated wavefront sensing, and high TRL deformable mirror technology have finally been combined within the same organization to offer a complete end-to-end telescope system in the lower end of the Class D cost range. This paper presents the latest results of real OAP polishing and metrology data, an optimized optical design, and finite element derived WFE

Propulsion Integrated Vehicle Health Management Technology Experiment (PITEX) Conducted

NASA Technical Reports Server (NTRS)

Maul, William A.; Chicatelli, Amy K.; Fulton, Christopher E.

2004-01-01

The Propulsion Integrated Vehicle Health Management (IVHM) Technology Experiment (PITEX) is a continuing NASA effort being conducted cooperatively by the NASA Glenn Research Center, the NASA Ames Research Center, and the NASA Kennedy Space Center. It was a key element of a Space Launch Initiative risk-reduction task performed by the Northrop Grumman Corporation in El Segundo, California. PITEX's main objectives are the continued maturation of diagnostic technologies that are relevant to second generation reusable launch vehicle (RLV) subsystems and the assessment of the real-time performance of the PITEX diagnostic solution. The PITEX effort has considerable legacy in the NASA IVHM Technology Experiment for X-vehicles (NITEX) that was selected to fly on the X-34 subscale RLV that was being developed by Orbital Sciences Corporation. NITEX, funded through the Future-X Program Office, was to advance the technology-readiness level of selected IVHM technologies within a flight environment and to begin the transition of these technologies from experimental status into RLV baseline designs. The experiment was to perform realtime fault detection and isolation and suggest potential recovery actions for the X-34 main propulsion system (MPS) during all mission phases by using a combination of system-level analysis and detailed diagnostic algorithms.

Weapons for the world/update: the U. S. corporate role in International Arms Transfers. [Booklet

DOE Office of Scientific and Technical Information (OSTI.GOV)

Lydenberg, S.

1977-01-01

The substantial growth of American arms exports in recent years has prompted the Council on Economic Priorities to study the role played by U.S. corporations in the sale of U.S. military equipment, training, and services throughout the world. Major findings of this Report include: U.S. arms sales and exports to foreign countries have risen dramatically from $2.9 billion in 1967, to $5 billion in 1971, to $10 to 12 billion annually from 1974 through 1976. Since 1973 a major shift has taken place in the nature of U.S. arms transfers from arms aid under the Military Assistance Program to armsmore » sales under the Foreign Military Sales program. The 10 U.S. corporations (Northrop, McDonnell Douglas, Grumman, Litton, General Electric, Raytheon, FMC, Hughes, Lockheed, and Textron) most extensively involved in U.S. arms exports in 1976 (profiled in this Report) received approximately 30% of their total military business from foreign arms sales. Congress has increased its active participation in U.S. arms-transfer policy through legislation passed in 1975 and 1976. This legislation has extended Congress' control over the Foreign Military Sales program in particular.« less

Aeroservoelastic and Structural Dynamics Research on Smart Structures Conducted at NASA Langley Research Center

NASA Technical Reports Server (NTRS)

McGowan, Anna-Maria Rivas; Wilkie, W. Keats; Moses, Robert W.; Lake, Renee C.; Florance, Jennifer Pinkerton; Wieseman, Carol D.; Reaves, Mercedes C.; Taleghani, Barmac K.; Mirick, Paul H.; Wilbur, Matthew L.

1998-01-01

An overview of smart structures research currently underway at the NASA Langley Research Center in the areas of aeroservoelasticity and structural dynamics is presented. Analytical and experimental results, plans, potential technology pay-offs, and challenges are discussed. The goal of this research is to develop the enabling technologies to actively and passively control aircraft and rotorcraft vibration and loads using smart devices. These enabling technologies and related research efforts include developing experimentally-validated finite element and aeroservoelastic modeling techniques; conducting bench experimental tests to assess feasibility and understand system trade-offs; and conducting large-scale wind- tunnel tests to demonstrate system performance. The key aeroservoelastic applications of this research include: active twist control of rotor blades using interdigitated electrode piezoelectric composites and active control of flutter, and gust and buffeting responses using discrete piezoelectric patches. In addition, NASA Langley is an active participant in the DARPA/ Air Force Research Laboratory/ NASA/ Northrop Grumman Smart Wing program which is assessing aerodynamic performance benefits using smart materials. Keywords: aeroelasticity, smart structures, piezoelectric actuators, active fiber composites, rotorcraft, buffet load alleviation, individual blade control, aeroservoelasticity, shape memory alloys, damping augmentation, piezoelectric power consumption

JWST Full-Scale Model on Display in Orlando

NASA Image and Video Library

2017-12-08

JWST Full-Scale Model on Display. A full-scale model of the James Webb Space Telescope was built by the prime contractor, Northrop Grumman, to provide a better understanding of the size, scale and complexity of this satellite. The model is constructed mainly of aluminum and steel, weighs 12,000 lb., and is approximately 80 feet long, 40 feet wide and 40 feet tall. The model requires 2 trucks to ship it and assembly takes a crew of 12 approximately four days. This model has traveled to a few sites since 2005. The photographs below were taken at some of its destinations. The model was on display at The International Society for Optical Engineering's (SPIE) week-long Astronomical Telescopes and Instrumentations conference,May 25 - 30, 2006. Credit: NASA/Goddard Space Flight Center/Dr Mark Clampin NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

Updates to SCORPION persistent surveillance system with universal gateway

NASA Astrophysics Data System (ADS)

Coster, Michael; Chambers, Jon; Winters, Michael; Brunck, Al

2008-10-01

This paper addresses benefits derived from the universal gateway utilized in Northrop Grumman Systems Corporation's (NGSC) SCORPION, a persistent surveillance and target recognition system produced by the Xetron campus in Cincinnati, Ohio. SCORPION is currently deployed in Operations Iraqi Freedom (OIF) and Enduring Freedom (OEF). The SCORPION universal gateway is a flexible, field programmable system that provides integration of over forty Unattended Ground Sensor (UGS) types from a variety of manufacturers, multiple visible and thermal electro-optical (EO) imagers, and numerous long haul satellite and terrestrial communications links, including the Army Research Lab (ARL) Blue Radio. Xetron has been integrating best in class sensors with this universal gateway to provide encrypted data exfiltration to Common Operational Picture (COP) systems and remote sensor command and control since 1998. In addition to being fed to COP systems, SCORPION data can be visualized in the Common sensor Status (CStat) graphical user interface that allows for viewing and analysis of images and sensor data from up to seven hundred SCORPION system gateways on single or multiple displays. This user friendly visualization enables a large amount of sensor data and imagery to be used as actionable intelligence by a minimum number of analysts.

JWST Town Meeting

NASA Technical Reports Server (NTRS)

Mather, John

2004-01-01

The James Webb Space Telescope (JWST) Science Working Group has published the key scientific study areas for the mission: the end of the dark ages, the assembly of galaxies, the birth of stars and protoplanetary systems, and planetary systems and the origins of life. With these objectives establishing the major scientific capabilities of the observatory, the JWST Project has successfully completed major reviews of the telescope architecture and budget plan and has reached agreement on the contributions for all three international partners (NASA, ESA, and the Canadian Space Agency). Northrop Grumman Space Technologies (NGST) is the prime contractor responsible for the spacecraft, telescope, and integration. GSFC/NASA oversees the development and integration of the science instruments. The Space Telescope Science Institute is developing the JWST Science & Operations Center. The JWST will be launched to L2 2011 using an Ariane V. At this town hall, the mission's Project Scientists will present the technical and scientific status of the mission, concentrating on those areas that have changed over the last year. This will be an excellent opportunity to learn about JWST and catch up on the most recent developments. Questions from the audience will be welcomed. The town hall speakers will be John Mather, Peter Jakobsen, John Hutchings, and Peter Stockman.

Multisensor interoperability for persistent surveillance and FOB protection with multiple technologies during the TNT exercise at Camp Roberts, California

NASA Astrophysics Data System (ADS)

Murarka, Naveen; Chambers, Jon

2012-06-01

Multiple sensors, providing actionable intelligence to the war fighter, often have difficulty interoperating with each other. Northrop Grumman (NG) is dedicated to solving these problems and providing complete solutions for persistent surveillance. In August, 2011, NG was invited to participate in the Tactical Network Topology (TNT) Capabilities Based Experimentation at Camp Roberts, CA to demonstrate integrated system capabilities providing Forward Operating Base (FOB) protection. This experiment was an opportunity to leverage previous efforts from NG's Rotorcraft Avionics Innovation Laboratory (RAIL) to integrate five prime systems with widely different capabilities. The five systems included a Hostile Fire and Missile Warning Sensor System, SCORPION II Unattended Ground Sensor system, Smart Integrated Vehicle Area Network (SiVAN), STARLite Synthetic Aperture Radar (SAR)/Ground Moving Target Indications (GMTI) radar system, and a vehicle with Target Location Module (TLM) and Laser Designation Module (LDM). These systems were integrated with each other and a Tactical Operations Center (TOC) equipped with RaptorX and Falconview providing a Common Operational Picture (COP) via Cursor on Target (CoT) messages. This paper will discuss this exercise, and the lessons learned, by integrating these five prime systems for persistent surveillance and FOB protection.

Lcross Lunar Impactor - Lessons Learned from a Small Satellite Mission

NASA Technical Reports Server (NTRS)

Andrews, Daniel

2010-01-01

The Lunar CRater Observation and Sensing Satellite (LCROSS) launched with the Lunar Reconnaissance Orbiter (LRO) on June 18, 2009. While the science purpose of the LCROSS mission was to determine the presence of water-ice in a permanently-shadowed crater on the moon, the functional purpose was to be a pioneer for future low-cost, risk-tolerant small satellite NASA missions. Recent strategic changes at the Agency level have only furthered the importance of small satellite missions. NASA Ames Research Center and its industry partner, Northrop-Grumman, initiated this spacecraft project two-years after its co-manifest mission had started, with less than one-fifth the budget. With a $79M total cost cap (including operations and reserves) and 31-months until launch, LCROSS needed a game-changing approach to be successful. At the LCROSS Confirmation Review, the ESMD Associate Administrator asked the Project team to keep a close record of lessons learned through the course of the mission and share their findings with the Agency at the end of the mission. This paper summarizes the Project, the mission, its risk position, and some of the more notable lessons learned.

Processing of mercurous chloride in reduced gravity

DOE Office of Scientific and Technical Information (OSTI.GOV)

Watson, C.; Singh, N.; Thomas, A.

1996-12-31

In a joint experiment between the Northrop-Grumman Science and Technology Center and the University of Alabama in Huntsville, Consortium for Materials Development in Space (UAH/CMDS), single crystals of mercurous chloride (Hg{sub 2}Cl{sub 2}) were grown in the Space Experiment Facility (SEF) transparent furnace that was flown on Spacelab 4 (STS-77) in May 1996. Single crystals of this material can be readily grown in normal gravity by closed-tube physical vapor transport, but the crystals generally contain structural inhomogeneities which degrade the optical performance. The nature and cause of these defects are not completely understood, but their degree appears to correlate withmore » the Rayleigh number that characterizes the convective transport during their growth; hence, it is suspected that uncontrolled convection may play a role in the defect structure. The objective of the flight experiment was to reduce the convective flows by several orders of magnitude to see if the structural inhomogeneities can be reduced or eliminated. This paper will describe the physical and thermal properties of the SEF furnace, the ampoule design and loading procedure, and the ground testing, and will also present the preliminary flight results.« less

LCROSS Lunar Impactor - Lessons Learned from a Small Satellite Mission

NASA Technical Reports Server (NTRS)

Andrews, Daniel R.

2010-01-01

The Lunar CRater Observation and Sensing Satellite (LCROSS) launched with the Lunar Reconnaissance Orbiter (LRO) on June 18, 2009. While the science function of the LCROSS mission was to determine the presence of water-ice in a permanently-shadowed crater on the moon, the operational purpose was to be a pioneer for future low-cost, risk-tolerant small satellite NASA missions. Recent strategic changes at the Agency level have only furthered the importance of small satellite missions. NASA Ames Research Center and its industry partner, Northrop-Grumman, initiated this spacecraft project two-years after its co-manifest mission had started, with less than one-fifth the budget. With a $79M total cost cap (including operations and reserves) and 31-months until launch, LCROSS needed a game-changing approach to be successful. At the LCROSS Confirmation Review, the ESMD Associate Administrator asked the Project team to keep a close record of lessons learned through the course of the mission and share their findings with the Agency at the end of the mission. This paper summarizes the Project, the mission, its risk position, and some of the more notable lessons learned.

Starshade Prototype

NASA Image and Video Library

2016-08-09

This image shows the bare bones of the first prototype starshade by NASA's Jet Propulsion Laboratory, Pasadena, California. The prototype was shown in technology partner Astro Aerospace/Northrup Grumman's facility in Santa Barbara, California in 2013. In order for the petals of the starshade to diffract starlight away from the camera of a space telescope, they must be deployed with accuracy once the starshade reaches space. The four petals pictured in the image are being measured for this positional accuracy with a laser. As shown by this 66-foot (20-meter) model, starshades can come in many shapes and sizes. This design shows petals that are more extreme in shape which properly diffracts starlight for smaller telescopes. http://photojournal.jpl.nasa.gov/catalog/PIA20903

Enhancing optical communication with deep neural networks

NASA Astrophysics Data System (ADS)

Lohani, Sanjaya; Knutson, Erin; Tkach, Sam; Huver, Sean; Glasser, Ryan; Tulane University Collaboration; Deep Science AI Collaboration

The spatial profile of optical modes may be altered such that they contain nonzero orbital angular momentum (OAM). Laguerre-Gauss (LG) states of light have a helical wavefront and well-defined OAM, and have recently been shown to allow for larger information transfer rates in optical communications as compared to using only Gaussian modes. A primary difficulty, however, is the accurate classification of different OAM optical states, which contain different values of OAM, in the detection stage. The difficulty in this differentiation increases as larger degrees of OAM are used. Here we show the performance of deep neural networks in the simultaneous classification of numerically generated, noisy, Laguerre-Gauss states with OAM value up to 100 can reach near 100% accuracy. This method relies only on the intensity profile of the detected OAM states, avoiding bulky and difficult-to-implement methods that are required to measure the phase profile of the modes in the receiver of the communication platform. This allows for a simplification in the network design and an increase in performance when using states with large degrees of OAM. We anticipate that this approach will allow for significant advances in the development of optical communication technologies. We acknowledge funding from the Louisiana State Board of Regents and Northrop Grumman - NG NEXT.

Aeroservoelastic Testing of a Sidewall Mounted Free Flying Wind-Tunnel Model

NASA Technical Reports Server (NTRS)

Scott, Robert C.; Vetter, Travis K.; Penning, Kevin B.; Coulson, David A.; Heeg, Jennifer

2008-01-01

A team comprised of the Air Force Research Laboratory (AFRL), Northrop Grumman, Lockheed Martin, and the NASA Langley Research Center conducted three j wind-tunnel tests in the Transonic Dynamics Tunnel to demonstrate active control technologies relevant to large, exible vehicles. In the rst of these three tests, a semispan, aeroelastically scaled, wind-tunnel model of a ying wing SensorCraft vehi- cle was mounted to a force balance to demonstrate gust load alleviation. In the second and third tests, the same wing was mated to a new, multi-degree-of-freedom, sidewall mount. This mount allowed the half-span model to translate vertically and pitch at the wing root, allowing better simulation of the full span vehicle's rigid-body modes. Gust Load Alleviation (GLA) and Body Freedom Flutter (BFF) suppression were successfully demonstrated. The rigid body degrees-of-freedom required that the model be own in the wind tunnel using an active control system. This risky mode of testing necessitated that a model arrestment system be integrated into the new mount. The safe and successful completion of these free-flying tests required the development and integration of custom hardware and software. This paper describes the many systems, software, and procedures that were developed as part of this effort.

Gamma-resonance Contraband Detection using a high current tandem accelerator

NASA Astrophysics Data System (ADS)

Milton, B. F.; Beis, J.; Dale, D.; Debiak, T.; Kamykowski, E.; Melnychuk, S.; Rathke, J.; Rogers, J.; Ruegg, R.; Sredniawski, J.

1999-04-01

TRIUMF and Northrop Grumman have developed a new system for the detection of concealed explosives and drugs. This Contraband Detection System (CDS) is based on the resonant absorption by 14N of gammas produced using 13C(p,γ)14N. The chosen reaction uses protons at 1.75 MeV and the gammas have an energy of 9.17 MeV. By measuring both the resonant and the non-resonant absorption using detectors with good spatial resolution, and applying standard tomographic techniques, we are able to produce 3D images of both the nitrogen partial density and the total density. The images together may be utilized with considerable confidence to determine if small amounts of nitrogen based explosives, heroin or cocaine are present in the interrogated containers. Practical Gamma Resonant Absorption (GRA) scanning requires an intense source of protons. However this proton source must also be very stable, have low energy spread, and have good spatial definition. These demands suggested a tandem as the accelerator of choice. We have therefore constructed a 2 MeV H- tandem optimized for high current (10 mA) operation, while minimizing the overall size of the accelerator. This has required several special innovations which will be presented in the paper. We will also present initial commissioning results.

LCROSS: A High Return, Small Satellite Mission

NASA Technical Reports Server (NTRS)

Andrews, Daniel R.

2010-01-01

Early in 2006, the NASA Exploration Systems Mission Directorate (ESMD) held a competition for NASA Centers to propose innovative ideas for a secondary payload mission to launch with the Lunar Reconnaissance Orbiter (LRO) to the Moon. The successful proposal could cost no more than $80 million dollars (less was preferred), would have to be ready to launch with the LRO in 31 months, could weigh no more than 1000 kg (fuelled), and would be designated a risk-tolerant "Class D" mission. In effect, NASA was offering a fixed-price contract to the winning NASA team to stay within a cost and schedule cap by accepting an unusually elevated risk position. To address this Announcement of Opportunity to develop a cost-and-schedule-capped secondary payload mission to fly with LRO, NASA Ames Research Center (ARC) in Moffett Field, CA, USA embarked on a brainstorming effort termed "Blue Ice" in which a small team was asked to explore a number of mission scenarios that might have a good chance for success and still fit within the stated programmatic constraints. From this work, ARC developed and submitted six of the nineteen mission proposals received by ESMD from throughout the Agency, one of which was LCROSS - a collaborative effort between ARC and its industrial partner, Northrop-Grumman (NG) in Redondo Beach, CA, USA.

Latency features of SafetyNet ground systems architecture for the National Polar-orbiting Operational Environmental Satellite System (NPOESS)

NASA Astrophysics Data System (ADS)

Duda, James L.; Mulligan, Joseph; Valenti, James; Wenkel, Michael

2005-01-01

A key feature of the National Polar-orbiting Operational Environmental Satellite System (NPOESS) is the Northrop Grumman Space Technology patent-pending innovative data routing and retrieval architecture called SafetyNetTM. The SafetyNetTM ground system architecture for the National Polar-orbiting Operational Environmental Satellite System (NPOESS), combined with the Interface Data Processing Segment (IDPS), will together provide low data latency and high data availability to its customers. The NPOESS will cut the time between observation and delivery by a factor of four when compared with today's space-based weather systems, the Defense Meteorological Satellite Program (DMSP) and NOAA's Polar-orbiting Operational Environmental Satellites (POES). SafetyNetTM will be a key element of the NPOESS architecture, delivering near real-time data over commercial telecommunications networks. Scattered around the globe, the 15 unmanned ground receptors are linked by fiber-optic systems to four central data processing centers in the U. S. known as Weather Centrals. The National Environmental Satellite, Data and Information Service; Air Force Weather Agency; Fleet Numerical Meteorology and Oceanography Center, and the Naval Oceanographic Office operate the Centrals. In addition, this ground system architecture will have unused capacity attendant with an infrastructure that can accommodate additional users.

The Northrop Grumman External Occulter Testbed: Preliminary Results

NASA Astrophysics Data System (ADS)

Lo, Amy; Glassman, T.; Lillie, C.

2007-05-01

We have built a subscale testbed to demonstrate and validate the performance of the New Worlds Observer (NWO), a terrestrial planet finder external-occulter mission concept. The external occulter concept allows observations of nearby exo-Earths using two spacecraft: one carrying an occulter that is tens of meters in diameter and the other carrying a generic space telescope. The occulter is completely opaque, resembling a flower, with petals having a hypergaussian profile that enable 10-10 intensity suppression of stars that potentially harbor terrestrial planets. The baseline flight NWO system has a 30 meter occulter flying 30,000 km in front of a 4 meter class telescope. Testing the flight configuration on the ground is not feasible, so we have matched the Fresnel number of the flight configuration ( 10) using a subscale occulter. Our testbed consists of an 80 meter length evacuated tube, with a high precision occulter in the center of the tube. The occulter is 4 cm in diameter, manufactured with ¼ micron metrological accuracy and less than 2 micron tip truncation. This mimics a 30 meter occulter with millimeter figure accuracy and less than centimeter tip truncation. Our testbed is an evolving experiment, and we report here the first, preliminary, results using a single wavelength laser (532 nm) as the source.

First Starshade Prototype at JPL

NASA Image and Video Library

2016-08-09

The first prototype starshade developed by NASA's Jet Propulsion Laboratory, shown in technology partner Astro Aerospace/Northrup Grumman's facility in Santa Barbara, California, in 2013. As shown by this 66 foot (20-meter) model, starshades can come in many shapes and sizes. This design shows petals that are more extreme in shape which properly diffracts starlight for smaller telescopes. Each petal is covered in a high-performance plastic film that resembles gold foil. On a starshade ready for launch, the thermal gold foil will only cover the side of the petals facing away from the telescope, with black on the other, so as not to reflect other light sources such as the Earth into its camera. http://photojournal.jpl.nasa.gov/catalog/PIA20906

NASA Prepares Webb Telescope Pathfinder for Famous Chamber

NASA Image and Video Library

2015-04-13

Engineers and technicians manually deployed the secondary mirror support structure (SMSS) of the James Webb Space Telescope's Pathfinder backplane test model, outside of a giant space simulation chamber called Chamber A, at NASA's Johnson Space Center in Houston. This historic test chamber was previously used in manned spaceflight missions and is being readied for a cryogenic test of a Webb telescope component. In the weightless environment of space, the SMSS is deployed by electric motors. On the ground, specially trained operators use a hand crank and a collection of mechanical ground support equipment to overcome the force of gravity. "This structure needs to be in the deployed configuration during the cryogenic test to see how the structure will operate in the frigid temperatures of space," said Will Rowland, senior mechanical test engineer for Northrop Grumman Aerospace Systems, Redondo Beach, California. "The test also demonstrates that the system works and can be successfully deployed." After the deployment was completed, Chamber A's circular door was opened and the rails (seen in the background of the photo) were installed so that the Pathfinder unit could be lifted, installed and rolled into the chamber on a cart. The team completed a fit check for the Pathfinder. Afterwards they readied the chamber for the cryogenic test, which will simulate the frigid temperatures the Webb telescope will encounter in space. “The team has been doing a great job keeping everything on schedule to getting our first optical test results, " said Lee Feinberg, NASA Optical Telescope Element Manager. The James Webb Space Telescope is the scientific successor to NASA's Hubble Space Telescope. It will be the most powerful space telescope ever built. Webb is an international project led by NASA with its partners, the European Space Agency and the Canadian Space Agency. Image credit: NASA/Desiree Stover Text credit: Laura Betz, NASA's Goddard Space Flight Center, Greenbelt, Maryland NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

By the Dozen: NASA's James Webb Space Telescope Mirrors

NASA Image and Video Library

2016-01-03

Caption: One dozen (out of 18) flight mirror segments that make up the primary mirror on NASA's James Webb Space Telescope have been installed at NASA's Goddard Space Flight Center. Credits: NASA/Chris Gunn More: Since December 2015, the team of scientists and engineers have been working tirelessly to install all the primary mirror segments onto the telescope structure in the large clean room at NASA's Goddard Space Flight Center in Greenbelt, Maryland. The twelfth mirror was installed on January 2, 2016. "This milestone signifies that all of the hexagonal shaped mirrors on the fixed central section of the telescope structure are installed and only the 3 mirrors on each wing are left for installation," said Lee Feinberg, NASA's Optical Telescope Element Manager at NASA Goddard. "The incredibly skilled and dedicated team assembling the telescope continues to find ways to do things faster and more efficiently." Each hexagonal-shaped segment measures just over 4.2 feet (1.3 meters) across and weighs approximately 88 pounds (40 kilograms). After being pieced together, the 18 primary mirror segments will work together as one large 21.3-foot (6.5-meter) mirror. The primary mirror will unfold and adjust to shape after launch. The mirrors are made of ultra-lightweight beryllium. The mirrors are placed on the telescope's backplane using a robotic arm, guided by engineers. The full installation is expected to be completed in a few months. The mirrors were built by Ball Aerospace & Technologies Corp., Boulder, Colorado. Ball is the principal subcontractor to Northrop Grumman for the optical technology and lightweight mirror system. The installation of the mirrors onto the telescope structure is performed by Harris Corporation of Rochester, New York. Harris Corporation leads integration and testing for the telescope. While the mirror assembly is a very significant milestone, there are many more steps involved in assembling the Webb telescope. The primary mirror and the tennis-court-sized sunshield are the largest and most visible components of the Webb telescope. However, there are four smaller components that are less visible, yet critical. The instruments that will fly aboard Webb - cameras and spectrographs with detectors able to record extremely faint signals — are part of the Integrated Science Instrument Module (ISIM), which is currently undergoing its final cryogenic vacuum test and will be integrated with the mirror later this year.

By the Dozen: NASA's James Webb Space Telescope Mirrors

NASA Image and Video Library

2016-01-03

A view of the one dozen (out of 18) flight mirror segments that make up the primary mirror on NASA's James Webb Space Telescope have been installed at NASA's Goddard Space Flight Center. Credits: NASA/Chris Gunn More: Since December 2015, the team of scientists and engineers have been working tirelessly to install all the primary mirror segments onto the telescope structure in the large clean room at NASA's Goddard Space Flight Center in Greenbelt, Maryland. The twelfth mirror was installed on January 2, 2016. "This milestone signifies that all of the hexagonal shaped mirrors on the fixed central section of the telescope structure are installed and only the 3 mirrors on each wing are left for installation," said Lee Feinberg, NASA's Optical Telescope Element Manager at NASA Goddard. "The incredibly skilled and dedicated team assembling the telescope continues to find ways to do things faster and more efficiently." Each hexagonal-shaped segment measures just over 4.2 feet (1.3 meters) across and weighs approximately 88 pounds (40 kilograms). After being pieced together, the 18 primary mirror segments will work together as one large 21.3-foot (6.5-meter) mirror. The primary mirror will unfold and adjust to shape after launch. The mirrors are made of ultra-lightweight beryllium. The mirrors are placed on the telescope's backplane using a robotic arm, guided by engineers. The full installation is expected to be completed in a few months. The mirrors were built by Ball Aerospace & Technologies Corp., Boulder, Colorado. Ball is the principal subcontractor to Northrop Grumman for the optical technology and lightweight mirror system. The installation of the mirrors onto the telescope structure is performed by Harris Corporation of Rochester, New York. Harris Corporation leads integration and testing for the telescope. While the mirror assembly is a very significant milestone, there are many more steps involved in assembling the Webb telescope. The primary mirror and the tennis-court-sized sunshield are the largest and most visible components of the Webb telescope. However, there are four smaller components that are less visible, yet critical. The instruments that will fly aboard Webb - cameras and spectrographs with detectors able to record extremely faint signals — are part of the Integrated Science Instrument Module (ISIM), which is currently undergoing its final cryogenic vacuum test and will be integrated with the mirror later this year.

Grumman Windstream 25 wind turbine generator. Final test report

DOE Office of Scientific and Technical Information (OSTI.GOV)

Sexton, J.H.

1980-03-01

The Grumman Windstream 25 Wind Turbine Generator (WTG) tested at the Rocky Flats Small Wind Systems Test Center (WSTC) was one of nineteen Windstream 25's manufactured by Grumman Energy Systems, Inc. The machine was considered a first generation prototype and is no longer being produced. While being tested at the WSTC, the Windstream 25 was still in a developmental stage, and operational problems were experienced during its testing period. It is important to underscore, however, that problems encountered during testing of the machine created valuable gains in experience and data for both Rocky Flats and Grumman personnel. It is believedmore » these gains have contributed significantly to further development of Grumman WTG's.« less

Three Generations of Tracking and Data Relay Satellite (TDRS) Spacecraft

NASA Technical Reports Server (NTRS)

Zaleski, Ron

2016-01-01

The current Tracking and Data Relay Satellite configuration consists of nine in-orbit satellites (four first generation, three second generation and two third generation satellites) globally distributed in geosynchronous orbit to provide near continuous data relay service to missions like Hubble Space Telescope and the International Space Station. The 1st generation spacecraft were designed by TRW/Northrop Grumman with their launches of the five spacecraft ranging from 1983 through 1995. The 2nd and 3rd generation spacecraft were designed by Boeing with their launches ranging 2000 - 2002 and 2013 - 2017 respectively. TDRS-3 is now 27 years on orbit, continues to be a capable asset for the TDRS constellation. Lack of need for inclination control combined with large fuel reserves and redundancy on critical elements provides spacecraft that operate well past design life, all of which contributes to expanded TDRS constellation support capabilities. All spacecraft generations have issues. Significant issues will be summarized with the focus on the Boeing related problems. Degradations and failures are continually assessed and provide the foundation for yearly updates to spacecraft reliability models, constellation service projections and deorbit plans (in order to meet NASAs mandate of limiting orbital debris). Even when accounting for degradations and failures, the life expectancy for the Boeing delivered 2nd generation TDRS-8, 9 10 TDRS are anticipated to be 25+ years.

Using Additive Manufacturing to Print a CubeSat Propulsion System

NASA Technical Reports Server (NTRS)

Marshall, William M.; Zemba, Michael; Shemelya, Corey; Wicker, Ryan; Espalin, David; MacDonald, Eric; Keif, Craig; Kwas, Andrew

2015-01-01

Small satellites, such as CubeSats, are increasingly being called upon to perform missions traditionally ascribed to larger satellite systems. However, the market of components and hardware for small satellites, particularly CubeSats, still falls short of providing the necessary capabilities required by ever increasing mission demands. One way to overcome this shortfall is to develop the ability to customize every build. By utilizing fabrication methods such as additive manufacturing, mission specific capabilities can be built into a system, or into the structure, that commercial off-the-shelf components may not be able to provide. A partnership between the University of Texas at El Paso, COSMIAC at the University of New Mexico, Northrop Grumman, and the NASA Glenn Research Center is looking into using additive manufacturing techniques to build a complete CubeSat, under the Small Spacecraft Technology Program. The W. M. Keck Center at the University of Texas at El Paso has previously demonstrated the ability to embed electronics and wires into the addtively manufactured structures. Using this technique, features such as antennas and propulsion systems can be included into the CubeSat structural body. Of interest to this paper, the team is investigating the ability to take a commercial micro pulsed plasma thruster and embed it into the printing process. Tests demonstrating the dielectric strength of the printed material and proof-of-concept demonstration of the printed thruster will be shown.

Gamma-resonance Contraband Detection using a high current tandem accelerator

DOE Office of Scientific and Technical Information (OSTI.GOV)

Milton, B. F.; Beis, J.; Dale, D.

1999-04-26

TRIUMF and Northrop Grumman have developed a new system for the detection of concealed explosives and drugs. This Contraband Detection System (CDS) is based on the resonant absorption by {sup 14}N of gammas produced using {sup 13}C(p,{gamma}){sup 14}N. The chosen reaction uses protons at 1.75 MeV and the gammas have an energy of 9.17 MeV. By measuring both the resonant and the non-resonant absorption using detectors with good spatial resolution, and applying standard tomographic techniques, we are able to produce 3D images of both the nitrogen partial density and the total density. The images together may be utilized with considerablemore » confidence to determine if small amounts of nitrogen based explosives, heroin or cocaine are present in the interrogated containers. Practical Gamma Resonant Absorption (GRA) scanning requires an intense source of protons. However this proton source must also be very stable, have low energy spread, and have good spatial definition. These demands suggested a tandem as the accelerator of choice. We have therefore constructed a 2 MeV H{sup -} tandem optimized for high current (10 mA) operation, while minimizing the overall size of the accelerator. This has required several special innovations which will be presented in the paper. We will also present initial commissioning results.« less

Computational model of miniature pulsating heat pipes

DOE Office of Scientific and Technical Information (OSTI.GOV)

Martinez, Mario J.; Givler, Richard C.

The modeling work described herein represents Sandia National Laboratories (SNL) portion of a collaborative three-year project with Northrop Grumman Electronic Systems (NGES) and the University of Missouri to develop an advanced, thermal ground-plane (TGP), which is a device, of planar configuration, that delivers heat from a source to an ambient environment with high efficiency. Work at all three institutions was funded by DARPA/MTO; Sandia was funded under DARPA/MTO project number 015070924. This is the final report on this project for SNL. This report presents a numerical model of a pulsating heat pipe, a device employing a two phase (liquid andmore » its vapor) working fluid confined in a closed loop channel etched/milled into a serpentine configuration in a solid metal plate. The device delivers heat from an evaporator (hot zone) to a condenser (cold zone). This new model includes key physical processes important to the operation of flat plate pulsating heat pipes (e.g. dynamic bubble nucleation, evaporation and condensation), together with conjugate heat transfer with the solid portion of the device. The model qualitatively and quantitatively predicts performance characteristics and metrics, which was demonstrated by favorable comparisons with experimental results on similar configurations. Application of the model also corroborated many previous performance observations with respect to key parameters such as heat load, fill ratio and orientation.« less

Terahertz-Regime, Micro-VEDs: Evaluation of Micromachined TWT Conceptual Designs

NASA Technical Reports Server (NTRS)

Booske, John H.; Kory, Carol L.; Gallagher, D.; van der Weide, Daniel W.; Limbach, S; Gustafson, P; Lee, W.-J.; Gallagher, S.; Jain, K.

