Science.gov

Sample records for launch market related

  1. Suborbital Reusable Launch Vehicles and Applicable Markets

    NASA Astrophysics Data System (ADS)

    Martin, J. C.; Law, G. W.

    2002-10-01

    The purpose of this report is to survey and characterize suborbital reusable launch vehicles (RLVs) in development, as well as to identify current and emerging suborbital market opportunities that these systems may enable. Over the past 30 years, NASA has accepted the burden of developing technologies that will enable cheaper access to orbital space, as evidenced by its past X-programs and the current Space Launch Initiative. Various private companies have also attempted, and are still attempting, to develop new RLV systems for orbital space applications. However, the large development costs of such systems, coupled with the downturn of the low Earth orbit market (e.g., Iridium, GlobalStar), have made private sector development of orbital RLV systems increasingly difficult at this time. Given these hurdles, many commercial space transportation companies have begun shifting focus toward suborbital market opportunities, for which the technical challenge is much lower and the cost of market entry less expensive.

  2. Reusable Launch Vehicle (RLV) Market Analysis Model

    NASA Technical Reports Server (NTRS)

    Prince, Frank A.

    1999-01-01

    The RLV Market Analysis model is at best a rough order approximation of actual market behavior. However, it does give a quick indication if the flights exists to enable an economically viable RLV, and the assumptions necessary for the vehicle to capture those flights. Additional analysis, market research, and updating with the latest information on payloads and launches would improve the model. Plans are to update the model as new information becomes available and new requirements are levied. This tool will continue to be a vital part of NASA's RLV business analysis capability for the foreseeable future.

  3. Reusable Launch Vehicle (RLV) Mission/Market Model

    NASA Technical Reports Server (NTRS)

    Prince, Frank A.

    1999-01-01

    The goal of this model was to assess the Reusable Launch Vehicle's (RLV) capability to support the International Space Station (ISS) servicing, determine the potential to leverage the commercial marketplace to reduce NASA's cost, and to evaluate the RLV's ability to expand the space economy. The presentation is in view-graph format.

  4. Legislative and regulatory issues related to reusable launch systems

    NASA Astrophysics Data System (ADS)

    Peinemann, Manfred K. A.

    1996-03-01

    The development of reusable launch systems with private investment funds for primarily commercial launch services raises a number of novel legal and regulatory issues. The issues discussed include requirements for a whole new spectrum of safety and environmental issues; new certification rules, procedures and oversight organizations; liability and jurisdiction definitions, taxation treatments; government commitments and/or participation in commercial enterprises; and international legal and business issues. The satisfactory solution to all of these issues is a necessary condition for the development and operation of reusable launch vehicles to be a viable commercial enterprise.

  5. Ground cloud related weather modification effects. [heavy lift launch vehicles

    NASA Technical Reports Server (NTRS)

    Lee, J.

    1980-01-01

    The principal concerns about inadvertent weather modification by the solar power satellite system rocket effluents are discussed, namely the possibility that the ground cloud might temporarily modify local weather and the cumulative effects of nearly 500 launches per year. These issues are discussed through the consideration of (1) the possible alteration of the microphysical processes of clouds in the general area due to rocket effluents and debris and cooling water entrained during the launch and (2) the direct dynamical and thermodynamical responses to the inputs of thermal energy and moisture from the rocket exhaust for given ambient meteorological conditions. The huge amount of thermal energy contained in the exhaust of the proposed launch vehicle would in some situations induce a saturated, wet convective cloud or enhance an existing convective activity. Nevertheless, the effects would be limited to the general area of the launch site. The observed long lasting high concentrations of cloud condensation nuclei produced during and after a rocket launch may appreciably affect the frequency of occurrence and persistence of fogs and haze. In view of the high mission frequency proposed for the vehicle launches, a potential exists for a cumulative effect.

  6. Market Related System Analysis of Satellite Communication Networks

    NASA Astrophysics Data System (ADS)

    Malyshev, V. V.; Panasenkova, M. V.

    2002-01-01

    The report is devoted to the technique of effectiveness analysis of communication space system with satellites in geostationary orbit using market models. The technique is worked out in order to choose the most optimal alternative of communication space system design. The alternative considered optimal and the system effective when the maximum profit from the system with limited system costs is achieved. The key point of the technique is a wide use of market models and application of market related parameters as an integral part of the design technique in order to secure the high commercial output of the communication space system. A range of models for decisive characteristics of communication space system is synthesized in terms of the technique. Flexible market model with detailed insight into the structure of the given market sector and its trends is created. The technique enables to choose the image and key parameters of the future system such as payload and ground sector characteristics so as to make the system most cost-effective and profitable. It is shown that such factors as the choice of launch vehicle can influence the system effectiveness rather dramatically. In particular, it is shown that under certain conditions delivering the small (five hundred kg) satellite to the geostationary orbit with the help of light-weight launch vehicle and the satellite's own electro-rocket thrusters is forty per cent more cost- effective than when the satellite is delivered with the help of the medium-size launch vehicle. The latter case can lead to the significant losses due to high launch costs that are nearly two times higher for the medium size launch vehicle than for the light launce vehicle. The technique is applicable both for designing a wide range of communication space systems and is recommended for those dealing with designing commercial systems. It can also be used to update and improve the systems that are already in operation.

  7. Optimum space shuttle launch times relative to natural environment

    NASA Technical Reports Server (NTRS)

    King, R. L.

    1977-01-01

    The probabilities of favorable and unfavorable weather conditions for launch and landing of the STS under different criteria were computed for every three hours on a yearly basis using 14 years of weather data. These temporal probability distributions were considered for three sets of weather criteria encompassing benign, moderate and severe weather conditions for both Kennedy Space Center and for Edwards Air Force Base. In addition, the conditional probabilities were computed for unfavorable weather conditions occurring after a delay which may or may not be due to weather conditions. Also for KSC, the probabilities of favorable landing conditions at various times after favorable launch conditions have prevailed. The probabilities were computed to indicate the significance of each weather element to the overall result.

  8. Optimum space shuttle launch times relative to natural environment

    NASA Technical Reports Server (NTRS)

    King, R. L.

    1977-01-01

    Three sets of meteorological criteria were analyzed to determine the probabilities of favorable launch and landing conditions. Probabilities were computed for every 3 hours on a yearly basis using 14 years of weather data. These temporal probability distributions, applicable to the three sets of weather criteria encompassing benign, moderate and severe weather conditions, were computed for both Kennedy Space Center (KSC) and Edwards Air Force Base. In addition, conditional probabilities were computed for unfavorable weather conditions occurring after a delay which may or may not be due to weather conditions. Also, for KSC, the probabilities of favorable landing conditions at various times after favorable launch conditions have prevailed have been computed so that mission probabilities may be more accurately computed for those time periods when persistence strongly correlates weather conditions. Moreover, the probabilities and conditional probabilities of the occurrence of both favorable and unfavorable events for each individual criterion were computed to indicate the significance of each weather element to the overall result.

  9. Launching Payloads Into Orbit at Relatively Low Cost

    NASA Technical Reports Server (NTRS)

    Wilcox, Brian

    2007-01-01

    A report proposes the development of a system for launching payloads into orbit at about one-fifth the cost per unit payload weight of current systems. The PILOT system was a solid-fuel, aerodynamically spun and spin-stabilized, five-stage rocket with onboard controls including little more than an optoelectronic horizon sensor and a timer for triggering the second and fifth stages, respectively. The proposal calls for four improvements over the PILOT system to enable control of orbital parameters: (1) the aerodynamic tipover of the rocket at the top of the atmosphere could be modeled as a nonuniform gyroscopic precession and could be controlled by selection of the initial rocket configuration and launch conditions; (2) the attitude of the rocket at the top of the first-stage trajectory could be measured by use of radar tracking or differential Global Positioning System receivers to determine when to trigger the second stage; (3) the final-stage engines could be configured around the payload to enhance spin stabilization during a half-orbit coast up to apoapsis where the final stage would be triggered; and (4) the final payload stage could be equipped with a "beltline" of small thrusters for correcting small errors in the trajectory as measured by an off-board tracking subsystem.

  10. Steady Increase In Prices For Oral Anticancer Drugs After Market Launch Suggests A Lack Of Competitive Pressure.

    PubMed

    Bennette, Caroline S; Richards, Catherine; Sullivan, Sean D; Ramsey, Scott D

    2016-05-01

    The cost of treating cancer has risen to unprecedented heights, putting tremendous financial pressure on patients, payers, and society. Previous studies have documented the rising prices of cancer drugs at launch, but less critical attention has been paid to the cost of these drugs after launch. We used pharmacy claims for commercially insured individuals to examine trends in postlaunch prices over time for orally administered anticancer drugs recently approved by the Food and Drug Administration (FDA). In the period 2007-13, inflation-adjusted per patient monthly drug prices increased 5 percent each year. Certain market changes also played a role, with prices rising an additional 10 percent with each supplemental indication approved by the FDA and declining 2 percent with the FDA's approval of a competitor drug. Our findings suggest that there is currently little competitive pressure in the oral anticancer drug market. Policy makers who wish to reduce the costs of anticancer drugs should consider implementing policies that affect prices not only at launch but also later. PMID:27140986

  11. Does marketing relate to hospital profitability?

    PubMed

    McDermott, D R; Franzak, F J; Little, M W

    1993-01-01

    The authors examine the relationship of hospitals' marketing activities--including the use of market intelligence activities, interfunctional coordination activities, and organizational responsiveness activities--to financial performance. The results suggest it would be valuable to hospital marketing managers to adopt a data-driven, proactive management style that incorporates a teamwork emphasis to improve their hospital's financial performance. PMID:10127061

  12. Kennedy Space Center (KSC) Launch Pad Avian Abatement Efforts Including Related KSC Road Kill Reduction Effort

    NASA Technical Reports Server (NTRS)

    Schlierf, Roland; Hight, Ron; Payne, Stephen J.; Shaffer, John P.; Missimer, Brad; Willis, Christopher

    2007-01-01

    While birds might seem harmless, there's a good reason for the concern. During the July 2005 launch of Discovery on mission STS-1 14, a vulture soaring around the launch pad impacted the shuttle's external tank just after liftoff. With a vulture's average weight ranging from 3 to 5 pounds. a strike at a critical point on the Shuttle -- like the nose or wing leading thermal protection panels -- could cause catastrophic damage to the vehicle. The foam chunk that fatefully struck Columbia's wing in 2003 weighed only 1.7 pounds. (Cheryl L. Mansfield "Bye Bye Birdies" 2006) To address this issue, NASA formed an "Avian Abatement Team". The team goal is to have safer Shuttle missions by reducing the vulture population at KSC near the pad area thereby reducing the probability of another vulture strike during a Shuttle launch.

  13. Marketing and Public Relations in ARL Libraries. SPEC Kit 240.

    ERIC Educational Resources Information Center

    Smykla, Evelyn Ortiz, Comp.

    1999-01-01

    This survey was conducted to delineate the growing relationship between marketing and public relations and library funding by identifying: (1) the extent to which North American research libraries have developed organized programs in the areas of marketing and public relations; (2) who holds positions in these areas; and (3) the impact these…

  14. Village poultry consumption and marketing in relation to gender, religious festivals and market access.

    PubMed

    Aklilu, H A; Almekinders, C J M; Udo, H M J; Van der Zijpp, A J

    2007-04-01

    This study aimed to examine village poultry consumption and marketing in Ethiopia in relation to gender, socio-cultural events and market access. The main objects of the research were producers, poultry markets, producer-sellers, and intermediary sellers in three locations representing different levels of market access in Tigray. About 3000 farm records were collected over a period of 12 months from 131 producers to obtain quantitative data on sales and consumption. Ninety-three semi-structured interviews with 58 producer-sellers and 35 intermediaries and 12 group discussions with these market actors were conducted to explore organization, price dynamics and socio-cultural aspects of poultry marketing. In total, 928 producer-sellers and 225 intermediaries were monitored monthly to examine participation by gender in poultry marketing. Better market access was associated with a shorter market chain and higher prices for the producers. Female-headed households had smaller poultry sales and consumption per household but sale and consumption per family member were 25% and 66% higher, respectively, than in male-headed households. While women dominated in the producer-sellers group, intermediaries were mainly men. Religious festivals periodically shifted local demand and prices of poultry. To improve the benefit of poultry keeping, poverty-stricken households may profit from better market access through better market information, infrastructure, market group formation and careful planning to match the dynamics in demand. PMID:17691541

  15. Cohesiveness in financial news and its relation to market volatility.

    PubMed

    Piškorec, Matija; Antulov-Fantulin, Nino; Novak, Petra Kralj; Mozetič, Igor; Grčar, Miha; Vodenska, Irena; Smuc, Tomislav

    2014-01-01

    Motivated by recent financial crises, significant research efforts have been put into studying contagion effects and herding behaviour in financial markets. Much less has been said regarding the influence of financial news on financial markets. We propose a novel measure of collective behaviour based on financial news on the Web, the News Cohesiveness Index (NCI), and we demonstrate that the index can be used as a financial market volatility indicator. We evaluate the NCI using financial documents from large Web news sources on a daily basis from October 2011 to July 2013 and analyse the interplay between financial markets and finance-related news. We hypothesise that strong cohesion in financial news reflects movements in the financial markets. Our results indicate that cohesiveness in financial news is highly correlated with and driven by volatility in financial markets. PMID:24849598

  16. Cohesiveness in Financial News and its Relation to Market Volatility

    PubMed Central

    Piškorec, Matija; Antulov-Fantulin, Nino; Novak, Petra Kralj; Mozetič, Igor; Grčar, Miha; Vodenska, Irena; Šmuc, Tomislav

    2014-01-01

    Motivated by recent financial crises, significant research efforts have been put into studying contagion effects and herding behaviour in financial markets. Much less has been said regarding the influence of financial news on financial markets. We propose a novel measure of collective behaviour based on financial news on the Web, the News Cohesiveness Index (NCI), and we demonstrate that the index can be used as a financial market volatility indicator. We evaluate the NCI using financial documents from large Web news sources on a daily basis from October 2011 to July 2013 and analyse the interplay between financial markets and finance-related news. We hypothesise that strong cohesion in financial news reflects movements in the financial markets. Our results indicate that cohesiveness in financial news is highly correlated with and driven by volatility in financial markets. PMID:24849598

  17. Cohesiveness in Financial News and its Relation to Market Volatility

    NASA Astrophysics Data System (ADS)

    Piškorec, Matija; Antulov-Fantulin, Nino; Novak, Petra Kralj; Mozetič, Igor; Grčar, Miha; Vodenska, Irena; Šmuc, Tomislav

    2014-05-01

    Motivated by recent financial crises, significant research efforts have been put into studying contagion effects and herding behaviour in financial markets. Much less has been said regarding the influence of financial news on financial markets. We propose a novel measure of collective behaviour based on financial news on the Web, the News Cohesiveness Index (NCI), and we demonstrate that the index can be used as a financial market volatility indicator. We evaluate the NCI using financial documents from large Web news sources on a daily basis from October 2011 to July 2013 and analyse the interplay between financial markets and finance-related news. We hypothesise that strong cohesion in financial news reflects movements in the financial markets. Our results indicate that cohesiveness in financial news is highly correlated with and driven by volatility in financial markets.

  18. COSMOS Launch Services

    NASA Astrophysics Data System (ADS)

    Kalnins, Indulis

    2002-01-01

    COSMOS-3M is a two stage launcher with liquid propellant rocket engines. Since 1960's COSMOS has launched satellites of up to 1.500kg in both circular low Earth and elliptical orbits with high inclination. The direct SSO ascent is available from Plesetsk launch site. The very high number of 759 launches and the achieved success rate of 97,4% makes this space transportation system one of the most reliable and successful launchers in the world. The German small satellite company OHB System co-operates since 1994 with the COSMOS manufacturer POLYOT, Omsk, in Russia. They have created the joint venture COSMOS International and successfully launched five German and Italian satellites in 1999 and 2000. The next commercial launches are contracted for 2002 and 2003. In 2005 -2007 COSMOS will be also used for the new German reconnaissance satellite launches. This paper provides an overview of COSMOS-3M launcher: its heritage and performance, examples of scientific and commercial primary and piggyback payload launches, the launch service organization and international cooperation. The COSMOS launch service business strategy main points are depicted. The current and future position of COSMOS in the worldwide market of launch services is outlined.

  19. Marketing. Retailing 102, Promotions 202, Relations in Business 202, Management 302, Marketing Practicum 302.

    ERIC Educational Resources Information Center

    Manitoba Dept. of Education, Winnipeg.

    This teaching guide contains guidelines for conducting five secondary-level marketing cluster courses--Retailing 102, Promotions 202, Relations in Business 202, Management 302, and Marketing Practicum 302. Covered first are goals and objectives, teachers' notes and suggested activities, lists of suggested materials, and guidelines for correlating…

  20. Russian Soyuz in Launch Position

    NASA Technical Reports Server (NTRS)

    2000-01-01

    The Soyuz TM-31 launch vehicle is shown in the vertical position for its launch from Baikonur, carrying the first resident crew to the International Space Station. The Russian Soyuz launch vehicle is an expendable spacecraft that evolved out of the original Class A (Sputnik). From the early 1960s until today, the Soyuz launch vehicle has been the backbone of Russia's marned and unmanned space launch fleet. Today, the Soyuz launch vehicle is marketed internationally by a joint Russian/French consortium called STARSEM. As of August 2001, there have been ten Soyuz missions under the STARSEM banner.

  1. Launch operations efficiency

    NASA Technical Reports Server (NTRS)

    Diloreto, Clem; Fischer, Carl; Atkins, Bob

    1988-01-01

    The paper discusses launch operations from a program perspective. Launch operations cost is a significant part of program cost. New approaches to launch operations, integrated with lessons learned, have the potential to increase safety and reliability as well as reduce cost. Operational efficiency must be an initial program goal. Design technology and management philosophy must be implemented early to ensure operational cost goals. Manufacturing cost and launch cost are related to operational efficiency. True program savings can be realized through implementation of launch operations cost saving approaches which do not correspondingly increase cost in other program areas such as manufacturing and software development and maintenance. Launch rate is a key factor in the cost/flight analysis and the determination of launch operations efficiency goals.

  2. Foreign launch competition growing

    NASA Astrophysics Data System (ADS)

    Brodsky, R. F.; Wolfe, M. G.; Pryke, I. W.

    1986-07-01

    A survey is given of progress made by other nations in providing or preparing to provide satellite launch services. The European Space Agency has four generations of Ariane vehicles, with a fifth recently approved; a second launch facility in French Guiana that has become operational has raised the possible Ariane launch rate to 10 per year, although a May failure of an Ariane 2 put launches on hold. The French Hermes spaceplane and the British HOTOL are discussed. Under the auspices of the Italian National Space Plane, the Iris orbital transfer vehicle is developed and China's Long March vehicles and the Soviet Protons and SL-4 vehicles are discussed; the Soviets moreover are apparently developing not only a Saturn V-class heavy lift vehicle with a 150,000-kg capacity (about five times the largest U.S. capacity) but also a space shuttle and a spaceplane. Four Japanese launch vehicles and some vehicles in an Indian program are also ready to provide launch services. In this new, tough market for launch services, the customers barely outnumber the suppliers. The competition develops just as the Challenger and Titan disasters place the U.S. at a disadvantage and underline the hard work ahead to recoup its heretofore leading position in launch services.

  3. Technology diffusion of energy-related products in residential markets

    SciTech Connect

    Davis, L.J.; Bruneau, C.L.

    1987-05-01

    Acceptance of energy-related technologies by end residential consumers, manufacturers of energy-related products, and other influential intermediate markets such as builders will influence the potential for market penetration of innovative energy-related technologies developed by the Department of Energy, Office of Building and Community Systems (OBCS). In this report, Pacific Northwest Laboratory reviewed the available information on technology adoption, diffusion, and decision-making processes to provide OBCS with a background and understanding of the type of research that has previously been conducted on this topic. Insight was gained as to the potential decision-making criteria and motivating factors that influence the decision-maker(s) selection of new technologies, and some of the barriers to technology adoption faced by potential markets for OBCS technologies.

  4. Scout Launch

    NASA Technical Reports Server (NTRS)

    1961-01-01

    Scout Launch. James Hansen wrote: 'As this sequence of photos demonstrates, the launch of ST-5 on 30 June 1961 went well; however, a failure of the rocket's third stage doomed the payload, a scientific satellite known as S-55 designed for micrometeorite studies in orbit.'

  5. Integrating Development, Alumni Relations, and Marketing for Fundraising Success

    ERIC Educational Resources Information Center

    Stevick, Thomas R.

    2010-01-01

    At many institutions, the vice president of institutional advancement oversees the functions of development, alumni relations, and marketing and communications. University leaders expect these functions to be integrated and to work hand-in-hand to advance the institution's mission, particularly in the area of private donations. The reality is that…

  6. Tracking the Relative Motion of Four Space Payloads Launched From a Sub-Orbital NASA Rocket

    NASA Technical Reports Server (NTRS)

    Martel, Hugh; Bull, Barton

    1999-01-01

    One problem, which is comparatively new in the field of GPS applications, is the determination of the relative trajectories of space vehicles. Applications include the docking of spacecraft, collision avoidance in the area of space stations, and trajectory reconstruction of multiple payloads. The required precision in any of these applications will vary, according to the requirements of the task and abilities of GPS to cope with the environment and the dynamics. This paper describes the post-mission reconstruction of the relative trajectories of four GPS receivers attached to four payloads jettisoned from a rocket in a sub-orbital NASA science mission. It is shown that the sub-decimetre level were achieved with single frequency GPS receivers.

  7. Marketing.

    ERIC Educational Resources Information Center

    Appel, David L.

    This booklet suggests ways in which institutions--Catholic schools in particular--can move beyond public relations and advertising to engage in the broader arena of marketing with its focus on consumer satisfaction. The first of the book's three chapters reviews the concept of marketing, providing definitions of key terms, clarification of…

  8. NPP Launch

    NASA Video Gallery

    NASA's National Polar-orbiting Operational Environmental Satellite System Preparatory Project (NPP) spacecraft was launched aboard a Delta II rocket at 5:48 a.m. EDT today, on a mission to measure ...

  9. The UK relative to other single payer-dominated healthcare markets for regenerative medicine therapies.

    PubMed

    Rose, James B; Williams, David J

    2012-05-01

    The UK has for many years been considered by businesses, including those based in the UK, as at best a second market for the launch of innovative medical technology products. Historically, this has been attributed to the slow pace of adoption in its National Health Service (NHS). The NHS is perceived to be subject to cost containment, high levels of fragmentation and a lack of strategic incentives to resolve its key failings as a market. Canada and Sweden offer examples of different operating models of healthcare delivery in a single payer-dominated market, and as a consequence, have evolved with different market characteristics. Together, these economies represent an important subsection of healthcare markets that are predominantly publically funded. This report examines the barriers to market entry for regenerative medicine products in these economies and attempts to evaluate the upcoming UK healthcare reforms in terms of impact on the regenerative medicine industry sector. PMID:22594333

  10. Launch system development in the Pacific Rim

    NASA Technical Reports Server (NTRS)

    Stone, Barbara A.; Page, John R.

    1993-01-01

    Several Western Pacific Rim nations are beginning to challenge the domination of the United States, Europe, and the former Soviet Union in the international market for commercial launch sevices. This paper examines the current development of launch systems in China, Japan, and Australia. China began commercial launch services with their Long March-3 in April 1990, and is making enhancements to vehicles in this family. Japan is developing the H-2 rocket which will be marketed on a commercial basis. In Australia, British Aerospace Ltd. is leading a team conducting a project definition study for an Australian Launch Vehicle, aimed at launching the new generation of satellites into low Earth orbit.

  11. Launch systems operations cost modeling

    NASA Astrophysics Data System (ADS)

    Jacobs, Mark K.

    1999-01-01

    This paper describes the launch systems operations modeling portion of a larger model development effort, NASA's Space Operations Cost Model (SOCM), led by NASA HQ. The SOCM study team, which includes cost and technical experts from each NASA Field Center and various contractors, has been tasked to model operations costs for all future NASA mission concepts including planetary and Earth orbiting science missions, space facilities, and launch systems. The launch systems operations modeling effort has near term significance for assessing affordability of our next generation launch vehicles and directing technology investments, although it provides only a part of the necessary inputs to assess life cycle costs for all elements that determine affordability for a launch system. Presented here is a methodology to estimate requirements associated with a launch facility infrastructure, or Spaceport, from start-up/initialization into steady-state operation. Included are descriptions of the reference data used, the unique estimating methodology that combines cost lookup tables, parametric relationships, and constructively-developed correlations of cost driver input values to collected reference data, and the output categories that can be used by economic and market models. Also, future plans to improve integration of launch vehicle development cost models, reliability and maintainability models, economic and market models, and this operations model to facilitate overall launch system life cycle performance simulations will be presented.

  12. 17 CFR 38.5 - Information relating to contract market compliance.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... contract market compliance. 38.5 Section 38.5 Commodity and Securities Exchanges COMMODITY FUTURES TRADING COMMISSION DESIGNATED CONTRACT MARKETS General Provisions § 38.5 Information relating to contract market compliance. (a) Requests for information. Upon request by the Commission, a designated contract market...

  13. 17 CFR 38.5 - Information relating to contract market compliance.

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ... contract market compliance. 38.5 Section 38.5 Commodity and Securities Exchanges COMMODITY FUTURES TRADING COMMISSION DESIGNATED CONTRACT MARKETS General Provisions § 38.5 Information relating to contract market compliance. (a) Requests for information. Upon request by the Commission, a designated contract market...

  14. 17 CFR 38.5 - Information relating to contract market compliance.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... contract market compliance. 38.5 Section 38.5 Commodity and Securities Exchanges COMMODITY FUTURES TRADING COMMISSION DESIGNATED CONTRACT MARKETS § 38.5 Information relating to contract market compliance. (a) Upon request by the Commission, a designated contract market shall file with the Commission such...

  15. 17 CFR 38.5 - Information relating to contract market compliance.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... contract market compliance. 38.5 Section 38.5 Commodity and Securities Exchanges COMMODITY FUTURES TRADING COMMISSION DESIGNATED CONTRACT MARKETS § 38.5 Information relating to contract market compliance. (a) Upon request by the Commission, a designated contract market shall file with the Commission such...

  16. 17 CFR 38.5 - Information relating to contract market compliance.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... contract market compliance. 38.5 Section 38.5 Commodity and Securities Exchanges COMMODITY FUTURES TRADING COMMISSION DESIGNATED CONTRACT MARKETS § 38.5 Information relating to contract market compliance. (a) Upon request by the Commission, a designated contract market shall file with the Commission such...

  17. Russian Soyuz Moves to Launch Pad

    NASA Technical Reports Server (NTRS)

    2000-01-01

    The Soyuz TM-31 launch vehicle, which carried the first resident crew to the International Space Station, moves toward the launch pad at the Baikonur complex in Kazakhstan. The Russian Soyuz launch vehicle is an expendable spacecraft that evolved out of the original Class A (Sputnik). From the early 1960' until today, the Soyuz launch vehicle has been the backbone of Russia's marned and unmanned space launch fleet. Today, the Soyuz launch vehicle is marketed internationally by a joint Russian/French consortium called STARSEM. As of August 2001, there have been ten Soyuz missions under the STARSEM banner.

  18. 17 CFR 75.4 - Permitted underwriting and market making-related activities.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... market making-related activities. 75.4 Section 75.4 Commodity and Securities Exchanges COMMODITY FUTURES... FUNDS Proprietary Trading § 75.4 Permitted underwriting and market making-related activities. (a... into account the liquidity, maturity, and depth of the market for the relevant type of security;...

  19. 36 CFR 223.52 - Market-related contract term additions.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... 36 Parks, Forests, and Public Property 2 2010-07-01 2010-07-01 false Market-related contract term... Provisions § 223.52 Market-related contract term additions. (a) Contract provision. (1) Except as provided in... the Forest Service has determined that adverse wood products market conditions have resulted in...

  20. Marketing.

    ERIC Educational Resources Information Center

    Doyle, Peter

    1987-01-01

    Explores the role of marketing in the modern firm and the key tasks of marketing management. Defines the term "marketing" and discusses it as an economic concept. Discusses three key marketing principals. (RKM)

  1. New Product Launching Ideas

    NASA Astrophysics Data System (ADS)

    Kiruthika, E.

    2012-09-01

    Launching a new product can be a tense time for a small or large business. There are those moments when you wonder if all of the work done to develop the product will pay off in revenue, but there are many things are can do to help increase the likelihood of a successful product launch. An open-minded consumer-oriented approach is imperative in todayís diverse global marketplace so a firm can identify and serve its target market, minimize dissatisfaction, and stay ahead of competitors. Final consumers purchase for personal, family, or household use. Finally, the kind of information that the marketing team needs to provide customers in different buying situations. In high-involvement decisions, the marketer needs to provide a good deal of information about the positive consequences of buying. The sales force may need to stress the important attributes of the product, the advantages compared with the competition; and maybe even encourage ìtrialî or ìsamplingî of the product in the hope of securing the sale. The final stage is the post-purchase evaluation of the decision. It is common for customers to experience concerns after making a purchase decision. This arises from a concept that is known as ìcognitive dissonance

  2. 14 CFR 415.111 - Launch operator organization.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... Launch Vehicle From a Non-Federal Launch Site § 415.111 Launch operator organization. An applicant's...-related goods or services for the launch of the launch vehicle. ... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Launch operator organization....

  3. 14 CFR 415.111 - Launch operator organization.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... Launch Vehicle From a Non-Federal Launch Site § 415.111 Launch operator organization. An applicant's...-related goods or services for the launch of the launch vehicle. ... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Launch operator organization....

  4. 14 CFR 415.111 - Launch operator organization.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... Launch Vehicle From a Non-Federal Launch Site § 415.111 Launch operator organization. An applicant's...-related goods or services for the launch of the launch vehicle. ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Launch operator organization....

  5. 14 CFR 415.111 - Launch operator organization.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... Launch Vehicle From a Non-Federal Launch Site § 415.111 Launch operator organization. An applicant's...-related goods or services for the launch of the launch vehicle. ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Launch operator organization....

  6. Marketing and Public Relations Needs Assessment for Glendale Community College.

    ERIC Educational Resources Information Center

    Atwood-Canter, Collene

    A description is provided of a study undertaken by Glendale Community College (GCC-Arizona) to determine what marketing and information dissemination activities could be undertaken by the college information office to increase enrollments among target markets. Chapter 1 provides an introduction to GCC and its college information office, looking at…

  7. Education, Markets and the Contradictions of Asia-Australia Relations.

    ERIC Educational Resources Information Center

    Alexander, Don; Rizvi, Fazal

    1993-01-01

    The cultural politics of the export of educational services by Australia to Asia are examined, focusing on tension between the persistent economic development perspective and an emerging market ideology that sees education as a commodity. Issues of postcolonialism, globalization, educational traditions vs. market orientation, educational aid and…

  8. The Relative Returns from Research and Teaching: A Market Perspective.

    ERIC Educational Resources Information Center

    Hum, Derek

    2000-01-01

    Employs a market perspective to explain why financial returns to college teaching and research are necessarily unequal. Research will receive greater rewards so long as its market reach is longer, research talent is in shorter supply, and the benefits of research can be partially appropriated by individual scholars. (Contains 13 references.) (MLH)

  9. Loading of Launch Vehicle when Launching from Floating Launch Platform

    NASA Astrophysics Data System (ADS)

    Agarkov, A. V.; Pyrig, V. A.

    2002-01-01

    equator, which is a most effective way from payload capability standpoint. But mobility of the Launch Platform conditions an increase in LV loading as compared with onground launch. Therefore, to provide efficiency of lounching from LP requires solving certain issues to minimize LV loading at launch processing. The paper at hand describes ways to solve these issues while creating and operating the international space launch system Sea Launch, which provides commercial spacecraft launches onboard Zenit-3SL launch vehicle from the floating launch platform located at the equator in the Pacific. Methods to decrease these loads by selecting the optimum position of LP and by correcting LP trim and heel were described. In order to account for impact of weather changing (i.e. waves and winds) and launch support operations on the launch capability, a system of predicted load calculation was designed. By measuring LP roll and pitch parameters as well as wind speed and direction, the system defines loading at LV root section, compares it with the allowable value and, based on the compavision, forms a conclusion on launch capability. launches by Sea Launch.

  10. VEGA, a small launch vehicle

    NASA Astrophysics Data System (ADS)

    Duret, François; Fabrizi, Antonio

    1999-09-01

    Several studies have been performed in Europe aiming to promote the full development of a small launch vehicle to put into orbit one ton class spacecrafts. But during the last ten years, the european workforce was mainly oriented towards the qualification of the heavy class ARIANE 5 launch vehicle.Then, due also to lack of visibility on this reduced segment of market, when comparing with the geosatcom market, no proposal was sufficiently attractive to get from the potentially interrested authorities a clear go-ahead, i.e. a financial committment. The situation is now rapidly evolving. Several european states, among them ITALY and FRANCE, are now convinced of the necessity of the availability of such a transportation system, an important argument to promote small missions, using small satellites. Application market will be mainly scientific experiments and earth observation; some telecommunications applications may be also envisaged such as placement of little LEO constellation satellites, or replacement after failure of big LEO constellation satellites. FIAT AVIO and AEROSPATIALE have proposed to their national agencies the development of such a small launch vehicle, named VEGA. The paper presents the story of the industrial proposal, and the present status of the project: Mission spectrum, technical definition, launch service and performance, target development plan and target recurring costs, as well as the industrial organisation for development, procurement, marketing and operations.

  11. Benefits of Government Incentives for Reusable Launch Vehicle Development

    NASA Technical Reports Server (NTRS)

    Shaw, Eric J.; Hamaker, Joseph W.; Prince, Frank A.

    1998-01-01

    Many exciting new opportunities in space, both government missions and business ventures, could be realized by a reduction in launch prices. Reusable launch vehicle (RLV) designs have the potential to lower launch costs dramatically from those of today's expendable and partially-expendable vehicles. Unfortunately, governments must budget to support existing launch capability, and so lack the resources necessary to completely fund development of new reusable systems. In addition, the new commercial space markets are too immature and uncertain to motivate the launch industry to undertake a project of this magnitude and risk. Low-cost launch vehicles will not be developed without a mature market to service; however, launch prices must be reduced in order for a commercial launch market to mature. This paper estimates and discusses the various benefits that may be reaped from government incentives for a commercial reusable launch vehicle program.

  12. VALUATION OF CLIMATE RELATED NATURAL AMENITIES IN PROPERTY MARKETS

    EPA Science Inventory

    Residential property markets reflect the values people assign to environmental amenities. In particular, such values can be examined through hedonic price models. For example, these models can be used to quantify the economic value of specific measures of weather that contribut...

  13. Compendium of small class ELV capabilities, costs, and constraints. [expendable launch vehicles for commercial spacecraft

    NASA Technical Reports Server (NTRS)

    Poniatowski, Karen S.

    1989-01-01

    Both NASA and DARPA are investigating programs to provide flight demonstration opportunities for new commercially developed rockets. Development of such rockets will be decisive for the success of expendable launch vehicle (ELV) commercialization. The costs and capabilities associated with the various vehicles are discussed here, emphasizing the constraints on their development and widespread utilization. An overview is presented of related international launch vehicle development plans, and the market for small ELVs in the 1990s is discussed.

  14. Launch summary for 1978

    NASA Technical Reports Server (NTRS)

    Vostreys, R. W.

    1978-01-01

    Sounding rocket, satellite, and space probe launchings are presented. Time, date, and location of the launches are provided. The sponsoring countries and the institutions responsible for the launch are listed.

  15. Pioneer Launch on Delta Vehicle

    NASA Technical Reports Server (NTRS)

    1969-01-01

    NASA launches the last in the series of interplanetary Pioneer spacecraft, Pioneer 10 from Cape Kennedy, Florida. The long-tank Delta launch vehicle placed the spacecraft in a solar orbit along the path of Earth's orbit. The spacecraft then passed inside and outside Earth's orbit, alternately speeding up and slowing down relative to Earth. The Delta launch vehicle family started development in 1959. The Delta was composed of parts from the Thor, an intermediate-range ballistic missile, as its first stage, and the Vanguard as its second. The first Delta was launched from Cape Canaveral on May 13, 1960 and was powerful enough to deliver a 100-pound spacecraft into geostationary transfer orbit. Delta has been used to launch civil, commercial, and military satellites into orbit. For more information about Delta, please see Chapter 3 in Roger Launius and Dennis Jenkins' book To Reach the High Frontier published by The University Press of Kentucky in 2002.

  16. A missing link? Workforce demand as the link between two health care related markets.

    PubMed

    Stanwick, S C; Humphreys, J

    1995-01-01

    Examines the links between workforce demand and two health care related markets, the first being the internal market between purchasers and providers of health care, and the second the market for education expressed between colleges of education as providers and NHS Trusts as purchasers of the courses. Workforce demand has to take account of the numbers of people on courses, but also specialist skills required to enable NHS Trusts to deliver changing health care needs of the future. PMID:10153233

  17. Small Space Launch: Origins & Challenges

    NASA Astrophysics Data System (ADS)

    Freeman, T.; Delarosa, J.

    2010-09-01

    The United States Space Situational Awareness capability continues to be a key element in obtaining and maintaining the high ground in space. Space Situational Awareness satellites are critical enablers for integrated air, ground and sea operations, and play an essential role in fighting and winning conflicts. The United States leads the world space community in spacecraft payload systems from the component level into spacecraft, and in the development of constellations of spacecraft. In the area of launch systems that support Space Situational Awareness, despite the recent development of small launch vehicles, the United States launch capability is dominated by an old, unresponsive and relatively expensive set of launchers in the Expandable, Expendable Launch Vehicles (EELV) platforms; Delta IV and Atlas V. The United States directed Air Force Space Command to develop the capability for operationally responsive access to space and use of space to support national security, including the ability to provide critical space capabilities in the event of a failure of launch or on-orbit capabilities. On 1 Aug 06, Air Force Space Command activated the Space Development & Test Wing (SDTW) to perform development, test and evaluation of Air Force space systems and to execute advanced space deployment and demonstration projects to exploit new concepts and technologies, and rapidly migrate capabilities to the warfighter. The SDTW charged the Launch Test Squadron (LTS) with the mission to develop the capability of small space launch, supporting government research and development space launches and missile defense target missions, with operationally responsive spacelift for Low-Earth-Orbit Space Situational Awareness assets as a future mission. This new mission created new challenges for LTS. The LTS mission tenets of developing space launches and missile defense target vehicles were an evolution from the squadrons previous mission of providing sounding rockets under the Rocket

  18. Launch Order, Launch Separation, and Loiter in the Constellation 1 1/2-Launch Solution

    NASA Technical Reports Server (NTRS)

    Stromgren, Chel; Cates, Grant; Cirillo, William

    2009-01-01

    The NASA Constellation Program (CxP) is developing a two-element Earth-to-Orbit launch system to enable human exploration of the Moon. The first element, Ares I, is a human-rated system that consists of a first stage based on the Space Shuttle Program's solid rocket booster (SRB) and an upper stage that consists of a four-crew Orion capsule, a service module, and a Launch Escape System. The second element, Ares V, is a Saturn V-plus category launch system that consists of the core stage with a cluster of six RS-68B engines and augmented with two 5.5-segment SRBs, a Saturn-derived J-2X engine powering an Earth Departure Stage (EDS), and the lunar-lander vehicle payload, Altair. Initial plans called for the Ares V to be launched first, followed the next day by the Ares I. After the EDS performs the final portion of ascent and subsequent orbit circularization, the Orion spacecraft then performs a rendezvous and docks with the EDS and its Altair payload. Following checkout, the integrated stack loiters in low Earth orbit (LEO) until the appropriate Trans-Lunar Injection (TLI) window opportunity opens, at which time the EDS propels the integrated Orion Altair to the Moon. Successful completion of this 1 1/2-launch solution carries risks related to both the orbital lifetime of the assets and the probability of achieving the launch of the second vehicle within the orbital lifetime of the first. These risks, which are significant in terms of overall system design choices and probability of mission success, dictated a thorough reevaluation of the launch strategy, including the order of vehicle launch and the planned time period between launches. The goal of the effort described in this paper was to select a launch strategy that would result in the greatest possible expected system performance, while accounting for launch risks and the cost of increased orbital lifetime. Discrete Event Simulation (DES) model of the launch strategies was created to determine the probability

  19. Should You Know How to Do Marketing, Advertising, & Public Relations Writing?

    ERIC Educational Resources Information Center

    Sides, Charles H.

    1992-01-01

    Argues that technical writers who develop broader writing skills prove to be more valuable to their employers during periods of economic downturn. Offers an overview of the basic skills needed to write marketing, advertising, and public relations documents. (PRA)

  20. Monopsony power and relative wages in the labor market for nurses.

    PubMed

    Hirsch, B T; Schumacher, E J

    1995-10-01

    This paper examines the thesis that monopsony power is an important determinant of wages in nursing labor markets. Using data from the 1985-93 Current Population Surveys, measures of relative nurse/non-nurse wage rates for 252 labor markets are constructed. Contrary to predictions from the monopsony model, no positive relationship exists between relative nursing wages and hospital density or market size. Nor is support found for the presence of monopsony power based on evidence on union wage premiums, slopes of experience profiles, or the mix of RN to total hospital employment. PMID:10153250

  1. Fifth FLTSATCOM to be launched

    NASA Technical Reports Server (NTRS)

    1981-01-01

    Launch of the FLTSATOOM-E, into an elliptical orbit by the Atlas Centaur launch vehicle is announced. The launch and relevant launch operations are described. A chart of the launch sequence for FLTSATCOM-E communication satellite is given.

  2. NASA's Space Launch System Progress Report

    NASA Technical Reports Server (NTRS)

    Singer, Joan A.; Cook, Jerry R.; Lyles, Garry M.; Beaman, David E.

    2011-01-01

    Exploration beyond Earth will be an enduring legacy for future generations, confirming America's commitment to explore, learn, and progress. NASA's Space Launch System (SLS) Program, managed at the Marshall Space Flight Center, is responsible for designing and developing the first exploration-class rocket since the Apollo Program's Saturn V that sent Americans to the Moon. The SLS offers a flexible design that may be configured for the MultiPurpose Crew Vehicle and associated equipment, or may be outfitted with a payload fairing that will accommodate flagship science instruments and a variety of high-priority experiments. Both options support a national capability that will pay dividends for future generations. Building on legacy systems, facilities, and expertise, the SLS will have an initial lift capability of 70 metric tons (mT) and will be evolvable to 130 mT. While commercial launch vehicle providers service the International Space Station market, this capability will surpass all vehicles, past and present, providing the means to do entirely new missions, such as human exploration of asteroids and Mars. With its superior lift capability, the SLS can expand the interplanetary highway to many possible destinations, conducting revolutionary missions that will change the way we view ourselves, our planet and its place in the cosmos. To perform missions such as these, the SLS will be the largest launch vehicle ever built. It is being designed for safety and affordability - to sustain our journey into the space age. Current plans include launching the first flight, without crew, later this decade, with crewed flights beginning early next decade. Development work now in progress is based on heritage space systems and working knowledge, allowing for a relatively quick start and for maturing the SLS rocket as future technologies become available. Together, NASA and the U.S. aerospace industry are partnering to develop this one-of-a-kind asset. Many of NASA's space

  3. A game theoretic model of drug launch in India.

    PubMed

    Bhaduri, Saradindu; Ray, Amit Shovon

    2006-01-01

    There is a popular belief that drug launch is delayed in developing countries like India because of delayed transfer of technology due to a 'post-launch' imitation threat through weak intellectual property rights (IPR). In fact, this belief has been a major reason for the imposition of the Trade Related Intellectual Property Rights regime under the WTO. This construct undermines the fact that in countries like India, with high reverse engineering capabilities, imitation can occur even before the formal technology transfer, and fails to recognize the first mover advantage in pharmaceutical markets. This paper argues that the first mover advantage is important and will vary across therapeutic areas, especially in developing countries with diverse levels of patient enlightenment and quality awareness. We construct a game theoretic model of incomplete information to examine the delay in drug launch in terms of costs and benefits of first move, assumed to be primarily a function of the therapeutic area of the new drug. Our model shows that drug launch will be delayed only for external (infective/communicable) diseases, while drugs for internal, non-communicable diseases (accounting for the overwhelming majority of new drug discovery) will be launched without delay. PMID:18634701

  4. Digital Public Relations: E-Marketing's Big Secret

    ERIC Educational Resources Information Center

    Gifford, Janet

    2010-01-01

    Online programs and courses are established presences in higher education, and so are processes such as online registration. Prospective students routinely turn to the web for information to help them decide on the most appropriate programs for their situation. Digital public relations (digital PR) is rapidly becoming one of the cornerstones of an…

  5. Cost and Economics for Advanced Launch Vehicles

    NASA Technical Reports Server (NTRS)

    Whitfield, Jeff

    1998-01-01

    Market sensitivity and weight-based cost estimating relationships are key drivers in determining the financial viability of advanced space launch vehicle designs. Due to decreasing space transportation budgets and increasing foreign competition, it has become essential for financial assessments of prospective launch vehicles to be performed during the conceptual design phase. As part of this financial assessment, it is imperative to understand the relationship between market volatility, the uncertainty of weight estimates, and the economic viability of an advanced space launch vehicle program. This paper reports the results of a study that evaluated the economic risk inherent in market variability and the uncertainty of developing weight estimates for an advanced space launch vehicle program. The purpose of this study was to determine the sensitivity of a business case for advanced space flight design with respect to the changing nature of market conditions and the complexity of determining accurate weight estimations during the conceptual design phase. The expected uncertainty associated with these two factors drives the economic risk of the overall program. The study incorporates Monte Carlo simulation techniques to determine the probability of attaining specific levels of economic performance when the market and weight parameters are allowed to vary. This structured approach toward uncertainties allows for the assessment of risks associated with a launch vehicle program's economic performance. This results in the determination of the value of the additional risk placed on the project by these two factors.

  6. IRIS Launch Animation

    NASA Video Gallery

    This animation demonstrates the launch and deployment of NASA's Interface Region Imaging Spectrograph (IRIS) mission satellite via a Pegasus rocket. The launch is scheduled for June 26, 2013 from V...

  7. Space Launch System Animation

    NASA Video Gallery

    NASA is ready to move forward with the development of the Space Launch System -- an advanced heavy-lift launch vehicle that will provide an entirely new national capability for human exploration be...

  8. Shuttle Era: Launch Directors

    NASA Video Gallery

    A space shuttle launch director is the leader of the complex choreography that goes into a shuttle liftoff. Ten people have served as shuttle launch directors, making the final decision whether the...

  9. Marketing nutrition & health-related benefits of food & beverage products: enforcement, litigation & liability issues.

    PubMed

    Roller, Sarah; Pippins, Raqiyyah

    2010-01-01

    Over the past decade, the liability risks associated with food and beverage product marketing have increased significantly, particularly with respect to nutrition and health-related product benefit claims. FDA and FTC enforcement priorities appear to have contributed to the increasing liability trends that are associated with these nutrition and health-related claims. This article examines key enforcement and litigation developments involving conventional food and beverage product marketing claims during the first 18 months of President Obama's administration: Part I considers FDA enforcement priorities and recent warning letters; Part II considers FTC enforcement priorities, warning letters, and consent orders; and Part III considers the relationship between FDA and FTC enforcement priorities and recent false advertising cases brought by private parties challenging nutrition and health-related marketing claims for food and beverage products. The article makes recommendations concerning ways in which food and beverage companies can help minimize liability risks associated with health-related marketing claims. In addition, the article suggests that federal policy reforms may be required to counter the perverse chilling effects current food liability trends appear to be having on health-related marketing claims for food and beverage products, and proposes a number of specific reforms that would help encourage the responsible use of well-substantiated marketing claims that can help foster healthy dietary practices. In view of the obesity prevention and other diet-related public health priorities of the Obama administration, the article suggests that this is an opportune time to address the apparent chilling effects increasing food liability risks are having on nutrition and health-related marketing claims for healthy food and beverage products, and potential adverse consequences for public health. PMID:24479235

  10. Launch Vehicle Operations Simulator

    NASA Technical Reports Server (NTRS)

    Blackledge, J. W.

    1974-01-01

    The Saturn Launch Vehicle Operations Simulator (LVOS) was developed for NASA at Kennedy Space Center. LVOS simulates the Saturn launch vehicle and its ground support equipment. The simulator was intended primarily to be used as a launch crew trainer but it is also being used for test procedure and software validation. A NASA/contractor team of engineers and programmers implemented the simulator after the Apollo XI lunar landing during the low activity periods between launches.

