Science.gov

Sample records for affordable advanced booster

  1. NASA's Space Launch System Advanced Booster Development

    NASA Technical Reports Server (NTRS)

    Robinson, Kimberly F.; Crumbly, Christopher M.; May, Todd A.

    2014-01-01

    The National Aeronautics and Space Administration's (NASA's) Space Launch System (SLS) Program, managed at the Marshall Space Flight Center, is making progress toward delivering a new capability for human space flight and scientific missions beyond Earth orbit. NASA is executing this development within flat budgetary guidelines by using existing engines assets and heritage technology to ready an initial 70 metric ton (t) lift capability for launch in 2017, and then employing a block upgrade approach to evolve a 130-t capability after 2021. A key component of the SLS acquisition plan is a three-phased approach for the first-stage boosters. The first phase is to expedite the 70-t configuration by completing development of the Space Shuttle heritage 5-segment solid rocket boosters (SRBs) for the initial flights of SLS. Since no existing boosters can meet the performance requirements for the 130-t class SLS, the next phases of the strategy focus on the eventual development of advanced boosters with an expected thrust class potentially double the current 5-segment solid rocket booster capability of 3.88 million pounds of thrust each. The second phase in the booster acquisition plan is the Advanced Booster Engineering Demonstration and/or Risk Reduction (ABEDRR) effort, for which contracts were awarded beginning in 2012 after a full and open competition, with a stated intent to reduce risks leading to an affordable advanced booster. NASA has awarded ABEDRR contracts to four industry teams, which are looking into new options for liquid-fuel booster engines, solid-fuel-motor propellants, and composite booster structures. Demonstrations and/or risk reduction efforts were required to be related to a proposed booster concept directly applicable to fielding an advanced booster. This paper will discuss the status of this acquisition strategy and its results toward readying both the 70 t and 130 t configurations of SLS. The third and final phase will be a full and open

  2. Space Launch System NASA Research Announcement Advanced Booster Engineering Demonstration and/or Risk Reduction

    NASA Technical Reports Server (NTRS)

    Crumbly, Christopher M.; Craig, Kellie D.

    2011-01-01

    The intent of the Advanced Booster Engineering Demonstration and/or Risk Reduction (ABEDRR) effort is to: (1) Reduce risks leading to an affordable Advanced Booster that meets the evolved capabilities of SLS (2) Enable competition by mitigating targeted Advanced Booster risks to enhance SLS affordability. Key Concepts (1) Offerors must propose an Advanced Booster concept that meets SLS Program requirements (2) Engineering Demonstration and/or Risk Reduction must relate to the Offeror s Advanced Booster concept (3) NASA Research Announcement (NRA) will not be prescriptive in defining Engineering Demonstration and/or Risk Reduction

  3. NASA's Space Launch System Advanced Booster Engineering Demonstration and/or Risk Reduction Efforts

    NASA Technical Reports Server (NTRS)

    Crumbly, Christopher M.; Dumbacher, Daniel L.; May, Todd A.

    2012-01-01

    The National Aeronautics and Space Administration (NASA) formally initiated the Space Launch System (SLS) development in September 2011, with the approval of the program s acquisition plan, which engages the current workforce and infrastructure to deliver an initial 70 metric ton (t) SLS capability in 2017, while using planned block upgrades to evolve to a full 130 t capability after 2021. A key component of the acquisition plan is a three-phased approach for the first stage boosters. The first phase is to complete the development of the Ares and Space Shuttle heritage 5-segment solid rocket boosters (SRBs) for initial exploration missions in 2017 and 2021. The second phase in the booster acquisition plan is the Advanced Booster Risk Reduction and/or Engineering Demonstration NASA Research Announcement (NRA), which was recently awarded after a full and open competition. The NRA was released to industry on February 9, 2012, with a stated intent to reduce risks leading to an affordable advanced booster and to enable competition. The third and final phase will be a full and open competition for Design, Development, Test, and Evaluation (DDT&E) of the advanced boosters. There are no existing boosters that can meet the performance requirements for the 130 t class SLS. The expected thrust class of the advanced boosters is potentially double the current 5-segment solid rocket booster capability. These new boosters will enable the flexible path approach to space exploration beyond Earth orbit (BEO), opening up vast opportunities including near-Earth asteroids, Lagrange Points, and Mars. This evolved capability offers large volume for science missions and payloads, will be modular and flexible, and will be right-sized for mission requirements. NASA developed the Advanced Booster Engineering Demonstration and/or Risk Reduction NRA to seek industry participation in reducing risks leading to an affordable advanced booster that meets the SLS performance requirements

  4. NASA's Space Launch System Advanced Booster Engineering Demonstration and Risk Reduction Efforts

    NASA Technical Reports Server (NTRS)

    Crumbly, Christopher M.; May, Todd; Dumbacher, Daniel

    2012-01-01

    The National Aeronautics and Space Administration (NASA) formally initiated the Space Launch System (SLS) development in September 2011, with the approval of the program s acquisition plan, which engages the current workforce and infrastructure to deliver an initial 70 metric ton (t) SLS capability in 2017, while using planned block upgrades to evolve to a full 130 t capability after 2021. A key component of the acquisition plan is a three-phased approach for the first stage boosters. The first phase is to complete the development of the Ares and Space Shuttle heritage 5-segment solid rocket boosters for initial exploration missions in 2017 and 2021. The second phase in the booster acquisition plan is the Advanced Booster Risk Reduction and/or Engineering Demonstration NASA Research Announcement (NRA), which was recently awarded after a full and open competition. The NRA was released to industry on February 9, 2012, and its stated intent was to reduce risks leading to an affordable Advanced Booster and to enable competition. The third and final phase will be a full and open competition for Design, Development, Test, and Evaluation (DDT&E) of the Advanced Boosters. There are no existing boosters that can meet the performance requirements for the 130 t class SLS. The expected thrust class of the Advanced Boosters is potentially double the current 5-segment solid rocket booster capability. These new boosters will enable the flexible path approach to space exploration beyond Earth orbit, opening up vast opportunities including near-Earth asteroids, Lagrange Points, and Mars. This evolved capability offers large volume for science missions and payloads, will be modular and flexible, and will be right-sized for mission requirements. NASA developed the Advanced Booster Engineering Demonstration and/or Risk Reduction NRA to seek industry participation in reducing risks leading to an affordable Advanced Booster that meets the SLS performance requirements. Demonstrations and

  5. Advanced space transportation systems, BARGOUZIN booster

    NASA Astrophysics Data System (ADS)

    Prampolini, Marco; Louaas, Eric; Prel, Yves; Kostromin, Sergey; Panichkin, Nickolay; Sumin, Yuriy; Osin, Mikhail; Iranzo-Greus, David; Rigault, Michel; Beaurain, André; Couteau, Jean-Noël

    2008-07-01

    In the framework of Advanced Space Transportation Systems Studies sponsored by CNES in 2006, a study called "BARGOUZIN" was performed by a joint team led by ASTRIUM ST and TSNIIMASH. Beyond these leaders, the team comprised MOLNIYA, DASSAULT AVIATION and SNECMA as subcontractors. The "BARGOUZIN" concept is a liquid fuelled fly-back booster (LFBB), mounted on the ARIANE 5 central core stage in place of the current solid rocket booster. The main originality of the concept lies in the fact that the "BARGOUZIN" features a cluster of VULCAIN II engines, similar to the one mounted on the central core stage of ARIANE 5. An astute permutation strategy, between the booster engines and central core engine is expected to lead to significant cost reductions. The following aspects were addressed during the preliminary system study: engine number per booster trade-off/abort scenario analysis, aerodynamic consolidation, engine reliability, ascent controllability, ground interfaces separation sequence analysis, programmatics. These topics will be briefly presented and synthesized in this paper, giving an overview of the credibility of the concept.

  6. Athena: Advanced air launched space booster

    NASA Technical Reports Server (NTRS)

    Booker, Corey G.; Ziemer, John; Plonka, John; Henderson, Scott; Copioli, Paul; Reese, Charles; Ullman, Christopher; Frank, Jeremy; Breslauer, Alan; Patonis, Hristos

    1994-01-01

    The infrastructure for routine, reliable, and inexpensive access of space is a goal that has been actively pursued over the past 50 years, but has yet not been realized. Current launch systems utilize ground launching facilities which require the booster vehicle to plow up through the dense lower atmosphere before reaching space. An air launched system on the other hand has the advantage of being launched from a carrier aircraft above this dense portion of the atmosphere and hence can be smaller and lighter compared to its ground based counterpart. The goal of last year's Aerospace Engineering Course 483 (AE 483) was to design a 227,272 kg (500,000 lb.) air launched space booster which would beat the customer's launch cost on existing launch vehicles by at least 50 percent. While the cost analysis conducted by the class showed that this goal could be met, the cost and size of the carrier aircraft make it appear dubious that any private company would be willing to invest in such a project. To avoid this potential pitfall, this year's AE 483 class was to design as large an air launched space booster as possible which can be launched from an existing or modification to an existing aircraft. An initial estimate of the weight of the booster is 136,363 kg (300,000 lb.) to 159,091 kg (350,000 lb.).

  7. Space Launch System (SLS) Program Overview NASA Research Announcement (NRA) Advanced Booster (AB) Engineering Demonstration and Risk Reduction (EDRR) Industry Day

    NASA Technical Reports Server (NTRS)

    May, Todd A.

    2011-01-01

    SLS is a national capability that empowers entirely new exploration for missions of national importance. Program key tenets are safety, affordability, and sustainability. SLS builds on a solid foundation of experience and current capacities to enable a timely initial capability and evolve to a flexible heavy-lift capability through competitive opportunities: (1) Reduce risks leading to an affordable Advanced Booster that meets the evolved capabilities of SLS (2) Enable competition by mitigating targeted Advanced Booster risks to enhance SLS affordability and performance The road ahead promises to be an exciting journey for present and future generations, and we look forward to working with you to continue America fs space exploration.

  8. Update on Risk Reduction Activities for a Liquid Advanced Booster for NASA's Space Launch System

    NASA Technical Reports Server (NTRS)

    Crocker, Andrew M.; Doering, Kimberly B; Meadows, Robert G.; Lariviere, Brian W.; Graham, Jerry B.

    2015-01-01

    The stated goals of NASA's Research Announcement for the Space Launch System (SLS) Advanced Booster Engineering Demonstration and/or Risk Reduction (ABEDRR) are to reduce risks leading to an affordable Advanced Booster that meets the evolved capabilities of SLS; and enable competition by mitigating targeted Advanced Booster risks to enhance SLS affordability. Dynetics, Inc. and Aerojet Rocketdyne (AR) formed a team to offer a wide-ranging set of risk reduction activities and full-scale, system-level demonstrations that support NASA's ABEDRR goals. For NASA's SLS ABEDRR procurement, Dynetics and AR formed a team to offer a series of full-scale risk mitigation hardware demonstrations for an affordable booster approach that meets the evolved capabilities of the SLS. To establish a basis for the risk reduction activities, the Dynetics Team developed a booster design that takes advantage of the flight-proven Apollo-Saturn F-1. Using NASA's vehicle assumptions for the SLS Block 2, a two-engine, F-1-based booster design delivers 150 mT (331 klbm) payload to LEO, 20 mT (44 klbm) above NASA's requirements. This enables a low-cost, robust approach to structural design. During the ABEDRR effort, the Dynetics Team has modified proven Apollo-Saturn components and subsystems to improve affordability and reliability (e.g., reduce parts counts, touch labor, or use lower cost manufacturing processes and materials). The team has built hardware to validate production costs and completed tests to demonstrate it can meet performance requirements. State-of-the-art manufacturing and processing techniques have been applied to the heritage F-1, resulting in a low recurring cost engine while retaining the benefits of Apollo-era experience. NASA test facilities have been used to perform low-cost risk-reduction engine testing. In early 2014, NASA and the Dynetics Team agreed to move additional large liquid oxygen/kerosene engine work under Dynetics' ABEDRR contract. Also led by AR, the

  9. Survey of Advanced Booster Options for Potential Shuttle Derivative Vehicles

    NASA Technical Reports Server (NTRS)

    Sackheim, Robert L.; Ryan, Richard; Threet, Ed; Kennedy, James W. (Technical Monitor)

    2001-01-01

    A never-ending major goal for the Space Shuttle program is to continually improve flight safety, as long as this launch system remains in operational service. One of the options to improve system safety and to enhance vehicle performance as well, that has been seriously studied over the past several decades, is to replace the existing strap-on four segment solid rocket boosters (SRB's) with more capable units. A number of booster upgrade options have been studied in some detail, ranging from five segment solids through hybrids and a wide variety of liquid strap-ons (both pressure and pump fed with various propellants); all the way to a completely reusable liquid fly back booster (complete with air breathing engines for controlled landing and return). All of these possibilities appear to offer improvements in varying degrees; and each has their strengths and weaknesses from both programmatic and technical points of view. The most beneficial booster upgrade/design, if the shuttle program were to continue long enough to justify the required investment, would be an approach that greatly increased both vehicle and crew safety. This would be accomplished by increasing the minimum range/minimum altitude envelope that would readily allow abort to orbit (ATO), possibly even to zero/zero, and possibly reduce or eliminate the Return to Launch Site (RTLS) and even the Trans Atlantic Landing (TAL) abort mode requirements. This paper will briefly survey and discuss all of the various booster'upgrade options studied previously, and compare their relative attributes. The survey will explicitly discuss, in summary comparative form, options that include: five segment solids; several hybrid possibilities; pressure and/or pump-fed liquids using either LO2/kerosene, H2O/kerosene and LO2/J2, any of which could be either fully expendable, partly or fully reusable; and finally a fully reusable liquid fly back booster system, with a number of propellant and propulsion system options

  10. Analysis of quasi-hybrid solid rocket booster concepts for advanced earth-to-orbit vehicles

    NASA Technical Reports Server (NTRS)

    Zurawski, Robert L.; Rapp, Douglas C.

    1987-01-01

    A study was conducted to assess the feasibility of quasi-hybrid solid rocket boosters for advanced Earth-to-orbit vehicles. Thermochemical calculations were conducted to determine the effect of liquid hydrogen addition, solids composition change plus liquid hydrogen addition, and the addition of an aluminum/liquid hydrogen slurry on the theoretical performance of a PBAN solid propellant rocket. The space shuttle solid rocket booster was used as a reference point. All three quasi-hybrid systems theoretically offer higher specific impulse when compared with the space shuttle solid rocket boosters. However, based on operational and safety considerations, the quasi-hybrid rocket is not a practical choice for near-term Earth-to-orbit booster applications. Safety and technology issues pertinent to quasi-hybrid rocket systems are discussed.

  11. Magnetic properties of the ALS (Advanced Light Source) booster synchrotron engineering model magnets

    SciTech Connect

    Keller, R.; Green, M.I.; Hoyer, E.; Koo, Y.M.; Luchini, K.; Marks, S.; Milburn, J.; Nelson, D.H.

    1989-03-01

    The Advanced Light Source (ALS) at Lawrence Berkeley Laboratory is designed to be a third-generation electron storage ring producing high-brightness VUV and X-ray radiation from wiggler and undulator insertion devices. Engineering models of all lattice magnets that are to be installed in the storage ring and its booster synchrotron have been built and are being tested to verify their performance. This paper is concerned with the magnets that form the booster lattice: dipoles, quadrupoles, sextupoles, and corrector dipoles (steerers). After a brief outline of measurement techniques and equipment, the major design parameters of these magnets are listed. Measured effective lengths and multipole field errors are then given for each type. All engineering models meet the specifications, and tracking studies including the measured systematic field errors show acceptable performance of the booster synchrotron; hence the designs are qualified for production. 3 refs., 7 figs., 4 tabs.

  12. Propulsion system advances that enable a reusable Liquid Fly Back Booster (LFBB)

    NASA Technical Reports Server (NTRS)

    Keith, E. L.; Rothschild, W. J.

    1998-01-01

    This paper provides an overview of the booster propulsion system for the Liquid Fly Back Booster (LFBB). This includes, system requirements, design approach, concept of operations, reliability, safety and cost assumptions. The paper summarizes the findings of the Boeing propulsion team that has been studying the LFBB feasibility as a booster replacement for the Space Shuttle. This paper will discuss recent advances including a new generation of kerosene and oxygen rich pre-burner staged combustion cycle main rocket engines. The engine reliability and safety is expected to be much higher than current standards by adding extra operating margins into the design and normally operating the engines at 75% of engine rated power. This allows for engine out capability. The new generation of main engines operates at significantly higher chamber pressure than the prior generation of gas generator cycle engines. The oxygen rich pre-burner engine cycle, unlike the fuel rich gas generator cycle, results in internally self-cleaning firings which facilitates reusability. Maintenance is further enhanced with integrated health monitoring to improve safety and turn-around efficiency. The maintainability of the LFBB LOX/kerosene engines is being improved by designing the vehicle/engine interfaces for easy access to key engine components.

  13. Propulsion System Advances that Enable a Reusable Liquid Fly Back Booster (LFBB)

    NASA Technical Reports Server (NTRS)

    Keith, Edward L.; Rothschild, William J.

    1998-01-01

    This paper provides an overview of the booster propulsion system for the Liquid Fly Back Booster (LFBB). This includes, system requirements, design approach, concept of operations, reliability, safety and cost assumptions. The paper summarizes the findings of the Boeing propulsion team that has been studying the LFBB feasibility as a booster replacement for the Space Shuttle. This paper will discuss recent advances including a new generation of kerosene and oxygen rich pre-burner staged combustion cycle main rocket engines. The engine reliability and safety is expected to be much higher than current standards by adding extra operating margins into the design and normally operating the engines at 75% of engine rated power. This allows for engine out capability. The new generation of main engines operates at significantly higher chamber pressure than the prior generation of gas generator cycle engines. The oxygen rich pre-burner engine cycle, unlike the fuel rich gas generator cycle, results in internally self-cleaning firings which facilitates reusability. Maintenance is further enhanced with integrated health monitoring to improve safety and turn-around efficiency. The maintainability of the LFBB LOX / kerosene engines is being improved by designing the vehicle/engine interfaces for easy access to key engine components.

  14. Advanced Modular Power Approach to Affordable, Supportable Space Systems

    NASA Technical Reports Server (NTRS)

    Oeftering, Richard C.; Kimnach, Greg L.; Fincannon, James; Mckissock,, Barbara I.; Loyselle, Patricia L.; Wong, Edmond

    2013-01-01

    Recent studies of missions to the Moon, Mars and Near Earth Asteroids (NEA) indicate that these missions often involve several distinct separately launched vehicles that must ultimately be integrated together in-flight and operate as one unit. Therefore, it is important to see these vehicles as elements of a larger segmented spacecraft rather than separate spacecraft flying in formation. The evolution of large multi-vehicle exploration architecture creates the need (and opportunity) to establish a global power architecture that is common across all vehicles. The Advanced Exploration Systems (AES) Modular Power System (AMPS) project managed by NASA Glenn Research Center (GRC) is aimed at establishing the modular power system architecture that will enable power systems to be built from a common set of modular building blocks. The project is developing, demonstrating and evaluating key modular power technologies that are expected to minimize non-recurring development costs, reduce recurring integration costs, as well as, mission operational and support costs. Further, modular power is expected to enhance mission flexibility, vehicle reliability, scalability and overall mission supportability. The AMPS project not only supports multi-vehicle architectures but should enable multi-mission capability as well. The AMPS technology development involves near term demonstrations involving developmental prototype vehicles and field demonstrations. These operational demonstrations not only serve as a means of evaluating modular technology but also provide feedback to developers that assure that they progress toward truly flexible and operationally supportable modular power architecture.

  15. Propulsion technology needs for advanced space transportation systems. [orbit maneuvering engine (space shuttle), space shuttle boosters

    NASA Technical Reports Server (NTRS)

    Gregory, J. W.

    1975-01-01

    Plans are formulated for chemical propulsion technology programs to meet the needs of advanced space transportation systems from 1980 to the year 2000. The many possible vehicle applications are reviewed and cataloged to isolate the common threads of primary propulsion technology that satisfies near term requirements in the first decade and at the same time establish the technology groundwork for various potential far term applications in the second decade. Thrust classes of primary propulsion engines that are apparent include: (1) 5,000 to 30,000 pounds thrust for upper stages and space maneuvering; and (2) large booster engines of over 250,000 pounds thrust. Major classes of propulsion systems and the important subdivisions of each class are identified. The relative importance of each class is discussed in terms of the number of potential applications, the likelihood of that application materializing, and the criticality of the technology needed. Specific technology programs are described and scheduled to fulfill the anticipated primary propulsion technology requirements.

  16. Space Launch System Accelerated Booster Development Cycle

    NASA Technical Reports Server (NTRS)

    Arockiam, Nicole; Whittecar, William; Edwards, Stephen

    2012-01-01

    With the retirement of the Space Shuttle, NASA is seeking to reinvigorate the national space program and recapture the public s interest in human space exploration by developing missions to the Moon, near-earth asteroids, Lagrange points, Mars, and beyond. The would-be successor to the Space Shuttle, NASA s Constellation Program, planned to take humans back to the Moon by 2020, but due to budgetary constraints was cancelled in 2010 in search of a more "affordable, sustainable, and realistic" concept2. Following a number of studies, the much anticipated Space Launch System (SLS) was unveiled in September of 2011. The SLS core architecture consists of a cryogenic first stage with five Space Shuttle Main Engines (SSMEs), and a cryogenic second stage using a new J-2X engine3. The baseline configuration employs two 5-segment solid rocket boosters to achieve a 70 metric ton payload capability, but a new, more capable booster system will be required to attain the goal of 130 metric tons to orbit. To this end, NASA s Marshall Space Flight Center recently released a NASA Research Announcement (NRA) entitled "Space Launch System (SLS) Advanced Booster Engineering Demonstration and/or Risk Reduction." The increased emphasis on affordability is evident in the language used in the NRA, which is focused on risk reduction "leading to an affordable Advanced Booster that meets the evolved capabilities of SLS" and "enabling competition" to "enhance SLS affordability. The purpose of the work presented in this paper is to perform an independent assessment of the elements that make up an affordable and realistic path forward for the SLS booster system, utilizing advanced design methods and technology evaluation techniques. The goal is to identify elements that will enable a more sustainable development program by exploring the trade space of heavy lift booster systems and focusing on affordability, operability, and reliability at the system and subsystem levels5. For this study

  17. Design, fabrication, and calibration of curved integral coils for measuring transfer function, uniformity, and effective length of LBL ALS (Lawrence Berkeley Laboratory Advanced Light Source) Booster Dipole Magnets

    SciTech Connect

    Green, M.I.; Nelson, D.; Marks, S.; Gee, B.; Wong, W.; Meneghetti, J.

    1989-03-01

    A matched pair of curved integral coils has been designed, fabricated and calibrated at Lawrence Berkeley Laboratory for measuring Advanced Light Source (ALS) Booster Dipole Magnets. Distinctive fabrication and calibration techniques are described. The use of multifilar magnet wire in fabrication integral search coils is described. Procedures used and results of AC and DC measurements of transfer function, effective length and uniformity of the prototype booster dipole magnet are presented in companion papers. 8 refs.

  18. Affordable In-Space Transportation Phase 2: An Advanced Concepts Project

    NASA Technical Reports Server (NTRS)

    1996-01-01

    The Affordable In-Space Transportation (AIST) program was established by the NASA Office of Space Access to improve transportation and lower the costs from Low Earth Orbit (LEO) to Geostationary Earth Orbit (GEO) and beyond (to Lunar orbit, Mars orbit, inner solar system missions, and return to LEO). A goal was established to identify and develop radically innovative concepts for new upper stages for Reusable Launch Vehicles (RLV) and Highly Reusable Space Transportation (HRST) systems. New architectures and technologies are being identified which have the potential to meet a cost goal of $1,000 to $2,000 per pound for transportation to GEO and beyond for overall mission cost (including the cost to LEO). A Technical Interchange Meeting (TTM) was held on October 16 and 17, 1996 in Huntsville, Alabama to review previous studies, present advanced concepts and review technologies that could be used to meet the stated goals. The TIN4 was managed by NASA-Marshall Space Flight Center (MSFC) Advanced Concepts Office with Mr. Alan Adams providing TIM coordination. Mr. John C. Mankins of NASA Headquarters provided overall sponsorship. The University of Alabama in Huntsville (UAH) Propulsion Research Center hosted the TIM at the UAH Research Center. Dr. Clark Hawk, Center Director, was the principal investigator. Technical support was provided by Christensen Associates. Approximately 70 attendees were present at the meeting. This Executive Summary provides a record of the key discussions and results of the TIN4 in a summary for-mat. It incorporates the response to the following basic issues of the TDVL which addressed the following questions: 1. What are the cost drivers and how can they be reduced? 2. What are the operational issues and their impact on cost? 3. What is the current technology readiness level (TRL) and what will it take to reach TRL 6? 4. What are the key enabling technologies and sequence for their accomplishment? 5 . What is the proposed implementation time

  19. Affordable In-Space Transportation. Phase 2; An Advanced Concepts Project

    NASA Technical Reports Server (NTRS)

    1996-01-01

    The Affordable In-Space Transportation (AIST) program was established by the NASA Office of Space Access to improve transportation and lower the costs from Low Earth Orbit (LEO) to Geostationary Earth Orbit (GEO) and beyond (to Lunar orbit, Mars orbit, inner solar system missions, and return to LEO). A goal was established to identify and develop radically innovative concepts for new upper stages for Reusable Launch Vehicles (RLV) and Highly Reusable Space Transportation (HRST) systems. New architectures and technologies are being identified which have the potential to meet a cost goal of $1,000 to $2,000 per pound for transportation to GEO and beyond for overall mission cost (including the cost to LEO). A Technical Interchange Meeting (ITM) was held on October 16 and 17, 1996 in Huntsville, Alabama to review previous studies, present advanced concepts and review technologies that could be used to meet the stated goals. The TIM was managed by NASA-Mar-shaU Space Flight Center (MSFC) Advanced Concepts Office with Mr. Alan Adams providing TIM coordination. Mr. John C. Manidns of NASA Headquarters provided overall sponsorship. The University of Alabama in Huntsville (UAH) Propulsion Research Center hosted the TM at the UAH Research Center. Dr. Clark Hawk, Center Director, was the principal investigator. Technical support was provided by Christensen Associates. Approximately 70 attendees were present at the meeting. This Executive Summary provides a record of the key discussions and results of the TIM in a summary format. It incorporates the response to the following basic issues of the TPA, which addressed the following questions: 1. What are the cost drivers and how can they be reduced? 2. What are the operational issues and their impact on cost? What is the current Technology Readiness Level (TRL) and what will it take to reach TRL 6? 4. What are the key enabling technologies and sequence for their accomplishment? 5. What is the proposed implementation time frame

  20. Liquid Rocket Booster Study. Volume 2, Book 1

    NASA Technical Reports Server (NTRS)

    1989-01-01

    The recommended Liquid Rocket Booster (LRB) concept is shown which uses a common main engine with the Advanced Launch System (ALS) which burns LO2 and LH2. The central rationale is based on the belief that the U.S. can only afford one big new rocket engine development in the 1990's. A LO2/LH2 engine in the half million pound thrust class could satisfy STS LRB, ALS, and Shuttle C (instead of SSMEs). Development costs and higher production rates can be shared by NASA and USAF. If the ALS program does not occur, the LO2/RP-1 propellants would produce slight lower costs for and STS LRB. When the planned Booster Engine portion of the Civil Space Transportation Initiatives has provided data on large pressure fed LO2/RP-1 engines, then the choice should be reevaluated.

  1. Advanced booster guidance studies

    NASA Technical Reports Server (NTRS)

    Cliff, Eugene M.

    1993-01-01

    This report is a summary of work done under Grant NAG1-946 for the period 19 December 1988 through 15 August 1992. Most of the technical work is described in the paper produced, including the NASA Contractor Report 4393 - 'Optimal Control Problems with Switching Points'. In the following pages we present a list of the papers along with a brief abstract. The technical work during the last months of the grant has not yet been submitted for publication so we present a summary of that work in an Appendix.

  2. Ram booster

    NASA Technical Reports Server (NTRS)

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

    2011-01-01

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

  3. Gas Test Loop Booster Fuel Hydraulic Testing

    SciTech Connect

    Gas Test Loop Hydraulic Testing Staff

    2006-09-01

    The Gas Test Loop (GTL) project is for the design of an adaptation to the Advanced Test Reactor (ATR) to create a fast-flux test space where fuels and materials for advanced reactor concepts can undergo irradiation testing. Incident to that design, it was found necessary to make use of special booster fuel to enhance the neutron flux in the reactor lobe in which the Gas Test Loop will be installed. Because the booster fuel is of a different composition and configuration from standard ATR fuel, it is necessary to qualify the booster fuel for use in the ATR. Part of that qualification is the determination that required thermal hydraulic criteria will be met under routine operation and under selected accident scenarios. The Hydraulic Testing task in the GTL project facilitates that determination by measuring flow coefficients (pressure drops) over various regions of the booster fuel over a range of primary coolant flow rates. A high-fidelity model of the NW lobe of the ATR with associated flow baffle, in-pile-tube, and below-core flow channels was designed, constructed and located in the Idaho State University Thermal Fluids Laboratory. A circulation loop was designed and constructed by the university to provide reactor-relevant water flow rates to the test system. Models of the four booster fuel elements required for GTL operation were fabricated from aluminum (no uranium or means of heating) and placed in the flow channel. One of these was instrumented with Pitot tubes to measure flow velocities in the channels between the three booster fuel plates and between the innermost and outermost plates and the side walls of the flow annulus. Flow coefficients in the range of 4 to 6.5 were determined from the measurements made for the upper and middle parts of the booster fuel elements. The flow coefficient for the lower end of the booster fuel and the sub-core flow channel was lower at 2.3.

  4. Developing the World's Most Powerful Solid Booster

    NASA Technical Reports Server (NTRS)

    Priskos, Alex S.; Frame, Kyle L.

    2016-01-01

    NASA's Journey to Mars has begun. Indicative of that challenge, this will be a multi-decadal effort requiring the development of technology, operational capability, and experience. The first steps are underway with more than 15 years of continuous human operations aboard the International Space Station (ISS) and development of commercial cargo and crew transportation capabilities. NASA is making progress on the transportation required for deep space exploration - the Orion crew spacecraft and the Space Launch System (SLS) heavy-lift rocket that will launch Orion and large components such as in-space stages, habitat modules, landers, and other hardware necessary for deep-space operations. SLS is a key enabling capability and is designed to evolve with mission requirements. The initial configuration of SLS - Block 1 - will be capable of launching more than 70 metric tons (t) of payload into low Earth orbit, greater mass than any other launch vehicle in existence. By enhancing the propulsion elements and larger payload fairings, future SLS variants will launch 130 t into space, an unprecedented capability that simplifies hardware design and in-space operations, reduces travel times, and enhances two solid propellant five-segment boosters, both based on space shuttle technologies. This paper will focus on development of the booster, which will provide more than 75 percent of total vehicle thrust at liftoff. Each booster is more than 17 stories tall, 3.6 meters (m) in diameter and weighs 725,000 kilograms (kg). While the SLS booster appears similar to the shuttle booster, it incorporates several changes. The additional propellant segment provides additional booster performance. Parachutes and other hardware associated with recovery operations have been deleted and the booster designated as expendable for affordability reasons. The new motor incorporates new avionics, new propellant grain, asbestos-free case insulation, a redesigned nozzle, streamlined manufacturing

  5. Opportunities in the Affordable Care Act to Advance Long-Term Services and Supports: The Role of Rehabilitation Counseling

    ERIC Educational Resources Information Center

    Caldwell, Joe; Alston, Reginald J.

    2012-01-01

    The Affordable Care Act includes many new provisions for long-term services and supports (LTSS). Among these are several new options, improvements, and incentives within Medicaid to balance service systems and expand access to home and community-based services. This article discusses some of the major provisions, implementations, and implications…

  6. Achieving health care affordability.

    PubMed

    Payson, Norman C

    2002-10-01

    Not all plans are jumping headlong into the consumer-centric arena. In this article, the CEO of Oxford Health Plans discusses how advanced managed care can achieve what other consumer-centric programs seek to do--provide affordable, quality health care. PMID:12391815

  7. Booster separation motor

    NASA Technical Reports Server (NTRS)

    1981-01-01

    The design, development, fabrication, testing, evaluation and flight qualification of the space shuttle booster separation motor is discussed. Delivery of flight hardware to support the research and development flights of the space shuttle is discussed.

  8. Second Generation Flyback Booster

    NASA Technical Reports Server (NTRS)

    2000-01-01

    This is a computer generated image of a Shuttle launch utilizing 2nd generation Reusable Launch Vehicle (RLV) flyback boosters, a futuristic concept that is currently undergoing study by NASA's Space Launch Initiative (SLI) Propulsion Office, managed by the Marshall Space Fight Center in Huntsville, Alabama, working in conjunction with the Agency's Glenn Research Center in Cleveland, Ohio. Currently, after providing thrust to the Space Shuttle, the solid rocket boosters are parachuted into the sea and are retrieved for reuse. The SLI is considering vehicle concepts that would fly first-stage boosters back to a designated landing site after separation from the orbital vehicle. These flyback boosters would be powered by several jet engines integrated into the booster capable of providing over 100,000 pounds of thrust. The study will determine the requirements for the engines, identify risk mitigation activities, and identify costs associated with risk mitigation and jet engine development and production, as well as determine candidate jet engine options to pursue for the flyback booster.

  9. Second Generation Flyback Booster

    NASA Technical Reports Server (NTRS)

    2000-01-01

    This is a computer generated image of a Shuttle in flight utilizing 2nd Generation Reusable Launch Vehicle (RLV) with flyback boosters, a futuristic concept that is currently undergoing study by NASA's Space Launch Initiative (SLI) Propulsion Office, managed by the Marshall Space Fight Center in Huntsville, Alabama, working in conjunction with the Agency's Glenn Research Center in Cleveland, Ohio. Currently, after providing thrust to the Space Shuttle, the solid rocket boosters are parachuted into the sea and are retrieved for reuse. The SLI is considering vehicle concepts that would fly first-stage boosters back to a designated landing site after separation from the orbital vehicle. These flyback boosters would be powered by several jet engines integrated into the booster capable of providing over 100,000 pounds of thrust. The study will determine the requirements for the engines, identify risk-mitigation activities, and identify costs associated with risk mitigation and jet engine development and production, as well as determine candidate jet engine options to pursue for the flyback booster.

  10. Review of superconducting booster linacs

    NASA Astrophysics Data System (ADS)

    Storm, D. W.

    1993-04-01

    Several superconducting boosters have been built and more are planned or under construction. These all use a number of independently phased resonators to permit acceleration of a wide variety of ion masses. For heavy ions, vhf frequencies are involved, and operation of the superconductors at 4.3 K, the normal boiling point of He, is practical. (Because fundamental losses in superconductors depend on frequency, some electron accelerators using much higher frequencies require colder resonators.) For boosters the resonator technology has evolved toward the use of quarter wave resonators with straight loading arms. The superconducting material is either niobium or lead. The latter is deposited as a film on copper, while the former may be sheet metal, may be bonded to copper, or may be (in principle) applied as a film on copper. The trade-offs involved and the successes of the various techniques are discussed. The rf must be controlled accurately both with regard to amplitude and phase. Because of the high unloaded Q of the resonators, additional loading is provided at some temperature well above that of the superconductor, in order to increase the bandwidth to a manageable point. Most boosters provide active control of phase by shifting the driving phase, although at least one system uses a frequency switching technique. Cross talk between independent resonator control systems must be avoided. The cryogenic systems have evolved toward a system based on a large helium refrigerator using turbine expansion and providing gas cooling to heat shields. Conservative design provides excess capacity beyond the expected requirements of the accelerator. Cryogenic distribution must be done carefully to avoid losses, and the system should be designed with capacity to match that of anticipated upgrades of the refrigerator. Most boosters use an approximately periodic focusing system with radial phase advance near 90° per unit cell. At Legnaro, however, waist to waist focusing is

  11. How Doula Care Can Advance the Goals of the Affordable Care Act: A Snapshot From New York City

    PubMed Central

    Strauss, Nan; Giessler, Katie; McAllister, Elan

    2015-01-01

    ABSTRACT Doula care meets each of the triple aims of the Affordable Care Act: improving health outcomes for all, improving the experience of care, and lowering costs by reducing non-beneficial and unwanted medical interventions. Cost is the greatest barrier to use of doula support. Reimbursement for doula services by private insurance, Medicaid, and Medicaid managed care organizations would significantly increase access to doulas. Widespread availability of doula care could significantly reduce cesarean rates, and increased access to community-based doula programs could reduce entrenched health disparities. PMID:26937157

  12. Space transportation booster engine configuration study. Volume 1: Executive Summary

    NASA Technical Reports Server (NTRS)

    1989-01-01

    The objective of the Space Transportation Booster Engine (STBE) Configuration Study is to contribute to the Advanced Launch System (ALS) development effort by providing highly reliable, low cost booster engine concepts for both expendable and reusable rocket engines. The objectives of the Space Transportation Booster Engine (STBE) Configuration Study were to identify engine configurations which enhance vehicle performance and provide operational flexibility at low cost, and to explore innovative approaches to the follow-on full-scale development (FSD) phase for the STBE.

  13. Ranger© - An Affordable, Advanced, Next-Generation, Dual-Pol, X-Band Weather Radar

    NASA Astrophysics Data System (ADS)

    Stedronsky, Richard

    2014-05-01

    The Enterprise Electronics Corporation (EEC) Ranger© system is a new generation, X-band (3 cm), Adaptive Polarization Doppler Weather Surveillance Radar that fills the gap between high-cost, high-power traditional radar systems and the passive ground station weather sensors. Developed in partnership with the University of Oklahoma Advanced Radar Research Center (ARRC), the system uses relatively low power solid-state transmitters and pulse compression technology to attain nearly the same performance capabilities of much more expensive traditional radar systems. The Ranger© also employs Adaptive Dual Polarization (ADP) techniques to allow Alternating or Simultaneous Dual Polarization capability with total control over the transmission polarization state using dual independent coherent transmitters. Ranger© has been designed using the very latest technology available in the industry and the technical and manufacturing experience gained through over four decades of successful radar system design and production at EEC. The entire Ranger© design concept emphasizes precision, stability, reliability, and value using proven solid state technology combined with the most advanced motion control system ever conceived for weather radar. Key applications include meteorology, hydrology, aviation, offshore oil/gas drilling, wind energy, and outdoor event situational awareness.

  14. The APS booster synchrotron: Commissioning and operational experience

    SciTech Connect

    Milton, S.V.

    1995-07-01

    The Advanced Photon Source (APS) at Argonne National Laboratory (ANL) was constructed to provide a large user community with intense and high brightness synchrotron radiation at x-ray wavelengths. A 7-GeV positron beam is used to generate this light. Acceleration of the beam from 450 MeV to 7 GeV is accomplished at a 2-Hz repetition rate by the booster synchrotron. Commissioning of the booster began in the second quarter of 1994 and continued on into early 1995. The booster is now routinely used to provide beam for the commissioning of the APS storage ring. Reported here are our commissioning and operational experiences with the booster synchrotron.

  15. Space Shuttle booster recovery planning.

    NASA Technical Reports Server (NTRS)

    Godfrey, R. E.

    1973-01-01

    At the initiation of the Space Shuttle Program, recoverable solid rocket boosters were base-lined, with an estimated savings of 30 per cent over expendable solid rockets. Present studies indicate that the solid rocket boosters in the 142-inch diameter range can be recovered using state-of-the-art recovery systems. Marshall Space Flight Center is conducting extensive studies to establish the most cost effective recovery system for the present Shuttle boosters. Model drop testing, in various facilities, and structural load testing are being conducted with model sizes ranging from 6 inches to 120 inches in diameter.

  16. Space Transportation Booster Engine (STBE) configuration study

    NASA Technical Reports Server (NTRS)

    1986-01-01

    The overall objective of this Space Transportation Booster Engine (STBE) study is to identify candidate engine configurations which enhance vehicle performance and provide operational flexibility at low cost. The specific objectives are as follows: (1) to identify and evaluate candidate LOX/HC engine configurations for the Advanced Space Transportation System for an early 1995 IOC and a late 2000 IOC; (2) to select one optimum engine for each time period; 3) to prepare a conceptual design for each configuration; (4) to develop a technology plan for the 2000 IOC engine; and, (5) to prepare preliminary programmatic planning and analysis for the 1995 IOC engine.

  17. Brake power servo booster

    SciTech Connect

    Kobayashi, M.; Shimamura, M.

    1988-04-19

    A brake power servo booster is described comprising: a power piston; a power piston return spring; at least two shells enclosing at least a portion of the power piston and defining a constant pressure chamber and a variable pressure chamber; a master cylinder for controlling the application of hydraulic pressure to a brake mechanism; an input shaft; a hollow cylindrical member integrally connected to the input shaft, a stopper member for limiting movement of the hollow cylindrical member in the second direction, a hollow output shaft integrally connected at one end thereof to the power piston; a connecting member integrally connected to the other end of the output shaft and slidably disposed inside the hollow cylindrical member, a valve member, a valve return spring for urging and valve member towards the first and second valve seats; and a key member provided between the connecting member and the hollow cylindrical member for allowing relative displacement between the connecting member and the hollow cylindrical member in the first and second directions within a predetermined range.

  18. New Approaches in Reuseable Booster System Life Cycle Cost Modeling

    NASA Technical Reports Server (NTRS)

    Zapata, Edgar

    2013-01-01

    This paper presents the results of a 2012 life cycle cost (LCC) study of hybrid Reusable Booster Systems (RBS) conducted by NASA Kennedy Space Center (KSC) and the Air Force Research Laboratory (AFRL). The work included the creation of a new cost estimating model and an LCC analysis, building on past work where applicable, but emphasizing the integration of new approaches in life cycle cost estimation. Specifically, the inclusion of industry processes/practices and indirect costs were a new and significant part of the analysis. The focus of LCC estimation has traditionally been from the perspective of technology, design characteristics, and related factors such as reliability. Technology has informed the cost related support to decision makers interested in risk and budget insight. This traditional emphasis on technology occurs even though it is well established that complex aerospace systems costs are mostly about indirect costs, with likely only partial influence in these indirect costs being due to the more visible technology products. Organizational considerations, processes/practices, and indirect costs are traditionally derived ("wrapped") only by relationship to tangible product characteristics. This traditional approach works well as long as it is understood that no significant changes, and by relation no significant improvements, are being pursued in the area of either the government acquisition or industry?s indirect costs. In this sense then, most launch systems cost models ignore most costs. The alternative was implemented in this LCC study, whereby the approach considered technology and process/practices in balance, with as much detail for one as the other. This RBS LCC study has avoided point-designs, for now, instead emphasizing exploring the trade-space of potential technology advances joined with potential process/practice advances. Given the range of decisions, and all their combinations, it was necessary to create a model of the original model

  19. New Approaches in Reusable Booster System Life Cycle Cost Modeling

    NASA Technical Reports Server (NTRS)

    Zapata, Edgar

    2013-01-01

    This paper presents the results of a 2012 life cycle cost (LCC) study of hybrid Reusable Booster Systems (RBS) conducted by NASA Kennedy Space Center (KSC) and the Air Force Research Laboratory (AFRL). The work included the creation of a new cost estimating model and an LCC analysis, building on past work where applicable, but emphasizing the integration of new approaches in life cycle cost estimation. Specifically, the inclusion of industry processes/practices and indirect costs were a new and significant part of the analysis. The focus of LCC estimation has traditionally been from the perspective of technology, design characteristics, and related factors such as reliability. Technology has informed the cost related support to decision makers interested in risk and budget insight. This traditional emphasis on technology occurs even though it is well established that complex aerospace systems costs are mostly about indirect costs, with likely only partial influence in these indirect costs being due to the more visible technology products. Organizational considerations, processes/practices, and indirect costs are traditionally derived ("wrapped") only by relationship to tangible product characteristics. This traditional approach works well as long as it is understood that no significant changes, and by relation no significant improvements, are being pursued in the area of either the government acquisition or industry?s indirect costs. In this sense then, most launch systems cost models ignore most costs. The alternative was implemented in this LCC study, whereby the approach considered technology and process/practices in balance, with as much detail for one as the other. This RBS LCC study has avoided point-designs, for now, instead emphasizing exploring the trade-space of potential technology advances joined with potential process/practice advances. Given the range of decisions, and all their combinations, it was necessary to create a model of the original model

  20. Solid Rocket Booster-Illustration

    NASA Technical Reports Server (NTRS)

    1977-01-01

    This illustration is a cutaway of the solid rocket booster (SRB) sections with callouts. The Shuttle's two SRB's are the largest solids ever built and the first designed for refurbishment and reuse. Standing nearly 150-feet high, the twin boosters provide the majority of thrust for the first two minutes of flight, about 5.8 million pounds, augmenting the Shuttle's main propulsion system during liftoff. The major design drivers for the solid rocket motors (SRM's) were high thrust and reuse. The desired thrust was achieved by using state-of-the-art solid propellant and by using a long cylindrical motor with a specific core design that allows the propellant to burn in a carefully controlled marner. At burnout, the boosters separate from the external tank and drop by parachute to the ocean for recovery and subsequent refurbishment. The boosters are designed to survive water impact at almost 60 miles per hour, maintain flotation with minimal damage, and preclude corrosion of the hardware exposed to the harsh seawater environment. Under the project management of the Marshall Space Flight Center, the SRB's are assembled and refurbished by the United Space Boosters. The SRM's are provided by the Morton Thiokol Corporation.

  1. Emulsion based cast booster - a priming system

    SciTech Connect

    Gupta, R.N.; Mishra, A.K.

    2005-07-01

    This paper explores the potential of emulsion based cast booster to be used as primer to initiate bulk delivered emulsion explosives used in mines. An attempt has been made for comparative study between conventional cast booster and emulsion based cast booster in terms of the initiation process developed and their capability to develop and maintain the stable detonation process in the column explosives. The study has been conducted using a continuous velocity of detonation (VOD) measuring instrument. During this study three blasts have been monitored. In each blast two holes have been selected for study, the first hole being initiated with conventional cast booster while the other one with emulsion based cast booster. The findings of the study advocates that emulsion based cast booster is capable of efficient priming of bulk delivered column explosive with stable detonation process in the column. Further, the booster had advantages over the conventional PETN/TNT based cast booster. 5 refs., 2 figs., 1 tab., 1 photo.

  2. The AGS Booster control system

    SciTech Connect

    Frankel, R.; Auerbach, E.; Culwick, B.; Clifford, T.; Mandell, S.; Mariotti, R.; Salwen, C.; Schumburg, N.

    1988-01-01

    Although moderate in size, the Booster construction project requires a comprehensive control system. There are three operational modes: as a high intensity proton injector for the AGS, as a heavy ion accelerator and injector supporting a wide range of ions and as a polarized proton storage injector. These requirements are met using a workstation based extension of the existing AGS control system. Since the Booster is joining a complex of existing accelerators, the new system will be capable of supporting multiuser operational scenarios. A short discussion of this system is discussed in this paper.

  3. 78 FR 21555 - Signal Booster Rules

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-04-11

    ...In this document, the Federal Communications Commission (Commission) amends its rules concerning signal boosters for consumer and industrial use in effort to enhance wireless coverage for consumers, particularly in rural, underserved, and difficult-to-serve areas by broadening the availability of signal boosters while ensuring that boosters do not adversely affect wireless...

  4. 47 CFR 22.527 - Signal boosters.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 47 Telecommunication 2 2014-10-01 2014-10-01 false Signal boosters. 22.527 Section 22.527 Telecommunication FEDERAL COMMUNICATIONS COMMISSION (CONTINUED) COMMON CARRIER SERVICES PUBLIC MOBILE SERVICES Paging and Radiotelephone Service § 22.527 Signal boosters. Licensees may install and operate signal boosters on channels listed in § 22.531...

  5. Single bunch instabilities of the RHIC booster

    SciTech Connect

    Ng, K.Y.

    1986-02-01

    In this paper, we try to estimate the stability limits and impedances of the Brookhaven RHIC booster. Some important data on the booster are shown. From the stability limits and impedances, it is clear that the booster is safe against either fast microwave instabilities or slow mode-colliding single bunch instabilities. 4 figs., 5 tabs.

  6. The AGS-Booster lattice

    SciTech Connect

    Lee, Y.Y.; Barton, D.S.; Claus, J.; Cottingham, J.G.; Courant, E.D.; Danby, G.T.; Dell, G.F.; Forsyth, E.B.; Gupta, R.C.; Kats, J.

    1987-01-01

    The AGS Booster has three objectives. They are to increase the space charge limit of the AGS, to increase the intensity of the polarized proton beam by accumulating many linac pulses (since the intensity is limited by the polarized ion source), and to reaccelerate heavy ions from the BNL Tandem Van de Graaff before injection into the AGS. The machine is capable of accelerating protons at 7.5 Hertz from 200 MeV to 1.5 GeV or to lower final energies at faster repetition rates. The machine will also be able to accelerate heavy ions from as low as 1 MeV/nucleon to a magnetic rigidity as high as 17.6 Tesla-meters with a one second repetition rate. As an accumulator for polarized protons, the Booster should be able to store the protons at 200 MeV for several seconds. We expect that the Booster will increase the AGS proton intensity by a factor of four, polarized proton intensity by a factor of twenty to thirty, and will also enable the AGS to accelerate all species of heavy ions (at present the AGS heavy ion program is limited to the elements lighter than sulfur because it can only accelerate fully stripped ions). The construction project started in FY 1985 and is expected to be completed in 1989. The purpose of this paper is to provide a future reference for the AGS Booster lattice.

  7. Space transportation booster engine configuration study. Volume 2: Design definition document and environmental analysis

    NASA Technical Reports Server (NTRS)

    1989-01-01

    The objective of the Space Transportation Booster Engine (STBE) Configuration Study is to contribute to the Advanced Launch System (ALS) development effort by providing highly reliable, low cost booster engine concepts for both expendable and reusable rocket engines. The objectives of the space Transportation Booster Engine (STBE) Configuration Study were: (1) to identify engine configurations which enhance vehicle performance and provide operational flexibility at low cost, and (2) to explore innovative approaches to the follow-on Full-Scale Development (FSD) phase for the STBE.

  8. The AGS Booster beam loss monitor system

    SciTech Connect

    Beadle, E.R.; Bennett, G.W.; Witkover, R.L.

    1991-01-01

    A beam loss monitor system has been developed for the Brookhaven National Laboratory Booster accelerator, and is designed for use with intensities of up to 1.5 {times} 10{sup 13} protons and carbon to gold ions at 50-3 {times} 10{sup 9} ions per pulse. This system is a significant advance over the present AGS system by improving the sensitivity, dynamic range, and data acquisition. In addition to the large dynamic range achievable, it is adaptively shifted when high losses are detected. The system uses up to 80 argon filled ion chambers as detectors, as well as newly designed electronics for processing and digitizing detector outputs. The hardware simultaneously integrates each detector output, interfaces to the beam interrupt systems, and digitizes all 80 channels to 21 bits at 170 KHz. This paper discuses the design, construction, and operation of the system. 4 refs., 2 figs.

  9. Booster aerodynamic heating: Test support

    NASA Technical Reports Server (NTRS)

    Engel, C. D.; Reardon, J. E.; Fuller, C. E.

    1974-01-01

    Several technical areas were encompassed in providing support for booster thermal environment test work. These areas included: (1) cavity flow heating, (2) rarefied flow heating, and (3) impulse operated model research and testing. Cavity flow heating problems were studied with respect to the proposed altitude control motors for the space shuttle. Available literature on this subject was reviewed and analytical predictive methods were summarized for use in planning testing work. Rarefied flow heating data was reviewed and correlated. The study showed the importance of considering rarefied flow conditions in launch thermal environment prediction. Impulse operated model research and testing was conducted to provide a basis for understanding and designing such models for booster thermal environment testing.