2001-01-01

Summary form only given. The Terahertz (THz) region of the electromagnetic spectrum (approx.300-3000 GHz) has enormous potential for high-data-rate communications, spectroscopy, astronomy, space research, medicine, biology, surveillance, remote sensing, industrial process control, etc. The most critical roadblock to full exploitation of the THz band is lack of coherent radiation sources that are powerful (0.01-10.0 W continuous wave), efficient (>1 %), frequency agile (instantaneously tunable over 1% bandwidths or more), reliable, and relatively inexpensive. Micro-machined Vacuum Electron Devices (micro-VEDs) represent a promising solution. We describe prospects for miniature, THz-regime TWTs fabricated using micromachining techniques. Several approx.600 GHz conceptual designs are compared. Their expected performance has been analyzed using SD, 2.51), and 3D TWT codes. A folded waveguide (FWG) TWT forward-wave amplifier design is presented based on a Northrop Grumman (NGC) optimized design procedure. This conceptual device is compared to the simulated performance of a novel, micro-VED helix TWT. Conceptual FWG TWT backward-wave amplifiers and oscillators are also discussed. A scaled (100 GHz) FWG TWT operating at a relatively low voltage (-12 kV) is under development at NGC. Also, actual-size micromachining experiments are planned to evaluate the feasibility of arrays of micro-VED TWTs. Progress and results of these efforts are described. This work was supported, in part by AFOSR, ONR, and NSF.

A High Current Tandem Accelerator for Gamma-Resonance Contraband Detection

NASA Astrophysics Data System (ADS)

Milton, Bruce

1997-05-01

TRIUMF and Northrop Grumman have developed a new system for the detection of concealed explosives and drugs. This Contraband Detection System (CDS) is based on the resonant absorption by ^14N of gammas produced using ^13C(p,γ)^14N. The chosen reaction uses protons at 1.75 MeV and the gammas have an energy of 9.17 MeV. By measuring both the resonant and the non -resonant absorption using detectors with good spatial resolution, and applying standard tomographic techniques, we are able to produce 3D images of both the nitrogen partial density and the total density. The images together may be utilized with considerable confidence to determine if small amounts of nitrogen based explosives, heroin or cocaine are present in the interrogated containers. Practical Gamma Resonant Absorption (GRA) scanning requires an intense source of protons. However this proton source must also be very stable, have low energy spread, and have good spatial definition. These demands suggested a tandem as the accelerator of choice. We have therefore constructed a 2 MeV H^- tandem optimized for high current (10 mA) operation, while minimizing the overall size of the accelerator. This has required several special innovations which will be presented in the paper. We will also present initial commissioning results.

A Multi-Frequency Wide-Swath Spaceborne Cloud and Precipitation Imaging Radar

NASA Technical Reports Server (NTRS)

Li, Lihua; Racette, Paul; Heymsfield, Gary; McLinden, Matthew; Venkatesh, Vijay; Coon, Michael; Perrine, Martin; Park, Richard; Cooley, Michael; Stenger, Pete;

Proof-of-principle contraband detection system for nonintrusive inspection

NASA Astrophysics Data System (ADS)

Sredniawski, Joseph J.; Debiak, T.; Kamykowski, E.; Rathke, John E.; Schmor, P.; Milton, Bill; Stanford, G.; Rogers, Joel; Boyd, J.; Brondo, J.

1997-02-01

A proof-of-principle (POP) contraband detection system (CDS), is under construction at Northrop Grumman's Advanced Technology and Development Center. We employ gamma resonance absorption to detect nitrogen or chlorine in explosives and certain forms of illegal drugs. Using tomography, 3D images of the total density and selected element density are generated. These characteristics together may be utilized with considerable confidence in determining if contraband is present in baggage or cargo. The CDS employs a high current DC electrostatic accelerator that provides a beam of proton sat either 1.75 or 1.89 MeV. These high energy particles impinge upon a target coated with 13C or 34S. The resultant resonant gamma rays are preferentially absorbed in either 14N or 35Cl. Because of the penetrating power of the gamma rays, this approach can be utilized for inspection of fully loaded aircraft containers such as the LD3. With proper design for handling baggage and with certain CDS design features not present in the POP, throughputs approaching 2000 bags/hour are estimated. Furthermore, the technology being developed for the CDS accelerator may have other applications such as for Boron Neutron Capture Therapy or Neutron Radiography. Our current program calls for testing of the POP CDS by late 1996. This paper presents the overall design, and characteristics of the CDS POP and the status of the program.

An Overview of the Performance of the Chandra X-ray Observatory

NASA Technical Reports Server (NTRS)

Weisskopf, M. C.; Aldcroft, T. L.; Bautz, M.; Cameron, R. A.; Dewey, D.; Drake, J. J.; Grant, C. E.; Marshall, H. L.; Murray, S. S.

2004-01-01

The Chandra X-ray Observatory is the X-ray component of NASA's Great Observatory Program which includes the recently launched Spitzer Infrared Telescope, the Hubble Space Telescope (HST) for observations in the visible, and the Compton Gamma-Ray Observatory (CGRO) which, after providing years of useful data has reentered the atmosphere. All these facilities provide, or provided, scientific data to the international astronomical community in response to peer-reviewed proposals for their use. The Chandra X-ray Observatory was the result of the efforts of many academic, commercial, and government organizations primarily in the United States but also in Europe. NASA s Marshall Space Flight Center (MSFC) manages the Project and provides Project Science; Northrop Grumman Space Technology (NGST - formerly TRW) served as prime contractor responsible for providing the spacecraft, the telescope, and assembling and testing the Observatory; and the Smithsonian Astrophysical Observatory (SAO) provides technical support and is responsible for ground operations including the Chandra X-ray Center (CXC). Telescope and instrument teams at SAO, the Massachusetts Institute of Technology (MIT), the Pennsylvania State University (PSU), the Space Research Institute of the Netherlands (SRON), the Max-Planck Institut fur extraterrestrische Physik (MPE), and the University of Kiel support also provide technical support to the Chandra Project. We present here a detailed description of the hardware, its on-orbit performance, and a brief overview of some of the remarkable discoveries that illustrate that performance.

Laboratory search for a long-range T-odd, P-odd interaction from axionlike particles using dual-species nuclear magnetic resonance with polarized 129Xe and 131Xe gas.

PubMed

Bulatowicz, M; Griffith, R; Larsen, M; Mirijanian, J; Fu, C B; Smith, E; Snow, W M; Yan, H; Walker, T G

2013-09-06

Various theories beyond the standard model predict new particles with masses in the sub-eV range with very weak couplings to ordinary matter. A new P-odd and T-odd interaction between polarized and unpolarized nucleons proportional to K·r is one such possibility, where r is the distance between the nucleons and K is the spin of the polarized nucleon. Such an interaction involving a scalar coupling gs at one vertex and a pseudoscalar coupling gp at the polarized nucleon vertex can be induced by the exchange of spin-0 bosons. We used the NMR cell test station at Northrop Grumman Corporation to search for NMR frequency shifts in polarized 129Xe and 131Xe when a nonmagnetic zirconia rod is moved near the NMR cell. Long (T2∼20  s) spin-relaxation times allow precision measurements of the NMR frequency ratios, which are insensitive to magnetic field fluctuations. Combined with existing theoretical calculations of the neutron spin contribution to the nuclear angular momentum in xenon nuclei, the measurements improve the laboratory upper bound on the product gsgp(n) by 2 orders of magnitude for distances near 1 mm. The sensitivity of this technique can be increased by at least two more orders of magnitude.

Bringing Perfect Vision to the Daniel K. Inouye Solar Telescope

NASA Astrophysics Data System (ADS)

Matijevich, Russ; Johansson, Erik; Johnson, Luke; Cavaco, Jeff; National Solar Observatory

2016-01-01

The world's largest ground-based solar telescope is one step closer to operation with the acceptance of the deformable mirror engineered by AOA Xinetics, a Northrop Grumman Corporation company. The Daniel K. Inouye Solar Telescope (DKIST), currently under construction in Haleakala, Hawaii, will offer unprecedented high-resolution images of the sun using the latest adaptive optics technology to provide its distortion-free imaging.Led by the National Solar Observatory (NSO) and the Association of Universities for Research in Astronomy (AURA), the Inouye Solar Telescope will help scientists better understand how magnetic fields affect the physical properties of the Sun, what roles they play in our solar system and how they affect Earth.Ground-based telescopes, whether observing the sun or the night sky must contend with atmospheric turbulence that acts as a flexible lens, constantly reshaping observed images. This turbulence makes research on solar activity difficult and drives the need for the latest adaptive optics technology.To provide DKIST with the distortion-free imaging it requires, AOA Xinetics designed a deformable mirror with 1,600 actuators, four times the normal actuator density. This deformable mirror (DM) is instrumental in removing all of the atmospheric blurriness that would otherwise limit the telescope's performance. The mirror also has an internal thermal management system to handle the intense solar energy coming from DKIST's telescope. This poster provides the history behind this incredible success story.

High Power Short Wavelength Laser Development

DTIC Science & Technology

1977-11-01

CO o •:’ ■ r LiJj ---’ D NORTHROP Research and Technology Center DISTRIBUTION STATEMENT Ä Approved for public le^easo; I/lstnbution...Contract N00014-76-C-1100 DISTP.irUTi Äpp’ : f, 1 Sponsored By ADVANCED RESEARCH PROJECTS AGENCY ARPA Order No. 3125 Monitored By OiTFICE OF NAVAL... RESEARCH NORTHROP CORPORATION ’ Northrop Research and Technology Center 3401 West Broadway Hawthorne, California 90250 Telephone

Space telerobotic systems: Applications and concepts

NASA Technical Reports Server (NTRS)

Jenkins, L.

1987-01-01

The definition of a variety of assembly, servicing, and maintenance missions has led to the generation of a number of space telerobot concepts. The remote operation of a space telerobot is seen as a means to increase astronaut productivity. Dexterous manipulator arms are controlled from the Space Shuttle Orbiter cabin or a Space Station module. Concepts for the telerobotic work system have been developed by the Lyndon B. Johnson Space Center through contracts with the Grumman Aerospace Corporation and Marin Marietta Corporation. These studies defined a concept for a telerobot with extravehicular activity (EVA) astronaut equivalent capability that would be controlled from the Space Shuttle. An evolutionary development of the system is proposed as a means of incorporating technology advances. Early flight testing is seen as needed to address the uncertainties of robotic manipulation in space. Space robotics can be expected to spin off technology to terrestrial robots, particularly in hazardous and unstructured applications.

Crew Training - Apollo 9 - Grumman Aircraft Eng. Corp. (GAEC)

NASA Image and Video Library

1969-01-25

S69-17615 (25 Jan. 1969) --- Astronaut Russell L. Schweickart, lunar module pilot of the Apollo 9 prime crew, participates in a press conference at the Grumman Aircraft Engineering Corporation. Grumman is the contractor to NASA for the Lunar Module. Schweickart is holding a model of a docked Lunar Module/Command and Service Modules. The Apollo 9 mission will evaluate spacecraft lunar module systems performance during manned Earth-orbital flight.

The James Webb Telescope Instrument Suite Layout: Optical System Engineering Considerations for a Large, Deployable Space Telescope

NASA Technical Reports Server (NTRS)

Bos, Brent; Davila, Pam; Jurotich, Matthew; Hobbs, Gurnie; Lightsey, Paul; Contreras, Jim; Whitman, Tony

2003-01-01

The James Webb Space Telescope (JWST) is a space-based, infrared observatory designed to study the early stages of galaxy formation in the Universe. The telescope will be launched into an elliptical orbit about the second Lagrange point and passively cooled to 30-50 K to enable astronomical observations from 0.6 to 28 microns. A group from the NASA Goddard Space Flight Center and the Northrop Grumman Space Technology prime contractor team has developed an optical and mechanical layout for the science instruments within the JWST field of view that satisfies the telescope s high-level performance requirements. Four instruments required accommodation within the telescope's field of view: a Near-Infrared Camera (NIRCam) provided by the University of Arizona; a Near-Mared Spectrometer (NIRSpec) provided by the European Space Agency; a Mid-Infrared Instrument (MIRI) provided by the Jet Propulsion Laboratory and a European consortium; and a Fine Guidance Sensor (FGS) with a tunable filter module provided by the Canadian Space Agency. The size and position of each instrument's field of view allocation were developed through an iterative, concurrent engineering process involving the key observatory stakeholders. While some of the system design considerations were those typically encountered during the development of an infrared observatory, others were unique to the deployable and controllable nature of JWST. This paper describes the optical and mechanical issues considered during the field of view layout development, as well as the supporting modeling and analysis activities.

Lifting Entry & Atmospheric Flight (LEAF) System Concept Applications at Solar System Bodies With an Atmosphere

NASA Astrophysics Data System (ADS)

Lee, Greg; Polidan, Ronald; Ross, Floyd; Sokol, Daniel; Warwick, Steve

2015-11-01

Northrop Grumman and L’Garde have continued the development of a hypersonic entry, semi-buoyant, maneuverable platform capable of performing long-duration (months to a year) in situ and remote measurements at any solar system body that possesses an atmosphere.The Lifting Entry & Atmospheric Flight (LEAF) family of vehicles achieves this capability by using a semi-buoyant, ultra-low ballistic coefficient vehicle whose lifting entry allows it to enter the atmosphere without an aeroshell. The mass savings realized by eliminating the heavy aeroshell allows significantly more payload to be accommodated by the platform for additional science collection and return.In this presentation, we discuss the application of the LEAF system at various solar system bodies: Venus, Titan, Mars, and Earth. We present the key differences in platform design as well as operational differences required by the various target environments. The Venus implementation includes propulsive capability to reach higher altitudes during the day and achieves full buoyancy in the mid-cloud layer of Venus’ atmosphere at night.Titan also offers an attractive operating environment, allowing LEAF designs that can target low or medium altitude operations, also with propulsive capabilities to roam within each altitude regime. The Mars version is a glider that descends gradually, allowing targeted delivery of payloads to the surface or high resolution surface imaging. Finally, an Earth version could remain in orbit in a stowed state until activated, allowing rapid response type deployments to any region of the globe.

Aeroservoelastic Testing of Free Flying Wind Tunnel Models Part 1: A Sidewall Supported Semispan Model Tested for Gust Load Alleviation and Flutter Suppression

NASA Technical Reports Server (NTRS)

Scott, Robert C.; Vetter, Travis K.; Penning, Kevin B.; Coulson, David A.; Heeg, Jennifer.

2013-01-01

of a two part document. Part 2 is titled: "Aeroservoelastic Testing of Free Flying Wind Tunnel Models, Part 2: A Centerline Supported Fullspan Model Tested for Gust Load Alleviation." A team comprised of the Air Force Research Laboratory (AFRL), Northrop Grumman, Lockheed Martin, and the NASA Langley Research Center conducted three aeroservoelastic wind tunnel tests in the Transonic Dynamics Tunnel to demonstrate active control technologies relevant to large, flexible vehicles. In the first of these three tests, a semispan, aeroelastically scaled, wind tunnel model of a flying wing SensorCraft vehicle was mounted to a force balance to demonstrate gust load alleviation. In the second and third tests, the same wing was mated to a new, multi-degree of freedom, sidewall mount. This mount allowed the half-span model to translate vertically and pitch at the wing root, allowing better simulation of the full span vehicle's rigid body modes. Gust load alleviation (GLA) and Body freedom flutter (BFF) suppression were successfully demonstrated. The rigid body degrees-of-freedom required that the model be flown in the wind tunnel using an active control system. This risky mode of testing necessitated that a model arrestment system be integrated into the new mount. The safe and successful completion of these free flying tests required the development and integration of custom hardware and software. This paper describes the many systems, software, and procedures that were developed as part of this effort.

JWST testbed telescope: a functionally accurate scaled version of the flight optical telescope element used to develop the flight wavefront sensing and control algorithm

NASA Astrophysics Data System (ADS)

Kingsbury, Lana K.; Atcheson, Paul D.

2004-10-01

The Northrop-Grumman/Ball/Kodak team is building the JWST observatory that will be launched in 2011. To develop the flight wavefront sensing and control (WFS&C) algorithms and software, Ball is designing and building a 1 meter diameter, functionally accurate version of the JWST optical telescope element (OTE). This testbed telescope (TBT) will incorporate the same optical element control capability as the flight OTE. The secondary mirror will be controlled by a 6 degree of freedom (dof) hexapod and each of the 18 segmented primary mirror assemblies will have 6 dof hexapod control as well as radius of curvature adjustment capability. In addition to the highly adjustable primary and secondary mirrors, the TBT will include a rigid tertiary mirror, 2 fold mirrors (to direct light into the TBT) and a very stable supporting structure. The total telescope system configured residual wavefront error will be better than 175 nm RMS double pass. The primary and secondary mirror hexapod assemblies enable 5 nm piston resolution, 0.0014 arcsec tilt resolution, 100 nm translation resolution, and 0.04497 arcsec clocking resolution. The supporting structure (specifically the secondary mirror support structure) is designed to ensure that the primary mirror segments will not change their despace position relative to the secondary mirror (spaced > 1 meter apart) by greater than 500 nm within a one hour period of ambient clean room operation.

Recent Stirling Conversion Technology Developments and Operational Measurements at NASA Glenn Research Center

NASA Technical Reports Server (NTRS)

Oriti, Salvatore M.; Schifer, Nicholas A.

2010-01-01

In support of the Advanced Stirling Radioisotope Generator (ASRG) project and other potential applications, NASA Glenn Research Center (GRC) has initiated convertor technology development efforts in the areas of acoustic emission, electromagnetic field mitigation, thermoacoustic Stirling conversion, and multiple-cylinder alpha arrangements of Stirling machines. The acoustic emission measurement effort was developed as a health monitoring metric for several Stirling convertors undergoing life testing. While accelerometers have been used in the past to monitor dynamic signature, the acoustic sensors were chosen to monitor cycle events, such gas bearing operation. Several electromagnetic interference (EMI) experiments were performed on a pair of Advanced Stirling Convertors (ASC). These tests demonstrated that a simple bucking coil was capable of reducing the alternating current (ac) magnetic field below the ASRG system specification. The thermoacoustic Stirling concept eliminates the displacer typically found in Stirling machines by making use of the pressure oscillations of a traveling acoustic wave. A 100 W-class thermoacoustic Stirling prototype manufactured by Northrop Grumman Space and Technology was received and tested. Another thermoacoustic prototype designed and fabricated by Sunpower, Inc., will be tested in the near future. A four cylinder free piston alpha prototype convertor was received from Sunpower, Inc. and has been tested at GRC. This hardware was used as a proof of concept to validate thermodynamic models and demonstrate stable operation of multiple-cylinder free-piston Stirling conversion. This paper will discuss each of these activities and the results they produced.

NORTHROP REACTOR. REVISION NO. 1 TO THE FINAL SAFEGUARDS REPORT

DOE Office of Scientific and Technical Information (OSTI.GOV)

Duncan, J.M.; Shimizu, B.; Romine, R.A.

1962-10-01

Additions and changes related to the original application concerning construction and operation of the Northrop Reactor are given. Answers to 13 questions relative to the Final Safeguards Report are included. Answers are also included concerning 12 questions regarding receipt, possession, and storage of fuel elements. Other information is included concerning personnel changes and changes from Al-clad fuel elements to improved stainless steelclad hydride elements. It is concluded that the improved Northrop Reactor does not present any undue hazard to the health and safety of the operating personnel or the public. (J.R.D.)

Decommissioning of the Northrop TRIGA reactor

DOE Office of Scientific and Technical Information (OSTI.GOV)

Cozens, George B.; Woo, Harry; Benveniste, Jack

1986-07-01

An overview of the administrative and operational aspects of decommissioning and dismantling the Northrop Mark F TRIGA Reactor, including: planning and preparation, personnel requirements, government interfacing, costs, contractor negotiations, fuel shipments, demolition, disposal of low level waste, final survey and disposition of the concrete biological shielding. (author)

Origins and Overview of the Shaped Sonic Boom Demonstration Program

NASA Technical Reports Server (NTRS)

Pawlowski, Joseph W.; Graham, David H.; Boccadoro, Charles H.; Coen, Peter G.; Maglieri, Domenic J.

2005-01-01

The goal of the DARPA Shaped Sonic Boom Demonstration (SSBD) Program was to demonstrate for the first time in flight that sonic booms can be substantially reduced by incorporating specialized aircraft shaping techniques. Although mitigation of the sonic boom via specialized shaping techniques was theorized decades ago, until now, this theory had never been tested with a flight vehicle subjected to actual flight conditions in a real atmosphere. The demonstrative success, which occurred on 27 August 2003 with repeat flights in the supersonic corridor at Edwards Air Force Base, is a critical milestone in the development of next generation supersonic aircraft that could one day fly unrestricted over land and help usher in a new era of time-critical air transport. Pressure measurements obtained on the ground and in the air confirmed that the specific modifications made to a Northrop Grumman F-5E aircraft not only changed the shape of the shock wave signature emanating from the aircraft, but also produced a flat-top signature whose shape persisted, as predicted, as the pressure waves propagated through the atmosphere to the ground. This accomplishment represents a major advance towards reducing the startling and potentially damaging noise of a sonic boom. This paper describes the evolution of the SSBD program, including the rationale for test article selection, and provides an overview of the history making accomplishments achieved during the SSBD effort, as well as, the follow-on NASA Shaped Sonic Boom Experiment (SSBE) Program, whose goal was to further evaluate the characteristics and robustness of shaped boom signatures.

An integrated radar model solution for mission level performance and cost trades

NASA Astrophysics Data System (ADS)

Hodge, John; Duncan, Kerron; Zimmerman, Madeline; Drupp, Rob; Manno, Mike; Barrett, Donald; Smith, Amelia

2017-05-01

A fully integrated Mission-Level Radar model is in development as part of a multi-year effort under the Northrop Grumman Mission Systems (NGMS) sector's Model Based Engineering (MBE) initiative to digitally interconnect and unify previously separate performance and cost models. In 2016, an NGMS internal research and development (IR and D) funded multidisciplinary team integrated radio frequency (RF), power, control, size, weight, thermal, and cost models together using a commercial-off-the-shelf software, ModelCenter, for an Active Electronically Scanned Array (AESA) radar system. Each represented model was digitally connected with standard interfaces and unified to allow end-to-end mission system optimization and trade studies. The radar model was then linked to the Air Force's own mission modeling framework (AFSIM). The team first had to identify the necessary models, and with the aid of subject matter experts (SMEs) understand and document the inputs, outputs, and behaviors of the component models. This agile development process and collaboration enabled rapid integration of disparate models and the validation of their combined system performance. This MBE framework will allow NGMS to design systems more efficiently and affordably, optimize architectures, and provide increased value to the customer. The model integrates detailed component models that validate cost and performance at the physics level with high-level models that provide visualization of a platform mission. This connectivity of component to mission models allows hardware and software design solutions to be better optimized to meet mission needs, creating cost-optimal solutions for the customer, while reducing design cycle time through risk mitigation and early validation of design decisions.

Phased Array-Fed Reflector (PAFR) Antenna Architectures for Space-Based Sensors

NASA Technical Reports Server (NTRS)

Cooley, Michael E.

2014-01-01

Communication link and target ranges for satellite communications (SATCOM) and space-based sensors (e.g. radars) vary from approximately 1000 km (for LEO satellites) to 35,800 km (for GEO satellites). At these long ranges, large antenna gains are required and legacy payloads have usually employed large reflectors with single beams that are either fixed or mechanically steered. For many applications, there are inherent limitations that are associated with the use of these legacy antennas/payloads. Hybrid antenna designs using Phased Array Fed Reflectors (PAFRs) provide a compromise between reflectors and Direct Radiating phased Arrays (DRAs). PAFRs provide many of the performance benefits of DRAs while utilizing much smaller, lower cost (feed) arrays. The primary limitation associated with hybrid PAFR architectures is electronic scan range; approximately +/-5 to +/- 10 degrees is typical, but this range depends on many factors. For LEO applications, the earth FOV is approximately +/-55 degrees which is well beyond the range of electronic scanning for PAFRs. However, for some LEO missions, limited scanning is sufficient or the CONOPS and space vehicle designs can be developed to incorporate a combination mechanical slewing and electronic scanning. In this paper, we review, compare and contrast various PAFR architectures with a focus on their general applicability to space missions. We compare the RF performance of various PAFR architectures and describe key hardware design and implementation trades. Space-based PAFR designs are highly multi-disciplinary and we briefly address key hardware engineering design areas. Finally, we briefly describe two PAFR antenna architectures that have been developed at Northrop Grumman.

Automated generation of weld path trajectories.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Sizemore, John M.; Hinman-Sweeney, Elaine Marie; Ames, Arlo Leroy

2003-06-01

AUTOmated GENeration of Control Programs for Robotic Welding of Ship Structure (AUTOGEN) is software that automates the planning and compiling of control programs for robotic welding of ship structure. The software works by evaluating computer representations of the ship design and the manufacturing plan. Based on this evaluation, AUTOGEN internally identifies and appropriately characterizes each weld. Then it constructs the robot motions necessary to accomplish the welds and determines for each the correct assignment of process control values. AUTOGEN generates these robot control programs completely without manual intervention or edits except to correct wrong or missing input data. Most shipmore » structure assemblies are unique or at best manufactured only a few times. Accordingly, the high cost inherent in all previous methods of preparing complex control programs has made robot welding of ship structures economically unattractive to the U.S. shipbuilding industry. AUTOGEN eliminates the cost of creating robot control programs. With programming costs eliminated, capitalization of robots to weld ship structures becomes economically viable. Robot welding of ship structures will result in reduced ship costs, uniform product quality, and enhanced worker safety. Sandia National Laboratories and Northrop Grumman Ship Systems worked with the National Shipbuilding Research Program to develop a means of automated path and process generation for robotic welding. This effort resulted in the AUTOGEN program, which has successfully demonstrated automated path generation and robot control. Although the current implementation of AUTOGEN is optimized for welding applications, the path and process planning capability has applicability to a number of industrial applications, including painting, riveting, and adhesive delivery.« less

Portable air pollution control equipment for the control of toxic particulate emissions

DOE Office of Scientific and Technical Information (OSTI.GOV)

Chaurushia, A.; Odabashian, S.; Busch, E.

1997-12-31

Chromium VI (Cr VI) has been identified by the environmental regulatory agencies as a potent carcinogen among eleven heavy metals. A threshold level of 0.0001 lb/year for Cr VI emissions has been established by the California Air Resources Board for reporting under Assembly Bill 2588. A need for an innovative control technology to reduce fugitive emissions of Cr VI was identified during the Air Toxic Emissions Reduction Program at Northrop Grumman Military Aircraft Systems Division (NGMASD). NGMASD operates an aircraft assembly facility in El Segundo, CA. Nearly all of the aircraft components are coated with a protective coating (primer) priormore » to assembly. The primer has Cr VI as a component for its excellent corrosion resistance property. The complex assembly process requires fasteners which also need primer coating. Therefore, NGMASD utilizes High Volume Low Pressure (HVLP) guns for the touch-up spray coating operations. During the touch-up spray coating operations, Cr VI particles are atomized and transferred to the aircraft surface. The South Coast Air Quality Management District (SCAQMD) has determined that the HVLP gun transfers 65% of the paint particles onto the substrate and the remaining 35% are emitted as an overspray if air pollution controls are not applied. NGMASD has developed the Portable Air Pollution Control Equipment (PAPCE) to capture and control the overspray in order to reduce fugitive Cr VI emissions from the touch-up spray coating operations. A source test was performed per SCAQMD guidelines and the final report has been approved by the SCAQMD.« less

Joint Urban 2003: Study Overview And Instrument Locations

DOE Office of Scientific and Technical Information (OSTI.GOV)

Allwine, K Jerry; Flaherty, Julia E.

2006-08-16

Quality-assured meteorological and tracer data sets are vital for establishing confidence that indoor and outdoor dispersion models used to simulate dispersal of potential toxic agents in urban atmospheres are giving trustworthy results. The U.S. Department of Defense-Defense Threat Reduction Agency and the U.S. Department of Homeland Security joined together to conduct the Joint Urban 2003 atmospheric dispersion study to provide this critically-needed high-resolution dispersion data. This major urban study was conducted from June 28 through July 31, 2003, in Oklahoma City, Oklahoma, with the participation of over 150 scientists and engineers from over 20 U.S. and foreign institutions. The Jointmore » Urban 2003 lead scientist was Jerry Allwine (Pacific Northwest National Laboratory) who oversaw study design, logistical arrangements and field operations with the help of Joe Shinn (Lawrence Livermore National Laboratory), Marty Leach (Lawrence Livermore National Laboratory), Ray Hosker (Atmospheric Turbulence and Diffusion Division), Leo Stockham (Northrop Grumman Information Technology) and Jim Bowers (Dugway Proving Grounds). This report gives a brief overview of the field campaign, describing the scientific objectives, the dates of the intensive observation periods, and the instruments deployed. The data from this field study is available to the scientific community through an on-line database that is managed by Dugway Proving Ground. This report will be included in the database to provide its users with some general information about the field study, and specific information about the instrument coordinates. Appendix A of this document provides the definitive record of the instrument locations during this field campaign, and Appendix B lists all the study principal investigators and participants.« less

ARC-2008-ACD07-0073-499

NASA Image and Video Library

2008-01-18

LCROSS leaves Northrup Grumman Redondo Beach, CA clean room post shippment verification tests before being mated to the Lunar Reconnaissance Orbitor (LR0) spacecraft for a piggyback ride to the Moon. With Kim Ennico Ames P.I. and Mark Shirley, Northrup Grumman.

By the Dozen: NASA's James Webb Space Telescope Mirrors

NASA Image and Video Library

2017-12-08

A view of the one dozen (out of 18) flight mirror segments that make up the primary mirror on NASA's James Webb Space Telescope have been installed at NASA's Goddard Space Flight Center. Credits: NASA/Chris Gunn More: Since December 2015, the team of scientists and engineers have been working tirelessly to install all the primary mirror segments onto the telescope structure in the large clean room at NASA's Goddard Space Flight Center in Greenbelt, Maryland. The twelfth mirror was installed on January 2, 2016. "This milestone signifies that all of the hexagonal shaped mirrors on the fixed central section of the telescope structure are installed and only the 3 mirrors on each wing are left for installation," said Lee Feinberg, NASA's Optical Telescope Element Manager at NASA Goddard. "The incredibly skilled and dedicated team assembling the telescope continues to find ways to do things faster and more efficiently." Each hexagonal-shaped segment measures just over 4.2 feet (1.3 meters) across and weighs approximately 88 pounds (40 kilograms). After being pieced together, the 18 primary mirror segments will work together as one large 21.3-foot (6.5-meter) mirror. The primary mirror will unfold and adjust to shape after launch. The mirrors are made of ultra-lightweight beryllium. The mirrors are placed on the telescope's backplane using a robotic arm, guided by engineers. The full installation is expected to be completed in a few months. The mirrors were built by Ball Aerospace & Technologies Corp., Boulder, Colorado. Ball is the principal subcontractor to Northrop Grumman for the optical technology and lightweight mirror system. The installation of the mirrors onto the telescope structure is performed by Harris Corporation of Rochester, New York. Harris Corporation leads integration and testing for the telescope. While the mirror assembly is a very significant milestone, there are many more steps involved in assembling the Webb telescope. The primary mirror and the tennis-court-sized sunshield are the largest and most visible components of the Webb telescope. However, there are four smaller components that are less visible, yet critical. The instruments that will fly aboard Webb - cameras and spectrographs with detectors able to record extremely faint signals — are part of the Integrated Science Instrument Module (ISIM), which is currently undergoing its final cryogenic vacuum test and will be integrated with the mirror later this year. Read more: www.nasa.gov/feature/goddard/2016/by-the-dozen-nasas-jame... NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

By the Dozen: NASA's James Webb Space Telescope Mirrors

NASA Image and Video Library

2016-01-07

Caption: One dozen (out of 18) flight mirror segments that make up the primary mirror on NASA's James Webb Space Telescope have been installed at NASA's Goddard Space Flight Center. Credits: NASA/Chris Gunn More: Since December 2015, the team of scientists and engineers have been working tirelessly to install all the primary mirror segments onto the telescope structure in the large clean room at NASA's Goddard Space Flight Center in Greenbelt, Maryland. The twelfth mirror was installed on January 2, 2016. "This milestone signifies that all of the hexagonal shaped mirrors on the fixed central section of the telescope structure are installed and only the 3 mirrors on each wing are left for installation," said Lee Feinberg, NASA's Optical Telescope Element Manager at NASA Goddard. "The incredibly skilled and dedicated team assembling the telescope continues to find ways to do things faster and more efficiently." Each hexagonal-shaped segment measures just over 4.2 feet (1.3 meters) across and weighs approximately 88 pounds (40 kilograms). After being pieced together, the 18 primary mirror segments will work together as one large 21.3-foot (6.5-meter) mirror. The primary mirror will unfold and adjust to shape after launch. The mirrors are made of ultra-lightweight beryllium. The mirrors are placed on the telescope's backplane using a robotic arm, guided by engineers. The full installation is expected to be completed in a few months. The mirrors were built by Ball Aerospace & Technologies Corp., Boulder, Colorado. Ball is the principal subcontractor to Northrop Grumman for the optical technology and lightweight mirror system. The installation of the mirrors onto the telescope structure is performed by Harris Corporation of Rochester, New York. Harris Corporation leads integration and testing for the telescope. While the mirror assembly is a very significant milestone, there are many more steps involved in assembling the Webb telescope. The primary mirror and the tennis-court-sized sunshield are the largest and most visible components of the Webb telescope. However, there are four smaller components that are less visible, yet critical. The instruments that will fly aboard Webb - cameras and spectrographs with detectors able to record extremely faint signals — are part of the Integrated Science Instrument Module (ISIM), which is currently undergoing its final cryogenic vacuum test and will be integrated with the mirror later this year. Read more: www.nasa.gov/feature/goddard/2016/by-the-dozen-nasas-jame... NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

The Secrets of NASA's Webb Telescope’s "Deployable Tower Assembly"

NASA Image and Video Library

2017-12-08

Building a space telescope to see the light from the earliest stars of our universe is a pretty complex task. Although much of the attention goes to instruments and the giant mirrors on NASA's James Webb Space Telescope, there are other components that have big jobs to do and that required imagination, engineering, and innovation to become a reality. For example, engineers working on the Webb telescope have to think of everything from keeping instruments from overheating or freezing, to packing up the Webb, which is as big as a tennis court, to fit inside the rocket that will take it to space. Those are two areas where the "DTA" or Deployable Tower Assembly (DTA) plays a major role. The DTA looks like a big black pipe and is made out of graphite-epoxy composite material to ensure stability and strength with extreme changes in temperature like those encountered in space. When fully deployed, the DTA reaches ten feet in length. The DTA interfaces and supports the spacecraft and the telescope structures. It features two large nested telescoping tubes, connected by a mechanized lead screw. It is a deployable structure that is both very light and extremely strong and stable. The Webb telescope’s secondary mirror support structure and DTA contribute to how the telescope and instruments fit into the rocket fairing in preparation for launch. The DTA allows the Webb to be short enough when stowed to fit in the rocket fairing with an acceptably low center of gravity for launch. Several days after the Webb telescope is launched, the DTA will deploy, or separate, the telescope mirrors and instruments from the spacecraft bus and sunshield. This separation allows the sunshield to unfurl and shade the telescope and instruments from radiant heat and stray light from the sun and Earth. The DTA was designed, built and tested by Astro Aerospace - a Northrop Grumman Company, in Carpinteria, California. The James Webb Space Telescope is the scientific successor to NASA's Hubble Space Telescope. It will be the most powerful space telescope ever built. The Webb telescope is an international project led by NASA with its partners, the European Space Agency and the Canadian Space Agency. For more information about the Webb telescope, visit: www.nasa.gov/webb or jwst.nasa.gov NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

Grumman Takes Initiative

ERIC Educational Resources Information Center

Gilmore, A. W.