  11. Heroin-related overdose: The unexplored influences of markets, marketing and source-types in the United States.

    PubMed

    Mars, Sarah G; Fessel, Jason N; Bourgois, Philippe; Montero, Fernando; Karandinos, George; Ciccarone, Daniel

    2015-09-01

    Heroin overdose, more accurately termed 'heroin-related overdose' due to the frequent involvement of other drugs, is the leading cause of mortality among regular heroin users. (Degenhardt et al., 2010) Heroin injectors are at greater risk of hospital admission for heroin-related overdose (HOD) in the eastern United States where Colombian-sourced powder heroin is sold than in the western US where black 'tar' heroin predominates. (Unick et al., 2014) This paper examines under-researched influences on HOD, both fatal and non-fatal, using data from a qualitative study of injecting drug users of black tar heroin in San Francisco and powder heroin in Philadelphia Data were collected through in-depth, semi-structured interviews carried out in 2012 that were conducted against a background of longer-term participant-observation, ethnographic studies of drug users and dealers in Philadelphia (2007-12) and of users in San Francisco (1994-2007, 2012). Our findings suggest three types of previously unconsidered influences on overdose risk that arise both from structural socio-economic factors and from the physical properties of the heroin source-types: 1) retail market structure including information flow between users; 2) marketing techniques such as branding, free samples and pricing and 3) differences in the physical characteristics of the two major heroin source forms and how they affect injecting techniques and vascular health. Although chosen for their contrasting source-forms, we found that the two cities have contrasting dominant models of drug retailing: San Francisco respondents tended to buy through private dealers and Philadelphia respondents frequented an open-air street market where heroin is branded and free samples are distributed, although each city included both types of drug sales. These market structures and marketing techniques shape the availability of information regarding heroin potency and its dissemination among users who tend to seek out the

  12. Heroin-related overdose: The unexplored influences of markets, marketing and source-types in the United States

    PubMed Central

    Mars, Sarah G.; Fessel, Jason N.; Bourgois, Philippe; Montero, Fernando; Karandinos, George; Ciccarone, Daniel

    2015-01-01

    Heroin overdose, more accurately termed ‘heroin-related overdose’ due to the frequent involvement of other drugs, is the leading cause of mortality among regular heroin users. (Degenhardt et al., 2010) Heroin injectors are at greater risk of hospital admission for heroin-related overdose (HOD) in the eastern United States where Colombian-sourced powder heroin is sold than in the western US where black ‘tar’ heroin predominates. (Unick et al., 2014) This paper examines under-researched influences on HOD, both fatal and non-fatal, using data from a qualitative study of injecting drug users of black tar heroin in San Francisco and powder heroin in Philadelphia Data were collected through in-depth, semi-structured interviews carried out in 2012 that were conducted against a background of longer-term participant-observation, ethnographic studies of drug users and dealers in Philadelphia (2007–12) and of users in San Francisco (1994–2007, 2012). Our findings suggest three types of previously unconsidered influences on overdose risk that arise both from structural socio-economic factors and from the physical properties of the heroin source-types: 1) retail market structure including information flow between users; 2) marketing techniques such as branding, free samples and pricing and 3) differences in the physical characteristics of the two major heroin source forms and how they affect injecting techniques and vascular health. Although chosen for their contrasting source-forms, we found that the two cities have contrasting dominant models of drug retailing: San Francisco respondents tended to buy through private dealers and Philadelphia respondents frequented an open-air street market where heroin is branded and free samples are distributed, although each city included both types of drug sales. These market structures and marketing techniques shape the availability of information regarding heroin potency and its dissemination among users who tend to seek out

  13. Launch Summary for 1979

    NASA Technical Reports Server (NTRS)

    Vostreys, R. W.

    1980-01-01

    Spacecraft launching for 1979 are identified and listed under the categories of (1) sounding rockets, and (2) artificial Earth satellites and space probes. The sounding rockets section includes a listing of the experiments, index of launch sites and tables of the meanings and codes used in the launch listing.

  14. Launch summary for 1980

    NASA Technical Reports Server (NTRS)

    Vostreys, R. W.

    1981-01-01

    Sounding rockets, artificial Earth satellites, and space probes launched betweeen January 1 and December 31, 1980 are listed. Data tabulated for the rocket launchings show launching site, instruments carried, date of launch, agency rocket identification, sponsoring country, experiment discipline, peak altitude, and the experimenter or institution responsible. Tables for satellites and space probes show COSPAR designation, spacecraft name, country, launch date, epoch date, orbit type, apoapsis, periapsis and inclination period. The functions and responsibilities of the World Data Center and the areas of scientific interest at the seven subcenters are defined. An alphabetical listing of experimenters using the sounding rockets is also provided.

  15. Case studies on employment-related health inequalities in countries representing different types of labor markets.

    PubMed

    Kim, Il-Ho; Muntaner, Carles; Chung, Haejoo; Benach, Joan

    2010-01-01

    The authors selected nine case studies, one country from each cluster of their labor market inequalities typology, to outline the macro-political and economic roots of employment relations and their impacts on health. These countries illustrate variations in labor markets and health, categorized into a global empirical typology. The case studies illustrated that workers' health is significantly connected with labor market characteristics and the welfare system. For a core country, the labor market is characterized by a formal sector. The labor institutions of Sweden traditionally have high union density and collective bargaining coverage and a universal health care system, which correlate closely with positive health, in comparison with Spain and the United States. For a semi-periphery country, the labor market is delineated by a growing informal economy. Although South Korea, Venezuela, and El Salvador provide some social welfare benefits, a high proportion of irregular and informal workers are excluded from these benefits and experience hazardous working conditions that adversely affect their health. Lastly, several countries in the global periphery--China, Nigeria, and Haiti--represent informal work and severe labor market insecurity. In the absence of labor market regulations, the majority of their workers toil in the informal sector in unsafe conditions with inadequate health care. PMID:20440969

  16. Aspirations and Capabilities of Rural Youth in Relation to Present and Projected Labor Market Requirements.

    ERIC Educational Resources Information Center

    Jordan, Max F.; And Others

    A study was conducted to: determine the aspirations and capabilities of rural youth in selected low-income counties in Arkansas; relate aspirations, capabilities, and the discrepancy between the two to the experience background of the youths studied; and relate the youths' occupational plans to present and projected labor market requirements. The…

  17. The New Rules of PR and Marketing: A Teaching Unit for College Public Relations Programs

    ERIC Educational Resources Information Center

    Mauldin, Candice

    2011-01-01

    The purpose of this lesson plan is to introduce the importance of social media and the Internet on public relations and marketing. The lesson describes the new rules for public relations versus the old rules. It is a more in depth look at how, and why, to use blogging, social media, and the Internet for promoting a company and appealing to buyers.…

  18. Electron launching voltage monitor

    DOEpatents

    Mendel, C.W.; Savage, M.E.

    1992-03-17

    An electron launching voltage monitor measures MITL voltage using a relationship between anode electric field and electron current launched from a cathode-mounted perturbation. An electron launching probe extends through and is spaced from the edge of an opening in a first MITL conductor, one end of the launching probe being in the gap between the MITL conductor, the other end being adjacent a first side of the first conductor away from the second conductor. A housing surrounds the launching probe and electrically connects the first side of the first conductor to the other end of the launching probe. A detector detects the current passing through the housing to the launching probe, the detected current being representative of the voltage between the conductors. 5 figs.

  19. Electron launching voltage monitor

    DOEpatents

    Mendel, Clifford W.; Savage, Mark E.

    1992-01-01

    An electron launching voltage monitor measures MITL voltage using a relationship between anode electric field and electron current launched from a cathode-mounted perturbation. An electron launching probe extends through and is spaced from the edge of an opening in a first MITL conductor, one end of the launching probe being in the gap between the MITL conductor, the other end being adjacent a first side of the first conductor away from the second conductor. A housing surrounds the launching probe and electrically connects the first side of the first conductor to the other end of the launching probe. A detector detects the current passing through the housing to the launching probe, the detected current being representative of the voltage between the conductors.

  20. Launch Services, a Proven Model

    NASA Astrophysics Data System (ADS)

    Trafton, W. C.; Simpson, J.

    2002-01-01

    From a commercial perspective, the ability to justify "leap frog" technology such as reusable systems has been difficult to justify because the estimated 5B to 10B investment is not supported in the current flat commercial market coupled with an oversupply of launch service suppliers. The market simply does not justify investment of that magnitude. Currently, next generation Expendable Launch Systems, including Boeing's Delta IV, Lockheed Martin's Atlas 5, Ariane V ESCA and RSC's H-IIA are being introduced into operations signifying that only upgrades to proven systems are planned to meet the changes in anticipated satellite demand (larger satellites, more lifetime, larger volumes, etc.) in the foreseeable future. We do not see a new fleet of ELVs emerging beyond that which is currently being introduced, only continuous upgrades of the fleet to meet the demands. To induce a radical change in the provision of launch services, a Multinational Government investment must be made and justified by World requirements. The commercial market alone cannot justify such an investment. And if an investment is made, we cannot afford to repeat previous mistakes by relying on one system such as shuttle for commercial deployment without having any back-up capability. Other issues that need to be considered are national science and security requirements, which to a large extent fuels the Japanese, Chinese, Indian, Former Soviet Union, European and United States space transportation entries. Additionally, this system must support or replace current Space Transportation Economies with across-the-board benefits. For the next 10 to 20 years, Multinational cooperation will be in the form of piecing together launch components and infrastructure to supplement existing launch systems and reducing the amount of non-recurring investment while meeting the future requirements of the End-User. Virtually all of the current systems have some form of multinational participation: Sea Launch

  1. Employment relations and global health: a typological study of world labor markets.

    PubMed

    Chung, Haejoo; Muntaner, Carles; Benach, Joan

    2010-01-01

    In this study, the authors investigate the global labor market and employment relations, which are central building blocks of the welfare state; the aim is to propose a global typology of labor markets to explain global inequalities in population health. Countries are categorized into core (21), semi-peripheral (42), and peripheral (71) countries, based on gross national product per capita (Atlas method). Labor market-related variables and factors are then used to generate clusters of countries with principal components and cluster analysis methods. The authors then examine the relationship between the resulting clusters and health outcomes. The clusters of countries are largely geographically defined, each cluster with similar historical background and developmental strategy. However, there are interesting exceptions, which warrant further elaboration. The relationship between health outcomes and clusters largely follows the authors' expectations (except for communicable diseases): more egalitarian labor institutions have better health outcomes. The world system, then, can be divided according to different types of labor markets that are predictive of population health outcomes at each level of economic development. As is the case for health and social policies, variability in labor market characteristics is likely to reflect, in part, the relative strength of a country's political actors. PMID:20440968

  2. Space Shuttle Launch Probability Analysis: Understanding History so We Can Predict the Future

    NASA Technical Reports Server (NTRS)

    Cates, Grant R.

    2014-01-01

    The Space Shuttle was launched 135 times and nearly half of those launches required 2 or more launch attempts. The Space Shuttle launch countdown historical data of 250 launch attempts provides a wealth of data that is important to analyze for strictly historical purposes as well as for use in predicting future launch vehicle launch countdown performance. This paper provides a statistical analysis of all Space Shuttle launch attempts including the empirical probability of launch on any given attempt and the cumulative probability of launch relative to the planned launch date at the start of the initial launch countdown. This information can be used to facilitate launch probability predictions of future launch vehicles such as NASA's Space Shuttle derived SLS. Understanding the cumulative probability of launch is particularly important for missions to Mars since the launch opportunities are relatively short in duration and one must wait for 2 years before a subsequent attempt can begin.

  3. 66. DETAIL OF LAUNCH CONDUCTOR AND ASSISTANT LAUNCH CONDUCTOR PANELS ...

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

    66. DETAIL OF LAUNCH CONDUCTOR AND ASSISTANT LAUNCH CONDUCTOR PANELS IN CONSOLE LOCATED CENTRALLY IN SLC-3E CONTROL ROOM. FROM LEFT TO RIGHT IN BACKGROUND: LAUNCH OPERATOR, LAUNCH ANALYST, AND FACILITIES PANELS. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Operations Building, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  4. Launch facilities as infrastructure

    NASA Astrophysics Data System (ADS)

    Trial, Mike

    The idea is put forth that launch facilities in the U.S. impose inefficiencies on launch service providers due to the way they have been constructed. Rather than constructing facilities for a specific program, then discarding them when the program is complete, a better use of the facilities investment would be in constructing facilities flexible enough for use by multiple vehicle types over the course of a 25-year design lifetime. The planned National Launch System (NLS) program offers one possible avenue for the federal government to provide a nucleus of launch infrastructure which can improve launch efficiencies. The NLS goals are to develop a new space launch system to meet civil and national needs. The new system will be jointly funded by DOD and NASA but will actively consider commercial space needs. The NLS will improve reliability, responsiveness, and mission performance, and reduce operating costs. The specifics of the infrastructure concept are discussed.

  5. Launch Services Safety Overview

    NASA Technical Reports Server (NTRS)

    Loftin, Charles E.

    2008-01-01

    NASA/KSC Launch Services Division Safety (SA-D) services include: (1) Assessing the safety of the launch vehicle (2) Assessing the safety of NASA ELV spacecraft (S/C) / launch vehicle (LV) interfaces (3) Assessing the safety of spacecraft processing to ensure resource protection of: - KSC facilities - KSC VAFB facilities - KSC controlled property - Other NASA assets (4) NASA personnel safety (5) Interfacing with payload organizations to review spacecraft for adequate safety implementation and compliance for integrated activities (6) Assisting in the integration of safety activities between the payload, launch vehicle, and processing facilities

  6. Kestrel balloon launch system

    SciTech Connect

    Newman, M.J.

    1991-10-01

    Kestrel is a high-altitude, Helium-gas-filled-balloon system used to launch scientific payloads in winds up to 20 knots, from small platforms or ships, anywhere over land or water, with a minimal crew and be able to hold in standby conditions. Its major components consist of two balloons (a tow balloon and a main balloon), the main deployment system, helium measurement system, a parachute recovery unit, and the scientific payload package. The main scope of the launch system was to eliminate the problems of being dependent of launching on long airfield runways, low wind conditions, and long launch preparation time. These objectives were clearly met with Kestrel 3.

  7. GPM: Waiting for Launch

    NASA Video Gallery

    The Global Precipitation Measurement mission's Core Observatory is poised for launch from the Japan Aerospace Exploration Agency's Tanegashima Space Center, scheduled for the afternoon of Feb. 27, ...

  8. Community Colleges and Labor Market Conditions: How Does Enrollment Demand Change Relative to Local Unemployment Rates?

    ERIC Educational Resources Information Center

    Hillman, Nicholas W.; Orians, Erica Lee

    2013-01-01

    This study uses fixed-effects panel data techniques to estimate the elasticity of community college enrollment demand relative to local unemployment rates. The findings suggest that community college enrollment demand is counter-cyclical to changes in the labor market, as enrollments rise during periods of weak economic conditions. Using national…

  9. 36 CFR 223.52 - Market-related contract term additions.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... 36 Parks, Forests, and Public Property 2 2011-07-01 2011-07-01 false Market-related contract term additions. 223.52 Section 223.52 Parks, Forests, and Public Property FOREST SERVICE, DEPARTMENT OF AGRICULTURE SALE AND DISPOSAL OF NATIONAL FOREST SYSTEM TIMBER, SPECIAL FOREST PRODUCTS, AND FOREST...

  10. 36 CFR 223.52 - Market-related contract term additions.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... 36 Parks, Forests, and Public Property 2 2013-07-01 2013-07-01 false Market-related contract term additions. 223.52 Section 223.52 Parks, Forests, and Public Property FOREST SERVICE, DEPARTMENT OF AGRICULTURE SALE AND DISPOSAL OF NATIONAL FOREST SYSTEM TIMBER, SPECIAL FOREST PRODUCTS, AND FOREST...

  11. 36 CFR 223.52 - Market-related contract term additions.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... 36 Parks, Forests, and Public Property 2 2012-07-01 2012-07-01 false Market-related contract term additions. 223.52 Section 223.52 Parks, Forests, and Public Property FOREST SERVICE, DEPARTMENT OF AGRICULTURE SALE AND DISPOSAL OF NATIONAL FOREST SYSTEM TIMBER, SPECIAL FOREST PRODUCTS, AND FOREST...

  12. 36 CFR 223.52 - Market-related contract term additions.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... 36 Parks, Forests, and Public Property 2 2014-07-01 2014-07-01 false Market-related contract term additions. 223.52 Section 223.52 Parks, Forests, and Public Property FOREST SERVICE, DEPARTMENT OF AGRICULTURE SALE AND DISPOSAL OF NATIONAL FOREST SYSTEM TIMBER, SPECIAL FOREST PRODUCTS, AND FOREST...

  13. Individualism, Inspiration and Personal Market as Related to Education and the Workplace.

    ERIC Educational Resources Information Center

    Fusch, Gene E.

    A review of human investment in education considers the pivotal human capital theory in relation to complementary, replacement, and opposing hypotheses and the interrelationship of workers, education, and workplace production. Analysis of definitions of human capital concludes that it is the marketable value of an individual that additional…

  14. Perceived Needs of Recent Graduates for Marketing-Related Knowledge and Skills: Implications for Pharmacy Education.

    ERIC Educational Resources Information Center

    Rupp, Michael T.; Szkudlarek, Beth A.

    1991-01-01

    A survey of 215 recent graduates of Purdue University School of Pharmacy investigated unmet needs for 9 marketing skill areas: measuring and forecasting demand; personal selling; public relations; purchasing and inventory control; strategic planning; managed care organizations; physician dispensing; physician prescribing and health care financers;…

  15. Career Effects of Occupation-Related Vocational Education: Evidence from the Military's Internal Labor Market

    ERIC Educational Resources Information Center

    Pema, Elda; Mehay, Stephen

    2012-01-01

    Prior research on the labor market success of secondary vocational education has produced mixed results, with several studies finding wage gains only for individuals who work in training-related occupations. We contribute to this debate by focusing on a single occupation and organization and by comparing the careers of employees with and without…

  16. Launch processing system concept to reality

    NASA Technical Reports Server (NTRS)

    Bailey, W. W.

    1985-01-01

    The Launch Processing System represents Kennedy Space Center's role in providing a major integrated hardware and software system for the test, checkout and launch of a new space vehicle. Past programs considered the active flight vehicle to ground interfaces as part of the flight systems and therefore the related ground system was provided by the Development Center. The major steps taken to transform the Launch Processing System from a concept to reality with the successful launches of the Shuttle Programs Space Transportation System are addressed.

  17. The Delta Launch Vehicle Model 2914 Series

    NASA Technical Reports Server (NTRS)

    Gunn, C. R.

    1973-01-01

    The newest Delta launch vehicle configuration, Model 2914 is described for potential users together with recent flight results. A functional description of the vehicle, its performance, flight profile, flight environment, injection accuracy, spacecraft integration requirements, user organizational interfaces, launch operations, costs and reimbursable users payment plan are provided. The versatile, relatively low cost Delta has a flight demonstrated reliability record of 92 percent that has been established in 96 launches over twelve years while concurrently undergoing ten major upratings to keep pace with the ever increasing performance and reliability requirements of its users. At least 40 more launches are scheduled over the next three years from the Eastern and Western Test Ranges.

  18. A typology of health marketing research methods--combining public relations methods with organizational concern.

    PubMed

    Rotarius, Timothy; Wan, Thomas T H; Liberman, Aaron

    2007-01-01

    Research plays a critical role throughout virtually every conduit of the health services industry. The key terms of research, public relations, and organizational interests are discussed. Combining public relations as a strategic methodology with the organizational concern as a factor, a typology of four different research methods emerges. These four health marketing research methods are: investigative, strategic, informative, and verification. The implications of these distinct and contrasting research methods are examined. PMID:19042536

  19. Launch Collision Probability

    NASA Technical Reports Server (NTRS)

    Bollenbacher, Gary; Guptill, James D.

    1999-01-01

    This report analyzes the probability of a launch vehicle colliding with one of the nearly 10,000 tracked objects orbiting the Earth, given that an object on a near-collision course with the launch vehicle has been identified. Knowledge of the probability of collision throughout the launch window can be used to avoid launching at times when the probability of collision is unacceptably high. The analysis in this report assumes that the positions of the orbiting objects and the launch vehicle can be predicted as a function of time and therefore that any tracked object which comes close to the launch vehicle can be identified. The analysis further assumes that the position uncertainty of the launch vehicle and the approaching space object can be described with position covariance matrices. With these and some additional simplifying assumptions, a closed-form solution is developed using two approaches. The solution shows that the probability of collision is a function of position uncertainties, the size of the two potentially colliding objects, and the nominal separation distance at the point of closest approach. ne impact of the simplifying assumptions on the accuracy of the final result is assessed and the application of the results to the Cassini mission, launched in October 1997, is described. Other factors that affect the probability of collision are also discussed. Finally, the report offers alternative approaches that can be used to evaluate the probability of collision.

  20. Asset price and trade volume relation in artificial market impacted by value investors

    NASA Astrophysics Data System (ADS)

    Tangmongkollert, K.; Suwanna, S.

    2016-05-01

    The relationship between return and trade volume has been of great interests in a financial market. The appearance of asymmetry in the price-volume relation in the bull and bear market is still unsettled. We present a model of the value investor traders (VIs) in the double auction system, in which agents make trading decision based on the pseudo fundamental price modelled by sawtooth oscillations. We investigate the system by two different time series for the asset fundamental price: one corresponds to the fundamental price in a growing phase; and the other corresponds to that in a declining phase. The simulation results show that the trade volume is proportional to the difference between the market price and the fundamental price, and that there is asymmetry between the buying and selling phases. Furthermore, the selling phase has more significant impact of price on the trade volume than the buying phase.

  1. Cost effective launch technology for communications satellites

    NASA Astrophysics Data System (ADS)

    Taylor, T. C.; Overman, A.

    1984-10-01

    The present investigation is concerned with the possibility to reduce the costs for placing satellites in orbit by making use of an 'Air Launch' system. It is pointed out that the launching of rockets to orbit from aircraft in flight has been done successfully. It is suggested to modify the existing technology for the purpose of launching communications satellites and other payloads to orbit. Thus, the Air Launch Concept combines aircraft and missile technologies to produce a method of transport to orbit. A heavy lift cargo aircraft is employed to fly a rocket and the satellite payload to a specific location at the service ceiling of the aircraft. Attention is given to aspects of cost reduction, commercial and technical benefits, the anticipated market, and technical details.

  2. NASA launch schedule

    NASA Astrophysics Data System (ADS)

    Bell, Peter M.

    The National Aeronautics and Space Administration (NASA) has a record-setting launch schedule for 1984—10 space shuttle flights (see Table 1), 10 satellite deployments from the space shuttle in orbit and 12 unmanned missions using expendable launch vehicles. Also scheduled is the launch on March 1 for the National Oceanic and Atmospheric Administration of Landsat D‧, the nation's second earth resources satellite.The launch activity will begin February 3 with the launch of shuttle mission 41-B using the orbiter Challenger. Two communications satellites will be deployed from 41-B: Westar-VI, for Western Union, and Palapa B-2 for the government of Indonesia. The 8-day mission will feature the first shuttle landing at Kennedy Space Center in Florida; and the first flight of the Manned Maneuvering Unit, a self-contained, propulsive backpack that will allow astronauts to move about in space without being tethered to the spacecraft.

  3. Gambling disorder in financial markets: Clinical and treatment-related features

    PubMed Central

    Shin, Young-Chul; Choi, Sam-Wook; Ha, Juwon; Choi, Jung-Seok; Kim, Dai-Jin

    2015-01-01

    Background and Aims To date, few studies have examined the clinical manifestation of disordered gamblers in financial markets. This study examined the differences in the clinical and treatment-related features of gambling disorder between financial markets and horse races. Methods Subjects who met the DSM-IV criteria for pathological gambling (PG) and who sought treatment were assessed by retrospective chart review. One hundred forty-four subjects were included in this sample, which consisted of the following groups: financial markets (n = 45; 28.6%) and horse races (n = 99; 71.4%). Results Multiple similar manifestations were found between the groups, including severity of PG, age of PG onset, amounts of gambling debts, drinking days per week, depressive mood, duration of seeking treatment after the onset of PG, and treatment follow-up duration. However, disordered gamblers who invested in the financial market were significantly more likely to be educated (p = 0.003), live with their spouses (p = 0.007), have full-time jobs (p = 0.006), and they were more likely to participate in the first type of gambling than the horse races group (p<0.001). Furthermore, the financial markets group received the anti-craving medication less often than the horse races group (p = 0.04). Discussion and Conclusions: These findings suggest that disordered gamblers in financial markets show different socio-demographic, clinical and treatment-related features compared with the horse race gamblers, despite a similar severity of gambling disorder. Understanding these differential manifestations may provide insight into prevention and treatment development for specific types of gambling. PMID:26690619

  4. [Study on supply and demand relation based on two stages division of market of Chinese materia medica].

    PubMed

    Yang, Guang; Guo, Lan-Ping; Wang, Nuo; Zeng, Yan; Huang, Lu-Qi

    2014-01-01

    The complex production processes and long industrial chain in traditional Chinese medicine (TCM) market result in difficulty in Chinese market microstructure research. Based on the defining the logical relationships among different concepts. This paper divides TCM market into two stages as Chinese materia medica resource market and traditional Chinese Patent Medicines market. Under this foundation, we investigated the supply capacity, approaching rules and motivation system of suppliers in TCM market, analyzed the demand situation in the perspective of demand side, and evaluated the purchasing power in terms of population profile, income, and insurance. Furthermore we also analyzed the price formation mechanism in two stages of TCM market. We hope this study can make a positive and promotion effect on TCM market related research. PMID:24761655

  5. Launch Pad in a Box

    NASA Technical Reports Server (NTRS)

    Mantovani, J. G.; Tamasy, G. J.; Mueller, R. P.; Townsend, I. I.; Sampson, J. W.; Lane, M. A.

    2016-01-01

    NASA Kennedy Space Center (KSC) is developing a new deployable launch system capability to support a small class of launch vehicles for NASA and commercial space companies to test and launch their vehicles. The deployable launch pad concept was first demonstrated on a smaller scale at KSC in 2012 in support of NASA Johnson Space Center's Morpheus Lander Project. The main objective of the Morpheus Project was to test a prototype planetary lander as a vertical takeoff and landing test-bed for advanced spacecraft technologies using a hazard field that KSC had constructed at the Shuttle Landing Facility (SLF). A steel pad for launch or landing was constructed using a modular design that allowed it to be reconfigurable and expandable. A steel flame trench was designed as an optional module that could be easily inserted in place of any modular steel plate component. The concept of a transportable modular launch and landing pad may also be applicable to planetary surfaces where the effects of rocket exhaust plume on surface regolith is problematic for hardware on the surface that may either be damaged by direct impact of high speed dust particles, or impaired by the accumulation of dust (e.g., solar array panels and thermal radiators). During the Morpheus free flight campaign in 2013-14, KSC performed two studies related to rocket plume effects. One study compared four different thermal ablatives that were applied to the interior of a steel flame trench that KSC had designed and built. The second study monitored the erosion of a concrete landing pad following each landing of the Morpheus vehicle on the same pad located in the hazard field. All surfaces of a portable flame trench that could be directly exposed to hot gas during launch of the Morpheus vehicle were coated with four types of ablatives. All ablative products had been tested by NASA KSC and/or the manufacturer. The ablative thicknesses were measured periodically following the twelve Morpheus free flight tests

  6. 65. DETAIL OF ASSISTANT LAUNCH CONTROLLER AND LAUNCH CONTROLLER PANELS ...

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

    65. DETAIL OF ASSISTANT LAUNCH CONTROLLER AND LAUNCH CONTROLLER PANELS LOCATED NEAR CENTER OF SLC-3E CONTROL ROOM. NOTE 30-CHANNEL COMMUNICATIONS PANELS. PAYLOAD ENVIRONMENTAL CONTROL AND MONITORING PANELS (LEFT) AND LAUNCH OPERATORS PANEL (RIGHT) IN BACKGROUND. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Operations Building, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  7. Electromagnetic launch of lunar material

    NASA Technical Reports Server (NTRS)

    Snow, William R.; Kolm, Henry H.

    1992-01-01

    Lunar soil can become a source of relatively inexpensive oxygen propellant for vehicles going from low Earth orbit (LEO) to geosynchronous Earth orbit (GEO) and beyond. This lunar oxygen could replace the oxygen propellant that, in current plans for these missions, is launched from the Earth's surface and amounts to approximately 75 percent of the total mass. The reason for considering the use of oxygen produced on the Moon is that the cost for the energy needed to transport things from the lunar surface to LEO is approximately 5 percent the cost from the surface of the Earth to LEO. Electromagnetic launchers, in particular the superconducting quenchgun, provide a method of getting this lunar oxygen off the lunar surface at minimal cost. This cost savings comes from the fact that the superconducting quenchgun gets its launch energy from locally supplied, solar- or nuclear-generated electrical power. We present a preliminary design to show the main features and components of a lunar-based superconducting quenchgun for use in launching 1-ton containers of liquid oxygen, one every 2 hours. At this rate, nearly 4400 tons of liquid oxygen would be launched into low lunar orbit in a year.

  8. GPM Launch Coverage

    NASA Video Gallery

    A Japanese H-IIA rocket with the NASA-Japan Aerospace Exploration Agency (JAXA) Global Precipitation Measurement (GPM) Core Observatory aboard, launched from the Tanegashima Space Center in Japan o...

  9. Advanced launch system

    NASA Technical Reports Server (NTRS)

    Monk, Jan C.

    1991-01-01

    The Advanced Launch System (ALS) is presented. The costs, reliability, capabilities, infrastructure are briefly described. Quality approach, failure modes, structural design, technology benefits, and key facilities are outlined. This presentation is represented by viewgraphs.

  10. Expedition 27 Launch

    NASA Video Gallery

    NASA astronaut Ron Garan and Russian cosmonauts Andrey Borisenko and Alexander Samokutyaev launch in their Soyuz TMA-21 spacecraft from the Baikonur Cosmodrome in Kazakhstan on April 4, 2011 (April...

  11. IRVE 3 Launch

    NASA Video Gallery

    The Inflatable Reentry Vehicle Experiment, or IRVE-3, launched on July 23, 2012, from NASA's Wallops Flight Facility. The purpose of the IRVE-3 test was to show that a space capsule can use an infl...

  12. Launch of Juno!

    NASA Video Gallery

    An Atlas V rocket lofted the Juno spacecraft toward Jupiter from Space Launch Complex-41. The 4-ton Juno spacecraft will take five years to reach Jupiter on a mission to study its structure and dec...

  13. Commercial space launches

    NASA Astrophysics Data System (ADS)

    Robb, David W.

    1984-04-01

    While the space shuttle is expected to be the principle Space Transportation System (STS) of the United States, the Reagan Administration is moving ahead with the President's declared space policy of encouraging private sector operation of expendable launch vehicles (ELV's). With the signing of the “Commercial Space Launch Law” on October 30, the administration hopes that it has opened up the door for commercial ventures into space by streamlining regulations and coordinating applications for launches. The administration considers the development and operation of private sector ELV's as an important part of an overall U.S. space policy, complementing the space shuttle and government ELV's. The law follows by nearly a year the creation of the Office of Commercial Space Transportation at the U.S. Department of Transportation (DOT), which will coordinate applications for commercial space launches.

  14. Genomic Data Commons launches

    Cancer.gov

    The Genomic Data Commons (GDC), a unified data system that promotes sharing of genomic and clinical data between researchers, launched today with a visit from Vice President Joe Biden to the operations center at the University of Chicago.

  15. Hi-C Launch

    NASA Video Gallery

    The High resolution Coronal Imager (Hi-C) was launched on a NASA Black Brant IX two-stage rocket from White Sands Missile Range in New Mexico July 11, 2012. The experiment reached a maximum velocit...

  16. Anchor Trial Launch

    Cancer.gov

    NCI has launched a multicenter phase III clinical trial called the ANCHOR Study -- Anal Cancer HSIL (High-grade Squamous Intraepithelial Lesion) Outcomes Research Study -- to determine if treatment of HSIL in HIV-infected individuals can prevent anal canc

  17. NASA Now: Glory Launch

    NASA Video Gallery

    In this episode of NASA Now, Dr. Hal Maring joins us to explain why the upcoming launch of the Glory satellite is so important to further our understanding of climate change. He also will speak on ...

  18. STS-64 launch view

    NASA Technical Reports Server (NTRS)

    1994-01-01

    Passing through some of the trailer clouds of an overcast sky which temporarily postponed its launch, the Space Shuttle Discovery heads for its 19th Earth orbital flight. Several kilometers away, astronaut John H. Casper, Jr., who took this picture, was piloting the Shuttle Training Aircraft (STA) from which the launch and landing area weather was being monitored. Onboard Discovery were astronauts Richard N. Richards, L. Blaine Hammond, Jr., Mark C. Lee, Carl J. Meade, Susan J. Helms, and Jerry M. Linenger.

  19. Dynamics Explorer launch

    NASA Technical Reports Server (NTRS)

    1981-01-01

    Simultaneously launched from the WSMC, two satellites are to be placed into polar, copolar orbit in order to acquire data on the coupling phenomena between Earth's lower thermosphere and the magnetosphere, as part of the Solar-Terrestrial Program. The mission sequence, instruments, and science data processing system are described as well as the characteristics of the Delta 3913 launch vehicle, and payload separation staging.

  20. NASA Dryden Towed Glider Air-Launch Concept

    NASA Video Gallery

    NASA Dryden Flight Research Center is developing a novel space access, rocket launching technique called the Towed Glider Air-Launch Concept. The idea is to build a relatively inexpensive, remotely...

  1. Technical Barriers, Gaps, and Opportunities Related to Home Energy Upgrade Market Delivery

    SciTech Connect

    Bianchi, M. V. A.

    2011-11-01

    This report outlines the technical barriers, gaps, and opportunities that arise in executing home energy upgrade market delivery approaches, as identified through research conducted by the U.S. Department of Energy's Building America program. The objective of this report is to outline the technical1 barriers, gaps, and opportunities that arise in executing home energy upgrade market delivery approaches, as identified through research conducted by the U.S. Department of Energy's (DOE) Building America program. This information will be used to provide guidance for new research necessary to enable the success of the approaches. Investigation for this report was conducted via publications related to home energy upgrade market delivery approaches, and a series of interviews with subject matter experts (contractors, consultants, program managers, manufacturers, trade organization representatives, and real estate agents). These experts specified technical barriers and gaps, and offered suggestions for how the technical community might address them. The potential benefits of home energy upgrades are many and varied: reduced energy use and costs; improved comfort, durability, and safety; increased property value; and job creation. Nevertheless, home energy upgrades do not comprise a large part of the overall home improvement market. Residential energy efficiency is the most complex climate intervention option to deliver because the market failures are many and transaction costs are high (Climate Change Capital 2009). The key reasons that energy efficiency investment is not being delivered are: (1) The opportunity is highly fragmented; and (2) The energy efficiency assets are nonstatus, low-visibility investments that are not properly valued. There are significant barriers to mobilizing the investment in home energy upgrades, including the 'hassle factor' (the time and effort required to identify and secure improvement works), access to financing, and the opportunity cost of

  2. Overview of GX launch services by GALEX

    NASA Astrophysics Data System (ADS)

    Sato, Koji; Kondou, Yoshirou

    2006-07-01

    Galaxy Express Corporation (GALEX) is a launch service company in Japan to develop a medium size rocket, GX rocket and to provide commercial launch services for medium/small low Earth orbit (LEO) and Sun synchronous orbit (SSO) payloads with a future potential for small geo-stationary transfer orbit (GTO). It is GALEX's view that small/medium LEO/SSO payloads compose of medium scaled but stable launch market due to the nature of the missions. GX rocket is a two-stage rocket of well flight proven liquid oxygen (LOX)/kerosene booster and LOX/liquid natural gas (LNG) upper stage. This LOX/LNG propulsion under development by Japan's Aerospace Exploration Agency (JAXA), is robust with comparable performance as other propulsions and have future potential for wider application such as exploration programs. GX rocket is being developed through a joint work between the industries and GX rocket is applying a business oriented approach in order to realize competitive launch services for which well flight proven hardware and necessary new technology are to be introduced as much as possible. It is GALEX's goal to offer “Easy Access to Space”, a highly reliable and user-friendly launch services with a competitive price. GX commercial launch will start in Japanese fiscal year (JFY) 2007 2008.

  3. International Launch Vehicle Selection for Interplanetary Travel

    NASA Technical Reports Server (NTRS)

    Ferrone, Kristine; Nguyen, Lori T.

    2010-01-01

    In developing a mission strategy for interplanetary travel, the first step is to consider launch capabilities which provide the basis for fundamental parameters of the mission. This investigation focuses on the numerous launch vehicles of various characteristics available and in development internationally with respect to upmass, launch site, payload shroud size, fuel type, cost, and launch frequency. This presentation will describe launch vehicles available and in development worldwide, then carefully detail a selection process for choosing appropriate vehicles for interplanetary missions focusing on international collaboration, risk management, and minimization of cost. The vehicles that fit the established criteria will be discussed in detail with emphasis on the specifications and limitations related to interplanetary travel. The final menu of options will include recommendations for overall mission design and strategy.

  4. GPM Core Observatory Launch Animation

    NASA Video Gallery

    This animation depicts the launch of the Global Precipitation Measurement (GPM) Core Observatory satellite from Tanegashima Space Center, Japan. The launch is currently scheduled for Feb. 27, 2014....

  5. The relevance of economic data in the decision-making process for orbital launch vehicle programs, a U.S. perspective

    NASA Astrophysics Data System (ADS)

    Hertzfeld, Henry R.; Williamson, Ray A.; Peter, Nicolas

    2007-12-01

    Over the past fifteen years, major U.S. initiatives for the development of new launch vehicles have been remarkably unsuccessful. The list is long: NLI, SLI, and X-33, not to mention several cancelled programs aimed at high speed airplanes (NASP, HSCT) which would share some similar technological problems. The economic aspects of these programs are equally as important to their success as are the technical aspects. In fact, by largely ignoring economic realities in the decisions to undertake these programs and in subsequent management decisions, space agencies (and their commercial partners) have inadvertently contributed to the eventual demise of these efforts. The transportation revolution that was envisaged by the promises of these programs has never occurred. Access to space is still very expensive; reliability of launch vehicles has remained constant over the years; and market demand has been relatively low, volatile and slow to develop. The changing international context of the industry (launching overcapacity, etc.) has also worked against the investment in new vehicles in the U.S. Today, unless there are unforeseen technical breakthroughs, orbital space access is likely to continue as it has been with high costs and market stagnation. Space exploration will require significant launching capabilities. The details of the future needs are not yet well defined. But, the question of the launch costs, the overall demand for vehicles, and the size and type of role that NASA will play in the overall launch market is likely to influence the industry. This paper will emphasize the lessons learned from the economic and management perspective from past launch programs, analyze the issues behind the demand for launches, and project the challenges that NASA will face as only one new customer in a very complex market situation. It will be important for NASA to make launch vehicle decisions based as much on economic considerations as it does on solving new technical

  6. Market analyses relative to the Renewable Energy, Inc. ethanol plant feasibility study

    SciTech Connect

    Not Available

    1982-05-10

    The document contains three distinct studies. The first addresses the long-term outlook for corn price and availability in the Paducah region, the second deals with the marketability of Distillers' Dried Grains and Solubles (DDGS), and the third analyzes the market outlook for ethanol in the fuel and industrial sectors, with an emphasis on the Paducah region. This document does not represent the full amount of work performed by the KEAC relative to the sub-contract as assessments of the environmental permits required to locate an ethanol plant in Paducah, a land ownership study and miscellaneous bits of required information have been fulfilled over the course of the sub-contract. Appendices include: tax incentives for alcohol fuels; and state initiatives on alcohol fuels (a state-by-state compendium of laws, regulations, and other activities involving alcohol fuels). (DMC)

  7. Objective Measures of Emotion Related to Brand Attitude: A New Way to Quantify Emotion-Related Aspects Relevant to Marketing

    PubMed Central

    Walla, Peter; Brenner, Gerhard; Koller, Monika

    2011-01-01

    With this study we wanted to test the hypothesis that individual like and dislike as occurring in relation to brand attitude can be objectively assessed. First, individuals rated common brands with respect to subjective preference. Then, they volunteered in an experiment during which their most liked and disliked brand names were visually presented while three different objective measures were taken. Participant's eye blinks as responses to acoustic startle probes were registered with electromyography (EMG) (i) and their skin conductance (ii) and their heart rate (iii) were recorded. We found significantly reduced eye blink amplitudes related to liked brand names compared to disliked brand names. This finding suggests that visual perception of liked brand names elicits higher degrees of pleasantness, more positive emotion and approach-oriented motivation than visual perception of disliked brand names. Also, skin conductance and heart rate were both reduced in case of liked versus disliked brand names. We conclude that all our physiological measures highlight emotion-related differences depending on the like and dislike toward individual brands. We suggest that objective measures should be used more frequently to quantify emotion-related aspects of brand attitude. In particular, there might be potential interest to introduce startle reflex modulation to measure emotion-related impact during product development, product design and various further fields relevant to marketing. Our findings are discussed in relation to the idea that self reported measures are most often cognitively polluted. PMID:22073192

  8. EADS Roadmap for Launch Vehicles

    NASA Astrophysics Data System (ADS)

    Eymar, Patrick; Grimard, Max

    2002-01-01

    still think about the future, especially at industry level in order to make the most judicious choices in technologies, vehicle types as well as human resources and facilities specialization (especially after recent merger moves). and production as prime contractor, industrial architect or stage provider have taken benefit of this expertise and especially of all the studies ran under national funding and own financing on reusable vehicles and ground/flight demonstrators have analyzed several scenarios. VEHICLES/ASTRIUM SI strategy w.r.t. launch vehicles for the two next decades. Among the main inputs taken into account of course visions of the market evolutions have been considered, but also enlargement of international cooperations and governments requests and supports (e.g. with the influence of large international ventures). 1 patrick.eymar@lanceurs.aeromatra.com 2

  9. AXONOMETRIC, LAUNCH DOOR AND DOOR CYLINDER, LAUNCH PLATFORM ROLLER GUIDE, ...

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

    AXONOMETRIC, LAUNCH DOOR AND DOOR CYLINDER, LAUNCH PLATFORM ROLLER GUIDE, CRIB SUSPENSION SHOCK STRUT, LAUNCH PLATFORM - Dyess Air Force Base, Atlas F Missle Site S-8, Launch Facility, Approximately 3 miles east of Winters, 500 feet southwest of Highway 1770, center of complex, Winters, Runnels County, TX

  10. Overcoming the launch crisis - A challenge for ELVs

    NASA Astrophysics Data System (ADS)

    Iserland, Klaus

    1988-10-01

    One of the consequences of the 'launch crisis' that followed the Challenger accident was an accumulation of satellites awaiting availability of new launch opportunities. Since the Shuttle is presently reserved for government and scientific launches, commercial satellite operators have now to rely on ELVs to launch their satellites. This paper discusses specific features of the following Western launchers: Delta 2, Atlas/Centaur 2, Titan III, and ARIANE 4. It is shown that, in terms of performance, the ELV fleet offers the commercial market a sufficient choice of launchers to guarantee competition.

  11. University-Industry Relations in the Market for Online Courses and Degrees. Research & Occasional Paper Series. CSHE.10.03

    ERIC Educational Resources Information Center

    Brint, Steven; Paxton-Jorgenson, Katrina; Vega, Erica

    2003-01-01

    The market for online courses and degrees has continued to grow in recent years in spite of an overall slowdown in the growth of Internet-related industries. Who will control the new market for online courses and degrees - universities or corporations, or will a division of labor emerge between the two? What are the advantages of universities and…

  12. Filling the launch gap

    NASA Astrophysics Data System (ADS)

    Hoeser, S.

    1986-05-01

    Vehicles proposed to fill the gap in the U.S. space program's space transport needs for the next decade resulting from the January Challenger disaster, are discussed. Prior to the accident, the Air Force planned to purchase a Complementary Expendable Launch Vehicle system consisting of 10 single-use Titan-34D7 rockets. Another heavy lift booster now considered is the Phoenix H. Commercial launch vehicle systems projected to be available in the necessary time frame include the 215,000-pound thrust 4000-pound LEO payload capacity NASA Delta, the 11,300-pound LEO payload capacity Atlas Centaur the first ICBM, and the all-solid propellant expendable 2000-pound LEO payload Conestoga rocket. Also considered is the man-rated fully reusable Phoenix vertical take-off and vertical-landing launch vehicle.

  13. Zvezda Launch Coverage

    NASA Technical Reports Server (NTRS)

    2000-01-01

    Footage shows the Proton Rocket (containing the Zvezda module) ready for launch at the Baikonur Cosmodrome in Kazakhstan, Russia. The interior and exterior of Zvezda are seen during construction. Computerized simulations show the solar arrays deploying on Zvezda in space, the maneuvers of the module as it approaches and connects with the International Space Station (ISS), the installation of the Z1 truss on the ISS and its solar arrays deploying, and the installations of the Destiny Laboratory, Remote Manipulator System, and Kibo Experiment Module. Live footage then shows the successful launch of the Proton Rocket.

  14. Juno II Launch Vehicle

    NASA Technical Reports Server (NTRS)

    1958-01-01

    The modified Jupiter C (sometimes called Juno I), used to launch Explorer I, had minimum payload lifting capabilities. Explorer I weighed slightly less than 31 pounds. Juno II was part of America's effort to increase payload lifting capabilities. Among other achievements, the vehicle successfully launched a Pioneer IV satellite on March 3, 1959, and an Explorer VII satellite on October 13, 1959. Responsibility for Juno II passed from the Army to the Marshall Space Flight Center when the Center was activated on July 1, 1960. On November 3, 1960, a Juno II sent Explorer VIII into a 1,000-mile deep orbit within the ionosphere.

  15. STS-64 launch view

    NASA Technical Reports Server (NTRS)

    1994-01-01

    With a crew of six NASA astronauts aboard, the Space Shuttle Discovery heads for its nineteenth Earth-orbital mission. Launch was delayed because of weather, but all systems were 'go,' and the spacecraft left the launch pad at 6:23 p.m. (EDT) on September 9, 1994. Onboard were astronauts Richard N. Richards, L. Blaine Hammond, Carl J. Meade, Mark C. Lee, Susan J. Helms, and Jerry M. Linenger (051-2); Making a bright reflection in nearby marsh waters, the Space Shuttle Discovery heads for its 19th mission in earth orbit (053).

  16. 47 CFR 25.113 - Station licenses and launch authority.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... must comply with the provisions of 47 CFR 1.1312 relating to environmental processing prior to... for and granted before a space station may be launched and operated in orbit. Request for launch... station that has been lost as a result of a launch failure or a catastrophic in-orbit failure....

  17. 47 CFR 25.113 - Station licenses and launch authority.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... must comply with the provisions of 47 CFR 1.1312 relating to environmental processing prior to... for and granted before a space station may be launched and operated in orbit. Request for launch... station that has been lost as a result of a launch failure or a catastrophic in-orbit failure....

  18. NASA Launch Services Program Overview

    NASA Technical Reports Server (NTRS)

    Higginbotham, Scott

    2016-01-01

    The National Aeronautics and Space Administration (NASA) has need to procure a variety of launch vehicles and services for its unmanned spacecraft. The Launch Services Program (LSP) provides the Agency with a single focus for the acquisition and management of Expendable Launch Vehicle (ELV) launch services. This presentation will provide an overview of the LSP and its organization, approach, and activities.

  19. 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

  20. 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

  1. Launch Vehicle Description

    NASA Technical Reports Server (NTRS)

    Coffey, E. E.; Geye, R. P.

    1970-01-01

    The Thorad-Agena is a two-stage launch vehicle consisting of a Thorad first-stage and an Agena second-stage, connected by a booster adapter. The composite vehicle, including the shroud and the booster adapter, is about 33 meters (109 ft) long. The total weight at lift-off is approximately 91 625 kilograms (202 000 lbm).

  2. Japan's launch vehicles

    NASA Astrophysics Data System (ADS)

    Kuroda, Y.; Hara, N.

    The development of Japan's Mu series scientific research launch vehicles, and N and H series practical applications vehicles, is described. The three-stage M-3C features a second-stage radio inertial guidance system. The evolution to the M-3S includes a first-stage TVC and Solid Motor Roll Control device, and eight 310-m strap-on boosters (SOB's). The M-3SII developed to launch an interplanetary satellite for the 1986 Halley's Comet apparition, employs two 735-mm SOB's and a microprocessor digitalized flight control system, and can put a 770 kg satellite into low earth orbit. The N-1 is a three-stage radio-guided vehicle using first and second stage liquid engines, a solid motor third stage, three SOB's, and having the capability to launch a 145 kg geostationary satellite. N-II improvements include a 350 kg geostationary payload capacity, nine SOB's, and an inertial guidance system. The H-1 planned for 1987 has a 550 kg geostationary payload capacity and a domestically developed cryogenic engine. The H-II planned for 1992 will be capable of launching a two-ton geostationary satellite, or LOX/LH2 plural satellites simultaneously. It will be powered by a single 95-ton thrust LE-7 main engine.

  3. AST Launch Vehicle Acoustics

    NASA Technical Reports Server (NTRS)

    Houston, Janice; Counter, D.; Giacomoni, D.

