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Sample records for aerocapture technology development

  1. Aerocapture Technology Development Overview

    NASA Technical Reports Server (NTRS)

    Munk, Michelle M.; Moon, Steven A.

    2008-01-01

    This paper will explain the investment strategy, the role of detailed systems analysis, and the hardware and modeling developments that have resulted from the past 5 years of work under NASA's In-Space Propulsion Program (ISPT) Aerocapture investment area. The organizations that have been funded by ISPT over that time period received awards from a 2002 NASA Research Announcement. They are: Lockheed Martin Space Systems, Applied Research Associates, Inc., Ball Aerospace, NASA s Ames Research Center, and NASA s Langley Research Center. Their accomplishments include improved understanding of entry aerothermal environments, particularly at Titan, demonstration of aerocapture guidance algorithm robustness at multiple bodies, manufacture and test of a 2-meter Carbon-Carbon "hot structure," development and test of evolutionary, high-temperature structural systems with efficient ablative materials, and development of aerothermal sensors that will fly on the Mars Science Laboratory in 2009. Due in large part to this sustained ISPT support for Aerocapture, the technology is ready to be validated in flight.

  2. NASA Development of Aerocapture Technologies

    NASA Technical Reports Server (NTRS)

    James, Bonnie; Munk, Michelle; Moon, Steve

    2004-01-01

    Aeroassist technology development is a vital part of the NASA In-Space Propulsion Program (ISP), which is managed by the NASA Headquarters Office of Space Science, and implemented by the Marshall Space Flight Center in Huntsville, Alabama. Aeroassist is the general term given to various techniques to maneuver a space vehicle within an atmosphere, using aerodynamic forces in lieu of propulsive fuel. Within the ISP, the current aeroassist technology development focus is aerocapture. The objective of the ISP Aerocapture Technology Project (ATP) is to develop technologies that can enable and/or benefit NASA science missions by significantly reducing cost, mass, and/or travel times. To accomplish this objective, the ATP identifies and prioritizes the most promising technologies using systems analysis, technology advancement and peer review, coupled with NASA Headquarters Office of Space Science target requirements. Plans are focused on developing mid-Technology Readiness Level (TRL) technologies to TRL 6 (ready for technology demonstration in space).

  3. Aerocapture Technologies

    NASA Technical Reports Server (NTRS)

    Keys, Andrew S.

    2006-01-01

    Aeroassist technology development is a vital part of the NASA In-Space Propulsion Technology (ISPT) Program. One of the main focus areas of ISPT is aeroassist technologies through the Aerocapture Technology (AT) Activity. Within the ISPT, the current aeroassist technology development focus is aerocapture. Aerocapture relies on the exchange of momentum with an atmosphere to achieve thrust, in this case a decelerating thrust leading to orbit capture. Without aerocapture, a substantial propulsion system would be needed on the spacecraft to perform the same reduction of velocity. This could cause reductions in the science payload delivered to the destination, increases in the size of the launch vehicle (to carry the additional fuel required for planetary capture) or could simply make the mission impossible due to additional propulsion requirements. The AT is advancing each technology needed for the successful implementation of aerocapture in future missions. The technology development focuses on both rigid aeroshell systems as well as the development of inflatable aerocapture systems, advanced aeroshell performance sensors, lightweight structure and higher temperature adhesives. Inflatable systems such as tethered trailing ballutes ('balloon parachutes'), clamped ballutes, and inflatable aeroshells are also under development. Aerocapture-specific computational tools required to support future aerocapture missions are also an integral part of the ATP. Tools include: engineering reference atmosphere models, guidance and navigation, aerothermodynamic modeling, radiation modeling and flight simulation. Systems analysis plays a key role in the AT development process. The NASA in-house aerocapture systems analysis team has been taken with multiple systems definition and concept studies to complement the technology development tasks. The team derives science requirements, develops guidance and navigation algorithms, as well as engineering reference atmosphere models and

  4. Aerocapture Technology Development for Planetary Science - Update

    NASA Technical Reports Server (NTRS)

    Munk, Michelle M.

    2006-01-01

    Within NASA's Science Mission Directorate is a technological program dedicated to improving the cost, mass, and trip time of future scientific missions throughout the Solar System. The In-Space Propulsion Technology (ISPT) Program, established in 2001, is charged with advancing propulsion systems used in space from Technology Readiness Level (TRL) 3 to TRL6, and with planning activities leading to flight readiness. The program's content has changed considerably since inception, as the program has refocused its priorities. One of the technologies that has remained in the ISPT portfolio through these changes is Aerocapture. Aerocapture is the use of a planetary body's atmosphere to slow a vehicle from hyperbolic velocity to a low-energy orbit suitable for science. Prospective use of this technology has repeatedly shown huge mass savings for missions of interest in planetary exploration, at Titan, Neptune, Venus, and Mars. With launch vehicle costs rising, these savings could be the key to mission viability. This paper provides an update on the current state of the Aerocapture technology development effort, summarizes some recent key findings, and highlights hardware developments that are ready for application to Aerocapture vehicles and entry probes alike. Description of Investments: The Aerocapture technology area within the ISPT program has utilized the expertise around NASA to perform Phase A-level studies of future missions, to identify technology gaps that need to be filled to achieve flight readiness. A 2002 study of the Titan Explorer mission concept showed that the combination of Aerocapture and a Solar Electric Propulsion system could deliver a lander and orbiter to Titan in half the time and on a smaller, less expensive launch vehicle, compared to a mission using chemical propulsion for the interplanetary injection and orbit insertion. The study also identified no component technology breakthroughs necessary to implement Aerocapture on such a mission

  5. Aerocapture Technology Development Needs for Outer Planet Exploration

    NASA Technical Reports Server (NTRS)

    Wercinski, Paul; Munk, Michelle; Powell, Richard; Hall, Jeff; Graves, Claude; Partridge, Harry (Technical Monitor)

    2002-01-01

    The purpose of this white paper is to identify aerocapture technology and system level development needs to enable NASA future mission planning to support Outer Planet Exploration. Aerocapture is a flight maneuver that takes place at very high speeds within a planet's atmosphere that provides a change in velocity using aerodynamic forces (in contrast to propulsive thrust) for orbit insertion. Aerocapture is very much a system level technology where individual disciplines such as system analysis and integrated vehicle design, aerodynamics, aerothermal environments, thermal protection systems (TPS), guidance, navigation and control (GN&C) instrumentation need to be integrated and optimized to meet mission specific requirements. This paper identifies on-going activities, their relevance and potential benefit to outer planet aerocapture that include New Millennium ST7 Aerocapture concept definition study, Mars Exploration Program aeroassist project level support, and FY01 Aeroassist In-Space Guideline tasks. The challenges of performing aerocapture for outer planet missions such as Titan Explorer or Neptune Orbiter require investments to advance the technology readiness of the aerocapture technology disciplines for the unique application of outer planet aerocapture. This white paper will identify critical technology gaps (with emphasis on aeroshell concepts) and strategies for advancement.

  6. ISP Aerocapture Technology

    NASA Astrophysics Data System (ADS)

    James, B.

    2004-11-01

    Aerocapture technology development is a vital part of the NASA In-Space Propulsion Program (ISP), which is managed by NASA Headquarters and implemented at the NASA Marshall Space Flight Center in Huntsville, Alabama. Aerocapture is a flight maneuver designed to aerodynamically decelerate a spacecraft from hyperbolic approach to a captured orbit during one pass through the atmosphere. Small amounts of propulsive fuel are used for attitude control and periapsis raise only. This technique is very attractive since it permits spacecraft to be launched from Earth at higher verlocities, reducing trip times. The aerocapture technique also significantly reduces the overall mass of the propulsion systems. This allows for more science payload to be added to the mission. Alternatively, a smaller launch vehicle could be used, reducing overall mission cost. Aerocapture can be realized in various ways. It can be accomplished using rigid aeroshells, such as those used in previous mission efforts (like Apollo, the planned Aeroassist Flight Experiment and the Mars Exploration Rovers). Aerocapture can also be achieved with inflatable deceleration systems. This family includes the use of a potentially lighter, inflatable aeroshell or a large, trailing ballute - a combination parachute and balloon made of durable, thin material and stowed behind the vehicle for deployment. Aerocapture utilizing inflatable decelerators is also derived from previous efforts, but will necessitate further research to reach the technology readiness level (TRL) that the rigid aeroshell has achieved. Results of recent Aerocapture Systems analysis studies for small bodies and giant planets show that aerocapture can be enhancing for most missions and absolutely enabling for some mission scenarios. In this way, Aerocapture could open up exciting, new science mission opportunities.

  7. Aerocapture Technology Project Overview

    NASA Technical Reports Server (NTRS)

    James, Bonnie; Munk, Michelle; Moon, Steve

    2003-01-01

    Aerocapture technology development is one of the highest priority investments for the NASA In-Space Propulsion Program (ISP). The ISP is managed by the NASA Headquarters Office of Space Science, and implemented by the Marshall Space Flight Center in Huntsville, Alabama. The objective of the ISP Aerocapture Technology Project (ATP) is to develop technologies that can enable and/or benefit NASA science missions by significantly reducing cost, mass, and trip times. To accomplish this objective, the ATP identifies and prioritizes the most promising technologies using systems analysis, technology advancement and peer review, coupled with NASA Headquarters Office of Space Science target requirements. Efforts are focused on developing mid-Technology Readiness Level (TRL) technologies to systems-level spaceflight validation.

  8. Aerocapture Technology Developments from NASA's In-Space Propulsion Technology Program

    NASA Technical Reports Server (NTRS)

    Munk, Michelle M.; Moon, Steven A.

    2007-01-01

    This paper will explain the investment strategy, the role of detailed systems analysis, and the hardware and modeling developments that have resulted from the past 5 years of work under NASA's In-Space Propulsion Program (ISPT) Aerocapture investment area. The organizations that have been funded by ISPT over that time period received awards from a 2002 NASA Research Announcement. They are: Lockheed Martin Space Systems, Applied Research Associates, Inc., Ball Aerospace, NASA's Ames Research Center, and NASA's Langley Research Center. Their accomplishments include improved understanding of entry aerothermal environments, particularly at Titan, demonstration of aerocapture guidance algorithm robustness at multiple bodies, manufacture and test of a 2-meter Carbon-Carbon "hot structure," development and test of evolutionary, high-temperature structural systems with efficient ablative materials, and development of aerothermal sensors that will fly on the Mars Science Laboratory in 2009. Due in large part to this sustained ISPT support for Aerocapture, the technology is ready to be validated in flight.

  9. Overview of a Proposed Flight Validation of Aerocapture System Technology for Planetary Missions

    NASA Technical Reports Server (NTRS)

    Keys, Andrew S.; Hall, Jeffery L.; Oh, David; Munk, Michelle M.

    2006-01-01

    Aerocapture System Technology for Planetary Missions is being proposed to NASA's New Millennium Program for flight aboard the Space Technology 9 (ST9) flight opportunity. The proposed ST9 aerocapture mission is a system-level flight validation of the aerocapture maneuver as performed by an instrumented, high-fidelity flight vehicle within a true in-space and atmospheric environment. Successful validation of the aerocapture maneuver will be enabled through the flight validation of an advanced guidance, navigation, and control system as developed by Ball Aerospace and two advanced Thermal Protection System (TPS) materials, Silicon Refined Ablative Material-20 (SRAM-20) and SRAM-14, as developed by Applied Research Associates (ARA) Ablatives Laboratory. The ST9 aerocapture flight validation will be sufficient for immediate infusion of these technologies into NASA science missions being proposed for flight to a variety of Solar System destinations possessing a significant planetary atmosphere.

  10. Aerocapture Benefits to Future Science Missions

    NASA Technical Reports Server (NTRS)

    Artis, Gwen; James, Bonnie

    2006-01-01

    NASA's In-Space Propulsion Technology (ISPT) Program is investing in technologies to revolutionize the robotic exploration of deep space. One of these technologies is Aerocapture, the most promising of the "aeroassist" techniques used to maneuver a space vehicle within an atmosphere, using aerodynamic forces in lieu of propellant. (Other aeroassist techniques include aeroentry and aerobraking.) Aerocapture relies on drag atmospheric drag to decelerate an incoming spacecraft and capture it into orbit. This technique is very attractive since it permits spacecraft to be launched from Earth at higher velocities, providing shorter trip times and saving mass and overall cost on future missions. Recent aerocapture systems analysis studies quantify the benefits of aerocapture to future exploration. The 2002 Titan aerocapture study showed that using aerocapture at Titan instead of conventional propulsive capture results in over twice as much payload delivered to Titan. Aerocapture at Venus results in almost twice the payload delivered to Venus as with aerobraking, and over six times more mass delivered into orbit than all-propulsive capture. Aerocapture at Mars shows significant benefits as the payload sizes increase and as missions become more complex. Recent Neptune aerocapture studies show that aerocapture opens up entirely new classes of missions at Neptune. Current aerocapture technology development is advancing the maturity of each subsystem technology needed for successful implementation of aerocapture on future missions. Recent development has focused on both rigid aeroshell and inflatable aerocapture systems. Rigid aeroshell systems development includes new ablative and non-ablative thermal protection systems, advanced aeroshell performance sensors, lightweight structures and higher temperature adhesives. Inflatable systems such as trailing tethered and clamped "ballutes" and inflatable aeroshells are also under development. Computational tools required to support

  11. Technology requirements for a generic aerocapture system. [for atmospheric entry

    NASA Technical Reports Server (NTRS)

    Cruz, M. I.

    1980-01-01

    The technology requirements for the design of a generic aerocapture vehicle system are summarized. These spacecraft have the capability of completely eliminating fuel-costly retropropulsion for planetary orbit capture through a single aerodynamically controlled atmospheric braking pass from a hyperbolic trajectory into a near circular orbit. This generic system has application at both the inner and outer planets. Spacecraft design integration, navigation, communications, and aerothermal protection system design problems were assessed in the technology requirements study and are discussed in this paper.

  12. Recent developments in aerocapture for the Mars Rover Sample Return Mission

    NASA Astrophysics Data System (ADS)

    Willcockson, W. H.

    A mission-enabling technology for the MRSRM is the use of aerocapture to inject the vehicle into Mars orbit. Using an aerodeceleration device, savings of 20-30 percent of effective vehicle mass can be achieved over an all-propulsive capture approach. Recent IR&D progress in the area of aerocapture for this mission is examined with particular attention given to developments in guidance, navigation, and control. Consideration is given to the following areas of study: load relief guidance, density shear sensitivity analysis, and coupled navigation and guidance simulations.

  13. Neptune Aerocapture Systems Analysis

    NASA Technical Reports Server (NTRS)

    Lockwood, Mary Kae

    2004-01-01

    A Neptune Aerocapture Systems Analysis is completed to determine the feasibility, benefit and risk of an aeroshell aerocapture system for Neptune and to identify technology gaps and technology performance goals. The high fidelity systems analysis is completed by a five center NASA team and includes the following disciplines and analyses: science; mission design; aeroshell configuration screening and definition; interplanetary navigation analyses; atmosphere modeling; computational fluid dynamics for aerodynamic performance and database definition; initial stability analyses; guidance development; atmospheric flight simulation; computational fluid dynamics and radiation analyses for aeroheating environment definition; thermal protection system design, concepts and sizing; mass properties; structures; spacecraft design and packaging; and mass sensitivities. Results show that aerocapture can deliver 1.4 times more mass to Neptune orbit than an all-propulsive system for the same launch vehicle. In addition aerocapture results in a 3-4 year reduction in trip time compared to all-propulsive systems. Aerocapture is feasible and performance is adequate for the Neptune aerocapture mission. Monte Carlo simulation results show 100% successful capture for all cases including conservative assumptions on atmosphere and navigation. Enabling technologies for this mission include TPS manufacturing; and aerothermodynamic methods and validation for determining coupled 3-D convection, radiation and ablation aeroheating rates and loads, and the effects on surface recession.

  14. A Comparative Study of Aerocapture Missions with a Mars Destination

    NASA Technical Reports Server (NTRS)

    Vaughan, Diane; Miller, Heather C.; Griffin, Brand; James, Bonnie F.; Munk, Michelle M.

    2005-01-01

    Conventional interplanetary spacecraft use propulsive systems to decelerate into orbit. Aerocapture is an alternative approach for orbit capture, in which the spacecraft makes a single pass through a target destination's atmosphere. Although this technique has never been performed, studies show there are substantial benefits of using aerocapture for reduction of propellant mass, spacecraft size, and mission cost. The In-Space Propulsion (ISP) Program, part of NASA's Science Mission Directorate, has invested in aerocapture technology development since 2002. Aerocapture investments within ISP are largely driven by mission systems analysis studies, The purpose of this NASA-funded report is to identify and document the fundamental parameters of aerocapture within previous human and robotic Mars mission studies which will assist the community in identifying technology research gaps in human and robotic missions, and provide insight for future technology investments. Upon examination of the final data set, some key attributes within the aerocapture disciplines are identified.

  15. Mars Aerocapture Systems Study

    NASA Technical Reports Server (NTRS)

    Wright, Henry S.; Oh, David Y.; Westhelle, Carlos H.; Fisher, Jody L.; Dyke, R. Eric; Edquist, Karl T.; Brown, James L.; Justh, Hilary L.; Munk, Michelle M.

    2006-01-01

    Mars Aerocapture Systems Study (MASS) is a detailed study of the application of aerocapture to a large Mars robotic orbiter to assess and identify key technology gaps. This study addressed use of an Opposition class return segment for use in the Mars Sample Return architecture. Study addressed mission architecture issues as well as system design. Key trade studies focused on design of aerocapture aeroshell, spacecraft design and packaging, guidance, navigation and control with simulation, computational fluid dynamics, and thermal protection system sizing. Detailed master equipment lists are included as well as a cursory cost assessment.

  16. Ballute Aerocapture Trajectories at Neptune

    NASA Technical Reports Server (NTRS)

    Lyons, Daniel T.; Johnson, Wyatt

    2004-01-01

    Using an inflatable ballute system for aerocapture at planets and moons with atmospheres has the potential to provide significant performance benefits compared not only to traditional all propulsive capture, but also to aeroshell based aerocapture technologies. This paper discusses the characteristics of entry trajectories for ballute aerocapture at Neptune. These trajectories are the first steps in a larger systems analysis effort that is underway to characterize and optimize the performance of a ballute aerocapture system for future missions not only at Neptune, but also the other bodies with atmospheres.

  17. Aerocapture Systems Analysis for a Neptune Mission

    NASA Technical Reports Server (NTRS)

    Lockwood, Mary Kae; Edquist, Karl T.; Starr, Brett R.; Hollis, Brian R.; Hrinda, Glenn A.; Bailey, Robert W.; Hall, Jeffery L.; Spilker, Thomas R.; Noca, Muriel A.; O'Kongo, N.

    2006-01-01

    A Systems Analysis was completed to determine the feasibility, benefit and risk of an aeroshell aerocapture system for Neptune and to identify technology gaps and technology performance goals. The systems analysis includes the following disciplines: science; mission design; aeroshell configuration; interplanetary navigation analyses; atmosphere modeling; computational fluid dynamics for aerodynamic performance and aeroheating environment; stability analyses; guidance development; atmospheric flight simulation; thermal protection system design; mass properties; structures; spacecraft design and packaging; and mass sensitivities. Results show that aerocapture is feasible and performance is adequate for the Neptune mission. Aerocapture can deliver 1.4 times more mass to Neptune orbit than an all-propulsive system for the same launch vehicle and results in a 3-4 year reduction in trip time compared to all-propulsive systems. Enabling technologies for this mission include TPS manufacturing; and aerothermodynamic methods for determining coupled 3-D convection, radiation and ablation aeroheating rates and loads.

  18. Aeroshell Design Techniques for Aerocapture Entry Vehicles

    NASA Technical Reports Server (NTRS)

    Dyke, R. Eric; Hrinda, Glenn A.

    2004-01-01

    A major goal of NASA s In-Space Propulsion Program is to shorten trip times for scientific planetary missions. To meet this challenge arrival speeds will increase, requiring significant braking for orbit insertion, and thus increased deceleration propellant mass that may exceed launch lift capabilities. A technology called aerocapture has been developed to expand the mission potential of exploratory probes destined for planets with suitable atmospheres. Aerocapture inserts a probe into planetary orbit via a single pass through the atmosphere using the probe s aeroshell drag to reduce velocity. The benefit of an aerocapture maneuver is a large reduction in propellant mass that may result in smaller, less costly missions and reduced mission cruise times. The methodology used to design rigid aerocapture aeroshells will be presented with an emphasis on a new systems tool under development. Current methods for fast, efficient evaluations of structural systems for exploratory vehicles to planets and moons within our solar system have been under development within NASA having limited success. Many systems tools that have been attempted applied structural mass estimation techniques based on historical data and curve fitting techniques that are difficult and cumbersome to apply to new vehicle concepts and missions. The resulting vehicle aeroshell mass may be incorrectly estimated or have high margins included to account for uncertainty. This new tool will reduce the guesswork previously found in conceptual aeroshell mass estimations.

  19. Analytical guidance law development for aerocapture at Mars

    NASA Technical Reports Server (NTRS)

    Calise, A. J.

    1992-01-01

    During the first part of this reporting period research has concentrated on performing a detailed evaluation, to zero order, of the guidance algorithm developed in the first period taking the numerical approach developed in the third period. A zero order matched asymptotic expansion (MAE) solution that closely satisfies a set of 6 implicit equations in 6 unknowns to an accuracy of 10(exp -10), was evaluated. Guidance law implementation entails treating the current state as a new initial state and repetitively solving the MAE problem to obtain the feedback controls. A zero order guided solution was evaluated and compared with optimal solution that was obtained by numerical methods. Numerical experience shows that the zero order guided solution is close to optimal solution, and that the zero order MAE outer solution plays a critical role in accounting for the variations in Loh's term near the exit phase of the maneuver. However, the deficiency that remains in several of the critical variables indicates the need for a first order correction. During the second part of this period, methods for computing a first order correction were explored.

  20. Atmospheric effects on Martian aerocapture

    NASA Technical Reports Server (NTRS)

    Ess, Robert H.

    1990-01-01

    A preliminary study of the effects of the atmosphere on Martian aerocapture has been completed at NASA-Johnson. Nominal cases were defined and several types of density dispersions utilized to show the effect of L/D ratio on aerocapture performance. Both open and closed loop three-degree-of-freedom simulations were developed. The open loop work demonstrated the reduction of the aerocapture corridor in the presence of density biases and shears. Closed loop runs were studied in the presence of shear-biases where the aerocapture trajectory was divided into three regions or phases. Each phase independently had a nominal density or a dispersed + 100 percent density. Two phase combinations were found to cause aerocapture failures with the three L/Ds considered: 0.3, 0.7, 1.0. There is a significant improvement in aerocapture performance as the L/D is increased from 0.3 to 0.7, but a much smaller increase in performance as the L/D is increased from 0.7 to 1.0. Based on current knowledge of the Martian atmosphere, a minimum L/D of 0.7 is recommended for early Mars missions.

  1. Demonstration of an Aerocapture GN and C System Through Hardware-in-the-Loop Simulations

    NASA Technical Reports Server (NTRS)

    Masciarelli, James; Deppen, Jennifer; Bladt, Jeff; Fleck, Jeff; Lawson, Dave

    2010-01-01

    Aerocapture is an orbit insertion maneuver in which a spacecraft flies through a planetary atmosphere one time using drag force to decelerate and effect a hyperbolic to elliptical orbit change. Aerocapture employs a feedback Guidance, Navigation, and Control (GN&C) system to deliver the spacecraft into a precise postatmospheric orbit despite the uncertainties inherent in planetary atmosphere knowledge, entry targeting and aerodynamic predictions. Only small amounts of propellant are required for attitude control and orbit adjustments, thereby providing mass savings of hundreds to thousands of kilograms over conventional all-propulsive techniques. The Analytic Predictor Corrector (APC) guidance algorithm has been developed to steer the vehicle through the aerocapture maneuver using bank angle control. Through funding provided by NASA's In-Space Propulsion Technology Program, the operation of an aerocapture GN&C system has been demonstrated in high-fidelity simulations that include real-time hardware in the loop, thus increasing the Technology Readiness Level (TRL) of aerocapture GN&C. First, a non-real-time (NRT), 6-DOF trajectory simulation was developed for the aerocapture trajectory. The simulation included vehicle dynamics, gravity model, atmosphere model, aerodynamics model, inertial measurement unit (IMU) model, attitude control thruster torque models, and GN&C algorithms (including the APC aerocapture guidance). The simulation used the vehicle and mission parameters from the ST-9 mission. A 2000 case Monte Carlo simulation was performed and results show an aerocapture success rate of greater than 99.7%, greater than 95% of total delta-V required for orbit insertion is provided by aerodynamic drag, and post-aerocapture orbit plane wedge angle error is less than 0.5 deg (3-sigma). Then a real-time (RT), 6-DOF simulation for the aerocapture trajectory was developed which demonstrated the guidance software executing on a flight-like computer, interfacing with a

  2. Aerocapture Systems Analysis for a Titan Mission

    NASA Technical Reports Server (NTRS)

    Lockwood, Mary K.; Queen, Eric M.; Way, David W.; Powell, Richard W.; Edquist, Karl; Starr, Brett W.; Hollis, Brian R.; Zoby, E. Vincent; Hrinda, Glenn A.; Bailey, Robert W.

    2006-01-01

    Performance projections for aerocapture show a vehicle mass savings of between 40 and 80%, dependent on destination, for an aerocapture vehicle compared to an all-propulsive chemical vehicle. In addition aerocapture is applicable to multiple planetary exploration destinations of interest to NASA. The 2001 NASA In-Space Propulsion Program (ISP) technology prioritization effort identified aerocapture as one of the top three propulsion technologies for solar system exploration missions. An additional finding was that aerocapture needed a better system definition and that supporting technology gaps needed to be identified. Consequently, the ISP program sponsored an aerocapture systems analysis effort that was completed in 2002. The focus of the effort was on aerocapture at Titan with a rigid aeroshell system. Titan was selected as the initial destination for the study due to potential interest in a follow-on mission to Cassini/Huygens. Aerocapture is feasible, and the performance is adequate, for the Titan mission and it can deliver 2.4 times more mass to Titan than an all-propulsive system for the same launch vehicle.

  3. Atmospheric Models for Aerocapture

    NASA Technical Reports Server (NTRS)

    Justus, C. G.; Duvall, Aleta L.; Keller, Vernon W.

    2004-01-01

    There are eight destinations in the solar System with sufficient atmosphere for aerocapture to be a viable aeroassist option - Venus, Earth, Mars, Jupiter, Saturn and its moon Titan, Uranus, and Neptune. Engineering-level atmospheric models for four of these targets (Earth, Mars, Titan, and Neptune) have been developed for NASA to support systems analysis studies of potential future aerocapture missions. Development of a similar atmospheric model for Venus has recently commenced. An important capability of all of these models is their ability to simulate quasi-random density perturbations for Monte Carlo analyses in developing guidance, navigation and control algorithm, and for thermal systems design. Similarities and differences among these atmospheric models are presented, with emphasis on the recently developed Neptune model and on planned characteristics of the Venus model. Example applications for aerocapture are also presented and illustrated. Recent updates to the Titan atmospheric model are discussed, in anticipation of applications for trajectory and atmospheric reconstruct of Huygens Probe entry at Titan.

  4. Guidance Trade-off for Aerocapture Missions

    NASA Astrophysics Data System (ADS)

    Vernis, P.; Gelly, G.; Ferreira, E.; da Costa, R.; Ortega, G.

    In the very late 90's, EADS-ST began home funded studies on aerocapture problems. The objectives of these studies were at that time to prepare a possible cooperation within the NASA/Cnes MSR-Orbiter program by investigating this new orbital insertion technique studying different algorithmic solutions from a guidance point of view. According to these preliminary studies, EADS-ST was retained in 2002 by ESA to study insertion techniques such as aerocapture, aero-gravity assist or aerobraking techniques within the frame of Technological Research Program able to bring solutions to Aurora program. In the frame of the ATPE (Aeroassist Technologies for Planetary Exploration) TRP program, EADS-ST, led by Astrium-Gmbh (now part of EADS-ST), developed and implemented an efficient and simple guidance scheme able to cope with mission requirements for aerocapture on Mars, Venus or the Earth: the Feedback Trajectory Control, or FTC. The development of this guidance scheme was made according to a preliminary trade-off analysis using different guidance schemes. Among those ones was an original predictor-corrector guidance scheme, already analyzed within the frame of the MSR-O mission. But, the FTC algoritm was prefered because of its good results and high simplicity. This paper presents an upgrade of the original Apoapsis Predictor, or AP, with the improvement of its robustness woth respect to off-nomonal flight conditions and its process simplification. A new trade-off analysis is then detailed on a Mars Sample return mission.

  5. Blended control, predictor-corrector guidance algorithm: an enabling technology for Mars aerocapture.

    PubMed

    Jits, Roman Y; Walberg, Gerald D

    2004-03-01

    A guidance scheme designed for coping with significant dispersion in the vehicle's state and atmospheric conditions is presented. In order to expand the flyable aerocapture envelope, control of the vehicle is realized through bank angle and angle-of-attack modulation. Thus, blended control of the vehicle is achieved, where the lateral and vertical motions of the vehicle are decoupled. The overall implementation approach is described, together with the guidance algorithm macrologic and structure. Results of guidance algorithm tests in the presence of various single and multiple off-nominal conditions are presented and discussed.

  6. Systems Analysis for a Venus Aerocapture Mission

    NASA Technical Reports Server (NTRS)

    Lockwood, Mary Kae; Starr, Brett R.; Paulson, John W., Jr.; Kontinos, Dean A.; Chen, Y. K.; Laub, Bernard; Olejniczak, Joseph; Wright, Michael J.; Takashima, Naruhisa; Justus, Carl G.

