KSC-08pd3249

NASA Image and Video Library

2008-10-17

CAPE CANAVERAL, Fla. - The Ares IX upper stage segments’ ballast assemblies have arrived at NASA’s Kennedy Space Center and are positioned along the floor of high bay 4 in the Vehicle Assembly Building, part of the preparations for the test of the Ares IX rocket. These ballast assemblies will be installed in the upper stage 1 and 7 segments and will mimic the mass of the fuel. Their total weight is approximately 160,000 pounds. The test launch of the Ares IX in 2009 will be the first designed to determine the flight-worthiness of the Ares I rocket. Ares I is an in-line, two-stage rocket that will transport the Orion crew exploration vehicle to low-Earth orbit. The Ares I first stage will be a five-segment solid rocket booster based on the four-segment design used for the space shuttle. Ares I’s fifth booster segment allows the launch vehicle to lift more weight and reach a higher altitude before the first stage separates from the upper stage, which ignites in midflight to propel the Orion spacecraft to Earth orbit. Photo credit: NASA/Kim Shiflett

KSC-08pd3248

NASA Image and Video Library

2008-10-17

CAPE CANAVERAL, Fla. - Ares IX upper stage segments’ ballast assemblies are positioned along the floor of high bay 4 in the Vehicle Assembly Building at NASA’s Kennedy Space Center, part of the preparations for the test of the Ares IX rocket. These ballast assemblies will be installed in the upper stage 1 and 7 segments and will mimic the mass of the fuel. Their total weight is approximately 160,000 pounds. The test launch of the Ares IX in 2009 will be the first designed to determine the flight-worthiness of the Ares I rocket. Ares I is an in-line, two-stage rocket that will transport the Orion crew exploration vehicle to low-Earth orbit. The Ares I first stage will be a five-segment solid rocket booster based on the four-segment design used for the space shuttle. Ares I’s fifth booster segment allows the launch vehicle to lift more weight and reach a higher altitude before the first stage separates from the upper stage, which ignites in midflight to propel the Orion spacecraft to Earth orbit. Photo credit: NASA/Kim Shiflett

KSC-08pd3250

NASA Image and Video Library

2008-10-17

CAPE CANAVERAL, Fla. - The Ares IX upper stage segments’ ballast assemblies have arrived at NASA’s Kennedy Space Center and are positioned along the floor of high bay 4 in the Vehicle Assembly Building, part of the preparations for the test of the Ares IX rocket. These ballast assemblies will be installed in the upper stage 1 and 7 segments and will mimic the mass of the fuel. Their total weight is approximately 160,000 pounds. The test launch of the Ares IX in 2009 will be the first designed to determine the flight-worthiness of the Ares I rocket. Ares I is an in-line, two-stage rocket that will transport the Orion crew exploration vehicle to low-Earth orbit. The Ares I first stage will be a five-segment solid rocket booster based on the four-segment design used for the space shuttle. Ares I’s fifth booster segment allows the launch vehicle to lift more weight and reach a higher altitude before the first stage separates from the upper stage, which ignites in midflight to propel the Orion spacecraft to Earth orbit. Photo credit: NASA/Kim Shiflett

Membrane technology for sustainable treated wastewater reuse: agricultural, environmental and hydrological considerations.

PubMed

Oron, Gideon; Gillerman, Leonid; Bick, Amos; Manor, Yossi; Buriakovsky, Nisan; Hagin, Joseph

2008-01-01

Field experiments were conducted in agricultural fields in which secondary wastewater of the City of Arad (Israel) is reused for irrigation. For sustainable agricultural production and safe groundwater recharge the secondary effluent is further polished by a combined two-stage membrane pilot system. The pilot membrane system consists of two main in row stages: Ultrafiltration (UF) and Reverse Osmosis (RO). The UF stage is efficient in the removal of the pathogens and suspended organic matter while the successive RO stage provides safe removal of the dissolved solids (salinity). Effluents of various qualities were applied for agricultural irrigation along with continuous monitoring of the membrane system performance. Best agricultural yields were obtained when applying effluent having minimal content of dissolved solids (after the RO stage) as compared with secondary effluent without any further treatment and extended storage. In regions with shallow groundwater reduced soil salinity in the upper productive layers, maintained by extra membrane treatment, will guarantee minimal dissolved solids migration to the aquifers and minimize salinisation processes. (c) IWA Publishing 2008.

Rho-Isp Revisited and Basic Stage Mass Estimating for Launch Vehicle Conceptual Sizing Studies

NASA Technical Reports Server (NTRS)

Kibbey, Timothy P.

2015-01-01

The ideal rocket equation is manipulated to demonstrate the essential link between propellant density and specific impulse as the two primary stage performance drivers for a launch vehicle. This is illustrated by examining volume-limited stages such as first stages and boosters. This proves to be a good approximation for first-order or Phase A vehicle design studies for solid rocket motors and for liquid stages, except when comparing to hydrogen-fueled stages. A next-order mass model is developed that is able to model the mass differences between hydrogen-fueled and other stages. Propellants considered range in density from liquid methane to inhibited red fuming nitric acid. Calculated comparisons are shown for solid rocket boosters, liquid first stages, liquid upper stages, and a balloon-deployed single-stage-to-orbit concept. The derived relationships are ripe for inclusion in a multi-stage design space exploration and optimization algorithm, as well as for single-parameter comparisons such as those shown herein.

Modular Approach to Launch Vehicle Design Based on a Common Core Element

NASA Technical Reports Server (NTRS)

Creech, Dennis M.; Threet, Grady E., Jr.; Philips, Alan D.; Waters, Eric D.; Baysinger, Mike

2010-01-01

With a heavy lift launch vehicle as the centerpiece of our nation's next exploration architecture's infrastructure, the Advanced Concepts Office at NASA's Marshall Space Flight Center initiated a study to examine the utilization of elements derived from a heavy lift launch vehicle for other potential launch vehicle applications. The premise of this study is to take a vehicle concept, which has been optimized for Lunar Exploration, and utilize the core stage with other existing or near existing stages and boosters to determine lift capabilities for alternative missions. This approach not only yields a vehicle matrix with a wide array of capabilities, but also produces an evolutionary pathway to a vehicle family based on a minimum development and production cost approach to a launch vehicle system architecture, instead of a purely performance driven approach. The upper stages and solid rocket booster selected for this study were chosen to reflect a cross-section of: modified existing assets in the form of a modified Delta IV upper stage and Castor-type boosters; potential near term launch vehicle component designs including an Ares I upper stage and 5-segment boosters; and longer lead vehicle components such as a Shuttle External Tank diameter upper stage. The results of this approach to a modular launch system are given in this paper.

HEUS-RS applications study, volume 2

NASA Technical Reports Server (NTRS)

1972-01-01

The final report of a High Energy Upper Stage Restartable Solid (HEUS-RS) Applications Study is presented. The material deals with launch program cost comparisons associated with meeting NASA mission model requirements with several different launch vehicle approaches.

Advanced Concept

NASA Image and Video Library

2008-03-15

A CONCEPT IMAGE SHOWS THE ARES I CREW LAUNCH VEHICLE DURING ASCENT. ARES I IS AN IN-LINE, TWO-STAGE ROCKET CONFIGURATION TOPED BY THE ORION CREW EXPLORATION VEHICLE AND LAUNCH ABORT SYSTEM. THE ARES I FIRST STAGE IS A SINGLE, FIVE-SEGMENT REUSABLE SOLID ROCKET BOOSTER, DERIVED FROM THE SPACE SHUTTLE. ITS UPPER STAGE IS POWERED BY A J-2X ENGINE. ARES I WILL CARRY THE ORION WITH ITS CRW OF UP TO SIX ASTRONAUTS TO EARTH ORBIT.

Dynamic Modeling and Control Studies of a Two-Stage Bubbling Fluidized Bed Adsorber-Reactor for Solid-Sorbent CO{sub 2} Capture

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

Modekurti, Srinivasarao; Bhattacharyya, Debangsu; Zitney, Stephen E.

2013-07-31

A one-dimensional, non-isothermal, pressure-driven dynamic model has been developed for a two-stage bubbling fluidized bed (BFB) adsorber-reactor for solid-sorbent carbon dioxide (CO{sub 2}) capture using Aspen Custom Modeler® (ACM). The BFB model for the flow of gas through a continuous phase of downward moving solids considers three regions: emulsion, bubble, and cloud-wake. Both the upper and lower reactor stages are of overflow-type configuration, i.e., the solids leave from the top of each stage. In addition, dynamic models have been developed for the downcomer that transfers solids between the stages and the exit hopper that removes solids from the bottom ofmore » the bed. The models of all auxiliary equipment such as valves and gas distributor have been integrated with the main model of the two-stage adsorber reactor. Using the developed dynamic model, the transient responses of various process variables such as CO{sub 2} capture rate and flue gas outlet temperatures have been studied by simulating typical disturbances such as change in the temperature, flowrate, and composition of the incoming flue gas from pulverized coal-fired power plants. In control studies, the performance of a proportional-integral-derivative (PID) controller, feedback-augmented feedforward controller, and linear model predictive controller (LMPC) are evaluated for maintaining the overall CO{sub 2} capture rate at a desired level in the face of typical disturbances.« less

Research on advanced transportation systems

NASA Astrophysics Data System (ADS)

Nagai, Hirokazu; Hashimoto, Ryouhei; Nosaka, Masataka; Koyari, Yukio; Yamada, Yoshio; Noda, Keiichirou; Shinohara, Suetsugu; Itou, Tetsuichi; Etou, Takao; Kaneko, Yutaka

1992-08-01

An overview of the researches on advanced space transportation systems is presented. Conceptual study is conducted on fly back boosters with expendable upper stage rocket systems assuming a launch capacity of 30 tons and returning to the launch site by the boosters, and prospect of their feasibility is obtained. Reviews are conducted on subjects as follows: (1) trial production of 10 tons sub scale engines for the purpose of acquiring hardware data and picking up technical problems for full scale 100 tons thrust engines using hydrocarbon fuels; (2) development techniques for advanced liquid propulsion systems from the aspects of development schedule, cost; (3) review of conventional technologies, and common use of component; (4) oxidant switching propulsion systems focusing on feasibility of Liquefied Air Cycle Engine (LACE) and Compressed Air Cycle Engine (CACE); (5) present status of slosh hydrogen manufacturing, storage, and handling; (6) construction of small high speed dynamometer for promoting research on mini pump development; (7) hybrid solid boosters under research all over the world as low-cost and clean propulsion systems; and (8) high performance solid propellant for upper stage and lower stage propulsion systems.

Orbit Transfer Systems with Emphasis on Shuttle Applications, 1986-1991

NASA Technical Reports Server (NTRS)

1977-01-01

A systems study is presented for a transportation system which will follow the interim upper stage and spinning solid upper stage. Included are concepts, concept comparisons, trends, parametric data, etc. associated with the future system. Relevant technical and programmatic information is developed. This information is intended to focus future activity to identify attractive options and to summarize the major issues associated with the future development of the system. To establish a common basis for identifying current transportation concepts, an orbit transfer vehicle (OTV) is defined as a propulsive (velocity producing) rocket or stage. When used with a crew transfer module, a manned sortie module or other payloads, the combination becomes an orbit transfer system (OTS). Standardization of OTV's and OTS's is required.

NASA Ares I Launch Vehicle Roll and Reaction Control Systems Design Status

NASA Technical Reports Server (NTRS)

Butt, Adam; Popp, Chris G.; Pitts, Hank M.; Sharp, David J.

2009-01-01

This paper provides an update of design status following the preliminary design review of NASA s Ares I first stage roll and upper stage reaction control systems. The Ares I launch vehicle has been chosen to return humans to the moon, mars, and beyond. It consists of a first stage five segment solid rocket booster and an upper stage liquid bi-propellant J-2X engine. Similar to many launch vehicles, the Ares I has reaction control systems used to provide the vehicle with three degrees of freedom stabilization during the mission. During launch, the first stage roll control system will provide the Ares I with the ability to counteract induced roll torque. After first stage booster separation, the upper stage reaction control system will provide the upper stage element with three degrees of freedom control as needed. Trade studies and design assessments conducted on the roll and reaction control systems include: propellant selection, thruster arrangement, pressurization system configuration, and system component trades. Since successful completion of the preliminary design review, work has progressed towards the critical design review with accomplishments made in the following areas: pressurant / propellant tank, thruster assembly, and other component configurations, as well as thruster module design, and waterhammer mitigation approach. Also, results from early development testing are discussed along with plans for upcoming system testing. This paper concludes by summarizing the process of down selecting to the current baseline configuration for the Ares I roll and reaction control systems.

Low energy stage study. Volume 1: Executive summary. [propulsion system configurations for orbital launching of space shuttle payloads

NASA Technical Reports Server (NTRS)

1978-01-01

Cost effective approaches for placing automated payloads into circular and elliptical orbits using energy requirements significantly lower than that provided by the smallest, currently planned shuttle upper stage, SSUS-D, were investigated. Launch costs were derived using both NASA existing/planned launch approaches as well as new propulsion concepts meeting low-energy regime requirements. Candidate new propulsion approaches considered were solid (tandem, cluster, and controlled), solid/liquid combinations and all-liquid stages. Results show that the most economical way to deliver the 129 low energy payloads is basically with a new modular, short liquid bipropellant stage system for the large majority of the payloads. For the remainder of the payloads, use the shuttle with integral OMS and the Scout form for a few specialized payloads until the Shuttle becomes operational.

KSC-05pd2547

NASA Image and Video Library

2005-12-01

KENNEDY SPACE CENTER, FLA. - In NASA Kennedy Space Center’s Payload Hazardous Servicing Facility, Boeing workers attach a crane to the top of the cover surrounding the third stage, or upper stage, for the New Horizons spacecraft. The third stage is a Boeing STAR 48 solid-propellant kick motor. The launch vehicle for New Horizons is the Atlas V rocket, scheduled to launch from Cape Canaveral Air Force Station, Fla., during a 35-day window that opens Jan. 11, and fly through the Pluto system as early as summer 2015.

Analytical investigation of solid rocket nozzle failure

NASA Technical Reports Server (NTRS)

Mccoy, K. E.; Hester, J.

1985-01-01

On April 5, 1983, an Inertial Upper Stage (IUS) spacecraft experienced loss of control during the burn of the second of two solid rocket motors. The anomaly investigation showed the cause to be a malfunction of the solid rocket motor. This paper presents a description of the IUS system, a failure analysis summary, an account of the thermal testing and computer modeling done at Marshall Space Flight Center, a comparison of analysis results with thermal data obtained from motor static tests, and describes some of the design enhancement incorporated to prevent recurrence of the anomaly.

The Ares Projects: Building America's Future in Space

NASA Technical Reports Server (NTRS)

Cook, Stephen A.

2009-01-01

NASA's Constellation Program is depending on the Ares Projects to deliver the crew and cargo launch capabilities needed to send human explorers to the Moon and beyond. In 2009, the Ares Projects plan to conduct the first test flight of Ares I, Ares I-X; the first firing of a five-segment development solid rocket motor for the Ares I first stage; building the first integrated Ares I upper stage; continue component testing for the J-2X upper stage engine; and perform more-detailed design studies for the Ares V cargo launch vehicle. Ares I and V will provide the core space launch capabilities needed to continue providing crew and cargo access to the International Space Station (ISS), and to build upon the U.S. history of human spaceflight to the Moon and beyond.

Ares First Stage "Systemology" - Combining Advanced Systems Engineering and Planning Tools to Assure Mission Success

NASA Technical Reports Server (NTRS)

Seiler, James; Brasfield, Fred; Cannon, Scott

2008-01-01

Ares is an integral part of NASA s Constellation architecture that will provide crew and cargo access to the International Space Station as well as low earth orbit support for lunar missions. Ares replaces the Space Shuttle in the post 2010 time frame. Ares I is an in-line, two-stage rocket topped by the Orion Crew Exploration Vehicle, its service module, and a launch abort system. The Ares I first stage is a single, five-segment reusable solid rocket booster derived from the Space Shuttle Program's reusable solid rocket motor. The Ares second or upper stage is propelled by a J-2X main engine fueled with liquid oxygen and liquid hydrogen. This paper describes the advanced systems engineering and planning tools being utilized for the design, test, and qualification of the Ares I first stage element. Included are descriptions of the current first stage design, the milestone schedule requirements, and the marriage of systems engineering, detailed planning efforts, and roadmapping employed to achieve these goals.

ARES I Upper Stage Subsystems Design and Development

NASA Technical Reports Server (NTRS)

Frate, David T.; Senick, Paul F.; Tolbert, Carol M.

2011-01-01

From 2005 through early 2011, NASA conducted concept definition, design, and development of the Ares I launch vehicle. The Ares I was conceived to serve as a crew launch vehicle for beyond-low-Earth-orbit human space exploration missions as part of the Constellation Program Architecture. The vehicle was configured with a single shuttle-derived solid rocket booster first stage and a new liquid oxygen/liquid hydrogen upper stage, propelled by a single, newly developed J-2X engine. The Orion Crew Exploration Vehicle was to be mated to the forward end of the Ares I upper stage through an interface with fairings and a payload adapter. The vehicle design passed a Preliminary Design Review in August 2008, and was nearing the Critical Design Review when efforts were concluded as a result of the Constellation Program s cancellation. At NASA Glenn Research Center, four subsystems were developed for the Ares I upper stage. These were thrust vector control (TVC) for the J-2X, electrical power system (EPS), purge and hazardous gas (P&HG), and development flight instrumentation (DFI). The teams working each of these subsystems achieved 80 percent or greater design completion and extensive development testing. These efforts were extremely successful representing state-of-the-art technology and hardware advances necessary to achieve Ares I reliability, safety, availability, and performance requirements. This paper documents the designs, development test activity, and results.

KSC-97PC870

NASA Image and Video Library

1997-05-30

A Titan IVB core vehicle and its twin Solid Rocket Motor Upgrades (SRMUs) depart from the Solid Rocket Motor Assembly and Readiness Facility (SMARF), Cape Canaveral Air Station (CCAS), en route to Launch Complex 40. At the pad, the Centaur upper stage will be added and, eventually, the prime payload, the Cassini spacecraft. Cassini will explore the Saturnian system, including the planet’s rings and moon, Titan. Launch of the Cassini mission to Saturn is scheduled for Oct. 6 from Pad 40, CCAS

Ablation Modeling of Ares-I Upper State Thermal Protection System Using Thermal Desktop

NASA Technical Reports Server (NTRS)

Sharp, John R.; Page, Arthur T.

2007-01-01

The thermal protection system (TPS) for the Ares-I Upper Stage will be based on Space Transportation System External Tank (ET) and Solid Rocket Booster (SRB) heritage materials. These TPS materials were qualified via hot gas testing that simulated ascent and re-entry aerothermodynamic convective heating environments. From this data, the recession rates due to ablation were characterized and used in thermal modeling for sizing the thickness required to maintain structural substrate temperatures. At Marshall Space Flight Center (MSFC), the in-house code ABL is currently used to predict TPS ablation and substrate temperatures as a FORTRAN application integrated within SINDA/G. This paper describes a comparison of the new ablation utility in Thermal Desktop and SINDA/FLUINT with the heritage ABL code and empirical test data which serves as the validation of the Thermal Desktop software for use on the design of the Ares-I Upper Stage project.

KSC-07pd1315

NASA Image and Video Library

2007-05-28

KENNEDY SPACE CENTER, FLA. -- In the mobile service tower on Launch Pad 17-B at Cape Canaveral Air Force Station, the Delta II first stage is ready to receive the upper stages and solid rocket boosters for launch. The rocket is the launch vehicle for the Dawn spacecraft, targeted for liftoff on June 30. Dawn's mission is to explore two of the asteroid belt's most intriguing and dissimilar occupants: asteroid Vesta and the dwarf planet Ceres. Photo credit: NASA/Amanda Diller

Inertial upper stage - Upgrading a stopgap proves difficult

NASA Astrophysics Data System (ADS)

Geddes, J. P.

The technological and project management difficulties associated with the Inertial Upper Stage's (IUS) development and performance to date are assessed, with a view to future prospects for this system. The IUS was designed for use both on the interim Titan 34D booster and the Space Shuttle Orbiter. The IUS malfunctions and cost overruns reported are substantially due to the system's reliance on novel propulsion and avionics technology. Its two solid rocket motors, which were selected on the basis of their inherent safety for use on the Space Shuttle, have the longest burn time extant. A three-dimensional carbon/carbon nozzle throat had to be developed to sustain this long burn, as were lightweight composite wound cases and shirts, insulation, igniters, and electromechanical thrust vector control.

Systems Simulation of NASA Shooting Star Experiment Using Matlab/Simulink

NASA Technical Reports Server (NTRS)

Reagan, Shawn

1997-01-01

The Shooting Star Experiment (SSE) is an experiment that incorporates advance propulsion technology. This project is being managed by the Marshall Space Flight Center, Huntsville, Alabama. Whenever spacecraft are launched from Low Earth Orbit (LEO), (typically 150 nautical miles) they are powered by a upper propulsive stage utilizing either a solid or liquid propellant engine. A typically mission for a spacecraft utilizing an upper stage would be a transfer from LEO to a Geostationary Orbit (GEO) or an interplanetary mission. These upper stages are heavy and bulky because they must carry propellants to provide sufficient energy to perform the mission. The SSE utilizes the energy of the Sun by focusing this energy by means of a Frensel lens into an engine where hydrogen (or nitrogen) gas is injected. The focusing of the solar energy heats the engine to very high temperatures. When the gas is injected into the hot engine, the gas is expelled at very high velocities. This process is extremely efficient. Because of the efficiency of the SSE type engine, more payload can be carried for a typical mission since the propulsive element is much smaller.

Overview of Experimental Investigations for Ares I Launch Vehicle Development

NASA Technical Reports Server (NTRS)

Tomek, William G.; Erickson, Gary E.; Pinier, Jeremy T.; Hanke, Jeremy L.

2011-01-01

Another concern for the vehicle during its design trajectory was the separation of the first stage solid rocket booster from the upper stage component after it had depleted its solid fuel propellant. There has been some concern about the interstage of the first stage from clearing the nozzle of the J2-X engine. A detailed separation aerodynamic wind tunnel investigation was conducted in the AEDC VKF Tunnel A to help to investigate the interaction aerodynamic effects5. A comparison of the separation plane details between the Ares I architecture and the Ares I-X demonstration flight architecture is shown in figure 12. The Ares I design requires a more complex separation sequence and requires better control in order to avoid contact with the nozzle of the upper stage engine. The interstage, which houses the J2-X engine for the Ares I vehicle, must be able to separate cleanly to avoid contact of the J2-X engine. There is only about approximately 18 inches of buffer inside the interstage on each size of the nozzle so this is a challenging controlled separation event. This complex experimental investigation required two separate Ares I models (upper stage and first stage with interstage attached) with independent strain gauge balances installed in each model. It also required the Captive Trajectory System (CTS) that was needed to precisely locate the components in space relative to each other to fill out the planned test matrix. The model setup in the AEDC VKF Tunnel A is shown in figure 13. The CTS remotely positioned the first stage at the required x, y, and z positions and was able to provide interactions within 0.2" of the upper stage. A sample of the axial force on the first stage booster is shown in figure 14. These results, as a function of separation distance between the two stages, are compared to pre-test CFD results. Since this is a very challenging, highly unsteady flow field for CFD to correctly model, the experimental results have been utilized by GN&C discipline to more accurately represent the interaction aerodynamics. In addition to the integrated forces and moments obtained from the test, flow visualization data was obtained from this test in the form of Schlieren photographs, as shown in figure 15, which show the shock structure and interaction effects after the two stages separate during flight. This separation test was crucial in the successful flight test of the Ares I-X vehicle and provided the GN&C discipline with the unpowered proximity aerodynamic effect for a separation of the Ares I vehicle.

Propulsion Progress for NASA's Space Launch System

NASA Technical Reports Server (NTRS)

May, Todd A.; Lyles, Garry M.; Priskos, Alex S.; Kynard, Michael H.; Lavoie, Anthony R.

2012-01-01

Leaders from NASA's Space Launch System (SLS) will participate in a panel discussing the progress made on the program's propulsion systems. The SLS will be the nation's next human-rated heavy-lift vehicle for new missions beyond Earth's orbit. With a first launch slated for 2017, the SLS Program is turning plans into progress, with the initial rocket being built in the U.S.A. today, engaging the aerospace workforce and infrastructure. Starting with an overview of the SLS mission and programmatic status, the discussion will then delve into progress on each of the primary SLS propulsion elements, including the boosters, core stage engines, upper stage engines, and stage hardware. Included will be a discussion of the 5-segment solid rocket motors (ATK), which are derived from Space Shuttle and Ares developments, as well as the RS-25 core stage engines from the Space Shuttle inventory and the J- 2X upper stage engine now in testing (Pratt and Whitney Rocketdyne). The panel will respond to audience questions about this important national capability for human and scientific space exploration missions.

Combustion Performance of a Staged Hybrid Rocket with Boron addition

NASA Astrophysics Data System (ADS)

Lee, D.; Lee, C.

2018-04-01

In this paper, the effect of boron on overall system specific impulse was investigated. Additionally, a series of combustion tests was carried out to analyze and evaluate the effect of boron addition on O/F variation and radial temperature profiles. To maintain the hybrid rocket engine advantages, upper limit of boron contents in solid fuel was set to be 10 wt%. The results also suggested that, when adding boron to solid fuel, it helped to provide more uniform radial temperature distribution and also to increase specific impulse by 3.2%.

Yeast community associated with the solid state fermentation of traditional Chinese Maotai-flavor liquor.

PubMed

Wu, Qun; Chen, Liangqiang; Xu, Yan

2013-09-02

Yeasts are the most important group of microorganisms contributing to liquor quality in the solid-state fermentation process of Chinese Maotai-flavor liquor. There occurred a complex yeast community structure during this process, including stages of Daqu (the starter) making, stacking fermentation on the ground and liquor fermentation in the pits. In the Daqu making stage, few yeast strains accumulated. However, the stacking fermentation stage accumulated nine yeast species with different physio-biochemical characteristics. But only four species kept dominant until liquor fermentation, which were Zygosaccharomyces bailii, Saccharomyces cerevisiae, Pichia membranifaciens, and Schizosaccharomyces pombe, implying their important functions in liquor making. The four species tended to inhabit in different locations of the stack and pits during stacking and liquor fermentation, due to the condition heterogeneity of the solid-state fermentation, including the different fermentation temperature profiles and oxygen density in different locations. Moreover, yeast population was much larger in the upper layer than that in the middle and bottom layers in liquor fermentation, which was in accordance with the profile of reducing sugar consumption and ethanol production. This was a systematical investigation of yeast community structure dynamics in the Maotai-flavor liquor fermentation process. It would be of help to understand the fermentative mechanism in solid-state fermentation for Maotai-flavor liquor. © 2013.

KSC-05pd2542

NASA Image and Video Library

2005-12-01

KENNEDY SPACE CENTER, FLA. - Inside NASA Kennedy Space Center’s Payload Hazardous Servicing Facility, workers push the newly arrived third stage, or upper stage for the New Horizons spacecraft, into position for uncovering. The third stage is a Boeing STAR 48 solid-propellant kick motor. The Atlas V is the launch vehicle for NASA’s New Horizons spacecraft, scheduled to launch from Cape Canaveral Air Force Station, Fla., during a 35-day window that opens Jan. 11 and fly through the Pluto system as early as summer 2015. New Horizons will be powered by a single radioisotope thermoelectric generator (RTG), provided by the Department of Energy, which will be installed shortly before launch.

KSC-05pd2539

NASA Image and Video Library

2005-12-01

KENNEDY SPACE CENTER, FLA. - Before dawn, the third stage, or upper stage for the New Horizons spacecraft, arrives at NASA Kennedy Space Center’s Payload Hazardous Servicing Facility. The third stage is a Boeing STAR 48 solid-propellant kick motor. The Atlas V is the launch vehicle for NASA’s New Horizons spacecraft, scheduled to launch from Cape Canaveral Air Force Station, Fla., during a 35-day window that opens Jan. 11 and fly through the Pluto system as early as summer 2015. New Horizons will be powered by a single radioisotope thermoelectric generator (RTG), provided by the Department of Energy, which will be installed shortly before launch.

KSC-05pd2541

NASA Image and Video Library

2005-12-01

KENNEDY SPACE CENTER, FLA. - The third stage, or upper stage for the New Horizons spacecraft, is moved toward the open door of NASA Kennedy Space Center’s Payload Hazardous Servicing Facility. The third stage is a Boeing STAR 48 solid-propellant kick motor. The Atlas V is the launch vehicle for NASA’s New Horizons spacecraft, scheduled to launch from Cape Canaveral Air Force Station, Fla., during a 35-day window that opens Jan. 11 and fly through the Pluto system as early as summer 2015. New Horizons will be powered by a single radioisotope thermoelectric generator (RTG), provided by the Department of Energy, which will be installed shortly before launch.

KSC-05pd2540

NASA Image and Video Library

2005-12-01

KENNEDY SPACE CENTER, FLA. - The third stage, or upper stage for the New Horizons spacecraft, is moved toward the open door of NASA Kennedy Space Center’s Payload Hazardous Servicing Facility. The third stage is a Boeing STAR 48 solid-propellant kick motor. The Atlas V is the launch vehicle for NASA’s New Horizons spacecraft, scheduled to launch from Cape Canaveral Air Force Station, Fla., during a 35-day window that opens Jan. 11 and fly through the Pluto system as early as summer 2015. New Horizons will be powered by a single radioisotope thermoelectric generator (RTG), provided by the Department of Energy, which will be installed shortly before launch.

KSC-05pd2543

NASA Image and Video Library

2005-12-01

KENNEDY SPACE CENTER, FLA. - Inside NASA Kennedy Space Center’s Payload Hazardous Servicing Facility, workers remove the protective cover from around the newly arrived third stage, or upper stage for the New Horizons spacecraft. The third stage is a Boeing STAR 48 solid-propellant kick motor. The Atlas V is the launch vehicle for NASA’s New Horizons spacecraft, scheduled to launch from Cape Canaveral Air Force Station, Fla., during a 35-day window that opens Jan. 11 and fly through the Pluto system as early as summer 2015. New Horizons will be powered by a single radioisotope thermoelectric generator (RTG), provided by the Department of Energy, which will be installed shortly before launch.

Ares V and RS-68B

NASA Technical Reports Server (NTRS)

Creech, Steve; Taylor, Jim; Bellamy, Scott; Kuck, Fritz

2008-01-01

Ares V is the heavy lift vehicle NASA is designing for lunar and other space missions. It has significantly more lift capability than the Saturn V vehicle used for the Apollo missions to the moon. Ares V is powered by two recoverable 5.5 segment solid rocket boosters and six RS-68B engines on the core stage. The upper stage, designated as the Earth Departure Stage, is powered by a single J-2X engine. This paper provides an overview of the Ares V vehicle and the RS-68B engine, an upgrade to the Pratt & Whitney Rocketdyne RS-68 engine developed for the Delta IV vehicle.

NASA's Space Launch System Takes Shape

NASA Technical Reports Server (NTRS)

Askins, Bruce R.; Robinson, Kimberly F.

2017-01-01

Significant hardware and software for NASA's Space Launch System (SLS) began rolling off assembly lines in 2016, setting the stage for critical testing in 2017 and the launch of new capability for deep-space human exploration. (Figure 1) At NASA's Michoud Assembly Facility (MAF) near New Orleans, LA, full-scale test articles are being joined by flight hardware. Structural test stands are nearing completion at NASA's Marshall Space Flight Center (MSFC), Huntsville, AL. An SLS booster solid rocket motor underwent test firing, while flight motor segments were cast. An RS-25 and Engine Control Unit (ECU) for early SLS flights were tested at NASA's Stennis Space Center (SSC). The upper stage for the first flight was completed, and NASA completed Preliminary Design Review (PDR) for a new, powerful upper stage. The pace of production and testing is expected to increase in 2017. This paper will discuss the technical and programmatic highlights and challenges of 2016 and look ahead to plans for 2017.

State and prospects of solid propellant rocket development

NASA Astrophysics Data System (ADS)

Kukushkin, V. Kh.

1992-07-01

An overview is presented of aspects of solid-propellant rocket engine (SPRE) development with individual treatment given to sustainer and spacecraft SPRE technologies. The paper focuses on low-modulus fuels of composite solid propellant, requirements for adhesion stability, and enhancement of the power characteristics of solid propellants. R&D activities are described that relate to the use of SPREs with extending nozzles and to the design of ultradimensional nozzles for upper-stage engines. Other developments for the SPREs include engines with separate loading and pasty fuel applications, and progress is reported in the direction of detonation SPREs. The SPREs using pasty propellants provide good control over thrust characteristics and fuel qualities. A device is incorporated that assures fuel burning in the combustion region and reliable ignition during restarting of these engines.

Ultrasonic sensor system to detect solids in a milk pasteurization process

NASA Astrophysics Data System (ADS)

Barroeta Z., Carlos; Sanchez M., Fernando L.; Fernando R., G. Moreno; Montes P., Laura

2002-11-01

In the food industry, many products require a specific process. In the milk industry, the raw milk passes through several process stages before reaching the end user in a very qualitative and healthy way. One of the problems of the milk is that it can contain solids in suspension, result of contamination of the milk, or inherent to the pasteurization process itself. In order to control these solids, a solid detection system is being developed, which will detect the solids by the reflection and refraction of ultrasonic waves. The sensor must be set in the upper part of the milk containers, and with a grid array to allow the control system to prevent these solids from entering into the pipes of the processing plant. The sensing system may activate an acoustic alarm to indicate that a solid has been detected, and a visual one to indicate the affected part of the process. (To be presented in Spanish.)

blessing ceremony for the rocket

NASA Image and Video Library

2014-02-27

The H-IIA No. 23 rocket that will carry the GPM Core Observatory into space arrived at Tanegashima Space Center on Jan. 20, 2014. The rocket has two stages, an lower first stage that, with the help of two solid rocket boosters gets them off the ground, and an upper second stage that lights up a few minutes after launch to boost the satellite the rest of the way to orbit. The launch services provider, Mitsubishi Heavy Industries (MHI), immediately began assembling the rocket. On Jan. 22, the GPM team in Tanegashima was invited to participate in a blessing ceremony for the rocket. Lynette Marbley, the Instruments Chief Safety and Mission Assurance Officer for GPM, represented the NASA team.

Waterhammer Testing and Modeling of the Ares I Upper Stage Reaction Control System

NASA Technical Reports Server (NTRS)

Williams, J. Hunter; Holt, Kimberly A.

2010-01-01

NASA's Ares I rocket is the agency's first step in completing the goals of the Constellation Program, which plans to deliver a new generation of space explorers into low earth orbit for future missions to the International Space Station, the moon, and other destinations within the solar system. Ares I is a two-stage rocket topped by the Orion crew capsule and its service module. The launch vehicle's First Stage is a single, five-segment reusable solid rocket booster (RSRB), derived from the Space Shuttle Program's four segment RSRB. The vehicle's Upper Stage, being designed at Marshall Space Flight Center (MSFC), is propelled by a single J-2X Main Engine fueled with liquid oxygen and liquid hydrogen. During active Upper Stage flight of the Ares I launch vehicle, the Upper Stage Reaction Control System (US ReCS) will perform attitude control operations for the vehicle. The US ReCS will provide three-axis attitude control capability (roll, pitch, and yaw) for the Upper Stage while the J-2X is not firing and roll control capability while the engine is firing. Because of the requirements imposed upon the system, the design must accommodate rapid pulsing of multiple thrusters simultaneously to maintain attitude control. In support of these design activities and in preparation for Critical Design Review, analytical models of the US ReCS propellant feed system have been developed using the Thermal Hydraulic Library of MSC.EASY5 v.2008, herein referred to as EASY5. EASY5 is a commercially available fluid system modeling package with significant history of modeling space propulsion systems. In Fall 2009, a series of development tests were conducted at MSFC on a cold-flow test article for the US ReCS, herein referred to as System Development Test Article (SDTA). A subset of those tests performed were aimed at examining the effects of waterhammer on a flight-representative system and to ensure that those effects could be quantified with analytical models and incorporated into the design of the flight system. This paper presents an overview of the test article and the test approach, along with a discussion of the analytical modeling methodology. In addition, the results of that subset of development tests, along with analytical model pre-test predictions and post-test model correlations, will also be discussed in detail.

Crew Launch Vehicle (CLV) Upper Stage Configuration Selection Process

NASA Technical Reports Server (NTRS)

Davis, Daniel J.; Coook, Jerry R.

2006-01-01

The Crew Launch Vehicle (CLV), a key component of NASA's blueprint for the next generation of spacecraft to take humans back to the moon, is being designed and built by engineers at NASA s Marshall Space Flight Center (MSFC). The vehicle s design is based on the results of NASA's 2005 Exploration Systems Architecture Study (ESAS), which called for development of a crew-launch system to reduce the gap between Shuttle retirement and Crew Exploration Vehicle (CEV) Initial Operating Capability, identification of key technologies required to enable and significantly enhance these reference exploration systems, and a reprioritization of near- and far-term technology investments. The Upper Stage Element (USE) of the CLV is a clean-sheet approach that is being designed and developed in-house, with element management at MSFC. The USE concept is a self-supporting cylindrical structure, approximately 115' long and 216" in diameter, consisting of the following subsystems: Primary Structures (LOX Tank, LH2 Tank, Intertank, Thrust Structure, Spacecraft Payload Adaptor, Interstage, Forward and Aft Skirts), Secondary Structures (Systems Tunnel), Avionics and Software, Main Propulsion System, Reaction Control System, Thrust Vector Control, Auxiliary Power Unit, and Hydraulic Systems. The ESAS originally recommended a CEV to be launched atop a four-segment Space Shuttle Main Engine (SSME) CLV, utilizing an RS-25 engine-powered upper stage. However, Agency decisions to utilize fewer CLV development steps to lunar missions, reduce the overall risk for the lunar program, and provide a more balanced engine production rate requirement prompted engineers to switch to a five-segment design with a single Saturn-derived J-2X engine. This approach provides for single upper stage engine development for the CLV and an Earth Departure Stage, single Reusable Solid Rocket Booster (RSRB) development for the CLV and a Cargo Launch Vehicle, and single core SSME development. While the RSRB design has changed since the CLV Project's inception, the USE design has remained essentially a clean-sheet approach. Although a clean-sheet upper stage design inherently carries more risk than a modified design, it does offer many advantages: a design for increased reliability; built-in extensibility to allow for commonality/growth without major redesign; and incorporation of state-of-the-art materials, hardware, and design, fabrication, and test techniques and processes to facilitate a potentially better, more reliable system. Because consideration was given in the ESAS to both clean-sheet and modified USE designs, this paper will highlight the advantages and disadvantages of both approaches and provide a detailed discussion of trades/selections made that led to the final upper stage configuration.

Ares 1 First Stage Design, Development, Test, and Evaluation

NASA Technical Reports Server (NTRS)

Williams, Tom; Cannon, Scott

2006-01-01

The Ares I Crew Launch Vehicle (CLV) is an integral part of NASA s exploration architecture that will provide crew and cargo access to the International Space Station as well as low earth orbit support for lunar missions. Currently in the system definition phase, the CLV is planned to replace the Space Shuttle for crew transport in the post 2010 time frame. It is comprised of a solid rocket booster (SRB) first stage derived from the current Space Shuttle SRB, a liquid oxygen/hydrogen fueled second stage utilizing a derivative of the Apollo upper stage engine for propulsion, and a Crew Exploration Vehicle (CEV) composed of command and service modules. This paper deals with current design, development, test, and evaluation planning for the CLV first stage SRB. Described are the current overall point-of-departure design and booster subsystems, systems engineering approach, and milestone schedule requirements.

KSC-2009-4610

NASA Image and Video Library

2009-08-12

CAPE CANAVERAL, Fla. – In the Vehicle Assembly Building's High Bay 3, the Ares I-X rocket is being assembled on the mobile launcher platform. Super Stack 4 has just been mated to Super Stack 3 on top. Five super stacks make up the upper stage that will be integrated with the four-segment solid rocket booster first stage on the mobile launch platform. Ares I-X is the test vehicle for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. The Ares I-X flight test is targeted for Oct. 31, pending formal NASA Headquarters approval. Photo credit: NASA/Jack Pfaller

KSC-2009-4609

NASA Image and Video Library

2009-08-12

CAPE CANAVERAL, Fla. – In the Vehicle Assembly Building's High Bay 3, the Ares I-X rocket is being assembled on the mobile launcher platform. Super Stack 4 has just been mated to Super Stack 3 on top. Five super stacks make up the upper stage that will be integrated with the four-segment solid rocket booster first stage on the mobile launch platform. Ares I-X is the test vehicle for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. The Ares I-X flight test is targeted for Oct. 31, pending formal NASA Headquarters approval. Photo credit: NASA/Jack Pfaller

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 development planning aiming at a first launch of ESC-B in 2006.

Modeling and Simulation of the ARES UPPER STAGE Transportation, Lifting, Stacking and Mating Operations Within the Vehicle Assembly Building at KSC

NASA Technical Reports Server (NTRS)

Kromis, Phillip A.

2010-01-01

This viewgraph presentation describes the modeling and simulation of the Ares Upper Stage Transportation, lifting, stacking, and mating operations within the Vehicle Assembly Building (VAB) at Kennedy Space Center (KSC). An aerial view of KSC Launch Shuttle Complex, two views of the Delmia process control layout, and an upper stage move subroutine and breakdown are shown. An overhead image of the VAB and the turning basin along with the Pegasus barge at the turning basin are also shown. This viewgraph presentation also shows the actual design and the removal of the mid-section spring tensioners, the removal of the AFT rear and forward tensioners tie downs, and removing the AFT hold down post and mount. US leaving the Pegasus Barge, the upper stage arriving at transfer aisle, upper stage receiving/inspection in transfer aisle, and an overhead view of upper stage receiving/inspection in transfer aisle are depicted. Five views of the actual connection of the cabling to the upper stage aft lifting hardware are shown. The upper stage transporter forward connector, two views of the rotation horizontal to vertical, the disconnection of the rear bolt ring cabling, the lowering of the upper stage to the inspection stand, disconnection of the rear bolt ring from the upper stage, the lifting of the upper stage and inspection of AFT fange, and the transfer of upper stage in an integrated stack are shown. Six views of the mating of the upper stage to the first stage are depicted. The preparation, inspection, and removal of the forward dome are shown. The upper stage mated on the integrated stack and crawler is also shown. This presentation concludes with A Rapid Upper Limb Assessment (RULA) utilizing male and female models for assessing risk factors to the upper extremities of human beings in an actual physical environment.

Experimental and theoretical study of iron and mild steel combustion in oxygen flows

NASA Astrophysics Data System (ADS)

El-Rabii, Hazem; Kazakov, Kirill A.; Muller, Maryse

2017-03-01

The effects of oxygen flow speed and pressure on the iron and mild steel combustion are investigated experimentally and theoretically. The studied specimens are vertical cylindrical rods subjected to an axial oxygen flow and ignited at the upper end by laser irradiation. Three main stages of the combustion process have been identified experimentally: (1) induction period, during which the rod is heated until an intensive metal oxidation begins at its upper end; (2) static combustion, during which a laminar liquid "cap'' slowly grows on the upper rod end, and, after the liquid cap detachment from the sample; (3) dynamic combustion, which is characterized by a rapid metal consumption and turbulent liquid motions. An analytical description of these stages is given. In particular, a model of the dynamic combustion is constructed based on the turbulent oxygen transport through the liquid metal-oxide flow. This model yields a simple expression for the fraction of metal burned in the process and allows one to calculate the normal propagation speed of the solid metal-liquid interface as a function of the oxygen flow speed and pressure. A comparison of the theory with the experimental results is made, and its potential application is mentioned.

GOES-S Countdown to T-Zero, Episode 3: Rocket Science

NASA Image and Video Library

2018-02-27

The United Launch Alliance Atlas V rocket reaches another major milestone on the road to T-Zero, as NOAA's GOES-S spacecraft prepares for launch. Stacking the rocket begins with the booster - the largest component - and continues with the addition of four solid rocket motors and the Centaur upper stage. GOES-S, the next in a series of advanced weather satellites, is slated to launch aboard the Atlas V from Cape Canaveral Air Force Station in Florida.

Ares I Crew Launch Vehicle Upper Stage Element Overview

NASA Technical Reports Server (NTRS)

McArthur, J. Craig

2008-01-01

This viewgraph presentation gives an overview of NASA's Ares I Crew Launch Vehicle Upper Stage Element. The topics include: 1) What is NASA s Mission?; 2) NASA s Exploration Roadmap What is our time line?; 3) Building on a Foundation of Proven Technologies Launch Vehicle Comparisons; 4) Ares I Upper Stage; 5) Upper Stage Primary Products; 6) Ares I Upper Stage Development Approach; 7) What progress have we made?; 8) Upper Stage Subsystem Highlights; 9) Structural Testing; 10) Common Bulkhead Processing; 11) Stage Installation at Stennis Space Center; 12) Boeing Producibility Team; 13) Upper Stage Low Cost Strategy; 14) Ares I and V Production at Michoud Assembly Facility (MAF); 15) Merged Manufacturing Flow; and 16) Manufacturing and Assembly Weld Tools.

Ares I-X: On the Threshold of Exploration

NASA Technical Reports Server (NTRS)

Davis, Stephan R.; Askins, Bruce

2009-01-01

Ares I-X, the first flight of the Ares I crew launch vehicle, is less than a year from launch. Ares I-X will test the flight characteristics of Ares I from liftoff to first stage separation and recovery. The flight also will demonstrate the computer hardware and software (avionics) needed to control the vehicle; deploy the parachutes that allow the first stage booster to land in the ocean safely; measure and control how much the rocket rolls during flight; test and measure the effects of first stage separation; and develop and try out new ground handling and rocket stacking procedures in the Vehicle Assembly Building (VAB) and first stage recovery procedures at Kennedy Space Center (KSC) in Florida. All Ares I-X major elements have completed their critical design reviews, and are nearing final fabrication. The first stage--four-segment solid rocket booster from the Space Shuttle inventory--incorporates new simulated forward structures to match the Ares I five-segment booster. The upper stage, Orion crew module, and launch abort system will comprise simulator hardware that incorporates developmental flight instrumentation for essential data collection during the mission. The upper stage simulator consists of smaller cylindrical segments, which were transported to KSC in fall 2008. The crew module and launch abort system simulator were shipped in December 2008. The first stage hardware, active roll control system (RoCS), and avionics components will be delivered to KSC in 2009. This paper will provide detailed statuses of the Ares I-X hardware elements as NASA's Constellation Program prepares for this first flight of a new exploration era in the summer of 2009.

Solid Waste Landfill Site Selection in the Sense of Environment Sensitive Sustainable Urbanization: Izmir, Turkey Case

NASA Astrophysics Data System (ADS)

TÜdeş, Şule; Kumlu, Kadriye Burcu Yavuz

2017-10-01

Each stage of the planning process should be based on the natural resource protection, in the sense of environmental sensitive and sustainable urban planning. Values, which are vital for the continuity of the life in the Earth, as soil, water, forest etc. should be protected from the undesired effects of the pollution and the other effects caused by the high urbanization levels. In this context, GIS-MCDM based solid waste landfill site selection is applied for Izmir, Turkey, where is a significant attraction place for tourism. As Multi criteria Decision Making (MCDM) technique, Analytical Hierarchy Process (AHP) is used. In this study, geological, tectonically and hydrological data, as well as agricultural land use, slope, distance to the settlement areas and the highways are used as inputs for AHP analysis. In the analysis stage, those inputs are rated and weighted. The weighted criteria are evaluated via GIS, by using weighted overlay tool. Therefore, an upper-scale analysis is conducted and a map, which shows the alternative places for the solid waste landfill sites, considering the environmental protection and evaluated in the context of environmental and urban criteria, are obtained.

Building and Leading the Next Generation of Exploration Launch Vehicles

NASA Technical Reports Server (NTRS)

Cook, Stephen A.; Vanhooser, Teresa

2010-01-01

NASA s Constellation Program is depending on the Ares Projects to deliver the crew and cargo launch capabilities needed to send human explorers to the Moon and beyond. Ares I and V will provide the core space launch capabilities needed to continue providing crew and cargo access to the International Space Station (ISS), and to build upon the U.S. history of human spaceflight to the Moon and beyond. Since 2005, Ares has made substantial progress on designing, developing, and testing the Ares I crew launch vehicle and has continued its in-depth studies of the Ares V cargo launch vehicle. In 2009, the Ares Projects plan to: conduct the first flight test of Ares I, test-fire the Ares I first stage solid rocket motor; build the first integrated Ares I upper stage; continue testing hardware for the J-2X upper stage engine, and continue refining the design of the Ares V cargo launch vehicle. These efforts come with serious challenges for the project leadership team as it continues to foster a culture of ownership and accountability, operate with limited funding, and works to maintain effective internal and external communications under intense external scrutiny.

Ares I First Stage Booster Deceleration System: An Overview

NASA Technical Reports Server (NTRS)

King, Ron; Hengel, John E.; Wolf, Dean

2009-01-01

In 2005, the Congressional NASA Authorization Act enacted a new space exploration program, the "Vision for Space Exploratien". The Constellation Program was formed to oversee the implementation of this new mission. With an intent not simply to support the International Space Station, but to build a permanent outpost on the Moon and then travel on to explore ever more distant terrains, the Constellation Program is supervising the development of a brand new fleet of launch vehicles, the Ares. The Ares lineup will include two new launch vehicles: the Ares I Crew Launch Vehicle and the Ares V Cargo Launch Vehicle. A crew exploration vehicle, Orion, will be launched on the Ares I. It will be capable of docking with the Space Station, the lunar lander, Altair, and the Earth Departure Stage of Ares V. The Ares V will be capable of lifting both large-scale hardware and the Altair into space. The Ares First Stage Team is tasked with developing the propulsion system necessary to liftoff from the Earth and loft the entire Ares vehicle stack toward low Earth orbit. The Ares I First Stage booster is a 12-foot diameter, five-segment, reusable solid rocket booster derived from the Space Shuttle's four segment reusable solid rocket booster (SRB). It is separated from the Upper Stage through the use of a Deceleration Subsystem (DSS). Booster Tumble Motors are used to induce the pitch tumble following separation from the Upper Stage. The spent Ares I booster must be recoverable using a parachute deceleration system similar to that of the Shuttle SRB heritage system. Since Ares I is much heavier and reenters the Earth's atmosphere from a higher altitude at a much higher velocity than the SRB, all of the parachutes must be redesigned to reliably meet the operational requisites of the new launch vehicles. This paper presents an overview of this new booster deceleration system. It includes comprehensive detail of the parachute deceleration system, its design and deployment sequences, including how and why it is being developed, the requirements it must meet, and the testing involved in its implementation.

Ares I Crew Launch Vehicle Upper Stage/Upper Stage Engine Element Overview

NASA Technical Reports Server (NTRS)

McArthur, J. Craig

2008-01-01

The Ares I upper stage is an integral part of the Constellation Program transportation system. The upper stage provides guidance, navigation and control (GN and C) for the second stage of ascent flight for the Ares I vehicle. The Saturn-derived J-2X upper stage engine will provide thrust and propulsive impulse for the second stage of ascent flight for the Ares I launch vehicle. Additionally, the upper stage is responsible for the avionics system of the the entire Ares I. This brief presentation highlights the requirements, design, progress and production of the upper stage. Additionally, test facilities to support J-2X development are discussed and an overview of the operational and manufacturing flows are provided. Building on the heritage of the Apollo and Space Shuttle Programs, the Ares I Us and USE teams are utilizing extensive lessons learned to place NASA and the US into another era of space exploration. The NASA, Boeing and PWR teams are integrated and working together to make progress designing and building the Ares I upper stage to minimize cost, technical and schedule risks.

The IRIS-GUS Shuttle Borne Upper Stage System

NASA Technical Reports Server (NTRS)

Tooley, Craig; Houghton, Martin; Bussolino, Luigi; Connors, Paul; Broudeur, Steve (Technical Monitor)

2002-01-01

This paper describes the Italian Research Interim Stage - Gyroscopic Upper Stage (IRIS-GUS) upper stage system that will be used to launch NASA's Triana Observatory from the Space Shuttle. Triana is a pathfinder earth science mission being executed on rapid schedule and small budget, therefore the mission's upper stage solution had to be a system that could be fielded quickly at relatively low cost and risk. The building of the IRIS-GUS system wa necessary because NASA lost the capability to launch moderately sized upper stage missions fro the Space Shuttle when the PAM-D system was retired. The IRIS-GUS system restores this capability. The resulting system is a hybrid which mates the existing, flight proven IRIS (Italian Research Interim Stage) airborne support equipment to a new upper stage, the Gyroscopic Upper Stage (GUS) built by the GSFC for Triana. Although a new system, the GUS exploits flight proven hardware and design approaches in most subsystems, in some cases implementing proven design approaches with state-of-the-art electronics. This paper describes the IRIS-GUS upper stage system elements, performance capabilities, and payload interfaces.

Mechanical design and simulation of two-wheeled wheelchair using solidworks

NASA Astrophysics Data System (ADS)

Altalmas, T. M.; Ahmad, S.; Aula, A.; Akmeliawati, R.; Sidek, S. N.

2013-12-01

This article is presented a new design of two-wheeled wheelchair that can balance on two wheels to make it suitable in the narrow areas, especially in the domestic environments; it has the ability to extend the height of the chair to help the user to act independently in the life for example, in the library to pick and put books on the shelves. The 3D model has been built up using SolidWorks Software. Nowadays, SolidWorks environment is considered as a powerful tool that is helping designer to design products and attain its performance before physical prototype stage. SolidWorks simulation model has been employed to test the frame of the wheelchair under the weight of the human body and the upper part of the wheelchair. The static analysis has been done on the frame using steel and aluminium; however the aluminium material has been selected due to its light weight

Solid motor diagnostic instrumentation. [design of self-contained instrumentation

NASA Technical Reports Server (NTRS)

Nakamura, Y.; Arens, W. E.; Wuest, W. S.

1973-01-01

A review of typical surveillance and monitoring practices followed during the flight phases of representative solid-propellant upper stages and apogee motors was conducted to evaluate the need for improved flight diagnostic instrumentation on future spacecraft. The capabilities of the flight instrumentation package were limited to the detection of whether or not the solid motor was the cause of failure and to the identification of probable primary failure modes. Conceptual designs of self-contained flight instrumentation packages capable of meeting these reqirements were generated and their performance, typical cost, and unit characteristics determined. Comparisons of a continuous real time and a thresholded hybrid design were made on the basis of performance, mass, power, cost, and expected life. The results of this analysis substantiated the feasibility of a self-contained independent flight instrumentation module as well as the existence of performance margins by which to exploit growth option applications.

Solid propulsion advanced concepts

NASA Technical Reports Server (NTRS)

Nakamura, Y.; Shafer, J. I.

1972-01-01

The feasibility and application of a solid propulsion powered spacecraft concept to implement high energy missions independent of multiplanetary swingby opportunities are assessed and recommendations offered for future work. An upper stage, solid propulsion launch vehicle augmentation system was selected as the baseline configuration in view of the established program goals of low cost and high reliability. Spacecraft and propulsion system data that characterize mission performance capabilities were generated to serve as the basis for subsequent tradeoff studies. A cost effectiveness model was used for the preliminary feasibility assessment to provide a meaningful comparative effectiveness measure of the various candidate designs. The results substantiated the feasibility of the powered spacecraft concept when used in conjunction with several intermediate-sized launch vehicles as well as the existence of energy margins by which to exploit the attainment of extended mission capabilities. Additionally, in growth option applications, the employment of advanced propulsion systems and alternate spacecraft approaches appear promising.

Firing test of propellant-cracked solid motor under X-ray TV

NASA Astrophysics Data System (ADS)

Fujiwara, Tsutomu; Tanemura, Toshiharu; Itoh, Katsuya; Kakuta, Yoshiaki; Shimizu, Morio; Takahashi, Michio

This paper presents the effects of a big crack on the combustion behaviors of the scaled-down Japanese H-I upper stage motors of the National Space Development Agency (NASDA). The big crack was generated by cooling down the propellant grain below -100 C; the crack was identified and measured with the X-ray computer tomography (CT) system designed for medical use. It was found that the crack spread widely from inner bore to liner and fore-and-aft of the motor. The firing test of the propellant-cracked solid motor was performed under X-ray TV observation, and the motor exploded just after the ignition because of the abrupt chamber pressure increase due to flame propagation into the crack.

Robotic planetary science missions enabled with small NTR engine/stage technologies

NASA Astrophysics Data System (ADS)

Borowski, Stanley K.

1995-10-01

The high specific impulse (Isp) and engine thrust-to-weight ratio of liquid hydrogen (LH2)-cooled nuclear thermal rocket (NTR) engines makes them ideal for upper stage applications to difficult robotic planetary science missions. A small 15 thousand pound force (klbf) NTR engine using a uranium-zirconium-niobium 'ternary carbide' fuel (Isp approximately 960 seconds at approximately 3025K) developed in the Commonwealth of Independent States (CIS) is examined and its use on an expendable injection stage is shown to provide major increases in payload delivered to the outer planets (Saturn, Uranus, Neptune and Pluto). Using a single 'Titan IV-class' launch vehicle, with a lift capability to low Earth orbit (LEO) of approximately 20 metric tons (t), an expendable NTR upper stage can inject two Pluto 'Fast Flyby' spacecraft (PFF/SC) plus support equipment-combined mass of approximately 508 kg--on high energy, '6.5-9.2 year' direct trajectory missions to Pluto. A conventional chemical propulsion mission would use a liquid oxygen (LOX)/LH2 'Centaur' upper stage and two solid rocket 'kick motors' to inject a single PFF/SC on the same Titan IV launch vehicle. For follow on Pluto missions, the NTR injection stage would utilize a Jupiter 'gravity assist' (JGA) maneuver to launch a LOX/liquid methane (CH4) capture stage (Isp approximately 375 seconds) and a Pluto 'orbiter' spacecraft weighing between approximately 167-312 kg. With chemical propulsion, a Pluto orbiter mission is not a viable option because c inadequate delivered mass. Using a 'standardized' NTR injection stage and the same single Titan IV launch scenario, 'direct flight' (no gravity assist) orbiter missions to Saturn, Uranus and Neptune are also enabled with transit times of 2.3, 6.6, and 12.6 years, respectively. Injected mass includes a storable, nitrogen tetroxide/monomethyl hydrazine (N2O4/MMH) capture stage (Isp approximately 330 seconds) and orbiter payloads 340 to 820% larger than that achievable using a LOX/LH2-fueled injection stage. The paper discusses NTR technology and mission characteristics, shows NTR stage and payload accommodations within the 26.2 m long Titan IV payload fairing, and discusses NTR stage performance as a function of assumed cryogenic tank technology.

Robotic Planetary Science Missions Enabled with Small NTR Engine/Stage Technologies

NASA Technical Reports Server (NTRS)

Borowski, Stanley K.

1995-01-01

The high specific impulse (Isp) and engine thrust-to-weight ratio of liquid hydrogen (LH2)-cooled nuclear thermal rocket (NTR) engines makes them ideal for upper stage applications to difficult robotic planetary science missions. A small 15 thousand pound force (klbf) NTR engine using a uranium-zirconium-niobium 'ternary carbide' fuel (Isp approximately 960 seconds at approximately 3025K) developed in the Commonwealth of Independent States (CIS) is examined and its use on an expendable injection stage is shown to provide major increases in payload delivered to the outer planets (Saturn, Uranus, Neptune and Pluto). Using a single 'Titan IV-class' launch vehicle, with a lift capability to low Earth orbit (LEO) of approximately 20 metric tons (t), an expendable NTR upper stage can inject two Pluto 'Fast Flyby' spacecraft (PFF/SC) plus support equipment-combined mass of approximately 508 kg--on high energy, '6.5-9.2 year' direct trajectory missions to Pluto. A conventional chemical propulsion mission would use a liquid oxygen (LOX)/LH2 'Centaur' upper stage and two solid rocket 'kick motors' to inject a single PFF/SC on the same Titan IV launch vehicle. For follow on Pluto missions, the NTR injection stage would utilize a Jupiter 'gravity assist' (JGA) maneuver to launch a LOX/liquid methane (CH4) capture stage (Isp approximately 375 seconds) and a Pluto 'orbiter' spacecraft weighing between approximately 167-312 kg. With chemical propulsion, a Pluto orbiter mission is not a viable option because c inadequate delivered mass. Using a 'standardized' NTR injection stage and the same single Titan IV launch scenario, 'direct flight' (no gravity assist) orbiter missions to Saturn, Uranus and Neptune are also enabled with transit times of 2.3, 6.6, and 12.6 years, respectively. Injected mass includes a storable, nitrogen tetroxide/monomethyl hydrazine (N2O4/MMH) capture stage (Isp approximately 330 seconds) and orbiter payloads 340 to 820% larger than that achievable using a LOX/LH2-fueled injection stage. The paper discusses NTR technology and mission characteristics, shows NTR stage and payload accommodations within the 26.2 m long Titan IV payload fairing, and discusses NTR stage performance as a function of assumed cryogenic tank technology.

Status of NASA's Space Launch System

NASA Technical Reports Server (NTRS)

Honeycutt, John; Lyles, Garry

2016-01-01

NASA's Space Launch System (SLS) continued to make significant progress in 2015 and 2016, completing hardware and testing that brings NASA closer to a new era of deep space exploration. Programmatically, SLS completed Critical Design Review (CDR) in 2015. A team of independent reviewers concluded that the vehicle design is technically and programmatically ready to move to Design Certification Review (DCR) and launch readiness in 2018. Just five years after program start, every major element has amassed development and flight hardware and completed key tests that will lead to an accelerated pace of manufacturing and testing in 2016 and 2017. Key to SLS' rapid progress has been the use of existing technologies adapted to the new launch vehicle. The existing fleet of RS-25 engines is undergoing adaptation tests to prove it can meet SLS requirements and environments with minimal change. The four-segment shuttle-era booster has been modified and updated with a fifth propellant segment, new insulation, and new avionics. The Interim Cryogenic Upper Stage is a modified version of an existing upper stage. The first Block I SLS configuration will launch a minimum of 70 metric tons (t) of payload to low Earth orbit (LEO). The vehicle architecture has a clear evolutionary path to more than 100t and, ultimately, to 130t. Among the program's major 2015-2016 accomplishments were two booster qualification hotfire tests, a series of RS-25 adaptation hotfire tests, manufacturing of most of the major components for both core stage test articles and first flight tank, delivery of the Pegasus core stage barge, and the upper stage simulator. Renovations to the B-2 test stand for stage green run testing was completed at NASA Stennis Space Center. This year will see the completion of welding for all qualification and flight EM-1 core stage components and testing of flight avionics, completion of core stage structural test stands, casting of the EM-1 solid rocket motors, additional testing of RS-25 engines and flight engine controllers This paper will discuss these and other technical and programmatic successes and challenges over the past year and provide a preview of work ahead before the first flight of this new capability.

Advanced Space Transportation Program (ASTP)

NASA Image and Video Library

2006-09-09

Named for the Greek god associated with Mars, the NASA developed Ares launch vehicles will return humans to the moon and later take them to Mars and other destinations. In this early illustration, the vehicle depicted on the left is the Ares I. Ares I is an inline, two-stage rocket configuration topped by the Orion crew vehicle and its launch abort system. In addition to its primary mission of carrying four to six member crews to Earth orbit, Ares I may also use its 25-ton payload capacity to deliver resources and supplies to the International Space Station (ISS), or to "park" payloads in orbit for retrieval by other spacecraft bound for the moon or other destinations. The Ares I employs a single five-segment solid rocket booster, a derivative of the space shuttle solid rocket booster, for the first stage. A liquid oxygen/liquid hydrogen J-2X engine derived from the J-2 engine used on the second stage of the Apollo vehicle will power the Ares V second stage. The Ares I can lift more than 55,000 pounds to low Earth orbit. The vehicle illustrated on the right is the Ares V, a heavy lift launch vehicle that will use five RS-68 liquid oxygen/liquid hydrogen engines mounted below a larger version of the space shuttle external tank, and two five-segment solid propellant rocket boosters for the first stage. The upper stage will use the same J-2X engine as the Ares I. The Ares V can lift more than 286,000 pounds to low Earth orbit and stands approximately 360 feet tall. This versatile system will be used to carry cargo and the components into orbit needed to go to the moon and later to Mars. Both vehicles are subject to configuration changes before they are actually launched. This illustration reflects the latest configuration as of September 2006.