1970-01-01

Grumman Company has attempted to counter their acute shortage of engineers with diversified experience by establishing the Engineering Professional Development Program (EPDP). Selected engineers participate in an evening scholarship program, assignments to various sections within the company, and in-house seminars and programs to prepare them for…

F-14A aircraft high-speed flow simulations

NASA Technical Reports Server (NTRS)

Boppe, C. W.; Rosen, B. S.

1985-01-01

A model of the Grumman/Navy F-14A aircraft was developed for analyses using the NASA/Grumman Transonic Wing-Body Code. Computations were performed for isolated wing and wing fuselage glove arrangements to determine the extent of aerodynamic interference effects which propagate outward onto the main wing outer panel. Additional studies were conducted using the full potential analysis, FLO 22, to calibrate any inaccuracies that might accrue because of small disturbance code limitations. Comparisons indicate that the NASA/Grumman code provides excellent flow simulations for the range of wing sweep angles and flow conditions that will be of interest for the upcoming F-14 Variable Sweep Flight Transition Experiment.

77 FR 64889 - Amendment of Class D and Class E Airspace; Hawthorne, CA

Federal Register 2010, 2011, 2012, 2013, 2014

2012-10-24

...-2012-1092; Airspace Docket No. 12-AWP-6] Amendment of Class D and Class E Airspace; Hawthorne, CA...: This action amends the airspace description for Class D and Class E airspace at Jack Northrop Field... the legal description of the existing Class D and E airspace at Jack Northrop Field/Hawthorne...

Grumman S2F-1 Tracker at NACA Lewis

NASA Image and Video Library

1956-08-21

The NACA’s Lewis Flight Propulsion Laboratory acquired the Grumman S2F-1 Tracker from the Navy in 1955 to study icing instrumentation. Lewis’s icing research program was winding down at the time. The use of jet engines was increasing thus reducing the threat of ice accumulation. Nonetheless Lewis continued research on the instrumentation used to detect icing conditions. The S2F-1 Tracker was a carrier-based submarine hunter for the Navy. Grumman developed the Tracker as a successor to its Korean War-era Guardian patrol aircraft. Prototypes first flew in late 1952 and battle-ready versions entered Naval service in early 1954. The Navy utilized the Trackers to protect fleets from attack.

Test and evaluation report for the Grumman-Olson Kurbwatt

DOE Office of Scientific and Technical Information (OSTI.GOV)

Barnett, J.H.; Carter, C.L.; Metcalfe, J.K.

1982-01-01

This report documents the results obtained from tests performed on the Kurbwatt, an electric vehicle (EV) designed and constructed by Grumman Olson (a divison of Grumman Allied Industries, Inc.), between August 1981 and April 1982 at the Tennessee Valley Authority (TVA) Electric Vehicle Test Facility (EVTF) in Chattanooga, Tennessee. Data on vehicle physical characteristics and performance acquired during tests conducted under test track, dynamometer, and on-road conditions are presented along with descriptions of the vehicle and its components and information on the reliability of the vehicle during the test period. This testing was performed by TVA and was sponsored bymore » the Electric Power Research Institute (EPRI).« less

Lightening the Load

DTIC Science & Technology

2007-09-09

Research, Engineering and Systems) Dr. John C. Sommerer NRAC, Vice Chair; Director, S&T, Johns Hopkins Applied Physics Laboratory Dr. Walt...O’Donohue, Staff Officer General Dynamics Robotic Systems John H. Northrop & Associates Mr. John H. Northrop, Executive Director General Dynamics...Equipment, US Army LtCol John Lemondes, PM Soldier as a System LTL Efforts US Army Mr. Bob Conklin, Staff UK LTL Efforts Equipment Capability

Three-Stage InP Submillimeter-Wave MMIC Amplifier

NASA Technical Reports Server (NTRS)

Pukala, David; Samoska, Lorene; Man, King; Gaier, Todd; Deal, William; Lai, Richard; Mei, Gerry; Makishi, Stella

2008-01-01

A submillimeter-wave monolithic integrated- circuit (S-MMIC) amplifier has been designed and fabricated using an indium phosphide (InP) 35-nm gate-length high electron mobility transistor (HEMT) device, developed at Northrop Grumman Corporation. The HEMT device employs two fingers each 15 micrometers wide. The HEMT wafers are grown by molecular beam epitaxy (MBE) and make use of a pseudomorphic In0.75Ga0.25As channel, a silicon delta-doping layer as the electron supply, an In0.52Al0.48As buffer layer, and an InP substrate. The three-stage design uses coplanar waveguide topology with a very narrow ground-to-ground spacing of 14 micrometers. Quarter-wave matching transmission lines, on-chip metal-insulator-metal shunt capacitors, series thin-film resistors, and matching stubs were used in the design. Series resistors in the shunt branch arm provide the basic circuit stabilization. The S-MMIC amplifier was measured for S-parameters and found to be centered at 320 GHz with 13-15-dB gain from 300-345 GHz. This chip was developed as part of the DARPA Submillimeter Wave Imaging Focal Plane Technology (SWIFT) program (see figure). Submillimeter-wave amplifiers could enable more sensitive receivers for earth science, planetary remote sensing, and astrophysics telescopes, particularly in radio astronomy, both from the ground and in space. A small atmospheric window at 340 GHz exists and could enable ground-based observations. However, the submillimeter-wave regime (above 300 GHz) is best used for space telescopes as Earth s atmosphere attenuates most of the signal through water and oxygen absorption. Future radio telescopes could make use of S-MMIC amplifiers for wideband, low noise, instantaneous frequency coverage, particularly in the case of heterodyne array receivers.

Titan Lifting Entry & Atmospheric Flight (T-LEAF) Science Mission

NASA Astrophysics Data System (ADS)

Lee, G.; Sen, B.; Ross, F.; Sokol, D.

2016-12-01

Northrop Grumman has been developing the Titan Lifting Entry & Atmospheric Flight (T-LEAF) sky rover to roam the lower atmosphere and observe at close quarters the lakes and plains of Saturn's ocean moon, Titan. T-LEAF also supports surface exploration and science by providing precision delivery of in-situ instruments to the surface of Titan. T-LEAF is a highly maneuverable sky rover and its aerodynamic shape (i.e., a flying wing) does not restrict it to following prevailing wind patterns on Titan, but allows mission operators to chart its course. This freedom of mobility allows T-LEAF to follow the shorelines of Titan's methane lakes, for example, or to target very specific surface locations. We will present a straw man concept of T-LEAF, including size, mass, power, on-board science payloads and measurement, and surface science dropsonde deployment CONOPS. We will discuss the various science instruments and their vehicle level impacts, such as meteorological and electric field sensors, acoustic sensors for measuring shallow depths, multi-spectral imagers, high definition cameras and surface science dropsondes. The stability of T-LEAF and its long residence time on Titan will provide for time to perform a large aerial survey of select prime surface targets deployment of dropsondes at selected locations surface measurements that are coordinated with on-board remote measurements communication relay capabilities to orbiter (or Earth). In this context, we will specifically focus upon key factors impacting the design and performance of T-LEAF science: science payload accommodation, constraints and opportunities characteristics of flight, payload deployment and measurement CONOPS in the Titan atmosphere. This presentation will show how these factors provide constraints as well as enable opportunities for novel long duration scientific studies of Titan's surface.

GreenHouse gas Observations of the Stratosphere and Troposphere (GHOST): Deployment of a Novel Shortwave Infrared Spectrometer On Board the NASA Global Hawk Unmanned Aerial Vehicle

NASA Astrophysics Data System (ADS)

Humpage, N.; Boesch, H.; Palmer, P. I.; Parr-Burman, P.; Vick, A.; Bezawada, N.; Black, M.; Born, A.; Gao, X.; Pearson, D.; Samara-Ratna, P.; Strachan, J.; Wells, M.

2015-12-01

GHOST is a novel, compact shortwave infrared spectrometer, designed for remote sensing of tropospheric columns of greenhouse gases (GHGs) over the ocean from an unmanned aircraft. This is achieved by observing solar radiation at high spectral resolution which has been directly reflected by the ocean surface. The GHOST system has been specifically designed and built to address the following science objectives: 1) testing of atmospheric transport models; 2) validation of GHG column observations over oceans obtained using polar orbiting satellites; and 3) complement in-situ tropopause transition layer observations from other instruments. During January and February 2015 GHOST successfully underwent rigorous environmental testing and was installed on board the Northrop Grumman Global Hawk N872NA, an unmanned aircraft operated by NASA from the Armstrong Flight Research Centre at Edwards Air Force Base, California. Here, we present first results from two Global Hawk flights which took place in March 2015 as part of the CAST-ATTREX campaign. The science flights comprised long, approximately north-south transects over the eastern Pacific Ocean, providing an opportunity to observe spatial trends in GHG column concentrations on regional scale. The second science flight on 10th March 2015 coincided with overpasses from both the NASA OCO-2 (Orbiting Carbon Observatory) and the JAXA GOSAT (Greenhouse gases Observing SATellite) satellites, enabling inter-comparison of the GHOST results with total column observations from both satellites. A TCCON (Total Carbon Column Observing Network) station was also operational at Edwards during the two flights, allowing the GHOST observations to be validated against ground based total column measurements of GHGs.

Light Microscopy Module Imaging Tested and Demonstrated

NASA Technical Reports Server (NTRS)

Gati, Frank

2004-01-01

The Fluids Integrated Rack (FIR), a facility-class payload, and the Light Microscopy Module (LMM), a subrack payload, are integrated research facilities that will fly in the U.S. Laboratory module, Destiny, aboard the International Space Station. Both facilities are being engineered, designed, and developed at the NASA Glenn Research Center by Northrop Grumman Information Technology. The FIR is a modular, multiuser scientific research facility that is one of two racks that make up the Fluids and Combustion Facility (the other being the Combustion Integrated Rack). The FIR has a large volume dedicated for experimental hardware; easily reconfigurable diagnostics, power, and data systems that allow for unique experiment configurations; and customizable software. The FIR will also provide imagers, light sources, power management and control, command and data handling for facility and experiment hardware, and data processing and storage. The first payload in the FIR will be the LMM. The LMM integrated with the FIR is a remotely controllable, automated, on-orbit microscope subrack facility, with key diagnostic capabilities for meeting science requirements--including video microscopy to observe microscopic phenonema and dynamic interactions, interferometry to make thin-film measurements with nanometer resolution, laser tweezers to manipulate micrometer-sized particles, confocal microscopy to provide enhanced three-dimensional visualization of structures, and spectrophotometry to measure the photonic properties of materials. Vibration disturbances were identified early in the LMM development phase as a high risk for contaminating the science microgravity environment. An integrated FIR-LMM test was conducted in Glenn's Acoustics Test Laboratory to assess mechanical sources of vibration and their impact to microscopic imaging. The primary purpose of the test was to characterize the LMM response at the sample location, the x-y stage within the microscope, to vibration emissions from the FIR and LMM support structures.

Power management and distribution system for a More-Electric Aircraft (MADMEL) -- Program status

DOE Office of Scientific and Technical Information (OSTI.GOV)

Maldonado, M.A.; Shah, N.M.; Cleek, K.J.

1995-12-31

A number of technology breakthroughs in recent years have rekindled the concept of a more-electric aircraft. High-power solid-state switching devices, electrohydrostatic actuators (EHAs), electromechanical actuators (EMAs), and high-power generators are just a few examples of component developments that have made dramatic improvements in properties such as weight, size, power, and cost. However, these components cannot be applied piecemeal. A complete, and somewhat revolutionary, system design approach is needed to exploit the benefits that a more-electric aircraft can provide. A five-phase Power Management and Distribution System for a More-Electric Aircraft (MADMEL) program was awarded by the Air Force to the Northrop/Grumman,more » Military Aircraft Division team in September 1991. The objective of the program is to design, develop, and demonstrate an advanced electrical power generation and distribution system for a more-electric aircraft (MEA). The MEA emphasizes the use of electrical power in place of hydraulics, pneumatic, and mechanical power to optimize the performance and life cycle cost of the aircraft. This paper presents an overview of the MADMEL program and a top-level summary of the program results, development and testing of major components to date. In Phase 1 and Phase 2 studies, the electrical load requirements were established and the electrical power system architecture was defined for both near-term (NT-year 1996) and far-term (FT-year 2003) MEA application. The detailed design and specification for the electrical power system (EPS), its interface with the Vehicle Management System, and the test set-up were developed under the recently completed Phase 3. The subsystem level hardware fabrication and testing will be performed under the on-going Phase 4 activities. The overall system level integration and testing will be performed in Phase 5.« less

Hexavalent chromium emissions from aerospace operations: A case study

DOE Office of Scientific and Technical Information (OSTI.GOV)

Chaurushia, A.; Bajza, C.

1994-12-31

Northrop Aircraft Division (NAD) is subject to several air toxic regulations such as EPA SARA Title 3, California Assembly Bill 2588 (AB2588), and Proposition 65 and is a voluntary participant in air toxic emissions reduction programs such as the EPA 33/50 and MERIT Program. To quantify emissions, NAD initially followed regulatory guidelines which recommend that emission inventories of air toxics be based on engineering assumptions and conservative emission factors in absence of specific source test data. NAD was concerned that Chromium VI emissions from NAD`s spray coating and chemical tank line operations were not representative due to these techniques. Moremore » recently, NAD has relied upon information from its ongoing source testing program to determine emission rates of Chromium VI. Based on these source test results, NAD revised emission calculations for use in Chromium VI inventories, impact assessments and control strategies. NAD has been successful in demonstrating a significant difference between emissions calculated utilizing the source test results and emissions based on the traditional mass balance using agency suggested methods.« less

The Fable of Recognition: A Study of Northrop Frye as a Prophet

ERIC Educational Resources Information Center

Li, Peng

2011-01-01

Northrop Frye is a famous Canadian literary critic, but his fame enjoyed its peak in the 50s and 60s as a representative of the myth-archetypal school of literary criticism. When deconstruction was on the rise, it faded greatly, and what's more, sometimes Frye was taken as a notorious obstinate structuralist. In fact, even his fame as an…

Baseline experiments in teleoperator control

NASA Technical Reports Server (NTRS)

Hankins, W. W., III; Mixon, R. W.

1986-01-01

Studies have been conducted at the NASA Langley Research Center (LaRC) to establish baseline human teleoperator interface data and to assess the influence of some of the interface parameters on human performance in teleoperation. As baseline data, the results will be used to assess future interface improvements resulting from this research in basic teleoperator human factors. In addition, the data have been used to validate LaRC's basic teleoperator hardware setup and to compare initial teleoperator study results. Four subjects controlled a modified industrial manipulator to perform a simple task involving both high and low precision. Two different schemes for controlling the manipulator were studied along with both direct and indirect viewing of the task. Performance of the task was measured as the length of time required to complete the task along with the number of errors made in the process. Analyses of variance were computed to determine the significance of the influences of each of the independent variables. Comparisons were also made between the LaRC data and data taken earlier by Grumman Aerospace Corp. at their facilities.

A structural model for composite rotor blades and lifting surfaces

NASA Technical Reports Server (NTRS)

Rehfield, Lawrence W.; Atilgan, Ali R.

1987-01-01

Composite material systems are currently candidates for aerospace structures, primarily for the design flexibiity they offer i.e., it is possible to tailor the material and manufacturing approach to the application. Two notable examples are the wing of the Grumman/USAF/DARPA X-29 and rotor blades under development by the U.S.A. Aerostructures Directorate (AVSCOM), Langley Research Center. A working definition of elastic or structural tailoring is the use of structural concept, fiber orientation, ply stacking sequence, and a blend of materials to achieve specific performance goals. In the design process, choices of materials and dimensions are made which produce specific response characteristics which permit the selected goals to be achieved. Common choices for tailoring goals are preventing instabilities or vibration resonances or enhancing damage tolerance. An essential, enabling factor in the design of tailored composite structures is structural modeling that accurately, but simply, characterizes response. The objective of this paper is to improve the single-cell beam model for composite rotor blades or lifting surfaces and to demonstrate its usefullness in applications.

Effects of Changes to Arc Dipole Length

DOE Office of Scientific and Technical Information (OSTI.GOV)

Tepikian, Steven

1994-06-01

The arc dipole magnetic length in the design is 9.45m. The first arc magnets were made with BNL parts and have the proper length, however, the dipoles made with Grumman parts has a shorter magnetic length. The current projected magnet length of the Grumman dipoles is 9.422m. In this note we discuss the consequences of this change.

Composite Failure Analysis Handbook. Volume 2. Technical Handbook/ Part 2. Atlas of Fractographs

DTIC Science & Technology

1992-02-01

ADDRESS( ES ) 8. PERFORMING ORGANIZATION Northrop Corporation REPORT NUMBER Aircraft Division One Northrop Avenue Hawthorne, California 90250-3277 9...SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS( ES ) 10. SPONSORING/ MONITORING Wright Laboratory (WL/MLSA) AGENCY REPORT NUMBER Materials Directorate...specimens of 0/90 laminates were tested in a Satec 25,000-lb capacity Universal test machine with the crosshead speed set at .001 in/min. Deflection

Supportability evaluation of thermoplastic and thermoset composites

NASA Technical Reports Server (NTRS)

Chanani, G. R.; Boldi, D.; Cramer, S. G.; Heimerdinger, M. W.

1990-01-01

Nearly 300 advanced composite components manufactured by Northrop Corporation are flying on U.S. Air Force and U.S. Navy supersonic aircraft as part of a three-year Air Force/Navy/Northrop supportability evaluation. Both thermoplastic and high-temperature thermoset composites were evaluated for their in-service performance on 48 USAF and Navy F-5E fighter and USAFT-38 trainer aircraft in the first large-scale, long-term maintenance evaluation of these advanced materials. Northrop manufactured four types of doors for the project-avionics bay access, oil fill, inlet duct inspection, and a main landing gear door. The doors are made of PEEK (polyetheretherketone) thermoplastic, which is tougher and potentially less expensive to manufacture than conventional composites; and 5250-3 BMI (bismaleimide) thermoset, which is manufactured like a conventional epoxy composite but can withstand higher service temperatures. Results obtained so far indicate that both the BMI and PEEK are durable with PEEK being somewhat better than BMI.

Navy DD(X), CG(X), and LCS Ship Acquisition Programs: Oversight Issues and Options for Congress

DTIC Science & Technology

2005-04-21

6. AUTHOR(S) 5d. PROJECT NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Congressional Research...between Northrop Grumman’s Ship System Division ( NGSS ) and General Dynamics’ Bath Iron Works (GD/BIW) for the right to build all DD(X)s. Several Members...premature” a Navy proposal to hold a one-time, winner-take-all competition between Northrop Grumman’s Ship System Division ( NGSS ) and General Dynamics

Navy DD(X), CG(X), and LCS Ship Acquisition Programs: Oversight Issues and Options for Congress

DTIC Science & Technology

2005-06-24

6. AUTHOR(S) 5d. PROJECT NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Congressional Research...competition between Northrop Grumman’s Ship System Division ( NGSS ) and General Dynamics’ Bath Iron Works (GD/BIW) for the right to build all DD(X)s. The...competition between Northrop Grumman’s Ship System Division ( NGSS ) and General Dynamics’ Bath Iron Works (GD/BIW) for the right to build all DD(X)s

Navy DD(X), CG(X), and LCS Ship Acquisition Programs: Oversight Issues and Options for Congress

DTIC Science & Technology

2006-03-07

PROJECT NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Congressional Research Service The...New Orleans and a third facility at Gulfport, MS, form Northrop Grumman’s Ship Systems ( NGSS ) division. The Navy has not procured any frigates since...the program, it had decided to award the contract for the next phase on a sole-source basis to Northrop Grumman’s Ship Systems ( NGSS ) division, which

Formalization of the engineering science discipline - knowledge engineering

NASA Astrophysics Data System (ADS)

Peng, Xiao

Knowledge is the most precious ingredient facilitating aerospace engineering research and product development activities. Currently, the most common knowledge retention methods are paper-based documents, such as reports, books and journals. However, those media have innate weaknesses. For example, four generations of flying wing aircraft (Horten, Northrop XB-35/YB-49, Boeing BWB and many others) were mostly developed in isolation. The subsequent engineers were not aware of the previous developments, because these projects were documented such which prevented the next generation of engineers to benefit from the previous lessons learned. In this manner, inefficient knowledge retention methods have become a primary obstacle for knowledge transfer from the experienced to the next generation of engineers. In addition, the quality of knowledge itself is a vital criterion; thus, an accurate measure of the quality of 'knowledge' is required. Although qualitative knowledge evaluation criteria have been researched in other disciplines, such as the AAA criterion by Ernest Sosa stemming from the field of philosophy, a quantitative knowledge evaluation criterion needs to be developed which is capable to numerically determine the qualities of knowledge for aerospace engineering research and product development activities. To provide engineers with a high-quality knowledge management tool, the engineering science discipline Knowledge Engineering has been formalized to systematically address knowledge retention issues. This research undertaking formalizes Knowledge Engineering as follows: 1. Categorize knowledge according to its formats and representations for the first time, which serves as the foundation for the subsequent knowledge management function development. 2. Develop an efficiency evaluation criterion for knowledge management by analyzing the characteristics of both knowledge and the parties involved in the knowledge management processes. 3. Propose and develop an innovative Knowledge-Based System (KBS), AVD KBS, forming a systematic approach facilitating knowledge management. 4. Demonstrate the efficiency advantages of AVDKBS over traditional knowledge management methods via selected design case studies. This research formalizes, for the first time, Knowledge Engineering as a distinct discipline by delivering a robust and high-quality knowledge management and process tool, AVDKBS. Formalizing knowledge proves to significantly impact the effectiveness of aerospace knowledge retention and utilization.

Grumman electric truck development

DOE Office of Scientific and Technical Information (OSTI.GOV)

Kessler, J.C.; Ferdman, S.

1981-11-01

An electric truck development was undertaken to prepare for the markets of the 1980's. Grumman is using its aluminum truck bodies technology to create a light weight vehicle. A redesigned unitized, all aluminum body and a new propulsion system resulted in the desired vehicle. The vehicle meets the requirements of the US Postal Service and the DOE Demonstration program. The unitized chassisless structure is designed to take major driving loads. Design features and performance characteristics are enumerated. Safety and service considerations have been incorporated into the vehicle.

Force Characteristics in the Submerged and Planing Condition of a 1/5.78-Scale Model of a Hydro-Ski-Wheel Combination for the Grumman JRF-5 Airplane. TED No. NACA DE 357

NASA Technical Reports Server (NTRS)

Land, Norman S.; Pelz, Charles A.

1952-01-01

Force characteristics determined from tank tests of a 1/5.78 scale model of a hydro-ski-wheel combination for the Grumman JRF-5 airplane are presented. The model was tested in both the submerged and planing conditions over a range of trim, speed, and load sufficiently large to represent the most probable full-size conditions.

UAS Related Activities at NASA's Dryden Flight Research Center

NASA Technical Reports Server (NTRS)

Bauer, Jeffrey E.

2009-01-01

NASA s Dryden Flight Research Center is completing its refurbishment and initial flights of one the pre-production Global Hawk aircraft it received from the U.S. Air Force. NASA Dryden has an agreement with the Global Hawk s manufacturer, Northrop Grumman, to partner in the refurbishment and flight operations of the vehicles. The National Oceanic and Atmospheric Administration (NOAA) has also partnered on the project and is assisting NASA with project management and pilot responsibilities for the aircraft. NASA and NOAA will be using the Global Hawks to conduct earth science research. The earth science community is increasing utilizing UAS of all sizes and capabilities to collect important data on a variety of issues including important global climate change issues. To pursue the data collection needs of the science community there is a growing demand for international collaboration with respect to operating UAS in global airspace. Operations of NASA s Ikhana aircraft continued this past year. The Ikhana is a modified Predator B UAS. A UAS dedicated to research at NASA Dryden is the X-48B blended wing body research aircraft. Flight tests with the 500- pound, remotely piloted test vehicle are now in a block 4 phase involving parameter identification and maneuvers to research the limits of the engine in stall situations. NASA s participation in the blended wing body research effort is focused on fundamental, advanced flight dynamics and structural design concepts within the Subsonic Fixed Wing project, part of the Fundamental Aeronautics program managed through NASA s Aeronautics Research Mission Directorate. Potential benefits of the aircraft include increased volume for carrying capacity, efficient aerodynamics for reduced fuel burn and possibly significant reductions in noise due to propulsion integration options. NASA Dryden continues to support the UAS industry by facilitating access to three specially designated test areas on Edwards Air Force Base for the development of small UAS.

Data annotation, recording and mapping system for the US open skies aircraft

DOE Office of Scientific and Technical Information (OSTI.GOV)

Brown, B.W.; Goede, W.F.; Farmer, R.G.

1996-11-01

This paper discusses the system developed by Northrop Grumman for the Defense Nuclear Agency (DNA), US Air Force, and the On-Site Inspection Agency (OSIA) to comply with the data annotation and reporting provisions of the Open Skies Treaty. This system, called the Data Annotation, Recording and Mapping System (DARMS), has been installed on the US OC-135 and meets or exceeds all annotation requirements for the Open Skies Treaty. The Open Skies Treaty, which will enter into force in the near future, allows any of the 26 signatory countries to fly fixed wing aircraft with imaging sensors over any of themore » other treaty participants, upon very short notice, and with no restricted flight areas. Sensor types presently allowed by the treaty are: optical framing and panoramic film cameras; video cameras ranging from analog PAL color television cameras to the more sophisticated digital monochrome and color line scanning or framing cameras; infrared line scanners; and synthetic aperture radars. Each sensor type has specific performance parameters which are limited by the treaty, as well as specific annotation requirements which must be achieved upon full entry into force. DARMS supports U.S. compliance with the Opens Skies Treaty by means of three subsystems: the Data Annotation Subsytem (DAS), which annotates sensor media with data obtained from sensors and the aircraft`s avionics system; the Data Recording System (DRS), which records all sensor and flight events on magnetic media for later use in generating Treaty mandated mission reports; and the Dynamic Sensor Mapping Subsystem (DSMS), which provides observers and sensor operators with a real-time moving map displays of the progress of the mission, complete with instantaneous and cumulative sensor coverages. This paper will describe DARMS and its subsystems in greater detail, along with the supporting avionics sub-systems. 7 figs.« less

Distributed Exhaust Nozzles for Jet Noise Reduction

NASA Technical Reports Server (NTRS)

Ahuja, K. K.; Gaeta, R. J.; Hellman, B.; Schein, D. B.; Solomon, W. D., Jr.; Huff, Dennis (Technical Monitor)

2001-01-01

The main objective of this study is to validate the jet noise reduction potential of a concept associated with distributed exhaust nozzles. Under this concept the propulsive thrust is generated by a larger number of discrete plumes issuing from an array of small or mini-nozzles. The potential of noise reduction of this concept stems from the fact that a large number of small jets will produce very high frequency noise and also, if spaced suitably, they will coalesce at a smaller velocity to produce low amplitude, low frequency noise. This is accomplished through detailed acoustic and fluid measurements along with a Computational Fluidic Dynamic (CFD) solution of the mean (DE) Distributed Exhaust nozzle flowfield performed by Northrop-Grumman. The acoustic performance is quantified in an anechoic chamber. Farfield acoustic data is acquired for a DE nozzle as well as a round nozzle of the same area. Both these types of nozzles are assessed numerically using Computational Fluid Dynamic (CFD) techniques. The CFD analysis ensures that both nozzles issued the same amount of airflow for a given nozzle pressure ratio. Data at a variety of nozzle pressure ratios are acquired at a range of polar and azimuthal angles. Flow visualization of the DE nozzle is used to assess the fluid dynamics of the small jet interactions. Results show that at high subsonic jet velocities, the DE nozzle shifts its frequency of peak amplitude to a higher frequency relative to a round nozzle of equivalent area (from a S(sub tD) = 0.24 to 1. 3). Furthermore, the DE nozzle shows reduced sound pressure levels (as much as 4 - 8 dB) in the low frequency part of the spectrum (less than S(sub tD) = 0.24 ) compared to the round nozzle. At supersonic jet velocities, the DE nozzle does not exhibit the jet screech and the shock-associated broadband noise is reduced by as much as 12 dB.

The Advanced Technology Microwave Sounder (ATMS): First Year On-Orbit

NASA Technical Reports Server (NTRS)

Kim, Edward J.

2012-01-01

The Advanced Technology Microwave Sounder (ATMS) is a new satellite microwave sounding sensor designed to provide operational weather agencies with atmospheric temperature and moisture profile information for global weather forecasting and climate applications. A TMS will continue the microwave sounding capabilities first provided by its predecessors, the Microwave Sounding Unit (MSU) and Advanced Microwave Sounding Unit (AMSU). The first flight unit was launched a year ago in October, 2011 aboard the Suomi-National Polar-Orbiting Partnership (S-NPP) satellite, part of the new Joint Polar-Orbiting Satellite System (JPSS). Microwave soundings by themselves are the highest-impact input data used by Numerical Weather Prediction models; and A TMS, when combined with the Cross-track Infrared Sounder (CrIS), forms the Cross-track Infrared and Microwave Sounding Suite (CrIMSS). The microwave soundings help meet sounding requirements under cloudy sky conditions and provide key profile information near the surface. ATMS was designed & built by Aerojet Corporation in Azusa, California, (now Northrop Grumman Electronic Systems). It has 22 channels spanning 23-183 GHz, closely following the channel set of the MSU, AMSU-AI/2, AMSU-B, Microwave Humidity Sounder (MHS), and Humidity Sounder for Brazil (HSB). It continues their cross-track scanning geometry, but for the first time, provides Nyquist sample spacing. All this is accomplished with approximately V. the volume, Y, the mass, and Y, the power of the three AMSUs. A description will be given of its performance from its first year of operation as determined by post-launch calibration activities. These activities include radiometric calibration using the on-board warm targets and cold space views, and geolocation determination. Example imagery and zooms of specific weather events will be shown. The second ATMS flight model is currently under construction and planned for launch on the "Jl" satellite of the JPSS program in approximately 2016. Additional units are expected on the J2 and 13 satellites, as well as potentially on future European METOP satellites.

Thermo-chemical Ice Penetrator for Icy Moons

NASA Astrophysics Data System (ADS)

Arenberg, J. W.; Lee, G.; Harpole, G.; Zamel, J.; Sen, B.; Ross, F.; Retherford, K. D.

2016-12-01

The ability to place sensors or to take samples below the ice surface enables a wide variety of potential scientific investigations. Penetrating an ice cap can be accomplished via a mechanical drill, laser drill, kinetic impactor, or heated penetrator. This poster reports on the development of technology for the latter most option, namely a self-heated probe driven by an exothermic chemical reaction: a Thermo-chemical ice penetrator (TChIP). Our penetrator design employs a eutectic mix of alkali metals that produce an exothermic reaction upon contact with an icy surface. This reaction increases once the ice starts melting, so no external power is required. This technology is inspired by a classified Cold-War era program developed at Northrop Grumman for the US Navy. Terrestrial demonstration of this technology took place in the Arctic; however, this device cannot be considered high TRL for application at the icy moons of the solar system due to the environmental differences between Earth's Arctic and the icy moons. These differences demand a TChIP design specific to these cold, low mass, airless worlds. It is expected that this model of TChIP performance will be complex, incorporating all of the forces on the penetrator, gravity, the thermo-chemistry at the interface between penetrator and ice, and multi-phase heat and mass transport, and hydrodynamics. Our initial efforts are aimed at the development of a validated set of tools and simulations to predict the performance of the penetrator for both the environment found on these icy moons and for a terrestrial environment. The purpose of the inclusion of the terrestrial environment is to aid in model validation. Once developed and validated, our models will allow us to design penetrators for a specific scientific application on a specific body. This poster discusses the range of scientific investigations that are enabled by TChIP. We also introduce the development plan to advance TChIP to the point where it can be considered for infusion into a program.

Technology for a Thermo-chemical Ice Penetrator for Icy Moons

NASA Astrophysics Data System (ADS)

Arenberg, Jonathan; Harpole, George; Zamel, James; Sen, Bashwar; Lee, Greg; Ross, Floyd; Retherford, Kurt D.

2016-10-01

The ability to place sensors or to take samples below the ice surface enables a wide variety of potential scientific investigations. Penetrating an ice cap can be accomplished via a mechanical drill, laser drill, kinetic impactor, or heated penetrator. This poster reports on the development of technology for the latter most option, namely a self-heated probe driven by an exothermic chemical reaction: a Thermo-chemical ice penetrator (TChIP). Our penetrator design employs a eutectic mix of alkali metals that produce an exothermic reaction upon contact with an icy surface. This reaction increases once the ice starts melting, so no external power is required. This technology is inspired by a classified Cold-War era program developed at Northrop Grumman for the US Navy. Terrestrial demonstration of this technology took place in the Arctic; however, this device cannot be considered high TRL for application at the icy moons of the solar system due to the environmental differences between Earth's Arctic and the icy moons. These differences demand a TChIP design specific to these cold, low mass, airless worlds. It is expected that this model of TChIP performance will be complex, incorporating all of the forces on the penetrator, gravity, the thermo-chemistry at the interface between penetrator and ice, and multi-phase heat and mass transport, and hydrodynamics. Our initial efforts are aimed at the development of a validated set of tools and simulations to predict the performance of the penetrator for both the environment found on these icy moons and for a terrestrial environment. The purpose of the inclusion of the terrestrial environment is to aid in model validation. Once developed and validated, our models will allow us to design penetrators for a specific scientific application on a specific body. This poster discusses the range of scientific investigations that are enabled by TChIP. We also introduce the development plan to advance TChIP to the point where it can be considered for infusion into a program.