    2006-01-01

    Previous high level analysis has indicated that significant mass savings may be possible for planetary science missions if aerocapture is employed to place a spacecraft in orbit. In 2001 the In-Space Propulsion program identified aerocapture as one of the top three propulsion technologies for planetary exploration but that higher fidelity analysis was required to verify the favorable results and to determine if any supporting technology gaps exist that would enable or enhance aerocapture missions. A series of three studies has been conducted to assess, from an overall system point of view, the merit of using aerocapture at Titan, Neptune and Venus. These were chosen as representative of a moon with an atmosphere, an outer giant gas planet and an inner planet. The Venus mission, based on desirable science from plans for Solar System Exploration and Principal Investigator proposals, to place a spacecraft in a 300km polar orbit was examined and the details of the study are presented in this paper.

  7. Aerocapture Guidance Algorithm Comparison Campaign

    NASA Technical Reports Server (NTRS)

    Rousseau, Stephane; Perot, Etienne; Graves, Claude; Masciarelli, James P.; Queen, Eric

    2002-01-01

    The aerocapture is a promising technique for the future human interplanetary missions. The Mars Sample Return was initially based on an insertion by aerocapture. A CNES orbiter Mars Premier was developed to demonstrate this concept. Mainly due to budget constraints, the aerocapture was cancelled for the French orbiter. A lot of studies were achieved during the three last years to develop and test different guidance algorithms (APC, EC, TPC, NPC). This work was shared between CNES and NASA, with a fruitful joint working group. To finish this study an evaluation campaign has been performed to test the different algorithms. The objective was to assess the robustness, accuracy, capability to limit the load, and the complexity of each algorithm. A simulation campaign has been specified and performed by CNES, with a similar activity on the NASA side to confirm the CNES results. This evaluation has demonstrated that the numerical guidance principal is not competitive compared to the analytical concepts. All the other algorithms are well adapted to guaranty the success of the aerocapture. The TPC appears to be the more robust, the APC the more accurate, and the EC appears to be a good compromise.

  8. Generic aerocapture atmospheric entry study, volume 1

    NASA Technical Reports Server (NTRS)

    1980-01-01

    An atmospheric entry study to fine a generic aerocapture vehicle capable of missions to Mars, Saturn, and Uranus is reported. A single external geometry was developed through atmospheric entry simulations. Aerocapture is a system design concept which uses an aerodynamically controlled atmospheric entry to provide the necessary velocity depletion to capture payloads into planetary orbit. Design concepts are presented which provide the control accuracy required while giving thermal protection for the mission payload. The system design concepts consist of the following elements: (1) an extendable biconic aerodynamic configuration with lift to drag ratio between 1.0 and 2.0; (2) roll control system concepts to control aerodynamic lift and disturbance torques; (3) aeroshell design concepts capable of meeting dynamic pressure loads during aerocapture; and (4) entry thermal protection system design concepts to meet thermodynamic loads during aerocapture.

  9. Development of a blended-control, predictor-corrector guidance algorithm for a crewed Mars aerocapture vehicle

    NASA Astrophysics Data System (ADS)

    Jits, Roman Yuryevich

    A robust blended-control guidance system for a crewed Mars aerocapture vehicle is developed. The key features of its guidance algorithm are the use of the both bank-angle and angle-of-attack modulation to control the aerobraking vehicle, and the use of multiple controls (sequenced pairs of bank-angles and angles-of-attack) within its numeric predictor-corrector targeting routine. The guidance algorithm macrologic is based on extensive open loop trajectory analyses, described in the present research, which led to the selection of a blended-control scheme. A heuristic approach to recover from situations where no converged guidance solution could be found by the numeric predictor-corrector is implemented in the guidance algorithm, and has been successfully demonstrated in a large number of test runs. In this research both the outer and inner loop of the guidance and control system employ the POST (Program to Optimize Simulated Trajectories) computer code as the basic simulation module. At each guidance update, the inner loop solves the rigorous three-dimensional equations of motion and computes the control (bank-angle and angle-of-attack) sequence that is required to meet the required atmospheric exit conditions. Throughout the aerocapture trajectory, the guidance algorithm modifies this control sequence computed by the inner loop, and generates commanded controls for the vehicle, which, when implemented by the outer loop, meet an imposed g-load constraint of 5 Earth g's and compensate for unexpected off-nominal conditions. This blended-control, predictor-corrector guidance algorithm has been successfully developed, implemented and tested and has been shown to be capable of meeting the prescribed g-load constraint and guiding the vehicle to the desired exit conditions for a range of off-nominal factors much wider than those which could be accommodated by prior algorithms and bank-angle-only guidance.

  10. Using Autonomously-Controlled Aerocapture to Achieve High-Priority Science

    NASA Astrophysics Data System (ADS)

    Spilker, T. R.; Hall, J. L.

    2006-05-01

    Aerocapture is a means of inserting a spacecraft into orbit at a planetary body with a substantial atmosphere, from a hyperbolic approach, via atmospheric drag in that atmosphere. Compared to current-practice propulsive insertion systems, it offers large reductions in the mass spent on orbit insertion, making available significantly more mass for science instruments and direct instrument support systems such as telecommunications. This yields much greater science return for a given launch mass. In some cases the gain in science return is so significant it enables the missions. The aerocapture maneuver itself, which involves hypersonic, guided flight through an imperfectly known and variable planetary atmosphere, critically depends on autonomous systems to guide the craft's flight path to a controlled exit at a pre-determined, much-reduced target speed and target direction. For the past five years NASA funded its Aerocapture Systems Analysis Team to conduct high-fidelity studies of aerocapture applications to destinations of high priority for planetary and solar system science. These studies aimed at deriving various aerocapture system parameters and performance figures for each destination, and to highlight technology developments needed to provide the requisite system parameters and performance. Significant progress has been made, to the point that aerocapture is fully ready for a flight demonstration, and soon after that implementation at some of the less-demanding destinations. Autonomous control algorithms of sufficient accuracy and speed are now available for a flight test, as is the hardware needed for computation, navigation, control, and thermal protection. Candidate destinations for which relatively low-performance systems are sufficient include Saturn's moon Titan, Venus, and Mars, while trips to more demanding destinations, such as Uranus, Neptune, Saturn, and possibly even and Pluto and Neptune's moon Triton, would require higher-performance systems

  11. Mission Trades for Aerocapture at Neptune

    NASA Technical Reports Server (NTRS)

    Noca, Muriel A.; Bailey, Robert W.

    2004-01-01

    A detailed Neptune aerocapture systems analysis and spacecraft design study was performed to improve our understanding of the techonology requirement for such a hard mission. The primary objective was to engineer a point design based on blunt body aeroshell technology and quantitatively assess feasibility and performance. This paper reviews the launch vehicle, propulsion, and trajectory options to reach Neptune in the 2015-2020 time frame using aerocapture and all-propulsive vehicles. It establishes the range of entry conditions that would be consistent with delivering a - 1900 kg total entry vehicle maximum expected mass to Neptune including a - 790 kg orbiter maximum expected mass to the science orbit. Two Neptune probes would be also be delivered prior to the aerocapture maneuver. Results show that inertial entry velocities in the range of 28 to 30 km/s are to be expected for chemical and solar electric propulsion options with several gravity assists (combinations of Venus, Earth and Jupiter gravity assists). Trip times range from approximately 10-11 years for aerocapture orbiters to 15 years for all-propulsive vehicles. This paper shows that the use of aerocapture enables this mission given the payload to deliver around Neptune compared to an all-propulsive orbit insertion approach. However, an all-propulsive chemical insertion option is possible for lower payload masses than the one needed for this science mission. Both approaches require a Delta IV heavy class launch vehicle.

  12. Outer Planet Mission Studies Neptune Aerocapture

    NASA Technical Reports Server (NTRS)

    Wercinski, Paul F.; Langhoff, Steven R. (Technical Monitor)

    1997-01-01

    Current and previous studies of orbiter missions to the outer planets have clearly identified high-energy aerocapture as a critical and enabling technology. Aerocapture involves the use of aerodynamic lift to fly a trajectory through a planet's atmosphere to sufficiently decelerate an entry vehicle to capture into planetary orbit. In the past, numerous studies of different configurations of lifting entry vehicles were studied for various planetary orbiter missions which identified aerocapture as a feasible concept yet complex and technically challenging. In order to determine the feasibility of high-speed aerocapture at the outer planets, an accurate trajectory simulation of the flight vehicle is the critical first step in the proposed research. Vehicle response to aerodynamic loading must be predicted accurately in the trajectory simulations. For several Neptune orbiter missions currently under study at the Jet Propulsion Laboratory (JPL), entry velocities relative to the rotating atmosphere ranging from 25 to 30 km/sec, are to be expected. Preliminary trajectory analysis has identified the various flow regimes the entry vehicle is expected to fly in the 8 1% H2 and 19% He atmosphere of Neptune. The size and mass of the vehicle are also determined by the launch vehicle constraints and orbiter spacecraft requirements. For a given baseline arrival conditions of an inertial entry velocity of 28 km/sec and an entry mass of 400 kg, a medium lift (L/D = 1), axisymmetric biconic shaped vehicle was selected in order to satisfy entry corridor width requirements expected for Neptune aerocapture. The analysis summarized in this study indicates that a biconic entry vehicle is a feasible concept for a Neptune aerocapture orbiter mission. The preliminary entry trajectory simulations has demonstrated adequate entry corridor control authority. Furthermore, estimates of the stagnation point heating environment has enabled the preliminary selection of candidate lightweight ceramic

  13. Trailing Ballute Aerocapture: Concept and Feasibility Assessment

    NASA Technical Reports Server (NTRS)

    Miller, Kevin L.; Gulick, Doug; Lewis, Jake; Trochman, Bill; Stein, Jim; Lyons, Daniel T.; Wilmoth, Richard G.

    2003-01-01

    Trailing Ballute Aerocapture offers the potential to obtain orbit insertion around a planetary body at a fraction of the mass of traditional methods. This allows for lower costs for launch, faster flight times and additional mass available for science payloads. The technique involves an inflated ballute (balloon-parachute) that provides aerodynamic drag area for use in the atmosphere of a planetary body to provide for orbit insertion in a relatively benign heating environment. To account for atmospheric, navigation and other uncertainties, the ballute is oversized and detached once the desired velocity change (Delta V) has been achieved. Analysis and trades have been performed for the purpose of assessing the feasibility of the technique including aerophysics, material assessments, inflation system and deployment sequence and dynamics, configuration trades, ballute separation and trajectory analysis. Outlined is the technology development required for advancing the technique to a level that would allow it to be viable for use in space exploration missions.

  14. Structural Design for a Neptune Aerocapture Mission

    NASA Technical Reports Server (NTRS)

    Dyke, R. Eric; Hrinda, Glenn A.

    2004-01-01

    A multi-center study was conducted in 2003 to assess the feasibility of and technology requirements for using aerocapture to insert a scientific platform into orbit around Neptune. The aerocapture technique offers a potential method of greatly reducing orbiter mass and thus total spacecraft launch mass by minimizing the required propulsion system mass. This study involved the collaborative efforts of personnel from Langley Research Center (LaRC), Johnson Space Flight Center (JSFC), Marshall Space Flight Center (MSFC), Ames Research Center (ARC), and the Jet Propulsion Laboratory (JPL). One aspect of this effort was the structural design of the full spacecraft configuration, including the ellipsled aerocapture orbiter and the in-space solar electric propulsion (SEP) module/cruise stage. This paper will discuss the functional and structural requirements for each of these components, some of the design trades leading to the final configuration, the loading environments, and the analysis methods used to ensure structural integrity. It will also highlight the design and structural challenges faced while trying to integrate all the mission requirements. Component sizes, materials, construction methods and analytical results, including masses and natural frequencies, will be presented, showing the feasibility of the resulting design for use in a Neptune aerocapture mission. Lastly, results of a post-study structural mass optimization effort on the ellipsled will be discussed, showing potential mass savings and their influence on structural strength and stiffness

  15. Aerocapture navigation at Neptune

    NASA Technical Reports Server (NTRS)

    Haw, Robert J.

    2003-01-01

    A proposed Neptune orbiter Aerocapture mission will use solar electric propulsion to send an orbiter to Neptune. Navigation feasibility of direct-entry aerocapture for orbit insertion at Neptune is shown. The navigation strategy baselines optical imaging and (delta)VLBI measurement in order to satisfy the flight system's atmosphere entry flight path angle, which is targeted to enter Neptune with an entry flight path angle of -11.6 . Error bars on the entry flight path angle of plus/minus0.55 (3(sigma)) are proposed. This requirement can be satisfied with a data cutoff 3.2 days prior to arrival. There is some margin in the arrival template to tighten (i.e. reduce) the entry corridor either by scheduling a data cutoff closer to Neptune or alternatively, reducing uncertainties by increasing the fidelity of the optical navigation camera.

  16. Modeling, Simulation and Visualization of Aerocapture

    NASA Astrophysics Data System (ADS)

    leszcynski, Zigmond V.

    1998-12-01

    A vehicle travelling from Earth to another planet on a ballistic trajectory approaches that planet at hyperbolic velocity. Upon arrival, the vehicle must significantly reduce its speed for orbit insertion. Traditionally, this deceleration has been achieved by propulsive capture, which consumes a large amount of propellant. Aerocapture offers a more fuel-efficient alternative by exploiting vehicular drag in the planet's atmosphere. However, this technique generates extreme heat, necessitating a special thermal protection shield (TPS). Performing a trade study between the propellant mass required for propulsive capture and the TPS mass required for aerocapture can help determine which method is more desirable for a particular mission. The research objective of this thesis was to analyze aerocapture dynamics for the advancement of this trade study process. The result was an aerocapture simulation tool (ACAPS) developed in MATLAB with SIMULINK, emphasizing code validation, upgradeability, user-friendliness and trajectory visualization. The current version, ACAPS 1.1, is a three- degrees-of-freedom point mass simulation model that incorporates a look-up table for the Mars atmosphere. ACAPS is expected to supplement the National Aeronautics and Space Administration (NASA) Jet Propulsion Laboratory (JPL) Project Design Center (PDC) toolkit as preliminary design software for the Mars 2005 Sample Return (MSR) Mission, Mars 2007 Mission, Mars Micromissions, Neptune/Triton Mission, and Human Mars Mission.

  17. Application of a Fully Numerical Guidance to Mars Aerocapture

    NASA Technical Reports Server (NTRS)

    Matz, Daniel A.; Lu, Ping; Mendeck, Gavin F.; Sostaric, Ronald R.

    2017-01-01

    An advanced guidance algorithm, Fully Numerical Predictor-corrector Aerocapture Guidance (FNPAG), has been developed to perform aerocapture maneuvers in an optimal manner. It is a model-based, numerical guidance that benefits from requiring few adjustments across a variety of different hypersonic vehicle lift-to-drag ratios, ballistic co-efficients, and atmospheric entry conditions. In this paper, FNPAG is first applied to the Mars Rigid Vehicle (MRV) mid lift-to-drag ratio concept. Then the study is generalized to a design map of potential Mars aerocapture missions and vehicles, ranging from the scale and requirements of recent robotic to potential human and precursor missions. The design map results show the versatility of FNPAG and provide insight for the design of Mars aerocapture vehicles and atmospheric entry conditions to achieve desired performance.

  18. AEROELASTIC SIMULATION TOOL FOR INFLATABLE BALLUTE AEROCAPTURE

    NASA Technical Reports Server (NTRS)

    Liever, P. A.; Sheta, E. F.; Habchi, S. D.

    2006-01-01

    A multidisciplinary analysis tool is under development for predicting the impact of aeroelastic effects on the functionality of inflatable ballute aeroassist vehicles in both the continuum and rarefied flow regimes. High-fidelity modules for continuum and rarefied aerodynamics, structural dynamics, heat transfer, and computational grid deformation are coupled in an integrated multi-physics, multi-disciplinary computing environment. This flexible and extensible approach allows the integration of state-of-the-art, stand-alone NASA and industry leading continuum and rarefied flow solvers and structural analysis codes into a computing environment in which the modules can run concurrently with synchronized data transfer. Coupled fluid-structure continuum flow demonstrations were conducted on a clamped ballute configuration. The feasibility of implementing a DSMC flow solver in the simulation framework was demonstrated, and loosely coupled rarefied flow aeroelastic demonstrations were performed. A NASA and industry technology survey identified CFD, DSMC and structural analysis codes capable of modeling non-linear shape and material response of thin-film inflated aeroshells. The simulation technology will find direct and immediate applications with NASA and industry in ongoing aerocapture technology development programs.

  19. Assessing the Relative Risk of Aerocapture Using Probabalistic Risk Assessment

    NASA Technical Reports Server (NTRS)

    Percy, Thomas K.; Bright, Ellanee; Torres, Abel O.

    2005-01-01

    A recent study performed for the Aerocapture Technology Area in the In-Space Propulsion Technology Projects Office at the Marshall Space Flight Center investigated the relative risk of various capture techniques for Mars missions. Aerocapture has been proposed as a possible capture technique for future Mars missions but has been perceived by many in the community as a higher risk option as compared to aerobraking and propulsive capture. By performing a probabilistic risk assessment on aerocapture, aerobraking and propulsive capture, a comparison was made to uncover the projected relative risks of these three maneuvers. For mission planners, this knowledge will allow them to decide if the mass savings provided by aerocapture warrant any incremental risk exposure. The study focuses on a Mars Sample Return mission currently under investigation at the Jet Propulsion Laboratory (JPL). In each case (propulsive, aerobraking and aerocapture), the Earth return vehicle is inserted into Martian orbit by one of the three techniques being investigated. A baseline spacecraft was established through initial sizing exercises performed by JPL's Team X. While Team X design results provided the baseline and common thread between the spacecraft, in each case the Team X results were supplemented by historical data as needed. Propulsion, thermal protection, guidance, navigation and control, software, solar arrays, navigation and targeting and atmospheric prediction were investigated. A qualitative assessment of human reliability was also included. Results show that different risk drivers contribute significantly to each capture technique. For aerocapture, the significant drivers include propulsion system failures and atmospheric prediction errors. Software and guidance hardware contribute the most to aerobraking risk. Propulsive capture risk is mainly driven by anomalous solar array degradation and propulsion system failures. While each subsystem contributes differently to the risk of

  20. Inflatable Aerocapture Decelerators for Mars Orbiters

    NASA Technical Reports Server (NTRS)

    Brown, Glen J.; Lingard, J. Stephen; Darley, Matthew G.; Underwood, John C.

    2007-01-01

    A multi-disciplinary research program was recently completed, sponsored by NASA Marshall Space Flight Center, on the subject of aerocapture of spacecraft weighing up to 5 metric tons at Mars. Heavier spacecraft will require deployable drag area beyond the dimensional limits of current and planned launch fairings. This research focuses on the approach of lightweight inflatable decelerators constructed with thin films, using fiber reinforcement and having a temperature limitation of 500 C. Trajectory analysis defines trajectories for a range of low ballistic coefficients for which convective heat flux is compatible with the material set. Fluid-Structure Interaction (FSI) tools are expanded to include the rarified flow regime. Several non-symmetrical configurations are evaluated for their capability to develop lift as part of the necessary trajectory control strategy. Manufacturing technology is developed for 3-D stretch forming of polyimide films and for tailored fiber reinforcement of thin films. Finally, the mass of the decelerator is estimated and compared to the mass of a traditional rigid aeroshell.

  1. Aerocapture Inflatable Decelerator (AID)

    NASA Technical Reports Server (NTRS)

    Reza, Sajjad

    2007-01-01

    Forward Attached Inflatable Decelerators, more commonly known as inflatable aeroshells, provide an effective, cost efficient means of decelerating spacecrafts by using atmospheric drag for aerocapture or planetary entry instead of conventional liquid propulsion deceleration systems. Entry into planetary atmospheres results in significant heating and aerodynamic pressures which stress aeroshell systems to their useful limits. Incorporation of lightweight inflatable decelerator surfaces with increased surface-area footprints provides the opportunity to reduce heat flux and induced temperatures, while increasing the payload mass fraction. Furthermore, inflatable aeroshell decelerators provide the needed deceleration at considerably higher altitudes and Mach numbers when compared with conventional rigid aeroshell entry systems. Inflatable aeroshells also provide for stowage in a compact space, with subsequent deployment of a large-area, lightweight heatshield to survive entry heating. Use of a deployable heatshield decelerator not only enables an increase in the spacecraft payload mass fraction and but may also eliminate the need for a spacecraft backshell and cruise stage. This document is the viewgraph slides for the paper's presentation.

  2. An onboard navigation system which fulfills Mars aerocapture guidance requirements

    NASA Technical Reports Server (NTRS)

    Brand, Timothy J.; Fuhry, Douglas P.; Shepperd, Stanley W.

    1989-01-01

    The development of a candidate autonomous onboard Mars approach navigation scheme capable of supporting aerocapture into Mars orbit is discussed. An aerocapture guidance and navigation system which can run independently of the preaerocapture navigation was used to define a preliminary set of accuracy requirements at entry interface. These requirements are used to evaluate the proposed preaerocapture navigation scheme. This scheme uses optical sightings on Deimos with a star tracker and an inertial measurement unit for instrumentation as a source for navigation nformation. Preliminary results suggest that the approach will adequately support aerocaputre into Mars orbit.

  3. Atmospheric Models for Mars Aerocapture

    NASA Technical Reports Server (NTRS)

    Justus, C. G.; Duvall, Aleta; Keller, Vernon W.

    2005-01-01

    level Mars atmospheric model. Applications include systems design, performance analysis, and operations planning for aerobraking, entry descent and landing, and aerocapture. Typical Mars aerocapture periapsis altitudes (for systems with rigid- aeroshell heat shields) are about 50 km. This altitude is above the 0-40 km height range covered by Mars Global Surveyor Thermal Emission Spectrometer (TES) nadir observations. Recently, TES limb sounding data have been made available, spanning more than two Mars years (more than 200,000 data profiles) with altitude coverage up to about 60 km, well within the height range of interest for aerocapture. Results are presented comparing Mars-GRAM atmospheric density with densities from TES nadir and limb sounding observations. A new Mars-GRAM feature is described which allows individual TES nadir or limb profiles to be extracted from the large TES databases, and to be used as an optional replacement for standard Mars-GRAM background (climatology) conditions. For Monte-Carlo applications such as aerocapture guidance and control studies, Mars-GRAM perturbations are available using these TES profile background conditions.

  4. The Status of Spacecraft Bus and Platform Technology Development under the NASA In-Space Propulsion Technology Program

    NASA Technical Reports Server (NTRS)

    Anderson, David; Pencil, Eric J.; Glaab, Louis; Falck, Robert D.; Dankanich, John

    2013-01-01

    NASA's In-Space Propulsion Technology (ISPT) program has been developing technologies for lowering the cost of planetary science missions. The technology areas include electric propulsion technologies, spacecraft bus technologies, entry vehicle technologies, and design tools for systems analysis and mission trajectories. The electric propulsion technologies include critical components of both gridded and non-gridded ion propulsion systems. The spacecraft bus technologies under development include an ultra-lightweight tank (ULTT) and advanced xenon feed system (AXFS). The entry vehicle technologies include the development of a multi-mission entry vehicle, mission design tools and aerocapture. The design tools under development include system analysis tools and mission trajectory design tools.

  5. Preliminary Assessment of a Neptune Aerocapture Mission Using an Integrated Design Tool

    NASA Technical Reports Server (NTRS)

    Gage, Peter J.; Wercinski, Paul F.

    1998-01-01

    Aerocapture is an efficient orbit insertion technique that uses the planet's atmosphere to decelerate an arriving spacecraft. With current technology and for vehicles of reasonable mass, it is the only technique that might deliver the high delta-V's required for insertion to orbits around the outer planets. Preliminary design studies for outer planet orbital missions must evaluate aerocapture strategies, and must therefore consider the coupling between vehicle geometry, aerodynamics, aerocapture trajectory, heating and thermal protection system mass. The analyses have been linked into an integrated design environment, with the critical parameters grouped in a global database. The designer is free to use single point evaluations, parametric variation, and numerical optimization to evaluate a range of vehicle shapes and insertion trajectories. The application of this design tool to a preliminary study for Neptune aerocapture has implications for the use of such computational environments for any atmospheric entry mission.

  6. Aerocapture - Guidance, navigation, and control

    NASA Astrophysics Data System (ADS)

    Mease, K. D.; Weidner, R. J.; Kechichian, J. A.; Wood, L. J.; Cruz, M. I.

    1982-08-01

    Aerocapture is a concept for inserting a spacecraft into orbit about a target planet. The energy required for orbit insertion is obtained from natural resources present at or near the target body, thereby reducing the amount of propellant which must be carried onboard. Specifically, the transfer from a hyperbolic flyby trajectory to a desired bound orbit is effected by aerodynamic lift and drag forces acting on the spacecraft during controlled flight through the atmosphere of either the target planet or a nearby satellite. A survey is provided of the trajectory guidance, navigation, and control aspects of aerocapture, and a summary is given of the results of a number of preliminary studies concerning certain of these aspects. The investigation has additional significance in connection with the current interest in aeroassisted orbital transfer vehicles, which may be used in conjunction with the Space Shuttle.

  7. Aerocapture - Guidance, navigation, and control

    NASA Technical Reports Server (NTRS)

    Mease, K. D.; Weidner, R. J.; Kechichian, J. A.; Wood, L. J.; Cruz, M. I.

    1982-01-01

    Aerocapture is a concept for inserting a spacecraft into orbit about a target planet. The energy required for orbit insertion is obtained from natural resources present at or near the target body, thereby reducing the amount of propellant which must be carried onboard. Specifically, the transfer from a hyperbolic flyby trajectory to a desired bound orbit is effected by aerodynamic lift and drag forces acting on the spacecraft during controlled flight through the atmosphere of either the target planet or a nearby satellite. A survey is provided of the trajectory guidance, navigation, and control aspects of aerocapture, and a summary is given of the results of a number of preliminary studies concerning certain of these aspects. The investigation has additional significance in connection with the current interest in aeroassisted orbital transfer vehicles, which may be used in conjunction with the Space Shuttle.

  8. New TPS materials for aerocapture

    NASA Astrophysics Data System (ADS)

    Laub, Bernard

    2002-01-01

    Many planetary probes, landers and aerocapture concepts are conceived for entry trajectories where peak convective heat flux is in the range 150-400 W/cm2. This may be too severe an environment for either reusable or low-density ablative materials. The high-density ablatives will work in such environments but the associated TPS weight requirements can be prohibitive. Unfortunately, there are few, if any, well-understood materials that provide reliable, predictable ablative performance for the 150-400 W/cm2 regime while still providing weight efficient TPS solutions. JPL has recently been evaluating an Earth aerocapture demonstration at an entry velocity of ~10 km/s. TPS thickness and areal weight requirements were determined for current ablative TPS candidates (e.g., SLA-561V, PICA) where, for the large integrated heat loads associated with aerocapture, it is shown that some of these materials may not provide efficient thermal protection. A new concept, employing a low catalycity, high emissivity coating on a low-density ceramic tile is evaluated and shown to provide significant benefits for such missions. .

  9. Physiologically constrained aerocapture for manned Mars missions

    NASA Technical Reports Server (NTRS)

    Lyne, James Evans

    1992-01-01

    Aerobraking has been proposed as a critical technology for manned missions to Mars. The variety of mission architectures currently under consideration presents aerobrake designers with an enormous range of potential entry scenarios. Two of the most important considerations in the design of an aerobrake are the required control authority (lift-to-drag ratio) and the aerothermal environment which the vehicle will encounter. Therefore, this study examined the entry corridor width and stagnation-point heating rate and load for the entire range of probable entry velocities, lift-to-drag ratios, and ballistic coefficients for capture at both Earth and Mars. To accomplish this, a peak deceleration limit for the aerocapture maneuvers had to be established. Previous studies had used a variety of load limits without adequate proof of their validity. Existing physiological and space flight data were examined, and it was concluded that a deceleration limit of 5 G was appropriate. When this load limit was applied, numerical studies showed that an aerobrake with an L/D of 0.3 could provide an entry corridor width of at least 1 degree for all Mars aerocaptures considered with entry velocities up to 9 km/s. If 10 km/s entries are required, an L/D of 0.4 to 0.5 would be necessary to maintain a corridor width of at least 1 degree. For Earth return aerocapture, a vehicle with an L/D of 0.4 to 0.5 was found to provide a corridor width of 0.7 degree or more for all entry velocities up to 14.5 km/s. Aerodynamic convective heating calculations were performed assuming a fully catalytic, 'cold' wall; radiative heating was calculated assuming that the shock layer was in thermochemical equilibrium. Heating rates were low enough for selected entries at Mars that a radiatively cooled thermal protection system might be feasible, although an ablative material would be required for most scenarios. Earth return heating rates were generally more severe than those encountered by the Apollo vehicles

  10. Technology Development.

    ERIC Educational Resources Information Center

    Gomory, Ralph E.

    1983-01-01

    The evolutionary character and complexity of technological development is discussed, focusing on the steam engine and computer as examples. Additional topics include characteristics of science/technology, cultural factors in technological development, technology transfer, and problems in technological organization. (JN)

  11. Aerocapture Guidance and Performance at Mars for High-Mass Systems

    NASA Technical Reports Server (NTRS)

    Zumwalt, Carlie H.; Sostaric, Ronald r.; Westhelle, Carlos H.; Cianciolo, Alicia Dwyer

    2010-01-01

    The objective of this study is to understand the performance associated with using the aerocapture maneuver to slow high-mass systems from an Earth-approach trajectory into orbit around Mars. This work is done in conjunction with the Mars Entry Descent and Landing Systems Analysis (EDL-SA) task to explore candidate technologies necessary for development in order to land large-scale payloads on the surface of Mars. Among the technologies considered include hypersonic inflatable aerodynamic decelerators (HIADs) and rigid mid-lift to drag (L/D) aeroshells. Nominal aerocapture trajectories were developed for the mid-L/D aeroshell and two sizes of HIADs, and Monte Carlo analysis was completed to understand sensitivities to dispersions. Additionally, a study was completed in order to determine the size of the larger of the two HIADs which would maintain design constraints on peak heat rate and diameter. Results show that each of the three aeroshell designs studied is a viable option for landing high-mass payloads as none of the three exceed performance requirements.