  10. Affordable Vehicle Avionics Overview

    NASA Technical Reports Server (NTRS)

    Cockrell, James J.

    2015-01-01

    Public and private launch vehicle developers are reducing the cost of propulsion for small commercial launchers, but conventional high-performance, high-reliability avionics remain the disproportionately high cost driver for launch. AVA technology performs as well or better than conventional launch vehicle avionics, but with a fraction of the recurring costs. AVA enables small launch providers to offer affordable rides to LEO to nano-satellites as primary payloads meaning, small payloads can afford to specify their own launch and orbit parameters

  11. Affordable Vehicle Avionics Overview

    NASA Technical Reports Server (NTRS)

    Cockrell, James J.

    2015-01-01

    Public and private launch vehicle developers are reducing the cost of propulsion for small commercial launchers, but conventional high-performance, high-reliability avionics remain the disproportionately high cost driver for launch. AVA technology performs as well or better than conventional launch vehicle avionics, but with a fraction of the recurring costs. AVA enables small launch providers to offer affordable rides to LEO to nano-satellites as primary payloads meaning, small payloads can afford to specify their own launch and orbit parameters.

  12. Affordable Care Act.

    PubMed

    Rak, Sofija; Coffin, Janis

    2013-01-01

    The Patient Protection and Affordable Care Act of 2010 (PPACA), although a subject of much debate in the Unites States, was enacted on March 23, 2010, and upheld by the Supreme Court on June 28, 2012. This act advocates that "healthcare is a right, not a privilege." The main goals of PPACA are to minimize the number of uninsured Americans and make healthcare available to everyone at an affordable price. The Congressional Budget Office has determined that 94% of Americans will have healthcare coverage while staying under the $900 billion limit that President Barack Obama established by bending the healthcare cost curve and reducing the deficit over the next 10 years. PMID:23767130

  13. Atlas SOHO Booster and Centaur Erection

    NASA Technical Reports Server (NTRS)

    1995-01-01

    The launch vehicle for the Solar Heliospheric Observatory (SOHO) mission is a two stage Atlas-IIAS (Atlas/Centaur). The Atlas, consists of a solid rocket booster stage powered by four Thiokol Castor IVA solid rocket boosters (SRB) and a core vehicle stage (booster and sustainer) powered by Rocketdyne MA-5A liquid propellant engines (RP-1 fuel and liquid oxygen). The multiple firing Centaur is powered by two Pratt and Whitney (RL10A-4) liquid hydrogen and liquid oxygen engines with extendible nozzles. This video shows the erection of the Atlas booster and transportation (to 36-B launching pad) and erection of the Centaur.

  14. Power flow control using quadrature boosters

    NASA Astrophysics Data System (ADS)

    Sadanandan, Sandeep N.

    A power system that can be controlled within security constraints would be an advantage to power planners and real-time operators. Controlling flows can lessen reliability issues such as thermal limit violations, power stability problems, and/or voltage stability conditions. Control of flows can also mitigate market issues by reducing congestion on some lines and rerouting power to less loaded lines or onto preferable paths. In the traditional control of power flows, phase shifters are often used. More advanced methods include using Flexible AC Transmission System (FACTS) Controllers. Some examples include Thyristor Controlled Series Capacitors, Synchronous Series Static Compensators, and Unified Power Flow Controllers. Quadrature Boosters (QBs) have similar structures to phase-shifters, but allow for higher voltage magnitude during real power flow control. In comparison with other FACTS controllers QBs are not as complex and not as expensive. The present study proposes to use QBs to control power flows on a power system. With the inclusion of QBs, real power flows can be controlled to desired scheduled values. In this thesis, the linearized power flow equations used for power flow analysis were modified for the control problem. This included modifying the Jacobian matrix, the power error vector, and calculating the voltage injected by the quadrature booster for the scheduled real power flow. Two scenarios were examined using the proposed power flow control method. First, the power flow in a line in a 5-bus system was modified with a QB using the method developed in this thesis. Simulation was carried out using Matlab. Second, the method was applied to a 30-bus system and then to a 118-bus system using several QBs. In all the cases, the calculated values of the QB voltages led to desired power flows in the designated line.

  15. Booster Main Engine Selection Criteria for the Liquid Fly-Back Booster

    NASA Technical Reports Server (NTRS)

    Ryan, Richard M.; Rothschild, William J.; Christensen, David L.

    1998-01-01

    The Liquid Fly-Back Booster (LFBB) Program seeks to enhance the Space Shuttle system safety, performance and economy of operations through the use of an advanced, liquid propellant Booster Main Engine (BME). There are several viable BME candidates that could be suitable for this application. The objective of this study was to identify the key Criteria to be applied in selecting among these BME candidates. This study involved an assessment of influences on the overall LFBB utility due to variations in the candidate rocket-engines characteristics. This includes BME impacts on vehicle system weight, performance, design approaches, abort modes, margins of safety, engine-out operations, and maintenance and support concepts. Systems engineering analyses and trade studies were performed to identify the LFBB system level sensitivities to a wide variety of BME related parameters. This presentation summarizes these trade studies and the resulting findings of the LFBB design teams regarding the BME characteristics that most significantly affect the LFBB system. The resulting BME choice should offer the best combination of reliability, performance, reusability, robustness, cost, and risk for the LFBB program.

  16. Booster Main Engine Selection Criteria for the Liquid Fly-Back Booster

    NASA Technical Reports Server (NTRS)

    Ryan, Richard M.; Rothschild, William J.; Christensen, David L.

    1998-01-01

    The Liquid Fly-Back Booster (LFBB) Program seeks to enhance the Space Shuttle system safety performance and economy of operations through the use of an advanced, liquid propellant Booster Main Engine (BME). There are several viable BME candidates that could be suitable for this application. The objective of this study was to identify the key criteria to be applied in selecting among these BME candidates. This study involved an assessment of influences on the overall LFBB utility due to variations in the candidate rocket engines' characteristics. This includes BME impacts on vehicle system weight, perfortnance,design approaches, abort modes, margins of safety, engine-out operations, and maintenance and support concepts. Systems engineering analyses and trade studies were performed to identify the LFBB system level sensitivities to a wide variety of BME related parameters. This presentation summarizes these trade studies and the resulting findings of the LFBB design teams regarding the BME characteristics that most significantly affect the LFBB system. The resulting BME choice should offer the best combination of reliability, performance, reusability, robustness, cost, and risk for the LFBB program.

  17. IPNS enriched uranium booster target

    SciTech Connect

    Schulke, A.W. Jr.

    1985-01-01

    Since startup in 1981, IPNS has operated on a fully depleted /sup 238/U target. With the booster as in the present system, high energy protons accelerated to 450 MeV by the Rapid Cycling Synchrotron are directed at the target and by mechanisms of spallation and fission of the uranium, produce fast neutrons. The neutrons from the target pass into adjacent moderator where they slow down to energies useful for spectroscopy. The target cooling systems and monitoring systems have operated very reliably and safely during this period. To provide higher neutron intensity, we have developed plans for an enriched uranium (booster) target. HETC-VIM calculations indicate that the target will produce approx.90 kW of heat, with a nominal x5 gain (k/sub eff/ = 0.80). The neutron beam intensity gain will be a factor of approx.3. Thermal-hydraulic and heat transport calculations indicate that approx.1/2 in. thick /sup 235/U discs are subject to about the same temperatures as the present /sup 238/U 1 in. thick discs. The coolant will be light demineralized water (H/sub 2/O) and the coolant flow rate must be doubled. The broadening of the fast neutron pulse width should not seriously affect the neutron scattering experiments. Delayed neutrons will appear at a level about 3% of the total (currently approx.0.5%). This may affect backgrounds in some experiments, so that we are assessing measures to control and correct for this (e.g., beam tube choppers). Safety analyses and neutronic calculations are nearing completion. Construction of the /sup 235/U discs at the ORNL Y-12 facility is scheduled to begin late 1985. The completion of the booster target and operation are scheduled for late 1986. No enriched uranium target assembly operating at the projected power level now exists in the world. This effort thus represents an important technological experiment as well as being a ''flux enhancer''.

  18. Progress with the AGS Booster

    SciTech Connect

    Weng, W.T.

    1988-01-01

    Rare K-decay, neutrino and heavy ion physics demands that a rapid- cycling high vacuum and high intensity Booster be built for the AGS at Brookhaven. For each mode of operation there are corresponding accelerator physics and design issues needing special attention. Problems pertinent to any single mode of operation have been encountered and solved before, but putting high intensity proton requirements and high vacuum heavy ion requirements into one machine demands careful design considerations and decisions. The lattice design and magnet characteristics will be briefly reviewed. Major design issues will be discussed and design choices explained. Finally, the construction status and schedule will be presented. 6 refs., 6 figs.

  19. Booster double harmonic setup notes

    SciTech Connect

    Gardner, C. J.

    2015-02-17

    The motivation behind implementing a booster double harmonic include the reduced transverse space charge force from a reduced peak beam current and reduced momentum spread of the beam, both of which can be achieved from flattening the RF bucket. RF capture and acceleration of polarized protons (PP) is first set up in the single harmonic mode with RF harmonic h=1. Once capture and acceleration have been set up in the single harmonic mode, the second harmonic system is brought on and programmed to operate in concert with the single harmonic system.

  20. GRYPHON: Air launched space booster

    NASA Technical Reports Server (NTRS)

    1993-01-01

    The project chosen for the winter semester Aero 483 class was the design of a next generation Air Launched Space Booster. Based on Orbital Sciences Corporation's Pegasus concept, the goal of Aero 483 was to design a 500,000 pound air launched space booster capable of delivering 17,000 pounds of payload to Low Earth Orbit and 8,000 pounds of payload to Geosynchronous Earth Orbit. The resulting launch vehicle was named the Gryphon. The class of forty senior aerospace engineering students was broken down into eight interdependent groups. Each group was assigned a subsystem or responsibility which then became their field of specialization. Spacecraft Integration was responsible for ensuring compatibility between subsystems. This group kept up to date on subsystem redesigns and informed those parties affected by the changes, monitored the vehicle's overall weight and dimensions, and calculated the mass properties of the booster. This group also performed the cost/profitability analysis of the Gryphon and obtained cost data for competing launch systems. The Mission Analysis Group was assigned the task of determining proper orbits, calculating the vehicle's flight trajectory for those orbits, and determining the aerodynamic characteristics of the vehicle. The Propulsion Group chose the engines that were best suited to the mission. This group also set the staging configurations for those engines and designed the tanks and fuel feed system. The commercial satellite market, dimensions and weights of typical satellites, and method of deploying satellites was determined by the Payloads Group. In addition, Payloads identified possible resupply packages for Space Station Freedom and identified those packages that were compatible with the Gryphon. The guidance, navigation, and control subsystems were designed by the Mission Control Group. This group identified required tracking hardware, communications hardware telemetry systems, and ground sites for the location of the Gryphon

  1. GRYPHON: Air launched space booster

    NASA Astrophysics Data System (ADS)

    1993-06-01

    The project chosen for the winter semester Aero 483 class was the design of a next generation Air Launched Space Booster. Based on Orbital Sciences Corporation's Pegasus concept, the goal of Aero 483 was to design a 500,000 pound air launched space booster capable of delivering 17,000 pounds of payload to Low Earth Orbit and 8,000 pounds of payload to Geosynchronous Earth Orbit. The resulting launch vehicle was named the Gryphon. The class of forty senior aerospace engineering students was broken down into eight interdependent groups. Each group was assigned a subsystem or responsibility which then became their field of specialization. Spacecraft Integration was responsible for ensuring compatibility between subsystems. This group kept up to date on subsystem redesigns and informed those parties affected by the changes, monitored the vehicle's overall weight and dimensions, and calculated the mass properties of the booster. This group also performed the cost/profitability analysis of the Gryphon and obtained cost data for competing launch systems. The Mission Analysis Group was assigned the task of determining proper orbits, calculating the vehicle's flight trajectory for those orbits, and determining the aerodynamic characteristics of the vehicle. The Propulsion Group chose the engines that were best suited to the mission. This group also set the staging configurations for those engines and designed the tanks and fuel feed system. The commercial satellite market, dimensions and weights of typical satellites, and method of deploying satellites was determined by the Payloads Group. In addition, Payloads identified possible resupply packages for Space Station Freedom and identified those packages that were compatible with the Gryphon. The guidance, navigation, and control subsystems were designed by the Mission Control Group. This group identified required tracking hardware, communications hardware telemetry systems, and ground sites for the location of the Gryphon

  2. SYNCHROTRON RADIATION MONITOR FOR NSLS BOOSTER.

    SciTech Connect

    PINAYEV, I.; SHAFTAN, T.

    2005-11-04

    NSLS booster diagnostics consisted of tune measurement system, system for turn-by-turn measurement on the electron beam, and beam intensity monitor, which is not absolutely calibrated. We present design and implementation of synchrotron light monitor for the booster, which expands diagnostics capabilities. The system allows to measure an orbit, beam sizes and coupling of the electron beam along the ramp.

  3. 47 CFR 22.527 - Signal boosters.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 47 Telecommunication 2 2011-10-01 2011-10-01 false Signal boosters. 22.527 Section 22.527 Telecommunication FEDERAL COMMUNICATIONS COMMISSION (CONTINUED) COMMON CARRIER SERVICES PUBLIC MOBILE SERVICES Paging and Radiotelephone Service § 22.527 Signal boosters. Licensees may install and operate...

  4. Booster Separation Motor (BSM) Test Fire

    NASA Technical Reports Server (NTRS)

    2007-01-01

    This photograph depicts a hot fire test of the Shuttle Booster Separation Motor (BSM) at the Marshall Space Flight Center (MSFC) test stand 116. The objective of the test was to test the aft heat seal in flight configuration. The function of the motor is to separate the Shuttle vehicle from the boosters that carry it into space.

  5. BOOSTER CHLORINATION FOR MANAGING DISINFECTANT RESIDUALS

    EPA Science Inventory

    Booster chlorination is an approach to residual maintenance in which chlorine is applied at strategic locations within the distribution system. Situations in which booster chlorination may be most effective for maintaining a residual are explained informally in the context of a ...

  6. 47 CFR 20.21 - Signal boosters.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... connection to the phone). (D) Power Limits. A booster's uplink power must not exceed 1 watt composite... at a level of +25 dBm per channel (assume a small, lightly loaded cell) and measuring the total... commercial mobile radio service system may operate a Consumer Signal Booster for personal use under...

  7. Atlas Centaur Rocket With Reusable Booster Engines

    NASA Technical Reports Server (NTRS)

    Martin, James A.

    1993-01-01

    Proposed modification of Atlas Centaur enables reuse of booster engines. Includes replacement of current booster engines with engine of new design in which hydrogen used for both cooling and generation of power. Use of hydrogen in new engine eliminates coking and clogging and improves performance significantly. Primary advantages: reduction of cost; increased reliability; and increased payload.

  8. Booster's coupled bunch damper upgrade

    SciTech Connect

    William A. Pellico and D. W. Wildman

    2003-08-14

    A new narrowband active damping system for longitudinal coupled bunch (CB) modes in the Fermilab Booster has recently been installed and tested. In the past, the Booster active damper system consisted of four independent front-ends. The summed output was distributed to the 18, h=84 RF accelerating cavities via the RF fan-out system. There were several problems using the normal fan-out system to deliver the longitudinal feedback RF. The high power RF amplifiers normally operate from 37 MHz to 53 MHz whereas the dampers operate around 83MHz. Daily variations in the tuning of the RF stations created tuning problems for the longitudinal damper system. The solution was to build a dedicated narrowband, Q {approx} 10, 83MHz cavity powered with a new 3.5kW solid-state amplifier. The cavity was installed in June 2002 and testing of the amplifier and damper front-end began in August 2002. A significant improvement has been made in both operational stability and high intensity beam damping. At present there are five CB modes being damped and a sixth mode module is being built. The new damper hardware is described and data showing the suppression of the coupled-bunch motion at high intensity is presented.

  9. Solid rocket booster retrieval operations

    NASA Technical Reports Server (NTRS)

    Rasmussen, A. M.

    1985-01-01

    Solid Rocket Booster Retrieval operations are discussed in detail. The recovery of expended boosters and associated hardware without damage attributable to retrieval procedures is the main goal. The retrieval force consists tof ship's personnel and retrieval team members, each of whom has been trained and is highly skilled in multi-faceted operations. The retrieval force is equipped with two specially-built, highly maneuverable ships outfitted with parachute reels, retrieval cranes, towing winches, large volume-low pressure air compressors, SCUBA diving gear, inflatable boats with outboard motors and diver-operated SRB dewatering devices. The two ships are deployed in sufficient time to conduct an electronic and visual search of the impact area prior to launch. Upon search completeion, each ship takes station a safe distance from the predetermined impact point initiating both visual and electronic search in the direction of flight path, ensuring SRB acquisition at splashdown. When safe, the ships enter the impact area and commence recovery of all floating flight hardware which is subsequently returned to the Disassembly Facility for refurbishment and reuse. Retrieval techniques have evolved in parallel with equipment and flight hardware configuration changes. Additional changes have been initiated to improve personnel safety.

  10. NASA's Space Launch System: Developing the World's Most Powerful Solid Booster

    NASA Technical Reports Server (NTRS)

    Priskos, Alex

    2016-01-01

    NASA's Journey to Mars has begun. Indicative of that challenge, this will be a multi-decadal effort requiring the development of technology, operational capability, and experience. The first steps are under way with more than 15 years of continuous human operations aboard the International Space Station (ISS) and development of commercial cargo and crew transportation capabilities. NASA is making progress on the transportation required for deep space exploration - the Orion crew spacecraft and the Space Launch System (SLS) heavy-lift rocket that will launch Orion and large components such as in-space stages, habitat modules, landers, and other hardware necessary for deep-space operations. SLS is a key enabling capability and is designed to evolve with mission requirements. The initial configuration of SLS - Block 1 - will be capable of launching more than 70 metric tons (t) of payload into low Earth orbit, greater mass than any other launch vehicle in existence. By enhancing the propulsion elements and larger payload fairings, future SLS variants will launch 130 t into space, an unprecedented capability that simplifies hardware design and in-space operations, reduces travel times, and enhances the odds of mission success. SLS will be powered by four liquid fuel RS-25 engines and two solid propellant five-segment boosters, both based on space shuttle technologies. This paper will focus on development of the booster, which will provide more than 75 percent of total vehicle thrust at liftoff. Each booster is more than 17 stories tall, 3.6 meters (m) in diameter and weighs 725,000 kilograms (kg). While the SLS booster appears similar to the shuttle booster, it incorporates several changes. The additional propellant segment provides additional booster performance. Parachutes and other hardware associated with recovery operations have been deleted and the booster designated as expendable for affordability reasons. The new motor incorporates new avionics, new propellant

  11. 75 FR 81662 - Agency Information Collection Activities; Submission for OMB Review; Comment Request; Affordable...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-28

    ...; Affordable Care Act Advance Notice of Rescission ACTION: Notice. SUMMARY: The Department of Labor (DOL... information collection request (ICR) titled, ``Affordable Care Act Advance Notice of Rescission,'' to the..._PRA_PUBLIC@dol.gov . SUPPLEMENTARY INFORMATION: The Patient Protection and Affordable Care Act...

  12. Space Shuttle solid rocket booster

    NASA Technical Reports Server (NTRS)

    Hardy, G. B.

    1979-01-01

    Details of the design, operation, testing and recovery procedures of the reusable solid rocket boosters (SRB) are given. Using a composite PBAN propellant, they will provide the primary thrust (six million pounds maximum at 20 s after ignition) within a 3 g acceleration constraint, as well as thrust vector control for the Space Shuttle. The drogues were tested to a load of 305,000 pounds, and the main parachutes to 205,000. Insulation in the solid rocket motor (SRM) will be provided by asbestos-silica dioxide filled acrylonitrile butadiene rubber ('asbestos filled NBR') except in high erosion areas (principally in the aft dome), where a carbon-filled ethylene propylene diene monomer-neopreme rubber will be utilized. Furthermore, twenty uses for the SRM nozzle will be allowed by its ablative materials, which are principally carbon cloth and silica cloth phenolics.

  13. Shuttle Upgrade Using 5-Segment Booster (FSB)

    NASA Technical Reports Server (NTRS)

    Sauvageau, Donald R.; Huppi, Hal D.; McCool, A. A. (Technical Monitor)

    2000-01-01

    In support of NASA's continuing effort to improve the over-all safety and reliability of the Shuttle system- a 5-segment booster (FSB) has been identified as an approach to satisfy that overall objective. To assess the feasibility of a 5-segment booster approach, NASA issued a feasibility study contract to evaluate the potential of a 5-segment booster to improve the overall capability of the Shuttle system, especially evaluating the potential to increase the system reliability and safety. In order to effectively evaluate the feasibility of the 5-segment concept, a four-member contractor team was established under the direction of NASA Marshall Space Flight Center (MSFC). MSFC provided the overall program oversight and integration as well as program contractual management. The contractor team consisted of Thiokol, Boeing North American Huntington Beach (BNA), Lockheed Martin Michoud Space Systems (LMMSS) and United Space Alliance (USA) and their subcontractor bd Systems (Control Dynamics Division, Huntsville, AL). United Space Alliance included the former members of United Space Booster Incorporated (USBI) who managed the booster element portion of the current Shuttle solid rocket boosters. Thiokol was responsible for the overall integration and coordination of the contractor team across all of the booster elements. They were also responsible for all of the motor modification evaluations. Boeing North American (BNA) was responsible for all systems integration analyses, generation of loads and environments. and performance and abort mode capabilities. Lockheed Martin Michoud Space Systems (LMMSS) was responsible for evaluating the impacts of any changes to the booster on the external tank (ET), and evaluating any design changes on the external tank necessary to accommodate the FSB. USA. including the former USBI contingent. was responsible for evaluating any modifications to facilities at the launch site as well as any booster component design modifications.

  14. Five-Segment Reusable Solid Rocket Booster Upgrade

    NASA Technical Reports Server (NTRS)

    Sauvageau, Don

    1999-01-01

    The Five Segment Reusable Solid Rocket Booster (RSRB) feasibility status is presented in viewgraph form. The Five Segment Booster (FSB) objective is to provide a low cost, low risk approach to increase reliability and safety of the Shuttle system. Topics include: booster upgrade requirements; design summary; reliability issues; booster trajectories; launch site assessment; and enhanced abort modes.

  15. Crucial Booster Test Fires Up in Utah

    NASA Video Gallery

    A booster for the most powerful rocket in the world, NASA’s Space Launch System (SLS), successfully fired up Tuesday for its second qualification ground test at Orbital ATK's test facilities in Pro...

  16. Booster 6-GeV study

    SciTech Connect

    Yang, Xi; Ankenbrandt, Charles M.; Pellico, William A.; Lackey, James; Padilla, Rene; Norem, J.; /Argonne

    2004-12-01

    Since a wider aperture has been obtained along the Booster beam line, this opens the opportunity for Booster running a higher intensity beam than ever before. Sooner or later, the available RF accelerating voltage will become a new limit for the beam intensity. Either by increasing the RFSUM or by reducing the accelerating rate can achieve the similar goal. The motivation for the 6-GeV study is to gain the relative accelerating voltage via a slower acceleration.

  17. Space shuttle booster separation motor design

    NASA Technical Reports Server (NTRS)

    Smith, G. W.; Chase, C. A.

    1976-01-01

    The separation characteristics of the space shuttle solid rocket boosters (SRBs) are introduced along with the system level requirements for the booster separation motors (BSMs). These system requirements are then translated into specific motor requirements that control the design of the BSM. Each motor component is discussed including its geometry, material selection, and fabrication process. Also discussed is the propellant selection, grain design, and performance capabilities of the motor. The upcoming test program to develop and qualify the motor is outlined.

  18. Local leadership and the Affordable Care Act.

    PubMed

    Williams, Stephen L; Nichols, Beverly L; Barton, M Katherine; De LaCruz, Maria; Hernandez, Benjamin

    2015-01-01

    Local health departments are in key positions to lead in the education and implementation efforts to advance the Patient Protection and Affordable Care Act. The first enrollment period is over, but the efforts to enroll the uninsured and advocate for expansion of Medicaid in the states that have not yet taken on this expansion will continue for years to come. Political climates may be unsupportive, but some actions may still be possible. PMID:25423062

  19. Pyro thruster for performing rocket booster attachment, disconnect, and jettison functions

    NASA Technical Reports Server (NTRS)

    Hornyak, Stephen

    1989-01-01

    The concept of a pyro thruster, combining an automatic structural attachment with quick disconnect and thrusting capability, is described. The purpose of the invention is to simplify booster installation, disengagement, and jettison functions for the U.S. Air Force Advanced Launch Systems (ALS) program.

  20. Survey and alignment of the Fermilab Booster Accelerator

    SciTech Connect

    Oshinowo, Babatunde O'Sheg; Kyle, John; /Fermilab

    2005-07-01

    The Fermilab Booster is a fast-cycling synchrotron which accelerates protons from 400 MeV to 8 GeV of kinetic energy for injection into the Main Injector and for use by all of the Lab's physics programs. The Booster was originally built in 1970. In 2004, as part of the Booster upgrade, a decision was made to upgrade the Booster survey network by densification with monuments and to survey the main Booster components using modern survey and alignment instruments. This paper discusses the survey and alignment methodology employed for the Booster Accelerator upgrade.

  1. Synchronization of the Fermilab Booster and Main Injector for multiple batch injection

    SciTech Connect

    Robert Zwaska et al.

    2004-07-09

    To date, the 120 GeV Fermilab Main Injector accelerator has accelerated a single batch of protons from the 8 GeV rapid-cycling Booster synchrotron for production of antiprotons for Run II. In the future, the Main Injector must accelerate 6 or more Booster batches simultaneously; the first will be extracted to the antiproton source, while the remaining are extracted for the NuMI/MINOS (Neutrinos at the Main Injector/Main Injector Neutrino Oscillation Search) neutrino experiment. Performing this multi-batch operation while avoiding unacceptable radioactivation of the beamlines requires a previously unnecessary synchronization between the accelerators. We describe a mechanism and present results of advancing or retarding the longitudinal progress of the Booster beam by active feedback radial manipulation of the beam during the acceleration period.

  2. Solid Rocket Booster Structural Test Article

    NASA Technical Reports Server (NTRS)

    1978-01-01

    The structural test article to be used in the solid rocket booster (SRB) structural and load verification tests is being assembled in a high bay building of the Marshall Space Flight Center (MSFC). The Shuttle's two SRB's are the largest solids ever built and the first designed for refurbishment and reuse. Standing nearly 150-feet high, the twin boosters provide the majority of thrust for the first two minutes of flight, about 5.8 million pounds, augmenting the Shuttle's main propulsion system during liftoff. The major design drivers for the solid rocket motors (SRM's) were high thrust and reuse. The desired thrust was achieved by using state-of-the-art solid propellant and by using a long cylindrical motor with a specific core design that allows the propellant to burn in a carefully controlled marner. At burnout, the boosters separate from the external tank and drop by parachute to the ocean for recovery and subsequent refurbishment.

  3. Summary of Booster Development and Qualification Report

    SciTech Connect

    Francois, Elizabeth G.; Harry, Herbert H.; Hartline, Ernest L.; Hooks, Daniel E.; Johnson, Carl E.; Morris, John S.; Novak, Alan M.; Ramos, Kyle J.; Sanders, Victor E.; Scovel, Christina A.; Lorenz, Thomas; Wright, Mark; Botcher, Tod; Marx, Erin; Gibson, Kevin

    2012-06-21

    This report outlines booster development work done at Los Alamos National Laboratory from 2007 to present. The booster is a critical link in the initiation train of explosive assemblies, from complex devices like nuclear weapons to conventional munitions. The booster bridges the gap from a small, relatively sensitive detonator to an insensitive, but massive, main charge. The movement throughout the explosives development community is to use more and more insensitive explosive components. With that, more energy is needed out of the booster. It has to initiate reliably, promptly, powerfully and safely. This report is divided into four sections. The first provides a summary of a collaborative effort between LANL, LLNL, and AWE to identify candidate materials and uniformly develop a testing plan for new boosters. Important parameters and the tests required to measure them were defined. The nature of the collaboration and the specific goals of the participating partners has changed over time, but the booster development plan stands on its own merit as a complete description of the test protocol necessary to compare and qualify booster materials, and is discussed in its entirety in this report. The second section describes a project, which began in 2009 with the Department of Defense to develop replacement booster formulations for PBXN-7. Replacement of PBXN-7 was necessary because it contained Triaminotrinitrobenzene (TATB), which was becoming unavailable to the DoD and because it contained Cyclotrimethylenetrinitramine (RDX), which was sensitive and toxic. A LANL-developed explosive, Diaminoazoxyfurazan (DAAF), was an important candidate. This project required any replacement formulation be a drop-in replacement in existing munitions. This project was timely, in that it made use of the collaborative booster development project, and had the additional constraint of matching shock sensitivity. Additionally it needed to be a safety improvement, and a performance

  4. Space Shuttle Solid Rocket Booster Lightweight Recovery System

    NASA Technical Reports Server (NTRS)

    Wolf, Dean; Runkle, Roy E.

    1995-01-01

    The cancellation of the Advanced Solid Rocket Booster Project and the earth-to-orbit payload requirements for the Space Station dictated that the National Aeronautics and Space Administration (NASA) look at performance enhancements from all Space Transportation System (STS) elements (Orbiter Project, Space Shuttle Main Engine Project, External Tank Project, Solid Rocket Motor Project, & Solid Rocket Booster Project). The manifest for launching of Space Station components indicated that an additional 12-13000 pound lift capability was required on 10 missions and 15-20,000 pound additional lift capability is required on two missions. Trade studies conducted by all STS elements indicate that by deleting the parachute Recovery System (and associated hardware) from the Solid Rocket Boosters (SRBS) and going to a lightweight External Tank (ET) the 20,000 pound additional lift capability can be realized for the two missions. The deletion of the parachute Recovery System means the loss of four SRBs and this option is two expensive (loss of reusable hardware) to be used on the other 10 Space Station missions. Accordingly, each STS element looked at potential methods of weight savings, increased performance, etc. As the SRB and ET projects are non-propulsive (i.e. does not have launch thrust elements) their only contribution to overall payload enhancement can be achieved by the saving of weight while maintaining adequate safety factors and margins. The enhancement factor for the SRB project is 1:10. That is for each 10 pounds saved on the two SRBS; approximately 1 additional pound of payload in the orbiter bay can be placed into orbit. The SRB project decided early that the SRB recovery system was a prime candidate for weight reduction as it was designed in the early 1970s and weight optimization had never been a primary criteria.

  5. Beam Diagnosis and Lattice Modeling of the Fermilab Booster

    SciTech Connect

    Huang, Xiaobiao

    2005-09-01

    A realistic lattice model is a fundamental basis for the operation of a synchrotron. In this study various beam-based measurements, including orbit response matrix (ORM) and BPM turn-by-turn data are used to verify and calibrate the lattice model of the Fermilab Booster. In the ORM study, despite the strong correlation between the gradient parameters of adjacent magnets which prevents a full determination of the model parameters, an equivalent lattice model is obtained by imposing appropriate constraints. The fitted gradient errors of the focusing magnets are within the design tolerance and the results point to the orbit offsets in the sextupole field as the source of gradient errors. A new method, the independent component analysis (ICA) is introduced to analyze multiple BPM turn-by-turn data taken simultaneously around a synchrotron. This method makes use of the redundancy of the data and the time correlation of the source signals to isolate various components, such as betatron motion and synchrotron motion, from raw BPM data. By extracting clean coherent betatron motion from noisy data and separates out the betatron normal modes when there is linear coupling, the ICA method provides a convenient means to measure the beta functions and betatron phase advances. It also separates synchrotron motion from the BPM samples for dispersion function measurement. The ICA method has the capability to separate other perturbation signals and is robust over the contamination of bad BPMs. The application of the ICA method to the Booster has enabled the measurement of the linear lattice functions which are used to verify the existing lattice model. The transverse impedance and chromaticity are measured from turn-by-turn data using high precision tune measurements. Synchrotron motion is also observed in the BPM data. The emittance growth of the Booster is also studied by data taken with ion profile monitor (IPM). Sources of emittance growth are examined and an approach to cure

  6. 5. VIEW OF BOOSTER STATION 2, FACING SOUTHEAST Nevada ...

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

    5. VIEW OF BOOSTER STATION 2, FACING SOUTHEAST - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

  7. Credit BG. Interior of Deluge Water Booster Station displaying highcapacity ...

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

    Credit BG. Interior of Deluge Water Booster Station displaying high-capacity electrically driven water pumps for fire fighting service - Edwards Air Force Base, North Base, Deluge Water Booster Station, Northeast of A Street, Boron, Kern County, CA

  8. 47 CFR 90.219 - Use of signal boosters.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... narrowband channel that the booster is designed to amplify. Class B broadband signal boosters must meet the... equipment may cause to other systems. Normal co-channel transmissions will not be considered as...

  9. 47 CFR 90.219 - Use of signal boosters.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... narrowband channel that the booster is designed to amplify. Class B broadband signal boosters must meet the... equipment may cause to other systems. Normal co-channel transmissions will not be considered as...

  10. 47 CFR 90.219 - Use of signal boosters.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... narrowband channel that the booster is designed to amplify. Class B broadband signal boosters must meet the... equipment may cause to other systems. Normal co-channel transmissions will not be considered as...

  11. 6. VIEW OF BOOSTER STATION 2 INTERIOR, FACING WEST ...

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

    6. VIEW OF BOOSTER STATION 2 INTERIOR, FACING WEST - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

  12. 3. VIEW OF BOOSTER STATION 1 INTERIOR, FACING EAST ...

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

    3. VIEW OF BOOSTER STATION 1 INTERIOR, FACING EAST - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

  13. 2. VIEW OF BOOSTER STATION 1, FACING NORTHEAST Nevada ...

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

    2. VIEW OF BOOSTER STATION 1, FACING NORTHEAST - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

  14. 4. VIEW OF BOOSTER STATION 2, FACING NORTHWEST Nevada ...

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

    4. VIEW OF BOOSTER STATION 2, FACING NORTHWEST - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

  15. 10. VIEW OF BOOSTER STATION 4, FACING NORTHWEST Nevada ...

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

    10. VIEW OF BOOSTER STATION 4, FACING NORTHWEST - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

  16. 9. VIEW OF BOOSTER STATION 3 INTERIOR, FACING NORTHEAST ...

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

    9. VIEW OF BOOSTER STATION 3 INTERIOR, FACING NORTHEAST - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

  17. 1. VIEW OF BOOSTER STATION 1, FACING SOUTHWEST Nevada ...

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

    1. VIEW OF BOOSTER STATION 1, FACING SOUTHWEST - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

  18. 12. VIEW OF BOOSTER STATION 4 INTERIOR, FACING SOUTHWEST ...

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

    12. VIEW OF BOOSTER STATION 4 INTERIOR, FACING SOUTHWEST - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

  19. 7. VIEW OF BOOSTER STATION 3, FACING NORTHWEST Nevada ...

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

    7. VIEW OF BOOSTER STATION 3, FACING NORTHWEST - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

  20. 8. VIEW OF BOOSTER STATION 3, FACING SOUTHEAST Nevada ...

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

    8. VIEW OF BOOSTER STATION 3, FACING SOUTHEAST - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

  1. 11. VIEW OF BOOSTER STATION 4, FACING SOUTHEAST Nevada ...

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

    11. VIEW OF BOOSTER STATION 4, FACING SOUTHEAST - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

  2. 13. VIEW OF BOOSTER STATION 4 CHLORINATOR INTERIOR, FACING NORTH ...

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

    13. VIEW OF BOOSTER STATION 4 CHLORINATOR INTERIOR, FACING NORTH - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

  3. Radiation issues in the Fermilab booster magnets

    SciTech Connect

    Prebys, E.; /Fermilab

    2005-05-01

    The demands of the Fermilab neutrino program will require the lab's 30+ year old 8 GeV Booster to deliver higher intensities than it ever has. Total proton throughput is limited by radiation damage and activation due to beam loss in the Booster tunnel. Of particular concern is the epoxy resin that acts as the insulation in the 96 combined function lattice magnets. This paper describes a simulation study to determine the integrated radiation dose to this epoxy and a discussion of the potential effects.

  4. Booster propulsion/vehicle impact study

    NASA Technical Reports Server (NTRS)

    Weldon, Vincent; Dunn, Michael; Fink, Lawrence; Phillips, Dwight; Wetzel, Eric

    1988-01-01

    The use of hydrogen RP-1, propane, and methane as fuels for booster engines of launch vehicles is discussed. An automated procedure for integrated launch vehicle, engine sizing, and design optimization was used to define two stage and single stage concepts for minimum dry weight. The two stage vehicles were unmanned and used a flyback booster and partially reusable orbiter. The single stage designs were fully reusable, manned flyback vehicles. Comparisons of these vehicle designs, showing the effects of using different fuels, as well as sensitivity and trending data, are presented. In addition, the automated design technique utilized for the study is described.

  5. Automated Euler and Navier-Stokes Database Generation for a Glide-Back Booster

    NASA Technical Reports Server (NTRS)

    Chaderjian, Neal M.; Rogers, Stuart E.; Aftosmis, Mike J.; Pandya, Shishir A.; Ahmad, Jasim U.; Tejnil, Edward

    2004-01-01

    The past two decades have seen a sustained increase in the use of high fidelity Computational Fluid Dynamics (CFD) in basic research, aircraft design, and the analysis of post-design issues. As the fidelity of a CFD method increases, the number of cases that can be readily and affordably computed greatly diminishes. However, computer speeds now exceed 2 GHz, hundreds of processors are currently available and more affordable, and advances in parallel CFD algorithms scale more readily with large numbers of processors. All of these factors make it feasible to compute thousands of high fidelity cases. However, there still remains the overwhelming task of monitoring the solution process. This paper presents an approach to automate the CFD solution process. A new software tool, AeroDB, is used to compute thousands of Euler and Navier-Stokes solutions for a 2nd generation glide-back booster in one week. The solution process exploits a common job-submission grid environment, the NASA Information Power Grid (IPG), using 13 computers located at 4 different geographical sites. Process automation and web-based access to a MySql database greatly reduces the user workload, removing much of the tedium and tendency for user input errors. The AeroDB framework is shown. The user submits/deletes jobs, monitors AeroDB's progress, and retrieves data and plots via a web portal. Once a job is in the database, a job launcher uses an IPG resource broker to decide which computers are best suited to run the job. Job/code requirements, the number of CPUs free on a remote system, and queue lengths are some of the parameters the broker takes into account. The Globus software provides secure services for user authentication, remote shell execution, and secure file transfers over an open network. AeroDB automatically decides when a job is completed. Currently, the Cart3D unstructured flow solver is used for the Euler equations, and the Overflow structured overset flow solver is used for the

  6. Closeup view of the Solid Rocket Booster Frustum and Nose ...

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

    Close-up view of the Solid Rocket Booster Frustum and Nose Cap assembly undergoing preparations and close-out procedures in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center. The Nose Cap contains the Pilot and Drogue Chutes and the Frustum contains the three Main Parachutes, Altitude Switches and forward booster Separation Motors. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

  7. Electron cloud in the Fermilab Booster

    SciTech Connect

    Ng, K.Y.; /Fermilab

    2007-06-01

    Simulations of the Fermilab Booster reveal a substantial electron-cloud buildup both inside the unshielded combined-function magnets and the beam pipes joining the magnets, when the second-emission yield (SEY) is larger than {approx}1.6. The implication of the electron-cloud effects on space charge and collective instabilities of the beam is discussed.

  8. What A Booster Club Can Do.

    ERIC Educational Resources Information Center

    Hidinger, George

    This speech was presented at the 1976 American Alliance for Health, Physical Education, and Recreation national convention by the principal of an Iowa high school. It discusses the development and effectiveness of the Jefferson High School Booster Club which was developed by an interested parent and has been quite successful. The club has assisted…

  9. Magnetic Booster Fast Ignition Macron Accelerator

    SciTech Connect

    Friedwardt Winterberg

    2007-10-01

    Fast Impact ignition using the magnetic booster target concept is studied for isentropic compression and for thermonuclear micro-detonation. Fast ignition of a dense beam-magnetized cylindrical pure D target by multi-megampere GeV proton beams generated with a Super Marx Generator is studied. Shear flow stabilization of think cylindrical axial current confined DT detonation targets.

  10. Implementing radial motion to the booster simulation

    SciTech Connect

    Yang, Xi; /Fermilab

    2007-04-01

    It's a puzzle that high intensity beams prefer a particular radial motion during transition in the Booster, and the result of removing such a radial motion is to increase the transition loss. In order to understand this observation, the radial motion should be taken into account in the longitudinal simulation.

  11. Spacecraft and their Boosters. Aerospace Education I.

    ERIC Educational Resources Information Center

    Coard, E. A.

    This book, one in the series on Aerospace Education I, provides a description of some of the discoveries that spacecraft have made possible and of the experience that American astronauts have had in piloting spacecraft. The basic principles behind the operation of spacecraft and their boosters are explained. Descriptions are also included on…

  12. Officials Stand Before Mercury-Redstone Booster

    NASA Technical Reports Server (NTRS)

    2004-01-01

    This photograph shows a group of officials standing before a Mercury-Redstone booster at the Marshall Space Flight Center (MSFC). Among those in the photograph are astronauts James Lovell, Walter Schirra, and Gus Grissom. Also pictured is Joachim Kuettner who managed responsibilities of MSFC's Mercury-Redstone program.

  13. 78 FR 29062 - Signal Booster Rules

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-17

    ... FR 21555, April 11, 2013, a document in the Signal Boosters proceeding, WT Docket No. 10-4, which... 78 FR 21555, April 11, 2013 regarding certain FCC rules governing radiofrequency radiation exposure... Register of 78 FR 21555, April 11, 2013. This document does not change any of the other rule amendments...

  14. Expendable second stage reusable space shuttle booster. Volume 2: Technical summary. Book 3: Booster vehicle modifications and ground systems definition

    NASA Technical Reports Server (NTRS)

    1972-01-01

    A definition of the expendable second stage and space shuttle booster separation system is presented. Modifications required on the reusable booster for expendable second stage/payload flight and the ground systems needed to operate the expendable second stage in conjuction with the space shuttle booster are described. The safety, reliability, and quality assurance program is explained. Launch complex operations and services are analyzed.

  15. Pressure-Equalizing Cradle for Booster Rocket Mounting

    NASA Technical Reports Server (NTRS)

    Rutan, Elbert L. (Inventor)

    2015-01-01

    A launch system and method improve the launch efficiency of a booster rocket and payload. A launch aircraft atop which the booster rocket is mounted in a cradle, is flown or towed to an elevation at which the booster rocket is released. The cradle provides for reduced structural requirements for the booster rocket by including a compressible layer, that may be provided by a plurality of gas or liquid-filled flexible chambers. The compressible layer contacts the booster rocket along most of the length of the booster rocket to distribute applied pressure, nearly eliminating bending loads. Distributing the pressure eliminates point loading conditions and bending moments that would otherwise be generated in the booster rocket structure during carrying. The chambers may be balloons distributed in rows and columns within the cradle or cylindrical chambers extending along a length of the cradle. The cradle may include a manifold communicating gas between chambers.

  16. Tune measurement in the NSLS booster synchrotron

    SciTech Connect

    Blum, E.B.; Nawrocky, R.

    1993-07-01

    The NSLS booster synchrotron can accelerate an electron beam from approximately 80 to 750 MeV in 0.7 sec. The betatron tunes can change during acceleration by as much as 0.1 units, causing beam loss as they cross resonance lines. Precise measurements with a conventional swept spectrum analyzer have always been difficult because of the rapid variation of tune as the magnets are ramped. We are now using a system based on a Tektronix 3052 digital spectrum analyzer that can obtain a complete frequency spectrum over a 10 MHz bandwidth in 200 {mu}sec. Betatron oscillations are stimulated for the measurements by applying white noise to the beam through stripline electrodes. We will describe the instrumentation, our measurements of tune as a function time during the acceleration cycle, and the resulting improvements to the booster operation.

  17. Numerically controlled oscillator for the Fermilab booster

    SciTech Connect

    Crisp, J.L.; Ducar, R.J.

    1989-04-01

    In order to improve the stability of the Fermilab Booster low level rf system, a numerically controlled oscillator system is being constructed. Although the system has not been implemented to date, the design is outlined in this paper. The heart of the new system consists of a numerically synthesized frequency generator manufactured by the Sciteq Company. The 3 Ghz/sec rate and 30 to 53 MHz range of the Booster frequency program required the design of a CAMAC based, fast-cycling (1 MHz), 65K X 32 bit, digital function generator. A 1 MHz digital adder and 12 bit analog to digital converter will be used to correct small program errors by phase locking the oscillator to the beam. 6 refs., 1 fig.

  18. Shuttle Liquid Fly Back Booster Configuration Options

    NASA Technical Reports Server (NTRS)

    Healy, T. J., Jr.

    1998-01-01

    This paper surveys the basic configuration options available to a Liquid Fly Back Booster (LFBB), integrated with the Space Shuttle system. The background of the development of the LFBB concept is given. The influence of the main booster engine (BME) installations and the Fly Back Engine (FBE) installation on the aerodynamic configurations are also discussed. Limits on the LFBB configuration design space imposed by the existing Shuttle flight and ground elements are also described. The objective of the paper is to put the constrains and design space for an LFBB in perspective. The object of the work is to define LFBB configurations that significantly improve safety, operability, reliability and performance of the Shuttle system and dramatically lower operations costs.

  19. Shuttle Liquid Fly Back Booster Configuration Options

    NASA Technical Reports Server (NTRS)

    Healy, Thomas J., Jr.

    1998-01-01

    This paper surveys the basic configuration options available to a Liquid Fly Back Booster (LFBB), integrated with the Space Shuttle system. The background of the development of the LFBB concept is given. The influence of the main booster engine (BME) installations and the fly back engine (FBE) installation on the aerodynamic configurations are also discussed. Limits on the LFBB configuration design space imposed by the existing Shuttle flight and ground elements are also described. The objective of the paper is to put the constrains and design space for an LFBB in perspective. The object of the work is to define LFBB configurations that significantly improve safety, operability, reliability and performance of the Shuttle system and dramatically lower operations costs.

  20. Development of Cogging at the Fermilab Booster

    SciTech Connect

    Seiya, K.; Chaurize, S.; Drennan, C.; Pellico, W.; Triplett, A. K.; Waller, A.

    2015-01-30

    The development of magnetic cogging is part of the Fermilab Booster upgrade within the Proton Improvement Plan (PIP). The Booster is going to send 2.25E17 protons/hour which is almost double the present flux, 1.4E17 protons/hour to the Main Injector (MI) and Recycler (RR). The extraction kicker gap has to synchronize to the MI and RR injection bucket in order to avoid a beam loss at the rising edge of the extraction and injection kickers. Magnetic cogging is able to control the revolution frequency and the position of the gap using the magnetic field from dipole correctors while radial position feedback keeps the beam at the central orbit. The new cogging is expected to reduce beam loss due to the orbit changes and reduce beam energy loss when the gap is created. The progress of the magnetic cogging system development is going to be discussed in this paper.

  1. The AGS Booster Beam Position Monitor system

    SciTech Connect

    Ciardullo, D.J.; Abola, A.; Beadle, E.R.; Smith, G.A.; Thomas, R.; Van Zwienen, W.; Warkentien, R.; Witkover, R.L.

    1991-01-01

    To accelerate both protons and heavy ions, the AGS Booster requires a broadband (multi-octave) beam position monitoring system with a dynamic range spanning several orders of magnitude (2 {times} 10{sup 10} to 1.5 {times} 10{sup 13} particles per pulse). System requirements include the ability to acquire single turn trajectory and average orbit information with {plus minus} 0.1 mm resolution. The design goal of {plus minus} 0.5 mm corrected accuracy requires that the detectors have repeatable linear performance after periodic bakeout at 300 {degree}C. The system design and capabilities of the Booster Beam Position Monitor will be described, and initial results presented. 7 refs., 5 figs.

  2. An affordable humanitarian mine detector

    NASA Astrophysics Data System (ADS)

    Daniels, David J.; Curtis, Paul; Amin, Rajan; Dittmer, Jon

    2004-09-01

    This paper describes the further development of the MINETECT affordable humanitarian mine detector produced by ERA Technology with sponsorship from the UK Department for International Development. Using a radically different patented approach from conventional ground penetrating radar (GPR) designs in terms of the man machine interface, MINETECT offers simplicity of use and affordability, both key factors in humanitarian demining operations. Following trials in 2002 and reported at SPIE 2002, further development work including research on classifying mines, based on data from planned trials in the United Kingdom, is presented. MINETECT has the capability of detecting completely non-metallic mines and offers a considerable improvement in hand-held mine detection.

  3. Results from the AGS Booster transverse damper

    SciTech Connect

    Russo, D.; Brennan, M.; Meth, M.; Roser, T.

    1993-01-01

    To reach the design intensity of 1.5 [times] 10[sup 13] protons per pulse in the AGS Booster, transverse coupled bunch instabilities with an estimated growth rate of 1500s[sup [minus]1] have to be dampened. A prototype transverse damper has been tested successfully using a one turn digital delay and closed orbit suppression implemented in a programmable gate array. An updated damper, which includes an algorithm to optimize damping for a changing betatron rune, will also be presented.

  4. Results from the AGS Booster transverse damper

    SciTech Connect

    Russo, D.; Brennan, M.; Meth, M.; Roser, T.

    1993-06-01

    To reach the design intensity of 1.5 {times} 10{sup 13} protons per pulse in the AGS Booster, transverse coupled bunch instabilities with an estimated growth rate of 1500s{sup {minus}1} have to be dampened. A prototype transverse damper has been tested successfully using a one turn digital delay and closed orbit suppression implemented in a programmable gate array. An updated damper, which includes an algorithm to optimize damping for a changing betatron rune, will also be presented.

  5. Solid rocket booster water impact test

    NASA Technical Reports Server (NTRS)

    Bugg, F.

    1982-01-01

    Water impact drop tests were performed on the space shuttle solid rocket boosters (SRB). Peak water impact pressures and pressure/time traces were measured for various impact velocities using a two-dimensional, full-scale SRB aft skirt internal ring model. Passive burst disc-type pressure transducers were calibrated for use on flight SRB's. The effects on impact pressure of small ring configuration changes and application of thermal protection system cork layers were found to be negligible.

  6. SNS RING STUDY AT THE AGS BOOSTER.

    SciTech Connect

    ZHANG, S.Y.; AHRENS, L.; BEEBE-WANG, J.; BLASKIEWICZ, M.; FEDOTOV, A.; GARDNER, C.; LEE, Y.Y.; LUCCIO, A.; MALITSKY, N.; ROSER, T.; WENG, W.T.; WEI, J.; ZENO, K.; REECE, K.; WANG, J.G.

    2000-06-30

    During the g-2 run at the BNL AGS in early 2000, a 200 MeV storage-ring-like magnetic cycle has been set-up and tuned at the Booster in preparing for the Spallation Neutron Source (SNS) accumulator ring study. In this article, we report the progress of the machine set-up, tuning, some preliminary studies, and the future plan.

  7. LMFBR with booster pump in pumping loop

    DOEpatents

    Rubinstein, H.J.

    1975-10-14

    A loop coolant circulation system is described for a liquid metal fast breeder reactor (LMFBR) utilizing a low head, high specific speed booster pump in the hot leg of the coolant loop with the main pump located in the cold leg of the loop, thereby providing the advantages of operating the main pump in the hot leg with the reliability of cold leg pump operation.