On-Wafer Measurement of a Multi-Stage MMIC Amplifier with 10 dB of Gain at 475 GHz

NASA Technical Reports Server (NTRS)

Samoska, Lorene A.; Fung, KingMan; Pukala, David M.; Kangaslahti, Pekka P.; Lai, Richard; Ferreira, Linda

2012-01-01

JPL has measured and calibrated a WR2.2 waveguide wafer probe from GGB Industries in order to allow for measurement of circuits in the 325-500 GHz range. Circuits were measured, and one of the circuits exhibited 10 dB of gain at 475 GHz. The MMIC circuit was fabricated at Northrop Grumman Corp. (NGC) as part of a NASA Innovative Partnerships Program, using NGC s 35-nm-gatelength InP HEMT process technology. The chip utilizes three stages of HEMT amplifiers, each having two gate fingers of 10 m in width. The circuits use grounded coplanar waveguide topology on a 50- m-thick substrate with through substrate vias. Broadband matching is achieved with coplanar waveguide transmission lines, on-chip capacitors, and open stubs. When tested with wafer probing, the chip exhibited 10 dB of gain at 475 GHz, with over 9 dB of gain from 445-490 GHz. Low-noise amplifiers in the 400-500 GHz range are useful for astrophysics receivers and earth science remote sensing instruments. In particular, molecular lines in the 400-500 GHz range include the CO 4-3 line at 460 GHz, and the CI fine structure line at 492 GHz. Future astrophysics heterodyne instruments could make use of high-gain, low-noise amplifiers such as the one described here. In addition, earth science remote sensing instruments could also make use of low-noise receivers with MMIC amplifier front ends. Present receiver technology typically employs mixers for frequency down-conversion in the 400-500 GHz band. Commercially available mixers have typical conversion loss in the range of 7-10 dB with noise figure of 1,000 K. A low-noise amplifier placed in front of such a mixer would have 10 dB of gain and lower noise figure, particularly if cooled to low temperature. Future work will involve measuring the noise figure of this amplifier.

Venus Atmospheric Maneuverable Platform (VAMP)

NASA Astrophysics Data System (ADS)

Shapiro Griffin, Kristen L.; Sokol, D.; Dailey, D.; Lee, G.; Polidan, R.

2013-10-01

We have explored a possible new approach to Venus upper atmosphere exploration by applying Northrop Grumman (non-NASA) development programs to the challenges associated with Venus upper atmosphere science missions. Our concept is a low ballistic coefficient (<50 Pa), semi-buoyant aircraft that deploys prior to entering the Venus atmosphere, enters the atmosphere without an aeroshell, and provides a long-lived (months to years), maneuverable vehicle capable of carrying science payloads to explore the Venus upper atmosphere. In this presentation we report results from our ongoing study and plans for future analyses and prototyping. We discuss the overall mission architecture and concept of operations from launch through Venus arrival, orbit, entry, and atmospheric science operations. We present a strawman concept of VAMP, including ballistic coefficient, planform area, percent buoyancy, inflation gas, wing span, vehicle mass, power supply, propulsion, materials considerations, structural elements, subsystems, and packaging. The interaction between the VAMP vehicle and the supporting orbiter will also be discussed. In this context, we specifically focus upon four key factors impacting the design and performance of VAMP: 1. Feasibility of and options for the deployment of the vehicle in space 2. Entry into the Venus atmosphere, including descent profile, heat rate, total heat load, stagnation temperature, control, and entry into level flight 3. Characteristics of flight operations and performance in the Venus atmosphere: altitude range, latitude and longitude access, day/night performance, aircraft performance (aerodynamics, power required vs. power available, propulsion, speed, percent buoyancy), performance sensitivity to payload weight 4. Science payload accommodation, constraints, and opportunities We discuss interdependencies of the above factors and the manner in which the VAMP strawman’s characteristics affect the CONOPs and the science objectives. We show how these factors provide constraints as well as enable opportunities for novel long duration scientific studies of the Venus upper atmosphere that support VEXAG goals 2 and 3.

Sensor-centric calibration and characterization of the VIIRS Ocean Color bands using Suomi NPP operational data

NASA Astrophysics Data System (ADS)

Pratt, P.

2012-12-01

Ocean color bands on VIIRS span the visible spectrum and include two NIR bands. There are sixteen detectors per band and two HAM (Half-angle mirror) sides giving a total of thirty two independent systems. For each scan, thirty two hundred pixels are collected and each has a fixed specific optical path and a dynamic position relative to the earth geoid. For a given calibration target where scene variation is minimized, sensor characteristics can be observed. This gives insight into the performance and calibration of the instrument from a sensor-centric perspective. Calibration of the blue bands is especially challenging since there are few blue targets on land. An ocean region called the South Pacific Gyre (SPG) was chosen for its known stability and large area to serve as a calibration target for this investigation. Thousands of pixels from every granule that views the SPG are collected daily through an automated system and tabulated along with the detector, HAM and scan position. These are then collated and organized in a sensor-centric set of tables. The data are then analyzed by slicing by each variable and then plotted in a number of ways over time. Trends in the data show that the VIIRS sensor is largely behaving as expected according to heritage data and also reveals weaknesses where additional characterization of the sensor is possible. This work by Northrop Grumman NPP CalVal Team is supporting the VIIRS on-orbit calibration and validation teams for the sensor and ocean color as well as providing scientists interested in performing ground truth with results that show which detectors and scan angles are the most reliable over time. This novel approach offers a comprehensive sensor-centric on-orbit characterization of the VIIRS instrument on the NASA Suomi NPP mission.

Richard G. Ewers

NASA Image and Video Library

1998-12-02

Richard G. (Dick) Ewers became a pilot in the Flight Crew Branch of NASA's Dryden Flight Research Center, Edwards, California, in May 1998. His flying duties focus on operation of the Airborne Science DC-8 and Systems Research F/A-18 aircraft, but he also maintains qualifications in the King Air and T-34C. He has more than 32 years and nearly 9,000 hours of military and civilian flight experience in all types of aircraft from jet fighters to blimps. Ewers came to NASA Dryden from a position as an engineering test pilot with Northrop Grumman's Electronic Sensors and Systems Division (formerly Westinghouse's Electronic Systems Group). He spent eight and a half years with Westinghouse flight testing radar and forward looking infrared systems under development for military and civilian use. Before going to work for Westinghouse, Ewers served for more than 21 years as a U.S. Marine Corps fighter and test pilot, flying F-4, A-4, and F/A-18 aircraft. He underwent flight training at Naval Air Station Pensacola, Fla., in 1969-70. He was subsequently assigned to both fighter/attack and reconnaissance squadrons before ultimately commanding an F-4S squadron for two years. Additionally, his flying included combat service in Vietnam and operational exchange tours with both U.S. Navy and U.S. Air Force squadrons flying F-4s around the world, including off aircraft carriers. Ewers graduated from the U.S. Naval Test Pilot School in 1981 and subsequently served two tours as a test pilot at the Naval Air Test Center, Patuxent River, Md. Most of his flight test experience was with the F/A-18 Hornet. He retired from the Marine Corps in 1989 with the rank of lieutenant colonel. Ewers graduated from the U.S. Air Force Academy in 1968 with a bachelor of science degree in engineering mechanics. He earned a master of science degree in aeronautical systems from the University of West Florida in 1970.

Integrated Decision Support for Global Environmental Change Adaptation

NASA Astrophysics Data System (ADS)

Kumar, S.; Cantrell, S.; Higgins, G. J.; Marshall, J.; VanWijngaarden, F.

2011-12-01

Environmental changes are happening now that has caused concern in many parts of the world; particularly vulnerable are the countries and communities with limited resources and with natural environments that are more susceptible to climate change impacts. Global leaders are concerned about the observed phenomena and events such as Amazon deforestation, shifting monsoon patterns affecting agriculture in the mountain slopes of Peru, floods in Pakistan, water shortages in Middle East, droughts impacting water supplies and wildlife migration in Africa, and sea level rise impacts on low lying coastal communities in Bangladesh. These environmental changes are likely to get exacerbated as the temperatures rise, the weather and climate patterns change, and sea level rise continues. Large populations and billions of dollars of infrastructure could be affected. At Northrop Grumman, we have developed an integrated decision support framework for providing necessary information to stakeholders and planners to adapt to the impacts of climate variability and change at the regional and local levels. This integrated approach takes into account assimilation and exploitation of large and disparate weather and climate data sets, regional downscaling (dynamic and statistical), uncertainty quantification and reduction, and a synthesis of scientific data with demographic and economic data to generate actionable information for the stakeholders and decision makers. Utilizing a flexible service oriented architecture and state-of-the-art visualization techniques, this information can be delivered via tailored GIS portals to meet diverse set of user needs and expectations. This integrated approach can be applied to regional and local risk assessments, predictions and decadal projections, and proactive adaptation planning for vulnerable communities. In this paper we will describe this comprehensive decision support approach with selected applications and case studies to illustrate how this system of systems approach could help the local governments and concerned institutions worldwide to adapt to gradually changing environmental conditions as well as manage impacts of extreme events such as droughts, floods, heat waves, wildfires, hurricanes, and storm surges.

SIM Planetquest Science and Technology: A Status Report

NASA Technical Reports Server (NTRS)

Edberg, Stephen J.; Laskin, Robert A.; Marr, James C., IV; Unwin, Stephen C.; Shao, Michael

2007-01-01

Optical interferometry will open new vistas for astronomy over the next decade. The Space Interferometry Mission (SIM-PlanetQuest), operating unfettered by the Earth's atmosphere, will offer unprecedented astrometric precision that promises the discovery of Earth-analog extra-solar planets as well as a wealth of important astrophysics. Results from SIM will permit the determination of stellar masses to accuracies of 2% or better for objects ranging from brown dwarfs through main sequence stars to evolved white dwarfs, neutron stars, and black holes. Studies of star clusters will yield age determinations and internal dynamics. Microlensing measurements will present the mass spectrum of the Milky Way internal to the Sun while proper motion surveys will show the Sun's orbital radius and speed. Studies of the Galaxy's halo component and companion dwarf galaxies permit the determination of the Milky Way's mass distribution, including its Dark Matter component and the mass distribution and Dark Matter component of the Local Group. Cosmology benefits from precision (1-2%) determination of distances to Cepheid and RR Lyrae standard candles. The emission mechanism of supermassive black holes will be investigated. Finally, radio and optical celestial reference frames will be tied together by an improvement of two orders of magnitude. Optical interferometers present severe technological challenges. The Jet Propulsion Laboratory, with the support of Lockheed Martin Advanced Technology Center (LM ATC) and Northrop Grumman Space Technology (NGST), has addressed these challenges with a technology development program that is now complete. The requirements for SIM have been satisfied, based on outside peer review, using a series of laboratory tests and appropriate computer simulations: laser metrology systems perform with 10 picometer precision; mechanical vibrations have been controlled to nanometers, demonstrating orders of magnitude disturbance rejection; and knowledge of component positions throughout the whole test assembly has been demonstrated to the required picometer level. Technology transfer to the SIM flight team is now well along.

SIM PlanetQuest science and technology: a status report

NASA Astrophysics Data System (ADS)

Edberg, Stephen J.; Laskin, Robert A.; Marr, James C., IV; Unwin, Stephen C.; Shao, Michael

2007-09-01

Optical interferometry will open new vistas for astronomy over the next decade. The Space Interferometry Mission (SIM-PlanetQuest), operating unfettered by the Earth's atmosphere, will offer unprecedented astrometric precision that promises the discovery of Earth-analog extra-solar planets as well as a wealth of important astrophysics. Results from SIM will permit the determination of stellar masses to accuracies of 2% or better for objects ranging from brown dwarfs through main sequence stars to evolved white dwarfs, neutron stars, and black holes. Studies of star clusters will yield age determinations and internal dynamics. Microlensing measurements will present the mass spectrum of the Milky Way internal to the Sun while proper motion surveys will show the Sun's orbital radius and speed. Studies of the Galaxy's halo component and companion dwarf galaxies permit the determination of the Milky Way's mass distribution, including its Dark Matter component and the mass distribution and Dark Matter component of the Local Group. Cosmology benefits from precision (1-2%) determination of distances to Cepheid and RR Lyrae standard candles. The emission mechanism of supermassive black holes will be investigated. Finally, radio and optical celestial reference frames will be tied together by an improvement of two orders of magnitude. Optical interferometers present severe technological challenges. The Jet Propulsion Laboratory, with the support of Lockheed Martin Advanced Technology Center (LM ATC) and Northrop Grumman Space Technology (NGST), has addressed these challenges with a technology development program that is now complete. The requirements for SIM have been satisfied, based on outside peer review, using a series of laboratory tests and appropriate computer simulations: laser metrology systems perform with 10 picometer precision; mechanical vibrations have been controlled to nanometers, demonstrating orders of magnitude disturbance rejection; and knowledge of component positions throughout the whole test assembly has been demonstrated to the required picometer level. Technology transfer to the SIM flight team is now well along.

Theory of helix traveling wave tubes with dielectric and vane loading

DOE Office of Scientific and Technical Information (OSTI.GOV)

Freund, H.P.; Zaidman, E.G.; Antonsen, T.M. Jr.

1996-08-01

A time-dependent nonlinear analysis of a helix traveling wave tube (TWT) is presented for a configuration where an electron beam propagates through a sheath helix surrounded by a conducting wall. The effects of dielectric and vane loading are included in the formulation as is efficiency enhancement by tapering the helix pitch. Dielectric loading is described under the assumption that the gap between the helix and the wall is uniformly filled by a dielectric material. The vane-loading model describes the insertion of an arbitrary number of vanes running the length of the helix, and the polarization of the field between themore » vanes is assumed to be an azimuthally symmetric transverse-electric mode. The field is represented as a superposition of azimuthally symmetric waves in a vacuum sheath helix. An overall explicit sinusoidal variation of the form exp({ital ikz}{minus}{ital i}{omega}{ital t}) is assumed (where {omega} denotes the angular frequency corresponding to the wave number {ital k} in the vacuum sheath helix), and the polarization and radial variation of each wave is determined by the boundary conditions in a vacuum sheath helix. The propagation of each wave {ital in} {ital vacuo} as well as the interaction of each wave with the electron beam is included by allowing the amplitudes of the waves to vary in {ital z} and {ital t}. A dynamical equation for the field amplitudes is derived analogously to Poynting{close_quote}s equation, and solved in conjunction with the three-dimensional Lorentz force equations for an ensemble of electrons. Electron beams with a both a continuous and emission-gated pulse format are analyzed, and the model is compared with linear theory of the interaction as well as with the performance of a TWTs operated at the Naval Research Laboratory and at Northrop{endash}Grumman Corporation. {copyright} {ital 1996 American Institute of Physics.}« less

Spin-Tunnel Investigation of a 1/20-Scale Model of the Northrop F-5E Airplane

NASA Technical Reports Server (NTRS)

Scher, Stanley H.; White, William L.

1977-01-01

An investigation has been conducted in the Langley spin tunnel to determine the spin and recovery characteristics of a 1/20-scale model of the Northrop F-5E airplane. The investigation included erect and inverted spins, a range of center-of- gravity locations and moments of inertia, symmetric and asymmetric store loadings, and a determination of the parachute size required for emergency spin recovery. The effects of increased elevator trailing-edge-up deflections, of leading-edge and trailing-edge flap deflections, and of simulating the geometry of large external stores were also determined.

Application of computational physics within Northrop

NASA Technical Reports Server (NTRS)

George, M. W.; Ling, R. T.; Mangus, J. F.; Thompkins, W. T.

1987-01-01

An overview of Northrop programs in computational physics is presented. These programs depend on access to today's supercomputers, such as the Numerical Aerodynamical Simulator (NAS), and future growth on the continuing evolution of computational engines. Descriptions here are concentrated on the following areas: computational fluid dynamics (CFD), computational electromagnetics (CEM), computer architectures, and expert systems. Current efforts and future directions in these areas are presented. The impact of advances in the CFD area is described, and parallels are drawn to analagous developments in CEM. The relationship between advances in these areas and the development of advances (parallel) architectures and expert systems is also presented.

Northrop F-5F shark nose development

NASA Technical Reports Server (NTRS)

Edwards, O. R.

1978-01-01

During spin susceptibility testing of the Northrop F-5F airplane, two erect spin entries were obtained from purely longitudinal control inputs at low speed. Post flight analysis of the data showed that the initial yaw departure occurred at zero sideslip, and review of wind tunnel data showed significant yawing moments present at angles of attack well above stall. Further analysis of this wind tunnel data indicated that the yawing moments were being generated by the long slender nose of the airplane. Redesign of the nose was accomplished, resulting in a nose configuration which completely alleviated the asymmetric yawing moments.

Grumman OV-1C in flight

NASA Technical Reports Server (NTRS)

1983-01-01

Grumman OV-1C in flight. This OV-1C Mohawk, serial #67-15932, was used in a joint NASA/US Army Aviation Engineering Flight Activity (USAAEFA) program to study a stall-speed warning system in the early 1980s. NASA designed and built an automated stall-speed warning system which presented both airspeed and stall speed to the pilot. Visual indication of impending stall would be displayed to the pilot as a cursor or pointer located on a conventional airspeed indicator. In addition, an aural warning at predetermined stall margins was presented to the pilot through a voice synthesizer. The Mohawk was developed by Grumman Aircraft as a photo observation and reconnaissance aircraft for the US Marines and the US Army. The OV-1 entered production in October 1959 and served the US Army in Europe, Korea, the Viet Nam War, Central and South America, Alaska, and during Desert Shield/Desert Storm in the Middle East. The Mohawk was retired from service in September 1996. 133 OV-1Cs were built, the 'C' designating the model which used an IR (infrared) imaging system to provide reconnaissance.

Ditching Investigation of a 1/10-Scale Model of the Grumman F9F-2 Airplane, TED No. NACA DE 335

NASA Technical Reports Server (NTRS)

Fisher, Lloyd J.; McBride, Ellis E.

1955-01-01

An investigation was made of a 1/10-scale dynamically similar model of the Grumman FgF-2 airplane to study its behavior when ditched. The model was landed in calm water at the Langley Tank No. 2 monorail. Various landing attitudes, speeds, and configurations were investigated. The behavior of the model was determined from visual observations, acceleration records, and motion-picture records of the ditchings. Data are presented in tabular form, sequence photographs, time-history acceleration curves, and plots of attitude and speed against distance after contact.

OLTARIS - Overview and Recent Updates

NASA Technical Reports Server (NTRS)

Sandridge, C. A.

2015-01-01

The On-Line Tool for the Assessment of Radiation in Space (OLTARIS) is a web-based set of tools and models that allow engineers and scientists to assess the effects of space radiation in spacecraft, habitats, rovers, and spacesuits. The site is intended to be a design tool for those studying the effects of space radiation for current and future missions as well as a research tool for those developing advanced material and shielding concepts. The tools and models are built around the HZETRN radiation transport code and are currently focused on human-related responses. OLTARIS was deployed in 2008. Since that time, many improvements and additional capabilities have been added to the site. The purpose of this poster/presentation is to give an overview of the current capabilities of OLTARIS and focus on the updates to the site since the last workshop presentation in 2014. OLTARIS currently has 240 active accounts - 87 accounts are government (including NASA, ORNL, JPL, AFRL, and FAA), 76 are university professors/researchers/students, and 51 are industry (including Boeing, Space X, Lockheed-Martin, ATK, Northrup Grumman, and Bigelow Aerospace). There have been 14,000 jobs run through OLTARIS since counting began in November 2009. ITAR restrictions were recently reversed, so the site is now available to registered users worldwide.

The DARPA compact superconducting x-ray lithography source features. [Defense Advanced Research Projects Agency (DARPA)

DOE Office of Scientific and Technical Information (OSTI.GOV)

Heese, R.; Kalsi, S.; Leung, E.

1991-01-01

Under DARPA sponsorship, a compact Superconducting X-ray Lithography Source (SXLS) is being designed and built by the Brookhaven National Laboratory (BNL) with industry participation from Grumman Corporation and General Dynamics. This source is optimized for lithography work for sub-micron high density computer chips, and is about the size of a billiard table (1.5 m {times} 4.0 m). The machine has a racetrack configuration with two 180{degree} bending magnets being designed and built by General Dynamics under a subcontract with Grumman Corporation. The machine will have 18 photon ports which would deliver light peaked at a wave length of 10 Angstroms.more » Grumman is commercializing the SXLS device and plans to book orders for delivery of industrialized SXLS (ISXLS) versions in 1995. This paper will describe the major features of this device. The commercial machine will be equipped with a fully automated user-friendly control systems, major features of which are already working on a compact warm dipole ring at BNL. This ring has normal dipole magnets with dimensions identical to the SXLS device, and has been successfully commissioned. 4 figs., 1 tab.« less

Grumman OV-1C in hangar

NASA Technical Reports Server (NTRS)

1983-01-01

Grumman OV-1C in the hangar used at the time by the Army at Edwards Air Force Base. This OV-1C Mohawk, serial #67-15932, was used in a joint NASA/US Army Aviation Engineering Flight Activity (USAAEFA) program to study a stall-speed warning system in the early 1980s. NASA designed and built an automated stall-speed warning system which presented both airspeed and stall speed to the pilot. Visual indication of impending stall would be displayed to the pilot as a cursor or pointer located on a conventional airspeed indicator. In addition, an aural warning at predetermined stall margins was presented to the pilot through a voice synthesizer. The Mohawk was developed by Grumman Aircraft as a photo observation and electronic reconnaissance aircraft for the US Marines and the US Army. The OV-1 entered production in October 1959 and served the US Army in Europe, Korea, the Viet Nam War, Central and South America, Alaska, and during Desert Shield/Desert Storm in the Middle East. The Mohawk was retired from service in September 1996. 133 OV-1Cs were built, the 'C' designating the model which used an IR (infrared) imaging system to provide reconnaissance.

Celebrating a Century of Flight

NASA Technical Reports Server (NTRS)

OKeefe, Sean O.; Jumper, John P.; Dailey, J. R.

2002-01-01

Since 1915, the National Advisory Committee for Aeronautics (NACA), transformed into NASA in 1958, has performed cutting-edge research to solve the problems of flight. Using a Grumman F4F-3 Wildcat during World War II, NACA engineers at the Langley Aeronautical Laboratory (now Langley Research Center) in Hampton, Virginia, used this aircraft to investigate the cuffs on the propeller blades to determine their efficiency. While not built to the full production standard of other Grumman Wildcats, research on this aircraft, the second F4F-3, proved most successful in advancing knowledge of the aerodynamics of this engine and propeller system. A close-up of the propeller blades with Curtiss Electric Propellers' logo is shown.

Aerodynamic characteristics of the Grumman H-33 orbiter mated to a three segment solid propellant booster

NASA Technical Reports Server (NTRS)

Sims, F.; Olive, R.

1971-01-01

Experimental aerodynamic investigations were conducted on a .003366-scale model of the Grumman space shuttle configuration mounted to a three (3) segmented solid propellant booster. These tests were conducted in the MSFC 14-inch trisonic wind tunnel over a Mach number range of 0.6 to 4.96. The purpose of the test was to determine the aerodynamic characteristics of this configuration. Aerodynamic data was taken over a nominal angle of attack and angle of sideslip of -10 degrees to 10 degrees at zero degrees beta and alpha respectively. In addition, data was obtained for the H-33 orbiter alone to supplement data from TWT 502 and TWT 503.

Wind tunnel test results of a 1/8-scale fan-in-wing model

NASA Technical Reports Server (NTRS)

Wilson, John C.; Gentry, Garl L.; Gorton, Susan A.

1996-01-01

A 1/8-scale model of a fan-in-wing concept considered for development by Grumman Aerospace Corporation for the U.S. Army was tested in the Langley 14- by 22-Foot Subsonic Tunnel. Hover testing, which included height above a pressure-instrumented ground plane, angle of pitch, and angle of roll for a range of fan thrust, was conducted in a model preparation area near the tunnel. The air loads and surface pressures on the model were measured for several configurations in the model preparation area and in the tunnel. The major hover configuration change was varying the angles of the vanes attached to the exit of the fans for producing propulsive force. As the model height above the ground was decreased, there was a significant variation of thrust-removed normal force with constant fan speed. The greatest variation was generally for the height-to-fan exit diameter ratio of less than 2.5; the variation was reduced by deflecting fan exit flow outboard with the vanes. In the tunnel angles of pitch and sideslip, height above the tunnel floor, and wind speed were varied for a range of fan thrust and different vane angle configurations. Other configuration features such as flap deflections and tail incidence were evaluated as well. Though the V-tail empennage provided an increase in static longitudinal stability, the total model configuration remained unstable.

Venus Atmospheric Maneuverable Platform (VAMP)

NASA Astrophysics Data System (ADS)

Griffin, K.; Sokol, D.; Lee, G.; Dailey, D.; Polidan, R.

2013-12-01

We have explored a possible new approach to Venus upper atmosphere exploration by applying recent Northrop Grumman (non-NASA) development programs to the challenges associated with Venus upper atmosphere science missions. Our concept is a low ballistic coefficient (<50 Pa), semi-buoyant aircraft that deploys prior to entering the Venus atmosphere, enters the Venus atmosphere without an aeroshell, and provides a long-lived (months to years), maneuverable vehicle capable of carrying science payloads to explore the Venus upper atmosphere. In 2012 we initiated a feasibility study for a semi-buoyant maneuverable vehicle that could operate in the upper atmosphere of Venus. In this presentation we report results from the ongoing study and plans for future analyses and prototyping to advance and refine the concept. We will discuss the overall mission architecture and concept of operations from launch through Venus arrival, orbit, entry, and atmospheric science operations. We will present a strawman concept of VAMP, including ballistic coefficient, planform area, percent buoyancy, inflation gas, wing span, vehicle mass, power supply, propulsion, materials considerations, structural elements, subsystems, and packaging. The interaction between the VAMP vehicle and the supporting orbiter will also be discussed. In this context, we will specifically focus upon four key factors impacting the design and performance of VAMP: 1. Feasibility of and options for the deployment of the vehicle in space 2. Entry into the Venus atmosphere, including descent profile, heat rate, total heat load, stagnation temperature, control, and entry into level flight 3. Characteristics of flight operations and performance in the Venus atmosphere: altitude range, latitude and longitude access, day/night performance, aircraft performance (aerodynamics, power required vs. power available, propulsion, speed, percent buoyancy), performance sensitivity to payload weight 4. Science payload accommodation, constraints, and opportunities We will discuss interdependencies of the above factors and the manner in which the VAMP strawman's characteristics affect the CONOPs and the science objectives. We will show how the these factors provide constraints as well as enable opportunities for novel long duration scientific studies of the Venus upper atmosphere that support VEXAG goals 2 and 3. We will also discuss how the VAMP platform itself can facilitate some of these science measurements.

Design and Testing of Non-Toxic RCS Thrusters for Second Generation Reusable Launch Vehicle

NASA Technical Reports Server (NTRS)

Calvignac, Jacky; Dang, Lisa; Tramel, Terri; Paseur, Lila; Champion, Robert (Technical Monitor)

2003-01-01

Under NASA sponsorship, Northrop Grumman Space Technology (NGST) designed, built and tested two non-toxic, reaction control engines, one using liquid oxygen (LOX) and liquid hydrogen (LH2) and the other using liquid oxygen and ethanol. This paper presents the design and testing of the LOX/LH2 thruster. The two key enabling technologies are the coaxial liquid-on-liquid pintle injector and the fuelcooling duct. The workhorse thruster was hotfire tested at the NASA Marshall Space Flight Center Test Stand 500 in March and April of 2002. All tests were performed at sea-level conditions. During the test program, 7 configurations were tested, including 2 combustion chambers, 3 LOX injector pintle tips, and 4 LHp injector settings. The operating conditions surveyed were 70 to 100% thrust levels, mixture ratios from 3.27 to 4.29, and LH2 duct cooling from 18.0 to 25.5% fuel flow. The copper heat sink chamber was used for 16 burns, each burn lasting from 0.4 to 10 seconds, totaling 51.4 seconds, followed by Haynes chamber testing ranging from 0.9 to 120 seconds, totaling 300.9 seconds. The performance of the engine reached 95% C* efficiency. The temperature on the Haynes chamber remained well below established material limits, with the exception of one localized hot spot. These results demonstrate that both the coaxial liquid-on-liquid pintle injector design and fuel duct concepts are viable for the intended application. The thruster headend design maintained cryogenic injection temperatures while firing, which validates the selected injector design approach for minimal heat soak-back. Also, off -nominal operation without adversely impacting the thermal response of the engine showed the robustness of the duct design, a key design feature for this application. By injecting fuel into the duct, the throat temperatures are manageable, yet the split of fuel through the cooling duct does not compromise the overall combstion efficiency, which indicates that, provided proper design refinement, such a concept could be applied to a high-performance version of the thruster.

Kelly Latimer

NASA Image and Video Library

2007-03-09

Kelly Latimer is a research pilot in the Flight Crew Branch of NASA's Dryden Flight Research Center, Edwards, Calif. Latimer joined NASA in March 2007 and will fly the T38, T-34, G-III, C-17 and the "Ikhana" Predator B. Latimer is Dryden's first female research test pilot. Prior to joining NASA, Latimer was on active duty with the U.S. Air Force. She has accumulated more than 5,000 hours of military and civilian flight experience in 30 aircraft. Latimer's first association with NASA was while attending graduate school at George Washington University, Washington, D.C. Her studies included work with the Joint Institute for the Advancement of Flight Sciences at NASA's Langley Research Center, Hampton, Va. She flew an Air Force C-17 during a 2005 NASA study to reduce aircraft noise. A team of California Polytechnic State University students and Northrop Grumman personnel were stationed on Rogers Dry Lake located at Edwards Air Force Base, Calif., to record the noise footprint of the aircraft as it made various landing approaches to Edwards' runway. Latimer completed undergraduate pilot training at Reese Air Force Base, Texas, in 1990. She remained at Reese as a T-38 instructor pilot until 1993. She was assigned as a C-141 aircraft commander at McCord Air Force Base, Tacoma, Wash., until 1996. Latimer graduated from the U.S. Air Force Test Pilot School at Edwards in Class 96B. She served as a C-17 and C-141 experimental test pilot at Edwards until 2000. She then became the chief of the Performance Branch and a T-38 instructor pilot at The Air Force Test Pilot School. She returned to McCord in 2002, where she was a C-17 aircraft commander and the operations officer for the 62nd Operations Support Squadron. In 2004, Latimer became the commander of Edwards' 418th Flight Test Squadron and director of the Global Reach Combined Test Force. Following that assignment, she deployed to Iraq as an advisor to the Iraqi Air Force. Her last active duty tour was as an instructor a

Overview of the DARPA/AFRL/NASA Smart Wing Phase II program

NASA Astrophysics Data System (ADS)

Kudva, Jayanth N.; Sanders, Brian P.; Pinkerton-Florance, Jennifer L.; Garcia, Ephrahim

2001-06-01

The DARPA/AFRL/NASA Smart Wing program, conducted by a team led by Northrop Grumman Corporation (NGC) under the DARPA Smart Materials and Structures initiative, addresses the development of smart technologies and demonstration of relevant concepts to improve the aerodynamic performance of military aircraft. This paper presents an overview of the smart wing program. The program is divided into two phases. Under Phase 1, (1995 - 1999) the NGC team developed adaptive wing structures with integrated actuation mechanisms to replace standard hinged control surfaces and provide variable, optimal aerodynamic shapes for a variety of flight regimes. Two half-span 16% scale wind tunnel models, representative of an advanced military aircraft wing, one with conventional control surfaces and the other with shape memory alloy (SMA) actuated smart control surfaces, were fabricated and tested in the NASA Langley Research Center (LaRC) Transonic Dynamics Tunnel (TDT) wind tunnel during two series of tests, conducted in May 1996 and June 1998, respectively. Details of the Phase 1 effort are documented in several papers. The on-going Phase 2 effort discussed here was started in January 1997 and includes several significant improvements over Phase 1: 1) a much larger, full-span model; 2) both leading edge (LE) and trailing edge (TE) smart control surfaces; 3) high-band width actuation systems; and 4) wind tunnel tests at transonic Mach numbers and high dynamic pressures (up to 300 psf.) representative of operational flight regimes. Phase 2 includes two wind tunnel tests, both at the NASA LaRC TDT - the first one was completed in March 2000 and the second (and final) test is scheduled for April 2001. The first test-demonstrated roll-effectiveness over a wide range of Mach numbers achieved using a combination of hingeless, smoothly contoured, SMA actuated, LE and TE control surfaces. The second test addresses the development and demonstration of high bandwidth actuation. An overview of the Phase 2 effort is presented here; detailed discussions of the wind tunnel testing, model design and fabrication, and actuation system development are given in companion papers.

Venus Atmospheric Maneuverable Platform (VAMP)

NASA Astrophysics Data System (ADS)

Polidan, R.; Lee, G.; Sokol, D.; Griffin, K.; Bolisay, L.; Barnes, N.

2014-04-01

Over the past years we have explored a possible new approach to Venus upper atmosphere exploration by applying recent Northrop Grumman (non-NASA) development programs to the challenges associated with Venus upper atmosphere science missions. Our concept is a low ballistic coefficient (<50 Pa), semibuoyant aircraft that deploys prior to entering the Venus atmosphere, enters the Venus atmosphere without an aeroshell, and provides a long-lived (months to years), maneuverable vehicle capable of carrying science payloads to explore the Venus upper atmosphere. VAMP targets the global Venus atmosphere between 55 and 70 km altitude and would be a platform to address VEXAG goals I.A, I.B, and I.C. We will discuss the overall mission architecture and concept of operations from launch through Venus arrival, orbit, entry, and atmospheric science operations. We will present a strawman concept of VAMP, including ballistic coefficient, planform area, percent buoyancy, inflation gas, wing span, vehicle mass, power supply, propulsion, materials considerations, structural elements, subsystems, and packaging. The interaction between the VAMP vehicle and the supporting orbiter will also be discussed. In this context, we will specifically focus upon four key factors impacting the design and performance of VAMP: 1. Science payload accommodation, constraints, and opportunities 2. Characteristics of flight operations and performance in the Venus atmosphere: altitude range, latitude and longitude access, day/night performance, aircraft performance, performance sensitivity to payload weight 3. Feasibility of and options for the deployment of the vehicle in space 4. Entry into the Venus atmosphere, including descent profile, heat rate, total heat load, stagnation temperature, control, and entry into level flight We will discuss interdependencies of the above factors and the manner in which the VAMP strawman's characteristics affect the CONOPs and the science objectives. We will show how the these factors provide constraints as well as enable opportunities for novel long duration scientific studies of the Venus upper atmosphere that support VEXAG goals I.A, I.B, and I.C.. We will also discuss how the VAMP platform itself can facilitate some of these science measurements.