  12. Neptune aerocapture mission and spacecraft design overview

    NASA Technical Reports Server (NTRS)

    Bailey, Robert W.; Hall, Jeff L.; Spliker, Tom R.; O'Kongo, Nora

    2004-01-01

    A detailed Neptune aerocapture systems analysis and spacecraft design study was performed as part of NASA's In-Space Propulsion Program. The primary objectives were to assess the feasibility of a spacecraft point design for a Neptune/Triton science mission. That uses aerocapture as the Neptune orbit insertion mechanism. This paper provides an overview of the science, mission and spacecraft design resulting from that study.

  13. Angle-of-Attack-Modulated Terminal Point Control for Neptune Aerocapture

    NASA Technical Reports Server (NTRS)

    Queen, Eric M.

    2004-01-01

    An aerocapture guidance algorithm based on a calculus of variations approach is developed, using angle of attack as the primary control variable. Bank angle is used as a secondary control to alleviate angle of attack extremes and to control inclination. The guidance equations are derived in detail. The controller has very small onboard computational requirements and is robust to atmospheric and aerodynamic dispersions. The algorithm is applied to aerocapture at Neptune. Three versions of the controller are considered with varying angle of attack authority. The three versions of the controller are evaluated using Monte Carlo simulations with expected dispersions.

  14. Aerocapture Guidance Performance for the Neptune Orbiter

    NASA Technical Reports Server (NTRS)

    Masciarelli, James P.; Westhelle, Carlos H.; Graves, Claude A.

    2004-01-01

    A performance evaluation of the Hybrid Predictor corrector Aerocapture Scheme (HYPAS) guidance algorithm for aerocapture at Neptune is presented in this paper for a Mission to Neptune and the Neptune moon Triton'. This mission has several challenges not experienced in previous aerocapture guidance assessments. These challengers are a very high Neptune arrival speed, atmospheric exit into a high energy orbit about Neptune, and a very high ballistic coefficient that results in a low altitude acceleration capability when combined with the aeroshell LD. The evaluation includes a definition of the entry corridor, a comparison to the theoretical optimum performance, and guidance responses to variations in atmospheric density, aerodynamic coefficients and flight path angle for various vehicle configurations (ballistic numbers). The benefits of utilizing angle-of-attack modulation in addition to bank angle modulation to improve flight performance is also discussed. The results show that despite large sensitivities in apoapsis targeting, the algorithm performs within the allocated AV budget for the Neptune mission bank angle only modulation. The addition of angle-of-attack modulation with as little as 5 degrees of amplitude significantly improves the scatter in final orbit apoapsis. Although the angle-of-attack modulation complicates the vehicle design, the performance enhancement reduces aerocapture risk and reduces the propellant consumption needed to reach the high energy target orbit for a conventional propulsion system.

  15. In-Space Propulsion Technologies for Robotic Exploration of the Solar System

    NASA Technical Reports Server (NTRS)

    Johnson, Les; Meyer, Rae Ann; Frame, Kyle

    2006-01-01

    Supporting NASA's Science Mission Directorate, the In-Space Propulsion Technology Program is developing the next generation of space propulsion technologies for robotic, deep-space exploration. Recent technological advancements and demonstrations of key, high-payoff propulsion technologies have been achieved and will be described. Technologies under development and test include aerocapture, solar electric propulsion, solar sail propulsion, and advanced chemical propulsion.

  16. Technology development.

    PubMed

    Gomory, R E

    1983-05-06

    In technology development significant advances are as often the result of a series of evolutionary steps as they are of breakthroughs. This is illustrated by the examples of the steam engine and the computer. Breakthroughs, such as the transistor, are relatively rare, and are often the result of the introduction of new knowledge coming from a quite different area. Technology development is often difficult to predict because of its complexity; practical considerations may far outweigh apparent scientific advantages, and cultural factors enter in at many levels. In a large technological organization problems exist in bringing scientific knowledge to bear on development, but much can be done to obviate these difficulties.

  17. Evaluation of an optimal aerocapture guidance algorithm for human Mars missions

    NASA Astrophysics Data System (ADS)

    Webb, Kyle

    Aeroassist guidance is concerned with providing steering commands to a vehicle flying through a planetary atmosphere in the form of an aerodynamic roll angle, or bank angle, which results in appropriate direction of the aerodynamic lift force so that the vehicle will safely and accurately reach its designated final condition. Aerocapture guidance is a particular subcategory of aeroassist guidance that involves atmospheric entry from an interplanetary transfer orbit, a guided flight through the atmosphere, and a final condition consisting of a post-atmospheric exit target orbit around the planet. Using aerocapture guidance to establish this target orbit can provide significant propellant mass savings when compared to traditional propulsive maneuvers. No current aerocapture guidance algorithms can ensure truly optimal performance in minimizing post-exit orbit insertion ?V requirements. This thesis investigates the development of a two-phase optimal aerocapture guidance algorithm. This closed-loop guidance algorithm uses a mathematically optimal bang-bang bank angle profile structure, in which a vehicle first flies with the lift vector pointed straight up, and then flies full lift-down until atmospheric exit. The optimal trajectory is found by determining the switching time between full lift-up and full lift-down flight. Results from testing the algorithm in a high-fidelity NASA simulation environment are presented and compared with results from existing state-of-the-art aerocapture guidance algorithms. These results show that the developed algorithm provides the robustness and adaptability of a numerical predictor-corrector guidance algorithm while demonstrating a significant reduction in ?V requirements compared to other existing algorithms.

  18. The Status of Spacecraft Bus and Platform Technology Development Under the NASA ISPT Program

    NASA Technical Reports Server (NTRS)

    Anderson, David; Munk, Michelle M.; Pencil, Eric; Dankanich, John; Glaab, Louis; Peterson, Todd

    2014-01-01

    The In-Space Propulsion Technology (ISPT) program is developing spacecraft bus and platform technologies that will enable or enhance NASA robotic science missions. The ISPT program is currently developing technology in three areas that include Propulsion System Technologies, Entry Vehicle Technologies, and Systems Mission Analysis. ISPTs propulsion technologies include: 1) NASAs Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system; 2) a Hall-effect electric propulsion (HEP) system for sample return and low cost missions; 3) the Advanced Xenon Flow Control System (AXFS); ultra-lightweight propellant tank technologies (ULTT); and propulsion technologies for a Mars Ascent Vehicle (MAV). The AXFS and ULTT are two component technologies being developed with nearer-term flight infusion in mind, whereas NEXT and the HEP are being developed as EP systems. ISPTs entry vehicle technologies are: 1) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures; guidance, navigation, and control (GNC) models of blunt-body rigid aeroshells; and aerothermal effect models; and 2) Multi-mission technologies for Earth Entry Vehicles (MMEEV) for sample return missions. The Systems Mission Analysis area is focused on developing tools and assessing the application of propulsion, entry vehicle, and spacecraft bus technologies to a wide variety of mission concepts. Several of the ISPT technologies are related to sample return missions and other spacecraft bus technology needs like: MAV propulsion, MMEEV, and electric propulsion. These technologies, as well as Aerocapture, are more vehicle and mission-focused, and present a different set of technology development challenges. These in-space propulsion technologies are applicable, and potentially enabling for future NASA Discovery, New Frontiers, Flagship and sample return missions currently under consideration. This paper provides

  19. Aerothermodynamic design feasibility of a Mars aerocapture/aeromaneuver vehicle

    NASA Technical Reports Server (NTRS)

    Florence, D. E.

    1981-01-01

    Lifting aerodynamic configurations have been screened and selected for the Mars aerocapture mission that (1) meet the geometric packaging requirements of the various payloads and the Space Shuttle cargo bay and (2) provide the aerodynamic performance characteristics required to obtain the atmospheric exit steering accuracy and the parachute deployment conditions desired. Hypersonic heat transfer and aerodynamic loads to the vehicle in the CO2 atmosphere are evaluated. Contemporary low density ablative thermal protection materials were selected that meet all the atmospheric entry requirements and provide a minimum mass solution. Results are presented of the aerodynamic configuration and thermal protection materials screening and selection. It is concluded that the aerothermodynamic design of this concept is feasible using state-of-the-art technology.

  20. Spacecraft Bus and Platform Technology Development under the NASA ISPT Program

    NASA Technical Reports Server (NTRS)

    Anderson, David J.; Munk, Michelle M.; Pencil, Eric J.; Dankanich, John W.; Glaab, Louis J.; Peterson, Todd T.

    2013-01-01

    The In-Space Propulsion Technology (ISPT) program is developing spacecraft bus and platform technologies that will enable or enhance NASA robotic science missions. The ISPT program is currently developing technology in four areas that include Propulsion System Technologies (electric and chemical), Entry Vehicle Technologies (aerocapture and Earth entry vehicles), Spacecraft Bus and Sample Return Propulsion Technologies (components and ascent vehicles), and Systems/Mission Analysis. Three technologies are ready for near-term flight infusion: 1) the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance 2) NASAs Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system and 3) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures guidance, navigation, and control (GN&C) models of blunt-body rigid aeroshells and aerothermal effect models. Two component technologies being developed with flight infusion in mind are the Advanced Xenon Flow Control System, and ultra-lightweight propellant tank technologies. Future direction for ISPT are technologies that relate to sample return missions and other spacecraft bus technology needs like: 1) Mars Ascent Vehicles (MAV) 2) multi-mission technologies for Earth Entry Vehicles (MMEEV) for sample return missions and 3) electric propulsion for sample return and low cost missions. These technologies are more vehicle and mission-focused, and present a different set of technology development and infusion steps beyond those previously implemented. The Systems/Mission Analysis area is focused on developing tools and assessing the application of propulsion and spacecraft bus technologies to a wide variety of mission concepts. These in-space propulsion technologies are applicable, and potentially enabling for future NASA Discovery, New Frontiers, and sample return missions currently

  1. The Status of Spacecraft Bus and Platform Technology Development under the NASA ISPT Program

    NASA Technical Reports Server (NTRS)

    Anderson, David J.; Munk, Michelle M.; Pencil, Eric; Dankanich, John; Glaab, Louis; Peterson, Todd

    2013-01-01

    The In-Space Propulsion Technology (ISPT) program is developing spacecraft bus and platform technologies that will enable or enhance NASA robotic science missions. The ISPT program is currently developing technology in four areas that include Propulsion System Technologies (electric and chemical), Entry Vehicle Technologies (aerocapture and Earth entry vehicles), Spacecraft Bus and Sample Return Propulsion Technologies (components and ascent vehicles), and Systems/Mission Analysis. Three technologies are ready for near-term flight infusion: 1) the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance; 2) NASA s Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system; and 3) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures; guidance, navigation, and control (GN&C) models of blunt-body rigid aeroshells; and aerothermal effect models. Two component technologies being developed with flight infusion in mind are the Advanced Xenon Flow Control System and ultralightweight propellant tank technologies. Future directions for ISPT are technologies that relate to sample return missions and other spacecraft bus technology needs like: 1) Mars Ascent Vehicles (MAV); 2) multi-mission technologies for Earth Entry Vehicles (MMEEV); and 3) electric propulsion. These technologies are more vehicles and mission-focused, and present a different set of technology development and infusion steps beyond those previously implemented. The Systems/Mission Analysis area is focused on developing tools and assessing the application of propulsion and spacecraft bus technologies to a wide variety of mission concepts. These inspace propulsion technologies are applicable, and potentially enabling for future NASA Discovery, New Frontiers, and sample return missions currently under consideration, as well as having broad applicability to

  2. The Status of Spacecraft Bus and Platform Technology Development Under the NASA ISPT Program

    NASA Technical Reports Server (NTRS)

    Anderson, David J.; Munk, Michelle M.; Pencil, Eric J.; Dankanich, John; Glaab, Louis J.

    2013-01-01

    The In-Space Propulsion Technology (ISPT) program is developing spacecraft bus and platform technologies that will enable or enhance NASA robotic science missions. The ISPT program is currently developing technology in four areas that include Propulsion System Technologies (electric and chemical), Entry Vehicle Technologies (aerocapture and Earth entry vehicles), Spacecraft Bus and Sample Return Propulsion Technologies (components and ascent vehicles), and Systems/Mission Analysis. Three technologies are ready for near-term flight infusion: 1) the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance 2) NASAs Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system and 3) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures guidance, navigation, and control (GN&C) models of blunt-body rigid aeroshells and aerothermal effect models. Two component technologies being developed with flight infusion in mind are the Advanced Xenon Flow Control System, and ultra-lightweight propellant tank technologies. Future direction for ISPT are technologies that relate to sample return missions and other spacecraft bus technology needs like: 1) Mars Ascent Vehicles (MAV) 2) multi-mission technologies for Earth Entry Vehicles (MMEEV) and 3) electric propulsion. These technologies are more vehicle and mission-focused, and present a different set of technology development and infusion steps beyond those previously implemented. The Systems/Mission Analysis area is focused on developing tools and assessing the application of propulsion and spacecraft bus technologies to a wide variety of mission concepts. These in-space propulsion technologies are applicable, and potentially enabling for future NASA Discovery, New Frontiers, and sample return missions currently under consideration, as well as having broad applicability to potential

  3. Spacecraft Bus and Platform Technology Development under the NASA ISPT Program

    NASA Technical Reports Server (NTRS)

    Anderson, David J.; Munk, Michelle M.; Pencil, Eric; Dankanich, John; Glaab, Louis; Peterson, Todd

    2013-01-01

    The In-Space Propulsion Technology (ISPT) program is developing spacecraft bus and platform technologies that will enable or enhance NASA robotic science missions. The ISPT program is currently developing technology in four areas that include Propulsion System Technologies (electric and chemical), Entry Vehicle Technologies (aerocapture and Earth entry vehicles), Spacecraft Bus and Sample Return Propulsion Technologies (components and ascent vehicles), and Systems/Mission Analysis. Three technologies are ready for near-term flight infusion: 1) the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance; 2) NASA s Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system; and 3) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures; guidance, navigation, and control (GN&C) models of blunt-body rigid aeroshells; and aerothermal effect models. Two component technologies being developed with flight infusion in mind are the Advanced Xenon Flow Control System, and ultra-lightweight propellant tank technologies. Future direction for ISPT are technologies that relate to sample return missions and other spacecraft bus technology needs like: 1) Mars Ascent Vehicles (MAV); 2) multi-mission technologies for Earth Entry Vehicles (MMEEV) for sample return missions; and 3) electric propulsion for sample return and low cost missions. These technologies are more vehicle and mission-focused, and present a different set of technology development and infusion steps beyond those previously implemented. The Systems/Mission Analysis area is focused on developing tools and assessing the application of propulsion and spacecraft bus technologies to a wide variety of mission concepts. These in-space propulsion technologies are applicable, and potentially enabling for future NASA Discovery, New Frontiers, and sample return missions

  4. The status of spacecraft bus and platform technology development under the NASA ISPT program

    NASA Astrophysics Data System (ADS)

    Anderson, D. J.; Munk, M. M.; Pencil, E.; Dankanich, J.; Glaab, L.; Peterson, T.

    The In-Space Propulsion Technology (ISPT) program is developing spacecraft bus and platform technologies that will enable or enhance NASA robotic science missions. The ISPT program is currently developing technology in four areas that include Propulsion System Technologies (electric and chemical), Entry Vehicle Technologies (aerocapture and Earth entry vehicles), Spacecraft Bus and Sample Return Propulsion Technologies (components and ascent vehicles), and Systems/Mission Analysis. Three technologies are ready for near-term flight infusion: 1) the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance; 2) NASA's Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system; and 3) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures; guidance, navigation, and control (GN& C) models of blunt-body rigid aeroshells; and aerothermal effect models. Two component technologies being developed with flight infusion in mind are the Advanced Xenon Flow Control System and ultra-lightweight propellant tank technologies. Future directions for ISPT are technologies that relate to sample return missions and other spacecraft bus technology needs like: 1) Mars Ascent Vehicles (MAV); 2) multi-mission technologies for Earth Entry Vehicles (MMEEV); and 3) electric propulsion. These technologies are more vehicles and mission-focused, and present a different set of technology development and infusion steps beyond those previously implemented. The Systems/Mission Analysis area is focused on developing tools and assessing the application of propulsion and spacecraft bus technologies to a wide variety of mission concepts. These in-space propulsion technologies are applicable, and potentially enabling for future NASA Discovery, New Frontiers, and sample return missions currently under consideration, as well as having broad applicabilit- to

  5. Mars Rover Sample Return aerocapture configuration design and packaging constraints

    NASA Technical Reports Server (NTRS)

    Lawson, Shelby J.

    1989-01-01

    This paper discusses the aerodynamics requirements, volume and mass constraints that lead to a biconic aeroshell vehicle design that protects the Mars Rover Sample Return (MRSR) mission elements from launch to Mars landing. The aerodynamic requirements for Mars aerocapture and entry and packaging constraints for the MRSR elements result in a symmetric biconic aeroshell that develops a L/D of 1.0 at 27.0 deg angle of attack. A significant problem in the study is obtaining a cg that provides adequate aerodynamic stability and performance within the mission imposed constraints. Packaging methods that relieve the cg problems include forward placement of aeroshell propellant tanks and incorporating aeroshell structure as lander structure. The MRSR missions developed during the pre-phase A study are discussed with dimensional and mass data included. Further study is needed for some missions to minimize MRSR element volume so that launch mass constraints can be met.

  6. Earth Return Aerocapture for the TransHab/Ellipsled Vehicle

    NASA Technical Reports Server (NTRS)

    Muth, W. D.; Hoffmann, C.; Lyne, J. E.

    2000-01-01

    The current architecture being considered by NASA for a human Mars mission involves the use of an aerocapture procedure at Mars arrival and possibly upon Earth return. This technique would be used to decelerate the vehicles and insert them into their desired target orbits, thereby eliminating the need for propulsive orbital insertions. The crew may make the interplanetary journey in a large, inflatable habitat known as the TransHab. It has been proposed that upon Earth return, this habitat be captured into orbit for use on subsequent missions. In this case, the TransHab would be complimented with an aeroshell, which would protect it from heating during the atmospheric entry and provide the vehicle with aerodynamic lift. The aeroshell has been dubbed the "Ellipsled" because of its characteristic shape. This paper reports the results of a preliminary study of the aerocapture of the TransHab/Ellipsled vehicle upon Earth return. Undershoot and overshoot boundaries have been determined for a range of entry velocities, and the effects of variations in the atmospheric density profile, the vehicle deceleration limit, the maximum vehicle roll rate, the target orbit, and the vehicle ballistic coefficient have been examined. A simple, 180 degree roll maneuver was implemented in the undershoot trajectories to target the desired 407 km circular Earth orbit. A three-roll sequence was developed to target not only a specific orbital energy, but also a particular inclination, thereby decreasing propulsive inclination changes and post-aerocapture delta-V requirements. Results show that the TransHab/Ellipsled vehicle has a nominal corridor width of at least 0.7 degrees for entry speeds up to 14.0 km/s. Most trajectories were simulated using continuum flow aerodynamics, but the impact of high-altitude viscous effects was evaluated and found to be minimal. In addition, entry corridor comparisons have been made between the TransHab/Ellipsled and a modified Apollo capsule which is also

  7. Trajectory Guidance for Mars Robotic Precursors: Aerocapture, Entry, Descent, and Landing

    NASA Technical Reports Server (NTRS)

    Sostaric, Ronald R.; Zumwalt, Carlie; Garcia-Llama, Eduardo; Powell, Richard; Shidner, Jeremy

    2011-01-01

    Future crewed missions to Mars require improvements in landed mass capability beyond that which is possible using state-of-the-art Mars Entry, Descent, and Landing (EDL) systems. Current systems are capable of an estimated maximum landed mass of 1-1.5 metric tons (MT), while human Mars studies require 20-40 MT. A set of technologies were investigated by the EDL Systems Analysis (SA) project to assess the performance of candidate EDL architectures. A single architecture was selected for the design of a robotic precursor mission, entitled Exploration Feed Forward (EFF), whose objective is to demonstrate these technologies. In particular, inflatable aerodynamic decelerators (IADs) and supersonic retro-propulsion (SRP) have been shown to have the greatest mass benefit and extensibility to future exploration missions. In order to evaluate these technologies and develop the mission, candidate guidance algorithms have been coded into the simulation for the purposes of studying system performance. These guidance algorithms include aerocapture, entry, and powered descent. The performance of the algorithms for each of these phases in the presence of dispersions has been assessed using a Monte Carlo technique.

  8. Neptune Orbiter Mission Scenario Based on Nuclear Electric Propulsion and Aerocapture Orbital Insertion

    NASA Astrophysics Data System (ADS)

    Jits, R.

    2002-01-01

    insertion of spacecraft into elliptical orbit around target planet is proposed for Neptune orbiter mission. The primary goal of combining nuclear electric propulsion (NEP) and aerocapture orbital insertion is a reduction of a trip time comparing to that of similar mission, which would use nuclear electric propulsion only. One of the limitations of the all NEP orbiter is that at the planetary approach it must match its arrival velocity with Neptune's orbital speed in order to initiate slow capture into the desired orbit using low thrust electric propulsion. Use of aerocapture for insertion into closed elliptical orbit around Neptune through a single aerodynamically controlled atmospheric pass gives advantage of having higher entry velocities than it would be possible in case of all NEP scenario, thus reducing trip time required for interplanetary transfer. propulsion and thermal protection systems. Moreover, because faster interplanetary trip times for combined NEP/Aerocapture orbiter result in a higher entry velocities into the Neptune's atmosphere, they will also drive the increase in aerobrake mass fraction. In addition, aerocapture at Neptune also presents a challenge for aerobrake's guidance system which must target vehicle to the desired atmospheric exit conditions in the presence of significant uncertainties in Neptune's atmospheric density. Hence, there is a need to design a robust nominal aerocapture trajectory capable of accommodating density dispersions and also optimized for minimum thermal protection mass, thus contributing to overall reduction of aerobrake mass fraction. determine the optimal combination between reduction of the trip time and increase in aerobrake mass fraction was undertaken. The initial assumptions on aerobrake thermal protection materials and NEP system characteristics were based on near term state of the art technology, corresponding to 2007-2010 time frame, when such a mission to Neptune could be launched. interplanetary

  9. Testing of Flexible Ballutes in Hypersonic Wind Tunnels for Planetary Aerocapture

    NASA Technical Reports Server (NTRS)

    Buck, Gregory M.

    2007-01-01

    Studies were conducted for the In-Space Propulsion (ISP) Ultralightweight Ballute Technology Development Program to increase the technical readiness level of inflatable decelerator systems for planetary aerocapture. The present experimental study was conducted to develop the capability for testing lightweight, flexible materials in hypersonic facilities. The primary objectives were to evaluate advanced polymer film materials in a high-temperature, high-speed flow environment and provide experimental data for comparisons with fluid-structure interaction modeling tools. Experimental testing was conducted in the Langley Aerothermodynamics Laboratory 20-Inch Hypersonic CF4 and 31-Inch Mach 10 Air blowdown wind tunnels. Quantitative flexure measurements were made for 60 degree half angle afterbody-attached ballutes, in which polyimide films (1-mil and 3- mil thick) were clamped between a 1/2-inch diameter disk and a base ring (4-inch and 6-inch diameters). Deflection measurements were made using a parallel light silhouette of the film surface through an existing schlieren optical system. The purpose of this paper is to discuss these results as well as free-flying testing techniques being developed for both an afterbody-attached and trailing toroidal ballute configuration to determine dynamic fluid-structural stability. Methods for measuring polymer film temperature were also explored using both temperature sensitive paints (for up to 370 C) and laser-etched thin-film gages.

  10. Testing of Flexible Ballutes in Hypersonic Wind Tunnels for Planetary Aerocapture

    NASA Technical Reports Server (NTRS)

    Buck, Gregory M.

    2006-01-01

    Studies were conducted for the In-Space Propulsion (ISP) Ultralightweight Ballute Technology Development Program to increase the technical readiness level of inflatable decelerator systems for planetary aerocapture. The present experimental study was conducted to develop the capability for testing lightweight, flexible materials in hypersonic facilities. The primary objectives were to evaluate advanced polymer film materials in a high-temperature, high-speed flow environment and provide experimental data for comparisons with fluid-structure interaction modeling tools. Experimental testing was conducted in the Langley Aerothermodynamics Laboratory 20-Inch Hypersonic CF4 and 31-Inch Mach 10 Air blowdown wind tunnels. Quantitative flexure measurements were made for 60 degree half angle afterbody-attached ballutes, in which polyimide films (1-mil and 3-mil thick) were clamped between a 1/2-inch diameter disk and a base ring (4-inch and 6-inch diameters). Deflection measurements were made using a parallel light silhouette of the film surface through an existing schlieren optical system. The purpose of this paper is to discuss these results as well as free-flying testing techniques being developed for both an afterbody-attached and trailing toroidal ballute configuration to determine dynamic fluid-structural stability. Methods for measuring polymer film temperature were also explored using both temperature sensitive paints (for up to 370 C) and laser-etched thin-film gages.

  11. Mars aerocapture using continuous roll techniques

    NASA Astrophysics Data System (ADS)

    Willcockson, W. H.

    1992-08-01

    Capture of a Mars vehicle into a closed orbit can benefit greatly from the use of aerodynamic deceleration (Aerocapture). Because of the unknowns associated with the Mars environment, the use of adaptive control techniques is critical to the successful outcome. This paper will describe work done over several years at assessing the performance of a continuous roll control technique coupled with a closed loop predictor corrector guidance system. The implementation of this system is called CLAAS (Closed Loop AeroAssist Simulation). This system has been tested against a variety of dispersions including a variety of atmospheric models, atmospheric shear waves, vehicle variations, and navigation errors. Results will be shown for a two mission applications, a representative manned Mars vehicle and an unmanned Mars Rover Sample Return (MRSR) system. Finally, a few observations on technical challenges for aerobraking a Mars vehicle are included in the conclusions.

  12. Aerothermodynamic environment of a Titan aerocapture vehicle

    NASA Technical Reports Server (NTRS)

    Tiwari, S. N.; Chow, H.

    1982-01-01

    The extent of convective and radiative heating for a Titan aerocapture vehicle is investigated. The flow in the shock layer is assumed to be axisymmetric, steady, viscous, and compressible. It is further assumed that the gas is in chemical and local thermodynamic equilibrium and tangent slab approximation is used for the radiative transport. The effect of the slip boundary conditions on the body surface and at the shock wave are included in the analysis of high-altitude entry conditions. The implicit finite difference techniques is used to solve the viscous shock-layer equations for a 45 degree sphere cone at zero angle of attack. Different compositions for the Titan atmosphere are assumed, and results are obtained for the entry conditions specified by the Jet Propulsion Laboratory.

  13. Aerocapture Inflatable Decelerator for Planetary Entry

    NASA Technical Reports Server (NTRS)

    Reza, Sajjad; Hund, Richard; Kustas, Frank; Willcockson, William; Songer, Jarvis; Brown, Glen

    2007-01-01

    Forward Attached Inflatable Decelerators, more commonly known as inflatable aeroshells, provide an effective, cost efficient means of decelerating spacecrafts by using atmospheric drag for aerocapture or planetary entry instead of conventional liquid propulsion deceleration systems. Entry into planetary atmospheres results in significant heating and aerodynamic pressures which stress aeroshell systems to their useful limits. Incorporation of lightweight inflatable decelerator surfaces with increased surface-area footprints provides the opportunity to reduce heat flux and induced temperatures, while increasing the payload mass fraction. Furthermore, inflatable aeroshell decelerators provide the needed deceleration at considerably higher altitudes and Mach numbers when compared with conventional rigid aeroshell entry systems. Inflatable aeroshells also provide for stowage in a compact space, with subsequent deployment of a large-area, lightweight heatshield to survive entry heating. Use of a deployable heatshield decelerator enables an increase in the spacecraft payload mass fraction and may eliminate the need for a spacecraft backshell.

  14. CNES-NASA Studies of the Mars Sample Return Orbiter Aerocapture Phase

    NASA Technical Reports Server (NTRS)

    Fraysse, H.; Powell, R.; Rousseau, S.; Striepe, S.

    2000-01-01

    A Mars Sample Return (MSR) mission has been proposed as a joint CNES (Centre National d'Etudes Spatiales) and NASA effort in the ongoing Mars Exploration Program. The MSR mission is designed to return the first samples of Martian soil to Earth. The primary elements of the mission are a lander, rover, ascent vehicle, orbiter, and an Earth entry vehicle. The Orbiter has been allocated only 2700 kg on the launch phase to perform its part of the mission. This mass restriction has led to the decision to use an aerocapture maneuver at Mars for the orbiter. Aerocapture replaces the initial propulsive capture maneuver with a single atmospheric pass. This atmospheric pass will result in the proper apoapsis, but a periapsis raise maneuver is required at the first apoapsis. The use of aerocapture reduces the total mass requirement by approx. 45% for the same payload. This mission will be the first to use the aerocapture technique. Because the spacecraft is flying through the atmosphere, guidance algorithms must be developed that will autonomously provide the proper commands to reach the desired orbit while not violating any of the design parameters (e.g. maximum deceleration, maximum heating rate, etc.). The guidance algorithm must be robust enough to account for uncertainties in delivery states, atmospheric conditions, mass properties, control system performance, and aerodynamics. To study this very critical phase of the mission, a joint CNES-NASA technical working group has been formed. This group is composed of atmospheric trajectory specialists from CNES, NASA Langley Research Center and NASA Johnson Space Center. This working group is tasked with developing and testing guidance algorithms, as well as cross-validating CNES and NASA flight simulators for the Mars atmospheric entry phase of this mission. The final result will be a recommendation to CNES on the algorithm to use, and an evaluation of the flight risks associated with the algorithm. This paper will describe the

  15. Aerocapture Guidance and Performance at Mars for High-Mass Systems

    NASA Technical Reports Server (NTRS)

    Zumwalt, Carlie H.; Sostaric, Ronald r.; Westhelle, Carlos H.