    2015-01-01

    The liftoff phase induces acoustic loading over a broad frequency range for a launch vehicle. These external acoustic environments are then used in the prediction of internal vibration responses of the vehicle and components which result in the qualification levels. Thus, predicting these liftoff acoustic (LOA) environments is critical to the design requirements of any launch vehicle. If there is a significant amount of uncertainty in the predictions or if acoustic mitigation options must be implemented, a subscale acoustic test is a feasible pre-launch test option to verify the LOA environments. The NASA Space Launch System (SLS) program initiated the Scale Model Acoustic Test (SMAT) to verify the predicted SLS LOA environments and to determine the acoustic reduction with an above deck water sound suppression system. The SMAT was conducted at Marshall Space Flight Center and the test article included a 5% scale SLS vehicle model, tower and Mobile Launcher. Acoustic and pressure data were measured by approximately 250 instruments. The SMAT liftoff acoustic results are presented, findings are discussed and a comparison is shown to the Ares I Scale Model Acoustic Test (ASMAT) results.

  4. AC 67 Launch Video

    NASA Technical Reports Server (NTRS)

    1987-01-01

    Live footage of the Unmanned Atlas Centaur (AC) 67 launch is presented on March 26, 1987 at the WESH television station in Florida. Lightning is shown after 49 seconds into the flight. The vehicle is totally destroyed due to a cloud-to-ground lightning flash.

  5. NLS Advanced Development - Launch operations

    NASA Technical Reports Server (NTRS)

    Parrish, Carrie L.

    1992-01-01

    Attention is given to Autonomous Launch Operations (ALO), one of a number of the USAF's National Launch System (NLS) Launch Operations projects whose aim is to research, develop and apply new technologies and more efficient approaches toward launch operations. The goal of the ALO project is to develop generic control and monitor software for launch operation subsystems. The result is enhanced reliability of system design, and reduced software development and retention of expert knowledge throughout the life-cycle of the system.

  6. Successful launch of SOHO

    NASA Astrophysics Data System (ADS)

    1995-12-01

    "Understanding how the Sun behaves is of crucial importance to all of us on Earth. It affects our everyday lives" said Roger Bonnet, Director of Science at ESA, who witnessed SOHO's spectacular nighttime launch from Cape Canaveral. "When SOHO begins work in four months time, scientists will, for the first time, be able to study this star 24 hours a day, 365 days a year". The 12 instruments on SOHO will probe the Sun inside out, from the star's very centre to the solar wind that blasts its way through the solar system. It will even listen to sounds, like musical notes, deep within the star by recording their vibrations when they reach the surface. SOHO was launched from Cape Canaveral Air Station, Florida, atop an Atlas IIAS rocket, at 09:08 CET on Saturday 2 December 1995. The 1.6 tonne observatory was released into its transfer orbit from the rocket's Centaur upper stage about two hours after launch. It will take four months for the satellite to reach its final position, a unique vantage point, located 1.5 million kilometres from Earth, where the gravitational pull of the Earth and Sun are equal. From here, the Lagrange point, SOHO will have an unobstructed view of the Sun all year round. SOHO's launch was delayed from 23 November because a flaw was discovered in a precision regulator, which throttles the power of the booster engine on the Atlas rocket. The system was replaced and retested before the launch. SOHO is a project of international cooperation between ESA and NASA. The spacecraft was designed and built in Europe, NASA provided the launch and will operate the satellite from its Goddard Space Flight Center, Maryland. European scientists provided eight of the observatory's instruments and US scientists a further three. The spacecraft is part of the international Solar-Terrestrial Science Programme, the next member of which is Cluster, a flotilla of four spacecraft that will study how the Sun affects Earth and surrounding space. Cluster is scheduled for

  7. Side launch of the Lena guyed tower jacket

    SciTech Connect

    Flood, J.K.; Danaczko, M.A.; Greiner, W.L.; Pichini, P.G.

    1984-05-01

    The launch of the 27,000-ton Lena jacket was a critical and challenging aspect of the Lena Guyed Tower installation. The Lena jacket was the longest one-piece jacket ever launched, and is the industry's first side launch of a major offshore structure. Although the side launch offered advantages over a conventional end launch, this technique presented unique problems that required extensive analysis and innovative solutions. In addition to requiring significant launch barge modifications, the side launch increased the potential for jacket skewing relative to the barge due to differential friction and caused higher-than normal slamming loads due to high entry velocities. This paper discusses the challenges that were faced and the solutions that were developed. Computer analyses and scale model launch tests are also discussed. Particular emphasis is placed on the jacket skewing solution which utilized a special release system similar to that used in the Space Shuttle Program.

  8. Free markets and the marriage market: structural adjustment, gender relations, and working conditions among Dominican women workers.

    PubMed

    Safa, H I

    1999-02-01

    The relationship between economic conditions and marriage patterns in the Dominican Republic is analyzed using data collected in 1994 on women working in a free-trade zone. The author concludes that changes associated with structural adjustment appear to have contributed to a deterioration of the job market and a greater prevalence of female-headed households. It is shown that "structural adjustment increases the need for women to work, because of cuts in government programs, declining real wages, growing inflation, and a deterioration in male employment, which weakens the man's role as principal breadwinner and increases the importance and visibility of women's contribution to the household economy. This change in the gender composition of the labor force has encouraged some women to resist marriage and/or remarriage because the ¿marriage market' of eligible men willing and able to support a family has been reduced, contributing to greater marital instability." PMID:12294805

  9. Cassini launch contingency effort

    NASA Astrophysics Data System (ADS)

    Chang, Yale; O'Neil, John M.; McGrath, Brian E.; Heyler, Gene A.; Brenza, Pete T.

    2002-01-01

    On 15 October 1997 at 4:43 AM EDT, the Cassini spacecraft was successfully launched on a Titan IVB/Centaur on a mission to explore the Saturnian system. It carried three Radioisotope Thermoelectric Generators (RTGs) and 117 Light Weight Radioisotope Heater Units (LWRHUs). As part of the joint National Aeronautics and Space Administration (NASA)/U.S. Department of Energy (DoE) safety effort, a contingency plan was prepared to address the unlikely events of an accidental suborbital reentry or out-of-orbital reentry. The objective of the plan was to develop procedures to predict, within hours, the Earth impact footprints (EIFs) for the nuclear heat sources released during the atmospheric reentry. The footprint predictions would be used in subsequent notification and recovery efforts. As part of a multi-agency team, The Johns Hopkins University Applied Physics Laboratory (JHU/APL) had the responsibility to predict the EIFs of the heat sources after a reentry, given the heat sources' release conditions from the main spacecraft. (No ablation burn-through of the heat sources' aeroshells was expected, as a result of earlier testing.) JHU/APL's other role was to predict the time of reentry from a potential orbital decay. The tools used were a three degree-of-freedom trajectory code, a database of aerodynamic coefficients for the heat sources, secure links to obtain tracking data, and a high fidelity special perturbation orbit integrator code to predict time of spacecraft reentry from orbital decay. In the weeks and days prior to launch, all the codes and procedures were exercised. Notional EIFs were derived from hypothetical reentry conditions. EIFs predicted by JHU/APL were compared to those by JPL and US SPACECOM, and were found to be in good agreement. The reentry time from orbital decay for a booster rocket for the Russian Progress M-36 freighter, a cargo ship for the Mir space station, was predicted to within 5 minutes more than two hours before reentry. For the

  10. The Demeter micro satellite launch campaign

    NASA Astrophysics Data System (ADS)

    Dubourg, V.; Kainov, V.; Thoby, M.; Silkin, O.; Solovey, V.

    The CNES Micro satellite DEMETER is planned for launch by the end of June 2004 on a DNEPR launcher, from the Baíkonur cosmodrome. DEMETER will be the main payload among nine co-passengers. DEMETER, initiated by CNES in 1998, is the first model of the MYRIADE micro satellites line of product; at the time when this abstract is issued, the satellite is going through the final integration tests, as well as the last system validation phase. The space head module of the launcher has been developed by the Ukrainian YSDO company, and a successful fit check test campaign has been performed in December 2003 and January 2004 that allowed confirming the compatibility of the payloads with their launcher interface. The launch campaign is in process of preparation, implying a close partnership between the satellite team at CNES and Russian and Ukrainian launcher authorities: DEMETER is a pioneer not only for the satellite concept itself, but also for being the first satellite of this range (3 axis stabilized, including an hydrazine propulsion system and developed by a national space agency) being launched on a Russian space adapted intercontinental ballistic missile SS18. The launch service is contracted and managed by ISC Kosmotras, and it will also be the first sun synchronous orbit launch for DNEPR. Thus the launch preparation proved to be a very challenging endeavour providing all the actors with very rich human experience, as well as technical exchanges, in the fields of launcher technology and interfaces, facilities adaptation, logistics and project coordination. In the coming paper, a short presentation of the DEMETER satellite and of the DNEPR launcher will be made, but the main purpose is to present: the launch campaign preparation milestones, the launch campaign itself and related preliminary results and the lessons learnt from this first CNES/DNEPR experience to open the way to the future MYRIADE launches. A common CNES/KOSMOTRAS presentation is proposed at the

  11. Marketing Across the Board.

    ERIC Educational Resources Information Center

    Lauer, Larry D.

    1999-01-01

    Outlines an eight-step approach to launching an integrated college or university marketing/fund-raising program: finding a visionary campus leader; getting presidential support; assembling a three-tier marketing structure; considering new ways of defining quality; developing a marketing "blueprint"; selling the program on campus; embracing…

  12. A perfect launch

    NASA Technical Reports Server (NTRS)

    2000-01-01

    Billows of smoke and steam spread across Launch Pad 39A as Space Shuttle Discovery lifts off on mission STS-92 to the International Space Station. The perfect on-time liftoff occurred at 7:17 p.m. EDT, sending a crew of seven on the 100th launch in the history of the Shuttle program. Discovery carries a payload that includes the Integrated Truss Structure Z-1, first of 10 trusses that will form the backbone of the Space Station, and the third Pressurized Mating Adapter that will provide a Shuttle docking port for solar array installation on the sixth Station flight and Lab installation on the seventh Station flight. Discovery's landing is expected Oct. 22 at 2:10 p.m. EDT.

  13. Can we well assess the relative efficacy and tolerability of a new drug versus others at the time of marketing authorization using mixed treatment comparisons? A detailed illustration with escitalopram

    PubMed Central

    Llorca, Pierre-Michel; Lançon, Christophe; Brignone, Mélanie; Painchault, Caroline; Rive, Benoit; Toumi, Mondher; François, Clément

    2015-01-01

    Objective To assess the variation of relative efficacy and tolerability of an antidepressant versus others based on both pre-marketing (registration studies) and post-marketing studies versus pre-marketing studies only in patients with major depressive disorder. Methods The relative efficacy and tolerability of antidepressants was assessed by mixed treatment comparisons (MTCs) using data acquired over two time periods: before registration of the reference drug escitalopram (1989–2002) and up to 5 years later (1989–2007). Ranking probability outputs were presented for efficacy, using change from baseline to 8 weeks on Montgomery–Åsberg Depression Rating Scale total score, and tolerability, using withdrawals due to adverse events. Results The relative efficacy and tolerability of some selected antidepressants, including escitalopram, varied considerably over the two time periods. The improved relative efficacy and tolerability of escitalopram over time, compared with citalopram, was demonstrated by greater separation of ranking probability curves for efficacy and tolerability. In 2002, escitalopram ranked low with 13.9% and 5.1% probability of being in the top four antidepressants’ relative efficacy and tolerability, respectively. In 2007, ranking probabilities for relative efficacy and tolerability of escitalopram increased to 52.5% and 82.1%, respectively. Conclusions Time of marketing authorization may not be the most appropriate time to evaluate the relative efficacy and tolerability of a new antidepressant based on MTC approach due to the asymmetry of information between new and older compounds. However, the first evaluation of relative effect of a new drug for health technology assessment recommendations is commonly done at this time. Re-evaluation of a drug several years after its launch is likely to provide a more accurate indication of its relative efficacy and tolerability. PMID:27123184

  14. Expendable launch vehicle propulsion

    NASA Technical Reports Server (NTRS)

    Fuller, Paul N.

    1991-01-01

    The current status is reviewed of the U.S. Expendable Launch Vehicle (ELV) fleet, the international competition, and the propulsion technology of both domestic and foreign ELVs. The ELV propulsion technology areas where research, development, and demonstration are most needed are identified. These propulsion technology recommendations are based on the work performed by the Commercial Space Transportation Advisory Committee (COMSTAC), an industry panel established by the Dept. of Transportation.

  15. Space Logistics: Launch Capabilities

    NASA Technical Reports Server (NTRS)

    Furnas, Randall B.

    1989-01-01

    The current maximum launch capability for the United States are shown. The predicted Earth-to-orbit requirements for the United States are presented. Contrasting the two indicates the strong National need for a major increase in Earth-to-orbit lift capability. Approximate weights for planned payloads are shown. NASA is studying the following options to meet the need for a new heavy-lift capability by mid to late 1990's: (1) Shuttle-C for near term (include growth versions); and (2) the Advanced Lauching System (ALS) for the long term. The current baseline two-engine Shuttle-C has a 15 x 82 ft payload bay and an expected lift capability of 82,000 lb to Low Earth Orbit. Several options are being considered which have expanded diameter payload bays. A three-engine Shuttle-C with an expected lift of 145,000 lb to LEO is being evaluated as well. The Advanced Launch System (ALS) is a potential joint development between the Air Force and NASA. This program is focused toward long-term launch requirements, specifically beyond the year 2000. The basic approach is to develop a family of vehicles with the same high reliability as the Shuttle system, yet offering a much greater lift capability at a greatly reduced cost (per pound of payload). The ALS unmanned family of vehicles will provide a low end lift capability equivalent to Titan IV, and a high end lift capability greater than the Soviet Energia if requirements for such a high-end vehicle are defined.In conclusion, the planning of the next generation space telescope should not be constrained to the current launch vehicles. New vehicle designs will be driven by the needs of anticipated heavy users.

  16. Launch of Zoological Letters.

    PubMed

    Fukatsu, Takema; Kuratani, Shigeru

    2016-02-01

    A new open-access journal, Zoological Letters, was launched as a sister journal to Zoological Science, in January 2015. The new journal aims at publishing topical papers of high quality from a wide range of basic zoological research fields. This review highlights the notable reviews and research articles that have been published in the first year of Zoological Letters, providing an overview on the current achievements and future directions of the journal. PMID:26853862

  17. Space Probe Launch

    NASA Technical Reports Server (NTRS)

    1970-01-01

    Managed by Marshall Space Flight Center, the Space Tug was a reusable multipurpose space vehicle designed to transport payloads to different orbital inclinations. Utilizing mission-specific combinations of its three primary modules (crew, propulsion, and cargo) and a variety of supplementary kits, the Space Tug was capable of numerous space applications. This 1970 artist's concept depicts the Tug's propulsion module launching a space probe into lunar orbit.

  18. NATO-3C/Delta launch

    NASA Technical Reports Server (NTRS)

    1978-01-01

    NATO-3C, the third in a series of NATO defense-related communication satellites, is scheduled to be launched on a delta vehicle from the Eastern Test Range no earlier than November 15, 1978. NATO-3A and -3B were successfully launched by Delta vehicles in April 1976 and January 1977, respectively. The NATO-3C spacecraft will be capable of transmitting voice, data, facsimile, and telex messages among military ground stations. The launch vehicle for the NATO-3C mission will be the Delta 2914 configuration. The launch vehicle is to place the spacecraft in a synchronous transfer orbit. The spacecraft Apogee Kick motor is to be fired at fifth transfer orbit apogee to circularize its orbit at geosynchronous altitude of 35,900 km(22,260 miles) above the equator over the Atlantic Ocean somewhere between 45 and 50 degrees W longitude.

  19. National Launch System comparative economic analysis

    NASA Technical Reports Server (NTRS)

    Prince, A.

    1992-01-01

    Results are presented from an analysis of economic benefits (or losses), in the form of the life cycle cost savings, resulting from the development of the National Launch System (NLS) family of launch vehicles. The analysis was carried out by comparing various NLS-based architectures with the current Shuttle/Titan IV fleet. The basic methodology behind this NLS analysis was to develop a set of annual payload requirements for the Space Station Freedom and LEO, to design launch vehicle architectures around these requirements, and to perform life-cycle cost analyses on all of the architectures. A SEI requirement was included. Launch failure costs were estimated and combined with the relative reliability assumptions to measure the effects of losses. Based on the analysis, a Shuttle/NLS architecture evolving into a pressurized-logistics-carrier/NLS architecture appears to offer the best long-term cost benefit.

  20. Umami and related components in "chilled" pork for the Japanese market.

    PubMed

    Ngapo, T M; Vachon, L

    2016-11-01

    The aim of this study was to evaluate umami-related components and their evolution in Canadian pork destined for the Japanese market. Export quality pork loins for Japan were subjectively selected on-line for marbling, colour and firmness; remaining loins were retained for the domestic market. At 48h post-mortem, samples were aged 5d at 4.0°C (fresh) or 13, 28, 43 or 58d at -1.7°C (chilled). Meat qualities differed only in pH (<0.1 pH unit; P<0.05). Generally, free amino acid concentrations increased and nucleotide concentrations decreased with longer ageing periods. The equivalent umami concentration (EUC) was highest in the pork aged 5d at 4.0°C and at 43d -1.7°C (P<0.05) which is estimated as the transportation time for Canadian chilled exports to Japan. A lack of differences in EUC between domestic and export pork and between fresh and 43d chilled ageing demonstrates that Canadian chilled pork in Japan has the EUC of its fresh 5d counterpart. PMID:27424307

  1. 73. VIEW OF LAUNCH OPERATOR AND LAUNCH ANAYLST PANELS LOCATED ...

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

    73. VIEW OF LAUNCH OPERATOR AND LAUNCH ANAYLST PANELS LOCATED NEAR CENTER OF SOUTH WALL OF SLC-3E CONTROL ROOM. FROM LEFT TO RIGHT ON WALL IN BACKGROUND: COMMUNICATIONS HEADSET AND FOOT PEDAL IN FORGROUND. ACCIDENT REPORTING EMERGENCY NOTIFICATION SYSTEM TELEPHONE, ATLAS H FUEL COUNTER, AND DIGITAL COUNTDOWN CLOCK. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Operations Building, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  2. Launching a world-class joint venture.

    PubMed

    Bamford, James; Ernst, David; Fubini, David G

    2004-02-01

    More than 5,000 joint ventures, and many more contractual alliances, have been launched worldwide in the past five years. Companies are realizing that JVs and alliances can be lucrative vehicles for developing new products, moving into new markets, and increasing revenues. The problem is, the success rate for JVs and alliances is on a par with that for mergers and acquisitions--which is to say not very good. The authors, all McKinsey consultants, argue that JV success remains elusive for most companies because they don't pay enough attention to launch planning and execution. Most companies are highly disciplined about integrating the companies they target through M&A, but they rarely commit sufficient resources to launching similarly sized joint ventures or alliances. As a result, the parent companies experience strategic conflicts, governance gridlock, and missed operational synergies. Often, they walk away from the deal. The launch phase begins with the parent companies' signing of a memorandum of understanding and continues through the first 100 days of the JV or alliance's operation. During this period, it's critical for the parents to convene a team dedicated to exposing inherent tensions early. Specifically, the launch team must tackle four basic challenges. First, build and maintain strategic alignment across the separate corporate entities, each of which has its own goals, market pressures, and shareholders. Second, create a shared governance system for the two parent companies. Third, manage the economic interdependencies between the corporate parents and the JV. And fourth, build a cohesive, high-performing organization (the JV or alliance)--not a simple task, since most managers come from, will want to return to, and may even hold simultaneous positions in the parent companies. Using real-world examples, the authors offer their suggestions for meeting these challenges. PMID:14971273

  3. 2011 Mars Science Laboratory Launch Period Design

    NASA Technical Reports Server (NTRS)

    Abilleira, Fernando

    2011-01-01

    The Mars Science Laboratory mission, set to launch in the fall of 2011, has the primary objective of landing the most advanced rover to date to the surface of Mars to assess whether Mars ever was, or still is today, able to sustain carbon-based life. Arriving at Mars in August 2012, the Mars Science Laboratory will also demonstrate the ability to deliver large payloads to the surface of Mars, land more accurately (than previous missions) in a 20-km by 25-km ellipse, and traverse up to 20 km. Following guided entry and parachute deployment, the spacecraft will descend on a parachute and a Powered Descent Vehicle to safely land the rover on the surface of Mars. The launch/arrival strategy is driven by several key requirements, which include: launch vehicle capability, atmosphere-relative entry speed, communications coverage during Entry, Descent and Landing, latitude accessibility, and dust storm season avoidance. Notable among these requirements is maintaining a telecommunications link from atmospheric entry to landing plus one minute, via a Direct-To-Earth X-band link and via orbital assets using an UHF link, to ensure that any failure during Entry, Descent and Landing can be reconstructed in case of a mission anomaly. Due to concerns related to the lifetime of the relay orbiters, two additional launch/arrival strategies have been developed to improve Entry, Descent, and Landing communications. This paper discusses the final launch/arrival strategy selected prior to the launch period down-selection that is scheduled to occur in August 2011. It is also important to note that this paper is an update to Ref. 1 in that it includes two new Type 1 launch periods and drops the Type 2 launch period that is no longer considered.

  4. Tannin profile of different Monastrell wines and its relation to projected market prices.

    PubMed

    Gómez-Plaza, Encarna; Olmos, Oscar; Bautista-Ortín, Ana Belén

    2016-08-01

    This study focuses on the differences or similarities in tannin composition and concentration in Monastrell wines from different wineries from the same geographic area and, within each winery, from wines elaborated based on different projected market prices, to determine whether there is any relationship between the wine tannin composition and the projected price. The tannin composition of the different wines, all of them analyzed at the same point during winemaking, indicated that those elaborated as premium wines presented higher phenol and tannin contents. The mean degree of polymerization of these wines was also positively related with the projected price, which agreed with the results obtained by size exclusion chromatography, that showed that wines with high projected prices had a higher proportion of polymeric tannins, suggesting that techniques favoring the extraction of skin tannins were mostly used in those wines projected as premium wines, probably looking for greater mouthfeel complexity. PMID:26988530

  5. Heavy Lift Launch Vehicle Concept

    NASA Technical Reports Server (NTRS)

    2004-01-01

    During the Space Shuttle development phase, Marshall plarners concluded a Heavy Lift Launch Vehicle (HLLV) would be needed for successful Space Industrialization. Shown here in this 1976's artist's conception is an early version of the HLLV during launch.

  6. SMAP Launch and Deployment Sequence

    NASA Video Gallery

    This video combines file footage of a Delta II rocket and computer animation to depict the launch and deployment of NASA's Soil Moisture Active Passive satellite. SMAP is scheduled to launch on Nov...

  7. Launch Services Program EMC Issues

    NASA Technical Reports Server (NTRS)

    trout, Dawn

    2004-01-01

    Presentation covers these issues: (1) Vehicles of the Launch Services Program, (2) RF Environment, (3) Common EMC Launch Vehicle Payload Integration Issues, (4) RF Sensitive Missions and (5) Lightning Monitoring,

  8. Launching Garbage-Bag Balloons.

    ERIC Educational Resources Information Center

    Kim, Hy

    1997-01-01

    Presents a modification of a procedure for making and launching hot air balloons made out of garbage bags. Student instructions for balloon construction, launching instructions, and scale diagrams are included. (DDR)

  9. Launch Vehicle Control Center Architectures

    NASA Technical Reports Server (NTRS)

    Watson, Michael D.; Epps, Amy; Woodruff, Van; Vachon, Michael Jacob; Monreal, Julio; Williams, Randall; McLaughlin, Tom

    2014-01-01

    This analysis is a survey of control center architectures of the NASA Space Launch System (SLS), United Launch Alliance (ULA) Atlas V and Delta IV, and the European Space Agency (ESA) Ariane 5. Each of these control center architectures have similarities in basic structure, and differences in functional distribution of responsibilities for the phases of operations: (a) Launch vehicles in the international community vary greatly in configuration and process; (b) Each launch site has a unique processing flow based on the specific configurations; (c) Launch and flight operations are managed through a set of control centers associated with each launch site, however the flight operations may be a different control center than the launch center; and (d) The engineering support centers are primarily located at the design center with a small engineering support team at the launch site.

  10. Intelsat satellite scheduled for launch

    NASA Technical Reports Server (NTRS)

    1981-01-01

    The launch schedule for Intelsat 5-B, the prime Intelsat satellite to provide communications services between the Americas, Europe, the Middle East, and Africa, is presented. The planned placement of the satellite into an elliptical transfer orbit, and circularization of the orbit at geosynchronous altitude over the equator are described. Characteristics of the Atlas Centaur launch vehicle, AC-56, are given. The launch operation is summarized and the launch sequence presented. The Intelsat team and contractors are listed.

  11. Launch Vehicle Control Center Architectures

    NASA Technical Reports Server (NTRS)

    Watson, Michael D.; Epps, Amy; Woodruff, Van; Vachon, Michael Jacob; Monreal, Julio; Levesque, Marl; Williams, Randall; Mclaughlin, Tom

    2014-01-01

    Launch vehicles within the international community vary greatly in their configuration and processing. Each launch site has a unique processing flow based on the specific launch vehicle configuration. Launch and flight operations are managed through a set of control centers associated with each launch site. Each launch site has a control center for launch operations; however flight operations support varies from being co-located with the launch site to being shared with the space vehicle control center. There is also a nuance of some having an engineering support center which may be co-located with either the launch or flight control center, or in a separate geographical location altogether. A survey of control center architectures is presented for various launch vehicles including the NASA Space Launch System (SLS), United Launch Alliance (ULA) Atlas V and Delta IV, and the European Space Agency (ESA) Ariane 5. Each of these control center architectures shares some similarities in basic structure while differences in functional distribution also exist. The driving functions which lead to these factors are considered and a model of control center architectures is proposed which supports these commonalities and variations.

  12. Expendable launch vehicle studies

    NASA Technical Reports Server (NTRS)

    Bainum, Peter M.; Reiss, Robert

    1995-01-01

    Analytical support studies of expendable launch vehicles concentrate on the stability of the dynamics during launch especially during or near the region of maximum dynamic pressure. The in-plane dynamic equations of a generic launch vehicle with multiple flexible bending and fuel sloshing modes are developed and linearized. The information from LeRC about the grids, masses, and modes is incorporated into the model. The eigenvalues of the plant are analyzed for several modeling factors: utilizing diagonal mass matrix, uniform beam assumption, inclusion of aerodynamics, and the interaction between the aerodynamics and the flexible bending motion. Preliminary PID, LQR, and LQG control designs with sensor and actuator dynamics for this system and simulations are also conducted. The initial analysis for comparison of PD (proportional-derivative) and full state feedback LQR Linear quadratic regulator) shows that the split weighted LQR controller has better performance than that of the PD. In order to meet both the performance and robustness requirements, the H(sub infinity) robust controller for the expendable launch vehicle is developed. The simulation indicates that both the performance and robustness of the H(sub infinity) controller are better than that for the PID and LQG controllers. The modelling and analysis support studies team has continued development of methodology, using eigensensitivity analysis, to solve three classes of discrete eigenvalue equations. In the first class, the matrix elements are non-linear functions of the eigenvector. All non-linear periodic motion can be cast in this form. Here the eigenvector is comprised of the coefficients of complete basis functions spanning the response space and the eigenvalue is the frequency. The second class of eigenvalue problems studied is the quadratic eigenvalue problem. Solutions for linear viscously damped structures or viscoelastic structures can be reduced to this form. Particular attention is paid to

  13. Space Shuttle Columbia launch

    NASA Technical Reports Server (NTRS)

    1995-01-01

    A Great Blue Heron seems oblivious to the tremendous spectacle of light and sound generated by a Shuttle liftoff, as the Space Shuttle Columbia (STS-73) soars skyward from Launch Pad 39B. Columbia's seven member crew's mission included continuing experimentation in the Marshall managed payloads including the United States Microgravity Laboratory 2 (USML-2) and the keel-mounted accelerometer that characterizes the very low frequency acceleration environment of the orbiter payload bay during space flight, known as the Orbital Acceleration Research Experiment (OARE).

  14. STS-39 Launch

    NASA Technical Reports Server (NTRS)

    1991-01-01

    Launched aboard the Space Shuttle Discovery on April 28, 1991 at 7:33:14 am (EDT), STS-39 was a Department of Defense (DOD) mission. The crew included seven astronauts: Michael L. Coats, commander; L. Blaine Hammond, pilot; Guion S. Buford, Jr., mission specialist 1; Gregory J. Harbaugh, mission specialist 2; Richard J. Hieb, mission specialist 3; Donald R. McMonagle, mission specialist 4; and Charles L. Veach, mission specialist 5. The primary unclassified payload included the Air Force Program 675 (AFP-675), the Infrared Background Signature Survey (IBSS), and the Shuttle Pallet Satellite II (SPAS II).

  15. Greenhouse-gas-trading markets.

    PubMed

    Sandor, Richard; Walsh, Michael; Marques, Rafael

    2002-08-15

    This paper summarizes the extension of new market mechanisms for environmental services, explains of the importance of generating price information indicative of the cost of mitigating greenhouse gases (GHGs) and presents the rationale and objectives for pilot GHG-trading markets. It also describes the steps being taken to define and launch pilot carbon markets in North America and Europe and reviews the key issues related to incorporating carbon sequestration into an emissions-trading market. There is an emerging consensus to employ market mechanisms to help address the threat of human-induced climate changes. Carbon-trading markets are now in development around the world. A UK market is set to launch in 2002, and the European Commission has called for a 2005 launch of an European Union (EU)-wide market, and a voluntary carbon market is now in formation in North America. These markets represent an initial step in resolving a fundamental problem in defining and implementing appropriate policy actions to address climate change. Policymakers currently suffer from two major information gaps: the economic value of potential damages arising from climate changes are highly uncertain, and there is a lack of reliable information on the cost of mitigating GHGs. These twin gaps significantly reduce the quality of the climate policy debate. The Chicago Climate Exchange, for which the authors serve as lead designers, is intended to provide an organized carbon-trading market involving energy, industry and carbon sequestration in forests and farms. Trading among these diverse sectors will provide price discovery that will help clarify the cost of combating climate change when a wide range of mitigation options is employed. By closing the information gap on mitigation costs, society and policymakers will be far better prepared to identify and implement optimal policies for managing the risks associated with climate change. Establishment of practical experience in providing

  16. State of play in direct-to-consumer genetic testing for lifestyle-related diseases: market, marketing content, user experiences and regulation.

    PubMed

    Saukko, Paula

    2013-02-01

    Direct-to-consumer (DTC) genetic tests have aroused controversy. Critics have argued many of the tests are not backed by scientific evidence, misguide their customers and should be regulated more stringently. Proponents suggest that finding out genetic susceptibilities for diseases could encourage healthier behaviours and makes the results of genetics research available to the public. This paper reviews the state of play in DTC genetic testing, focusing on tests identifying susceptibilities for lifestyle-related diseases. It will start with mapping the market for the tests. The paper will review (1) research on the content of the online marketing of DTC tests, (2) studies on the effects of DTC genetic tests on customers and (3) academic and policy proposals on how to regulate the tests. Current studies suggest that the marketing of DTC genetic tests often exaggerates their predictive powers, which could misguide consumers. However, research indicates that the tests do not seem to have major negative effects (worry and confusion) but neither do they engender positive effects (lifestyle change) on current users. Research on regulation of the tests has most commonly suggested regulating the marketing claims of the companies. In conclusion, the risks and benefits of DTC genetic tests are less significant than what has been predicted by critics and proponents, which will be argued reflects broader historical trends transforming health and medicine. PMID:23336560

  17. To Market, to Market

    ERIC Educational Resources Information Center

    Barden, Dennis M.

    2006-01-01

    The institution is part of a national market and its presidential options are dictated by that market, the reputation, the challenges of the position, and the relative compensation for the opportunity to lead the organization. Many in academe are uncomfortable with the idea that hiring in higher education should be governed by the laws of supply…

  18. Aircraft operability methods applied to space launch vehicles

    SciTech Connect

    Young, D.

    1997-01-01

    The commercial space launch market requirement for low vehicle operations costs necessitates the application of methods and technologies developed and proven for complex aircraft systems. The {open_quotes}building in{close_quotes} of reliability and maintainability, which is applied extensively in the aircraft industry, has yet to be applied to the maximum extent possible on launch vehicles. Use of vehicle system and structural health monitoring, automated ground systems and diagnostic design methods derived from aircraft applications support the goal of achieving low cost launch vehicle operations. Transforming these operability techniques to space applications where diagnostic effectiveness has significantly different metrics is critical to the success of future launch systems. These concepts will be discussed with reference to broad launch vehicle applicability. Lessons learned and techniques used in the adaptation of these methods will be outlined drawing from recent aircraft programs and implementation on phase 1 of the X-33/RLV technology development program. {copyright} {ital 1997 American Institute of Physics.}

  19. Aircraft operability methods applied to space launch vehicles

    NASA Astrophysics Data System (ADS)

    Young, Douglas

    1997-01-01

    The commercial space launch market requirement for low vehicle operations costs necessitates the application of methods and technologies developed and proven for complex aircraft systems. The ``building in'' of reliability and maintainability, which is applied extensively in the aircraft industry, has yet to be applied to the maximum extent possible on launch vehicles. Use of vehicle system and structural health monitoring, automated ground systems and diagnostic design methods derived from aircraft applications support the goal of achieving low cost launch vehicle operations. Transforming these operability techniques to space applications where diagnostic effectiveness has significantly different metrics is critical to the success of future launch systems. These concepts will be discussed with reference to broad launch vehicle applicability. Lessons learned and techniques used in the adaptation of these methods will be outlined drawing from recent aircraft programs and implementation on phase 1 of the X-33/RLV technology development program.

  20. Launch Pad Flame Trench Refractory Materials

    NASA Technical Reports Server (NTRS)

    Calle, Luz M.; Hintze, Paul E.; Parlier, Christopher R.; Bucherl, Cori; Sampson, Jeffrey W.; Curran, Jerome P.; Kolody, Mark; Perusich, Steve; Whitten, Mary

    2010-01-01

    The launch complexes at NASA's John F. Kennedy Space Center (KSC) are critical support facilities for the successful launch of space-based vehicles. These facilities include a flame trench that bisects the pad at ground level. This trench includes a flame deflector system that consists of an inverted, V-shaped steel structure covered with a high temperature concrete material five inches thick that extends across the center of the flame trench. One side of the "V11 receives and deflects the flames from the orbiter main engines; the opposite side deflects the flames from the solid rocket boosters. There are also two movable deflectors at the top of the trench to provide additional protection to shuttle hardware from the solid rocket booster flames. These facilities are over 40 years old and are experiencing constant deterioration from launch heat/blast effects and environmental exposure. The refractory material currently used in launch pad flame deflectors has become susceptible to failure, resulting in large sections of the material breaking away from the steel base structure and creating high-speed projectiles during launch. These projectiles jeopardize the safety of the launch complex, crew, and vehicle. Post launch inspections have revealed that the number and frequency of repairs, as well as the area and size of the damage, is increasing with the number of launches. The Space Shuttle Program has accepted the extensive ground processing costs for post launch repair of damaged areas and investigations of future launch related failures for the remainder of the program. There currently are no long term solutions available for Constellation Program ground operations to address the poor performance and subsequent failures of the refractory materials. Over the last three years, significant liberation of refractory material in the flame trench and fire bricks along the adjacent trench walls following Space Shuttle launches have resulted in extensive investigations of

  1. STS-86 Atlantis Launch

    NASA Technical Reports Server (NTRS)

    1997-01-01

    The Space Shuttle Atlantis blazes through the night sky to begin the STS-86 mission, slated to be the seventh of nine planned dockings of the Space Shuttle with the Russian Space Station Mir. Liftoff on Sept. 25 from Launch Pad 39A was at 10:34:19 p.m. EDT, within seconds of the preferred time, during a six-minute, 45- second launch window. The 10-day flight will include the transfer of the sixth U.S. astronaut to live and work aboard the Mir. After the docking, STS-86 Mission Specialist David A. Wolf will become a member of the Mir 24 crew, replacing astronaut C. Michael Foale, who will return to Earth aboard Atlantis with the remainder of the STS-86 crew. Foale has been on the Russian Space Station since mid-May. Wolf is scheduled to remain there about four months. Besides Wolf (embarking to Mir) and Foale (returning), the STS-86 crew includes Commander James D. Wetherbee, Pilot Michael J. Bloomfield, and Mission Specialists Wendy B. Lawrence, Scott E. Parazynski, Vladimir Georgievich Titov of the Russian Space Agency, and Jean-Loup J.M. Chretien of the French Space Agency, CNES. Other primary objectives of the mission are a spacewalk by Parazynski and Titov, and the exchange of about three-and-a-half tons of science/logistical equipment and supplies between Atlantis and the Mir.

  2. STS-86 Launch

    NASA Technical Reports Server (NTRS)

    1997-01-01

    The Space Shuttle Atlantis blazes through the night sky to begin the STS-86 mission, slated to be the seventh of nine planned dockings of the Space Shuttle with the Russian Space Station Mir. Liftoff on September 25 from Launch Pad 39A was at 10:34 p.m. EDT, within seconds of the preferred time, during a six minute, 45 second launch window. The 10 day flight will include the transfer of the sixth U.S. astronaut to live and work aboard the Mir. After the docking, STS-86 Mission Specialist David A. Wolf will become a member of the Mir 24 crew, replacing astronaut C. Michael Foale, who will return to Earth aboard Atlantis with the remainder of the STS-86 crew. Foale has been on the Russian Space Station since mid May. Wolf is scheduled to remain there about four months. Besides Wolf (embarking to Mir) and Foale (returning), the STS-86 crew includes Commander James D. Wetherbee, Pilot Michael J. Bloomfield, and Mission Specialists Wendy B. Lawrence, Scott E. Parazynski, Vladimir Georgievich Titov of the Russian Space Agency, and Jean-Loup J.M. Chretien of the French Space Agency, CNES. Other primary objectives of the mission are a spacewalk by Parazynski and Titov, and the exchange of about 3.5 tons of science/logistical equipment and supplies between Atlantis and the Mir.

  3. Mortar launched surveillance system

    NASA Astrophysics Data System (ADS)

    Lewis, Carl E.; Carlton, Lindley A.

    2001-02-01

    Accurate Automation Corporation has completed the conceptual design of a mortar launched air vehicle system to perform close range or over-the-horizon surveillance missions. Law enforcement and military units require an organic capability to obtain real time intelligence information of time critical targets. Our design will permit law enforcement to detect, classify, locate and track these time critical targets. The surveillance system is a simple, unmanned fixed-winged aircraft deployed via a conventional mortar tube. The aircraft's flight surfaces are deployed following mortar launch to permit maximum range and time over target. The aircraft and sensor system are field retrievable. The aircraft can be configured with an engine to permit extended time over target or range. The aircraft has an integrated surveillance sensor system; a programmable CMOS sensor array. The integrated RF transmitted to capable of down- linking real-time video over line-of-sight distances exceeding 10 kilometers. The major benefit of the modular design is the ability to provide surveillance or tracking quickly at a low cost. Vehicle operational radius and sensor field coverage as well as design trade results of vehicle range and endurance performance and payload capacity at operational range are presented for various mortar configurations.

  4. Magnetic Launch Assist

    NASA Technical Reports Server (NTRS)

    Jacobs, W. A.

    2000-01-01

    With the ever-increasing cost of getting to space and the need for safe, reliable, and inexpensive ways to access space, NASA is taking a look at technologies that will get us there. One of these technologies is Magnetic Launch Assist (MagLev). This is the concept of using both magnetic levitation and magnetic propulsion to provide an initial velocity by using electrical power from ground sources. The use of ground based power can significantly reduce operational costs over the consumables necessary to attain the same velocity. The technologies to accomplish this are both old and new. The concept of MagLev has been around for a long time and several MagLev Trains have already been made. Where NASA's MagLev diverges from the traditional train is in the immense power required to propel this vehicle to 600 feet per second in less than 10 seconds. New technologies or the upgrade of existing technologies will need to be investigated in areas of energy storage and power switching. Plus the separation of a very large mass (the space vehicle) and the aerodynamics of that vehicle while on the carrier are also of great concern and require considerable study and testing. NASA's plan is to mature these technologies in the next 10 years to achieve our goal of launching a full sized space vehicle off a MagLev rail.

  5. Comments on the commercialization of expendable launch vehicles

    NASA Technical Reports Server (NTRS)

    Trilling, D. R.

    1984-01-01

    The President's national space policy encourages private sector investment and involvement in civil space activities. Last November, the President designated the Department of Transportation as lead agency for the commercialization of expendable launch vehicles. This presents a substantial challenge to the United States Government, since the guidelines and requirements that are set now will have great influence on whether American firms can become a viable competitive industry in the world launch market. There is a dual need to protect public safety and free the private sector launch industry from needless regulatory barriers so that it can grow and prosper.

  6. Comments on the commercialization of expendable launch vehicles

    NASA Astrophysics Data System (ADS)

    Trilling, D. R.

    1984-10-01

    The President's national space policy encourages private sector investment and involvement in civil space activities. Last November, the President designated the Department of Transportation as lead agency for the commercialization of expendable launch vehicles. This presents a substantial challenge to the United States Government, since the guidelines and requirements that are set now will have great influence on whether American firms can become a viable competitive industry in the world launch market. There is a dual need to protect public safety and free the private sector launch industry from needless regulatory barriers so that it can grow and prosper.

  7. Magnetic Launch Assist System Demonstration

    NASA Technical Reports Server (NTRS)

    1999-01-01

    This Quick Time movie demonstrates the Magnetic Launch Assist system, previously referred to as the Magnetic Levitation (Maglev) system, for space launch using a 5 foot model of a reusable Bantam Class launch vehicle on a 50 foot track that provided 6-g acceleration and 6-g de-acceleration. Overcoming the grip of Earth's gravity is a supreme challenge for engineers who design rockets that leave the planet. Engineers at the Marshall Space Flight Center have developed and tested Magnetic Launch Assist technologies that could levitate and accelerate a launch vehicle along a track at high speeds before it leaves the ground. Using electricity and magnetic fields, a Magnetic Launch Assist system would drive a spacecraft along a horizontal track until it reaches desired speeds. A full-scale, operational track would be about 1.5-miles long and capable of accelerating a vehicle to 600 mph in 9.5 seconds. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the takeoff, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  8. Direct launch using the electric rail gun

    NASA Technical Reports Server (NTRS)

    Barber, J. P.

    1983-01-01

    The concept explored involves using a large single stage electric rail gun to achieve orbital velocities. Exit aerodynamics, launch package design and size, interior ballistics, system and component sizing and design concepts are treated. Technology development status and development requirements are identified and described. The expense of placing payloads in Earth orbit using conventional chemical rockets is considerable. Chemical rockets are very inefficient in converting chemical energy into payload kinetic energy. A rocket motor is relatively expensive and is usually expended on each launch. In addition specialized and expensive forms of fuel are required. Gun launching payloads directly to orbit from the Earth's surface is a possible alternative. Guns are much more energy efficient than rockets. The high capital cost of the gun installation can be recovered by reusing it over and over again. Finally, relatively inexpensive fuel and large quantities of energy are readily available to a fixed installation on the Earth's surface.

  9. eLaunch Hypersonics: An Advanced Launch System

    NASA Technical Reports Server (NTRS)

    Starr, Stanley

    2010-01-01

    This presentation describes a new space launch system that NASA can and should develop. This approach can significantly reduce ground processing and launch costs, improve reliability, and broaden the scope of what we do in near earth orbit. The concept (not new) is to launch a re-usable air-breathing hypersonic vehicle from a ground based electric track. This vehicle launches a final rocket stage at high altitude/velocity for the final leg to orbit. The proposal here differs from past studies in that we will launch above Mach 1.5 (above transonic pinch point) which further improves the efficiency of air breathing, horizontal take-off launch systems. The approach described here significantly reduces cost per kilogram to orbit, increases safety and reliability of the boost systems, and reduces ground costs due to horizontal-processing. Finally, this approach provides significant technology transfer benefits for our national infrastructure.

  10. A Diagnostic Technique for Formulating Market Strategies in Higher Education Based on Relative Competitive Position.

    ERIC Educational Resources Information Center

    Dolinsky, Arthur L.; Quazi, Hesan A.

    1994-01-01

    Importance-performance analysis, a marketing research technique using analysis of consumer attitudes toward salient product or service attributes, is found useful for colleges and universities in developing marketing strategies, particularly when competition is considered as an important dimension. Data are drawn from a survey of 252 students at 1…

  11. LAUNCH_BLTMS.DLL

    Energy Science and Technology Software Center (ESTSC)

    2005-12-14

    Postprocessor for the integration of the BLT-MS (Breach Leach Transport-Multi Species) code with GoldSim{trademark}. The program is intended as a DLL for use with a GoldSim{trademark}. The program is intended as a DLL for use with a GoldSim{trademark} model file. The code executes BTLMS.EXE using a standard BLT-MS input file and allocated parameters to memory for subsequent input of BLTMS.EXE output dat to a GoldSim{trademark} model file. This DLL is used for performing Monte Carlomore » analyses. The software is used as part of a modeling package that consists of BLTMS.EXE, GoldSim{trademark}, Read_BLT.DLL and Launch_BLTMS.DLL. The modeling package is used to run Monte Crlo analyses for performance assessment of Low level Radioactive Waste Repositories.« less

  12. STS-112 Launch

    NASA Technical Reports Server (NTRS)

    2002-01-01

    Space Shuttle Orbiter Atlantis hurdles toward space from Launch Pad 39B at Kennedy Space Center in Florida for the STS-112 mission. Liftoff occurred at 3:46pm EDT, October 7, 2002. Atlantis carried the Starboard-1 (S1) Integrated Truss Structure and the Crew and Equipment Translation Aid (CETA) Cart A. The S1 was the second truss structure installed on the International Space Station (ISS). It was attached to the S0 truss which was previously installed by the STS-110 mission. The CETA is the first of two human-powered carts that ride along the ISS railway, providing mobile work platforms for future space walking astronauts. The 11 day mission performed three space walks to attach the S1 truss.

  13. STS-92 Discovery Launch

    NASA Technical Reports Server (NTRS)

    2000-01-01

    Viewed from across the waters of Banana Creek, clouds of smoke and steam are illuminated by the flames from Space Shuttle Discovery'''s perfect on-time launch at 7:17 p.m. EDT. Discovery carries a crew of seven on a construction flight to the International Space Station. Discovery also carries a payload that includes the Integrated Truss Structure Z-1, first of 10 trusses that will form the backbone of the Space Station, and the third Pressurized Mating Adapter that will provide a Shuttle docking port for solar array installation on the sixth Station flight and Lab installation on the seventh Station flight. Discovery'''s landing is expected Oct. 22 at 2:10 p.m. EDT.

  14. Payload Launch Lock Mechanism

    NASA Technical Reports Server (NTRS)

    Young, Ken (Inventor); Hindle, Timothy (Inventor)

    2014-01-01

    A payload launch lock mechanism includes a base, a preload clamp, a fastener, and a shape memory alloy (SMA) actuator. The preload clamp is configured to releasibly restrain a payload. The fastener extends, along an axis, through the preload clamp and into the base, and supplies a force to the preload clamp sufficient to restrain the payload. The SMA actuator is disposed between the base and the clamp. The SMA actuator is adapted to receive electrical current and is configured, upon receipt of the electrical current, to supply a force that causes the fastener to elongate without fracturing. The preload clamp, in response to the fastener elongation, either rotates or pivots to thereby release the payload.

  15. STS-118 Launch

    NASA Technical Reports Server (NTRS)

    2007-01-01

    Enroute to the International Space Station (ISS), Space Shuttle Endeavor and its seven member STS-118 crew, blasted off from the launch pad at Kennedy Space Center on August 8, 2007. Construction resumed on the ISS as STS-118 mission specialists and the Expedition 15 crew completed installation of the third Starboard 5 (S-5) truss segment, removed a faulty Control Moment Gyroscope (CMG-3), installed a new CMG into the Z1 truss, relocated the S-band Antenna Sub-Assembly from the Port 6 (P6) to Port 1 (P1) truss, installed a new transponder on P1, retrieved the P6 transponder, and delivered roughly 5,000 pounds of equipment and supplies.

  16. STS-87 Columbia Launch

    NASA Technical Reports Server (NTRS)

    1997-01-01

    Like a rising sun lighting up the afternoon sky, the Space Shuttle Columbia soars from Launch Pad 39B at 2:46:00 p.m. EST, November 19, on the fourth flight of the United States Microgravity Payload and Spartan-201 satellite. The crew members include Mission Commander Kevin Kregel.; Pilot Steven Lindsey; Mission Specialists Kalpana Chawla, Ph.D., Winston Scott, and Takao Doi, Ph.D., of the National Space Development Agency of Japan; and Payload Specialist Leonid Kadenyuk of the National Space Agency of Ukraine. During the 16-day STS-87 mission, the crew will oversee experiments in microgravity; deploy and retrieve a solar satellite; and test a new experimental camera, the AERCam Sprint. Dr. Doi and Scott also will perform a spacewalk to practice International Space Station maneuvers.