  8. Engine protection system for recoverable rocket booster

    NASA Technical Reports Server (NTRS)

    Shelby, Jr., Jerry A. (Inventor)

    1994-01-01

    A rocket engine protection system for a recoverable rocket booster which is arranged to land in a salt water body in substantially a nose down attitude. The system includes an inflatable bag which is stowed on a portion of a flat annular rim of the aft skirt of the booster. The bag is hinged at opposing sides and is provided with springs that urge the bag open. The bag is latched in a stowed position during launch and prior to landing for recovery is unlatched to permit the bag to be urged open and into sealing engagement with the rim. A source of pressurized gas further inflates the bag and urges it into sealing engagement with the rim of the skirt where it is locked into position. The gas provides a positive pressure upon the interior of the bag to preclude entry of salt water into the skirt and into contact with the engine. A flotation arrangement may assist in precluding the skirt of the booster from becoming submerged.

  9. Momentum Cogging at the Fermilab Booster

    SciTech Connect

    Seiya, K.; Drennan, C.; Pellico, W.A.; Triplett, K.; Waller, A.; /Fermilab

    2012-05-01

    The Fermilab Booster has an upgrade plan called the Proton Improvement Plan (PIP). The flux throughput goal is 2E17 protons/hour which, is almost double the present flux, 1.1E17 protons/hour. The beam loss in the machine is going to be an issue. The Booster accelerates beam from 400 MeV to 8 GeV and extracts to the Main Injector (MI). The current cogging process synchronizes the extraction kicker gap to the MI by changing radial position of the beam during the cycle. The gap creation occurs at about 700 MeV, which is about 6 ms into the cycle. The cycle-to-cycle variations of the Booster are larger at lower energy. However, changing the radial position at low energy for cogging is limited because of aperture. Momentum cogging is able to move the gap creation to an earlier time by using dipole correctors and radial position feedback, and is able to control the revolution frequency and radial position at the same time. The new cogging is expected to reduce beam loss and not be limited by aperture. The progress of the momentum cogging system development is going to be discussed in this paper.

  10. Developing Strategies for Affordable Bandwidth.

    ERIC Educational Resources Information Center

    Educause Quarterly, 2000

    2000-01-01

    Written by Educause's Net@EDU Broadband Pricing Working Group, this article discusses what institutions of higher education can do to develop good partnerships with broadband vendors in order to negotiate affordable pricing for increased bandwidth. Describes problems with the marketplace, examples from a few universities, and points to remember…

  11. Multiturn injection of EBIS ions in booster

    SciTech Connect

    Gardner, C.J.

    2010-09-01

    Ions from EBIS are injected into Booster after acceleration by an RFQ and a Linac. The velocity of the ions at Booster injection is c{beta} where c is the velocity of light and (1) {beta} = 0.0655. The kinetic energy is (2) W = mc{sup 2}({gamma}-1) where m is the ion mass and (3) {gamma} = (1-{beta}{sup 2}){sup -1/2}. Putting in numbers one gets a kinetic energy of approximately 2 MeV per nucleon for each ion. The revolution period at injection is 10.276 {micro}s. The ions in the EBIS trap are delivered in a beam pulse that ranges from 10 to 40 {micro}s in length. This amounts to 1 to 4 turns around the machine. The transverse emittance (un-normalized) of EBIS beams just prior to injection into Booster is 11{pi} mm milliradians in both planes. This is an order of magnitude larger than the nominal 1{pi} mm milliradians for Tandem beams. Injection proceeds by means of an electrostatic inflector in the C3 straight section and four programmable injection dipoles in the C1, C3, C7, and D1 straights. These devices have been in use for many years for the injection of ions from Tandem as described in [1] and [2]. The inflector brings the incoming beam to the edge of the Booster acceptance and the dipoles produce a closed orbit bump that initially places the closed orbit near the septum at the in ector exit. During injection the orbit bump must be collapsed at a rate that keeps the injected beam from hitting the septum while continuing to allow beam to be injected into the machine acceptance. The process is discussed in [2] and [3]. There it is assumed that the injected beam moves with the closed orbit as the bump collapses. In the present report this is shown to be a valid approximation if the bump collapses sufficiently slowly. It is also shown that by judiciously choosing the horizontal tune and the initial distance of the closed orbit from the septum one can inject up to 4 turns of EBIS beams without loss on the septum. The reason for wanting to inject over a period of

  12. Liquid Rocket Booster (LRB) for the Space Transportation System (STS) systems study. Appendix F: Performance and trajectory for ALS/LRB launch vehicles

    NASA Technical Reports Server (NTRS)

    1989-01-01

    By simply combining two baseline pump-fed LOX/RP-1 Liquid Rocket Boosters (LRBs) with the Denver core, a launch vehicle (Option 1 Advanced Launch System (ALS)) is obtained that can perform both the 28.5 deg (ALS) mission and the polar orbit ALS mission. The Option 2 LRB was obtained by finding the optimum LOX/LH2 engine for the STS/LRB reference mission (70.5 K lb payload). Then this engine and booster were used to estimate ALS payload for the 28.5 deg inclination ALS mission. Previous studies indicated that the optimum number of STS/LRB engines is four. When the engine/booster sizing was performed, each engine had 478 K lb sea level thrust and the booster carried 625,000 lb of useable propellant. Two of these LRBs combined with the Denver core provided a launch vehicle that meets the payload requirements for both the ALS and STS reference missions. The Option 3 LRB uses common engines for the cores and boosters. The booster engines do not have the nozzle extension. These engines were sized as common ALS engines. An ALS launch vehicle that has six core engines and five engines per booster provides 109,100 lb payload for the 28.5 deg mission. Each of these LOX/LH2 LRBs carries 714,100 lb of useable propellant. It is estimated that the STS/LRB reference mission payload would be 75,900 lb.

  13. Study of solid rocket motors for a space shuttle booster. Appendix D: Recovery and reuse 156-inch diameter solid rocket motor booster

    NASA Technical Reports Server (NTRS)

    1972-01-01

    The baseline for a space shuttle configuration utilizing two parallel-burn, 156-in.-diameter SRMs with three segments and techroll seal movable nozzles is presented. The concept and general economic benefits of SRM recovery are equally valid for the series-burn SRMs, provided that those SRMs are also designed for the same strength, stiffness, segmentation, and interchangeability as the present design, and that those SRMs are also recovered as individual units. Feasibility studies were initiated to investigate SRM recoverability. These studies were based upon recovery of the SRM boosters for the Titan 3C. Ground rules precluded SRM modification that required significant changes in motor qualification or schedule. Even with this restriction, the study determined that the recoverable booster concept was completely feasible, both technically and economically. Parachute recovery has been selected as the best method, principally because it can accomplish the task with a minimum development cost and time to achieve operational recovery status. This system affords the highest probability for achieving large cost reductions.

  14. Space Shuttle Five-Segment Booster (Short Course)

    NASA Technical Reports Server (NTRS)

    Graves, Stanley R.; Rudolphi, Michael (Technical Monitor)

    2002-01-01

    NASA is considering upgrading the Space Shuttle by adding a fifth segment (FSB) to the current four-segment solid rocket booster. Course materials cover design and engineering issues related to the Reusable Solid Rocket Motor (RSRM) raised by the addition of a fifth segment to the rocket booster. Topics cover include: four segment vs. five segment booster, abort modes, FSB grain design, erosive burning, enhanced propellant burn rate, FSB erosive burning model development and hardware configuration.

  15. Closeup view of the Solid Rocket Booster (SRB) Forward Skirt, ...

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

    Close-up view of the Solid Rocket Booster (SRB) Forward Skirt, Frustum and Nose Cap mated assembly undergoing final preparations in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center. In this view the access panel on the Forward Skirt is removed and you can see a small portion of the interior of the Forward Skirt. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

  16. StarBooster Demonstrator Cluster Configuration Analysis/Verification Program

    NASA Technical Reports Server (NTRS)

    DeTurris, Dianne J.

    2003-01-01

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

  17. Closeup view of the Solid Rocket Booster Frustum and Nose ...

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

    Close-up view of the Solid Rocket Booster Frustum and Nose Cap assembly undergoing preparations and assembly procedures in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center. The Nose Cap contains the Pilot and Drogue Chutes and the Frustum contains the three Main Parachutes, Altitude Switches and forward booster Separation Motors. In this view the assembly is rotated so that the four Separation Motors are in view and aligned with the approximate centerline of the image. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

  18. Toward Affordability: Policy Recommendations for Virginia Higher Education

    ERIC Educational Resources Information Center

    State Council of Higher Education for Virginia, 2009

    2009-01-01

    In its 2007-13 strategic plan, Advancing Virginia: Access, Alignment, Investment, the State Council highlighted 12 strategic higher education initiatives that it believed were necessary to ensure Virginia's future. Key among these goals was improvement of the affordability of a college education in the Commonwealth. Recent events have reinforced…

  19. An international analysis of cigarette affordability

    PubMed Central

    Blecher, E; van Walbeek, C P

    2004-01-01

    Objective: To investigate how affordable cigarettes are in developed and developing countries, and to calculate by how much the affordability of cigarettes has changed between 1990 and 2001; and secondly, to investigate the relation between cigarette affordability and consumption. Design: Affordability was defined as the cost of cigarettes relative to per capita income. Trends in cigarette affordability, and affordability elasticities of demand, were estimated using regression techniques. Subjects: Seventy countries were investigated, of which 28 are categorised as high income developed countries, while 42 are categorised as developing countries. Cigarette prices were obtained for the main city/cities in the countries. Results: Despite the fact that cigarettes are more expensive in developed countries, the high levels of income make cigarettes more affordable in these countries vis-à-vis developing countries. Of the 28 developed countries, cigarettes became more affordable in 11 and less affordable in 17 countries during the 1990s. Of the 42 developing countries, cigarettes became more affordable in 24 and less affordable in 18 countries. Based on a cross sectional analysis, a 1% increase in the relative income price (the inverse of cigarette affordability) is expected to decrease cigarette consumption by between 0.49–0.57%. Conclusions: Cigarette affordability, more than just the price, determines cigarette consumption. While cigarettes have become more affordable in many developing countries, some developing countries (for example, South Africa, Poland, and Thailand) have implemented strong and effective tobacco control policies, and have been able to decrease cigarette consumption as a result. PMID:15564616

  20. Optics learning through affordable kit

    SciTech Connect

    P, Anusha N E-mail: chitrashaji@gmail.com Shaji, Chitra E-mail: chitrashaji@gmail.com Sharan, Alok E-mail: chitrashaji@gmail.com

    2014-10-15

    An affordable kit which helps to understand some of the optical phenomena qualitatively and quantitatively is presented in this paper. It supplements optics taught in classes. The kit consists of equipments which are available in the market at nominal cost such as laser pointer, lenses, glass plates, razor blades, coins, ball bearing etc. Experiments which come under wave optics (interference and diffraction) and ray optics (reflection and refraction) are explained using this kit.

  1. Optics learning through affordable kit

    NASA Astrophysics Data System (ADS)

    P, Anusha N.; Shaji, Chitra; Sharan, Alok

    2014-10-01

    An affordable kit which helps to understand some of the optical phenomena qualitatively and quantitatively is presented in this paper. It supplements optics taught in classes. The kit consists of equipments which are available in the market at nominal cost such as laser pointer, lenses, glass plates, razor blades, coins, ball bearing etc. Experiments which come under wave optics (interference and diffraction) and ray optics (reflection and refraction) are explained using this kit.

  2. Solid rocket booster thermal protection system materials development. [space shuttle boosters

    NASA Technical Reports Server (NTRS)

    Dean, W. G.

    1978-01-01

    A complete run log of all tests conducted in the NASA-MSFC hot gas test facility during the development of materials for the space shuttle solid rocket booster thermal protection system are presented. Lists of technical reports and drawings generated under the contract are included.

  3. Space-charge compensation in proton boosters

    SciTech Connect

    Alexey Burov; William Foster; Vladimir Shiltsev

    2001-06-26

    Recently, it was proposed to use negatively charged electron beams for compensation of beam-beam effects due to protons in the Tevatron collider. We show that a similar compensation is possible in space-charge dominated low energy proton beams. The idea has a potential of several-fold increase of the FNAL Booster beam brightness. Best results will be obtained using three electron lenses around the machine circumference, using co-moving electron beam with time structure and profile approximately to the proton beam. This technique, if feasible, will be more cost effective than the straightforward alternative increasing the energy of the injection linac.

  4. The low energy booster project status

    SciTech Connect

    Tuttle, G.W.

    1993-05-01

    In order to achieve the required injection momentum, the Superconducting Super Collider (SSC) has an accelerator chain comprised of a Linear Accelerator and three synchrotrons. The Low Energy Booster (LEB) is the first synchrotron in this chain. The LEB project has made significant progress in the development of major subsystems and conventional construction. This paper briefly reviews the performance requirements of the LEB and describes significant achievements in each of the major subsystem areas. Highlighted among these achievements are the LEB foreign collaborations with the Budker Institute of Nuclear Physics (BINP) located in Novosibirsk, Russia.

  5. Transition crossing simulation at the Fermilab Booster

    SciTech Connect

    Yang, X.; Drozhdin, A.I.; Pellico, W.; /Fermilab

    2007-06-01

    The demand in high intensity and low emittance of the beam extracted from the Booster requires a better control over the momentum spread growth and bunch length shortening at transition crossing, in order to prevent beam loss and coupled bunch instability. Since the transition crossing involves both longitudinal and transverse dynamics, the recently modified 3-D STRUCT code provides an opportunity to numerically investigate the different transition crossing schemes in the machine environment, and apply the results of simulation to minimize the beam loss and emittance growth operationally.

  6. New corrector system for the Fermilab booster

    SciTech Connect

    Prebys, E.J.; Drennan, C.C.; Harding, D.J.; Kashikhin, V.; Lackey, J.R.; Makarov, A.; Pellico, W.A.; /Fermilab

    2007-06-01

    We present an ambitious ongoing project to build and install a new corrector system in the Fermilab 8 GeV Booster. The system consists of 48 corrector packages, each containing horizontal and vertical dipoles, normal and skew quadrupoles, and normal and skew sextupoles. Space limitations in the machine have motivated a unique design, which utilizes custom wound coils around a 12 pole laminated core. Each of the 288 discrete multipole elements in the system will have a dedicated power supply, the output current of which is controlled by an individual programmable ramp. This paper describes the physics considerations which drove the design, as well as issues in the control of the system.

  7. Credit BG. Northwest facade of Building 4504 (Deluge Water Booster ...

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

    Credit BG. Northwest facade of Building 4504 (Deluge Water Booster Station) is in view at left, with 500,000 gallon water tank (Building 4503) at right. Fenced electrical substation in view between the above structures is Building 4510. Building 4505 is in background - Edwards Air Force Base, North Base, Deluge Water Booster Station, Northeast of A Street, Boron, Kern County, CA

  8. 47 CFR 22.9 - Operation of certificated signal boosters.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 47 Telecommunication 2 2014-10-01 2014-10-01 false Operation of certificated signal boosters. 22.9 Section 22.9 Telecommunication FEDERAL COMMUNICATIONS COMMISSION (CONTINUED) COMMON CARRIER SERVICES PUBLIC MOBILE SERVICES Scope and Authority § 22.9 Operation of certificated signal boosters. Individuals and non-individuals may...

  9. Results from commissioning the AGS Booster orbit system

    SciTech Connect

    Bleser, E.

    1993-06-01

    This note reports results from the commissioning of three systems in the AGS Booster. The beam position monitor system, which works to a relative accuracy of 0.36 millimeters; the uncorrected Booster orbit, which has quite large excursions; and the passive eddy current correction system, which eliminates all but a few percent of the eddy current dipole effect.

  10. Liquid rocket booster study. Volume 1: Executive summary

    NASA Technical Reports Server (NTRS)

    1989-01-01

    The purpose of this study was to determine the feasibility of Liquid Rocket Boosters (LRBs) replacing Solid Rocket Boosters on the Space Shuttle program. The major findings are given. The most significant conclusion is that LRBs offer significantly safety and performance advantages over the SRBs currently used by the STS without major impact to the ongoing program.

  11. General view of the Solid Rocket Booster's (SRB) Solid Rocket ...

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

    General view of the Solid Rocket Booster's (SRB) Solid Rocket Motor Segments in the Surge Building of the Rotation Processing and Surge Facility at Kennedy Space Center awaiting transfer to the Vehicle Assembly Building and subsequent mounting and assembly on the Mobile Launch Platform. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

  12. General view of a fully assembled Solid Rocket Booster sitting ...

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

    General view of a fully assembled Solid Rocket Booster sitting atop the Mobile Launch Platform in the Vehicle Assembly Building at Kennedy Space Center - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

  13. 47 CFR 101.151 - Use of signal boosters.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 47 Telecommunication 5 2010-10-01 2010-10-01 false Use of signal boosters. 101.151 Section 101.151 Telecommunication FEDERAL COMMUNICATIONS COMMISSION (CONTINUED) SAFETY AND SPECIAL RADIO SERVICES FIXED MICROWAVE SERVICES Technical Standards § 101.151 Use of signal boosters. Private operational-fixed...

  14. 47 CFR 101.151 - Use of signal boosters.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 47 Telecommunication 5 2011-10-01 2011-10-01 false Use of signal boosters. 101.151 Section 101.151 Telecommunication FEDERAL COMMUNICATIONS COMMISSION (CONTINUED) SAFETY AND SPECIAL RADIO SERVICES FIXED MICROWAVE SERVICES Technical Standards § 101.151 Use of signal boosters. Private operational-fixed...

  15. 47 CFR 90.219 - Use of signal boosters.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... operate this device. You MUST register Class B signal boosters (as defined in 47 CFR 90.219) online at www... initially adjust a signal booster. Distributed Antenna System (DAS). A network of spatially separated antenna nodes connected to a common source via a transport medium that provides wireless service within...

  16. 47 CFR 90.219 - Use of signal boosters.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... operate this device. You MUST register Class B signal boosters (as defined in 47 CFR 90.219) online at www... initially adjust a signal booster. Distributed Antenna System (DAS). A network of spatially separated antenna nodes connected to a common source via a transport medium that provides wireless service within...

  17. 47 CFR 101.151 - Use of signal boosters.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 47 Telecommunication 5 2012-10-01 2012-10-01 false Use of signal boosters. 101.151 Section 101.151 Telecommunication FEDERAL COMMUNICATIONS COMMISSION (CONTINUED) SAFETY AND SPECIAL RADIO SERVICES FIXED MICROWAVE SERVICES Technical Standards § 101.151 Use of signal boosters. Private operational-fixed...

  18. 47 CFR 101.151 - Use of signal boosters.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 47 Telecommunication 5 2014-10-01 2014-10-01 false Use of signal boosters. 101.151 Section 101.151 Telecommunication FEDERAL COMMUNICATIONS COMMISSION (CONTINUED) SAFETY AND SPECIAL RADIO SERVICES FIXED MICROWAVE SERVICES Technical Standards § 101.151 Use of signal boosters. Private operational-fixed...

  19. 47 CFR 101.151 - Use of signal boosters.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 47 Telecommunication 5 2013-10-01 2013-10-01 false Use of signal boosters. 101.151 Section 101.151 Telecommunication FEDERAL COMMUNICATIONS COMMISSION (CONTINUED) SAFETY AND SPECIAL RADIO SERVICES FIXED MICROWAVE SERVICES Technical Standards § 101.151 Use of signal boosters. Private operational-fixed...

  20. Compensation of dogleg effect in Fermilab Booster

    SciTech Connect

    Xiaobiao Huang; Sho Ohnuma

    2003-10-06

    The edge focusing of dogleg magnets in Fermilab Booster has been causing severe distortion to the horizontal linear optics. The doglegs are vertical rectangular bends, therefore the vertical edge focusing is canceled by body focusing and the overall effect is focusing in the horizontal plane. The maximum horizontal beta function is changed from 33.7m to 46.9m and maximum dispersion from 3.19m to 6.14m. Beam size increases accordingly. This is believed to be one of the major reasons of beam loss. In this technote we demonstrate that this effect can be effectively corrected with Booster's quadrupole correctors in short straight sections (QS). There are 24 QS correctors which can alter horizontal linear optics with negligible perturbation to the vertical plane. The currents of correctors are determined by harmonic compensation, i.e., cancellation of dogleg's harmonics that are responsible for the distortion with that of QS correctors. By considering a few leading harmonics, the ideal lattice can be partly restored. For the current dogleg layout, maximum {beta}{sub x} is reduced to 40.6m and maximum D{sub x} is reduced to 4.19m. This scheme can be useful after the dogleg in section No.3 is repositioned. In this case it can bring {beta}{sub x} from 40.9m down to 37.7m, D{sub x} from 4.57m to 4.01m.

  1. Smoking Bans in Affordable Housing Benefit All

    MedlinePlus

    ... 160501.html Smoking Bans in Affordable Housing Benefit All: Study Secondhand exposure lowered, and smokers more likely ... residents of eight affordable housing properties in Minnesota. All the properties prohibited smoking indoors and three also ...

  2. Booster recovery following premature space shuttle stage separation

    NASA Technical Reports Server (NTRS)

    Hurley, M. J.

    1972-01-01

    Abort criteria necessary to satisfy space shuttle program requirements to include intact vehicle abort capability are discussed. Intact abort implies the ability of the booster and orbiter to separate and both continue flight to a safe landing, with a full payload aboard the orbiter. Obviously, the requirement to separate early along the ascent trajectory presupposes critical operational problems that are probably booster problems and may preclude booster recovery. On the other hand, some critical problems while mated can become manageable when separated and should result in full booster recovery. All critical orbiter problems fall into this category; since stage separation without orbiter thrust is a capability of some separation system concepts, booster stage recovery following separation is a requirement.

  3. A Method for Sizing Booster Charges in Pyrotechnic Mechanisms

    NASA Technical Reports Server (NTRS)

    Bement, Laurence J.

    1998-01-01

    Since no generally accepted guidelines exist on sizing booster charges to assure functional margins in pyrotechnically actuated devices, a study was conducted to provide an approach to meet this need. An existing pyrovalve was modified from a single cartridge input to a dual-cartridge input with a booster charge. The objectives of this effort were to demonstrate an energy-based functional margin approach for sizing booster charges, and to determine booster charge energy delivery characteristics in this valve. Functional margin was demonstrated by determining the energy required to actuate the valve through weight drop tests for comparison to the energy delivered by the cartridge and booster charge in firings in the modified valve. The results of this study indicated that this energy-based approach fully met the study objectives, showing its usefulness for this and possibly other pyrotechnic devices.

  4. Superconducting racetrack booster for the ion complex of MEIC

    NASA Astrophysics Data System (ADS)

    Filatov, Yu; Kondratenko, A. M.; Kondratenko, M. A.; Kovalenko, A.; Derbenev, Ya S.; Lin, F.; Morozov, V. S.; Zhang, Y.

    2016-02-01

    The current design of the Medium-energy Electron-Ion Collider (MEIC) project at Jefferson lab features a single 8 GeV/c figure-8 booster based on super-ferric magnets. Reducing the circumference of the booster by switching to a racetrack design may improve its performance by limiting the space charge effect and lower its cost. We consider problems of preserving proton and deuteron polarizations in a superconducting racetrack booster. We show that using magnets based on hollow high-current NbTi composite superconducting cable similar to those designed at JINR for the Nuclotron guarantees preservation of the ion polarization in a racetrack booster up to 8 GeV/c. The booster operation cycle would be a few seconds that would improve the operating efficiency of the MEIC ion complex.

  5. Can China afford rapid aging?

    PubMed

    Jiang, Quanbao; Yang, Shucai; Sánchez-Barricarte, Jesús J

    2016-01-01

    China's rapid aging has caused widespread concern, but it seems that the situations and consequences of rapid aging are not adequately acknowledged. This study analyzed the problem of ageing in China from the aspects of elderly people's health status, income source, daily care, suicide, the weak social security system in terms of pension, health expenses, and long-term care costs as well as incoming accelerating ageing process in China. All these factors indicate that it is difficult for China to afford the issue of a rapidly aging population. PMID:27478724

  6. The Value of Full Correction: Achieving Excellent and Affordable Results.

    PubMed

    Kaplan, Julie Bass

    2016-01-01

    Patients often come to medical aesthetic offices with hopes to fully correct lost facial volume and achieve a natural appearance. Unfortunately, the cost per syringe of dermal filler can be a barrier to desired outcomes. Many aesthetic practitioners do the best they can with the amount of product the patient can afford, often falling short of the "wow" effect for the patient. This article describes what one office implemented to solve the conundrum of affordability while still allowing offices to cover its own financial realities. This tool can help patients achieve beautiful, natural, and affordable outcomes while helping offices advance in manufacturer's tiers, improve word-of-mouth advertising, and increase job satisfaction. PMID:27606585

  7. Perceiving Affordances for Fitting through Apertures

    ERIC Educational Resources Information Center

    Ishak, Shaziela; Adolph, Karen E.; Lin, Grace C.

    2008-01-01

    Affordances--possibilities for action--are constrained by the match between actors and their environments. For motor decisions to be adaptive, affordances must be detected accurately. Three experiments examined the correspondence between motor decisions and affordances as participants reached through apertures of varying size. A psychophysical…

  8. Main Chamber Injectors for Advanced Hydrocarbon Booster Engines

    NASA Technical Reports Server (NTRS)

    Long, Matthew R.; Bazarov, Vladimir G.; Anderson, William E.

    2003-01-01

    Achieving the highest possible specific impulse has long been a key driver for space launch systems. Recently, more importance has been placed on the need for increased reliability and streamlined launch operations. These general factors along with more specific mission requirements have provided a new focus that is centered on the oxidizer rich staged combustion (ORSC) cycle. Despite a history of use in Russia that extends back to the 1960's, a proven design methodology for ORSC cycle engines does not exist in the West. This lack of design expertise extends to the main chamber injector, a critical subcomponent that largely determines the engine performance and main chamber life. The goals of the effort described here are to establish an empirical knowledge base to provide a fundamental understanding of main chamber injectors and for verification of an injector design methodology for the ORSC cycle. The design of a baseline injector element, derived from information on Russian engines in the open literature, is presented. The baseline injector comprises a gaseous oxidizer core flow and an annular swirling fuel flow. Sets of equations describing the steady-state and the dynamic characteristics of the injector are presented; these equations, which form the basis of the design analysis methodology, will be verified in tests later this year. On-going cold flow studies, using nitrogen and water as simulants, are described which indicate highly atomized and symmetric sprays.

  9. Energy efficient affordable housing. Final report

    SciTech Connect

    1995-07-01

    In 1994, the Southface Energy Institute, working with support from US DOE, initiated a program to provide technical assistance to nonprofit organizations developing affordable housing in the Olympic target communities of Atlanta. The specific project goals were: Identify the barriers that nonprofit affordable housing providers face in increasing the energy and resource efficiency of affordable housing; Assist them in developing the resources to overcome these barriers; Develop specific technical materials and program models that will enable these affordable housing groups to continue to improve the energy efficiency of their programs; and, To transfer the program materials to other affordable housing providers. This report summarizes the progress made in each of these areas.

  10. Booster vaccination: the role of reduced antigen content vaccines as a preschool booster.

    PubMed

    Gabutti, Giovanni; Trucchi, Cecilia; Conversano, Michele; Zivelonghi, Giambattista; Zoppi, Giorgio

    2014-01-01

    The need for boosters for tetanus, diphtheria, pertussis, and polio, starting from preschool age, is related to the waning immune protection conferred by vaccination, the elimination/reduction of natural boosters due to large-scale immunization programs, and the possibility of reintroduction of wild agents from endemic areas. Taking into account the relevance of safety/tolerability in the compliance with vaccination among the population, it have been assessed whether today enough scientific evidences are available to support the use of dTap-IPV booster in preschool age. The review of the literature was conducted using the PubMed search engine. A total of 41 works has been selected; besides, the documentation produced by the World Health Organization, the European Centre for Disease Control, and the Italian Ministry of Health has been consulted. Many recent papers confirm the opportunity to use a low antigenic dose vaccine starting from 4 to 6 years of age. There is also evidence that 10 years after immunization the rate of seroprotected subjects against diphtheria does not differ significantly between those vaccinated with paediatric dose (DTaP) or reduced dose (dTaP or dTap) product. The dTpa vaccine is highly immunogenic for diphtheria toxoids regardless of prior vaccination history (2 + 1 and 3 + 1 schedules). PMID:24678509

  11. Ocean recovery of Shuttle Solid Rocket Boosters.

    NASA Technical Reports Server (NTRS)

    Junker, L. J.

    1973-01-01

    Cost effective recovery of the expended Space-Shuttle Solid Rocket Boosters (SRB) from the ocean will result in significant overall cost savings to the Space Shuttle Program. The ocean recovery mission begins with the dispatching of the recovery team to the predicted splashdown area. The SRBs, drogue parachutes and main parachutes must be tracked, located, retrieved, and transported to land where they will be refurbished and recycled for reuse. Trade studies to be conducted will consider the recovery mission requirements and weigh the advantages, disadvantages and costs of various candidate recovery systems. Major parameters effecting the selection of the final system will ensure that the system will meet overall objectives. Large- and small-scale SRB model testing has been conducted to establish characteristics of SRBs during water entry, floating free and under tow.

  12. Shuttle rocket booster computational fluid dynamics

    NASA Technical Reports Server (NTRS)

    Chung, T. J.; Park, O. Y.

    1988-01-01

    Additional results and a revised and improved computer program listing from the shuttle rocket booster computational fluid dynamics formulations are presented. Numerical calculations for the flame zone of solid propellants are carried out using the Galerkin finite elements, with perturbations expanded to the zeroth, first, and second orders. The results indicate that amplification of oscillatory motions does indeed prevail in high frequency regions. For the second order system, the trend is similar to the first order system for low frequencies, but instabilities may appear at frequencies lower than those of the first order system. The most significant effect of the second order system is that the admittance is extremely oscillatory between moderately high frequency ranges.

  13. Clustered Lance Booster (CLB) feasibility study

    NASA Astrophysics Data System (ADS)

    1993-01-01

    Loral Vought (LV) was requested to investigate the feasibility of clustering four Lance propulsion systems as the first stage of a two-stage target vehicle. Two vehicle configurations were considered, both using the Clustered Lance Booster (CLB) as the first stage. On one configuration, the second stage will be the 40-inch diameter Liquid Fueled Target (LFT-40), which was the subject of an LTV Aerospace and Defense Company study in 1991. This configuration is designated as the CLB/LFT-40. The second stage of the other configuration will be a modified Lance having the same external shape as the Lance missile (22-inch diameter). This configuration is designated as the CLB/LFT-22.

  14. Weight control of a large space booster

    NASA Astrophysics Data System (ADS)

    Metheny, Gary R.

    1989-05-01

    The Titan IV vehicle, a stretching of the Titan III to possess longer fuel and oxidizer tanks on both stages while retaining the constant, 10-ft diameter, would have to withstand larger P-equivalent loads due to the increased weight of skin, stringer, and frame structure strengthening. Upon analysis, it was established that increased vehicle and payload fairing lengths imparted a large bending moment to the booster at design Q-alpha total flight conditions, so that stiffness rather than axial load became the design driver. Weight problems thus incurred were addressed by critical structural element analyses using target weight vs stress margin comparisons. Items were thus identified for successful weight reduction treatment.

  15. SRB dewatering set. [space shuttle boosters revcovery

    NASA Technical Reports Server (NTRS)

    Wickham, R. E.

    1981-01-01

    The system components and operation of the space shuttle solid rocket booster (SRB) dewatering set are described. The SRB dewatering set consists of a nozzle plug, control console, remote control unit, power distribution unit, umbilical cable, interconnect cables, and various handling and storage items. The nozzle plug (NP) is a remotely controlled, tethered underwater vehicle that is launched from the retrieval vessel (RV) by a crane, descends down the side of the SRB, and is positioned below the SRB nozzle. A TV camera mounted at the top of the NP central core is used by the control console operator to visually guide the NP during descent and docking. The NP is then driven up and locked into the nozzle. Compressed air is passed through the umbilical from the RV, through the NP and into the SRB motor. The water inside the SRB is expelled causing the SRB to rotate to a near horizontal attitude on the surface of the water.

  16. Status of the AGC Booster project

    SciTech Connect

    Weng, W.T.

    1988-01-01

    To meet the needs of new experiments in high energy and nuclear physics, a rapid-cycling Booster for the AGS has been under construction at Brookhaven. For each mode of operation there are corresponding accelerator physics and design issues that need special attention. Problems pertinent to any single mode of operation have been encountered and solved before, but putting high intensity proton requirements and high vacuum heavy ion requirements into one machine demands careful design considerations and decisions. The lattice design and magnet characteristics will be briefly reviewed. Major design issues will be discussed and design issues will be discussed and design choices explained. And finally, the construction status and schedule will be presented. 6 refs., 5 figs., 1 tab.

  17. Space Shuttle solid rocket booster dewatering system

    NASA Technical Reports Server (NTRS)

    Fishel, K. R.

    1982-01-01

    After the launch of the Space Shuttle, the two solid rocket boosters (SRB's) are jettisoned into the ocean where they float in a spar (vertical) mode. It is cost effective to recover the SRB's. A remote controlled submersible vehicle has been developed to aid in their recovery. The vehicle is launched from a support ship, maneuvered to the SRB, then taken to depth and guided into the rocket nozzle. It then dewaters the SRB, using compressed air from the ship, and seals the nozzle. When dewatered, the SRB floats in a log (horizontal) mode and can be towed to port for reuse. The design of the remote controlled vehicle and its propulsion system is presented.

  18. Technology for low cost solid rocket boosters.

    NASA Technical Reports Server (NTRS)

    Ciepluch, C.

    1971-01-01

    A review of low cost large solid rocket motors developed at the Lewis Research Center is given. An estimate is made of the total cost reduction obtainable by incorporating this new technology package into the rocket motor design. The propellant, case material, insulation, nozzle ablatives, and thrust vector control are discussed. The effect of the new technology on motor cost is calculated for a typical expandable 260-in. booster application. Included in the cost analysis is the influence of motor performance variations due to specific impulse and weight changes. It is found for this application that motor costs may be reduced by up to 30% and that the economic attractiveness of future large solid rocket motors will be improved when the new technology is implemented.

  19. Designing for solid rocket booster reusability

    NASA Technical Reports Server (NTRS)

    Nevins, C. D.

    1975-01-01

    The Solid Rocket Booster (SRB) of the Space Shuttle Program has been designed to be recovered, refurbished, and reused up to 19 times on subsequent launches. The design modifications to the SRB to incorporate this capability include the addition of a parachute recovery system and minor structural modifications to the nose cone, forward skirt, aft skirt, and solid rocket motor structures for withstanding the water impact loading. In addition, the detail design of subsystem hardware requires careful attention to corrosion prevention and facility of refurbishment operations. A cost analysis comparing the reusable SRB with an expendable version shows a substantial reduction in Space Shuttle cost per flight is achieved with the reusable design approach.

  20. Rf beam control for the AGS Booster

    SciTech Connect

    Brennan, J.M.

    1994-09-26

    RF beam control systems for hadron synchrotrons have evolved over the past three decades into an essentially standard design. The key difference between hadron and lepton machines is the absence of radiation damping and existence of significant frequency variation in the case of hadrons. Although the motion of the hadron in the potential well of the rf wave is inherently stable it is not strongly damped. Damping must be provided by electronic feedback through the accelerating system. This feedback is typically called the phase loop. The technology of the rf beam control system for the AGS Booster synchrotron is described. First, the overall philosophy of the design is explained in terms of a conventional servo system that regulates the beam horizontal position in the vacuum chamber. The concept of beam transfer functions is fundamental to the mathematics of the design process and is reviewed. The beam transfer functions required for this design are derived from first principles. An overview of the beam signal pick-ups and high level rf equipment is given. The major subsystems, the frequency program, the heterodyne system, and beam feedback loops, are described in detail. Beyond accelerating the beam, the rf system must also synchronize the bunches in the Booster to the buckets in the AGS before transfer. The technical challenge in this process is heightened by the need to accomplish synchronization while the frequency is still changing. Details of the synchronization system are given. This report is intended to serve two purposes. One is to document the hardware and performance of the systems that have been built. The other is to serve as a tutorial vehicle from which the non-expert can not only learn the details of this system but also learn the principles of beam control that have led to the particular design choices made.

  1. NASA's Space Launch System: Affordability for Sustainability

    NASA Technical Reports Server (NTRS)

    May, Todd A.; Creech, Stephen D.

    2012-01-01

    The National Aeronautics and Space Administration's (NASA) Space Launch System (SLS) Program, managed at the Marshall Space Flight Center, is charged with delivering a new capability for human exploration beyond Earth orbit in an austere economic climate. But the SLS value is clear and codified in United States (U.S.) budget law. The SLS Program knows that affordability is the key to sustainability and will provide an overview of initiatives designed to fit within the funding guidelines by using existing engine assets and hardware now in testing to meet a first launch by 2017 within the projected budget. It also has a long-range plan to keep the budget flat, yet evolve the 70-tonne (t) initial lift capability to 130-t lift capability after the first two flights. To achieve the evolved configuration, advanced technologies must offer appropriate return on investment to be selected through the competitive process. For context, the SLS will be larger than the Saturn V that took 12 men on 6 trips for a total of 11 days on the lunar surface some 40 years ago. Astronauts train for long-duration voyages on platforms such as the International Space Station, but have not had transportation to go beyond Earth orbit in modern times, until now. To arrive at the launch vehicle concept, the SLS Program conducted internal engineering and business studies that have been externally validated by industry and reviewed by independent assessment panels. In parallel with SLS concept studies, NASA is now refining its mission manifest, guided by U.S. space policy and the Global Exploration Roadmap, which reflects the mutual goals of a dozen member nations. This mission planning will converge with a flexible heavy-lift rocket that can carry international crews and the air, water, food, and equipment they need for extended trips to asteroids and Mars. In addition, the SLS capability will accommodate very large science instruments and other payloads, using a series of modular fairings and

  2. Affordable In-Space Transportation

    NASA Technical Reports Server (NTRS)

    Curtis, L. A.; VanDyke, M. K.; Lajoie, R. M.; Woodcock, G. R.

    1996-01-01

    Current and proposed launch systems will provide access to low-Earth orbit (LEO), and destinations beyond LEO, but the cost of delivering payloads will preclude the use of these services by many users. To develop and encourage revolutionary commercial utilization of geosynchronous orbit (GEO) and to provide an affordable means to continue NASA space science and exploration missions, the transportation costs to in-space destinations must be reduced. The principal objective of this study was to conceptually define three to four promising approaches to in-space transportation for delivery of satellites and other payloads, 3,000- to 10,000-lb class, to GEO destinations. This study established a methodology for evaluating in-space transportation systems based on life-cycle cost. The reusable concepts seemed to fare better in the evaluation than expendable, since a major driver in the life-cycle cost was the stage production cost.

  3. The StarBooster System: A Cargo Aircraft for Space

    NASA Technical Reports Server (NTRS)

    Davis, Hubert P.; Dula, Arthur M.; McLaughlin, Don; Frassanito, John; Andrews, Jason (Editor)

    1999-01-01

    Starcraft Boosters has developed a different approach for lowering the cost of access to space. We propose developing a new aircraft that will house an existing expendable rocket stage. This vehicle, termed StarBooster, will be the first stage of a family of launch vehicles. By combining these elements, we believe we can reduce the cost and risk of fielding a new partially reusable launch system. This report summarizes the work performed on the StarBooster concept since the company's inception in 1996. Detailed analyses are on-going and future reports will focus on the maturation of the vehicle and system design.

  4. Closeup view of the Solid Rocket Booster (SRB) Forward Skirt, ...

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

    Close-up view of the Solid Rocket Booster (SRB) Forward Skirt, Frustum and Nose Cap mated assembly undergoing final preparations in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center. The prominent feature in this view is the Forward Thrust Attach Fitting which mates up with the Forward Thrust Attach Fitting of the External Tank (ET) at the ends of the SRB Beam that runs through the ET's Inter Tank Assembly. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

  5. Closeup view of the Solid Rocket Booster (SRB) Forward Skirt ...

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

    Close-up view of the Solid Rocket Booster (SRB) Forward Skirt sitting on ground support equipment in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center while being prepared for mating with the Frustum-Nose Cap Assembly and the Forward Rocket Motor Segment. The prominent feature in this view is the electrical, data, telemetry and safety systems terminal which connects to the Aft Skirt Assembly systems via the Systems Tunnel that runs the length of the Rocket Motor. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

  6. Closeup view of the Solid Rocket Booster (SRB) Forward Skirt ...

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

    Close-up view of the Solid Rocket Booster (SRB) Forward Skirt sitting on ground support equipment in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center while being prepared for mating with the Frustum-Nose Cap Assembly and the Forward Rocket Motor Segment. The prominent feature in this view is the Forward Thrust Attach Fitting which mates up with the Forward Thrust Attach Fitting of the External Tank (ET) at the ends of the SRB Beam that runs through the ET's Inter Tank Assembly. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

  7. Closeup view of the Solid Rocket Booster (SRB) Nose Caps ...

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

    Close-up view of the Solid Rocket Booster (SRB) Nose Caps mounted on ground support equipment in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center as they are being prepared for attachment to the SRB Frustum. The Nose Cap contains the Pilot and Drogue Chutes that are deployed prior to the main chutes as the SRBs descend to a splashdown in the Atlantic Ocean where they are recovered refurbished and reused. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

  8. 39. VIEW OF CHRYSLER WORKERS LOADING A SATURN IB BOOSTER ...

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

    39. VIEW OF CHRYSLER WORKERS LOADING A SATURN IB BOOSTER INTO THE EAST POSITION ON THE STATIC TEST TOWER. AS THE MAIN CONTRACTOR OF THE SATURN IB BOOSTER, CHRYSLER TOOK OVER OPERATIONS OF THE EAST POSITION OF THE STATIC TEST TOWER IN 1963. THAT SAME YEAR, THE WEST POSITION OF THE TEST TOWER WAS MODIFIED (AS SEEN IN THE PHOTO) FOR RESEARCH AND DEVELOPMENT TESTS OF THE SATURN V BOOSTER'S ENGINE, THE F-1. MARCH 1963, MSFC PHOTO LAB. - Marshall Space Flight Center, Saturn Propulsion & Structural Test Facility, East Test Area, Huntsville, Madison County, AL

  9. Overview of the Pegasus Air-Launched Space Booster

    NASA Astrophysics Data System (ADS)

    Lindberg, Robert E.

    1989-09-01

    The Pegasus Air-Launched Space Booster is an innovative new space launch vehicle now under full-scale development in a privately-funded joint venture by Orbital Sciences Corporation (OSC) and Hercules Aerospace Company. Pegasus is a three-stage, solid-propellant, inertially-guided, all-composite winged vehicle that is launched at an altitude of 40,000 ft from its carrier aircraft. The 41,000 lb vehicle can deliver payloads as massive as 900 lb to low earth orbit. This status report on the Pegasus developemt program first details the advantages of the airborne launch concept, then describes the design and performance of the Pegasus vehicle and conlcludes with a review of the progress of the program from its conception in April 1987 through September 1989. First launch of Pegasus is scheduled for October 31, 1989, under contract to the Defense Advanced Research Projects Agency (DARPA). The second flight under the DARPA contract will be held several months later.

  10. Air Force Reusable Booster System: A Quick-look, Design Focused Modeling and Cost Analysis Study

    NASA Technical Reports Server (NTRS)

    Zapata, Edgar

    2011-01-01

    This paper presents a method and an initial analysis of the costs of a reusable booster system (RBS) as envisioned by the US Department of Defense (DoD) and numerous initiatives that form the concept of Operationally Responsive Space (ORS). This paper leverages the knowledge gained from decades of experience with the semi-reusable NASA Space Shuttle to understand how the costs of a military next generation semi-reusable space transport might behave in the real world - and how it might be made as affordable as desired. The NASA Space Shuttle had a semi-expendable booster, that being the reusable Solid Rocket MotorslBoosters (SRMlSRB) and the expendable cryogenic External Tank (ET), with a reusable cargo and crew capable orbiter. This paper will explore DoD concepts that invert this architectural arrangement, using a reusable booster plane that flies back to base soon after launch, with the in-space elements of the launch system being the expendable portions. Cost estimating in the earliest stages of any potential, large scale program has limited usefulness. As a result, the emphasis here is on developing an approach, a structure, and the basic concepts that could continue to be matured as the program gains knowledge. Where cost estimates are provided, these results by necessity carry many caveats and assumptions, and this analysis becomes more about ways in which drivers of costs for diverse scenarios can be better understood. The paper is informed throughout with a design-for-cost philosophy whereby the design and technology features of the proposed RBS (who and what, the "architecture") are taken as linked at the hip to a desire to perform a certain mission (where and when), and together these inform the cost, responsiveness, performance and sustainability (how) of the system. Concepts for developing, acquiring, producing or operating the system will be shown for their inextricable relationship to the "architecture" of the system, and how these too relate to costs

  11. Monolithic QCL design approaches for improved reliability and affordability

    NASA Astrophysics Data System (ADS)

    Law, K. K.

    2013-12-01

    Many advances have been made recently in mid-wave infrared and long-wave infrared quantum cascade lasers (QCLs) technologies, and there is an increasing demand for these laser sources for ever expanding Naval, DoD and homeland security applications. We will discuss in this paper a portfolio of various Naval Air Warfare Weapons Division's current and future small business innovative research programs and efforts on significantly improving QCLs' performance, affordability, and reliability.

  12. 38. DETAIL OF COOLING WATER BOOSTER PUMP FOR OXYGEN FURNACES, ...

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

    38. DETAIL OF COOLING WATER BOOSTER PUMP FOR OXYGEN FURNACES, LANCES, AND FUME HOODS IN THE GAS WASHER PUMP HOUSE LOOKING EAST. - U.S. Steel Duquesne Works, Basic Oxygen Steelmaking Plant, Along Monongahela River, Duquesne, Allegheny County, PA

  13. 21. VIEW OF CLARK OXYGEN BOOSTER COMPRESSOR IN THE HIGH ...

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

    21. VIEW OF CLARK OXYGEN BOOSTER COMPRESSOR IN THE HIGH PURITY OXYGEN BUILDING LOOKING SOUTH. - U.S. Steel Duquesne Works, Fuel & Utilities Plant, Along Monongahela River, Duquesne, Allegheny County, PA

  14. Solid rocket booster performance evaluation model. Volume 4: Program listing

    NASA Technical Reports Server (NTRS)

    1974-01-01

    All subprograms or routines associated with the solid rocket booster performance evaluation model are indexed in this computer listing. An alphanumeric list of each routine in the index is provided in a table of contents.

  15. The qualification of the shuttle booster separation motors

    NASA Technical Reports Server (NTRS)

    Chase, C. A.; Fisher, K. M.; Eoff, W.

    1978-01-01

    Four booster separation motors (BSM) located at each end of every solid rocket booster (SRB) provide the needed side force to separate the boosters from the external tank at booster burnout. Four BSMs at the top of the SRB are located in a box pattern in the nose cone frustum. The four BSMs at the aft end of the SRB are arranged side-by-side on the SRB aft skirt. Aspects of BSM design and performance are considered, taking into account a motor design/performance summary, the case design, the insulation, the grain design, the nozzle/aft closure design, the ignition system, the propellant, and the motor assembly. Details of motor testing are also discussed, giving attention to development testing, qualification testing, and flight testing.

  16. Aerodynamic separation and glideback of a Mach 3 staged booster

    NASA Astrophysics Data System (ADS)

    Naftel, J. C.; Powell, R. W.

    1990-01-01

    A study has been conducted of the staging maneuver for a two-stage, vertical-takeoff, launch vehicle and the subsequent glideback of the booster to a launch site runway. The booster and orbiter are both winged, fully reusable, and have liquid rocket main propulsion. for the staging maneuver, which nominally occurs at Mach 3, a flight control system and separation technique were devised which produced successful separations over a wide range of staging angles of attack. A guidance algorithm was developed for the unpowered glide-back of the booster from the completion of the staging maneuver to touchdown on a runway in the vicinity of the launch site. Using this guidance technique, the booster successfully touched down on the runway while being subjected to a wide range of seasonal and perturbed atmospheric conditions with and without wids as well as errors in staging state conditions and errors in predicted aerodynamics.

  17. Space Shuttle Solid Rocket Booster Joins Propulsion Park Display

    NASA Video Gallery

    A crane lifts a space shuttle solid rocket booster into its final position in the “propulsion park” outside Building 4205, the Propulsion Research & Development Laboratory at the Marshall Cente...

  18. Closeup view of the Solid Rocket Booster (SRB) Frustum mounted ...

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

    Close-up view of the Solid Rocket Booster (SRB) Frustum mounted on ground support equipment in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center as it is being prepared to be mated with the Nose Cap and Forward Skirt. The Frustum contains the three Main Parachutes, Altitude Switches and forward booster Separation Motors. The Separation Motors burn for one second to ensure the SRBs drift away from the External Tank and Orbiter at separation. The three main parachutes are deployed to reduce speed as the SRBs descend to a splashdown in the Atlantic Ocean where they are recovered refurbished and reused. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

  19. Closeup view of the Solid Rocket Booster (SRB) Frustum mounted ...

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

    Close-up view of the Solid Rocket Booster (SRB) Frustum mounted on ground support equipment in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center as it is being prepared to be mated with the Nose Cap and Forward Skirt. The Frustum contains the three Main Parachutes, Altitude Switches and forward booster Separation Motors. The Separation Motors burn for one second to ensure the SRBs drift away from the External Tank and Orbiter at separation. The three main parachutes are deployed to reduce speed as the SRBs descend to a splashdown in the Atlantic Ocean where they are recovered refurbished and reused. In this view the assembly is rotated so that the four Separation Motors are in view and aligned with the approximate centerline of the image. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

  20. Data on ocean conditions for space shuttle booster recovery criteria

    NASA Technical Reports Server (NTRS)

    Beck, P. E.

    1972-01-01

    Empirical data are presented on the probable sea states that will be encountered by the booster recovery forces. Such data are required to establish the criteria for the recovery equipment and procedures

  1. Approach to an Affordable and Productive Space Transportation System

    NASA Technical Reports Server (NTRS)

    McCleskey, Carey M.; Rhodes, Russel E.; Lepsch, Roger A.; Henderson, Edward M.; Robinson, John W.

    2012-01-01

    This paper describes an approach for creating space transportation architectures that are affordable, productive, and sustainable. The architectural scope includes both flight and ground system elements, and focuses on their compatibility to achieve a technical solution that is operationally productive, and also affordable throughout its life cycle. Previous papers by the authors and other members of the Space Propulsion Synergy Team (SPST) focused on space flight system engineering methods, along with operationally efficient propulsion system concepts and technologies. This paper follows up previous work by using a structured process to derive examples of conceptual architectures that integrate a number of advanced concepts and technologies. The examples are not intended to provide a near-term alternative architecture to displace current near-term design and development activity. Rather, the examples demonstrate an approach that promotes early investments in advanced system concept studies and trades (flight and ground), as well as in advanced technologies with the goal of enabling highly affordable, productive flight and ground space transportation systems.

  2. SIMULATIONS OF TRANSVERSE STACKING IN THE NSLS-II BOOSTER

    SciTech Connect

    Fliller III, R.; Shaftan, T.

