Dynamic Mechanical Analysis (DMA) to Help Characterize Vespel SP-211 Polyimide Material for Use as a 750 F Valve Seal on the Ares I Upper Stage J-2X Engine

NASA Technical Reports Server (NTRS)

Wingard, Doug

2013-01-01

DuPont (TM) Vespel (R) SP-211 polyimide was selected as the top candidate seal material for use in the Oxidizer Turbine Bypass Valve (OTBV) on NASA's Ares I Upper Stage J-2X engine. In the OTBV, the seal material would get exposed to temperatures up to 750degF for approx 10 minutes at a time. Although the J-2X engine is not reusable, the valve material could be exposed to multiple temperature cycles up to 750 F during engine operation. The Constellation Program that included the Ares I rocket was eventually cancelled, but the J-2X engine was chosen for continued use for development of NASA's Space Launch System (SLS). The SLS is a heavy-lift launch vehicle that will have capability of taking astronauts and hardware to the Moon, Mars and asteroids. Dynamic mechanical analysis (DMA) was one of several test techniques used to characterize Vespel SP-211 to help prove its worthiness for use on the OTBV of the J-2X engine.

Dynamic Mechanical Analysis (DMA) to Help Characterize Vespel SP-211 Polyimide Material for Use as a 750 F Valve Seal on the Ares I Upper Stage J-2X Engine

NASA Technical Reports Server (NTRS)

Wingard, Doug

2013-01-01

DuPont(tm) Vespel(R) SP-211 polyimide was selected as the top candidate seal material for use in the Oxidizer Turbine Bypass Valve (OTBV) on NASA's Ares I Upper Stage J-2X engine. In the OTBV, the seal material would get exposed to temperatures up to 750degF for approx 10 minutes at a time. Although the J-2X engine is not reusable, the valve material could be exposed to multiple temperature cycles up to 750degF during engine operation. The Constellation Program that included the Ares I rocket was eventually cancelled, but the J-2X engine was chosen for continued use for development of NASA's Space Launch System (SLS). The SLS is a heavy-lift launch vehicle that will have capability of taking astronauts and hardware to the Moon, Mars and asteroids. Dynamic mechanical analysis (DMA) was one of several test techniques used to characterize Vespel SP-211 to help prove its worthiness for use on the OTBV of the J-2X engine.

Development of the J-2X Engine for the Ares I Crew Launch Vehicle and the Ares V Cargo Launch Vehicle: Building on the Apollo Program for Lunar Return Missions

NASA Technical Reports Server (NTRS)

Snoddy, Jim

2006-01-01

The United States (U.S.) Vision for Space Exploration directs NASA to develop two new launch vehicles for sending humans to the Moon, Mars, and beyond. In January 2006, NASA streamlined its hardware development approach for replacing the Space Shuttle after it is retired in 2010. Benefits of this approach include reduced programmatic and technical risks and the potential to return to the Moon by 2020, by developing the Ares I Crew Launch Vehicle (CLV) propulsion elements now, with full extensibility to future Ares V Cargo Launch Vehicle (CaLV) lunar systems. This decision was reached after the Exploration Launch Projects Office performed a variety of risk analyses, commonality assessments, and trade studies. The Constellation Program selected the Pratt & Whitney Rocketdyne J-2X engine to power the Ares I Upper Stage Element and the Ares V Earth Departure Stage. This paper narrates the evolution of that decision; describes the performance capabilities expected of the J-2X design, including potential commonality challenges and opportunities between the Ares I and Ares V launch vehicles; and provides a current status of J-2X design, development, and hardware testing activities. This paper also explains how the J-2X engine effort mitigates risk by building on the Apollo Program and other lessons lived to deliver a human-rated engine that is on an aggressive development schedule, with its first demonstration flight in 2012.

Powerful lineup

NASA Image and Video Library

2012-10-11

Two J-2X engines and a powerpack, developed for NASA by Pratt and Whitney Rocketdyne, sit side-by-side Oct. 11 at Stennis Space Center as work continues on the Space Launch System. Engine 10001 (far left) has been removed from the A-2 Test Stand after being hot-fire tested 21 times, for a total of 2,697 seconds. The engine is now undergoing a series of post-test inspections. A J-2X powerpack (center) has been removed from the A-1 Test Stand to receive additional instrumentation. So far, the powerpack been hot-fire tested 10 times, for a total of 4,162 seconds. Meanwhile, assembly on the second J-2X engine, known as Engine 10002 and located to the far right, has begun in earnest, with engine completion scheduled for this November. Engine 10002 is about 15 percent complete.

J-2X Turbopump Cavitation Diagnostics

NASA Technical Reports Server (NTRS)

Santi, I. Michael; Butas, John P.; Tyler, Thomas R., Jr.; Aguilar, Robert; Sowers, T. Shane

2010-01-01

The J-2X is the upper stage engine currently being designed by Pratt & Whitney Rocketdyne (PWR) for the Ares I Crew Launch Vehicle (CLV). Propellant supply requirements for the J-2X are defined by the Ares Upper Stage to J-2X Interface Control Document (ICD). Supply conditions outside ICD defined start or run boxes can induce turbopump cavitation leading to interruption of J-2X propellant flow during hot fire operation. In severe cases, cavitation can lead to uncontained engine failure with the potential to cause a vehicle catastrophic event. Turbopump and engine system performance models supported by system design information and test data are required to predict existence, severity, and consequences of a cavitation event. A cavitation model for each of the J-2X fuel and oxidizer turbopumps was developed using data from pump water flow test facilities at Pratt & Whitney Rocketdyne (PWR) and Marshall Space Flight Center (MSFC) together with data from Powerpack 1A testing at Stennis Space Center (SSC) and from heritage systems. These component models were implemented within the PWR J-2X Real Time Model (RTM) to provide a foundation for predicting system level effects following turbopump cavitation. The RTM serves as a general failure simulation platform supporting estimation of J-2X redline system effectiveness. A study to compare cavitation induced conditions with component level structural limit thresholds throughout the engine was performed using the RTM. Results provided insight into system level turbopump cavitation effects and redline system effectiveness in preventing structural limit violations. A need to better understand structural limits and redline system failure mitigation potential in the event of fuel side cavitation was indicated. This paper examines study results, efforts to mature J-2X turbopump cavitation models and structural limits, and issues with engine redline detection of cavitation and the use of vehicle-side abort triggers to augment the engine redline system.

Status on the Verification of Combustion Stability for the J-2X Engine Thrust Chamber Assembly

NASA Technical Reports Server (NTRS)

Casiano, Matthew; Hinerman, Tim; Kenny, R. Jeremy; Hulka, Jim; Barnett, Greg; Dodd, Fred; Martin, Tom

2013-01-01

Development is underway of the J -2X engine, a liquid oxygen/liquid hydrogen rocket engine for use on the Space Launch System. The Engine E10001 began hot fire testing in June 2011 and testing will continue with subsequent engines. The J -2X engine main combustion chamber contains both acoustic cavities and baffles. These stability aids are intended to dampen the acoustics in the main combustion chamber. Verification of the engine thrust chamber stability is determined primarily by examining experimental data using a dynamic stability rating technique; however, additional requirements were included to guard against any spontaneous instability or rough combustion. Startup and shutdown chug oscillations are also characterized for this engine. This paper details the stability requirements and verification including low and high frequency dynamics, a discussion on sensor selection and sensor port dynamics, and the process developed to assess combustion stability. A status on the stability results is also provided and discussed.

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.

Development of the J-2X Engine for the Ares I Crew Launch Vehicle and the Ares V Cargo Launch Vehicle: Building on the Apollo Program for Lunar Return Missions

NASA Technical Reports Server (NTRS)

Greene, WIlliam

2007-01-01

The United States (U.S.) Vision for Space Exploration has directed NASA to develop two new launch vehicles for sending humans to the Moon, Mars, and beyond. In January 2006, NASA streamlined its hardware development approach for replacing the Space Shuttle after it is retired in 2010. Benefits of this approach include reduced programmatic and technical risks and the potential to return to the Moon by 2020 by developing the Ares I Crew Launch Vehicle (CLV) propulsion elements now, with full extensibility to future Ares V Cargo Launch Vehicle (CaLV) lunar systems. The Constellation Program selected the Pratt & Whitney Rocketdyne J-2X engine to power the Ares I Upper Stage Element and the Ares V Earth Departure Stage (EDS). This decision was reached during the Exploration Systems Architecture Study and confirmed after the Exploration Launch Projects Office performed a variety of risk analyses, commonality assessments, and trade studies. This paper narrates the evolution of that decision; describes the performance capabilities expected of the J-2X design, including potential commonality challenges and opportunities between the Ares I and Ares V launch vehicles; and provides a current status of J-2X design, development, and hardware testing activities. This paper also explains how the J-2X engine effort mitigates risk by testing existing engine hardware and designs; building on the Apollo Program (1961 to 1975), the Space Shuttle Program (1972 to 2010); and consulting with Apollo era experts to derive other lessons learned to deliver a human-rated engine that is on an aggressive development schedule, with its first demonstration flight in 2012.

Development of the J-2X Engine for the Ares I Crew Launch Vehicle and the Ares V Cargo Launch Vehicle: Building on the Apollo Program for Lunar Return Missions

NASA Technical Reports Server (NTRS)

Greene, William D.; Snoddy, Jim

2007-01-01

The United States (U.S.) Vision for Space Exploration has directed NASA to develop two new launch vehicles for sending humans to the Moon, Mars, and beyond. In January 2006, NASA streamlined its hardware development approach for replacing the Space Shuttle after it is retired in 2010. Benefits of this approach include reduced programmatic and technical risks and the potential to return to the Moon by 2020, by developing the Ares I Crew Launch Vehicle (CLV) propulsion elements now, with full extensibility to future Ares V Cargo Launch Vehicle (CaLV) lunar systems. The Constellation Program selected the Pratt & Whitney Rocketdyne J-2X engine to power the Ares I Upper Stage Element and the Ares V Earth Departure Stage. This decision was reached during the Exploration Systems Architecture Study and confirmed after the Exploration Launch Projects Office performed a variety of risk analyses, commonality assessments, and trade studies. This paper narrates the evolution of that decision; describes the performance capabilities expected of the J-2X design, including potential commonality challenges and opportunities between the Ares I and Ares V launch vehicles; and provides a current status of J-2X design, development, and hardware testing activities. This paper also explains how the J-2X engine effort mitigates risk by testing existing engine hardware and designs; building on the Apollo Program (1961 to 1975), the Space Shuttle Program (1972 to 2010); and consulting with Apollo-era experts to derive other lessons lived to deliver a human-rated engine that is on an aggressive development schedule, with its first demonstration flight in 2012.

Testing to Transition the J-2X from Paper to Hardware

NASA Technical Reports Server (NTRS)

Byrd, Tom

2010-01-01

The J-2X Upper Stage Engine (USE) will be the first new human-rated upper stage engine since the Apollo program of the 1960s. It is designed to carry the Ares I and Ares V into orbit and send the Ares V to the Moon as part of NASA's Constellation Program. This paper will provide an overview of progress on the design, testing, and manufacturing of this new engine in 2009 and 2010. The J-2X embodies the program goals of basing the design on proven technology and experience and seeking commonality between the Ares vehicles as a way to minimize risk, shorten development times, and live within current budget constraints. It is based on the proven J-2 engine used on the Saturn IB and Saturn V launch vehicles. The prime contractor for the J-2X is Pratt & Whitney Rocketdyne (PWR), which is under a design, development, test, and engineering (DDT&E) contract covering the period from June 2006 through September 2014. For Ares I, the J-2X will provide engine start at approximately 190,000 feet, operate roughly 500 seconds, and shut down. For Ares V, the J-2X will start at roughly 190,000 feet to place the Earth departure stage (EDS) in orbit, shut down and loiter for up to five days, re-start on command and operate for roughly 300 seconds at its secondary power level to perform trans lunar injection (TLI), followed by final engine shutdown. The J-2X development effort focuses on four key areas: early risk mitigation, design risk mitigation, component and subassembly testing, and engine system testing. Following that plan, the J-2X successfully completed its critical design review (CDR) in 2008, and it has made significant progress in 2009 and 2010 in moving from the drawing board to the machine shop and test stand. Post-CDR manufacturing is well under way, including PWR in-house and vendor hardware. In addition, a wide range of component and sub-component tests have been completed, and more component tests are planned. Testing includes heritage powerpack, turbopump inducer water flow, turbine air flow, turbopump seal testing, main injector and gas generator, injector testing, augmented spark igniter testing, nozzle side loads cold flow testing, nozzle extension film cooling flow testing, control system testing with hardware in the loop, and nozzle extension emissivity coating tests. In parallel with hardware manufacturing, work is progressing on the new A-3 test stand to support full duration altitude testing. The Stennis A-2 test stand is scheduled to be turned over to the Constellation Program in September 2010 to be modified for J-2X testing also. As the structural steel was rising on the A-3 stand, work was under way in the nearby E complex on the chemical steam generator and subscale diffuser concepts to be used to evacuate the A-3 test cell and simulate altitude conditions.

System Engineering on the Use for Ares I,V - the Simpler, the Better

NASA Technical Reports Server (NTRS)

Kelly, William; Greene, William D.; Greasley, Paul; Ackerman, Peter C.

2008-01-01

The Ares I and Ares V Vehicles will utilize the J-2X rocket engine developed for NASA by the Pratt & Whitney Rocketdyne Company. The J-2X is an improved higher power version of the original J-2 engine used during the Apollo program. With higher power and updated requirements for safety and performance, the J-2X becomes a new engine using state-of-the-art design methodology, materials and manufacturing processes. The implementation of Systems Engineering (SE) principles enables the rapid J-2X development program to remain aligned with the ARES I and V vehicle programs, Meeting the aggressive development schedule is a challenge. Coordinating the best expertise thai NASA and PWR have to offer requires effectively utilizing resources at multiple sites. This presents formidable communication challenges. SE allows honest and open discussions of issues and problems. This simple idea is often overlooked in large and complex SE programs. Regular and effective meetings linking SE objectives to component designs are used to voice differences of opinions with customer and contractor in attendance so that the best mutual decisions can be made on the shortest possible schedule. Regular technical interchange meetings on secure program wide computer networks and CM processes are effective,in the "Controlled Change" process that exemplifies good SE. Good communication is a key effective SE implementation. The System of Systems approach is the vision of the Orion program which facilitates the establishment of dynamic SE processes at all levels including the engine. SE enables requirements evolution by facilitating organizational and process agility. Flow down and distribution of requirements is controlled by Allocation Reports which breakdown numerical design objectives (weight, reliability, etc.) into quanta goals for each component area. Linked databases of design and verification requirements helps eliminate redundancy and potential mistakes inherent m separated systems. Another tool, the Architecture Design Description, is being used to control J-2X system architecture and effectively communicate configuration changes to those involved in the design process. But the proof is in successful program accomplishment. The SE is the methodology being used to meet the challenge of completing J-2X engine certification 2 years ahead of any engine program ever developed at PWR. The Ares I SE system of systems has delivered according to expectations thus far. All major design reviews (SRR. PDR, CDR) have been successfully conducted to satisfy overall program objectives using SE as the basis for accomplishment. The paper describes SE tools and techniques utilized to achieve this success.

Design, Activation, and Operation of the J2-X Subscale Simulator (JSS)

NASA Technical Reports Server (NTRS)

Saunders, Grady P.; Raines, Nickey G.; Varner, Darrel G.

2009-01-01

The purpose of this paper is to give a detailed description of the design, activation, and operation of the J2-X Subscale Simulator (JSS) installed in Cell 1 of the E3 test facility at Stennis Space Center, MS (SSC). The primary purpose of the JSS is to simulate the installation of the J2-X engine in the A3 Subscale Rocket Altitude Test Facility at SSC. The JSS is designed to give aerodynamically and thermodynamically similar plume properties as the J2-X engine currently under development for use as the upper stage engine on the ARES I and ARES V spacecraft. The JSS is a scale pressure fed, LOX/GH fueled rocket that is geometrically similar to the J2-X from the throat to the nozzle exit plane (NEP) and is operated at the same oxidizer to fuel ratios and chamber pressures. This paper describes the heritage hardware used as the basis of the JSS design, the newly designed rocket hardware, igniter systems used, and the activation and operation of the JSS.

J-2X Gas Generator Development Testing at NASA Marshall Space Flight Center

NASA Technical Reports Server (NTRS)

Reynolds, D. C.; Hormonzian, Carlo

2010-01-01

NASA is developing a liquid oxygen/liquid hydrogen rocket engine for upper stage and trans-lunar applications of the Ares vehicles for the Constellation program. This engine, designated the J-2X, is a higher pressure, higher thrust variant of the Apollo-era J-2 engine. Development was contracted to Pratt & Whitney Rocketdyne in 2006. Over the past several years, two phases of testing have been completed on the development of the gas generator for the J-2X engine. The hardware has progressed through a variety of workhorse injector, chamber, and feed system configurations. Several of these configurations have resulted in combustion instability of the gas generator assembly. Development of the final configuration of workhorse hardware (which will ultimately be used to verify critical requirements on a component level) has required a balance between changes in the injector and chamber hardware in order to successfully mitigate the combustion instability without sacrificing other engine system requirements. This paper provides an overview of the two completed test series, performed at NASA s Marshall Space Flight Center. The requirements, facility setup, hardware configurations, and test series progression are detailed. Significant levels of analysis have been performed in order to provide design solutions to mitigate the combustion stability issues, and these are briefly covered. Also discussed are the results of analyses related to either anomalous readings or off-nominal testing throughout the two test series.

The J-2X Upper Stage Engine: From Heritage to Hardware

NASA Technical Reports Server (NTRS)

Byrd, THomas

2008-01-01

NASA's Global Exploration Strategy requires safe, reliable, robust, efficient transportation to support sustainable operations from Earth to orbit and into the far reaches of the solar system. NASA selected the Ares I crew launch vehicle and the Ares V cargo launch vehicle to provide that transportation. Guiding principles in creating the architecture represented by the Ares vehicles were the maximum use of heritage hardware and legacy knowledge, particularly Space Shuttle assets, and commonality between the Ares vehicles where possible to streamline the hardware development approach and reduce programmatic, technical, and budget risks. The J-2X exemplifies those goals. It was selected by the Exploration Systems Architecture Study (ESAS) as the upper stage propulsion for the Ares I Upper Stage and the Ares V Earth Departure Stage (EDS). The J-2X is an evolved version ofthe historic J-2 engine that successfully powered the second stage of the Saturn I launch vehicle and the second and third stages of the Saturn V launch vehicle. The Constellation architecture, however, requires performance greater than its predecessor. The new architecture calls for larger payloads delivered to the Moon and demands greater loss of mission reliability and numerous other requirements associated with human rating that were not applied to the original J-2. As a result, the J-2X must operate at much higher temperatures, pressures, and flow rates than the heritage J-2, making it one of the highest performing gas generator cycle engines ever built, approaching the efficiency of more complex stage combustion engines. Development is focused on early risk mitigation, component and subassembly test, and engine system test. The development plans include testing engine components, including the subscale injector, main igniter, powerpack assembly (turbopumps, gas generator and associated ducting and structural mounts), full-scale gas generator, valves, and control software with hardware-in-the-loop. Testing expanded in 2007, accompanied by the refinement of the design through several key milestones. This paper discusses those 2007 tests and milestones, as well as updates key developments in 2008.

Future NTP Development Synergy Leveraged from Current J-2X Engine Development

NASA Astrophysics Data System (ADS)

Ballard, Richard O.

2008-01-01

This paper is a discussion of how the many long-lead development elements required for the realization of a future nuclear thermal propulsion (NTP) system can be effectively leveraged from the ongoing work being conducted on the J-2X engine program for the Constellation Program. Development studies conducted to date for NTP forward planning have identified a number of technical areas that will require advancement to acceptable technology readiness levels (TRLs) before they can be utilized in NTP system development. These include high-temperature, high-area ratio nozzle extension; long-life, low-NPSP turbomachinery; and low-boiloff propellant management, and a qualified nuclear fuel element. The current J-2X program is working many of these areas that can be leveraged to support NTP development in a highly compatible and synergistic fashion. In addition to supporting technical development, there are other programmatic issues being worked in the J-2X program that can be leveraged by a future NTP development program. These include compliance with recently-evolved space system requirements such as human-rating, fault tolerance and fracture control. These and other similar mandatory system requirements have been adopted by NASA and can result in a significant technical impact beyond elevation of the root technologies required by NTP. Finally, the exploitation of experience, methodologies, and procedures developed by the J-2X program in the areas of verification, qualification, certification, altitude simulation testing, and facility definition will be especially applicable to a future NTP system. The similarities in system mission (in-space propulsion) and operational environment (vacuum, zero-gee) between J-2X and NTP make this highly synergistic. Thus, it can be shown that the collective benefit of leveraging experience and technologies developed during the J-2X program can result in significant savings in development cost and schedule for NTP.

Future NTP Development Synergy Leveraged from Current J-2X Engine Development

NASA Technical Reports Server (NTRS)

Ballard, Richard O.

2008-01-01

This paper is a discussion of how the many long-lead development elements required for the realization of a future nuclear thermal propulsion (NTP) system can be effectively leveraged from the ongoing work being conducted on the J-2X engine program for the Constellation Program. Development studies conducted to date for NTP forward planning have identified a number of technical areas that will require advancement to acceptable technology readiness levels (TRLs) before they can be utilized in NTP system development. These include high-temperature, high-area ratio nozzle extension; long-life, low-NPSP. turbomachinery; and low-boiloff propellant management; and a qualified nuclear fuel element. The current J-2X program is working many of these areas that can be leveraged to support NTP development in a highly compatible and synergistic fashion. In addition to supporting technical development, there are other programmatic issues being worked in the J-2X program that can be leveraged by a future NTP development program. These include compliance with recently-evolved space system requirements such as human-rating, fault tolerance and fracture control. These and other similar mandatory system requirements have been adopted by NASA and can result in a significant technical impact beyond elevation of the root technologies required by NTP. Finally, the exploitation of experience, methodologies, and procedures developed by the J-2X program in the areas of verification, qualification, certification, altitude simulation testing, and facility definition will be especially applicable to a future NTP system. The similarities in system mission (in-space propulsion) and operational environment (vacuum, zero-gee) between J-2X and NTP make this highly synergistic. Thus, it can be $hown that the collective benefit of leveraging experience and technologies developed during the J-2X program can result in significant savings in development cost and schedule for NTP.

Development of the Functional Flow Block Diagram for the J-2X Rocket Engine System

NASA Technical Reports Server (NTRS)

White, Thomas; Stoller, Sandra L.; Greene, WIlliam D.; Christenson, Rick L.; Bowen, Barry C.

2007-01-01

The J-2X program calls for the upgrade of the Apollo-era Rocketdyne J-2 engine to higher power levels, using new materials and manufacturing techniques, and with more restrictive safety and reliability requirements than prior human-rated engines in NASA history. Such requirements demand a comprehensive systems engineering effort to ensure success. Pratt & Whitney Rocketdyne system engineers performed a functional analysis of the engine to establish the functional architecture. J-2X functions were captured in six major operational blocks. Each block was divided into sub-blocks or states. In each sub-block, functions necessary to perform each state were determined. A functional engine schematic consistent with the fidelity of the system model was defined for this analysis. The blocks, sub-blocks, and functions were sequentially numbered to differentiate the states in which the function were performed and to indicate the sequence of events. The Engine System was functionally partitioned, to provide separate and unique functional operators. Establishing unique functional operators as work output of the System Architecture process is novel in Liquid Propulsion Engine design. Each functional operator was described such that its unique functionality was identified. The decomposed functions were then allocated to the functional operators both of which were the inputs to the subsystem or component performance specifications. PWR also used a novel approach to identify and map the engine functional requirements to customer-specified functions. The final result was a comprehensive Functional Flow Block Diagram (FFBD) for the J-2X Engine System, decomposed to the component level and mapped to all functional requirements. This FFBD greatly facilitates component specification development, providing a well-defined trade space for functional trades at the subsystem and component level. It also provides a framework for function-based failure modes and effects analysis (FMEA), and a rigorous baseline for the functional architecture.

Digital Image Correlation Techniques Applied to Large Scale Rocket Engine Testing

NASA Technical Reports Server (NTRS)

Gradl, Paul R.

2016-01-01

Rocket engine hot-fire ground testing is necessary to understand component performance, reliability and engine system interactions during development. The J-2X upper stage engine completed a series of developmental hot-fire tests that derived performance of the engine and components, validated analytical models and provided the necessary data to identify where design changes, process improvements and technology development were needed. The J-2X development engines were heavily instrumented to provide the data necessary to support these activities which enabled the team to investigate any anomalies experienced during the test program. This paper describes the development of an optical digital image correlation technique to augment the data provided by traditional strain gauges which are prone to debonding at elevated temperatures and limited to localized measurements. The feasibility of this optical measurement system was demonstrated during full scale hot-fire testing of J-2X, during which a digital image correlation system, incorporating a pair of high speed cameras to measure three-dimensional, real-time displacements and strains was installed and operated under the extreme environments present on the test stand. The camera and facility setup, pre-test calibrations, data collection, hot-fire test data collection and post-test analysis and results are presented in this paper.

Turbine Design and Analysis for the J-2X Engine Turbopumps

NASA Technical Reports Server (NTRS)

Marcu, Bogdan; Tran, Ken; Dorney, Daniel J.; Schmauch, Preston

2008-01-01

Pratt and Whitney Rocketdyne and NASA Marshall Space Flight Center are developing the advanced upper stage J-2X engine based on the legacy design of the J-2/J-2S family of engines which powered the Apollo missions. The cryogenic propellant turbopumps have been denoted as Mark72-F and Mark72-0 for the fuel and oxidizer side, respectively. Special attention is focused on preserving the essential flight-proven design features while adapting the design to the new turbopump configuration. Advanced 3-D CFD analysis has been employed to verify turbine aero performance at current flow regime boundary conditions and to mitigate risks associated with stresses. A limited amount of redesign and overall configuration modifications allow for a robust design with performance level matching or exceeding requirement.

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.

Sub-Scale Testing and Development of the J-2X Fuel Turbopump Inducer

NASA Technical Reports Server (NTRS)

Sargent, Scott R.; Becht, David G.

2011-01-01

In the early stages of the J-2X upper stage engine program, various inducer configurations proposed for use in the fuel turbopump (FTP) were tested in water. The primary objectives of this test effort were twofold. First, to obtain a more comprehensive data set than that which existed in the Pratt & Whitney Rocketdyne (PWR) historical archives from the original J-2S program, and second, to supplement that data set with information regarding the cavitation induced vibrations for both the historical J-2S configuration as well as those tested for the J-2X program. The J-2X FTP inducer, which actually consists of an inducer stage mechanically attached to a kicker stage, underwent 4 primary iterations utilizing sub-scaled test articles manufactured and tested in PWR's Engineering Development Laboratory (EDL). The kicker remained unchanged throughout the test series. The four inducer configurations tested retained many of the basic design features of the J-2S inducer, but also included variations on leading edge blade thickness and blade angle distribution, primarily aimed at improving suction performance at higher flow coefficients. From these data sets, the effects of the tested design variables on hydrodynamic performance and cavitation instabilities were discerned. A limited comparison of impact to the inducer efficiency was determined as well.

J-2X engine

NASA Image and Video Library

2012-05-16

On May 16, 2012, engineers at Stennis Space Center conducted a test of the next-generation J-2X engine that will help power NASA's new Space Launch System, moving NASA even closer to a return to deep space.

Signal Processing Methods for Liquid Rocket Engine Combustion Spontaneous Stability and Rough Combustion Assessments

NASA Technical Reports Server (NTRS)

Kenny, R. Jeremy; Casiano, Matthew; Fischbach, Sean; Hulka, James R.

2012-01-01

Liquid rocket engine combustion stability assessments are traditionally broken into three categories: dynamic stability, spontaneous stability, and rough combustion. This work focuses on comparing the spontaneous stability and rough combustion assessments for several liquid engine programs. The techniques used are those developed at Marshall Space Flight Center (MSFC) for the J-2X Workhorse Gas Generator program. Stability assessment data from the Integrated Powerhead Demonstrator (IPD), FASTRAC, and Common Extensible Cryogenic Engine (CECE) programs are compared against previously processed J-2X Gas Generator data. Prior metrics for spontaneous stability assessments are updated based on the compilation of all data sets.

J-2X powerpack

NASA Image and Video Library

2012-10-05

NASA removed J-2X engine No. 10001 from the A-2 Test Stand at Stennis Space Center in early October. Opening of the test stand clamshell flooring allowed a clear view of the next-generation engine and stub nozzle, which is being built to help power future deep-space missions. The engine is an upgrade from the heritage J-2 rocket engine, which helped power Apollo missions to the moon during the late 1960s and early 1970s.

J-2X Powerpack hot-fire test

NASA Image and Video Library

2008-01-31

The first hot-fire test of the J-2X power pack 1A gas generator was performed Jan. 31 on the A-1 Test Stand at Stennis Space Center. Initial indications are that all test objectives were met. The test was designed as a 3.42-second helium spin start with gas generator ignition and it went the full scheduled duration. Test conductors reported a smooth start with normal shutdown and described the event as a 'good test.' The test was part of the early component testing for the new J-2X engine being built by NASA to power the Ares I and Ares V rockets that will carry humans back to the moon and on to Mars. It was performed as one in a series of 12 scheduled tests. Those tests began last November at Stennis, but the January 31 event represented the first hot-fire test. The Stennis tests are a critical step in the successful development of the J-2X engine.

Scissors Duct

NASA Image and Video Library

2007-06-26

Stennis Space Center engineers are preparing to conduct water tests on an updated version of the scissors duct component of the J-2X engine. Measuring about 2 feet long and about 8 inches in diameter, the duct on the J-2X predecessor, the J-2, connected its fuel turbo pumps to the flight vehicle's upper stage run tanks. According to NASA's J-2X project manager at SSC, Gary Benton, the water tests should establish the limits of the duct's ability to withstand vibration.

Analyses of Longitudinal Mode Combustion Instability in J-2X Gas Generator Development

NASA Technical Reports Server (NTRS)

Hulka, J. R.; Protz, C. S.; Casiano, M. J.; Kenny, R. J.

2011-01-01

The National Aeronautics and Space Administration (NASA) and Pratt & Whitney Rocketdyne are developing a liquid oxygen/liquid hydrogen rocket engine for future upper stage and trans-lunar applications. This engine, designated the J-2X, is a higher pressure, higher thrust variant of the Apollo-era J-2 engine. The contract for development was let to Pratt & Whitney Rocketdyne in 2006. Over the past several years, development of the gas generator for the J-2X engine has progressed through a variety of workhorse injector, chamber, and feed system configurations on the component test stand at the NASA Marshall Space Flight Center (MSFC). Several of the initial configurations resulted in combustion instability of the workhorse gas generator assembly at a frequency near the first longitudinal mode of the combustion chamber. In this paper, several aspects of these combustion instabilities are discussed, including injector, combustion chamber, feed system, and nozzle influences. To ensure elimination of the instabilities at the engine level, and to understand the stability margin, the gas generator system has been modeled at the NASA MSFC with two techniques, the Rocket Combustor Interaction Design and Analysis (ROCCID) code and a lumped-parameter MATLAB(TradeMark) model created as an alternative calculation to the ROCCID methodology. To correctly predict the instability characteristics of all the chamber and injector geometries and test conditions as a whole, several inputs to the submodels in ROCCID and the MATLAB(TradeMark) model were modified. Extensive sensitivity calculations were conducted to determine how to model and anchor a lumped-parameter injector response, and finite-element and acoustic analyses were conducted on several complicated combustion chamber geometries to determine how to model and anchor the chamber response. These modifications and their ramification for future stability analyses of this type are discussed.

The Grid Density Dependence of the Unsteady Pressures of the J-2X Turbines

NASA Technical Reports Server (NTRS)

Schmauch, Preston B.

2011-01-01

The J-2X engine was originally designed for the upper stage of the cancelled Crew Launch Vehicle. Although the Crew Launch Vehicle was cancelled the J-2X engine, which is currently undergoing hot-fire testing, may be used on future programs. The J-2X engine is a direct descendent of the J-2 engine which powered the upper stage during the Apollo program. Many changes including a thrust increase from 230K to 294K lbf have been implemented in this engine. As part of the design requirements, the turbine blades must meet minimum high cycle fatigue factors of safety for various vibrational modes that have resonant frequencies in the engine's operating range. The unsteady blade loading is calculated directly from CFD simulations. A grid density study was performed to understand the sensitivity of the spatial loading and the magnitude of the on blade loading due to changes in grid density. Given that the unsteady blade loading has a first order effect on the high cycle fatigue factors of safety, it is important to understand the level of convergence when applying the unsteady loads. The convergence of the unsteady pressures of several grid densities will be presented for various frequencies in the engine's operating range.

Technologies for Energy from Biomass by Direct Combustion, Gasification, and Liquefaction.

DTIC Science & Technology

1981-05-01

1980 1982 1984 Development Alberta Industrial Dev. X American Fyr. Feeder X Andco, Inc. X Applied Engineering Co., Inc. X Biomass Corp. X Bio-Solar x...Feeder ANDCO, Inc. Applied Engineering Company Biomass Corporation Bio-Solar Research and Development Corporation Combustion Power Company, Inc. Davy...Andco. Inc. X Applied Engineering Co., Inc. X Biomass Corp. X , Big-Solar .X I Combustion Power .. XI Davy Powergas X j Dekalb Acresearch, Inc.- x Duvant

Combustion Stability Analyses for J-2X Gas Generator Development

NASA Technical Reports Server (NTRS)

Hulka, J. R.; Protz, C. S.; Casiano, M. J.; Kenny, R. J.

2010-01-01

The National Aeronautics and Space Administration (NASA) is developing a liquid oxygen/liquid hydrogen rocket engine for upper stage and trans-lunar applications of the Ares vehicles for the Constellation program. This engine, designated the J-2X, is a higher pressure, higher thrust variant of the Apollo-era J-2 engine. Development was contracted to Pratt & Whitney Rocketdyne in 2006. Over the past several years, development of the gas generator for the J-2X engine has progressed through a variety of workhorse injector, chamber, and feed system configurations. Several of these configurations have resulted in injection-coupled combustion instability of the gas generator assembly at the first longitudinal mode of the combustion chamber. In this paper, the longitudinal mode combustion instabilities observed on the workhorse test stand are discussed in detail. Aspects of this combustion instability have been modeled at the NASA Marshall Space Flight Center with several codes, including the Rocket Combustor Interaction Design and Analysis (ROCCID) code and a new lumped-parameter MatLab model. To accurately predict the instability characteristics of all the chamber and injector geometries and test conditions, several features of the submodels in the ROCCID suite of calculations required modification. Finite-element analyses were conducted of several complicated combustion chamber geometries to determine how to model and anchor the chamber response in ROCCID. A large suite of sensitivity calculations were conducted to determine how to model and anchor the injector response in ROCCID. These modifications and their ramification for future stability analyses of this type are discussed in detail. The lumped-parameter MatLab model of the gas generator assembly was created as an alternative calculation to the ROCCID methodology. This paper also describes this model and the stability calculations.

Capitol Day

NASA Image and Video Library

2009-02-19

Stennis Space Center Director Gene Goldman visits with Mississippi Gov. Haley Barbour during NASA Day at the Capitol activities on Feb. 19. During the visit, Goldman presented the governor with a model of the J-2X rocket engine currently in development. Stennis engineers did early component testing for the new engine.

J-2X, The Engine of the Future

NASA Technical Reports Server (NTRS)

Smith, Gail

2009-01-01

My project was two-fold, with both parts involving the J-2X Upper Stage engine (which will be used on both the Ares I and V). Mainly, I am responsible for using a program called Iris to create visual represen tations of the rocket engine's telemetry data. Also, my project includes the application of my newly acquired Pro Engineer skills in develo ping a 3D model of the engine's nozzle.

Altitude Testing of Large Liquid Propellant Engines

NASA Technical Reports Server (NTRS)

Maynard, Bryon T.; Raines, Nickey G.

2010-01-01

The National Aeronautics and Space Administration entered a new age on January 14, 2004 with President Bush s announcement of the creation the Vision for Space Exploration that will take mankind back to the Moon and on beyond to Mars. In January, 2006, after two years of hard, dedicated labor, engineers within NASA and its contractor workforce decided that the J2X rocket, based on the heritage of the Apollo J2 engine, would be the new engine for the NASA Constellation Ares upper stage vehicle. This engine and vehicle combination would provide assured access to the International Space Station to replace that role played by the Space Shuttle and additionally, would serve as the Earth Departure Stage, to push the Crew Excursion Vehicle out of Earth Orbit and head it on a path for rendezvous with the Moon. Test as you fly, fly as you test was chosen to be the guiding philosophy and a pre-requisite for the engine design, development, test and evaluation program. An exhaustive survey of national test facility assets proved the required capability to test the J2X engine at high altitude for long durations did not exist so therefore, a high altitude/near space environment testing capability would have to be developed. After several agency concepts the A3 High Altitude Testing Facility proposal was selected by the J2X engine program on March 2, 2007 and later confirmed by a broad panel of NASA senior leadership in May 2007. This facility is to be built at NASA s John C. Stennis Space Center located near Gulfport, Mississippi. 30 plus years of Space Shuttle Main Engine development and flight certification testing makes Stennis uniquely suited to support the Vision For Space Exploration Return to the Moon. Propellant handling infrastructure, engine assembly facilities, a trained and dedicated workforce and a broad and varied technical support base will all ensure that the A3 facility will be built on time to support the schedule needs of the J2X engine and the ultimate flight of the first Ares I vehicle. The A3 facility will be able to simulate pre-ignition altitude from sea-level to 100,000 feet and maintain it up to 650 seconds. Additionally the facility will be able to accommodate initial ignition, shutdown and then restart test profiles. A3 will produce up to 5000 lbm/sec of superheated steam utilizing a Chemical Steam generation system. Two separate inline steam ejectors will be used to produce a test cell vacuum to simulate the 100,000 ft required altitude. Operational capability will ensure that the facility can start up and shutdown without producing adverse pressure gradients across the J2X nozzle. The facility will have a modern thrust measurement system for accurate determination of engine performance. The latest advances in data acquisition and control will be incorporated to measure performance parameters during hotfire testing. Provisions are being made in the initial design of the new altitude facility to allow for testing of other, larger engines and potential upper stage launch vehicles that might require vacuum start testing of the engines. The new facility at Stennis Space Center will be complete and ready for hotfire operations in late 2010.

Testing and Functions of the J2X Gas Generator

NASA Technical Reports Server (NTRS)

Miller, Nicholas

2009-01-01

The Ares I, NASA s new solid rocket based crew launch vehicle, is a two stage in line rocket that has made its waytothe forefront of NASA s endeavors. The Ares I s Upper Stage (US) will be propelled by a J-2X engine which is fueled by liquid hydrogen and liquid oxygen. The J-2X is a variation based on two of its predecessor s, the J-2 and J-2S engines. ET50 is providing the design support for hardware required to run tests on the J-2X Gas Generator (GG) that increases the delivery pressure of the supplied combustion fuels that the engine burns. The test area will be running a series of tests using different lengths and curved segments of pipe and different sized nozzles to determine the configuration that best satisfies the thrust, heat, and stability requirements for the engine. I have had to research the configurations that are being tested and gain an understanding of the purpose of the tests. I then had to research the parts that would be used in the test configurations. I was taken to see parts similar to the ones used in the test configurations and was allowed to review drawings and dimensions used for those parts. My job over this summer has been to use the knowledge I have gained to design, model, and create drawings for the un-fabricated parts that are necessary for the J-2X Workhorse Gas Generator Phase IIcTest.

A Basic Comparison of the Space Shuttle Main Engine and the J-2X Engine

NASA Technical Reports Server (NTRS)

Ayer, Adam

2007-01-01

With the introduction of the new manned space effort through the Constellation Program, there is an interest to have a basic comparison of the current Space Shuttle Main Engine (SSME) to the J-2X engine used for the second stage of both the Ares I and Ares V rockets. This paper seeks to compare size, weight and thrust capabilities while drawing simple conclusions on differences between the two engines.

J-2X installation on A-1

NASA Image and Video Library

2007-09-20

Core components of the J-2X engine being designed for NASA's Constellation Program recently were installed on the A-1 Test Stand at NASA's Stennis Space Center near Bay St. Louis, Miss. Tests of the components, known as Powerpack 1A, will be conducted from November 2007 through February 2008. The Powerpack 1A test article consists of a gas generator and engine turbopumps originally developed for the Apollo Program that put Americans on the moon in the late 1960s and early 1970s. Engineers are testing these heritage components to obtain data that will help them modify the turbomachinery to meet the higher performance requirements of the Ares I and Ares V launch vehicles. The upcoming tests will simulate inlet and outlet conditions that would be present on the turbomachinery during a full-up engine hot-fire test.

A-2 Test Stand modification work

NASA Image and Video Library

2010-10-27

John C. Stennis Space Center employees install a new master interface tool on the A-2 Test Stand on Oct. 27, 2010. Until July 2009, the stand had been used for testing space shuttle main engines. With that test series complete, employees are preparing the stand for testing the next-generation J-2X rocket engine being developed. Testing of the new engine is scheduled to begin in 2011.

1000542

NASA Image and Video Library

2010-04-13

HORACE STORNG (AEROSPACE ENGINEER, ER31 PROPULSION TURBOMACHINERY DESIGN & DEVELOPMENT BRANCH) ADJUSTS A UNIQUE MECHANICAL TEST SETUP THAT MEASURES STRAIN ON A SINGLE SAMPLE, USING TWO DIFFERENT TECHNIQUES AT THE SAME TIME. THE TEST FIXTURE HOLDS A SPECIMEN THAT REPRESENTS A LIQUID OXYGEN (LOX) BEARING FROM THE J2-X ENGINE

Engineering Design Handbook. Metric Conversion Guide

DTIC Science & Technology

1976-07-01

TD •r- (0 T3 i- rtj (l) S...cn c ai TD tr 0) +J +J •i— 3 1= •i— T3 _1 fl) W rt> —> 1- W o +J ɜ- •i— C i—I ^ oo 2-12 DARCOM-P 706-470 o u I J CO < z o...12) to joules. a. Assume 2 significant digits. b. From Table 5-1: 1 Btu = 1.055 06 X 103 J c. Convert: 2.6 X 104Btu X 105506x 1Q3 J =

J-2X Test Articles Using FDM Process

NASA Technical Reports Server (NTRS)

Anderson, Ted; Ruf, Joe; Steele, Phil

2010-01-01

This viewgraph presentation gives a brief history of the J-2X engine, along with detailed description of the material demonstrator and test articles that were created using Fused Deposition Modeling (FDM) process.

Line Crack Subject to Antiplane Shear.

DTIC Science & Technology

1978-07-01

34" (X𔃻j)a( fx -xI) (2. 4) a(lx-xl)= a exp[- ($/a)2 (x’-x)-(x’-x)] , where S is a constant, a is the lattice parameter, and a0 is determined by the...94720 Princeton University Princeton, New Jersey 08540 Prof. J.R.Rice Division of Engineering Dr. S.L. Koh Brown University School of Aero., Astro

PowerPack Developments

NASA Technical Reports Server (NTRS)

2007-01-01

A vintage 1960 J-2 thrust chamber is fitted with brackets and pumps recently at the Pratt & Whitney Rocketdyne assembly facility in Stennis Space Center's Building 9101. Together, the parts comprise the J-2X Powerpack 1A test article. Mississippi Space Services machined the new bracket (the V-shaped arm on the right), making this the first time parts for an engine test article were machined, welded and assembled on site at SSC.

PowerPack Developments

NASA Image and Video Library

2007-04-11

A vintage 1960 J-2 thrust chamber is fitted with brackets and pumps recently at the Pratt & Whitney Rocketdyne assembly facility in Stennis Space Center's Building 9101. Together, the parts comprise the J-2X Powerpack 1A test article. Mississippi Space Services machined the new bracket (the V-shaped arm on the right), making this the first time parts for an engine test article were machined, welded and assembled on site at SSC.

1000537

NASA Image and Video Library

2010-04-13

NATHAN HORACE STRONG (AEROSPACE ENGINEER, ER31 PROPULSION TURBOMACHINERY DESIGN & DEVELOPMENT BRANCH) AND NATHAN COFFEE (EM10 MATERIALS TEST ENGINEER, JACOBS ESTS GROUP/JTI) ADJUST A UNIQUE MECHANICAL TEST SETUP THAT MEASURES STRAIN ON A SINGLE SAMPLE, USING TWO DIFFERENT TECHNIQUES AT THE SAME TIME. THE TEST FIXTURE HOLDS A SPECIMEN THAT REPRESENTS A LIQUID OXYGEN (LOX) BEARING FROM THE J2-X ENGINE. COFFEY, AT RIGHT, WORK IN A LAB IN BUILDING 4612 ON A BEARING TEST

Diffuser Test

NASA Image and Video Library

2007-09-13

Tests begun at Stennis Space Center's E Complex Sept. 13 evaluated a liquid oxygen lead for engine start performance, part of the A-3 Test Facility Subscale Diffuser Risk Mitigation Project at SSC's E-3 Test Facility. Phase 1 of the subscale diffuser project, completed Sept. 24, was a series of 18 hot-fire tests using a 1,000-pound liquid oxygen and gaseous hydrogen thruster to verify maximum duration and repeatability for steam generation supporting the A-3 Test Stand project. The thruster is a stand-in for NASA's developing J-2X engine, to validate a 6 percent scale version of A-3's exhaust diffuser. Testing the J-2X at altitude conditions requires an enormous diffuser. Engineers will generate nearly 4,600 pounds per second of steam to reduce pressure inside A-3's test cell to simulate altitude conditions. A-3's exhaust diffuser has to be able to withstand regulated pressure, temperatures and the safe discharge of the steam produced during those tests. Before the real thing is built, engineers hope to work out any issues on the miniature version. Phase 2 testing is scheduled to begin this month.

Using Innovative Technologies for Manufacturing Rocket Engine Hardware

NASA Technical Reports Server (NTRS)

Betts, E. M.; Eddleman, D. E.; Reynolds, D. C.; Hardin, N. A.

2011-01-01

Many of the manufacturing techniques that are currently used for rocket engine component production are traditional methods that have been proven through years of experience and historical precedence. As the United States enters into the next space age where new launch vehicles are being designed and propulsion systems are being improved upon, it is sometimes necessary to adopt innovative techniques for manufacturing hardware. With a heavy emphasis on cost reduction and improvements in manufacturing time, rapid manufacturing techniques such as Direct Metal Laser Sintering (DMLS) are being adopted and evaluated for their use on NASA s Space Launch System (SLS) upper stage engine, J-2X, with hopes of employing this technology on a wide variety of future projects. DMLS has the potential to significantly reduce the processing time and cost of engine hardware, while achieving desirable material properties by using a layered powder metal manufacturing process in order to produce complex part geometries. Marshall Space Flight Center (MSFC) has recently hot-fire tested a J-2X gas generator (GG) discharge duct that was manufactured using DMLS. The duct was inspected and proof tested prior to the hot-fire test. Using a workhorse gas generator (WHGG) test fixture at MSFC's East Test Area, the duct was subjected to extreme J-2X hot gas environments during 7 tests for a total of 537 seconds of hot-fire time. The duct underwent extensive post-test evaluation and showed no signs of degradation. DMLS manufacturing has proven to be a viable option for manufacturing rocket engine hardware, and further development and use of this manufacturing method is recommended.

Feasibility of Conducting J-2X Engine Testing at the Glenn Research Center Plum Brook Station B-2 Facility

NASA Technical Reports Server (NTRS)

Schafer, Charles F.; Cheston, Derrick J.; Worlund, Armis L.; Brown, James R.; Hooper, William G.; Monk, Jan C.; Winstead, Thomas W.

2008-01-01

A trade study of the feasibility of conducting J-2X testing in the Glenn Research Center (GRC) Plum Brook Station (PBS) B-2 facility was initiated in May 2006 with results available in October 2006. The Propulsion Test Integration Group (PTIG) led the study with support from Marshall Space Flight Center (MSFC) and Jacobs Sverdrup Engineering. The primary focus of the trade study was on facility design concepts and their capability to satisfy the J-2X altitude simulation test requirements. The propulsion systems tested in the B-2 facility were in the 30,000-pound (30K) thrust class. The J-2X thrust is approximately 10 times larger. Therefore, concepts significantly different from the current configuration are necessary for the diffuser, spray chamber subsystems, and cooling water. Steam exhaust condensation in the spray chamber is judged to be the key risk consideration relative to acceptable spray chamber pressure. Further assessment via computational fluid dynamics (CFD) and other simulation capabilities (e.g. methodology for anchoring predictions with actual test data and subscale testing to support investigation.

CFD Simulation on the J-2X Engine Exhaust in the Center-Body Diffuser and Spray Chamber at the B-2 Facility

NASA Technical Reports Server (NTRS)

Wang, Xiao-Yen; Wey, Thomas; Buehrle, Robert

2009-01-01

A computational fluid dynamic (CFD) code is used to simulate the J-2X engine exhaust in the center-body diffuser and spray chamber at the Spacecraft Propulsion Facility (B-2). The CFD code is named as the space-time conservation element and solution element (CESE) Euler solver and is very robust at shock capturing. The CESE results are compared with independent analysis results obtained by using the National Combustion Code (NCC) and show excellent agreement.

Using Innovative Techniques for Manufacturing Rocket Engine Hardware

NASA Technical Reports Server (NTRS)

Betts, Erin M.; Reynolds, David C.; Eddleman, David E.; Hardin, Andy

2011-01-01

Many of the manufacturing techniques that are currently used for rocket engine component production are traditional methods that have been proven through years of experience and historical precedence. As we enter into a new space age where new launch vehicles are being designed and propulsion systems are being improved upon, it is sometimes necessary to adopt new and innovative techniques for manufacturing hardware. With a heavy emphasis on cost reduction and improvements in manufacturing time, manufacturing techniques such as Direct Metal Laser Sintering (DMLS) are being adopted and evaluated for their use on J-2X, with hopes of employing this technology on a wide variety of future projects. DMLS has the potential to significantly reduce the processing time and cost of engine hardware, while achieving desirable material properties by using a layered powder metal manufacturing process in order to produce complex part geometries. Marshall Space Flight Center (MSFC) has recently hot-fire tested a J-2X gas generator discharge duct that was manufactured using DMLS. The duct was inspected and proof tested prior to the hot-fire test. Using the Workhorse Gas Generator (WHGG) test setup at MSFC?s East Test Area test stand 116, the duct was subject to extreme J-2X gas generator environments and endured a total of 538 seconds of hot-fire time. The duct survived the testing and was inspected after the test. DMLS manufacturing has proven to be a viable option for manufacturing rocket engine hardware, and further development and use of this manufacturing method is recommended.

J-2X Powerpack tests begin

NASA Image and Video Library

2007-12-18

COLD FLOW - Liquid oxygen runs through the piping on Stennis Space Center's A-1 Test Stand on Dec. 18 to test the ability of the J-2X engine's Powerpack 1A to withstand the temperature change and pressure. Just visible above and to the right of the test article's nozzle is a frosty pipe, indicating the supercold fuel is flowing as it should.

Combustion Devices CFD Team Analyses Review

NASA Technical Reports Server (NTRS)

Rocker, Marvin

2008-01-01

A variety of CFD simulations performed by the Combustion Devices CFD Team at Marshall Space Flight Center will be presented. These analyses were performed to support Space Shuttle operations and Ares-1 Crew Launch Vehicle design. Results from the analyses will be shown along with pertinent information on the CFD codes and computational resources used to obtain the results. Six analyses will be presented - two related to the Space Shuttle and four related to the Ares I-1 launch vehicle now under development at NASA. First, a CFD analysis of the flow fields around the Space Shuttle during the first six seconds of flight and potential debris trajectories within those flow fields will be discussed. Second, the combusting flows within the Space Shuttle Main Engine's main combustion chamber will be shown. For the Ares I-1, an analysis of the performance of the roll control thrusters during flight will be described. Several studies are discussed related to the J2-X engine to be used on the upper stage of the Ares I-1 vehicle. A parametric study of the propellant flow sequences and mixture ratios within the GOX/GH2 spark igniters on the J2-X is discussed. Transient simulations will be described that predict the asymmetric pressure loads that occur on the rocket nozzle during the engine start as the nozzle fills with combusting gases. Simulations of issues that affect temperature uniformity within the gas generator used to drive the J-2X turbines will described as well, both upstream of the chamber in the injector manifolds and within the combustion chamber itself.

Combustion Stability of the Gas Generator Assembly from J-2X Engine E10001 and Powerpack Tests

NASA Technical Reports Server (NTRS)

Hulka, J. R.; Kenny, R. L.; Casiano, M. J.

2013-01-01

Testing of a powerpack configuration (turbomachinery and gas generator assembly) and the first complete engine system of the liquid oxygen/liquid hydrogen propellant J-2X rocket engine have been completed at the NASA Stennis Space Center. The combustion stability characteristics of the gas generator assemblies on these two systems are of interest for reporting since considerable effort was expended to eliminate combustion instability during early development of the gas generator assembly with workhorse hardware. Comparing the final workhorse gas generator assembly development test data to the powerpack and engine system test data provides an opportunity to investigate how the nearly identical configurations of gas generator assemblies operate with two very different propellant supply systems one the autonomous pressure-fed test configuration on the workhorse development test stand, the other the pump-fed configurations on the powerpack and engine systems. The development of the gas generator assembly and the elimination of the combustion instability on the pressure-fed workhorse test stand have been reported extensively in the two previous Liquid Propulsion Subcommittee meetings 1-7. The powerpack and engine system testing have been conducted from mid-2011 through 2012. All tests of the powerpack and engine system gas generator systems to date have been stable. However, measureable dynamic behavior, similar to that observed on the pressure-fed test stand and reported in Ref. [6] and attributed to an injection-coupled response, has appeared in both powerpack and engine system tests. As discussed in Ref. [6], these injection-coupled responses are influenced by the interaction of the combustion chamber with a branch pipe in the hot gas duct that supplies gaseous helium to pre-spin the turbine during the start transient. This paper presents the powerpack and engine system gas generator test data, compares these data to the development test data, and provides additional combustion stability analyses of the configurations.

Proceedings of Symposium on Energy Engineering in the 21st Century (SEE 2000). Volume Three

DTIC Science & Technology

2000-01-13

osmotic agents for dehydration of vegetables and fruits are table salt, sucrose, glucose, fructose , starch, corn syrup , glycerol, and plant... High Intense Drying Process of Wet Porous Materials 905 X. Wang, M. H. Shi and W. P. Yu N2. Osmotic Dehydration Pretreatment in Drying of...Steady State Model for the High -Pressure Side of Unitary Air-Conditioners 1076 P. J. Petit andJ P. Meyer P9. Development and Experimental Testing of an

The J-2X Upper Stage Engine: From Design to Hardware

NASA Technical Reports Server (NTRS)

Byrd, Thomas

2010-01-01

NASA is well on its way toward developing a new generation of launch vehicles to support of national space policy to retire the Space Shuttle fleet, complete the International Space Station, and return to the Moon as the first step in resuming this nation s exploration of deep space. The Constellation Program is developing the launch vehicles, spacecraft, surface systems, and ground systems to support those plans. Two launch vehicles will support those ambitious plans the Ares I and Ares V. (Figure 1) The J-2X Upper Stage Engine is a critical element of both of these new launchers. This paper will provide an overview of the J-2X design background, progress to date in design, testing, and manufacturing. The Ares I crew launch vehicle will lift the Orion crew exploration vehicle and up to four astronauts into low Earth orbit (LEO) to rendezvous with the space station or the first leg of mission to the Moon. The Ares V cargo launch vehicle is designed to lift a lunar lander into Earth orbit where it will be docked with the Orion spacecraft, and provide the thrust for the trans-lunar journey. While these vehicles bear some visual resemblance to the 1960s-era Saturn vehicles that carried astronauts to the Moon, the Ares vehicles are designed to carry more crew and more cargo to more places to carry out more ambitious tasks than the vehicles they succeed. The government/industry team designing the Ares rockets is mining a rich history of technology and expertise from the Shuttle, Saturn and other programs and seeking commonality where feasible between the Ares crew and cargo rockets as a way to minimize risk, shorten development times, and live within the budget constraints of its original guidance.

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.

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.

Developing Animal Models for Optimizing the Musculoskeletal Repair Potential of Emerging Human Progenitor Cell Therapies

DTIC Science & Technology

2014-06-01

into a central hub for group analysis and reporting. It is now being used for a just received R21 award to assess skeletal variation in a population...model to produce, and the use of the 3D X-rays the extent of deformity and the tempo of repair can be easily documented. Addition of the...Liu, Y., Boyd, N., Dennis, J., Jiang, X., Xin, X., Wang, L., Aguila, H., Rowe, D., Lichtler, A. and Goldberg , J. Developmental engineering of bone

Saturn Apollo Program

NASA Image and Video Library

1960-01-01

Workmen inspect a J-2 engine at Rocketdyne's Canoga Park, California production facility. The J-2, developed under the direction of the Marshall Space Flight Center, was propelled by liquid hydrogen and liquid oxygen. A single J-2 engine was used in the S-IVB stage (the second stage of the Saturn IB and third stage for the Saturn V) and a cluster of five J-2 engines was used to propel the second stage of the Saturn V, the S-II. Initially rated at 200,000 pounds of thrust, the J-2 engine was later uprated in the Saturn V program to 230,000 pounds.

Computer-Aided Structural Engineering (CASE) Project. CBASIN--Structural Design of Saint Anthony Falls Stilling Basins According to Corps of Engineers Criteria for Hydraulic Structures. Computer Program X0098

DTIC Science & Technology

1989-08-01

was entered as 1 in line four. Its values are entered under the following prompting message: UNIT WGT UNIT WGT LAT SOIL COEF DEPTH WIDTH MOIST...basins, tuese thick- A67 54 1 16 Hsi/2 : \\l 2 7 >- 9 >- 0x HSl/2 L 3 U- HSV /2 ( \\ i ^\\^ (J-HSl)/2 ! ^ I TYPE(A) i 6 N/2 : 1 2...program uses working stress analysis in accordance with Corps of Engineers EM 1110- 1 -2101, "Working Stresses." C METHODS D. EQUIPMENT DETAILS

U.S. Air Force Turbine Engine Emission Survey. Volume II. Individual Engine Test Reports.

DTIC Science & Technology

1978-08-01

is 3 »- n rx — o J i •r UJ tD ,n a > J3 3 *- UJ X Q r fr- — JUI T .J Ul »- ^ »— Z Z JO u. >-U. -" •- — — «u. Mi 3 « 3 3 33 i-X T M...yji? U Z Z 3 UJ -4 td />3 — /> ü *J •- 1 < MJ r 9 a >/» aj • x ~> M>« a • 4j r a . o Mi Ml «9 za 1 aß > r»> ip ijfl 1 -• M...o - flj MMM t r»- *£> co in a* er JJ o r^ -4 O X u a IT — .» « cc a O M l\\J rU — in I t o i/. -^ ^ » i • • • • • i m in «o ^- i^ i

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.

Saturn Apollo Program

NASA Image and Video Library

1965-03-04

Pictured is a J-2 engine being processed at Marshall Space Flight Center (MSFC). A single J-2 engine was utilized on the S-IVB stage, the second stage of the Saturn IB and the third stage of the Saturn V vehicles, while a cluster of five J-2 engines powered the second (S-II) stage of the Saturn V launch vehicle. The Saturn V was designed, developed, and tested by engineers at MSFC.

Saturn Apollo Program

NASA Image and Video Library

1960-01-01

This image illustrates the basic differences between the three Saturn launch vehicles developed by the Marshall Space Flight Center. The Saturn I, consisted of two stages, the S-I (eight H-1 engines) and the S-IV (six RL-10 engines). The Saturn IB (center) also consisted of two stages, the S-IB (eight H-1 engines) and the S-IVB (one J-2 engine). The Saturn V consisted of three stages, the S-IC (five F-1 engines), the S-II (five J-2 engines), and the S-IVB (one J-2 engine).

Comprehensive Forced Response Analysis of J2X Turbine Bladed-Discs with 36- Degree Variation in CFD Loading

NASA Technical Reports Server (NTRS)

Elrod, David; Christensen, Eric; Brown, Andrew

2011-01-01

At NASA/MSFC, Structural Dynamics personnel continue to perform advanced analysis for the turbomachinery in the J2X Rocket Engine, which is under consideration for the new Space Launch System. One of the most challenging analyses in the program is predicting turbine blade structural capability. Resonance was predicted by modal analysis, so comprehensive forced response analyses using high fidelity cyclic symmetric finite element models were initiated as required. Analysis methodologies up to this point have assumed the flow field could be fully described by a sector, so the loading on every blade would be identical as it travelled through it. However, in the J2X the CFD flow field varied over the 360 deg of a revolution because of the flow speeds and tortuous axial path. MSFC therefore developed a complex procedure using Nastran Dmap's and Matlab scripts to apply this circumferentially varying loading onto the cyclically symmetric structural models to produce accurate dynamic stresses for every blade on the disk. This procedure is coupled with static, spin, and thermal loading to produce high cycle fatigue safety factors resulting in much more accurate analytical assessments of the blades.

Application of Probabilistic Methods to Assess Risk Due to Resonance in the Design of J-2X Rocket Engine Turbine Blades

NASA Technical Reports Server (NTRS)

Brown, Andrew M.; DeHaye, Michael; DeLessio, Steven

2011-01-01

The LOX-Hydrogen J-2X Rocket Engine, which is proposed for use as an upper-stage engine for numerous earth-to-orbit and heavy lift launch vehicle architectures, is presently in the design phase and will move shortly to the initial development test phase. Analysis of the design has revealed numerous potential resonance issues with hardware in the turbomachinery turbine-side flow-path. The analysis of the fuel pump turbine blades requires particular care because resonant failure of the blades, which are rotating in excess of 30,000 revolutions/minutes (RPM), could be catastrophic for the engine and the entire launch vehicle. This paper describes a series of probabilistic analyses performed to assess the risk of failure of the turbine blades due to resonant vibration during past and present test series. Some significant results are that the probability of failure during a single complete engine hot-fire test is low (1%) because of the small likelihood of resonance, but that the probability increases to around 30% for a more focused turbomachinery-only test because all speeds will be ramped through and there is a greater likelihood of dwelling at more speeds. These risk calculations have been invaluable for use by program management in deciding if risk-reduction methods such as dampers are necessary immediately or if the test can be performed before the risk-reduction hardware is ready.

1000541

NASA Image and Video Library

2010-04-13

TATHAN COFFEE (EM10 MATERIALS TEST ENGINEER, JACOBS ESTS GROUP/JTI) ADJUSTS A UNIQUE MECHANICAL TEST SETUP THAT MEASURES STRAIN ON A SINGLE SAMPLE, USING TWO DIFFERENT TECHNIQUES AT THE SAME TIME. THE TEST FIXTURE HOLDS A SPECIMEN THAT REPRESENTS A LIQUID OXYGEN (LOX) BEARING FROM THE J2-X ENGINE

1000539

NASA Image and Video Library

2010-04-13

AYMAN GIRGIS (EM10 MATERIALS TEST ENGINEER, JACOBS ESTS GROUP/JTI) AND ERIC EARHART (AEROSPACE ENGINEER, ER41 PROPULSION STRUCTURAL & DYNAMICS ANALYSIS BRANCH) DISCUSS DATA PRODUCED BY A UNIQUE MECHANICAL TEST SETUP THAT MEASURES STRAIN ON A SINGLE SAMPLE, USING TWO DIFFERENT TECHNIQUES AT THE SAME TIME. THE TEST FIXTURE HOLDS A SPECIMEN THAT REPRESENTS A LIQUID OXYGEN (LOX) BEARING FROM THE J2-X ENGINE.

1000538

NASA Image and Video Library

2010-04-13

AYMAN GIRGIS (EM10 MATERIALS TEST ENGINEER, JACOBS ESTS GROUP/JTI) ADJUSTS DUAL LENSES FOR A UNIQUE MECHANICAL TST SETUP THAT MEASURES STRAIN ON A SINGLE SAMPLE, USING TWO DIFFERENT TECHNIQUES AT THE SAME TIME. THE TEST FIXTURE HOLDS A SPECIMEN THAT REPRESENTS A LIQUID OXYGEN (LOX) BEARING FROM THE J2-X ENGINE

1000540

NASA Image and Video Library

2010-04-13

ERIC EARHART (AEROSPACE ENGINEER, ER41 PROPULSION STRUCTURAL & DYNAMICS ANALYSIS BRANCH) DISCUSSES DATA PRODUCED BY A UNIQUE MECHANICAL TEST SETUP THAT MEASURES STRAIN ON A SINGLE SAMPLE, USING TWO DIFFERENT TECHNIQUES AT THE SAME TIME. THE TEST FIXTURE HOLDS A SPECIMEN THAT REPRESENTS A LIQUID OXYGEN (LOX) BEARING FROM THE J2-X ENGINE

MESH2D Grid generator design and use

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

Flach, G. P.