High-Speed Wind-Tunnel Investigation of the Longitudinal Stability and Control Characteristics of a 0.10-Scale Model of the Grumman XF9F-2 Airplane, TED No. NACA DE301

NASA Technical Reports Server (NTRS)

Polhamus, Edward C.; King, Thomas J., Jr.

1948-01-01

An investigation was made in the Langley high-speed 7-by 10-foot tunnel to determine the high-speed longitudinal stability end con&o1 characteristics of a 0.01-scale model of the Grumman XF9F-2 airplane in the Mach number range from 0.40 to 0.85. The results indicated that the lift and drag force breaks occurred at a Mach number of about 0.76. The aerodynamic-center position moved rearward after the force break and control position stability was present for all Mach numbers up to a Mach number of 0.80.

F-111B in Ames 40x80 Foot Wind Tunnel.

NASA Image and Video Library

1969-02-06

Installation Photos, 3/4 front view from below. F-111B in Ames 40x80 Foot Wind Tunnel. The General Dynamics/Grumman F-111B was a long-range carrier-based interceptor aircraft that was planned to be a follow-on to the F-4 Phantom II. The F-111B was developed in the 1960s by General Dynamics in conjunction with Grumman for the United States Navy (USN) as part of the joint Tactical Fighter Experimental (TFX) with the United States Air Force (USAF) to produce a common fighter for the services that could perform a variety of missions. It incorporated innovations such as variable-geometry wings, afterburning turbofan engines, and a long-range radar and missile weapons system.

A theoretical treatment of technical risk in modern propulsion system design

NASA Astrophysics Data System (ADS)

Roth, Bryce Alexander

2000-09-01

A prevalent trend in modern aerospace systems is increasing complexity and cost, which in turn drives increased risk. Consequently, there is a clear and present need for the development of formalized methods to analyze the impact of risk on the design of aerospace vehicles. The objective of this work is to develop such a method that enables analysis of risk via a consistent, comprehensive treatment of aerothermodynamic and mass properties aspects of vehicle design. The key elements enabling the creation of this methodology are recent developments in the analytical estimation of work potential based on the second law of thermodynamics. This dissertation develops the theoretical foundation of a vehicle analysis method based on work potential and validates it using the Northrop F-5E with GE J85-GE-21 engines as a case study. Although the method is broadly applicable, emphasis is given to aircraft propulsion applications. Three work potential figures of merit are applied using this method: exergy, available energy, and thrust work potential. It is shown that each possesses unique properties making them useful for specific vehicle analysis tasks, though the latter two are actually special cases of exergy. All three are demonstrated on the analysis of the J85-GE-21 propulsion system, resulting in a comprehensive description of propulsion system thermodynamic loss. This "loss management" method is used to analyze aerodynamic drag loss of the F-5E and is then used in conjunction with the propulsive loss model to analyze the usage of fuel work potential throughout the F-5E design mission. The results clearly show how and where work potential is used during flight and yield considerable insight as to where the greatest opportunity for design improvement is. Next, usage of work potential is translated into fuel weight so that the aerothermodynamic performance of the F-5E can be expressed entirely in terms of vehicle gross weight. This technique is then applied as a means to quantify the impact of engine cycle technologies on the F-5E airframe. Finally, loss management methods are used in conjunction with probabilistic analysis methods to quantify the impact of risk on F-5E aerothermodynamic performance.

Superconducting Electromagnetic Suspension (EMS) system for Grumman Maglev concept

NASA Technical Reports Server (NTRS)

Kalsi, Swarn S.

1994-01-01

The Grumman developed Electromagnetic Suspension (EMS) Maglev system has the following key characteristics: a large operating airgap--40 mm; levitation at all speeds; both high speed and low speed applications; no deleterious effects on SC coils at low vehicle speeds; low magnetic field at the SC coil--less than 0.35 T; no need to use non-magnetic/non-metallic rebar in the guideway structure; low magnetic field in passenger cabin--approximately 1 G; low forces on the SC coil; employs state-of-the-art NbTi wire; no need for an active magnet quench protection system; and lower weight than a magnet system with copper coils. The EMS Maglev described in this paper does not require development of any new technologies. The system could be built with the existing SC magnet technology.

Aeroelastic analysis and ground vibration survey of the NASA, Grumman American Yankee modified for spin testing

NASA Technical Reports Server (NTRS)

Kroeger, R. A.

1977-01-01

A complete ground vibration and aeroelastic analysis was made of a modified version of the Grumman American Yankee. The aircraft had been modified for four empennage configurations, a wing boom was added, a spin chute installed and provisions included for large masses in the wing tip to vary the lateral and directional inertia. Other minor changes were made which have much less influence on the flutter and vibrations. Neither static divergence nor aileron reversal was considered since the wing structure was not sufficiently changed to affect its static aeroelastic qualities. The aircraft was found to be free from flutter in all of the normal modes explored in the ground shake test. The analysis demonstrated freedom from flutter up to 214 miles per hour.

Wind-Tunnel Investigation at Low Speed of the Yawing, Pitching, and Static Stability Characteristics of a 1/10-Scale Model of the Grumman F9F-9 Airplane, TED No. NACA AD 3109

NASA Technical Reports Server (NTRS)

Wolhart, Walter D.; Thomas, David F., Jr.

1955-01-01

An experimental investigation has been made in the Langley stability tunnel to determine the low-speed yawing, pitching, and static stability characteristics of a 1/10-scale model of the Grumman F9F-9 airplane. Tests were made to determine the effects of duct-entrance-fairing plugs on the static lateral and longitudinal stability characteristics of the complete model in the clean condition. The remaining tests were concerned with determining tail contributions as well as the effect of duct-entrance-fairing plugs, slats, flaps, and landing gear on the yawing and pitching stability derivatives. These data are presented without analysis in order to expedite distribution.

Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/10-Scale Model of the Grumman F9F-9 Airplane, TED No. NACA AD 3109

NASA Technical Reports Server (NTRS)

Wolhart, Walter D.; Thomas, David F., Jr.

1955-01-01

An experimental investigation has been made in the Langley stability tunnel to determine the low-speed yawing, pitching, and static stability characteristics of a 1/10-scale model of the Grumman F9F-9 airplane. Tests were made to determine the effects of duct-entrance-fairing plugs on the static lateral and longitudinal stability characteristics of the complete model in the clean condition. The remaining tests were concerned with determining tail contributions as well as the effect of duct-entrance-fairing plugs, slats, flaps, and landing gear on the yawing and pitching stability derivatives. These data are presented without analysis in order to expedite distribution.

System concept definition of the Grumman superconducting Electromagnetic Suspension (EMS) Maglev design

NASA Technical Reports Server (NTRS)

Proise, M.

1994-01-01

Grumman, under contract to the Army Corps of Engineers, completed a System Concept Definition (SCD) study to design a high-speed 134 m/s (300 m.p.h.) magnetically levitated (Maglev) transportation system. The primary development goals were to design a Maglev that is safe, reliable, environmentally acceptable, and low-cost. The cost issue was a predominant one, since previous studies have shown that an economically viable Maglev system (one that is attractive to investors for future models of passenger and/or freight transportation) requires a cost that is about $12.4 M/km ($20 Million per mile). The design is based on the electromagnetic suspension (EMS) system using superconducting iron-core magnets mounted along both sides of the vehicle. The EMS system has several advantages compared to the electrodynamic suspension (EDS) Maglev systems such as low stray magnetic fields in the passenger cabin and the surrounding areas, uniform load distribution along the full length of the vehicle, and small pole pitch for smoother propulsion and ride comfort. It is also levitated at all speeds and incorporates a wrap-around design of safer operation. The Grumman design has all the advantages of an EMS system identified above, while eliminating (or significantly improving) drawbacks associated with normal magnet powered EMS systems. Improvements include larger gap clearance, lighter weight, lower number of control servos, and higher off line switching speeds. The design also incorporates vehicle tilt (plus or minus 9 deg) for higher coordinated turn and turn out speed capability.

SAFEGUARDS REPORT FOR THE NORTHROP PULSE RADIATION FACILITY

DOE Office of Scientific and Technical Information (OSTI.GOV)

Feinauer, E.; Thomas, R.D.

1961-03-22

Ae description is given of the Northrop pulse Radiation Facility, (NPRF), which consists of a TRlGA Mark-F reactor and associated supporting equipment. The NPRF was designed to operate in the following modes: Mode 1-100 kw steady-state operation; Mode II--Pulsed operation up to a maximum transient giving a maximum measured fuel element temperature of 470 deg C, which corresponds to an energy release of about 18 Mw-sec (approximately 1.9% sigma K/ K). The movable reactor will be operated in three general areas in the pool: adjacent to the exposure room; adjacent to the beam ponts; or at intermediate positions. Based onmore » the analyses presented and operating experience with the prototype TRIGA Mark F and other TRlGA reactors, it is concluded that operation of the NPRF does not present any undue hazard to the health and safety of the operating personnel or the public. (auth)« less

Tilt Nacelle Vertical and Short Takeoff and Landing Engine

NASA Image and Video Library

1979-03-21

Center Director John McCarthy, left, and researcher Al Johns pose with a one-third scale model of a Grumman Aerospace tilt engine nacelle for Vertical and Short Takeoff and Landing (V/STOL) in the 9- by 15-Foot Low Speed Wind Tunnel at the National Aeronautics and Space Administration (NASA) Lewis Research Center. Lewis researchers had been studying tilt nacelle and inlet issues for several years. One area of concern was the inlet flow separation during the transition from horizontal to vertical flight. The separation of air flow from the inlet’s internal components could significantly stress the fan blades or cause a loss of thrust. In 1978 NASA researchers Robert Williams and Al Johns teamed with Grumman’s H.C. Potonides to develop a series of tests in the Lewis 9- by 15-foot tunnel to study a device designed to delay the flow separation by blowing additional air into the inlet. A jet of air, supplied through the hose on the right, was blown over the inlet surfaces. The researchers verified that the air jet slowed the flow separation. They found that the blowing on boundary layer control resulted in a doubling of the angle-of-attack and decreases in compressor blade stresses and fan distortion. The tests were the first time the concept of blowing air for boundary layer control was demonstrated. Boundary layer control devices like this could result in smaller and lighter V/STOL inlets.

Town of Riverhead Calverton rail access rehabilitation

DOT National Transportation Integrated Search

2010-10-01

Enterprise Park at Calverton (EPCAL) is located on the property formerly occupied by Grumman Corporation in Riverhead that was operated as the United States Naval Weapons Industrial Reserve Plant at Calverton. Today EPCAL contains an Industrial Park ...

MSFC Three Point Docking Mechanism design review

NASA Technical Reports Server (NTRS)

Schaefer, Otto; Ambrosio, Anthony

1992-01-01

In the next few decades, we will be launching expensive satellites and space platforms that will require recovery for economic reasons, because of initial malfunction, servicing, repairs, or out of a concern for post lifetime debris removal. The planned availability of a Three Point Docking Mechanism (TPDM) is a positive step towards an operational satellite retrieval infrastructure. This study effort supports NASA/MSFC engineering work in developing an automated docking capability. The work was performed by the Grumman Space & Electronics Group as a concept evaluation/test for the Tumbling Satellite Retrieval Kit. Simulation of a TPDM capture was performed in Grumman's Large Amplitude Space Simulator (LASS) using mockups of both parts (the mechanism and payload). Similar TPDM simulation activities and more extensive hardware testing was performed at NASA/MSFC in the Flight Robotics Laboratory and Space Station/Space Operations Mechanism Test Bed (6-DOF Facility).

Starshade Night Test

NASA Image and Video Library

2016-08-09

A night test of a small-scale starshade model, in a dry lake bed in central Nevada's Smith Creek by Northrup Grumman, took place in May to June 2014. A telescope points toward a bright light, which in the darkness of the desert mimics the conditions of starlight in space. Other lights, which are up to 10 million times fainter than the light source standing in for the star, represent the reflected light of planets. Telescopes searching for the relatively dim light of an exoplanet next to its much brighter star are faced with a challenge as difficult as searching from Los Angeles for a firefly in New York -- if the firefly is next to the brightness of a lighthouse. The tests by Northrup Grumman determined that a starshade, or external occulter, is capable of blocking starlight to a degree that can indeed reveal the light of a planet. http://photojournal.jpl.nasa.gov/catalog/PIA20901

Application for certification, 1993 model-year light-duty trucks - Grumman Olson

DOE Office of Scientific and Technical Information (OSTI.GOV)

Not Available

1992-01-01

Every year, each manufacturer of passenger cars, light-duty trucks, motorcycles, or heavy-duty engines submits to EPA an application for certification. The report deals with light-duty trucks from Grumman Olson Company. In the application, the manufacturer gives a detailed technical description of the vehicles or engines he intends to market during the upcoming model year. These engineering data include explanations and/or drawings which describe engine/vehicle parameters such as basic engine design, fuel systems, ignition systems and exhaust and evaporative emission control systems. It also provides information on emission test procedures, service accumulation procedures, fuels to be used, and proposed maintenance requirementsmore » to be followed during testing. Section 16 of the application contains the results of emission testing, a statement of compliance to the regulations, production engine parameters, and a Summary Sheet Input Form on which issuance of a Certificate of Conformity is based.« less

High-Speed Wind-Tunnel Investigation of the Lateral Stability Characteristics of a 0.10-Scale Model of the Grumman XF9F-2 Airplane, TED No. NACA DE 301

NASA Technical Reports Server (NTRS)

Polhamus, Edward C.; King, Thomas J., Jr.

1949-01-01

An investigation was made in the Langley high-speed 7- by 10-foot tunnel to determine the high-speed lateral and directional stability characteristics of a 0.10-scale model of the Grumman XF9F-2 airplane in the Mach number range from 0.40 to 0.85. The results indicate that static lateral and directional stability is present throughout the Mach number range investigated although in the Mach number range from 0.75 to 0.85 there is an appreciable decrease in rolling moment due to sideslip. Calculations of the dynamic stability indicate that according to current flying-quality requirements the damping of the lateral oscillation, although probably satisfactory for the sea-level condition, may not be satisfactory for the majority of the altitude conditions investigated

Air Force KC-X Tanker Aircraft Program: Background and Issues for Congress

DTIC Science & Technology

2010-03-12

obtained by CRS. 16 Gopal Ratnam and Alison Fitzgerald , “Northrop Declines Tanker Bid on...1-50. 19 Statement of General Duncan J. McNabb, USAF, Commander, United States Transportation Command, Before the House Armed Services Air & Land

Primary deuterium and tritium isotope effects upon V/K in the liver alcohol dehydrogenase reaction with ethanol.

PubMed

Damgaard, S E

1981-09-29

The primary isotope effect upon V/K when ethanol stereospecifically labeled with deuterium or tritium is oxidized by liver alcohol dehydrogenase has been measured between pH 6 and 9. The deuterium isotope effect was obtained with high reproducibility by the use of two different radioactive tracers, viz. 14C and 3H, to follow the rate of acetaldehyde formation from deuterium-labeled ethanol and normal ethanol, respectively. Synthesis of the necessary labeled compounds is described in this and earlier work referred to. V/K isotope effects for both tritium and deuterium have been measured with three different coenzymes, NAD+, thio-NAD+, and acetyl-NAD+. With NAD+ at pH 7, D(V/K) was 3.0 and T(V/K) was 6.5. With increasing pH, these values decreased to 1.5 and 2.5 at pH 9. The intrinsic isotope effect evaluated by the method of Northrop [Northrop, D.B. (1977) in Isotope Effects on Enzyme-Catalyzed Reactions (Cleland, W. W., O'Leary, M, H., & Northrop, D. B., Eds.) pp 112-152, University Park Press, Baltimore] varies little with pH. It amounts to about 10 with NAD+ and about 5 with the coenzyme analogues. Commitment functions and their dependence upon pH calculated in this connection appear to be in agreement with known kinetic parameters of liver alcohol dehydrogenase. This assay method was also applied in vivo in the rat. Being a noninvasive method because only trace amounts of isotopes are needed, it may yield information about alternative routes of ethanol oxidation in vivo. In naive rats at low concentrations of ethanol, it confirms the discrete role of the non alcohol dehydrogenase systems.

ITER's Tokamak Cooling Water System and the the Use of ASME Codes to Comply with French Regulations of Nuclear Pressure Equipment

DOE Office of Scientific and Technical Information (OSTI.GOV)

Berry, Jan; Ferrada, Juan J; Curd, Warren

During inductive plasma operation of ITER, fusion power will reach 500 MW with an energy multiplication factor of 10. The heat will be transferred by the Tokamak Cooling Water System (TCWS) to the environment using the secondary cooling system. Plasma operations are inherently safe even under the most severe postulated accident condition a large, in-vessel break that results in a loss-of-coolant accident. A functioning cooling water system is not required to ensure safe shutdown. Even though ITER is inherently safe, TCWS equipment (e.g., heat exchangers, piping, pressurizers) are classified as safety important components. This is because the water is predictedmore » to contain low-levels of radionuclides (e.g., activated corrosion products, tritium) with activity levels high enough to require the design of components to be in accordance with French regulations for nuclear pressure equipment, i.e., the French Order dated 12 December 2005 (ESPN). ESPN has extended the practical application of the methodology established by the Pressure Equipment Directive (97/23/EC) to nuclear pressure equipment, under French Decree 99-1046 dated 13 December 1999, and Order dated 21 December 1999 (ESP). ASME codes and supplementary analyses (e.g., Failure Modes and Effects Analysis) will be used to demonstrate that the TCWS equipment meets these essential safety requirements. TCWS is being designed to provide not only cooling, with a capacity of approximately 1 GW energy removal, but also elevated temperature baking of first-wall/blanket, vacuum vessel, and divertor. Additional TCWS functions include chemical control of water, draining and drying for maintenance, and facilitation of leak detection/localization. The TCWS interfaces with the majority of ITER systems, including the secondary cooling system. U.S. ITER is responsible for design, engineering, and procurement of the TCWS with industry support from an Engineering Services Organization (ESO) (AREVA Federal Services, with support from Northrop Grumman, and OneCIS). ITER International Organization (ITER-IO) is responsible for design oversight and equipment installation in Cadarache, France. TCWS equipment will be fabricated using ASME design codes with quality assurance and oversight by an Agreed Notified Body (approved by the French regulator) that will ensure regulatory compliance. This paper describes the TCWS design and how U.S. ITER and fabricators will use ASME codes to comply with EU Directives and French Orders and Decrees.« less

NASA's Webb Sunshield Stacks Up to Test

NASA Image and Video Library

2014-07-24

The Sunshield on NASA's James Webb Space Telescope is the largest part of the observatory—five layers of thin membrane that must unfurl reliably in space to precise tolerances. Last week, for the first time, engineers stacked and unfurled a full-sized test unit of the Sunshield and it worked perfectly. The Sunshield is about the length of a tennis court, and will be folded up like an umbrella around the Webb telescope’s mirrors and instruments during launch. Once it reaches its orbit, the Webb telescope will receive a command from Earth to unfold, and separate the Sunshield's five layers into their precisely stacked arrangement with its kite-like shape. The Sunshield test unit was stacked and expanded at a cleanroom in the Northrop Grumman facility in Redondo Beach, California. The Sunshield separates the observatory into a warm sun-facing side and a cold side where the sunshine is blocked from interfering with the sensitive infrared instruments. The infrared instruments need to be kept very cold (under 50 K or -370 degrees F) to operate. The Sunshield protects these sensitive instruments with an effective sun protection factor or SPF of 1,000,000 (suntan lotion generally has an SPF of 8-50). In addition to providing a cold environment, the Sunshield provides a thermally stable environment. This stability is essential to maintaining proper alignment of the primary mirror segments as the telescope changes its orientation to the sun. The James Webb Space Telescope is the successor to NASA's Hubble Space Telescope. It will be the most powerful space telescope ever built. Webb is an international project led by NASA with its partners, the European Space Agency and the Canadian Space Agency. For more information about the Webb telescope, visit: www.jwst.nasa.gov or www.nasa.gov/webb For more information on the Webb Sunshield, visit: jwst.nasa.gov/sunshield.html Credit: NASA/Goddard/Chris Gunn NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

Using Airborne Lidar Data from IcePod to Measure Annual and Seasonal Ice Changes Over Greenland

NASA Astrophysics Data System (ADS)

Frearson, N.; Bertinato, C.; Das, I.

2014-12-01

The IcePod is a multi-sensor airborne science platform that supports a wide suite of instruments, including a Riegl VQ-580 infrared scanning laser, GPS-inertial positioning system, shallow and deep-ice radars, visible-wave and infrared cameras, and upward-looking pyrometer. These instruments allow us to image the ice from top to bottom, including the surface of melt-water plumes that originate at the ice-ocean boundary. In collaboration with the New York Air National Guard 109th Airlift Wing, the IcePod is flown on LC-130 aircraft, which presents the unique opportunity to routinely image the Greenland ice sheet several times within a season. This is particularly important for mass balance studies, as we can measure elevation changes during the melt season. During the 2014 summer, laser data was collected via IcePod over the Greenland ice sheet, including Russell Glacier, Jakobshavn Glacier, Eqip Glacier, and Summit Camp. The Icepod will also be routinely operated in Antarctica. We present the initial testing, calibration, and error estimates from the first set of laser data that were collected on IcePod. At a survey altitude of 1000 m, the laser swath covers ~ 1000 m. A Northrop-Grumman LN-200 tactical grade IMU is rigidly attached to the laser scanner to provide attitude data at a rate of 200 Hz. Several methods were used to determine the lever arm between the IMU center of navigation and GPS antenna phase center, terrestrial scanning laser, total station survey, and optimal estimation. Additionally, initial bore sight calibration flights yielded misalignment angles within an accuracy of ±4 cm. We also performed routine passes over the airport ramp in Kangerlussuaq, Greenland, comparing the airborne GPS and Lidar data to a reference GPS-based ground survey across the ramp, spot GPS points on the ramp and a nearby GPS base station. Positioning errors can severely impact the accuracy of a laser altimeter when flying over remote regions such as across the ice sheets. Setting up GPS base stations along the flight track can prove to be logistically challenging. We have processed the GPS-inertial data using both DGPS and PPP and present the comparison of those results here. Finally, we discuss our processing, calibration and error estimation methods and compare our results to previously flown IceBridge lines.

10. View of Draper darby chain loom from warp beam ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

10. View of Draper darby chain loom from warp beam end, patent date 1913, made by Drpaer Corporation, Hopedale, Massachusetts. Acquired ca. 1941. Note Draper-Northrop name on automatic spindle changer. - Riverdale Cotton Mill, Corner of Middle & Lower Streets, Valley, Chambers County, AL

ARC-2008-ACD07-0073-468

NASA Image and Video Library

2008-01-14

LCROSS in Ames clean room N-240- securing the special made crate for transfer to Northrup Grumman Redondo Beach, CA where more calibration will be done before finally being sent for mating with the LRO spacecraft with Steve Ord, Ames Project Management Office

Being "Secondary" is Important for a Webb Telescope Mirror

NASA Image and Video Library

2017-12-08

NASA release July 19, 2011 Click here to learn about the James Webb Space Telescope The secondary mirror (shown here) was polished at the L3 Integrated Optical Systems - Tinsley in Richmond, Calif. to accuracies of less than one millionth of an inch. That accuracy is important for forming the sharpest images when the mirrors cool to -400°F (-240°C) in the cold of space. The Webb's secondary mirror was recently completed, following polishing and gold-coating. "Secondary" may not sound as important as "primary" but when it comes to the next-generation James Webb Space Telescope a secondary mirror plays a critical role in ensuring the telescope gathers information from the cosmos. The Webb's secondary mirror was recently completed, following polishing and gold-coating. There are four different types of mirrors that will fly on the James Webb Space Telescope, and all are made of a light metal called beryllium. It is very strong for its weight and holds its shape across a range of temperatures. There are primary mirror segments (18 total that combined make the large primary mirror providing a collecting area of 25 meters squared/269.1 square feet), the secondary mirror, tertiary mirror and the fine steering mirror. Unlike the primary mirror, which is molded into the shape of a hexagon, the secondary mirror is perfectly rounded. The mirror is also convex, so the reflective surface bulges toward a light source. It looks much like a curved mirror that you'll see on the wall near the exit of a parking garage that lets motorists see around a corner. This mirror is coated with a microscopic layer of gold to enable it to efficiently reflect infrared light (which is what the Webb telescope's cameras see). The quality of the secondary mirror surface is so good that the final convex surface at cold temperatures does not deviate from the design by more than a few millionths of a millimeter - or about one ten thousandth the diameter of a human hair. "As the only convex mirror on the Webb telescope, the secondary mirror has always been recognized to be the hardest of all of the mirrors to polish and test, so we are delighted that its performance meets all specifications," said Lee Feinberg, Webb Optical Telescope manager at NASA's Goddard Space Flight Center in Greenbelt, Md. Convex mirrors are particularly hard to test because light that strikes them diverges away from the mirror. Feinberg noted, "The Webb telescope convex secondary mirror is approximately the size of the Spitzer Space Telescope's primary mirror and is by far the largest convex cryogenic mirror ever built for a NASA program." It was data from the Spitzer's mirrors that helped make the decision to use beryllium for the Webb telescope mirrors. Spitzer's mirrors were also made of beryllium. So why is this mirror so critical? Because the secondary mirror captures light from the 18 primary mirror segments and relays those distant images of the cosmos to the telescope's science cameras. The secondary mirror is mounted on folding "arms" that position it in front of the 18 primary mirror segments. The secondary mirror will soon come to NASA's Goddard Space Flight Center in Greenbelt, Md. where it will be installed on the telescope structure. Then, as a complete unit, the telescope structure and mirrors will undergo acoustic and vibration testing. The secondary mirror was developed at Ball Aerospace & Technology Corp. of Boulder, Colo. and the mirror recently completed polishing at the L3–IOS-Tinsley facility in Richmond, Calif. Northrop Grumman space Systems is the prime contractor on the Webb telescope program. The James Webb Space Telescope is the world’s next-generation space observatory and successor to the Hubble Space Telescope. The most powerful space telescope ever built, Webb will observe the most distant objects in the universe, provide images of the very first galaxies ever formed and see unexplored planets around distant stars. The Webb Telescope is a joint project of NASA, the European Space Agency and the Canadian Space Agency. Credit:NASA/Ball Aerospace/Tinsley NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

ARC-1969-A-20485

NASA Image and Video Library

1955-06-22

Grumman F9F-6 (Bu. No. 128138) Cougar airplane. EVALUATION OF CARRIER APPROACH TECHNIQUES Boundary Layer Control, STOL, and V/STOL Note: Used in publication in Flight Research at Ames; 57 Years of Development and Validation of Aeronautical Technology NASA SP-1998-3300 fig. 101

Dispersion, Mixing, and Combustion in Turbulent and High-Speed Flows, Air-Breathing Propulsion, and Hypersonic Flight

DTIC Science & Technology

2010-03-31

postdoctoral research of Antonino Ferrante (currently Assistant Professor at the University of Washington). The fluid dynamics video "LES of an inclined jet...Northrop Professor of Aeronautics and Professor of Applied Physics, Caltech, and ChiefTechnologist, JPL. Ferrante, Antonino : Postdoctoral Scholar in

77 FR 34067 - Notice Pursuant to the National Cooperative Research and Production Act of 1993-Robotics...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-06-08

... Production Act of 1993--Robotics Technology Consortium, Inc. Notice is hereby given that, on April 30, 2012... seq. (``the Act''), Robotics Technology Consortium, Inc. (``RTC'') has filed written notifications... Inc., Huntsville, AL; John H. Northrop & Associates, Inc., Burke, VA; Lithos Robotics Corporation...

Inoculation testing of Apollo 12 materials

NASA Technical Reports Server (NTRS)

1969-01-01

E. Landrum Young, Brown and Root Northrop, injects a young Japanese quail with a suspension of pulvarized Apollo 12 lunar material within a quarantine cabinet in the Invertebrate, Aves and Fish Laboratory of the Lunar Receiving Laboratory, bldg 37, Manned Spacecraft Center. The bird is being inoculated in the abdominal cavity.

Thermal performance evaluation of the Northrop model NSC-01-0732 concentrating solar collector array at outdoor conditions. [Marshall Space Flight Center solar house test facility

NASA Technical Reports Server (NTRS)

1979-01-01

The thermal efficiency of the concentrating, tracking solar collector was tested after ten months of operation at the Marshall Space Flight Center solar house. The test procedures and results are presented.

Northrop TRIGA facility decommissioning plan versus actual results

DOE Office of Scientific and Technical Information (OSTI.GOV)

Gardner, F.W.

1986-01-01

This paper compares the TRIGA facility decontamination and decommissioning (D and D) plan to the actual results and discusses key areas where operational activities were impacted by the final US Nuclear Regulatory Commission approved D and D plan. A discussion of fuel transport, release criteria, and release survey plans is included.

NASTRAN finite element analysis activity at Northrop

NASA Technical Reports Server (NTRS)

Thordarson, S.

1978-01-01

In-house evaluation of the various analytical capabilities of the MSC version of NASTRAN, prior to production release, is a continuous effort. The NASTRAN superelement and subsonic aero features are presently being tested and brought on-line for production use. Two examples of recent NASTRAN structural solutions are also presented.

Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the Grumman XF9F-2 Airplane, TED No. NACA DE 317

NASA Technical Reports Server (NTRS)

Berman, Theodore

1948-01-01

An investigation of the spin and recovery characteristics of a scale model of the Grumman XF9F-2 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model in the flight loading were determined. The investigation also included spin-recovery-parachute, pilot-escape, and rudder-pedal- . force tests. The recovery characteristics of the model were satisfactory for all configurations tested. Spins for the normal control configuration were oscillatory in roll and yaw. Deflecting the leading-edge flaps or the dive brakes did not change the spin and recovery characteristics of the model noticeably. A 10.0-foot tail parachute or a 6.0-foot wing-tip parachute (drag coefficient of 0.75) was found to be effective for recoveries from demonstration spins. The rudder forces in the spin appeared to be within the capabilities of the pilot.

Emittance measurements in Grumman 1 MeV beamline

DOE Office of Scientific and Technical Information (OSTI.GOV)

Debiak, T.; Gammel, G.; Melnychuk, S.

1992-12-01

The emittance of a 30 keV H{sup {minus}} beam has been measured with an Allison type electrostatic analyser at two positions separated by 85 cm along the Grumman 1 MeV beamline LEBT at low currents (about 4 mA, no Cs{sub 2}O additive in the source) and at higher currents (10-15 mA, with Cs{sub 2}O additive in the source). No emittance growth was observed between the two positions, but, at the higher current level, the emittance was about 60% higher than at the low current level ({Sigma}{sub n},rms = .0045 {pi} cm-mrad vs. 0070 {pi} cm-mrad). Argon was then introduced upmore » to a partial pressure of 4x10{sup {minus}5} torr, and the emittance decreased back to a range corresponding to that found at the lower currents. However, beam noise was observed at the downstream position, and there is evidence for a small amount of emittance growth (<20%) between the two positions.« less

Supplementary Investigation in the Free-Spinning Tunnel of a 1/24-Scale Model of the Grumman F9F-6 Airplane Incorporating only Flaperons for Lateral Control, TED No. NACA DE 364

NASA Technical Reports Server (NTRS)

Klinar, Walter J.; Lee, Henry A.

1954-01-01

A supplementary investigation was conducted in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the Grumman F9F-6 airplane. The primary purpose of the investigation was to reevaluate the spin-recovery characteristics of the airplane in view of the fact that the ailerons had been eliminated from the flaperon-aileron lateral control system of the airplane. A spin-tunnel investigation on a model of the earlier version of the F9F-6 airplane had indicated that use of ailerons with the spin (stick right in a right spin) was essential to insure recovery. The results indicate that with.ailerons eliminated, it may be difficult to obtain an erect developed spin but if a fully developed spin is obtained on the airplane, recovery therefrom may be difficult or impossible. Flaperon deflection should have little effect on spins or recoveries.

