27. VAL, DETAIL OF LAUNCHER SLAB AND LAUNCHER RAIL WITH ...

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

27. VAL, DETAIL OF LAUNCHER SLAB AND LAUNCHER RAIL WITH 7 INCH DIAMETER HOLE FOR SUPPORT CARRIAGE LOCKING PIN. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

4. VAL PARTIAL ELEVATION SHOWING LAUNCHER BRIDGE ON SUPPORTS, LAUNCHER ...

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

4. VAL PARTIAL ELEVATION SHOWING LAUNCHER BRIDGE ON SUPPORTS, LAUNCHER SLAB, SUPPORT CARRIAGE, CONCRETE 'A' FRAME STRUCTURE AND CAMERA TOWER LOOKING SOUTHEAST. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

Dimensions and Measurements of Debuncher Band 1 and 2 Waveguide-Coax Launchers (Final Version)

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

Sun, Ding; /Fermilab

2000-02-15

This note is a document about dimensions and measurement results of waveguide-coax launchers (Band 1 and 2) installed on the arrays in debuncher cooling upgrade. Shown in Figure 1, 5, 8 and 12 are schematic drawings of launchers in the cross section along the longitudinal direction (beam direction) of the arrays. The unit in these drawings is inch. Note: although there are upper band and lower band for pickup arrays, the launchers are the same to avoid possible confusion during installation. RF Measurements were made on all launchers (port) and printed in hard copies for future reference. Since the measurementmore » results are similar to each other, only a few plots for each type of launcher/band are presented in this document. There are two types of measured S11 parameters. One is the measurement made at the end of design/tuning stage using a straight section of band 1 or 2 waveguide terminated with a cone of absorber. I use 'Original' to denote this kind of measurement. As shown in Figure 2, 6, 9 and 13, the original S11 of all launchers are below or around - 20 db over the full band 1 or 2. The other type of measurement is the one made after these launchers were installed onto the array including elbows and several type N feedthrough or connectors. The kicker arrays were terminated with wedges of absorber. During all measurements (pickup array or kicker array) when one launcher was being measured, all other launchers were terminated with 50 ohm terminator. As shown in Figure 3, 4, 7, 10, 11 and 14 these 'final' S11s are around -15 db.« less

Little Joe Model Mercury Project

NASA Image and Video Library

1959-06-26

Publicity photograph of a technician measuring a wind tunnel model of the Little Joe test vehicle. Joseph Shortal noted that (vol. 3, p. 29): The largest project at Wallops in support of Mercury was the Little Joe project, designed to qualify the abort-escape system under flight conditions. James Hansen (p. 47) writes: STG engineers Max Faget and Paul Purser, then of Langley's PARD, had conceived Little Joe as a space capsule test vehicle even before the establishment of NASA and the formation of the STG. Girlruth understood the importance of the Little Joe tests: We had to be sure there were no serious performance and operational problems that we had simply not thought of in such a new and radical type of flight vehicle. -- Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, (Washington: NASA, 1995), p. 47 Joseph A. Shortal, History of Wallops Station: Origins and Activities Through 1949, (Wallops Island, VA: National Aeronautics and Space Administration, Wallops Station, nd), Comment Edition.

Functional characterization of an unusual phytochelatin synthase, LjPCS3, of Lotus japonicus.

PubMed

Ramos, Javier; Naya, Loreto; Gay, Marina; Abián, Joaquín; Becana, Manuel

2008-09-01

In plants and many other organisms, phytochelatin synthase (PCS) catalyzes the synthesis of phytochelatins from glutathione in the presence of certain metals and metalloids. We have used budding yeast (Saccharomyces cerevisiae) as a heterologous system to characterize two PCS proteins, LjPCS1 and LjPCS3, of the model legume Lotus japonicus. Initial experiments revealed that the metal tolerance of yeast cells in vivo depends on the concentrations of divalent cations in the growth medium. Detailed in vivo (intact cells) and in vitro (broken cells) assays of PCS activity were performed with yeast expressing the plant enzymes, and values of phytochelatin production for each metal tested were normalized with respect to those of cadmium to correct for the lower expression level of LjPCS3. Our results showed that lead was the best activator of LjPCS1 in the in vitro assay, whereas, for both assays, arsenic, iron, and aluminum were better activators of LjPCS3 and mercury was similarly active with the two enzymes. Most interestingly, zinc was a powerful activator, especially of LjPCS3, when assayed in vivo, whereas copper and silver were the strongest activators in the in vitro assay. We conclude that the in vivo and in vitro assays are useful and complementary to assess the response of LjPCS1 and LjPCS3 to a wide range of metals and that the differences in the C-terminal domains of the two proteins are responsible for their distinct expression levels or stabilities in heterologous systems and patterns of metal activation.

The anti-tumor effects of the recombinant toxin protein rLj-RGD3 from Lampetra japonica on pancreatic carcinoma Panc-1 cells in nude mice.

PubMed

Wang, Yue; Zheng, Yuanyuan; Tu, Zuoyu; Dai, Yongguo; Xu, Hong; Lv, Li; Wang, Jihong

2017-02-01

Recombinant Lampetra japonica RGD peptide (rLj-RGD3) is a soluble toxin protein with three RGD (Arg-Gly-Asp) motifs and a molecular weight of 13.5kDa. The aim of this study was to investigate the effects and mechanisms of rLj-RGD3 on tumor growth and survival in pancreatic carcinoma Panc-1 cell-bearing mice. A Panc-1 human pancreatic carcinoma-bearing nude mouse model was successfully generated, and the animals were treated with different doses of rLj-RGD3 for 3 weeks. The volume and weight of the subcutaneous tumors, the survival of the nude mice, histopathological changes, the intratumoral MVD, the number of apoptotic Panc-1 cells, and apoptosis-related proteins and gene expressions were determined. rLj-RGD3 significantly decreased the tumor volumes and weights, and the maximum tumor volume and weight IR values were 53.2% (p<0.001) and 55.9% (p<0.001), respectively. The life expectancy of Panc-1-bearing nude mice treated with rLj-RGD3 was increased by 56.3% (p<0.001). Meanwhile, rLj-RGD3 promoted the expression of Bax, caspase-3, and caspase-9 and inhibited Bcl-2 and VEGF expression. In addition, rLj-RGD3 did not change FAK, PI3K and Akt expression, but p-FAK, p-PI3K and p-Akt, levels were down-regulated. These results show that rLj-RGD3 induced potent anti-tumor activity in vivo and suppressed the growth of transplanted Panc-1 cells in a nude mouse model, implying that rLj-RGD3 may serve as a potent clinical therapeutic agent for human pancreatic carcinoma. Copyright © 2016 Elsevier Inc. All rights reserved.

Electromagnetic Launchers and Guns. Phase 1

DTIC Science & Technology

1980-06-01

a high-speed maglev transportation system based on a linear synchronous motor (1,2,3). In 1975 Gerard K. O’Neill of Princeton University...fact that the very important railgun- homopolar launcher technology is already being pursued at Westinghouse and university of Texas, Austin. The...shown in Fig. 14 on the following page. There are three comparable options for energy storage: an engine-driven homopolar generator followed by an

Interactive electromagnetic launcher simulation

NASA Astrophysics Data System (ADS)

Young, F. J.; Howland, H. R.; Hughes, W. F.; Fikse, D. A.

1982-01-01

The mathematical model, usage, and documentation of an interactive computer simulation for an electromagnetic launcher is presented. The launcher is modeled as an electrical circuit. Three slight variations of the program permit studies of a launcher with (1) rail skin effects, (2) rail skin effects and approximated storage coil skin effects, or (3) neither of these effects. Usage of the program as currently implemented on the Westinghouse R&D Univac 1106 is described, with a sample session shown. The implementation of the program permits rapid scoping of the effects of parameter changes.

Estimation of Freshwater Flow to Joe Bay, South Florida.

NASA Astrophysics Data System (ADS)

Zucker, M. A.; Hittle, C. D.

2002-05-01

During the last century, drainage canals were constructed as part of the Central and Southern Flood Control (C&SF) project. Flood control was achieved but degradation to the Everglades ecosystem was evident. Problems related to Florida Bay include sea grass die off, algae blooms, and extreme salinity conditions. Modifications to the C&SF project are proposed as part of the Comprehensive Everglades Restoration Plan (CERP). One objective of CERP is to improve the timing and distribution of freshwater flow within the Everglades ecosystem and to Florida Bay. Several CERP projects propose changes to the existing canal network that borders Everglades National Park (ENP) in southern Miami-Dade County. An examination of flows to Joe Bay, a small embayment on the northeastern shores of Florida Bay, has provided baseline information on current spatial and temporal water deliveries prior to CERP modifications. Understanding the existing complex water delivery system and the effects the system has on Everglades hydrology will provide a necessary benchmark against which to measure restoration success. The study was initiated by the U.S. Geological Survey (USGS) in May 1999 to estimate creek flows to Joe Bay and determine the relative amounts derived from Taylor Slough and overflow from the C-111 Canal. It is important to understand the source of freshwater to Joe Bay before it enters Florida Bay. Taylor Slough transports freshwater to northeastern Florida Bay from the northwest while overflow from the C-111 Canal provides freshwater to northeastern Florida Bay from the northeast. Joe Bay, receives part of the freshwater from each of these sources via sheet flow and small estuarine creeks, and subsequently discharges southward to northeastern Florida Bay via Trout Creek. Trout Creek contributes approximately 50 percent of the total freshwater flow to northeastern Florida Bay (Hittle 2001). Eight non-gaged creeks entering Joe Bay were selected for acoustic Doppler current

The Joe Show on Third Rock Radio

NASA Image and Video Library

2017-12-01

Tune into Third Rock Radio for The Joe Show starring Joe Acaba as Guest DJ on Thursday, December 7th at 5pm ET. Third Rock Radio's Guest DJ series spotlights NASA astronauts aboard the International Space Station, playing music and sharing their experiences. For more information visit: thirdrockradio.rfcmedia.com

76 FR 51412 - Joe C. Fermo, M.D.; Revocation of Registration

Federal Register 2010, 2011, 2012, 2013, 2014

2011-08-18

... DEPARTMENT OF JUSTICE Drug Enforcement Administration Joe C. Fermo, M.D.; Revocation of... Enforcement Administration, issued an Order to Show Cause to Joe C. Fermo, M.D. (Registrant), of Tulsa... Order at 1 (citing 21 U.S.C. 823(f) and 824(a)(4)). The Show Cause Order specifically alleged that on...

Biocontrol agent Bacillus amyloliquefaciens LJ02 induces systemic resistance against cucurbits powdery mildew.

PubMed

Li, Yunlong; Gu, Yilin; Li, Juan; Xu, Mingzhu; Wei, Qing; Wang, Yuanhong

2015-01-01

Powdery mildew is a fungal disease found in a wide range of plants and can significantly reduce crop yields. Bacterial strain LJ02 is a biocontrol agent (BCA) isolated from a greenhouse in Tianjin, China. In combination of morphological, physiological, biochemical and phylogenetic analyses, strain LJ02 was classified as a new member of Bacillus amyloliquefaciens. Greenhouse trials showed that LJ02 fermentation broth (LJ02FB) can effectively diminish the occurrence of cucurbits powdery mildew. When treated with LJ02FB, cucumber seedlings produced significantly elevated production of superoxide dismutase, peroxidase, polyphenol oxidase and phenylalanine ammonia lyase as compared to that of the control. We further confirmed that the production of free salicylic acid (SA) and expression of one pathogenesis-related (PR) gene PR-1 in cucumber leaves were markedly elevated after treating with LJ02FB, suggesting that SA-mediated defense response was stimulated. Moreover, LJ02FB-treated cucumber leaves could secrete resistance-related substances into rhizosphere that inhibit the germination of fungi spores and the growth of pathogens. Finally, we separated bacterium and its fermented substances to test their respective effects and found that both components have SA-inducing activity and bacterium plays major roles. Altogether, we identified a BCA against powdery mildew and its mode of action by inducing systemic resistance such as SA signaling pathway.

New Modular Camera No Ordinary Joe

NASA Technical Reports Server (NTRS)

2003-01-01

Although dubbed 'Little Joe' for its small-format characteristics, a new wavefront sensor camera has proved that it is far from coming up short when paired with high-speed, low-noise applications. SciMeasure Analytical Systems, Inc., a provider of cameras and imaging accessories for use in biomedical research and industrial inspection and quality control, is the eye behind Little Joe's shutter, manufacturing and selling the modular, multi-purpose camera worldwide to advance fields such as astronomy, neurobiology, and cardiology.

33 CFR 175.113 - Launchers.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 33 Navigation and Navigable Waters 2 2014-07-01 2014-07-01 false Launchers. 175.113 Section 175... SAFETY EQUIPMENT REQUIREMENTS Visual Distress Signals § 175.113 Launchers. (a) When a visual distress signal carried to meet the requirements of § 175.110 requires a launcher to activate, then a launcher...

33 CFR 175.113 - Launchers.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 33 Navigation and Navigable Waters 2 2013-07-01 2013-07-01 false Launchers. 175.113 Section 175... SAFETY EQUIPMENT REQUIREMENTS Visual Distress Signals § 175.113 Launchers. (a) When a visual distress signal carried to meet the requirements of § 175.110 requires a launcher to activate, then a launcher...

33 CFR 175.113 - Launchers.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 33 Navigation and Navigable Waters 2 2011-07-01 2011-07-01 false Launchers. 175.113 Section 175... SAFETY EQUIPMENT REQUIREMENTS Visual Distress Signals § 175.113 Launchers. (a) When a visual distress signal carried to meet the requirements of § 175.110 requires a launcher to activate, then a launcher...

33 CFR 175.113 - Launchers.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 33 Navigation and Navigable Waters 2 2012-07-01 2012-07-01 false Launchers. 175.113 Section 175... SAFETY EQUIPMENT REQUIREMENTS Visual Distress Signals § 175.113 Launchers. (a) When a visual distress signal carried to meet the requirements of § 175.110 requires a launcher to activate, then a launcher...

33 CFR 175.113 - Launchers.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 33 Navigation and Navigable Waters 2 2010-07-01 2010-07-01 false Launchers. 175.113 Section 175... SAFETY EQUIPMENT REQUIREMENTS Visual Distress Signals § 175.113 Launchers. (a) When a visual distress signal carried to meet the requirements of § 175.110 requires a launcher to activate, then a launcher...

Historic and Current Launcher Success Rates

NASA Technical Reports Server (NTRS)

Rust, Randy

2002-01-01

This presentation reviews historic and current space launcher success rates from all nations with a mature launcher industry. Data from the 1950's through present day is reviewed for possible trends such as when in the launch timeline a failure occurred, which stages had the highest failure rate, overall launcher reliability, a decade by decade look at launcher reliability, when in a launchers history did failures occur, and the reliability of United States human-rated launchers. This information is useful in determining where launcher reliability can be improved and where additional measures for crew survival (i.e., Crew Escape systems) will have the greatest emphasis

Launch Vehicle Flight Report - Nasa Project Apollo Little Joe 2 Qualification Test Vehicle 12-50-1

NASA Technical Reports Server (NTRS)

1963-01-01

The Little Joe II Qualification Test Vehicle, Model 12-50-1, was launched from Army Launch Area 3 {ALA-3) at White Sands Missile Range, New Mexico, on 28 August 1963. This was the first launch of this class of boosters. The Little Joe II Launch Vehicle was designed as a test vehicle for boosting payloads into flight. For the Apollo Program, its mission is to serve as a launch vehicle for flight testing of the Apollo spacecraft. Accomplishment of this mission requires that the vehicle be capable of boosting the Apollo payload to parameters ranging from high dynamic pressures at low altitude to very high altitude flight. The fixed-fin 12-50 version was designed to accomplish the low-altitude parameter. The 12-51 version incorporates an attitude control system to accomplish the high altitude mission. This launch was designed to demonstrate the Little Joe II capability of meeting the high dynamic pressure parameter for the Apollo Program. For this test, a boiler-plate version of the Apollo capsule, service module and escape tower were attached to the launch vehicle to simulate weight, center of gravity and aerodynamic shape of the Apollo configuration. No attempt was made to separate the payload in flight. The test was conducted in compliance with Project Apollo Flight Mission Directive for QTV-1, NASA-MSC, dated 3 June 1963, under authority of NASA Contract NAS 9-492,

Rocket/launcher structural dynamics

NASA Technical Reports Server (NTRS)

Ferragut, N. J.

1976-01-01

The equations of motion describing the interactions between a rocket and a launcher were derived using Lagrange's Equation. A rocket launching was simulated. The motions of both the rocket and the launcher can be considered in detail. The model contains flexible elements and rigid elements. The rigid elements (masses) were judiciously utilized to simplify the derivation of the equations. The advantages of simultaneous shoe release were illustrated. Also, the loading history of the interstage structure of a boosted configuration was determined. The equations shown in this analysis could be used as a design tool during the modification of old launchers and the design of new launchers.

Air-Powered Projectile Launcher

NASA Technical Reports Server (NTRS)

Andrews, T.; Bjorklund, R. A.; Elliott, D. G.; Jones, L. K.

1987-01-01

Air-powered launcher fires plastic projectiles without using explosive propellants. Does not generate high temperatures. Launcher developed for combat training for U.S. Army. With reservoir pressurized, air launcher ready to fire. When pilot valve opened, sleeve (main valve) moves to rear. Projectile rapidly propelled through barrel, pushed by air from reservoir. Potential applications in seismic measurements, avalanche control, and testing impact resistance of windshields on vehicles.

Long Exposure Photos of Mobile Launcher

NASA Image and Video Library

2017-03-14

A long-exposure view of the mobile launcher at NASA's Kennedy Space Center in Florida. Cranes and rigging are being used to lift the bracket for the Orion Service Module Umbilical (OSMU) up for installation on the mobile launcher tower. The tower will be equipped with a number of lines, called umbilicals, that will connect to the Space Launch System rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The OSMU will be located high on the mobile launcher tower and, prior to launch, will transfer liquid coolant for the electronics and air for the Environmental Control System to the Orion service module that houses these critical systems to support the spacecraft. EM-1 is scheduled to launch in 2018. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

76 FR 63851 - Special Conditions: Learjet Inc., Model LJ-200-1A10 Airplane, Pilot-Compartment View Through...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-10-14

... certificate for a new Model LJ-200-1A10 airplane. This airplane is 68 feet long with a 65-foot wing span and..., without continuous attention on the part of the crew, in conditions from light misting precipitation to...

Non-US electrodynamic launchers research and development

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

Parker, J.V.; Batteh, J.H.; Greig, J.R.

Electrodynamic launcher research and development work of scientists outside the United States is analyzed and assessed by six internationally recognized US experts in the field of electromagnetic and electrothermal launchers. The assessment covers five broad technology areas: (1) Experimental railguns; (2) Railgun theory and design; (3) Induction launchers; (4) Electrothermal guns; (5) Energy storage and power supplies. The overall conclusion is that non-US work on electrodynamic launchers is maturing rapidly after a relatively late start in many countries. No foreign program challenges the US efforts in scope, but it is evident that the United States may be surpassed in somemore » technologies within the next few years. Until recently, published Russian work focused on hypervelocity for research purposes. Within the last two years, large facilities have been described where military-oriented development has been underway since the mid-1980s. Financial support for these large facilities appears to have collapsed, leaving no effective effort to develop practical launchers for military or civilian applications. Electrodynamic launcher research in Europe is making rapid progress by focusing on a single application, tactical launchers for the military. Four major laboratories, in Britain, France, Germany, and the Netherlands, are working on this problem. Though narrower in scope than the US effort, the European work enjoys a continuity of support that has accelerated its progress. The next decade will see the deployment of electrodynamic launcher technology, probably in the form of an electrothermal-chemical upgrade for an existing gun system. The time scale for deployment of electromagnetic launchers is entirely dependent on the level of research-and-development effort. If resources remain limited, the advantage will lie with cooperative efforts that have reasonably stable funding such as the present French-German program.« less

71. Joe Moore, Photographer. September, 1996. BEVATRON ROOF SHIELDING AND ...

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

71. Joe Moore, Photographer. September, 1996. BEVATRON ROOF SHIELDING AND BUILDING TRUSS STRUCTURE - University of California Radiation Laboratory, Bevatron, 1 Cyclotron Road, Berkeley, Alameda County, CA

Genome Integration and Excision by a New Streptomyces Bacteriophage, ϕJoe.

PubMed

Fogg, Paul C M; Haley, Joshua A; Stark, W Marshall; Smith, Margaret C M

2017-03-01

Bacteriophages are the source of many valuable tools for molecular biology and genetic manipulation. In Streptomyces , most DNA cloning vectors are based on serine integrase site-specific DNA recombination systems derived from phage. Because of their efficiency and simplicity, serine integrases are also used for diverse synthetic biology applications. Here, we present the genome of a new Streptomyces phage, ϕJoe, and investigate the conditions for integration and excision of the ϕJoe genome. ϕJoe belongs to the largest Streptomyces phage cluster (R4-like) and encodes a serine integrase. The attB site from Streptomyces venezuelae was used efficiently by an integrating plasmid, pCMF92, constructed using the ϕJoe int-attP locus. The attB site for ϕJoe integrase was occupied in several Streptomyces genomes, including that of S. coelicolor , by a mobile element that varies in gene content and size between host species. Serine integrases require a phage-encoded recombination directionality factor (RDF) to activate the excision reaction. The ϕJoe RDF was identified, and its function was confirmed in vivo Both the integrase and RDF were active in in vitro recombination assays. The ϕJoe site-specific recombination system is likely to be an important addition to the synthetic biology and genome engineering toolbox. IMPORTANCE Streptomyces spp. are prolific producers of secondary metabolites, including many clinically useful antibiotics. Bacteriophage-derived integrases are important tools for genetic engineering, as they enable integration of heterologous DNA into the Streptomyces chromosome with ease and high efficiency. Recently, researchers have been applying phage integrases for a variety of applications in synthetic biology, including rapid assembly of novel combinations of genes, biosensors, and biocomputing. An important requirement for optimal experimental design and predictability when using integrases, however, is the need for multiple enzymes with different

Genome Integration and Excision by a New Streptomyces Bacteriophage, ϕJoe

PubMed Central

Haley, Joshua A.; Stark, W. Marshall

2016-01-01

ABSTRACT Bacteriophages are the source of many valuable tools for molecular biology and genetic manipulation. In Streptomyces, most DNA cloning vectors are based on serine integrase site-specific DNA recombination systems derived from phage. Because of their efficiency and simplicity, serine integrases are also used for diverse synthetic biology applications. Here, we present the genome of a new Streptomyces phage, ϕJoe, and investigate the conditions for integration and excision of the ϕJoe genome. ϕJoe belongs to the largest Streptomyces phage cluster (R4-like) and encodes a serine integrase. The attB site from Streptomyces venezuelae was used efficiently by an integrating plasmid, pCMF92, constructed using the ϕJoe int-attP locus. The attB site for ϕJoe integrase was occupied in several Streptomyces genomes, including that of S. coelicolor, by a mobile element that varies in gene content and size between host species. Serine integrases require a phage-encoded recombination directionality factor (RDF) to activate the excision reaction. The ϕJoe RDF was identified, and its function was confirmed in vivo. Both the integrase and RDF were active in in vitro recombination assays. The ϕJoe site-specific recombination system is likely to be an important addition to the synthetic biology and genome engineering toolbox. IMPORTANCE Streptomyces spp. are prolific producers of secondary metabolites, including many clinically useful antibiotics. Bacteriophage-derived integrases are important tools for genetic engineering, as they enable integration of heterologous DNA into the Streptomyces chromosome with ease and high efficiency. Recently, researchers have been applying phage integrases for a variety of applications in synthetic biology, including rapid assembly of novel combinations of genes, biosensors, and biocomputing. An important requirement for optimal experimental design and predictability when using integrases, however, is the need for multiple enzymes with

VIEW OF HB1 (VAB HIGH BAY) WITH MOBILE LAUNCHER PLATFORM ...

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

VIEW OF HB-1 (VAB HIGH BAY) WITH MOBILE LAUNCHER PLATFORM (VEHICLE ACCESS PLATFORMS ARE VISIBLE IN THE CENTER), FACING WEST - Cape Canaveral Air Force Station, Launch Complex 39, Vehicle Assembly Building, VAB Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

70. Joe Moore, Photographer. September, 1996. BEVATRON HIGH BAY: SOUTH ...

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

70. Joe Moore, Photographer. September, 1996. BEVATRON HIGH BAY: SOUTH SIDE, LOOKING WEST TOWARD 51A - University of California Radiation Laboratory, Bevatron, 1 Cyclotron Road, Berkeley, Alameda County, CA

72. Joe Moore, Photographer. September, 1996. BEVATRON COOLING TOWERS (3 ...

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

72. Joe Moore, Photographer. September, 1996. BEVATRON COOLING TOWERS (3 SHOWN) AND MOTOR GENERATOR ON RIGHT - University of California Radiation Laboratory, Bevatron, 1 Cyclotron Road, Berkeley, Alameda County, CA

Recovery of the Little Joe 5A spacecraft

NASA Image and Video Library

1961-03-18

S61-01398 (18 March 1961) --- View of the recovery of the Little Joe-5A spacecraft which lifted off on March 18, 1961 from Wallops Island. The photo was taken from the recovery helicopter and shows the craft's parachute still attached and floating in the water next to the capsule. Little Joe-5A was a suborbital flight to test the Mercury capsule. The escape rocket motor fired prematurely and prior to capsule release. Photo credit: NASA

73. Joe Moore, Photographer. September, 1996. BEVATRON HIGH BAY: SOUTH ...

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

73. Joe Moore, Photographer. September, 1996. BEVATRON HIGH BAY: SOUTH SIDE, LOOKING EAST TOWARD MAIN CONTROL ROOM - University of California Radiation Laboratory, Bevatron, 1 Cyclotron Road, Berkeley, Alameda County, CA

The DSI small satellite launcher

NASA Technical Reports Server (NTRS)

Nichols, S.; Gibbons, D.; Wise, J.; Nguyen, D.

1992-01-01

A new launcher has been developed by DSI, that is compatible with the GAS canisters. It has the proven capability to deploy a satellite from an orbiting Shuttle that is 18 inches in diameter, 31 inches long, and weighing 190 pounds. These DSI Launchers were used aboard the Discovery (STS-39) in May 1991 as part of the Infrared Background Signature Survey (IBSS) to deploy three small satellites known as Chemical Release Observation (CRO) satellites A, B, and C. Because the satellites contained hazardous liquids (MMH, UDMH, and MON-10) and were launched from GAS Cylinders without motorized doors, the launchers were required to pass NASA Shuttle Payload safety and verification requirements. Some of the more interesting components of the design were the V-band retention and separation mechanism, the separation springs, and the launcher electronics which provided a properly inhibited release sequence operated through the Small Payload Accommodations Switch Panel (SPASP) on board the Orbiter. The original plan for this launcher was to use a motorized door. The launcher electronics, therefore has the capability to be modified to accommodate the door, if desired.

Views of Astronaut (Col.) Joe Engle and son Jon with L-5 Piper Cub

NASA Technical Reports Server (NTRS)

1981-01-01

Views of Astronaut (Col.) Joe Engle and son Jon with L-5 Piper Cub at Clover Airport. Photos includes Jon Engle sitting on side door frame working on portion of wing. Joe Engle is behind him working on a wing strut (34329); Joe Engle works on tightening bolt (34330); Jon Engle works on portion of wing which connects to the cockpit. Joe Engle works on connecting strut to wing (34331).

Chartering Launchers for Small Satellites

NASA Astrophysics Data System (ADS)

Hernandez, Daniel

The question of how to launch small satellites has been solved over the years by the larger launchers offering small satellites the possibility of piggy-backing. Specific fixtures have been developed and commercialized: Arianespace developed the ASAP interface, the USAF studied ESPA, NASA has promoted Shuttle launch possibilities, Russian authorities and companies have been able to find solutions with many different launchers... It is fair to say that most launcher suppliers have worked hard and finally often been able to find solutions to launch most small satellites into orbit. It is also true, however, that most of these small satellites were technology demonstration missions capable of accepting a wide range of orbit and launch characteristics: orbit altitude and inclination, launch date, etc. In some cases the small satellite missions required a well-defined type of orbit and have therefore been obliged to hire a small launcher on which they were the prime passenger. In our paper we would like to propose an additional solution to all these possibilities: launchers could plan well in advance (for example about 3 years), trips to precisely defined orbits to allow potential passengers to organize themselves and be ready on the D-Day. On the scheduled date the chartered launcher goes to the stated orbit while on another date, another chartered launcher goes to another orbit. The idea is to organize departures for space like trains or airplanes leaving on known schedules for known destinations.

LITTLE JOE II - LIFTOFF - WHITE SANDS MISSILE RANGE (WSMR), NM

NASA Image and Video Library

1963-08-28

S63-15701 (28 August 1963) --- All seven motors of Little Joe II, ignited simultaneously at launch, with a total thrust of about 310,000 pounds. A maximum height of 24,000 feet was attained as Little Joe II traveled 47,000 feet north on the White Sands Test Range.

67. Joe Moore, Photographer. September, 1996. BEVATRON EXPERIMENTAL HALL (51B), ...

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

67. Joe Moore, Photographer. September, 1996. BEVATRON EXPERIMENTAL HALL (51B), LOOKING SOUTH EAST - University of California Radiation Laboratory, Bevatron, 1 Cyclotron Road, Berkeley, Alameda County, CA

Speaking Personally--With Joe Freidhoff

ERIC Educational Resources Information Center

Clark, Tom

2013-01-01

This article presents an interview with Joe Freidhoff, the director of online learning research and innovation at the "Michigan Virtual University"[R] ("MVU"[R]), a nonprofit corporation in Michigan. He publishes and presents frequently in the area of K-12 online and blended learning research. Dr. Freidhoff completed his…

View of VAB from Mobile Launcher

NASA Image and Video Library

2017-03-13

A view of the north side of the Vehicle Assembly Building (VAB) from the top of the mobile launcher tower at NASA's Kennedy Space Center in Florida. Inside the VAB, 10 levels of platforms, 20 platform halves altogether, have been installed in High Bay 3. The platforms will surround NASA's Space Launch System (SLS) rocket and the Orion spacecraft and allow access during processing for missions, including the first uncrewed flight test of Orion atop the SLS rocket in 2018. Crawler-transporter 2 will carry the rocket and spacecraft atop the mobile launcher to Launch Pad 39B for Exploration Mission 1. The Ground Systems Development and Operations Program, with support from the center's Engineering Directorate, is overseeing upgrades and modifications to the VAB and the mobile launcher.

A Dicarboxylate Transporter, LjALMT4, Mainly Expressed in Nodules of Lotus japonicus.

PubMed

Takanashi, Kojiro; Sasaki, Takayuki; Kan, Tomohiro; Saida, Yuka; Sugiyama, Akifumi; Yamamoto, Yoko; Yazaki, Kazufumi

2016-07-01

Legume plants can establish symbiosis with soil bacteria called rhizobia to obtain nitrogen as a nutrient directly from atmospheric N2 via symbiotic nitrogen fixation. Legumes and rhizobia form nodules, symbiotic organs in which fixed-nitrogen and photosynthetic products are exchanged between rhizobia and plant cells. The photosynthetic products supplied to rhizobia are thought to be dicarboxylates but little is known about the movement of dicarboxylates in the nodules. In terms of dicarboxylate transporters, an aluminum-activated malate transporter (ALMT) family is a strong candidate responsible for the membrane transport of carboxylates in nodules. Among the seven ALMT genes in the Lotus japonicus genome, only one, LjALMT4, shows a high expression in the nodules. LjALMT4 showed transport activity in a Xenopus oocyte system, with LjALMT4 mediating the efflux of dicarboxylates including malate, succinate, and fumarate, but not tricarboxylates such as citrate. LjALMT4 also mediated the influx of several inorganic anions. Organ-specific gene expression analysis showed LjALMT4 mRNA mainly in the parenchyma cells of nodule vascular bundles. These results suggest that LjALMT4 may not be involved in the direct supply of dicarboxylates to rhizobia in infected cells but is responsible for supplying malate as well as several anions necessary for symbiotic nitrogen fixation, via nodule vasculatures.

68. Joe Moore, Photographer. September, 1996. B51 SHOWING HIGH BAY ...

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

68. Joe Moore, Photographer. September, 1996. B51 SHOWING HIGH BAY DOOR (C) and B51L IN FOREGROUND - University of California Radiation Laboratory, Bevatron, 1 Cyclotron Road, Berkeley, Alameda County, CA

Interview with Joe F. Head

ERIC Educational Resources Information Center

West, Kim

2008-01-01

This article presents an interview with Joe F. Head, Dean of University Admissions and Enrollment Services at Kennesaw State University (KSU) in Georgia, who has more than 35 years of experience in admissions and enrollment services. After completing an M.Ed. in higher education at Georgia Southern University, Head immediately landed a position as…

NPS CubeSat Launcher Program Management

DTIC Science & Technology

2009-09-01

NAVAL POSTGRADUATE SCHOOL MONTEREY, CALIFORNIA THESIS Approved for public release; distribution is unlimited NPS CUBESAT LAUNCHER ...CubeSat Launcher Program Management 6. AUTHOR(S) Christina M. Hicks 5. FUNDING NUMBERS 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES...article in support of the NPS CubeSat Launcher (NPSCuL) project. This thesis will describe the process, experience, and results of managing the NPSCuL

The ESA activities on future launchers

NASA Technical Reports Server (NTRS)

Pfeffer, H.

1984-01-01

A future launcher development scenario depends on many assumptions, such as the impetus provided by the probability of future missions, and the political willingness of member states to undertake future developments. Because of the long timescale implied by a coherent launcher development, a step-wise approach within an overall future launcher development plan appears essential. The definition of development steps allows the launcher developments to be adapted to the driving external forces, so that no possible opportunity to Europe in the space launch business is missed out because of improper planning on the absence of a long term goal. The launcher senario, to be presented in 1985, forms part of Europe's overall STS plan for the future. This overall STS plan is one product of the complete STS LTPP, a first draft of which should exist by 1985, and which will be updated regularly to take into account the changing political and economic perspectives.

Mobile Launcher

NASA Image and Video Library

2017-05-30

A view of the mobile launcher (ML) taken from the "eyebrow" of the nearby Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. The ML tower will be equipped with a number of lines, called umbilicals that will connect to the Space Launch System rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The Orion Service Module Umbilical and Core State Forward Skirt Umbilical were recently installed on the ML. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

An electomagnetic lunar launcher utilizing superconductivity technology

NASA Technical Reports Server (NTRS)

Bilby, Curt; Nozette, Stewart; Kolm, Henry

1989-01-01

The application of superconductivity technology to the lunar launcher problem was considered, and a quenchgun concept was formulated to reduce the mass of the launcher system by incorporating the energy storage in the launcher itself and using the efficiency of the quenchgun to reduce the power requirements. A conceptual design for the quenchgun launcher is presented, and the integration of the system into a lunar base logistics model for evaluation is addressed. The results of these evaluations under the NASA Office of Exploration lunar base scenarios are reported.

Feasibility study of superconducting LSM rocket launcher system

NASA Technical Reports Server (NTRS)

Yoshida, Kinjiro; Ohashi, Takaaki; Shiraishi, Katsuto; Takami, Hiroshi

1994-01-01

A feasibility study is presented concerning an application of a superconducting linear synchronous motor (LSM) to a large-scale rocket launcher, whose acceleration guide tube of LSM armature windings is constructed 1,500 meters under the ground. The rocket is released from the linear launcher just after it gets to a peak speed of about 900 kilometers per hour, and it flies out of the guide tube to obtain the speed of 700 kilometers per hour at the height of 100 meters above ground. The linear launcher is brought to a stop at the ground surface for a very short time of 5 seconds by a quick control of deceleration. Very large current variations in the single-layer windings of the LSM armature, which are produced at the higher speed region of 600 to 900 kilometers per hour, are controlled successfully by adopting the double-layer windings. The proposed control method makes the rocket launcher ascend stably in the superconducting LSM system, controlling the Coriolis force.

LITTLE JOE 2 - LAUNCH VEHICLES - VA

NASA Image and Video Library

1961-04-13

G61-00030 (4 Nov. 1959) --- Launch of Little Joe-2 from Wallops Island carrying Mercury spacecraft test article. The suborbital test flight of the Mercury capsule was to test the escape system. Vehicle functioned perfectly, but escape rocket ignited several seconds too late. Photo credit: NASA

Rebecca Knuth: LJ Teaching Award 2009

ERIC Educational Resources Information Center

Berry, John N., III

2009-01-01

This article profiles Rebecca Knuth, winner of the LJ Teaching Award for 2009. The way she plans a class she's teaching illustrates why she was nominated by her students and won the award. The award, which comes with a $5000 honorarium and a celebration at the American Library Association (ALA) Midwinter Meeting, is sponsored by ProQuest. For…

Joseph (Joe) A. Walker

NASA Technical Reports Server (NTRS)

1956-01-01

In March 1945 Joseph A. Walker joined the National Advisory Committee for Aeronautics' Aircraft Engine Research Laboratory, Cleveland, Ohio, (later NASA's Lewis Research Center, now the Glenn Research Center) as a physicist. He transferred to the NACA High-Speed Flight Research Station, Edwards, California in 1951, as a research pilot. For the next fifteen years Walker served as a pilot at the Edwards flight research facility (today known as NASA's Dryden Flight Research Center) on such projects as the Bell X-1#2 (2 flights, first on August 27, 1951), Bell X-1A (1 flight on July 20, 1955), X-1E (21 flights, first on December 12, 1955), Douglas D-558-I #3 Skystreak (14 flights, first on June 29, 1951), Douglas D-558-II #2 Skyrocket (3 flights, first on April 29, 1955), Douglas D-558-II #3 Skyrocket (2 flights, first on May 7, 1954). On the Douglas X-3, Joe was project pilot and made all 20 flights, the first on August 1, 1954. Joe considered this aircraft the 'worst' plane he ever flew. He flew the Northrup X-4 (2 flights, first on October 18, 1951), Bell X-5 (78 flights, first on January 9, 1952). He also flew programs involving the F-100, F-101, F-102, F-104 and the B-47. Walker made the first NASA flight on the North American X-15 on March 25, 1960. His 25th and final X-15 flight on August 22, 1963, reached 354,200 feet, an unofficial record altitude of almost 67 miles. On October 30, 1964, Walker took the first Bell Lunar Landing Research Vehicle (LLRV) on its maiden flight, reaching a peak altitude of 10 feet and a free flight time of just under one minute. Two LLRV's and three Lunar Landing Training Vehicles developed from them were used to develop piloting and operational techniques for lunar landings. In November, he left the program after 35 flights on the first LLRV. Walker flew chase flights as well as research flights. On June 8, 1966 he was flying chase in NASA's F-104N for the Air Force's experimental bomber, North American XB-70A, when he was fatally

Mercury Project

NASA Image and Video Library

1960-01-21

The Little Joe launch vehicle for the LJ1 mission on the launch pad at the wallops Flight Facility, Wallops Island, Virginia, on January 21, 1960. This mission achieved the suborbital Mercury cupsule test, testing of the escape system, and biomedical tests by using a monkey, named Miss Sam.

Superconducting Magnetic Projectile Launcher

NASA Technical Reports Server (NTRS)

Jan, Darrell L.; Lawson, Daniel D.

1991-01-01

Proposed projectile launcher exploits Meissner effect to transfer much of kinetic energy of relatively massive superconducting plunger to smaller projectile, accelerating projectile to high speed. Because it operates with magnetic fields, launcher not limited by gas-expansion thermodynamics. Plunger energized mechanically and/or chemically, avoiding need for large electrical power supplies and energy-storage systems. Potential applications include launching of projectiles for military purposes and for scientific and industrial tests of hypervelocity impacts.

21. VAL, DETAIL OF MUZZLE END OF LAUNCHER BRIDGE SHOWING ...

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

21. VAL, DETAIL OF MUZZLE END OF LAUNCHER BRIDGE SHOWING BOTH LAUNCHER TUBES TAKEN FROM RESERVOIR LOOKING NORTH. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

32. VAL, DETAIL SHOWING LOADING PLATFORM, PROJECTILE LOADING CAR, LAUNCHER ...

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

32. VAL, DETAIL SHOWING LOADING PLATFORM, PROJECTILE LOADING CAR, LAUNCHER SLAB AND UNDERSIDE OF LAUNCHER BRIDGE LOOKING SOUTHWEST. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

ICPSU Install onto Mobile Launcher

NASA Image and Video Library

2018-03-16

A heavy-lift crane slowly lifts the Interim Cryogenic Propulsion Stage Umbilical (ICPSU) high up for installation on the tower of the mobile launcher (ML) at NASA's Kennedy Space Center in Florida. The last of the large umbilicals to be installed, the ICPSU will provide super-cooled hydrogen and liquid oxygen to the Space Launch System (SLS) rocket's interim cryogenic propulsion stage, or upper stage, at T-0 for Exploration Mission-1. The umbilical is located at about the 240-foot-level of the mobile launcher and will supply fuel, oxidizer, gaseous helium, hazardous gas leak detection, electrical commodities and environment control systems to the upper stage of the SLS rocket during launch. Exploration Ground Systems is overseeing installation of the umbilicals on the ML.

ICPSU Install onto Mobile Launcher

NASA Image and Video Library

2018-03-16

A crane and rigging lines are used to install the Interim Cryogenic Propulsion Stage Umbilical (ICPSU) high up on the mobile launcher (ML) at NASA's Kennedy Space Center in Florida. The last of the large umbilicals to be installed, the ICPSU will provide super-cooled hydrogen and liquid oxygen to the Space Launch System (SLS) rocket's interim cryogenic propulsion stage, or upper stage, at T-0 for Exploration Mission-1. The umbilical is located at about the 240-foot-level of the mobile launcher and will supply fuel, oxidizer, gaseous helium, hazardous gas leak detection, electrical commodities and environment control systems to the upper stage of the SLS rocket during launch. Exploration Ground Systems is overseeing installation of the umbilicals on the ML.

ICPSU Install onto Mobile Launcher

NASA Image and Video Library

2018-03-16

Construction workers with JP Donovan install the Interim Cryogenic Propulsion Stage Umbilical (ICPSU) at about the 240-foot-level of the mobile launcher (ML) tower at NASA's Kennedy Space Center in Florida. The last of the large umbilicals to be installed, the ICPSU will provide super-cooled hydrogen and liquid oxygen to the Space Launch System (SLS) rocket's interim cryogenic propulsion stage, or upper stage, at T-0 for Exploration Mission-1. The umbilical is located at about the 240-foot-level of the mobile launcher and will supply fuel, oxidizer, gaseous helium, hazardous gas leak detection, electrical commodities and environment control systems to the upper stage of the SLS rocket during launch. Exploration Ground Systems is overseeing installation of the umbilicals on the ML.

ICPSU Install onto Mobile Launcher

NASA Image and Video Library

2018-03-16

A heavy-lift crane slowly lifts the Interim Cryogenic Propulsion Stage Umbilical (ICPSU) up for installation on the tower of the mobile launcher (ML) at NASA's Kennedy Space Center in Florida. The last of the large umbilicals to be installed, the ICPSU will provide super-cooled hydrogen and liquid oxygen to the Space Launch System (SLS) rocket's interim cryogenic propulsion stage, or upper stage, at T-0 for Exploration Mission-1. The umbilical is located at about the 240-foot-level of the mobile launcher and will supply fuel, oxidizer, gaseous helium, hazardous gas leak detection, electrical commodities and environment control systems to the upper stage of the SLS rocket during launch. Exploration Ground Systems is overseeing installation of the umbilicals on the ML.

Crew Access Arm arrival at Mobile Launcher

NASA Image and Video Library

2017-11-09

A heavy-load transport truck carrying the Orion crew access arm arrives at the mobile launcher (ML) at NASA's Kennedy Space Center in Florida. The crew access arm will be installed at about the 274-foot level on the mobile launcher tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower to prepare for Exploration Mission-1.

Generic Software Architecture for Launchers

NASA Astrophysics Data System (ADS)

Carre, Emilien; Gast, Philippe; Hiron, Emmanuel; Leblanc, Alain; Lesens, David; Mescam, Emmanuelle; Moro, Pierre

2015-09-01

The definition and reuse of generic software architecture for launchers is not so usual for several reasons: the number of European launcher families is very small (Ariane 5 and Vega for these last decades); the real time constraints (reactivity and determinism needs) are very hard; low levels of versatility are required (implying often an ad hoc development of the launcher mission). In comparison, satellites are often built on a generic platform made up of reusable hardware building blocks (processors, star-trackers, gyroscopes, etc.) and reusable software building blocks (middleware, TM/TC, On Board Control Procedure, etc.). If some of these reasons are still valid (e.g. the limited number of development), the increase of the available CPU power makes today an approach based on a generic time triggered middleware (ensuring the full determinism of the system) and a centralised mission and vehicle management (offering more flexibility in the design and facilitating the long term maintenance) achievable. This paper presents an example of generic software architecture which could be envisaged for future launchers, based on the previously described principles and supported by model driven engineering and automatic code generation.

30. VAL LOOKING DOWN THE LAUNCHER SLAB STAIRS AT THE ...

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

30. VAL LOOKING DOWN THE LAUNCHER SLAB STAIRS AT THE PROJECTILE LOADING CAR AND LOADING PLATFORM ADJACENT TO THE PROJECTILE LOADING DECK AND LAUNCHER BRIDGE. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

Mercury Project

NASA Image and Video Library

1960-01-21

The launch of the Little Joe booster for the LJ1B mission on the launch pad from the wallops Flight Facility, Wallops Island, Virginia, on January 21, 1960. This mission achieved the suborbital Mercury capsule test, testing of the escape system, and biomedical tests by using a monkey, named Miss Sam.

Arcas Rocket with Special Tubular Launcher

NASA Image and Video Library

1959-07-31

Arcas Rocket with Special Tubular Launcher: Lt. Commander W. Houston checks elevation adjustment of special tubular launcher for Arcas rocket, July 31, 1959. Photograph published in A New Dimension Wallops Island Flight Test Range: The First Fifteen Years by Joseph Shortal. A NASA publication. Page 697.

New developments in the field of launchers

NASA Astrophysics Data System (ADS)

Koelle, H. H.; Arend, H.

The current status of launch-system technology is discussed in a global survey. Topics addressed include the factors influencing launcher cost effectiveness; the capabilities of state-of-the-art Soviet, U.S., European, Chinese, and Japanese systems; possible improvements to the current launchers; alternative technologies (the ESA Hermes shuttle, SSTO vehicles, etc.); and future trends in the commercial launch market. Particular attention is given to the Neptun two-stage reusable ballistic launcher proposed by Apel et al. (1985). It is suggested that it may be possible to lower specific transport costs to about $500/kg, or even to $100/kg if the lifetime cargo capacity of reusable launchers can be extended to the order of 2 Tg. Extensive diagrams, drawings, and tables of numerical data are provided.

LJ Teaching Award 2007: Rick J. Block

ERIC Educational Resources Information Center

Berry, John N., III

2008-01-01

This article profiles Rick J. Block, the recipient of the 2008 "LJ Teaching Award." Despite his "day job" and a heavy schedule of classroom teaching, Block finds time and intense energy to be the mentor, internship supervisor, and individual advisor to the students who fill every available seat in his classes at two LIS…

Resent Status of ITER Equatorial Launcher Development

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

Takahashi, K.; Kajiwara, K.; Kasugai, A.

2009-11-26

The ITER equatorial launcher is divided into a front shield and a port plug. The front shield is composed of fourteen blanket shield modules so as to form three openings for the injection of mm-wave beams into plasma. Twenty-four waveguide transmission lines, internal shields, cooling pipes and so on are installed in the port plug. The transmission lines consist of the corrugated waveguides, miter bends and the free space propagation region utilizing two mirrors in front of the waveguide outlet. The analysis of mm-wave beam propagation in the region shows that the transmission efficiency more than 99.5% is attained. Themore » high power experiments of the launcher mock-up have been carried out and the measured field patterns at each mirror and the outlet of the launcher are agreed with the calculations. It is concluded that the transmission line components in the launcher mock-up are fabricated as designed and the present mm-wave design in the launcher is feasible.« less

Impurity Radiation From The LHCD Launcher During Operation In JET And Investigation Of Launcher Damage

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

Kirov, K.K.; Mailloux, J.; Ekedahl, A.

2005-09-26

In this study, the most likely causes of the enhanced radiation in front of the LHCD launcher are investigated: fast ions from the warm plasma, fast electrons parasitically accelerated in front of the grill and arcs. Evidence for the presence of each of these mechanisms is discussed. The experimental conditions favouring the appearance of these phenomena and their impact on the launcher have also been highlighted.

3. AERIAL VIEW OF MOBILE LAUNCHER. ON TOP OF LUT ...

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

3. AERIAL VIEW OF MOBILE LAUNCHER. ON TOP OF LUT SITS A 25 TON HAMMERHEAD CRANE. STRUCTURE ON LEFT SIDE OF LAUNCH PLATFORM IS KNOWN AS A 'MILK STOOL' AND ALLOWS A SATURN 1B ROCKET TO BE USED IN PLACE OF THE SATURN V ROCKET. - Mobile Launcher One, Kennedy Space Center, Titusville, Brevard County, FL

Small launchers (current and future projects in the world)

NASA Astrophysics Data System (ADS)

Naumann, W. G.

1993-01-01

Small satellites need launching services using small launchers capable of injecting 100 to 1000 kg into a polar orbit at an altitude of 1000 km. Operational small launchers are reviewed as well as developing and planned ones. Launcher characteristics, constraints, performance, and status are detailed. Few technical problems are encountered, as most launcher projects call for existing components and well known technologies. Most of the difficulties have come from launch site availability and from financial considerations.

Space transportation propulsion USSR launcher technology, 1990

NASA Technical Reports Server (NTRS)

1991-01-01

Space transportation propulsion U.S.S.R. launcher technology is discussed. The following subject areas are covered: Energia background (launch vehicle summary, Soviet launcher family) and Energia propulsion characteristics (booster propulsion, core propulsion, and growth capability).

Explosively driven hypervelocity launcher: Second-stage augmentation techniques

NASA Technical Reports Server (NTRS)

Baum, D. W.

1973-01-01

The results are described of a continuing study aimed at developing a two-stage explosively driven hypervelocity launcher capable of achieving projectile velocities between 15 and 20 km/sec. The testing and evaluation of a new cylindrical impact technique for collapsing the barrel of two-stage launcher are reported. Previous two-stage launchers have been limited in ultimate performance by incomplete barrel collapse behind the projectile. The cylindrical impact technique explosively collapses a steel tube concentric with and surrounding the barrel of the launcher. The impact of the tube on the barrel produces extremely high stresses which cause the barrel to collapse. The collapse rate can be adjusted by appropriate variation of the explosive charge and tubing parameters. Launcher experiments demonstrated that the technique did achieve complete barrel collapse and form a second-stage piston. However, jetting occurred in the barrel collapse process and was responsible for severe projectile damage.

Dimensions and Measurements of Debuncher Band 3 and 4 Waveguide-Coax Launchers

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

Sun, Ding; /Fermilab

2000-09-13

This note is a document about dimensions and measurement results of waveguide-coax launchers (Band 3 and 4) installed on the arrays in debuncher cooling upgrade. Shown in Figure 1 and 5 are schematic drawings of launchers (pick-up) in the cross section along the longitudinal direction (beam direction) of the arrays. The unit in these drawings is inch. Note: although there are upper band and lower band for pickup arrays, the launchers are the same to avoid possible confusion during installation. Launchers for band 3 and 4 kickers were made by Penn-engineering Inc., therefor no schematic drawings are presented in thismore » note. RF Measurements were made on all launchers (port) and printed in hard copies for future reference. Since the measurement results are similar to each other, only a few plots for each type of launcher/band are presented in this document. There are two types of measured S11 parameters. One is the measurement made at the end of design/tuning stage using a launcher and a straight section of band 3 or 4 waveguide terminated with a cone of absorber. I use 'Original' to denote this kind of measurement. As shown in Figure 2, 6, 9 and 12, the original S11 of all launchers are below or around -20 db over the full band 3 or 4. The other type of measurement is the one made after these launchers were installed onto the array including several type N feedthrough or connectors, elbows, waveguide bends (kicker) and magic Ts (kicker) etc. The kicker arrays were terminated with wedges of absorber. During all measurements (pickup array or kicker array) when one launcher was being measured, all other launchers were terminated with 50 ohm terminator. As shown in Figure 3, 4, 7, 8, 10, 11, 13 and 14 these 'final' S11s are around -15 db.« less

The microspace launcher: first step to the fully air-breathing space launcher

NASA Astrophysics Data System (ADS)

Falempin, F.; Bouchez, M.; Calabro, M.

2009-09-01

A possible application for the high-speed air-breathing propulsion is the fully or partially reusable space launcher. Indeed, by combining the high-speed air-breathing propulsion with a conventional rocket engine (combined cycle or combined propulsion system), it should be possible to improve the average installed specific impulse along the ascent trajectory and then make possible more performing launchers and, hopefully, a fully reusable one. During the last 15 years, a lot of system studies have been performed in France on that subject within the framework of different and consecutive programs. Nevertheless, these studies never clearly demonstrated that a space launcher could take advantage of using a combined propulsion system. During last years, the interest to air-breathing propulsion for space application has been revisited. During this review and taking into account technologies development activities already in progress in Europe, clear priorities have been identified regarding a minimum complementary research and technology program addressing specific needs of space launcher application. It was also clearly identified that there is the need to restart system studies taking advantage of recent progress made regarding knowledge, tools, and technology and focusing on more innovative airframe/propulsion system concepts enabling better trade-off between structural efficiency and propulsion system performance. In that field, a fully axisymmetric configuration has been considered for a microspace launcher (10 kg payload). The vehicle is based on a main stage powered by air-breathing propulsion, combined or not with liquid rocket mode. A "kick stage," powered by a solid rocket engine provides the final acceleration. A preliminary design has been performed for different variants: one using a separated booster and a purely air-breathing main stage, a second one using a booster and a main stage combining air-breathing and rocket mode, a third one without separated

ICPSU Install onto Mobile Launcher

NASA Image and Video Library

2018-03-16

The mobile launcher (ML) is reflected in the sunglasses of a construction worker with JP Donovan at NASA's Kennedy Space Center in Florida. A crane is lifting the Interim Cryogenic Propulsion Stage Umbilical (ICPSU) up for installation on the tower of the ML. The last of the large umbilicals to be installed, the ICPSU will provide super-cooled hydrogen and liquid oxygen to the Space Launch System (SLS) rocket's interim cryogenic propulsion stage, or upper stage, at T-0 for Exploration Mission-1. The umbilical is located at about the 240-foot-level of the mobile launcher and will supply fuel, oxidizer, gaseous helium, hazardous gas leak detection, electrical commodities and environment control systems to the upper stage of the SLS rocket during launch. Exploration Ground Systems is overseeing installation of the umbilicals on the ML.