Mesh2d is a Fortran90 program originally designed to generate two-dimensional structured grids of the form [x(i),y(i,j)] where [x,y] are grid coordinates identified by indices (i,j). x-coordinates depending only on index i implies strictly vertical x-grid lines, whereas the y-grid lines can undulate. Mesh2d also assigns an integer material type to each grid cell, mtyp(i,j), in a user-specified manner. The complete grid is specified through three separate input files defining the x(i), y(i,j), and mtyp(i,j) variations. Since the original development effort, Mesh2d has been extended to more general two-dimensional structured grids of the form [x(i,j),(i,j)].

Corps of Engineers Hydraulic Design Criteria. Volume 2

DTIC Science & Technology

1977-01-01

21.7 (Chart 310-1/1) 6 a = T - =0.3 ft. 2.7 Effective pressure D + a = 75.0 + 0.3 = 75.3 ft. I : CREST GATES1 WAVC PRESSURE SAMPLE COMPUTATION HYDRAULIC... T -x 75.3.- 25.7 ft Maximum hydraulic load on gate (R) RR y + -j--- x gate height V y - specific weight of water -62.4 lb/ft 3 16.41.7;+25.7)2...j- xhih f tutr -62.4 ( -2;5.) 80 - 192,000 lb/ft of width / t Note: Equivalent for still-water level is 175,000 lb/ft of width. CREST GATES WAVE

The Application of Design to Cost and Life Cycle to Aircraft Engines.

DTIC Science & Technology

1980-05-01

appearing in both columns include AGE (common and peculiar), transportation, management, and training. These cost elements are not usually large in...Proc. of install engine X CIP x Spare engine X Spare parts (base/depot) X Depot labor X Base labor X ECPs-mod/retro X X AGE (peculiar/common) X X...introduits de maniere aleatoire dans le cadre j’hypotheses. En outre les moteurs ou les sous-ensembles, compte tenu du suivi de leur age et de leur

Common Ada Missile Packages. Phase 2. (CAMP-2). Volume 2. 11th Missile Demonstration

DTIC Science & Technology

1988-11-01

report describes the work performed, Ihe results obtained, and the conclusions reached during the Common Ada Missile Packages Phase-2 (CAMP-2) contract ... contract was performed between Sep- tember 1985. and March 1988. The MDAC-STL CAMP program manager was: Dr. Daniel G. McNicholl Technology Branch...j DEC Code Management System X X Software Development Files x x Development Status Database x ! X i Smart Cade Counter X j

Nondestructive Evaluation of the J-2X Direct Metal Laser Sintered Gas Generator Discharge Duct

NASA Technical Reports Server (NTRS)

Esther, Elizabeth A.; Beshears, Ronald D.; Lash, Rhonda K.

2012-01-01

The J-2X program at NASA's Marshall Space Flight Center (MSFC) procured a direct metal laser sintered (DMLS) gas generator discharge duct from Pratt & Whitney Rocketdyne and Morris Technologies for a test program that would evaluate the material properties and durability of the duct in an engine-like environment. DMLS technology was pursued as a manufacturing alternative to traditional techniques, which used off nominal practices to manufacture the gas generator duct's 180 degree turn geometry. MSFC's Nondestructive Evaluation (NDE) Team performed radiographic, ultrasonic, computed tomographic, and fluorescent penetrant examinations of the duct. Results from the NDE examinations reveal some shallow porosity but no major defects in the as-manufactured material. NDE examinations were also performed after hot-fire testing the gas generator duct and yielded similar results pre and post-test and showed no flaw growth or development.

Center for Urban Transportation Studies | College of Engineering & Applied

Science.gov Websites

Engineering of the College of Engineering and Applied Science as well as with the faculty at UW-Madison, UW Science A B C D E F G H I J K L M N O P Q R S T U V W X Y Z D2L PAWS Email My UW-System About UWM Jobs D2L PAWS Email My UW-System University of Wisconsin-Milwaukee College ofEngineering &

Engine Rotor Dynamics, Synchronous and Nonsynchronous Whirl Control

DTIC Science & Technology

1979-02-01

models and experimental tests, a method of design optimization was de -, loped to obtain the best trade-off between all the rotor design variables...onsnchrorous What Task X Dphrmiaatoos * Conxduct u rede Study to Determine Sat Comnpromise Damper Support F~ure 1, Rotor Dyna micso Powe agrbin Overview 12 Tlsv...Program - Pj,k-I + l P-l -2 +. + 2 " 1jk Pjjkll + 1+’- + + 2 flJk Pj+I,k (20) where Rj,k = f3,j-,d- + f4j.k de and f3j, k I f4j,k are the functions

Combustion Stability Verification for the Thrust Chamber Assembly of J-2X Developmental Engines 10001, 10002, and 10003

NASA Technical Reports Server (NTRS)

Morgan, C. J.; Hulka, J. R.; Casiano, M. J.; Kenny, R. J.; Hinerman, T. D.; Scholten, N.

2015-01-01

The J-2X engine, a liquid oxygen/liquid hydrogen propellant rocket engine available for future use on the upper stage of the Space Launch System vehicle, has completed testing of three developmental engines at NASA Stennis Space Center. Twenty-one tests of engine E10001 were conducted from June 2011 through September 2012, thirteen tests of the engine E10002 were conducted from February 2013 through September 2013, and twelve tests of engine E10003 were conducted from November 2013 to April 2014. Verification of combustion stability of the thrust chamber assembly was conducted by perturbing each of the three developmental engines. The primary mechanism for combustion stability verification was examining the response caused by an artificial perturbation (bomb) in the main combustion chamber, i.e., dynamic combustion stability rating. No dynamic instabilities were observed in the TCA, although a few conditions were not bombed. Additional requirements, included to guard against spontaneous instability or rough combustion, were also investigated. Under certain conditions, discrete responses were observed in the dynamic pressure data. The discrete responses were of low amplitude and posed minimal risk to safe engine operability. Rough combustion analyses showed that all three engines met requirements for broad-banded frequency oscillations. Start and shutdown transient chug oscillations were also examined to assess the overall stability characteristics, with no major issues observed.

Review of Combustion Stability Characteristics of Swirl Coaxial Element Injectors

NASA Technical Reports Server (NTRS)

Hulka, J. R.; Casiano, M. J.

2013-01-01

Liquid propellant rocket engine injectors using coaxial elements where the center liquid is swirled have become more common in the United States over the past several decades, although primarily for technology or advanced development programs. Currently, only one flight engine operates with this element type in the United States (the RL10 engine), while the element type is very common in Russian (and ex-Soviet) liquid propellant rocket engines. In the United States, the understanding of combustion stability characteristics of swirl coaxial element injectors is still very limited, despite the influx of experimental and theoretical information from Russia. The empirical and theoretical understanding is much less advanced than for the other prevalent liquid propellant rocket injector element types, the shear coaxial and like-on-like paired doublet. This paper compiles, compares and explores the combustion stability characteristics of swirl coaxial element injectors tested in the United States, dating back to J-2 and RL-10 development, and extending to very recent programs at the NASA MSFC using liquid oxygen and liquid methane and kerosene propellants. Included in this study are several other relatively recent design and test programs, including the Space Transportation Main Engine (STME), COBRA, J-2X, and the Common Extensible Cryogenic Engine (CECE). A presentation of the basic data characteristics is included, followed by an evaluation by several analysis techniques, including those included in Rocket Combustor Interactive Design and Analysis Computer Program (ROCCID), and methodologies described by Hewitt and Bazarov.

A Paradigm for Developing Sediment Toxicity Bioassays for the Regulatory Evaluation of Dredged Material

DTIC Science & Technology

1994-06-01

sediment-associated toxicant in the lower Fox River and Green Bay , Wisconsin," Environ. Toxicol. Chem. 9, 313-322. Burton, G. A., Jr., Stemmer, B. L...Barton, J. ¶ USEPA, Region X, Seatle, WA Bay . S. It So. CA Coastal Water Research Project, Long Beach, CA Black, J. t EA Engineering, Science and...Umbeck F. I USAGE, Seattle District, Seattle, WA Ward, J. f Battelle Northwest Pacific Laboratory, Sequim , WA Weber, C.¶ USEPA, Cincinnati, OH Welch, T

Cone Quasi-Concave Multi-Objective Programming Theory and Dominance Cone Constructions.

DTIC Science & Technology

1988-08-01

generalized cone concavity and nondominated solutions for later use in our development. We also derive some properties of generalized cone concavity. A set S...A-quasiconcave on S" if g(.x 1+(1-X)x 2)-Min{g(x0), g(x 2)) e IntA forallxl*x 2 E SandX e (0,1), where (in ( gi (x’), gi (x2)) Min [g (0i), g (x2 ) - 1...will lead to elimination of the points of J3 by using the dominance cone W3 . Associated with W3 , only the points of J1 and J2 are nondominated, and

Signal Processing Methods for Liquid Rocket Engine Combustion Stability Assessments

NASA Technical Reports Server (NTRS)

Kenny, R. Jeremy; Lee, Erik; Hulka, James R.; Casiano, Matthew

2011-01-01

The J2X Gas Generator engine design specifications include dynamic, spontaneous, and broadband combustion stability requirements. These requirements are verified empirically based high frequency chamber pressure measurements and analyses. Dynamic stability is determined with the dynamic pressure response due to an artificial perturbation of the combustion chamber pressure (bomb testing), and spontaneous and broadband stability are determined from the dynamic pressure responses during steady operation starting at specified power levels. J2X Workhorse Gas Generator testing included bomb tests with multiple hardware configurations and operating conditions, including a configuration used explicitly for engine verification test series. This work covers signal processing techniques developed at Marshall Space Flight Center (MSFC) to help assess engine design stability requirements. Dynamic stability assessments were performed following both the CPIA 655 guidelines and a MSFC in-house developed statistical-based approach. The statistical approach was developed to better verify when the dynamic pressure amplitudes corresponding to a particular frequency returned back to pre-bomb characteristics. This was accomplished by first determining the statistical characteristics of the pre-bomb dynamic levels. The pre-bomb statistical characterization provided 95% coverage bounds; these bounds were used as a quantitative measure to determine when the post-bomb signal returned to pre-bomb conditions. The time for post-bomb levels to acceptably return to pre-bomb levels was compared to the dominant frequency-dependent time recommended by CPIA 655. Results for multiple test configurations, including stable and unstable configurations, were reviewed. Spontaneous stability was assessed using two processes: 1) characterization of the ratio of the peak response amplitudes to the excited chamber acoustic mode amplitudes and 2) characterization of the variability of the peak response's frequency over the test duration. This characterization process assists in evaluating the discreteness of a signal as well as the stability of the chamber response. Broadband stability was assessed using a running root-mean-square evaluation. These techniques were also employed, in a comparative analysis, on available Fastrac data, and these results are presented here.

A-1 modification work under way

NASA Technical Reports Server (NTRS)

2008-01-01

Phil Schemanski of Pratt & Whitney Rocketdyne removes equipment inside the thrust drum on the A-1 Test Stand as part of a comprehensive modification project to prepare for testing the new J-2X engine.

Hire a Milwaukee Engineer | College of Engineering & Applied Science

Science.gov Websites

A B C D E F G H I J K L M N O P Q R S T U V W X Y Z D2L PAWS Email My UW-System About UWM UWM Jobs D2L PAWS Email My UW-System University of Wisconsin-Milwaukee College ofEngineering & Olympiad Girls Who Code Club FIRST Tech Challenge NSF I-Corps Site of Southeastern Wisconsin UW-Milwaukee

April 2016 Milwaukee Engineer | College of Engineering & Applied Science

Science.gov Websites

A B C D E F G H I J K L M N O P Q R S T U V W X Y Z D2L PAWS Email My UW-System About UWM UWM Jobs D2L PAWS Email My UW-System University of Wisconsin-Milwaukee College ofEngineering & Olympiad Girls Who Code Club FIRST Tech Challenge NSF I-Corps Site of Southeastern Wisconsin UW-Milwaukee

V/STOL Rotary Propulsor Noise Prediction Model Update and Evaluation.

DTIC Science & Technology

1979-12-01

Noise as Observed on and Jacques the Bertin Aerotrain July 1976 JSV 54(2) 3) Hoch, Berthelot Use of the Bertin Aerotrain for the Investigation July 1976...Atencio G.E. X376-B Jots 2 Drevet, et al Aerotrain - G.E. J85 9 Jaeck Wind Tunnel - G.E. J85 Nozzles 13 Pacbian, et al Wind Tunnel Model Jet 23 Brooks...Calculat6d Full-Scale Jet Noise Data Base Item 2. - This paper presents measurements made of the noise from a J85 engine installed on the Aerotrain . Data

Aerodynamic and Thermal Performance Characteristics of Supersonic-X Type Decelerators at Mach Number 8

DTIC Science & Technology

1977-02-01

SUPERSONIC -X TYPE DECELERATORS AT MACH NUMBER 8 t’z.r I # I JJ’, o,. VON KARMAN GAS DYNAMICS FACILITY ARNOLD ENGINEERING DEVELOPMENT CENTER AIR FORCE...AERODYNAMIC AND THERMAL PERFORMANCE CHARACTERISTICS OF SUPERSONIC - X TYPE DECELERATORS AT MACH NUMBER 8 ’ 7 AU THORCs,: p ; J . D. Corce , ARO, Inc...pe r fo rmance cha rac t e r i s t i c s of model nylon, Kevlar 29, and Bisbenzimidazobenzophenanthroline Supersonic -X type parachutes behind a

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.

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.

Parametric Engineering System Definition Model. Volume II. Appendix C. FORTRAN Listings

DTIC Science & Technology

1979-08-01

x ý_ .V L , x 0w X: U Aw a U= U2 LL (A9 > cAL .D- 3: w.. = L I- ;< c Q 4 -- uj- 2: UZLL - ccZ4 .W - U. C ~ U- FLJ LLt- CLL>JuU. j Z Xf jZ x V- *O L...ý - P- u Z.." - S.. = 2- U :- - - - LUý zz w z c IN.U 4( 4 U.-JC uI. 0 > u .C Cj ’t a. u c , L0> V)QV)e in G.t O~ .0 P- ct tD ~ *-cMc" -t m C c...7 0 7; n, C-1600 z c t= orw > w I Z z z. z Z tn - w 1 t CU Z ": < - z -a>- C- LL Z = z - , - a I-. LU * C-161 0X w -U. c td , Ln U-lU_ U. LL.- Wj~ W z

A-3 Test Stand

NASA Image and Video Library

2011-08-19

The A-3 Test Stand under construction at Stennis Space Center is set for completion and activation in 2013. It will allow operators to conduct simulated high-altitude testing on the next-generation J-2X rocket engine.

Training Extract, AFSC 113X0B, Flight Engineer, Helicopter Qualified.

DTIC Science & Technology

1982-12-01

TRAINING .................................................................. 1I0 SE. GENERAL rLIGHT RULES A 9 C t | 7. PeRFORM INSPECIIOIS 12 7A... TRAINING .................................................................. lIC 6E. GENERAL FLIGHT RULES A a C...ME"BERS PERFORMING I-A I PROGRAM GENERATED VECTOR IMEMBERS/ NO TYPE VECTOR MEAN - SC DESCRIPTION I TN. SEP J.6 2.J TRAINING EMPHASIS RATINSS I IIOS

Printing Outside the Box: Additive Manufacturing Processes for Fabrication of Large Aerospace Structures

NASA Technical Reports Server (NTRS)

Babai, Majid; Peters, Warren

2015-01-01

To achieve NASA's mission of space exploration, innovative manufacturing processes are being applied to the fabrication of propulsion elements. Liquid rocket engines (LREs) are comprised of a thrust chamber and nozzle extension as illustrated in figure 1 for the J2X upper stage engine. Development of the J2X engine, designed for the Ares I launch vehicle, is currently being incorporated on the Space Launch System. A nozzle extension is attached to the combustion chamber to obtain the expansion ratio needed to increase specific impulse. If the nozzle extension could be printed as one piece using free-form additive manufacturing (AM) processes, rather than the current method of forming welded parts, a considerable time savings could be realized. Not only would this provide a more homogenous microstructure than a welded structure, but could also greatly shorten the overall fabrication time. The main objective of this study is to fabricate test specimens using a pulsed arc source and solid wire as shown in figure 2. The mechanical properties of these specimens will be compared with those fabricated using the powder bed, selective laser melting technology at NASA Marshall Space Flight Center. As printed components become larger, maintaining a constant temperature during the build process becomes critical. This predictive capability will require modeling of the moving heat source as illustrated in figure 3. Predictive understanding of the heat profile will allow a constant temperature to be maintained as a function of height from substrate while printing complex shapes. In addition, to avoid slumping, this will also allow better control of the microstructural development and hence the properties. Figure 4 shows a preliminary comparison of the mechanical properties obtained.

Evaluation of Start Transient Oscillations with the J-2X Engine Gas Generator Assembly

NASA Technical Reports Server (NTRS)

Hulka, J. R.; Morgan, C. J.; Casiano, M. J.

2015-01-01

During development of the gas generator for the liquid oxygen/liquid hydrogen propellant J-2X rocket engine, distinctive and oftentimes high-amplitude pressure oscillations and hardware vibrations occurred during the start transient of nearly every workhorse gas generator assembly test, as well as during many tests of engine system hardware. These oscillations appeared whether the steady-state conditions exhibited stable behavior or not. They occurred similarly with three different injector types, and with every combustion chamber configuration tested, including chamber lengths ranging over a 5:1 range, several different nozzle types, and with or without a side branch line simulating a turbine spin start gas supply line. Generally, two sets of oscillations occurred, one earlier in the start transient and at higher frequencies, and the other almost immediately following and at lower frequencies. Multiple dynamic pressure measurements in the workhorse combustion chambers indicated that the oscillations were associated with longitudinal acoustic modes of the combustion chambers, with the earlier and higher frequency oscillation usually related to the second longitudinal acoustic mode and the later and lower frequency oscillation usually related to the first longitudinal acoustic mode. Given that several early development gas generator assemblies exhibited unstable behavior at frequencies near the first longitudinal acoustic modes of longer combustion chambers, the start transient oscillations are presumed to provide additional insight into the nature of the combustion instability mechanisms. Aspects of the steadystate oscillations and combustion instabilities from development and engine system test programs have been reported extensively in the three previous JANNAF Liquid Propulsion Subcommittee meetings (see references below). This paper describes the hardware configurations, start transient sequence operations, and transient and dynamic test data during the start transient. The implications of these results on previous analyses and understanding of the combustion instability observed during steady-state conditions, especially the effects of injector influences, is discussed.

International Workshop on Beam Injection Assessment of Defects in Semiconductors Held in Meudon-Bellevue (France) on 18-20 July 1988

DTIC Science & Technology

1989-07-20

Krause , Phys. Stat. Sol. (a) 102, 443 (1987) 2) \\1. Tajima, in "Defects and Properties of Semiconductors: Defect Engineering", edited by J. Chikawa (Tokyo...illustrate that the newly developed electron optical column satisfies all the requirements for internal measurements on VLSI circuits. (1] E. Wolfgang ...JEME29, rue Jeanne Marvig 13397 MARSEILLE CEDE-X 13 31400 TOULOUSE FRANCE FRANCE PICQUERA-S Javier- SCHROTER Wolfgang Dpto de Fisica de Materiales IV

Graphical User Interface for Simulink Integrated Performance Analysis Model

NASA Technical Reports Server (NTRS)

Durham, R. Caitlyn

2009-01-01

The J-2X Engine (built by Pratt & Whitney Rocketdyne,) in the Upper Stage of the Ares I Crew Launch Vehicle, will only start within a certain range of temperature and pressure for Liquid Hydrogen and Liquid Oxygen propellants. The purpose of the Simulink Integrated Performance Analysis Model is to verify that in all reasonable conditions the temperature and pressure of the propellants are within the required J-2X engine start boxes. In order to run the simulation, test variables must be entered at all reasonable values of parameters such as heat leak and mass flow rate. To make this testing process as efficient as possible in order to save the maximum amount of time and money, and to show that the J-2X engine will start when it is required to do so, a graphical user interface (GUI) was created to allow the input of values to be used as parameters in the Simulink Model, without opening or altering the contents of the model. The GUI must allow for test data to come from Microsoft Excel files, allow those values to be edited before testing, place those values into the Simulink Model, and get the output from the Simulink Model. The GUI was built using MATLAB, and will run the Simulink simulation when the Simulate option is activated. After running the simulation, the GUI will construct a new Microsoft Excel file, as well as a MATLAB matrix file, using the output values for each test of the simulation so that they may graphed and compared to other values.

48 CFR Appendix A to Part 1219 - Appendix A to Part 1219

Code of Federal Regulations, 2010 CFR

2010-10-01

...* FPDS products and service code (1) Engineering Development AT94 (2) Systems Engineering Services (Only) R414 (3) Radio/TV Communication Equipment (except airborne) 5820 (4) Maintenance, Repair, and Rebuilding of engines, turbines, components and weapons equipment J028/J010 (5) ADP Central Processing Units...

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A-3 Groundbreaking Ceremony

NASA Image and Video Library

2007-08-23

NASA officials and government leaders participated in a groundbreaking event for a new rocket engine test stand at NASA's Stennis Space Center, Miss. Pictured (left to right) are Deputy Associate Administrator for Exploration Systems Doug Cooke, Pratt & Whitney Rocketdyne President Jim Maser, Stennis Space Center Director Richard Gilbrech, NASA Associate Administrator for Exploration Systems Scott Horowitz, NASA Deputy Administrator Shana Dale, Mississippi Gov. Haley Barbour, Sen. Thad Cochran, Sen. Trent Lott, Rep. Gene Taylor, SSC's Deputy Director Gene Goldman, and SSC's A-3 Project Manager Lonnie Dutreix. Stennis' A-3 Test Stand will provide altitude testing for NASA's developing J-2X engine. That engine will power the upper stages of NASA's Ares I and Ares V rockets. A-3 is the first large test stand to be built at SSC since the site's inception in the 1960s.

Experimental Investigation into Beam-Riding Physics of Lightcraft Engines: Progress Report

NASA Astrophysics Data System (ADS)

Kenoyer, David A.; Myrabo, Leik N.; Notaro, Samuel J.; Bragulla, Paul W.

2010-05-01

A twin Lumonics K922M pulsed TFA CO2 laser system (pulse duration of approximately 200 ns FWHM spike with 1 us tail) was employed to experimentally measure beam-riding behavior of Type ♯200 lightcraft engines, using the Angular Impulse Measurement Device (AIMD). Beam-riding forces and moments were examined along with engine thrust-vectoring behavior, as a function of: a) laser beam angular and lateral offset from the vehicle axis of symmetry; b) laser pulse energy 12 to 36 joules); c) pulse duration (100 ns and 1 μs); and d) engine size (97.7 mm to 161.2 mm). Maximum lateral momentum coupling coefficients (CM) of 135 N-s/MJ were achieved with the K922M laser whereas previous PLVTS laser (420 J, 18 μs duration) results indicated 15-30 N-s/MJ—an improvement of 4.5x to 9x. Maximum axial CM performance with the K922M is li1ely to be 4x to 7x larger than lateral CM values, but must await confirmation in upcoming tests.

Workshop on Scientific Analysis and Policy in Network Security

DTIC Science & Technology

2010-09-10

IBBT Dcpt. Electrical Engineering-ESAT/COSlC. Kasteelpark Arenberg 10 Bus 2446, B-3001 Leuven. Belgium bart.preneelflesat.kuleuven.be Abstract. This...Bouissou1,3 1 Electricity de France R&D, 1 avenue du General de Gaulle, 92141 Clamart, France 2 Institut Telecom, Telecom ParisTech, 46 rue Barrault...for any x G Aj1; /, !,_0(x) is a probability distribution on AQ, such that if x G S{i then £jeS, (/’.^(.OXj) = L illul if x e Dii > then £j

Development of ultrashort x-ray/gamma-ray sources using ultrahigh power lasers (Conference Presentation)

NASA Astrophysics Data System (ADS)

Kim, Hyung Taek; Nakajima, Kazuhisa; Hojbota, Calin; Jeon, Jong Ho; Rhee, Yong-Joo; Lee, Kyung Hwan; Lee, Seong Ku; Sung, Jae Hee; Lee, Hwang Woon; Pathak, Vishwa B.; Pae, Ki Hong; Sebban, Stéphane; Tissandier, Fabien; Gautier, Julien; Ta Phuoc, Kim; Malka, Victor; Nam, Chang Hee

2017-05-01

Short-pulse x-ray/gamma-ray sources have become indispensable light sources for investigating material science, bio technology, and photo-nuclear physics. In past decades, rapid advancement of high intensity laser technology led extensive progresses in the field of radiation sources based on laser-plasma interactions - x-ray lasers, betatron radiation and Compton gamma-rays. Ever since the installation of a 100-TW laser in 2006, we have pursued the development of ultrashort x-ray/gamma-ray radiations, such as x-ray lasers, relativistic high-order harmonics, betatron radiation and all-optical Compton gamma-rays. With the construction of two PW Ti:Sapphire laser beamlines having peak powers of 1.0 PW and 1.5 PW in 2010 and 2012, respectively [1], we have investigated the generation of multi-GeV electron beams [2] and MeV betatron radiations. We plan to carry out the Compton backscattering to generate MeV gamma-rays from the interaction of a GeV electron beam and a PW laser beam. Here, we present the recent progress in the development of ultrashort x-ray/gamma-ray radiation sources based on laser plasma interactions and the plan for developing Compton gamma-ray sources driven by the PW lasers. In addition, we will present the applications of laser-plasma x-ray lasers to x-ray holography and coherent diffraction imaging. [references] 1. J. H. Sung, S. K. Lee, T. J. Yu, T. M. Jeong, and J. Lee, Opt. Lett. 35, 3021 (2010). 2. H. T. Kim, K. H. Pae, H. J. Cha, I J. Kim, T. J. Yu, J. H. Sung, S. K. Lee, T. M. Jeong, J. Lee, Phys. Rev. Lett. 111, 165002 (2013).

Behavior of an Automatic Pacemaker Sensing Algorithm for Single-Pass VDD Atrial Electrograms

DTIC Science & Technology

2001-10-25

830- s lead (Medico), during several different body postures, deep respiration, and walking. The algorithm had a pre - determined sensing dynamic range...SINGLE-PASS VDD ATRIAL ELECTROGRAMS J. Kim1, S.H. Lee1, S.Y.Yang2, B. S . Cho2, and W. Huh1 1Department of Electronics Engineering, Myongji...University, Yongin, Korea 2Department of Information and Communication, Dongwon College, Kwangju, Korea S T = 5 0 % x ( B + C ) / 2 S T = 5 0 % x ( A + B

Remembering the Giants: Apollo Rocket Propulsion Development

NASA Technical Reports Server (NTRS)

Fisher, Steven C. (Editor); Rahman, Shamim A. (Editor)

2009-01-01

Topics discussed include: Rocketdyne - F-1 Saturn V First Stage Engine; Rocketdyne - J-2 Saturn V 2nd & 3rd Stage Engine; Rocketdyne - SE-7 & SE-8 Engines; Aerojet - AJ10-137 Apollo Service Module Engine; Aerojet - Attitude Control Engines; TRW - Lunar Descent Engine; and Rocketdyne - Lunar Ascent Engine.

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2016 Milwaukee Engineering Research Conference | College of Engineering &

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Fast Facts | College of Engineering & Applied Science

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Strategic Plan | College of Engineering & Applied Science

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College-Wide Support | College of Engineering & Applied Science

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50th Anniversary | College of Engineering & Applied Science

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FAQ's and Deadlines | College of Engineering & Applied Science

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Office of Research Support | College of Engineering & Applied Science

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Department Chairs and Staff | College of Engineering & Applied Science

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National Program for Inspection of Non-Federal Dams. Morris Reservoir Dam (CT 00473), Naugatuck River Basin, Morris & Litchfield, Connecticut. Phase I Inspection Report.

DTIC Science & Technology

1979-05-01

Materials Branch Engineering Division " w ..- .* -.. CA RNEY )U TERZ IAN , C HA IR MAN ,’ ’’’’’ Chief, Structural Section..- .. ..Design Branch...8217/ ~ ., iJ V ’ _W7 V,~ ~ /N. ) w Y1 joyN V < ~ ’\\ ’bI _a,_ .55. .. It" C.-.N ’~.:..~i5~Ak.,~.0 2.d~ ) lbK&~> -2,. /C jji 5.x. ;50~ \\~ IV .J\\/ W.. 4

Experimental investigation of gasoline compression ignition combustion in a light-duty diesel engine

NASA Astrophysics Data System (ADS)

Loeper, C. Paul

Due to increased ignition delay and volatility, low temperature combustion (LTC) research utilizing gasoline fuel has experienced recent interest [1-3]. These characteristics improve air-fuel mixing prior to ignition allowing for reduced emissions of nitrogen oxides (NOx) and soot (or particulate matter, PM). Computational fluid dynamics (CFD) results at the University of Wisconsin-Madison's Engine Research Center (Ra et al. [4, 5]) have validated these attributes and established baseline operating parameters for a gasoline compression ignition (GCI) concept in a light-duty diesel engine over a large load range (3-16 bar net IMEP). In addition to validating these computational results, subsequent experiments at the Engine Research Center utilizing a single cylinder research engine based on a GM 1.9-liter diesel engine have progressed fundamental understanding of gasoline autoignition processes, and established the capability of critical controlling input parameters to better control GCI operation. The focus of this thesis can be divided into three segments: 1) establishment of operating requirements in the low-load operating limit, including operation sensitivities with respect to inlet temperature, and the capabilities of injection strategy to minimize NOx emissions while maintaining good cycle-to-cycle combustion stability; 2) development of novel three-injection strategies to extend the high load limit; and 3) having developed fundamental understanding of gasoline autoignition kinetics, and how changes in physical processes (e.g. engine speed effects, inlet pressure variation, and air-fuel mixture processes) affects operation, develop operating strategies to maintain robust engine operation. Collectively, experimental results have demonstrated the ability of GCI strategies to operate over a large load-speed range (3 bar to 17.8 bar net IMEP and 1300-2500 RPM, respectively) with low emissions (NOx and PM less than 1 g/kg-FI and 0.2 g/kg-FI, respectively), and low fuel consumption (gross indicated fuel consumption <200 g/kWh). [1] Dec, J. E., Yang, Y., and Dronniou, N., 2011, "Boosted HCCI - Controlling Pressure- Rise Rates for Performance Improvements using Partial Fuel Stratification with Conventional Gasoline," SAE Int. J. Engines, 4(1), pp. 1169-1189. [2] Kalghatgi, G., Hildingsson, L., and Johansson, B., 2010, "Low NO(x) and Low Smoke Operation of a Diesel Engine Using Gasolinelike Fuels," Journal of Engineering for Gas Turbines and Power-Transactions of the Asme, 132(9), p. 9. [3] Manente, V., Zander, C.-G., Johansson, B., Tunestal, P., and Cannella, W., 2010, "An Advanced Internal Combustion Engine Concept for Low Emissions and High Efficiency from Idle to Max Load Using Gasoline Partially Premixed Combustion," SAE International, 2010-01-2198. [4] Ra, Y., Loeper, P., Reitz, R., Andrie, M., Krieger, R., Foster, D., Durrett, R., Gopalakrishnan, V., Plazas, A., Peterson, R., and Szymkowicz, P., 2011, "Study of High Speed Gasoline Direct Injection Compression Ignition (GDICI) Engine Operation in the LTC Regime," SAE Int. J. Engines, 4(1), pp. 1412-1430. [5] Ra, Y., Loeper, P., Andrie, M., Krieger, R., Foster, D., Reitz, R., and Durrett, R., 2012, "Gasoline DICI Engine Operation in the LTC Regime Using Triple- Pulse Injection," SAE Int. J. Engines, 5(3), pp. 1109-1132.

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.

Rocketdyne - J-2 Saturn V 2nd and 3rd Stage Engine. Chapter 2, Appendix D

NASA Technical Reports Server (NTRS)

Coffman, Paul

2009-01-01

The J-2 engine was unique in many respects. Technology was not nearly as well-developed in oxygen/hydrogen engines at the start of the J-2 project. As a result, it experienced a number of "teething" problems. It was used in two stages on the Saturn V vehicle in the Apollo Program, as well as on the later Skylab and Apollo/Soyuz programs. In the Apollo Program, it was used on the S-II stage, which was the second stage of the Saturn V vehicle. There were five J-2 engines at the back end of the S-II Stage. In the S-IV-B stage, it was a single engine, but that single engine had to restart. The Apollo mission called for the entire vehicle to reach orbital velocity in low Earth orbit after the first firing of the Saturn-IV-B stage and, subsequently, to fire a second time to go on to the moon. The engine had to be man-rated (worthy of transporting humans). It had to have a high thrust rate and performance associated with oxygen/hydrogen engines, although there were some compromises there. It had to gimbal for thrust vector control. It was an open-cycle gas generator engine delivering up to 230,000 pounds of thrust.

Interstage Flammability Analysis Approach

NASA Technical Reports Server (NTRS)

Little, Jeffrey K.; Eppard, William M.

2011-01-01

The Interstage of the Ares I launch platform houses several key components which are on standby during First Stage operation: the Reaction Control System (ReCS), the Upper Stage (US) Thrust Vector Control (TVC) and the J-2X with the Main Propulsion System (MPS) propellant feed system. Therefore potentially dangerous leaks of propellants could develop. The Interstage leaks analysis addresses the concerns of localized mixing of hydrogen and oxygen gases to produce deflagration zones in the Interstage of the Ares I launch vehicle during First Stage operation. This report details the approach taken to accomplish the analysis. Specified leakage profiles and actual flammability results are not presented due to proprietary and security restrictions. The interior volume formed by the Interstage walls, bounding interfaces with the Upper and First Stages, and surrounding the J2-X engine was modeled using Loci-CHEM to assess the potential for flammable gas mixtures to develop during First Stage operations. The transient analysis included a derived flammability indicator based on mixture ratios to maintain achievable simulation times. Validation of results was based on a comparison to Interstage pressure profiles outlined in prior NASA studies. The approach proved useful in the bounding of flammability risk in supporting program hazard reviews.

Using Decision Trees to Detect and Isolate Simulated Leaks in the J-2X Rocket Engine

NASA Technical Reports Server (NTRS)

Schwabacher, Mark A.; Aguilar, Robert; Figueroa, Fernando F.

2009-01-01

The goal of this work was to use data-driven methods to automatically detect and isolate faults in the J-2X rocket engine. It was decided to use decision trees, since they tend to be easier to interpret than other data-driven methods. The decision tree algorithm automatically "learns" a decision tree by performing a search through the space of possible decision trees to find one that fits the training data. The particular decision tree algorithm used is known as C4.5. Simulated J-2X data from a high-fidelity simulator developed at Pratt & Whitney Rocketdyne and known as the Detailed Real-Time Model (DRTM) was used to "train" and test the decision tree. Fifty-six DRTM simulations were performed for this purpose, with different leak sizes, different leak locations, and different times of leak onset. To make the simulations as realistic as possible, they included simulated sensor noise, and included a gradual degradation in both fuel and oxidizer turbine efficiency. A decision tree was trained using 11 of these simulations, and tested using the remaining 45 simulations. In the training phase, the C4.5 algorithm was provided with labeled examples of data from nominal operation and data including leaks in each leak location. From the data, it "learned" a decision tree that can classify unseen data as having no leak or having a leak in one of the five leak locations. In the test phase, the decision tree produced very low false alarm rates and low missed detection rates on the unseen data. It had very good fault isolation rates for three of the five simulated leak locations, but it tended to confuse the remaining two locations, perhaps because a large leak at one of these two locations can look very similar to a small leak at the other location.

NASA Crew and Cargo Launch Vehicle Development Approach Builds on Lessons from Past and Present Missions

NASA Technical Reports Server (NTRS)

Dumbacher, Daniel L.

2006-01-01

The United States (US) Vision for Space Exploration, announced in January 2004, outlines the National Aeronautics and Space Administration's (NASA) strategic goals and objectives, including retiring the Space Shuttle and replacing it with new space transportation systems for missions to the Moon, Mars, and beyond. The Crew Exploration Vehicle (CEV) that the new human-rated Crew Launch Vehicle (CLV) lofts into space early next decade will initially ferry astronauts to the International Space Station (ISS) Toward the end of the next decade, a heavy-lift Cargo Launch Vehicle (CaLV) will deliver the Earth Departure Stage (EDS) carrying the Lunar Surface Access Module (LSAM) to low-Earth orbit (LEO), where it will rendezvous with the CEV launched on the CLV and return astronauts to the Moon for the first time in over 30 years. This paper outlines how NASA is building these new space transportation systems on a foundation of legacy technical and management knowledge, using extensive experience gained from past and ongoing launch vehicle programs to maximize its design and development approach, with the objective of reducing total life cycle costs through operational efficiencies such as hardware commonality. For example, the CLV in-line configuration is composed of a 5-segment Reusable Solid Rocket Booster (RSRB), which is an upgrade of the current Space Shuttle 4- segment RSRB, and a new upper stage powered by the liquid oxygen/liquid hydrogen (LOX/LH2) J-2X engine, which is an evolution of the J-2 engine that powered the Apollo Program s Saturn V second and third stages in the 1960s and 1970s. The CaLV configuration consists of a propulsion system composed of two 5-segment RSRBs and a 33- foot core stage that will provide the LOX/LED needed for five commercially available RS-68 main engines. The J-2X also will power the EDS. The Exploration Launch Projects, managed by the Exploration Launch Office located at NASA's Marshall Space Flight Center, is leading the design, development, testing, and operations planning for these new space transportation systems. Utilizing a foundation of heritage hardware and management lessons learned mitigates both technical and programmatic risk. Project engineers and managers work closely with the Space Shuttle Program to transition hardware, infrastructure, and workforce assets to the new launch systems, leveraging a wealth of knowledge from Shuffle operations. In addition, NASA and its industry partners have tapped into valuable Apollo databases and are applying corporate wisdom conveyed firsthand by Apollo-era veterans of America s original Moon missions. Learning from its successes and failures, NASA employs rigorous systems engineering and systems management processes and principles in a disciplined, integrated fashion to further improve the probability of mission success.

Saturn Apollo Program

NASA Image and Video Library

1960-01-01

A J-2 engine undergoes static firing. The J-2, developed under the direction of the Marshall Space Flight Center, was propelled by liquid hydrogen and liquid oxygen. A single J-2 was utilized in the S-IVB stage (the second stage for the Saturn IB and third stage for the Saturn V) and in a cluster of five for the second stage (S-II) of the Saturn V. Initially rated at 200,000 pounds of thrust, the engine was later uprated in the Saturn V program to 230,000 pounds.

Phase Transitions and Magnetocaloric Effects in GdNi2MnX

NASA Astrophysics Data System (ADS)

Aryal, Anil; Quetz, Abdiel; Pandey, Sudip; Samanta, Tapas; Dubenko, Igor; Stadler, Shane; Ali, Naushad

2015-03-01

The structural and magnetic properties of the GdNi2Mnx system (for x = 0.5, 0.6, 0.8, 1.0, 1.2, 1.4, 1.5) have been studied by x-ray diffraction and magnetization measurements. A rhombohedral PuNi3-type structure was observed in the XRD data. A second order magnetic phase transition from ferromagnetic (FM) to paramagnetic (PM) was found, characterized by a long-range exchange interaction as predicted by mean field theory. A magnetic entropy change of | Δ SM | = 3.1 J/kg K and 2.9 J/kg K for ΔH = 5 T was observed in the vicinity of the Curie temperature (TC) for GdNi2Mn0.8 and GdNi2Mn1.4 respectively. In spite of the low values of ΔSM, the relative cooling power (RCP) was found to be 176 J/Kg for the GdNi2Mn0.8 compound. . This work was supported by the Office of Basic Energy Sciences, Material Science and Engineering Division of the U.S. Department of Energy (USDOE-DE-FG02-06ER46291 and DE-FG02-13ER46946).

Supernova Remnant W49B

NASA Image and Video Library

2017-12-08

Release date Dec. 30, 2009 In the supernova remnant W49B, Suzaku found another fossil fireball. It detected X-rays produced when heavily ionized iron atoms recapture an electron. This view combines infrared images from the ground (red, green) with X-ray data from NASA's Chandra X-Ray Observatory (blue). Credit: Caltech/SSC/J. Rho and T. Jarrett and NASA/CXC/SSC/J. Keohane et al. To learn more about this image go to: www.nasa.gov/mission_pages/astro-e2/news/fossil-fireballs... NASA Goddard Space Flight Center is home to the nation's largest organization of combined scientists, engineers and technologists that build spacecraft, instruments and new technology to study the Earth, the sun, our solar system, and the universe.

Center for By-Products Utilization (CBU) | College of Engineering & Applied

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Development of the scintillator-based probe for fast-ion losses in the HL-2A tokamak

NASA Astrophysics Data System (ADS)

Zhang, Y. P.; Liu, Yi; Luo, X. B.; Isobe, M.; Yuan, G. L.; Liu, Y. Q.; Hua, Y.; Song, X. Y.; Yang, J. W.; Li, X.; Chen, W.; Li, Y.; Yan, L. W.; Song, X. M.; Yang, Q. W.; Duan, X. R.

2014-05-01

A new scintillator-based lost fast-ion probe (SLIP) has been developed and operated in the HL-2A tokamak [L. W. Yan, X. R. Duan, X. T. Ding, J. Q. Dong, Q. W. Yang, Yi Liu, X. L. Zou, D. Q. Liu, W. M. Xuan, L. Y. Chen, J. Rao, X. M. Song, Y. Huang, W. C. Mao, Q. M. Wang, Q. Li, Z. Cao, B. Li, J. Y. Cao, G. J. Lei, J. H. Zhang, X. D. Li, W. Chen, J. Chen, C. H. Cui, Z. Y. Cui, Z. C. Deng, Y. B. Dong, B. B. Feng, Q. D. Gao, X. Y. Han, W. Y. Hong, M. Huang, X. Q. Ji, Z. H. Kang, D. F. Kong, T. Lan, G. S. Li, H. J. Li, Qing Li, W. Li, Y. G. Li, A. D. Liu, Z. T. Liu, C. W. Luo, X. H. Mao, Y. D. Pan, J. F. Peng, Z. B. Shi, S. D. Song, X. Y. Song, H. J. Sun, A. K. Wang, M. X. Wang, Y. Q. Wang, W. W. Xiao, Y. F. Xie, L. H. Yao, D. L. Yu, B. S. Yuan, K. J. Zhao, G. W. Zhong, J. Zhou, J. C. Yan, C. X. Yu, C. H. Pan, Y. Liu, and the HL-2A Team, Nucl. Fusion 51, 094016 (2011)] to measure the losses of neutral beam ions. The design of the probe is based on the concept of the α-particle detectors on Tokamak Fusion Test Reactor (TFTR) using scintillator plates. The probe is capable of traveling across an equatorial plane port and sweeping the aperture angle rotationally with respect to the axis of the probe shaft by two step motors, in order to optimize the radial position and the collimator angle. The energy and the pitch angle of the lost fast ions can be simultaneously measured if the two-dimensional image of scintillation light intensity due to the impact of the lost fast ions is detected. Measurements of the fast-ion losses using the probe have been performed during HL-2A neutral beam injection discharges. The clear experimental evidence of enhanced losses of beam ions during disruptions has been obtained by means of the SLIP system. A detailed description of the probe system and the first experimental results are reported.

Development of the scintillator-based probe for fast-ion losses in the HL-2A tokamak

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

Zhang, Y. P., E-mail: zhangyp@swip.ac.cn; Liu, Yi; Yuan, G. L.

A new scintillator-based lost fast-ion probe (SLIP) has been developed and operated in the HL-2A tokamak [L. W. Yan, X. R. Duan, X. T. Ding, J. Q. Dong, Q. W. Yang, Yi Liu, X. L. Zou, D. Q. Liu, W. M. Xuan, L. Y. Chen, J. Rao, X. M. Song, Y. Huang, W. C. Mao, Q. M. Wang, Q. Li, Z. Cao, B. Li, J. Y. Cao, G. J. Lei, J. H. Zhang, X. D. Li, W. Chen, J. Chen, C. H. Cui, Z. Y. Cui, Z. C. Deng, Y. B. Dong, B. B. Feng, Q. D. Gao, X. Y.more » Han, W. Y. Hong, M. Huang, X. Q. Ji, Z. H. Kang, D. F. Kong, T. Lan, G. S. Li, H. J. Li, Qing Li, W. Li, Y. G. Li, A. D. Liu, Z. T. Liu, C. W. Luo, X. H. Mao, Y. D. Pan, J. F. Peng, Z. B. Shi, S. D. Song, X. Y. Song, H. J. Sun, A. K. Wang, M. X. Wang, Y. Q. Wang, W. W. Xiao, Y. F. Xie, L. H. Yao, D. L. Yu, B. S. Yuan, K. J. Zhao, G. W. Zhong, J. Zhou, J. C. Yan, C. X. Yu, C. H. Pan, Y. Liu, and the HL-2A Team , Nucl. Fusion 51, 094016 (2011)] to measure the losses of neutral beam ions. The design of the probe is based on the concept of the α-particle detectors on Tokamak Fusion Test Reactor (TFTR) using scintillator plates. The probe is capable of traveling across an equatorial plane port and sweeping the aperture angle rotationally with respect to the axis of the probe shaft by two step motors, in order to optimize the radial position and the collimator angle. The energy and the pitch angle of the lost fast ions can be simultaneously measured if the two-dimensional image of scintillation light intensity due to the impact of the lost fast ions is detected. Measurements of the fast-ion losses using the probe have been performed during HL-2A neutral beam injection discharges. The clear experimental evidence of enhanced losses of beam ions during disruptions has been obtained by means of the SLIP system. A detailed description of the probe system and the first experimental results are reported.« less

Diagnosis of Plasma States in X-Ray Laser Experiments

DTIC Science & Technology

1992-10-01

J e AD-A256 909 FOREIGN AEROSPACE SCIENCE AND TECHNOLOGY CENTER DTIC 4 OCT 2 6 1992’ DIAGNOSIS OF PLASMA STATES IN X-RAY LASER EXPERIMENTS by Yang ...0619-92 HUMAN TRANSLATION FASTC-ID(RS)T-0619-92 8 October 1992 DIAGNOSIS OF PLASMA STATES IN X-RAY LASER EXPERIMENTS By: Yang Shangjin, Cai Yuqin, Chunyu... Yang Shangjin, Cai Yuqin, and Chunyu Shutai China Academy of Engineering Physics Abstract At an LF-12 laser installation, an Nd glass laser of

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.

Development of very high J c in Ba(Fe 1-xCo x) 2As 2 thin films grown on CaF 2

DOE PAGES

Tarantini, C.; Kametani, F.; Lee, S.; ...

2014-12-03

Ba(Fe 1-xCo x) 2As 2 is the most tunable of the Fe-based superconductors (FBS) in terms of acceptance of high densities of self-assembled and artificially introduced pinning centres which are effective in significantly increasing the critical current density, J c. Moreover, FBS are very sensitive to strain, which induces an important enhancement in critical temperature,T c, of the material. In this study we demonstrate that strain induced by the substrate can further improve J c of both single and multilayer films by more than that expected simply due to the increase in T c. The multilayer deposition of Ba(Fe 1-xComore » x) 2As 2 on CaF 2 increases the pinning force density (F p=J c x μ₀H) by more than 60% compared to a single layer film, reaching a maximum of 84 GN/m 3 at 22.5 T and 4.2 K, the highest value ever reported in any 122 phase.« less

A-1 Test Stand modifications

NASA Image and Video Library

2011-09-14

Team members check the progress of a liquid nitrogen cold shock test on the A-1 Test Stand at Stennis Space Center on Sept. 15. The cold shock test is used to confirm the test stand's support system can withstand test conditions, when super-cold rocket engine propellant is piped. The A-1 Test Stand is preparing to conduct tests on the powerpack component of the J-2X rocket engine, beginning in early 2012.

Catalyst Grants: Contributing to X-Ray History | College of Engineering &

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Applied Science A B C D E F G H I J K L M N O P Q R S T U V W X Y Z D2L PAWS Email My UW Visit Apply Give to UWM Jobs D2L PAWS Email My UW-System University of Wisconsin-Milwaukee College Olympiad Girls Who Code Club FIRST Tech Challenge NSF I-Corps Site of Southeastern Wisconsin UW-Milwaukee

Environmental Assessment for the Construction and Operation of the Constellation Program A-3 Test Stand

NASA Technical Reports Server (NTRS)

Kennedy, Carolyn D.

2007-01-01

This document is an environmental assessment that examines the environmental impacts of a proposed plan to clear land and to construct a test stand for use in testing the J-2X rocket engine at simulated altitude conditions in support of NASA's Constellation Program.

Constellation

NASA Image and Video Library

2008-02-15

SHOWN IS A CONCEPT IMAGE OF THE ARES V EARTH DEPARTURE STAGE AND LUNAR SURFACE ACCESS MODULE DOCKED WITH THE ORION CREW EXPLORATION VEHICLE IN EARTH ORBIT. THE DEPARTURE STAGE, POWERED BY A J-2X ENGINE, IS NEEDED TO ESCAPE EARTH'S GRAVITY AND SEND THE CREW VEHICLE AND LUNAR MODULE ON THEIR JOURNEY TO THE MOON.

Modeling Potential Carbon Monoxide Exposure Due to Operation of a Major Rocket Engine Altitude Test Facility Using Computational Fluid Dynamics

NASA Technical Reports Server (NTRS)

Blotzer, Michael J.; Woods, Jody L.

2009-01-01

This viewgraph presentation reviews computational fluid dynamics as a tool for modelling the dispersion of carbon monoxide at the Stennis Space Center's A3 Test Stand. The contents include: 1) Constellation Program; 2) Constellation Launch Vehicles; 3) J2X Engine; 4) A-3 Test Stand; 5) Chemical Steam Generators; 6) Emission Estimates; 7) Located in Existing Test Complex; 8) Computational Fluid Dynamics; 9) Computational Tools; 10) CO Modeling; 11) CO Model results; and 12) Next steps.

Saturn Apollo Program

NASA Image and Video Library

1967-09-09

This image depicts the test firing of a J-2 engine in the S-IVB Test Stand at the Marshall Space Flight Center (MSFC). The J-2, developed by Rocketdyne under the direction of MSFC, was propelled by liquid hydrogen and liquid oxygen. A single J-2 was utilized in the S-IVB stage (the second stage for the Saturn IB and third stage for the Saturn V) and in a cluster of five for the second stage (S-II) of the Saturn V. Initially rated at 200,000 pounds of thrust, the engine was later upgraded in the Saturn V program to 230,000 pounds.

Illustration of Ares I During Launch

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. In this early illustration, the Ares I is illustrated during lift off. Ares I is an inline, two-stage rocket configuration topped by the Orion crew vehicle and its launch abort system. With a 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. Ares I uses 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 I second stage. Ares I can lift more than 55,000 pounds to low Earth orbit. The Ares I is subject to configuration changes before it is actually launched. This illustration reflects the latest configuration as of September 2006.

Illustration of Ares I Launch Vehicle With Call Outs

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. This is an illustration of the Ares I with call outs. Ares I is an inline, two-stage rocket configuration topped by the Orion crew vehicle and its launch abort system. In addition to the primary mission of carrying crews of four to six astronauts to Earth orbit, Ares I may also use its 25-ton payload capacity to deliver resources and supplies to the International Space Station, or to 'park' payloads in orbit for retrieval by other spacecraft bound for the moon or other destinations. 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 Apollo second stage will power the Ares I second stage. The Ares I can lift more than 55,000 pounds to low Earth orbit. Ares I is subject to configuration changes before it is actually launched. This illustration reflects the latest configuration as of January 2007.

A Computer Code to Calculate the Effect of Internal Waves on Acoustic Propagation

DTIC Science & Technology

1975-03-01

Trt 36 ■ ■ im Y(J4)=BI4>TI X(J3»=BR^-TK Y( J!>)=8U-TI TR=-0.707lOb7612»(BK7*BI7l TI=Ü.707lÜ6 7dl2*(BR7-HI7) X(J6>=BR6*TR Y( Jt>)= Bl6 *TI...X(J7>=BR6-TR Y(J7)= B16 -TI 1 CUNTINUE 3 IF(N2POW-3*N8POW-l) !>l6t7 6 UOölJ=l,NTHPU f2 Ri=X(J)>X(Jfl» xi j*n = x( J>-X( j + u XCJ)=Kl FIl = Y

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.

DARPA/USAF/USN J-UCAS X-45A System Demonstration Program: A Review of Flight Test Site Processes and Personnel

NASA Technical Reports Server (NTRS)

Cosentino, Gary B.

2008-01-01

The Joint Unmanned Combat Air Systems (J-UCAS) program is a collaborative effort between the Defense Advanced Research Project Agency (DARPA), the US Air Force (USAF) and the US Navy (USN). Together they have reviewed X-45A flight test site processes and personnel as part of a system demonstration program for the UCAV-ATD Flight Test Program. The goal was to provide a disciplined controlled process for system integration and testing and demonstration flight tests. NASA's Dryden Flight Research Center (DFRC) acted as the project manager during this effort and was tasked with the responsibilities of range and ground safety, the provision of flight test support and infrastructure and the monitoring of technical and engineering tasks. DFRC also contributed their engineering knowledge through their contributions in the areas of autonomous ground taxi control development, structural dynamics testing and analysis and the provision of other flight test support including telemetry data, tracking radars, and communications and control support equipment. The Air Force Flight Test Center acted at the Deputy Project Manager in this effort and was responsible for the provision of system safety support and airfield management and air traffic control services, among other supporting roles. The T-33 served as a J-UCAS surrogate aircraft and demonstrated flight characteristics similar to that of the the X-45A. The surrogate served as a significant risk reduction resource providing mission planning verification, range safety mission assessment and team training, among other contributions.

Experimental Determination of the Dynamic Hydraulic Transfer Function for the J-2X Oxidizer Turbopump. Part One; Methodology

NASA Technical Reports Server (NTRS)

Zoladz, Tom; Patel, Sandeep; Lee, Erik; Karon, Dave

2011-01-01

An advanced methodology for extracting the hydraulic dynamic pump transfer matrix (Yp) for a cavitating liquid rocket engine turbopump inducer+impeller has been developed. The transfer function is required for integrated vehicle pogo stability analysis as well as optimization of local inducer pumping stability. Laboratory pulsed subscale waterflow test of the J-2X oxygen turbo pump is introduced and our new extraction method applied to the data collected. From accurate measures of pump inlet and discharge perturbational mass flows and pressures, and one-dimensional flow models that represents complete waterflow loop physics, we are able to derive Yp and hence extract the characteristic pump parameters: compliance, pump gain, impedance, mass flow gain. Detailed modeling is necessary to accurately translate instrument plane measurements to the pump inlet and discharge and extract Yp. We present the MSFC Dynamic Lump Parameter Fluid Model Framework and describe critical dynamic component details. We report on fit minimization techniques, cost (fitness) function derivation, and resulting model fits to our experimental data are presented. Comparisons are made to alternate techniques for spatially translating measurement stations to actual pump inlet and discharge.

Saturn Apollo Program

NASA Image and Video Library

1967-01-01

Workmen secure a J-2 engine onto the S-IVB (second) stage thrust structure. As part of Marshall Space Center's "building block" approach to the Saturn development, the S-IVB was utilized in the Saturn IBC launch vehicle as a second stage and the Saturn V launch vehicle as a third stage. The booster, built for NASA by McDornell Douglas Corporation, was powered by a single J-2 engine, initially capable of 200,000 pounds of thrust.

Saturn Apollo Program

NASA Image and Video Library

1963-01-01

Smokeless flame juts from the diffuser of a unique vacuum chamber in which the upper stage rocket engine, the hydrogen fueled J-2, was tested at a simulated space altitude in excess of 60,000 feet. The smoke you see is actually steam. In operation, vacuum is established by injecting steam into the chamber and is maintained by the thrust of the engine firing through the diffuser. The engine was tested in this environment for start, stop, coast, restart, and full-duration operations. The chamber was located at Rocketdyne's Propulsion Field Laboratory, in the Santa Susana Mountains, near Canoga Park, California. The J-2 engine was developed by Rocketdyne for the Marshall Space Flight Center.

Meteoroid Flux from Lunar Impact Monitoring

NASA Technical Reports Server (NTRS)

Suggs, Robert; Moser, Danielle; Cooke, William; Suggs, Ronnie

2015-01-01

The flux of kilogram-sized meteoroids has been determined from the first 5 years of observations by NASA's Lunar Impact Monitoring Program (Suggs et al. 2014). Telescopic video observations of 126 impact flashes observed during photometric conditions were calibrated and the flux of meteoroids to a limiting mass of 30 g was determined to be 6.14 x 10(exp -10) m(exp -2) yr(exp -1) at the Moon, in agreement with the Grun et al. (1985) model value of 7.5 x 10(exp -10) m(exp -2) yr(exp -1). After accounting for gravitational focusing effects, the flux at the Earth to a limiting impact energy of 3.0 x10(exp -6) kilotons of TNT (1.3 x 10(exp 7) J) was determined to be consistent with the results in Brown et al. (2002). Approximately 62% of the impact flashes were correlated with major meteor showers as cataloged in visual/optical meteor shower databases. These flux measurements, coupled with cratering and ejecta models, can be used to develop impact ejecta engineering environments for use in lunar surface spacecraft design and risk analyses.

Engineering Test Report Paint Waste Reduction Fluidized Bed Process Demonstration at Letterkenny Army Depot Chambersburg, Pennsylvania

DTIC Science & Technology

1991-07-01

predicted by equation using actual chart response obtained from each calibration gas response. (Concentration of cal. gas,l Calibration error, % span • ppm...Analyzer predicted by cali- Col. gas Chart divisions equation* bration Cylinder conc., error,** Drift,***INo. ppm or % Pretest Posttest Pretest Posttest...2m ~J * Correlation coef. * qgq’jq **Analyzer ca.error, % spn (Cal. gas conc. conc. predicted ) x 1003 cal spanSpan value Acceptable limit x ɚ% of

The ROSCOE Manual. Volume 2-1. Sample Case.

DTIC Science & Technology

1980-03-01

X X — !*• » X X r*- ro H •1 ^ X IN UJ ** "O r Jul%9 c a 2 O J M X UJ .. 3 U — CO PH 4 X 3C t- L3 u • • 1C U. U3 H tD UJ UJ a...3 •-ooaooao-n »-030300030331 »-oooooooooox» »-00 3303000am i-a a 3 x •- ua 1-0 tO •- L3 2 •-• -3 ^ IU Q JaJ J...O C3 nuuv) tD CO CD 2 IftJ UJ •- I J J J M Iß Ifl li. WCJUCO o o (BfDIDZiiituHlO • • Z CO x 3 OCM

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.

A Dynamic Model of an Axisymmetric, Transversely Isotropic, Fluid-Loaded, Fully Elastic Cylindrical Shell

DTIC Science & Technology

2010-01-11

and circumferential directions. These equations are fX XK £rr =—<Jrr --^-a9d ~^~axx » tr tr hx fX XV £0e =- — °’rr + — (766 —~^~axx » hr tr tx vrx ...constants in equations (1) and (2) can be solved for in terms of engineering constants. They are cll = ’ \\\\j) (1 + vrx )(1 - urx - 2vrxvxr) Erorx(l...oxr) > (14) (^ + uny(\\-u„-2urxuxr) c13 = > U->) Eruxr(\\- vrx ) c33=—« : r> (16) Vrx <\\- Vrx -2»rx»xr) and CA4=Gxr = .n E* ,- (17) 2(l + uxr

The Subchronic Inhalation Toxicity of DF2 (Diesel Fuel) Used in Vehicle Engine Exhaust Smoke Systems (VEESS).

DTIC Science & Technology

1986-03-01

4-I +4 .- -+ + _C tL+ + + +i + T + +- + - -) 4. c_ --- - * - 4A _ __ _ -- 0 0 ICx" C ) 4j cliou 0 N4cr(\\lc’ + + ++ ++ + + +1 -4++111+ = 0 m x...Charles L. Crouse SP6 David C . Burnett Garnet E. Affleck Dale H. Heitkamp Edmund G. Cummings, Ph.D. Carlyle Lilly Richard L. Farrand, Ph.D. Joseph J...Feeney, Ph.D. Robert W. Dorsey Michael Rausa SP6 Mohammed S. Ghumman Ernest H. Kandel Robert D. Armstrong Jeffrey D. Bergmann William C . Stark. John

Spring 2014 Internship Diffuser Data Analysis

NASA Technical Reports Server (NTRS)

Laigaie, Robert T.; Ryan, Harry M.

2014-01-01

J-2X engine testing on the A-2 test stand at the NASA John C. Stennis Space Center (SSC) has recently concluded. As part of that test campaign, the engine was operated at lower power levels in support of expanding the use of J-2X to other missions. However, the A-2 diffuser was not designed for engine testing at the proposed low power levels. To evaluate the risk of damage to the diffuser, computer simulations were created of the rocket engine exhaust plume inside the 50ft long, water-cooled, altitude-simulating diffuser. The simulations predicted that low power level testing would cause the plume to oscillate in the lower sections of the diffuser. This can possibly cause excessive vibrations, stress, and heat transfer from the plume to the diffuser walls. To understand and assess the performance of the diffuser during low power level engine testing, nine accelerometers and four strain gages were installed around the outer surface of the diffuser. The added instrumentation also allowed for the verification of the rocket exhaust plume computational model. Prior to engine hot-fire testing, a diffuser water-flow test was conducted to verify the proper operation of the newly installed instrumentation. Subsequently, two J-2X engine hot-fire tests were completed. Hot-Fire Test 1 was 11.5 seconds in duration, and accelerometer and strain data verified that the rocket engine plume oscillated in the lower sections of the diffuser. The accelerometers showed very different results dependent upon location. The diffuser consists of four sections, with Section 1 being closest to the engine nozzle and Section 4 being farthest from the engine nozzle. Section 1 accelerometers showed increased amplitudes at startup and shutdown, but low amplitudes while the diffuser was started. Section 3 accelerometers showed the opposite results with near zero G amplitudes prior to and after diffuser start and peak amplitudes to +/- 100G while the diffuser was started. Hot-Fire Test 1 strain gages showed different data dependent on section. Section 1 strains were small, and were in the range of 50 to 150 microstrain, which would result in stresses from 1.45 to 4.35 ksi. The yield stress of the material, A-285 Grade C Steel, is 29.7 ksi. Section 4 strain gages showed much higher values with strains peaking at 1600 microstrain. This strain corresponds to a stress of 46.41 ksi, which is in excess of the yield stress, but below the ultimate stress of 55 to 75 ksi. The decreased accelerations and strain in Section 1, and the increased accelerations and strain in Sections 3 and 4 verified the computer simulation prediction of increased plume oscillations in the lower sections of the diffuser. Hot-Fire Test 2 ran for a duration of 125 seconds. The engine operated at a slightly higher power level than Hot-Fire Test 1 for the initial 35 seconds of the test. After 35 seconds the power level was lowered to Hot-Fire Test 1 levels. The acceleration and strain data for Hot-Fire Test 2 was similar during the initial part of the test. However, just prior to the engine being lowered to the Hot-Fire Test 1 power level, the strain gage data in Section 4 showed a large decrease to strains near zero microstrain from their peak at 1500 microstrain. Future work includes further strain and acceleration data analysis and evaluation.

X-15A-2 with test pilot Pete Knight

NASA Technical Reports Server (NTRS)

1965-01-01

Air Force pilot William J. 'Pete' Knight is seen here in front of the X-15A-2 aircraft (56-6671). Pete Knight made 16 flights in the X-15, and set the world unofficial speed record for fixed wing aircraft, 4,520 mph (mach 6.7), in the X-15A-2. He also made one flight above 50 miles, qualifying him for astronaut wings. The X-15 was a rocket-powered aircraft 50 ft long with a wingspan of 22 ft. It was a missile-shaped vehicle with an unusual wedge-shaped vertical tail, thin stubby wings, and unique fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was capable of developing 57,000 lb of rated thrust (actual thrust reportedly climbed to 60,000 lb). North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow-on program used the aircraft as a testbed to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudder surfaces on the vertical stabilizers to control yaw and canted horizontal surfaces on the tail to control pitch when moving in synchronization or roll when moved differentially. For flight in the thin air outside of the appreciable Earth's atmosphere, the X-15 used a reaction control system. Hydrogen peroxide thrust rockets located on the nose of the aircraft provided pitch and yaw control. Those on the wings provided roll control. Because of the large fuel consumption, the X-15 was air launched from a B-52 aircraft at 45,000 ft and a speed of about 500 mph. Depending on the mission, the rocket engine provided thrust for the first 80 to 120 sec of flight. The remainder of the normal 10 to 11 min. flight was powerless and ended with a 200-mph glide landing. Generally, one of two types of X-15 flight profiles was used: a high-altitude flight plan that called for the pilot to maintain a steep rate of climb, or a speed profile that called for the pilot to push over and maintain a level altitude. The X-15 was flown over a period of nearly 10 years--June 1959 to Oct. 1968--and set the world's unofficial speed and altitude records of 4,520 mph (Mach 6.7) and 354,200 ft (over 67 mi) in a program to investigate all aspects of piloted hypersonic flight. Information gained from the highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo manned spaceflight programs, and also the Space Shuttle program. The X-15s made a total of 199 flights and were manufactured by North American Aviation. X-15-1, serial number 56-6670, is now located at the National Air and Space Museum, Washington DC. North American X-15A-2, serial number 56-6671, is at the United States Air Force Museum, Wright-Patterson AFB, Ohio. The X-15-3, serial number 56-6672, crashed on 15 November 1967, resulting in the death of Maj. Michael J. Adams.