Hazardous Waste Cleanup: Naval Weapons Industrial Reserve Plant in Calverton, New York

EPA Pesticide Factsheets

The Naval Weapons Industrial Reserve Plant (NWIRP) is located on Grumman Boulevard in Calverton, New York. The facility is bordered by Middle County Road (route 25) to the north, agricultural land to the east, River Road to the south, and Wading River Road

X-4 in flight

NASA Technical Reports Server (NTRS)

1951-01-01

In the early days of transonic flight research, many aerodynamicists believed that eliminating conventional tail surfaces could reduce the problems created by shock wave interaction with the tail's lifting surfaces. To address this issue, the Army Air Forces's Air Technical Service awarded a contract to Northrop Aircraft Corporation on 5 April 1946 to build a piloted 'flying laboratory.' Northrop already had experience with tailless flying wing designs such as the N-1M, N-9M, XB-35, and YB-49. Subsequently, the manufacturer built two semi-tailless X-4 research aircraft, the first of which flew half a century ago. The X-4 was designed to investigate transonic compressibility effects at speeds near Mach 0.85 to 0.88, slightly below the speed of sound. Northrop project engineer Arthur Lusk designed the aircraft with swept wings and a conventional fuselage that housed two turbojet engines. It had a vertical stabilizer, but no horizontal tail surfaces. It was one of the smallest X-planes ever built, and every bit of internal space was used for systems and instrumentation. The first X-4 arrived at Muroc Air Force Base by truck on 15 November 1948. Over the course of several weeks, engineers conducted static tests, and Northrop test pilot Charles Tucker made initial taxi runs. Although small of stature, he barely fit into the diminutive craft. Tucker, a veteran Northrop test pilot, had previously flown the XB-35 and YB-49 flying wing bomber prototypes. Prior to flying for Northrop, he had logged 400 hours in jet airplanes as a test pilot for Lockheed and the Air Force. He would now be responsible for completing the contractor phase of the X-4 flight test program. Finally, all was ready. Tucker climbed into the cockpit, and made the first flight on 15 December 1948. It only lasted 18 minutes, allowing just enough time for the pilot to become familiar with the basic handling qualities of the craft. The X-4 handled well, but Tucker noted some longitudinal instability at all speeds. Data generated during the initial flight led to design changes that improved handling and performance. While the first aircraft underwent modifications, the second X-4 arrived at Muroc in early 1949. Heavy rains flooded the dry lakebed at Muroc, delaying further flight testing until 27 April. The first X-4 made a few more flights, but was beset by mechanical problems. Soon, the second aircraft became the workhorse of the contractor test program. Its first flight was accomplished on 7 June 1949. It was more completely instrumented than its stablemate, and didn't suffer from the same plague of malfunctions. The National Advisory Committee for Aeronautics (NACA) expressed interest in using the second X-4 for research, but was frustrated by the slow pace of the contractor's test phase. Both X-4 aircraft were grounded temporarily for installation of spin recovery parachutes, and improvements to the landing gear uplock system. After these tasks were completed, the first X-4 made its tenth and final flight on 26 January 1950. It was grounded, and used as a source of spare parts for the second aircraft. On 17 February, the remaining X-4 completed the contractor testing phase. The aircraft was then turned over to the NACA and the Air Force for a joint research program. NACA technicians prepared the aircraft, and made a number of design improvements. The joint NACA/USAF program consisted of 82 flights to evaluate handling qualities, stability and control, and performance at various lift-to-drag ratios. NACA pilots during the program included Stanley Butchart, George Cooper, Scott Crossfield, John Griffith, Walter Jones, John 'Jack' McKay, and Joe Walker. The Air Force pilots included B/Gen. Albert Boyd, Col. Frank 'Pete' Everest, Lt. Col. Richard Johnson, Capt. J. S. Nash, and Maj. Charles 'Chuck' Yeager. The final X-4 flight took place in September 1953. Further flights were planned, but a chronic fuel leak lead to cancellation of the program. NACA engineers had acquired a wealth of data, and the cost of repairing the leak could not be justified. Although the X-4 was never designed to fly at supersonic speeds, it gathered transonic data that proved that conventional tailless swept-wing configurations were unsuitable for supersonic performance. The design suffered from noticeable instability in all directions, increasing as it approached the speed of sound. It was, however, a valuable tool for dynamic stability research. Additionally low lift-to-drag data gathered with the X-4 was later beneficial to development of the X-15. On 10 March 1954, both X-4 aircraft were returned to the Air Force. The ejection seat from the second X-4 was retained by the NACA for use in the X-1E. The first X-4 is currently on display at the United States Air Force Academy in Colorado. The second aircraft is displayed at the USAF Museum in Ohio. This movie clip running approximately 7 seconds shows the Northrop X-4 in an air-to-air view climbing away from its chase aircraft.

Paradigm, Persona and Epideictic: The Lovesongs of Eurythmics.

ERIC Educational Resources Information Center

Oglesbee, Frank W.

A study examined the lyrics of the lovesongs of the musical partnership Eurythmics (David Stewart and Annie Lennox), a popular music group. The method used was based on the James Chesbro study, which classified lyrics using a critical paradigm that combined Northrop Frye's hierarchy of communications systems (Ironic, Mimetic, Leader-centered,…

The Viability of Literary Texts.

ERIC Educational Resources Information Center

Gambone, Kenneth Felix

This study explored whether or not there was an increase in understanding from one literary genre to another, whether or not this growth was apparent from one grade level to another, and whether the growth followed Northrop Frye's suggestion of order: romance, comedy, tragedy, and satire. The high school subjects were asked to read "Merchant of…

CFD validation needs for advanced concepts at Northrop Corporation

NASA Technical Reports Server (NTRS)

George, Michael W.

1987-01-01

Information is given in viewgraph form on the Computational Fluid Dynamics (CFD) Workshop held July 14 - 16, 1987. Topics covered include the philosophy of CFD validation, current validation efforts, the wing-body-tail Euler code, F-20 Euler simulated oil flow, and Euler Navier-Stokes code validation for 2D and 3D nozzle afterbody applications.

Does Scale Really Matter? Ultra-Large-Scale Systems Seven Years after the Study

DTIC Science & Technology

2013-05-24

Beyonce Knowles releases second consecutive No.1 album and fourth No.1 single in the US BlackBerry users numbered 4,900,000 in March, 2006...And yet…there is a fast growing gap between our research and reality. 75 Does Scale Really Matter?: ULS Systems Seven Years Later Linda Northrop

Wallace Stevens: A Collection of Critical Essays. Twentieth Century Views Series.

ERIC Educational Resources Information Center

Borroff, Marie, Ed.

One of a series of works aimed at presenting contemporary critical opinion on major authors, this collection includes essays by Marie Borroff, Wallace Stevens, Joseph N. Riddle, Hi Simons, Sister M. Bernetta Quinn, C. Roland Wagner, Harold Bloom, Ralph J. Mills, Jr., Roy Harvey Pearce, Louis L. Martz, Morton Dauwen Zabel, and Northrop Frye--all…

NASA Dryden's T-38 Talon trainer jet in flight over the main base complex at Edwards Air Force Base

NASA Image and Video Library

2006-05-05

NASA Dryden's T-38 Talon trainer jet in flight over the main base complex at Edwards Air Force Base. Formerly at NASA's Langley Research Center, this Northrop T-38 Talon is now used for mission support and pilot proficiency at the Dryden Flight Research Center.

Unit 1002: The Modes and Functions of Discourse.

ERIC Educational Resources Information Center

Minnesota Univ., Minneapolis. Center for Curriculum Development in English.

The purpose of this 10th-grade unit on language is to pose, for students, basic and tentative questions about the rhetorical uses of language. Examples are provided which designate the modes of language: Daniel Fogarty's story of rhetoric to show language which informs; materials from Northrop Frye to show language which inquires; a John F.…

Overview of computational structural methods for modern military aircraft

NASA Technical Reports Server (NTRS)

Kudva, J. N.

1992-01-01

Computational structural methods are essential for designing modern military aircraft. This briefing deals with computational structural methods (CSM) currently used. First a brief summary of modern day aircraft structural design procedures is presented. Following this, several ongoing CSM related projects at Northrop are discussed. Finally, shortcomings in this area, future requirements, and summary remarks are given.

76 FR 67103 - Proposed Revision of Class D and Class E Airspace; Hawthorne, CA

Federal Register 2010, 2011, 2012, 2013, 2014

2011-10-31

...-0610; Airspace Docket No. 11-AWP-10] Proposed Revision of Class D and Class E Airspace; Hawthorne, CA...: This action proposes to revise Class D and E airspace at Jack Northrop Field/Hawthorne Municipal... (14 CFR) Part 71 by revising Class D airspace and Class E airspace designated as an extension to Class...

West European and East Asian Perspectives on Defense, Deterrence and Strategy. Volume 1. Main Report.

DTIC Science & Technology

1984-05-16

this School -- especially in the SDP under David Owen’s leadership -- in raising the nuclear threshold in Europe by strengthening conventional...ConrolDEPARTMENT OF DEFENSE CONTRACTORS US European Commnand ATTN: ECJ-3 Grumman-CTEC. Inc ATTM: ECJ-5 ATTN: S. Shrier us National Military

How To Avoid Acquisition Disasters and Create Affordable Solutions for America’s Air Warriors by Applying Lessons from the Past

DTIC Science & Technology

2011-02-16

Strike Fighter Program. Research Report, Air Command and Staff College, Air University, Montgomery: Air University, 2008. Boyne, Walter J. Messerschmitt...Restructures Program. Testimony, Washington, D.C.: General Accounting Office, 2010. Gillcrist, Paul T. Tomcat: The Grumman F-14 Story. Atglen: Schiffer

Free-Spinning Tunnel Tests of a 1/24-Scale Model of the Grumman XTB3F-1 Airplane, TED No. NACA DE304

NASA Technical Reports Server (NTRS)

Berman, Theodore

1947-01-01

In accordance with a request of the Bureau of Aeronautics, Navy Department, tests were performed in the Langley 20-foot free-spinning tunnel to determine the spin and recovery characteristics of a 1/24 scale model of the Grumman XTB3F-1 airplane. The airplane is a two-place, midwing torpedo bomber equipped with a tractor propeller and an auxiliary jet engine. The effect of control setting and movement on the erect and inverted spin and recovery characteristics of the model were determined for the normal loading. Brief tests with mass extended slightly along the fuselage were also made, however, in order to determine the effect of such a mass variation on elevator effectiveness. Tests were performed to determine the size of emergency spin-recovery tail and wing-tip parachutes required for satisfactory recovery by parachute action alone. The investigation also included emergency pilot-escape tests and tests to determine the rudder pedal and elevator stick forces necessary to move the rudder and elevator for recovery.

A beamline systems model for Accelerator-Driven Transmutation Technology (ADTT) facilities

DOE Office of Scientific and Technical Information (OSTI.GOV)

Todd, A.M.M.; Paulson, C.C.; Peacock, M.A.

1995-10-01

A beamline systems code, that is being developed for Accelerator-Driven Transmutation Technology (ADTT) facility trade studies, is described. The overall program is a joint Grumman, G.H. Gillespie Associates (GHGA) and Los Alamos National Laboratory effort. The GHGA Accelerator Systems Model (ASM) has been adopted as the framework on which this effort is based. Relevant accelerator and beam transport models from earlier Grumman systems codes are being adapted to this framework. Preliminary physics and engineering models for each ADTT beamline component have been constructed. Examples noted include a Bridge Coupled Drift Tube Linac (BCDTL) and the accelerator thermal system. A decisionmore » has been made to confine the ASM framework principally to beamline modeling, while detailed target/blanket, balance-of-plant and facility costing analysis will be performed externally. An interfacing external balance-of-plant and facility costing model, which will permit the performance of iterative facility trade studies, is under separate development. An ABC (Accelerator Based Conversion) example is used to highlight the present models and capabilities.« less

A beamline systems model for Accelerator-Driven Transmutation Technology (ADTT) facilities

DOE Office of Scientific and Technical Information (OSTI.GOV)

Todd, Alan M. M.; Paulson, C. C.; Peacock, M. A.

1995-09-15

A beamline systems code, that is being developed for Accelerator-Driven Transmutation Technology (ADTT) facility trade studies, is described. The overall program is a joint Grumman, G. H. Gillespie Associates (GHGA) and Los Alamos National Laboratory effort. The GHGA Accelerator Systems Model (ASM) has been adopted as the framework on which this effort is based. Relevant accelerator and beam transport models from earlier Grumman systems codes are being adapted to this framework. Preliminary physics and engineering models for each ADTT beamline component have been constructed. Examples noted include a Bridge Coupled Drift Tube Linac (BCDTL) and the accelerator thermal system. Amore » decision has been made to confine the ASM framework principally to beamline modeling, while detailed target/blanket, balance-of-plant and facility costing analysis will be performed externally. An interfacing external balance-of-plant and facility costing model, which will permit the performance of iterative facility trade studies, is under separate development. An ABC (Accelerator Based Conversion) example is used to highlight the present models and capabilities.« less

Tank Investigation of the Grumman JRF-5 Airplane Equipped with Twin Hydro-Skis TED No. NACA DE 357

NASA Technical Reports Server (NTRS)

Ramsen, John A.; Gray, George R.

1951-01-01

A tank investigation has been conducted on a 1/8-size powered dynamic model of the Grumman JRF-5 airplane equipped with twin hydro-skis. The results of tests using two types of skis are presented: one had vertical sides joining the top surface to the chine; the other had the top surface faired to the chine to eliminate the vertical sides. Both configurations had satisfactory longitudinal stability although the model had a slightly greater stable elevator range available when the skis without the vertical sides were attached. Free model tests indicated no instability present when one ski emerged before the other. Considerable excess thrust was available at all speeds with either type of skis. A hump gross load-resistance ratio of 3.37 was obtained with the skis with the vertical sides and 3.53 with the other skis. Landing behavior in smooth water with yaw up to 15deg and roll up to 15deg in opposite directions was satisfactory with either type of skis.

Free-Spinning-Tunnel Investigation of a 1/24-Scale Model of the Grumman F9F-6 Airplane TED No. NACA DE 364

NASA Technical Reports Server (NTRS)

Klinar, Walter J.; Healy, Frederick M.

1952-01-01

An investigation of a 1/24-scale model of the Grumman F9F-6 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The erect and inverted spin and recovery characteristics of the model were determined for the normal flight loading with the model in the clean condition. The effect of loading variations was investigated briefly. Spin-recovery parachute tests were also performed. The results indicate that erect spins obtained on the airplane in the clean condition will be satisfactorily terminated for all loading conditions provided full rudder reversal is accompanied by moving the ailerons and flaperons (lateral controls) to full with the spin (stick right in a right spin). Inverted spins should be satisfactorily terminated by full reversal of the rudder alone. The model tests indicate that an 11.4-foot (laid-out-flat diameter) tail parachute (drag coefficient approximately 0.73) should be effective as an emergency spin-recovery device during demonstration spins of the airplane provided the towline is attached above the horizontal stabilizer.

Preliminary Results Obtained from Flight Test of a 1/7-Scale Rocket-Powered Model of the Grumman XF10F Airplane Configuration in the Swept-Wing Condition, TED No. NACA DE 354

NASA Technical Reports Server (NTRS)

Gardner, William N.

1951-01-01

A flight investigation of a 1/7-scale rocket-powered model of the XF10F Grumman XFl0F airplane in the swept-wing configuration has been made. The purpose of this test was to determine the static longitudinal stability, damping in pitch, and longitudinal control effectiveness of the airplane with the center of gravity at 20 percent of the wing mean aerodynamic chord. Only a small amount of data was obtained from the test because, immediately after booster separation at a Mach number of 0.88, the configuration was directionally unstable and diverged in sideslip. Simultaneous with the sideslip divergence, the model became longitudinally unstable at 3 degree angle of attack and -6 degree sideslip and diverged in pitch to a high angle of attack. During the pitch-up the free-floating horizontal tail became unstable at 5 degree angle of attack and the tail drifted against its positive deflection limit.

Flight Measurements of the Longitudinal Stability and Control Characteristics of the Grumman F8F-1 Airplane, TED No. NACA 2379

NASA Technical Reports Server (NTRS)

Assadourian, Arthur; Reeder, John P.

1948-01-01

A series of flight tests have been made at the Langley Flight Research Division at the request of the Bureau of Aeronautics, Department of the Navy, to determine the flying qualities of the Grumman F8F-1 air- plane. This paper presents the test results necessary to determine the longitudinal stability and control characteristics end the stalling characteristics. These tests were made between February and June of 1947- The range of Mach numbers covered in this investigation was approximately 0.10 to 0.62, and no attempt was made to investigate compressibility effects at higher Mach numbers. The lateral and directional stability and control characteristics of the subject airplane have already been reported (reference 1). Also presented in this paper is a discussion of the normal accelerations induced by yawing velocity and sideslip which were considered ob,jectionable by the pilot for this airplane. A discussion of the undesirable accelerations has been included with a view towards formulating some flying-qualities requirements limiting them.

On-Orbit Performance of the TES Pulse Tube Cryocooler System and the Instrument - Six Years in Space

NASA Technical Reports Server (NTRS)

Rodriguez, J. I.; Na-Nakornpanom, A.

2011-01-01

The Tropospheric Emission Spectrometer (TES) instrument pulse tube cryocoolers began operation 36 days after launch of the NASA Earth Observing System (EOS) Aura spacecraft on July 15, 2004. TES is designed with four infrared Mercury Cadmium Telluride focal plane arrays in two separate housings cooled by a pair of Northrup Grumman Aerospace Systems (NGAS) single-stage pulse tube cryocoolers. The instrument also makes use of a two-stage passive cooler to cool the optical bench. The instrument is a high-resolution infrared imaging Fourier transform spectrometer with 3.3-15.4 micron spectral coverage. After four weeks of outgassing, the instrument optical bench and focal planes were cooled to their operating temperatures to begin science operations. During the early months of the mission, ice contamination of the cryogenic surfaces including the focal planes led to increased cryocooler loads and the need for periodic decontamination cycles. After a highly successful 5 years of continuous in-space operations, TES was granted a 2 year extension. This paper reports on the TES cryogenic system performance including the two-stage passive cooler. After a brief overview of the cryogenic design, the paper presents detailed data on the highly successful space operation of the pulse tube cryocoolers and instrument thermal design over the past six years since the original turn-on in 2004. The data shows the cryogenic contamination decreased substantially to where decontamination cycles are now performed every six months. The cooler stroke required for constant-temperature operation has not increased indicating near-constant cooler efficiency and the instrument's thermal design has also provided a nearly constant heat rejection sink. At this time TES continues to operate in space providing important Earth science data.

Advanced Technology Subsonic Transport Study: N+3 Technologies and Design Concepts

NASA Technical Reports Server (NTRS)

Raymer, Daniel P.; Wilson, Jack; Perkins, H. Douglas; Rizzi, Arthur; Zhang, Mengmeng; RamirezPuentes, Alfredo

2011-01-01

Conceptual Research Corporation, the Science of the Possible, has completed a two-year study of concepts and technologies for future airliners in the 180-passenger class. This NASA-funded contract was primarily focused on the ambitious goal of a 70 percent reduction in fuel consumption versus the market-dominating Boeing 737-800. The study is related to the N+3 contracts awarded in 2008 by NASA s Aeronautics Research Mission Directorate to teams led by Boeing, GE Aviation, MIT, and Northrop Grumman, but with more modest goals and funding. CRC s contract featured a predominant emphasis on propulsion and fuel consumption, but since fuel consumption depends upon air vehicle design as much as on propulsion technology, the study included notional vehicle design, analysis, and parametric studies. Other NASA goals including NOx and noise reduction are of long-standing interest but were not highlighted in this study, other than their inclusion in the propulsion system provided to CRC by NASA. The B-737-800 was used as a benchmark, parametric tool, and design point of departure. It was modeled in the RDS-Professional aircraft design software then subjected to extensive parametric variations of parasitic drag, drag-due-to-lift, specific fuel consumption, and unsized empty weight. These studies indicated that the goal of a 70 percent reduction in fuel consumption could be attained with roughly a 30 percent improvement in all four parameters. The results were then fit to a Response Surface and coded for ease of use in subsequent trade studies. Potential technologies to obtain such savings were identified and discussed. More than 16 advanced concept designs were then prepared, attempting to investigate almost every possible emerging concept for application to this class airliner. A preliminary assessment of these concepts was done based on their total wetted area after design normalization of trimmed maximum lift. This assessment points towards a Tailless Airliner concept which was designed and analyzed in some detail. To make it work, a retracting canard and an all-moving chin rudder were employed, along with the use of the Active Aeroelastic Wing technology. Results indicate that a 60 percent savings in fuel burn may be credibly attained, but this depends upon a lot of technology maturation, concept development, and risk reduction. This should be expected-such a dramatic reduction in fuel consumption is a "game changer" in the world of commercial aviation. It won t be easy.

Learning from Space Entrepreneurs

NASA Technical Reports Server (NTRS)

Pomerantz, William

2008-01-01

The early days of rocketry and space exploration in the United States were marked by incredibly rapid progress: a seemingly endless parade of firsts. Not coincidentally, this period also saw more than its fair share of failure, especially in the infamous "kaputnik" days prior to the successful launch of Explorer. Without a standard canon of known quantities to turn to, the early pioneers of rocketry and space flight were forced to dream up new ideas that ranged from the elegant to the bizarre and to accept the fact that the price of radical progress is occasional failure. Nowadays, rapid prototyping and testing have slowed, as we rely more and more on the extensive knowledge pined by our predecessors and on the embarrassment of riches modern engineers get from computational modeling and computer assisted design. In many cases, this leads to much improved or phenomenally more efficient designs. It also, however, fosters a culture so terrified of failure that we over-engineer and overanalyze everything, often tweaking designs for decades before a new system takes flight. (This is not a problem unique to rockets; the same phenomenon seems to have occurred in high-performance jets.) This is one reason why it was possible for President Kennedy to dream of the completion of the Mercury and Gemini missions and a successful landing on the moon in under a decade, while returning to the moon may take nearly twice as long. Lacking access to the tremendous computational resources of the national space program-and, just as importantly, removed from the harsh judgment of public shareholders or congressional appropriations committees-the hungry entrepreneurs who compete for our prizes tend not to display such fear of failure. Instead, most of them follow a rapid "build, test, fly" program. They are willing to throw a handful of concepts against the wall and see what sticks. They often go from drawing on the back of a napkin to firing engines or even flying vehicles in a matter of weeks or months, learning valuable lessons along the way. Indeed, our teams have repeatedly learned many of the most valuable lessons after only a few moments of working with real hardware-lessons that could never have been learned from a CAD drawing, like finding the failure modes of different welding practices or tracking down the interference between an onboard camera and a GPS unit. As Paul Breed, the leader of a Northrop Grumman Lunar Lander Challenge team (playfully called Unreasonable Rocket), is fond of saying, "In computer simulations the plumbing never leaks. In real life, it always does."

Erosion Coatings Developed to Increase the Life and Durability of Composites

NASA Technical Reports Server (NTRS)

Sutter, James K.; Naik, Subhash K.; Bowman, Cheryl L.; Siefker, Robert; Miyoshi, Kazuhisa; Perusek, Gail P.

2004-01-01

Both the NASA Glenn Research Center and the Allison Advanced Development Company (AADC) have worked to develop and demonstrate erosion-resistant coatings that would increase the life and durability of composite materials used in commercial aircraft engines. These composite materials reduce component weight by 20 to 30 percent and result in less fuel burn and emissions and more fuel savings. Previously, however, their use was limited because of poor erosion resistance, which causes concerns about safety and leads to high maintenance costs. The coatings were tested by the University of Cincinnati, and the composites were manufactured by Texas Composites and coated by Engelhard and NASA Glenn. Rolls-Royce Corporation uses composite materials, which are stronger and less dense than steel or titanium, to make bypass vanes for their AE3007 engines. These engines are widely used in regional jet aircraft (Embraer) and unmanned air vehicles such as the Northrop Grumman Global Hawk. Coatings developed by NASA/Rolls-Royce can reduce erosion from abrasive materials and from impurities in the air that pass over these vanes, allowing Rolls-Royce to take advantage of the benefits of composite materials over titanium without the added costs of increased maintenance and/or engine failure. The Higher Operating Temperature Propulsion Components (HOTPC) Project developed cost-effective, durable coatings as part of NASA's goal to increase aviation system capacity growth. These erosion coatings will reduce the number of special inspections or instances of discontinued service due to erosion, allowing aircraft capacity to be maintained without inconveniencing the traveling public. A specific example of extending component life showed that these coatings increased the life of graphite fiber and polymer composite bypass vanes up to 8 times over that of the uncoated vanes. This increased durability allows components to operate to full design life without the fear of wear or failure. Recently, Rolls-Royce completed over 2000 hr of engine testing with the coated fan exit bypass vanes. There was no loss of coating after nearly 5000 typical engine cycles. Midway through the engine tests, the coated vanes were removed from the engine during a scheduled maintenance and inspection period. The vanes were shipped back to Glenn, where they underwent further stress testing in the Structural Dynamics Lab, mimicking more extreme conditions than those typical of the AE3007 engine cycle. These vanes were then replaced in the AE3007 and subjected to another 1000 hr of engine tests. Once again, there was no loss of coating and only a minimal appearance of cracking.

PREFACE: The 11th International Superconductive Electronics Conference (ISEC 07)

NASA Astrophysics Data System (ADS)

Miller, Donald L.; Wellstood, Fred; Donaldson, Gordon

2007-11-01

The 11th International Superconductive Electronics Conference (ISEC 07) was held in June 2007 in Washington, DC, USA. This special issue is a compendium of selected papers based on the technology presented at that meeting. ISEC, held on a biennial basis, traditionally rotates from Japan to Europe to the United States. The single exception to this rotation has been the 2003 conference which was held in Australia. This conference brings together the world's experts in superconductive electronics in a forum which is conducive to interaction among the participants with maximal interchange between the various topics. The conference this year was truly an international event with participation from 13 countries over six continents. The quality of presentations was also high. The conference witnessed the continued maturation of both digital/mixed signal electronics and SQUID-based instrumentation along with a number of novel devices. Of particular note was the transition of superconducting quantum computing research from a novel abstract concept to a broad-based research activity. The organizing committee was able to gather an exemplary group of invited speakers to share their results and visions for future progress. These presentations spanned both the subtopics of superconductor electronics and the history of the field. As I reflect on the efforts which went into making this conference a success, I must express my appreciation to many individuals and organizations, in no particular order. I would like to thank Northrop Grumman for their support for my activities as chair of the conference, both in terms of making my time available and for direct financial considerations. Centennial Conferences, as the conference organizer, provided invaluable guidance and administrative support. I would also like to acknowledge the support of the IEEE Council on Superconductivity, in particular in the persons of Moises Levy and John Spargo. I would be remiss if I did not thank John Przybysz, both for his influence in my assuming the chairmanship of the conference and for his continued advice throughout the planning process. I owe a huge debt of gratitude to Fred Wellstood and the rest of the program committee. The amount of work and dedication that went towards the coherent and stimulating program that they provided is nothing short of amazing to me. And finally, I would like to thank each and every participant at ISEC 07. Without your work and your willingness to share the fruits of your labors with the rest of us, this conference could never have happened. Donald L Miller, Chairman ISEC 07

Climate Change, Public Health, and Decision Support: The New Threat of Vector-borne Disease

NASA Astrophysics Data System (ADS)

Grant, F.; Kumar, S.

2011-12-01

Climate change and vector-borne diseases constitute a massive threat to human development. It will not be enough to cut emissions of greenhouse gases-the tide of the future has already been established. Climate change and vector-borne diseases are already undermining the world's efforts to reduce extreme poverty. It is in the best interests of the world leaders to think in terms of concerted global actions, but adaptation and mitigation must be accomplished within the context of local community conditions, resources, and needs. Failure to act will continue to consign developed countries to completely avoidable health risks and significant expense. Failure to act will also reduce poorest of the world's population-some 2.6 billion people-to a future of diminished opportunity. Northrop Grumman has taken significant steps forward to develop the tools needed to assess climate change impacts on public health, collect relevant data for decision making, model projections at regional and local levels; and, deliver information and knowledge to local and regional stakeholders. Supporting these tools is an advanced enterprise architecture consisting of high performance computing, GIS visualization, and standards-based architecture. To address current deficiencies in local planning and decision making with respect to regional climate change and its effect on human health, our research is focused on performing a dynamical downscaling with the Weather Research and Forecasting (WRF) model to develop decision aids that translate the regional climate data into actionable information for users. For the present climate WRF was forced with the Max Planck Institute European Center/Hamburg Model version 5 (ECHAM5) General Circulation Model 20th century simulation. For the 21th century climate, we used an ECHAM5 simulation with the Special Report on Emissions (SRES) A1B emissions scenario. WRF was run in nested mode at spatial resolution of 108 km, 36 km and 12 km and 28 vertical levels. This model was examined relative to two mosquito vectors, both competent carriers of dengue fever, a viral, vector-borne disease. Models which incorporate public health considerations can enable decision makers to take proactive steps to mitigate the impacts and adapt to the changing environmental conditions. In this paper we provide a snapshot of our climate initiative and some examples relative to our public health practice work in vector-borne diseases to illustrate how integrated decision support could be of assistance to regional and local communities worldwide.

Recasting the American Dream and American Politics: Barack Obama's Keynote Address to the 2004 Democratic National Convention

ERIC Educational Resources Information Center

Rowland, Robert C.; Jones, John M.

2007-01-01

This essay draws upon the work of Northrop Frye to show that stories enacting the American Dream contain elements associated with romance, and briefly traces how Ronald Reagan and conservatives utilized the romance of the American Dream to the point that many Americans associated it exclusively with conservatism. The essay then details how Barack…

"Words with Power" for Social Transformation: An Anatomy of Biblical Criticism for Theological Education

ERIC Educational Resources Information Center

Walker-Jones, Arthur

2008-01-01

The proliferation of methods of literary criticism in biblical studies raises the question of how to introduce students to the field. This article argues that the work of Northrop Frye is useful for teaching the existential meaning and social impact of the Bible. The first section introduces relevant aspects of Frye's literary theory. The second…

Do Joint Fighter Programs Save Money? Technical Appendixes on Methodology

DTIC Science & Technology

2013-01-01

Bookstore Make a charitable contribution Limited Electronic Distribution Rights This document and trademark(s) contained herein are protected by...research clients and sponsors. Support RAND—make a tax-deductible charitable contribution at www.rand.org/giving/contribute.html R® is a registered...Evidence, Organisation for Economic Co-Operation and Development, Economics Department Working Paper 317, January 17, 2002. Anderson, Fred, Northrop

The Study of Literature as a Systematic Disciplinary Practice. Elementary Subjects Center Series No. 7.

ERIC Educational Resources Information Center

Johnsen, William A.

The study of literature can be a discipline only insofar as it is capable of the systemization typical of other human sciences. The possibility of system poses two directions of research: (1) exploring what conditions make system possible; and (2) discovering what follows from the fact of system's possibility. Northrop Frye followed the second…

Facilitating Integration of Electron Beam Lithography Devices with Interactive Videodisc, Computer-Based Simulation and Job Aids.

ERIC Educational Resources Information Center

Von Der Linn, Robert Christopher

A needs assessment of the Grumman E-Beam Systems Group identified the requirement for additional skill mastery for the engineers who assemble, integrate, and maintain devices used to manufacture integrated circuits. Further analysis of the tasks involved led to the decision to develop interactive videodisc, computer-based job aids to enable…

Solar Energy Systems

NASA Technical Reports Server (NTRS)

1981-01-01

A waste water treatment plant in Wilton, Maine, where sludge is converted to methane gas, and Monsanto Company's Environmental Health Laboratory in St. Louis Missouri, where more than 200 solar collectors provide preheating of boiler feed water for laboratory use are representative of Grumman's Sunstream line of solar energy equipment. This equipment was developed with technology from NASA's Apollo lunar module program.

LUNAR SAMPLES - APOLLO XI - MSC

NASA Image and Video Library

1969-08-03

S69-40740 (July 1969) --- Dr. Ross Taylor (seated), Australian National University, and John Allen, Brown and Root-Northrop technician, review preliminary data from the optical emission spectrograph in the Spectrographic Laboratory of the Physical-Chemical Test Laboratory. Tests were being conducted on lunar surface material collected by astronauts Neil A. Armstrong and Edwin E. Aldrin Jr. during their lunar surface extravehicular activity on July 20, 1969.

Northrop Triga facility decommissioning plan versus actual results

DOE Office of Scientific and Technical Information (OSTI.GOV)

Gardner, F.W.

1986-01-01

This paper compares the Triga facility decontamination and decommissioning plan to the actual results and discusses key areas where operational activities were impacted upon by the final US Nuclear Regulatory Commission (NRC)-approved decontamination and decommissioning plan. Total exposures for fuel transfer were a factor of 4 less than planned. The design of the Triga reactor components allowed the majority of the components to be unconditionally released.

Saturn Apollo Program

NASA Image and Video Library

1970-03-20

Under the direction of Marshall Space Flight Center (MSFC), the Lunar Roving Vehicle (LRV) was designed to allow Apollo astronauts a greater range of mobility during lunar exploration missions. During the development process, LRV prototype wheels underwent soil tests in building 4481 at Marshall Space Flight Center (MSFC). Pictured from left to right are the wheels for: LRV, Bendix Corporation, Local Scientific Survey Module (LSSM), and Grumman Industries.

Acceleration Measurements During Landing in Rough Water of a 1/7-Scale Dynamic Model of Grumman XJR2F-1 Amphibian - Langley Tank Model 212, TED No. NACA 2378

NASA Technical Reports Server (NTRS)

Land, Norman S.; Zeck, Howard

1947-01-01

Tests of a 1/7 size model of the Grumman XJR2F-1 amphibian were made in Langley tank no.1 to examine the landing behavior in rough water and to measure the normal and angular accelerations experienced by the model during these landings. All landings were made normal to the direction of wave advance, a condition assumed to produce the greatest accelerations. Wave heights of 4.4 and 8.0 inches (2.5 and 4.7 ft, full size) were used in the tests and the wave lengths were varied between 10 and 50 feet (70 and 350 ft, full size). Maximum normal accelerations of about 6.5g were obtained in 4.4 inch waves and 8.5g were obtained in 8.0 inch waves. A maximum angular acceleration corresponding to 16 radians per second per second, full size, was obtained in the higher waves. The data indicate that the airplane will experience its greatest accelerations when landing in waves of about 20 feet (140 ft, full size) in length.

Space fabrication demonstration system, technical volume

NASA Technical Reports Server (NTRS)

1979-01-01

The automatic beam builder ABB was developed, fabricated, and demonstrated within the established contract cost and schedule constraints. The ABB demonstrated the feasibility of: producing lightweight beams automatically within the required rate of 1 to 5 ft of completed beam per minute and producing structurally sound beams with axial design load of 5538 N based on the Grumman photovoltaic satellite solar power system design reference structure.

Appraisal Requirements for CMMI (Registered Trademark) Version 1.3 (ARC, V1.3)

DTIC Science & Technology

2011-04-01

Software Engineering Institute) • Rassa, Robert C . (Raytheon Space and Airborne Systems ) • Richter, Karen (OSD/IDA) • Young, Rusty (Software...CMU/SEI-2011-TR-006 | 21 • Penn, Lynn (Lockheed Martin) • Rassa, Robert C . (Raytheon Space and Airborne Systems) • Wilson, Harold G. (Northrop...Government Contract Number FA8721-05- C -0003 with Carnegie Mellon University for the operation of the Software Engineering Institute, a federally funded

ARC-1944-A-6538

NASA Image and Video Library

1944-09-28

NACA photographer Northrop P-61A Black Widow towing P-51B to release altitude of 28,000 ft over Muroc Dry Lake, California for in flight validating of wind tunnel measurements of drag. After the pilot released the tow cable, drag measurementrs were obtained at various airspeeds in a 20-minute unpowered flight. Note: Used in publication in Flight Research at Ames; 57 Years of Development and Validation of Aeronautical Technology NASA SP-1998-3300 Fig. 17

Global Positioning System En Route/Terminal Exploratory Tests.