  17. The Launch of an Atlas/Centaur Launch Vehicle

    NASA Technical Reports Server (NTRS)

    1978-01-01

    The launch of an Atlas/Centaur launch vehicle is shown in this photograph. The Atlas/Centaur, launched on November 13, 1978, carried the High Energy Astronomy Observatory (HEAO)-2 into the required orbit. The second observatory, the HEAO-2 (nicknamed the Einstein Observatory in honor of the centernial of the birth of Albert Einstein) carried the first telescope capable of producing actual photographs of x-ray objects.

  18. Achieving a Launch on Demand Capability

    NASA Astrophysics Data System (ADS)

    Greenberg, Joel S.

    2002-01-01

    The ability to place payloads [satellites] into orbit as and when required, often referred to as launch on demand, continues to be an elusive and yet largely unfulfilled goal. But what is the value of achieving launch on demand [LOD], and what metrics are appropriate? Achievement of a desired level of LOD capability must consider transportation system thruput, alternative transportation systems that comprise the transportation architecture, transportation demand, reliability and failure recovery characteristics of the alternatives, schedule guarantees, launch delays, payload integration schedules, procurement policies, and other factors. Measures of LOD capability should relate to the objective of the transportation architecture: the placement of payloads into orbit as and when required. Launch on demand capability must be defined in probabilistic terms such as the probability of not incurring a delay in excess of T when it is determined that it is necessary to place a payload into orbit. Three specific aspects of launch on demand are considered: [1] the ability to recover from adversity [i.e., a launch failure] and to keep up with the steady-state demand for placing satellites into orbit [this has been referred to as operability and resiliency], [2] the ability to respond to the requirement to launch a satellite when the need arises unexpectedly either because of an unexpected [random] on-orbit satellite failure that requires replacement or because of the sudden recognition of an unanticipated requirement, and [3] the ability to recover from adversity [i.e., a launch failure] during the placement of a constellation into orbit. The objective of this paper is to outline a formal approach for analyzing alternative transportation architectures in terms of their ability to provide a LOD capability. The economic aspect of LOD is developed by establishing a relationship between scheduling and the elimination of on-orbit spares while achieving the desired level of on

  19. KSC Vertical Launch Site Evaluation

    NASA Technical Reports Server (NTRS)

    Phillips, Lynne V.

    2007-01-01

    RS&H was tasked to evaluate the potential available launch sites for a combined two user launch pad. The Launch sites were to be contained entirely within current Kennedy Space Center property lines. The user launch vehicles to be used for evaluation are in the one million pounds of first stage thrust range. Additionally a second evaluation criterion was added early on in the study. A single user launch site was to be evaluated for a two million pound first stage thrust vehicle. Both scenarios were to be included in the report. To provide fidelity to the study criteria, a specific launch vehicle in the one million pound thrust range was chosen as a guide post or straw-man launch vehicle. The RpK K-1 vehicle is a current Commercial Orbital Transportation System (COTS), contract awardee along with the SpaceX Falcon 9 vehicle. SpaceX, at the time of writing, is planning to launch COTS and possibly other payloads from Cx-40 on Cape Canaveral Air Force Station property. RpK has yet to declare a specific launch site as their east coast US launch location. As such it was deemed appropriate that RpK's vehicle requirements be used as conceptual criteria. For the purposes of this study those criteria were marginally generalized to make them less specifiC.

  20. Reusable launch vehicle facts and fantasies

    NASA Astrophysics Data System (ADS)

    Kaplan, Marshall H.

    2002-01-01

    Many people refuse to address many of the realities of reusable launch vehicle systems, technologies, operations and economics. Basic principles of physics, space flight operations, and business limitations are applied to the creation of a practical vision of future expectations. While reusable launcher concepts have been proposed for several decades, serious review of potential designs began in the mid-1990s, when NASA decided that a Space Shuttle replacement had to be pursued. A great deal of excitement and interest was quickly generated by the prospect of ``orders-of-magnitude'' reduction in launch costs. The potential for a vastly expanded space program motivated the entire space community. By the late-1990s, and after over one billion dollars were spent on the technology development and privately-funded concepts, it had become clear that there would be no new, near-term operational reusable vehicle. Many factors contributed to a very expensive and disappointing effort to create a new generation of launch vehicles. It began with overly optimistic projections of technology advancements and the belief that a greatly increased demand for satellite launches would be realized early in the 21st century. Contractors contributed to the perception of quickly reachable technology and business goals, thus, accelerating the enthusiasm and helping to create a ``gold rush'' euphoria. Cost, schedule and performance margins were all highly optimistic. Several entrepreneurs launched start up companies to take advantage of the excitement and the availability of investor capital. Millions were raised from private investors and venture capitalists, based on little more than flashy presentations and animations. Well over $500 million were raised by little-known start up groups to create reusable systems, which might complete for the coming market in launch services. By 1999, it was clear that market projections, made just two years earlier, were not going to be realized. Investors

  1. Microwave Anisotrophy Probe Launch and Early Operations

    NASA Technical Reports Server (NTRS)

    ODonnell, James R., Jr.; Andrews, Stephen F.; Starin, Scott R.; Ward, David K.; Bauer, Frank H. (Technical Monitor)

    2002-01-01

    The Microwave Anisotropy Probe (MAP), a follow-on to the Differential Microwave Radiometer (DMR) instrument on the Cosmic Background Explorer (COBE), was launched from the Kennedy Space Center at 19:46:46 UTC on June 30, 2001. The powered flight and separation from the Delta II appeared to go as designed, with the launch placing MAP well within sigma launch dispersion and with less than 7 Nms of tip-off momentum. Because of this relatively low momentum, MAP was able to acquire the sun within only 15 minutes with a battery state of charge of 94%. After MAP's successful launch, a six week period of in-orbit checkout and orbit maneuvers followed. The dual purpose of the in-orbit checkout period was to validate the correct performance of all of MAP's systems and, from the attitude control system (ACS) point of view, to calibrate the performance of the spacecraft ACS sensors and actuators to maximize system performance. In addition to the checkout activities performed by the MAP team, the other critical activity taking place during the first six weeks after launch were a series of orbit maneuvers necessary to get the spacecraft from its launch orbit out to its desired orbit about L2, the second Earth-Sun Lagrange point. As MAP continues its standard operations, its ACS design is meeting all of its requirements to successfully complete the mission. This paper will describe the launch and early operations summarized above in greater detail, and show the performance of the attitude control and attitude determination system versus its requirements. Additionally, some of the unexpected events that occurred during this period will be discussed, including two events which dropped the spacecraft into its Safehold Mode and the presence of an "anomalous force" observed during each of the perigee orbit maneuvers that had the potential to cause these critical maneuvers to be prematurely aborted.

  2. 14 CFR 417.125 - Launch of an unguided suborbital launch vehicle.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... Launch of an unguided suborbital launch vehicle. (a) Applicability. This section applies only to a launch operator conducting a launch of an unguided suborbital launch vehicle. (b) Need for flight safety system. A launch operator must launch an unguided suborbital launch vehicle with a flight safety system...

  3. 14 CFR 417.125 - Launch of an unguided suborbital launch vehicle.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... Launch of an unguided suborbital launch vehicle. (a) Applicability. This section applies only to a launch operator conducting a launch of an unguided suborbital launch vehicle. (b) Need for flight safety system. A launch operator must launch an unguided suborbital launch vehicle with a flight safety system...

  4. 14 CFR 417.125 - Launch of an unguided suborbital launch vehicle.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... Launch of an unguided suborbital launch vehicle. (a) Applicability. This section applies only to a launch operator conducting a launch of an unguided suborbital launch vehicle. (b) Need for flight safety system. A launch operator must launch an unguided suborbital launch vehicle with a flight safety system...

  5. Design of launch systems using continuous improvement process

    NASA Technical Reports Server (NTRS)

    Brown, Richard W.

    1995-01-01

    The purpose of this paper is to identify a systematic process for improving ground operations for future launch systems. This approach is based on the Total Quality Management (TQM) continuous improvement process. While the continuous improvement process is normally identified with making incremental changes to an existing system, it can be used on new systems if they use past experience as a knowledge base. In the case of the Reusable Launch Vehicle (RLV), the Space Shuttle operations provide many lessons. The TQM methodology used for this paper will be borrowed from the United States Air Force 'Quality Air Force' Program. There is a general overview of the continuous improvement process, with concentration on the formulation phase. During this phase critical analyses are conducted to determine the strategy and goals for the remaining development process. These analyses include analyzing the mission from the customers point of view, developing an operations concept for the future, assessing current capabilities and determining the gap to be closed between current capabilities and future needs and requirements. A brief analyses of the RLV, relative to the Space Shuttle, will be used to illustrate the concept. Using the continuous improvement design concept has many advantages. These include a customer oriented process which will develop a more marketable product and a better integration of operations and systems during the design phase. But, the use of TQM techniques will require changes, including more discipline in the design process and more emphasis on data gathering for operational systems. The benefits will far outweigh the additional effort.

  6. Marketing Reference Services.

    ERIC Educational Resources Information Center

    Norman, O. Gene

    1995-01-01

    Relates the marketing concept to library reference services. Highlights include a review of the literature and an overview of marketing, including research, the marketing mix, strategic plan, marketing plan, and marketing audit. Marketing principles are applied to reference services through the marketing mix elements of product, price, place, and…

  7. Telecommunication service markets through the year 2000 in relation to millimeter wave satellite systems

    NASA Technical Reports Server (NTRS)

    Stevenson, S. M.

    1979-01-01

    NASA is currently conducting a series of millimeter wave satellite system market studies to develop 30/20 GHz satellite system concepts that have commercial potential. Four contractual efforts were undertaken: two parallel and independent system studies and two parallel and independent market studies. The marketing efforts are focused on forecasting the total domestic demand for long haul telecommunications services for the 1980-2000 period. Work completed to date and reported in this paper include projections of: geographical distribution of traffic; traffic volume as a function of urban area size; and user identification and forecasted demand.

  8. 59 FR- Marketing and Selling Real Property on an Individual Basis and Disposition of Real Estate-Related...

    Federal Register 2010, 2011, 2012, 2013, 2014

    1994-11-23

    ... Disposition of Real Estate-Related Assets AGENCY: Resolution Trust Corporation. ACTION: Final rule. SUMMARY... marketing of real estate owned (REO) assets on an individual basis and for the disposition of REO assets with a book value of more than $400,000 and non-performing real estate loans with a book value of...

  9. 59 FR- Marketing and Selling Real Property on an Individual Basis and Disposition of Real Estate-Related...

    Federal Register 2010, 2011, 2012, 2013, 2014

    1994-09-19

    ... Disposition of Real Estate-Related Assets AGENCY: Resolution Trust Corporation. ACTION: Interim rule with... subsections (w)(2) and (3) for the marketing of real estate owned (REO) assets on an individual basis and for the disposition of REO assets with a book value of more than $400,000 and non-performing real...

  10. Learning with LinkedIn: Students' Perceptions of Incorporating Subject-Related Blogging in an International Marketing Course

    ERIC Educational Resources Information Center

    Galan, Nataliya; Khodabandehloo, Akbar

    2016-01-01

    Purpose: This paper aims to report the results of implementation of blogging within a LinkedIn discussion group in an international marketing course for a multicultural group of students focusing on the students' perceptions of the subject-related blogging. Design/Methodology/ Approach: This study adopts a qualitative approach; data have been…

  11. 17 CFR 240.15g-2 - Penny stock disclosure document relating to the penny stock market.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... required by paragraph (a) of this section for the period specified in 17 CFR 240.17a-4(b) of this chapter... 17 Commodity and Securities Exchanges 3 2011-04-01 2011-04-01 false Penny stock disclosure document relating to the penny stock market. 240.15g-2 Section 240.15g-2 Commodity and Securities...

  12. Developing and Evaluating a Multimodal Course Format: Danish for Knowledge Workers--Labour Market-Related Danish

    ERIC Educational Resources Information Center

    Frederiksen, Karen-Margrete; Laursen, Katja Årosin

    2015-01-01

    This paper presents our reflections on developing the Computer-Assisted Language Learning (CALL) course "Danish for knowledge workers--labour market-related Danish." As defined by Laursen and Frederiksen (2015), knowledge workers are "highly educated people who typically work at universities, at other institutions of higher…

  13. Launch of STS-63 Discovery

    NASA Technical Reports Server (NTRS)

    1995-01-01

    This wide lux image of the Space Shuttle Discovery as it began its race to catch up with Russia's Mir Space Station shows the base of the launch pad as well as the orbiter just clearing the gantry. Liftoff from Launch Pad 39B, Kennedy Space Center (KSC) occurred at 12:22:04 (EST) February 3, 1995. Discovery is the first in the current fleet of four space shuttle vehicles to make 20 launches.

  14. Launch of STS-63 Discovery

    NASA Technical Reports Server (NTRS)

    1995-01-01

    A 35mm camera was used to expose this image of the Space Shuttle Discovery as it began its race to catch up with Russia's Mir Space Station. Liftoff from Launch Pad 39B, Kennedy Space Center (KSC) occurred at 12:22:04 (EST) February 3, 1995. Discovery is the first in the current fleet of four space shuttle vehicles to make 20 launches. The launch pad and orbiter can be seen reflected in the water directly in front of it.

  15. Launch of STS-63 Discovery

    NASA Technical Reports Server (NTRS)

    1995-01-01

    A 70mm camera was used to expose this image of the Space Shuttle Discovery as it began its race to catch up with Russia's Mir Space Station. Liftoff from Launch Pad 39B, Kennedy Space Center (KSC) occurred at 12:22:04 (EST) February 3, 1995. Discovery is the first in the current fleet of four space shuttle vehicles to make 20 launches. The launch pad and orbiter can be seen reflected in the water directly in front of it.

  16. Peer Review of Launch Environments

    NASA Technical Reports Server (NTRS)

    Wilson, Timmy R.

    2011-01-01

    Catastrophic failures of launch vehicles during launch and ascent are currently modeled using equivalent trinitrotoluene (TNT) estimates. This approach tends to over-predict the blast effect with subsequent impact to launch vehicle and crew escape requirements. Bangham Engineering, located in Huntsville, Alabama, assembled a less-conservative model based on historical failure and test data coupled with physical models and estimates. This white paper summarizes NESC's peer review of the Bangham analytical work completed to date.

  17. Assembly vs. direct launch of transfer vehicles

    NASA Technical Reports Server (NTRS)

    Katzberg, Stephen J.; Pritchard, E. Brian

    1990-01-01

    A top level assessment is performed of the relative impacts of on-orbit assembly of the lunar or Mars transfer vehicles versus direct launch. The objective is to identify the major option paths for the Earth-to-orbit, ETO, transportation systems. Heavy lift launch vehicles, if large enough, could reduce or eliminate on-orbit assembly. However, with every new approach, there are always counter-balancing considerations and it is the objective to begin the delineation of the necessary follow-on trade study issues.

  18. Control of the launch of attosecond pulses

    SciTech Connect

    Cao Wei; Lu Peixiang; Lan Pengfei; Wang Xinlin; Li Yuhua

    2007-06-15

    We propose an approach to steer the launch of attosecond (as) pulses with a high precision. We numerically demonstrate that by adding a weak second-harmonic (SH) field to the fundamental beam the ionization and recollision process of the electron will be perturbed, which can induce a variation of the emission time of high harmonics. Through modifying the relative intensity of the SH and fundamental fields, the launch of as pulses can be manipulated with a resolution less than 40 as. This will show significant potential for ultrafast optics.

  19. An investigation of electromagnetic launch repeatability

    NASA Astrophysics Data System (ADS)

    Cornette, James B.; Heyse, Mark W.; Brown, Jere L.

    1993-01-01

    Electromagnetic launcher (EML) performance repeatability has been identified as a potential development issue for several years. Investigation of this issue has been difficult because an EML that is powered on a relatively continuous basis to provide long duration operation has not been available. A battery charged capacitor power system has enabled long duration, 6 to 7 seconds, EML experiments. This paper provides a summary of an experiment to investigate EML launch to launch performance consistency. A series of 8 ten-shot bursts, each separated by 15 to 30 minutes, performed in a single day using a single set of bore materials is the subject of this paper.

  20. Study to forecast and determine characteristics of world satellite communications market

    NASA Technical Reports Server (NTRS)

    Filep, R. T.; Schnapf, A.; Fordyce, S. W.

    1983-01-01

    The world commercial communications satellite market during the spring and summer of 1983 was examined and characteristics and forecasts of the market extending to the year 2000 were developed. Past, present and planned satellites were documented in relation to frequencies, procurement and launch dates, costs, transponders, and prime contractor. Characteristics of the market are outlined for the periods 1965 - 1985, 1986 - 1989, and 1990 - 2000. Market share forecasts, discussions of potential competitors in various world markets, and profiles of major communication satellite manufacturing and user countries are documented.

  1. Rocket Launch Trajectory Simulations Mechanism

    NASA Technical Reports Server (NTRS)

    Margasahayam, Ravi; Caimi, Raoul E.; Hauss, Sharon; Voska, N. (Technical Monitor)

    2002-01-01

    The design and development of a Trajectory Simulation Mechanism (TSM) for the Launch Systems Testbed (LST) is outlined. In addition to being one-of-a-kind facility in the world, TSM serves as a platform to study the interaction of rocket launch-induced environments and subsequent dynamic effects on the equipment and structures in the close vicinity of the launch pad. For the first time, researchers and academicians alike will be able to perform tests in a laboratory environment and assess the impact of vibroacoustic behavior of structures in a moving rocket scenario on ground equipment, launch vehicle, and its valuable payload or spacecraft.

  2. Commonality of Ground Systems in Launch Operations

    NASA Technical Reports Server (NTRS)

    Quinn, Shawn M.

    2008-01-01

    NASA is examining the utility of requiring a certain degree of commonality in both flight and ground systems in the Constellation Program. While the benefits of commonality seem obvious in terms of minimizing upfront development and long-term operations and maintenance costs, success in real, large-scale engineering systems used to support launch operations is relatively unknown. A broad literature review conducted for this paper did not yield a single paper specifically addressing the application of commonality for ground systems at any launch site in the United States or abroad. This paper provides a broad overview of the ground systems, captures historical and current application of commonality at the launch site, and offers suggestions for additional research to further develop commonality approaches.

  3. 14 CFR 415.121 - Launch schedule.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... TRANSPORTATION LICENSING LAUNCH LICENSE Safety Review and Approval for Launch of an Expendable Launch Vehicle From a Non-Federal Launch Site § 415.121 Launch schedule. An applicant's safety review document must... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Launch schedule. 415.121 Section...

  4. 14 CFR 415.121 - Launch schedule.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... TRANSPORTATION LICENSING LAUNCH LICENSE Safety Review and Approval for Launch of an Expendable Launch Vehicle From a Non-Federal Launch Site § 415.121 Launch schedule. An applicant's safety review document must... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Launch schedule. 415.121 Section...

  5. 14 CFR 415.121 - Launch schedule.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... TRANSPORTATION LICENSING LAUNCH LICENSE Safety Review and Approval for Launch of an Expendable Launch Vehicle From a Non-Federal Launch Site § 415.121 Launch schedule. An applicant's safety review document must... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Launch schedule. 415.121 Section...

  6. 14 CFR 415.121 - Launch schedule.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... TRANSPORTATION LICENSING LAUNCH LICENSE Safety Review and Approval for Launch of an Expendable Launch Vehicle From a Non-Federal Launch Site § 415.121 Launch schedule. An applicant's safety review document must... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Launch schedule. 415.121 Section...

  7. 14 CFR 415.119 - Launch plans.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... TRANSPORTATION LICENSING LAUNCH LICENSE Safety Review and Approval for Launch of an Expendable Launch Vehicle From a Non-Federal Launch Site § 415.119 Launch plans. An applicant's safety review document must... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Launch plans. 415.119 Section...

  8. 14 CFR 415.119 - Launch plans.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... TRANSPORTATION LICENSING LAUNCH LICENSE Safety Review and Approval for Launch of an Expendable Launch Vehicle From a Non-Federal Launch Site § 415.119 Launch plans. An applicant's safety review document must... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Launch plans. 415.119 Section...

  9. Technical Barriers, Gaps,and Opportunities Related to Home Energy Upgrade Market Delivery

    SciTech Connect

    Bianchi, Marcus V.A.

    2011-11-01

    This report outlines the technical barriers, gaps, and opportunities that arise in executing home energy upgrade market delivery approaches, as identified through research conducted by the U.S. Department of Energy's Building America program.

  10. 7. OVERALL VIEW OF LAUNCH PAD, SHOWING HELIPAD AT LAUNCH ...

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

    7. OVERALL VIEW OF LAUNCH PAD, SHOWING HELIPAD AT LAUNCH AREA, WHEN VIEWED WITH NEGATIVE NO. CA-57-8(BELOW), LOOKING NORTH. BASKETBALL COURT IN BACKGROUND Everett Weinreb, photographer, March 1988 - Mount Gleason Nike Missile Site, Angeles National Forest, South of Soledad Canyon, Sylmar, Los Angeles County, CA

  11. Size, Book-to-Market Ratio and Relativity of Accounting Information Value: Empirical Research on the Chinese Listed Company

    NASA Astrophysics Data System (ADS)

    Yu, Jing; Cheng, Siwei; Xu, Bin

    Recently there are many literatures studying the effect of factors such as size or book-market ratio on fluctuation of accounting earnings, stock price or earnings respectively, but so far their affection on accounting information value relativity has been scarcely addressed. This paper presents the detail analyses of their effect of the two factors to the relativity of accounting information value respectively by taking Shanghai and Shenzhen stock markets as sample. And the analyses supports the following two hypotheses, (1) The relativity of accounting information value of big size corporation is more than that of small size corporation. (2) The relativity of accounting information value of low B/M ratio corporation is more than that of low B/M ratio corporation.

  12. Co-axial geometry electromagnetic launch to space

    SciTech Connect

    Turman, B.N.; Lipinski, R.J.; Palmer, M.R.; Leung, E.M.W.

    1994-09-01

    Small or moderate-weight space launches could significantly benefit from an electrically powered launch complex, based on an electromagnetic coil launcher. This paper presents results of studies to estimate the required launcher parameters, and estimate the cost of such a launch facility. This study is based on electromagnetic launch, or electromagnetic gun technology which is constrained to a coaxial geometry to take advantage of the efficiency of closely-coupled coils. This geometry, along with reasonable constraints on the length and power requirements for the launcher, match most naturally to relatively small satellites in low-earth orbits. The launcher energy and power requirements fall in the range of 60 - 260 GJ and 20 - 400 GW electric. Parametric evaluations have been conducted with a launcher length of 1-2 km, exit velocity of 1 - 6 km/s, and payloads of 100 - 1000 kg. The launch requires high acceleration, so the satellite package must be hardened. The EM launch complex could greatly reduce the amount of fuels handling, reduce the turnaround time between launches, allow more concurrence in launch preparation, reduce the manpower requirements for launch vehicle preparation and increase the reliability of launch by using more standardized vehicle preparations.

  13. STS-82 Discovery Launch

    NASA Technical Reports Server (NTRS)

    1997-01-01

    The Space Shuttle Discovery cuts a bright swath through the early-morning darkness as it lifts off from Launch Pad 39A on a scheduled 10-day flight to service the Hubble Space Telescope (HST). Liftoff of Mission STS-82 occurred on-time at 3:55:17 a.m. EST, Feb. 11, 1997. Leading the veteran crew is Mission Commander Kenneth D. Bowersox. Scott J. 'Doc' Horowitz is the pilot. Mark C. Lee is the payload commander. Rounding out the seven-member crew are Mission Specialists Steven L. Smith, Gregory J. Harbaugh, Joseph R. 'Joe' Tanner and Steven A. Hawley. Four of the astronauts will be divided into two teams to perform the scheduled four back-to-back extravehicular activities (EVAs) or spacewalks. Lee and Smith will team up for EVAs 1 and 3 on flight days 4 and 6; Harbaugh and Tanner will perform EVAs 2 and 4 on flight days 5 and 7. Among the tasks will be to replace two outdated scientific instruments with two new instruments the Space Telescope Imaging Spectrograph (STIS) and the Near Infrared Camera and Multi-Object Spectrometer (NICMOS). This is the second servicing mission for HST, which was originally deployed in 1990 and designed to be serviced on-orbit about every three years. Hubble was first serviced in 1993. STS-82 is the second of eight planned flights in 1997. It is the 22nd flight of Discovery and the 82nd Shuttle mission.

  14. STS-82 launch

    NASA Technical Reports Server (NTRS)

    1997-01-01

    The Space Shuttle Discovery cuts a bright swath through the early-morning darkness as it lifts off from Launch Pad 39A on a scheduled 10-day flight to service the Hubble Space Telescope (HST). Liftoff of Mission STS-82 occurred on-time at 3:55:17 a.m. EST, Feb. 11, 1997. Leading the veteran crew is Mission Commander Kenneth D. Bowersox. Scott J. 'Doc' Horowitz is the pilot. Mark C. Lee is the payload commander. Rounding out the seven-member crew are Mission Specialists Steven L. Smith, Gregory J. Harbaugh, Joseph R. 'Joe' Tanner and Steven A. Hawley. Four of the astronauts will be divided into two teams to perform the scheduled four back-to-back extravehicular activities (EVAs) or spacewalks. Lee and Smith will team up for EVAs 1 and 3 on flight days 4 and 6; Harbaugh and Tanner will perform EVAs 2 and 4 on flight days 5 and 7. Among the tasks will be to replace two outdated scientific instruments with two new instruments - the Space Telescope Imaging Spectrograph (STIS) and the Near Infrared Camera and Multi-Object Spectrometer (NICMOS). This is the second servicing mission for HST, which was originally deployed in 1990 and designed to be serviced on-orbit about every three years. Hubble was first serviced in 1993. STS-82 is the second of eight planned flights in 1997. It is the 22nd flight of Discovery and the 82nd Shuttle mission.

  15. STS-85 Discovery Launch

    NASA Technical Reports Server (NTRS)

    1997-01-01

    Blasting through the hazy late morning sky, the Space Shuttle Discovery soars from Launch Pad 39A at 10:41 a.m. EDT Aug. 7 on the 11-day STS-85 mission. Aboard Discovery are Commander Curtis L. Brown, Jr.; Pilot Kent V. Rominger, Payload Commander N. Jan Davis, Mission Specialist Robert L. Curbeam, Jr., Mission Specialist Stephen K. Robinson and Payload Specialist Bjarni V. Tryggvason, a Canadian Space Agency astronaut . The primary payload aboard the Space Shuttle orbiter Discovery is the Cryogenic Infrared Spectrometers and Telescopes for the Atmosphere-Shuttle Pallet Satellite-2 (CRISTA-SPAS-2) free-flyer. The CRISTA-SPAS-2 will be deployed on flight day 1 to study trace gases in the Earths atmosphere as a part of NASAs Mission to Planet Earth program. Also aboard the free-flying research platform will be the Middle Atmosphere High Resolution Spectrograph Instrument (MAHRSI). Other payloads on the 11-day mission include the Manipulator Flight Demonstration (MFD), a Japanese Space Agency-sponsored experiment. Also in Discoverys payload bay are the Technology Applications and Science-1 (TAS-1) and International Extreme Ultraviolet Hitchhiker-2 (IEH-2) experiments.

  16. Launch Support Video Site

    NASA Technical Reports Server (NTRS)

    OFarrell, Zachary L.

    2013-01-01

    The goal of this project is to create a website that displays video, countdown clock, and event times to customers during launches, without needing to be connected to the internal operations network. The requirements of this project are to also minimize the delay in the clock and events to be less than two seconds. The two parts of this are the webpage, which will display the data and videos to the user, and a server to send clock and event data to the webpage. The webpage is written in HTML with CSS and JavaScript. The JavaScript is responsible for connecting to the server, receiving new clock data, and updating the webpage. JavaScript is used for this because it can send custom HTTP requests from the webpage, and provides the ability to update parts of the webpage without having to refresh the entire page. The server application will act as a relay between the operations network, and the open internet. On the operations network side, the application receives multicast packets that contain countdown clock and events data. It will then parse the data into current countdown times and events, and create a packet with that information that can be sent to webpages. The other part will accept HTTP requests from the webpage, and respond to them with current data. The server is written in C# with some C++ files used to define the structure of data packets. The videos for the webpage will be shown in an embedded player from UStream.

  17. Knowledge, Attitudes, and Practices (KAP) Relating to Avian Influenza (H10N8) among Farmers’ Markets Workers in Nanchang, China

    PubMed Central

    Guo, Shuangli; Wu, Jingwen; Wang, Bin; Hu, Wei; Sun, Yanshuang; Li, Hui; Liu, Mingbin; Moore, Justin B.; Chen, Haiying

    2015-01-01

    Three cases of avian influenza virus H10N8 were reported in Nanchang, China, as of April 2014. To identify the knowledge, attitudes, and practices (KAP) related to H10N8 among farmers’ market workers, a cross-sectional survey was conducted in 63 farmers’ markets in Nanchang. Using the resulting data, characteristics of poultry and non-poultry workers’ knowledge, attitudes, and practice were described. Results suggest that interventions targeting high-risk workers should be developed and implemented by public health agencies to prevent the spread of H10N8. Additionally policies that encourage farmers’ market workers to receive influenza vaccine should be developed, adopted, and enforced. PMID:25993111

  18. Rockot Launch Vehicle Commercial Operations for Grace and Iridium Program

    NASA Astrophysics Data System (ADS)

    Viertel, Y.; Kinnersley, M.; Schumacher, I.

    2002-01-01

    The GRACE mission and the IRIDIUM mission on ROCKOT launch vehicle are presented. Two identical GRACE satellites to measure in tandem the gravitational field of the earth with previously unattainable accuracy - it's called the Gravity Research and Climate Experiment, or and is a joint project of the U.S. space agency, NASA and the German Centre for Aeronautics and Space Flight, DLR. In order to send the GRACE twins into a 500x500 km , 89deg. orbit, the Rockot launch vehicle was selected. A dual launch of two Iridium satellites was scheduled for June 2002 using the ROCKOT launch vehicle from Plesetsk Cosmodrome in Northern Russia. This launch will inject two replacement satellites into a low earth orbit (LEO) to support the maintenance of the Iridium constellation. In September 2001, Eurockot successfully carried out a "Pathfinder Campaign" to simulate the entire Iridium mission cycle at Plesetsk. The campaign comprised the transport of simulators and related equipment to the Russian port-of-entry and launch site and also included the integration and encapsulation of the simulators with the actual Rockot launch vehicle at Eurockot's dedicated launch facilities at Plesetsk Cosmodrome. The pathfinder campaign lasted four weeks and was carried out by a joint team that also included Khrunichev, Russian Space Forces and Eurockot personnel on the contractors' side. The pathfinder mission confirmed the capability of Eurockot Launch Services to perform the Iridium launch on cost and on schedule at Plesetsk following Eurockot's major investment in international standard preparation, integration and launch facilities including customer facilities and a new hotel. In 2003, Eurockot will also launch the Japanese SERVI'S-1 satellite for USEF. The ROCKOT launch vehicle is a 3 stage liquid fuel rocket whose first 2 stages have been adapted from the Russian SS-19. A third stage, called "Breeze", can be repeatedly ignited and is extraordinarily capable of manoeuvre. Rockot can place

  19. Launch Vehicle Assessment for Space Solar Power

    NASA Technical Reports Server (NTRS)

    Olds, John R.

    1998-01-01

    A recently completed study at Georgia Tech examined various launch vehicle options for deploying a future constellation of Space Solar Power satellites of the Suntower configuration. One of the motivations of the study was to determine whether the aggressive $400/kg launch price goal established for SSP package delivery would result in an attractive economic scenario for a future RLV developer. That is, would the potential revenue and traffic to be derived from a large scale SSP project be enough of an economic "carrot" to attract an RLV company into developing a new, low cost launch vehicle to address this market. Preliminary results presented in the attached charts show that there is enough economic reward for RLV developers, specifically in the case of the latest large GEO-based Suntower constellations (over 15,500 MT per year delivery for 30 years). For that SSP model, internal rates of return for the 30 year economic scenario exceed 22%. However, up-front government assistance to the RLV developer in terms of ground facilities, operations technologies, guaranteed low-interest rate loans, and partial offsets of some vehicle development expenses is necessary to achieve these positive results. This white paper is meant to serve as a companion to the data supplied in the accompanying charts. It's purpose is to provide more detail on the vehicles and design processes used, to highlight key decisions and issues, and to emphasize key results from each phase of the Georgia Tech study.

  20. Launch mission summary: FLTSATCOM-D Atlas/Centaur-57

    NASA Technical Reports Server (NTRS)

    1980-01-01

    The largest and heaviest spacecraft yet to be launched into geosynchronous orbit by an Atlas Centaur launch vehicle, FLTSATCOM D is part of a versatile military satellite communication system which includes terminals at Navy land bases, and on naval aircraft, ships, and submarines. The design and capabilities of the launch vehicle are described as well as those of the satellite. Information relative to launch windows, flight plan, radar and telemetry coverage, selected trajectory information is presented. A brief sequence of flight events is included.

  1. Marketing fundamentals.

    PubMed

    Redmond, W H

    2001-01-01

    This chapter outlines current marketing practice from a managerial perspective. The role of marketing within an organization is discussed in relation to efficiency and adaptation to changing environments. Fundamental terms and concepts are presented in an applied context. The implementation of marketing plans is organized around the four P's of marketing: product (or service), promotion (including advertising), place of delivery, and pricing. These are the tools with which marketers seek to better serve their clients and form the basis for competing with other organizations. Basic concepts of strategic relationship management are outlined. Lastly, alternate viewpoints on the role of advertising in healthcare markets are examined. PMID:11401791

  2. Delta launch vehicle accident investigation

    NASA Astrophysics Data System (ADS)

    1986-03-01

    The text of the testimony given by several witnesses during the House hearings on the Delta launch vehicle accident of May 3, 1986 is given. Pre-launch procedures, failure analysis, the possibility of sabotage, and design and testing are among the topics discussed.

  3. Beyond Percheron - Launch vehicle systems from the private sector

    NASA Astrophysics Data System (ADS)

    Horne, W. C.; Pavia, T. C.; Schrick, B. L.; Wolf, R. S.; Fruchterman, J. R.; Ross, D. J.

    Private ventures for operation of spacecraft launching services are discussed in terms of alternative strategies for commercialization of space activities. The Percheron was the product of a philosophy of a cost-, rather than a weight-, minimized a lunch vehicle. Although the engine exploded during a static test firing, other private projects continued, including the launch of the Conestoga, an Aries second stage Minuteman I. Consideration is being directed toward commercial production and launch of the Delta rocket, and $1 and a $1.5 billion offers have been tendered for financing a fifth Orbiter for NASA in exchange for marketing rights. Funding for the ventures is contingent upon analyses of the size and projected growth rate of payload markets, a favorable national policy, investor confidence, and agreeable capitalization levels. It is shown that no significant barriers exist against satisfying the criteria, and private space ventures are projected to result in more cost-effective operations due to increased competition.

  4. Marketing 101.

    ERIC Educational Resources Information Center

    Henderson, Karla A.

    1997-01-01

    A marketing model for camps includes a mix of services, presentation, and communication elements that promote the virtues of camp, convince potential campers and their families of the benefits of camp, and successfully distinguish the camp from others. Includes resources related to marketing strategies, theme merchandise, and market trends…

  5. No Launch Before Its Time

    NASA Technical Reports Server (NTRS)

    Townsend, Bill

    2004-01-01

    Aura is an Earth-observing satellite developed to help us study the quality of the air we breathe. It will look at the state of the ozone and the atmospheric composition in regards to the Earth's changing climate. I headed to California on July 5, 2004. The plan was that the satellite would launch on the tenth, but we had a few problems getting it off. This was the fifty-ninth launch of my career, and it was also a little different than most of my previous launches. Most of the time it's weather that postpones a launch; there aren't usually that many technical issues this late in the game. This time. however, we had several problems, equally split between the launch vehicle and the spacecraft. I remember a member of the crew asking me, 'Is this normal?' And in my experience, it wasn't.

  6. STS-51 Launch

    NASA Technical Reports Server (NTRS)

    1993-01-01

    The Space Shuttle Discovery takes off from Launch Pad 39B at the Kennedy Space Center, Florida, to begin Mission STS-51 on 12 September 1993. The 57th shuttle mission began at 7:45 a.m. EDT, and lasted 9 days, 20 hours, 11 minutes, 11 seconds, while traveling a total distance of 4,106,411 miles. The Advanced Communications Technology Satellite (ACTS) was one of the projects deployed. This satellite serves as a test bed for advanced experimental communications satellite concepts and technology. Another payload on this mission was the Orbiting Retrievable Far and Extreme Ultraviolet Spectrometer (ORFEUS) telescope mounted on the Shuttle Pallet Satellite (SPAS) payload carrier. ORFEUS was designed to investigate very hot and very cold matter in the universe. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into

  7. Improved guidance hardware study for the scout launch vehicle

    NASA Technical Reports Server (NTRS)

    Schappell, R. T.; Salis, M. L.; Mueller, R.; Best, L. E.; Bradt, A. J.; Harrison, R.; Burrell, J. H.

    1972-01-01

    A market survey and evaluation of inertial guidance systems (inertial measurement units and digital computers) were made. Comparisons were made to determine the candidate systems for use in the Scout launch vehicle. Error analyses were made using typical Scout trajectories. A reaction control system was sized for the fourth stage. The guidance hardware to Scout vehicle interface was listed.

  8. Failure to Launch: Structural Shift and the New Lost Generation

    ERIC Educational Resources Information Center

    Carnevale, Anthony P.; Hanson, Andrew R.; Gulish, Artem

    2013-01-01

    The lockstep march from school to work and then on to retirement no longer applies for a growing share of Americans. Many young adults are launching their careers later, while older adults are working longer. As a result, the education and labor market institutions that were the foundation of a 20th century system are out of sync with the 21st…

  9. The continuing challenge of electromagnetic launch

    SciTech Connect

    Cowan, M.; Cnare, E.C.; Duggin, B.W.; Kaye, R.J.; Marder, B.M.; Shokair, I.R.

    1993-07-01

    Interest in launching payloads through the atmosphere to ever higher velocity is robust. For hundreds of years, guns and rockets have been improved for this purpose until they are now considered to be near to their performance limits. While the potential of electromagnetic technology to increase launch velocity has been known since late in the nineteenth century, it was not until about 1980 that a sustained and large-scale effort was started to exploit it. Electromagnetic launcher technology is restricted here to mean only that technology which establishes both a current density, J, and a magnetic field, B, within a part of the launch package, called the armature, so that J {times} B integrated over the volume of the armature is the launching force. Research and development activity was triggered by the discovery that high velocity can be produced with a simple railgun which uses an arc for its armature. This so called ``plasma-armature railgun`` has been the launcher technology upon which nearly all of the work has focused. Still, a relatively small parallel effort has also been made to explore the potential of electromagnetic launchers which do not use sliding contacts on stationary rails to establish current in the armature. One electromagnetic launcher of this type is called an induction coilgun because armature current is established by electromagnetic induction. In this paper, we first establish terminology which we will use not only to specify requirements for successful endoatmospheric launch but also to compare different launcher types. Then, we summarize the statuses of the railgun and induction coilgun technologies and discuss the issues which must be resolved before either of these launchers can offer substantial advantage for endoatomospheric launch.

  10. Magnetic Launch Assist Demonstration Test

    NASA Technical Reports Server (NTRS)

    2001-01-01

    This image shows a 1/9 subscale model vehicle clearing the Magnetic Launch Assist System, formerly referred to as the Magnetic Levitation (MagLev), test track during a demonstration test conducted at the Marshall Space Flight Center (MSFC). Engineers at MSFC have developed and tested Magnetic Launch Assist technologies. To launch spacecraft into orbit, a Magnetic Launch Assist System would use magnetic fields to levitate and accelerate a vehicle along a track at very high speeds. Similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway, a launch-assist system would electromagnetically drive a space vehicle along the track. A full-scale, operational track would be about 1.5-miles long and capable of accelerating a vehicle to 600 mph in 9.5 seconds. This track is an advanced linear induction motor. Induction motors are common in fans, power drills, and sewing machines. Instead of spinning in a circular motion to turn a shaft or gears, a linear induction motor produces thrust in a straight line. Mounted on concrete pedestals, the track is 100-feet long, about 2-feet wide and about 1.5-feet high. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  11. The launch of new-look Chishango.

    PubMed

    Chavasse, D

    2002-09-01

    PSI/Malawi is a local affiliate of the non-profit NGO, Population Services International, which operates in over 50 countries worldwide. PSI/Malawi's mission is to "improve and sustain the health of all Malawians through cost-effective social marketing of needed and affordable health products". In this context, social marketing involves using a range of media channels to create demand for branded health products which are sold at subsidised prices through a wide range of distribution outlets (e.g. wholesalers/retailers, institutions, NGOs, the workplace, etc.). Chishango is PSI/Malawi's condom brand which was launched in 1994 to provide sexually active Malawians with an affordable means of protecting themselves and their partners from HIV transmission. In 2001, research indicated that the brand needed a 'face lift' to improve its relevance to modern Malawians and therefore lead to an increase in consistent condom use resulting in a further reduction in HIV transmission. The newly packaged and positioned Chishango was launched on the 13th May 2002. The speech below was given by the Resident Director of PSI/Malawi, Dr Desmond Chavasse at the relaunch of Chishango. PMID:27528941

  12. 47 CFR 25.113 - Station licenses and launch authority.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... must comply with the provisions of 47 CFR 1.1312 relating to environmental processing prior to... and operated in orbit. Request for launch authorization may be included in an application for space... of a launch failure or a catastrophic in-orbit failure. (h) Licensees of Non-Geostationary...

  13. 47 CFR 25.113 - Station licenses and launch authority.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... must comply with the provisions of 47 CFR 1.1312 relating to environmental processing prior to... and operated in orbit. Request for launch authorization may be included in an application for space... of a launch failure or a catastrophic in-orbit failure. (h) Licensees of Non-Geostationary...

  14. STS-29: Pre-Launch Preparations/Launch and Landing

    NASA Technical Reports Server (NTRS)

    1989-01-01

    Live footage shows the crewmembers of STS-29, Commander Michael L. Coats, Pilot John E. Blaha, and Mission Specialists James P. Bagian, James F. Buchli, and Robert C. Springer, seated in the White Room with the traditional cake. The crew is seen performing various pre-launch activities including suit-up, and walk out to the Astro-van. This early morning launch shows countdown, main engine start, liftoff, booster separation, and various isolated footage of the launch from different cameras. Also presented are footage of the approach, gear touchdown, rollout at Edwards Air Force Base, and various isolated views of the landing.

  15. The reusable launch vehicle technology program

    NASA Technical Reports Server (NTRS)

    Cook, S.

    1995-01-01

    Today's launch systems have major shortcomings that will increase in significance in the future, and thus are principal drivers for seeking major improvements in space transportation. They are too costly; insufficiently reliable, safe, and operable; and increasingly losing market share to international competition. For the United States to continue its leadership in the human exploration and wide ranging utilization of space, the first order of business must be to achieve low cost, reliable transportatin to Earth orbit. NASA's Access to Space Study, in 1993, recommended the development of a fully reusable single-stage-to-orbit (SSTO) rocket vehicle as an Agency goal. The goal of the Reusable Launch Vehicle (RLV) technology program is to mature the technologies essential for a next-generation reusable launch system capable of reliably serving National space transportation needs at substantially reduced costs. The primary objectives of the RLV technology program are to (1) mature the technologies required for the next-generation system, (2) demonstrate the capability to achieve low development and operational cost, and rapid launch turnaround times and (3) reduce business and technical risks to encourage significant private investment in the commercial development and operation of the next-generation system. Developing and demonstrating the technologies required for a Single Stage to Orbit (SSTO) rocket is a focus of the program becuase past studies indicate that it has the best potential for achieving the lowest space access cost while acting as an RLV technology driver (since it also encompasses the technology requirements of reusable rocket vehicles in general).

  16. [CAEC launches an innovative IEC program].

    PubMed

    Okigbo, C

    1996-01-01

    The African Council for Education in Communication (CAEC) has launched an innovative program for training in IEC, following long discussions with specialists in the US Agency for International Development, Johns Hopkins University, Family Health International/AIDSCAP, and other international development and UN agencies. The four social marketing study and training modules will examine principles and practice, research and evaluation, planning campaign strategies, and production of materials. Two of the modules were presented in 1996. 26 participants from UNICEF bureaus in Kenya, Nigeria, Sierra Leone, and Namibia attended a course in application and principles of social marketing and IEC in Nairobi in August 1996. The second course, on research and evaluation in social marketing and IEC, was held in Nairobi in late 1996. The remaining two modules will be presented in Nairobi in 1997, while the first two are to be presented in West Africa and South Africa. Several institutions in the 26 CAEC member countries have expressed interest in the courses. The second phase of development of this training project calls for studies of social marketing, promotion, and social mobilization. Programs in international development communication and other topics will be added for personnel of UNICEF and other UN agencies. PMID:12320947

  17. 49 CFR 1242.84 - Marketing, sales, and public relations and advertising (accounts XX-63-88, XX-63-89 and XX-63-93).

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 49 Transportation 9 2011-10-01 2011-10-01 false Marketing, sales, and public relations and advertising (accounts XX-63-88, XX-63-89 and XX-63-93). 1242.84 Section 1242.84 Transportation Other... PASSENGER SERVICE FOR RAILROADS 1 Operating Expenses § 1242.84 Marketing, sales, and public relations...

  18. 49 CFR 1242.84 - Marketing, sales, and public relations and advertising (accounts XX-63-88, XX-63-89 and XX-63-93).

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 49 Transportation 9 2010-10-01 2010-10-01 false Marketing, sales, and public relations and advertising (accounts XX-63-88, XX-63-89 and XX-63-93). 1242.84 Section 1242.84 Transportation Other... PASSENGER SERVICE FOR RAILROADS 1 Operating Expenses § 1242.84 Marketing, sales, and public relations...

  19. Reusable Launch Vehicle Technology Program

    NASA Technical Reports Server (NTRS)

    Freeman, Delma C., Jr.; Talay, Theodore A.; Austin, R. Eugene

    1996-01-01

    Industry/NASA Reusable Launch Vehicle (RLV) Technology Program efforts are underway to design, test, and develop technologies and concepts for viable commercial launch systems that also satisfy national needs at acceptable recurring costs. Significant progress has been made in understanding the technical challenges of fully reusable launch systems and the accompanying management and operational approaches for achieving a low-cost program. This paper reviews the current status of the Reusable Launch Vehicle Technology Program including the DC-XA, X-33 and X-34 flight systems and associated technology programs. It addresses the specific technologies being tested that address the technical and operability challenges of reusable launch systems including reusable cryogenic propellant tanks, composite structures, thermal protection systems, improved propulsion, and subsystem operability enhancements. The recently concluded DC-XA test program demonstrated some of these technologies in ground and flight tests. Contracts were awarded recently for both the X-33 and X-34 flight demonstrator systems. The Orbital Sciences Corporation X-34 flight test vehicle will demonstrate an air-launched reusable vehicle capable of flight to speeds of Mach 8. The Lockheed-Martin X-33 flight test vehicle will expand the test envelope for critical technologies to flight speeds of Mach 15. A propulsion program to test the X-33 linear aerospike rocket engine using a NASA SR-71 high speed aircraft as a test bed is also discussed. The paper also describes the management and operational approaches that address the challenge of new cost-effective, reusable launch vehicle systems.

  20. STS Derived Exploration Launch Operations

    NASA Technical Reports Server (NTRS)

    Best, Joel; Sorge, L.; Siders, J.; Sias, Dave

    2004-01-01

    A key aspect of the new space exploration programs will be the approach to optimize launch operations. A STS Derived Launch Vehicle (SDLV) Program can provide a cost effective, low risk, and logical step to launch all of the elements of the exploration program. Many benefits can be gained by utilizing the synergy of a common launch site as an exploration spaceport as well as evolving the resources of the current Space Shuttle Program (SSP) to meet the challenges of the Vision for Space Exploration. In particular, the launch operation resources of the SSP can be transitioned to the exploration program and combined with the operations efficiencies of unmanned EELVs to obtain the best of both worlds, resulting in lean launch operations for crew and cargo missions of the exploration program. The SDLV Program would then not only capture the extensive human space flight launch operations knowledge, but also provide for the safe fly-out of the SSP through continuity of system critical skills, manufacturing infrastructure, and ability to maintain and attract critical skill personnel. Thus, a SDLV Program can smoothly transition resources from the SSP and meet the transportation needs to continue the voyage of discovery of the space exploration program.

  1. Perception of Business Related Graduate Degrees by Market Research Managers within the Health Care Industry.

    ERIC Educational Resources Information Center

    Phillips, Jan Hirsch; And Others

    1986-01-01

    A survey of market research managers' perceptions of the outcomes of a pharmacy administration master's program as compared to those of two popular master's-level business administration programs found a lack of awareness and understanding of the pharmacy administration degree program and a resulting perception of lower skill levels among its…

  2. Capacity Markets and Market Stability

    SciTech Connect

    Stauffer, Hoff

    2006-04-15

    The good news is that market stability can be achieved through a combination of longer-term contracts, auctions for far enough in the future to permit new entry, a capacity management system, and a demand curve. The bad news is that if and when stable capacity markets are designed, the markets may seem to be relatively close to where we started - with integrated resource planning. Market ideologues will find this anathema. (author)

  3. Research gaps related to tobacco product marketing and sales in the Family Smoking Prevention and Tobacco Control Act.