The Development of a Graphical User Interface Engine for the Convenient Use of the HL7 Version 2.x Interface Engine

PubMed Central

Kim, Hwa Sun; Cho, Hune

2011-01-01

Objectives The Health Level Seven Interface Engine (HL7 IE), developed by Kyungpook National University, has been employed in health information systems, however users without a background in programming have reported difficulties in using it. Therefore, we developed a graphical user interface (GUI) engine to make the use of the HL7 IE more convenient. Methods The GUI engine was directly connected with the HL7 IE to handle the HL7 version 2.x messages. Furthermore, the information exchange rules (called the mapping data), represented by a conceptual graph in the GUI engine, were transformed into program objects that were made available to the HL7 IE; the mapping data were stored as binary files for reuse. The usefulness of the GUI engine was examined through information exchange tests between an HL7 version 2.x message and a health information database system. Results Users could easily create HL7 version 2.x messages by creating a conceptual graph through the GUI engine without requiring assistance from programmers. In addition, time could be saved when creating new information exchange rules by reusing the stored mapping data. Conclusions The GUI engine was not able to incorporate information types (e.g., extensible markup language, XML) other than the HL7 version 2.x messages and the database, because it was designed exclusively for the HL7 IE protocol. However, in future work, by including additional parsers to manage XML-based information such as Continuity of Care Documents (CCD) and Continuity of Care Records (CCR), we plan to ensure that the GUI engine will be more widely accessible for the health field. PMID:22259723

The Development of a Graphical User Interface Engine for the Convenient Use of the HL7 Version 2.x Interface Engine.

PubMed

Kim, Hwa Sun; Cho, Hune; Lee, In Keun

2011-12-01

The Health Level Seven Interface Engine (HL7 IE), developed by Kyungpook National University, has been employed in health information systems, however users without a background in programming have reported difficulties in using it. Therefore, we developed a graphical user interface (GUI) engine to make the use of the HL7 IE more convenient. The GUI engine was directly connected with the HL7 IE to handle the HL7 version 2.x messages. Furthermore, the information exchange rules (called the mapping data), represented by a conceptual graph in the GUI engine, were transformed into program objects that were made available to the HL7 IE; the mapping data were stored as binary files for reuse. The usefulness of the GUI engine was examined through information exchange tests between an HL7 version 2.x message and a health information database system. Users could easily create HL7 version 2.x messages by creating a conceptual graph through the GUI engine without requiring assistance from programmers. In addition, time could be saved when creating new information exchange rules by reusing the stored mapping data. The GUI engine was not able to incorporate information types (e.g., extensible markup language, XML) other than the HL7 version 2.x messages and the database, because it was designed exclusively for the HL7 IE protocol. However, in future work, by including additional parsers to manage XML-based information such as Continuity of Care Documents (CCD) and Continuity of Care Records (CCR), we plan to ensure that the GUI engine will be more widely accessible for the health field.

Observation of the decay B-->J/psietaK and search for X(3872)-->J/psieta.

PubMed

Aubert, B; Barate, R; Boutigny, D; Couderc, F; Gaillard, J M; Hicheur, A; Karyotakis, Y; Lees, J P; Tisserand, V; Zghiche, A; Palano, A; Pompili, A; Chen, J C; Qi, N D; Rong, G; Wang, P; Zhu, Y S; Eigen, G; Ofte, I; Stugu, B; Abrams, G S; Borgland, A W; Breon, A B; Brown, D N; Button-Shafer, J; Cahn, R N; Charles, E; Day, C T; Gill, M S; Gritsan, A V; Groysman, Y; Jacobsen, R G; Kadel, R W; Kadyk, J; Kerth, L T; Kolomensky, Yu G; Kukartsev, G; LeClerc, C; Levi, M E; Lynch, G; Mir, L M; Oddone, P J; Orimoto, T J; Pripstein, M; Roe, N A; Ronan, M T; Shelkov, V G; Telnov, A V; Wenzel, W A; Ford, K; Harrison, T J; Hawkes, C M; Morgan, S E; Watson, A T; Watson, N K; Fritsch, M; Goetzen, K; Held, T; Koch, H; Lewandowski, B; Pelizaeus, M; Steinke, M; Boyd, J T; Chevalier, N; Cottingham, W N; Kelly, M P; Latham, T E; Wilson, F F; Abe, K; Cuhadar-Donszelmann, T; Hearty, C; Mattison, T S; McKenna, J A; Thiessen, D; Kyberd, P; Teodorescu, L; Blinov, V E; Bukin, A D; Druzhinin, V P; Golubev, V B; Ivanchenko, V N; Kravchenko, E A; Onuchin, A P; Serednyakov, S I; Skovpen, Yu I; Solodov, E P; Yushkov, A N; Best, D; Bruinsma, M; Chao, M; Eschrich, I; Kirkby, D; Lankford, A J; Mandelkern, M; Mommsen, R K; Roethel, W; Stoker, D P; Buchanan, C; Hartfiel, B L; Gary, J W; Shen, B C; Wang, K; del Re, D; Hadavand, H K; Hill, E J; MacFarlane, D B; Paar, H P; Rahatlou, Sh; Sharma, V; Berryhill, J W; Campagnari, C; Dahmes, B; Levy, S L; Long, O; Lu, A; Mazur, M A; Richman, J D; Verkerke, W; Beck, T W; Eisner, A M; Heusch, C A; Lockman, W S; Schalk, T; Schmitz, R E; Schumm, B A; Seiden, A; Spradlin, P; Williams, D C; Wilson, M G; Albert, J; Chen, E; Dubois-Felsmann, G P; Dvoretskii, A; Hitlin, D G; Narsky, I; Piatenko, T; Porter, F C; Ryd, A; Samuel, A; Yang, S; Jayatilleke, S; Mancinelli, G; Meadows, B T; Sokoloff, M D; Abe, T; Blanc, F; Bloom, P; Chen, S; Clark, P J; Ford, W T; Nauenberg, U; Olivas, A; Rankin, P; Smith, J G; van Hoek, W C; Zhang, L; Harton, J L; Hu, T; Soffer, A; Toki, W H; Wilson, R J; Zeng, Q; Altenburg, D; Brandt, T; Brose, J; Colberg, T; Dickopp, M; Feltresi, E; Hauke, A; Lacker, H M; Maly, E; Müller-Pfefferkorn, R; Nogowski, R; Otto, S; Schubert, J; Schubert, K R; Schwierz, R; Spaan, B; Bernard, D; Bonneaud, G R; Brochard, F; Grenier, P; Thiebaux, Ch; Vasileiadis, G; Verderi, M; Bard, D J; Khan, A; Lavin, D; Muheim, F; Playfer, S; Andreotti, M; Azzolini, V; Bettoni, D; Bozzi, C; Calabrese, R; Cibinetto, G; Luppi, E; Negrini, M; Sarti, A; Treadwell, E; Baldini-Ferroli, R; Calcaterra, A; de Sangro, R; Finocchiaro, G; Patteri, P; Piccolo, M; Zallo, A; Buzzo, A; Capra, R; Contri, R; Crosetti, G; Lo Vetere, M; Macri, M; Monge, M R; Passaggio, S; Patrignani, C; Robutti, E; Santroni, A; Tosi, S; Bailey, S; Brandenburg, G; Morii, M; Won, E; Dubitzky, R S; Langenegger, U; Bhimji, W; Bowerman, D A; Dauncey, P D; Egede, U; Gaillard, J R; Morton, G W; Nash, J A; Taylor, G P; Grenier, G J; Lee, S J; Mallik, U; Cochran, J; Crawley, H B; Lamsa, J; Meyer, W T; Prell, S; Rosenberg, E I; Yi, J; Davier, M; Grosdidier, G; Höcker, A; Laplace, S; Le Diberder, F; Lepeltier, V; Lutz, A M; Petersen, T C; Plaszczynski, S; Schune, M H; Tantot, L; Wormser, G; Cheng, C H; Lange, D J; Simani, M C; Wright, D M; Bevan, A J; Coleman, J P; Fry, J R; Gabathuler, E; Gamet, R; Kay, M; Parry, R J; Payne, D J; Sloane, R J; Touramanis, C; Back, J J; Harrison, P F; Mohanty, G B; Brown, C L; Cowan, G; Flack, R L; Flaecher, H U; George, S; Green, M G; Kurup, A; Marker, C E; McMahon, T R; Ricciardi, S; Salvatore, F; Vaitsas, G; Winter, M A; Brown, D; Davis, C L; Allison, J; Barlow, N R; Barlow, R J; Hart, P A; Hodgkinson, M C; Lafferty, G D; Lyon, A J; Williams, J C; Farbin, A; Hulsbergen, W D; Jawahery, A; Kovalskyi, D; Lae, C K; Lillard, V; Roberts, D A; Blaylock, G; Dallapiccola, C; Flood, K T; Hertzbach, S S; Kofler, R; Koptchev, V B; Moore, T B; Saremi, S; Staengle, H; Willocq, S; Cowan, R; Sciolla, G; Taylor, F; Yamamoto, R K; Mangeol, D J J; Patel, P M; Robertson, S H; Lazzaro, A; Palombo, F; Bauer, J M; Cremaldi, L; Eschenburg, V; Godang, R; Kroeger, R; Reidy, J; Sanders, D A; Summers, D J; Zhao, H W; Brunet, S; Côté, D; Taras, P; Nicholson, H; Cartaro, C; Cavallo, N; Fabozzi, F; Gatto, C; Lista, L; Monorchio, D; Paolucci, P; Piccolo, D; Sciacca, C; Baak, M; Raven, G; Wilden, L; Jessop, C P; LoSecco, J M; Gabriel, T A; Allmendinger, T; Brau, B; Gan, K K; Honscheid, K; Hufnagel, D; Kagan, H; Kass, R; Pulliam, T; Ter-Antonyan, R; Wong, Q K; Brau, J; Frey, R; Igonkina, O; Potter, C T; Sinev, N B; Strom, D; Torrence, E; Colecchia, F; Dorigo, A; Galeazzi, F; Margoni, M; Morandin, M; Posocco, M; Rotondo, M; Simonetto, F; Stroili, R; Tiozzo, G; Voci, C; Benayoun, M; Briand, H; Chauveau, J; David, P; de la Vaissière, Ch; Del Buono, L; Hamon, O; John, M J J; Leruste, Ph; Ocariz, J; Pivk, M; Roos, L; T'Jampens, S; Therin, G; Manfredi, P F; Re, V; Behera, P K; Gladney, L; Guo, Q H; Panetta, J; Anulli, F; Biasini, M; Peruzzi, I M; Pioppi, M; Angelini, C; Batignani, G; Bettarini, S; Bondioli, M; Bucci, F; Calderini, G; Carpinelli, M; Del Gamba, V; Forti, F; Giorgi, M A; Lusiani, A; Marchiori, G; Martinez-Vidal, F; Morganti, M; Neri, N; Paoloni, E; Rama, M; Rizzo, G; Sandrelli, F; Walsh, J; Haire, M; Judd, D; Paick, K; Wagoner, D E; Danielson, N; Elmer, P; Lu, C; Miftakov, V; Olsen, J; Smith, A J S; Varnes, E W; Bellini, F; Cavoto, G; Faccini, R; Ferrarotto, F; Ferroni, F; Gaspero, M; Li Gioi, L; Mazzoni, M A; Morganti, S; Pierini, M; Piredda, G; Tehrani, F Safai; Voena, C; Christ, S; Wagner, G; Waldi, R; Adye, T; De Groot, N; Franek, B; Geddes, N I; Gopal, G P; Olaiya, E O; Xella, S M; Aleksan, R; Emery, S; Gaidot, A; Ganzhur, S F; Giraud, P F; Hamel de Monchenault, G; Kozanecki, W; Langer, M; Legendre, M; London, G W; Mayer, B; Schott, G; Vasseur, G; Yèche, Ch; Zito, M; Purohit, M V; Weidemann, A W; Yumiceva, F X; Aston, D; Bartoldus, R; Berger, N; Boyarski, A M; Buchmueller, O L; Convery, M R; Cristinziani, M; De Nardo, G; Dong, D; Dorfan, J; Dujmic, D; Dunwoodie, W; Elsen, E E; Field, R C; Glanzman, T; Gowdy, S J; Hadig, T; Halyo, V; Hryn'ova, T; Innes, W R; Kelsey, M H; Kim, P; Kocian, M L; Leith, D W G S; Libby, J; Luitz, S; Luth, V; Lynch, H L; Marsiske, H; Messner, R; Muller, D R; O'Grady, C P; Ozcan, V E; Perazzo, A; Perl, M; Petrak, S; Ratcliff, B N; Roodman, A; Salnikov, A A; Schindler, R H; Schwiening, J; Simi, G; Snyder, A; Soha, A; Stelzer, J; Su, D; Sullivan, M K; Va'vra, J; Wagner, S R; Weaver, M; Weinstein, A J R; Wisniewski, W J; Wittgen, M; Wright, D H; Young, C C; Burchat, P R; Edwards, A J; Meyer, T I; Petersen, B A; Roat, C; Ahmed, S; Alam, M S; Ernst, J A; Saeed, M A; Saleem, M; Wappler, F R; Bugg, W; Krishnamurthy, M; Spanier, S M; Eckmann, R; Kim, H; Ritchie, J L; Satpathy, A; Schwitters, R F; Izen, J M; Kitayama, I; Lou, X C; Ye, S; Bianchi, F; Bona, M; Gallo, F; Gamba, D; Borean, C; Bosisio, L; Cossutti, F; Della Ricca, G; Dittongo, S; Grancagnolo, S; Lanceri, L; Poropat, P; Vitale, L; Vuagnin, G; Panvini, R S; Banerjee, Sw; Brown, C M; Fortin, D; Jackson, P D; Kowalewski, R; Roney, J M; Band, H R; Dasu, S; Datta, M; Eichenbaum, A M; Hollar, J J; Johnson, J R; Kutter, P E; Li, H; Liu, R; Di Lodovico, F; Mihalyi, A; Mohapatra, A K; Pan, Y; Prepost, R; Sekula, S J; Tan, P; von Wimmersperg-Toeller, J H; Wu, J; Wu, S L; Yu, Z; Neal, H

2004-07-23

We report the observation of the B meson decay B+/- -->J/psietaK+/- and evidence for the decay B0-->J/psietaK0S, using 90 x 10(6) BB; events collected at the Upsilon(4S) resonance with the BABAR detector at the SLAC PEP-II e+e- asymmetric-energy storage ring. We obtain branching fractions of B(B+/- -->J/psietaK+/-) = [10.8 +/- 2.3(stat) +/- 2.4(syst)] x 10(-5) and B(B0-->J/psietaK0S) = [8.4 +/- 2.6(stat) +/- 2.7(syst)] x 10(-5). We search for the new narrow mass state, the X(3872), recently reported by the Belle Collaboration, in the decay B+/- -->X(3872)K+/-,X(3872)-->J/psieta and determine an upper limit of B[B +/- -->X(3872)K+/- -->J/psietaK+/-] < 7.7 x 10(-6) at 90% confidence level. Copyright 2004 The American Physical Society

Shallow-Water Reverberation

DTIC Science & Technology

2000-09-30

Shallow- Water Reverberation J. X. Zhou School of Mechanical Engineering Georgia Institute of Technology Atlanta, Georgia 30332-0405 phone: (404) 894...6793 fax: (404) 894-7790 e-mail: jixun.zhou@me.gatech.edu Award Number: N00014-97-1-0170 Thrust Category: Shallow- Water Acoustics LONG-TERM GOALS...The long-term goals of this work are: to develop a theoretical model for predicting the reverberation in shallow water , to derive both small-angle

Last SSME test on A-1

NASA Image and Video Library

2006-09-29

The Stennis Space Center conducted the final space shuttle main engine test on its A-1 Test Stand Friday. The A-1 Test Stand was the site of the first test on a shuttle main engine in 1975. Stennis will continue testing shuttle main engines on its A-2 Test Stand through the end of the Space Shuttle Program in 2010. The A-1 stand begins a new chapter in its operational history in October. It will be temporarily decommissioned to convert it for testing the J-2X engine, which will power the upper stage of NASA's new crew launch vehicle, the Ares I. Although this ends the stand's work on the Space Shuttle Program, it will soon be used for the rocket that will carry America's next generation human spacecraft, Orion.

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A B C D E F G H I J K L M N O P Q R S T U V W X Y Z D2L PAWS Email My UW-System About UWM UWM Jobs D2L PAWS Email My UW-System University of Wisconsin-Milwaukee College ofEngineering & Olympiad Girls Who Code Club FIRST Tech Challenge NSF I-Corps Site of Southeastern Wisconsin UW-Milwaukee

Classification of Corrosion Defects in NiAl Bronze Through Image Analysis

DTIC Science & Technology

2010-01-01

the sub-band coefficient matrix as: EntropypðkÞ ¼ X i X j jCpk;ði;jÞj 2 log jCpk;ði;jÞj 2 ð2Þ EnergypðkÞ ¼ X i X j jCpk;ði;jÞj 2 ð3Þ where...Wharton, R.C. Barik , G. Kear, R.J.K. Wood, K.R. Stokes, F.C. Walsh, The corrosion of nickel–aluminum bronze in seawater, Corros. Sci. 47 (2005) 3336...corrosion under fatigue conditions, J . Aircraft (7–8) (2009) 1253–1259. [10] H.S. Isaacs, Initiation of stress corrosion cracking of sensitized type

Enhanced Condensation of R-113 on a Small Bundle of Horizontal Tubes

DTIC Science & Technology

1991-12-01

Anthony J. l lcaley, Ch an )epartment of Mechanic’ Engineering ABSTRACT Condensation of R-113 was studied using an evaporator/condenser test platform. The...IF 7825 FOR I=1 TO Npair5 7830 ENTER @File;Xa,Ya 7835 S×=Sx+Xa 7840 Sy=Sy+Ya 7845 5x2=Sx2+XaŖ 7850 Sxy-Sxy+Xa*Ya 7855 X=(Xa-Xmin)*Sfx 7860 Y-(Ya-Ymin...9th Int. Heat Transfer Conf., Vol. 3, pp. 15-20, 1990. 33. Fujii, T., Wang, W. Ch ., Koyama, Sh. and Y. Shimizu, Heat Transfer Enhancement for Gravity

78 FR 49109 - Airworthiness Directives; Pratt & Whitney Canada Corp. Turboprop Engines

Federal Register 2010, 2011, 2012, 2013, 2014

2013-08-13

..., J4G 1A1; phone: 800-268-8000; fax: 450-647-2888; Internet: www.pwc.ca. You may view this service... installation; or (2) Perform a one-time X-ray inspection of the affected first- stage PT blades, using...-268-8000; fax: 450-647-2888; Internet: www.pwc.ca. (4) You may view this service information at the...

Integrated System Health Management (ISHM) for Test Stand and J-2X Engine: Core Implementation

NASA Technical Reports Server (NTRS)

Figueroa, Jorge F.; Schmalzel, John L.; Aguilar, Robert; Shwabacher, Mark; Morris, Jon

2008-01-01

ISHM capability enables a system to detect anomalies, determine causes and effects, predict future anomalies, and provides an integrated awareness of the health of the system to users (operators, customers, management, etc.). NASA Stennis Space Center, NASA Ames Research Center, and Pratt & Whitney Rocketdyne have implemented a core ISHM capability that encompasses the A1 Test Stand and the J-2X Engine. The implementation incorporates all aspects of ISHM; from anomaly detection (e.g. leaks) to root-cause-analysis based on failure mode and effects analysis (FMEA), to a user interface for an integrated visualization of the health of the system (Test Stand and Engine). The implementation provides a low functional capability level (FCL) in that it is populated with few algorithms and approaches for anomaly detection, and root-cause trees from a limited FMEA effort. However, it is a demonstration of a credible ISHM capability, and it is inherently designed for continuous and systematic augmentation of the capability. The ISHM capability is grounded on an integrating software environment used to create an ISHM model of the system. The ISHM model follows an object-oriented approach: includes all elements of the system (from schematics) and provides for compartmentalized storage of information associated with each element. For instance, a sensor object contains a transducer electronic data sheet (TEDS) with information that might be used by algorithms and approaches for anomaly detection, diagnostics, etc. Similarly, a component, such as a tank, contains a Component Electronic Data Sheet (CEDS). Each element also includes a Health Electronic Data Sheet (HEDS) that contains health-related information such as anomalies and health state. Some practical aspects of the implementation include: (1) near real-time data flow from the test stand data acquisition system through the ISHM model, for near real-time detection of anomalies and diagnostics, (2) insertion of the J-2X predictive model providing predicted sensor values for comparison with measured values and use in anomaly detection and diagnostics, and (3) insertion of third-party anomaly detection algorithms into the integrated ISHM model.

An Empirical Method For Estimating the Effect of Ground Proximity on the Jet-Induced Lift of V/STOL Aircraft Employing Rectangular Jets.

DTIC Science & Technology

1981-08-01

OFFICE NAME AND ADDRESS 12. -A&PORT DATE Naval Air Development Center jAug Ŝ 1 Warmninster, PA 18974 -1j NUMBER OF PAGES 14 MONITORING AGENCY NAME...vii NOMENCLATURE x 1.0 INTRODUCTION I 2.0 METHODOLOGY DEVELOPMENT 4 2.1 SUCKDOWN 5 2.1.1 FREE-AIR SUCKDOWN 5 2.1.2 ALTITUDE DEPENDENT SUCKDOWN 5 2.2...Width (Figures 2.3-2 and 2.3-4) Superscripts II, 11, IV Referring to 2, 3 or 4 Nozzle Planforms X NADC 79298-60 1.0 INTRODUCTION The flow field in the

Kenneth J. Szalai

NASA Technical Reports Server (NTRS)

1991-01-01

Kenneth J. Szalai is Director of the NASA Hugh L. Dryden Flight Research Center, Edwards, California. He was named Center director in January 1994 assuming the position on March 1, 1994. Before that, he served as Ames-Dryden Deputy Center Director and Director of the Dryden Flight Research Facility from December 3, 1990, to March 1, 1994. Ken began his NASA career at Dryden in 1964 following graduation from the University of Wisconsin with a bachelor of science degree in electrical engineering. He also received a master of science degree in mechanical engineering from the University of Southern California in 1970. Szalai was principal investigator on the F-8 Digital Fly-By-Wire program, which successfully flew the first aircraft equipped with a digital electronic flight control system without any mechanical reversion capability. He has worked in various technical and management positions on such programs as the F-111 IPCS, AFTI/F-16, HiMAT, F-15 DEEC, F-15 HIDEC, X-29, X-31, F-16XL Laminar Flow, Space Shuttle Orbiter, Pathfinder Solar Powered Aircraft, SR-71 Sonic Boom, F-15 and MD-11 Propulsion Controlled Aircraft, X-33, and X-38. Szalai has authored over 25 papers and reports and has been a lecturer for the NATO Advisory Group for Aeronautical Research and Development (AGARD). He has served on various technical committees and subcommittees for the American Institute of Aeronautics and Astronautics (AIAA) and Society of Automotive Engineers (SAE). Szalai, a Fellow of the AIAA, also served on the National Academy of Science's 'Aeronautics-2000' study. Among the awards Szalai has received are NASA's Exceptional Service Medal, the NASA Outstanding Leadership Medal, and the Presidential Meritorious and Distinguished Rank Awards.

CrossTalk: The Journal of Defense Software Engineering. Volume 18, Number 2

DTIC Science & Technology

2005-02-01

Richard J. Adams , Sergio Alvarado, Suellen Eslinger, and Joanne Tagami all with The Aerospace Corporation, and Scott A. Whitmire at ODS Software...Kiczales, G., and M. Kersten . “Show Me the Structure.” Software Develop- ment Apr. 2000. Notes 1. Please note that the M1-M11 number- ing of concepts did...VA: Integrated Computer Engineering, Inc., 2 Aug. 2000 (http://www.spmn.com). 3 Adams , Richard J., Suellen Eslinger, Karen L. Owens, and Mary A. Rich

Development of a Noninterference Technique for Measurement of Turbine Engine Compressor Blade Stress

DTIC Science & Technology

1980-06-01

TECHNIQUE FOR MEASUREMENT OF TURBINE ENGINE COMPRESSOR BLADE STRESS 7 A U T H O R ( s ) P . E. M c C a r t y a n d J . W. Thompson , J r...e a e a ~ and tdentJ~ by b|ock numbe~ A noninterference technique for measuring stress in compressor blades of turbine engines is being developed...43 4 AEDC-TR-79-78 1.0 INTRODUCTION 1.1 BACKGROUND Compressor rotor blades in turbojet engines are subjected to

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.

Numerical Modeling of the Nearshore Region.

DTIC Science & Technology

1982-06-01

Model 10 f = 0.01 i0 _ -- 2 Linear’Model f = 0.015 - 3 Linear Modelf 0 .02 EN 41 Data Set 1 600- U 40 4 -C 20 T Longshore Current Velocity V (r/sec...IX CZ Oxn 0 00 Cw LU 39’L 0f C:1- 3 LU x 4 3 00 0~ ~ -L U - 3 0 0 f, c0 ID - ox (9 o. 0 o4, n -i u x --- C- 0 cc 1*j.i Ix~ > A a, 0 r- w-0 4 1 En 00U...r AD-AL1A 518 DELAWARE UN IV NEWARK DEPT OF CIVIL ENGINEERING F/G 8/ 3 NUMER ICAL MODELI NG OF THE NEARS" ORE REGION U) JUN 82 j T KIRBY, R A OALR

Diode Laser-Based Detection of Combustor Instabilities with Application to a Scramjet Engine

DTIC Science & Technology

2010-02-01

Exhibit, Reno, NV, January 9–12, 2006 . [16] G. Rieker, H. Li, X. Liu, et al ., Proc. Combust. Inst. 31 (2007) 3041–3049. [17] H. Li, G.B. Rieker, X...Cincinnati, OH, July 2006 . [24] M. Gruber, J. Donbar, K. Jackson, et al ., J. Propul. Power 17 (2001) 1296–1304. ...in inlet unstart, which causes a significant decrease in captured air massute. Published by Elsevier Inc. All rights reserved. 832 G.B. Rieker et al

Education of Sustainability Engineers

NASA Astrophysics Data System (ADS)

Oleschko, K.; Perrier, E.; Tarquis, A. M.

2010-05-01

It's not the same to educate the sustainable engineers as to prepare the engineers of Sustainability. In the latter case all existing methods of inventive creativity (Altshuller, 1988) should be introduced in the teaching and research processes in order to create a culture of innovation at a group. The Theory of Inventing Problem Solving (TRIZ) is based on the pioneer works of Genrich Altshuller (1988) and his associated. Altshuller reviewed over 2 million patents beginning in 1946 (Orlov, 2006) and developed the Laws of Evolution of Technological Systems; An Algorithm for Inventive Problem Solving (ARIZ); forty typical Techniques for Overcoming System Conflicts (TOSC); a system of 76 Standard Approaches to Inventive Problems (Standards) etc. (Fey and Rivin, 1997). Nowadays, "a theory and constructive instrument package for the controlled synthesis of ideas and the focused transformation of the object to be improved" (Orlov, 2006) are used with high efficacy as the teaching and thinking inventive problem-solving methods in some high schools (Barak and Mesika, 2006; Sokoi et al., 2008) as well as a framework for research (Moehrle, 2005) in construction industry (Zhang et al., 2009); chemical engineering (Cortes Robles et al., 2008) etc. In 2005 US Congress passed the innovation act with the intent of increasing research investment (Gupta, 2007), while China had included inventive principles of TRIZ in strategy and decision making structure design (Kai Yang, 2010). The integrating of TRIZ into eco-innovation diminishes the common conflicts between technology and environment (Chang and Chen, 2004). In our presentation we show discuss some examples of future patents elaborated by the master degree students of Queretaro University, Faculty of Engineering, Mexico using TRIZ methods. References 1. Altshuller, G., 1988. Creativity as an Exact Science. Gordon and Breach, New York. 2. Chang, Hsiang-Tang and Chen, Jahau Lewis, 2004. The conflict-problem-solving CAD software integrating TRIZ into eco-innovation. Advances in Engineering Software, 35: 553-566. 3. Cortes Robles, G., Negny, S. and Le Lann, J.M., 2008. Case-based reasoning and TRIZ: A coupling for innovative conception in Chemical Engineering. Chemical Engineering and Processing: Process Intensification, 48 (1): 239-249. 4. Gupta, P., 2007. Real Innovation Commentary. http://www. RealInnovation.com. 5. Kai Yang, 2010. Inventive principles of TRIZ with Chinás 36 strategies. TRIZ J., 1-20. 6. Moehrle, M. G., 2005. What is TRIZ? From conceptual basics to a framework for research. Social Science research Network, http://papers.ssrn.com/sol13/papers.cfm?abstract_id=674062. 7. Orlov, M., 2006. Inventive Thinking through TRIZ. A practical Guide, Springer, Berlin, 351. 8. Zhang, X., Mao, X. and AbouRizk, S.M, 2009. Developing a knowledge management system for improved value engineering practices in the construction industry. Automation in Construction, 18 (6): 777-789. 9. Sokol, A., Oget, D., Sonntag, M. and Khomenko, N., 2008. The development of inventive thinking skills in the upper secondary language classroom. Thinking Skills and Creativity, 3 (1): 34-46.

Higher-order multipole amplitudes in charmonium radiative transitions

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

Artuso, M.; Blusk, S.; Khalil, S.

2009-12-01

Using 24x10{sup 6} {psi}{sup '}{identical_to}{psi}(2S) decays in CLEO-c, we have searched for higher multipole admixtures in electric-dipole-dominated radiative transitions in charmonia. We find good agreement between our data and theoretical predictions for magnetic quadrupole (M2) amplitudes in the transitions {psi}{sup '}{yields}{gamma}{chi}{sub c1,c2} and {chi}{sub c1,c2}{yields}{gamma}J/{psi}, in striking contrast to some previous measurements. Let b{sub 2}{sup J} and a{sub 2}{sup J} denote the normalized M2 amplitudes in the respective aforementioned decays, where the superscript J refers to the angular momentum of the {chi}{sub cJ}. By performing unbinned maximum likelihood fits to full five-parameter angular distributions, we found the following values ofmore » M2 admixtures for J{sub {chi}}=1: a{sub 2}{sup J={sup 1}}=(-6.26{+-}0.63{+-}0.24)x10{sup -2} and b{sub 2}{sup J={sup 1}}=(2.76{+-}0.73{+-}0.23)x10{sup -2}, which agree well with theoretical expectations for a vanishing anomalous magnetic moment of the charm quark. For J{sub {chi}}=2, if we fix the electric octupole (E3) amplitudes to zero as theory predicts for transitions between charmonium S states and P states, we find a{sub 2}{sup J={sup 2}}=(-9.3{+-}1.6{+-}0.3)x10{sup -2} and b{sub 2}{sup J={sup 2}}=(1.0{+-}1.3{+-}0.3)x10{sup -2}. If we allow for E3 amplitudes we find, with a four-parameter fit, a{sub 2}{sup J={sup 2}}=(-7.9{+-}1.9{+-}0.3)x10{sup -2}, b{sub 2}{sup J={sup 2}}=(0.2{+-}1.4{+-}0.4)x10{sup -2}, a{sub 3}{sup J={sup 2}}=(1.7{+-}1.4{+-}0.3)x10{sup -2}, and b{sub 3}{sup J={sup 2}}=(-0.8{+-}1.2{+-}0.2)x10{sup -2}. We determine the ratios a{sub 2}{sup J={sup 1}}/a{sub 2}{sup J={sup 2}}=0.67{sub -0.13}{sup +0.19} and a{sub 2}{sup J={sup 1}}/b{sub 2}{sup J={sup 1}}=-2.27{sub -0.99}{sup +0.57}, where the theoretical predictions are independent of the charmed quark magnetic moment and are a{sub 2}{sup J={sup 1}}/a{sub 2}{sup J={sup 2}}=0.676{+-}0.071 and a{sub 2}{sup J={sup 1}}/b{sub 2}{sup J={sup 1}}=-2.27{+-}0.16.« less

Search for charmonium and charmoniumlike states in {Upsilon}(2S) radiative decays

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

Wang, X. L.; Yuan, C. Z.; Wang, P.

2011-10-01

Using a sample of 158x10{sup 6} {Upsilon}(2S) events collected with the Belle detector, charmonium and charmoniumlike states with even charge parity are searched for in {Upsilon}(2S) radiative decays. No significant {chi}{sub cJ} or {eta}{sub c} signal is observed, and the following upper limits at 90% confidence level (C. L.) are obtained: B({Upsilon}(2S){yields}{gamma}{chi}{sub c0})<1.0x10{sup -4}, B({Upsilon}(2S){yields}{gamma}{chi}{sub c1})<3.6x10{sup -6}, B({Upsilon}(2S){yields}{gamma}{chi}{sub c2})<1.5x10{sup -5}, and B({Upsilon}(2S){yields}{gamma}{eta}{sub c})<2.7x10{sup -5}. No significant signal of any charmoniumlike state is observed, and we obtain the limits B({Upsilon}(2S){yields}{gamma}X(3872))xB(X(3872){yields}{pi}{sup +}{pi}{sup -}J/{psi})<0.8x10{sup -6}, B({Upsilon}(2S){yields}{gamma}X(3872))x B(X(3872){yields}{pi}{sup +}{pi}{sup -}{pi}{sup 0}J/{psi})<2.4x10{sup -6}, B({Upsilon}(2S){yields}{gamma}X(3915))xB(X(3915){yields}{omega}J/{psi})<2.8x10{sup -6}, B({Upsilon}(2S){yields}{gamma}Y(4140))xB(Y(4140){yields}{phi}J/{psi}))<1.2x10{sup -6}, and B({Upsilon}(2S){yields}{gamma}X(4350))xB(X(4350){yields}{phi}J/{psi}))<1.3x10{sup -6} at 90% C. L.

Deriving Link Travel-Time Distributions via Stochastic Speed Processes

DTIC Science & Technology

2004-02-01

general, an exact expression for the inverse transform is available when Equation (9) is a vector of rational functions in both of the complex variables...Otherwise, recovery of the original function is accom- plished through the inverse transform f t= 1 2(j ∫ c+j c−j estf ∗s ds (13) which is usually...given by f x t = f ∗s1 s2 = ∫ 0 ∫ 0 e−s1x+s2tf x t dx dt (14) with inverse transform f x t = 1 4(2 ∫ c1+j c1−j ∫ c2+j c2−j e

United States Air Force Summer Research Program 1991. Summer Faculty Research Program (SFRP) Reports. Volume 4. Rome Laboratory, Arnold Engineering Development Center, F. J. Seiler Research Laboratory

DTIC Science & Technology

1992-01-09

Herschfelder, J. 0., C . F. Curtis, and R. B. Bird, "Molecular Theory of Gases and Liquids", John Willey and Sons, New York, (1954), Chs. 7 and 8. 12...AL iryLt’ AND SLOTME 5- FUIING NUERS 1991 Sumn~er FAculty Resezrzi! ?ro-rz~ (SFBZF) Volne 2SbV0d. 4 F496202-4:4#- C -CO076 MtrGary_ Soore ___________ 7...Engineering Tools for Parallel Software Development Dr. John Antonio 2 (Report Not Available at this Time) Dr. Abdul Aziz Bhatti 3 A Taxonomy for

J-2 Engine ready to go into test stand

NASA Technical Reports Server (NTRS)

1965-01-01

Two technicians watch carefully as cables prepare to lift a J-2 engine into a test stand. The J-2 powered the second stage and the third stage of the Saturn V moon rocket. The towering 363-foot Saturn V was a multi-stage, multi-engine launch vehicle standing taller than the Statue of Liberty. Altogether, the Saturn V engines produced as much power as 85 Hoover Dams.

Temperature- and Phase-Dependent Phonon Renormalization in 1T'-MoS2.

PubMed

Tan, Sherman Jun Rong; Sarkar, Soumya; Zhao, Xiaoxu; Luo, Xin; Luo, Yong Zheng; Poh, Sock Mui; Abdelwahab, Ibrahim; Zhou, Wu; Venkatesan, Thirumalai; Chen, Wei; Quek, Su Ying; Loh, Kian Ping

2018-05-22

Polymorph engineering of 2H-MoS 2 , which can be achieved by alkali metal intercalation to obtain either the mixed 2H/1T' phases or a homogeneous 1T' phase, has received wide interest recently, since this serves as an effective route to tune the electrical and catalytic properties of MoS 2 . As opposed to an idealized single crystal-to-single crystal phase conversion, the 2H to 1T' phase conversion results in crystal domain size reduction as well as strained lattices, although how these develop with composition is not well understood. Herein, the evolution of the phonon modes in Li-intercalated 1T'-MoS 2 (Li x MoS 2 ) are investigated as a function of different 1T'-2H compositions. We observed that the strain evolution in the mixed phases is revealed by the softening of four Raman modes, B g ( J 1 ), A g ( J 3 ), E 1 2g , and A 1g , with increasing 1T' phase composition. Additionally, the first-order temperature coefficients of the 1T' phonon mode vary linearly with increasing 1T' composition, which is explained by increased electron-phonon and strain-phonon coupling.

Validation of a 2.5D CFD model for cylindrical gas–solids fluidized beds

DOE PAGES

Li, Tingwen

2015-09-25

The 2.5D model recently proposed by Li et al. (Li, T., Benyahia, S., Dietiker, J., Musser, J., and Sun, X., 2015. A 2.5D computational method to simulate cylindrical fluidized beds. Chemical Engineering Science. 123, 236-246.) was validated for two cylindrical gas-solids bubbling fluidized bed systems. Different types of particles tested under various flow conditions were simulated using the traditional 2D model and the 2.5D model. Detailed comparison against the experimental measurements on solid concentration and velocity were conducted. Comparing to the traditional Cartesian 2D flow simulation, the 2.5D model yielded better agreement with the experimental data especially for the solidmore » velocity prediction in the column wall region.« less

United States Air Force Statistical Digest, Fiscal Year 1951. Sixth Edition

DTIC Science & Technology

1952-11-18

2 2 2 Mili tary Air Transport Service Squadron - Total 2 2 g 2 g g 2 s 1 ! 1 ! , curce a Qrganhat10n geccr- de (AFASC-6F)j oenerea orden from Major...STATISTICAL SERVICES DeS COMPTROLLER", USAF WASHINGTON, DC .J DEPARTMENT OF THE AIR FORCE WASHINGTON, 20 SEPTEMBER 1948 Am FORCE REGULATION) NO. 5-24...AND LUBES. 223 PART V III STOCKPILING •. 235 PART IX INDUSTRIAL RESERVE’ 241 PART X TRANSPORTATION ..• Z8S PART X I RESEARCH AND DEVELOPMENT 2𔄁 t

Excimer Laser Research

DTIC Science & Technology

1976-10-01

X> X ^^ X X E o lmm X X X X X > J Ä2 NX x xs 10 n N(P) X...to the cell through a stainless steel valve. The crystals and sample cylinder were repeatedly allowed to outgas at room temperature (under vacuum... 350 (1975). 3. J.J. Ewing and C.A. Brau, Appl. Phys. Lett. 27, 557(1975). 4. J.J. Ewing and C.A. Brau, Phys. Rev. A12, 129(1975). 5

Saturn Apollo Program

NASA Image and Video Library

1960-01-01

This chart is an illustration of J-2 Engine characteristics. A cluster of five J-2 engines powered the Saturn V S-II (second) stage with each engine providing a thrust of 200,000 pounds. A single J-2 engine powered the S-IVB stage, the Saturn IB second stage, and the Saturn V third stage. The engine was uprated to provide 230,000 pounds of thrust for the fourth Apollo Saturn V flight and subsequent missions. Burning liquid hydrogen as fuel and using liquid oxygen as the oxidizer, the cluster of five J-2 engines for the S-II stage burned over one ton of propellant per second, during about 6 1/2 minutes of operation, to take the vehicle to an altitude of about 108 miles and a speed of near orbital velocity, about 17,400 miles per hour.

A simple measuring technique of surface flow velocity to analyze the behavior of velocity fields in hydraulic engineering applications.

NASA Astrophysics Data System (ADS)

Tellez, Jackson; Gomez, Manuel; Russo, Beniamino; Redondo, Jose M.

2015-04-01

An important achievement in hydraulic engineering is the proposal and development of new techniques for the measurement of field velocities in hydraulic problems. The technological advances in digital cameras with high resolution and high speed found in the market, and the advances in digital image processing techniques now provides a tremendous potential to measure and study the behavior of the water surface flows. This technique was applied at the Laboratory of Hydraulics at the Technical University of Catalonia - Barcelona Tech to study the 2D velocity fields in the vicinity of a grate inlet. We used a platform to test grate inlets capacity with dimensions of 5.5 m long and 4 m wide allowing a zone of useful study of 5.5m x 3m, where the width is similar of the urban road lane. The platform allows you to modify the longitudinal slopes from 0% to 10% and transversal slope from 0% to 4%. Flow rates can arrive to 200 l/s. In addition a high resolution camera with 1280 x 1024 pixels resolution with maximum speed of 488 frames per second was used. A novel technique using particle image velocimetry to measure surface flow velocities has been developed and validated with the experimental data from the grate inlets capacity. In this case, the proposed methodology can become a useful tools to understand the velocity fields of the flow approaching the inlet where the traditional measuring equipment have serious problems and limitations. References DigiFlow User Guide. (2012), (June). Russo, B., Gómez, M., & Tellez, J. (2013). Methodology to Estimate the Hydraulic Efficiency of Nontested Continuous Transverse Grates. Journal of Irrigation and Drainage Engineering, 139(10), 864-871. doi:10.1061/(ASCE)IR.1943-4774.0000625 Teresa Vila (1), Jackson Tellez (1), Jesus Maria Sanchez (2), Laura Sotillos (1), Margarita Diez (3, 1), and J., & (1), M. R. (2014). Diffusion in fractal wakes and convective thermoelectric flows. Geophysical Research Abstracts - EGU General Assembly 2014. RetrievedJanuary 07, 2015, from http://meetingorganizer.copernicus.org/EGU2014/EGU2014-1204.pdf

Center for Alternative Fuels Research Program | College of Engineering &

Science.gov Websites

Applied Science A B C D E F G H I J K L M N O P Q R S T U V W X Y Z D2L PAWS Email My UW Visit Apply Give to UWM Jobs D2L PAWS Email My UW-System University of Wisconsin-Milwaukee College Olympiad Girls Who Code Club FIRST Tech Challenge NSF I-Corps Site of Southeastern Wisconsin UW-Milwaukee

Foundry and Solidification Processing Laboratory | College of Engineering &

Science.gov Websites

Applied Science A B C D E F G H I J K L M N O P Q R S T U V W X Y Z D2L PAWS Email My UW Visit Apply Give to UWM Jobs D2L PAWS Email My UW-System University of Wisconsin-Milwaukee College Olympiad Girls Who Code Club FIRST Tech Challenge NSF I-Corps Site of Southeastern Wisconsin UW-Milwaukee

Center for Advanced Materials Manufacturing | College of Engineering &

Science.gov Websites

Applied Science A B C D E F G H I J K L M N O P Q R S T U V W X Y Z D2L PAWS Email My UW Visit Apply Give to UWM Jobs D2L PAWS Email My UW-System University of Wisconsin-Milwaukee College Olympiad Girls Who Code Club FIRST Tech Challenge NSF I-Corps Site of Southeastern Wisconsin UW-Milwaukee

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.

Prediction of the production of nitrogen oxide (NOx) in turbojet engines

NASA Astrophysics Data System (ADS)

Tsague, Louis; Tsogo, Joseph; Tatietse, Thomas Tamo

Gaseous nitrogen oxides (NO+NO2=NOx) are known as atmospheric trace constituent. These gases remain a big concern despite the advances in low NOx emission technology because they play a critical role in regulating the oxidization capacity of the atmosphere according to Crutzen [1995. My life with O 3, NO x and other YZO x S; Nobel Lecture; Chemistry 1995; pp 195; December 8, 1995] . Aircraft emissions of nitrogen oxides ( NOx) are regulated by the International Civil Aviation Organization. The prediction of NOx emission in turbojet engines by combining combustion operational data produced information showing correlation between the analytical and empirical results. There is close similarity between the calculated emission index and experimental data. The correlation shows improved accuracy when the 2124 experimental data from 11 gas turbine engines are evaluated than a previous semi empirical correlation approach proposed by Pearce et al. [1993. The prediction of thermal NOx in gas turbine exhausts. Eleventh International Symposium on Air Breathing Engines, Tokyo, 1993, pp. 6-9]. The new method we propose predict the production of NOx with far more improved accuracy than previous methods. Since a turbojet engine works in an atmosphere where temperature, pressure and humidity change frequently, a correction factor is developed with standard atmospheric laws and some correlations taken from scientific literature [Swartwelder, M., 2000. Aerospace engineering 410 Term Project performance analysis, November 17, 2000, pp. 2-5; Reed, J.A. Java Gas Turbine Simulator Documentation. pp. 4-5]. The new correction factor is validated with experimental observations from 19 turbojet engines cruising at altitudes of 9 and 13 km given in the ICAO repertory [Middleton, D., 1992. Appendix K (FAA/SETA). Section 1: Boeing Method Two Indices, 1992, pp. 2-3]. This correction factor will enable the prediction of cruise NOx emissions of turbojet engines at cruising speeds. The ICAO database [Goehlich, R.A., 2000. Investigation into the applicability of pollutant emission models for computer aided preliminary aircraft design, Book number 175654, 4.2.2000, pp. 57-79] can now be completed using the approach we propose to complete the whole mission flight NOx emissions.

Modeling of Supersonic Film Cooling on the J-2X Nozzle Extension

NASA Technical Reports Server (NTRS)

Ruf, Joseph H.; Morris, Christopher I.

2011-01-01

Supersonic film cooling (SSFC) of nozzles has been used in several liquid rocket engine designs, and is being applied to the nozzle extension (NE) of the J-2X upper stage engine currently under development. Turbine exhaust gas (TEG) is injected tangentially from a manifold along the NE, and provides a thermal barrier from the core nozzle flow for the NE. As the TEG stream mixes with the nozzle flow, the effectiveness of the thermal barrier is reduced. This paper documents computational fluid dynamics (CFD) analysis work performed by NASA Marshall Space Flight Center (MSFC) to model the flow of the TEG through the manifold, into the nozzle, and the subsequent mixing of the TEG stream with the core flow. The geometry and grid of the TEG manifold, structural support ribs, and the NE wall will be shown, and the CFD boundary conditions described. The Loci-CHEM CFD code used in this work will also be briefly described. A unique approach to modeling the combined TEG manifold/thrust chamber assembly (TCA) was employed, as it was not practical to model the entire 360 circumferential range in one simulation. Prior CFD validation work modeling Calspan SSFC experiments in the early 1990s, documented in a previous AIAA paper, will also be briefly discussed. The fluid dynamics of the TEG flow through the manifold, into and between the structural support ribs, and into the nozzlette that feeds the TCA will be described. Significant swirl and non-uniformities are present, which along with the wakes from the ribs, act to degrade the film cooling effectiveness compared to idealized injection of TEG gas. The effect of these flow characteristics on the adiabatic wall temperature profile on the NE will be discussed.

Altitude Performance of Modified J71 Afterburner with Revised Engine Operating Conditions

NASA Technical Reports Server (NTRS)

Useller, James W.; Russey, Robert E.

1955-01-01

An investigation was conducted in an altitude test chamber at the NACA Lewis laboratory to determine the effect of a revision of the rated engine operating conditions and modifications to the afterburner fue1 system, flameholder, and shell cooling on the augmented performance of the J71-A-2 (x-29) turbo jet engine operating at altitude . The afterburner modifications were made by the manufacturer to improve the endurance at sea-level, high-pressure conditions and to reduce the afterburner shell temperatures. The engine operating conditions of rated rotational speed and turbine-outlet gas temperature were increased. Data were obtained at conditions simulating flight at a Mach number of 0.9 and at altitudes from 40,000 to 60,000 feet. The afterburner modifications caused a reduction in afterburner combustion efficiency. The increase in rated engine speed and turbine-outlet temperature coupled with the afterburner modifications resulted in the over-all thrust of the engine and afterburner being unchanged at a given afterburner equivalence ratio, while the specific fuel consumption was increased slightly. A moderate shift in the range of equivalence ratios over which the afterburner would operate was encountered, but the maximum operable altitude remained unaltered. The afterburner-shell temperatures were also slightly reduced because of the modifications to the afterburner.

Waste Water Handling Proof of Concepts at McMurdo Station, Antarctica

DTIC Science & Technology

2014-09-17

ERDC) solves the nation’s toughest engineering and environmental challenges . ERDC develops innovative solutions in civil and military engineering...h.- vlc •K-too’l /0 Yo tii-<- 3t~o ,?_.$•- j.J’?-- · ~ -,-L~ ~..J- .... s.-~ fi.,,/.-J.~:. t• y.Jj J(r . to ./""’:ls ~ s;yoo r’ ~-~ "" .... lc

Present status of PIT round wires of 122-type iron-based superconductors

NASA Astrophysics Data System (ADS)

Tamegai, T.; Suwa, T.; Pyon, S.; Kajitani, H.; Takano, K.; Koizumi, N.; Awaji, S.; Watanabe, K.

2017-12-01

Outstanding characteristics with high T c and H c2 and small anisotropy in iron-based superconductors (IBSs) have triggered the development of superconducting wires and tapes using these novel superconductors. In this short article, developments and present status of round wires of 122-type IBSs are reviewed. By introducing hot-isostatic pressing (HIP) technique, J c in round wires of 122-type IBSs has been improved significantly. Further improvements have been realized by refining the fabrication process of the core material and introducing partial texturing of the wire core. The largest transport J c for round wires at 4.2 K at self-field and 100 kOe are 2.0x105 A/cm2 and 3.8x104 A/cm2, respectively. We also compare the J c characteristics of wires and tapes processed by HIP.

Operation and Characteristics of the Flash X-Ray Generator at the Naval Postgraduate School

DTIC Science & Technology

1989-06-01

DTIC users Unclassified \\aoNe of Re. , .; e Ind\\. z. 22b Telephone (i’iud .4o rc-code’ 2:¢ O :ice S.\\mb . X K Nlzru’amal (40’S 6J4(-2431 l) 1) 1 1).\\ 14...from the NAVAL POSTGR ADUATE SCHOO. June 1989 Author: tg, Ree f.Iltruszkam X. K. laruyani7 hlesis Advisor ;;100 k S Reader K. E . \\\\oehler. Chairman...Department of IPh1 siLs G. E . Schacher. Dean of Science and Engineering m mm m mm mmli mmmm I i N mmmmm m m 11 ABSTRACT Installation of the Model I 12A

Compact 1 mJ fiber MOPA for space-based laser-ablation resonant ionization mass spectrometry (LARIMS)

NASA Astrophysics Data System (ADS)

Mu, Xiaodong; Crain, William; Nguyen, Can; Ionov, Pavel; Steinvurzel, Paul; Dotan, Yaniv; Karuza, Petras; Lotshaw, William; Rose, Todd; Beck, Steven; Anderson, F. Scott

2018-02-01

A 1064 nm, 1 mJ pulsed fiber MOPA module, housed in 16"x14"x2.5" package for application in a lunar and planetary in-situ surface dating instrument is demonstrated. The module is based on a three-stage MOPA with a 60 μm core tapered fiber terminal amplifier. The master oscillator and first two preamplifier stages, which generate 20 μJ pulses, are all contained on a 13"x11"x1" board. Several improvements to the electronic signal control were instrumental to the laser development, including bipolar drive of the phase modulator for SBS suppression, shaping of the seed pulse to compensate pulse steepening, and pulsed operation of the power amplifier pump to reduce spontaneous emission at low pulse repetition frequency. The packaged laser runs at a repetition rate of 10 kHz and generates 10 ns pulses at 1 mJ with a 40 GHz linewidth, an M2 1.2 beam quality, and an 18 dB polarization extinction ratio. The modular design enables seven independent lasers to be stacked in a 20"x18"x16.25" enclosure, supporting a path towards a fiber laser based LARIMS for advanced materials characterization and chronological dating in harsh and remote environments.

Thermomechanical Cracking in Layered Media from Moving Friction Load,

DTIC Science & Technology

1984-07-01

Dimensionless Temperature The materials of the surface layer and the substrate are the same as Figure 1. D = Hi = 2, x = 0.01 in 61 13. Dimensionless...J 2 (j 2 M2 )] )(60) and 01) (4 ) / 2 2 2 , ")VI’ - [(i - M2 /J 2) + (U - M2 2/ ,(1) + ( - M2/12 )(I - M2/j2)V(1 ) = 0 ( 61 ) 18 .. .. mm...ii - -iii - -ml m . . . . . . . .-... -- Equation ( 61 ) has a characteristic equation x4 _ (I - M2/J2) + (1 - M2/12 )]x2 +(1 - M2/12 )(1 - M2

Comprehensive Forced Response Analysis of J2X Turbine Bladed-Discs with 360 Degree Variation in CFD Loading

NASA Technical Reports Server (NTRS)

Elrod, David; Christensen, Eric; Brown, Andrew

2011-01-01

The temporal frequency content of the dynamic pressure predicted by a 360 degree computational fluid dynamics (CFD) analysis of a turbine flow field provides indicators of forcing function excitation frequencies (e.g., multiples of blade pass frequency) for turbine components. For the Pratt and Whitney Rocketdyne J-2X engine turbopumps, Campbell diagrams generated using these forcing function frequencies and the results of NASTRAN modal analyses show a number of components with modes in the engine operating range. As a consequence, forced response and static analyses are required for the prediction of combined stress, high cycle fatigue safety factors (HCFSF). Cyclically symmetric structural models have been used to analyze turbine vane and blade rows, not only in modal analyses, but also in forced response and static analyses. Due to the tortuous flow pattern in the turbine, dynamic pressure loading is not cyclically symmetric. Furthermore, CFD analyses predict dynamic pressure waves caused by adjacent and non-adjacent blade/vane rows upstream and downstream of the row analyzed. A MATLAB script has been written to calculate displacements due to the complex cyclically asymmetric dynamic pressure components predicted by CFD analysis, for all grids in a blade/vane row, at a chosen turbopump running speed. The MATLAB displacements are then read into NASTRAN, and dynamic stresses are calculated, including an adjustment for possible mistuning. In a cyclically symmetric NASTRAN static analysis, static stresses due to centrifugal, thermal, and pressure loading at the mode running speed are calculated. MATLAB is used to generate the HCFSF at each grid in the blade/vane row. When compared to an approach assuming cyclic symmetry in the dynamic flow field, the current approach provides better assurance that the worst case safety factor has been identified. An extended example for a J-2X turbopump component is provided.

Synthetic and Spectroscopic Studies on N-(i,j-Disubstituted Phenyl)-4- Substituted Benzenesulphonamides, 4-X'C6H4SO2NH(i,j-X2C6H3), where X' = H, CH3, C2H5, F, Cl or Br; i, j = 2, 3; 2, 4; 2, 5; 2, 6 or 3, 4; and X = CH3 or Cl

NASA Astrophysics Data System (ADS)

Shetty, Mahesha; Gowda, B. Thimme

2005-02-01

Fifty four N-(i,j-disubstituted phenyl)-4-substituted benzenesulphonamides of the general formula 4-X'C6H4SO2NH(i,j-X2C6H3), where X' = H, CH3, C2H5, F, Cl or Br; i,j = 2,3; 2,4; 2,5; 2,6 or 3, 4; and X = CH3 or Cl, are prepared and characterized and their infrared, 1H and 13C NMR spectra in solution are studied. The N-H stretching vibrations νN-H absorb in the range 3305 - 3205 cm-1, while the asymmetric and symmetric SO2 vibrations vary in the ranges 1377 - 1307 cm-1 and 1184 - 1128 cm-1, respectively. The N-(i,j-disubstituted phenyl)-4-substituted benzenesulphonamides show C-S, S-N and C-N stretching vibrations in the ranges 844 - 800 cm-1, 945 - 891 cm-1 and 1309 - 1170 cm-1, respectively. The compounds do not exhibit particular trends in the variation of these frequencies on substitution either at ortho or meta positions with either a methyl group or Cl. The observed 1H and 13C chemical shifts of are assigned to protons and carbon atoms of the two benzene rings. Incremental shifts of the ring protons and carbon atoms due to -SO2NH(i,j-X2C6H3) groups in C6H5SO2NH(i,j-X2C6H3) and 4-X'C6H4SO2NH- groups in 4-X'C6H4SO2NH(C6H*) are computed and employed to calculate the chemical shifts of the ring protons and carbon atoms in the substituted compounds 4-X'C6H4SO2NH(i,j-X2C6H3). The different methods of calculation lead to almost the same values in most cases and agree well with the observed chemical shifts, indicating the validity of the principle of additivity of the substituent effects with chemical shifts in these compounds.

Recent Development of the Two-Stroke Engine. 2 - Design Features

DTIC Science & Technology

1945-05-01

NATIONALADVISORYCOMMI~EE FOR AERONAUTICS. TECHNICAL MEMORANDUM No, 1082 R~CENT DEVELOPMENT OX’ THE TWO–STROKE ENGTNE II - DES IGN l’llATURliS By J...MEMORANDUM . ... . ,., . ,.!. .,, .,- ... —--— — FOR AERONAUTICS ‘ NO. 1082 , > ,. RECENT DEVELOPMENT OF THE TWO-STROKE ENGINE II - DESIGN FEATURES* ,“” By...lUOTE: Reprint of R.T.P.3 Translation No. 2382; issued by the Ministry of Aircraft Production, London, England. II: ._: 2 NACA TM NO. 1082 (=“) The

T(2)-weighted microMRI and evoked potential of the visual system measurements during the development of hypomyelinated transgenic mice.

PubMed

Martin, Melanie; Reyes, Samuel D; Hiltner, Timothy D; Givogri, M Irene; Tyszka, J Michael; Fisher, Robin; Campagnoni, Anthony T; Fraser, Scott E; Jacobs, Russell E; Readhead, Carol

2007-02-01

Our objective was to follow the course of a dysmyelinating disease followed by partial recovery in transgenic mice using non-invasive high-resolution (117 x 117 x 70 microm) magnetic resonance (microMRI) and evoked potential of the visual system (VEP) techniques. We used JOE (for J37 golli overexpressing) transgenic mice engineered to overexpress golli J37, a product of the Golli-mbp gene complex, specifically in oligodendrocytes. Individual JOE transgenics and their unaffected siblings were followed from 21 until 75-days-old using non-invasive in vivo VEPs and 3D T2-weighted microMRI on an 11.7 T scanner, performing what we believe is the first longitudinal study of its kind. The microMRI data indicated clear, global hypomyelination during the period of peak myelination (21-42 days), which was partially corrected at later ages (>60 days) in the JOE mice compared to controls. These microMRI data correlated well with [Campagnoni AT (1995) "Molecular biology of myelination". In: Ransom B, Kettenmann H (eds) Neuroglia--a Treatise. Oxford University Press, London, pp 555-570] myelin staining, [Campagnoni AT, Macklin WB (1988) Cellular and molecular aspects of myelin protein gene-expression. Mol Neurobiol 2:41-89] a transient intention tremor during the peak period of myelination, which abated at later ages, and [Lees MB, Brostoff SW (1984) Proteins in myelin. In: Morell (ed) Myelin. Plenum Press, New York and London, pp 197-224] VEPs which all indicated a significant delay of CNS myelin development and persistent hypomyelination in JOE mice. Overall these non-invasive techniques are capable of spatially resolving the increase in myelination in the normally developing and developmentally delayed mouse brain.

Using Innovative Technologies for Manufacturing and Evaluating Rocket Engine Hardware

NASA Technical Reports Server (NTRS)

Betts, Erin M.; Hardin, Andy

2011-01-01

Many of the manufacturing and evaluation techniques that are currently used for rocket engine component production are traditional methods that have been proven through years of experience and historical precedence. As we enter into a new space age where new launch vehicles are being designed and propulsion systems are being improved upon, it is sometimes necessary to adopt new and innovative techniques for manufacturing and evaluating hardware. With a heavy emphasis on cost reduction and improvements in manufacturing time, manufacturing techniques such as Direct Metal Laser Sintering (DMLS) and white light scanning are being adopted and evaluated for their use on J-2X, with hopes of employing both technologies on a wide variety of future projects. DMLS has the potential to significantly reduce the processing time and cost of engine hardware, while achieving desirable material properties by using a layered powdered metal manufacturing process in order to produce complex part geometries. The white light technique is a non-invasive method that can be used to inspect for geometric feature alignment. Both the DMLS manufacturing method and the white light scanning technique have proven to be viable options for manufacturing and evaluating rocket engine hardware, and further development and use of these techniques is recommended.

Evaluation of the in-flight noise signature of a 32-chute suppressor nozzle: Acoustic data report. [outdoor static and 40 x 80 ft. wind tunnel tests

NASA Technical Reports Server (NTRS)

Moore, M. T.; Doyle, V. L.

1977-01-01

Outdoor static and 40 x 80 FT wind tunnel tests of the J79-15 engine/nacelle system with the conic nozzle and 32-chute exhaust suppressor were conducted to acquire the data necessary to evaluate the simulated in-flight signature of an engine-size 32-chute exhaust nozzle suppressor using the 40 x 80 ft wind tunnel and to study possible engine core noise contamination of the jet signature. The tests are described and and a sampling of the data acquired is presented. Included are aero performance summaries, as-measured and composite 1/3 OBSPL spectra for the 70 ft sideline high and low mics from the outdoor static tests, sideline traverse spectra and internal noise measurements from both the outdoor static and the 40 x 80 ft wind tunnel tests.

Broadband Dielectric Spectroscopy of Ruddlesden-Popper Srn+1TinO3n+1 (n = 1,2,3) Thin Films

DTIC Science & Technology

2009-01-29

permittivity, strontium compounds N. D. Orloff, W. Tian, C. J. Fennie , C. H. Lee, D. Gu, J. Mateu, X. X. Xi, K. M. Rabe, D. G. Schlom, I. Takeuchi, J...of Ruddlesden–Popper Srn+1TinO3n+1 (n = 1,2,3) thin films N. D. Orloff, W. Tian, C. J. Fennie , C. H. Lee, D. Gu et al. Citation: Appl. Phys. Lett... Fennie ,4 C. H. Lee,3,5 D. Gu,2 J. Mateu,6 X. X. Xi,5 K. M. Rabe,7 D. G. Schlom,3 I. Takeuchi,1 and J. C. Booth2 1Department of Materials Science and

A Numerical Simulation of a Carbon Black Suspension Cell Via a Time-Reversed, Double Layer Compute Algorithm

DTIC Science & Technology

1999-12-01

be accounted for by conventional descriptions of the system response. To remedy this deficiency , researchers developed a theory or model of the...timex,tO, tev, tps REAL*8 uO, width, x, xx, yy, zz, zr REAL*8 FRACi, FRAC2,F0_XX,F0_YY,F0_ZZ REAL*8 TKl, TK2 ,TQl,Tq2 INTEGER I, J, JJ, K, KK, L, NUM...UU2(J+1) !KK = Layer J+i’s time counter. TK1 = TAU(J+1) TK2 = TK1 + DELTAT(KK) j LOOP MCM C: DO KQ = UU2(J+1), KSUM PLTTIME = TIME * 1E+09 DO

Finite-Element Analysis of Crack Arrest Properties of Fiber Reinforced Composites Application in Semi-Elliptical Cracked Pipelines

NASA Astrophysics Data System (ADS)

Wang, Linyuan; Song, Shulei; Deng, Hongbo; Zhong, Kai

2018-04-01

In nowadays, repair method using fiber reinforced composites as the mainstream pipe repair technology, it can provide security for X100 high-grade steel energy long-distance pipelines in engineering. In this paper, analysis of cracked X100 high-grade steel pipe was conducted, simulation analysis was made on structure of pipes and crack arresters (CAs) to obtain the J-integral value in virtue of ANSYS Workbench finite element software and evaluation on crack arrest effects was done through measured elastic-plastic fracture mechanics parameter J-integral and the crack arrest coefficient K, in a bid to summarize effect laws of composite CAs and size of pipes and cracks for repairing CAs. The results indicate that the K value is correlated with laying angle λ, laying length L2/D1, laying thickness T1/T2of CAs, crack depth c/T1 and crack length a/c, and calculate recommended parameters for repairing fiber reinforced composite CAs in terms of two different crack forms.

GE Fan in Wing VZ-11 VTOL airplane in Ames 40x80 Foot Wind Tunnel.

NASA Image and Video Library

1962-12-27

3/4 front view VZ-11 ground test - variable height struts. Engines of the VZ-11 are a pair of General Electric J85-5 turbojets, mounted in high in the centre fuselage, well away from fan disturbance. Designed in the Ames 40x80 foot wind tunnel.