DTIC Science & Technology

1982-12-01

the set in a Grumman G-159 Gulf stream during June and July 1981. •»-*r P "» _^„. ~kjfe. 11 H. "»> ’•! This report contains the test...i . ».....•. :. • i i r iia^ri 1 I.-—„., nlMllltt—’ PLOT STAAT TIME 21 42 20 PLOT ENO TIME 23 1» 20 DATE RECOnOFO- TIOtlM TIME OPS

Field tests with a highly concentrated Bacillus thuringiensis formula against spruce budworm, Choristoneura fumiferana (Clem.) (Lepidoptera: tortricidae)

Treesearch

W. A. Smirnoff

1985-01-01

Field tests were conducted in 1980, 1981, and 1982 with a new Bacillus thuringiensis formula called Futura. Tests were conducted with a Grumman AgCat aircraft on 40 ha forest blocks and with a DC-4G aircraft on larger forested areas. Futura which is able to disperse the required 20 x 109 I.U./ha for spruce budworm control in 2....

The Aerodynamic Characteristics in Pitch of a 1/15-Scale Model of the Grumman F11F-1 Airplane at Mach Numbers of 1.41, 1.61, and 2.01, TED No. NACA DE 390

NASA Technical Reports Server (NTRS)

Driver, Cornelius

1956-01-01

Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 to determine the static longitudinal stability and control characteristics of various arrangements of the Grumman F11F-1 airplane. Tests were made of the complete model and various combinations of its component parts and, in addition, the effects of various body modifications, a revised vertical tail, and wing fences on the longitudinal characteristics were determined. The results indicate that for a horizontal-tail incidence of -10 deg the trim lift coefficient varied from 0.29 at a Mach number of 1.61 to 0.23 at a Mach number of 2.01 with a corresponding decrease in lift-drag trim from 3.72 to 3.15. Stick-position instability was indicated in the low-supersonic-speed range. A photographic-type nose modification resulted in slightly higher values of minimum drag coefficient but did not significantly affect the static stability or lift-curve slope. The minimum drag coefficient for the complete model with the production nose remained essentially constant at 0.047 throughout the Mach number range investigated.

Women in Aerospace Awards

NASA Image and Video Library

2010-10-26

NASA Langley Aerospace Engineer Jill Lynette Hanna Prince receives the Women in Aerospace Achievement in Aerospace award from North Carolina State Professor Robert Tolson during the Women in Aerospace organization's annual awards ceremony and banquet held at the Ritz-Carlton Hotel in Arlington, VA on Tuesday, Oct. 26, 2010. Four current NASA leaders and one retiree were recognized for their work by Women in Aerospace. The event celebrates women's professional excellence in aerospace and honors women who have made outstanding contributions to the aerospace community. Photo Credit: (NASA/Bill Ingalls)

R and D work on the constrained vapor bubble system for a microgravity experiment

NASA Technical Reports Server (NTRS)

Wayner, P. C., Jr.; Plawsky, J. L.

2005-01-01

We are working with Project Scientists R. Balasubramanian and Sang Young Son, and a NASA Projects Team headed by Sue Motil at the Glenn Research Center on the design and development of an experimental system for use on the International Space Station during the year 2006. John Eustace is the coordinator for the flight experiment at Zin-Tech (previously Northrop-Grumman) for the design and development of the Constrained Vapor Bubble Heat Exchanger, CVBHX, cell which will fit into the Light Microscope Module, LMM. Good progress is being made. The CDR for the LMM being developed was held on December 10-1 1,2003. Experimental results obtained under microgravity conditions will be compared with those obtained at Rensselaer. Basic and applied research at Rensselaer continues on the experimental and theoretical details associated with passive phase change heat transfer processes controlled by interfacial forces in the CVBHX. The extensive results of our current research are presented in the 23 external publications listed below. Twenty-two external presentations have been given. Briefly, evaporation/condensation data from both vertical and horizontal CVBHX systems were obtained and analyzed for both polar (wetting) and apolar (partially wetting) fluids. The vertical system is axi-symmetric, but strongly effected by gravity. Whereas, the horizontal system is asymmetric, but weakly effected by gravity. Therefore, there will be significant differences in the operation of the cell in the earth s environment versus the operation under microgravity conditions. Due to its relative large size, the system s performance should be optimum under micro-gravity conditions, where the CVBHX should be a very effective passive heat exchanger. The CVBHX was found to be an ideal experimental setup in which to study the effects of interfacial phenomena on both the evaporation and drop-wise condensation processes. The optical technique (Image Analyzing Interferometry, IAI), which is based on the measurement and analysis of the reflectivity pattern of a thin film, was significantly improved. The accuracy of the IAI system is of critical importance to the success of the mission because it is used to measure the details of the pressure field in the liquid by measuring the film thickness profile. The accuracy was found to be excellent and various publications/presentations documenting these new results were written. Significant new results were also obtained for the effect of the oscillating contact line region on evaporation. Three doctoral students graduated under this grant. All three work in US industry, two for Intel. Another doctoral student is in his third year of study and will finish under an extension of the NASA grant: # NNC05GA27G.

FY2005 Progress Summary and FY2006 Program Plan Statement of Work and Deliverables for Development of High Average Power Diode-Pumped Solid State Lasers, and Complementary Technologies, for Applications in Energy and Defense

DOE Office of Scientific and Technical Information (OSTI.GOV)

Ebbers, C

The primary focus this year was to operate the system with two amplifiers populated with and pumped by eight high power diode arrays. The system was operated for extended run periods which enabled average power testing of components, diagnostics, and controls. These tests were highly successful, with a demonstrated energy level of over 55 joules for 4 cumulative hours at a repetition rate of 10 Hz (average power 0.55 kW). In addition, high average power second harmonic generation was demonstrated, achieving 227 W of 523.5 nm light (22.7 J, 10 Hz, 15 ns, 30 minutes) Plans to achieve higher energymore » levels and average powers are in progress. The dual amplifier system utilizes a 4-pass optical arrangement. The Yb:S-FAP slabs were mounted in aerodynamic aluminum vane structures to allow turbulent helium gas flow across the faces. Diagnostic packages that monitored beam performance were deployed during operation. The laser experiments involved injecting a seed beam from the front end into the system and making four passes through both amplifiers. Beam performance diagnostics monitored the beam on each pass to assess system parameters such as gain and nearfield intensity profiles. This year, an active mirror and wavefront sensor were procured and demonstrated in an off-line facility. The active mirror technology can correct for low order phase distortions at user specified operating conditions (such as repetition rates different than 10 Hz) and is a complementary technology to the static phase plates used in the system for higher order distortions. A picture of the laser system with amplifier No.2 (foreground) and amplifier No.1 (background) is shown in Fig. 1.0.1.1. The control system and diagnostics were recently enhanced for faster processing and allow remote operation of the system. The growth and fabrication of the Yb:S-FAP slabs constituted another major element of our program objectives. Our goal was to produce at least fourteen 4x6 cm2 crystalline slabs. These goals were met. Nine crystal boules were successfully grown to produce 14 slabs. In addition, we have prepared the way to scale the Yb:S-FAP crystals to the next growth diameter (10-inch diameter as opposed to 7-inch diameter). An outside contract was placed with Northrop-Grumman to scaleup the Yb:S-FAP crystal size. The following sections discuss the above accomplishments in more technical detail and are followed by plans and a budget request for FY2006.« less

NASA Awards Chandra X-Ray Observatory Follow-On Contract

NASA Astrophysics Data System (ADS)

2003-08-01

NASA has awarded a contract to the Smithsonian Astrophysical Observatory in Cambridge, Mass., to provide science and operational support for the Chandra X-ray Observatory, one of the world's most powerful tools to better understand the structure and evolution of the universe. The contract will have a period of performance from August 31, 2003, through July 31, 2010, with an estimated value of 373 million. It is a follow-on contract to the existing contract with Smithsonian Astrophysical Observatory that has provided science and operations support to the Observatory since its launch in July 1999. At launch the intended mission life was five years. As a result of Chandra's success, NASA extended the mission from five to 10 years. The value of the original contract was 289 million. The follow-on contract with the Smithsonian Astrophysical Observatory will continue through the 10-year mission. The contract type is cost reimbursement with no fee. The contract covers mission operations and data analysis, which includes the observatory operations, science data processing and the general and guaranteed time observer (astronomer) support. The observatory operations tasks include monitoring the health and status of the observatory and developing and up linking the observation sequences during Chandra's communication coverage periods. The science data processing tasks include the competitive selection, planning, and coordination of science observations with the general observers and processing and delivery of the resulting scientific data. There are approximately 200 to 250 observing proposals selected annually out of about 800 submitted, with a total amount of observing time of about 20 million seconds. Chandra has exceeded expectations of scientists, giving them unique insight into phenomena light years away, such as exotic celestial objects, matter falling into black holes, and stellar explosions. X-ray astronomy can only be performed from space because Earth's atmosphere blocks X-rays from reaching the surface. The Chandra Observatory travels one-third of the way to the moon during its orbit around the Earth every 64 hours. At its highest point, Chandra's highly elliptical, or egg- shaped, orbit is 200 times higher than that of its visible- light-gathering sister, the Hubble Space Telescope. NASA's Marshall Space Flight Center, Huntsville, Ala., manages the Chandra program for the Office of Space Science, NASA Headquarters, Washington. Northrop Grumman of Redondo Beach, Calif., formerly TRW, Inc., was the prime development contractor for the observatory. The Smithsonian Astrophysical Observatory controls science and flight operations from the Chandra X-ray Center in Cambridge, Mass. For information about NASA on the Internet, visit: http://www.nasa.gov For information about the Chandra X-ray Observatory on the Internet, visit: http://chandra.harvard.edu and http://chandra.nasa.gov

A Survey of Electric Laser Codes.

DTIC Science & Technology

1983-06-01

709-71M R M> Asset, latcs lirute Maftson (505) 24 J-560’. Northrop R t. T Center William B. Lacina «213) 377-4811 X »62 Lo < kheed... Pulsar Device. ASSESSMENT OF LIMITATIONS: The enerc^ extraction routine is not pasea on physical optics principles, so predictions are of limited...Along Optics] Axis: No i- lo \\c Direction; KO KINETICS MODELED: Pulsed; V CW: _ Nl’MERlCAL SCHEME USED IN RATE CALCULATION i^ I

Air Force KC-X Tanker Aircraft Program: Background and Issues for Congress

DTIC Science & Technology

2010-07-15

18 Gopal Ratnam and Alison Fitzgerald , “Northrop Declines Tanker Bid on ‘Financial Burdens’ (Update2),” Bloomberg.com, December 1, 2009...May 2009, p. 1-50. 21 Statement of General Duncan J. McNabb, USAF, Commander, United States Transportation Command, Before the House Armed Services...the Duncan Hunter National Defense Authorization Act for Fiscal Year 2009 (P.L. 110-417; 122 Stat. 4561) not later than 60 days after the date of the

A Case Study of the F-20 Tigershark

DTIC Science & Technology

1987-06-01

RAND Graduate School. This paper was prepared for the Spring 1987 R &D and Systems Acquisition Workshop led by George Donohue and Michael Rich. - II1...however, disagreement about why this was so. This paper examines the F-20 program from both a research and development ( R &D) and a marketing perspective...Northrop considers the F-20 R &D effort to have been successful. This examination leads us to discuss the problematic issue of finding and using

Field Operational and Environmental Evaluation of the Automated Integrated Surveying Instrument (AISI). Volume 2

DTIC Science & Technology

1988-04-01

2M - sub go, or empNm, anl arn rftle a dm sIected rme 4( eserih (AM’ me (a s -el. Useful f(o work ia m Joh. wft um bemiauris. * EF az Q~, The guss...with calibrated eauior-er 3 Recorder Honeywell ENV 6047 D 4-20-87 10-20-87 Sand and Dust Recorder Leeds & Northrop E 6034 D 4-15-87 10-15-87 Anemometer

Free-Spinning-Tunnel Tests of a 1/20-Scale Model of the Northrop N-9M Airplane

NASA Technical Reports Server (NTRS)

MacDougall, George F., Jr.; Lichtenstein, Jacob H.

1946-01-01

Spin tests of a 1/20-scale model of the Northrop N-9M airplane have been performed in the Langley 20-foot free-spinning tunnel. The erect and inverted spin and recovery characteristics were determined for various loading conditions and the effect of deflecting the flaps and of extending the landing gear was investigated. The investigation also included tests to determine the size parachute required for satisfactory spin recovery by parachute action alone. The tests were performed at an equivalent spin altitude of 15,000 feet. A specialized recovery technique consisting of rapid full reversal of the rudder pedals against the spin combined with turning the wheel against the spin and movement of the stick forward is recommended for all loadings and configurations of the airplane. The results also indicated that a 7-foot-diameter spin-recovery parachute having a drag coefficient of 0.7 attached to the outboard wing tip with a towline of 10 to 30 feet or an 8.8-foot-diameter parachute attached to the fixed portion of the wing between the elevons and the pitch flaps with a 30-foot towline would provide satisfactory recovery from demonstration spins by parachute action alone. It appears possible that the first N-9M airplane may have crashed because of failure to recover from a spin.

Index of international publications in aerospace medicine.

DOT National Transportation Integrated Search

1993-02-01

The Index of International Publications in Aerospace Medicine is a comprehensive listing of international publications in clinical aerospace medicine, operational aerospace medicine, aerospace physiology, environmental medicine/physiology, diving med...

Index of international publications in aerospace medicine

DOT National Transportation Integrated Search

2001-08-01

The Index of International Publications in Aerospace Medicine is a comprehensive listing of international publications in clinical aerospace medicine, operational aerospace medicine, aerospace physiology, environmental medicine/physiology, diving med...

Software Technology for Adaptable, Reliable Systems (STARS) Technical Program Plan,

DTIC Science & Technology

1986-08-06

Shadow projects that are being considered by the SEI: Service Project Company . . Army FATDS Magnavox CSS To Be Determined PLRS Hughes Navy BSY-I IBM...ISCS Rockwell ACDS Hughes Air Force Simulators Boeing CSSR GTE ATF Grumman MILSTAR Lockheed Figure 4-2 Candidate FY 1986 Shadow Projects 4.2.3 SHADOW...Journal of the Armed Forces Communications and Electronic Association, September 1985. 11. Schill, J., Smeaton, R., and Jackman , R., The Conversion of

Green Flight Challenge

NASA Image and Video Library

2011-09-25

The Embry-Riddle Aeronautical University, EcoEagle is seen as it passes a Grumman Albatross during the 2011 Green Flight Challenge, sponsored by Google, at the Charles M. Schulz Sonoma County Airport in Santa Rosa, Calif. on Monday, Sept. 26, 2011. NASA and the Comparative Aircraft Flight Efficiency (CAFE) Foundation are having the challenge with the goal to advance technologies in fuel efficiency and reduced emissions with cleaner renewable fuels and electric aircraft. Photo Credit: (NASA/Bill Ingalls)

Index of international publications in aerospace medicine.

DOT National Transportation Integrated Search

2014-05-01

The 5th edition of the Index of International Publications in Aerospace Medicine is a comprehensive : listing of international publications in clinical aerospace medicine, operational aerospace medicine, : aerospace physiology, environmental medicine...

Index of International Publications in Aerospace Medicine

DOT National Transportation Integrated Search

2007-01-01

The 3rd edition of theIndex of International Publications in Aerospace Medicine is a comprehensive listing of : international publications in clinical aerospace medicine, operational aerospace medicine, aerospace : physiology, environmental medicine/...

Aerospace Community. Aerospace Education I.

ERIC Educational Resources Information Center

Mickey, V. V.

This book, one in the series on Aerospace Education I, emphasizes the two sides of aerospace--military aerospace and civilian aerospace. Chapter 1 includes a brief discussion on the organization of Air Force bases and missile sites in relation to their missions. Chapter 2 examines the community services provided by Air Force bases. The topics…

NASA/DOD Aerospace Knowledge Diffusion Research Project. Paper 12: The diffusion of federally funded aerospace research and development (R/D) and the information seeking behavior of US aerospace engineers and scientists

NASA Technical Reports Server (NTRS)

Pinelli, Thomas E.; Kennedy, John M.; Barclay, Rebecca O.

1991-01-01

In this paper, the diffusion of federally funded aerospace R&D is explored from the perspective of the information-seeking behavior of U.S. aerospace engineers and scientists. The following three assumptions frame this exploration: (1) knowledge production, transfer, and utilization are equally important components of the aerospace R&D process; (2) the diffusion of knowledge resulting from federally funded aerospace R&D is indispensable for the U.S. to remain a world leader in aerospace; and (3) U.S. government technical reports, produced by NASA and DOD, play an important, but as yet undefined, role in the diffusion of federally funded aerospace R&D. A conceptual model for federally funded aerospace knowledge diffusion, one that emphasizes U.S. goverment technical reports, is presented. Data regarding three research questions concerning the information-seeking behavior of U.S. aerospace engineers and scientists are also presented.

NASA/DOD Aerospace Knowledge Diffusion Research Project. Paper 26: The relationship between technology policy and scientific and technical information within the US and Japanese aerospace industries

NASA Technical Reports Server (NTRS)

Pinelli, Thomas E.; Barclay, Rebecca O.; Kennedy, John M.

1993-01-01

Government technology policy has nurtured the growth of the aerospace industry which is vital to both the U.S. and Japanese economies. Japanese technology policy differs significantly from U.S. technology policy, however, particularly with respect to the production, transfer, and use of scientific and technical information (STI). In this paper, we discuss the unique position of the aerospace industry in the U.S. and Japan, U.S. and Japanese aerospace policy, and the role of STI in the process of aerospace innovation. The information-seeking behaviors of U.S. and Japanese aerospace engineers and scientists are compared. The authors advocate the development of innovation-adoption technology and STI policy goals for U.S. aerospace and the inclusion of an aerospace knowledge diffusion transfer system with an 'active' component for scanning and acquiring foreign aerospace technology and STI.

NASA/DoD Aerospace Knowledge Diffusion Research Project. XXVI - The relationship between technology policy and scientific and technical information within the U.S. and Japanese aerospace industries

NASA Technical Reports Server (NTRS)

Pinelli, Thomas E.; Barclay, Rebecca O.; Lahr, Tom; Hoetker, Glenn

1993-01-01

Government technology policy has nurtured the growth of the aerospace industry, which is vital to both the U.S. and Japanese economies. Japanese technology policy differs significantly from U.S. technology policy, however, particularly with respect to the production, transfer, and use of scientific and technical information (STI). In this paper, we discuss the unique position of the aerospace industry in the U.S. and Japan, U.S. and Japanese aerospace policy, and the role of STI in the process of aerospace innovation. The information-seeking behaviors of U.S. and Japanese aerospace engineers and scientists are compared. The authors advocate the development of innovation-adoption technology and STI policy goals for U.S. aerospace and the inclusion of an aerospace knowledge diffusion transfer system with an 'active' component for scanning and acquiring foreign aerospace technology and STI.

Effect of Multiaxial Loading on Crack Growth. Volume 2. Compilation of Experimental Data

DTIC Science & Technology

1978-12-01

3121 9. PERFORMING ORGANIZATION NAME AND ADORESS 10 . PROGRAM ELEMENT. PROJECT, TASK Northrop Corporation AREA & WORK UNIT NUMBERS Aircraft Group 3901...Stresses in the Center of the 2024-T351 9 Cruciform Specimen 9 Stress Distribution along the X-axis of the 10 Cruciform Specimen 10 Stress Distribution...Tensile Test Results for 7075-T7351 584 8 Tensile Test Results for 7075-T7351 600 9 Tensile Test Results for 2024-T351 610 10 Tensile Test Results for

Validation of MIL-F-9490D - General Specification for Flight Control System for Piloted Military Aircraft. Volume II. YF-17 Lightweight Fighter Validation

DTIC Science & Technology

1977-04-01

Leakage current shall not exceed 10 milliamps when a dielectric stress voltage of 1,200 volts, 60 liz, is applied for 1 minute between insulated...include requirements which eqtial or exceed requirements of this paragraph. However, lower values for dielectric stress voltage and insulation...resistance were specified for solid state elec- tronic assemblies. Northrop’s requirement for dielectric strenirth specifies a test voltage of 300 volts RMS

Social and Economic Impacts of Selected Potential Dredged Material Containment Facilities in Long Island Sound.

DTIC Science & Technology

1981-09-01

GRANT NuMBER(s) CENTER FOR THE ENVIRONMENT AND MAN, INC. DACW 33-8U-~e--’-e/ Work Order No. 8 I.~3 PERFORMING ORGANIZATION NAME AND ADDRESS 10. PROGRAM ...08-735 Program Manager Lynn E. Johnson Principal Investigator Gaylord M. Northrop Project Staff John Ball Kenneth Bober Kayla Costenoble Brian...determination of the merits of continuing the program . This is a Stage 2 report. While six potential dredged material containment facilities are

Navy DD(X), GC(X), and LCS Ship Acquisition Programs: Oversight Issues and Options for Congress

DTIC Science & Technology

2005-08-18

5d. PROJECT NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) David D. Acker Library and Knowledge...System Division ( NGSS ) and General Dynamics’ Bath Iron Works (GD/BIW) for the right to build all DD(X)s. The Emergency Supplemental Appropriations Act...take-all competition between Northrop Grumman’s Ship System Division ( NGSS ) and General Dynamics’ Bath Iron Works (GD/BIW) for the right to build

Navy DD(X) and LCS Ship Acquisition Programs: Oversight Issues and Options for Congress

DTIC Science & Technology

2005-01-25

PROJECT NUMBER 5e . TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Congressional Research Service,The...the contract for the next phase on a sole-source basis to NGSS . The first DD(X) would be built by Northrop/Ingalls, while the second would be built...by GD/BIW. The Navy has also stated that “The ship construction contracts will be allocated equally between NGSS and BIW for the first six ships

Proceedings of the Annual Mechanics of Composites Review (8th) Held at Wright-Patterson AFB, Ohio on 5-7 October 1982.

DTIC Science & Technology

1983-04-01

Spectrum Fatigue Behavior of Postbuckled Shear Panels; PO01 246 Development of Analysis for Predicting Compression Fatigt Life and Residual Strength in...Lazyup and Frequency Effects on Fatigue Life of Composites, POOl 256 Effect of Stress Ratio on Fatigue Life of Composites,’ POOl 257 High-Load Transfer...L. Agerwall, Northrop Corporation 0950-1020 BREAK 1020-1100 DEVELOPMENT OF ANALYSIS FOR PREDICTING COMPRESSION 34 FATIGUE LIFE AND RESIDUAL STRENGTH

KSC-07pd3546

NASA Image and Video Library

2007-12-03

KENNEDY SPACE CENTER, FLA. -- STS-122 Pilot Alan Poindexter seems satisfied with the landing practice session he has just completed aboard a shuttle training aircraft, or STA, at Kennedy Space Center's Shuttle Landing Facility. Poindexter and Commander Steve Frick are preparing for the Dec. 6 launch on space shuttle Atlantis. The STA is a Grumman American Aviation-built Gulf Stream II jet that was modified to simulate an orbiter's cockpit, motion and visual cues, and handling qualities. Photo credit: NASA/Kim Shiflett

KSC-07pd3545

NASA Image and Video Library

2007-12-03

KENNEDY SPACE CENTER, FLA. -- STS-122 Commander Steve Frick seems satisfied with the landing practice session he has just completed aboard a shuttle training aircraft, or STA, at Kennedy Space Center's Shuttle Landing Facility. Frick and Pilot Alan Poindexter are preparing for the Dec. 6 launch on space shuttle Atlantis. The STA is a Grumman American Aviation-built Gulf Stream II jet that was modified to simulate an orbiter's cockpit, motion and visual cues, and handling qualities. Photo credit: NASA/Kim Shiflett

Store Separation Lessons Learned During the Last 30 Years

DTIC Science & Technology

2010-01-01

the same time period the Influence Function Method (IFM) was also developed5. This method allowed for a straight STORE SEPARATION LESSONS LEARNED...developed at Grumman under an Air Force contract. The Influence Function Method (IFM)5,6,7 was used to determine the effect of the aircraft flowfield on...A Chimera Grid Scheme,” Advances in Grid Generation, ASME, June 1983. 5. Meyer, R., Cenko, A., and Yaros, S., “An Influence Function Method for

Green Flight Challenge

NASA Image and Video Library

2011-09-25

The Pipistrel-USA, Taurus G4 aircraft approaches for landing as a Grumman Albatross plane is seen in the forground during the 2011 Green Flight Challenge, sponsored by Google, at the Charles M. Schulz Sonoma County Airport in Santa Rosa, Calif. on Monday, Sept. 26, 2011. NASA and the Comparative Aircraft Flight Efficiency (CAFE) Foundation are having the challenge with the goal to advance technologies in fuel efficiency and reduced emissions with cleaner renewable fuels and electric aircraft. Photo Credit: (NASA/Bill Ingalls)

Concluding Report on Free-Spinning and Recovery Characteristics of a 1/24-Scale Model of the Grumman F11F-1 Airplane, TED No. NACA AD 395

NASA Technical Reports Server (NTRS)

Bowman, James S., Jr.

1956-01-01

An investigation has been completed in the Langley 20-foot free-spinning tunnel on a l/24-scale model of the Grumman F11F-1 airplane to determine its spin and recovery characteristics. An interim report, Research Memorandum SL55G20, was published earlier and the present report concludes the presentation of results of the investigation. Primarily, the present report presents results obtained with engine gyroscopic moments simulated on the model. Also, the current results were obtained with a revised larger vertical tail recently incorporated on the airplane. It was difficult to obtain developed spins on the model when the spin direction was in the same sense as that of the engine rotation (right spin on the airplane). The developed spins obtained were very oscillatory and the recoveries were unsatisfactory. These results were similar to those previously reported for which engine rotation was not simulated. When the spin direction was in the opposite sense (left spin on the airplane), however, developed spins were readily obtainable. Recoveries from these spins also were unsatisfactory. Satisfactory recoveries were obtained on the model, however, when rudder reversal was accompanied by extension of small canards near the nose of the airplane or by deflection of the horizontal tail differentially with the spin.

Low-Lift Drag of the Grumman F9F-9 Airplane as Obtained by a 1/7.5-Scale Rocket-Boosted Model and by Three 1/45.85-Scale Equivalent-Body Models between Mach Numbers of 0.8 and 1.3, TED No. NACA DE 391

NASA Technical Reports Server (NTRS)

Stevens, Joseph E.

1955-01-01

Low-lift drag data are presented herein for one 1/7.5-scale rocket-boosted model and three 1/45.85-scale equivalent-body models of the Grumman F9F-9 airplane, The data were obtained over a Reynolds number range of about 5 x 10(exp 6) to 10 x 10(exp 6) based on wing mean aerodynamic chord for the rocket model and total body length for the equivalent-body models. The rocket-boosted model showed a drag rise of about 0,037 (based on included wing area) between the subsonic level and the peak supersonic drag coefficient at the maximum Mach number of this test. The base drag coefficient measured on this model varied from a value of -0,0015 in the subsonic range to a maximum of about 0.0020 at a Mach number of 1.28, Drag coefficients for the equivalent-body models varied from about 0.125 (based on body maximum area) in the subsonic range to about 0.300 at a Mach number of 1.25. Increasing the total fineness ratio by a small amount raised the drag-rise Mach number slightly.

Grumman OV-1B Mohawk Maps the Ice over the Great Lakes

NASA Image and Video Library

1973-03-21

A Grumman OV-1B Mohawk maps Great Lakes’ ice flows for the National Aeronautics and Space Administration (NASA) Lewis Research Center in Cleveland, Ohio. The regular freezing of large portions of the Great Lakes during the winter frequently stalled the region’s shipping industry. Lewis developed two complementary systems to monitor the ice. The Side Looking Airborne Radar (SLAR) system used microwaves to measure the ice distribution, and electromagnetic systems employed noise modulation to determine the thickness of the ice. Once this dual system was in place, the information could be generated during a single pass of a research aircraft and quickly distributed to ship captains planning their routes. The SLAR was superior to aerial photography for this task because it was able to penetrate cloud cover. The SLAR system used pulsed microwaves to examine a band of ice or water on either side of the aircraft up to 31 miles wide. The Lewis ice mapping devices were first tested during the winter of 1972 and 1973. The system was installed on the tail of the Coast Guard’s OV-1B aircraft. An infrared thermal mapping instrument was installed on Lewis’ DC-3 to determine the ice temperature and estimate its thickness. The team created 160 ice charts that were sent to 28 ships and 2 icebreakers. Shipping was able to continue throughout the season for the first time that winter.

76 FR 58776 - U.S. Aerospace Supplier & Investment Mission

Federal Register 2010, 2011, 2012, 2013, 2014

2011-09-22

... DEPARTMENT OF COMMERCE International Trade Administration U.S. Aerospace Supplier & Investment... organizing a U.S. Aerospace Supplier & Investment Mission to Montreal, Canada, May 6-9, 2012. This aerospace.... Participation Requirements All parties interested in participating in the U.S. aerospace trade and investment...

Women in Aerospace Awards

NASA Image and Video Library

2010-10-26

NASA Headquarters Program Planning Specialist Beth Beck speaks after being given the Women in Aerospace's Aerospace Awareness Award at the organization's annual awards ceremony and banquet held at the Ritz-Carlton Hotel in Arlington, VA on Tuesday, Oct. 26, 2010. Four current NASA leaders and one retiree were recognized for their work by Women in Aerospace. The event celebrates women's professional excellence in aerospace and honors women who have made outstanding contributions to the aerospace community. Photo Credit: (NASA/Bill Ingalls)

The Aerospace Age. Aerospace Education I.

ERIC Educational Resources Information Center

Smith, J. C.

This book is written for use only in the Air Force ROTC program and cannot be purchased on the open market. The book describes the historical development of aerospace industry. The first chapter contains a brief review of the aerospace environment and the nature of technological changes brought by the aerospace revolution. The following chapter…

Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail

NASA Technical Reports Server (NTRS)

Arbic, R. G.

1955-01-01

Results are presented of a free-flight investigation between Mach numbers of 0.7 to 1.3 and Reynolds numbers of 3.1 x 10(exp 6) to 7.0 x 10(exp 6) to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. This missile has a weng, body, and vertical tail, but has no horizontal tail. The basic wing plan form has an aspect ratio of 5.5, 45 deg of sweepback of the 0.406 streamwise chord line, and a taper ratio of 0.4. A 1/10-scale steel-wing model of the missile was flown with modifications to the basic wing plan form consisting of leading-edge chord-extensions deflected 7 deg downward together with the forward 15 percent of the wing chord, and inboard trailing-edge flaps deflected 5 deg downward. In addition, the model had a static-pressure tube mounted at the tip of the vertical tail for position-error measurements and had a speed brake also mounted on the vertical tail to trim the model to positive lift coefficients and to permit determination of the trim and drag effectiveness of the brake. The data are uncorrected for the effects of wing elasticity, but experimental wing influence coefficients are presented.

Aerospace Education - An Overview

ERIC Educational Resources Information Center

Journal of Aerospace Education, 1975

1975-01-01

Discusses the surge of interest throughout the country in aerospace education and discusses what aerospace education is, the implications in career education and the relevance of aerospace education in the curriculum. (BR)

Basic Aerospace Education Library

ERIC Educational Resources Information Center

Journal of Aerospace Education, 1975

1975-01-01

Lists the most significant resource items on aerospace education which are presently available. Includes source books, bibliographies, directories, encyclopedias, dictionaries, audiovisuals, curriculum/planning guides, aerospace statistics, aerospace education statistics and newsletters. (BR)

NASA/DOD Aerospace Knowledge Diffusion Research Project. Paper 5: Aerospace librarians and technical information specialists as information intermediaries: A report of phase 2 activities of the NASA/DOD Aerospace Knowledge Diffusion Research Project

NASA Technical Reports Server (NTRS)

Pinelli, Thomas E.; Kennedy, John M.

1990-01-01

The objective of the NASA/DOD Aerospace Knowledge Diffusion Research Project is to provide descriptive and analytical data regarding the flow of scientific and technical information (STI) at the individual, organizational, national, and international levels, placing emphasis on the systems used to diffuse the results of federally funded aerospace STI. An overview of project assumptions, objectives, and design is presented and preliminary results of the phase 2 aerospace library survey are summarized. Phase 2 addressed aerospace knowledge transfer and use within the larger social system and focused on the flow of aerospace STI in government and industry and the role of the information intermediary in knowledge transfer.

NASA/DOD Aerospace Knowledge Diffusion Research Project. Paper 39: The role of computer networks in aerospace engineering

NASA Technical Reports Server (NTRS)

Bishop, Ann P.; Pinelli, Thomas E.

1994-01-01

This paper presents selected results from an empirical investigation into the use of computer networks in aerospace engineering. Such networks allow aerospace engineers to communicate with people and access remote resources through electronic mail, file transfer, and remote log-in. The study drew its subjects from private sector, government and academic organizations in the U.S. aerospace industry. Data presented here were gathered in a mail survey, conducted in Spring 1993, that was distributed to aerospace engineers performing a wide variety of jobs. Results from the mail survey provide a snapshot of the current use of computer networks in the aerospace industry, suggest factors associated with the use of networks, and identify perceived impacts of networks on aerospace engineering work and communication.

Low Cost Manufacturing of Composite Cryotanks

NASA Technical Reports Server (NTRS)

Meredith, Brent; Palm, Tod; Deo, Ravi; Munafo, Paul M. (Technical Monitor)

2002-01-01

This viewgraph presentation reviews research and development of cryotank manufacturing conducted by Northrup Grumman. The objectives of the research and development included the development and validation of manufacturing processes and technology for fabrication of large scale cryogenic tanks, the establishment of a scale-up and facilitization plan for full scale cryotanks, the development of non-autoclave composite manufacturing processes, the fabrication of subscale tank joints for element tests, the performance of manufacturing risk reduction trials for the subscale tank, and the development of full-scale tank manufacturing concepts.

Thermoluminescent dosimetry for LDEF experiment M0006

NASA Technical Reports Server (NTRS)

Chang, J. Y.; Giangano, D.; Kantorcik, T.; Stauber, M.; Snead, L.