A general theory of DC electromagnetic launchers

NASA Astrophysics Data System (ADS)

Engel, Thomas G.; Timpson, Erik J.

2015-08-01

The non-linear, transient operation of DC electromagnetic launchers (EMLs) complicates their theoretical understanding and prevents scaling studies and performance comparisons without the aid of detailed numerical models. This paper presents a general theory for DC electromagnetic launchers that has simplified these tasks by identifying critical EML parameters and relationships affecting the EML's voltage, current, and power scaling, as well as its performance and energy conversion efficiency. EML parameters and relationships discussed in this paper include the specific force, the operating mode, the launcher constant, the launcher characteristic velocity, the contact characteristic velocity, the energy conversion efficiency, and the kinetic power and voltage-current scaling relationship. The concepts of the ideal EML, same-scale comparisons, and EML impedance are discussed. This paper defines conditions needed for the EML to operate in the steady-state. A comparison of the general theory with experimental results of several different types of DC (i.e., non-induction) electromagnetic launchers ranging from medium velocity (100's m/s) to high velocity (1000's m/s) is performed. There is good agreement between the general theory and the experimental results.

13. 22'X34' original vellum, VariableAngle Launcher, 'SIDEVIEW CAMERA CAR TRACK ...

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

13. 22'X34' original vellum, Variable-Angle Launcher, 'SIDEVIEW CAMERA CAR TRACK DETAILS' drawn at 1/4'=1'-0' (BUORD Sketch # 208078, PAPW 908). - Variable Angle Launcher Complex, Camera Car & Track, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

10. 22'X34' original blueprint, VariableAngle Launcher, 'SIDE VIEW CAMERA CARSTEEL ...

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

10. 22'X34' original blueprint, Variable-Angle Launcher, 'SIDE VIEW CAMERA CAR-STEEL FRAME AND AXLES' drawn at 1/2'=1'-0'. (BOURD Sketch # 209124). - Variable Angle Launcher Complex, Camera Car & Track, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

18. VAL, DETAIL OF LAUNCHER BRIDGE ALONG THE SIDE OF ...

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

18. VAL, DETAIL OF LAUNCHER BRIDGE ALONG THE SIDE OF THE 32' DIAMETER LAUNCHING TUBE LOOKING SOUTHWEST. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

Joe L. Kincheloe: Embracing Criticality in Science Education

ERIC Educational Resources Information Center

Bayne, Gillian U.

2009-01-01

This article reviews significant contributions made by Joe L. Kincheloe to critical research in science education, especially through a multimethodological, multitheoretical, and multidisciplinary informed lens that incorporates social, cultural, political, economic, and cognitive dynamics--the bricolage. Kincheloe's ideas provide for a compelling…

Launch Pad Activities

NASA Image and Video Library

1959-09-08

Big Joe Capsule Launch Pad Activities: This film covers both the Big Joe and a Little Joe Project Mercury flight test with a research and development version of the Mercury capsule. Big Joe was an Atlas missile that successfully launched a boilerplate model of the Mercury capsule on September 9, 1959. The lower half of the capsule was created at NASA Lewis. The scenes include coverage of the assembly and erection of the boosters, delivery of the capsules, mating of the capsules to the boosters, prelaunch views of the capsule and boosters on launchers, mission control, the launches, and recovery.

79. VIEW OF VAL FIRING RANGE LOOKING SOUTHWEST SHOWING LAUNCHER ...

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

79. VIEW OF VAL FIRING RANGE LOOKING SOUTHWEST SHOWING LAUNCHER BRIDGE, BARGES, SONAR BUOY RANGE AND MORRIS DAM IN BACKGROUND, June 10, 1948. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

6. MOBILE LAUNCHER SIDE 4, SHOWING MILK STOOL AND LUT. ...

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

6. MOBILE LAUNCHER SIDE 4, SHOWING MILK STOOL AND LUT. PROTRUSION ON UPPER RIGHT HAND SIDE OF LUT IS SWING ARM NINE WHICH PROVIDED ACCESS TO CAPSULE OF LAUNCH VEHICLE WHILE ON LAUNCHER. - Mobile Launcher One, Kennedy Space Center, Titusville, Brevard County, FL

Joe L. Kincheloe: Genies and Wishes--A Review of "Key Works in Critical Pedagogy"

ERIC Educational Resources Information Center

Ali-Khan, Carolyne; Siry, Christina

2012-01-01

We review "Key Works in Critical Pedagogy: Joe L. Kincheloe" edited by Kecia Hayes, Shirley R. Steinberg and Kenneth Tobin, which gathers the seminal works of Joe. L. Kincheloe and pairs them with contemporary scholars who respond to and push forward Kincheloe's work. The chapters of "Key Works in Critical Pedagogy" are arranged to begin with…

Multirail electromagnetic launcher powered from a pulsed magnetohydrodynamic generator

NASA Astrophysics Data System (ADS)

Afonin, A. G.; Butov, V. G.; Panchenko, V. P.; Sinyaev, S. V.; Solonenko, V. A.; Shvetsov, G. A.; Yakushev, A. A.

2015-09-01

The operation of an electromagnetic multirail launcher of solids powered from a pulsed magnetohydrodynamic (MHD) generator is studied. The plasma flow in the channel of the pulsed MHD generator and the possibility of launching solids in a rapid-fire mode of launcher operation are considered. It is shown that this mode of launcher operation can be implemented by matching the plasma flow dynamics in the channel of the pulsed MHD generator and the launching conditions. It is also shown that powerful pulsed MHD generators can be used as a source of electrical energy for rapid-fire electromagnetic rail launchers operating in a burst mode.

Nondestructive inspection of a composite missile launcher

NASA Astrophysics Data System (ADS)

Ley, O.; Chung, S.; Butera, M.; Valatka, T.; Triplett, M. H.; Godinez, V.

2012-05-01

Lighter weight alternatives are being sought to replace metallic components currently used in high performance aviation and missile systems. Benefits of lightweight, high strength carbon fiber reinforced composites in missile launchers and rocket motor cases include improved fuel economy, increased flight times, enhanced lethality and/or increased velocity. In this work, various nondestructive inspection techniques are investigated for the damage assessment of a composite missile launcher system for use in U.S. Army attack helicopters. The launcher system, which includes rails and a hardback, can be subject to impact damage from accidental tool drops, routine operation, and/or ballistic threats. The composite hardback and the launch rails both have complex geometries that can challenge the inspection process. Scanning techniques such as line scanning thermography, ultrasonic, and acousto-ultrasonics will be used and compared to determine damage detection accuracy, reliability, and efficiency. Results will also be compared with visual observations to determine if there is a correlation. The goal is to establish an inspection method that quickly and accurately assesses damage extent in order to minimize service time and return the missile system back into the field [1].

Traveling-wave induction launchers

NASA Technical Reports Server (NTRS)

Elliott, David G.

1989-01-01

An analysis of traveling-wave induction launchers shows that induction is a feasible method of producing armature current and that efficient accelerators can be built without sliding contacts or arcs. In a traveling-wave induction launcher the armature current is induced by a slip speed between the armature and a traveling magnetic field. At 9 m/s slip speed a 9 kg projectile with an aluminum armature weighing 25 percent of the total mass can be accelerated to 3000 m/s in a 5 m-long barrel with a total ohmic loss in the barrel coils and armature of 4 percent of the launch kinetic energy and with an average armature temperature rise of 220 deg C, but a peak excitation frequency of 8600 Hz is required. With a 2 kg launch mass the ohmic loss is 7 percent. A launcher system optimized for rotating generators would have a peak frequency of 4850 Hz; with an aluminum armature weighing 33 percent of the launch mass and a slip speed of 30 m/s the total ohmic loss in the generators, cables, and accelerator would be 43 percent of the launch kinetic energy, and the average armature temperature rise would be 510 deg C.

Modeling the capillary discharge of an electrothermal (ET) launcher

NASA Astrophysics Data System (ADS)

Least, Travis

Over the past few decades, different branches of the US Department of Defense (DoD) have invested at improving the field ability of electromagnetic launchers. One such focus has been on achieving hypervelocity launch velocities in excess of 7 km/s for direct launch to space applications [1]. It has been shown that pre-injection is required for this to be achieved. One method of pre-injection which has promise involves using an electro-thermal (ET) due to its ability to achieve the desired velocities with a minimal amount of hot plasma injected into the launcher behind the projectile. Despite the demonstration of pre-injection using this method, polymer ablation is not very well known and this makes it challenging to predict how the system will behave for a given input of electrical power. In this work, the rate of ablation has been studied and predicted using different models to generate the best possible characteristic curve. [1] - Wetz, David A., Francis Stefani, Jerald V. Parker, and Ian R. McNab. "Advancements in the Development of a Plasma-Driven Electromagnetic Launcher." IEEE TRANSACTIONS ON MAGNETICS 45.1 (2009): 495--500. IEEE Xplore. Web. 18 Aug. 2012.

83. DETAIL OF THE MUZZLE END OF THE LAUNCHER BRIDGE ...

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

83. DETAIL OF THE MUZZLE END OF THE LAUNCHER BRIDGE ON TEMPORARY SUPPORTS LOOKING NORTHEAST SHOWING TWO LAUNCHING TUBES, Date unknown, circa 1950'S. (Original photograph in possession of Dave Willis, San Diego, California.) - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

82. DETAIL OF THE MUZZLE END OF THE LAUNCHER BRIDGE ...

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

82. DETAIL OF THE MUZZLE END OF THE LAUNCHER BRIDGE LOOKING NORTH SHOWING THE CONNECTING BRIDGE AND TWO LAUNCHING TUBES, Date unknown, circa 1952. (Original photograph in possession of Dave Willis, San Diego, California.) - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

Results from Sandia National Laboratories/Lockheed Martin Electromagnetic Missile Launcher (EMML).

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

Lockner, Thomas Ramsbeck; Skurdal, Ben; Gaigler, Randy

2005-05-01

Sandia national laboratories (SNL) and lockheed martin MS2 are designing an electromagnetic missile launcher (EMML) for naval applications. The EMML uses an induction coilgun topology with the requirement of launching a 3600 lb. missile up to a velocity of 40 m/s. To demonstrate the feasibility of the electromagnetic propulsion design, a demonstrator launcher was built that consists of approximately 10% of the propulsion coils needed for a tactical design. The demonstrator verified the design by launching a 1430 lb weighted sled to a height of 24 ft in mid-December 2004 (Figure 1). This paper provides the general launcher design, specificmore » pulsed power system component details, system operation, and demonstration results.« less

View of elevated West Side (Joe Dimaggio) Highway, Riverside Park ...

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

View of elevated West Side (Joe Dimaggio) Highway, Riverside Park South, and Trump Place development from 71st to 66th streets. Shot taken from Pier 1 (Riverside Park South) looking southeast. Henry Hudson Parkway (HHP) starts just to the left of the view, one block north. 69th Street Transfer Bridge in center. - Henry Hudson Parkway, Extending 11.2 miles from West 72nd Street to Bronx-Westchester border, New York County, NY

Hypervelocity Launcher for Aerothermodynamic Experiments. Phase 2

NASA Technical Reports Server (NTRS)

Scholz, Timothy J.; Bauer, David P.

1995-01-01

The capability of an Ultra Distributed Energy Store System (UDESS) powered electromagnetic launcher (EM) is experimentally assessed. The UDESS system was developed specifically to address the velocity speed limit seen in plasma armature EM launchers. Metal armature launch packages were also developed and tested to assess the usefulness of the UDESS concept for low velocity applications.

Future launcher demonstrator. Challenge and pathfinder

NASA Astrophysics Data System (ADS)

Kleinau, W.; Guerra, L.; Parkinson, R. C.; Lieberherr, J. F.

1996-02-01

For future and advanced launch vehicles emphasis is focused on single-stage-to-orbit (SSTO) concepts and on completely reusable versions with the goal to reduce the recurrent launch cost, to improve the mission success probability and also safety for the space transportation of economically attractive payloads into Low Earth Orbit. Both issues, the SSTO launcher and the low cost reusability are extremely challenging and cannot be proven by studies and on-ground tests alone. In-flight demonstration tests are required to verify the assumptions and the new technologies, and to justify the new launcher-and operations-concepts. Because a number of SSTO launch vehicles are currently under discussion in terms of configurations and concepts such as winged vehicles for vertical or horizontal launch and landing (from ground or a flying platform), or wingless vehicles for vertical take-off and landing, and also in terms of propulsion (pure rockets or a combination of air breathing and rocket engines), an experimental demonstrator vehicle appears necessary in order to serve as a pathfinder in this area of multiple challenges. A suborbital Reusable Rocket Launcher Demonstrator (RRLD) has been studied recently by a European industrial team for ESA. This is a multipurpose, evolutionary demonstrator, conceived around a modular approach of incremental improvements of subsystems and materials, to achieve a better propellant mass fraction i.e. a better performance, and specifically for the accomplishment of an incremental flight test programme. While the RRLD basic test programme will acquire knowledge about hypersonic flight, re-entry and landing of a cryogenic rocket propelled launcher — and the low cost reusability (short turnaround on ground) in the utilization programme beyond basic testing, the RRLD will serve as a test bed for generic testing of technologies required for the realization of an SSTO launcher. This paper will present the results of the European RRLD study which

Development of Composite Technologies for the European Next Generation Launcher

NASA Astrophysics Data System (ADS)

Fatemi, Javad; van der Bas, Finn

2014-06-01

In the frame of the European Space Agency's Future Launchers Preparatory Programme (FLPP), in conjunction with national Research and Technology programs, Dutch Space has undertaken the development of composite technologies for application in the Europe's next generation launcher, Ariane 6. The efforts have focused on development of a Carbon Fibre Reinforced Plastic (CFRP) Engine Thrust Frame (ETF) for the upper-stage of Ariane6 launcher. These new technologies are expected to improve performance and to lower cost of development and exploitation of the launcher. Although the first targeted application is the thrust frame, the developed technologies are set to be generic in the sense that they can be applied to other structures of the launcher, e.g. inter-stage structures.This paper addresses the design, analysis, manufacturing and testing activities related to the composite technology developments.

ICPSU Install at Mobile Launcher

NASA Image and Video Library

2018-03-14

A colorful sunrise serves as the backdrop for the mobile launcher (ML) at NASA's Kennedy Space Center in Florida. Several launch umbilicals have been installed on the ML tower. Exploration Ground Systems is overseeing installation of umbilicals and launch accessories on the ML to prepare for the first integrated test flight of the Orion spacecraft on the agency's Space Launch System rocket on Exploration Mission-1.

Small ICBM area narrowing report. Volume 1. Hard mobile launcher in random movement basing mode

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

Not Available

The purpose of this report is to identify those areas that could potentially support deployment of the Small Intercontinental Ballistic Missile (ICBM) utilizing basing modes presently considered viable: the Hard Mobile Launcher in Random Movement, the Hard Mobile Launcher at Minuteman Facilities, and the Hard Silo in Patterned Array. Specifically, this report describes the process and the rationale supporting the application of Exclusionary and Evaluative Criteria and lists those locations that were eliminated through the application of these criteria. The remaining locations will be the subject of further investigations.

Design Performance of Front Steering-Type Electron Cyclotron Launcher for ITER

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

Takahashi, K.; Imai, T.; Kobayashi, N.

2005-01-15

The performance of a front steering (FS)-type electron cyclotron launcher designed for the International Thermonuclear Experimental Reactor (ITER) is evaluated with a thermal, electromagnetic, and nuclear analysis of the components; a mechanical test of a spiral tube for the steering mirror; and a rotational test of bearings. The launcher consists of a front shield and a launcher plug where three movable optic mirrors to steer incident multimegawatt radio-frequency beam power, waveguide components, nuclear shields, and vacuum windows are installed. The windows are located behind a closure plate to isolate the transmission lines from the radioactivated circumstance (vacuum vessel). The waveguidemore » lines of the launcher are doglegged to reduce the direct neutron streaming toward the vacuum windows and other components. The maximum stresses on the critical components such as the steering mirror, its cooling tube, and the front shield are less than their allowable stresses. It was also identified that the stress on the launcher, which yielded from electromagnetic force caused by plasma disruption, was a little larger than the criteria, and a modification of the launcher plug structure was necessary. The nuclear analysis result shows that the neutron shield capability of the launcher satisfies the shield criteria of the ITER. It concludes that the design of the FS launcher is generally suitable for application to the ITER.« less

Computational model for simulation small testing launcher, technical solution

NASA Astrophysics Data System (ADS)

Chelaru, Teodor-Viorel; Cristian, Barbu; Chelaru, Adrian

2014-12-01

The purpose of this paper is to present some aspects regarding the computational model and technical solutions for multistage suborbital launcher for testing (SLT) used to test spatial equipment and scientific measurements. The computational model consists in numerical simulation of SLT evolution for different start conditions. The launcher model presented will be with six degrees of freedom (6DOF) and variable mass. The results analysed will be the flight parameters and ballistic performances. The discussions area will focus around the technical possibility to realize a small multi-stage launcher, by recycling military rocket motors. From technical point of view, the paper is focused on national project "Suborbital Launcher for Testing" (SLT), which is based on hybrid propulsion and control systems, obtained through an original design. Therefore, while classical suborbital sounding rockets are unguided and they use as propulsion solid fuel motor having an uncontrolled ballistic flight, SLT project is introducing a different approach, by proposing the creation of a guided suborbital launcher, which is basically a satellite launcher at a smaller scale, containing its main subsystems. This is why the project itself can be considered an intermediary step in the development of a wider range of launching systems based on hybrid propulsion technology, which may have a major impact in the future European launchers programs. SLT project, as it is shown in the title, has two major objectives: first, a short term objective, which consists in obtaining a suborbital launching system which will be able to go into service in a predictable period of time, and a long term objective that consists in the development and testing of some unconventional sub-systems which will be integrated later in the satellite launcher as a part of the European space program. This is why the technical content of the project must be carried out beyond the range of the existing suborbital vehicle

Computational model for simulation small testing launcher, technical solution

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

Chelaru, Teodor-Viorel, E-mail: teodor.chelaru@upb.ro; Cristian, Barbu, E-mail: barbucr@mta.ro; Chelaru, Adrian, E-mail: achelaru@incas.ro

The purpose of this paper is to present some aspects regarding the computational model and technical solutions for multistage suborbital launcher for testing (SLT) used to test spatial equipment and scientific measurements. The computational model consists in numerical simulation of SLT evolution for different start conditions. The launcher model presented will be with six degrees of freedom (6DOF) and variable mass. The results analysed will be the flight parameters and ballistic performances. The discussions area will focus around the technical possibility to realize a small multi-stage launcher, by recycling military rocket motors. From technical point of view, the paper ismore » focused on national project 'Suborbital Launcher for Testing' (SLT), which is based on hybrid propulsion and control systems, obtained through an original design. Therefore, while classical suborbital sounding rockets are unguided and they use as propulsion solid fuel motor having an uncontrolled ballistic flight, SLT project is introducing a different approach, by proposing the creation of a guided suborbital launcher, which is basically a satellite launcher at a smaller scale, containing its main subsystems. This is why the project itself can be considered an intermediary step in the development of a wider range of launching systems based on hybrid propulsion technology, which may have a major impact in the future European launchers programs. SLT project, as it is shown in the title, has two major objectives: first, a short term objective, which consists in obtaining a suborbital launching system which will be able to go into service in a predictable period of time, and a long term objective that consists in the development and testing of some unconventional sub-systems which will be integrated later in the satellite launcher as a part of the European space program. This is why the technical content of the project must be carried out beyond the range of the existing suborbital

New coplanar waveguide to rectangular waveguide end launcher

NASA Technical Reports Server (NTRS)

Simons, R. N.; Taub, S. R.

1992-01-01

A new coplanar waveguide to rectangular waveguide end launcher is experimentally demonstrated. The end launcher operates over the Ka-band frequencies that are designated for the NASA Advanced Communication Technology Satellite uplink. The measured insertion loss and return loss are better than 0.5 and -10 dB, respectively.

Multi-walled boron nitride nanotubes as self-excited launchers.

PubMed

Li, Yifan; Zhou, Yi; Wu, Yan; Huang, Chengchi; Wang, Long; Zhou, Xuyan; Zhao, Zhenyang; Li, Hui

2017-07-27

A self-excited launcher consisting of multi-walled boron nitride nanotubes (BNNTs) has been investigated using molecular dynamics simulation. The results show that, after a period of high frequency oscillation, the innermost BNNT can be spontaneously ejected along its central axis at a relatively fast speed. The launching is caused by the energy transfer between the nanotubes and without absorbing energy from the external environment. Most self-excited launchers could launch their innermost nanotube, although an inappropriate structure of the nanotubes contributes to a blocked or failed launch. In addition, a launch angle corrector and a nanotube receiver associated with a self-excited launcher are also manufactured to precisely control the launch angle and distance of the BNNTs. This study provides the possibility to fabricate and design self-excited launchers using multi-walled nanotubes.

Launch of Little Joe I-B from Wallops Island

NASA Image and Video Library

1960-01-21

B60-00364 (4 Nov. 1959) --- Launch of Little Joe-2 from Wallops Island carrying Mercury spacecraft test article. The suborbital test flight of the Mercury capsule was to test the escape system. Vehicle functioned perfectly, but escape rocket ignited several seconds too late. Photo credit: NASA

Parameterization of Highly Charged Metal Ions Using the 12-6-4 LJ-Type Nonbonded Model in Explicit Water

PubMed Central

2015-01-01

Highly charged metal ions act as catalytic centers and structural elements in a broad range of chemical complexes. The nonbonded model for metal ions is extensively used in molecular simulations due to its simple form, computational speed, and transferability. We have proposed and parametrized a 12-6-4 LJ (Lennard-Jones)-type nonbonded model for divalent metal ions in previous work, which showed a marked improvement over the 12-6 LJ nonbonded model. In the present study, by treating the experimental hydration free energies and ion–oxygen distances of the first solvation shell as targets for our parametrization, we evaluated 12-6 LJ parameters for 18 M(III) and 6 M(IV) metal ions for three widely used water models (TIP3P, SPC/E, and TIP4PEW). As expected, the interaction energy underestimation of the 12-6 LJ nonbonded model increases dramatically for the highly charged metal ions. We then parametrized the 12-6-4 LJ-type nonbonded model for these metal ions with the three water models. The final parameters reproduced the target values with good accuracy, which is consistent with our previous experience using this potential. Finally, tests were performed on a protein system, and the obtained results validate the transferability of these nonbonded model parameters. PMID:25145273

Analysis of two potential long-distance signaling molecules, LjCLE-RS1/2 and jasmonic acid, in a hypernodulating mutant too much love.

PubMed

Magori, Shimpei; Kawaguchi, Masayoshi

2010-04-01

Legume plants tightly control the number and development of root nodules. This is partly regulated by a long-distance signaling known as auto-regulation of nodulation (AON). AON signaling involves at least two potential long-distance signals: root-derived signal and shoot-derived signal. However, their molecular characteristics and the mode of action remain unclear. In our recent study, we isolated a novel Lotus japonicus hypernodulating mutant too much love (tml). Based on several grafting experiments, we concluded that its causative gene TML functions as a receptor of the shoot-derived signal. This finding prompted us to ask how the candidates of the long-distance signal molecules, LjCLE-RS1/2 and jasmonic acid (JA), are affected in tml mutants. Expression analysis revealed that rapid induction of LjCLE-RS1/2 upon rhizobial inoculation is still intact in tml, supporting that TML plays a role in reception of the shoot-derived signal but not in generation of the root-derived signal. Furthermore, physiological analysis showed that JA, a candidate of the shoot-derived signal, can suppress tml hypernodulation. Therefore, contrary to the previous report, JA might not be a component of AON signaling.

Orion Service Module Umbilical (OSMU) Installation on Mobile Launcher (ML)

NASA Image and Video Library

2017-03-13

Cranes and rigging are being used to lift the bracket for the Orion Service Module Umbilical (OSMU) up for installation on the mobile launcher tower. The tower will be equipped with a number of lines, called umbilicals, that will connect to the Space Launch System rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The OSMU will be located high on the mobile launcher tower and, prior to launch, will transfer liquid coolant for the electronics and air for the Environmental Control System to the Orion service module that houses these critical systems to support the spacecraft. EM-1 is scheduled to launch in 2018. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

Launcher Systems Development Cost: Behavior, Uncertainty, Influences, Barriers and Strategies for Reduction

NASA Technical Reports Server (NTRS)

Shaw, Eric J.

2001-01-01

This paper will report on the activities of the IAA Launcher Systems Economics Working Group in preparations for its Launcher Systems Development Cost Behavior Study. The Study goals include: improve launcher system and other space system parametric cost analysis accuracy; improve launcher system and other space system cost analysis credibility; and provide launcher system and technology development program managers and other decisionmakers with useful information on development cost impacts of their decisions. The Working Group plans to explore at least the following five areas in the Study: define and explain development cost behavior terms and concepts for use in the Study; identify and quantify sources of development cost and cost estimating uncertainty; identify and quantify significant influences on development cost behavior; identify common barriers to development cost understanding and reduction; and recommend practical, realistic strategies to accomplish reductions in launcher system development cost.

ISAS' new satellite launcher M-V

NASA Astrophysics Data System (ADS)

Akiba, R.; Matsuo, H.; Kohno, M.

The concept of the M-V, a new version of Japanese satellite launchers that is being developed by the Institute of Space and Astronautical Science, is described. The M-V is a three-stage solid propellant rocket that could lift about 2 tons of payload into LEO. Its first flight is scheduled to be at the beginning of 1995, when M-V will carry an engineering test satelline to prove the technology for Space VLBE. The basic parameters of the M-V launcher, the vehicle configuration diagram, and motor-design diagrams are presented.

Magnetic reconnection launcher

DOEpatents

Cowan, M.

1987-04-06

An electromagnetic launcher includes a plurality of electrical stages which are energized sequentially in the launcher with the passage of a projectiles. Each stage of the launcher includes two or more coils which are arranged coaxially on either closed-loop or straight lines to form gaps between their ends. The projectile has an electrically conductive gap-portion that passes through all the gaps of all the stages in a direction transverse to the axes of the coils. The coils receive an electric current, store magnetic energy, and convert a significant portion of the stored magnetic energy into kinetic energy of the projectile moves through the gap. The magnetic polarity of the opposing coils is in the same direction, e.g. N-S-N-S. A gap portion of the projectile may be made from aluminum and is propelled by the reconnection of magnetic flux stored in the coils which causes accelerating forces to act upon the projectile and at the horizontal surfaces of the projectile near its rear. The gap portion of the projectile may be flat, rectangular and longer than the length of the opposing coils. The gap portion of the projectile permits substantially unrestricted distribution of the induced currents so that current densities are only high where the useful magnetic force is high. This allows designs which permit ohmic oblation from the rear surfaces of the gap portion of the projectile allowing much high velocities to be achieved. An electric power apparatus controls the electric power supplied to the opposing coils until the gap portion of the projectile substantially occupies the gap between the coils, at which time the coils are supplied with peak current quickly. 8 figs.

LH Power Losses In Front of the JET Launcher

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

Jacquet, P.; Arnoux, G.; Kirov, K.

2009-11-26

In recent JET experiments, Lower Hybrid (LH) power losses in the Scrape-Off Layer (SOL) were characterized using infra-red (IR) thermography. Hot spots were observed on objects intercepting the field lines passing in front of the LH launcher, i.e. on poloidal limiters and on dumplates located at the top of the tokamak; their locations being in good agreement with magnetic field line tracing using the EFIT equilibrium code. The dumplate temperature was monitored while scanning the launcher position so that the radial distance between field lines intercepting the hot spots and the launcher was increased up to 3.5 cm. The dissipationmore » layer in front of the launcher was estimated to be at least 3.5 cm wide, in agreement with recent measurements on Tore-Supra, but not with simple models that predict a dissipation layer in the mm range.« less

Final Report Advanced Quasioptical Launcher System

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

Jeffrey Neilson

2010-04-30

This program developed an analytical design tool for designing antenna and mirror systems to convert whispering gallery RF modes to Gaussian or HE11 modes. Whispering gallery modes are generated by gyrotrons used for electron cyclotron heating of fusion plasmas in tokamaks. These modes cannot be easily transmitted and must be converted to free space or waveguide modes compatible with transmission line systems.This program improved the capability of SURF3D/LOT, which was initially developed in a previous SBIR program. This suite of codes revolutionized quasi-optical launcher design, and this code, or equivalent codes, are now used worldwide. This program added functionality tomore » SURF3D/LOT to allow creating of more compact launcher and mirror systems and provide direct coupling to corrugated waveguide within the vacuum envelope of the gyrotron. Analysis was also extended to include full-wave analysis of mirror transmission line systems. The code includes a graphical user interface and is available for advanced design of launcher systems.« less

SIDON: A simulator of radio-frequency networks. Application to WEST ICRF launchers

NASA Astrophysics Data System (ADS)

Helou, Walid; Dumortier, Pierre; Durodié, Frédéric; Goniche, Marc; Hillairet, Julien; Mollard, Patrick; Berger-By, Gilles; Bernard, Jean-Michel; Colas, Laurent; Lombard, Gilles; Maggiora, Riccardo; Magne, Roland; Milanesio, Daniele; Moreau, Didier

2015-12-01

SIDON (SImulator of raDiO-frequency Networks) is an in-house developed Radio-Frequency (RF) network solver that has been implemented to cross-validate the design of WEST ICRF launchers and simulate their impedance matching algorithm while considering all mutual couplings and asymmetries. In this paper, the authors illustrate the theory of SIDON as well as results of its calculations. The authors have built time-varying plasma scenarios (a sequence of launchers front-faces L-mode and H-mode Z-matrices), where at each time step (1 millisecond here), SIDON solves the RF network. At the same time, when activated, the impedance matching algorithm controls the matching elements (vacuum capacitors) and thus their corresponding S-matrices. Typically a 1-second pulse requires around 10 seconds of computational time on a desktop computer. These tasks can be hardly handled by commercial RF software. This innovative work allows identifying strategies for the launchers future operation while insuring the limitations on the currents, voltages and electric fields, matching and Load-Resilience, as well as the required straps voltage amplitude/phase balance. In this paper, a particular attention is paid to the simulation of the launchers behavior when arcs appear at several locations of their circuits using SIDON calculator. This latter work shall confirm or identify strategies for the arc detection using various RF electrical signals. One shall note that the use of such solvers in not limited to ICRF launchers simulations but can be employed, in principle, to any linear or linearized RF problem.

ICPSU Install onto Mobile Launcher - Preps for Lift

NASA Image and Video Library

2018-03-15

Construction workers with JP Donovan assist with preparations to lift and install the Interim Cryogenic Propulsion Stage Umbilical on the tower of the mobile launcher at NASA's Kennedy Space Center in Florida. The last of the large umbilicals to be installed, the ICPSU will provide super-cooled hydrogen and liquid oxygen to the Space Launch System (SLS) rocket's interim cryogenic propulsion stage, or upper stage, at T-0 for Exploration Mission-1. The umbilical is located at about the 240-foot-level of the mobile launcher and will supply fuel, oxidizer, gaseous helium, hazardous gas leak detection, electrical commodities and environment control systems to the upper stage of the SLS rocket during launch. Exploration Ground Systems is overseeing installation of the umbilicals on the ML.

Experimental launcher facility - ELF-I: Design and operation

NASA Astrophysics Data System (ADS)

Deis, D. W.; Ross, D. P.

1982-01-01

In order to investigate the general area of ultra-high-current density, high-velocity sliding contacts as applied to electromagnetic launcher armatures, a small experimental launcher, ELF-I, has been developed, and preliminary experiments have been performed. The system uses a 36 kJ, 5 kV capacitor bank as a primary pulse power source. When used in conjunction with a 5-microhenry pulse conditioning coil, a 100-kA peak current and 10-ms-wide pulse is obtained. A three-station 150 kV flash X-ray system is operational for obtaining in-bore photographs of the projectiles. Experimental results obtained for both metal and plasma armatures at sliding velocities of up to 1 km/s are discussed with emphasis on armature-rail interactions.

Future launchers strategy : the ariane 2010 initiative

NASA Astrophysics Data System (ADS)

Bonnal, Ch.; Eymard, M.; Soccodato, C.

2001-03-01

With the new cryogenic upper stage ESC, the European heavy launcher Ariane 5+ is perfectly suited to the space market envisioned for the coming decade: flexible to cope with any payload and commercially attractive despite a fierce competition. Current Arianespace projections for the following years 2010-2020 indicate two major trends: satellites may still become larger and may require very different final orbits; today's market largely dominated by GEO may well evolve, influenced by LEO operations such as those linked to ISS or by constellations, to remain competitive, the launch cost has to be reduced. The future generation of the European heavy launcher has therefore to focus on an ever increased flexibility with a drastic cost reduction. Two strategies are possible to achieve this double goal: reusable launchers, either partially or totally, may ease the access to space, limiting costly expendable stages; the assessment of their technical feasibility and financial viability is undergoing in Europe under the Future Launchers Technology Program (FLTP), expendable launchers, derived from the future Ariane 5+. This second way started by CNES at the end of year 1999 is called the "Ariane 2010 initiative". The main objectives are simultaneously an increase of 25% in performance and a reduction of 30% in launch cost wrt Ariane 5+. To achieve these very ambitious goals, numerous major modifications are studied: technical improvements : modifications of the Solid Rocket Boosters may consist in filament winding casing, increased loading, simplified casting, improved grain, simplified Thrust Vector Control, … evolution of the Vulcain engine leading to higher efficiency despite a simplified design, flow separation controlled nozzle extension, propellant management of the two cryogenic stages, simplified electrical system, increased standardization, for instance on flanged interfaces and manufacturing processes, operational improvements such as launch cycle simplification

Sphere launcher

NASA Technical Reports Server (NTRS)

Reed, W. B.

1972-01-01

The sphere launcher was designed to eject a 200 lb, 15 in. diameter sphere from a space vehicle or missile, at a velocity of 58 ft/sec without imparting excessive lateral loads to the vehicle. This launching is accomplished with the vehicle operating in vacuum conditions and under a 9 g acceleration. Two principal elements are used: a high thrust, short burn time rocket motor and two snubbers for reducing the lateral loads to acceptable limits.

Photographic copy of photograph, view of rail launcher used for ...

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

Photographic copy of photograph, view of rail launcher used for 'Baby Corporal E' missiles on 6 and 7 May 1946 at JPL-Muroc Army Air Base (later Edwards Air Force Base) (This launcher was also used for 'Baby WAC' missiles at Goldstone, Fort Irwin, California in 1945). Photocopy of 35mm photograph made in December 1994, looking west with Test Stand 'A' immediately behind the rail launcher. - Jet Propulsion Laboratory Edwards Facility, Edwards Air Force Base, Boron, Kern County, CA

Electromechanical Dynamics Simulations of Superconducting LSM Rocket Launcher System in Attractive-Mode

NASA Technical Reports Server (NTRS)

Yoshida, Kinjiro; Hayashi, Kengo; Takami, Hiroshi

1996-01-01

Further feasibility study on a superconducting linear synchronous motor (LSM) rocket launcher system is presented on the basis of dynamic simulations of electric power, efficiency and power factor as well as the ascending motions of the launcher and rocket. The advantages of attractive-mode operation are found from comparison with repulsive-mode operation. It is made clear that the LSM rocket launcher system, of which the long-stator is divided optimally into 60 sections according to launcher speeds, can obtain high efficiency and power factor.

ICPSU Install at Mobile Launcher

NASA Image and Video Library

2018-03-14

A sliver of the Moon is visible just before sunrise at NASA's Kennedy Space Center in Florida. In view is one of the steel structures of the mobile launcher (ML). Several launch umbilicals have been installed on the ML tower. Exploration Ground Systems is overseeing installation of umbilicals and launch accessories on the ML to prepare for the first integrated test flight of the Orion spacecraft on the agency's Space Launch System rocket on Exploration Mission-1.

Three-phase hypervelocity projectile launcher

DOEpatents

Fugelso, L. Erik; Langner, Gerald C.; Burns, Kerry L.; Albright, James N.

1994-01-01

A hypervelocity projectile launcher for use in perforating borehole casings provides improved penetration into the surrounding rock structure. The launcher includes a first cylinder of explosive material that defines an axial air-filled cavity, a second cylinder of explosive material defining an axial frustum-shaped cavity abutting and axially aligned with the first cylinder. A pliant washer is located between and axially aligned with the first and second cylinders. The frustum shaped cavity is lined with a metal liner effective to form a projectile when the first and second cylinders are detonated. The washer forms a unique intermediate projectile in advance of the liner projectile and enables the liner projectile to further penetrate into and fracture the adjacent rock structure.

Cyclopropanyldehydrocostunolide LJ attenuates high glucose-induced podocyte injury by suppressing RANKL/RANK-mediated NF-κB and MAPK signaling pathways.

PubMed

Chen, Xiao-Wen; Liu, Wen-Ting; Wang, Yu-Xian; Chen, Wen-Jing; Li, Hong-Yu; Chen, Yi-Hua; Du, Xiao-Yan; Peng, Fen-Fen; Zhou, Wei-Dong; Xu, Zhao-Zhong; Long, Hai-Bo

2016-07-01

The aim of this research was to investigate the effects of cyclopropanyldehydrocostunolide (also named LJ), a derivative of sesquiterpene lactones (SLs), on high glucose (HG)-induced podocyte injury and the associated molecular mechanisms. Differentiated mouse podocytes were incubated in different treatments. The migration and albumin filtration of podocytes were examined by Transwell filters. The protein and mRNA levels of MCP-1 were measured using enzyme-linked immunosorbent assay (ELISA) and quantitative real-time PCR (q-PCR). Protein expression and phosphorylation were detected by western blot, and the nuclear translocation of NF-κB was performed with a confocal microscope. The gene expression of the receptor activator for NF-κB (RANK) was silenced by small interfering RNA (siRNA). Our results showed that HG enhanced migration, albumin filtration and MCP-1 expression in podocytes. At the molecular level, HG promoted the phosphorylation of NF-κB/p65, IKKβ, IκBα, mitogen-activated protein kinase (MAPK) and the nuclear translocation of p65. LJ reversed the effects of HG in a dose-dependent manner. Furthermore, our data provided the first demonstration that the receptor activator for NF-κB ligand (RANKL) and its cognate receptor RANK were overexpressed in HG-induced podocytes and were downregulated by LJ. RANK siRNA also attenuated HG-induced podocyte injury and markedly inhibited the activation of NF-κB and MAPK signaling pathways. LJ attenuates HG-induced podocyte injury by suppressing RANKL/RANK-mediated NF-κB and MAPK signaling pathways. Copyright © 2016 Elsevier Inc. All rights reserved.

First University of Michigan Strongarm sounding rocket on launcher at Wallops for test, November 10, 1959E5-188 Shop and Launcher Pictures

NASA Image and Video Library

1959-11-10

L59-7932 First University of Michigan Strongarm sounding rocket on launcher at Wallops for test, November 10, 1959. Photograph published in A New Dimension Wallops Island Flight Test Range: The First Fifteen Years by Joseph Shortal. A NASA publication. Page 701.E5-188 Shop and Launcher Pictures

Core Stage Forward Skirt Umbilical Installation onto Mobile Launcher

NASA Image and Video Library

2017-06-29

Just north of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, the core stage forward skirt umbilical is installed on the mobile launcher. The mobile launcher is designed to support the assembly, testing and check-out of the agency's Space Launch System (SLS) rocket and the Orion spacecraft.

ICPSU Install onto Mobile Launcher - Preps for Lift

NASA Image and Video Library

2018-03-15

A construction worker with JP Donovan helps prepare the Interim Cryogenic Propulsion Stage Umbilical (ICPSU) for installation high up on the tower of the mobile launcher (ML) at NASA's Kennedy Space Center in Florida. The last of the large umbilicals to be installed, the ICPSU will provide super-cooled hydrogen and liquid oxygen to the Space Launch System (SLS) rocket's interim cryogenic propulsion stage, or upper stage, at T-0 for Exploration Mission-1. The umbilical will be located at about the 240-foot-level of the mobile launcher and will supply fuel, oxidizer, gaseous helium, hazardous gas leak detection, electrical commodities and environment control systems to the upper stage of the SLS rocket during launch. Exploration Ground Systems is overseeing installation of the umbilicals on the ML.

Thermal limitations in a rapid-fire multirail launcher powered by a pulsed magnetodhydrodynamic generator

NASA Astrophysics Data System (ADS)

Stankevich, S. V.; Shvetsov, G. A.; Butov, V. G.; Sinyaev, S. V.

2017-09-01

The operation of rapid burst firing multirail electromagnetic launchers of solids is numerically simulated using unsteady two-dimensional and three-dimensional models. In the calculations, the launchers are powered by a Sakhalin pulsed magnetohydrodynamic generator. Launchers with three and five pairs of parallel rails connected in a series electrical circuit are considered. Firing sequences of different numbers of solid projectiles of different masses is modeled. It is established that the heating of the rails is one of the main factors limiting the performance of launchers under such conditions. It is shown that the rate of heating of the rails is determined by the nonuniformity of the current density distribution over the rail cross-section due to the unsteady diffusion of the magnetic field into the rails. Calculations taking into account the unsteady current density distribution in the rails of a multirail launcher show that with an appropriate of the mass of the projectiles (up to 800 g), their number in the sequence, and the material of the rails, it is possible to attain launching velocities of 1.8-2.5 km/s with moderate heating of the rails.

The Physics Performance Of The Front Steering Launcher For The ITER ECRH Upper Port

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

Henderson, M.; Chavan, R.; Nikkola, P.

2005-09-26

The capability of any given e.m.-wave plasma heating system to be utilized for physics applications depends strongly on the technical properties of the launching antenna (or launcher). An effective ECH launcher must project a small mm-wave beam spot size far into the plasma and 'steer' the beam across a large fraction of the plasma cross section (along the resonance surface). Thus the choice in the launcher concept and design may either severely limit or enhance the capability of a heating system to be effectively applied for physics applications, such as sawtooth stabilization, control of the Neoclassical Tearing Mode (NTM), Edgemore » Localized Mode (ELM) control, etc. Presently, two antenna concepts are under consideration for the ITER upper port ECH launcher: front steering (FS) and remote steering (RS) launchers. The RS launcher has the technical advantage of easier maintenance access to the steering mirror, which is isolated from the torus vacuum. The FS launcher places the steering mirror near the plasma increasing the technical challenges, but significantly enhancing the focusing and steering capabilities of the launcher, offering a threefold increase in NTM stabilization efficiency over the RS launcher as well as the potential for application to other critical physics issues such as ELM or sawtooth control.« less

The role of prophage for genome diversification within a clonal lineage of Lactobacillus johnsonii: characterization of the defective prophage LJ771.

PubMed

Denou, Emmanuel; Pridmore, Raymond David; Ventura, Marco; Pittet, Anne-Cécile; Zwahlen, Marie-Camille; Berger, Bernard; Barretto, Caroline; Panoff, Jean-Michel; Brüssow, Harald

2008-09-01

Two independent isolates of the gut commensal Lactobacillus johnsonii were sequenced. These isolates belonged to the same clonal lineage and differed mainly by a 40.8-kb prophage, LJ771, belonging to the Sfi11 phage lineage. LJ771 shares close DNA sequence identity with Lactobacillus gasseri prophages. LJ771 coexists as an integrated prophage and excised circular phage DNA, but phage DNA packaged into extracellular phage particles was not detected. Between the phage lysin gene and attR a likely mazE ("antitoxin")/pemK ("toxin") gene cassette was detected in LJ771 but not in the L. gasseri prophages. Expressed pemK could be cloned in Escherichia coli only together with the mazE gene. LJ771 was shown to be highly stable and could be cured only by coexpression of mazE from a plasmid. The prophage was integrated into the methionine sulfoxide reductase gene (msrA) and complemented the 5' end of this gene, creating a protein with a slightly altered N-terminal sequence. The two L. johnsonii strains had identical in vitro growth and in vivo gut persistence phenotypes. Also, in an isogenic background, the presence of the prophage resulted in no growth disadvantage.

Geologic map of the St. Joe quadrangle, Searcy and Marion Counties, Arkansas

USGS Publications Warehouse

Hudson, Mark R.; Turner, Kenzie J.

2009-01-01

This map summarizes the geology of the St. Joe 7.5-minute quadrangle in the Ozark Plateaus region of northern Arkansas. Geologically, the area lies on the southern flank of the Ozark dome, an uplift that exposes oldest rocks at its center in Missouri. Physiographically, the St. Joe quadrangle lies within the Springfield Plateau, a topographic surface generally held up by Mississippian cherty limestone. The quadrangle also contains isolated mountains (for example, Pilot Mountain) capped by Pennsylvanian rocks that are erosional outliers of the higher Boston Mountains plateau to the south. Tomahawk Creek, a tributary of the Buffalo River, flows through the eastern part of the map area, enhancing bedrock erosion. Exposed bedrock of this region comprises an approximately 1,300-ft-thick sequence of Ordovician, Mississippian, and Pennsylvanian carbonate and clastic sedimentary rocks that have been mildly deformed by a series of faults and folds. The geology of the St. Joe quadrangle was mapped by McKnight (1935) as part of a larger area at 1:125,000 scale. The current map confirms many features of this previous study, but it also identifies new structures and uses a revised stratigraphy. Mapping for this study was conducted by field inspection of numerous sites and was compiled as a 1:24,000-scale geographic information system (GIS) database. Locations and elevations of sites were determined with the aid of a global positioning satellite receiver and a hand-held barometric altimeter that was frequently recalibrated at points of known elevation. Hill-shade-relief and slope maps derived from a U.S. Geological Survey 10-m digital elevation model as well as U.S. Geological Survey orthophotographs from 2000 were used to help trace ledge-forming units between field traverses within the Upper Mississippian and Pennsylvanian part of the stratigraphic sequence. Strikes and dips of beds were typically measured along stream drainages or at well-exposed ledges. Beds dipping less

Study of nsLTPs in Lotus japonicus genome reveal a specific epidermal cell member (LjLTP10) regulated by drought stress in aerial organs with a putative role in cutin formation.

PubMed

Tapia, G; Morales-Quintana, L; Parra, C; Berbel, A; Alcorta, M

2013-07-01

The cuticle is the first defense against pathogens and the second way water is lost in plants. Hydrophobic layers covering aerial plant organs from primary stages of development form cuticle, including major classes of aliphatic wax components and cutin. Extensive research has been conducted to understand cuticle formation mechanisms in plants. However, many questions remain unresolved in the transport of lipid components to form cuticle. Database studies of the Lotus japonicus genome have revealed the presence of 24 sequences classified as putative non-specific lipid transfer proteins (nsLTPs), which were classified in seven groups; four groups were selected because of their expression in aerial organs. LjLTP8 forms a cluster with DIR1 in Arabidopsis thaliana while LjLTP6, LjLTP9, and LjLTP10 were grouped as type I LTPs. In silico studies showed a high level of structural conservation, and substrate affinity studies revealed palmitoyl-CoA as the most likely ligand for these LTPs, although the Lyso-Myristoyl Phosphatidyl Choline, Lyso-myristoyl phosphatidyl glycerol, and Lyso-stearyl phosphatidyl choline ligands also showed a high affinity with the proteins. The LjLTP6 and LjLTP10 genes were expressed in both the stems and the leaves under normal conditions and were highly induced during drought stress. LjLTP10 was the most induced gene in shoots during drought. The gene was only expressed in the epidermal cells of stems, primordial leaves, and young leaflets. LjLTP10 was positively regulated by MeJA but repressed by abscisic acid (ABA), ethylene, and H2O2, while LjLTP6 was weakly induced by MeJA, repressed by H2O2, and not affected by ABA and ethylene. We suggest that LjLTP10 is involved in plant development of stem and leaf cuticle, but also in acclimation to tolerate drought stress in L. japonicus.

7. VARIABLEANGLE LAUNCHER DEDICATION PLAQUE SHOWING JAMES H. JENNISON (LEFT), ...

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

7. VARIABLE-ANGLE LAUNCHER DEDICATION PLAQUE SHOWING JAMES H. JENNISON (LEFT), AND W.H. SAYLOR (RIGHT), AT THE DEDICATION CEREMONY, May 7, 1948. (Original photograph in possession of Dave Willis, San Diego, California.) - Variable Angle Launcher Complex, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

23. VIEW DOWN INTO LAUNCHER AND FLAME BUCKET FROM STATION ...

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

23. VIEW DOWN INTO LAUNCHER AND FLAME BUCKET FROM STATION 48 IN SLC-3W MST. NOTE REMOVABLE METAL PLANKS BELOW LAUNCHER AND ROPE NET OVER FLAME BUCKET. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 West, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

Magnetic reconnection launcher

DOEpatents

Cowan, Maynard

1989-01-01

An electromagnetic launcher includes a plurality of electrical stages which are energized sequentially in synchrony with the passage of a projectile. Each stage of the launcher includes two or more coils which are arranged coaxially on either closed-loop or straight lines to form gaps between their ends. The projectile has an electrically conductive gap-portion that passes through all the gaps of all the stages in a direction transverse to the axes of the coils. The coils receive an electric current, store magnetic energy, and convert a significant portion of the stored magnetic energy into kinetic energy of the projectile by magnetic reconnection as the gap portion of the projectile moves through the gap. The magnetic polarity of the opposing coils is in the same direction, e.g. N-S-N-S. A gap portion of the projectile may be made from aluminum and is propelled by the reconnection of magnetic flux stored in the coils which causes accelerating forces to act upon the projectile at both the rear vertical surface of the projectile and at the horizontal surfaces of the projectile near its rear. The gap portion of the projectile may be flat, rectangular and longer than the length of the opposing coils and fit loosely within the gap between the opposing coils.

Mesh-matrix analysis method for electromagnetic launchers

NASA Technical Reports Server (NTRS)

Elliott, David G.

1989-01-01

The mesh-matrix method is a procedure for calculating the current distribution in the conductors of electromagnetic launchers with coil or flat-plate geometry. Once the current distribution is known the launcher performance can be calculated. The method divides the conductors into parallel current paths, or meshes, and finds the current in each mesh by matrix inversion. The author presents procedures for writing equations for the current and voltage relations for a few meshes to serve as a pattern for writing the computer code. An available subroutine package provides routines for field and flux coefficients and equation solution.

Electromagnetic launchers for space applications

NASA Technical Reports Server (NTRS)

Schroeder, J. M.; Gully, J. H.; Driga, M. D.

1989-01-01

An electromagnetic launcher (EML) was designed for NASA-Langley to boost large models to hypervelocity for flight evaluation. Two different concepts were developed using railgun and coilgun principles. A coilgun was designed to accelerate a 14-kg mass to 6 km/s and, by adding additional equipment, to accelerate a 10-kg mass to 11 km/s. The railgun system was designed to accelerate only 14 kg to 6 km/s. Of significance in this development is the opportunity to use the launcher for aeroballistic research of the upper atmosphere, eventually placing packages in low earth orbit using a small rocket. The authors describe the railgun and coilgun launch designs and suggest a reconfiguration for placement of 150-kg parcels into low earth orbit for aeroballistic studies and possible space lab support. Each design is detailed along with the performance adjustments which would be required for circular orbit payload placement.

Where Are They Now? LJ Revisits a Decade's Worth of Graduates

ERIC Educational Resources Information Center

Kuzyk, Raya

2006-01-01

In this article, the author revisits 11 graduates who were profiled as part of LJ's annual Placements & Salaries issue. Armed with a library science degree from various institutions, they had just secured jobs in librarianship and were off to a good start forging their careers. Since then, they have worked at elementary school, college, and…

Preliminary feasibility assessment for Earth-to-space electromagnetic (Railgun) launchers

NASA Technical Reports Server (NTRS)

Rice, E. E.; Miller, L. A.; Earhart, R. W.

1982-01-01

An Earth to space electromagnetic (railgun) launcher (ESRL) for launching material into space was studied. Potential ESRL applications were identified and initially assessed to formulate preliminary system requirements. The potential applications included nuclear waste disposal in space, Earth orbital applications, deep space probe launchers, atmospheric research, and boost of chemical rockets. The ESRL system concept consisted of two separate railgun launcher tubes (one at 20 deg from the horizontal for Earth orbital missions, the other vertical for solar system escape disposal missions) powered by a common power plant. Each 2040 m launcher tube is surrounded by 10,200 homopolar generator/inductor units to transmit the power to the walls. Projectile masses are 6500 kg for Earth orbital missions and 2055 kg for nuclear waste disposal missions. For the Earth orbital missions, the projectile requires a propulsion system, leaving an estimated payload mass of 650 kg. For the nuclear waste disposal in space mission, the high level waste mass was estimated at 250 kg. This preliminary assessment included technical, environmental, and economic analyses.

RL-10 Based Combined Cycle For A Small Reusable Single-Stage-To-Orbit Launcher

NASA Technical Reports Server (NTRS)

Balepin, Vladimir; Price, John; Filipenco, Victor

1999-01-01

This paper discusses a new application of the combined propulsion known as the KLIN(TM) cycle, consisting of a thermally integrated deeply cooled turbojet (DCTJ) and liquid rocket engine (LRE). If based on the RL10 rocket engine family, the KLIN (TM) cycle makes a small single-stage-to-orbit (SSTO) reusable launcher feasible and economically very attractive. Considered in this paper are the concept and parameters of a small SSTO reusable launch vehicle (RLV) powered by the KLIN (TM) cycle (sSSTO(TM)) launcher. Also discussed are the benefits of the small launcher, the reusability, and the combined cycle application. This paper shows the significant reduction of the gross take off weight (GTOW) and dry weight of the KLIN(TM) cycle-powered launcher compared to an all-rocket launcher.