    2009-01-01

    The Mars Entry, Descent, and Landing System Analysis (EDL-SA) project has been tasked with performing systems analysis to identify the optimal technologies required to land a 20-50 MT Exploration-class mission on Mars. It has been shown that it is not possible to safely land these large systems using heritage Mars EDL systems, or analogous Earth or Moon EDL systems. In 2007, NASA conducted a Mars Exploration Architecture Study which included an in depth review of the science motivations and engineering technology requirements for a human Mars mission campaign. This study resulted in an update to the Mars Design Reference Architecture (DRA 5.0). Among the primary findings and recommendations was the conclusion that landing of large payloads (greater than 1 MT) on the surface of Mars remains a key architectural challenge. Additionally, research and system studies of fundamental EDL technologies were highly recommended. The EDL-SA project identified the candidate technologies and assembled them into full capture and EDL sequences so that simulations could be developed to evaluate them. The chosen architectures combine the various technologies of interest in eight different ways. For aerocapture, only two scenarios were considered. The first is a rigid mid-L/D aeroshell (AS), which is represented in architectures 1, 4, 5, and 7. This scenario calls for a vehicle that flies at a 55-degree angle of attack, resulting in ballistic coefficient and L/D values of 490 kg/m 2 and 0.43, respectively. The second is a lifting hypersonic inflatable aerodynamic decelerator (HIAD), which is represented in architectures 2, 6, and 8. This scenario requires the vehicle to fly at a 22.2- degree angle of attack, which correlates to an L/D of 0.3 and was sized to provide a ballistic coefficient of 165 kg/m 2 . Architecture 3 is an all-propulsive sequence, and is not considered in this study.

  16. Saturn/Titan Rendezvous: A Solar-Sail Aerocapture Mission

    NASA Technical Reports Server (NTRS)

    Matloff, Gregory L.; Taylor, Travis; Powell, Conley

    2004-01-01

    A low-mass Titan orbiter is proposed that uses conservative or optimistic solar sails for all post-Earth-escape propulsion. After accelerating the probe onto a trans-Saturn trajectory, the sail is used parachute style for Saturn capture during a pass through Saturn's outer atmosphere. If the apoapsis of the Saturn-capture orbit is appropriate, the aerocapture maneuver can later be repeated at Titan so that the spacecraft becomes a satellite of Titan. An isodensity-atmosphere model is applied to screen aerocapture trajectories. Huygens/Cassini should greatly reduce uncertainties regarding the upper atmospheres of Saturn and Titan.

  17. Parametric entry corridors for lunar/Mars aerocapture missions

    NASA Technical Reports Server (NTRS)

    Ling, Lisa M.; Baseggio, Franco M.; Fuhry, Douglas P.

    1991-01-01

    Parametric atmospheric entry corridor data are presented for Earth and Mars aerocapture. Parameter ranges were dictated by the range of mission designs currently envisioned as possibilities for the Human Exploration Initiative (HEI). This data, while not providing a means for exhaustive evaluation of aerocapture performance, should prove to be a useful aid for preliminary mission design and evaluation. Entry corridors are expressed as ranges of allowable vacuum periapse altitude of the planetary approach hyperbolic orbit, with chart provided for conversion to an approximate flight path angle corridor at entry interface (125 km altitude). The corridor boundaries are defined by open-loop aerocapture trajectories which satisfy boundary constraints while utilizing the full aerodynamic control capability of the vehicle (i.e., full lift-up or full lift-down). Parameters examined were limited to those of greatest importance from an aerocapture performance standpoint, including the approach orbit hyperbolic excess velocity, the vehicle lift to drag ratio, maximum aerodynamic load factor limit, and the apoapse of the target orbit. The impact of the atmospheric density bias uncertainties are also included. The corridor data is presented in graphical format, and examples of the utilization of these graphs for mission design and evaluation are included.

  18. Sample Return Propulsion Technology Development Under NASA's ISPT Project

    NASA Technical Reports Server (NTRS)

    Anderson, David J.; Dankanich, John; Hahne, David; Pencil, Eric; Peterson, Todd; Munk, Michelle M.

    2011-01-01

    Abstract In 2009, the In-Space Propulsion Technology (ISPT) program was tasked to start development of propulsion technologies that would enable future sample return missions. Sample return missions can be quite varied, from collecting and bringing back samples of comets or asteroids, to soil, rocks, or atmosphere from planets or moons. As a result, ISPT s propulsion technology development needs are also broad, and include: 1) Sample Return Propulsion (SRP), 2) Planetary Ascent Vehicles (PAV), 3) Multi-mission technologies for Earth Entry Vehicles (MMEEV), and 4) Systems/mission analysis and tools that focuses on sample return propulsion. The SRP area includes electric propulsion for sample return and low cost Discovery-class missions, and propulsion systems for Earth Return Vehicles (ERV) including transfer stages to the destination. Initially the SRP effort will transition ongoing work on a High-Voltage Hall Accelerator (HIVHAC) thruster into developing a full HIVHAC system. SRP will also leverage recent lightweight propellant-tanks advancements and develop flight-qualified propellant tanks with direct applicability to the Mars Sample Return (MSR) mission and with general applicability to all future planetary spacecraft. ISPT s previous aerocapture efforts will merge with earlier Earth Entry Vehicles developments to form the starting point for the MMEEV effort. The first task under the Planetary Ascent Vehicles (PAV) effort is the development of a Mars Ascent Vehicle (MAV). The new MAV effort will leverage past MAV analysis and technology developments from the Mars Technology Program (MTP) and previous MSR studies. This paper will describe the state of ISPT project s propulsion technology development for future sample return missions.12

  19. Significant science at Titan and Neptune from aerocaptured missions

    NASA Astrophysics Data System (ADS)

    Spilker, Thomas R.

    2005-04-01

    In 2001, NASA began assembling the Aerocapture Systems Analysis Team, a team of scientists and engineers from multiple NASA centers. Their charter is to perform high-fidelity analyses of delivering scientifically compelling orbital missions that use aerocapture for orbit insertion at their destinations. After establishing scientific credibility, studies focus on aerocapture systems design and performance, including approach navigation, flight mechanics, aerothermodynamics, and thermal protection. The team's October 2001-September 2002 study examined a mission to explore the organic environment of Titan and its chemical, geological, and dynamical context. Its architecture includes a Titan polar orbiter that would complete and extend Cassini's soon-to-begin global mapping, aiding global extrapolation of findings from a mobile in situ element (rover, blimp, etc.). The in situ element would perform remote sensing and in situ investigations, for analysis and characterization of Titan's surface, shallow subsurface, atmosphere, processes occurring there, and energy sources driving it all. The study concentrated on the orbiter and orbit insertion, largely treating the in situ element as a black box with data relay requirements. October 2002-September 2003 the team studied a mission to perform Cassini/Huygens-level exploration of the Neptune system. Before aerocapture this mission would deploy and support multiple Neptune atmospheric entry probes. After aerocapture the orbiter uses Triton as a "tour engine", in much the same manner as Cassini uses Titan, to provide many Triton flybys and orbit evolution for detailed investigation of Neptune's interior, atmosphere, magnetosphere, rings, and satellites. This presentation summarizes the missions' science objectives, instrumentation, and data requirements that served as the foundations for the studies, and describes mission design requirements and constraints that affect the science investigations.

  20. Review of NASA In-Space Propulsion Technology Program Inflatable Decelerator Investments

    NASA Technical Reports Server (NTRS)

    Richardson, E. H.; Mnk, M. M.; James, B. F.; Moon, S. A.

    2005-01-01

    The NASA In-Space Propulsion Technology (ISPT) Program is managed by the NASA Headquarters Science Mission Directorate and is implemented by the Marshall Space Flight Center in Huntsville, Alabama. The ISPT objective is to fund development of promising in-space propulsion technologies that can decrease flight times, decrease cost, or increase delivered payload mass for future science missions. Before ISPT will invest in a technology, the Technology Readiness Level (TRL) of the concept must be estimated to be at TRL 3. A TRL 3 signifies that the technical community agrees that the feasibility of the concept has been proven through experiment or analysis. One of the highest priority technology investments for ISPT is Aerocapture. The aerocapture maneuver uses a planetary atmosphere to reduce or alter the speed of a vehicle allowing for quick, propellantless (or using very little propellant) orbit capture. The atmosphere is used as a brake, transferring the energy associated with the vehicle's high speed into thermal energy. The ISPT Aerocapture Technology Area (ATA) is currently investing in the development of advanced lightweight ablative thermal protection systems, high temperature composite structures, and heat-flux sensors for rigid aeroshells. The heritage of rigid aeroshells extends back to the Apollo era and this technology will most likely be used by the first generation aerocapture vehicle. As a second generation aerocapture technology, ISPT is investing in three inflatable aerodynamic decelerator concepts for planetary aerocapture. They are: trailing ballute (balloon-parachute), attached afterbody ballute, and an inflatable aeroshell. ISPT also leverages the NASA Small Business Innovative Research Program for additional inflatable decelerator technology development. In mid-2004 ISPT requested an independent review of the three inflatable decelerator technologies funded directly by ISPT to validate the TRL and to identify technology maturation concerns. An

  1. Review of NASA In-Space Propulsion Technology Program Inflatable Decelerator Investments

    NASA Technical Reports Server (NTRS)

    Richardson, Erin H.; Munk, Michelle M.; James, Bonnie F.; Moon, Steve A.

    2005-01-01

    The NASA In-Space Propulsion Technology (ISPT) Program is managed by the NASA Headquarters Science Mission Directorate and is implemented by the Marshall Space Flight Center in Huntsville, Alabama. The ISPT objective is to fund development of promising in- space propulsion technologies that can decrease flight times, decrease cost, or increase delivered payload mass for future science missions. Before ISPT will invest in a technology, the Technology Readiness Level (TRL) of the concept must be estimated to be at TRL 3. A TRL 3 signifies that the technical community agrees that the feasibility of the concept has been proven through experiment or analysis. One of the highest priority technology investments for ISPT is Aerocapture. The aerocapture maneuver uses a planetary atmosphere to reduce or alter the speed of a vehicle allowing for quick, propellantless (or using very little propellant) orbit capture. The atmosphere is used as a brake, transferring the energy associated with the vehicle s high speed into thermal energy. The ISPT Aerocapture Technology Area (ATA) is currently investing in the development of advanced lightweight ablative thermal protection systems, high temperature composite structures, and heat-flux sensors for rigid aeroshells. The heritage of rigid aeroshells extends back to the Apollo era and this technology will most likely be used by the first generation aerocapture vehicle. As a second generation aerocapture technology, ISPT is investing in three inflatable aerodynamic decelerator concepts for planetary aerocapture. They are: trailing ballute (balloon-parachute), attached afterbody ballute, and an inflatable aeroshell. ISPT also leverages the NASA Small Business Innovative Research Program for additional inflatable decelerator technology development. In mid-2004 ISPT requested an independent review of the three inflatable decelerator technologies funded directly by ISPT to validate the TRL and to identify technology maturation concerns. An

  2. Exploration Technology Development & Demonstration

    NASA Video Gallery

    Chris Moore delivers a presentation from the Exploration Technology Development & Demonstration (ETDD) study team on May 25, 2010, at the NASA Exploration Enterprise Workshop held in Galveston, TX....

  3. Post-aerocapture orbit selection and maintenance for the Aerofast mission to Mars

    NASA Astrophysics Data System (ADS)

    Pontani, Mauro; Teofilatto, Paolo

    2012-10-01

    Aerofast is the abbreviation of “aerocapture for future space transportation” and represents a project aimed at developing aerocapture techniques with regard to an interplanetary mission to Mars, in the context of the 7th Framework Program, with the financial support of the European Union. This paper describes the fundamental characteristics of the operational orbit after aerocapture for the mission of interest, as well as the related maintenance strategy. The final orbit selection depends on the desired lighting conditions, maximum revisit time of specific target regions, and feasibility of the orbit maintenance strategy. A sunsynchronous, frozen, repeating-ground-track orbit is chosen. First, the period of repetition is such that adjacent ascending node crossings (over the Mars surface) have a separation compatible with the swath of the optical payload. Secondly, the sunsynchronism condition ensures that a given latitude is periodically visited at the same local time, which condition is essential for comparing images of the same region at different epochs. Lastly, the fulfillment of the frozen condition guarantees improved orbit stability with respect to perturbations due to the zonal harmonics of Mars gravitational field. These three fundamental features of the operational orbit lead to determining its mean orbital elements. The evaluation of short and long period effects (e.g., those due to the sectorial harmonics of the gravitational field or to the aerodynamic drag) requires the determination of the osculating orbital elements at an initial reference time. This research describes a simple and accurate approach that leads to numerically determining these initial values, without employing complicated analytical developments. Numerical simulations demonstrate the long-period stability of the orbit when a significant number of harmonics of the gravitational field are taken into account. However, aerodynamic drag produces a relatively slow orbital decay at the

  4. Aerocapture Performance Analysis for a Neptune-Triton Exploration Mission

    NASA Technical Reports Server (NTRS)

    Starr, Brett R.; Westhelle, Carlos H.; Masciarelli, James P.

    2004-01-01

    A systems analysis has been conducted for a Neptune-Triton Exploration Mission in which aerocapture is used to capture a spacecraft at Neptune. Aerocapture uses aerodynamic drag instead of propulsion to decelerate from the interplanetary approach trajectory to a captured orbit during a single pass through the atmosphere. After capture, propulsion is used to move the spacecraft from the initial captured orbit to the desired science orbit. A preliminary assessment identified that a spacecraft with a lift to drag ratio of 0.8 was required for aerocapture. Performance analyses of the 0.8 L/D vehicle were performed using a high fidelity flight simulation within a Monte Carlo executive to determine mission success statistics. The simulation was the Program to Optimize Simulated Trajectories (POST) modified to include Neptune specific atmospheric and planet models, spacecraft aerodynamic characteristics, and interplanetary trajectory models. To these were added autonomous guidance and pseudo flight controller models. The Monte Carlo analyses incorporated approach trajectory delivery errors, aerodynamic characteristics uncertainties, and atmospheric density variations. Monte Carlo analyses were performed for a reference set of uncertainties and sets of uncertainties modified to produce increased and reduced atmospheric variability. For the reference uncertainties, the 0.8 L/D flatbottom ellipsled vehicle achieves 100% successful capture and has a 99.87 probability of attaining the science orbit with a 360 m/s V budget for apoapsis and periapsis adjustment. Monte Carlo analyses were also performed for a guidance system that modulates both bank angle and angle of attack with the reference set of uncertainties. An alpha and bank modulation guidance system reduces the 99.87 percentile DELTA V 173 m/s (48%) to 187 m/s for the reference set of uncertainties.

  5. Metals technology development plan

    SciTech Connect

    Betts, W.S.

    1987-03-01

    This document presents the plan for the metals technology development required to support the design of the MHTGR within the US National Gas-Cooled Reactor Program. Besides descriptions of the required technology development, cost estimates, and schedules, the plan also includes the associated design functions and design requirements.

  6. NASA balloon technology developments

    NASA Astrophysics Data System (ADS)

    Fairbrother, D. A.

    The National Aeronautics and Space Administration (NASA) Balloon Program has been, and will continue to be, committed to improving the capabilities of balloons to support science missions. Fundamental to vehicle improvement is a program of technology development that will enable improved flight performance throughout the next decade. The program's technology thrust areas include: materials, vehicle design & development, structural analysis, operations & support systems, performance modeling and planetary balloons. Building on the foundations of the 18-year research and development program, a technology roadmap has been generated which identifies specific areas of interest to NASA and the vision of future developments. The major components of the roadmap are: vehicle systems, ballooncraft systems, operational and safety support systems, and planetary vehicles. Current technology activities include nanocomposite balloon films, a new balloon designed to lift 3600 kgs to 36 km, a balloon rotation rate study and Mars pumpkin balloon investigations. The technology roadmap, as well as specific projects and recent advancements, will be presented.

  7. NASA Balloon Technology Developments

    NASA Technical Reports Server (NTRS)

    Fairbrother, D. A.

    2004-01-01

    The National Aeronautics and Space Administration (NASA) Balloon Program has been, and will continue to be, committed to improving the capabilities of balloons to support science missions. Fundamental to vehicle improvement is a program of technology development that will enable improved flight performance throughout the next decade. The program s technology thrust areas include: materials, vehicle design & development, structural analysis, operations & support systems, performance modeling and planetary balloons. Building on the foundations of the 18-year research and development program, a technology roadmap has been generated which identifies specific areas of interest to NASA and the vision of future developments. The major components of the roadmap are: vehicle systems, balloon-craft systems, operational and safety support systems, and planetary vehicles. Current technology activities include nanocomposite balloon films, a new balloon designed to lift 3600 kgs to 36 km, a balloon rotation rate study and Mars pumpkin balloon investigations. The technology roadmap, as well as specific projects and recent advancements, will be presented.

  8. Numerical Roll Reversal Predictor Corrector Aerocapture and Precision Landing Guidance Algorithms for the Mars Surveyor Program 2001 Missions

    NASA Technical Reports Server (NTRS)

    Powell, Richard W.

    1998-01-01

    This paper describes the development and evaluation of a numerical roll reversal predictor-corrector guidance algorithm for the atmospheric flight portion of the Mars Surveyor Program 2001 Orbiter and Lander missions. The Lander mission utilizes direct entry and has a demanding requirement to deploy its parachute within 10 km of the target deployment point. The Orbiter mission utilizes aerocapture to achieve a precise captured orbit with a single atmospheric pass. Detailed descriptions of these predictor-corrector algorithms are given. Also, results of three and six degree-of-freedom Monte Carlo simulations which include navigation, aerodynamics, mass properties and atmospheric density uncertainties are presented.

  9. Mobile Router Technology Development

    NASA Technical Reports Server (NTRS)

    Ivancic, William D.; Stewart, David H.; Bell, Terry L.; Kachmar, Brian A.; Shell, Dan; Leung, Kent

    2002-01-01

    Cisco Systems and NASA have been performing joint research on mobile routing technology under a NASA Space Act Agreement. Cisco developed mobile router technology and provided that technology to NASA for applications to aeronautic and space-based missions. NASA has performed stringent performance testing of the mobile router, including the interaction of routing and transport-level protocols. This paper describes mobile routing, the mobile router, and some key configuration parameters. In addition, the paper describes the mobile routing test network and test results documenting the performance of transport protocols in dynamic routing environments.

  10. Fusion development and technology

    SciTech Connect

    Montgomery, D.B.

    1992-01-01

    This report discusses the following: superconducting magnet technology; high field superconductors; advanced magnetic system and divertor development; poloidal field coils; gyrotron development; commercial reactor studies--aries; ITER physics: alpha physics and alcator R D for ITER; lower hybrid current drive and heating in the ITER device; ITER superconducting PF scenario and magnet analysis; ITER systems studies; and safety, environmental and economic factors in fusion development.

  11. Lunar/Mars earth return aerocapture heating constraint

    NASA Astrophysics Data System (ADS)

    Cuthbert, P. A.; Tigges, M. A.; Bryant, L. E.

    Trajectory design issues beyond those under consideration in the Aeroassist Flight Experiment (AFE) program and more in line with the Shuttle design concept are presented. This is deemed necessary as flight regimes encountered in Lunar/Mars aerocapture trajectories at Mars and return-to-earth will provide more stringent requirements on vehicle design than AFE and are not exactly quantifiable at this time. Investigations are conducted of areas where explicit trajectory control is practical and can most directly influence constraints critical to vehicle design for manned and unmanned interplanetary missions. Primary consideration is given to the ability to control vehicle heating during entry, and this particular area of Shuttle entry design is discussed in detail.

  12. Enhancement of the Natural Earth Satellite Population Through Meteoroid Aerocapture

    NASA Technical Reports Server (NTRS)

    Moorhead, Althea V.; Cooke, William J.

    2014-01-01

    The vast majority of meteoroids either fall to the ground as meteorites or ablate completely in the atmosphere. However, large meteoroids have been observed to pass through the atmosphere and reenter space in a few instances. These atmosphere-grazing meteoroids have been characterized using ground-based observation and satellite-based infrared detection. As these methods become more sensitive, smaller atmospheregrazing meteoroids will likely be detected. In anticipation of this increased detection rate, we compute the frequency with which centimeter-sized meteoroids graze and exit Earth's atmosphere. We characterize the post-atmosphere orbital characteristics of these bodies and conduct numerical simulations of their orbital evolution under the perturbing influence of the Sun and Moon. We find that a small subset of aerocaptured meteoroids are perturbed away from immediate atmospheric reentry and become temporary natural Earth satellites.

  13. Martian Aerocapture Terminal Point Guidance: A Reference Path Optimization Study

    NASA Technical Reports Server (NTRS)

    Ro, Theodore U.; Queen, Eric M.; Striepe, Scott A.

    1999-01-01

    An effective method of terminal point guidance is to employ influence coefficients, which are solved from a set of differential equations adjoint to the linearized perturbations of the equations of motion about a reference trajectory. Hence, to optimize this type of guidance, one must first optimize the reference trajectory that the guidance is based upon. This study concentrates on various methods to optimize a reference trajectory for a Martian aerocapture maneuver, including a parametric analysis and first order gradient method. Resulting reference trajectories were tested in separate 2000 6-DOF Monte Carlo runs, using the Atmospheric Guidance Algorithm Testbed for the Mars Surveyor Program 2001 (MSP '01) Orbiter. These results were compared to an August 1998 study using the same terminal point control guidance algorithm and simulation testbed. Satisfactory improvements over the 1998 study are amply demonstrated.

  14. Emerging Propulsion Technologies

    NASA Technical Reports Server (NTRS)

    Keys, Andrew S.

    2006-01-01

    The Emerging Propulsion Technologies (EPT) investment area is the newest area within the In-Space Propulsion Technology (ISPT) Project and strives to bridge technologies in the lower Technology Readiness Level (TRL) range (2 to 3) to the mid TRL range (4 to 6). A prioritization process, the Integrated In-Space Transportation Planning (IISTP), was developed and applied in FY01 to establish initial program priorities. The EPT investment area emerged for technologies that scored well in the IISTP but had a low technical maturity level. One particular technology, the Momentum-eXchange Electrodynamic-Reboost (MXER) tether, scored extraordinarily high and had broad applicability in the IISTP. However, its technical maturity was too low for ranking alongside technologies like the ion engine or aerocapture. Thus MXER tethers assumed top priority at EPT startup in FY03 with an aggressive schedule and adequate budget. It was originally envisioned that future technologies would enter the ISP portfolio through EPT, and EPT developed an EPT/ISP Entrance Process for future candidate ISP technologies. EPT has funded the following secondary, candidate ISP technologies at a low level: ultra-lightweight solar sails, general space/near-earth tether development, electrodynamic tether development, advanced electric propulsion, and in-space mechanism development. However, the scope of the ISPT program has focused over time to more closely match SMD needs and technology advancement successes. As a result, the funding for MXER and other EPT technologies is not currently available. Consequently, the MXER tether tasks and other EPT tasks were expected to phased out by November 2006. Presentation slides are presented which provide activity overviews for the aerocapture technology and emerging propulsion technology projects.

  15. Space station - Technology development

    NASA Technical Reports Server (NTRS)

    Carlisle, R. F.

    1984-01-01

    The NASA manned space station program's systems technology effort involves the development of novel techniques that will reduce the scope of tasks neeeded for design, development, testing and evaluation of the hardware. Operations technology efforts encompass analyses that will define those techniques best able to improve the efficiency and reduce the costs of space station functions. The technology objective for data management calls for a fault-tolerant, distributed, expandable and adaptable, as well as repairable and user-friendly, flight data management system that employs state-of-the-art hardware and software. The space station's power system includes the largest element, a 'solar blanket', and the heaviest component, the batteries, of all the subsystems. A thermal management system for the power system is of paramount importance. Attention is also given to the exacting demands of attitude control and stabilization and a regenerative life support system of the requisite capacity and reliability.

  16. Marine & hydrokinetic technology development.

    SciTech Connect

    LiVecchi, Al; Jepsen, Richard Alan

    2010-06-01

    The Wind and Water Power Program supports the development of marine and hydrokinetic devices, which capture energy from waves, tides, ocean currents, the natural flow of water in rivers, and marine thermal gradients, without building new dams or diversions. The program works closely with industry and the Department of Energy's national laboratories to advance the development and testing of marine and hydrokinetic devices. In 2008, the program funded projects to develop and test point absorber, oscillating wave column, and tidal turbine technologies. The program also funds component design, such as techniques for manufacturing and installing coldwater pipes critical for ocean thermal energy conversion (OTEC) systems. Rigorous device testing is necessary to validate and optimize prototypes before beginning full-scale demonstration and deployment. The program supports device testing by providing technology developers with information on testing facilities. Technology developers require access to facilities capable of simulating open-water conditions in order to refine and validate device operability. The program has identified more than 20 tank testing operators in the United States with capabilities suited to the marine and hydrokinetic technology industry. This information is available to the public in the program's Hydrodynamic Testing Facilities Database. The program also supports the development of open-water, grid-connected testing facilities, as well as resource assessments that will improve simulations done in dry-dock and closed-water testing facilities. The program has established two university-led National Marine Renewable Energy Centers to be used for device testing. These centers are located on coasts and will have open-water testing berths, allowing researchers to investigate marine and estuary conditions. Optimal array design, development, modeling and testing are needed to maximize efficiency and electricity generation at marine and hydrokinetic power

  17. Remediation Technology Collaboration Development

    NASA Technical Reports Server (NTRS)

    Mahoney, John; Olsen, Wade

    2010-01-01

    This slide presentation reviews programs at NASA aimed at development at Remediation Technology development for removal of environmental pollutants from NASA sites. This is challenging because there are many sites with different environments, and various jurisdictions and regulations. There are also multiple contaminants. There must be different approaches based on location and type of contamination. There are other challenges: such as costs, increased need for resources and the amount of resources available, and a regulatory environment that is increasing.

  18. Textile technology development

    NASA Technical Reports Server (NTRS)

    Shah, Bharat M.

    1995-01-01

    The objectives of this report were to evaluate and select resin systems for Resin Transfer Molding (RTM) and Powder Towpreg Material, to develop and evaluate advanced textile processes by comparing 2-D and 3-D braiding for fuselage frame applications and develop window belt and side panel structural design concepts, to evaluate textile material properties, and to develop low cost manufacturing and tooling processes for the automated manufacturing of fuselage primary structures. This research was in support of the NASA and Langley Research Center (LaRc) Advanced Composite Structural Concepts and Materials Technologies for Primary Aircraft Structures program.

  19. Technology Development Center at NICT

    NASA Technical Reports Server (NTRS)

    Takefuji, Kazuhiro; Ujihara, Hideki

    2013-01-01

    The National Institute of Information and Communications Technology (NICT) is developing and testing VLBI technologies and conducts observations with this new equipment. This report gives an overview of the Technology Development Center (TDC) at NICT and summarizes recent activities.

  20. ECH Technology Development

    SciTech Connect

    Temkin, Richard

    2014-12-24

    Electron Cyclotron Heating (ECH) is needed for plasma heating, current drive, plasma stability control, and other applications in fusion energy sciences research. The program of fusion energy sciences supported by U. S. DOE, Office of Science, Fusion Energy Sciences relies on the development of ECH technology to meet the needs of several plasma devices working at the frontier of fusion energy sciences research. The largest operating ECH system in the world is at DIII-D, consisting of six 1 MW, 110 GHz gyrotrons capable of ten second pulsed operation, plus two newer gyrotrons. The ECH Technology Development research program investigated the options for upgrading the DIII-D 110 GHz ECH system. Options included extending present-day 1 MW technology to 1.3 – 1.5 MW power levels or developing an entirely new approach to achieve up to 2 MW of power per gyrotron. The research consisted of theoretical research and designs conducted by Communication and Power Industries of Palo Alto, CA working with MIT. Results of the study would be validated in a later phase by research on short pulse length gyrotrons at MIT and long pulse / cw gyrotrons in industry. This research follows a highly successful program of development that has led to the highly reliable, six megawatt ECH system at the DIII-D tokamak. Eventually, gyrotrons at the 1.5 megawatt to multi-megawatt power level will be needed for heating and current drive in large scale plasmas including ITER and DEMO.

  1. Graphite Technology Development Plan

    SciTech Connect

    W. Windes; T. Burchell; R. Bratton

    2007-09-01

    This technology development plan is designed to provide a clear understanding of the research and development direction necessary for the qualification of nuclear grade graphite for use within the Next Generation Nuclear Plant (NGNP) reactor. The NGNP will be a helium gas cooled Very High Temperature Reactor (VHTR) with a large graphite core. Graphite physically contains the fuel and comprises the majority of the core volume. Considerable effort will be required to ensure that the graphite performance is not compromised during operation. Based upon the perceived requirements the major data needs are outlined and justified from the perspective of reactor design, reatcor performance, or the reactor safety case. The path forward for technology development can then be easily determined for each data need. How the data will be obtained and the inter-relationships between the experimental and modeling activities will define the technology development for graphite R&D. Finally, the variables affecting this R&D program are discussed from a general perspective. Factors that can significantly affect the R&D program such as funding, schedules, available resources, multiple reactor designs, and graphite acquisition are analyzed.

  2. Graphite Technology Development Plan

    SciTech Connect

    W. Windes; T. Burchell; M.Carroll

    2010-10-01

    The Next Generation Nuclear Plant (NGNP) will be a helium-cooled High Temperature Gas Reactor (HTGR) with a large graphite core. Graphite physically contains the fuel and comprises the majority of the core volume. Graphite has been used effectively as a structural and moderator material in both research and commercial high-temperature gas-cooled reactors. This development has resulted in graphite being established as a viable structural material for HTGRs. While the general characteristics necessary for producing nuclear grade graphite are understood, historical “nuclear” grades no longer exist. New grades must be fabricated, characterized, and irradiated to demonstrate that current grades of graphite exhibit acceptable non-irradiated and irradiated properties upon which the thermomechanical design of the structural graphite in NGNP is based. This Technology Development Plan outlines the research and development (R&D) activities and associated rationale necessary to qualify nuclear grade graphite for use within the NGNP reactor.