    PubMed

    Ribisl, Kurt M

    2012-01-01

    This paper is part of a collection that identifies research priorities that will help guide the efforts of the U.S. Food and Drug Administration (FDA) as it regulates tobacco products. This paper examines the major provisions related to tobacco product advertising, marketing, sales, and distribution included in Public Law 111-31, the "Family Smoking Prevention and Tobacco Control Act". This paper covers 5 areas related to (a) marketing regulations (e.g., ban on color and imagery in ads, ban on nontobacco gifts with purchase); (b) granting FDA authority over the sale, distribution, accessibility, advertising, and promotion of tobacco and lifting state preemption over advertising; (c) remote tobacco sales (mail order and Internet); (d) prevention of illicit and cross-border trade; and (e) noncompliant export products. Each of the 5 sections of this paper provides a description and brief history of regulation, what is known about this regulatory strategy, and research opportunities. PMID:21690316

  4. Mars Pathfinder Status at Launch

    NASA Technical Reports Server (NTRS)

    Spear, A. J.; Freeman, Delma C., Jr.; Braun, Robert D.

    1996-01-01

    The Mars Pathfinder Flight System is in final test, assembly and launch preparations at the Kennedy Space Center in Florida. Launch is scheduled for 2 Dec. 1996. The Flight System development, in particular the Entry, Descent, and Landing (EDL) system, was a major team effort involving JPL, other NASA centers and industry. This paper provides a summary Mars Pathfinder description and status at launch. In addition, a section by NASA's Langley Research Center, a key EDL contributor, is provided on their support to Mars Pathfinder. This section is included as an example of the work performed by Pathfinder team members outside JPL.

  5. Airborne Simulation of Launch Vehicle Dynamics

    NASA Technical Reports Server (NTRS)

    Miller, Christopher J.; Orr, Jeb S.; Hanson, Curtis E.; Gilligan, Eric T.

    2015-01-01

    In this paper we present a technique for approximating the short-period dynamics of an exploration-class launch vehicle during flight test with a high-performance surrogate aircraft in relatively benign endoatmospheric flight conditions. The surrogate vehicle relies upon a nonlinear dynamic inversion scheme with proportional-integral feedback to drive a subset of the aircraft states into coincidence with the states of a time-varying reference model that simulates the unstable rigid body dynamics, servodynamics, and parasitic elastic and sloshing dynamics of the launch vehicle. The surrogate aircraft flies a constant pitch rate trajectory to approximate the boost phase gravity turn ascent, and the aircraft's closed-loop bandwidth is sufficient to simulate the launch vehicle's fundamental lateral bending and sloshing modes by exciting the rigid body dynamics of the aircraft. A novel control allocation scheme is employed to utilize the aircraft's relatively fast control effectors in inducing various failure modes for the purposes of evaluating control system performance. Sufficient dynamic similarity is achieved such that the control system under evaluation is configured for the full-scale vehicle with no changes to its parameters, and pilot-control system interaction studies can be performed to characterize the effects of guidance takeover during boost. High-fidelity simulation and flight-test results are presented that demonstrate the efficacy of the design in simulating the Space Launch System (SLS) launch vehicle dynamics using the National Aeronautics and Space Administration (NASA) Armstrong Flight Research Center Fullscale Advanced Systems Testbed (FAST), a modified F/A-18 airplane (McDonnell Douglas, now The Boeing Company, Chicago, Illinois), over a range of scenarios designed to stress the SLS's Adaptive Augmenting Control (AAC) algorithm.

  6. Airborne Simulation of Launch Vehicle Dynamics

    NASA Technical Reports Server (NTRS)

    Gilligan, Eric T.; Miller, Christopher J.; Hanson, Curtis E.; Orr, Jeb S.

    2014-01-01

    In this paper we present a technique for approximating the short-period dynamics of an exploration-class launch vehicle during flight test with a high-performance surrogate aircraft in relatively benign endoatmospheric flight conditions. The surrogate vehicle relies upon a nonlinear dynamic inversion scheme with proportional-integral feedback to drive a subset of the aircraft states into coincidence with the states of a time-varying reference model that simulates the unstable rigid body dynamics, servodynamics, and parasitic elastic and sloshing dynamics of the launch vehicle. The surrogate aircraft flies a constant pitch rate trajectory to approximate the boost phase gravity-turn ascent, and the aircraft's closed-loop bandwidth is sufficient to simulate the launch vehicle's fundamental lateral bending and sloshing modes by exciting the rigid body dynamics of the aircraft. A novel control allocation scheme is employed to utilize the aircraft's relatively fast control effectors in inducing various failure modes for the purposes of evaluating control system performance. Sufficient dynamic similarity is achieved such that the control system under evaluation is optimized for the full-scale vehicle with no changes to its parameters, and pilot-control system interaction studies can be performed to characterize the effects of guidance takeover during boost. High-fidelity simulation and flight test results are presented that demonstrate the efficacy of the design in simulating the Space Launch System (SLS) launch vehicle dynamics using NASA Dryden Flight Research Center's Full-scale Advanced Systems Testbed (FAST), a modified F/A-18 airplane, over a range of scenarios designed to stress the SLS's adaptive augmenting control (AAC) algorithm.

  7. 14 CFR 415.119 - Launch plans.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Launch plans. 415.119 Section 415.119 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LAUNCH LICENSE Safety Review and Approval for Launch of an Expendable Launch Vehicle From a Non-Federal Launch Site §...

  8. 14 CFR 415.121 - Launch schedule.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Launch schedule. 415.121 Section 415.121 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LAUNCH LICENSE Safety Review and Approval for Launch of an Expendable Launch Vehicle From a Non-Federal Launch Site §...

  9. Closed end launch tube (CELT)

    NASA Astrophysics Data System (ADS)

    Lueck, Dale E.; Parrish, Clyde F.

    2001-02-01

    As an alternative to magnetic propulsion for launch assist, the authors propose a pneumatic launch assist system. Using off-the-shelf components, coupled with familiar steel and concrete construction, a launch assist system can be brought from the initial feasibility stage, through a flight capable 5000 kg demonstrator to a deployed full size launch assist system in 10 years. The final system would be capable of accelerating a 450,000 kg vehicle to 270 ms-1. The CELT system uses commercially available compressors and valves to build a fail-safe system in less than half the time of a full Mag-Lev (magnetic levitation) system, and at a small fraction of the development cost. The resulting system could be ready in time to support some Gen 2 (Generation 2) vehicles, as well as the proposed Gen 3 vehicle. .

  10. Advanced Launch Development Program status

    NASA Technical Reports Server (NTRS)

    Colgrove, Roger

    1990-01-01

    The Advanced Launch System is a joint NASA - Air Force program originally directed to define the concept for a modular family of launch vehicles, to continue development programs and preliminary design activities focused primarily on low cost to orbit, and to offer maturing technologies to existing systems. The program was restructed in the spring of 1990 as a result of funding reductions and renamed the Advanced Launch Development Program. This paper addresses the program's status following that restructuring and as NASA and the Air Force commence a period of deliberation over future space launch needs and the budgetary resources available to meet those needs. The program is currently poised to protect a full-scale development decision in the mid-1990's through the appropriate application of program resources. These resources are concentrated upon maintaining the phase II system contractor teams, continuing the Space Transportation Engine development activity, and refocusing the Advanced Development Program demonstrated activities.

  11. STS-135 Fused Launch Video

    NASA Video Gallery

    Imaging experts funded by the Space Shuttle Program and located at NASA's Ames Research Center prepared this video of the STS-135 launch by merging images taken by a set of six cameras capturing fi...

  12. Environmentally-Preferable Launch Coatings

    NASA Technical Reports Server (NTRS)

    Kessel, Kurt R.

    2015-01-01

    The Ground Systems Development and Operations (GSDO) Program at NASA Kennedy Space Center (KSC), Florida, has the primary objective of modernizing and transforming the launch and range complex at KSC to benefit current and future NASA programs along with other emerging users. Described as the launch support and infrastructure modernization program in the NASA Authorization Act of 2010, the GSDO Program will develop and implement shared infrastructure and process improvements to provide more flexible, affordable, and responsive capabilities to a multi-user community. In support of NASA and the GSDO Program, the objective of this project is to determine the feasibility of environmentally friendly corrosion protecting coatings for launch facilities and ground support equipment (GSE). The focus of the project is corrosion resistance and survivability with the goal to reduce the amount of maintenance required to preserve the performance of launch facilities while reducing mission risk. The project compares coating performance of the selected alternatives to existing coating systems or standards.

  13. Nanosatellite Launch Adapter System (NLAS)

    NASA Technical Reports Server (NTRS)

    Yost, Bruce D.; Hines, John W.; Agasid, Elwood F.; Buckley, Steven J.

    2010-01-01

    The utility of small spacecraft based on the University cubesat standard is becoming evident as more and more agencies and organizations are launching or planning to include nanosatellites in their mission portfolios. Cubesats are typically launched as secondary spacecraft in enclosed, containerized deployers such as the CalPoly Poly Picosat Orbital Deployer (P-POD) system. The P-POD allows for ease of integration and significantly reduces the risk exposure to the primary spacecraft and mission. NASA/ARC and the Operationally Responsive Space office are collaborating to develop a Nanosatellite Launch Adapter System (NLAS), which can accommodate multiple cubesat or cubesat-derived spacecraft on a single launch vehicle. NLAS is composed of the adapter structure, P-POD or similar spacecraft dispensers, and a sequencer/deployer system. This paper describes the NLAS system and it s future capabilities, and also provides status on the system s development and potential first use in space.

  14. Re-entry Experiment Launch

    NASA Video Gallery

    On August 10, 2009, NASA successfully launched the Inflatable Re-entry Vehicle Experiment (IRVE) and proved that spacecraft can use inflatable heat shields to reduce speed and provide protection du...

  15. Robonaut 2 Readied for Launch

    NASA Video Gallery

    Robonaut 2 is being prepared for its history making launch to the International Space Station on STS-133. The robot, known as R2, will be the first humanoid machine to work in orbit. With a upper t...

  16. Closed End Launch Tube (CELT)

    NASA Technical Reports Server (NTRS)

    Lueck, Dale E.; Parrish, Clyde F.; Delgado, H. (Technical Monitor)

    2000-01-01

    As an alternative to magnetic propulsion for launch assist, the authors propose a pneumatic launch assist system. Using off the shelf components, coupled with familiar steel and concrete construction, a launch assist system can be brought from the initial feasibility stage, through a flight capable 5000 kg. demonstrator to a deployed full size launch assist system in 10 years. The final system would be capable of accelerating a 450,000 kg. vehicle to 270 meters per second. The CELT system uses commercially available compressors and valves to build a fail-safe system in less than half the time of a full Mag-Lev (magnetic levitation) system, and at a small fraction of the development cost. The resulting system could be ready in time to support some Gen 2 (generation 2) vehicles, as well as the proposed Gen 3 vehicle.

  17. Launch Abort System Pathfinder Arrival

    NASA Video Gallery

    The Orion Launch Abort System, or LAS, pathfinder returned home to NASA Langley on Oct. 18 on its way to NASA's Kennedy Space Center. The hardware was built at Langley and was used in preparation f...

  18. Space Launch System: Future Frontier

    NASA Video Gallery

    Featuring NASA Marshall’s Foundations of Influence, Relationships, Success & Teamwork (FIRST) employees and student interns, "Future Frontier" discusses the new Space Launch System (SLS) heavy-li...

  19. Lighting the Sky: ATREX Launches

    NASA Video Gallery

    NASA successfully launched five suborbital sounding rockets early March 27, 2012 from its Wallops Flight Facility in Virginia as part of a study of the upper level jet stream. The first rocket was ...

  20. BARREL Team Launching 20 Balloons

    NASA Video Gallery

    A movie made by the NASA-Funded Balloon Array for Radiation belt Relativistic Electron Losses, or BARREL, team on their work launching 20 balloons in Antarctica during the Dec. 2013/Jan. 2014 campa...

  1. Launch Commit Criteria Monitoring Agent

    NASA Technical Reports Server (NTRS)

    Semmel, Glenn S.; Davis, Steven R.; Leucht, Kurt W.; Rowe, Dan A.; Kelly, Andrew O.; Boeloeni, Ladislau

    2005-01-01

    The Spaceport Processing Systems Branch at NASA Kennedy Space Center has developed and deployed a software agent to monitor the Space Shuttle's ground processing telemetry stream. The application, the Launch Commit Criteria Monitoring Agent, increases situational awareness for system and hardware engineers during Shuttle launch countdown. The agent provides autonomous monitoring of the telemetry stream, automatically alerts system engineers when predefined criteria have been met, identifies limit warnings and violations of launch commit criteria, aids Shuttle engineers through troubleshooting procedures, and provides additional insight to verify appropriate troubleshooting of problems by contractors. The agent has successfully detected launch commit criteria warnings and violations on a simulated playback data stream. Efficiency and safety are improved through increased automation.

  2. Japan launches mission to Venus

    NASA Astrophysics Data System (ADS)

    Banks, Michael

    2010-06-01

    The Japanese space agency JAXA has launched its first mission to Venus. The Akatsuki craft, which means "dawn" in Japanese, took off last month from the Tanegashima Space Center on the island of Kagoshima, south-west of mainland Japan.

  3. Are stock market returns related to the weather effects? Empirical evidence from Taiwan

    NASA Astrophysics Data System (ADS)

    Chang, Tsangyao; Nieh, Chien-Chung; Yang, Ming Jing; Yang, Tse-Yu

    2006-05-01

    In this study, we employ a recently developed econometric technique of the threshold model with the GJR-GARCH process on error terms to investigate the relationships between weather factors and stock market returns in Taiwan using daily data for the period of 1 July 1997-22 October 2003. The major weather factors studied include temperature, humidity, and cloud cover. Our empirical evidence shows that temperature and cloud cover are two important weather factors that affect the stock returns in Taiwan. Our empirical findings further support the previous arguments that advocate the inclusion of economically neutral behavioral variables in asset pricing models. These results also have significant implications for individual investors and financial institutions planning to invest in the Taiwan stock market.

  4. New Horizons Launch Contingency Effort

    NASA Astrophysics Data System (ADS)

    Chang, Yale; Lear, Matthew H.; McGrath, Brian E.; Heyler, Gene A.; Takashima, Naruhisa; Owings, W. Donald

    2007-01-01

    On 19 January 2006 at 2:00 PM EST, the NASA New Horizons spacecraft (SC) was launched from the Cape Canaveral Air Force Station (CCAFS), FL, onboard an Atlas V 551/Centaur/STAR™ 48B launch vehicle (LV) on a mission to explore the Pluto Charon planetary system and possibly other Kuiper Belt Objects. It carried a single Radioisotope Thermoelectric Generator (RTG). As part of the joint NASA/US Department of Energy (DOE) safety effort, contingency plans were prepared to address the unlikely events of launch accidents leading to a near-pad impact, a suborbital reentry, an orbital reentry, or a heliocentric orbit. As the implementing organization. The Johns Hopkins University Applied Physics Laboratory (JHU/APL) had expanded roles in the New Horizons launch contingency effort over those for the Cassini mission and Mars Exploration Rovers missions. The expanded tasks included participation in the Radiological Control Center (RADCC) at the Kennedy Space Center (KSC), preparation of contingency plans, coordination of space tracking assets, improved aerodynamics characterization of the RTG's 18 General Purpose Heat Source (GPHS) modules, and development of spacecraft and RTG reentry breakup analysis tools. Other JHU/APL tasks were prediction of the Earth impact footprints (ElFs) for the GPHS modules released during the atmospheric reentry (for purposes of notification and recovery), prediction of the time of SC reentry from a potential orbital decay, pre-launch dissemination of ballistic coefficients of various possible reentry configurations, and launch support of an Emergency Operations Center (EOC) on the JHU/APL campus. For the New Horizons launch, JHU/APL personnel at the RADCC and at the EOC were ready to implement any real-time launch contingency activities. A successful New Horizons launch and interplanetary injection precluded any further contingency actions. The New Horizons launch contingency was an interagency effort by several organizations. This paper

  5. Rockot-an available launch system for affordable access to space

    NASA Astrophysics Data System (ADS)

    de Vries, U.; Kinnersley, M.; Freeborn, P.

    2000-01-01

    The Rockot launcher will perform its fifth launch, the first commercial launch, in Spring 2000 from the Plesetsk Cosmodrome in Northern Russia carrying two American satellites into a LEO orbit. In preparation for that a launch pad verification flight will be carried out in November this year to prove the functionality of the adapted facilities at the Plesetsk launch site and by placing a Russian satellite into a highly inclined orbit. The results of the launches will be described in detail in the paper as well as the installations at the launch site. Eurockot, the German-Russian joint-venture company marketing and managing the Rockot launch vehicle is meanwhile an integral part of the space launch community. Eurockot was formed by DaimlerChrysler Aerospace and Khrunichev State Research and Production Space Center. A brief overview of its activities, the commercial program and the performance/services offered by Eurockot is presented. Rockot can launch satellites weighing up to 1850 kg into polar or other low earth orbits (LEO). The Rockot launch vehicle is based on the former Russian SS-19 strategic missile. The first and second stages are inherited from the SS-19, the third stage Breeze which has already been developed has multiple ignition capability. The Breeze upper stage is under production at Khrunichev in Moscow. The Rockot launch system is flight proven and is operated from the Plesetsk as well as from the Baikonur launch site. .

  6. CubeSat Launch Initiative

    NASA Technical Reports Server (NTRS)

    Higginbotham, Scott

    2016-01-01

    The National Aeronautics and Space Administration (NASA) recognizes the tremendous potential that CubeSats (very small satellites) have to inexpensively demonstrate advanced technologies, collect scientific data, and enhance student engagement in Science, Technology, Engineering, and Mathematics (STEM). The CubeSat Launch Initiative (CSLI) was created to provide launch opportunities for CubeSats developed by academic institutions, non-profit entities, and NASA centers. This presentation will provide an overview of the CSLI, its benefits, and its results.

  7. STS-53 Launch and Landing

    NASA Technical Reports Server (NTRS)

    1992-01-01

    Footage of various stages of the STS-53 Discovery launch is shown, including shots of the crew at breakfast, getting suited up, and departing to board the Orbiter. The launch is seen from many vantage points, as is the landing. On-orbit activities show the crew performing several medical experiments, such as taking a picture of the retina and measuring the pressure on the eyeball. One crewmember demonstrates how to use the rowing machine in an antigravity environment.

  8. Launch of STS-63 Discovery

    NASA Technical Reports Server (NTRS)

    1995-01-01

    A 35mm camera was used to expose this close-up image of the Space Shuttle Discovery as it began its race to catch up with Russia's Mir Space Station. Liftoff from Launch Pad 39B, Kennedy Space Center (KSC) occurred at 12:22:04 (EST) February 3, 1995. Discovery is the first in the current fleet of four space shuttle vehicles to make 20 launches.

  9. Magnetic Launch Assist Experimental Track

    NASA Technical Reports Server (NTRS)

    1999-01-01

    In this photograph, a futuristic spacecraft model sits atop a carrier on the Magnetic Launch Assist System, formerly known as the Magnetic Levitation (MagLev) System, experimental track at the Marshall Space Flight Center (MSFC). Engineers at MSFC have developed and tested Magnetic Launch Assist technologies that would use magnetic fields to levitate and accelerate a vehicle along a track at very high speeds. Similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway, a Magnetic Launch Assist system would electromagnetically drive a space vehicle along the track. A full-scale, operational track would be about 1.5-miles long and capable of accelerating a vehicle to 600 mph in 9.5 seconds. This track is an advanced linear induction motor. Induction motors are common in fans, power drills, and sewing machines. Instead of spinning in a circular motion to turn a shaft or gears, a linear induction motor produces thrust in a straight line. Mounted on concrete pedestals, the track is 100-feet long, about 2-feet wide, and about 1.5-feet high. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  10. Launch mission summary: Intelsat 5 (F3) Atlas/Centaur-55

    NASA Technical Reports Server (NTRS)

    1981-01-01

    Intelsat 5 (F3) spacecraft, launch vehicle, and mission are described. Information relative to launch windows, flight plan, radar and telemetry coverage, selected trajectory information, and a brief sequence of flight events is provided.

  11. Launch mission summary INTELSAT V (F5) Atlas/Centaur-60

    NASA Technical Reports Server (NTRS)

    1982-01-01

    The Atlas/Centaur 60 launch vehicle, INTELSAT V (F5) spacecraft, and mission are summarized. Also included is information relative to launch windows, flight plan, radar and telemetry coverage, selected trajectory information, and a brief sequence of flight events.

  12. Mercury-Atlas Test Launch

    NASA Technical Reports Server (NTRS)

    1961-01-01

    A NASA Project Mercury spacecraft was test launched at 11:15 AM EST on April 25, 1961 from Cape Canaveral, Florida, in a test designed to qualify the Mercury Spacecraft and all systems, which must function during orbit and reentry from orbit. The Mercury-Atlas vehicle was destroyed by Range Safety Officer about 40 seconds after liftoff. The spacecraft was recovered and appeared to be in good condition. Atlas was designed to launch payloads into low Earth orbit, geosynchronous transfer orbit or geosynchronous orbit. NASA first launched Atlas as a space launch vehicle in 1958. Project SCORE, the first communications satellite that transmitted President Eisenhower's pre-recorded Christmas speech around the world, was launched on an Atlas. For all three robotic lunar exploration programs, Atlas was used. Atlas/ Centaur vehicles launched both Mariner and Pioneer planetary probes. The current operational Atlas II family has a 100% mission success rating. For more information about Atlas, please see Chapter 2 in Roger Launius and Dennis Jenkins' book To Reach the High Frontier published by The University Press of Kentucky in 2002.

  13. SLI Artist `s Launch Concept

    NASA Technical Reports Server (NTRS)

    2002-01-01

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

  14. Reusable Launch Vehicle Technology Program

    NASA Technical Reports Server (NTRS)

    Freeman, Delma C., Jr.; Talay, Theodore A.; Austin, R. Eugene

    1997-01-01

    Industry/NASA reusable launch vehicle (RLV) technology program efforts are underway to design, test, and develop technologies and concepts for viable commercial launch systems that also satisfy national needs at acceptable recurring costs. Significant progress has been made in understanding the technical challenges of fully reusable launch systems and the accompanying management and operational approaches for achieving a low cost program. This paper reviews the current status of the RLV technology program including the DC-XA, X-33 and X-34 flight systems and associated technology programs. It addresses the specific technologies being tested that address the technical and operability challenges of reusable launch systems including reusable cryogenic propellant tanks, composite structures, thermal protection systems, improved propulsion and subsystem operability enhancements. The recently concluded DC-XA test program demonstrated some of these technologies in ground and flight test. Contracts were awarded recently for both the X-33 and X-34 flight demonstrator systems. The Orbital Sciences Corporation X-34 flight test vehicle will demonstrate an air-launched reusable vehicle capable of flight to speeds of Mach 8. The Lockheed-Martin X-33 flight test vehicle will expand the test envelope for critical technologies to flight speeds of Mach 15. A propulsion program to test the X-33 linear aerospike rocket engine using a NASA SR-71 high speed aircraft as a test bed is also discussed. The paper also describes the management and operational approaches that address the challenge of new cost effective, reusable launch vehicle systems.

  15. Reusable launch vehicle technology program

    NASA Astrophysics Data System (ADS)

    Freeman, Delma C.; Talay, Theodore A.; Austin, R. Eugene

    Industry/NASA reusable launch vehicle (RLV) technology program efforts are underway to design, test, and develop technologies and concepts for viable commercial launch systems that also satisfy national needs at acceptable recurring costs. Significant progress has been made in understanding the technical challenges of fully reusable launch systems and the accompanying management and operational approaches for achieving a low-cost program. This paper reviews the current status of the RLV technology program including the DC-XA, X-33 and X-34 flight systems and associated technology programs. It addresses the specific technologies being tested that address the technical and operability challenges of reusable launch systems including reusable cryogenic propellant tanks, composite structures, thermal protection systems, improved propulsion, and subsystem operability enhancements. The recently concluded DC-XA test program demonstrated some of these technologies in ground and flight tests. Contracts were awarded recently for both the X-33 and X-34 flight demonstrator systems. The Orbital Sciences Corporation X-34 flight test vehicle will demonstrate an air-launched reusable vehicle capable of flight to speeds of Mach 8. The Lockheed-Martin X-33 flight test vehicle will expand the test envelope for critical technologies to flight speeds of Mach 15. A propulsion program to test the X-33 linear aerospike rocket engine using a NASA SR-71 high speed aircraft as a test bed is also discussed. The paper also describes the management and operational approaches that address the challenge of new cost-effective, reusable launch vehicle systems.

  16. Use of Smoothed Measured Winds to Predict and Assess Launch Environments

    NASA Technical Reports Server (NTRS)

    Cordova, Henry S.; Leahy, Frank; Adelfang, Stanley; Roberts, Barry; Starr, Brett; Duffin, Paul; Pueri, Daniel

    2011-01-01

    Since many of the larger launch vehicles are operated near their design limits during the ascent phase of flight to optimize payload to orbit, it often becomes necessary to verify that the vehicle will remain within certification limits during the ascent phase as part of the go/no-go review made prior to launch. This paper describes the approach used to predict Ares I-X launch vehicle structural air loads and controllability prior to launch which represents a distinct departure from the methodology of the Space Shuttle and Evolved Expendable Launch Vehicle (EELV) programs. Protection for uncertainty of key environment and trajectory parameters is added to the nominal assessment of launch capability to ensure that critical launch trajectory variables would be within the integrated vehicle certification envelopes. This process was applied by the launch team as a key element of the launch day go/no-go recommendation. Pre-launch assessments of vehicle launch capability for NASA's Space Shuttle and the EELV heavy lift versions require the use of a high-resolution wind profile measurements, which have relatively small sample size compared with low-resolution profile databases (which include low-resolution balloons and radar wind profilers). The approach described in this paper has the potential to allow the pre-launch assessment team to use larger samples of wind measurements from low-resolution wind profile databases that will improve the accuracy of pre-launch assessments of launch availability with no degradation of mission assurance or launch safety.

  17. Huge Data-Sharing Project Launched.

    PubMed

    Rose, Suzanne

    2016-01-01

    Aiming to advance precision medicine in oncology and improve patient care, the American Association for Cancer Research has launched an international initiative known as AACR Project Genomics, Evidence, Neoplasia, Information, Exchange (GENIE). The venture will pool existing and future next-generation clinical sequencing data with longitudinal clinical outcomes and related pathology reports from several institutions in the United States, Canada, and Europe, to find new mutations, assess potential biomarkers, and identify patient populations that might benefit from existing treatments. PMID:26546297

  18. NASA's Space Launch System: Momentum Builds Towards First Launch

    NASA Technical Reports Server (NTRS)

    May, Todd; Lyles, Garry

    2014-01-01

    NASA's Space Launch System (SLS) is gaining momentum programmatically and technically toward the first launch of a new exploration-class heavy lift launch vehicle for international exploration and science initiatives. The SLS comprises an architecture that begins with a vehicle capable of launching 70 metric tons (t) into low Earth orbit. Its first mission will be the launch of the Orion Multi-Purpose Crew Vehicle (MPCV) on its first autonomous flight beyond the Moon and back. SLS will also launch the first Orion crewed flight in 2021. SLS can evolve to a 130-t lift capability and serve as a baseline for numerous robotic and human missions ranging from a Mars sample return to delivering the first astronauts to explore another planet. Managed by NASA's Marshall Space Flight Center, the SLS Program formally transitioned from the formulation phase to implementation with the successful completion of the rigorous Key Decision Point C review in 2014. At KDP-C, the Agency Planning Management Council determines the readiness of a program to go to the next life-cycle phase and makes technical, cost, and schedule commitments to its external stakeholders. As a result, the Agency authorized the Program to move forward to Critical Design Review, scheduled for 2015, and a launch readiness date of November 2018. Every SLS element is currently in testing or test preparations. The Program shipped its first flight hardware in 2014 in preparation for Orion's Exploration Flight Test-1 (EFT-1) launch on a Delta IV Heavy rocket in December, a significant first step toward human journeys into deep space. Accomplishments during 2014 included manufacture of Core Stage test articles and preparations for qualification testing the Solid Rocket Boosters and the RS-25 Core Stage engines. SLS was conceived with the goals of safety, affordability, and sustainability, while also providing unprecedented capability for human exploration and scientific discovery beyond Earth orbit. In an environment

  19. Spitzer Pre Launch Mission Operations System - The Road to Launch

    NASA Technical Reports Server (NTRS)

    Scott, Charles P.; Wilson, Robert K.

    2006-01-01

    Spitzer Space Telescope was launched on 25 August 2003 into an Earth-trailing solar orbit to acquire infrared observations from space. Development of the Mission Operations System (MOS) portion prior to launch was very different from planetary missions from the stand point that the MOS teams and Ground Data System had to be ready to support all aspects of the mission at launch (i.e., no cruise period for finalizing the implementation). For Spitzer, all mission-critical events post launch happen in hours or days rather than months or years, as is traditional with deep space missions. At the end of 2000 the Project was dealt a major blow when the Mission Operations System (MOS) had an unsuccessful Critical Design Review (CDR). The project made major changes at the beginning of 2001 in an effort to get the MOS (and Project) back on track. The result for the Spitzer Space Telescope was a successful launch of the observatory followed by an extremely successful In Orbit Checkout (IOC) and operations phase. This paper describes how the project was able to recover the MOS to a successful Delta (CDR) by mid 2001, and what changes in philosophies, experiences, and lessons learned followed. It describes how projects must invest early or else invest heavily later in the development phase to achieve a successful operations phase.

  20. Antares: A low cost modular launch vehicle for the future

    NASA Astrophysics Data System (ADS)

    The single-stage-to-orbit launch vehicle Antares is a revolutionary concept based on identical modular units, enabling the Antares to efficiently launch communications satellites, as well as heavy payloads, into Earth orbit and beyond. The basic unit of the modular system, a single Antares vehicle, is aimed at launching approximately 10,000 kg (22,000 lb) into low Earth orbit (LEO). When coupled with a standard Centaur upper stage, it is capable of placing 4000 kg (8800 lb) into geosynchronous Earth orbit (GE0). The Antares incorporates a reusable engine, the Dual Mixture Ratio Engine (DMRE), as its propulsive device. This enables Antares to compete and excel in the satellite launch market by dramatically reducing launch costs. Inherent in the design is the capability to attach several of these vehicles together to provide heavy lift capability. Any number of these vehicles can be attached depending on the payload and mission requirements. With a seven-vehicle configuration, the Antares' modular concept provides a heavy lift capability of approximately 70,000 kg (154,000 lb) to LEO. This expandability allows for a wide range of payload options, such as large Earth satellites, Space Station Freedom material, and interplanetary spacecraft, and also offers a significant cost savings over a mixed fleet based on different launch vehicles.

  1. Antares: A low cost modular launch vehicle for the future

    NASA Technical Reports Server (NTRS)

    1991-01-01

    The single-stage-to-orbit launch vehicle Antares is a revolutionary concept based on identical modular units, enabling the Antares to efficiently launch communications satellites, as well as heavy payloads, into Earth orbit and beyond. The basic unit of the modular system, a single Antares vehicle, is aimed at launching approximately 10,000 kg (22,000 lb) into low Earth orbit (LEO). When coupled with a standard Centaur upper stage, it is capable of placing 4000 kg (8800 lb) into geosynchronous Earth orbit (GE0). The Antares incorporates a reusable engine, the Dual Mixture Ratio Engine (DMRE), as its propulsive device. This enables Antares to compete and excel in the satellite launch market by dramatically reducing launch costs. Inherent in the design is the capability to attach several of these vehicles together to provide heavy lift capability. Any number of these vehicles can be attached depending on the payload and mission requirements. With a seven-vehicle configuration, the Antares' modular concept provides a heavy lift capability of approximately 70,000 kg (154,000 lb) to LEO. This expandability allows for a wide range of payload options, such as large Earth satellites, Space Station Freedom material, and interplanetary spacecraft, and also offers a significant cost savings over a mixed fleet based on different launch vehicles.

  2. Developing Primary Propulsion for the Ares I Crew Launch Vehicle and Ares V Cargo Launch Vehicle

    NASA Technical Reports Server (NTRS)

    Priskos, Alex S.; Williams, Thomas L.; Ezell, Timothy G.; Burt, Rick

    2007-01-01

    In accordance with the U.S. Vision for Space Exploration, NASA has been tasked to send human beings to the moon, Mars, and beyond. The first stage of NASA's new Ares I crew launch vehicle (Figure 1), which will loft the Orion crew exploration vehicle into low-Earth orbit early next decade, will consist of a Space Shuttle-derived five-segment Reusable Solid Rocket Booster (RSRB); a pair of similar RSRBs also will be used on the Ares V cargo launch vehicle's core stage propulsion system. This paper will discuss the basis for choosing this particular propulsion system; describe the activities the Exploration Launch Projects (ELP) Office is engaged in at present to develop the first stage; and offer a preview of future development activities related to the first Ares l integrated test flight, which is planned for 2009.

  3. Launch site integration for mixed fleet operations

    NASA Technical Reports Server (NTRS)

    Scott, L. P.

    1990-01-01

    Launch site impacts and integration planning issues are presented to support launch operations for a mixed vehicle fleet (manned and cargo). Proposed ground systems and launch site configurations are described. Prelaunch processing scenarios and schedules are developed for candidate launch vehicles. Earth-to-orbit (ETO) vehicle architectures are presented to meet future launch requirements, including the Space Exploration Initiative (SEI). Flight vehicle design recommendations to enhance launch processing are discussed. The significance of operational designs for future launch vehicles is shown to be a critical factor in planning for mixed fleet launch site operations.

  4. NASA Exploration Launch Projects Overview: The Crew Launch Vehicle and the Cargo Launch Vehicle Systems

    NASA Technical Reports Server (NTRS)

    Snoddy, Jimmy R.; Dumbacher, Daniel L.; Cook, Stephen A.

    2006-01-01

    The U.S. Vision for Space Exploration (January 2004) serves as the foundation for the National Aeronautics and Space Administration's (NASA) strategic goals and objectives. As the NASA Administrator outlined during his confirmation hearing in April 2005, these include: 1) Flying the Space Shuttle as safely as possible until its retirement, not later than 2010. 2) Bringing a new Crew Exploration Vehicle (CEV) into service as soon as possible after Shuttle retirement. 3) Developing a balanced overall program of science, exploration, and aeronautics at NASA, consistent with the redirection of the human space flight program to focus on exploration. 4) Completing the International Space Station (ISS) in a manner consistent with international partner commitments and the needs of human exploration. 5) Encouraging the pursuit of appropriate partnerships with the emerging commercial space sector. 6) Establishing a lunar return program having the maximum possible utility for later missions to Mars and other destinations. In spring 2005, the Agency commissioned a team of aerospace subject matter experts to perform the Exploration Systems Architecture Study (ESAS). The ESAS team performed in-depth evaluations of a number of space transportation architectures and provided recommendations based on their findings? The ESAS analysis focused on a human-rated Crew Launch Vehicle (CLV) for astronaut transport and a heavy lift Cargo Launch Vehicle (CaLV) to carry equipment, materials, and supplies for lunar missions and, later, the first human journeys to Mars. After several months of intense study utilizing safety and reliability, technical performance, budget, and schedule figures of merit in relation to design reference missions, the ESAS design options were unveiled in summer 2005. As part of NASA's systems engineering approach, these point of departure architectures have been refined through trade studies during the ongoing design phase leading to the development phase that

  5. Safety evaluation of RTG launches aboard Titan IV launch vehicles

    SciTech Connect

    Rosko, Robert J.; Loughin, Stephen

    1997-01-10

    The analytical tool used to evaluate accidents aboard a Titan IV launch vehicle involving a Radioisotope Thermoelectric Generator (RTG) is discussed. The Launch Accident Scenario Evaluation Program-Titan IV version (LASEP-T) uses a Monte Carlo approach to determine the response of an RTG to various threatening environments. The threatening environments arise from a complex interplay of probabilistic and deterministic processes, and are therefore parameterized by a set of random variables with probability distributions. The assessment of the RTG response to a given environment is based on both empirical data and theoretical modeling. Imbedding detailed, complex response models into the LASEP-T calculation was not practical. Simpler response models have been constructed to capture both the inherent variability due to the phenomenology of the accident scenario along with the uncertainty of predicting response behavior. The treatment of variability and uncertainty as it pertains to the launch accident evaluation of RTG response will be discussed.

  6. Safety evaluation of RTG launches aboard Titan IV launch vehicles

    NASA Astrophysics Data System (ADS)

    Rosko, Robert J.; Loughin, Stephen

    1997-01-01

    The analytical tool used to evaluate accidents aboard a Titan IV launch vehicle involving a Radioisotope Thermoelectric Generator (RTG) is discussed. The Launch Accident Scenario Evaluation Program-Titan IV version (LASEP-T) uses a Monte Carlo approach to determine the response of an RTG to various threatening environments. The threatening environments arise from a complex interplay of probabilistic and deterministic processes, and are therefore parameterized by a set of random variables with probability distributions. The assessment of the RTG response to a given environment is based on both empirical data and theoretical modeling. Imbedding detailed, complex response models into the LASEP-T calculation was not practical. Simpler response models have been constructed to capture both the inherent variability due to the phenomenology of the accident scenario along with the uncertainty of predicting response behavior. The treatment of variability and uncertainty as it pertains to the launch accident evaluation of RTG response will be discussed.

  7. Softgels: consumer perceptions and market impact relative to other oral dosage forms.

    PubMed

    Jones, W J; Francis, J J

    2000-01-01

    Softgels, which contain a liquid formulation of a drug, often provide clinical benefit over other solid oral dosage forms and may represent an attractive alternative to them. A consumer preference survey of softgels versus other solid forms investigated four areas: (1) identification of various dosage forms; (2) perception of therapeutic benefit (easiest to swallow, faster-acting, work longer); (3) impact of individual product characteristics on overall product selection; and (4) market impact in terms of premiums consumers would pay on the basis of dosage form. The 300 survey participants strongly preferred clear softgels over other dosage forms in virtually every area. Softgels were perceived as easy to swallow and fast-acting, with a duration of action second only to that of a two-piece capsule. Overall preference was driven by ease of swallowing, and softgels were rated first by the majority of respondents. Consumers would be interested in various products if these were available as softgels rather than in their current oral dosage forms and may be willing to pay a premium for softgel products. This survey confirms consumer preferences for particular dosage forms and for softgels over other solid forms. Pharmaceutical scientists and marketers should consider softgels as alternative dosage forms when developing new compounds or considering life-cycle management of existing products. PMID:11186141

  8. Apollo 11 Facts Project [Pre-Launch Activities and Launch

    NASA Technical Reports Server (NTRS)

    1994-01-01

    The crewmembers of Apollo 11, Commander Neil A. Armstrong, Command Module Pilot Michael Collins, and Lunar Module Pilot Edwin E. Aldrin, Jr., are seen during various stages of preparation for the launch of Apollo 11, including suitup, breakfast, and boarding the spacecraft. They are also seen during mission training, including preparation for extravehicular activity on the surface of the Moon. The launch of Apollo 11 is shown. The ground support crew is also seen as they wait for the spacecraft to approach the Moon.

  9. The commercial Aquila Launch Vehicle

    NASA Astrophysics Data System (ADS)

    Flittie, Kirk J.; McFarlane, Scott

    1991-06-01

    The American Rocket Company's (AMROC) Aquila Launch Vehicle is a ground-launched, four-stage, all-hybrid propulsion, inertially-guided commercial space booster designed to deliver 2000 pound payloads into low earth orbit. By using AMROC's low-cost hybrid propulsion, the Aquila launch service will provide quick, on-demand, routine access to space; high accuracy orbital placement; and an unprecedented degree of production, ground and flight safety. The first launch of the Aquila will be in early 1995. Aquila utilizes AMROc's unique hybrid propulsion systems consisting of an inert solid polybutadiene fuel and either liquid oxygen or nitrous oxide as oxidizer. A hybrid propulsion system is distinct from all other rocket propulsion systems in that hybrids cannot explode; hybrids offer safe handling, operation and launch pad abort; and hybrids offer start/stop and full throttling capability for trajectory optimization and precise payload placement on orbit. In addition, the exhaust products do not contain hydrogen chlorides which are environmentally degrading.

  10. Provider Communication and Role Modeling Related to Patients' Perceptions and Use of a Federally Qualified Health Center-based Farmers' Market

    PubMed Central

    Friedman, Daniela B.; Freedman, Darcy A.; Choi, Seul Ki; Anadu, Edith C.; Brandt, Heather M.; Carvalho, Natalia; Hurley, Thomas G.; Young, Vicki M.; Hebert, James R.

    2013-01-01

    Farmers’ markets have the potential to improve the health of underserved communities, shape people’s perceptions, values, and behaviors about healthy eating, and serve as a social space for both community members and vendors. This study explored the influence of health care provider communication and role modeling for diabetic patients within the context of a farmers’ market located at a federally qualified health center (FQHC). Although provider communication about diet decreased over time, communication strategies included: providing patients with “prescriptions” and vouchers for market purchases; educating patients about diet; and modeling healthy purchases. Data from patient interviews and provider surveys revealed that patients enjoyed social aspects of the market including interactions with their health care provider, and providers distributed prescriptions and vouchers to patients, shopped at the market, and believed the market had potential to improve the health of FHQC staff and patients. Provider modeling of healthy behaviors may influence patients’ food-related perceptions and dietary behaviors. PMID:23986503

  11. Contraception. Low-dose pill launched.

    PubMed

    1993-01-01

    At a vibrant ceremony in Kampala, Uganda, the Minister of Women in Development, Youth and Culture launched the new low-dose oral contraceptive Pilplan which provides women more options for birth spacing. Diplomats, physicians, government officials, and business leaders attended the ceremony at the Sheraton Hotel Kampala. A dance group did an interpretation of "Women in Uganda: Gaining Momentum." The Minister considered the introduction of this new pill as a turning point for reproductive rights. A baseline survey among Ugandan women has shown that although almost all women were familiar with the pill, only 36% have ever used it and only 15% were currently using it. 80% thought that pill use was preferable to having an unplanned pregnancy. These findings convinced the Minister that ignorance and misconception keep women from using the pill. The government, health providers, and others need to educate women about Pilplan and how to use it correctly. A bilateral agreement between the Ministry of Health and USAID set in motion a social marketing project which has now launched two contraceptive methods: Pilplan in 1993 and the Protector condom in 1990. USAID vowed to continue to support Pilplan, particularly if men could also help in supporting birth spacing. A Uganda-based pharmaceutical firm will distribute Pilplan in Uganda through pharmacies, clinics, and health facilities. Pilplan targets all middle- to low-income women. PMID:12319754

  12. Theory and evidence about the structure of the international oil market: 1974-1980; a collection of related essays

    SciTech Connect

    Loderer, C.F.

    1983-01-01

    One can argue that the international oil market is competitive. This dissertation, a collection of related essays, tries to resolve that issue by considering the 1974-80 period. The first essay tests the hypotheses that OPEC affects market prices. The analysis employs time-series tests involving spot prices of oil products and stock market portfolio returns. The findings confirm the hypothesis. The second essay looks for other evidence supporting the claim that OPEC is an effective cartel. The cartel is modelled as a dominant producer in a multiperiod world. The evidence contradicts the model. The findings cast doubts on most cartel explanations of the high oil prices. The third essay builds on MacAvoy's findings that the oil prices of the 1970's are mainly the result of an increasing demand and of declining new discoveries. During the first half of the 1970's, ownership of most crude oil reserves in the world was shifted from the international oil producing companies to their host countries through nationalizations and more or less forced equity participation agreements. The evidence shows that the timing of output policy changes in individual countries. However, controlling for changes in price expectations and reserve accumulations, these events are not an important determinant of output rates. Assuming the methodology used is correct, they cannot be a major reason for the oil price increase of the 1970's.

  13. NASA's Launch Propulsion Systems Technology Roadmap

    NASA Technical Reports Server (NTRS)

    McConnaughey, Paul K.; Femminineo, Mark G.; Koelfgen, Syri J.; Lepsch, Roger A; Ryan, Richard M.; Taylor, Steven A.

    2012-01-01

    Safe, reliable, and affordable access to low-Earth (LEO) orbit is necessary for all of the United States (US) space endeavors. In 2010, NASA s Office of the Chief Technologist commissioned 14 teams to develop technology roadmaps that could be used to guide the Agency s and US technology investment decisions for the next few decades. The Launch Propulsion Systems Technology Area (LPSTA) team was tasked to address the propulsion technology challenges for access to LEO. The developed LPSTA roadmap addresses technologies that enhance existing solid or liquid propulsion technologies and their related ancillary systems or significantly advance the technology readiness level (TRL) of less mature systems like airbreathing, unconventional, and other launch technologies. In developing this roadmap, the LPSTA team consulted previous NASA, military, and industry studies as well as subject matter experts to develop their assessment of this field, which has fundamental technological and strategic impacts for US space capabilities.

  14. Power and transmission-rate orders and related documents. Office of power marketing coordination: data compiled through December 1979

    SciTech Connect

    Not Available

    1981-07-01

    Prior to the establishment of the Department of Energy, power from Federal projects was marketed by five power marketing agencies under the Department of the Interior. These were the Alaska Power Administration (APA), the Bonneville Power Administration (BPA), the Southeastern Power Administration(SEPA), the Southwestern Power Administration (SWPA), and the United States Bureau of Reclamation(USBR). Under the ratemaking process, in effect prior to the establishment of DOE, the rates and charges for electric power by the then four power administrations were prepared by the individual Administrators subject to confirmation and approval by the FPC. The rates and charges for electric power marketed by the USBR, were subject to final approval of the Secretary of the Interior. In 1977 the Secretary of Energy authorized the Economic Regulatory Administration (ERA) to confirm and approve all Federal power rate adjustments proposed by the five power administrations, and in December 1978 the Secretary of Energy, signed Delegation Order No. 0204-33 which delegated to the Assistant Secretary for Resource Applications the authority to confirm, approve, and place in effect power and transmission rates on an interim basis and delegated to the FERC the authority to confirm and approve such rates on a final basis. The delegation order became effective January 1, 1979. This publication is a compilation of all rate orders issued by the Assistant Secretary for Resource Applications during Calendar Year 1979 under that delegation order. It also includes all final confirmations and approvals by the ERA and the FERC from October 1, 1977, through December 31, 1979. For ready reference, also included are all delegation orders and departmental orders relating to Federal power marketing.

  15. STS-120 on Launch Pad

    NASA Technical Reports Server (NTRS)

    2007-01-01

    A photographer used a fisheye lens attached to an electronic still camera to record a series of photos of the Space Shuttle Discovery at the launch pad while the STS-120 crew was at Kennedy Space Center for the Terminal Countdown Demonstration Test in October 2007. The STS-120 mission launched from Kennedy Space Center's launch pad 39A at 11:38:19 a.m. (EDT) on October 23, 2007. The crew included Scott E. Parazynski, Douglas H. Wheelock, Stephanie D. Wilson, all mission specialists; George D. Zamka, pilot; Pamela A. Melroy, commander; Daniel M. Tani, Expedition 16 flight engineer; and Paolo A. Nespoli, mission specialist representing the European Space Agency (ESA). Major objectives included the installation of the P6 solar array of the port truss and delivery and installment of Harmony, the Italian-built U.S. Node 2 on the International Space Station (ISS).

  16. Nanosatellite Launch Adapter System (NLAS)

    NASA Technical Reports Server (NTRS)

    Chartres, James; Cappuccio, Gelsomina

    2015-01-01

    The Nanosatellite Launch Adapter System (NLAS) was developed to increase access to space while simplifying the integration process of miniature satellites, called nanosats or CubeSats, onto launch vehicles. A standard CubeSat measures about 10 cm square, and is referred to as a 1-unit (1U) CubeSat. A single NLAS provides the capability to deploy 24U of CubeSats. The system is designed to accommodate satellites measuring 1U, 1.5U, 2U, 3U and 6U sizes for deployment into orbit. The NLAS may be configured for use on different launch vehicles. The system also enables flight demonstrations of new technologies in the space environment.