1992-01-01

Experiment M0006 on the Long Duration Exposure Facility had as its objective the investigation of space radiation effects on various electronic and optical components, as well as on seed germination. The Grumman Corporate Research Center provided the radiation dosimetric measurements for M0006, comprising the preparation of thermoluminescent dosimeters (TLD) and the subsequent measurement and analysis of flight exposed and control samples. In addition, various laboratory exposures of TLD's with gamma rays and protons were performed to obtain a better understanding of the flight exposures.

Grumman evaluates Space Station thermal control and power systems

DOE Office of Scientific and Technical Information (OSTI.GOV)

Kandebo, S.W.

1985-09-01

Attention is given to the definition of requirements for the NASA Space Station's electrical power and thermal control systems, which must be highly dependable to minimize the need for external support and will embody a highly flexible modular design concept. Module maintenance will be performed by in-orbit replacement of failed modules, and energy storage system growth will be accomplished by the incorporation of additional modules. Both photovoltaic and solar heat-driven electrical generator concepts are under consideration as the basis of the power system.

Weapon System Software Acquisition and Support: A Theory of System Structure and Behavior.

DTIC Science & Technology

1982-03-01

Labs, Raytheon, FMC Inorganic Chemicals Division, Motorola Military Electroncs, Hughes Aircraft, General Dynamics/Fort Worth, Grumman and IBM, among...Organization Engineering Manpower M-16A Engineers Authorized ENGEN Expected Nunber of M-17 Engineers Engineers LEI Level of Engineers M-17A Engineers...productivity sector are listed below: ENGEX.K=ENGEX.J+DT(ENGCT.JK-REXEL.JK -RREA.JK) M-21,Level ENGEN =LEI M-17N,Initial ENGTOT=LEI M-18N,Initial ENGEX=LEI M

Artists concept of Apollo 11 Astronaut Neil Armstrong on the moon

NASA Technical Reports Server (NTRS)

1969-01-01

A Grumman Aircraft Engineering Corporation artist's concept depicting mankind's first walk on another celestianl body. Here, Astronaut Neil Armstrong, Apollo 11 commander, is making his first step onto the surface of the moon. In the background is the Earth, some 240,000 miles away. Armstrong. They are continuing their postflight debriefings. The three astronauts will be released from quarantine on August 11, 1969. Donald K. Slayton (right), MSC Director of Flight Crew Operations; and Lloyd Reeder, training coordinator.

[NASA/DOD Aerospace Knowledge Diffusion Research Project. Paper 7:] The NASA/DOD Aerospace Knowledge Diffusion Research Project: The DOD perspective

NASA Technical Reports Server (NTRS)

Pinelli, Thomas E.; Kennedy, John M.

1990-01-01

This project will provide descriptive and analytical data regarding the flow of STI at the individual, organizational, national, and international levels. It will examine both the channels used to communicate information and the social system of the aerospace knowledge diffusion process. Results of the project should provide useful information to R and D managers, information managers, and others concerned with improving access to and use of STI. Objectives include: (1) understanding the aerospace knowledge diffusion process at the individual, organizational, and national levels, placing particular emphasis on the diffusion of Federally funded aerospace STI; (2) understanding the international aerospace knowledge diffusion process at the individual and organizational levels, placing particular emphasis on the systems used to diffuse the results of Federally funded aerospace STI; (3) understanding the roles NASA/DoD technical report and aerospace librarians play in the transfer and use of knowledge derived from Federally funded aerospace R and D; (4) achieving recognition and acceptance within NASA, DoD and throughout the aerospace community that STI is a valuable strategic resource for innovation, problem solving, and productivity; and (5) providing results that can be used to optimize the effectiveness and efficiency of the Federal STI aerospace transfer system and exchange mechanism.

Aerospace management techniques: Commercial and governmental applications

NASA Technical Reports Server (NTRS)

Milliken, J. G.; Morrison, E. J.

1971-01-01

A guidebook for managers and administrators is presented as a source of useful information on new management methods in business, industry, and government. The major topics discussed include: actual and potential applications of aerospace management techniques to commercial and governmental organizations; aerospace management techniques and their use within the aerospace sector; and the aerospace sector's application of innovative management techniques.

X-4 with Pilot Joe Walker, Preflight Briefing

NASA Technical Reports Server (NTRS)

1952-01-01

In this 1952 photograph NACA test pilot Joe Walker (on left) is seen discussing tests points to be flown on the X-4 aircraft with NACA research engineer Donald Bellman. The X-4 Bantam, a single-place, low swept-wing, semi-tailless aircraft, was designed and built by Northrop Aircraft, Inc. It had no horizontal tail surfaces and its mission was to obtain in-flight data on the stability and control of semi-tailless aircraft at high subsonic speeds. The Northrop X-4, Bantam, was a single-place, swept-wing, semi-tailless airplane designed and built to investigate that configuration at transonic speeds (defined as speeds just below and just above the speed of sound, but in this case, the testing was done primarily at just below the speed of sound). The hope of some aerodynamicists was that eliminating the horizontal tail would also do away with stability problems at transonic speeds resulting from the interaction of supersonic shock waves from the wings and the horizontal stabilizers. Northrop Aircraft, Inc. built two X-4 aircraft, the first of which proved to be mechanically unsound. However, ship number 2, with a thicker trailing edge on the wings and elevon, was very reliable. Ship 1 was then grounded and used as parts for ship 2. While being tested from 1950 to 1953 at the NACA High-Speed Flight Research Station (predecessor of today's NASA Dryden Flight Research Center, Edwards, California), the X-4's semi-tailless configuration exhibited inherent longitudinal stability problems (porpoising) as it approached the speed of sound. The X-4 was a small twinjet-engine airplane that had no horizontal tail surfaces, depending instead on combined elevator and aileron control surfaces (called elevons) for control in pitch and roll attitudes. Data gathered from the aircraft's blunt elevon research were helpful in the design of the Bell X-2, which had ailerons with blunted trailing edges. The NACA X-4 program also provided substantial data on the interactions of combined pitching, rolling, and yawing motions. This interaction was soon to become critical to upcoming high-performance military fighters. The X-4, ship 2, flew 82 research flights from 1950 to 1953. With a minimal lift-to-drag ratio of less than 3, the X-4 performance was similar to the soon-to-be-developed X-15. With this similarity in mind, NACA conducted approach and landing studies of X-15-generation aircraft using the X-4. The X-4, retired in 1954, ended its days as a pilot trainer.

NASA/DOD Aerospace Knowledge Diffusion Research Project. Paper 11: The Voice of the User: How US Aerospace Engineers and Scientists View DoD Technical Reports

NASA Technical Reports Server (NTRS)

Pinelli, Thomas E.; Kennedy, John M.

1991-01-01

The project examines how the results of NASA/DOD research diffuse into the aerospace R&D process, and empirically analyzes the implications of the aerospace knowledge diffusion process. Specific issues considered are the roles played by government technical reports, the recognition of the value of scientific and technical information (STI), and the optimization of the STI aerospace transfer system. Information-seeking habits are assessed for the U.S. aerospace community, the general community, the academic sector, and the international community. U.S. aerospace engineers and scientists use 65 percent of working time to communicate STI, and prefer 'internal' STI over 'external' STI. The isolation from 'external' information is found to be detrimental to U.S. aerospace R&D in general.

NASA/DOD Aerospace Knowledge Diffusion Research Project. Paper 14: An analysis of the technical communications practices reported by Israeli and US aerospace engineers and scientists

NASA Technical Reports Server (NTRS)

Barclay, Rebecca O.; Pinelli, Thomas E.; Elazar, David; Kennedy, John M.

1991-01-01

As part of Phase 4 of the NASA/DoD Aerospace Knowledge Diffusion Research Project, two pilot studies were conducted that investigated the technical communications practices of Israeli and U.S. aerospace engineers and scientists. Both studies had the same five objectives: first, to solicit the opinions of aerospace engineers and scientists regarding the importance of technical communications to their profession; second, to determine the use and production of technical communications by aerospace engineers and scientists; third, to seek their view about the appropriate content of an undergraduate course in technical communications; fourth, to determine aerospace engineers' and scientists' use of libraries, technical information centers, and on-line databases; and fifth, to determine the use and importance of computer and information technology to them. A self-administered questionnaire was mailed to randomly selected U.S. aerospace engineers and scientists who are working in cryogenics, adaptive walls, and magnetic suspension. A slightly modified version was sent to Israeli aerospace engineers and scientists working at Israel Aircraft Industries, LTD. Responses of the Israeli and U.S. aerospace engineers and scientists to selected questions are presented in this paper.

78 FR 1265 - Aerospace Safety Advisory Panel; Meeting

Federal Register 2010, 2011, 2012, 2013, 2014

2013-01-08

... NATIONAL AERONAUTICS AND SPACE ADMINISTRATION [Notice 13-001] Aerospace Safety Advisory Panel... Aeronautics and Space Administration announces a forthcoming meeting of the Aerospace Safety Advisory Panel..., Aerospace Safety Advisory Panel Executive Director, National Aeronautics and Space Administration...

76 FR 62455 - Aerospace Safety Advisory Panel; Meeting

Federal Register 2010, 2011, 2012, 2013, 2014

2011-10-07

... NATIONAL AERONAUTICS AND SPACE ADMINISTRATION [Notice (11-088)] Aerospace Safety Advisory Panel... Aeronautics and Space Administration announces a forthcoming meeting of the Aerospace Safety Advisory Panel... Burch, Aerospace Safety Advisory Panel Administrative Officer, National Aeronautics and Space...

U.S. Aerospace and Aviation Industry: A State-By-State Analysis

NASA Technical Reports Server (NTRS)

2002-01-01

President George W. Bush and the Congress created the Commission on the Future of the United States Aerospace Industry to evaluate the current and future health of the industry as well as the challenges that lie ahead for the U.S. workforce and the economy. To accomplish our mission, we commissioned a study on the economic impact of the aerospace industry nationally and on a state-by-state basis, using the best available U.S. government data. This study sought to define the core of the aerospace industry. The resulting data represents that very core those jobs specifically tied to commercial and civilian aerospace. U.S. Aerospace and Aviation: A State-by-State Analysis examines the civilian and commercial aerospace and aviation industry by employment, wages, payroll, and establishments. The report found that the U.S. civilian and commercial aerospace and aviation industry employed over 2 million workers in 2001.

Recent advances in the development of aerospace materials

NASA Astrophysics Data System (ADS)

Zhang, Xuesong; Chen, Yongjun; Hu, Junling

2018-02-01

In recent years, much progress has been made on the development of aerospace materials for structural and engine applications. Alloys, such as Al-based alloys, Mg-based alloys, Ti-based alloys, and Ni-based alloys, are developed for aerospace industry with outstanding advantages. Composite materials, the innovative materials, are taking more and more important roles in aircrafts. However, recent aerospace materials still face some major challenges, such as insufficient mechanical properties, fretting wear, stress corrosion cracking, and corrosion. Consequently, extensive studies have been conducted to develop the next generation aerospace materials with superior mechanical performance and corrosion resistance to achieve improvements in both performance and life cycle cost. This review focuses on the following topics: (1) materials requirements in design of aircraft structures and engines, (2) recent advances in the development of aerospace materials, (3) challenges faced by recent aerospace materials, and (4) future trends in aerospace materials.

Proceedings of a Conference on Multi-Cultural Aerospace Education Programs in Schools and Museums (June 11-12, 1979).

ERIC Educational Resources Information Center

Joels, Kerry M., Ed.; Podolske, Helen W., Ed.

Twenty papers on multi-cultural aerospace education are presented and cover a wide range of topics, all dealing with some aspect of teaching aerospace education with or without applications to the teaching of minority students. Aerospace education as a motivating force in learning is the topic of two papers. Minorities in aerospace education, as a…

Encyclopedia of U.S. Air Force Aircraft and Missile Systems. Volume 2. Post-World War II Bombers, 1945-1973

DTIC Science & Technology

1988-01-01

36 program. Of perhaps greater import, this cooperation would blend Northrop’s engineering skill and Convair’s experience in quantity production of...projects. Small swept winglets were attached along- side the nose of the reconfigured bomber-NB-52E. A long probe extended from the nose of the modified...the aircraft’s winglets (canards), which reduced 30 percent of the vertical and 50 percent of the horizontal vibrations caused by air gusts. The NB

Navy DDG-1000 (DD(X)) and CG(X) Programs: Background and Issues for Congress

DTIC Science & Technology

2006-06-20

Report RL32665, Navy Force Structure and Shipbuilding Plans : Background and Issues for Congress, by Ronald O’Rourke. The Navy wants to procure a total of 7...DDG-1000s and 19 CG(X)s as part of a proposed 313-ship fleet.2 Under the Navy’s proposed plan , the first two DDG-1000s are to be procured in FY2007...major DDG-1000 contractors, including Northrop Grumman’s Ship Systems ( NGSS ) division (which includes the Ingalls Shipyard in Pascagoula, MS), General

75 FR 61219 - Aerospace Safety Advisory Panel; Meeting

Federal Register 2010, 2011, 2012, 2013, 2014

2010-10-04

... NATIONAL AERONAUTICS AND SPACE ADMINISTRATION [Notice (10-116)] Aerospace Safety Advisory Panel... Aeronautics and Space Administration announces a forthcoming meeting of the Aerospace Safety Advisory Panel... Dakon, Aerospace Safety Advisory Panel Executive Director, National Aeronautics and Space Administration...

76 FR 19147 - Aerospace Safety Advisory Panel; Meeting.

Federal Register 2010, 2011, 2012, 2013, 2014

2011-04-06

... NATIONAL AERONAUTICS AND SPACE ADMINISTRATION [Notice (11-030)] Aerospace Safety Advisory Panel... Aeronautics and Space Administration announce a forthcoming meeting of the Aerospace Safety Advisory Panel.... Kathy Dakon, Aerospace Safety Advisory Panel Executive Director, National Aeronautics and Space...

78 FR 15976 - Aerospace Safety Advisory Panel; Meeting.

Federal Register 2010, 2011, 2012, 2013, 2014

2013-03-13

... NATIONAL AERONAUTICS AND SPACE ADMINISTRATION [Notice: 13-023] Aerospace Safety Advisory Panel... Aeronautics and Space Administration announce a forthcoming meeting of the Aerospace Safety Advisory Panel... Space Administration, Washington, DC 20546, (202) 358-1857. SUPPLEMENTARY INFORMATION: The Aerospace...

78 FR 56941 - Aerospace Safety Advisory Panel; Meeting

Federal Register 2010, 2011, 2012, 2013, 2014

2013-09-16

... NATIONAL AERONAUTICS AND SPACE ADMINISTRATION [Notice: 13-114] Aerospace Safety Advisory Panel... Aeronautics and Space Administration announces a forthcoming meeting of the Aerospace Safety Advisory Panel.... Harmony Myers, Aerospace Safety Advisory Panel Executive Director, National Aeronautics and Space...

77 FR 58413 - Aerospace Safety Advisory Panel; Meeting

Federal Register 2010, 2011, 2012, 2013, 2014

2012-09-20

... NATIONAL AERONAUTICS AND SPACE ADMINISTRATION [Notice 12-074] Aerospace Safety Advisory Panel... Aeronautics and Space Administration announces a forthcoming meeting of the Aerospace Safety Advisory Panel.... Harmony Myers, Aerospace Safety Advisory Panel Executive Director, National Aeronautics and Space...

77 FR 38090 - Aerospace Safety Advisory Panel; Meeting.

Federal Register 2010, 2011, 2012, 2013, 2014

2012-06-26

... NATIONAL AERONAUTICS AND SPACE ADMINISTRATION [Notice 12-044] Aerospace Safety Advisory Panel... Aeronautics and Space Administration announces a forthcoming meeting of the Aerospace Safety Advisory Panel.... Harmony Myers, Aerospace Safety Advisory Panel Executive Director, National Aeronautics and Space...

Free-Spinning Characteristics of a 1/24-Scale Model of the Grumman F11F-1 Airplane, TED No. NACA AD 395

NASA Technical Reports Server (NTRS)

Bowman, James S., Jr.

1955-01-01

An investigation is being conducted in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the Grumman F11F-1 airplane to determine spin and recovery characteristics and the minimum-size parachute required to satisfactorily terminate the spin in an emergency. Results obtained to date are presented herein. Test results indicate that it may be difficult to obtain an erect or inverted spin on the airplane, but, if a spin is obtained, the spin will be very oscillatory and recovery from the developed erect spin by rudder reversal may not be possible. The lateral controls will have no appreciable effect on recoveries from erect.spins. Recovery from the inverted spin by merely neutralizing the rudder will be satisfactory. After recoveries by rudder reversal and after recoveries from spins without control movement (no spins), the model oftentimes rolled very rapidly about the X-axis. Based on limited preliminary tests made in this investigation to make the model recover satisfactorily, it appears that canards near the nose of the airplane or differentially operated horizontal tails may be utilized to provide rapid recoveries. The parachute test results indicate that an 11-foot-diameter (laid-out-flat) parachute with a drag coefficient of 0.650 (based on the laid- out-flat diameter) and with a towline length equal to the wing span is the minimum-size parachute required to satisfactorily terminate an erect or inverted spin in an emergency.

An Investigation of the Free-Spinning and Recovery Characteristics of a 1/24-Scale Model of the Grumman F11F-1 Airplane with Alternate Nose Configurations with and without Wing Fuel Tanks, TED No. NACA AD 395

NASA Technical Reports Server (NTRS)

Bowman, James S., Jr.

1958-01-01

A supplementary investigation has been conducted in the langley 20-foot free-spinning tunnel on a l/24-scale model of the Grumman F11F-1 airplane to determine the spin and recovery characteristics with alternate nose configurations, the production version and the elongated APS-67 version, with and without empty and full wing tanks. When spins were obtained with either alternate nose configuration, they were oscillatory and recovery characteristics were considered unsatisfactory on the basis of the fact that very slow recoveries were indicated to be possible. The simultaneous extension of canards near the nose of the model with rudder reversal was effective in rapidly terminating the spin. The addition of empty wing tanks had little effect on the developed spin and recovery characteristics. The model did not spin erect with full wing tanks. For optimum recovery from inverted spins, the rudder should be reversed to 22O against the spin and simultaneously the flaperons should be moved with the developed spin; the stick should be held at or moved to full forward longitudinally. The minimum size parachute required to insure satisfactory recoveries in an emergency was found to be 12 feet in diameter (laid out flat) with a drag coefficient of 0.64 (based on the laid-out-flat diameter) and a towline length of 32 feet.

77 FR 74579 - Airworthiness Directives; Gulfstream Aerospace Corporation Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-12-17

... Airworthiness Directives; Gulfstream Aerospace Corporation Airplanes AGENCY: Federal Aviation Administration... directive (AD) for certain Gulfstream Aerospace Corporation Model GIV-X airplanes. This AD requires... Aerospace Corporation, Technical Publications Dept., P.O. Box 2206, Savannah, GA 31402-2206; telephone 800...

An Assessment of the Effectiveness of Selected Aerospace Education Workshops in Tennessee

ERIC Educational Resources Information Center

Maupin, Pauline Hicks

1976-01-01

Data from questionnaires indicated that the Tennessee Aerospace Education Workshops were successful in reaching their stated goals, which included developing a greater awareness of aerospace education and helping teachers incorporate more aerospace education in classroom activities. (MLH)

International Access to Aerospace Information.

DTIC Science & Technology

1980-04-01

data that belong into the category ’reproducible" belong here into the category ’conditions controlled by man" " non reproducible data’ belong into the...SESSION IV - NON -LITERATURE DATA IN AEROSPACE RESEARCH AND DEVELOPMENT THE NUMERIC AEROSPACE DATA: PROBLEMS OF EVALUATION, HANDLING AND DISSEMINATION...34. Sessions III and IV, held on 18 October, were entitled "Problems of Utilization of Aerospace Literature" and " Non -Literature Data in Aerospace and

NASA/DoD Aerospace Knowledge Diffusion Research Project, Paper Six: Aerospace Knowledge Diffusion in the Academic Community: A Report of Phase 3 Activities of the NASA/DoD Aerospace Knowledge Diffusion Research Project

DTIC Science & Technology

1990-06-27

empirically derived data, very little is known about the diffusion of knowledge in the aerospace industry both in terms of the channels used to communicate... diffusion of knowledge resulting from federally funded aerospace R&D and the academic community. Faced with shrinking enrollments, particularly at the

Lightning Protection Guidelines for Aerospace Vehicles

NASA Technical Reports Server (NTRS)

Goodloe, C. C.

1999-01-01

This technical memorandum provides lightning protection engineering guidelines and technical procedures used by the George C. Marshall Space Flight Center (MSFC) Electromagnetics and Aerospace Environments Branch for aerospace vehicles. The overviews illustrate the technical support available to project managers, chief engineers, and design engineers to ensure that aerospace vehicles managed by MSFC are adequately protected from direct and indirect effects of lightning. Generic descriptions of the lightning environment and vehicle protection technical processes are presented. More specific aerospace vehicle requirements for lightning protection design, performance, and interface characteristics are available upon request to the MSFC Electromagnetics and Aerospace Environments Branch, mail code EL23.

75 FR 39911 - Aerospace Supplier Development Mission to China

Federal Register 2010, 2011, 2012, 2013, 2014

2010-07-13

... DEPARTMENT OF COMMERCE International Trade Administration Aerospace Supplier Development Mission... Commercial Service (CS) is organizing an Aerospace Supplier Development Mission to China from November 7-17, 2010. The 2010 Aerospace Supplier Development Mission to China is being developed due to a successful...

78 FR 49908 - Airworthiness Directives; Eclipse Aerospace, Inc. Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-08-16

... Airworthiness Directives; Eclipse Aerospace, Inc. Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for all Eclipse Aerospace... Eclipse Aerospace, Inc., 26 East Palatine Road, Wheeling, Illinois 60090; telephone: (877) 373-7978...

Aerospace Education. NSTA Position Statement

ERIC Educational Resources Information Center

National Science Teachers Association (NJ1), 2008

2008-01-01

National Science Teachers Association (NSTA) has developed a new position statement, "Aerospace Education." NSTA believes that aerospace education is an important component of comprehensive preK-12 science education programs. This statement highlights key considerations that should be addressed when implementing a high quality aerospace education…

Technical communications in aerospace - An analysis of the practices reported by U.S. and European aerospace engineers and scientists

NASA Technical Reports Server (NTRS)

Pinelli, Thomas E.; Barclay, Rebecca O.; Kennedy, John M.; Glassman, Myron

1990-01-01

The flow of scientific and technical information (STI) at the individual, organizational, national, and international levels is studied. The responses of U.S and European aerospace engineers and scientists to questionnaires concerning technical communications in aerospace are examined. Particular attention is given to the means used to communicate information and the social system of the aerospace knowledge diffusion process. Demographic data about the survey respondents are provided. The methods used to communicate technical data and the sources utilized to solve technical problems are described. The importance of technical writing skills and the use of computer technology in the aerospace field are discussed. The derived data are useful for R&D and information managers in order to improve access to and utilization of aerospace STI.

NASA/DOD Aerospace Knowledge Diffusion Research Project. Paper 33: Technical communications practices and the use of information technologies as reported by Dutch and US aerospace engineers

NASA Technical Reports Server (NTRS)

Barclay, Rebecca O.; Pinelli, Thomas E.; Tan, Axel S. T.; Kennedy, John M.

1993-01-01

As part of Phase 4 of the NASA/DOD Aerospace Knowledge Diffusion Research Project, two studies were conducted that investigated the technical communications practices of Dutch and U.S. aerospace engineers and scientists. A self-administered questionnaire was distributed to aerospace engineers and scientists at the National Aerospace Laboratory (The Netherlands), and NASA ARC (U.S.), and NASA LaRC (U.S.). This paper presents responses of the Dutch and U.S. participants to selected questions concerning four of the seven project objectives: determining the importance of technical communications to aerospace engineering professionals, investigating the production of technical communications, examining the use and importance of computer and information technology, and exploring the use of electronic networks.

NASA-UVa light aerospace alloy and structures technology program

NASA Technical Reports Server (NTRS)

Gangloff, Richard P.; Haviland, John K.; Herakovich, Carl T.; Pilkey, Walter D.; Pindera, Marek-Jerzy; Scully, John R.; Stoner, Glenn E.; Swanson, Robert E.; Thornton, Earl A.; Wawner, Franklin E., Jr.

1991-01-01

The general objective of the NASA-UVa Light Aerospace Alloy and Structures Technology Program was to conduct research on the performance of next generation, light weight aerospace alloys, composites, and associated thermal gradient structures. The following research areas were actively investigated: (1) mechanical and environmental degradation mechanisms in advanced light metals and composites; (2) aerospace materials science; (3) mechanics of materials and composites for aerospace structures; and (4) thermal gradient structures.

Women in Aerospace Awards

NASA Image and Video Library

2010-10-26

NASA Deputy Administrator Lori Garver speaks after being given the Women in Aerospace's Outstanding Member Award at the organization's annual awards ceremony and banquet held at the Ritz-Carlton Hotel in Arlington, VA on Tuesday, Oct. 26, 2010. Four current NASA leaders and one retiree were recognized for their work by Women in Aerospace. The event celebrates women's professional excellence in aerospace and honors women who have made outstanding contributions to the aerospace community. Photo Credit: (NASA/Bill Ingalls)

NASA/DOD Aerospace Knowledge Diffusion Research Project. Paper 69: Writing for the Aerospace Industry. Chapter 3; The Practice of Technical and Scientific Communication: Writing in Professional Contexts

NASA Technical Reports Server (NTRS)

Barclay, Rebecca O.; Pinelli, Thomas E.

1997-01-01

The large and complex aerospace industry, which employed approximately 850,000 people in 1994 (Aerospace Facts, 1994-95, p. 11), plays a vital role in the nation's economy. Although only a small percentage of those employed in aerospace are technical communicators, they perform a wide variety of communication duties in government and the private sector.

Women in Aerospace Awards

NASA Image and Video Library

2010-10-26

NASA's Langley Research Center Lesa Roe speaks after being given the Women in Aerospace's Leadership Award at the organization's annual awards ceremony and banquet held at the Ritz-Carlton Hotel in Arlington, VA on Tuesday, Oct. 26, 2010. Four current NASA leaders and one retiree were recognized for their work by Women in Aerospace. The event celebrates women's professional excellence in aerospace and honors women who have made outstanding contributions to the aerospace community. Photo Credit: (NASA/Bill Ingalls)

76 FR 1600 - U.S. Aerospace Supplier & Investment Mission

Federal Register 2010, 2011, 2012, 2013, 2014

2011-01-11

... DEPARTMENT OF COMMERCE International Trade Administration U.S. Aerospace Supplier & Investment... Commercial Service is organizing a U.S. Aerospace Supplier & Investment Mission to Montreal, Canada on May 2... parties interested in participating in the U.S. Aerospace Trade and Investment Mission must complete and...

75 FR 16662 - Airworthiness Directives; Kelly Aerospace Energy Systems, LLC Rebuilt Turbochargers

Federal Register 2010, 2011, 2012, 2013, 2014

2010-04-02

... Airworthiness Directives; Kelly Aerospace Energy Systems, LLC Rebuilt Turbochargers AGENCY: Federal Aviation... airworthiness directive (AD) for certain Kelly Aerospace Energy Systems, LLC (KAES) rebuilt turbochargers. This... Federal holidays. Fax: (202) 493-2251. Contact Kelly Aerospace Energy Systems, LLC, 2900 Selma Highway...

Aerospace Meteorology Lessons Learned Relative to Aerospace Vehicle Design and Operations

NASA Technical Reports Server (NTRS)

Vaughan, William W.; Anderson, B. Jeffrey

2004-01-01

Aerospace Meteorology came into being in the 1950s as the development of rockets for military and civilian usage grew in the United States. The term was coined to identify those involved in the development of natural environment models, design/operational requirements, and environment measurement systems to support the needs of aerospace vehicles, both launch vehicles and spacecraft. It encompassed the atmospheric environment of the Earth, including Earth orbit environments. Several groups within the United States were active in this area, including the Department of Defense, National Aeronautics and Space Administration, and a few of the aerospace industry groups. Some aerospace meteorology efforts were similar to those being undertaken relative to aviation interests. As part of the aerospace meteorology activities a number of lessons learned resulted that produced follow on efforts which benefited from these experiences, thus leading to the rather efficient and technologically current descriptions of terrestrial environment design requirements, prelaunch monitoring systems, and forecast capabilities available to support the development and operations of aerospace vehicles.

NASA/DOD Aerospace Knowledge Diffusion Research Project. Paper 42: An analysis of the transfer of Scientific and Technical Information (STI) in the US aerospace industry

NASA Technical Reports Server (NTRS)

Kennedy, John M.; Pinelli, Thomas E.; Hecht, Laura F.; Barclay, Rebecca O.

1994-01-01

The U.S. aerospace industry has a long history of federal support for research related to its needs. Since the establishment of the National Advisory Committee for Aeronautics (NACA) in 1915, the federal government has provided continuous research support related to flight and aircraft design. This research has contributed to the international preeminence of the U.S. aerospace industry. In this paper, we present a sociological analysis of aerospace engineers and scientists and how their attitudes and behaviors impact the flow of scientific and technical information (STI). We use a constructivist framework to explain the spotty dissemination of federally funded aerospace research. Our research is aimed towards providing federal policymakers with a clearer understanding of how and when federally funded aerospace research is used. This understanding will help policymakers design improved information transfer systems that will aid the competitiveness of the U.S. aerospace industry.

NASA/DOD Aerospace Knowledge Diffusion Research Project. Paper 6: Aerospace knowledge diffusion in the academic community: A report of phase 3 activities of the NASA/DOD Aerospace Knowledge Diffusion Research Project

NASA Technical Reports Server (NTRS)

Pinelli, Thomas E.; Kennedy, John M.

1990-01-01

Descriptive and analytical data regarding the flow of aerospace-based scientific and technical information (STI) in the academic community are presented. An overview is provided of the Federal Aerospace Knowledge Diffusion Research Project, illustrating a five-year program on aerospace knowledge diffusion. Preliminary results are presented of the project's research concerning the information-seeking habits, practices, and attitudes of U.S. aerospace engineering and science students and faculty. The type and amount of education and training in the use of information sources are examined. The use and importance ascribed to various information products by U.S. aerospace faculty and students including computer and other information technology is assessed. An evaluation of NASA technical reports is presented and it is concluded that NASA technical reports are rated high in terms of quality and comprehensiveness, citing Engineering Index and IAA as the most frequently used materials by faculty and students.

NASA/DOD Aerospace Knowledge Diffusion Research Project. Report 23: The communications practices of US aerospace engineering faculty and students: Results of the phase 3 survey

NASA Technical Reports Server (NTRS)

Pinelli, Thomas E.; Barclay, Rebecca O.; Kennedy, John M.

1994-01-01

The U.S. government technical report is a primary means by which the results of federally funded research and development (R&D) are transferred to the U.S. aerospace industry. However, little is known about this information product in terms of its actual use, importance, and value in the transfer of federally funded R&D. To help establish a body of knowledge, the U.S. government technical report is being investigated as part of the NASA/DOD Aerospace Knowledge Diffusion Research Project. In this report, we summarize the literature on technical reports and provide a model that depicts the transfer of federally funded aerospace R&D via the U.S. government technical report. We present results from our investigation of aerospace knowledge diffusion vis-a-vis the U.S. government technical report, and present the results of research that investigated aerospace knowledge diffusion vis-a-vis U.S. aerospace engineering faculty and students.

NASA/DoD aerospace knowledge diffusion research project. VIII - The role of the information intermediary in the diffusion of aerospace knowledge

NASA Technical Reports Server (NTRS)

Pinelli, Thomas E.; Kennedy, John M.; Barclay, Rebecca O.

1990-01-01

The U.S. aerospace industry is experiencing profound changes created by a combination of domestic actions and circumstances such as airline deregulation. Other changes result from external trends such as emerging foreign competition. These circumstances intensify the need to understand the production, transfer, and utilization of knowledge as a precursor to the rapid diffusion of technology. This article presents a conceptual framework for understanding the diffusion of aerospace knowledge. The framework focuses on the information channels and members of the social system associated with the aerospace knowledge diffusion process, placing particular emphasis on aerospace librarians as information intermediaries.

NASA/DOD Aerospace Knowledge Diffusion Research Project. Paper 41: Technical communication practices of Dutch and US aerospace engineers and scientists: International perspective on aerospace

NASA Technical Reports Server (NTRS)

Barclay, Rebecca O.; Pinelli, Thomas E.; Kennedy, John M.

1994-01-01

As part of Phase 4 of the NASA/DOD Aerospace Knowledge Diffusion Research Project, studies were conducted that investigated the technical communications practices of Dutch and U.S. aerospace engineers and scientists. The studies had the following objectives: (1) to solicit the opinions of aerospace engineers and scientists regarding the importance of technical communication to their professions, (2) to determine the use and production of technical communication by aerospace engineers and scientists, (3) to investigate their use of libraries and technical information centers, (4) to investigate their use of and the importance to them of computer and information technology, (5) to examine their use of electronic networks, and (6) to determine their use of foreign and domestically produced technical reports. Self-administered (mail) questionnaires were distributed to Dutch aerospace engineers and scientists at the National Aerospace Laboratory (NLR) in the Netherlands, the NASA Ames Research Center in the U.S., and the NASA Langley Research Center in the U.S. Responses of the Dutch and U.S. participants to selected questions are presented in this paper.

NASA/DOD Aerospace Knowledge Diffusion Research Project. Report 45; The Technical Communications Practices of US Aerospace Engineers and Scientists: Results of the Phase 3 US Aerospace Engineering Educators Survey

NASA Technical Reports Server (NTRS)

Pinelli, Thomas E.; Barclay, Rebecca O.; Kennedy, John M.

1996-01-01

The U.S. government technical report is a primary means by which the results of federally funded research and development (R&D) are transferred to the U.S. aerospace industry. However, little is known about this information product in terms of its actual use, importance, and value in the transfer of federally funded R&D. Little is also known about the intermediary-based system that is used to transfer the results of federally funded R&D to the U.S. aerospace industry. To help establish a body of knowledge, the U.S. government technical report is being investigated as part of the NASA/DOD Aerospace Knowledge Diffusion Research Project. In this report, we summarize the literature on technical reports, present a model that depicts the transfer of federally funded aerospace R&D via the U.S. government technical report, and present the results of research that investigated aerospace knowledge diffusion vis-a-vis the technical communication practices of U.S. aerospace engineers and scientists who were members of the American Institute of Aeronautics and Astronautics (AIAA) and identified themselves as educators.