Investigation of Modularly Configured Attached Processors with Intelligent Memories

DTIC Science & Technology

1994-09-30

sequence of computations becomes cl = c11 + C[i, i] := Cli, j] + A[i, k) * Blk, j]; al x bti, c12 - c12 + k X bkX2, C13 = C1 3 + alk X b 3 , ... , c =n...Cin + alk X bkn, C2 1 = Cat + a2k x bkl , The sequence of computations becomes cii = a I x bli, C22 = cU2 + a2k x b2, ... Cj a2 1x bij, ca3j = aa x...1 to 1/2 Least significant 1/2 address bits Fig. 1. Block diagram of a memory module PREGVJKE is v I pis P16 16 ItO16 = 4-81T OECD - = AMKSS A s-Byrf

Organic Compounds in the Exhaust of a J85-5 Turbine Engine

DTIC Science & Technology

1980-09-01

8217 rcoe E)a•se, Teyxes uno r job vrder 79?31D-11-1H ilhen J.. averegt , spe: i czt ~ 1 -s , oir r=the data are used -’) an 7,rx~se oither than 2: rei...the USAFSAM sorption tube atmospheric sample system ( AF Invention No. 12,052; U.S. Patent No. 4,170,901). The collected samples were analyzed with a...f ’a- @1. 06 a C L v M~~I w ,a!j 1 ’l l .1 cNm l c0 w EL In c , .0 0 ) d’ 3 G)I’ c af a c. I%0 111 , 3 >1u w z w" r ojn 3..c N m enj m L. Nuw X >- 12

A-3 First Tree Cutting

NASA Technical Reports Server (NTRS)

2007-01-01

Tree clearing for the site of the new A-3 Test Stand at Stennis Space center began June 13. NASA's first new large rocket engine test stand to be built since the site's inception, A-3 construction begins a historic era for America's largest rocket engine test complex. The 300-foot-tall structure is scheduled for completion in August 2010. A-3 will perform altitude tests on the Constellation's J-2X engine that will power the upper stage of the Ares I crew launch vehicle and earth departure stage of the Ares V cargo launch vehicle. The Constellation Program, NASA's plan for carrying out the nation's Vision for Space Exploration, will return humans to the moon and eventually carry them to Mars and beyond.

A-3 First Tree Cutting

NASA Image and Video Library

2007-06-13

Tree clearing for the site of the new A-3 Test Stand at Stennis Space center began June 13. NASA's first new large rocket engine test stand to be built since the site's inception, A-3 construction begins a historic era for America's largest rocket engine test complex. The 300-foot-tall structure is scheduled for completion in August 2010. A-3 will perform altitude tests on the Constellation's J-2X engine that will power the upper stage of the Ares I crew launch vehicle and earth departure stage of the Ares V cargo launch vehicle. The Constellation Program, NASA's plan for carrying out the nation's Vision for Space Exploration, will return humans to the moon and eventually carry them to Mars and beyond.

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.

A Comparison of the Optimization and Analysis of Doubly Curved Shells Using MSC/NASTRAN and ASTROS

DTIC Science & Technology

1990-12-01

BMC(7,5)=I.OD+00 CALL BMAT (X1,RI,X2,R2,0.OD+00,B,DL) CALL EMAT(DNU,E,T,G) C C DO BMC*E*B C DO 100 J1=1,7 DO 100 J2=1,5 DO 100 J3=1,5 DO 100 J4=1,6...ELEMENT LENGTH. C SUBROUTINE BMAT (XI,RI,X2,R2,DKSI,B,DL) DOUBLE PRECISION XI,RI,X2,R2,DKSI,B(S,6),DL,R,PHI,CPR,SPR,R, &DKMDKP, DLINV C C EXPLANATION OF

Where are the r-modes? Chandra Observations of Millisecond Pulsars

NASA Technical Reports Server (NTRS)

Mahmoodifar, Simin; Strohmayer, Tod E.

2017-01-01

We present the results of Chandra observations of two non-accreting millisecond pulsars, PSRs J1640+2224(J1640) and J1709+2313 (J1709), with low inferred magnetic fields and spin-down rates in order to constrain their surface temperatures, obtain limits on the amplitude of unstable r-modes in them, and make comparisons with similar limits obtained for a sample of accreting low-mass X-ray binary (LMXB) neutron stars. We detect both pulsars in the X-ray band for the first time. They are faint, with inferred soft X-ray fluxes(0.3-3 keV) of approx. 6 x 10(exp -15) and 3 x 10( exp -15) erg/sq cm for J1640 and J1709, respectively. Spectral analysis assuming hydrogen atmosphere emission gives global effective temperature upper limits (90% confidence) of 3.3-4.3 x 10(exp 5) K for J1640 and 3.6-4.7 x 10(exp 5) K for J1709, where the low end of the range corresponds to canonical neutron stars (M = 1.4 Stellar Mass), and the upper end corresponds to higher-mass stars (M = 2.21 Stellar Mass). Under the assumption that r-mode heating provides the thermal support, we obtain dimensionless r-mode amplitude upper limits of 3.2-4.8 x 10(exp -8) and 1.8-2.8 x 10(exp -7) for J1640 and J1709, respectively, where again the low end of the range corresponds to lower-mass, canonical neutron stars (M =1.4 Stellar Mass). These limits are about an order of magnitude lower than those we derived previously for a sample of LMXBs, except for the accreting millisecond X-ray pulsar SAX J1808.43658, which has a comparable amplitude limit to J1640 and J1709.

Automatic Data Partitioning on Distributed Memory Multiprocessors

DTIC Science & Technology

1990-10-01

DISTRIBUTED MEMORY MULTIPROCESSORS D 1"’ 1 C . Manish Gupta NOV,1 41990.NOV 1 41990m Prithviraj Banerjee D Coordinated Science Laboratory College of...developed on the partitioning of arrays can as well be applied to other programming languages, such as C . 3 The rest of this paper is organized as follows...value 1, as in Fortran. a) N= 4, N 2 = 1: f(i) = J,(j) = 03 b) =Ni 1, N 2 =4: fA(i) =, f() - c ) NI 2, X) 2: f()=[., f2(j) = [L-.j d) N 1 , N 2 =4: fA(i

Ignition of an automobile engine by high-peak power Nd:YAG/Cr⁴⁺:YAG laser-spark devices.

PubMed

Pavel, Nicolaie; Dascalu, Traian; Salamu, Gabriela; Dinca, Mihai; Boicea, Niculae; Birtas, Adrian

2015-12-28

Laser sparks that were built with high-peak power passively Q-switched Nd:YAG/Cr(4+):YAG lasers have been used to operate a Renault automobile engine. The design of such a laser spark igniter is discussed. The Nd:YAG/Cr(4+):YAG laser delivered pulses with energy of 4 mJ and 0.8-ns duration, corresponding to pulse peak power of 5 MW. The coefficients of variability of maximum pressure (COV(Pmax)) and of indicated mean effective pressure (COV(IMEP)) and specific emissions like hydrocarbons (HC), carbon monoxide (CO), nitrogen oxides (NO(x)) and carbon dioxide (CO2) were measured at various engine speeds and high loads. Improved engine stability in terms of COV(Pmax) and COV(Pmax) and decreased emissions of CO and HC were obtained for the engine that was run by laser sparks in comparison with classical ignition by electrical spark plugs.

Interferometric Lens Testing

DTIC Science & Technology

1976-09-01

8217///> 350 DO 340 K-l.NS DO 323 4*3.31 IP( JHIN.GT.O ) GO TO 321 IF(X( J.t.N).LT.0.0001 ) GO TO 323 JMIN-J 321 IF(X( J.K.N ).LT...4 )»JMAX*1 CO TO 330 340 CONTINUE 140 ■ ■■ ’ ■•■****% . c c IF(N.EQ.2) 00 TO 360 M-2 N8«NST O-POSX TAB2-POSY OO tO 350 ...SIMC1-SIN(D1 )/Dl 00 TO 7 6 SINC1-1.00 00 TO 7 7 V2 - 6.283J8S«(C3 ♦ C4»X ♦ C9»X2 »CM^ XS •C20«X4 ♦C24»X5 ♦ C30#X6

KWIK Smoke Obscuration Model: User’s Guide.

DTIC Science & Technology

1982-09-01

t ’ustr ( td I IK,j) 384: prt 3o :: pr t 6 k AC 1-4G" 36~b : pr t " ~ L 3b7: if j~i;prt &t(t1,] 3 8 8: it J=2;pr. "&str(Zjl,1,KI) 3 0 9: j~r t "I 39u...t.2~t71. * j3 3 2u: w r t 7uX ,"i(Lz~j i21iJ "c3wt70, )i: lnt 4 5X, "irI I U uIL - = 01 17.2;wrt 701,kq3 j~b: Lirt. 45x,"a..~c4 uAT - LiLY = g,t4.2

Data Validation and Summary for the NRL Remote Sensing Experiment: Phelps Bank, July, 1982. Part 2. Meteorology.

DTIC Science & Technology

1983-08-26

c "J X = •. : • C X X ’J* «• «• tr «f ^" j’ — *- — *..—; ^- <-• c»j i\\- > X X — •" -- — c <= N *r X T *• !*! -’ -". > -"••- •-’ < No»o».«*« iwm

Advanced Transportation System Studies. Technical Area 3: Alternate Propulsion Subsystem Concepts. Volume 1; Executive Summary

NASA Technical Reports Server (NTRS)

Levack, Daniel J. H.

2000-01-01

The Alternate Propulsion Subsystem Concepts contract had seven tasks defined that are reported under this contract deliverable. The tasks were: FAA Restart Study, J-2S Restart Study, Propulsion Database Development. SSME Upper Stage Use. CERs for Liquid Propellant Rocket Engines. Advanced Low Cost Engines, and Tripropellant Comparison Study. The two restart studies, F-1A and J-2S, generated program plans for restarting production of each engine. Special emphasis was placed on determining changes to individual parts due to obsolete materials, changes in OSHA and environmental concerns, new processes available, and any configuration changes to the engines. The Propulsion Database Development task developed a database structure and format which is easy to use and modify while also being comprehensive in the level of detail available. The database structure included extensive engine information and allows for parametric data generation for conceptual engine concepts. The SSME Upper Stage Use task examined the changes needed or desirable to use the SSME as an upper stage engine both in a second stage and in a translunar injection stage. The CERs for Liquid Engines task developed qualitative parametric cost estimating relationships at the engine and major subassembly level for estimating development and production costs of chemical propulsion liquid rocket engines. The Advanced Low Cost Engines task examined propulsion systems for SSTO applications including engine concept definition, mission analysis. trade studies. operating point selection, turbomachinery alternatives, life cycle cost, weight definition. and point design conceptual drawings and component design. The task concentrated on bipropellant engines, but also examined tripropellant engines. The Tripropellant Comparison Study task provided an unambiguous comparison among various tripropellant implementation approaches and cycle choices, and then compared them to similarly designed bipropellant engines in the SSTO mission This volume overviews each of the tasks giving its objectives, main results. and conclusions. More detailed Final Task Reports are available on each individual task.

X-15 #2 on lakebed after engine failure forced pilot Jack McKay to make an emergency landing at Mud

NASA Technical Reports Server (NTRS)

1962-01-01

On 9 November 1962, an engine failure forced Jack McKay, a NASA research pilot, to make an emergency landing at Mud Lake, Nevada, in the second X-15 (56-6671); its landing gear collapsed and the X-15 flipped over on its back. McKay was promptly rescued by an Air Force medical team standing by near the launch site, and eventually recovered to fly the X-15 again. But his injuries, more serious than at first thought, eventually forced his retirement from NASA. The aircraft was sent back to the manufacturer, where it underwent extensive repairs and modifications. It returned to Edwards in February 1964 as the X-15A-2, with a longer fuselage (52 ft 5 in) and external fuel tanks. The basic X-15 was a rocket-powered aircraft 50 ft long with a wingspan of 22 ft. It was a missile-shaped vehicle with an unusual wedge-shaped vertical tail, thin stubby wings, and unique side fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was capable of developing 57,000 lb of thrust. North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow-on program used the aircraft as a testbed to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudder surfaces on the vertical stabilizers to control yaw and movable horizontal stabilizers to control pitch when moving in synchronization or roll when moved differentially. For flight in the thin air outside of the appreciable Earth's atmosphere, the X-15 used a reaction control system. Hydrogen peroxide thrust rockets located on the nose of the aircraft provided pitch and yaw control. Those on the wings provided roll control. Because of the large fuel consumption, the X-15 was air launched from a B-52 aircraft at 45,000 ft and a speed of about 500 mph. Depending on the mission, the rocket engine provided thrust for the first 80 to 120 sec of flight. The remainder of the normal 10 to 11 min. flight was powerless and ended with a 200-mph glide landing. Generally, one of two types of X-15 flight profiles was used; a high-altitude flight plan that called for the pilot to maintain a steep rate of climb, or a speed profile that called for the pilot to push over and maintain a level altitude. The X-15 was flown over a period of nearly 10 years--June 1959 to Oct. 1968--and set the world's unofficial speed and altitude records of 4,520 mph (Mach 6.7) and 354,200 ft in a program to investigate all aspects of manned hypersonic flight. Information gained from the highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo manned spaceflight programs, and also the Space Shuttle program. The X-15s made a total of 199 flights, and were manufactured by North American Aviation. X-15-1, serial number 56-6670, is now located at the National Air and Space Museum, Washington DC. North American X-15A-2, serial number 56-6671, is at the United States Air Force Museum, Wright-Patterson AFB, Ohio. The X-15-3, serial number 56-6672, crashed on 15 November 1967, resulting in the death of Maj. Michael J. Adams.

Ball Aerospace Long Life, Low Temperature Space Cryocoolers

NASA Astrophysics Data System (ADS)

Glaister, D. S.; Gully, W.; Marquardt, E.; Stack, R.

2004-06-01

This paper describes the development, qualification, characterization testing and performance at Ball Aerospace of long life, low temperature (from 4 to 35 K) space cryocoolers. For over a decade, Ball has built long life (>10 year), multi-stage Stirling and Joule-Thomson (J-T) cryocoolers for space applications, with specific performance and design features for low temperature operation. As infrared space missions have continually pushed for operation at longer wavelengths, the applications for these low temperature cryocoolers have increased. The Ball cryocooler technologies have culminated in the flight qualified SB235 Cryocooler and the in-development 6 K NASA/JPL ACTDP (Advanced Cryocooler Technology Development Program) Cryocooler. The SB235 and its model derivative SB235E are 2-stage coolers designed to provide simultaneous cooling at 35 K (typically, for Mercury Cadmium Telluride or MCT detectors) and 100 K (typically, for the optics) and were baselined for the Raytheon SBIRS Low Track Sensor. The Ball ACTDP cooler is a hybrid Stirling/J-T cooler that has completed its preliminary design with an Engineering Model to be tested in 2005. The ACTDP cooler provides simultaneous cooling at 6 K (typically, for either doped Si detectors or as a sub-Kelvin precooler) and 18 K (typically, for optics or shielding). The ACTDP cooler is under development for the NASA JWST (James Webb Space Telescope), TPF (Terrestrial Planet Finder), and Con-X (Constellation X-Ray) missions. Both the SB235 and ACTDP Coolers are highly leveraged off previous Ball space coolers including multiple life test and flight units.

Improvement of critical current density in thallium-based (Tl,Bi)Sr(1.6)Ba(0.4)Ca2Cu3O(x) superconductors

NASA Technical Reports Server (NTRS)

Ren, Z. F.; Wang, C. A.; Wang, J. H.; Miller, D. J.; Goretta, K. C.

1995-01-01

Epitaxial (Tl,Bi)Sr(1.6)Ba(0.4)Ca2Cu3O(x) ((Tl,Bi)-1223) thin films on (100) single crystal LaAlO3 substrates were synthesized by a two-step procedure. Phase development, microstructure, and relationships between film and substrate were studied by X-ray diffraction (XRD), scanning electron microscopy (SEM), and transmission electron microscopy (TEM). Resistance versus temperature, zero-field-cooled and field cooled magnetization, and transport critical current density (J(sub c)) were measured. The zero-resistance temperature was 105-111 K. J(sub c) at 77 K and zero field was greater than 2 x 10(exp 6) A/sq cm. The films exhibited good flux pinning properties.

Saturn Apollo Program

NASA Image and Video Library

1964-02-07

This illustration, with callouts, is of the Saturn V SII (2nd Stage) developed by the Space Division of North American Aviation under the direction of the Marshall Space Flight Center. The 82-foot-long and 33-foot-diameter S-II stage utilized five J-2 engines, each with a 200,000-pound thrust capability. The engine used liquid oxygen and liquid hydrogen as its propellants.

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.

Results of a Survey Software Development Project Management in the U.S. Aerospace Industry. Volume II. Project Management Techniques, Procedures and Tools.

DTIC Science & Technology

1979-12-18

I Z I UO W-1 eu 0 - 0 tD CL 0, 0 -I7 NW 2 - x M.j a CL W2 X 41 a ~ 0 0,a 4~~ 0 Z .D .J 0 2. N 0 ~N IU 0 4 - 2 0 ~. 0 Q. ’o ~ 0, 𔃺e U - U ~- 0, 0 -a...0 .44 A A A Ao 0 - 2. -U 2- 4’ A 4’ A o .~ 0 .~ 2. flJ 2. A Ao ~. a 2. 𔃾 2- @2 @2 @2 A 0 .~. a I- 2. Xii - 0 2 @2 ON AXe Re 2- Oi. K A.. A A AU .40...Project manager or person appointed by him SE/ TD project manager b. Senior ADP Manager Director Director computer programming Software program design

Evaluation of the Utilization of Research and Development Results by the Naval Facilities Engineering Command.

DTIC Science & Technology

1980-09-01

Transfer, Vol. 3, No. 2, Spring 1979. Jolly, J. A., J. W . Creighton, and David A. Tansik, The Journal of Technology Transfer, Vol. 4, No. 1, Fall 1-9-79...200 Stovall Strr t , . VA 22332. Released as a Technical Report by: W . M. Tolles Dean of Research Unclassified SECURITY CLASSIFICATION OF ’wee 0469 Rom...SUPPLEMENTARY NOT*5S IN Itv a 110010 (Cewtfn,. -R .evoro old* It 066040pweE OW defo 4V blooS .MSe) Technology Transfer Civil Engineering Laboratory Research and

A Multi-Objective Approach to a Bipartite Assignment Matching Problem Using Weighted Values from Multiple Contraints

DTIC Science & Technology

2010-03-15

2001. 4. Colucci, Simona, Tommaso Di Noia, Eugenio Di Sciascio, Francesco M Donini , Marina Mongiello, and Giacomo Piscitelli. "Semantic-based Approach...0 = = = = = = = = ≥ ∀ ∑∑ ∑ ∑ m n i , j i , j i j n i , j i j m i , j j i i , j c x s.t. x a i , , m x b j , , n x i, j. min Model...from i to j (1) while meeting the requirements of supply (2) and demand (3). For this formulation, there is a restriction that 1 1= = =∑ ∑ m n i j

Fuel Testing for Sylvatex: Cooperative Research and Development Final Report, CRADA Number CRD-16-636

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

Burton, Jonathan L.

Sylvatex is a green nano-chemistry company that has developed a platform technology utilizing renewable, non-toxic inputs to create a stable nanoparticle that can be used in multiple applications. Their mission is to increase the use of renewables globally, to empower a cleaner and healthier future. The main application is a fuel technology product - MicroX - that utilizes proprietary knowledge to scale low-cost, cleaner-burning renewable diesel fuel and additives by using a co-location commercial model. The aspects of this project will include testing of two Sylvatex MicroX fuels on an engine dynamometer platform. Industry standard ultra-low sulfur diesel (ULSD) B3more » fuel and a ULSD B20 will both be used for comparison of the Sylvatex fuels (U.S. standard diesel fuel at the pump contains an average of approximately 3% biodiesel; this is why B3 would be used as a baseline comparison). Sylvatex is currently using a prototype formulation (MicroX 1) that applies a high cost surfactant. An experimental formulation (MicroX 2) that uses lower cost materials is under development. The MicroX 1 will be blended at a 10% level into the B3 ULSD fuel and the MicroX 2 will be blended at a 10% level into both the B3 and the B20 ULSD fuels for study on the engine dynamometer test platform. All fuel blends will be tested over the FTP transient engine test cycle and a steady state ramped modal engine test cycle. Each test cycle will be performed a minimum of 3 times for each fuel. Tailpipe and/or engine out gaseous exhaust emissions (CO2, CO, NOx, THC, O2,), engine out PM emissions, and brake-specific fuel consumption rates will be evaluated for all test cycles.« less

Improvement of critical current density in thallium-based (Tl,Bi)Sr{sub 1.6}Ba{sub 0.4}Ca{sub 2}Cu{sub 3}O{sub x} superconductors

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

Ren, Z.F.; Wang, C.A.; Wang, J.H.

1994-12-31

Epitaxial (Tl,Bi)Sr{sub 1.6}Ba{sub 0.4}Ca{sub 2}Cu{sub 3}O{sub x} (Tl,Bi)-1223 thin films on (100) single crystal LaAlO{sub 3} substrates were synthesized by a two-step procedure. Phase development, microstructure, and relationships between film and substrate were studied by X-ray diffraction (XRD), scanning electron microscopy (SEM), and transmission electron microscopy (TEM). Resistance versus temperature, zero-field-cooled and field-cooled magnetization, and transport critical current density (J{sub c}) were measured. The zero-resistance temperature was 105-111 K. J{sub c} at 77 K and zero field was > 2 x 10{sup 6} A/cm{sup 2}. The films exhibited good flux pinning properties.

Review of NASA's Hypersonic Research Engine Project

NASA Technical Reports Server (NTRS)

Andrews, Earl H.; Mackley, Ernest A.

1993-01-01

The goals of the NASA Hypersonic Research Engine (HRE) Project, which began in 1964, were to design, develop, and construct a hypersonic research ramjet/scramjet engine for high performance and to flight-test the developed concept over the speed range from Mach 3 to 8. The project was planned to be accomplished in three phases: project definition, research engine development, and flight test using the X-15A-2 research aircraft, which was modified to carry hydrogen fuel for the research engine. The project goal of an engine flight test was eliminated when the X-15 program was canceled in 1968. Ground tests of engine models then became the focus of the project. Two axisymmetric full-scale engine models having 18-inch-diameter cowls were fabricated and tested: a structural model and a combustion/propulsion model. A brief historical review of the project with salient features, typical data results, and lessons learned is presented.

The alpha(3) Scheme - A Fourth-Order Neutrally Stable CESE Solver

NASA Technical Reports Server (NTRS)

Chang, Sin-Chung

2007-01-01

The conservation element and solution element (CESE) development is driven by a belief that a solver should (i) enforce conservation laws in both space and time, and (ii) be built from a non-dissipative (i.e., neutrally stable) core scheme so that the numerical dissipation can be controlled effectively. To provide a solid foundation for a systematic CESE development of high order schemes, in this paper we describe a new 4th-order neutrally stable CESE solver of the advection equation Theta u/Theta + alpha Theta u/Theta x = 0. The space-time stencil of this two-level explicit scheme is formed by one point at the upper time level and three points at the lower time level. Because it is associated with three independent mesh variables u(sup n) (sub j), (u(sub x))(sup n) (sub j) , and (uxz)(sup n) (sub j) (the numerical analogues of u, Theta u/Theta x, and Theta(exp 2)u/Theta x(exp 2), respectively) and four equations per mesh point, the new scheme is referred to as the alpha(3) scheme. As in the case of other similar CESE neutrally stable solvers, the alpha(3) scheme enforces conservation laws in space-time locally and globally, and it has the basic, forward marching, and backward marching forms. These forms are equivalent and satisfy a space-time inversion (STI) invariant property which is shared by the advection equation. Based on the concept of STI invariance, a set of algebraic relations is developed and used to prove that the alpha(3) scheme must be neutrally stable when it is stable. Moreover it is proved rigorously that all three amplification factors of the alpha(3) scheme are of unit magnitude for all phase angles if |v| <= 1/2 (v = alpha delta t/delta x). This theoretical result is consistent with the numerical stability condition |v| <= 1/2. Through numerical experiments, it is established that the alpha(3) scheme generally is (i) 4th-order accurate for the mesh variables u(sup n) (sub j) and (ux)(sup n) (sub j); and 2nd-order accurate for (uxx)(sup n) (sub j). However, in some exceptional cases, the scheme can achieve perfect accuracy aside from round-off errors.

Transport and Submillimeter Wave Spectroscopy of GaAs/Al sub xGa sub 1-x and In sub x Ga sub 1-x As Heterostructures

DTIC Science & Technology

1989-06-16

J.F. Lievin, F. Alexandre , J.C. Harmand, J. Dangla, C. Dubon-Chevallier and D. Ankri, Appl. Phys. Lett. 40, 1260 (1986); R.A> Davies, M.J. Kelly and...z 30 0.6 u 20 (B) 77K (B) 0.4 (-)00.2 20 0 20 -0.4 10 0.20 I 0 I 2 3 4 5 6 BIAS VOLTAE Figure 4: The I-V characteristics of sample A at (A) 4.2K and

Achieving 14.4% Alcohol-Based Solution-Processed Cu(In,Ga)(S,Se)2 Thin Film Solar Cell through Interface Engineering.

PubMed

Park, Gi Soon; Chu, Van Ben; Kim, Byoung Woo; Kim, Dong-Wook; Oh, Hyung-Suk; Hwang, Yun Jeong; Min, Byoung Koun

2018-03-28

An optimization of band alignment at the p-n junction interface is realized on alcohol-based solution-processed Cu(In,Ga)(S,Se) 2 (CIGS) thin film solar cells, achieving a power-conversion-efficiency (PCE) of 14.4%. To obtain a CIGS thin film suitable for interface engineering, we designed a novel "3-step chalcogenization process" for Cu 2- x Se-derived grain growth and a double band gap grading structure. Considering S-rich surface of the CIGS thin film, an alternative ternary (Cd,Zn)S buffer layer is adopted to build favorable "spike" type conduction band alignment instead of "cliff" type. Suppression of interface recombination is elucidated by comparing recombination activation energies using a dark J- V- T analysis.

CFD Simulations of Supersonic Highly Swirling Flow Exiting a Turbine Vane Row Compared with Experimental Observations

NASA Technical Reports Server (NTRS)

West, Jeff S.; Richardson, Brian R.; Schmauch, Preston; Kenny, Robert J.

2011-01-01

Marshall Space Flight Center (MSFC) has been heavily involved in developing the J2-X engine. The Center has been testing a Work Horse Gas Generator (WHGG) to supply gas products to J2-X turbine components at realistic flight-like operating conditions. Three-dimensional time accurate CFD simulations and analytical fluid analysis have been performed to support WHGG tests at MSFC. The general purpose CFD program LOCI/Chem was utilized to simulate flow of products from the WHGG through a turbine manifold, a stationary row of turbine vanes, into a Can and orifice assembly used to control the back pressure at the turbine vane row and finally through an aspirator plate and flame bucket. Simulations showed that supersonic swirling flow downstream of the turbine imparted a much higher pressure on the Can wall than expected for a non-swirling flow. This result was verified by developing an analytical model that predicts wall pressure due to swirling flow. The CFD simulations predicted that the higher downstream pressure would cause the pressure drop across the nozzle row to be approximately half the value of the test objective. With CFD support, a redesign of the Can orifice and aspirator plate was performed. WHGG experimental results and observations compared well with pre-test and post-test CFD simulations. CFD simulations for both quasi-static and transient test conditions correctly predicted the pressure environment downstream of the turbine row and the behavior of the gas generator product plume as it exited the WHGG test article, impacted the flame bucket and interacted with the external environment.

X-15 #2 just after launch

NASA Technical Reports Server (NTRS)

1960-01-01

The X-15 #2 (56-6671) launches away from the B-52 mothership with its rocket engine ignited. The white patches near the middle of the ship are frost from the liquid oxygen used in the propulsion system, although very cold liquid nitrogen was also used to cool the payload bay, cockpit, windshields, and nose. The X-15 was a rocket-powered aircraft 50 ft long with a wingspan of 22 ft. It was a missile-shaped vehicle with an unusual wedge-shaped vertical tail, thin stubby wings, and unique fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was capable of developing 57,000 lb of rated thrust (actual thrust reportedly climbed to 60,000 lb). North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow-on program used the aircraft as a testbed to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudder surfaces on the vertical stabilizers to control yaw and canted horizontal surfaces on the tail to control pitch when moving in synchronization or roll when moved differentially. For flight in the thin air outside of the appreciable Earth's atmosphere, the X-15 used a reaction control system. Hydrogen peroxide thrust rockets located on the nose of the aircraft provided pitch and yaw control. Those on the wings provided roll control. Because of the large fuel consumption, the X-15 was air launched from a B-52 aircraft at 45,000 ft and a speed of about 500 mph. Depending on the mission, the rocket engine provided thrust for the first 80 to 120 sec of flight. The remainder of the normal 10 to 11 min. flight was powerless and ended with a 200-mph glide landing. Generally, one of two types of X-15 flight profiles was used: a high-altitude flight plan that called for the pilot to maintain a steep rate of climb, or a speed profile that called for the pilot to push over and maintain a level altitude. The X-15 was flown over a period of nearly 10 years--June 1959 to Oct. 1968--and set the world's unofficial speed and altitude records of 4,520 mph (Mach 6.7) and 354,200 ft (over 67 mi) in a program to investigate all aspects of piloted hypersonic flight. Information gained from the highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo manned spaceflight programs, and also the Space Shuttle program. The X-15s made a total of 199 flights and were manufactured by North American Aviation. X-15-1, serial number 56-6670, is now located at the National Air and Space Museum, Washington DC. North American X-15A-2, serial number 56-6671, is at the United States Air Force Museum, Wright-Patterson AFB, Ohio. The X-15-3, serial number 56-6672, crashed on 15 November 1967, resulting in the death of Maj. Michael J. Adams.

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)

X-15 Hardware Design Challenges

NASA Technical Reports Server (NTRS)

Storms, Harrison A., Jr.

1991-01-01

Historical events in the development of the X-15 hardware design are presented. Some of the topics covered include: (1) drivers that led to the development of the X-15; (2) X-15 space research objectives; (3) original performance targets; (4) the X-15 typical mission; (5) X-15 dimensions and weight; (5) the propulsion system; (6) X-15 development milestones; (7) engineering and manufacturing challenges; (8) the X-15 structure; (9) ballistic flight control; (10) landing gear; (11) nose gear; and (12) an X-15 program recap.

A new mouse model to explore therapies for preeclampsia.

PubMed

Ahmed, Abdulwahab; Singh, Jameel; Khan, Ysodra; Seshan, Surya V; Girardi, Guillermina

2010-10-27

Pre-eclampsia, a pregnancy-specific multisystemic disorder is a leading cause of maternal and perinatal mortality and morbidity. This syndrome has been known to medical science since ancient times. However, despite considerable research, the cause/s of preeclampsia remain unclear, and there is no effective treatment. Development of an animal model that recapitulates this complex pregnancy-related disorder may help to expand our understanding and may hold great potential for the design and implementation of effective treatment. Here we show that the CBA/J x DBA/2 mouse model of recurrent miscarriage is also a model of immunologically-mediated preeclampsia (PE). DBA/J mated CBA/J females spontaneously develop many features of human PE (primigravidity, albuminuria, endotheliosis, increased sensitivity to angiotensin II and increased plasma leptin levels) that correlates with bad pregnancy outcomes. We previously reported that antagonism of vascular endothelial growth factor (VEGF) signaling by soluble VEGF receptor 1 (sFlt-1) is involved in placental and fetal injury in CBA/J x DBA/2 mice. Using this animal model that recapitulates many of the features of preeclampsia in women, we found that pravastatin restores angiogenic balance, ameliorates glomerular injury, diminishes hypersensitivity to angiotensin II and protects pregnancies. We described a new mouse model of PE, were the relevant key features of human preeclampsia develop spontaneously. The CBA/J x DBA/2 model, that recapitulates this complex disorder, helped us identify pravastatin as a candidate therapy to prevent preeclampsia and its related complications. We recognize that these studies were conducted in mice and that clinical trials are needed to confirm its application to humans.

Computer Aided Engineering of Semiconductor Integrated Circuits

DTIC Science & Technology

1976-04-01

from that of the ideal charge-contrpl model. Application of the test developed here to a practical MOS NAND gate demonstrates marked violations of...defining properties: [31] J. E. Meyer, RCA Review, 321, 42 (1971). [32] R.S.C. Cobbold , Theory and Applications of Field-Effect Transistors...decrease of thxs dxs- I ’ [!] H.K.J. Ihantola and J. L. Moll, Solid State Electronics, 7, 423 (1964). [2] R.S.C. Cobbold , Theory and

A Practical Approximation Algorithm for the LTS Estimator

DTIC Science & Technology

2015-07-02

are computed quantities. We begin with a few standard definitions [19, 20]. Consider a d-vector x and a d × d matrix X. Let Xi, j denote the element...separately. By definition , the middle factor is just κ(XE). To analyze the first factor, observe that ‖yE − y∗E‖2 = ∑ j∈E(y j − y∗j)2. By our earlier...y j − y∗j)2 ≤ med j∈H(y j − y∗j)2 (h/2) med j∈H(y j − y∗j)2 ≤ 2 h . To analyze the third factor, recall that from the definition of the Frobenius

High critical currents in heavily doped (Gd,Y)Ba 2Cu 3O x superconductor tapes

DOE PAGES

Selvamanickam, V.; Gharahcheshmeh, M. Heydari; Xu, A.; ...

2015-01-20

REBa 2Cu 3O x superconductor tapes with moderate levels of dopants have been optimized for high critical current density in low magnetic fields at 77 K, but they do not exhibit exemplary performance in conditions of interest for practical applications, i.e., temperatures less than 50 K and fields of 2–30 T. Heavy doping of REBCO tapes has been avoided by researchers thus far due to deterioration in properties. Here, we report achievement of critical current densities (J c) above 20 MA/cm 2 at 30 K, 3 T in heavily doped (25 mol. % Zr-added) (Gd,Y)Ba 2Cu 3O x superconductor tapes,more » which is more than three times higher than the J c typically obtained in moderately doped tapes. Pinning force levels above 1000 GN/m 3 have also been attained at 20 K. A composition map of lift factor in J c (ratio of J c at 30 K, 3 T to the J c at 77 K, 0 T) has been developed which reveals the optimum film composition to obtain lift factors above six, which is thrice the typical value. A highly c-axis aligned BaZrO 3 (BZO) nanocolumn defect density of nearly 7 × 10 11 cm –2 as well as 2–3nm sized particles rich in Cu and Zr have been found in the high J c films.« less

Cortisol Release in Response to UVB Exposure in Xiphophorus Fish

PubMed Central

Contreras, Adam J.; Boswell, Mikki; Downs, Kevin P.; Pasquali, Amanda; Walter, Ronald B.

2014-01-01

Xiphophorus fishes are comprised of 26 known species. Interspecies hybridization between select species has been utilized to produce experimental models to study melanoma development. Xiphophorus melanoma induction protocols utilize ultraviolet light (UVB) to induce DNA damage and associated downstream tumorigenesis. However, the impact of induced stress caused by the UVB treatment of the experimental animals undergoing tumor induction protocols has not been assessed. Stress is an adaptive physiological response to excessive or unpredictable environmental stimuli. The stress response in fishes may be measured by assay of cortisol released into the water. Here, we present results from investigations of stress response during experimental treatment and UVB exposure in X. maculatus Jp 163 B, X. couchianus, and F1 interspecies hybrids produced from the mating X. maculatus Jp 163 B x X. couchianus. Overall, cortisol release rates for males and females after UVB exposure showed no statistical differences. At lower UVB doses (8 and 16 kJ/m2), X. couchianus exhibited 2 fold higher levels of DNA damage then either X. maculatus or the F1 hybrid. However, based on cortisol release rates, none of the fish types tested induced a primary stress response at the UVB lower doses (8 and 16 kJ/m2). In contrast, at a very high UVB dose (32 kJ/m2) both X. maculatus and the F1 hybrid showed a 5 fold increase in cortisol release rate. To determine the effect of pigmentation on UVB induced stress, wild type and albino X. hellerii were exposed to UVB (32 kJ/m2). Albino X. hellerii exhibited 3.7 fold increase in cortisol release while wild type X. hellerii did not exhibit a significant cortisol response to UVB. Overall, the data suggest the rather low UVB doses often employed in tumour induction protocols do not induce a primary stress response in Xiphophorus fishes. PMID:24625568

Dollar Summary of Prime Contract Awards by Contractor, State or Country, and Place, FY 87. Part 3. Finalco Group, Incorporated-Kennedy Electric Company.

DTIC Science & Technology

1987-01-01

CO: y6)-t . I439Ct- 311 -9.I _sx3~ 9XXx ~ 3: t3 : 1911I wIl 41 l WLL wU1 .6)6WU. Ii li-I.J ... jAj .1.A.u4,J’jW O j jU. C. .J 1 .1-.1...4 -U . U to...511Wm L - 100x > .. (n OL4(AUC UI IA cc td )( I0- 4e cci5 eC 0 1- P j X3 I a . .I . -4. - 6i- -4 x 2 x . ).E x4 xx.4xx x 6LC L 0 (A I of- .. .. ~ ....43

Vaccine of engineered tumor cells secreting stromal cell-derived factor-1 induces T-cell dependent antitumor responses.

PubMed

Shi, Meiqing; Hao, Siguo; Su, Liping; Zhang, Xueshu; Yuan, Jinying; Guo, Xuling; Zheng, Changyu; Xiang, Jim

2005-08-01

The CXC chemokine SDF-1 has been characterized as a T-cell chemoattractant both in vitro and in vivo. To determine whether SDF-1 expression within tumors can influence tumor growth, we transfected an expression vector pCI-SDF-1 for SDF-1 into J558 myeloma cells and tested their ability to form tumors in BALB/c. Production of biologically active SDF-1 (1.2 ng/mL) was detected in the culture supernatants of cells transfected with the expression vector pCI-SDF-1. J558 cells gave rise to a 100% tumor incidence, whereas SDF-1-expressing J558/SDF-1 tumors invariably regressed in BALB/c mice and became infiltrated with CD4(+) and CD8(+) T cells. Regression of the J558/SDF-1 tumors was dependent on both CD4(+) and CD8(+) T-cells. Our data also indicate that TIT cells containing both CD4(+) and CD8(+) T-cells within J558/SDF-1 tumors express the SDF-1 receptor CXCR4, and that SDF-1 specifically chemoattracts these cells in vitro. Furthermore, immunization of mice with engineered J558/SDF-1 cells elicited the most potent protective immunity against 0.5 x 10(6) cells J558 tumor challenge in vivo, compared to immunization with the J558 alone, and this antitumor immunity mediated by J558/SDF-1 tumor cell vaccination in vivo appeared to be dependent on CD8(+) CTL. Thus, SDF-1 has natural adjuvant activities that may augment antitumor responses through their effects on T-cells and thereby could be important in gene transfer immunotherapies for some cancers.

Measurements of J/{psi} and {psi}(2S) decays into {lambda}{lambda}{pi}{sup 0} and {lambda}{lambda}{eta}

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

Ablikim, M.; Bai, J. Z.; Cai, X.

2007-11-01

Using 58x10{sup 6} J/{psi} and 14x10{sup 6} {psi}(2S) events collected by the BESII detector at the BEPC, branching fractions or upper limits for the decays J/{psi} and {psi}(2S){yields}{lambda}{lambda}{pi}{sup 0} and {lambda}{lambda}{eta} are measured. For the isospin violating decays, the upper limits are determined to be B(J/{psi}{yields}{lambda}{lambda}{pi}{sup 0})<6.4x10{sup -5} and B[{psi}(2S){yields}{lambda}{lambda}{pi}{sup 0}]<4.9x10{sup -5} at the 90% confidence level. The isospin conserving process J/{psi}{yields}{lambda}{lambda}{eta} is observed for the first time, and its branching fraction is measured to be B(J/{psi}{yields}{lambda}{lambda}{eta})=(2.62{+-}0.60{+-}0.44)x10{sup -4}, where the first error is statistical and the second one is systematic. No {lambda}{lambda}{eta} signal is observed in {psi}(2S) decays, and B[{psi}(2S){yields}{lambda}{lambda}{eta}]<1.2x10{supmore » -4} is set at the 90% confidence level. Branching fractions of J/{psi} decays into {sigma}{sup +}{pi}{sup -}{lambda} and {sigma}{sup -}{pi}{sup +}{lambda} are also reported, and the sum of these branching fractions is determined to be B(J/{psi}{yields}{sigma}{sup +}{pi}{sup -}{lambda}+c.c.)=(1.52{+-}0.08{+-}0.16)x10{sup -3}.« less

Search for charmonium and charmoniumlike states in {Upsilon}(1S) radiative decays

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

Shen, C. P.; University of Hawaii, Honolulu, Hawaii 96822; Wang, X. L.

2010-09-01

Using a sample of 102x10{sup 6} {Upsilon}(1S) events collected with the Belle detector, we report on the first search for charge-parity-even charmonium and charmoniumlike states in {Upsilon}(1S) radiative decays. No significant {chi}{sub cJ} or {eta}{sub c} signal is observed and 90% C.L. limits on B({Upsilon}(1S){yields}{gamma}{chi}{sub c0})<6.5x10{sup -4}, B({Upsilon}(1S){yields}{gamma}{chi}{sub c1})<2.3x10{sup -5}, B({Upsilon}(1S){yields}{gamma}{chi}{sub c2})<7.6x10{sup -6}, and B({Upsilon}(1S){yields}{gamma}{eta}{sub c})<5.7x10{sup -5} are obtained. The product branching fraction limits B({Upsilon}(1S){yields}{gamma}X(3872))B(X(3872){yields}{pi}{sup +}{pi}{sup -}{pi}{sup +}{pi}{sup -}J/{psi})<1.6x10{sup -6}, B({Upsilon}(1S){yields}{gamma}X(3872))B(X(3872){yields}{pi}{sup +}{pi}{sup -}{pi}{sup 0}J/{psi})<2.8x10{sup -6}, B({Upsilon}(1S){yields}{gamma}X(3915)) B(X(3915){yields}{omega}J/{psi})<3.0x10{sup -6}, and B({Upsilon}(1S){yields}{gamma}Y(4140))B(Y(4140){yields}{phi}J/{psi})<2.2x10{sup -6} are obtained at the 90% C.L. Furthermore, no evidence is found for excited charmonium states below 4.8 GeV/c{sup 2}.

Fracture mechanics criteria for turbine engine hot section components

NASA Technical Reports Server (NTRS)

Meyers, G. J.

1982-01-01

The application of several fracture mechanics data correlation parameters to predicting the crack propagation life of turbine engine hot section components was evaluated. An engine survey was conducted to determine the locations where conventional fracture mechanics approaches may not be adequate to characterize cracking behavior. Both linear and nonlinear fracture mechanics analyses of a cracked annular combustor liner configuration were performed. Isothermal and variable temperature crack propagation tests were performed on Hastelloy X combustor liner material. The crack growth data was reduced using the stress intensity factor, the strain intensity factor, the J integral, crack opening displacement, and Tomkins' model. The parameter which showed the most effectiveness in correlation high temperature and variable temperature Hastelloy X crack growth data was crack opening displacement.

Nature of the Unidentified TeV Source HESS J1614-518 Revealed by Suzaku and XMM-Newton Observations

NASA Astrophysics Data System (ADS)

Sakai, M.; Yajima, Y.; Matsumoto, H.

2013-03-01

We report new results concerning HESS J1614-518, which exhibits two regions with intense γ-ray emission. The south and center regions of HESS J1614-518 were observed with Suzaku in 2008, while the north region with the 1st brightest peak was observed in 2006. No X-ray counterpart is found at the 2nd brightest peak; the upper limit of the X-ray flux is estimated as 1.6 × 10-13 erg cm-2 s-1 in the 2-10 keV band. A previously-known soft X-ray source, Suzaku J1614-5152, is detected at the center of HESS J1614-518. Analyzing the XMM-Newton archival data, we reveal that Suzaku J1614-5152 consists of multiple point sources. The X-ray spectrum of the brightest point source, XMMU J161406.0-515225, could be described by a power-law model with the photon index Γ = 5.2+0.6-0.5 or a blackbody model with the temperature kT = 0.38+0.04-0.04 {keV}. In the blackbody model, the estimated column density N H = 1.1+0.3-0.2 × 1022 {cm}-2 is almost the same as that of the hard extended X-ray emission in Suzaku J1614-5141, spatially coincident with the 1st peak position. In this case, XMMU J161406.0-515225 may be physically related to Suzaku J1614-5141 and HESS J1614-518.

Security Police Career Ladders AFSCs 811X0, 811X2, and 811X2A.

DTIC Science & Technology

1984-11-01

MONITORS (GRP658) PERCENT MEMBERS PERFORMING TASKS (N=186) J424 PERFORM SPCDS OPERATOR REACTIONS TO SENSOR ALARM, LINE FAULT, OR UNIQUE LINE FAULT...MESSAGES 96 J426 PERFORM SPCDS VERIFICATION PROCEDURES 96 J423 PERFORM SMALL PERMANENT COMMUNICATIONS DISPLAY SEGMENT ( SPCDS ) SHUT-DOWN PROCEDURES 92 J425...PERFORM SPCDS START-UP PROCEDURES 91 J419 PERFORM BISS OPERATOR REACTION TO PRIME POWER LOSS OR SEVERE WEATHER WARNINGS 91 E192 MAKE ENTRIES ON AF

Models of GexSe1-x

NASA Astrophysics Data System (ADS)

Malouin, Marc-André.; Mousseau, Normand

2008-03-01

We present numerical models of chalcogenide glasses constructed using the effective two and three body interaction potential developed by Mauro and Varshneya [1] combined with the activation-relaxation technique (ART nouveau) [2]. Structures are prepared starting from a random distribution, avoiding biases and crystalline remnants. Structural properties are studied mainly via characteristic system measurements including partial and total radial distribution functions, bond angle distributions, mean coordinations and bonds population. Results are shown for GexSe1-x for various x concentrations and compared to both experimental measurements and ab initio simulation results. [1] J.C. Mauro and A.K. Varshneya, J. Am. Ceram. Soc., 89 [7] 2323-6 (2006). [2] R. Malek and N. Mousseau, Phys. Rev. E 62, 7723 (2000).

Transform Methods for Precision Nonlinear Wave Models of Flexible space Structures

DTIC Science & Technology

1990-08-20

developed, each of which has motivated a structural control methodology in a natural way. The Transform Element Modelling (TEM) approach uses the Laplace...IEk A L 2 = -, c G= ( C .3 a ,b ) Talng the Laplace transfor-m (neglecting initial conditions) )ields [1+tjSZ-(,s) +S ((X’S) + al2a~ pS4 (X’S) j(X’s) (04

Optical Measurement Techniques for Rocket Engine Testing and Component Applications: Digital Image Correlation and Dynamic Photogrammetry

NASA Technical Reports Server (NTRS)

Gradl, Paul

2016-01-01

NASA Marshall Space Flight Center (MSFC) has been advancing dynamic optical measurement systems, primarily Digital Image Correlation, for extreme environment rocket engine test applications. The Digital Image Correlation (DIC) technology is used to track local and full field deformations, displacement vectors and local and global strain measurements. This technology has been evaluated at MSFC through lab testing to full scale hotfire engine testing of the J-2X Upper Stage engine at Stennis Space Center. It has been shown to provide reliable measurement data and has replaced many traditional measurement techniques for NASA applications. NASA and AMRDEC have recently signed agreements for NASA to train and transition the technology to applications for missile and helicopter testing. This presentation will provide an overview and progression of the technology, various testing applications at NASA MSFC, overview of Army-NASA test collaborations and application lessons learned about Digital Image Correlation.

Broad-band characteristics of seven new hard X-ray selected cataclysmic variables

NASA Astrophysics Data System (ADS)

Bernardini, F.; de Martino, D.; Mukai, K.; Russell, D. M.; Falanga, M.; Masetti, N.; Ferrigno, C.; Israel, G.

2017-10-01

We present timing and spectral analysis of a sample of seven hard X-ray selected cataclysmic variable candidates based on simultaneous X-ray and optical observations collected with XMM-Newton, complemented with Swift/BAT and INTEGRAL /IBIS hard X-ray data and ground-based optical photometry. For six sources, X-ray pulsations are detected for the first time in the range of ˜296-6098 s, identifying them as members of the magnetic class. Swift J0927.7-6945, Swift J0958.0-4208, Swift J1701.3-4304, Swift J2113.5+5422 and possibly PBC J0801.2-4625 are intermediate polars (IPs), while Swift J0706.8+0325 is a short (1.7 h) orbital period polar, the 11th hard X-ray-selected identified so far. X-ray orbital modulation is also observed in Swift J0927.7-6945 (5.2 h) and Swift J2113.5+5422 (4.1 h). Swift J1701.3-4304 is discovered as the longest orbital period (12.8 h) deep eclipsing IP. The spectra of the magnetic systems reveal optically thin multitemperature emission between 0.2 and 60 keV. Energy-dependent spin pulses and the orbital modulation in Swift J0927.7-6945 and Swift J2113.5+5422 are due to intervening local high-density absorbing material (NH ˜ 1022 - 23 cm-2). In Swift J0958.0-4208 and Swift J1701.3-4304, a soft X-ray blackbody (kT ˜ 50 and ˜80 eV) is detected, adding them to the growing group of `soft' IPs. White dwarf masses are determined in the range of ˜ 0.58-1.18 M⊙, indicating massive accreting primaries in five of them. Most sources accrete at rates lower than the expected secular value for their orbital period. Formerly proposed as a long-period (9.4 h) nova-like CV, Swift J0746.3-1608 shows peculiar spectrum and light curves suggesting either an atypical low-luminosity CV or a low-mass X-ray binary.

Saturn Apollo Program

NASA Image and Video Library

1967-01-01

This is a cutaway illustration of the Saturn V launch vehicle with callouts of the major components. The Saturn V is the largest and most powerful launch vehicle developed in the United States. It was a three stage rocket, 363 feet in height, used for sending American astronauts to the moon and for placing the Skylab in Earth orbit. The Saturn V was designed to perform Earth orbital missions through the use of the first two stages, while all three stages were used for lunar expeditions. The S-IC stage (first stage) was powered by five F- engines, which burned kerosene and liquid oxygen to produce more than 7,500,000 pounds of thrust. The S-II (second) stage was powered by five J-2 engines, that burned liquid hydrogen and liquid oxygen and produced 1,150,000 pounds thrust. The S-IVB (third) stage used one J-2 engine, producing 230,000 pounds of thrust, with a re-start capability. The Marshall Space Flight Center and its contractors designed, developed, and assembled the Saturn V launch vehicle stages.

Cavity Ringdown Spectroscopy and Kinetics of HO_2+HCHO: Detection of the ν_1 and {A}- {X} Bands of HOCH_2OOCAVITY Ringdown Spectroscopy and Kinetics of HO_2+HCHO: Detection of the ν_1 and {A}- {X} Bands of HOCH_2OO

NASA Astrophysics Data System (ADS)

Sprague, Matthew K.; Okumura, Mitchio; Sander, Stanley P.

2011-06-01

The reactions of HO_2 with carbonyl compounds are believed to be a sink for carbonyl compounds in the upper troposphere and lower stratosphere. These reactions proceed through a hydrogen bound intermediate before isomerizing. The reaction of HO_2 + formaldehyde (HCHO) serves as a prototype for this class of reactions, forming the isomerization product hydroxymethylperoxy (HOCH_2OO, HMP). Previous studies measured the spectrum and kinetics of HMP using either FTIR detection of the end products or direct detection of HMP by the unstructured tilde{B}-tilde{X} transition. Despite these studies, considerable uncertainty exists in the rate constant of HMP formation (±80%, 2σ). In this talk, we report the first detection of the ν_1 (OH stretch) and tilde{A}-tilde{X} electronic spectra of the HMP radical. The OH stretch spectrum is broad and featureless, while the tilde{A}(0)-tilde{X}(0) origin and combination band with the OOCO torsion tilde{A}(NOOCO=1)-tilde{X}(0) are rotationally resolved. Quantum chemistry calculations have been performed on both the tilde{A} and tilde{X} states as a function of the OOCO and HOCO dihedral angles to estimate the tilde{A}-tilde{X} transition frequency and to assess the coupling between the two torsional modes. We also present kinetics data showing the rates of production and destruction of HMP. I. Hermans, J. F. Muller, T. L. Nguyen, P. A. Jacobs, and J. Peeters. J. Phys. Chem. A 2005, 109, 4303. F. Su, J. G. Calvert, and J. H. Shaw J. Phys. Chem. 1979, 83, 3185. B. Veyret, R. Lesclaux, M. T. Rayez, J. C. Rayez, R. A. Cox, and G. K. Moortgat J. Phys. Chem. 1989, 93, 2368. J. P. Burrows, G. K. Moortgat, G. S. Tyndall, R. A. Cox, M. E. Jenkin, G. D. Hayman, and B. Veyret J. Phys. Chem. 1989, 93, 2375 S. P. Sander, B. J. Finlayson-Pitts, D. M. Golden, R. E. Huie, C. E. Kolb, M. J. Kurylo, M. J. Molina, et al. Chemical Kinetics and Photochemical Data for Use in Atmospheric Studies, Evaluation Number 16, Jet Propulsion Laboratory, 2009 I. Hermans, J. F. Muller, T. L. Nguyen, P. A. Jacobs, and J. Peeters. J. Phys. Chem. A 2005, 109, 4303.

From Concept to Design: Progress on the J-2X Upper Stage Engine for the Ares Launch Vehicles

NASA Technical Reports Server (NTRS)

Byrd, Thomas

2008-01-01

In accordance with national policy and NASA's Global Exploration Strategy, the Ares Projects Office is embarking on development of a new launch vehicle fleet to fulfill the national goals of replacing the space shuttle fleet, returning to the moon, and exploring farther destinations like Mars. These goals are shaped by the decision to retire the shuttle fleet by 2010, budgetary constraints, and the requirement to create a new fleet that is safer, more reliable, operationally more efficient than the shuttle fleet, and capable of supporting long-range exploration goals. The present architecture for the Constellation Program is the result of extensive trades during the Exploration Systems Architecture Study and subsequent refinement by the Ares Projects Office at Marshall Space Flight Center.

Scattering of Tone Bursts from Spherical Shells: Computations Based on Fourier Transform Method.

DTIC Science & Technology

1991-08-30

0 SALP =0. 0 N1=0 SUM=0. 0 CALL STVAL(X,X1,X2 ,ALPN, BETN,CBN1, BN1,SNN1,RH,XSN,X2S,XCS) 20 CONTINUE CE-N2= PCB(N+3)/PCB(N+2) Q=FLOAT (N+1) 88 ANUM-(Q...BETN*BETN1)) FAC=XSIGN* (2. 0*Q-1. 0) SALP = SALP +FAC*ALPN SBET=SBET+FAC* BETN ALPN=ALPN1 BETN=BETN1 SUM=SUM+ADD IF ((ABS(ADD/SUM)).LT.1.OE-8) GO TO 90...J=O N=N±1 XSIGN=-XSIGN GO TO 20 90 J=J+1 IF (J.EQ.5) GO TO 100 N=N+1 XSIGN=-XSIGN GO TO 20 100 YP=(-4.0/(X**2))*SUM FAC=-XSIGN* (2. 0*Q+1.0) SALP = SALP

A new Morse-oscillator based Hamiltonian for H 3+: Calculation of line strengths

NASA Astrophysics Data System (ADS)

Jensen, Per; Špirko, V.

1986-07-01

In two recent publications [V. Špirko, P. Jensen, P. R. Bunker, and A. Čejchan, J. Mol. Spectrosc.112, 183-202 (1985); P. Jensen, V. Špirko, and P. R. Bunker, J. Mol. Spectrosc.115, 269-293 (1986)], we have described the development of Morse oscillator adapted rotation-vibration Hamiltonians for equilateral triangular X3 and Y2X molecules, and we have used these Hamiltonians to calculate the rotation-vibration energies for H 3+ and its X3+ and Y2X+ isotopes from ab initio potential energy functions. The present paper presents a method for calculating rotation-vibration line strengths of H 3+ and its isotopes using an ab initio dipole moment function [G. D. Carney and R. N. Porter, J. Chem. Phys.60, 4251-4264 (1974)] together with the energies and wave-functions obtained by diagonalization of the Morse oscillator adapted Hamiltonians. We use this method for calculating the vibrational transition moments involving the lowest vibrational states of H 3+, D 3+, H 2D +, and D 2H +. Further, we calculate the line strengths of the low- J transitions in the rotational spectra of H 3+ in the vibrational ground state and in the ν1 and ν2 states. We hope that the calculations presented will facilitate the search for further rotation-vibration transitions of H 3+ and its isotopes.

Johnson Controls | College of Engineering & Applied Science

Science.gov Websites

students at UW-Milwaukee and UW-Madison. Advancement in Battery Energy Storage Systems Grants The UWM applications from UW-Milwaukee and UW-Madison for funding R&D in systems technology, materials technology A B C D E F G H I J K L M N O P Q R S T U V W X Y Z D2L PAWS Email My UW-System About UWM

Advanced ADA Workshop Held in Biloxi, Mississippi on 24-27 January 1989

DTIC Science & Technology

1989-01-27

Software Engineering (Break at 2:30j 6:30-8:00 Keesler AFB Reception Officers’ Club WEDNESDAY - 25 JANIJ1APY 9:00-12:00 Bldc 1002 Generics (Break at 10...TextIO.FileType: -- NO! procedure Wrong; -- problem is FileType is limited private Object Parameters A More Useful Example generic Control -Block : in out... control the precision used Float Type Parameters An Example generic type FloatType is digits <>; function Sqrt(X : FloatType) return FloatType

Hydrostatic Response of Submarine Nickel Aluminum Bronze Valves with Corrosion Damage

DTIC Science & Technology

2008-07-01

Engineering PO Box 1000 Halifax, Nova Scotia B3J 2X4 Project Manager: Dr. T.S. Koko , 902-425-5101 Contract Number: W7707-078022/001/HAL Contract...Manager: Dr. T.S. Koko , 902-425-5101 ext 243 Contract Number: W7707-078022/001/HAL Contract Scientific Authority: Dr. Y. Wang, 902-427-3035...Hydrostatic Response of Submarine Nickel Aluminum Bronze Valves with Corrosion Damage B.K.C. Yuen; T.S. Koko ; R. Warner; DRDC Atlantic CR 2008

Supersonic Transport Noise Reduction Technology Program - Phase 2, Volume 2

DTIC Science & Technology

1975-09-01

a J85 is shown on Figure 350. The J85 turbojet engine has an eight-stage compressor (with an air bleed system) and a two-stage turbine . Blade ...investigated in this program using a YJ85 engine . Both turbine second-stage spacing ( blade - vane ) and exhaust duct treatment were determined to be...using a J85 engine with massive Inlet suppressor and open nozzle to unmask the turbine . Second-stag« turbine blade /nozzle spacing and exhaust

Early Training Estimation System

DTIC Science & Technology

1984-06-01

Cybernetics and Society, 1980, pp. 1067-1974. J. David , J. Price, Successful communication in full scale engineering development statements of work. Air Force...Technical Memorandum 24-80, 1980, US Army Engineering Laboratory. S. Shrier , Algorithms for system design. Proceedings of the international conference on

Learning to Understand Natural Language with Less Human Effort

DTIC Science & Technology

2015-05-01

j ); if one of these has the correct logical form, ` j = `i, then tj is taken as the approximate maximizer. 29 2.3 Discussion This chapter...where j indexes entity tuples (e1, e2). Training optimizes the semantic parser parameters θ to predict Y = yj,Z = zj given S = sj . The parameters θ...be au tif ul / J J N 1 /N 1 λ f .f L on do n /N N P N λ x .M (x ,“ lo nd on ”, C IT Y ) N : λ x .M (x ,“ lo nd on ”, C IT Y ) (S [d cl ]\\N

Alternative Optical Architectures for Multichannel Adaptive Optical Processing

DTIC Science & Technology

1993-04-01

0j +,de 2; j__ -L12 izi j=#1 Pj F2VSIm YS F2 vdI ) N X exp[,2 x (,j + fF,)t]w.-- akx 2 f Fxxp(-j2Xskr W, (16)fsL 2Iu(-LJ:aherir F2VsIJX( 2 fk))r(6 ka...1:512) -off-we); Puss (offset) -1; Rl-Puls8. *31n(2*pi* ([1: 2048 )4phaisrr ./10.24); sukx1la±(221) ,plM (Rl) tit~le ( ’sen chanrnel niqual’) U~sin loop

KSC-2012-1824

NASA Image and Video Library

2012-01-30

HAWTHORNE, Calif. -- NASA astronauts and industry experts check out the crew accommodations in the Dragon spacecraft under development by Space Exploration Technologies SpaceX of Hawthorne, Calif., for the agency's Commercial Crew Program. On top, from left, are NASA Crew Survival Engineering Team Lead Dustin Gohmert, NASA astronauts Tony Antonelli and Lee Archambault, and SpaceX Mission Operations Engineer Laura Crabtree. On bottom, from left, are SpaceX Thermal Engineer Brenda Hernandez and NASA astronauts Rex Walheim and Tim Kopra. In 2011, NASA selected SpaceX during Commercial Crew Development Round 2 CCDev2) activities to mature the design and development of a crew transportation system with the overall goal of accelerating a United States-led capability to the International Space Station. The goal of CCP is to drive down the cost of space travel as well as open up space to more people than ever before by balancing industry’s own innovative capabilities with NASA's 50 years of human spaceflight experience. Six other aerospace companies also are maturing launch vehicle and spacecraft designs under CCDev2, including Alliant Techsystems Inc. ATK, The Boeing Co., Excalibur Almaz Inc., Blue Origin, Sierra Nevada, and United Launch Alliance ULA. For more information, visit www.nasa.gov/commercialcrew. Image credit: Space Exploration Technologies

Algorithms for Nonlinear Least-Squares Problems

DTIC Science & Technology

1988-09-01

O -,i(x) 2 , where each -,(x) is a smooth function mapping Rn to R. J - The m x n Jacobian matrix of f. ... x g - The gradient of the nonlinear least...V211f(X*)I112~ l~ l) J(xk)T J(xk) 2 + O(k - X*) For more convergence results and detailed convergence analysis for the Gauss-Newton method, see, e. g ...for a class of nonlinear least-squares problems that includes zero-residual prob- lems. The function Jt is the pseudo-inverse of Jk (see, e. g

Nonadiabatic dynamics of O(1D) + N2(X1Σg+) → O(3P) + N2(X1Σg+) on three coupled potential surfaces: symmetry, Coriolis, spin-orbit, and Renner-Teller effects.

PubMed

Defazio, Paolo; Gamallo, Pablo; Petrongolo, Carlo

2012-02-07

We present the spin-orbit (SO) and Renner-Teller (RT) quantum dynamics of the spin-forbidden quenching O((1)D) + N(2)(X(1)Σ(g)(+)) → O((3)P) + N(2)(X(1)Σ(g)(+)) on the N(2)O X(1)A', ã(3)A", and b(3)A' coupled PESs. We use the permutation-inversion symmetry, propagate coupled-channel (CC) real wavepackets, and compute initial-state-resolved probabilities and cross sections σ(j(0)) for the ground vibrational and the first two rotational states of N(2), j(0) = 0 and 1. Labeling symmetry angular states by j and K, we report selection rules for j and for the minimum K value associated with any electronic state, showing that ã(3)A" is uncoupled in the centrifugal-sudden (CS) approximation at j(0) = 0. The dynamics is resonance-dominated, the probabilities are larger at low K, σ(j(0)) decrease with the collision energy and increase with j(0), and the CS σ(0) is lower than the CC one. The nonadiabatic interactions play different roles on the quenching dynamics, because the X(1)A'-b(3)A' SO effects are those most important while the ã(3)A"-b(3)A' RT ones are negligible.

Longitudinal aerodynamic characteristics of a large scale model with a swept wing and augmented jet flap in ground effect

NASA Technical Reports Server (NTRS)

Falarski, M. D.; Koenig, D. G.

1972-01-01

The investigation of the in-ground-effect, longitudinal aerodynamic characteristics of a large scale swept augmentor wing model is presented, using 40 x 80 ft wind tunnel. The investigation was conducted at three ground heights; h/c equals 2.01, 1.61, and 1.34. The induced effect of underwing nacelles, was studied with two powered nacelle configurations. One configuration used four JT-15D turbofans while the other used two J-85 turbojet engines. Two conical nozzles on each J-85 were used to deflect the thrust at angles from 0 to 120 deg. Tests were also performed without nacelles to allow comparison with previous data from ground effect.

High expression of survivin and down-regulation of Stat-3 characterize the feto-maternal interface in failing murine pregnancies during the implantation period.