Design and testing of a coil-unit barrel for helical coil electromagnetic launcher.

PubMed

Yang, Dong; Liu, Zhenxiang; Shu, Ting; Yang, Lijia; Ouyang, Jianming

2018-01-01

A coil-unit barrel for a helical coil electromagnetic launcher is described. It provides better features of high structural strength and flexible adjustability. It is convenient to replace the damaged coil units and easy to adjust the number of turns in the stator coils due to the modular design. In our experiments, the highest velocity measured for a 4.5-kg projectile is 47.3 m/s and the mechanical reinforcement of the launcher could bear 35 kA peak current. The relationship between the energy conversion efficiency and the inductance gradient of the launcher is also studied. In the region of low inductance gradient, the efficiency is positively correlated with the inductance gradient. However, in the region of high inductance gradient, the inter-turn arc erosion becomes a major problem of limiting the efficiency and velocity of the launcher. This modular barrel allows further studies in the inter-turn arc and the variable inductance gradient helical coil launcher.

Design and testing of a coil-unit barrel for helical coil electromagnetic launcher

NASA Astrophysics Data System (ADS)

Yang, Dong; Liu, Zhenxiang; Shu, Ting; Yang, Lijia; Ouyang, Jianming

2018-01-01

A coil-unit barrel for a helical coil electromagnetic launcher is described. It provides better features of high structural strength and flexible adjustability. It is convenient to replace the damaged coil units and easy to adjust the number of turns in the stator coils due to the modular design. In our experiments, the highest velocity measured for a 4.5-kg projectile is 47.3 m/s and the mechanical reinforcement of the launcher could bear 35 kA peak current. The relationship between the energy conversion efficiency and the inductance gradient of the launcher is also studied. In the region of low inductance gradient, the efficiency is positively correlated with the inductance gradient. However, in the region of high inductance gradient, the inter-turn arc erosion becomes a major problem of limiting the efficiency and velocity of the launcher. This modular barrel allows further studies in the inter-turn arc and the variable inductance gradient helical coil launcher.

Electromagnetic launcher for heavy projectiles

NASA Astrophysics Data System (ADS)

Kozlov, A. V.; Kotov, A. V.; Polistchook, V. P.; Shurupov, A. V.; Shurupov, M. A.

2017-11-01

In this paper, we present the electromagnetic launcher with capacitive power source of 4.8 MJ. Our installation allows studying of the projectile acceleration in railgun in two regimes: with a solid armature and with a plasma piston. The experiments with plasma piston were performed in the railgun with the length of barrel of 0.7-1.0 m and its inner diameter of 17-24 mm. The velocities of lexan projectiles with weight of 5-15 g were in a range of 2.5-3.5 km/s. The physical mechanisms that limit speed of throwing in railgun are discussed.

Characterization of the Electrostatic Environment of Launchers

NASA Astrophysics Data System (ADS)

Soyah, Jamila; Mantion, Pascal; Herlem, Yannick

2016-05-01

The purpose of this study was to update knowledge in characterization of the electrostatic environment of launchers in order to be able to propose reductions of design constraints.The first part of this study showed that flashover discharges are the most energetic discharges likely to occur on a launcher. They are mostly due to accumulations of charges by triboelectricity on the external surface of the launcher while flying through clouds containing a lot of small solid particles.Actually flashover discharges are mitigated by limiting the surface's resistance of dielectric materials such as thermal protection set on the external skin of the launcher, thanks to antistatic paints that avoid significant accumulations of charges.But this specified limitation leads to a lot of non- conformances during production phases and, as a result, this leads to additional costs and delays in launches campaigns. That is why on-ground tests have been defined in order to assess the accessibility of a relaxation of those specifications, which would reduce non-conformances.On-ground tests have been carried out, in the second part, on samples of thermal protections covered with antistatic paints with different degraded values of surface resistance. These tests aimed at checking in which conditions a surface discharge can occur in order to deduce a relationship between characteristics of the samples (surface resistance, half-discharge time) and the occurrence of a surface discharge, at ambient pressure and at low pressure.In the third part, in-flight experiments have been defined in order to confirm some hypotheses considered in the study and to assess some parameters in a more accurate way like the incoming charges density per surface unit or the voltage between stages when they get separated, in order to assess more accurately whether the unwinding equalization wire dedicated to maintain the electrostatic balance between stages is necessary or not.

Electromagnetic Meissner-Effect Launcher

NASA Technical Reports Server (NTRS)

Robertson, Glen A.

1990-01-01

Proposed electromagnetic Meissner-effect launching apparatus differs from previous electromagnetic launchers; no need for electromagnet coil on projectile. Result, no need for brush contacts and high-voltage commutation equipment to supply current directly to projectile coil, or for pulse circuitry to induce current in projectile coil if brush contacts not used. Compresses magnetic field surrounding rear surface of projectile, creating gradient of magnetic pressure pushing projectile forward.

Joe L. Kincheloe: Embracing criticality in science education

NASA Astrophysics Data System (ADS)

Bayne, Gillian U.

2009-09-01

This article reviews significant contributions made by Joe L. Kincheloe to critical research in science education, especially through a multimethodological, multitheoretical, and multidisciplinary informed lens that incorporates social, cultural, political, economic, and cognitive dynamics—the bricolage. Kincheloe's ideas provide for a compelling understanding of, and insights into, the forces that shape the intricacies of teaching and learning science and science education. They have implications in improving science education policies, in developing actions that challenge and cultivate the intellect while operating in ways that are more understanding of difference and are socially just.

Additive Layer Manufacturing for Launcher's Applications

NASA Astrophysics Data System (ADS)

Vilanova, J.; Romera, P.; Lasagni, F.; Zorrilla, A.; Perinan, A.

2014-06-01

In the next years the European space industry has the challenge of maintaining its competitiveness in launch vehicles (LV) production, due to the growth of competition worldwide. It has to assure its position developing new applied technologies. In this field the effort is focussed on the production of short series of customized products, like payloads, flight components or launcher parts. ALM (Additive Layer Manufacturing) could be a powerful tool that offers new competitiveness factors for this industry, comprising a set of emerging technologies that are becoming a competitor to forming, casting and machining as well as being utilised directly as a complementary alternative.Originally used for prototypes and models, now ALM becomes a very useful technology capable to fabricate functional parts for the space industrial sector. Its demands on rapid technologies are different to "earth" industries, and they aren't so easily satisfied because space is a field with different requirements depending on its application: launchers, reusable vehicles, satellites, probes, low gravity researches, manned spacecraft, or even moon and planetary exploration.This paper reports on the ALM potential applications, under ESA requirements, exploring the challenges and possibilities for its use in the launchers market, trying to answer two basic questions: the first one, whether ALM is a mature technology to be ready for its use as flight hardware; and the second one, if it can be used to reduce the product cycle, and consequently, the development, production and operational costs.

A hypervelocity launcher for simulated large fragment space debris impacts at 10 km/s

NASA Technical Reports Server (NTRS)

Tullos, R. J.; Gray, W. M.; Mullin, S. A.; Cour-Palais, B. G.

1989-01-01

The background, design, and testing of two explosive launchers for simulating large fragment space debris impacts are presented. The objective was to develop a launcher capable of launching one gram aluminum fragments at velocities of 10 km/s. The two launchers developed are based on modified versions of an explosive shaped charge, common in many military weapons. One launcher design has yielded a stable fragment launch of approximately one gram of aluminum at 8.93 km/s velocity. The other design yielded velocities in excess of 10 km/s, but failed to produce a cohesive fragment launch. This work is ongoing, and future plans are given.

Summary of EM launcher experiments performed at LLNL

NASA Astrophysics Data System (ADS)

Hawke, R. S.; Nellis, W. J.; Newman, G. H.; Rego, J.; Susoeff, A. R.

1986-11-01

Performance results for three railguns are summarized. The system used a helium gas-driven injector and railgun launcher to accelerate 1- and 4-g polycarbonate projectiles intact up to 6.6 and 3.0 km/sc, respectively. A 625 kJ capacitor bank powered the railgun, and an adjustable inductor provided pulse shaping and peak current control. Operation in hard and soft vacuum was reliably achieved. The diagnostic system measured the projectile position and launch velocity, verified that the projectile was launched intact in the desired direction, and identified system components where improvements could enhance performance. Flash X-ray radiography measured velocity and verified that projectiles were intact. Pre-launch projectile travel along the axis of the launcher without tilt was recorded with flash radiographs and impact impressions or holes in witness plates. The sysem performed as expected up to 4-5 km/sec but below expectations at higher velocities. Diagnostics suggest that the decreased performance was probably cuased by the restriking of a second arc in the breech of the railgun, which shunted the current from the propulsive arc.

11. 28'X40' original vellum, VariableAngle Launcher, 'INDEX TO Drawings' drawn ...

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

11. 28'X40' original vellum, Variable-Angle Launcher, 'INDEX TO Drawings' drawn at no scale (P.W.DWG.No. 1781). - Variable Angle Launcher Complex, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

75 FR 11899 - Certificate of Alternative Compliance for the Tugboat MR JOE

Federal Register 2010, 2011, 2012, 2013, 2014

2010-03-12

... DEPARTMENT OF HOMELAND SECURITY Coast Guard [Docket No. USCG-2010-0015] Certificate of Alternative... announces that a Certificate of Alternative Compliance was issued for the tugboat MR JOE as required by 33 U.S.C. 1605(c) and 33 CFR 81.18. DATES: The Certificate of Alternative Compliance was issued on...

Joe Louis as a Key Functionary: White Reactions toward a Black Champion.

ERIC Educational Resources Information Center

Evans, Art

1985-01-01

Investigates White Americans' responses toward Joe Louis, the Black champion. Focuses on the Louis-Schmeling heavyweight title fight of 1938 as exemplifying Louis' role as a key functionary for the American system. Argues that Louis's achieved status as the American representative fighting against Nazism did not negate Whites' negative perception…

Effect of the electric field pattern on the generation of fast electrons in front of lower hybrid launchers

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

Valade, Laurent, E-mail: laurent.valade@cea.fr; Ekedahl, Annika; Colas, Laurent

2015-12-10

The effect of the detailed waveguide spectrum on the electron acceleration has been studied for the 3.7 GHz LHCD launchers in Tore Supra, i.e. the ITER-like passive-active multijunction (PAM) launcher and the fully-active-multijunction (FAM) launcher, using test electron modelling technique. The detailed launched antenna wave spectrum is used as input to the code that computes the dynamics of the electrons in the electric field. Comparison with the LHCD launchers in EAST, operating at 2.45 GHz and 4.6 GHz, has also been made. The simulations show that the PAM-design generates lower flux of fast electrons than FAM-launchers, this could be themore » consequence of the wider waveguide of PAM-launcher (14.65 mm for Tore-Supra) than FAM-launcher (8 mm for Tore-Supra)« less

Design of Launcher Towards Spacecraft Comfort: Ariane 6 Objectives

NASA Astrophysics Data System (ADS)

Mourey, Patrick; Lambare, Hadrien; Valbuena, Matias F.

2014-06-01

Preliminary advanced studies were performed recently to select the possible concepts for a launcher that could succeed to Ariane 5. During the end of 2012 Space Ministry Conference, a configuration defining the propellant of the stages and the coarse staging ("PPH") was frozen in order to engage the preliminary selection concept studies. The first phase consisted to select the main features of the architecture in order to go deeper in the different matters or the advanced studies. The concept was selected mid of 2013.During all these phases of the preliminary project, different criteria (such as the recurring cost which is a major one) were used to quote the different concepts, among which the "payload comfort", ie the minimization of the environment generated by the launcher toward the satellites.The minimization of the environment was first expressed in term of objectives in the Mission Requirement Document (MRD) for the different mechanical environment such as quasi-static loads, dynamic loads, acoustics, shocks... Criteria such as usable volume, satellites frequency requirement and interface requirement are also expressed in the MRD.The definition of these different criteria was of course fixed taking benefit from the launcher operator experience based on a long story of dealing with spacecraft-launcher interface issues on Ariane, Soyouz and Vega. The general idea is to target improved or similar levels than those currently applicable for Ariane 5. For some environment for which a special need is anticipated from the potential end users, a special effort is aimed.The preliminary advanced study phase is currently running and has to address specific topics such as the definition of the upper part layout including geometry ofthe fairing, the definition of the launch pad with preliminary ideas to minimize acoustics and blast wave or first calculations on dimensioning dynamic load- cases such as thrust oscillations of the solid rocket motors (SRM).The present paper

Integrated plasmonic semi-circular launcher for dielectric-loaded surface plasmon-polariton waveguide.

PubMed

Li, Xiaowei; Huang, Lingling; Tan, Qiaofeng; Bai, Benfeng; Jin, Guofan

2011-03-28

A semi-circular plasmonic launcher integrated with dielectric-loaded surface plasmon-polaritons waveguide (DLSPPW) is proposed and analyzed theoretically, which can focus and efficiently couple the excited surface plasmon polaritons (SPPs) into the DLSPPW via the highly matched spatial field distribution with the waveguide mode in the focal plane. By tuning the incident angle or polarization of the illuminating beam, it is shown that the launcher may be conveniently used as a switch or a multiplexer that have potential applications in plasmonic circuitry. Furthermore, from an applicational point of view, it is analyzed how the coupling performance of the launcher can be further improved by employing multiple semi-circular slits.

Vehicle Support Posts Installation onto Mobile Launcher

NASA Image and Video Library

2017-05-11

Several heavy lift cranes surround the mobile launcher at NASA's Kennedy Space Center in Florida. Preparations are underway to lift a vehicle support post up and onto the mobile launcher for installation on the deck. A total of eight support posts will be installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff, and will drop down before vehicle liftoff to avoid contact with the flight hardware. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

VEGA, the European small launcher: Development status, future perspectives, and applications

NASA Astrophysics Data System (ADS)

Bianchi, Stefano; VEGA Integrated Project Team (IPT)

2008-07-01

This paper presents a technical and programmatic overview of the VEGA launch system program currently in development for the European Space Agency, which includes the development and qualification activities of the small launcher VEGA, of the ground infrastructure, and of all the launcher elements. Several programmatic milestones have been successfully achieved so far: most subsystems have gone through the critical design review or qualification review. The launcher system critical design review has been performed during spring 2007 as well. Concerning propulsion, all the three development models of the solid rocket motors have been successfully tested between December 2005 and December 2006. The first qualification model engine of the liquid propulsion upper module has successfully completed its firing campaign and the test campaign for the second model has just started. The liquid upper stage AVUM engine has been tested as well. The VEGA ground segment program has entered its final lapse by completing the detailed design of the various subsystems. The installation phase in the launch range site (Kourou, French Guyane) is in full swing. The integration of the Mobile Gantry, necessary to integrate the launcher, is almost completed as for the main structure.

High-Efficiency Helical Coil Electromagnetic Launcher

DTIC Science & Technology

2006-08-31

significant launcher performance benefits by super-cooling the conductor in the armature (i.e., liquid nitrogen temperatures). 20061102530 14. ABSTRACT...i.e., liquid nitrogen temperatures). 15. SUBJECT TERMS 16. SECURITY CLASSIFICATION OF: 17. LIMITATION 18. NUMBER 19a. NAME OF RESPONSIBLE PERSON...31 Liquid Nitrogen Cooled Armature

International Space Station-Based Electromagnetic Launcher for Space Science Payloads

NASA Technical Reports Server (NTRS)

Jones, Ross M.

2013-01-01

A method was developed of lowering the cost of planetary exploration missions by using an electromagnetic propulsion/launcher, rather than a chemical-fueled rocket for propulsion. An electromagnetic launcher (EML) based at the International Space Station (ISS) would be used to launch small science payloads to the Moon and near Earth asteroids (NEAs) for the science and exploration missions. An ISS-based electromagnetic launcher could also inject science payloads into orbits around the Earth and perhaps to Mars. The EML would replace rocket technology for certain missions. The EML is a high-energy system that uses electricity rather than propellant to accelerate payloads to high velocities. The most common type of EML is the rail gun. Other types are possible, e.g., a coil gun, also known as a Gauss gun or mass driver. The EML could also "drop" science payloads into the Earth's upper

Optimizing LHCD launcher using poloidal steering on Alcator C-Mod and ADX

NASA Astrophysics Data System (ADS)

Bonoli, P.; Labombard, B.; Parker, R.; Shiraiwa, S.; Wallace, G.; Wukitch, S.; Leccacorvi, R.; Vieira, R.; Alcator C-Mod Team

2014-10-01

The poloidal location of the lower hybrid current drive (LHCD) launcher has a strong influence on the trajectory and absorption of the LH wave (poloidal steering). The physics design of an additional off-midplane launcher (LH3) for Alcator C-Mod exploits this characteristic. By shifting the launcher from the mid-plane by 25cm, it is predicted to realize strong (>80%) single pass absorption localized at about r/a = 0.7 in conjunction with the mid-plane (LH2) antenna. While LH3 is a proposal to overcome the LH density limit and to provide a unique opportunity to validate LHCD simulation codes under reactor-like conditions, poloidal steering can be used more extensively by launching waves from the high field side (HFS). On ADX, the LHCD launcher is proposed to be located on the HFS. Better accessibility due to higher magnetic field allows for using lower N//, which results in higher current drive efficiency. Also a more quiescent edge plasma may reduce the effect of N// shifts due to scattering from density fluctuations. LHCD simulations for target plasmas expected on ADX, optimization of poloidal steering, and RF simulation of high field side launcher will be presented. This work supported by USDoE awards DE-FC02-99ER54512 and DE-AC02-09CH11466.

NPS Cubesat Launcher-Lite Sequencer

DTIC Science & Technology

2009-06-01

AND SUBTITLE NPS Cubesat Launcher-Lite Sequencer 6. AUTHOR(S) Harris, Anthony D. 5. FUNDING NUMBERS RSPXL 7. PERFORMING ORGANIZATION NAME(S) AND...ADDRESS(ES) Naval Postgraduate School Monterey, CA 93943-5000 8. PERFORMING ORGANIZATION REPORT NUMBER 9. SPONSORING /MONITORING AGENCY...international nanosatellite manufacturers. On April 28, 2009, Indian Space Research Organization launched 8 nanosatellites on the Polar Satellite Launch

First AFSWC Javelin Sounding Rocket On Launcher at Wallops Island.

NASA Image and Video Library

1959-07-07

Air Force Javelin Rocket on Launcher (USAF JV-1) Wallops Model D4-78 L59-5144 First AFSWC Javelin sounding rocket ready for flight test, July 7, 1959. Photograph published in A New Dimension Wallops Island Flight Test Range: The First Fifteen Years by Joseph Shortal. A NASA publication. Page 704.

Basic and applied studies of the ram accelerator as a hypervelocity projectile launcher

NASA Astrophysics Data System (ADS)

Bruckner, Adam P.; Knowlen, Carl

1993-12-01

The potential of using ram accelerator technology for an impulsive launcher of autonomously guided interceptors, such as the LEAP, has been studied during this contract period. In addition, fundamental investigations on some of the engineering issues which must be addressed for enabling ram accelerator propulsive modes to operate at 4 km/sec have been undertaken. An experimental investigation of the gas dynamic limits of ram accelerator operation has demonstrated the existence of two distinct limiting mechanisms that must be accounted for when designing projectiles for these launchers. Other experiments were conducted to make detailed pressure measurements of the flow fields at the tube walls to study the effects of projectile canting. Results from this LEAP launcher study and the experimental investigations indicate that the ram accelerator technology is well suited for applications as a transportable launcher capable of meeting the needs of theater ballistic missile defense missions.

Development of a large-area planar surface-wave plasma source with a cavity launcher driven by a 915 MHz UHF wave

NASA Astrophysics Data System (ADS)

Chang, Xijiang; Kunii, Kazuki; Liang, Rongqing; Nagatsu, Masaaki

2013-04-01

A large-area planar surface-wave plasma (SWP) source driven by a 915 MHz ultrahigh frequency (UHF) wave was developed. To avoid using large, thick dielectric plates as vacuum windows, we propose a cavity launcher consisting of a cylindrical cavity with several small quartz discs at the bottom. Three types of launchers with quartz discs located at different positions were tested to compare their plasma production efficiencies and spatial distributions of electron density. With the optimum launcher, large-area plasma discharges with a radial uniformity within ±10% were obtained in a radius of about 25-30 cm in Ar gas at 8 Pa for incident power in the range 0.5-2.5 kW. The maximum electron density and temperature were approximately (0.95-1.1) × 1011 cm-3 and 1.9-2.0 eV, respectively, as measured by a Langmuir probe located 24 cm below the bottom of the cavity launcher. Using an Ar/NH3 SWP with the optimum launcher, we demonstrated large-area amino-group surface modification of polyurethane sheets. Experimental results indicated that a uniform amino-group modification was achieved over a radius of approximately 40 cm, which is slightly larger than the radial uniformity of the electron density distribution.

Flow structure and unsteadiness in the supersonic wake of a generic space launcher

NASA Astrophysics Data System (ADS)

Schreyer, Anne-Marie; Stephan, Sören; Radespiel, Rolf

2015-11-01

At the junction between the rocket engine and the main body of a classical space launcher, a separation-dominated and highly unstable flow field develops and induces strong wall-pressure oscillations. These can excite structural vibrations detrimental to the launcher. It is desirable to minimize these effects, for which a better understanding of the flow field is required. We study the wake flow of a generic axisymmetric space-launcher model with and without propulsive jet (cold air). Experimental investigations are performed at Mach 2.9 and a Reynolds number ReD = 1 . 3 .106 based on model diameter D. The jet exits the nozzle at Mach 2.5. Velocity measurements by means of Particle Image Velocimetry and mean and unsteady wall-pressure measurements on the main-body base are performed simultaneously. Additionally, we performed hot-wire measurements at selected points in the wake. We can thus observe the evolution of the wake flow along with its spectral content. We describe the mean and turbulent flow topology and evolution of the structures in the wake flow and discuss the origin of characteristic frequencies observed in the pressure signal at the launcher base. The influence of a propulsive jet on the evolution and topology of the wake flow is discussed in detail. The German Research Foundation DFG is gratefully acknowledged for funding this research within the SFB-TR40 ``Technological foundations for the design of thermally and mechanically highly loaded components of future space transportation systems.''

Development of fiber optic sensing interrogators for launchers

NASA Astrophysics Data System (ADS)

Plattner, M. P.; Buck, T. C.; Eder, B.; Reutlinger, A.; McKenzie, I.

2017-11-01

We present our work about the development of two complementary interrogation schemes based on fiber optic sensing for the use of structural and thermal monitoring of Ariane launchers. The advantages of fiber optic sensing in particular light-weight, immunity to electromagnetic interferences and the possibility of sensor distribution along optical fibers are driving factors for utilization of this technology in space crafts [1]. The edge-filter (EF) and scanning-laser (SL) interrogators for determination of the mean wavelength of fiber Bragg grating (FBG) sensors have been implemented as two separate demonstrators. Within this paper we describe the functional principles of both interrogators. Furthermore we present test results where the developed systems have been used for readout of FBG sensors which are implemented in an Ariane structural demonstrator during thermal, thermal-vacuum and vibration tests. Functionality of both systems is demonstrated and their potential for further development towards space qualified systems is shown. Since the performance characteristics of the two systems are different from each other, they are dedicated for different sensing applications on a launcher. The EF sensor interrogator provides a sample rate of 20 kHz at a number of 4 connected sensors and supports parallel readout and aliasing free operation. Therefore it is best suited for high priority measurement. Structural monitoring which requires the acquisition of real time sensor information in order to support control of the launcher is one operation area for a future EF system. The SL interrogator provides an overall measurement rate of 1 kHz at a number of 24 connected sensors distributed on three sensor channels. It can be adapted to any sensors that have design wavelengths lying within the output spectrum of the laser diode. Furthermore the number of overall sensors to be read out with this system can be adapted easily. Thermal mapping of satellite panels is one possible

An Interview with Joe McMann: His Life Lessons

NASA Technical Reports Server (NTRS)

McMann, Joe

2011-01-01

Pica Kahn conducted "An Interview with Joe McMann: His Life Lessons" on May 23, 2011. With over 40 years of experience in the aerospace industry, McMann has gained a wealth of knowledge. Many have been interested in his biography, progression of work at NASA, impact on the U.S. spacesuit, and career accomplishments. This interview highlighted the influences and decision-making methods that impacted his technical and management contributions to the space program. McMann shared information about the accomplishments and technical advances that committed individuals can make.

High Velocity Linear Induction Launcher with Exit-Edge Compensation for Testing of Aerospace Components

NASA Technical Reports Server (NTRS)

Kuznetsov, Stephen; Marriott, Darin

2008-01-01

Advances in ultra high speed linear induction electromagnetic launchers over the past decade have focused on magnetic compensation of the exit and entry-edge transient flux wave to produce efficient and compact linear electric machinery. The paper discusses two approaches to edge compensation in long-stator induction catapults with typical end speeds of 150 to 1,500 m/s. In classical linear induction machines, the exit-edge effect is manifest as two auxiliary traveling waves that produce a magnetic drag on the projectile and a loss of magnetic flux over the main surface of the machine. In the new design for the Stator Compensated Induction Machine (SCIM) high velocity launcher, the exit-edge effect is nulled by a dual wavelength machine or alternately the airgap flux is peaked at a location prior to the exit edge. A four (4) stage LIM catapult is presently being constructed for 180 m/s end speed operation using double-sided longitudinal flux machines. Advanced exit and entry edge compensation is being used to maximize system efficiency, and minimize stray heating of the reaction armature. Each stage will output approximately 60 kN of force and produce over 500 G s of acceleration on the armature. The advantage of this design is there is no ablation to the projectile and no sliding contacts, allowing repeated firing of the launcher without maintenance of any sort. The paper shows results of a parametric study for 500 m/s and 1,500 m/s linear induction launchers incorporating two of the latest compensation techniques for an air-core stator primary and an iron-core primary winding. Typical thrust densities for these machines are in the range of 150 kN/sq.m. to 225 kN/sq.m. and these compete favorably with permanent magnet linear synchronous machines. The operational advantages of the high speed SCIM launcher are shown by eliminating the need for pole-angle position sensors as would be required by synchronous systems. The stator power factor is also improved.

Basic Research Investigations into Multimode Laser and EM Launchers for Affordable, Rapid Access to Space (Volumes 1 and 2)

DTIC Science & Technology

2010-08-31

The physics and operating principles for TEA C02 lasers can be found in several useful references (Patel, 1968; Siegman , 1986; Svelto, 1998 and...AND SUBTITLE 5a. CONTRACT NUMBER F A9550-05-1-0392 "Basic Research Investigations into Multimode Laser and 5b. GRANT NUMBER EM Launchers for...pulsed airbreathing/rocket laser propulsion. investigates the physics of laser energy deposition into stationary and hypersonic working fluids

New life for expendable launchers

NASA Astrophysics Data System (ADS)

Lopez, Ramon L.; Waskul, Greg

The U.S. commercial expendable launch vehicle (ELV) industry is examined. The use of Titan, Delta, Atlas-Centaur, and Liberty boosters to launch domestic and foreign commercial payloads is analyzed. The ELV commercialization agreement which explains the division of liability between the parties is described. Consideration is given to the competition to the U.S. industry from Europe's Ariane, China's Long March, and the Soviet Proton launchers.

EGSE (Electrical Ground Support Equipment) for ESA VEGA Launcher

NASA Astrophysics Data System (ADS)

Ferrante, M.; Ortenzi, A.; del Re, V.; Bordin, M.; Saccucci, Fr.

2004-08-01

Activities belonging to Assembly, Integration and Validation (AIV) phase of a launch vehicle are fundamental in development of a so much delicate system. The equipment used to support this long and crucial phase can be described as a set of Mechanical and Electrical Ground Support Equipment (EGSE). This paper describes the approach followed to develop such a system, and the benefits that this brings in terms of lower risk, more coordinated interfaces and improved functionality. The paper briefly outlines VEGA Electrical Ground Support Equipment major characteristics. In particular, this paper describes the EGSE design for a small launch vehicle such as VEGA. The objective of EGSE is to provide hardware and software for efficient electrical testing of either single stages and integrated launcher. The needs to develop a small launcher is a response to a Resolution in the Space Transportation Strategy adopted by the ESA Council in June 2000, aiming at: "completing, in the medium term, the range of launch services offered by the addition of European manufactured small and medium launcher, complementary to Ariane, consistent with diversified users' needs and relying on common elements, such as stages, subsystems, technologies, production facilities and operational infrastructure, thereby increasing the European launcher industry's competitiveness". Three different parts principally compose the Vega EGSE: TCS (Test Configuration System), TES (Test Execution System), PPS (Post Processing System). The TES is the part of the EGSE devoted to the tests execution; it has capabilities of immediate test data analysis, parameters monitoring and it is able to undertake pre-defined actions, in case of anomalous events happen, in order to put in safe conditions the Unity Under Test (UUT). The TES is composed of two main components: HLCS and LLCS. The HLCS is based on SCOS 2000 ESA product; it is mainly devoted to the interaction with operators. It allows loading Test Sequences and

Development of concepts for the protection of space launchers against lightning

NASA Astrophysics Data System (ADS)

Taillet, Joseph

1988-12-01

Following a review of the characteristics of lightning and the effects of lightning on space launchers, various strategies for protection against lightning are discussed. Special attention is given to the damage inflicted on the Apollo 12 and Atlas/Centaur vehicles by lightning. It is demonstrated that the protection of space launchers is best performed by the real-time observation of atmospheric discharges at high altitude by such systems as the interferometric lightning alert system, SAFIR.

Microwave impedance matching strategies of an applicator supplied by a bi-directional magnetron waveguide launcher.

PubMed

Roussy, Georges; Kongmark, Nils

2003-01-01

It is shown that a bi-directional waveguide launcher can be used advantageously for reducing the reflection coefficient mismatch of an input impedance of an applicator. In a simple bi-directional waveguide launcher, the magnetron is placed in the waveguide and generates a nominal field distribution with significant output impedance in both directions of the waveguide. If a standing wave is tolerated in the torus, which connects the launcher and the applicator, the power transfer from the magnetron to the applicator can be optimal, without using special matching devices. It is also possible to match the bi-directional launcher with two inductance stubs near the antenna of the magnetron and use them for supplying a two-input applicator without reflection.

Apparatus for and method of operating a cylindrical pulsed induction mass launcher

DOEpatents

Cowan, Jr., Maynard; Duggin, Billy W.; Widner, Melvin M.

1992-01-01

An electromagnetic cylindrical projectile mass launcher and a method of operation is provided which includes a cylindrical projectile having a conducting armature, a cylindrical barrel in which the armature is received, a plurality of electromagnetic drive coil stages, a plurality of pulse energy sources, and a pulsed power arrangement for generating magnetic pulses forming a pulsed magnetic wave along the length of the launcher barrel. The pulsed magnetic wave provides a propelling force on the projectile along the drive coil. The pulsed magnetic wave of the drive coil stages is advanced along the armature faster than the projectile to thereby generate an induced current wave in the armature. The pulsed generation of the magnetic wave minimizes electromagnetic heating of the projectile and provides for smooth acceleration of the projectile through the barrel of the launcher.

Metal vapor vacuum arc switching - Applications and results. [for launchers

NASA Technical Reports Server (NTRS)

Cope, D.; Mongeau, P.

1984-01-01

The design of metal-vapor vacuum-arc switches (MVSs) for electromagnetic launchers is discussed, and preliminary results are presented for an experimental MVS. The general principles of triggered-vacuum-gap and vacuum-interrupter MVSs are reviewed, and the requirements of electromagnetic launchers are analyzed. High-current design problems such as electrode erosion, current sharing, magnetic effects, and thermal effects are examined. The experimental MVS employs stainless-steel flanges, a glass vacuum vessel, an adjustable electrode gap, autonomous internal magnetic-field coils, and a tungsten-pin trigger assembly. Some results from tests without magnetic augmentation are presented graphically.

Integrated fiber-coupled launcher for slow plasmon-polariton waves.

PubMed

Della Valle, Giuseppe; Longhi, Stefano

2012-01-30

We propose and numerically demonstrate an integrated fiber-coupled launcher for slow surface plasmon-polaritons. The device is based on a novel plasmonic mode-converter providing efficient power transfer from the fast to the slow modes of a metallic nanostripe. Total coupling efficiency with standard single-mode fiber approaching 30% (including ohmic losses) has been numerically predicted for a 25-µm long gold-based device operating at 1.55 µm telecom wavelength.

Views of Astronaut (Col.) Joe Engle and son Jon with L-5 Piper Cub

NASA Technical Reports Server (NTRS)

1981-01-01

Views of Astronaut (Col.) Joe Engle and son Jon with L-5 Piper Cub at Clover Airport. Photos include Engle turning propeller while his son sits in the cockpit (34323); both Engle and son examine propeller (34324); Engle works on engine while his son sits in cockpit (34325).

5 Things You Didn't Know About Astronaut Joe Acaba

NASA Image and Video Library

2017-09-25

He’s been an astronaut since 2004 and launched last week with more than four months in space to his credit on two previous missions, so there’s not much more to know about Joe Acaba, right? Nope: the California native, former middle school math and science teacher and Peace Corps veteran has a few more tricks up his sleeve, and he shares five of them with you right here. _______________________________________ FOLLOW THE SPACE STATION! Twitter: https://twitter.com/Space_Station Facebook: https://www.facebook.com/ISS Instagram: https://instagram.com/iss/

Apparatus for and method of operating a cylindrical pulsed induction mass launcher

DOEpatents

Cowan, M. Jr.; Duggin, B.W.; Widner, M.M.

1992-06-30

An electromagnetic cylindrical projectile mass launcher and a method of operation is provided which includes a cylindrical projectile having a conducting armature, a cylindrical barrel in which the armature is received, a plurality of electromagnetic drive coil stages, a plurality of pulse energy sources, and a pulsed power arrangement for generating magnetic pulses forming a pulsed magnetic wave along the length of the launcher barrel. The pulsed magnetic wave provides a propelling force on the projectile along the drive coil. The pulsed magnetic wave of the drive coil stages is advanced along the armature faster than the projectile to thereby generate an induced current wave in the armature. The pulsed generation of the magnetic wave minimizes electromagnetic heating of the projectile and provides for smooth acceleration of the projectile through the barrel of the launcher. 2 figs.

Nano-Launcher Technologies, Approaches, and Life Cycle Assessment. Phase II

NASA Technical Reports Server (NTRS)

Zapata, Edgar

2014-01-01

Assist in understanding NASA technology and investment approaches, and other driving factors, necessary for enabling dedicated nano-launchers by industry at a cost and flight rate that (1) could support and be supported by an emerging nano-satellite market and (2) would benefit NASAs needs. Develop life-cycle cost, performance and other NASA analysis tools or models required to understand issues, drivers and challenges.

75 FR 11899 - Certificate of Alternative Compliance for the Offshore Supply Vessel JOE GRIFFIN

Federal Register 2010, 2011, 2012, 2013, 2014

2010-03-12

... ``Search.'' FOR FURTHER INFORMATION CONTACT: If you have questions on this notice, call CWO2 David Mauldin, District Eight, Prevention Branch, U.S. Coast Guard, telephone 504-671-2153. If you have questions on... for the offshore supply vessel JOE GRIFFIN. Full compliance with 72 COLREGS and the Inland Rules Act...

A Reflective Conversation with Joe Renzulli and Sally Reis: About the Renzulli Learning System

ERIC Educational Resources Information Center

Renzulli, Joe; Reis, Sally; Shaughnessy, Michael F

2014-01-01

In this reflective conversation, Dr. Joe Renzulli and Dr. Sally Reis respond to questions about the newly developed Renzulli Learning System. They discuss the system in light of the Schoolwide Enrichment Model (SEM) and provide information regarding its use with curriculum compacting and Renzulli's "Three Ring Conceptualization of…

Electromagnetic Meissner effect launcher

NASA Technical Reports Server (NTRS)

Robertson, Glen A. (Inventor)

1991-01-01

An electromagnetic projectile launcher provides acceleration of a superconducting projectile through the diamagnetic repulsion of the superconducting projectile. A superconducting layer is provided aft of the projectile, either directly on the projectile or on a platform upon which the projectile is carried, and a traveling magnetic field is caused to propagate along a magnetic field drive coil in which the projectile is disposed. The resulting diamagnetic repulsion between the superconducting projectile and the traveling magnetic field causes the projectile to be propelled along the coil. In one embodiment, a segmented drive coil is used to generate the traveling magnetic field.

The anti-tumour activity of rLj-RGD4, an RGD toxin protein from Lampetra japonica, on human laryngeal squamous carcinoma Hep-2 cells in nude mice.

PubMed

Shao, Fangyu; Lv, Mei; Zheng, Yuanyuan; Jiang, Junshu; Wang, Yue; Lv, Li; Wang, Jihong

2015-12-01

The objective of this study is to investigate the antiproliferative activity and mechanism of integrin-binding rLj-RGD4 in a Hep-2 human laryngeal carcinoma-bearing nude mouse model. Human laryngeal squamous carcinoma cells (Hep-2) were inoculated subcutaneously into the axilla of nude mice to generate a Hep-2 human laryngeal carcinoma-bearing nude mouse model. When the Hep-2 xenograft model was successfully established, the animals were randomly separated into five groups. Three groups were treated with different dosages of rLj-RGD4. Cisplatin was administered to the positive control group, and normal saline (NaCl) was administered to the negative control group for 3 weeks. The body weights and the survival of the nude mice were evaluated, and the volumes and weights of the solid tumours were measured. The mechanism underlying rLj-RGD4 inhibition of tumour growth in transplanted Hep-2 human laryngeal carcinoma-bearing nude mice was evaluated by haematoxylin-eosin (HE) staining, terminal deoxynucleotidyl transferase-mediated dUTP-biotin nick end labelling (TUNEL), measurement of intratumoural microvessel density (MVD), Western blotting, and quantitative reverse transcription-polymerase chain reaction (qRT-PCR). The tumour volumes and weights of the treatment groups were reduced compared with the model group, and survival times were improved by rLj-RGD4 treatment in Hep-2 human laryngeal carcinoma-bearing nude mice. The number of apoptotic Hep-2 human cells and intratumoural MVD significantly decreased after the administration of rLj-RGD4. In the xenograft tissue of animals treated with rLj-RGD4, FAK, PI3K, and Akt expression was unaltered, whereas P-FAK, P-PI3K, Bcl-2, P-Akt, and VEGF levels were down-regulated. In addition, activated caspase-3, activated caspase-9, and Bax levels were up-regulated. rLj-RGD4 exhibits potent in vivo activity and inhibits the growth of transplanted Hep-2 human laryngeal carcinoma cells in a nude mouse model. Thus, these results

Non-Rocket Missile Rope Launcher

NASA Technical Reports Server (NTRS)

Bolonkin, Alexander

2002-01-01

The method, installation, and estimation for delivering payload and missiles into outer space are presented. This method uses, in general, the engines and straight or closed-loop cables disposed on a planet surface. The installation consists of a space apparatus, power drive stations located along trajectory of the apparatus, the cables connected to the apparatus and to the power stations, a system for suspending the cable, and disconnected device. The drive stations accelerate the apparatus up to hypersonic speed. The estimations and computations show the possibility of making these projects a reality in a short period of time (see attached project: launcher for missiles and loads). The launch will be very cheap $1-$2 per LB. We need only light strong cable, which can be made from artificial fibers, whiskers, nanotubes, which exist in industry and scientific laboratories.

Post-Formalist Explanation of Academic Achievement: Exploring the Contribution of John Ogbu and Joe Kincheloe

ERIC Educational Resources Information Center

Sinha, Chetan

2016-01-01

The present paper attempts to interrogate the existing approach to understand academic achievement in the mainstream educational psychology. The paper explores the persistent question of "why academic achievement gap" in the modern society from the cultural ecological and postformalist framework of John Ogbu and Joe Kincheloe…

Methodologies for launcher-payload coupled dynamic analysis

NASA Astrophysics Data System (ADS)

Fransen, S. H. J. A.

2012-06-01

An important step in the design and verification process of spacecraft structures is the coupled dynamic analysis with the launch vehicle in the low-frequency domain, also referred to as coupled loads analysis (CLA). The objective of such analyses is the computation of the dynamic environment of the spacecraft (payload) in terms of interface accelerations, interface forces, center of gravity (CoG) accelerations as well as the internal state of stress. In order to perform an efficient, fast and accurate launcher-payload coupled dynamic analysis, various methodologies have been applied and developed. The methods are related to substructuring techniques, data recovery techniques, the effects of prestress and fluids and time integration problems. The aim of this paper was to give an overview of these methodologies and to show why, how and where these techniques can be used in the process of launcher-payload coupled dynamic analysis. In addition, it will be shown how these methodologies fit together in a library of procedures which can be used with the MSC.Nastran™ solution sequences.

Electromagnetic launchers

NASA Astrophysics Data System (ADS)

Kolm, H.; Mongeau, P.; Williams, F.

1980-09-01

Recent advances in energy storage, switching and magnet technology make electromagnetic acceleration a viable alternative to chemical propulsion for certain tasks, and a means to perform other tasks not previously feasible. Applications include the acceleration of gram-size particles for hypervelocity research and the initiation of fusion by impact, a replacement for chemically propelled artillery, the transportation of cargo and personnel over inaccessible terrain, and the launching of space vehicles to supply massive space operations, and for the disposal of nuclear waste. The simplest launcher of interest is the railgun, in which a short-circuit slide or an arc is driven along two rails by direct current. The most sophisticated studied thus far is the mass driver, in which a superconducting shuttle bucket is accelerated by a line of pulse coils energized by capacitors at energy conversion efficiencies better than 90%. Other accelerators of interest include helical, brush-commutated motors, discrete coil arc commutated drivers, flux compression momentum transformers, and various hybrid electrochemical devices.

Probing the plasma near high power wave launchers in fusion devices for static and dynamic electric fields

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

Klepper, C Christopher; Martin, Elijah H; Isler, Ralph C

2014-01-01

An exploratory study was carried out in the long-pulse tokamak Tore Supra, to determine if electric fields in the plasma around high-power, RF wave launchers could be measured with non-intrusive, passive, optical emission spectroscopy. The focus was in particular on the use of the external electric field Stark effect. The feasibility was found to be strongly dependent on the spatial extent of the electric fields and overlap between regions of strong (> 1 kV/cm) electric fields and regions of plasma particle recycling and plasma-induced, spectral line emission. Most amenable to the measurement was the RF electric field in edge plasma,more » in front of a lower hybrid heating and current drive launcher. Electric field strengths and direction, derived from fitting the acquired spectra to a model including time-dependent Stark effect and the tokamak-range magnetic field Zeeman-effect, were found to be in good agreement with full-wave modeling of the observed launcher.« less

Boulder 'Big Joe' And Surface Changes On Mars

NASA Technical Reports Server (NTRS)

1976-01-01

This pair of pictures from Viking Lander 1 at Mars' Chryse Planitia shows the only unequivocal change in the Martian surface seen by either lander. Both images show the one-meter (3-foot) high boulder nicknamed 'Big Joe.' Just to the lower right of the rock (right photo) is a small-scale slump feature. The picture at left shows a smooth, dust-covered slope; in the picture at right the top surface layer can be seen to have slipped downslope. The event occurred sometime between Oct. 4, 1976, and Jan 24, 1977. (Pictures taken before Oct. 4 do not show the slump; the first picture in which it appears was taken Jan. 24.) The surface layer, between one-half and one centimeter (one-fifth to one-third inch) thick, is apparently less cohesive than the underlying material. The layer that slipped formed a 30-centimeter-long (11.8-inch) 'tongue' of soil and a patch of exposed underlying material. The triggering mechanism for the event is unknown, but could have been temperature variations, wind gusts, a seismic event, or perhaps the lander's touchdown on July 20, 1976.

Eruptive history, petrology, and petrogenesis of the Joe Lott Tuff Member of the Mount Belknap Volcanics, Marysvale volcanic field, west-central Utah

USGS Publications Warehouse

Budding, Karin E.

1982-01-01

The Joe Lott Tuff Member of the Mount Belknap Volcanics is the largest rhyolitic ash-flow tuff sheet in the Marysvale volcanic field. It was erupted 19 m.y. ago, shortly after the changeover from intermediate-composition calc-alkalic volcanism to bimodal basalt-rhyolite volcanism. Eruption of the tuff resulted in the formation of the Mount Belknap Caldera whose pyroclastic intracaldera stratigraphy parallels that in the outflow facies. The Joe Loft Tuff Member is a composite ash-flow sheet that changes laterally from a simple cooling unit near the source to four distinct cooling units toward the distal end. The lowest of these units is the largest and most widespread; it is 64 m thick and contains a basal vitrophyre. Eruption of the lower unit led to the initial collapse of the caldera. The lower unit is followed upward by a 43 m middle unit, a 26 m pink-colored unit which is separated by a prominent air- fall layer, and a 31 m upper unit. The Joe Loft Tuff Member is an alkali rhyolite with 75.85-77.31 wt. % silica and 8.06-9.32 wt. % K2O+Na2O; the agpaitic index (Na2O+ K2O/Al2O3) is .77-.98. The tuff contains about I% phenocrysts of quartz, sanidine, oligoclase, augite, apatite, zircon, sphene, biotite, and oxidized Fe-Ti oxides. The basal vitrophyre contains accessory allanite, chevkinite, and magnesiohastingsite. The main cooling units are chemically and mineralogically zoned indicating that the magma chamber restratified prior to each major eruption. Within each of the two thickest cooling units, the mineralogy changes systematically upwards; the Or content and relative volume of sanidine decreases and An content of plagioclase increases. The basal vitrophyre of the lower unit has a bulk composition that lies in the thermal trough near the minima of Or-Ab-Q at 1 kb PH2O. Microprobe analyses of feldspar and chemical modeling on experimental systems indicate that pre-eruption temperatures were near 750?C and that the temperature increased during the eruption of

Development of explosively driven launcher for meteoroid studies

NASA Technical Reports Server (NTRS)

Baum, D. W.

1973-01-01

The results of a continuing program to develop an explosively driven 2-stage hypervelocity launcher capable of achieving velocities between 15 and 20 km/sec are described. Previous efforts had identified incomplete barrel collapse as a limiting factor in launcher performance. Correlation of experimental and computational results obtained in the present study indicate that boundary-layer gases within the barrel act to prevent complete closure. Simplified calculations suggest that in-contact explosives may have insufficient energy densities to collapse the barrel against a developed boundary layer. Higher energy densities, sufficient to produce complete closure, were obtained with the use of steel flyer plates accelerated by a phased explosive lens. However, when flat flyer plates were impacted on the barrel, the sides of the barrel were observed to rupture and leak gas prior to barrel closure. A promising solution to this problem (untested) is to produce a symmetrical collapse with a cylindrical tube around the barrel.

Distinguishing between Schemes of Mathematical Equivalence: Joe's Transition to Anticipatory Quantitative Relational Equivalence

ERIC Educational Resources Information Center

Woodward, Jerry

2016-01-01

This study examined how a child constructed a scheme (abbreviated QRE) for producing mathematical equivalence via operations on composite units between two multiplicative situations consisting of singletons and composite units. Within the context of a teaching experiment, the work of one child, Joe, was analyzed over the course of 14 teaching…

A versatile fibre optic sensor interrogation system for the Ariane Launcher based on an electro-optically tuneable laser diode

NASA Astrophysics Data System (ADS)

Plattner, M. P.; Hirth, F.; Müller, M. S.; Hoffmann, L.; Buck, T. C.; Koch, A. W.

2017-11-01

Availability of reliable flight sensor data and knowledge of the structural behaviour are essential for safe operation of the Ariane launcher. The Ariane launcher is currently monitored by hundreds of electric sensors during test and qualification. Fibre optic sensors are regarded as a potential technique to overcome limitations of recent monitoring systems for the Ariane launcher [1]. These limitations include cumbersome application of sensors and harness as well as a very limited degree of distributed sensing capability. But, in order to exploit the various advantages of fibre optic sensors (high degree of multiplexing, distributed sensing capability, lower mass impact, etc.) dedicated measurement systems have to be developed and investigated. State-of-the-art fibre optic measurement systems often use free beam setups making them bulky and sensitive to vibration impact. Therefore a new measurement system is developed as part of the ESAstudy [2].

Variable dual-frequency electrostatic wave launcher for plasma applications.

PubMed

Jorns, Benjamin; Sorenson, Robert; Choueiri, Edgar

2011-12-01

A variable tuning system is presented for launching two electrostatic waves concurrently in a magnetized plasma. The purpose of this system is to satisfy the wave launching requirements for plasma applications where maximal power must be coupled into two carefully tuned electrostatic waves while minimizing erosion to the launching antenna. Two parallel LC traps with fixed inductors and variable capacitors are used to provide an impedance match between a two-wave source and a loop antenna placed outside the plasma. Equivalent circuit analysis is then employed to derive an analytical expression for the normalized, average magnetic flux density produced by the antenna in this system as a function of capacitance and frequency. It is found with this metric that the wave launcher can couple to electrostatic modes at two variable frequencies concurrently while attenuating noise from the source signal at undesired frequencies. An example based on an experiment for plasma heating with two electrostatic waves is used to demonstrate a procedure for tailoring the wave launcher to accommodate the frequency range and flux densities of a specific two-wave application. This example is also used to illustrate a method based on averaging over wave frequencies for evaluating the overall efficacy of the system. The wave launcher is shown to be particularly effective for the illustrative example--generating magnetic flux densities in excess of 50% of the ideal case at two variable frequencies concurrently--with a high adaptability to a number of plasma dynamics and heating applications.

Energy stores and switches for rail-launcher systems

NASA Technical Reports Server (NTRS)

Weldon, W. F.; Zowarka, R. C.; Marshall, R. A.

1983-01-01

An overview of existing switch and power supply technology applicable to space launch, a new candidate pulsed power supply for Earth-to-space rail launcher duty, the inverse railgun flux compressor, and a set of switching experiments to study further the feasibility of Earth-to-space launch are discussed.

Energy stores and switches for rail-launcher systems

NASA Astrophysics Data System (ADS)

Weldon, W. F.; Zowarka, R. C.; Marshall, R. A.

An overview of existing switch and power supply technology applicable to space launch, a new candidate pulsed power supply for Earth-to-space rail launcher duty, the inverse railgun flux compressor, and a set of switching experiments to study further the feasibility of Earth-to-space launch are discussed.

Comparison between broadband Bessel beam launchers based on either Bessel or Hankel aperture distribution for millimeter wave short pulse generation.

PubMed

Pavone, Santi C; Mazzinghi, Agnese; Freni, Angelo; Albani, Matteo

2017-08-07

In this paper, a comparison is presented between Bessel beam launchers at millimeter waves based on either a cylindrical standing wave (CSW) or a cylindrical inward traveling wave (CITW) aperture distribution. It is theoretically shown that CITW launchers are better suited for the generation of electromagnetic short pulses because they maintain their performances over a larger bandwidth than those realizing a CSW aperture distribution. Moreover, the wavenumber dispersion of both the launchers is evaluated both theoretically and numerically. To this end, two planar Bessel beam launchers, one enforcing a CSW and the other enforcing a CITW aperture distribution, are designed at millimeter waves with a center operating frequency of f¯=60GHz and analyzed in the bandwidth 50 - 70 GHz by using an in-house developed numerical code to solve Maxwell's equations based on the method of moments. It is shown that a monochromatic Bessel beam can be efficiently generated by both the launchers over a wide fractional bandwidth. Finally, we investigate the generation of limited-diffractive electromagnetic pulses at millimeter waves, up to a certain non-diffractive range. Namely, it is shown that by feeding the launcher with a Gaussian short pulse, a spatially confined electromagnetic pulse can be efficiently generated in front of the launcher.

Level II scour analysis for Bridge 4 (DANVTH00010004) on Town Highway 1, crossing Joes Brook, Danville, Vermont

USGS Publications Warehouse

Flynn, Robert H.; Boehmler, Erick M.

1997-01-01

This report provides the results of a detailed Level II analysis of scour potential at structure DANVTH00010004 on Town Highway 1 crossing Joes Brook, Danville, Vermont (figures 1–8). A Level II study is a basic engineering analysis of the site, including a quantitative analysis of stream stability and scour (U.S. Department of Transportation, 1993). Results of a Level I scour investigation also are included in Appendix E of this report. A Level I investigation provides a qualitative geomorphic characterization of the study site. Information on the bridge, gleaned from Vermont Agency of Transportation (VTAOT) files, was compiled prior to conducting Level I and Level II analyses and is found in Appendix D. The site is in the New England Upland section of the New England physiographic province in northeastern Vermont. The 42.5-mi2 drainage area is in a predominantly rural and forested basin. In the vicinity of the study site, the surface cover is pasture along the upstream and downstream left banks with trees and brush along the immediate banks. The upstream and downstream right banks are forested. In the study area, Joes Brook has an incised, sinuous channel with a slope of approximately 0.02 ft/ft, an average channel top width of 68 ft and an average bank height of 5 ft. The channel bed material ranges from gravel to bedrock with a median grain size (D50) of 80.1 mm (0.263 ft). The geomorphic assessment at the time of the Level I and Level II site visit on August 22, 1995, indicated that the reach was stable. The Town Highway 1 crossing of Joes Brook is a 49-ft-long, two-lane bridge consisting of one 45-foot steel-beam span (Vermont Agency of Transportation, written communication, March 17, 1995). The opening length of the structure parallel to the bridge face is 45 ft.The bridge is supported by vertical, concrete abutments with wingwalls. The channel is skewed approximately 15 degrees to the opening and the computed opening-skew-to-roadway is 15 degrees. A scour

75 FR 47899 - Bayside Savings Bank, Port St. Joe, FL; Notice of Appointment of Receiver

Federal Register 2010, 2011, 2012, 2013, 2014

2010-08-09

... DEPARTMENT OF THE TREASURY Office of Thrift Supervision Bayside Savings Bank, Port St. Joe, FL... section 5(d)(2) of the Home Owners' Loan Act, the Office of Thrift Supervision has duly appointed the..., (OTS No. 17957) on July 30, 2010. Dated: August 2, 2010. By the Office of Thrift Supervision. Sandra E...

An Engineering Design STEM Project: T-Shirt Launcher

ERIC Educational Resources Information Center

Fantz, Todd D.; Grant, Melva R.