    2011-03-28

    The NSLS-II injection system consists of a 200 MeV linac and a 3 GeV booster. The linac needs to deliver 15 nC in 80 - 150 bunches to the booster every minute to achieve current stability goals in the storage ring. This is a very stringent requirement that has not been demonstrated at an operating light source. We have developed a scheme to transversely stack two bunch trains in the NSLS-II booster in order to alleviate the charge requirements on the linac. This scheme has been outlined previously. In this paper we show particle tracking simulations of the tracking scheme. We show simulations of the booster ramp with a stacked beam for a variety of lattice errors and injected beam parameters. In all cases the performance of the proposed stacking method is sufficient to reduce the required charge from the linac. For this reason the injection system of the NSLS-II booster is being designed to include this feature. The NSLS-II injection system consists of a 200 MeV linac and a 3 GeV booster. The injectors must provide 7.5nC in bunch trains 80-150 bunches long every minute for top off operation of the storage ring. Top off then requires that the linac deliver 15nC of charge once losses in the injector chain are taken into consideration. This is a very stringent requirement that has not been demonstrated at an operating light source. For this reason we have developed a method to transversely stack two bunch trains in the booster while maintaining the charge transport efficiency. This stacking scheme has been discussed previously. In this paper we show the simulations of the booster ramp with a single bunch train in the booster. Then we give a brief overview of the stacking scheme. Following, we show the results of stacking two bunch trains in the booster with varying beam emittances and train separations. The behavior of the beam through the ramp is examined showing that it is possible to stack two bunch trains in the booster.

  3. Fermilab's Booster Correction Element Power Supply Silicon Temperature Rise

    SciTech Connect

    Krafczyk, G.; Jensen, C.; Pfeffer, H.; Warchol, G.; /Fermilab

    2009-05-01

    Fermilab is in the process of upgrading its Booster Correction Element System to include full field correction element magnets to correct position and chromaticity throughout the booster cycle. For good reliability of the switchmode power supplies designed to power the magnets, it is important to limit both the maximum temperature and the repetitive temperature cycling of the silicon junctions of the switching elements. We will describe how we measured these parameters and the results of our measurements.

  4. Liquid rocket booster study. Volume 2, book 5, appendix 9: LRB alternate applications and evolutionary growth

    NASA Technical Reports Server (NTRS)

    1989-01-01

    The analyses performed in assessing the merit of the Liquid Rocket Booster concept for use in alternate applications such as for Shuttle C, for Standalone Expendable Launch Vehicles, and possibly for use with the Air Force's Advanced Launch System are presented. A comparison is also presented of the three LRB candidate designs, namely: (1) the LO2/LH2 pump fed, (2) the LO2/RP-1 pump fed, and (3) the LO2/RP-1 pressure fed propellant systems in terms of evolution along with design and cost factors, and other qualitative considerations. A further description is also presented of the recommended LRB standalone, core-to-orbit launch vehicle concept.

  5. Counterrotatable booster compressor assembly for a gas turbine engine

    NASA Technical Reports Server (NTRS)

    Moniz, Thomas Ory (Inventor); Orlando, Robert Joseph (Inventor)

    2004-01-01

    A counterrotatable booster compressor assembly for a gas turbine engine having a counterrotatable fan section with a first fan blade row connected to a first drive shaft and a second fan blade row axially spaced from the first fan blade row and connected to a second drive shaft, the counterrotatable booster compressor assembly including a first compressor blade row connected to the first drive shaft and a second compressor blade row interdigitated with the first compressor blade row and connected to the second drive shaft. A portion of each fan blade of the second fan blade row extends through a flowpath of the counterrotatable booster compressor so as to function as a compressor blade in the second compressor blade row. The counterrotatable booster compressor further includes a first platform member integral with each fan blade of the second fan blade row at a first location so as to form an inner flowpath for the counterrotatable booster compressor and a second platform member integral with each fan blade of the second fan blade row at a second location so as to form an outer flowpath for the counterrotatable booster compressor.

  6. Perpendicular Biased Ferrite Tuned Cavities for the Fermilab Booster

    SciTech Connect

    Romanov, Gennady; Awida, Mohamed; Khabiboulline, Timergali; Pellico, William; Tan, Cheng-Yang; Terechkine, Iouri; Yakovlev, Vyacheslav; Zwaska, Robert

    2014-07-01

    The aging Fermilab Booster RF system needs an upgrade to support future experimental program. The important feature of the upgrade is substantial enhancement of the requirements for the accelerating cavities. The new requirements include enlargement of the cavity beam pipe aperture, increase of the cavity voltage and increase in the repetition rate. The modification of the present traditional parallel biased ferrite cavities is rather challenging. An alternative to rebuilding the present Fermilab Booster RF cavities is to design and construct new perpendicular biased RF cavities, which potentially offer a number of advantages. An evaluation and a preliminary design of the perpendicular biased ferrite tuned cavities for the Fermilab Booster upgrade is described in the paper. Also it is desirable for better Booster performance to improve the capture of beam in the Booster during injection and at the start of the ramp. One possible way to do that is to flatten the bucket by introducing second harmonic cavities into the Booster. This paper also looks into the option of using perpendicularly biased ferrite tuners for the second harmonic cavities.

  7. A rookie's guide to Booster operations. Booster technical note no. 231

    SciTech Connect

    Zeno, K.

    1998-09-29

    The purpose of the Booster is to act as an injector for the AGS. It accelerates both protons and other ions. Proton acceleration is distinguished from the acceleration of other ions for several reasons. First, the experimental physics associated with protons, called High Energy Physics is different than that associated with other Ions, called Heavy Ion Physics. From the machine perspective, the process of injection of so called Heavy Ions (ions which are not protons), is distinctly different, from that of protons. A different preinjector, or injector for the Booster, is used for each case. For Protons, a 200 MeV Linear accelerator (The Linac) serves as a preinjector; for Heavy Ions, the Tandem Van De Graaf (The Tandem) is the preinjector. An attribute of the circulating beam which determines to a large degree what problems and what type of machine setup is involved is the beam intensity. The author's focus in this guide is on trying to convey the knowledge and experience involved in the operation of the Booster. Many of the problems encountered can be traced back to equipment failures, often power supplies. Although diagnostics are used, there can also be issues with the controls system itself. Problems with the controls system and prevent fixing or even finding a problem with a machine. The issue of improving a machines' performance can often involve trial and error and observations. The hard part is finding the relationships between things in the day to day operation of the machine. Abstractions about physics, information about controls and instrumentation, and purely empirical observations of how the machine behaves are all part of it.

  8. Booster propulsion/vehicle impact study, 2

    NASA Technical Reports Server (NTRS)

    Johnson, P.; Satterthwaite, S.; Carson, C.; Schnackel, J.

    1988-01-01

    This is the final report in a study examining the impact of launch vehicles for various boost propulsion design options. These options included: differing boost phase engines using different combinations of fuels and coolants to include RP-1, methane, propane (subcooled and normal boiling point), and hydrogen; variable and high mixture ratio hydrogen engines; translating nozzles on boost phase engines; and cross feeding propellants from the booster to second stage. Vehicles examined included a fully reusable two stage cargo vehicle and a single stage to orbit vehicle. The use of subcooled propane as a fuel generated vehicles with the lowest total vehicle dry mass. Engines with hydrogen cooling generated only slight mass reductions from the reference, all-hydrogen vehicle. Cross feeding propellants generated the most significant mass reductions from the reference two stage vehicle. The use of high mixture ratio or variable mixture ratio hydrogen engines in the boost phase of flight resulted in vehicles with total dry mass 20 percent greater than the reference hydrogen vehicle. Translating nozzles for boost phase engines generated a heavier vehicle. Also examined were the design impacts on the vehicle and ground support subsystems when subcooled propane is used as a fuel. The most significant cost difference between facilities to handle normal boiling point versus subcooled propane is 5 million dollars. Vehicle cost differences were negligible. A significant technical challenge exists for properly conditioning the vehicle propellant on the ground and in flight when subcooled propane is used as fuel.

  9. [Booster vaccination against Bordella pertussis during pregnancy].

    PubMed

    Esteves-Jaramillo, Alejandra; Gómez Altamirano, César Misael; Esparza Aguilar, Marcelino; López-Collada, Vesta L Richardson

    2012-05-01

    During the last decades, the incidence of whopping cough, has been rising worldwide, despite the high coverage of the immunization programs. The highest mortality is found among children under 6 month of age, who are too young to have completed a primary vaccination series with three doses the pertussis vaccine, nevertheless this disease also affects adolescents and adults, who may only manifest mild symptomatology. Hence they do not get diagnosed or treated, becoming a potential community source of infection for young children. In order to prevent this transmission, the recommendation of vaccinating adolescents and adults, including of women in child bearing age, was issued. Nevertheless the immunization coverage among these populations was low. Postpartum vaccination was also recommended, but recent evidence have shown that the antibody levels in breast milk are detectable at least a week after immunization, allowing a window of opportunity for the infection in the newborn. Finally, it has been suggested that a booster dose against Bordetella pertussis, given to pregnant women is safe and immunogenic. Therefore, the antibody transferred across the placenta and through breast milk, could protect the product in the early stages of life. PMID:23301426

  10. NSRL Extraction Bump Control in the Booster

    SciTech Connect

    Brennan,L.

    2008-10-01

    Due to inadequacies in the user interface of the booster orbit control system, a number of new tools were developed. The first priority was an accurate calculation of the winding currents given specific displacements at each extraction septa. Next, the physical limits of the power supplies ({+-}600 amps) needed to be taken into account. In light of this limit, a system is developed that indicates to the user what the allowed values of one bump parameter are once the other two have been specified. Finally, techniques are developed to account for the orbit behavior once power supplies are requested to exceed their {+-}600 amp limit. This includes a recalculation of bump parameters and a calculation of the amplitude of the residuals. Following this, possible areas for further development are outlined. These techniques were computationally developed in Mathematica and tested in the Methodical Accelerator Design (MAD) program before they were implemented into the control system. At the end, a description of the implementation of these techniques in a new interface is described. This includes a depiction of the appearance and functionality of the graphical user interface, a description of the input and output flow, and an outline of how each important calculation is performed.

  11. Multiphase booster ups production from subsea well

    SciTech Connect

    1995-05-01

    The Rogn South subsea well has the world`s first commercial subsea multiphase boosting system. The well produces to A/S Norske Shell`s Draugen field, in the Norwegian Sea. The Smubs (Shell multiphase underwater booster station) provides additional energy to transport a mixture of gas and liquids over long distances. This reduces the back pressure on the reservoir to potentially enhance both production and recovery. In-house Shell International Petroleum Maatschappij B.V. (SIPM) has studied estimated facility costs and performance for a multiphase boosting system for a typical small (50 million bbl) field between 20--50 km from a host facility in water depths between 150--1,000 m. The studies showed that technical costs per barrel of oil produced could be cut by up to 30% compared to conventional technology. The Smubs main features are: A single retrievable cartridge that houses all active components susceptible to wear; No orientation requirements for the pump cartridge unit; No orientation requirements for the pump cartridge unit; Hydraulically set and tested seals; and Vertical installation and retrieval with a single tool, and a remotely operated vehicle (ROV) only for a monitoring.

  12. Booster Applications Facility report, Phase 2

    SciTech Connect

    Thieberger, P.

    1991-06-01

    This report summarizes studies and planning performed by Brookhaven National Laboratory (BNL) personnel at the request of NASA for the design, construction and operation of experimental areas and facilities for utilization of ion beams from the BNL Booster synchrotron particle accelerator. These facilities would be primarily utilized to simulate space radiation for radiobiological research, shielding studies and detector calibrations. The feasibility of such a project has been established, preliminary designs and cost estimates have been developed and a formal proposal can be submitted pending DOE concurrence. The main body of this report consists of the material presented by BNL during the meeting with a NASA appointed Panel on December 10 and 11, 1990. The individual speakers have provided brief summaries of their talks and explanations of their figures. In addition there are two appendices. One, contains detailed discussion of the shared mode of operation and the corresponding beam compatibility tables. The second appendix contains cost estimate details. An executive summary on budgets and schedules has been added, containing possible phased construction and outfitting scenarios and the corresponding expense and commitment profiles as well as new operational cost estimates. Material contained in the executive summary reflects the correction of some errors and new studies performed in response to the NASA Panel suggestions.

  13. Commercial Platforms Allow Affordable Space Research

    NASA Technical Reports Server (NTRS)

    2013-01-01

    At an altitude of about 240 miles, its orbital path carries it over 90 percent of the Earth s population. It circles the Earth in continuous free fall; its crew of six and one Robonaut pass the days, experiencing 16 sunrises and 16 sunsets every 24 hours, in microgravity, an environment in which everything from bodily functions to the physical behavior of materials changes drastically from what is common on the ground. Outside its shielded confines, temperatures cycle from one extreme to the other, radiation is rampant, and atomic oxygen corrodes everything it touches. A unique feat of engineering, the International Space Station (ISS) also represents the most remarkable platform for scientific research ever devised. In 2005, anticipating the space station s potential for NASA and non-NASA scientists alike, the NASA Authorization Act designated the US segment of the ISS as a national laboratory, instructing the Agency to "increase the utilization of the ISS by other Federal entities and the private sector." With the ISS set to maintain operations through at least 2020, the station offers an unprecedented long-term access to space conditions, enabling research not previously possible. "There will be new drug discoveries, new pharmaceuticals, a better understanding of how we affect the planet and how we can maintain it," says Marybeth Edeen, the ISS National Laboratory manager, based at Johnson Space Center. The ISS, she says, represents a major example of the government s role in making such advancements possible. "The government is key in that researchers cannot afford to build the kind of infrastructure that the government can provide. But we then have to make that infrastructure available at a reasonable cost." Enter Jeff Manber, who saw in the ISS National Lab an extraordinary opportunity to advance science, education, and business in ways never before seen.

  14. 24 CFR 572.120 - Affordability standards.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... 24 Housing and Urban Development 3 2014-04-01 2013-04-01 true Affordability standards. 572.120...) Homeownership Program Requirements-Implementation Grants § 572.120 Affordability standards. (a) Initial... annual incomes of eligible families using reasonable standards and procedures consistently applied.)...

  15. College Affordability: Implications for College Opportunity

    ERIC Educational Resources Information Center

    Perna, Laura W.; Li, Chunyan

    2006-01-01

    By examining trends in college affordability, this article explores the extent to which the public perception that college is not affordable is justified. First, the article describes trends in national indicators that contribute to ability to pay, including income growth, health care costs, debt burden, and personal savings rates. Trends in…

  16. Affordability Funding Models for Early Childhood Services

    ERIC Educational Resources Information Center

    Purcal, Christiane; Fisher, Karen

    2006-01-01

    This paper presents a model of the approaches open to government to ensure that early childhood services are affordable to families. We derived the model from a comparative literature review of affordability approaches taken by government, both in Australia and internationally. The model adds significantly to the literature by proposing a means to…

  17. Section 8: Affordable Housing for Exceptional Families

    ERIC Educational Resources Information Center

    Wright, Wesley E.

    2009-01-01

    Shelter is a basic human need. Unfortunately, affordable housing is a need that low income families who are caring for children and adults with disabilities can rarely afford without assistance. Because participating families generally pay rent of no more than 30 percent of their adjusted monthly income, the Section 8 program can provide…

  18. Advanced Space Transportation Concepts and Propulsion Technologies for a New Delivery Paradigm

    NASA Technical Reports Server (NTRS)

    Robinson, John W.; McCleskey, Carey M.; Rhodes, Russel E.; Lepsch, Roger A.; Henderson, Edward M.; Joyner, Claude R., III; Levack, Daniel J. H.

    2013-01-01

    This paper describes Advanced Space Transportation Concepts and Propulsion Technologies for a New Delivery Paradigm. It builds on the work of the previous paper "Approach to an Affordable and Productive Space Transportation System". The scope includes both flight and ground system elements, and focuses on their compatibility and capability to achieve a technical solution that is operationally productive and also affordable. A clear and revolutionary approach, including advanced propulsion systems (advanced LOX rich booster engine concept having independent LOX and fuel cooling systems, thrust augmentation with LOX rich boost and fuel rich operation at altitude), improved vehicle concepts (autogeneous pressurization, turbo alternator for electric power during ascent, hot gases to purge system and keep moisture out), and ground delivery systems, was examined. Previous papers by the authors and other members of the Space Propulsion Synergy Team (SPST) focused on space flight system engineering methods, along with operationally efficient propulsion system concepts and technologies. This paper continues the previous work by exploring the propulsion technology aspects in more depth and how they may enable the vehicle designs from the previous paper. Subsequent papers will explore the vehicle design, the ground support system, and the operations aspects of the new delivery paradigm in greater detail.

  19. Monte Carlo modeling and analyses of YALINA-booster subcritical assembly part 1: analytical models and main neutronics parameters.

    SciTech Connect

    Talamo, A.; Gohar, M. Y. A.; Nuclear Engineering Division

    2008-09-11

    This study was carried out to model and analyze the YALINA-Booster facility, of the Joint Institute for Power and Nuclear Research of Belarus, with the long term objective of advancing the utilization of accelerator driven systems for the incineration of nuclear waste. The YALINA-Booster facility is a subcritical assembly, driven by an external neutron source, which has been constructed to study the neutron physics and to develop and refine methodologies to control the operation of accelerator driven systems. The external neutron source consists of Californium-252 spontaneous fission neutrons, 2.45 MeV neutrons from Deuterium-Deuterium reactions, or 14.1 MeV neutrons from Deuterium-Tritium reactions. In the latter two cases a deuteron beam is used to generate the neutrons. This study is a part of the collaborative activity between Argonne National Laboratory (ANL) of USA and the Joint Institute for Power and Nuclear Research of Belarus. In addition, the International Atomic Energy Agency (IAEA) has a coordinated research project benchmarking and comparing the results of different numerical codes with the experimental data available from the YALINA-Booster facility and ANL has a leading role coordinating the IAEA activity. The YALINA-Booster facility has been modeled according to the benchmark specifications defined for the IAEA activity without any geometrical homogenization using the Monte Carlo codes MONK and MCNP/MCNPX/MCB. The MONK model perfectly matches the MCNP one. The computational analyses have been extended through the MCB code, which is an extension of the MCNP code with burnup capability because of its additional feature for analyzing source driven multiplying assemblies. The main neutronics parameters of the YALINA-Booster facility were calculated using these computer codes with different nuclear data libraries based on ENDF/B-VI-0, -6, JEF-2.2, and JEF-3.1.

  20. Affordability Approaches for Human Space Exploration

    NASA Technical Reports Server (NTRS)

    Holladay, Jon; Smith, David Alan

    2012-01-01

    The design and development of historical NASA Programs (Apollo, Shuttle and International Space Station), have been based on pre-agreed missions which included specific pre-defined destinations (e.g., the Moon and low Earth orbit). Due to more constrained budget profiles, and the desire to have a more flexible architecture for Mission capture as it is affordable, NASA is working toward a set of Programs that are capability based, rather than mission and/or destination specific. This means designing for a performance capability that can be applied to a specific human exploration mission/destination later (sometime years later). This approach does support developing systems to flatter budgets over time, however, it also poses the challenge of how to accomplish this effectively while maintaining a trained workforce, extensive manufacturing, test and launch facilities, and ensuring mission success ranging from Low Earth Orbit to asteroid destinations. NASA Marshall Space Flight Center (MSFC) in support of Exploration Systems Directorate (ESD) in Washington, DC has been developing approaches to track affordability across multiple Programs. The first step is to ensure a common definition of affordability: the discipline to bear cost in meeting a budget with margin over the life of the program. The second step is to infuse responsibility and accountability for affordability into all levels of the implementing organization since affordability is no single person s job; it is everyone s job. The third step is to use existing data to identify common affordability elements organized by configuration (vehicle/facility), cost, schedule, and risk. The fourth step is to analyze and trend this affordability data using an affordability dashboard to provide status, measures, and trends for ESD and Program level of affordability tracking. This paper will provide examples of how regular application of this approach supports affordable and therefore sustainable human space exploration

  1. Hybrid boosters for future launch vehicles

    NASA Astrophysics Data System (ADS)

    Dargies, E.; Lo, R. E.

    There is a striking similarity in the design of the US Space Transportation System, the European ARI-ANE 5P and the Japanese II-II: they all use a high energy cryogenic core stage along with two large solid propellant rocket boosters (SRB's) in order to provide for a high lift-off thrust level. Prior to last years disasters with Challenger and Titan it was widely held that SRB's were cheap, uncomplicated and safe. Even before the revelation by these accidents of severe safety hazards, shuttle operations demonstrated that the SRB's were by no means as cheap as reusable systems ought to be. In addition, they became known as sources of considerable environmental pollution. In contrast, hybrid rocket propulsion systems offer the following potential advantages: • much higher savety level (TNT equivalent almost zero, shut-down capability in case of ignition failure of one unit, inert against unbonding) • choice of non-toxic propellant combinations • equal or higher specific performance For these reasons, system analysis were carried out to examine hybrids as potential alternative to SRB's. Various analytical tools (mass- and performance models, trajectory simulation etc.) were developed for parametrical studies of hybrid propulsion systems. Special attention was devoted to the well-known primary concern of hybrids: geometrical design of the solid fuel grain and regression rate of the ablating surface. Experimental data were used as input wherever possible. In 1985 first studies were carried out to find possible fields of application for hybrid rocket engines. A mass model and a performance model for hybrid rocket motors were developed, taking into account the peculiarities of hybrid combustion as there are i.e. low regression rate and shifting mixture ratio during operation. After some analytical work was done, hybrids proved to be a promising alternative to SRB's. Compared with solids, hybrids offer many advantages.

  2. First results of proton injection commissioning of the AGS Booster synchrotron

    SciTech Connect

    Reece, R.K.; Ahrens, L.; Alessi, J.; Bleser, E.; Brennan, J.M.; Luccio, A.; Skelly, J.; Soukas, A.; van Asselt, W.; Weng, W.T.; Witkover, R.

    1991-01-01

    Beam performance for the injection phase of proton beam commissioning of the AGS Booster synchrotron will be presented. The beam from the 200 MeV Linac is transported through a new beam line into the Booster. This Linac-to Booster (LTB) beam line includes a 126{degree} bend and brings the injected beam onto the Booster injection orbit through the backleg of a main ring dipole magnet. Transfer of beam from the Linac to the Booster, spiralling beam and closing the orbit in the Booster ring are discussed. Injection and transport through one sector of the ring has been accomplished. 8 refs., 1 fig.

  3. Estimation of critical flow velocity for collapse of booster fuel assembly

    SciTech Connect

    Donna Guillen; Mark J. Russell

    2005-09-01

    A Gas Test Loop (GTL) system is currently being designed to provide a high intensity fast-flux irradiation environment for testing fuels and materials for advanced concept nuclear reactors. To assess the performance of candidate reactor fuels, these fuels must be irradiated under actual fast reactor flux conditions and operating environments, preferably in an existing irradiation facility. The GTL system is being designed for operation in the northwest test lobe of the Advanced Test Reactor (ATR) at the Idaho National Laboratory. The Technical and Functional Requirements (T&FRs) for the GTL stipulate a minimum neutron flux intensity (10{sup 15} n/cm{sup 2} {center_dot} s) and fast to thermal neutron ratio (>15) for the test environment. The incorporation of booster fuel within the test lobe is necessary to achieve these neutron flux requirements. The current design of the booster fuel assembly for the GTL calls for 3 concentric rings of 4 ft long uranium silicide fuel plates clad with 6061 aluminum.

  4. Booster Synchrotron RF System Upgrade for SPEAR3

    SciTech Connect

    Park, Sanghyun; Corbett, Jeff; /SLAC

    2012-07-06

    Recent progress at the SPEAR3 includes the increase in stored current from 100 mA to 200 mA and top-off injection to allow beamlines to stay open during injection. Presently the booster injects 3.0 GeV beam to SPEAR3 three times a day. The stored beam decays to about 150 mA between the injections. The growing user demands are to increase the stored current to the design value of 500 mA, and to maintain it at a constant value within a percent or so. To achieve this goal the booster must inject once every few minutes. For improved injection efficiency, all RF systems at the linac, booster and SPEAR3 need to be phase-locked. The present booster RF system is basically a copy of the SPEAR2 RF system with 358.5 MHz and 40 kW peak RF power driving a 5-cell RF cavity for 1.0 MV gap voltage. These requirements entail a booster RF system upgrade to a scaled down version of the SPEAR3 RF system of 476.3 MHz with 1.2 MW cw klystron output power capabilities. We will analyze each subsystem option for their merits within budgetary and geometric space constraints. A substantial portion of the system will come from the decommissioned PEP-II RF stations.

  5. Understanding and improving the Fermilab booster high field orbit

    SciTech Connect

    Chao, Y.; Ketcham, L.; Moore, C.D.

    1989-03-01

    This note is an account of the authors' effort in both understanding the Booster high field orbit and controlling it through displacements of the main combined function magnets. We were able to achieve the second goal with considerable accuracy while having limited success with the first, due to insufficient knowledge of the Booster dynamics. This work was initiated in Spring 1987 with the orbit control via magnet moves the chief purpose. A series of magnet moves in 1987 and 1988 resulting from this study testified to its reliability. The understanding of the Booster orbit in general remains an ongoing process in which we keep modifying our model with the hope of eventually having a quantitative grasp of the closed orbit and being able to manipulate it with more flexibility and accuracy. In this paper we give a brief description of the Booster environment in which the magnet moves are carried out, together with background information concerning the magnet moves. The method we use is discussed. The result of the moves is documented, and our effort to understand the Booster high field orbit is given a detailed account. 12 figs., 5 tabs.

  6. A Unique Hybrid Propulsion System Design for Large Space Boosters

    NASA Technical Reports Server (NTRS)

    Rodgers, Frederick C.

    1990-01-01

    A study was made of the application of hybrid rocket propulsion technology to large space boosters. Safety, reliability, cost, and performance comprised the evaluation criteria, in order of relative importance, for this study. The effort considered the so called classic hybrid design approach versus a novel approach which utilizes a fuel-rich gas generator for the fuel source. Other trades included various fuel/oxidizer combinations, pressure-fed versus pump fed oxidizer delivery systems, and reusable versus expandable booster systems. Following this initial trade study, a point design was generated. A gas generated-type fuel grain with pump fed liquid oxygen comprised the basis of this point design. This design study provided a mechanism for considering the means of implementing the gas generator approach for further defining details of the design. Subsequently, a system trade study was performed which determined the sensitivity of the design to various design parameters and predicted optimum values for these same parameters. The study concluded that a gas generator hybrid booster design offers enhanced safety and reliability over current of proposed solid booster designs while providing equal or greater performance levels. These improvements can be accomplished at considerably lower cost than for the liquid booster designs of equivalent capability.

  7. Affordable WDM components: the polymer solution

    NASA Astrophysics Data System (ADS)

    Eldada, Louay A.; Yin, Shing; Norwood, Robert A.; Yardley, James T.

    1998-02-01

    An advanced polymeric waveguide technology was developed for affordable WDM components that address the needs of both the Telecom and the Datacom industries. We engineered high- performance organic polymers that can be readily made into both multimode and single-mode optical waveguide structures of controlled numerical aperture and geometry. These materials are formed from highly-crosslinked acrylate monomers with specific linkages that determine properties such as flexibility, toughness, loss, and environmental stability. These monomers are intermiscible, providing for precise adjustment of the refractive index from 1.3 to 1.6. In polymer form, they exhibit state-of-the-art loss values, high thermal stability, high humidity resistance, low dispersion and low birefringence. Waveguides are formed photolithographically, with the liquid monomer mixture polymerizing upon illumination in the UV via either mask exposure or laser direct writing. A wide range of rigid and flexible substrates can be used, including glass, quartz, oxidized silicon, glass-filled epoxy printed circuit board substrate, and flexible polyimide film. Waveguiding structures measuring tens of inches in length can be produced on computer boards, and guides that are meters long can be printed on rolls of plastic. We describe the fabrication of both Bragg gratings and waveguide grating routes in our polymers for filtering and demultiplexing applications in Telecom WDM systems. In Datacom, we describe polymeric components that we produced for aerospace WDM sensor systems. The importance of CAD tools in designing WDM devices is emphasized in this work. We further discuss the low-cost manufacturing of WDM components in an industrial environment.

  8. New pulsed orbit bump magnets for the Fermilab Booster Synchrotron

    SciTech Connect

    Lackey, J.R.; Carson, J.A.; Ginsburg, C.M.; Glass, H.D.; Harding, D.J.; Kashikhin, V.S.; Makarov, A.; Prebys, E.J.; /Fermilab

    2005-05-01

    The beam from the Fermilab Linac is injected onto a bump in the closed orbit of the Booster Synchrotron where a carbon foil strips the electrons from the Linac's negative ion hydrogen beam. Although the Booster itself runs at 15 Hz, heat dissipation in the orbit bump magnets has been one limitation to the fraction of the cycles that can be used for beam. New 0.28 T pulsed dipole magnets have been constructed that will fit into the same space as the old ones, run at the full repetition rate of the Booster, and provide a larger bump to allow a cleaner injection orbit. The new magnets use a ferrite in the yoke rather than laminated steel.

  9. Feasibility of recovering a one million-pound booster

    NASA Technical Reports Server (NTRS)

    Toni, R. A.; Eckstrom, C. V.

    1980-01-01

    The concept of reusing spacecraft and launch vehicles is currently exemplified by the Space Shuttle Orbiter and the two recoverable and reusable solid rocket boosters (SRBs) which are part of its launch system. It is shown that it is possible to recover launch systems weighing as much as one million pounds at reasonable impact velocities using a hybrid parachute-retrorocket recovery system. The new Kevlar materials, which have a much higher strength-to-weight ratio than nylon materials, make it possible to recover a one-million-pound booster for a reasonable weight penalty. The selected input parameters to the parachute weight equation result in an accurate estimation of the current Space Shuttle solid rocket booster parachute recovery system.

  10. Economics of the solid rocket booster for space shuttle

    NASA Technical Reports Server (NTRS)

    Rice, W. C.

    1979-01-01

    The paper examines economics of the solid rocket booster for the Space Shuttle. Costs have been held down by adapting existing technology to the 146 in. SRB selected, with NASA reducing the cost of expendables and reusing the expensive nonexpendable hardware. Drop tests of Titan III motor cases and nozzles proved that boosters can survive water impact at vertical velocities of 100 ft/sec so that SRB components can be reused. The cost of expendables was minimized by selecting proven propellants, insulation, and nozzle ablatives of known costs; the propellant has the lowest available cost formulation, and low cost ablatives, such as pitch carbon fibers, will be used when available. Thus, the use of proven technology and low cost expendables will make the SRB an economical booster for the Space Shuttle.

  11. The Solid Rocket Booster Auxiliary Power Unit: Meeting the Challenge

    NASA Technical Reports Server (NTRS)

    Hughes, R. W.

    1985-01-01

    The thrust vector control systems of the solid rocket boosters are turbine-powered, electrically controlled hydraulic systems which function through hydraulic actuators to gimbal the nozzles of the solid rocket boosters and provide vehicle steering for the Space Shuttle. Turbine power for the thrust vector control systems is provided through hydrazine fueled auxiliary power units which drive the hydraulic pumps. The solid rocket booster auxiliary power unit resulted from trade studies which indicated significant advantages would result if an existing engine could be found to meet the program goal of 20 missions reusability and adapted to meet the seawater environments associated with ocean landings. During its maturation, the auxiliary power unit underwent many design iterations and provided its flight worthiness through full qualification programs both as a component and as part of the thrust vector control system. More significant, the auxiliary power unit has successfully completed six Shuttle missions.

  12. Left atrial booster function in valvular heart disease

    PubMed Central

    Heidenreich, Fred P.; Shaver, James A.; Thompson, Mark E.; Leonard, James J.

    1970-01-01

    This study was designed to assess atrial booster pump action in valvular heart disease and to dissect booster pump from reservoir-conduit functions. In five patients with aortic stenosis and six with mitral stenosis, sequential atrioventricular (A-V) pacing was instituted during the course of diagnostic cardiac catheterization. Continuous recording of valvular gradient allowed estimation of flow for each cardiac cycle by transposition of the Gorlin formula. Left ventricular ejection time and left ventricular stroke work in aortic stenosis or left ventricular mean systolic pressure in mitral stenosis were also determined. Control observations were recorded during sequential A-V pacing with well-timed atrial systole. Cardiac cycles were then produced with no atrial contraction but undisturbed atrial reservoir function by intermittently interrupting the atrial pacing stimulus during sequential A-V pacing. This intervention significantly reduced valvular gradient, flow, left ventricular ejection time, and left ventricular mean systolic pressure or stroke work. Cardiac cycles were then produced with atrial booster action eliminated by instituting synchronous A-V pacing. The resultant simultaneous contraction of the atrium and ventricle not only eliminated effective atrial systole but also placed atrial systole during the normal period of atrial reservoir function. This also significantly reduced all the hemodynamic measurements. However, comparison of the magnitude of change from these two different pacing interventions showed no greater impairment of hemodynamic state when both booster pump action and reservoir function were impaired than when booster pump action alone was impaired. The study confirms the potential benefit of well placed atrial booster pump action in valvular heart disease in man. PMID:5449701

  13. The Booster to AGS beam transfer fast kicker systems

    SciTech Connect

    Zhang, W.; Bunicci, J.; Soukas, A.V.; Zhang, S.Y.

    1992-01-01

    The Brookhaven AGS Booster has a very successful commissioning period in June 1991. The third phase of that commissioning was a beam extraction test. The Booster extraction fast kicker (F3) deflected a 1.2 GeV proton beam from the Booster circulating orbit into the extraction septum aperture, partially down the extraction line to a temporary beam stop. Now, the Booster is committed to the AGS operations program for both heavy ion and proton beams. Thus, the Booster extraction and the corresponding AGS injection systems must operate routinely up to a pulse repetition frequency of 7.5 Hertz, and up to a beam energy of 1.5 Gev. The injection fast kicker is located in the A5 section of the AGS ring and is used to deflect the proton or heavy ion beam into its final AGS closed orbit. A distinctive feature of the AGS injection fast kicker modulators is the tail-bitting function required for proton beam injection. This enables the system to produce a fast current fall time to go along with the high current pulse amplitude with a fast rise time. The AGS injection fast kicker system has three pulse modulators, and each modulator consists of two thyratrons. The main PFN thyratrons switch on the current, and the tail bitting thyratrons are used to force the magnet current to decrease rapidly. Two digital pulse delay generators are used to align the main thyratrons and the tail bitting thyratrons respectively. The system has been tested and installed. The final commissioning of the Booster to AGS beam transfer line and injection is currently being undertaken. In this article, the system design, realization techniques and performance data will be presented.

  14. The Booster to AGS beam transfer fast kicker systems

    SciTech Connect

    Zhang, W.; Bunicci, J.; Soukas, A.V.; Zhang, S.Y.

    1992-08-01

    The Brookhaven AGS Booster has a very successful commissioning period in June 1991. The third phase of that commissioning was a beam extraction test. The Booster extraction fast kicker (F3) deflected a 1.2 GeV proton beam from the Booster circulating orbit into the extraction septum aperture, partially down the extraction line to a temporary beam stop. Now, the Booster is committed to the AGS operations program for both heavy ion and proton beams. Thus, the Booster extraction and the corresponding AGS injection systems must operate routinely up to a pulse repetition frequency of 7.5 Hertz, and up to a beam energy of 1.5 Gev. The injection fast kicker is located in the A5 section of the AGS ring and is used to deflect the proton or heavy ion beam into its final AGS closed orbit. A distinctive feature of the AGS injection fast kicker modulators is the tail-bitting function required for proton beam injection. This enables the system to produce a fast current fall time to go along with the high current pulse amplitude with a fast rise time. The AGS injection fast kicker system has three pulse modulators, and each modulator consists of two thyratrons. The main PFN thyratrons switch on the current, and the tail bitting thyratrons are used to force the magnet current to decrease rapidly. Two digital pulse delay generators are used to align the main thyratrons and the tail bitting thyratrons respectively. The system has been tested and installed. The final commissioning of the Booster to AGS beam transfer line and injection is currently being undertaken. In this article, the system design, realization techniques and performance data will be presented.

  15. MISSE-X: Affordable Space Environment Testing

    NASA Video Gallery

    MISSE–X is a robotically serviceable ISS external facility providing government, industry and academia experimenters with affordable access to space for materials durability testing of potential ...

  16. Body-scaled affordances in sensory substitution.

    PubMed

    Travieso, David; Gómez-Jordana, Luis; Díaz, Alex; Lobo, Lorena; Jacobs, David M

    2015-12-15

    The research field on sensory substitution devices has strong implications for theoretical work on perceptual consciousness. One of these implications concerns the extent to which the devices allow distal attribution. The present study applies a classic empirical approach on the perception of affordances to the field of sensory substitution. The reported experiment considers the perception of the stair-climbing affordance. Participants judged the climbability of steps apprehended through a vibrotactile sensory substitution device. If measured with standard metric units, climbability judgments of tall and short participants differed, but if measured in units of leg length, judgments did not differ. These results are similar to paradigmatic results in regular visual perception. We conclude that our sensory substitution device allows the perception of affordances. More generally, we argue that the theory of affordances may enrich theoretical debates concerning sensory substitution to a larger extent than has hitherto been the case. PMID:26587958

  17. Initiation Capacity of a Specially Shaped Booster Pellet and Numerical Simulation of Its Initiation Process

    NASA Astrophysics Data System (ADS)

    Hu, Li-Shuang; Hu, Shuang-Qi; Cao, Xiong; Zhang, Jian-Ren

    2014-01-01

    The insensitive main charge explosive is creating new requirements for the booster pellet of detonation trains. The traditional cylindrical booster pellet has insufficient energy output to reliably initiate the insensitive main charge explosive. In this research, a concave spherical booster pellet was designed. The initiation capacity of the concave spherical booster pellet was studied using varied composition and axial steel dent methods. The initiation process of the concave spherical booster pellet was also simulated by ANSYS/LS-DYNA. The results showed that using a concave spherical booster allows a 42% reduction in the amount of explosive needed to match the initiation capacity of a conventional cylindrical booster of the same dimensions. With the other parameters kept constant, the initiation capacity of the concave spherical booster pellet increases with decreased cone angle and concave radius. The numerical simulation results are in good agreement with the experimental data.

  18. Space shuttle with common fuel tank for liquid rocket booster and main engines (supertanker space shuttle)

    NASA Technical Reports Server (NTRS)

    Thorpe, Douglas G.

    1991-01-01

    An operation and schedule enhancement is shown that replaces the four-body cluster (Space Shuttle Orbiter (SSO), external tank, and two solid rocket boosters) with a simpler two-body cluster (SSO and liquid rocket booster/external tank). At staging velocity, the booster unit (liquid-fueled booster engines and vehicle support structure) is jettisoned while the remaining SSO and supertank continues on to orbit. The simpler two-bodied cluster reduces the processing and stack time until SSO mate from 57 days (for the solid rocket booster) to 20 days (for the liquid rocket booster). The areas in which liquid booster systems are superior to solid rocket boosters are discussed. Alternative and future generation vehicles are reviewed to reveal greater performance and operations enhancements with more modifications to the current methods of propulsion design philosophy, e.g., combined cycle engines, and concentric propellant tanks.

  19. Modulation of visual attention by object affordance.

    PubMed

    Garrido-Vásquez, Patricia; Schubö, Anna

    2014-01-01

    Some objects in our environment are strongly tied to motor actions, a phenomenon called object affordance. A cup, for example, affords us to reach out to it and grasp it by its handle. Studies indicate that merely viewing an affording object triggers motor activations in the brain. The present study investigated whether object affordance would also result in an attention bias, that is, whether observers would rather attend to graspable objects within reach compared to non-graspable but reachable objects or to graspable objects out of reach. To this end, we conducted a combined reaction time and motion tracking study with a table in a virtual three-dimensional space. Two objects were positioned on the table, one near, the other one far from the observer. In each trial, two graspable objects, two non-graspable objects, or a combination of both was presented. Participants were instructed to detect a probe appearing on one of the objects as quickly as possible. Detection times served as indirect measure of attention allocation. The motor association with the graspable object was additionally enhanced by having participants grasp a real object in some of the trials. We hypothesized that visual attention would be preferentially allocated to the near graspable object, which should be reflected in reduced reaction times in this condition. Our results confirm this assumption: probe detection was fastest at the graspable object at the near position compared to the far position or to a non-graspable object. A follow-up experiment revealed that in addition to object affordance per se, immediate graspability of an affording object may also influence this near-space advantage. Our results suggest that visuospatial attention is preferentially allocated to affording objects which are immediately graspable, and thus establish a strong link between an object' s motor affordance and visual attention. PMID:24567725

  20. Electron cloud and space charge effects in the Fermilab Booster

    SciTech Connect

    Ng, K.Y.; /Fermilab

    2007-06-01

    The stable region of the Fermilab Booster beam in the complex coherent-tune-shift plane appears to have been shifted far away from the origin by its intense space charge making Landau damping appear impossible. Simulations reveal a substantial buildup of electron cloud in the whole Booster ramping cycle, both inside the unshielded combined-function magnets and the beam pipes joining the magnets, whenever the secondary-emission yield (SEY) is larger than {approx}1.6. The implication of the electron-cloud effects on the space charge and collective instabilities of the beam is investigated.

  1. Space shuttle solid rocket booster recovery system definition, volume 1

    NASA Technical Reports Server (NTRS)

    1973-01-01

    The performance requirements, preliminary designs, and development program plans for an airborne recovery system for the space shuttle solid rocket booster are discussed. The analyses performed during the study phase of the program are presented. The basic considerations which established the system configuration are defined. A Monte Carlo statistical technique using random sampling of the probability distribution for the critical water impact parameters was used to determine the failure probability of each solid rocket booster component as functions of impact velocity and component strength capability.

  2. Multi-Physics Analysis of the Fermilab Booster RF Cavity

    SciTech Connect

    Awida, M.; Reid, J.; Yakovlev, V.; Lebedev, V.; Khabiboulline, T.; Champion, M.; /Fermilab

    2012-05-14

    After about 40 years of operation the RF accelerating cavities in Fermilab Booster need an upgrade to improve their reliability and to increase the repetition rate in order to support a future experimental program. An increase in the repetition rate from 7 to 15 Hz entails increasing the power dissipation in the RF cavities, their ferrite loaded tuners, and HOM dampers. The increased duty factor requires careful modelling for the RF heating effects in the cavity. A multi-physic analysis investigating both the RF and thermal properties of Booster cavity under various operating conditions is presented in this paper.

  3. Observation and correction of resonance stopbands in the AGS Booster

    SciTech Connect

    Gardner, C.; Shoji, Y.; Ahrens, L.; Glenn, J.W.; Lee, Y.Y.; Roser, T.; Soukas, A.; van Asselt, W.; Weng, W.T.

    1993-06-01

    At the design intensity of 1.5 {times} 10{sup 13} ppp, the space charge tune shift in the AGS Booster at injection has been estimated to be about 0.35. Therefore, the beam is spread over may lower order resonance lines and the stopbands have to be corrected to minimize the amplitude growth by proper compensation of the driving harmonics resulting from random errors. The observation and correction of second and third order resonance stopbands in the AGS Booster, and the establishment of a favorable operating point at high intensity are discussed.

  4. Measured longitudinal beam impedance of booster gradient magnets

    SciTech Connect

    James L Crisp and Brian J. Fellenz

    2001-08-24

    The Booster gradient magnets have no vacuum pipe which forces the beam image current to flow along the laminated pole tips. Both D and F style magnets were measured with a stretched wire to determine the longitudinal beam impedance caused by these laminations. Results are compared to calculations done 30 years ago. The inductive part of the magnet impedance is interesting because it partially compensates for the negative inductance effects of space charge on the beam. An R/L circuit consisting of 37K{center_dot} in parallel with between 40 and 100uH is a reasonable approximation to the total impedance of Booster magnet laminations.

  5. Debris control design achievements of the booster separation motors

    NASA Technical Reports Server (NTRS)

    Smith, G. W.; Chase, C. A.

    1985-01-01

    The stringent debris control requirements imposed on the design of the Space Shuttle booster separation motor are described along with the verification program implemented to ensure compliance with debris control objectives. The principal areas emphasized in the design and development of the Booster Separation Motor (BSM) relative to debris control were the propellant formulation and nozzle closures which protect the motors from aerodynamic heating and moisture. A description of the motor design requirements, the propellant formulation and verification program, and the nozzle closures design and verification are presented.

  6. The Affordable Care Act versus Medicare for All.

    PubMed

    Seidman, Laurence

    2015-08-01

    Many problems facing the Affordable Care Act would disappear if the nation were instead implementing Medicare for All - the extension of Medicare to every age group. Every American would be automatically covered for life. Premiums would be replaced with a set of Medicare taxes. There would be no patient cost sharing. Individuals would have free choice of doctors. Medicare's single-payer bargaining power would slow price increases and reduce medical cost as a percentage of gross domestic product (GDP). Taxes as a percentage of GDP would rise from below average to average for economically advanced nations. Medicare for All would be phased in by age. PMID:26124300

  7. Affordability of the Health Expenditures of Insured Americans Before the Affordable Care Act.

    PubMed

    Nyman, John A; Trenz, Helen M

    2016-02-01

    Central to the Affordable Care Act is the notion of affordability and the role of health insurance in making otherwise unaffordable health care affordable. We used data from the 1996 to 2008 versions of the Medical Expenditure Panel Survey to estimate the portion of overall health care expenditures by insured respondents that would otherwise have been beyond their disposable incomes and assets. We found that about one third of insured expenditures would have been unaffordable, with a much higher percentage among publicly insured individuals. This result suggests that one of the main functions of insurance is to cover expenses that insured individuals would not otherwise be able to afford. PMID:26691116

  8. Affordable housing: Reducing the energy cost burden

    SciTech Connect

    Lee, A.D.; Chin, R.I.; Marden, C.L.

    1995-01-01

    Residential energy expenditures are a key determinant of housing affordability, particularly for lower Income households. For years, federal, state and local governments and agencies have sought to defray energy expenses and Increase residential energy efficiency for low Income households through legislative and regulatory actions and programs. Nevertheless, household energy costs continue to place a major burden on lower Income families. This issue paper was written to help formulate national energy policy by providing the United States Department of Energy`s (DOE`s) Office of Energy Efficiency and Renewable Energy (EE) with Information to help define the affordable housing issue; Identify major drivers, key factors, and primary stakeholders shaping the affordable housing issue; and review how responding to this Issue may impact EE`s goals and objectives and Influence the strategic direction of the office. Typically, housing affordability is an Issue associated with lower income households. This issue paper adopts this perspective, but it is important to note that reducing energy utility costs can make {open_quotes}better{close_quote} housing affordable to any household regardless of income. As energy efficiency is improved throughout all sectors of the economy, special consideration must be given to low income households. Of all households, low income households are burdened the most by residential energy costs; their residences often are the least energy-efficient and have the greatest potential for efficiency improvements, but the occupants have the fewest resources to dedicate to conservation measures. This paper begins with a definition of {open_quotes}affordability{close_quotes} as it pertains to total housing costs and summarizes several key statistics related to housing affordability and energy use by lower income households.

  9. FNAL Booster intensity, extraction, and synchronization control for collider operation

    SciTech Connect

    Ducar, R.J.; Lackey, J.R.; Tawzer, S.R.

    1987-03-01

    Booster operation for collider physics is considerably different than for fixed target operation. Various scenarios for collider physics, machine studies, and P-Bar targeting may require that the intensity vary from 5E10 PPP to 3E12 PPP at a 15 Hertz machine cycle rate. In addition to the normal Booster single turn extraction mode, collider operations require that the Booster inject into the Main Ring a small number of beam bunches for coalescing into a single high intensity bunch. These bunches must be synchronized such that the center bunch arrives in the RF bucket which corresponds to the zero phase of the coalescing cavity. The system implemented has the ability to deliver a precise fraction of the available 84 Booster beam bunches to Main Ring or to the P-Bar Debuncher via the newly installed AP-4 beam line for tune-up and studies. It is required that all of the various intensity and extraction scenarios be accommodated with minimal operator intervention.

  10. Progress and status of the AGS Booster project

    SciTech Connect

    Weng, W.T. )

    1989-01-01

    New physics opportunities, such as: rare K-decay, neutrino and heavy ion physics demand that a rapid-cycling high vacuum and high intensity Booster be built for the AGS at Brookhaven National Laboratory. The circumference of the Booster ring is one-quarter that of the AGS. Three modes of operation for various particles are envisioned. For unpolarized protons, four Booster pulses would be injected at a 7.5 Hz repetition rate within a 400 ms flat bottom of the AGS, enabling the present 1.5 {times} 10{sup 13} ppp to be increased to 6 {times} 10{sup 13} ppp. The protons would be accelerated to 1.5 GeV although the bending capability provided for heavy ions would eventually allow protons to be accelerated to 2.5 GeV. For heavy ions the rep rates is about 1 Hz and only one pulse would be injected into the AGS. For polarized protons 20 or so pulses can be stored in the Booster ring before injecting them into the AGS. Provisions for mixed modes of operation into a super cycle has been provided for future needs. In this paper, the lattice design and magnet characteristics will be briefly reviewed and major design issues will be discussed and design choices explained. Finally, the construction status and schedule will be presented. 9 refs., 3 figs.

  11. Effectiveness of an Electronic Booster Session Delivered to Mandated Students.

    PubMed

    Linowski, Sally A; DiFulvio, Gloria T; Fedorchak, Diane; Puleo, Elaine

    2016-01-01

    College student drinking continues to be a problem in the United States. Students who have violated campus alcohol policy are at particularly high risk for dangerous drinking. While Brief Alcohol Screening and Intervention for College Students (BASICS) has been found to be an effective strategy in reducing high-risk drinking and associated consequences, questions remain about ways to further reduce risk or sustain changes associated with a face-to face intervention. The purpose of this study was to assess the effectiveness of a computer-delivered personalized feedback (electronic booster) delivered to policy violators who completed a mandated BASICS program. At 3-month post-intervention, 346 participants (60.4% male and 39.6% female) were randomized to one of two conditions: assessment only (n = 171) or electronic booster feedback (n = 175). Follow-up assessments were given to all participants at 3, 6, and 12-month post-initial intervention. Both groups showed reductions in drinking after the in-person BASICS intervention, but no additional reductions were seen with the addition of an electronic booster session. Findings suggest that although brief motivational interventions delivered in person to mandated students have been shown to be effective with mandated students, there is no additional benefit from an electronic booster session delivered 3-month post-intervention for this population. PMID:26857563

  12. 30 CFR 57.8518 - Main and booster fans.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... 30 Mineral Resources 1 2012-07-01 2012-07-01 false Main and booster fans. 57.8518 Section 57.8518 Mineral Resources MINE SAFETY AND HEALTH ADMINISTRATION, DEPARTMENT OF LABOR METAL AND NONMETAL MINE SAFETY AND HEALTH SAFETY AND HEALTH STANDARDS-UNDERGROUND METAL AND NONMETAL MINES Ventilation Surface and Underground § 57.8518 Main and...

  13. 30 CFR 57.8518 - Main and booster fans.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... 30 Mineral Resources 1 2013-07-01 2013-07-01 false Main and booster fans. 57.8518 Section 57.8518 Mineral Resources MINE SAFETY AND HEALTH ADMINISTRATION, DEPARTMENT OF LABOR METAL AND NONMETAL MINE... shall be tested at least within 2-hours of the discovery of the fan failure, and at least every...

  14. 30 CFR 57.8518 - Main and booster fans.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... 30 Mineral Resources 1 2011-07-01 2011-07-01 false Main and booster fans. 57.8518 Section 57.8518 Mineral Resources MINE SAFETY AND HEALTH ADMINISTRATION, DEPARTMENT OF LABOR METAL AND NONMETAL MINE... shall be tested at least within 2-hours of the discovery of the fan failure, and at least every...

  15. 30 CFR 57.8518 - Main and booster fans.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... 30 Mineral Resources 1 2014-07-01 2014-07-01 false Main and booster fans. 57.8518 Section 57.8518 Mineral Resources MINE SAFETY AND HEALTH ADMINISTRATION, DEPARTMENT OF LABOR METAL AND NONMETAL MINE... shall be tested at least within 2-hours of the discovery of the fan failure, and at least every...

  16. Year 5 Booster Units. The National Literacy Strategy.

    ERIC Educational Resources Information Center

    Department for Education and Employment, London (England).