  17. Labor market segmentation and relative black/white teenage birth rates.

    PubMed

    Mccrate, E

    1990-01-01

    "Teenage mothers typically have lower educational attainment than other women. Most observers have argued that this is a major reason for their greater risk of poverty. This article takes the opposite view: that circumstances associated with poverty contribute to a greater likelihood of teenage childbearing. In particular, poor educational quality and the chances of secondary sector employment are more common for black women, regardless of their age at first birth. Hence the payoffs to education may be quite low for these women, which may be the reason for early motherhood. This argument is presented in terms of segmented labor market theory. Data to support it is presented from the [U.S.] National Longitudinal Survey of Youth. Other common explanations of teenage motherhood are critiqued." PMID:12285449

  18. 2nd Generation Reusable Launch Vehicle Potential Commercial Development Scenarios

    NASA Technical Reports Server (NTRS)

    Creech, Stephen D.; Rogacki, John R. (Technical Monitor)

    2001-01-01

    The presentation will discuss potential commercial development scenarios for a Second Generation Reusable Launch Vehicle. The analysis of potential scenarios will include commercial rates of return, government return on investment, and market considerations. The presentation will include policy considerations in addition to analysis of Second Generation Reusable Launch Vehicle economics. The data discussed is being developed as a part of NASA's Second Generation Reusable Launch Vehicle Program, for consideration as potential scenarios for enabling a next generation system. Material will include potential scenarios not previously considered by NASA or presented at other conferences. Candidate paper has not been presented at a previous meeting, and conference attendance of the author has been approved by NASA.

  19. Personnel Launch System (PLS) study

    NASA Technical Reports Server (NTRS)

    Ehrlich, Carl F., Jr.

    1991-01-01

    NASA is currently studying a personnel launch system (PLS) approach to help satisfy the crew rotation requirements for the Space Station Freedom. Several concepts from low L/D capsules to lifting body vehicles are being examined in a series of studies as a potential augmentation to the Space Shuttle launch system. Rockwell International Corporation, under contract to NASA, analyzed a lifting body concept to determine whether the lifting body class of vehicles is appropriate for the PLS function. The results of the study are given.

  20. The Scout Launch Vehicle program

    NASA Technical Reports Server (NTRS)

    Foster, L. R., Jr.; Urash, R. G.

    1981-01-01

    The Scout Launch Vehicle Program to utilize solid propellant rockets by the DOD and to provide a reliable, low cost vehicle for scientific and applications aircraft is discussed. The program's history is reviewed and a vehicle description is given. The Vandenberg Air Force Base and the San Marco launch sites are described, and capabilities such as payload weight, orbital inclinations, payload volume and mission integration time spans are discussed. Current and future plans for improvement, including larger heat shields and individual rocket motors are also reviewed.

  1. The U.S. Commercial Space Launch Program and the Department of Defense Dilemma

    NASA Technical Reports Server (NTRS)

    Clapp, William G.

    1995-01-01

    The U.S. space launch program no longer dominates the world and is now playing 'catch-up' with the world's first commercial launch company, Arianespace. A healthy U.S. commercial launch program is essential and will assure continued low-cost military access to space. The effort to regain the lead in commercial space launch market has been hindered by declining Department of Defense budgets. President Clinton's space policy prohibits expensive new launch vehicles and limits the Department of Defense to low cost upgrades of existing launch vehicles. The U.S. government created the space sector and must ensure a smooth and effective split from the emerging commercial space program in order to regain world dominance. Until U.S. government and commercial ties are severed, the Department of Defense must consider commercial space launch interests when making military decisions. Ariane provides an excellent 'bench mark' for the U.S. to base future launch vehicle upgrades. Ariane advantages were identified and low-cost recommendations have been made. If the U.S. sets the target of first equaling and then surpassing Ariane by incorporating these recommendations, then the U.S. could once again dominate the world commercial launch market and ensure low cost military access to space.

  2. Reusable Reentry Satellite (RRS): Launch tradeoff study

    NASA Technical Reports Server (NTRS)

    1990-01-01

    A goal of the Phase B study is to define the launch system interfaces for the reusable reentry satellite (RRS) program. The focus of the launch tradeoff study, documented in this report, is to determine which expendable launch vehicles (ELV's) are best suited for the RRS application by understanding the impact of all viable launch systems on RRS design and operation.

  3. Intelsat communications satellite scheduled for launch

    NASA Technical Reports Server (NTRS)

    1983-01-01

    To be placed into a highly elliptical transfer orbit by the Atlas Centaur (AC-61) launch vehicle, the INTELSAT V-F satellite has 12,000 voice circuits and 2 color television channels and incorporates a maritime communication system for ship to shore communications. The stages of the launch vehicle and the launch operations are described. A table shows the launch sequence.

  4. Macroeconomic Benefits of Low-Cost Reusable Launch Vehicles

    NASA Technical Reports Server (NTRS)

    Shaw, Eric J.; Greenberg, Joel

    1998-01-01

    The National Aeronautics and Space Administration (NASA) initiated its Reusable Launch Vehicle (RLV) Technology Program to provide information on the technical and commercial feasibility of single-stage to orbit (SSTO), fully-reusable launchers. Because RLVs would not depend on expendable hardware to achieve orbit, they could take better advantage of economies of scale than expendable launch vehicles (ELVs) that discard costly hardware on ascent. The X-33 experimental vehicle, a sub-orbital, 60%-scale prototype of Lockheed Martin's VentureStar SSTO RLV concept, is being built by Skunk Works for a 1999 first flight. If RLVs achieve prices to low-earth orbit of less than $1000 US per pound, they could hold promise for eliciting an elastic response from the launch services market. As opposed to the capture of existing market, this elastic market would represent new space-based industry businesses. These new opportunities would be created from the next tier of business concepts, such as space manufacturing and satellite servicing, that cannot earn a profit at today's launch prices but could when enabled by lower launch costs. New business creation contributes benefits to the US Government (USG) and the US economy through increases in tax revenues and employment. Assumptions about the costs and revenues of these new ventures, based on existing space-based and aeronautics sector businesses, can be used to estimate the macroeconomic benefits provided by new businesses. This paper examines these benefits and the flight prices and rates that may be required to enable these new space industries.

  5. Adaptive Attitude Control of the Crew Launch Vehicle

    NASA Technical Reports Server (NTRS)

    Muse, Jonathan

    2010-01-01

    An H(sub infinity)-NMA architecture for the Crew Launch Vehicle was developed in a state feedback setting. The minimal complexity adaptive law was shown to improve base line performance relative to a performance metric based on Crew Launch Vehicle design requirements for all most all of the Worst-on-Worst dispersion cases. The adaptive law was able to maintain stability for some dispersions that are unstable with the nominal control law. Due to the nature of the H(sub infinity)-NMA architecture, the augmented adaptive control signal has low bandwidth which is a great benefit for a manned launch vehicle.

  6. Is the core-periphery labour market structure related to perceived health? findings of the Northern Swedish Cohort

    PubMed Central

    2011-01-01

    Background There is controversy as to whether peripheral employment is related to poor health status or not. This study aims at examining whether 1) the accumulation of time in peripheral labour market positions is associated with psychological distress and poor or average self-rated health; 2) the proposed association is different among women than among men. Method Participants in the 1995 and 2007 follow-up surveys of the Northern Swedish Cohort (n = 985) completed self-administered questionnaires about psychological and general health and about employment positions during the follow-up years. Associations between 12 year peripheral labour market positions (no, low, medium and high exposure) and health were examined using logistic regression. Results Exposure to peripheral employment was positively related to psychological distress in both women and men (p-values for trend < 0.001). Adjustment for sociodemographics and psychological distress at baseline, as well as for unemployment and being out of the labour market at the follow-up, resulted in attenuation of the odds ratios, particularly in the group with high exposure to peripheral employment, although results remained significant in men in the fully adjusted model. Women and men with high exposure to peripheral employment had high odds of poor or average self-rated health, but the association was rendered non-significant after adjustment for the covariates. Conclusions Our findings suggest that exposure to peripheral employment positions has an impact particularly on mental health, partly due to the over-representation of other unfavourable social and employment conditions among those with substantial exposure to peripheral employment. PMID:22202436

  7. STS-1 Pre-Launch

    NASA Technical Reports Server (NTRS)

    1981-01-01

    A timed exposure of the Space Shuttle, STS-1, at Launch Pad A, Complex 39, turns the space vehicle and support facilities into a night- time fantasy of light. Structures to the left of the Shuttle are the fixed and the rotating service structure.

  8. Skylab Components in Launch Configuration

    NASA Technical Reports Server (NTRS)

    1969-01-01

    This cutaway drawing illustrates major Skylab components in launch configuration on top of the Saturn V. In an early effort to extend the use of Apollo for further applications, NASA established the Apollo Applications Program (AAP) in August of 1965. The AAP was to include long duration Earth orbital missions during which astronauts would carry out scientific, technological, and engineering experiments in space by utilizing modified Saturn launch vehicles and the Apollo spacecraft. Established in 1970, the Skylab Program was the forerurner of the AAP. The goals of the Skylab were to enrich our scientific knowledge of the Earth, the Sun, the stars, and cosmic space; to study the effects of weightlessness on living organisms, including man; to study the effects of the processing and manufacturing of materials utilizing the absence of gravity; and to conduct Earth resource observations. The Skylab also conducted 19 selected experiments submitted by high school students. Skylab's 3 different 3-man crews spent up to 84 days in Earth orbit. The Marshall Space Flight Center (MSFC) had responsibility for developing and integrating most of the major components of the Skylab: the Orbital Workshop (OWS), Airlock Module (AM), Multiple Docking Adapter (MDA), Apollo Telescope Mount (ATM), Payload Shroud (PS), and most of the experiments. MSFC was also responsible for providing the Saturn IB launch vehicles for three Apollo spacecraft and crews and a Saturn V launch vehicle for the Skylab.

  9. Deep Impact on Launch Pad

    NASA Technical Reports Server (NTRS)

    2005-01-01

    Deep Impact awaits launch from Cape Canaveral Air Force Station, Fla. on Jan. 12, 2005.

    The spacecraft will travel to comet Tempel 1 and release an impactor, creating a crater on the surface of the comet. Scientists believe the exposed materials may give clues to the formation of our solar system.

  10. Space Shuttle Launch: STS-129

    NASA Video Gallery

    STS-129. Space shuttle Atlantis and its six-member crew began an 11-day delivery flight to the International Space Station on Monday, Nov 16, 2009, with a 2:28 p.m. EST launch from NASA's Kennedy S...

  11. Relation between Financial Market Structure and the Real Economy: Comparison between Clustering Methods

    PubMed Central

    Musmeci, Nicoló; Aste, Tomaso; Di Matteo, T.

    2015-01-01

    We quantify the amount of information filtered by different hierarchical clustering methods on correlations between stock returns comparing the clustering structure with the underlying industrial activity classification. We apply, for the first time to financial data, a novel hierarchical clustering approach, the Directed Bubble Hierarchical Tree and we compare it with other methods including the Linkage and k-medoids. By taking the industrial sector classification of stocks as a benchmark partition, we evaluate how the different methods retrieve this classification. The results show that the Directed Bubble Hierarchical Tree can outperform other methods, being able to retrieve more information with fewer clusters. Moreover, we show that the economic information is hidden at different levels of the hierarchical structures depending on the clustering method. The dynamical analysis on a rolling window also reveals that the different methods show different degrees of sensitivity to events affecting financial markets, like crises. These results can be of interest for all the applications of clustering methods to portfolio optimization and risk hedging. PMID:25786703

  12. Relation between financial market structure and the real economy: comparison between clustering methods.

    PubMed

    Musmeci, Nicoló; Aste, Tomaso; Di Matteo, T

    2015-01-01

    We quantify the amount of information filtered by different hierarchical clustering methods on correlations between stock returns comparing the clustering structure with the underlying industrial activity classification. We apply, for the first time to financial data, a novel hierarchical clustering approach, the Directed Bubble Hierarchical Tree and we compare it with other methods including the Linkage and k-medoids. By taking the industrial sector classification of stocks as a benchmark partition, we evaluate how the different methods retrieve this classification. The results show that the Directed Bubble Hierarchical Tree can outperform other methods, being able to retrieve more information with fewer clusters. Moreover,we show that the economic information is hidden at different levels of the hierarchical structures depending on the clustering method. The dynamical analysis on a rolling window also reveals that the different methods show different degrees of sensitivity to events affecting financial markets, like crises. These results can be of interest for all the applications of clustering methods to portfolio optimization and risk hedging [corrected]. PMID:25786703

  13. Worker illness related to newly marketed pesticides--Douglas County, Washington, 2014.

    PubMed

    Calvert, Geoffrey M; Rodriguez, Luis; Prado, Joanne Bonnar

    2015-01-23

    On April 10, 2014 the Washington State Department of Agriculture (WSDA) was notified by a local newspaper of a suspected pesticide poisoning incident in Douglas County involving pesticides not previously reported in the published literature to be associated with human illness. On that same day, WSDA notified the Washington State Department of Health, which investigated this incident by conducting a site visit, reviewing medical and applicator records, and interviewing affected farmworkers, pesticide applicators, and the farmworkers' employer. In addition, on April 11, WSDA collected swab, foliage, and clothing samples and tested them for residues of pyridaben, novaluron, and triflumizole. In this incident, all 20 farmworkers working in a cherry orchard became ill from off-target drift of a pesticide mixture that was being applied to a neighboring pear orchard. Sixteen sought medical treatment for neurologic, gastrointestinal, ocular, and respiratory symptoms. This event highlights the need for greater efforts to prevent off-target drift exposures and promote awareness about the toxicity of some recently marketed pesticides. Incidents such as this could be prevented if farm managers planning pesticide applications notify their neighbors of their plans. PMID:25611169

  14. Quality defects in market beef and dairy cows and bulls sold through livestock auction markets in the Western United States: II. Relative effects on selling price.

    PubMed

    Ahola, J K; Foster, H A; Vanoverbeke, D L; Jensen, K S; Wilson, R L; Glaze, J B; Fife, T E; Gray, C W; Nash, S A; Panting, R R; Rimbey, N R

    2011-05-01

    Relative effects of Beef Quality Assurance (BQA)-related defects in market beef and dairy cows and bulls on selling price at auction was evaluated during 2008. The presence and severity of 23 BQA-related traits were determined during sales in Idaho, California, and Utah. Overall, 18,949 unique lots consisting of 23,479 animals were assessed during 125 dairy sales and 79 beef sales. Mean sale price ± SD (per 45.5 kg) for market beef cows, beef bulls, dairy cows, and dairy bulls was $45.15 ± 9.42, $56.30 ± 9.21, $42.23 ± 12.26, and $55.10 ± 9.07, respectively. When combined, all recorded traits explained 36% of the variation in selling price in beef cows, 35% in beef bulls, 61% in dairy cows, and 56% in dairy bulls. Premiums and discounts were determined in comparison with a "par" or "base" animal. Compared with a base BCS 5 beef cow (on a 9-point beef scale), BCS 1 to 4 cows were discounted (P < 0.0001), whereas premiums (P < 0.05) were estimated for BCS 6 to 8. Compared with a base BCS 3.0 dairy cow (on a 5-point dairy scale), more body condition resulted in a premium (P ≤ 0.001), whereas a less-than-desirable BCS of 2.0 or 2.5 was discounted (P < 0.0001). Emaciated or near-emaciated cows (beef BCS 1 or 2; dairy BCS 1.0 or 1.5) were discounted (P < 0.0001). Compared with base cows weighing 545 to 635 kg, lighter BW beef cows were discounted (P < 0.0001), whereas heavier beef cows received (P < 0.05) a premium. Compared with a base dairy cow weighing 636 to 727 kg, lighter BW cows were discounted (P < 0.0001), whereas heavier cows (727 to 909 kg) received a premium (P < 0.01). Beef and dairy cows with any evidence of lameness were discounted (P < 0.0001). Presence of ocular neoplasia in the precancerous stage discounted (P = 0.05) beef cows and discounted (P < 0.01) dairy cows, whereas at the cancerous stage, it discounted (P < 0.0001) all cows. Hide color influenced (P < 0.0001) selling price in beef cattle but had no effect (P = 0.17) in dairy cows. Animals

  15. NASA's Space Launch System: Momentum Builds Toward First Launch

    NASA Technical Reports Server (NTRS)

    May, Todd A.; Lyles, Garry M.

    2014-01-01

    NASA's Space Launch System (SLS) is gaining momentum toward the first launch of a new exploration-class heavy lift launch vehicle for international exploration and science initiatives. The SLS comprises an architecture that begins with a vehicle capable of launching 70 metric tons (t) into low Earth orbit. It will launch the Orion Multi-Purpose Crew Vehicle (MPCV) on its first autonomous flight beyond the Moon and back in December 2017. Its first crewed flight follows in 2021. SLS can evolve to a130-t lift capability and serve as a baseline for numerous robotic and human missions ranging from a Mars sample return to delivering the first astronauts to explore another planet. The SLS Program formally transitioned from the formulation phase to implementation with the successful completion of the rigorous Key Decision Point C review in 2014. As a result, the Agency authorized the Program to move forward to Critical Design Review, scheduled for 2015. In the NASA project life cycle process, SLS has completed 50 percent of its major milestones toward first flight. Every SLS element manufactured development hardware for testing over the past year. Accomplishments during 2013/2014 included manufacture of core stage test articles, preparations for qualification testing the solid rocket boosters and the RS-25 main engines, and shipment of the first flight hardware in preparation for the Exploration Flight Test-1 (EFT-1) in 2014. SLS was conceived with the goals of safety, affordability, and sustainability, while also providing unprecedented capability for human exploration and scientific discovery beyond Earth orbit. In an environment of economic challenges, the SLS team continues to meet ambitious budget and schedule targets through the studied use of hardware, infrastructure, and workforce investments the United States made in the last half century, while selectively using new technologies for design, manufacturing, and testing, as well as streamlined management approaches

  16. Tourism Marketing.

    ERIC Educational Resources Information Center

    North Carolina State Dept. of Public Instruction, Raleigh. Div. of Vocational Education.

    This document contains teacher materials for a 6-unit, 1-year distributive education course in marketing tourism offered in grades 11 and 12 in North Carolina. Although in general the material presented concerns marketing tourism anywhere, some of it is specifically related to tourism within North Carolina. A purpose statement explains the…

  17. Launch vehicle and power level impacts on electric GEO insertion

    NASA Technical Reports Server (NTRS)

    Oleson, Steven R.; Myers, Roger M.

    1996-01-01

    Solar Electric Propulsion (SEP) has been shown to increase net geosynchronous spacecraft mass when used for station keeping and final orbit insertion. The impact of launch vehicle selection and power level on the benefits of this approach were examined for 20 and 25 kW systems launched using the Ariane 5, Atlas IIAR, Long March, Proton, and Sea Launch vehicles. Two advanced on-board propulsion technologies, 5 kW ion and Hall thruster systems, were used to establish the relative merits of the technologies and launch vehicles. GaAs solar arrays were assumed. The analysis identifies the optimal starting orbits for the SEP orbit raising/plane changing while considering the impacts of radiation degradation in the Van Allen belts, shading, power degradation, and oblateness. This use of SEP to provide part of the orbit insertion results in net mass increases of 15 - 38% and 18 - 46% for one to two month trip times, respectively, over just using SEP for 15 years of north/south station keeping. SEP technology was shown to have a greater impact on net masses of launch vehicles with higher launch latitudes when avoidance of solar array and payload degradation is desired. This greater impact of SEP could help reduce the plane changing disadvantage of high latitude launch sites. Comparison with results for 10 and 15 kW systems show clear benefits of incremental increases in SEP power level, suggesting that an evolutionary approach to high power SEP for geosynchronous spacecraft is possible.

  18. 14 CFR 420.21 - Launch site location review-launch site boundary.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... the debris dispersion radius of the largest launch vehicle type and weight class proposed for the launch point. (b) For a launch site supporting any expendable launch vehicle, an applicant shall use the largest distance provided by table 2 for the type and weight class of any launch vehicle proposed for...

  19. 14 CFR 420.21 - Launch site location review-launch site boundary.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... the debris dispersion radius of the largest launch vehicle type and weight class proposed for the launch point. (b) For a launch site supporting any expendable launch vehicle, an applicant shall use the largest distance provided by table 2 for the type and weight class of any launch vehicle proposed for...

  20. 14 CFR 420.21 - Launch site location review-launch site boundary.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... the debris dispersion radius of the largest launch vehicle type and weight class proposed for the launch point. (b) For a launch site supporting any expendable launch vehicle, an applicant shall use the largest distance provided by table 2 for the type and weight class of any launch vehicle proposed for...

  1. 14 CFR 420.29 - Launch site location review for unproven launch vehicles.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... launch vehicles. An applicant for a license to operate a launch site for an unproven launch vehicle shall... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Launch site location review for unproven launch vehicles. 420.29 Section 420.29 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION,...

  2. 14 CFR 420.29 - Launch site location review for unproven launch vehicles.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... launch vehicles. An applicant for a license to operate a launch site for an unproven launch vehicle shall... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Launch site location review for unproven launch vehicles. 420.29 Section 420.29 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION,...

  3. 14 CFR 420.29 - Launch site location review for unproven launch vehicles.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... launch vehicles. An applicant for a license to operate a launch site for an unproven launch vehicle shall... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Launch site location review for unproven launch vehicles. 420.29 Section 420.29 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION,...

  4. 14 CFR 420.21 - Launch site location review-launch site boundary.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... the debris dispersion radius of the largest launch vehicle type and weight class proposed for the launch point. (b) For a launch site supporting any expendable launch vehicle, an applicant shall use the largest distance provided by table 2 for the type and weight class of any launch vehicle proposed for...

  5. 14 CFR 420.29 - Launch site location review for unproven launch vehicles.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... launch vehicles. An applicant for a license to operate a launch site for an unproven launch vehicle shall... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Launch site location review for unproven launch vehicles. 420.29 Section 420.29 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION,...

  6. 14 CFR 417.125 - Launch of an unguided suborbital launch vehicle.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Launch of an unguided suborbital launch vehicle. 417.125 Section 417.125 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LAUNCH SAFETY Launch Safety Responsibilities § 417.125 Launch of an unguided...

  7. Safety evaluation of RTG launches aboard Titan IV launch vehicles

    SciTech Connect

    Rosko, R.J.; Loughin, S.

    1997-01-01

    The analytical tool used to evaluate accidents aboard a Titan IV launch vehicle involving a Radioisotope Thermoelectric Generator (RTG) is discussed. The Launch Accident Scenario Evaluation Program-Titan IV version (LASEP-T) uses a Monte Carlo approach to determine the response of an RTG to various threatening environments. The threatening environments arise from a complex interplay of probabilistic and deterministic processes, and are therefore parameterized by a set of random variables with probability distributions. The assessment of the RTG response to a given environment is based on both empirical data and theoretical modeling. Imbedding detailed, complex response models into the LASEP-T calculation was not practical. Simpler response models have been constructed to capture both the inherent variability due to the phenomenology of the accident scenario along with the uncertainty of predicting response behavior. The treatment of variability and uncertainty as it pertains to the launch accident evaluation of RTG response will be discussed. {copyright} {ital 1997 American Institute of Physics.}

  8. Space Launch System Development Status

    NASA Technical Reports Server (NTRS)

    Lyles, Garry

    2014-01-01

    Development of NASA's Space Launch System (SLS) heavy lift rocket is shifting from the formulation phase into the implementation phase in 2014, a little more than three years after formal program approval. Current development is focused on delivering a vehicle capable of launching 70 metric tons (t) into low Earth orbit. This "Block 1" configuration will launch the Orion Multi-Purpose Crew Vehicle (MPCV) on its first autonomous flight beyond the Moon and back in December 2017, followed by its first crewed flight in 2021. SLS can evolve to a130-t lift capability and serve as a baseline for numerous robotic and human missions ranging from a Mars sample return to delivering the first astronauts to explore another planet. Benefits associated with its unprecedented mass and volume include reduced trip times and simplified payload design. Every SLS element achieved significant, tangible progress over the past year. Among the Program's many accomplishments are: manufacture of Core Stage test panels; testing of Solid Rocket Booster development hardware including thrust vector controls and avionics; planning for testing the RS-25 Core Stage engine; and more than 4,000 wind tunnel runs to refine vehicle configuration, trajectory, and guidance. The Program shipped its first flight hardware - the Multi-Purpose Crew Vehicle Stage Adapter (MSA) - to the United Launch Alliance for integration with the Delta IV heavy rocket that will launch an Orion test article in 2014 from NASA's Kennedy Space Center. Objectives of this Earth-orbit flight include validating the performance of Orion's heat shield and the MSA design, which will be manufactured again for SLS missions to deep space. The Program successfully completed Preliminary Design Review in 2013 and Key Decision Point C in early 2014. NASA has authorized the Program to move forward to Critical Design Review, scheduled for 2015 and a December 2017 first launch. The Program's success to date is due to prudent use of proven

  9. Dynamic Tow Maneuver Orbital Launch Technique

    NASA Technical Reports Server (NTRS)

    Rutan, Elbert L. (Inventor)

    2014-01-01

    An orbital launch system and its method of operation use a maneuver to improve the launch condition of a booster rocket and payload. A towed launch aircraft, to which the booster rocket is mounted, is towed to a predetermined elevation and airspeed. The towed launch aircraft begins the maneuver by increasing its lift, thereby increasing the flight path angle, which increases the tension on the towline connecting the towed launch aircraft to a towing aircraft. The increased tension accelerates the towed launch aircraft and booster rocket, while decreasing the speed (and thus the kinetic energy) of the towing aircraft, while increasing kinetic energy of the towed launch aircraft and booster rocket by transferring energy from the towing aircraft. The potential energy of the towed launch aircraft and booster rocket is also increased, due to the increased lift. The booster rocket is released and ignited, completing the launch.

  10. NASA's Space Launch System: Moving Toward the Launch Pad

    NASA Technical Reports Server (NTRS)

    Creech, Stephen D.; May, Todd A.

    2013-01-01

    The National Aeronautics and Space Administration's (NASA's) Space Launch System (SLS) Program, managed at the Marshall Space Flight Center (MSFC), is making progress toward delivering a new capability for human space flight and scientific missions beyond Earth orbit. Designed with the goals of safety, affordability, and sustainability in mind, the SLS rocket will launch the Orion Multi-Purpose Crew Vehicle (MPCV), equipment, supplies, and major science missions for exploration and discovery. Supporting Orion's first autonomous flight to lunar orbit and back in 2017 and its first crewed flight in 2021, the SLS will evolve into the most powerful launch vehicle ever flown via an upgrade approach that will provide building blocks for future space exploration. NASA is working to deliver this new capability in an austere economic climate, a fact that has inspired the SLS team to find innovative solutions to the challenges of designing, developing, fielding, and operating the largest rocket in history. This paper will summarize the planned capabilities of the vehicle, the progress the SLS Program has made in the 2 years since the Agency formally announced its architecture in September 2011, the path it is following to reach the launch pad in 2017 and then to evolve the 70 metric ton (t) initial lift capability to 130-t lift capability after 2021. The paper will explain how, to meet the challenge of a flat funding curve, an architecture was chosen that combines the use and enhancement of legacy systems and technology with strategic new developments that will evolve the launch vehicle's capabilities. This approach reduces the time and cost of delivering the initial 70 t Block 1 vehicle, and reduces the number of parallel development investments required to deliver the evolved 130 t Block 2 vehicle. The paper will outline the milestones the program has already reached, from developmental milestones such as the manufacture of the first flight hardware, to life

  11. NASA's Space Launch System: Moving Toward the Launch Pad

    NASA Technical Reports Server (NTRS)

    Creech, Stephen D.; May, Todd

    2013-01-01

    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. Developed with the goals of safety, affordability, and sustainability in mind, the SLS rocket will launch the Orion Multi-Purpose Crew Vehicle (MPCV), equipment, supplies, and major science missions for exploration and discovery. Supporting Orion's first autonomous flight to lunar orbit and back in 2017 and its first crewed flight in 2021, the SLS will evolve into the most powerful launch vehicle ever flown, via an upgrade approach that will provide building blocks for future space exploration and development. NASA is working to develop this new capability in an austere economic climate, a fact which has inspired the SLS team to find innovative solutions to the challenges of designing, developing, fielding, and operating the largest rocket in history. This paper will summarize the planned capabilities of the vehicle, the progress the SLS program has made in the 2 years since the Agency formally announced its architecture in September 2011, and the path the program is following to reach the launch pad in 2017 and then to evolve the 70 metric ton (t) initial lift capability to 130-t lift capability. The paper will explain how, to meet the challenge of a flat funding curve, an architecture was chosen which combines the use and enhancement of legacy systems and technology with strategic new development projects that will evolve the capabilities of the launch vehicle. This approach reduces the time and cost of delivering the initial 70 t Block 1 vehicle, and reduces the number of parallel development investments required to deliver the evolved version of the vehicle. The paper will outline the milestones the program has already reached, from developmental milestones such as the manufacture of the first flight

  12. From Relationships to Relationship Marketing: Applying Database Technology to Public Relations.

    ERIC Educational Resources Information Center

    Petrison, Lisa A.; Wang, Paul

    1993-01-01

    Notes that advances in new technologies and uses of databases have expanded the definition of publics and increased the ability to target messages to narrower and narrower ranges of publics. Explores the implications of these developments for the public relations profession. (RS)

  13. Alcohol-Related Incident Guardianship and Undergraduate College Parties: Enhancing the Social Norms Marketing Approach

    ERIC Educational Resources Information Center

    Gilbertson, Troy A.

    2006-01-01

    This randomized experiment examines the effects of contextual information on undergraduate college student's levels of alcohol-related incident guardianship at college parties. The research is conceptualized using routine activities theory and the theory of planned behavior. The experiment examines attitudinal variations about heavy drinking…

  14. Phobos/Harp post launch support

    NASA Technical Reports Server (NTRS)

    Nagy, Andrew

    1993-01-01

    The activity under this grant concentrated on: (1) post-launch calibration of the HARP instrument; and (2) analysis and interpretation of the data from the HARP and other related instruments. The HARP was taken by scientists and engineers from the Hungarian Central Research Institute for Physics (CRIP) to NASA/MSFC for calibration in their plasma chamber, with partial support of this grant. This electron and ion calibration of the HARP, helped in transforming measured currents to actual flux values. The analysis and interpretation of the data, carried out jointly by our Russian and Hungarian colleagues and us, led to a number of journal publications and presentations at scientific meetings.

  15. Aqua 10 Years After Launch

    NASA Technical Reports Server (NTRS)

    Parkinson, Claire L.

    2013-01-01

    A little over ten years ago, in the early morning hours of May 4, 2002, crowds of spectators stood anxiously watching as the Delta II rocket carrying NASA's Aqua spacecraft lifted off from its launch pad at Vandenberg Air Force Base in California at 2:55 a.m. The rocket quickly went through a low-lying cloud cover, after which the main portion of the rocket fell to the waters below and the rockets second stage proceeded to carry Aqua south across the Pacific, onward over Antarctica, and north to Africa, where the spacecraft separated from the rocket 59.5 minutes after launch. Then, 12.5 minutes later, the solar array unfurled over Europe, and Aqua was on its way in the first of what by now have become over 50,000 successful orbits of the Earth.

  16. Launching jets from accretion belts

    NASA Astrophysics Data System (ADS)

    Schreier, Ron; Soker, Noam

    2016-05-01

    We propose that sub-Keplerian accretion belts around stars might launch jets. The sub-Keplerian inflow does not form a rotationally supported accretion disk, but it rather reaches the accreting object from a wide solid angle. The basic ingredients of the flow are a turbulent region where the accretion belt interacts with the accreting object via a shear layer, and two avoidance regions on the poles where the accretion rate is very low. A dynamo that is developed in the shear layer amplifies magnetic fields to high values. It is likely that the amplified magnetic fields form polar outflows from the avoidance regions. Our speculative belt-launched jets model has implications on a rich variety of astrophysical objects, from the removal of common envelopes to the explosion of core collapse supernovae by jittering jets.

  17. TDRS is ready for launch

    NASA Technical Reports Server (NTRS)

    2000-01-01

    In the early morning hours on Launch Pad 36A, Cape Canaveral Air Force Station, the tower rolls back from NASA's Tracking and Data Relay Satellite (TDRS-H) before liftoff atop an Atlas IIA/Centaur rocket. One of three satellites (labeled H, I and J) being built by the Hughes Space and Communications Company, the latest TDRS uses an innovative springback antenna design. A pair of 15-foot- diameter, flexible mesh antenna reflectors fold up for launch, then spring back into their original cupped circular shape on orbit. The new satellites will augment the TDRS system's existing S- and Ku-band frequencies by adding Ka-band capability. TDRS will serve as the sole means of continuous, high-data-rate communication with the Space Shuttle, with the International Space Station upon its completion, and with dozens of unmanned scientific satellites in low earth orbit.

  18. 17 CFR 229.201 - (Item 201) Market price of and dividends on the registrant's common equity and related...

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ...) Identify the principal United States market or markets in which each class of the registrant's common..., for each class of the registrant's common equity. (ii) If the principal United States market for such...) Dividends. (1) State the frequency and amount of any cash dividends declared on each class of its...

  19. 17 CFR 229.201 - (Item 201) Market price of and dividends on the registrant's common equity and related...

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ...) Identify the principal United States market or markets in which each class of the registrant's common..., for each class of the registrant's common equity. (ii) If the principal United States market for such...) Dividends. (1) State the frequency and amount of any cash dividends declared on each class of its...

  20. The launch of MCBEND 10.

    PubMed

    Cowan, P; Shuttleworth, E; Bird, A; Cooper, A

    2005-01-01

    MCBEND 10 is the latest release of the general radiation transport Monte Carlo code from the ANSWERS Software Service of Serco Assurance. MCBEND is developed within a Nuclear Code Development (NCD) partnership between Serco Assurance and BNFL. The ANSWERS vision is 'to provide easy-to-use software that meets the current and emerging needs of the user community'. In the case of MCBEND, this vision focuses on the key areas of accuracy, understanding of uncertainties, efficiency and user-friendliness. MCBEND 10 is a major launch of the code with many new and enhanced features. New developments in MCBEND 10 include automatic splitting mesh generation, point energy adjoint for neutrons, calculation of uncertainty in the results due to material cross section uncertainties and a unified source facility. Enhanced features include improved temperature treatment, extended scoring of sensitivity to geometry perturbations, geometry improvements, extensions to formulae and improved user guide image. The user-friendliness of the MCBEND code has been further enhanced by recent developments to the visualisation tools, VISAGE and VISTA-RAY. Developments have been made to the three-dimensional visualisation tool, VISTA-RAY, to simplify the detailed checking of a model, with the option to use a mouse-pointer to select regions of interest for further detail and to visually highlight incorrectly defined areas. A further development to VISTA-RAY is the inclusion of the capability to overlay a representation of a user-designated set of results from a MCBEND analysis on the model. Improvements have also been made to the graphical user interface LaunchPad for submitting and controlling calculation submission, with a common user-image across all the systems. Recent enhancements to LaunchPad include a job-scheduler to simplify processing multiple tasks. A selection of the new developments in MCBEND 10, VISTA-RAY and LaunchPad will be described in this paper. PMID:16381755

  1. Minuteman 2 launched small satellite

    NASA Technical Reports Server (NTRS)

    Chan, Sunny; Hinders, Kriss; Martin, Trent; Mcmillian, Shandy; Sharp, Brad; Vajdos, Greg

    1994-01-01

    The goal of LEOSat Industries' Spring 1994 project was to design a small satellite that has a strong technology demonstration or scientific justification and incorporates a high level of student involvement. The satellite is to be launched into low earth orbit by the converted Minuteman 2 satellite launcher designed by Minotaur Designs, Inc. in 1993. The launch vehicle shroud was modified to a height of 90 inches, a diameter of 48 inches at the bottom and 35 inches at the top for a total volume of 85 cubic feet. The maximum allowable mass of the payload is about 1100 lb., depending on the launch site, orbit altitude, and inclination. The satellite designed by LEOSat Industries is TerraSat, a remote-sensing satellite that will provide information for use in space-based earth studies. It will consist of infrared and ultraviolet/visible sensors similar to the SDI-developed sensors being tested on Clementine. The sensors will be mounted on the Defense Systems, Inc. Standard Satellite-1 spacecraft bus. LEOSat has planned for two satellites orbiting the Earth with trajectories similar to that of LANDSAT 5. The semi-major axis is 7080 kilometers, the eccentricity is 0, and the inclination is 98.2 degrees. The estimated mass of TerraSat is 145 kilograms and the estimated volume is 1.8 cubic meters. The estimated cost of TerraSat is $13.7 million. The projected length of time from assembly of the sensors to launch of the spacecraft is 13 months.

  2. Pulsed power for electromagnetic launching

    SciTech Connect

    Cowan, M

    1980-12-01

    There are system advantages to producing power for electromagnetic propulsion by real-time generation rather than by a sequence of generation-storage-switching. The best type of generator for this purpose is the flux compression generator. Different types of flux compression generator which have been developed at Sandia National Laboratories are reviewed and their applications to electric launching are discussed. New experimental facilities for producing more powerful generators are described and cost comparisons are made.

  3. Pulsed power for electromagnetic launching

    NASA Astrophysics Data System (ADS)

    Cowan, M.

    1980-12-01

    There are system advantages to producing power for electromagnetic propulsion by real-time generation rather than by a sequence of generation-storage-switching. The best type of generator for this purpose is the flux compression generator which have been developed at Sandia National Laboratories are reviewed and their applications to electric launching are discussed. New experimental facilities for producing more powerful generators are described and cost comparisons are made.

  4. Pulsed power for electromagnetic launching

    NASA Astrophysics Data System (ADS)

    Cowan, M.

    1982-01-01

    There are system advantages to producing power for electromagnetic propulsion by real time generation rather than by a sequence of generation-storage-switching. The best type of generator for this purpose is the flux compression generator. Different types of flux compression generator which have been developed at Sandia National Laboratories are reviewed and their applications to electric launching are discussed. New experimental facilities for producing more powerful generators are described and cost comparisons are made.

  5. Atmosphere Explorer set for launch

    NASA Technical Reports Server (NTRS)

    1975-01-01

    The Atmosphere Explorer-D (Explorer-54) is described which will explore in detail an area of the earth's outer atmosphere where important energy transfer, atomic and molecular processes, and chemical reactions occur that are critical to the heat balance of the atmosphere. Data are presented on the mission facts, launch vehicle operations, AE-D/Delta flight events, spacecraft description, scientific instruments, tracking, and data acquisition.

  6. Hermes rescue strategies during launch

    NASA Astrophysics Data System (ADS)

    Cledassou, Rodelphe

    Safety and rescue strategies during the launch of Hermes space plane by Ariane 5 are discussed. Before solid booster separation, the pilots must be ejected by seats which are later recovered. After solid booster separation it becomes possible to extract the plane, which can perform a reentry leading to an available landing site or to sea recovery. When there is no useful landing site, the plane can be injected on a downgraded orbit.

  7. Trust-Building in Electronic Markets: Relative Importance and Interaction Effects of Trust-Building Mechanisms

    NASA Astrophysics Data System (ADS)

    Tams, Stefan

    We examine the relative and complementary effectiveness of trust-building strategies in online environments. While prior research has examined various antecedents to trust, we investigated two trust-building mechanisms more in depth: Web site trust and vendor reputation. We tried to understand the relative effectiveness of these two important mechanisms to provide online businesses with a clear recommendation of how to establish trust in an effective and efficient manner. Drawing from the literature on trust, we proposed vendor reputation to be more effective than Web site trust. Moreover, we examined a potential complementary effect of these mechanisms so as to provide online businesses with a deeper understanding of how to derive superior trust. We hypothesize a small such effect. The study proposes a laboratory experiment to test the model.

  8. Voice command weapons launching system

    NASA Astrophysics Data System (ADS)

    Brown, H. E.

    1984-09-01

    This abstract discloses a voice-controlled weapons launching system for use by a pilot of an aircraft against a plurality of simultaneously appearing (i.e., existing) targets, such as two or more aggressor aircraft (or tanks, or the like) attacking more aggressor aircraft. The system includes, in combination, a voice controlled input device linked to and controlling a computer; apparatus (such as a television camera, receiver, and display), linked to and actuated by the computer by a voice command from the pilot, for acquiring and displaying an image of the multi-target area; a laser, linked to and actuated by the computer by a voice command from the pilot to point to (and to lock on to) any one of the plurality of targets, with the laser emitting a beam toward the designated (i.e., selected) target; and a plurality of laser beam-rider missiles, with a different missile being launched toward and attacking each different designated target by riding the laser beam to that target. Unlike the prior art, the system allows the pilot to use his hands full-time to fly and to control the aircraft, while also permitting him to launch each different missile in rapid sequence by giving a two-word spoken command after he has visually selected each target of the plurality of targets, thereby making it possible for the pilot of a single defender aircraft to prevail against the plurality of simultaneously attacking aircraft, or tanks, or the like.

  9. Situational analysis of the health insurance market and related educational needs in the era of health care reform in Thailand.

    PubMed

    Sriratanaban, J; Supapong, S; Kamolratanakul, P; Tatiyakawee, K; Srithamrongsawat, S

    2000-12-01

    The purposes of this study were to explore the situation of health insurance in Thailand, to compare public and private perspectives and to identify related educational needs. Between March and April of 1998, the study employed in-depth interviews of 12 public and private major stakeholders of the health insurance systems, including policy makers, providers and insurers. Additional inputs were gathered in a brainstorming session with 41 participants from organizations with important roles in regulating, monitoring, paying, or providing health care services, as well as research and education. The findings indicated the health insurance market was expanding. But there was no national policy on health insurance. Insurance-related law was outdated. Public and private schemes overlapped, and were generally characterized by inadequate risk diversification, overutilization of services, lack of effective cost containment, inconsistent service quality, and poor understanding of health insurance principles. There were needs for more education and training in various aspects of health services management and health-insurance related functions. Consequently, continuing education and training related to health insurance services for policy makers, system administrators, managers, providers and insurers are strongly recommended during the health-care reform process. PMID:11253889

  10. Defensive marketing: how a strong incumbent can protect its position.

    PubMed

    Roberts, John H

    2005-11-01

    There has been a lot of research on marketing as an offensive tactic-how it can help companies successfully launch new products, enter new markets, or gain share with existing products in their current markets. But for nearly every new product launch, market entrant, or industry upstart grabbing market share, there is an incumbent that must defend its position. And there has been little research on how these defenders can use marketing to preemptively respond to new or anticipated threats. John H. Roberts outlines four basic types of defensive marketing strategies: positive, inertial, parity, and retarding. With the first two, you establish and communicate your points of superiority relative to the new entrant; with the second two, you establish and communicate strategic points of comparability with your rival. Before choosing a strategy, you need to assess the weapons you have available to protect your market position-your brand identity, the products and services that support that identity, and your means of communicating it. Then assess your customers' value to you and their vulnerability to being poached by rivals. The author explains how Australian telecommunications company Telstra, facing deregulation, used a combination of the four strategies (plus the author's customer response model) to fend off market newcomer Optus. Telstra was prepared, for instance, to reach deep into its pockets and engage in a price war. But the customer response model indicated that a parity strategy-in which Telstra would offer lower rates on some routes and at certain times of day, even though its prices, on average, were higher than its rival's-was more likely to prevent consumers from switching. Ultimately, Telstra was able to retain several points of market share it otherwise would have lost. The strategies described here, though specific to Telstra's situation, offer lessons for any company facing new and potentially damaging competition. PMID:16299967

  11. NASA's Space Launch System Progress Report

    NASA Technical Reports Server (NTRS)

    May, Todd A.; Singer, Joan A.; Cook, Jerry R.; Lyles, Garry M.; Beaman, David E.

    2012-01-01

    Exploration beyond Earth orbit will be an enduring legacy for future generations, as it provides a platform for science and exploration that will define new knowledge and redefine known boundaries. NASA s Space Launch System (SLS) Program, managed at the Marshall Space Flight Center, is responsible for designing and developing the first exploration-class rocket since the Apollo Program s Saturn V that sent Americans to the Moon in the 1960s and 1970s. The SLS offers a flexible design that may be configured for the Orion Multi-Purpose Crew Vehicle with associated life-support equipment and provisions for long journeys or may be outfitted with a payload fairing that will accommodate flagship science instruments and a variety of high-priority experiments. Building on legacy systems, facilities, and expertise, the SLS will have an initial lift capability of 70 tonnes (t) in 2017 and will be evolvable to 130 t after 2021. While commercial launch vehicle providers service the International Space Station market, this capability will surpass all vehicles, past and present, providing the means to do entirely new missions, such as human exploration of Mars. Building on the foundation laid by over 50 years of human and scientific space flight and on the lessons learned from the Apollo, Space Shuttle, and Constellation Programs the SLS team is delivering both technical trade studies and business case analyses to ensure that the SLS architecture will be safe, affordable, reliable, and sustainable. This panel will address the planning and progress being made by NASA s SLS Program.

  12. Effectivity of atmospheric electricity on launch availability

    NASA Technical Reports Server (NTRS)

    Ernst, John A.

    1991-01-01

    Thunderstorm days at KSC; percentage of frequency of thunderstorms (1957-1989); effect of lightning advisory on ground operations; Shuttle launch history; Shuttle launch weather history; applied meteorology unit; and goals/operational benefits. This presentation is represented by viewgraphs.

  13. Delta launch vehicle inertial guidance system (DIGS)

    NASA Technical Reports Server (NTRS)

    Duck, K. I.

    1973-01-01

    The Delta inertial guidance system, part of the Delta launch vehicle improvement effort, has been flown on three launches and was found to perform as expected for a variety of mission profiles and vehicle configurations.

  14. NASA's Space Launch System: Powering Forward

    NASA Video Gallery

    One year ago, NASA announced a new capability for America's space program: a heavy-lift rocket to launch humans farther into space than ever before. See how far the Space Launch System has come in ...

  15. Soyuz Rolled to Launch Pad in Kazakhstan

    NASA Video Gallery

    The Soyuz rocket is rolled out to the launch pad by train on Tuesday, March 26, 2013, at the Baikonur Cosmodrome in Kazakhstan. Launch of the Soyuz rocket is scheduled for March 29 and will send Ex...

  16. Expedition 30 Soyuz Moves to Launch Pad

    NASA Video Gallery

    On Dec. 19, the Soyuz TMA-03M spacecraft and its booster were moved to the launch pad at the Baikonur Cosmodrome in Kazakhstan for final preparations before launch to the International Space Statio...

  17. Delta XTE Launch Activities (Scrub #2)

    NASA Technical Reports Server (NTRS)

    1995-01-01

    This NASA Kennedy Space Center video presents Delta XTE (X-Ray Timing Explorer) launch activities on 12/11/95. The launch was rescheduled for next weekend due to out of limit upper level wind conditions.

  18. Nanosatellite Launch Adapter System (NLAS) Overview

    NASA Technical Reports Server (NTRS)

    Chartres, James

    2015-01-01

    An overview of the Nanosatellite Launch Adapter System (NLAS) is provided that contains information on NLAS' objectives and relevance, structural components and position in the launch vehicle stack, and details on its three main components.

  19. Market review - Market values summary/July market review/current market data

    SciTech Connect

    1995-08-01

    This article is the July 1995 uranium market review. Data for current uranium market is presented, and a summary of recent transactions is also given. During this reporting period, there was one concentrate deal, two transactions in the long-term natural uranium market and conversion market, and three spot market transactions in the enrichment market. Active uranium supply fell, as did demand, and prices in all sectors were relatively stable.

  20. The Virginia Space Flight Center model for an integrated federal/commercial launch range

    NASA Astrophysics Data System (ADS)

    Reed, Billie M.

    2000-01-01

    Until 1998, the federal government has been the predominant purchaser of space launches in the U.S. through the purchase of hardware and services. Historically, the government provided the necessary infrastructure for launches from the federal DoD and NASA launch ranges. In this historical model, the federal government had complete ownership, responsibility, liability, and expense for launch activities. In 1998, commercial space launches accounted for 60% of U.S. launches. This growth in commercial launches has increased the demand for launch range services. However, the expense, complexity of activities, and issues over certification of flight safety have deterred the establishment of purely commercial launch sites, with purely commercial being defined as without benefit of capabilities provided by the federal government. Provisions of the Commercial Space Launch Act have enabled DoD and NASA to support commercial launches from government launch ranges on a cost-reimbursable, non-interference basis. The government provides services including use of facilities, tracking and data services, and range and flight safety. In the 1990's, commercial space market projections indicated strong potential for large numbers of commercial satellites to be launched well into the first decade of the 21st century. In response to this significant opportunity for economic growth, several states established spaceports to provide the services necessary to meet these forecast commercial needs. In 1997, NASA agreed to the establishment of the Virginia Space Flight Center (VSFC), a commercial spaceport, at its Wallops Flight Facility. Under this arrangement, NASA agreed to allow the Virginia Commercial Space Flight Authority (VCSFA) to construct facilities on NASA property and agreed to provide launch range and other services in accordance with the Space Act and Commercial Space Launch Act in support of VSFC launch customers. A partnership relationship between NASA and VCSFA has emerged

  1. STS-91 Launch of Discovery from Launch Pad 39-A

    NASA Technical Reports Server (NTRS)

    1998-01-01

    The last mission of the Shuttle-Mir program begins as the Space Shuttle Discovery lifts off from Launch Pad 39A at 6:06:24 p.m. EDT June 2. A torrent of water is seen flowing onto the mobile launcher platform (MLP) from numerous large quench nozzles, or 'rainbirds,' mounted on its surface. This water, part of the Sound Suppression System, helps protect the orbiter and its payloads from damage by acoustical energy and rocket exhaust reflected from the flame trench and MLP during launch. On board Discovery are Mission Commander Charles J. Precourt; Pilot Dominic L. Gorie; and Mission Specialists Wendy B. Lawrence, Franklin R. Chang-Diaz, Janet Lynn Kavandi and Valery Victorovitch Ryumin. The nearly 10-day mission will feature the ninth and final Shuttle docking with the Russian space station Mir, the first Mir docking for the Space Shuttle orbiter Discovery, the first on-orbit test of the Alpha Magnetic Spectrometer (AMS), and the first flight of the new Space Shuttle super lightweight external tank. Astronaut Andrew S. W. Thomas will be returning to Earth as an STS-91 crew member after living more than four months aboard Mir.