2013-01-01

The article offers information on making technology education students interested in science and mathematics through the use of a T-shirt launcher design project. This project was designed for junior and senior level high school students who have completed or are currently taking physics and precalculus. The project involves designing an…

Probing the plasma near high power wave launchers in fusion devices for static and dynamic electric fields (invited)

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

Klepper, C. C., E-mail: kleppercc@ornl.gov; Isler, R. C.; Biewer, T. M.

2014-11-15

An exploratory study was carried out in the long-pulse tokamak Tore Supra, to determine if electric fields in the plasma around high-power, RF wave launchers could be measured with non-intrusive, passive, optical emission spectroscopy. The focus was in particular on the use of the external electric field Stark effect. The feasibility was found to be strongly dependent on the spatial extent of the electric fields and overlap between regions of strong (>∼1 kV/cm) electric fields and regions of plasma particle recycling and plasma-induced, spectral line emission. Most amenable to the measurement was the RF electric field in edge plasma, inmore » front of a lower hybrid heating and current drive launcher. Electric field strengths and direction, derived from fitting the acquired spectra to a model including time-dependent Stark effect and the tokamak-range magnetic field Zeeman-effect, were found to be in good agreement with full-wave modeling of the observed launcher.« less

Probing the plasma near high power wave launchers in fusion devices for static and dynamic electric fields (invited).

PubMed

Klepper, C C; Martin, E H; Isler, R C; Colas, L; Goniche, M; Hillairet, J; Panayotis, S; Pegourié, B; Jacquot, J; Lotte, Ph; Colledani, G; Biewer, T M; Caughman, J B; Ekedahl, A; Green, D L; Harris, J H; Hillis, D L; Shannon, S C; Litaudon, X

2014-11-01

An exploratory study was carried out in the long-pulse tokamak Tore Supra, to determine if electric fields in the plasma around high-power, RF wave launchers could be measured with non-intrusive, passive, optical emission spectroscopy. The focus was in particular on the use of the external electric field Stark effect. The feasibility was found to be strongly dependent on the spatial extent of the electric fields and overlap between regions of strong (>∼1 kV/cm) electric fields and regions of plasma particle recycling and plasma-induced, spectral line emission. Most amenable to the measurement was the RF electric field in edge plasma, in front of a lower hybrid heating and current drive launcher. Electric field strengths and direction, derived from fitting the acquired spectra to a model including time-dependent Stark effect and the tokamak-range magnetic field Zeeman-effect, were found to be in good agreement with full-wave modeling of the observed launcher.

Note Launchers: Promoting Active Reading of Mathematics Textbooks

ERIC Educational Resources Information Center

Helms, Josh W.; Helms, Kimberly Turner

2010-01-01

Note launchers, an instructor-designed reading guide, model how to select, decide, and focus upon what textbook material is important to learn. Reading guides are specially-designed study aids that can steer students through difficult parts of assigned readings (Bean, 1996) while encouraging advance preparation. As an example of a reading guide,…

Advanced Optics for a Full Quasi-Optical Front Steering ECRH Upper Launcher for ITER

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

Moro, A.; Alessi, E.; Bruschi, A.

2009-11-26

A full quasi-optical setup for the internal optics of the Front Steering Electron Cyclotron Resonance Heating (ECRH) Upper Launcher for ITER was designed, proving to be feasible and favorable in terms of additional flexibility and cost reduction with respect to the former design. This full quasi-optical solution foresees the replacement of the mitre-bends in the final section of the launcher with dedicated free-space mirrors to realize the last changes of directions in the launcher. A description of the launcher is given and its advantages presented. The parameters of the expected output beams as well as preliminary evaluations of truncation effectsmore » with the physical optics GRASP code are shown. Moreover, a study of mitre-bends replacement with single mirrors for multiple beams is described. In principle it could allow the beams to be larger at the mirror locations (with a further decrease of the peak power density due to partial overlapping) and has the additional advantage to get a larger opening with compressed beams to avoid conflicts with side-walls port. Constraints on the setup, arising both from the resulting beam characteristics in the space of free parameters and from mechanical requirements are taken into account in the analysis.« less

5. GENERAL VIEW OF LAUNCHER BUILDING 28402 SHOWING LAUNCH DECK ...

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

5. GENERAL VIEW OF LAUNCHER BUILDING 28402 SHOWING LAUNCH DECK AT RIGHT; VIEW TO NORTHEAST. - Cape Canaveral Air Station, Launch Complex 17, Facility 28402, East end of Lighthouse Road, Cape Canaveral, Brevard County, FL

STS 2000: Structural design of the airbreathing launcher

NASA Astrophysics Data System (ADS)

Boyeldieu, E.

This paper presents a description of the structural design and the choice of materials of the different parts of the Space Transportation System 2000 (STS 2000). This launcher is one of the different concepts studied by AEROSPATIALE to evaluate its feasibility and its performance. The STS 2000 Single-Stage-To-Orbit (SSTO) is a reusable single stage launcher using airbreathing propulsion till Mach 6. This SSTO takes off horizontally using an undercarriage It takes off with a speed of 150 m/s and with an incidence angle of 12 deg. The STS 2000 flights from Mach 0.4 to Mach 3.6 using four turbo-rockets engines, from Mach 3.6 to Mach 6 using four ramjets-rockets engines and from Mach 6 to Mach 25 using four rockets engines. During its reentry, it glides from orbit to earth and it horizontally lands at the same base (KOUROU in French Guiana). The initial take-off mass is 338 metric tons. The ascent phase specification are: a maximum axial acceleration of 4 g's and a maximum dynamic pressure of 70 kPa.

56. VIEW OF LAUNCHER FROM SOUTHWEST. NITROGEN CONTROL UNIT ON ...

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

56. VIEW OF LAUNCHER FROM SOUTHWEST. NITROGEN CONTROL UNIT ON RIGHT; UMBILICAL MAST ON LEFT. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 East, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

Development of a smart IUD launcher for prevention of uterine perforation.

PubMed

Al-Ashwal, Rania Hussein; Aziz, Noor Afatin Che; Nooh, Syed Mohd

2016-10-01

Intrauterine contraception is a widely used, highly effective and reversible means of birth control. One potential disadvantage with the use of intrauterine devices (IUDs) is the risk of uterine perforation. During the process of IUD insertion, there is a possibility to perforate the wall of the uterus during which health workers might injure the fundus of the uterus, due to inadequate knowledge or insufficient training. This paper discusses the development of a smart IUD launcher insertion system that would be used to prevent perforation of the uterine wall by detecting a specific distance to the wall for the safe release of the IUD using a sensor. Several launcher prototypes were developed prior to the final version of the IUD launcher. The results from testing experiments, that have been conducted to evaluate the performance of the proposed device, show that the sensor is able to detect a distance up to 5 mm and is also capable of detecting the distance to the target even in high viscosity liquid. The developed prototype promises a solution for more accurate IUD insertion that could be used as a training module for health care providers, helping remove fear from using this long-lasting contraceptive method and promote an affordable modern contraceptive method to society.

6. VIEW OF LAUNCHER BUILDING 28402 SHOWING STEEL STAIRS LEADING ...

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

6. VIEW OF LAUNCHER BUILDING 28402 SHOWING STEEL STAIRS LEADING UP TO LAUNCH DECK; VIEW TO NORTHWEST. - Cape Canaveral Air Station, Launch Complex 17, Facility 28402, East end of Lighthouse Road, Cape Canaveral, Brevard County, FL

Optimized use of superconducting magnetic energy storage for electromagnetic rail launcher powering

NASA Astrophysics Data System (ADS)

Badel, Arnaud; Tixador, Pascal; Arniet, Michel

2012-01-01

Electromagnetic rail launchers (EMRLs) require very high currents, from hundreds of kA to several MA. They are usually powered by capacitors. The use of superconducting magnetic energy storage (SMES) in the supply chain of an EMRL is investigated, as an energy buffer and as direct powering source. Simulations of direct powering are conducted to quantify the benefits of this method in terms of required primary energy. In order to enhance further the benefits of SMES powering, a novel integration concept is proposed, the superconducting self-supplied electromagnetic launcher (S3EL). In the S3EL, the SMES is used as a power supply for the EMRL but its coil serves also as an additional source of magnetic flux density, in order to increase the thrust (or reduce the required current for a given thrust). Optimization principles for this new concept are presented. Simulations based on the characteristics of an existing launcher demonstrate that the required current could be reduced by a factor of seven. Realizing such devices with HTS cables should be possible in the near future, especially if the S3EL concept is used in combination with the XRAM principle, allowing current multiplication.

Conceptual design studies of the Electron Cyclotron launcher for DEMO reactor

NASA Astrophysics Data System (ADS)

Moro, Alessandro; Bruschi, Alex; Franke, Thomas; Garavaglia, Saul; Granucci, Gustavo; Grossetti, Giovanni; Hizanidis, Kyriakos; Tigelis, Ioannis; Tran, Minh-Quang; Tsironis, Christos

2017-10-01

A demonstration fusion power plant (DEMO) producing electricity for the grid at the level of a few hundred megawatts is included in the European Roadmap [1]. The engineering design and R&D for the electron cyclotron (EC), ion cyclotron and neutral beam systems for the DEMO reactor is being performed by Work Package Heating and Current Drive (WPHCD) in the framework of EUROfusion Consortium activities. The EC target power to the plasma is about 50 MW, in which the required power for NTM control and burn control is included. EC launcher conceptual design studies are here presented, showing how the main design drivers of the system have been taken into account (physics requirements, reactor relevant operations, issues related to its integration as in-vessel components). Different options for the antenna are studied in a parameters space including a selection of frequencies, injection angles and launch points to get the best performances for the antenna configuration, using beam tracing calculations to evaluate plasma accessibility and deposited power. This conceptual design studies comes up with the identification of possible limits, constraints and critical issues, essential in the selection process of launcher setup solution.

Technology demonstration for reusable launchers

NASA Astrophysics Data System (ADS)

Baiocco, P.; Bonnal, Ch.

2016-03-01

Reusable launchers have been studied under CNES contracts for more than 30 years, with early concepts such as STS-2000 or Oriflamme, more recently with very significant efforts devoted to Liquid Fly Back Boosters as with the Bargouzin project led with Tsniimash, TSTO with the Everest concept studied by Airbus-DS as prime contractor or the RFS Reusable First Stage concept of a large first stage associated to a cryotechnic second stage. These investigations, summarized in the first part of the paper, enabled CNES to identify clearly the technology requirements associated to reusability, as well as cost efficiency through detailed non-recurring costs and mission costs analysis. In parallel, CNES set in place development logic for sub-systems and equipment based on demonstrators, hardware test benches enabling maturation of technologies up to a TRL such that an actual development can be decided with limited risk. This philosophy has been applied so far to a large number of cases, such as TPTech and TPX for Hydrogen turbo pump, GGPX as demonstrator of innovative gas generator, HX demonstrator of modern cryotechnic upper stage with a dozen of different objectives (Thermal Protection, 20K Helium storage, measurements …). This virtuous approach, "learn as you test", is currently applied in the phased approach towards scaled down reusable booster stage, whose possibility to be used as first stage of a microlaunch vehicle is under investigation. The selected technologies allow paving the way towards reusable booster stages for Ariane 6 evolutions or main reusable stage for a further generation of heavy launchers. The paper describes the logic behind this project, together with the demonstration objectives set for the various sub-systems as well as operations.

What's Wrong with America's Playgrounds and How to Fix Them: An Interview with Joe L. Frost

ERIC Educational Resources Information Center

American Journal of Play, 2008

2008-01-01

Joe L. Frost is Parker Centennial Professor Emeritus at the University of Texas, Austin, and one of America's leading experts on play and playgrounds. In addition to having taught child development and early childhood education at Texas and several other universities, he has written or edited fifteen university-level textbooks and more than one…

Dr. Wernher Von Braun near the mobile launcher.

NASA Technical Reports Server (NTRS)

1999-01-01

Dr. George Mueller, NASA associate administrator for manned space flight, and Dr. Wernher Von Braun (right), director of the Marshall Space Flight Center, are seen near the mobile launcher carrying a 363 foot tall Saturn V space launch vehicle as the rocket is rolled from the vehicle assembly building at KSC for its three mile trip to the launch pad.

Plasma-material interaction in electrothermal and electromagnetic launchers

NASA Astrophysics Data System (ADS)

Bourham, M. A.; Gilligan, J. G.; Hankins, O. E.

1993-07-01

Various material surfaces have been exposed to high heat fluxes from 2 to 80 GW/sq m over 100 microsec duration using the electrothermal launcher, SIRENS. The vapor shield is effective in reducing the heat to the ablating surface, and the energy transmission factor through the vapor shield decreases as the incident heat flux increases. Results show good agreement with code predictions. Visible light emission spectra have been observed both in-bore and from the muzzle flash of the barrel, and from the flash of the source. Measurements of visible emission from the source indicate time averaged temperatures of 1 to 3 eV, and about 1 to 2 eV along the axis of the device, which agree with the theory and experimental measurements of the average heat flux and plasma conductivity.

The Big Deal over a Camel: What "Joe Smooth" Should Teach Us about Children's Media Research.

ERIC Educational Resources Information Center

Warren, Ron

The Joe Camel campaign by RJR Nabisco began in 1990 in an attempt to increase the brand's sagging market share. Studies showed the campaign's appeal to young children and teenagers. In the debate that followed, several children's advocates renewed their appeals for restriction on cigarette ads. A review of the literature shows that children are at…

Analysis of LH Launcher Arrays (Like the ITER One) Using the TOPLHA Code

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

Maggiora, R.; Milanesio, D.; Vecchi, G.

2009-11-26

TOPLHA (Torino Polytechnic Lower Hybrid Antenna) code is an innovative tool for the 3D/1D simulation of Lower Hybrid (LH) antennas, i.e. accounting for realistic 3D waveguides geometry and for accurate 1D plasma models, and without restrictions on waveguide shape, including curvature. This tool provides a detailed performances prediction of any LH launcher, by computing the antenna scattering parameters, the current distribution, electric field maps and power spectra for any user-specified waveguide excitation. In addition, a fully parallelized and multi-cavity version of TOPLHA permits the analysis of large and complex waveguide arrays in a reasonable simulation time. A detailed analysis ofmore » the performances of the proposed ITER LH antenna geometry has been carried out, underlining the strong dependence of the antenna input parameters with respect to plasma conditions. A preliminary optimization of the antenna dimensions has also been accomplished. Electric current distribution on conductors, electric field distribution at the interface with plasma, and power spectra have been calculated as well. The analysis shows the strong capabilities of the TOPLHA code as a predictive tool and its usefulness to LH launcher arrays detailed design.« less

Dynamic Load Predictions for Launchers Using Extra-Large Eddy Simulations X-Les

NASA Astrophysics Data System (ADS)

Maseland, J. E. J.; Soemarwoto, B. I.; Kok, J. C.

2005-02-01

Flow-induced unsteady loads can have a strong impact on performance and flight characteristics of aerospace vehicles and therefore play a crucial role in their design and operation. Complementary to costly flight tests and delicate wind-tunnel experiments, unsteady loads can be calculated using time-accurate Computational Fluid Dynamics. A capability to accurately predict the dynamic loads on aerospace structures at flight Reynolds numbers can be of great value for the design and analysis of aerospace vehicles. Advanced space launchers are subject to dynamic loads in the base region during the ascent to space. In particular the engine and nozzle experience aerodynamic pressure fluctuations resulting from massive flow separations. Understanding these phenomena is essential for performance enhancements for future launchers which operate a larger nozzle. A new hybrid RANS-LES turbulence modelling approach termed eXtra-Large Eddy Simulations (X-LES) holds the promise to capture the flow structures associated with massive separations and enables the prediction of the broad-band spectrum of dynamic loads. This type of method has become a focal point, reducing the cost of full LES, driven by the demand for their applicability in an industrial environment. The industrial feasibility of X-LES simulations is demonstrated by computing the unsteady aerodynamic loads on the main-engine nozzle of a generic space launcher configuration. The potential to calculate the dynamic loads is qualitatively assessed for transonic flow conditions in a comparison to wind-tunnel experiments. In terms of turn-around-times, X-LES computations are already feasible within the time-frames of the development process to support the structural design. Key words: massive separated flows; buffet loads; nozzle vibrations; space launchers; time-accurate CFD; composite RANS-LES formulation.

Comparative modelling of lower hybrid current drive with two launcher designs in the Tore Supra tokamak

NASA Astrophysics Data System (ADS)

Nilsson, E.; Decker, J.; Peysson, Y.; Artaud, J.-F.; Ekedahl, A.; Hillairet, J.; Aniel, T.; Basiuk, V.; Goniche, M.; Imbeaux, F.; Mazon, D.; Sharma, P.

2013-08-01

Fully non-inductive operation with lower hybrid current drive (LHCD) in the Tore Supra tokamak is achieved using either a fully active multijunction (FAM) launcher or a more recent ITER-relevant passive active multijunction (PAM) launcher, or both launchers simultaneously. While both antennas show comparable experimental efficiencies, the analysis of stability properties in long discharges suggest different current profiles. We present comparative modelling of LHCD with the two different launchers to characterize the effect of the respective antenna spectra on the driven current profile. The interpretative modelling of LHCD is carried out using a chain of codes calculating, respectively, the global discharge evolution (tokamak simulator METIS), the spectrum at the antenna mouth (LH coupling code ALOHA), the LH wave propagation (ray-tracing code C3PO), and the distribution function (3D Fokker-Planck code LUKE). Essential aspects of the fast electron dynamics in time, space and energy are obtained from hard x-ray measurements of fast electron bremsstrahlung emission using a dedicated tomographic system. LHCD simulations are validated by systematic comparisons between these experimental measurements and the reconstructed signal calculated by the code R5X2 from the LUKE electron distribution. An excellent agreement is obtained in the presence of strong Landau damping (found under low density and high-power conditions in Tore Supra) for which the ray-tracing model is valid for modelling the LH wave propagation. Two aspects of the antenna spectra are found to have a significant effect on LHCD. First, the driven current is found to be proportional to the directivity, which depends upon the respective weight of the main positive and main negative lobes and is particularly sensitive to the density in front of the antenna. Second, the position of the main negative lobe in the spectrum is different for the two launchers. As this lobe drives a counter-current, the resulting

Full Moon with Vehicle Assembly Building and Mobile Launcher

NASA Image and Video Library

2018-02-01

A full Moon sets behind the Vehicle Assembly Building and Mobile Launcher at NASA’s Kennedy Space Center in Florida. At the nation’s premier multi-user spaceport, NASA and its commercial and international partners are looking to return humans to the Moon and beyond utilizing a variety of rockets and capabilities.

Navajo Code Talker Joe Morris, Sr. shared insights from his time as a secret World War Two messenger

NASA Technical Reports Server (NTRS)

2002-01-01

Navajo Code Talker Joe Morris, Sr. shared insights from his time as a secret World War Two messenger with his audience at NASA's Dryden Flight Research Center on Nov. 26, 2002. NASA Dryden is located on Edwards Air Force Base in California's Mojave Desert.

Superconducting magnetic energy storage and superconducting self-supplied electromagnetic launcher

NASA Astrophysics Data System (ADS)

Ciceron, Jérémie; Badel, Arnaud; Tixador, Pascal

2017-10-01

Superconductors can be used to build energy storage systems called Superconducting Magnetic Energy Storage (SMES), which are promising as inductive pulse power source and suitable for powering electromagnetic launchers. The second generation of high critical temperature superconductors is called coated conductors or REBCO (Rare Earth Barium Copper Oxide) tapes. Their current carrying capability in high magnetic field and their thermal stability are expanding the SMES application field. The BOSSE (Bobine Supraconductrice pour le Stockage d'Energie) project aims to develop and to master the use of these superconducting tapes through two prototypes. The first one is a SMES with high energy density. Thanks to the performances of REBCO tapes, the volume energy and specific energy of existing SMES systems can be surpassed. A study has been undertaken to make the best use of the REBCO tapes and to determine the most adapted topology in order to reach our objective, which is to beat the world record of mass energy density for a superconducting coil. This objective is conflicting with the classical strategies of superconducting coil protection. A different protection approach is proposed. The second prototype of the BOSSE project is a small-scale demonstrator of a Superconducting Self-Supplied Electromagnetic Launcher (S3EL), in which a SMES is integrated around the launcher which benefits from the generated magnetic field to increase the thrust applied to the projectile. The S3EL principle and its design are presented. Contribution to the topical issue "Electrical Engineering Symposium (SGE 2016)", edited by Adel Razek

41. VIEW OF UMBILICAL MAST AND LAUNCH PAD FROM LAUNCHER; ...

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

41. VIEW OF UMBILICAL MAST AND LAUNCH PAD FROM LAUNCHER; SOUTH FACE OF MST IN BACKGROUND. RAIL SYSTEM FROM BASE OF MST PARALLEL TO MAST. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 East, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

63. VIEW OF FLAME BUCKET AND LAUNCHER FROM SOUTHEAST. TRICHLOROETHENE ...

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

63. VIEW OF FLAME BUCKET AND LAUNCHER FROM SOUTHEAST. TRICHLOROETHENE RECOVERY TANK LEFT OF FLAME BUCKET; LIQUID OXYGEN CATCH TANK RIGHT OF FLAME BUCKET. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 East, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

Down-Bore Two-Laser Heterodyne Velocimetry of an Implosion-Driven Hypervelocity Launcher

NASA Astrophysics Data System (ADS)

Hildebrand, Myles; Huneault, Justin; Loiseau, Jason; Higgins, Andrew J.

2015-06-01

The implosion-driven launcher uses explosives to shock-compress helium, driving well-characterized projectiles to velocities exceeding 10 km/s. The masses of projectiles range between 0.1 - 10 g, and the design shows excellent scalability, reaching similar velocities across different projectile sizes. In the past, velocity measurements have been limited to muzzle velocity obtained via a high-speed videography upon the projectile exiting the launch tube. Recently, Photonic Doppler Velocimetry (PDV) has demonstrated the ability to continuously measure in-bore velocity, even in the presence of significant blow-by of high temperature helium propellant past the projectile. While a single-laser PDV is limited to approximately 8 km/s, a two-laser PDV system is developed that uses two lasers operating near 1550 nm to provide velocity measurement capabilities up to 16 km/s. The two laser PDV system is used to obtain a continuous velocity history of the projectile throughout the entire launch cycle. These continuous velocity data are used to validate models of the launcher cycle and compare different advanced concepts aimed at increasing the projectile velocity to well beyond 10 km/s.

62. VIEW OF FLAME BUCKET BELOW LAUNCHER ON SOUTH END ...

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

62. VIEW OF FLAME BUCKET BELOW LAUNCHER ON SOUTH END OF LAUNCH PAD. FIRE SUPPRESSION EQUIPMENT RIGHT OF FLAME BUCKET. SOUTH FACE OF MST IS IN BACKGROUND. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 East, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

58. VIEW OF SOUTHWEST SIDE OF LAUNCHER FROM ABOVE. AFRAME ...

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

58. VIEW OF SOUTHWEST SIDE OF LAUNCHER FROM ABOVE. A-FRAME PIVOT POINT IN CENTER OF PHOTOGRAPH; NITROGEN CONTROL UNIT IN UPPER LEFT CORNER OF PHOTOGRAPH. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 East, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

Optimization of the ITER electron cyclotron equatorial launcher for improved heating and current drive functional capabilities

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

Farina, D.; Figini, L.; Henderson, M.

2014-06-15

The design of the ITER Electron Cyclotron Heating and Current Drive (EC H and CD) system has evolved in the last years both in goals and functionalities by considering an expanded range of applications. A large effort has been devoted to a better integration of the equatorial and the upper launchers, both from the point of view of the performance and of the design impact on the engineering constraints. However, from the analysis of the ECCD performance in two references H-mode scenarios at burn (the inductive H-mode and the advanced non-inductive scenario), it was clear that the EC power depositionmore » was not optimal for steady-state applications in the plasma region around mid radius. An optimization study of the equatorial launcher is presented here aiming at removing this limitation of the EC system capabilities. Changing the steering of the equatorial launcher from toroidal to poloidal ensures EC power deposition out to the normalized toroidal radius ρ ≈ 0.6, and nearly doubles the EC driven current around mid radius, without significant performance degradation in the core plasma region. In addition to the improved performance, the proposed design change is able to relax some engineering design constraints on both launchers.« less

Appraisal of UTIAS implosion-driven hypervelocity launchers and shock tubes.

NASA Technical Reports Server (NTRS)

Glass, I. I.

1972-01-01

A critical appraisal is made of the design, research, development, and operation of the novel UTIAS implosion-driven hypervelocity launchers and shock tubes. Explosively driven (PbN6-lead azide, PETN-pentaerythritetetranitrate) implosions in detonating stoichiometric hydrogen-oxygen mixtures have been successfully developed as drivers for hypervelocity launchers and shock tubes in a safe and reusable facility. Intense loadings at very high calculated pressures, densities, and temperatures, at the implosion center, cause severe problems with projectile integrity. Misalignment of the focal point can occur and add to the difficulty in using small caliber projectiles. In addition, the extreme driving conditions cause barrel expansion, erosion, and possible gas leakage from the base to the head of the projectile which cut the predicted muzzle velocities to half or a third of the lossless calculated values. However, in the case of a shock-tube operation these difficulties are minimized or eliminated and the possibilities of approaching Jovian reentry velocities are encouraging.

Propulsive jet simulation with air and helium in launcher wake flows

NASA Astrophysics Data System (ADS)

Stephan, Sören; Radespiel, Rolf

2017-06-01

The influence on the turbulent wake of a generic space launcher model due to the presence of an under-expanded jet is investigated experimentally. Wake flow phenomena represent a significant source of uncertainties in the design of a space launcher. Especially critical are dynamic loads on the structure. The wake flow is investigated at supersonic (M=2.9) and hypersonic (M=5.9) flow regimes. The jet flow is simulated using air and helium as working gas. Due to the lower molar mass of helium, higher jet velocities are realized, and therefore, velocity ratios similar to space launchers can be simulated. The degree of under-expansion of the jet is moderate for the supersonic case (p_e/p_∞ ≈ 5) and high for the hypersonic case (p_e/p_∞ ≈ 90). The flow topology is described by Schlieren visualization and mean-pressure measurements. Unsteady pressure measurements are performed to describe the dynamic wake flow. The influences of the under-expanded jet and different jet velocities are reported. On the base fluctuations at a Strouhal number, around St_D ≈ 0.25 dominate for supersonic free-stream flows. With air jet, a fluctuation-level increase on the base is observed for Strouhal numbers above St_D ≈ 0.75 in hypersonic flow regime. With helium jet, distinct peaks at higher frequencies are found. This is attributed to the interactions of wake flow and jet.

ICPSU Install onto Mobile Launcher - Preps for Lift

NASA Image and Video Library

2018-03-15

The mobile launcher (ML) tower is lit up before early morning sunrise at NASA's Kennedy Space Center in Florida. Preparations are underway to lift and install the Interim Cryogenic Propulsion Stage Umbilical (ICPSU) at about the 240-foot-level on the tower. The last of the large umbilicals to be installed, the ICPSU will provide super-cooled hydrogen and liquid oxygen to the Space Launch System (SLS) rocket's interim cryogenic propulsion stage, or upper stage, at T-0 for Exploration Mission-1. The umbilical will supply fuel, oxidizer, gaseous helium, hazardous gas leak detection, electrical commodities and environment control systems to the upper stage of the SLS rocket during launch. Exploration Ground Systems is overseeing installation of the umbilicals on the ML.

A socio-economic impact assessment of the European launcher sector

NASA Astrophysics Data System (ADS)

Monte, Luca del; Scatteia, Luigi

2017-08-01

In a context where the economic strains are challenging European policies as well as the very fabric of governmental contributions to public life, innovation and efficacy of public policy in research are called upon to support growth in Europe and to sustain employment and entrepreneurial capacities. Governments need evidence that the investments in space, while providing strategic tools to implement sovereign policies, create jobs and build the competitive European economy of the future. This is particularly true when the decisions at stake have a potential bearing on the future of the European space sector for at least the next 30 years, as it has been the case for the ESA Council at ministerial level meeting in December 2014. On that occasion, Ministers took the decision to start the development of a new Ariane 6 launcher and Vega evolutions having a critical bearing on the Member States' strategic industrial capabilities and on the sustainability of the European guaranteed access to space. Given the importance of the subject, and following similar studies undertaken in the past for e.g. the Ariane 1-4 programme, the Agency has requested an independent consulting team to perform a dedicated study to assess ex-post the direct, indirect and induced socio-economic impacts of the Ariane 5 programme (mid-term evaluation) and of the Vega programme (early evaluation) globally, at European level, and within the economies and industries of each ESA Member State. This paper presents the assessment of the socio-economic impacts allowing the evaluation of the return on public investments in launchers through ESA in a wider perspective, going beyond the purely economic terms. The scope of the assessment covered in total approximately 25 ESA programmatic and activity lines and 30,000 commitments from 1986 to end 2012. In the framework of the study, the economic impact of the European launcher programmes is measured through a GDP impact defined as the straight economic

A fermented bean flour extract downregulates LOX-1, CHOP and ICAM-1 in HMEC-1 stimulated by ox-LDL.

PubMed

Gabriele, Morena; Pucci, Laura; La Marca, Margherita; Lucchesi, Daniela; Della Croce, Clara Maria; Longo, Vincenzo; Lubrano, Valter

2016-01-01

This study focused on an extract from fermented flour from the Lady Joy variety of the common bean Phaseolus vulgaris . The extract, Lady Joy lysate (Lys LJ), is enriched in antioxidant compounds during the fermentation. We assessed it for its protective effect on endothelial cells treated with oxidized-LDL (ox-LDL). The oxidative stress was determined by measuring the contents of thiobarbituric acid-reactive substances and reactive oxygen metabolites. ICAM-1, ET-1 and IL-6 concentrations were assessed using ELISA. LOX-1 and CHOP expression were analyzed using both quantitative RT-PCR and ELISA or western blotting. Ox-LDL treatment induced significant oxidative stress, which was strongly reduced by pre-treatment with the extract. The ox-LDL exposure significantly enhanced ICAM-1, IL-6 and ET-1 levels over basal levels. Lys LJ pre-treatment exerted an inhibitory effect on ox-LDL-induced endothelial activation with ICAM-1 levels comparable to those for the untreated cells. IL-6 and ET-1 production, although reduced, was still significantly higher than for the control. Both LOX-1 and CHOP expression were upregulated after ox-LDL exposure, but this effect was significantly decreased after Lys LJ pre-treatment. Lys LJ alone did not alter the ICAM-1, IL-6 and ET-1 concentrations or CHOP expression, but it did significantly lower the LOX-1 protein level. Our data suggest that Lys LJ is an effective antioxidant that is able to inhibit the oxidation process, but that it is only marginally active against inflammation and ET-1 production in HMEC-1 exposed to ox-LDL.

Rocket launcher: A novel reduction technique for posterior hip dislocations and review of current literature.

PubMed

Dan, Michael; Phillips, Alfred; Simonian, Marcus; Flannagan, Scott

2015-06-01

We provide a review of literature on reduction techniques for posterior hip dislocations and present our experience with a novel technique for the reduction of acute posterior hip dislocations in the ED, 'the rocket launcher' technique. We present our results with six patients with prosthetic posterior hip dislocation treated in our rural ED. We recorded patient demographics. The technique involves placing the patient's knee over the shoulder, and holding the lower leg like a 'Rocket Launcher' allow the physician's shoulder to work as a fulcrum, in an ergonomically friendly manner for the reducer. We used Fisher's t-test for cohort analysis between reduction techniques. Of our patients, the mean age was 74 years (range 66 to 85 years). We had a 83% success rate. The one patient who the 'rocket launcher' failed in, was a hemi-arthroplasty patient who also failed all other closed techniques and needed open reduction. When compared with Allis (62% success rate), Whistler (60% success rate) and Captain Morgan (92% success rate) techniques, there was no statistically significant difference in the successfulness of the reduction techniques. There were no neurovascular or periprosthetic complications. We have described a reduction technique for posterior hip dislocations. Placing the patient's knee over the shoulder, and holding the lower leg like a 'Rocket Launcher' allow the physician's shoulder to work as a fulcrum, thus mechanically and ergonomically superior to standard techniques. © 2015 Australasian College for Emergency Medicine and Australasian Society for Emergency Medicine.

Passive Active Multi-Junction 3, 7 GHZ launcher for Tore-Supra Long Pulse Experiments. Manufacturing Process and Tests

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

Guilhem, D.; Achard, J.; Bertrand, B.

2009-11-26

The design and the fabrication of a new Lower Hybrid (LH) actively cooled antenna based on the passive active concept is a part of the CIMES project (Components for the Injection of Mater and Energy in Steady-state). The major objectives of Tore-Supra program is to achieve 1000 s pulses with this LH launcher, by coupling routinely >3 MW of LH wave at 3.7 GHz to the plasma with a parallel index n{sub ||} = 1.7 {sup {+-}}{sup 0.2}. The launcher is on its way to achieve its validation tests--low power Radio Frequency (RF) measurements, vacuum and hydraulic leak tests--and willmore » be installed and commissioned on plasma during the fall of 2009.« less

Small ICBM area narrowing report. Volume 2. Hard mobile launcher at minuteman facilities basing mode

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

Not Available

The purpose of this report is to identify those areas that could potentially support deployment of the Small Intercontinental Ballistic Missile (ICBM) utilizing basing modes presently considered viable: the Hard Mobile Launcher in Random Movement, the Hard Mobile Launcher at Minuteman Facilities, and the Hard Silo in Patterned Array. Specifically, this report describes the process and the rationale supporting the application of Exclusionary and Evaluative Criteria and lists those locations that were eliminated through the application of these criteria. The remaining locations will be the subject of further investigations.

Predicting Trainability of M1 Crewmen

DTIC Science & Technology

1982-10-01

Load Main Gun Clear Main Gun LOAD/UNLOAD M250 GRENADE LAUNCHER ON M1 TANK* Load Grenade Launcher Unload Grenade Launcher PREPARE GUNNER’S STATION...Clear Main Gun LOAD/UNLOAD M250 GRENADE LAUNCHER ON Ml TANK* Load Grenade Launcher Unload Grenade Lauacher PREPARE GUNNER’S STATION FOR OPERATION ON Ml

13. Photocopy of drawing of missile launcher from 'Procedures and ...

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

13. Photocopy of drawing of missile launcher from 'Procedures and Drills for the NIKE Ajax System,' Department of the Army Field Manual, FM-44-80 from Institute for Military History, Carlisle Barracks, Carlisle, PA, 1956 - NIKE Missile Battery PR-79, East Windsor Road south of State Route 101, Foster, Providence County, RI

Crew Access Arm Installation onto Mobile Launcher

NASA Image and Video Library

2018-02-26

With a control panel visible in the foreground, a technician begins installation of the Orion crew access arm (CAA) to the mobile launcher (ML) tower at NASA's Kennedy Space Center in Florida. NASA's Exploration Ground Systems organization has been overseeing installation of umbilicals and other launch accessories on the 380-foot-tall ML in preparation for stacking the first launch of the Space launch System, or SLS, rocket with an Orion spacecraft. The CAA is designed to rotate from its retracted position and line up with Orion's crew hatch providing entry for astronauts and technicians.

Crew Access Arm Installation onto Mobile Launcher

NASA Image and Video Library

2018-02-26

Viewed from the 274-foot level mobile launcher (ML), technicians help install the Orion crew access arm (CAA) to the tower at NASA's Kennedy Space Center in Florida. NASA's Exploration Ground Systems organization has been overseeing installation of umbilicals and other launch accessories on the 380-foot-tall ML in preparation for stacking the first launch of the Space launch System (SLS), rocket with an Orion spacecraft. The CAA is designed to rotate from its retracted position and line up with Orion's crew hatch providing entry for astronauts and technicians.

ICPSU Install onto Mobile Launcher - Preps for Lift

NASA Image and Video Library

2018-03-15

Construction workers with JP Donovan attach a heavy-lift crane to the Interim Cryogenic Propulsion Stage Umbilical (ICPSU) to prepare for lifting and installation on the mobile launcher (ML) tower at NASA's Kennedy Space Center in Florida. The last of the large umbilicals to be installed, the ICPSU will provide super-cooled hydrogen and liquid oxygen to the Space Launch System (SLS) rocket's interim cryogenic propulsion stage, or upper stage, at T-0 for Exploration Mission-1. The umbilical will be located at about the 240-foot-level of the ML and will supply fuel, oxidizer, gaseous helium, hazardous gas leak detection, electrical commodities and environment control systems to the upper stage of the SLS rocket during launch. Exploration Ground Systems is overseeing installation of the umbilicals on the ML.

Millimeter wave experiment of ITER equatorial EC launcher mock-up

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

Takahashi, K.; Oda, Y.; Kajiwara, K.

2014-02-12

The full-scale mock-up of the equatorial launcher was fabricated in basis of the baseline design to investigate the mm-wave propagation properties of the launcher, the manufacturability, the cooling line management, how to assemble the components and so on. The mock-up consists of one of three mm-wave transmission sets and one of eight waveguide lines can deliver the mm-wave power. The mock-up was connected to the ITER compatible transmission line and the 170GHz gyrotron and the high power experiment was carried out. The measured radiation pattern of the beam at the location of 2.5m away from the EL mock-up shows themore » successful steering capability of 20°∼40°. It was also revealed that the radiated profile at both steering and fixed focusing mirror agreed with the calculation. The result also suggests that some unwanted modes are included in the radiated beam. Transmission of 0.5MW-0.4sec and of 0.12MW-50sec were also demonstrated.« less

Brand logo recognition by children aged 3 to 6 years. Mickey Mouse and Old Joe the Camel.

PubMed

Fischer, P M; Schwartz, M P; Richards, J W; Goldstein, A O; Rojas, T H

1991-12-11

Little is known about the influence of advertising on very young children. We, therefore, measured product logo recognition by subjects aged 3 to 6 years. Children were instructed to match logos with one of 12 products pictured on a game board. Twenty-two logos were tested, including those representing children's products, adult products, and those for two popular cigarette brands (Camel and Marlboro). Preschools in Augusta and Atlanta, Ga. A convenience sample of 229 children attending preschool. The children demonstrated high rates of logo recognition. When analyzed by product category, the level of recognition of cigarette logos was intermediate between children's and adult products. The recognition rates of The Disney Channel logo and Old Joe (the cartoon character promoting Camel cigarettes) were highest in their respective product categories. Recognition rates increased with age. Approximately 30% of 3-year-old children correctly matched Old Joe with a picture of a cigarette compared with 91.3% of 6-year-old children. Very young children see, understand, and remember advertising. Given the serious health consequences of smoking, the exposure of children to environmental tobacco advertising may represent an important health risk and should be studied further.

Flood of October 8, 1962, on Bachman Branch and Joes Creek at Dallas, Texas

USGS Publications Warehouse

Ruggles, Frederick H.

1966-01-01

This report presents hydrologic data that enable the user to define areas susceptible to flooding and to evaluate the flood hazard along Bachman Branch and Joes Creek. The data provide a technical basis for making sound decisions concerning the use of flood-plain lands. The report will be useful for preparing building and zoning regulations, locating waste disposal facilities, purchasing unoccupied land, developing recreational areas, and managing surface water in relation to ground-water resources. This is one of the series of reports delineating the flood hazard on streams in the Dallas area.

Impact of Launchers on the Environment in French Guiana

NASA Astrophysics Data System (ADS)

Richard, S.; Chemoul, B.

2012-01-01

The main combustion products of the Ariane 5 solid rocket boosters are alumina and chlorhyde gas. When the launcher lift off the significant concentrations of this components are around the launch zone. We use samplers to evaluate the concentrations of this two elements. To optimize the localisation of the samplers we use a model to obtain the projected traces of the combustion cloud according to meteorological data (software sarrim). During the first seconds of takes 1000 m3 of water flood the base right to decrease the acoustic vibration. The major parts of the pollutants fall close to the launch zone and acidic cloud is formed. Once having stabilized the cloud begins diluting, it is subjected to the influence of the different layers of wind. To measure air quality we use first continuous analysers, secondly containers with distilled water to sample the acidic particles from the cloud. We also monitor the physicochemical quality of water in a river near the launch zone, the impact of the combustion products on vegetation, the aquatic fauna. Noise and vibrations are also measured. For terrestrial fauna like birds, we monitor the general population and a colony of wade. The most important colony of this species is located on the base : around 75% of the population of the French Guiana. We use also a new protocol to estimate the impact of launch by measuring the thickness of eggshells. We use research results which show that calcium can be replaced by alumina. When the thickness of eggshells is thin, the reproduction can be affected. For each measurement campaign, we have more than 100 sites and around 600 samples. The results shows that the land around the space centre is like a natural refuge. The impact of the launches is low, hunting is forbidden and security personal controls the zone base is a protected zone. The space centre is now a natural wildlife refuge. For the two new launchers, Vega and Soyuz, we will also monitor the environmental impact of the launch

Shuttle Hitchhiker Experiment Launcher System (SHELS)

NASA Technical Reports Server (NTRS)

Daelemans, Gerry

1999-01-01

NASA's Goddard Space Flight Center Shuttle Small Payloads Project (SSPP), in partnership with the United States Air Force and NASA's Explorer Program, is developing a Shuttle based launch system called SHELS (Shuttle Hitchhiker Experiment Launcher System), which shall be capable of launching up to a 400 pound spacecraft from the Shuttle cargo bay. SHELS consists of a Marman band clamp push-plate ejection system mounted to a launch structure; the launch structure is mounted to one Orbiter sidewall adapter beam. Avionics mounted to the adapter beam will interface with Orbiter electrical services and provide optional umbilical services and ejection circuitry. SHELS provides an array of manifesting possibilities to a wide range of satellites.

Turbojet-type engines for the airbreathing propulsion of reusable winged launchers

NASA Astrophysics Data System (ADS)

Duparcq, J. L.; Hermant, E.; Scherrer, D.

Combined propulsion systems for hypersonic application have become new challenges for industrial and research organizations. In France, SNECMA and SEP, which have just joined together for a common effort on hypersonics within Hyperspace, and ONERA have been involved, under CNES (French space agency) contracts, in the assessment of new propulsion concepts for reusable winged launchers (SSTO or TSTO). As potential solutions for the airbreathing propulsion, some turbojet-type engines are presented: —the twin spool turbojet or turbofan with reheat —the turbojet with reheat —the twin-duct turbojet ramjet —the precooled turbojet with reheat. All these engines have been sized for a flight Mach number under seven with a cryogenic fuel (liquid hydrogen). Mainly due to total temperature and pressure encountered along the trajectory, the systems will have to withstand severe physical constraints. Coupled with performance and size requirements, like specific thrust and maximum air capture area, these operating conditions have been taken into account in order to select each engine cycle and technical arrangement. Performance and mass criteria make it possible to compare these systems and to emphasize their distinctive features among the propulsion concepts envisioned for the future reusable winged launchers (including airbreathing combined engines under study in France). The first step of the final selection, leading to the best adaptation between the engine and the vehicle, will then be tackled. This will be particularly enhanced by the analysis of potential advantages or technical difficulties, like thrust-to-weight ratio or needs of variable geometry and heat exchangers. The twin-duct turbojet ramjet, for example, is probably one of the best candidates for the first stages of propulsion of a reusable winged launcher.

Crew Access Arm Installation onto Mobile Launcher

NASA Image and Video Library

2018-02-26

Viewed from the 274-foot level mobile launcher (ML), the Orion crew access arm (CAA) is beign installed on the tower. The CAA will support the Space launch System (SLS) rocket at NASA's Kennedy Space Center in Florida. NASA's Exploration Ground Systems organization has been overseeing installation of umbilicals and other launch accessories on the 380-foot-tall ML in preparation for stacking the first launch of the Space launch System, or SLS, rocket with an Orion spacecraft. The CAA is designed to rotate from its retracted position and line up with Orion's crew hatch providing entry for astronauts and technicians.

Crew Access Arm Installation onto Mobile Launcher

NASA Image and Video Library

2018-02-26

Viewed from the 274-foot level mobile launcher (ML), a technician begins installation of the Orion crew access arm (CAA) to the tower. The CAA will support the Space launch System (SLS) rocket at NASA's Kennedy Space Center in Florida. NASA's Exploration Ground Systems organization has been overseeing installation of umbilicals and other launch accessories on the 380-foot-tall ML in preparation for stacking the first launch of the Space launch System, or SLS, rocket with an Orion spacecraft. The CAA is designed to rotate from its retracted position and line up with Orion's crew hatch providing entry for astronauts and technicians.

Crew Access Arm Installation onto Mobile Launcher

NASA Image and Video Library

2018-02-26

Viewed from the 274-foot level mobile launcher (ML), a crane positions the Orion crew access arm (CAA) so it can be attached to the tower that will support the Space launch System (SLS) rocket at NASA's Kennedy Space Center in Florida. NASA's Exploration Ground Systems organization has been overseeing installation of umbilicals and other launch accessories on the 380-foot-tall ML in preparation for stacking the first launch of the SLS, rocket with an Orion spacecraft. The CAA is designed to rotate from its retracted position and line up with Orion's crew hatch providing entry for astronauts and technicians.

Crew Access Arm Installation onto Mobile Launcher

NASA Image and Video Library

2018-02-24

At NASA's Kennedy Space Center in Florida, the Orion crew access arm (CAA) is lifted and attached to the Mobile Launcher (ML). The arm is installed at about the 274-foot level on the ML tower. NASA's Exploration Ground Systems organization has been overseeing installation of umbilicals and other launch accessories on the 380-foot-tall ML in preparation for stacking the first launch of the Space launch System (SLS), rocket with an Orion spacecraft. The CAA is designed to rotate from its retracted position and line up with Orion's crew hatch providing entry for astronauts and technicians.

Crew Access Arm Install on Mobile Launcher

NASA Image and Video Library

2018-02-24

At NASA's Kennedy Space Center in Florida, the Orion crew access arm (CAA) is lifted and attached to the Mobile Launcher (ML). The arm is installed at about the 274-foot level on the ML tower. NASA's Exploration Ground Systems organization has been overseeing installation of umbilicals and other launch accessories on the 380-foot-tall ML in preparation for stacking the first launch of the Space launch System (SLS), rocket with an Orion spacecraft. The CAA is designed to rotate from its retracted position and line up with Orion's crew hatch providing entry for astronauts and technicians.

Crew Access Arm Installation onto Mobile Launcher

NASA Image and Video Library

2018-02-26

At NASA's Kennedy Space Center in Florida, a crane positions the Orion crew access arm (CAA) so it can be attached to the mobile launcher (ML). The arm will be installed at about the 274-foot level on the ML tower. NASA's Exploration Ground Systems organization has been overseeing installation of umbilicals and other launch accessories on the 380-foot-tall ML in preparation for stacking the first launch of the Space launch System (SLS), rocket with an Orion spacecraft. The CAA is designed to rotate from its retracted position and line up with Orion's crew hatch providing entry for astronauts and technicians.

Crew Access Arm Installation onto Mobile Launcher

NASA Image and Video Library

2018-02-26

At NASA's Kennedy Space Center in Florida, a crane lifts the Orion crew access arm (CAA) so it can be attached to the mobile launcher (ML). The arm will be installed at about the 274-foot level on the ML tower. NASA's Exploration Ground Systems organization has been overseeing installation of umbilicals and other launch accessories on the 380-foot-tall ML in preparation for stacking the first launch of the Space launch System (SLS), rocket with an Orion spacecraft. The CAA is designed to rotate from its retracted position and line up with Orion's crew hatch providing entry for astronauts and technicians.

Design of a high power TM01 mode launcher optimized for manufacturing by milling

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

Dal Forno, Massimo

2016-12-15

Recent research on high-gradient rf acceleration found that hard metals, such as hard copper and hard copper-silver, have lower breakdown rate than soft metals. Traditional high-gradient accelerating structures are manufactured with parts joined by high-temperature brazing. The high temperature used in brazing makes the metal soft; therefore, this process cannot be used to manufacture structures out of hard metal alloys. In order to build the structure with hard metals, the components must be designed for joining without high-temperature brazing. One method is to build the accelerating structures out of two halves, and join them by using a low-temperature technique, atmore » the symmetry plane along the beam axis. The structure has input and output rf power couplers. We use a TM01 mode launcher as a rf power coupler, which was introduced during the Next Linear Collider (NLC) work. The part of the mode launcher will be built in each half of the structure. This paper presents a novel geometry of a mode launcher, optimized for manufacturing by milling. The coupler was designed for the CERN CLIC working frequency f = 11.9942 GHz; the same geometry can be scaled to any other frequency.« less

Numerical predictions of EML (electromagnetic launcher) system performance

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

Schnurr, N.M.; Kerrisk, J.F.; Davidson, R.F.

1987-01-01

The performance of an electromagnetic launcher (EML) depends on a large number of parameters, including the characteristics of the power supply, rail geometry, rail and insulator material properties, injection velocity, and projectile mass. EML system performance is frequently limited by structural or thermal effects in the launcher (railgun). A series of computer codes has been developed at the Los Alamos National Laboratory to predict EML system performance and to determine the structural and thermal constraints on barrel design. These codes include FLD, a two-dimensional electrostatic code used to calculate the high-frequency inductance gradient and surface current density distribution for themore » rails; TOPAZRG, a two-dimensional finite-element code that simultaneously analyzes thermal and electromagnetic diffusion in the rails; and LARGE, a code that predicts the performance of the entire EML system. Trhe NIKE2D code, developed at the Lawrence Livermore National Laboratory, is used to perform structural analyses of the rails. These codes have been instrumental in the design of the Lethality Test System (LTS) at Los Alamos, which has an ultimate goal of accelerating a 30-g projectile to a velocity of 15 km/s. The capabilities of the individual codes and the coupling of these codes to perform a comprehensive analysis is discussed in relation to the LTS design. Numerical predictions are compared with experimental data and presented for the LTS prototype tests.« less

Laboratory spectroscopy and space astrophysics: A tribute to Joe Reader

NASA Astrophysics Data System (ADS)

Leckrone, David S.

2013-07-01

Beginning with the launch of the Copernicus Satellite in 1973, and continuing with the International Ultraviolet Explorer (IUE), and the state-of-the-art spectrographs on the Hubble Space Telescope (GHRS, FOS, STIS and COS), astrophysics experienced dramatic advancements in capabilities to study the composition and physical properties of planets, comets, stars, nebulae, the interstellar medium, galaxies, quasars and the intergalactic medium at visible and ultraviolet wavelengths. It became clear almost immediately that the available atomic data needed to calibrate and quantitatively analyze these superb spectroscopic observations, obtained at great cost from space observatories, was not up to that task. Over the past 3+ decades, Joe Reader and his collaborators at NIST have provided, essentially "on demand", laboratory observations and analyses of extraordinary quality to help astrophysicists extract the maximum possible physical understanding of objects in the cosmos from their space observations. This talk is one scientist's grateful retrospective about these invaluable collaborations.

Advanced concepts. [specific impulse, mass drivers, electromagnetic launchers, and the rail gun

NASA Technical Reports Server (NTRS)

Banks, B. A.

1980-01-01

The relative strengths of those interactions which enable propulsive forces are listed as well as the specific impulse of various propellants. Graphics show the linear synchronous motor of the mass driver, the principle of the direct current electromagnetic launcher, and the characteristics of the rail gun.

Vehicle Support Posts Installation at Mobile Launcher

NASA Image and Video Library

2017-05-11

Construction workers at the Mobile Launcher at NASA's Kennedy Space Center in Florida, prepare to install vehicle support posts. A total of eight support posts are being installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

Crew Access Arm Installation onto Mobile Launcher

NASA Image and Video Library

2018-02-24

At NASA's Kennedy Space Center in Florida, a crane is prepared to lift the Orion crew access arm (CAA) so it can be attached to the mobile launcher (ML). The arm will be installed at about the 274-foot level on the ML tower. NASA's Exploration Ground Systems organization has been overseeing installation of umbilicals and other launch accessories on the 380-foot-tall ML in preparation for stacking the first launch of the Space launch System, or SLS, rocket with an Orion spacecraft. The CAA is designed to rotate from its retracted position and line up with Orion's crew hatch providing entry for astronauts and technicians.

Crew Access Arm Installation onto Mobile Launcher

NASA Image and Video Library

2018-02-26

At NASA's Kennedy Space Center in Florida, technicians assist as a crane lifts the Orion crew access arm (CAA) so it can be attached to the mobile launcher (ML). The arm will be installed at about the 274-foot level on the ML tower. NASA's Exploration Ground Systems organization has been overseeing installation of umbilicals and other launch accessories on the 380-foot-tall ML in preparation for stacking the first launch of the Space launch System (SLS), rocket with an Orion spacecraft. The CAA is designed to rotate from its retracted position and line up with Orion's crew hatch providing entry for astronauts and technicians.

Crew Access Arm Installation onto Mobile Launcher

NASA Image and Video Library

2018-02-26

At NASA's Kennedy Space Center in Florida, a crane begins lifting the Orion crew access arm (CAA) so it can be attached to the mobile launcher (ML). The arm will be installed at about the 274-foot level on the ML tower. NASA's Exploration Ground Systems organization has been overseeing installation of umbilicals and other launch accessories on the 380-foot-tall ML in preparation for stacking the first launch of the Space launch System (SLS), rocket with an Orion spacecraft. The CAA is designed to rotate from its retracted position and line up with Orion's crew hatch providing entry for astronauts and technicians.

A coaxial radial opening switch for a distributed-energy-store rail launcher

NASA Astrophysics Data System (ADS)

Upshaw, J. L.; Zowarka, R. C.

1984-03-01

The design, fabrication, and initial testing results for a coaxial radial opening switch for a distributed-energy-store rail launcher are presented. In this nonarcing switch, the voltage needed to transfer current to the rail launcher is generated in a fixed resistor sized to absorb the energy required to accomplish the switching. The coaxial geometry consisting of concentric rings allowed flexibility in defining the conductive and resistive portions of the switch, and also provided tight coupling by minimizing the inductance of the current path between the charging path and the load path to minimize the energy absorption requirements. The resistive portion of the switch is composed of a series of stacked circular steel ring laminations. Switching is completed in three intervals through radial actuation. The switch parts were machined from ETP 110 electrical tough pitch copper plate, 2000 series aluminum plate, and close-tolerance standed GFR epoxy. Current may be transferred at levels less than 20 kA.