Illustration of Ares I and Ares V Launch Vehicles

NASA Technical Reports Server (NTRS)

2006-01-01

Named for the Greek god associated with Mars, the NASA developed Ares launch vehicles will return humans to the moon and later take them to Mars and other destinations. In this early illustration, the vehicle depicted on the left is the Ares I. Ares I is an inline, two-stage rocket configuration topped by the Orion crew vehicle and its launch abort system. In addition to its primary mission of carrying four to six member crews to Earth orbit, Ares I may also use its 25-ton payload capacity to deliver resources and supplies to the International Space Station (ISS), or to 'park' payloads in orbit for retrieval by other spacecraft bound for the moon or other destinations. The Ares I employs a single five-segment solid rocket booster, a derivative of the space shuttle solid rocket booster, for the first stage. A liquid oxygen/liquid hydrogen J-2X engine derived from the J-2 engine used on the second stage of the Apollo vehicle will power the Ares V second stage. The Ares I can lift more than 55,000 pounds to low Earth orbit. The vehicle illustrated on the right is the Ares V, a heavy lift launch vehicle that will use five RS-68 liquid oxygen/liquid hydrogen engines mounted below a larger version of the space shuttle external tank, and two five-segment solid propellant rocket boosters for the first stage. The upper stage will use the same J-2X engine as the Ares I. The Ares V can lift more than 286,000 pounds to low Earth orbit and stands approximately 360 feet tall. This versatile system will be used to carry cargo and the components into orbit needed to go to the moon and later to Mars. Both vehicles are subject to configuration changes before they are actually launched. This illustration reflects the latest configuration as of September 2006.

StarBooster Demonstrator Cluster Configuration Analysis/Verification Program

NASA Technical Reports Server (NTRS)

DeTurris, Dianne J.

2003-01-01

In order to study the flight dynamics of the cluster configuration of two first stage boosters and upper-stage, flight-testing of subsonic sub-scale models has been undertaken using two glideback boosters launched on a center upper-stage. Three high power rockets clustered together were built and flown to demonstrate vertical launch, separation and horizontal recovery of the boosters. Although the boosters fly to conventional aircraft landing, the centerstage comes down separately under its own parachute. The goal of the project has been to collect data during separation and flight for comparison with a six degree of freedom simulation. The configuration for the delta wing canard boosters comes from a design by Starcraft Boosters, Inc. The subscale rockets were constructed of foam covered in carbon or fiberglass and were launched with commercially available solid rocket motors. The first set of boosters built were 3-ft tall with a 4-ft tall centerstage, and two additional sets of boosters were made that were each over 5-ft tall with a 7.5 ft centerstage. The rocket cluster is launched vertically, then after motor bum out the boosters are separated and flown to a horizontal landing under radio-control. An on-board data acquisition system recorded data during both the launch and glide phases of flight.

Ares I-X First Stage Separation Loads and Dynamics Reconstruction

NASA Technical Reports Server (NTRS)

Demory, Lee; Rooker, BIll; Jarmulowicz, Marc; Glaese, John

2011-01-01

The Ares I-X flight test provided NASA with the opportunity to test hardware and gather critical data to ensure the success of future Ares I flights. One of the primary test flight objectives was to evaluate the environment during First Stage separation to better understand the conditions that the J-2X second stage engine will experience at ignition [1]. A secondary objective was to evaluate the effectiveness of the stage separation motors. The Ares I-X flight test vehicle was successfully launched on October 29, 2009, achieving most of its primary and secondary test objectives. Ground based video camera recordings of the separation event appeared to show recontact of the First Stage and the Upper Stage Simulator followed by an unconventional tumbling of the Upper Stage Simulator. Closer inspection of the videos and flight test data showed that recontact did not occur. Also, the motion during staging was as predicted through CFD analysis performed during the Ares I-X development. This paper describes the efforts to reconstruct the vehicle dynamics and loads through the staging event by means of a time integrated simulation developed in TREETOPS, a multi-body dynamics software tool developed at NASA [2]. The simulation was built around vehicle mass and geometry properties at the time of staging and thrust profiles for the first stage solid rocket motor as well as for the booster deceleration motors and booster tumble motors. Aerodynamic forces were determined by models created from a combination of wind tunnel testing and CFD. The initial conditions such as position, velocity, and attitude were obtained from the Best Estimated Trajectory (BET), which is compiled from multiple ground based and vehicle mounted instruments. Dynamic loads were calculated by subtracting the inertial forces from the applied forces. The simulation results were compared to the Best Estimated Trajectory, accelerometer flight data, and to ground based video.

Thrust vector control of upper stage with a gimbaled thruster during orbit transfer

NASA Astrophysics Data System (ADS)

Wang, Zhaohui; Jia, Yinghong; Jin, Lei; Duan, Jiajia

2016-10-01

In launching Multi-Satellite with One-Vehicle, the main thruster provided by the upper stage is mounted on a two-axis gimbal. During orbit transfer, the thrust vector of this gimbaled thruster (GT) should theoretically pass through the mass center of the upper stage and align with the command direction to provide orbit transfer impetus. However, it is hard to be implemented from the viewpoint of the engineering mission. The deviations of the thrust vector from the command direction would result in large velocity errors. Moreover, the deviations of the thrust vector from the upper stage mass center would produce large disturbance torques. This paper discusses the thrust vector control (TVC) of the upper stage during its orbit transfer. Firstly, the accurate nonlinear coupled kinematic and dynamic equations of the upper stage body, the two-axis gimbal and the GT are derived by taking the upper stage as a multi-body system. Then, a thrust vector control system consisting of the special attitude control of the upper stage and the gimbal rotation of the gimbaled thruster is proposed. The special attitude control defined by the desired attitude that draws the thrust vector to align with the command direction when the gimbal control makes the thrust vector passes through the upper stage mass center. Finally, the validity of the proposed method is verified through numerical simulations.

Launch Vehicles

NASA Image and Video Library

2007-09-09

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. The launch vehicle's first stage is a single, five-segment reusable solid rocket booster derived from the Space Shuttle Program's reusable solid rocket motor that burns a specially formulated and shaped solid propellant called polybutadiene acrylonitrile (PBAN). The second or upper stage will be propelled by a J-2X main engine fueled with liquid oxygen and liquid hydrogen. This HD video image depicts a test firing of a 40k subscale J2X injector at MSFC's test stand 115. (Highest resolution available)

A queuing-theory-based interval-fuzzy robust two-stage programming model for environmental management under uncertainty

NASA Astrophysics Data System (ADS)

Sun, Y.; Li, Y. P.; Huang, G. H.

2012-06-01

In this study, a queuing-theory-based interval-fuzzy robust two-stage programming (QB-IRTP) model is developed through introducing queuing theory into an interval-fuzzy robust two-stage (IRTP) optimization framework. The developed QB-IRTP model can not only address highly uncertain information for the lower and upper bounds of interval parameters but also be used for analysing a variety of policy scenarios that are associated with different levels of economic penalties when the promised targets are violated. Moreover, it can reflect uncertainties in queuing theory problems. The developed method has been applied to a case of long-term municipal solid waste (MSW) management planning. Interval solutions associated with different waste-generation rates, different waiting costs and different arriving rates have been obtained. They can be used for generating decision alternatives and thus help managers to identify desired MSW management policies under various economic objectives and system reliability constraints.

KSC-08pd1859

NASA Image and Video Library

2008-07-01

CAPE CANAVERAL, Fla. – In the Assembly and Refurbishment Facility at NASA's Kennedy Space Center, a crane is lowered over the aft skirt for the Ares 1-X rocket. The segment is being lifted into a machine shop work stand for drilling modifications. The modifications will prepare it for the installation of the auxiliary power unit controller, the reduced-rate gyro unit, the booster decelerator motors and the booster tumble motors. Ares I is an in-line, two-stage rocket that will transport the Orion crew exploration vehicle to low-Earth orbit. Ares I-X is a test rocket. The Ares I first stage will be a five-segment solid rocket booster based on the four-segment design used for the shuttle. Ares I’s fifth booster segment allows the launch vehicle to lift more weight and reach a higher altitude before the first stage separates from the upper stage, which ignites in midflight to propel the Orion spacecraft to Earth orbit. Photo credit: NASA/Jim Grossmann

Environmental protection requirements for scout/shuttle auxiliary stages

NASA Technical Reports Server (NTRS)

Qualls, G. L.; Kress, S. S.; Storey, W. W.; Ransdell, P. N.

1980-01-01

The requirements for enabling the Scout upper stages to endure the expected temperature, mechanical shock, acoustical and mechanical vibration environments during a specified shuttle mission were determined. The study consisted of: determining a shuttle mission trajectory for a 545 kilogram (1200 pound) Scout payload; compilation of shuttle environmental conditions; determining of Scout upper stages environments in shuttle missions; compilation of Scout upper stages environmental qualification criteria and comparison to shuttle mission expected environments; and recommendations for enabling Scout upper stages to endure the exptected shuttle mission environments.

Advanced Launch Vehicle Upper Stages Using Liquid Propulsion and Metallized Propellants

NASA Technical Reports Server (NTRS)

Palaszewski, Bryan A.

1990-01-01

Metallized propellants are liquid propellants with a metal additive suspended in a gelled fuel or oxidizer. Typically, aluminum (Al) particles are the metal additive. These propellants provide increase in the density and/or the specific impulse of the propulsion system. Using metallized propellant for volume-and mass-constrained upper stages can deliver modest increases in performance for low earth orbit to geosynchronous earth orbit (LEO-GEO) and other earth orbital transfer missions. Metallized propellants, however, can enable very fast planetary missions with a single-stage upper stage system. Trade studies comparing metallized propellant stage performance with non-metallized upper stages and the Inertial Upper Stage (IUS) are presented. These upper stages are both one- and two-stage vehicles that provide the added energy to send payloads to altitudes and onto trajectories that are unattainable with only the launch vehicle. The stage designs are controlled by the volume and the mass constraints of the Space Transportation System (STS) and Space Transportation System-Cargo (STS-C) launch vehicles. The influences of the density and specific impulse increases enabled by metallized propellants are examined for a variety of different stage and propellant combinations.

Seal Analysis for the Ares-I Upper Stage Fuel Tank Manhole Cover

NASA Technical Reports Server (NTRS)

Phillips, Dawn R.; Wingate, Robert J.

2010-01-01

Techniques for studying the performance of Naflex pressure-assisted seals in the Ares-I Upper Stage liquid hydrogen tank manhole cover seal joint are explored. To assess the feasibility of using the identical seal design for the Upper Stage as was used for the Space Shuttle External Tank manhole covers, a preliminary seal deflection analysis using the ABAQUS commercial finite element software is employed. The ABAQUS analyses are performed using three-dimensional symmetric wedge finite element models. This analysis technique is validated by first modeling a heritage External Tank liquid hydrogen tank manhole cover joint and correlating the results to heritage test data. Once the technique is validated, the Upper Stage configuration is modeled. The Upper Stage analyses are performed at 1.4 times the expected pressure to comply with the Constellation Program factor of safety requirement on joint separation. Results from the analyses performed with the External Tank and Upper Stage models demonstrate the effects of several modeling assumptions on the seal deflection. The analyses for Upper Stage show that the integrity of the seal is successfully maintained.

APN401 in Treating Patients With Recurrent or Metastatic Pancreatic Cancer, Colorectal Cancer, or Other Solid Tumors That Cannot Be Removed by Surgery

ClinicalTrials.gov

2018-03-29

Metastatic Malignant Neoplasm in the Brain; Metastatic Solid Neoplasm; Recurrent Colorectal Carcinoma; Recurrent Pancreatic Carcinoma; Recurrent Solid Neoplasm; Stage IV Colorectal Cancer; Stage IV Pancreatic Cancer; Stage IVA Colorectal Cancer; Stage IVA Pancreatic Cancer; Stage IVB Colorectal Cancer; Stage IVB Pancreatic Cancer; Unresectable Solid Neoplasm

Development Status of the J-2X

NASA Technical Reports Server (NTRS)

Kynard, Mike; Vilja, John

2008-01-01

In June 2006, the NASA Marshall Space Flight Center (MSFC) and Pratt & Whitney Rocketdyne began development of an engine for use on the Ares I crew launch vehicle and the Ares V cargo launch vehicle. The development program will be completed in December 2012 at the end of a Design Certification Review and after certification testing of two flight configuration engines. A team of over 600 people within NASA and Pratt & Whitney Rocketdyne are currently working to prepare for the fall 2008 Critical Design Review (CDR), along with supporting an extensive risk mitigation test program. The J-2X will power the Ares I upper stage and the Ares V earth departure stage (EDS). The initial use will be in the Ares I, used to launch the Orion crew exploration vehicle. In this application, it will power the upper stage after being sent aloft on a Space Shuttle-derived. 5-segment solid rocket booster first stage. In this mission. the engine will ignite at altitude and provide the necessary acceleration force to allow the Orion to achieve orbital velocity. The Ares I upper stage, along with the J-2X. will then be expended. On the Ares V. first stage propulsion is provided by five RS-68B engines and two 5-segment boosters similar to the Ares I configuration. In the Ares V mission. the J-2X is first started to power the EDS and its payload. the Altair lunar lander. into earth orbit, then shut-down and get prepared for its next start. The EDS/Altair will remain in a parking orbit, awaiting rendezvous and docking with Orion. Once the two spacecraft are mated, the J-2X will be restarted to achieve earth departure velocity. After powering the Orion and Altair, the EDS will be expended. By using the J-2X Engine in both applications, a significant infrastructure cost savings is realized. Only one engine development is required, and the sustaining engineering and flight support infrastructures can be combined. There is also flexibility for changing, the production and flight manifest because a single production line can support both missions with minimal differences between each engine configuration kit.

NASA Ares I Crew Launch Vehicle Upper Stage Avionics and Software Overview

NASA Technical Reports Server (NTRS)

Nola, Charles L.; Blue, Lisa

2008-01-01

Building on the heritage of the Saturn and Space Shuttle Programs for the Design, Development, Test, and Evaluation (DDT and E) of avionics and software for NASA's Ares I Crew Launch Vehicle (CLV), the Ares I Upper Stage Element is a vital part of the Constellation Program's transportation system. The Upper Stage Element's Avionics Subsystem is actively proceeding toward its objective of delivering a flight-certified Upper Stage Avionics System for the Ares I CLV.

KSC-08pd0848

NASA Image and Video Library

2008-03-27

CAPE CANAVERAL, Fla. --- Under a waning moon (upper right) at Cape Canaveral Air Force Station, the Delta II rocket to launch NASA's Gamma-ray Large Area Space Telescope, or GLAST, spacecraft is poised to receive the first of the solid rocket boosters. A series of nine strap-on solid rocket motors will help power the first stage. The GLAST is a powerful space observatory that will explore the Universe's ultimate frontier, where nature harnesses forces and energies far beyond anything possible on Earth; probe some of science's deepest questions, such as what our Universe is made of, and search for new laws of physics; explain how black holes accelerate jets of material to nearly light speed; and help crack the mystery of stupendously powerful explosions known as gamma-ray bursts. Launch is currently planned for May 16 from Pad 17-B. Photo credit: NASA/Dimitri Gerondidakis

Updated estimates of long-term average dissolved-solids loading in streams and rivers of the Upper Colorado River Basin

USGS Publications Warehouse

Tillman, Fred D.; Anning, David W.

2014-01-01

The Colorado River and its tributaries supply water to more than 35 million people in the United States and 3 million people in Mexico, irrigating over 4.5 million acres of farmland, and annually generating about 12 billion kilowatt hours of hydroelectric power. The Upper Colorado River Basin, part of the Colorado River Basin, encompasses more than 110,000 mi2 and is the source of much of more than 9 million tons of dissolved solids that annually flows past the Hoover Dam. High dissolved-solids concentrations in the river are the cause of substantial economic damages to users, primarily in reduced agricultural crop yields and corrosion, with damages estimated to be greater than 300 million dollars annually. In 1974, the Colorado River Basin Salinity Control Act created the Colorado River Basin Salinity Control Program to investigate and implement a broad range of salinity control measures. A 2009 study by the U.S. Geological Survey, supported by the Salinity Control Program, used the Spatially Referenced Regressions on Watershed Attributes surface-water quality model to examine dissolved-solids supply and transport within the Upper Colorado River Basin. Dissolved-solids loads developed for 218 monitoring sites were used to calibrate the 2009 Upper Colorado River Basin Spatially Referenced Regressions on Watershed Attributes dissolved-solids model. This study updates and develops new dissolved-solids loading estimates for 323 Upper Colorado River Basin monitoring sites using streamflow and dissolved-solids concentration data through 2012, to support a planned Spatially Referenced Regressions on Watershed Attributes modeling effort that will investigate the contributions to dissolved-solids loads from irrigation and rangeland practices.

Integrated Testing Approaches for the NASA Ares I Crew Launch Vehicle

NASA Technical Reports Server (NTRS)

Taylor, James L.; Cockrell, Charles E.; Tuma, Margaret L.; Askins, Bruce R.; Bland, Jeff D.; Davis, Stephan R.; Patterson, Alan F.; Taylor, Terry L.; Robinson, Kimberly L.

2008-01-01

The Ares I crew launch vehicle is being developed by the U.S. National Aeronautics and Space Administration (NASA) to provide crew and cargo access to the International Space Station (ISS) and, together with the Ares V cargo launch vehicle, serves as a critical component of NASA's future human exploration of the Moon. During the preliminary design phase, NASA defined and began implementing plans for integrated ground and flight testing necessary to achieve the first human launch of Ares I. The individual Ares I flight hardware elements - including the first stage five segment booster (FSB), upper stage, and J-2X upper stage engine - will undergo extensive development, qualification, and certification testing prior to flight. Key integrated system tests include the upper stage Main Propulsion Test Article (MPTA), acceptance tests of the integrated upper stage and upper stage engine assembly, a full-scale integrated vehicle ground vibration test (IVGVT), aerodynamic testing to characterize vehicle performance, and integrated testing of the avionics and software components. The Ares I-X development flight test will provide flight data to validate engineering models for aerodynamic performance, stage separation, structural dynamic performance, and control system functionality. The Ares I-Y flight test will validate ascent performance of the first stage, stage separation functionality, validate the ability of the upper stage to manage cryogenic propellants to achieve upper stage engine start conditions, and a high-altitude demonstration of the launch abort system (LAS) following stage separation. The Orion 1 flight test will be conducted as a full, un-crewed, operational flight test through the entire ascent flight profile prior to the first crewed launch.

Evaluation of light penetration on Navigation Pools 8 and 13 of the Upper Mississippi River

USGS Publications Warehouse

Giblin, Shawn; Hoff, Kraig; Fischer, Jim; Dukerschein, Terry

2010-01-01

The availability of light can have a dramatic affect on macrophyte and phytoplankton abundance in virtually all aquatic ecosystems. The Long Term Resource Monitoring Program and other monitoring programs often measure factors that affect light extinction (nonvolatile suspended solids, volatile suspended solids, and chlorophyll) and correlates of light extinction (turbidity and Secchi depth), but rarely do they directly measure light extinction. Data on light extinction, Secchi depth, transparency tube, turbidity, total suspended solids, and volatile suspended solids were collected during summer 2003 on Pools 8 and 13 of the Upper Mississippi River. Regressions were developed to predict light extinction based upon Secchi depth, transparency tube, turbidity, and total suspended solids. Transparency tube, Secchi depth, and turbidity all showed strong relations with light extinction and can effectively predict light extinction. Total suspended solids did not show as strong a relation to light extinction. Volatile suspended solids had a greater affect on light extinction than nonvolatile suspended solids. The data were compared to recommended criteria established for light extinction, Secchi depth, total suspended solids, and turbidity by the Upper Mississippi River Conservation Committee to sustain submersed aquatic vegetation in the Upper Mississippi River. During the study period, the average condition in Pool 8 met or exceeded all of the criteria whereas the average condition in Pool 13 failed to meet any of the criteria. This report provides river managers with an effective tool to predict light extinction based upon readily available data.

Trametinib and Navitoclax in Treating Patients With Advanced or Metastatic Solid Tumors

ClinicalTrials.gov

2018-06-08

Advanced Malignant Solid Neoplasm; KRAS Gene Mutation; Metastatic Malignant Solid Neoplasm; NRAS Gene Mutation; Recurrent Colorectal Carcinoma; Recurrent Lung Carcinoma; Recurrent Malignant Solid Neoplasm; Recurrent Pancreatic Carcinoma; Stage III Colorectal Cancer AJCC v7; Stage III Lung Cancer AJCC v7; Stage III Pancreatic Cancer AJCC v6 and v7; Stage IIIA Colorectal Cancer AJCC v7; Stage IIIB Colorectal Cancer AJCC v7; Stage IIIC Colorectal Cancer AJCC v7; Stage IV Colorectal Cancer AJCC v7; Stage IV Lung Cancer AJCC v7; Stage IV Pancreatic Cancer AJCC v6 and v7; Stage IVA Colorectal Cancer AJCC v7; Stage IVB Colorectal Cancer AJCC v7; Unresectable Malignant Neoplasm

Analysis of pressure blips in aft-finocyl solid rocket motor

NASA Astrophysics Data System (ADS)

Di Giacinto, M.; Favini, B.; Cavallini, E.

2016-07-01

Ballistic anomalies have frequently occurred during the firing of several solid rocket motors (SRMs) (Inertial Upper Stage, Space Shuttle Redesigned SRM (RSRM) and Titan IV SRM Upgrade (SRMU)), producing even relevant and unexpected variations of the SRM pressure trace from its nominal profile. This paper has the purpose to provide a numerical analysis of the following possible causes of ballistic anomalies in SRMs: an inert object discharge, a slag ejection, and an unexpected increase in the propellant burning rate or in the combustion surface. The SRM configuration under investigation is an aft-finocyl SRM with a first-stage/small booster design. The numerical simulations are performed with a quasi-one-dimensional (Q1D) unsteady model of the SRM internal ballistics, properly tailored to model each possible cause of the ballistic anomalies. The results have shown that a classification based on the head-end pressure (HEP) signature, relating each other the HEP shape and the ballistic anomaly cause, can be made. For each cause of ballistic anomalies, a deepened discussion of the parameters driving the HEP signatures is provided, as well as qualitative and quantitative assessments of the resultant pressure signals.

KSC-97PC1542

NASA Image and Video Library

1997-10-14

At Launch Complex 40 on Cape Canaveral Air Station, the Mobile Service Tower has been retracted away from the Titan IVB/Centaur carrying the Cassini spacecraft and its attached Huygens probe. This is the second launch attempt for the Saturn-bound mission; a first try Oct. 13 was scrubbed primarily due to concerns about upper level wind conditions. Liftoff Oct. 15 is set to occur during a launch window opening at 4:43 a.m. EDT and extending until 7:03 a.m. Clearly visible in this view are the 66-foot-tall, 17-foot-wide payload fairing atop the vehicle, in which Cassini and the attached Centaur stage are encased, the two-stage liquid propellant core vehicle, and the twin 112-foot long solid rocket motor upgrades (SRMUs) straddling the core vehicle. It is the SRMUs which ignite first to begin the launch sequence

KSC-97PC1760

NASA Image and Video Library

1997-12-09

NASA's Lunar Prospector is taken out of its crate at Astrotech, a commercial payload processing facility, in Titusville, Fla. The small robotic spacecraft, to be launched for NASA on an Athena 2 rocket by Lockheed Martin, is designed to provide the first global maps of the Moon's surface compositional elements and its gravitational and magnetic fields. While at Astrotech, Lunar Prospector will be fueled with its attitude control propellant and then mated to a Trans-Lunar Injection Stage which is a solid propellant upper stage motor. The combination will next be spin tested to verify proper balance, then encapsulated into an Athena nose fairing. Then the Lunar Prospector will be transported from Astrotech to Cape Canaveral Air Station and mated to an Athena rocket. The launch of Lunar Prospector is scheduled for Jan. 5, 1998 at 8:31 p.m

KSC-97PC1759

NASA Image and Video Library

1997-12-09

NASA's Lunar Prospector is taken out of its crate at Astrotech, a commercial payload processing facility, in Titusville, Fla. The small robotic spacecraft, to be launched for NASA on an Athena 2 rocket by Lockheed Martin, is designed to provide the first global maps of the Moon's surface compositional elements and its gravitational and magnetic fields. While at Astrotech, Lunar Prospector will be fueled with its attitude control propellant and then mated to a Trans-Lunar Injection Stage which is a solid propellant upper stage motor. The combination will next be spin tested to verify proper balance, then encapsulated into an Athena nose fairing. Then the Lunar Prospector will be transported from Astrotech to Cape Canaveral Air Station and mated to an Athena rocket. The launch of Lunar Prospector is scheduled for Jan. 5, 1998 at 8:31 p.m

Aerial View: SLS Intertank Arrives at Marshall for Critical Structural Testing

NASA Image and Video Library

2018-03-08

A structural test version of the intertank for NASA's new deep-space rocket, the Space Launch System, arrives at NASA’s Marshall Space Flight Center in Huntsville, Alabama, March 4, aboard the barge Pegasus. The intertank is the second piece of structural hardware for the massive SLS core stage built at NASA's Michoud Assembly Facility in New Orleans delivered to Marshall for testing. The structural test article will undergo critical testing as engineers push, pull and bend the hardware with millions of pounds of force to ensure it can withstand the forces of launch and ascent. The test hardware is structurally identical to the flight version of the intertank that will connect the core stage's two colossal propellant tanks, serve as the upper-connection point for the two solid rocket boosters and house critical avionics and electronics. Pegasus, originally used during the Space Shuttle Program, has been redesigned and extended to accommodate the SLS rocket's massive, 212-foot-long core stage -- the backbone of the rocket. The 310-foot-long barge will ferry the flight core stage from Michoud to other NASA centers for tests and launch.

Glembatumumab Vedotin, Nivolumab, and Ipilimumab in Treating Patients With Advanced Metastatic Solid Tumors That Cannot Be Removed by Surgery

ClinicalTrials.gov

2018-06-11

Advanced Malignant Solid Neoplasm; Estrogen Receptor Negative; GPNMB Positive; HER2/Neu Negative; Metastatic Malignant Solid Neoplasm; Metastatic Melanoma; Progesterone Receptor Negative; Stage III Breast Cancer AJCC v7; Stage III Cutaneous Melanoma AJCC v7; Stage III Uveal Melanoma AJCC v7; Stage IIIA Cutaneous Melanoma AJCC v7; Stage IIIB Cutaneous Melanoma AJCC v7; Stage IIIC Cutaneous Melanoma AJCC v7; Stage IV Breast Cancer AJCC v6 and v7; Stage IV Cutaneous Melanoma AJCC v6 and v7; Stage IV Uveal Melanoma AJCC v7; Triple-Negative Breast Carcinoma; Unresectable Solid Neoplasm

Oxygen chemisorption compressor study for cryogenic J-T refrigeration

NASA Technical Reports Server (NTRS)

Jones, Jack A.; Blue, Gary D.

1987-01-01

Over twenty potentially reversible heat-powered oxide reactions have been studied and/or tested to determine their potential use as thermochemical oxygen compressors for cryogenic J-T LO2 refrigerators. One gas-solid compound family, Pr(1-n)Ce(n)O(x), proved to be completely reversible with fast kinetics for all pressure ranges tested below 650 C. With a heat-powered charcoal/methane physical adsorption upper stage and a Pr(1-n)Ce(n)O(x) chemisorption lower stage, temperatures should be attainable in the 55-80 K range for less power and over five times less weight than for charcoal/nitrogen sorption refrigeration systems. Total system power requirements with a hydride chemisorption lower stage (10 K to 7 K minimum) are about three times less than any mechanical refrigerator, and spacecraft refrigeration weights are about twenty times less. Due to the lack of wear-related moving parts in sorption refrigerators, life expectancy is at least ten years, and there essentially no vibration.

Heavy Lift for Exploration: Options and Utilization

NASA Technical Reports Server (NTRS)

Creech, Steve; Sumrall, Phil

2010-01-01

Every study of exploration capabilities since the Apollo Program has recommended the renewal of a heavy lift launch capability for the United States. NASA is aggressively pursuing that capability. This paper will discuss several aspects of that effort and the potential uses for that heavy lift capability. The need for heavy lift was cited most recent in the findings of the Review of U.S. Human Space Flight Plans Committee. Combined with considerations of launch availability and on-orbit operations, the Committee finds that exploration will benefit from the availability of a heavy-lift vehicle, the report said. In addition, heavy lift would enable the launching of large scientific observatories and more capable deep-space missions. It may also provide benefit in national security applications. The most recent focus of NASA s heavy lift effort is the Ares V cargo launch vehicle, which is part of the Constellation Program architecture for human exploration beyond low Earth orbit (LEO). The most recent point-of-departure configuration of the Ares V was approved during the Lunar Capabilities concept Review (LCCR) in 2008. The Ares V first stage propulsion system consists of a core stage powered by six commercial liquid hydrogen/liquid oxygen (LH2/LOX) RS-68 engines, flanked by two 5.5-segment solid rocket boosters (SRBs) based on the 5-segment Ares I first stage. The boosters use the same Polybutadiene Acrylonitrile (PBAN) propellant as the Space Shuttle. Atop the core stage is the Earth departure stage (EDS), powered by a single J-2X upper stage engine based on the Ares I upper stage engine. The 33-foot-diameter payload shroud can enclose a lunar lander, scientific instruments, or other payloads. Since LCCR, NASA has continued to refine the design through several successive internal design cycles. In addition, NASA has worked to quantify the broad national consensus for heavy lift in ways that, to the extent possible, meet the needs of the user community.

Eribulin Mesylate and Gemcitabine Hydrochloride in Treating Patients With Metastatic Solid Tumors or Solid Tumors That Cannot be Removed by Surgery

ClinicalTrials.gov

2017-09-19

Adult Solid Neoplasm; Recurrent Ovarian Carcinoma; Recurrent Uterine Corpus Carcinoma; Stage III Ovarian Cancer; Stage III Uterine Corpus Cancer; Stage IV Ovarian Cancer; Stage IV Uterine Corpus Cancer

Trigriluzole With Nivolumab and Pembrolizumab in Treating Patients With Metastatic or Unresectable Solid Malignancies or Lymphoma

ClinicalTrials.gov

2018-05-23

Lymphoma; Metastatic Malignant Solid Neoplasm; Metastatic Melanoma; Metastatic Renal Cell Cancer; Recurrent Bladder Carcinoma; Recurrent Classical Hodgkin Lymphoma; Recurrent Head and Neck Squamous Cell Carcinoma; Recurrent Lymphoma; Recurrent Malignant Solid Neoplasm; Recurrent Renal Cell Carcinoma; Stage III Bladder Cancer; Stage III Lymphoma; Stage III Non-Small Cell Lung Cancer AJCC v7; Stage III Renal Cell Cancer; Stage III Skin Melanoma; Stage IIIA Non-Small Cell Lung Cancer AJCC v7; Stage IIIA Skin Melanoma; Stage IIIB Non-Small Cell Lung Cancer AJCC v7; Stage IIIB Skin Melanoma; Stage IIIC Skin Melanoma; Stage IV Bladder Cancer; Stage IV Lymphoma; Stage IV Non-Small Cell Lung Cancer AJCC v7; Stage IV Renal Cell Cancer; Stage IV Skin Melanoma; Stage IVA Bladder Cancer; Stage IVB Bladder Cancer; Unresectable Head and Neck Squamous Cell Carcinoma; Unresectable Solid Neoplasm

Navitoclax and Vistusertib in Treating Patients With Relapsed Small Cell Lung Cancer and Other Solid Tumors

ClinicalTrials.gov

2018-06-15

Metastatic Malignant Solid Neoplasm; Recurrent Malignant Solid Neoplasm; Recurrent Small Cell Lung Carcinoma; Stage III Small Cell Lung Carcinoma AJCC v7; Stage IIIA Small Cell Lung Carcinoma AJCC v7; Stage IIIB Small Cell Lung Carcinoma AJCC v7; Stage IV Small Cell Lung Carcinoma AJCC v7; Unresectable Solid Neoplasm

Riluzole and Sorafenib Tosylate in Treating Patients With Advanced Solid Tumors or Melanoma

ClinicalTrials.gov

2018-05-15

Advanced Malignant Solid Neoplasm; Recurrent Melanoma; Refractory Malignant Solid Neoplasm; Stage III Cutaneous Melanoma AJCC v7; Stage IIIA Cutaneous Melanoma AJCC v7; Stage IIIB Cutaneous Melanoma AJCC v7; Stage IIIC Cutaneous Melanoma AJCC v7; Stage IV Cutaneous Melanoma AJCC v6 and v7

Reusable Agena study. Volume 1: Executive summary. [space shuttle Agena upper stage tug concept

NASA Technical Reports Server (NTRS)

1974-01-01

The shuttle Agena upper stage interim tug concept is based on a building block approach. These building block concepts are extensions of existing ascent Agena configurations. Several current improvements, have been used in developing the shuttle/Agena upper stage concepts. High-density acid is used as the Agena upper stage oxidizer. The baffled injector is used in the main engine. The DF-224 is a fourth generation computer currently in development and will be flight proven in the near future. The Agena upper stage building block concept uses the current Agena as a baseline, adds an 8.5-inch (21.6 cm) extension to the fuel tank for optimum mixture ratio, uses monomethyl hydrazine as fuel, exchanges a 150:1 nozzle extension for the existing 45:1, exchanges an Autonetics DF-224 for the existing Honeywell computer, and adds a star sensor for guidance update. These modifications to the current Agena provide a 5-foot (1.52m) diameter shuttle/Agena upper stage that will fly all Vandenberg Air Force Base missions in the reusable mode without resorting to a kick motor. The delta V velocity of the Agena is increased by use of a strap-on propellant tank option. This option provides a shuttle/Agena upper stage with the capability to place almost 3900 pounds (1769 kg) into geosynchronous orbit (24 hour period) without the aid of kick motors.

Physics Identity Development: A Snapshot of the Stages of Development of Upper-Level Physics Students

ERIC Educational Resources Information Center

Irving, Paul W.; Sayre, Eleanor C.

2013-01-01

As part of a longitudinal study into identity development in upper-level physics students a phenomenographic research method is employed to assess the stages of identity development of a group of upper-level students. Three categories of description were discovered which indicate the three different stages of identity development for this group…

Characterization of the non axial thrust generated by large solid propellant rocket motors in three axis stabilized ascent

NASA Technical Reports Server (NTRS)

Kosmann, W. J.; Dionne, E. R.; Klemetson, R. W.

1978-01-01

Nonaxial thrusts produced by solid rocket motors during three-axis stabilized attitude control have been determined from ascent experience on twenty three Burner II, Burner IIA and Block 5D-1 upper stage vehicles. A data base representing four different rocket motor designs (three spherical and one extended spherical) totaling twenty five three-axis stabilized firings is generated. Solid rocket motor time-varying resultant and lateral side force vector magnitudes, directions and total impulses, and roll torque couple magnitudes, directions, and total impulses are tabulated in the appendix. Population means and three sigma deviations are plotted. Existing applicable ground test side force and roll torque magnitudes and total impulses are evaluated and compared to the above experience data base. Within the spherical motor population, the selected AEDC ground test data consistently underestimated experienced motor side forces, roll torques and total impulses. Within the extended spherical motor population, the selected AEDC test data predicted experienced motor side forces, roll torques, and total impulses, with surprising accuracy considering the very small size of the test and experience populations.

Upper gastrointestinal bleeding in patients with CKD.

PubMed

Liang, Chih-Chia; Wang, Su-Ming; Kuo, Huey-Liang; Chang, Chiz-Tzung; Liu, Jiung-Hsiun; Lin, Hsin-Hung; Wang, I-Kuan; Yang, Ya-Fei; Lu, Yueh-Ju; Chou, Che-Yi; Huang, Chiu-Ching

2014-08-07

Patients with CKD receiving maintenance dialysis are at risk for upper gastrointestinal bleeding. However, the risk of upper gastrointestinal bleeding in patients with early CKD who are not receiving dialysis is unknown. The hypothesis was that their risk of upper gastrointestinal bleeding is negatively linked to renal function. To test this hypothesis, the association between eGFR and risk of upper gastrointestinal bleeding in patients with stages 3-5 CKD who were not receiving dialysis was analyzed. Patients with stages 3-5 CKD in the CKD program from 2003 to 2009 were enrolled and prospectively followed until December of 2012 to monitor the development of upper gastrointestinal bleeding. The risk of upper gastrointestinal bleeding was analyzed using competing-risks regression with time-varying covariates. In total, 2968 patients with stages 3-5 CKD who were not receiving dialysis were followed for a median of 1.9 years. The incidence of upper gastrointestinal bleeding per 100 patient-years was 3.7 (95% confidence interval, 3.5 to 3.9) in patients with stage 3 CKD, 5.0 (95% confidence interval, 4.8 to 5.3) in patients with stage 4 CKD, and 13.9 (95% confidence interval, 13.1 to 14.8) in patients with stage 5 CKD. Higher eGFR was associated with a lower risk of upper gastrointestinal bleeding (P=0.03), with a subdistribution hazard ratio of 0.93 (95% confidence interval, 0.87 to 0.99) for every 5 ml/min per 1.73 m(2) higher eGFR. A history of upper gastrointestinal bleeding (P<0.001) and lower serum albumin (P=0.004) were independently associated with higher upper gastrointestinal bleeding risk. In patients with CKD who are not receiving dialysis, lower renal function is associated with higher risk for upper gastrointestinal bleeding. The risk is higher in patients with previous upper gastrointestinal bleeding history and low serum albumin. Copyright © 2014 by the American Society of Nephrology.

Ares I Integrated Test Approach

NASA Technical Reports Server (NTRS)

Taylor, Jim

2008-01-01

This slide presentation reviews the testing approach that NASA is developing for the Ares I launch vehicle. NASA is planning a complete series of development, qualification and verification tests. These include: (1) Upper stage engine sea-level and altitude testing (2) First stage development and qualification motors (3) Upper stage structural and thermal development and qualification test articles (4) Main Propulsion Test Article (MPTA) (5) Upper stage green run testing (6) Integrated Vehicle Ground Vibration Testing (IVGVT) and (7) Aerodynamic characterization testing.

Advanced space program studies. Overall executive summary

NASA Technical Reports Server (NTRS)

Wolfe, M. G.

1977-01-01

NASA and DoD requirements and planning data were used in multidiscipline advanced planning investigations of space operations and associated elements (including man), identification of potential low cost approaches, vehicle design, cost synthesis techniques, technology forecasting and opportunities for DoD technology transfer, and the development near-, mid-, and far-term space initiatives and development plans with emphasis on domestic and military commonality. An overview of objectives and results are presented for the following studies: advanced space planning and conceptual analysis, shuttle users, technology assessment and new opportunities, standardization and program practice, integrated STS operations planning, solid spinning upper stage, and integrated planning support functions.

Study of solid rocket motor for space shuttle booster, volume 2, book 1

NASA Technical Reports Server (NTRS)

1972-01-01

The technical requirements for the solid propellant rocket engine to be used with the space shuttle orbiter are presented. The subjects discussed are: (1) propulsion system definition, (2) solid rocket engine stage design, (3) solid rocket engine stage recovery, (4) environmental effects, (5) manrating of the solid rocket engine stage, (6) system safety analysis, and (7) ground support equipment.

Propulsion at the Marshall Space Flight Center - A brief history

NASA Technical Reports Server (NTRS)

Jones, L. W.; Fisher, M. F.; Mccool, A. A.; Mccarty, J. P.

1991-01-01

The history of propulsion development at the NASA Marshall Space Flight Center is summarized, beginning with the development of the propulsion system for the Redstone missile. This course of propulsion development continues through the Jupiter IRBM, the Saturn family of launch vehicles and the engines that powered them, the Centaur upper stage and RL-10 engine, the Reactor In-Flight Test stage and the NERVA nuclear engine. The Space Shuttle Main Engine and Solid Rocket Boosters are covered, as are spacecraft propulsion systems, including the reaction control systems for the High Energy Astronomy Observatory and the Space Station. The paper includes a description of several technology efforts such as those in high pressure turbomachinery, aerospike engines, and the AS203 cyrogenic fluid management flight experiment. These and other propulsion projects are documented, and the scope of activities in support of these efforts at Marshall delineated.

Creation of an Upper Stage Trajectory Capability Boundary to Enable Booster System Trade Space Exploration

NASA Technical Reports Server (NTRS)

Walsh, Ptrick; Coulon, Adam; Edwards, Stephen; Mavris, Dimitri N.

2012-01-01

The problem of trajectory optimization is important in all space missions. The solution of this problem enables one to specify the optimum thrust steering program which should be followed to achieve a specified mission objective, simultaneously satisfying the constraints.1 It is well known that whether or not the ascent trajectory is optimal can have a significant impact on propellant usage for a given payload, or on payload weight for the same gross vehicle weight.2 Consequently, ascent guidance commands are usually optimized in some fashion. Multi-stage vehicles add complexity to this analysis process as changes in vehicle properties in one stage propagate to the other stages through gear ratios and changes in the optimal trajectory. These effects can cause an increase in analysis time as more variables are added and convergence of the optimizer to system closure requires more analysis iterations. In this paper, an approach to simplifying this multi-stage problem through the creation of an upper stage capability boundary is presented. This work was completed as part of a larger study focused on trade space exploration for the advanced booster system that will eventually form a part of NASA s new Space Launch System.3 The approach developed leverages Design of Experiments and Surrogate Modeling4 techniques to create a predictive model of the SLS upper stage performance. The design of the SLS core stages is considered fixed for the purposes of this study, which results in trajectory parameters such as staging conditions being the only variables relevant to the upper stage. Through the creation of a surrogate model, which takes staging conditions as inputs and predicts the payload mass delivered by the SLS upper stage to a reference orbit as the response, it is possible to identify a "surface" of staging conditions which all satisfy the SLS requirement of placing 130 metric tons into low-Earth orbit (LEO).3 This identified surface represents the 130 metric ton capability boundary for the upper stage, such that if the combined first stage and boosters can achieve any one staging point on that surface, then the design is identified as feasible. With the surrogate model created, design and analysis of advanced booster concepts is streamlined, as optimization of the upper stage trajectory is no longer required in every design loop.

Afatinib Dimaleate and Capecitabine in Treating Patients With Advanced Refractory Solid Tumors, Pancreatic Cancer or Biliary Cancer

ClinicalTrials.gov

2017-10-26

Advanced Malignant Solid Neoplasm; Bile Duct Carcinoma; Recurrent Malignant Solid Neoplasm; Recurrent Pancreatic Carcinoma; Stage III Pancreatic Cancer AJCC v6 and v7; Stage IVA Pancreatic Cancer; Stage IVB Pancreatic Cancer

Two-statge sorption type cryogenic refrigerator including heat regeneration system

NASA Technical Reports Server (NTRS)

Jones, Jack A. (Inventor); Wen, Liang-Chi (Inventor); Bard, Steven (Inventor)

1989-01-01

A lower stage chemisorption refrigeration system physically and functionally coupled to an upper stage physical adsorption refrigeration system. Waste heat generated by the lower stage cycle is regenerated to fuel the upper stage cycle thereby greatly improving the energy efficiency of a two-stage sorption refrigerator. The two stages are joined by disposing a first pressurization chamber providing a high pressure flow of a first refrigerant for the lower stage refrigeration cycle within a second pressurization chamber providing a high pressure flow of a second refrigerant for the upper stage refrigeration cycle. The first pressurization chamber is separated from the second pressurization chamber by a gas-gap thermal switch which at times is filled with a thermoconductive fluid to allow conduction of heat from the first pressurization chamber to the second pressurization chamber.

Two stage sorption type cryogenic refrigerator including heat regeneration system

NASA Technical Reports Server (NTRS)

Jones, Jack A. (Inventor); Wen, Liang-Chi (Inventor); Bard, Steven (Inventor)

1989-01-01

A lower stage chemisorption refrigeration system physically and functionally coupled to an upper stage physical adsorption refrigeration system is disclosed. Waste heat generated by the lower stage cycle is regenerated to fuel the upper stage cycle thereby greatly improving the energy efficiency of a two-stage sorption refrigerator. The two stages are joined by disposing a first pressurization chamber providing a high pressure flow of a first refrigerant for the lower stage refrigeration cycle within a second pressurization chamber providing a high pressure flow of a second refrigerant for the upper stage refrigeration cycle. The first pressurization chamber is separated from the second pressurization chamber by a gas-gap thermal switch which at times is filled with a thermoconductive fluid to allow conduction of heat from the first pressurization chamber to the second pressurization chamber.

Dissolved-Solids Load in Henrys Fork Upstream from the Confluence with Antelope Wash, Wyoming, Water Years 1970-2009

USGS Publications Warehouse

Foster, Katharine; Kenney, Terry A.

2010-01-01

Annual dissolved-solids load at the mouth of Henrys Fork was estimated by using data from U.S. Geological Survey streamflow-gaging station 09229500, Henrys Fork near Manila, Utah. The annual dissolved-solids load for water years 1970-2009 ranged from 18,300 tons in 1977 to 123,300 tons in 1983. Annual streamflows for this period ranged from 14,100 acre-feet in 1977 to 197,500 acre-feet in 1983. The 25-percent trimmed mean dissolved-solids load for water years 1970-2009 was 44,300 tons per year at Henrys Fork near Manila, Utah. Previous simulations using a SPAtially Referenced Regression On Watershed attributes (SPARROW) model for dissolved solids specific to water year 1991 conditions in the Upper Colorado River Basin predicted an annual dissolved-solids load of 25,000 tons for the Henrys Fork Basin upstream from Antelope Wash. On the basis of computed dissolved-solids load data from Henrys Fork near Manila, Utah, together with estimated annual dissolved-solids load from Antelope Wash and Peoples Canal, this prediction was adjusted to 37,200 tons. As determined by simulations with the Upper Colorado River Basin SPARROW model, approximately 56 percent (14,000 tons per year) of the dissolved-solids load at Henrys Fork upstream from Antelope Wash is associated with the 21,500 acres of irrigated agricultural lands in the upper Henrys Fork Basin.

Dental Age Estimation (DAE): Data management for tooth development stages including the third molar. Appropriate censoring of Stage H, the final stage of tooth development.

PubMed

Roberts, Graham J; McDonald, Fraser; Andiappan, Manoharan; Lucas, Victoria S

2015-11-01

The final stage of dental development of third molars is usually helpful to indicate whether or not a subject is aged over 18 years. A complexity is that the final stage of development is unlimited in its upper border. Investigators usually select an inappropriate upper age limit or censor point for this tooth development stage. The literature was searched for appropriate data sets for dental age estimation and those that provided the count (n), the mean (x¯), and the standard deviation (sd) for each of the tooth development stages. The Demirjian G and Demirjian H were used for this study. Upper and lower limits of the Stage G and Stage H data were calculated limiting the data to plus or minus three standard deviations from the mean. The upper border of Stage H was limited by appropriate censoring at the maximum value for Stage G. The maximum age at attainment from published data, for Stage H, ranged from 22.60 years to 34.50 years. These data were explored to demonstrate how censoring provides an estimate for the correct maximum age for the final stage of Stage H as 21.64 years for UK Caucasians. This study shows that confining the data array of individual tooth developments stages to ± 3sd provides a reliable and logical way of censoring the data for tooth development stages with a Normal distribution of data. For Stage H this is inappropriate as it is unbounded in its upper limit. The use of a censored data array for Stage H using Percentile values is appropriate. This increases the reliability of using third molar Stage H alone to determine whether or not an individual is over 18 years old. For Stage H, individual ancestral groups should be censored using the same technique. Copyright © 2015 Elsevier Ltd and Faculty of Forensic and Legal Medicine. All rights reserved.

Integrated System Test Approaches for the NASA Ares I Crew Launch Vehicle

NASA Technical Reports Server (NTRS)

Cockrell, Charles

2008-01-01

NASA is maturing test and evaluation plans leading to flight readiness of the Ares I crew launch vehicle. Key development, qualification, and verification tests are planned . Upper stage engine sea-level and altitude testing. First stage development and qualification motors. Upper stage structural and thermal development and qualification test articles. Main Propulsion Test Article (MPTA). Upper stage green run testing. Integrated Vehicle Ground Vibration Testing (IVGVT). Aerodynamic characterization testing. Test and evaluation supports initial validation flights (Ares I-Y and Orion 1) and design certification.

Entinostat, Nivolumab, and Ipilimumab in Treating Patients With Solid Tumors That Are Metastatic or Cannot Be Removed by Surgery or Locally Advanced or Metastatic HER2-Negative Breast Cancer

ClinicalTrials.gov

2018-03-22

Breast Adenocarcinoma; HER2/Neu Negative; Invasive Breast Carcinoma; Metastatic Malignant Solid Neoplasm; Stage III Breast Cancer AJCC v7; Stage IIIA Breast Cancer AJCC v7; Stage IIIB Breast Cancer AJCC v7; Stage IIIC Breast Cancer AJCC v7; Stage IV Breast Cancer AJCC v6 and v7; Unresectable Solid Neoplasm

Decitabine in Treating Patients With Advanced Solid Tumors

ClinicalTrials.gov

2013-02-06

Male Breast Cancer; Recurrent Bladder Cancer; Recurrent Breast Cancer; Recurrent Melanoma; Stage III Melanoma; Stage IV Bladder Cancer; Stage IV Breast Cancer; Stage IV Melanoma; Unspecified Adult Solid Tumor, Protocol Specific

GTI-2040, Oxaliplatin, and Capecitabine in Treating Patients With Locally Advanced or Metastatic Colorectal Cancer or Other Solid Tumors

ClinicalTrials.gov

2013-03-26

Recurrent Colon Cancer; Recurrent Rectal Cancer; Stage IIIC Colon Cancer; Stage IIIC Rectal Cancer; Stage IVA Colon Cancer; Stage IVA Rectal Cancer; Stage IVB Colon Cancer; Stage IVB Rectal Cancer; Unspecified Adult Solid Tumor, Protocol Specific

Preoperative local MRI-staging of patients with a suspected pancreatic mass.

PubMed

Fischer, U; Vosshenrich, R; Horstmann, O; Becker, H; Salamat, B; Baum, F; Grabbe, E

2002-02-01

The aim of this study was to define the value of MRI of the pancreas for preoperative local staging of patients with a suspected pancreatic mass. Ninety-four patients (41 women, 53 men; age range 32-87 years) with a suspected pancreatic tumor underwent preoperative staging with MRI on a 1.5-T system. The MRI protocol included breath-hold MR cholangiopancreatography in turbo spin-echo technique, biphasic contrast-enhanced 3D MR angiography, and MRI of the upper abdomen with breath-hold T2-weighted half-Fourier acquired single-shot turbo spin-echo and T1-weighted fast-low-angle-shot (pre- and postcontrast) sequences. Data were collected prospectively and analyzed by two radiologists in agreement modality. Evaluation criteria were vascular involvement, resectability, and a characterization benign vs malignant. Results were compared to histopathology in 78 patients. Sixteen patients were followed-up. In 74 of 94 patients a solid tumor or an inflammation of the pancreas ( n=62) or the papilla ( n=12) was detected. In this group, MRI had a sensitivity of 98%, a specificity of 92%, and an accuracy of 96% in the characterization of malignant tumors. Regarding only the solid tumors, the positive predictive value of MRI was 87% with respect to resectability. Other pathologic findings included adenoma or inflammation of the duodenum ( n=5), carcinoma or benign stenosis of the choledochus duct ( n=7) and carcinoma of the gall bladder ( n=2). In 6 patients MRI did not depict any pathologic findings, and follow-up confirmed this interpretation. Magnetic resonance imaging allows a local preoperative staging in patients with suspected pancreatic tumor. Limitations, however, concern to the diagnostics of peritoneal and/or liver metastases.

Constellation's First Flight Test: Ares I-X

NASA Technical Reports Server (NTRS)

Davis, Stephan R.; Askins, Bruce R.

2010-01-01

On October 28, 2009, NASA launched Ares I-X, the first flight test of the Constellation Program that will send human beings to the Moon and beyond. This successful test is the culmination of a three-and-a-half-year, multi-center effort to design, build, and fly the first demonstration vehicle of the Ares I crew launch vehicle, the successor vehicle to the Space Shuttle. The suborbital mission was designed to evaluate the atmospheric flight characteristics of a vehicle dynamically similar to Ares I; perform a first stage separation and evaluate its effects; characterize and control roll torque; stack, fly, and recover a solid-motor first stage testing the Ares I parachutes; characterize ground, flight, and reentry environments; and develop and execute new ground hardware and procedures. Built from existing flight and new simulator hardware, Ares I-X integrated a Shuttle-heritage four-segment solid rocket booster for first stage propulsion, a spacer segment to simulate a five-segment booster, Peacekeeper axial engines for roll control, and Atlas V avionics, as well as simulators for the upper stage, crew module, and launch abort system. The mission leveraged existing logistical and ground support equipment while also developing new ones to accommodate the first in-line rocket for flying astronauts since the Saturn IB last flew from Kennedy Space Center (KSC) in 1975. This paper will describe the development and integration of the various vehicle and ground elements, from conception to stacking in KSC s Vehicle Assembly Building; hardware performance prior to, during, and after the launch; and preliminary lessons and data gathered from the flight. While the Constellation Program is currently under review, Ares I-X has and will continue to provide vital lessons for NASA personnel in taking a vehicle concept from design to flight.

Pembrolizumab in Treating Participants With Metastatic, Recurrent or Locally Advanced Cancer and Genomic Instability

ClinicalTrials.gov

2018-03-22

BRCA1 Gene Mutation; BRCA2 Gene Mutation; Locally Advanced Solid Neoplasm; Metastatic Malignant Solid Neoplasm; POLD1 Gene Mutation; POLE Gene Mutation; Recurrent Malignant Solid Neoplasm; Recurrent Ovarian Carcinoma; Stage III Breast Cancer AJCC v7; Stage III Ovarian Cancer AJCC v8; Stage IIIA Breast Cancer AJCC v7; Stage IIIA Ovarian Cancer AJCC v8; Stage IIIB Breast Cancer AJCC v7; Stage IIIB Ovarian Cancer AJCC v8; Stage IIIC Breast Cancer AJCC v7; Stage IIIC Ovarian Cancer AJCC v8; Stage IV Breast Cancer AJCC v6 and v7; Stage IV Ovarian Cancer AJCC v8; Stage IVA Ovarian Cancer AJCC v8; Stage IVB Ovarian Cancer AJCC v8

Palbociclib With Cisplatin or Carboplatin in Advanced Solid Tumors

ClinicalTrials.gov

2017-11-22

Solid Neoplasm; Stage III Pancreatic Cancer; Stage IIIA Breast Cancer; Stage IIIA Non-Small Cell Lung Cancer; Stage IIIB Breast Cancer; Stage IIIB Non-Small Cell Lung Cancer; Stage IIIC Breast Cancer; Stage IV Breast Cancer; Stage IV Non-Small Cell Lung Cancer; Stage IVA Pancreatic Cancer; Stage IVB Pancreatic Cancer; Sarcoma; Colorectal Cancer; Head and Neck Cancer; Cancer of Unknown Primary; Bladder Cancer; Ovarian Cancer

Aerodynamic characteristics of the upper stages of a launch vehicle in low-density regime

NASA Astrophysics Data System (ADS)

Oh, Bum Seok; Lee, Joon Ho

2016-11-01

Aerodynamic characteristics of the orbital block (remaining configuration after separation of nose fairing and 1st and 2nd stages of the launch vehicle) and the upper 2-3stage (configuration after separation of 1st stage) of the 3 stages launch vehicle (KSLV-II, Korea Space Launch Vehicle) at high altitude of low-density regime are analyzed by SMILE code which is based on DSMC (Direct Simulation Monte-Carlo) method. To validating of the SMILE code, coefficients of axial force and normal forces of Apollo capsule are also calculated and the results agree very well with the data predicted by others. For the additional validations and applications of the DSMC code, aerodynamic calculation results of simple shapes of plate and wedge in low-density regime are also introduced. Generally, aerodynamic characteristics in low-density regime differ from those of continuum regime. To understand those kinds of differences, aerodynamic coefficients of the upper stages (including upper 2-3 stage and the orbital block) of the launch vehicle in low-density regime are analyzed as a function of Mach numbers and altitudes. The predicted axial force coefficients of the upper stages of the launch vehicle are very high compared to those in continuum regime. In case of the orbital block which flies at very high altitude (higher than 250km), all aerodynamic coefficients are more dependent on velocity variations than altitude variations. In case of the upper 2-3 stage which flies at high altitude (80km-150km), while the axial force coefficients and the locations of center of pressure are less changed with the variations of Knudsen numbers (altitudes), the normal force coefficients and pitching moment coefficients are more affected by variations of Knudsen numbers (altitude).

PI3Kbeta Inhibitor AZD8186 and Docetaxel in Treating Patients Advanced Solid Tumors With PTEN or PIK3CB Mutations That Are Metastatic or Cannot Be Removed by Surgery

ClinicalTrials.gov

2018-05-16

Advanced Malignant Solid Neoplasm; Anatomic Stage III Breast Cancer AJCC v8; Anatomic Stage IIIA Breast Cancer AJCC v8; Anatomic Stage IIIB Breast Cancer AJCC v8; Anatomic Stage IIIC Breast Cancer AJCC v8; Anatomic Stage IV Breast Cancer AJCC v8; Castration-Resistant Prostate Carcinoma; Estrogen Receptor Negative; Estrogen Receptor Positive; HER2/Neu Negative; Metastatic Malignant Solid Neoplasm; Metastatic Prostate Carcinoma; PIK3CB Gene Mutation; Progesterone Receptor Negative; Prognostic Stage III Breast Cancer AJCC v8; Prognostic Stage IIIA Breast Cancer AJCC v8; Prognostic Stage IIIB Breast Cancer AJCC v8; Prognostic Stage IIIC Breast Cancer AJCC v8; Prognostic Stage IV Breast Cancer AJCC v8; PTEN Gene Mutation; PTEN Loss; Stage III Prostate Cancer AJCC v8; Stage IIIA Prostate Cancer AJCC v8; Stage IIIB Prostate Cancer AJCC v8; Stage IIIC Prostate Cancer AJCC v8; Stage IV Prostate Cancer AJCC v8; Stage IVA Prostate Cancer AJCC v8; Stage IVB Prostate Cancer AJCC v8; Triple-Negative Breast Carcinoma; Unresectable Solid Neoplasm

Upper stage technology evaluation studies

NASA Technical Reports Server (NTRS)

1972-01-01

Studies to evaluate advanced technology relative to chemical upper stages and orbit-to-orbit stages are reported. The work described includes: development of LH2/LOX stage data, development of data to indicate stage sensitivity to engine tolerance, modified thermal routines to accommodate storable propellants, added stage geometries to computer program for monopropellant configurations, determination of the relative gain obtainable through improvement of stage mass fraction, future propulsion concepts, effect of ultrahigh chamber-pressure increases, and relative gains obtainable through improved mass fraction.

Sliding-gate valve for use with abrasive materials

DOEpatents

Ayers, Jr., William J.; Carter, Charles R.; Griffith, Richard A.; Loomis, Richard B.; Notestein, John E.

1985-01-01

The invention is a flow and pressure-sealing valve for use with abrasive solids. The valve embodies special features which provide for long, reliable operating lifetimes in solids-handling service. The valve includes upper and lower transversely slidable gates, contained in separate chambers. The upper gate provides a solids-flow control function, whereas the lower gate provides a pressure-sealing function. The lower gate is supported by means for (a) lifting that gate into sealing engagement with its seat when the gate is in its open and closed positions and (b) lowering the gate out of contact with its seat to permit abrasion-free transit of the gate between its open and closed positions. When closed, the upper gate isolates the lower gate from the solids. Because of this shielding action, the sealing surface of the lower gate is not exposed to solids during transit or when it is being lifted or lowered. The chamber containing the lower gate normally is pressurized slightly, and a sweep gas is directed inwardly across the lower-gate sealing surface during the vertical translation of the gate.

Comparison of joining processes for Haynes 230 nickel based super alloy

NASA Astrophysics Data System (ADS)

Williston, David Hugh

Haynes 230 is a nickel based, solid-solution strengthened alloy that is used for high-temperature applications in the aero-engine and power generation industries. The alloy composition is balanced to avoid precipitation of undesirable topologically closed-packed (TCP) intermetallic phases, such as Sigma, Mu, or Laves-type, that are detrimental to mechanical and corrosion properties. This material is currently being used for the NASA's J2X upper stage rocket nozzle extension. Current fabrication procedures use fusion welding processes to join blanks that are subsequently formed. Cracks have been noted to occur in the fusion welded region during the forming operations. Use of solid state joining processes, such as friction stir welding are being proposed to eliminate the fusion weld cracks. Of interest is a modified friction stir welding process called thermal stir welding. Three welding process: Gas Metal Arc Welding (GMAW), Electron Beam Welding (EBW), and Thermal Stir Welding (TSWing) are compared in this study.

Nivolumab With or Without Ipilimumab in Treating Younger Patients With Recurrent or Refractory Solid Tumors or Sarcomas

ClinicalTrials.gov

2018-06-25

Metastatic Melanoma; Recurrent Ewing Sarcoma/Peripheral Primitive Neuroectodermal Tumor; Recurrent Hodgkin Lymphoma; Recurrent Malignant Solid Neoplasm; Recurrent Melanoma; Recurrent Neuroblastoma; Recurrent Non-Hodgkin Lymphoma; Recurrent Osteosarcoma; Recurrent Rhabdomyosarcoma; Refractory Hodgkin Lymphoma; Refractory Malignant Solid Neoplasm; Refractory Non-Hodgkin Lymphoma; Stage III Cutaneous Melanoma AJCC v7; Stage IIIA Cutaneous Melanoma AJCC v7; Stage IIIB Cutaneous Melanoma AJCC v7; Stage IIIC Cutaneous Melanoma AJCC v7; Stage IV Cutaneous Melanoma AJCC v6 and v7

Dinoflagellates: Fossil motile-stage tests from the upper cretaceous of the Northern New Jersey coastal plain

USGS Publications Warehouse

May, F.E.

1976-01-01

Fossil dinoflagellate tests have been considered to represent encysted, nonmotile stages. The discovery of flagellar porelike structures and probable trichocyst pores in the Upper Cretaceous genus Dinogymnium suggests that motile stage tests are also preserved as acid-resistant, organic-walled microfossils.

Selumetinib and Cyclosporine in Treating Patients With Advanced Solid Tumors or Advanced or Metastatic Colorectal Cancer

ClinicalTrials.gov

2018-03-23

Recurrent Colorectal Carcinoma; Solid Neoplasm; Stage IIIA Colorectal Cancer AJCC v7; Stage IIIB Colorectal Cancer AJCC v7; Stage IIIC Colorectal Cancer AJCC v7; Stage IVA Colorectal Cancer AJCC v7; Stage IVB Colorectal Cancer AJCC v7

Mobility of arsenic in a Bangladesh aquifer: Inferences from geochemical profiles, leaching data, and mineralogical characterization

NASA Astrophysics Data System (ADS)

Swartz, Christopher H.; Blute, Nicole Keon; Badruzzman, Borhan; Ali, Ashraf; Brabander, Daniel; Jay, Jenny; Besancon, James; Islam, Shafiqul; Hemond, Harold F.; Harvey, Charles F.

2004-11-01

Aquifer geochemistry was characterized at a field site in the Munshiganj district of Bangladesh where the groundwater is severely contaminated by As. Vertical profiles of aqueous and solid phase parameters were measured in a sandy deep aquifer (depth >150 m) below a thick confining clay (119 to 150 m), a sandy upper aquifer (3.5 to 119 m) above this confining layer, and a surficial clay layer (<3.5 m). In the deep aquifer and near the top of the upper aquifer, aqueous As levels are low (<10 μg/L), but aqueous As approaches a maximum of 640 μg/L at a depth of 30 to 40 m and falls to 58 μg/L near the base (107 m) of the upper aquifer. In contrast, solid phase As concentrations are uniformly low, rarely exceeding 2 μg/g in the two sandy aquifers and never exceeding 10 μg/g in the clay layers. Solid phase As is also similarly distributed among a variety of reservoirs in the deep and upper aquifer, including adsorbed As, As coprecipitated in solids leachable by mild acids and reductants, and As incorporated in silicates and other more recalcitrant phases. One notable difference among depths is that sorbed As loads, considered with respect to solid phase Fe extractable with 1 N HCl, 0.2 M oxalic acid, and a 0.5 M Ti(III)-citrate-EDTA solution, appear to be at capacity at depths where aqueous As is highest; this suggests that sorption limitations may, in part, explain the aqueous As depth profile at this site. Competition for sorption sites by silicate, phosphate, and carbonate oxyanions appear to sustain elevated aqueous As levels in the upper aquifer. Furthermore, geochemical profiles are consistent with the hypothesis that past or ongoing reductive dissolution of Fe(III) oxyhydroxides acts synergistically with competitive sorption to maintain elevated dissolved As levels in the upper aquifer. Microprobe data indicate substantial spatial comapping between As and Fe in both the upper and deep aquifer sediments, and microscopic observations reveal ubiquitous Fe coatings on most solid phases, including quartz, feldspars, and aluminosilicates. Extraction results and XRD analysis of density/magnetic separates suggest that these coatings may comprise predominantly Fe(II) and mixed valence Fe solids, although the presence of Fe(III) oxyhydroxides can not be ruled out. These data suggest As release may continue to be linked to dissolution processes targeting Fe, or Fe-rich, phases in these aquifers.