  3. SEDSAT-1 Technology Development

    NASA Technical Reports Server (NTRS)

    Maier, Mark W.; Wells, B. Earl

    1996-01-01

    The Students for the Exploration and Development of Space Satellite (SEDSAT-1) is an ambitious project to design, build, and fly a generally-accessible low-cost satellite which will 1) act as a technology demonstration to verify the suitability of novel optical, battery, microprocessor, and memory hardware for space flight environments, (2) to advance the understanding of tether dynamics and environmental science through the development of advanced imaging experiments, (3) to act as a communication link for radio amateurs, and (4) to provide graduate and undergraduate students with a unique multi-disciplinary experience in designing complex real-world hardware/software. This report highlights the progress made on this project during the time period from January 2, 1996 to June 1, 1996 at the end of which time the SEASIS 0.7 version software was completed and integrated on the SEASIS breadboard, a functional prototype of the Panoramic Annual Lenses (PAL) camera was developed, the preferred image compression technique was selected, the layout of the SEASIS board was begun, porting of the SCOS operating system to the command data system (CDS) board was begun, a new design for a tether release mechanism was developed, safety circuitry to inhibit tether cutting was developed and prototyped, material was prepared to support a comprehensive safety review of the project which was held at Johnson Space Center (JSC) (which was personally attended by one of the Principal Investigators), and prototype ground software was developed.

  4. Mars Aerocapture Studies for the Design Reference Mission

    NASA Technical Reports Server (NTRS)

    Lyne, James Evans; Wercinski, Paul; Walberg, Gerald; Jits, Roman

    1997-01-01

    The recent discovery of possible fossilized microbes in a Martian meteorite sample and the spectacular success of the Mars Pathfinder mission have substantially increased public interest and support for future robotic and manned exploration of Mars. NASA is currently refining a plan known as the Design Reference Mission (DRM) in which the first human landing would occur in 2014 after a series of cargo launches which would place surface systems and an Earth return vehicle at Mars two years prior to the crew's arrival. At each subsequent launch opportunity (which occur approximately every twenty-six months), an additional Earth return vehicle, surface facility and crew would depart for Mars, with each crew employing the systems launched during the previous opportunity. The mission design calls for a long-duration surface stay, rapid crew transits, in-situ manufacture of the Mars ascent propellant, nuclear thermal propulsion for the trans-Mars injection burn, and the use of aerocapture for both the cargo and crew vehicles at Mars.

  5. Physiological constraints on deceleration during the aerocapture of manned vehicles

    NASA Technical Reports Server (NTRS)

    Lyne, J. E.

    1992-01-01

    The peak deceleration load allowed for aerobraking of manned vehicles is a critical parameter in planning future excursions to Mars. However, considerable variation exists in the limits used by various investigators. The goal of this study was to determine the most appropriate level for this limit. Methods: Since previous U.S. space flights have been limited to 84 days duration, Soviet flight results were examined. Published details of Soviet entry trajectories were not available. However, personal communication with Soviet cosmonauts suggested that peak entry loads of 5-6 G had been encountered upon return from 8 months in orbit. Soyuz entry capsule's characteristics were established and the capsule's entry trajectory was numerically calculated. The results confirm a peak load of 5 to 6 G. Results: Although the Soviet flights were of shorter duration than expected Mars missions, evidence exists that the deceleration experience is applicable. G tolerance has been shown to stabilize after 1 to 3 months in space if adequate countermeasures are used. The calculated Soyuz deceleration histories are graphically compared with those expected for Mars aerobraking. Conclusions: Previous spaceflight experience supports the use of a 5 G limit for the aerocapture of a manned vehicle at Mars.

  6. Occulter Starshade Technology Development

    NASA Astrophysics Data System (ADS)

    Lisman, P. D.; Thomson, M.; Kissil, A.; Walkemeyer, P.; Polanco, O.

    2010-10-01

    Imaging Earth-like exoplanets with a free flying occulter requires developing a large, lightweight, flower-shaped, deployable structure with precisely controlled edge position and profile. In-plane tolerance requirements are considerably tighter than heritage antenna systems, but the more difficult to control out-of-plane tolerances are actually much looser. This paper presents a novel occulter mechanical design that delivers the required performance with a highly reliable deployment scheme. A very compact stowed volume is an added benefit that enables launching the occulter together with a 1 to 2m class telescope, using a single, currently available launch vehicle. Demonstrating the petal deployment function and compliance with key tolerance specifications is the focus of current technology efforts. A series of prototype models of increasing fidelity are planned, starting with a proof of concept model that is currently in fabrication. The occulter design and current development status is presented herein.

  7. Payload software technology: Software technology development plan

    NASA Technical Reports Server (NTRS)

    1977-01-01

    Programmatic requirements for the advancement of software technology are identified for meeting the space flight requirements in the 1980 to 1990 time period. The development items are described, and software technology item derivation worksheets are presented along with the cost/time/priority assessments.

  8. IDC Infrasound technology development

    NASA Astrophysics Data System (ADS)

    Mialle, P.; Brown, D. J.; Le Bras, R.; Charbit, M. J. C.; Given, J. W.

    2014-12-01

    The first atmospheric event built only from infrasound arrivals was reported in the Reviewed Event Bulletin (REB) of the International Data Centre (IDC) of the Comprehensive Nuclear Test Ban Treaty Organization (CTBTO) in 2003. In the last decade, 48 infrasound stations from the International Monitoring System (IMS) have been installed and are transmitting data to the IDC. The infrasound component of the IMS daily registers infragenic signals originating from various sources such as volcanic eruptions, earthquakes, microbaroms, meteorites entering the atmosphere and accidental explosions. The IDC routinely and automatically processes infrasound data reviewed by interactive analysis; the detected and located events are then included in the IDC products. The IDC advances its methods and continuously improves its automatic system for the infrasound technology. The IDC focuses on enhancing the automatic system for the identification of valid signals and the optimization of the network detection threshold by identifying ways to refine signal characterization methodology and association criteria. An objective of this study is to reduce the number of associated infrasound arrivals that are rejected from the automatic bulletins when generating the reviewed event bulletins. A number of ongoing projects at the IDC will be presented, such as: - improving the detection accuracy at the station processing stage by enhancing the infrasound signal detector DFX-PMCC (Detection and Feature eXtraction - Progressive Multi-Channel Correlation) and by evaluating the performances of detection software. - separating infrasound data from other waveform technologies at the automatic network processing stage for technology development and for preparing the implementation of next generation of waveform association algorithm. Infrasound rules in Global Association (GA) are revisited to pursue a lower ratio of false alarms. - determining station noise for IMS infrasound, seismic and

  9. JPL antenna technology development

    NASA Technical Reports Server (NTRS)

    Freeland, R. E.

    1981-01-01

    Plans for evaluating, designing, fabricating, transporting and deploying cost effective and STS compatible offset wrap rib antennas up to 300 meters in diameter for mobile communications, Earth resources observation, and for the orbiting VLBI are reviewed. The JPL surface measurement system, intended for large mesh deployable antenna applications will be demonstrated and validated as part of the antenna ground based demonstration program. Results of the offset wrap rib deployable antenna technology development will include: (1) high confidence structural designs for antennas up to 100 meters in diameter; (2) high confidence estimates of functional performance and fabrication cost for a wide range of antenna sizes (up to 300 meters in diameter); (3) risk assessment for fabricating the large size antennas; and (4) 55 meter diameter flight quality hardware that can be cost effectively completed toto accommodate a flight experiment and/or application.

  10. A Design Study of Onboard Navigation and Guidance During Aerocapture at Mars. M.S. Thesis

    NASA Technical Reports Server (NTRS)

    Fuhry, Douglas Paul

    1988-01-01

    The navigation and guidance of a high lift-to-drag ratio sample return vehicle during aerocapture at Mars are investigated. Emphasis is placed on integrated systems design, with guidance algorithm synthesis and analysis based on vehicle state and atmospheric density uncertainty estimates provided by the navigation system. The latter utilizes a Kalman filter for state vector estimation, with useful update information obtained through radar altimeter measurements and density altitude measurements based on IMU-measured drag acceleration. A three-phase guidance algorithm, featuring constant bank numeric predictor/corrector atmospheric capture and exit phases and an extended constant altitude cruise phase, is developed to provide controlled capture and depletion of orbital energy, orbital plane control, and exit apoapsis control. Integrated navigation and guidance systems performance are analyzed using a four degree-of-freedom computer simulation. The simulation environment includes an atmospheric density model with spatially correlated perturbations to provide realistic variations over the vehicle trajectory. Navigation filter initial conditions for the analysis are based on planetary approach optical navigation results. Results from a selection of test cases are presented to give insight into systems performance.

  11. Mars Technology Program: Planetary Protection Technology Development

    NASA Technical Reports Server (NTRS)

    Lin, Ying

    2006-01-01

    This slide presentation reviews the development of Planetary Protection Technology in the Mars Technology Program. The goal of the program is to develop technologies that will enable NASA to build, launch, and operate a mission that has subsystems with different Planetary Protection (PP) classifications, specifically for operating a Category IVb-equivalent subsystem from a Category IVa platform. The IVa category of planetary protection requires bioburden reduction (i.e., no sterilization is required) The IVb category in addition to IVa requirements: (i.e., terminal sterilization of spacecraft is required). The differences between the categories are further reviewed.

  12. Advanced Adaptive Optics Technology Development

    SciTech Connect

    Olivier, S

    2001-09-18

    The NSF Center for Adaptive Optics (CfAO) is supporting research on advanced adaptive optics technologies. CfAO research activities include development and characterization of micro-electro-mechanical systems (MEMS) deformable mirror (DM) technology, as well as development and characterization of high-resolution adaptive optics systems using liquid crystal (LC) spatial light modulator (SLM) technology. This paper presents an overview of the CfAO advanced adaptive optics technology development activities including current status and future plans.

  13. Haystack Observatory Technology Development Center

    NASA Technical Reports Server (NTRS)

    Beaudoin, Chris; Corey, Brian; Niell, Arthur; Cappallo, Roger; Whitney, Alan

    2013-01-01

    Technology development at MIT Haystack Observatory were focused on four areas in 2012: VGOS developments at GGAO; Digital backend developments and workshop; RFI compatibility at VLBI stations; Mark 6 VLBI data system development.

  14. Mars Technology Program Planetary Protection Technology Development

    NASA Technical Reports Server (NTRS)

    Lin, Ying

    2006-01-01

    The objectives of the NASA Planetary Protection program are to preserve biological and organic conditions of solar-system bodies for future scientific exploration and to protect the Earth from potential hazardous extraterrestrial contamination. As the exploration of solar system continues, NASA remains committed to the implementation of planetary protection policy and regulations. To fulfill this commitment, the Mars Technology Program (MTP) has invested in a portfolio of tasks for developing necessary technologies to meet planetary protection requirements for the next decade missions.

  15. Technology Education and Development

    ERIC Educational Resources Information Center

    Lazinica, Aleksandar, Ed.; Calafate, Carlos, Ed.

    2009-01-01

    The widespread deployment and use of Information Technologies (IT) has paved the way for change in many fields of our societies. The Internet, mobile computing, social networks and many other advances in human communications have become essential to promote and boost education, technology and industry. On the education side, the new challenges…

  16. Development and Validation of Reentry Simulation Using MATLAB

    DTIC Science & Technology

    2006-03-01

    used in the planning for the Mars Airplane (Murray, 2001:3), the aerocapture simulation for the Titan Explorer Mission to the Saturnian system (Way...1980. 17. Way, David W., et al. Aerocapture Simulation and Performance for the Titan Explorer Mission. 2003-4951. American Institute of...DEVELOPMENT AND VALIDATION OF REENTRY SIMULATION USING MATLAB THESIS Robert E Jameson Jr

  17. Orbital transfer vehicle concept definition and system analysis study. Volume 10: Aerocapture for manned Mars missions

    NASA Technical Reports Server (NTRS)

    Willcockson, W. H.

    1988-01-01

    A manned expedition to Mars has been under consideration as a potential mission for the early 21st century. The necessarily large vehicle requirements have sparked interest in aerocapture as a means of reducing propellant usage. This volume summarizes the work performed to establish concepts and feasibility of such a mission which makes maximum use of aeroassist maneuvers.

  18. Smart Fabrics Technology Development

    NASA Technical Reports Server (NTRS)

    Simon, Cory; Potter, Elliott; Potter, Elliott; McCabe, Mary; Baggerman, Clint

    2010-01-01

    Advances in Smart Fabrics technology are enabling an exciting array of new applications for NASA exploration missions, the biomedical community, and consumer electronics. This report summarizes the findings of a brief investigation into the state of the art and potential applications of smart fabrics to address challenges in human spaceflight.

  19. Developments in Enzyme Technology.

    ERIC Educational Resources Information Center

    Chaplin, M. F.

    1984-01-01

    Enzyme technology has a well-established industrial base, with applications that have survived competition. The most prominent applications of enzymes in biotechnology are examined with an explanation of some theoretical background. Topics include extending an enzyme's useful life, partition and diffusion, industrial uses, and therapeutic uses.…

  20. Robotics Technology Development Program. Technology summary

    SciTech Connect

    Not Available

    1994-02-01

    The Robotics Technology Development Program (RTDP) is a ``needs-driven`` effort. A lengthy series of presentations and discussions at DOE sites considered critical to DOE`s Environmental Restoration and Waste Management (EM) Programs resulted in a clear understanding of needed robotics applications toward resolving definitive problems at the sites. A detailed analysis of the Tank Waste Retrieval (TWR), Contaminant Analysis Automation (CAA), Mixed Waste Operations (MWO), and Decontamination & Dismantlement (D&D). The RTDP Group realized that much of the technology development was common (Cross Cutting-CC) to each of these robotics application areas, for example, computer control and sensor interface protocols. Further, the OTD approach to the Research, Development, Demonstration, Testing, and Evaluation (RDDT&E) process urged an additional organizational break-out between short-term (1--3 years) and long-term (3--5 years) efforts (Advanced Technology-AT). The RDTP is thus organized around these application areas -- TWR, CAA, MWO, D&D and CC&AT -- with the first four developing short-term applied robotics. An RTDP Five-Year Plan was developed for organizing the Program to meet the needs in these application areas.

  1. Technology development in space projects

    NASA Astrophysics Data System (ADS)

    Kelhae, Vaeinoe; Kurki, Jouko

    1993-01-01

    Space activities have existed for 34 years around the world. Demanding technology operating in extreme conditions has been developed for space projects, instruments, satellites and shuttles. The nature of space technology is basic development and it also serves well the purposes of conventional, industrial and commercial applications. ESA's industrial return makes it possible for the industry and research organizations to participate in space projects. In that way, Finland has a possibility to widen its technological know-how base, get technology knowledge for developing new commercial products, and get a base for controlling quality. Many of the space instrument and Earth observation projects (for example, GOMOS ozone analyzer) are also socially important.

  2. New Space Technology Development

    NASA Technical Reports Server (NTRS)

    Mueller, Rob

    2014-01-01

    Visitors from Moon Express, a privately funded commercial space company, will be visiting KSC Swamp Works. This presentation includes a high-level introduction to NASA and commercial partnerships, as well as brief background on the moon - what we used to think about it hundreds of years ago, and what we know today with advanced technologies.***This third part being added includes Swamp Works technical capabilities and has a high-level overview of a selection of projects.***

  3. JWST Mirror Technology Development

    NASA Technical Reports Server (NTRS)

    Stahl, H. Philip

    2010-01-01

    Since the initial Design Studies leading to JWST, Mirror Technology was identified as a (if not the) critical capability necessary to enable the next generation of large aperture space telescopes required to achieve the science goals of imaging the earliest galaxies and proto-galaxies after the big bang. Specific telescope architectures were explored via three independent design concept studies conducted during the summer of 1996. Achieving the desired science objectives required a never before demonstrated space telescope capability, one with an 8 meter class primary mirror that is diffraction limited at 2 micrometers and operating in deep space at temperatures well below 70K. Beryllium was identified in the NASA "Yardstick" design as the preferred material because of its ability to provide stable optical performance in the anticipated thermal environment as well as its excellent specific stiffness. Because of launch vehicle constraints, two very significant architectural constraints were placed upon the telescope: segmentation and areal density. Each of these directly resulted in specific technology capability requirements. First, because the maximum launch vehicle payload fairing diameter is approximately 4.5 meters, the only way to launch an 8 meter class mirror is to segment it, fold it and deploy it on orbit - resulting in actuation and control requirements. Second, because of launch vehicle mass limits, the primary mirror allocation was only 1000 kg - resulting in a maximum areal density specification of 20 kilograms per square meter.

  4. NASA In-Space Propulsion Technologies and Their Infusion Potential

    NASA Technical Reports Server (NTRS)

    Anderson, David; Munk, Michelle; Pencil, Eric; Dankanich, John; Glaab, Lou; Peterson, Todd; Vento, Dan

    2012-01-01

    The In-Space Propulsion Technology (ISPT) program has been developing in-space propulsion technologies that will enable or enhance NASA robotic science missions. The ISPT program is currently developing technology in four areas that include Propulsion System Technologies (Electric and Chemical), Entry Vehicle Technologies (Aerocapture and Earth entry vehicles), Spacecraft Bus and Sample Return Propulsion Technologies (components and ascent vehicles), and Systems/Mission Analysis. Three technologies are ready for flight infusion: 1) the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance; 2) NASA s Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system; and 3) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures; guidance, navigation, and control (GN&C) models of blunt-body rigid aeroshells; and aerothermal effect models. Two component technologies that will be ready for flight infusion in the near future will be Advanced Xenon Flow Control System, and ultra-lightweight propellant tank technologies. Future focuses for ISPT are sample return missions and other spacecraft bus technologies like: 1) Mars Ascent Vehicles (MAV); 2) multi-mission technologies for Earth Entry Vehicles (MMEEV) for sample return missions; and 3) electric propulsion for sample return and low cost missions. These technologies are more vehicle-focused, and present a different set of technology infusion challenges. While the Systems/Mission Analysis area is focused on developing tools and assessing the application of propulsion technologies to a wide variety of mission concepts. These in-space propulsion technologies are applicable, and potentially enabling for future NASA Discovery, New Frontiers, and sample return missions currently under consideration, as well as having broad applicability to potential Flagship missions. This paper

  5. Aerodynamic requirements for a Mars rover/sample return aerocapture vehicle

    NASA Technical Reports Server (NTRS)

    Ess, Robert H., Jr.; Munday, Stephen R.

    1989-01-01

    The sensitivity of Martian aerocapture performance to L/D and flight path angle is studied. By adding the minimum energy constraint to the classical corridor width definition, an L/D of at least 0.8 was found to be necessary to ensure a 3.0-deg actual corridor width. The plane change desired during the aeropass was also found to affect L/D requirements.

  6. Insensitive control technology development

    NASA Technical Reports Server (NTRS)

    Harvey, C. A.; Pope, R. E.

    1978-01-01

    THe investigation of two insensitive controller synthesis techniques was reported. The finite dimensional inverse approach produces a time varying insensitive controller and/or parameter identifier by constructing inverse functions derived from a finite number of input output pair relationships. The MD/IM concept relies on the information matrix theory that was developed in the estimation and identification field. The MD/IM synthesis technique is based on the hypothesis that minimizing the information matrix will reduce system identifiability and consequently system sensitivity to uncertain parameters. The controllers designed with both techniques were evaluated on a realistic C-5A aircraft flight control problem. Results indicate that the FDI controller is more suited to trajectory type problems because of its time varying nature. The MD/IM controller performed as well as the top-rated controllers of the initial effort and has direct application to aircraft flight control problems.

  7. Magnetic Suspension Technology Development

    NASA Technical Reports Server (NTRS)

    Britcher, Colin

    1998-01-01

    This Cooperative Agreement, intended to support focused research efforts in the area of magnetic suspension systems, was initiated between NASA Langley Research Center (LaRC) and Old Dominion University (ODU) starting January 1, 1997. The original proposal called for a three-year effort, but funding for the second year proved to be unavailable, leading to termination of the agreement following a 5-month no-cost extension. This report covers work completed during the entire 17-month period of the award. This research built on work that had taken place over recent years involving both NASA LARC and the Principal Investigator (PI). The research was of a rather fundamental nature, although specific applications were kept in mind at all times, such as wind tunnel Magnetic Suspension and Balance Systems (MSBS), space payload pointing and vibration isolation systems, magnetic bearings for unconventional applications, magnetically levitated ground transportation and electromagnetic launch systems. Fundamental work was undertaken in areas such as the development of optimized magnetic configurations, analysis and modelling of eddy current effects, control strategies for magnetically levitated wind tunnel models and system calibration procedures. Despite the termination of this Cooperative Agreement, several aspects of the research work are currently continuing with alternative forms of support.

  8. Thermal protection system development, testing, and qualification for atmospheric probes and sample return missions. Examples for Saturn, Titan and Stardust-type sample return

    NASA Astrophysics Data System (ADS)

    Venkatapathy, E.; Laub, B.; Hartman, G. J.; Arnold, J. O.; Wright, M. J.; Allen, G. A.

    2009-07-01

    The science community has continued to be interested in planetary entry probes, aerocapture, and sample return missions to improve our understanding of the Solar System. As in the case of the Galileo entry probe, such missions are critical to the understanding not only of the individual planets, but also to further knowledge regarding the formation of the Solar System. It is believed that Saturn probes to depths corresponding to 10 bars will be sufficient to provide the desired data on its atmospheric composition. An aerocapture mission would enable delivery of a satellite to provide insight into how gravitational forces cause dynamic changes in Saturn's ring structure that are akin to the evolution of protoplanetary accretion disks. Heating rates for the "shallow" Saturn probes, Saturn aerocapture, and sample Earth return missions with higher re-entry speeds (13-15 km/s) from Mars, Venus, comets, and asteroids are in the range of 1-6 KW/cm 2. New, mid-density thermal protection system (TPS) materials for such probes can be mission enabling for mass efficiency and also for use on smaller vehicles enabled by advancements in scientific instrumentation. Past consideration of new Jovian multiprobe missions has been considered problematic without the Giant Planet arcjet facility that was used to qualify carbon phenolic for the Galileo probe. This paper describes emerging TPS technologies and the proposed use of an affordable, small 5 MW arcjet that can be used for TPS development, in test gases appropriate for future planetary probe and aerocapture applications. Emerging TPS technologies of interest include new versions of the Apollo Avcoat material and a densified variant of Phenolic Impregnated Carbon Ablator (PICA). Application of these and other TPS materials and the use of other facilities for development and qualification of TPS for Saturn, Titan, and Sample Return missions of the Stardust class with entry speeds from 6.0 to 28.6 km/s are discussed.

  9. Testing of Candidate Rigid Heatshield Materials at LHMEL for the Entry, Descent, and Landing Technology Development Project

    NASA Technical Reports Server (NTRS)

    Sepka, Steven; Gasch, Matthew; Beck, Robin A.; White, Susan

    2012-01-01

    The material testing results described in this paper were part of a material development program of vendor-supplied, proposed heat shield materials. The goal of this program was to develop low density, rigid material systems with an appreciable weight savings over phenolic-impregnated carbon ablator (PICA) while improving material response performance. New technologies, such as PICA-like materials in honeycomb or materials with variable density through-the-thickness were tested. The material testing took place at the Wright-Patterson Air Force Base Laser Hardened Materials Laboratory (LHMEL) using a 10.6 micron CO2 laser operating with the test articles immersed in a nitrogen-gas environment at 1 atmosphere pressure. Test measurements included thermocouple readings of in-depth temperatures, pyrometer readings of surface temperatures, weight scale readings of mass loss, and sectioned-sample readings of char depth. Two laser exposures were applied. The first exposure was at an irradiance of 450 W/cm2 for 50 or 60 seconds to simulate an aerocapture maneuver. The second laser exposure was at an irradiance of 115 W/cm2 for 100 seconds to simulate a planetary entry. Results from Rounds 1 and 2 of these screening tests are summarized.

  10. JWST Mirror Technology Development Results

    NASA Technical Reports Server (NTRS)

    Stahl, H. Philip

    2007-01-01

    Mirror technology is a critical enabling capability for the James Webb Space Telescope (JWST). JWST requires a Primary Mirror Segment Assembly (PMSA) that can survive launch, deploy and align itself to form a 25 square meter collecting area 6.5 meter diameter primary mirror with a 131 nm rms wavefront error at temperatures less than 50K and provide stable optical performance. At the inception of JWST in 1996, such a capability did not exist. A highly successful technology development program was initiated including the Sub-scale Beryllium Mirror Demonstrator (SBMD) and Advanced Mirror System Demonstrator (AMSD) projects. These projects along with flight program activities have matured and demonstrated mirror technology for JWST. Directly traceable prototypes or flight hardware has been built, tested and operated in a relevant environment. This paper summarizes that technology development effort.

  11. VLBI Technology Development at SHAO

    NASA Technical Reports Server (NTRS)

    Zhang, Xiuzhong; Shu, Fengchun; Xiang, Ying; Zhu, Renjie; Xu, Zhijun; Chen, Zhong; Zheng, Weimin; Luo, Jintao; Wu, Yajun

    2010-01-01

    VLBI technology development made significant progress at SHAO in the last few years. The development status of the Chinese DBBC, the software and FPGA-based correlators, and the new VLBI antenna, as well as VLBI applications are summarized in this paper.

  12. Astronomy, technology development and industry

    NASA Astrophysics Data System (ADS)

    Vigroux, Laurent

    2011-06-01

    Astronomy is perhaps the best example of fundamental research aiming to increase our knowledge well beyond our human neighborhood. But astronomy is also a Big Science, which is partly technology-driven. Progress in observational capabilities is due to progress in detectors, telescopes, satellites, etc. I use three examples -radio astronomy, adaptive optics and detectors- to describe the complex interactions between astronomy, technology development and industry. I conclude by a short description of the global economic impact of astronomy.

  13. Advanced Mirror & Modelling Technology Development

    NASA Technical Reports Server (NTRS)

    Effinger, Michael; Stahl, H. Philip; Abplanalp, Laura; Maffett, Steven; Egerman, Robert; Eng, Ron; Arnold, William; Mosier, Gary; Blaurock, Carl

    2014-01-01

    The 2020 Decadal technology survey is starting in 2018. Technology on the shelf at that time will help guide selection to future low risk and low cost missions. The Advanced Mirror Technology Development (AMTD) team has identified development priorities based on science goals and engineering requirements for Ultraviolet Optical near-Infrared (UVOIR) missions in order to contribute to the selection process. One key development identified was lightweight mirror fabrication and testing. A monolithic, stacked, deep core mirror was fused and replicated twice to achieve the desired radius of curvature. It was subsequently successfully polished and tested. A recently awarded second phase to the AMTD project will develop larger mirrors to demonstrate the lateral scaling of the deep core mirror technology. Another key development was rapid modeling for the mirror. One model focused on generating optical and structural model results in minutes instead of months. Many variables could be accounted for regarding the core, face plate and back structure details. A portion of a spacecraft model was also developed. The spacecraft model incorporated direct integration to transform optical path difference to Point Spread Function (PSF) and between PSF to modulation transfer function. The second phase to the project will take the results of the rapid mirror modeler and integrate them into the rapid spacecraft modeler.

  14. Lost Circulation Technology Development Status

    SciTech Connect

    Glowka, David A.; Schafer, Diane M.; Loeppke, Glen E.; Scott, Douglas D.; Wernig, Marcus D.; Wright, Elton K.

    1992-03-24

    Lost circulation is the loss of drilling fluid from the wellbore to fractures or pores in the rock formation. In geothermal drilling, lost circulation is often a serious problem that contributes greatly to the cost of the average geothermal well. The Lost Circulation Technology Development Program is sponsored at Sandia National Laboratories by the U.S. Department of Energy. The goal of the program is to reduce lost circulation costs by 30-50% through the development of mitigation and characterization technology. This paper describes the technical progress made in this program during the period April, 1991-March, 1992.

  15. Night vision device technology development

    SciTech Connect

    Funsten, H.; Nordholt, J.; Suszcynsky, D.

    1996-09-01

    This is the final report of a one-year, Laboratory-Directed Research and Development (LDRD) project at the Los Alamos National Laboratory (LANL). This project sought to develop microchannel plate (MCP) technologies for enhancement of night vision device (NVD) capabilities. First, segmented microchannel plates with independent gain control to minimize loss of low level light images in the presence of a bright light source (e.g., battlefield lasers, flares, and headlights) need to be developed. This enables, for example, enhanced vision capabilities during night operations in, for example, a city environment and continuous capability of aviators to see the horizon, nearground obstructions, and ground targets. Furthermore, curved microchannel plate technology to increase the field of view of NVDs while minimizing optical aberrations needs to be developed and applied. This development would significantly enhance peripheral vision capabilities of aviators and result in easier adaptation of the human eye to NVDs.

  16. Satellite Servicing Technology Development Missions

    NASA Technical Reports Server (NTRS)

    Middleton, R.; Waltz, D.; Schrock, S.

    1984-01-01

    A new capability regarding the U.S. space efforts will be related to the servicing of satellites in orbit utilizing first-generation space station as the collection point or base for Shuttle-delivered payloads. Orbital maneuvering vehicles could move payloads or spacecraft assembled at the Shuttle/space station terminus to other earth orbit locations. It is assumed that such a capability will be initially available in the early 1990's. The benefits provided by satellite servicing in orbit are discussed, taking into account extended satellite lifetimes, lower acquisition cost, improved satellite performance, the possibility to change a satellite's mission, optimized science, and higher satellite reliability. The requirements for Satellite Servicing Technology Development Missions (TDMs) are considered. It is found that existing technology is insufficient, in various areas, to perform the servicing operations. A list is provided of critical technologies which must be developed.

  17. Technology to Develop Algebraic Reasoning

    ERIC Educational Resources Information Center

    Polly, Drew

    2011-01-01

    Students' use of technology allows them to generate and manipulate multiple representations of a concept, compute numbers with relative ease, and focus more on mathematical concepts and higher-order thinking skills. In elementary school mathematics classrooms, students develop higher-order thinking skills by completing complex tasks that require…

  18. Technology and Motor Ability Development

    ERIC Educational Resources Information Center

    Wang, Lin; Lang, Yong; Luo, Zhongmin

    2014-01-01

    As a new member joining the technology family, active video games have been developed to promote physical exercise. This working-in-progress paper shares an ongoing project on examining the basic motor abilities that are enhanced through participating in commercially available active video games. [For the full proceedings see ED557181.