Identification and characterisation of ROS modulator 1 in Lampetra japonica.

PubMed

Zhao, Chunhui; Feng, Bin; Cao, Ying; Xie, Peng; Xu, Jie; Pang, Yue; Liu, Xin; Li, Qingwei

2013-08-01

Reactive oxygen species (ROS) are a heterogeneous group of highly reactive molecules that oxidise targets in biological systems. ROS are also considered important immune regulators. In this study, we identified a homologue of reactive oxygen species modulator 1 (Romo1) in the Japanese lamprey (Lampetra japonica). The L japonica Romo1 (Lj-Romo1) gene shares high sequence homology with the Romo1 genes of jawed vertebrates. Real-time quantitative PCR demonstrated the wide distribution of Lj-Romo1 in lamprey tissues. Furthermore, after the lampreys were stimulated with lipopolysaccharide (LPS), the level of Lj-Romo1 mRNA was markedly up-regulated in the liver, gill, kidney, and intestine tissues. Lj-Romo1 was localised to the mitochondria and has the capacity to increase the ROS level in cells. The results obtained in the present study will help us to understand the roles of Romo1 in ROS production and innate immune responses in jawless vertebrates. Copyright © 2013 Elsevier Ltd. All rights reserved.

Demonstration of a high speed hybrid electrical and optical sensing system for next generation launcher applications

NASA Astrophysics Data System (ADS)

Ibrahim, Selwan K.; O'Dowd, John A.; Honniball, Arthur; Bessler, Vivian; Farnan, Martin; O'Connor, Peter; Melicher, Milos; Gleeson, Danny

2017-09-01

The Future Launchers Preparatory Programme (FLPP) supported by the European Space Agency (ESA) has a goal of developing various launch vehicle system concepts and identifying the technologies required for the design of Europe's Next-Generation Launcher (NGL) while maintaining competitiveness on the commercial market. Avionics fiber optic sensing technology was investigated as part of the FLPP programme. Here we demonstrate and evaluate a high speed hybrid electrical/optical data acquisition system based on commercial off the shelf (COTS) technology capable of acquiring data from traditional electrical sensors and optical Fibre Bragg Grating (FBG) sensors. The proposed system consists of the KAM-500 data acquisition system developed by Curtis-Wright and the I4 tunable laser based fiber optic sensor interrogator developed by FAZ Technology. The key objective was to demonstrate the capability of the hybrid system to acquire data from traditional electrical sensors used in launcher applications e.g. strain, temperature and pressure in combination with optical FBG sensors, as well as data delivery to spacecraft avionics systems. The KAM-500 was configured as the main acquisition unit (MAU) and provided a 1 kHz sampling clock to the I4 interrogator that was configured as the secondary acquisition unit (SAU) to synchronize the data acquisition sample rate between both systems. The SAU acquired data from an array of optical FBG sensors, while the MAU data acquisition system acquired data from the electrical sensors. Data acquired from the optical sensors was processed by the FAZ I4 interrogation system and then encapsulated into UDP/IP packets and transferred to the KAM-500. The KAM-500 encapsulated the optical sensor data together with the data acquired from electrical sensors and transmitted the data over MIL-STD-1553 and Ethernet data interface. The temperature measurements resulted in the optical and electrical sensors performing on a par with each other, with all

LauncherOne: Virgin Orbit's Dedicated Launch Vehicle for Small Satellites & Impact to the Space Enterprise Vision

NASA Astrophysics Data System (ADS)

Vaughn, M.; Kwong, J.; Pomerantz, W.

Virgin Orbit is developing a space transportation service to provide an affordable, reliable, and responsive dedicated ride to orbit for smaller payloads. No longer will small satellite users be forced to make a choice between accepting the limitations of flight as a secondary payload, paying dramatically more for a dedicated launch vehicle, or dealing with the added complexity associated with export control requirements and international travel to distant launch sites. Virgin Orbit has made significant progress towards first flight of a new vehicle that will give satellite developers and operators a better option for carrying their small satellites into orbit. This new service is called LauncherOne (See the figure below). LauncherOne is a two stage, air-launched liquid propulsion (LOX/RP) rocket. Air launched from a specially modified 747-400 carrier aircraft (named “Cosmic Girl”), this system is designed to conduct operations from a variety of locations, allowing customers to select various launch azimuths and increasing available orbital launch windows. This provides small satellite customers an affordable, flexible and dedicated option for access to space. In addition to developing the LauncherOne vehicle, Virgin Orbit has worked with US government customers and across the new, emerging commercial sector to refine concepts for resiliency, constellation replenishment and responsive launch elements that can be key enables for the Space Enterprise Vision (SEV). This element of customer interaction is being led by their new subsidiary company, VOX Space. This paper summarizes technical progress made on LauncherOne in the past year and extends the thinking of how commercial space, small satellites and this new emerging market can be brought to bear to enable true space system resiliency.

BIO 300, a nanosuspension of genistein, mitigates pneumonitis/fibrosis following high-dose radiation exposure in the C57L/J murine model.

PubMed

Jackson, Isabel L; Zodda, Andrew; Gurung, Ganga; Pavlovic, Radmila; Kaytor, Michael D; Kuskowski, Michael A; Vujaskovic, Zeljko

2017-12-01

BIO 300 nanosuspension (Humanetics Corporation) is being developed as a medical countermeasure (MCM) for the mitigation of the delayed effects of acute radiation exposure, specifically pneumonitis and fibrosis of the lung. The objective of this study was to determine the best dose and treatment duration of BIO 300 to mitigate lung injury and improve the likelihood for survival in C57L/J mice exposed to whole thorax lung irradiation (WTLI). Age- and sex-matched C57L/J mice received a single dose of 11.0 or 12.5 Gy WTLI. BIO 300 (200 or 400 mg·kg -1 , oral gavage) was administered daily starting 24 h post-exposure for a duration of 2, 4, 6 or, in some cases, 10 weeks. Non-treated controls were included for comparison in both sexes. Animals were observed daily for signs of major morbidity. Respiratory function was assessed biweekly. Lungs were collected, weighed and paraffin embedded for histological evaluation post mortem. BIO 300 administered at an oral dose of 400 mg·kg -1 for 4 to 6 weeks starting 24 h post-WTLI reduced morbidity associated with WTLI. The improvement in survival correlated with reduced respiratory frequency and enhanced pause. The irradiated lungs of mice treated with BIO 300 (400 mg·kg -1 ) for 4 to 6 weeks displayed less morphological damage and airway loss due to oedema, congestion and fibrotic scarring than the untreated, irradiated controls. BIO 300 is a promising MCM candidate to mitigate pneumonitis/fibrosis when administered daily for 4-6 weeks starting 24 h post-exposure. © 2017 The British Pharmacological Society.

Interaction of the electron density fluctuations with electron cyclotron waves from the equatorial launcher in ITER

NASA Astrophysics Data System (ADS)

Snicker, A.; Poli, E.; Maj, O.; Guidi, L.; Köhn, A.; Weber, H.; Conway, G. D.; Henderson, M.; Saibene, G.

2018-01-01

We present a numerical investigation of electron cyclotron beams interacting with electron density fluctuations in the ITER 15 MA H-mode scenario. In particular, here we study how the beam from the equatorial launcher, which shall be utilized to influence the sawtooth instability, is affected by the fluctuations. Moreover, we present the theory and first estimates of the power that is scattered from the injected O-mode to a secondary X-mode in the presence of the fluctuations. It is shown that for ITER parameters the scattered power stays within acceptable limits and broadening of the equatorial beams is less than those from the upper launcher.

An Interview with Joe McMann: Lessons Learned from Fifty Years of Observing Hardware and Human Behavior

NASA Technical Reports Server (NTRS)

McMann, Joe

2011-01-01

Pica Kahn conducted "An Interview with Joe McMann: Lessons Learned in Human and Hardware Behavior" on August 16, 2011. With more than 40 years of experience in the aerospace industry, McMann has gained a wealth of knowledge. This presentation focused on lessons learned in human and hardware behavior. During his many years in the industry, McMann observed that the hardware development process was intertwined with human influences, which impacted the outcome of the product.

Optimization of the launcher ascent trajectory leading to the global optimum without any initialization: the breakthrough of the Hamilton-Jacobi-Bellman approach

NASA Astrophysics Data System (ADS)

Bourgeois, E.; Bokanowski, O.; Zidani, H.; Désilles, A.

2018-06-01

The resolution of the launcher ascent trajectory problem by the so-called Hamilton-Jacobi-Bellman (HJB) approach, relying on the Dynamic Programming Principle, has been investigated. The method gives a global optimum and does not need any initialization procedure. Despite these advantages, this approach is seldom used because of the dicculties of computing the solution of the HJB equation for high dimension problems. The present study shows that an eccient resolution is found. An illustration of the method is proposed on a heavy class launcher, for a typical GEO (Geostationary Earth Orbit) mission. This study has been performed in the frame of the Centre National d'Etudes Spatiales (CNES) Launchers Research & Technology Program.

Crew Access Arm Installation onto Mobile Launcher

NASA Image and Video Library

2018-02-24

Under the watchful eye of technicians and engineers, a crane is prepared to lift the Orion crew access arm (CAA) so it can be attached to the mobile launcher (ML) at NASA's Kennedy Space Center in Florida. The arm will be installed at about the 274-foot level on the ML tower. NASA's Exploration Ground Systems organization has been overseeing installation of umbilicals and other launch accessories on the 380-foot-tall ML in preparation for stacking the first launch of the Space launch System, or SLS, rocket with an Orion spacecraft. The CAA is designed to rotate from its retracted position and line up with Orion's crew hatch providing entry for astronauts and technicians.

Crew Access Arm Installation onto Mobile Launcher

NASA Image and Video Library

2018-02-26

Under the watchful eye of technicians and engineers, a crane begins lifting the Orion crew access arm (CAA) so it can be attached to the mobile launcher (ML) at NASA's Kennedy Space Center in Florida. The arm will be installed at about the 274-foot level on the ML tower. NASA's Exploration Ground Systems organization has been overseeing installation of umbilicals and other launch accessories on the 380-foot-tall ML in preparation for stacking the first launch of the Space launch System (SLS), rocket with an Orion spacecraft. The CAA is designed to rotate from its retracted position and line up with Orion's crew hatch providing entry for astronauts and technicians.

Crew Access Arm Installation onto Mobile Launcher

NASA Image and Video Library

2018-02-26

Seen to the right of the iconic Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, a crane positions the Orion crew access arm (CAA) so it can be attached to the mobile launcher (ML). The arm will be installed at about the 274-foot level on the ML tower. NASA's Exploration Ground Systems organization has been overseeing installation of umbilicals and other launch accessories on the 380-foot-tall ML in preparation for stacking the first launch of the Space launch System (SLS), rocket with an Orion spacecraft. The CAA is designed to rotate from its retracted position and line up with Orion's crew hatch providing entry for astronauts and technicians.

Analysis of Poloidal Asymmetric Density Behaviors in SOL Induced by 4.6-GHz Lower Hybrid Launcher Power in EAST

NASA Astrophysics Data System (ADS)

Li, Y. C.; Ding, B. J.; Li, M. H.; Wang, M.; Liu, L.; Wang, X. J.; Xu, H. D.; Shan, J. F.; Liu, F. K.

2018-02-01

On the experimental advanced superconducting tokamak (EAST), a series of striations, including a few strong emissivity striations and several low emissivity striations, were observed in front of the 4.6-GHz lower hybrid (LH) launcher with the visible video camera for the LH power discharge. These striations indicate that LH may create significant poloidal scrape-off layer (SOL) density profile asymmetries in front of the LH launcher. These poloidal asymmetric density behaviors are further confirmed with the edge density measured by two Langmuir probes installed at the top and bottom of the LH launcher. The measured density depends on LH power injection and magnetic field direction. A 2D diffusive convective model was used to study the mechanisms of the observed striations and poloidal asymmetric density. The simulation results qualitatively match with the measured density, indicating these poloidal asymmetric effects are ascribed to the LHW-induced E LH × B t drift.

BCM Search Launcher--an integrated interface to molecular biology data base search and analysis services available on the World Wide Web.

PubMed

Smith, R F; Wiese, B A; Wojzynski, M K; Davison, D B; Worley, K C

1996-05-01

The BCM Search Launcher is an integrated set of World Wide Web (WWW) pages that organize molecular biology-related search and analysis services available on the WWW by function, and provide a single point of entry for related searches. The Protein Sequence Search Page, for example, provides a single sequence entry form for submitting sequences to WWW servers that offer remote access to a variety of different protein sequence search tools, including BLAST, FASTA, Smith-Waterman, BEAUTY, PROSITE, and BLOCKS searches. Other Launch pages provide access to (1) nucleic acid sequence searches, (2) multiple and pair-wise sequence alignments, (3) gene feature searches, (4) protein secondary structure prediction, and (5) miscellaneous sequence utilities (e.g., six-frame translation). The BCM Search Launcher also provides a mechanism to extend the utility of other WWW services by adding supplementary hypertext links to results returned by remote servers. For example, links to the NCBI's Entrez data base and to the Sequence Retrieval System (SRS) are added to search results returned by the NCBI's WWW BLAST server. These links provide easy access to auxiliary information, such as Medline abstracts, that can be extremely helpful when analyzing BLAST data base hits. For new or infrequent users of sequence data base search tools, we have preset the default search parameters to provide the most informative first-pass sequence analysis possible. We have also developed a batch client interface for Unix and Macintosh computers that allows multiple input sequences to be searched automatically as a background task, with the results returned as individual HTML documents directly to the user's system. The BCM Search Launcher and batch client are available on the WWW at URL http:@gc.bcm.tmc.edu:8088/search-launcher.html.

Workers in the VAB move sling into place to lift Columbia to mobile launcher

NASA Technical Reports Server (NTRS)

1982-01-01

Workers in the Vehicle Assembly Building (VAB) move a specially-built sling into place to lift Orbiter Columbia from the transfer aisle to the mobile launcher platform (27015); Columbia is lifted from the floor of the VAB transfer aisle (27016).

The Hazard of an Explosion of the ARIANE 5 Launcher- The Risks for the Astronauts Sitting on the Ejector Seats

DTIC Science & Technology

1990-08-30

velocities (a first approach). In a first step, we <<construct>> the launcher. A launcher is composed of structures (propellant reservoirs for example... structures and the unburnt propellant included in the cone C, are all part of the fragments’ <<environment>> (Fig. 3). Its D mass W,is concentrated on the...dynamic fluid- structure interactions*. Computer Methods in Applied Mechanics And Engineering 33 (1982) 689-723. 1151 M. ECK, M.MUKUNDA : <<Predicting

Optimization of the propulsion for multistage solid rocket motor launchers

NASA Astrophysics Data System (ADS)

Calabro, M.; Dufour, A.; Macaire, A.

2002-02-01

Some tools focused on a rapid multidisciplinary optimization capability for multistage launch vehicle design were developed at EADS-LV. These tools may be broken down into two categories, those related to propulsion design optimization and a computer code devoted to trajectories and under constraints optimization. Both are linked in order to obtain optimal vehicle design after an iterative process. After a description of the two categories tools, an example of application is given on a small space launcher.

Vehicle Support Posts Installation onto Mobile Launcher

NASA Image and Video Library

2017-05-25

Construction workers on the deck of the mobile launcher at NASA's Kennedy Space Center in Florida, prepare to install a vehicle support post. A total of eight support posts are being installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff, and will drop down before vehicle liftoff to avoid contact with the flight hardware. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

Vehicle Support Posts Installation onto Mobile Launcher

NASA Image and Video Library

2017-05-25

At NASA's Kennedy Space Center in Florida, construction workers on the deck of the mobile launcher install the final four vehicle support posts. A total of eight support posts are being installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff, and will drop down before vehicle liftoff to avoid contact with the flight hardware. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

Vehicle Support Posts Installation onto Mobile Launcher

NASA Image and Video Library

2017-05-25

At NASA's Kennedy Space Center in Florida, the final four vehicle support posts are being installed on the deck of the mobile launcher. A total of eight support posts are being installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff, and will drop down before vehicle liftoff to avoid contact with the flight hardware. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

Vehicle Support Posts Installation onto Mobile Launcher

NASA Image and Video Library

2017-05-11

Four vehicle support posts have been installed on the deck of the mobile launcher at NASA's Kennedy Space Center in Florida. A total of eight support posts will be installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff, and will drop down before vehicle liftoff to avoid contact with the flight hardware. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

Vehicle Support Posts Installation onto Mobile Launcher

NASA Image and Video Library

2017-05-11

Construction workers on the deck of the mobile launcher at NASA's Kennedy Space Center in Florida, prepare a platform for installation of a vehicle support post. A total of eight support posts will be installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff, and will drop down before vehicle liftoff to avoid contact with the flight hardware. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

Vehicle Support Posts Installation onto Mobile Launcher

NASA Image and Video Library

2017-05-11

A vehicle support post will lifted up by crane and lowered onto the deck of the mobile launcher at NASA's Kennedy Space Center in Florida. A total of eight support posts will be installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff, and will drop down before vehicle liftoff to avoid contact with the flight hardware. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

Vehicle Support Posts Installation onto Mobile Launcher

NASA Image and Video Library

2017-05-11

In view are three vehicle support posts installed on the deck of the mobile launcher at NASA's Kennedy Space Center in Florida. A total of eight support posts will be installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff, and will drop down before vehicle liftoff to avoid contact with the flight hardware. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

Mission-Based Analyses of Armor Training Requirements. Volume 7. Training Objectives for the XM1 Loader

DTIC Science & Technology

1982-04-01

the gas particulate filter system MODULE L: OPERATE THE M250 BRENADE LAUNCHER 1L. Load the grenade launcher 2L. Unload the grenade launcher MODULE M...k Initia~ng Stimulus: Thei (11rdLr from the T.C. to load the M250 .p grenade launcher. J ACTION Loader will: 1L. Load the grenade launcher. 2L. Unload

The Aurora space launcher concept

NASA Astrophysics Data System (ADS)

Kopp, Alexander; Stappert, Sven; Mattsson, David; Olofsson, Kurt; Marklund, Erik; Kurth, Guido; Mooij, Erwin; Roorda, Evelyne

2017-11-01

This paper gives an overview about the Aurora reusable space launcher concept study that was initiated in late-2015/early-2016. Within the Aurora study, several spaceplane-like vehicle configurations with different geometries, propulsion systems and mission profiles will be designed, investigated and evaluated with respect to their technical and economic feasibility. The first part of this paper will discuss the study logic and the current status of the Aurora studies and introduces the first vehicle configurations and their system design status. As the identification of highly efficient structural designs is of particular interest for Aurora, the structural design and analysis approach will be discussed in higher level of detail. A special design feature of the Aurora vehicle configurations is the utilization of the novel thin-ply composite material technology for structural mass reductions. Therefore, the second part of this paper will briefly discuss this technology and investigate the application and potential mass savings on vehicle level within simplified structural analysis studies. The results indicate that significant mass savings could be possible. Finally, an outlook on the next steps is provided.

The Aurora space launcher concept

NASA Astrophysics Data System (ADS)

Kopp, Alexander; Stappert, Sven; Mattsson, David; Olofsson, Kurt; Marklund, Erik; Kurth, Guido; Mooij, Erwin; Roorda, Evelyne

2018-06-01

This paper gives an overview about the Aurora reusable space launcher concept study that was initiated in late-2015/early-2016. Within the Aurora study, several spaceplane-like vehicle configurations with different geometries, propulsion systems and mission profiles will be designed, investigated and evaluated with respect to their technical and economic feasibility. The first part of this paper will discuss the study logic and the current status of the Aurora studies and introduces the first vehicle configurations and their system design status. As the identification of highly efficient structural designs is of particular interest for Aurora, the structural design and analysis approach will be discussed in higher level of detail. A special design feature of the Aurora vehicle configurations is the utilization of the novel thin-ply composite material technology for structural mass reductions. Therefore, the second part of this paper will briefly discuss this technology and investigate the application and potential mass savings on vehicle level within simplified structural analysis studies. The results indicate that significant mass savings could be possible. Finally, an outlook on the next steps is provided.

The Jupiter ONERA Electron (JOE) and Jupiter ONERA Proton (JOP) specification models

NASA Astrophysics Data System (ADS)

Bourdarie, S.; Sicard-Piet, A.

2008-09-01

The use of recent improvement in the understanding of the Jovian radiation belt structure has allowed to develop a more accurate engineering model of the Jovian electron and proton radiation belts. The basic idea was to combine the results of the Salammbô code when available (for proton and electron species) with the Divine and Garret model 1983 and/or with GIRE. The advantage of such an approach was that the resulting model is global in term of spatial and energy coverage, is optimised inside Europa orbit (the Divine and Garret model is not accurate inside Io orbit due to poor in-situ data there - note that inside Io is the region where ionizing radiation fluxes are maximum) and take advantage of the two models. The resulting JOE-JOP models will be presented, pro and cons will be listed and commented. Finally future plans to upgrade these models will be given.

A Monte Carlo Analysis for Collision Risk Assessment on Vega Launcher Payloads and LARES Satellite

NASA Astrophysics Data System (ADS)

Sindoni, G.; Ciufolini, I.; Battie, F.

2016-03-01

This work has been developed in the framework of the LARES mission of the Italian Space Agency (ASI). The LARES satellite has been built to test, with high accuracy, the frame-dragging effect predicted by the theory of General Relativity, specifically the Lense-Thirring drag of its node. LARES was the main payload in the qualification flight of the European Space Agency launcher VEGA. A concern arose about the possibility of an impact between the eight secondary payloads among themselves, with LARES and with the last stage of the launcher (AVUM). An impact would have caused failure on the payloads and the production of debris in violation of the space debris mitigation measures established internationally. As an additional contribution, this study allowed the effect of the payload release on the final manoeuvers of the AVUM to be understood.

Preliminary analysis of space mission applications for electromagnetic launchers

NASA Technical Reports Server (NTRS)

Miller, L. A.; Rice, E. E.; Earhart, R. W.; Conlon, R. J.

1984-01-01

The technical and economic feasibility of using electromagnetically launched EML payloads propelled from the Earth's surface to LEO, GEO, lunar orbit, or to interplanetary space was assessed. Analyses of the designs of rail accelerators and coaxial magnetic accelerators show that each is capable of launching to space payloads of 800 KG or more. A hybrid launcher in which EML is used for the first 2 KM/sec followed by chemical rocket stages was also tested. A cost estimates study shows that one to two EML launches per day are needed to break even, compared to a four-stage rocket. Development models are discussed for: (1) Earth orbital missions; (2) lunar base supply mission; (3) solar system escape mission; (4) Earth escape missions; (5) suborbital missions; (6) electromagnetic boost missions; and (7) space-based missions. Safety factors, environmental impacts, and EML systems analysis are discussed. Alternate systems examined include electrothermal thrustors, an EML rocket gun; an EML theta gun, and Soviet electromagnetic accelerators.

British government, industry agree to fund Hotel launcher studies

NASA Astrophysics Data System (ADS)

Brown, D. A.

1986-02-01

A program status assessment is presented for the horizontal takeoff and landing 'Hotol' single-stage-to-orbit space launcher, for which parallel, two-year airframe and propulsion system proof-of-concept studies have been approved. A two-year initial development program for the airframe would be followed by a four-year development and manufacturing phase that would begin upon the propulsion system concept's successful demonstration. Flight trials could begin in 1996. A number of significant modifications have already been made to the initial design concept, such as to the foreplanes, afterbody, engine intake, and orbital control system.

Engineers Jim Murray and Joe Pahle prepare a deployable, inflatable wing technology demonstrator exp

NASA Technical Reports Server (NTRS)

2001-01-01

Engineers Jim Murray and Joe Pahle prepare a deployable, inflatable wing technology demonstrator experiment flown by the NASA Dryden Flight Research Center, Edwards, California. The inflatable wing project represented a basic flight research effort by Dryden personnel. Three successful flights of the I2000 inflatable wing aircraft occurred. During the flights, the team air-launched the radio-controlled (R/C) I2000 from an R/C utility airplane at an altitude of 800-1000 feet. As the I2000 separated from the carrier aircraft, its inflatable wings 'popped-out,' deploying rapidly via an on-board nitrogen bottle. The aircraft remained stable as it transitioned from wingless to winged flight. The unpowered I2000 glided down to a smooth landing under complete control.

Vehicle Support Posts Installation onto Mobile Launcher

NASA Image and Video Library

2017-05-11

A construction worker on the deck of the mobile launcher welds a portion of a platform for installation of a vehicle support post at NASA's Kennedy Space Center in Florida. A total of eight support posts will be installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff, and will drop down before vehicle liftoff to avoid contact with the flight hardware. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

Infrared tracker for a portable missile launcher

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

Carlson, J.J.

1993-07-13

An infrared beam tracker is described for arrangement to a housing that is unitary with a portable missile launcher, comprising: a rotating beam splitter positioned to intercept the infrared beam passing a first portion of the beam through the beam splitter along a first direction and reflecting the remaining portion along a different direction; a first infrared detector for receiving the beam reflected portion from the beam splitter and produce electric signals responsive thereto; a second infrared detector for receiving the beam portion that passes through the beam splitter and providing electric signals responsive thereto; and means interconnected to themore » first and second infrared detectors and responsive to the electric signals generated by said detectors for determining errors in missile flight direction and communicating course correction information to the missile.« less

Vehicle Support Posts Installation onto Mobile Launcher

NASA Image and Video Library

2017-05-11

Construction workers on the deck of the mobile launcher prepare the platforms for installation of vehicle support posts at NASA's Kennedy Space Center in Florida. At left, four of the support posts are installed. A total of eight support posts will be installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff, and will drop down before vehicle liftoff to avoid contact with the flight hardware. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

High-Efficiency Helical Coil Electromagnetic Launcher and High Power Hall-Effect Switch

DTIC Science & Technology

2008-02-29

also given that demonstrate significant launcher performance benefits by super-cooling the armature (i.e., using liquid nitrogen ). 14. ABSTRACT... liquid nitrogen temperatures). A computer model for a magnetically-controlled Hall-effect switch is developed. The model is constructed in the PSpice...of super-cooling is demonstrated with liquid nitrogen cooling and indicates super-cooled EML operation is desirable if cryo-cooling is practical for

Post Flight Presentation with Joe Acaba and Mark Vande Hei at NASA HQ

NASA Image and Video Library

2018-06-15

During a post flight presentation June 15 at NASA Headquarters, astronauts Joe Acaba and Mark Vande Hei shared their experiences living and working on the International Space Station as members of the Expedition 53/54 crew. Acaba and Vande Hei launched to the space station aboard a Soyuz spacecraft from Baikonur Cosmodrome in Kazakhstan on Sept. 12, 2017 and returned to Earth on Feb. 27, 2018 after 168 days in space. During their time on the station, they conducted research studying bacteria, looked at the manufacture of fiber optics in microgravity, measured the total amount of sunlight Earth received, gathered data on space debris in low-Earth orbit, and studied self-replicating materials. They also conducted spacewalks and encouraged students around the world to pursue STEM careers and kicked off YES, the Year of Education on Station.

Quantity Distance for the Kennedy Space Center Vehicle Assembly Building for Solid Propellant Fueled Launchers

NASA Technical Reports Server (NTRS)

Stover, Steven; Diebler, Corey; Frazier, Wayne

2006-01-01

The NASA KSC VAB was built to process Apollo launchers in the 1960's, and later adapted to process Space Shuttles. The VAB has served as a place to assemble solid rocket motors (5RM) and mate them to the vehicle's external fuel tank and Orbiter before rollout to the launch pad. As Space Shuttle is phased out, and new launchers are developed, the VAB may again be adapted to process these new launchers. Current launch vehicle designs call for continued and perhaps increased use of SRM segments; hence, the safe separation distances are in the process of being re-calculated. Cognizant NASA personnel and the solid rocket contractor have revisited the above VAB QD considerations and suggest that it may be revised to allow a greater number of motor segments within the VAB. This revision assumes that an inadvertent ignition of one SRM stack in its High Bay need not cause immediate and complete involvement of boosters that are part of a vehicle in adjacent High Bay. To support this assumption, NASA and contractor personnel proposed a strawman test approach for obtaining subscale data that may be used to develop phenomenological insight and to develop confidence in an analysis model for later use on full-scale situations. A team of subject matter experts in safety and siting of propellants and explosives were assembled to review the subscale test approach and provide options to NASA. Upon deliberations regarding the various options, the team arrived at some preliminary recommendations for NASA.

Properties of water along the liquid-vapor coexistence curve via molecular dynamics simulations using the polarizable TIP4P-QDP-LJ water model

PubMed Central

Bauer, Brad A.; Patel, Sandeep

2009-01-01

We present an extension of the TIP4P-QDP model, TIP4P-QDP-LJ, that is designed to couple changes in repulsive and dispersive nonbond interactions to changes in polarizability. Polarizability is intimately related to the dispersion component of classical force field models of interactions, and we explore the effect of incorporating this connection explicitly on properties along the liquid-vapor coexistence curve of pure water. Parametrized to reproduce condensed-phase liquid water properties at 298 K, the TIP4P-QDP-LJ model predicts density, enthalpy of vaporization, self-diffusion constant, and the dielectric constant at ambient conditions to about the same accuracy as TIP4P-QDP but shows remarkable improvement in reproducing the liquid-vapor coexistence curve. TIP4P-QDP-LJ predicts critical constants of Tc=623 K, ρc=0.351 g∕cm3, and Pc=250.9 atm, which are in good agreement with experimental values of Tc=647.1 K, ρc=0.322 g∕cm3, and Pc=218 atm, respectively. Applying a scaling factor correction (obtained by fitting the experimental vapor-liquid equilibrium data to the law of rectilinear diameters using a three-term Wegner expansion) the model predicts critical constants (Tc=631 K and ρc=0.308 g∕cm3). Dependence of enthalpy of vaporization, self-diffusion constant, surface tension, and dielectric constant on temperature are shown to reproduce experimental trends. We also explore the interfacial potential drop across the liquid-vapor interface for the temperatures studied. The interfacial potential demonstrates little temperature dependence at lower temperatures (300–450 K) and significantly enhanced (exponential) dependence at elevated temperatures. Terms arising from the decomposition of the interfacial potential into dipole and quadrupole contributions are shown to monotonically approach zero as the temperature approaches the critical temperature. Results of this study suggest that self-consistently treating the coupling of phase

Properties of water along the liquid-vapor coexistence curve via molecular dynamics simulations using the polarizable TIP4P-QDP-LJ water model.

PubMed

Bauer, Brad A; Patel, Sandeep

2009-08-28

We present an extension of the TIP4P-QDP model, TIP4P-QDP-LJ, that is designed to couple changes in repulsive and dispersive nonbond interactions to changes in polarizability. Polarizability is intimately related to the dispersion component of classical force field models of interactions, and we explore the effect of incorporating this connection explicitly on properties along the liquid-vapor coexistence curve of pure water. Parametrized to reproduce condensed-phase liquid water properties at 298 K, the TIP4P-QDP-LJ model predicts density, enthalpy of vaporization, self-diffusion constant, and the dielectric constant at ambient conditions to about the same accuracy as TIP4P-QDP but shows remarkable improvement in reproducing the liquid-vapor coexistence curve. TIP4P-QDP-LJ predicts critical constants of T(c)=623 K, rho(c)=0.351 g/cm(3), and P(c)=250.9 atm, which are in good agreement with experimental values of T(c)=647.1 K, rho(c)=0.322 g/cm(3), and P(c)=218 atm, respectively. Applying a scaling factor correction (obtained by fitting the experimental vapor-liquid equilibrium data to the law of rectilinear diameters using a three-term Wegner expansion) the model predicts critical constants (T(c)=631 K and rho(c)=0.308 g/cm(3)). Dependence of enthalpy of vaporization, self-diffusion constant, surface tension, and dielectric constant on temperature are shown to reproduce experimental trends. We also explore the interfacial potential drop across the liquid-vapor interface for the temperatures studied. The interfacial potential demonstrates little temperature dependence at lower temperatures (300-450 K) and significantly enhanced (exponential) dependence at elevated temperatures. Terms arising from the decomposition of the interfacial potential into dipole and quadrupole contributions are shown to monotonically approach zero as the temperature approaches the critical temperature. Results of this study suggest that self-consistently treating the coupling of phase

Inhibition of type 1 diabetes correlated to a Lactobacillus johnsonii N6.2-mediated Th17 bias.

PubMed

Lau, Kenneth; Benitez, Patrick; Ardissone, Alexandria; Wilson, Tenisha D; Collins, Erin L; Lorca, Graciela; Li, Nan; Sankar, Dhyana; Wasserfall, Clive; Neu, Josef; Atkinson, Mark A; Shatz, Desmond; Triplett, Eric W; Larkin, Joseph

2011-03-15

Although it is known that resident gut flora contribute to immune system function and homeostasis, their role in the progression of the autoimmune disease type 1 diabetes (T1D) is poorly understood. Comparison of stool samples isolated from Bio-Breeding rats, a classic model of T1D, shows that distinct bacterial populations reside in spontaneous Bio-Breeding diabetes-prone (BBDP) and Bio-Breeding diabetes-resistant animals. We have previously shown that the oral transfer of Lactobacillus johnsonii strain N6.2 (LjN6.2) from Bio-Breeding diabetes-resistant to BBDP rodents conferred T1D resistance to BBDP rodents, whereas Lactobacillus reuteri strain TD1 did not. In this study, we show that diabetes resistance in LjN6.2-fed BBDP rodents was correlated to a Th17 cell bias within the mesenteric lymph nodes. The Th17 bias was not observed in the non-gut-draining axillary lymph nodes, suggesting that the Th17 bias was because of immune system interactions with LjN6.2 within the mesenteric lymph node. LjN6.2 interactions with the immune system were observed in the spleens of diabetes-resistant, LjN6.2-fed BBDP rats, as they also possessed a Th17 bias in comparison with control or Lactobacillus reuteri strain TD1-fed rats. Using C57BL/6 mouse in vitro assays, we show that LjN6.2 directly mediated enhanced Th17 differentiation of lymphocytes in the presence of TCR stimulation, which required APCs. Finally, we show that footpad vaccination of NOD mice with LjN6.2-pulsed dendritic cells was sufficient to mediate a Th17 bias in vivo. Together, these data suggest an interesting paradigm whereby T1D induction can be circumvented by gut flora-mediated Th17 differentiation.

Inhibited Shaped Charge Launcher Testing of Spacecraft Shield Designs

NASA Technical Reports Server (NTRS)

Grosch, Donald J.

1996-01-01

This report describes a test program in which several orbital debris shield designs were impact tested using the inhibited shaped charge launcher facility at Southwest Research Institute. This facility enables researchers to study the impact of one-gram aluminum projectiles on various shielding designs at velocities above 11 km/s. A total of twenty tests were conducted on targets provided by NASA-MSFC. This report discusses in detail the shield design, the projectile parameters and the test configuration used for each test. A brief discussion of the target damage is provided, as the detailed analysis of the target response will be done by NASA-MSFC.

Geology of the Joe Davis Hill quadrangle, Dolores and San Miguel counties, Colorado

USGS Publications Warehouse

Cater, Fred W.; Bell, Henry

1953-01-01

The Joe Davis Hill quadrangle is one of eighteen 7 1/2-minute quadrangles covering the principal carnotite-producing area of southwestern Colorado. The geology of these quadrangles was mapped by the U.S. Geological Survey for the Atomic Energy Commission as part of a comprehensive study of carnotite deposits. The rocks exposed in the eighteen quadrangles consist of crystalline rocks of pre-Cambrian age and sedimentary rocks that range in age from late Paleozoic to Quaternary. Over much of the area the sedimentary rocks are flat lying, but in places the rocks are disrupted by hih-angle faults, and northwest-trending folds. Conspicuous among the folds are large anticlines having cores of intrusive salt and gypsum. Most of the carnotite deposits are confined to Salt Wash sandstone member of the Jurassic Morrison formation. Within this sandstone, most of the deposits are spottily distributed through an arcuate zone known as the "Uravan Mineral Belt". Individual deposits range in size from irregular masses containing only a few tons of ore to large, tabular masses containing many thousands of tons. The ore consists largely of sandstone selectively impregnated and in part replaced by uranium and vanadium minerals. Most of the deposits appear to be related to certain sedimentary structures in sandstones of favorable composition.

Aktiv De-Orbiting Onboard System from Leo of Upper Stages of Launchers

NASA Astrophysics Data System (ADS)

Trushlyakov, V.; Shalay, V.; Shatrov, J.; Jakovlev, M.; Kostantino, A.

2009-03-01

The active de-orbiting onboard system (VDOS) of upper separable parts (USP) stage of launchers from LEO into orbits of utilization with term of existence orbital lifetimes till 25 years is offered. ADOS it is based on use of power resources of not produced rests of liquid fuel onboard USP launchers with liquid propulsion module (LPM). Following systems enter in structure VDOS: the gas jet propulsion system consisting of a system of gasification, chambers of gas engines (GE), a control system. For gasification of the rests of liquid fuel the heat-carrier received in the autonomous gas generator is used. The gasification propellant components from each tank with temperature and the pressure determined by strength of the corresponding tank, move in chambers of the GE established on a top of a fuel compartment. After separation of a payload execute twist USP for preservation of its position in the space by activity of the GE. Ways of increase of a system effectiveness of gasification are offered by superposition on the entered heat-carrier of ultrasonic oscillations, and also introduction in gaseous fuel nanopowder of aluminum. The volume of adaptations of construction USP, connected with introduction VDOS does not exceed 5 % from weight of a dry construction.

A more accurate analysis and design of coaxial-to-rectangular waveguide end launcher

NASA Astrophysics Data System (ADS)

Saad, Saad Michael

1990-02-01

An electromagnetic model is developed for the analysis of the coaxial-to-rectangular waveguide transition of the end-launcher type. The model describes the coupling mechanism in terms of an excitation probe which is fed by a transmission line intermediate section. The model is compared with a coupling loop model. The two models have a few analytical steps in common, but expressions for the probe model are easier to derive and compute. The two models are presented together with numerical examples and experimental verification. The superiority of the probe model is illustrated, and a design method yielding a maximum voltage standing wave ratio of 1.035 over 13 percent bandwidth is outlined.

University of Maryland-Republic Terrapin Sounding Rocket H121-2681-I(Terrapin) Model on the Launcher

NASA Image and Video Library

1956-10-21

LAL 95,647 University of Maryland-Republic Terrapin sounding rocket mounted on special launcher, September 21, 1956. Photograph published in A New Dimension Wallops Island Flight Test Range: The First Fifteen Years by Joseph Shortal. A NASA publication. Page 506.

Characterisation of SOL density fluctuations in front of the LHCD PAM launcher in Tore

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

Oosako, T.; Ekedahl, A.; Goniche, M.

2011-12-23

The density fluctuations, modified by Lower Hybrid Wave (LHW), is analyzed in Tore Supra with reference to the injected LHW power, density and the gap between LCFS (Last Closed Flux Surface) and the PAM (passive-active-multijunction) launcher. The density fluctuations are measured with RF probes installed at the PAM launcher front. A density scan at nominal toroidal field (3.8 T) shows that the fluctuations rate stays nearly constant ({approx}50%) for <3.5x10{sup 19}m{sup -3} and with LHW power up to 2MW. However, when increasing the density above <{approx}4.2x10{sup 19}m{sup -3}, using strong gas puffing, the fluctuation rate increases to >70%more » and is characterized by strong negative spikes, with typical frequency >100kHz. These are most likely originating from acceleration of electrons in the LHW near field due to parasitic absorption, as evidenced on the IR images, showing hot spots on the side limiters.« less

Pilot Joe Walker in Lunar Landing Research Vehicle (LLRV) on ramp

NASA Technical Reports Server (NTRS)

1964-01-01

In this 1964 NASA Flight Research Center photograph, NASA Pilot Joe Walker is setting in the pilot's platform of the the Lunar Landing Research Vehicle (LLRV) number 1. This photograph provides a good view of the pilot setting in front of the primary instrumentation panel. When Apollo planning was underway in 1960, NASA was looking for a simulator to profile the descent to the moon's surface. Three concepts surfaced: an electronic simulator, a tethered device, and the ambitious Dryden contribution, a free-flying vehicle. All three became serious projects, but eventually the NASA Flight Research Center's (FRC) Landing Research Vehicle (LLRV) became the most significant one. Hubert M. Drake is credited with originating the idea, while Donald Bellman and Gene Matranga were senior engineers on the project, with Bellman, the project manager. Simultaneously, and independently, Bell Aerosystems Company, Buffalo, N.Y., a company with experience in vertical takeoff and landing (VTOL) aircraft, had conceived a similar free-flying simulator and proposed their concept to NASA headquarters. NASA Headquarters put FRC and Bell together to collaborate. The challenge was; to allow a pilot to make a vertical landing on earth in a simulated moon environment, one sixth of the earth's gravity and with totally transparent aerodynamic forces in a 'free flight' vehicle with no tether forces acting on it. Built of tubular aluminum like a giant four-legged bedstead, the vehicle was to simulate a lunar landing profile from around 1500 feet to the moon's surface. To do this, the LLRV had a General Electric CF-700-2V turbofan engine mounted vertically in gimbals, with 4200 pounds of thrust. The engine, using JP-4 fuel, got the vehicle up to the test altitude and was then throttled back to support five-sixths of the vehicle's weight, simulating the reduced gravity of the moon. Two hydrogen-peroxide lift rockets with thrust that could be varied from 100 to 500 pounds handled the LLRV's rate of

Design and development of the redundant launcher stabilization system for the Atlas 2 launch vehicle

NASA Technical Reports Server (NTRS)

Nakamura, M.

1991-01-01

The Launcher Stabilization System (LSS) is a pneumatic/hydraulic ground system used to support an Atlas launch vehicle prior to launch. The redesign and development activity undertaken to achieve an LSS with increased load capacity and a redundant hydraulic system for the Atlas 2 launch vehicle are described.

Observability of satellite launcher navigation with INS, GPS, attitude sensors and reference trajectory

NASA Astrophysics Data System (ADS)

Beaudoin, Yanick; Desbiens, André; Gagnon, Eric; Landry, René

2018-01-01

The navigation system of a satellite launcher is of paramount importance. In order to correct the trajectory of the launcher, the position, velocity and attitude must be known with the best possible precision. In this paper, the observability of four navigation solutions is investigated. The first one is the INS/GPS couple. Then, attitude reference sensors, such as magnetometers, are added to the INS/GPS solution. The authors have already demonstrated that the reference trajectory could be used to improve the navigation performance. This approach is added to the two previously mentioned navigation systems. For each navigation solution, the observability is analyzed with different sensor error models. First, sensor biases are neglected. Then, sensor biases are modelled as random walks and as first order Markov processes. The observability is tested with the rank and condition number of the observability matrix, the time evolution of the covariance matrix and sensitivity to measurement outlier tests. The covariance matrix is exploited to evaluate the correlation between states in order to detect structural unobservability problems. Finally, when an unobservable subspace is detected, the result is verified with theoretical analysis of the navigation equations. The results show that evaluating only the observability of a model does not guarantee the ability of the aiding sensors to correct the INS estimates within the mission time. The analysis of the covariance matrix time evolution could be a powerful tool to detect this situation, however in some cases, the problem is only revealed with a sensitivity to measurement outlier test. None of the tested solutions provide GPS position bias observability. For the considered mission, the modelling of the sensor biases as random walks or Markov processes gives equivalent results. Relying on the reference trajectory can improve the precision of the roll estimates. But, in the context of a satellite launcher, the roll

Analytical Study on Flight Performance of a RP Laser Launcher

NASA Astrophysics Data System (ADS)

Katsurayama, H.; Ushio, M.; Komurasaki, K.; Arakawa, Y.

2005-04-01

An air-breathing RP Laser Launcher has been proposed as the alternative to conventional chemical launch systems. This paper analytically examines the feasibility of SSTO system powered by RP lasers. The trajectory from the ground to the geosynchronous orbit is computed and the launch cost including laser-base development is estimated. The engine performance is evaluated by CFD computations and a cycle analysis. The results show that the beam power of 2.3MW per unit initial vehicle mass is optimum to reach a geo-synchronous transfer orbit, and 3,000 launches are necessary to redeem the cost for laser transmitter.

Navajo Code Talker Joe Morris, Sr. shared insights from his time as a secret World War Two messenger with his audience at NASA's Dryden Flight Research Center

NASA Image and Video Library

2002-11-26

Navajo Code Talker Joe Morris, Sr. shared insights from his time as a secret World War Two messenger with his audience at NASA's Dryden Flight Research Center on Nov. 26, 2002. NASA Dryden is located on Edwards Air Force Base in California's Mojave Desert.

Robotic weather balloon launchers spread in Alaska

NASA Astrophysics Data System (ADS)

Rosen, Julia

2018-04-01

Last week, things began stirring inside the truck-size box that sat among melting piles of snow at the airport in Fairbanks, Alaska. Before long, the roof of the box yawned open and a weather balloon took off into the sunny afternoon, instruments dangling. The entire launch was triggered with the touch of a button, 5 kilometers away at an office of the National Weather Service (NWS). The flight was smooth, just one of hundreds of twice-daily balloon launches around the world that radio back crucial data for weather forecasts. But most of those balloons are launched by people; the robotic launchers, which are rolling out across Alaska, are proving to be controversial. NWS says the autolaunchers will save money and free up staff to work on more pressing matters. But representatives of the employee union question their reliability, and say they will hasten the end of Alaska's remote weather offices, where forecasting duties and hours have already been slashed.

Feasibility of an earth-to-space rail launcher system. [emphasizing nuclear waste disposal application

NASA Technical Reports Server (NTRS)

Rice, E. E.; Miller, L. A.; Marshall, R. A.; Kerslake, W. R.

1982-01-01

The feasibility of earth-to-space electromagnetic (railgun) launchers (ESRL) is considered, in order to determine their technical practicality and economic viability. The potential applications of the launcher include nuclear waste disposal into space, deep space probe launches, and atmospheric research. Examples of performance requirements of the ESRL system are a maximum acceleration of 10,000 g's for nuclear waste disposal in space (NWDS) missions and 2,500 g's for earth orbital missions, a 20 km/sec launch velocity for NWDS missions, and a launch azimuth of 90 degrees E. A brief configuration description is given, and test results indicate that for the 2020-2050 time period, as much as 3.0 MT per day of bulk material could be launched, and about 0.5 MT per day of high-level nuclear waste could be launched. For earth orbital missions, a significant projectile mass was approximately 6.5 MT, and an integral distributed energy store launch system demonstrated a good potential performance. ESRL prove to be economically and environmentally feasible, but an operational ESRL of the proposed size is not considered achievable before the year 2020.

Visible light emission measurements from a dense electrothermal launcher plasma

NASA Astrophysics Data System (ADS)

Hankins, O. E.; Bourham, M. A.; Earnhart, J.; Gilligan, J. G.

1993-01-01

Measurements of the visible light emission from dense, weakly non-ideal plasmas have been performed on the experimental electrothermal launcher device 'SIRENS'. The plasma is created by the ablation or a Lexan insulator in the source, which then flows through a cylindrical barrel which serves as the material sample. Visible light emission spectra have been observed both in-bore and from the muzzle flash or the barrel, and from the flash or the source. Due to high plasma opacity (the plasma emits as a near blackbody) and absorption by the molecular components of the vapor shield, the hotter core or the arc has been difficult to observe. Recent measurements along the axis or the device indicate time-averaged plasma temperatures in the barrel or about 1 eV for lower energy shots, which agree with experimental measurements of the average heat flux and plasma conductivity along the barrel. Measurements or visible emission from the source indicate time averaged temperatures of 1 to 2 eV which agree with the theoretical estimates derived from ablated mass measurements and calculated estimates derived from plasma conductivity measurements.

STS-30 Atlantis, OV-104, on the mobile launcher platform heads to KSC LC pad

NASA Technical Reports Server (NTRS)

1989-01-01

STS-30 Atlantis, Orbiter Vehicle (OV) 104, riding atop the mobile launcher platform and the crawler transporter approaches Kennedy Space Center (KSC) Launch Complex (LC) pad 39B. This backlit view highlights OV-104's profile, the external tank (ET), and one of the two solid rocket boosters (SRBs) as it moves up LC pad 39B incline.

STS-30 Atlantis, OV-104, at KSC LC Pad 39B atop mobile launcher platform

NASA Technical Reports Server (NTRS)

1989-01-01

STS-30 Atlantis, Orbiter Vehicle (OV) 104, arrives at Kennedy Space Center (KSC) Launch Complex (LC) Pad 39B atop mobile launcher platform. The fixed service structure (FSS) towers above OV-104, its external tank (ET), and its solid rocket boosters (SRBs). The rotating service structure (RSS) is retracted. The launch tower catwalks are also retracted.

Utilizing NX Advanced Simulation for NASA's New Mobile Launcher for Ares-l

NASA Technical Reports Server (NTRS)

Brown, Christopher

2010-01-01

This slide presentation reviews the use of NX to simulate the new Mobile Launcher (ML) for the Ares-I. It includes: a comparison of the sizes of the Saturn 5, the Space Shuttle, the Ares I, and the Ares V, with the height, and payload capability; the loads control plan; drawings of the base framing, the underside of the ML, beam arrangement, and the finished base and the origin of the 3D CAD data. It also reviews the modeling approach, meshing. the assembly Finite Element Modeling, the model summary. and beam improvements.

Enhanced hypervelocity launcher: Capabilities to 16 km/s

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

Chhabildas, L.C.; Kmetyk, L.N.; Reinhart, W.D.

1993-12-31

A systematic study is described which has led to the successful launch of thin flier plates to velocities of 16 km/s. The energy required to launch a flier plant to 16 km/s is approximately 10 to 15 times the energy required to melt and vaporize the plate. The energy must, therefore, be deposited in a well-controlled manner to prevent melt or vaporation. This is achieved by using a graded-density assembly to impact a stationary flier-plate upon impact time dependent, structure, high pressure pulses are generated and used to propel the plantes plates to hypervelocities without melt or fracture. In previousmore » studies, a graded density impact of 7.3 km/s was used to launch a 0.5 mm thick plate to a velocity of over 12 km/s. If impact techniques alone were to be used to achieve flier-plate velocities approaching 16 km/s, this would require that the graded-density impact occur at {approximately} 10 km/s. In this paper, we describe a new technique that has been implemented to enhance the performance of the Sandia hypervelocity launcher. This technique of creating an impact-generated acceleration reservoir, has allowed the launch of 0.5 mm to 1.0 mm thick plates to record velocities up to 15.8 km/s. In these experiments, both titanium (Ti-6A1-4V) and aluminum (6061-T6) alloy were used for the flier-plate material. These are the highest metallic projectile plate velocities ever achieved for masses in the range of 0.1 g to 1 g.« less

Estimation of Lightning Levels on a Launcher Using a BEM-Compressed Model

NASA Astrophysics Data System (ADS)

Silly, J.; Chaigne, B.; Aspas-Puertolas, J.; Herlem, Y.

2016-05-01

As development cycles in the space industry are being considerably reduced, it seems mandatory to deploy in parallel fast analysis methods for engineering purposes, but without sacrificing accuracy. In this paper we present the application of such methods to early Phase A-B [1] evaluation of lightning constraints on a launch vehicle.A complete 3D parametric model of a launcher has been thus developed and simulated with a Boundary Element Method (BEM)-frequency simulator (equipped with a low frequency algorithm). The time domain values of the observed currents and fields are obtained by post-treatment using an inverse discrete Fourier transform (IDFT).This model is used for lightning studies, especially the simulation are useful to analyse the influence of lightning injected currents on resulting circulated currents on external cable raceways. The description of the model and some of those results are presented in this article.

Mobile Launcher Crew Access Arm Transport from Cocoa FL to KSC

NASA Image and Video Library

2017-10-17

The Orion crew access arm is secured on a flatbed truck at Precision Fabricating and Cleaning in Cocoa, Florida and ready to be transported to a storage location at NASA's Kennedy Space Center in Florida. Later this month, the arm will be transported to the mobile launcher (ML) tower at the center. The crew access arm will be located at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower.

Mobile Launcher Crew Access Arm Transport from Cocoa FL to KSC

NASA Image and Video Library

2017-10-17

The Orion crew access arm departs Precision Fabricating and Cleaning in Cocoa, Florida, atop a flatbed truck. The access arm will be transported to a storage location at NASA's Kennedy Space Center in Florida. Later this month, the arm will be transported to the mobile launcher (ML) tower at the center. The crew access arm will be located at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower.

Mobile Launcher Crew Access Arm Transport from Cocoa FL to KSC

NASA Image and Video Library

2017-10-17

A flatbed truck with the Orion crew access arm secured atop arrives in a storage location at NASA's Kennedy Space Center in Florida. The access arm was transported from Precision Fabricating and Cleaning in Cocoa, Florida. Later this month, the arm will be transported to the mobile launcher (ML) tower at the center. The crew access arm will be located at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower.

Modifications of Hinge Mechanisms for the Mobile Launcher

NASA Technical Reports Server (NTRS)

Ganzak, Jacob D.

2018-01-01

The further development and modifications made towards the integration of the upper and lower hinge assemblies for the Exploration Upper Stage umbilical are presented. Investigative work is included to show the process of applying updated NASA Standards within component and assembly drawings for selected manufacturers. Component modifications with the addition of drawings are created to precisely display part geometries and geometric tolerances, along with proper methods of fabrication. Comparison of newly updated components with original Apollo era components is essential to correctly model the part characteristics and parameters, i.e. mass properties, material selection, weldments, and tolerances. 3-Dimensional modeling software is used to demonstrate the necessary improvements. In order to share and corroborate these changes, a document management system is used to store the various components and associated drawings. These efforts will contribute towards the Mobile Launcher for Exploration Mission 2 to provide proper rotation of the Exploration Upper Stage umbilical, necessary for providing cryogenic fill and drain capabilities.

Water Quality Analysis Simulation (WASP) and Model ...