Propranolol Hydrochloride in Treating Patients With Locally Recurrent or Metastatic Solid Tumors That Cannot Be Removed By Surgery

ClinicalTrials.gov

2017-11-27

Male Breast Cancer; Recurrent Melanoma; Stage IV Breast Cancer; Stage IV Melanoma; Stage IV Ovarian Epithelial Cancer; Stage IV Ovarian Germ Cell Tumor; Unspecified Adult Solid Tumor, Protocol Specific; Hepatocellular Carcinoma

Sunitinib Malate and Bevacizumab in Treating Patients With Kidney Cancer or Advanced Solid Malignancies

ClinicalTrials.gov

2014-04-01

Clear Cell Renal Cell Carcinoma; Recurrent Renal Cell Cancer; Stage I Renal Cell Cancer; Stage II Renal Cell Cancer; Stage III Renal Cell Cancer; Stage IV Renal Cell Cancer; Unspecified Adult Solid Tumor, Protocol Specific

Formation of Different Si3N4 Nanostructures by Salt-Assisted Nitridation.

PubMed

Liu, Xiongzhang; Guo, Ran; Zhang, Sengjing; Li, Qingda; Saito, Genki; Yi, Xuemei; Nomura, Takahiro

2018-04-11

Silicon nitride (Si 3 N 4 ) products with different nanostructure morphologies and different phases for Si 3 N 4 ceramic with high thermal conductivity were synthesized by a direct nitriding method. NaCl and NH 4 Cl were added to raw Si powders, and the reaction was carried out under a nitrogen gas flow of 100 mL/min. The phase composition and morphologies of the products were systemically characterized by X-ray diffraction, field emission scanning electron microscopy, and high-resolution transmission electron microscopy. At 1450 °C, the NaCl content was 30 wt %, the NH 4 Cl content was 3 wt %, and the maximum α-Si 3 N 4 content was 96 wt %. The process of Si nitridation can be divided into three stages by analyzing the reaction schemes: in the first stage (25-900 °C), NH 4 Cl decomposition and the generation of stacked amorphous Si 3 N 4 occurs; in the second stage (900-1450 °C), NaCl melts and Si 3 N 4 generates; and in the third stage (>1450 °C), α-Si 3 N 4 → β-Si 3 N 4 phase change and the evaporation of NaCl occurs. The products are made of two layers: a thin upper layer of nanowires containing different nanostructures and a lower layer mainly comprising fluffy, blocky, and short needlelike products. The introduction of NaCl and NH 4 Cl facilitated the evaporation of Si powders and the decomposition of Al 2 O 3 from porcelain boat and furnace tube, which resulted in the mixing of N 2 , O 2 , Al 2 O, and Si vapors and generated Al x Si y O z nanowires with rough surfaces and lead to thin Si 3 N 4 nanowires, nanobranches by the vapor-solid (VS), vapor-liquid-solid (VLS), and the double-stage VLS base and VS tip growth mechanisms.

Expression of regulatory proteins and proliferative activity in relation to phenotypic characteristics of upper urothelial carcinoma.

PubMed

Dolićanin, Zana; Velicković, Ljubinka Janković; Djordjević, Biljana; Visnjić, Milan; Pesić, Ivana; Ristić, Ana; Marjanović, Vesna

2011-07-01

Deregulation of the normal cell cycle is common in upper urothelial carcinoma (UUC). The aim of this study was to investigate the expression of regulatory proteins of the cell cycle (p53, p16, cyclin D1, HER-2) and proliferative Ki-67 activity in UUC, and to determine their interaction and influence on the phenotypic characteristics of UUC. In 44 patients with UUC, histopathological and immunohistochemical analyses (p53, p16, cyclin D1, HER-2, and Ki-67) of tumors were done. Overexpression/altered expression of p53, p16, cyclin D1 or HER-2 was detected in 20%, 57%, 64%, and 57% of tumors, respectively. Eleven (25%) UUC had a high proliferative Ki-67 index. Forty patients (91%) had at least one marker altered, while four (9%) tumors had a wild-type status. Analysis of relationship between expressions of molecular markers showed that only high expression of p53 was significantly associated with altered p16 activity (p < 0.05). High Ki-67 index was associated with the high stage (p < 0.005), solid growth (p < 0.01), high grade (p < 0.05), and multifocality p < 0.05) of UUC, while high expression of p53 was associated with the solid growth (p < 0.05). In regression models that included all molecular markers and phenotypic characteristics, only Ki-67 correlated with the growth (p < 0.0001), stage (p < 0.01), grade (p < 0.05) and multifocality (p < 0.05) of UCC; (Ki-67 and HER-2 expression correlated with the lymphovascular invasion (p < 0.05). This investigation showed that only negative regulatory proteins of the cell cycle, p53 and p16, were significantly associated in UUC, while proliferative marker Ki-67 was in relation to the key phenotypic characteristics of UUC in the best way.

Underfed stoker boiler for burning bituminous coal and other solid fuel particles

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

Marcotte, R.P.; Dumont, J.W. Jr.

1987-10-06

An automatic stoker boiler is described for space or process heating with steam or hot water. The boiler includes a heat transfer compartment having a water inlet and an outlet for steam or hot water, an exhaust, a combustion chamber, a transverse partition in the chamber, drive and driven shafts below the chamber, sprockets supported by the shaft and an endless belt of the link type trained about the sprockets. There are also means to deliver underfire air upwardly through the upper course. The upper portion has a throat opening adjacent to the second end, heat exchanging passageways extending throughmore » the compartment, means to deliver overfire air into the chamber, means to deliver solid fuel particles to the upper course adjacent to the first end, means in the exhaust operable to induce draft in the upper portion and control means operable to effect the advance of the belt. There are means operable to deliver solid fuel to the upper course in predetermined, proportional increments, means to vary the induced draft by predetermined, proportional increments and means to adjust the underfire air volume by predetermined, proportional increments.« less

Effect of film thickness on morphological evolution in dewetting and crystallization of polystyrene/poly(ε-caprolactone) blend films.

PubMed

Ma, Meng; He, Zhoukun; Yang, Jinghui; Chen, Feng; Wang, Ke; Zhang, Qin; Deng, Hua; Fu, Qiang

2011-11-01

In this Article, the morphological evolution in the blend thin film of polystyrene (PS)/poly(ε-caprolactone) (PCL) was investigated via mainly AFM. It was found that an enriched two-layer structure with PS at the upper layer and PCL at the bottom layer was formed during spinning coating. By changing the solution concentration, different kinds of crystal morphologies, such as finger-like, dendritic, and spherulitic-like, could be obtained at the bottom PCL layer. These different initial states led to the morphological evolution processes to be quite different from each other, so the phase separation, dewetting, and crystalline morphology of PS/PCL blend films as a function of time were studied. It was interesting to find that the morphological evolution of PS at the upper layer was largely dependent on the film thickness. For the ultrathin (15 nm) blend film, a liquid-solid/liquid-liquid dewetting-wetting process was observed, forming ribbons that rupture into discrete circular PS islands on voronoi finger-like PCL crystal. For the thick (30 nm) blend film, the liquid-liquid dewetting of the upper PS layer from the underlying adsorbed PCL layer was found, forming interconnected rim structures that rupture into discrete circular PS islands embedded in the single lamellar PCL dendritic crystal due to Rayleigh instability. For the thicker (60 nm) blend film, a two-step liquid-liquid dewetting process with regular holes decorated with dendritic PCL crystal at early annealing stage and small holes decorated with spherulite-like PCL crystal among the early dewetting holes at later annealing stage was observed. The mechanism of this unusual morphological evolution process was discussed on the basis of the entropy effect and annealing-induced phase separation.

Gamma-Secretase/Notch Signalling Pathway Inhibitor RO4929097 and Temsirolimus in Treating Patients With Advanced Solid Tumors

ClinicalTrials.gov

2014-05-29

Endometrial Papillary Serous Carcinoma; Recurrent Endometrial Carcinoma; Recurrent Renal Cell Cancer; Stage III Endometrial Carcinoma; Stage III Renal Cell Cancer; Stage IV Endometrial Carcinoma; Stage IV Renal Cell Cancer; Unspecified Adult Solid Tumor, Protocol Specific

Targeted Therapy Directed by Genetic Testing in Treating Pediatric Patients With Relapsed or Refractory Advanced Solid Tumors, Non-Hodgkin Lymphomas, or Histiocytic Disorders (The Pediatric MATCH Screening Trial)

ClinicalTrials.gov

2018-06-25

Advanced Malignant Solid Neoplasm; Ann Arbor Stage III Childhood Non-Hodgkin Lymphoma; Ann Arbor Stage IV Childhood Non-Hodgkin Lymphoma; Childhood Langerhans Cell Histiocytosis; Histiocytic Sarcoma; Juvenile Xanthogranuloma; Malignant Glioma; Recurrent Central Nervous System Neoplasm; Recurrent Childhood Ependymoma; Recurrent Childhood Malignant Germ Cell Tumor; Recurrent Childhood Medulloblastoma; Recurrent Childhood Non-Hodgkin Lymphoma; Recurrent Childhood Rhabdomyosarcoma; Recurrent Childhood Soft Tissue Sarcoma; Recurrent Ewing Sarcoma; Recurrent Glioma; Recurrent Hepatoblastoma; Recurrent Langerhans Cell Histiocytosis; Recurrent Malignant Solid Neoplasm; Recurrent Neuroblastoma; Recurrent Osteosarcoma; Recurrent Peripheral Primitive Neuroectodermal Tumor; Refractory Central Nervous System Neoplasm; Refractory Childhood Malignant Germ Cell Tumor; Refractory Langerhans Cell Histiocytosis; Refractory Malignant Solid Neoplasm; Refractory Neuroblastoma; Rhabdoid Tumor; Stage III Osteosarcoma AJCC v7; Stage III Soft Tissue Sarcoma AJCC v7; Stage IV Osteosarcoma AJCC v7; Stage IV Soft Tissue Sarcoma AJCC v7; Stage IVA Osteosarcoma AJCC v7; Stage IVB Osteosarcoma AJCC v7; Wilms Tumor

Larotrectinib in Treating Patients With Relapsed or Refractory Advanced Solid Tumors, Non-Hodgkin Lymphoma, or Histiocytic Disorders With NTRK Fusions (A Pediatric MATCH Treatment Trial)

ClinicalTrials.gov

2018-06-25

Advanced Malignant Solid Neoplasm; Ann Arbor Stage III Childhood Non-Hodgkin Lymphoma; Ann Arbor Stage IV Childhood Non-Hodgkin Lymphoma; Malignant Glioma; NTRK1 Fusion Positive; NTRK2 Fusion Positive; NTRK3 Fusion Positive; Recurrent Central Nervous System Neoplasm; Recurrent Childhood Ependymoma; Recurrent Childhood Malignant Germ Cell Tumor; Recurrent Childhood Medulloblastoma; Recurrent Childhood Non-Hodgkin Lymphoma; Recurrent Childhood Rhabdomyosarcoma; Recurrent Childhood Soft Tissue Sarcoma; Recurrent Ewing Sarcoma; Recurrent Glioma; Recurrent Hepatoblastoma; Recurrent Langerhans Cell Histiocytosis; Recurrent Malignant Solid Neoplasm; Recurrent Neuroblastoma; Recurrent Osteosarcoma; Recurrent Peripheral Primitive Neuroectodermal Tumor; Refractory Central Nervous System Neoplasm; Refractory Childhood Malignant Germ Cell Tumor; Refractory Langerhans Cell Histiocytosis; Refractory Malignant Solid Neoplasm; Refractory Neuroblastoma; Refractory Non-Hodgkin Lymphoma; Rhabdoid Tumor; Stage III Osteosarcoma AJCC v7; Stage III Soft Tissue Sarcoma AJCC v7; Stage IV Osteosarcoma AJCC v7; Stage IV Soft Tissue Sarcoma AJCC v7; Stage IVA Osteosarcoma AJCC v7; Stage IVB Osteosarcoma AJCC v7; Wilms Tumor

PI3K/mTOR Inhibitor LY3023414 in Treating Patients With Relapsed or Refractory Advanced Solid Tumors, Non-Hodgkin Lymphoma, or Histiocytic Disorders With TSC or PI3K/MTOR Mutations (A Pediatric MATCH Treatment Trial)

ClinicalTrials.gov

2018-06-18

Advanced Malignant Solid Neoplasm; Ann Arbor Stage III Non-Hodgkin Lymphoma; Ann Arbor Stage IV Non-Hodgkin Lymphoma; Malignant Glioma; Recurrent Central Nervous System Neoplasm; Recurrent Childhood Ependymoma; Recurrent Ewing Sarcoma; Recurrent Glioma; Recurrent Hepatoblastoma; Recurrent Langerhans Cell Histiocytosis; Recurrent Malignant Germ Cell Tumor; Recurrent Malignant Solid Neoplasm; Recurrent Medulloblastoma; Recurrent Neuroblastoma; Recurrent Non-Hodgkin Lymphoma; Recurrent Osteosarcoma; Recurrent Peripheral Primitive Neuroectodermal Tumor; Recurrent Rhabdomyosarcoma; Recurrent Soft Tissue Sarcoma; Refractory Central Nervous System Neoplasm; Refractory Langerhans Cell Histiocytosis; Refractory Malignant Germ Cell Tumor; Refractory Malignant Solid Neoplasm; Refractory Neuroblastoma; Refractory Non-Hodgkin Lymphoma; Rhabdoid Tumor; Stage III Osteosarcoma AJCC v7; Stage III Soft Tissue Sarcoma AJCC v7; Stage IV Osteosarcoma AJCC v7; Stage IV Soft Tissue Sarcoma AJCC v7; Stage IVA Osteosarcoma AJCC v7; Stage IVB Osteosarcoma AJCC v7; TSC1 Gene Mutation; TSC2 Gene Mutation; Wilms Tumor

Advanced Space Transportation Program (ASTP)

NASA Image and Video Library

2006-12-05

The NASA developed Ares rockets, named for the Greek god associated with Mars, will return humans to the moon and later take them to Mars and other destinations. This is an illustration of the Ares V with call outs. The Ares V is a heavy lift launch vehicle that will use five RS-68 liquid oxygen/liquid hydrogen engines mounted below a larger version of the space shuttle external tank, and two five-segment solid propellant rocket boosters for the first stage. The upper stage will use the same J-2X engine as the Ares I and past Apollo vehicles. The Ares V can lift more than 286,000 pounds to low Earth orbit and stands approximately 360 feet tall. This versatile system will be used to carry cargo and the components into orbit needed to go to the moon and later to Mars. Ares V is subject to configuration changes before it is actually launched. This illustration reflects the latest configuration as of January 2007.

Illustration of Ares V Launch Vehicle With Call Outs

NASA Technical Reports Server (NTRS)

2006-01-01

The NASA developed Ares rockets, named for the Greek god associated with Mars, will return humans to the moon and later take them to Mars and other destinations. This is an illustration of the Ares V with call outs. The Ares V is a heavy lift launch vehicle that will use five RS-68 liquid oxygen/liquid hydrogen engines mounted below a larger version of the space shuttle external tank, and two five-segment solid propellant rocket boosters for the first stage. The upper stage will use the same J-2X engine as the Ares I and past Apollo vehicles. The Ares V can lift more than 286,000 pounds to low Earth orbit and stands approximately 360 feet tall. This versatile system will be used to carry cargo and the components into orbit needed to go to the moon and later to Mars. Ares V is subject to configuration changes before it is actually launched. This illustration reflects the latest configuration as of January 2007.

Model of the Ares V Launch System

NASA Technical Reports Server (NTRS)

2006-01-01

This is a studio photograph of a model of the Ares V rocket. Named for the Greek god associated with Mars, Ares vehicles will return humans to the moon and later take them to Mars and other destinations. The Ares V is a heavy lift launch vehicle that will use five RS-68 liquid oxygen/liquid hydrogen engines mounted below a larger version of the space shuttle external tank, and two five-segment solid propellant rocket boosters for the first stage. The upper stage will use the same J-2X engine as the Ares I. The Ares V can lift more than 286,000 pounds to low Earth orbit and stands approximately 360 feet tall. This versatile system will be used to carry cargo and the components into orbit needed to go to the moon and later to Mars, while the Crew will be carried by the Ares I. Ares V is subject to configuration changes before it is actually launched. This illustration reflects the latest configuration as of September 2006.

SLS Resource Reel Aug 2016 orig

NASA Image and Video Library

2016-07-04

Space Launch System Resource Reel Description: This video includes launch animation of NASA’s Space Launch System (SLS), as well as work taking place across NASA centers and the country to build and test the various components that make up the rocket including: the 5-segment solid rocket boosters, the RS-25 rocket engines, the massive tanks that make up the Core Stage of the rocket that fuels the RS-25 engines, and upper portions of the rocket that connect the interim cryogenic propulsion stage to the Orion spacecraft. SLS, is an advanced launch vehicle for a new era of exploration beyond Earth’s orbit into deep space. SLS, the world’s most powerful rocket, will launch astronauts in the agency’s Orion spacecraft on missions to an asteroid and eventually to Mars, while opening new possibilities for other payloads including robotic scientific missions to places like Mars, Saturn and Jupiter. Graphic Information: PAO Name:Kim Henry Phone Number:256-544-1899 Email Address: kimberly.m.henry@nasa.gov

KSC-03pd0536

NASA Image and Video Library

2003-02-24

KENNEDY SPACE CENTER, FLA. -- The cruise stage, aeroshell and lander for the Mars Exploration Rover-1 mission and the MER-2 rover arrive at KSC. The same flight hardware for the MER-2 rover arrived Jan. 27; however, the MER-2 rover is scheduled to arrive at KSC in March. While at KSC, each of the two rovers, the aeroshells and the landers will undergo a full mission simulation. All of these flight elements will then be integrated together. After spin balance testing, each spacecraft will be mated to a solid propellant upper stage booster that will propel the spacecraft out of Earth orbit. Approximately 10 days before launch they will be transported to the launch pad for mating with their respective Boeing Delta II rockets. The rovers will serve as robotic geologists to seek answers about the evolution of Mars, particularly for a history of water. The rovers will be identical to each other, but will land at different regions of Mars. Launch of the MER-1 is scheduled for May 30. MER-2 will follow June 25.

Dynamic Simulation of VEGA SRM Bench Firing By Using Propellant Complex Characterization

NASA Astrophysics Data System (ADS)

Di Trapani, C. D.; Mastrella, E.; Bartoccini, D.; Squeo, E. A.; Mastroddi, F.; Coppotelli, G.; Linari, M.

2012-07-01

During the VEGA launcher development, from the 2004 up to now, 8 firing tests have been performed at Salto di Quirra (Sardinia, Italy) and Kourou (Guyana, Fr) with the objective to characterize and qualify of the Zefiros and P80 Solid Rocket Motors (SRM). In fact the VEGA launcher configuration foreseen 3 solid stages based on P80, Z23 and Z9 Solid Rocket Motors respectively. One of the primary objectives of the firing test is to correctly characterize the dynamic response of the SRM in order to apply such a characterization to the predictions and simulations of the VEGA launch dynamic environment. Considering that the solid propellant is around 90% of the SRM mass, it is very important to dynamically characterize it, and to increase the confidence in the simulation of the dynamic levels transmitted to the LV upper part from the SRMs. The activity is articulated in three parts: • consolidation of an experimental method for the dynamic characterization of the complex dynamic elasticity modulus of elasticity of visco-elastic materials applicable to the SRM propellant operative conditions • introduction of the complex dynamic elasticity modulus in a numerical FEM benchmark based on MSC NASTRAN solver • analysis of the effect of the introduction of the complex dynamic elasticity modulus in the Zefiros FEM focusing on experimental firing test data reproduction with numerical approach.

Upper stage alternatives for the shuttle era

NASA Technical Reports Server (NTRS)

1981-01-01

The status and general characteristics of Space Shuttle upper stages now in use or in development, as well as new vehicle possibilities are examined. Upper stage requirements for both civil and Department of Defense missions, categorized generally into near-term (early and mid-1980's), mid-term (late 1980's to mid-1990's), and far-term (late 1990's and beyond) are discussed. Finally, the technical, schedule and cost impact of alternative ways in which these requirements could be met are examined, and a number of conclusions and recommendations are reached.

Simulink Model of the Ares I Upper Stage Main Propulsion System

NASA Technical Reports Server (NTRS)

Burchett, Bradley T.

2008-01-01

A numerical model of the Ares I upper stage main propulsion system is formulated based on first principles. Equation's are written as non-linear ordinary differential equations. The GASP fortran code is used to compute thermophysical properties of the working fluids. Complicated algebraic constraints are numerically solved. The model is implemented in Simulink and provides a rudimentary simulation of the time history of important pressures and temperatures during re-pressurization, boost and upper stage firing. The model is validated against an existing reliable code, and typical results are shown.

KSC-98pc1113

NASA Image and Video Library

1998-09-17

A solid rocket booster (left) is raised for installation onto the Boeing Delta 7326 rocket that will launch Deep Space 1 at Launch Pad 17A, Cape Canaveral Air Station. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches. Delta's origins go back to the Thor intermediate-range ballistic missile, which was developed in the mid-1950s for the U.S. Air Force. The Thor a single-stage, liquid-fueled rocket later was modified to become the Delta launch vehicle. The Delta 7236 has three solid rocket boosters and a Star 37 upper stage. Delta IIs are manufactured in Huntington Beach, Calif. Rocketdyne, a division of The Boeing Company, builds Delta II's main engine in Canoga Park, Calif. Final assembly takes place at the Boeing facility in Pueblo, Colo. Deep Space 1, the first flight in NASA's New Millennium Program, is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include an ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999

KSC-98pc1115

NASA Image and Video Library

1998-09-17

A solid rocket booster is maneuvered into place for installation on the Boeing Delta 7326 rocket that will launch Deep Space 1 at Launch Pad 17A, Cape Canaveral Air Station. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches. Delta's origins go back to the Thor intermediate-range ballistic missile, which was developed in the mid-1950s for the U.S. Air Force. The Thor a single-stage, liquid-fueled rocket later was modified to become the Delta launch vehicle. The Delta 7236 has three solid rocket boosters and a Star 37 upper stage. Delta IIs are manufactured in Huntington Beach, Calif. Rocketdyne, a division of The Boeing Company, builds Delta II's main engine in Canoga Park, Calif. Final assembly takes place at the Boeing facility in Pueblo, Colo. Deep Space 1, the first flight in NASA's New Millennium Program, is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include an ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999

KSC-98pc1114

NASA Image and Video Library

1998-09-17

A Boeing Delta 7326 rocket with two solid rocket boosters attached sits on Launch Pad 17A, Cape Canaveral Air Station. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches. Delta's origins go back to the Thor intermediate-range ballistic missile, which was developed in the mid-1950s for the U.S. Air Force. The Thor a single-stage, liquid-fueled rocket later was modified to become the Delta launch vehicle. Delta IIs are manufactured in Huntington Beach, Calif. Rocketdyne, a division of The Boeing Company, builds Delta II's main engine in Canoga Park, Calif. Final assembly takes place at the Boeing facility in Pueblo, Colo. The Delta 7236, which has three solid rocket boosters and a Star 37 upper stage, will launch Deep Space 1, the first flight in NASA's New Millennium Program. It is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include an ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999

KSC-98pc1112

NASA Image and Video Library

1998-09-17

(Left) A solid rocket booster is lifted for installation onto the Boeing Delta 7326 rocket that will launch Deep Space 1 at Launch Pad 17A, Cape Canaveral Air Station. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches. Delta's origins go back to the Thor intermediate-range ballistic missile, which was developed in the mid-1950s for the U.S. Air Force. The Thor a single-stage, liquid-fueled rocket later was modified to become the Delta launch vehicle. The Delta 7236 has three solid rocket boosters and a Star 37 upper stage. Delta IIs are manufactured in Huntington Beach, Calif. Rocketdyne, a division of The Boeing Company, builds Delta II's main engine in Canoga Park, Calif. Final assembly takes place at the Boeing facility in Pueblo, Colo. Deep Space 1, the first flight in NASA's New Millennium Program, is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include an ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999

Characteristics and trends of streamflow and dissolved solids in the upper Colorado River Basin, Arizona, Colorado, New Mexico, Utah, and Wyoming

USGS Publications Warehouse

Liebermann, Timothy D.; Mueller, David K.; Kircher, James E.; Choquette, Anne F.

1989-01-01

Annual and monthly concentrations and loads of dissolved solids and major constituents were estimated for 70 streamflow-gaging stations in the Upper Colorado River Basin. Trends in streamflow, dissolved-solids concentrations, and dissolved-solids loads were identified. Nonparametric trend-analysis techniques were used to determine step trends resulting from human activities upstream and long-term monotonic trends. Results were compared with physical characteristics of the basin and historical water-resource development in the basin to determine source areas of dissolved solids and possible cause of trends. Mean annual dissolved-solids concentration increases from less than 100 milligrams per liter in the headwater streams to more than 500 milligrams per liter in the outflow from the Upper Colorado River Basin. All the major tributaries that have high concentrations of dissolved solids are downstream from extensive areas of irrigated agriculture. However, irrigation predated the period of record for most sites and was not a factor in many identified trends. Significant annual trends were identified for 30 sites. Most of these trends were related to transbasin exports, changes in land use, salinity-control practices, or reservoir development. The primary factor affecting streamflow and dissolved-solids concentration and load has been the construction of large reservoirs. Reservoirs have decreased the seasonal and annual variability of streamflow and dissolved solids in streams that drain the Gunnison and San Juan River basins. Fontenelle and Flaming Gorge Reservoirs have increased the dissolved-solids load in the Green River because of dissolution of mineral salts from the bank material. The largest trends occurred downstream from Lake Powell. However, the period of record since the completion of filling was too short to estimate the long-term effects of that reservoir.

SLS Intertank Transported to NASA's Barge Pegasus for Shipment, Testing

NASA Image and Video Library

2018-02-22

A structural test version of the intertank for NASA's new heavy-lift rocket, the Space Launch System, is loaded onto the barge Pegasus Feb. 22, at NASA’s Michoud Assembly Facility in New Orleans. NASA engineers and technicians used the agency's new self-propelled modular transporters -- highly specialized, mobile platforms specifically designed to transport SLS hardware -- to transport the critical test hardware to the barge. The intertank is the second piece of structural hardware for the rocket's massive core stage scheduled for delivery to NASA's Marshall Space Flight Center in Huntsville, Alabama, for testing. Engineers at Marshall will push, pull and bend the intertank with millions of pounds of force to ensure the hardware can withstand the forces of launch and ascent. The flight version of the intertank will connect the core stage's two colossal fuel tanks, serve as the upper-connection point for the two solid rocket boosters and house the avionics and electronics that will serve as the "brains" of the rocket. Pegasus, originally used during the Space Shuttle Program, has been redesigned and extended to accommodate the SLS rocket's massive, 212-foot-long core stage -- the backbone of the rocket. The 310-foot-long barge will ferry the core stage elements from Michoud to other NASA centers for tests and launches.

SLS Intertank Transported to NASA's Barge Pegasus for Shipment, testing

NASA Image and Video Library

2018-02-22

A structural test version of the intertank for NASA's new heavy-lift rocket, the Space Launch System, is loaded onto the barge Pegasus Feb. 22, at NASA’s Michoud Assembly Facility in New Orleans. NASA engineers and technicians used the agency's new self-propelled modular transporters -- highly specialized, mobile platforms specifically designed to transport SLS hardware -- to transport the critical test hardware to the barge. The intertank is the second piece of structural hardware for the rocket's massive core stage scheduled for delivery to NASA's Marshall Space Flight Center in Huntsville, Alabama, for testing. Engineers at Marshall will push, pull and bend the intertank with millions of pounds of force to ensure the hardware can withstand the forces of launch and ascent. The flight version of the intertank will connect the core stage's two colossal fuel tanks, serve as the upper-connection point for the two solid rocket boosters and house the avionics and electronics that will serve as the "brains" of the rocket. Pegasus, originally used during the Space Shuttle Program, has been redesigned and extended to accommodate the SLS rocket's massive, 212-foot-long core stage -- the backbone of the rocket. The 310-foot-long barge will ferry the core stage elements from Michoud to other NASA centers for tests and launches.

Methoxyamine, Cisplatin, and Pemetrexed Disodium in Treating Patients With Advanced Solid Tumors or Mesothelioma That Cannot Be Removed by Surgery or Mesothelioma That Is Refractory to Pemetrexed Disodium and Cisplatin or Carboplatin

ClinicalTrials.gov

2018-04-23

Advanced Malignant Solid Neoplasm; Advanced Peritoneal Malignant Mesothelioma; Advanced Pleural Malignant Mesothelioma; Recurrent Peritoneal Malignant Mesothelioma; Recurrent Pleural Malignant Mesothelioma; Stage III Non-Small Cell Lung Cancer AJCC v7; Stage III Ovarian Cancer AJCC v6 and v7; Stage III Pleural Malignant Mesothelioma AJCC v7; Stage IIIA Non-Small Cell Lung Cancer AJCC v7; Stage IIIA Ovarian Cancer AJCC v6 and v7; Stage IIIB Non-Small Cell Lung Cancer AJCC v7; Stage IIIB Ovarian Cancer AJCC v6 and v7; Stage IIIC Ovarian Cancer AJCC v6 and v7; Stage IV Non-Small Cell Lung Cancer AJCC v7; Stage IV Ovarian Cancer AJCC v6 and v7; Stage IV Pleural Malignant Mesothelioma AJCC v7; Thymoma; Unresectable Solid Neoplasm

Seismic stratigraphy of the Mississippi-Alabama shelf and upper continental slope

USGS Publications Warehouse

Kindinger, J.L.

1988-01-01

The Mississippi-Alabama shelf and upper continental slope contain relatively thin Upper Pleistocene and Holocene deposits. Five stages of shelf evolution can be identified from the early Wisconsinan to present. The stages were controlled by glacioeustatic or relative sea-level changes and are defined by the stratigraphic position of depositional and erosional episodes. The stratigraphy was identified on seismic profiles by means of geomorphic pattern, high-angle clinoform progradational deposits, buried stream entrenchments, planar conformities, and erosional unconformities. The oldest stage (stage 1) of evolution occurred during the early Wisconsinan lowstand; the subaerially exposed shelf was eroded to a smooth seaward-sloping surface. This paleosurface is overlain by a thin (< 10 m) drape of transgressive deposits (stage 2). Stage 3 occurred in three phases as the late Wisconsinan sea retreated: (1) fluvial channel systems eroded across the shelf, (2) deposited a thick (90 m) shelf-margin delta, and (3) contemporaneously deposited sediments on the upper slope. Stage 4 included the rapid Holocene sea-level rise that deposited a relatively thin transgressive facies over parts of the shelf. The last major depositional episode (stage 5) was the progradation of the St. Bernard delta over the northwestern and central parts of the area. A depositional hiatus has occurred since the St. Bernard progradation. These Upper Quaternary shelf and slope deposits provide models for analogous deposits in the geologic record. Primarily, they are examples of cyclic sedimentation caused by changes in sea level and may be useful in describing short-term, sandy depositional episodes in prograding shelf and slope sequences. ?? 1988.

Low Cost, Upper Stage-Class Propulsion

NASA Technical Reports Server (NTRS)

Vickers, John

2015-01-01

The low cost, upper stage-class propulsion (LCUSP) element will develop a high strength copper alloy additive manufacturing (AM) process as well as critical components for an upper stage-class propulsion system that will be demonstrated with testing. As manufacturing technologies have matured, it now appears possible to build all the major components and subsystems of an upper stage-class rocket engine for substantially less money and much faster than traditionally done. However, several enabling technologies must be developed before that can happen. This activity will address these technologies and demonstrate the concept by designing, manufacturing, and testing the critical components of a rocket engine. The processes developed and materials' property data will be transitioned to industry upon completion of the activity. Technologies to enable the concept are AM copper alloy process development, AM post-processing finishing to minimize surface roughness, AM material deposition on existing copper alloy substrate, and materials characterization.

A Fully Coupled Multi-Rigid-Body Fuel Slosh Dynamics Model Applied to the Triana Stack

NASA Technical Reports Server (NTRS)

London, K. W.

2001-01-01

A somewhat general multibody model is presented that accounts for energy dissipation associated with fuel slosh and which unifies some of the existing more specialized representations. This model is used to predict the mutation growth time constant for the Triana Spacecraft, or Stack, consisting of the Triana Observatory mated with the Gyroscopic Upper Stage of GUS (includes the solid rocket motor, SRM, booster). At the nominal spin rate of 60 rpm and with 145 kg of hydrazine propellant on board, a time constant of 116 s is predicted for worst case sloshing of a spherical slug model compared to 1,681 s (nominal), 1,043 s (worst case) for sloshing of a three degree of freedom pendulum model.

Determination of the availability of appropriate aged flight rocket motors. [captive tests to determine case bond separation and grain bore cracking

NASA Technical Reports Server (NTRS)

Martin, P. J.

1974-01-01

A program to identify surplus solid rocket propellant engines which would be available for a program of functional integrity testing was conducted. The engines are classified as: (1) upper stage and apogee engines, (2) sounding rocket and launch vehicle engines, and (3) jato, sled, and tactical engines. Nearly all the engines were available because their age exceeds the warranted shelf life. The preference for testing included tests at nominal flight conditions, at design limits, and to establish margin limits. The principal failure modes of interest were case bond separation and grain bore cracking. Data concerning the identification and characteristics of each engine are tabulated. Methods for conducting the tests are described.

Additive Manufacturing a Liquid Hydrogen Rocket Engine

NASA Technical Reports Server (NTRS)

Jones, Carl P.; Robertson, Elizabeth H.; Koelbl, Mary Beth; Singer, Chris

2016-01-01

Space Propulsion is a 5 day event being held from 2nd May to the 6th May 2016 at the Rome Marriott Park Hotel in Rome, Italy. This event showcases products like Propulsion sub-systems and components, Production and manufacturing issues, Liquid, Solid, Hybrid and Air-breathing Propulsion Systems for Launcher and Upper Stages, Overview of current programmes, AIV issues and tools, Flight testing and experience, Technology building blocks for Future Space Transportation Propulsion Systems : Launchers, Exploration platforms & Space Tourism, Green Propulsion for Space Transportation, New propellants, Rocket propulsion & global environment, Cost related aspects of Space Transportation propulsion, Modelling, Pressure-Thrust oscillations issues, Impact of new requirements and regulations on design etc. in the Automotive, Manufacturing, Fabrication, Repair & Maintenance industries.

CRYOGENIC UPPER STAGE SYSTEM SAFETY

NASA Technical Reports Server (NTRS)

Smith, R. Kenneth; French, James V.; LaRue, Peter F.; Taylor, James L.; Pollard, Kathy (Technical Monitor)

2005-01-01

NASA s Exploration Initiative will require development of many new systems or systems of systems. One specific example is that safe, affordable, and reliable upper stage systems to place cargo and crew in stable low earth orbit are urgently required. In this paper, we examine the failure history of previous upper stages with liquid oxygen (LOX)/liquid hydrogen (LH2) propulsion systems. Launch data from 1964 until midyear 2005 are analyzed and presented. This data analysis covers upper stage systems from the Ariane, Centaur, H-IIA, Saturn, and Atlas in addition to other vehicles. Upper stage propulsion system elements have the highest impact on reliability. This paper discusses failure occurrence in all aspects of the operational phases (Le., initial burn, coast, restarts, and trends in failure rates over time). In an effort to understand the likelihood of future failures in flight, we present timelines of engine system failures relevant to initial flight histories. Some evidence suggests that propulsion system failures as a result of design problems occur shortly after initial development of the propulsion system; whereas failures because of manufacturing or assembly processing errors may occur during any phase of the system builds process, This paper also explores the detectability of historical failures. Observations from this review are used to ascertain the potential for increased upper stage reliability given investments in integrated system health management. Based on a clear understanding of the failure and success history of previous efforts by multiple space hardware development groups, the paper will investigate potential improvements that can be realized through application of system safety principles.

GTI-2040 and Docetaxel in Treating Patients With Recurrent, Metastatic, or Unresectable Locally Advanced Non-Small Cell Lung Cancer, Prostate Cancer, or Other Solid Tumors

ClinicalTrials.gov

2013-01-23

Recurrent Non-small Cell Lung Cancer; Recurrent Prostate Cancer; Stage III Prostate Cancer; Stage IIIA Non-small Cell Lung Cancer; Stage IIIB Non-small Cell Lung Cancer; Stage IV Non-small Cell Lung Cancer; Stage IV Prostate Cancer; Unspecified Adult Solid Tumor, Protocol Specific

Monte Carlo analysis of the Titan III/Transfer Orbit Stage guidance system for the Mars Observer mission

NASA Astrophysics Data System (ADS)

Bell, Stephen C.; Ginsburg, Marc A.; Rao, Prabhakara P.

An important part of space launch vehicle mission planning for a planetary mission is the integrated analysis of guidance and performance dispersions for both booster and upper stage vehicles. For the Mars Observer mission, an integrated trajectory analysis was used to maximize the scientific payload and to minimize injection errors by optimizing the energy management of both vehicles. This was accomplished by designing the Titan III booster vehicle to inject into a hyperbolic departure plane, and the Transfer Orbit Stage (TOS) to correct any booster dispersions. An integrated Monte Carlo analysis of the performance and guidance dispersions of both vehicles provided sensitivities, an evaluation of their guidance schemes and an injection error covariance matrix. The polynomial guidance schemes used for the Titan III variable flight azimuth computations and the TOS solid rocket motor ignition time and burn direction derivations accounted for a wide variation of launch times, performance dispersions, and target conditions. The Mars Observer spacecraft was launched on 25 September 1992 on the Titan III/TOS vehicle. The post flight analysis indicated that a near perfect park orbit injection was achieved, followed by a trans-Mars injection with less than 2sigma errors.

KSC-07pd1513

NASA Image and Video Library

2007-06-15

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 17-B at Cape Canaveral Air Force Station, the second stage of the Delta II launch vehicle for the Dawn spacecraft arrives at the upper level of the mobile service tower. It will be moved inside the tower and mated with the first stage already in the tower. The Delta II-Heavy, manufactured by the United Launch Alliance, is scheduled to launch the Dawn spacecraft on its 4-year flight to the asteroid belt. The Delta II-Heavy is the strongest rocket in the Delta II class. It will use three stages and nine solid-fueled booster rockets to propel Dawn on its way. A 9.5-foot payload fairing will protect the spacecraft from the heat and stresses of launch. Dawn's goal is to characterize the conditions and processes of the solar system's earliest epoch by investigating in detail the largest protoplanets that have remained intact since their formations: asteroid Vesta and the dwarf planet Ceres. They reside in the extensive zone between Mars and Jupiter together with many other smaller bodies, called the asteroid belt. Dawn is scheduled to launch July 7. Photo credit: NASA/Jack Pfaller

Effects of virtual reality training with modified constraint-induced movement therapy on upper extremity function in acute stage stroke: a preliminary study.

PubMed

Ji, Eun-Kyu; Lee, Sang-Heon

2016-11-01

[Purpose] The purpose of this study was to investigate the effects of virtual reality training combined with modified constraint-induced movement therapy on upper extremity motor function recovery in acute stage stroke patients. [Subjects and Methods] Four acute stage stroke patients participated in the study. A multiple baseline single subject experimental design was utilized. Modified constraint-induced movement therapy was used according to the EXplaining PLastICITy after stroke protocol during baseline sessions. Virtual reality training with modified constraint-induced movement therapy was applied during treatment sessions. The Manual Function Test and the Box and Block Test were used to measure upper extremity function before every session. [Results] The subjects' upper extremity function improved during the intervention period. [Conclusion] Virtual reality training combined with modified constraint-induced movement is effective for upper extremity function recovery in acute stroke patients.

AFP464 in Treating Patients With Metastatic or Refractory Solid Tumors That Cannot Be Removed By Surgery

ClinicalTrials.gov

2014-02-21

Male Breast Cancer; Recurrent Breast Cancer; Recurrent Ovarian Epithelial Cancer; Recurrent Primary Peritoneal Cavity Cancer; Recurrent Renal Cell Cancer; Stage IV Breast Cancer; Stage IV Ovarian Epithelial Cancer; Stage IV Primary Peritoneal Cavity Cancer; Stage IV Renal Cell Cancer; Unspecified Adult Solid Tumor, Protocol Specific

Romidepsin in Treating Patients With Lymphoma, Chronic Lymphocytic Leukemia, or Solid Tumors With Liver Dysfunction

ClinicalTrials.gov

2018-04-02

Glioma; Lymphoma; Metastatic Malignant Solid Neoplasm; Neuroendocrine Neoplasm; Recurrent Adult Soft Tissue Sarcoma; Recurrent Bladder Carcinoma; Recurrent Breast Carcinoma; Recurrent Chronic Lymphocytic Leukemia; Recurrent Colorectal Carcinoma; Recurrent Head and Neck Carcinoma; Recurrent Lung Carcinoma; Recurrent Malignant Solid Neoplasm; Recurrent Melanoma; Recurrent Pancreatic Carcinoma; Recurrent Primary Cutaneous T-Cell Non-Hodgkin Lymphoma; Recurrent Prostate Carcinoma; Recurrent Renal Cell Carcinoma; Recurrent Thyroid Gland Carcinoma; Refractory Chronic Lymphocytic Leukemia; Refractory Mature T-Cell and NK-Cell Non-Hodgkin Lymphoma; Refractory Primary Cutaneous T-Cell Non-Hodgkin Lymphoma; Stage III Breast Cancer AJCC v7; Stage III Colorectal Cancer AJCC v7; Stage III Cutaneous Melanoma AJCC v7; Stage III Lung Cancer AJCC v7; Stage III Pancreatic Cancer AJCC v6 and v7; Stage III Prostate Cancer AJCC v7; Stage III Renal Cell Cancer AJCC v7; Stage III Soft Tissue Sarcoma AJCC v7; Stage IIIA Breast Cancer AJCC v7; Stage IIIA Colorectal Cancer AJCC v7; Stage IIIA Cutaneous Melanoma AJCC v7; Stage IIIB Breast Cancer AJCC v7; Stage IIIB Colorectal Cancer AJCC v7; Stage IIIB Cutaneous Melanoma AJCC v7; Stage IIIC Breast Cancer AJCC v7; Stage IIIC Colorectal Cancer AJCC v7; Stage IIIC Cutaneous Melanoma AJCC v7; Stage IV Breast Cancer AJCC v6 and v7; Stage IV Colorectal Cancer AJCC v7; Stage IV Cutaneous Melanoma AJCC v6 and v7; Stage IV Lung Cancer AJCC v7; Stage IV Pancreatic Cancer AJCC v6 and v7; Stage IV Prostate Cancer AJCC v7; Stage IV Renal Cell Cancer AJCC v7; Stage IV Soft Tissue Sarcoma AJCC v7; Stage IVA Colorectal Cancer AJCC v7; Stage IVB Colorectal Cancer AJCC v7; Unresectable Solid Neoplasm

Marshall Space Flight Center Digital Manufacturing

NASA Technical Reports Server (NTRS)

Arays, Edward; Phillips, Steven

2008-01-01

This presentation highlights the history of DELMIA at MSFC; provides an overview of the Constellation Program; examines the manufacturing of Ares 1 Upper Stage; explains the digital manufacturing implementation for Ares 1 Upper Stage; and, discusses manufacturing and development problems and challenges.

STS upper stage operations

NASA Technical Reports Server (NTRS)

Kitchens, M. D.; Schnyer, A. D.

1977-01-01

Several design/development and operational approaches for STS upper stages are being pursued to realize maximum operational and economic benefits upon the introduction of the STS in the 1980s. The paper focuses special attention on safety operations, launch site operations and on-orbit operations.

Operations analysis (study 2.1). Contingency analysis. [of failure modes anticipated during space shuttle upper stage planning

NASA Technical Reports Server (NTRS)

1974-01-01

Future operational concepts for the space transportation system were studied in terms of space shuttle upper stage failure contingencies possible during deployment, retrieval, or space servicing of automated satellite programs. Problems anticipated during mission planning were isolated using a modified 'fault tree' technique, normally used in safety analyses. A comprehensive space servicing hazard analysis is presented which classifies possible failure modes under the catagories of catastrophic collision, failure to rendezvous and dock, servicing failure, and failure to undock. The failure contingencies defined are to be taken into account during design of the upper stage.

Elevated temperature forming method and preheater apparatus

DOEpatents

Krajewski, Paul E; Hammar, Richard Harry; Singh, Jugraj; Cedar, Dennis; Friedman, Peter A; Luo, Yingbing

2013-06-11

An elevated temperature forming system in which a sheet metal workpiece is provided in a first stage position of a multi-stage pre-heater, is heated to a first stage temperature lower than a desired pre-heat temperature, is moved to a final stage position where it is heated to a desired final stage temperature, is transferred to a forming press, and is formed by the forming press. The preheater includes upper and lower platens that transfer heat into workpieces disposed between the platens. A shim spaces the upper platen from the lower platen by a distance greater than a thickness of the workpieces to be heated by the platens and less than a distance at which the upper platen would require an undesirably high input of energy to effectively heat the workpiece without being pressed into contact with the workpiece.

Early evolution and dynamics of Earth from a molten initial stage

NASA Astrophysics Data System (ADS)

Louro Lourenço, D. J.; Tackley, P. J.

2014-12-01

It is now well established that most of the terrestrial planets underwent a magma ocean stage during their accretion. On Earth, it is probable that at the end of accretion, giant impacts like the hypothesised Moon-forming impact, together with other sources of heat, melted a substantial part of the mantle. The thermal and chemical evolution of the resulting magma ocean most certainly had dramatic consequences on the history of the planet. Considerable research has been done on magma oceans using simple 1-D models (e.g.: Abe, PEPI 1997; Solomatov, Treat. Geophys. 2007; Elkins-Tanton EPSL 2008). However, some aspects of the dynamics may not be adequately addressed in 1-D and require the use of 2-D or 3-D models. Moreover, new developments in mineral physics that indicate that melt can be denser than solid at high pressures (e.g.: de Koker et al., EPSL 2013) can have very important impacts on the classical views of the solidification of magma oceans (Labrosse et al., Nature 2007). The goal of our study is to understand and characterize the influence of melting on the long-term thermo-chemical evolution of rocky planet interiors, starting from an initial molten state (magma ocean). Our approach is to model viscous creep of the solid mantle, while parameterizing processes that involve melt as previously done in 1-D models, including melt-solid separation at all melt fractions, the use of an effective diffusivity to parameterize turbulent mixing, coupling to a parameterized core heat balance and a radiative surface boundary condition. These enhancements have been made to the numerical code StagYY (Tackley, PEPI 2008). We will present results for the evolution of an Earth-like planet from a molten initial state to present day, while testing the effect of uncertainties in parameters such as melt-solid density differences, surface heat loss and efficiency of turbulent mixing. Our results show rapid cooling and crystallization until the rheological transition then much slower crystallization, large-scale overturn well before full solidification, the formation and subduction of an early crust while a partially-molten upper mantle is still present, transitioning to mostly-solid-state long-term mantle convection and plate tectonics.

Akt Inhibitor MK2206 and Hydroxychloroquine in Treating Patients With Advanced Solid Tumors, Melanoma, Prostate or Kidney Cancer

ClinicalTrials.gov

2018-05-15

Adult Solid Neoplasm; Hormone-Resistant Prostate Carcinoma; Recurrent Melanoma; Recurrent Prostate Carcinoma; Recurrent Renal Cell Carcinoma; Stage IIIA Cutaneous Melanoma AJCC v7; Stage IIIB Cutaneous Melanoma AJCC v7; Stage IIIC Cutaneous Melanoma AJCC v7; Stage IV Cutaneous Melanoma AJCC v6 and v7; Stage IV Prostate Cancer AJCC v7; Stage IV Renal Cell Cancer AJCC v7

Early Rockets

NASA Image and Video Library

1950-02-24

Bumper Wac liftoff at the Long Range Proving Ground located at Cape Canaveral, Florida. At White Sands, New Mexico, the German rocket team experimented with a two-stage rocket called Bumper Wac, which intended to provide data for upper atmospheric research. On February 24, 1950, the Bumper, which employed a V-2 as the first stage with a Wac Corporal upper stage, obtained a peak altitude of more than 240 miles.

Dabrafenib, Trametinib, and Navitoclax in Treating Patients With BRAF Mutant Melanoma or Solid Tumors That Are Metastatic or Cannot Be Removed by Surgery

ClinicalTrials.gov

2018-05-21

BRAF V600E Mutation Present; BRAF V600K Mutation Present; Metastatic Melanoma; Solid Neoplasm; Stage III Cutaneous Melanoma AJCC v7; Stage IIIA Cutaneous Melanoma AJCC v7; Stage IIIB Cutaneous Melanoma AJCC v7; Stage IIIC Cutaneous Melanoma AJCC v7; Stage IV Cutaneous Melanoma AJCC v6 and v7

Talazoparib in Treating Patients With Advanced or Metastatic Solid Tumors That Cannot Be Removed by Surgery and Liver or Kidney Dysfunction

ClinicalTrials.gov

2017-04-20

Estrogen Receptor Negative; Head and Neck Squamous Cell Carcinoma; HER2/Neu Negative; Hormone-Resistant Prostate Cancer; Metastatic Pancreatic Adenocarcinoma; Progesterone Receptor Negative; Solid Neoplasm; Stage III Mesothelioma; Stage IIIA Gastric Cancer; Stage IIIA Non-Small Cell Lung Cancer; Stage IIIA Ovarian Cancer; Stage IIIA Small Cell Lung Carcinoma; Stage IIIB Gastric Cancer; Stage IIIB Non-Small Cell Lung Cancer; Stage IIIB Ovarian Cancer; Stage IIIB Small Cell Lung Carcinoma; Stage IIIC Gastric Cancer; Stage IIIC Ovarian Cancer; Stage IV Mesothelioma; Stage IV Non-Small Cell Lung Cancer; Stage IV Ovarian Cancer; Stage IV Small Cell Lung Carcinoma; Triple-Negative Breast Carcinoma

Upper Airway Collapsibility (Pcrit) and Pharyngeal Dilator Muscle Activity are Sleep Stage Dependent

PubMed Central

Carberry, Jayne C.; Jordan, Amy S.; White, David P.; Wellman, Andrew; Eckert, Danny J.

2016-01-01

Study Objectives: An anatomically narrow/highly collapsible upper airway is the main cause of obstructive sleep apnea (OSA). Upper airway muscle activity contributes to airway patency and, like apnea severity, can be sleep stage dependent. Conversely, existing data derived from a small number of participants suggest that upper airway collapsibility, measured by the passive pharyngeal critical closing pressure (Pcrit) technique, is not sleep stage dependent. This study aimed to determine the effect of sleep stage on Pcrit and upper airway muscle activity in a larger cohort than previously tested. Methods: Pcrit and/or muscle data were obtained from 72 adults aged 20–64 y with and without OSA.Pcrit was determined via transient reductions in continuous positive airway pressure (CPAP) during N2, slow wave sleep (SWS) and rapid eye movement (REM) sleep. Genioglossus and tensor palatini muscle activities were measured: (1) awake with and without CPAP, (2) during stable sleep on CPAP, and (3) in response to the CPAP reductions used to quantify Pcrit. Results: Pcrit was 4.9 ± 1.4 cmH2O higher (more collapsible) during REM versus SWS (P = 0.012), 2.3 ± 0.6 cmH2O higher during REM versus N2 (P < 0.001), and 1.6 ± 0.7 cmH2O higher in N2 versus SWS (P = 0.048). Muscle activity decreased from wakefulness to sleep and from SWS to N2 to REM sleep for genioglossus but not for tensor palatini. Pharyngeal muscle activity increased by ∼50% by breath 5 following CPAP reductions. Conclusions: Upper airway collapsibility measured via the Pcrit technique and genioglossus muscle activity vary with sleep stage. These findings should be taken into account when performing and interpreting “passive” Pcrit measurements. Citation: Carberry JC, Jordan AS, White DP, Wellman A, Eckert DJ. Upper airway collapsibility (Pcrit) and pharyngeal dilator muscle activity are sleep stage dependent. SLEEP 2016;39(3):511–521. PMID:26612386

Waterhammer Modeling for the Ares I Upper Stage Reaction Control System Cold Flow Development Test Article

NASA Technical Reports Server (NTRS)

Williams, Jonathan H.

2010-01-01

The Upper Stage Reaction Control System provides three-axis attitude control for the Ares I launch vehicle during active Upper Stage flight. The system design must accommodate rapid thruster firing to maintain the proper launch trajectory and thus allow for the possibility to pulse multiple thrusters simultaneously. Rapid thruster valve closure creates an increase in static pressure, known as waterhammer, which propagates throughout the propellant system at pressures exceeding nominal design values. A series of development tests conducted in the fall of 2009 at Marshall Space Flight Center were performed using a water-flow test article to better understand fluid performance characteristics of the Upper Stage Reaction Control System. A subset of the tests examined waterhammer along with the subsequent pressure and frequency response in the flight-representative system and provided data to anchor numerical models. This thesis presents a comparison of waterhammer test results with numerical model and analytical results. An overview of the flight system, test article, modeling and analysis are also provided.

Waterhammer modeling for the Ares I Upper Stage Reaction Control System cold flow development test article

NASA Astrophysics Data System (ADS)

Williams, Jonathan Hunter

The Upper Stage Reaction Control System provides in-flight three-axis attitude control for the Ares I Upper Stage. The system design must accommodate rapid thruster firing to maintain proper launch trajectory and thus allow for the possibility to pulse multiple thrusters simultaneously. Rapid thruster valve closure creates an increase in static pressure, known as waterhammer, which propagates throughout the propellant system at pressures exceeding nominal design values. A series of development tests conducted at Marshall Space Flight Center in 2009 were performed using a water-flow test article to better understand fluid characteristics of the Upper Stage Reaction Control System. A subset of the tests examined the waterhammer pressure and frequency response in the flight-representative system and provided data to anchor numerical models. This thesis presents a comparison of waterhammer test results with numerical model and analytical results. An overview of the flight system, test article, modeling and analysis are also provided.

Process for oil shale retorting using gravity-driven solids flow and solid-solid heat exchange

DOEpatents

Lewis, A.E.; Braun, R.L.; Mallon, R.G.; Walton, O.R.

1983-09-21

A cascading bed retorting process and apparatus are disclosed in which cold raw crushed shale enters at the middle of a retort column into a mixer stage where it is rapidly mixed with hot recycled shale and thereby heated to pyrolysis temperature. The heated mixture then passes through a pyrolyzer stage where it resides for a sufficient time for complete pyrolysis to occur. The spent shale from the pyrolyzer is recirculated through a burner stage where the residual char is burned to heat the shale which then enters the mixer stage.

Process for oil shale retorting using gravity-driven solids flow and solid-solid heat exchange

DOEpatents

Lewis, Arthur E.; Braun, Robert L.; Mallon, Richard G.; Walton, Otis R.

1986-01-01

A cascading bed retorting process and apparatus in which cold raw crushed shale enters at the middle of a retort column into a mixer stage where it is rapidly mixed with hot recycled shale and thereby heated to pyrolysis temperature. The heated mixture then passes through a pyrolyzer stage where it resides for a sufficient time for complete pyrolysis to occur. The spent shale from the pyrolyzer is recirculated through a burner stage where the residual char is burned to heat the shale which then enters the mixer stage.

Integrated process for the solvent refining of coal

DOEpatents

Garg, Diwakar

1983-01-01

A process is set forth for the integrated liquefaction of coal by the catalytic solvent refining of a feed coal in a first stage to liquid and solid products and the catalytic hydrogenation of the solid product in a second stage to produce additional liquid product. A fresh inexpensive, throw-away catalyst is utilized in the second stage hydrogenation of the solid product and this catalyst is recovered and recycled for catalyst duty in the solvent refining stage without any activation steps performed on the used catalyst prior to its use in the solvent refining of feed coal.

Veliparib in Combination With Carboplatin and Paclitaxel in Treating Patients With Locally Advanced or Metastatic Solid Tumors

ClinicalTrials.gov

2015-05-22

Adult Solid Neoplasm; Estrogen Receptor Negative; Estrogen Receptor Positive; HER2/Neu Negative; Male Breast Carcinoma; Progesterone Receptor Negative; Recurrent Breast Carcinoma; Stage IIIB Breast Cancer; Stage IIIC Breast Cancer; Stage IV Breast Cancer; Triple-Negative Breast Carcinoma

Subsystem Hazard Analysis Methodology for the Ares I Upper Stage Source Controlled Items

NASA Technical Reports Server (NTRS)

Mitchell, Michael S.; Winner, David R.

2010-01-01

This article describes processes involved in developing subsystem hazard analyses for Source Controlled Items (SCI), specific components, sub-assemblies, and/or piece parts, of the NASA ARES I Upper Stage (US) project. SCIs will be designed, developed and /or procured by Boeing as an end item or an off-the-shelf item. Objectives include explaining the methodology, tools, stakeholders and products involved in development of these hazard analyses. Progress made and further challenges in identifying potential subsystem hazards are also provided in an effort to assist the System Safety community in understanding one part of the ARES I Upper Stage project.

Multiple Removal of Spent Rocket Upper Stages with an Ion Beam Shepherd

NASA Astrophysics Data System (ADS)

Bombardelli, C.; Herrera-Montojo, J.; Gonzalo, J. L.

2013-08-01

Among the many advantages of the recently proposed ion beam shepherd (IBS) debris removal technique is the capability to deal with multiple targets in a single mission. A preliminary analysis is here conducted in order to estimate the cost in terms of spacecraft mass and total mission time to remove multiple large-size upper stages of the Zenit family. Zenit-2 upper stages are clustered at 71 degrees inclination around 850 km altitude in low Earth orbit. It is found that a removal of two targets per year is feasible with a modest size spacecraft. The most favorable combinations of targets are outlined.

Liquefaction of solid carbonaceous material with catalyst recycle

DOEpatents

Gupta, Avinash; Greene, Marvin I.

1992-01-01

In the two stage liquefaction of a carbonaceous solid such as coal wherein coal is liquefied in a first stage in the presence of a liquefaction solvent and the first stage effluent is hydrogenated in the presence of a supported hydrogenation catalyst in a second stage, catalyst which has been previously employed in the second stage and comminuted to a particle size distribution equivalent to 100% passing through U.S. 100 Mesh, is passed to the first stage to improve the overall operation.

A Comparison of Modeled and Observed Ocean Mixed Layer Behavior in a Sea Breeze Influenced Coastal Region

DTIC Science & Technology

1993-12-21

Latent(Lower Solid), Net Infrared (Dashed), and Net viii Heat Loss (Upper Solid - the Other 3 Surmmed) are Plotted, with Positive Values :ndicating...gained from solar insolation, Qs, and the heat lost from the surface due to latent, Qe, sensible, Qh, and net infrared radiation, Qb is positive...five empirically derived dimensionless constants in the model. With the introduction of two new unknowns, <E> and < ww2 >, the prediction of the upper

Veliparib and Irinotecan Hydrochloride in Treating Patients With Cancer That Is Metastatic or Cannot Be Removed by Surgery

ClinicalTrials.gov

2018-04-12

Advanced Malignant Solid Neoplasm; Estrogen Receptor Negative; HER2/Neu Negative; Hodgkin Lymphoma; Metastatic Malignant Neoplasm; Metastatic Malignant Solid Neoplasm; Non-Hodgkin Lymphoma; Progesterone Receptor Negative; Stage III Breast Cancer AJCC v7; Stage III Colon Cancer AJCC v7; Stage III Lung Cancer AJCC v7; Stage III Ovarian Cancer AJCC v6 and v7; Stage III Pancreatic Cancer AJCC v6 and v7; Stage IIIA Breast Cancer AJCC v7; Stage IIIA Colon Cancer AJCC v7; Stage IIIA Ovarian Cancer AJCC v6 and v7; Stage IIIB Breast Cancer AJCC v7; Stage IIIB Colon Cancer AJCC v7; Stage IIIB Ovarian Cancer AJCC v6 and v7; Stage IIIC Breast Cancer AJCC v7; Stage IIIC Colon Cancer AJCC v7; Stage IIIC Ovarian Cancer AJCC v6 and v7; Stage IV Breast Cancer AJCC v6 and v7; Stage IV Colon Cancer AJCC v7; Stage IV Lung Cancer AJCC v7; Stage IV Ovarian Cancer AJCC v6 and v7; Stage IV Pancreatic Cancer AJCC v6 and v7; Stage IVA Colon Cancer AJCC v7; Stage IVB Colon Cancer AJCC v7; Triple-Negative Breast Carcinoma; Unresectable Malignant Neoplasm; Unresectable Solid Neoplasm

Pembrolizumab and Ziv-aflibercept in Treating Patients With Advanced Solid Tumors

ClinicalTrials.gov

2018-03-08

Adult Solid Neoplasm; Metastatic Melanoma; Metastatic Renal Cell Cancer; Recurrent Colorectal Carcinoma; Recurrent Melanoma; Recurrent Ovarian Carcinoma; Recurrent Renal Cell Carcinoma; Stage IV Ovarian Cancer AJCC v6 and v7; Stage IVA Colorectal Cancer AJCC v7; Stage IVB Colorectal Cancer AJCC v7

Characterization and migration of oil and solids in oily sludge during centrifugation.

PubMed

Wang, Jun; Han, Xu; Huang, Qunxing; Ma, Zengyi; Chi, Yong; Yan, Jianhua

2018-05-01

The migration behaviors of oil, water and solids in sludge during centrifugation were elaborated. Size distribution, surface topography and lypohydrophilic properties were studied in detail. The average size of solids was 61 μm in original sludge, 31 μm in upper layer and 235 μm in bottom layer. The result shows that solvent is essential to separate oil phase into molecular light and weight fractions during centrifugation. With solvent/oil ratio increases from 1:2, 1:1, 2:1 to 5:1, molecular weight in upper layer decreases from 1044, 1043, 1020 to 846 combined with that in bottom layer increases. A model was proposed to calculate the oil residue content in solid phases after sedimentation. The findings of this paper provide information for optimizing the oil recovery and clean treatment.

Mars Exploration Rover -2

NASA Image and Video Library

2003-03-06

In the Payload Hazardous Servicing Facility resides one of the Mars Exploration Rovers, MER-2. MER-1 and MER-2, their aeroshells and landers will undergo a full mission simulation before being integrated. After spin balance testing, each spacecraft will be mated to a solid propellant upper stage booster that will propel the spacecraft out of Earth orbit. Approximately 10 days before launch they will be transported to the launch pad for mating with their respective Boeing Delta II rockets. The rovers will serve as robotic geologists to seek answers about the evolution of Mars, particularly for a history of water. The rovers are identical to each other, but will land at different regions of Mars. Launch of the first rover is scheduled for May 30 from Cape Canaveral Air Force Station. The second will follow June 25.

Mars Exploration Rover -2

NASA Image and Video Library

2003-03-06

Technicians in the Payload Hazardous Servicing Facility look over the Mars Exploration Rover -2. MER-1 and MER-2, their aeroshells and landers will undergo a full mission simulation before being integrated. After spin balance testing, each spacecraft will be mated to a solid propellant upper stage booster that will propel the spacecraft out of Earth orbit. Approximately 10 days before launch they will be transported to the launch pad for mating with their respective Boeing Delta II rockets. The rovers will serve as robotic geologists to seek answers about the evolution of Mars, particularly for a history of water. The rovers are identical to each other, but will land at different regions of Mars. Launch of the first rover is scheduled for May 30 from Cape Canaveral Air Force Station. The second will follow June 25.

Ground-water quality of the surficial aquifer system and the upper Floridan Aquifer, Ocala National Forest and Lake County, Florida, 1990-99

USGS Publications Warehouse

Adamski, J.C.; Knowles, Leel

2001-01-01

Data from 217 ground-water samples were statistically analyzed to assess the water quality of the surficial aquifer system and Upper Floridan aquifer in the Ocala National Forest and Lake County, Florida. Samples were collected from 49 wells tapping the surficial aquifer system, 141 wells tapping the Upper Floridan aquifer, and from 27 springs that discharge water from the Upper Floridan aquifer. A total of 136 samples was collected by the U.S. Geological Survey from 1995 through 1999. These data were supplemented with 81 samples collected by the St. Johns River Water Management District and Lake County Water Resources Management from 1990 through 1998. In general, the surficial aquifer system has low concentrations of total dissolved solids (median was 41 milligrams per liter) and major ions. Water quality of the surficial aquifer system, however, is not homogeneous throughout the study area. Concentrations of total dissolved solids, many major ions, and nutrients are greater in samples from Lake County outside the Ocala National Forest than in samples from within the Forest. These results indicate that the surficial aquifer system in Lake County outside the Ocala National Forest probably is being affected by agricultural and (or) urban land-use practices. High concentrations of dissolved oxygen (less than 0.1 to 8.2 milligrams per liter) in the surficial aquifer system underlying the Ocala National Forest indicate that the aquifer is readily recharged by precipitation and is susceptible to surface contamination. Concentrations of total dissolved solids were significantly greater in the Upper Floridan aquifer (median was 182 milligrams per liter) than in the surficial aquifer system. In general, water quality of the Upper Floridan aquifer was homogeneous, primarily being a calcium or calciummagnesium- bicarbonate water type. Near the St. Johns River, the water type of the Upper Floridan aquifer is sodium-chloride, corresponding to an increase in total dissolved solids. Dissolvedoxygen concentrations in the Upper Floridan aquifer ranged from less than 0.1 to 7.3 milligrams per liter, indicating that, in parts of the aquifer, ground water is rapidly recharged by rainfall and is susceptible to surface contamination. Median concentrations of nutrients in the Upper Floridan aquifer were not significantly different between the Ocala National Forest and the area of Lake County outside the Forest. The maximum nitrate concentration in the Upper Floridan aquifer in Ocala National Forest was only 0.20 milligram per liter, whereas, 9 of 39 samples from the Upper Floridan aquifer in Lake County had elevated nitrate concentrations (greater than 1.0 milligram per liter). Hence, nitrate concentrations of the Upper Floridan aquifer appear to be affected by land use in Lake County.