  19. Unshrouded Impeller Technology Development Status

    NASA Technical Reports Server (NTRS)

    Droege, Alan R.; Williams, Robert W.; Garcia, Roberto

    2000-01-01

    To increase payload and decrease the cost of future Reusable Launch Vehicles (RLVs), engineers at NASA/MSFC and Boeing, Rocketdyne are developing unshrouded impeller technology for application to rocket turbopumps. An unshrouded two-stage high-pressure fuel pump is being developed to meet the performance objectives of a three-stage shrouded pump. The new pump will have reduced manufacturing costs and pump weight. The lower pump weight will allow for increased payload.

  20. Products from NASA's In-Space Propulsion Technology Program Applicable to Low-Cost Planetary Missions

    NASA Technical Reports Server (NTRS)

    Anderson, David J.; Pencil, Eric; Vento, Daniel; Peterson, Todd; Dankanich, John; Hahne, David; Munk, Michelle M.

    2011-01-01

    Since September 2001 NASA s In-Space Propulsion Technology (ISPT) program has been developing technologies for lowering the cost of planetary science missions. Recently completed is the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance for lower cost. Two other cost saving technologies nearing completion are the NEXT ion thruster and the Aerocapture technology project. Also under development are several technologies for low cost sample return missions. These include a low cost Hall effect thruster (HIVHAC) which will be completed in 2011, light weight propellant tanks, and a Multi-Mission Earth Entry Vehicle (MMEEV). This paper will discuss the status of the technology development, the cost savings or performance benefits, and applicability of these in-space propulsion technologies to NASA s future Discovery, and New Frontiers missions, as well as their relevance for sample return missions.

  1. Technology development life cycle processes.

    SciTech Connect

    Beck, David Franklin

    2013-05-01

    This report and set of appendices are a collection of memoranda originally drafted in 2009 for the purpose of providing motivation and the necessary background material to support the definition and integration of engineering and management processes related to technology development. At the time there was interest and support to move from Capability Maturity Model Integration (CMMI) Level One (ad hoc processes) to Level Three. As presented herein, the material begins with a survey of open literature perspectives on technology development life cycles, including published data on %E2%80%9Cwhat went wrong.%E2%80%9D The main thrust of the material presents a rational expose%CC%81 of a structured technology development life cycle that uses the scientific method as a framework, with further rigor added from adapting relevant portions of the systems engineering process. The material concludes with a discussion on the use of multiple measures to assess technology maturity, including consideration of the viewpoint of potential users.

  2. The NASA In-Space Propulsion Technology Project, Products, and Mission Applicability

    NASA Technical Reports Server (NTRS)

    Anderson, David J.; Pencil, Eric; Liou, Larry; Dankanich, John; Munk, Michelle M.; Kremic, Tibor

    2009-01-01

    The In-Space Propulsion Technology (ISPT) Project, funded by NASA s Science Mission Directorate (SMD), is continuing to invest in propulsion technologies that will enable or enhance NASA robotic science missions. This overview provides development status, near-term mission benefits, applicability, and availability of in-space propulsion technologies in the areas of aerocapture, electric propulsion, advanced chemical thrusters, and systems analysis tools. Aerocapture investments improved: guidance, navigation, and control models of blunt-body rigid aeroshells; atmospheric models for Earth, Titan, Mars, and Venus; and models for aerothermal effects. Investments in electric propulsion technologies focused on completing NASA s Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6 to 7 kW throttle-able gridded ion system. The project is also concluding its High Voltage Hall Accelerator (HiVHAC) mid-term product specifically designed for a low-cost electric propulsion option. The primary chemical propulsion investment is on the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance for lower cost. The project is also delivering products to assist technology infusion and quantify mission applicability and benefits through mission analysis and tools. In-space propulsion technologies are applicable, and potentially enabling for flagship destinations currently under evaluation, as well as having broad applicability to future Discovery and New Frontiers mission solicitations.

  3. NASA's In-Space Propulsion Technology Project Overview, Near-term Products and Mission Applicability

    NASA Technical Reports Server (NTRS)

    Dankanich, John; Anderson, David J.

    2008-01-01

    The In-Space Propulsion Technology (ISPT) Project, funded by NASA's Science Mission Directorate (SMD), is continuing to invest in propulsion technologies that will enable or enhance NASA robotic science missions. This overview provides development status, near-term mission benefits, applicability, and availability of in-space propulsion technologies in the areas of aerocapture, electric propulsion, advanced chemical thrusters, and systems analysis tools. Aerocapture investments improved (1) guidance, navigation, and control models of blunt-body rigid aeroshells, 2) atmospheric models for Earth, Titan, Mars and Venus, and 3) models for aerothermal effects. Investments in electric propulsion technologies focused on completing NASA s Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system. The project is also concluding its High Voltage Hall Accelerator (HiVHAC) mid-term product specifically designed for a low-cost electric propulsion option. The primary chemical propulsion investment is on the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance for lower cost. The project is also delivering products to assist technology infusion and quantify mission applicability and benefits through mission analysis and tools. In-space propulsion technologies are applicable, and potentially enabling for flagship destinations currently under evaluation, as well as having broad applicability to future Discovery and New Frontiers mission solicitations.

  4. Theory and applications of ballute aerocapture and dual-use ballute systems for exploration of the solar system

    NASA Astrophysics Data System (ADS)

    Medlock, Kristin Lynne Gates

    The use of a large, lightweight inflatable device for aerocapture could provide a significant mass savings over propulsive orbit insertion or rigid aeroshell aerocapture. Ballute aerocapture combines the benefit of non-propulsive capture with the advantages of high altitude capture, such as lower heating rates than achieved with traditional aeroshells. The dual-use ballute concept employs the ballute to capture a spacecraft and, subsequently, descend a payload to the surface. The primary objective of this thesis is to determine the feasibility of using ballute aerocapture systems and dual-use ballute systems at the atmosphere-bearing bodies in the Solar System. In anticipation of future human missions, particular attention is paid to the problem of delivering high-mass payloads to Mars. To date, no dual-use ballute studies, neither numerical nor analytical, have been published. In this investigation, new and existing analytical theories are derived and explicit expressions are found for the maximum heating rates, maximum deceleration, and maximum dynamic pressure during a dual-use ballute trajectory. Each of the resulting expressions is a function of the ballistic coefficient and of the capture trajectory, which in turn provides the required size (area/mass ratio) of the ballute for the dual-use ballute system. An aerocapture study is conducted to assess propellant mass costs for orbit insertion and compare those costs to the system masses of aerocapture ballutes and aerocapture tethers at Venus, Earth, Mars, Jupiter, Saturn, Titan, Uranus, and Neptune. Based on the mass comparison, ballutes are more favorable than tethers and propellant for Venus, Earth, Mars, Titan, Uranus, and Neptune, and least favorable for Jupiter. Aerothermodynamic and trajectory analysis is critical in determining if ballutes are feasible for high-mass Mars aerocapture and entry applications. Trajectories, thermal protection system (TPS) trades, and aerothermodynamics of ballute

  5. Advanced Modular Inverter Technology Development

    SciTech Connect

    Adam Szczepanek

    2006-02-04

    Electric and hybrid-electric vehicle systems require an inverter to convert the direct current (DC) output of the energy generation/storage system (engine, fuel cells, or batteries) to the alternating current (AC) that vehicle propulsion motors use. Vehicle support systems, such as lights and air conditioning, also use the inverter AC output. Distributed energy systems require an inverter to provide the high quality AC output that energy system customers demand. Today's inverters are expensive due to the cost of the power electronics components, and system designers must also tailor the inverter for individual applications. Thus, the benefits of mass production are not available, resulting in high initial procurement costs as well as high inverter maintenance and repair costs. Electricore, Inc. (www.electricore.org) a public good 501 (c) (3) not-for-profit advanced technology development consortium assembled a highly qualified team consisting of AeroVironment Inc. (www.aerovironment.com) and Delphi Automotive Systems LLC (Delphi), (www.delphi.com), as equal tiered technical leads, to develop an advanced, modular construction, inverter packaging technology that will offer a 30% cost reduction over conventional designs adding to the development of energy conversion technologies for crosscutting applications in the building, industry, transportation, and utility sectors. The proposed inverter allows for a reduction of weight and size of power electronics in the above-mentioned sectors and is scalable over the range of 15 to 500kW. The main objective of this program was to optimize existing AeroVironment inverter technology to improve power density, reliability and producibility as well as develop new topology to reduce line filter size. The newly developed inverter design will be used in automotive and distribution generation applications. In the first part of this program the high-density power stages were redesigned, optimized and fabricated. One of the main tasks

  6. Magnesium Research and Technology Development

    SciTech Connect

    Nyberg, Eric A.; Joost, William; Smith, Mark T.

    2009-12-30

    The Magnesium Research and Technical Development (MR&TD) project supports efforts to increase using magnesium in automotive applications, including improving technology, lowering costs and increasing the knowledge needed to enable alloy and manufacturing process optimization. MR&TD supports the U.S. Department of Energy (DOE)/United States Automotive Materials Partnership (USAMP) Magnesium Front End Research and Development (MFERD) project in collaboration with China and Canada. The MR&TD projects also maintains the magnesium bibliographic database at magnesium.pnl.gov.

  7. Benefits of Application of Advanced Technologies for a Neptune Orbiter, Atmospheric Probes and Triton Lander

    NASA Technical Reports Server (NTRS)

    Somers, Alan; Celano, Luigi; Kauffman, Jeffrey; Rogers, Laura; Peterson, Craig

    2005-01-01

    Missions with planned launch dates several years from today pose significant design challenges in properly accounting for technology advances that may occur in the time leading up to actual spacecraft design, build, test and launch. Conceptual mission and spacecraft designs that rely solely on off the shelf technology will result in conservative estimates that may not be attractive or truly representative of the mission as it actually will be designed and built. This past summer, as part of one of NASA s Vision Mission Studies, a group of students at the Laboratory for Spacecraft and Mission Design (LSMD) have developed and analyzed different Neptune mission baselines, and determined the benefits of various assumed technology improvements. The baseline mission uses either a chemical propulsion system or a solar-electric system. Insertion into orbit around Neptune is achieved by means of aerocapture. Neptune s large moon Triton is used as a tour engine. With these technologies a comprehensive Cassini-class investigation of the Neptune system is possible. Technologies under investigation include the aerocapture heat shield and thermal protection system, both chemical and solar electric propulsion systems, spacecraft power, and energy storage systems.

  8. EAGLE: relay mirror technology development

    NASA Astrophysics Data System (ADS)

    Hartman, Mary; Restaino, Sergio R.; Baker, Jeffrey T.; Payne, Don M.; Bukley, Jerry W.

    2002-06-01

    EAGLE (Evolutionary Air & Space Global Laser Engagement) is the proposed high power weapon system with a high power laser source, a relay mirror constellation, and the necessary ground and communications links. The relay mirror itself will be a satellite composed of two optically-coupled telescopes/mirrors used to redirect laser energy from ground, air, or space based laser sources to distant points on the earth or space. The receiver telescope captures the incoming energy, relays it through an optical system that cleans up the beam, then a separate transmitter telescope/mirror redirects the laser energy at the desired target. Not only is it a key component in extending the range of DoD's current laser weapon systems, it also enables ancillary missions. Furthermore, if the vacuum of space is utilized, then the atmospheric effects on the laser beam propagation will be greatly attenuated. Finally, several critical technologies are being developed to make the EAGLE/Relay Mirror concept a reality, and the Relay Mirror Technology Development Program was set up to address them. This paper will discuss each critical technology, the current state of the work, and the future implications of this program.

  9. Developing optic technologies in Belarus

    NASA Astrophysics Data System (ADS)

    Rubanov, Alexander S.; Shkadarevich, Alexei P.

    2001-03-01

    In this work we give a retrospective analysis of the development of optical technologies in Belarus. In the post-war period a great scientific and technological potential has been built up in this sphere, highly skilled specialist have been trained and prestigious scientific and technical schools have appeared. Belarusian multiprofile optical industry is noticed to be capable of producing not only the materials and equipment for optical production but also optical goods of the highest level of complication. The characteristics of cosmic photoequipment, photogrammetric and cinetheodolite techniques, a variety of laser devices and optical goods for civic purposes are given as an example. The instances demonstrating the realization of unique optical projects are considered as well. High quality of Belarusian optical production makes it be much in demand in Russia, Japan, USA, Germany, France, China, Korea, Sweden, Spain, England, United Arab Emirates and other countries.

  10. Children's Developing Understanding of Technology

    ERIC Educational Resources Information Center

    Mawson, Brent

    2010-01-01

    The issue of children's conceptions of technology and technology education is seen as important by technology educators. While there is a solid body of literature that documents groups of children's understandings of technology and technology education, this is primarily focused on snapshot studies of children aged 11 and above. There is little…

  11. Technology Development for NASA Mars Missions

    NASA Technical Reports Server (NTRS)

    Hayati, Samad

    2005-01-01

    A viewgraph presentation on technology development for NASA Mars Missions is shown. The topics include: 1) Mars mission roadmaps; 2) Focus and Base Technology programs; 3) Technology Infusion; and 4) Feed Forward to Future Missions.

  12. Lunar Dust Mitigation Technology Development

    NASA Technical Reports Server (NTRS)

    Hyatt, Mark J.; Deluane, Paul B.

    2008-01-01

    NASA s plans for implementing the Vision for Space Exploration include returning to the moon as a stepping stone for further exploration of Mars, and beyond. Dust on the lunar surface has a ubiquitous presence which must be explicitly addressed during upcoming human lunar exploration missions. While the operational challenges attributable to dust during the Apollo missions did not prove critical, the comparatively long duration of impending missions presents a different challenge. Near term plans to revisit the moon places a primary emphasis on characterization and mitigation of lunar dust. Comprised of regolith particles ranging in size from tens of nanometers to microns, lunar dust is a manifestation of the complex interaction of the lunar soil with multiple mechanical, electrical, and gravitational effects. The environmental and anthropogenic factors effecting the perturbation, transport, and deposition of lunar dust must be studied in order to mitigate it s potentially harmful effects on exploration systems. This paper presents the current perspective and implementation of dust knowledge management and integration, and mitigation technology development activities within NASA s Exploration Technology Development Program. This work is presented within the context of the Constellation Program s Integrated Lunar Dust Management Strategy. The Lunar Dust Mitigation Technology Development project has been implemented within the ETDP. Project scope and plans will be presented, along with a a perspective on lessons learned from Apollo and forensics engineering studies of Apollo hardware. This paper further outlines the scientific basis for lunar dust behavior, it s characteristics and potential effects, and surveys several potential strategies for its control and mitigation both for lunar surface operations and within the working volumes of a lunar outpost.

  13. Preliminary Convective-Radiative Heating Environments for a Neptune Aerocapture Mission

    NASA Technical Reports Server (NTRS)

    Hollis, Brian R.; Wright, Michael J.; Olejniczak, Joseph; Takashima, Naruhisa; Sutton, Kenneth; Prabhu, Dinesh

    2004-01-01

    Convective and radiative heating environments have been computed for a three-dimensional ellipsled configuration which would perform an aerocapture maneuver at Neptune. This work was performed as part of a one-year Neptune aerocapture spacecraft systems study that also included analyses of trajectories, atmospheric modeling, aerodynamics, structural design, and other disciplines. Complementary heating analyses were conducted by separate teams using independent sets of aerothermodynamic modeling tools (i.e. Navier-Stokes and radiation transport codes). Environments were generated for a large 5.50 m length ellipsled and a small 2.88 m length ellipsled. Radiative heating was found to contribute up to 80% of the total heating rate at the ellipsled nose depending on the trajectory point. Good agreement between convective heating predictions from the two Navier-Stokes solvers was obtained. However, the radiation analysis revealed several uncertainties in the computational models employed in both sets of codes, as well as large differences between the predicted radiative heating rates.

  14. Information Communication Technology Planning in Developing Countries

    ERIC Educational Resources Information Center

    Malapile, Sandy; Keengwe, Jared

    2014-01-01

    This article explores major issues related to Information Communication Technology (ICT) in education and technology planning. Using the diffusion of innovation theory, the authors examine technology planning opportunities and challenges in Developing countries (DCs), technology planning trends in schools, and existing technology planning models…

  15. Nonequilibrium radiation and chemistry models for aerocapture vehicle flowfields

    NASA Technical Reports Server (NTRS)

    Carlson, Leland A.

    1990-01-01

    The continued development and improvement of the viscous shock layer (VSL) nonequilibrium chemistry blunt body engineering code, the incorporation in a coupled manner of radiation models into the VSL code, and the initial development of appropriate precursor models are presented.

  16. Nonequilibrium radiation and chemistry models for aerocapture vehicle flowfields

    NASA Technical Reports Server (NTRS)

    Carlson, Leland A.

    1991-01-01

    The primary tasks performed are: (1) the development of a second order local thermodynamic nonequilibrium (LTNE) model for atoms; (2) the continued development of vibrational nonequilibrium models; and (3) the development of a new multicomponent diffusion model. In addition, studies comparing these new models with previous models and results were conducted and reported.

  17. Advanced Refrigerator/Freezer Technology Development. Technology Assessment

    NASA Technical Reports Server (NTRS)

    Gaseor, Thomas; Hunter, Rick; Hamill, Doris

    1996-01-01

    The NASA Lewis Research Center, through contract with Oceaneering Space Systems, is engaged in a project to develop advanced refrigerator/freezer (R/F) technologies for future Life and Biomedical Sciences space flight missions. The first phase of this project, a technology assessment, has been completed to identify the advanced R/F technologies needed and best suited to meet the requirements for the five R/F classifications specified by Life and Biomedical Science researchers. Additional objectives of the technology assessment were to rank those technologies based on benefit and risk, and to recommend technology development activities that can be accomplished within this project. This report presents the basis, the methodology, and results of the R/F technology assessment, along with technology development recommendations.

  18. Two Phase Technology Development Initiatives

    NASA Technical Reports Server (NTRS)

    Didion, Jeffrey R.

    1999-01-01

    Three promising thermal technology development initiatives, vapor compression thermal control system, electronics cooling, and electrohydrodynamics applications are outlined herein. These technologies will provide thermal engineers with additional tools to meet the thermal challenges presented by increased power densities and reduced architectural options that will be available in future spacecraft. Goddard Space Flight Center and the University of Maryland are fabricating and testing a 'proto- flight' vapor compression based thermal control system for the Ultra Long Duration Balloon (ULDB) Program. The vapor compression system will be capable of transporting approximately 400 W of heat while providing a temperature lift of 60C. The system is constructed of 'commercial off-the-shelf' hardware that is modified to meet the unique environmental requirements of the ULDB. A demonstration flight is planned for 1999 or early 2000. Goddard Space Flight Center has embarked upon a multi-discipline effort to address a number of design issues regarding spacecraft electronics. The program addressed the high priority design issues concerning the total mass of standard spacecraft electronics enclosures and the impact of design changes on thermal performance. This presentation reviews the pertinent results of the Lightweight Electronics Enclosure Program. Electronics cooling is a growing challenge to thermal engineers due to increasing power densities and spacecraft architecture. The space-flight qualification program and preliminary results of thermal performance tests of copper-water heat pipes are presented. Electrohydrodynamics (EHD) is an emerging technology that uses the secondary forces that result from the application of an electric field to a flowing fluid to enhance heat transfer and manage fluid flow. A brief review of current EHD capabilities regarding heat transfer enhancement of commercial heat exchangers and capillary pumped loops is presented. Goddard Space Flight

  19. Nonequilibrium radiation and chemistry models for aerocapture vehicle flowfields

    NASA Technical Reports Server (NTRS)

    Carlson, Leland A.

    1990-01-01

    The primary tasks during January 1990 to June 1990 have been the development and evaluation of various electron and electron-electronic energy equation models, the continued development of improved nonequilibrium radiation models for molecules and atoms, and the continued development and investigation of precursor models and their effects. In addition, work was initiated to develop a vibrational model for the viscous shock layer (VSL) nonequilibrium chemistry blunt body engineering code. Also, an effort was started associated with the effects of including carbon species, say from an ablator, in the flowfield.

  20. Advanced baffle materials technology development

    NASA Astrophysics Data System (ADS)

    Johnson, E. A.; Vonbenken, C. J.; Halverson, W. D.; Evans, R. D.; Wollam, J. S.

    1991-10-01

    Optical sensors for strategic defense will require optical baffles to achieve adequate off-axis stray light rejection and pointing accuracy. Baffle materials must maintain their optical performance after exposure to both operational and threat environments. In addition, baffle materials must not introduce contamination which would compromise the system signal-to-noise performance or impair system mission readiness. Critical examination of failure mechanisms in current baffle materials are quite fragile and contribute to system contamination problems. Spire has developed technology to texture the substrate directly, thereby, removing minute, fragile interfaces subject to mechanical failure. This program has demonstrated that ion beam texturing produces extremely dark surfaces which are immune to damage from ordinary handling. This technology allows control of surface texture feature size and hence the optical wavelength at which the surface absorbs. The USAMTL/Spire program has produced dramatic improvements in the reflectance of ion beam textured aluminum without compromising mechanical hardness. In simulated launch vibration tests, this material produced no detectable contamination on adjacent catcher plates.

  1. Developing technologies for synthetic fuels

    NASA Astrophysics Data System (ADS)

    Sprow, F. B.

    1981-05-01

    After consideration of a likely timetable for the development of a synthetic fuels industry and its necessary supporting technology, the large variety of such fuels and their potential roles is assessed along with their commercialization outlook. Among the fuel production methods considered are: (1) above-ground retorting of oil shale; (2) in-situ shale retorting; (3) open pit mining of tar sands; (4) in-situ steam stimulation of tar sands; (5) coal gasification; (6) methanol synthesis from carbon monoxide and hydrogen; and (7) direct coal liquefaction by the hydrogenation of coal. It is shown that while the U.S. has very limited resource bases for tar sands and heavy crudes, the abundance of shale in the western states and the abundance and greater geographical dispersion of coal will make these the two most important resources of a future synthetic fuels industry.

  2. Technology in Sustainable Development Context

    NASA Astrophysics Data System (ADS)

    Uno, Kimio

    The economic and demographic growth in Asia has put increased importance to this part of the world whose contribution to the global community is vital in meeting global challenges. International cooperation in engineering education assumes a pivotal role in providing access to the frontiers of scientific and technological knowledge to the growing youths in the region. The thrust for advancement has been provided by the logic coming from the academic world itself, whereas expectations are high that the engineering education responds to challenges that are coming from outside the universities, such as environmental management, disaster management, and provision of common knowledge platform across disciplinary lines. Some cases are introduced in curriculum development that incorporates fieldwork and laboratory work intended to enhance the ability to cooperate. The new mode is discussed with focus on production, screening, storing/delivery, and leaning phases of knowledge. The strength of shared information will be enhanced through international cooperation.

  3. Fiber composite materials technology development

    SciTech Connect

    Chiao, T.T.

    1980-10-23

    The FY1980 technical accomplishments from the Lawrence Livermore National laboratory (LLNL) for the Fiber Composite Materials Technology Development Task fo the MEST project are summarized. The task is divided into three areas: Engineering data base for flywheel design (Washington University will report this part separately), new materials evaluation, and time-dependent behavior of Kevlar composite strands. An epoxy matrix was formulated which can be used in composites for 120/sup 0/C service with good processing and mechanical properties. Preliminary results on the time-dependent properties of the Kevlar 49/epoxy strands indicate: Fatigue loading, as compared to sustained loading, drastically reduces the lifetime of a Kevlar composie; the more the number of on-off load cycles, the less the lifetime; and dynamic fatigue of the Kevlar composite can not be predicted by current damage theories such as Miner's Rule.

  4. LISA Technology Development at GSFC

    NASA Technical Reports Server (NTRS)

    Thorpe, James Ira; McWilliams, S.; Baker, J.

    2008-01-01

    The prime focus of LISA technology development efforts at NASA/GSFC has been in LISA interferometry, specifically in the area of laser frequency noise mitigation. Laser frequency noise is addressed through a combination of stabilization and common-mode rejection. Current plans call for two stages of stabilization, pre-stabilization to a local frequency reference and further stabilization using the constellation as a frequency reference. In order for these techniques to be used simultaneously, the pre-stabilization step must provide an adjustable frequency offset. Here, we report on a modification to the standard modulation/demodulation techniques used to stabilize to optical cavities that generates a frequency-tunable reference from a fixed-length cavity. This technique requires no modifications to the cavity itself and only minor modifications to the components. The measured noise performance and dynamic range of the laboratory prototype meets the LISA requirements.

  5. Nonequilibrium radiation and chemistry models for aerocapture vehicle flowfields

    NASA Technical Reports Server (NTRS)

    Carlson, Leland A.

    1993-01-01

    The period from Jan. 1993 thru Aug. 1993 is covered. The primary tasks during this period were the development of a single and multi-vibrational temperature preferential vibration-dissociation coupling model, the development of a normal shock nonequilibrium radiation-gasdynamic coupling model based upon the blunt body model, and the comparison of results obtained with these models with experimental data. In addition, an extensive series of computations were conducted using the blunt body model to develop a set of reference results covering a wide range of vehicle sizes, altitudes, and entry velocities.

  6. DOE lost circulation technology development

    SciTech Connect

    Glowka, D.A.; Staller, G.E.; Sattler, A.R.

    1996-09-01

    Lost circulation is a problem common in both the geothermal and the solution mining industries. In both cases, drilling is on a relatively large scale (geothermal holes can be as large as 26 inches). Lost circulation technology development for geothermal drilling has been in progress at Sandia National Laboratories for more than 15 years. The initial work centered on lost circulation materials, but testing and modeling indicated that if the aperture of a loss zone is very large (larger than the drill bit nozzles) it cannot be plugged by simply adding materials to the drilling fluid. Thus, the lost circulation work evolved to include: (1) Development of metering techniques that accurately measure and characterize drilling fluid inflow and outflow for rapid diagnosis of los circulation and/or fluid balance while drilling. (2) Construction of a laboratory facility for testing drillable straddle packers (to improve the plugging efficiency of cementing operations) and the actual testing of components of the straddle packer. (3) Construction of a laboratory facility for the testing of candidate porous fabrics as a part of a program to develop a porous packer that places polyurethane foam into a loss zone. (4) Implementing (with Halliburton and CalEnergy Company), a program to test cementitious lost circulation material as an alternative to Portland cement.

  7. Colorado Technology Transfer Plan for Economic Development.

    ERIC Educational Resources Information Center

    Colorado Advanced Tech. Inst., Denver.

    Recognizing the importance of technology transfer to economic growth, the U.S. Economic Development Administration (EDA) provided the Colorado Advanced Technology Institute (CATI) with a grant to coordinate the development of a plan for using technology transfer in Colorado's economic development. The plan, outlined in this report, describes the…

  8. Instructional Technology and Faculty Development.

    ERIC Educational Resources Information Center

    Holden, Carole A.

    This paper explores the challenges instructional technology presents to faculty and administration. For example: students will not accept lectures that fail to draw upon Internet resources; integrating technology sparks the faculty debate that the use of technology will "dehumanize teaching and learning"; community college professors…

  9. Nonequilibrium radiation and chemistry models for aerocapture vehicle flowfields

    NASA Technical Reports Server (NTRS)

    Carlson, Leland A.

    1994-01-01

    The primary accomplishments of the project were as follows: (1) From an overall standpoint, the primary accomplishment of this research was the development of a complete gasdynamic-radiatively coupled nonequilibrium viscous shock layer solution method for axisymmetric blunt bodies. This method can be used for rapid engineering modeling of nonequilibrium re-entry flowfields over a wide range of conditions. (2) Another significant accomplishment was the development of an air radiation model that included local thermodynamic nonequilibrium (LTNE) phenomena. (3) As part of this research, three electron-electronic energy models were developed. The first was a quasi-equilibrium electron (QEE) model which determined an effective free electron temperature and assumed that the electronic states were in equilibrium with the free electrons. The second was a quasi-equilibrium electron-electronic (QEEE) model which computed an effective electron-electronic temperature. The third model was a full electron-electronic (FEE) differential equation model which included convective, collisional, viscous, conductive, vibrational coupling, and chemical effects on electron-electronic energy. (4) Since vibration-dissociation coupling phenomena as well as vibrational thermal nonequilibrium phenomena are important in the nonequilibrium zone behind a shock front, a vibrational energy and vibration-dissociation coupling model was developed and included in the flowfield model. This model was a modified coupled vibrational dissociation vibrational (MCVDV) model and also included electron-vibrational coupling. (5) Another accomplishment of the project was the usage of the developed models to investigate radiative heating. (6) A multi-component diffusion model which properly models the multi-component nature of diffusion in complex gas mixtures such as air, was developed and incorporated into the blunt body model. (7) A model was developed to predict the magnitude and characteristics of the shock

  10. Arctic Energy Technology Development Laboratory

    SciTech Connect

    Sukumar Bandopadhyay; Charles Chamberlin; Robert Chaney; Gang Chen; Godwin Chukwu; James Clough; Steve Colt; Anthony Covescek; Robert Crosby; Abhijit Dandekar; Paul Decker; Brandon Galloway; Rajive Ganguli; Catherine Hanks; Rich Haut; Kristie Hilton; Larry Hinzman; Gwen Holdman; Kristie Holland; Robert Hunter; Ron Johnson; Thomas Johnson; Doug Kame; Mikhail Kaneveskly; Tristan Kenny; Santanu Khataniar; Abhijeet Kulkami; Peter Lehman; Mary Beth Leigh; Jenn-Tai Liang; Michael Lilly; Chuen-Sen Lin; Paul Martin; Pete McGrail; Dan Miller; Debasmita Misra; Nagendra Nagabhushana; David Ogbe; Amanda Osborne; Antoinette Owen; Sharish Patil; Rocky Reifenstuhl; Doug Reynolds; Eric Robertson; Todd Schaef; Jack Schmid; Yuri Shur; Arion Tussing; Jack Walker; Katey Walter; Shannon Watson; Daniel White; Gregory White; Mark White; Richard Wies; Tom Williams; Dennis Witmer; Craig Wollard; Tao Zhu

    2008-12-31

    The Arctic Energy Technology Development Laboratory was created by the University of Alaska Fairbanks in response to a congressionally mandated funding opportunity through the U.S. Department of Energy (DOE), specifically to encourage research partnerships between the university, the Alaskan energy industry, and the DOE. The enabling legislation permitted research in a broad variety of topics particularly of interest to Alaska, including providing more efficient and economical electrical power generation in rural villages, as well as research in coal, oil, and gas. The contract was managed as a cooperative research agreement, with active project monitoring and management from the DOE. In the eight years of this partnership, approximately 30 projects were funded and completed. These projects, which were selected using an industry panel of Alaskan energy industry engineers and managers, cover a wide range of topics, such as diesel engine efficiency, fuel cells, coal combustion, methane gas hydrates, heavy oil recovery, and water issues associated with ice road construction in the oil fields of the North Slope. Each project was managed as a separate DOE contract, and the final technical report for each completed project is included with this final report. The intent of this process was to address the energy research needs of Alaska and to develop research capability at the university. As such, the intent from the beginning of this process was to encourage development of partnerships and skills that would permit a transition to direct competitive funding opportunities managed from funding sources. This project has succeeded at both the individual project level and at the institutional development level, as many of the researchers at the university are currently submitting proposals to funding agencies, with some success.