PubMed

Garcia, Mariana G; Tirado-Gonzalez, Irene; Handjiski, Bori; Tometten, Mareike; Orsal, Arif S; Hajos, Silvia E; Fernández, Nelson; Arck, Petra C; Blois, Sandra M

2007-07-01

The materno-fetal interface has for long been considered as an immune privileged biological site and thus understanding the mechanisms underlying fetal survival have been the focus of intense research. In adults, survivin and Stat-3 proteins are involved in tolerance as well as the induction of apoptosis. However, the role of these molecules in pregnancy and development has not been addressed. We have evaluated the expression of survivin and Stat-3 in allogeneic mouse models of low abortions (CBA/J x Balb/c), abortion prone (CBA/J x DBA/2J) and stress-triggered abortions from DBA/2J-mated CBA/J mice. We show that survivin is over-expressed in abortion-prone mating on gestation day 7.5. This effect was also found in stress-exposed mice, whereas expression was low in normal pregnancy mice. The phosphorylated Stat-3 (p-Stat-3) was down regulated in high abortion mating compared with low abortion mating, CBA/J x Balb/c. The level of apoptosis was similar in the three groups studied. Our results suggest that high expression of survivin and low expression of p-Stat-3 are involved in pregnancy loss in mice.

NASA's Hypersonic Research Engine Project: A review

NASA Technical Reports Server (NTRS)

Andrews, Earl H.; Mackley, Ernest A.

1994-01-01

The goals of the NASA Hypersonic Research Engine (HRE) Project, which began in 1964, were to design, develop, and construct a high-performance hypersonic research ramjet/scramjet engine for flight tests of the developed concept over the speed range of Mach 4 to 8. The project was planned to be accomplished in three phases: project definition, research engine development, and flight test using the X-15A-2 research airplane, which was modified to carry hydrogen fuel for the research engine. The project goal of an engine flight test was eliminated when the X-15 program was canceled in 1968. Ground tests of full-scale engine models then became the focus of the project. Two axisymmetric full-scale engine models, having 18-inch-diameter cowls, were fabricated and tested: a structural model and combustion/propulsion model. A brief historical review of the project, with salient features, typical data results, and lessons learned, is presented. An extensive number of documents were generated during the HRE Project and are listed.

SEARCHES FOR MILLISECOND PULSAR CANDIDATES AMONG THE UNIDENTIFIED FERMI OBJECTS

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

Hui, C. Y.; Park, S. M.; Hu, C. P.

2015-08-10

Here we report the results of searching millisecond pulsar (MSP) candidates from the Fermi LAT second source catalog (2FGL). Seven unassociated γ-ray sources in this catalog are identified as promising MSP candidates based on their γ-ray properties. Through the X-ray analysis, we have detected possible X-ray counterparts, localized to an arcsecond accuracy. We have systematically estimated their X-ray fluxes and compared them with the corresponding γ-ray fluxes. The X-ray to γ-ray flux ratios for 2FGL J1653.6-0159 and 2FGL J1946.4-5402 are comparable with the typical value for pulsars. For 2FGL J1625.2-0020, 2FGL J1653.6-0159, and 2FGL J1946.4-5402, their candidate X-ray counterparts aremore » bright enough to perform a detailed spectral and temporal analysis to discriminate their thermal/non-thermal nature and search for the periodic signal. We have also searched for possible optical/IR counterparts at the X-ray positions. For the optical/IR source coincident with the brightest X-ray object associated with 2FGL J1120.0-2204, its spectral energy distribution is comparable with a late-type star. Evidence for the variability has also been found by examining its optical light curve. All the aforementioned 2FGL sources resemble a pulsar in one or more aspects, making them promising targets for follow-up investigations.« less

Early Training Estimation System

DTIC Science & Technology

1980-08-01

first year efforts in CTES development were Cecil Wakelin, Gavin Livingstone, Ray Walsh« Peter Weddle, David Herlihy, Laurel Brown, Drs. Paul Ronco...and Society, 1980, pp. 1067-1974. David , J., Price, J. Successful communication in full scale engineering development statements of work. Air Force...1980, U.S. Army Engineering Laboratory. Shrier , S. Algorithms for system design. Proceedings of the International Conference on Cybernetics and

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

Stephen W. Feldberg; Lewis, Ernie R.

In this study, the principle of unchanging total concentration as described by Oldham and Feldberg [J. Phys. Chem. B, 103, 1699 (1999)] is invoked to analyze systems comprising a redox pair (X z1 1 and X z2 2) plus one or more non-electroactive species (X z3 3,X z4 4...X zjmax jmax) where X zj j is the j th species with charge z j and concentration; c j. The principle states that if the diffusion coefficients for all species are identical and mass transport is governed by the Nernst-Planck expression, the total concentration does not change during any electrochemical perturbation,more » i.e.: Σ jmax j=1[X zj j]=Σ jmax j=1 c j = S P With this principle we deduce the electrochemically induced difference between the surface and bulk concentrations for each species. Those concentration differences are translated into density differences which are a function of the density of the solvent and of the concentration differences, molecular masses and the standard partial molar volumes of all species. Those density differences in turn can induce convection that will ultimately modify the observed current. However, we did not attempt to quantify details of the natural convection and current modification produced by those density differences.« less

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.

Information Protection Engineering: Using Technology and Experience to Protect Assets

DTIC Science & Technology

2001-07-01

SAIC’s highly experienced team has developed technology, techniques and expertise in protecting these information assets from electronic attack by...criminals, terrorists, hackers or nation states. INFORMATION PROTECTION ENGINEERING : Using Technology and Experience to Protect Assets William J. Marlow... Engineering : Using Technology and Experience to Protect Assets Contract or Grant Number Program Element Number Authors Marlow, William J. Project

EDITORIAL: MEMS in biology and medicine MEMS in biology and medicine

NASA Astrophysics Data System (ADS)

Pruitt, Beth L.; Herr, Amy E.

2011-05-01

Stimulating—the first word that springs to mind regarding the emerging and expanding role of MEMS in biological inquiry. When invited to guest-edit this special issue on 'MEMS in biology and medicine' for JMM, we jumped at the opportunity. Partly owing to the breadth of the stimulating research in this nascent area and partly owing to the stimulating of biological function made possible with MEMS accessible length and time scales, we were eager to assemble manuscripts detailing some of the most cutting edge biological research being conducted around the globe. In addition to cutting edge engineering, this special issue features challenging biological questions addressed with innovative MEMS technologies. Topics span from Yetisen and colleagues' inquiry into quantifying pollen tube behaviour in response to pistil tissues [1] to Morimoto and colleagues' engineering efforts to produce monodisperse droplets capable of encapsulating single cells (without surface modification) [2]. Questions are bold, including a means to achieve therapeutically-relevant scaling for enrichment of leukocytes from blood (Inglis et al [3]), assessing the dependence of Escherichia coli biofilm formation on bacterial signalling (Meyer et al [4]), and elucidation of adhesion dynamics of circulating tumour cells (Cheung et al [5]) among others. Technologies are diverse, including microfabricated magnetic actuators (Lee et al [6]), stimuli-responsive polymer nanocomposites (Hess et al [7]), and SU-8 electrothermal microgrippers (Chu et al [8]) to name but a few. Contributing authors do indeed span a large swathe of the globe, with contributions from Australia, Italy, China, Canada, Denmark, Japan, the USA and numerous other locations. Collaboration finds a home here—with researchers from macromolecular science and electrical engineering collaborating with the Veterans Affairs Medical Center or neurosurgery researchers working with biological and electrical engineers. The questions posed by this generation of MEMS researchers encapsulate the mission of JMM to 'cover all aspects of microelectromechanical systems, devices and structures as well as micromechanics, microengineering and microfabrication' as the physics and chemical processes under study match the scales of the MEMS technologies now possible. As evidenced by the articles assembled in this issue, the combined maturation of both our biological model systems and our tools is driving a new paradigm in the formulation of biological hypotheses. The intersection of MEMS with cell biology is evidenced in reviews of both methods for applying microscale forces in biological environments by Zheng and Zhang [9] as well as the manipulation of biology through mechanical interactions by Rajagopalan and Saif [10]. Additionally, the potential for microfluidic platforms to miniaturize and improve for a diverse set of biological measurements and assays for medical diagnostics is further reviewed by Tentori and Herr [11]. We hope that you find, as we do, this special issue to be 'essential reading for all MEMS researchers' and perhaps even of technical interest to your life sciences colleagues. References [1] Yetisen A K et al 2011 J. Micromech. Microeng. 21 054018 [2] Morimoto Y et al 2011 J. Micromech. Microeng. 21 054031 [3] Inglis D W et al 2011 J. Micromech. Microeng. 21 054024 [4] Meyer M T et al 2011 J. Micromech. Microeng. 21 054023 [5] Cheung L S-L et al 2011 J. Micromech. Microeng. 21 054033 [6] Lee S A et al 2011 J. Micromech. Microeng. 21 054006 [7] Hess A E et al 2011 J. Micromech. Microeng. 21 054009 [8] Chu J et al 2011 J. Micromech. Microeng. 21 054030 [9] Zheng X R and Zhang X 2011 J. Micromech. Microeng. 21 054003 [10] Rajagopalan J and Saif M T A 2011 J. Micromech. Microeng. 21 054002 [11] Tentori A M and Herr A E 2011 J. Micromech. Microeng. 21 054001

Measurements of double-helicity asymmetries in inclusive J /ψ production in longitudinally polarized p +p collisions at √{s }=510 GeV

NASA Astrophysics Data System (ADS)

Adare, A.; Aidala, C.; Ajitanand, N. N.; Akiba, Y.; Akimoto, R.; Alfred, M.; Apadula, N.; Aramaki, Y.; Asano, H.; Atomssa, E. T.; Awes, T. C.; Azmoun, B.; Babintsev, V.; Bai, M.; Bandara, N. S.; Bannier, B.; Barish, K. N.; Bathe, S.; Bazilevsky, A.; Beaumier, M.; Beckman, S.; Belmont, R.; Berdnikov, A.; Berdnikov, Y.; Black, D.; Blau, D. S.; Bok, J. S.; Boyle, K.; Brooks, M. L.; Bryslawskyj, J.; Buesching, H.; Bumazhnov, V.; Campbell, S.; Chen, C.-H.; Chi, C. Y.; Chiu, M.; Choi, I. J.; Choi, J. B.; Chujo, T.; Citron, Z.; Csanád, M.; Csörgő, T.; Danley, T. W.; Datta, A.; Daugherity, M. S.; David, G.; Deblasio, K.; Dehmelt, K.; Denisov, A.; Deshpande, A.; Desmond, E. J.; Ding, L.; Dion, A.; Diss, P. B.; Do, J. H.; Drees, A.; Drees, K. A.; Durham, J. M.; Durum, A.; Enokizono, A.; En'yo, H.; Esumi, S.; Fadem, B.; Feege, N.; Fields, D. E.; Finger, M.; Finger, M.; Fokin, S. L.; Frantz, J. E.; Franz, A.; Frawley, A. D.; Gal, C.; Gallus, P.; Garg, P.; Ge, H.; Giordano, F.; Glenn, A.; Goto, Y.; Grau, N.; Greene, S. V.; Grosse Perdekamp, M.; Gu, Y.; Gunji, T.; Guragain, H.; Hachiya, T.; Haggerty, J. S.; Hahn, K. I.; Hamagaki, H.; Hamilton, H. F.; Han, S. Y.; Hanks, J.; Hasegawa, S.; Haseler, T. O. S.; Hashimoto, K.; He, X.; Hemmick, T. K.; Hill, J. C.; Hollis, R. S.; Homma, K.; Hong, B.; Hoshino, T.; Hotvedt, N.; Huang, J.; Huang, S.; Ikeda, Y.; Imai, K.; Imazu, Y.; Inaba, M.; Iordanova, A.; Isenhower, D.; Ivanishchev, D.; Jacak, B. V.; Jeon, S. J.; Jezghani, M.; Jia, J.; Jiang, X.; Johnson, B. M.; Joo, E.; Joo, K. S.; Jouan, D.; Jumper, D. S.; Kanda, S.; Kang, J. H.; Kang, J. S.; Kawall, D.; Kazantsev, A. V.; Key, J. A.; Khachatryan, V.; Khanzadeev, A.; Kihara, K.; Kim, C.; Kim, D. H.; Kim, D. J.; Kim, E.-J.; Kim, G. W.; Kim, H.-J.; Kim, M.; Kim, Y. K.; Kimelman, B.; Kistenev, E.; Kitamura, R.; Klatsky, J.; Kleinjan, D.; Kline, P.; Koblesky, T.; Kofarago, M.; Komkov, B.; Koster, J.; Kotov, D.; Kurita, K.; Kurosawa, M.; Kwon, Y.; Lacey, R.; Lajoie, J. G.; Lebedev, A.; Lee, K. B.; Lee, S.; Lee, S. H.; Leitch, M. J.; Leitgab, M.; Li, X.; Lim, S. H.; Liu, M. X.; Lynch, D.; Makdisi, Y. I.; Makek, M.; Manion, A.; Manko, V. I.; Mannel, E.; McCumber, M.; McGaughey, P. L.; McGlinchey, D.; McKinney, C.; Meles, A.; Mendoza, M.; Meredith, B.; Miake, Y.; Mignerey, A. C.; Miller, A. J.; Milov, A.; Mishra, D. K.; Mitchell, J. T.; Miyasaka, S.; Mizuno, S.; Mohanty, A. K.; Montuenga, P.; Moon, T.; Morrison, D. P.; Moukhanova, T. V.; Murakami, T.; Murata, J.; Mwai, A.; Nagamiya, S.; Nagashima, K.; Nagle, J. L.; Nagy, M. I.; Nakagawa, I.; Nakagomi, H.; Nakano, K.; Nattrass, C.; Netrakanti, P. K.; Nihashi, M.; Niida, T.; Nishimura, S.; Nouicer, R.; Novák, T.; Novitzky, N.; Nyanin, A. S.; O'Brien, E.; Ogilvie, C. A.; Orjuela Koop, J. D.; Osborn, J. D.; Oskarsson, A.; Ozawa, K.; Pak, R.; Pantuev, V.; Papavassiliou, V.; Park, J. S.; Park, S.; Pate, S. F.; Patel, L.; Patel, M.; Peng, J.-C.; Perepelitsa, D. V.; Perera, G. D. N.; Peressounko, D. Yu.; Perry, J.; Petti, R.; Pinkenburg, C.; Pinson, R.; Pisani, R. P.; Purschke, M. L.; Rak, J.; Ramson, B. J.; Ravinovich, I.; Read, K. F.; Reynolds, D.; Riabov, V.; Riabov, Y.; Rinn, T.; Riveli, N.; Roach, D.; Rolnick, S. D.; Rosati, M.; Rowan, Z.; Rubin, J. G.; Sahlmueller, B.; Saito, N.; Sakaguchi, T.; Sako, H.; Samsonov, V.; Sarsour, M.; Sato, S.; Sawada, S.; Schaefer, B.; Schmoll, B. K.; Sedgwick, K.; Seele, J.; Seidl, R.; Sen, A.; Seto, R.; Sett, P.; Sexton, A.; Sharma, D.; Shein, I.; Shibata, T.-A.; Shigaki, K.; Shimomura, M.; Shukla, P.; Sickles, A.; Silva, C. L.; Silvermyr, D.; Singh, B. K.; Singh, C. P.; Singh, V.; Slunečka, M.; Snowball, M.; Soltz, R. A.; Sondheim, W. E.; Sorensen, S. P.; Sourikova, I. V.; Stankus, P. W.; Stepanov, M.; Stoll, S. P.; Sugitate, T.; Sukhanov, A.; Sumita, T.; Sun, J.; Sziklai, J.; Takahara, A.; Taketani, A.; Tanida, K.; Tannenbaum, M. J.; Tarafdar, S.; Taranenko, A.; Tieulent, R.; Timilsina, A.; Todoroki, T.; Tomášek, M.; Torii, H.; Towell, C. L.; Towell, M.; Towell, R.; Towell, R. S.; Tserruya, I.; van Hecke, H. W.; Vargyas, M.; Velkovska, J.; Virius, M.; Vrba, V.; Vznuzdaev, E.; Wang, X. R.; Watanabe, D.; Watanabe, Y.; Watanabe, Y. S.; Wei, F.; Whitaker, S.; White, A. S.; Wolin, S.; Woody, C. L.; Wysocki, M.; Xia, B.; Xue, L.; Yalcin, S.; Yamaguchi, Y. L.; Yanovich, A.; Yoo, J. H.; Yoon, I.; Younus, I.; Yu, H.; Yushmanov, I. E.; Zajc, W. A.; Zelenski, A.; Zhou, S.; Zou, L.; Phenix Collaboration

2016-12-01

We report the double-helicity asymmetry, ALL J /ψ, in inclusive J /ψ production at forward rapidity as a function of transverse momentum pT and rapidity |y |. The data analyzed were taken during √{s }=510 GeV longitudinally polarized p +p collisions at the Relativistic Heavy Ion Collider in the 2013 run using the PHENIX detector. At this collision energy, J /ψ particles are predominantly produced through gluon-gluon scatterings, thus ALL J /ψ is sensitive to the gluon polarization inside the proton. We measured ALL J /ψ by detecting the decay daughter muon pairs μ+μ- within the PHENIX muon spectrometers in the rapidity range 1.2 <|y |<2.2 . In this kinematic range, we measured the ALL J /ψ to be 0.012 ±0.010 (stat) ±0.003 (syst). The ALL J /ψ can be expressed to be proportional to the product of the gluon polarization distributions at two distinct ranges of Bjorken x : one at moderate range x ≈5 ×10-2 where recent data of jet and π0 double helicity spin asymmetries have shown evidence for significant gluon polarization, and the other one covering the poorly known small-x region x ≈2 ×10-3. Thus our new results could be used to further constrain the gluon polarization for x <5 ×10-2.

Development of a Smooth Trajectory Maneuver Method to Accommodate the Ares I Flight Control Constraints

NASA Technical Reports Server (NTRS)

Pinson, Robin M.; Schmitt, Terri L.; Hanson, John M.

2008-01-01

Six degree-of-freedom (DOF) launch vehicle trajectories are designed to follow an optimized 3-DOF reference trajectory. A vehicle has a finite amount of control power that it can allocate to performing maneuvers. Therefore, the 3-DOF trajectory must be designed to refrain from using 100% of the allowable control capability to perform maneuvers, saving control power for handling off-nominal conditions, wind gusts and other perturbations. During the Ares I trajectory analysis, two maneuvers were found to be hard for the control system to implement; a roll maneuver prior to the gravity turn and an angle of attack maneuver immediately after the J-2X engine start-up. It was decided to develop an approach for creating smooth maneuvers in the optimized reference trajectories that accounts for the thrust available from the engines. A feature of this method is that no additional angular velocity in the direction of the maneuver has been added to the vehicle after the maneuver completion. This paper discusses the equations behind these new maneuvers and their implementation into the Ares I trajectory design cycle. Also discussed is a possible extension to adjusting closed-loop guidance.

X-15 test pilots - Engle, Rushworth, McKay, Knight, Thompson, and Dana

NASA Technical Reports Server (NTRS)

1966-01-01

The X-15 flight crew, left to right; Air Force Captain Joseph H. Engle, Air Force Major Robert A. Rushworth, NASA pilot John B. 'Jack' McKay, Air Force pilot William J. 'Pete' Knight, NASA pilot Milton O. Thompson, and NASA pilot Bill Dana. of their 125 X-15 flights, 8 were above the 50 miles that constituted the Air Force's definition of the beginning of space (Engle 3, Dana 2, Rushworth, Knight, and McKay one each). NASA used the international definition of space as beginning at 62 miles above the earth. The X-15 was a rocket-powered aircraft 50 ft long with a wingspan of 22 ft. It was a missile-shaped vehicle with an unusual wedge-shaped vertical tail, thin stubby wings, and unique fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was capable of developing 57,000 lb of rated thrust (actual thrust reportedly climbed to 60,000 lb). North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow-on program used the aircraft as a testbed to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudder surfaces on the vertical stabilizers to control yaw and canted horizontal surfaces on the tail to control pitch when moving in synchronization or roll when moved differentially. For flight in the thin air outside of the appreciable Earth's atmosphere, the X-15 used a reaction control system. Hydrogen peroxide thrust rockets located on the nose of the aircraft provided pitch and yaw control. Those on the wings provided roll control. Because of the large fuel consumption, the X-15 was air launched from a B-52 aircraft at 45,000 ft and a speed of about 500 mph. Depending on the mission, the rocket engine provided thrust for the first 80 to 120 sec of flight. The remainder of the normal 10 to 11 min. flight was powerless and ended with a 200-mph glide landing. Generally, one of two types of X-15 flight profiles was used: a high-altitude flight plan that called for the pilot to maintain a steep rate of climb, or a speed profile that called for the pilot to push over and maintain a level altitude. The X-15 was flown over a period of nearly 10 years--June 1959 to Oct. 1968--and set the world's unofficial speed and altitude records of 4,520 mph (Mach 6.7) and 354,200 ft (over 67 mi) in a program to investigate all aspects of piloted hypersonic flight. Information gained from the highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo manned spaceflight programs, and also the Space Shuttle program. The X-15s made a total of 199 flights and were manufactured by North American Aviation. X-15-1, serial number 56-6670, is now located at the National Air and Space Museum, Washington DC. North American X-15A-2, serial number 56-6671, is at the United States Air Force Museum, Wright-Patterson AFB, Ohio. The X-15-3, serial number 56-6672, crashed on 15 November 1967, resulting in the death of Maj. Michael J. Adams.

An Efficient Algorithm for a Visibility-Based Surveillance-Evasion Game

DTIC Science & Technology

2012-01-01

function vs : Ω2free → R for the static game as (8) vs(x0E , x 0 P ) := sup σP∈ A inf σE∈ A J (x0E , x0P , σE , σP ). In general, it can be shown that...the optimal controls (or -suboptimal controls, see Remark 2.2), formally written as σ∗P ∈ arg sup σP∈ A inf σE∈ A J (x0E , x0P , σE , σP ),(9) σ∗E...arg inf σE∈ A J (x0E , x0P , σE , σ∗P ),(10) provided the game ends in finite time. For brevity, we shall refer to the static visibility-based

Saturn Apollo Program

NASA Image and Video Library

1965-04-26

Two technicians watch carefully as cables prepare to lift a J-2 engine into a test stand. The J-2 powered the second stage and the third stage of the Saturn V moon rocket. The towering 363-foot Saturn V was a multi-stage, multi-engine launch vehicle standing taller than the Statue of Liberty. Altogether, the Saturn V engines produced as much power as 85 Hoover Dams.

The monoclonal antibody that recognizes an epitope in the C-terminal region of the fibrinogen alpha-chain reacts with soluble fibrin and fibrin monomer generated by thrombin but not with those formed as plasmin degradation products.

PubMed

Suzuki, Akiko; Ebinuma, Hiroyuki; Matsuo, Masanao; Miyazaki, Osamu; Yago, Hirokazu

2007-01-01

The presence of soluble fibrin (SF) provides evidence of thrombin activation in the blood; therefore, SF is a useful marker for diagnosing blood coagulation diseases such as disseminated intravascular coagulation (DIC). The antibody that specifically detects SF could be a useful tool for diagnosing thrombotic diseases. By using an acid-solubilized desAA-FM (fibrin monomer) as an immunogen, we developed a monoclonal antibody, namely J2-23, which specifically reacts with SF and FM. We examined the specificity of J2-23 by ELISA and immunoblotting and confirmed the reactivity of J2-23 with SF and FM by gel filtration. J2-23 specifically reacted with SF, but not with fibrinogen or plasmic fibrinogen-derived Fbg-X, Fbg-Y, Fbg-E, and D; thrombin-treated Fbn-X, Fbn-Y, and Fbn-E; and plasmic cross-linked fibrin (DD, XDP). The epitope recognized by J2-23 was located within the Aalpha 502-521 region on the C-terminal of the fibrinogen alpha-chain. The reactivity of J2-23 disappeared following the action of the fibrinolytic enzyme plasmin. Furthermore, J2-23 reacted not only with SF but also with FM in plasma from DIC patients. This indicated that J2-23 specifically detected coagulation without reflecting the plasmin action. We demonstrated the potential of J2-23 as a useful antibody for detecting SF for diagnosing blood coagulation.

Pulsed Laser Device Development Program. Volume 3. ABEL II (Air- Breathing Electric Laser II) Small-Scale Flow Test Report

DTIC Science & Technology

1981-06-01

about 0.18 x 104 f or X 5260 A. 4.3 EFFECT OF FLOW PLATE In this series of experiments, we studied the effect of a screen positioned over the orifice... 104 Ŕ 0 A -03 -0.2 -0.1 0 0.1 0.2 0.3 RaU1 U2 WR I+u 2 J9683 Figure 14 Effect of Shear on Phase Aberration; = 5260 .• 42 -AVCO EVERETT in Fiue1; 56...US Army Missile Command Redstone Arsenal, AL 35898 Attn: DRSMI- RHB , Dr. T.A. Roberts RHE, Mr. J.C. Walters - RHC, Mr. K. Smith RHC, Mr. Myron Cole

Saturn Apollo Program

NASA Image and Video Library

1963-01-01

J-2 engines for the Saturn IB/Saturn V launch vehicles are lined up in the assembly area at Rocketdyne's manufacturing plant in Canoga Park, California. Five J-2 engines provided more than 1,000,000 pounds of thrust to accelerate the second stage toward a Moon trajectory.

Sur la modélisation des supraconducteurs: le "modèle de l'état critique" de bean, en trois dimensions

NASA Astrophysics Data System (ADS)

Bossavit, A.

1994-03-01

La formule (22), p. 386, soit u_x(v) = si|v| < j_c(x); alors; 0; sinon; ρ(x)|v|^2/2, aurait dû être u_x(v) = si|v| < j_c(x); alors; 0; sinon; ρ(x)(|v|^2)/2. La même erreur apparaît dans l'introduction (page 376, une ligne après l'équation (10)) et page 390.

Elliptic Curve Integral Points on y2 = x3 + 3x ‑ 14

NASA Astrophysics Data System (ADS)

Zhao, Jianhong

2018-03-01

The positive integer points and integral points of elliptic curves are very important in the theory of number and arithmetic algebra, it has a wide range of applications in cryptography and other fields. There are some results of positive integer points of elliptic curve y 2 = x 3 + ax + b, a, b ∈ Z In 1987, D. Zagier submit the question of the integer points on y 2 = x 3 ‑ 27x + 62, it count a great deal to the study of the arithmetic properties of elliptic curves. In 2009, Zhu H L and Chen J H solved the problem of the integer points on y 2 = x 3 ‑ 27x + 62 by using algebraic number theory and P-adic analysis method. In 2010, By using the elementary method, Wu H M obtain all the integral points of elliptic curves y 2 = x 3 ‑ 27x ‑ 62. In 2015, Li Y Z and Cui B J solved the problem of the integer points on y 2 = x 3 ‑ 21x ‑ 90 By using the elementary method. In 2016, Guo J solved the problem of the integer points on y 2 = x 3 + 27x + 62 by using the elementary method. In 2017, Guo J proved that y 2 = x 3 ‑ 21x + 90 has no integer points by using the elementary method. Up to now, there is no relevant conclusions on the integral points of elliptic curves y 2 = x 3 + 3x ‑ 14, which is the subject of this paper. By using congruence and Legendre Symbol, it can be proved that elliptic curve y 2 = x 3 + 3x ‑ 14 has only one integer point: (x, y) = (2, 0).

Research in Electronics - JSEP (Joint Services Electronics Program)

DTIC Science & Technology

1982-04-01

intramolecular V-E coupling in ir laser excited polyatomicso, J. Chem. Phys. 25, 5311 (1981). 5. H . Helvajian and C. Wittig, nVibrational quenching of HgBr(X...Phys. Chem. 86, 438 (1982). 13. H . Helvajian and C. Wittig, "Collisional deexcitation of Hg(6 3po) by HgBr(X), Br(4 2p)8, and Br2(X): evidence for ion...Distribution List. Sincerely, William H . Steier Director Enclosures fJS (j A Y j LI I .. . . . ... rJ .. .. -.. ,1L Lu. UNIVERSITY OF SOUTHERN

Blast Overpressure Studies with Animals and Man: Biological Response to Complex Blast Waves

DTIC Science & Technology

1993-10-31

cases, hemorrhage and edema reduced the lumen diameter of the organ making it difficult to breath. In subjects with extensive lung hemorrhage, confluent...IAF ui UU LU WiL N .4 C A p ... 4 n 1 - u- --- -j -j -j*-1 LA ZN MA’ P W I 4A MC I A U A( A fac U a*gJ*J~ U09 "~L rn in CM ININ~~ :2-. :2 a) - 41...tuU UU j ** ~ ~ ~ ( (A 0O~ -t u’ CO (Ao -*~~~L us~N-sr, ULA -U z, zd z~ 2*- . .01 -0 c Xo cm 1:2 𔃺 CO 2 L^m C .- Mp i m 3 - K -1§ LA x ’U.’x 0’ x Ixx

A Multi-Wavelength Search for a Counterpart of the Unidentified Gamma-ray source 3EG J2020+4017 (2CG078+2)

NASA Technical Reports Server (NTRS)

Becker, Werner; Weisskopf, Martin C.; Arzoumanian, Zaven; Lorimer, Duncan; Camilo, Fernando; Elsner, Ronald F.; Kanbach, Gottfried; Reimer, Olaf; Swartz, Douglas A.; Tennant, Allyn F.

2004-01-01

In search of the counterpart to the brightest unidentified gamma-ray source 3EG J2020+4017 (2CG078+2) we report on new X-ray and radio observations of the gamma-Cygni field with the Chandra X-ray Observatory and with the Green Bank Telescope (GBT). We also report on reanalysis of archival ROSAT data. With Chandra it became possible for the first time to measure the position of the putative gamma-ray counterpart RX J2020.2+4026 with sub-arcsec accuracy and to deduce its X-ray spectral characteristics. These observations demonstrate that RX J2020.2+4026 is associated with a K field star and therefore is unlikely to be the counterpart of the bright gamma-ray source 2CG078+2 in the SNR G78.2+2.1 as had been previously suggested. The Chandra observation detected 37 additional X-ray sources which were correlated with catalogs of optical and infrared data. Subsequent GBT radio observations covered the complete 99% EGRET likelihood contour of 3EG J2020+4017 with a sensitivity limit of L(sub 820) approx. 0.1 mJy kpc(exp 2) which is lower than most of the recent deep radio search limits. If there is a pulsar operating in 3EG J2020+4017, this sensitivity limit suggests that the pulsar either does not produce significant amounts of radio emission or that its geometry is such that the radio beam does not intersect with the line of sight. Finally, reanalysis of archival ROSAT data leads to a flux upper limit of f(sub x)(0.1-2.4 keV) < 1.8 x 10(exp -13) erg/s/sq cm for a putative point-like X-ray source located within the 68% confidence contour of 3EG J2020+4017. Adopting the SNR age of 5400 yrs and assuming a spin-down to X-ray energy conversion factor of 10(exp -3) this upper limit constraints the parameters of a putative neutron star as a counterpart for 3EG J2020+4017 to be P > or approx. 160/(d/1.5 kpc) ms, P > or approx. 5 x 10(exp -13)/(d/1.5kpc) s s1 and B > or approx. 9 x 10(exp 12)/(d/1.5 kpc) G.

Experimental Investigation of Axial and Beam-Riding Propulsive Physics with TEA CO{sub 2} laser

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

Kenoyer, D. A.; Salvador, I.; Myrabo, L. N.

2010-10-08

A twin Lumonics K922M pulsed TEA CO{sub 2} laser system (pulse duration of approximately 100 ns FWHM spike, with optional 1 {mu}s tail, depending upon laser gas mix) was employed to experimentally measure both axial thrust and beam-riding behavior of Type no. 200 lightcraft engines, using a ballistic pendulum and Angular Impulse Measurement Device (AIMD, respectively. Beam-riding forces and moments were examined along with engine thrust-vectoring behavior, as a function of: a) laser beam lateral offset from the vehicle axis of symmetry; b) laser pulse energy ({approx}12 to 40 joules); c) pulse duration (100 ns, and 1 {mu}s); and d)more » engine size (97.7 mm to 161.2 mm). Maximum lateral momentum coupling coefficients (C{sub M}) of 75 N-s/MJ were achieved with the K922M laser whereas previous PLVTS laser (420 J, 18 {mu}s duration) results reached only 15 N-s/MJ--an improvement of 5x. Maximum axial C{sub M} performance with the K922M reached 225 N-s/MJ, or about {approx}3x larger than the lateral C{sub M} values. These axial C{sub M} results are sharply higher than the 120 N/MW previously reported for long pulse (e.g., 10-18 {mu}s)CO{sub 2} electric discharge lasers.« less

Potential for Imaging Engineered Tissues with X-Ray Phase Contrast

PubMed Central

Appel, Alyssa; Anastasio, Mark A.

2011-01-01

As the field of tissue engineering advances, it is crucial to develop imaging methods capable of providing detailed three-dimensional information on tissue structure. X-ray imaging techniques based on phase-contrast (PC) have great potential for a number of biomedical applications due to their ability to provide information about soft tissue structure without exogenous contrast agents. X-ray PC techniques retain the excellent spatial resolution, tissue penetration, and calcified tissue contrast of conventional X-ray techniques while providing drastically improved imaging of soft tissue and biomaterials. This suggests that X-ray PC techniques are very promising for evaluation of engineered tissues. In this review, four different implementations of X-ray PC imaging are described and applications to tissues of relevance to tissue engineering reviewed. In addition, recent applications of X-ray PC to the evaluation of biomaterial scaffolds and engineered tissues are presented and areas for further development and application of these techniques are discussed. Imaging techniques based on X-ray PC have significant potential for improving our ability to image and characterize engineered tissues, and their continued development and optimization could have significant impact on the field of tissue engineering. PMID:21682604

The role of chemical engineering in medicinal research including Alzheimer's.

PubMed

Kontogeorgis, Georgios M

2015-01-01

Various disciplines of chemical engineering, especially thermodynamics and kinetics, play an important role in medicinal research and this has been particularly recognized during the last 10-15 years (von Stockar and van der Wielen, J Biotechnol 59:25, 1997; Prausnitz, Fluid Phase Equilib 53:439, 1989; Prausnitz, Pure Appl Chem 79:1435, 2007; Dey and Prausnitz, Ind Eng Chem Res 50:3, 2011; Prausnitz, J Chem Thermodynamics 35:21, 2003; Tsivintzelis et al. AIChE J 55:756, 2009). It is expected that during the twenty-first century chemical engineering and especially thermodynamics can contribute as significantly to the life sciences development as it has been done with the oil and gas and chemical sectors in the twentieth century. Moreover, it has during the recent years recognized that thermodynamics can help in understanding diseases like human cataract, sickle-cell anemia, Creuzfeldt-Jacob ("mad cow" disease), and Alzheimer's which are connected to "protein aggregation." Several articles in the Perspectives section of prominent chemical engineering journals have addressed this issue (Hall, AIChE J 54:1956, 2008; Vekilov, AIChE J 54:2508, 2008). This work reviews recent applications of thermodynamics (and other areas of chemical engineering) first in drug development and then in the understanding of the mechanism of Alzheimer's and similar diseases.

Flow processes in overexpanded chemical rocket nozzles. Part 2: Side loads due to asymmetric separation

NASA Technical Reports Server (NTRS)

Schmucker, R. H.

1984-01-01

Methods for measuring the lateral forces, occurring as a result of asymmetric nozzle flow separation, are discussed. The effect of some parameters on the side load is explained. A new method was developed for calculation of the side load. The values calculated are compared with side load data of the J-2 engine. Results are used for predicting side loads of the space shuttle main engine.

ON THE PUZZLING HIGH-ENERGY PULSATIONS OF THE ENERGETIC RADIO-QUIET γ-RAY PULSAR J1813–1246

DOE PAGES

Marelli, M.; Harding, A.; Pizzocaro, D.; ...

2014-10-28

In this study, we have analyzed the new deep XMM-Newton and Chandra observations of the energetic, radio-quiet pulsar J1813–1246. The X-ray spectrum is nonthermal, very hard, and absorbed. Based on spectral considerations, we propose that J1813 is located at a distance further than 2.5 kpc. J1813 is highly pulsed in the X-ray domain, with a light curve characterized by two sharp, asymmetrical peaks, separated by 0.5 in phase. We detected no significant X-ray spectral changes during the pulsar phase. We extended the available Fermi ephemeris to five years. We found two glitches. The γ-ray light curve is characterized by twomore » peaks, separated by 0.5 in phase, with a bridge in between and no off-pulse emission. The spectrum shows clear evolution in phase, being softer at the peaks and hardening toward the bridge. Surprisingly, both X-ray peaks lag behind the γ-ray ones by a quarter of phase. We found a hint of detection in the 30-500 keV band with INTEGRAL, which is consistent with the extrapolation of both the soft X-ray and γ-ray emission of J1813. The unique X-ray and γ-ray phasing suggests a singular emission geometry. We discuss some possibilities within the current pulsar emission models. Finally, we develop an alternative geometrical model where the X-ray emission comes from polar cap pair cascades.« less

On the Puzzling High-Energy Pulsations of the Energetic Radio-Quiet -Ray Pulsar J1813-1246

NASA Technical Reports Server (NTRS)

Marelli, M.; Harding, Alice K.; Pizzocaro, D.; De Luca, A.; Wood, K. S.; Caraveo, P.; Salvetti, D.; Parkinson, P. M.; Acero, F.

2014-01-01

We have analyzed the new deep XMM-Newton and Chandra observations of the energetic, radio-quiet pulsar J1813-1246. The X-ray spectrum is nonthermal, very hard, and absorbed. Based on spectral considerations, we propose that J1813 is located at a distance further than 2.5 kpc. J1813 is highly pulsed in the X-ray domain, with a light curve characterized by two sharp, asymmetrical peaks, separated by 0.5 in phase. We detected no significant X-ray spectral changes during the pulsar phase.We extended the available Fermi ephemeris to five years.We found two glitches. The gamma-ray light curve is characterized by two peaks, separated by 0.5 in phase, with a bridge in between and no off-pulse emission. The spectrum shows clear evolution in phase, being softer at the peaks and hardening toward the bridge. Surprisingly, both X-ray peaks lag behind the gamma-ray ones by a quarter of phase. We found a hint of detection in the 30-500 keV band with INTEGRAL, which is consistent with the extrapolation of both the soft X-ray and gamma-ray emission of J1813. The unique X-ray and gamma-ray phasing suggests a singular emission geometry. We discuss some possibilities within the current pulsar emission models. Finally, we develop an alternative geometrical model where the X-ray emission comes from polar cap pair cascades.

Emission calibration of a J-58 afterburning turbojet engine at simulated supersonic stratospheric flight conditions

NASA Technical Reports Server (NTRS)

Holdeman, J. D.

1974-01-01

Emissions of total oxides of nitrogen, unburned hydrocarbons, and carbon monoxide from a J-58 engine at simulated flight conditions of Mach 2.0, 2.4, and 2.8 at 19.8 km altitude are reported. For each flight condition, measurements were made for four engine power levels from maximum power without afterburning through maximum afterburning. These measurements were made 7 cm downstream of the engine primary nozzle using a single point traversing gas sample probe. Results show that emissions vary with flight speed, engine power level, and with radial position across the exhaust.

Emission calibration of a J-58 afterburning turbojet engine at simulated supersonic, stratospheric flight conditions

NASA Technical Reports Server (NTRS)

Holdeman, J. D.

1974-01-01

Emissions of total oxides of nitrogen, unburned hydrocarbons, and carbon monoxide from a J-58 engine at simulated flight conditions of Mach 2.0, 2.4, and 2.8 at 19.8 km altitude are reported. For each flight condition, measurements were made for four engine power levels from maximum power without afterburning through maximum afterburning. These measurements were made 7 cm downstream of the engine primary nozzle using a single point traversing gas sample probe. Results show that emissions vary with flight speed, engine power level, and with radial position across the exhaust.

Preliminary experimental results of tungsten wire-array Z-pinches on primary test stand

NASA Astrophysics Data System (ADS)

Huang, Xian-Bin; Zhou, Shao-Tong; Dan, Jia-Kun; Ren, Xiao-Dong; Wang, Kun-Lun; Zhang, Si-Qun; Li, Jing; Xu, Qiang; Cai, Hong-Chun; Duan, Shu-Chao; Ouyang, Kai; Chen, Guang-Hua; Ji, Ce; Wei, Bing; Feng, Shu-Ping; Wang, Meng; Xie, Wei-Ping; Deng, Jian-Jun; Zhou, Xiu-Wen; Yang, Yi

2015-07-01

The Primary Test Stand (PTS) developed at the China Academy of Engineering Physics is a 20 TW pulsed power driver, which can deliver a ˜10 MA, 70 ns rise-time (10%-90%) current to a short-circuit load and has important applications in Z-pinch driven inertial confinement fusion and high energy density physics. Preliminary results of tungsten wire-array Z-pinch experiments on PTS are presented. The load geometries investigated include 15-mm-tall cylindrical single and nested arrays with diameter ranging from 13 mm to 30 mm, consisting of 132-300 tungsten wires with 5-10 μm in diameter. Multiple diagnostics were fielded to characterize the x-ray radiation from wire-array Z pinches. The x-ray peak power (˜50 TW) and total radiated energy (˜500 kJ) were obtained from a single 20-mm-diam array with 80-ns stagnation time. The highest x-ray peak power up to 80 TW with 2.4 ns FWHM was achieved by using a nested array with 20-mm outer diameter, and the total x-ray energy from the nested array is comparable to that of single array. Implosion velocity estimated from the time-resolved image measurement exceeds 30 cm/μs. The detailed experimental results and other findings are presented and discussed.

Pnicogen bonded complexes of PO2X (X = F, Cl) with nitrogen bases.

PubMed

Alkorta, Ibon; Elguero, José; Del Bene, Janet E

2013-10-10

An ab initio MP2/aug'-cc-pVTZ study has been carried out on complexes formed between PO2X (X = F and Cl) as the Lewis acids and a series of nitrogen bases ZN, including NH3, H2C═NH, NH2F, NP, NCH, NCF, NF3, and N2. Binding energies of these complexes vary from -10 to -150 kJ/mol, and P-N distances from 1.88 to 2.72 Å. Complexes ZN:PO2F have stronger P(...)N bonds and shorter P-N distances than the corresponding complexes ZN:PO2Cl. Charge transfer from the N lone pair through the π-hole to the P-X and P-O σ* orbitals leads to stabilization of these complexes, although charge-transfer energies can be evaluated only for complexes with binding energies less than -71 kJ/mol. Complexation of PO2X with the strongest bases leads to P···N bonds with a significant degree of covalency, and P-N distances that approach the P-N distances in the molecules PO2NC and PO2NH2. In these complexes, the PO2X molecules distort from planarity. Changes in (31)P absolute chemical shieldings upon complexation do not correlate with changes in charges on P, although they do correlate with the binding energies of the complexes. EOM-CCSD spin-spin coupling constants (1p)J(P-N) are dominated by the Fermi-contact term, which is an excellent approximation to total J. (1p)J(P-N) values are small at long distances, increase as the distance decreases, but then decrease at short P-N distances. At the shortest distances, values of (1p)J(P-N) approach (1)J(P-N) for the molecules PO2NC and PO2NH2.

Flow Quality for Turbine Engine Loads Simulator (TELS) Facility

DTIC Science & Technology

1980-06-01

2.2 GAS INGESTION A mathematical simulation of the turbojet engine and jet deflector was formulated to estimate the severity of the recirculating...3. Swain. R. L. and Mitchell, J. G. "’Smlulatlon of Turbine Engine Operational Loads." Journal of Aircraft Vol. 15, No. 6, June 1978• 4. Ryan, J...3 AEDC-TR-79-83 ~...~ i ,i g - Flow Quality for Turbine Engine Loads Simulator (TELS) Facility R..I. Schulz ARO, Inc. June 1980

Link Between Deployment Factors and Parenting Stress in Navy Families

DTIC Science & Technology

2016-04-11

problems and parents’ coping. Infant and Child Development , 20(2), 162-180. doi:10.1002/icd.681 Taylor, C. A., Guterman, N. B., Lee, S. J., & Rathouz...community survey. Child : Care, Health and Development , 38(5), 654-664. doi:10.1111/j.1365-2214.2011.01333.x Ellison, C. G., & Fan, D. (2008). Daily...hardship to child difficulties: Main and moderating effects of perceived social support. Child : Care, Health and Development , 37(5), 679-691. doi

Saturn Apollo Program

NASA Image and Video Library

1963-02-01

This image depicts an overall view of the vertical test stand for testing the J-2 engine at Rocketdyne's Propulsion Field Laboratory, in the Santa Susana Mountains, near Canoga Park, California. The J-2 engines were assembled and tested at Rocketdyne under the direction of the Marshall Space Flight Center.

Search for X(3872) in gammagamma fusion and radiative production at CLEO.

PubMed

Dobbs, S; Metreveli, Z; Seth, K K; Tomaradze, A; Zweber, P; Ernst, J; Mahmood, A H; Severini, H; Asner, D M; Dytman, S A; Love, W; Mehrabyan, S; Mueller, J A; Savinov, V; Li, Z; Lopez, A; Mendez, H; Ramirez, J; Huang, G S; Miller, D H; Pavlunin, V; Sanghi, B; Shibata, E I; Shipsey, I P J; Adams, G S; Chasse, M; Cravey, M; Cummings, J P; Danko, I; Napolitano, J; Cronin-Hennessy, D; Park, C S; Park, W; Thayer, J B; Thorndike, E H; Coan, T E; Gao, Y S; Liu, F; Artuso, M; Boulahouache, C; Blusk, S; Butt, J; Dambasuren, E; Dorjkhaidav, O; Menaa, N; Mountain, R; Muramatsu, H; Nandakumar, R; Redjimi, R; Sia, R; Skwarnicki, T; Stone, S; Wang, J C; Zhang, K; Csorna, S E; Bonvicini, G; Cinabro, D; Dubrovin, M; Bornheim, A; Pappas, S P; Weinstein, A J; Rosner, J L; Briere, R A; Chen, G P; Ferguson, T; Tatishvili, G; Vogel, H; Watkins, M E; Adam, N E; Alexander, J P; Berkelman, K; Cassel, D G; Crede, V; Duboscq, J E; Ecklund, K M; Ehrlich, R; Fields, L; Galik, R S; Gibbons, L; Gittelman, B; Gray, R; Gray, S W; Hartill, D L; Heltsley, B K; Hertz, D; Hsu, L; Jones, C D; Kandaswamy, J; Kreinick, D L; Kuznetsov, V E; Mahlke-Krüger, H; Meyer, T O; Onyisi, P U E; Patterson, J R; Peterson, D; Pivarski, J; Riley, D; Ryd, A; Sadoff, A J; Schwarthoff, H; Shepherd, M R; Stroiney, S; Sun, W M; Thayer, J G; Urner, D; Wilksen, T; Weinberger, M; Athar, S B; Avery, P; Breva-Newell, L; Patel, R; Potlia, V; Stoeck, H; Yelton, J; Rubin, P; Cawlfield, C; Eisenstein, B I; Gollin, G D; Karliner, I; Kim, D; Lowrey, N; Naik, P; Sedlack, C; Selen, M; Thaler, J J; Williams, J; Wiss, J; Edwards, K W; Besson, D; Pedlar, T K; Gao, K Y; Gong, D T; Kubota, Y; Lang, B W; Li, S Z; Poling, R; Scott, A W; Smith, A; Stepaniak, C J

2005-01-28

We report on a search for the recently reported X(3872) state using 15.1 fb(-1) of e(+)e(-) data taken in the sqrt[s] = 9.46-11.30 GeV region. Separate searches for the production of the X(3872) in untagged gammagamma fusion and e(+)e(-) annihilation following initial state radiation are made by taking advantage of the unique angular correlation between the leptons from the decay J/psi --> l(+)l(-) in X(3872) decay to pi(+)pi(-)J/psi. No signals are observed in either case, and 90% confidence upper limits are established as (2J+1)Gamma(gammagamma)(X(3872))B(X --> pi(+)pi(-)J/psi) < 12.9 eV and Gamma(ee)(X(3872))B(X- -> pi(+)pi(-)J/psi) < 8.3 eV.

Differential Acquisition of Lever Pressing in Inbred and Outbred Mice: Comparison of One-Lever and Two-Lever Procedures and Correlation with Differences in Locomotor Activity

PubMed Central

McKerchar, Todd L; Zarcone, Troy J; Fowler, Stephen C

2005-01-01

Recent progress in mouse genetics has led to an increased interest in developing procedures for assessing mouse behavior, but relatively few of the behavioral procedures developed involve positively reinforced operant behavior. When operant methods are used, nose poking, not lever pressing, is the target response. In the current study differential acquisition of milk-reinforced lever pressing was observed in five inbred strains (C57BL/6J, DBA/2J, 129X1/SvJ, C3H/HeJ, and BALB/cJ) and one outbred stock (CD-1) of mice. Regardless of whether one or two levers (an “operative” and “inoperative” lever) were in the operant chamber, a concomitant variable-time fixed-ratio schedule of milk reinforcement established lever pressing in the majority of mice within two 120-min sessions. Substantial differences in lever pressing were observed across mice and between procedures. Adding an inoperative lever retarded acquisition in C57BL/6J, DBA/2J, 129X1/SvJ, and C3H/HeJ mice, but not in CD-1 and BALB/cJ mice. Locomotor activity was positively correlated with number of lever presses in both procedures. Analyses of durations of the subcomponents (e.g., time to move from hopper to lever) of operant behavior revealed further differences among the six types of mice. Together, the data suggest that appetitively reinforced lever pressing can be acquired rapidly in mice and that a combination of procedural, behavioral, and genetic variables contributes to this acquisition. PMID:16596969

Concentration and density changes at an electrode surface and the principle of unchanging total concentration

DOE PAGES

Stephen W. Feldberg; Lewis, Ernie R.

2016-02-17

In this study, the principle of unchanging total concentration as described by Oldham and Feldberg [J. Phys. Chem. B, 103, 1699 (1999)] is invoked to analyze systems comprising a redox pair (X z1 1 and X z2 2) plus one or more non-electroactive species (X z3 3,X z4 4...X zjmax jmax) where X zj j is the j th species with charge z j and concentration; c j. The principle states that if the diffusion coefficients for all species are identical and mass transport is governed by the Nernst-Planck expression, the total concentration does not change during any electrochemical perturbation,more » i.e.: Σ jmax j=1[X zj j]=Σ jmax j=1 c j = S P With this principle we deduce the electrochemically induced difference between the surface and bulk concentrations for each species. Those concentration differences are translated into density differences which are a function of the density of the solvent and of the concentration differences, molecular masses and the standard partial molar volumes of all species. Those density differences in turn can induce convection that will ultimately modify the observed current. However, we did not attempt to quantify details of the natural convection and current modification produced by those density differences.« less

Deflocculants for Tape Casting Barium Titanate Dielectrics.

DTIC Science & Technology

1988-02-01

was estimated for two spheres with radii of 0.5 microns using the a form of the Hamaker expression for spheres of equal radii: A#( 1 1 (x(x +-2)1VA...2+ 22n 2(9) 12t x(x + 2) + 1 2) (x + J J where a is the particle radius, H is the particle separation, x - H/2a, and A’ is the effective Hamaker ...Organic Chemistry, 3rd ed., Allyn and Bacon, Inc., Boston, 1973. 33. F. A. Cotton and G. Wilkinson, Advanced Inorganic Chemistry, 4th +ed., John

15 CFR 742.14 - Significant items: hot section technology for the development, production or overhaul of...

Code of Federal Regulations, 2012 CFR

2012-01-01

... or overhaul of commercial aircraft engines controlled under ECCN 9E003.a.1 through a.8, .h,.i and .j... or overhaul of commercial aircraft engines controlled by ECCN 9E003a.1 through a.8, .h,.i, and .j...

15 CFR 742.14 - Significant items: hot section technology for the development, production or overhaul of...

Code of Federal Regulations, 2014 CFR

2014-01-01

... or overhaul of commercial aircraft engines controlled under ECCN 9E003.a.1 through a.8, .h,.i and .j... or overhaul of commercial aircraft engines controlled by ECCN 9E003a.1 through a.8, .h,.i, and .j...

15 CFR 742.14 - Significant items: hot section technology for the development, production or overhaul of...

Code of Federal Regulations, 2013 CFR

2013-01-01

... or overhaul of commercial aircraft engines controlled under ECCN 9E003.a.1 through a.8, .h,.i and .j... or overhaul of commercial aircraft engines controlled by ECCN 9E003a.1 through a.8, .h,.i, and .j...

Silicon Wafer Advanced Packaging (SWAP). Multichip Module (MCM) Foundry Study. Version 2

DTIC Science & Technology

1991-04-08

Next Layer Dielectric Spacing - Additional Metal Thickness Impact on Dielectric Uniformity/Adhiesion. The first step in .!Ie EPerimental design would be... design CAM - computer aided manufacturing CAE - computer aided engineering CALCE - computer aided life cycle engineering center CARMA - computer aided...expansion 5 j- CVD - chemical vapor deposition J . ..- j DA - design automation J , DEC - Digital Equipment Corporation --- DFT - design for testability

Modelling with Integer Variables.

DTIC Science & Technology

1984-01-01

Computational Comparison of * ’Equivalent’ Mixed Integer Formulations," Naval Research Logistics Quarterly 28 (1981), pp. 115- 131 . 39. R. R, Meyer and...jE(i) 3 K ".- .e I " Z A . .,.. x jCI (i) IJ ~s ;:. ... i=I 1 1X. integer A- k . . . . . . . . . . . ... . ... . . . . . . . . . o...be such that Z X.. = 1 andIfxCi’e k jcI (i) 11 13 kx m). *x + E okv . Then by putting Xil and X.=O for j* i, j£I(i) kE (2.3.4) holds. Hence S’ Pi" As

Measurements of double-helicity asymmetries in inclusive J / ψ production in longitudinally polarized p + p collisions at s = 510 GeV

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

Adare, A.; Aidala, C.; Ajitanand, N. N.

We report the double-helicity asymmetry, A J/ψ LL, in inclusive J/ψ production at forward rapidity as a function of transverse momentum p T and rapidity |y|. The data analyzed were taken during √s = 510 GeV longitudinally polarized p + p collisions at the Relativistic Heavy Ion Collider in the 2013 run using the PHENIX detector. At this collision energy, J/ψ particles are predominantly produced through gluon-gluon scatterings, thus A J/ψ LL is sensitive to the gluon polarization inside the proton. We measured A J/ψ LL by detecting the decay daughter muon pairs μ +μ – within the PHENIX muonmore » spectrometers in the rapidity range 1.2 < |y| < 2.2. In this kinematic range, we measured the A J/ψ LL to be 0.012 ± 0.010 (stat) ±0.003 (syst). The A J/ψ LL can be expressed to be proportional to the product of the gluon polarization distributions at two distinct ranges of Bjorken x: one at moderate range x ≈ 5 × 10 –2 where recent data of jet and π 0 double helicity spin asymmetries have shown evidence for significant gluon polarization, and the other one covering the poorly known small-x region x ≈ 2 × 10 –3. Furthermore, our new results could be used to further constrain the gluon polarization for x < 5 × 10 –2.« less

Measurements of double-helicity asymmetries in inclusive J / ψ production in longitudinally polarized p + p collisions at s = 510 GeV

DOE PAGES

Adare, A.; Aidala, C.; Ajitanand, N. N.; ...

2016-12-29

We report the double-helicity asymmetry, A J/ψ LL, in inclusive J/ψ production at forward rapidity as a function of transverse momentum p T and rapidity |y|. The data analyzed were taken during √s = 510 GeV longitudinally polarized p + p collisions at the Relativistic Heavy Ion Collider in the 2013 run using the PHENIX detector. At this collision energy, J/ψ particles are predominantly produced through gluon-gluon scatterings, thus A J/ψ LL is sensitive to the gluon polarization inside the proton. We measured A J/ψ LL by detecting the decay daughter muon pairs μ +μ – within the PHENIX muonmore » spectrometers in the rapidity range 1.2 < |y| < 2.2. In this kinematic range, we measured the A J/ψ LL to be 0.012 ± 0.010 (stat) ±0.003 (syst). The A J/ψ LL can be expressed to be proportional to the product of the gluon polarization distributions at two distinct ranges of Bjorken x: one at moderate range x ≈ 5 × 10 –2 where recent data of jet and π 0 double helicity spin asymmetries have shown evidence for significant gluon polarization, and the other one covering the poorly known small-x region x ≈ 2 × 10 –3. Furthermore, our new results could be used to further constrain the gluon polarization for x < 5 × 10 –2.« less

Probability Current in Hydrogen with Spin-Orbit Interaction

NASA Astrophysics Data System (ADS)

Hodge, William; Migirditch, Sam; Kerr, William

2013-03-01

The spin-orbit interaction is a coupling between a particle's spin and its motion. The Hamiltonian for a spin- 1 / 2 particle which includes this coupling is H =p2/2 m + V (x) +∇/V (x) × p 2m2c2 . S . To describe the flow of probability in this system, we derive the continuity equation, which takes the usual form. In this case, however, we find the probability current density j (x , t) to be the sum of two terms. The first term is the one obtained by most quantum mechanics textbooks during their derivation of the continuity equation. The second term, js (x , t) =1/2m2c2 ∑ σ , σ ' = ↑ , ↓ [ ψ* (x , σ , t) < σ | S | σ ' > ψ (x , σ ' , t) ] × ∇ V (x) , arises due to the inclusion of the spin-orbit term in the Hamiltonian and is small compared to the first. Using a perturbative treatment, we calculate j (x , t) for hydrogenlike atoms; for states with l = 0 , we find that j (x , t) =js (x , t) .

EDITORIAL: Announcing the 2012 Measurement Science and Technology Outstanding Paper Awards Announcing the 2012 Measurement Science and Technology Outstanding Paper Awards

NASA Astrophysics Data System (ADS)

Foss, John; Dewhurst, Richard; Yacoot, Andrew; Regtien, Paul; Peters, Kara

2013-07-01

Since 1991, Measurement Science and Technology has awarded a Best Paper prize. The Editorial Board of this journal believes that such a prize is an opportunity to thank authors for submitting their work, and serves as an integral part of the on-going quality review of the journal. The current breadth of topical areas that are covered by MST has made it advisable to expand the recognition of excellent publications. Hence, since 2005 the Editorial Board have presented 'Outstanding Paper Awards'. This year awards were presented in the areas of 'Measurement Science' and 'Fluid Mechanics'. Although the categories mirror subject sections in the journal, the Editorial Board consider articles from all categories in the selection process. 2012 Award Winners—Measurement Science Physical characterization and performance evaluation of an x-ray micro-computed tomography system for dimensional metrology applications J Hiller1, M Maisl2 and L M Reindl3 1 Department of Mechanical Engineering, Technical University of Denmark (DTU), Produktionstorvet, Building 425, 2800 Kgs Lyngby, Denmark 2 Development Center for X-Ray Technology (EZRT), Fraunhofer Institute for Non-Destructive Testing (IZFP), Campus E3 1, 66123 Saarbrücken, Germany 3 Laboratory for Electrical Instrumentation, Institute for Microsystem Technology (IMTEK), University of Freiburg, Georges-Köhler-Allee 103, 79110 Freiburg, Germany This year's award goes to another paper [1] dealing with micro-measurements, using a scientific measurement technique that is both old and traditional. However, it is the advent of modern technology with computational techniques that have offered new insights into the capability of the measurement method. The paper describes an x-ray computed tomography (CT) system. Such systems are increasingly used in production engineering, where non-destructive measurements of the internal geometries of workpieces can be made with high information density. CT offers important alternatives to tactile or optical measurement systems which sometimes cannot reach internal features. The subject discussed is very important for measurement science. It is concerned with the many factors that affect precision and accuracy in CT metrology. These include issues in the scanning and reconstruction process, the image processing, and the 3D data evaluation. They all influence the dimensional measurement properties of the system as a whole. Therefore, as the authors point out, it is important to know what leads to, and what are the consequences of, such things as experimental geometrical misalignment of the scanner system, or image unsharpness (blurring), or noise or image artefacts. This paper is therefore directed at the implementation of a modern CT system, identifying what is important with implementation of the technique, and what are the likely sources of systematic and random error. After a useful introduction, the paper carefully describes a 3D micro-CT system developed at the Fraunhofer Institute for Non-Destructive Testing in Saarbrücken, Germany, to carry out dimensional measurements on small plastic and metal parts. Considerable emphasis is placed on the characterization of the x-ray tube, with discussion about the effective focal spot size and focus drift. Likewise, there is a detailed account of the flat-panel detector, before examining the contrast and noise transfer properties in the measuring volume. These features are important for achieving short term accuracy, whilst a later section discusses temperature measurements that affect long term accuracy. As a consequence, the image sharpness, noise or image artefacts, are evaluated. In a simple example, the length measurement property of the scanner for a given set of scanning parameters was obtained by using a calibrated ball-bar with a reference length of 8.7678 mm. Two different approaches for systematic error compensation were applied. They obtained an expanded measurement uncertainty of 6.9 µm down to 1.0 µm, which confirms the excellent dimensional measurement that can be achieved with a micro-CT scanner. The paper concludes with a useful summary of their characterization and performance studies. It also sets down possible future research activities in CT metrology. In particular, it identifies the need for development of CT scanning planning strategies to reduce measurement uncertainties in general and to minimize user influence in particular. This paper is excellent in its presentation and scientific description. Issues have been clearly described, and the paper should help establish x-ray micro-computed CT as a fully accepted measuring system in manufacturing engineering. Its contents were supported by 66 references. This helps to put the contribution into context with contributions from previous research papers. The nomination for this paper was supported by seven panel members, higher than any other paper, and it was rated as excellent during the refereeing process. 2012 Award Winners—Fluid Mechanics Polynomial element velocimetry (PEV): a technique for continuous in-plane velocity and velocity gradient measurements for low Reynolds number flows C R Samarage1,2, J Carberry2, G J Sheard2 and A Fouras1,2 1 Laboratory for Dynamic Imaging, Monash University, Melbourne, VIC 3800, Australia 2 Department of Mechanical and Aerospace Engineering, Monash University, Melbourne, VIC 3800, Australia The technique proposed in this article [2] is highly relevant to the wide community of experimentalists that make use of particle image velocimetry. The authors have addressed the issue of how to accurately measure the velocity field and the velocity gradient distribution. The method proposed is elegant and innovative in that it introduces polynomial base functions to represent the spatially varying velocity field within an 'element'. The working principle is clearly described and illustrated. It is noted that the authors have taken a modest position by limiting their conclusions to the case of low Reynolds number flows. It is expected that further developments of this work could lead to successful applications at higher Reynolds numbers and turbulent flows. For the cases analyzed in this work, the authors have achieved a significant improvement in describing the velocity and the vorticity in proximity of the wall. Lastly, the authors have discussed with an open attitude the possible shortcomings of the method. They have indicated the points that will deserve attention when further research efforts are dedicated to the topic. Given the above considerations, the MST outstanding paper selection committee for measurements in fluids, chaired by Professor John Foss, has nominated this article for the MST 2012 outstanding paper award. The chairmen would like to thank the authors for choosing to publish their work in Measurement Science and Technology, and hope that other researchers enjoy reading these works and feel encouraged to submit their own best work to the journal. References [1] Hiller J, Maisl M and Reindl L M 2012 Physical characterization and performance evaluation of an x-ray micro-computed tomography system for dimensional metrology applications Meas. Sci. Technol. 23 085404 (18pp) [2] Samarage C R, Carberry J, Sheard G J and Fouras A 2012 Polynomial element velocimetry (PEV): a technique for continuous in-plane velocity and velocity gradient measurements for low Reynolds number flows Meas. Sci. Technol. 23 105304 (16pp)

Correlation function for generalized Pólya urns: Finite-size scaling analysis

NASA Astrophysics Data System (ADS)

Mori, Shintaro; Hisakado, Masato

2015-11-01

We describe a universality class for the transitions of a generalized Pólya urn by studying the asymptotic behavior of the normalized correlation function C (t ) using finite-size scaling analysis. X (1 ),X (2 ),... are the successive additions of a red (blue) ball [X (t )=1 (0 )] at stage t and C (t )≡Cov[X (1 ),X (t +1 )]/Var[X (1 )] . Furthermore, z (t ) =∑s=1tX (s ) /t represents the successive proportions of red balls in an urn to which, at the (t +1 )th stage, a red ball is added [X (t +1 )=1 ] with probability q [z (t )]=(tanh{J [2 z (t )-1 ]+h }+1 )/2 ,J ≥0 , and a blue ball is added [X (t +1 )=0 ] with probability 1 -q [z (t )] . A boundary [Jc(h ) ,h ] exists in the (J ,h ) plane between a region with one stable fixed point and another region with two stable fixed points for q (z ) . C (t ) ˜c +c'.tl -1 with c =0 (>0 ) for J Jc) , and l is the (larger) value of the slope(s) of q (z ) at the stable fixed point(s). On the boundary J =Jc(h ) ,C (t ) ≃c +c'.(lnt) -α' and c =0 (c >0 ) ,α'=1 /2 (1 ) for h =0 (h ≠0 ) . The system shows a continuous phase transition for h =0 and C (t ) behaves as C (t ) ≃(lnt) -α'g [(1 -l ) lnt ] with a universal function g (x ) and a length scale 1 /(1 -l ) with respect to lnt . β =ν||.α' holds with β =1 /2 and ν||=1 .