Head and neck cancer in transplant recipients.

PubMed

Deeb, Robert; Sharma, Saurabh; Mahan, Meredith; Al-Khudari, Samer; Hall, Francis; Yoshida, Atsushi; Schweitzer, Vanessa

2012-07-01

The development of malignancy in organ transplant patients is a well-known complication of long-term immunosuppressive therapy. We sought to characterize our institution's 20-year experience with head and neck cancer after solid organ transplantation. Retrospective review. Patients who underwent a solid organ transplant with subsequent development of a head and neck malignancy, including cutaneous and noncutaneous (upper aerodigestive tract and salivary gland) cancers, from January 1990 through December 2011 were identified. Patients were stratified according to cancer type, location, stage, and survival and compared to a nontransplant cohort in our institution's tumor registry. Of 95 patients identified, 17 had noncutaneous and 78 had cutaneous head and neck malignancies post-transplant. Among the noncutaneous group, no statistically significant differences occurred in age, gender, stage, or 5-year survival status when compared to the nontransplant tumor registry cohort. However, significantly fewer transplant patients were alive at 1 year. Among the cutaneous group, >50% had multiple malignancies. The total incidence of head and neck cancer following organ transplantation was 2.6%. Although the development of head and neck cancer is a rare side effect of immunosuppression, it still warrants attention. These patients have been found to be less likely to survive >1 year when compared to their nontransplant counterparts. Patients who develop head and neck malignancies following organ transplantation require aggressive screening, treatment, and follow-up, as this diagnosis may portend a poor prognosis. Copyright © 2012 The American Laryngological, Rhinological, and Otological Society, Inc.

ISRO's solid rocket motors

NASA Astrophysics Data System (ADS)

Nagappa, R.; Kurup, M. R.; Muthunayagam, A. E.

1989-08-01

Solid rocket motors have been the mainstay of ISRO's sounding rockets and the first generation satellite launch vehicles. For the new launch vehicle under development also, the solid rocket motors contribute significantly to the vehicle's total propulsive power. The rocket motors in use and under development have been developed for a variety of applications and range in size from 30 mm dia employing 450 g of solid propellant—employed for providing a spin to the apogee motors—to the giant 2.8 m dia motor employing nearly 130 tonnes of solid propellant. The initial development, undertaken in 1967 was of small calibre motor of 75 mm dia using a double base charge. The development was essentially to understand the technological elements. Extruded aluminium tubes were used as a rocket motor casing. The fore and aft closures were machined from aluminium rods. The grain was a seven-pointed star with an enlargement of the port at the aft end and was charged into the chamber using a polyester resin system. The nozzle was a metallic heat sink type with graphite throat insert. The motor was ignited with a black powder charge and fired for 2.0 s. Subsequent to this, further developmental activities were undertaken using PVC plastisol based propellants. A class of sounding rockets ranging from 125 to 560 mm calibre were realized. These rocket motors employed improved designs and had delivered lsp ranging from 2060 to 2256 Ns/kg. Case bonding could not be adopted due to the higher cure temperatures of the plastisol propellants but improvements were made in the grain charging techniques and in the design of the igniters and the nozzle. Ablative nozzles based on asbestos phenolic and silica phenolic with graphite inserts were used. For the larger calibre rocket motors, the lsp could be improved by metallic additives. In the early 1970s designs were evolved for larger and more efficient motors. A series of 4 motors for the country's first satellite launch vehicle SLV-3 were developed. The first and second stages of 1 and 0.8 m dia respectively used low carbon steel casing and PBAN propellant. The first stage used segmented construction with a total propellant weight of 8600 kg. The second stage employed about 3 tonnes of the same propellant. The third and fourth stages were of GFRP construction and employed respectively 1100 and 275 kg of CTPB type propellants. Nozzle expansion ratios upto 30 were employed and delivered vacuum lsp of 2766 Ns/kg realized. The fourth stage motor was subsequently used as the apogee motor for orbit injection of India's first geosynchronous satellite—APPLE. All these motors have been flight proven a number of times. Further design improvements have been incorporated and these motors continue to be in use. Starting in 1984 design for a large booster was undertaken. This booster employs a nominal propellant weight of 125 tonne in a 2.8 m dia casing. The motor is expected to be qualified for flight test in 1989. Side by side a high performance motor housing nearly 7 tonnes of propellant in composite casing of 2 m dia and having flex nozzle control system is also under development for upper stage application. Details of the development of the motors, their leading specifications and performance are described.

Carbon Dioxide Gas Sensors and Method of Manufacturing and Using Same

NASA Technical Reports Server (NTRS)

Liu, Chung Chiun (Inventor); Ward, Benjamin J. (Inventor); Hunter, Gary W. (Inventor); Xu, Jennifer C. (Inventor)

2011-01-01

A gas sensor includes a substrate and a pair of interdigitated metal electrodes selected from the group consisting of Pt, Pd, Au, Ir, Ag, Ru, Rh, In, and Os. The electrodes each include an upper surface. A first solid electrolyte resides between the interdigitated electrodes and partially engages the upper surfaces of the electrodes. The first solid electrolyte is selected from the group consisting of NASICON, LISICON, KSICON, and .beta.''-Alumina (beta prime-prime alumina in which when prepared as an electrolyte is complexed with a mobile ion selected from the group consisting of Na.sup.+, K.sup.+, Li.sup.+, Ag.sup.+, H.sup.+, Pb.sup.2+, Sr.sup.2+ or Ba.sup.2+). A second electrolyte partially engages the upper surfaces of the electrodes and engages the first solid electrolyte in at least one point. The second electrolyte is selected from the group of compounds consisting of Na.sup.+, K.sup.+, Li.sup.+, Ag.sup.+, H.sup.+, Pb.sup.2+, Sr.sup.2+ or Ba.sup.2+ ions or combinations thereof.

Forensic age estimation based on magnetic resonance imaging of third molars: converting 2D staging into 3D staging.

PubMed

De Tobel, Jannick; Hillewig, Elke; Verstraete, Koenraad

2017-03-01

Established methods to stage development of third molars for forensic age estimation are based on the evaluation of radiographs, which show a 2D projection. It has not been investigated whether these methods require any adjustments in order to apply them to stage third molars on magnetic resonance imaging (MRI), which shows 3D information. To prospectively study root stage assessment of third molars in age estimation using 3 Tesla MRI and to compare this with panoramic radiographs, in order to provide considerations for converting 2D staging into 3D staging and to determine the decisive root. All third molars were evaluated in 52 healthy participants aged 14-26 years using MRI in three planes. Three staging methods were investigated by two observers. In sixteen of the participants, MRI findings were compared with findings on panoramic radiographs. Decisive roots were palatal in upper third molars and distal in lower third molars. Fifty-seven per cent of upper third molars were not assessable on the radiograph, while 96.9% were on MRI. Upper third molars were more difficult to evaluate on radiographs than on MRI (p < .001). Lower third molars were equally assessable on both imaging techniques (93.8% MRI, 98.4% radiograph), with no difference in level of difficulty (p = .375). Inter- and intra-observer agreement for evaluation was higher in MRI than in radiographs. In both imaging techniques lower third molars showed greater inter- and intra-observer agreement compared to upper third molars. MR images in the sagittal plane proved to be essential for staging. In age estimation, 3T MRI of third molars could be valuable. Some considerations are, however, necessary to transfer known staging methods to this 3D technique.

Around Marshall

NASA Image and Video Library

2006-07-14

A model of the new Aries I crew launch vehicle, for which NASA is designing, testing and evaluating hardware and related systems, is seen here on display at the Marshall Space Fight Center (MSFC), in Huntsville, Alabama. The Ares I crew launch vehicle is the rocket that will carry a new generation of space explorers into orbit. Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA’s Constellation Program. These transportation systems will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is led by the Exploration Launch Projects Office at NASA’s MFSC. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module and a launch abort system. The launch vehicle’s first stage is a single, five-segment reusable solid rocket booster derived from the Space Shuttle Program’s reusable solid rocket motor that burns a specially formulated and shaped solid propellant called polybutadiene acrylonitrile (PBAN). The second or upper stage will be propelled by a J-2X main engine fueled with liquid oxygen and liquid hydrogen. In addition to its primary mission of carrying crews of four to six astronauts to Earth orbit, the launch vehicle’s 25-ton payload capacity might be used for delivering cargo to space, bringing resources and supplies to the International Space Station or dropping payloads off in orbit for retrieval and transport to exploration teams on the moon. Crew transportation to the space station is planned to begin no later than 2014. The first lunar excursion is scheduled for the 2020 timeframe.

KSC-07pd1638

NASA Image and Video Library

2007-06-26

KENNEDY SPACE CENTER, FLA. -- At Astrotech, technicians move the first segment of the lower canister around the upper stage booster below the Dawn spacecraft. When enclosed in the canister, Dawn will be transported to Launch Pad 17-B and lifted into the mobile service tower for mating with the Delta II launch vehicle. The Delta II-Heavy, manufactured by the United Launch Alliance, is scheduled to launch the Dawn spacecraft on its 4-year flight to the asteroid belt. The Delta II-Heavy will use three stages and nine solid-fueled booster rockets to propel Dawn on its way. A 9.5-foot payload fairing will protect the spacecraft from the heat and stresses of launch. Dawn's goal is to characterize the conditions and processes of the solar system's earliest epoch by investigating in detail the largest protoplanets that have remained intact since their formations: asteroid Vesta and the dwarf planet Ceres. They reside in the extensive zone between Mars and Jupiter together with many other smaller bodies, called the asteroid belt. Dawn is scheduled to launch July 7. Photo credit: NASA/George Shelton

KSC-07pd1641

NASA Image and Video Library

2007-06-26

KENNEDY SPACE CENTER, FLA. -- At Astrotech, technicians place another segment of the canister around the upper stage booster below the Dawn spacecraft. When enclosed in the canister, Dawn will be transported to Launch Pad 17-B and lifted into the mobile service tower for mating with the Delta II launch vehicle. The Delta II-Heavy, manufactured by the United Launch Alliance, is scheduled to launch the Dawn spacecraft on its 4-year flight to the asteroid belt. The Delta II-Heavy will use three stages and nine solid-fueled booster rockets to propel Dawn on its way. A 9.5-foot payload fairing will protect the spacecraft from the heat and stresses of launch. Dawn's goal is to characterize the conditions and processes of the solar system's earliest epoch by investigating in detail the largest protoplanets that have remained intact since their formations: asteroid Vesta and the dwarf planet Ceres. They reside in the extensive zone between Mars and Jupiter together with many other smaller bodies, called the asteroid belt. Dawn is scheduled to launch July 7. Photo credit: NASA/George Shelton

KSC-07pd1639

NASA Image and Video Library

2007-06-26

KENNEDY SPACE CENTER, FLA. -- At Astrotech, technicians move the first segment of the lower canister around the upper stage booster below the Dawn spacecraft. When enclosed in the canister, Dawn will be transported to Launch Pad 17-B and lifted into the mobile service tower for mating with the Delta II launch vehicle. The Delta II-Heavy, manufactured by the United Launch Alliance, is scheduled to launch the Dawn spacecraft on its 4-year flight to the asteroid belt. The Delta II-Heavy will use three stages and nine solid-fueled booster rockets to propel Dawn on its way. A 9.5-foot payload fairing will protect the spacecraft from the heat and stresses of launch. Dawn's goal is to characterize the conditions and processes of the solar system's earliest epoch by investigating in detail the largest protoplanets that have remained intact since their formations: asteroid Vesta and the dwarf planet Ceres. They reside in the extensive zone between Mars and Jupiter together with many other smaller bodies, called the asteroid belt. Dawn is scheduled to launch July 7. Photo credit: NASA/George Shelton

KSC-03pd0537

NASA Image and Video Library

2003-02-24

KENNEDY SPACE CENTER, FLA. -- The cruise stage, aeroshell and lander for the Mars Exploration Rover-1 mission and the MER-2 rover arrive at KSC's Multi-Payload Processing Facility. The same flight hardware for the MER-2 rover arrived Jan. 27; however, the MER-2 rover is scheduled to arrive at KSC in March. While at KSC, each of the two rovers, the aeroshells and the landers will undergo a full mission simulation. All of these flight elements will then be integrated together. After spin balance testing, each spacecraft will be mated to a solid propellant upper stage booster that will propel the spacecraft out of Earth orbit. Approximately 10 days before launch they will be transported to the launch pad for mating with their respective Boeing Delta II rockets. The rovers will serve as robotic geologists to seek answers about the evolution of Mars, particularly for a history of water. The rovers will be identical to each other, but will land at different regions of Mars. Launch of the MER-1 is scheduled for May 30. MER-2 will follow June 25.

The potential value of employing a RLV-based ``pop-up'' trajectory approach for space access

NASA Astrophysics Data System (ADS)

Nielsen, Edward; O'Leary, Robert

1997-01-01

This paper presents the potential benefits of employing useful upper stages with planned reusable launch vehicle systems to increase payload performance to various earth orbits. It highlights these benefits through performance analysis on a generic vehicle/upper-stage combination (basing all estimates on realistic technology availability). A nominal 34,019 kg [75,000 lbm] dry mass RLV capable of orbiting 454 kg into a polar orbit by itself (SSTO) would be capable of orbiting 9500-10,000 kg into a polar orbit using a nominal upper stage released from a suborbital trajectory. The paper also emphasizes the technical and operational issues associated with actually executing a ``pop-up'' trajectory launch and deployment.

Integrated System Test Approaches for the NASA Ares I Crew Launch Vehicle

NASA Technical Reports Server (NTRS)

Cockrell, Charles E., Jr.; Askins, Bruce R.; Bland, Jeffrey; Davis, Stephan; Holladay, Jon B.; Taylor, James L.; Taylor, Terry L.; Robinson, Kimberly F.; Roberts, Ryan E.; Tuma, Margaret

2007-01-01

The Ares I Crew Launch Vehicle (CLV) is being developed by the U.S. National Aeronautics and Space Administration (NASA) to provide crew access to the International Space Station (ISS) and, together with the Ares V Cargo Launch Vehicle (CaLV), serves as one component of a future launch capability for human exploration of the Moon. During the system requirements definition process and early design cycles, NASA defined and began implementing plans for integrated ground and flight testing necessary to achieve the first human launch of Ares I. The individual Ares I flight hardware elements: the first stage five segment booster (FSB), upper stage, and J-2X upper stage engine, will undergo extensive development, qualification, and certification testing prior to flight. Key integrated system tests include the Main Propulsion Test Article (MPTA), acceptance tests of the integrated upper stage and upper stage engine assembly, a full-scale integrated vehicle dynamic test (IVDT), aerodynamic testing to characterize vehicle performance, and integrated testing of the avionics and software components. The Ares I-X development flight test will provide flight data to validate engineering models for aerodynamic performance, stage separation, structural dynamic performance, and control system functionality. The Ares I-Y flight test will validate ascent performance of the first stage, stage separation functionality, and a highaltitude actuation of the launch abort system (LAS) following separation. The Orion-1 flight test will be conducted as a full, un-crewed, operational flight test through the entire ascent flight profile prior to the first crewed launch.

Materials, Processes and Manufacturing in Ares 1 Upper Stage: Integration with Systems Design and Development

NASA Technical Reports Server (NTRS)

Bhat, Biliyar N.

2008-01-01

Ares I Crew Launch Vehicle Upper Stage is designed and developed based on sound systems engineering principles. Systems Engineering starts with Concept of Operations and Mission requirements, which in turn determine the launch system architecture and its performance requirements. The Ares I-Upper Stage is designed and developed to meet these requirements. Designers depend on the support from materials, processes and manufacturing during the design, development and verification of subsystems and components. The requirements relative to reliability, safety, operability and availability are also dependent on materials availability, characterization, process maturation and vendor support. This paper discusses the roles and responsibilities of materials and manufacturing engineering during the various phases of Ares IUS development, including design and analysis, hardware development, test and verification. Emphasis is placed how materials, processes and manufacturing support is integrated over the Upper Stage Project, both horizontally and vertically. In addition, the paper describes the approach used to ensure compliance with materials, processes, and manufacturing requirements during the project cycle, with focus on hardware systems design and development.

Solid Lymph Nodes as an Imaging Biomarker for Risk Stratification in Human Papillomavirus-Related Oropharyngeal Squamous Cell Carcinoma.

PubMed

Rath, T J; Narayanan, S; Hughes, M A; Ferris, R L; Chiosea, S I; Branstetter, B F

2017-07-01

Human papillomavirus-related oropharyngeal squamous cell carcinoma is associated with cystic lymph nodes on CT and has a favorable prognosis. A subset of patients with aggressive disease experience treatment failure. Our aim was to determine whether the extent of cystic lymph node burden on staging CT can serve as an imaging biomarker to predict treatment failure in human papillomavirus-related oropharyngeal squamous cell carcinoma. We identified patients with human papilloma virus-related oropharyngeal squamous cell carcinoma and staging neck CTs. Demographic and clinical variables were recorded. We retrospectively classified the metastatic lymph node burden on CT as cystic or solid and assessed radiologic extracapsular spread. Biopsy, subsequent imaging, or clinical follow-up was the reference standard for treatment failure. The primary end point was disease-free survival. Cox proportional hazard regression analyses of clinical, demographic, and anatomic variables for treatment failure were performed. One hundred eighty-three patients were included with a mean follow-up of 38 months. In univariate analysis, the following variables had a statistically significant association with treatment failure: solid-versus-cystic lymph nodes, clinical T-stage, clinical N-stage, and radiologic evidence of extracapsular spread. The multivariate Cox proportional hazard model resulted in a model that included solid-versus-cystic lymph nodes, T-stage, and radiologic evidence of extracapsular spread as independent predictors of treatment failure. Patients with cystic nodal metastasis at staging had significantly better disease-free survival than patients with solid lymph nodes. In human papilloma virus-related oropharyngeal squamous cell carcinoma, patients with solid lymph node metastases are at higher risk for treatment failure with worse disease-free survival. Solid lymph nodes may serve as an imaging biomarker to tailor individual treatment regimens. © 2017 by American Journal of Neuroradiology.

Conceptual design of two-stage-to-orbit hybrid launch vehicle

NASA Technical Reports Server (NTRS)

1991-01-01

The object of this design class was to design an earth-to orbit vehicle to replace the present NASA space shuttle. The major motivations for designing a new vehicle were to reduce the cost of putting payloads into orbit and to design a vehicle that could better service the space station with a faster turn-around time. Another factor considered in the design was that near-term technology was to be used. Materials, engines and other important technologies were to be realized in the next 10 to 15 years. The first concept put forth by NASA to meet these objectives was the National Aerospace Plane (NASP). The NASP is a single-stage earth-to-orbit air-breathing vehicle. This concept ran into problems with the air-breathing engine providing enough thrust in the upper atmosphere, among other things. The solution of this design class is a two-stage-to-orbit vehicle. The first stage is air-breathing and the second stage is rocket-powered, similar to the space shuttle. The second stage is mounted on the top of the first stage in a piggy-back style. The vehicle takes off horizontally using only air-breathing engines, flies to Mach six at 100,000 feet, and launches the second stage towards its orbital path. The first stage, or booster, will weigh approximately 800,000 pounds and the second stage, or orbiter will weigh approximately 300,000 pounds. The major advantage of this design is the full recoverability of the first stage compared with the present solid rocket booster that are only partially recoverable and used only a few times. This reduces the cost as well as providing a more reliable and more readily available design for servicing the space station. The booster can fly an orbiter up, turn around, land, refuel, and be ready to launch another orbiter in a matter of hours.

Questionnaires in Identifying Upper Extremity Function and Quality of Life After Treatment in Patients With Breast Cancer

ClinicalTrials.gov

2017-04-11

Musculoskeletal Complication; Recurrent Breast Carcinoma; Stage IA Breast Cancer; Stage IB Breast Cancer; Stage IIA Breast Cancer; Stage IIB Breast Cancer; Stage IIIA Breast Cancer; Stage IIIB Breast Cancer; Stage IIIC Breast Cancer; Stage IV Breast Cancer; Therapy-Related Toxicity

Polar Satellite Launch Vehicle (PSLV) development programme in India

NASA Astrophysics Data System (ADS)

Janardhana, E.

The design of the Indian Polar Satellite Launch Vehicle (PSLV), for the launching (by 1990) of 1-1.5-tonne payloads into 900-km sun-synchronous orbit, is discussed, and the mission development program is described. The first stage is a solid propellant motor augmented by six solid strap-ons, and the second stage of liquid storable propellant has a high thrust gimballed engine. A high performance solid motor incorporates a flex nozzle for control as the third stage, and the fourth stage is a liquid propulsion system using N204 and MMH propellant with two regeneratively cooled engines. The vehicle equipment bay, housing the inertial guidance and control system, and the TTC system are located around the fourth stage for guidance and tracking with the associated ground segment until spacecraft ejection into orbit.

FDG-PET/CT Limited to the Thorax and Upper Abdomen for Staging and Management of Lung Cancer.

PubMed

Arens, Anne I J; Postema, Jan W A; Schreurs, Wendy M J; Lafeber, Albert; Hendrickx, Baudewijn W; Oyen, Wim J G; Vogel, Wouter V

2016-01-01

This study evaluates the diagnostic accuracy of [F-18]-fluorodeoxyglucose-positron emission tomography/computed tomography (FDG-PET/CT) of the chest/upper abdomen compared to the generally performed scan from head to upper thighs, for staging and management of (suspected) lung cancer in patients with no history of malignancy or complaints outside the thorax. FDG-PET/CT scans of 1059 patients with suspected or recently proven lung cancer, with no history of malignancy or complaints outside the thorax, were analysed in a retrospective multi-centre trial. Suspect FDG-avid lesions in the chest and upper abdomen, the head and neck area above the shoulder line and in the abdomen and pelvis below the caudal tip of the liver were noted. The impact of lesions detected in the head and neck area and abdomen and pelvis on additional diagnostic procedures, staging and treatment decisions was evaluated. The head and neck area revealed additional suspect lesions in 7.2%, and the abdomen and pelvis in 15.8% of patients. Imaging of the head and neck area and the abdomen and pelvic area showed additional lesions in 19.5%, inducing additional diagnostic procedures in 7.8%. This resulted in discovery of additional lesions considered malignant in 10.7%, changing patient management for lung cancer in 1.2%. In (suspected) lung cancer, PET/CT limited to the chest and upper abdomen resulted in correct staging in 98.7% of patients, which led to the identical management as full field of view PET in 98.8% of patients. High value of FDG-PET/CT for staging and correct patient management is already achieved with chest and upper abdomen. Findings in head and neck area and abdomen and pelvis generally induce investigations with limited or no impact on staging and treatment of NSCLC, and can be interpreted accordingly.

Maturation of enabling technologies for the next generation reignitable cryogenic upper stage

NASA Astrophysics Data System (ADS)

Mueller, Mark

Following the ESA decision in November 2008, a pre-development phase (Phase 1) of a future evolution of the Ariane 5 launcher (named Ariane 5 Midlife Evolution, A5ME) was started under Astrium Prime leadership. This upgraded version of the Ariane 5 launcher is based on an enhanced performance Upper Stage including the cryogenic re-ignitable VINCI engine. Thanks to this reignition capability, this new Upper Stage shall be "versatile" in the sense that it shall fulfil customer needs on a broader spectrum of orbits than the "standard" orbits (i.e. Geosynchronous Transfer Orbits, GTO) typically used for commercial telecommunications satellites. In order to meet the challenges of versatility, new technologies are currently being investigated. These technologies are mainly related -but not limited-to propellant management during the extended coasting phases with the related heat transfer into the tanks and the required multiple engine re-ignitions. Within the frame of the ESA Future Launchers Preparatory Programme (Period 2 Slice 1), the Cryogenic Upper Stage Technology project (CUST) aims to mature critical technologies to such a Technology Readiness Level (TRL) that they can be integrated into the baseline A5ME Upper Stage development schedule. In addition to A5ME application, these technologies can also be used on the future next generation European launcher. This paper shows the down-selection process implemented to identify the most crucial enabling technologies for a future versatile Upper Stage and gives a description of each technology finally selected for maturation in the frame of CUST. These include -amongst others-a Sandwich Common Bulkhead for the propellant tank, an external thermal insulation kit and various propellant management devices for the coasting phase. The paper also gives an overview on the related development and maturation plan including the tests to be conducted, as well as first results of the maturation activities themselves.

Hydrodynamic instability of elastic-plastic solid plates at the early stage of acceleration.

PubMed

Piriz, A R; Sun, Y B; Tahir, N A

2015-03-01

A model is presented for the linear Rayleigh-Taylor instability taking place at the early stage of acceleration of an elastic-plastic solid, when the shock wave is still running into the solid and is driven by a time varying pressure on the interface. When the the shock is formed sufficiently close to the interface, this stage is considered to follow a previous initial phase controlled by the Ritchmyer-Meshkov instability that settles new initial conditions. The model reproduces the behavior of the instability observed in former numerical simulation results and provides a relatively simpler physical picture than the currently existing one for this stage of the instability evolution.

Everolimus and Vatalanib in Treating Patients With Advanced Solid Tumors

ClinicalTrials.gov

2018-01-12

Gastrinoma; Glucagonoma; Insulinoma; Metastatic Gastrointestinal Carcinoid Tumor; Metastatic Pheochromocytoma; Pancreatic Polypeptide Tumor; Recurrent Gastrointestinal Carcinoid Tumor; Recurrent Islet Cell Carcinoma; Recurrent Melanoma; Recurrent Neuroendocrine Carcinoma of the Skin; Recurrent Non-small Cell Lung Cancer; Recurrent Pheochromocytoma; Recurrent Renal Cell Cancer; Somatostatinoma; Stage III Neuroendocrine Carcinoma of the Skin; Stage IV Melanoma; Stage IV Non-small Cell Lung Cancer; Stage IV Renal Cell Cancer; Thyroid Gland Medullary Carcinoma; Unspecified Adult Solid Tumor, Protocol Specific

Erdafitinib in Treating Patients With Relapsed or Refractory Advanced Solid Tumors, Non-Hodgkin Lymphoma, or Histiocytic Disorders With FGFR Mutations (A Pediatric MATCH Treatment Trial)

ClinicalTrials.gov

2018-06-25

Advanced Malignant Solid Neoplasm; Ann Arbor Stage III Childhood Non-Hodgkin Lymphoma; Ann Arbor Stage IV Childhood Non-Hodgkin Lymphoma; FGFR1 Gene Mutation; FGFR2 Gene Mutation; FGFR3 Gene Mutation; FGFR4 Gene Mutation; Histiocytosis; Low Grade Glioma; Malignant Glioma; Recurrent Central Nervous System Neoplasm; Recurrent Childhood Ependymoma; Recurrent Childhood Malignant Germ Cell Tumor; Recurrent Childhood Medulloblastoma; Recurrent Childhood Non-Hodgkin Lymphoma; Recurrent Childhood Rhabdomyosarcoma; Recurrent Childhood Soft Tissue Sarcoma; Recurrent Ewing Sarcoma/Peripheral Primitive Neuroectodermal Tumor; Recurrent Hepatoblastoma; Recurrent Langerhans Cell Histiocytosis; Recurrent Malignant Solid Neoplasm; Recurrent Neuroblastoma; Recurrent Osteosarcoma; Refractory Central Nervous System Neoplasm; Refractory Langerhans Cell Histiocytosis; Refractory Malignant Solid Neoplasm; Refractory Neuroblastoma; Refractory Non-Hodgkin Lymphoma; Rhabdoid Tumor; Stage III Soft Tissue Sarcoma AJCC v7; Stage IV Soft Tissue Sarcoma AJCC v7; Wilms Tumor

Lessons Learned from Ares I Upper Stage Structures and Thermal Design

NASA Technical Reports Server (NTRS)

Ahmed, Rafiq

2012-01-01

The Ares 1 Upper Stage was part of the vehicle intended to succeed the Space Shuttle as the United States manned spaceflight vehicle. Although the Upper Stage project was cancelled, there were many lessons learned that are applicable to future vehicle design. Lessons learned that are briefly detailed in this Technical Memorandum are for specific technical areas such as tank design, common bulkhead design, thrust oscillation, control of flight and slosh loads, purge and hazardous gas system. In addition, lessons learned from a systems engineering and vehicle integration perspective are also included, such as computer aided design and engineering, scheduling, and data management. The need for detailed systems engineering in the early stages of a project is emphasized throughout this report. The intent is that future projects will be able to apply these lessons learned to keep costs down, schedules brief, and deliver products that perform to the expectations of their customers.

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.

Hot-Fire Test of Liquid Oxygen/Hydrogen Space Launch Mission Injector Applicable to Exploration Upper Stage

NASA Technical Reports Server (NTRS)

Barnett, Greg; Turpin, Jason; Nettles, Mindy

2015-01-01

This task is to hot-fire test an existing Space Launch Mission (SLM) injector that is applicable for all expander cycle engines being considered for the exploration upper stage. The work leverages investment made in FY 2013 that was used to additively manufacture three injectors (fig. 1) all by different vendors..

The Peroxide Pathway

NASA Technical Reports Server (NTRS)

McNeal, Curtis I., Jr.; Anderson, William

1999-01-01

NASA's current focus on technology roadmaps as a tool for guiding investment decisions leads naturally to a discussion of NASA's roadmap for peroxide propulsion system development. NASA's new Second Generation Space Transportation System roadmap calls for an integrated Reusable Upper-Stage (RUS) engine technology demonstration in the FY03/FY04 time period. Preceding this integrated demonstration are several years of component developments and subsystem technology demonstrations. NASA and the Air Force took the first steps at developing focused upper stage technologies with the initiation of the Upper Stage Flight Experiment with Orbital Sciences in December 1997. A review of this program's peroxide propulsion development is a useful first step in establishing the peroxide propulsion pathway that could lead to a RUS demonstration in 2004.

SLS Block 1-B and Exploration Upper Stage Navigation System Design

NASA Technical Reports Server (NTRS)

Oliver, T. Emerson; Park, Thomas B.; Smith, Austin; Anzalone, Evan; Bernard, Bill; Strickland, Dennis; Geohagan, Kevin; Green, Melissa; Leggett, Jarred

2018-01-01

The SLS Block 1B vehicle is planned to extend NASA's heavy lift capability beyond the initial SLS Block 1 vehicle. The most noticeable change for this vehicle from SLS Block 1 is the swapping of the upper stage from the Interim Cryogenic Propulsion stage (ICPS), a modified Delta IV upper stage, to the more capable Exploration Upper Stage (EUS). As the vehicle evolves to provide greater lift capability and execute more demanding missions so must the SLS Integrated Navigation System to support those missions. The SLS Block 1 vehicle carries two independent navigation systems. The responsibility of the two systems is delineated between ascent and upper stage flight. The Block 1 navigation system is responsible for the phase of flight between the launch pad and insertion into Low-Earth Orbit (LEO). The upper stage system assumes the mission from LEO to payload separation. For the Block 1B vehicle, the two functions are combined into a single system intended to navigate from ground to payload insertion. Both are responsible for self-disposal once payload delivery is achieved. The evolution of the navigation hardware and algorithms from an inertial-only navigation system for Block 1 ascent flight to a tightly coupled GPS-aided inertial navigation system for Block 1-B is described. The Block 1 GN&C system has been designed to meet a LEO insertion target with a specified accuracy. The Block 1-B vehicle navigation system is designed to support the Block 1 LEO target accuracy as well as trans-lunar or trans-planetary injection accuracy. This is measured in terms of payload impact and stage disposal requirements. Additionally, the Block 1-B vehicle is designed to support human exploration and thus is designed to minimize the probability of Loss of Crew (LOC) through high-quality inertial instruments and Fault Detection, Isolation, and Recovery (FDIR) logic. The preliminary Block 1B integrated navigation system design is presented along with the challenges associated with meeting the design objectives. This paper also addresses the design considerations associated with the use of Block 1 and Commercial Off-the-Shelf (COTS) avionics for Block 1-B/EUS as part of an integrated vehicle suite for orbital operations.

KSC-08pd3464

NASA Image and Video Library

2008-10-30

CAPE CANAVERAL, Fla. – On Launch Pad 17-B at Cape Canaveral Air Force Station in Florida, workers on an upper level of the launch tower watch as a strap-on solid rocket booster is lifted into place to mate to the first stage of the Delta 2 launch vehicle that will carry the Kepler spacecraft into orbit. The Kepler mission is specifically designed to survey our region of the Milky Way galaxy to discover hundreds of Earth-size and smaller planets in or near the habitable zone and determine how many of the billions of stars in our galaxy have such planets. Results from this mission will allow us to place our solar system within the continuum of planetary systems in the Galaxy. NASA's planet-hunting Kepler mission is scheduled to launch no earlier than March 5, 2009. Photo credit: NASA/Jim Grossmann

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

Stanislav S. Gornostayev; Jouko J. Haerkki

Examinations of polished and dry cut sections of feed and tuyere coke revealed some possible mechanisms for the physical influence of mineral compounds on the reactivity and strength of coke. It was observed that rounded particles of mineral phases that are exposed to the pore walls and surface of coke at high temperature create an inorganic cover, thus reducing the surface available for gas-solid reactions. The particles of mineral matter that have a low melting point and viscosity can affect the coke at earlier stages in the blast furnace process, acting in the upper parts of the blast furnace (BF).more » The temperature-driven redistribution of mineral phases within the coke matrix probably leads to the creation of weak spots and in general to anisotropy in its properties, thus reducing its strength. 9 refs., 2 figs., 1 tab.« less

KSC-08pd3463

NASA Image and Video Library

2008-10-30

CAPE CANAVERAL, Fla. – On Launch Pad 17-B at Cape Canaveral Air Force Station in Florida, a view from an upper level of the launch tower show air-lit strap-on solid rocket boosters being added to the first stage of the Delta 2 launch vehicle that will carry the Kepler spacecraft into orbit. The Kepler mission is specifically designed to survey our region of the Milky Way galaxy to discover hundreds of Earth-size and smaller planets in or near the habitable zone and determine how many of the billions of stars in our galaxy have such planets. Results from this mission will allow us to place our solar system within the continuum of planetary systems in the Galaxy. NASA's planet-hunting Kepler mission is scheduled to launch no earlier than March 5, 2009. Photo credit: NASA/Jim Grossmann

Mars Exploration Rover -2

NASA Image and Video Library

2003-03-06

Technicians in the Payload Hazardous Servicing Facility work on components of the Mars Exploration Rovers. In the center is a lander. MER-1 and MER-2, their aeroshells and landers will undergo a full mission simulation before being integrated. After spin balance testing, each spacecraft will be mated to a solid propellant upper stage booster that will propel the spacecraft out of Earth orbit. Approximately 10 days before launch they will be transported to the launch pad for mating with their respective Boeing Delta II rockets. The rovers will serve as robotic geologists to seek answers about the evolution of Mars, particularly for a history of water. The rovers are identical to each other, but will land at different regions of Mars. Launch of the first rover is scheduled for May 30 from Cape Canaveral Air Force Station. The second will follow June 25.

STS-43 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W.

1991-01-01

The STS-43 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem operations during the forty-second flight of the Space Shuttle Program and the ninth flight of the Orbiter Vehicle Atlantis (OV-104). In addition to the Atlantis vehicle, the flight vehicle consisted of the following: an External Tank (ET) designated as ET-47 (LWT-40); three Space Shuttle main engines (SSME's) (serial numbers 2024, 2012, and 2028 in positions 1, 2, and 3, respectively); and two Solid Rocket Boosters (SRB's) designated as BI-045. The primary objective of the STS-43 mission was to successfully deploy the Tracking and Data Relay Satellite-E/Inertial Upper Stage (TDRS-E/IUS) satellite and to perform all operations necessary to support the requirements of the Shuttle Solar Backscatter Ultraviolet (SSBUV) payload and the Space Station Heat Pipe Advanced Radiator Element (SHARE-2).

STS-43 Space Shuttle mission report

NASA Astrophysics Data System (ADS)

Fricke, Robert W.

1991-09-01

The STS-43 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem operations during the forty-second flight of the Space Shuttle Program and the ninth flight of the Orbiter Vehicle Atlantis (OV-104). In addition to the Atlantis vehicle, the flight vehicle consisted of the following: an External Tank (ET) designated as ET-47 (LWT-40); three Space Shuttle main engines (SSME's) (serial numbers 2024, 2012, and 2028 in positions 1, 2, and 3, respectively); and two Solid Rocket Boosters (SRB's) designated as BI-045. The primary objective of the STS-43 mission was to successfully deploy the Tracking and Data Relay Satellite-E/Inertial Upper Stage (TDRS-E/IUS) satellite and to perform all operations necessary to support the requirements of the Shuttle Solar Backscatter Ultraviolet (SSBUV) payload and the Space Station Heat Pipe Advanced Radiator Element (SHARE-2).

Composting of sewage sludge with solid fraction of digested pulp from agricultural biogas plant

NASA Astrophysics Data System (ADS)

Czekała, Wojciech; Dach, Jacek; Przybył, Jacek; Mazurwiekiwcz, Jakub; Janczak, Damian; Lewicki, Andrzej; Smurzyńska, Anna; Kozłowski, Kamil

2018-02-01

Sewage sludge management is an important element of environmental protection. Composting and anaerobic digestion are the biological conversion methods for sewage sludge management. Mass and volume reduction is a result of a properly composted process. Solid fraction of digested pulp can be use as co-substrate, because it is good structural material. The aim of the study was to determine the possibility of composting sewage sludge with a solid fraction of digestate. The compost mix consisted of 25 kilograms of sewage sludge and 20 kilograms solid fraction of digestate in fresh mass. The experiment was carried out in laboratory conditions. Bioreactors of 165 dm3 volume were used. The experiment included two stages. Stage I took place in bioreactors and lasted until the cooling phase of the compost was complete. Stage II included compost maturation for a period of eight months (to 287 day of composting). The reduction of mass obtained at the end of Stage I amounted 30.2%. At the end of Stage II, it was 86.7% relative to the initial weight of the compost. The maximum value of temperature was 75.1°C. Studies have shown that sludge with a solid fraction of digestate can be a suitable substrate for composting with sewage sludge.

Early evolution and dynamics of Earth from a molten initial stage

NASA Astrophysics Data System (ADS)

Louro Lourenço, Diogo; Tackley, Paul J.

2016-04-01

It is now well established that most of the terrestrial planets underwent a magma ocean stage during their accretion. On Earth, it is probable that at the end of accretion, giant impacts like the hypothesised Moon-forming impact, together with other sources of heat, melted a substantial part of the mantle. The thermal and chemical evolution of the resulting magma ocean most certainly had dramatic consequences on the history of the planet. Considerable research has been done on magma oceans using simple 1-D models (e.g.: Abe, PEPI 1997; Solomatov, Treat. Geophys. 2007; Elkins-Tanton EPSL 2008). However, some aspects of the dynamics may not be adequately addressed in 1-D and require the use of 2-D or 3-D models. Moreover, new developments in mineral physics that indicate that melt can be denser than solid at high pressures (e.g.: de Koker et al., EPSL 2013) can have very important impacts on the classical views of the solidification of magma oceans (Labrosse et al., Nature 2007). The goal of our study is to understand and characterize the influence of melting on the long-term thermo-chemical evolution of rocky planet interiors, starting from an initial molten state (magma ocean). Our approach is to model viscous creep of the solid mantle, while parameterizing processes that involve melt as previously done in 1-D models, including melt-solid separation at all melt fractions, the use of an effective diffusivity to parameterize turbulent mixing, coupling to a parameterized core heat balance and a radiative surface boundary condition. These enhancements have been made to the numerical code StagYY (Tackley, PEPI 2008). We present results for the evolution of an Earth-like planet from a molten initial state to present day, while testing the effect of uncertainties in parameters such as melt-solid density differences, surface heat loss and efficiency of turbulent mixing. Our results show rapid cooling and crystallization until the rheological transition then much slower crystallization, large-scale overturn well before full solidification, the formation and subduction of an early crust while a partially-molten upper mantle is still present, transitioning to mostly-solid-state long-term mantle convection and plate tectonics or an episodic-lid regime.

Early evolution and dynamics of Earth from a molten initial stage

NASA Astrophysics Data System (ADS)

Lourenço, Diogo; Tackley, Paul

2015-04-01

It is now well established that most of the terrestrial planets underwent a magma ocean stage during their accretion. On Earth, it is probable that at the end of accretion, giant impacts like the hypothesised Moon-forming impact, together with other sources of heat, melted a substantial part of the mantle. The thermal and chemical evolution of the resulting magma ocean most certainly had dramatic consequences on the history of the planet. Considerable research has been done on magma oceans using simple 1-D models (e.g.: Abe, PEPI 1997; Solomatov, Treat. Geophys. 2007; Elkins-Tanton EPSL 2008). However, some aspects of the dynamics may not be adequately addressed in 1-D and require the use of 2-D or 3-D models. Moreover, new developments in mineral physics that indicate that melt can be denser than solid at high pressures (e.g.: de Koker et al., EPSL 2013) can have very important impacts on the classical views of the solidification of magma oceans (Labrosse et al., Nature 2007). The goal of our study is to understand and characterize the influence of melting on the long-term thermo-chemical evolution of rocky planet interiors, starting from an initial molten state (magma ocean). Our approach is to model viscous creep of the solid mantle, while parameterizing processes that involve melt as previously done in 1-D models, including melt-solid separation at all melt fractions, the use of an effective diffusivity to parameterize turbulent mixing, coupling to a parameterized core heat balance and a radiative surface boundary condition. These enhancements have been made to the numerical code StagYY (Tackley, PEPI 2008). We will present results for the evolution of an Earth-like planet from a molten initial state to present day, while testing the effect of uncertainties in parameters such as melt-solid density differences, surface heat loss and efficiency of turbulent mixing. Our results show rapid cooling and crystallization until the rheological transition then much slower crystallization, large-scale overturn well before full solidification, the formation and subduction of an early crust while a partially-molten upper mantle is still present, transitioning to mostly-solid-state long-term mantle convection and plate tectonics or an episodic-lid regime.

Evolution and dynamics of Earth from a molten initial stage

NASA Astrophysics Data System (ADS)

Louro Lourenço, D. J.; Tackley, P.

2016-12-01

It is now well established that most of the terrestrial planets underwent a magma ocean stage during their accretion. On Earth, it is probable that at the end of accretion, giant impacts like the hypothesised Moon-forming impact, together with other sources of heat, melted a substantial part of the mantle. The thermal and chemical evolution of the resulting magma ocean most certainly had dramatic consequences on the history of the planet. Considerable research has been done on magma oceans using simple 1-D models (e.g.: Abe, PEPI 1997; Solomatov, Treat. Geophys. 2007; Elkins-Tanton EPSL 2008). However, some aspects of the dynamics may not be adequately addressed in 1-D and require the use of 2-D or 3-D models. Moreover, new developments in mineral physics that indicate that melt can be denser than solid at high pressures (e.g.: de Koker et al., EPSL 2013) can have very important impacts on the classical views of the solidification of magma oceans (Labrosse et al., Nature 2007; Labrosse et al., The Early Earth 2015). The goal of our study is to understand and characterize the influence of melting on the long-term thermo-chemical evolution of rocky planet interiors, starting from an initial molten state (magma ocean). Our approach is to model viscous creep of the solid mantle, while parameterizing processes that involve melt as previously done in 1-D models, including melt-solid separation at all melt fractions, the use of an effective diffusivity to parameterize turbulent mixing, coupling to a parameterized core heat balance and a radiative surface boundary condition. These enhancements have been made to the numerical code StagYY (Tackley, PEPI 2008). We present results for the evolution of an Earth-like planet from a molten initial state to present day, while testing the effect of uncertainties in parameters such as melt-solid density differences, surface heat loss and efficiency of turbulent mixing. Our results show rapid cooling and crystallization until the rheological transition then much slower crystallization, large-scale overturn well before full solidification, the formation and subduction of an early crust while a partially-molten upper mantle is still present, transitioning to mostly-solid-state long-term mantle convection and plate tectonics or an episodic-lid regime.

Breast metastasis from cutaneous malignant melanoma mimicking a breast cancer.

PubMed

Maniglio, Marina; Capalbo, Emanuela; Viganò, Sara; Trecate, Giovanna; Scaperrotta, Gianfranco Paride; Panizza, Pietro

2015-06-25

Breast metastases are very uncommon, either from solid tumors or malignant melanoma. We present the case of a 42-year-old woman with a history of cutaneous melanoma of the shoulder excised 21 years ago. She presented with a palpable lump in the upper outer quadrant of the right breast. Ultrasound demonstrated a solid mass within a cystic lesion. A core biopsy was taken and first histology reported a poorly differentiated primary breast cancer suspected to be triple negative. MRI detected a satellite lesion in the same breast, a focus of suspected enhancement in the other breast, and the extramammary finding of an enhancing pulmonary lesion. Staging computed tomography detected widespread metastases to the lungs, brain, subcutaneous left shoulder, liver, pancreas, and hepatorenal recess. A core biopsy was taken from the left breast lesion and the previous slides were reviewed; histopathology and immunohistochemistry were in keeping with metastasis from melanoma. The possibility of a metastatic lesion to the breast should be taken into account in any patient presenting with a breast lump and a previous history of melanoma. Breast involvement cannot be considered an isolated finding, as it might be the first manifestation of widespread disease.

Electric Propulsion Upper-Stage for Launch Vehicle Capability Enhancement

NASA Technical Reports Server (NTRS)

Kemp, Gregory E.; Dankanich, John W.; Woodcock, Gordon R.; Wingo, Dennis R.

2007-01-01

The NASA In-Space Propulsion Technology Project Office initiated a preliminary study to evaluate the performance benefits of a solar electric propulsion (SEP) upper-stage with existing and near-term small launch vehicles. The analysis included circular and elliptical Low Earth Orbit (LEO) to Geosynchronous Earth Orbit (GEO) transfers, and LEO to Low Lunar Orbit (LLO) applications. SEP subsystem options included state-of-the-art and near-term solar arrays and electric thrusters. In-depth evaluations of the Aerojet BPT-4000 Hall thruster and NEXT gridded ion engine were conducted to compare performance, cost and revenue potential. Preliminary results indicate that Hall thruster technology is favored for low-cost, low power SEP stages, while gridded-ion engines are favored for higher power SEP systems unfettered by transfer time constraints. A low-cost point design is presented that details one possible stage configuration and outlines system limitations, in particular fairing volume constraints. The results demonstrate mission enhancements to large and medium class launch vehicles, and mission enabling performance when SEP system upper stages are mounted to low-cost launchers such as the Minotaur and Falcon 1. Study results indicate the potential use of SEP upper stages to double GEO payload mass capability and to possibly enable launch on demand capability for GEO assets. Transition from government to commercial applications, with associated cost/benefit analysis, has also been assessed. The sensitivity of system performance to specific impulse, array power, thruster size, and component costs are also discussed.

Effects of wearing rubber gloves on activities of the forearm and shoulder muscles during different dishwashing stages

PubMed Central

Yoo, Won-Gyu

2015-01-01

[Purpose] The present study examined the effects of wearing rubber gloves on the activities of the forearm and shoulder muscles during two dishwashing stages. [Subjects] This study included 10 young females. [Methods] The participants performed two dishwashing stages (washing and rinsing) with and without rubber gloves. The activities of the wrist flexor and upper trapezius muscles were measured using wireless electromyography. [Results] During the washing stage, the activities of the wrist flexor and upper trapezius muscles were significantly greater without gloves than with gloves when performing the same tasks. However, during the rinsing stage, the activities of these muscles did not differ significantly according to the use of gloves. [Conclusion] Dishwashers should wear gloves during the washing stage to prevent wrist and shoulder pain. PMID:26311980

NASA Ares I Crew Launch Vehicle Upper Stage Overview

NASA Technical Reports Server (NTRS)

Davusm Daniel J.; McArthur, J. Craig

2008-01-01

By incorporating rigorous engineering practices, innovative manufacturing processes and test techniques, a unique multi-center government/contractor partnership, and a clean-sheet design developed around the primary requirements for the International Space Station (ISS) and Lunar missions, the Upper Stage Element of NASA's Crew Launch Vehicle (CLV), the "Ares I," is a vital part of the Constellation Program's transportation system.

J-2X engine test

NASA Image and Video Library

2011-12-01

NASA conducted a key stability test firing of the J-2X rocket engine on the A-2 Test Stand at Stennis Space Center on Dec. 1, marking another step forward in development of the upper-stage engine that will carry humans deeper into space than ever before. The J-2X will provide upper-stage power for NASA's new Space Launch System.

Orbit decay analysis of STS upper stage boosters

NASA Technical Reports Server (NTRS)

Graf, O. F., Jr.; Mueller, A. C.

1979-01-01

An orbit decay analysis of the space transportation system upper stage boosters is presented. An overview of the computer trajectory programs, DSTROB, algorithm is presented. Atmospheric drag and perturbation models are described. The development of launch windows, such that the transfer orbit will decay within two years, is discussed. A study of the lifetimes of geosynchronous transfer orbits is presented.

Testing of Selective Laser Melting Turbomachinery Applicable to Exploration Upper Stage

NASA Technical Reports Server (NTRS)

Calvert, Marty; Turpin, Jason; Nettles, Mindy

2015-01-01

This task is to design, fabricate, and spin test to failure a Ti6-4 hydrogen turbopump impeller that was built using the selective laser melting (SLM) fabrication process (fig. 1). The impeller is sized around upper stage engine requirements. In addition to the spin burst test, material testing will be performed on coupons that are built with the impeller.

Development and Testing of Carbon-Carbon Nozzle Extensions for Upper Stage Liquid Rocket Engines

NASA Technical Reports Server (NTRS)

Valentine, Peter G.; Gradl, Paul R.; Greene, Sandra E.

2017-01-01

Carbon-carbon (C-C) composite nozzle extensions are of interest for use on a variety of launch vehicle upper stage engines and in-space propulsion systems. The C-C nozzle extension technology and test capabilities being developed are intended to support National Aeronautics and Space Administration (NASA) and Department of Defense (DOD) requirements, as well as those of the broader Commercial Space industry. For NASA, C-C nozzle extension technology development primarily supports the NASA Space Launch System (SLS) and NASA's Commercial Space partners. Marshall Space Flight Center (MSFC) efforts are aimed at both (a) further developing the technology and databases needed to enable the use of composite nozzle extensions on cryogenic upper stage engines, and (b) developing and demonstrating low-cost capabilities for testing and qualifying composite nozzle extensions. Recent, on-going, and potential future work supporting NASA, DOD, and Commercial Space needs will be discussed. Information to be presented will include (a) recent and on-going mechanical, thermal, and hot-fire testing, as well as (b) potential future efforts to further develop and qualify domestic C-C nozzle extension solutions for the various upper stage engines under development.

There Must Be A-Way (to Deal with Solid Waste).

ERIC Educational Resources Information Center

Fortner, Rosanne W.

1991-01-01

Presents a class project to help upper elementary students grasp the extent of the solid waste disposal problem and develop an individual response. Includes background information for the teacher, project objectives, materials, procedures, and a listing for additional resources. (MCO)

Intensity-Modulated Radiation Therapy in Treating Younger Patients With Lung Metastases

ClinicalTrials.gov

2013-09-23

Adult Rhabdomyosarcoma; Lung Metastases; Metastatic Ewing Sarcoma/Peripheral Primitive Neuroectodermal Tumor; Previously Treated Childhood Rhabdomyosarcoma; Recurrent Adult Soft Tissue Sarcoma; Recurrent Childhood Rhabdomyosarcoma; Recurrent Ewing Sarcoma/Peripheral Primitive Neuroectodermal Tumor; Recurrent Wilms Tumor and Other Childhood Kidney Tumors; Stage IV Adult Soft Tissue Sarcoma; Stage IV Wilms Tumor; Stage V Wilms Tumor; Unspecified Adult Solid Tumor, Protocol Specific; Unspecified Childhood Solid Tumor, Protocol Specific

Advanced Concept

NASA Image and Video Library

2008-03-15

Shown is an illustration of the Ares I concept. The first stage will be a single, five-segment solid rocket booster derived from the space shuttle programs reusable solid rocket motor. The first stage is managed by NASA's Marshall Space Flight Center in Huntsville, Alabama for NASA's Constellation program.

Development of an Interactive Shoreline Management Tool for the Lower Wood River Valley, Oregon - Phase I: Stage-Volume and Stage-Area Relations

USGS Publications Warehouse

Haluska, Tana L.; Snyder, Daniel T.

2007-01-01

This report presents the parcel and inundation area geographic information system (GIS) layers for various surface-water stages. It also presents data tables containing the water stage, inundation area, and water volume relations developed from analysis of detailed land surface elevation derived from Light Detection and Ranging (LiDAR) data recently collected for the Wood River Valley at the northern margin of Agency Lake in Klamath County, Oregon. Former shoreline wetlands that have been cut off from Upper Klamath and Agency Lakes by dikes might in the future be reconnected to Upper Klamath and Agency Lakes by breaching the dikes. Issues of interest associated with restoring wetlands in this way include the area that will be inundated, the volume of water that may be stored, the change in wetland habitat, and the variation in these characteristics as surface-water stage is changed. Products from this analysis can assist water managers in assessing the effect of breaching dikes and changing surface-water stage. The study area is in the approximate former northern margins of Upper Klamath and Agency Lakes in the Wood River Valley.

Selumetinib in Treating Patients With Relapsed or Refractory Advanced Solid Tumors, Non-Hodgkin Lymphoma, or Histiocytic Disorders With Activating MAPK Pathway Mutations (A Pediatric MATCH Treatment Trial)

ClinicalTrials.gov

2018-06-25

Advanced Malignant Solid Neoplasm; Ann Arbor Stage III Childhood Non-Hodgkin Lymphoma; Ann Arbor Stage IV Childhood Non-Hodgkin Lymphoma; BRAF Gene Mutation; GNA11 Gene Mutation; GNAQ Gene Mutation; Histiocytosis; HRAS Gene Mutation; KRAS Gene Mutation; NF1 Gene Mutation; NRAS Gene Mutation; Recurrent Childhood Central Nervous System Neoplasm; Recurrent Childhood Non-Hodgkin Lymphoma; Recurrent Malignant Solid Neoplasm; Recurrent Neuroblastoma; Refractory Central Nervous System Neoplasm; Refractory Malignant Solid Neoplasm; Refractory Neuroblastoma; Refractory Non-Hodgkin Lymphoma

MRI-based assessment of the pineal gland in a large population of children aged 0-5 years and comparison with pineoblastoma: part I, the solid gland.

PubMed

Galluzzi, Paolo; de Jong, Marcus C; Sirin, Selma; Maeder, Philippe; Piu, Pietro; Cerase, Alfonso; Monti, Lucia; Brisse, Hervé J; Castelijns, Jonas A; de Graaf, Pim; Goericke, Sophia L

2016-07-01

Differentiation between normal solid (non-cystic) pineal glands and pineal pathologies on brain MRI is difficult. The aim of this study was to assess the size of the solid pineal gland in children (0-5 years) and compare the findings with published pineoblastoma cases. We retrospectively analyzed the size (width, height, planimetric area) of solid pineal glands in 184 non-retinoblastoma patients (73 female, 111 male) aged 0-5 years on MRI. The effect of age and gender on gland size was evaluated. Linear regression analysis was performed to analyze the relation between size and age. Ninety-nine percent prediction intervals around the mean were added to construct a normal size range per age, with the upper bound of the predictive interval as the parameter of interest as a cutoff for normalcy. There was no significant interaction of gender and age for all the three pineal gland parameters (width, height, and area). Linear regression analysis gave 99 % upper prediction bounds of 7.9, 4.8, and 25.4 mm(2), respectively, for width, height, and area. The slopes (size increase per month) of each parameter were 0.046, 0.023, and 0.202, respectively. Ninety-three percent (95 % CI 66-100 %) of asymptomatic solid pineoblastomas were larger in size than the 99 % upper bound. This study establishes norms for solid pineal gland size in non-retinoblastoma children aged 0-5 years. Knowledge of the size of the normal pineal gland is helpful for detection of pineal gland abnormalities, particularly pineoblastoma.

Upper Stage Flight Experiment 10K Engine Design and Test Results

NASA Technical Reports Server (NTRS)

Ross, R.; Morgan, D.; Crockett, D.; Martinez, L.; Anderson, W.; McNeal, C.

2000-01-01

A 10,000 lbf thrust chamber was developed for the Upper Stage Flight Experiment (USFE). This thrust chamber uses hydrogen peroxide/JP-8 oxidizer/fuel combination. The thrust chamber comprises an oxidizer dome and manifold, catalyst bed assembly, fuel injector, and chamber/nozzle assembly. Testing of the engine was done at NASA's Stennis Space Center (SSC) to verify its performance and life for future upper stage or Reusable Launch Vehicle applications. Various combinations of silver screen catalyst beds, fuel injectors, and combustion chambers were tested. Results of the tests showed high C* efficiencies (97% - 100%) and vacuum specific impulses of 275 - 298 seconds. With fuel film cooling, heating rates were low enough that the silica/quartz phenolic throat experienced minimal erosion. Mission derived requirements were met, along with a perfect safety record.

Dynamic Changes in the Myometrium during the Third Stage of Labor, Evaluated Using Two-Dimensional Ultrasound, in Women with Normal and Abnormal Third Stage of Labor and in Women with Obstetric Complications.

PubMed

Patwardhan, Manasi; Hernandez-Andrade, Edgar; Ahn, Hyunyoung; Korzeniewski, Steven J; Schwartz, Alyse; Hassan, Sonia S; Romero, Roberto

2015-01-01

To investigate dynamic changes in myometrial thickness during the third stage of labor. Myometrial thickness was measured using ultrasound at one-minute time intervals during the third stage of labor in the mid-region of the upper and lower uterine segments in 151 patients including: women with a long third stage of labor (n = 30), postpartum hemorrhage (n = 4), preterm delivery (n = 7) and clinical chorioamnionitis (n = 4). Differences between myometrial thickness of the uterine segments and as a function of time were evaluated. There was a significant linear increase in the mean myometrial thickness of the upper uterine segments, as well as a significant linear decrease in the mean myometrial thickness of the lower uterine segments until the expulsion of the placenta (p < 0.001). The ratio of the measurements of the upper to the lower uterine segments increased significantly as a function of time (p < 0.0001). In women with postpartum hemorrhage, preterm delivery, and clinical chorioamnionitis, an uncoordinated pattern among the uterine segments was observed. A well-coordinated activity between the upper and lower uterine segments is demonstrated in normal placental delivery. In some clinical conditions this pattern is not observed, increasing the time for placental delivery and the risk of postpartum hemorrhage. © 2015 S. Karger AG, Basel.

Dynamic changes in the myometrium during the third stage of labor, evaluated using two-dimensional ultrasound, in women with normal and abnormal third stage of labor and in women with obstetric complications

PubMed Central

Patwardhan, Manasi; Hernandez-Andrade, Edgar; Ahn, Hyunyoung; Korzeniewski, Steven J; Schwartz, Alyse; Hassan, Sonia S; Romero, Roberto

2015-01-01

Objective To investigate dynamic changes in myometrial thickness during the third stage of labor. Methods Myometrial thickness was measured using ultrasound at one-minute time intervals during the third stage of labor in the mid-region of the upper and lower uterine segments in 151 patients including: women with a long third stage of labor (n=30), post-partum hemorrhage (n=4), preterm delivery (n=7) or clinical chorioamnionitis (n=4). Differences between uterine segments and as a function of time were evaluated. Results There was a significant linear increase in the mean myometrial thickness of the upper uterine segments, as well as a significant linear decrease in the mean myometrial thickness of the lower uterine segments until the expulsion of the placenta (p<0.001). The ratio of the measurements of the upper to the lower uterine segments increased significantly as a function of time (p<0.0001). In women with postpartum hemorrhage, preterm delivery and clinical chorioamnionitis, an uncoordinated pattern between the uterine segments was observed. Conclusion A well-coordinated activity between the upper and lower uterine segments is demonstrated in normal placental delivery. In some clinical conditions this pattern is not observed, increasing the time for placental delivery and the risk for post-partum hemorrhage. PMID:25634647

Assessment and Verification of SLS Block 1-B Exploration Upper Stage and Stage Disposal Performance

NASA Technical Reports Server (NTRS)

Patrick, Sean; Oliver, T. Emerson; Anzalone, Evan J.

2018-01-01

Delta-v allocation to correct for insertion errors caused by state uncertainty is one of the key performance requirements imposed on the SLS Navigation System. Additionally, SLS mission requirements include the need for the Exploration Up-per Stage (EUS) to be disposed of successfully. To assess these requirements, the SLS navigation team has developed and implemented a series of analysis methods. Here the authors detail the Delta-Delta-V approach to assessing delta-v allocation as well as the EUS disposal optimization approach.

Allogenic controls on the fluvial architecture and fossil preservation of the Upper Triassic Ischigualasto Formation, NW Argentina

NASA Astrophysics Data System (ADS)

Colombi, Carina E.; Limarino, Carlos O.; Alcober, Oscar A.

2017-12-01

The Upper Triassic Ischigualasto Formation in NW Argentina was deposited in a fluvial system during the synrift filling of the extensional Ischigualasto-Villa Unión Basin. The expansive exposures of the fluvial architecture and paleosols provide a framework to reconstruct the paleoenvironmental evolution of this basin during the Upper Triassic using continental sequence stratigraphy. The Ischigualasto Formation deposition can be divided into seven sequential sedimentary stages: the 1) Bypass stage; 2) Confined low-accommodation stage; 3) Confined high accommodation stage; 4) Unstable-accommodation stage; 5) Unconfined high-accommodation stage; 6) Unconfined low-accommodation stage; and finally, 7) Unconfined high-accommodation stage. The sedimentary evolution of the Ischigualasto Formation was driven by different allogenic controls such as rises and falls in lake levels, local tectonism, subsidence, volcanism, and climate, which also produced modifications of the equilibrium profile of the fluvial systems. All of these factors result in different accommodations in central and flank areas of the basin, which led to different architectural configurations of channels and floodplains. Allogenic processes affected not only the sequence stratigraphy of the basin but also the vertebrate and plant taphocenosis. Therefore, the sequence stratigraphy can be used not only as a predictive tool related to fossil occurrence but also to understand the taphonomic history of the basin at each temporal interval.

An upper bound on the particle-laden dependency of shear stresses at solid-fluid interfaces

NASA Astrophysics Data System (ADS)

Zohdi, T. I.

2018-03-01

In modern advanced manufacturing processes, such as three-dimensional printing of electronics, fine-scale particles are added to a base fluid yielding a modified fluid. For example, in three-dimensional printing, particle-functionalized inks are created by adding particles to freely flowing solvents forming a mixture, which is then deposited onto a surface, which upon curing yields desirable solid properties, such as thermal conductivity, electrical permittivity and magnetic permeability. However, wear at solid-fluid interfaces within the machinery walls that deliver such particle-laden fluids is typically attributed to the fluid-induced shear stresses, which increase with the volume fraction of added particles. The objective of this work is to develop a rigorous strict upper bound for the tolerable volume fraction of particles that can be added, while remaining below a given stress threshold at a fluid-solid interface. To illustrate the bound's utility, the expression is applied to a series of classical flow regimes.

Mass-radius relationships and constraints on the composition of Pluto

NASA Technical Reports Server (NTRS)

Lupo, M. J.; Lewis, J. S.

1980-01-01

With the new upper limit of Pluto's mass, an upper limit for Pluto's density of 1.74 g/cu cm has been found. Assuming Pluto to be 100% methane, available methane density data can be used to set a lower limit of 0.53 g/cu cm on Pluto's density, thus placing an absolute upper limit of 1909 km on the radius and a lower limit of 0.32 on the albedo. The results of 280 computer models covering a wide range of composition ratios of rock, water ice, and methane ice are reported. Limits are placed on Pluto's silicate content, and a simple spacecraft method for determining Pluto's water content from its density and moment of inertia is given. The low thermal conductivity and strength of solid methane suggest rapid solid-state convection in Pluto's methane layer.

TORC1/2 Inhibitor MLN0128 and Bevacizumab in Treating Patients With Recurrent Glioblastoma or Advanced Solid Tumors

ClinicalTrials.gov

2018-05-14

Adult Glioblastoma; Endometrial Clear Cell Adenocarcinoma; Endometrial Serous Adenocarcinoma; Ovarian Clear Cell Cystadenocarcinoma; Ovarian Endometrioid Adenocarcinoma; Ovarian Mucinous Cystadenocarcinoma; Ovarian Serous Cystadenocarcinoma; Recurrent Fallopian Tube Carcinoma; Recurrent Ovarian Carcinoma; Recurrent Primary Peritoneal Carcinoma; Recurrent Uterine Corpus Carcinoma; Solid Neoplasm; Stage IIIA Fallopian Tube Cancer AJCC v7; Stage IIIA Ovarian Cancer AJCC v6 and v7; Stage IIIA Primary Peritoneal Cancer AJCC v7; Stage IIIB Fallopian Tube Cancer AJCC v7; Stage IIIB Ovarian Cancer AJCC v6 and v7; Stage IIIB Primary Peritoneal Cancer AJCC v7; Stage IIIC Fallopian Tube Cancer AJCC v7; Stage IIIC Ovarian Cancer AJCC v6 and v7; Stage IIIC Primary Peritoneal Cancer AJCC v7; Stage IV Fallopian Tube Cancer AJCC v6 and v7; Stage IV Ovarian Cancer AJCC v6 and v7; Stage IV Primary Peritoneal Cancer AJCC v7

Evidence of two-stage melting of Wigner solids

NASA Astrophysics Data System (ADS)

Knighton, Talbot; Wu, Zhe; Huang, Jian; Serafin, Alessandro; Xia, J. S.; Pfeiffer, L. N.; West, K. W.