EPA Pesticide Factsheets

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Beam masking to reduce cyclic error in beam launcher of interferometer

NASA Technical Reports Server (NTRS)

Ames, Lawrence L. (Inventor); Bell, Raymond Mark (Inventor); Dutta, Kalyan (Inventor)

2005-01-01

Embodiments of the present invention are directed to reducing cyclic error in the beam launcher of an interferometer. In one embodiment, an interferometry apparatus comprises a reference beam directed along a reference path, and a measurement beam spatially separated from the reference beam and being directed along a measurement path contacting a measurement object. The reference beam and the measurement beam have a single frequency. At least a portion of the reference beam and at least a portion of the measurement beam overlapping along a common path. One or more masks are disposed in the common path or in the reference path and the measurement path to spatially isolate the reference beam and the measurement beam from one another.

Mobile Launcher Crew Access Arm Transport from Cocoa FL to KSC

NASA Image and Video Library

2017-10-17

Two heavy-lift cranes are used to lower the Orion crew access arm onto a work stand in a storage location at NASA's Kennedy Space Center in Florida. The access arm was transported from Precision Fabricating and Cleaning in Cocoa, Florida. Later this month, the arm will be transported to the mobile launcher (ML) tower at the center. The crew access arm will be located at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower.

Mobile Launcher Crew Access Arm Prep for Transport to Kennedy Sp

NASA Image and Video Library

2017-10-16

The Orion crew access arm is being secured on a flatbed truck at Precision Fabricating and Cleaning in Cocoa, Florida. The crew access arm will be transported to a storage location near NASA's Kennedy Space Center in Florida. Later this month, the arm will be transported to the mobile launcher (ML) tower at the center. The crew access arm will be located at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower.

Mobile Launcher Crew Access Arm Prep for Transport to Kennedy Sp

NASA Image and Video Library

2017-10-16

Two heavy-lift cranes are used to lower the Orion crew access arm onto a flatbed truck at Precision Fabricating and Cleaning in Cocoa, Florida. The crew access arm will be transported to a storage location near NASA's Kennedy Space Center in Florida. Later this month, the arm will be transported to the mobile launcher (ML) tower at the center. The crew access arm will be located at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower.

Mobile Launcher Crew Access Arm Prep for Transport to Kennedy Sp

NASA Image and Video Library

2017-10-16

The Orion crew access arm is being secured onto a flatbed truck at Precision Fabricating and Cleaning in Cocoa, Florida. The crew access arm will be transported to a storage location near NASA's Kennedy Space Center in Florida. Later this month, the arm will be transported to the mobile launcher (ML) tower at the center. The crew access arm will be located at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower.

Mobile Launcher Crew Access Arm Prep for Transport to Kennedy Sp

NASA Image and Video Library

2017-10-16

The Orion crew access arm is secured on a flatbed truck at Precision Fabricating and Cleaning in Cocoa, Florida. The crew access arm will be transported to a storage location near NASA's Kennedy Space Center in Florida. Later this month, the arm will be transported to the mobile launcher (ML) tower at the center. The crew access arm will be located at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower.

Mobile Launcher Crew Access Arm Prep for Transport to Kennedy Sp

NASA Image and Video Library

2017-10-16

The Orion crew access arm is being moved by crane onto a flatbed truck at Precision Fabricating and Cleaning in Cocoa, Florida. The crew access arm will be transported to a storage location near NASA's Kennedy Space Center in Florida. Later this month, the arm will be transported to the mobile launcher (ML) tower at the center. The crew access arm will be located at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower.

Mobile Launcher Crew Access Arm Transport from Cocoa FL to KSC

NASA Image and Video Library

2017-10-17

A flatbed truck with the Orion crew access arm secured atop travels along a road in Cocoa, Florida, after departing Precision Fabricating and Cleaning. The access arm will be transported to a storage location at NASA's Kennedy Space Center in Florida. Later this month, the arm will be transported to the mobile launcher (ML) tower at the center. The crew access arm will be located at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower.

Mobile Launcher Crew Access Arm Transport from Cocoa FL to KSC

NASA Image and Video Library

2017-10-17

Two heavy-lift cranes lower the Orion crew access arm onto a work stand in a storage location at NASA's Kennedy Space Center in Florida. The access arm was transported from Precision Fabricating and Cleaning in Cocoa, Florida. Later this month, the arm will be transported to the mobile launcher (ML) tower at the center. The crew access arm will be located at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower.

Mobile Launcher Crew Access Arm Transport from Cocoa FL to KSC

NASA Image and Video Library

2017-10-17

Two heavy-lift cranes are used to tilt and lower the Orion crew access arm onto a work stand in a storage location at NASA's Kennedy Space Center in Florida. The access arm was transported from Precision Fabricating and Cleaning in Cocoa, Florida. Later this month, the arm will be transported to the mobile launcher (ML) tower at the center. The crew access arm will be located at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower.

Mobile Launcher Crew Access Arm Prep for Transport to Kennedy Sp

NASA Image and Video Library

2017-10-16

Two heavy-lift cranes are being used to lower the Orion crew access arm onto a flatbed truck at Precision Fabricating and Cleaning in Cocoa, Florida. The crew access arm will be transported to a storage location near NASA's Kennedy Space Center in Florida. Later this month, the arm will be transported to the mobile launcher (ML) tower at the center. The crew access arm will be located at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower.

Mobile Launcher Crew Access Arm Transport from Cocoa FL to KSC

NASA Image and Video Library

2017-10-17

Two heavy-lift cranes are used to lift the Orion crew access arm up from a flatbed truck in a storage location at NASA's Kennedy Space Center in Florida. The access arm was transported from Precision Fabricating and Cleaning in Cocoa, Florida. Later this month, the arm will be transported to the mobile launcher (ML) tower at the center. The crew access arm will be located at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower.

Regulation of nonsymbiotic and truncated hemoglobin genes of Lotus japonicus in plant organs and in response to nitric oxide and hormones.

PubMed

Bustos-Sanmamed, Pilar; Tovar-Méndez, Alejandro; Crespi, Martin; Sato, Shusei; Tabata, Satoshi; Becana, Manuel

2011-02-01

• In legumes, symbiotic leghemoglobins facilitate oxygen diffusion to the bacteroids, but the roles of nonsymbiotic and truncated hemoglobins are largely unknown. Here the five hemoglobin genes of Lotus japonicus have been functionally characterized to gain insight into their regulatory mechanisms. • Plants were exposed to nitric oxide donors, stressful conditions, and hormones. Gene expression profiling was determined by quantitative PCR, and gene activities were localized using in situ hybridization and promoter-reporter gene fusions. • The LjGLB1-1, LjGLB2, and LjGLB3-1 mRNA expression levels were very high in nodules relative to other plant organs. The expression of these genes was localized in the vascular bundles, cortex, and infected tissue. LjGLB1-1 was the only gene induced by nitric oxide. Cytokinins caused nearly complete inactivation of LjGLB2 and LjGLB3-1 in nodules and induction of LjGLB1-1 in roots. Abscisic acid induced LjGLB1-1 in nodules and LjGLB1-2 and LjGLB2 in roots, whereas polyamines and jasmonic acid induced LjGLB1-1 only in roots. • The enhanced expression of the three types of hemoglobins in nodules, the colocalization of gene activities in nodule and root tissues with high metabolic rates, and their distinct regulatory mechanisms point out complementary roles of hemoglobins and strongly support the hypothesis that LjGLB1-1, LjGLB2, and LjGLB3-1 are required for symbiosis. © 2010 The Authors. New Phytologist © 2010 New Phytologist Trust.

LH launcher Arcs Formation and Detection on JET

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

Baranov, Yu. F.; Challis, C. D.; Kirov, K.

2011-12-23

Mechanisms of arc formation have been analyzed and the critical electric fields for the multipactor effect calculated, compared to the experimental values and found to be within the normal operational space of the LH system on JET. It has been shown that the characteristic electron energy (20-1000)eV for the highest multipactor resonances (N = 4-9) are within the limits of secondary electron yield above 1 required for multipactoring. Electrons with these energies provide the highest gas desorption efficiency when hitting the waveguide walls. The effect of higher waveguide modes and magnetic field on the multipactor was also considered. The distributionmore » function for electrons accelerated by LH waves in front of the launcher has been calculated. The field emission currents have been estimated and found to be small. It is proposed that emission of Fel5, 16 lines, which can be obtained with improved diagnostics, could be used to detect arcs that are missed by a protection system based on the reflected power. The reliability and time response of these signals are discussed. A similar technique based on the observation of the emission of low ionized atoms can be used for a fast detection of other undesirable events to avoid sputtering or melting of the plasma facing components such as RF antenna. These techniques are especially powerful if they are based on emission uniquely associated with specific locations and components.« less

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

Sharp and the Jules Verne Launcher

NASA Astrophysics Data System (ADS)

Hunter, John; Cartland, Harry

1996-03-01

Lawrence Livermore National Laboratory (LLNL) has built the worlds largest hydrogen gas gun called SHARP, (Super High Altitude Research Project). Originally designed to launch 5 kg to a 450 km altitude, SHARP is configured horizontally at Site 300 in Tracy, California. SHARP is successfully delivering 5 kg scramjets at Mach 9 in aerophysics tests. Some of the results of the scramjet tests are enlightening and are presented insofar as they are relevant to future launches into space. Using a light gas gun to launch payloads into orbit has been analyzed. We look at LEO (Low Earth Orbit), GEO (Geosynchronous Earth Orbit), and LO (Lunar Orbit). We present a conceptual design for a large light gas gun called the Jules Verne Launcher (JVL). The JVL can deliver 3.3 metric tons to a 500 km low earth orbit. We anticipate one launch per day. We present the history of light gas guns, the SHARP design and performance, and the JVL design. Another section is devoted to the vehicle environment and resultant design. Lastly, we present a cost analysis. Our results indicated that the JVL will be able to deliver 1000 metric tons of payload to LEO yearly. The cost will be 5% of the best US rocket delivery cost. This technology will enable the next phase of man's exploration of space.

Development of a CFRP Engine Thrust Frame for the Next Generation Launchers

NASA Astrophysics Data System (ADS)

Fatemi, Javad; van der Bas, Finn; Cruijssen, Henk

2012-07-01

This paper addresses the activities related to the development of technologies for a composite Engine Thrust Frame (ETF) for the next generation launchers. In particular, the design and analyses of a full Carbon Fibre Reinforced Plastic (CFRP) engine thrust frame are presented in more detail. The ETF concept is composed of three main parts, i.e. an aluminium top-ring which connects the ETF to the upper-stage tank, a CFRP cone, and a CFRP cone-cap which connects the Vinci engine to the ETF. The main challenging requirements for development of a CFRP ETF are recalled. The ETF concept and its mechanical performances are assessed.

Mobile Launcher Crew Access Arm Prep for Transport to Kennedy Sp

NASA Image and Video Library

2017-10-16

Two heavy-lift cranes are being used to move the Orion crew access arm and lower it onto a flatbed truck at Precision Fabricating and Cleaning in Cocoa, Florida. The crew access arm will be transported to a storage location near NASA's Kennedy Space Center in Florida. Later this month, the arm will be transported to the mobile launcher (ML) tower at the center. The crew access arm will be located at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower.

On The Aerodynamic Heating Of Vega Launcher: Compressible Chimera Navier-Stokes Simulation With Complex Surfaces

NASA Astrophysics Data System (ADS)

Di Mascio, A.; Zaghi, S.; Muscari, R.; Broglia, R.; Cavallini, E.; Favini, B.; Scaccia, A.

2011-05-01

The results of accurate compressible Navier-Stokes simulations of aerodynamic heating of the Vega launcher are presented. Three selected steady conditions of the Vega mission profile are considered: the first corresponding to the altitude of 18 km, the second to 25 km and the last to 33 km. The numerical code is based on the Favre- Average Navier-Stokes equations; the turbulent model chosen for closure is the one-equation model by Spalart- Allmaras. The equations are discretized by a finite volume approach, that can handle block-structured meshes with partial overlap (“Chimera” grid-overlapping technique). The isothermal boundary condition has been applied to the lancher wall. Particular care was devoted to the construction of the discrete model; indeed, the launcher is equipped with many protrusions and geometrical peculiarities (as antennas, raceways, inter-stage connection flanges and retrorockets) that are expected to affect considerably the local thermal flow-field and the level of heat fluxes, because the flow have to undergo strong variation in space; con- sequently, special attention was devoted to the definition of a tailored mesh, capable of catching local details of the aerothermal flow field (shocks, expansion fans, boundary layer, etc..). The computed results are reported together with uncertainty and actual convergence order, that were estimated by the standard procedures suggested by AIAA [Ame98].

The enhanced ASDEX Upgrade pellet centrifuge launcher

NASA Astrophysics Data System (ADS)

Plöckl, B.; Lang, P. T.

2013-10-01

Pellets played an important role in the program of ASDEX Upgrade serving both for investigations on efficient particle fuelling and high density scenarios but also for pioneering work on Edge Localised Mode (ELM) pacing and mitigation. Initially designed for launching fuelling pellets from the magnetic low field side, the system was converted already some time ago to inject pellets from the magnetic high field side as much higher fuelling efficiency was found using this configuration. In operation for more than 20 years, the pellet launching system had to undergo a major revision and upgrading, in particular of its control system. Furthermore, the control system installed adjacent to the launcher had to be transferred to a more distant location enforcing a complete galvanic separation from torus potential and a fully remote control solution. Changing from a hybrid system consisting of PLC S5/S7 and some hard wired relay control to a state of the art PLC system allowed the introduction of several new operational options enabling more flexibility in the pellet experiments. This article describes the new system architecture of control hardware and software, the operating procedure, and the extended operational window. First successful applications for ELM pacing and triggering studies are presented as well as utilization for the development of high density scenarios.

The enhanced ASDEX Upgrade pellet centrifuge launcher.

PubMed

Plöckl, B; Lang, P T

2013-10-01

Pellets played an important role in the program of ASDEX Upgrade serving both for investigations on efficient particle fuelling and high density scenarios but also for pioneering work on Edge Localised Mode (ELM) pacing and mitigation. Initially designed for launching fuelling pellets from the magnetic low field side, the system was converted already some time ago to inject pellets from the magnetic high field side as much higher fuelling efficiency was found using this configuration. In operation for more than 20 years, the pellet launching system had to undergo a major revision and upgrading, in particular of its control system. Furthermore, the control system installed adjacent to the launcher had to be transferred to a more distant location enforcing a complete galvanic separation from torus potential and a fully remote control solution. Changing from a hybrid system consisting of PLC S5/S7 and some hard wired relay control to a state of the art PLC system allowed the introduction of several new operational options enabling more flexibility in the pellet experiments. This article describes the new system architecture of control hardware and software, the operating procedure, and the extended operational window. First successful applications for ELM pacing and triggering studies are presented as well as utilization for the development of high density scenarios.

OMA analysis of a launcher under operational conditions with time-varying properties

NASA Astrophysics Data System (ADS)

Eugeni, M.; Coppotelli, G.; Mastroddi, F.; Gaudenzi, P.; Muller, S.; Troclet, B.

2018-05-01

The objective of this paper is the investigation of the capability of operational modal analysis approaches to deal with time-varying system in the low-frequency domain. Specifically, the problem of the identification of the dynamic properties of a launch vehicle, working under actual operative conditions, is studied. Two OMA methods are considered: the frequency-domain decomposition and the Hilbert transform method. It is demonstrated that both OMA approaches allow the time-tracking of modal parameters, namely, natural frequencies, damping ratios, and mode shapes, from the response accelerations only recorded during actual flight tests of a launcher characterized by a large mass variation due to fuel burning typical of the first phase of the flight.

Calibrating Accelerometers Using an Electromagnetic Launcher

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

Erik Timpson

A Pulse Forming Network (PFN), Helical Electromagnetic Launcher (HEML), Command Module (CM), and Calibration Table (CT) were built and evaluated for the combined ability to calibrate an accelerometer. The PFN has a maximum stored energy of 19.25 kJ bank and is fired by a silicon controlled rectifier (SCR), with appropriate safety precautions. The HEML is constructed out of G-10 fiberglass and is designed to accelerate 600 grams to 10 meters per second. The CM is microcontroller based running Arduino Software. The CM has a keypad input and 7 segment outputs of the bank voltage and desired voltage. After entering amore » desired bank voltage, the CM controls the charge of the PFN. When the two voltages are equal it allows the fire button to send a pulse to the SCR to fire the PFN and in turn, the HEML. The HEML projectile's tip hits a target that is held by the CT. The CT consists of a table to hold the PFN and HEML, a vacuum chuck, air bearing, velocity meter and catch pot. The Target is held with the vacuum chuck awaiting impact. After impact, the air bearing allows the target to fall freely for the velocity meter to get an accurate reading. A known acceleration is determined from the known change in velocity of the target. Thus, if an accelerometer was attached to the target, the measured value can be compared to the known value.« less

Commercial space development needs cheap launchers

NASA Astrophysics Data System (ADS)

Benson, James William

1998-01-01

SpaceDev is in the market for a deep space launch, and we are not going to pay $50 million for it. There is an ongoing debate about the elasticity of demand related to launch costs. On the one hand there are the ``big iron'' NASA and DoD contractors who say that there is no market for small or inexpensive launchers, that lowering launch costs will not result in significantly more launches, and that the current uncompetitive pricing scheme is appropriate. On the other hand are commercial companies which compete in the real world, and who say that there would be innumerable new launches if prices were to drop dramatically. I participated directly in the microcomputer revolution, and saw first hand what happened to the big iron computer companies who failed to see or heed the handwriting on the wall. We are at the same stage in the space access revolution that personal computers were in the late '70s and early '80s. The global economy is about to be changed in ways that are just as unpredictable as those changes wrought after the introduction of the personal computer. Companies which fail to innovate and keep producing only big iron will suffer the same fate as IBM and all the now-extinct mainframe and minicomputer companies. A few will remain, but with a small share of the market, never again to be in a position to dominate.

Approaches to Learning or Levels of Processing: What Did Marton and Säljö (1976a) Really Say? the Legacy of the Work of the Göteborg Group in the 1970s

ERIC Educational Resources Information Center

Richardson, John T.

2015-01-01

Marton and Säljö ("Br J Educ Psychol" 46:4-11, 1976a) described deep-level and surface-level processing in experiments in which students read and recalled academic texts. They did not discuss whether levels of processing had any counterparts in students' everyday studies. However, their article is often credited as the source of the…

Slots in dielectric image line as mode launchers and circuit elements

NASA Astrophysics Data System (ADS)

Solbach, K.

1981-01-01

A planar resonator model is used to investigate slots in the ground plane of dielectric image lines. An equivalent circuit representation of the slot discontinuity is obtained, and the launching efficiency of the slot as a mode launcher is analyzed. Slots are also shown to be useful in the realization of dielectric image line array antennas. It is found that the slot discontinuity can be shown as a T-junction of the dielectric image line and a metal waveguide. The launching efficiency is found to increase with the dielectric constant of the dielectric image line, exhibiting a maximum value for guides whose height is slightly less than half a wavelength in the dielectric medium. The measured launching efficiencies of low permittivity dielectric image lines are found to be in good agreement with calculated values

The enhanced ASDEX Upgrade pellet centrifuge launcher

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

Plöckl, B.; Lang, P. T.

2013-10-15

Pellets played an important role in the program of ASDEX Upgrade serving both for investigations on efficient particle fuelling and high density scenarios but also for pioneering work on Edge Localised Mode (ELM) pacing and mitigation. Initially designed for launching fuelling pellets from the magnetic low field side, the system was converted already some time ago to inject pellets from the magnetic high field side as much higher fuelling efficiency was found using this configuration. In operation for more than 20 years, the pellet launching system had to undergo a major revision and upgrading, in particular of its control system.more » Furthermore, the control system installed adjacent to the launcher had to be transferred to a more distant location enforcing a complete galvanic separation from torus potential and a fully remote control solution. Changing from a hybrid system consisting of PLC S5/S7 and some hard wired relay control to a state of the art PLC system allowed the introduction of several new operational options enabling more flexibility in the pellet experiments. This article describes the new system architecture of control hardware and software, the operating procedure, and the extended operational window. First successful applications for ELM pacing and triggering studies are presented as well as utilization for the development of high density scenarios.« less

Trauma potential and ballistic parameters of cal. 9 mm P.A. dummy launchers.

PubMed

Frank, Matthias; Bockholdt, Britta; Philipp, Klaus-Peter; Ekkernkamp, Axel

2010-07-15

Blank cartridge actuated dummy launching devices are used by migratory bird hunters to train dogs to retrieve downed birds. The devices create a loud noise while simultaneously propelling a hard foam dummy for retrieval. A newly developed dummy launcher is based on a modified cal. 9 mm P.A. blank handgun with an extension tube pinned and welded to the barrel imitation. Currently, there are no experimental investigations on the ballistic background and trauma potential of these uncommon shooting devices. An experimental test set-up consisting of a photoelectric infrared light barrier was used for measurement of the velocity of hard foam dummies propelled with an automatic dummy launcher. Ballistic parameters of the dummies and an aluminium sleeve as improvised projectile (kinetic energy (E), impulse (p), energy density (E') and threshold velocity (v(tsh)) to cause penetrating wounds as a function of cross-sectional density (S)) were calculated. The average velocity (v) of the dummies was measured 25.71 m/s exerting an average impulse (p) of 3.342 Ns. The average kinetic energy (E) was calculated 43.04 J with an average energy density (E') of 0.069 J/mm(2). The average velocity (v) of the aluminium sleeves as improvised projectiles was measured 79.58 m/s exerting an average impulse (p) of 2.228 Ns. The average kinetic energy (E) of the aluminium sleeves was calculated as 88.70 J with an average energy density (E') of 0.282 J/mm(2). The energy delivered by these shooting devices is high enough to cause relevant injuries. The absence of skin penetration must not mislead the emergency physician or forensic expert into neglecting the potential damage from these devices. (c) 2010 Elsevier Ireland Ltd. All rights reserved.

The STS-93 external tank and booster stack sits at the Mobile Launcher Platform park site

NASA Technical Reports Server (NTRS)

1999-01-01

The STS-93 stack of solid rocket boosters and external tank sits at the Mobile Launcher Platform park site waiting for lightning shield wires to be installed on the Vehicle Assembly Building (VAB) in the background. The stack is being temporarily stored outside the VAB while Space Shuttle Discovery undergoes repair to hail damage in High Bay 1. Discovery was rolled back from Pad 39B to the VAB for repairs because access to all of the damaged areas was not possible at the pad. The STS-93 stack will be moved under the wires at the VAB for protection until Discovery returns to the pad, later this week. The scheduled date for launch of mission STS-96 is no earlier than May 27. STS-93 is targeted for launch on July 22, carrying the Chandra X-ray Observatory.

Down-bore two-laser heterodyne velocimetry of an implosion-driven hypervelocity launcher

NASA Astrophysics Data System (ADS)

Hildebrand, Myles; Huneault, Justin; Loiseau, Jason; Higgins, Andrew J.

2017-01-01

The implosion-driven launcher uses explosives to shock-compress helium, driving well-characterized projectiles to velocities exceeding 10 km/s. The masses of projectiles range between 0.1 - 15 g, and the design shows excellent scalability, reaching similar velocities across different projectile sizes. In the past, velocity measurements have been limited to muzzle velocity obtained via a high-speed videography upon the projectile exiting the launch tube. Recently, Photon Doppler Velocimetry (PDV) has demonstrated the ability to continuously measure in-bore velocity, even in the presence of significant blow-by of high temperature helium propellant past the projectile. While a single laser system sampled at 40 GS/s with a 13 GHz detector/scope bandwidth is limited to 8 km/s, a two-laser PDV system is developed that uses two lasers operating near 1550 nm to provide velocity measurement capabilities up to 16 km/s with the same bandwidth and sampling rate. The two-laser PDV system is used to obtain a continuous velocity history of the projectile throughout the entire launch cycle. These internal ballistics trajectories are used to compare different advanced concepts aimed at increasing the projectile velocity to well beyond 10 km/s.

Characterization of the Heme Pocket Structure and Ligand Binding Kinetics of Non-symbiotic Hemoglobins from the Model Legume Lotus japonicus.

PubMed

Calvo-Begueria, Laura; Cuypers, Bert; Van Doorslaer, Sabine; Abbruzzetti, Stefania; Bruno, Stefano; Berghmans, Herald; Dewilde, Sylvia; Ramos, Javier; Viappiani, Cristiano; Becana, Manuel

2017-01-01

Plant hemoglobins (Hbs) are found in nodules of legumes and actinorhizal plants but also in non-symbiotic organs of monocots and dicots. Non-symbiotic Hbs (nsHbs) have been classified into two phylogenetic groups. Class 1 nsHbs show an extremely high O 2 affinity and are induced by hypoxia and nitric oxide (NO), whereas class 2 nsHbs have moderate O 2 affinity and are induced by cold and cytokinins. The functions of nsHbs are still unclear, but some of them rely on the capacity of hemes to bind diatomic ligands and catalyze the NO dioxygenase (NOD) reaction (oxyferrous Hb + NO → ferric Hb + nitrate). Moreover, NO may nitrosylate Cys residues of proteins. It is therefore important to determine the ligand binding properties of the hemes and the role of Cys residues. Here, we have addressed these issues with the two class 1 nsHbs (LjGlb1-1 and LjGlb1-2) and the single class 2 nsHb (LjGlb2) of Lotus japonicus , which is a model legume used to facilitate the transfer of genetic and biochemical information into crops. We have employed carbon monoxide (CO) as a model ligand and resonance Raman, laser flash photolysis, and stopped-flow spectroscopies to unveil major differences in the heme environments and ligand binding kinetics of the three proteins, which suggest non-redundant functions. In the deoxyferrous state, LjGlb1-1 is partially hexacoordinate, whereas LjGlb1-2 shows complete hexacoordination (behaving like class 2 nsHbs) and LjGlb2 is mostly pentacoordinate (unlike other class 2 nsHbs). LjGlb1-1 binds CO very strongly by stabilizing it through hydrogen bonding, but LjGlb1-2 and LjGlb2 show lower CO stabilization. The changes in CO stabilization would explain the different affinities of the three proteins for gaseous ligands. These affinities are determined by the dissociation rates and follow the order LjGlb1-1 > LjGlb1-2 > LjGlb2. Mutations LjGlb1-1 C78S and LjGlb1-2 C79S caused important alterations in protein dynamics and stability, indicating a structural

Phytochelatin synthases of the model legume Lotus japonicus. A small multigene family with differential response to cadmium and alternatively spliced variants.

PubMed

Ramos, Javier; Clemente, Maria R; Naya, Loreto; Loscos, Jorge; Pérez-Rontomé, Carmen; Sato, Shusei; Tabata, Satoshi; Becana, Manuel

2007-03-01

The biosynthesis of phytochelatins and homophytochelatins has been studied in nodulated plants of the model legume Lotus (Lotus japonicus). In the first 6 to 24 h of treatment with cadmium (Cd), roots started to synthesize elevated amounts of both polypeptides, with a concomitant increase of glutathione and a decrease of homoglutathione, indicating the presence of active phytochelatin synthase (PCS) genes. Screening of transformation-competent artificial chromosome libraries allowed identification of a cluster of three genes, LjPCS1, LjPCS2, and LjPCS3, which were mapped at 69.0 cM on chromosome 1. The genes differ in exon-intron composition and responsiveness to Cd. Gene structures and phylogenetic analysis of the three protein products, LjPCS1-8R, LjPCS2-7N, and LjPCS3-7N, are consistent with two sequential gene duplication events during evolution of vascular plants. Two sites for alternative splicing in the primary transcripts were identified. One of them, involving intron 2 of the LjPCS2 gene, was confirmed by the finding of the two predicted mRNAs, encoding LjPCS2-7R in roots and LjPCS2-7N in nodules. The amino acid sequences of LjPCS2-7R (or LjPCS2-7N) and LjPCS3-7N share 90% identity, but have only 43% to 59% identity with respect to the typical PCS1 enzymes of Lotus and other plants. The unusual LjPCS2-7N and LjPCS3-7N proteins conferred Cd tolerance when expressed in yeast (Saccharomyces cerevisiae) cells, whereas the alternatively spliced form, LjPCS2-7R, differing only in a five-amino acid motif (GRKWK) did not. These results unveil complex regulatory mechanisms of PCS expression in legume tissues in response to heavy metals and probably to other developmental and environmental factors.

Performance and technical feasibility comparison of reusable launch systems: A synthesis of the ESA winged launcher studies

NASA Astrophysics Data System (ADS)

Berry, W.; Grallert, H.

1996-02-01

The paper presents a synthesis of the performance and technical feasibility assessment of 7 reusable launcher types, comprising 13 different vehicles, studied by European Industry for ESA in the ESA Winged Launcher Study in the period January 1988 to May 1994. The vehicles comprised single-stage-to-orbit (SSTO) and two-stage-to-orbit (TSTO) vehicles, propelled by either air-breathing/rocket propulsion or entirely by rocket propulsion. The results showed that an SSTO vehicle of the HOTOL-type, propelled by subsonic combustion air-breathing/rocket engines could barely deliver the specified payload mass and was aerodynamically unstable; that a TSTO vehicle of the Saenger type, employing subsonic combustion airbreathing propulsion in its first stage and rocket propulsion in its second stage, could readily deliver the specified payload mass and was found to be technically feasible and versatile; that an SSTO vehicle of the NASP type, propelled by supersonic combustion airbreathing/rocket propulsion was able to deliver a reduced payload mass, was very complex and required very advanced technologies; that an air-launched rocket propelled vehicle of the Interim HOTOL type, although technically feasible, could deliver only a reduced payload mass, being constrained by the lifting capability of the carrier airplane; that three different, entirely rocket-propelled vehicles could deliver the specified payload mass, were technically feasible but required relatively advanced technologies.

Characterization of the Heme Pocket Structure and Ligand Binding Kinetics of Non-symbiotic Hemoglobins from the Model Legume Lotus japonicus

PubMed Central

Calvo-Begueria, Laura; Cuypers, Bert; Van Doorslaer, Sabine; Abbruzzetti, Stefania; Bruno, Stefano; Berghmans, Herald; Dewilde, Sylvia; Ramos, Javier; Viappiani, Cristiano; Becana, Manuel

2017-01-01

Plant hemoglobins (Hbs) are found in nodules of legumes and actinorhizal plants but also in non-symbiotic organs of monocots and dicots. Non-symbiotic Hbs (nsHbs) have been classified into two phylogenetic groups. Class 1 nsHbs show an extremely high O2 affinity and are induced by hypoxia and nitric oxide (NO), whereas class 2 nsHbs have moderate O2 affinity and are induced by cold and cytokinins. The functions of nsHbs are still unclear, but some of them rely on the capacity of hemes to bind diatomic ligands and catalyze the NO dioxygenase (NOD) reaction (oxyferrous Hb + NO → ferric Hb + nitrate). Moreover, NO may nitrosylate Cys residues of proteins. It is therefore important to determine the ligand binding properties of the hemes and the role of Cys residues. Here, we have addressed these issues with the two class 1 nsHbs (LjGlb1-1 and LjGlb1-2) and the single class 2 nsHb (LjGlb2) of Lotus japonicus, which is a model legume used to facilitate the transfer of genetic and biochemical information into crops. We have employed carbon monoxide (CO) as a model ligand and resonance Raman, laser flash photolysis, and stopped-flow spectroscopies to unveil major differences in the heme environments and ligand binding kinetics of the three proteins, which suggest non-redundant functions. In the deoxyferrous state, LjGlb1-1 is partially hexacoordinate, whereas LjGlb1-2 shows complete hexacoordination (behaving like class 2 nsHbs) and LjGlb2 is mostly pentacoordinate (unlike other class 2 nsHbs). LjGlb1-1 binds CO very strongly by stabilizing it through hydrogen bonding, but LjGlb1-2 and LjGlb2 show lower CO stabilization. The changes in CO stabilization would explain the different affinities of the three proteins for gaseous ligands. These affinities are determined by the dissociation rates and follow the order LjGlb1-1 > LjGlb1-2 > LjGlb2. Mutations LjGlb1-1 C78S and LjGlb1-2 C79S caused important alterations in protein dynamics and stability, indicating a structural

Live Probiotic Lactobacillus johnsonii BS15 Promotes Growth Performance and Lowers Fat Deposition by Improving Lipid Metabolism, Intestinal Development, and Gut Microflora in Broilers.

PubMed

Wang, Hesong; Ni, Xueqin; Qing, Xiaodan; Zeng, Dong; Luo, Min; Liu, Lei; Li, Guangyao; Pan, Kangcheng; Jing, Bo

2017-01-01

Numerous studies have focused on the beneficial effects of probiotics in animals. Even so, additional information should be obtained about the mechanisms by which a useful probiotic strain successfully exerts such beneficial effects. In this study, we evaluated the effect of the dietary supplementation of both live and disrupted Lactobacillus johnsonii (LJ) strain BS15 in broilers at different ages. Specifically, growth performance, lipid metabolism, gut microbiota, intestinal development, and digestive ability of the broilers were assessed. A total of 180 1-day-old Cobb 500 chicks were randomly distributed into three groups. These chicks were fed diets supplemented with 1 × 10 6 colony-forming units (cfu) LJ per gram of feed (LJ group); 1 × 10 6 cfu disrupted LJ per gram of feed (D-LJ group); and de Man, Rogosa, and Sharpe liquid medium (control group), respectively, throughout a 42-day experimental period. The results demonstrated that LJ supplementation of feed had a positive effect on the average daily gain and starter feed conversion ratio. In addition, LJ supplementation of feed decreased serum triglyceride and low-density lipid cholesterol levels, as well as abdominal fat deposition. LJ also reduced the mRNA levels of lipoprotein lipase in adipose tissue and stearoyl-CoA desaturase-1 in the liver. LJ diminished the mRNA quantities of the sterol regulatory element binding protein-1c and fatty acid synthase, as well as increased the level of serum high-density lipid cholesterol. LJ increased the mRNA quantities of peroxisome proliferator-activated receptor α, acyl-CoA oxidase in the liver, and carnitine palmitoyltransferase-1. LJ also improved the intestinal development and digestive ability mainly by increasing the villus height/crypt depth ratio in the ileum. The probiotic increased the levels of epidermal growth factor and insulin-like growth factor-1, as well as the activities of trypsin and lipase in the jejunum and ileum. LJ exerted beneficial effects

A small scale lunar launcher for early lunar material utilization

NASA Technical Reports Server (NTRS)

Snow, W. R.; Kubby, J. A.; Dunbar, R. S.

1981-01-01

A system for the launching of lunar derived oxygen or raw materials into low lunar orbit or to L2 for transfer to low earth orbit is presented. The system described is a greatly simplified version of the conventional and sophisticated approach suggested by O'Neill using mass drivers with recirculating buckets. An electromagnetic accelerator is located on the lunar surface which launches 125 kg 'smart' containers of liquid oxygen or raw materials into a transfer orbit. Upon reaching apolune a kick motor is fired to circularize the orbit at 100 km altitude or L2. These containers are collected and their payloads transferred to a tanker OTV. The empty containers then have their kick motors refurbished and then are returned to the launcher site on the lunar surface for reuse. Initial launch capability is designed for about 500T of liquid oxygen delivered to low earth orbit per year with upgrading to higher levels, delivery of lunar soil for shielding, or raw materials for processing given the demand.

Acoustic and Vibration Environment for Crew Launch Vehicle Mobile Launcher

NASA Technical Reports Server (NTRS)

Vu, Bruce T.

2007-01-01

A launch-induced acoustic environment represents a dynamic load on the exposed facilities and ground support equipment (GSE) in the form of random pressures fluctuating around the ambient atmospheric pressure. In response to these fluctuating pressures, structural vibrations are generated and transmitted throughout the structure and to the equipment items supported by the structure. Certain equipment items are also excited by the direct acoustic input as well as by the vibration transmitted through the supporting structure. This paper presents the predicted acoustic and vibration environments induced by the launch of the Crew Launch Vehicle (CLV) from Launch Complex (LC) 39. The predicted acoustic environment depicted in this paper was calculated by scaling the statistically processed measured data available from Saturn V launches to the anticipated environment of the CLV launch. The scaling was accomplished by using the 5-segment Solid Rocket Booster (SRB) engine parameters. Derivation of vibration environment for various Mobile Launcher (ML) structures throughout the base and tower was accomplished by scaling the Saturn V vibration environment.

Inverse synthetic aperture radar imagery of a man with a rocket propelled grenade launcher

NASA Astrophysics Data System (ADS)

Tran, Chi N.; Innocenti, Roberto; Kirose, Getachew; Ranney, Kenneth I.; Smith, Gregory

2004-08-01

As the Army moves toward more lightly armored Future Combat System (FCS) vehicles, enemy personnel will present an increasing threat to U.S. soldiers. In particular, they face a very real threat from adversaries using shoulder-launched, rocket propelled grenade (RPG). The Army Research Laboratory has utilized its Aberdeen Proving Ground (APG) turntable facility to collect very high resolution, fully polarimetric Ka band radar data at low depression angles of a man holding an RPG. In this paper, we examine the resulting low resolution and high resolution range profiles; and based on the observed radar cross section (RCS) value, we attempt to determine the utility of Ka band radar for detecting enemy personnel carrying RPG launchers.

Spatial variability of damage around faults in the Joe Lott Tuff Member of the Mount Belknap Volcanics, southwestern Utah: An analog to faulting in tuff on Mars

NASA Astrophysics Data System (ADS)

Okubo, C. H.

2011-12-01

The equatorial layered deposits on Mars exhibit abundant evidence for the sustained presence of groundwater, and therefore insight into past water-related processes may be gained through the study of these deposits. Pyroclastic and evaporitic sediments are two broad lithologies that are known or inferred to comprise these deposits. Investigations into the effects of faulting on fluid flow potential through such Mars analog lithologies have been limited. Thus a study into the effects of faulting on fluid flow pathways through fine-grained pyroclastic sediments has been undertaken, and the results of this study are presented here. Faults and their damage zones can influence the trapping and migration of fluids by acting as either conduits or barriers to fluid flow. In clastic sedimentary rocks, the conductivity of fault damage zones is primarily a function of the microstructure of the host rock, stress history, phyllosilicate content, and cementation. The chemical composition of the host rock influences the mechanical strength of the grains, the susceptibility of the grains to alteration, and the availability of authigenic cements. The spatial distribution of fault-related damage is investigated within the Joe Lott Tuff Member of the Mount Belknap Volcanics, Utah. Damage is characterized by measuring fracture densities along the fault, and by mapping the gas permeability of the surrounding rock. The Joe Lott Tuff is a partially welded, crystal-poor, rhyolite ash-flow tuff of Miocene age. While the rhyolitic chemical composition of the Joe Lott Tuff is not analogous to the basaltic compositions expected for Mars, the mechanical behavior of a poorly indurated mixture of fine-grained glass and pumice is pertinent to understanding the fundamental mechanics of faulting in Martian pyroclastic sediments. Results of mapping around two faults are presented here. The first fault is entirely exposed in cross-section and has a down-dip height of ~10 m. The second fault is

Specifications and implementation of the RT MHD control system for the EC launcher of FTU

NASA Astrophysics Data System (ADS)

Galperti, C.; Alessi, E.; Boncagni, L.; Bruschi, A.; Granucci, G.; Grosso, A.; Iannone, F.; Marchetto, C.; Nowak, S.; Panella, M.; Sozzi, C.; Tilia, B.

2012-09-01

To perform real time plasma control experiments using EC heating waves by using the new fast launcher installed on FTU a dedicated data acquisition and elaboration system has been designed recently. A prototypical version of the acquisition/control system has been recently developed and will be tested on FTU machine in its next experimental campaign. The open-source framework MARTe (Multi-threaded Application Real-Time executor) on Linux/RTAI real-time operating system has been chosen as software platform to realize the control system. Standard open-architecture industrial PCs, based either on VME bus and CompactPCI bus equipped with standard input/output cards are the chosen hardware platform.

Very High Specific Energy, Medium Power Li/CFx Primary Battery for Launchers and Space Probes

NASA Astrophysics Data System (ADS)

Brochard, Paul; Godillot, Gerome; Peres, Jean Paul; Corbin, Julien; Espinosa, Amaya

2014-08-01

Benchmark with existing technologies shows the advantages of the lithium-fluorinated carbon (Li/CFx) technology for use aboard future launchers in terms of a low Total Cost of Ownership (TCO), especially for high energy demanding missions such as re-ignitable upper stages for long GTO+ missions and probes for deep space exploration.This paper presents the new results obtained on this chemistry in terms of electrical and climatic performances, abuse tests and life tests. Studies - co-financed between CNES and Saft - looked at a pure CFx version with a specific energy up to 500 Wh/kg along with a medium power of 80 to 100 W/kg.

JPSS-1 Mission Science Briefing

NASA Image and Video Library

2017-11-12

JPSS-1 Mission Science Briefing hosted by Steve Cole, NASA Communications, with Mitch Goldberg, Chief Program Scientist, NOAA Joint Polar Satellite System, Joe Pica, Director, NOAA National Weather Service Office of Observations, James Gleason, Senior Project Scientist, NASA Joint Polar Satellite System, and Jana Luis, Division Chief, CAL FIRE Predictive Services.

MLP-1 on Crawler Transporter 2 (CT-2)

NASA Image and Video Library

2017-03-22

NASA's upgraded crawler-transporter 2 (CT-2), carrying mobile launcher platform 1, moves slowly along the crawlerway at the agency's Kennedy Space Center in Florida. The crawler's upgrades and modifications will be monitored and tested under loaded conditions during its travel to the crawlerway Pad A/B split and back to the crawler yard to confirm it is ready to support the load of the mobile launcher carrying the Space Launch System with Orion atop for the first test flight, Exploration Mission 1. The Ground Systems Development and Operations Program at Kennedy is managing upgrades to the crawler.

Exploring Lightning Jump Characteristics

NASA Technical Reports Server (NTRS)

Chronis, Themis; Carey, Larry D.; Schultz, Christopher J.; Schultz, Elise; Calhoun, Kristin; Goodman, Steven J.

2014-01-01

This study is concerned with the characteristics of storms exhibiting an abrupt temporal increase in the total lightning flash rate (i.e., lightning jump, LJ). An automated storm tracking method is used to identify storm "clusters" and total lightning activity from three different lightning detection systems over Oklahoma, northern Alabama and Washington, D.C. On average and for different employed thresholds, the clusters that encompass at least one LJ (LJ1) last longer, relate to higher Maximum Expected Size of Hail, Vertical Integrated Liquid and lightning flash rates (area-normalized) than the clusters that did not exhibit any LJ (LJ0). The respective mean values for LJ1 (LJ0) clusters are 80 min (35 min), 14 mm (8 mm), 25 kg per square meter (18 kg per square meter) and 0.05 flash per min per square kilometer (0.01 flash per min per square kilometer). Furthermore, the LJ1 clusters are also characterized by slower decaying autocorrelation functions, a result that implies a less "random" behavior in the temporal flash rate evolution. In addition, the temporal occurrence of the last LJ provides an estimate of the time remaining to the storm's dissipation. Depending of the LJ strength (i.e., varying thresholds), these values typically range between 20-60 min, with stronger jumps indicating more time until storm decay. This study's results support the hypothesis that the LJ is a proxy for the storm's kinematic and microphysical state rather than a coincidental value.

Experimental Investigation Of Base Flow Buffeting On The Ariane 5 Launcher Using High Speed PIV

NASA Astrophysics Data System (ADS)

Schrijer, F. F. J.; Sciacchitano, A.; Scarrano, F.; Hannemann, K.; Pallegoix, J.-F.; Maseand, J. E. J.; Schwane, R.

2011-05-01

Experiments have been performed on a 1:60 scale Ariane 5 launcher in the DNW HST wind tunnel by means of two-component particle image velocimetry (2C-PIV). Measurements are performed for Mach 0.5 and Mach 0.8. The investigation focuses on studying the flow-buffeting phenomenon in the base of an Ariane V rocket. In total four configurations are tested: reference configuration, skirt, scoop and reference configuration without struts. It has been found that the presence of the struts has a large effect on the flow field; the secondary flow caused by the struts decreases the separated region and increases the overall turbulence. The skirt has the effect that the shear layer separates later and therefore does not reattach on the nozzle. Also in the separated region a secondary recirculation region is formed. For the scoop configuration it was observed that a second wake was formed by the scoop element causing the overall shear layer to become thicker. Finally using POD analysis two dominant modes are identified that can be associated to the separation bubble and shear layer dynamics.

Guidelines for internal optics optimization of the ITER EC H and CD upper launcher

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

Moro, A.; Bruschi, A.; Figini, L.

2014-02-12

The importance of localized injection of Electron Cyclotron waves to control Magneto-HydroDynamic instability is well assessed in tokamak physics and the set of four Electron Cyclotron (EC) Upper Launchers (UL) in ITER is mainly designed for this purpose. Each of the 4 ULs uses quasi-optical mirrors (shaping and planes, fixed and steerable) to redirect and focus 8 beams (in two rows, with power close to 1 MW per beam coming from the EC transmission lines) in the plasma region where the instability appears. Small beam dimensions and maximum beam superposition guarantee the necessary localization of the driven current. To achievemore » the goal of MHD stabilization with minimum EC power to preserve the energy confinement in the outer half of the plasma cross section, optimization of the quasi-optical design is required and a guideline of a strategy is presented. As a result of this process and following the guidelines indicated, modifications of the design (new mirrors positions, rotation axes and/or focal properties) will be proposed for the next step of an iterative process, including the mandatory compatibility check with the mechanical constraints.« less

X-15 #2 with test pilot Joe Walker

NASA Technical Reports Server (NTRS)

1961-01-01

Joe Walker is seen here after a flight in front of the X-15 #2 (56-6671) rocket-powered research aircraft. Joseph A. Walker was a Chief Research Pilot at the NASA Dryden Flight Research Center during the mid-1960s. He joined NACA in March 1945, and served as project pilot at the Edwards flight research facility on such pioneering research projects as the D-558-1, D-558-2, X-1, X-3, X-4, X-5, and the X-15. He also flew programs involving the F-100, F-101, F-102, F-104, and the B-47. Walker made the first NASA X-15 flight on March 25, 1960. He flew the research aircraft 24 times and achieved its highest altitude. He attained a speed of 4,104 mph (Mach 5.92) during a flight on June 27, 1962, and reached an altitude of 354,200 feet (67.08 miles) on August 22, 1963 (his last X-15 flight). This was one of three flights by Walker that achieved altitudes over 50 miles. Walker was killed on June 8, 1966, when his F-104 collided with the XB-70. The X-15 was a rocket-powered aircraft 50 ft long with a wingspan of 22 ft. It was a missile-shaped vehicle with an unusual wedge-shaped vertical tail, thin stubby wings, and unique fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was capable of developing 57,000 lb of rated thrust (actual thrust reportedly climbed to 60,000 lb). North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow-on program used the aircraft as a testbed to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudder surfaces on the

ESC-B: The Cryogenic Upper Stage for Europe's Heavy Lift Launcher Ariane 5ECB

NASA Astrophysics Data System (ADS)

Juhls, A.

2002-01-01

-A. Juhls, Astrium GmbH -M. Lepelletier, Snecma Moteurs -JM. Bahu, CNES -C. Poincheval, CNES. In the year 1998 the European ministerial council decided to initiate the Ariane 5 Plus programme in order to upgrade the European heavy lift launcher Ariane 5. The market was changing more rapidly than predicted showing steadily growing satellite mass and the demand for flexible missions while strong competitors were intensifying their preparations to enter the commercial business. The answer was to improve the Ariane 5 launcher by modifying the cryogenic first (or lower ?) stage and the solid boosters and by introducing two cryogenic upper stages in two steps: In order to cope with the short term need of a significant growth of GTO lift capacity up to 10 t the first denoted ESC-A shall enter commercial service in 2002. Four years later a more powerful second version shall take over enabling a GTO performance of 12 t and providing versatile mission capability. The paper will focus on this new cryogenic upper stage denoted ESC-B giving first a general description of main characteristics and constituents. The article will highlight different challenging aspects of the ESC-B development: Ambitious economical conditions regarding both limited development budgets and the strong need to reduce production cost require improved working methods and an adjustment of the conventional development logic, in particular regarding new verification methods. Furthermore Europe is now facing the complex combination of versatile mission capability together with a powerful cryogenic upper stage. The paper will present the approach to define reasonable mission scenarios in order to cover customer demands while avoiding too stringent system requirements. Along with VINCI, Europe's first expander cycle type engine featuring an extendable nozzle dedicated subsystems will be described which allow 4 re-ignitions and 6 hours of ballistic flight. The paper concludes with the summary of the

MLP-1 on Crawler Transporter 2 (CT-2)

NASA Image and Video Library

2017-03-22

Ground support technicians walk alongside NASA's upgraded crawler-transporter 2 (CT-2), carrying mobile launcher platform 1, as it slowly travels on the crawlerway at the agency's Kennedy Space Center in Florida. The crawler's upgrades and modifications will be monitored and tested under loaded conditions during its travel to the crawlerway Pad A/B split and back to the crawler yard to confirm it is ready to support the load of the mobile launcher carrying the Space Launch System with Orion atop for the first test flight, Exploration Mission 1. The Ground Systems Development and Operations Program at Kennedy is managing upgrades to the crawler.

MLP-1 on Crawler Transporter 2 (CT-2)

NASA Image and Video Library

2017-03-22

NASA's upgraded crawler-transporter 2 (CT-2), carrying mobile launcher platform 1, moves slowly along the crawlerway toward the Vehicle Assembly Building at the agency's Kennedy Space Center in Florida. The crawler's upgrades and modifications were monitored and tested during a loaded test to the crawlerway Pad A/B split. CT-2 will return to the crawler yard. The crawler is being tested to confirm it is ready to support the load of the mobile launcher carrying the Space Launch System with Orion atop for the first test flight, Exploration Mission 1. The Ground Systems Development and Operations Program at Kennedy is managing upgrades to the crawler.

High Field Side Lower Hybrid Current Drive Launcher Design for DIII-D

NASA Astrophysics Data System (ADS)

Wallace, G. M.; Leccacori, R.; Doody, J.; Vieira, R.; Shiraiwa, S.; Wukitch, S. J.; Holcomb, C.; Pinsker, R. I.

2017-10-01

Efficient off-axis current drive scalable to reactors is a key enabling technology for a steady-state tokamak. Simulations of DIII-D discharges have identified high performance scenarios with excellent lower hybrid (LH) wave penetration, single pass absorption and high current drive efficiency. The strategy was to adapt known launching technology utilized in previous experiments on C-Mod (poloidal splitter) and Tore Supra (bi-junction) and remain within power density limits established in JET and Tore Supra. For a 2 MW source power antenna, the launcher consists of 32 toroidal apertures and 4 poloidal rows. The aperture is 60 mm x 5 mm with 1 mm septa and the peak n| | is 2.7+/-0.2 for 90□ phasing. Eight WR187 waveguides are routed from the R-1 port down under the lower cryopump, under the existing divertor, and up the central column with the long waveguide dimension along the vacuum vessel. Above the inner strike point region, each waveguide is twisted to orient the long dimension perpendicular to the vacuum vessel and splits into 4 toroidal apertures via bi-junctions. To protect the waveguide, the inner wall radius will need to increase by 2.5 cm. RF, disruption, and thermal analysis of the latest design will be presented. Work supported by the U.S. Department of Energy, Office of Science, Office of Fusion Energy Sciences, using User Facility DIII-D, under Award Number DE-FC02-04ER54698 and by MIT PSFC cooperative agreement DE-SC0014264.

Zero Boil Off Cryogen Storage for Future Launchers

NASA Technical Reports Server (NTRS)

Valentian, D.; Plachta, D.; Kittel, P.; Hastings, L. J.; Salerno, Louis J.; Arnold, James O. (Technical Monitor)

2001-01-01

Zero boil off (ZBO) cryogen storage using both cryocoolers and passive insulation technologies will enable long-term exploration missions by allowing designers to optimize tankage without the need for excess cryogen storage to account for boil off. Studies of ZBO (zero boil off) have been on-going in the USA for several years. More recently, a review of the needs of advanced space propulsion took place in Europe. This showed the interest of the European community in cryogenic propulsion for planetary missions as well as the use of liquid hydrogen for large power electric propulsion (manned Mars missions). Although natural boiling could be acceptable for single leg missions, passive insulation techniques yield roughly a I% per month cryogen loss and this would not be cost effective for robotic planetary missions involving storage times greater than one year. To make economic sense, long-term exploration missions require lower tank capacity and longer storage times. Recent advances in cryocooler technology, resulting in vast improvements in both cooler efficiency and reliability, make ZBO is a clear choice for planetary exploration missions. Other, more near term applications of ZBO include boil-off reduction or elimination applied to first and upper stages of future earth-to-orbit (ETO) launchers. This would extend launch windows and reduce infrastructure costs. Successors to vehicles like Ariane 5 could greatly benefit by implementing ZBO. Zero Boil Off will only be successful in ETO launcher applications if it makes economic sense to implement. The energy cost is only a fraction of the total cost of buying liquid cryogen, the rest being transportation and other overhead. Because of this, higher boiling point cryogens will benefit more from on-board liquefaction, thus reducing the infrastructure costs. Since hydrogen requires a liquefier with at least a 17% efficiency just to break even from a cost standpoint, one approach for implementing ZBO in upper stages would

Rockot - a new cost effective launcher for small satellites

NASA Astrophysics Data System (ADS)

Mosenkis, Regina

1996-01-01

Daimler-Benz Aerospace of Germany and the Russian Khrunichev State Research and Production Space Center have formed a jointly owned EUROCKOT Launch Services GmbH to offer worldwide cost effective launch services for the ROCKOT launch vehicle. ROCKOT, produced by Khrunichev, builder of the famous PROTON launcher, aims at the market of small and medium size satellites ranging from 300 to 1800 kg to be launched into low earth or sunsynchronous orbits. These comprize scientific, earth observation and polar meteorological satellites as well as the new generation of small communication satellites in low earth orbits, known as the ``Constellations''. ROCKOT is a three stage liquid propellant launch vehicle, composed of a former Russian SS 19 strategic missile, which has been withdrawn from military use, and a highly sophisticated, flight-proven upper stage named Breeze, which is particularly suited for a variety of civic and commercial space applications. Usable payload envelope has a length of 4.75 meters and a maximum diameter of 2.26 meters for accomodating the payload within the payload fairing. ROCKOT can also accomodate multiple payloads which can be deployed into the same or different orbits. So far ROCKOT has been successfully launched three times from Baikonur. The commercial launch services on ROCKOT from the Plesetsk launch site, Russia, will begin in 1997 and will be available worldwide at a highly competitive price.