    The eight units of work in this document are designed to complement existing literacy booster units. Each unit is based on teaching objectives from the National Literacy Strategy Framework. They have been produced with the help of Year 5 teachers and have been trialled with pupils in a range of schools. The units support teachers' work with Year 5…

  17. History of the ZGS 500 MeV booster.

    SciTech Connect

    Simpson, J.; Martin; R.; Kustom, R.

    2006-05-09

    The history of the design and construction of the Argonne 500 MeV booster proton synchrotron from 1969 to 1982 is described. This accelerator has since been in steady use for the past 25 years to power the Argonne Intense Pulsed Neutron Source (IPNS).

  18. Injection of large transverse emittance EBIS beams in booster

    SciTech Connect

    Gardner, C.

    2011-10-10

    During the commissioning of EBIS beams in Booster in November 2010 and in April, May and June 2011, it was found that the transverse emittances of the EBIS beams just upstream of Booster were much larger than expected. Beam emittances of 11{pi} mm milliradians had been expected, but numbers 3 to 4 times larger were measured. Here and throughout this note the beam emittance, {pi}{epsilon}{sub 0}, is taken to be the area of the smallest ellipse that contains 95% of the beam. We call this smallest ellipse the beam ellipse. If the beam distribution is gaussian, the rms emittance of the distribution is very nearly one sixth the area of the beam ellipse. The normalized rms emittance is the rms emittance times the relativistic factor {beta}{gamma} = 0.06564. This amounts to 0.12{pi} mm milliradians for the 11{pi} mm milliradian beam ellipse. In [1] we modeled the injection and turn-by-turn evolution of an 11{pi} mm milliradian beam ellipse in the horizontal plane in Booster. It was shown that with the present injection system, up to 4 turns of this beam could be injected and stored in Booster without loss. In the present note we extend this analysis to the injection of larger emittance beams. We consider only the emittance in the horizontal plane. Emittance in the vertical plane and the effects of dispersion are treated in [2].

  19. 47 CFR 27.9 - Operation of certificated signal boosters.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 47 Telecommunication 2 2013-10-01 2013-10-01 false Operation of certificated signal boosters. 27.9 Section 27.9 Telecommunication FEDERAL COMMUNICATIONS COMMISSION (CONTINUED) COMMON CARRIER SERVICES MISCELLANEOUS WIRELESS COMMUNICATIONS SERVICES General Information § 27.9 Operation of certificated...

  20. 47 CFR 27.9 - Operation of certificated signal boosters.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 47 Telecommunication 2 2014-10-01 2014-10-01 false Operation of certificated signal boosters. 27.9 Section 27.9 Telecommunication FEDERAL COMMUNICATIONS COMMISSION (CONTINUED) COMMON CARRIER SERVICES MISCELLANEOUS WIRELESS COMMUNICATIONS SERVICES General Information § 27.9 Operation of certificated...

  1. Alignment and Aperture Scan at the Fermilab Booster

    SciTech Connect

    Seiya, K.; Lackey, J.; Marsh, W.; Pellico, W.; Still, D.; Triplet, K.; Waller, A.; /Fermilab

    2012-05-01

    The Fermilab Booster is currently in the process of an intensity upgrade referred to as the Proton Improvement Plan (PIP). The goal of PIP is to have the Booster provide a proton beam flux of 2 x 10{sup 17} protons/hour. This is almost double the current operation of 1.1 x 10{sup 17} protons/hour. Beam losses in the machine due to the increased flux will create larger integrated doses on aperture limiting components that will need to be mitigated. The Booster accelerates beam from 400 MeV to 8 GeV at a rep rate of 15hz and then extracts beam to the Main Injector. Several percent of the beam is lost within 3 msec after injection in the early part of acceleration. The aperture at injection energy was recently measured using corrector scans. Along with magnet survey data and aperture scan data a plan to realign the magnets in the Booster was developed and implemented in May 2012. The beam studies, analysis of the scan and alignment data, and the result of the magnet moves are presented.

  2. Space transportation booster engine configuration study. Addendum: Design definition document

    NASA Technical Reports Server (NTRS)

    1989-01-01

    Gas generator engine characteristics and results of engine configuration refinements are discussed. Updated component mechanical design, performance, and manufacturing information is provided. The results are also provided of ocean recovery studies and various engine integration tasks. The details are provided of the maintenance plan for the Space Transportation Booster Engine.

  3. Liquid flyback booster pre-phase: A study assessment

    NASA Technical Reports Server (NTRS)

    Peterson, W.; Ankney, W.; Bell, J.; Berning, M.; Bryant, L.; Bufkin, A.; Cain, L.; Caram, J.; Cockrell, B.; Curry, D.

    1994-01-01

    The concept of a flyback booster has been around since early in the shuttle program. The original two-stage shuttle concepts used a manned flyback booster. These boosters were eliminated from the program for funding and size reasons. The current shuttle uses two Redesigned Solid Rocket Motors (RSRM's), which are recovered and refurbished after each flight; this is one of the major cost factors of the program. Replacement options have been studied over the past ten years. The conclusion reached by the most recent study is that the liquid flyback booster (LFBB) is the only competitive option from a life-cycle cost perspective. The purpose of this study was to assess the feasibility and practicality of LFBB's. The study provides an expansion of the recommendations made during the aforementioned study. The primary benefits are the potential for enhanced reusability and a reduction of recurring costs. The potential savings in vehicle turnaround could offset the up-front costs. Development of LFBB's requires a commitment to the shuttle program for 20 to 30 years. LFBB's also offer enhanced safety and abort capabilities. Currently, any failure of an RSRM can be considered catastrophic, since there are no intact abort capabilities during the burn of the RSRM's. The performance goal of the LFBB's was to lift a fully loaded orbiter under optimal conditions, so as not to be the limiting factor of the performance capability of the shuttle. In addition, a final benefit is the availability of growth paths for applications other than shuttle.

  4. Solid rocket booster performance evaluation model. Volume 2: Users manual

    NASA Technical Reports Server (NTRS)

    1974-01-01

    This users manual for the solid rocket booster performance evaluation model (SRB-II) contains descriptions of the model, the program options, the required program inputs, the program output format and the program error messages. SRB-II is written in FORTRAN and is operational on both the IBM 370/155 and the MSFC UNIVAC 1108 computers.

  5. Closeup view of the External Tank and Solid Rocket Boosters ...

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

    Close-up view of the External Tank and Solid Rocket Boosters at the Launch Pad at Kennedy Space Center. Note the Hydrogen Vent Arm extending out from the Fixed Service Structure at attached to the Intertank segment of the External Tank. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

  6. 30 CFR 57.8518 - Main and booster fans.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ..., or adjustments. (b) In the event of main or booster fan failure due to a malfunction, accident, power failure, or other such unplanned or unscheduled event: (1) The air quality in the affected active workings shall be tested at least within 2-hours of the discovery of the fan failure, and at least every...

  7. Simulation of proton RF capture in the AGS Booster

    SciTech Connect

    Khiari, F.Z.; Luccio, A.U.; Weng, W.T.

    1988-01-01

    RF capture of the proton beam in the AGS Booster has been simulated with the longitudinal phase-space tracking code ESME. Results show that a capture in excess of 95% can be achieved with multiturn injection of a chopped beam.

  8. Anger and Violence Prevention: Enhancing Treatment Effects through Booster Sessions

    ERIC Educational Resources Information Center

    Bundy, Alysha; McWhirter, Paula T.; McWhirter, J. Jeffries

    2011-01-01

    This study was designed to evaluate the effectiveness of booster sessions on the maintenance of intervention gains following an anger management prevention program: "Student Created Aggression Replacement Education Program" ("SCARE"). Participants who had completed the "SCARE" program a year earlier were randomly assigned into either a booster…

  9. Spacecraft and Their Boosters. Aerospace Education I. Instructor Handbook.

    ERIC Educational Resources Information Center

    Air Univ., Maxwell AFB, AL. Junior Reserve Office Training Corps.

    This curriculum guide is prepared for the textbook entitled "Spacecraft and their Boosters," published in the Aerospace Education I series. Specific guidelines are provided for teachers on each chapter included in the textbook. The guidelines are organized in nine categories: objectives, behavioral objectives, textbook outline, orientation,…

  10. OPTIMAL SCHEDULING OF BOOSTER DISINFECTION IN WATER DISTRIBUTION SYSTEMS

    EPA Science Inventory

    Booster disinfection is the addition of disinfectant at locations distributed throughout a water distribution system. Such a strategy can reduce the mass of disinfectant required to maintain a detectable residual at points of consumption in the distribution system, which may lea...

  11. Structural Dynamics of Filament-Wound Booster Rockets

    NASA Technical Reports Server (NTRS)

    Bugg, F. M.

    1987-01-01

    Report summarizes program of measurements and calculations of vibrations in filament-wound composite models of Space Shuttle solid-rocket boosters. Vibrational behavior predicted by finite-element computer model of structural dynamics correlates well with data from tests on full- and quarter-scale models. Computer model developed with NASTRAN general-purpose structural-analysis computer code.

  12. Liquid Rocket Booster (LRB) for the Space Transportation System (STS) systems study. Appendix C: Battery report for the liquid rocket booster TVC actuators

    NASA Technical Reports Server (NTRS)

    1989-01-01

    The actuators for control of engine valves and gimbals for a booster require 165 kW or more peak power at 270 volts direct current (VDC) during the 2 or 3 minutes of first stage ascent; other booster devices require much less power at 28 VDC. It is desired that a booster supply its own electrical power and satisfy redundancy requirements of the Solid Rocket Booster Shuttle, when applicable. The power of a Liquid Rocket Booster is therefore provided by two subsystems: Actuator Battery Power (270 VDC) Subsystem for the engine actuators, and Electrical Power and Distribution (28 VDC) Subsystem, to power everything else. Boosters will receive no electrical power from Orbiter, only commands and data, according to current plans. It was concluded that nine 30 volt silver-zinc batteries-in-series be used to provide the 270 volt, 37 kW average (165 kW peak).

  13. Abdominal Injuries in Belt-Positioning Booster Seats

    PubMed Central

    Arbogast, Kristy B.; Ghati, Yoganand

    2009-01-01

    Previous studies have demonstrated that booster seats reduce the risk of abdominal injuries by improving the fit of the seat belt on young children and encouraging better posture and compatibility with the vehicle seat. Recently, several studies have reported cases of abdominal injuries in booster seated children questioning the protective effects of these restraints. The objective of this study was to examine cases of abdominal injuries in booster seated children through parametric modeling to gain a thorough understanding of the injury causation scenarios. The Partners for Child Passenger Safety and CIREN in-depth crash investigation databases were queried to identify children in belt-positioning booster seats with abdominal injuries. The injury causation scenarios for these injuries were delineated using the CIREN Biotab method. The cases were modeled, using MADYMO with variations in key parameters, to determine the ranges of loads and loading rates for the abdomen and thorax. A parametric study was completed examining the influence of pretensioners and load limiters on the injury metrics obtained. Query of the two databases revealed three cases involving abdominal injuries to booster seated children. Children in two of the cases sustained a thoracic injury (AIS 3/AIS 4) in addition to their abdominal injuries (AIS 2) and review of these cases pointed to the role of shoulder belt loading in the injury causation. Modeling of these cases revealed chest compressions and accelerations of 30–53 mm and 41–89 g, respectively and abdominal deflection and velocity of 7.0–13.3 mm and 1.2–2.2 m/s, respectively. Parametric study suggested that coupling shoulder belt load limiting and lap belt buckle pretensioning resulted in improved chest and abdominal metrics while reducing head excursion, indicating that these technologies may provide injury reduction potential to pediatric rear seat occupants. PMID:20184845

  14. Mechanical Solitaire Thrombectomy with Low-Dose Booster Tirofiban Injection

    PubMed Central

    Goh, Duck-Ho; Jeong, Hae Woong; Ha, Sam Yeol

    2016-01-01

    Purpose Mechanical thrombectomy using a Solitaire stent has been associated with a high recanalization rate and favorable clinical outcome in intra-arterial thrombolysis. To achieve a higher recanalization rate for mechanical Solitaire thrombectomy, we used an intra-arterial low-dose booster tirofiban injection into the occluded segment after stent deployment. We report the safety and recanalization rates for mechanical Solitaire thrombectomy with a low-dose booster tirofiban injection. Materials and Methods Between February and March 2013, 13 consecutive patients underwent mechanical Solitaire thrombectomy with low-dose booster tirofiban injection. The occlusion sites included the proximal middle cerebral artery (5 patients), the internal carotid artery (5 patients), the top of the basilar artery (2 patients) and the distal middle cerebral artery (M2 segment, 1 patient). Six patients underwent bridge treatment, including intravenous tissue plasminogen activator. Tirofiban of 250 µg was used in all patients except one (500 µg). All occluded vessels were recanalized after 3 attempts at stent retrieval (1 time, n=9; 2 times, n=2; 3 times, n=2). Results Successful recanalization was achieved in all patients (TICI 3, n=8; TICI 2b, n=5). Procedural complications developed in 3 patients (subarachnoid hemorrhage, n=2; hemorrhagic transformation, n=1). Mortality occurred in one patient with a basilar artery occlusion due to reperfusion brain swelling after mechanical Solitaire thrombectomy with low-dose booster tirofiban injection. Favorable clinical outcome (mRS≤2) was observed in 8 patients (61.5%). Conclusion Our modified mechanical Solitaire thrombectomy method using a low-dose booster tirofiban injection might enhance the recanalization rate with no additive hemorrhagic complications. PMID:27621948

  15. Hypersonic aerothermal characteristics of a manned low finenes ratio shuttle booster

    NASA Technical Reports Server (NTRS)

    Bernot, P. T.; Throckmorton, D. A.

    1972-01-01

    An investigation of a winged booster model having canards and an ascent configuration comprised of the booster mounted in tandem with an orbiter model has been conducted at Mach 10.2 in the continuous flow hypersonic tunnel. Longitudinal and lateral directional force characteristics were obtained over angle of attack ranges of -12 deg to 60 deg for the booster and -11 deg to 11 deg for the ascent configuration. Interference heating effects on the booster using the phase-change coating technique were determined at 0 deg angle of attack. Some oil flow photographs of the isolated booster and orbiter and ascent configuration are also presented.

  16. Achieving Sustainable Construction in Affordable Housing

    SciTech Connect

    Barcik, M.K.; Creech, D.B.; Ternes, M.P.

    1998-12-07

    An energy-efficient design and construction checklist and information sheets on energy-efficient design and construction are two products being developed. These products will help affordable housing providers take the first steps toward a whole-house approach to the design and implementation of energy-efficient construction practices. The checklist presents simple and clear guidance on energy improvements that can be readily addressed now by most affordable housing providers. The information sheets complement the checklist by providing installation instructions and material specifications that are accompanied by detailed graphics. The information sheets also identify benefits of recommended energy-efficiency measures and procedures including cost savings and impacts on health and comfort. This paper presents details on the checklist and information sheets and discusses their use in two affordable housing projects.

  17. Affordances and the musically extended mind.

    PubMed

    Krueger, Joel

    2014-01-01

    I defend a model of the musically extended mind. I consider how acts of "musicking" grant access to novel emotional experiences otherwise inaccessible. First, I discuss the idea of "musical affordances" and specify both what musical affordances are and how they invite different forms of entrainment. Next, I argue that musical affordances - via soliciting different forms of entrainment - enhance the functionality of various endogenous, emotion-granting regulative processes, drawing novel experiences out of us with an expanded complexity and phenomenal character. I argue that music therefore ought to be thought of as part of the vehicle needed to realize these emotional experiences. I appeal to different sources of empirical work to develop this idea. PMID:24432008

  18. The Transformation of Ergonomic Affordances into Cultural Affordances: The Case of the Alnuset System

    ERIC Educational Resources Information Center

    Chiappini, Giampaolo

    2012-01-01

    Is it possible to study the ergonomic affordances offered by a system designed for educational aims and their transformation into cultural affordances? To this purpose, what references can we adopt? This work describes the theoretical framework used to realise this study referring to AlNuSet, a system realised within the EC ReMath project to…

  19. The Affordable Care Act and orthopaedic trauma.

    PubMed

    Issar, Neil M; Jahangir, A Alex

    2014-10-01

    The Affordable Care Act has resulted in a dramatic governmental restructuring of the healthcare insurance market and delivery system. Orthopaedic traumatologists must be aware of the law's impact on their clinical practice, finances, and overall business model. This includes the effect of accountable care organizations, the Independent Payment Advisory Board, and the Physician Value-Based Payment Modifier program, as well as the impact of the Affordable Care Act's grace period provision, medical device excise tax, and cuts to funding for the Disproportionate Share Hospital program. PMID:25229683

  20. Affordance Templates for Shared Robot Control

    NASA Technical Reports Server (NTRS)

    Hart, Stephen; Dinh, Paul; Hambuchen, Kim

    2014-01-01

    This paper introduces the Affordance Template framework used to supervise task behaviors on the NASA-JSC Valkyrie robot at the 2013 DARPA Robotics Challenge (DRC) Trials. This framework provides graphical interfaces to human supervisors that are adjustable based on the run-time environmental context (e.g., size, location, and shape of objects that the robot must interact with, etc.). Additional improvements, described below, inject degrees of autonomy into instantiations of affordance templates at run-time in order to enable efficient human supervision of the robot for accomplishing tasks.

  1. Ares I First Stage Booster Deceleration System: An Overview

    NASA Technical Reports Server (NTRS)

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

    2009-01-01

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

  2. No Role for Motor Affordances in Visual Working Memory

    ERIC Educational Resources Information Center

    Pecher, Diane

    2013-01-01

    Motor affordances have been shown to play a role in visual object identification and categorization. The present study explored whether working memory is likewise supported by motor affordances. Use of motor affordances should be disrupted by motor interference, and this effect should be larger for objects that have motor affordances than for…

  3. Are Selective Private and Public Colleges Affordable?

    ERIC Educational Resources Information Center

    Karikari, John A.; Dezhbakhsh, Hashem

    2013-01-01

    We examine college affordability under the existing pricing and financial aid system that awards both non need-based and need-based aid. Using data of freshmen attending a large number of selective private and public colleges in the USA, we find that the prices students actually pay for college have increased over time. Need-based grant aid has…

  4. Options for Affordable Fission Surface Power Systems

    NASA Technical Reports Server (NTRS)

    Houts, Mike; Gaddis, Steve; Porter, Ron; VanDyke, Melissa; Martin Jim; Godfroy, Tom; Bragg-Sitton, Shannon; Garber, Anne; Pearson, Boise

    2006-01-01

    Fission surface power systems could provide abundant power anywhere on free surface of the moon or Mars. Locations could include permanently shaded regions on the moon and high latitudes on Mars. To be fully utilized; however, fission surface power systems must be safe, have adequate performance, and be affordable. This paper discusses options for the design and development of such systems.

  5. Can the US afford a lunar base

    SciTech Connect

    Keaton, P.W.

    1986-01-01

    Establishing a lunar base will require steady funding for a decade or two. The question addressed here is whether such a large space project is affordable at this time. The relevant facts and methodology are presented so that the reader may formulate independent answers. It is shown that a permanent lunar base can be financed without increasing NASA's historical budgetary trends.

  6. 9 Tips for Affordable Student Trips

    ERIC Educational Resources Information Center

    Adams, Jonathan

    2013-01-01

    The trick to having a successful and affordable trip is planning ahead and planning thoroughly. Keep the spirits high and the costs low by following a well-traveled ensemble director's suggestions as presented in this article. These tips include finding local attractions that are unique to the city that the group will be visiting, looking at…

  7. Actions and Affordances in Syntactic Ambiguity Resolution

    ERIC Educational Resources Information Center

    Chambers, Craig G.; Tanenhaus, Michael K.; Magnuson, James S.

    2004-01-01

    In 2 experiments, eye movements were monitored as participants followed instructions containing temporary syntactic ambiguities (e.g., "Pour the egg in the bowl over the flour"). The authors varied the affordances of task-relevant objects with respect to the action required by the instruction (e.g., whether 1 or both eggs in the visual workspace…

  8. Diabetes and the Affordable Care Act

    PubMed Central

    Schade, David S.

    2014-01-01

    Abstract The Affordable Care Act—“Obamacare”—is the most important federal medical legislation to be enacted since Medicare. Although the goal of the Affordable Care Act is to improve healthcare coverage, access, and quality for all Americans, people with diabetes are especially poised to benefit from the comprehensive reforms included in the act. Signed into law in 2010, this massive legislation will slowly be enacted over the next 10 years. In the making for at least a decade, it will affect every person in the United States, either directly or indirectly. In this review, we discuss the major changes in healthcare that will take place in the next several years, including (1) who needs to purchase insurance on the Web-based exchange, (2) the cost to individuals and the rebates that they may expect, (3) the rules and regulations for purchasing insurance, (4) the characteristics of the different “metallic” insurance plans that are available, and (5) the states that have agreed to participate. With both tables and figures, we have tried to make the Affordable Care Act both understandable and appreciated. The goal of this comprehensive review is to highlight aspects of the Affordable Care Act that are of importance to practitioners who care for people with diabetes by discussing both the positive and the potentially negative aspects of the program as they relate to diabetes care. PMID:24927108

  9. Affordances of Instrumentation in General Chemistry Laboratories

    ERIC Educational Resources Information Center

    Sherman, Kristin Mary Daniels

    2010-01-01

    The purpose of this study is to find out what students in the first chemistry course at the undergraduate level (general chemistry for science majors) know about the affordances of instrumentation used in the general chemistry laboratory and how their knowledge develops over time. Overall, students see the PASCO(TM) system as a useful and accurate…

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

    NASA Technical Reports Server (NTRS)

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

    2012-01-01

    The problem of trajectory optimization is important in all space missions. The solution of this problem enables one to specify the optimum thrust steering program which should be followed to achieve a specified mission objective, simultaneously satisfying the constraints.1 It is well known that whether or not the ascent trajectory is optimal can have a significant impact on propellant usage for a given payload, or on payload weight for the same gross vehicle weight.2 Consequently, ascent guidance commands are usually optimized in some fashion. Multi-stage vehicles add complexity to this analysis process as changes in vehicle properties in one stage propagate to the other stages through gear ratios and changes in the optimal trajectory. These effects can cause an increase in analysis time as more variables are added and convergence of the optimizer to system closure requires more analysis iterations. In this paper, an approach to simplifying this multi-stage problem through the creation of an upper stage capability boundary is presented. This work was completed as part of a larger study focused on trade space exploration for the advanced booster system that will eventually form a part of NASA s new Space Launch System.3 The approach developed leverages Design of Experiments and Surrogate Modeling4 techniques to create a predictive model of the SLS upper stage performance. The design of the SLS core stages is considered fixed for the purposes of this study, which results in trajectory parameters such as staging conditions being the only variables relevant to the upper stage. Through the creation of a surrogate model, which takes staging conditions as inputs and predicts the payload mass delivered by the SLS upper stage to a reference orbit as the response, it is possible to identify a "surface" of staging conditions which all satisfy the SLS requirement of placing 130 metric tons into low-Earth orbit (LEO).3 This identified surface represents the 130 metric ton

  11. Preliminary study of AC power feeders for AGS booster

    SciTech Connect

    Meth, M.

    1992-07-17

    It has been proposed that the AGS Heavy Ion/Proton Booster be excited directly from the electric power distribution system without intervening an energy storage buffer such as an MG set or a magnetic energy buffer. The average power requirement of the AGS Booster is less than many single-loads presently housed on the lab site. However, the power swing will be the largest single pulsating load on the lab site. The large power swings will impact on the power grid producing utility-line disturbances such as voltage fluctuations and harmonic generation. Thus, it is necessary to carefully evaluate the quality of the electric power system resulting from the interconnection, such that the utility system is not degraded either on the lab site or at LILCO`s substation.

  12. Preliminary study of AC power feeders for AGS booster

    SciTech Connect

    Meth, M.

    1992-07-17

    It has been proposed that the AGS Heavy Ion/Proton Booster be excited directly from the electric power distribution system without intervening an energy storage buffer such as an MG set or a magnetic energy buffer. The average power requirement of the AGS Booster is less than many single-loads presently housed on the lab site. However, the power swing will be the largest single pulsating load on the lab site. The large power swings will impact on the power grid producing utility-line disturbances such as voltage fluctuations and harmonic generation. Thus, it is necessary to carefully evaluate the quality of the electric power system resulting from the interconnection, such that the utility system is not degraded either on the lab site or at LILCO's substation.

  13. Fermilab booster ion profile monitor system using LABVIEW

    SciTech Connect

    Zagel, J.R.; Chen, D.; Crisp, J.

    1995-05-05

    The new Booster Ion Profile Monitor has been implemented to simultaneously capture both horizontal and vertical profiles at a once-per-turn sample rate, throughout a Booster cycle. The system uses LabVIEW software running on a MacIntosh Quadra 650 talking to both VME and CAMAC hardware. Microchannel plate voltage is turned on just prior to making a measurement and automatically turned off when the measurement is complete. This action allows using a high gain while preserving microchannel plate lifetime. The data captured may be archived for later analysis. Current analysis available include position, emittance/sigma, 2D color intensity plot of raw data, and single turn profiles for any turn during the cycle. {copyright} {ital 1995} {ital American} {ital Institute} {ital of} {ital Physics}.

  14. Fermilab Booster Operational Status: Beam Loss and Collimation

    NASA Astrophysics Data System (ADS)

    Webber, Robert C.

    2002-12-01

    Beam loss reduction and control challenges confronting the Fermilab Booster are presented in the context of the current operational status. In Summer 2002 the programmatic demand for 8 GeV protons will increase to 5E20/year. This is an order of magnitude above recent high rates and nearly as many protons as the machine has produced in its entire 30-year lifetime. Catastrophic radiation damage to accelerator components must be avoided, maintenance in an elevated residual radiation environment must be addressed, and operation within a tight safety envelope must be conducted to limit prompt radiation in the buildings and grounds around the Booster. Diagnostic and performance tracking improvements, enhanced orbit control, and a beam loss collimation/localization system are essential elements in the approach to achieving the expected level of performance and are described here.

  15. Fermilab Booster Transition Crossing Simulations and Beam Studies

    SciTech Connect

    Bhat, C. M.; Tan, C. Y.

    2016-01-01

    The Fermilab Booster accelerates beam from 400 MeV to 8 GeV at 15 Hz. In the PIP (Proton Improvement Plan) era, it is required that Booster deliver 4.2 x $10^{12}$ protons per pulse to extraction. One of the obstacles for providing quality beam to the users is the longitudinal quadrupole oscillation that the beam suffers from right after transition. Although this oscillation is well taken care of with quadrupole dampers, it is important to understand the source of these oscillations in light of the PIP II requirements that require 6.5 x $10^{12}$ protons per pulse at extraction. This paper explores the results from machine studies, computer simulations and solutions to prevent the quadrupole oscillations after transition.

  16. Design optimization of gas generator hybrid propulsion boosters

    NASA Technical Reports Server (NTRS)

    Weldon, Vincent; Phillips, Dwight U.; Fink, Lawrence E.

    1990-01-01

    A methodology used in support of a contract study for NASA/MSFC to optimize the design of gas generator hybrid propulsion booster for uprating the National Space Transportation System (NSTS) is presented. The objective was to compare alternative configurations for this booster approach, optimizing each candidate concept on different bases, in order to develop data for a trade table on which a final decision was based. The methodology is capable of processing a large number of independent and dependent variables, adjusting the overall subsystems characteristics to arrive at a best compromise integrated design to meet various specified optimization criteria subject to selected constraints. For each system considered, a detailed weight statement was generated along with preliminary cost and reliability estimates.

  17. Design Optimization of Gas Generator Hybrid Propulsion Boosters

    NASA Technical Reports Server (NTRS)

    Weldon, Vincent; Phillips, Dwight; Fink, Larry

    1990-01-01

    A methodology used in support of a study for NASA/MSFC to optimize the design of gas generator hybrid propulsion booster for uprating the National Space Transportation System (NSTS) is presented. The objective was to compare alternative configurations for this booster approach, optimizing each candidate concept on different bases, in order to develop data for a trade table on which a final decision was based. The methodology is capable of processing a large number of independent and dependent variables, adjusting the overall subsystems characteristics to arrive at a best compromise integrated design to meet various specific optimization criteria subject to selected constraints. For each system considered, a detailed weight statement was generated along with preliminary cost and reliability estimates.

  18. Injection system of teh SSC Medium Energy Booster

    SciTech Connect

    Mao, N.; Gerig, R.; McGill, J.; Brown, K.

    1994-04-01

    The Medium Energy Booster (MEB) is the third of the SSCL accelerators and the largest of the resistive magnet synchrotrons. It accelerates protons from an injection momentum of 12 GeV/c to a top momentum of 200 GeV/c. A beam injection system has been designed to inject the beam transferred from the Low Energy Booster onto the MEB closed orbit in the MEB injection insertion region. The beam is injected via a vertical bending Lambertson septum magnet and a horizontal kicker with appropriate matching and very little beam loss and emittance dilution. The beam optics of the injection system is described in this paper. The required parameters of the Lambertson septum magnet and the injection kicker are given.

  19. Ignition Transients of Large Segmented Solid Rocket Boosters

    NASA Technical Reports Server (NTRS)

    Caveny, L. H.; Kuo, K. K.

    1976-01-01

    A model is described which provides a means for analyzing the complexities of ignition transients and pressure peaks of large, high performance, segmented solid rocket boosters. The method accounts for: (1) temporal and spatial development of the flow field set up by the head end igniter discharge, (2) ignition and flame spreading coupled to chamber flow, (3) the steep velocity, pressure, and temperature gradients that occur during the early phases of ignition, and (4) the interactions that produce ignition spikes (i.e., compression of chamber gases during pressurization, erosive burning, and mass added effect of igniter discharge). The technique differs from earlier models in that the flow interactions between the slots and main chamber are accounted for, and the original computer program for monolithic motors is improved. The procedures were used to predict the ignition transients of the current design for the space shuttle booster.

  20. Placement Of O-Rings In Solid Rocket Booster

    NASA Technical Reports Server (NTRS)

    Wood, Charles

    1991-01-01

    Brief report proposes to modify placement of O-ring seals in joints of Solid Rocket Booster of Space Shuttle. Modified joint and seal essentially "inside-out" version of old joint and seal. O-rings placed between outer side of tang and clevis. Joint rotation pushes tang harder against O-rings, thereby making even tighter seal. Proposal derived from analysis of Space Shuttle Challenger disaster, attributed to failure of these O-ring seals.

  1. The Aquila Launch Vehicle - A hybrid propulsion space booster

    NASA Astrophysics Data System (ADS)

    Flittie, Kirk J.; Estey, Paul N.; Kniffen, R. J.

    1991-10-01

    The Aquila Launch Vehicle is the first low-cost hybrid rocket propulsion space booster capable of placing 1450-kg payloads into LEO with high availability and reliability, as well as unprecedented levels of production, ground, and flight operations safety. Since hybrid rockets cannot explode, they may be readily manufactured in light-industrial production facilities. Polar-orbit operations with commercial and government-project payloads are scheduled to begin from Vandenberg AFB in 1995.

  2. Construction and early commissioning results of the AGS Booster

    SciTech Connect

    Weng, W.T.; Ahrens, L.; Damm, R.; McNerney, A.J.

    1991-01-01

    The AGS Booster synchrotron has been designed to accelerate protons from 200 MeV to 1.5 GeV and heavy ions from several MeV per nucleon to several hundred MeV per nucleon for all the nuclei up to gold. The design requirements and measurements results of major accelerator components and systems are presented. The early commissioning results of the injection is also presented. 12 refs., 9 figs., 2 tabs.

  3. Space shuttle program solid rocket booster decelerator subsystem

    NASA Technical Reports Server (NTRS)

    Barnard, J. W.

    1985-01-01

    The recovery of the Solid Rocket Boosters presented a major challenge. The SRB represents the largest payload ever recovered and presents the added complication that it is continually emitting hot gases and burning particles of insulation and other debris. Some items, such as portions of the nozzle, are large enough to burn through the nylon parachute material. The SRB Decelerator Subsystem program was highly successful in that no SRB has been lost as a result of inadequate performance of the DSS.

  4. A Linac afterburner to supercharge the Fermilab booster

    SciTech Connect

    Charles M Ankenbrandt et al.

    2002-10-21

    A Linac Afterburner is proposed to raise the energy of the beam injected into the Femrilab Booster from 400 MeV to about 600 MeV, thereby alleviating the longitudinal and transverse space-charge effects at low energy that currently limit its performance. The primary motivation is to increase the integrated luminosity of the Tevatron Collider in Run II, but other future programs would also recap substantial benefits. The estimated cost is $23M.

  5. Propellant Management in Booster and Upper Stage Propulsion Systems

    NASA Technical Reports Server (NTRS)

    Fisher, Mark F.

    1997-01-01

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

  6. Space shuttle solid rocket booster redesign and testing

    NASA Technical Reports Server (NTRS)

    Mitchell, R. E.

    1989-01-01

    The redesigned solid rocket motor of the Space Shuttle is described. Improvements over the model that led to the loss of the Space Shuttle Challenger are outlined. Scale and full-size tests carried out to verify the quality of the redesign are described. A unique feature of the test program is the introduction of deliberate flaws into some test articles. Post-flight evaluation of the redesigned boosters show excellent results.

  7. Analysis of emittance growth in the Fermilab Booster

    SciTech Connect

    Ng, K.Y.; Huang, X.; Lee, S.Y.; /Indiana U.

    2006-05-01

    Multi-particle simulations are performed to study emittance growth in the Fermilab Booster. Analysis shows that the source of vertical emittance growth comes mostly from random errors in skew quadrupoles in the presence of a strong transverse space-charge force. [1] Random errors in dipole rolls and the Montague resonance do contribute but to lesser extent. The effect of random errors in the quadrupoles is small because the betatron envelope tunes are reasonably far away from the half-integer stopband.

  8. Landau damping of space-charge dominated Fermilab Booster beam

    SciTech Connect

    Ng, K.Y.; /Fermilab

    2008-09-01

    The stable region of the Fermilab Booster beam in the complex coherent-tune-shift plane appears to have been shifted far away from the origin by its intense space-charge making Landau damping impossible. However, it is shown that the bunching structure of the beam reduces the mean space-charge tune shift. As a result, the beam can be stabilized by suitable octupole-driven tune spread.

  9. Designing an RF thruster booster unit with TOPICA

    NASA Astrophysics Data System (ADS)

    Lancellotti, Vito; Vecchi, Giuseppe; Maggiora, Riccardo

    2007-11-01

    Electromagnetic (RF) plasma-based propulsion systems have gained increasing interest, as able to yield continuous thrust and controllable and wide-ranging exhaust velocities. An RF plasma thruster essentially features a plasma source, a booster unit and a magnetic nozzle. The usual choice for the booster is the ion-cyclotron resonance heating (ICRH), a well-established technology in fusion experiments to convey RF powers to magnetized plasmas. To help design the booster unit, TOPICA was extended to deal with magnetized cylindrical inhomogeneous plasmas [1]. The latter required a new module in charge of solving Maxwell's equations within the plasma to obtain the pertinent Green's function in the Fourier domain, i.e. the relation between the transverse magnetic and electric fields at the air-plasma interface. Calculating the antenna impedance---and hence the plasma loading---relies on an integral-equation formulation and subsequent finite-element weighted-residual scheme to evaluate the current density distribution on the conducting bodies and at the air-plasma interface. In this work the design of an ICRH stage with TOPICA is discussed. [1] V. Lancellotti et al. (2007) Proc. Joint Propulsion Conf. AIAA-2007-5129

  10. BERLinPro Booster Cavity Design, Fabrication and Test Plans

    SciTech Connect

    Burrill, Andrew; Anders, W; Frahm, A.; Knobloch, Jens; Neumann, Axel; Ciovati, Gianluigi; Kneisel, Peter K.; Turlington, Larry D.

    2014-12-01

    The bERLinPro project, a 100 mA, 50 MeV superconducting RF (SRF) Energy Recovery Linac (ERL) is under construction at Helmholtz-Zentrum Berlin for the purpose of studying the technical challenges and physics of operating a high current, c.w., 1.3 GHz ERL. This machine will utilize three unique SRF cryomodules for the injector, booster and linac module respectively. The booster cryomodule will contain three 2-cell SRF cavities, based on the original design by Cornell University, and will be equipped with twin 115 kW RF power couplers in order to provide the appropriate acceleration to the high current electron beam. This paper will review the status of the fabrication of the 4 booster cavities that have been built for this project by Jefferson Laboratory and look at the challenges presented by the incorporation of fundamental power couplers capable of delivering 115 kW. The test plan for the cavities and couplers will be given along with a brief overview of the cryomodule design.

  11. Power booster internal combustion engine flywheel

    SciTech Connect

    Dingess, B.E.

    1989-08-08

    This patent describes a flywheel apparatus for an internal combustion engine. The engine comprises a crankshaft, a cam shaft, a means of advancing the crankshaft in rotation on the power strokes to that of the flywheel, means of retarding the crankshaft on the compression strokes the flywheel. The apparatus further comprising, a first flywheel, linkage means connecting a flywheel shaft to the crankshaft, a first flywheel housing, bearing means of linking the first flywheel to the flywheel shaft, a plurality of cylinders housed to the first flywheel housing, a plurality of nitrogen charged bladders housed within the cylinders, a plurality of cam action rods housed within the cylinders, a cam housed to the flywheel shaft, linkage means linking the cam action rods to the bladders, second linkage means linking the cam action rods by way of a cam roller to the cam, a freewheeling flywheel housing, bearing means linking the freewheeling flywheel to the flywheel shaft, third linkage means linking a freewheeling clutch between the freewheeling flywheel housing and the flywheel shaft, a shifter apparatus comprising means of locking the first flywheel housing to the freewheeling flywheel housing in a first position, means of connecting the flywheel shaft and the freewheeling flywheel housing by way of the freewheeling clutch in a second position, a front flywheel comprising means of driving the cam shaft at a balanced rotational speed from the crankshaft when the crankshaft is rotating at varying rotational speeds within each revolution of the crankshaft.

  12. An Affordable Open-Source Turbidimeter

    PubMed Central

    Kelley, Christopher D.; Krolick, Alexander; Brunner, Logan; Burklund, Alison; Kahn, Daniel; Ball, William P.; Weber-Shirk, Monroe

    2014-01-01

    Turbidity is an internationally recognized criterion for assessing drinking water quality, because the colloidal particles in turbid water may harbor pathogens, chemically reduce oxidizing disinfectants, and hinder attempts to disinfect water with ultraviolet radiation. A turbidimeter is an electronic/optical instrument that assesses turbidity by measuring the scattering of light passing through a water sample containing such colloidal particles. Commercial turbidimeters cost hundreds or thousands of dollars, putting them beyond the reach of low-resource communities around the world. An affordable open-source turbidimeter based on a single light-to-frequency sensor was designed and constructed, and evaluated against a portable commercial turbidimeter. The final product, which builds on extensive published research, is intended to catalyze further developments in affordable water and sanitation monitoring. PMID:24759114

  13. System Concepts for Affordable Fission Surface Power

    NASA Technical Reports Server (NTRS)

    Mason, Lee; Poston, David; Qualls, Louis

    2008-01-01

    This paper presents an overview of an affordable Fission Surface Power (FSP) system that could be used for NASA applications on the Moon and Mars. The proposed FSP system uses a low temperature, uranium dioxide-fueled, liquid metal-cooled fission reactor coupled to free-piston Stirling converters. The concept was determined by a 12 month NASA/DOE study that examined design options and development strategies based on affordability and risk. The system is considered a low development risk based on the use of terrestrial-derived reactor technology, high efficiency power conversion, and conventional materials. The low-risk approach was selected over other options that could offer higher performance and/or lower mass.

  14. Affordances and the musically extended mind

    PubMed Central

    Krueger, Joel

    2014-01-01

    I defend a model of the musically extended mind. I consider how acts of “musicking” grant access to novel emotional experiences otherwise inaccessible. First, I discuss the idea of “musical affordances” and specify both what musical affordances are and how they invite different forms of entrainment. Next, I argue that musical affordances – via soliciting different forms of entrainment – enhance the functionality of various endogenous, emotion-granting regulative processes, drawing novel experiences out of us with an expanded complexity and phenomenal character. I argue that music therefore ought to be thought of as part of the vehicle needed to realize these emotional experiences. I appeal to different sources of empirical work to develop this idea. PMID:24432008

  15. An affordable open-source turbidimeter.

    PubMed

    Kelley, Christopher D; Krolick, Alexander; Brunner, Logan; Burklund, Alison; Kahn, Daniel; Ball, William P; Weber-Shirk, Monroe

    2014-01-01

    Turbidity is an internationally recognized criterion for assessing drinking water quality, because the colloidal particles in turbid water may harbor pathogens, chemically reduce oxidizing disinfectants, and hinder attempts to disinfect water with ultraviolet radiation. A turbidimeter is an electronic/optical instrument that assesses turbidity by measuring the scattering of light passing through a water sample containing such colloidal particles. Commercial turbidimeters cost hundreds or thousands of dollars, putting them beyond the reach of low-resource communities around the world. An affordable open-source turbidimeter based on a single light-to-frequency sensor was designed and constructed, and evaluated against a portable commercial turbidimeter. The final product, which builds on extensive published research, is intended to catalyze further developments in affordable water and sanitation monitoring. PMID:24759114

  16. Affordable Heavy Lift Capability: 2000-2004

    NASA Technical Reports Server (NTRS)

    2004-01-01

    This custom bibliography from the NASA Scientific and Technical Information Program lists a sampling of records found in the NASA Aeronautics and Space Database. The scope of this topic includes technologies to allow robust, affordable access of cargo, particularly to low-Earth orbit. This area of focus is one of the enabling technologies as defined by NASA s Report of the President s Commission on Implementation of United States Space Exploration Policy, published in June 2004.

  17. Patient Protection and Affordable Care Act

    THOMAS, 111th Congress

    Rep. Rangel, Charles B. [D-NY-15

    2009-09-17

    03/23/2010 Became Public Law No: 111-148. (TXT | PDF) (All Actions) Notes: H.R.4872 makes a number of health-related financing and revenue changes to this bill. Read together, this bill and the health care-related provisions of H.R.4872 are commonly referred to as the Affordable Care Act (ACA). Tracker: This bill has the status Became LawHere are the steps for Status of Legislation:

  18. The Affordable Care Act and emergency care.

    PubMed

    McClelland, Mark; Asplin, Brent; Epstein, Stephen K; Kocher, Keith Eric; Pilgrim, Randy; Pines, Jesse; Rabin, Elaine Judith; Rathlev, Niels Kumar

    2014-10-01

    The Affordable Care Act (ACA) will have far-reaching effects on the way health care is designed and delivered. Several elements of the ACA will directly affect both demand for ED care and expectations for its role in providing coordinated care. Hospitals will need to employ strategies to reduce ED crowding as the ACA expands insurance coverage. Discussions between EDs and primary care physicians about their respective roles providing acute unscheduled care would promote the goals of the ACA. PMID:25121814

  19. America's Affordable Health Choices Act of 2009

    THOMAS, 111th Congress

    Rep. Dingell, John D. [D-MI-15

    2009-07-14

    10/14/2009 Placed on the Union Calendar, Calendar No. 168. (All Actions) Notes: For further action, see H.R.3590, which became Public Law 111-148 on 3/23/2010. H.R.3590, often referred to as the Affordable Care Act, is the bill that became the health care reform law. Tracker: This bill has the status IntroducedHere are the steps for Status of Legislation:

  20. Effects of broken affordance on visual extinction

    PubMed Central

    Wulff, Melanie; Humphreys, Glyn W.

    2015-01-01

    Previous studies have shown that visual extinction can be reduced if two objects are positioned to “afford” an action. Here we tested if this affordance effect was disrupted by “breaking” the affordance, i.e., if one of the objects actively used in the action had a broken handle. We assessed the effects of broken affordance on recovery from extinction in eight patients with right hemisphere lesions and left-sided extinction. Patients viewed object pairs that were or were not commonly used together and that were positioned for left- or right-hand actions. In the unrelated pair conditions, either two tools or two objects were presented. In line with previous research (e.g., Riddoch et al., 2006), extinction was reduced when action-related object pairs and when unrelated tool pairs were presented compared to unrelated object pairs. There was no significant difference in recovery rate between action-related (object-tool) and unrelated tool pairs. In addition, performance with action-related objects decreased when the tool appeared on the ipsilesional side compared to when it was on the contralesional side, but only when the tool handle was intact. There were minimal effects of breaking the handle of an object rather than a tool, and there was no effect of breaking the handle on either tools or objects on single item trials. The data suggest that breaking the handle of a tool lessens the degree to which it captures attention, with this attentional capture being strongest when the tool appears on the ipsilesional side. The capture of attention by the ipsilesional item then reduces the chance of detecting the contralesional stimulus. This attentional capture effect is mediated by the affordance to the intact tool. PMID:26441612

  1. A study of two statistical methods as applied to shuttle solid rocket booster expenditures

    NASA Technical Reports Server (NTRS)

    Perlmutter, M.; Huang, Y.; Graves, M.

    1974-01-01

    The state probability technique and the Monte Carlo technique are applied to finding shuttle solid rocket booster expenditure statistics. For a given attrition rate per launch, the probable number of boosters needed for a given mission of 440 launches is calculated. Several cases are considered, including the elimination of the booster after a maximum of 20 consecutive launches. Also considered is the case where the booster is composed of replaceable components with independent attrition rates. A simple cost analysis is carried out to indicate the number of boosters to build initially, depending on booster costs. Two statistical methods were applied in the analysis: (1) state probability method which consists of defining an appropriate state space for the outcome of the random trials, and (2) model simulation method or the Monte Carlo technique. It was found that the model simulation method was easier to formulate while the state probability method required less computing time and was more accurate.

  2. Ariane 5 solid rocket booster dynamic behavior with respect to pressure oscillations

    NASA Astrophysics Data System (ADS)

    Durin, G.; Bouvier, F.; Mastrangelo, G.; Robert, E.

    2011-10-01

    Numerical simulations are performed to simulate the dynamic behavior of the Ariane 5 Solid Rocket Booster (SRB) excited by internal pressure oscillations. These pressure oscillations have sliding frequencies close to acoustic natural frequencies and changing amplitudes. Because the modal behavior of the booster is also continuously changing during the flight due to propellant burning, predictions with finite-element (FE) modeling (modal analyses, harmonic and transient responses) are necessary to predict and understand the dynamic behavior of the booster.

  3. NASA Affordable Vehicle Avionics (AVA): Common Modular Avionics System for Nano-Launchers Offering Affordable Access to Space

    NASA Technical Reports Server (NTRS)

    Cockrell, James

    2015-01-01

    Small satellites are becoming ever more capable of performing valuable missions for both government and commercial customers. However, currently these satellites can only be launched affordably as secondary payloads. This makes it difficult for the small satellite mission to launch when needed, to the desired orbit, and with acceptable risk. NASA Ames Research Center has developed and tested a prototype low-cost avionics package for space launch vehicles that provides complete GNC functionality in a package smaller than a tissue box with a mass less than 0.84 kg. AVA takes advantage of commercially available, low-cost, mass-produced, miniaturized sensors, filtering their more noisy inertial data with realtime GPS data. The goal of the Advanced Vehicle Avionics project is to produce and flight-verify a common suite of avionics and software that deliver affordable, capable GNC and telemetry avionics with application to multiple nano-launch vehicles at 1 the cost of current state-of-the-art avionics.

  4. Longitudinal emittance measurements in the Booster and AGS during the 2014 RHIC gold run

    SciTech Connect

    Zeno, K.

    2014-08-18

    This note describes longitudinal emittance measurements that were made in the Booster and AGS during the 2014 RHIC Gold run. It also contains an overview of the longitudinal aspects of their setup during this run. Each bunch intended for RHIC is composed of beam from 4 Booster cycles, and there are two of them per AGS cycle. For each of the 8 Booster cycles required to produce the 2 bunches in the AGS, a beam pulse from EVIS is injected into the Booster and captured in four h=4 buckets. Then those bunches are accelerated to a porch where they are merged into 2 bunches and then into 1 bunch.

  5. Utilizing Fission Technology to Enable Rapid and Affordable Access to any Point in the Solar System

    NASA Technical Reports Server (NTRS)

    Houts, Mike; Bonometti, Joe; Morton, Jeff; Hrbud, Ivana; Bitteker, Leo; VanDyke, Melissa; Godfroy, T.; Pedersen, K.; Dobson, C.; Patton, B.; Martin, J.; Chakrabarti, S.

    2000-01-01

    Fission technology can enable rapid, affordable access to any point in the solar system. Potential fission-based transportation options include bimodal nuclear thermal rockets, high specific energy propulsion systems, and pulsed fission propulsion systems. In-space propellant re-supply enhances the effective performance of all systems, but requires significant infrastructure development. Safe, timely, affordable utilization of first-generation space fission propulsion systems will enable the development of more advanced systems. First generation systems can build on over 45 years of US and international space fission system technology development to minimize cost.

  6. 75 FR 60482 - Proposed Extension of Information Collection Request Submitted for Public Comment; Affordable...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-09-30

    ... Comment; Affordable Care Act Enrollment Opportunity Notice Relating to Dependent Coverage; Affordable Care Act Grandfathered Health Plan Disclosure and Recordkeeping Requirement; Affordable Care Act Rescission Notice; Affordable Care Act Patient Protections Notice; Affordable Care Act Enrollment Opportunity...

  7. Price, availability and affordability of medicines

    PubMed Central

    Mhlanga, Brenda S.

    2014-01-01

    Abstract Background Medicines play an important role in healthcare, but prices can be a barrier to patient care. Few studies have looked at the prices of essential medicines in low- and middle-income countries in terms of patient affordability. Aim To determine the prices, availability and affordability of medicines along the supply chain in Swaziland. Setting Private- and public-sector facilities in Manzini, Swaziland. Methods The standardised methodology designed by the World Health Organization and Health Action International was used to survey 16 chronic disease medicines. Data were collected in one administrative area in 10 private retail pharmacies and 10 public health facilities. Originator brand (OB) and lowest-priced generic equivalent (LPG) medicines were monitored and these prices were then compared with international reference prices (IRPs). Affordability was calculated in terms of the daily wage of the lowest-paid unskilled government worker. Results Mean availability was 68% in the public sector. Private sector OB medicines were priced 32.4 times higher than IRPs, whilst LPGs were 7.32 times higher. OBs cost 473% more than LPGs. The total cumulative mark-ups for individual medicines range from 190.99% – 440.27%. The largest contributor to add-on cost was the retail mark-up (31% – 53%). Standard treatment with originator brands cost more than a day's wage. Conclusion Various policy measures such as introducing price capping at all levels of the medicine supply chain, may increase the availability, whilst at the same time reducing the prices of essential medicines for the low income population. PMID:26245401

  8. Perceiving Affordances for Different Motor Skills

    PubMed Central

    Cole, Whitney G.; Chan, Gladys L. Y.; Vereijken, Beatrix; Adolph, Karen E.