2018-02-01

Ultralow carrier concentrations of two-dimensional holes down to p =1 ×109cm-2 are realized. Remarkable insulating states are found below a critical density of pc=4 ×109cm-2 or rs≈40 . Sensitive dc V-I measurement as a function of temperature and electric field reveals a two-stage phase transition supporting the melting of a Wigner solid as a two-stage first-order transition.

Ares I Upper Stage Update

NASA Technical Reports Server (NTRS)

Davis, Daniel J.

2010-01-01

These presentation slides review the progress in the development of the Ares I upper stage. The development includes development of a manufacturing and processing assembly that will reduce the time required over 100 days, development of a weld tool that is a robotic tool that is the largest welder of its kind in the United States, development of avionics and software, and development of logisitics and operations systems.

A mechanism for upper airway stability during slow wave sleep.

PubMed

McSharry, David G; Saboisky, Julian P; Deyoung, Pam; Matteis, Paul; Jordan, Amy S; Trinder, John; Smales, Erik; Hess, Lauren; Guo, Mengshuang; Malhotra, Atul

2013-04-01

The severity of obstructive sleep apnea is diminished (sometimes markedly) during slow wave sleep (SWS). We sought to understand why SWS stabilizes the upper airway. Increased single motor unit (SMU) activity of the major upper airway dilating muscle (genioglossus) should improve upper airway stability. Therefore, we hypothesized that genioglossus SMUs would increase their activity during SWS in comparison with Stage N2 sleep. The activity of genioglossus SMUs was studied on both sides of the transition between Stage N2 sleep and SWS. Sleep laboratory. Twenty-nine subjects (age 38 ± 13 yr, 17 males) were studied. SWS. Subjects slept overnight with fine-wire electrodes in their genioglossus muscles and with full polysomnographic and end tidal carbon dioxide monitors. Fifteen inspiratory phasic (IP) and 11 inspiratory tonic (IT) units were identified from seven subjects and these units exhibited significantly increased inspiratory discharge frequencies during SWS compared with Stage N2 sleep. The peak discharge frequency of the inspiratory units (IP and IT) was 22.7 ± 4.1 Hz in SWS versus 20.3 ± 4.5 Hz in Stage N2 (P < 0.001). The IP units also fired for a longer duration (expressed as a percentage of inspiratory time) during SWS (104.6 ± 39.5 %TI) versus Stage N2 sleep (82.6 ± 39.5 %TI, P < 0.001). The IT units fired faster during expiration in SWS (14.2 ± 1.8 Hz) versus Stage N2 sleep (12.6 ± 3.1 Hz, P = 0.035). There was minimal recruitment or derecruitment of units between SWS and Stage N2 sleep. Increased genioglossus SMU activity likely makes the airway more stable and resistant to collapse throughout the respiratory cycle during SWS.

Novel single-nucleotide polymorphism markers confirm successful spawning of endangered pallid sturgeon in the upper Missouri River Basin

USGS Publications Warehouse

Eichelberger, Jennifer S.; Braaten, P. J.; Fuller, D. B.; Krampe, Matthew S.; Heist, Edward J.

2014-01-01

Spawning of the federally endangered Pallid Sturgeon Scaphirhynchus albus is known to occur in the upper Missouri River basin, but progeny from natural reproductive events have not been observed and recruitment to juvenile or adult life stages has not been documented in recent decades. Identification of Pallid Sturgeon progeny is confounded by the fact that Shovelnose Sturgeon S. platorynchus occurs throughout the entire range of Pallid Sturgeon and the two species are essentially indistinguishable (morphometrically and meristically) during early life stages. Moreover, free embryos of sympatric Paddlefish Polyodon spathula are very similar to the two sturgeon species. In this study, three single-nucleotide polymorphism (SNP) assays were employed to screen acipenseriform free embryos and larvae collected from the upper Missouri River basin in 2011, 2012, and 2013. A mitochondrial DNA SNP discriminates Paddlefish from sturgeon, and specific multilocus genotypes at two nuclear DNA SNPs occurred in 98.9% of wild adult Pallid Sturgeon but only in 3% of Shovelnose Sturgeon sampled in the upper Missouri River. Individuals identified as potential Pallid Sturgeon based on SNP genotypes were further analyzed at 19 microsatellite loci for species discrimination. Out of 1,423 free embryos collected over 3 years of sampling, 971 Paddlefish, 446 Shovelnose Sturgeon, and 6 Pallid Sturgeon were identified. Additionally, 249 Scaphirhynchus spp. benthic larvae were screened, but no Pallid Sturgeon were detected. These SNP markers provide an efficient method of screening acipenseriform early life stages for the presence of Pallid Sturgeon in the Missouri River basin. Detection of wild Pallid Sturgeon free embryos in the upper Missouri and Yellowstone rivers supports the hypothesis that the failure of wild Pallid Sturgeon to recruit to the juvenile life stage in the upper Missouri River basin is caused by early life stage mortality rather than by lack of successful spawning.

Experimental Investigation of Rotating Menisci

NASA Astrophysics Data System (ADS)

Reichel, Yvonne; Dreyer, Michael E.

2014-07-01

In upper stages of spacecrafts, Propellant Management Devices (PMD's) can be used to position liquid propellant over the outlet in the absence of gravity. Centrifugal forces due to spin of the upper stage can drive the liquid away from the desired location resulting in malfunction of the stage. In this study, a simplified model consisting of two parallel, segmented and unsegmented disks and a central tube assembled at the center of the upper disk is analyzed experimentally during rotation in microgravity. For each drop tower experiment, the angular speed caused by a centrifugal stage in the drop capsule is kept constant. Steady-states for the menisci between the disks are observed for moderate rotation. For larger angular speeds, a stable shape of the free surfaces fail to sustain and the liquid is driven away. Additionally, tests were performed without rotation to quantify two effects: the removal of a metallic cylinder around the model to establish the liquid column and the determination of the the settling time from terrestrial to microgravity conditions.

Utility of blind forceps biopsy of the main carina and upper-lobe carina in patients with non-small cell lung cancer.

PubMed

Gunen, H; Kizkin, O; Tahaoglu, C; Aktas, O

2001-02-01

Preoperative detection of non-small cell lung cancer (NSCLC) metastasis to the main carina and upper-lobe carina can alter the operative approach, preclude further staging procedures, and save many patients from thoracotomy. This study assessed whether bronchoscopic forceps biopsy of the normal-appearing main carina and upper-lobe carina (blind biopsy) ipsilateral to the primary NSCLC lesion improved the accuracy of cancer staging and helped guide the management of these patients. A prospective study of 52 patients was carried out at the SSK Süreyyapasa Center for Chest Disease and Cardiothoracic Surgery. Over a 6-month period, we bronchoscopically evaluated 52 consecutive NSCLC patients who were radiologically classified as operable. At least five blind forceps biopsy specimens were obtained from the main carina and/or upper-lobe carina during each patient's initial fiberoptic bronchoscopic examination. Biopsy specimens were collected from the main carina and upper-lobe carina in 51 and 17 patients, respectively. Initially, all patients were staged and evaluated for operability in standard fashion, without histologic assessment of the blind biopsy specimens. We then restaged the disease and reassessed the patients' operability in light of the biopsy findings. Metastasis was histologically diagnosed in seven patients (13.7%) who underwent main carina biopsy and in four patients (23.5%) who underwent upper-lobe carina biopsy. Cancer-positive blind biopsy results changed the status of 25% (6 of 24) of patients from operable to inoperable, and changed the surgical approach in 11.1% (2 of 18) of patients who ultimately did undergo surgery. We found no statistical relationship between metastasis to either carina and tumor type, stage of disease, visibility of the tumor on fiberoptic bronchoscopy, primary tumor location, T status, or N status (p > 0.05). A blind forceps biopsy of the main carina and upper-lobe carina ipsilateral to the lesion site should be done routinely at initial bronchoscopic examination of all radiologically operable patients with suspected lung cancer. This type of screening can save a significant number of NSCLC patients from inappropriate or unnecessary thoracotomy and further staging procedures with their associated morbidity and risk.

Bleeding and starving: fasting and delayed refeeding after upper gastrointestinal bleeding.

PubMed

Fonseca, Jorge; Meira, Tânia; Nunes, Ana; Santos, Carla Adriana

2014-01-01

Early refeeding after nonvariceal upper gastrointestinal bleeding is safe and reduces hospital stay/costs. The aim of this study was obtaining objective data on refeeding after nonvariceal upper gastrointestinal bleeding. From 1 year span records of nonvariceal upper gastrointestinal bleeding patients that underwent urgent endoscopy: clinical features; rockall score; endoscopic data, including severity of lesions and therapy; feeding related records of seven days: liquid diet prescription, first liquid intake, soft/solid diet prescription, first soft/solid intake. From 133 patients (84 men) Rockall classification was possible in 126: 76 score ≥5, 50 score <5. One persistent bleeding, eight rebled, two underwent surgery, 13 died. Ulcer was the major bleeding cause, 63 patients underwent endoscopic therapy. There was 142/532 possible refeeding records, no record 37% patients. Only 16% were fed during the first day and half were only fed on third day or later. Rockall <5 patients started oral diet sooner than Rockall ≥5. Patients that underwent endoscopic therapy were refed earlier than those without endotherapy. Most feeding records are missing. Data reveals delayed refeeding, especially in patients with low-risk lesions who should have been fed immediately. Nonvariceal upper gastrointestinal bleeding patients must be refed earlier, according to guidelines.

Navitoclax and Sorafenib Tosylate in Treating Patients With Relapsed or Refractory Solid Tumors

ClinicalTrials.gov

2018-06-01

Cirrhosis; Hepatitis B Infection; Hepatitis C Infection; Metastatic Malignant Solid Neoplasm; Recurrent Hepatocellular Carcinoma; Recurrent Malignant Solid Neoplasm; Refractory Malignant Neoplasm; Stage IV Hepatocellular Carcinoma AJCC v7; Unresectable Solid Neoplasm

Measurements of electron detection efficiencies in solid state detectors.

NASA Technical Reports Server (NTRS)

Lupton, J. E.; Stone, E. C.

1972-01-01

Detailed laboratory measurement of the electron response of solid state detectors as a function of incident electron energy, detector depletion depth, and energy-loss discriminator threshold. These response functions were determined by exposing totally depleted silicon surface barrier detectors with depletion depths between 50 and 1000 microns to the beam from a magnetic beta-ray spectrometer. The data were extended to 5000 microns depletion depth using the results of previously published Monte Carlo electron calculations. When the electron counting efficiency of a given detector is plotted as a function of energy-loss threshold for various incident energies, the efficiency curves are bounded by a smooth envelope which represents the upper limit to the detection efficiency. These upper limit curves, which scale in a simple way, make it possible to easily estimate the electron sensitivity of solid-state detector systems.

The origin of the Avram Iancu U-Ni-Co-Bi-As mineralization, Băiţa (Bihor) metallogenic district, Bihor Mts., Romania

NASA Astrophysics Data System (ADS)

Zajzon, Norbert; Szentpéteri, Krisztián; Szakáll, Sándor; Kristály, Ferenc

2015-10-01

The Băiţa metallogenic district in the Bihor Mountains is a historically important mining area in Romania. Uranium mining took place between 1952 and 1998 from various deposits, but very little is known about the geology and mineralogy of these deposits. In this paper, we describe geology and mineralogy of uranium mineralization of the Avram Iancu uranium mine from waste dump samples collected before complete remediation of the site. Texturally and mineralogically complex assemblages of nickeline, cobaltite-gersdorffite solid solution, native Bi, Bi-sulfosalts, molybdenite, and pyrite-chalcopyrite-sphalerite occur with uraninite, "pitchblende," and brannerite in most of the ore samples. The association of nickel, cobalt, and arsenic with uranium is reminiscent of five-element association of vein type U-Ni-Co-Bi-As deposits; however, the Avram Iancu ores appear to be more replacement-type stratiform/stratabound. Avram Iancu ore samples contain multistage complex, skarn, uranium sulfide, arsenide assemblages that can be interpreted to have been formed in the retrograde cooling stages of the skarn hydrothermal system. This mineralizing system may have built-up along Upper Cretaceous-Paleogene "Banatite" intrusions of diorite-to-granite composition. The intrusions crosscut the underlying uraniferous Permian formations in the stacked NW-verging Biharia Nappe System. The mineralization forms stacked, multilayer replacement horizons, along carbonate-rich lithologies within the metavolcanic (tuffaceous) Muncel Series. Mineral paragenesis and some mineral chemistry suggest moderate-to-high <450, i.e., 350-310 °C, formation temperatures for the uranium sulfide stage along stratigraphically controlled replacement zones and minor veins. Uranium minerals formed abundantly in this early stage and include botryoidal, sooty and euhedral uraninite, brannerite, and coffinite. Later and/or lower-temperature mineral assemblages include heterogeneous, complexly zoned arsenide-sulfarsenide solid solutions associated with minute but abundant uranium minerals. Within the later arsenide-sulfarsenide mineral assemblage, there is great variation in Ni, Co, and S content with generally increasing arsenic content. Uranium minerals in this late-stage assemblage include very fine euhedral uraninite and brannerite inclusions in arsenide-sulfarsenide minerals. Native bismuth and Bi-sulfosalt krupkaite are observed in this As-S-rich assemblage strongly associated with cobaltite.

Solid-liquid staged combustion space boosters

NASA Technical Reports Server (NTRS)

Culver, D. W.

1990-01-01

NASA has begun to evaluate solid-liquid hybrid propulsion for launch vehicle booster. A three-phase program was outlined to identify, acquire, and demonstrate technology needed to approximate solid and liquid propulsion state of the art. Aerojet has completed a Phase 1 study and recommends a solid-liquid staged combustion concept in which turbopump fed LO2 is burned with fuel-rich solid propellant effluent in aft-mounted thrust chambers.These reasonably sized thrust chambers are LO2 regeneratively cooled, supplemented with fuel-rich barrier cooling. Turbopumps are driven by the resulting GO2 coolant in an expander-bleed-burnoff cycle. Turbine exhaust pressurizes the LO2 tankage directly, and the excess is bled into supersonic nozzle splitlines, where it combusts with the fuel rich boundary layer. Thrust vector control is enhanced by supersonic nozzle movement on flexseal mounts. Every hybrid solid-liquid concept examined improves booster energy management and launch propellant safety compared to current solid boosters. Solid-liquid staged combustion improves hybrid performance by improving both combustion efficiency and combustion stability, especially important for large boosters. These improvements result from careful fluid management and use of smaller combustors. The study shows NASA safety, reliability, cost, and performance criteria are best met with this concept, wherein simple hardware relies on several separate emerging technologies, all of which have been demonstrated successfully.

Effect of Elevated CO2 Concentration, Elevated Temperature and No Nitrogen Fertilization on Methanogenic Archaeal and Methane-Oxidizing Bacterial Community Structures in Paddy Soil

PubMed Central

Liu, Dongyan; Tago, Kanako; Hayatsu, Masahito; Tokida, Takeshi; Sakai, Hidemitsu; Nakamura, Hirofumi; Usui, Yasuhiro; Hasegawa, Toshihiro; Asakawa, Susumu

2016-01-01

Elevated concentrations of atmospheric CO2 ([CO2]) enhance the production and emission of methane in paddy fields. In the present study, the effects of elevated [CO2], elevated temperature (ET), and no nitrogen fertilization (LN) on methanogenic archaeal and methane-oxidizing bacterial community structures in a free-air CO2 enrichment (FACE) experimental paddy field were investigated by PCR-DGGE and real-time quantitative PCR. Soil samples were collected from the upper and lower soil layers at the rice panicle initiation (PI) and mid-ripening (MR) stages. The composition of the methanogenic archaeal community in the upper and lower soil layers was not markedly affected by the elevated [CO2], ET, or LN condition. The abundance of the methanogenic archaeal community in the upper and lower soil layers was also not affected by elevated [CO2] or ET, but was significantly increased at the rice PI stage and significantly decreased by LN in the lower soil layer. In contrast, the composition of the methane-oxidizing bacterial community was affected by rice-growing stages in the upper soil layer. The abundance of methane-oxidizing bacteria was significantly decreased by elevated [CO2] and LN in both soil layers at the rice MR stage and by ET in the upper soil layer. The ratio of mcrA/pmoA genes correlated with methane emission from ambient and FACE paddy plots at the PI stage. These results indicate that the decrease observed in the abundance of methane-oxidizing bacteria was related to increased methane emission from the paddy field under the elevated [CO2], ET, and LN conditions. PMID:27600710

Effect of Elevated CO2 Concentration, Elevated Temperature and No Nitrogen Fertilization on Methanogenic Archaeal and Methane-Oxidizing Bacterial Community Structures in Paddy Soil.

PubMed

Liu, Dongyan; Tago, Kanako; Hayatsu, Masahito; Tokida, Takeshi; Sakai, Hidemitsu; Nakamura, Hirofumi; Usui, Yasuhiro; Hasegawa, Toshihiro; Asakawa, Susumu

2016-09-29

Elevated concentrations of atmospheric CO2 ([CO2]) enhance the production and emission of methane in paddy fields. In the present study, the effects of elevated [CO2], elevated temperature (ET), and no nitrogen fertilization (LN) on methanogenic archaeal and methane-oxidizing bacterial community structures in a free-air CO2 enrichment (FACE) experimental paddy field were investigated by PCR-DGGE and real-time quantitative PCR. Soil samples were collected from the upper and lower soil layers at the rice panicle initiation (PI) and mid-ripening (MR) stages. The composition of the methanogenic archaeal community in the upper and lower soil layers was not markedly affected by the elevated [CO2], ET, or LN condition. The abundance of the methanogenic archaeal community in the upper and lower soil layers was also not affected by elevated [CO2] or ET, but was significantly increased at the rice PI stage and significantly decreased by LN in the lower soil layer. In contrast, the composition of the methane-oxidizing bacterial community was affected by rice-growing stages in the upper soil layer. The abundance of methane-oxidizing bacteria was significantly decreased by elevated [CO2] and LN in both soil layers at the rice MR stage and by ET in the upper soil layer. The ratio of mcrA/pmoA genes correlated with methane emission from ambient and FACE paddy plots at the PI stage. These results indicate that the decrease observed in the abundance of methane-oxidizing bacteria was related to increased methane emission from the paddy field under the elevated [CO2], ET, and LN conditions.

Variation in the diel vertical distributions of larvae and transforming stages of oceanic fishes across the tropical and equatorial Atlantic

NASA Astrophysics Data System (ADS)

Olivar, M. Pilar; Contreras, Tabit; Hulley, P. Alexander; Emelianov, Mikhail; López-Pérez, Cristina; Tuset, Víctor; Castellón, Arturo

2018-01-01

The vertical distributions of early developmental stages of oceanic fishes were investigated across the tropical and equatorial Atlantic, from oligotrophic waters close to the Brazilian coast to more productive waters close to the Mauritanian Upwelling Region. Stratification of the water column was observed throughout the study region. Fishes were caught with a MOCNESS-1 net with mouth area of 1 m2 at 11 stations. Each station was sampled both during the day and at night within a single 24-h period. The investigation covered both larvae and transforming stages from the surface to 800 m depth. Distribution patterns were analysed, and weighted mean depths for the larvae and transforming stages of each species were calculated for day and night conditions. Forty-seven different species were found. The highest number of species occurred in the three stations south of Cape Verde Islands, characterized by a mixture of South Atlantic Central Water (SACW) and Eastern North Atlantic Central Water (ENACW). There was a marked drop in species richness in the three stations closer to the African upwelling, dominated by ENACW. The highest abundances occurred in the families Myctophidae, Sternoptychidae, Gonostomatidae and Phosichthyidae. Day and night vertical distributions of larvae and transforming stages showed contrasting patterns, both in the depths of the main concentration layers in the water column, and in the diel migration patterns (where these were observed). Larvae generally showed a preference for the upper mixed layer (ca. 0-50 m) and upper thermocline (ca. 50-100 m), except for sternoptychids, which were also abundant in the lower thermocline layer (100-200 m) and even extended into the mesopelagic zone (down to 500 m). Transforming stages showed a more widespread distribution, with main concentrations in the mesopelagic zone (200-800 m). Larvae showed peak concentrations in the more illuminated and zooplankton-rich upper mixed layers during the day and a wider distribution through the upper 100 m during the night. For most species, transforming stages were concentrated in the mesopelagic layers both day and night, although in some species (Diaphus cf. vanhoeffeni and Vinciguerria nimbaria), the transforming stages displayed vertical migration into the upper 100 m at night, in a manner similar to their adult stages.

NASA's Space Launch System Takes Shape

NASA Technical Reports Server (NTRS)

Askins, Bruce; Robinson, Kimberly F.

2017-01-01

Major hardware and software for NASA's Space Launch System (SLS) began rolling off assembly lines in 2016, setting the stage for critical testing in 2017 and the launch of a major new capability for deep space human exploration. SLS continues to pursue a 2018 first launch of Exploration Mission 1 (EM-1). At NASA's Michoud Assembly Facility near New Orleans, LA, Boeing completed welding of structural test and flight liquid hydrogen tanks, and engine sections. Test stands for core stage structural tests at NASA's Marshall Space Flight Center, Huntsville, AL. neared completion. The B2 test stand at NASA's Stennis Space Center, MS, completed major structural renovation to support core stage green run testing in 2018. Orbital ATK successfully test fired its second qualification solid rocket motor in the Utah desert and began casting the motor segments for EM-1. Aerojet Rocketdyne completed its series of test firings to adapt the heritage RS-25 engine to SLS performance requirements. Production is under way on the first five new engine controllers. NASA also signed a contract with Aerojet Rocketdyne for propulsion of the RL10 engines for the Exploration Upper Stage. United Launch Alliance delivered the structural test article for the Interim Cryogenic Propulsion Stage to MSFC for tests and construction was under way on the flight stage. Flight software testing at MSFC, including power quality and command and data handling, was completed. Substantial progress is planned for 2017. Liquid oxygen tank production will be completed at Michoud. Structural testing at Marshall will get under way. RS-25 hotfire testing will verify the new engine controllers. Core stage horizontal integration will begin. The core stage pathfinder mockup will arrive at the B2 test stand for fit checks and tests. EUS will complete preliminary design review. This paper will discuss the technical and programmatic successes and challenges of 2016 and look ahead to plans for 2017.

Infusing Training into the Documentation and Culture of Ares I Upper Stage Design and Manufacturing

NASA Technical Reports Server (NTRS)

Scott, David W.

2009-01-01

In roughly two years time, Marshall Space Flight Center's (MSFC) Mission Operations Laboratory (MOL) has incubated a personnel training and certification program for about 1000 learners and multiple phases of the Ares I Upper Stage (US) project. Previous MOL-developed training programs focused on about 100 learners with a focus on operations, and had enough full-time training staff to develop courseware and provide training administration. This paper discusses 1) how creation of a broad, structured training program unfolded as feedback from more narrowly defined tasks, 2) how training philosophy, development methods, and administration are being simplified and tailored so that many Upper Stage organizations can grow their own training yet maintain consistency, accountability, and traceability across the project, and 3) possibilities for interfacing with the production contractor's training system and staff.

Ensartinib in Treating Patients With Relapsed or Refractory Advanced Solid Tumors, Non-Hodgkin Lymphoma, or Histiocytic Disorders With ALK or ROS1 Genomic Alterations (A Pediatric MATCH Treatment Trial)

ClinicalTrials.gov

2018-06-25

Advanced Malignant Solid Neoplasm; ALK Fusion Protein Expression; ALK Gene Mutation; ALK Gene Translocation; Ann Arbor Stage III Childhood Non-Hodgkin Lymphoma; Ann Arbor Stage IV Childhood Non-Hodgkin Lymphoma; Histiocytosis; Recurrent Childhood Central Nervous System Neoplasm; Recurrent Childhood Non-Hodgkin Lymphoma; Recurrent Malignant Solid Neoplasm; Recurrent Neuroblastoma; Refractory Central Nervous System Neoplasm; Refractory Malignant Solid Neoplasm; Refractory Neuroblastoma; Refractory Non-Hodgkin Lymphoma; ROS1 Fusion Positive; ROS1 Gene Mutation; ROS1 Gene Translocation

[Remote intelligent Brunnstrom assessment system for upper limb rehabilitation for post-stroke based on extreme learning machine].

PubMed

Wang, Yue; Yu, Lei; Fu, Jianming; Fang, Qiang

2014-04-01

In order to realize an individualized and specialized rehabilitation assessment of remoteness and intelligence, we set up a remote intelligent assessment system of upper limb movement function of post-stroke patients during rehabilitation. By using the remote rehabilitation training sensors and client data sampling software, we collected and uploaded the gesture data from a patient's forearm and upper arm during rehabilitation training to database of the server. Then a remote intelligent assessment system, which had been developed based on the extreme learning machine (ELM) algorithm and Brunnstrom stage assessment standard, was used to evaluate the gesture data. To evaluate the reliability of the proposed method, a group of 23 stroke patients, whose upper limb movement functions were in different recovery stages, and 4 healthy people, whose upper limb movement functions were normal, were recruited to finish the same training task. The results showed that, compared to that of the experienced rehabilitation expert who used the Brunnstrom stage standard table, the accuracy of the proposed remote Brunnstrom intelligent assessment system can reach a higher level, as 92.1%. The practical effects of surgery have proved that the proposed system could realize the intelligent assessment of upper limb movement function of post-stroke patients remotely, and it could also make the rehabilitation of the post-stroke patients at home or in a community care center possible.

Mucinous breast carcinoma with tall columnar cells.

PubMed

Tsoukalas, N; Kiakou, M; Tolia, M; Kostakis, I D; Galanopoulos, M; Nakos, G; Tryfonopoulos, D; Kyrgias, G; Koumakis, G

2018-05-01

Mucinous carcinoma of the breast represents 1%-4% of all breast cancers. The World Health Organization classification divides this type of tumour into three different subtypes: mucinous carcinoma, mucinous carcinoma with tall columnar cells (mucinous cystadenocarcinoma and columnar cell mucinous carcinoma) and signet ring cell carcinoma. A 74-year-old woman presented a tumour with inflammatory features in the upper outer quadrant of her left breast, 7 cm in diameter. The core biopsy showed infiltrating ductal carcinoma of no specific type. The tumour-node-metastasis clinical staging was T4cN3M0 (Stage IIIC). She received neoadjuvant chemotherapy, underwent left mastectomy with radical axillary resection and subsequently received radiotherapy and chemotherapy. The histological examination of the surgical specimen revealed two solid tumors in the tail of Spence, which corresponded to adenocarcinoma with high columnar cells. The patient died 16 months after the diagnosis, suffering from pulmonary metastases and anterior chest wall infiltration. A review of the literature revealed only 21 reports of mucinous carcinoma of the breast with tall columnar cells, including our case. This is only the third time that the specific histological type of columnar cell mucinous carcinoma has been reported in the literature.

Magellan Prelaunch Mission Operations Report

NASA Technical Reports Server (NTRS)

1989-01-01

The Magellan spacecraft will be launched from Kennedy Space Center (KSC) within a 31-day overall launch period extending from April 28 to May 28, 1989. The launch will use the Shuttle Orbiter Atlantis to lift an Inertial Upper Stage (IUS) and the Magellan Spacecraft into low Earth orbit. After the Shuttle achieves its parking orbit, the IUS and attached Magellan spacecraft are deployed from the payload bay. After a short coast time, the two-stage IUS is fired to inject the Magellan spacecraft into an Earth-Venus transfer trajectory. The Magellan spacecraft is powered by single degree of freedom, sun-tracking, solar panels charging a set of nickel-cadmium batteries. The spacecraft is three-axis stabilized by reaction wheels using gyros and a star sensor for attitude reference. The spacecraft carries a solid rocket motor for Venus Orbit Insertion (VOI). A hydrazine propulsion system allows trajectory correction and prevents saturation of the reaction wheels. Communication with Earth through the Deep Space Network (DSN) is provided by S- and X-band telemetry channels, through alternatively a low, medium, or 3.7 m high-gain parabolic antenna rigidly attached to the spacecraft. The high-gain antenna also serves as the radar and radiometer antenna during orbit around Venus.

Ares I-X Flight Test Vehicle Modal Test

NASA Technical Reports Server (NTRS)

Buehrle, Ralph D.; Templeton, Justin D.; Reaves, Mercedes C.; Horta, Lucas G.; Gaspar, James L.; Bartolotta, Paul A.; Parks, Russel A.; Lazor, Daniel R.

2010-01-01

The first test flight of NASA's Ares I crew launch vehicle, called Ares I-X, was launched on October 28, 2009. Ares I-X used a 4-segment reusable solid rocket booster from the Space Shuttle heritage with mass simulators for the 5th segment, upper stage, crew module and launch abort system. Flight test data will provide important information on ascent loads, vehicle control, separation, and first stage reentry dynamics. As part of hardware verification, a series of modal tests were designed to verify the dynamic finite element model (FEM) used in loads assessments and flight control evaluations. Based on flight control system studies, the critical modes were the first three free-free bending mode pairs. Since a test of the free-free vehicle was not practical within project constraints, modal tests for several configurations during vehicle stacking were defined to calibrate the FEM. Test configurations included two partial stacks and the full Ares I-X flight test vehicle on the Mobile Launcher Platform. This report describes the test requirements, constraints, pre-test analysis, test execution and results for the Ares I-X flight test vehicle modal test on the Mobile Launcher Platform. Initial comparisons between pre-test predictions and test data are also presented.

Simulation of active tectonic processes for a convecting mantle with moving continents

USGS Publications Warehouse

Trubitsyn, V.; Kaban, M.; Mooney, W.; Reigber, C.; Schwintzer, P.

2006-01-01

Numerical models are presented that simulate several active tectonic processes. These models include a continent that is thermally and mechanically coupled with viscous mantle flow. The assumption of rigid continents allows use of solid body equations to describe the continents' motion and to calculate their velocities. The starting point is a quasi-steady state model of mantle convection with temperature/ pressure-dependent viscosity. After placing a continent on top of the mantle, the convection pattern changes. The mantle flow subsequently passes through several stages, eventually resembling the mantle structure under present-day continents: (a) Extension tectonics and marginal basins form on boundary of a continent approaching to subduction zone, roll back of subduction takes place in front of moving continent; (b) The continent reaches the subduction zone, the extension regime at the continental edge is replaced by strong compression. The roll back of the subduction zone still continues after closure of the marginal basin and the continent moves towards the upwelling. As a result the ocean becomes non-symmetric and (c) The continent overrides the upwelling and subduction in its classical form stops. The third stage appears only in the upper mantle model with localized upwellings. ?? 2006 The Authors Journal compilation ?? 2006 RAS.

Comparative evaluation of existing expendable upper stages for space shuttle

NASA Technical Reports Server (NTRS)

Weyers, V. J.; Sagerman, G. D.; Borsody, J.; Lubick, R. J.

1974-01-01

The use of existing expendable upper stages in the space shuttle during its early years of operation is evaluated. The Burner 2, Scout, Delta, Agena, Transtage, and Centaur were each studied under contract by their respective manufacturers to determine the extent and cost of the minimum modifications necessary to integrate the stage with the shuttle orbiter. A comparative economic analysis of thirty-five different families of these stages is discussed. Results show that the overall transportation system cost differences between many of the families are quite small. However, by considering several factors in addition to cost, it is possible to select one family as being representative of the capability of the minimum modification existing stage approach. The selected family meets all of the specified mission requirements during the early years of shuttle operation.

Hydrolysis and acidification of agricultural waste in a non-airtight system: Effect of solid content, temperature, and mixing mode.

PubMed

Yu, Jiadong; Zhao, Yubin; Zhang, Huan; Hua, Binbin; Yuan, Xufeng; Zhu, Wanbin; Wang, Xiaofen; Cui, Zongjun

2017-01-01

A two-phase digestion system for treating agricultural waste is beneficial for methane production. This study explored the effect of solid content, temperature, and mixing mode on the process of hydrolysis and acidification using rice straw and cow dung launched in non-airtight acidogenic system. The results showed that the substrate could be hydrolyzed efficiently in the initial stage, the hydrolysis coefficient (k) of maximum cellulose and hemicellulose can be increased by 217.9% and 290.5%, respectively, compared with those of middle and last stages. High solid content played a leading role in promoting hydrolysis, resulted in hydrolysate content (sCOD) that was significantly higher than in treatments with low solid content (P<0.01), and led to organic acids accumulation up to 5.8 and 6.7g/L at mesophilic and thermophilic temperatures. Thermophilic temperature stimulated the hydrolysis and acidification of low solid content (P<0.05), and improved organic acid accumulation of high solid content only during the middle stage (P<0.01). Mixing mode was not a major factor, but increasing the mixing time was necessary for organic acid accumulation during the last stage (P<0.05). In addition, the study comprehensively analyzed a series of corresponding relationships among each operating parameter during the whole treatment process using canonical correspondence analysis. Copyright © 2016 Elsevier Ltd. All rights reserved.

Reflection spectra of solids of planetary interest

NASA Technical Reports Server (NTRS)

Sill, G. T.

1973-01-01

The spectra of solids are reproduced which might be found on the surfaces of planetary bodies or as solid condensates in the upper planetary atmosphere. Among these are spectra of various iron compounds of interest in the study of the clouds of Venus. Other spectra are included of various sulfides, some at low temperature, relevant to the planet Jupiter. Meteorite and coal abstracts are also included, to illustrate dark carbon compounds.

Reflection spectra of solids of planetary interest

NASA Technical Reports Server (NTRS)

Sill, G. T.; Carm, O.

1973-01-01

This paper reproduces the spectra of solids which might be found on the surfaces of planetary bodies or as solid condensates in the upper planetary atmosphere. Among these are spectra of various iron compounds of interest in the study of the clouds of Venus. Other spectra (some at low temperature) are included for various sulfides relevant to the planet Jupiter. Meteorite and coal spectra are also included to illustrate dark carbon compounds.

Analytical Approach for Estimating Preliminary Mass of ARES I Crew Launch Vehicle Upper Stage Structural Components

NASA Technical Reports Server (NTRS)

Aggarwal, Pravin

2007-01-01

In January 2004, President Bush gave the National Aeronautics and Space Administration (NASA) a vision for Space Exploration by setting our sight on a bold new path to go back to the Moon, then to Mars and beyond. In response to this vision, NASA started the Constellation Program, which is a new exploration launch vehicle program. The primary mission for the Constellation Program is to carry out a series of human expeditions ranging from Low Earth Orbit to the surface of Mars and beyond for the purposes of conducting human exploration of space, as specified by the Vision for Space Exploration (VSE). The intent is that the information and technology developed by this program will provide the foundation for broader exploration activities as our operational experience grows. The ARES I Crew Launch Vehicle (CLV) has been designated as the launch vehicle that will be developed as a "first step" to facilitate the aforementioned human expeditions. The CLV Project is broken into four major elements: First Stage, Upper Stage Engine, Upper Stage (US), and the Crew Exploration Vehicle (CEV). NASA's Marshall Space Flight Center (MSFC) is responsible for the design of the CLV and has the prime responsibility to design the upper stage of the vehicle. The US is the second propulsive stage of the CLV and provides CEV insertion into low Earth orbit (LEO) after separation from the First Stage of the Crew Launch Vehicle. The fully integrated Upper Stage is a mix of modified existing heritage hardware (J-2X Engine) and new development (primary structure, subsystems, and avionics). The Upper Stage assembly is a structurally stabilized cylindrical structure, which is powered by a single J-2X engine which is developed as a separate Element of the CLV. The primary structure includes the load bearing liquid hydrogen (LH2) and liquid oxygen (LOX) propellant tanks, a Forward Skirt, the Intertank structure, the Aft Skirt and the Thrust Structure. A Systems Tunnel, which carries fluid and electrical power functions to other Elements of the CLV, is included as secondary structure. The MSFC has an overall responsibility for the integrated US element as well as structural design an thermal control of the fuel tanks, intertank, interstage, avionics, main propulsion system, Reaction Control System (RCS) for both the Upper Stage and the First Stage. MSFC's Spacecraft and Vehicle Department, Structural and Analysis Design Division is developing a set of predicted mass of these elements. This paper details the methodology, criterion and tools used for the preliminary mass predictions of the upper stage structural assembly components. In general, weight of the cylindrical barrel sections are estimated using the commercial code Hypersizer, whereas, weight of the domes are developed using classical solutions. HyperSizer is software that performs automated structural analysis and sizing optimization based on aerospace methods for strength, stability, and stiffness. Analysis methods range from closed form, traditional hand calculations repeated every day in industry to more advanced panel buckling algorithms. Margin-of-safety reporting for every potential failure provides the engineer with a powerful insight into the structural problem. Optimization capabilities include finding minimum weight panel or beam concepts, material selections, cross sectional dimensions, thicknesses, and lay-ups from a library of 40 different stiffened and sandwich designs and a database of composite, metallic, honeycomb, and foam materials. Multiple different concepts (orthogrid, isogrid, and skin stiffener) were run for multiple loading combinations of ascent design load with and with out tank pressure as well as proof pressure condition. Subsequently, selected optimized concept obtained from Hypersizer runs was translated into a computer aid design (CAD) model to account for the wall thickness tolerance, weld land etc for developing the most probable weight of the components. The flow diram summarizes the analysis steps used in developing these predicted mass.

Geospatial datasets for assessing the effects of rangeland conditions on dissolved-solids yields in the Upper Colorado River Basin

USGS Publications Warehouse

Tillman, Fred D.; Flynn, Marilyn E.; Anning, David W.

2015-01-01

In 2009, the U.S. Geological Survey (USGS) developed a Spatially Referenced Regressions on Watershed Attributes (SPARROW) surface-water quality model for the Upper Colorado River Basin (UCRB) relating dissolved-solids sources and transport in the 1991 water year to upstream catchment characteristics. The SPARROW model focused on geologic and agricultural sources of dissolved solids in the UCRB and was calibrated using water-year 1991 dissolved-solids loads from 218 monitoring sites. A new UCRB SPARROW model is planned that will update the investigation of dissolved-solids sources and transport in the basin to circa 2010 conditions and will improve upon the 2009 model by incorporating more detailed information about agricultural-irrigation and rangeland-management practices, among other improvements. Geospatial datasets relating to circa 2010 rangeland conditions are required for the new UCRB SPARROW modeling effort. This study compiled geospatial datasets for the UCRB that relate to the biotic alterations and rangeland conditions of grazing, fire and other land disturbance, and vegetation type and cover. Datasets representing abiotic alterations of access control (off-highway vehicles) and sediment generation and transport in general, were also compiled. These geospatial datasets may be tested in the upcoming SPARROW model to better understand the potential contribution of rangelands to dissolved-solids loading in UCRB streams.

Alder Establishment and Channel Dynamics in a Tributary of the South Fork Eel River, Mendocino County, California

Treesearch

William J. Trush; Edward C. Connor; Knight Alan W.

1989-01-01

Riparian communities established along Elder Creek, a tributary of the upper South Fork Eel River, are bounded by two frequencies of periodic flooding. The upper limit for the riparian zone occurs at bankfull stage. The lower riparian limit is associated with a more frequent stage height, called the active channel, having an exceedance probability of 11 percent on a...

Propellant Management in Booster and Upper Stage Propulsion Systems

NASA Technical Reports Server (NTRS)

Fisher, Mark F.

1997-01-01

A summary review of some of the technical issues which surround the design of the propulsion systems for Booster and Upper Stage systems are presented. The work focuses on Propellant Geyser, Slosh, and Orientation. A brief description of the concern is given with graphics which help the reader to understand the physics of the situation. The most common solutions to these problems are given with there respective advantages and disadvantages.

The Status of National Values in the Books of Social Studies for the Grades of the Upper Primary Stage in Jordan

ERIC Educational Resources Information Center

Subheyyin, Eid H.; Mawajdeh, Baker S.; Talhouni, Mansour H.; Rfou', Mohammad O.

2017-01-01

This study aimed at determining the most important national values that should be included in the textbooks of social studies for the upper-primary stage grades in Jordan; and then identifying the degree of their inclusion in those books. The study used a descriptive-analytical approach. A study tool which includes twelve national values was…

Inertial Upper Stage (IUS) software analysis

NASA Technical Reports Server (NTRS)

Grayson, W. L.; Nickel, C. E.; Rose, P. L.; Singh, R. P.

1979-01-01

The Inertial Upper Stage (IUS) System, an extension of the Space Transportation System (STS) operating regime to include higher orbits, orbital plane changes, geosynchronous orbits, and interplanetary trajectories is presented. The IUS software design, the IUS software interfaces with other systems, and the cost effectiveness in software verification are described. Tasks of the IUS discussed include: (1) design analysis; (2) validation requirements analysis; (3) interface analysis; and (4) requirements analysis.

Microwave-Assisted Hydantoins Synthesis on Solid Support

ERIC Educational Resources Information Center

Coursindel, Thibault; Martinez, Jean; Parrot, Isabelle

2010-01-01

In this laboratory activity, students are introduced to a three-step synthesis of hydantoin (imidazolidine-2,4-dione), a moiety that is found in many biologically active compounds. Using a microwave oven and solid-support technology, this synthetic experiment is designed for masters-degree candidates working in organic chemistry or upper-level…

KSC-99pc0185

NASA Image and Video Library

1999-02-09

In the Solid Motor Assembly Building, Cape Canaveral Air Station, looking over the Inertial Upper Stage booster being readied for their mission are (left to right) STS-93 Pilot Jeffrey S. Ashby and Mission Specialists Michel Tognini, who represents the Centre National d'Etudes Spatiales (CNES), and Steven A. Hawley. On the far right is Eric Herrburger, with Boeing. Other crew members (not shown) are Commander Eileen Collins and Mission Specialist Catherine G. Coleman. STS-93, scheduled to launch July 9 aboard Space Shuttle Columbia, has the primary mission of the deployment of the Chandra X-ray Observatory. Formerly called the Advanced X-ray Astrophysics Facility, Chandra comprises three major elements: the spacecraft, the science instrument module (SIM), and the world's most powerful X-ray telescope. Chandra will allow scientists from around the world to see previously invisible black holes and high-temperature gas clouds, giving the observatory the potential to rewrite the books on the structure and evolution of our universe

KSC-99pc0187

NASA Image and Video Library

1999-02-09

In the Solid Motor Assembly Building, Cape Canaveral Air Station, STS-93 Mission Specialist Catherine G. Coleman kneels next to the Inertial Upper Stage booster being readied for the mission. Other crew members (not shown) are Commander Eileen Collins, Pilot Jeffrey S. Ashby and Mission Specialists Steven A. Hawley and Michel Tognini of France, who represents the Centre National d'Etudes Spatiales (CNES). STS-93, scheduled to launch July 9 aboard Space Shuttle Columbia, has the primary mission of the deployment of the Chandra X-ray Observatory. Formerly called the Advanced X-ray Astrophysics Facility, Chandra comprises three major elements: the spacecraft, the science instrument module (SIM), and the world's most powerful X-ray telescope. Chandra will allow scientists from around the world to see previously invisible black holes and high-temperature gas clouds, giving the observatory the potential to rewrite the books on the structure and evolution of our universe

KSC-99pc0186

NASA Image and Video Library

1999-02-09

In the Solid Motor Assembly Building, Cape Canaveral Air Station, STS-93 Pilot Jeffrey S. Ashby and Mission Specialist Steven A. Hawley look over the Inertial Upper Stage booster being readied for their mission. Other crew members (not shown) are Commander Eileen Collins and Mission Specialists Catherine G. Coleman and Michel Tognini of France, who represents the Centre National d'Etudes Spatiales (CNES). STS-93, scheduled to launch July 9 aboard Space Shuttle Columbia, has the primary mission of the deployment of the Chandra X-ray Observatory. Formerly called the Advanced X-ray Astrophysics Facility, Chandra comprises three major elements: the spacecraft, the science instrument module (SIM), and the world's most powerful X-ray telescope. Chandra will allow scientists from around the world to see previously invisible black holes and high-temperature gas clouds, giving the observatory the potential to rewrite the books on the structure and evolution of our universe

Artist's Concept of the Atlas V-401 Rocket

NASA Image and Video Library

2018-01-25

Interior Exploration using Seismic Investigations, Geodesy and Heat Transport, or InSight, is scheduled to launch from Vandenberg Air Force Base on California's Pacific coast between May 5 and June 8, 2018. The lander will launch to Mars aboard an Atlas V-401 launch vehicle, one of the biggest rockets available for interplanetary flight. It stands 188 feet (57.3 meters) tall, or about as tall as a 19-story building. Fully stacked, with the spacecraft, the Atlas V-401 weighs about 730,000 pounds (333,000 kilograms). That's about 14 big rigs, fully loaded with cargo! The three numbers in the 401 designation signify: 4: a payload fairing -- or nose cone -- that is about 13 feet (4 meters) in diameter 0: solid-rocket boosters supplementing the main booster 1: the upper stage, which has one engine https://photojournal.jpl.nasa.gov/catalog/PIA22231

Mars Exploration Rover -2

NASA Image and Video Library

2003-03-06

Components of the two Mars Exploration Rovers (MER) reside in the Payload Hazardous Servicing Facility. At right MER-2. At left is a lander. In the background is one of the aeroshells. MER-1 and MER-2, their aeroshells and landers will undergo a full mission simulation before being integrated. After spin balance testing, each spacecraft will be mated to a solid propellant upper stage booster that will propel the spacecraft out of Earth orbit. Approximately 10 days before launch they will be transported to the launch pad for mating with their respective Boeing Delta II rockets. The rovers will serve as robotic geologists to seek answers about the evolution of Mars, particularly for a history of water. The rovers are identical to each other, but will land at different regions of Mars. Launch of the first rover is scheduled for May 30 from Cape Canaveral Air Force Station. The second will follow June 25.

Ares I-X Flight Test Vehicle: Stack 5 Modal Test

NASA Technical Reports Server (NTRS)

Buehrle, Ralph D.; Templeton, Justin D.; Reaves, Mercedes C.; Horta, Lucas G.; Gaspar, James L.; Bartolotta, Paul A.; Parks, Russel A.; Lazor, Danel R.

2010-01-01

Ares I-X was the first flight test vehicle used in the development of NASA's Ares I crew launch vehicle. The Ares I-X used a 4-segment reusable solid rocket booster from the Space Shuttle heritage with mass simulators for the 5th segment, upper stage, crew module and launch abort system. Three modal tests were defined to verify the dynamic finite element model of the Ares I-X flight test vehicle. Test configurations included two partial stacks and the full Ares I-X flight test vehicle on the Mobile Launcher Platform. This report focuses on the first modal test that was performed on the top section of the vehicle referred to as Stack 5, which consisted of the spacecraft adapter, service module, crew module and launch abort system simulators. This report describes the test requirements, constraints, pre-test analysis, test operations and data analysis for the Ares I-X Stack 5 modal test.

Ares I-X Flight Test Vehicle:Stack 1 Modal Test

NASA Technical Reports Server (NTRS)

Buehrle, Ralph D.; Templeton, Justin D.; Reaves, Mercedes C.; Horta, Lucas G.; Gaspar, James L.; Bartolotta, Paul A.; Parks, Russel A.; Lazor, Daniel R.

2010-01-01

Ares I-X was the first flight test vehicle used in the development of NASA s Ares I crew launch vehicle. The Ares I-X used a 4-segment reusable solid rocket booster from the Space Shuttle heritage with mass simulators for the 5th segment, upper stage, crew module and launch abort system. Three modal tests were defined to verify the dynamic finite element model of the Ares I-X flight test vehicle. Test configurations included two partial stacks and the full Ares I-X flight test vehicle on the Mobile Launcher Platform. This report focuses on the second modal test that was performed on the middle section of the vehicle referred to as Stack 1, which consisted of the subassembly from the 5th segment simulator through the interstage. This report describes the test requirements, constraints, pre-test analysis, test operations and data analysis for the Ares I-X Stack 1 modal test.

Augmentation of blood circulation to the fingers by warming distant body areas

NASA Technical Reports Server (NTRS)

Koscheyev, V. S.; Leon, G. R.; Paul, S.; Tranchida, D.; Linder, I. V.

2000-01-01

Future activities in space will require greater periods of time in extreme environments in which the body periphery will be vulnerable to chilling. Maintaining the hands and fingers in comfortable conditions enhances finger flexibility and dexterity, and thus effects better work performance. We have evaluated the efficacy of promoting heat transfer and release by the extremities by increasing the blood flow to the periphery from more distant parts of the body. The experimental garment paradigm developed by the investigators was used to manipulate the temperature of different body areas. Six subjects, two females and four males, were evaluated in a stage-1 baseline condition, with the inlet temperature of the circulating water in the liquid cooling/warming garment (LCWG) at 33 degrees C. At stage 2 the total LCWG water inlet temperature was cooled to 8 degrees C, and at stage 3 the inlet water temperature in specific segments of the LCWG was warmed (according to protocol) to 45 degrees C, while the inlet temperature in the rest of the LCWG was maintained at 8 degrees C. The following four body-area-warming conditions were studied in separate sessions: (1) head, (2) upper torso/arm, (3) upper torso/arm/head, and (4) legs/feet. Skin temperature, heat flux and blood perfusion of the fingers, and subjective perception of thermal sensations and overall physical comfort were assessed. Finger temperature (T(fing)) analyses showed a statistically significant condition x stage interaction. Post-hoc comparisons (T(fing)) indicated that at stage 3, the upper torso/arm/head warming condition was significantly different from the head, upper torso/arm and legs/feet conditions, showing an increase in T(fing). There was a significant increase in blood perfusion in the fingers at stage 3 in all conditions. Subjective perception of hand warmth, and overall physical comfort level significantly increased in the stage 3 upper torso/arm/head condition. The findings indicate that physiological methods to enhance heat transfer by the blood to the periphery within protective clothing provide an additional tool for increasing total and local human comfort in extreme environments.

A Mechanism for Upper Airway Stability during Slow Wave Sleep

PubMed Central

McSharry, David G.; Saboisky, Julian P.; DeYoung, Pam; Matteis, Paul; Jordan, Amy S.; Trinder, John; Smales, Erik; Hess, Lauren; Guo, Mengshuang; Malhotra, Atul

2013-01-01

Study Objectives: The severity of obstructive sleep apnea is diminished (sometimes markedly) during slow wave sleep (SWS). We sought to understand why SWS stabilizes the upper airway. Increased single motor unit (SMU) activity of the major upper airway dilating muscle (genioglossus) should improve upper airway stability. Therefore, we hypothesized that genioglossus SMUs would increase their activity during SWS in comparison with Stage N2 sleep. Design: The activity of genioglossus SMUs was studied on both sides of the transition between Stage N2 sleep and SWS. Setting: Sleep laboratory. Participants: Twenty-nine subjects (age 38 ± 13 yr, 17 males) were studied. Intervention: SWS. Measurement and Results: Subjects slept overnight with fine-wire electrodes in their genioglossus muscles and with full polysomnographic and end tidal carbon dioxide monitors. Fifteen inspiratory phasic (IP) and 11 inspiratory tonic (IT) units were identified from seven subjects and these units exhibited significantly increased inspiratory discharge frequencies during SWS compared with Stage N2 sleep. The peak discharge frequency of the inspiratory units (IP and IT) was 22.7 ± 4.1 Hz in SWS versus 20.3 ± 4.5 Hz in Stage N2 (P < 0.001). The IP units also fired for a longer duration (expressed as a percentage of inspiratory time) during SWS (104.6 ± 39.5 %TI) versus Stage N2 sleep (82.6 ± 39.5 %TI, P < 0.001). The IT units fired faster during expiration in SWS (14.2 ± 1.8 Hz) versus Stage N2 sleep (12.6 ± 3.1 Hz, P = 0.035). There was minimal recruitment or derecruitment of units between SWS and Stage N2 sleep. Conclusion: Increased genioglossus SMU activity likely makes the airway more stable and resistant to collapse throughout the respiratory cycle during SWS. Citation: McSharry DG; Saboisky JP; DeYoung P; Matteis P; Jordan AS; Trinder J; Smales E; Hess L; Guo M; Malhotra A. A mechanism for upper airway stability during slow wave sleep. SLEEP 2013;36(4):555-563. PMID:23565001

Main-belt asteroid exploration - Mission options for the 1990s

NASA Technical Reports Server (NTRS)

Yen, Chen-Wan L.

1989-01-01

An extensive investigation of the ways to rendezvous with diverse groups of asteroids residing between 2.0 and 5.0 AU is made, and the extent of achievable missions using the STS upper-stage launch vehicles (IUS 2-Stage/Star-48 or NASA Centaur) is examined. With judicious use of earth, Mars, and Jupiter gravity assists, rendezvous with some asteroids in all regions of space is possible. It is also shown that the STS upper stages are capable of carrying out missions beyond a single rendezvous, namely with several flybys and/or multiple rendezvous.

KSC-2009-3221

NASA Image and Video Library

2009-05-21

CAPE CANAVERAL, Fla. – In the Assembly and Refurbishment Facility at NASA's Kennedy Space Center in Florida, the Ares I-X frustum is being mated to the forward skirt and forward skirt extension to complete the forward assembly. The assembly will be moved to the Vehicle Assembly Building for stacking operations. Resembling a giant funnel, the frustum's function is to transition the primary flight loads from the rocket's upper stage to the first stage. The frustum is located between the forward skirt extension and the upper stage of the Ares I-X. The launch of Ares I-X is targeted for August 2009. Photo credit: NASA/Troy Cryder

KSC-2009-3223

NASA Image and Video Library

2009-05-21

CAPE CANAVERAL, Fla. – In the Assembly and Refurbishment Facility at NASA's Kennedy Space Center in Florida, the Ares I-X frustum is being mated to the forward skirt and forward skirt extension to complete the forward assembly. The assembly will be moved to the Vehicle Assembly Building for stacking operations. Resembling a giant funnel, the frustum's function is to transition the primary flight loads from the rocket's upper stage to the first stage. The frustum is located between the forward skirt extension and the upper stage of the Ares I-X. The launch of Ares I-X is targeted for August 2009. Photo credit: NASA/Troy Cryder

KSC-2009-3222

NASA Image and Video Library

2009-05-21

CAPE CANAVERAL, Fla. – In the Assembly and Refurbishment Facility at NASA's Kennedy Space Center in Florida, the Ares I-X frustum is being mated to the forward skirt and forward skirt extension to complete the forward assembly. The assembly will be moved to the Vehicle Assembly Building for stacking operations. Resembling a giant funnel, the frustum's function is to transition the primary flight loads from the rocket's upper stage to the first stage. The frustum is located between the forward skirt extension and the upper stage of the Ares I-X. The launch of Ares I-X is targeted for August 2009. Photo credit: NASA/Troy Cryder

Biofuel production utilizing a dual-phase cultivation system with filamentous cyanobacteria.

PubMed

Aoki, Jinichi; Kawamata, Toru; Kodaka, Asuka; Minakawa, Masayuki; Imamura, Nobukazu; Tsuzuki, Mikio; Asayama, Munehiko

2018-04-17

Biomass yields and biofuel production were examined in a dual (solid and liquid)-phase cultivation system (DuPHA) with the unique filamentous cyanobacteria, Pseudanabaena sp. ABRG 5-3 and Limnothrix sp. SK1-2-1. Continuous circular cultivation was driven under the indoor closed (IC) or indoor opened (IO) conditions and provided biomass yields of approximately 8 to 27 g dry cell weight (DCW) floor m -2 d -1 . Alkanes of heptadecane (C 17 H 36 ) or pentadecane (C 15 H 32 ) as liquid biofuels were also recovered from the lower liquid-phase, in which cyanobacteria were dropped from the upper solid-phase and continuously cultivated with a small amount of medium. After the main cultivation in DuPHA, the upper solid-phase of a cotton cloth on which cyanobacteria grew was dried and directly subjected to a combustion test. This resulted in the thermal power (kJ s -1 ) of the cloth with microalgae increasing approximately 20 to 50% higher than that of the cloth only, suggesting a possibility of using the solid phase with microalgae as solid biofuel. Copyright © 2018. Published by Elsevier B.V.

Wernher von Braun

NASA Image and Video Library

1950-01-01

Dr. von Braun stands beside a model of the upper stage (Earth-returnable stage) of the three-stage launch vehicle built for the series of the motion picture productions of space flight produced by Walt Disney in the mid-1950's.

A Composite Diagnosis of Synoptic-Scale Extratropical Cyclone Development over the United States

NASA Technical Reports Server (NTRS)

Rolfson, Donald M.; Smith, Phillip J.

1996-01-01

This paper presents a composite diagnosis of synoptic-scale forcing mechanisms associated with extratropical cyclone evolution. Drawn from 12 cyclone cases that occurred over the continental United States during the cool season months, the diagnosis provides a 'climatology' of development mechanisms for difference categories of cyclone evolution ranging from cyclone weakening through three stages of cyclone intensification. Computational results were obtained using an 'extended' form of the Zwack-Okossi equation applied to routine upper-air and surface data analyzed on a 230 km x 230 km grid. Results show that cyclonic vorticity advection, which maximizes in the upper troposphere, was the primary contributor to cyclone development regardless of the stage of development. A second consistent contributor to development was latent heat release. Horizontal temperature advection, often acknowledged as a development mechanism, was found to contribute to development only during more intense stages. During weakening and weaker development stages, temperature advection opposed development, as the warm-air advection invariably found at upper levels was dominated by cold air advection in the lower half of the troposphere. In the more intense stages, development was moderated by dry-adiabatic cooling associated with the ascending vertical motions.

Upper gastrointestinal symptoms in patients with advanced cancer: relationship to nutritional and performance status.

PubMed

Bovio, G; Montagna, G; Bariani, C; Baiardi, P

2009-10-01

The goals of the study were to determine the relationship of upper gastrointestinal symptoms with nutritional status and to assess their association with performance status in patients with advanced cancer. We studied 143 patients (50 F, 93 M, mean age 68 +/- 11 years, mean body mass index 22.39 +/- 4.3 kg/m(2)). Assessed symptoms were the following: anorexia, nausea, vomiting, dysphagia for solids, dysphagia for liquids, xerostomia, hypogeusia, dysgeusia, hiccup and chewing disturbances. We determined anthropometric parameters, daily energy intake and serum albumin, prealbumin and transferrin. The most common upper gastrointestinal symptoms were xerostomia (73%), anorexia (49%) and chewing disturbances (40%). Fifty-four percent of patients had weight loss greater than 10%. Seventy-three patients (51%) had daily energy intake lower than their resting energy expenditure. Mean serum prealbumin, albumin and transferrin were below normal range. Mean Eastern Cooperative Oncology Group performance status scale was 3.1 +/- 0.49. Symptoms were often strongly correlated, and usually, patients experienced at least three upper gastrointestinal symptoms at the same time. Anorexia, nausea and vomiting were the symptoms mostly correlated with other symptoms. A correlation was found between vomiting and hiccup. Energy intake (EI) was the nutritional parameter mostly affected by upper gastrointestinal symptoms; moreover, EI is the most predictive factor of upper gastrointestinal symptoms, particularly xerostomia, anorexia and dysphagia for solids. Upper gastrointestinal symptoms are linked to nutritional parameters: In particular, energy intake represents the most predictive variable of symptom occurrence. The performance status is not affected by upper gastrointestinal symptoms. A rigorous nutritional assessment and the managing of upper gastrointestinal symptoms are crucial in patients with advanced cancer.

Mechanical anisotropy control on strain localization in upper mantle shear zones

NASA Astrophysics Data System (ADS)

Herwegh, Marco; Mercolli, Ivan; Linckens, Jolien; Müntener, Othmar

2016-05-01

Mantle rocks at oceanic spreading centers reveal dramatic rheological changes from partially molten to solid-state ductile to brittle deformation with progressive cooling. Using the crustal-scale Wadi al Wasit mantle shear zone (SZ, Semail ophiolite, Oman), we monitor such changes based on quantitative field and microstructural investigations combined with petrological and geochemical analyses. The spatial distribution of magmatic dikes and high strain zones gives important information on the location of magmatic and tectonic activity. In the SZ, dikes derived from primitive melts (websterites) are distributed over the entire SZ but are more abundant in the center; dikes from more evolved, plagioclase saturated melts (gabbronorites) are restricted to the SZ center. Accordingly, harzburgite deformation fabrics show a transition from protomylonite (1100°C), mylonite (900-800°C) to ultramylonite (<700°C) and a serpentine foliation (<500°C) from the SZ rim to the center. The spatial correlation between solid-state deformation fabrics and magmatic features indicates progressive strain localization in the SZ on the cooling path. Three stages can be discriminated: (i) Cycles of melt injection (dunite channels and websterite dikes) and solid-state deformation (protomylonites-mylonites; 1100-900°C), (ii) dominant solid-state deformation in harzburgite mylonites (900-800°C) with some last melt injections (gabbronorites) and ultramylonites (<700°C), and (iii) infiltration of seawater inducing a serpentine foliation (<500°C) followed by cataclasis during obduction. The change of these processes in space and time indicates that early dike-related ridge-parallel deformation controls the onset of the entire strain localization history promoting nucleation sites for different strain weakening processes as a consequence of changing physicochemical conditions.

Strategies for the anaerobic digestion of the organic fraction of municipal solid waste: an overview.

PubMed

Hartmann, H; Ahring, B K

2006-01-01

Different process strategies for anaerobic digestion of the organic fraction of municipal solid waste (OFMSW) are reviewed weighing high-solids versus low-solids, mesophilic versus thermophilic and single-stage versus multi-stage processes. The influence of different waste characteristics such as composition of biodegradable fractions, C:N ratio and particle size is described. Generally, source sorting of OFMSW and a high content of food waste leads to higher biogas yields than the use of mechanically sorted OFMSW. Thermophilic processes are more efficient than mesophilic processes in terms of higher biogas yields at different organic loading rates (OLR). Highest biogas yields are achieved by means of wet thermophilic processes at OLRs lower than 6 kg-VS x m(-3) d(-1). High-solids processes appear to be relatively more efficient when OLRs higher than 6 kg-VS x m(-3)d(-1) are applied. Multi-stage systems show in some investigations a higher reduction of recalcitrant organic matter compared to single-stage systems, but they are seldom applied in full-scale. An extended cost-benefit calculation shows that the highest overall benefit of the process is achieved at an OLR that is lower and a hydraulic retention time (HRT) that is longer than those values of OLR and HRT, at which the highest biogas production is achieved.

Prospective Cohort Study Depending on the Use of Palliative Care for Advanced Stage of Cancer Patients

ClinicalTrials.gov

2017-09-05

Stage IV Breast Cancer; Stage IV Pancreatic Cancer; Stage IV Colon Cancer; Stage IV Gastric Cancer; Stage IV Lung Cancer; Stage IV Liver Cancer; Malignant Hematologic Neoplasm; Biliary Cancer Metastatic; Pediatric Leukemia; Pediatric Lymphoma; Pediatric Brain Tumor; Pediatric Solid Tumor

Growing a Training System and Culture for the Ares I Upper Stage Project

NASA Technical Reports Server (NTRS)

Scott, David W.

2009-01-01

In roughly two years time, Marshall Space Flight Center s (MSFC) Mission Operations Laboratory (MOL) has incubated a personnel training and certification program for about 1000 learners and multiple phases of the Ares I Upper Stage (US) project. Previous MOL-developed training programs focused on about 100 learners with a focus on operations, and had enough full-time training staff to develop courseware and provide training administration. This paper discusses 1) the basics of MOL's training philosophy, 2) how creation of a broad, structured training program unfolded as feedback from more narrowly defined tasks, 3) how training philosophy, development methods, and administration are being simplified and tailored so that many Upper Stage organizations can "grow their own" training yet maintain consistency, accountability, and traceability across the project, 4) interfacing with the production contractor's training system and staff, and 5) reaping training value from existing materials and events.

Development of a predictive model for 6 month survival in patients with venous thromboembolism and solid malignancy requiring IVC filter placement.