  2. Artist's rendering of Launch and Translunar Injection

    NASA Technical Reports Server (NTRS)

    1969-01-01

    Launch and Translunar Injection: On launch day at Complex 39A, Kennedy Space Center, Fla., the astronauts enter the spacecraft. After launch and Saturn V first-stage burnout and jettison, the S-II second stage ignites. The crew checks spacecraft systems in Earth orbit before the S-IVB third stage ignites the second time to send Apollo 11 to the Moon.

  3. Lightning interaction with launch facilities

    NASA Astrophysics Data System (ADS)

    Mata, C. T.; Rakov, V. A.

    2009-12-01

    Lightning is a major threat to launch facilities. In 2008 and 2009 there have been a significant number of strikes within 5 nautical miles of Launch Complexes 39A and 39B at the Kennedy Space Center. On several occasions, the Shuttle Space Vehicle (SSV) was at the pad. Fortunately, no accidents or damage to the flight hardware occurred, but these events resulted in many launch delays, one launch scrub, and many hours of retesting. For complex structures, such as launch facilities, the design of the lightning protection system (LPS) cannot be done using the lightning protection standard guidelines. As a result, there are some “unprotected” or “exposed” areas. In order to quantify the lightning threat to these areas, a Monte Carlo statistical tool has been developed. This statistical tool uses two random number generators: a uniform distribution to generate origins of downward propagating leaders and a lognormal distribution to generate returns stroke peak currents. Downward leaders propagate vertically downward and their striking distances are defined by the polarity and peak current. Following the electrogeometrical concept, we assume that the leader attaches to the closest object within its striking distance. The statistical analysis is run for a large number of years using a long term ground flash density that corresponds to the geographical region where the structures being analyzed are located or will be installed. The output of the program is the probability of direct attachment to objects of interest with its corresponding peak current distribution. This tool was used in designing the lightning protection system of Launch Complex 39B at the Kennedy Space Center, FL, for NASA’s Constellation program. The tool allowed the designers to select the position of the towers and to design the catenary wire system to minimize the probability of direct strikes to the spacecraft and associated ground support equipment. This tool can be used to evaluate

  4. Shape Memory Alloy (SMA)-Based Launch Lock

    NASA Technical Reports Server (NTRS)

    Badescu, Mircea; Bao, Xiaoqi; Bar-Cohen, Yoseph

    2014-01-01

    Most NASA missions require the use of a launch lock for securing moving components during the launch or securing the payload before release. A launch lock is a device used to prevent unwanted motion and secure the controlled components. The current launch locks are based on pyrotechnic, electro mechanically or NiTi driven pin pullers and they are mostly one time use mechanisms that are usually bulky and involve a relatively high mass. Generally, the use of piezoelectric actuation provides high precession nanometer accuracy but it relies on friction to generate displacement. During launch, the generated vibrations can release the normal force between the actuator components allowing shaft's free motion which could result in damage to the actuated structures or instruments. This problem is common to other linear actuators that consist of a ball screw mechanism. The authors are exploring the development of a novel launch lock mechanism that is activated by a shape memory alloy (SMA) material ring, a rigid element and an SMA ring holding flexure. The proposed design and analytical model will be described and discussed in this paper.

  5. The Mars Climate Orbiter launches from Pad 17A, CCAS

    NASA Technical Reports Server (NTRS)

    1998-01-01

    A Boeing Delta II expendable launch vehicle lifts off with NASA's Mars Climate Orbiter at 1:45:51 p.m. EST, on Dec. 11, 1998, from Launch Complex 17A, Cape Canaveral Air Station. The launch was delayed one day when personnel detected a battery-related software problem in the spacecraft. The problem was corrected and the launch was rescheduled for the next day. The first of a pair of spacecraft to be launched in the Mars Surveyor '98 Project, the orbiter is heading for Mars where it will first provide support to its companion Mars Polar Lander spacecraft, which is planned for launch on Jan. 3, 1999. The orbiter's instruments will then monitor the Martian atmosphere and image the planet's surface on a daily basis for one Martian year (1.8 Earth years). It will observe the appearance and movement of atmospheric dust and water vapor, as well as characterize seasonal changes on the surface. The detailed images of the surface features will provide important clues to the planet's early climate history and give scientists more information about possible liquid water reserves beneath the surface.

  6. Shape Memory Alloy (SMA)-based launch lock

    NASA Astrophysics Data System (ADS)

    Badescu, Mircea; Bao, Xiaoqi; Bar-Cohen, Yoseph

    2014-04-01

    Most NASA missions require the use of a launch lock for securing moving components during the launch or securing the payload before release. A launch lock is a device used to prevent unwanted motion and secure the controlled components. The current launch locks are based on pyrotechnic, electro mechanically or NiTi driven pin pullers and they are mostly one time use mechanisms that are usually bulky and involve a relatively high mass. Generally, the use of piezoelectric actuation provides high precession nanometer accuracy but it relies on friction to generate displacement. During launch, the generated vibrations can release the normal force between the actuator components allowing free motion of the shaft, which could result in damage to the actuated structures or instruments. This problem is common to other linear actuators that consist of a ball screw mechanism. The authors are exploring the development of a novel launch lock mechanism that is activated by a shape memory alloy (SMA) material ring, a rigid element and an SMA ring holding flexure. The proposed design and analytical model will be described and discussed in this paper.

  7. Titan III-C Launch

    NASA Technical Reports Server (NTRS)

    1970-01-01

    This photograph shows a Titan III-C launch vehicle. Titan vehicles are designed to carry payloads equal to the size and weight of those on the space shuttle. The Titan IV Centaur can put 10,000 pound payloads into geosynchronous orbit, 22,300 miles above Earth. For more information about Titan and Centaur, please see chapters 4 and 8, respectively, in Roger Launius and Dennis Jenkins' book To Reach the High Frontier published by The University Press of Kentucky in 2002.

  8. Reusable launch vehicle development research

    NASA Technical Reports Server (NTRS)

    1995-01-01

    NASA has generated a program approach for a SSTO reusable launch vehicle technology (RLV) development which includes a follow-on to the Ballistic Missile Defense Organization's (BMDO) successful DC-X program, the DC-XA (Advanced). Also, a separate sub-scale flight demonstrator, designated the X-33, will be built and flight tested along with numerous ground based technologies programs. For this to be a successful effort, a balance between technical, schedule, and budgetary risks must be attained. The adoption of BMDO's 'fast track' management practices will be a key element in the eventual success of NASA's effort.

  9. Saturn I (SA-4) Launch

    NASA Technical Reports Server (NTRS)

    1963-01-01

    The Saturn I (SA-4) flight lifted off from Kennedy Space Center launch Complex 34, March 28, 1963. The fourth launch of Saturn launch vehicles developed at the Marshall Space Flight Center (MSFC), under the direction of Dr. Wernher von Braun, incorporated a Saturn I, Block I engine. The typical height of a Block I vehicle was approximately 163 feet and had only one live stage. It consisted of eight tanks, each 70 inches in diameter, clustered around a central tank, 105 inches in diameter. Four of the external tanks were fuel tanks for the RP-1 (kerosene) fuel. The other four, spaced alternately with the fuel tanks, were liquid oxygen tanks as was the large center tank. All fuel tanks and liquid oxygen tanks drained at the same rates respectively. The thrust for the stage came from eight H-1 engines, each producing a thrust of 165,000 pounds, for a total thrust of over 1,300,000 pounds. The engines were arranged in a double pattern. Four engines, located inboard, were fixed in a square pattern around the stage axis and canted outward slightly, while the remaining four engines were located outboard in a larger square pattern offset 40 degrees from the inner pattern. Unlike the inner engines, each outer engine was gimbaled. That is, each could be swung through an arc. They were gimbaled as a means of steering the rocket, by letting the instrumentation of the rocket correct any deviations of its powered trajectory. The block I required engine gimabling as the only method of guiding and stabilizing the rocket through the lower atmosphere. The upper stages of the Block I rocket reflected the three-stage configuration of the Saturn I vehicle. Like SA-3, the SA-4 flight's upper stage ejected 113,560 liters (30,000 gallons) of ballast water in the upper atmosphere for 'Project Highwater' physics experiment. Release of this vast quantity of water in a near-space environment marked the second purely scientific large-scale experiment. The SA-4 was the last Block I rocket

  10. Saturn I (SA-4) Launch

    NASA Technical Reports Server (NTRS)

    1963-01-01

    The Saturn I (SA-4) flight lifted off from Kennedy Space Center launch Complex 34, March 28, 1963. The fourth launch of Saturn launch vehicles, developed at the Marshall Space Flight Center (MSFC) under the direction of Dr. Wernher von Braun, incorporated a Saturn I, Block I engine. The typical height of a Block I vehicle was approximately 163 feet and had only one live stage. It consisted of eight tanks, each 70 inches in diameter, clustered around a central tank, 105 inches in diameter. Four of the external tanks were fuel tanks for the RP-1 (kerosene) fuel. The other four, spaced alternately with the fuel tanks, were liquid oxygen tanks as was the large center tank. All fuel tanks and liquid oxygen tanks drained at the same rates respectively. The thrust for the stage came from eight H-1 engines, each producing a thrust of 165,000 pounds, for a total thrust of over 1,300,000 pounds. The engines were arranged in a double pattern. Four engines, located inboard, were fixed in a square pattern around the stage axis and canted outward slightly, while the remaining four engines were located outboard in a larger square pattern offset 40 degrees from the inner pattern. Unlike the inner engines, each outer engine was gimbaled. That is, each could be swung through an arc. They were gimbaled as a means of steering the rocket, by letting the instrumentation of the rocket correct any deviations of its powered trajectory. The block I required engine gimabling as the only method of guiding and stabilizing the rocket through the lower atmosphere. The upper stages of the Block I rocket reflected the three-stage configuration of the Saturn I vehicle. Like SA-3, the SA-4 flight's upper stage ejected 113,560 liters (30,000 gallons) of ballast water in the upper atmosphere for 'Project Highwater' physics experiment. Release of this vast quantity of water in a near-space environment marked the second purely scientific large-scale experiment. The SA-4 was the last Block I rocket

  11. EB welding of launch vehicles

    NASA Astrophysics Data System (ADS)

    Szabo, Attila

    While large structural components can be electron beam (EB) welded, equipment and operating costs increase with the requisite vacuum chamber's size. Attention is presently given to cost-effective ways of EB welding launch-vehicle assemblies without compromise of weld quality in such alloys as 2219, 2090, Weldalite, and HP9-4-30/20. Weld strengths at both room and cryogenic temperatures that were 50 percent higher than those obtainable for such materials with arc welding have been demonstrated. Fracture toughnesses were also 40-50 percent higher than arc-welded values. Attention is given to EB joint fit-up allowables for 2219-T87 Al alloy.

  12. APOLLO 12: A heartstopping launch

    NASA Technical Reports Server (NTRS)

    1974-01-01

    APOLLO 12: A heartstopping launch as the rocket is struck by lightning. From the film documentary 'APOLLO 12: 'Pinpoint for Science'', part of a documentary series on the APOLLO missions made in the early '70's and narrated by Burgess Meredith. APOLLO 12: Second manned lunar landing and return with Charles 'Pete' Conrad, Jr., Richard F. Gordon, and Alan F. Bean. Landed in the Ocean of Storms on November 19, 1969; deployed television camera and ALSEP experiments; two EVA's performed; collected core samples and lunar materials; photographed and retrieved parts from surveyor 3 spacecraft. Mission duration 244hrs 36min 24sec

  13. 14 CFR 417.25 - Post launch report.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Post launch report. 417.25 Section 417.25... TRANSPORTATION LICENSING LAUNCH SAFETY General and License Terms and Conditions § 417.25 Post launch report. (a) For a launch operator launching from a Federal launch range, a launch operator must file a post...

  14. 14 CFR 417.25 - Post launch report.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Post launch report. 417.25 Section 417.25... TRANSPORTATION LICENSING LAUNCH SAFETY General and License Terms and Conditions § 417.25 Post launch report. (a) For a launch operator launching from a Federal launch range, a launch operator must file a post...

  15. 14 CFR 417.25 - Post launch report.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Post launch report. 417.25 Section 417.25... TRANSPORTATION LICENSING LAUNCH SAFETY General and License Terms and Conditions § 417.25 Post launch report. (a) For a launch operator launching from a Federal launch range, a launch operator must file a post...

  16. 14 CFR 417.25 - Post launch report.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Post launch report. 417.25 Section 417.25... TRANSPORTATION LICENSING LAUNCH SAFETY General and License Terms and Conditions § 417.25 Post launch report. (a) For a launch operator launching from a Federal launch range, a launch operator must file a post...

  17. Immunity-Related Protein Expression and Pathological Lung Damage in Mice Poststimulation with Ambient Particulate Matter from Live Bird Markets.

    PubMed

    Meng, Kai; Wu, Bo; Gao, Jing; Cai, Yumei; Yao, Meiling; Wei, Liangmeng; Chai, Tongjie

    2016-01-01

    The objective of this study was to obtain insight into the adverse health effects of airborne particulate matter (PM) collected from live bird markets and to determine whether biological material in PM accounts for immune-related inflammatory response. Mice were exposed to a single or repeated dose of PM, after which the expression of toll-like receptors (TLRs), cytokines, and chemokines in the lungs of infected mice were examined by enzyme-linked immunosorbent assay and histopathological analysis. Results after single and repeated PM stimulation with [Formula: see text] indicated that TLR2 and TLR4 played a dominant role in the inflammatory responses of the lung. Further analysis demonstrated that the expression levels of IL-1β, TNF-α, IFN-γ, IL-8, IP-10, and MCP-1 increased significantly, which could eventually contribute to lung injury. Moreover, biological components in PM were critical in mediating immune-related inflammatory responses and should therefore not be overlooked. PMID:27446082

  18. Immunity-Related Protein Expression and Pathological Lung Damage in Mice Poststimulation with Ambient Particulate Matter from Live Bird Markets

    PubMed Central

    Meng, Kai; Wu, Bo; Gao, Jing; Cai, Yumei; Yao, Meiling; Wei, Liangmeng; Chai, Tongjie

    2016-01-01

    The objective of this study was to obtain insight into the adverse health effects of airborne particulate matter (PM) collected from live bird markets and to determine whether biological material in PM accounts for immune-related inflammatory response. Mice were exposed to a single or repeated dose of PM, after which the expression of toll-like receptors (TLRs), cytokines, and chemokines in the lungs of infected mice were examined by enzyme-linked immunosorbent assay and histopathological analysis. Results after single and repeated PM stimulation with PM2.5+,PM2.5−,PM10+, and PM10− indicated that TLR2 and TLR4 played a dominant role in the inflammatory responses of the lung. Further analysis demonstrated that the expression levels of IL-1β, TNF-α, IFN-γ, IL-8, IP-10, and MCP-1 increased significantly, which could eventually contribute to lung injury. Moreover, biological components in PM were critical in mediating immune-related inflammatory responses and should therefore not be overlooked. PMID:27446082

  19. The Wallops Flight Facility Model for an Integrated Federal/Commercial Launch Range

    NASA Technical Reports Server (NTRS)

    Underwood, Bruce E.

    1999-01-01

    Historically, the federal government has been the predominant purchaser of space launches in the United States. The government met its needs through purchase of hardware and services. It also provided the infrastructure necessary to conduct launch operations through federal launch ranges, both military and NASA. Under this model, the government had the complete ownership, responsibility, liability, and expense for launch activities. As the commercial space sector grew, there emerged a corresponding growth in demand for launch range services. However, the expense and complexity of activities has thus far deterred a rapid rise in the establishment of purely commercial launch sites. In this context, purely commercial is defined as "without benefit of capabilities provided by the federal government." Consistent with the Commercial Space Launch Act, in recent years NASA and the Air Force have supported commercial launches from government launch ranges on a cost-reimbursable, non-interference basis. In this mode the commercial launch service providers contract with the government to provide services including use of facilities, tracking and data services, and range safety. As the commercial market projections began to show significant opportunities for economic development, several states established spaceports to provide the services necessary to meet these projected commercial needs. In 1997, NASA agreed to the establishment of the Virginia Space Flight Center (VSFC) at the Wallops Flight Facility. Under this arrangement, NASA agreed to allow Virginia Commercial Space Flight Authority (VCSFA) to construct facilities on NASA property and agreed to provide services in accordance with the Space Act of 1958 and the Commercial Space Launch Act of 1984 (as amended) to support VSFC launch customers. The relationship between NASA and VCSFA, however, has evolved beyond a customer supplier relationship. A partnership relationship has emerged which pairs the strengths of the

  20. KSC Launch Pad Flame Trench Environment Assessment

    NASA Technical Reports Server (NTRS)

    Calle, Luz Marina; Hintze, Paul E.; Parlier, Christopher R.; Curran, Jerome P.; Kolody, Mark R.; Sampson, Jeffrey W.

    2010-01-01

    This report summarizes conditions in the Launch Complex 39 (LC-39) flame trenches during a Space Shuttle Launch, as they have been measured to date. Instrumentation of the flame trench has been carried out by NASA and United Space Alliance for four Shuttle launches. Measurements in the flame trench are planned to continue for the duration of the Shuttle Program. The assessment of the launch environment is intended to provide guidance in selecting appropriate test methods for refractory materials used in the flame trench and to provide data used to improve models of the launch environment in the flame trench.

  1. Near-term Horizontal Launch for Flexible Operations: Results of the DARPA/NASA Horizontal Launch Study

    NASA Technical Reports Server (NTRS)

    Bartolotta, Paul A.; Wilhite, Alan W.; Schaffer, Mark G.; Huebner, Lawrence D.; Voland, Randall T.; Voracek, David F.

    2012-01-01

    Horizontal launch has been investigated for 60 years by over 130 different studies. During this time only one concept, Pegasus, has ever been in operation. The attractiveness of horizontal launch is the capability to provide a "mobile launch pad" that can use existing aircraft runways, cruise above weather, loiter for mission instructions, and provide precise placement for orbital intercept, rendezvous, or reconnaissance. A jointly sponsored study by DARPA and NASA, completed in 2011, explored the trade space of horizontal launch system concepts which included an exhaustive literature review of the past 70 years. The Horizontal Launch Study identified potential near- and mid-term concepts capable of delivering 15,000 lb payloads to a 28.5 due East inclination, 100 nautical-mile low-Earth orbit. Results are presented for a range of near-term system concepts selected for their availability and relatively low design, development, test, and evaluation (DDT&E) costs. This study identified a viable low-cost development path forward to make a robust and resilient horizontal launch capability a reality.

  2. 14 CFR 1214.117 - Launch and orbit parameters for a standard launch.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 5 2012-01-01 2012-01-01 false Launch and orbit parameters for a standard..., Reimbursable Customers § 1214.117 Launch and orbit parameters for a standard launch. To qualify for the...) Launch from Kennedy Space Center (KSC) into the customer's choice of two standard mission orbits: 160...

  3. 14 CFR 1214.117 - Launch and orbit parameters for a standard launch.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 5 2013-01-01 2013-01-01 false Launch and orbit parameters for a standard..., Reimbursable Customers § 1214.117 Launch and orbit parameters for a standard launch. To qualify for the...) Launch from Kennedy Space Center (KSC) into the customer's choice of two standard mission orbits: 160...

  4. 14 CFR 1214.117 - Launch and orbit parameters for a standard launch.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 5 2011-01-01 2010-01-01 true Launch and orbit parameters for a standard..., Reimbursable Customers § 1214.117 Launch and orbit parameters for a standard launch. To qualify for the...) Launch from Kennedy Space Center (KSC) into the customer's choice of two standard mission orbits: 160...

  5. 14 CFR 1214.117 - Launch and orbit parameters for a standard launch.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 5 2010-01-01 2010-01-01 false Launch and orbit parameters for a standard..., Reimbursable Customers § 1214.117 Launch and orbit parameters for a standard launch. To qualify for the...) Launch from Kennedy Space Center (KSC) into the customer's choice of two standard mission orbits: 160...

  6. Railgun launch of small bodies

    SciTech Connect

    Drobyshevski, E.M.; Zhukov, B.G.; Sakharov, V.A.

    1995-01-01

    The small body launching using gas or plasma faces the fundamental problem caused by excess energy loss due to great wall surface/volume of the barrel ratio. That is why the efficiency of the plasma armature (PA) railgun acceleration is maximum for 8--10 mm-size bodies and drops as their size decreases. For the nuclear fusion applications, where {number_sign}1--2 mm-size pellets at 5--10 km/s velocity are desirable, one is forced to search for compromise between the body size (3--4 mm) and its velocity (3 km/s). Under these conditions, EM launchers did not demonstrate an advantage over the light-gas guns. When elaborating the {number_sign}1 mm railgun, the authors made use of the ideology of the body launching at constant acceleration close to the body strength or the electrode skin-layer explosion limits. That shortened the barrel length sufficiently. The system becomes highly compact thus permitting rapid test of new operation modes and different modifications of the design including the magnetic field augmentation. As a result of these refinements, the difficulties caused by the catastrophic supply of mass ablated from the electrodes were overcome and regimes of {number_sign}1 mm body non-sabot speed-up to 4.5 km/s were found. Potentialities of the small system created are far from being exhausted.

  7. Mortar-launched surveillance system

    NASA Astrophysics Data System (ADS)

    Lewis, Carl E.; Cooper, Steve; Carlton, Lindley A.

    2001-09-01

    Accurate Automation Corporation has completed the conceptual design of a mortar launched air vehicle system to perform close range or over-the-horizon surveillance missions. Law enforcement and military units require an organic capability to obtain real time intelligence information of time critical targets. Our design will permit law enforcement to detect, classify, locate and track these time critical targets. The surveillance system is a simple, unmanned fixed-winged aircraft deployed via a conventional mortar tube. The aircraft's flight surfaces are deployed following mortar launch to permit maximum range and time over target. The aircraft and sensor system are field retrievable. The aircraft can be configured with an engine to permit extended time over target or range. The aircraft has an integrated surveillance sensor system; a programmable CMOS sensor array. The integrated RF transmitter is capable of down- linking real-time video over line-of-sight distances exceeding 10 kilometers. The major benefit of the modular design is the ability to provide surveillance or tracking quickly at a low cost. Vehicle operational radius and sensor field coverage as well as design trade results of vehicle range and endurance performance and payload capacity at operational range are presented for various mortar configurations.

  8. STS-109 Shuttle Mission Launch

    NASA Technical Reports Server (NTRS)

    2002-01-01

    Carrying the STS-109 crew of seven, the Space Shuttle Orbiter Columbia blasted from its launch pad as it began its 27th flight and 108th flight overall in NASA's Space Shuttle Program. Launched March 1, 2002, the goal of the mission was the maintenance and upgrade of the Hubble Space Telescope (HST) which was developed, designed, and constructed by the Marshall Space Flight Center. Captured and secured on a work stand in Columbia's payload bay using Columbia's robotic arm, the HST received the following upgrades: replacement of the solar array panels; replacement of the power control unit (PCU); replacement of the Faint Object Camera (FOC) with a new advanced camera for Surveys (ACS); and installation of the experimental cooling system for the Hubble's Near-Infrared Camera and Multi-object Spectrometer (NICMOS), which had been dormant since January 1999 when it original coolant ran out. Four of the crewmembers performed 5 space walks in the 10 days, 22 hours, and 11 minutes of the the STS-109 mission.

  9. Magnetic Launch Assist Vehicle-Artist's Concept

    NASA Technical Reports Server (NTRS)

    1999-01-01

    This artist's concept depicts a Magnetic Launch Assist vehicle clearing the track and shifting to rocket engines for launch into orbit. The system, formerly referred as the Magnetic Levitation (MagLev) system, is a launch system developed and tested by Engineers at the Marshall Space Flight Center (MSFC) that could levitate and accelerate a launch vehicle along a track at high speeds before it leaves the ground. Using an off-board electric energy source and magnetic fields, a Magnetic Launch Assist system would drive a spacecraft along a horizontal track until it reaches desired speeds. The system is similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway. A full-scale, operational track would be about 1.5-miles long, capable of accelerating a vehicle to 600 mph in 9.5 seconds, and the vehicle would then shift to rocket engines for launch into orbit. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  10. Remote video assessment for missile launch facilities

    SciTech Connect

    Wagner, G.G.; Stewart, W.A.

    1995-07-01

    The widely dispersed, unmanned launch facilities (LFs) for land-based ICBMs (intercontinental ballistic missiles) currently do not have visual assessment capability for existing intrusion alarms. The security response force currently must assess each alarm on-site. Remote assessment will enhance manpower, safety, and security efforts. Sandia National Laboratories was tasked by the USAF Electronic Systems Center to research, recommend, and demonstrate a cost-effective remote video assessment capability at missile LFs. The project`s charter was to provide: system concepts; market survey analysis; technology search recommendations; and operational hardware demonstrations for remote video assessment from a missile LF to a remote security center via a cost-effective transmission medium and without using visible, on-site lighting. The technical challenges of this project were to: analyze various video transmission media and emphasize using the existing missile system copper line which can be as long as 30 miles; accentuate and extremely low-cost system because of the many sites requiring system installation; integrate the video assessment system with the current LF alarm system; and provide video assessment at the remote sites with non-visible lighting.

  11. The competitive effects of launch vehicle technology

    NASA Astrophysics Data System (ADS)

    Dupnick, Edwin; Hopkins, Charles

    1996-03-01

    We performed a study to evaluate the economics of advanced technology incorporation in selected expendable launch vehicles, the Ariane, the Atlas, and the Delta. The competitive merits of these launch vehicles were assessed against a reference mission—the delivery of a telecommunications satellite to geostationary orbit. We provide estimates of the cost of the launch services for the competing missions; the GE PRICE models were used to provide cost estimates for the three launch vehicles. Using publicly available data, a comparison of cost with price for the launch was utilized to examine the issue of potential profit earned and/or subsidization of the cost. Other factors such as the location of the launch site, transportation costs, exchange rates, the availability of financing at competitive rates and communication problems was also considered in evaluating the competitive launch vehicle systems.

  12. The competitive effects of launch vehicle technology

    SciTech Connect

    Dupnick, E.; Hopkins, C.

    1996-03-01

    We performed a study to evaluate the economics of advanced technology incorporation in selected expendable launch vehicles, the Ariane, the Atlas, and the Delta. The competitive merits of these launch vehicles were assessed against a reference mission{emdash}the delivery of a telecommunications satellite to geostationary orbit. We provide estimates of the cost of the launch services for the competing missions; the GE PRICE models were used to provide cost estimates for the three launch vehicles. Using publicly available data, a comparison of cost with price for the launch was utilized to examine the issue of potential profit earned and/or subsidization of the cost. Other factors such as the location of the launch site, transportation costs, exchange rates, the availability of financing at competitive rates and communication problems was also considered in evaluating the competitive launch vehicle systems. {copyright} {ital 1996 American Institute of Physics.}

  13. Three Dimensional Lightning Launch Commit Criteria Visualization Tool

    NASA Technical Reports Server (NTRS)

    Bauman, William H., III

    2014-01-01

    Lightning occurrence too close to a NASA LSP or future SLS program launch vehicle in flight would have disastrous results. The sensitive electronics on the vehicle could be damaged to the point of causing an anomalous flight path and ultimate destruction of the vehicle and payload.According to 45th Weather Squadron (45 WS) Lightning Launch Commit Criteria (LLCC), a vehicle cannot launch if lightning is within 10 NM of its pre-determined flight path. The 45 WS Launch Weather Officers (LWOs) evaluate this LLCC for their launch customers to ensure the safety of the vehicle in flight. Currently, the LWOs conduct a subjective analysis of the distance between lightning and the flight path using data from different display systems. A 3-D display in which the lightning data and flight path are together would greatly reduce the ambiguity in evaluating this LLCC. It would give the LWOs and launch directors more confidence in whether a GO or NO GO for launch should be issued. When lightning appears close to the path, the LWOs likely err on the side of conservatism and deem the lightning to be within 10 NM. This would cause a costly delay or scrub. If the LWOs can determine with a strong level of certainty that the lightning is beyond 10 NM, launch availability would increase without compromising safety of the vehicle, payload or, in the future, astronauts.The AMU was tasked to conduct a market research of commercial, government, and open source software that might be able to ingest and display the 3-D lightning data from the KSC Lightning Mapping Array (LMA), the 45th Space Wing Weather Surveillance Radar (WSR), the National Weather Service in Melbourne Weather Surveillance Radar 1988 Doppler (WSR-88D), and the vehicle flight path data so that all can be visualized together. To accomplish this, the AMU conducted Internet searches for potential software candidates and interviewed software developers.None of the available off-the-shelf software had a 3-D capability that could

  14. Atlas V Launch Incorporated NASA Glenn Thermal Barrier

    NASA Technical Reports Server (NTRS)

    Dunlap, Patrick H., Jr.; Steinetz, Bruce M.

    2004-01-01

    In the Spring of 2002, Aerojet experienced a major failure during a qualification test of the solid rocket motor that they were developing for the Atlas V Enhanced Expendable Launch Vehicle. In that test, hot combustion gas reached the O-rings in the nozzle-to-case joint and caused a structural failure that resulted in loss of the nozzle and aft dome sections of the motor. To improve the design of this joint, Aerojet decided to incorporate three braided carbon-fiber thermal barriers developed at the NASA Glenn Research Center. The thermal barriers were used to block the searing-hot 5500 F pressurized gases from reaching the temperature-sensitive O-rings that seal the joint. Glenn originally developed the thermal barriers for the nozzle joints of the space shuttle solid rocket motors, and Aerojet decided to use them on the basis of the results of several successful ground tests of the thermal barriers in the shuttle rockets. Aerojet undertook an aggressive schedule to redesign the rocket nozzle-to-case joint with the thermal barriers and to qualify it in time for a launch planned for the middle of 2003. They performed two successful qualification tests (Oct. and Dec. 2002) in which the Glenn thermal barriers effectively protected the O-rings. These qualification tests saved hundreds of thousands of dollars in development costs and put the Lockheed-Martin/Aerojet team back on schedule. On July 17, 2003, the first flight of an Atlas V boosted with solid rocket motors successfully launched a commercial satellite into orbit from Cape Canaveral Air Force Station. Aero-jet's two 67-ft solid rocket boosters performed flawlessly, with each providing thrust in excess of 250,000 lbf. Both motors incorporated three Glenn-developed thermal barriers in their nozzle-to-case joints. The Cablevision satellite launched on this mission will be used to provide direct-to-home satellite television programming for the U.S. market starting in late 2003. The Atlas V is a product of the

  15. Marketing factors affecting physician choice as related to consumers' extent of use and predisposition toward use of physician services.

    PubMed

    Wotruba, T R; Haas, R W; Oulhen, H

    1985-01-01

    This study explores the relationship between predisposition toward, and the extent of actual use of, physician services. Factors in a physician's marketing offering of most importance to consumers in various predisposition and use categories are identified along with their demographic differences, and marketing strategy implications are noted. PMID:10275160

  16. Teachers' Work in Curricular Markets: Conditions of Design and Relations between the International Baccalaureate Diploma and the Local Curriculum

    ERIC Educational Resources Information Center

    Doherty, Catherine; Shield, Paul

    2012-01-01

    School-level strategy enabled by neoliberal choice policies can produce internal curricular markets whereby branded curricula such as the International Baccalaureate are offered alongside the local government curriculum in the same school. This project investigated how such curricular markets operating in Australian schools impacted on teachers'…

  17. The European launch vehicle Ariane: Its commercial status - Its evolution

    NASA Astrophysics Data System (ADS)

    Glavany, M.

    The status of the Ariane program is summarized. The shareholders and participating countries in the French private firm Arianespace are listed and the Ariane rocket is very briefly described, depicting the planned models and showing their anticipated performances and the types of fairing available to them, and comparing the available volume in Ariane 3 and 4 and foreign competitors. The current status of the Ariane program, including the development phase, promotional series, and commercial phase are briefly presented. The Guiana space center and second launch pad are described and the advantages of Arianespace's launch service and the vehicle are listed, along with Ariane's advantages over the Space Shuttle. The expected market share for Ariane is shown in comparison with that of the Shuttle and other nations.

  18. Tracks for Eastern/Western European Future Launch Vehicles Cooperation

    NASA Astrophysics Data System (ADS)

    Eymar, Patrick; Bertschi, Markus

    2002-01-01

    exclusively upon Western European elements indigenously produced. Yet some private initiatives took place successfully in the second half of the nineties (Eurockot and Starsem) bringing together companies from Western and Eastern Europe. Evolution of these JV's are already envisioned. But these ventures relied mostly on already existing vehicles. broadening the bases in order to enlarge the reachable world market appears attractive, even if structural difficulties are complicating the process. had recently started to analyze, with KSRC counterparts how mixing Russian and Western European based elements would provide potential competitive edges. and RKA in the frame of the new ESA's Future Launch Preparatory Programme (FLPP). main technical which have been considered as the most promising (reusable LOx/Hydrocarbon engine, experimental reentry vehicles or demonstrators and reusable launch vehicle first stage or booster. international approach. 1 patrick.eymar@lanceurs.aeromatra.com 2

  19. Provider communication and role modeling related to patients' perceptions and use of a federally qualified health center-based farmers' market.

    PubMed

    Friedman, Daniela B; Freedman, Darcy A; Choi, Seul Ki; Anadu, Edith C; Brandt, Heather M; Carvalho, Natalia; Hurley, Thomas G; Young, Vicki M; Hébert, James R

    2014-03-01

    Farmers' markets have the potential to improve the health of underserved communities, shape people's perceptions, values, and behaviors about healthy eating, and serve as a social space for both community members and vendors. This study explored the influence of health care provider communication and role modeling for diabetic patients within the context of a farmers' market located at a federally qualified health center. Although provider communication about diet decreased over time, communication strategies included: providing patients with "prescriptions" and vouchers for market purchases; educating patients about diet; and modeling healthy purchases. Data from patient interviews and provider surveys revealed that patients enjoyed social aspects of the market including interactions with their health care provider, and providers distributed prescriptions and vouchers to patients, shopped at the market, and believed that the market had potential to improve the health of staff and patients of the federally qualified health center. Provider modeling of healthy behaviors may influence patients' food-related perceptions and dietary behaviors. PMID:23986503

  20. Saturn I (SA-3) Launch

    NASA Technical Reports Server (NTRS)

    1962-01-01

    The Saturn I (SA-3) flight lifted off from Kennedy Space Center launch Complex 34, November 16, 1962. The third launch of Saturn launch vehicles, developed at the Marshall Space Flight Center (MSFC) under the direction of Dr. Wernher von Braun, incorporated a Saturn I, Block I engine. The typical height of a Block I vehicle was approximately 163 feet. and had only one live stage. It consisted of eight tanks, each 70 inches in diameter, clustered around a central tank, 105 inches in diameter. Four of the external tanks were fuel tanks for the RP-1 (kerosene) fuel. The other four, spaced alternately with the fuel tanks, were liquid oxygen tanks as was the large center tank. All fuel tanks and liquid oxygen tanks drained at the same rates respectively. The thrust for the stage came from eight H-1 engines, each producing a thrust of 165,000 pounds, for a total thrust of over 1,300,000 pounds. The engines were arranged in a double pattern. Four engines, located inboard, were fixed in a square pattern around the stage axis and canted outward slightly, while the remaining four engines were located outboard in a larger square pattern offset 40 degrees from the inner pattern. Unlike the inner engines, each outer engine was gimbaled. That is, each could be swung through an arc. They were gimbaled as a means of steering the rocket, by letting the instrumentation of the rocket correct any deviations of its powered trajectory. The block I required engine gimabling as the only method of guiding and stabilizing the rocket through the lower atmosphere. The upper stages of the Block I rocket reflected the three-stage configuration of the Saturn I vehicle. During the SA-3 flight, the upper stage ejected 113,560 liters (30,000 gallons) of ballast water in the upper atmosphere for 'Project Highwater' physics experiment. The water was released at an altitude of 65 miles, where within only 5 seconds, it expanded into a massive ice cloud 4.6 miles in diameter. Release of this vast

  1. Missile launch detection electric field perturbation experiment. Final report

    SciTech Connect

    Kane, R.J.; Rynne, T.M.

    1993-04-28

    The Lawrence Livermore National Laboratory and SARA Inc. participated in the ATMD missile launch activities that occurred at WSMR during January 1993. LLNL and SARA deployed sensors for monitoring of basic phenomena. An attempt was made to measure perturbations of the earth geo-potential during the launch of a Lance missile. The occurrence of the perturbation is expected from the conducting body of the missile and the exhaust plume. A set of voltage-probe antennas were used to monitor the local electric field perturbation from the launch at ranges of approximately 1 km. Examination of the data acquired during the launch period failed to show identifiable correlation of the field variations with the launch event. Three reasons are ascribed to this lack of event data: (1) The electric field potential variations have a limited spatial correlation length - the fields measured in one region have little correlation to measurements made at distances of a kilometer away. The potential variations are related to localized atmospheric disturbances and are generally unpredictable. A value for the spatial correlation length is also not known. (2) The conductivity of the plume and missile body are not adequate to produce a field perturbation of adequate magnitude. Phenomena related to the exhaust plume and missile may exist and be outside of the collection range of the equipment employed for these measurements. (3) The presence of 60 Hz power line noise was of sufficient magnitude to irreversibly contaminate measurements.

  2. Evolving Markets for Commercial, Civil, and Military Services

    NASA Astrophysics Data System (ADS)

    Kaplan, Marshall H.

    2003-01-01

    Recent commercial failures in the LEO market, declining budgets for research, and other political factors have made it difficult for entrepreneurs and financial institutions to realize returns from investments in new space transportation systems and satellites. This paper explores the major factors impacting future markets that make use of our space infrastructure. At the top of the list is the high cost of space access. This has been extremely expensive, and will continue to be expensive as long as space access remains low on the nation's priority list. While launch prices have generally been reduced over the past several years, they remain well above the elastic range of supply and demand. Our best estimate is that it will take an order of magnitude reduction to significantly expand the market. Projections about market segments that will represent future winners in space and launch demand forecasts are presented. Future markets, outside of traditional strongholds, are explored, including a long-term view of new commercial space activities, conventional and ambitious future/futuristic activities, and related business aspects.

  3. Launch operations of the SSME

    NASA Astrophysics Data System (ADS)

    Klatt, F. P.

    1983-10-01

    The mission profile, performance over the first eight flights, and inspection and repair procedures for the Shuttle main engines (SSME) are outlined. The Orbiter has three SSMEs, each delivering 470,000 lb thrust at rated level and 512,000 lb thrust at full power level. The engines each have a design lifetime of 55 launches and 27,000 sec operating life. After eight STS flights the SSME maintenance requirements and part replacements have generally followed those experiences during ground tests, i.e., routine checkout of some items are performed every flight, some after a few flights, and replacements are made as needed or scheduled. Hot-fire tests are performed only if a generic defect has been recognized and corrective action taken. Attention is also given to engine sensors to verify functioning status. Details of the inspection procedures, unscheduled maintenance, and inspection tools and instruments are provided.

  4. TDRS is launched from CCAFS

    NASA Technical Reports Server (NTRS)

    2000-01-01

    Leaving billowing clouds of steam and smoke behind, NASA's Tracking and Data Relay Satellite (TDRS-H) shoots into the blue sky aboard an Atlas IIA/Centaur rocket from Pad 36A, Cape Canaveral Air Force Station. Liftoff occurred at 8:56 a.m. EDT. One of three satellites (labeled H, I and J) being built by the Hughes Space and Communications Company, the latest TDRS uses an innovative springback antenna design. A pair of 15-foot-diameter, flexible mesh antenna reflectors fold up for launch, then spring back into their original cupped circular shape on orbit. The new satellites will augment the TDRS system's existing S- and Ku-band frequencies by adding Ka-band capability. TDRS will serve as the sole means of continuous, high-data-rate communication with the space shuttle, with the International Space Station upon its completion, and with dozens of unmanned scientific satellites in low earth orbit.

  5. TDRS is launched from CCAFS

    NASA Technical Reports Server (NTRS)

    2000-01-01

    Looking like a Roman candle, NASA's Tracking and Data Relay Satellite (TDRS-H) shoots into the blue sky aboard an Atlas IIA/Centaur rocket from Pad 36A, Cape Canaveral Air Force Station. Liftoff occurred at 8:56 a.m. EDT. One of three satellites (labeled H, I and J) being built by the Hughes Space and Communications Company, the latest TDRS uses an innovative springback antenna design. A pair of 15-foot-diameter, flexible mesh antenna reflectors fold up for launch, then spring back into their original cupped circular shape on orbit. The new satellites will augment the TDRS system's existing S- and Ku-band frequencies by adding Ka-band capability. TDRS will serve as the sole means of continuous, high-data-rate communication with the space shuttle, with the International Space Station upon its completion, and with dozens of unmanned scientific satellites in low earth orbit.

  6. Redstone Missile on Launch Pad

    NASA Technical Reports Server (NTRS)

    1958-01-01

    Redstone missile No. 1002 on the launch pad at Cape Canaveral, Florida, on May 16, 1958. The Redstone ballistic missile was a high-accuracy, liquid-propelled, surface-to-surface missile developed by the Army Ballistic Missile Agency, Redstone Arsenal, in Huntsville, Alabama, under the direction of Dr. von Braun. The Redstone engine was a modified and improved version of the Air Force's Navaho cruise missile engine of the late forties. The A-series, as this would be known, utilized a cylindrical combustion chamber as compared with the bulky, spherical V-2 chamber. By 1951, the Army was moving rapidly toward the design of the Redstone missile, and production was begun in 1952. Redstone rockets became the 'reliable workhorse' for America's early space program. As an example of the versatility, Redstone was utilized in the booster for Explorer 1, the first American satellite, with no major changes to the engine or missile

  7. The relationship between early recruitment-related activities and the application decisions of new labor-market entrants: a brand equity approach to recruitment.

    PubMed

    Collins, Christopher J; Stevens, Cynthia Kay

    2002-12-01

    Theory and research from the marketing literature on customer-based brand equity were used to predict how positive exposure to 4 early recruitment-related activities-publicity, sponsorships, word-of-mouth endorsements, and advertising-may affect the application decisions of engineering students. Similar to prior marketing findings, the results suggested that early recruitment-related activities were indirectly related to intentions and decisions through 2 dimensions of employer brand image: general attitudes toward the company and perceived job attributes. The relationships between word-of-mouth endorsements and the 2 dimensions of brand image were particularly strong. In addition, it was found that early recruitment-related activities interacted with one another such that employer brand image was stronger when firms used publicity in conjunction with other early recruitment-related activities. PMID:12558218

  8. Magnetic Launch Assist System-Artist's Concept

    NASA Technical Reports Server (NTRS)

    1999-01-01

    This illustration is an artist's concept of a Magnetic Launch Assist System, formerly referred as the Magnetic Levitation (Maglev) system, for space launch. Overcoming the grip of Earth's gravity is a supreme challenge for engineers who design rockets that leave the planet. Engineers at the Marshall Space Flight Center have developed and tested Magnetic Launch Assist System technologies that could levitate and accelerate a launch vehicle along a track at high speeds before it leaves the ground. Using electricity and magnetic fields, a Magnetic Launch Assist system would drive a spacecraft along a horizontal track until it reaches desired speeds. A full-scale, operational track would be about 1.5-miles long and capable of accelerating a vehicle to 600 mph in 9.5 seconds. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, landing gear and the wing size, as well as the elimination of propellant weight resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  9. Project Antares: A low cost modular launch vehicle for the future

    NASA Astrophysics Data System (ADS)

    Aarnio, Steve; Anderson, Hobie; Arzaz, El Mehdi; Bailey, Michelle; Beeghly, Jeff; Cartwright, Curt; Chau, William; Dawdy, Andrew; Detert, Bruce; Ervin, Miles

    1991-06-01

    The single stage to orbit launch vehicle Antares is based upon the revolutionary concept of modularity, enabling the Antares to efficiently launch communications satellites, as well as heavy payloads, into Earth's orbit and beyond. The basic unit of the modular system, a single Antares vehicle, is aimed at launching approximately 10,000 kg into low Earth orbit (LEO). When coupled with a Centaur upper stage it is capable of placing 3500 kg into geostationary orbit. The Antares incorporates a reusable engine, the Dual Mixture Ratio Engine (DMRE), as its propulsive device. This enables Antares to compete and excel in the satellite launch market by dramatically reducing launch costs. Antares' projected launch costs are $1340 per kg to LEO which offers a tremendous savings over launch vehicles available today. Inherent in the design is the capability to attach several of these vehicles together to provide heavy lift capability. Any number of these vehicles, up to seven, can be attached depending on the payload and mission requirements. With a seven vehicle configuration Antares's modular concept provides a heavy lift capability of approximately 70,000 kg to LEO. This expandability allows for a wider range of payload options such as large Earth satellites, Space Station Freedom support, and interplanetary spacecraft, and also offers a significant cost savings over a mixed fleet based on different launch vehicles.

  10. Project Antares: A low cost modular launch vehicle for the future

    NASA Technical Reports Server (NTRS)

    Aarnio, Steve; Anderson, Hobie; Arzaz, El Mehdi; Bailey, Michelle; Beeghly, Jeff; Cartwright, Curt; Chau, William; Dawdy, Andrew; Detert, Bruce; Ervin, Miles

    1991-01-01

    The single stage to orbit launch vehicle Antares is based upon the revolutionary concept of modularity, enabling the Antares to efficiently launch communications satellites, as well as heavy payloads, into Earth's orbit and beyond. The basic unit of the modular system, a single Antares vehicle, is aimed at launching approximately 10,000 kg into low Earth orbit (LEO). When coupled with a Centaur upper stage it is capable of placing 3500 kg into geostationary orbit. The Antares incorporates a reusable engine, the Dual Mixture Ratio Engine (DMRE), as its propulsive device. This enables Antares to compete and excel in the satellite launch market by dramatically reducing launch costs. Antares' projected launch costs are $1340 per kg to LEO which offers a tremendous savings over launch vehicles available today. Inherent in the design is the capability to attach several of these vehicles together to provide heavy lift capability. Any number of these vehicles, up to seven, can be attached depending on the payload and mission requirements. With a seven vehicle configuration Antares's modular concept provides a heavy lift capability of approximately 70,000 kg to LEO. This expandability allows for a wider range of payload options such as large Earth satellites, Space Station Freedom support, and interplanetary spacecraft, and also offers a significant cost savings over a mixed fleet based on different launch vehicles.

  11. [MATCHE: Management Approach to Teaching Consumer and Homemaking Education.] Economically Depressed Areas Strand: Management. Module III-F-3: Marketing Practices in Relation to Low Income Clientele.

    ERIC Educational Resources Information Center

    California State Univ., Fresno. Dept. of Home Economics.

    This competency-based preservice home economics teacher education module on marketing practices in relation to low income clientele is the third in a set of three modules on management in economically depressed areas (EDAs). (This set is part of a larger set of sixty-seven modules on the Management Approach to Teaching Consumer and Homemaking…

  12. Space Stations using the Skylon Launch System

    NASA Astrophysics Data System (ADS)

    Hempsell, M.

    After the International Space Station is decommissioned in 2020 or soon after, Skylon will be an operating launch system and it is the obvious means to launch any successor in orbit infrastructure. The study looked at establishing 14 stations of 7 different types located from Low Earth Orbit to the Moon's surface with common elements all launched by Skylon. The key reason for the study was to validate Skylon could launch such an infrastructure, but the study's secondary objectives were to contribute to consideration of what should replace the ISS, and explore a ``multiple small station'' architecture. It was found that the total acquisition costs for LEO stations could be below 1 billion (2010) while for stations beyond LEO total acquisition costs were found to be between 3 and £5 billion. No technical constraints on the Skylon launch system were found that would prevent it launching all 14 stations in under 5 years.

  13. Chemical launch system options for microspacecraft

    NASA Technical Reports Server (NTRS)

    Sargent, Mark G.

    1989-01-01

    The paper presents launch vehicle and upper-stage options for application to lunar and interplanetary microspacecraft missions. Particular attention is given to the capabilities of Piggyback, small launch vehicles, and large launch vehicles. It is noted that Piggyback options on the Shuttle and expendable launch vehicles enable near-term earth-orbital missions and the potential for lunar and planetary missions if an electric-propulsion upper-stage is developed. Launch systems like the Space Shuttle could be used to launch large members of microspacecraft in 'constellation deployment' and 'shotgun' class missions to a variety of solar-system targets such as the sun, asteroids, comets, the moon, Mars, and Saturn.