KENNEDY SPACE CENTER, FLA. - A worker sandblasts the surface behind the Mobile Launcher Platform on Launch Pad 39A . Routine maintenance includes sandblasting and repainting as preventive means to minimize corrosion.

NASA Image and Video Library

2003-09-12

KENNEDY SPACE CENTER, FLA. - A worker sandblasts the surface behind the Mobile Launcher Platform on Launch Pad 39A . Routine maintenance includes sandblasting and repainting as preventive means to minimize corrosion.

Design of a robust control law for the Vega launcher ballistic phase

NASA Astrophysics Data System (ADS)

Valli, Monica; Lavagna, Michèle R.; Panozzo, Thomas

2012-02-01

This work presents the design of a robust control law, and the related control system architecture, for the Vega launcher ballistic phase, taking into account the complete six degrees of freedom dynamics. To gain robustness a non-linear control approach has been preferred: more specifically the Lyapunov's second stability theorem has been exploited, being a very powerful tool to guarantee asymptotic stability of the controlled dynamics. The dynamics of Vega's actuators has also been taken into account. The system performance has been checked and analyzed by numerical simulations run on real mission data for different operational and configuration scenarios, and the effectiveness of the synthesized control highlighted: in particular scenarios including a wide range of composite's inertial configurations performing various typologies of maneuvers have been run. The robustness of the controlled dynamics has been validated by 100 cases Monte Carlo analysis campaign: the containment of the dispersion for the controlled variables - say the composite roll, yaw and pitch angles - confirmed the wide validity and generality of the proposed control law. This paper will show the theoretical approach and discuss the obtained results.

Does lemon juice increase radioiodine reaccumulation within the parotid glands more than if lemon juice is not administered?

PubMed

Kulkarni, Kanchan; Van Nostrand, Douglas; Atkins, Francis; Mete, Mihriye; Wexler, Jason; Wartofsky, Leonard

2014-02-01

The protective effect of sialagogues following I therapy became controversial after a study proposed that sialagogues increase the reaccumulation of I in the parotid glands (PGs) to a level higher than when sialagogues are not administered ('rebound effect'). The present study examined PG radiopharmacokinetics within 2-4 h after radioiodine administration to evaluate whether sialagogues cause a 'rebound effect'. This prospective study was conducted at the Medstar Washington Hospital Center. The study patients had (i) differentiated thyroid cancer, (ii) no history of salivary gland disease or medications affecting the salivary glands, (iii) a clinical salivary scan (SS) with lemon juice (LJ) (SSwLJ) that was performed before I therapy, and (iv) a second SS performed without LJ (SSwoLJ) performed prior to I therapy after giving informed consent. Each PG was assessed for I uptake using time-activity curves (TACs) that were (i) corrected for background and decay, (ii) smoothed using a seven-point unweighted moving average, and (iii) normalized to the administered I activity. TACs of the SSwLJ and SSwoLJ were compared with activity at each time point over 120 min. Areas under the TACs for the PGs were calculated for each gland's SSwLJ and SSwoLJ, and the relative percentage change in potential radiation absorbed dose (PRAD) was calculated. A total of 2100 time points were analyzed in nine patients (18 PGs). I activity in the PGs on SSwLJ exceeded activity seen on the SSwoLJ at 134 time points (6.3%), and 98 (73%) of these were on the basis of spontaneous salivation during SSwoLJ. Mean percentage decrease in relative PRAD was 34.2±17.4% (range, 3.1-66.1%). During the time period studied, LJ administration did not result in a 'rebound effect' but resulted in mean relative decrease of 34.2% in PRAD to the PGs.

Launcher Roadmap for the CrVI Substitution of Surface Treatments. Screening of Trivalent-Chromium Conversion Solutions and First Promising Results for Repair Applications on Aluminium Alloys

NASA Astrophysics Data System (ADS)

Debout, Vincent; Pettier, Sophie

2014-06-01

Airbus Defence and Space, Space System is involved in a global roadmap for launchers in order to substitute hexavalent chromium (CrVI) and Cadmium in the current surface treatments on metallic structures.Within this framework, a screening of trivalent chromium (CrIII) conversion solutions for touch-up applications has been carried out since this step is crucial to perform local application or to repair minor damages on launcher structures but it leads to higher risks of exposure for the workers.Three commercial CrIII conversion solutions have been evaluated on high performance aluminum alloys such as AA2024 T3 and AA7175 T7351 that are often used as structural materials.This preliminary investigation highlights the effect of surface preparation, rinsing and conversion process on the final corrosion performance of conversion coatings (CCs). The results are also discussed in terms of visual aspect and adhesion with new Cr-free primers.Two operating sets of parameters are identified with promising results that represent the first steps towards the development of a new Cr-free touch-up process.

Renoprotective Effects of a Highly Selective A3 Adenosine Receptor Antagonist in a Mouse Model of Adriamycin-induced Nephropathy.

PubMed

Min, Hye Sook; Cha, Jin Joo; Kim, Kitae; Kim, Jung Eun; Ghee, Jung Yeon; Kim, Hyunwook; Lee, Ji Eun; Han, Jee Young; Jeong, Lak Shin; Cha, Dae Ryong; Kang, Young Sun

2016-09-01

The concentration of adenosine in the normal kidney increases markedly during renal hypoxia, ischemia, and inflammation. A recent study reported that an A3 adenosine receptor (A3AR) antagonist attenuated the progression of renal fibrosis. The adriamycin (ADX)-induced nephropathy model induces podocyte injury, which results in severe proteinuria and progressive glomerulosclerosis. In this study, we investigated the preventive effect of a highly selective A3AR antagonist (LJ1888) in ADX-induced nephropathy. Three groups of six-week-old Balb/c mice were treated with ADX (11 mg/kg) for four weeks and LJ1888 (10 mg/kg) for two weeks as following: 1) control; 2) ADX; and 3) ADX + LJ1888. ADX treatment decreased body weight without a change in water and food intake, but this was ameliorated by LJ1888 treatment. Interestingly, LJ1888 lowered plasma creatinine level, proteinuria, and albuminuria, which had increased during ADX treatment. Furthermore, LJ1888 inhibited urinary nephrin excretion as a podocyte injury marker, and urine 8-isoprostane and kidney lipid peroxide concentration, which are markers of oxidative stress, increased after injection of ADX. ADX also induced the activation of proinflammatory and profibrotic molecules such as TGF-β1, MCP-1, PAI-1, type IV collagen, NF-κB, NOX4, TLR4, TNFα, IL-1β, and IFN-γ, but they were remarkably suppressed after LJ1888 treatment. In conclusion, our results suggest that LJ1888 has a renoprotective effect in ADX-induced nephropathy, which might be associated with podocyte injury through oxidative stress. Therefore, LJ1888, a selective A3AR antagonist, could be considered as a potential therapeutic agent in renal glomerular diseases which include podocyte injury and proteinuria.

Flavone synthases from Lonicera japonica and L. macranthoides reveal differential flavone accumulation

NASA Astrophysics Data System (ADS)

Wu, Jie; Wang, Xiao-Chen; Liu, Yang; Du, Hui; Shu, Qing-Yan; Su, Shang; Wang, Li-Jin; Li, Shan-Shan; Wang, Liang-Sheng

2016-01-01

Flavones are important secondary metabolites found in many plants. In Lonicera species, flavones contribute both physiological and pharmaceutical properties. However, flavone synthase (FNS), the key enzyme responsible for flavone biosynthesis, has not yet been characterized in Lonicera species. In this study, FNSII genes were identified from Lonicera japonica Thunb. and L. macranthoides Hand.-Mazz. In the presence of NADPH, the recombinant cytochrome P450 proteins encoded by LjFNSII-1.1, LjFNSII-2.1, and LmFNSII-1.1 converted eriodictyol, naringenin, and liquiritigenin to the corresponding flavones directly. The different catalytic properties between LjFNSII-2.1 and LjFNSII-1.1 were caused by a single amino acid substitution at position 242 (glutamic acid to lysine). A methionine at position 206 and a leucine at position 381 contributed considerably to the high catalytic activity of LjFNSII-1.1. In addition, LjFNSII-1.1&2.1 and LmFNSII-1.1 also biosynthesize flavones that were further modified by O-glycosylation in transgenic tobacco. The expression levels of the FNSII genes were consistent with flavone accumulation patterns in flower buds. Our findings suggested that the weak catalytic activity of LmFNSII-1.1 and the relatively low expression of LmFNSII-1.1 in flowers might be responsible for the low levels of flavone accumulation in flower buds of L. macranthoides.

Function of glutathione peroxidases in legume root nodules.

PubMed

Matamoros, Manuel A; Saiz, Ana; Peñuelas, Maria; Bustos-Sanmamed, Pilar; Mulet, Jose M; Barja, Maria V; Rouhier, Nicolas; Moore, Marten; James, Euan K; Dietz, Karl-Josef; Becana, Manuel

2015-05-01

Glutathione peroxidases (Gpxs) are antioxidant enzymes not studied so far in legume nodules, despite the fact that reactive oxygen species are produced at different steps of the symbiosis. The function of two Gpxs that are highly expressed in nodules of the model legume Lotus japonicus was examined. Gene expression analysis, enzymatic and nitrosylation assays, yeast cell complementation, in situ mRNA hybridization, immunoelectron microscopy, and LjGpx-green fluorescent protein (GFP) fusions were used to characterize the enzymes and to localize each transcript and isoform in nodules. The LjGpx1 and LjGpx3 genes encode thioredoxin-dependent phospholipid hydroperoxidases and are differentially regulated in response to nitric oxide (NO) and hormones. LjGpx1 and LjGpx3 are nitrosylated in vitro or in plants treated with S-nitrosoglutathione (GSNO). Consistent with the modification of the peroxidatic cysteine of LjGpx3, in vitro assays demonstrated that this modification results in enzyme inhibition. The enzymes are highly expressed in the infected zone, but the LjGpx3 mRNA is also detected in the cortex and vascular bundles. LjGpx1 is localized to the plastids and nuclei, and LjGpx3 to the cytosol and endoplasmic reticulum. Based on yeast complementation experiments, both enzymes protect against oxidative stress, salt stress, and membrane damage. It is concluded that both LjGpxs perform major antioxidative functions in nodules, preventing lipid peroxidation and other oxidative processes at different subcellular sites of vascular and infected cells. The enzymes are probably involved in hormone and NO signalling, and may be regulated through nitrosylation of the peroxidatic cysteine essential for catalytic function. © The Author 2015. Published by Oxford University Press on behalf of the Society for Experimental Biology.

KENNEDY SPACE CENTER, FLA. - Sandblasting begins on the Mobile Launcher Platform on Launch Pad 39A to remove corrosion before repainting. Routine maintenance includes sandblasting and repainting as preventive means to minimize corrosion.

NASA Image and Video Library

2003-09-12

KENNEDY SPACE CENTER, FLA. - Sandblasting begins on the Mobile Launcher Platform on Launch Pad 39A to remove corrosion before repainting. Routine maintenance includes sandblasting and repainting as preventive means to minimize corrosion.

Large Spun Formed Friction-Stir Welded Tank Domes for Liquid Propellant Tanks Made from AA2195: A Technology Demonstration for the Next Generation of Heavy Lift Launchers

NASA Technical Reports Server (NTRS)

Stachulla, M.; Pernpeinter, R.; Brewster J.; Curreri, P.; Hoffman, E.

2010-01-01

Improving structural efficiency while reducing manufacturing costs are key objectives when making future heavy-lift launchers more performing and cost efficient. The main enabling technologies are the application of advanced high performance materials as well as cost effective manufacture processes. This paper presents the status and main results of a joint industrial research & development effort to demonstrate TRL 6 of a novel manufacturing process for large liquid propellant tanks for launcher applications. Using high strength aluminium-lithium alloy combined with the spin forming manufacturing technique, this development aims at thinner wall thickness and weight savings up to 25% as well as a significant reduction in manufacturing effort. In this program, the concave spin forming process is used to manufacture tank domes from a single flat plate. Applied to aluminium alloy, this process allows reaching the highest possible material strength status T8, eliminating numerous welding steps which are typically necessary to assemble tank domes from 3D-curved panels. To minimize raw material costs for large diameter tank domes for launchers, the dome blank has been composed from standard plates welded together prior to spin forming by friction stir welding. After welding, the dome blank is contoured in order to meet the required wall thickness distribution. For achieving a material state of T8, also in the welding seams, the applied spin forming process allows the required cold stretching of the 3D-curved dome, with a subsequent ageing in a furnace. This combined manufacturing process has been demonstrated up to TRL 6 for tank domes with a 5.4 m diameter. In this paper, the manufacturing process as well as test results are presented. Plans are shown how this process could be applied to future heavy-lift launch vehicles developments, also for larger dome diameters.

Excretion into feces of asialo GM1 in the murine digestive tract and Lactobacillus johnsonii exhibiting binding ability toward asialo GM1. A possible role of epithelial glycolipids in the discharge of intestinal bacteria.

PubMed

Iwamori, Masao; Iwamori, Yuriko; Adachi, Shigeki; Nomura, Taisei

2011-01-01

In the digestive tract of mice (HR-1, 5 months old, ♀), asialo GM1 (GA1) exhibiting receptor activity toward several intestinal bacteria was preferentially expressed in the small intestine. Also, less than 10% of GA1 in the small intestine was converted into fucosylated and sulfated derivatives, but it was completely converted to fucosyl GA1 (FGA1) in the stomach, cecum and colon. Among the lipid components in these tissues, glycolipids other than Forssman antigen and cholesterol sulfate (CS) were present in the digestive tract contents. However, sulfated GA1, sulfatide and fucosyl GM1 in the gastro-intestinal contents were not present in the cecal and colonic contents, in which the major glycolipids were ceramide monohexoside (CMH), GA1 and FGA1. The total amount of GA1 in the whole contents was 20% of that in the tissues. Thus, glycolipids were stable during the process of digestion, and excreted from the body together with cholesterol and CS. On the other hand, Lactobacillus johnsonii (LJ), whose receptor is GA1, was detected in the cecal and colonic contents on sequential analysis of 16S-ribosomal RNA and TLC-immunostaining of antigenic glycolipids with anti-LJ antiserum. LJ was found to comprise 20% of the total bacteria cultured in the lactobacillus medium under aerobic conditions, and to be present in the cecal and colonic contents, 9.8 × 10(7) cells versus 37 μg GA1 and 1.4 × 10(8) cells versus 49 μg GA1, respectively. Thus, GA1 in the contents might facilitate the discharge of intestinal bacteria by becoming attached them to prevent their irregular diffusion.

Cryogenic pellet launcher adapted for controlling of tokamak plasma edge instabilities.

PubMed

Lang, P T; Cierpka, P; Harhausen, J; Neuhauser, J; Wittmann, C; Gál, K; Kálvin, S; Kocsis, G; Sárközi, J; Szepesi, T; Dorner, C; Kauke, G

2007-02-01

One of the main challenges posed recently on pellet launcher systems in fusion-oriented plasma physics is the control of the plasma edge region. Strong energy bursts ejected from the plasma due to edge localized modes (ELMs) can form a severe threat for in-vessel components but can be mitigated by sufficiently frequent triggering of the underlying instabilities using hydrogen isotope pellet injection. However, pellet injection systems developed mainly for the task of ELM control, keeping the unwanted pellet fueling minimized, are still missing. Here, we report on a novel system developed under the premise of its suitability for control and mitigation of plasma edge instabilities. The system is based on the blower gun principle and is capable of combining high repetition rates up to 143 Hz with low pellet velocities. Thus, the flexibility of the accessible injection geometry can be maximized and the pellet size kept low. As a result the new system allows for an enhancement in the tokamak operation as well as for more sophisticated experiments investigating the underlying physics of the plasma edge instabilities. This article reports on the design of the new system, its main operational characteristics as determined in extensive test bed runs, and also its first test at the tokamak experiment ASDEX Upgrade.

Inherent work suit buoyancy distribution: effects on lifejacket self-righting performance.

PubMed

Barwood, Martin J; Long, Geoffrey M; Lunt, Heather; Tipton, Michael J

2014-09-01

Accidental immersion in cold water is an occupational risk. Work suits and life jackets (LJ) should work effectively in combination to keep the airway clear of the water (freeboard) and enable self-righting. We hypothesized that inherent buoyancy, in the suit or LJ, would be beneficial for enabling freeboard, but its distribution may influence LJ self-righting. Six participants consented to complete nine immersions. Suits and LJ tested were: flotation suit (FLOAT; 85 N inherent buoyancy); oilskins 1 (OS-1) and 2 (OS-2), both with no inherent buoyancy; LJs (inherent buoyancy/buoyancy after inflation/total buoyancy), LJ-1 50/150/200 N, LJ-2 0/290/290 N, LJ-3 80/190/270 N. Once dressed, the subject entered an immersion pool where uninflated freeboard, self-righting performance, and inflated freeboard were measured. Data were compared using Friedman's test to the 0.05 alpha level. All suits and LJs enabled uninflated and inflated freeboard, but differences were seen between the suits and LJs. Self-righting was achieved on 43 of 54 occasions, irrespective of suit or LJ. On all occasions that self-righting was not achieved, this occurred in an LJ that included inherent buoyancy (11/54 occasions). Of these 11 failures, 8 occurred (73% of occasions) when the FLOAT suit was being worn. LJs that included inherent buoyancy, that are certified as effective on their own, worked less effectively from the perspective of self-righting in combination with a work suit that also included inherent buoyancy. Equipment that is approved for use in the workplace should be tested in combination to ensure adequate performance in an emergency scenario.

The design of a light aircraft automated dropsonde launcher

NASA Astrophysics Data System (ADS)

Pasken, Gregory R.

The use of the National Center for Atmospheric Research's dropsonde system is currently limited to large NASA, NSF and NOAA operated research aircraft, which are expensive to fly and are over-subscribed. Designing a new dropsonde system for a smaller, less expensive to operate light aircraft will make the dropsonde system available to a much wider research community. To test this concept, a dropsonde launch system designed to fit in the cargo door of a twin engine Piper Seminole is developed and tested. Although the launch system for the light aircraft dropsonde launcher has gone through many designs, a prototype is built and tested from the final design using Tetra for the computation fluid dynamics and stress testing, as Tetra has material properties for solids as well as fluids. The design is further tested in the wind tunnel. These tests show that the new design is a viable alternative for light aircraft, thus allowing dropsondes to be more widely used. The results of the ABAQUS, SC Tetra simulations, and the wind tunnel results of the final design are covered and discussed. The settings used for the ABAQUS and SC Tetra simulations are described in detail. ABAQUS simulations are conducted to perform stress testing and SC Tetra is used for CFD simulations. The SC Tetra simulations provide a more comprehensive picture of the design, as SC Tetra is able to perform the stress testing, as well as pressure testing, allowing for more accurate results. The limitations of ABAQUS simulations require numerous assumptions for loading that may or may not be realistic.

Type 1 diabetes

MedlinePlus

... Larsen PR, Kronenberg HM, eds. Williams Textbook of Endocrinology . 13th ed. Philadelphia, PA: Elsevier; 2016:chap 32. ... Groot LJ, de Kretser DM, et al, eds. Endocrinology: Adult and Pediatric . 7th ed. Philadelphia, PA: Elsevier ...

NASA DC-8 Ground Support Technician Joe Niquette performs routine maintenance on the DC-8 aircraft in Punta Arenas, Chile

NASA Image and Video Library

2004-03-17

NASA DC-8 Ground Support Technician Joe Niquette performs routine maintenance on the DC-8 aircraft at Carlos Ibanez del Campo International Airport in Punta Arenas, Chile. AirSAR 2004 is a three-week expedition by an international team of scientists that is using an all-weather imaging tool, called the Airborne Synthetic Aperture Radar (AirSAR) which is located onboard NASA's DC-8 airborne laboratory. Scientists from many parts of the world including NASA's Jet Propulsion Laboratory are combining ground research done in several areas in Central and South America with NASA's AirSAR technology to improve and expand on the quality of research they are able to conduct. In South America and Antarctica, AirSAR will collect imagery and data to help determine the contribution of Southern Hemisphere glaciers to sea level rise due to climate change. In Patagonia, researchers found this contribution had more than doubled from 1995 to 2000, compared to the previous 25 years. AirSAR data will make it possible to determine whether that trend is decreasing, continuing or accelerating. AirSAR will also provide reliable information on ice shelf thickness to measure the contribution of the glaciers to sea level.

Lightweight Towed Howitzer Demonstrator. Phase 1 and Partial Phase 2. Volume B. Technical Presentations - Part 1.

DTIC Science & Technology

1987-04-01

tray hsg assy 1 85 5 62360 . ..Frame 1 TRAD Ti 70 0.16 281 45 6 G2370 . ..Wrap 1 Kevlar/epoxy 70 0.05 700 35 6 62380 . ..Coating 1 Urethane 70 0.05...CL -4L- I-J .4cm=CLC ~LU LAJL~ I.-- LL== L6 0 - -JA z ~ LA =c = La z 4c > =w ZwI . z C/)-- oc W LA. 0z C 0 CI. CC Z u z LJ -6 C-.- -4 mAC. L6 w z 4c0

78 FR 76822 - 36(b)(1) Arms Sales Notification

Federal Register 2010, 2011, 2012, 2013, 2014

2013-12-19

... missiles, containers, spare and repair parts, support equipment, tools and test equipment, publications and... missiles, 7 Fly-to-Buy TOW2A missiles, containers, spare and repair parts, support equipment, tools and... thermal) for the launcher to track and guide the missile in flight. Guidance commands from the launcher...

Accurate Monte Carlo simulations on FCC and HCP Lennard-Jones solids at very low temperatures and high reduced densities up to 1.30

NASA Astrophysics Data System (ADS)

Adidharma, Hertanto; Tan, Sugata P.

2016-07-01

Canonical Monte Carlo simulations on face-centered cubic (FCC) and hexagonal closed packed (HCP) Lennard-Jones (LJ) solids are conducted at very low temperatures (0.10 ≤ T∗ ≤ 1.20) and high densities (0.96 ≤ ρ∗ ≤ 1.30). A simple and robust method is introduced to determine whether or not the cutoff distance used in the simulation is large enough to provide accurate thermodynamic properties, which enables us to distinguish the properties of FCC from that of HCP LJ solids with confidence, despite their close similarities. Free-energy expressions derived from the simulation results are also proposed, not only to describe the properties of those individual structures but also the FCC-liquid, FCC-vapor, and FCC-HCP solid phase equilibria.

U.S. EPA, Pesticide Product Label, 2, NITRO-2-ETHYL-1, 3-PROPANEDIOL, 03/19/1969

EPA Pesticide Factsheets

2011-04-13

... ( 1,1,') c.;. II v ,> U .... · 1 jul ey , '. ,J • I'll L 1'1Il i, 'iiJG, SIP, • (lS) J. L. Ril~U:~UIliL't', J. Ot'g. CI,,·iil. g, lH2-U:i'1 (L'j'iu). (L7) V 1 •• 1 . • lJ.:->. J 1 I r <;. ...

Hidden Cameras: Everything You Need to Know About Covert Recording, Undercover Cameras and Secret Filming Plomin Joe Hidden Cameras: Everything You Need to Know About Covert Recording, Undercover Cameras and Secret Filming 224pp £12.99 Jessica Kingsley 9781849056434 1849056439 [Formula: see text].

PubMed

2016-05-27

LAST YEAR, the Care Quality Commission issued guidance to families on using hidden cameras if they are concerned that their relatives are being abused or receiving poor care. Filming in care settings has also resulted in high profile prosecutions, and numerous TV documentaries. Joe Plomin, the author, was the undercover producer who exposed the abuse at Winterbourne View, near Bristol, in 2011.

1. MAGAZINE COMPLEX, O, P, AND Q. MAGAZINE P IN ...

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

1. MAGAZINE COMPLEX, O, P, AND Q. MAGAZINE P IN BACKGROUND, LOOKING NORTHEAST. - NIKE Missile Base C-84, Underground Storage Magazines & Launcher-Loader Assemblies, Easternmost portion of launch area, Barrington, Cook County, IL

Update on Progress of Space Station Integrated Kinetic Launcher for Orbital Payload Systems (SSIKLOPS) - Cyclops

NASA Technical Reports Server (NTRS)

Newswander, Daniel; Smith, James P.; Lamb, Craig R.; Ballard, Perry G.

2014-01-01

The Space Station Integrated Kinetic Launcher for Orbital Payload Systems (SSIKLOPS), known as "Cyclops" to the International Space Station (ISS) community, was introduced last August (2013) during Technical Session V: From Earth to Orbit of the 27th Annual AIAA/USU Conference on Small Satellites. Cyclops is a collaboration between the NASA ISS Program, NASA Johnson Space Center Engineering, and Department of Defense (DoD) Space Test Program (STP) communities to develop a dedicated 50-100 kg class ISS small satellite deployment system. This paper will address the progress of Cyclops through its fabrication, assembly, flight certification, and on-orbit demonstration phases. It will also go into more detail regarding its anatomy, its satellite deployment concept of operations, and its satellite interfaces and requirements. Cyclops is manifested to fly on Space-X 4 which is currently scheduled in July 2014 with its initial satellite deployment demonstration of DoD STP's SpinSat and UT/TAMU's Lonestar satellites being late summer or fall of 2014.

78 FR 76825 - 36(b)(1) Arms Sales Notification

Federal Register 2010, 2011, 2012, 2013, 2014

2013-12-19

... RF missiles, 91 TOW-2A Fly-to-Buy missiles, 49 TOW-2B Fly-to-Buy missiles, containers, spare and... missiles, containers, spare and repair parts, support equipment, tools and test equipment, publications and... launcher to track and guide the missile in flight. Guidance commands from the launcher are provided to the...

The Ardennes Campaign Simulation Data Base (ACSDB). Volume 1. Volume 2

DTIC Science & Technology

1990-02-07

Railway Artillery Battalion RRArtBt Railway Artillery Battery SS Schutzstaffeln (indicates combat elements of SS -- Waffen SS) SSArtBN SS Artillery...34 Rocket Launcher) Battalion VWBty Volkswerfer ("People’s" Rocket Launcher) Battery VTB Volga Tartar Battalion Note: SS = Waffen SS (Schutz Staffeln

X-15 with test pilot Capt. Joe Engle

NASA Technical Reports Server (NTRS)

1965-01-01

Captain Joe Engle is seen here next to the X-15-2 (56-6671) rocket-powered research aircraft after a flight. Engle made 16 flights in the X-15 between October 7, 1963, and October 14, 1965. Three of the flights, on June 29, August 10, and October 14, 1965, were above 50 miles, qualifying him for astronaut wings under the Air Force definition. (NASA followed the international definition of space as starting at 62 miles.) Engle was selected as a NASA astronaut in 1966, making him the only person who had flown in space before being selected as an astronaut. First assigned to the Apollo program, he served on the support crew for Apollo X and then as backup lunar module pilot for Apollo XIV. In 1977, he was commander of one of two crews who were launched from atop a modified Boeing 747 in order to conduct approach and landing tests with the Space Shuttle Enterprise. Then in November 1981, he commanded the second flight of the Shuttle Columbia and manually flew the re-entry--performing 29 flight test maneuvers--from Mach 25 through landing roll out. This was the first and, so far, only time that a winged aerospace vehicle has been manually flown from orbit through landing. He accumulated the last of his 224 hours in space when he commanded the Shuttle Discovery during STS-51-I in August of 1985. The X-15 was a rocket-powered aircraft 50 ft long with a wingspan of 22 ft. It was a missile-shaped vehicle with an unusual wedge-shaped vertical tail, thin stubby wings, and unique fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was capable of developing 57,000 lb of rated thrust (actual thrust reportedly climbed to 60,000 lb). North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures

78 FR 695 - 36(b)(1) Arms Sales Notification

Federal Register 2010, 2011, 2012, 2013, 2014

2013-01-04

... Consideration for Purchase: 7 M142 High Mobility Artillery Rocket System (HIMARS) Launchers with the Universal... M68A2 Trainers, 1 Advanced Field Artillery Tactical Data System (AFATDS); 2 M1151A1 High Mobility..., transportation, wheeled vehicles, communications equipment, spare and repair parts, support equipment, tools and...

Wave induced density modification in RF sheaths and close to wave launchers

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

Van Eester, D., E-mail: d.van.eester@fz-juelich.de; Crombé, K.; Department of Applied Physics, Ghent University, Ghent

2015-12-10

With the return to full metal walls - a necessary step towards viable fusion machines - and due to the high power densities of current-day ICRH (Ion Cyclotron Resonance Heating) or RF (radio frequency) antennas, there is ample renewed interest in exploring the reasons for wave-induced sputtering and formation of hot spots. Moreover, there is experimental evidence on various machines that RF waves influence the density profile close to the wave launchers so that waves indirectly influence their own coupling efficiency. The present study presents a return to first principles and describes the wave-particle interaction using a 2-time scale modelmore » involving the equation of motion, the continuity equation and the wave equation on each of the time scales. Through the changing density pattern, the fast time scale dynamics is affected by the slow time scale events. In turn, the slow time scale density and flows are modified by the presence of the RF waves through quasilinear terms. Although finite zero order flows are identified, the usual cold plasma dielectric tensor - ignoring such flows - is adopted as a first approximation to describe the wave response to the RF driver. The resulting set of equations is composed of linear and nonlinear equations and is tackled in 1D in the present paper. Whereas the former can be solved using standard numerical techniques, the latter require special handling. At the price of multiple iterations, a simple ’derivative switch-on’ procedure allows to reformulate the nonlinear problem as a sequence of linear problems. Analytical expressions allow a first crude assessment - revealing that the ponderomotive potential plays a role similar to that of the electrostatic potential arising from charge separation - but numerical implementation is required to get a feeling of the full dynamics. A few tentative examples are provided to illustrate the phenomena involved.« less

Steady-State Cycle Deck Launcher Developed for Numerical Propulsion System Simulation

NASA Technical Reports Server (NTRS)

VanDrei, Donald E.

1997-01-01

industry and NASA. The NPSS Steady-State Cycle Deck team released a batch version of the Steady-State Cycle Deck in March 1996. Version 1.1 was released in June 1996. During fiscal 1997, NPSS accepted enhancements and modifications to the Steady-State Cycle Deck launcher. Consistent with NPSS' commercialization plan, these modifications will be done by a third party that can provide long-term software support.

The Development of a Single Tank Tactical Exercise for Training M1 Tank Commanders

DTIC Science & Technology

1987-06-01

Evaluate the Conduct of Training NL NL NS Fire an M250 Grenade Launcher S S NS Identify Adjoining Map Sheets S S NS Identify Terrain Features on a Map S S...the Commander’s Weapon Station Establish, Enter, and Leave a Radio Net Estimate Range Evaluate the Conduct of Training Fire an M250 Grenade Launcher...from the Commander’s Weapon S Station (CWS) Fire an M250 Smoke Grenade Launcher Set Headspace and Timing on a Caliber .50 M2 HB Machinegun Zero a

EM-1 Countdown Simulation with Charlie Blackwell-Thompson

NASA Image and Video Library

2018-03-29

Main Propulsion System Engineers Krista Riggs, left, and Joe Pavicic, both with Jacobs, monitor operations from their consoles in Firing Room 1 at the Kennedy Space Center's Launch Control Center during a countdown simulation for Exploration Mission 1. It was the agency's first simulation of a portion of the countdown for the first launch of a Space Launch System rocket and Orion spacecraft that will eventually take astronauts beyond low-Earth orbit to destinations such as the Moon and Mars.

Design and Characterization of Thin Stainless Steel Burst Disks for Increasing Two-Stage Light Gas Launcher Efficiency

NASA Technical Reports Server (NTRS)

Tylka, Jonathan M.; Johnson, Kenneth L.; Henderson, Donald; Rodriguez, Karen

2012-01-01

Laser etched 300 series Stainless Steel Burst Disks (SSBD) ranging between 0.178 mm (0.007-in.) and 0.508mm (0.020-in.) thick were designed for use in a 17-caliber two-stage light gas launcher. First, a disk manufacturing method was selected using a combination of wire electrical discharge machining (EDM) to form the blank disks and laser etching to define the pedaling fracture pattern. Second, a replaceable insert was designed to go between the SSDB and the barrel. This insert reduced the stress concentration between the SSBD and the barrel, providing a place for the petals of the SSDB to open, and protecting the rifling on the inside of the barrel. Thereafter, a design of experiments was implemented to test and characterize the burst characteristics of SSBDs. Extensive hydrostatic burst testing of the SSBDs was performed to complete the design of experiments study with one-hundred and seven burst tests. The experiment simultaneously tested the effects of the following: two SSBD material states (full hard, annealed); five SSBD thicknesses 0.178, 0.254, 0.305, 0.381 mm (0.007, 0.010, 0.012, 0.015, 0.020-in.); two grain directions relative); number of times the laser etch pattern was repeated (varies between 5-200 times); two heat sink configurations (with and without heat sink); and, two barrel configurations (with and without insert). These tests resulted in the quantification of the relationship between SSBD thickness, laser etch parameters, and desired burst pressure. Of the factors investigated only thickness and number of laser etches were needed to develop a mathematical relationship predicting hydrostatic burst pressure of disks using the same barrel configuration. The fracture surfaces of two representative SSBD bursts were then investigated with a scanning electron microscope, one burst hydrostatically in a fixture and another dynamically in the launcher. The fracture analysis verified that both burst conditions resulted in a ductile overload failure

McDonnell F4-H1 Airplane Rocket Model

NASA Image and Video Library

1957-12-23

L57-2809 Rocket model of McDonnell F4-H1 airplane on Terrier launcher with Nike booster, June 17, 1957. Photograph published in A New Dimension Wallops Island Flight Test Range: The First Fifteen Years by Joseph Shortal. A NASA publication. Page 500.

Analyzing NPS Scheduling Using OSIRIS

DTIC Science & Technology

1993-03-01

School TEACHER SCHEDULE BLOCKS REPORT Date: 2/19/93 Period Name ID Term Days 1234 Adragna , Joe 170401 1 F xx Agrawal, Brij 120101 1 F xx Almquist...LOAD REPORT Date: 3/18/93 Total Max Consec Total Teacher ID Term Classes Classes Stud Adragna , Joe 170401 1 1 1 3 Agrawal, Brij 120101 1 2 2 98 Aiello

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO ...

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

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO MOBILE LAUNCHER PLATFORM NO. 1. NASA, John F. Kennedy Space Center, Florida. Drawing 79K04401, Reynolds, Smith and Hills, March, 1975. ISOMETRIC: EXISTING ML NO. 3 LAUNCHER. Sheet A1 - Cape Canaveral Air Force Station, Launch Complex 39, Mobile Launcher Platforms, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

Performance of Mycobacterium Growth Indicator Tube BACTEC 960 with Lowenstein-Jensen method for diagnosis of Mycobacterium tuberculosis at Ethiopian National Tuberculosis Reference Laboratory, Addis Ababa, Ethiopia.

PubMed

Diriba, Getu; Kebede, Abebaw; Yaregal, Zelalem; Getahun, Muluwork; Tadesse, Mengistu; Meaza, Abyot; Dagne, Zekarias; Moga, Shewki; Dilebo, Jibril; Gudena, Kebebe; Hassen, Mulu; Desta, Kassu

2017-05-10

Bacteriological confirmed active case detection remains the corner stone for diagnosing tuberculosis. Non-radiometric liquid culture system Mycobacterium Growth Indicator Tube with automated interface had been recommended by expert groups in addition to conventional solid culture media such as Lowenstein-Jensen. However in high burden resource limited countries advanced non-radiometric based tuberculosis diagnostic methods such as MGIT 960 is limited. Therefore we have evaluated the performance of MGIT 960 system compared to LJ for recovery of Mycobacterium complex (MTBC) from clinical specimens. A cross sectional study was conducted from a total of 908 samples between January 1st, 2013 to December 31st, 2014. Clinical specimens were processed following standard procedures and the final suspension was inoculated to MGIT tubes and LJ slant. Identification and confirmation of MTBC was done by ZN staining and SD Bioline test. Data was analyzed by SPSS version 20. The sensitivity, specificity, recovery rate and the average turnaround time to recover the organism was computed. From a total of 908 clinical specimens processed using both LJ and BACTEC MGIT liquid culture methods the recovery rate for LJ and MGIT, for smear positive samples was 66.7% (74/111) and 87.4% (97/ 111) respectively while for smear negative samples was 13.4% (108/797) and 17.4% (139/797) for LJ and MGIT methods respectively. The overall recovery rate for MGIT is significantly higher than LJ methods [26% (236/908; vs. 20%, 182/908, P = 0.002)]. The average turnaround time for smear positive samples was 16 and 31 days for MGIT and LJ respectively. Turnaround time for smear negative samples was 20 and 36 days for MGIT and LJ respectively. The overall agreement between MGIT and LJ was fairly good with Kappa value of 0.59 (P < 0.001). In the present study the contamination rate for MGIT is higher than the LJ methods, 15 and 9.3% respectively. The BACTEC MGIT liquid culture system has better MTBC

Inhibition of an aquatic rhabdovirus demonstrates promise of a broad-spectrum antiviral for use in aquaculture

USGS Publications Warehouse

Balmer, Bethany F.; Powers, Rachel L.; Zhang, Ting-Hu; Lee, Jihye; Vigant, Frederic; Lee, Benhur; Jung, Michael E.; Purcell, Maureen K.; Snekvik, Kevin; Aguilar, Hector C.

2017-01-01

Many enveloped viruses cause devastating disease in aquaculture, resulting in significant economic impact. LJ001 is a broad-spectrum antiviral compound that inhibits enveloped virus infections by specifically targeting phospholipids in the lipid bilayer via the production of singlet oxygen (1O2). This stabilizes positive curvature and decreases membrane fluidity, which inhibits virus-cell membrane fusion during viral entry. Based on data from previous mammalian studies and the requirement of light for the activation of LJ001, we hypothesized that LJ001 may be useful as a preventative and/or therapeutic agent for infections by enveloped viruses in aquaculture. Here, we report that LJ001 was more stable with a prolonged inhibitory half-life at relevant aquaculture temperatures (15°C), than in mammalian studies at 37°C. When LJ001 was preincubated with our model virus, infectious hematopoietic necrosis virus (IHNV), infectivity was significantly inhibited in vitro (using the epithelioma papulosum cyprini [EPC] fish cell line) and in vivo (using rainbow trout fry) in a dose-dependent and time-dependent manner. While horizontal transmission of IHNV in a static cohabitation challenge model was reduced by LJ001, transmission was not completely blocked at established antiviral doses. Therefore, LJ001 may be best suited as a therapeutic for aquaculture settings that include viral infections with lower virus-shedding rates than IHNV or where higher viral titers are required to initiate infection of naive fish. Importantly, our data also suggest that LJ001-inactivated IHNV elicited an innate immune response in the rainbow trout host, making LJ001 potentially useful for future vaccination approaches.

1. GENERAL VIEW OF LAUNCH PAD A WITH MOBILE SERVICE ...

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

1. GENERAL VIEW OF LAUNCH PAD A WITH MOBILE SERVICE STRUCTURE IN LOCKED POSITION OVER LAUNCHER BUILDING AND RETENTION POND AT RIGHT; VIEW TO NORTHWEST. - Cape Canaveral Air Station, Launch Complex 17, Facility 28501, East end of Lighthouse Road, Cape Canaveral, Brevard County, FL

Experimental and numerical investigation of the turbulent wake flow of a generic space launcher configuration

NASA Astrophysics Data System (ADS)

Statnikov, V.; Saile, D.; Meiß, J.-H.; Henckels, A.; Meinke, M.; Gülhan, A.; Schröder, W.

2015-06-01

The turbulent wake of a generic space launcher at cold hypersonic freestream conditions is investigated experimentally and numerically to gain detailed insight into the intricate base flow phenomena of space vehicles at upper stages of the flight trajectory. The experiments are done at Ma∞ = 6 and ReD = 1.7 · 106 m-1 by the German Aerospace Center (DLR) and the corresponding computations are performed by the Institute of Aerodynamics Aachen using a zonal Reynolds-averaged Navier-Stokes / Large-Eddy Simulation (RANS/LES) approach. Two different aft-body geometries consisting of a blunt base and an attached cylindrical nozzle dummy are considered. It is found that the wind tunnel model support attached to the upper side of the main body has a nonnegligible impact on the wake along the whole circumference, albeit on the opposite side, the effects are minimal compared to an axisymmetric configuration. In the blunt-base case, the turbulent supersonic boundary layer undergoes a strong aftexpansion on the model shoulder leading to the formation of a confined low-pressure (p/p∞ ≈ 0.2) recirculation region. Adding a nozzle dummy causes the shear layer to reattach on the its wall at x/D ˜ 0.6 and the base pressure level to increase (p/p∞ ≈ 0.25) compared to the blunt-base case. For both configurations, the pressure fluctuations on the base wall feature dominant frequencies at SrD ≈ 0.05 and SrD ≈ 0.2-0.27, but are of small amplitudes (prms/p∞ = 0.02-0.025) compared to the main body boundary layer. For the nozzle dummy configuration, when moving downstream along the nozzle extension, the wall pressure is increasingly influenced by the reattaching shear layer and the periodic low-frequency behavior becomes less pronounced. Directly behind the reattachment point, the wall pressure reaches maximum mean and root-mean-square (rms) values of about p/p∞ = 1 and p'rms/p∞ = 0.1 and features a broadband specrms trum without distinct frequencies determined by the

Lactobacillus johnsonii HY7042 ameliorates Gardnerella vaginalis-induced vaginosis by killing Gardnerella vaginalis and inhibiting NF-κB activation.

PubMed

Joo, Hyun-Min; Hyun, Yang-Jin; Myoung, Kil-Sun; Ahn, Young-Tae; Lee, Jung-Hee; Huh, Chul-Sung; Han, Myung Joo; Kim, Dong-Hyun

2011-11-01

Hydrogen peroxide-producing lactic acid bacteria (LAB) were isolated from women's vaginas and their anti-inflammatory effects against Gardnerella vaginalis-induced vaginosis were examined in β-estradiol-immunosuppressed mice. Oral and intravaginal treatment with five LABs significantly decreased viable G. vaginalis numbers in vaginal cavities and myeloperoxidase activity in mouse vaginal tissues. Of the LABs examined, Lactobacillus johnsonii HY7042 (LJ) most potently inhibited G. vaginalis-induced vaginosis. This LAB also inhibited the expressions of IL-1β, IL-6, TNF-α, COX-2, and iNOS, and the activation of NF-κB in vaginal tissues, but increased IL-10 expression. Orally administered LJ (0.2×10(8) CFU/mouse) also inhibited the expression of TNF-α by 91.7% in β-estradiol-immunosuppressed mice intraperitoneally injected with LPS. However, it increased IL-10 expression by 63.3% in these mice. Furthermore, LJ inhibited the expressions of the pro-inflammatory cytokines, TNF-α and IL-1β, and the activation of NF-κB in lipopolysaccharide-stimulated peritoneal macrophages. LJ also killed G. vaginalis attached with and without HeLa cells. These findings suggest that LJ inhibits bacterial vaginosis by inhibiting the expressions of COX-2, iNOS, IL-1β, and TNF-α by regulating NF-κB activation and by killing G. vaginalis, and that LJ could ameliorate bacterial vaginosis. Copyright © 2011 Elsevier B.V. All rights reserved.

Recent progress in the upgrade of the TCV EC-system with two 1MW/2s dual-frequency (84/126GHz) gyrotrons

NASA Astrophysics Data System (ADS)

Alberti, Stefano; Genoud, Jérémy; Goodman, Timothy; Hogge, Jean-Philippe; Porte, Laurie; Silva, Miguel; Tran, Trach-Minh; Tran, Minh-Quang; Avramidis, Konstantinos; Pagonakis, Ioannis; Jin, Jianbo; Illy, Stefan; Gantenbein, Gerd; Jelonnek, John; Thumm, Manfred; Bin, William; Bruschi, Alex; Garavaglia, Saul; Moro, Alessandro; Kasparek, Walter; Legrand, François; Perial, Etienne; Rozier, Yoan; Cismondi, Fabio; Doelman, Niek

2017-10-01

The upgrade of the EC-system of the TCV tokamak has entered in its realization phase and is part of a broader upgrade of TCV. The MW-class dual-frequency gyrotrons (84 or 126GHz/2s/1MW) are presently being manufactured by Thales Electron Devices with the first gyrotron foreseen to be delivered at SPC by the end of 2017. In parallel to the gyrotron development, for extending the level of operational flexibility of the TCV EC-system the integration of the dual-frequency gyrotrons adds a significant complexity in the evacuated 63.5mm-diameter HE11 transmission line system connected to the various TCV low-field side and top launchers. As discussed in [1], an important part of the present TCV-upgrade consists in inserting a modular closed divertor chamber. This will have an impact on the X3 top-launcher which will have to be reduced in size. For using the new compact launcher we are considering employing a Fast Directional Switch (FADIS), combining the two 1MW/126GHz/2s rf-beams into a single 2MW rf-beam.

Inhibition of an Aquatic Rhabdovirus Demonstrates Promise of a Broad-Spectrum Antiviral for Use in Aquaculture.

PubMed

Balmer, Bethany F; Powers, Rachel L; Zhang, Ting-Hu; Lee, Jihye; Vigant, Frederic; Lee, Benhur; Jung, Michael E; Purcell, Maureen K; Snekvik, Kevin; Aguilar, Hector C

2017-02-15

Many enveloped viruses cause devastating disease in aquaculture, resulting in significant economic impact. LJ001 is a broad-spectrum antiviral compound that inhibits enveloped virus infections by specifically targeting phospholipids in the lipid bilayer via the production of singlet oxygen ( 1 O 2 ). This stabilizes positive curvature and decreases membrane fluidity, which inhibits virus-cell membrane fusion during viral entry. Based on data from previous mammalian studies and the requirement of light for the activation of LJ001, we hypothesized that LJ001 may be useful as a preventative and/or therapeutic agent for infections by enveloped viruses in aquaculture. Here, we report that LJ001 was more stable with a prolonged inhibitory half-life at relevant aquaculture temperatures (15°C), than in mammalian studies at 37°C. When LJ001 was preincubated with our model virus, infectious hematopoietic necrosis virus (IHNV), infectivity was significantly inhibited in vitro (using the epithelioma papulosum cyprini [EPC] fish cell line) and in vivo (using rainbow trout fry) in a dose-dependent and time-dependent manner. While horizontal transmission of IHNV in a static cohabitation challenge model was reduced by LJ001, transmission was not completely blocked at established antiviral doses. Therefore, LJ001 may be best suited as a therapeutic for aquaculture settings that include viral infections with lower virus-shedding rates than IHNV or where higher viral titers are required to initiate infection of naive fish. Importantly, our data also suggest that LJ001-inactivated IHNV elicited an innate immune response in the rainbow trout host, making LJ001 potentially useful for future vaccination approaches. Viral diseases in aquaculture are challenging because there are few preventative measures and/or treatments. Broad-spectrum antivirals are highly sought after and studied because they target common components of viruses. In our studies, we used LJ001, a broad

Measurement Uncertainty Analysis of an Accelerometer Calibration Using a POC Electromagnetic Launcher

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

Timpson, Erik J.; Engel, T. G.

A pulse forming network (PFN), helical electromagnetic launcher (HEML), command module (CM), and calibration table (CT) were built and evaluated for the combined ability to calibrate an accelerometer. The PFN has a maximum stored nergy of 19.25 kJ bank and is fired by a silicon controlled rectifier (SCR), with appropriate safety precautions. The HEML is constructed out of G-10 fiberglass reinforced epoxy and is designed to accelerate a mass of 600 grams to a velocity of 10 meters per second. The CM is microcontroller-based running Arduino Software. The CM has a keypad input and 7 segment outputs of the PFNmore » voltage and desired charging voltage. After entering a desired PFN voltage, the CM controls the charging of the PFN. When the two voltages are equal it sends a pulse to the SCR to fire the PFN and in turn, the HEML. The HEML projectile’s tip hits a target that is held by the CT. The CT consists of a table to hold the PFN and HEML, a vacuum chuck, air bearing, velocimeter and catch pot. The target is held with the vacuum chuck awaiting impact. After impact, the air bearing allows the target to fall freely so that the velocimeter can accurately read. A known acceleration is determined from the known change in velocity of the target. Thus, if an accelerometer was attached to the target, the measured value can be compared to the known value.« less

BCAT-C1 Session in the JPM

NASA Image and Video Library

2012-08-08

ISS032-E-014593 (6 Aug. 2012) --- NASA astronaut Joe Acaba, Expedition 32 flight engineer, conducts a session with the Binary Colloidal Alloy Test-6 (BCAT-6) experiment in the Kibo laboratory of the International Space Station.

1st Stage Separation Aerodynamics Of VEGA Launcher

NASA Astrophysics Data System (ADS)

Genito, M.; Paglia, F.; Mogavero, A.; Barbagallo, D.

2011-05-01

VEGA is an European launch vehicle under development by the Prime Contractor ELV S.p.A. in the frame of an ESA contract. It is constituted by four stages, dedicated to the scientific/commercial market of small satellites (300 ÷ 2500 kg) into Low Earth Orbits, with inclinations ranging from 5.2° up to Sun Synchronous Orbits and with altitude ranging from 300 to 1500 km. Aim of this paper is to present a study of flow field due to retro-rockets impingement during the 1st stage VEGA separation phase. In particular the main goal of the present work is to present the aerodynamic activities performed for the justification of the separation phase.

The glutathione peroxidase gene family of Lotus japonicus: characterization of genomic clones, expression analyses and immunolocalization in legumes.

PubMed

Ramos, Javier; Matamoros, Manuel A; Naya, Loreto; James, Euan K; Rouhier, Nicolas; Sato, Shusei; Tabata, Satoshi; Becana, Manuel

2009-01-01

Despite the multiple roles played by antioxidants in rhizobia-legume symbioses, little is known about glutathione peroxidases (GPXs) in legumes. Here the characterization of six GPX genes of Lotus japonicus is reported. Expression of GPX genes was analysed by quantitative reverse transcription-polymerase chain reaction in L. japonicus and Lotus corniculatus plants exposed to various treatments known to generate reactive oxygen and/or nitrogen species. LjGPX1 and LjGPX3 were the most abundantly expressed genes in leaves, roots and nodules. Compared with roots, LjGPX1 and LjGPX6 were highly expressed in leaves and LjGPX3 and LjGPX6 in nodules. In roots, salinity decreased GPX4 expression, aluminium decreased expression of the six genes, and cadmium caused up-regulation of GPX3, GPX4 and GPX5 after 1 h and down-regulation of GPX1, GPX2, GPX4 and GPX6 after 3-24 h. Exposure of roots to sodium nitroprusside (a nitric oxide donor) for 1 h increased the mRNA levels of GPX4 and GPX6 by 3.3- and 30-fold, respectively. Thereafter, the GPX6 mRNA level remained consistently higher than that of the control. Immunogold labelling revealed the presence of GPX proteins in root and nodule amyloplasts and in leaf chloroplasts of L. japonicus and other legumes. Labelling was associated with starch grains. These results underscore the differential regulation of GPX expression in response to cadmium, aluminium and nitric oxide, and strongly support a role for GPX6 and possibly other GPX genes in stress and/or metabolic signalling.

KENNEDY SPACE CENTER, FLA. - Workers, covered in protective clothing and breathing apparatus, continue sandblasting on the Mobile Launcher Platform on Launch Pad 39A to remove corrosion before repainting. Routine maintenance includes sandblasting and repainting as preventive means to minimize corrosion.

NASA Image and Video Library

2003-09-12

KENNEDY SPACE CENTER, FLA. - Workers, covered in protective clothing and breathing apparatus, continue sandblasting on the Mobile Launcher Platform on Launch Pad 39A to remove corrosion before repainting. Routine maintenance includes sandblasting and repainting as preventive means to minimize corrosion.

KENNEDY SPACE CENTER, FLA. - On Launch Pad 39A, clouds of dust float away from the Mobile Launcher Platform, which is undergoing sandblasting to remove corrosion before repainting. Routine maintenance includes sandblasting and repainting as preventive means to minimize corrosion.

NASA Image and Video Library

2003-09-12

KENNEDY SPACE CENTER, FLA. - On Launch Pad 39A, clouds of dust float away from the Mobile Launcher Platform, which is undergoing sandblasting to remove corrosion before repainting. Routine maintenance includes sandblasting and repainting as preventive means to minimize corrosion.

Structure Design Approach and Technology Selection for Next Generation European Launchers

NASA Astrophysics Data System (ADS)

Baiocco, P.; Ramusat, G.; Kauffmann, J.; Jaredson, D.; Bouilly, Th.; Lavelle, F.; Louaas, E.

2012-07-01

In the framework of the next generation launchers activity at ESA, a top-down and a bottom-up approach has been performed for the alternative conception and promising technologies of NGL sub-assemblies and sub-systems. The top-down approach consisted in looking for system-driven design solutions and the bottom-up in the proposal of design solutions taking to substantial advantages for the system. The main investigations have been focused on structures and technologies tight to structures and interfaces. Specifications coming from a preliminary system design have been used in order to permit sub-system design with the goal to find the major advantage for the overall launch system. In this respect selection criteria have been identified and among these a specific evaluation of the payload mass over recurring cost advantage has been evaluated. The development cost, recurring cost and operational aspects have been considered as competitiveness factors for the identification of the most interesting solutions. The TRL/IRL has been assessed and a preliminary development plan has been identified. This approach is dedicated to reference NGL architectures, but alternative architectures have been investigated in order to assess their interest in terms of competitiveness factors and study of other technologies. This paper deals mainly with metallic and composite structures owing to sub-systems or sub-assemblies proposed for the NGL. The major sub-systems and structures analysed are the engine thrust frame (ETF), inter stage structures (ISS), cryogenic propellant tanks, feeding lines and attachments, pressurisation systems and fairing. The paper provides an overview of the main results of this investigation and the potential benefit it can provide.

Safety-factor profile tailoring by improved electron cyclotron system for sawtooth control and reverse shear scenarios in ITER

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

Zucca, C.; Sauter, O.; Fable, E.