PubMed

Huang, Steven Y; Odisio, Bruno C; Sabir, Sharjeel H; Ensor, Joe E; Niekamp, Andrew S; Huynh, Tam T; Kroll, Michael; Gupta, Sanjay

2017-07-01

Our purpose was to develop a predictive model for short-term survival (i.e. <6 months) following inferior vena cava filter placement in patients with venous thromboembolism (VTE) and solid malignancy. Clinical and laboratory parameters were retrospectively reviewed for patients with solid malignancy who received a filter between January 2009 and December 2011 at a tertiary care cancer center. Multivariate Cox proportional hazards modeling was used to assess variables associated with 6 month survival following filter placement in patients with VTE and solid malignancy. Significant variables were used to generate a predictive model. 397 patients with solid malignancy received a filter during the study period. Three variables were associated with 6 month survival: (1) serum albumin [hazard ratio (HR) 0.496, P < 0.0001], (2) recent or planned surgery (<30 days) (HR 0.409, P < 0.0001), (3) TNM staging (stage 1 or 2 vs. stage 4, HR 0.177, P = 0.0001; stage 3 vs. stage 4, HR 0.367, P = 0.0002). These variables were used to develop a predictive model to estimate 6 month survival with an area under the receiver operating characteristic curve of 0.815, sensitivity of 0.782, and specificity of 0.715. Six month survival in patients with VTE and solid malignancy requiring filter placement can be predicted from three patient variables. Our predictive model could be used to help physicians decide whether a permanent or retrievable filter may be more appropriate as well as to assess the risks and benefits for filter retrieval within the context of survival longevity in patients with cancer.

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 - 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.

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.

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.

The Malemute development program. [rocket upper stage engine design

NASA Technical Reports Server (NTRS)

Bolster, W. J.; Hoekstra, P. W.

1976-01-01

The Malemute vehicle systems are two-stage systems based on utilizing a new high performance upper stage motor with two existing military boosters. The Malmute development program is described relative to program structure, preliminary design, vehicle subsystems, and the Malemute motor. Two vehicle systems, the Nike-Malemute and Terrier-Malemute, were developed which are capable of transporting comparatively large diameter (16 in.) 200-lb payloads to altitudes of 500 and 700 km, respectively. These vehicles provide relatively low-cost transportation with two-stage reliability and launch simplicity. Flight tests of both vehicle systems revealed their performance capabilities, with the Terrier-Malemute system involving a unique Malemute motor spin sensitivity problem. It is suggested that the vehicles can be successfully flown by lowering the burnout spin rate.

Vemurafenib in Treating Patients With Relapsed or Refractory Advanced Solid Tumors, Non-Hodgkin Lymphoma, or Histiocytic Disorders With BRAF V600 Mutations (A Pediatric MATCH Treatment Trial)

ClinicalTrials.gov

2018-06-25

Advanced Malignant Solid Neoplasm; Ann Arbor Stage III Childhood Non-Hodgkin Lymphoma; Ann Arbor Stage IV Childhood Non-Hodgkin Lymphoma; BRAF NP_004324.2:p.V600X; Ependymoma; Ewing Sarcoma; Hepatoblastoma; Histiocytosis; Langerhans Cell Histiocytosis; Malignant Germ Cell Tumor; Malignant Glioma; Osteosarcoma; Peripheral Primitive Neuroectodermal Tumor; Recurrent Childhood Central Nervous System Neoplasm; Recurrent Childhood Non-Hodgkin Lymphoma; Recurrent Malignant Solid Neoplasm; Recurrent Neuroblastoma; Refractory Central Nervous System Neoplasm; Refractory Malignant Solid Neoplasm; Refractory Neuroblastoma; Refractory Non-Hodgkin Lymphoma; Rhabdoid Tumor; Rhabdomyosarcoma; Soft Tissue Sarcoma; Wilms Tumor

From Paper to Production: An Update on NASA's Upper Stage Engine for Exploration

NASA Technical Reports Server (NTRS)

Kynard, Mike

2010-01-01

In 2006, NASA selected an evolved variant of the proven Saturn/Apollo J-2 upper stage engine to power the Ares I crew launch vehicle upper stage and the Ares V cargo launch vehicle Earth departure stage (EDS) for the Constellation Program. Any design changes needed by the new engine would be based where possible on proven hardware from the Space Shuttle, commercial launchers, and other programs. In addition to the thrust and efficiency requirements needed for the Constellation reference missions, it would be an order of magnitude safer than past engines. It required the J-2X government/industry team to develop the highest performance engine of its type in history and develop it for use in two vehicles for two different missions. In the attempt to achieve these goals in the past five years, the Upper Stage Engine team has made significant progress, successfully passing System Requirements Review (SRR), System Design Review (SDR), Preliminary Design Review (PDR), and Critical Design Review (CDR). As of spring 2010, more than 100,000 experimental and development engine parts have been completed or are in various stages of manufacture. Approximately 1,300 of more than 1,600 engine drawings have been released for manufacturing. This progress has been due to a combination of factors: the heritage hardware starting point, advanced computer analysis, and early heritage and development component testing to understand performance, validate computer modeling, and inform design trades. This work will increase the odds of success as engine team prepares for powerpack and development engine hot fire testing in calendar 2011. This paper will provide an overview of the engine development program and progress to date.

Development of the arterial pattern in the upper limb of staged human embryos: normal development and anatomic variations

PubMed Central

RODRÍGUEZ-NIEDENFÜHR, M.; BURTON, G. J.; DEU, J.; SAÑUDO, J. R.

2001-01-01

A total of 112 human embryos (224 upper limbs) between stages 12 and 23 of development were examined. It was observed that formation of the arterial system in the upper limb takes place as a dual process. An initial capillary plexus appears from the dorsal aorta during stage 12 and develops at the same rate as the limb. At stage 13, the capillary plexus begins a maturation process involving the enlargement and differentiation of selected parts. This remodelling process starts in the aorta and continues in a proximal to distal sequence. By stage 15 the differentiation has reached the subclavian and axillary arteries, by stage 17 it has reached the brachial artery as far as the elbow, by stage 18 it has reached the forearm arteries except for the distal part of the radial, and finally by stage 21 the whole arterial pattern is present in its definitive morphology. This differentiation process parallels the development of the skeletal system chronologically. A number of arterial variations were observed, and classified as follows: superficial brachial (7.7%), accessory brachial (0.6%), brachioradial (14%), superficial brachioulnar (4.7%), superficial brachioulnoradial (0.7%), palmar pattern of the median (18.7%) and superficial brachiomedian (0.7%) arteries. They were observed in embryos belonging to stages 17–23 and were not related to a specific stage of development. Statistical comparison with the rates of variations reported in adults did not show significant differences. It is suggested that the variations arise through the persistence, enlargement and differentiation of parts of the initial network which would normally remain as capillaries or even regress. PMID:11693301

Radical and sparing surgical treatment of patients with upper urinary tract transitional cell carcinomas (UUT -TCC) - preliminary results.

PubMed

Jabłonowski, Zbigniew; Kędzierski, Robert; Sosnowski, Marek

2011-01-01

Tumors originating from transitional epithelium of the renal pelvis and ureter are infrequent. Their course is asymptomatic at early stages of the disease, and diagnosis and institution of appropriate treatment delayed. The aim of the study is to assess the results of treatment in patients with upper urinary tract transitional cell carcinomas (UUT-TCC). Fifteen patients treated in 2005-2010 for UUT-TCC were qualified for the retrospective study. Clinical symptoms, diagnostic methods, tumor location, clinical stage and histopathological characteristics of the tumors were assessed. Then, the instituted treatment and its results were analyzed. The average follow-up period was 51 month (range 6-65), UUT-TCC accounted for 6.7% of renal tumors treated. Concurrent treated vesical tumors were observed in 4 (26.7%) patients. Primary UUT-TCC was diagnosed in 10 (66.7%) patients. Radical surgery was performed in 10 (66.7%) patients, whereas 5 (33.3%) underwent sparing operations. Macroscopic hematuria was the predominant clinical symptom. In most cases T2-T3 clinical stage (60.0%) and high-grade (66.7%) were observed. Development of an upper urinary tract tumor after treatment of a vesical tumor was noted in 4 (26.7%) patients. During the follow-up period, urinary bladder carcinomas were diagnosed in 5 (33.3%) patients with primary upper urinary tract tumors. Nephroureterectomy remains the standard treatment for UUT-TCC. Organ-sparing surgery is possible in selected patients with low clinical stage and low grade tumors. Patients treated for urinary bladder carcinomas require regular monitoring of the upper urinary tract.

Zone separator for multiple zone vessels

DOEpatents

Jones, John B.

1983-02-01

A solids-gas contact vessel, having two vertically disposed distinct reaction zones, includes a dynamic seal passing solids from an upper to a lower zone and maintaining a gas seal against the transfer of the separate treating gases from one zone to the other, and including a stream of sealing fluid at the seal.

Spreadsheet Modeling of Electron Distributions in Solids

ERIC Educational Resources Information Center

Glassy, Wingfield V.

2006-01-01

A series of spreadsheet modeling exercises constructed as part of a new upper-level elective course on solid state materials and surface chemistry is described. The spreadsheet exercises are developed to provide students with the opportunity to interact with the conceptual framework where the role of the density of states and the Fermi-Dirac…

Transport and Use of a Centaur Second Stage in Space

NASA Technical Reports Server (NTRS)

Strong, James M.; Morgowicz, Bernard; Drucker, Eric; Tompkins, Paul D.; Kennedy, Brian; Barber, Robert D,; Luzod, Louie T.; Kennedy, Brian Michael; Luzod, Louie T.

2010-01-01

As nations continue to explore space, the desire to reduce costs will continue to grow. As a method of cost reduction, transporting and/or use of launch system components as integral components of missions may become more commonplace in the future. There have been numerous scenarios written for using launch vehicle components (primarily space shuttle used external tanks) as part of flight missions or future habitats. Future studies for possible uses of launch vehicle upper stages might include asteroid diverter using gravity orbital perturbation, orbiting station component, raw material at an outpost, and kinetic impactor. The LCROSS (Lunar CRater Observation and Sensing Satellite) mission was conceived as a low-cost means of determining whether water exists at the polar regions of the moon. Manifested as a secondary payload with the LRO (Lunar Reconnaissance Orbiter) spacecraft aboard an Atlas V launch vehicle, LCROSS guided its spent Centaur Earth Departure Upper Stage (EDUS) into the lunar crater Cabeu's, as a kinetic impactor. This paper describes some of the challenges that the LCROSS project encountered in planning, designing, launching with and carrying the Centaur upper stage to the moon.

Gamma-Secretase Inhibitor RO4929097 and Cediranib Maleate in Treating Patients With Advanced Solid Tumors

ClinicalTrials.gov

2014-12-22

Adult Anaplastic Astrocytoma; Adult Anaplastic Ependymoma; Adult Anaplastic Oligodendroglioma; Adult Brain Stem Glioma; Adult Giant Cell Glioblastoma; Adult Glioblastoma; Adult Gliosarcoma; Adult Mixed Glioma; Adult Solid Neoplasm; Male Breast Carcinoma; Recurrent Adult Brain Neoplasm; Recurrent Breast Carcinoma; Recurrent Colon Carcinoma; Recurrent Melanoma; Recurrent Non-Small Cell Lung Carcinoma; Recurrent Ovarian Carcinoma; Recurrent Ovarian Germ Cell Tumor; Recurrent Pancreatic Carcinoma; Recurrent Rectal Carcinoma; Recurrent Renal Cell Carcinoma; Stage III Pancreatic Cancer; Stage III Renal Cell Cancer; Stage IIIA Colon Cancer; Stage IIIA Non-Small Cell Lung Cancer; Stage IIIA Ovarian Cancer; Stage IIIA Ovarian Germ Cell Tumor; Stage IIIA Rectal Cancer; Stage IIIA Skin Melanoma; Stage IIIB Breast Cancer; Stage IIIB Colon Cancer; Stage IIIB Non-Small Cell Lung Cancer; Stage IIIB Ovarian Cancer; Stage IIIB Ovarian Germ Cell Tumor; Stage IIIB Rectal Cancer; Stage IIIB Skin Melanoma; Stage IIIC Breast Cancer; Stage IIIC Colon Cancer; Stage IIIC Ovarian Cancer; Stage IIIC Ovarian Germ Cell Tumor; Stage IIIC Rectal Cancer; Stage IIIC Skin Melanoma; Stage IV Breast Cancer; Stage IV Non-Small Cell Lung Cancer; Stage IV Ovarian Cancer; Stage IV Ovarian Germ Cell Tumor; Stage IV Pancreatic Cancer; Stage IV Renal Cell Cancer; Stage IV Skin Melanoma; Stage IVA Colon Cancer; Stage IVA Rectal Cancer; Stage IVB Colon Cancer; Stage IVB Rectal Cancer

Tissue expansion in the treatment of giant congenital melanocytic nevi of the upper extremity

PubMed Central

Ma, Tengxiao; Fan, Ke; Li, Lei; Xie, Feng; Li, Hao; Chou, Haiyan; Zhang, Zhengwen

2017-01-01

Abstract The aim of our study was to use tissue expansion for the treatment of giant congenital melanocytic nevi of the upper extremity and examine potential advantages over traditional techniques. There were 3 stages in the treatment of giant congenital melanocytic nevi of the upper extremities using tissue expansion: first, the expander was inserted into the subcutaneous pocket; second, the expander was removed, lesions were excised, and the wound of the upper extremity was placed into the pocket to delay healing; third, the residual lesion was excised and the pedicle was removed. The pedicle flap was then unfolded to resurface the wound. During the period between June 2007 and December 2015, there were 11 patients with giant congenital melanocytic nevi of the upper extremities who underwent reconstruction at our department with skin expansion. Few complications were noted in each stage of treatment. The functional and aesthetic results were observed and discussed in this study. Optimal aesthetic and functional results were obtained using tissue expansion to reconstruct the upper extremities due to the giant congenital melanocytic nevi. PMID:28353563

Solid oxide fuel cell with monolithic core

DOEpatents

McPheeters, Charles C.; Mrazek, Franklin C.

1988-01-01

A solid oxide fuel cell in which fuel and oxidant gases undergo an electrochemical reaction to produce an electrical output includes a monolithic core comprised of a corrugated conductive sheet disposed between upper and lower generally flat sheets. The corrugated sheet includes a plurality of spaced, parallel, elongated slots which form a series of closed, linear, first upper and second lower gas flow channels with the upper and lower sheets within which a fuel gas and an oxidant gas respectively flow. Facing ends of the fuel cell are generally V-shaped and provide for fuel and oxidant gas inlet and outlet flow, respectively, and include inlet and outlet gas flow channels which are continuous with the aforementioned upper fuel gas and lower oxidant gas flow channels. The upper and lower flat sheets and the intermediate corrugated sheet are preferably comprised of ceramic materials and are securely coupled together such as by assembly in the green state and sintering together during firing at high temperatures. A potential difference across the fuel cell, or across a stacked array of similar fuel cells, is generated when an oxidant gas such as air and a fuel such as hydrogen gas is directed through the fuel cell at high temperatures, e.g., between 700.degree. C. and 1100.degree. C.

Solid oxide fuel cell with monolithic core

DOEpatents

McPheeters, C.C.; Mrazek, F.C.

1988-08-02

A solid oxide fuel cell in which fuel and oxidant gases undergo an electrochemical reaction to produce an electrical output includes a monolithic core comprised of a corrugated conductive sheet disposed between upper and lower generally flat sheets. The corrugated sheet includes a plurality of spaced, parallel, elongated slots which form a series of closed, linear, first upper and second lower gas flow channels with the upper and lower sheets within which a fuel gas and an oxidant gas respectively flow. Facing ends of the fuel cell are generally V-shaped and provide for fuel and oxidant gas inlet and outlet flow, respectively, and include inlet and outlet gas flow channels which are continuous with the aforementioned upper fuel gas and lower oxidant gas flow channels. The upper and lower flat sheets and the intermediate corrugated sheet are preferably comprised of ceramic materials and are securely coupled together such as by assembly in the green state and sintering together during firing at high temperatures. A potential difference across the fuel cell, or across a stacked array of similar fuel cells, is generated when an oxidant gas such as air and a fuel such as hydrogen gas is directed through the fuel cell at high temperatures, e.g., between 700 C and 1,100 C. 8 figs.

Systemic irradiation for selected stage IV and recurrent pediatric solid tumors: method, toxicity, and preliminary results

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

Wharam, M.D.; Kaizer, H.; Leventhal, B.G.

1980-02-01

Eight patients with advanced pediatric solid tumors received either sequential upper and lower half-body irradiation (HBI) (7.5 rad/min to 500 rad total) or total body irradiation (TBI) (7.5 rad/min to 800 rad total) as part of two multimodality treatment regimens. All patients received combination chemotherapy; drugs were determined by the tumor type. The TBI regimen was selected for two patients who had progression of disease with conventional chemotherapy and for two patients with stage IV neuroblastoma. This intensive regimen consisted of bone marrow harvesting, followed by local radiation to gross disease, marrow-ablative chemotherapy, TBI, and re-infusion of the cryopreserved autologousmore » marrow. Significant acute toxicity was followed by hematologic reconstitution in each patient within seven weeks. At this writing, two patients survived, one of whom is disease free two and one half years without maintenance chemotherapy. A less intensive, outpatient regimen was selected for four patients; three had a complete or good partial response to chemotherapy. The fourth patient had tumor-involved bone marrow not responsive to chemotherapy and was therefore ineligible for marrow cryopreservation and TBI. Each of these four patients received HBI after chemotherapy and local radiation to the primary and/or metastatic sites. Acute toxicity was limited to nausea and vomiting. Significant leukopenia and thrombocytopenia occurred in three patients. All four patients were alive 10 to 26 months post HBI. This pilot study demonstrates that chemotherapy can be integrated with local fractionated radiation, and systemic radiation given as HBI or TBI with acceptable toxicity; sufficient bone marrow stem cells can be harvested after conventional chemotherapy and then cryopreserved to permit hematologic reconstitution of the patient who receives marrow ablative therapy.« less

Present state of knowledge of the upper atmosphere: An assessment report

NASA Technical Reports Server (NTRS)

1984-01-01

A program of research, technology, and monitoring of the phenomena of the upper atmosphere, to provide for an understanding of and to maintain the chemical and physical integrity of the Earth's upper atmosphere was developed. NASA implemented a long-range upper atmospheric science program aimed at developing an organized, solid body of knowledge of upper atmospheric processes while providing, in the near term, assessments of potential effects of human activities on the atmosphere. The effects of chlorofluorocarbon (CFC) releases on stratospheric ozone were reported. Issues relating the current understanding of ozone predictions and trends and highlights recent and future anticipated developments that will improve our understanding of the system are summarized.

Restartable solid motor stage for shuttle applications

NASA Technical Reports Server (NTRS)

Rohrbaugh, D. J.

1973-01-01

The application of restartable solid motor stages to shuttle missions has been shown to provide a viable supplement to the shuttle program. Restartable solid motors in the 3000 pound class provide a small expendable transfer stage that reduces the demand on the shuttle for the lower energy missions. Shuttle operational requirements and preliminary performance data provided an input for defining design features required for restartable solid motor applications. These data provided a basis for a configuration definition that is compatible with shuttle operations. Mission by mission analysis showed the impact on a NASA supplied mission model. The results showed a 15% reduction in the number of shuttle flights required. In addition the amount of shuttle capability used to complete the mission objectives was significantly reduced. For example, in the 1979 missions there was a 62% reduction in shuttle capability used. The study also showed that the solid motor could provide a supplement to the TUG that would allow TUGS to be used in a recoverable rather than an expendable mode. The study shows a 71% reduction in the number of TUGs that would be expended.

Synthesis of 10-Ethyl Flavin: A Multistep Synthesis Organic Chemistry Laboratory Experiment for Upper-Division Undergraduate Students

ERIC Educational Resources Information Center

Sichula, Vincent A.

2015-01-01

A multistep synthesis of 10-ethyl flavin was developed as an organic chemistry laboratory experiment for upper-division undergraduate students. Students synthesize 10-ethyl flavin as a bright yellow solid via a five-step sequence. The experiment introduces students to various hands-on experimental organic synthetic techniques, such as column…

Gasification of carbonaceous solids

DOEpatents

Coates, Ralph L.

1976-10-26

A process and apparatus for converting coal and other carbonaceous solids to an intermediate heating value fuel gas or to a synthesis gas. A stream of entrained pulverized coal is fed into the combustion stage of a three-stage gasifier along with a mixture of oxygen and steam at selected pressure and temperature. The products of the combustion stage pass into the second or quench stage where they are partially cooled and further reacted with water and/or steam. Ash is solidified into small particles and the formation of soot is suppressed by water/steam injections in the quench stage. The design of the quench stage prevents slag from solidifying on the walls. The products from the quench stage pass directly into a heat recovery stage where the products pass through the tube, or tubes, of a single-pass, shell and tube heat exchanger and steam is generated on the shell side and utilized for steam feed requirements of the process.

STS-41 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Camp, David W.; Germany, D. M.; Nicholson, Leonard S.

1990-01-01

The STS-41 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem activities on this thirty-sixth flight of the Space Shuttle and the eleventh flight of the Orbiter vehicle, Discovery (OV-103). In addition to the Discovery vehicle, the flight vehicle consisted of an External Tank (ET) (designated as ET-39/LWT-32), three Space Shuttle main engines (SSME's) (serial numbers 2011, 2031, and 2107), and two Solid Rocket Boosters (SRB's), designated as BI-040. The primary objective of the STS-41 mission was to successfully deploy the Ulysses/inertial upper stage (IUS)/payload assist module (PAM-S) spacecraft. The secondary objectives were to perform all operations necessary to support the requirements of the Shuttle Backscatter Ultraviolet (SSBUV) Spectrometer, Solid Surface Combustion Experiment (SSCE), Space Life Sciences Training Program Chromosome and Plant Cell Division in Space (CHROMEX), Voice Command System (VCS), Physiological Systems Experiment (PSE), Radiation Monitoring Experiment - 3 (RME-3), Investigations into Polymer Membrane Processing (IPMP), Air Force Maui Optical Calibration Test (AMOS), and Intelsat Solar Array Coupon (ISAC) payloads. The sequence of events for this mission is shown in tabular form. Summarized are the significant problems that occurred in the Orbiter subsystems during the mission. The official problem tracking list is presented. In addition, each Orbiter problem is cited in the subsystem discussion.

Overview of the Main Propulsion System for the NASA Ares I Upper Stage

NASA Technical Reports Server (NTRS)

Quinn, Jason E.; Swanson, Luke A.

2009-01-01

A functional overview of the Main Propulsion System (MPS) of the NASA Ares I Upper Stage is provided. In addition to a simple overview of the key MPS functions and design philosophies, major lessons learned are discussed. The intent is to provide a technical overview with enough detail to allow engineers outside of the MPS Integrated Product Team (IPT) to develop a rough understanding of MPS operations, components, design philosophy, and lessons learned.

LOX/LH2 propulsion system for launch vehicle upper stage, test results

NASA Technical Reports Server (NTRS)

Ikeda, T.; Imachi, U.; Yuzawa, Y.; Kondo, Y.; Miyoshi, K.; Higashino, K.

1984-01-01

The test results of small LOX/LH2 engines for two propulsion systems, a pump fed system and a pressure fed system are reported. The pump fed system has the advantages of higher performances and higher mass fraction. The pressure fed system has the advantages of higher reliability and relative simplicity. Adoption of these cryogenic propulsion systems for upper stage of launch vehicle increases the payload capability with low cost. The 1,000 kg thrust class engine was selected for this cryogenic stage. A thrust chamber assembly for the pressure fed propulsion system was tested. It is indicated that it has good performance to meet system requirements.

Validation of the Omron M3 Intellisense (HEM-7051-E) upper arm blood pressure monitor, for self-measurement, according to the European Society of Hypertension International Protocol revision 2010 in a stage 3-5 chronic kidney disease population.

PubMed

Akpolat, Tekin; Erdem, Emre; Aydogdu, Türkan

2012-01-01

Encouragement of home blood pressure (BP) monitoring has a great potential to improve hypertension control rates. The purpose of this study was to test validation of the Omron M3 Intellisense (HEM-7051-E) upper arm BP measuring monitor for self-measurement according to the European Society of Hypertension International Protocol revision 2010 (ESH-IP2) in stage 3-5 chronic kidney disease (CKD) patients. 66 patients having CKD stage 3-5 were included in the study. Nine consecutive measurements were made according to the ESH-IP2 protocol. The Omron M3 Intellisense device fulfills the validation criteria of the ESH-IP2 for stage 3-5 CKD patients. Although arterial stiffness can affect accurate BP measurement, there are limited data regarding the use of automated oscillometric devices in CKD. To our knowledge, this is the first study investigating validation of an oscillometric device in stage 3-5 predialysis CKD patients. This study validates the Omron M3 Intellisense upper arm device for stage 3-5 CKD patients. New validation studies investigating other oscillometric sphygmomanometers for CKD patients and involvement of nephrologists in these studies have great potential to increase patient care in CKD. Copyright © 2011 S. Karger AG, Basel.

Glacial stages and post-glacial environmental evolution in the Upper Garonne valley, Central Pyrenees.

PubMed

Fernandes, M; Oliva, M; Palma, P; Ruiz-Fernández, J; Lopes, L

2017-04-15

The maximum glacial extent in the Central Pyrenees during the Last Glaciation is known to have occurred before the global Last Glacial Maximum, but the succession of cold events afterwards and their impact on the landscape are still relatively unknown. This study focuses on the environmental evolution in the upper valley of the Garonne River since the Last Glaciation. Geomorphological mapping allows analysis of the spatial distribution of inherited and current processes and landforms in the study area. The distribution of glacial records (moraines, till, erratic boulders, glacial thresholds) suggests the existence of four glacial stages, from the maximum expansion to the end of the glaciation. GIS modeling allows quantification of the Equilibrium Line Altitude, extent, thickness and volume of ice in each glacial stage. During the first stage, the Garonne glacier reached 460m in the Loures-Barousse-Barbazan basin, where it formed a piedmont glacier 88km from the head and extended over 960km 2 . At a second stage of glacier stabilization during the deglaciation process, the valley glaciers were 12-23km from the head until elevations of 1000-1850m, covering an area of 157km 2 . Glaciers during stage three remained isolated in the upper parts of the valley, at heights of 2050-2200m and 2.6-4.5km from the head, with a glacial surface of 16km 2 . In stage four, cirque glaciers were formed between 2260m and 2590m, with a length of 0.4-2km and a glacial area of 5.7km 2 . Also, the wide range of periglacial, slope, nival and alluvial landforms existing in the formerly glaciated environments allows reconstruction of the post-glacial environmental dynamics in the upper Garonne basin. Today, the highest lands are organized following three elevation belts: subnival (1500-1900m), nival (1900-2300m) and periglacial/cryonival (2300-2800m). Copyright © 2017 Elsevier B.V. All rights reserved.

Solid-State Powered X-band Accelerator

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

Othman, Mohamed A.K.; Nann, Emilio A.; Dolgashev, Valery A.

2017-03-06

In this report we disseminate the hot test results of an X-band 100-W solid state amplifier chain for linear accelerator (linac) applications. Solid state power amplifiers have become increasingly attractive solutions for achieving high power in radar and maritime applications. Here the performance of solid state amplifiers when driving an RF cavity is investigated. Commercially available, matched and fully-packaged GaN on SiC HEMTs are utilized, comprising a wideband driver stage and two power stages. The amplifier chain has a high poweradded- efficiency and is able to supply up to ~1.2 MV/m field gradient at 9.2 GHz in a simple testmore » cavity, with a peak power exceeding 100 W. These findings set forth the enabling technology for solid-state powered linacs.« less

Dr. von Braun With a Model of a Launch Vehicle

NASA Technical Reports Server (NTRS)

1950-01-01

Dr. von Braun stands beside a model of the upper stage (Earth-returnable stage) of the three-stage launch vehicle built for the series of the motion picture productions of space flight produced by Walt Disney in the mid-1950's.

Idebenone-loaded solid lipid nanoparticles for drug delivery to the skin: in vitro evaluation.

PubMed

Montenegro, Lucia; Sinico, Chiara; Castangia, Ines; Carbone, Claudia; Puglisi, Giovanni

2012-09-15

Idebenone (IDE), a synthetic derivative of ubiquinone, shows a potent antioxidant activity that could be beneficial in the treatment of skin oxidative damages. In this work, the feasibility of targeting IDE into the upper layers of the skin by topical application of IDE-loaded solid lipid nanoparticles (SLN) was evaluated. SLN loading different amounts of IDE were prepared by the phase inversion temperature method using cetyl palmitate as solid lipid and three different non-ionic surfactants: ceteth-20, isoceteth-20 and oleth-20. All IDE loaded SLN showed a mean particle size in the range of 30-49 nm and a single peak in size distribution. In vitro permeation/penetration experiments were performed on pig skin using Franz-type diffusion cells. IDE penetration into the different skin layers depended on the type of SLN used while no IDE permeation occurred from all the SLN under investigation. The highest IDE content was found in the epidermis when SLN contained ceteth-20 or isoceteth-20 as surfactant while IDE distribution into the upper skin layers depended on the amount of IDE loaded when oleth-20 was used as surfactant. These results suggest that the SLN tested could be an interesting carrier for IDE targeting to the upper skin layers. Copyright © 2012 Elsevier B.V. All rights reserved.

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.

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.

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.

The Delta launch vehicle Model 2914 series

NASA Technical Reports Server (NTRS)

Gunn, C. R.

1973-01-01

Description of a new, medium-class Delta launch-vehicle configuration, the three-stage Model 2914. The first stage of this vehicle is composed of a liquid-propellant core which is thrust-augmented with up to nine strap-on solid-propellant motors. The second stage, recently uprated with a strap-down inertial guidance system, is now being modified to adapt the liquid-propellant descent engine from the Apollo Lunar Excursion Module. The third stage is a spin-stabilized solid-propellant motor. The Model 2914 is capable of injecting 2040 kg into low earth orbit, 705 kg into geosynchronous transfer orbit, or 455 kg into an escape trajectory.

Middle Pleistocene Climate Change Recorded in Fossil Mammal Teeth from Tarija, Bolivia, and Upper Limit of the Ensenadan Land-Mammal Age

NASA Astrophysics Data System (ADS)

MacFadden, Bruce J.

2000-07-01

Fossiliferous middle Pleistocene sediments of the Tarija basin of southern Bolivia contain a classic Ensenadan land-mammal fauna. New carbon isotopic data reported here for 50 specimens of the grazing mammals Equus (horse) and Cuvieronius (mastodon), documented from eight stratigraphic levels at Tarija, vary significantly in the δ13C values of their teeth. The pattern of variation appears to reflect the proportion of C3 and C4 grasses eaten during colder (more C3) and warmer (more C4) times. Within age limits set by associated magnetostratigraphy, the cold periods can be correlated with particular even-numbered stages in the marine oxygen-isotope record, and the warm periods can be correlated with odd-numbered stages. The oldest fossil teeth analyzed from the Tarija section can thereby be assigned to stage 29, and the youngest to stages 17 or 15, that is; the teeth range in age from about 1.1 myr to as young as 0.7 myr. Based on correlation of the upper part of the Tarija beds to the isotopic stages, the upper limit of the Ensenadan land-mammal age is between 0.7 and 0.6 myr, which is younger than stated in most previous studies.

Evolution of oceanic molybdenum and uranium reservoir size around the Ediacaran-Cambrian transition: Evidence from western Zhejiang, South China

NASA Astrophysics Data System (ADS)

Xiang, Lei; Schoepfer, Shane D.; Shen, Shu-zhong; Cao, Chang-qun; Zhang, Hua

2017-04-01

The "Cambrian explosion" is one of the most fascinating episodes of diversification in the history of life; however, its relationship to the oxygenation of the oceans and atmosphere around the Ediacaran-Cambrian transition is not fully understood. Marine inventories of redox-sensitive trace elements reflect the relative balance of oxidative weathering on land and deposition in anoxic water masses, and can be used to explore the evolution of oceanic and atmospheric redox conditions. For this study, we conducted a series of geochemical analyses on the upper Lantian, Piyuancun, and Hetang formations in the Chunye-1 well, part of the lower Yangtze Block in western Zhejiang. Iron speciation results indicate that the entire studied interval was deposited under anoxic conditions, with three intervals of persistent euxinia occurring in the uppermost Lantian Fm., the lower Hetang Formation (Fm.), and the upper Hetang Fm. Molybdenum (Mo) and uranium (U) contents and Mo/TOC and U/TOC ratios from the anoxic/euxinic intervals of the Chunye-1 well, combined with published data from the sections in the middle and upper Yangtze Block, suggest that the oceanic Mo reservoir declined consistently from the Ediacaran to Cambrian Stage 3, while the size of the oceanic U reservoir remained relatively constant. Both metals were depleted in the ocean in lower Cambrian Stage 4, before increasing markedly at the end of Stage 4. The lack of an apparent increase in the size of the marine Mo and U reservoir from the upper Ediacaran to Cambrian Stage 3 suggests that oxic water masses did not expand until Cambrian Stage 4. The increase in marine Mo and U availability in the upper Hetang Fm. may have been due to the expansion of oxic water masses in the oceans, associated with oxygenation of the atmosphere during Cambrian Stage 4. This expansion of oxic waters in the global ocean postdates the main phase of Cambrian diversification, suggesting that pervasive oxygenation of the ocean on a large scale was not the primary control on animal diversity following the Ediacaran-Cambrian transition.

High-efficiency removal of phytic acid in soy meal using two-stage temperature-induced Aspergillus oryzae solid-state fermentation.

PubMed

Chen, Liyan; Vadlani, Praveen V; Madl, Ronald L

2014-01-15

Phytic acid of soy meal (SM) could influence protein and important mineral digestion of monogastric animals. Aspergillus oryzae (ATCC 9362) solid-state fermentation was applied to degrade phytic acid in SM. Two-stage temperature fermentation protocol was investigated to increase the degradation rate. The first stage was to maximize phytase production and the second stage was to realize the maximum enzymatic degradation. In the first stage, a combination of 41% moisture, a temperature of 37 °C and inoculum size of 1.7 mL in 5 g substrate (dry matter basis) favored maximum phytase production, yielding phytase activity of 58.7 U, optimized via central composite design. By the end of second-stage fermentation, 57% phytic acid was degraded from SM fermented at 50 °C, compared with 39% of that fermented at 37 °C. The nutritional profile of fermented SM was also studied. Oligosaccharides were totally removed after fermentation and 67% of total non-reducing polysaccharides were decreased. Protein content increased by 9.5%. Two-stage temperature protocol achieved better phytic acid degradation during A. oryzae solid state fermentation. The fermented SM has lower antinutritional factors (phytic acid, oligosaccharides and non-reducing polysaccharides) and higher nutritional value for animal feed. © 2013 Society of Chemical Industry.

Do-It-Yourself Guide to: A Solid Waste Seminar. Construction Plans and Use Guidelines.

ERIC Educational Resources Information Center

Quarry Hill Nature Center, Rochester, Minn.

Ten learning stations dealing with solid waste comprise the seminar described in this booklet. At each station, students observe a display and then answer questions listed on their data sheets. Although the seminar was intended for junior high school students, it has been used successfully with upper elementary and adult participants. Among the…

Electrocatalytic cermet gas detector/sensor

DOEpatents

Vogt, Michael C.; Shoemarker, Erika L.; Fraioli, deceased, Anthony V.

1995-01-01

An electrocatalytic device for sensing gases. The gas sensing device includes a substrate layer, a reference electrode disposed on the substrate layer comprised of a nonstoichiometric chemical compound enabling oxygen diffusion therethrough, a lower reference electrode coupled to the reference electrode, a solid electrolyte coupled to the lower reference electrode and an upper catalytically active electrode coupled to the solid electrolyte.

Alkene Isomerization Using a Solid Acid as Activator and Support for a Homogeneous Catalyst

ERIC Educational Resources Information Center

Seen, Andrew J.

2004-01-01

An upper-level undergraduate experiment that, in addition to introducing students to catalysis using an air sensitive transition-metal complex, introduces the use of a solid acid as an activator and support for the catalyst is developed. The increased stability acquired in the course of the process affords the opportunity to characterize the…

Gain-loss study along two streams in the upper Sabine River basin, Texas; August-September 1981

USGS Publications Warehouse

Myers, Dennis R.

1983-01-01

Dissolved solids concentrations in the Sabine River, estimated from specific conductance, increased from about 120 milligrams per liter near the upstream end of the reach to about 400 milligrams per liter near the downstream end of the reach. Water with these concentrations of dissolved solids generally is suitable for most uses.

Diagnostic Laparoscopy

MedlinePlus

... Series SAGES Masters Program Facebook Collaboratives Acute Care Surgery Bariatric Biliary Colorectal Flexible Endoscopy (upper or lower) Foregut Hernia Robotics The SAGES HPB/Solid Organ Program The SAGES ...

Flood-inundation maps for the Saddle River from Upper Saddle River Borough to Saddle River Borough, New Jersey, 2013

USGS Publications Warehouse

Watson, Kara M.; Hoppe, Heidi L.

2013-01-01

Digital flood-inundation maps for a 4.1-mile reach of the Saddle River from 0.6 miles downstream from the New Jersey-New York State boundary in Upper Saddle River Borough to 0.2 miles downstream from the East Allendale Road bridge in Saddle River Borough, New Jersey, were created by the U.S. Geological Survey (USGS) in cooperation with the New Jersey Department of Environmental Protection (NJDEP). The inundation maps, which can be accessed through the USGS Flood Inundation Mapping Science Web site at http://water.usgs.gov/osw/flood_inundation/, depict estimates of the areal extent and depth of flooding corresponding to select water levels (stages) at the USGS streamgage 01390450, Saddle River at Upper Saddle River, New Jersey. Current conditions for estimating near real-time areas of inundation using USGS streamgage information may be obtained on the Internet at http://waterdata.usgs.gov/nwis/uv?site_no=01390450. The National Weather Service (NWS) forecasts flood hydrographs at many places that are often collocated with USGS streamgages. NWS-forecasted peak-stage information may be used in conjunction with the maps developed in this study to show predicted areas of flood inundation. In this study, flood profiles were computed for the stream reach by means of a one-dimensional step-backwater model. The model was calibrated by using the most current stage-discharge relations (in effect March 2013) at USGS streamgage 01390450, Saddle River at Upper Saddle River, New Jersey, and documented high-water marks from recent floods. The hydraulic model was then used to determine eight water-surface profiles for flood stages at 0.5-foot (ft) intervals referenced to the streamgage datum, North American Vertical Datum of 1988 (NAVD 88), and ranging from bankfull, 0.5 ft below NWS Action Stage, to the upper extent of the stage-discharge rating which is approximately 1 ft higher than the highest recorded water level at the streamgage. Action Stage is the stage which when reached by a rising stream the NWS or a partner needs to take some type of mitigation action in preparation for possible significant hydrologic activity. The simulated water-surface profiles were then combined with a geographic information system 3-meter (9.84 ft) digital elevation model (derived from Light Detection and Ranging (LiDAR) data) in order to delineate the area flooded at each water level. The availability of these maps along with real-time streamflow data and information regarding current stage from USGS streamgages and forecasted stream stages from the NWS provide emergency management personnel and residents with information that is critical for flood response activities, such as evacuations and road closures, as well as for post-flood recovery efforts.

Saturn Apollo Program

NASA Image and Video Library

1962-04-25

The second flight of the Saturn I vehicle, the SA-2, was successfully launched from Cape Canaveral, Florida on April 15, 1962. This vehicle had a secondary mission. After the first stage shutoff, at a 65-mile altitude, the water-filled upper stage was exploded, dumping 95 tons of water in the upper atmosphere. The resulting massive ice cloud rose to a height of 90 miles. The experiment, called Project Highwater, was intended to investigate the effects on the ionosphere of the sudden release of such a great volume of water.

J-2X Upper Stage Engine: Hardware and Testing 2009

NASA Technical Reports Server (NTRS)

Buzzell, James C.

2009-01-01

Mission: Common upper stage engine for Ares I and Ares V. Challenge: Use proven technology from Saturn X-33, RS-68 to develop the highest Isp GG cycle engine in history for 2 missions in record time . Key Features: LOX/LH2 GG cycle, series turbines (2), HIP-bonded MCC, pneumatic ball-sector valves, on-board engine controller, tube-wall regen nozzle/large passively-cooled nozzle extension, TEG boost/cooling . Development Philosophy: proven hardware, aggressive schedule, early risk reduction, requirements-driven.

Design and Stability of an On-Orbit Attitude Control System Using Reaction Control Thrusters

NASA Technical Reports Server (NTRS)

Hall, Robert A.; Hough, Steven; Orphee, Carolina; Clements, Keith

2016-01-01

NASA is providing preliminary design and requirements for the Space Launch System Exploration Upper Stage (EUS). The EUS will provide upper stage capability for vehicle ascent as well as on-orbit control capability. Requirements include performance of on-orbit burn to provide Orion vehicle with escape velocity. On-orbit attitude control is accommodated by a on-off Reaction Control System (RCS). Paper provides overview of approaches for design and stability of an attitude control system using a RCS.

The hydrolytic stage in high solids temperature phased anaerobic digestion improves the downstream methane production rate.

PubMed

Buffière, P; Dooms, M; Hattou, S; Benbelkacem, H

2018-07-01

The role of the hydrolytic stage in high solids temperature phased anaerobic digestion was investigated with a mixture of cattle slurry and maize silage with variable ratios (100, 70 and 30% volatile solids coming from cattle slurry). It was incubated for 48 h at 37, 55, 65 and 72 °C. Soluble chemical oxygen demand and biochemical methane potential were measured at 0, 24 and 48 h. Higher temperatures improved the amount of solubilized COD, which confirmed previously reported results. Nevertheless, solubilization mostly took place during the first 24 h. The rate of methane production in post-hydrolysis BMPs increased after 48 h hydrolysis time, but not after 24 h. The first order kinetic constant rose by 40% on average. No correlation was observed between soluble COD and downstream methane production rate, indicating a possible modification of the physical structure of the particulate solids during the hydrolytic stage. Copyright © 2018 Elsevier Ltd. All rights reserved.

Deep artesian aquifers of Sanibel and Captiva Islands, Lee County, Florida

USGS Publications Warehouse

Boggess, D.H.; O'Donnell, T. H.

1982-01-01

The principal sources of water on Sanibel and Captiva Islands, Lee County, Florida, are two deep artesian aquifers within the upper and lower parts of the Hawthorn Formation. Both aquifers are under artesian pressure and wells flow at the land surface. Water from the upper aquifer is of better quality than that from the lower aquifer and can be used in some areas without desalination. Dissolved solids concentrations in the upper aquifer average 1,540 milligrams per liter. Water levels in wells in the upper aquifer range from 8 to 15 feet above sea level; most wells flow as much as 15 gallons per minute at land surface. The lower aquifer is the source of the public supply for the islands. Dissolved solids concentrations in the lower aquifer range from 1,700 to 4,130 milligrams per liter and average 2,571 milligrams per liter. From July to November 1977, water levels in the aquifer ranged from 7 to 32 feet above sea level throughout Sanibel-Captiva Islands. In 1977 the average pumpage from public supply wells was 1.4 million gallons per day. Pumpage from the artesian aquifers during 1977 was about 690 million gallons. The water is desalinated before distribution. (USGS)

Are Upper-Body Axial Symptoms a Feature of Early Parkinson’s Disease?

PubMed Central

Moreau, Caroline; Baille, Guillaume; Delval, Arnaud; Tard, Céline; Perez, Thierry; Danel-Buhl, Nicolas; Seguy, David; Labreuche, Julien; Duhamel, Alain; Delliaux, Marie; Dujardin, Kathy; Defebvre, Luc

2016-01-01

Background Axial disorders are considered to appear late in the course of Parkinson’s disease (PD). The associated impact on quality of life (QoL) and survival and the lack of an effective treatment mean that understanding and treating axial disorders is a key challenge. However, upper-body axial disorders (namely dysarthria, swallowing and breathing disorders) have never been prospectively assessed in early-stage PD patients. Objectives To characterize upper-body axial symptoms and QoL in consecutive patients with early-stage PD. Methods We prospectively enrolled 66 consecutive patients with early-stage PD (less than 3 years of disease progression) and assessed dysarthria, dysphagia and respiratory function (relative to 36 controls) using both objective and patient-reported outcomes. Results The mean disease duration was 1.26 years and the mean UPDRS motor score was 19.4 out of 108. 74% of the patients presented slight dysarthria (primarily dysprosodia). Men appeared to be more severely affected (i.e. dysphonia). This dysfunction was strongly correlated with low swallowing speed (despite the absence of complaints about dysphagia), respiratory insufficiency and poor QoL. Videofluorography showed that oral-phase swallowing disorders affected 60% of the 31 tested patients and that pharyngeal-phase disorders affected 21%. 24% of the patients reported occasional dyspnea, which was correlated with anxiety in women but not in men. Marked diaphragmatic dysfunction was suspected in 42% of the patients (predominantly in men). Conclusion Upper body axial symptoms were frequent in men with early-stage PD, whereas women presented worst non-motor impairments. New assessment methods are required because currently available tools do not reliably detect these upper-body axial disorders. PMID:27654040

High-Efficiency Power Module

NASA Technical Reports Server (NTRS)

Simons, Rainee N (Inventor); Wintucky, Edwin G (Inventor)

2013-01-01

One or more embodiments of the present invention pertain to an all solid-state microwave power module. The module includes a plurality of solid-state amplifiers configured to amplify a signal using a low power stage, a medium power stage, and a high power stage. The module also includes a power conditioner configured to activate a voltage sequencer (e.g., bias controller) when power is received from a power source. The voltage sequencer is configured to sequentially apply voltage to a gate of each amplifier and sequentially apply voltage to a drain of each amplifier.

High-Efficiency Power Module

NASA Technical Reports Server (NTRS)

Simons, Rainee N. (Inventor); Wintucky, Edwin G. (Inventor)

2015-01-01

One or more embodiments of the present invention pertain to an all solid-state microwave power module. The module includes a plurality of solid-state amplifiers configured to amplify a signal using a low power stage, a medium power stage, and a high power stage. The module also includes a power conditioner configured to activate a voltage sequencer (e.g., bias controller) when power is received from a power source. The voltage sequencer is configured to sequentially apply voltage to a gate of each amplifier and sequentially apply voltage to a drain of each amplifier.

40 CFR 264.554 - Staging piles.

Code of Federal Regulations, 2010 CFR

2010-07-01

... staging pile? A staging pile is an accumulation of solid, non-flowing remediation waste (as defined in...) [Reserved] (b) When may I use a staging pile? You may use a staging pile to store hazardous remediation waste (or remediation waste otherwise subject to land disposal restrictions) only if you follow the...

--No Title--

Science.gov Websites

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Oblimersen and Gemcitabine in Treating Patients With Advanced Solid Tumor or Lymphoma

ClinicalTrials.gov

2013-01-24

Extranodal Marginal Zone B-cell Lymphoma of Mucosa-associated Lymphoid Tissue; Nodal Marginal Zone B-cell Lymphoma; Recurrent Adult Burkitt Lymphoma; Recurrent Adult Diffuse Large Cell Lymphoma; Recurrent Adult Diffuse Mixed Cell Lymphoma; Recurrent Adult Diffuse Small Cleaved Cell Lymphoma; Recurrent Adult Hodgkin Lymphoma; Recurrent Adult Immunoblastic Large Cell Lymphoma; Recurrent Adult Lymphoblastic Lymphoma; Recurrent Adult T-cell Leukemia/Lymphoma; Recurrent Cutaneous T-cell Non-Hodgkin Lymphoma; Recurrent Grade 1 Follicular Lymphoma; Recurrent Grade 2 Follicular Lymphoma; Recurrent Grade 3 Follicular Lymphoma; Recurrent Mantle Cell Lymphoma; Recurrent Marginal Zone Lymphoma; Recurrent Small Lymphocytic Lymphoma; Splenic Marginal Zone Lymphoma; Stage IV Adult Burkitt Lymphoma; Stage IV Adult Diffuse Large Cell Lymphoma; Stage IV Adult Diffuse Mixed Cell Lymphoma; Stage IV Adult Diffuse Small Cleaved Cell Lymphoma; Stage IV Adult Hodgkin Lymphoma; Stage IV Adult Immunoblastic Large Cell Lymphoma; Stage IV Adult Lymphoblastic Lymphoma; Stage IV Adult T-cell Leukemia/Lymphoma; Stage IV Cutaneous T-cell Non-Hodgkin Lymphoma; Stage IV Grade 1 Follicular Lymphoma; Stage IV Grade 2 Follicular Lymphoma; Stage IV Grade 3 Follicular Lymphoma; Stage IV Mantle Cell Lymphoma; Stage IV Marginal Zone Lymphoma; Stage IV Small Lymphocytic Lymphoma; Unspecified Adult Solid Tumor, Protocol Specific

Laparoscopic Spine Surgery

MedlinePlus

... Series SAGES Masters Program Facebook Collaboratives Acute Care Surgery Bariatric Biliary Colorectal Flexible Endoscopy (upper or lower) Foregut Hernia Robotics The SAGES HPB/Solid Organ Program The SAGES ...

Laparoscopic Colon Resection

MedlinePlus

... Series SAGES Masters Program Facebook Collaboratives Acute Care Surgery Bariatric Biliary Colorectal Flexible Endoscopy (upper or lower) Foregut Hernia Robotics The SAGES HPB/Solid Organ Program The SAGES ...

The role of baseflow in dissolved solids delivery to streams in the Upper Colorado River Basin

NASA Astrophysics Data System (ADS)

Rumsey, C.; Miller, M. P.; Schwarz, G. E.; Susong, D.

2017-12-01

Salinity has a major effect on water users in the Colorado River Basin, estimated to cause almost $300 million per year in economic damages. The Colorado River Basin Salinity Control Program implements and manages projects to reduce salinity (dissolved solids) loads, investing millions of dollars per year in irrigation upgrades, canal projects, and other mitigation strategies. To inform and improve mitigation efforts, there is a need to better understand sources of salinity to streams and how salinity has changed over time. This study explores salinity in baseflow, or groundwater discharge to streams, to assess whether groundwater is a significant contributor of dissolved solids to streams in the Upper Colorado River Basin (UCRB). Chemical hydrograph separation was used to estimate long-term mean annual baseflow discharge and baseflow dissolved solids loads at stream gages (n=69) across the UCRB. On average, it is estimated that 89% of dissolved solids loads originate from the baseflow fraction of streamflow. Additionally, a statistical trend analysis using weighted regressions on time, discharge, and season was used to evaluate changes in baseflow dissolved solids loads in streams with data from 1987 to 2011 (n=29). About two-thirds (62%) of these streams showed statistically significant decreasing trends in baseflow dissolved solids loads. At the two most downstream sites, Green River at Green River, UT and Colorado River at Cisco, UT, baseflow dissolved solids loads decreased by a combined 780,000 metric tons, which is approximately 65% of the estimated basin-scale decrease in total dissolved solids loads in the UCRB attributed to salinity control efforts. Results indicate that groundwater discharged to streams, and therefore subsurface transport processes, play a large role in delivering dissolved solids to streams in the UCRB. Decreasing trends in baseflow dissolved solids loads suggest that salinity mitigation projects, changes in land use, and/or climate are decreasing salinity in groundwater transported to streams.

A biorefinery approach based on fractionation with a cheap industrial by-product for getting value from an invasive woody species.

PubMed

Domínguez, Elena; Romaní, Aloia; Alonso, José Luis; Parajó, Juan Carlos; Yáñez, Remedios

2014-12-01

Acacia dealbata wood (an invasive species) was subjected to fractionation with glycerol (a cheap industrial by-product), and the resulting solid phase was used as a substrate for enzymatic hydrolysis. Glycerol fractionation allowed an extensive delignification while preserving cellulose in solid phase. The solids from the fractionation stage showed high susceptibility to enzymatic hydrolysis. Solids obtained under selected fractionation conditions (glycerol content of media, 80 wt%; duration, 1h; liquid to solid ratio, 6 g/g; alkaline and neutral washing stages) were subjected to enzymatic saccharification to achieve glucose concentrations up to 85.40 g/L, with almost complete cellulose conversion into glucose. The results confirmed the potential of glycerol as a fractionation agent for biorefineries. Copyright © 2014 Elsevier Ltd. All rights reserved.

Lernpunkt Deutsch--Stage 1.

ERIC Educational Resources Information Center

Theil, Elvira

1997-01-01

Evaluates the first stage of "Lernpunkt Deutsch," a new three-stage German course designed for upper elementary and early secondary school. Describes the publisher's package of materials and the appropriateness of the course, utility of the different package elements, format of the materials, and assesses whether the course provides pedagogically…

Tooth demineralization and associated factors in patients on fixed orthodontic treatment.

PubMed

Salmerón-Valdés, Elías Nahúm; Lara-Carrillo, Edith; Medina-Solís, Carlo Eduardo; Robles-Bermeo, Norma Leticia; Scougall-Vilchis, Rogelio José; Casanova-Rosado, Juan Fernando; Pontigo-Loyola, América Patricia; Fernández Barrera, Miguel Ángel

2016-11-02

Dental demineralization was determined in patients at three time points during fixed orthodontic treatment. A multiple cross-sectional study included 108 patients divided into three different groups: (1) beginning of orthodontic treatment; (2) one year into treatment; and (3) two years into treatment. Demineralization was estimated using a DIAGNOdent pen. We obtained data from multiple tooth-by-tooth demineralization readings combined with salivary pH and patients' oral hygienic and dietary behaviors. A t-test for independent samples and Spearman´s correlation were performed. No demineralizations differences were found between the initial stage and one year into treatment. Between one and two years small differences were observed, but demineralization increased between the initial stage and second treatment year, predominating in upper right central incisors (p = 0.056), upper left lateral incisors (p = 0.040), both upper canines (p = 0.055 and p = 0.040, respectively) and first left premolars (p = 0.034 and p = 0.053, respectively). We did not find associations between oral hygiene and dietary behaviours or salivary pH. In conclusion, demineralization occurred in first year of treatment and increased during second year, predominating in the upper arch and the left side mainly in upper right central incisors, upper left lateral incisors, both upper canines, and first left premolars.

STS-54 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1993-01-01

The STS-54 Space Shuttle Program Mission Report is a summary of the Orbiter, External Tank (ET), Solid Rocket Booster/Redesigned Solid Rocket Motor (SRB/RSRM), and the Space Shuttle Main Engine (SSME) subsystems performance during this fifty-third flight of the Space Shuttle Program, and the third flight of the Orbiter vehicle Endeavour (OV-105). In addition to the Orbiter, the flight vehicle consisted of an ET, which was designated ET-51; three SSME's, which were serial numbers 2019, 2033, and 2018 in positions 1, 2, and 3, respectively; and two retrievable and reusable SRB's which were designated BI-056. The lightweight RSRM's that were installed in each SRB were designated 360L029A for the left SRB, and 360L029B for the right SRB. The primary objectives of this flight were to perform the operations to deploy the Tracking and Data Relay Satellite-F/Inertial Upper Stage payload and to fulfill the requirements of the Diffuse X-Ray Spectrometer (DXS) payload. The secondary objective was to fly the Chromosome and Plant Cell Division in Space (CHROMEX), Commercial Generic Bioprocessing Apparatus (CGBA), Physiological and Anatomical Rodent Experiment (PARE), and the Solid Surface Combustion Experiment (SSCE). In addition to presenting a summary of subsystem performance, this report also discusses each Orbiter, ET, SSME, SRB, and RSRM in-flight anomaly in the applicable section of the report. The official tracking number for each in-flight anomaly, assigned by the cognizant project, is also shown. All times are given in Greenwich mean time (G.m.t.) and mission elapsed time (MET).

The Inertial Upper Stage - Flight experience and capabilities

NASA Astrophysics Data System (ADS)

Kuhns, Randall H.; Maricich, Peter L.; Bangsund, Edward L.; Friske, Stephen A.; Hallman, Wayne P.; Goldstein, Allen E.

1993-10-01

The Inertial Upper Stage (IUS) is a two-stage rocket designed to place a variety of payloads in high earth orbit or on interplanetary trajectories, which has been boosted to date, together with its payloads, from the earth's surface to low altitude park orbits by the USAF Titan launcher and the NASA Space Shuttle. This paper discusses the IUS redundancy and presents data on the value of the IST's redundant design and the past uses of the vehicle's redundant capability to achieve mission success. The value of IUS's redundancy has been confirmed on several flights. The paper presents block diagrams of the IUS redundancy architecture and of the redundancy hardware switching and commands.

Hypersonic flight performance improvements by overfueled ramjet combustion

NASA Astrophysics Data System (ADS)

Sachs, G.; Bayer, R.; Lederer, R.; Schaber, R.

1991-12-01

The performance characteristics of hypersonic airbreathing engines are examined with emphasis on the effect of overfueled combustion on thrust and specific fuel-consumption, as well as on the combustion temperature, real gas effects, and pollution due to exhaust gas. It is shown that overfueled ramjet combustion can provide a means for improving flight performance at hypersonic speed and, consequently, reduce the mission fuel burn and the propulsion system weight. It is also shown that, in the separation flight maneuver, the separation condition for the upper stage can be improved by overfueled ramjet combustion of the first stage, making it possible to increase the payload which the upper stage can deliver into orbit. The flight mechanics modeling considerations are presented.

A Supersonic/Hypersonic Aerodynamic Investigation of the Saturn 1B/Apollo Upper Stage

NASA Technical Reports Server (NTRS)

1966-01-01

The static stability and axial force characteristics of an upper stage Saturn 1B/Apollo model were investigated in a series of wind tunnel tests at Mach numbers between 1. 93 and 8. 05. This report presents and analyzes the results of these small-scale studies. Test procedures and models are described, and consideration of boundary layer characteristics and violated modeling rules yields an assessment of the validity of the data. Four basic models provided evaluation of the basic launch vehicle characteristics, as well as the effects of two modes of mission abort and jettison of the launch escape system. The launch configuration experienced sudden, strong changes in stability derivatives and axial force coefficients near Mach 5. No similar changes were observed on the other configurations. Effects of Reynolds number, Mach number and boundary layer trips were obtained for each shape. The faired curves are believed to be valid for full-scale flight of the Saturn 1B/Apollo upper stage.

Lifetime Estimation of the Upper Stage of GSAT-14 in Geostationary Transfer Orbit.

PubMed

Jeyakodi David, Jim Fletcher; Sharma, Ram Krishan

2014-01-01

The combination of atmospheric drag and lunar and solar perturbations in addition to Earth's oblateness influences the orbital lifetime of an upper stage in geostationary transfer orbit (GTO). These high eccentric orbits undergo fluctuations in both perturbations and velocity and are very sensitive to the initial conditions. The main objective of this paper is to predict the reentry time of the upper stage of the Indian geosynchronous satellite launch vehicle, GSLV-D5, which inserted the satellite GSAT-14 into a GTO on January 05, 2014, with mean perigee and apogee altitudes of 170 km and 35975 km. Four intervals of near linear variation of the mean apogee altitude observed were used in predicting the orbital lifetime. For these four intervals, optimal values of the initial osculating eccentricity and ballistic coefficient for matching the mean apogee altitudes were estimated with the response surface methodology using a genetic algorithm. It was found that the orbital lifetime from these four time spans was between 144 and 148 days.

Lifetime Estimation of the Upper Stage of GSAT-14 in Geostationary Transfer Orbit

PubMed Central

Jeyakodi David, Jim Fletcher; Sharma, Ram Krishan

2014-01-01

The combination of atmospheric drag and lunar and solar perturbations in addition to Earth's oblateness influences the orbital lifetime of an upper stage in geostationary transfer orbit (GTO). These high eccentric orbits undergo fluctuations in both perturbations and velocity and are very sensitive to the initial conditions. The main objective of this paper is to predict the reentry time of the upper stage of the Indian geosynchronous satellite launch vehicle, GSLV-D5, which inserted the satellite GSAT-14 into a GTO on January 05, 2014, with mean perigee and apogee altitudes of 170 km and 35975 km. Four intervals of near linear variation of the mean apogee altitude observed were used in predicting the orbital lifetime. For these four intervals, optimal values of the initial osculating eccentricity and ballistic coefficient for matching the mean apogee altitudes were estimated with the response surface methodology using a genetic algorithm. It was found that the orbital lifetime from these four time spans was between 144 and 148 days. PMID:27437491

Optical Measurements of Tumbling Rocket Bodies

NASA Technical Reports Server (NTRS)

Read, J.; Cowardin, H.; Liou, J.-C.

2012-01-01

A component of interest in the active debris removal (ADR) effort in low Earth orbit is spent rocket upper stages. Proximity operations for such missions require an understanding of the tumbling characteristics of these targets. This research was conducted to assist in laying the ground work for realistic ADR mission planning. To better understand the tumbling characteristics of these spent upper stages, the NASA Orbital Debris Program Office has acquired over 400 recorded lightcurves using telescopes located in Colorado and New Mexico. This effort focuses on a population of over 250 Russian SL-8 and SL-16 spent upper stages. The oldest of these have been in orbit for 45 years, and some have exhibited unplanned orbit changes up to 22 years after launch. This paper describes the techniques of how this optical data was acquired and summarizes the optical signatures for this population of targets, including categorization, tumbling period, and investigations into specific targets in which the optical signature changed dramatically over different time periods. Results from period analysis performed on these lightcurves are summarized.

Delta II Geotail -- 1st Stage and Solid Motor Booster Erection

NASA Technical Reports Server (NTRS)

1992-01-01

The Geotail mission's goal was to investigate the structure and dynamics of the geomagnetic tail that extends on the nightside of the Earth. The launch date was July 24, 1992. This video shows the Delta II on the pad, being prepared for the launch. The first stage and the solid motor booster are shown being moved into place on the rocket.

Laparoscopic Ventral Hernia Repair

MedlinePlus

... Series SAGES Masters Program Facebook Collaboratives Acute Care Surgery Bariatric Biliary Colorectal Flexible Endoscopy (upper or lower) Foregut Hernia Robotics The SAGES HPB/Solid Organ Program The SAGES ...

Laparoscopic Spleen Removal (Splenectomy)

MedlinePlus

... Series SAGES Masters Program Facebook Collaboratives Acute Care Surgery Bariatric Biliary Colorectal Flexible Endoscopy (upper or lower) Foregut Hernia Robotics The SAGES HPB/Solid Organ Program The SAGES ...

Laparoscopic Adrenal Gland Removal

MedlinePlus

... Series SAGES Masters Program Facebook Collaboratives Acute Care Surgery Bariatric Biliary Colorectal Flexible Endoscopy (upper or lower) Foregut Hernia Robotics The SAGES HPB/Solid Organ Program The SAGES ...

Laparoscopic Inguinal Hernia Repair

MedlinePlus

... Series SAGES Masters Program Facebook Collaboratives Acute Care Surgery Bariatric Biliary Colorectal Flexible Endoscopy (upper or lower) Foregut Hernia Robotics The SAGES HPB/Solid Organ Program The SAGES ...

Treatment of wastewater containing a large amount of suspended solids by a novel multi-staged UASB reactor.

PubMed

Uemura, S; Harada, H; Ohashi, A; Torimura, S

2005-12-01

Treatment of artificial wastewater containing a large amount of suspended solids comprised of soybean processing waste and pig fodder was studied using a novel multi-staged upflow anaerobic sludge blanket reactor. The reactor consisted of three compartments, each containing a gas solid separator. The wastewater had chemical oxygen demand of approximately 21600 mg l(-1), suspended solids of 12800 mg l(-1), and an ammonia concentration of 945 mg l(-1). A continuous experiment without effluent circulation showed that the multi-staged reactor was not that effective for the treatment of wastewater containing a large amount of suspended solids. However, operation of the reactor with circulation of effluent enabled the reactor to achieve organic removal of 85% and approximately 70% methane conversion at loading rates of between 4.0 to 5.4 kg-chemical oxygen demand per cubic meter per day, meaning that the reactor was more effective when effluent was circulated. Morphological investigation revealed that the crude fiber in the sludge was partially degraded and that it had many small depressions on its surface. Evolved biogas may have become caught in these depressions of the fibers and caused washout of the sludge.

Direct Reduction of Ferrous Oxides to form an Iron-Rich Alternative Charge Material

NASA Astrophysics Data System (ADS)

Ünal, H. İbrahim; Turgut, Enes; Atapek, Ş. H.; Alkan, Attila

2015-12-01

In this study, production of sponge iron by direct reduction of oxides and the effect of reductant on metallization were investigated. In the first stage of the study, scale formed during hot rolling of slabs was reduced in a rotating furnace using solid and gas reductants. Coal was used as solid reductant and hydrogen released from the combustion reaction of LNG was used as the gas one. The sponge iron produced by direct reduction was melted and solidified. In the second stage, Hematite ore in the form of pellets was reduced using solid carbon in a furnace heated up to 1,100°C for 60 and 120 minutes. Reduction degree of process was evaluated as a function of time and the ratio of Cfix/Fetotal. In the third stage, final products were examined using scanning electron microscope and microanalysis was carried out by energy dispersive x-ray spectrometer attached to the electron microscope. It is concluded that (i) direct reduction using both solid and gas reductants caused higher metallization compared to using only solid reductant, (ii) as the reduction time and ratio of Cfix/Fetotal increased %-reduction of ore increased.

Initial Assessment of the Ares I-X Launch Vehicle Upper Stage to Vibroacoustic Flight Environments

NASA Technical Reports Server (NTRS)

Larko, Jeffrey M.; Hughes, William O.