  14. Launch of Jupiter-C/Explorer 1

    NASA Technical Reports Server (NTRS)

    1958-01-01

    Launch of Jupiter-C/Explorer 1 at Cape Canaveral, Florida on January 31, 1958. After the Russian Sputnik 1 was launched in October 1957, the launching of an American satellite assumed much greater importance. After the Vanguard rocket exploded on the pad in December 1957, the ability to orbit a satellite became a matter of national prestige. On January 31, 1958, slightly more than four weeks after the launch of Sputnik.The ABMA (Army Ballistic Missile Agency) in Redstone Arsenal, Huntsville, Alabama, in cooperation with the Jet Propulsion Laboratory, launched a Jupiter from Cape Canaveral, Florida. The rocket consisted of a modified version of the Redstone rocket's first stage and two upper stages of clustered Baby Sergeant rockets developed by the Jet Propulsion Laboratory and later designated as Juno boosters for space launches

  15. Launch, Jupiter-C, Explorer 1

    NASA Technical Reports Server (NTRS)

    1958-01-01

    Launch of Jupiter-C/Explorer 1 at Cape Canaveral, Florida on January 31, 1958. After the Russian Sputnik 1 was launched in October 1957, the launching of an American satellite assumed much greater importance. After the Vanguard rocket exploded on the pad in December 1957, the ability to orbit a satellite became a matter of national prestige. On January 31, 1958, slightly more than four weeks after the launch of Sputnik.The ABMA (Army Ballistic Missile Agency) in Redstone Arsenal, Huntsville, Alabama, in cooperation with the Jet Propulsion Laboratory, launched a Jupiter from Cape Canaveral, Florida. The rocket consisted of a modified version of the Redstone rocket's first stage and two upper stages of clustered Baby Sergeant rockets developed by the Jet Propulsion Laboratory and later designated as Juno boosters for space launches

  16. Inhibitions and implications associated with celebrity participation in health-related social marketing: an exploratory research focused on HIV prevention in Portugal.

    PubMed

    Casais, Beatriz; Proença, João F

    2012-01-01

    This article discusses motivations and inhibitions among celebrities to participate in health-related social marketing. The research identifies the implications that this involvement may have upon their lives. Results from in-depth interviews with 27 Portuguese celebrities show that they expect a fee for endorsements of commercial and government social marketing, despite the positive image they may gain from endorsing public health. The results demonstrate an absence of celebrity prejudice against HIV because of its serious nature and the social stigma attached to AIDS. This research suggests there is a positive bias and presents helpful information for negotiations between institutions and celebrities. PMID:22905943

  17. 14 CFR 415.119 - Launch plans.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Launch plans. 415.119 Section 415.119... From a Non-Federal Launch Site § 415.119 Launch plans. An applicant's safety review document must contain the plans required by § 417.111 of this chapter, except for the countdown plan of § 417.111(l)...

  18. 14 CFR 415.119 - Launch plans.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Launch plans. 415.119 Section 415.119... From a Non-Federal Launch Site § 415.119 Launch plans. An applicant's safety review document must contain the plans required by § 417.111 of this chapter, except for the countdown plan of § 417.111(l)...

  19. ISS Service Module Pre-Launch

    NASA Technical Reports Server (NTRS)

    2000-01-01

    Various shots show Discovery at the launch pad during the final 30-minute countdown. The prelaunch conditions are described and information is given on the upcoming launch and the orbiter's docking with the International Space Station (ISS). A brief collage of rollout and launch footage of STS-92 Endeavour commemorates the 100th Space Shuttle mission and the 100th anniversary of the Philadelphia Orchestra (also seen). The music of '2001: A Space Odyssey) is played by the orchestra.

  20. Prelaunch summary: NOAA-B launch

    NASA Technical Reports Server (NTRS)

    1980-01-01

    The NOAA-B satellite will launch from the Western Test Range into Sun-synchronous orbit to replace the TIROSN-satellite as part of the national operational environmental satellite system in support of the Global Atmospheric Research Program and the World Weather Watch. The mission objectives, primary environmental sensors, launch particulars, flight sequence of events, mission support, and project costs for NOAA-A through NOAA-G are discussed. NASA's responsibilities include launch, in-orbit evaluation and spacecraft checkout.

  1. Simulation of Wind Profile Perturbations for Launch Vehicle Design

    NASA Technical Reports Server (NTRS)

    Adelfang, S. I.

    2004-01-01

    Ideally, a statistically representative sample of measured high-resolution wind profiles with wavelengths as small as tens of meters is required in design studies to establish aerodynamic load indicator dispersions and vehicle control system capability. At most potential launch sites, high- resolution wind profiles may not exist. Representative samples of Rawinsonde wind profiles to altitudes of 30 km are more likely to be available from the extensive network of measurement sites established for routine sampling in support of weather observing and forecasting activity. Such a sample, large enough to be statistically representative of relatively large wavelength perturbations, would be inadequate for launch vehicle design assessments because the Rawinsonde system accurately measures wind perturbations with wavelengths no smaller than 2000 m (1000 m altitude increment). The Kennedy Space Center (KSC) Jimsphere wind profiles (150/month and seasonal 2 and 3.5-hr pairs) are the only adequate samples of high resolution profiles approx. 150 to 300 m effective resolution, but over-sampled at 25 m intervals) that have been used extensively for launch vehicle design assessments. Therefore, a simulation process has been developed for enhancement of measured low-resolution Rawinsonde profiles that would be applicable in preliminary launch vehicle design studies at launch sites other than KSC.

  2. STS-121: Discovery Launch Postponement MMT Briefing

    NASA Technical Reports Server (NTRS)

    2006-01-01

    Bruce Buckingham from NASA Public Affairs introduces the panel who consist of: John Shannon, MMT chairman JSC; Mike Leinbach, NASA Launch Director; and 1st Lieutenant Kaleb Nordren, USAF 45th Weather Squadron. An opening statement is given from John Shannon on the postponement of the launch due to thunderstorms. Mike Leinbach also elaborates on the weather and talks about scrubbing two hours early, draining the vehicle, and reloading the hydrogen for the fuel cells for a possible launch attempt on Tuesday morning. Norden gives his weather forecast for Tuesday and Wednesday. Questions from the media on launch attempts, weather, and the cost of the scrub are addressed.

  3. Overcoming Scalability Challenges for Tool Daemon Launching

    SciTech Connect

    Ahn, D H; Arnold, D C; de Supinski, B R; Lee, G L; Miller, B P; Schulz, M

    2008-02-15

    Many tools that target parallel and distributed environments must co-locate a set of daemons with the distributed processes of the target application. However, efficient and portable deployment of these daemons on large scale systems is an unsolved problem. We overcome this gap with LaunchMON, a scalable, robust, portable, secure, and general purpose infrastructure for launching tool daemons. Its API allows tool builders to identify all processes of a target job, launch daemons on the relevant nodes and control daemon interaction. Our results show that Launch-MON scales to very large daemon counts and substantially enhances performance over existing ad hoc mechanisms.

  4. 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.).

  5. Mars Science Laboratory Launch Pad Thermal Control

    NASA Technical Reports Server (NTRS)

    Bhandari, Pradeep; Dudik, Brenda; Birur, Gajanana; Bame, David

    2011-01-01

    This paper will describe the challenges faced in accommodating the warm Multi Mission Radioisotope Thermoelectric Generator (MMRTG) during the pre-launch phases of integration, launch pad operations as well as during launch. Predictions of temperatures during these phases will be presented when all the cooling systems (HRS and A/C) are operational. In-air tests conducted on the spacecraft in December 2008 to simulate the launch conditions were very successful and showed that all components would be within their allowable limits during these phases. Results of these tests will be shared in this paper.

  6. KOMPSAT Satellite Launch and Deployment Operations

    NASA Astrophysics Data System (ADS)

    Baek, Myung-Jin; Chang, Young-Keun; Lee, Jin-Ho

    1999-12-01

    In this paper, KOMPSAT satellite launch and deployment operations are discussed. The U.S. Taurus launch vehicle delivers KOMPSAT satellite into the mission orbit directly. Launch and deployment operations is monitored and controlled by several international ground stations including Korean Ground Station (KGS). After separation from launch vehicle, KOMPSAT spacecraft deploys solar array by on-board autonomous stored commands without ground inter-vention and stabilizes the satellite such that solar arrays point to the sun. Autonomous ground communication is designed for KOMPSAT for the early orbit ground contact. KOMPSAT space-craft has capability of handing contingency situation by on-board fault management design to retry deployment sequence.

  7. Ten-year space launch technology plan

    NASA Technical Reports Server (NTRS)

    1992-01-01

    This document is the response to the National Space Policy Directive-4 (NSPD-4), signed by the President on 10 Jul. 1991. Directive NSPD-4 calls upon the Department of Defense (DoD), the Department of Energy (DOE), and the National Aeronautics and Space Administration (NASA) to coordinate national space launch technology efforts and to jointly prepare a 10-year space launch technology plan. The nation's future in space rests on the strength of its national launch technology program. This plan documents our current launch technology efforts, plans for future initiatives in this arena, and the overarching philosophy that links these activities into an integrated national technology program.

  8. Launch site comparison between the earth, the moon, and Mars

    NASA Astrophysics Data System (ADS)

    Hodge, Suzanne M.; Caldwell, Ronald

    The launch operations required for human space exploration are considered in an integrated analysis of the operations and support planning processes and systems engineering. The large quantity of materials and equipment needed to support the space activities is shown to be a critical operations parameter. Sustaining system operations during crew visits is an important challenge, and it is suggested that low-maintenance high-reliability operational equipment is needed for lunar and Martian surface operations. Operations and support considerations for the Space Exploration Initiative are divided into three areas: (1) ground and flight/mission operations; (2) nodal and orbital transfer operations; and (3) lunar or Martian surface operations. The capability and nature of the operations and support facilities are related to earth-based launch-site processing. The incorporation of operational factors into launch-site designs can help reduce costs and improve the chances of mission success.

  9. Stratospheric ozone reactive chemicals generated by space launches worldwide

    SciTech Connect

    Brady, B.B.; Fournier, E.W.; Martin, L.R.; Cohen, R.B.

    1994-11-01

    We report quantities of inorganic chlorine compounds and aluminum oxide particles (Al203) deposited in the stratosphere and troposphere by solid rocket propelled launch vehicles. Totals are presented by launch vehicle type, summarized on an annual basis, and projected to the year 2010 using standard mission models. Data are given for Air Force, NASA (shuttle and expendable vehicles), the European Space Agency (ESA) (Ariane 5), and the Japanese Space Agency (H-1 and H-2). Whereas inorganic chlorine compounds released by solid rockets are directly related to stratospheric ozone depletion, much uncertainty surrounds reactivity of aluminum oxide particles. We also compare current and future effects of space launch on stratospheric ozone depletion with those of Ozone Depleting Chemicals (ODCs). As a baseline, we use projections of future ODC use by SMC, Air Force Materiel Command (AFMC), and the world. Relevant stratospheric chemistry is considered to make a legitimate comparison of ODC and solid rocket exhaust.

  10. Representational momentum and Michotte's (1946/1963) "launching effect" paradigm.

    PubMed

    Hubbard, T L; Blessum, J A; Ruppel, S E

    2001-01-01

    In A. Michotte's (1946/1963) launching effect, a moving launcher contacts a stationary target, and then the launcher becomes stationary and the target begins to move. In this experiment, observers viewed modifications of a launching effect display, and displacement in memory for the location of targets was measured. Forward displacement of targets in launching effect displays was decreased relative to that of targets (a) that were presented in isolation and either moved at a constant fast or slow velocity or decelerated or (b) that moved in a direction orthogonal to previous motion of the launcher. Possible explanations involving a deceleration of motion or landmark attraction effects were ruled out. Displacement patterns were consistent with naive impetus theory and the hypothesis that observers believed impetus from the launcher was imparted to the target and then dissipated. PMID:11204104

  11. The Feasibility of Railgun Horizontal-Launch Assist

    NASA Technical Reports Server (NTRS)

    Youngquist, Robert C.; Cox, Robert B.

    2011-01-01

    Railguns typically operate for a few milliseconds, supplying thousands of G's of acceleration to a small projectile, resulting in exceptional speeds. This paper argues through analysis and experiment, that this "standard" technology can be modified to provide 2-3 G's acceleration to a relatively heavy launch vehicle for a time period exceeding several seconds, yielding a launch assist velocity in excess of Mach 1. The key insight here is that an efficient rail gun operates at a speed approximately given by the system resistance divided by the inductance gradient, which can be tailored because recent MOSFET and ultra-capacitor advances allow very low total power supply resistances with high capacitance and augmented railgun architectures provide a scalable inductance gradient. Consequently, it should now be possible to construct a horizontal launch assist system utilizing railgun based architecture.

  12. 14 CFR 415.113 - Launch personnel certification program.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LAUNCH LICENSE Safety Review and Approval for Launch of an Expendable Launch Vehicle From a Non-Federal Launch Site § 415.113 Launch personnel certification program. (a... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Launch personnel certification program....

  13. 14 CFR 415.113 - Launch personnel certification program.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LAUNCH LICENSE Safety Review and Approval for Launch of an Expendable Launch Vehicle From a Non-Federal Launch Site § 415.113 Launch personnel certification program. (a... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Launch personnel certification program....

  14. 14 CFR 415.133 - Safety at end of launch.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... Launch Vehicle From a Non-Federal Launch Site § 415.133 Safety at end of launch. An applicant must demonstrate compliance with § 417.129 of this chapter, for any proposed launch of a launch vehicle with a... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Safety at end of launch. 415.133...

  15. 14 CFR 415.133 - Safety at end of launch.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... Launch Vehicle From a Non-Federal Launch Site § 415.133 Safety at end of launch. An applicant must demonstrate compliance with § 417.129 of this chapter, for any proposed launch of a launch vehicle with a... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Safety at end of launch. 415.133...

  16. 14 CFR 415.113 - Launch personnel certification program.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LAUNCH LICENSE Safety Review and Approval for Launch of an Expendable Launch Vehicle From a Non-Federal Launch Site § 415.113 Launch personnel certification program. (a... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Launch personnel certification program....

  17. 14 CFR 415.133 - Safety at end of launch.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... Launch Vehicle From a Non-Federal Launch Site § 415.133 Safety at end of launch. An applicant must demonstrate compliance with § 417.129 of this chapter, for any proposed launch of a launch vehicle with a... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Safety at end of launch. 415.133...

  18. 14 CFR 415.133 - Safety at end of launch.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... Launch Vehicle From a Non-Federal Launch Site § 415.133 Safety at end of launch. An applicant must demonstrate compliance with § 417.129 of this chapter, for any proposed launch of a launch vehicle with a... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Safety at end of launch. 415.133...

  19. 14 CFR 415.113 - Launch personnel certification program.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LAUNCH LICENSE Safety Review and Approval for Launch of an Expendable Launch Vehicle From a Non-Federal Launch Site § 415.113 Launch personnel certification program. (a... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Launch personnel certification program....

  20. Strypi VII R launch vehicle

    SciTech Connect

    Wente, H.A.

    1982-01-01

    The Strypi VII R is a three-stage solid propellant launch vehicle designed to boost payloads ranging from 50 to 300 pounds to re-entry environment conditions. The first stage, a fin-stabilized ballistic rocket boosts the final two stages into an exoatmospheric trajectory where an attitude control system (ACS) precesses the spinning stages into the re-entry attitude. The ACS section is then jettisoned, and ignition of the spin-stabilized upper stages is initiated at a time determined to provide a zero angle-of-attack at beginning of re-entry. Four vehicles have been flown carrying three different re-entry test vehicles. Originally designed for use with a Castor II motor, the highly aluminized propellant in the first stage spinning environment contributed to a case rupture resulting in failure of the second flight. The last two flights were flown successfully using Castor I motors. Typically, the Strypi VII R can boost a 100 lbm RV to a speed of 19,500 fps on a flight path of -30 degrees at 300,000 feet altitude.

  1. Crew Launch Vehicle Upper Stage

    NASA Technical Reports Server (NTRS)

    Davis, D. J.; Cook, J. R.

    2006-01-01

    The Agency s Crew Launch Vehicle (CLV) will be the first human rated space transportation system developed in the United States since the Space Shuttle. The CLV will utilize existing Shuttle heritage hardware and systems combined with a "clean sheet design" for the Upper Stage. The Upper Stage element will be designed and developed by a team of NASA engineers managed by the Marshall Space Flight Center (MSFC) in Huntsville, Alabama. The team will design the Upper Stage based on the Exploration Systems Architecture Study (ESAS) Team s point of departure conceptual design as illustrated in the figure below. This concept is a self-supporting cylindrical structure, approximately 1 15 feet long and 216 inches in diameter. While this "clean-sheet" upper stage design inherently carries more risk than utilizing a modified design, the approach also has many advantages. This paper will discuss the advantages and disadvantages of pursuing a "clean-sheet" design for the new CLV Upper Stage as well as describe in detail the overall design of the Upper Stage and its integration into NASA s CLV.

  2. Burundi launches campaign against AIDS.

    PubMed

    1999-05-10

    The conflict-ridden central African state of Burundi launched a campaign against AIDS as the health minister said 160,000 children were orphans as a result of the disease. "This day can be considered the real beginning of the war against AIDS in our country," said Leonce Ngendakumana National Assembly President. He was opening a workshop designed to develop strategies to combat the spread of HIV, which was attended by UN agencies, aid organizations, and members of the government. Health Minister Juma Kariburyo said 30,000 people had died of AIDS in 2 years in Burundi, which has a population of around 6 million. "We had less than 1% of infection in 1983, but today the urban area figures are more than 20%, and more than 14% in the rural areas," he added. But Jeanne Gapiya, president of a Burundian association for people who are HIV positive, said she feared the true figures could be far higher. Gapiya is HIV positive and has lost her husband, child, brother and sister to AIDS. Minister of Defense Colonel Alfred Nkurunziza told the workshop the disease was rampant within the army. Burundi's Tutsi-dominated army is fighting a bitter civil war against ethnic Hutu rebels. The conflict has caused large refugee movements, which has exacerbated the spread of infectious diseases. PMID:12349334

  3. Launch of Russian reactor postponed

    SciTech Connect

    Not Available

    1993-02-05

    Astronomers and weapons scientists seemed heated on a collision course a few months ago over the military's plans to send a Russian nuclear reactor into space. But an agreement reached in late January has prevented a pile-up, at least for 6 months. The astronomers, led by Donald Lamb of the University of Chicago, were objecting to plans by the Strategic Defense Initiative Office (SDIO) to launch Topaz 2, an experimental Russian nuclear reactor, arguing that rogue particles from it might ruin sensitive gamma ray experiments. The reactor is designed to propel itself in space with a jet of xenon ions. One worry was that leaking gamma rays and positrons, which can travel in the earth's magnetic field and pop up in the darndest places, might cause false signals in gamma ray monitors (Science, 18 December 1992, p. 1878). The worry has abated now that SDI officials will postpone choosing a rocket and mission altitutde for Topaz 2 for 6 months, while experts study how its emissions at various altitudes might affect instruments aboard the Gamma Ray Observatory and other satellites. In effect, the SDIO has agreed to an environmental impact study for space, following an unusual meeting organized by former Russian space official Roald Sagdeev at the University of Maryland on 19 January. There the Russian designers of Topaz 2, its new owners at the SDIO, and critics in the astronomy community achieved common ground: that more study was needed.

  4. 48 CFR 1852.228-78 - Cross-waiver of liability for NASA expendable launch vehicle launches.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... Space Act agreement that contains the cross-waiver of liability provision authorized in 14 CFR 1266.104... Vehicle (ELV) Launches (SEP 1993) (a) As prescribed by regulation (14 CFR part 1266), NASA agreements... parties related entities to encourage participation in space exploration, use, and investment. The...

  5. Assessment of existing and future launch vehicle liquid engine development

    NASA Astrophysics Data System (ADS)

    Stampfl, E.; Meyer, L.

    Existing liquid propellant engines for large launch vehicles are described in terms of pertinent engine and propellant parameters and their launch vehicle application. The development approach and the maturity of engine technology which prevailed prior to and early in specific engine development programs are discussed including lessons learned. New engines, including improved conventional and new concepts that could support the next generation launch vehicle, are delineated with emphasis on technology. The technology maturity and development needed to alleviate the potential development risk are presented along with projected gains in performance, operability, reusability, reliability and producibility. A technology ranking methodology which incorporates a relative transportation system life cycle cost (LCC) as the payoff function is developed. The methodology is useful for establishing preliminary but timely cost effectiveness rankings of various technologies. The methodology uses conventional cost estimating relations (CER) in non-dimensional form. The relative overall transportation system payoff resulting from the implementation of new propulsion system technology is developed from recurring and non-recurring costs of major transportation system elements including the vehicle, operations and launch complex. A ranking of engine concepts and associated technologies is given for several transportation system candidates which serve a high activity mission model.

  6. Improving Conceptual Design for Launch Vehicles

    NASA Technical Reports Server (NTRS)

    Olds, John R.

    1998-01-01

    This report summarizes activities performed during the second year of a three year cooperative agreement between NASA - Langley Research Center and Georgia Tech. Year 1 of the project resulted in the creation of a new Cost and Business Assessment Model (CABAM) for estimating the economic performance of advanced reusable launch vehicles including non-recurring costs, recurring costs, and revenue. The current year (second year) activities were focused on the evaluation of automated, collaborative design frameworks (computation architectures or computational frameworks) for automating the design process in advanced space vehicle design. Consistent with NASA's new thrust area in developing and understanding Intelligent Synthesis Environments (ISE), the goals of this year's research efforts were to develop and apply computer integration techniques and near-term computational frameworks for conducting advanced space vehicle design. NASA - Langley (VAB) has taken a lead role in developing a web-based computing architectures within which the designer can interact with disciplinary analysis tools through a flexible web interface. The advantages of this approach are, 1) flexible access to the designer interface through a simple web browser (e.g. Netscape Navigator), 2) ability to include existing 'legacy' codes, and 3) ability to include distributed analysis tools running on remote computers. To date, VAB's internal emphasis has been on developing this test system for the planetary entry mission under the joint Integrated Design System (IDS) program with NASA - Ames and JPL. Georgia Tech's complementary goals this year were to: 1) Examine an alternate 'custom' computational architecture for the three-discipline IDS planetary entry problem to assess the advantages and disadvantages relative to the web-based approach.and 2) Develop and examine a web-based interface and framework for a typical launch vehicle design problem.

  7. EXPLORER 11 LIFTS OFF FROM LAUNCH COMPLEX 26B BY A JUNO LAUNCH VEHICLE

    NASA Technical Reports Server (NTRS)

    1961-01-01

    NASA today launched from Cape Canaveral a 75 pound experiment designed to transmit information about the structure of the ionosphere, called the S-15. It was launched at 0917 AM. All four stages fired successfully.

  8. Energy impact assessment of NASA's past, present, and future space launch vehicles

    NASA Technical Reports Server (NTRS)

    Rice, E. E.

    1978-01-01

    An approach to analyze the total energy required for overall support of space launch vehicles is outlined along with some of the basic data required for such analyses. Selected results obtained by using this approach are presented for various past (some are already phased out), present, and future NASA launch vehicles, including an estimate of the total annual energy required to support one projected NASA launch vehicle traffic model. The material presented is expected to give a better insight into the details of an energy impact analysis. Major conclusions are that: (1) for expendable launch vehicle systems, the energy required to manufacture hardware and support launch operations is most significant; (2) for totally reusable systems, the energy required to process/manufacture propellants and fluids is by far the most significant contributor; and (3) up to 1991, the projected highest annual energy requirement for the NASA launch vehicles does not constitute a significant energy impact relative to the nation's total energy needs.

  9. Implications of previous space commercialization experiences for the reusable launch vehicle

    NASA Astrophysics Data System (ADS)

    Obermann, Richard M.; Williamson, Ray A.

    2003-07-01

    The United States' 1994 National Space Transportation Policy directed the National Aeronautics and Space Administration (NASA) to work with industry on the development of technologies required for a reusable launch vehicle (RLV). In the partnership that has evolved from that directive, NASA envisions its role as providing support for technological risk reduction and for developing space transportation to serve government needs. NASA officials assume that the development of an operational, commercial RLV will be carried out by the private sector without use of government funds. Under that scenario, the Federal government will simply become a customer for commercial RLV services. In evaluating the prospects for the development of a commercially viable RLV, it may be useful to examine "lessons learned" from previous space commercialization efforts—both those that succeeded and those that did not. It can be argued that several distinct streams of market and technological development may have to converge for successful commercialization of space systems to occur. Potential factors influencing the prospects for commercialization include the size and growth rate of the potential customer base, the extent to which a governmental customer exists to underpin the market, the development of associated "value-added" markets, the stability of governmental policies, the levels of technological and business risk, and the degree to which competitive markets exist. This paper examines two previous space commercialization experiences, evaluates the relative importance of the various factors that influence the prospects for success of commercialization efforts, and assesses the implications of those factors for the commercial viability of the proposed RLV.

  10. Saturn V - Design Considerations and Launch Issues

    NASA Technical Reports Server (NTRS)

    Interbartolo, Michael

    2009-01-01

    Objectives include: a) Understand some of the design considerations that went into creating the Saturn V launch vehicle; b) Gain an appreciation for some of the manufacturing issues concerning the Saturn V; and c) Review three major problems that affected Saturn V launches.

  11. Launch of STS-66 Space Shuttle Atlantis

    NASA Technical Reports Server (NTRS)

    1994-01-01

    The Space Shuttle Atlantis returns to work after a refurbishing and a two-year layoff, as liftoff for NASA's STS-66 occurs at noon (EDT), November 3, 1994. A 70mm camera was used to record the image. Note the vegetation and the reflection of the launch in the water across from the launch pad.

  12. Launch of STS-67 Space Shuttle Endeavour

    NASA Technical Reports Server (NTRS)

    1995-01-01

    Carrying a crew of seven and a complement of astronomic experiments, the Space Shuttle Endeavour embarks on NASA's longest shuttle flight to date. Endeavour's liftoff from Launch Pad 39A occurred at 1:38:13 a.m. (EST), March 2, 1995. In this view the fence line near the launch pad is evident in the foreground.

  13. Launch of STS-66 Space Shuttle Atlantis

    NASA Technical Reports Server (NTRS)

    1994-01-01

    The Space Shuttle Atlantis returns to work after a refurbishing and a two-year layoff, as liftoff for NASA's STS-66 occurs at noon (EDT), November 3, 1994. A 35mm camera was used to record the image, which includes much of the base of the launch site as well as the launch itself.

  14. Pigeons' Discrimination of Michotte's Launching Effect

    ERIC Educational Resources Information Center

    Young, Michael E.; Beckmann, Joshua S.; Wasserman, Edward A.

    2006-01-01

    We trained four pigeons to discriminate a Michotte launching animation from three other animations using a go/no-go task. The pigeons received food for pecking at one of the animations, but not for pecking at the others. The four animations featured two types of interactions among objects: causal (direct launching) and noncausal (delayed, distal,…

  15. Launching into the Podcast/Vodcast Universe

    ERIC Educational Resources Information Center

    Sampson, Jo Ann

    2006-01-01

    In the fall of 2005, the Orange County Library System (OCLS), located in the Orlando metropolitan area of Florida, launched a mission to explore podcasting. This article, written in the form of a "captain's log," prepares the reader for their own journey into the universe of successfully launching podcasts and a vodcast (video podcast). This…

  16. Space Launch Flight Termination System initial development

    NASA Astrophysics Data System (ADS)

    Ratkevich, B.; Brierley, S.; Lupia, D.; Leiker, T.

    This paper describes the studies, capabilities and challenges in initial development of a new digital encrypted termination system for space launch vehicles. This system is called the Space Launch Flight Termination System (SLFTS). Development of SLFTS is required to address an obsolescence issue and to improve the security of flight termination systems presently in use on the nation's space launch vehicles. SLFTS development was implemented in a four phase approach with the goal of producing a high secure, cost effective flight termination system for United Launch Alliance (ULA) and the United States Air Force (USAF) Evolved Expendable Launch Vehicle (EELV). These detailed study phases developed the requirements, design and implementation approach for a new high secure flight termination system. Studies led to a cost effective approach to replace the High Alphabet Command Receiver Decoders (HA-CRD) presently used on the EELV (Delta-IV & Atlas-V), with a common SLFTS unit. SLFTS is the next generation flight termination system for space launch vehicles, providing an assured high secure command destruct system for launch vehicles in flight. The unique capabilities and challenges to develop this technology for space launch use will be addressed in this paper in detail. This paper summarizes the current development status, design and capabilities of SLFTS for EELV.

  17. Indian Launch Services - Its Evolution and Potential

    NASA Astrophysics Data System (ADS)

    Balakrishnan, S. S.; Narayana Moorthi, D.; Sridhara Murthy, K. R.; Ramakrishnan, S.

    2002-01-01

    Development and operationalisation of the Polar Satellite Launch Vehicle (PSLV) has enabled the Indian Space Research Organisation (ISRO) end-to-end capability from launch to application in remote sensing satellites from the year 1997. Even as the PSLV was getting developed, its potential to provide launch services to international customers after meeting the internal demand was recognized. A unique method of carrying two microsatellites in every launch was worked out. Four piggyback payloads were flown in the last two flights of PSLV. The main payload has been flown with a standard interface. Having deployed through PSLV five primary satellites and four piggyback satellites, PSLV can carry a combination of satellites of different masses including the use of a dual launch adapter. With the successful flight of the Geosynchronous Satellite Launch Vehicle (GSLV) in its very first attempt, soon this will also be available on a commercial basis. Thus, ISRO has the capability to offer commercial launch opportunity through Antrix Corporation Limited, the commercial wing of the Department of Space from 10 kg to 1300 kg in SSO or 1000-2000 kg in to GTO or into any other LEO or MEO. This paper provides a brief account of the evolution of Indian Launch Services over the years and the future potential.

  18. Launch operations manpower yesterday, today and tomorrow

    NASA Astrophysics Data System (ADS)

    Ojalehto, George

    1991-05-01

    The manpower to accomplish spacecraft launch operations was analyzed. It seems that the ratio of personnel to launches was much higher in the beginning of the space program than in later years. The analysis was performed to see why the operational efficiency was better then than now and how that efficiency can be reattained.

  19. Target marketing of tobacco and alcohol-related products to ethnic minority groups in the United States.

    PubMed

    Moore, D J; Williams, J D; Qualls, W J

    1996-01-01

    This paper examines whether increased consumption of tobacco and alcohol products by minority groups is a function of the target marketing campaigns directed at these groups by marketers, and whether such contributes to the perpetuation of racism. First, a description of the tobacco and alcohol consumption rates of blacks and Hispanics compared to whites is presented, including a comparative analysis of the health effects and mortality rates resulting from the consumption of tobacco and alcohol. Second, the paper examines specific marketing strategies of targeting tobacco and alcohol products to ethnic minority consumers. This is followed by a discussion of whether these practices are a deliberate strategy driven by racism or just the pursuit of profit. A framework for answering the question is provided. Finally, the paper assesses the prospects for change in the future, and analyzes specific needs for future research. PMID:8882838

  20. Highly reusable space transportation: Approaches for reducing ETO launch costs to $100 - $200 per pound of payload

    NASA Technical Reports Server (NTRS)

    Olds, John R.

    1995-01-01

    The Commercial Space Transportation Study (CSTS) suggests that considerable market expansion in earth-to-orbit transportation would take place if current launch prices could be reduced to around $400 per pound of payload. If these low prices can be achieved, annual payload delivered to low earth orbit (LEO) is predicted to reach 6.7 million pounds. The primary market growth will occur in communications, government missions, and civil transportation. By establishing a cost target of $100-$200 per pound of payload for a new launch system, the Highly Reusable Space Transportation (HRST) program has clearly set its sights on removing the current restriction on market growth imposed by today's high launch costs. In particular, achieving the goal of $100-$200 per pound of payload will require significant coordinated efforts in (1) marketing strategy development, (2) business planning, (3) system operational strategy, (4) vehicle technical design, and (5) vehicle maintenance strategy.

  1. 14 CFR § 1214.117 - Launch and orbit parameters for a standard launch.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 5 2014-01-01 2014-01-01 false Launch and orbit parameters for a standard.... Government, Reimbursable Customers § 1214.117 Launch and orbit parameters for a standard launch. To qualify... orbits: 160 NM circular orbit, 28.5° inclination (nominal), or 160 NM circular orbit, 57°...

  2. KSC Launch Complex 34 during Apollo/Saturn Mission 202 pre-launch alert

    NASA Technical Reports Server (NTRS)

    1966-01-01

    Scene at the Kennedy Space Center's Launch Complex 34 during an Apollo/Saturn Mission 202 pre-launch alert. The mission was a step toward qualifying the Apollo Command and Service modules and the uprated Saturn I launch vehicle for manned flight.

  3. 14 CFR 417.125 - Launch of an unguided suborbital launch vehicle.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... energy to reach any populated area in any direction from the launch point; or (2) A launch operator demonstrates through the licensing process that the launch will be conducted using a wind weighting safety system that meets the requirements of paragraph (c) of this section. (c) Wind weighting safety system....

  4. 14 CFR 420.21 - Launch site location review-launch site boundary.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Launch site location review-launch site boundary. 420.21 Section 420.21 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LICENSE TO OPERATE A LAUNCH SITE Criteria and Information Requirements for Obtaining a...

  5. 14 CFR 420.29 - Launch site location review for unproven launch vehicles.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Launch site location review for unproven launch vehicles. 420.29 Section 420.29 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LICENSE TO OPERATE A LAUNCH SITE Criteria and Information Requirements for Obtaining...

  6. 14 CFR 417.17 - Launch reporting requirements and launch specific updates.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ..., including the launch vehicle, planned flight path, staging and impact locations, and any on-orbit activity... modification under § 417.11. (3) Thirty-day flight safety analysis update. A launch operator must file updated flight safety analysis products, using previously approved methodologies, for each launch no later...

  7. 14 CFR 417.17 - Launch reporting requirements and launch specific updates.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... Notification. Not later than noon, EST, 15 days before each licensed flight, a launch operator must file a... modification under § 417.11. (3) Thirty-day flight safety analysis update. A launch operator must file updated flight safety analysis products, using previously approved methodologies, for each launch no later...

  8. Launching the Future... Constellation Program at KSC

    NASA Technical Reports Server (NTRS)

    Denson, Erik C.

    2010-01-01

    With the Constellation Program, NASA is entering a new age of space exploration that will take us back to the Moon, to Mars, and beyond, and NASA is developing the new technology and vehicles to take us there. At the forefront are the Orion spacecraft and the Ares I launch vehicle. As NASA's gateway to space, Kennedy Space Center (KSC) will process and launch the new vehicles. This will require new systems and extensive changes to existing infrastructure. KSC is designing a new mobile launcher, a new launch control system, and new ground support equipment; modifying the Vehicle Assembly Building, one of the launch pads, and other facilities; and launching the Ares I-X flight test. It is an exciting and challenging time to be an engineer at KSC.

  9. Ceremony celebrates 50 years of rocket launches

    NASA Technical Reports Server (NTRS)

    2000-01-01

    Ceremony celebrates 50 years of rocket launches PL00C-10364.12 At the 50th anniversary ceremony celebrating the first rocket launch from pad 3 on what is now Cape Canaveral Air Force Station, Norris Gray waves to the audience. Gray was part of the team who successfully launched the first rocket, known as Bumper 8. The ceremony was hosted by the Air Force Space & Missile Museum Foundation, Inc. , and included launch of a Bumper 8 model rocket, presentation of a Bumper Award to Florida Sen. George Kirkpatrick by the National Space Club; plus remarks by Sen. Kirkpatrick, KSC's Center Director Roy Bridges, and the Commander of the 45th Space Wing, Brig. Gen. Donald Pettit. Also attending the ceremony were other members of the original Bumper 8 team. A reception followed at Hangar C. Since 1950 there have been a total of 3,245 launches from Cape Canaveral.

  10. Program Computes Sound Pressures at Rocket Launches

    NASA Technical Reports Server (NTRS)

    Ogg, Gary; Heyman, Roy; White, Michael; Edquist, Karl

    2005-01-01

    Launch Vehicle External Sound Pressure is a computer program that predicts the ignition overpressure and the acoustic pressure on the surfaces and in the vicinity of a rocket and launch pad during launch. The program generates a graphical user interface (GUI) that gathers input data from the user. These data include the critical dimensions of the rocket and of any launch-pad structures that may act as acoustic reflectors, the size and shape of the exhaust duct or flame deflector, and geometrical and operational parameters of the rocket engine. For the ignition-overpressure calculations, histories of the chamber pressure and mass flow rate also are required. Once the GUI has gathered the input data, it feeds them to ignition-overpressure and launch-acoustics routines, which are based on several approximate mathematical models of distributed sources, transmission, and reflection of acoustic waves. The output of the program includes ignition overpressures and acoustic pressures at specified locations.

  11. Environmental noise assessment STS-1 Columbia launch

    NASA Technical Reports Server (NTRS)

    Putnicki, G. J.

    1982-01-01

    An environmental noise assessement of the initial launch of the Space Transportation System, STS-1 Columbia was conducted. The principal objective of the environmental noise assessment was to measure the noise generated during the initial launch of the space shuttle to ascertain the validity of the levels predicted in the 1979 environmental impact statement. In the 1979 study information obtained for expendable launch vehicles, Titan, Saturn and Atlas was used to predict the noise levels that would be generated by the simultaneous firing of the two solid rocket boosters and the three space shuttle main engines. Fifteen monitoring sites were established in accessable areas located from 4,953 to 23,640 meters from the launch pad. Precision sound level meters were used to capture the peak level during the launch. Data obtained was compared to the predicted levels and were also compared to the identified levels, standards and criteria established by the federal agencies with noise abatement and control responsibilities.

  12. Students Participate in Rocket Launch Project

    NASA Technical Reports Server (NTRS)

    2002-01-01

    Filled with anticipation, students from three Huntsville area high schools: Randolph, Sparkman, and Johnson High Schools, counted down to launch the rockets they designed and built at the Army test site on Redstone Arsenal in Huntsville, Alabama. The projected two-mile high launch culminated more than a year's work and demonstrated the student team's ability to meet the challenge set by the Marshall Space Flight Center's (MSFC) Student Launch Initiative (SLI) program to apply science and math to experience, judgment, and common sense, and proved to NASA officials that they have successfully built reusable launch vehicles (RLVs), another challenge set by NASA's SLI program. MSFC's SLI program is an educational effort that aims to motivate students to pursue careers in science, math, and engineering. It provides hands-on, practical aerospace experience. In this picture, Randolph High School students are assembling their rocket in preparation for launch.

  13. An exploratory analysis of cigarette price premium, market share and consumer loyalty in relation to continued consumption versus cessation in a national US panel

    PubMed Central

    Lewis, Michael; Wang, Yanwen; Cahn, Zachary; Berg, Carla J

    2015-01-01

    Introduction Brand equity and consumer loyalty play a role in continued purchasing behaviour; however, this research has largely focused on non-addictive products without counter-marketing tactics. We examined the impact of brand equity (price premium, market share) and consumer loyalty (switching rates) on smoking cessation (discontinued cigarette purchases for 1 year) among smokers in a consumer panel. Methods In Spring 2015, we analysed 1077 cigarette-purchasing households in the Nielsen Homescan Panel. We analysed cessation in relation to brand equity, consumer loyalty, other purchasing behaviours (nicotine intake, frequency), sociodemographics and tobacco control activities (per state-specific data) over a 6-year period (2004–2009) using Cox proportional hazard modelling. Results The sample was 13.28% African-American; the average income was $52 334 (SD=31 445). The average price premium and market share of smokers’ dominant brands were $1.31 (SD=0.49) and 15.41% (SD=19.15), respectively. The mean brand loyalty level was 0.90 (SD=0.17), indicating high loyalty. In our final model, a higher price premium and market share were associated with lower quit rates (p=0.039); however, an interaction effect suggested that greater market share was not associated with lower cessation rates for African-American smokers (p=0.006). Consumer loyalty was not associated with cessation. Other predictors of lower quit rates included a higher nicotine intake (p=0.006) and baseline purchase frequency (p<0.001). Tobacco control factors were not significantly associated. Conclusions Smokers of high-equity cigarette brands are less likely to quit, perhaps due to strong brand–consumer relationships. Thus, continued efforts should aim to regulate tobacco marketing efforts in order to disrupt these relationships to promote cessation. PMID:26534732

  14. NASA's Space Launch System Mission Capabilities for Exploration

    NASA Technical Reports Server (NTRS)

    Creech, Stephen D.; Crumbly, Christopher M.; Robinson, Kimberly F.

    2015-01-01

    Designed to enable human space exploration missions, including eventual landings on Mars, NASA's Space Launch System (SLS) represents a unique launch capability with a wide range of utilization opportunities, from delivering habitation systems into the lunar vicinity to high-energy transits through the outer solar system. Developed with the goals of safety, affordability and sustainability in mind, SLS is a foundational capability for NASA's future plans for exploration, along with the Orion crew vehicle and upgraded ground systems at the agency's Kennedy Space Center. Substantial progress has been made toward the first launch of the initial configuration of SLS, which will be able to deliver more than 70 metric tons of payload into low Earth orbit (LEO), greater mass-to-orbit capability than any contemporary launch vehicle. The vehicle will then be evolved into more powerful configurations, culminating with the capability to deliver more than 130 metric tons to LEO, greater even than the Saturn V rocket that enabled human landings on the moon. SLS will also be able to carry larger payload fairings than any contemporary launch vehicle, and will offer opportunities for co-manifested and secondary payloads. Because of its substantial mass-lift capability, SLS will also offer unrivaled departure energy, enabling mission profiles currently not possible. Early collaboration with science teams planning future decadal-class missions have contributed to a greater understanding of the vehicle's potential range of utilization. This presentation will discuss the potential opportunities this vehicle poses for the planetary sciences community, relating the vehicle's evolution to practical implications for mission capture. As this paper will explain, SLS will be a global launch infrastructure asset, employing sustainable solutions and technological innovations to deliver capabilities for space exploration to power human and robotic systems beyond our Moon and in to deep space.

  15. NASA'S Space Launch System Mission Capabilities for Exploration

    NASA Technical Reports Server (NTRS)

    Creech, Stephen D.; Crumbly, Christopher M.; Robinson, Kimberly F.

    2015-01-01

    Designed to enable human space exploration missions, including eventual landings on Mars, NASA’s Space Launch System (SLS) represents a unique launch capability with a wide range of utilization opportunities, from delivering habitation systems into the lunar vicinity to high-energy transits through the outer solar system. Developed with the goals of safety, affordability and sustainability in mind, SLS is a foundational capability for NASA’s future plans for exploration, along with the Orion crew vehicle and upgraded ground systems at the agency’s Kennedy Space Center. Substantial progress has been made toward the first launch of the initial configuration of SLS, which will be able to deliver more than 70 metric tons of payload into low Earth orbit (LEO), greater mass-to-orbit capability than any contemporary launch vehicle. The vehicle will then be evolved into more powerful configurations, culminating with the capability to deliver more than 130 metric tons to LEO, greater even than the Saturn V rocket that enabled human landings on the moon. SLS will also be able to carry larger payload fairings than any contemporary launch vehicle, and will offer opportunities for co-manifested and secondary payloads. Because of its substantial mass-lift capability, SLS will also offer unrivaled departure energy, enabling mission profiles currently not possible. Early collaboration with science teams planning future decadal-class missions have contributed to a greater understanding of the vehicle’s potential range of utilization. This presentation will discuss the potential opportunities this vehicle poses for the planetary sciences community, relating the vehicle’s evolution to practical implications for mission capture. As this paper will explain, SLS will be a global launch infrastructure asset, employing sustainable solutions and technological innovations to deliver capabilities for space exploration to power human and robotic systems beyond our Moon and in to

  16. Recommended Screening Practices for Launch Collision Aviodance

    NASA Technical Reports Server (NTRS)

    Beaver, Brian A.; Hametz, Mark E.; Ollivierre, Jarmaine C.; Newman, Lauri K.; Hejduk, Matthew D.

    2015-01-01

    The objective of this document is to assess the value of launch collision avoidance (COLA) practices and provide recommendations regarding its implementation for NASA robotic missions. The scope of this effort is limited to launch COLA screens against catalog objects that are either spacecraft or debris. No modifications to manned safety COLA practices are considered in this effort. An assessment of the value of launch COLA can be broken down into two fundamental questions: 1) Does collision during launch represent a significant risk to either the payload being launched or the space environment? 2) Can launch collision mitigation be performed in a manner that provides meaningful risk reduction at an acceptable level of operational impact? While it has been possible to piece together partial answers to these questions for some time, the first attempt to comprehensively address them is documented in reference (a), Launch COLA Operations: an Examination of Data Products, Procedures, and Thresholds, Revision A. This report is the product of an extensive study that addressed fundamental technical questions surrounding launch collision avoidance analysis and practice. The results provided in reference (a) will be cited throughout this document as these two questions are addressed. The premise of this assessment is that in order to conclude that launch COLA is a value-added activity, the answer to both of these questions must be affirmative. A "no" answer to either of these questions points toward the conclusion that launch COLA provides little or no risk mitigation benefit. The remainder of this assessment will focus on addressing these two questions.

  17. Lockheed Martin approach to a Reusable Launch Vehicle (RLV)

    NASA Astrophysics Data System (ADS)

    Elvin, John D.

    1996-03-01

    This paper discusses Lockheed Martin's perspective on the development of a cost effective Reusable Launch Vehicle (RLV). Critical to a successful Single Stage To Orbit (SSTO) program are; an economic development plan sensitive to fiscal constraints; a vehicle concept satisfying present and future US launch needs; and an operations concept commensurate with a market driven program. Participation in the economic plan by government, industry, and the commercial sector is a key element of integrating our development plan and funding profile. The RLV baseline concept design, development evolution and several critical trade studies illustrate the superior performance achieved by our innovative approach to the problem of SSTO. Findings from initial aerodynamic and aerothermodynamic wind tunnel tests and trajectory analyses on this concept confirm the superior characteristics of the lifting body shape combined with the Linear Aerospike rocket engine. This Aero Ballistic Rocket (ABR) concept captures the essence of The Skunk Works approach to SSTO RLV technology integration and system engineering. These programmatic and concept development topics chronicle the key elements to implementing an innovative market driven next generation RLV.

  18. Commissioning healthcare for people with long term conditions: the persistence of relational contracting in England’s NHS quasi-market

    PubMed Central

    2013-01-01

    Background Since 1991, there has been a series of reforms of the English National Health Service (NHS) entailing an increasing separation between the commissioners of services and a widening range of public and independent sector providers able to compete for contracts to provide services to NHS patients. We examine the extent to which local commissioners had adopted a market-oriented (transactional) model of commissioning of care for people with long term conditions several years into the latest period of market-oriented reform. The paper also considers the factors that may have inhibited or supported market-oriented behaviour, including the presence of conditions conducive to a health care quasi-market. Methods We studied the commissioning of services for people with three long term conditions - diabetes, stroke and dementia - in three English primary care trust (PCT) areas over two years (2010-12). We took a broadly ethnographic approach to understanding the day-to-day practice of commissioning. Data were collected through interviews, observation of meetings and from documents. Results In contrast to a transactional, market-related approach organised around commissioner choice of provider and associated contracting, commissioning was largely relational, based on trust and collaboration with incumbent providers. There was limited sign of commissioners significantly challenging providers, changing providers, or decommissioning services. In none of the service areas were all the conditions for a well functioning quasi-market in health care in place. Choice of provider was generally absent or limited; information on demand and resource requirements was highly imperfect; motivations were complex; and transaction costs uncertain, but likely to be high. It was difficult to divide care into neat units for contracting purposes. As a result, it is scarcely surprising that commissioning practice in relation to all six commissioning developments was dominated by a

  19. Launch mission summary: INTELSAT 5(F1) ATLAS/CENTAUR-56

    NASA Technical Reports Server (NTRS)

    1981-01-01

    The technology and capability of the INTELSAT 5 series satellites and the Atlas-Centaur launch vehicle are described. Data relative to launch windows, flight plans, radar, and telemetry are included along with selected trajectory information and a sequence of flight events.

  20. Radar Evaluation of Optical Cloud Constraints to Space Launch Operations

    NASA Technical Reports Server (NTRS)

    Merceret, Francis J.; Short, David A.; Ward, Jennifer G.

    2005-01-01

    Weather constraints to launching space vehicles are designed to prevent loss of the vehicle or mission due to weather hazards (See, e.g., Ref 1). Constraints include Lightning Launch Commit Criteria (LLCC) designed to avoid natural and triggered lightning. The LLCC currently in use at most American launch sites including the Eastern Range and Kennedy Space Center require the Launch Weather Officer to determine the height of cloud bases and tops, the location of cloud edges, and cloud transparency. The preferred method of making these determinations is visual observation, but when that isn't possible due to darkness or obscured vision, it is permissible to use radar. This note examines the relationship between visual and radar observations in three ways: A theoretical consideration of the relationship between radar reflectivity and optical transparency. An observational study relating radar reflectivity to cloud edge determined from in-situ measurements of cloud particle concentrations that determine the visible cloud edge. An observational study relating standard radar products to anvil cloud transparency. It is shown that these three approaches yield results consistent with each other and with the radar threshold specified in Reference 2 for LLCC evaluation.