  11. Aerocapture guidance and navigation for the Rosetta Comet Nucleus Sample Return Mission

    NASA Astrophysics Data System (ADS)

    Serrano-Martinez, J. B.; Hechler, M.

    The aerocapture/reentry phase of the Comet Nucleus Sample Return Mission Rosetta when returning from the Comet back to earth is discussed. The guidance and navigation process for a guided atmospheric entry to ground from an entry velocity of over 15 km/s has been simulated and the feasibility of such an entry at an entry angle of -10.5 deg, using an Apollo shape vehicle and guidance methods similar to those used for Apollo and the Shuttle Orbiter, has been demonstrated. Landing precision of less than 10 km at accelerations below 20 g can be reached. Critical areas of system design like the center of gravity location of the entry vehicle are addressed.

  12. Policy issues inherent in advanced technology development

    SciTech Connect

    Baumann, P.D.

    1994-12-31

    In the development of advanced technologies, there are several forces which are involved in the success of the development of those technologies. In the overall development of new technologies, a sufficient number of these forces must be present and working in order to have a successful opportunity at developing, introducing and integrating into the marketplace a new technology. This paper discusses some of these forces and how they enter into the equation for success in advanced technology research, development, demonstration, commercialization and deployment. This paper limits itself to programs which are generally governmental funded, which in essence represent most of the technology development efforts that provide defense, energy and environmental technological products. Along with the identification of these forces are some suggestions as to how changes may be brought about to better ensure success in a long term to attempt to minimize time and financial losses.

  13. Energy Storage (II): Developing Advanced Technologies

    ERIC Educational Resources Information Center

    Robinson, Arthur L

    1974-01-01

    Energy storage, considered by some scientists to be the best technological and economic advancement after advanced nuclear power, still rates only modest funding for research concerning the development of advanced technologies. (PEB)

  14. FY-95 technology catalog. Technology development for buried waste remediation

    SciTech Connect

    1995-10-01

    The US Department of Energy`s (DOE) Buried Waste Integrated Demonstration (BWID) program, which is now part of the Landfill Stabilization Focus Area (LSFA), supports applied research, development, demonstration, and evaluation of a multitude of advanced technologies dealing with underground radioactive and hazardous waste remediation. These innovative technologies are being developed as part of integrated comprehensive remediation systems for the effective and efficient remediation of buried waste sites throughout the DOE complex. These efforts are identified and coordinated in support of Environmental Restoration (EM-40) and Waste Management (EM-30) needs and objectives. Sponsored by the DOE Office of Technology Development (EM-50), BWID and LSFA work with universities and private industry to develop technologies that are being transferred to the private sector for use nationally and internationally. This report contains the details of the purpose, logic, and methodology used to develop and demonstrate DOE buried waste remediation technologies. It also provides a catalog of technologies and capabilities with development status for potential users. Past FY-92 through FY-94 technology testing, field trials, and demonstrations are summarized. Continuing and new FY-95 technology demonstrations also are described.

  15. Mobile Sensor Technologies Being Developed

    NASA Technical Reports Server (NTRS)

    Greer, Lawrence C.; Oberle, Lawrence G.

    2003-01-01

    The NASA Glenn Research Center is developing small mobile platforms for sensor placement, as well as methods for communicating between roving platforms and a central command location. The first part of this project is to use commercially available equipment to miniaturize an existing sensor platform. We developed a five-circuit-board suite, with an average board size of 1.5 by 3 cm. Shown in the preceding photograph, this suite provides all motor control, direction finding, and communications capabilities for a 27- by 21- by 40-mm prototype mobile platform. The second part of the project is to provide communications between mobile platforms, and also between multiple platforms and a central command location. This is accomplished with a low-power network labeled "SPAN," Sensor Platform Area Network, a local area network made up of proximity elements. In practice, these proximity elements are composed of fixed- and mobile-sensor-laden science packages that communicate to each other via radiofrequency links. Data in the network will be shared by a central command location that will pass information into and out of the network through its access to a backbone element. The result will be a protocol portable to general purpose microcontrollers satisfying a host of sensor networking tasks. This network will enter the gap somewhere between television remotes and Bluetooth but, unlike 802.15.4, will not specify a physical layer, thus allowing for many data rates over optical, acoustical, radiofrequency, hardwire, or other media. Since the protocol will exist as portable C-code, developers may be able to embed it in a host of microcontrollers from commercial to space grade and, of course, to design it into ASICs. Unlike in 802.15.4, the nodes will relate to each other as peers. A demonstration of this protocol using the two test bed platforms was recently held. Two NASA modified, commercially available, mobile platforms communicated and shared data with each other and a

  16. Technology and the Developing Institution

    ERIC Educational Resources Information Center

    Powers, Glenn F.

    1973-01-01

    Northeast Louisiana University, a new university, has used technology effectively, with equipment such as closed circuit TV systems, electronic pianos, video taping of student teachers, programmed research, and even electronic chimes in the clock tower. (PG)

  17. Development of Pollution Prevention Technologies

    SciTech Connect

    Polle, Juergen; Sanchez-Delgado, Roberto

    2013-12-30

    This project investigated technologies that may reduce environmental pollution. This was a basic research/educational project addressing two major areas: A. In the algae research project, newly isolated strains of microalgae were investigated for feedstock production to address the production of renewable fuels. An existing collection of microalgae was screened for lipid composition to determine strains with superior composition of biofuel molecules. As many microalgae store triacylglycerides in so-called oil bodies, selected candidate strains identified from the first screen that accumulate oil bodies were selected for further biochemical analysis, because almost nothing was known about the biochemistry of these oil bodies. Understanding sequestration of triacylglycerides in intracellular storage compartments is essential to developing better strains for achieving high oil productivities by microalgae. At the onset of the project there was almost no information available on how to obtain detailed profiles of lipids from strains of microalgae. Our research developed analytical methods to determine the lipid profiles of novel microalgal strains. The project was embedded into other ongoing microalgal projects in the Polle laboratory. The project benefited the public, because students were trained in cell cultivation and in the operation of state-of-the-art analytical equipment. In addition, students at Brooklyn College were introduced into the concept of a systems biology approach to study algal biofuels production. B. A series of new nanostructured catalysts were synthesized, and characterized by a variety of physical and chemical methods. Our catalyst design leads to active nanostructures comprising small metal particles in intimate contact with strongly basic sites provided by the supports, which include poly(4-vinylpyridine), magnesium oxide, functionalized multi-walled carbon nanotubes, and graphene oxide. The new materials display a good potential as catalysts

  18. CROSSCUTTING TECHNOLOGY DEVELOPMENT AT THE CENTER FOR ADVANCED SEPARATION TECHNOLOGIES

    SciTech Connect

    Christopher E. Hull

    2006-05-15

    This Technical Progress Report describes progress made on the twenty nine subprojects awarded in the second year of Cooperative Agreement DE-FC26-02NT41607: Crosscutting Technology Development at the Center for Advanced Separation Technologies. This work is summarized in the body of the main report: the individual sub-project Technical Progress Reports are attached as Appendices.

  19. CROSSCUTTING TECHNOLOGY DEVELOPMENT AT THE CENTER FOR ADVANCED SEPARATION TECHNOLOGIES

    SciTech Connect

    Christopher E. Hull

    2005-11-04

    This Technical Progress Report describes progress made on the twenty nine subprojects awarded in the second year of Cooperative Agreement DE-FC26-02NT41607: Crosscutting Technology Development at the Center for Advanced Separation Technologies. This work is summarized in the body of the main report: the individual sub-project Technical Progress Reports are attached as Appendices.

  20. Crosscutting Technology Development at the Center for Advanced Separation Technologies

    SciTech Connect

    Christopher E. Hull

    2006-09-30

    This Technical Progress Report describes progress made on the twenty nine subprojects awarded in the second year of Cooperative Agreement DE-FC26-02NT41607: Crosscutting Technology Development at the Center for Advanced Separation Technologies. This work is summarized in the body of the main report: the individual sub-project Technical Progress Reports are attached as Appendices.

  1. Technology Mapping: An Approach for Developing Technological Pedagogical Content Knowledge

    ERIC Educational Resources Information Center

    Angeli, Charoula; Valanides, Nicos

    2013-01-01

    Technology mapping[TM] is proposed as an approach for developing technological pedagogical content knowledge (TPCK). The study discusses in detail instructional design guidelines in relation to the enactment of TM, and reports on empirical findings from a study with 72 pre-service primary teachers within the context of teaching them how to teach…

  2. History of nuclear technology development in Japan

    SciTech Connect

    Yamashita, Kiyonobu

    2015-04-29

    Nuclear technology development in Japan has been carried out based on the Atomic Energy Basic Act brought into effect in 1955. The nuclear technology development is limited to peaceful purposes and made in a principle to assure their safety. Now, the technologies for research reactors radiation application and nuclear power plants are delivered to developing countries. First of all, safety measures of nuclear power plants (NPPs) will be enhanced based on lesson learned from TEPCO Fukushima Daiichi NPS accident.

  3. Space Station engineering and technology development

    NASA Technical Reports Server (NTRS)

    1985-01-01

    Historical background, costs, organizational assignments, technology development, user requirements, mission evolution, systems analyses and design, systems engineering and integration, contracting, and policies of the space station are discussed.

  4. Clean Technology Evaluation & Workforce Development Program

    SciTech Connect

    Patricia Glaza

    2012-12-01

    The overall objective of the Clean Technology Evaluation portion of the award was to design a process to speed up the identification of new clean energy technologies and match organizations to testing and early adoption partners. The project was successful in identifying new technologies targeted to utilities and utility technology integrators, in developing a process to review and rank the new technologies, and in facilitating new partnerships for technology testing and adoption. The purpose of the Workforce Development portion of the award was to create an education outreach program for middle & high-school students focused on clean technology science and engineering. While originally targeting San Diego, California and Cambridge, Massachusetts, the scope of the program was expanded to include a major clean technology speaking series and expo as part of the USA Science & Engineering Festival on the National Mall in Washington, D.C.

  5. Lunar Surface Systems Supportability Technology Development Roadmap

    NASA Technical Reports Server (NTRS)

    Oeftering, Richard C.; Struk, Peter M.; Green, Jennifer L.; Chau, Savio N.; Curell, Philip C.; Dempsey, Cathy A.; Patterson, Linda P.; Robbins, William; Steele, Michael A.; DAnnunzio, Anthony; Meseroll, Robert; Quiter, John; Shannon, Russell; Easton, John W.; Madaras, Eric I.; BrownTaminger, Karen M.; Tabera, John T.; Tellado, Joseph; Williams, Marth K.; Zeitlin, Nancy P.

    2011-01-01

    The Lunar Surface Systems Supportability Technology Development Roadmap is a guide for developing the technologies needed to enable the supportable, sustainable, and affordable exploration of the Moon and other destinations beyond Earth. Supportability is defined in terms of space maintenance, repair, and related logistics. This report considers the supportability lessons learned from NASA and the Department of Defense. Lunar Outpost supportability needs are summarized, and a supportability technology strategy is established to make the transition from high logistics dependence to logistics independence. This strategy will enable flight crews to act effectively to respond to problems and exploit opportunities in an environment of extreme resource scarcity and isolation. The supportability roadmap defines the general technology selection criteria. Technologies are organized into three categories: diagnostics, test, and verification; maintenance and repair; and scavenge and recycle. Furthermore, "embedded technologies" and "process technologies" are used to designate distinct technology types with different development cycles. The roadmap examines the current technology readiness level and lays out a four-phase incremental development schedule with selection decision gates. The supportability technology roadmap is intended to develop technologies with the widest possible capability and utility while minimizing the impact on crew time and training and remaining within the time and cost constraints of the program.

  6. JWST Primary Mirror Technology Development

    NASA Technical Reports Server (NTRS)

    Stahl, H. Philip

    2010-01-01

    Mirror Technology was identified as a (if not the) critical capability necessary to achieve the Level 1 science goals. A never before demonstrated space telescope capability was required: 6 to 8 meter class pri mary mirror, diffraction limited at 2 micrometers and operates at temperatures below 50K. Launch vehicle constraints placed significant architectural constraints: deployed/segmented primary mirror (4.5 meter fairing diameter) 20 kg/m2 areal density (PM 1000 kg mass) Such mirror technology had never been demonstrated - and did not exist

  7. Oil heat technology research and development

    SciTech Connect

    Kweller, E.R.; McDonald, R.J.

    1995-04-01

    The purpose of this United States Department of Energy (DOE)/Brookhaven National Laboratory (BNL) program is to develop a technology base for advancing the state-of-the-art related to oilfired combustion equipment. The major thrust is through technology based research that will seek new knowledge leading to improved designs and equipment optimization. The Combustion Equipment space Conditioning Technology program currently deals exclusively with residential and small commercial building oil heat technology.

  8. Innovative Technology Development Program. Final summary report

    SciTech Connect

    Beller, J.

    1995-08-01

    Through the Office of Technology Development (OTD), the U.S. Department of Energy (DOE) has initiated a national applied research, development, demonstration, testing, and evaluation program, whose goal has been to resolve the major technical issues and rapidly advance technologies for environmental restoration and waste management. The Innovative Technology Development (ITD) Program was established as a part of the DOE, Research, Development, Demonstration, Testing, and Evaluation (RDDT&E) Program. The plan is part of the DOE`s program to restore sites impacted by weapons production and to upgrade future waste management operations. On July 10, 1990, DOE issued a Program Research and Development Announcement (PRDA) through the Idaho Operations Office to solicit private sector help in developing innovative technologies to support DOE`s clean-up goals. This report presents summaries of each of the seven projects, which developed and tested the technologies proposed by the seven private contractors selected through the PRDA process.

  9. Technology transfer to a developing nation, Korea

    NASA Technical Reports Server (NTRS)

    Stone, C. A.; Uccetta, S. J.

    1973-01-01

    An experimental project is reported which was undertaken. to determine if selected types of technology developed for the aerospace program during the past decade are relevant to specific industrial problems of a developing nation and to test whether a structured program could facilitate the transfer of relevant technologies. The Korea Institute of Science and Technology and the IIT Research Institute were selected as the active transfer agents to participate in the program. The pilot project was based upon the approach to the transfer of domestic technology developed by the NASA Technology Utilization Division and utilized the extensive data and technical resources available through the Space Agency and its contractors. This pilot project has helped to clarify some aspects of the international technology transfer process and to upgrade Korean technological capabilities.

  10. Technology Development Roadmaps - a Systematic Approach to Maturing Needed Technologies

    SciTech Connect

    John W. Colllins; Layne Pincock

    2010-07-01

    Abstract. Planning and decision making represent important challenges for all projects. This paper presents the steps needed to assess technical readiness and determine the path forward to mature the technologies required for the Next Generation Nuclear Plant. A Technology Readiness Assessment is used to evaluate the required systems, subsystems, and components (SSC) comprising the desired plant architecture and assess the SSCs against established Technology Readiness Levels (TRLs). A validated TRL baseline is then established for the proposed physical design. Technology Development Roadmaps are generated to define the path forward and focus project research and development and engineering tasks on advancing the technologies to increasing levels of maturity. Tasks include modeling, testing, bench-scale demonstrations, pilot-scale demonstrations, and fully integrated prototype demonstrations. The roadmaps identify precise project objectives and requirements; create a consensus vision of project needs; provide a structured, defensible, decision-based project plan; and, minimize project costs and schedules.

  11. Welding technology. [technology transfer of NASA developments to commercial organizations

    NASA Technical Reports Server (NTRS)

    1974-01-01

    Welding processes which have been developed during NASA space program activities are discussed. The subjects considered are: (1) welding with an electron gun, (2) technology of welding special alloys, and (3) welding shop techniques and equipment. The material presented is part of the combined efforts of NASA and the Small Business Administration to provide technology transfer of space-related developments to the benefit of commercial organizations.

  12. Pipe Leak Detection Technology Development

    EPA Science Inventory

    The U. S. Environmental Protection Agency (EPA) has determined that one of the nation’s biggest infrastructural needs is the replacement or rehabilitation of the water distribution and transmission systems. The institution of more effective pipe leak detection technology will im...

  13. Robotics Technology Development Program Cross Cutting and Advanced Technology

    SciTech Connect

    Harrigan, R.W.; Horschel, D.S.

    1994-04-01

    Need-based cross cutting technology is being developed which is broadly applicable to the clean up of hazardous and radioactive waste within the US Department of Energy`s complex. Highly modular, reusable technologies which plug into integrated system architectures to meet specific robotic needs result from this research. In addition, advanced technologies which significantly extend current capabilities such as automated planning and sensor-based control in unstructured environments for remote system operation are also being developed and rapidly integrated into operating systems.

  14. KSC Education Technology Research and Development Plan

    NASA Technical Reports Server (NTRS)

    Odell, Michael R. L.

    2003-01-01

    Educational technology is facilitating new approaches to teaching and learning science, technology, engineering, and mathematics (STEM) education. Cognitive research is beginning to inform educators about how students learn providing a basis for design of more effective learning environments incorporating technology. At the same time, access to computers, the Internet and other technology tools are becoming common features in K-20 classrooms. Encouraged by these developments, STEM educators are transforming traditional STEM education into active learning environments that hold the promise of enhancing learning. This document illustrates the use of technology in STEM education today, identifies possible areas of development, links this development to the NASA Strategic Plan, and makes recommendations for the Kennedy Space Center (KSC) Education Office for consideration in the research, development, and design of new educational technologies and applications.

  15. Microhole Drilling Tractor Technology Development

    SciTech Connect

    Western Well Tool

    2007-07-09

    In an effort to increase the U.S. energy reserves and lower costs for finding and retrieving oil, the USDOE created a solicitation to encourage industry to focus on means to operate in small diameter well-Microhole. Partially in response to this solicitation and because Western Well Tool's (WWT) corporate objective to develop small diameter coiled tubing drilling tractor, WWT responded to and was awarded a contract to design, prototype, shop test, and field demonstrate a Microhole Drilling Tractor (MDT). The benefit to the oil industry and the US consumer from the project is that with the MDT's ability to facilitate Coiled Tubing drilled wells to be 1000-3000 feet longer horizontally, US brown fields can be more efficiently exploited resulting in fewer wells, less environmental impact, greater and faster oil recovery, and lower drilling costs. Shortly after award of the contract, WWT was approached by a major oil company that strongly indicated that the specified size of a tractor of 3.0 inches diameter was inappropriate and that immediate applications for a 3.38-inch diameter tractor would substantially increase the usefulness of the tool to the oil industry. Based on this along with an understanding with the oil company to use the tractor in multiple field applications, WWT applied for and was granted a no-cost change-of-scope contract amendment to design, manufacture, assemble, shop test and field demonstrate a prototype a 3.38 inch diameter MDT. Utilizing existing WWT tractor technology and conforming to an industry developed specification for the tool, the Microhole Drilling Tractor was designed. Specific features of the MDT that increase it usefulness are: (1) Operation on differential pressure of the drilling fluid, (2) On-Off Capability, (3) Patented unique gripping elements (4) High strength and flexibility, (5) Compatibility to existing Coiled Tubing drilling equipment and operations. The ability to power the MDT with drilling fluid results in a highly

  16. Aligning Technology Education Teaching with Brain Development

    ERIC Educational Resources Information Center

    Katsioloudis, Petros

    2015-01-01

    This exploratory study was designed to determine if there is a level of alignment between technology education curriculum and theories of intellectual development. The researcher compared Epstein's Brain Growth Theory and Piaget's Status of Intellectual Development with technology education curriculum from Australia, England, and the United…

  17. Advances in Technology, Education and Development

    ERIC Educational Resources Information Center

    Kouwenhoven, Wim, Ed.

    2009-01-01

    From 3rd to 5th March 2008 the International Association of Technology, Education and Development organised its International Technology, Education and Development Conference in Valencia, Spain. Over a hundred papers were presented by participants from a great variety of countries. Summarising, this book provides a kaleidoscopic view of work that…

  18. The Human Response to Technological Development.

    ERIC Educational Resources Information Center

    Ramey, Luellen

    Technological development and our human potential are two of the greatest challenges facing humankind today. The appropriate response to technological development seems to be to shape it for positive and productive human uses. Just as America once shifted from an agricultural economy to an industrial economy, we are now shifting from an industrial…

  19. SRS environmental technology development field test platform

    SciTech Connect

    Riha, B.D.; Rossabi, J.; Eddy-Dilek, C.A.

    1995-09-01

    A critical and difficult step in the development and implementation of new technologies for environmental monitoring and characterization is successfully transferring these technologies to industry and government users for routine assessment and compliance activities. The Environmental Sciences Section of the DOE Savannah River Technology Center provides a forum for developers, potential users, and regulatory organizations to evaluate new technologies in comparison with baseline technologies in a well characterized field test bed. The principal objective of this project is to conduct comprehensive, objective field tests of monitoring and characterization technologies that are not currently used in EPA standard methods and evaluate their performance during actual operating conditions against baseline methods. This paper provides an overview of the field test site and a description of some of the technologies demonstrated at the site including their field applications.

  20. Advanced Reactor Technology -- Regulatory Technology Development Plan (RTDP)

    SciTech Connect

    Moe, Wayne Leland

    2015-05-01

    This DOE-NE Advanced Small Modular Reactor (AdvSMR) regulatory technology development plan (RTDP) will link critical DOE nuclear reactor technology development programs to important regulatory and policy-related issues likely to impact a “critical path” for establishing a viable commercial AdvSMR presence in the domestic energy market. Accordingly, the regulatory considerations that are set forth in the AdvSMR RTDP will not be limited to any one particular type or subset of advanced reactor technology(s) but rather broadly consider potential regulatory approaches and the licensing implications that accompany all DOE-sponsored research and technology development activity that deal with commercial non-light water reactors. However, it is also important to remember that certain “minimum” levels of design and safety approach knowledge concerning these technology(s) must be defined and available to an extent that supports appropriate pre-licensing regulatory analysis within the RTDP. Final resolution to advanced reactor licensing issues is most often predicated on the detailed design information and specific safety approach as documented in a facility license application and submitted for licensing review. Because the AdvSMR RTDP is focused on identifying and assessing the potential regulatory implications of DOE-sponsored reactor technology research very early in the pre-license application development phase, the information necessary to support a comprehensive regulatory analysis of a new reactor technology, and the resolution of resulting issues, will generally not be available. As such, the regulatory considerations documented in the RTDP should be considered an initial “first step” in the licensing process which will continue until a license is issued to build and operate the said nuclear facility. Because a facility license application relies heavily on the data and information generated by technology development studies, the anticipated regulatory

  1. Technology development and applications at Fernald

    SciTech Connect

    Pettit, P.J.; Skriba, M.C.; Warner, R.D.

    1995-02-01

    At the Fernald Environmental Management Project (FEMP) northwest of Cincinnati, Ohio, the U.S. Department of Energy and contractor Fernald Environmental Restoration Management Corporation (FERMCO) are aggressively pursuing both the development and the application of improved, innovative technology to the environmental restoration task. Application of emerging technologies is particularly challenging in a regulatory environment that places pressure on operational managers to develop and meet tight schedules. The regulatory and operational needs make close communication essential between technology developers and technology users (CERCLA/RCRA Unit managers). At Fernald this cooperation and communication has led, not only to the development and demonstration of new technologies with applications at other sites, but also to application of new technologies directly to the Fernald clean up. New technologies have been applied to improve environmental safety and health, improve the effectiveness of restoration efforts, and to cut restoration costs. The paper will describe successful efforts to develop and apply new technologies at the FEMP and will emphasize those technologies that have been applied and are planned for use in the clean up of this former uranium production facility.

  2. Titan probe technology assessment and technology development plan study

    NASA Technical Reports Server (NTRS)

    Castro, A. J.

    1980-01-01

    The need for technology advances to accomplish the Titan probe mission was determined by defining mission conditions and requirements and evaluating the technology impact on the baseline probe configuration. Mission characteristics found to be technology drivers include (1) ten years dormant life in space vacuum; (2) unknown surface conditions, various sample materials, and a surface temperature; and (3) mission constraints of the Saturn Orbiter Dual Probe mission regarding weight allocation. The following areas were identified for further development: surface sample acquisition system; battery powered system; nonmetallic materials; magnetic bubble memory devices, and the landing system. Preentry science, reliability, and weight reduction and redundancy must also be considered.

  3. Developments on Bearingless Drive Technology

    NASA Astrophysics Data System (ADS)

    Amrhein, Wolfgang; Silber, Siegfried; Nenninger, Klaus; Trauner, Gernot; Reisinger, Martin; Schoeb, Reto

    Meanwhile the bearingless motor technology offers a lot of mechanical and electrical design variants for various kinds of applications. A comparison of switched reluctance motor, asynchronous motor and permanent magnet motor technology shows advantages and disadvantages with regard to different technical requirements. Especially for small motor applications with large air gaps the permanent magnet motor is of great importance. This is confirmed by a comparison of electromagnetic and permanent-magnetic pole designs. Based on bearingless permanent magnet motors with integrated winding systems for levitation as well as torque generation reliability and fault-tolerant design studies are carried out. It is shown that with an appropriate motor design a failure of an arbitrary phase can be compensated by the motor itself. In such a case there is no need for failure detection in order to switch over to special auxiliary control algorithms. A further advantage of the integrated winding system is the high grade of copper utilization independent of the ratio of radial force and torque loads.

  4. Space Technology Mission Directorate: Game Changing Development

    NASA Technical Reports Server (NTRS)

    Gaddis, Stephen W.

    2015-01-01

    NASA and the aerospace community have deep roots in manufacturing technology and innovation. Through it's Game Changing Development Program and the Advanced Manufacturing Technology Project NASA develops and matures innovative, low-cost manufacturing processes and products. Launch vehicle propulsion systems are a particular area of interest since they typically comprise a large percentage of the total vehicle cost and development schedule. NASA is currently working to develop and utilize emerging technologies such as additive manufacturing (i.e. 3D printing) and computational materials and processing tools that could dramatically improve affordability, capability, and reduce schedule for rocket propulsion hardware.

  5. Development of Inflatable Entry Systems Technologies

    NASA Technical Reports Server (NTRS)

    Player, Charles J.; Cheatwood, F. McNeil; Corliss, James

    2005-01-01

    Achieving the objectives of NASA s Vision for Space Exploration will require the development of new technologies, which will in turn require higher fidelity modeling and analysis techniques, and innovative testing capabilities. Development of entry systems technologies can be especially difficult due to the lack of facilities and resources available to test these new technologies in mission relevant environments. This paper discusses the technology development process to bring inflatable aeroshell technology from Technology Readiness Level 2 (TRL-2) to TRL-7. This paper focuses mainly on two projects: Inflatable Reentry Vehicle Experiment (IRVE), and Inflatable Aeroshell and Thermal Protection System Development (IATD). The objectives of IRVE are to conduct an inflatable aeroshell flight test that demonstrates exoatmospheric deployment and inflation, reentry survivability and stability, and predictable drag performance. IATD will continue the development of the technology by conducting exploration specific trade studies and feeding forward those results into three more flight tests. Through an examination of these projects, and other potential projects, this paper discusses some of the risks, issues, and unexpected benefits associated with the development of inflatable entry systems technology.

  6. Development of High Temperature Gas Sensor Technology

    NASA Technical Reports Server (NTRS)

    Hunter, Gary W.; Chen, Liang-Yu; Neudeck, Philip G.; Knight, Dak; Liu, Chung-Chiun; Wu, Quing-Hai; Zhou, Huan-Jun

    1997-01-01

    The measurement of engine emissions is important for their monitoring and control. However, the ability to measure these emissions in-situ is limited. We are developing a family of high temperature gas sensors which are intended to operate in harsh environments such as those in an engine. The development of these sensors is based on progress in two types of technology: (1) The development of SiC-based semiconductor technology; and (2) Improvements in micromachining and microfabrication technology. These technologies are being used to develop point-contact sensors to measure gases which are important in emission control especially hydrogen, hydrocarbons, nitrogen oxides, and oxygen. The purpose of this paper is to discuss the development of this point-contact sensor technology. The detection of each type of gas involves its own challenges in the fields of materials science and fabrication technology. Of particular importance is sensor sensitivity, selectivity, and stability in long-term, high temperature operation. An overview is presented of each sensor type with an evaluation of its stage of development. It is concluded that this technology has significant potential for use in engine applications but further development is necessary.

  7. Advanced technology satellite demodulator development

    NASA Technical Reports Server (NTRS)

    Ames, Stephen A.