2008-01-01

The Ares I launch vehicle will be NASA s first new launch vehicle since 1981. Currently in design, it will replace the Space Shuttle in taking astronauts to the International Space Station, and will eventually play a major role in humankind s return to the Moon and eventually to Mars. Prior to any manned flight of this vehicle, unmanned test readiness flights will be flown. The first of these readiness flights, named Ares I-X, is scheduled to be launched in April 2009. The NASA Glenn Research Center is responsible for the design, manufacture, test and analysis of the Ares I-X upper stage simulator (USS) element. As part of the design effort, the structural dynamic response of the Ares I-X launch vehicle to its vibroacoustic flight environments must be analyzed. The launch vehicle will be exposed to extremely high acoustic pressures during its lift-off and aerodynamic stages of flight. This in turn will cause high levels of random vibration on the vehicle's outer surface that will be transmitted to its interior. Critical flight equipment, such as its avionics and flight guidance components are susceptible to damage from this excitation. This study addresses the modelling, analysis and predictions from examining the structural dynamic response of the Ares I-X upper stage to its vibroacoustic excitations. A statistical energy analysis (SEA) model was used to predict the high frequency response of the vehicle at locations of interest. Key to this study was the definition of the excitation fields corresponding to lift off acoustics and the unsteady aerodynamic pressure fluctuations during flight. The predicted results will be used by the Ares I-X Project to verify the flight qualification status of the Ares I-X upper stage components.

Ares I-X Launch Vehicle Modal Test Overview

NASA Technical Reports Server (NTRS)

Buehrle, Ralph D.; Bartolotta, Paul A.; Templeton, Justin D.; Reaves, Mercedes C.; Horta, Lucas G.; Gaspar, James L.; Parks, Russell A.; Lazor, Daniel R.

2010-01-01

The first test flight of NASA's Ares I crew launch vehicle, called Ares I-X, is scheduled for launch in 2009. Ares IX will use a 4-segment reusable solid rocket booster from the Space Shuttle heritage with mass simulators for the 5th segment, upper stage, crew module and launch abort system. Flight test data will provide important information on ascent loads, vehicle control, separation, and first stage reentry dynamics. As part of hardware verification, a series of modal tests were designed to verify the dynamic finite element model (FEM) used in loads assessments and flight control evaluations. Based on flight control system studies, the critical modes were the first three free-free bending mode pairs. Since a test of the free-free vehicle is not practical within project constraints, modal tests for several configurations in the nominal integration flow were defined to calibrate the FEM. A traceability study by Aerospace Corporation was used to identify the critical modes for the tested configurations. Test configurations included two partial stacks and the full Ares I-X launch vehicle on the Mobile Launcher Platform. This paper provides an overview for companion papers in the Ares I-X Modal Test Session. The requirements flow down, pre-test analysis, constraints and overall test planning are described.

Use of Thermoset Composite Materials in Cryogenic Tanks

NASA Astrophysics Data System (ADS)

Diaz, V.; Cardone, T.; Ramusat, G.

2014-06-01

To improve the performances of Future Expendable Launchers, one of the key aspects to be considered is the mass optimization of the cryogenic upper stage of the launcher, where a mass saving of one Kg, is directly transferred to one more Kg of payload.This optimization is inherently linked to the use of composite materials in all the structures that conforms the upper stage of the launcher.Currently, most of the upper stage structures of the operational launchers, like Ariane 5, are made in composite materials, with the exception of the cryogenic (LH2 and LOX) tanks which remain metallic.So, from a structural point of view, the next qualitative step in the development of new expendable launcher, would be the manufacturing of the upper stage cryogenic tanks in composite materials.To reach this objective important concerns mainly related to the potential for leaks and the compatibility with the LOX need to be resolved.In the frame of the FLPP (Future Launcher Preparatory Program) funded by ESA, an activity related to the use of thermoset composite material in the cryogenic tanks has been included.This paper presents a summary of the performed work which includes:* The selection and characterization of the most suitable candidate materials for the considered application* The design and analysis of a subscale demonstrator representative of the LH2 compartment* The design, manufacturing and testing of some test articles representatives of the selected design solutions* The manufacturing and testing of the selected subscale demonstrator.

Random Vibrations

NASA Technical Reports Server (NTRS)

Messaro. Semma; Harrison, Phillip

2010-01-01

Ares I Zonal Random vibration environments due to acoustic impingement and combustion processes are develop for liftoff, ascent and reentry. Random Vibration test criteria for Ares I Upper Stage pyrotechnic components are developed by enveloping the applicable zonal environments where each component is located. Random vibration tests will be conducted to assure that these components will survive and function appropriately after exposure to the expected vibration environments. Methodology: Random Vibration test criteria for Ares I Upper Stage pyrotechnic components were desired that would envelope all the applicable environments where each component was located. Applicable Ares I Vehicle drawings and design information needed to be assessed to determine the location(s) for each component on the Ares I Upper Stage. Design and test criteria needed to be developed by plotting and enveloping the applicable environments using Microsoft Excel Spreadsheet Software and documenting them in a report Using Microsoft Word Processing Software. Conclusion: Random vibration liftoff, ascent, and green run design & test criteria for the Upper Stage Pyrotechnic Components were developed by using Microsoft Excel to envelope zonal environments applicable to each component. Results were transferred from Excel into a report using Microsoft Word. After the report is reviewed and edited by my mentor it will be submitted for publication as an attachment to a memorandum. Pyrotechnic component designers will extract criteria from my report for incorporation into the design and test specifications for components. Eventually the hardware will be tested to the environments I developed to assure that the components will survive and function appropriately after exposure to the expected vibration environments.

Reduced upper obstructions in N3 and increased lower obstructions in REM sleep stage detected with manometry.

PubMed

Wirth, Markus; Schramm, Juliane; Bautz, Maximilian; Hofauer, Benedikt; Edenharter, Günther; Ott, Armin; Heiser, Clemens

2018-01-01

In obstructive sleep apnea (OSA), airway obstruction occurs at different anatomic levels. The frequency and location of obstructions play a crucial role in the planning of surgical treatment. The aim of this study was to evaluate the pharyngeal obstruction levels in different sleep stages with manometry in OSA patients. In addition, the manometry results were compared with drug-induced sleep endoscopy (DISE). Forty-one patients with OSA received manometry measurements during one night of sleep. All patients were simultaneously evaluated with polysomnography. The frequency of obstructions in different sleep stages was assessed. Twenty patients were additionally studied with DISE. Obstruction levels detected with manometry were compared with DISE. The frequency of upper and to a lesser extent lower obstructions decreased in sleep stage N3. In rapid eye movement (REM) sleep, lower obstructions increased. The overall proportion of upper and lower obstructions detected with manometry corresponded with DISE in 13 of 20 cases. A significant change in the obstruction levels was detected with manometry in N3 and REM sleep. The reduction of both upper and to a lesser extent lower obstructions in N3 suggests more stable airways in slow-wave sleep. Relevant lower obstructions were not detected in DISE compared to manometry in 5 out of 20 examinations. This could be a potential reason for treatment failure of site-specific surgical OSA treatment when only performing DISE preoperatively. Therefore, manometry could be a useful complementary tool in the preoperative evaluation for OSA.

Study of Required Thrust Profile Determination of a Three Stages Small Launch Vehicle

NASA Astrophysics Data System (ADS)

Fariz, A.; Sasongko, R. A.; Poetro, R. E.

2018-04-01

The effect of solid rocket motor specifications, i.e. specific impulse and mass flow rate, and coast time on the thrust profile of three stages small launch vehicle is studied. Solid rocket motor specifications are collected from various small launch vehicle that had ever been in operation phase, and also from previous study. Comparison of orbital parameters shows that the radius of apocenter targeted can be approached using one combination of solid rocket motor specifications and appropriate coast time. However, the launch vehicle designed is failed to achieve the targeted orbit nor injecting the satellite to any orbit.

Timing of Acute Palliative Care Consultation in Critically Ill Patients

ClinicalTrials.gov

2016-08-03

Multiple Organ Failure; End Stage Cardiac Failure; End Stage Chronic Obstructive Airways Disease; Chronic Kidney Disease Stage 5; Hepatic Encephalopathy; Sepsis; Dementia; Multiple Sclerosis; Parkinson's Disease; In-Hospital Cardiac Arrest; Solid Organ Cancer

Influence of everyday bolus consistencies in different body positions on high-resolution esophageal pressure topography (HREPT) parameters.

PubMed

Hasan, Y; Go, J; Hashmi, S M; Valestin, J; Schey, R

2015-04-01

The standard protocol for esophageal manometry involves placing the patient in the supine position with head turned to left (supine head left [SHL]) while evaluating liquid bolus swallows. Routinely, semisolid or solid boluses are not evaluated. Currently, the daily American diet includes up to 40% solid or semisolid texture. Thus far, the data on the effect of different bolus on high-resolution esophageal pressure topography (HREPT) parameters are scarce. This study aims to evaluate the effect of every day bolus consistencies in different body positions on HREPT variables. HREPT was performed on healthy volunteers with a modified protocol including liquid swallows in the SHL position followed by applesauce (semisolid), cracker (solid), and marshmallow (soft solid) in three different positions (SHL, sitting, and standing). A total of 38 healthy adult subjects (22 males and 16 females, median age = 27, and mean body mass index = 25) were evaluated. The resting upper esophageal sphincter pressure was significantly different while subjects swallowed crackers, applesauce, and marshmallows in most positions compared with liquid SHL (P < 0.05). The lower esophageal sphincter, contractile front velocity, and distal contractile integral pressures did not differ in all different consistencies compared with SHL. The integrated relaxation period was significantly higher with solid bolus compared with liquid bolus only in SHL position. The intrabolus pressure was significantly different with solid and soft solid boluses in all postures compared to liquid SHL. The American diet consistency affects upper esophageal sphincter pressure and partially integrated relaxation period and intrabolus pressure in various positions. Semisolid bolus swallows do not cause substantial pressure changes and are safe for evaluation and maintaining adequate caloric intake in patients with dysphagia who cannot tolerate solids. © 2014 International Society for Diseases of the Esophagus.

A data reconnaissance on the effect of suspended-sediment concentrations on dissolved-solids concentrations in rivers and tributaries in the Upper Colorado River Basin

USGS Publications Warehouse

Tillman, Fred D.; Anning, David W.

2014-01-01

The Colorado River is one of the most important sources of water in the western United States, supplying water to over 35 million people in the U.S. and 3 million people in Mexico. High dissolved-solids loading to the River and tributaries are derived primarily from geologic material deposited in inland seas in the mid-to-late Cretaceous Period, but this loading may be increased by human activities. High dissolved solids in the River causes substantial damages to users, primarily in reduced agricultural crop yields and corrosion. The Colorado River Basin Salinity Control Program was created to manage dissolved-solids loading to the River and has focused primarily on reducing irrigation-related loading from agricultural areas. This work presents a reconnaissance of existing data from sites in the Upper Colorado River Basin (UCRB) in order to highlight areas where suspended-sediment control measures may be useful in reducing dissolved-solids concentrations. Multiple linear regression was used on data from 164 sites in the UCRB to develop dissolved-solids models that include combinations of explanatory variables of suspended sediment, flow, and time. Results from the partial t-test, overall likelihood ratio, and partial likelihood ratio on the models were used to group the sites into categories of strong, moderate, weak, and no-evidence of a relation between suspended-sediment and dissolved-solids concentrations. Results show 68 sites have strong or moderate evidence of a relation, with drainage areas for many of these sites composed of a large percentage of clastic sedimentary rocks. These results could assist water managers in the region in directing field-scale evaluation of suspended-sediment control measures to reduce UCRB dissolved-solids loading.

Electrocatalytic cermet gas detector/sensor

DOEpatents

Vogt, M.C.; Shoemarker, E.L.; Fraioli, A.V.

1995-07-04

An electrocatalytic device for sensing gases is described. The gas sensing device includes a substrate layer, a reference electrode disposed on the substrate layer comprised of a nonstoichiometric chemical compound enabling oxygen diffusion therethrough, a lower reference electrode coupled to the reference electrode, a solid electrolyte coupled to the lower reference electrode and an upper catalytically active electrode coupled to the solid electrolyte. 41 figs.

Ares I-X Management Office (MMO) Integrated Master Schedule (IMS)

NASA Technical Reports Server (NTRS)

Heintzman, Keith; Askins, Bruce

2010-01-01

Objectives: Demonstrate control of a dynamically similar, integrated Ares I/Orion, using Ares I relevant ascent control algorithms. Perform an in-flight separation/staging event between a Ares I-similar First Stage and a representative Upper Stage. Demonstrate assembly and recovery of a new Ares I-like First Stage element at KSC. Demonstrate First Stage separation sequencing, and quantify First Stage atmospheric entry dynamics, and parachute performance. Characterize magnitude of integrated vehicle roll torque throughout First Stage flight.

Study of solid rocket motor for space shuttle booster, volume 2, book 2

NASA Technical Reports Server (NTRS)

1972-01-01

A technical analysis of the solid propellant rocket engines for use with the space shuttle is presented. The subjects discussed are: (1) solid rocket motor stage recovery, (2) environmental effects, (3) man rating of the solid propellant rocket engines, (4) system safety analysis, (5) ground support equipment, and (6) transportation, assembly, and checkout.

The origin of groundwater composition in the Pampeano Aquifer underlying the Del Azul Creek basin, Argentina.

PubMed

Zabala, M E; Manzano, M; Vives, L

2015-06-15

The Pampean plain is the most productive region in Argentina. The Pampeano Aquifer beneath the Pampean plain is used mostly for drinking water. The study area is the sector of the Pampeano Aquifer underlying the Del Azul Creek basin, in Buenos Aires province. The main objective is to characterize the chemical and isotopic compositions of groundwater and their origin on a regional scale. The methodology used involved the identification and characterization of potential sources of solutes, the study of rain water and groundwater chemical and isotopic characteristics to deduce processes, the development of a hydrogeochemical conceptual model, and its validation by hydrogeochemical modelling with PHREEQC. Groundwater samples come mostly from a two-depth monitoring network of the "Dr. Eduardo J. Usunoff" Large Plains Hydrology Institute (IHLLA). Groundwater salinity increases from SW to NE, where groundwater is saline. In the upper basin groundwater is of the HCO3-Ca type, in the middle basin it is HCO3-Na, and in the lower basin it is ClSO4-NaCa and Cl-Na. The main processes incorporating solutes to groundwater during recharge in the upper basin are rain water evaporation, dissolution of CO2, calcite, dolomite, silica, and anorthite; cationic exchange with Na release and Ca and Mg uptake, and clay precipitation. The main processes modifying groundwater chemistry along horizontal flow at 30 m depth from the upper to the lower basin are cationic exchange, dissolution of silica and anorthite, and clay precipitation. The origin of salinity in the middle and lower basin is secular evaporation in a naturally endorheic area. In the upper and middle basins there is agricultural pollution. In the lower basin the main pollution source is human liquid and solid wastes. Vertical infiltration through the boreholes annular space during the yearly flooding stages is probably the pollution mechanism of the samples at 30 m depth. Copyright © 2015 Elsevier B.V. All rights reserved.

Flight and Integrated Vehicle Testing: Laying the Groundwork for the Next Generation of Space Exploration Launch Vehicles

NASA Technical Reports Server (NTRS)

Taylor, J. L.; Cockrell, C. E.

2009-01-01

Integrated vehicle testing will be critical to ensuring proper vehicle integration of the Ares I crew launch vehicle and Ares V cargo launch vehicle. The Ares Projects, based at Marshall Space Flight Center in Alabama, created the Flight and Integrated Test Office (FITO) as a separate team to ensure that testing is an integral part of the vehicle development process. As its name indicates, FITO is responsible for managing flight testing for the Ares vehicles. FITO personnel are well on the way toward assembling and flying the first flight test vehicle of Ares I, the Ares I-X. This suborbital development flight will evaluate the performance of Ares I from liftoff to first stage separation, testing flight control algorithms, vehicle roll control, separation and recovery systems, and ground operations. Ares I-X is now scheduled to fly in summer 2009. The follow-on flight, Ares I-Y, will test a full five-segment first stage booster and will include cryogenic propellants in the upper stage, an upper stage engine simulator, and an active launch abort system. The following flight, Orion 1, will be the first flight of an active upper stage and upper stage engine, as well as the first uncrewed flight of an Orion spacecraft into orbit. The Ares Projects are using an incremental buildup of flight capabilities prior to the first operational crewed flight of Ares I and the Orion crew exploration vehicle in 2015. In addition to flight testing, the FITO team will be responsible for conducting hardware, software, and ground vibration tests of the integrated launch vehicle. These efforts will include verifying hardware, software, and ground handling interfaces. Through flight and integrated testing, the Ares Projects will identify and mitigate risks early as the United States prepares to take its next giant leaps to the Moon and beyond.

[Microscopic anatomy and volatile secondary metabolites at three stages of development of the inflorescences of Lantana camara (Verbenaceae)].

PubMed

Caroprese Araque, José Fernando; Parra Garcés, María Isabel; Arrieta Prieto, Dagoberto; Stashenko, Elena

2011-03-01

Plants of the Verbenaceae family, like L. camara, have called the attention of researchers, not only because of its high diversity and its distribution around the world, but also for its variable use as popular medicine to treat diseases like tetanus, rheumatism and malaria, and as bactericide and insecticide. To assess this, the morphology and ontogeny of the inflorescences of Lantana camara and the chemical composition of volatile secondary metabolites were analyzed at three different ontogeny stages. Plants were collected from the experimental crop area in CENIVAM, Bucaramanga, Colombia. Fresh inflorescence stages were established and analyzed using a stereoscopic microscope, fixed in FAA and included in parafine. Transversal and longitudinal 10 microm thick sections were prepared using a rotative microtome, safranine-fastgreen stained and were observed and photographed using a light microscope. The chemical composition of volatile secondary metabolites were analyzed for each stage. The analytes, obtained from 0.7 g of plant, were isolated by solid phase micro-extraction in the headspace mode (HS-SPME) and were placed in 20 ml vials. The components were analyzed by gas chromatography coupled to mass spectrometry (GC-MS). Stage I was microscopically characterized by an immature development in which the meristematic differentiation begins with a mass of cells. In Stage II, the morphogenetic movement gives way to the formation of the respective floral sexual structures, calyx and corolla. In Stage III, the different organs are conspicuous: four stamens epipetals and didynamous, monocarpelar, biloculate and globose gynoecium, upper ovary and lateral stigma; the flowers are hermaphroditic. The main secondary metabolites detected by GC-MS were bicyclosesquiphellandrene, E-beta-farnesene, E-beta-caryophyllene, gamma-muurolene + gamma-curcumene and alpha-zingiberene. Nevertheless, this study reports for the first time in plant species alpha-gurjunene, gamma-amorphene, alpha-muurolene, sesquithujene, alpha-trans-bergamotene and trans-cadina-1,4-diene. The diversity of compounds found can be only explained by the extraction methods employed, the developmental stages and section of the plant, the geographic conditions, collection time and the genetic constitution of the evaluated species.

Tazemetostat in Treating Patients With Relapsed or Refractory Advanced Solid Tumors, Non-Hodgkin Lymphoma, or Histiocytic Disorders With EZH2, SMARCB1, or SMARCA4 Gene Mutations (A Pediatric MATCH Treatment Trial)

ClinicalTrials.gov

2018-06-20

Advanced Malignant Solid Neoplasm; Ann Arbor Stage III Childhood Hodgkin Lymphoma; Ann Arbor Stage III Childhood Non-Hodgkin Lymphoma; Ann Arbor Stage IV Childhood Hodgkin Lymphoma; Ann Arbor Stage IV Childhood Non-Hodgkin Lymphoma; Ewing Sarcoma/Peripheral Primitive Neuroectodermal Tumor; EZH2 Gain of Function; EZH2 Gene Mutation; Histiocytosis; Loss of BRG1 Protein Expression; Loss of INI 1 Protein Expression; Low Grade Glioma; Recurrent Childhood Central Nervous System Neoplasm; Recurrent Childhood Ependymoma; Recurrent Childhood Soft Tissue Sarcoma; Recurrent Ewing Sarcoma; Recurrent Glioma; Recurrent Hepatoblastoma; Recurrent Hodgkin Lymphoma; Recurrent Langerhans Cell Histiocytosis; Recurrent Malignant Germ Cell Tumor; Recurrent Malignant Glioma; Recurrent Malignant Solid Neoplasm; Recurrent Medulloblastoma; Recurrent Neuroblastoma; Recurrent Non-Hodgkin Lymphoma; Recurrent Osteosarcoma; Recurrent Peripheral Primitive Neuroectodermal Tumor; Recurrent Rhabdoid Tumor; Recurrent Rhabdomyosarcoma; Recurrent Soft Tissue Sarcoma; Refractory Central Nervous System Neoplasm; Refractory Hodgkin Lymphoma; Refractory Langerhans Cell Histiocytosis; Refractory Malignant Germ Cell Tumor; Refractory Malignant Glioma; Refractory Medulloblastoma; Refractory Neuroblastoma; Refractory Non-Hodgkin Lymphoma; Refractory Osteosarcoma; Refractory Peripheral Primitive Neuroectodermal Tumor; Refractory Rhabdoid Tumor; Refractory Soft Tissue Sarcoma; Rhabdoid Tumor; SMARCA4 Gene Inactivation; SMARCB1 Gene Inactivation; Stage III Soft Tissue Sarcoma AJCC v7; Stage IV Soft Tissue Sarcoma AJCC v7; Wilms Tumor

Development of Weld Inspection of the Ares I Crew Launch Vehicle Upper Stage

NASA Technical Reports Server (NTRS)

Russell, Sam; Ezell, David

2010-01-01

NASA is designing a new crewed launch vehicle called Ares I to replace the Space Shuttle after its scheduled retirement in 2010. This new launch vehicle will build on the Shuttle technology in many ways including using a first stage based upon the Space Shuttle Solid Rocket Booster, advanced aluminum alloys for the second stage tanks, and friction stir welding to assemble the second stage. Friction stir welding uses a spinning pin that is inserted in the joint between two panels that are to be welded. The pin mechanically mixes the metal together below the melting temperature to form the weld. Friction stir welding allows high strength joints in metals that would otherwise lose much of their strength as they are melted during the fusion welding process. One significant change from the Space Shuttle that impacts NDE is the implementation of self-reacting friction stir welding for non-linear welds on the primary metallic structure. The self-reacting technique differs from the conventional technique because the load of the pin tool pressing down on the metal being joined is reacted by a nut on the end of the tool rather than an anvil behind the part. No spacecraft has ever flown with a self-reacting friction stir weld, so this is a major advancement in the manufacturing process, bringing with it a whole new set of challenges for NDE to overcome. The metal microstructure and possible defects are different from other weld processes. Friction plug welds will be used to close out the hole remaining in the radial welds when friction stir welded. This plug welding also has unique challenges in inspection. The current state of development of these inspections will be presented, along with other information pertinent to NDE of the Ares I.

Scout

NASA Image and Video Library

1960-09-22

Photographed on 09/22/1960. -- An examination of the Aerojet-General "Aerobee 150A" propulsion system in February 1960. James Hansen described this as follows: "As for the technical definition of the rocket...the Langley engineers tried to keep developmental costs and time to a minimum by selecting components from off-the-shelf hardware. the majority of Scout's components were to come from an inventory of solid-fuel rockets produced for the military, although everyone involved understood that some improved motors would also have to be developed under contract. By early 1959, after intensive technical analysis and reviews, Langley settled on a design and finalized the selection of the major contractors. The rocket's 40-inch-diameter first stage was to be a new "Algol" motor, a combination of the Jupiter Senior and the navy Polaris produced by the Aerojet General Corporation, Sacramento, California. The 31-inch-diameter second stage, "Castor," was derived from the army's Sergeant and was to be manufactured by the Redstone Division of the Thiokol company in Huntsville, Alabama. the motor for the 30-inch-diameter third stage, "Antares," evolved under NASA contract from the ABL X248 design into a new version called the X254 (and subsequently into the X259); it was built under contract to NASA by ABL, a U.S. Navy Bureau of Ordnance facility operated by the Hercules Powder Company, Cumberland, Maryland. the final upper-stage propulsion unit, "Altair," which was 25.7 inches in diameter (34 inches at the heat shield), amounted to an improved edition of the X248 that was also manufactured by ABL." -- Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, NASA SP-4308, pp.200-201.

Design and operation of an anaerobic digester for waste management and fuel generation during long term lunar mission

NASA Astrophysics Data System (ADS)

Dhoble, Abhishek S.; Pullammanappallil, Pratap C.

2014-10-01

Waste treatment and management for manned long term exploratory missions to moon will be a challenge due to longer mission duration. The present study investigated appropriate digester technologies that could be used on the base. The effect of stirring, operation temperature, organic loading rate and reactor design on the methane production rate and methane yield was studied. For the same duration of digestion, the unmixed digester produced 20-50% more methane than mixed system. Two-stage design which separated the soluble components from the solids and treated them separately had more rapid kinetics than one stage system, producing the target methane potential in one-half the retention time than the one stage system. The two stage system degraded 6% more solids than the single stage system. The two stage design formed the basis of a prototype digester sized for a four-person crew during one year exploratory lunar mission.

Scientific Reasoning and Its Relationship with Problem Solving: The Case of Upper Primary Science Teachers

ERIC Educational Resources Information Center

Alshamali, Mahmoud A.; Daher, Wajeeh M.

2016-01-01

This study aimed at identifying the levels of scientific reasoning of upper primary stage (grades 4-7) science teachers based on their use of a problem-solving strategy. The study sample (N = 138; 32 % male and 68 % female) was randomly selected using stratified sampling from an original population of 437 upper primary school teachers. The…

Evaluating the Needs of Patients Living With Solid Tumor Cancer: A Survey Design.

PubMed

Schmidt, April L; Lorenz, Rebecca A; Buchanan, Paula M; McLaughlin, Laura

2018-03-01

To describe the unmet needs of adult patients living with solid tumor cancer. Survey design. Adult patients living with solid tumor cancer from two outpatient clinics were mailed the Sheffield Profile for Assessment and Referral to Care, a holistic screening questionnaire for assessing palliative care needs, and a demographics questionnaire. One hundred fifteen patients returned the instruments, corresponding to a 62% response rate. There were no significant differences by cancer type (breast, non-breast) or gender. However, Caucasians reported significantly more psychological issues, such as anxiety, than non-Caucasians ([ n = 101 (87.8%)] and [ n = 14 (12.2%)], respectively, p = .032). Older patients reported more concerns about loss of independence/activity ( p = .012) compared with younger age groups. Patients living with Stage III/IV cancer reported more distressed about independence/activity ( p = .034), family/social issues ( p = .007), and treatment side effects ( p = .027) than patients living with Stage I/II cancer. Patients living with solid tumor cancer have a myriad of unmet needs regardless of age, gender, cancer type, or cancer stage. There appears to be important differences by cancer stage. The Sheffield Profile for Assessment and Referral to Care questionnaire provides a holistic approach for nurses to identify unmet needs and concerns. Future research should explore the preferred methods of receiving support and information.

Effect of proton-conduction in electrolyte on electric efficiency of multi-stage solid oxide fuel cells

PubMed Central

Matsuzaki, Yoshio; Tachikawa, Yuya; Somekawa, Takaaki; Hatae, Toru; Matsumoto, Hiroshige; Taniguchi, Shunsuke; Sasaki, Kazunari

2015-01-01

Solid oxide fuel cells (SOFCs) are promising electrochemical devices that enable the highest fuel-to-electricity conversion efficiencies under high operating temperatures. The concept of multi-stage electrochemical oxidation using SOFCs has been proposed and studied over the past several decades for further improving the electrical efficiency. However, the improvement is limited by fuel dilution downstream of the fuel flow. Therefore, evolved technologies are required to achieve considerably higher electrical efficiencies. Here we present an innovative concept for a critically-high fuel-to-electricity conversion efficiency of up to 85% based on the lower heating value (LHV), in which a high-temperature multi-stage electrochemical oxidation is combined with a proton-conducting solid electrolyte. Switching a solid electrolyte material from a conventional oxide-ion conducting material to a proton-conducting material under the high-temperature multi-stage electrochemical oxidation mechanism has proven to be highly advantageous for the electrical efficiency. The DC efficiency of 85% (LHV) corresponds to a net AC efficiency of approximately 76% (LHV), where the net AC efficiency refers to the transmission-end AC efficiency. This evolved concept will yield a considerably higher efficiency with a much smaller generation capacity than the state-of-the-art several tens-of-MW-class most advanced combined cycle (MACC). PMID:26218470

Two stage fluid bed-plasma gasification process for solid waste valorisation: Technical review and preliminary thermodynamic modelling of sulphur emissions

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

Morrin, Shane, E-mail: shane.morrin@ucl.ac.uk; Advanced Plasma Power, South Marston Business park, Swindon, SN3 4DE; Lettieri, Paola, E-mail: p.lettieri@ucl.ac.uk

2012-04-15

Highlights: Black-Right-Pointing-Pointer We investigate sulphur during MSW gasification within a fluid bed-plasma process. Black-Right-Pointing-Pointer We review the literature on the feed, sulphur and process principles therein. Black-Right-Pointing-Pointer The need for research in this area was identified. Black-Right-Pointing-Pointer We perform thermodynamic modelling of the fluid bed stage. Black-Right-Pointing-Pointer Initial findings indicate the prominence of solid phase sulphur. - Abstract: Gasification of solid waste for energy has significant potential given an abundant feed supply and strong policy drivers. Nonetheless, significant ambiguities in the knowledge base are apparent. Consequently this study investigates sulphur mechanisms within a novel two stage fluid bed-plasma gasification process.more » This paper includes a detailed review of gasification and plasma fundamentals in relation to the specific process, along with insight on MSW based feedstock properties and sulphur pollutant therein. As a first step to understanding sulphur partitioning and speciation within the process, thermodynamic modelling of the fluid bed stage has been performed. Preliminary findings, supported by plant experience, indicate the prominence of solid phase sulphur species (as opposed to H{sub 2}S) - Na and K based species in particular. Work is underway to further investigate and validate this.« less

Effect of proton-conduction in electrolyte on electric efficiency of multi-stage solid oxide fuel cells.

PubMed

Matsuzaki, Yoshio; Tachikawa, Yuya; Somekawa, Takaaki; Hatae, Toru; Matsumoto, Hiroshige; Taniguchi, Shunsuke; Sasaki, Kazunari

2015-07-28

Solid oxide fuel cells (SOFCs) are promising electrochemical devices that enable the highest fuel-to-electricity conversion efficiencies under high operating temperatures. The concept of multi-stage electrochemical oxidation using SOFCs has been proposed and studied over the past several decades for further improving the electrical efficiency. However, the improvement is limited by fuel dilution downstream of the fuel flow. Therefore, evolved technologies are required to achieve considerably higher electrical efficiencies. Here we present an innovative concept for a critically-high fuel-to-electricity conversion efficiency of up to 85% based on the lower heating value (LHV), in which a high-temperature multi-stage electrochemical oxidation is combined with a proton-conducting solid electrolyte. Switching a solid electrolyte material from a conventional oxide-ion conducting material to a proton-conducting material under the high-temperature multi-stage electrochemical oxidation mechanism has proven to be highly advantageous for the electrical efficiency. The DC efficiency of 85% (LHV) corresponds to a net AC efficiency of approximately 76% (LHV), where the net AC efficiency refers to the transmission-end AC efficiency. This evolved concept will yield a considerably higher efficiency with a much smaller generation capacity than the state-of-the-art several tens-of-MW-class most advanced combined cycle (MACC).

Two-Stage Technique Used to Manage Severe Upper Airway Obstruction and Avoid Surgical Tracheostomy: A Case Report.

PubMed

Onwochei, Desire N; El-Boghdadly, Kariem; Ahmad, Imran

2018-03-01

Severe upper airway obstruction is commonly managed with surgical tracheostomy under local anesthesia. We present a 49-year-old woman with postradiotherapy laryngeal fixation and transglottic stenosis for dilation of a pharyngeal stricture who refused elective tracheostomy. A 2-stage technique was used, which involved an awake fiberoptic intubation, followed by the transtracheal insertion of a Cricath needle and ventilation using an ejector-based Ventrain device. We discuss management aspects of this clinical scenario and the principles by which the Ventrain works.

[Treatment tactics of hemorroidal disease stage III-IV].

PubMed

Goncharuk, R A; Stegniĭ, K V; Krekoten', A A; Grossman, S S; Sarychev, V A

2013-01-01

The Miligan-Morgan's operation has long been considered to be the "golden standard" of hemorrhoids' stage I-III treatment. The invention of distal branches of the upper rectal artery' suture ligation with mucopexia and lifting of the anal canal mucosa discovered new possibilities for hemorrhoids surgery, though there are still some questions considering long-term results. 151 cases of recurrence within 1-6 months were analyzed. The use of CT-angiography with 3D reconstruction of the upper rectal artery allowed to chose the operative technique more relevant and thus improve the treatment results.

Preliminary Performance of Lithium-ion Cell Designs for Ares I Upper Stage Applications

NASA Technical Reports Server (NTRS)

Miller, Thomas B.; Reid, Concha M.; Kussmaul, Michael T.

2011-01-01

NASA's Ares I Crew Launch Vehicle (CLV) baselined lithium-ion technology for the Upper Stage (US). Under this effort, the NASA Glenn Research Center investigated three different aerospace lithium-ion cell suppliers to assess the performance of the various lithium-ion cell designs under acceptance and characterization testing. This paper describes the overall testing approaches associated with lithium-ion cells, their ampere-hour capacity as a function of temperature and discharge rates, as well as their performance limitations for use on the Ares I US vehicle.

A 20k Payload Launch Vehicle Fast Track Development Concept Using an RD-180 Engine and a Centaur Upper Stage

NASA Technical Reports Server (NTRS)

Toelle, Ronald (Compiler)

1995-01-01

A launch vehicle concept to deliver 20,000 lb of payload to a 100-nmi orbit has been defined. A new liquid oxygen/kerosene booster powered by an RD-180 engine was designed while using a slightly modified Centaur upper stage. The design, development, and test program met the imposed 40-mo schedule by elimination of major structural testing by increased factors of safety and concurrent engineering concepts. A growth path to attain 65,000 lb of payload is developed.

Development of diapiric structures in the upper mantle due to phase transitions

NASA Technical Reports Server (NTRS)

Liu, M.; Yuen, D. A.; Zhao, W.; Honda, S.

1991-01-01

Solid-state phase transition in time-dependent mantle convection can induce diapiric flows in the upper mantle. When a deep mantle plume rises toward phase boundaries in the upper mantle, the changes in the local thermal buoyancy, local heat capacity, and latent heat associated with the phase change at a depth of 670 kilometers tend to pinch off the plume head from the feeding stem and form a diapir. This mechanism may explain episodic hot spot volcanism. The nature of the multiple phase boundaries at the boundary between the upper and lower mantle may control the fate of deep mantle plumes, allowing hot plumes to go through and retarding the tepid ones.

Development of advanced fluid-bed agglomeration and cyclonic incineration for simultaneous waste disposal and energy recovery

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

Rehmat, A.; Khinkis, M.

The Institute of Gas Technology (IGT) is currently developing a two-stage fluidized-bed/cyclonic agglomerating incineration system for waste disposal that is based on combining the fluidized-bed agglomeration/incineration and cyclonic combustion techologies. Both technologies have been developed individually at IGT over many years. This combination has resulted in a unique and extremely flexible incinerator for solid, liquid, and gaseous wastes including municipal sludges. The system can operate over a wide range of conditions in the first stage, from low temperature (desorption) to high temperature (agglomeration), including gasification of wastes. In the combined system, solid, liquid, and gaseous organic wastes are incinerated withmore » ease and great efficiency (>99.99% destruction and removal efficiency (DRE)), while solid inorganic contaminants contained within a glassy matrix are rendered benign and suitable for disposal in an ordinary landfill. The heat generated within the incinerator can be recovered using the state-of-the-art boilers. The development of the two-stage incinerator is a culmination of extensive research and development efforts on each stage of the incinerator. The variety of data obtained with solid, liquid, and gaseous wastes for both stages includes agglomeration of ash, incineration and reclamation of used blast grit and foundry sand, partial combustion of carbonaceous fuels, in-situ desulfurization, combustion of low-Btu gases, incineration of industrial wastewater, and incineration of carbon tetrachloride. 5 refs., 7 figs., 12 tabs.« less

The Finite Element Simulation of the Upper Airway of Patients with Moderate and Severe Obstructive Sleep Apnea Hypopnea Syndrome

PubMed Central

Luo, Huiping; Scholp, Austin

2017-01-01

Objectives To investigate the snoring modes of patients with Obstructive Sleep Apnea Hypopnea Syndrome and to discover the main sources of snoring in soft tissue vibrations. Methods A three-dimensional finite element model was developed with SolidEdge to simulate the human upper airway. The inherent modal simulation was conducted to obtain the frequencies and the corresponding shapes of the soft tissue vibrations. The respiration process was simulated with the fluid-solid interaction method through ANSYS. Results The first 6 orders of modal vibration were 12 Hz, 18 Hz, 21 Hz, 22 Hz, 36 Hz, and 39 Hz. Frequencies of modes 1, 2, 4, and 5 were from tongue vibrations. Frequencies of modes 3 and 6 were from soft palate vibrations. Steady pressure distribution and air distribution lines in the upper airway were shown clearly in the fluid-solid interaction simulation results. Conclusions We were able to observe the vibrations of soft tissue and the modeled airflow by applying the finite element methods. Future studies could focus on improving the soft tissues vibration compliances by adjusting the model parameters. Additionally, more attention should be paid to vibrational components below 20 Hz when performing an acoustic analysis of human snore sounds due to the presence of these frequencies in this model. PMID:29204444

The Finite Element Simulation of the Upper Airway of Patients with Moderate and Severe Obstructive Sleep Apnea Hypopnea Syndrome.

PubMed

Luo, Huiping; Scholp, Austin; Jiang, Jack J

2017-01-01

To investigate the snoring modes of patients with Obstructive Sleep Apnea Hypopnea Syndrome and to discover the main sources of snoring in soft tissue vibrations. A three-dimensional finite element model was developed with SolidEdge to simulate the human upper airway. The inherent modal simulation was conducted to obtain the frequencies and the corresponding shapes of the soft tissue vibrations. The respiration process was simulated with the fluid-solid interaction method through ANSYS. The first 6 orders of modal vibration were 12 Hz, 18 Hz, 21 Hz, 22 Hz, 36 Hz, and 39 Hz. Frequencies of modes 1, 2, 4, and 5 were from tongue vibrations. Frequencies of modes 3 and 6 were from soft palate vibrations. Steady pressure distribution and air distribution lines in the upper airway were shown clearly in the fluid-solid interaction simulation results. We were able to observe the vibrations of soft tissue and the modeled airflow by applying the finite element methods. Future studies could focus on improving the soft tissues vibration compliances by adjusting the model parameters. Additionally, more attention should be paid to vibrational components below 20 Hz when performing an acoustic analysis of human snore sounds due to the presence of these frequencies in this model.

Paclitaxel and Carboplatin in Treating Patients With Metastatic or Recurrent Solid Tumors and HIV Infection

ClinicalTrials.gov

2017-12-19

HIV Infection; Recurrent Anal Cancer; Recurrent Breast Cancer; Recurrent Esophageal Cancer; Recurrent Gastric Cancer; Recurrent Metastatic Squamous Neck Cancer With Occult Primary; Recurrent Non-small Cell Lung Cancer; Recurrent Ovarian Epithelial Cancer; Recurrent Salivary Gland Cancer; Recurrent Squamous Cell Carcinoma of the Hypopharynx; Recurrent Squamous Cell Carcinoma of the Larynx; Recurrent Squamous Cell Carcinoma of the Lip and Oral Cavity; Recurrent Squamous Cell Carcinoma of the Nasopharynx; Recurrent Squamous Cell Carcinoma of the Oropharynx; Recurrent Squamous Cell Carcinoma of the Paranasal Sinus and Nasal Cavity; Recurrent Verrucous Carcinoma of the Larynx; Recurrent Verrucous Carcinoma of the Oral Cavity; Salivary Gland Squamous Cell Carcinoma; Stage IV Anal Cancer; Stage IV Breast Cancer; Stage IV Esophageal Cancer; Stage IV Gastric Cancer; Stage IV Non-small Cell Lung Cancer; Stage IV Ovarian Epithelial Cancer; Stage IV Salivary Gland Cancer; Stage IV Squamous Cell Carcinoma of the Hypopharynx; Stage IV Squamous Cell Carcinoma of the Larynx; Stage IV Squamous Cell Carcinoma of the Lip and Oral Cavity; Stage IV Squamous Cell Carcinoma of the Nasopharynx; Stage IV Squamous Cell Carcinoma of the Oropharynx; Stage IV Squamous Cell Carcinoma of the Paranasal Sinus and Nasal Cavity; Stage IV Verrucous Carcinoma of the Larynx; Stage IV Verrucous Carcinoma of the Oral Cavity; Unspecified Adult Solid Tumor, Protocol Specific

Stage Separation Failure: Model Based Diagnostics and Prognostics

NASA Technical Reports Server (NTRS)

Luchinsky, Dmitry; Hafiychuk, Vasyl; Kulikov, Igor; Smelyanskiy, Vadim; Patterson-Hine, Ann; Hanson, John; Hill, Ashley

2010-01-01

Safety of the next-generation space flight vehicles requires development of an in-flight Failure Detection and Prognostic (FD&P) system. Development of such system is challenging task that involves analysis of many hard hitting engineering problems across the board. In this paper we report progress in the development of FD&P for the re-contact fault between upper stage nozzle and the inter-stage caused by the first stage and upper stage separation failure. A high-fidelity models and analytical estimations are applied to analyze the following sequence of events: (i) structural dynamics of the nozzle extension during the impact; (ii) structural stability of the deformed nozzle in the presence of the pressure and temperature loads induced by the hot gas flow during engine start up; and (iii) the fault induced thrust changes in the steady burning regime. The diagnostic is based on the measurements of the impact torque. The prognostic is based on the analysis of the correlation between the actuator signal and fault-induced changes in the nozzle structural stability and thrust.

KSC-99pc0188

NASA Image and Video Library

1999-02-09

In the Solid Motor Assembly Building, Cape Canaveral Air Station, STS-93 Mission Specialist Catherine G. Coleman (left) lifts the protective covering to look at the avionics box on the Inertial Upper Stage booster. Next to her are Eric Herrburger (center), with Boeing, and crew member Mission Specialist Michel Tognini (right) of France, who represents the Centre National d'Etudes Spatiales (CNES). STS-93 is scheduled to launch July 9 aboard Space Shuttle Columbia and has the primary mission of the deployment of the Chandra X-ray Observatory. Formerly called the Advanced X-ray Astrophysics Facility, Chandra comprises three major elements: the spacecraft, the science instrument module (SIM), and the world's most powerful X-ray telescope. Chandra will allow scientists from around the world to see previously invisible black holes and high-temperature gas clouds, giving the observatory the potential to rewrite the books on the structure and evolution of our universe. Other STS-93 crew members are Commander Eileen M. Collins, Pilot Jeffrey S. Ashby and Mission Specialist Steven A. Hawley

KSC-07pd1645

NASA Image and Video Library

2007-06-26

KENNEDY SPACE CENTER, FLA. -- At Astrotech, technicians lower the upper canister over the Dawn spacecraft. After enclosure, Dawn will be transported to Launch Pad 17-B and lifted into the mobile service tower for mating with the Delta II launch vehicle. The Delta II-Heavy, manufactured by the United Launch Alliance, is scheduled to launch the Dawn spacecraft on its 4-year flight to the asteroid belt. The Delta II-Heavy will use three stages and nine solid-fueled booster rockets to propel Dawn on its way. A 9.5-foot payload fairing will protect the spacecraft from the heat and stresses of launch. Dawn's goal is to characterize the conditions and processes of the solar system's earliest epoch by investigating in detail the largest protoplanets that have remained intact since their formations: asteroid Vesta and the dwarf planet Ceres. They reside in the extensive zone between Mars and Jupiter together with many other smaller bodies, called the asteroid belt. Dawn is scheduled to launch July 7. Photo credit: NASA/George Shelton

KSC-07pd1646

NASA Image and Video Library

2007-06-26

KENNEDY SPACE CENTER, FLA. -- At Astrotech, technicians secure the upper canister over the Dawn spacecraft. Dawn will be transported to Launch Pad 17-B and lifted into the mobile service tower for mating with the Delta II launch vehicle. The Delta II-Heavy, manufactured by the United Launch Alliance, is scheduled to launch the Dawn spacecraft on its 4-year flight to the asteroid belt. The Delta II-Heavy will use three stages and nine solid-fueled booster rockets to propel Dawn on its way. A 9.5-foot payload fairing will protect the spacecraft from the heat and stresses of launch. Dawn's goal is to characterize the conditions and processes of the solar system's earliest epoch by investigating in detail the largest protoplanets that have remained intact since their formations: asteroid Vesta and the dwarf planet Ceres. They reside in the extensive zone between Mars and Jupiter together with many other smaller bodies, called the asteroid belt. Dawn is scheduled to launch July 7. Photo credit: NASA/George Shelton

KSC-07pd1644

NASA Image and Video Library

2007-06-26

KENNEDY SPACE CENTER, FLA. -- At Astrotech, technicians begin lowering the upper canister over the Dawn spacecraft. After enclosure, Dawn will be transported to Launch Pad 17-B and lifted into the mobile service tower for mating with the Delta II launch vehicle. The Delta II-Heavy, manufactured by the United Launch Alliance, is scheduled to launch the Dawn spacecraft on its 4-year flight to the asteroid belt. The Delta II-Heavy will use three stages and nine solid-fueled booster rockets to propel Dawn on its way. A 9.5-foot payload fairing will protect the spacecraft from the heat and stresses of launch. Dawn's goal is to characterize the conditions and processes of the solar system's earliest epoch by investigating in detail the largest protoplanets that have remained intact since their formations: asteroid Vesta and the dwarf planet Ceres. They reside in the extensive zone between Mars and Jupiter together with many other smaller bodies, called the asteroid belt. Dawn is scheduled to launch July 7. Photo credit: NASA/George Shelton

Geology, hydrology, and water quality of the Tracy-Dos Palos area, San Joaquin Valley, California

USGS Publications Warehouse

Hotchkiss, W.R.; Balding, G.O.

1971-01-01

The Tracy-Dos Palos area includes about 1,800 square miles on the northwest side of the San Joaquin Valley. The Tulare Formation of Pliocene and Pleistocene age, terrace deposits of Pleistocene age, and alluvium and flood-basin deposits of Pleistocene and Holocene age constitute the fresh ground-water reservoir Pre-Tertiary and Tertiary sedimentary and crystalline rocks, undifferentiated, underlie the valley and yield saline water. Hydrologically most important, the Tulare Formation is divided into a lower water-bearing zone confined by the Corcoran Clay Member and an upper zone that is confined, semiconfined, and unconfined in different parts of the area. Alluvium and flood-basin deposits are included in the upper zone. Surficial alluvium and flood-basin deposits contain a shallow water-bearing zone. Lower zone wells were flowing in 1908, but subsequent irrigation development caused head declines and land subsidence. Overdraft in both zones ended in 1951 with import of surface water. Bicarbonate water flows into the area from the Sierra Nevada and Diablo Range. Diablo Range water is higher in sulfate, chloride, and dissolved solids. Upper zone water averages between 400 and 1,200 mg/l (milligrams per liter) dissolved solids and water hardness generally exceeds 180 mg/l as calcium carbonate. Nitrate, fluoride, iron, and boron occur in excessive concentrations in water from some wells. Dissolved constituents in lower zone water generally are sodium chloride and sodium sulfate with higher dissolved solids concentration than water from the upper zone. The foothills of the Diablo Range provide favorable conditions for artificial recharge, but shallow water problems plague about 50 percent of the area and artificial recharge is undesirable at this time.

A novel voice coil motor-driven compliant micropositioning stage based on flexure mechanism

NASA Astrophysics Data System (ADS)

Shang, Jiangkun; Tian, Yanling; Li, Zheng; Wang, Fujun; Cai, Kunhai

2015-09-01

This paper presents a 2-degrees of freedom flexure-based micropositioning stage with a flexible decoupling mechanism. The stage is composed of an upper planar stage and four vertical support links to improve the out-of-plane stiffness. The moving platform is driven by two voice coil motors, and thus it has the capability of large working stroke. The upper stage is connected with the base through six double parallel four-bar linkages mechanisms, which are orthogonally arranged to implement the motion decoupling in the x and y directions. The vertical support links with serially connected hook joints are utilized to guarantee good planar motion with heavy-loads. The static stiffness and the dynamic resonant frequencies are obtained based on the theoretical analyses. Finite element analysis is used to investigate the characteristics of the developed stage. Experiments are carried out to validate the established models and the performance of the developed stage. It is noted that the developed stage has the capability of translational motion stroke of 1.8 mm and 1.78 mm in working axes. The maximum coupling errors in the x and y directions are 0.65% and 0.82%, respectively, and the motion resolution is less than 200 nm. The experimental results show that the developed stage has good capability for trajectory tracking.

Saturn Apollo Program

NASA Image and Video Library

1960-01-01

RL-10 engine characteristics. The RL-10 engine was developed under the management of the Marshall Space Flight Center (MSFC) to power the Saturn I upper stage (S-IV stage). The six RL-10 engines, which used liquid hydrogen and liquid oxygen as propellants, were arranged in a circle on the aft end of the S-IV stage.

Bevacizumab and Cediranib Maleate in Treating Patients With Metastatic or Unresectable Solid Tumor, Lymphoma, Intracranial Glioblastoma, Gliosarcoma or Anaplastic Astrocytoma

ClinicalTrials.gov

2014-02-14

Adult Grade III Lymphomatoid Granulomatosis; Adult Nasal Type Extranodal NK/T-cell Lymphoma; Anaplastic Large Cell Lymphoma; Angioimmunoblastic T-cell Lymphoma; Childhood Burkitt Lymphoma; Childhood Diffuse Large Cell Lymphoma; Childhood Grade III Lymphomatoid Granulomatosis; Childhood Immunoblastic Large Cell Lymphoma; Childhood Nasal Type Extranodal NK/T-cell Lymphoma; Cutaneous B-cell Non-Hodgkin Lymphoma; Extranodal Marginal Zone B-cell Lymphoma of Mucosa-associated Lymphoid Tissue; Hepatosplenic T-cell Lymphoma; Intraocular Lymphoma; Nodal Marginal Zone B-cell Lymphoma; Noncutaneous Extranodal Lymphoma; Peripheral T-cell Lymphoma; Progressive Hairy Cell Leukemia, Initial Treatment; Recurrent Adult Burkitt Lymphoma; Recurrent Adult Diffuse Large Cell Lymphoma; Recurrent Adult Diffuse Mixed Cell Lymphoma; Recurrent Adult Diffuse Small Cleaved Cell Lymphoma; Recurrent Adult Hodgkin Lymphoma; Recurrent Adult Immunoblastic Large Cell Lymphoma; Recurrent Adult Lymphoblastic Lymphoma; Recurrent Adult T-cell Leukemia/Lymphoma; Recurrent Childhood Anaplastic Large Cell Lymphoma; Recurrent Childhood Large Cell Lymphoma; Recurrent Childhood Lymphoblastic Lymphoma; Recurrent Childhood Small Noncleaved Cell Lymphoma; Recurrent Grade 1 Follicular Lymphoma; Recurrent Grade 2 Follicular Lymphoma; Recurrent Grade 3 Follicular Lymphoma; Recurrent Mantle Cell Lymphoma; Recurrent Mycosis Fungoides/Sezary Syndrome; Recurrent/Refractory Childhood Hodgkin Lymphoma; Refractory Hairy Cell Leukemia; Small Intestine Lymphoma; Splenic Marginal Zone Lymphoma; Stage IV Adult Burkitt Lymphoma; Stage IV Adult Diffuse Large Cell Lymphoma; Stage IV Adult Diffuse Mixed Cell Lymphoma; Stage IV Adult Diffuse Small Cleaved Cell Lymphoma; Stage IV Adult Hodgkin Lymphoma; Stage IV Adult Immunoblastic Large Cell Lymphoma; Stage IV Adult Lymphoblastic Lymphoma; Stage IV Adult T-cell Leukemia/Lymphoma; Stage IV Childhood Anaplastic Large Cell Lymphoma; Stage IV Childhood Hodgkin Lymphoma; Stage IV Childhood Large Cell Lymphoma; Stage IV Childhood Lymphoblastic Lymphoma; Stage IV Childhood Small Noncleaved Cell Lymphoma; Stage IV Grade 1 Follicular Lymphoma; Stage IV Grade 2 Follicular Lymphoma; Stage IV Grade 3 Follicular Lymphoma; Stage IV Mantle Cell Lymphoma; Stage IVA Mycosis Fungoides/Sezary Syndrome; Stage IVB Mycosis Fungoides/Sezary Syndrome; T-cell Large Granular Lymphocyte Leukemia; Testicular Lymphoma; Unspecified Adult Solid Tumor, Protocol Specific; Unspecified Childhood Solid Tumor, Protocol Specific; Waldenström Macroglobulinemia

TDRS-M Atlas V Booster and Centaur Stages Arrival, Offload, and Transport (Booster) to ASOC

NASA Image and Video Library

2017-06-26

The United Launch Alliance (ULA) Mariner arrives at Port Canaveral in Florida carrying an Atlas V rocket booster and centaur upper stage bounded for Cape Canaveral Air Force Station. The centaur upper stage is transported from the company's Mariner ship to the Delta Operations Center. The booster stage is transported to the Atlas Spaceflight Operations Center. The rocket is scheduled to launch the Tracking and Data Relay Satellite, TDRS-M. It will be the latest spacecraft destined for the agency's constellation of communications satellites that allows nearly continuous contact with orbiting spacecraft ranging from the International Space Station and Hubble Space Telescope to the array of scientific observatories. Liftoff atop the ULA Atlas V rocket is scheduled to take place from Cape Canaveral's Space Launch Complex 41 on Aug. 3, 2017 at 9:02 a.m. EDT.

Ram booster

NASA Technical Reports Server (NTRS)

Brand, Vance D. (Inventor); Morgan, Walter Ray (Inventor)

2011-01-01

The present invention is a space launch system and method to propel a payload bearing craft into earth orbit. The invention has two, or preferably, three stages. The upper stage has rocket engines capable of carrying a payload to orbit and provides the capability of releasably attaching to the lower, or preferably, middle stage. Similar to the lower stage, the middle stage is a reusable booster stage that employs all air breathing engines, is recoverable, and can be turned-around in a short time between missions.

Alkylation of organic aromatic compounds

DOEpatents

Smith, Jr., Lawrence A.; Arganbright, Robert P.; Hearn, Dennis

1993-01-01

Aromatic compounds are alkylated in a combination reactor/distillation column comprising a vessel suitable for operating between 70.degree. C. and 500.degree. C. and from 0.5 to 20 atmospheres pressure; an inert distillation packing in the lower one-third of said vessel; solid acidic catalytic material such as zeolites or an acidic cation exchange resin supported in the middle one-third of said vessel; and inert distillation packing in the upper one-third of said vessel. A benzene inlet is located near the upper end of the vessel; an olefin inlet is juxtaposed with said solid acidic catalytic material; a bottoms outlet is positioned near the bottom of said vessel for removing said cumene and ethyl benzene; and an overhead outlet is placed at the top of said vessel for removing any unreacted benzene and olefin.

Alkylation of organic aromatic compounds

DOEpatents

Smith, L.A. Jr.; Arganbright, R.P.; Hearn, D.

1993-01-05

Aromatic compounds are alkylated in a combination reactor/distillation column comprising a vessel suitable for operating between 70 C and 500 C and from 0.5 to 20 atmospheres pressure; an inert distillation packing in the lower one-third of said vessel; solid acidic catalytic material such as zeolites or an acidic cation exchange resin supported in the middle one-third of said vessel; and inert distillation packing in the upper one-third of said vessel. A benzene inlet is located near the upper end of the vessel; an olefin inlet is juxtaposed with said solid acidic catalytic material; a bottoms outlet is positioned near the bottom of said vessel for removing said cumene and ethyl benzene; and an overhead outlet is placed at the top of said vessel for removing any unreacted benzene and olefin.

Waste Away--Information and Activities for Investigating Trash Problems and Solutions for Upper Elementary and Junior High School Students.

ERIC Educational Resources Information Center

Vermont Inst. of Natural Science, Woodstock.

The solid waste problem is so pervasive that it can no longer be ignored. The purpose of this set of materials is to encourage a lifestyle that includes the use of the three R's: Reduce, Reuse, Recycle. It was designed to educate upper elementary and junior high school students who may educate their classmates, families, and community about the…

Effect of agitation on methanogenesis stage of two-stage anaerobic digestion of palm oil mill effluent (POME) into biogas

NASA Astrophysics Data System (ADS)

Trisakti, Bambang; Irvan, Zahara, Intan; Taslim, Turmuzi, Muhammad

2017-05-01

This study is an assessment of the effect of agitation on biogas production on methanogenesis stage. Methanogenesis is the second stage of two-stage anaerobic digestion of palm oil effluent (POME) into biogas. The purpose of this study is to get the effect of agitation on growth of microorganisms, degradation of organic substances, and biogas production and composition. Initially, the suitable loading up was determined by varying the HRT at 100, 40, 6, and 4 days in the continuous stirred tank reactor (CSTR) with agitation rate 100 rpm, pH 6.7-7.5, at room temperature. Next, effect of agitation on the process was determined by varying agitation rate at 50, 100, 150, and 200 rpm. The substrate used was the effluent of the acidogenesis stage that fed to the CSTR four times a day. Analysis of total solids (TS), volatile solids (VS), total suspended solids (TSS), volatile suspended solids (VSS), and chemical oxygen demand (COD) were conducted in order to study the growth of microorganisms and their abilities in converting organic compound to produce biogas. Production and composition of biogas were also determined by measuring the volume of biogas and content of H2S and CO2. The result showed that the pH and alkalinity it was still within the range of methanogenesis process. The growth of microorganisms were increased with the increasing of agitation rate. However, the best degradation of organic substances, biogas production, and biogas composition were achieved at 100 rpm. The VS decomposition, COD removal, biogas production, CO2 content, and CH4 content at 100 rpm were 67.44 ± 3.59%, 81.00%, 58.87 ± 6.27 L/kg-ΔVS, 23.36%, and 76.64%, respectively.

Study of solid rocket motors for a space shuttle booster. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

1972-01-01

An analysis of the solid propellant rocket engines for use with the space shuttle booster was conducted. A definition of the specific solid propellant rocket engine stage designs, development program requirements, production requirements, launch requirements, and cost data for each program phase were developed.

STS-44 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W.

1992-01-01

The STS-44 Space Shuttle Program Mission Report is a summary of the vehicle subsystem operations during the forty-fourth flight of the Space Shuttle Program and the tenth flight of the Orbiter vehicle Atlantis (OV-104). In addition to the Atlantis vehicle, the flight vehicle consisted of the following: an External Tank (ET) designated as ET-53 (LWT-46); three Space Shuttle main engines (SSME's) (serial numbers 2015, 2030, and 2029 in positions 1, 2, and 3, respectively); and two Solid Rocket Boosters (SRB's) designated as BI-047. The lightweight redesigned Solid Rocket Motors (RSRM's) installed in each one of the SRB's were designated as 360L019A for the left SRB and 360W019B for the right SRB. The primary objective of the STS-44 mission was to successfully deploy the Department of Defense (DOD) Defense Support Program (DSP) satellite/inertial upper stage (IUS) into a 195 nmi. earth orbit at an inclination of 28.45 deg. Secondary objectives of this flight were to perform all operations necessary to support the requirements of the following: Terra Scout, Military Man in Space (M88-1), Air Force Maui Optical System Calibration Test (AMOS), Cosmic Radiation Effects and Activation Monitor (CREAM), Shuttle Activation Monitor (SAM), Radiation Monitoring Equipment-3 (RME-3), Visual Function Tester-1 (VFT-1), and the Interim Operational Contamination Monitor (IOCM) secondary payloads/experiments.

NASA Ares I Crew Launch Vehicle Upper Stage Overview

NASA Technical Reports Server (NTRS)

Davis, Daniel J.

2008-01-01

By incorporating rigorous engineering practices, innovative manufacturing processes and test techniques, a unique multi-center government/contractor partnership, and a clean-sheet design developed around the primary requirements for the International Space Station (ISS) and Lunar missions, the Upper Stage Element of NASA's Crew Launch Vehicle (CLV), the "Ares I," is a vital part of the Constellation Program's transportation system. Constellation's exploration missions will include Ares I and Ares V launch vehicles required to place crew and cargo in low-Earth orbit (LEO), crew and cargo transportation systems required for human space travel, and transportation systems and scientific equipment required for human exploration of the Moon and Mars. Early Ares I configurations will support ISS re-supply missions. A self-supporting cylindrical structure, the Ares I Upper Stage will be approximately 84' long and 18' in diameter. The Upper Stage Element is being designed for increased supportability and increased reliability to meet human-rating requirements imposed by NASA standards. The design also incorporates state-of-the-art materials, hardware, design, and integrated logistics planning, thus facilitating a supportable, reliable, and operable system. With NASA retiring the Space Shuttle fleet in 2010, the success of the Ares I Project is essential to America's continued leadership in space. The first Ares I test flight, called Ares 1-X, is scheduled for 2009. Subsequent test flights will continue thereafter, with the first crewed flight of the Crew Exploration Vehicle (CEV), "Orion," planned for no later than 2015. Crew transportation to the ISS will follow within the same decade, and the first Lunar excursion is scheduled for the 2020 timeframe.

NASA Ares I Crew Launch Vehicle Upper Stage Overview

NASA Technical Reports Server (NTRS)

McArthur, J. Craig

2008-01-01

By incorporating rigorous engineering practices, innovative manufacturing processes and test techniques, a unique multi-center government/contractor partnership, and a clean-sheet design developed around the primary requirements for the International Space Station (ISS) and Lunar missions, the Upper Stage Element of NASA's Crew Launch Vehicle (CLV), the "Ares I," is a vital part of the Constellation Program's transportation system. Constellation's exploration missions will include Ares I and Ares V launch vehicles required to place crew and cargo in low-Earth orbit (LEO), crew and cargo transportation systems required for human space travel, and transportation systems and scientific equipment required for human exploration of the Moon and Mars. Early Ares I configurations will support ISS re-supply missions. A self-supporting cylindrical structure, the Ares I Upper Stage will be approximately 84' long and 18' in diameter. The Upper Stage Element is being designed for increased supportability and increased reliability to meet human-rating requirements imposed by NASA standards. The design also incorporates state-of-the-art materials, hardware, design, and integrated logistics planning, thus facilitating a supportable, reliable, and operable system. With NASA retiring the Space Shuttle fleet in 2010, the success of the Ares I Project is essential to America's continued leadership in space. The first Ares I test flight, called Ares I-X, is scheduled for 2009. Subsequent test flights will continue thereafter, with the first crewed flight of the Crew Exploration Vehicle (CEV), "Orion," planned for no later than 2015. Crew transportation to the ISS will follow within the same decade, and the first Lunar excursion is scheduled for the 2020 timeframe.

Model study on transesterification of soybean oil to biodiesel with methanol using solid base catalyst.

PubMed

Liu, Xuejun; Piao, Xianglan; Wang, Yujun; Zhu, Shenlin

2010-03-25

Modeling of the transesterification of vegetable oils to biodiesel using a solid base as a catalyst is very important because the mutual solubilities of oil and methanol will increase with the increasing biodiesel yield. The heterogeneous liquid-liquid-solid reaction system would become a liquid-solid system when the biodiesel reaches a certain content. In this work, we adopted a two-film theory and a steady state approximation assumption, then established a heterogeneous liquid-liquid-solid model in the first stage. After the diffusion coefficients on the liquid-liquid interface and the liquid-solid interface were calculated on the basis of the properties of the system, the theoretical value of biodiesel productivity changing with time was obtained. The predicted values were very near the experimental data, which indicated that the proposed models were suitable for the transesterification of soybean oil to biodiesel when solid bases were used as catalysts. Meanwhile, the model indicated that the transesterification reaction was controlled by both mass transfer and reaction. The total resistance will decrease with the increase in biodiesel yield in the liquid-liquid-solid stage. The solid base catalyst exhibited an activation energy range of 9-20 kcal/mol, which was consistent with the reported activation energy range of homogeneous catalysts.

Gastric emptying of solids in children: reference values for the (13) C-octanoic acid breath test.

PubMed

Hauser, B; Roelants, M; De Schepper, J; Veereman, G; Caveliers, V; Devreker, T; De Greef, E; Vandenplas, Y

2016-10-01

(99m) Technetium scintigraphy ((99m) TS) is the 'gold standard' for measuring gastric emptying (GE), but it is associated with a radiation exposure. For this reason, the (13) C-octanoic acid breath test ((13) C-OBT) was developed for measuring GE of solids. The objective of this study was to determine normal values for gastric half-emptying time (t1/2 GE) of solids in healthy children. Gastric emptying of a standardized solid test meal consisting of a pancake evaluated with (99m) TS and (13) C-OBT was compared in 22 children aged between 1 and 15 years with upper gastrointestinal symptoms. Subsequently, the (13) C-OBT was used to determine normal values for GE of the same solid test meal in 120 healthy children aged between 1 and 17 years. The results showed a significant correlation (r = 0.748, p = 0.0001) between t1/2 GE measured with both techniques in the group of children with upper gastrointestinal symptoms. In the group of healthy children, mean t1/2 GE was 157.7 ± 54.0 min (range 71-415 min), but t1/2 GE decreased with age between 1 and 10 years and remained stable afterward. There was no influence of gender, weight, height, body mass index, and body surface area on t1/2 GE. Normal values for GE of solids measured with the (13) C-OBT using a standardized methodology were determined in healthy children. We propose to use this method and corresponding reference ranges to study GE of solids in children with gastrointestinal problems. © 2016 John Wiley & Sons Ltd.