2008-11-01

The effect of the predicted local electron cyclotron current driven by the optimized electron cyclotron system on ITER is discussed. A design variant was recently proposed to enlarge the physics program covered by the upper and equatorial launchers. By extending the functionality range of the upper launcher, significant control capabilities of the sawtooth period can be obtained. The upper launcher improvement still allows enough margin to exceed the requirements for neoclassical tearing mode stabilization, for which it was originally designed. The analysis of the sawtooth control is carried on with the ASTRA transport code, coupled with the threshold model bymore » Por-celli, to study the control capabilities of the improved upper launcher on the sawtooth instability. The simulations take into account the significant stabilizing effect of the fusion alpha particles. The sawtooth period can be increased by a factor of 1.5 with co-ECCD outside the q = 1 surface, and decreased by at least 30% with co-ECCD inside q = 1. The present ITER base-line design has the electron cyclotron launchers providing only co-ECCD. The variant for the equatorial launcher proposes the possibility to drive counter-ECCD with 1 of the 3 rows of mirrors: the counter-ECCD can then be balanced with co-ECCD and provide pure ECH with no net driven current. The difference between full co-ECCD off-axis using all 20MW from the equatorial launcher and 20MW co-ECCD driven by 2/3 from the equatorial launcher and 1/3 from the upper launcher is shown to be negligible. Cnt-ECCD also offers greater control of the plasma current density, therefore this analysis addresses the performance of the equatorial launcher to control the central q profile. The equatorial launcher is shown to control very efficiently the value of q{sub 0.2}-q{sub min} in advanced scenarios, if one row provides counter-ECCD.« less

Controlling of growth performance, lipid deposits and fatty acid composition of chicken meat through a probiotic, Lactobacillus johnsonii during subclinical Clostridium perfringens infection.

PubMed

Wang, Hesong; Ni, Xueqin; Liu, Lei; Zeng, Dong; Lai, Jing; Qing, Xiaodan; Li, Guangyao; Pan, Kangcheng; Jing, Bo

2017-02-10

Meat is considered as a major source of polyunsaturated fatty acid (PUFA) which is essential for humans, therefore its lipid level and fatty acid composition have drawn great attention. As no clinical sign can be found in chicks subclinically infected by Clostridium perfringens (CP), the meat may be purchased and eaten. The objective of the present study was to determine whether Lactobacillus johnsonii (LJ) can control the CP-caused impact on growth, lipid levels, fatty acid composition and other flavor or nutritional quality in the meat. 480 one-day-old chicks were divided into four groups and fed with basal diet (control and CP group). Supplemented with 1 × 10 5 (L-LJ) and 1 × 10 6 (H-LJ) colony-forming unit (cfu), CP diet was fed for 42 days. From day 19 to 22, birds of CP and LJ groups were administered with CP twice per day and the control was administered with liver broth. LJ-treated chickens were free from negative influences on growth performance and significant decrease of abdominal fat deposit., LJ inhibited CP-caused shearing force and drip loss increase and pH 40 min and 24 h decrease after sacrifice. In addition, LJ exhibited a positive effect on muscle lipid peroxidation by significantly increasing SOD, CAT and GSH-Px activity and decreasing MDA level. Besides, LJ attenuated the decrease of intramuscular fat, total cholesterol and triglyceride contents caused by CP infection. However, levels of total protein and most of amino acids were not changed. CP infection decreased C18:3n-3 (α-LA), C20:4n-6, C20:5n-3(EPA), C22:4n-6, C22:5n-3, C22:6n-3(DHA), total PUFA, n-3 PUFA and PUFA:SFA ratio and increased C14:0, total SFA and n-6:n-3 ratio. LJ was found to protect the muscle from these changes. Meanwhile, the 28-day gut permeability level was higher in CP group. These findings suggest that CP may affect the growth performance of chicks and negatively influence lipid content and fatty acid composition in chicken meat. Meanwhile, LJ treatment

The Joe Joe Series: A Culturally Responsive Resource

ERIC Educational Resources Information Center

Boyd, Nichelle C.; Hill-Clarke, Kantaylieniere

2004-01-01

In the elementary classroom, teachers often introduce new units through the use of trade books. Children's literature, the best of which brings social studies content to life, is usually more engaging than textbook prose. Children's literature that shares the experiences, contributions, and perspectives of various cultural groups achieves several…

User Guide for the LORE1 Insertion Mutant Resource.

PubMed

Mun, Terry; Małolepszy, Anna; Sandal, Niels; Stougaard, Jens; Andersen, Stig U

2017-01-01

Lotus japonicus is a model legume used in the study of plant-microbe interactions, especially in the field of biological nitrogen fixation due to its ability to enter into a symbiotic relationship with a soil bacterium, Mesorhizobium loti. The LORE1 mutant population is a valuable resource for reverse genetics in L. japonicus due to its non-transgenic nature, high tagging efficiency, and low copy count. Here, we outline a workflow for identifying, ordering, and establishing homozygous LORE1 mutant lines for a gene of interest, LjFls2, including protocols for growth and genotyping of a segregating LORE1 population.

Evaluation of a rapid culture method for tuberculosis diagnosis: a Latin American multi-center study.

PubMed

Robledo, J A; Mejía, G I; Morcillo, N; Chacón, L; Camacho, M; Luna, J; Zurita, J; Bodon, A; Velasco, M; Palomino, J C; Martin, A; Portaels, F

2006-06-01

Tuberculosis (TB) diagnostic laboratories in Latin America. Evaluation of thin-layer agar (TLA) compared to Löwenstein-Jensen (LJ) culture for the diagnosis of TB. Phase II prospective study in six laboratories. Samples included sputum and extra-pulmonary specimens from patients with a clinical diagnosis of TB. Respiratory samples were decontaminated using NaOH/ NALC; all samples were centrifuged, stained with Ziehl-Neelsen for acid-fast bacilli (AFB), cultured on LJ and TLA and identified according to recommended procedures. Sensitivity and likelihood ratios (LR), growth detection time and contamination rate were calculated for both media. A total of 1118 clinical specimens were studied. Cultures detected Mycobacterium tuberculosis in all AFB-positive samples, whereas for AFB-negative specimens LJ detected 3.2% and TLA 4.4%. Sensitivity was 92.6% (95%CI 87.9-95.9) and 84.7% (95%CI 78.8-89.0) for TLA and LJ, respectively. Positive and negative LRs were similar. Contamination was 5.1% for TLA and 3.0% for LJ. Median time to detection of a positive culture was 11.5 days (95%CI 9.3-15.0) for TLA and 30.5 days (95%CI 26.9-39.0) for LJ (P < 0.0001). Difference in the characteristics of the participating laboratories, the disease prevalence and the number and type of specimens processed did not affect the overall performance of TLA as compared to LJ, supporting the robustness of the method and its feasibility in different laboratory settings.

Hypervelocity Impact Testing of International Space Station Meteoroid/Orbital Debris Shielding Using an Inhibited Shaped Charge Launcher

NASA Technical Reports Server (NTRS)

Kerr, Justin H.; Grosch, Donald

2001-01-01

Engineers at the NASA Johnson Space Center have conducted hypervelocity impact (HVI) performance evaluations of spacecraft meteoroid and orbital debris (M/OD) shields at velocities in excess of 7 km/s. The inhibited shaped charge launcher (ISCL), developed by the Southwest Research Institute, launches hollow, circular, cylindrical jet tips to approximately 11 km/s. Since traditional M/OD shield ballistic limit performance is defined as the diameter of sphere required to just perforate or spall a spacecraft pressure wall, engineers must decide how to compare ISCL derived data with those of the spherical impactor data set. Knowing the mass of the ISCL impactor, an equivalent sphere diameter may be calculated. This approach is conservative since ISCL jet tips are more damaging than equal mass spheres. A total of 12 tests were recently conducted at the Southwest Research Institute (SWRI) on International Space Station M/OD shields. Results of these tests are presented and compared to existing ballistic limit equations. Modification of these equations is suggested based on the results.

Naval Postgraduate School Research. Volume 10, Number 1, February 2000

DTIC Science & Technology

2000-02-01

morale waned along with public perceptions of the military; reports of disciplinary problems, drug use, and substandard performance circulated widely...1.78 m long, 0.86 m wide, and 0.61 m deep. Inserted at the center of both sides of the tank, are 37x27x0.6 cm viewing glass windows (Figure 2...potential research directions in multimedia and network- ing. NATIONAL SECURITY AFFAIRS L.J. Roberts, The Lebanese in Ecuador: A History of Emerging

Development of a high-velocity free-flight launcher : the Ames light-gas gun

NASA Technical Reports Server (NTRS)

Charters, A C; Denardo, B Pat; Rossow, Vernon J

1955-01-01

Recent interest in long-range missiles has stimulated a search for new experimental techniques which can reproduce in the laboratory the high temperatures and Mach numbers associated with the missiles' flight. One promising possibility lies in free-flight testing of laboratory models which are flown at the full velocity of the missile. In this type of test, temperatures are approximated and aerodynamic heating of the model is representative of that experienced by the missile in high-velocity flight. A prime requirement of the free-flight test technique is a device which had the capacity for launching models at the velocities desired. In response to thie need, a gun firing light models at velocities up to 15,000 feet per second has been developed at the Ames Aeronautical Laboratory. The design of this gun, the analysis of its performance, and the results of the initial firing trials are described in this paper. The firing trials showed that the measured velocities and pressures agreed well with the predicted values. Also, the erosion of the launch tube was very small for the eleven rounds fired. The performance of the gun suggests that it will prove to be a satisfactory launcher for high-velocity free-flight tests. However, it should be mentioned that only the gross performance has been evaluated so far, and, consequently, the operation of the gun must be investigated in further detail before its performance can be reliably predicted over its full operating range.

Structures, Material and Processes Technology in the Future Launchers Preparatory Program

NASA Astrophysics Data System (ADS)

Baiocco, P.; Ramusat, G.; Breteau, J.; Bouilly, Th.; Lavelle, Fl.; Cardone, T.; Fischer, H.; Appel, S.; Block, U.

2014-06-01

In the frame of the technology / demonstration activity for European launchers developments and evolutions, a top-down / bottom-up approach has been employed to identify promising technologies and alternative conception. The top-down approach consists in looking for system-driven design solutions and the bottom-up approach features design solutions leading to substantial advantages for the system. The main investigations have been devoted to structures, material and process technology.Preliminary specifications have been used in order to permit sub-system design with the goal to find the major benefit for the overall launch system. In this respect competitiveness factors have been defined to down- select the technology and the corresponding optimized design. The development cost, non-recurring cost, industrialization and operational aspects have been considered for the identification of the most interesting solutions. The TRL/IRL has been assessed depending on the manufacturing company and a preliminary development plan has been issued for some technology.The reference launch systems for the technology and demonstration programs are mainly Ariane 6 with its evolutions, VEGA C/E and others possible longer term systems. Requirements and reference structures architectures have been considered in order to state requirements for representative subscale or full scale demonstrators. The major sub-systems and structures analyzed are for instance the upper stage structures, the engine thrust frame (ETF), the inter stage structures (ISS), the cryogenic propellant tanks, the feeding lines and their attachments, the pressurization systems, the payload adapters and fairings. A specific analysis has been devoted to the efficiency of production processes associated to technologies and design features.The paper provides an overview of the main results of the technology and demonstration activities with the associated system benefits. The materials used for the main structures are

XBP1, Unfolded Protein Response, and Endocrine Responsiveness

DTIC Science & Technology

2009-05-01

through regu- lation of large-scale chromatin unfolding. Biochem Biophys Res Commun 2004, 323(1): 269-74. 59. Vaupel, P., Kelleher, D.K. and Hockel...stage 2 (M2)” or “ crisis ” [64]. 2.6. Endocrine-induced cell death in breast cancer Precisely how breast cancer cells die following estrogen with- drawal...2005) 2747–2757. [17] R.C. Coombes , E. Hall, L.J. Gibson, R. Paridaens, J. Jassem, T. Delozier, S.E. Jones, I. Alvarez, G. Bertelli, O. Ortmann, A.S

Technical Report for the Period 1 January 1963 to 30 June 1963

DTIC Science & Technology

1963-08-23

mixed mononitrates with periodic acid to remove glycerol 1 -nitrate; glycerol 2-nitrate di-4-nitrobenzoate, m.p. 1520C, has been prepared. Nitration of...Based on Phenazine Preparation of polymers from dibasic acids (e.g. adipic and terephthalic) and dihydrophenazine by various methods was attempted but...L.J. Hydrogen Bonding in WAC and Pace, R.J. Carboxylic Acids - 142/031 I. Oxalic Acids Spectrochim. Acta, 1963, 19, 435 Bellamy, L.J., - ditto - Luke

Immunobiotic Lactobacillus jensenii as immune-health promoting factor to improve growth performance and productivity in post-weaning pigs.

PubMed

Suda, Yoshihito; Villena, Julio; Takahashi, Yu; Hosoya, Shoichi; Tomosada, Yohsuke; Tsukida, Kohichiro; Shimazu, Tomoyuki; Aso, Hisashi; Tohno, Masanori; Ishida, Mitsuharu; Makino, Seiya; Ikegami, Shuji; Kitazawa, Haruki

2014-06-19

Immunoregulatory probiotics (immunobiotics) have been proposed to improve piglets' immune system to avoid intestinal infections and reduce unproductive inflammation after weaning. Previously, it was demonstrated that Lactobacillus jensenii TL2937 (LjTL2937) attenuated the inflammatory response triggered by activation of Toll-like receptor 4 (TLR-4) in porcine intestinal epithelial (PIE) cells and antigen presenting cells (APCs) from porcine Peyer's patches (PP). In view of the critical importance of PIE-APCs interactions in the regulation of intestinal immune responses, we aimed to examine the effect of LjTL2937 on activation patterns of APCs from swine PPs in co-cultures with PIE cells. In addition, we investigated whether LjTL2937 was able to beneficially modulate intestinal immunity of piglets after weaning to improve immune-health status. Stimulation of PIE-APCs co-cultures with LjTL2937 increased the expression of MHC-II, CD80/86, IL-10, and Bcl-3 in CD172a+CD11R1- and CD172a+CD11R1high APCs. In addition, the TL2937 strain caused the upregulation of three negative regulators of TLR4 in PIE cells: MKP-1, Bcl-3 and A20. These changes significantly reduced the inflammatory response triggered by TLR4 activation in PIE-APCs co-cultures. The in vivo experiments using castrated male piglets (crossbreeding (LWD) with Landrace (L), Large Yorkshire (W) and Duroc (D))of 3 weeks of age demonstrated that feeding with LjTL2937 significantly reduced blood complement activity and C reactive protein concentrations while no changes were observed in blood leukocytes, ratio of granulocytes to lymphocyte numbers, macrophages' activity and antibody levels. In addition, treatment with LjTL2937 significantly improved growth performance and productivity, and increased carcass quality. We demonstrated that the use of immunobiotics strains like LjTL2937, as supplemental additives for piglets feedings, could be used as a strategy to maintain and improve intestinal homeostasis; that is

hwhap_Ep10_Average Joe, Educator, Astronaut

NASA Image and Video Library

2017-09-15

>> HOUSTON, WE HAVE A PODCAST. WELCOME TO THE OFFICIAL PODCAST OF THE NASA JOHNSON SPACE CENTER, EPISODE 10: AVERAGE JOE, EDUCATOR, ASTRONAUT. I’M GARY JORDAN AND I’LL BE YOUR HOST TODAY. SO IF YOU’RE NEW TO THE SHOW, THIS IS WHERE WE BRING IN THE EXPERTS-- NASA SCIENTISTS, ENGINEERS, ASTRONAUTS-- PRETTY MUCH ALL THE FOLKS THAT HAVE THE COOLEST INFORMATION, THE STUFF YOU REALLY WANT TO KNOW RIGHT ON THE SHOW AND WILL TELL YOU MORE ABOUT EVERYTHING NASA. SO TODAY WE’RE TALKING WITH JOE ACABA. HE’S A U.S. ASTRONAUT, AND HE JUST LAUNCHED TO THE INTERNATIONAL SPACE STATION A FEW DAYS AGO ON SEPTEMBER 12, 2017 FOR HIS SECOND LONG-DURATION MISSION ABOARD THE ORBITING COMPLEX. WE TALKED ABOUT HIS TIME IN THE MARINE CORPS AND PEACE CORPS, HIS PREVIOUS MISSIONS TO SPACE, AND HIS BACKGROUND AS A HIGH SCHOOL AND MIDDLE SCHOOL EDUCATOR, AND A LITTLE BIT ABOUT HOW HE VIEWS THE IMPORTANCE OF BEING AN EDUCATOR IN SPACE. SO WITH NO FURTHER DELAY, LET’S GO LIGHT SPEED AND JUMP RIGHT AHEAD TO OUR TALK WITH MR. JOE ACABA. ENJOY. [ MUSIC ] >> T MINUS FIVE SECONDS AND COUNTING-- MARK. [ INDISTINCT RADIO CHATTER ] >> HOUSTON, WE HAVE A PODCAST. [ MUSIC ] >> OKAY, WELL, THANKS FOR COMING ON THE SHOW TODAY, JOE. I KNOW YOU’RE VERY BUSY, ESPECIALLY COMING SO CLOSE TO YOUR LAUNCH DATE. AND LIKE WE JUST TALKED ABOUT BEFORE, YOU HAVE AN ACCELERATED TRAINING PROGRAM. YOU’RE NOT DOING THE TWO YEAR THING, YOU’RE DOING SIX MONTHS. SO YOU’VE KIND OF GOT A PRETTY JAM-PACKED SCHEDULE, HUH? >> I’M GLAD TO BE HERE, AND I’M GLAD WE FOUND THE TIME, AND IT IS-- IT’S A LITTLE BIT UNIQUE, WHERE USUALLY OUR TRAINING FLOW IS, DEPENDING ON YOUR EXPERIENCE, 18 MONTHS TO 2 YEARS, AND I’VE GOT A WHOLE 6 MONTHS, SO IT’S-- TIME IS BUSY, BUT IT’S GOING REALLY WELL. >> VERY COOL. ALL RIGHT, WELL, HOW DO YOU FEEL ABOUT NOW GOING ON YOUR SECOND LONG-DURATION MISSION? YOU WENT ON YOUR FIRST ONE BACK IN 2012, SO THIS IS KIND OF PRETTY CLOSE, RIGHT? 2012, 2017, SO NOT BAD. >> YEAH, I CAN�

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO ...

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

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO MOBILE LAUNCHER PLATFORM NO. 1. NASA, John F. Kennedy Space Center, Florida. Drawing 79K04401, Reynolds, Smith and Hills, March, 1975. ISOMETRIC VIEW: MLP NO. 1. Sheet A10 - Cape Canaveral Air Force Station, Launch Complex 39, Mobile Launcher Platforms, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

Use of a portable tower and remote-controlled launcher to improve physical conditioning in a rehabilitating wild mallard (Anas platyrhynchos).

PubMed

Pollard-Wright, Holly M; Wright, Mark T; Warren, Jeffrey M

2010-12-01

Prerelease reconditioning improves the chance of survival of rehabilitating raptors. Reconditioning may also help to rehabilitate waterfowl, including those that are threatened or endangered, especially if the birds are released during periods of migration. A flying harness, creance, remote-controlled launcher, and portable tower were used to create a means of reconditioning a rehabilitating 5-month-old female wild mallard duck (Anas platyrhynchos) that had been housed in a rehabilitation center for 7 weeks while recovering from an injury. Pre- and postflight serum lactate levels, body condition index scores, and controlled flight distances were used to assess the bird's degree of conditioning. Postflight serum lactate levels never returned to preflight levels and were not deemed a reliable indicator of physical fitness. However, the mallard showed an increase in endurance and strength as well as improved body condition index scores over the course of the reconditioning program.

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO ...

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

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO MOBILE LAUNCHER PLATFORM NO. 1. NASA, John F. Kennedy Space Center, Florida. Drawing 79K04401, Reynolds, Smith and Hills, March, 1975. GENERAL ARRANGEMENT, MLP NO. 1, ELEVATION – SIDE 1 & 2. Sheet A15 - Cape Canaveral Air Force Station, Launch Complex 39, Mobile Launcher Platforms, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

Assembly and Commissioning of Naval Postgraduate School Gas Gun for Impact Studies

DTIC Science & Technology

2009-12-01

MAIN GAS GUN ASSEMBLY............................................................ 12 1. Launcher Mount Assembly...12 Figure 8. Launcher Mount Assembly [After 5].................................................... 13 Figure 9. Breech...5] The main gas gun assembly comprises of eight sub-assemblies. The assemblies are mounted onto the launcher mount assembly, where it acts as a

The Efficacy of LY293558 in Blocking Seizures and Associated Morphological, and Behavioral Alterations Induced by Soman in Immature Male Rats and the Role of the M1 Muscarinic Acetylcholine Receptor in Organophosphate Induced Seizures

DTIC Science & Technology

2015-01-30

Neurology 48:1363-7 140. Koliatsos VE, Martin LJ, Walker LC, Richardson RT, DeLong MR, Price DL. 1988. Topographic, non-collateralized basal...297-323 169. Martin LJ, Doebler JA, Shih TM, Anthony A. 1985. Protective effect of diazepam pretreatment on soman-induced brain lesion formation...G, Watson C. 2005. The rat brain in stereotaxic coordinates. Amsterdam ; Boston: Elsevier Academic Press 216. Petras JM. 1994. Neurology and

Finding of No Significant Impact: Integrated Natural Resources Management Plan at New Boston Air Force Station, New Hampshire

DTIC Science & Technology

2006-09-22

rushes (Juncus spp.), Virginia chain fern (Woodwardia virginica), pitcher plant ( Sarracenia purpurea ), meadowsweet (Spirea alba), boneset (Eupatoreum...ophioglossoides), and pitcher plant ( Sarracenia purpurea ). The protected nature of the station makes uncontrolled collection of these species by... purpurea NL NL S2 Open forest. Joe English Hill. 1 Orange- spotted idia Idia diminuendis NL NL S2S4 Open forest. Joe English Hill. 1 Butterflies and

The Tactics of Hope

ERIC Educational Resources Information Center

Cytrynbaum, Pamela

2010-01-01

In this article, the author provides an intimate glimpse into the writing work that Joe Cytrynbaum did with students from Manley Career Academy High School in Chicago. The author's discussion of Joe's "tactics of hope" is layered and brought to life by Joe's poetry and the poetry of his students. The author presents Joe's poems and the…

M2-F1 in flight over lakebed on tow line

NASA Image and Video Library

1963-08-30

Following the first M2-F1 airtow flight on 16 August 1963, the Flight Research Center used the vehicle for both research flights and to check out new lifting-body pilots. These included Bruce Peterson, Don Mallick, Fred Haise, and Bill Dana from NASA. Air Force pilots who flew the M2-F1 included Chuck Yeager, Jerry Gentry, Joe Engle, Jim Wood, and Don Sorlie, although Wood, Haise, and Engle only flew on car tows. In the three years between the first and last flights of the M2-F1, it made about 400 car tows and 77 air tows.

Phase separation of a Lennard-Jones fluid interacting with a long, condensed polymer chain: implications for the nuclear body formation near chromosomes.

PubMed

Oh, Inrok; Choi, Saehyun; Jung, YounJoon; Kim, Jun Soo

2015-08-28

Phase separation in a biological cell nucleus occurs in a heterogeneous environment filled with a high density of chromatins and thus it is inevitably influenced by interactions with chromatins. As a model system of nuclear body formation in a cell nucleus filled with chromatins, we simulate the phase separation of a low-density Lennard-Jones (LJ) fluid interacting with a long, condensed polymer chain. The influence of the density variation of LJ particles above and below the phase boundary and the role of attractive interactions between LJ particles and polymer segments are investigated at a fixed value of strong self-interaction between LJ particles. For a density of LJ particles above the phase boundary, phase separation occurs and a dense domain of LJ particles forms irrespective of interactions with the condensed polymer chain whereas its localization relative to the polymer chain is determined by the LJ-polymer attraction strength. Especially, in the case of moderately weak attractions, the domain forms separately from the polymer chain and subsequently associates with the polymer chain. When the density is below the phase boundary, however, the formation of a dense domain is possible only when the LJ-polymer attraction is strong enough, for which the domain grows in direct contact with the interacting polymer chain. In this work, different growth behaviors of LJ particles result from the differences in the density of LJ particles and in the LJ-polymer interaction, and this work suggests that the distinct formation of activity-dependent and activity-independent nuclear bodies (NBs) in a cell nucleus may originate from the differences in the concentrations of body-specific NB components and in their interaction with chromatins.

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO ...

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

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO MOBILE LAUNCHER PLATFORM NO. 1. NASA, John F. Kennedy Space Center, Florida. Drawing 79K04401, Reynolds, Smith and Hills, March, 1975. GENERAL ARRANGEMENT, MLP NO. 1, PLAN – DECK A. Sheet A13 - Cape Canaveral Air Force Station, Launch Complex 39, Mobile Launcher Platforms, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO ...

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

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO MOBILE LAUNCHER PLATFORM NO. 1. NASA, John F. Kennedy Space Center, Florida. Drawing 79K04401, Reynolds, Smith and Hills, March, 1975. GENERAL ARRANGEMENT, MLP NO. 1, SECTIONS I. Sheet A17 - Cape Canaveral Air Force Station, Launch Complex 39, Mobile Launcher Platforms, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO ...

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

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO MOBILE LAUNCHER PLATFORM NO. 1. NASA, John F. Kennedy Space Center, Florida. Drawing 79K04401, Reynolds, Smith and Hills, March, 1975. GENERAL ARRANGEMENT, MLP NO. 1, SECTIONS II. Sheet A18 - Cape Canaveral Air Force Station, Launch Complex 39, Mobile Launcher Platforms, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO ...

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

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO MOBILE LAUNCHER PLATFORM NO. 1. NASA, John F. Kennedy Space Center, Florida. Drawing 79K04401, Reynolds, Smith and Hills, March, 1975. GENERAL ARRANGEMENT, MLP NO. 1, PLAN – DECK B. Sheet A14 - Cape Canaveral Air Force Station, Launch Complex 39, Mobile Launcher Platforms, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO ...

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

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO MOBILE LAUNCHER PLATFORM NO. 1. NASA, John F. Kennedy Space Center, Florida. Drawing 79K04401, Reynolds, Smith and Hills, March, 1975. GENERAL ARRANGEMENT, MLP NO. 1, PLAN – DECK 0. Sheet A12 - Cape Canaveral Air Force Station, Launch Complex 39, Mobile Launcher Platforms, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO ...

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

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO MOBILE LAUNCHER PLATFORM NO. 1. NASA, John F. Kennedy Space Center, Florida. Drawing 79K04401, Reynolds, Smith and Hills, March, 1975. GENERAL ARRANGEMENT, MLP NO. 1, SECTIONS IV. Sheet A20 - Cape Canaveral Air Force Station, Launch Complex 39, Mobile Launcher Platforms, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

The Recent Evolution of a Symbiotic Ion Channel in the Legume Family Altered Ion Conductance and Improved Functionality in Calcium Signaling[C][W

PubMed Central

Venkateshwaran, Muthusubramanian; Cosme, Ana; Han, Lu; Banba, Mari; Satyshur, Kenneth A.; Schleiff, Enrico; Parniske, Martin; Imaizumi-Anraku, Haruko; Ané, Jean-Michel

2012-01-01

Arbuscular mycorrhiza and the rhizobia-legume symbiosis are two major root endosymbioses that facilitate plant nutrition. In Lotus japonicus, two symbiotic cation channels, CASTOR and POLLUX, are indispensable for the induction of nuclear calcium spiking, one of the earliest plant responses to symbiotic partner recognition. During recent evolution, a single amino acid substitution in DOES NOT MAKE INFECTIONS1 (DMI1), the POLLUX putative ortholog in the closely related Medicago truncatula, rendered the channel solo sufficient for symbiosis; castor, pollux, and castor pollux double mutants of L. japonicus were rescued by DMI1 alone, while both Lj-CASTOR and Lj-POLLUX were required for rescuing a dmi1 mutant of M. truncatula. Experimental replacement of the critical serine by an alanine in the selectivity filter of Lj-POLLUX conferred a symbiotic performance indistinguishable from DMI1. Electrophysiological characterization of DMI1 and Lj-CASTOR (wild-type and mutants) by planar lipid bilayer experiments combined with calcium imaging in Human Embryonic Kidney-293 cells expressing DMI1 (the wild type and mutants) suggest that the serine-to-alanine substitution conferred reduced conductance with a long open state to DMI1 and improved its efficiency in mediating calcium oscillations. We propose that this single amino acid replacement in the selectivity filter made DMI1 solo sufficient for symbiosis, thus explaining the selective advantage of this allele at the mechanistic level. PMID:22706284

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO ...

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

Photocopy of drawing. MODIFICATIONS TO CONVERT ML NO. 3 TO MOBILE LAUNCHER PLATFORM NO. 1. NASA, John F. Kennedy Space Center, Florida. Drawing 79K04401, Reynolds, Smith and Hills, March, 1975. GENERAL ARRANGEMENT, MLP NO. 1, ELEVATION – SIDE 3 & 4. Sheet A16 - Cape Canaveral Air Force Station, Launch Complex 39, Mobile Launcher Platforms, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

First order capsules comparative arrangements

NASA Technical Reports Server (NTRS)

1963-01-01

Pen and ink views of comparative arragements of several capsules including the existing 'Big Joe' design, the compromise 'Big Joe' design, and the 'Little Joe'. All capsule designs are labeled and include dimensions.

Immunobiotic Lactobacillus jensenii as immune-health promoting factor to improve growth performance and productivity in post-weaning pigs

PubMed Central

2014-01-01

Background Immunoregulatory probiotics (immunobiotics) have been proposed to improve piglets’ immune system to avoid intestinal infections and reduce unproductive inflammation after weaning. Previously, it was demonstrated that Lactobacillus jensenii TL2937 (LjTL2937) attenuated the inflammatory response triggered by activation of Toll-like receptor 4 (TLR-4) in porcine intestinal epithelial (PIE) cells and antigen presenting cells (APCs) from porcine Peyer’s patches (PP). Objective In view of the critical importance of PIE-APCs interactions in the regulation of intestinal immune responses, we aimed to examine the effect of LjTL2937 on activation patterns of APCs from swine PPs in co-cultures with PIE cells. In addition, we investigated whether LjTL2937 was able to beneficially modulate intestinal immunity of piglets after weaning to improve immune-health status. Results Stimulation of PIE-APCs co-cultures with LjTL2937 increased the expression of MHC-II, CD80/86, IL-10, and Bcl-3 in CD172a+CD11R1- and CD172a+CD11R1high APCs. In addition, the TL2937 strain caused the upregulation of three negative regulators of TLR4 in PIE cells: MKP-1, Bcl-3 and A20. These changes significantly reduced the inflammatory response triggered by TLR4 activation in PIE-APCs co-cultures. The in vivo experiments using castrated male piglets (crossbreeding (LWD) with Landrace (L), Large Yorkshire (W) and Duroc (D))of 3 weeks of age demonstrated that feeding with LjTL2937 significantly reduced blood complement activity and C reactive protein concentrations while no changes were observed in blood leukocytes, ratio of granulocytes to lymphocyte numbers, macrophages’ activity and antibody levels. In addition, treatment with LjTL2937 significantly improved growth performance and productivity, and increased carcass quality. Conclusions We demonstrated that the use of immunobiotics strains like LjTL2937, as supplemental additives for piglets feedings, could be used as a strategy to

A molecular dynamics study on the role of attractive and repulsive forces in internal energy, internal pressure and structure of dense fluids

NASA Astrophysics Data System (ADS)

Goharshadi, Elaheh K.; Morsali, Ali; Mansoori, G. Ali

2007-01-01

Isotherms of experimental data of internal pressure of dense fluids versus molar volume, Vm are shown to have each a maximum point at a Vmax below the critical molar volume. In this study, we investigated the role of attractive and repulsive intermolecular energies on this behavior using a molecular dynamics simulation technique. In the simulation, we choose the Lennard-Jones (LJ) intermolecular potential energy function. The LJ potential is known to be an effective potential representing a statistical average of the true pair and many-body interactions in simple molecular systems. The LJ potential function is divided into attractive and repulsive parts. MD calculations have produced internal energy, potential energy, transitional kinetic energy, and radial distribution function (RDF) for argon at 180 K and 450 K using LJ potential, LJ repulsive, and LJ attractive parts. It is shown that the LJ potential function is well capable of predicting the inflection point in the internal energy-molar volume curve as well as maximum point in the internal pressure-molar volume curve. It is also shown that at molar volumes higher than Vmax, the attractive forces have strong influence on determination of internal energy and internal pressure. At volumes lower than Vmax, neither repulsive nor attractive forces are dominating. Also, the coincidence between RDFs resulting from LJ potential and repulsive parts of LJ potential improves as molar volume approaches Vmax from high molar volumes. The coincidence becomes complete at Vmax ⩾ V.

Sputum induction is a safe procedure to use in prisoners and MGIT is the best culture method to diagnose tuberculosis in prisons: a cohort study.

PubMed

Rueda, Zulma Vanessa; López, Lucelly; Marín, Diana; Vélez, Lázaro A; Arbeláez, María Patricia

2015-04-01

To evaluate the concordance and safety of induced sputum (IS) and spontaneous sputum (SS), and estimate concordance and time to detection of M. tuberculosis between Lowenstein-Jensen (LJ), thin-layer agar (TLA), and the Mycobacteria Growth Indicator Tube system (MGIT). This was a cohort study. Prisoners with pulmonary tuberculosis (PTB) were followed for 2 years. At baseline and every follow-up visit, three sputum samples were taken on consecutive days (one IS and two SS) and adverse events occurring before, during, and 30 min after IS were registered. All sputum samples were stained with auramine and cultured in LJ, TLA (to test resistance), and MGIT. Five hundred eighty-six IS and 532 SS were performed on 64 PTB patients. Breathlessness (1.6%), cough (1.2%), hemoptysis (0.3%), and cyanosis (0.2%) were the only complications. Concordance between IS and SS was 0.78 (95% confidence interval 0.69-0.87); 11 positive cultures from IS samples were negative in SS, and 11 positive cultures from SS samples were negative in IS. One hundred seventy-eight cultures were positive by any technique: MGIT 95%, LJ 73%, and TLA 57%. Time to detection of M. tuberculosis in LJ, TLA, and MGIT was 31, 18, and 11 days, respectively. The IS procedure is safe in prisons. The MGIT system is better and faster than LJ and TLA in the diagnosis of M. tuberculosis. Copyright © 2015 The Authors. Published by Elsevier Ltd.. All rights reserved.

Identification and analysis of CYP450 genes from transcriptome of Lonicera japonica and expression analysis of chlorogenic acid biosynthesis related CYP450s.

PubMed

Qi, Xiwu; Yu, Xu; Xu, Daohua; Fang, Hailing; Dong, Ke; Li, Weilin; Liang, Chengyuan

2017-01-01

patterns during the flower development and LjC3H2 exhibited a similar expression pattern with CGA concentration measured by HPLC. The expression patterns of three LjC4Hs were quite different and the expression pattern of LjC4H3 was quite similar with that of LjC3H1 . Our results provide a comprehensive identification and characterization of CYP450s in L. japonica . Five CGA biosynthesis related CYP450s were cloned and their expression patterns were explored. The different expression patterns of two LjC3Hs and three LjC4Hs may be due to functional divergence of both substrate and catalytic specificity during plant evolution. The co-expression pattern of LjC3H1 and LjC4H3 strongly suggested that they were under coordinated regulation by the same transcription factors due to same cis elements in their promoters. In conclusion, this study provides insight into CYP450s and will effectively facilitate the research of biosynthesis of CGA in L. japonica .

40 CFR 62.2353 - Identification of sources.

Code of Federal Regulations, 2010 CFR

2010-07-01

...) Champion International Corporation (Formerly St. Regis Paper Company) in Cantonment (d) Container... Paper Company in Jacksonville (g) St. Joe Paper Company in Port St. Joe (h) Southwest Forest Industries... (Tall Oil Plant) in Port St. Joe [53 FR 30053, Aug. 10, 1988] ...

The occurrence and source identification of bisphenol compounds in wastewaters.

PubMed

Česen, Marjeta; Lenarčič, Kaja; Mislej, Vesna; Levstek, Meta; Kovačič, Ana; Cimrmančič, Bernardka; Uranjek, Nataša; Kosjek, Tina; Heath, David; Dolenc, Marija Sollner; Heath, Ester

2018-03-01

This study reports the occurrence of eight bisphenols (BPs): bisphenol AF (BPAF), bisphenol AP (BPAP), bisphenol B (BPB), bisphenol C (BPC), bisphenol E (BPE), bisphenol F (BPF), bisphenol S (BPS) and bisphenol Z (BPZ) in wastewaters (WWs). Sample preparation involved pre-concentration with SPE cartridges (Oasis HLB), followed by derivatization using N-(tert-butyldimethylsilyl)-N-methyltrifluoroacetamide with 1% tert-butyldimethylchlorosilane. Chemical analysis was based on gas chromatography-mass spectrometry. A validated method with limits of detection (LODs) at ngL -1 range was applied to WWs collected at five Slovene wastewater treatment plants (WWTPs) and WW inflows from industrial, commercial and residential sources entering the sewerage systems of two catchments (Domžale-Kamnik (DK) and Ljubljana (LJ)). The presence of all BPs was confirmed in three inflows in DK and two inflows in the LJ catchments. High cumulative concentrations of all BPs were determined in WW from food processing facilities (LJ: 3030ngL -1 and DK: 599ngL -1 ). A high detection frequency was observed in the WW from two textile cleaning companies (6 BPs for LJ and 8 BPs for DK). The analysis of WW from WWTPs revealed that only BPF (36.7ngL -1 ) and BPS (40.6ngL -1 ) were >LODs in the influents, whereas other BPs were detected also in the effluents. BPZ was found in the highest concentration (403ngL -1 at WWTP-DK). WW collected at this WWTP also contained the highest amount of BPE (238ngL -1 ). Although BPs removal could not be directly compared between the WWTPs, with the exception of BPAP and BPB in the case of two smaller WWTPs (6.39%-43.2%) bisphenols were in general highly removed (≥96.2%). Finally, levels of BPC>LOD are reported for first time (WWTP in the DK catchment: 1.01ngL -1 -11.8ngL -1 ; LJ inflow from food processing plant up to 2560ngL -1 ). Copyright © 2017 The Authors. Published by Elsevier B.V. All rights reserved.

Orion Service Module Umbilical (OSMU) Lift & Preparation for Ins

NASA Image and Video Library

2017-03-13

A view from below the mobile launcher shows a crane positioning the bracket for the Orion Service Module Umbilical (OSMU) high up for installation on the mobile launcher tower at NASA's Kennedy Space Center in Florida. The mobile launcher tower will be equipped with a number of lines, called umbilicals, that will connect to the Space Launch System rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The OSMU will be located high on the mobile launcher tower and, prior to launch, will transfer liquid coolant for the electronics and air for the Environmental Control System to the Orion service module that houses these critical systems to support the spacecraft. EM-1 is scheduled to launch in 2018. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

Orion Service Module Umbilical (OSMU) Lift & Preparation for Ins

NASA Image and Video Library

2017-03-13

In this view looking down from high up on the mobile launcher, a crane positions the bracket for the Orion Service Module Umbilical (OSMU) for installation on the mobile launcher tower at NASA's Kennedy Space Center in Florida. The mobile launcher tower will be equipped with a number of lines, called umbilicals, that will connect to the Space Launch System rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The OSMU will be located high on the mobile launcher tower and, prior to launch, will transfer liquid coolant for the electronics and air for the Environmental Control System to the Orion service module that houses these critical systems to support the spacecraft. EM-1 is scheduled to launch in 2018. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

Evaluation of nutrient agar for the culture of Mycobacterium tuberculosis using the microcolony detection method.

PubMed

Satti, L; Abbasi, S; Faiz, U

2012-07-01

We evaluated nutrient agar using the microcolony detection method for the recovery of Mycobacterium tuberculosis on 37 acid-fast bacilli (AFB) positive sputum specimens, and compared it with conventional Löwenstein-Jensen (LJ) medium. Nutrient agar detected 35 isolates compared to 34 on LJ medium. The mean time to detection of mycobacteria on nutrient agar and LJ medium was respectively 9.6 and 21.4 days. The contamination rate on nutrient agar and LJ medium was respectively 5.4% and 2.7%. Nutrient agar detects M. tuberculosis more rapidly than LJ medium, and could be an economical, rapid culture method in resource-poor settings, provided our findings are confirmed by further studies.

A trial of adding Lactobacillus johnsonii EM1 to levocetirizine for treatment of perennial allergic rhinitis in children aged 7-12 years.

PubMed

Lue, Ko-Haung; Sun, Hai-Lun; Lu, Ko-Hsiu; Ku, Min-Sho; Sheu, Ji-Nan; Chan, Ching-Hui; Wang, Yun-Hu

2012-07-01

Supplementary consumption of probiotics may temporarily alter the intestinal microflora of infants and children, thereby preventing and treating allergic disorders. To compare the clinical efficacy of levocetirizine with that of levocetirizine plus Lactobacillus johnsonii EM1 (Lj EM1) for treating perennial allergic rhinitis (PAR) in children. Sixty-three children aged 7-12 years fulfilled the entry criteria for the study and had moderate to severe PAR of at least 1 year's duration. The treatment followed a randomized, open-label crossover design: all subjects were randomized to 2 crossover treatment regimens of levocetirizine with Lj EM1 (group 1) or levocetirizine alone (group 2) for 12 weeks; subsequently, treatments were reversed for a further 12 weeks. The effects of the 2 regimens were compared using the Pediatric Rhinoconjunctivitis Quality of Life Questionnaire (PRQLQ) and the total symptom score (TSS) from diary cards. The parameters evaluated were nasal peak expiratory flow rate (nPEFR), FVC, FEV1, serum immunoglobulin E (IgE), mite-specific IgE, eosinophilic cationic protein (ECP), resistin, blood eosinophils, eosinophil percentage in nasal smears, IL-4, IL-10, interferon-γ (IFN-γ), and transforming growth factor-β (TGF-β). After the first 12 weeks of treatment, TSS in both groups had improved progressively compared with that in the run-in period. Both groups had improved TSS at weeks 4, 8, and 12 (P<0.05), and group 1 was more efficacious than group 2 at week 4 (P=0.014), week 8 (P=0.011), and week 12 (P<0.009). During the second 12-week period, group 2 showed continual and progressive improvement, while group 1 did not. The PRQLQ scores were significantly decreased in both groups (P<0.05), but there was no statistically significant difference between the 2 groups (P=0.446). The eosinophil percentage in nasal smears decreased in both groups compared with that in the run-in period, and significant differences were detected in groups 2 and 1at 16 and

Rapid and improved recovery rate of Mycobacterium tuberculosis in Mycobacteria Growth Indicator Tube combined with solid Löwenstein Jensen medium.

PubMed

Rivera, A B; Tupasi, T E; Grimaldo, E R; Cardano, R C; Co, V M

1997-10-01

Clinical microbiology laboratory with limited resources in a developing country. To determine the recovery rate of Mycobacterium tuberculosis (MTB) in Mycobacteria Growth Indicator Tube (MGIT) combined with Löwenstein Jensen (LJ) culture medium. Stock cultures and reference strains of mycobacteria and clinical specimens were inoculated into MGIT and onto LJ. The combined recovery rate was determined and time to positive culture in each medium was compared. All known stock and reference cultures of mycobacteria grew in both media. MGIT combined with LJ increased the recovery rate from 109 (63.4%) to 122 (70.9%) of 172 clinical specimens. Of those isolated, the yield in MGIT (99.2%) exceeded that in LJ (89.3%). The average day to detection of MTB in MGIT was earlier by 14.2 days compared to LJ (15.7 days vs. 29.9 days). For mycobacteria other than tuberculosis (MOTT), there was little difference in the recovery time, except for M. kansasii where growth in MGIT was earlier by one week and M. triviale where growth in MGIT was detected later than LJ. MGIT is an excellent system for the rapid isolation of mycobacteria. It increases the recovery rate of MTB when combined with LJ.

A bibliometric analysis of two PubMed-indexed high-impact factor endodontic journals: A comparison of India with other countries

PubMed Central

Mishra, Lora; Pattnaik, Prajna; Kumar, Manoj; Aggarwal, Sonia; Misra, Satya Ranjan

2016-01-01

Aim: The present study was conducted with an aim to determine the number and trends of published articles in the International Endodontic Journal (IEJ) and Journal of Endodontics (JOE) from 2009 to 2014. Settings and Designs: A retrospective observational study was conducted for IEJ and JOE. Subjects and Methods: All issues of IEJ and JOE were electronically and hand searched for the following parameters: Amount of papers, publication year, affiliated organizations, and countries. Statistical Analysis Used: The data were organized and analyzed using software SPSS version 21.0; descriptive statistics was used. Results: A total of 872 articles were analyzed in the IEJ and JOE with 1606 papers. Brazil had the largest number of articles (170) mainly in IEJ, and the USA (350) in JOE. Indians published more of their research in JOE than IEJ. Conclusions: Original articles in endodontic publication from different universities in India have considerably increased, showing that research is becoming more important. PMID:27795645

Study of cavity type antenna structure of large-area 915 MHz ultra-high frequency wave plasma device based on three-dimensional finite difference time-domain analysis

NASA Astrophysics Data System (ADS)

Chang, Xijiang; Kunii, Kazuki; Liang, Rongqing; Nagatsu, Masaaki

2013-11-01

A large-area planar plasma source with a resonant cavity type launcher driven by a 915 MHz ultra-high frequency wave was developed. Theoretical analysis with the three-dimensional finite difference time-domain simulation was carried out to determine the optimized launcher structure by analyzing the resonant transverse magnetic mode in the resonant cavity. Numerical result expects that the resonant electric field distribution inside the cavity dominantly consists of the TM410 mode. The resonant cavity type launcher having 8 holes in an octagonal geometry was designed to fit the resonant transverse magnetic mode. Adjusting 8 hole positions of the launcher to the field pattern of the resonant TM410 mode, we found that the plasma density increased about 40%˜50% from 1.0˜1.1 × 1011 cm-3 to ˜1.5 × 1011 cm-3 at the same incident power of 2.5 kW, compared with the previous results with the launcher having 6 holes in the hexagonal geometry. It is also noted that the electron density changes almost linearly with the incident wave power without any mode jumps.

PROJECT SQUID. Field Survey Report. Volume 1, Part 3. Materials

DTIC Science & Technology

1947-06-30

are thought to deserve consideration as to rfrator meals iththoe otaie~l y tit~kl~~lj materials of construction ,titanium, tungsten, tanta- tion of...provide This is a time.consuming costly process with no guar - the n. (, .d data. antee of achieving optimum results. The determina- tion of the

KENNEDY SPACE CENTER, FLA. - A camera is installed on the aft skirt of a solid rocket booster in preparation for a vibration test of the Mobile Launcher Platform with SRBs and external tank mounted. The MLP will roll from one bay to another in the Vehicle Assembly Building.

NASA Image and Video Library

2003-11-06

KENNEDY SPACE CENTER, FLA. - A camera is installed on the aft skirt of a solid rocket booster in preparation for a vibration test of the Mobile Launcher Platform with SRBs and external tank mounted. The MLP will roll from one bay to another in the Vehicle Assembly Building.

Identification of genes associated with the long-gut-persistence phenotype of the probiotic Lactobacillus johnsonii strain NCC533 using a combination of genomics and transcriptome analysis.

PubMed

Denou, Emmanuel; Pridmore, Raymond David; Berger, Bernard; Panoff, Jean-Michel; Arigoni, Fabrizio; Brüssow, Harald

2008-05-01

Lactobacillus johnsonii strains NCC533 and ATCC 33200 (the type strain of this species) differed significantly in gut residence time (12 versus 5 days) after oral feeding to mice. Genes affecting the long gut residence time of the probiotic strain NCC533 were targeted for analysis. We hypothesized that genes specific for this strain, which are expressed during passage of the bacterium through the gut, affect the phenotype. When the DNA of the type strain was hybridized against a microarray of the sequenced NCC533 strain, we identified 233 genes that were specific for the long-gut-persistence isolate. Whole-genome transcription analysis of the NCC533 strain using the microarray format identified 174 genes that were strongly and consistently expressed in the jejunum of mice monocolonized with this strain. Fusion of the two microarray data sets identified three gene loci that were both expressed in vivo and specific to the long-gut-persistence isolate. The identified genes included LJ1027 and LJ1028, two glycosyltransferase genes in the exopolysaccharide synthesis operon; LJ1654 to LJ1656, encoding a sugar phosphotransferase system (PTS) transporter annotated as mannose PTS; and LJ1680, whose product shares 30% amino acid identity with immunoglobulin A proteases from pathogenic bacteria. Knockout mutants were tested in vivo. The experiments revealed that deletion of LJ1654 to LJ1656 and LJ1680 decreased the gut residence time, while a mutant with a deleted exopolysaccharide biosynthesis cluster had a slightly increased residence time.

Interaction Potentials for Br(2P) + Ar, Kr, Xe (1S) by the Crossed Molecular Beams Method.

DTIC Science & Technology

1981-03-01

recombination was significantly affected by eBr-RG" In their study, the interaction potential between Br and RG was assumed to be of the Lennard ... Jones (L-J) form with the following parameters: RG=Ar, c=1.0 kcal/mole, a=3.0 A; RG=Xe, e-1.0 kcal/mole, a=3.5 A. A slightly shallower Br-Ar potential ...AOA-A00 002 CALIFORNIA UNIV BERKELEY LAWRENCE BERKELEY LAB F/6 20/7 INTERACTION POTENTIALS FOR BR2P) + AR. KR. XE (IS) BY THE CROS--ETCfIU MAR 81 P

Case Study, California Black Rail (Laterallus jamaicensis corturniculus): Science Foundation Chapter 5, Appendix 5.1 in The Baylands and climate change: What can we do?

USGS Publications Warehouse

Evens, Jules G.; Thorne, Karen M.

2015-01-01

The Black Rail is the smallest member of the avian family Rallidae and has a wide-ranging but highly scattered distribution throughout the New World. Of five subspecies, two occur in North America—the Eastern Black Rail (L.j. jamaicensis) and the California Black Rail (L.j. coturniculus). Throughout its range, the Black Rail is a secretive inhabitant of tidal and freshwater wetlands and rarely ventures out from the cover of dense marsh vegetation. It is more likely to be heard than seen; spontaneous vocalizations tend to be concentrated in the nesting season and are much less common during the rest of the year.

"The Two Joes Meet--Joe College, Joe Veteran": The G. I. Bill, College Education, and Postwar American Culture.

ERIC Educational Resources Information Center

Clark, Daniel A.

1998-01-01

Examines how the World War II veterans' influx into higher education changed the perception of that institution in the minds of the public and its portrayal in popular media. Previously characterized as an upper-crust indulgence, college became an acceptable symbol of social mobility. Includes reproductions of magazine advertisements. (MJP)

3 Lakota Grandmother Stories - Health Lessons for Young People.

ERIC Educational Resources Information Center

Sneve, Virginia Driving Hawk

Presenting a different situation dealing with the importance of health care, these three Lakota short stories involve two Lakota Sioux children, Joe and his sister Marie. In "Clean Hands", Joe and Marie discuss the importance of clean hands with their grandmother. "A Hospital Trip" is about Joe's stay in the hospital after he…

BEAUTY-X: enhanced BLAST searches for DNA queries.

PubMed

Worley, K C; Culpepper, P; Wiese, B A; Smith, R F

1998-01-01

BEAUTY (BLAST Enhanced Alignment Utility) is an enhanced version of the BLAST database search tool that facilitates identification of the functions of matched sequences. Three recent improvements to the BEAUTY program described here make the enhanced output (1) available for DNA queries, (2) available for searches of any protein database, and (3) more up-to-date, with periodic updates of the domain information. BEAUTY searches of the NCBI and EMBL non-redundant protein sequence databases are available from the BCM Search Launcher Web pages (http://gc.bcm.tmc. edu:8088/search-launcher/launcher.html). BEAUTY Post-Processing of submitted search results is available using the BCM Search Launcher Batch Client (version 2.6) (ftp://gc.bcm.tmc. edu/pub/software/search-launcher/). Example figures are available at http://dot.bcm.tmc. edu:9331/papers/beautypp.html (kworley,culpep)@bcm.tmc.edu

HIV, Art, a Journey Toward Healing: One Man's Story

ERIC Educational Resources Information Center

Kellman, Julia

2005-01-01

This paper includes two main narrative strands--one personal and the other the result of the author's research with Joe, a member of an art class for people with HIV/AIDS in a local hospital. Both stories, Joe's and the author's, probe the mystery of disease, expression, and the search for coherence. The author's research and Joe's story weave…

Joe Simon | NREL

Science.gov Websites

, and analysis. To enable market transformation and growth, he continuously supports several DOE-funded Building science Renewable energy Modular construction Start-ups Solar Education Competitions Education

Study of cavity type antenna structure of large-area 915 MHz ultra-high frequency wave plasma device based on three-dimensional finite difference time-domain analysis

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

Chang, Xijiang; Graduate School of Science and Engineering, Shizuoka University, 3-5-1 Johoku, Hamamatsu 432-8561; Kunii, Kazuki

2013-11-14

A large-area planar plasma source with a resonant cavity type launcher driven by a 915 MHz ultra-high frequency wave was developed. Theoretical analysis with the three-dimensional finite difference time-domain simulation was carried out to determine the optimized launcher structure by analyzing the resonant transverse magnetic mode in the resonant cavity. Numerical result expects that the resonant electric field distribution inside the cavity dominantly consists of the TM{sub 410} mode. The resonant cavity type launcher having 8 holes in an octagonal geometry was designed to fit the resonant transverse magnetic mode. Adjusting 8 hole positions of the launcher to the fieldmore » pattern of the resonant TM{sub 410} mode, we found that the plasma density increased about 40%∼50% from 1.0∼1.1 × 10{sup 11} cm{sup −3} to ∼1.5 × 10{sup 11} cm{sup −3} at the same incident power of 2.5 kW, compared with the previous results with the launcher having 6 holes in the hexagonal geometry. It is also noted that the electron density changes almost linearly with the incident wave power without any mode jumps.« less