    2013-01-01

    We examined several factors that affect people’s ability to perceive possibilities for action. In Experiment 1, 24 participants crossed expanses of various sizes in three conditions: leaping, a familiar, launching action system; arm-swinging on monkey bars, an unpracticed skill that uses the arms rather than the legs; and crawling on hands and knees, a disused skill that involves all four limbs. Before and after performing each action, participants gave verbal judgments about the largest gap they could cross. Participants scaled initial judgments to their actual abilities in all three conditions. But they considerably underestimated their abilities for leaping, a launching action, and for arm-swinging when it was performed as a launching action; judgments about crawling, a non-launching action, and arm-swinging when it was performed as a non-launching action were more accurate. Thus, launching actions appear to produce a deficit in perceiving affordances that is not ameliorated by familiarity with the action. However, after performing the actions, participants partially corrected for the deficiency and more accurately judged their abilities for launching actions—suggesting that even brief action experience facilitates the perception of affordances. In Experiment 2, we confirmed that the deficit was due to the launching nature of the leaping and arm-swinging actions in Experiment 1. We asked an additional 12 participants to cross expanses using two non-launching actions using the legs (stepping across an expanse) and the arms (reaching across an expanse). Participants were highly accurate when judging affordances for these actions, supporting launching as the cause of the underestimation reported in Experiment 1. PMID:23411672

  9. Situated language understanding as filtering perceived affordances.

    PubMed

    Gorniak, Peter; Roy, Deb

    2007-03-01

    We introduce a computational theory of situated language understanding in which the meaning of words and utterances depends on the physical environment and the goals and plans of communication partners. According to the theory, concepts that ground linguistic meaning are neither internal nor external to language users, but instead span the objective-subjective boundary. To model the possible interactions between subject and object, the theory relies on the notion of perceived affordances: structured units of interaction that can be used for prediction at multiple levels of abstraction. Language understanding is treated as a process of filtering perceived affordances. The theory accounts for many aspects of the situated nature of human language use and provides a unified solution to a number of demands on any theory of language understanding including conceptual combination, prototypicality effects, and the generative nature of lexical items. To support the theory, we describe an implemented system that understands verbal commands situated in a virtual gaming environment. The implementation uses probabilistic hierarchical plan recognition to generate perceived affordances. The system has been evaluated on its ability to correctly interpret free-form spontaneous verbal commands recorded from unrehearsed game play between human players. The system is able to "step into the shoes" of human players and correctly respond to a broad range of verbal commands in which linguistic meaning depends on social and physical context. We quantitatively compare the system's predictions in response to direct player commands with the actions taken by human players and show generalization to unseen data across a range of situations and verbal constructions. PMID:21635295

  10. Breastfeeding and the Affordable Care Act.

    PubMed

    Hawkins, Summer Sherburne; Dow-Fleisner, Sarah; Noble, Alice

    2015-10-01

    Mothers who receive or qualify for the Women, Infants, and Children (WIC) program or have lower income are less likely to start and continue breastfeeding than their more advantaged counterparts. The Patient Protection and Affordable Care Act (ACA) requires employers to provide break time and space to express breast milk and requires insurance companies to cover breastfeeding support, supplies, and counseling at no cost to mothers. This ACA benefit does not extend to all Medicaid recipients or women in the WIC program. Legislative and regulatory efforts are needed to provide comprehensive coverage for all women and reduce disparities in breastfeeding. PMID:26318941

  11. Dignity for all: affordable assisted living.

    PubMed

    Janeski, James F; Pruchnicki, Alec

    2006-01-01

    In 2026, the first of the baby boomers, including Presidents Clinton and Bush, will reach the age of 80, the average age of residents currently in assisted living facilities. In her book The Denial of Aging: Perpetual Youth, Eternal Life, and Other Dangerous Fantasies, Muriel Gillick proposes that the baby boomers will seek assisted living as an alternative to nursing home care. But what about that portion of the population not able to afford the high cost of private assisted living? What option will be available to the low-asset/low-income population in lieu of nursing home care? PMID:17214248

  12. Fitting the fully coupled ORM for the Fermilab Booster

    SciTech Connect

    Huang, X.; Lee, S.Y.; Prebys, Eric; Ankenbrandt, Charles; /Fermilab

    2005-05-01

    The orbit response matrix (ORM) method [1] is applied to model the Fermilab Booster with parameters such as the BPM gains and rolls, and parameters in the lattice model, including the gradient errors and magnets rolls. We found that the gradients and rolls of the adjacent combined-function magnets were deeply correlated, preventing full determination of the model parameters. Suitable constraints of the parameters were introduced to guarantee an unique, equivalent solution. Simulations show that such solution preserves proper combinations of the adjacent parameters. The result shows that the gradient errors of combined-function magnets are within design limits.

  13. Liquid Rocket Booster Integration Study. Volume 2: Study synopsis

    NASA Technical Reports Server (NTRS)

    1988-01-01

    The impacts of introducing liquid rocket booster engines (LRB) into the Space Transportation System (STS)/Kennedy Space Center (KSC) launch environment are identified and evaluated. Proposed ground systems configurations are presented along with a launch site requirements summary. Prelaunch processing scenarios are described and the required facility modifications and new facility requirements are analyzed. Flight vehicle design recommendations to enhance launch processing are discussed. Processing approaches to integrate LRB with existing STS launch operations are evaluated. The key features and significance of launch site transition to a new STS configuration in parallel with ongoing launch activities are enumerated. This volume is the study summary of the five volume series.

  14. Liquid rocket booster integration study. Volume 1: Executive summary

    NASA Technical Reports Server (NTRS)

    1988-01-01

    The impacts of introducing liquid rocket booster engines (LRB) into the Space Transportation System (STS)/Kennedy Space Center (KSC) launch environment are identified and evaluated. Proposed ground systems configurations are presented along with a launch site requirements summary. Prelaunch processing scenarios are described and the required facility modifications and new facility requirements are analyzed. Flight vehicle design recommendations to enhance launch processing are discussed. Processing approaches to integrate LRB with existing STS launch operations are evaluated. The key features and significance of launch site transition to a new STS configuration in parallel with ongoing launch activities are enumerated. This volume is the executive summary of the five volume series.

  15. Progress on the IPNS Enriched Uranium Booster Target

    SciTech Connect

    Knox, A E; Carpenter, J M; Bailey, J L; Armani, R J; Blomquist, R N; Brown, B S; Henley, D R; Hins, A G; Loomis, B A; Schulke, A W

    1986-09-01

    We describe the Enriched Uranium Booster Target designed for use in Argonne's Intense Pulsed Neutron Source. This report contains a general description of the system, and descriptions of the thermal-hydraulic and loss-of-coolant accident analyses, of the neutronic, criticality and power density calculations, of the assessment of radiation and thermal cycling growth, and of the disk fabrication methods. We also describe the calculations of radionuclide buildup and the related hazards analysis and our calculations of the temperature and stress profiles in the disks, and briefly allude to considerations of security and safeguards.

  16. Solid rocket booster thermal radiation model, volume 1

    NASA Technical Reports Server (NTRS)

    Watson, G. H.; Lee, A. L.

    1976-01-01

    A solid rocket booster (SRB) thermal radiation model, capable of defining the influence of the plume flowfield structure on the magnitude and distribution of thermal radiation leaving the plume, was prepared and documented. Radiant heating rates may be calculated for a single SRB plume or for the dual SRB plumes astride the space shuttle. The plumes may be gimbaled in the yaw and pitch planes. Space shuttle surface geometries are simulated with combinations of quadric surfaces. The effect of surface shading is included. The computer program also has the capability to calculate view factors between the SRB plumes and space shuttle surfaces as well as surface-to-surface view factors.

  17. Thermally stable booster explosive and process for manufacture

    DOEpatents

    Quinlin, William T.; Thorpe, Raymond; Lightfoot, James M.

    2006-03-21

    A thermally stable booster explosive and process for the manufacture of the explosive. The product explosive is 2,4,7,9-tetranitro-10H-benzo[4,5]furo[3,2-b]indole (TNBFI). A reactant/solvent such as n-methylpyrrolidone (NMP) or dimethyl formamide (DMF) is made slightly basic. The solution is heated to reduce the water content. The solution is cooled and hexanitrostilbene is added. The solution is heated to a predetermined temperature for a specific time period, cooled, and the product is collected by filtration.

  18. Identification of uncertain structural parameters in flexible boosters

    NASA Astrophysics Data System (ADS)

    Sawai, Shujiro; Kawaguchi, Jun'ichiro; Matsuo, Hiroki

    A novel algorithm for identification of unknown structural parameters in flexible boosters is presented here. In this method, first of all coefficient matrices in recursive form are estimated based on sensor outputs, which is followed by identifying structural parameters utilizing matrix relations between those and system description form. This algorithm is relatively robust and promising, since neither modal coordinates nor state reconstruction is required, in which tremendous amount of efforts have been to be concentrated to. Numerical discussion here was carried out and it demonstrated its practical effectiveness.

  19. Solid Rocket Booster (SRB) Flight System Integration at Its Best

    NASA Technical Reports Server (NTRS)

    Wood, T. David; Kanner, Howard S.; Freeland, Donna M.; Olson, Derek T.

    2011-01-01

    The Solid Rocket Booster (SRB) element integrates all the subsystems needed for ascent flight, entry, and recovery of the combined Booster and Motor system. These include the structures, avionics, thrust vector control, pyrotechnic, range safety, deceleration, thermal protection, and retrieval systems. This represents the only human-rated, recoverable and refurbishable solid rocket ever developed and flown. Challenges included subsystem integration, thermal environments and severe loads (including water impact), sometimes resulting in hardware attrition. Several of the subsystems evolved during the program through design changes. These included the thermal protection system, range safety system, parachute/recovery system, and others. Because the system was recovered, the SRB was ideal for data and imagery acquisition, which proved essential for understanding loads, environments and system response. The three main parachutes that lower the SRBs to the ocean are the largest parachutes ever designed, and the SRBs are the largest structures ever to be lowered by parachutes. SRB recovery from the ocean was a unique process and represented a significant operational challenge; requiring personnel, facilities, transportation, and ground support equipment. The SRB element achieved reliability via extensive system testing and checkout, redundancy management, and a thorough postflight assessment process. However, the in-flight data and postflight assessment process revealed the hardware was affected much more strongly than originally anticipated. Assembly and integration of the booster subsystems required acceptance testing of reused hardware components for each build. Extensive testing was done to assure hardware functionality at each level of stage integration. Because the booster element is recoverable, subsystems were available for inspection and testing postflight, unique to the Shuttle launch vehicle. Problems were noted and corrective actions were implemented as needed

  20. Recent Activities in Tandem, Booster and TRIAC at Tokai

    SciTech Connect

    Ishii, Tetsuro; Matsuda, Makoto; Kabumoto, Hiroshi; Osa, Akihiko

    2009-05-04

    Present status and recent developments of the tandem accelerator, superconducting booster, and radioactive nuclear beam accelerator TRIAC are presented. The terminal voltage of the tandem accelerator reached 19.1 MV by replacing acceleration tubes. The multi-charged positive-ion injector was installed in the terminal of the tandem accelerator, supplying noble-gas ions. A superconducting cavity for low-velocity ions was developed. Radioactive nuclear beams of {sup 8}Li, {sup 123}In, and {sup 143}Ba were accelerated. Recent experimental results of nuclear physics are also reported.

  1. Liquid rocket booster integration study. Volume 5, part 1: Appendices

    NASA Technical Reports Server (NTRS)

    1988-01-01

    The impacts of introducing liquid rocket booster engines (LRB) into the Space Transportation System (STS)/Kennedy Space Center (KSC) launch environment are identified and evaluated. Proposed ground systems configurations are presented along with a launch site requirements summary. Prelaunch processing scenarios are described and the required facility modifications and new facility requirements are analyzed. Flight vehicle design recommendations to enhance launch processing are discussed. Processing approaches to integrate LRB with existing STS launch operations are evaluated. The key features and significance of launch site transition to a new STS configuration in parallel with ongoing launch activities are enumerated. This volume is the appendices of the five volume series.

  2. Prepreg and Melt Infiltration Technology Developed for Affordable, Robust Manufacturing of Ceramic Matrix Composites

    NASA Technical Reports Server (NTRS)

    Singh, Mrityunjay; Petko, Jeannie F.

    2004-01-01

    Affordable fiber-reinforced ceramic matrix composites with multifunctional properties are critically needed for high-temperature aerospace and space transportation applications. These materials have various applications in advanced high-efficiency and high-performance engines, airframe and propulsion components for next-generation launch vehicles, and components for land-based systems. A number of these applications require materials with specific functional characteristics: for example, thick component, hybrid layups for environmental durability and stress management, and self-healing and smart composite matrices. At present, with limited success and very high cost, traditional composite fabrication technologies have been utilized to manufacture some large, complex-shape components of these materials. However, many challenges still remain in developing affordable, robust, and flexible manufacturing technologies for large, complex-shape components with multifunctional properties. The prepreg and melt infiltration (PREMI) technology provides an affordable and robust manufacturing route for low-cost, large-scale production of multifunctional ceramic composite components.

  3. 12 CFR 1807.400 - Affordable housing-general.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 12 Banks and Banking 9 2013-01-01 2013-01-01 false Affordable housing-general. 1807.400 Section 1807.400 Banks and Banking COMMUNITY DEVELOPMENT FINANCIAL INSTITUTIONS FUND, DEPARTMENT OF THE TREASURY CAPITAL MAGNET FUND Qualification as Affordable Housing § 1807.400 Affordable...

  4. 12 CFR 1807.402 - Affordable housing-homeownership.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 12 Banks and Banking 7 2011-01-01 2011-01-01 false Affordable housing-homeownership. 1807.402 Section 1807.402 Banks and Banking COMMUNITY DEVELOPMENT FINANCIAL INSTITUTIONS FUND, DEPARTMENT OF THE TREASURY CAPITAL MAGNET FUND Qualification as Affordable Housing § 1807.402 Affordable...

  5. 12 CFR 1807.400 - Affordable housing-general.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 12 Banks and Banking 7 2011-01-01 2011-01-01 false Affordable housing-general. 1807.400 Section 1807.400 Banks and Banking COMMUNITY DEVELOPMENT FINANCIAL INSTITUTIONS FUND, DEPARTMENT OF THE TREASURY CAPITAL MAGNET FUND Qualification as Affordable Housing § 1807.400 Affordable...

  6. 12 CFR 1807.400 - Affordable housing-general.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 12 Banks and Banking 9 2012-01-01 2012-01-01 false Affordable housing-general. 1807.400 Section 1807.400 Banks and Banking COMMUNITY DEVELOPMENT FINANCIAL INSTITUTIONS FUND, DEPARTMENT OF THE TREASURY CAPITAL MAGNET FUND Qualification as Affordable Housing § 1807.400 Affordable...

  7. 12 CFR 1807.400 - Affordable housing-general.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 12 Banks and Banking 10 2014-01-01 2014-01-01 false Affordable housing-general. 1807.400 Section 1807.400 Banks and Banking COMMUNITY DEVELOPMENT FINANCIAL INSTITUTIONS FUND, DEPARTMENT OF THE TREASURY CAPITAL MAGNET FUND Qualification as Affordable Housing § 1807.400 Affordable...

  8. 12 CFR 1807.402 - Affordable housing-homeownership.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 12 Banks and Banking 9 2012-01-01 2012-01-01 false Affordable housing-homeownership. 1807.402 Section 1807.402 Banks and Banking COMMUNITY DEVELOPMENT FINANCIAL INSTITUTIONS FUND, DEPARTMENT OF THE TREASURY CAPITAL MAGNET FUND Qualification as Affordable Housing § 1807.402 Affordable...

  9. 12 CFR 1807.402 - Affordable housing-homeownership.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 12 Banks and Banking 10 2014-01-01 2014-01-01 false Affordable housing-homeownership. 1807.402 Section 1807.402 Banks and Banking COMMUNITY DEVELOPMENT FINANCIAL INSTITUTIONS FUND, DEPARTMENT OF THE TREASURY CAPITAL MAGNET FUND Qualification as Affordable Housing § 1807.402 Affordable...

  10. 12 CFR 1807.402 - Affordable housing-homeownership.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 12 Banks and Banking 9 2013-01-01 2013-01-01 false Affordable housing-homeownership. 1807.402 Section 1807.402 Banks and Banking COMMUNITY DEVELOPMENT FINANCIAL INSTITUTIONS FUND, DEPARTMENT OF THE TREASURY CAPITAL MAGNET FUND Qualification as Affordable Housing § 1807.402 Affordable...

  11. 12 CFR 1291.12 - Affordable Housing Reserve Fund.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 12 Banks and Banking 7 2011-01-01 2011-01-01 false Affordable Housing Reserve Fund. 1291.12 Section 1291.12 Banks and Banking FEDERAL HOUSING FINANCE AGENCY HOUSING GOALS AND MISSION FEDERAL HOME LOAN BANKS' AFFORDABLE HOUSING PROGRAM § 1291.12 Affordable Housing Reserve Fund. (a) Deposits. If...

  12. 12 CFR 1291.12 - Affordable Housing Reserve Fund.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 12 Banks and Banking 9 2013-01-01 2013-01-01 false Affordable Housing Reserve Fund. 1291.12 Section 1291.12 Banks and Banking FEDERAL HOUSING FINANCE AGENCY HOUSING GOALS AND MISSION FEDERAL HOME LOAN BANKS' AFFORDABLE HOUSING PROGRAM § 1291.12 Affordable Housing Reserve Fund. (a) Deposits. If...

  13. 12 CFR 1291.12 - Affordable Housing Reserve Fund.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 12 Banks and Banking 10 2014-01-01 2014-01-01 false Affordable Housing Reserve Fund. 1291.12 Section 1291.12 Banks and Banking FEDERAL HOUSING FINANCE AGENCY HOUSING GOALS AND MISSION FEDERAL HOME LOAN BANKS' AFFORDABLE HOUSING PROGRAM § 1291.12 Affordable Housing Reserve Fund. (a) Deposits. If...

  14. 12 CFR 1291.12 - Affordable Housing Reserve Fund.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 12 Banks and Banking 9 2012-01-01 2012-01-01 false Affordable Housing Reserve Fund. 1291.12 Section 1291.12 Banks and Banking FEDERAL HOUSING FINANCE AGENCY HOUSING GOALS AND MISSION FEDERAL HOME LOAN BANKS' AFFORDABLE HOUSING PROGRAM § 1291.12 Affordable Housing Reserve Fund. (a) Deposits. If...

  15. 12 CFR 1291.12 - Affordable Housing Reserve Fund.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 12 Banks and Banking 7 2010-01-01 2010-01-01 false Affordable Housing Reserve Fund. 1291.12 Section 1291.12 Banks and Banking FEDERAL HOUSING FINANCE AGENCY HOUSING GOALS AND MISSION FEDERAL HOME LOAN BANKS' AFFORDABLE HOUSING PROGRAM § 1291.12 Affordable Housing Reserve Fund. (a) Deposits. If...

  16. Immunologic protection afforded by sunscreens in vitro.

    PubMed

    Davenport, V; Morris, J F; Chu, A C

    1997-06-01

    Several studies have suggested a lack of correlation between sunscreen sun protection factor and protection of the skin immune system, potentially allowing greater damage to the skin by removing the natural protective erythemal response to sun exposure. Despite this, routine testing of immune protection afforded by sunscreens is not performed by industry. Current laboratory methods for investigating the efficacy of sunscreen protection of epidermal immune function use the induction of contact hypersensitivity or epidermal cell alloantigen presentation. Animal models, cell culture systems, and in vivo human studies are commonly employed, but all these systems have significant drawbacks for use in routine testing. The purpose of this study was to develop an in vitro system for testing the immunologic protection afforded by sunscreens in human skin. Five test sunscreens plus a vehicle control were tested in a "blind" fashion for their in vitro level of immune protection. Creams were applied in a standard manner to human whole skin explants and were irradiated over a range of physiologic doses using an Oriel solar simulator. A mixed epidermal lymphocyte reaction was used to quantify epidermal alloantigen-presenting capacity, in the presence or absence of test cream, for five explants. Results consistently demonstrated that all the test sunscreens protected beyond their designated sun protection factors, whereas the vehicle conferred no protection. The explant-mixed epidermal lymphocyte reaction system gave consistent, reproducible results and may prove useful for the allocation of an immune protection factor to all sunscreens. PMID:9182811

  17. Affordable access to care for the undocumented.

    PubMed

    Rosen, Dennis

    2014-09-01

    How do you tell a sick kid that nobody cares if he gets better? That's an exaggeration, of course, but it is the fundamental message our society sends when we tell him that, because he and his family are undocumented immigrants, we are unwilling to extend them access to affordable and reliable health insurance. One major shortcoming of the Affordable Care Act is its specific exclusion of the almost twelve million undocumented immigrants-including millions of children-in this country from access to the state and federal insurance exchanges where coverage can be purchased. It is true that providing undocumented immigrants access to the exchanges and subsidies mandated by the ACA would require additional funding. However, a recent analysis in California has found that the costs of expanding state-supported care to include undocumented immigrants would largely be offset by the increased state sales tax revenue paid by managed care organizations and by reduced spending at the county level on emergency-room and hospital care of the uninsured. PMID:25231664

  18. Feasibility demonstration of booster cross-over system for 3 1/2 inch SRB/MLP frangible nut system

    NASA Technical Reports Server (NTRS)

    1983-01-01

    Recent testing of the SRB/MLP Frangible Nut System (SOS Part Number 114850-9/Boosters P/N 114848-3) at NASA indicated a need to reduce the function time between boosters (2) within a single frangible nut. These boosters are initiated separately by electrical impulse(s). Coupling the output of each detonator with an explosive cross-over would reduce the function time between boosters (independent of electrical impulse) while providing additional redundancy to the system. The objectives of this program were to: provide an explosive cross-over between boosters, reduce function time between boosters to less than one (1) millisecond within a given nut, reduce cost of boosters, be compatible with the existing frangible nut system, and meet requirements of USBI Spec's (nut 10SPC-0030, booster 10SPC-0031).

  19. Expendable second stage reusable space shuttle booster. Volume 4: Detail mass properties data

    NASA Technical Reports Server (NTRS)

    1971-01-01

    Mass properties data are presented to describe the characteristics of an expendable second stage with a reusable space shuttle booster. The final mass characteristics of the vehicle configurations for three specified payloads are presented in terms of weight, center of gravity, and mass moments of inertia. Three basic subjects are the integrated vehicle system, the expendable second stage, and the booster modifications.

  20. 47 CFR 74.1290 - FM translator and booster station information available on the Internet.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... available on the Internet. 74.1290 Section 74.1290 Telecommunication FEDERAL COMMUNICATIONS COMMISSION... translator and booster station information available on the Internet. The Media Bureau's Audio Division provides information on the Internet regarding FM translator and booster stations, rules, and policies...

  1. Expendable second stage reusable space shuttle booster. Volume 12: Design data book

    NASA Technical Reports Server (NTRS)

    1971-01-01

    The general and design criteria for the expendable second stage of the reusable space shuttle booster are presented. The subjects discussed are: (1) trajectory development, (2) aerodynamic heating on basic payloads, (3) vehicle configurations, trajectory, and heat regimes, (4) orbit maneuvering system, (5) structural analysis, and (6) booster loads and structural sizing.

  2. 47 CFR 74.780 - Broadcast regulations applicable to translators, low power, and booster stations.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... PROGRAM DISTRIBUTIONAL SERVICES Low Power TV, TV Translator, and TV Booster Stations § 74.780 Broadcast... TV translator, low power TV, and TV booster stations: Section 73.653—Operation of TV aural and visual... non-network program arrangements. Part 73, Subpart G—Emergency Broadcast System (for low power...

  3. 47 CFR 74.780 - Broadcast regulations applicable to translators, low power, and booster stations.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... PROGRAM DISTRIBUTIONAL SERVICES Low Power TV, TV Translator, and TV Booster Stations § 74.780 Broadcast... TV translator, low power TV, and TV booster stations: Section 73.653—Operation of TV aural and visual... non-network program arrangements. Part 73, Subpart G—Emergency Broadcast System (for low power...

  4. 47 CFR 74.780 - Broadcast regulations applicable to translators, low power, and booster stations.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... PROGRAM DISTRIBUTIONAL SERVICES Low Power TV, TV Translator, and TV Booster Stations § 74.780 Broadcast... TV translator, low power TV, and TV booster stations: Section 73.653—Operation of TV aural and visual... non-network program arrangements. Part 73, Subpart G—Emergency Broadcast System (for low power...

  5. 47 CFR 74.780 - Broadcast regulations applicable to translators, low power, and booster stations.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... PROGRAM DISTRIBUTIONAL SERVICES Low Power TV, TV Translator, and TV Booster Stations § 74.780 Broadcast... TV translator, low power TV, and TV booster stations: Part 5—Experimental authorizations. Section 73.653—Operation of TV aural and visual transmitters. Section 73.658—Affiliation agreements and...

  6. 47 CFR 74.780 - Broadcast regulations applicable to translators, low power, and booster stations.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... PROGRAM DISTRIBUTIONAL SERVICES Low Power TV, TV Translator, and TV Booster Stations § 74.780 Broadcast... TV translator, low power TV, and TV booster stations: Part 5—Experimental authorizations. Section 73.653—Operation of TV aural and visual transmitters. Section 73.658—Affiliation agreements and...

  7. Solid rocket booster internal flow analysis by highly accurate adaptive computational methods

    NASA Technical Reports Server (NTRS)

    Huang, C. Y.; Tworzydlo, W.; Oden, J. T.; Bass, J. M.; Cullen, C.; Vadaketh, S.

    1991-01-01

    The primary objective of this project was to develop an adaptive finite element flow solver for simulating internal flows in the solid rocket booster. Described here is a unique flow simulator code for analyzing highly complex flow phenomena in the solid rocket booster. New methodologies and features incorporated into this analysis tool are described.

  8. 47 CFR 74.1290 - FM translator and booster station information available on the Internet.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... available on the Internet. 74.1290 Section 74.1290 Telecommunication FEDERAL COMMUNICATIONS COMMISSION... translator and booster station information available on the Internet. The Media Bureau's Audio Division provides information on the Internet regarding FM translator and booster stations, rules, and policies...

  9. Study of solid rocket motors for a space shuttle booster. Volume 3: Program acquisition planning

    NASA Technical Reports Server (NTRS)

    Vonderesch, A. H.

    1972-01-01

    Plans for conducting Phase C/D for a solid rocket motor booster vehicle are presented. Methods for conducting this program with details of scheduling, testing, and program management and control are included. The requirements of the space shuttle program to deliver a minimum cost/maximum reliability booster vehicle are examined.

  10. 75 FR 68664 - Federal Motor Vehicle Safety Standards; Child Restraint Systems; Booster Seat Effectiveness...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-11-08

    ... April 11, 2000 (65 FR 19477) or you may visit http://www.regulations.gov . Please send two paper copies... Systems; Booster Seat Effectiveness Estimates Based on CDS and State Data AGENCY: National Highway Traffic... Standard 213, Child Restraint Systems. The report's title is: Booster Seat ] Effectiveness Estimates...

  11. Solid rocket booster performance evaluation model. Volume 1: Engineering description

    NASA Technical Reports Server (NTRS)

    1974-01-01

    The space shuttle solid rocket booster performance evaluation model (SRB-II) is made up of analytical and functional simulation techniques linked together so that a single pass through the model will predict the performance of the propulsion elements of a space shuttle solid rocket booster. The available options allow the user to predict static test performance, predict nominal and off nominal flight performance, and reconstruct actual flight and static test performance. Options selected by the user are dependent on the data available. These can include data derived from theoretical analysis, small scale motor test data, large motor test data and motor configuration data. The user has several options for output format that include print, cards, tape and plots. Output includes all major performance parameters (Isp, thrust, flowrate, mass accounting and operating pressures) as a function of time as well as calculated single point performance data. The engineering description of SRB-II discusses the engineering and programming fundamentals used, the function of each module, and the limitations of each module.

  12. Commercial winged booster to launch satellites from B-52

    NASA Astrophysics Data System (ADS)

    Covault, Craig

    1988-06-01

    A newly developed commercial winged space booster, the Pegasus, which will launch satellites from a B-52, is described. The booster will be able to launch a 600 lb, 72 in long craft into a 250 nm equatorial orbit. The Pegasus is 49.2 ft long with a 22 ft wing span and a weight of 40,000 lb. The winged design allows for an angle of attack of 20 degrees and a supersonic lift over drag ratio of 4:1. It operates with three solid rocket motors and will be launched from a B-52 at an altitude of 40,000 ft. The first motor provides an average of 112,000 lbs of thrust for about 82 seconds; burnout occurs at 208,000 ft and Mach 8.7. The third stage provides 9,000 lbs of thrust for 65 seconds, accelerating the vehicle into 25,000 fps orbital velocity. The first launch will be a 400 lb relay satellite targeted for July 1989 over the Pacific Ocean. Future launches will be possible from any site and will cost 10 million dollars. The Pegasus can also carry a 1500 payload at high altitude Mach cruise flights that do not achieve orbit, providing data to validate spaceplane conceptual fluid dynamic codes generated by computer.

  13. Design and testing of the AGS Booster BPM detector

    SciTech Connect

    Thomas, R.; Ciardullo, D.J.; Van Zwienen, W.

    1991-01-01

    The AGS Booster beam position monitor system must accurately measure the position of beams and bunches over a wide range of intensity. The frequency of operation must also cover a wide range (600 kHz to 4.2 MHz) since the Booster accelerates both protons and heavy ions. Split-cylinder electrodes were chosen to monitor the position of the beam because of their good low frequency response and high linearity. The need to accelerate low-energy partially-stripped heavy ions requires the pick-up electrodes (PUEs) to operate in a 3 {times} 10{sup {minus}11} torr vacuum. The PUEs are to measure the beam position to an absolute accuracy of {plus minus}0.5 mm and must therefore be mechanically stable despite the requirements that they be vacuum fired at 950{degree}C and baked periodically to 300{degree}C. This presentation describes both the mechanical design of the PUEs and the automated test procedure used to ensure the stability, accuracy, and linearity of each unit. 3 refs., 5 figs.

  14. Improvement of Digital Filter for the FNAL Booster Transverse Dampers

    SciTech Connect

    Zolkin, Timofey; Eddy, N.; Lebedev, V.

    2013-09-26

    Fermilab Booster has two transverse dampers which independently suppress beam instabilities in the horizontal and vertical planes. A suppression of the common mode signal is achieved by digital notch filter which is based on subtracting beam positions for two consecutive turns. Such system operates well if the orbit position changes sufficiently slow. Unfortunately it is not the case for FNAL Booster where the entire accelerating cycle consists of about 20000 turns, and successful transition crossing requires the orbit drifts up to about 10 μm/turn, resulting in excessive power, power amplifier saturation and loss of stability. To suppress this effect we suggest an improvement of the digital filter which can take into account fast orbit changes by using bunch positions of a few previous turns. To take into account the orbit change up toN-th order polynomial in time the system requires (N + 3) turns of “prehistory”. In the case of sufficiently small gain the damping rate and the optimal digital filter coefficients are obtained analytically. Numerical simulations verify analytical theory for the small gain and predict a system performance with gain increase.

  15. DESIGN OF A RESONANT EXTRACTION SYSTEM FOR THE AGS BOOSTER.

    SciTech Connect

    BROWN,K.; CULLEN,J.; GLENN,J.W.; LEE,Y.Y.; MCNERNEY,A.; NIEDERER,J.; ROSER,T,; SOUKAS,A.; TUOZZOLO,J.; TSOUPAS,N.

    1999-03-29

    The Booster Application Facility (BAF) will employ heavy ion beams of many different ion species and at beam energies ranging from 0.04 to 3.07 GeV/nucleon. Resonant extraction is required in order to deliver a continuous stream of particles. In this report we describe the beam requirements and the system design. The basic design is a third integer resonant extraction process which employs a single thin magnetic septum and a thick septum ejector magnet The expected extraction efficiency is about 85%, based on the thin septum thickness and the predicted step size of the resonant beam at the septum. This is more than sufficient for the low intensity low energy heavy ion beams needed for the BAF. In this report we will present a detailed discussion of the design of the various elements and a discussion of the detailed modeling of resonant extraction from the AGS Booster. The extraction process was modeled using a BNL version of MAD which allowed us to interactively observe detailed particle tracking of the process. This was a key tool to have in hand which permitted us to pose and answer various questions in a very short period of time.

  16. Application of emulsifiers in the manufacture of cast boosters and related products

    SciTech Connect

    Joginadham, C.; Shankar, P.S.; Gupta, A.N.

    1996-12-01

    Cast boosters made with pentaerythritol tetranitrate (PETN) and trinitro toluene (TNT) give high velocities of detonation and are sensitive to initiation even under high pressures. However, the manufacture of the same involves heating of TNT to its melting temperature and mixing of dry PETN in it. In the present work, wet PETN, TNT and water soluble nitrate salts were used for the manufacture of the boosters. The nitrate salt solution formed with the excess water available in wet PETN was emulsified with the aid of emulsifiers. The velocities of detonation of boosters with various percentages of water were determined. The data of explosive characters of these boosters were compared with normal pentolite cast boosters.

  17. Piecing Together the College Affordability Puzzle: Student Characteristics and Patterns of (Un)Affordability

    ERIC Educational Resources Information Center

    Welbeck, Rashida; Diamond, John; Mayer, Alexander; Richburg-Hayes, Lashawn

    2014-01-01

    The cost of attending college has risen sharply over the last 40 years. Although more credit and grant aid have been made available to students, there are still major gaps between aid and the cost of attendance for many students in the United States, all of whom are left to figure out whether they can afford the remaining costs associated with…

  18. Rheumatic heart disease echocardiographic screening: approaching practical and affordable solutions.

    PubMed

    Nascimento, Bruno R; Nunes, Maria Carmo P; Lopes, Eduardo L V; Rezende, Vitória M L R; Landay, Taylor; Ribeiro, Antonio L P; Sable, Craig; Beaton, Andrea Z

    2016-05-01

    Rheumatic heart disease (RHD) affects at least 32.9 million people worldwide and ranks as a leading cause of death and disability in low-income and middle-income countries (LMICs). Echocardiographic screening has been demonstrated to be a powerful tool for early RHD detection, and holds potential for global RHD control. However, national screening programmes have not emerged. Major barriers to implementation include the lack of human and financial resources in LMICs. Here, we focus on recent research advances that could make echocardiographic screening more practical and affordable, including handheld echocardiography devices, simplified screening protocols and task shifting of echocardiographic screening to non-experts. Additionally, we highlight some important remaining questions before echocardiographic screening can be widely recommended, including demonstration of cost-effectiveness, assessment of the impact of screening on children and communities, and determining the importance of latent RHD. While a single strategy for echocardiographic screening in all high-prevalence areas is unlikely, we believe recent advancements are bringing the public health community closer to developing sustainable programmes for echocardiographic screening. PMID:26891757

  19. Enabling Dedicated, Affordable Space Access Through Aggressive Technology Maturation

    NASA Technical Reports Server (NTRS)

    Jones, Jonathan; Kibbey, Tim; Lampton, Pat; Brown, Thomas

    2014-01-01

    A recent explosion in nano-sat, small-sat, and university class payloads has been driven by low cost electronics and sensors, wide component availability, as well as low cost, miniature computational capability and open source code. Increasing numbers of these very small spacecraft are being launched as secondary payloads, dramatically decreasing costs, and allowing greater access to operations and experimentation using actual space flight systems. While manifesting as a secondary payload provides inexpensive rides to orbit, these arrangements also have certain limitations. Small, secondary payloads are typically included with very limited payload accommodations, supported on a non interference basis (to the prime payload), and are delivered to orbital conditions driven by the primary launch customer. Integration of propulsion systems or other hazardous capabilities will further complicate secondary launch arrangements, and accommodation requirements. The National Aeronautics and Space Administration's Marshall Space Flight Center has begun work on the development of small, low cost launch system concepts that could provide dedicated, affordable launch alternatives to small, risk tolerant university type payloads and spacecraft. These efforts include development of small propulsion systems and highly optimized structural efficiency, utilizing modern advanced manufacturing techniques. This paper outlines the plans and accomplishments of these efforts and investigates opportunities for truly revolutionary reductions in launch and operations costs. Both evolution of existing sounding rocket systems to orbital delivery, and the development of clean sheet, optimized small launch systems are addressed. A launch vehicle at the scale and price point which allows developers to take reasonable risks with new propulsion and avionics hardware solutions does not exist today. Establishing this service provides a ride through the proverbial "valley of death" that lies between

  20. Affordable Laser Communication in the Classroom

    NASA Astrophysics Data System (ADS)

    Walker, Constance E.; Sparks, R.; Pompea, S.

    2006-12-01

    Several companies sell systems that illustrate laser communication such as Arbor Scientific1. These systems can be too expensive for classroom use. We will demonstrate a technique to modulate a standard diode laser using a microphone or other sound source that is capable of transmitting voice and music. This affordable system can transmit over 350 feet using simple, inexpensive parts readily available at your local electronics store. We will provide a list of parts necessary for assembly, detailed assembly instructions, as well as some suggested investigations using the laser communication system. This system can be used in the classroom either as a demonstration or hands-on activity to explore the physics and technology involved, citing more sophisticated laser communication systems on board spacecraft such as the Mercury Messenger Mission and the Mars Telecommunications Orbiter. 1http://www.arborsci.com

  1. Why epidemiologists cannot afford to ignore poverty.

    PubMed

    Krieger, Nancy

    2007-11-01

    Epidemiologists cannot afford to ignore poverty. To do so would, first, wrongly obscure the devastating impact of poverty on population health, and, second, undercut our commitment to scientific rigor. At issue is doing correct science, not "politically correct" science. Blot poverty and inequity from view, and not only will we contribute to making suffering invisible but our understanding of disease etiology and distribution will be marred. To make this case, I address current debates about the causal relationships between poverty and health, and provide examples of how failing to consider the impact of socioeconomic position has biased epidemiologic knowledge and harmed the public's health. By definition, the people we study are simultaneously social beings and biologic organisms-and we cannot study the latter without taking into account the former. It is the responsibility of all epidemiologists, and not only social epidemiologists, to keep in mind the connections between poverty and health. PMID:18049180

  2. Affordable Care Act and Diabetes Mellitus.

    PubMed

    Shi, Qian; Nellans, Frank P; Shi, Lizheng

    2015-12-01

    The Affordable Care Act (ACA) has the potential for great impact on U.S. health care, especially for chronic disease patients requiring long-term care and management. The act was designed to improve insurance coverage, health care access, and quality of care for all Americans, which will assist patients with diabetes mellitus in acquiring routine monitoring and diabetes-related complication screening for better health management and outcomes. There is great potential for patients with diabetes to benefit from the new policy mandating health insurance coverage and plan improvement, Medicaid expansion, minimum coverage guarantees, and free preventative care. However, policy variability among states and ACA implementation present challenges to people with diabetes in understanding and optimizing ACA impact. This paper aims to select the most influential components of the ACA as relates to people with diabetes and discuss how the ACA may improve health care for this vulnerable population. PMID:26458377

  3. Safe, Affordable, Nuclear Thermal Propulsion Systems

    NASA Technical Reports Server (NTRS)

    Houts, M. G.; Kim, T.; Emrich, W. J.; Hickman, R. R.; Broadway, J. W.; Gerrish, H. P.; Doughty, G. E.

    2014-01-01

    The fundamental capability of Nuclear Thermal Propulsion (NTP) is game changing for space exploration. A first generation Nuclear Cryogenic Propulsion Stage (NCPS) based on NTP could provide high thrust at a specific impulse above 900 s, roughly double that of state of the art chemical engines. Characteristics of fission and NTP indicate that useful first generation systems will provide a foundation for future systems with extremely high performance. The role of the NCPS in the development of advanced nuclear propulsion systems could be analogous to the role of the DC-3 in the development of advanced aviation. Progress made under the NCPS project could help enable both advanced NTP and advanced Nuclear Electric Propulsion (NEP).

  4. Performance and measurements of the AGS and Booster beams

    SciTech Connect

    Weng, W.T.

    1996-06-01

    In May 1995, the AGS reached its upgrade intensity goal of 6{times}10{sup 13} ppp, the highest world intensity record for a proton synchrotron on a single pulse basis. At the same time, the Booster reached 2.2{times}10{sup 13} ppp surpassing the design goal of 1.5{times}10{sup 13} ppp due to the introduction of second harmonic cavity during injection. The critical accelerator manipulations, such as resonance stopband corrections, second harmonics cavity, direct rf feedback, gamma-transition jump, longitudinal phase space dilution, and transverse instability damping, will be described as well as some beam measurements. Possible future intensity and brightness upgrades will also be reported. {copyright} {ital 1996 American Institute of Physics.}

  5. Cathodic protection deployment on space shuttle solid rocket boosters

    SciTech Connect

    Zook, L.M.

    1999-07-01

    Corrosion protection of the space shuttle solid rocket boosters incorporates the use of cathodic protection (anodes) in concert with several coatings systems. The SRB design has large carbon/carbon composite (motor nozzle) electrically connected to an aluminum alloy structure. Early in the STS program, the aluminum structures incurred tremendous corrosive attack at coating damage locations due primarily to galvanic coupling with the carbon/carbon nozzle. Also contributing to the galvanic corrosion problem were stainless steel and titanium alloy components housed within the aluminum structures and electrically connected to the aluminum structures. This paper highlights the evolution in the protection of the aluminum structures, providing historical information and summary data from the operation of the corrosion protection systems. Also, data and information are included regarding the evaluation and application of inorganic zinc rich primers to provide anode area on the aluminum structures.

  6. Application of independent component analysis to Fermilab Booster

    SciTech Connect

    Huang, X.B.; Lee, S.Y.; Prebys, E.; Tomlin, R.; /Indiana U. /Fermilab

    2005-01-01

    Autocorrelation is applied to analyze sets of finite-sampling data such as the turn-by-turn beam position monitor (BPM) data in an accelerator. This method of data analysis, called the independent component analysis (ICA), is shown to be a powerful beam diagnosis tool for being able to decompose sampled signals into its underlying source signals. They find that the ICA has an advantage over the principle component analysis (PCA) used in the model-independent analysis (MIA) in isolating independent modes. The tolerance of the ICA method to noise in the BPM system is systematically studied. The ICA is applied to analyze the complicated beam motion in a rapid-cycling booster synchrotron at the Fermilab. Difficulties and limitations of the ICA method are also discussed.

  7. Space shuttle solid rocket booster water entry cavity collapse loads

    NASA Technical Reports Server (NTRS)

    Keefe, R. T.; Rawls, E. A.; Kross, D. A.

    1982-01-01

    Solid rocket booster cavity collapse flight measurements included external pressures on the motor case and aft skirt, internal motor case pressures, accelerometers located in the forward skirt, mid-body area, and aft skirt, as well as strain gages located on the skin of the motor case. This flight data yielded applied pressure longitudinal and circumferential distributions which compare well with model test predictions. The internal motor case ullage pressure, which is below atmospheric due to the rapid cooling of the hot internal gas, was more severe (lower) than anticipated due to the ullage gas being hotter than predicted. The structural dynamic response characteristics were as expected. Structural ring and wall damage are detailed and are considered to be attributable to the direct application of cavity collapse pressure combined with the structurally destabilizing, low internal motor case pressure.

  8. Design and operation of the AGS Booster Ionization Profile Monitor

    SciTech Connect

    Stillman, A.N.; Thern, R.E.; Van Zwienen, W.H.; Witkover, R.L.

    1991-12-31

    The AGS Booster Ionization Profile Monitor (IPM) must operate in a vacuum of about 3 {times} 10{sup {minus}11} Torr. The ultra-high vacuum imposes certain requirements on detector gain and restrictions on construction techniques. Each detector is a two-stage micro-channel plate with an integral substrate containing sixty-four printed anodes. Formed electrodes provide uniform collection fields without the use of resistors, which would be unacceptable in these vacuum conditions. An ultra-violet light calibrates the detector in its permanent mounting. An extra set of electrodes performs a first order correction to the perturbations imposed by the horizontal and vertical collection electrodes. This paper will present details of the design of the profile monitor and recent operational results. 4 refs., 6 figs.

  9. Design and operation of the AGS Booster Ionization Profile Monitor

    SciTech Connect

    Stillman, A.N.; Thern, R.E.; Van Zwienen, W.H.; Witkover, R.L.

    1991-01-01

    The AGS Booster Ionization Profile Monitor (IPM) must operate in a vacuum of about 3 {times} 10{sup {minus}11} Torr. The ultra-high vacuum imposes certain requirements on detector gain and restrictions on construction techniques. Each detector is a two-stage micro-channel plate with an integral substrate containing sixty-four printed anodes. Formed electrodes provide uniform collection fields without the use of resistors, which would be unacceptable in these vacuum conditions. An ultra-violet light calibrates the detector in its permanent mounting. An extra set of electrodes performs a first order correction to the perturbations imposed by the horizontal and vertical collection electrodes. This paper will present details of the design of the profile monitor and recent operational results. 4 refs., 6 figs.

  10. Nonlinear shell analysis of the Space Shuttle Solid Rocket Boosters

    NASA Technical Reports Server (NTRS)

    Knight, N. F., Jr.; Gillian, R. E.; Nemeth, M. P.

    1990-01-01

    A variety of structural analyses have been performed on the Solid Rocket Boosters (SRB's) to provide information that would contribute to the understanding of the failure which destroyed the Space Shuttle Challenger. This paper describes nonlinear shell analyses that were performed to characterize the behavior of an overall SRB structure and a segment of the SRB in the vicinity of the External Tank Attachment (ETA) ring. Shell finite element models were used that would accurately reflect the global load transfer in an SRB in a manner such that nonlinear shell collapse and ovalization could be assessed. The purpose of these analyses was to calculate the overall deflection and stress distributions for these SRB models when subjected to mechanical loads corresponding to critical times during the launch sequence. Static analyses of these SRB models were performed using a 'snapshot picture' of the loads. Analytical results obtained using these models show no evidence of nonlinear shell collapse for the pre-liftoff loading cases considered.

  11. Cathodic Protection Deployment on Space Shuttle Solid Rocket Boosters

    NASA Technical Reports Server (NTRS)

    Zook, Lee M.

    1998-01-01

    Corrosion protection of the space shuttle solid rocket boosters incorporates the use of cathodic protection(anodes) in concert with several coatings systems. The SRB design has large carbon/carbon composites(motor nozzle) electrically connected to an aluminum alloy structure. Early in the STS program, the aluminum structures incurred tremendous corrosive attack due primarily to the galvanic couple to the carbon/carbon nozzle at coating damage locations. Also contributing to the galvanic corrosion problem were stainless steel and titanium alloy components housed within the aluminum structures and electrically connected to the aluminum structures. This paper will highlight the evolution in the protection of the aluminum structures, providing historical information and summary data from the operation of the corrosion protection systems. Also, data and information will be included regarding the evaluation and deployment of inorganic zinc rich primers as anode area on the aluminum structures.

  12. Design of the AGS Booster Ionization Profile Monitor

    SciTech Connect

    Stillman, A.N.; Thern, R.E.; Witkover, R.L.; Van Zwienen, W.H.

    1991-01-01

    The AGS Booster Ionization Profile Monitor (IPM) must operate in a vacuum of about 3 {times} 10{sup {minus}11} Torr. The ultra-high vacuum imposes certain requirements on detector gain and restrictions on construction techniques. Each detector is a two-stage microchannel plate with an integral substrate containing sixty-four printed anodes. Formed electrodes provide uniform collection fields without the use of resistors, which would be unacceptable in these vacuum conditions. An ultra-violet light calibrates the detector in its permanent mounting. An extra set of electrodes performs a first order correction to the perturbations imposed by the horizontal and vertical collection electrodes. This paper will present details of the design of the profile monitor. 4 refs., 2 figs.

  13. A New correction magnet package for the Fermilab Booster Synchrotron

    SciTech Connect

    Kashikhin, V.S.; Carson, J.A.; Harding, D.J.; Lackey, J.R.; Makarov, A.; Pellico, W.; Prebys, E.J.; /Fermilab

    2005-05-01

    Since its initial operation over 30 years ago, most correction magnets in the Fermilab Booster Synchrotron have only been able to fully correct the orbit, tunes, coupling, and chromaticity at injection (400MeV). We have designed a new correction package, including horizontal and vertical dipoles, normal and skew quadrupoles, and normal and skew sextupoles, to provide control up to the extraction energy (8GeV). In addition to tracking the 15Hz cycle of the main, combined function magnets, the quadrupoles and sextupoles must swing through their full range in 1 ms during transition crossing. The magnet is made from 12 water-cooled racetrack coils and an iron core with 12 poles, dramatically reducing the effective magnet air gap and increasing the corrector efficiency. Magnetic field analyses of different combinations of multipoles are included.

  14. Nonlinear shell analyses of the space shuttle solid rocket boosters

    NASA Technical Reports Server (NTRS)

    Knight, Norman F., Jr.; Gillian, Ronnie E.; Nemeth, Michael P.

    1989-01-01

    A variety of structural analyses have been performed on the Solid Rocket Boosters (SRB's) to provide information that would contribute to the understanding of the failure which destroyed the Space Shuttle Challenger. This paper describes nonlinear shell analyses that were performed to characterize the behavior of an overall SRB structure and a segment of the SRB in the vicinity of the External Tank Attachment (ETA) ring. Shell finite element models were used that would accurately reflect the global load transfer in an SRB in a manner such that nonlinear shell collapse and ovalization could be assessed. The purpose of these analyses was to calculate the overall deflection and stress distributions for these SRB models when subjected to mechanical loads corresponding to critical times during the launch sequence. Static analyses of these SRB models were performed using a snapshot picture of the loads. Analytical results obtained using these models show no evidence of nonlinear shell collapse for the pre-liftoff loading cases considered.

  15. Space transportation system solid rocket booster thrust vector control system

    NASA Technical Reports Server (NTRS)

    Verble, A. J., Jr.; Mccool, A. A.; Potter, J. H.

    1979-01-01

    The Solid Rocket Booster, Thrust Vector Control (TVC) system was designed in accordance with the following requirements: self-contained power supply, fail-safe operation, 20 flight uses after exposure to seawater landings, optimized cost, and component interchangeability. Trade studies were performed which led to the selection of a recirculating hydraulic system powered by Auxiliary Power Units (APU) which drive the hydraulic actuators and gimbal the solid rocket motor nozzle. Other approaches for the system design were studied in arriving at the recirculating hydraulic system powered by an APU. These systems must withstand the imposed environment and be usable for a minimum of 20 Space Transportation System flights with a minimum of refurbishment. The TVC system has completed the major portion of qualification and verification tests and is prepared to be cleared for the first Shuttle flight (STS-1). Substantiation data will include analytical and test data.

  16. Space Transportation System solid rocket booster thrust vector control system

    NASA Technical Reports Server (NTRS)

    Verble, A. J., Jr.; Mccool, A. A.; Potter, J. H.

    1980-01-01

    The Solid Rocket Booster, Thrust Vector Control (TVC) system was designed in accordance with the following requirements: self-contained power supply, failsafe operation, 20 flight uses after exposure to seawater landings, optimized cost, and component interchangeability. Trade studies were performed which led to the selection of a recirculating hydraulic system powered by Auxiliary Power Units (APU) which drive the hydraulic actuators and gimbal the solid rocket motor nozzle. Other approaches for the system design were studied in arriving at the recirculating hydraulic system powered by an APU. These systems must withstand the imposed environment and be usable for a minimum of 20 Space Transportation System flights with a minimum of refurbishment. The TVC system completed the required qualification and verification tests and is certified for the intended application. Substantiation data include analytical and test data.

  17. Performance evaluation of DAAF as a booster material using the onionskin test

    SciTech Connect

    Morris, John S; Francois, Elizabeth G; Hooks, Daniel E; Hill, Larry G; Harry, Herbert H

    2010-12-02

    Initiation of insensitive high explosive (IHE) formulations requires the use of a booster explosive in the initiation train. Booster material selection is crucial, as the initiation must reliably function across some spectrum of physical parameters. The interest in Diaminoazoxyfurazan (DAAF) for this application stems from the fact that it possesses many traits of an IHE but is shock sensitive enough to serve as an explosive booster. A hemispherical wave breakout test, termed the onionskin test, is one of the methods used to evaluate the performance of a booster material. The wave breakout time-position history at the surface of a hemispherical IHE charge is recorded and the relative uniformity of the breakout can be quantitatively compared between booster materials. A series of onionskin tests were performed to investigate breakout and propagation diaminoazoxyfurazan (DAAF) at low temperatures to evaluate ignition and detonation spreading in comparison to other explosives commonly used in booster applications. Some wave perturbation was observed with the DAAF booster in the onionskin tests presented. The results of these tests will be presented and discussed.