A comparison of solids collected in sediment traps and automated water samplers

USGS Publications Warehouse

Bartsch, L.A.; Rada, R.G.; Sullivan, J.F.

1996-01-01

Sediment traps are being used in some pollution monitoring programs in the USA to sample suspended solids for contaminant analyses. This monitoring approach assumes that the characteristics of solids obtained in sediment traps are the same as those collected in whole-water sampling devices. We tested this assumption in the upper Mississippi River, based on the inorganic particle-size distribution (determined with a laser particle- analyzer) and volatile matter content of solids (a surrogate for organic matter). Cylindrical sediment traps (aspect ratio 3) were attached to a rigid mooring device and deployed in a flowing side channel in Navigation Pool 7 of the upper Mississippi River. On each side of the mooring device, a trap was situated adjacent to a port of an autosampler that collected raw water samples hourly to form 2-d composite samples. Paired samples (one trap and one raw water, composite sample) were removed from each end of the mooring device at 2-d intervals during the 30-d study period and compared. The relative particle collection efficiency of paired samplers did not vary temporally. Particle-size distributions of inorganic solids from sediment traps and water samples were not significantly different. The volatile matter content of solids was lesser in sediment traps (mean, 9.5%) than in corresponding water samples (mean, 22.7%). This bias may have been partly due to under-collection of phytoplankton (mainly cyanobacteria), which were abundant in the water column during the study. The positioning of water samplers and sediment traps in the mooring device did not influence the particle-size distribution or total solids of samples. We observed a small difference in the amount of organic matter collected by water samplers situated at opposite ends of the mooring device.

Concept of Operations Visualization in Support of Ares I Production

NASA Technical Reports Server (NTRS)

Chilton, James H.; Smith, Daid Alan

2008-01-01

Boeing was selected in 2007 to manufacture Ares I Upper Stage and Instrument Unit according to NASA's design which would require the use of the latest manufacturing and integration processes to meet NASA budget and schedule targets. Past production experience has established that the majority of the life cycle cost is established during the initial design process. Concept of Operations (CONOPs) visualizations/simulations help to reduce life cycle cost during the early design stage. Production and operation visualizations can reduce tooling, factory capacity, safety, and build process risks while spreading program support across government, academic, media and public constituencies. The NASA/Boeing production visualization (DELMIA; Digital Enterprise Lean Manufacturing Interactive Application) promotes timely, concurrent and collaborative producibility analysis (Boeing)while supporting Upper Stage Design Cycles (NASA). The DELMIA CONOPs visualization reduced overall Upper Stage production flow time at the manufacturing facility by over 100 man-days to 312.5 man-days and helped to identify technical access issues. The NASA/Boeing Interactive Concept of Operations (ICON) provides interactive access to Ares using real mission parameters, allows users to configure the mission which encourages ownership and identifies areas for improvement, allows mission operations or spacecraft detail to be added as needed, and provides an effective, low coast advocacy, outreach and education tool.

Large-Scale Liquid Hydrogen Tank Rapid Chill and Fill Testing for the Advanced Shuttle Upper Stage Concept

NASA Technical Reports Server (NTRS)

Flachbart, R. H.; Hedayat, A.; Holt, K. A.; Sims, J.; Johnson, E. F.; Hastings, L. J.; Lak, T.

2013-01-01

Cryogenic upper stages in the Space Shuttle program were prohibited primarily due to a safety risk of a 'return to launch site' abort. An upper stage concept addressed this concern by proposing that the stage be launched empty and filled using shuttle external tank residuals after the atmospheric pressure could no longer sustain an explosion. However, only about 5 minutes was allowed for tank fill. Liquid hydrogen testing was conducted within a near-ambient environment using the multipurpose hydrogen test bed 638.5 ft3 (18m3) cylindrical tank with a spray bar mounted longitudinally inside. Although the tank was filled within 5 minutes, chilldown of the tank structure was incomplete, and excessive tank pressures occurred upon vent valve closure. Elevated tank wall temperatures below the liquid level were clearly characteristic of film boiling. The test results have substantial implications for on-orbit cryogen transfer since the formation of a vapor film would be much less inhibited due to the reduced gravity. However, the heavy tank walls could become an asset in normal gravity testing for on-orbit transfer, i.e., if film boiling in a nonflight weight tank can be inhibited in normal gravity, then analytical modeling anchored with the data could be applied to reduced gravity environments with increased confidence.

Ares V: Progress Toward Unprecedented Heavy Lift

NASA Technical Reports Server (NTRS)

Sumrall, Phil

2010-01-01

Ares V represents the vehicle that will again make possible human exploration beyond low Earth orbit. The Ares V is part of NASA s Constellation Program architecture developed to support the International Space Station (ISS), establish a permanent human presence on the Moon, and explore it to an extent far greater than was possible with the Apollo Program. Ares V will carry the lunar lander to orbit where it will join the Orion crew spacecraft, launched by the smaller Ares I launch vehicle. Then the Ares V upper stage will send the Orion and lander to the Moon. Ares V is also intended to launch automated cargo landers to the Moon. The Ares vehicles are designed to employ the proven technologies and experience from the Space Shuttle, Delta IV, and earlier U.S. programs, as well as sharing common components where feasible. The Ares V is in an early stage of concept development. However, commonality allows it to benefit from development work already under way on the Ares I, including the first stage booster, and upper stage, J-2X upper stage engine. This paper will discuss progress to date on the Ares V and its potential for freeing payload designers from current mass and volume constraints. Progress includes development progress on Ares I elements that will be shared by the two launch vehicles. The Ares I first stage recently completed a successful test firing of Development Motor 1 (DM-1). The J-2X engine is proceeding with manufacturing of components for the first development engines that will be used for testing. Several component-level tests have been completed or are under way that will help verify designs and confirm solutions to design challenges. The Ares V Earth departure stage will benefit from the Ares I upper stage development, including design, manufacturing, and materials testing. NASA is also working with government and industry to collect data on flights and testing of the operational RS-68 engine and potential upgrades. The Ares V team continues to evaluate technical options, vehicle configurations, and operations concepts for the Ares V. The team recently completed a Fall Face-to-Face meeting that served as a stepping-stone to the Systems Requirements Review (SRR). This four-day meeting served as an information exchange for the various teams at several NASA field centers and supporting contractors.

Ares I-X Upper Stage Simulator Residual Stress Analysis

NASA Technical Reports Server (NTRS)

Raju, Ivatury S.; Brust, Frederick W.; Phillips, Dawn R.; Cheston, Derrick

2008-01-01

The structural analyses described in the present report were performed in support of the NASA Engineering and Safety Center (NESC) Critical Initial Flaw Size (CIFS) assessment for the Ares I-X Upper Stage Simulator (USS) common shell segment. An independent assessment was conducted to determine the critical initial flaw size (CIFS) for the flange-to-skin weld in the Ares I-X Upper Stage Simulator (USS). The Ares system of space launch vehicles is the US National Aeronautics and Space Administration s plan for replacement of the aging space shuttle. The new Ares space launch system is somewhat of a combination of the space shuttle system and the Saturn launch vehicles used prior to the shuttle. Here, a series of weld analyses are performed to determine the residual stresses in a critical region of the USS. Weld residual stresses both increase constraint and mean stress thereby having an important effect on fatigue and fracture life. The results of this effort served as one of the critical load inputs required to perform a CIFS assessment of the same segment.

Model Based Definition

NASA Technical Reports Server (NTRS)

Rowe, Sidney E.

2010-01-01

In September 2007, the Engineering Directorate at the Marshall Space Flight Center (MSFC) created the Design System Focus Team (DSFT). MSFC was responsible for the in-house design and development of the Ares 1 Upper Stage and the Engineering Directorate was preparing to deploy a new electronic Configuration Management and Data Management System with the Design Data Management System (DDMS) based upon a Commercial Off The Shelf (COTS) Product Data Management (PDM) System. The DSFT was to establish standardized CAD practices and a new data life cycle for design data. Of special interest here, the design teams were to implement Model Based Definition (MBD) in support of the Upper Stage manufacturing contract. It is noted that this MBD does use partially dimensioned drawings for auxiliary information to the model. The design data lifecycle implemented several new release states to be used prior to formal release that allowed the models to move through a flow of progressive maturity. The DSFT identified some 17 Lessons Learned as outcomes of the standards development, pathfinder deployments and initial application to the Upper Stage design completion. Some of the high value examples are reviewed.

Safety and Mission Assurance for In-House Design Lessons Learned from Ares I Upper Stage

NASA Technical Reports Server (NTRS)

Anderson, Joel M.

2011-01-01

This viewgraph presentation identifies lessons learned in the course of the Ares I Upper Stage design and in-house development effort. The contents include: 1) Constellation Organization; 2) Upper Stage Organization; 3) Presentation Structure; 4) Lesson-Importance of Systems Engineering/Integration; 5) Lesson-Importance of Early S&MA Involvement; 6) Lesson-Importance of Appropriate Staffing Levels; 7) Lesson-Importance S&MA Team Deployment; 8) Lesson-Understanding of S&MA In-Line Engineering versus Assurance; 9) Lesson-Importance of Close Coordination between Supportability and Reliability/Maintainability; 10) Lesson-Importance of Engineering Data Systems; 11) Lesson-Importance of Early Development of Supporting Databases; 12) Lesson-Importance of Coordination with Safety Assessment/Review Panels; 13) Lesson-Implementation of Software Reliability; 14) Lesson-Implementation of S&MA Technical Authority/Chief S&MA Officer; 15) Lesson-Importance of S&MA Evaluation of Project Risks; 16) Lesson-Implementation of Critical Items List and Government Mandatory Inspections; 17) Lesson-Implementation of Critical Items List Mandatory Inspections; 18) Lesson-Implementation of Test Article Safety Analysis; and 19) Lesson-Importance of Procurement Quality.

Staged heating by oxidation of carbonaceous material

DOEpatents

Knell, Everett W.; Green, Norman W.

1978-01-31

A carbonaceous material is pyrolyzed in the presence of a particulate source of heat obtained by the partial oxidation of a carbon containing solid residue of the carbonaceous material. The heat obtained from the oxidation of the carbon containing solid residue is maximized by preheating the carbon containing solid residue with a hot gas stream obtained by oxidizing the gaseous combustion products of the carbon containing solid residue.

Long-term effects of surface coal mining on ground-water levels and quality in two small watersheds in eastern Ohio

USGS Publications Warehouse

Cunningham, W.L.; Jones, R.L.

1990-01-01

Two small watersheds in eastern Ohio that were surface mined for coal and reclaimed were studied during 1986-89. Water-level and water-quality data were compared with similar data collected during previous investigations conducted during 1976-83 to determine long-term effects of surface mining on the hydrologic system. Before mining, the watersheds were characterized by sequences of flat-lying sedimentary rocks containing two major coal seams and underclays. An aquifer was present above each of the underclays. Surface mining removed the upper aquifer, stripped the coal seam, and replaced the sediment. This created a new upper aquifer with different hydraulic and chemical characteristics. Mining did not disturb the middle aquifer. A third, deeper aquifer in each watershed was not studied. Water levels were continuously recorded in one well in each aquifer. Other wells were measured every 2 months. Water levels in the upper aquifers reached hydraulic equilibrium from 2 to 5 years after mining ceased. Water levels in the middle aquifers increased more than 5 feet during mining and reached equilibrium almost immediately thereafter. Water samples were collected from three upper-aquifer well, a seep from the upper aquifer, and the stream in each watershed. Two samples were collected in 1986 and 1987, and one each in 1988 and 1989. In both watersheds, sulfate replaced bicarbonate as the dominant upper-aquifer and surface-water anion after mining. For the upper aquifer of a watershed located in Muskingum County, water-quality data were grouped into premining and late postmining time periods (1986-89). The premining median pH and concentration of dissolved solids and sulfate were 7.6, 378 mg/L (milligrams per liter), and 41 mg/L, respectively. The premining median concentrations of iron and manganese were 10? /L (micrograms per liter) and 25?, respectively. The postmining median values of pH, dissolved solids, and sulfate were 6.7, 1,150 mg/L, and 560 mg/L, respectively. The postmining median concentrations of iron and manganese were 3,900?g/L and 1,900? g/L, respectively. For the upper aquifer of a watershed located in Jefferson County, the water-quality data were grouped into three time periods of premining, early postmining, and late postmining. The premining median pH and concentrations of dissolved solids and sulfate were 7.0, 335 mg/L, and 85 mg/L, respectively. The premining median concentrations of iron and manganese were 30? g/L for each constituent. Late postmining median pH and concentrations of dissolved solids and sulfate were 6.7, 1,495 mg/L, and 825 mg/L, respectively. The postmining median concentrations of iron and manganese were 31? g/L and 1,015? g/L, respectively. Chemistry of water in the middle aquifer in each watershed underwent similar changes. In general, statistically significant increases in concentrations of dissolved constituents occurred because of surface mining. In some constituents, concentrations increased by more than an order of magnitude. The continued decrease in pH indicated that ground water had no reached geochemical equilibrium in either watershed more than 8 years after mining.

NASA's Space Launch System: Progress Report

NASA Technical Reports Server (NTRS)

Cook, Jerry; Lyles, Garry

2017-01-01

NASA and its commercial industry team achieved significant progress in 2016 in manufacturing and testing of the Block 1 vehicle for the first launch of the Space Launch System (SLS). Test and flight article hardware for the liquid hydrogen fuel tank as well as the engine section for the core stage were completed at Michoud Assembly Facility (MAF) in New Orleans. Test stands neared completion at Marshall Space Flight Center for the propellant tanks, engine section, intertank and payload section. Stennis Space Center completed major structural renovations on the B2 test stand, where the core stage "green run" test program will be conducted. The SLS team completed a hotfire test series at Stennis to successfully demonstrate the ability of the RS-25 engine to operate under SLS environments and performance conditions. The team also test fired the second qualification five-segment solid rocket motor and cast the first six motor segments for the first SLS mission. The Interim Cryogenic Propulsion Stage (ICPS) test article was delivered to Marshall for structural tests, and work is nearly finished on the flight stage. Flight software testing completed at Marshall included power quality and command and data handling. In 2017, that work continues. SLS completed Preliminary Design Review (PDR) on the Exploration Upper Stage (EUS), a powerful, human-rated spacecraft that will propel explorers to cis-lunar space. In 2017, hardware will continue to be integrated at MAF for core stage structural test articles and the first two operational flights. RS-25 hotfire testing will continue to explore engine performance, as well as test flight-like software and four new Engine Controller Units (ECUs) for the first mission. Production of development components for a more affordable RS-25 design is underway. Core stage structural test articles have begun arriving at Marshall. While engineering challenges typical of a new development are possible, SLS is working toward launch readiness in late 2018. This paper will discuss these and other technical and programmatic successes and challenges over the past year and provide a preview of work ahead before first flight

Language Learning at Key Stage 2: Findings from a Longitudinal Study

ERIC Educational Resources Information Center

Cable, Carrie; Driscoll, Patricia; Mitchell, Rosamond; Sing, Sue; Cremin, Teresa; Earl, Justine; Eyres, Ian; Holmes, Bernardette; Martin, Cynthia; Heins, Barbara

2012-01-01

This paper discusses some of the findings from a 3-year longitudinal study of language learning in the upper stage of English primary schools, i.e. at Key Stage 2. This largely qualitative study (commissioned by the then Department for Children, Schools and Families) was designed to explore and document developing provision and practice in a…

Safety Practices Followed in ISRO Launch Complex- An Overview

NASA Astrophysics Data System (ADS)

Krishnamurty, V.; Srivastava, V. K.; Ramesh, M.

2005-12-01

The spaceport of India, Satish Dhawan Space Centre (SDSC) SHAR of Indian Space Research Organisation (ISRO), is located at Sriharikota, a spindle shaped island on the east coast of southern India.SDSC SHAR has a unique combination of facilities, such as a solid propellant production plant, a rocket motor static test facility, launch complexes for different types of rockets, telemetry, telecommand, tracking, data acquisition and processing facilities and other support services.The Solid Propellant Space Booster Plant (SPROB) located at SDSC SHAR produces composite solid propellant for rocket motors of ISRO. The main ingredients of the propellant produced here are ammonium perchlorate (oxidizer), fine aluminium powder (fuel) and hydroxyl terminated polybutadiene (binder).SDSC SHAR has facilities for testing solid rocket motors, both at ambient conditions and at simulated high altitude conditions. Other test facilities for the environmental testing of rocket motors and their subsystems include Vibration, Shock, Constant Acceleration and Thermal / Humidity.SDSC SHAR has the necessary infrastructure for launching satellites into low earth orbit, polar orbit and geo-stationary transfer orbit. The launch complexes provide complete support for vehicle assembly, fuelling with both earth storable and cryogenic propellants, checkout and launch operations. Apart from these, it has facilities for launching sounding rockets for studying the Earth's upper atmosphere and for controlled reentry and recovery of ISRO's space capsule reentry missions.Safety plays a major role at SDSC SHAR right from the mission / facility design phase to post launch operations. This paper presents briefly the infrastructure available at SDSC SHAR of ISRO for launching sounding rockets, satellite launch vehicles, controlled reentry missions and the built in safety systems. The range safety methodology followed as a part of the real time mission monitoring is presented. The built in safety systems provided onboard the launch vehicle are automatic shut off the propulsion system based on real time mission performance and a passivation system incorporated in the orbit insertion stage are highlighted.

Quality of Life and Survivorship Care in Patients Undergoing Hyperthermic Intraperitoneal Chemotherapy (HIPEC)

ClinicalTrials.gov

2017-05-25

Advanced Malignant Mesothelioma; Carcinoma of the Appendix; Ovarian Sarcoma; Ovarian Stromal Cancer; Pseudomyxoma Peritonei; Recurrent Colon Cancer; Recurrent Malignant Mesothelioma; Recurrent Ovarian Epithelial Cancer; Recurrent Ovarian Germ Cell Tumor; Stage III Colon Cancer; Stage III Ovarian Epithelial Cancer; Stage III Ovarian Germ Cell Tumor; Stage IV Colon Cancer; Stage IV Ovarian Epithelial Cancer; Stage IV Ovarian Germ Cell Tumor; Unspecified Childhood Solid Tumor, Protocol Specific

Rocket stage - Trans-orbit booster Fregat

NASA Astrophysics Data System (ADS)

Asyushkin, V. A.; Papkov, O. V.

1993-10-01

This paper discusses a proposal for increasing the payload-carrying capability of a launch vehicle by using the Fregat booster stage (as the fourth stage for the R-7A launcher and as the fifth stage for the Proton launch vehicle). Particular attention is given to the tasks which the Fregat booster stage is designed to fulfill, the systems which are part of the Fregat, and the launch vehicles which will use Fregat as the upper stage. The main performance parameters of the Fregat stage are presented, as well as diagrams illustrating the performance of the Fregat booster stage.

Upper Gastrointestinal Tract Motility Disorders in Women, Gastroparesis, and Gastroesophageal Reflux Disease.

PubMed

Zia, Jasmine K; Heitkemper, Margaret M

2016-06-01

This article reviews the sex differences in upper gastrointestinal (GI) motility for both healthy and common dysmotility conditions. It focuses on gastroesophageal reflux disease and other esophageal motor disorders for the esophagus and on gastroparesis and accelerated gastric emptying for the stomach. It also describes differences in upper GI motility signs and symptoms during each female hormonal stage (ie, menstrual cycle, pregnancy, perimenopause, menopause) for both healthy participants and those suffering from one of the aforementioned upper GI dysmotility conditions. More research still needs to be conducted to better understand sex differences in upper GI motility. Copyright © 2016 Elsevier Inc. All rights reserved.

Upper-Stage Flight Experiment

NASA Technical Reports Server (NTRS)

Anderson, W. E.; Boxwell, R.; Crockett, D. V.; Ross, R.; Lewis, T.; McNeal, C.; Verdarame, K.

1999-01-01

For propulsion applications that require that the propellants are storable for long periods, have a high density impulse, and are environmentally clean and non-toxic, the best choice is a combination of high-concentration hydrogen peroxide (High Test Peroxide, or HTP) and a liquid hydrocarbon (LHC) fuel. The HTP/LHC combination is suitable for low-cost launch vehicles, space taxi and space maneuvering vehicles, and kick stages. Orbital Sciences Corporation is under contract with the NASA Marshall Space Flight Center in cooperation with the Air Force Research Lab to design, develop and demonstrate a new low-cost liquid upper stage based on HTP and JP-8. The Upper Stage Flight Experiment (USFE) focuses on key technologies necessary to demonstrate the operation of an inherently simple propulsion system with an innovative, state-of-the-art structure. Two key low-cost vehicle elements will be demonstrated - a 10,000 lbf thrust engine and an integrated composite tank structure. The suborbital flight test of the USFE is scheduled for 2001. Preceding the flight tests are two major series of ground tests at NASA Stennis Space Center and a subscale tank development program to identify compatible composite materials and to verify their compatibility over long periods of time. The ground tests include a thrust chamber development test series and an integrated stage test. This paper summarizes the results from the first phase of the thrust chamber development tests and the results to date from the tank material compatibility tests. Engine and tank configurations that meet the goals of the program are described.

Evaluation of Composting for Reducing Volume of Solid Waste on Contingency Bases

DTIC Science & Technology

2012-05-23

Incineration Two Stage Burn Higher Burn Temperature Smaller Footprint No Sorting High Cost – Capital and Fuel Scaling and Capacity Issues...National Def nse Cent rgy and Environment Nitrogen Carbon Vapor/Gas (Void Space) Water Moisture Dry Solids Water Vapor Carbon Nitrogen Two other elements...and Environment Compost to Reduce SW on Contingency Bases, 23 May 2012, E2S2 7 National Def nse Cent rgy and Environment  The stage of the

Sorafenib in Treating Patients With Metastatic or Unresectable Solid Tumors, Multiple Myeloma, or Non-Hodgkin's Lymphoma With or Without Impaired Liver or Kidney Function

ClinicalTrials.gov

2013-01-04

Extranodal Marginal Zone B-cell Lymphoma of Mucosa-associated Lymphoid Tissue; Nodal Marginal Zone B-cell Lymphoma; Recurrent Adult Burkitt Lymphoma; Recurrent Adult Diffuse Large Cell Lymphoma; Recurrent Adult Diffuse Mixed Cell Lymphoma; Recurrent Adult Diffuse Small Cleaved Cell Lymphoma; Recurrent Adult Grade III Lymphomatoid Granulomatosis; Recurrent Adult Immunoblastic Large Cell Lymphoma; Recurrent Adult Lymphoblastic Lymphoma; Recurrent Grade 1 Follicular Lymphoma; Recurrent Grade 2 Follicular Lymphoma; Recurrent Grade 3 Follicular Lymphoma; Recurrent Mantle Cell Lymphoma; Recurrent Marginal Zone Lymphoma; Recurrent Small Lymphocytic Lymphoma; Refractory Multiple Myeloma; Splenic Marginal Zone Lymphoma; Stage II Multiple Myeloma; Stage III Adult Burkitt Lymphoma; Stage III Adult Diffuse Large Cell Lymphoma; Stage III Adult Diffuse Mixed Cell Lymphoma; Stage III Adult Diffuse Small Cleaved Cell Lymphoma; Stage III Adult Immunoblastic Large Cell Lymphoma; Stage III Adult Lymphoblastic Lymphoma; Stage III Grade 1 Follicular Lymphoma; Stage III Grade 2 Follicular Lymphoma; Stage III Grade 3 Follicular Lymphoma; Stage III Mantle Cell Lymphoma; Stage III Marginal Zone Lymphoma; Stage III Multiple Myeloma; Stage III Small Lymphocytic Lymphoma; Stage IV Adult Burkitt Lymphoma; Stage IV Adult Diffuse Large Cell Lymphoma; Stage IV Adult Diffuse Mixed Cell Lymphoma; Stage IV Adult Diffuse Small Cleaved Cell Lymphoma; Stage IV Adult Immunoblastic Large Cell Lymphoma; Stage IV Adult Lymphoblastic Lymphoma; Stage IV Grade 1 Follicular Lymphoma; Stage IV Grade 2 Follicular Lymphoma; Stage IV Grade 3 Follicular Lymphoma; Stage IV Mantle Cell Lymphoma; Stage IV Marginal Zone Lymphoma; Stage IV Small Lymphocytic Lymphoma; Unspecified Adult Solid Tumor, Protocol Specific; Waldenström Macroglobulinemia

Health disparities are important determinants of outcome for children with solid tumor malignancies

PubMed Central

Austin, Mary T.; Nguyen, Hoang; Eberth, Jan M.; Chang, Yuchia; Heczey, Andras; Hughes, Dennis P.; Lally, Kevin P.; Elting, Linda S.

2015-01-01

Purpose The purpose of this study was to identify health disparities in children with non-CNS solid tumor malignancies and examine their impact on disease presentation and outcome. Methods We examined the records of all children (age ≤ 18 years) diagnosed with a non-CNS solid tumor malignancy and enrolled in the Texas Cancer Registry between 1995 and 2009 (n = 4603). The primary outcome measures were disease stage and overall survival (OS). Covariates included gender, age, race/ethnicity, year of diagnosis, socioeconomic status (SES), and driving distance to the nearest pediatric cancer treatment facility. Statistical analyses included life table methods, logistic, and Cox regression. Statistical significance was defined as p < 0.05. Results Children with advanced-stage disease were more likely to be male, <10 years old, and Hispanic or non-Hispanic Blacks (all p < 0.05). Distance to treatment and SES did not impact stage of disease at presentation. However, Hispanic and non-Hispanic Blacks and patients in the lowest SES quartile had the worst 1- and 5-year survival (all p < 0.05). The adjusted OS differed by age, race, and stage, but not SES or distance to the nearest treatment facility. Conclusions Race/ethnicity plays an important role in survival for children with non-CNS solid tumor malignancies. Future work should better define these differences to establish mechanisms to decrease their impact. PMID:25598116

Crystallization process

DOEpatents

Adler, Robert J.; Brown, William R.; Auyang, Lun; Liu, Yin-Chang; Cook, W. Jeffrey

1986-01-01

An improved crystallization process is disclosed for separating a crystallizable material and an excluded material which is at least partially excluded from the solid phase of the crystallizable material obtained upon freezing a liquid phase of the materials. The solid phase is more dense than the liquid phase, and it is separated therefrom by relative movement with the formation of a packed bed of solid phase. The packed bed is continuously formed adjacent its lower end and passed from the liquid phase into a countercurrent flow of backwash liquid. The packed bed extends through the level of the backwash liquid to provide a drained bed of solid phase adjacent its upper end which is melted by a condensing vapor.

Investigation of two-stage air-cooled turbine suitable for flight at Mach number of 2.5 II : blade design

NASA Technical Reports Server (NTRS)

Miser, James W; Stewart, Warner L

1957-01-01

A blade design study is presented for a two-stage air-cooled turbine suitable for flight at a Mach number of 2.5 for which velocity diagrams have been previously obtained. The detailed procedure used in the design of the blades is given. In addition, the design blade shapes, surface velocity distributions, inner and outer wall contours, and other design data are presented. Of all the blade rows, the first-stage rotor has the highest solidity, with a value of 2.289 at the mean section. The second-stage stator also had a high mean-section solidity of 1.927, mainly because of its high inlet whirl. The second-stage rotor has the highest value of the suction-surface diffusion parameter, with a value of 0.151. All other blade rows have values for this parameter under 0.100.

Global distribution of particle phase state in atmospheric secondary organic aerosols

NASA Astrophysics Data System (ADS)

Shiraiwa, Manabu; Li, Ying; Tsimpidi, Alexandra P.; Karydis, Vlassis A.; Berkemeier, Thomas; Pandis, Spyros N.; Lelieveld, Jos; Koop, Thomas; Pöschl, Ulrich

2017-04-01

Secondary organic aerosols (SOA) are a large source of uncertainty in our current understanding of climate change and air pollution. The phase state of SOA is important for quantifying their effects on climate and air quality, but its global distribution is poorly characterized. We developed a method to estimate glass transition temperatures based on the molar mass and molecular O:C ratio of SOA components, and we used the global chemistry climate model EMAC with the organic aerosol module ORACLE to predict the phase state of atmospheric SOA. For the planetary boundary layer, global simulations indicate that SOA are mostly liquid in tropical and polar air with high relative humidity, semi-solid in the mid-latitudes and solid over dry lands. We find that in the middle and upper troposphere SOA should be mostly in a glassy solid phase state. Thus, slow diffusion of water, oxidants and organic molecules could kinetically limit gas-particle interactions of SOA in the free and upper troposphere, promote ice nucleation and facilitate long-range transport of reactive and toxic organic pollutants embedded in SOA.

Global distribution of particle phase state in atmospheric secondary organic aerosols.

PubMed

Shiraiwa, Manabu; Li, Ying; Tsimpidi, Alexandra P; Karydis, Vlassis A; Berkemeier, Thomas; Pandis, Spyros N; Lelieveld, Jos; Koop, Thomas; Pöschl, Ulrich

2017-04-21

Secondary organic aerosols (SOA) are a large source of uncertainty in our current understanding of climate change and air pollution. The phase state of SOA is important for quantifying their effects on climate and air quality, but its global distribution is poorly characterized. We developed a method to estimate glass transition temperatures based on the molar mass and molecular O:C ratio of SOA components, and we used the global chemistry climate model EMAC with the organic aerosol module ORACLE to predict the phase state of atmospheric SOA. For the planetary boundary layer, global simulations indicate that SOA are mostly liquid in tropical and polar air with high relative humidity, semi-solid in the mid-latitudes and solid over dry lands. We find that in the middle and upper troposphere SOA should be mostly in a glassy solid phase state. Thus, slow diffusion of water, oxidants and organic molecules could kinetically limit gas-particle interactions of SOA in the free and upper troposphere, promote ice nucleation and facilitate long-range transport of reactive and toxic organic pollutants embedded in SOA.

Global distribution of particle phase state in atmospheric secondary organic aerosols

PubMed Central

Shiraiwa, Manabu; Li, Ying; Tsimpidi, Alexandra P.; Karydis, Vlassis A.; Berkemeier, Thomas; Pandis, Spyros N.; Lelieveld, Jos; Koop, Thomas; Pöschl, Ulrich

2017-01-01

Secondary organic aerosols (SOA) are a large source of uncertainty in our current understanding of climate change and air pollution. The phase state of SOA is important for quantifying their effects on climate and air quality, but its global distribution is poorly characterized. We developed a method to estimate glass transition temperatures based on the molar mass and molecular O:C ratio of SOA components, and we used the global chemistry climate model EMAC with the organic aerosol module ORACLE to predict the phase state of atmospheric SOA. For the planetary boundary layer, global simulations indicate that SOA are mostly liquid in tropical and polar air with high relative humidity, semi-solid in the mid-latitudes and solid over dry lands. We find that in the middle and upper troposphere SOA should be mostly in a glassy solid phase state. Thus, slow diffusion of water, oxidants and organic molecules could kinetically limit gas–particle interactions of SOA in the free and upper troposphere, promote ice nucleation and facilitate long-range transport of reactive and toxic organic pollutants embedded in SOA. PMID:28429776

Shuttle/IUS performance for planetary missions. [Interim Upper Stage

NASA Technical Reports Server (NTRS)

Cork, M. J.; Driver, J. M.; Wright, J. L.

1975-01-01

Potential requirements for planetary missions in the 1980s, capabilities of the Interim Upper Stage (IUS) candidates to perform those missions, and Shuttle/IUS mission profile options for performance enhancement are examined. The most demanding planetary missions are the Pioneer Saturn/Uranus/Titan Probe and the Mariner-class orbiters of Mercury, Jupiter, and Saturn. Options available to designers of these missions will depend on the specific IUS selected for development and the programmatic phasing of the IUS and the NASA Tug. Use of Shuttle elliptic orbits as initial conditions for IUS ignition offers significant performance improvements; specific values are mission dependent.

Effects of leaf age within growth stages of pepper and sorghum plants on leaf thickness, water, chlorophyll, and light reflectance. [in spectral vegetation discrimination

NASA Technical Reports Server (NTRS)

Gausman, H. W.; Cardenas, R.; Berumen, A.

1974-01-01

Pepper and sorghum plants (characterized by porous and compact leaf mesophylls, respectively) were used to study the influence of leaf age on light reflectance. Measurements were limited to the upper five nodal positions within each growth stage, since upper leaves make up most of the reflectance surfaces remotely sensed. The increase in leaf thickness and water content with increasing leaf age was taken into consideration, since each of these factors affects the reflectance as well as the selection of spectral wavelength intervals for optimum discrimination of vegetation.

Technicians listen to instructions during STS-44 DSP / IUS transfer operation

NASA Technical Reports Server (NTRS)

1991-01-01

Clean-suited technicians, wearing headsets, listen to instructions during Defense Support Program (DSP) satellite / inertial upper stage (IUS) transfer operations in a processing facility at Cape Canaveral Air Force Station. In the background, the DSP satellite atop an inertial upper stage (IUS) is readied for transfer to a payload canister transporter. DSP, a surveillance satellite that can detect missle and space launches as well as nuclear detonations will be boosted into geosynchronous Earth orbit by the IUS during STS-44 mission. View provided by the Kennedy Space Center (KSC) with alternate number KSC-91PC-1748.

Design and Analysis of a Turbopump for a Conceptual Expander Cycle Upper-Stage Engine

NASA Technical Reports Server (NTRS)

Dorney, Daniel J.; Rothermel, Jeffry; Griffin, Lisa W.; Thornton, Randall J.; Forbes, John C.; Skelly, Stephen E.; Huber, Frank W.

2006-01-01

As part of the development of technologies for rocket engines that will power spacecraft to the Moon and Mars, a program was initiated to develop a conceptual upper stage engine with wide flow range capability. The resulting expander cycle engine design employs a radial turbine to allow higher pump speeds and efficiencies. In this paper, the design and analysis of the pump section of the engine are discussed. One-dimensional meanline analyses and three-dimensional unsteady computational fluid dynamics simulations were performed for the pump stage. Configurations with both vaneless and vaned diffusers were investigated. Both the meanline analysis and computational predictions show that the pump will meet the performance objectives. Additional details describing the development of a water flow facility test are also presented.

KSC-2009-1772

NASA Image and Video Library

2009-02-21

CAPE CANAVERAL, Fla. – In the Assembly and Refurbishment Facility, or ARF, at NASA's Kennedy Space Center, an overhead crane lowers the frustum for the Ares I-X test rocket onto supports on the floor. The frustum is the last manufactured section of the Ares I-X. Resembling a giant funnel, the frustum's function is to transition the primary flight loads from the rocket's upper stage to the first stage. The frustum is located between the forward skirt extension and the upper stage of the Ares I-X. The frustum will be integrated with the forward skirt and forward skirt extension, which already are in the ARF. That will complete the forward assembly. The assembly then will be moved to the Vehicle Assembly Building for stacking operations, which are scheduled to begin in April. Photo credit: NASA/Kim Shiflett

KSC-2009-1771

NASA Image and Video Library

2009-02-21

CAPE CANAVERAL, Fla. – In the Assembly and Refurbishment Facility, or ARF, at NASA's Kennedy Space Center, an overhead crane lowers the frustum for the Ares I-X test rocket onto supports on the floor. The frustum is the last manufactured section of the Ares I-X. Resembling a giant funnel, the frustum's function is to transition the primary flight loads from the rocket's upper stage to the first stage. The frustum is located between the forward skirt extension and the upper stage of the Ares I-X. The frustum will be integrated with the forward skirt and forward skirt extension, which already are in the ARF. That will complete the forward assembly. The assembly then will be moved to the Vehicle Assembly Building for stacking operations, which are scheduled to begin in April. Photo credit: NASA/Kim Shiflett

TDRS-M: Atlas V 2nd Stage Erection/Off-site Verticle Integration (OVI)

NASA Image and Video Library

2017-07-13

A United Launch Alliance Atlas V Centaur upper stage arrives at the Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. United Launch Alliance team members monitor the operation progress as the Centaur upper stage is lifted and mated to the Atlas V booster in the vertical position. The rocket is scheduled to help launch the Tracking and Data Relay Satellite, TDRS-M. It will be the latest spacecraft destined for the agency's constellation of communications satellites that allows nearly continuous contact with orbiting spacecraft ranging from the International Space Station and Hubble Space Telescope to the array of scientific observatories. Liftoff atop the ULA Atlas V rocket is scheduled to take place from Cape Canaveral's Space Launch Complex 41 in early August.

On-line Toxicity Monitors and Their Use in an Upper Mississippi Watershed Water Quality Monitoring Network

EPA Science Inventory

A collaborative effort to monitor the upper Mississippi River watershed using On-line Toxicity Monitors (OTMs) is underway with three sites currently deployed and several more at various stages of development. Federal, State, and Local, agencies as well as utilities and Universi...

Sirolimus and Gold Sodium Thiomalate in Treating Patients With Advanced Squamous Non-Small Cell Lung Cancer

ClinicalTrials.gov

2012-12-13

Recurrent Non-small Cell Lung Cancer; Squamous Cell Lung Cancer; Stage IIIA Non-small Cell Lung Cancer; Stage IIIB Non-small Cell Lung Cancer; Stage IV Non-small Cell Lung Cancer; Unspecified Adult Solid Tumor, Protocol Specific

Recombinant EphB4-HSA Fusion Protein With Standard Chemotherapy Regimens in Treating Patients With Advanced or Metastatic Solid Tumors

ClinicalTrials.gov

2017-07-15

Head and Neck Squamous Cell Carcinoma; Metastatic Pancreatic Adenocarcinoma; Non-Resectable Cholangiocarcinoma; Pancreatic Adenocarcinoma; Recurrent Gallbladder Carcinoma; Recurrent Non-Small Cell Lung Carcinoma; Stage III Pancreatic Cancer; Stage IIIA Gallbladder Cancer; Stage IIIA Non-Small Cell Lung Cancer; Stage IIIB Gallbladder Cancer; Stage IIIB Non-Small Cell Lung Cancer; Stage IV Gallbladder Cancer; Stage IV Non-Small Cell Lung Cancer; Stage IV Pancreatic Cancer; Unresectable Gallbladder Carcinoma; Unresectable Pancreatic Cancer

Low energy stage study. Volume 3: Conceptual design, interface analysis, flight and ground operations. [launching space shuttle payloads

NASA Technical Reports Server (NTRS)

1978-01-01

Low energy conceptual stage designs and adaptations to existing/planned shuttle upper stages were developed and their performance established. Selected propulsion modes and subsystems were used as a basis to develop airborne support equipment (ASE) design concepts. Orbiter installation and integration (both physical and electrical interfaces) were defined. Low energy stages were adapted to the orbiter and ASE interfaces. Selected low energy stages were then used to define and describe typical ground and flight operations.

Health disparities and impact on outcomes in children with primary central nervous system solid tumors.

PubMed

Austin, Mary T; Hamilton, Emma; Zebda, Denna; Nguyen, Hoang; Eberth, Jan M; Chang, Yuchia; Elting, Linda S; Sandberg, David I

2016-11-01

OBJECTIVE Health disparities in access to care, early detection, and survival exist among adult patients with cancer. However, there have been few reports assessing how health disparities impact pediatric patients with malignancies. The objective in this study was to examine the impact of racial/ethnic and social factors on disease presentation and outcome for children with primary CNS solid tumors. METHODS The authors examined all children (age ≤ 18 years) in whom CNS solid tumors were diagnosed and who were enrolled in the Texas Cancer Registry between 1995 and 2009 (n = 2421). Geocoded information was used to calculate the driving distance between a patient's home and the nearest pediatric cancer treatment center. Socioeconomic status (SES) was determined using the Agency for Healthcare Research and Quality formula and 2007-2011 US Census block group data. Logistic regression was used to determine factors associated with advanced-stage disease. Survival probability and hazard ratios were calculated using life table methods and Cox regression. RESULTS Children with advanced-stage CNS solid tumors were more likely to be < 1 year old, Hispanic, and in the lowest SES quartile (all p < 0.05). The adjusted odds ratios of presenting with advanced-stage disease were higher in children < 1 year old compared with children > 10 years old (OR 1.71, 95% CI 1.06-2.75), and in Hispanic patients compared with non-Hispanic white patients (OR 1.56, 95% CI 1.19-2.04). Distance to treatment and SES did not impact disease stage at presentation in the adjusted analysis. Furthermore, 1- and 5-year survival probability were worst in children 1-10 years old, Hispanic patients, non-Hispanic black patients, and those in the lowest SES quartile (p < 0.05). In the adjusted survival model, only advanced disease and malignant behavior were predictive of mortality. CONCLUSIONS Racial/ethnic disparities are associated with advanced-stage disease presentation for children with CNS solid tumors. Disease stage at presentation and tumor behavior are the most important predictors of survival.

Urothelial carcinoma of the bladder and the upper tract: disparate twins.

PubMed

Green, David A; Rink, Michael; Xylinas, Evanguelos; Matin, Surena F; Stenzl, Arnulf; Roupret, Morgan; Karakiewicz, Pierre I; Scherr, Douglas S; Shariat, Shahrokh F

2013-04-01

Urothelial carcinoma of the bladder is the 4th most common malignancy in men and the 8th most common cause of male cancer death in the United States. Conversely, upper tract urothelial carcinoma accounts for only 5% to 10% of all urothelial carcinoma. Due to the relative preponderance of urothelial carcinoma of the bladder, much of the clinical decision making regarding upper tract urothelial carcinoma is extrapolated from evidence that is based on urothelial carcinoma of the bladder cohorts. In fact, only 1 major urological organization has treatment guidelines specific for upper tract urothelial carcinoma. While significant similarities exist between these 2 diseases, ignoring the important differences may be preventing us from optimizing therapy in patients with upper tract urothelial carcinoma. Therefore, we explored these dissimilarities, including the differential importance of gender, anatomy, staging, intracavitary therapy, surgical lymphadenectomy and perioperative systemic chemotherapy on the behavior of urothelial carcinoma of the bladder and upper tract urothelial carcinoma. A nonsystematic literature search using the MEDLINE/PubMed® database was conducted to identify original articles, review articles and editorials. Searches were limited to the English language and studies in humans and in adults, and used the key words urothelial carcinoma, upper tract urothelial carcinoma or transitional cell carcinoma combined with several different sets of key words to identify appropriate publications for each section of the manuscript. The key words, broken down by section, were 1) epidemiology, sex, gender; 2) location, tumor location; 3) staging, stage; 4) intracavitary, intravesical, topical therapy; 5) lymphadenectomy, lymph node, lymph node dissection and 6) adjuvant, neoadjuvant, chemotherapy. Women who present with urothelial carcinoma of the bladder do so with less favorable tumor characteristics and have worse survival than men. However, gender does not appear to be associated with survival outcomes in upper tract urothelial carcinoma. The prognostic effect that urothelial carcinoma tumor location has on outcomes prediction is a matter of debate, and the influence of tumor location may reflect our technical ability to accurately stage and treat the disease more than the actual tumor biology. Moreover, technical limitations of upper tract urothelial carcinoma sampling compared to transurethral resection for urothelial carcinoma of the bladder are the most important source of staging differences between the 2 diseases. Intravesical chemotherapy and immunotherapy are essential components of standard of care for most nonmuscle invasive bladder cancer, while adjuvant intracavitary therapy for patients with upper tract urothelial carcinoma treated endoscopically or percutaneously has been sparsely used and without any clear guidelines. The widespread adoption of the use of intracavitary therapy in the upper tract will likely not only require additional data to support its efficacy, but will also require a less cumbersome means of administration. Lymphadenectomy at the time of radical cystectomy is widely accepted while lymphadenectomy at the time of radical nephroureterectomy is performed largely at the discretion of the surgeon. Among other reasons, this may be due in part to the variable lymphatic drainage along the course of the ureter compared to the relatively confined lymphatic landing sites for the bladder. Level I evidence has demonstrated a clear survival benefit for systemic chemotherapy before radical surgery or radiation in patients with clinical T2-4N0M0 urothelial carcinoma of the bladder. Such data are not available in the population with upper tract urothelial carcinoma. However, the use of neoadjuvant chemotherapy may be even more important in upper tract urothelial carcinoma than in urothelial carcinoma of the bladder because of the obligatory kidney function loss that occurs at radical nephroureterectomy. While urothelial carcinoma of the bladder and upper tract urothelial carcinoma share many characteristics, they represent 2 distinct diseases. There are practical, anatomical, biological and molecular differences that warrant consideration when risk stratifying and treating patients with these disparate twin diseases. To overcome the challenges that impede progress toward evidence-based medicine in upper tract urothelial carcinoma, we believe that focused collaborative efforts will best augment our understanding of this rare disease and ultimately improve the care we deliver to our patients. Copyright © 2013 American Urological Association Education and Research, Inc. Published by Elsevier Inc. All rights reserved.

Efficacy of pectin solution for preventing gastro-esophageal reflux events in patients with percutaneous endoscopic gastrostomy.

PubMed

Adachi, Kyoichi; Furuta, Kenji; Aimi, Masahito; Fukazawa, Kousuke; Shimura, Shino; Ohara, Shunji; Nakata, Shuji; Inoue, Yukiko; Ryuko, Kanji; Ishine, Junichi; Katoh, Kyoko; Hirata, Toshiaki; Ohhata, Shuzo; Katoh, Setsushi; Moriyama, Mika; Sumikawa, Masuko; Sanpei, Mari; Kinoshita, Yoshikazu

2012-05-01

The aim of this study was to determine the efficacy of pectin solution, which increases the viscosity of liquid nutrient, for prevention of gastro-esophageal reflux in comparison with half-solid nutrient. The subjects were 10 elderly patients undergoing percutaneous endoscopic gastrostomy feeding. Twenty-four-hour esophageal multichannel intraluminal impedance and pH testing was performed during intake of half-solid nutrient and a combination of pectin solution and liquid nutrient. During 4 h after delivery, there was no significant difference in the total number of gastro-esophageal reflux events between the feeding of the half-solid nutrient and the combination of pectin solution and liquid nutrient (5.7 ± 1.2 vs 5.3 ± 1.0/4 h). Acidic reflux after delivery of the half-solid nutrient was significantly more frequent than that after delivery of the combination of pectin solution and liquid nutrient (80.7% vs 60.4%, p = 0.018). The incidence of gastro-esophageal reflux reaching the upper portion of the esophagus tended to be higher during delivery of the half-solid nutrient than during delivery of the combination of pectin solution and liquid nutrient (47.4% vs 34.0%, p = 0.153). In conclusion, the usage of pectin solution combined with liquid nutrient is effective for preventing acidic gastro-esophageal reflux and gastro-esophageal reflux reaching the upper portion of the esophagus.

Anaerobic digestion of municipal solid waste: Technical developments

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

Rivard, C.J.

1996-01-01

The anaerobic biogasification of organic wastes generates two useful products: a medium-Btu fuel gas and a compost-quality organic residue. Although commercial-scale digestion systems are used to treat municipal sewage wastes, the disposal of solid organic wastes, including municipal solid wastes (MSW), requires a more cost-efficient process. Modern biogasification systems employ high-rate, high-solids fermentation methods to improve process efficiency and reduce capital costs. The design criteria and development stages are discussed. These systems are also compared with conventional low-solids fermentation technology.

Growth behavior of surface cracks in the circumferential plane of solid and hollow cylinders

NASA Technical Reports Server (NTRS)

Forman, R. G.; Shivakumar, V.

1986-01-01

Experiments were conducted to study the growth behavior of surface fatigue cracks in the circumferential plane of solid and hollow cylinders. In the solid cylinders, the fatigue cracks were found to have a circular arc crack front with specific upper and lower limits to the arc radius. In the hollow cylinders, the fatigue cracks were found to agree accurately with the shape of a transformed semiellipse. A modification to the usual nondimensionalization expression used for surface flaws in flat plates was found to give correct trends for the hollow cylinder problem.

Impact of smoking on the age at diagnosis of upper tract urothelial carcinoma: Subanalysis of the Japanese Urological Association multi-institutional national database.

PubMed

Miyazaki, Jun; Nishiyama, Hiroyuki; Fujimoto, Hiroyuki; Ohyama, Chikara; Koie, Takuya; Hinotsu, Shiro; Kikuchi, Eiji; Sakura, Mizuaki; Inokuchi, Junichi; Hara, Tomohiko

2015-11-01

To examine the influence of smoking history on the diagnosis and other tumor characteristics of upper tract urothelial carcinoma in Japan. A total of 1509 patients with upper tract urothelial carcinoma who were diagnosed in 2005 from 348 Japanese institutions were registered using the multi-institutional national database of the Japanese Urological Association and included in this analysis. Clinical data of the patients were collected in 2011. The associations between the patients' self-reported smoking history and their age at the diagnosis of upper tract urothelial carcinoma, sex, pathological T stage and tumor grade were analyzed. The mean age at the diagnosis of upper tract urothelial carcinoma was approximately 5 years earlier for the 238 current smokers than for the 618 current non-smokers (P < 0.0001). Similar associations between smoking and the early diagnosis of upper tract urothelial carcinoma were shown in the sex subgroups and in subgroups stratified by pathological T stages. Among the current smokers, the age at diagnosis for the smoking ≥ 20 cigarettes per day group was 6.5 years lower than that of the < 20 cigarettes per day group, which was significantly different (P < 0.0001). Current smoking is a significant risk factor for the earlier diagnosis of upper tract urothelial carcinoma. The finding is important from the perspective of both healthcare and medical economies. © 2015 The Japanese Urological Association.

Primed Physical Therapy Enhances Recovery of Upper Limb Function in Chronic Stroke Patients.

PubMed

Ackerley, Suzanne J; Byblow, Winston D; Barber, P Alan; MacDonald, Hayley; McIntyre-Robinson, Andrew; Stinear, Cathy M

2016-05-01

Recovery of upper limb function is important for regaining independence after stroke. To test the effects of priming upper limb physical therapy with intermittent theta burst stimulation (iTBS), a form of noninvasive brain stimulation. Eighteen adults with first-ever chronic monohemispheric subcortical stroke participated in this randomized, controlled, triple-blinded trial. Intervention consisted of priming with real or sham iTBS to the ipsilesional primary motor cortex immediately before 45 minutes of upper limb physical therapy, daily for 10 days. Changes in upper limb function (Action Research Arm Test [ARAT]), upper limb impairment (Fugl-Meyer Scale), and corticomotor excitability, were assessed before, during, and immediately, 1 month and 3 months after the intervention. Functional magnetic resonance images were acquired before and at one month after the intervention. Improvements in ARAT were observed after the intervention period when therapy was primed with real iTBS, but not sham, and were maintained at 1 month. These improvements were not apparent halfway through the intervention, indicating a dose effect. Improvements in ARAT at 1 month were related to balancing of corticomotor excitability and an increase in ipsilesional premotor cortex activation during paretic hand grip. Two weeks of iTBS-primed therapy improves upper limb function at the chronic stage of stroke, for at least 1 month postintervention, whereas therapy alone may not be sufficient to alter function. This indicates a potential role for iTBS as an adjuvant to therapy delivered at the chronic stage. © The Author(s) 2015.

Crew Launch Vehicle (CLV) Avionics and Software Integration Overview

NASA Technical Reports Server (NTRS)

Monell, Donald W.; Flynn, Kevin C.; Maroney, Johnny

2006-01-01

On January 14, 2004, the President of the United States announced a new plan to explore space and extend a human presence across our solar system. The National Aeronautics and Space Administration (NASA) established the Exploration Systems Mission Directorate (ESMD) to develop and field a Constellation Architecture that will bring the Space Exploration vision to fruition. The Constellation Architecture includes a human-rated Crew Launch Vehicle (CLV) segment, managed by the Marshall Space Flight Center (MSFC), comprised of the First Stage (FS), Upper Stage (US), and Upper Stage Engine (USE) elements. The CLV s purpose is to provide safe and reliable crew and cargo transportation into Low Earth Orbit (LEO), as well as insertion into trans-lunar trajectories. The architecture's Spacecraft segment includes, among other elements, the Crew Exploration Vehicle (CEV), managed by the Johnson Space Flight Center (JSC), which is launched atop the CLV. MSFC is also responsible for CLV and CEV stack integration. This paper provides an overview of the Avionics and Software integration approach (which includes the Integrated System Health Management (ISHM) functions), both within the CLV, and across the CEV interface; it addresses the requirements to be met, logistics of meeting those requirements, and the roles of the various groups. The Avionics Integration and Vehicle Systems Test (ANST) Office was established at the MSFC with system engineering responsibilities for defining and developing the integrated CLV Avionics and Software system. The AIVST Office has defined two Groups, the Avionics and Software Integration Group (AVSIG), and the Integrated System Simulation and Test Integration Group (ISSTIG), and four Panels which will direct trade studies and analyses to ensure the CLV avionics and software meet CLV system and CEV interface requirements. The four panels are: 1) Avionics Integration Panel (AIP), 2) Software Integration Panel, 3) EEE Panel, and 4) Systems Simulation and Test Panel. Membership on the groups and panels includes the MSFC representatives from the requisite engineering disciplines, the First Stage, the Upper Stage, the Upper Stage Engine projects, and key personnel from other NASA centers. The four panels will take the results of trade studies and analyses and develop documentation in support of Design Analysis Cycle Reviews and ultimately the System Requirements Review.

Thermal habitat restricts patterns of occurrence in multiple life-stages of a headwater fish

Treesearch

Mischa P. Turschwell; Stephen R. Balcombe; E. Ashley Steel; Fran Sheldon; Erin E. Peterson

2017-01-01

Our lack of knowledge on the spatiotemporal drivers of the distribution of many freshwater fishes, particularly as they differ among life-history stages, is a challenge to conservation of these species. We used 2-stage hurdle models to investigate drivers of occurrence and abundance of locally threatened adult and juvenile Northern River Blackfish in the upper...

[Study on the histological anatomy on medicinal parts of Semiaquilegia adoxoides in different developmental stages].

PubMed

Yang, Jun; Peng, Hua-Sheng; Wang, De-Qun; Sun, Jing

2012-08-01

To study the structural characteristics of medicinal parts at different developmental stages of Semiaquilegia adoxoides. Observed on sections of medicinal parts of Semiaquilegia adoxoides at various developmental stages during growth periods. There was a great difference between the upper and bottom of the medicinal parts of Semiaquilegia adoxoides: rhizome at the top of root had the structure of rhizome with pith; The upper one third of enlarged root was root-stem transition zone, also with pith; And the other two thirds of enlarged root had the structure of root without pith. The microscopic structures of the medicinal parts of Semiaquilegia adoxoides at various developmental stages presented great disparities, the structures regularly increased as the size of plant increased. It was the first time to find that there were structure of growth rings in xylem of the root and rhizome of Semiaquilegia adoxoides. The method of identification of characteristics and histology of medicinal parts of Semiaquilegia adoxoides at different developmental stages is established, and the results provide a basis for identification of Semiaquilegia adoxoides medicinal materials.

Ares I and Ares I-X Stage Separation Aerodynamic Testing

NASA Technical Reports Server (NTRS)

Pinier, Jeremy T.; Niskey, Charles J.

2011-01-01

The aerodynamics of the Ares I crew launch vehicle (CLV) and Ares I-X flight test vehicle (FTV) during stage separation was characterized by testing 1%-scale models at the Arnold Engineering Development Center s (AEDC) von Karman Gas Dynamics Facility (VKF) Tunnel A at Mach numbers of 4.5 and 5.5. To fill a large matrix of data points in an efficient manner, an injection system supported the upper stage and a captive trajectory system (CTS) was utilized as a support system for the first stage located downstream of the upper stage. In an overall extremely successful test, this complex experimental setup associated with advanced postprocessing of the wind tunnel data has enabled the construction of a multi-dimensional aerodynamic database for the analysis and simulation of the critical phase of stage separation at high supersonic Mach numbers. Additionally, an extensive set of data from repeated wind tunnel runs was gathered purposefully to ensure that the experimental uncertainty would be accurately quantified in this type of flow where few historical data is available for comparison on this type of vehicle and where Reynolds-averaged Navier-Stokes (RANS) computational simulations remain far from being a reliable source of static aerodynamic data.

Two-stage, acetic acid-aqueous ammonia, fractionation of empty fruit bunches for increased lignocellulosic biomass utilization.

PubMed

Kim, Dong Young; Kim, Young Soo; Kim, Tae Hyun; Oh, Kyeong Keun

2016-01-01

Fractionation of EFB was conducted in two consecutive steps using a batch reaction system: hemicellulose hydrolysis using acetic acid (AA; 3.0-7.0 wt.%) at 170-190°C for 10-20 min in the first stage, and lignin solubilization using ammonium hydroxide (5-20 wt.%) at 140-220°C for 5-25 min in the second stage. The two-stage process effectively fractionated empty fruit bunches (EFB) in terms of hemicellulose hydrolysis (53.6%) and lignin removal (59.5%). After the two-stage treatment, the fractionated solid contained 65.3% glucan. Among three investigated process parameters, reaction temperature and ammonia concentration had greater impact on the delignification reaction in the second stage than reaction time. The two-stage fractionation processing improved the enzymatic digestibility to 72.9% with 15 FPU of cellulase/g of glucan supplemented with 70 pNPG of β-glycosidase (Novozyme 188)/g-glucan, which was significantly enhanced from the equivalent digestibility of 28.3% for untreated EFB and 45.7% for AAH-fractionated solid. Copyright © 2015 Elsevier Ltd. All rights reserved.

The creative brain in the figural domain: Distinct patterns of EEG alpha power during idea generation and idea elaboration.

PubMed

Rominger, Christian; Papousek, Ilona; Perchtold, Corinna M; Weber, Bernhard; Weiss, Elisabeth M; Fink, Andreas

2018-02-13

This study investigated EEG activity in the upper alpha band during the well-known Picture Completion Task of the Torrance Test of Creative Thinking (TTCT), a widely used creative ideation task in the figural domain. The application of a sophisticated computerized version of the TTCT facilitating the online assessment and digitalizing of participant's drawings allowed to separate two central stages of the creative ideation process (i.e., idea generation and idea elaboration). During idea generation, the participants' task was to generate an initial draft of an original and creative completion of the presented abstract lines and figures of the TTCT. During idea elaboration, the participants were required to mentally improve the originality of the initially generated idea/draft. Creative ideation in this figural task was generally associated with comparatively strong desynchronization of upper alpha power over parietal and occipital sites, indicating high visual/figural processing demands. Interestingly, the stage of idea elaboration was accompanied by a relative increase of upper alpha power at parietal and occipital sites compared to the stage of idea generation, indicating heightened top-down processing demands. Furthermore, task performance was associated with relative increases of upper alpha power at frontal sites and relative decreases at centro-temporal sites from the stage of idea generation to idea elaboration. This association suggests the importance of increased inhibitory control over stimulus-based bottom-up information and motor imagery in order to achieve more creative outputs. Taken together these findings add to the relevant literature in that they a) extend research on the relationship between EEG alpha activity and creativity to the figural domain, and b) support a multistage view of creative ideation, involving cognitive control and mental imagery as important components of creativity. Copyright © 2018 Elsevier Ltd. All rights reserved.

HESTIA Commodities Exchange Pallet and Sounding Rocket Test Stand

NASA Technical Reports Server (NTRS)

Chaparro, Javier

2013-01-01

During my Spring 2016 internship, my two major contributions were the design of the Commodities Exchange Pallet and the design of a test stand for a 100 pounds-thrust sounding rocket. The Commodities Exchange Pallet is a prototype developed for the Human Exploration Spacecraft Testbed for Integration and Advancement (HESTIA) program. Under the HESTIA initiative the Commodities Exchange Pallet was developed as a method for demonstrating multi-system integration thru the transportation of In-Situ Resource Utilization produced oxygen and water to a human habitat. Ultimately, this prototype's performance will allow for future evaluation of integration, which may lead to the development of a flight capable pallet for future deep-space exploration missions. For HESTIA, my main task was to design the Commodities Exchange Pallet system to be used for completing an integration demonstration. Under the guidance of my mentor, I designed, both, the structural frame and fluid delivery system for the commodities pallet. The fluid delivery system includes a liquid-oxygen to gaseous-oxygen system, a water delivery system, and a carbon-dioxide compressors system. The structural frame is designed to meet safety and transportation requirements, as well as the ability to interface with the ER division's Portable Utility Pallet. The commodities pallet structure also includes independent instrumentation oxygen/water panels for operation and system monitoring. My major accomplishments for the commodities exchange pallet were the completion of the fluid delivery systems and the structural frame designs. In addition, parts selection was completed in order to expedite construction of the prototype, scheduled to begin in May of 2016. Once the commodities pallet is assembled and tested it is expected to complete a fully integrated transfer demonstration with the ISRU unit and the Environmental Control and Life Support System test chamber in September of 2016. In addition to the development of the Commodities Exchange Pallet, I also assisted in preparation for testing the upper stage of a sounding rocket developed as a Center Innovation Fund project. The main objective of this project is to demonstrate the integration between a propulsion system and a solid oxide fuel cell (SOFC). The upper stage and SOFC are scheduled to complete an integrated test in August of 2016. As part of preparation for scheduled testing, I was responsible for designing the upper stage's test stand/support structure and main engine plume deflector to be used during hot-fire testing (fig. 3). The structural components of the test stand need to meet safety requirements for operation of the propulsion system, which consist of a 100 pounds-thrust main engine and two 15 pounds-thrust reaction control thrusters. My main accomplishment for this project was the completion of the design and the parts selection for construction of the structure, scheduled to begin late April of 2016.

Forestry as a possible solution to the environmental and energy difficulties facing semi-arid Africa. The case of Upper Volta

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

Weinstabel, P.E.; Zech, W.

1982-01-01

The total annual demand for wood in Upper Volta is about 4.2 million cubic m solid wood, 94% of the population depends on wood for energy (compared with 84% in the Sahel states as a whole), and more than 30% of income in urban areas is spent on acquiring wood. Any policy aimed at securing adequate food supplies for the population must therefore be accompanied by a programme for safeguarding energy supplies. Measures which should be included in an integrated energy programme are presented and details are given of Upper Volta's forestry programme. 21 references.

The Space Launch System -The Biggest, Most Capable Rocket Ever Built, for Entirely New Human Exploration Missions Beyond Earth's Orbit

NASA Technical Reports Server (NTRS)

Shivers, C. Herb

2012-01-01

NASA is developing the Space Launch System -- an advanced heavy-lift launch vehicle that will provide an entirely new capability for human exploration beyond Earth's orbit. The Space Launch System will provide a safe, affordable and sustainable means of reaching beyond our current limits and opening up new discoveries from the unique vantage point of space. The first developmental flight, or mission, is targeted for the end of 2017. The Space Launch System, or SLS, will be designed to carry the Orion Multi-Purpose Crew Vehicle, as well as important cargo, equipment and science experiments to Earth's orbit and destinations beyond. Additionally, the SLS will serve as a backup for commercial and international partner transportation services to the International Space Station. The SLS rocket will incorporate technological investments from the Space Shuttle Program and the Constellation Program in order to take advantage of proven hardware and cutting-edge tooling and manufacturing technology that will significantly reduce development and operations costs. The rocket will use a liquid hydrogen and liquid oxygen propulsion system, which will include the RS-25D/E from the Space Shuttle Program for the core stage and the J-2X engine for the upper stage. SLS will also use solid rocket boosters for the initial development flights, while follow-on boosters will be competed based on performance requirements and affordability considerations.

NASA Ares I Launch Vehicle Roll and Reaction Control Systems Lessons Learned

NASA Technical Reports Server (NTRS)

Butt, Adam; Popp, Chris G.; Jernigan, Frankie R.; Paseur, Lila F.; Pitts, Hank M.

2011-01-01

On April 15, 2010 President Barak Obama made the official announcement that the Constellation Program, which included the Ares I launch vehicle, would be canceled. NASA s Ares I launch vehicle was being designed to launch the Orion Crew Exploration Vehicle, returning humans to the moon, Mars, and beyond. It consisted of a First Stage (FS) five segment solid rocket booster and a liquid J-2X Upper Stage (US) engine. Roll control for the FS was planned to be handled by a dedicated Roll Control System (RoCS), located on the connecting interstage. Induced yaw or pitch moments experienced during FS ascent would have been handled by vectoring of the booster nozzle. After FS booster separation, the US Reaction Control System (ReCS) would have provided the US Element with three degrees of freedom control as needed. The lessons learned documented in this paper will be focused on the technical designs and producibility of both systems along with the partnership between NASA and Boeing, who was on contract to build the Ares I US Element, which included the FS RoCS and US ReCS. In regards to partnership, focus will be placed on integration along with technical work accomplished by Boeing with special emphasis on each task order. In summary, this paper attempts to capture key lessons learned that should be helpful in the development of future launch vehicle RCS designs.