Value at 2 of the L-function of an elliptic curve

NASA Astrophysics Data System (ADS)

Brunault, Francois

2006-02-01

We study the special value at 2 of L-functions of modular forms of weight 2 on congruence subgroups of the modular group. We prove an explicit version of Beilinson's theorem for the modular curve X_1(N). When N is prime, we deduce that the target space of Beilinson's regulator map is generated by the images of Milnor symbols associated to modular units of X_1(N). We also suggest a reformulation of Zagier's conjecture on L(E,2) for the jacobian J_1(N) of X_1(N), where E is an elliptic curve of conductor N. In this direction we define an analogue of the elliptic dilogarithm for any jacobian J : it is a function R_J from the complex points of J to a finite-dimensional vector space. In the case J=J_1(N), we establish a link between the aforementioned L-values and the function R_J evaluated at Q-rational points of the cuspidal subgroup of J.

Pulsars as Calibration Tools and X-Ray Observations of Spider Pulsars

NASA Astrophysics Data System (ADS)

Gentile, Peter Anthony

We present the polarization pulse profiles for 29 pulsars observed with the Arecibo Observatory by the North American Nanohertz Observatory for Gravitational Waves (NANOGrav) timing project at 2.1 GHz, 1.4 GHz, and 430 MHz. These profiles represent the most sensitive polarimetric millisecond pulsar profiles to date, revealing the existence of microcomponents (that is, pulse components with peak intensities much lower than the total pulse peak intensity). Although microcomponents have been detected in some pulsars previously, we are able to detect new microcomponents for PSRs B1937+21, J1713+0747, and J2234+0944. We also present rotation measures for 28 of these pulsars, determined independently at different observation frequencies and epochs, and find the Galactic magnetic fields derived from these rotation measures to be consistent with current models. These polarization profiles were made using measurement equation template matching, which allows us to generate the polarimetric response of the Arecibo Observatory on an epoch-by-epoch basis. We use this method to describe its time variability, and find that the polarimetric responses of the Arecibo Observatory's 1.4 and 2.1 GHz receivers varies significantly with time. We then describe the first X-ray observations of five short orbital period (PB < 1 day), gamma-ray emitting, binary millisecond pulsars. Four of these--PSRs J0023+0923, J1124-3653, J1810+1744, and J2256-1024--are "black-widow" pulsars, with degenerate companions of mass 0.1 solar mass, three of which exhibit radio eclipses. The fifth source, PSR J2215+5135, is an eclipsing "redback" with a near Roche-lobe filling 0.2 solar mass non-degenerate companion. Data were taken using the Chandra X-Ray Observatory and covered a full binary orbit for each pulsar. Two pulsars, PSRs J2215+5135 and J2256-1024, show significant orbital variability while PSR J1124-3653 shows marginal orbital variability. The lightcurves for these three pulsars have X-ray flux minima coinciding with the phases of the radio eclipses. This phenomenon is consistent with an intrabinary shock emission interpretation for the X-rays. The other two pulsars, PSRs J0023+0923 and J1810+1744, are fainter and do not demonstrate variability at a level we can detect in these data. All five spectra are fit with three separate models: a power-law model, a blackbody model, and a combined model with both power-law and blackbody components. The preferred spectral fits yield power-law indices that range from 1.3 to 3.2 and blackbody temperatures in the hundreds of eV. The spectrum for PSR J2215+5135 shows a significant hard X-ray component, with a large number of counts above 2 keV, which is additional evidence for the presence of intrabinary shock emission. This is similar to what has been detected in the low-mass X-ray binary to MSP transition object PSR J1023+0038. We also describe X-Ray observations of three "redback" pulsars taken with the XMM-Newton X-Ray telescope, and cover at least one orbit for each source. We had previously analyzed data for one of these sources, PSR J2215+5135, taken with the Chandra X-Ray Observatory . These new observations also show orbital variability in PSR J2215+5135's X-Ray lightcurve, including an X-Ray minimum near superior conjunction, and the increased sensitivity allows us to see two clear features away from superior conjunction. For the other two sources, PSRs J1622-0315 and J1908+2105, we do not detect enough counts to constrain the X-Ray orbital variability. The spectra for each of these sources showed significant hard X-Ray emission, and were therefore not well described by thermal models. We report power-law indices from these fits in the range of 1.28 to 2.0. These spectral properties are consistent with intrabinary shock emission.

National Program for Inspection of Non-Federal Dams. Collins Company Upper Dam (CT 00674), Connecticut River Basin, Canton, Connecticut. Phase I Inspection Report.

DTIC Science & Technology

1979-07-01

Engineering Division p 0 CAR WE H FRZIAN, NENBER Design Branch Engineering Division J SEPE FIN~EGAN, JR.,CIV ater Control Branch * Engineering Division...Operator g. Purpose of Dam h. Design and Construction History i. Normal Operational Procedures 1.3 PERTINENT DATA ........................... 4 a...Tunnel i. Spillways j. Regulating Outlets SECTION 2: ENGINEERING DATA 2.1 DESIGN .............................. 9 a. Available Data b. Design Features c

Estimated Emissions from the Prime-Movers of Unconventional Natural Gas Well Development Using Recently Collected In-Use Data in the United States.

PubMed

Johnson, Derek; Heltzel, Robert; Nix, Andrew; Darzi, Mahdi; Oliver, Dakota

2018-05-01

Natural gas from shale plays dominates new production and growth. However, unconventional well development is an energy intensive process. The prime movers, which include over-the-road service trucks, horizontal drilling rigs, and hydraulic fracturing pumps, are predominately powered by diesel engines that impact air quality. Instead of relying on certification data or outdated emission factors, this model uses new in-use emissions and activity data combined with historical literature to develop a national emissions inventory. For the diesel only case, hydraulic fracturing engines produced the most NO x emissions, while drilling engines produced the most CO emissions, and truck engines produced the most THC emissions. By implementing dual-fuel and dedicated natural gas engines, total fuel energy consumed, CO 2 , CO, THC, and CH 4 emissions would increase, while NO x emissions, diesel fuel consumption, and fuel costs would decrease. Dedicated natural gas engines offered significant reductions in NO x emissions. Additional scenarios examined extreme cases of full fleet conversions. While deep market penetrations could reduce fuel costs, both technologies could significantly increase CH 4 emissions. While this model is based on a small sample size of engine configurations, data were collected during real in-use activity and is representative of real world activity.

Soft X-ray Spectromicroscopy of Polymers

NASA Astrophysics Data System (ADS)

Ade, Harald

1997-03-01

The development of Near Edge X-ray Absorption Fine Structure (NEXAFS) microscopy^1 and linear dichroism microscopy^2 over the last few years utilizing the X1-Scanning Transmission X-ray Microscope (X1-STXM) at the National Synchrotron Light Source provides excellent specificity to various functional groups and moieties in organic molecules and polymeric materials at a spatial resolution of 50 nm. This chemical specificity can be utilized to map the distribution of various compounds in a material, or to micro-chemically analyze small sample areas. Examples of applications include the study of various phase-separated polymers (polyurethanes, liquid crystalline polyesters), multicomponent polymer blends, polymer laminates, and other organic materials such as coal^3. Linear dichroism microscopy furthermore explores the polarization dependence of NEXAFS in (partially) oriented materials, and can determine the orientation of specific functional groups. Applications of linear dichroism microscopy have focused so far on determining the relative degree of radial orientation in Kevlar fibers^3. ^1 H. Ade, X. Zhang, S. Cameron, C. Costello, J. Kirz, and S. Williams, Science 258, 972 (1992). ^2 H. Ade and B. Hsiao, Science 262, 1427 (1993). ^3 Acknowledgement: My callaborators are B. Hsiao, S. Subramoney, B. Wood, I. Plotzker, E. Rightor, G. Mitchell, C. Sloop, D.-J. Liu, S.-C. Liu, J. Marti, C. Zimba, A. P. Smith, R. Spontak, R. Fornes, R. Gilbert, C. Cody, A. Hitchcock and S. Urquhart. The X1-STXM is built and maintained by J. Kirz and C. Jacobsen and their groups. Work supported by: NSF Young Investigator Award (DMR-9458060), DuPont Young Professor Grant, and Dow Chemical.

NASA astronauts and industry experts check out the crew accommod

NASA Image and Video Library

2012-01-30

HAWTHORNE, Calif. -- NASA astronauts and industry experts check out the crew accommodations in the Dragon spacecraft under development by Space Exploration Technologies SpaceX of Hawthorne, Calif., for the agency's Commercial Crew Program. On top, from left, are NASA Crew Survival Engineering Team Lead Dustin Gohmert, NASA astronauts Tony Antonelli and Lee Archambault, and SpaceX Mission Operations Engineer Laura Crabtree. On bottom, from left, are SpaceX Thermal Engineer Brenda Hernandez and NASA astronauts Rex Walheim and Tim Kopra. In 2011, NASA selected SpaceX during Commercial Crew Development Round 2 CCDev2) activities to mature the design and development of a crew transportation system with the overall goal of accelerating a United States-led capability to the International Space Station. The goal of CCP is to drive down the cost of space travel as well as open up space to more people than ever before by balancing industry’s own innovative capabilities with NASA's 50 years of human spaceflight experience. Six other aerospace companies also are maturing launch vehicle and spacecraft designs under CCDev2, including Alliant Techsystems Inc. ATK, The Boeing Co., Excalibur Almaz Inc., Blue Origin, Sierra Nevada, and United Launch Alliance ULA. For more information, visit www.nasa.gov/commercialcrew. Image credit: Space Exploration Technologies

CHANDRA OBSERVATIONS OF FIVE INTEGRAL SOURCES: NEW X-RAY POSITIONS FOR IGR J16393-4643 AND IGR J17091-3624

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

Bodaghee, A.; Tomsick, J. A.; Rahoui, F.

2012-06-01

The Chandra High Resolution Camera observed the fields of five hard X-ray sources in order to help us obtain X-ray coordinates with subarcsecond precision. These observations provide the most accurate X-ray positions known for IGR J16393-4643 and IGR J17091-3624. The obscured X-ray pulsar IGR J16393-4643 lies at R.A. (J2000) = 16{sup h}39{sup m}05.{sup s}47, and decl. = -46 Degree-Sign 42'13.''0 (error radius of 0.''6 at 90% confidence). This position is incompatible with the previously proposed counterpart 2MASS J16390535-4642137, and it points instead to a new counterpart candidate that is possibly blended with the Two Micron All Sky Survey star. Themore » black hole candidate IGR J17091-3624 was observed during its 2011 outburst providing coordinates of R.A. = 17{sup h}09{sup m}07.{sup s}59, and decl. = -36 Degree-Sign 24'25.''4. This position is compatible with those of the proposed optical/IR and radio counterparts, solidifying the source's status as a microquasar. Three targets, IGR J14043-6148, IGR J16358-4726, and IGR J17597-2201, were not detected. We obtained 3{sigma} upper limits of, respectively, 1.7, 1.8, and 1.5 Multiplication-Sign 10{sup -12} erg cm{sup -2} s{sup -1} on their 2-10 keV fluxes.« less

Strategy Planning Visualization Tool (SPVT) for the Air Operations Center (AOC). Volume 2: Information Operations (IO) Planning Enhancements

DTIC Science & Technology

2009-12-31

Status and Assessment data interfaces leverage the TBONE Services and data model. The services and supporting Java 2 Platform Enterprise Edition (J2EE...existing Java ™ and .Net developed “Fat Clients.” The IOPC-X design includes an Open Services Gateway Initiative (OSGi) compliant plug-in...J2EE Java 2 Platform Enterprise Edition JAOP Joint Air Operations Plan JAST JAOP AOD Status Tool JFACC Joint Forces Air Component Commander Data

Discovery of a Hand X-Ray Source, SAX J0635+0533, in the Error Box of the Gamma-Ray Source 2EG J0635+0521

NASA Technical Reports Server (NTRS)

Kaaret, P.; Piraino, S.; Halpern, Jules P.; Eracleous, M.; Oliversen, Ronald (Technical Monitor)

2001-01-01

We have discovered an X-ray source, SAX J0635+0533, with a hard spectrum within the error box of the GeV gamma-ray source in Monoceros, 2EG J0635+0521. The unabsorbed flux from the source is 1.2 x 10(exp -11) ergs /sq cm s in the 2-10 keV band. The X-ray spectrum is consistent with a simple power-law model with absorption. The photon index is 1.50 +/- 0.08, and we detect emission out to 40 keV. Optical observations identify a counterpart with a V magnitude of 12.8. The counterpart has broad emission lines and the colors of an early B-type star. If the identification of the X-ray/optical source with the gamma-ray source is correct, then the source would be a gamma-ray-emitting X-ray binary.

Adaptation of an In Situ Ground-Based Tropospheric OH/HO2 Instrument for Aircraft Use

NASA Technical Reports Server (NTRS)

Brune, William H.

1997-01-01

In-situ HO(x) (OH and HO2) measurements are an essential part of understanding the photochemistry of aircraft exhaust in the atmosphere. HO(x) affects the partitioning of nitrogen species in the NO(y) family. Its reactions are important sources and sinks for tropospheric ozone, thus providing a link between the NO(x) in aircraft exhaust and tropospheric ozone. OH mixing ratios are enhanced in aircraft wakes due to the photolysis of the HONO that is made close to the engine. Measurements of HO(x) in aircraft wakes, along with NO(x) measurements, thus provides a constraint on chemical models of the engine combustion and exhaust. The development of the Airborne Tropospheric Hydrogen Oxides Sensor (ATHOS) is reported. We designed, developed, and successfully flew this instrument. It was part of the instrument complement on board the NASA DC-8 during SUCCESS, which took place in Kansas in April and May, 1996. ATHOS has a limit-of-detection for OH (S/N = 2) of 10(exp 5) OH molecules cm(exp -3) in less than 150 seconds. While this sensitivity is about 2-3 times less than the initial projections in the proposal, it is more than adequate for good measurements of OH and HO2 from the planetary boundary layer to the stratosphere. Our participation in SUCCESS was to be engineering test flights for ATHOS; however, the high-quality measurements we obtained are being used to study HO(x) photochemistry in contrails, clouds, and the clear air.

Ares I Ares V Overview

NASA Technical Reports Server (NTRS)

Sumrall, Phil

2009-01-01

This slide presentation is an overview of the Ares I and Ares V projects. It includes a comparison of the launch vehicles from the Saturn V, the Space Shuttle, and the planned Ares I and Ares V. In order to reduce operating cost, the Ares and V will use much of the same hardware. The elements of the Ares I and V. are reviewed and there is a view of the upper stage avionics. The elements of the J-2X engine to be used on both the Ares I and V are viewed.

Base Structure Annex to Manpower Requirements Report for FY 1980

DTIC Science & Technology

1979-01-01

Printing and Reproduction Installation Safety Installation Engineering Service Related Investment"* Support Groups/Units assigned to these functions...c 04 o1 fn n a K~~~2 W U4u~ S -Ct ’- .dc w u .S . . . ...... - . ..l .. .AF) . ... .. . z -, IVf ’ N 1 j C0 ---- -K dl fl~ t. I . .Wz x A jt vd idz "oz...actions must beanalyzed to determine if any of the activities associated with the action will cause a significuant impact on the human environ-ment or

Research and Development of Ultra-High Strength X100 Welded Pipe

NASA Astrophysics Data System (ADS)

Chuanguo, Zhang; Lei, Zheng; Ping, Hu; Bei, Zhang; Kougen, Wu; Weifeng, Huang

Ultra-high strength X100 welded pipe can be used in the construction of long distance oil and gas pipeline to improve transmission capacity and reduce operation cost. By using the way of thermo-simulation and pilot rolling, the CCT (Continuous Cooling Transformation) diagram and the relationship between ACC (Accelerated Cooling) parameters, microstructure and mechanical properties were studied for the designed X100 pipeline steel with low carbon, high manganese and niobium micro-alloyed composition in lab. The analysis of CCT diagram indicates that the suitable hardness and microstructure can be obtained in the cooling rate of 20 80°C/sec. The pilot rolling results show that the ACC cooling start temperature below Ar3 phase transformation point is beneficial to increase uniform elongation, and the cooling stop temperature of 150 350°C is helpful to obtain high strength and toughness combination. Based on the research conclusions, the X100 plate and UOE pipe with dimension in O.D.1219×W.T.14.8mm, O.D.1219×W.T.17.8mm, designed for the natural gas transmission pipeline, were trial produced. The manufactured pipe body impact absorbed energy at -10°C is over 250J. The DWTT shear area ratio at 0°C is over 85%. The transverse strength meets the X100 grade requirement, and uniform elongation is over 4%. The X100 plate and UOE pipe with dimension in O.D.711×W.T.20.0mm, O.D.711×W.T.12.5mm, designed for an offshore engineering, were also trial produced. The average impact absorbed energy of pipe body at -30°C is over 200J. The average impact absorbed energy of HAZ (Heat-affected zone) and WM (Welded Seam) at -30°C is over 100J. And the good pipe shapes were obtained

Hypersonic research engine/aerothermodynamic integration model: Experimental results. Volume 3: Mach 7 component integration and performance

NASA Technical Reports Server (NTRS)

Andrews, E. H., Jr.; Mackley, E. A.

1976-01-01

The NASA Hypersonic Research Engine Project was undertaken to design, develop, and construct a hypersonic research ramjet engine for high performance and to flight test the developed concept on the X-15-2A airplane over the speed range from Mach 3 to 8. Computer program results are presented here for the Mach 7 component integration and performance tests.

Computer Generation of Fourier Transform Libraries for Distributed Memory Architectures

DTIC Science & Technology

2010-12-01

m + m -1] = A (x[i*n:1:i* m + m -1]); y = (Am ⊗ In )x y = ( n−1 ∑ j=0 S (h j ,n )AmG(h j ,n ) ) x for(i=0;i<n;i++) y[i:n:i+ m -1] = A (x[i:n:i+ m -1]); y = (In ⊗ Am...L mn n x y = ( n−1 ∑ j=0 S (h jm,1)AmG(h j ,n ) ) x for(i=0;i<n;i++) y[i*n:1:i* m + m -1] = A (x[i:n:i+ m -1]); TABLE 2.4: Translating SPL to Σ-SPL, and then...Ip ⊗‖ (Am ⊗ Iµ))(L mn m ⊗̄Iµ) → p−1 ∑ k=0 ‖ SDT(qk,n/µ,µ)

An X-Ray Counterpart of HESS J1427-608 Discovered with Suzaku

NASA Astrophysics Data System (ADS)

Fujinaga, Takahisa; Mori, Koji; Bamba, Aya; Kimura, Shoichi; Dotani, Tadayasu; Ozaki, Masanobu; Matsuta, Keiko; Pülhofer, Gerd; Uchiyama, Hideki; Hiraga, Junko S.; Matsumoto, Hironori; Terada, Yukikatsu

2013-06-01

We report on the discovery of an X-ray counterpart of the unidentified very high-energy gamma-ray source HESS J1427-608. In the sky field coincident with HESS J1427-608, an extended source was found in the 2-8 keV band, and was designated as Suzaku J1427-6051. Its X-ray radial profile has an extension of σ = 0.'9 ± 0.'1 if approximated by a Gaussian. The spectrum was well fitted by an absorbed power-law with NH = (1.1 ± 0.3) × 1023 cm-2, Γ = 3.1+0.6-0.5, and the unabsorbed flux FX = (9+4-2) × 10-13 erg s-1 cm-2 in the 2-10 keV band. Using XMM-Newton archive data, we found seven point sources in the Suzaku source region. However, because their total flux and absorbing column densities are more than an order of magnitude lower than those of Suzaku J1427-6051, we consider that they are unrelated to the Suzaku source. Thus, Suzaku J1427-6051 is considered to be a truly diffuse source and an X-ray counterpart of HESS J1427-608. The possible nature of HESS J1427-608 is discussed based on the observational properties.

A Nonparametric Statistical Approach to the Validation of Computer Simulation Models

DTIC Science & Technology

1985-11-01

Ballistic Research Laboratory, the Experimental Design and Analysis Branch of the Systems Engineering and Concepts Analysis Division was funded to...2 Winter. E M. Wisemiler. D P. azd UjiharmJ K. Venrgcation ad Validatiot of Engineering Simulatiots with Minimal D2ta." Pmeedinr’ of the 1976 Summer...used by numerous authors. Law%6 has augmented their approach with specific suggestions for each of the three stage’s: 1. develop high face-validity

Measurement of Deep Levels at InGaAs(P)/InP Heterojunctions

DTIC Science & Technology

1990-04-01

by write Eq. (10) to obtain (for shallow or deep donor traps): VD(O) = VDK + q/K f. N, (x*)(x* -x)dx* -qAx/ o, - + J N,(x)dx J-* +_N,, F(x)dx KFc . N...8217T, P. Andre, 1. N. Patillon, J. L. Gentler, E. P. Menu , D. Moroni, and G. Case 2: Bias sweep frequency large (e,, <Wf~ccw) M. Martin, Int. Symp. GaAs

Directed 3D Cell Alignment and Elongation in Microengineered Hydrogels

DTIC Science & Technology

2010-01-01

Merok J, Vunjak- Novakovic G, Freed LE. Tissue engineering of functional cardiac muscle: molecular, structural, and electro- physiological studies. Am J...endothelial cells and smooth muscle cells. J Biomech 2004;37(4):531e9. [4] Vunjak- Novakovic G, Altman G, Horan R, Kaplan DL. Tissue engineering of...483e95. [9] Burdick JA, Vunjak- Novakovic G. Engineered microenvironments for controlled stem cell differentiation. Tissue Eng Part A 2009;15(2):205e19

Engineering of pulsed laser deposited calcium phosphate biomaterials in controlled atmospheres

NASA Astrophysics Data System (ADS)

Drukteinis, Saulius E.

Synthetic calcium phosphates (CAP) such as hydroxyapatite (HA) have been used as regenerative bone graft materials and also as thin films to improve the integration of biomedical implant devices within skeletal tissue. Pulsed laser deposition (PLD) can deposit crystalline HA with significant adhesion on titanium biomaterials. However, there are PLD processing constraints due to the complex physical and chemical interactions occurring simultaneously during PLD, which influence ablation plume formation and development. In this investigation PLD CAP films were engineered with a focus on novel decoupling of partial pressure of H2O (g) ( PH2O ) from total background pressure, in combination with substrate heat treatment and laser energy density control. Characterization of these films was performed with X-ray Diffraction, Scanning Electron Microscopy, Energy Dispersive X-ray Spectroscopy, Fourier Transform Infrared Spectroscopy, and Optical Profilometry. In vitro cellular adhesion testing was also performed using osteoblast (MC3T3) cell lines to evaluate adhesion of bone-forming cells on processed PLD CAP samples. Preferred a-axis orientation films were deposited in H2O (g) saturated atmospheres with reduced laser fluence (< 4 J/cm2). Crystalline HA/tetracalcium phosphate (TTCP) films were deposited in H2O ( g)-deficient atmospheres with higher laser fluence (> 3 J/cm 2). Varied PH2O resulted in control of biphasic HA/TTCP composition with increasing TTCP at lower PH2O . These were dense continuous films composed of micron-scale particles. Cellular adhesion assays did not demonstrate a significant difference between osteoblast adhesion density on HA films compared with biphasic HA/TTCP films. Room temperature PLD at varied PH2O combined with furnace heat treatment resulted in controlled variation in surface amplitude parameters including surface roughness (S a), root mean square (Sq), peak to valley height (St), and ten-point height ( Sz). These discontinuous films were composed of nano-scale particles and resulted in significant osteoblast adhesion compared to control samples or to PLD CAP films deposited on heated substrates. Surface amplitude parameters (Sa, Sq, St, and Sz) correlated with osteoblast adhesion. This new approach of control over H2O ( g) operating atmospheres enabled the deposition of unique PLD CAP films with potential use as thin films for biomedical implants or as regenerative bone graft materials. Keywords: hydroxyapatite, pulsed laser deposition, biomaterials.

Physical Therapy, AFSC 4J0X2

DTIC Science & Technology

1998-05-01

TABLE 19 HYDROTHERAPY EQUIPMENT USED OR OPERATED BY 20 PERCENT OR MORE OF 4J0X2 FIRST-JOB OR FIRST-ENLISTMENT PERSONNEL 37 TABLE 20 MEASUREMENT...which had responses of greater than 20 percent) (see Table 18) 9 types of hydrotherapy equipment (7 of which had responses greater than 20 percent...75 89 84 64 60 33 33 72 65 36 TABLE 19 HYDROTHERAPY EQUIPMENT USED OR OPERATED BY 20 PERCENT OR MORE OF 4J0X2 FIRST-JOB OR FIRST-ENLISTMENT

X-ray observations of black widow pulsars

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

Gentile, P. A.; McLaughlin, M. A.; Roberts, M. S. E.

2014-03-10

We describe the first X-ray observations of five short orbital period (P{sub B} < 1 day), γ-ray emitting, binary millisecond pulsars (MSPs). Four of these—PSRs J0023+0923, J1124–3653, J1810+1744, and J2256–1024—are 'black-widow' pulsars, with degenerate companions of mass <<0.1 M {sub ☉}, three of which exhibit radio eclipses. The fifth source, PSR J2215+5135, is an eclipsing 'redback' with a near Roche-lobe filling ∼0.2 solar mass non-degenerate companion. Data were taken using the Chandra X-Ray Observatory and covered a full binary orbit for each pulsar. Two pulsars, PSRs J2215+5135 and J2256–1024, show significant orbital variability while PSR J1124–3653 shows marginal orbital variability.more » The lightcurves for these three pulsars have X-ray flux minima coinciding with the phases of the radio eclipses. This phenomenon is consistent with an intrabinary shock emission interpretation for the X-rays. The other two pulsars, PSRs J0023+0923 and J1810+1744, are fainter and do not demonstrate variability at a level we can detect in these data. All five spectra are fit with three separate models: a power-law model, a blackbody model, and a combined model with both power-law and blackbody components. The preferred spectral fits yield power-law indices that range from 1.3 to 3.2 and blackbody temperatures in the hundreds of eV. The spectrum for PSR J2215+5135 shows a significant hard X-ray component, with a large number of counts above 2 keV, which is additional evidence for the presence of intrabinary shock emission. This is similar to what has been detected in the low-mass X-ray binary to MSP transition object PSR J1023+0038.« less

Higher-Dimensional Signal Processing via Multiscale Geometric Analysis

DTIC Science & Technology

2010-02-10

dimensions. Surflets allowed a multiscale, piecewise polynomial approximation of discontinuities. We also created a compression algorithm using ...h (p) g (p) g (p) 0 1 g (p) g (p) 1,p 2,p 2,p dg h d h d 1,p 3,p 3,p 3,p 3,p Figure 1: The 1-D dual-tree CWT is implemented using a pair of...ψh(x)ψh(y) + j1ψg(x)ψh(y) + j2ψh(x)ψg(y) + j3ψg(x)ψg(y). (19) To compute the QWT coefficients, we can use a separable 2-D implementation [4] of the

Combustion Heat Release Rate Comparison of Algae Hydroprocessed Renewable Diesel to F-76 in a Two-Stroke Diesel Engine

DTIC Science & Technology

2013-06-01

SAE Int. J. Engines, vol. 1, no. 1, 2008. [12] P. A. Caton, S. A.Williams, R. A. Kamin, D. Luning -Prak, L. J. Hamilton and J. S. Cowart...Detroit, MI, Feb. 27- Mar. 2, 1984. [14] J. Cowart, M. Carr, P. Caton, L. Stoulig, D. Luning -Prak, A. Moore and L. Hamilton, “High Cetane Fuel Combustion

NACA Aircraft on Lakebed - D-558-2, X-1B, and X-1E

NASA Technical Reports Server (NTRS)

1955-01-01

Early NACA research aircraft on the lakebed at the High Speed Research Station in 1955: Left to right: X-1E, D-558-2, X-1B There were four versions of the original Bell X-1 rocket-powered research aircraft that flew at the NACA High-Speed Flight Research Station, Edwards, California. The bullet-shaped X-1 aircraft were built by Bell Aircraft Corporation, Buffalo, N.Y. for the U.S. Army Air Forces (after 1947, U.S. Air Force) and the National Advisory Committee for Aeronautics (NACA). The X-1 Program was originally designated the XS-1 for EXperimental Supersonic. The X-1's mission was to investigate the transonic speed range (speeds from just below to just above the speed of sound) and, if possible, to break the 'sound barrier.' Three different X-1s were built and designated: X-1-1, X-1-2 (later modified to become the X-1E), and X-1-3. The basic X-1 aircraft were flown by a large number of different pilots from 1946 to 1951. The X-1 Program not only proved that humans could go beyond the speed of sound, it reinforced the understanding that technological barriers could be overcome. The X-1s pioneered many structural and aerodynamic advances including extremely thin, yet extremely strong wing sections; supersonic fuselage configurations; control system requirements; powerplant compatibility; and cockpit environments. The X-1 aircraft were the first transonic-capable aircraft to use an all-moving stabilizer. The flights of the X-1s opened up a new era in aviation. The first X-1 was air-launched unpowered from a Boeing B-29 Superfortress on January 25, 1946. Powered flights began in December 1946. On October 14, 1947, the X-1-1, piloted by Air Force Captain Charles 'Chuck' Yeager, became the first aircraft to exceed the speed of sound, reaching about 700 miles per hour (Mach 1.06) and an altitude of 43,000 feet. The number 2 X-1 was modified and redesignated the X-1E. The modifications included adding a conventional canopy, an ejection seat, a low-pressure fuel system of increased capacity, and a thinner high-speed wing. The X-1E was used to obtain in-flight data at twice the speed of sound, with particular emphasis placed on investigating the improvements achieved with the high-speed wing. These wings, made by Stanley Aircraft, were only 3-3/8-inches thick at the root and had 343 gauges installed in them to measure structural loads and aerodynamic heating. The X-1E used its rocket engine to power it up to a speed of 1,471 miles per hour (Mach 2.24) and to an altitude of 73,000 feet. Like the X-1 it was air-launched. The X-1 aircraft were almost 31 feet long and had a wingspan of 28 feet. The X-1 was built of conventional aluminum stressed-skin construction to extremely high structural standards. The X-1E was also 31 feet long but had a wingspan of only 22 feet, 10 inches. It was powered by a Reaction Motors, Inc., XLR-8-RM-5, four-chamber rocket engine. As did all X-1 rocket engines, the LR-8-RM-5 engine did not have throttle capability, but instead, depended on ignition of any one chamber or group of chambers to vary speed. The X-1A, X-1B, and the X-1D were growth versions of the X-1. They were almost five feet longer, almost 2,500 pounds heavier and had conventional canopies. The X-1A and X-1B were modified to have ejection seats. Their mission was to continue the X-1 studies at higher speeds and altitudes. The X-1A began this research after the X-1D was destroyed in an explosion on a captive flight before it made any research flights. On December 12, 1953, Major Charles Yeager flew the X-1A up to a speed of 1,612 miles per hour (almost two-and-a-half times the speed of sound). Then on August 26, 1954, Major Arthur Murray took the X-1A up to an altitude of 90,440 feet. Those two performances were the records for the X-1 program. Later the X-1A was also destroyed after being jettisoned from the carrier aircraft because of an explosion. The X-1B was fitted with 300 thermocouples for exploratory aerodynamic heating tests. It also was the first aircraft to fly with a reaction control system, a prototype of the system used on the X-15. The X-1C was cancelled before production. Three D-558-2 'Skyrockets' were built by Douglas Aircraft, Inc. for NACA and the Navy. The mission of the D-558-2 program was to investigate the flight characteristics of a swept-wing aircraft at high supersonic speeds. Particular attention was given to the problem of 'pitch-up,' a phenomenon often encountered with swept-wing configured aircraft. The D-558-2 was a single-place, 35-degree swept-wing aircraft measuring 42 feet in length. It was 12 feet, 8 inches in height and had a wingspan of 25 feet. Fully fueled it weighed from about 10,572 pounds to 15,787 pounds depending on configuration. The first of the three D-558-IIs had a Westinghouse J34-40 jet engine and took off under its own power. The second was equipped with a turbojet engine replaced in 1950 with a Reaction Motors Inc. LR8-RM-6 rocket engine. This aircraft was modified so it could be air-launched from a P2B-1S (Navy designation for the B-29) carrier aircraft. The third Skyrocket had the jet engine and the rocket engine but was also modified so it could be air-launched. The jet engine was for takeoff and climbing to altitude and the four-chambered rocket engine was for reaching supersonic speeds. The rocket engine was rated at 6,000 pounds of thrust. The D-558-2 was first flown on Feb. 4, 1948, by John Martin, a Douglas test pilot. A NACA pilot, Scott Crossfield, became the first person to fly faster than twice the speed of sound when he piloted the D-558-II to its maximum speed of 1,291 miles per hour on Nov. 20, 1953. Its peak altitude, 83,235 feet, a record in its day, was reached with USMC Lt. Col. Marion Carl behind the controls.

Discovery of Diffuse Hard X-Ray Emission from the Vicinity of PSR J1648-4611 with Suzaku

NASA Astrophysics Data System (ADS)

Sakai, Michito; Matsumoto, Hironori; Haba, Yoshito; Kanou, Yasufumi; Miyamoto, Youhei

2013-06-01

We observed the pulsar PSR J1648-4611 with Suzaku. Two X-ray sources, Suzaku J1648-4610 (Src A) and Suzaku J1648-4615 (Src B), were found in the field of view. Src A is coincident with the pulsar PSR J1648-4611, which was also detected by the Fermi Gamma-ray Space Telescope. A hard-band image indicates that Src A is spatially extended. We found point sources in the vicinity of Src A by using a Chandra image of the same region, but the point sources have soft X-ray emission, and cannot explain the hard X-ray emission of Src A. The hard-band spectrum of Src A can be reproduced by a power-law model with a photon index of 2.0+0.9-0.7. The X-ray flux in the 2-10 keV band is 1.4 × 10-13 erg cm-2 s-1. The diffuse emission suggests a pulsar wind nebula around PSR J1648&"8211;4611, but the luminosity of Src A is much larger than that expected from the spin-down luminosity of the pulsar. Parts of the very-high-energy γ-ray emission of HESS J1646-458 may be powered by this pulsar wind nebula driven by PSR J1648-4611. Src B has soft emission, and its X-ray spectrum can be described by a power-law model with a photon index of 3.0+1.4-0.8. The X-ray flux in the 0.4-10 keV band is 6.4 × 10-14 erg s-1 cm-2. No counterpart for Src B has been found in the literature.

A Theory of L 1-Dissipative Solvers for Scalar Conservation Laws with Discontinuous Flux

NASA Astrophysics Data System (ADS)

Andreianov, Boris; Karlsen, Kenneth Hvistendahl; Risebro, Nils Henrik

2011-07-01

We propose a general framework for the study of L 1 contractive semigroups of solutions to conservation laws with discontinuous flux: u_t + mathfrak{f}(x,u)_x=0, qquad mathfrak{f}(x,u)= left\\{begin{array}{ll} f^l(u),& x < 0,\\ f^r(u), & x > 0, right.quadquadquad (CL) where the fluxes f l , f r are mainly assumed to be continuous. Developing the ideas of a number of preceding works ( Baiti and Jenssen in J Differ Equ 140(1):161-185, 1997; Towers in SIAM J Numer Anal 38(2):681-698, 2000; Towers in SIAM J Numer Anal 39(4):1197-1218, 2001; Towers et al. in Skr K Nor Vidensk Selsk 3:1-49, 2003; Adimurthi et al. in J Math Kyoto University 43(1):27-70, 2003; Adimurthi et al. in J Hyperbolic Differ Equ 2(4):783-837, 2005; Audusse and Perthame in Proc Roy Soc Edinburgh A 135(2):253-265, 2005; Garavello et al. in Netw Heterog Media 2:159-179, 2007; Bürger et al. in SIAM J Numer Anal 47:1684-1712, 2009), we claim that the whole admissibility issue is reduced to the selection of a family of "elementary solutions", which are piecewise constant weak solutions of the form c(x)=c^l11_{left\\{{x < 0}right\\}}+c^r11_{left\\{{x > 0}right\\}}. We refer to such a family as a "germ". It is well known that (CL) admits many different L 1 contractive semigroups, some of which reflect different physical applications. We revisit a number of the existing admissibility (or entropy) conditions and identify the germs that underly these conditions. We devote specific attention to the "vanishing viscosity" germ, which is a way of expressing the "Γ-condition" of D iehl (J Hyperbolic Differ Equ 6(1):127-159, 2009). For any given germ, we formulate "germ-based" admissibility conditions in the form of a trace condition on the flux discontinuity line { x = 0} [in the spirit of V ol'pert (Math USSR Sbornik 2(2):225-267, 1967)] and in the form of a family of global entropy inequalities [following K ruzhkov (Math USSR Sbornik 10(2):217-243, 1970) and C arrillo (Arch Ration Mech Anal 147(4):269-361, 1999)]. We characterize those germs that lead to the L 1-contraction property for the associated admissible solutions. Our approach offers a streamlined and unifying perspective on many of the known entropy conditions, making it possible to recover earlier uniqueness results under weaker conditions than before, and to provide new results for other less studied problems. Several strategies for proving the existence of admissible solutions are discussed, and existence results are given for fluxes satisfying some additional conditions. These are based on convergence results either for the vanishing viscosity method (with standard viscosity or with specific viscosities "adapted" to the choice of a germ), or for specific germ-adapted finite volume schemes.

A Layman's Guide to Thrust Engine Development for Super/Hyper Sonic Flight.

ERIC Educational Resources Information Center

Thiesse, James L.

The intention of this paper is to discuss the advances in thrust engines from the initial development of the J58/SR-71 (JT11D-20) of the U.S. Air Force's SR-71 Blackbird to the development of the RAM and SCRAM engines necessary to propel the new generations of high-flying super-speed aircraft. Engineering complexities suggest that the engines and…

Effect of laser shot peening on precipitation hardened aluminum alloy 6061-T6 using low energy laser

NASA Astrophysics Data System (ADS)

Sathyajith, S.; Kalainathan, S.

2012-03-01

Mechanical properties of engineering material can be improved by introducing compressive residual stress on the material surface and refinement of their microstructure. Variety of mechanical process such as shot peening, water jet peening, ultrasonic peening, laser shot peening were developed in the last decades on this contrast. Among these, lasers shot peening emerged as a novel industrial treatment to improve the crack resistance of turbine blades and the stress corrosion cracking (SCC) of austenic stainless steel in power plants. In this study we successfully performed laser shot peening on precipitation hardened aluminum alloy 6061-T6 with low energy (300 mJ, 1064 nm) Nd:YAG laser using different pulse densities of 22 pulses/mm 2 and 32 pulses/mm 2. Residual stress evaluation based on X-ray diffraction sin 2 ψ method indicates a maximum of 190% percentage increase on surface compressive stress. Depth profile of micro-hardness shows the impact of laser generated shock wave up to 1.2 mm from the surface. Apart from that, the crystalline size and micro-strain on the laser shot peened surfaces have been investigated and compared with the unpeened surface using X-ray diffraction in conjunction with line broadening analysis through the Williamson-Hall plot.

A biomimetic functionalization approach to integration of carbon nanoutbes into biological systems

NASA Astrophysics Data System (ADS)

Chen, Xing; Tam, Un Chong; Bertozzi, Carolyn; Zettl, Alex

2006-03-01

Due to their remarkable structural, electrical, and mechanical properties, carbon nanotubes (CNTs) have potential applications in biology ranging from imaging and tissue engineering. To realize these applications, however, new strategies for controlling the interaction between CNTs and biological systems such as proteins and cells are required. Here we describe a biomimetic approach to functionalize CNTs and therefore render them biocompatibility in order to facilitate their integration into biological systems. CNTs were coated with synthetic gycopolymers that mimic cell surface mucin gycoproteins. The functionalized CNTs were soluble in water, resisted non-specific protein binding and bound specifically to biomolecules. The coated CNTs could then be integrated onto mammalian cell surface by virtue of glycan-receptor interactions. Furthermore, the functionalized CNTs are non-toxic to cells. This strategy offers new opportunities for development of biosensor to probe biological processes. References: 1. X. Chen, G. S. Lee, A. Zettl, C. R. Bertozzi, Angewandte Chemie-International Edition 43, 6111 (2004). 2. X. Chen, U. C. Tam, J. L. Czlapanski, G. S. Lee, D. Rabuka, A. Zettl, C. R. Bertozzi, submitted.

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.

Failure Modes, Effects and Criticality Analysis (FMECA) of Type AN/GRN-27 (V) Instrument Landing System with Traveling-Wave Localizer Antenna.

DTIC Science & Technology

1983-02-01

reference glideslope). three an- common to tennas. both trans- ,11 =. 635 nitters), an side band immediate ref.) shutdown after an automatic IlA transfer will...CONDITION PRESENT: PINT CL 5.n8X 10-. BI8 HR)2 + (1.14O X10-6 .168 HR) _ 1.g2X10-4 PCF =___ - 4X XX10- 44.1J2 + 13 ~C (~j7X10-2 4 4 8 PCLVA )(1.92 X 10

X-Ray Investigation of the Diffuse Emission around Plausible γ-Ray Emitting Pulsar Wind Nebulae in Kookaburra Region

NASA Astrophysics Data System (ADS)

Kishishita, Tetsuichi; Bamba, Aya; Uchiyama, Yasunobu; Tanaka, Yasuyuki; Takahashi, Tadayuki

2012-05-01

We report on the results from Suzaku X-ray observations of the radio complex region called Kookaburra, which includes two adjacent TeV γ-ray sources HESS J1418-609 and HESS J1420-607. The Suzaku observation revealed X-ray diffuse emission around a middle-aged pulsar PSR J1420-6048 and a plausible pulsar wind nebula (PWN) Rabbit with elongated sizes of σX = 1farcm66 and σX = 1farcm49, respectively. The peaks of the diffuse X-ray emission are located within the γ-ray excess maps obtained by H.E.S.S. and the offsets from the γ-ray peaks are 2farcm8 for PSR J1420-6048 and 4farcm5 for Rabbit. The X-ray spectra of the two sources were well reproduced by absorbed power-law models with Γ = 1.7-2.3. The spectral shapes tend to become softer according to the distance from the X-ray peaks. Assuming the one-zone electron emission model as the first-order approximation, the ambient magnetic field strengths of HESS J1420-607 and HESS J1418-609 can be estimated as 3 μG and 2.5 μG, respectively. The X-ray spectral and spatial properties strongly support that both TeV sources are PWNe, in which electrons and positrons accelerated at termination shocks of the pulsar winds are losing their energies via the synchrotron radiation and inverse Compton scattering as they are transported outward.

Biological and Clinical Characterization of Novel lncRNAs Associated with Metastatic Prostate Cancer

DTIC Science & Technology

2015-11-01

R. Bedenis, N. McGregor, T. Ma, W. Chen, S. Han, X. Jing, X. Cao, X. Wang, B. Chandler, W. Yan, J . Siddiqui, L.P. Kunju, S.M. Dhanasekaran, K.J...antagonizes the SWI/SNF complex. Nat Genet 2013;45: 1392–8. 8. Tomlins SA, Aubin SM, Siddiqui J , Lonigro RJ, Sefton-Miller L, Miick S, et al. Urine TMPRSS2...support vector machine. Nucleic Acids Res 2007;35:W345–9. 13. Yu J , Mani RS, Cao Q, Brenner CJ, Cao X, Wang X, et al. An integrated network of androgen

Population Control of Self-Replicating Systems: Option C

NASA Technical Reports Server (NTRS)

Mccord, R. L.

1983-01-01

From the conception and development of the theory of self-replicating automata by John von Neumann, others have expanded on his theories. In 1980, Georg von Tiesenhausen and Wesley A. Darbro developed a report which is a "first' in presenting the theories in a conceptualized engineering setting. In that report several options involving self-replicating systems are presented. One of the options allows each primary to generate n replicas, one in each sequential time frame after its own generation. Each replica is limited to a maximum of m ancestors. This study involves determining the state vector of the replicas in an efficient manner. The problem is cast in matrix notation, where F = fij is a non-diagonalizable matrix. Any element fij represents the number of elements of type j = (c,d) in time frame k+1 generated from type i = (a,b) in time frame k. It is then shown that the state vector is: bar F(k)=bar F (non-zero) X F sub K = bar F (non-zero) xmx J sub kx m sub-1 where J is a matrix in Jordan form having the same eigenvalues as F. M is a matrix composed of the eigenvectors and the generalized eigenvectors of F.

Lightweight Advanced Post-Boost Vehicle Propulsion Feed System Development

DTIC Science & Technology

1981-08-01

E < CD O a tu o u c en ID V u < CO •- V ID C C c c C — a...ataBS^ ■n^-^w*.-’ ^r»^^ 2*» 22 20 - cat 3 18 i/> </\\ Ui at a. liS H Z O a: 14 a. *™* X 12 *v a> _i a 10 < o _/ z. 8 X : E o cc...m \\0 _l — ao -a- 4-j n) O o c — LT\\ <*> — L. 0 U *. vß -> 4J ao -3- T3 O o x: m ro to i/) m -■■ — — — — — w o

Studies of the kinetics and thermochemistry of the forward and reverse reaction Cl + C6H6 = HCl + C6H5.

PubMed

Alecu, I M; Gao, Yide; Hsieh, P-C; Sand, Jordan P; Ors, Ahmet; McLeod, A; Marshall, Paul

2007-05-17

The laser flash photolysis resonance fluorescence technique was used to monitor atomic Cl kinetics. Loss of Cl following photolysis of CCl4 and NaCl was used to determine k(Cl + C6H6) = 6.4 x 10(-12) exp(-18.1 kJ mol(-1)/RT) cm(3) molecule(-1) s(-1) over 578-922 K and k(Cl + C6D6) = 6.2 x 10(-12) exp(-22.8 kJ mol(-1)/RT) cm(3) molecule(-1) s(-1) over 635-922 K. Inclusion of literature data at room temperature leads to a recommendation of k(Cl + C6H6) = 6.1 x 10(-11) exp(-31.6 kJ mol(-1)/RT) cm(3) molecule(-1) s(-1) for 296-922 K. Monitoring growth of Cl during the reaction of phenyl with HCl led to k(C6H5 + HCl) = 1.14 x 10(-12) exp(+5.2 kJ mol(-1)/RT) cm(3) molecule(-1) s(-1) over 294-748 K, k(C6H5 + DCl) = 7.7 x 10(-13) exp(+4.9 kJ mol(-1)/RT) cm(3) molecule(-1) s(-1) over 292-546 K, an approximate k(C6H5 + C6H5I) = 2 x 10(-11) cm(3) molecule(-1) s(-1) over 300-750 K, and an upper limit k(Cl + C6H5I) < or = 5.3 x 10(-12) exp(+2.8 kJ mol(-1)/RT) cm(3) molecule(-1) s(-1) over 300-750 K. Confidence limits are discussed in the text. Third-law analysis of the equilibrium constant yields the bond dissociation enthalpy D(298)(C6H5-H) = 472.1 +/- 2.5 kJ mol(-1) and thus the enthalpy of formation Delta(f)H(298)(C6H5) = 337.0 +/- 2.5 kJ mol(-1).

Enhancement and Angular Dependence of Transport Critical Current Density in Pulsed Laser Deposited YBa2Cu3O7-x+BaSnO3 Films in Applied Magnetic Fields (Postprint)

DTIC Science & Technology

2007-09-25

Foltyn, Q. X. Jia, H. Wang, A. Serquis, L. Civale, B. Maiorov, M. E. Hawley , M. P. Maley, and D. E. Peterson, Nat. Mater. 3, 439 2004. 4C...J. O. Willis , J. Y. Coulter, H. Wang, Q. X. Jia, P. N. Arendt, J. L. MacManus-Driscoll, M. P. Maley, and S. R. Foltyn, Appl. Phys. Lett. 84, 2121...Jia, P. N. Arendt, H. Wang, J. O. Willis , J. Y. Coulter, T. G. Holesinger, J. L. MacManus- Driscoll, M. W. Rupich, W. Zhang, and X. Li, Physica C

Post-growth annealing of germanium-tin alloys using pulsed excimer laser

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

Wang, Lanxiang; Wang, Wei; Zhou, Qian

2015-07-14

We investigate the impact of pulsed excimer laser anneal on fully strained germanium-tin alloys (Ge{sub 1−x}Sn{sub x}) epitaxially grown on Ge substrate by molecular beam epitaxy. Using atomic force microscopy, X-ray diffraction, transmission electron microscopy, and X-ray photoelectron spectroscopy, the morphological and compositional evolution of Ge{sub 1−x}Sn{sub x} with Sn content up to 17% after annealing using various conditions is studied. Ge{sub 0.83}Sn{sub 0.17} samples annealed at 80 mJ/cm{sup 2} or 150 mJ/cm{sup 2} have no observable changes with respect to the as-grown sample. However, Ge{sub 0.83}Sn{sub 0.17} samples annealed at 250 mJ/cm{sup 2} or 300 mJ/cm{sup 2} have Sn-richmore » islands on the surface, which is due to Sn segregation in the compressively strained epitaxial film. For Ge{sub 0.89}Sn{sub 0.11}, significant Sn redistribution occurs only when annealed at 300 mJ/cm{sup 2}, indicating that it has better thermal stability than Ge{sub 0.83}Sn{sub 0.17}. A mechanism is proposed to explain the formation of Sn-rich islands and Sn-depleted regions.« less

Advanced transportation system studies, technical area 3. Alternate propulsion subsystem concepts: J-2S restart study

NASA Astrophysics Data System (ADS)

Vilja, John; Levack, Daniel

1993-04-01

The objectives were to assess what design changes would be required to remit late production of the J-2S engine for use as a large high energy upper stage engine. The study assessed design changes required to perform per the J-2S model specification, manufacturing changes required due to obsolescence or improvements in state-of-the-practice, availability issues for supplier provided items, and provided cost and schedule estimates for this configuration. The confidence that J-2S production could be reinitiated within reasonable costs and schedules was provided. No significant technical issues were identified in either the producibility study or in the review of previous technical data. Areas of potential cost reduction were identified which could be quantified to a greater extent with further manufacturing planning. The proposed schedule can be met with no foreseeable impacts. The results of the study provided the necessary foundation for the detailed manufacturing and test plans and non-recurring and recurring cost estimates that are needed to complete the effort to reinitiate production of the J-2S engine system.

Influence of Fe-substitution on structural, magnetic and magnetocaloric properties of Nd2Fe17-xCox solid solutions

NASA Astrophysics Data System (ADS)

Bouchaala, N.; Jemmali, M.; Bartoli, T.; Nouri, K.; Hentech, I.; Walha, S.; Bessais, L.; Salah, A. Ben

2018-02-01

Nd2Fe17-xCox (x = 0 , 1 , 2 , 3 , 4) intermetallic compounds, obtained under arc-melting conditions, have been investigated by means of X-ray diffraction analysis (XRD), Mössbauer spectrometry and magnetic measurements. The Rietveld refinement revealed that the sample is a pure compound with rhombohedral Th2Zn17-type structure (R 3 bar m space group) with the following lattice parameters: a = 8.5792 (2) Å, c = 12.4615 (2) Å. Using Mössbauer spectrometry analysis coupled with structural consideration we have unambiguously determined the cobalt atoms preferred inequivalent crystallographic site. Nd2Fe17 show an increase of 3.5 T in their weighted average hyperfine fields upon cobalt substitution. Whatever the cobalt content, the hyperfine field of these compounds follow this sequence Hhf { 6 c } >Hhf { 9 d } >Hhf { 18 f } >Hhf { 18 h }. The magnetic measurements showed that the Curie temperature increases with the Co content. The magnetic entropy change (ΔSM) was estimated from isothermal magnetization curves and it increases from 3.35 J/Kg K for x = 0 to 5.83 J/Kg K for x = 2 at μ0 H = 1.6 T . The relative cooling power (RCP) is in the range of 11.6 J/kg (x = 0) and 16 J/kg (x = 2).

Measurement of the X(3872) production cross section via decays to J/ψπ + π - in pp collisions at $$ \\sqrt{s}=7 $$ TeV

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

Chatrchyan, S.; Khachatryan, V.; Sirunyan, A. M.

The production of the X(3872) is studied in pp collisions at sqrt(s) = 7 TeV, using decays to J/psi pi pi, where the J/psi decays to two muons. The data were recorded by the CMS experiment and correspond to an integrated luminosity of 4.8 inverse femtobarns. The measurements are performed in a kinematic range in which the X(3872) candidates have a transverse momentum 10 < pt < 50 GeV and rapidity abs(y) < 1.2. The ratio of the X(3872) and psi(2S) cross sections times their branching fractions into J/psi pi pi is measured as a function of pt. In addition,more » the fraction of X(3872) originating from B decays is determined. From these measurements the prompt X(3872) differential cross section times branching fraction as a function of pt is extracted. The pi pi mass spectrum of the J/psi pi pi system in the X(3872) decays is also investigated.« less

X-15A-2 with dummy ramjet

NASA Technical Reports Server (NTRS)

1967-01-01

This photo shows the X-15A-2 (56-6671) on a research flight with a dummy ramjet engine attached to the bottom of its wedge-shaped vertical tail. One of the experiments planned for the X-15A-2 involved tests of a functional ramjet at speeds above Mach 5. This photo was taken with a dummy ramjet. On this research flight, the X-15A-2 did not carry the two drop tanks used on its Mach 6.7 flight. It also had not yet been covered with an ablative coating. The X-15A-2 made several flights with the dummy ramjet, leading to the record Mach 6.7 flight on October 3, 1967. Delays in producing the operational ramjet, aerodynamic heating damage to the aircraft during the record flight (despite the ablative coating), and the end of the X-15 program in 1968 resulted in no flights with the actual ramjet. The X-15 was a rocket-powered aircraft. The original three aircraft were about 50 ft long with a wingspan of 22 ft. The modified #2 aircraft (X-15A-2 was longer.) They were a missile-shaped vehicles with unusual wedge-shaped vertical tails, thin stubby wings, and unique side fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was rated at 57,000 lb of thrust, although there are indications that it actually achieved up to 60,000 lb. North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow-on program used the aircraft as testbeds to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudder surfaces on the vertical stabilizers to control yaw and movable horizontal stabilizers to control pitch when moving in synchronization or roll when moved differentially. For flight in the thin air outside of the appreciable Earth's atmosphere, the X-15 used a reaction control system. Hydrogen peroxide thrust rockets located on the nose of the aircraft provided pitch and yaw control. Those on the wings provided roll control. Because of the large fuel consumption, the X-15 was air launched from a B-52 aircraft at approximately 45,000 ft and a speed of about 500 mph. Depending on the mission, the rocket engine provided thrust for the first 80 to 120 sec of flight. The remainder of the normal 10 to 11 min. flight was powerless and ended with a 200-mph glide landing. Generally, one of two types of X-15 flight profiles was used; a high-altitude flight plan that called for the pilot to maintain a steep rate of climb, or a speed profile that called for the pilot to push over and maintain a level altitude. The X-15 was flown over a period of nearly 10 years -- June 1959 to Oct. 1968 -- and set the world's unofficial speed and altitude records of 4,520 mph (Mach 6.7) and 354,200 ft in a program to investigate all aspects of manned hypersonic flight. Information gained from the highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo manned spaceflight programs, and also the Space Shuttle program. The X-15s made a total of 199 flights, and were manufactured by North American Aviation. X-15-1, serial number 56-6670, is now located at the National Air and Space Museum, Washington DC. North American X-15A-2, serial number 56-6671, is at the United States Air Force Museum, Wright-Patterson AFB, Ohio. X-15-3, serial number 56-6672, crashed on 15 November 1967, resulting in the death of Maj. Michael J. Adams.

Data Traffic Reduction Schemes for Cholesky Factorization on Asynchronous Multiprocessor Systems

DTIC Science & Technology

1989-06-01

Engineering NASA Langley Research Center Hampton, Virginia 23665-5225 Operated by the Universities Space Research Association DTIC ELECTE NASA jAUG 23...Hampton, VA 23665. ti- 1. Introduction Consider the problem of solving a system of linear equations Ax=b where .4 is an n x n symmetric, positive

Observation of Psi(3770)-->gammachi(c1)-->gammagammaJ/Psi.

PubMed

Coan, T E; Gao, Y S; Liu, F; Artuso, M; Boulahouache, C; Blusk, S; Butt, J; Dorjkhaidav, O; Li, J; Menaa, N; Mountain, R; Nandakumar, R; Randrianarivony, K; Redjimi, R; Sia, R; Skwarnicki, T; Stone, S; Wang, J C; Zhang, K; Csorna, S E; Bonvicini, G; Cinabro, D; Dubrovin, M; Lincoln, A; Briere, R A; Chen, G P; Chen, J; Ferguson, T; Tatishvili, G; Vogel, H; Watkins, M E; Rosner, J L; Adam, N E; Alexander, J P; Berkelman, K; Cassel, D G; Crede, V; Duboscq, J E; Ecklund, K M; Ehrlich, R; Fields, L; Galik, R S; Gibbons, L; Gittelman, B; Gray, R; Gray, S W; Hartill, D L; Heltsley, B K; Hertz, D; Jones, C D; Kandaswamy, J; Kreinick, D L; Kuznetsov, V E; Mahlke-Krüger, H; Meyer, T O; Onyisi, P U E; Patterson, J R; Peterson, D; Phillips, E A; Pivarski, J; Riley, D; Ryd, A; Sadoff, A J; Schwarthoff, H; Shi, X; Shepherd, M R; Stroiney, S; Sun, W M; Urner, D; Wilksen, T; Weaver, K M; Weinberger, M; Athar, S B; Avery, P; Breva-Newell, L; Patel, R; Potlia, V; Stoeck, H; Yelton, J; Rubin, P; Cawlfield, C; Eisenstein, B I; Gollin, G D; Karliner, I; Kim, D; Lowrey, N; Naik, P; Sedlack, C; Selen, M; White, E J; Williams, J; Wiss, J; Asner, D M; Edwards, K W; Besson, D; Pedlar, T K; Cronin-Hennessy, D; Gao, K Y; Gong, D T; Hietala, J; Kubota, Y; Klein, T; Lang, B W; Li, S Z; Poling, R; Scott, A W; Smith, A; Dobbs, S; Metreveli, Z; Seth, K K; Tomaradze, A; Zweber, P; Ernst, J; Severini, H; Dytman, S A; Love, W; Mehrabyan, S; Mueller, J A; Savinov, V; Li, Z; Lopez, A; Mendez, H; Ramirez, J; Huang, G S; Miller, D H; Pavlunin, V; Sanghi, B; Shipsey, I P J; Adams, G S; Anderson, M; Cummings, J P; Danko, I; Napolitano, J; He, Q; Muramatsu, H; Park, C S; Thorndike, E H

2006-05-12

From e(+)e(-) collision data acquired with the CLEO detector at the Cornell Electron Storage Ring, we observe the non-DD(_) decay Psi(3770))-->gammachi(c1) with a statistical significance of 6.6 standard deviations, using the two-photon cascades to J/Psi and J/Psi-->l(+)l(-). We determine sigma(e(=)e(-)-->Psi(3770))xBeta(Psi(3770)-->gammachi(c1))=(18.0 +/- 3.3 +/- 2.5) pb and branching fraction Beta(Psi(3770)-->gammachi(c1)=(2.8 +/- 0.5+/-0.4) x 10(-3). We set 90% C.L. upper limits for the transition to chi(c2) (chi(c0)): sigma x Beta<5.7 pb (<282 pb) and Beta<0.9 x 10(-3) (<44 x 10(-3)). We also determine Gamma(Psi(3770)gammachi(c1))/Gamma(Psi(3770)-->pi(+)pi(-)J/Psi)=1.5 +/- 0.3 +/- 0.3 (>1.0 at 90% C.L.), which bears upon the interpretation of X(3872).

Development of the Nonhydrostatic Unified Model of the Atmosphere (NUMA): Limited-Area Mode (Preprint)

DTIC Science & Technology

2011-04-14

such that qN(x, t ) = MN ∑ j =1 qj( t )ψj(x) (9) 6 whereMN = (N+1) 3 is the number of nodes per element andN is the order of the basis functions. The...M.H. Mawson , A. Staniforth, A.A. White, N. Wood, A new dynamical core for the Met Office’s global and regional modelling of the atmosphere, Q. J . R...Tufo, M. Levy, T . Voran, Development of a scalable global discontinuous Galerkin atmospheric model, Int. J . of Comput. Sci. Eng. In Press (2008). [6

Recent progress of Spectrolab high-efficiency space solar cells

NASA Astrophysics Data System (ADS)

Law, Daniel C.; Boisvert, J. C.; Rehder, E. M.; Chiu, P. T.; Mesropian, S.; Woo, R. L.; Liu, X. Q.; Hong, W. D.; Fetzer, C. M.; Singer, S. B.; Bhusari, D. M.; Edmondson, K. M.; Zakaria, A.; Jun, B.; Krut, D. D.; King, R. R.; Sharma, S. K.; Karam, N. H.

2013-09-01

Recent progress in III-V multijunction space solar cell has led to Spectrolab's GaInP/GaAs/Ge triple-junction, XTJ, cells with average 1-sun efficiency of 29% (AM0, 28°C) for cell size ranging from 59 to 72-cm2. High-efficiency inverted metamorphic (IMM) multijunction cells are developed as the next space solar cell architecture. Spectrolab's large-area IMM3J and IMM4J cells have achieved 33% and 34% 1-sun, AM0 efficiencies, respectively. The IMM3J and the IMM4J cells have both demonstrated normalized power retention of 0.86 at 5x1014 e-/cm2 fluence and 0.83 and 0.82 at 1x1015 e-/cm2 fluence post 1-MeV electron radiation, respectively. The IMM cells were further assembled into coverglass-interconnect-cell (CIC) strings and affixed to typical rigid aluminum honeycomb panels for thermal cycling characterization. Preliminary temperature cycling data of two coupons populated with IMM cell strings showed no performance degradation. Spectrolab has also developed semiconductor bonded technology (SBT) where highperformance component subcells were grown on GaAs and InP substrates separately then bonded directly to form the final multijunction cells. Large-area SBT 5-junction cells have achieved a 35.1% efficiency under 1-sun, AM0 condition.

Analysis of the quantum numbers J(PC) of the X(3872) particle.