  18. 75 FR 81659 - Agency Information Collection Activities; Submission for OMB Review; Comment Request; Affordable...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-28

    ...; Affordable Care Act Enrollment Opportunity Notice--Prohibition on Lifetime Limits ACTION: Notice. SUMMARY... Administration (EBSA) sponsored information collection request (ICR) titled, ``Affordable Care Act Enrollment... INFORMATION: The Patient Protection and Affordable Care Act (the Affordable Care Act)......

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

    NASA Technical Reports Server (NTRS)

    1972-01-01

    The design, development, production, and launch support analysis for determining the solid propellant rocket engine to be used with the space shuttle are discussed. Specific program objectives considered were: (1) definition of engine designs to satisfy the performance and configuration requirements of the various vehicle/booster concepts, (2) definition of requirements to produce booster stages at rates of 60, 40, 20, and 10 launches per year in a man-rated system, and (3) estimation of costs for the defined SRM booster stages.

  20. Partnerships for affordable and equitable disaster insurance

    NASA Astrophysics Data System (ADS)

    Mysiak, J.; Pérez-Blanco, C. D.

    2015-08-01

    Extreme events are becoming more frequent and intense, inflating the economic damages and social hardship set-off by natural catastrophes. Amidst budgetary cuts, there is a growing concern on societies' ability to design solvent disaster recovery strategies, while addressing equity and affordability concerns. The participation of private sector along with public one through Public-Private Partnerships (PPPs) has gained on importance as a means to address these seemingly conflicting objectives through the provision of (catastrophic) natural hazard insurance. This is the case of many OECD countries, notably some EU Member States such as the United Kingdom and Spain. The EU legislator has adapted to this new scenario and recently produced major reforms in the legislation and regulation that govern the framework in which PPPs for (catastrophic) natural hazard insurance develop. This paper has a dual objective: (1) review the complex legal background that rules the provision of insurance against natural catastrophes in the EU after these major reforms, (2) assess the implications of the reforms and offer concise Policy Guiding Principles.

  1. Affordable underwater wireless optical communication using LEDs

    NASA Astrophysics Data System (ADS)

    Pilipenko, Vladimir; Arnon, Shlomi

    2013-09-01

    In recent years the need for high data rate underwater wireless communication (WC) has increased. Nowadays, the conventional technology for underwater communication is acoustic. However, the maximum data rate that acoustic technology can provide is a few kilobits per second. On the other hand, emerging applications such as underwater imaging, networks of sensors and swarms of underwater vehicles require much faster data rates. As a result, underwater optical WC, which can provide much higher data rates, has been proposed as an alternative means of communication. In addition to high data rates, affordable communication systems become an important feature in the development requirements. The outcome of these requirements is a new system design based on off-the-shelf components such as blue and green light emitting diodes (LEDs). This is due to the fact that LEDs offer solutions characterized by low cost, high efficiency, reliability and compactness. However, there are some challenges to be met when incorporating LEDs as part of the optical transmitter, such as low modulation rates and non linearity. In this paper, we review the main challenges facing the incorporation of LEDs as an integral part of underwater WC systems and propose some techniques to mitigate the LED limitations in order to achieve high data rate communication

  2. Affordable, Robust Ceramic Joining Technology (ARCJoint) Developed

    NASA Technical Reports Server (NTRS)

    Steele, Gynelle C.

    2001-01-01

    Affordable, Robust Ceramic Joining Technology (ARCJoint) is a method for joining high temperature- resistant ceramic pieces together, establishing joints that are strong, and allowing joining to be done in the field. This new way of joining allows complex shapes to be formed by joining together geometrically simple shapes. The joining technology at NASA is one of the enabling technologies for the application of silicon-carbide-based ceramic and composite components in demanding and high-temperature applications. The technology is being developed and tested for high-temperature propulsion parts for aerospace use. Commercially, it can be used for joining ceramic pieces used for high temperature applications in the power-generating and chemical industries, as well as in the microelectronics industry. This innovation could yield big payoffs for not only the power-generating industry but also the Silicon Valley chipmakers. This technology, which was developed at the NASA Glenn Research Center by Dr. Mrityunjay Singh, is a two-step process involving first using a paste to join together ceramic pieces and bonding them by heating the joint to 110 to 120 C for between 10 and 20 min. This makes the joint strong enough to be handled for the final joining. Then, a silicon-based substance is applied to the joint and heated to 1400 C for 10 to 15 min. The resulting joint is as strong as the original ceramic material and can withstand the same high temperatures.

  3. Control your mind, make affordance available.

    PubMed

    Jin, Zheng; Lee, Yang; Zhu, Jin

    2015-01-01

    Evaluating the affordance-control interpretation of the relationship between performance and object estimation has been proposed by psychophysical and psychonomic studies. This study examined the weight estimation-performance relationship. Individuals with visual impairment or blindness put shots that varied in weight among five scales. In Experiment 1, only the perceived weight was a significant performance constraint. In Experiment 2, the weight was perceived as heavier when the participants' actions were manipulated through cognitive interpretation. The increase in perceived weight appeared to be related to performance and intrinsically scaled to the action, even when the action was only mental rather than physical. The study's findings suggest that bodily experience and action are the basis for physical judgments and likely underlie other basic cognitive interpretations of sensory stimuli. This suggestion goes hand in hand with the biofunctional approaches which assume direct experience of the integrated wholeness of one's body is fundamental for developing other kinds of awareness. Different perspectives from oriental philosophy and psychology are also discussed. PMID:25741298

  4. Empathy and the responsiveness to social affordances.

    PubMed

    Kiverstein, Julian

    2015-11-01

    The direct perception theory of empathy claims that we can immediately experience a person's state of mind. I can see for instance that my neighbour is angry with me in his bodily countenance. I develop a version of the direct perception theory of empathy which takes this perceptual capacity to depend upon recognising in what way the other person is responsive to the affordances the environment provides. By recognising which possibilities for action are relevant to a person, I can thereby understand something about the meaning they give to the world. I come to share something of their perspective on the world, and this allows me to grasp based on my perception of them something about their current state of mind. I argue that shared affect plays a central role in this perceptual capacity. Shared affect allows me to orient my attention to possibilities for action that matter to the other person. I end by briefly discuss the implications of this view of empathy for the disturbances in so-called "cognitive empathy" that are found in people diagnosed with autism spectrum disorder. PMID:26021190

  5. Income Dynamics and the Affordable Care Act

    PubMed Central

    Shore-Sheppard, Lara D

    2014-01-01

    Objective To examine the sources of family income dynamics leading to movement into and out of Medicaid expansion and subsidy eligibility under the Affordable Care Act. Data Source Survey of Income and Program Participation (SIPP): 1996, 2001, 2004, 2008 panels. Study Design Considering four broad subsidy eligibility categories for monthly Modified Adjusted Gross Income (MAGI) (<138 percent of the Federal Poverty Level [FPL], 138–250 percent FPL, 250–400 percent FPL, and >400 percent FPL), I use duration analysis to examine determinants of movements between categories over the course of a year. Data Collection/Extraction Using detailed monthly data, I determine the members of tax-filing units and calculate an approximation of MAGI at the monthly level. The analysis sample is adults ages 22–64 years. Principal Findings Incomes are highly variable within a year, particularly at the lower end of the income distribution. Employment transitions, including transitions not involving a period of nonemployment, and family structure changes strongly predict sufficient income volatility to trigger a change in subsidy category. Conclusions Income volatility arising from employment and family structure changes is likely to trigger changes in subsidy eligibility within the year, but the sources and effects of the volatility differ substantially depending on the individual's position in the income distribution. PMID:25327987

  6. Composite Nozzle/Thrust Chambers Analyzed for Low-Cost Boosters

    NASA Technical Reports Server (NTRS)

    Sullivan, Roy M.

    1999-01-01

    The Low Cost Booster Technology Program is an initiative to minimize the cost of future liquid engines by using advanced materials and innovative designs, and by reducing engine complexity. NASA Marshall Space Flight Center s 60K FASTRAC Engine is one example where these design philosophies have been put into practice. This engine burns a liquid kerosene/oxygen mixture. It uses a one-piece, polymer composite thrust chamber/nozzle that is constructed of a tape-wrapped silica phenolic liner, a metallic injector interface ring, and a filament-wound epoxy overwrap. A cooperative effort between NASA Lewis Research Center s Structures Division and Marshall is underway to perform a finite element analysis of the FASTRAC chamber/nozzle under all the loading and environmental conditions that it will experience during its lifetime. The chamber/nozzle is a complex composite structure. Of its three different materials, the two composite components have distinctly different fiber architectures and, consequently, require separate material model descriptions. Since the liner is tape wrapped, it is orthotropic in the nozzle global coordinates; and since the overwrap is filament wound, it is treated as a monoclinic material. Furthermore, the wind angle on the overwrap varies continuously along the length of the chamber/nozzle.

  7. Optimization of heat transfer in a high-energy booster rocket

    SciTech Connect

    Tarpley, C.; Lewis, M.J.

    1994-11-01

    This article describes the performance optimization of a high-energy booster rocket powered by the proton/antiproton annihilation reaction. This procedure can be used to evaluate and optimize new concepts for advanced high-energy propulsion systems as well as to improve performance in nuclear thermal engines if coupled with a neutronics code. The analysis includes a one-speed estimation of the gamma radiation transport in the engine shield and an analysis of the heat transfer to the hydrogen working fluid as it flows through the engine. The engine performance model is optimized using the method of feasible directions concept as implemented in the CONMIN Fortran package. CONMIN is used to explore the performance limit of this conceptual design and develop sensitivity information from which conclusions are drawn about the direction of future work. The optimized engine has a specific impulse of 1037 s. The total launch system mass as designed is 890,000 kg, which includes a payload of 50,000 kg. 16 refs.

  8. Environmental risks associated with booster biocides leaching from spent anti-fouling paint particles in coastal environments.

    PubMed

    Hasan, Chowdhury K; Turner, Andrew; Readman, James; Frickers, Trish

    2014-12-01

    Boat maintenance facilities in coastal areas contribute a significant amount of antifouling paint particles (APP) to coastal environments. Very few studies have concentrated on the leaching of booster biocides embedded in old paint particles. Therefore, this study attempted to assess the leaching of Dichlofluanid and Irgarol 1051 from APP collected from Mayflower Marina in southwest England. They were analyzed by GC-MS. A leaching experiment revealed that a considerable amount of Dichlofluanid (ca. 24 μg/L) leached from 0.4 g/L of APP after the first hour, followed by a marked decline in the amount measured in the water over time, almost degrading after 24 h in seawater, affording less of an environmental threat to non-target organisms. Conversely, Irgarol 1051 appeared to be persistent and continuously leached from the 0.4 g/L of APP even after 10 days, yielding a concentration of 0.61 μg/L in seawater, potentially posing a significant threat to the aquatic environment through leaching from APP. PMID:25654936

  9. Essential drugs in AIDS care: issues of availability and affordability.

    PubMed

    Kaur, S R

    1996-01-01

    Several antiretroviral drugs against HIV/AIDS have been developed in recent years. These drugs, reverse transcriptase inhibitors and protease inhibitors, inhibit the reproduction of HIV, but do not eliminate the presence of HIV in the body. The cost of drugs to treat one person with HIV/AIDS easily runs into the thousands of US dollars per year. These new drugs are therefore routinely used in developed countries, but not among the masses in developing countries. Many of the drugs needed to treat the opportunistic infections present during advanced HIV infection and AIDS are also prohibitively expensive for both developing countries and most individuals in those countries. The imposition of World Bank and International Monetary Fund structural adjustment programs together with decreased household purchasing power during the 1990s has led to increased demand for public sector services amid reduced public expenditure. The private sector is increasingly taking over the drug supply in developing countries, driving the cost of drugs out of the range of affordability for the vast majority of the poor. One strategy to contain the cost of drugs is for governments to develop and implement an integrated national drug policy based upon the concept of essential drugs and their rational use. PMID:12292110

  10. Mission and Implementation of an Affordable Lunar Return

    NASA Technical Reports Server (NTRS)

    Spudis, Paul; Lavoie, Anthony

    2010-01-01

    We present an architecture that establishes the infrastructure for routine space travel by taking advantage of the Moon's resources, proximity and accessibility. We use robotic assets on the Moon that are teleoperated from Earth to prospect, test, demonstrate and produce water from lunar resources before human arrival. This plan is affordable, flexible and not tied to any specific launch vehicle solution. Individual surface pieces are small, permitting them to be deployed separately on small launchers or combined together on single large launchers. Schedule is our free variable; even under highly constrained budgets, the architecture permits this program to be continuously pursued using small, incremental, cumulative steps. The end stage is a fully functional, human-tended lunar outpost capable of producing 150 metric tonnes of water per year enough to export water from the Moon and create a transportation system that allows routine access to all of cislunar space. This cost-effective lunar architecture advances technology and builds a sustainable transportation infrastructure. By eliminating the need to launch everything from the surface of the Earth, we fundamentally change the paradigm of spaceflight.

  11. Ground Processing Affordability for Space Vehicles

    NASA Technical Reports Server (NTRS)

    Ingalls, John; Scott, Russell

    2011-01-01

    Launch vehicles and most of their payloads spend the majority of their time on the ground. The cost of ground operations is very high. So, why so often is so little attention given to ground processing during development? The current global space industry and economic environment are driving more need for efficiencies to save time and money. Affordability and sustainability are more important now than ever. We can not continue to treat space vehicles as mere science projects. More RLV's (Reusable Launch Vehicles) are being developed for the gains of reusability which are not available for ELV's (Expendable Launch Vehicles). More human-rated vehicles are being developed, with the retirement of the Space Shuttles, and for a new global space race, yet these cost more than the many unmanned vehicles of today. We can learn many lessons on affordability from RLV's. DFO (Design for Operations) considers ground operations during design, development, and manufacturing-before the first flight. This is often minimized for space vehicles, but is very important. Vehicles are designed for launch and mission operations. You will not be able to do it again if it is too slow or costly to get there. Many times, technology changes faster than space products such that what is launched includes outdated features, thus reducing competitiveness. Ground operations must be considered for the full product Lifecycle, from concept to retirement. Once manufactured, launch vehicles along with their payloads and launch systems require a long path of processing before launch. Initial assembly and testing always discover problems to address. A solid integration program is essential to minimize these impacts, as was seen in the Constellation Ares I-X test rocket. For RLV's, landing/recovery and post-flight turnaround activities are performed. Multi-use vehicles require reconfiguration. MRO (Maintenance, Repair, and Overhaul) must be well-planned--- even for the unplanned problems. Defect limits and

  12. Affordable Space Tourism: SpaceStationSim

    NASA Technical Reports Server (NTRS)

    2006-01-01

    For over 5 years, people have been living and working in space on the International Space Station (ISS), a state-of-the-art laboratory complex orbiting high above the Earth. Offering a large, sustained microgravity environment that cannot be duplicated on Earth, the ISS furthers humankind s knowledge of science and how the body functions for extended periods of time in space all of which will prove vital on long-duration missions to Mars. On-orbit construction of the station began in November 1998, with the launch of the Russian Zarya Control Module, which provided battery power and fuel storage. This module was followed by additional components and supplies over the course of several months. In November 2000, the first ISS Expedition crew moved in. Since then, the ISS has continued to change and evolve. The space station is currently 240 feet wide, measured across the solar arrays, and 171 feet long, from the NASA Destiny Laboratory to the Russian Zvezda Habitation Module. It is 90 feet tall, and it weighs approximately 404,000 pounds. Crews inhabit a living space of about 15,000 cubic feet. To date, 90 scientific investigations have been conducted on the space station. New results from space station research, from basic science to exploration research, are being published each month, and more breakthroughs are likely to come. It is not all work on the space station, though. The orbiting home affords many of the comforts one finds on Earth. There is a weightless "weight room" and even a musical keyboard alongside research facilities. Holidays are observed, and with them, traditional foods such as turkey and cobbler are eaten, with lemonade to wash them down

  13. NEW EMPLOYEE ON THE JOB - LEO C FRANCISCUS MISSIONS ANALYSIS BRANCH WORKING ON RECOVERABLE BOOSTERS

    NASA Technical Reports Server (NTRS)

    1963-01-01

    NEW EMPLOYEE ON THE JOB - LEO C FRANCISCUS MISSIONS ANALYSIS BRANCH WORKING ON RECOVERABLE BOOSTERS - PERFORM MISSION ANALYSIS STUDIES - AT PRESENT TIME STUDYING SUBSONIC AND SUPERSONIC COMBUSTION RAM JET ENGINES - ALSO PERFORMING ANALYTICAL STUDIES

  14. Study on the Structures of Two Booster Pellets Having High Initiation Capacity

    NASA Astrophysics Data System (ADS)

    Shuang-Qi, Hu; Hong-Rong, Liu; Li-shuang, Hu; Xiong, Cao; Xiang-Chao, Mi; Hai-Xia, Zhao

    2014-05-01

    Insensitive munitions (IM) improve the survivability of both weapons and their associated platforms, which can lead to a reduction in casualties, mission losses, and whole life costs. All weapon systems contain an explosive train that needs to meet IM criteria but reliably initiate a main charge explosive. To ensure that these diametrically opposed requirements can be achieved, new highly effective booster charge structures were designed. The initiation capacity of the two booster pellets was studied using varied composition and axial-steel-dent methods. The results showed that the two new booster pellets can initiate standard main charge pellets with less explosive mass than the ordinary cylindrical booster pellet. The numerical simulation results were in good agreement with the experiment results.

  15. Effects of 1980 technology on weight of a recovery system for a one million pound booster

    NASA Technical Reports Server (NTRS)

    Eckstrom, C. V.

    1975-01-01

    The effects were evaluated of 1980 technology on the weight of recovery systems capable of decelerating a one-million-pound booster to vertical velocities of 60 or 30 ft/sec at sea level impact. A nominal set of booster staging conditions were assumed and there were no constraints on parachute size, number or type. The effects of new materials that would be available by 1980, the effects of booster attitude during entry, various parachute staging methods, parachute reefing schemes, parachute-retro rocket hybrid systems, and the effects of dividing the booster into separate pieces for recovery were evaluated. It was determined that for the systems considered, a hybrid parachute-retro-rocket recovery system would have the minimum weight. New materials now becoming available for parachute fabrication should result in a 37-percent reduction in hybrid recovery system weight for an impact velocity of 30 fps.

  16. Thermodynamic and chemical parameters of the exhaust effluents from the HARPOON booster motor

    NASA Technical Reports Server (NTRS)

    Stephens, J. B.; Goldford, A. I.

    1978-01-01

    The exhaust products from the Harpoon booster motors were analyzed using both thermodynamic analysis and finite-rate chemistry. The resulting constituents are presented together with a discussion of the techniques employed.

  17. MEASUREMENTS AND MODELING OF EDDY CURRENT EFFECTS IN BNL'S AGS BOOSTER.

    SciTech Connect

    BROWN, K.A.; AHRENS, L.; GARDNER, C.; GLENN, J.W.; HARVEY, M.; MENG, W.; ZENO, K.

    2006-06-23

    Recent beam experiments at BNL's AGS Booster have enabled us to study in more detail the effects of eddy currents on the lattice structure and our control over the betatron tune. The Booster is capable of operating at ramp rates as high as 9 T/sec. At these ramp rates eddy currents in the vacuum chambers significantly alter the fields and gradients seen by the beam as it is accelerated. The Booster was designed with these effects in mind and to help control the field uniformity and linearity in the Booster Dipoles special vacuum chambers were designed with current windings to negate the affect of the induced eddy currents. In this report results from betatron tune measurements and eddy current simulations will be presented. We will then present results from modeling the accelerator using the results of the magnetic field simulations and compare these to the measurements.

  18. 78 FR 15409 - Patient Protection and Affordable Care Act; HHS Notice of Benefit and Payment Parameters for 2014

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-03-11

    ... parameters for these programs. \\1\\ 77 FR 17220 (March 23, 2012). Advance payments of the premium tax credit.../Av-csr-bulletin.pdf . \\3\\ 77 FR 18310 (March 27, 2012). Federally-facilitated Exchange user fees... Affordable Care Act'' (75 FR 74864) which established standards for the MLR program. Since then, we have...

  19. Affordable Development and Demonstrationof a Small NTR Engine and Stage: A Preliminary NASA, DOE and Industry Assessment

    NASA Technical Reports Server (NTRS)

    Borowski, Stanley K.; Sefcik, Robert J.; Qualls, A. L.; Schnitzler, B.G.; Joyner, C. R.

    2014-01-01

    Formulation of Affordable and Sustainable NTP Development Strategy is Underway Involving NASA, DOE and Industry. In FY11, Nuclear Thermal Propulsion (NTP) was identified as a key propulsion option under the Advanced In-Space Propulsion (AISP) component of NASA's Exploration Technology Development and Demonstration (ETDD) program.

  20. Affordance Analysis--Matching Learning Tasks with Learning Technologies

    ERIC Educational Resources Information Center

    Bower, Matt

    2008-01-01

    This article presents a design methodology for matching learning tasks with learning technologies. First a working definition of "affordances" is provided based on the need to describe the action potentials of the technologies (utility). Categories of affordances are then proposed to provide a framework for analysis. Following this, a methodology…

  1. The Influence of Affordability in Strategic Enrollment Management

    ERIC Educational Resources Information Center

    Pugh, Susan L.; Thompson, Roger J.

    2008-01-01

    In state houses around the country, one of the common higher education themes is affordability. As tuition costs have increased at rates exceeding that of inflation, students and families have pressed their legislative representatives to examine these increases. Affordability is a term used by various constituent groups, and its definition varies…

  2. 24 CFR 1006.20 - Grants for affordable housing activities.

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ... URBAN DEVELOPMENT NATIVE HAWAIIAN HOUSING BLOCK GRANT PROGRAM General § 1006.20 Grants for affordable housing activities. (a) Annual grant. Each fiscal year, HUD will make a grant (to the extent that amounts... 24 Housing and Urban Development 4 2013-04-01 2013-04-01 false Grants for affordable...

  3. 24 CFR 1006.20 - Grants for affordable housing activities.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... URBAN DEVELOPMENT NATIVE HAWAIIAN HOUSING BLOCK GRANT PROGRAM General § 1006.20 Grants for affordable housing activities. (a) Annual grant. Each fiscal year, HUD will make a grant (to the extent that amounts... 24 Housing and Urban Development 4 2012-04-01 2012-04-01 false Grants for affordable...

  4. 24 CFR 1006.20 - Grants for affordable housing activities.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... URBAN DEVELOPMENT NATIVE HAWAIIAN HOUSING BLOCK GRANT PROGRAM General § 1006.20 Grants for affordable housing activities. (a) Annual grant. Each fiscal year, HUD will make a grant (to the extent that amounts... 24 Housing and Urban Development 4 2014-04-01 2014-04-01 false Grants for affordable...

  5. 24 CFR 1006.20 - Grants for affordable housing activities.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... URBAN DEVELOPMENT NATIVE HAWAIIAN HOUSING BLOCK GRANT PROGRAM General § 1006.20 Grants for affordable housing activities. (a) Annual grant. Each fiscal year, HUD will make a grant (to the extent that amounts... 24 Housing and Urban Development 4 2010-04-01 2010-04-01 false Grants for affordable...

  6. One Hand, Two Objects: Emergence of Affordance in Contexts

    ERIC Educational Resources Information Center

    Borghi, Anna M.; Flumini, Andrea; Natraj, Nikhilesh; Wheaton, Lewis A.

    2012-01-01

    Studies on affordances typically focus on single objects. We investigated whether affordances are modulated by the context, defined by the relation between two objects and a hand. Participants were presented with pictures displaying two manipulable objects linked by a functional (knife-butter), a spatial (knife-coffee mug), or by no relation. They…

  7. Providing Affordable Housing: Small Communities Benefit from Upgrading Dilapidated Homes.

    ERIC Educational Resources Information Center

    Hestekin, Kay

    1991-01-01

    Describes the Affordable Housing Opportunities Program (AHOP) created by the Eau Claire County Housing Authority in Wisconsin. The AHOP buys, renovates, and sells homes for prices below fair market value. This provides safe, sanitary housing for families who could not otherwise afford it. Describes the purchase, renovation, and sale of four…

  8. What's the Issue about Affordability of Public Higher Education?

    ERIC Educational Resources Information Center

    Goff, Donald Gary

    This study compared and contrasted data reports of two national policy centers on the affordability of public higher education. The study examined cost findings of the National Center for Educational Statistics (NCES) and the major affordability findings of the National Center for Public Policy and Higher Education (NCPPHE). Both policy centers…

  9. 24 CFR 92.254 - Qualification as affordable housing: Homeownership.

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ... 24 Housing and Urban Development 1 2013-04-01 2013-04-01 false Qualification as affordable housing: Homeownership. 92.254 Section 92.254 Housing and Urban Development Office of the Secretary, Department of Housing and Urban Development HOME INVESTMENT PARTNERSHIPS PROGRAM Project Requirements § 92.254 Qualification as affordable...

  10. 24 CFR 92.254 - Qualification as affordable housing: Homeownership.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... application under 24 CFR part 597 has incorporated the type of market data described above, that submission... 24 Housing and Urban Development 1 2011-04-01 2011-04-01 false Qualification as affordable housing... Qualification as affordable housing: Homeownership. (a) Acquisition with or without rehabilitation. Housing...

  11. Nurturing Opportunities for Educational Leadership: How Affordance and Leadership Interconnect

    ERIC Educational Resources Information Center

    Margolin, Ilana

    2013-01-01

    This qualitative ethnographic study focused on the affordances that facilitated the emergence of leadership, capturing a range of perspectives on leadership and leadership development of four groups: district superintendents; teacher-educators; mentor-teachers and graduates. The term "affordances" implies a reciprocal relationship…

  12. Response to Booster Doses of Hepatitis B Vaccine among Young Adults Who Had Received Neonatal Vaccination

    PubMed Central

    Chan, Paul K. S.; Ngai, Karry L. K.; Lao, Terence T.; Wong, Martin C. S.; Cheung, Theresa; Yeung, Apple C. M.; Chan, Martin C. W.; Luk, Scotty W. C.

    2014-01-01

    Background Newborns who have received hepatitis B immunization in 1980s are now young adults joining healthcare disciplines. The need for booster, pre- and post-booster checks becomes a practical question. Aims The aim of this study is to refine the HBV vaccination policy for newly admitted students in the future. Methods A prospective study on medical and nursing school entrants to evaluate hepatitis B serostatus and the response to booster doses among young adults. Findings Among 212 students, 17–23-year-old, born after adoption of neonatal immunization, 2 (0.9%) were HBsAg positive, 40 (18.9%) were anti-HBs positive. At 1 month after a single-dose booster for anti-HBs-negative students, 14.5% had anti-HBs <10 mIU/mL, 29.0% and 56.5% were 10–100 and >100 mIU/mL, respectively. The anti-HBs levels were significantly higher for females than males (mean [SD]: 431 [418] vs. 246 [339] mIU/mL, P = 0.047). At 2–4 month after the third booster dose, 97.1% had anti-HBs >100 mIU/mL and 2.9% had 10–100 mIU/mL. Conclusions Pre-booster check is still worthwhile to identify carriers among newly recruited healthcare workers born after adoption of neonatal immunization. A 3-dose booster, rather than a single dose, is required for the majority to achieve an anti-HBs level >100 mIU/mL, as memory immunity has declined in a substantial proportion of individuals. Cost-effectiveness of post-booster check for anti-HBs is low and should be further evaluated based on contextual specific utilization of results. PMID:25198289

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

    NASA Technical Reports Server (NTRS)

    Vonderesch, A. H.

    1972-01-01

    The factors affecting the choice of the 156 inch diameter, parallel burn, solid propellant rocket engine for use with the space shuttle booster are presented. Primary considerations leading to the selection are: (1) low booster vehicle cost, (2) the largest proven transportable system, (3) a demonstrated design, (4) recovery/reuse is feasible, (5) abort can be easily accomplished, and (6) ecological effects are minor.

  14. Design and fabrication of a multi-element corrector magnet for the Fermilab Booster

    SciTech Connect

    Makarov, A.; Drennan, C.; DiMarco, J.; Harding, David J.; Kashikhin, V.S.; Lackey, J.R.; Prebys, E.J.; Schlabach, P.; Velev, G.V.; Walbridge, D.G.; /Fermilab

    2007-08-01

    A new package of six corrector elements has been designed to better control the beam position, tune, and chromaticity in the Fermilab Booster synchrotron. It incorporates both normal and skew orientations of dipole, quadrupole, and sextupole magnets. These new corrector magnets will be installed in the Fermilab Booster ring in place of old style corrector elements. A severe space restriction and rapid slew rate have posed special challenges. The magnet design, construction, and performance are presented.

  15. An Affordability Comparison Tool (ACT) for Space Transportation

    NASA Technical Reports Server (NTRS)

    McCleskey, C. M.; Bollo, T. R.; Garcia, J. L.

    2012-01-01

    NASA bas recently emphasized the importance of affordability for Commercial Crew Development Program (CCDP), Space Launch Systems (SLS) and Multi-Purpose Crew Vehicle (MPCV). System architects and designers are challenged to come up with architectures and designs that do not bust the budget. This paper describes the Affordability Comparison Tool (ACT) analyzes different systems or architecture configurations for affordability that allows for a comparison of: total life cycle cost; annual recurring costs, affordability figures-of-merit, such as cost per pound, cost per seat, and cost per flight, as well as productivity measures, such as payload throughput. Although ACT is not a deterministic model, the paper develops algorithms and parametric factors that use characteristics of the architectures or systems being compared to produce important system outcomes (figures-of-merit). Example applications of outcome figures-of-merit are also documented to provide the designer with information on the relative affordability and productivity of different space transportation applications.

  16. Ice Particle Analysis of the Honeywell AL502 Engine Booster

    NASA Technical Reports Server (NTRS)

    Bidwell, Colin S.; Rigby, David L.

    2015-01-01

    A flow and ice particle trajectory analysis was performed for the booster of the Honeywell ALF502 engine. The analysis focused on two closely related conditions one of which produced an icing event and another which did not during testing of the ALF502 engine in the Propulsion Systems Lab (PSL) at NASA Glenn Research Center. The flow analysis was generated using the NASA Glenn GlennHT flow solver and the particle analysis was generated using the NASA Glenn LEWICE3D v3.63 ice accretion software. The inflow conditions for the two conditions were similar with the main differences being that the condition that produced the icing event was 6.8 K colder than the non-icing event case and the inflow ice water content (IWC) for the non-icing event case was 50% less than for the icing event case. The particle analysis, which considered sublimation, evaporation and phase change, was generated for a 5 micron ice particle with a sticky impact model and for a 24 micron median volume diameter (MVD), 7 bin ice particle distribution with a supercooled large droplet (SLD) splash model used to simulate ice particle breakup. The particle analysis did not consider the effect of the runback and re-impingement of water resulting from the heated spinner and anti-icing system. The results from the analysis showed that the amount of impingement for the components were similar for the same particle size and impact model for the icing and non-icing event conditions. This was attributed to the similar aerodynamic conditions in the booster for the two cases. The particle temperature and melt fraction were higher at the same location and particle size for the non-icing event than for the icing event case due to the higher incoming inflow temperature for the non-event case. The 5 micron ice particle case produced higher impact temperatures and higher melt fractions on the components downstream of the fan than the 24 micron MVD case because the average particle size generated by the particle

  17. Research on advanced transportation systems

    NASA Astrophysics Data System (ADS)

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

    1992-08-01

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

  18. Modeling improvements in booster seat use: a discrete choice conjoint experiment.

    PubMed

    Cunningham, Charles E; Bruce, Beth S; Snowdon, Anne W; Chen, Yvonne; Kolga, Carol; Piotrowski, Caroline; Warda, Lynne; Correale, Heather; Clark, Erica; Barwick, Melanie

    2011-11-01

    Automobile crashes are the leading cause of death in children aged 1-14 years. Many children, however, are not properly restrained in safety seats that reduce serious injury and death. This study used a discrete choice conjoint experiment to study factors influencing the decision to use booster seats. Parents of 1714 children aged 4-9 years from nine Canadian provinces completed choice tasks presenting experimentally varied combinations of 15 4-level booster seat promotion attributes. Latent class analysis yielded three segments of parents. The choices of the Benefit Sensitive segment (50%) were most sensitive to the injury prevention benefits of booster seats. The choices of parents in the Context Sensitive segment (33.5%) were more likely to be influenced by installation complexity, oppositional behavior, and the prospect that their child may be teased for riding in booster seats. Parents in the High Risk segment (16.5%) were younger, less educated, and less knowledgeable about vehicle safety legislation. They anticipated fewer benefits, expected more barriers and were less likely to use booster seats. Simulations suggest that consistent enforcement coupled with advertising focusing on injury prevention and the use of booster seats by other parents would increase adoption. PMID:21819828

  19. Space shuttle phase B wind tunnel model and test information. Volume 1: Booster configuration

    NASA Technical Reports Server (NTRS)

    Glynn, J. L.; Poucher, D. E.

    1988-01-01

    Archived wind tunnel test data are available for flyback booster or other alternative recoverable configurations as well as reusable orbiters studied during initial development (Phase B) of the Space Shuttle. Considerable wind tunnel data was acquired by the competing contractors and the NASA Centers for an extensive variety of configurations with an array of wing and body planforms. All contractor and NASA wind tunnel test data acquired in the Phase B development have been compiled into a database and are available for application to current winged flyback or recoverable booster aerodynamic studies. The Space Shuttle Phase B Wind Tunnel Database is structured by vehicle component and configuration type. Basic components include the booster, the orbiter and the launch vehicle. Booster configuration types include straight and delta wings, canard, cylindrical, retroglide and twin body. Orbiter configuration types include straight and delta wings, lifting body, drop tanks, and double delta wings. Launch configurations include booster and orbiter components in various stacked and tandem combinations. This is Volume 1 (Part 1) of the report -- Booster Configuration.

  20. Space shuttle phase B wind tunnel model and test information. Volume 1: Booster configuration

    NASA Technical Reports Server (NTRS)

    Glynn, J. L.; Poucher, D. E.

    1988-01-01

    Archived wind tunnel test data are available for flyback booster or other alternative recoverable configurations as well as reusable orbiters studied during initial development (Phase B) of the Space Shuttle. Considerable wind tunnel data was acquired by the competing contractors and the NASA Centers for an extensive variety of configurations with an array of wing and body planforms. All contractor and NASA wind tunnel test data acquired in the Phase B development have been compiled into a database and are available for application to current winged flyback or recoverable booster aerodynamic studies. The Space Shuttle Phase B Wind Tunnel Database is structured by vehicle component and configuration type. Basic components include the booster, the orbiter, and the launch vehicle. Booster configuration types include straight and delta wings, canard, cylindrical, retroglide and twin body. Orbiter configuration types include straight and delta wings, lifting body, drop tanks and double delta wings. Launch configurations include booster and orbiter components in various stacked and tandem combinations. This is Volume 1 (Part 2) of the report -- Booster Configuration.

  1. Early Beam Injection Scheme for the Fermilab Booster: A Path for Intensity Upgrade

    SciTech Connect

    Bhat, C. M.

    2015-10-28

    Over the past decade, Fermilab has focused efforts on the intensity frontier physics and is committed to increase the average beam power delivered to the neutrino and muon programs substantially. Many upgrades to the existing injector accelerators, namely, the current 400 MeV LINAC and the Booster, are in progress under the Proton Improvement Plan (PIP). Proton Improvement Plan-II (PIP-II) proposes to replace the existing 400 MeV LINAC by a new 800 MeV LINAC, as an injector to the Booster which will increase Booster output power by nearly a factor of two from the PIP design value by the end of its completion. In any case, the Fermilab Booster is going to play a very significant role for nearly next two decades. In this context, I have developed and investigated a new beam injection scheme called "early injection scheme" (EIS) for the Booster with the goal to significantly increase the beam intensity output from the Booster thereby increasing the beam power to the HEP experiments even before PIP-II era. The scheme, if implemented, will also help improve the slip-stacking efficiency in the MI/RR. Here I present results from recent simulations, beam studies, current status and future plans for the new scheme.

  2. Crashworthy Seats Would Afford Superior Protection

    NASA Technical Reports Server (NTRS)

    Gohmert, Dustin

    2009-01-01

    Seats to prevent or limit crash injuries to astronauts aboard the crew vehicle of the Orion spacecraft are undergoing development. The design of these seats incorporates and goes beyond crash-protection concepts embodied in prior spacecraft and racing-car seats to afford superior protection against impacts. Although the seats are designed to support astronauts in a recumbent, quasi-fetal posture that would likely not be suitable for non-spacecraft applications, parts of the design could be adapted to military and some civilian aircraft seats and to racing car seats to increase levels of protection. The main problem in designing any crashworthy seat is to provide full support of the occupant against anticipated crash and emergency-landing loads so as to safely limit motion, along any axis, of any part of the occupant s body relative to (1) any other part of the occupant s body, (2) the spacecraft or other vehicle, and (3) the seat itself. In the original Orion spacecraft application and in other applications that could easily be envisioned, the problem is complicated by severe limits on space available for the seat, a requirement to enable rapid egress by the occupant after a crash, and a requirement to provide for fitting of the seat to a wide range of sizes and shapes of a human body covered by a crash suit, space suit, or other protective garment. The problem is further complicated by other Orion-application-specific requirements that must be omitted here for the sake of brevity. To accommodate the wide range of crewmember body lengths within the limits on available space in the original Orion application, the design provides for taller crewmembers to pull their legs back closer toward their chests, while shorter crewmembers can allow their legs to stretch out further. The range of hip-support seat adjustments needed to effect this accommodation, as derived from NASA s Human Systems Integration Standard, was found to define a parabolic path along which the knees

  3. The Affording Mars Workshop: Background and Recommendations

    NASA Technical Reports Server (NTRS)

    Thronson, Harley A.; Carberry, Christopher

    2014-01-01

    . The workshop was organized around three topical breakout sessions: 1. The ISS and the path to Mars: The critical coming decade 2. Affordability and sustainability: what does it mean and what are its implications within guidelines established at the start of the workshop? 3. Notional sequence(s) of cost-achievable missions for the 2020s to 2030s, including capability objectives at each stage and opportunities for coordinated robotic partnerships.

  4. Liquid Rocket Booster (LRB) for the Space Transportation System (STS) systems study. Appendix E: Pressure-fed booster test bed for the liquid rocket booster study

    NASA Technical Reports Server (NTRS)

    1989-01-01

    The stress analysis/structural design of the Pressure-Fed Booster Engine Test Bed using the existing F-1 Test Facility Test Stand at Huntsville, Alabama is described. The analysis has been coded and set up for solution on NASTRAN. A separate stress program was established to take the NASTRAN output and perform stress checks on the members. Joint checks and other necessary additional checks were performed by hand. The notes include a brief description of other programs which assist in reproducing and reviewing the NASTRAN results. The redesign of the test stand members and the stress analysis was performed per the A.I.S.C. Code. Loads on the stand consist of the loaded run tanks; wind loads; seismic loads; live loads consisting of snow and ice: live and dead loads of steel; and loaded pressurant bottle. In combining loads, wind loads and seismic loads were each combined with full live loads. Wind and seismic loads were not combined. No one third increase in allowables was taken for the environmental loads except at decks 147 and 214, where the increase was used when considering the stay rods, brackets and stay beams. Wind and seismic loads were considered from each of the four coordinate directions (i.e. N,S,E,W) to give eight basic conditions. The analysis was run with the pressurant tank mounted at level 125. One seismic condition was also run with the tank mounted at levels 169 and 214. No failures were noted with mounting at level 169, but extensive deck failure with mounting at level 214 (the loadsets used are included on the tape, but no detailed results are included in the package). Decking support beams at levels 147 and 214 are not included in the model. The stress program thus does not reduce strut lengths to the length between support beams (the struts are attached to the beams at intersection points) and gives stress ratios larger than one for some of the struts. The affected members were therefore checked by hand.

  5. Balancing adequacy and affordability?: Essential Health Benefits under the Affordable Care Act.

    PubMed

    Haeder, Simon F

    2014-12-01

    The Essential Health Benefits provisions under the Affordable Care Act require that eligible plans provide coverage for certain broadly defined service categories, limit consumer cost-sharing, and meet certain actuarial value requirements. Although the Department of Health and Human Services (HHS) was tasked with the regulatory development of these EHB under the ACA, the department quickly devolved this task to the states. Not surprisingly, states fully exploited the leeway provided by HHS, and state decision processes and outcomes differed widely. However, none of the states took advantage of the opportunity to restructure fundamentally their health insurance markets, and only a very limited number of states actually included sophisticated policy expertise in their decisionmaking processes. As a result, and despite a major expansion of coverage, the status quo ex ante in state insurance markets was largely perpetuated. Decisionmaking for the 2016 revisions should be transparent, included a wide variety of stakeholders and policy experts, and focus on balancing adequacy and affordability. However, the 2016 revisions provide an opportunity to address these previous shortcomings. PMID:25316210

  6. Are Americans finding affordable coverage in the health insurance marketplaces? Results from the Commonwealth Fund Affordable Care Act Tracking Survey.

    PubMed

    Rasmussen, Petra W; Collins, Sara R; Doty, Michelle M; Beutel, Sophie

    2014-09-01

    By the end of the first open enrollment period for coverage offered through the Affordable Care Act's marketplaces, increasing numbers of people said they found it easy to find a plan they could afford, according to The Commonwealth Fund's Affordable Care Act Tracking Survey, April-June 2014. Adults with low or moderate incomes were more likely to say it was easy to find an affordable plan than were adults with higher incomes. Adults with low or moderate incomes who purchased a plan through the marketplaces this year have similar premium costs and deductibles as adults in the same income ranges with employer-provided coverage. A majority of adults with marketplace coverage gave high ratings to their insurance and were confident in their ability to afford the care they need when sick. PMID:25265646

  7. Residual Silicone Detection. [external tank and solid rocket booster surfaces

    NASA Technical Reports Server (NTRS)

    Smith, T.

    1980-01-01

    Both photoelectron emission and ellipsometry proved successful in detecting silicone contamination on unpainted and epoxy painted metal surfaces such as those of the external tank and the solid rocket booster. Great success was achieved using photoelectron emission (PEE). Panels were deliberately contaminated to controlled levels and then mapped with PEE to reveal the areas and levels that were contaminated. The panels were then tested with regard to adhesive properties. Tapes were bonded over the contaminated and uncontaminated regions and the peel force was measured, or the contaminated panels were bonded (with CPR 483 foam) to uncontaminated panels and made into lap shear specimens. Other panels were bonded and made into wedge specimens for hydrothermal stress endurance tests. Strong adhesion resulted if the PEE signal fell within an acceptance window, but was poor outside the acceptance window. A prototype instrument is being prepared which can automatically be scanned over the external liquid hydrogen tank and identify those regions that are contaminated and will cause bond degradation.

  8. Analytic evaluation of LAMPF 2 Booster Cavity design

    NASA Astrophysics Data System (ADS)

    Friedrichs, C. C.

    Through the past few decades, a great deal of sophistication has evolved in the numeric codes used to evaluate electromagnetically resonant structures. The numeric methods are extremely precise, even for complicated geometries, whereas analytic methods require a simple uniform geometry and a simple, known mode configuration if the same precision is to be obtained. The code SUPERFISH, which is near the present state of the art of numeric methods, does have the following limitations: No circumferential geometry variations are permissible; there are no provisions for magnetic or dielectric losses; and finally, it is impractical (because of the complexity of the code) to modify it to extract particular bits of data one might want that are not provided by the code as written. SUPERFISH was used as an aid in derivating an analytic model of the Los Alamos Meson Physics Facility (LAMPF) II Booster Cavity. One a satisfactory model was derived, simple FORTRAN codes were generated to provide whatever data was required. The analytic model is made up of TEM and radial mode transmission line sections, as well as lumped elements where appropriate. Radial transmission line equations, which include losses, were not found in any literature, and the extension of the lossless equations to include magnetic and dielectric losses are included.

  9. Exploring the Solid Rocket Boosters and Properties of Matter

    NASA Technical Reports Server (NTRS)

    Moffett, Amy

    2007-01-01

    I worked for the United Space Alliance, LLC (USA) with the Solid Rocket Booster (SRB) Materials and Process engineers (M&P). I was assigned a project in which I needed to research and collect chemical and physical properties information, material safety data sheets (MSDS), and other product information from the vendor's websites and existing "inhouse" files for a select group of materials used in building and refurbishing the SRBs. This information was then compiled in a report that summarized the information collected. My work site was at the Kennedy Space Center (KSC). This allowed for many opportunities to visit and tour sites operated by NASA, by USA, and by the Air Force. This included the vehicle assembly building (VAB), orbital processing facilities (OPF), the crawler with the mobile launch pad (MLP), and the SRB assembly and refurbishment facility (ARF), to name a few. In addition, the launch, of STS- 117 took place within the first week of employment allowing a day by day following of that mission including post flight operations for the SRBs. Two Delta II rockets were also launched during these 7 weeks. The sights were incredible and the operations witnessed were amazing. I learned so many things I never knew about the entire program and the shuttle itself. The entire experience, especially my work with the SRB materials, inspired my plan for implementation into the classroom.

  10. Thrust augmentation nozzle (TAN) concept for rocket engine booster applications

    NASA Astrophysics Data System (ADS)

    Forde, Scott; Bulman, Mel; Neill, Todd

    2006-07-01

    Aerojet used the patented thrust augmented nozzle (TAN) concept to validate a unique means of increasing sea-level thrust in a liquid rocket booster engine. We have used knowledge gained from hypersonic Scramjet research to inject propellants into the supersonic region of the rocket engine nozzle to significantly increase sea-level thrust without significantly impacting specific impulse. The TAN concept overcomes conventional engine limitations by injecting propellants and combusting in an annular region in the divergent section of the nozzle. This injection of propellants at moderate pressures allows for obtaining high thrust at takeoff without overexpansion thrust losses. The main chamber is operated at a constant pressure while maintaining a constant head rise and flow rate of the main propellant pumps. Recent hot-fire tests have validated the design approach and thrust augmentation ratios. Calculations of nozzle performance and wall pressures were made using computational fluid dynamics analyses with and without thrust augmentation flow, resulting in good agreement between calculated and measured quantities including augmentation thrust. This paper describes the TAN concept, the test setup, test results, and calculation results.

  11. Five-Segment Booster (FSB) Abort to Orbit (ATO) Studies

    NASA Technical Reports Server (NTRS)

    Tobias, Mark; Sauvageau, Donald R.; Hines, Mark; Geiser, Norman L.; Cash, Steve (Technical Monitor)

    2002-01-01

    The Five Segment Booster (FSB) concept has been evolving for a number of years as a means to enhance the overall safety and reliability of the Space Shuttle system by minimizing the need to fly the more challenging Return to Launch Site (RTLS) and Transoceanic Abort Landing (TAL) abort profiles. The initial evaluation of the FSB concept was conducted in 1996 to determine the feasibility of the FSB in achieving transatlantic abort leading TAL from the pad, thus eliminating the return to launch site (RTLS) abort mode. The initial study was conducted by ATK Thiokol and did show the potential for the FSB to eliminate the RTLS abort mode. Later Rockwell (now Boeing) conducted a similar study utilizing FSB performance characteristics and verified that the FSB could indeed achieve TAL from the pad, thereby eliminating the necessity for the RTLS abort. The purpose of this paper is to discuss the details of the enhancements achieved through the internally funded study conducted by Boeing and ATK Thiokol. To better understand the enhancements that were addressed as part of this follow-on study, some background on what was achieved in the Phase A study is appropriate.

  12. Design Exploration of Aerodynamic Wing Shape for RLV Flyback Booster

    NASA Astrophysics Data System (ADS)

    Chiba, Kazuhisa; Obayashi, Shigeru; Nakahashi, Kazuhiro

    The wing shape of flyback booster for a Two-Stage-To-Orbit reusable launch vehicle has been optimized considering four objectives. The objectives are to minimize the shift of aerodynamic center between supersonic and transonic conditions, transonic pitching moment and transonic drag coefficient, as well as to maximize subsonic lift coefficient. The three-dimensional Reynolds-averaged Navier-Stokes computation using the modified Spalart-Allmaras one-equation model is used in aerodynamic evaluation accounting for possible flow separations. Adaptive range multi-objective genetic algorithm is used for the present study because tradeoff can be obtained using a smaller number of individuals than conventional multi-objective genetic algorithms. Consequently, four-objective optimization has produced 102 non-dominated solutions, which represent tradeoff information among four objective functions. Moreover, Self-Organizing Maps have been used to analyze the present non-dominated solutions and to visualize tradeoffs and influence of design variables to the four objectives. Self-Organizing Maps contoured by the four objective functions and design variables are found to visualize tradeoffs and effects of each design variable.

  13. Analytic evaluation of LAMPF II Booster Cavity design

    SciTech Connect

    Friedrichs, C.C.

    1985-01-01

    Through the past few decades, a great deal of sophistication has evolved in the numeric codes used to evaluate electromagnetically resonant structures. The numeric methods are extremely precise, even for complicated geometries, whereas analytic methods require a simple uniform geometry and a simple, known mode configuration if the same precision is to be obtained. The code SUPERFISH, which is near the present state-of-the-art of numeric methods, does have the following limitations: No circumferential geometry variations are permissible; there are no provisions for magnetic or dielectric losses; and finally, it is impractical (because of the complexity of the code) to modify it to extract particular bits of data one might want that are not provided by the code as written. This paper describes how SUPERFISH was used as an aid in derivating an analytic model of the LAMPF II Booster Cavity. Once a satisfactory model was derived, simple FORTRAN codes were generated to provide whatever data was required. The analytic model is made up of TEM- and radial-mode transmission-line sections, as well as lumped elements where appropriate. Radial transmission-line equations, which include losses, were not found in any literature, and the extension of the lossless equations to include magnetic and dielectric losses are included in this paper.

  14. Hybrid propulsion for launch vehicle boosters: A program status update

    NASA Technical Reports Server (NTRS)

    Carpenter, R. L.; Boardman, T. A.; Claflin, S. E.; Harwell, R. J.

    1995-01-01

    Results obtained in studying the origin and suppression of large-amplitude pressure oscillations in a 24 in. diameter hybrid motor using a liquid oxygen/hydroxylterminated polybutadiene/polycyclopentadiene propellant system are discussed. Tests conducted with liquid oxygen flow rates varying from 10 to 40 lbm/sec were designed to gauge the effectiveness of various vaporization chamber flow fields, injector designs, and levels of heat addition in suppressing high-frequency longitudinal mode oscillations. Longitudinal acoustic modes did not arise in any tests. However, initial testing revealed the presence of high-amplitude, sinusoidal, nonacoustic oscillations persisting throughout the burn durations. Analysis showed this to be analogous to chug mode instability in liquid rocket engines brought about by a coupling of motor combustion processes and the liquid oxygen feed system. Analytical models were developed and verified by test data to predict the amplitude and frequency of feed-system-coupled combustion pressure oscillations. Subsequent testing showed that increasing the feed system impedance eliminated the bulk mode instability. This paper documents the work completed to date in performance of the Hybrid Propulsion Technology for Launch Vehicle Boosters Program (NAS8-39942) sponsored by NASA's George C. Marshall Space Flight Center.

  15. Slip-stacking Dynamics and the 20 Hz Booster

    SciTech Connect

    Eldred, Jeffery; Zwaska, Robert

    2015-03-01

    Slip-stacking is an accumulation technique used at Fermilab since 2004 which nearly doubles the proton intensity. The Proton Improvement Plan II intensity upgrades require a reduction in slip-stacking losses by approximately a factor of 2. We study the single-particle dynamics that determine the stability of slip-stacking particles. We introduce universal area factors to calculate the available phase space area for any set of beam parameters without individual simulation. We show the particle loss as a function of time. We calculate the injection efficiency as a function of longitudinal emittance and aspect-ratio. We demonstrate that the losses from RF single particle dynamics can be reduced by a factor of 4-10 (depending on beam parameters) by upgrading the Fermilab Booster from a 15-Hz cycle-rate to a 20-Hz cycle-rate. We recommend a change in injection scheme to eliminate the need for a greater momentum aperture in the Fermilab Recycler.