PubMed

Abulencia, A; Adelman, J; Affolder, T; Akimoto, T; Albrow, M G; Ambrose, D; Amerio, S; Amidei, D; Anastassov, A; Anikeev, K; Annovi, A; Antos, J; Aoki, M; Apollinari, G; Arguin, J-F; Arisawa, T; Artikov, A; Ashmanskas, W; Attal, A; Azfar, F; Azzi-Bacchetta, P; Azzurri, P; Bacchetta, N; Badgett, W; Barbaro-Galtieri, A; Barnes, V E; Barnett, B A; Baroiant, S; Bartsch, V; Bauer, G; Bedeschi, F; Behari, S; Belforte, S; Bellettini, G; Bellinger, J; Belloni, A; Benjamin, D; Beretvas, A; Beringer, J; Berry, T; Bhatti, A; Binkley, M; Bisello, D; Blair, R E; Blocker, C; Blumenfeld, B; Bocci, A; Bodek, A; Boisvert, V; Bolla, G; Bolshov, A; Bortoletto, D; Boudreau, J; Boveia, A; Brau, B; Brigliadori, L; Bromberg, C; Brubaker, E; Budagov, J; Budd, H S; Budd, S; Budroni, S; Burkett, K; Busetto, G; Bussey, P; Byrum, K L; Cabrera, S; Campanelli, M; Campbell, M; Canelli, F; Canepa, A; Carillo, S; Carlsmith, D; Carosi, R; Casarsa, M; Castro, A; Catastini, P; Cauz, D; Cavalli-Sforza, M; Cerri, A; Cerrito, L; Chang, S H; Chen, Y C; Chertok, M; Chiarelli, G; Chlachidze, G; Chlebana, F; Cho, I; Cho, K; Chokheli, D; Chou, J P; Choudalakis, G; Chuang, S H; Chung, K; Chung, W H; Chung, Y S; Ciljak, M; Ciobanu, C I; Ciocci, M A; Clark, A; Clark, D; Coca, M; Compostella, G; Convery, M E; Conway, J; Cooper, B; Copic, K; Cordelli, M; Cortiana, G; Crescioli, F; Cuenca Almenar, C; Cuevas, J; Culbertson, R; Cully, J C; Cyr, D; Daronco, S; Datta, M; D'Auria, S; Davies, T; D'Onofrio, M; Dagenhart, D; de Barbaro, P; De Cecco, S; Deisher, A; De Lentdecker, G; Dell'Orso, M; Delli Paoli, F; Demortier, L; Deng, J; Deninno, M; De Pedis, D; Derwent, P F; Di Giovanni, G P; Dionisi, C; Di Ruzza, B; Dittmann, J R; DiTuro, P; Dörr, C; Donati, S; Donega, M; Dong, P; Donini, J; Dorigo, T; Dube, S; Efron, J; Erbacher, R; Errede, D; Errede, S; Eusebi, R; Fang, H C; Farrington, S; Fedorko, I; Fedorko, W T; Feild, R G; Feindt, M; Fernandez, J P; Field, R; Flanagan, G; Foland, A; Forrester, S; Foster, G W; Franklin, M; Freeman, J C; Furic, I; Gallinaro, M; Galyardt, J; Garcia, J E; Garberson, F; Garfinkel, A F; Gay, C; Gerberich, H; Gerdes, D; Giagu, S; Giannetti, P; Gibson, A; Gibson, K; Gimmell, J L; Ginsburg, C; Giokaris, N; Giordani, M; Giromini, P; Giunta, M; Giurgiu, G; Glagolev, V; Glenzinski, D; Gold, M; Goldschmidt, N; Goldstein, J; Golossanov, A; Gomez, G; Gomez-Ceballos, G; Goncharov, M; González, O; Gorelov, I; Goshaw, A T; Goulianos, K; Gresele, A; Griffiths, M; Grinstein, S; Grosso-Pilcher, C; Grundler, U; Guimaraes da Costa, J; Gunay-Unalan, Z; Haber, C; Hahn, K; Hahn, S R; Halkiadakis, E; Hamilton, A; Han, B-Y; Han, J Y; Handler, R; Happacher, F; Hara, K; Hare, M; Harper, S; Harr, R F; Harris, R M; Hartz, M; Hatakeyama, K; Hauser, J; Heijboer, A; Heinemann, B; Heinrich, J; Henderson, C; Herndon, M; Heuser, J; Hidas, D; Hill, C S; Hirschbuehl, D; Hocker, A; Holloway, A; Hou, S; Houlden, M; Hsu, S-C; Huffman, B T; Hughes, R E; Husemann, U; Huston, J; Incandela, J; Introzzi, G; Iori, M; Ishizawa, Y; Ivanov, A; Iyutin, B; James, E; Jang, D; Jayatilaka, B; Jeans, D; Jensen, H; Jeon, E J; Jindariani, S; Jones, M; Joo, K K; Jun, S Y; Jung, J E; Junk, T R; Kamon, T; Karchin, P E; Kato, Y; Kemp, Y; Kephart, R; Kerzel, U; Khotilovich, V; Kilminster, B; Kim, D H; Kim, H S; Kim, J E; Kim, M J; Kim, S B; Kim, S H; Kim, Y K; Kimura, N; Kirsch, L; Klimenko, S; Klute, M; Knuteson, B; Ko, B R; Kondo, K; Kong, D J; Konigsberg, J; Korytov, A; Kotwal, A V; Kovalev, A; Kraan, A C; Kraus, J; Kravchenko, I; Kreps, M; Kroll, J; Krumnack, N; Kruse, M; Krutelyov, V; Kubo, T; Kuhlmann, S E; Kuhr, T; Kusakabe, Y; Kwang, S; Laasanen, A T; Lai, S; Lami, S; Lammel, S; Lancaster, M; Lander, R L; Lannon, K; Lath, A; Latino, G; Lazzizzera, I; LeCompte, T; Lee, J; Lee, J; Lee, Y J; Lee, S W; Lefèvre, R; Leonardo, N; Leone, S; Levy, S; Lewis, J D; Lin, C; Lin, C S; Lindgren, M; Lipeles, E; Lister, A; Litvintsev, D O; Liu, T; Lockyer, N S; Loginov, A; Loreti, M; Loverre, P; Lu, R-S; Lucchesi, D; Lujan, P; Lukens, P; Lungu, G; Lyons, L; Lys, J; Lysak, R; Lytken, E; Mack, P; MacQueen, D; Madrak, R; Maeshima, K; Makhoul, K; Maki, T; Maksimovic, P; Malde, S; Manca, G; Margaroli, F; Marginean, R; Marino, C; Marino, C P; Martin, A; Martin, M; Martin, V; Martínez, M; Maruyama, T; Mastrandrea, P; Masubuchi, T; Matsunaga, H; Mattson, M E; Mazini, R; Mazzanti, P; McFarland, K S; McIntyre, P; McNulty, R; Mehta, A; Mehtala, P; Menzemer, S; Menzione, A; Merkel, P; Mesropian, C; Messina, A; Miao, T; Miladinovic, N; Miles, J; Miller, R; Mills, C; Milnik, M; Mitra, A; Mitselmakher, G; Miyamoto, A; Moed, S; Moggi, N; Mohr, B; Moore, R; Morello, M; Movilla Fernandez, P; Mülmenstädt, J; Mukherjee, A; Muller, Th; Mumford, R; Murat, P; Nachtman, J; Nagano, A; Naganoma, J; Nakano, I; Napier, A; Necula, V; Neu, C; Neubauer, M S; Nielsen, J; Nigmanov, T; Nodulman, L; Norniella, O; Nurse, E; Oh, S H; Oh, Y D; Oksuzian, I; Okusawa, T; Oldeman, R; Orava, R; Osterberg, K; Pagliarone, C; Palencia, E; Papadimitriou, V; Paramonov, A A; Parks, B; Pashapour, S; Patrick, J; Pauletta, G; Paulini, M; Paus, C; Pellett, D E; Penzo, A; Phillips, T J; Piacentino, G; Piedra, J; Pinera, L; Pitts, K; Plager, C; Pondrom, L; Portell, X; Poukhov, O; Pounder, N; Prakoshyn, F; Pronko, A; Proudfoot, J; Ptohos, F; Punzi, G; Pursley, J; Rademacker, J; Rahaman, A; Ranjan, N; Rappoccio, S; Reisert, B; Rekovic, V; Renton, P; Rescigno, M; Richter, S; Rimondi, F; Ristori, L; Robson, A; Rodrigo, T; Rogers, E; Rolli, S; Roser, R; Rossi, M; Rossin, R; Ruiz, A; Russ, J; Rusu, V; Saarikko, H; Sabik, S; Safonov, A; Sakumoto, W K; Salamanna, G; Saltó, O; Saltzberg, D; Sánchez, C; Santi, L; Sarkar, S; Sartori, L; Sato, K; Savard, P; Savoy-Navarro, A; Scheidle, T; Schlabach, P; Schmidt, E E; Schmidt, M P; Schmitt, M; Schwarz, T; Scodellaro, L; Scott, A L; Scribano, A; Scuri, F; Sedov, A; Seidel, S; Seiya, Y; Semenov, A; Sexton-Kennedy, L; Sfyrla, A; Shapiro, M D; Shears, T; Shepard, P F; Sherman, D; Shimojima, M; Shochet, M; Shon, Y; Shreyber, I; Sidoti, A; Sinervo, P; Sisakyan, A; Sjolin, J; Slaughter, A J; Slaunwhite, J; Sliwa, K; Smith, J R; Snider, F D; Snihur, R; Soderberg, M; Soha, A; Somalwar, S; Sorin, V; Spalding, J; Spinella, F; Spreitzer, T; Squillacioti, P; Stanitzki, M; Staveris-Polykalas, A; St Denis, R; Stelzer, B; Stelzer-Chilton, O; Stentz, D; Strologas, J; Stuart, D; Suh, J S; Sukhanov, A; Sun, H; Suzuki, T; Taffard, A; Takashima, R; Takeuchi, Y; Takikawa, K; Tanaka, M; Tanaka, R; Tecchio, M; Teng, P K; Terashi, K; Thom, J; Thompson, A S; Thomson, E; Tipton, P; Tiwari, V; Tkaczyk, S; Toback, D; Tokar, S; Tollefson, K; Tomura, T; Tonelli, D; Torre, S; Torretta, D; Tourneur, S; Trischuk, W; Tsuchiya, R; Tsuno, S; Turini, N; Ukegawa, F; Unverhau, T; Uozumi, S; Usynin, D; Vallecorsa, S; van Remortel, N; Varganov, A; Vataga, E; Vázquez, F; Velev, G; Veramendi, G; Veszpremi, V; Vidal, R; Vila, I; Vilar, R; Vine, T; Vollrath, I; Volobouev, I; Volpi, G; Würthwein, F; Wagner, P; Wagner, R G; Wagner, R L; Wagner, J; Wagner, W; Wallny, R; Wang, S M; Warburton, A; Waschke, S; Waters, D; Wester, W C; Whitehouse, B; Whiteson, D; Wicklund, A B; Wicklund, E; Williams, G; Williams, H H; Wilson, P; Winer, B L; Wittich, P; Wolbers, S; Wolfe, C; Wright, T; Wu, X; Wynne, S M; Yagil, A; Yamamoto, K; Yamaoka, J; Yamashita, T; Yang, C; Yang, U K; Yang, Y C; Yao, W M; Yeh, G P; Yoh, J; Yorita, K; Yoshida, T; Yu, G B; Yu, I; Yu, S S; Yun, J C; Zanello, L; Zanetti, A; Zaw, I; Zhang, X; Zhou, J; Zucchelli, S

2007-03-30

We present an analysis of angular distributions and correlations of the X(3872) particle in the exclusive decay mode X(3872)-->J/psipi+ pi- with J/psi-->mu+ mu-. We use 780 pb-1 of data from pp[over ] collisions at sqrt[s]=1.96 TeV collected with the CDF II detector at the Fermilab Tevatron. We derive constraints on spin, parity, and charge conjugation parity of the X(3872) particle by comparing measured angular distributions of the decay products with predictions for different J(PC) hypotheses. The assignments J(PC)=1++ and 2-+ are the only ones consistent with the data.

X-ray micro-beam techniques and phase contrast tomography applied to biomaterials

NASA Astrophysics Data System (ADS)

Fratini, Michela; Campi, Gaetano; Bukreeva, Inna; Pelliccia, Daniele; Burghammer, Manfred; Tromba, Giuliana; Cancedda, Ranieri; Mastrogiacomo, Maddalena; Cedola, Alessia

2015-12-01

A deeper comprehension of the biomineralization (BM) process is at the basis of tissue engineering and regenerative medicine developments. Several in-vivo and in-vitro studies were dedicated to this purpose via the application of 2D and 3D diagnostic techniques. Here, we develop a new methodology, based on different complementary experimental techniques (X-ray phase contrast tomography, micro-X-ray diffraction and micro-X-ray fluorescence scanning technique) coupled to new analytical tools. A qualitative and quantitative structural investigation, from the atomic to the micrometric length scale, is obtained for engineered bone tissues. The high spatial resolution achieved by X-ray scanning techniques allows us to monitor the bone formation at the first-formed mineral deposit at the organic-mineral interface within a porous scaffold. This work aims at providing a full comprehension of the morphology and functionality of the biomineralization process, which is of key importance for developing new drugs for preventing and healing bone diseases and for the development of bio-inspired materials.

X-15 launch from B-52 mothership

NASA Technical Reports Server (NTRS)

1959-01-01

This photo illustrates how the X-15 rocket-powered aircraft was taken aloft under the wing of a B-52. Because of the large fuel consumption, the X-15 was air launched from a B-52 aircraft at 45,000 ft and a speed of about 500 mph. This was one of the early powered flights using a pair of XLR-11 engines (until the XLR-99 became available). The X-15 was a rocket-powered aircraft 50 ft long with a wingspan of 22 ft. It was a missile-shaped vehicle with an unusual wedge-shaped vertical tail, thin stubby wings, and unique fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was capable of developing 57,000 lb of rated thrust (actual thrust reportedly climbed to 60,000 lb). North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow-on program used the aircraft as a testbed to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudder surfaces on the vertical stabilizers to control yaw and canted horizontal surfaces on the tail to control pitch when moving in synchronization or roll when moved differentially. For flight in the thin air outside of the appreciable Earth's atmosphere, the X-15 used a reaction control system. Hydrogen peroxide thrust rockets located on the nose of the aircraft provided pitch and yaw control. Those on the wings provided roll control. Because of the large fuel consumption, the X-15 was air launched from a B-52 aircraft at 45,000 ft and a speed of about 500 mph. Depending on the mission, the rocket engine provided thrust for the first 80 to 120 sec of flight. The remainder of the normal 10 to 11 min. flight was powerless and ended with a 200-mph glide landing. Generally, one of two types of X-15 flight profiles was used: a high-altitude flight plan that called for the pilot to maintain a steep rate of climb, or a speed profile that called for the pilot to push over and maintain a level altitude. The X-15 was flown over a period of nearly 10 years--June 1959 to Oct. 1968--and set the world's unofficial speed and altitude records of 4,520 mph (Mach 6.7) and 354,200 ft (over 67 mi) in a program to investigate all aspects of piloted hypersonic flight. Information gained from the highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo manned spaceflight programs, and also the Space Shuttle program. The X-15s made a total of 199 flights and were manufactured by North American Aviation. X-15-1, serial number 56-6670, is now located at the National Air and Space Museum, Washington DC. North American X-15A-2, serial number 56-6671, is at the United States Air Force Museum, Wright-Patterson AFB, Ohio. The X-15-3, serial number 56-6672, crashed on 15 November 1967, resulting in the death of Maj. Michael J. Adams.

Astronomical Applications of New Line Lists for CN, C_2 and Their Isotopologues

NASA Astrophysics Data System (ADS)

Bernath, Peter F.; Sneden, Chris; Brooke, James S. A.; Ram, Ram

2014-06-01

For cool stellar and substellar objects, atomic lines weaken, and detailed elemental and isotopic abundances are often derived from molecular absorption features. We have embarked on a project to provide molecular line lists by combining experimental observations for line positions with ab initio calculations for line strengths. So far we have results for MgH (A-X and B-X transitions), C2 (Swan system), CP (A-X transition), NH (vibration-rotation bands) and OH (Meinel system). This talk will briefly describe the new line lists for the Swan system (d3Π-a3Π) of C2 and 12C13C, and the red (A2Π-X2Σ+) and violet (B2Σ+-X2Σ+) systems of CN, 13CN and C15N. Applications to the spectra of carbon-enhanced metal-poor stars, the K-giant Arcturus, the metal-rich open cluster NGC 6791, the Sun and comets will be presented. E. GharibNezhad, A. Shayesteh and P. F. Bernath, Mon. Notices R. Astro. Soc. 432, 2043-2047 (2013) . H. Hinkle, L. Wallace, R. S. Ram, P. F. Bernath, C. Sneden and S. Lucatello, Astrophys. J. Suppl. 207, 26 (7pp) (2013) J. S. A. Brooke, P. F. Bernath, T. W. Schmidt and G. B. Bacskay, J. Quant. Spectrosc. Rad. Trans. 124, 11-20 (2013) R. S. Ram, J. S. A. Brooke, P. F. Bernath, C. Sneden and S. Lucatello, Astrophys. J. Suppl. 211, 5 (7pp) (2014) J. S. A. Brooke, R. S. Ram, C. M. Western, G. Li, D. W. Schwenke and P. F. Bernath, Astrophys. J. Suppl. 210, 23 (15pp) (2014) R. S. Ram, J. S. A. Brooke, C.M. Western and P. F. Bernath, J. Quant. Spectrosc. Rad. Transfer (in press) J. S. A. Brooke et al., this meeting, P301

Measurements of ψ(2S) and X(3872) → J/ψπ +π – production in pp collisions at $$ \\sqrt{s}=8 $$ TeV with the ATLAS detector

DOE PAGES

Aaboud, M.; Aad, G.; Abbott, B.; ...

2017-01-26

Differential cross sections are presented for the prompt and non-prompt production of the hidden-charm states X(3872) and ψ(2S), in the decay mode J/ψπ +π –, measured using 11.4 fb –1 of pp collisions at √s = 8 TeV by the ATLAS detector at the LHC. The ratio of cross-sections X(3872)/ψ(2S) is also given, separately for prompt and non-prompt components, as well as the non-prompt fractions of X(3872) and ψ(2S). Assuming independent single effective lifetimes for non-prompt X(3872) and ψ(2S) production gives R B = B(B→X(3872)+any)B(X(3872)→J/ψπ+π–)/B(B→ψ(2S)+any)B(ψ(2S)→J/ψπ+π–)=(3.95±0.32(stat)±0.08(sys))×10 –2 separating short- and long-lived contributions, assuming that the short-lived component is due to Bmore » c decays, gives R B = (3.57 ± 0.33(stat) ± 0.11(sys)) × 10 –2, with the fraction of non-prompt X(3872) produced via B c decays for p T(X(3872)) > 10 GeV being (25 ± 13(stat) ± 2(sys) ± 5(spin))%. The distributions of the dipion invariant mass in the X(3872) and ψ(2S) decays are also measured and compared to theoretical predictions.« less

Measurements of ψ(2S) and X(3872) → J/ψπ +π – production in pp collisions at $$ \\sqrt{s}=8 $$ TeV with the ATLAS detector

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

Aaboud, M.; Aad, G.; Abbott, B.

Differential cross sections are presented for the prompt and non-prompt production of the hidden-charm states X(3872) and ψ(2S), in the decay mode J/ψπ +π –, measured using 11.4 fb –1 of pp collisions at √s = 8 TeV by the ATLAS detector at the LHC. The ratio of cross-sections X(3872)/ψ(2S) is also given, separately for prompt and non-prompt components, as well as the non-prompt fractions of X(3872) and ψ(2S). Assuming independent single effective lifetimes for non-prompt X(3872) and ψ(2S) production gives R B = B(B→X(3872)+any)B(X(3872)→J/ψπ+π–)/B(B→ψ(2S)+any)B(ψ(2S)→J/ψπ+π–)=(3.95±0.32(stat)±0.08(sys))×10 –2 separating short- and long-lived contributions, assuming that the short-lived component is due to Bmore » c decays, gives R B = (3.57 ± 0.33(stat) ± 0.11(sys)) × 10 –2, with the fraction of non-prompt X(3872) produced via B c decays for p T(X(3872)) > 10 GeV being (25 ± 13(stat) ± 2(sys) ± 5(spin))%. The distributions of the dipion invariant mass in the X(3872) and ψ(2S) decays are also measured and compared to theoretical predictions.« less

Electron-Beam Sustained Mercuric Bromide Laser Study.

DTIC Science & Technology

1982-04-29

CATALOG NUMBER R82-925096-1 b~ h PIO COEE 4. TITLE (and Subttle) . TYPE OF REPORT & PERIOD COVERED Final Report Electron-Beam Sustained Mercuric...fractional ionization is taken into account. I3 33 h I 10-10 I Ar* x 102 ’v 10.11 - 107E HgBr2+ E 1) Vd 10-12- -106 2x 10 -7 10-6 105 2x10 -5 FRACTIONAL...pleasure to acknowledge the helpful discussions with our UTRC colleagues J. J. Hinchen, H . H . Michels and W. J. Wiegand, and with Professor D. W

Hard X-Ray Emission from SH 2-104: A NuSTAR Search for Gamma-Ray Counterparts

NASA Technical Reports Server (NTRS)

Gotthelf, E. V.; Mori, K.; Aliu, E.; Paredes, J. M.; Tomsick, J. A.; Boggs, S. E.; Christensen, F. E.; Craig, W. W.; Hailey, C. J.; Harrison, F. A.;

Automated Performance Monitoring and Assessment for DCS Digital Systems.

DTIC Science & Technology

1977-10-01

5.2 Analog Radio Systems 439 A.6 Group Data Modem (AN/USC-26) 453 A.6.1 Data Rates 453 vii ^II^^^IH^^^H^^^ HH ^ HH ^MflH^MBHBIEiiH^B^B&99S&_ 7...in U. 03 ÜJ 03 1 is «r V X V 1 ts ro O O M O 1 rs CM ^r 1- 1 rs TI o _i ! is o *•* OI- hh -Hhh- «c o> s Ci ÜJ li’ UJ UJ ÜJ u i •o o IS H d Ci Ci...j 0) tOOOOQiklkHH 03 03 UI0)BfiSSAAHI> HH ttaaAuuuuoocccs s E z xi 03 o^i a a i- 2: x x x x cß<:ffi<:ä<i:ä<:a«iB<c« s- 1- > r> z r: z z u u M M x

A Finite Element Model of a White-Metzner Viscoelastic Polymer Extrudate.

DTIC Science & Technology

1981-02-01

for Va as: Forward Difference: ail~ a WiX + Yl Jjxf + 2 1 jijX 2 + 1 32a~i jAy2 + 0i,j+l = i~j + Da~Ax 1 92a iA*2+ 1 32a *2 ’T -a .Ax + 75. h...and gyro element coincide, and 5. The rotor bearing structure is rigid. For a platform stabilized single degree of freedom gyro, these assumptions lead

Nonadiabatic dynamics of O({sup 1}D) + N{sub 2}(X{sup 1}{Sigma}{sub g}{sup +}){yields}O({sup 3}P) + N{sub 2}(X{sup 1}{Sigma}{sub g}{sup +}) on three coupled potential surfaces: Symmetry, Coriolis, spin-orbit, and Renner-Teller effects

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

Defazio, Paolo; Gamallo, Pablo; Petrongolo, Carlo

2012-02-07

We present the spin-orbit (SO) and Renner-Teller (RT) quantum dynamics of the spin-forbidden quenching O({sup 1}D) + N{sub 2}(X{sup 1}{Sigma}{sub g}{sup +}){yields}O({sup 3}P) + N{sub 2}(X{sup 1}{Sigma}{sub g}{sup +}) on the N{sub 2}O X-tilde{sup 1}A{sup '}, a-tilde{sup 3}A', and b-tilde{sup 3}A{sup '} coupled PESs. We use the permutation-inversion symmetry, propagate coupled-channel (CC) real wavepackets, and compute initial-state-resolved probabilities and cross sections {sigma}{sub j0} for the ground vibrational and the first two rotational states of N{sub 2}, j{sub 0}= 0 and 1. Labeling symmetry angular states by j and K, we report selection rules for j and for the minimum Kmore » value associated with any electronic state, showing that a-tilde{sup 3}A' is uncoupled in the centrifugal-sudden (CS) approximation at j{sub 0}= 0. The dynamics is resonance-dominated, the probabilities are larger at low K, {sigma}{sub j0} decrease with the collision energy and increase with j{sub 0}, and the CS {sigma}{sub 0} is lower than the CC one. The nonadiabatic interactions play different roles on the quenching dynamics, because the X-tilde{sup 1}A{sup '}-b-tilde{sup 3}A{sup '} SO effects are those most important while the a-tilde{sup 3}A'-b-tilde{sup 3}A{sup '} RT ones are negligible.« less

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.

X-15 flight crew - Engle, Rushworth, McKay, Knight, Thompson, and Dana

NASA Technical Reports Server (NTRS)

1966-01-01

The X-15 flight crew, left to right; Air Force Captain Joseph H. Engle, Air Force Major Robert A. Rushworth, NASA pilot John B. 'Jack' McKay, Air Force Major William J. 'Pete' Knight, NASA pilot Milton O. Thompson, and NASA pilot Bill Dana. These six pilots made 125 of the 199 total flights in the X-15. Rushworth made 34 flights (the most of any X-15 pilot); McKay flew 29 times; Engle, Knight, and Dana each flew 16 times; Thompson's total was 14. The X-15 was a rocket-powered aircraft 50 ft long with a wingspan of 22 ft. It was a missile-shaped vehicle with an unusual wedge-shaped vertical tail, thin stubby wings, and unique fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was capable of developing 57,000 lb of rated thrust (actual thrust reportedly climbed to 60,000 lb). North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow-on program used the aircraft as a testbed to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudder surfaces on the vertical stabilizers to control yaw and canted horizontal surfaces on the tail to control pitch when moving in synchronization or roll when moved differentially. For flight in the thin air outside of the appreciable Earth's atmosphere, the X-15 used a reaction control system. Hydrogen peroxide thrust rockets located on the nose of the aircraft provided pitch and yaw control. Those on the wings provided roll control. Because of the large fuel consumption, the X-15 was air launched from a B-52 aircraft at 45,000 ft and a speed of about 500 mph. Depending on the mission, the rocket engine provided thrust for the first 80 to 120 sec of flight. The remainder of the normal 10 to 11 min. flight was powerless and ended with a 200-mph glide landing. Generally, one of two types of X-15 flight profiles was used: a high-altitude flight plan that called for the pilot to maintain a steep rate of climb, or a speed profile that called for the pilot to push over and maintain a level altitude. The X-15 was flown over a period of nearly 10 years--June 1959 to Oct. 1968--and set the world's unofficial speed and altitude records of 4,520 mph (Mach 6.7) and 354,200 ft (over 67 mi) in a program to investigate all aspects of piloted hypersonic flight. Information gained from the highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo manned spaceflight programs, and also the Space Shuttle program. The X-15s made a total of 199 flights and were manufactured by North American Aviation. X-15-1, serial number 56-6670, is now located at the National Air and Space Museum, Washington DC. North American X-15A-2, serial number 56-6671, is at the United States Air Force Museum, Wright-Patterson AFB, Ohio. The X-15-3, serial number 56-6672, crashed on 15 November 1967, resulting in the death of Maj. Michael J. Adams.

Manufacture of bulk superconducting YBa2Cu3O(7-delta) by a continuous process

NASA Technical Reports Server (NTRS)

Meng, R. L.; Kinalidis, C.; Sun, Y. Y.; Gao, L.; Tao, Y. K.

1990-01-01

The development of a continuous process for fabricating large bulk superconductors with a predetermined grain orientation is reported. A bar of the 123 compound with dimensions 5 x 0.5 x about 0.3 cm with excellent grain alignment has been fabricated continuously. The bulk 123 thus obtained has magnetically determined J(c)s of about 30,000 and 12,000 A/sq cm at 0 and 1 T, respectively, and transport J(c)s of 20,000, 11,000, and 7500 A-sq cm at 0, 0.54, and 0.83 T.

Optical Studies of 15 Hard X-Ray Selected Cataclysmic Binaries

NASA Astrophysics Data System (ADS)

Halpern, Jules P.; Thorstensen, John R.; Cho, Patricia; Collver, Gabriel; Motsoaledi, Mokhine; Breytenbach, Hannes; Buckley, David A. H.; Woudt, Patrick A.

2018-06-01

We conducted time-resolved optical spectroscopy and/or time-series photometry of 15 cataclysmic binaries that were discovered in hard X-ray surveys by the Swift Burst Alert Telescope and the International Gamma-Ray Astrophysics Laboratory, with the goal of measuring their orbital periods and searching for spin periods. Four of the objects in this study are new optical identifications: Swift J0535.2+2830, Swift J2006.4+3645, IGR J21095+4322, and Swift J2116.5+5336. Coherent pulsations are detected from three objects for the first time, Swift J0535.2+2830 (1523 s), 2PBC J1911.4+1412 (747 s), and 1SWXRT J230642.7+550817 (464 s), indicating that they are intermediate polars (IPs). We find two new eclipsing systems in time-series photometry: 2PBC J0658.0‑1746, a polar with a period of 2.38 hr, and Swift J2116.5+5336, a disk system that has an eclipse period of 6.56 hr. Exact or approximate spectroscopic orbital periods are found for six additional targets. Of note is the long 4.637-day orbit for Swift J0623.9‑0939, which is revealed by the radial velocities of the photospheric absorption lines of the secondary star. We also discover a 12.76 hr orbital period for RX J2015.6+3711, which confirms that the previously detected 2.00 hr X-ray period from this star is the spin period of an IP, as inferred by Coti Zelati et al. These results support the conclusion that hard X-ray selection favors magnetic CVs, with IPs outnumbering polars.

More Intelligent Gas Turbine Engines (Des turbomoteurs plus intelligents)

DTIC Science & Technology

2009-04-01

Group 128. by Dennis Culley, NASA Glenn Research Center Sanjay Garg, NASA Glenn Research Center S.-J. Hiller, MTU Aero Engines GmbH Wolfgang Horn...in Swirled Gas Turbine Combustors”, AIAA-2005-116. [2.90] Seume, J.R., Vortmeyer, N., Krause , W., Hermann, J., Hantschk, C.-C., Zangl, P., Gleis, S...TR-AVT-128 8 - 1 Chapter 8 – SUMMARY AND RECOMMENDATIONS by Sanjay Garg (NASA Glenn Research Center), Wolfgang Horn and S.-J. Hiller (MTU

X-15 #3 and F-104A chase plane landing

NASA Technical Reports Server (NTRS)

1960-01-01

Followed by a Lockheed F-104A Starfighter chase plane, the North American X-15 ship #3 (56-6672) sinks toward touchdown on Rogers Dry Lake following a research flight. In the foreground is green smoke, used to indicate wind direction. The F-104 chase pilot joined up with the X-15 as it glided to the landing. The chase pilot was there to warn the X-15 pilot of any problems and to call out the altitude above the lakebed. F-104 aircraft were also used for X-15 pilot training to simulate the landing characteristics of the rocket-powered airplane, which landed without engine power since the rocket engine had already burned all of its propellant before the landing. The F-104s could simulate the steep descent of the X-15 as it glided to a landing. They did this by extending the landing gear and speed brakes while setting the throttle to idle. The X-15 was a rocket-powered aircraft. The original three aircraft were about 50 ft long with a wingspan of 22 ft. The modified #2 aircraft (X-15A-2 was longer.) They were a missile-shaped vehicles with unusual wedge-shaped vertical tails, thin stubby wings, and unique side fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was rated at 57,000 lb of thrust, although there are indications that it actually achieved up to 60,000 lb. North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow-on program used the aircraft as testbeds to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudder surfaces on the vertical stabilizers to control yaw and movable horizontal stabilizers to control pitch when moving in synchronization or roll when moved differentially. For flight in the thin air outside of the appreciable Earth's atmosphere, the X-15 used a reaction control system. Hydrogen peroxide thrust rockets located on the nose of the aircraft provided pitch and yaw control. Those on the wings provided roll control. Because of the large fuel consumption, the X-15 was air launched from a B-52 aircraft at approximately 45,000 ft and a speed of about 500 mph. Depending on the mission, the rocket engine provided thrust for the first 80 to 120 sec of flight. The remainder of the normal 10 to 11 min. flight was powerless and ended with a 200-mph glide landing. Generally, one of two types of X-15 flight profiles was used; a high-altitude flight plan that called for the pilot to maintain a steep rate of climb, or a speed profile that called for the pilot to push over and maintain a level altitude. The X-15 was flown over a period of nearly 10 years -- June 1959 to Oct. 1968 -- and set the world's unofficial speed and altitude records of 4,520 mph (Mach 6.7) and 354,200 ft in a program to investigate all aspects of manned hypersonic flight. Information gained from the highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo manned spaceflight programs, and also the Space Shuttle program. The X-15s made a total of 199 flights, and were manufactured by North American Aviation. X-15-1, serial number 56-6670, is now located at the National Air and Space Museum, Washington DC. North American X-15A-2, serial number 56-6671, is at the United States Air Force Museum, Wright-Patterson AFB, Ohio. X-15-3, serial number 56-6672, crashed on 15 November 1967, resulting in the death of Maj. Michael J. Adams.

Subcontracting Opportunities with DoD Major Prime Contractors

DTIC Science & Technology

1991-01-01

W 0in W(wL W -4L-0 M I 0cr0 mix C/(/7 - I.- > ’-4 m 031 #-4W#-t uW <F-4"- ..J 1-107 1-- C4(/ 01 1--W1- zz1- -Zj x wJ3- w Z< c D~ MM-J -J=L0 -J I.-w...W) La4mN04 W C4 t- 24C𔃾 XɜN WZO) -c44 WI CCCC4 x--cc-W 4C-4 "e 5-4C- dC[Jo hLX-4 WZ.X 4 m0-I xx-Iq -X.-4 maC) kfC -M- >0CLo -Ji r n WOC CU O (nCl)Ut...zc U)C aJ 0 z U) -4 1-’CI 4 0. -4N C 0C 00 4 .0_4 004n cc -400 WI 2-’ o WI2W -Z- 0 =~ I)4 0 W n IdT M1 0 . 01-4 1 . 1 -4 W 3z) 1.41 I U) i 0-00 Mix

KSC-2012-2692

NASA Image and Video Library

2012-04-25

HAWTHORNE, Calif. -- NASA astronauts and industry experts check out the crew accommodations in the Dragon spacecraft under development by Space Exploration Technologies SpaceX of Hawthorne, Calif., for the agency's Commercial Crew Program. On top, from left, are NASA Crew Survival Engineering Team Lead Dustin Gohmert, NASA astronauts Tony Antonelli and Eric Boe and SpaceX Mission Operations Engineer Laura Crabtree. On bottom, from left, are SpaceX Thermal Engineer Brenda Hernandez and NASA astronauts Rex Walheim and Tim Kopra. This is the second crew accommodation check that allowed passengers to get a feel for Dragon’s interior, including displays and simulated control panels. In 2011, NASA selected SpaceX during Commercial Crew Development Round 2 CCDev2) activities to mature the design and development of a crew transportation system with the overall goal of accelerating a United States-led capability to the International Space Station. The goal of CCP is to drive down the cost of space travel as well as open up space to more people than ever before by balancing industry’s own innovative capabilities with NASA's 50 years of human spaceflight experience. Six other aerospace companies also are maturing launch vehicle and spacecraft designs under CCDev2, including Alliant Techsystems Inc. ATK, The Boeing Co., Excalibur Almaz Inc., Blue Origin, Sierra Nevada, and United Launch Alliance ULA. For more information, visit www.nasa.gov/commercialcrew. Image credit: Space Exploration Technologies

Hard X-Ray Emission from Sh 2-104: A NuSTAR Search for Gamma-Ray Counterparts

NASA Astrophysics Data System (ADS)

Gotthelf, E. V.; Mori, K.; Aliu, E.; Paredes, J. M.; Tomsick, J. A.; Boggs, S. E.; Christensen, F. E.; Craig, W. W.; Hailey, C. J.; Harrison, F. A.; Hong, J. S.; Rahoui, F.; Stern, D.; Zhang, W. W.

2016-07-01

We present NuSTAR hard X-ray observations of Sh 2-104, a compact H II region containing several young massive stellar clusters (YMSCs). We have detected distinct hard X-ray sources coincident with localized VERITAS TeV emission recently resolved from the giant gamma-ray complex MGRO J2019+37 in the Cygnus region. Fainter, diffuse X-rays coincident with the eastern YMSC in Sh2-104 likely result from the colliding winds of a component star. Just outside the radio shell of Sh 2-104 lies 3XMM J201744.7+365045 and a nearby nebula, NuSTAR J201744.3+364812, whose properties are most consistent with extragalactic objects. The combined XMM-Newton and NuSTAR spectrum of 3XMM J201744.7+365045 is well-fit to an absorbed power-law model with {N}{{H}}=(3.1+/- 1.0)× {10}22 cm-2 and a photon index {{Γ }}=2.1+/- 0.1. Based on possible long-term flux variation and the lack of detected pulsations (≤43% modulation), this object is likely a background active galactic nucleus rather than a Galactic pulsar. The spectrum of the NuSTAR nebula shows evidence of an emission line at E = 5.6 keV, suggesting an optically obscured galaxy cluster at z = 0.19 ± 0.02 (d = 800 Mpc) and L X = 1.2 × 1044 erg s-1. Follow-up Chandra observations of Sh 2-104 will help identify the nature of the X-ray sources and their relation to MGRO J2019+37. We also show that the putative VERITAS excess south of Sh 2-104, is most likely associated with the newly discovered Fermi pulsar PSR J2017+3625 and not the H II region.

In(x)Ga(₁-x)As nanowires on silicon: one-dimensional heterogeneous epitaxy, bandgap engineering, and photovoltaics.

PubMed

Shin, Jae Cheol; Kim, Kyou Hyun; Yu, Ki Jun; Hu, Hefei; Yin, Leijun; Ning, Cun-Zheng; Rogers, John A; Zuo, Jian-Min; Li, Xiuling

2011-11-09

We report on the one-dimensional (1D) heteroepitaxial growth of In(x)Ga(1-x)As (x = 0.2-1) nanowires (NWs) on silicon (Si) substrates over almost the entire composition range using metalorganic chemical vapor deposition (MOCVD) without catalysts or masks. The epitaxial growth takes place spontaneously producing uniform, nontapered, high aspect ratio NW arrays with a density exceeding 1 × 10(8)/cm(2). NW diameter (∼30-250 nm) is inversely proportional to the lattice mismatch between In(x)Ga(1-x)As and Si (∼4-11%), and can be further tuned by MOCVD growth condition. Remarkably, no dislocations have been found in all composition In(x)Ga(1-x)As NWs, even though massive stacking faults and twin planes are present. Indium rich NWs show more zinc-blende and Ga-rich NWs exhibit dominantly wurtzite polytype, as confirmed by scanning transmission electron microscopy (STEM) and photoluminescence spectra. Solar cells fabricated using an n-type In(0.3)Ga(0.7)As NW array on a p-type Si(111) substrate with a ∼ 2.2% area coverage, operates at an open circuit voltage, V(oc), and a short circuit current density, J(sc), of 0.37 V and 12.9 mA/cm(2), respectively. This work represents the first systematic report on direct 1D heteroepitaxy of ternary In(x)Ga(1-x)As NWs on silicon substrate in a wide composition/bandgap range that can be used for wafer-scale monolithic heterogeneous integration for high performance photovoltaics.

Piezoelectric and Electrostrictive Materials for Transducer Applications. Volume 1

DTIC Science & Technology

1991-01-31

compo sition No. i, 24.S kV/cm oaxmposition No. 12 and 29 kV/cm ofomposi. sitsm No. 4. tia No. 4. 62 J. ApI . P M., Vol. 6,, No. 12. 15 Oecenulm ItOU Pan...symmetry Pm3m is I I: G 1 = 3Xo(T-To)P32 + P34 + P36 + 13032 + v034 +0P32032 - 1/2sll(X12+X22+X32)- S12(XIX 2+X2X 3+X3XI) - 1/2s44(X4 2 + X52 + X62) - (Qi 1...Piewitt, Acta Cryst. B25, 925 (1969). FIG. 7. Inhomogeneous order in a PST ceramic grain. 5L . E. Cross, Ferroelectrics 76, 241-267 (1987). J. Mater

Development of Mechanistic Flexible Pavement Design Concepts for the Heavyweight F-15 Aircraft

DTIC Science & Technology

1986-01-01

UPON REPETITION - VERTICAL SUBGRADE STRAIN RESULTS 131 B-l AC TENSILE STRAIN VERSUS AC THICKNESS, VARYING GRANULAR BASE THICKNESS 204 B...Log SR - 0.8243 - .4095(Log TAg)(Log E*^) - .0110(TGR/Log TAC) ♦ . 0132 (ERi) - .3811(Log ERi) R2-.947 SEE-.0506 (1.124) R2-.923 SEE-.06 Log DO...Thickness. 204 lk^»-^>W »-» •■■*-»«.■■»-»*-!»*» »j(i »*Ä«**»«iutft^^*fij»Ä^»t’Äa*a<uiKajtfj»«iBym^j,Ä*^j’jifjauai**Ä: -**> -"> V \\X%M?J(fjtfJK

Analyses of Injection-Coupled Combustion Instability from J-2X Gas Generator Development

NASA Technical Reports Server (NTRS)

Hulka, James R.; Kenny, R. Jeremy; Protz, Chris; Casiano, Matthew

2011-01-01

During development of the gas generator for the liquid oxygen/liquid hydrogen propellant J-2X rocket engine, combustion instabilities were observed near the frequency of the first longitudinal acoustic mode of the hot gas combustion chamber duct. These instabilities were similar to intermediate-frequency or buzz-type instabilities as described in historical programs, except for several aspects: 1) the frequencies were low, in the realm of chug; 2) at times the instability oscillation amplitudes were quite large, with peak-to-peak amplitudes exceeding 50% of the mean chamber pressure along with the appearance of harmonics; 3) the chamber excitation was related to but not exactly at the first longitudinal combustion chamber acoustic mode; and 4) the injector provided mass flow rate oscillations induced by capacitance and inertance effects in the injector rather than by organ pipe resonances of the coaxial oxidizer posts. This type of combustion instability is referred to as "injection coupling" because one critical driving source of the instability is mass flow rate oscillations from the injector. However, the type of injection coupling observed here is different than observed in previous instances of buzz instability with coaxial injectors, because of the lower frequencies and lack of influence from the oxidizer post organ pipe resonances. Test data and preliminary analyses of the initial combustion instabilities were presented in several papers at the 5th Liquid Propulsion Subcommittee meeting. Since that time, additional hot-fire tests with several new hardware configurations have been conducted, and additional analyses have been completed. The analytical models described in previous papers have been updated to include the influences of new geometrical configurations, including a different oxidizer injector manifold configuration and a branch pipe in the hot gas duct that supplies gaseous helium during the start transient to pre-spin the turbine. In addition, the analysis methodology has been revisited to evaluate the potential influence of a combustion response as well as an injection response.

Pilot Neil Armstrong in the X-15 #1 cockpit

NASA Technical Reports Server (NTRS)

1961-01-01

NASA pilot Neil Armstrong is seen here in the cockpit of the X-15 ship #1 (56-6670) after a research flight. A U.S. Navy pilot in the Korean War who flew 78 combat missions in F9F-2 jet fighters and who was awarded the Air Medal and two Gold Stars, Armstrong graduated from Purdue University in 1955 with a bachelor degree in aeronautical engineering. That same year, he joined the National Advisory Committee for Aeronautics' Lewis Flight Propulsion Laboratory in Cleveland, Ohio (today, the NASA Glenn Research Center). In July 1955, Armstrong transferred to the High-Speed Flight Station (HSFS, as Dryden Flight Research Center was then called) as an aeronautical research engineer. Soon thereafter, he became a research pilot. For the first few years at the HSFS, Armstrong worked on a number of projects. He was a pilot on the Navy P2B-1S used to launch the D-558-2 and also flew the F-100A, F-100C, F-101, F-104A, and X-5. His introduction to rocket flight came on August 15, 1957, with his first flight (of four, total) on the X-1B. He then became one of the first three NASA pilots to fly the X-15, the others being Joe Walker and Jack McKay. (Scott Crossfield, a former NACA pilot, flew the X-15 first but did so as a North American Aviation pilot.) The X-15 was a rocket-powered aircraft. The original three aircraft were about 50 ft long with a wingspan of 22 ft. The modified #2 aircraft (X-15A-2 was longer.) They were a missile-shaped vehicles with unusual wedge-shaped vertical tails, thin stubby wings, and unique side fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was rated at 57,000 lb of thrust, although there are indications that it actually achieved up to 60,000 lb. North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow-on program used the aircraft as testbeds to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudder surfaces on the vertical stabilizers to control yaw and movable horizontal stabilizers to control pitch when moving in synchronization or roll when moved differentially. For flight in the thin air outside of the appreciable Earth's atmosphere, the X-15 used a reaction control system. Hydrogen peroxide thrust rockets located on the nose of the aircraft provided pitch and yaw control. Those on the wings provided roll control. Because of the large fuel consumption, the X-15 was air launched from a B-52 aircraft at approximately 45,000 ft and a speed of about 500 mph. Depending on the mission, the rocket engine provided thrust for the first 80 to 120 sec of flight. The remainder of the normal 10 to 11 min. flight was powerless and ended with a 200-mph glide landing. Generally, one of two types of X-15 flight profiles was used; a high-altitude flight plan that called for the pilot to maintain a steep rate of climb, or a speed profile that called for the pilot to push over and maintain a level altitude. The X-15 was flown over a period of nearly 10 years -- June 1959 to Oct. 1968 -- and set the world's unofficial speed and altitude records of 4,520 mph (Mach 6.7) and 354,200 ft in a program to investigate all aspects of manned hypersonic flight. Information gained from the highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo manned spaceflight programs, and also the Space Shuttle program. The X-15s made a total of 199 flights, and were manufactured by North American Aviation. X-15-1, serial number 56-6670, is now located at the National Air and Space Museum, Washington DC. North American X-15A-2, serial number 56-6671, is at the United States Air Force Museum, Wright-Patterson AFB, Ohio. X-15-3, serial number 56-6672, crashed on 15 November 1967, resulting in the death of Maj. Michael J. Adams.

X-15A-2 with full-scale ablative coating (pink X-15) in Building 4821

NASA Technical Reports Server (NTRS)

1967-01-01

In June 1967, the X-15A-2 rocket-powered research aircraft received a full-scale ablative coating to protect the craft from the high temperatures associated with hypersonic flight (above Mach 5). This pink eraser-like substance, applied to the X-15A-2 aircraft (56-6671), was then covered with a white sealant coat before flight. This coating would help the #2 aircraft reach the record speed of 4,520 mph (Mach 6.7). The basic X-15 was a rocket-powered aircraft 50 ft long with a wingspan of 22 ft. However, the X-15A-2 had been elongated to 52 ft 5 in. Like the other two X-15s, it was a missile-shaped vehicle with an unusual wedge-shaped vertical tail, thin stubby wings, and unique side fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was capable of developing 57,000 lb of thrust. North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow-on program used the aircraft as a testbed to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudder surfaces on the vertical stabilizers to control yaw and movable horizontal stabilizers to control pitch when moving in synchronization or roll when moved differentially. For flight in the thin air outside of the appreciable Earth's atmosphere, the X-15 used a reaction control system. Hydrogen peroxide thrust rockets located on the nose of the aircraft provided pitch and yaw control. Those on the wings provided roll control. Because of the large fuel consumption, the X-15 was air launched from a B-52 aircraft at 45,000 ft and a speed of about 500 mph. Depending on the mission, the rocket engine provided thrust for the first 80 to 120 sec of flight. The remainder of the normal 10 to 11 min. flight was powerless and ended with a 200-mph glide landing. Generally, one of two types of X-15 flight profiles was used; a high-altitude flight plan that called for the pilot to maintain a steep rate of climb, or a speed profile that called for the pilot to push over and maintain a level altitude. The X-15 was flown over a period of nearly 10 years -- June 1959 to Oct. 1968 -- and set the world's unofficial speed and altitude records of 4,520 mph (Mach 6.7) and 354,200 ft in a program to investigate all aspects of manned hypersonic flight. Information gained from the highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo manned spaceflight programs, and also the Space Shuttle program. The X-15s made a total of 199 flights, and were manufactured by North American Aviation. X-15-1, serial number 56-6670, is now located at the National Air and Space Museum, Washington DC. North American X-15A-2, serial number 56-6671, is at the United States Air Force Museum, Wright-Patterson AFB, Ohio. X-15-3, serial number 56-6672, crashed on 15 November 1967, resulting in the death of Maj. Michael J. Adams.

Homogeneous Chaos, p-Forms, Scaling and the Feynman Integral

DTIC Science & Technology

1989-09-01

f)] = f I (f)(x)dPl(X) = 0; T oIR+) (v) EflI p(f),2j = E[ JI p)j 2 p p = p! 11f11 < p!lf11I ; (vi) E[I p(f)I p(g)] = E[I l )Ip (g)] = p! (f’g) 2 p From...p. 62]. ji is only 15 finitely additive on T but is countably additive on T for each fixed ir. (H,.%.) is called a finitely additive canonical...pilS)"’i(Sk)0i (sk + l ) ° ’ ’ ** Ji R xRkl. =1 p 1 k k+ 0i2k (S2k)* #i2k+l pSjkl)"’"#ip(Sp)J-e (s l ..... k )eJ (sk+1 .... S2k)dsl-...*dsk " ds k+l

Hyper-X Engine Testing in the NASA Langley 8-Foot High Temperature Tunnel

NASA Technical Reports Server (NTRS)

Huebner, Lawrence D.; Rock, Kenneth E.; Witte, David W.; Ruf, Edward G.; Andrews, Earl H., Jr.

2000-01-01

Airframe-integrated scramjet engine tests have 8 completed at Mach 7 in the NASA Langley 8-Foot High Temperature Tunnel under the Hyper-X program. These tests provided critical engine data as well as design and database verification for the Mach 7 flight tests of the Hyper-X research vehicle (X-43), which will provide the first-ever airframe- integrated scramjet flight data. The first model tested was the Hyper-X Engine Model (HXEM), and the second was the Hyper-X Flight Engine (HXFE). The HXEM, a partial-width, full-height engine that is mounted on an airframe structure to simulate the forebody features of the X-43, was tested to provide data linking flowpath development databases to the complete airframe-integrated three-dimensional flight configuration and to isolate effects of ground testing conditions and techniques. The HXFE, an exact geometric representation of the X-43 scramjet engine mounted on an airframe structure that duplicates the entire three-dimensional propulsion flowpath from the vehicle leading edge to the vehicle base, was tested to verify the complete design as it will be flight tested. This paper presents an overview of these two tests, their importance to the Hyper-X program, and the significance of their contribution to scramjet database development.

New method for blowup of the Euler-Poisson system

NASA Astrophysics Data System (ADS)

Kwong, Man Kam; Yuen, Manwai

2016-08-01

In this paper, we provide a new method for establishing the blowup of C2 solutions for the pressureless Euler-Poisson system with attractive forces for RN (N ≥ 2) with ρ(0, x0) > 0 and Ω 0 i j ( x 0 ) = /1 2 [" separators=" ∂ i u j ( 0 , x 0 ) - ∂ j u i ( 0 , x 0 ) ] = 0 at some point x0 ∈ RN. By applying the generalized Hubble transformation div u ( t , x 0 ( t ) ) = /N a ˙ ( t ) a ( t ) to a reduced Riccati differential inequality derived from the system, we simplify the inequality into the Emden equation a ̈ ( t ) = - /λ a ( t ) N - 1 , a ( 0 ) = 1 , a ˙ ( 0 ) = /div u ( 0 , x 0 ) N . Known results on its blowup set allow us to easily obtain the blowup conditions of the Euler-Poisson system.

United States Air Force Summer Research Program -- 1993. Volume 16. Arnold Engineering Development Center. Frank J. Seiler Research Laboratory. Wilford Hall Medical Center

DTIC Science & Technology

1993-12-01

A I 7f t UNITED STATE AIR FORCE SUMMER RESEARCH PROGRAM -- 1993 SUMMER RESEARCH PROGRAM FINAL REPORTS VOLUME 16 ARNOLD ENGINEERING DEVELOPMENT CENTER...FRANK J. SELLER RESEARCH LABORATORY WILFORD HALL MEDICAL CENTER RESEARCH & DEVELOPMENT LABORATORIES 5800 Uplander Way Culver City, CA 90230-6608...National Rd. Vol-Page No: 15-44 Dist Tecumseh High School 8.4 New Carlisle, OH 45344-0000 Barber, Jason Laboratory: AL/CF 1000 10th St. Vol-Page No

National Dam Safety Program. Hickory Hollow Lake Dam (MO-31068). Mississippi - Kaskaskia - St. Louis Basin, Perry County, Missouri. Phase I Inspection Report.

DTIC Science & Technology

1980-03-01

Charts 2-1 and 2-2, was prepared by Mr. Thomas J. Dean, Geologist, with the Missouri Department of Applied Engineering & Urban Geology. In the report... Applied Engineering & Urban Geology G oolo & Land Survey J o 8, 1976 TJD bh M: Howard Davis, 425 N. Highway 61, Perryville, MO 63775 Soil Conservation

Automotive Stirling reference engine design report

NASA Technical Reports Server (NTRS)

1981-01-01

The reference Stirling engine system is described which provides the best possible fuel economy while meeting or exceeding all other program objectives. The system was designed to meet the requirements of a 1984 Pontiac Phoenix (X-body). This design utilizes all new technology that can reasonably be expected to be developed by 1984 and that is judged to provide significant improvement, relative to development risk and cost. Topics covered include: (1) external heat system; (2) hot engine system; (3) cold engine system; (4) engine drive system; (5) power control system and auxiliaries; (6) engine instalation; (7) optimization and vehicle simulation; (8) engine materials; and (9) production cost analysis.

Get immersed and black in fire ash world. Field Wildgeographers experience.

NASA Astrophysics Data System (ADS)

Pereira, Paulo; Cerdà, Artemi; Misiune, Ieva; Jordan, Antonio

2015-04-01

Ash is the footprint left by the fire. This residue is very important to landscape recover and is an important source of soil protection after the fire. Get immersed in fire ash world is the same thing of get dirty and do not be recognizable in a fire affected area. To measure ash in the field we have to be careful where to step, how to do the experimental design, collect samples and find with accuracy the places measured before. A good methodology is needed in design field experiments, collect ash samples and monitoring ash evolution (Cerdà and Doerr, 2008; Bodi et al., 2014; Pereira and Ubeda, 2010; Pereira et al. 2011; 2012, 2013, 2014, 2015). The objective of this work is to share with the Avatar world the methodologies used when wildgeographers get immersed in fire ash world, including: 1) Identify the best study area 2) Experimental design 3) Sample collection 4) Get dirty and have fun in the field 5) Laboratory, Statistical and spatial analysis Acknoledgements The author are thankful for the support of the projects POSTFIRE (Soil quality, erosion control and plant cover recovery under different post-fire management scenarios, CGL2013-47862-C2-1-R) funded by the Spanish Ministry of Economy and Competitiveness; GL2008-02879/BTE, LEDDRA 243857, RECARE (Preventing and Remediating Degradation of Soils in Europe Through Land Care, FP7-ENV-2013-TWO STAGE), funded by the European Commission; and for the COST action ES1306 (Connecteur: Connecting European Connectivity Research), FUEGORED (Spanish Network of Forest Fire Effects on Soils, http://grupo.us.es/fuegored/) and to Comissionat per a Universitats i Recerca del DIUE de la Generalitat de Catalunya. References Bodi, M., Martin, D.A., Santin, C., Balfour, V., Doerr, S.H., Pereira, P., Cerda, A., Mataix-Solera, J. (2014) Wildland fire ash: production, composition and eco-hydro-geomorphic effects. Earth-Science Reviews, 130, 103-127. Cerdà, A. y Doerr, S.H. 2008. The effect of ash and needle cover on surface runoff and erosion in the immediate post-fire period. Catena, 74 , 256- 263. doi:10.1016/S0341-8162(02)00027-9 Pereira, P., Cerdà, A., Úbeda, X., Mataix-Solera, J. Arcenegui, V., Zavala, L. 2015. Modelling the impacts of wildfire on ash thickness in a short-term period, Land Degradation and Development, (In Press), DOI: 10.1002/ldr.2195 Pereira, P., Cerdà, A., Úbeda, X., Mataix-Solera, J., Jordan, A. Burguet, M. (2013) Spatial models for monitoring the spatio-temporal evolution of ashes after fire - a case study of a burnt grassland in Lithuania, Solid Earth, 4, 153-165. Pereira, P., Úbeda, X. (2010) Spatial variation of heavy metals released from ashes after a wildfire, Journal of Environmental Engineering and Landscape Management, 18(1), 13-22. Pereira, P., Ubeda, X., Martin, D. (2012) Fire severity effects on ash chemical composition and water-extractable elements, Geoderma, 191, 105-114. Pereira, P., Úbeda, X., Martin, D., Mataix-Solera, J., Guerrero, C. (2011) Effects of a low prescribed fire in ash water soluble elements in a Cork Oak (Quercus suber) forest located in Northeast of Iberian Peninsula, Environmental Research, 111(2), 237-247. Pereira, P., Úbeda, X., Martin, D., Mataix-Solera, J., Cerdà, A., Burguet, M. (2014) Wildfire effects on extractable elements in ash from a Pinus pinaster forest in Portugal, Hydrological Processes, 28, 3681-3690

X-15 mock-up with test pilot Milt Thompson

NASA Technical Reports Server (NTRS)

1993-01-01

NASA research pilot Milt Thompson is seen here with the mock-up of X-15 #3 that was later installed at the NASA Dryden Flight Research Center, Edwards, California. Milton 0. Thompson was a research pilot, Chief Engineer and Director of Research Projects during a long career at the NASA Dryden Flight Research Center. Thompson was hired as an engineer at the flight research facility on 19 March 1956, when it was still under the auspices of NACA. He became a research pilot on 25 May 1958. Thompson was one of the 12 NASA, Air Force, and Navy pilots to fly the X-15 rocket-powered research aircraft between 1959 and 1968. He began flying X-15s on 29 October 1963. He flew the aircraft 14 times during the following two years, reaching a maximum speed of 3723 mph (Mach 5.42) and a peak altitude of 214,100 feet on separate flights. (On a different flight, he reached a Mach number of 5.48 but his mph was only 3712.) Thompson concluded his active flying career in 1968, becoming Director of Research Projects. In 1975 he was appointed Chief Engineer and retained the position until his death on 8 August 1993. The X-15 was a rocket powered aircraft 50 ft long with a wingspan of 22 ft. It was a missile-shaped vehicle with an unusual wedge-shaped vertical tail, thin stubby wings, and unique side fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was capable of developing 57,000 lb of thrust. North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow on program used the aircraft as a testbed to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudder surfaces on the vertical stabilizers to control yaw and movable horizontal stabilizers to control pitch when moving in synchronization or roll when moved differentially. For flight in the thin air outside of the appreciable Earth's atmosphere, the X-15 used a reaction control system. Hydrogen peroxide thrust rockets located on the nose of the aircraft provided pitch and yaw control. Those on the wings provided roll control. Because of the large fuel consumption, the X-15 was air launched from a B-52 aircraft at 45,000 ft and a speed of about 500 mph. Depending on the mission, the rocket engine provided thrust for the first 80 to 120 sec of flight. The remainder of the normal 10 to 11 min. flight was powerless and ended with a 200-mph glide landing. Generally, one of two types of X-15 flight profiles was used; a high-altitude flight plan that called for the pilot to maintain a steep rate of climb, or a speed profile that called for the pilot to push over and maintain a level altitude. The X-15 was flown over a period of nearly 10 years -- June 1959 to Oct. 1968 -- and set the world's unofficial speed and altitude records of 4,520 mph (Mach 6.7) and 354,200 ft in a program to investigate all aspects of manned hypersonic flight. Information gained from the highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo manned spaceflight programs, and also the Space Shuttle program. The X-15s made a total of 199 flights, and were manufactured by North American Aviation. X-15-1, serial number 56-6670, is now located at the National Air and Space Museum, Washington DC. North American X-15A-2, serial number 56-6671, is at the United States Air Force Museum, Wright-Patterson AFB, Ohio. The X-15-3, serial number 56-6672, crashed on 15 November 1967, resulting in the death of Maj. Michael J. Adams.

X-15 mock-up with test pilot Milt Thompson

NASA Technical Reports Server (NTRS)

1993-01-01

NASA research pilot Milt Thompson stands next to a mock-up of X-15 number 3 that was later installed at the NASA Dryden Flight Research Center, Edwards, California. Milton 0. Thompson was a research pilot, Chief Engineer and Director of Research Projects during a long career at the NASA Dryden Flight Research Center. Thompson was hired as an engineer at the flight research facility on 19 March 1956, when it was still under the auspices of NACA. He became a research pilot on 25 May 1958. Thompson was one of the 12 NASA, Air Force, and Navy pilots to fly the X-15 rocket-powered research aircraft between 1959 and 1968. He began flying X-15s on 29 October 1963. He flew the aircraft 14 times during the following two years, reaching a maximum speed of 3723 mph (Mach 5.42) and a peak altitude of 214,100 feet on separate flights. Thompson concluded his active flying career in 1968, becoming Director of Research Projects. In 1975 he was appointed Chief Engineer and retained the position until his death on 8 August 1993. The X-15 was a rocket-powered aircraft 50 ft long with a wingspan of 22 ft. It was a missile-shaped vehicle with an unusual wedge-shaped vertical tail, thin stubby wings, and unique side fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was capable of developing 57,000 lb of thrust. North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow-on program used the aircraft as a testbed to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudder surfaces on the vertical stabilizers to control yaw and moving horizontal stabilizers which control pitch when moving in synchronization or roll when moved differentially. For flight in the thin air outside of the appreciable Earth's atmosphere, the X-15 used a reaction control system. Hydrogen peroxide thrust rockets located on the nose of the aircraft provided pitch and yaw control. Those on the wings provided roll control. Because of the large fuel consumption, the X-15 was air launched from a B-52 aircraft at 45,000 ft and a speed of about 500 mph. Depending on the mission, the rocket engine provided thrust for the first 80 to 120 sec of flight. The remainder of the normal 10 to 11 min. flight was powerless and ended with a 200-mph glide landing. Generally, one of two types of X-15 flight profiles was used; a high-altitude flight plan that called for the pilot to maintain a steep rate of climb, or a speed profile that called for the pilot to push over and maintain a level altitude. The X-15 was flown over a period of nearly 10 years -- June 1959 to Oct. 1968 -- and set the world's unofficial speed and altitude records of 4,520 mph (Mach 6.7) and 354,200 ft in a program to investigate all aspects of manned hypersonic flight. Information gained from the highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo manned spaceflight programs, and also the Space Shuttle program. The X-15s made a total of 199 flights, and were manufactured by North American Aviation. X-15-1, serial number 56-6670, is now located at the National Air and Space Museum, Washington DC. North American X-15A-2, serial number 56-6671, is at the United States Air Force Museum, Wright-Patterson AFB, Ohio. The X-15-3, serial number 56-6672, crashed on 15 Novemebr 1967, resulting in the death of Maj. Michael J. Adams.

X-15 #3 with test pilot Milt Thompson

NASA Technical Reports Server (NTRS)

1964-01-01

NASA research pilot Milt Thompson stands next to the X-15 #3 ship after a research flight. Milton 0. Thompson was a research pilot, Chief Engineer and Director of Research Projects during a long career at the NASA Dryden Flight Research Center. Thompson was hired as an engineer at the Flight Research Facility on March 19, 1956, when it was still under the auspices of NACA. He became a research pilot on May 25, 1958. Thompson was one of the 12 NASA, Air Force, and Navy pilots to fly the X-15 rocket-powered research aircraft between 1959 and 1968. He began flying X-15s on October 29, 1963. He flew the aircraft 14 times during the following two years, reaching a maximum speed of 3723 mph (Mach 5.42) and a peak altitude of 214,100 feet on separate flights. Thompson concluded his active flying career in 1968, becoming Director of Research Projects. In 1975 he was appointed Chief Engineer and retained the position until his death on August 8, 1993. The X-15 was a rocket-powered aircraft 50 ft long with a wingspan of 22 ft. It was a missile-shaped vehicle with an unusual wedge-shaped vertical tail, thin stubby wings, andunique side fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was capable of developing 57,000 lb of thrust. North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow-on program used the aircraft as a testbed to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudders on the vertical stabilizers to control yaw and movable horizontal stabilizers to control pitch when moving in synchronization or roll when moved differentially. For flight in the thin air outside of the appreciable Earth's atmosphere, the X-15 used a ballistic control system. Hydrogen peroxide thrust rockets located on the nose of the aircraft provided pitch and yaw control. Those on the wings provided roll control. Because of the large fuel consumption, the X-15 was air launched from a B-52 aircraft at 45,000 ft and a speed of about 500 mph. Depending on the mission, the rocket engine provided thrust for the first 80 to 120 sec of flight. The remainder of the normal 10 to 11 min. flight was powerless and ended with a 200-mph glide landing. Generally, one of two types of X-15 flight profiles was used; a high-altitude flight plan that called for the pilot to maintain a steep rate of climb, or a speed profile that called for the pilot to push over and maintain a level altitude. The X-15 was flown over a period of nearly 10 years -- June 1959 to Oct. 1968 -- and set the world's unofficial speed and altitude records of 4,520 mph (Mach 6.7) and 354,200 ft in a program to investigate all aspects of manned hypersonic flight. Information gained from the highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo manned spaceflight programs, and also the Space Shuttle program. The X-15s made a total of 199 flights, and were manufactured by North American Aviation. X-15-1, serial number 56-6670, is now located at the National Air and Space Museum, Washington DC. North American X-15A-2, serial number 56-6671, is at the United States Air Force Museum, Wright-Patterson AFB, Ohio. X-15-3, serial number 56-6672, crashed on 15 November 1967, resulting in the death of Maj. Michael J. Adams.

2D and 3D Modeling Efforts in Fuel Film Cooling of Liquid Rocket Engines (Conference Paper with Briefing Charts)

DTIC Science & Technology

2017-01-12

J =0.13%, FFC Varies (b) J =0.13%, Main chamber Varies ( c ) J ...b) J =0.13%, Main Varies ( c ) J =1.23%, FFC Varies (d) J =1.18%, Main Varies (e) J =7.89%, FFC Varies (f) J =7.34%, Main Varies Figure 8. Power Spectral...Statement A: Approved for Public Release; Distribution Unlimited. PA Clearance #16569 (a) J =0.13%, FFC Varies (b) J =0.13%, Main Varies ( c ) J =2.79%,

Observation of Slow Relaxation and Single-Molecule Toroidal Behavior in a Family of Butterfly-Shaped Ln4 Complexes.

PubMed

Biswas, Sourav; Das, Sourav; Gupta, Tulika; Singh, Saurabh Kumar; Pissas, Michael; Rajaraman, Gopalan; Chandrasekhar, Vadapalli

2016-12-19

A family of five isostructural butterfly complexes with a tetranuclear [Ln 4 ] core of the general formula [Ln 4 (LH) 2 (μ 2 -η 1 η 1 Piv)(η 2 -Piv)(μ 3 -OH) 2 ]⋅x H 2 O⋅y MeOH⋅z CHCl 3 (1: Ln=Dy III , x=2, y=2, z=0; 2: Ln=Tb III , x=0, y=0, z=6; 3: Ln=Er III , x=2, y=2, z=0; 4: Ln=Ho III , x=2, y=2, z=0; 5: Ln=Yb III , x=2, y=2, z=0; LH 4 =6-{[bis(2-hydroxyethyl)amino]methyl}-N'-(2-hydroxy-3-methoxybenzylidene)picolinohydrazide; PivH=pivalic acid) was isolated and characterized both structurally and magnetically. Complexes 1-5 were probed by direct and alternating current (dc and ac) magnetic susceptibility measurements and, except for 1, they did not display single-molecule magnetism (SMM) behavior. The ac magnetic susceptibility measurements show frequency-dependent out-of-phase signals with one relaxation process for complex 1 and the estimated effective energy barrier for the relaxation process was found to be 49 K. We have carried out extensive ab initio (CASSCF+RASSI-SO+SINGLE_ANISO+POLY_ANISO) calculations on all the five complexes to gain deeper insights into the nature of magnetic anisotropy and the presence and absence of slow relaxation in these complexes. Our calculations yield three different exchange coupling for these Ln 4 complexes and all the extracted J values are found to be weakly ferro/antiferromagentic in nature (J 1 =+2.35, J 2 =-0.58, and J 3 =-0.29 cm -1 for 1; J 1 =+0.45, J 2 =-0.68, and J 3 =-0.29 cm -1 for 2; J 1 =+0.03, J 2 =-0.98, and J 3 =-0.19 cm -1 for 3; J 1 =+4.15, J 2 =-0.23, and J 3 =-0.54 cm -1 for 4 and J 1 =+0.15, J 2 =-0.28, and J 3 =-1.18 cm -1 for 5). Our calculations reveal the presence of very large mixed toroidal moment in complex 1 and this is essentially due to the specific exchange topology present in this cluster. Our calculations also suggest presence of single-molecule toroics (SMTs) in complex 2. For complexes 3-5 on the other hand, the transverse anisotropy was computed to be large, leading to the absence of slow relaxation of magnetization. As the magnetic field produced by SMTs decays faster than the normal spin moments, the concept of SMTs can be exploited to build qubits in which less interference and dense packing are possible. Our systematic study on these series of Ln 4 complexes suggest how the ligand design can help to bring forth such SMT characteristics in lanthanide complexes. © 2016 Wiley-VCH Verlag GmbH & Co. KGaA, Weinheim.

Observation of K*(892){sup 0}K*(892){sup 0} in {chi}{sub cJ} decays

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

Ablikim, M.; Bai, J.Z.; Bian, J.G.

2004-11-01

K*(892){sup 0}K*(892){sup 0} signals from {chi}{sub cJ}(J=0,1,2) decays are observed for the first time using a data sample of 14 million {psi}(2S) events accumulated in the BES II detector. The branching fractions B[{chi}{sub cJ}{yields}K*(892){sup 0}K*(892){sup 0}] (J=0,1,2) are determined to be (1.78{+-}0.34{+-}0.34)x10{sup -3} (1.67{+-}0.32{+-}0.31)x10{sup -3}, and (4.86{+-}0.56{+-}0.88)x10{sup -3} for the {chi}{sub c0}, {chi}{sub c1}, and {chi}{sub c2} decays, respectively, where the first errors are statistical and the second are systematic. The significances of these signals are about 4.7{sigma}, 4.5{sigma}, and 7.6{sigma}, respectively.

The International Reference Ionosphere: Model Update 2016

NASA Astrophysics Data System (ADS)

Bilitza, Dieter; Altadill, David; Reinisch, Bodo; Galkin, Ivan; Shubin, Valentin; Truhlik, Vladimir

2016-04-01

The International Reference Ionosphere (IRI) is recognized as the official standard for the ionosphere (COSPAR, URSI, ISO) and is widely used for a multitude of different applications as evidenced by the many papers in science and engineering journals that acknowledge the use of IRI (e.g., about 11% of all Radio Science papers each year). One of the shortcomings of the model has been the dependence of the F2 peak height modeling on the propagation factor M(3000)F2. With the 2016 version of IRI, two new models will be introduced for hmF2 that were developed directly based on hmF2 measurements by ionosondes [Altadill et al., 2013] and by COSMIC radio occultation [Shubin, 2015], respectively. In addition IRI-2016 will include an improved representation of the ionosphere during the very low solar activities that were reached during the last solar minimum in 2008/2009. This presentation will review these and other improvements that are being implemented with the 2016 version of the IRI model. We will also discuss recent IRI workshops and their findings and results. One of the most exciting new projects is the development of the Real-Time IRI [Galkin et al., 2012]. We will discuss the current status and plans for the future. Altadill, D., S. Magdaleno, J.M. Torta, E. Blanch (2013), Global empirical models of the density peak height and of the equivalent scale height for quiet conditions, Advances in Space Research 52, 1756-1769, doi:10.1016/j.asr.2012.11.018. Galkin, I.A., B.W. Reinisch, X. Huang, and D. Bilitza (2012), Assimilation of GIRO Data into a Real-Time IRI, Radio Science, 47, RS0L07, doi:10.1029/2011RS004952. Shubin V.N. (2015), Global median model of the F2-layer peak height based on ionospheric radio-occultation and ground-based Digisonde observations, Advances in Space Research 56, 916-928, doi:10.1016/j.asr.2015.05.029.

Sea level side loads in high-area-ratio rocket engines

NASA Technical Reports Server (NTRS)

Nave, L. H.; Coffey, G. A.

1973-01-01

An empirical separation and side load model to obtain applied aerodynamic loads has been developed based on data obtained from full-scale J-2S (265K-pound-thrust engine with an area ratio of 40:1) engine and model testing. Experimental data include visual observations of the separation patterns that show the dynamic nature of the separation phenomenon. Comparisons between measured and applied side loads are made. Correlations relating the separation location to the applied side loads and the methods used to determine the separation location are given.

X-ray Emission from the Millisecond Pulsar J1012+5307

NASA Astrophysics Data System (ADS)

Halpern, J. P.; Wang, F. Y.-H.

1997-12-01

The recently discovered 5.3 ms pulsar J1012+5307 at a distance of 520 pc is in an area of the sky which is particularly deficient in absorbing gas. The column density along the line of sight is less than 7.5 x 10(19) cm(-2) , which facilitates soft X-ray observations. Halpern (1996, ApJ, 459, L9) reported a possible ROSAT PSPC detection of the pulsar in a serendipitous, off-axis observation. We have now confirmed the X-ray emission of PSR J1012+5307 in a 23 ksec observation with the ROSAT HRI. A point source is detected within 3('') of the radio position. Its count rate of 1.6 +/- 0.3 x 10(-3) s(-1) corresponds to an unbsorbed 0.1--2.4 keV flux of 6.4 x 10(-14) ergs cm(-2) s(-1) , similar to that reported previously. This counts-to-flux conversion is valid for N_H = 5 x 10(19) cm(-2) , and either a power-law spectrum of photon index 2.5 or a blackbody of kT = 0.1 keV. The implied X-ray luminosity of 2.0 x 10(30) ergs s(-1) is 5 x 10(-4) of the pulsar's spin-down power dot E, and similar to that of the nearest millisecond pulsar J0437--4715, which is nearly a twin of J1012+5307 in P and dot E. We subjected the 37 photons (and 13 background counts) within the source region to a pulsar search, but no evidence for pulsation was found. The pulsar apparently emits over a large fraction of its rotation cycle, and the absence of sharp modulation can be taken as evidence for surface thermal emission, as is favored for PSR J0437--4715 (Zavlin & Pavlov 1997, A&A, in press), rather than magnetospheric X-ray emission which is apparent in the sharp pulses of the much more energetic millisecond pulsar B1821--24 (Saito et al. 1997, ApJ, 477, L37). A further test of this interpretation will be made with a longer ROSAT observation, which will increase the number of photons collected by a factor of 5, and permit a more sensitive examination of the light curve for modulation due to emission from heated polar caps. If found, such modulation will be further evidence that surface reheating by the impact of particles accelerated along open field lines operates in these ~ 10(9) yr old pulsars.

X-15A-2 with full scale ablative coating (pink X-15) on NASA ramp

NASA Technical Reports Server (NTRS)

1967-01-01

In June 1967, the X-15A-2 rocket powered research aircraft received a full-scale ablative coating to protect the craft from the high temperatures associated with supersonic flight. This pink eraser-like substance, applied to the #2 aircraft (56-6671), was then covered with a white sealant coat before flight. This coating would help the #2 aircraft reach the record speed of 4,520 mph (Mach 6.7). The X-15 was a rocket-powered aircraft 50 ft long with a wingspan of 22 ft. However, the X-15A-2 had been elongated to 52 ft 5 in. Like the other two X-15s, it was a missile-shaped vehicle with an unusual wedge-shaped vertical tail, thin stubby wings, and unique side fairings that extended along the side of the fuselage. The X-15 weighed about14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was capable of developing 57,000 lb of thrust. North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow on program used the aircraft as a testbed to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudder surfaces on the vertical stabilizers to control yaw and movable horizontal stabilizers to control pitch when moving in synchronization or roll when moved differentially. For flight in the thin air outside of the appreciable Earth's atmosphere, the X-15 used a reaction control system. Hydrogen peroxide thrust rockets located on the nose of the aircraft provided pitch and yaw control. Those on the wings provided roll control. Because of the large fuel consumption, the X-15 was air launched from a B-52 aircraft at 45,000 ft and a speed of about 500 mph. Depending on the mission, the rocket engine provided thrust for the first 80 to 120 sec of flight. The remainder of the normal 10 to 11 min. flight was powerless and ended with a 200-mph glide landing. Generally, one of two types of X-15 flight profiles was used; a high-altitude flight plan that called for the pilot to maintain a steep rate of climb, or a speed profile that called for the pilot to push over and maintain a level altitude. The X-15 was flown over a period of nearly 10 years -- June 1959 to Oct. 1968 -- and set the world's unofficial speed and altitude records of 4,520 mph (Mach 6.7) and 354,200 ft in a program to investigate all aspects of piloted hypersonic flight. Information gained fromthe highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo piloted spaceflight programs, and also the Space Shuttle program. The X-15s made a total of 199 flights, and were manufactured by North American Aviation. X-15-1, serial number 56-6670, is now located at the National Air and Space Museum, Washington DC. North American X-15A-2, serial number 56-6671, is at the United States Air Force Museum, Wright-Patterson AFB, Ohio. X-15-3, serial number 56-6672, crashed on 15 November 1967, resulting in the death of Maj. Michael J Adams.

Kenneth J. Szalai

NASA Technical Reports Server (NTRS)

1997-01-01

Kenneth J. Szalai was Director of the NASA Hugh L. Dryden Flight Research Center, Edwards, Calif., from January 1994 through July 1998. He retired from NASA at the end of July to join IBP Aerospace Group, Inc., as the company's new president and chief operating officer. As NASA's primary installation for flight research for more than half a century, Dryden is chartered to conceive and conduct experimental flight research for integrated flight and propulsion controls; advanced optical sensors and controls; viscous drag reduction; advanced configurations; high-altitude, long-endurance aircraft; remotely piloted vehicle technology; hypersonic vehicle experiments; high-speed research for civil transportation; atmospheric tests of advanced rocket and airbreathing propulsion concepts; instrumentation systems; and flight loads predictions. In carrying out this mission, Dryden operates some of the most advanced research aircraft in the nation. When Dryden was administratively a part of the NASA Ames Research Center, Moffett Field, Calif., Szalai was director and also held the position of Ames Deputy Director for Dryden from December 1990 until assuming his current position From 1982 until December 1990, Szalai directed the Dryden Research Engineering Division. He served as Associate Director of the Ames Research Center in 1989. Prior to 1982 he was chief of the Research Engineering Division's Dynamics and Control Branch, and chief of the Flight Control Section. Szalai began his NASA career at Dryden in 1964 following graduation from the University of Wisconsin, where he attended both the Milwaukee and Madison campuses. His bachelor of science degree is in electrical engineering. He also received a master of science degree in mechanical engineering from the University of Southern California in 1970. Szalai was principal investigator on the F-8 Digital Fly-By-Wire program, which successfully flew the first aircraft equipped with a digital electronic flight control system without any mechanical reversion capability. Szalai also held research and systems engineering positions on several research aircraft programs investigating flying qualities, integrated flight controls, and fault tolerant-flight critical systems. He was also flight test engineer and principal investigator on the NASA Airborne Simulator before assuming management positions within the Research Engineering Division. Szalai has worked in various technical and management positions on such programs as the F-111 IPCS, AFTI/F-16, HiMAT, F-15 DEEC, F-15 HIDEC, X-29, X-31, F-16XL Laminar Flow, Space Shuttle Orbiter, Pathfinder Solar Powered Aircraft, SR-71 Sonic Boom, F-15 and MD-11 Propulsion Controlled Aircraft, X-33, and X-38. Szalai has authored over 25 papers and reports and has been a lecturer for the NATO Advisory Group for Aeronautical Research and Development (AGARD). He has served on various technical committees and subcommittees for the American Institute of Aeronautics and Astronautics (AIAA) and Society of Automotive Engineers (SAE). Szalai, a Fellow of the AIAA, also served on the National Academy of Science's 'Aeronautics-2000' study. Among the awards Szalai has received are NASA's Exceptional Service Medal, the NASA Outstanding Leadership Medal, and the Presidential Meritorious and Distinguished Rank awards. Szalai was born June 1, 1942, in Milwaukee, Wisc., where he graduated from West Division High School.

Evaluation of Microencapsulated Penetrant Inspection.

DTIC Science & Technology

1980-12-01

AD-A9b 826 GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE GROUP F/6 IA/2ADG EVALUATION OF MICROENCAPSULATED PENETRANT INSPECTION.(U) DEC 80 J M...4156 ADA096826 EVALUATION OF MICROENCAPSULATED PENETRANT INSPECTION i :I J.M. Portaz Aircraft Engine Group General Electric Company Cincinnati, Ohio... Microencapsulated Penetrant 5 7riJF-Iehica17 = Inspection p un May@84 -1 ---- --- ---- 19AMFGK657j7 7. AiJTHOR(s) nVCWRACT OR GRANT m 𔃻 " JO J.M./Portaz

Contact Selectivity Engineering in a 2 μm Thick Ultrathin c-Si Solar Cell Using Transition-Metal Oxides Achieving an Efficiency of 10.8.

PubMed

Xue, Muyu; Islam, Raisul; Meng, Andrew C; Lyu, Zheng; Lu, Ching-Ying; Tae, Christian; Braun, Michael R; Zang, Kai; McIntyre, Paul C; Kamins, Theodore I; Saraswat, Krishna C; Harris, James S

2017-12-06

In this paper, the integration of metal oxides as carrier-selective contacts for ultrathin crystalline silicon (c-Si) solar cells is demonstrated which results in an ∼13% relative improvement in efficiency. The improvement in efficiency originates from the suppression of the contact recombination current due to the band offset asymmetry of these oxides with Si. First, an ultrathin c-Si solar cell having a total thickness of 2 μm is shown to have >10% efficiency without any light-trapping scheme. This is achieved by the integration of nickel oxide (NiO x ) as a hole-selective contact interlayer material, which has a low valence band offset and high conduction band offset with Si. Second, we show a champion cell efficiency of 10.8% with the additional integration of titanium oxide (TiO x ), a well-known material for an electron-selective contact interlayer. Key parameters including V oc and J sc also show different degrees of enhancement if single (NiO x only) or double (both NiO x and TiO x ) carrier-selective contacts are integrated. The fabrication process for TiO x and NiO x layer integration is scalable and shows good compatibility with the device.

Determining immune components necessary for progression of pigment dispersing disease to glaucoma in DBA/2J mice

PubMed Central

2014-01-01

Background The molecular mechanisms causing pigment dispersion syndrome (PDS) and the pathway(s) by which it progresses to pigmentary glaucoma are not known. Mutations in two melanosomal protein genes (Tyrp1 b and Gpnmb R150X ) are responsible for pigment dispersing iris disease, which progresses to intraocular pressure (IOP) elevation and subsequent glaucoma in DBA/2J mice. Melanosomal defects along with ocular immune abnormalities play a role in the propagation of pigment dispersion and progression to IOP elevation. Here, we tested the role of specific immune components in the progression of the iris disease and high IOP. Results We tested the role of NK cells in disease etiology by genetically modifying the B6.D2-Gpnmb R150X Tyrp1 b strain, which develops the same iris disease as DBA/2J mice. Our findings demonstrate that neither diminishing NK mediated cytotoxic activity (Prf1 mutation) nor NK cell depletion (Il2rg mutation) has any influence on the severity or timing of Gpnmb R150X Tyrp1 b mediated iris disease. Since DBA/2J mice are deficient in CD94, an important immune modulator that often acts as an immune suppressor, we generated DBA/2J mice sufficient in CD94. Sufficiency of CD94 failed to alter either the iris disease or the subsequent IOP elevation. Additionally CD94 status had no detected effect on glaucomatous optic nerve damage. Conclusion Our previous data implicate immune components in the manifestation of pigment dispersion and/or IOP elevation in DBA/2J mice. The current study eliminates important immune components, specifically NK cells and CD94 deficiency, as critical in the progression of iris disease and glaucoma. This narrows the field of possible immune components responsible for disease progression. PMID:24678736

VizieR Online Data Catalog: σ Orionis cluster stellar population (Hernandez+, 2014)

NASA Astrophysics Data System (ADS)

Hernandez, J.; Calvet, N.; Perez, A.; Briceno, C.; Olguin, L.; Contreras, M. E.; Hartmann, L.; Allen, L.; Espaillat, C.; Hernan, R.

2017-04-01

We obtained optical photometry (UBVRCIC) of the center on 2011 December 24 using the Ohio State Multi-Object Spectrograph (OSMOS) on the MDM 2.4 m Hiltner telescope (Stoll et al. 2010SPIE.7735E..4LS; Martini et al. 2011PASP..123..187M). We obtained two sets of images, one short exposure set (20, 15, 10, 5, and 5 s for U, B, V, RC and IC, respectively) and one long exposures set (3x200, 3x200, 3x150, 3x100, and 3x100 s for U, B, V, RC, and IC, respectively). The initial sample in this study includes all Two Micron All Sky Survey (2MASS) sources (4659 sources; Cutri et al. 2003yCat.2246....0C) in a region of 48'x48' centered at RA=84.7° and DE=-2.6°. This region covers the field studied in H07b (Hernandez et al. 2007, J/ApJ/662/1067) using the four channels of the InfraRed Array Camera (IRAC; Fazio et al. 2004ApJS..154...39F). The 2MASS catalog (Cutri et al. 2003yCat.2246....0C, Cat.II/246) is complete down to J<15.8, which includes stars beyond the substellar limit expected for the σ Orionis cluster (e.g., J~14.6; Hernandez et al. 2007, J/ApJ/662/1067). (8 data files).

Thermochemistry and gas-phase ion energetics of 2-hydroxy-4-methoxy-benzophenone (oxybenzone).

PubMed

Lago, A F; Jimenez, P; Herrero, R; Dávalos, J Z; Abboud, J-L M

2008-04-10

We have investigated the thermochemistry and ion energetics of the oxybenzone (2-hydroxy-4-methoxy-benzophenone, C14H12O3, 1H) molecule. The following parameters have been determined for this species: gas-phase enthalpy for the of neutral molecule at 298.15K, (Delta(f)H0(m)(g) = -303.5 +/- 5.1 kJ x mol-1), the intrinsic (gas-phase) acidity (GA(1H) = 1402.1 +/- 8.4 kJ x mol-1), enthalpy of formation for the oxybenzone anion (Delta(f)H0(m)(1-,g) = -402.3 +/- 9.8 kJ x mol-1). We also have obtained the enthalpy of formation of, 4-hydroxy-4'-methoxybenzophenone (Delta(f)H0(m)(g) = -275.4 +/- 10 kJ x mol-1) and 3-methoxyphenol anion (Delta(f)H0(m)(C7H7O2-,g) = -317.7 +/- 8.7 kJ x mol-1). A reliable experimental estimation of enthalpy related to intramolecular hydrogen bonding in oxybenzone has also been obtained (30.1 +/- 6.3 kJ x mol-1) and compared with our theoretical calculations at the B3LYP/6-311++G** level of theory, by means of an isodesmic reaction scheme. In addition, heat capacities, temperature, and enthalpy of fusion have been determined for this molecule by differential scanning calorimetry.

Measurements of ψ(2S) and X(3872) → J/ψπ + π - production in pp collisions at $$ \\sqrt{s}=8 $$ TeV with the ATLAS detector

DOE PAGES

Aaboud, M.; Aad, G.; Abbott, B.; ...

2017-01-01

Differential cross sections are presented for the prompt and non-prompt production of the hidden-charm states X(3872) and ψ(2S), in the decay mode J/ψπ+π-, measured using 11.4 fb-1 of pp collisions at \\sqrt{s}=8 TeV by the ATLAS detector at the LHC. The ratio of cross-sections X(3872)/ψ(2S) is also given, separately for prompt and non-prompt components, as well as the non-prompt fractions of X(3872) and ψ(2S). Assuming independent single effective lifetimes for non-prompt X(3872) and ψ(2S) production gives {R}_B=\\frac{\\mathrm{\\mathcal{B}}\\left(B\\to X(3872)+\\mathrm{any}\\right)\\mathrm{\\mathcal{B}}\\left(X(3872)\\to J/\\psi {\\pi}^{+}{\\pi}^{-}\\right)}{\\mathrm{\\mathcal{B}}\\left(B\\to \\psi (2S)+\\mathrm{any}\\right)\\mathrm{\\mathcal{B}}\\left(\\psi (2S)\\to J/\\psi {\\pi}^{+}{\\pi}^{-}\\right)}=\\left(3.95\\pm 0.32\\left(\\mathrm{s}\\mathrm{tat}\\right)\\pm 0.08\\left(\\mathrm{s}\\mathrm{y}\\mathrm{s}\\right)\\right)\\times {10}^{-2} separating short- and long-lived contributions, assuming that the short-lived component is duemore » to Bc decays, gives RB = (3.57 ± 0.33(stat) ± 0.11(sys)) × 10-2, with the fraction of non-prompt X(3872) produced via Bc decays for pT(X(3872)) > 10 GeV being (25 ± 13(stat) ± 2(sys) ± 5(spin))%. The distributions of the dipion invariant mass in the X(3872) and ψ(2S) decays are also measured and compared to theoretical predictions.« less

Precocious Supermassive Black Holes Challenge Theories

NASA Astrophysics Data System (ADS)

2004-11-01

NASA's Chandra X-ray Observatory has obtained definitive evidence that a distant quasar formed less than a billion years after the Big Bang contains a fully-grown supermassive black hole generating energy at the rate of twenty trillion Suns. The existence of such massive black holes at this early epoch of the Universe challenges theories of the formation of galaxies and supermassive black holes. Astronomers Daniel Schwartz and Shanil Virani of the Harvard-Smithsonian Center for Astrophysics in Cambridge, MA observed the quasar, known as SDSSp J1306, which is 12.7 billion light years away. Since the Universe is estimated to be 13.7 billion years old, we see the quasar as it was a billion years after the Big Bang. They found that the distribution of X-rays with energy, or X-ray spectrum, is indistinguishable from that of nearby, older quasars. Likewise, the relative brightness at optical and X-ray wavelengths of SDSSp J1306 was similar to that of the nearby group of quasars. Optical observations suggest that the mass of the black hole is about a billion solar masses. Illustration of Quasar SDSSp J1306 Illustration of Quasar SDSSp J1306 Evidence of another early-epoch supermassive black hole was published previously by a team of scientists from the California Institute of Technology and the United Kingdom using the XMM-Newton X-ray satellite. They observed the quasar SDSSp J1030 at a distance of 12.8 billion light years and found essentially the same result for the X-ray spectrum as the Smithsonian scientists found for SDSSp J1306. Chandra's precise location and spectrum for SDSSp J1306 with nearly the same properties eliminate any lingering uncertainty that precocious supermassive black holes exist. "These two results seem to indicate that the way supermassive black holes produce X-rays has remained essentially the same from a very early date in the Universe," said Schwartz. "This implies that the central black hole engine in a massive galaxy was formed very soon after the Big Bang." There is general agreement among astronomers that X-radiation from the vicinity of supermassive black holes is produced as gas is pulled toward a black hole, and heated to temperatures ranging from millions to billions of degrees. Most of the infalling gas is concentrated in a rapidly rotating disk, the inner part of which has a hot atmosphere or corona where temperatures can climb to billions of degrees. Although the precise geometry and details of the X-ray production are not known, observations of numerous quasars, or supermassive black holes, have shown that many of them have very similar X-ray spectra, especially at high X-ray energies. This suggests that the basic geometry and mechanism are the same for these objects. Chandra X-ray Image of SDSSp J1306 Chandra X-ray Image of SDSSp J1306 The remarkable similarity of the X-ray spectra of the young supermassive black holes to those of much older ones means that the supermassive black holes and their accretion disks, were already in place less than a billion years after the Big Bang. One possibility is that millions of 100 solar mass black holes formed from the collapse of massive stars in the young galaxy, and subsequently built up a billion-solar mass black hole in the center of the galaxy through mergers and accretion of gas. To answer the question of how and when supermassive black holes were formed, astronomers plan to use the very deep Chandra exposures and other surveys to identify and study quasars at even earlier ages. The paper by Schwartz and Virani on SDSSp J1306 was published in the November 1, 2004 issue of The Astrophysical Journal. The paper by Duncan Farrah and colleagues on SDSS J1030 was published in the August 10, 2004 issue of The Astrophysical Journal. Chandra observed J1306 with its Advanced CCD Imaging Spectrometer (ACIS) instrument for approximately 33 hours in November 2003. NASA's Marshall Space Flight Center, Huntsville, Ala., manages the Chandra program for NASA's Office of Space Science, Washington. Northrop Grumman of Redondo Beach, Calif., formerly TRW, Inc., was the prime development contractor for the observatory. The Smithsonian Astrophysical Observatory controls science and flight operations from the Chandra X-ray Center in Cambridge, Mass. Additional information and images are available at: http://chandra.harvard.edu and http://chandra.nasa.gov

Space Debris Mitigation CONOPS Development

DTIC Science & Technology

2013-06-01

SPACE DEBRIS MITIGATION CONOPS DEVELOPMENT THESIS Earl B. Alejandro, Capt, USAF AFIT-ENV-13-J...04DL SPACE DEBRIS MITIGATION CONOPS DEVELOPMENT THESIS Presented to the Faculty Department of Systems Engineering and Management...June 2013 DISTRIBUTION STATEMENT A APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLIMITED AFIT-ENV-13-J-04DL SPACE DEBRIS

VizieR Online Data Catalog: HIP and TGAS stars reddening and extinction (Gontcharov+ 2018)

NASA Astrophysics Data System (ADS)

Gontcharov, G. A.; Mosenkov, A. V.

2018-01-01

These are the reddening, interstellar extinction and extinction-to-reddening ratio estimates interpolated for 730,496 Gaia DR1 TGAS and Hipparcos stars within 415 pc from the Sun based on the 3D reddening map of Gontcharov (J/PAZh/43/521) and 3D extinction-to-reddening (total-to-selective extinction) ratio Rv=Av/E(B-V) map of Gontcharov (J/PAZh/38/15). For 711,237 Gaia DR1 TGAS stars the rMoMW distances from Astraatmadja and Bailer-Jones (2016ApJ...833..119A, Cat. J/ApJ/833/119) are used. For 19,259 Hipparcos stars, not in Gaia DR1 TGAS, the distances as the inversion of Hipparcos (I/311) parallaxes are used. The E(B-V) are calculated from initial E(J-Ks) as E(B-V)=E(J-Ks)*(0.047X3-0.1X2-0.09X+1.74), where X=(BT-VT) (B_T and V_T Tycho-2 bands) following the extinction law. This refined relation supersedes E(B-V)=1.655E(J-Ks) in the original 3D reddening map of Gontcharov. The Rv are interpolated from the 3D map of Rv of Gontcharov (2012AstL...38...12G, 2012PAZh...38...15G, Cat. J/PAZh/38/15). The Av are the product of E(B-V) and Rv. (2 data files).

Ocean Engineering Studies. Volume 1. Acrylic Submersibles

DTIC Science & Technology

1990-04-01

2.3 ASTM-DIO03-61 Heat distortion temperature +3.60F/minute at 264 psi 200OF: ASTM-0648-56 +3.60F/minute at 66 psi 220OF ASTM-0648-56 Thermal...of Revolution with Axisymmetric Pressures, Temperatures, and Distributed Loads", WAPD -TM-398, December 1963. 4. Stachiw, J. D., Mack, K. L., "The...at 264 psi 200°F +3.6°F/min at 66 psi 220°F Thermal expansion/°F at 20°F 35 x 10-6 Fed. Stan. 406 Method 2031 Water absorpt,.on; 1/8 inch ASTM-D570

Amorphous/crystalline (A/C) thermodynamic "rules of thumb": estimating standard thermodynamic data for amorphous materials using standard data for their crystalline counterparts.

PubMed

Holland, Diane; Jenkins, H Donald Brooke

2012-05-07

Standard thermochemical data (in the form of Δ(f)H° and Δ(f)G°) are available for crystalline (c) materials but rarely for their corresponding amorphous (a) counterparts. This paper establishes correlations between the sets of data for the two material forms (where known), which can then be used as a guideline for estimation of missing data. Accordingly, Δ(f)H°(a)/kJ mol(-1) ≈ 0.993Δ(f)H°(c)/kJ mol(-1) + 12.52 (R(2) = 0.9999; n = 50) and Δ(f)G°/kJ mol(-1) ≈ 0.988Δ(f)H°(c)/kJ mol(-1) + 0.70 (R(2) = 0.9999; n = 10). Much more tentatively, we propose that S°(298)(c)/J K(-1) mol(-1) ≈ 1.084S°(298)(c)/J K(-1) mol(-1) + 6.54 (R(2) = 0.9873; n = 11). An amorphous hydrate enthalpic version of the Difference Rule is also proposed (and tested) in the form [Δ(f)H°(M(p)X(q)·nH(2)O,a) - Δ(f)H°(M(p)X(q),a)]/kJ mol(-1) ≈ Θ(Hf)n ≈ -302.0n, where M(p)X(q)·nH(2)O represents an amorphous hydrate and M(p)X(q) the corresponding amorphous anhydrous parent salt.

Measurement of J/psi production in continuum e(+)e(-) annihilations near square root of s = 10.6 GeV.

PubMed

Aubert, B; Boutigny, D; Gaillard, J M; Hicheur, A; Karyotakis, Y; Lees, J P; Robbe, P; Tisserand, V; Palano, A; Chen, G P; Chen, J C; Qi, N D; Rong, G; Wang, P; Zhu, Y S; Eigen, G; Reinertsen, P L; Stugu, B; Abbott, B; Abrams, G S; Borgland, A W; Breon, A B; Brown, D N; Button-Shafer, J; Cahn, R N; Clark, A R; Fan, Q; Gill, M S; Gritsan, A; Groysman, Y; Jacobsen, R G; Kadel, R W; Kadyk, J; Kerth, L T; Kluth, S; Kolomensky, Y G; Kral, J F; LeClerc, C; Levi, M E; Liu, T; Lynch, G; Meyer, A B; Momayezi, M; Oddone, P J; Perazzo, A; Pripstein, M; Roe, N A; Romosan, A; Ronan, M T; Shelkov, V G; Telnov, A V; Wenzel, W A; Bright-Thomas, P G; Harrison, T J; Hawkes, C M; Kirk, A; Knowles, D J; O'Neale, S W; Penny, R C; Watson, A T; Watson, N K; Deppermann, T; Goetzen, K; Koch, H; Krug, J; Kunze, M; Lewandowski, B; Peters, K; Schmuecker, H; Steinke, M; Andress, J C; Barlow, N R; Bhimji, W; Chevalier, N; Clark, P J; Cottingham, W N; De Groot, N; Dyce, N; Foster, B; Mass, A; McFall, J D; Wallom, D; Wilson, F F; Abe, K; Hearty, C; Mattison, T S; McKenna, J A; Thiessen, D; Camanzi, B; Jolly, S; McKemey, A K; Tinslay, J; Blinov, V E; Bukin, A D; Bukin, D A; Buzykaev, A R; Dubrovin, M S; Golubev, V B; Ivanchenko, V N; Korol, A A; Kravchenko, E A; Onuchin, A P; Salnikov, A A; Serednyakov, S I; Skovpen, Y I; Telnov, V I; Yushkov, A N; Best, D; Lankford, A J; Mandelkern, M; McMahon, S; Stoker, D P; Ahsan, A; Arisaka, K; Buchanan, C; Chun, S; Branson, J G; MacFarlane, D B; Prell, S; Rahatlou, S; Raven, G; Sharma, V; Campagnari, C; Dahmes, B; Hart, P A; Kuznetsova, N; Levy, S L; Long, O; Lu, A; Richman, J D; Verkerke, W; Witherell, M; Yellin, S; Beringer, J; Dorfan, D E; Eisner, A M; Frey, A; Grillo, A A; Grothe, M; Heusch, C A; Johnson, R P; Kroeger, W; Lockman, W S; Pulliam, T; Sadrozinski, H; Schalk, T; Schmitz, R E; Schumm, B A; Seiden, A; Turri, M; Walkowiak, W; Williams, D C; Wilson, M G; Chen, E; Dubois-Felsmann, G P; Dvoretskii, A; Hitlin, D G; Metzler, S; Oyang, J; Porter, F C; Ryd, A; Samuel, A; Weaver, M; Yang, S; Zhu, R Y; Devmal, S; Geld, T L; Jayatilleke, S; Mancinelli, G; Meadows, B T; Sokoloff, M D; Bloom, P; Dima, M O; Fahey, S; Ford, W T; Gaede, F; Johnson, D R; Michael, A K; Nauenberg, U; Olivas, A; Park, H; Rankin, P; Roy, J; Sen, S; Smith, J G; van Hoek, W C; Wagner, D L; Blouw, J; Harton, J L; Krishnamurthy, M; Soffer, A; Toki, W H; Wilson, R J; Zhang, J; Brandt, T; Brose, J; Colberg, T; Dahlinger, G; Dickopp, M; Dubitzky, R S; Maly, E; Müller-Pfefferkorn, R; Otto, S; Schubert, K R; Schwierz, R; Spaan, B; Wilden, L; Behr, L; Bernard, D; Bonneaud, G R; Brochard, F; Cohen-Tanugi, J; Ferrag, S; Roussot, E; T'Jampens, S; Thiebaux, C; Vasileiadis, G; Verderi, M; Anjomshoaa, A; Bernet, R; Khan, A; Muheim, F; Playfer, S; Swain, J E; Falbo, M; Borean, C; Bozzi, C; Dittongo, S; Folegani, M; Piemontese, L; Treadwell, E; Anulli, F; Baldini-Ferroli, R; Calcaterra, A; de Sangro, R; Falciai, D; Finocchiaro, G; Patteri, P; Peruzzi, I M; Piccolo, M; Xie, Y; Zallo, A; Bagnasco, S; Buzzo, A; Contri, R; Crosetti, G; Fabbricatore, P; Farinon, S; Lo Vetere, M; Macri, M; Monge, M R; Musenich, R; Pallavicini, M; Parodi, R; Passaggio, S; Pastore, F C; Patrignani, C; Pia, M G; Priano, C; Robutti, E; Santroni, A; Morii, M; Bartoldus, R; Dignan, T; Hamilton, R; Mallik, U; Cochran, J; Crawley, H B; Fischer, P A; Lamsa, J; Meyer, W T; Rosenberg, E I; Benkebil, M; Grosdidier, G; Hast, C; Höcker, A; Lacker, H M; Lepeltier, V; Lutz, A M; Plaszczynski, S; Schune, M H; Trincaz-Duvoid, S; Valassi, A; Wormser, G; Bionta, R M; Brigljević, V; Fackler, O; Fujino, D; Lange, D J; Mugge, M; Shi, X; van Bibber, K; Wenaus, T J; Wright, D M; Wuest, C R; Carroll, M; Fry, J R; Gabathuler, E; Gamet, R; George, M; Kay, M; Payne, D J; Sloane, R J; Touramanis, C; Aspinwall, M L; Bowerman, D A; Dauncey, P D; Egede, U; Eschrich, I; Gunawardane, N J; Martin, R; Nash, J A; Sanders, P; Smith, D; Azzopardi, D E; Back, J J; Dixon, P; Harrison, P F; Potter, R J; Shorthouse, H W; Strother, P; Vidal, P B; Williams, M I; Cowan, G; George, S; Green, M G; Kurup, A; Marker, C E; McGrath, P; McMahon, T R; Ricciardi, S; Salvatore, F; Scott, I; Vaitsas, G; Brown, D; Davis, C L; Allison, J; Barlow, R J; Boyd, J T; Forti, A C; Fullwood, J; Jackson, F; Lafferty, G D; Savvas, N; Simopoulos, E T; Weatherall, J H; Farbin, A; Jawahery, A; Lillard, V; Olsen, J; Roberts, D A; Schieck, J R; Blaylock, G; Dallapiccola, C; Flood, K T; Hertzbach, S S; Kofler, R; Lin, C S; Moore, T B; Staengle, H; Willocq, S; Wittlin, J; Brau, B; Cowan, R; Sciolla, G; Taylor, F; Yamamoto, R K; Britton, D I; Milek, M; Patel, P M; Trischuk, J; Lanni, F; Palombo, F; Bauer, J M; Booke, M; Cremaldi, L; Eschenburg, V; Kroeger, R; Reidy, J; Sanders, D A; Summers, D J; Martin, J P; Nief, J Y; Seitz, R; Taras, P; Zacek, V; Nicholson, H; Sutton, C S; Cartaro, C; Cavallo, N; De Nardo, G; Fabozzi, F; Gatto, C; Lista, L; Paolucci, P; Piccolo, D; Sciacca, C; LoSecco, J M; Alsmiller, J R; Gabriel, T A; Handler, T; Brau, J; Frey, R; Iwasaki, M; Sinev, N B; Strom, D; Colecchia, F; Dal Corso, F; Dorigo, A; Galeazzi, F; Margoni, M; Michelon, G; Morandin, M; Posocco, M; Rotondo, M; Simonetto, F; Stroili, R; Torassa, E; Voci, C; Benayoun, M; Briand, H; Chauveau, J; David, P; de la Vaissière, C; Del Buono, L; Hamon, O; Le Diberder, F; Leruste, P; Lory, J; Roos, L; Stark, J; Versillé, S; Manfredi, P F; Re, V; Speziali, V; Frank, E D; Gladney, L; Guo, Q H; Panetta, J H; Angelini, C; Batignani, G; Bettarini, S; Bondioli, M; Carpinelli, M; Forti, F; Giorgi, M A; Lusiani, A; Martinez-Vidal, F; Morganti, M; Neri, N; Paoloni, E; Rama, M; Rizzo, G; Sandrelli, F; Simi, G; Triggiani, G; Walsh, J; Haire, M; Judd, D; Paick, K; Turnbull, L; Wagoner, D E; Albert, J; Bula, C; Elmer, P; Lu, C; McDonald, K T; Miftakov, V; Schaffner, S F; Smith, A J; Tumanov, A; Varnes, E W; Cavoto, G; del Re, D; Faccini, R; Ferrarotto, F; Ferroni, F; Fratini, K; Lamanna, E; Leonardi, E; Mazzoni, M A; Morganti, S; Piredda, G; Safai Tehrani, F; Serra, M; Voena, C; Christ, S; Waldi, R; Adye, T; Franek, B; Geddes, N I; Gopal, G P; Xella, S M; Aleksan, R; De Domenico, G; Emery, S; Gaidot, A; Ganzhur, S F; Giraud, P F; Hamel de Monchenault, G; Kozanecki, W; Langer, M; London, G W; Mayer, B; Serfass, B; Vasseur, G; Yèche, C; Zito, M; Copty, N; Purohit, M V; Singh, H; Yumiceva, F X; Adam, I; Anthony, P L; Aston, D; Baird, K; Bloom, E; Boyarski, A M; Bulos, F; Calderini, G; Claus, R; Convery, M R; Coupal, D P; Coward, D H; Dorfan, J; Doser, M; Dunwoodie, W; Field, R C; Glanzman, T; Godfrey, G L; Gowdy, S J; Grosso, P; Himel, T; Huffer, M E; Innes, W R; Jessop, C P; Kelsey, M H; Kim, P; Kocian, M L; Langenegger, U; Leith, D W; Luitz, S; Luth, V; Lynch, H L; Manzin, G; Marsiske, H; Menke, S; Messner, R; Moffeit, K C; Mount, R; Muller, D R; O'Grady, C P; Perl, M; Petrak, S; Quinn, H; Ratcliff, B N; Robertson, S H; Rochester, L S; Roodman, A; Schietinger, T; Schindler, R H; Schwiening, J; Serbo, V V; Snyder, A; Soha, A; Spanier, S M; Stahl, A; Stelzer, J; Su, D; Sullivan, M K; Talby, M; Tanaka, H A; Trunov, A; Va'vra, J; Wagner, S R; Weinstein, A J; Wisniewski, W J; Wright, D H; Young, C C; Burchat, P R; Cheng, C H; Kirkby, D; Meyer, T I; Roat, C; Henderson, R; Bugg, W; Cohn, H; Hart, E; Weidemann, A W; Benninger, T; Izen, J M; Kitayama, I; Lou, X C; Turcotte, M; Bianchi, F; Bona, M; Di Girolamo, B; Gamba, D; Smol, A; Zanin, D; Lanceri, L; Pompili, A; Vaugin, G; Panvini, R S; Brown, C M; De Silva, A; Kowalewski, R; Roney, J M; Band, H R; Charles, E; Dasu, S; Di Lodovico, F; Eichenbaum, A M; Hu, H; Johnson, J R; Liu, R; Nielsen, J; Orejudos, W; Pan, Y; Prepost, R; Scott, I J; Sekula, S J; von Wimmersperg-Toeller, J H; Wu, S L; Yu, Z; Zobernig, H; Kordich, T M; Neal, H

2001-10-15

The production of J/psi mesons in continuum e(+)e(-) annihilations has been studied with the BABAR detector at energies near the Upsilon(4S) resonance. The mesons are distinguished from J/psi production in B decays through their center-of-mass momentum and energy. We measure the cross section e(+)e(-)-->J/psi X to be 2.52+/-0.21+/-0.21 pb. We set a 90% C.L. upper limit on the branching fraction for direct Upsilon(4S)-->J/psi X decays at 4.7 x 10(-4).

Discovery Of Nine Gamma-Ray Pulsars In Fermi Large Area Telescope Data Using A New Blind Search Method

DOE PAGES

Pletsch, H. J.; Guillemot, L.; Allen, B.; ...

2011-12-20

We report the discovery of nine previously unknown gamma-ray pulsars in a blind search of data from the Fermi Large Area Telescope (LAT). The pulsars were found with a novel hierarchical search method originally developed for detecting continuous gravitational waves from rapidly rotating neutron stars. Designed to find isolated pulsars spinning at up to kHz frequencies, the new method is computationally efficient, and incorporates several advances, including a metric-based gridding of the search parameter space (frequency, frequency derivative and sky location) and the use of photon probability weights. The nine pulsars have spin frequencies between 3 and 12 Hz, andmore » characteristic ages ranging from 17 kyr to 3 Myr. Two of them, PSRs J1803–2149 and J2111+4606, are young and energetic Galactic-plane pulsars (spin-down power above 6X10 35 erg s -1 and ages below 100 kyr). The seven remaining pulsars, PSRs J0106+4855, J0622+3749, J1620–4927, J1746–3239, J2028+3332, J2030+4415, J2139+4716, are older and less energetic; two of them are located at higher Galactic latitudes (jbj > 10°). PSR J0106+4855 has the largest characteristic age (3 Myr) and the smallest surface magnetic field (2X10 11G) of all LAT blind-search pulsars. PSR J2139+4716 has the lowest spin-down power (3X10 33 erg s -1) among all non-recycled gamma-ray pulsars ever found. Despite extensive multi-frequency observations, only PSR J0106+4855 has detectable pulsations in the radio band. The other eight pulsars belong to the increasing population of radio-quiet gamma-ray pulsars.« less

Injection Laser Structure Design.

DTIC Science & Technology

1985-01-30

A. Linz and J. Butler Electrical Engineering Department Southern Methodist University Dallas, Texas 75275 Abstract A numerical method and the... NUMERICAL AND EFFECTIVE-INDEX METHODS FOR A CLASS OF DIELECTRIC WAVEGUIDES* H-.2 A. Linz and J.K. Butler Electrical Engineering Department Southern...University, Dallas, TX, where he is now Professor of Electrical methd w usd i notpraticl fr etensve odeingdue Engineering . His primary research areas are solid

Mechanistic Investigations of Organic Aggregates with Different Topologies for Optical Limiting Applications

DTIC Science & Technology

2012-03-08

transport properties quinoidal oligothiophenes demonstrate remarkable nonlinear absorption properties in a very broad spectral range.12,13 Recent...7.6x10-76cm6s2phot-2 3. Fluorene-based oligomers, Chem. Eur. J., 2009, 15, 11681 3 =3.6x10-77cm6s2phot-2 4. Organometallic Dendrimers , Ang.Chem...Int.Ed. 2007, 46, 731 3 =1.5x10-77cm6s2phot-2 5. BDPADSB dendrimer , J. Lumin. 2007, 127, 28 3 =1.5x10-79cm6s2phot-2 Figure 5

Selective Cytotoxicity of 1,3,4-Thiadiazolium Mesoionic Derivatives on Hepatocarcinoma Cells (HepG2)

PubMed Central

Valdameri, Glaucio; Rocha, Maria Eliane Merlin; Martinez, Glaucia Regina; Noleto, Guilhermina Rodrigues; Acco, Alexandra; Alves de Souza, Carlos Eduardo; Echevarria, Aurea; Moretto dos Reis, Camilla; Di Pietro, Attilio; Suter Correia Cadena, Sílvia Maria

2015-01-01

In this work, we evaluated the cytotoxicity of mesoionic 4-phenyl-5-(2-Y, 4-X or 4-X-cinnamoyl)-1,3,4-thiadiazolium-2-phenylamine chloride derivatives (MI-J: X=OH, Y=H; MI-D: X=NO2, Y=H; MI-4F: X=F, Y=H; MI-2,4diF: X=Y=F) on human hepatocellular carcinoma (HepG2), and non-tumor cells (rat hepatocytes) for comparison. MI-J, M-4F and MI-2,4diF reduced HepG2 viability by ~ 50% at 25 μM after 24-h treatment, whereas MI-D required a 50 μM concentration, as shown by 3-(4,5-dimethythiazol-2-yl)-2,5-diphenyltetrazolium bromide assays. The cytotoxicity was confirmed with lactate dehydrogenase assay, of which activity was increased by 55, 24 and 16% for MI-J, MI-4F and MI-2,4diF respectively (at 25 μM after 24 h). To identify the death pathway related to cytotoxicity, the HepG2 cells treated by mesoionic compounds were labeled with both annexin V and PI, and analyzed by flow cytometry. All compounds increased the number of doubly-stained cells at 25 μM after 24 h: by 76% for MI-J, 25% for MI-4F and MI-2,4diF, and 11% for MI-D. It was also verified that increased DNA fragmentation occurred upon MI-J, MI-4F and MI-2,4diF treatments (by 12%, 9% and 8%, respectively, at 25 μM after 24 h). These compounds were only weakly, or not at all, transported by the main multidrug transporters, P-glycoprotein, ABCG2 and MRP1, and were able to slightly inhibit their drug-transport activity. It may be concluded that 1,3,4-thiadiazolium compounds, especially the hydroxy derivative MI-J, constitute promising candidates for future investigations on in-vivo treatment of hepatocellular carcinoma. PMID:26083249

Jam Resistant Communications Systems Techniques

DTIC Science & Technology

1982-12-01

ina rayo iteeet -- :."-,(constraint elements plus two resolution elements). •j, r,2 -- ’:." ~d c =0 .4 3 ),, dr l :3 .2X , dr 2 4 5 X @d -900 , s :33...E.K. Walton (Section VIII), and Dr. I.J. Gupta (Sections IX and X ). Mr. R.C. Taylor and R.W. Evans made significant contributions to all experimental...IN THE SAME CUT 190 E. CONCLUSIONS 200 F. REFERENCES 00 SECTION X ELEMENT PLACEMENT FOR ADAPTIVE ANTENNA ARRAYS 201 A. INTRODUCTION 201 B. THE ELEMENT

Inclusive χbJ(nP) decays to D0X

NASA Astrophysics Data System (ADS)

Briere, R. A.; Ferguson, T.; Tatishvili, G.; Vogel, H.; Watkins, M. E.; Rosner, J. L.; Alexander, J. P.; Cassel, D. G.; Duboscq, J. E.; Ehrlich, R.; Fields, L.; Galik, R. S.; Gibbons, L.; Gray, R.; Gray, S. W.; Hartill, D. L.; Heltsley, B. K.; Hertz, D.; Kandaswamy, J.; Kreinick, D. L.; Kuznetsov, V. E.; Mahlke-Krüger, H.; Mohapatra, D.; Onyisi, P. U. E.; Patterson, J. R.; Peterson, D.; Riley, D.; Ryd, A.; Sadoff, A. J.; Shi, X.; Stroiney, S.; Sun, W. M.; Wilksen, T.; Athar, S. B.; Patel, R.; Yelton, J.; Rubin, P.; Eisenstein, B. I.; Karliner, I.; Mehrabyan, S.; Lowrey, N.; Selen, M.; White, E. J.; Wiss, J.; Mitchell, R. E.; Shepherd, M. R.; Besson, D.; Pedlar, T. K.; Cronin-Hennessy, D.; Gao, K. Y.; Hietala, J.; Kubota, Y.; Klein, T.; Lang, B. W.; Poling, R.; Scott, A. W.; Zweber, P.; Dobbs, S.; Metreveli, Z.; Seth, K. K.; Tomaradze, A.; Libby, J.; Powell, A.; Wilkinson, G.; Ecklund, K. M.; Love, W.; Savinov, V.; Lopez, A.; Mendez, H.; Ramirez, J.; Ge, J. Y.; Miller, D. H.; Shipsey, I. P. J.; Xin, B.; Adams, G. S.; Anderson, M.; Cummings, J. P.; Danko, I.; Hu, D.; Moziak, B.; Napolitano, J.; He, Q.; Insler, J.; Muramatsu, H.; Park, C. S.; Thorndike, E. H.; Yang, F.; Artuso, M.; Blusk, S.; Khalil, S.; Li, J.; Mountain, R.; Nisar, S.; Randrianarivony, K.; Sultana, N.; Skwarnicki, T.; Stone, S.; Wang, J. C.; Zhang, L. M.; Bonvicini, G.; Cinabro, D.; Dubrovin, M.; Lincoln, A.; Naik, P.; Rademacker, J.; Asner, D. M.; Edwards, K. W.; Reed, J.

2008-11-01

Using Υ(2S) and Υ(3S) data collected with the CLEO III detector we have searched for decays of χbJ to final states with open charm. We fully reconstruct D0 mesons with pD0>2.5GeV/c in three decay modes (K-π+, K-π+π0, and K-π-π+π+) in coincidence with radiative transition photons that tag the production of one of the χbJ(nP) states. Significant signals are obtained for the two J=1 states. Recent nonrelativistic QCD (NRQCD) calculations of χbJ(nP)→c cmacr X depend on one nonperturbative parameter per χbJ triplet. The extrapolation from the observed D0X rate over a limited momentum range to a full c cmacr X rate also depends on these same parameters. Using our data to fit for these parameters, we extract results which agree well with NRQCD predictions, confirming the expectation that charm production is largest for the J=1 states. In particular, for J=1, our results are consistent with c cmacr g accounting for about one-quarter of all hadronic decays.

D-558-1 in flight

NASA Technical Reports Server (NTRS)

1952-01-01

This 1952 NACA High-Speed Flight Research Station inflight photograph of the Douglas D-558-1 #3 Skystreak. Even with partial cloud cover the white aircraft was easy to see. The D-558-1 reflected NACA (National Advisory Committee for Aeronautics) ideas on a transonic research aircraft. NACA engineers favored a turbojet engine, as they saw a rocket-powered research aircraft as too risky. They were also more interested in transonic speed--from about Mach 0.8 to Mach 1.2--than in breaking the 'sound barrier' for the sake of doing so. The Army Air Forces had a different approach and developed the rocket-powered XS-1, which the NACA also flew and supported, although it favored the D-558-1. Conceived in 1945, the D558-1 Skystreak was designed by the Douglas Aircraft Company for the U.S. Navy Bureau of Aeronautics, in conjunction with the National Advisory Committee for Aeronautics (NACA). The Skystreaks were turojet powered aircraft that took off from the ground under their own power and had straight wings and tails. All three D-558-1 Skystreaks were powered by Allison J35-A-11 turbojet engines producing 5,000 pounds of thrust. All the Skystreaks were initially painted scarlet, which lead to the nickname 'crimson test tube.' NACA later had the color of the Skystreaks changed to white to improve optical tracking and photography. The Skystreaks carried 634 pounds of instrumentation and were ideal first-generation, simple, transonic research airplanes. Much of the research performed by the D-558-1 Skystreaks, was quickly overshadowed in the public mind by Chuck Yeager and the X-1 rocketplane. However, the Skystreak performed an important role in aeronautical research by flying for extended periods of time at transonic speeds, which freed the X-1 to fly for limited periods at supersonic speeds.

Handbook for Sampling and Sample Preservation of Water and Wastewater

DTIC Science & Technology

1992-05-01

integers from 1 to N. N E Xi = XI1 + X 2 + X 3 . ..... + XN i=l 1 In the above example (from Table 4.1), X1 = 35.8, X2 = 33.0, ... , XN = X52 32.4; N E...41e 0 b10) -4 r- -C) a) 5l %Dt C) ON qc -0 Cl qtr C -4 %D cvj qw a) C )L- L~~~J enC- ..4 m~a CV) .4 c P.. .4 cnm0 q5C) )n me .-4C) - (J 1 () e U m. 0-4...X(l) = X = 35.8, X(2) = X2 = 33.0,..., X(52) = X52 = 32.4. X(t) is the linear trend. X’(t) is the random component. In this case, the trend can be

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.

Real-Time Simulation of the X-33 Aerospace Engine

NASA Technical Reports Server (NTRS)

Aguilar, Robert

1999-01-01

This paper discusses the development and performance of the X-33 Aerospike Engine RealTime Model. This model was developed for the purposes of control law development, six degree-of-freedom trajectory analysis, vehicle system integration testing, and hardware-in-the loop controller verification. The Real-Time Model uses time-step marching solution of non-linear differential equations representing the physical processes involved in the operation of a liquid propellant rocket engine, albeit in a simplified form. These processes include heat transfer, fluid dynamics, combustion, and turbomachine performance. Two engine models are typically employed in order to accurately model maneuvering and the powerpack-out condition where the power section of one engine is used to supply propellants to both engines if one engine malfunctions. The X-33 Real-Time Model is compared to actual hot fire test data and is been found to be in good agreement.

Investigation of a Graphical CONOPS Development Environment for Agile Systems Engineering - Phase 2

DTIC Science & Technology

2010-05-31

Westerman, Crawshaw , Hockey, and Sauer, 1998) for practitioners. Thus, CTA extends research by providing a toolbox of methods for understanding teams...drive process and performance. Washington, DC: American Psychological Association. pp. 3-8. Shrayne, N. M., Westerman, S. J., Crawshaw , C. M

Branching ratio measurements of B meson decays to J/psi meson eta meson kaon and charged B meson decays to neutral D meson charged kaon with neutral D meson decays to positive pion negative pion neutral pion

NASA Astrophysics Data System (ADS)

Zeng, Qinglin

Results are presented for the decays of B → J/psietaK and B+/- → DK+/-, respectively, with experimental data collected with BABAR detector at PEP-II, located at Stanford Linear Accelerator Center (SLAC). With 90 x 106 BB¯ events at the Upsilon(4S) resonance, we obtained branching fractions of B (B+/- → J/psietaK +/-) = [10.8 +/- 2.3(stat) +/- 2.4(syst)] x 10-5 and B (B0 → J/psieta K0S ) = [8.4 +/- 2.6(stat) +/- 2.7( syst)] x 10-5; and we set an upper limit of B [B+/- → X(3872) K+/- → J/psietaK +/-] < 7.7 x 10-6 at 90% confidence level. The branching fraction of decay chain B (B+/- → DK +/- → pi+pi-pi 0K+/-) = [5.5 +/- 1.0( stat) +/- 0.7(syst)] x 10-6 with 229 x 106 BB¯ events at Upsilon(4S) resonance, here D represents the neutral D meson. The decay rate asymmetry is A = 0.02 +/- 0.16(stat) +/- 0.03(syst) for this full decay chain. This decay can be used to extract the unitarity angle gamma, a weak CP violation phase, through the interference of decay production of D0 and D¯ 0 to pi+pi-pi 0.

Manufacturing Methods and Technology Project Execution Report

DTIC Science & Technology

1981-08-01

DISTRIBUTED. 77 3183 IMPROVED PROCESSES FOR INERTIAL GRADE Q-FLEX ACCELERDMETER SuNSTRAND IMPROVED ACCELEROMETER blAS STABILITY, BY THICKENING GOLD ...O h- ^O UJ —« X -H 1— —i 0 □ LU UO U. 1-0 < a. O 3 LU <£ LU O a LU LO C 0 0 LU O < etf <t X) 1/1 ^ O + ^JJ 3 <I to cL • r-J 3 ■L. LU a: a ^ z < 0...x 2 X O Etf a: >- • Q- aC Q_ ct Q- at :£ ^ Q -^ Ct a C^ £ UJ at J at ac UJ J a a kU a. m —" < X ci; _J ac LU Wl i— O ^- —) <o "O i/J to Ml LU if! O

Maximum Solutions of Normalized Ricci Flow on 4-Manifolds

NASA Astrophysics Data System (ADS)

Fang, Fuquan; Zhang, Yuguang; Zhang, Zhenlei

2008-10-01

We consider the maximum solution g( t), t ∈ [0, + ∞), to the normalized Ricci flow. Among other things, we prove that, if ( M, ω) is a smooth compact symplectic 4-manifold such that {b_2^+(M) > 1} and let g( t), t ∈ [0, ∞), be a solution to (1.3) on M whose Ricci curvature satisfies that |Ric( g( t))| ≤ 3 and additionally χ( M) = 3τ ( M) > 0, then there exists an {min mathbb{N}} , and a sequence of points { x j, k ∈ M}, j = 1, . . . , m, satisfying that, by passing to a subsequence, {{(M, g(tk+t), x_{1,k},ldots, x_{m,k})stackrel{d_{GH}}longrightarrow ({\\coprod limitsm_{j=1}} N_j , g_{infty}, x_{1,infty}, ldots, x_{m,infty}),}} t ∈ [0, ∞), in the m-pointed Gromov-Hausdorff sense for any sequence t k → ∞, where ( N j , g ∞), j = 1, . . . , m, are complete complex hyperbolic orbifolds of complex dimension 2 with at most finitely many isolated orbifold points. Moreover, the convergence is C ∞ in the non-singular part of {\\coprod _1^m Nj} and {text{Vol}_{g0}(M)=sum_{j=1}mtext{Vol}_{g_{infty}}(Nj)} , where χ( M) (resp. τ( M)) is the Euler characteristic (resp. signature) of M.

Quantitative trait locus analysis of plasma cholesterol and triglyceride levels in C57BL/6J x RR F2 mice.

PubMed

Suto, Jun-ichi; Takahashi, Yuji; Sekikawa, Kenji

2004-10-01

A highly significant cholesterol quantitative trait locus (QTL) (Cq6) was identified on chromosome 1 in C57BL/6J x RR F2 mice. The Cq6 was located over the gene for apolipoprotein A-Il (Apoa2), and the RR allele was associated with increased plasma cholesterol. C57BL/6J has Apoa2a alleles and RR has Apoa2b alleles. Three different Apoa2 alleles are known on the basis of amino acid substitutions at four residues. Analysis with partial Apoa2 congenic strains possessing Apoa2a, Apoa2b, and Apoa2C alleles revealed that the Apoa2b allele is unique in the ability to increase cholesterol among the three Apoa2 alleles, and that the Ala-to-Val substitution at residue 61 may be crucial as far as cholesterol metabolism is concerned. We also investigated the question of whether the Apoa1 gene is responsible for the cholesterol QTLs (Cq4 and Cq5) that had been identified previously on chromosome 9 in C57BL/6J x KK-Ay/a F2 and in KK x RR F2, but not in C57BL/6J x RR F2 mice. Similar to Apoa2 alleles, three different Apoal alleles with two successive amino acid substitutions were revealed among the strains. However, we could not correlate Apoal polymorphisms with the occurrence of QTLs in these three sets of F2 mice.

Modeling and Characterization of Phonon Transmission and Generation across Engineered and Strained Interfaces for Developing Structure-Property Relations of Functional Nanostructures

DTIC Science & Technology

2015-05-21

translation of; report supersedes; old edition number, etc. 14. ABSTRACT. A brief (approximately 200 words) factual summary of the most significant... Chemistry C, Vol. 117, pp. 24716-24725, 2013. 21. Jose Ordonez-Miranda, Ronggui Yang, and J.J. Alvarado-Gil, A New Constitutive Equation for Nano-to...for attending ASME/IMECE 2012 in Houston, TX. Jun Liu, March 2012, “Most Excited Molecules” for his presentation at 12th GEAR2S Conference

High strength kiloampere Bi 2Sr 2CaCu 2O x cables for high-field magnet applications

DOE PAGES

Shen, Tengming; Li, Pei; Jiang, Jianyi; ...

2015-04-17

Multifilamentary Ag-sheathed Bi 2Sr 2CaCu 2O x (Bi-2212) wire can carry sufficient critical current density J c for the development of powerful superconducting magnets. But, the range of its applications is limited by the low mechanical strength of the Ag/Bi-2212 strand. A potential solution is to cable Ag/Bi-2212 wire with high-strength materials that are compatible with the Bi-2212 heat treatment in an oxygen atmosphere. Past attempts have not always been successful, because the high-strength materials reacted with Bi-2212 wires, significantly reducing their J c. We examined the nature of reactions occurring when Ag/Bi-2212 wires are heat-treated in direct contact withmore » several commonly used high-strength alloys and a new Fe-Cr-Al alloy. INCONEL X750 and INCONEL 600 resulted in significant J c loss, whereas Ni80-Cr caused little or no J c loss; however, all of them formed chromium oxide that subsequently reacted with silver, creating cracks in the silver sheath. We found that Fe-Cr-Al did not show significant reactions with Ag/Bi-2212 strands. Scanning electron microscopy (SEM) and energy dispersive x-ray (EDS) examinations revealed that the Fe-Cr-Al alloy benefits from the formation of a uniform, crack-free, continuous alumina layer on its surface that does not react with Ag and that helps minimize the Cu loss found with INCONEL X750 and INCONEL 600. We then fabricated prototype 6-around-1 cables with six Bi-2212 strands twisted and transposed around an Fe-Cr-Al alloy core coated with TiO 2. After standard 1 bar melt processing, the cable retained 100% of the total current-carrying capability of its strands, and, after a 10 bar overpressure processing, the cable reached a total current of 1025 A at 4.2 K and 10 T. Tensile tests showed that Fe-Cr-Al becomes brittle after being cooled to 4.2 K, whereas INCONEL X750 remains ductile and retains a modulus of 183 GPa. Finally. we proposed new cable designs that take advantage of the chemical compatibility of Fe-Cr-Al and high strength of INCONEL X750 for various high-field magnet applications.« less

The Building Loads Analysis System Thermodynamics (BLAST) Program, Version 2.0: Input Booklet.

DTIC Science & Technology

1979-06-01

U 3 a S - ELä ’*- rt it 3 — n I -£ 5 5 = •-> = " 5 ? o * r ^3 •-< U" X if) tD r...1 i 1 • S < , —, — 3 Z 1 I" . i .j, fi td •4 ft | i J-l 5 1 i i > ^ — US 1 • * ^ so...X U c — ~ m 43 -j U ŗ V .— CO ts -* ^L cc -3 IV", *_* 111 c u n TD 1- H lr j p LU — ?3 — E 2 O H- •M , r: < X t- 0 ~3 U

Strategies for Competition Beyond Open Architecture (OA): Acquisition at the Edge of Chaos

DTIC Science & Technology

2014-04-30

Discipline of Systems Engineering. SERC -2009-TR-006: Systems Engineering Research Center. Wade, D. J., & Madni, D. A. (2010). Development of 3-Year...Roadmap to Transform the Discipline of Systems Engineering. SERC -2009-TR-006: Systems Engineering Research Center. Wikipedia. (2012, 4 10

JPRS Report, Science & Technology, Japan, Powder Metallurgy Technology

DTIC Science & Technology

1988-12-13

100 mO« 132 Hz i i i i -K H JL x’ c-p’an« (film) ! f • j 0 60 70 M TOO 90 1C Figure 3. Real and...necessary to develop a new manufacturing process focusing on the control of grain orientation. References 1. M . Okada, et al., Jpn. J. Appl. Phys. 27...Tc drops as the amount of Sr added is increased. References 1. M . Oda, et al., Jpn. J. Phys., 26, L804, 1987. 2. Z. Qi-rui, et al., Solid State

Graduate Counseling Students' Levels of Ego Development, Wellness, and Psychological Disturbance: An Exploratory Investigation

ERIC Educational Resources Information Center

Lambie, Glenn W.; Smith, Heather L.; Ieva, Kara P.

2009-01-01

The authors report the findings of a descriptive, correlational study of 111 graduate counseling students' levels of ego development (L. X. Hy & J. Loevinger, 1996), wellness (J. E. Myers & T. J. Sweeney, 2005), and psychological disturbance (M. J. Lambert et al., 2004). Higher levels of ego maturity were associated with higher wellness scores.…