  16. Solid Rocket Booster Hydraulic Pump Port Cap Joint Load Testing

    NASA Technical Reports Server (NTRS)

    Gamwell, W. R.; Murphy, N. C.

    2004-01-01

    The solid rocket booster uses hydraulic pumps fabricated from cast C355 aluminum alloy, with 17-4 PH stainless steel pump port caps. Corrosion-resistant steel, MS51830 CA204L self-locking screw thread inserts are installed into C355 pump housings, with A286 stainless steel fasteners installed into the insert to secure the pump port cap to the housing. In the past, pump port cap fasteners were installed to a torque of 33 Nm (300 in-lb). However, the structural analyses used a significantly higher nut factor than indicated during tests conducted by Boeing Space Systems. When the torque values were reassessed using Boeing's nut factor, the fastener preload had a factor of safety of less than 1, with potential for overloading the joint. This paper describes how behavior was determined for a preloaded joint with a steel bolt threaded into steel inserts in aluminum parts. Finite element models were compared with test results. For all initial bolt preloads, bolt loads increased as external applied loads increased. For higher initial bolt preloads, less load was transferred into the bolt, due to external applied loading. Lower torque limits were established for pump port cap fasteners and additional limits were placed on insert axial deformation under operating conditions after seating the insert with an initial preload.

  17. "White Box" Epidemiology and the Social Neuroscience of Health Behaviors: The Environmental Affordances Model.

    PubMed

    Mezuk, Briana; Abdou, Cleopatra M; Hudson, Darrell; Kershaw, Kiarri N; Rafferty, Jane A; Lee, Hedwig; Jackson, James S

    2013-07-01

    Crucial advances have been made in our knowledge of the social determinants of health and health behaviors. Existing research on health disparities, however, generally fails to address a known paradox in the literature: While blacks have higher risk of medical morbidity relative to non-Hispanic whites, blacks have lower rates of common stress-related forms of psychopathology such as major depression and anxiety disorders. In this article we propose a new theoretical approach, the Environmental Affordances Model, as an integrative framework for the origins of both physical and mental health disparities. We highlight early empirical support and a growing body of experimental animal and human research on self-regulatory health behaviors and stress coping that is consistent with the proposed framework. We conclude that transdisciplinary approaches, such as the Environmental Affordances Model, are needed to understand the origins of group-based disparities to implement effective solutions to racial and ethnic group inequalities in physical and mental health. PMID:24224131

  18. “White Box” Epidemiology and the Social Neuroscience of Health Behaviors: The Environmental Affordances Model

    PubMed Central

    Mezuk, Briana; Abdou, Cleopatra M.; Hudson, Darrell; Kershaw, Kiarri N.; Rafferty, Jane A.; Lee, Hedwig; Jackson, James S.

    2013-01-01

    Crucial advances have been made in our knowledge of the social determinants of health and health behaviors. Existing research on health disparities, however, generally fails to address a known paradox in the literature: While blacks have higher risk of medical morbidity relative to non-Hispanic whites, blacks have lower rates of common stress-related forms of psychopathology such as major depression and anxiety disorders. In this article we propose a new theoretical approach, the Environmental Affordances Model, as an integrative framework for the origins of both physical and mental health disparities. We highlight early empirical support and a growing body of experimental animal and human research on self-regulatory health behaviors and stress coping that is consistent with the proposed framework. We conclude that transdisciplinary approaches, such as the Environmental Affordances Model, are needed to understand the origins of group-based disparities to implement effective solutions to racial and ethnic group inequalities in physical and mental health. PMID:24224131

  19. Motivation for aggressive religious radicalization: goal regulation theory and a personality × threat × affordance hypothesis.

    PubMed

    McGregor, Ian; Hayes, Joseph; Prentice, Mike

    2015-01-01

    A new set of hypotheses is presented regarding the cause of aggressive religious radicalization (ARR). It is grounded in classic and contemporary theory of human motivation and goal regulation, together with recent empirical advances in personality, social, and neurophysiological psychology. We specify personality traits, threats, and group affordances that combine to divert normal motivational processes toward ARR. Conducive personality traits are oppositional, anxiety-prone, and identity-weak (i.e., morally bewildered). Conducive threats are those that arise from seemingly insurmountable external forces and frustrate effective goal regulation. Conducive affordances include opportunity for immediate and concrete engagement in active groups that are powered by conspiracy narratives, infused with cosmic significance, encouraging of moral violence, and sealed with religious unfalsifiability. We propose that ARR is rewarding because it can spur approach motivated states that mask vulnerability for people whose dispositions and circumstances would otherwise leave them mired in anxious distress. PMID:26441709

  20. Motivation for aggressive religious radicalization: goal regulation theory and a personality × threat × affordance hypothesis

    PubMed Central

    McGregor, Ian; Hayes, Joseph; Prentice, Mike

    2015-01-01

    A new set of hypotheses is presented regarding the cause of aggressive religious radicalization (ARR). It is grounded in classic and contemporary theory of human motivation and goal regulation, together with recent empirical advances in personality, social, and neurophysiological psychology. We specify personality traits, threats, and group affordances that combine to divert normal motivational processes toward ARR. Conducive personality traits are oppositional, anxiety-prone, and identity-weak (i.e., morally bewildered). Conducive threats are those that arise from seemingly insurmountable external forces and frustrate effective goal regulation. Conducive affordances include opportunity for immediate and concrete engagement in active groups that are powered by conspiracy narratives, infused with cosmic significance, encouraging of moral violence, and sealed with religious unfalsifiability. We propose that ARR is rewarding because it can spur approach motivated states that mask vulnerability for people whose dispositions and circumstances would otherwise leave them mired in anxious distress. PMID:26441709

  1. Polyimide Based Nanocomposites for Affordable Space Transport

    NASA Technical Reports Server (NTRS)

    Dean, Derrick; Islam, Mohsina; Small, Sharee; Aldridge, Brandon; Campbell, Sandra G. (Technical Monitor)

    2001-01-01

    In setting forth its strategic plan, NASA has indicated that low-cost access to space is the key to unleashing the commercial potential of space and greatly expanding space research and exploration. The development of advanced materials will be an enabling technology for this quest for low-cost space access. In this research program, we are attempting to address the need for new advanced materials by developing high-performance nanodispersed inorganic/organic and organic/organic polyimide composites utilizing specific interactions. Our goal is to systematically manipulate these interactions and investigate the resulting processing morphology-property relationships. Specifically, we will investigate three main parameters on these relationships. These include (1) the type of polyimide; (2) the structure of the inorganic nanoparticle being used; and (3) manipulation of the interfacial energy. During the first year of this effort, we have demonstrated the successful synthesis of PMR-15/layered silicate nanocomposites. Morphological studies indicate that exfoliated structures were obtained in most instances, with a mixture of exfoliated and intercalated structures being observed also. Significant enhancements of the onset of decomposition were obtained by varying the strength of the interaction between the nanoparticle and the polymer. Varying the amount of a specific nanoparticle also affected the decomposition temperatures. A slight catalytic effect of the nanoparticles on both the imidization and crosslinking reaction has been observed and will be presented. In addition, incorporation of the nanoparticles was found to increase the glass transition temperature and slightly broaden the breadth of this relaxation.

  2. Effects of vehicle seat and belt geometry on belt fit for children with and without belt positioning booster seats.

    PubMed

    Reed, Matthew P; Ebert-Hamilton, Sheila M; Klinich, Kathleen D; Manary, Miriam A; Rupp, Jonathan D

    2013-01-01

    A laboratory study was conducted to quantify the effects of belt-positioning boosters on lap and shoulder belt fit. Postures and belt fit were measured for forty-four boys and girls ages 5-12 in four highback boosters, one backless booster, and on a vehicle seat without a booster. Belt anchorage locations were varied over a wide range. Seat cushion angle, seat back angle, and seat cushion length were varied in the no-booster conditions. All boosters produced better mean lap belt fit than was observed in the no-booster condition, but the differences among boosters were relatively large. With one midrange belt configuration, the lap belt was not fully below the anterior-superior iliac spine (ASIS) landmark on the front of the pelvis for 89% of children in one booster, and 75% of children failed to achieve that level of belt fit in another. In contrast, the lap belt was fully below the ASIS for all but two children in the best-performing booster. Child body size had a statistically significant but relatively small effect on lap belt fit. The largest children sitting without a booster had approximately the same lap belt fit as the smallest children experienced in the worst-performing booster. Increasing lap belt angle relative to horizontal produced significantly better lap belt fit in the no-booster condition, but the boosters isolated the children from the effects of lap belt angles. Reducing seat cushion length in the no-booster condition improved lap belt fit but changing cushion angle did not. Belt upper anchorage (D-ring) location had a strong effect on shoulder belt fit in conditions without shoulder belt routing from the booster. Unexpectedly, the worst average shoulder belt fit was observed in one highback booster with a poorly positioned shoulder belt routing clip. The shoulder belt was routed more outboard, on average, with a backless booster than without a booster, but raising the child also amplified the effect of D-ring location, such that children were

  3. Setting a standard of affordability for health insurance coverage.

    PubMed

    Blumberg, Linda J; Holahan, John; Hadley, Jack; Nordahl, Katharine

    2007-01-01

    Recently, Massachusetts passed landmark legislation designed to expand health insurance coverage. This legislation includes a requirement that all adults enroll in a health insurance plan. This mandate takes effect only if an "affordable" plan is available. The definition of affordability for individuals and families of different incomes or circumstances is a critical decision in implementation and is relevant to any state or federal reform requiring individual premium or cost-sharing contributions, or both. This analysis was done to assist the policy design process in Massachusetts and delineates an empirically based approach to setting affordability standards. PMID:17548341

  4. Liquid Rocket Booster (LRB) for the Space Transportion System (STS) systems study. Appendix D: Trade study summary for the liquid rocket booster

    NASA Technical Reports Server (NTRS)

    1989-01-01

    Trade studies plans for a number of elements in the Liquid Rocket Booster (LRB) component of the Space Transportation System (STS) are given in viewgraph form. Some of the elements covered include: avionics/flight control; avionics architecture; thrust vector control studies; engine control electronics; liquid rocket propellants; propellant pressurization systems; recoverable spacecraft; cryogenic tanks; and spacecraft construction materials.

  5. Expendable second stage reusable space shuttle booster. Volume 2: Technical summary. Book 1: Expendable second stage/reusable booster system definition

    NASA Technical Reports Server (NTRS)

    1971-01-01

    A systems analysis of the expendable second stage/reusable booster system is presented. The subjects discussed are: (1) mission/system requirements, (2) spacecraft performance, (3) trajectories, (4) aerodynamics, (5) stability and control, (6) loads, (7) heating, and (8) acoustic environment.

  6. Space Transportation Booster Engine Configuration Study. Volume 3: Program Cost estimates and work breakdown structure and WBS dictionary

    NASA Technical Reports Server (NTRS)

    1989-01-01

    The objective of the Space Transportation Booster Engine Configuration Study is to contribute to the ALS development effort by providing highly reliable, low cost booster engine concepts for both expendable and reusable rocket engines. The objectives of the Space Transportation Booster Engine (STBE) Configuration Study were: (1) to identify engine development configurations which enhance vehicle performance and provide operational flexibility at low cost; and (2) to explore innovative approaches to the follow-on Full-Scale Development (FSD) phase for the STBE.

  7. Issaquah Highlands Zero Energy Affordable Housing (WA) - YWCA

    SciTech Connect

    Tom, Vincent; DeRobbio, Wendy; Hall, Linda

    2012-04-30

    The YWCA Family Village at Issaquah, Net Zero Energy Approach Project provides a compelling model for how the nation can seriously respond to the critical need for affordable housing while advancing environmental standards and reducing economic inequities. Affordable housing developments for vulnerable members of the community and in today's workforce cannot overlook issues, such as climate impact, energy security and water conservation. This project's advanced building design was based on the goal of creating a 100 year building that could achieve net zero energy usage if funding had been available to support the final pieces of energy generation. The team worked closely with community stakeholders to ensure the baseline components of high quality and efficient building envelopes along with efficient systems were in place to set the stage for future incorporation of energy generating systems such as solar panels. As built, these 146 homes, large child care center and community services areas are proving the value of investing upfront for the benefit of future generations by reducing ongoing utility and maintenance costs with an eye toward environmental stewardship and community/resident education. The DOE award helped fund two critical energy conservation features for the YWCA Family Village at Issaquah campus: 1) super-insulated roof assembly with a continuous air barrier and 2) domestic hot water preheat system. The roof system at the YWCA Family Village at Issaquah project was built to include 6" of Polyiso rigid insulation (R-38) on top of the roof sheathing to provide a super-insulated roof in line with the other green features of the project. Placing the rigid insulation on top of the roof sheathing allows the building to have a continuous layer of insulation and provides a continuous air barrier. The domestic hot water preheat system includes flat panel arrays on roofs of the buildings that heat the water using solar power, which reduces the amount of

  8. Energy Servers Deliver Clean, Affordable Power

    NASA Technical Reports Server (NTRS)

    2010-01-01

    K.R. Sridhar developed a fuel cell device for Ames Research Center, that could use solar power to split water into oxygen for breathing and hydrogen for fuel on Mars. Sridhar saw the potential of the technology, when reversed, to create clean energy on Earth. He founded Bloom Energy, of Sunnyvale, California, to advance the technology. Today, the Bloom Energy Server is providing cost-effective, environmentally friendly energy to a host of companies such as eBay, Google, and The Coca-Cola Company. Bloom's NASA-derived Energy Servers generate energy that is about 67-percent cleaner than a typical coal-fired power plant when using fossil fuels and 100-percent cleaner with renewable fuels.

  9. Can consumers make affordable care affordable? The value of choice architecture.

    PubMed

    Johnson, Eric J; Hassin, Ran; Baker, Tom; Bajger, Allison T; Treuer, Galen

    2013-01-01

    Tens of millions of people are currently choosing health coverage on a state or federal health insurance exchange as part of the Patient Protection and Affordable Care Act. We examine how well people make these choices, how well they think they do, and what can be done to improve these choices. We conducted 6 experiments asking people to choose the most cost-effective policy using websites modeled on current exchanges. Our results suggest there is significant room for improvement. Without interventions, respondents perform at near chance levels and show a significant bias, overweighting out-of-pocket expenses and deductibles. Financial incentives do not improve performance, and decision-makers do not realize that they are performing poorly. However, performance can be improved quite markedly by providing calculation aids, and by choosing a "smart" default. Implementing these psychologically based principles could save purchasers of policies and taxpayers approximately 10 billion dollars every year. PMID:24367484

  10. Can Consumers Make Affordable Care Affordable? The Value of Choice Architecture

    PubMed Central

    Johnson, Eric J.; Hassin, Ran; Baker, Tom; Bajger, Allison T.; Treuer, Galen

    2013-01-01

    Tens of millions of people are currently choosing health coverage on a state or federal health insurance exchange as part of the Patient Protection and Affordable Care Act. We examine how well people make these choices, how well they think they do, and what can be done to improve these choices. We conducted 6 experiments asking people to choose the most cost-effective policy using websites modeled on current exchanges. Our results suggest there is significant room for improvement. Without interventions, respondents perform at near chance levels and show a significant bias, overweighting out-of-pocket expenses and deductibles. Financial incentives do not improve performance, and decision-makers do not realize that they are performing poorly. However, performance can be improved quite markedly by providing calculation aids, and by choosing a “smart” default. Implementing these psychologically based principles could save purchasers of policies and taxpayers approximately 10 billion dollars every year. PMID:24367484

  11. Lessons Learned for Follow-up Phone Booster Counseling Calls with Substance Abusing Emergency Department Patients

    PubMed Central

    Donovan, Dennis M.; Hatch-Maillette, Mary A.; Phares, Melissa M.; McGarry, Ernest; Peavy, K. Michelle; Taborsky, Julie

    2014-01-01

    Background Post-visit “booster” sessions have been recommended to augment the impact of brief interventions delivered in the Emergency Department (ED). This paper, which focuses on implementation issues, presents descriptive information and interventionists’ qualitative perspectives on providing brief interventions over the phone, challenges, “lessons learned”, and recommendations for others attempting to implement adjunctive booster calls. Method Attempts were made to complete two 20-minute telephone “booster” calls within a week following a patient’s ED discharge with 425 patients who screened positive for and had recent problematic substance use other than alcohol or nicotine. Results Over half (56.2%) of participants completed the initial call; 66.9% of those who received the initial call also completed the second call. Median number of attempts to successfully contact participants for the first and second calls was 4 and 3, respectively. Each completed call lasted an average of about 22 minutes. Common challenges/barriers identified by booster callers included unstable housing, limited phone access, unavailability due to additional treatment, lack of compensation for booster calls, and booster calls coming from an area code different than the participants’ locale and from someone other than ED staff. Conclusions Specific recommendations are presented with respect to implementing a successful centralized adjunctive booster call system. Future use of booster calls might be informed by research on contingency management (e.g., incentivizing call completions), smoking cessation quitlines, and phone-based continuing care for substance abuse patients. Future research needs to evaluate the incremental benefit of adjunctive booster calls on outcomes over and above that of brief motivational interventions delivered in the ED setting. PMID:25534151

  12. Antibody response after a four-site intradermal booster vaccination with cell-culture rabies vaccine.

    PubMed

    Tantawichien, T; Benjavongkulchai, M; Limsuwan, K; Khawplod, P; Kaewchompoo, W; Chomchey, P; Sitprija, V

    1999-05-01

    The current World Health Organization recommendation for booster vaccination of previously immunized individuals with potential exposure to rabies is two doses of vaccine intramuscularly or intradermally on days 0 and 3. We report responses to two types of postexposure treatment of healthy individuals who had received preexposure rabies vaccination 1 year previously. Group A individuals received four intradermal doses (one-fifth of the diluent volume of vaccine per dose) on day 0, and group B individuals received two intramuscular doses on days 0 and 3. Immunogenicity of the two booster regimens was assessed by titrating the amount of neutralizing antibody (Nab). We found that the booster doses of vaccine produced remarkable responses in all subjects. Nab titers of > or = 0.5 IU/mL (acceptable antibody level for protection against rabies) were detected in all subjects on day 14, and they were shown to be consistently high 1 year after the booster vaccination. We also found that the Nab titers for group A were significantly higher (two- to eightfold) than those for group B on days 5, 14, 150, and 360 after the initial booster vaccination (P < .05). Our study shows that the four-site intradermal booster regimen with use of one-fifth of the diluent volume of cell-culture rabies vaccine on day 0 is associated with a significantly higher antibody response than is the conventional booster regimen for subsequent postexposure rabies treatment of individuals who have received preexposure rabies vaccination with cell-culture rabies vaccine 1 year previously. PMID:10452642

  13. Development of the beam extraction synchronization system at the Fermilab Booster

    NASA Astrophysics Data System (ADS)

    Seiya, K.; Chaurize, S.; Drennan, C. C.; Pellico, W.; Sullivan, T.; Triplett, A. K.; Waller, A. M.

    2015-11-01

    The new beam extraction synchronization control system called "Magnetic Cogging" was developed at the Fermilab Booster and it replaces a system called "RF Cogging" as part of the Proton Improvement Plan (PIP).[1] The flux throughput goal for the PIP is 2.2×1017 protons per hour, which is double the present flux. The flux increase will be accomplished by doubling the number of beam cycles which, in turn, will double the beam loss in the Booster accelerator if nothing else is done. The Booster accelerates beam from 400 MeV to 8 GeV and extracts it to the Main Injector (MI) or Recycler Ring (RR). Cogging controls the beam extraction gap position which is created early in the Booster cycle and synchronizes the gap to the rising edge of the Booster extraction kicker and the MI/RR injection kicker. The RF Cogging system controls the gap position by changing only the radial position of the beam thus limiting the beam aperture and creating beam loss due to beam scraping. The Magnetic Cogging system controls the gap position with the magnetic field of the dipole correctors while the radial position feedback keeps the beam on a central orbit. Also with Magnetic Cogging the gap creation can occur earlier in the Booster cycle when the removed particles are at a lower energy. Thus Magnetic Cogging reduces the deposited energy of the lost particles (beam energy loss) and results in less beam loss activation. Energy loss was reduced by 40% by moving the gap creation energy from 700 MeV to 400 MeV when the Booster Cogging system was switched from RF Cogging to Magnetic Cogging in March 2015.

  14. Scientific experimentation afforded by the International Asteroid Mission

    NASA Astrophysics Data System (ADS)

    The International Asteroid Mission (IAM) affords scientists the opportunity to perform interesting and important experimentations. This opportunity is not sufficient in its own right to mandate inclusion of science into the mission. Certain scientific experimentations are essential to the success of the mission, and are the driving force behind the inclusion of science. Instrument designs incorporate the need for direct contribution to the success of the mining mission. Examples of these applications include the search for additional candidate asteroids, especially at the Earth-Sun Trojan points, with an infrared telescope facility; a gamma ray burst detector provides the crew with real-time notification of potentially harmful solar-flare activity; and a materials processing laboratory provides information on the porosity, composition, and crystalline structure of samples to optimize the mining operations in addition to yielding great insight into the history and formation of the solar-system. Instrument designs have emphasized the use of off-the-shelf hardware, demonstrated technologies. Their scientific value is derived from the location on an interplanetary platform, not necessarily advancements in technology or detection methods. Instrumentation will be delivered to the IAM project after completion of a thorough certification program. The program will include qualification, acceptance, performance, thermal balance, thermal vacuum, vibration, electromagnetic susceptibility and compatibility, and calibration testing. After delivery to the assembly-site in low-Earth orbit, an additional series of functional and compatibility tests will be required prior to initiation of the mission. The scientific instrumentation proposed for the IAM consists of experiments using a Gamma Ray Burst Detector, a Infrared Observatory, a Materials Processing Facility, Long-Wavelength Radar, Seismic Measurement Devices, Cosmic Ray Detectors, Interplanetary Plasma Measurements, a Solar

  15. Performance evaluation of booster materials in the plastic bonded explosive PBX 9502 in a hemispherical wave breakout test

    SciTech Connect

    Hooks, Daniel E; Morris, John S; Hill, Larry G; Francois, Elizabeth

    2008-01-01

    An explosive booster is normally required to initiate detonation in an insensitive high explosive (lHE). Booster materials must be ignitable by a conventional detonator and deliver sufficient energy and favorable pulse shape to initiate the IHE charge. The explosive booster should be as insensitive as reasonably possible to maintain the overall safety margin of the explosive assembly. A hemispherical wave breakout test termed the on ionskin test is one of the methods of testing the performance of booster materials in an initiation train assembly. There are several variations of this basic test which are known by other names. In this test, the wave breakout time-position history at the surface of a hemispherical IHE acceptor charge is recorded, and the relative uniformity of breakout allows qualitative comparison between booster candidates and quantitative comparison of several metrics. The results of a series of onionskin experiments evaluating the performance of some new booster formulations in the triaminotrinitrobenzene (TA TB) -based plastic bonded explosive PBX 9502 will be presented. The boosters were tested in an onionskin arrangement in which the booster pellet was cylindrical, and the tests were performed at a temperature of-55{sup o}C to emphasize variations in spreading performance. The modification from the traditional hemispherical geometry facilitated efficient explosive fabrication and charge assembly, but the results indicate that this geometry was not ideal for several reasons. Despite the complications arising from geometry, promising performance was observed from booster formulations including 3,3' -diamino-4,4'azoxyfurazan.

  16. NASA's Space Launch System Takes Shape: Progress Toward Safe, Affordable, Exploration

    NASA Technical Reports Server (NTRS)

    Askins, Bruce R.; Robinson, Kimberly F.

    2014-01-01

    Development of NASA's Space Launch System (SLS) exploration-class heavy lift rocket has moved from the formulation phase to implementation in 3 years and will make significant progress this year toward its first launch, slated December 2017. SLS represents a safe, affordable, and evolutionary path to development of an unprecedented capability for future human and robotic exploration and use of space. For the United States current development is focused on a configuration with a 70 metric ton (t) payload to low Earth orbit (LEO), more than double any operational vehicle. This version will launch NASA's Orion Multi-Purpose Crew Vehicle (MPCV) on its first autonomous flight beyond the Moon and back, as well as the first crewed Orion flight. SLS is designed to evolve to a 130 t lift capability that can reduce mission costs, simplify payload design, reduce trip times, and lower overall risk. Each vehicle element completed its respective Preliminary Design Reviews, followed by the SLS Program. The Program also completed the Key Decision Point-C milestone to move from formulation to implementation in 2014. NASA hasthorized the program to proceed to Critical Design Review, scheduled for 2015. Accomplihments to date include: manufacture of core stage test hardware, as well as preparations for testing the world's most powerful solid rocket boosters and main engines that flew 135 successful Space Shuttle missions. The Program's success to date is due to prudent use of existing technology, infrastructure, and workforce; streamlined management approach; and judicious use of new technologies. This paper will discuss SLS Program successes over the past year and examine milestones and challenges ahead. The SLS Program and its elements are managed at NASA's Marshall Space Flight Center (MSFC).

  17. NASA's Space Launch System Takes Shape: Progress Toward Safe, Affordable Exploration

    NASA Technical Reports Server (NTRS)

    Askins, Bruce

    2014-01-01

    Development of NASA's Space Launch System exploration-class heavy lift rocket has moved from the formulation phase to implementation in 3 years and will make significant progress this year toward its first launch, slated for December 2017. In recognition of the current fiscal realities, SLS represents a safe, affordable, and evolutionary path to development of an unprecedented capability for future human and robotic exploration and use of space. Current development is focused on a configuration with a 70 metric ton (t) payload to low Earth orbit (LEO), more than double any operational vehicle. It is this version that will launch NASA's Orion Multi-Purpose Crew Vehicle (MPCV) on its first autonomous flight beyond the Moon and back, as well as the first crewed Orion flight. This configuration is also designed to evolve to 130 t lift capability that offers several benefits, such as reduced mission costs, simplified payload design, faster trip times, and lower overall risk for missions of national significance. The SLS Program formally transitioned from the formulation phase to implementation during the past year, passing its Preliminary Design Review in 2013 and completion of Key Decision Point C in early 2014. NASA has authorized the Program to move forward to Critical Design Review, scheduled for 2015. Among the Program's many accomplishments are manufacture of core stage test hardware, as well as preparations for testing the world's most powerful solid rocket boosters and the main engines that flew 135 successful Space Shuttle missions. The Program's success to date is due to prudent use of existing technology, infrastructure, and workforce; streamlined management approach; and judicious use of new technologies. The result is a launch vehicle that will carry human and robotic exploration on the history-making missions in the coming decades. This paper will discuss the program and technical successes over the past year and provide a look at the milestones and

  18. Object Affordances Potentiate Responses but Do Not Guide Attentional Prioritization

    PubMed Central

    Yamani, Yusuke; Ariga, Atsunori; Yamada, Yuki

    2016-01-01

    Handled objects automatically activate afforded responses. The current experiment examined whether objects that afford a response are also prioritized for attentional processing in visual search. Targets were pictures of coffee cups with handles oriented either to the right or the left. Subjects searched for a target, a right-handled vs. left-handled coffee cup, among a varying number of distractor cups oriented in the opposite direction. Responses were faster when the direction of target handle and the key press were spatially matched than mismatched (stimulus-response compatibility (SRC) effect), but object affordance did not moderate slopes of the search functions, indicating the absence of attentional prioritization effect. These findings imply that handled objects prime afforded responses without influencing attentional prioritization. PMID:26793077

  19. Development of Basic Housing Systems for Maximum Affordability

    SciTech Connect

    Aglan, H.; Gibbons, A.; McQueen, T.M.; Morris, C.; Raines, J.; Wendt, R.L.

    1999-04-19

    The ability to provide safe, habitable, comfortable housing for very low income residents within the target budget of $10,000 presents unique design and construction challenges. However, a number of preliminary conclusions have been inferred as being important concepts relative to the study of affordable housing. The term affordable housing can have many meanings and research is needed to define this explicitly. As it is most often used, affordable housing refers to an economic relationship between the price of housing, household income and current interest rates available from a lending institution. There is no direct relationship between architectural style, construction technology or user needs and the concept of affordability. For any home to be affordable, the home owner must balance the combination of housing needs and desires within the limits of an actual budget. There are many misconceptions that affordable housing must be defined as housing for those who cannot afford the free-market price. The concept of affordable housing must also include a component that recognizes the quality of the housing as an important element of the design and construction. In addition, responses to local climate impacts are necessary and are always part of a regional expression of architectural design. By using careful planning and design it may be possible to construct a limited dwelling unit today for a sum of approximately $10,000. Since the organization of the construction process must involve the owner/occupants as well as other volunteers, the project must not only be well conceived, but well developed and coordinated.

  20. Affordable Exploration of Mars: Recommendations from a Community Workshop

    NASA Technical Reports Server (NTRS)

    Thronson, Harley A.; Carberry, Chris; Cassady, R. Joseph; Cooke, Doug; Kirkpatrick, Jim; Perino, Maria Antonietta; Raftery, Michael; Westenberg, Artemis; Zucker, Richard

    2014-01-01

    There is a growing opinion that within two decades initial human missions to Mars are affordable under plausible budget scenarios, with sustained international participation, and --- especially --- without requiring those first missions to achieve a burdensome number of goals. In response to this view, a group of experts from the Mars exploration stakeholder communities attended the "Affording Mars" workshop at George Washington University in December 2013. Participants reviewed scenarios for proposed affordable and sustainable human and robotic exploration of Mars, the role of the International Space Station as the essential early step toward humans to Mars, possible "bridge" or "transition" missions in the 2020s, key capabilities required for affordable initial missions, international partnerships, and usable definitions of affordability and sustainability. We report here the findings, observations, and recommendations that were agreed to at that workshop. In the context of affordable early missions to Mars, we also discuss the recent report of the National Research Council on human space flight and a pair of recent scenarios that appear to promise reduced costs.

  1. Affordability of alcohol and alcohol-related mortality in Belarus.

    PubMed

    Razvodovsky, Yury E

    2013-01-01

    Alcohol abuse has numerous adverse health and social consequences. The consumer response to changes in alcohol affordability is an important issue on alcohol policy debates. Studies from many countries have shown an inverse relationship between alcohol prices and alcohol consumption in the population. There are, however, suggestions that increasing the price of alcohol by rising taxes may have limited effect on alcohol-related problems, associated with long-term heavy drinking. The aim of the present study was to evaluate the relationship between alcohol affordability and alcohol-related mortality rates in post-Soviet Belarus. For this purpose trends in alcohol-related mortality rates (mortality from liver cirrhosis, pancreatitis, alcoholism and alcohol psychoses) and affordability of vodka between 1990 and 2010 were compared. The time series analysis revealed that 1% increase in vodka affordability is associated with an increase in liver cirrhosis mortality of 0,77%, an increase in pancreatitis mortality of 0.53%, an increase in mortality from alcoholism and alcohol psychoses of 0,70%. The major conclusion emerging from this study is that affordability of alcohol is one of the most important predictor of alcohol-related problems in a population. These findings provide additional evidence that decreasing in affordability of alcohol is an effective strategy for reducing alcohol consumption and alcohol-related harm. PMID:23748944

  2. Stable and variable affordances are both automatic and flexible

    PubMed Central

    Borghi, Anna M.; Riggio, Lucia

    2015-01-01

    The mere observation of pictures or words referring to manipulable objects is sufficient to evoke their affordances since objects and their nouns elicit components of appropriate motor programs associated with object interaction. While nobody doubts that objects actually evoke motor information, the degree of automaticity of this activation has been recently disputed. Recent evidence has indeed revealed that affordances activation is flexibly modulated by the task and by the physical and social context. It is therefore crucial to understand whether these results challenge previous evidence showing that motor information is activated independently from the task. The context and the task can indeed act as an early or late filter. We will review recent data consistent with the notion that objects automatically elicit multiple affordances and that top-down processes select among them probably inhibiting motor information that is not consistent with behavior goals. We will therefore argue that automaticity and flexibility of affordances are not in conflict. We will also discuss how language can incorporate affordances showing similarities, but also differences, between the motor information elicited by vision and language. Finally we will show how the distinction between stable and variable affordances can accommodate all these effects. PMID:26150778

  3. Hybrid booster strap-ons for the next generation launch system

    NASA Astrophysics Data System (ADS)

    Flittie, K. J.; McKinney, B.

    1993-06-01

    Currently, national planners are involved with the analysis and design of the Next Generation Launch Vehicle. During the latest studies of the proposed Spacelifter launch vehicle, a core vehicle was proposed that would utilize strap-on boosters to provide a wide range of payload capability into low Earth orbit. In such a scenario, a hybrid rocket motor provides a premier design option for the strap-on booster due to the hybrid's inherent safety, operational flexibility and low-cost. This paper describes the features of the hybrid motor that make it the choice for the next generation space boosters. Strap-on booster designs are presented that meet the mission goals of 20,000 to 50,000 pounds to low Earth orbit. A development plan is presented that provides a flight demonstration of a high-thrust large scale hybrid and allows scaling from the present state-of-the-art 250,000 pound thrust boosters to those needed for the next generation systems. A program schedule and rough order of magnitude cost data are presented.

  4. Inviscid and Viscous CFD Analysis of Booster Separation for the Space Launch System Vehicle

    NASA Technical Reports Server (NTRS)

    Dalle, Derek J.; Rogers, Stuart E.; Chan, William M.; Lee, Henry C.

    2016-01-01

    This paper presents details of Computational Fluid Dynamic (CFD) simulations of the Space Launch System during solid-rocket booster separation using the Cart3D inviscid and Overflow viscous CFD codes. The discussion addresses the use of multiple data sources of computational aerodynamics, experimental aerodynamics, and trajectory simulations for this critical phase of flight. Comparisons are shown between Cart3D simulations and a wind tunnel test performed at NASA Langley Research Center's Unitary Plan Wind Tunnel, and further comparisons are shown between Cart3D and viscous Overflow solutions for the flight vehicle. The Space Launch System (SLS) is a new exploration-class launch vehicle currently in development that includes two Solid Rocket Boosters (SRBs) modified from Space Shuttle hardware. These SRBs must separate from the SLS core during a phase of flight where aerodynamic loads are nontrivial. The main challenges for creating a separation aerodynamic database are the large number of independent variables (including orientation of the core, relative position and orientation of the boosters, and rocket thrust levels) and the complex flow caused by exhaust plumes of the booster separation motors (BSMs), which are small rockets designed to push the boosters away from the core by firing partially in the direction opposite to the motion of the vehicle.

  5. Challenges and opportunities for promoting booster seat use: progressive dissemination of a high-threat message.

    PubMed

    Will, Kelli England; Dunaway, Krystall E; Kokorelis, Diane A; Sabo, Cynthia Shier; Lorek, Edward J

    2012-11-01

    Motivating parents to take certain safety precautions when traveling with their children remains challenging for advocates. Caregivers of booster-aged children are particularly difficult to reach because they do not consider their children to be of "safety-seat" age and have inherently low perceptions of vulnerability to crash injury. Unfortunately, most booster seat programs fail to adequately motivate their intended population because they are primarily informational in nature and rely on caregivers to seek out and attend to the information. In this article, interventions using threat appeal tactics and progressive dissemination methods are recommended to effectively target participation and perceptions of vulnerability among this population. Recent research on risk communication indicates that threat appeals are supported when they contain high threat and high efficacy components. Threat appeal tactics are particularly desirable when perception of vulnerability is low, as is the case with parents of booster-aged children. In addition to theoretical arguments for more aggressive intervention approaches, a case example is presented wherein such techniques were used to promote booster seat use. The intervention resulted in significant increases in knowledge, risk-reduction attitudes, sense of efficacy, and observed booster seat use. Through use of progressive dissemination methods, the intervention has reached an audience of 431,600 people and counting. PMID:22090153

  6. Space Launch System Booster Separation Aerodynamic Database Development and Uncertainty Quantification

    NASA Technical Reports Server (NTRS)

    Chan, David T.; Pinier, Jeremy T.; Wilcox, Floyd J., Jr.; Dalle, Derek J.; Rogers, Stuart E.; Gomez, Reynaldo J.

    2016-01-01

    The development of the aerodynamic database for the Space Launch System (SLS) booster separation environment has presented many challenges because of the complex physics of the ow around three independent bodies due to proximity e ects and jet inter- actions from the booster separation motors and the core stage engines. This aerodynamic environment is dicult to simulate in a wind tunnel experiment and also dicult to simu- late with computational uid dynamics. The database is further complicated by the high dimensionality of the independent variable space, which includes the orientation of the core stage, the relative positions and orientations of the solid rocket boosters, and the thrust lev- els of the various engines. Moreover, the clearance between the core stage and the boosters during the separation event is sensitive to the aerodynamic uncertainties of the database. This paper will present the development process for Version 3 of the SLS booster separa- tion aerodynamic database and the statistics-based uncertainty quanti cation process for the database.

  7. A new one-man submarine is tested as vehicle for solid rocket booster retrieval

    NASA Technical Reports Server (NTRS)

    2000-01-01

    A mockup of a solid rocket booster nozzle is lowered into the waters of the Atlantic during a test of a new booster retrieval method. A one-man submarine known as DeepWorker 2000 is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

  8. Booster Breaks in the workplace: participants’ perspectives on health-promoting work breaks

    PubMed Central

    Taylor, Wendell C.; King, Kathryn E.; Shegog, Ross; Paxton, Raheem J.; Evans-Hudnall, Gina L.; Rempel, David M.; Chen, Vincent; Yancey, Antronette K.

    2013-01-01

    Increasing sedentary work has been associated with greater cardiovascular and metabolic risk, as well as premature mortality. Interrupting the sedentary workday with health-promoting work breaks can counter these negative health effects. To examine the potential sustainability of work-break programs, we assessed the acceptance of these breaks among participants in a Booster Break program. We analyzed qualitative responses from 35 participants across five worksites where one 15-min physical activity break was taken each workday. Two worksites completed a 1-year intervention and three worksites completed a 6-month intervention. Responses to two open-ended questions about the acceptance and feasibility of Booster Breaks were obtained from a survey administered after the intervention. Three themes for benefits and two themes for barriers were identified. The benefit themes were (i) reduced stress and promoted enjoyment, (ii) increased health awareness and facilitated behavior change, and (iii) enhanced workplace social interaction. The barrier themes were the need for (iv) greater variety in Booster Break routines and (v) greater management support. This study provides empirical support for the acceptance and feasibility of Booster Breaks during the workday. Emphasizing the benefits and minimizing the barriers are strategies that can be used to implement Booster Breaks in other workplaces. PMID:23466367

  9. Evaluation of community-based programs to increase booster seat use.

    PubMed

    St Louis, Renée M; Parow, Julie E; Eby, David W; Bingham, C Raymond; Hockanson, Heather M; Greenspan, Arlene I

    2008-01-01

    This manuscript reports the results of an evaluation of two community-based booster seat promotion programs in Michigan; one program focused on a low-income community, while the other focused on a Hispanic community. Each community received funding to develop and implement a booster seat intervention program specific to their community. To determine the effectiveness of each program, direct observation surveys of booster seat use were conducted in each community, as well as in similarly composed comparison communities, before and after program implementation. A process evaluation documented activities and provided additional information for interpreting the results of the direct observation survey. Target age children (4-8 years) were observed traveling in cars, vans/minivans, sport-utility vehicles, and pickup trucks in each community. Baseline booster seat use was 19.0+/-5.3% and 9.7+/-2.5% for the low-income and Hispanic program communities, respectively. Post program results showed no significant change for the low-income program community, and a significant increase within the Hispanic program community. The process evaluation revealed challenges for each program and suggestions to overcome those challenges. Findings from the study can be useful to other communities interested in implementing programs to increase the use of booster seats. PMID:18215561

  10. Toward Sustainable and Affordable Space Exploration: The Role of NASA's Space Product Development Program

    NASA Astrophysics Data System (ADS)

    Schowengerdt, Franklin D.

    2005-02-01

    The National Vision for Space Exploration calls for sustainable and affordable human and robotic missions to explore the solar system. Sustainability requires that the program produce visible benefits to the public, along with scientific and technological advances in support of exploration that would be expected from a program of this magnitude. Affordability requires that the private sector be heavily involved, not just as contractors to NASA, but as sources of investment and direct beneficiaries of returns; in short, full participants in a long-term program that can transform the future of mankind. In order to make the vision both sustainable and affordable, true partnerships involving industry, academia and government must exist to create Earth benefits while working on needed exploration technologies and, at the same time, provide the added investments that will inevitably be required in extended periods of fiscal restraint. Such partnership programs, embodied in the Research Partnership Centers, have long existed within NASA. They have recently been realigned to more fully support the exploration vision and brought into the Exploration Systems Mission Directorate. This program and its past and potential contributions to the exploration vision will be described in detail at the conference.

  11. Nondestructive Evaluation (NDE) Results on Sikorsky Aircraft Survivable Affordable Reparable Airframe Program (SARAP) Samples

    NASA Technical Reports Server (NTRS)

    Zalameda, Joseph N.; Anastasi, Robert F.; Madaras, Eric I.

    2004-01-01

    The Survivable, Affordable, Reparable Airframe Program (SARAP) will develop/produce new structural design concepts with lower structural weight, reduced manufacturing complexity and development time, increased readiness, and improved threat protection. These new structural concepts will require advanced field capable inspection technologies to help meet the SARAP structural objectives. In the area of repair, damage assessment using nondestructive inspection (NDI) is critical to identify repair location and size. The purpose of this work is to conduct an assessment of new and emerging NDI methods that can potentially satisfy the SARAP program goals.

  12. Expendable Second Stage Reusable Space Shuttle Booster. Volume 10: Technology Requirements

    NASA Technical Reports Server (NTRS)

    1971-01-01

    Technology requirements for the expendable second stage of the space shuttle booster system are discussed. The primary objective of the expendable second stage (ESS) program is to define a low-cost system for placing large payloads, such as the space station or reusable nuclear shuttle, into low earth orbit. The proposed concept is to utilize a modified Saturn 5 second stage (S-2) in conjunction with the space shuttle reusable booster. The ESS retains the major S-2 structure, modified for attachment to the space shuttle booster, and incorporates both Saturn and shuttle developed propulsion and avionics hardware. No major technology breakthroughs are required to develop this ESS system. Technology application and implementation efforts in selected areas, however, should be conducted in support of the ESS detail design and development phase. The selected ESS system incorporates recovery of propulsion and avionics hardware by the shuttle orbiter for ESS reuse to minimize cost.

  13. Aerodynamic stability and control characteristics of TBC shuttle booster AR-11981-3

    NASA Technical Reports Server (NTRS)

    Phelps, E. R.; Watts, L. L.; Ainsworth, R. W.

    1972-01-01

    A scale model of the Boeing Company space shuttle booster configuration 3 was tested in the MSFC 14-inch trisonic wind tunnel. This test was proposed to fill-in the original test run schedule as well as to investigate the aerodynamic stability and control characteristics of the booster with three wing configurations not previously tested. The configurations tested included: (1) a cylindrical booster body with an axisymmetric nose, (2) clipped delta canards that had variable incidence from 0 deg to -60 deg, (3) different aft body mounted wing configurations, (4) two vertical fin configurations, and (5) a Grumman G-3 orbiter configuration. Tests were conducted over a Mach range from 0.6 to 5.0.

  14. Implications of a 20-Hz Booster cycle-rate for Slip-stacking

    SciTech Connect

    Eldred, Jeffrey; Zwaska, Robert

    2014-06-10

    We examine the potential impacts to slip-stacking from a change of the Booster cycle-rate from 15- to 20-Hz. We find that changing the Booster cycle-rate to 20-Hz would greatly increase the slip-stacking bucket area, while potentially requiring greater usage of the Recycler momentum aperture and additional power dissipation in the RF cavities. In particular, the losses from RF interference can be reduced by a factor of 4-10 (depending on Booster beam longitudinal parameters). We discuss the aspect ratio and beam emittance requirements for efficient slip-stacking in both cycle-rate cases. Using a different injection scheme can eliminate the need for greater momentum aperture in the Recycler.

  15. Unsteady aerodynamic analysis of space shuttle vehicles. Part 3: Booster interference effects

    NASA Technical Reports Server (NTRS)

    Reding, J. P.; Ericsson, L. E.

    1973-01-01

    An investigation of the interference flow field on the space-shuttle boost configuration has been made. The results show that the interference effects can dominate the shuttle aerodynamics. Vortices shed from shock-induced flow separations on the forward portion of the vehicle affect the aerodynamic loads on the aft portion of the booster. Thus, the forebody and aft-body flow fields are coupled. This coupling and the associated time lag due to the finite convection speed of the vortices furnish a mechanism whereby the unsteady aerodynamics can cause undamping of certain low frequency elastic modes of the booster. A preliminary order-of-magnitude analysis of the aeroelastic stability of the shuttle booster indicates that negative aerodynamic damping could occur for at least one bending mode and be of sufficient magnitude to dominate the structural damping. The implication of these results, (with the possibility of undamped oscillations leading to structural failure), is serious enough to warrant further, more detailed analysis.

  16. System overview for the multi-element corrector magnets and controls for the Fermilab Booster

    SciTech Connect

    Drennan, C.; Ball, M.; Franck, A.R.; Harding, D.J.; Kasley, P.A.; Krafczyk, G.E.; Kucera, M.J.; Lackey, J.; McArthur, D.; Misek, J.; Pellico, W.; /Fermilab

    2007-06-01

    To better control the beam position, tune, and chromaticity in the Fermilab Booster synchrotron, a new package of six corrector elements has been designed, incorporating both normal and skew orientations of dipole, quadrupole, and sextupole magnets. The devices are under construction and will be installed in 48 locations in the Booster accelerator. Each of these 288 corrector magnets will be individually powered. Each of the magnets will be individually controlled using operator programmed current ramps designed specifically for each type of Booster acceleration cycle. This paper provides an overview of the corrector magnet installation in the accelerator enclosure, power and sensor interconnections, specifications for the switch-mode power supplies, rack and equipment layouts, controls and interlock electronics, and the features of the operator interface for programming the current ramps and adjusting the timing of the system triggers.

  17. Design and optimization of a large flow rate booster pump in SWRO energy recovery system

    NASA Astrophysics Data System (ADS)

    Lai, Z. N.; Wu, P.; Wu, D. Z.; Wang, L. Q.

    2013-12-01

    Seawater reverse osmosis (SWRO) is a high energy-consumption industry, so energy efficiency is an important issue. Energy recovery systems, which contain a pressure exchanger and a booster pump, are widely used in SWRO plants. As a key part of energy recovery system, the difficulty of designing booster pumps lies in high inlet pressure, high medium causticity and large flow rate. High inlet pressure adds difficulties to seal design, and large flow rate and high efficiency requirement bring high demand for hydraulic design. In this paper, a 625 m3/h booster pump is designed and optimized according to the CFD (Computational Fluid Dynamics) simulation results. The impeller and volute is well designed, a new type of high pressure mechanical seal is applied and axial force is well balanced. After optimization based on blade redesign, the efficiency of the pump was improved. The best efficiency reaches more than 85% at design point according to the CFD simulation result.

  18. Solid Rocket Booster Large Main and Drogue Parachute Reliability Analysis

    NASA Technical Reports Server (NTRS)

    Clifford, Courtenay B.; Hengel, John E.

    2009-01-01

    The parachutes on the Space Transportation System (STS) Solid Rocket Booster (SRB) are the means for decelerating the SRB and allowing it to impact the water at a nominal vertical velocity of 75 feet per second. Each SRB has one pilot, one drogue, and three main parachutes. About four minutes after SRB separation, the SRB nose cap is jettisoned, deploying the pilot parachute. The pilot chute then deploys the drogue parachute. The drogue chute provides initial deceleration and proper SRB orientation prior to frustum separation. At frustum separation, the drogue pulls the frustum from the SRB and allows the main parachutes that are mounted in the frustum to unpack and inflate. These chutes are retrieved, inspected, cleaned, repaired as needed, and returned to the flight inventory and reused. Over the course of the Shuttle Program, several improvements have been introduced to the SRB main parachutes. A major change was the replacement of the small (115 ft. diameter) main parachutes with the larger (136 ft. diameter) main parachutes. Other modifications were made to the main parachutes, main parachute support structure, and SRB frustum to eliminate failure mechanisms, improve damage tolerance, and improve deployment and inflation characteristics. This reliability analysis is limited to the examination of the SRB Large Main Parachute (LMP) and drogue parachute failure history to assess the reliability of these chutes. From the inventory analysis, 68 Large Main Parachutes were used in 651 deployments, and 7 chute failures occurred in the 651 deployments. Logistic regression was used to analyze the LMP failure history, and it showed that reliability growth has occurred over the period of use resulting in a current chute reliability of R = .9983. This result was then used to determine the reliability of the 3 LMPs on the SRB, when all must function. There are 29 drogue parachutes that were used in 244 deployments, and no in-flight failures have occurred. Since there are no

  19. X-43A hypersonic research aircraft mated to its modified Pegasus booster rocket.

    NASA Technical Reports Server (NTRS)

    2001-01-01

    The first of three X-43A hypersonic research aircraft was mated to its modified Pegasus booster rocket in late January at NASA's Dryden Flight Research Center, Edwards, Calif. FIRST X-43A MATED TO BOOSTER -- The first of three X-43A hypersonic research aircraft was mated to its modified Pegasus booster rocket in late January at NASA's Dryden Flight Research Center, Edwards, Calif. Mating of the X-43A and its specially-designed adapter to the first stage of the booster rocket marks a major milestone in the Hyper-X hypersonic research program. The 12-foot, unpiloted research vehicle was developed and built by MicroCraft Inc., Tullahoma, Tenn., for NASA. The booster, built by Orbital Sciences Corp., Dulles, Va., will accelerate the X-43A after the X-43A booster 'stack' is air-launched from NASA's venerable NB-52 mothership. The X-43A will separate from the rocket at a predetermined altitude and speed and fly a pre-programmed trajectory, conducting aerodynamic and propulsion experiments until it impacts into the Pacific Ocean. Three research flights are planned, two at Mach 7 and one at Mach 10 (seven and 10 times the speed of sound respectively) with the first tentatively scheduled for early summer of 2001. The X-43A is powered by a revolutionary supersonic-combustion ramjet ('scramjet') engine, and will use the underbody of the aircraft to form critical elements of the engine. The forebody shape helps compress the intake airflow, while the aft section acts as a nozzle to direct thrust. The X-43A flights will be the first actual flight tests of an aircraft powered by an air-breathing scramjet engine.

  20. Theoretical Analysis and Bench Tests of a Control-Surface Booster Employing a Variable Displacement Hydraulic Pump

    NASA Technical Reports Server (NTRS)

    Mathews, Charles W.; Kleckner, Harold F.

    1947-01-01

    The NACA is conducting a general investigation of servo-mechanisms for use in powering aircraft control surfaces. This paper presents a theoretical analysis and the results of bench tests of a control-booster system which employs a variable displacement hydraulic pump. The booster is intended for use in a flight investigation to determine the effects of various booster parameters on the handling qualities of airplanes. Such a flight investigation would aid in formulating specific requirements concerning the design of control boosters in general. Results of the theoretical analysis and the bench tests indicate that the subject booster is representative of types which show promise of satisfactory performance. The bench tests showed that the following desirable features were inherent in this booster system: (1) No lost motion or play in any part of the system; (2) no detectable lag between motion of the contra1 stick and control surface; and (3) Good agreement between control displacements and stick-force variations with no hysteresis in the stick-force characteristics. The final design configuration of this booster system showed no tendency to oscillate, overshoot, or have other undesirable transient characteristics common to boosters.