    1989-01-01

    Ford Aerospace has developed a proof-of-concept satellite 8 phase shift keying (PSK) modulation and coding system operating in the Time Division Multiple Access (TDMA) mode at a data range of 200 Mbps using rate 5/6 forward error correction coding. The 80 Msps 8 PSK modem was developed in a mostly digital form and is amenable to an ASIC realization in the next phase of development. The codec was developed as a paper design only. The power efficiency goal was to be within 2 dB of theoretical at a bit error rate (BER) of 5x10(exp 7) while the measured implementation loss was 4.5 dB. The bandwidth efficiency goal was 2 bits/sec/Hz while the realized bandwidth efficiency was 1.8 bits/sec/Hz. The burst format used a preamble of only 40 8 PSK symbol times including 32 symbols of all zeros and an eight symbol unique word. The modem and associated special test equipment (STE) were fabricated mostly on a specially designed stitch-weld board although a few of the highest rate circuits were built on printed circuit cards. All the digital circuits were ECL to support the clock rates of from 80 MHz to 360 MHz. The transmitter and receiver matched filters were square-root Nyquist bandpass filters realized at the 3.37 GHz i.f. The modem operated as a coherent system although no analog phase locked (PLL) loop was employed. Within the budgetary constraints of the program, the approach to the demodulator has been proven and is eligible to proceed to the next phase of development of a satellite demodulator engineering model. This would entail the development of an ASIC version of the digital portion of the demodulator, and MMIC version of the quadrature detector, and SAW Nyquist filters to realize the bandwidth efficiency.

  8. Science, Technology and Black Community Development.

    ERIC Educational Resources Information Center

    Johnson, Robert C.

    1984-01-01

    Argues that unless Blacks become aware of and examine scientific breakthroughs and technological developments, they risk being subjugated to the vicissitudes of scientific and technological forces that are as oppressive, demeaning, and domineering as the socioeconomic and political forces of racism and exploitation. (Author/CMG)

  9. UH Information Technology Services: Faculty Development Program

    ERIC Educational Resources Information Center

    Okimoto, Hae

    2002-01-01

    Universities are increasingly looking toward technology to overcome geographical barriers to access, and this has placed new demands on faculty to explore the potential of technology in their classrooms. As a result, faculty development in the use of appropriate applications for teaching and learning has become a critical issue. In the 2000…

  10. Genetic Technology and Agricultural Development

    ERIC Educational Resources Information Center

    Staub, William J.; Blase, Melvin G.

    1971-01-01

    Examines the nature, application, limits and potential of applied genetics in plant breeding as a factor in South Asian agricultural development. Concludes other factors were also present in recent agricultural growth, and indicates some economic implications of continued growth, including problems of employment of displaced rural workers. (AL)

  11. Open Technology Development: Roadmap Plan

    DTIC Science & Technology

    2006-04-01

    Benevolent Dictator(s). In the case of the development of Linux, Linus Torvalds makes the final decision with respect to direction of the code...roadmap study: • Paul Brinkley, OSD, Business Transformation Office • Dale Christensen, SECNAV, DON CIO Office • Robert Gold, Associate Director for

  12. Geo energy research and development: technology transfer

    SciTech Connect

    Traeger, R.K.

    1982-03-01

    Sandia Geo Energy Programs related to geothermal, coal, oil and gas, and synfuel resources have provided a useful mechanism for transferring laboratory technologies to private industry. Significant transfer of hardware, computer programs, diagnostics and instrumentation, advanced materials, and in situ process understanding has occurred through US/DOE supported programs in the past five years. The text briefly reviews the technology transfer procedures and summarizes 32 items that have been transferred and another 20 technologies that are now being considered for possible transfer to industry. A major factor in successful transfer has been personal interactions between Sandia engineers and the technical staff from private industry during all aspects of the technology development.

  13. Nuclear Technology for the Sustainable Development Goals

    NASA Astrophysics Data System (ADS)

    Darby, Iain

    2017-01-01

    Science, technology and innovation will play a crucial role in helping countries achieve the ambitious Sustainable Development Goals (SDGs). Since the discovery of nuclear fission in the 1930s, the peaceful applications of nuclear technology have helped many countries improve crops, fight pests, advance health, protect the environment and guarantee a stable supply of energy. Highlighting the goals related to health, hunger, energy and the environment, in this presentation I will discuss how nuclear technology contributes to the SDGs and how nuclear technology can further contribute to the well-being of people, help protect the planet and boost prosperity.

  14. Space power development impact on technology requirements

    NASA Technical Reports Server (NTRS)

    Cassidy, J. F.; Fitzgerald, T. J.; Gilje, R. I.; Gordon, J. D.

    1986-01-01

    The paper is concerned with the selection of a specific spacecraft power technology and the identification of technology development to meet system requirements. Requirements which influence the selection of a given technology include the power level required, whether the load is constant or transient in nature, and in the case of transient loads, the time required to recover the power, and overall system safety. Various power technologies, such as solar voltaic power, solar dynamic power, nuclear power systems, and electrochemical energy storage, are briefly described.

  15. Oxygen Generation Assembly Technology Development

    NASA Technical Reports Server (NTRS)

    Bagdigian, Robert; Cloud, Dale

    1999-01-01

    Hamilton Standard Space Systems International (HSSI) is under contract to NASA Marshall Space Flight Center (MSFC) to develop an Oxygen Generation Assembly (OGA) for the International Space Station (ISS). The International Space Station Oxygen Generation Assembly (OGA) electrolyzes potable water from the Water Recovery System (WRS) to provide gaseous oxygen to the Space Station module atmosphere. The OGA produces oxygen for metabolic consumption by crew and biological specimens. The OGA also replenishes oxygen lost by experiment ingestion, airlock depressurization, CO2 venting, and leakage. As a byproduct, gaseous hydrogen is generated. The hydrogen will be supplied at a specified pressure range above ambient to support future utilization. Initially, the hydrogen will be vented overboard to space vacuum. This paper describes the OGA integration into the ISS Node 3. It details the development history supporting the design and describes the OGA System characteristics and its physical layout.

  16. Developments in Science and Technology.

    DTIC Science & Technology

    1980-01-01

    3 Aail and/or st special A; Iwo FOREWORD The Applied Physics Laboratory (APL), a division of The Johns Hopkins University, is located in Howard County ...of Jupiter. In addition, volcanic products from Io were detected. In support of the Space Shuttle mission, APL has developed a computer model for the...provide valuable dicating that ionized volcanic products (oxygen and experimental constraints for the modeling of truly sulfur) from the satellite lo

  17. Developments in Science and Technology

    DTIC Science & Technology

    1979-01-01

    safety, and combustion ef- Since the sixteen priority research topics may ficiency). be more than a realistic research budget can support, the final...are, in l~guration used to develop and test ASP microcom- order of priority , command, telemetry, analog-to- puter hardware and firmware included an...options. The options inNde selection of the specific synthesizer to be used and specification of announce- ment priorities ; a high priority announcement

  18. Water Processor Assembly Technology Development

    NASA Technical Reports Server (NTRS)

    Bagdigian, Robert; Parker, Dave; OConnor, Ed

    1999-01-01

    The International Space Station (ISS) Water Processor Assembly (WPA) produces potable quality water from humidity condensate, carbon dioxide reduction water, water obtained from fuel cells, reclaimed urine distillate, shower, handwash and oral hygiene waste waters. This paper describes the WPA integration into the ISS Node 3. It details the substantial development history supporting the design and describes the WPA System characteristics and its physical layout.

  19. EPA SUPPORT OF TECHNOLOGY DEVELOPMENT FOR REHABILITATION

    EPA Science Inventory

    Several EPA projects are currently underway to encourage technology development and dissemination in key aspects of the condition assessment and rehabilitation and replacement process for water and wastewater systems. The progress on one of these projects, Task Order 58 -- being ...

  20. Aerospace Flywheel Technology Development for IPACS Applications

    NASA Technical Reports Server (NTRS)

    McLallin, Kerry L.; Jansen, Ralph H.; Fausz, Jerry; Bauer, Robert D.

    2001-01-01

    The National Aeronautics and Space Administration (NASA) and the Air Force Research Laboratory (AFRL) are cooperating under a space act agreement to sponsor the research and development of aerospace flywheel technologies to address mutual future mission needs. Flywheel technology offers significantly enhanced capability or is an enabling technology. Generally these missions are for energy storage and/or integrated power and attitude control systems (IPACS) for mid-to-large satellites in low earth orbit. These missions require significant energy storage as well as a CMG or reaction wheel function for attitude control. A summary description of the NASA and AFRL flywheel technology development programs is provided, followed by specific descriptions of the development plans for integrated flywheel system tests for IPACS applications utilizing both fixed and actuated flywheel units. These flywheel system development tests will be conducted at facilities at AFRL and NASA Glenn Research Center and include participation by industry participants Honeywell and Lockheed Martin.

  1. CROSSCUTTING TECHNOLOGY DEVELOPMENT AT THE CENTER FOR ADVANCED SEPARATION TECHNOLOGIES

    SciTech Connect

    Hugh W. Rimmer

    2004-05-12

    This Technical Progress Report describes progress made on the seventeen subprojects awarded in the first year of Cooperative Agreement DE-FC26-02NT41607: Crosscutting Technology Development at the Center for Advanced Separation Technologies. This work is summarized in the body of the main report: the individual sub-project Technical Progress Reports are attached as Appendices. Due to the time taken up by the solicitation/selection process, these cover the initial 6-month period of project activity only. The U.S. is the largest producer of mining products in the world. In 1999, U.S. mining operations produced $66.7 billion worth of raw materials that contributed a total of $533 billion to the nation's wealth. Despite these contributions, the mining industry has not been well supported with research and development funds as compared to mining industries in other countries. To overcome this problem, the Center for Advanced Separation Technologies (CAST) was established to develop technologies that can be used by the U.S. mining industry to create new products, reduce production costs, and meet environmental regulations. Originally set up by Virginia Tech and West Virginia University, this endeavor has been expanded into a seven-university consortium--Virginia Tech, West Virginia University, University of Kentucky, University of Utah, Montana Tech, New Mexico Tech and University of Nevada, Reno--that is supported through U.S. DOE Cooperative Agreement No. DE-FC26-02NT41607: Crosscutting Technology Development at the Center for Advanced Separation Technologies. Much of the research to be conducted with Cooperative Agreement funds will be longer-term, high-risk, basic research and will be carried out in five broad areas: (1) Solid-solid separation (2) Solid-liquid separation (3) Chemical/Biological Extraction (4) Modeling and Control, and (5) Environmental Control.

  2. X-43 Hypersonic Vehicle Technology Development

    NASA Technical Reports Server (NTRS)

    Voland, Randall T.; Huebner, Lawrence D.; McClinton, Charles R.

    2005-01-01

    NASA recently completed two major programs in Hypersonics: Hyper-X, with the record-breaking flights of the X-43A, and the Next Generation Launch Technology (NGLT) Program. The X-43A flights, the culmination of the Hyper-X Program, were the first-ever examples of a scramjet engine propelling a hypersonic vehicle and provided unique, convincing, detailed flight data required to validate the design tools needed for design and development of future operational hypersonic airbreathing vehicles. Concurrent with Hyper-X, NASA's NGLT Program focused on technologies needed for future revolutionary launch vehicles. The NGLT was "competed" by NASA in response to the President s redirection of the agency to space exploration, after making significant progress towards maturing technologies required to enable airbreathing hypersonic launch vehicles. NGLT quantified the benefits, identified technology needs, developed airframe and propulsion technology, chartered a broad University base, and developed detailed plans to mature and validate hypersonic airbreathing technology for space access. NASA is currently in the process of defining plans for a new Hypersonic Technology Program. Details of that plan are not currently available. This paper highlights results from the successful Mach 7 and 10 flights of the X-43A, and the current state of hypersonic technology.

  3. Technology Challenges in Small UAV Development

    NASA Technical Reports Server (NTRS)

    Logan, Michael J.; Vranas, Thomas L.; Motter, Mark; Shams, Qamar; Pollock, Dion S.

    2005-01-01

    Development of highly capable small UAVs present unique challenges for technology protagonists. Size constraints, the desire for ultra low cost and/or disposable platforms, lack of capable design and analysis tools, and unique mission requirements all add to the level of difficulty in creating state-of-the-art small UAVs. This paper presents the results of several small UAV developments, the difficulties encountered, and proposes a list of technology shortfalls that need to be addressed.

  4. Advances in space technology: the NSBRI Technology Development Team.

    PubMed

    Maurer, R H; Charles, H K; Pisacane, V L

    2002-01-01

    As evidenced from Mir and other long-duration space missions, the space environment can cause significant alterations in the human physiology that could prove dangerous for astronauts. The NASA programme to develop countermeasures for these deleterious human health effects is being carried out by the National Space Biomedical Research Institute (NSBRI). The NSBRI has 12 research teams, ten of which are primarily physiology based, one addresses on-board medical care, and the twelfth focuses on technology development in support of the other research teams. This Technology Development (TD) Team initially supported four instrumentation developments: (1) an advanced, multiple projection, dual energy X ray absorptiometry (AMPDXA) scanning system: (2) a portable neutron spectrometer; (3) a miniature time-of-flight mass spectrometer: and (4) a cardiovascular identification system. Technical highlights of the original projects are presented along with an introduction to the five new TD Team projects being funded by the NSBRI.

  5. Advances in space technology: the NSBRI Technology Development Team

    NASA Technical Reports Server (NTRS)

    Maurer, R. H.; Charles, H. K. Jr; Pisacane, V. L.

    2002-01-01

    As evidenced from Mir and other long-duration space missions, the space environment can cause significant alterations in the human physiology that could prove dangerous for astronauts. The NASA programme to develop countermeasures for these deleterious human health effects is being carried out by the National Space Biomedical Research Institute (NSBRI). The NSBRI has 12 research teams, ten of which are primarily physiology based, one addresses on-board medical care, and the twelfth focuses on technology development in support of the other research teams. This Technology Development (TD) Team initially supported four instrumentation developments: (1) an advanced, multiple projection, dual energy X ray absorptiometry (AMPDXA) scanning system: (2) a portable neutron spectrometer; (3) a miniature time-of-flight mass spectrometer: and (4) a cardiovascular identification system. Technical highlights of the original projects are presented along with an introduction to the five new TD Team projects being funded by the NSBRI.

  6. Assistive Technology Developments in Puerto Rico.

    ERIC Educational Resources Information Center

    Lizama, Mauricio A.; Mendez, Hector L.

    Recent efforts to develop Spanish-based adaptations for alternate computer input devices are considered, as are their implications for Hispanics with disabilities and for the development of language sensitive devices worldwide. Emphasis is placed on the particular need to develop low-cost high technology devices for Puerto Rico and Latin America…

  7. Capitalizing on App Development Tools and Technologies

    ERIC Educational Resources Information Center

    Luterbach, Kenneth J.; Hubbell, Kenneth R.

    2015-01-01

    Instructional developers and others creating apps must choose from a wide variety of app development tools and technologies. Some app development tools have incorporated visual programming features, which enable some drag and drop coding and contextual programming. While those features help novices begin programming with greater ease, questions…

  8. Global Nuclear Energy Partnership Technology Development Plan

    SciTech Connect

    David J. Hill

    2007-07-01

    This plan describes the GNEP Technology Demonstration Program (GNEP-TDP). It has been prepared to guide the development of integrated plans and budgets for realizing the domestic portion of the GNEP vision as well as providing the basis for developing international cooperation. Beginning with the GNEP overall goals, it describes the basic technical objectives for each element of the program, summarizes the technology status and identifies the areas of greatest technical risk. On this basis a proposed technology demonstration program is described that can deliver the required information for a Secretarial decision in the summer of 2008 and support construction of facilities.

  9. Role of research aircraft in technology development

    NASA Technical Reports Server (NTRS)

    Szalai, K. J.

    1984-01-01

    The United States's aeronautical research program has been rich in the use of research aircraft to explore new flight regimes, develop individual aeronautical concepts, and investigate new vehicle classes and configurations. This paper reviews the NASA supercritical wing, digital fly-by-wire, HiMAT, and AD-1 oblique-wing flight research programs, and draws from these examples general conclusions regarding the role and impact of research aircraft in technology development. The impact of a flight program on spinoff technology is also addressed. The secondary, serendipitous results are often highly significant. Finally, future research aircraft programs are examined for technology trends and expected results.

  10. Molten nitrate salt technology development

    NASA Astrophysics Data System (ADS)

    Carling, R. W.; Kramer, C. M.; Bradshaw, R. W.; Nissen, D. A.; Goods, S. H.; Mar, R. W.; Munford, J. W.; Karnowsky, M. M.; Biefeld, R. N.; Norem, N. J.

    1981-03-01

    Of the fluids proposed for heat transfer and energy storage, molten nitrate salts offer significant economic advantages. The nitrate salt of most interest is a binary mixture of NaNO3 and KNO3. Although nitrate/nitrite mixtures were used for decades as heat transfer and heat treatment fluids the use was at temperatures of about 4500 C and lower. In solar thermal power systems the salts will experience a temperature range of 350 to 6000 C. Because central receiver applications place more rigorous demands and higher temperatures on nitrate salts a comprehensive experimental program was developed to examine what effects, if any, the new demands and temperatures have on the salts. The experiments include corrosion testing, environmental cracking of containment materials, and determinations of physical properties and decomposition mechanisms.

  11. Development of laser technology in Poland: 2016

    NASA Astrophysics Data System (ADS)

    Jankiewicz, Zdzisław; Jabczyński, Jan K.; Romaniuk, Ryszard S.

    2016-12-01

    The paper is an introduction to the volume of proceedings and a concise digest of works presented during the XIth National Symposium on Laser Technology (SLT2016) [1]. The Symposium is organized since 1984 every three years [2-8]. SLT2016 was organized by the Institute of Optoelectronics, Military University of Technology (IO, WAT) [9], Warsaw, with cooperation of Warsaw University of Technology (WUT) [10], in Jastarnia on 27-30 September 2016. Symposium Proceedings are traditionally published by SPIE [11-19]. The meeting has gathered around 150 participants who presented around 120 research and technical papers. The Symposium, organized every 3 years is a good portrait of laser technology and laser applications development in Poland at university laboratories, governmental institutes, company R&D laboratories, etc. The SLT also presents the current technical projects under realization by the national research, development and industrial teams. Topical tracks of the Symposium, traditionally divided to two large areas - sources and applications, were: laser sources in near and medium infrared, picosecond and femtosecond lasers, optical fiber lasers and amplifiers, semiconductor lasers, high power and high energy lasers and their applications, new materials and components for laser technology, applications of laser technology in measurements, metrology and science, military applications of laser technology, laser applications in environment protection and remote detection of trace substances, laser applications in medicine and biomedical engineering, laser applications in industry, technologies and material engineering.

  12. DEVELOPMENT OF EMERGING TECHNOLOGIES WITHIN THE SITE PROGRAM

    EPA Science Inventory

    The Site Program is formed by five research programs: the Demonstration Program, the Emerging Technology Program, the Measurement and Monitoring Technology Development Program, the Innovative Technology Program, and the Technology Transfer Program. The Emerging Technology (ET) P...

  13. Development of the AP Technology Through Time

    NASA Astrophysics Data System (ADS)

    Charmier, F.; Martin, O.; Gariepy, R.

    2015-02-01

    This article presents the historical development of the AP Technology (Aluval, Voreppe, France) pot series starting with the AP13 in the 1960s, followed by the AP18 and the AP30 in the 1980s and 1990s. For most of the modern-era technology, from the late 1970s on, development has been based on a three-stage pattern, the first one being the pot modeling, followed by the pot prototype stage, and then the industrial stage, which fully validated the technology. This development pattern has proven to be successful since it has led to the very robust AP Technology pot design generation and a large number of greenfield smelters built in the 1990-2010 selected the AP Technology design. AP60 is the latest of this series: The development at the prototype level was initiated in the 1990s and is presented in the article. It is now followed by the first industrial realization at Jonquière with the startup in late 2013 and the full validation of the technology in mid-2014. The development of APXe, which aims at very low energy consumption, uses many common elements pertaining to the AP60 design and is presented in the article. AP Technology has also addressed the need for continuous and fast improvement of pot performances adapted to each existing client or site specifics; for this purpose, a new development methodology has recently emerged thanks to the very high modeling capabilities. This methodology, based on the validation of "technology bricks" and their integration in the final design following a strict process, is presented in the last section of this article.

  14. Industrial Arts Test Development, Book III. Resource Items for Graphics Technology, Power Technology, Production Technology.

    ERIC Educational Resources Information Center

    New York State Education Dept., Albany.

    This booklet is designed to assist teachers in developing examinations for classroom use. It is a collection of 955 objective test questions, mostly multiple choice, for industrial arts students in the three areas of graphics technology, power technology, and production technology. Scoring keys are provided. There are no copyright restrictions,…

  15. SMD Technology Development Story for NASA Annual Technology report

    NASA Technical Reports Server (NTRS)

    Seablom, Michael S.

    2017-01-01

    The role of the Science Mission Directorate (SMD) is to enable NASA to achieve its science goals in the context of the Nation's science agenda. SMD's strategic decisions regarding future missions and scientific pursuits are guided by Agency goals, input from the science community-including the recommendations set forth in the National Research Council (NRC) decadal surveys-and a commitment to preserve a balanced program across the major science disciplines. Toward this end, each of the four SMD science divisions-Heliophysics, Earth Science, Planetary Science, and Astrophysics-develops fundamental science questions upon which to base future research and mission programs. Often the breakthrough science required to answer these questions requires significant technological innovation-e.g., instruments or platforms with capabilities beyond the current state of the art. SMD's targeted technology investments fill technology gaps, enabling NASA to build the challenging and complex missions that accomplish groundbreaking science.

  16. Technology certification and technology acceptance: Promoting interstate cooperation and market development for innovative technologies

    SciTech Connect

    Brockbank, B.R.

    1995-03-01

    In the past two years, public and private efforts to promote development and deployment of innovative environmental technologies have shifted from the analysis of barriers to the implementation of a variety of initiatives aimed at surmounting those barriers. Particular attention has been directed at (1) streamlining fragmented technology acceptance processes within and among the states, and (2) alleviating disincentives, created by inadequate or unverified technology cost and performance data, for users and regulators to choose innovative technologies. Market fragmentation currently imposes significant cost burdens on technology developers and inhibits the investment of private capital in environmental technology companies. Among the responses to these problems are state and federal technology certification/validation programs, efforts to standardize cost/performance data reporting, and initiatives aimed at promoting interstate cooperation in technology testing and evaluation. This paper reviews the current status of these initiatives, identifies critical challenges to their success, and recommends strategies for addressing those challenges.

  17. HUMID AIR TURBINE CYCLE TECHNOLOGY DEVELOPMENT PROGRAM

    SciTech Connect

    Richard Tuthill

    2002-07-18

    The Humid Air Turbine (HAT) Cycle Technology Development Program focused on obtaining HAT cycle combustor technology that will be the foundation of future products. The work carried out under the auspices of the HAT Program built on the extensive low emissions stationary gas turbine work performed in the past by Pratt & Whitney (P&W). This Program is an integral part of technology base development within the Advanced Turbine Systems Program at the Department of Energy (DOE) and its experiments stretched over 5 years. The goal of the project was to fill in technological data gaps in the development of the HAT cycle and identify a combustor configuration that would efficiently burn high moisture, high-pressure gaseous fuels with low emissions. The major emphasis will be on the development of kinetic data, computer modeling, and evaluations of combustor configurations. The Program commenced during the 4th Quarter of 1996 and closed in the 4th Quarter of 2001. It teamed the National Energy Technology Laboratory (NETL) with P&W, the United Technologies Research Center (UTRC), and a subcontractor on-site at UTRC, kraftWork Systems Inc. The execution of the program started with bench-top experiments that were conducted at UTRC for extending kinetic mechanisms to HAT cycle temperature, pressure, and moisture conditions. The fundamental data generated in the bench-top experiments was incorporated into the analytical tools available at P&W to design the fuel injectors and combustors. The NETL then used the hardware to conduct combustion rig experiments to evaluate the performance of the combustion systems at elevated pressure and temperature conditions representative of the HAT cycle. The results were integrated into systems analysis done by kraftWork to verify that sufficient understanding of the technology had been achieved and that large-scale technological application and demonstration could be undertaken as follow-on activity. An optional program extended the

  18. Advances in Robotic Servicing Technology Development

    NASA Technical Reports Server (NTRS)

    Gefke, Gardell G.; Janas, Alex; Pellegrino, Joseph; Sammons, Matthew; Reed, Benjamin

    2015-01-01

    NASA's Satellite Servicing Capabilities Office (SSCO) has matured robotic and automation technologies applicable to in-space robotic servicing and robotic exploration over the last six years. This paper presents the progress of technology development activities at the Goddard Space Flight Center Servicing Technology Center and on the ISS, with an emphasis on those occurring in the past year. Highlighted advancements are design reference mission analysis for servicing in low Earth orbit (LEO) and near Earth asteroid boulder retrieval; delivery of the engineering development unit of the NASA Servicing Arm; an update on International Space Station Robotic Refueling Mission; and status of a comprehensive ground-based space robot technology demonstration expanding in-space robotic servicing capabilities beginning fall 2015.

  19. Advances in Robotic Servicing Technology Development

    NASA Technical Reports Server (NTRS)

    Gefke, Gardell G.; Janas, Alex; Pellegrino, Joseph; Sammons, Matthew; Reed, Benjamin

    2015-01-01

    NASA's Satellite Servicing Capabilities Office (SSCO) has matured robotic and automation technologies applicable to in-space robotic servicing and robotic exploration over the last six years. This paper presents the progress of technology development activities at the Goddard Space Flight Center Servicing Technology Center and on the ISS, with an emphasis on those occurring in the past year. Highlighted advancements are design reference mission analysis for servicing in low Earth orbit (LEO) and asteroid redirection; delivery of the engineering development unit of the NASA Servicing Arm; an update on International Space Station Robotic Refueling Mission; and status of a comprehensive ground-based space robot technology demonstration expanding in-space robotic servicing capabilities beginning fall 2015.

  20. Earth feature identification and tracking technology development

    NASA Technical Reports Server (NTRS)

    Wilson, R. G.; Sivertson, W. E., Jr.

    1979-01-01

    The paper discusses needs for smart sensing in terrestrial and atmospheric remote sensing as related to current technology and a scheduled Shuttle experiment. An approach is outlined involving Shuttle-borne experiments to develop earth feature identification and tracking technology including a Feature Identification and Location Experiment (FILE) scheduled for flight on the NASA Shuttle with an objective of classifying earth features into categories of bare land, water, vegetation, and clouds, snow, and ice. The plan for evolution of the FILE-related technology leads to capabilities for pointing instruments to predetermined sites, reacquiring earth features or landmarks, and tracking features such as coastlines and rivers. Technology concepts relative to an overall system transfer function is discussed, and the development status outlined.

  1. Cyrogenic Life Support Technology Development Project

    NASA Technical Reports Server (NTRS)

    Bush, David R.

    2015-01-01

    KSC has used cryogenic life support (liquid air based) technology successfully for many years to support spaceflight operations. This technology has many benefits unique to cryogenics when compared to traditional compressed gas systems: passive cooling, lighter, longer duration, and lower operating pressure. However, there are also several limiting factors that have prevented the technology from being commercialized. The National Institute of Occupational Safety and Health, Office of Mine Safety and Health Research (NIOSH-OMSHR) has partnered with NASA to develop a complete liquid air based life support solution for emergency mine escape and rescue. The project will develop and demonstrate various prototype devices and incorporate new technological innovations that have to date prevented commercialization.

  2. Fission Surface Power Technology Development Status

    NASA Technical Reports Server (NTRS)

    Palac, Donald T.; Mason, Lee S.; Houts, Michael G.; Harlow, Scott

    2010-01-01

    Power is a critical consideration in planning exploration of the surfaces of the Moon, Mars, and beyond. Nuclear power is an important option, especially for locations in the solar system where sunlight is limited in availability or intensity. NASA is maintaining the option for fission surface power for the Moon and Mars by developing and demonstrating technology for an affordable fission surface power system. Because affordability drove the determination of the system concept that this technology will make possible, low development and recurring costs result, while required safety standards are maintained. However, an affordable approach to fission surface power also provides the benefits of simplicity, robustness, and conservatism in design. This paper will illuminate the multiplicity of benefits to an affordable approach to fission surface power, and will describe how the foundation for these benefits is being developed and demonstrated in the Exploration Technology Development Program s Fission Surface Power Project.

  3. Aviation technology applicable to developing regions

    NASA Technical Reports Server (NTRS)

    Zuk, John; Alton, Larry R.

    1988-01-01

    This paper is an analysis of aviation technologies useful for formulation of development plans to the year 2000 for emerging nations. The Caribbean Basin was used as a specific application. This development promises to be so explosive over the next 15 years as to be virtually unpredictable.

  4. Human Capital and Technology Development in Malaysia

    ERIC Educational Resources Information Center

    Awang, Halimah

    2004-01-01

    This paper examines the development of Information and Communication Technology (ICT) and its relation to the development of human capital in Malaysia as a country undergoing transformation into an ICT-driven and knowledge-based society. Education and training, being the key variable of human capital, is examined in terms of the government…

  5. New Achievements in Technology Education and Development

    ERIC Educational Resources Information Center

    Soomro, Safeeullah, Ed.

    2010-01-01

    Since many decades Education Science and Technology has an achieved tremendous recognition and has been applied to variety of disciplines, mainly Curriculum development, methodology to develop e-learning systems and education management. Many efforts have been taken to improve knowledge of students, researchers, educationists in the field of…

  6. Science and Technology Education and National Development.

    ERIC Educational Resources Information Center

    United Nations Educational, Scientific, and Cultural Organization, Paris (France).

    This three-part book focuses on the condition of science and technology (ST) education worldwide by discussing ways in which it can contribute to social, economic, and cultural developments. Part 1 examines ways in which ST can affect national development, beginning with a consideration of the impact of ST on the individual, the community, and on…

  7. MICROHOLE TECHNOLOGY PROGRESS ON BOREHOLE INSTRUMENTATION DEVELOPMENT

    SciTech Connect

    J. ALBRIGHT

    2000-09-01

    Microhole technology development is based on the premise that with advances in electronics and sensors, large conventional-diameter wells are no longer necessary for obtaining subsurface information. Furthermore, microholes offer an environment for improved substance measurement. The combination of deep microholes having diameters of 1-3/8 in. at their terminal depth and 7/8-in. diameter logging tools will comprise a very low cost alternative to currently available technology for deep subsurface characterization and monitoring.

  8. ATDRS payload technology research and development

    NASA Technical Reports Server (NTRS)

    Anzic, G.; Connolly, D. J.; Fujikawa, G.; Andro, M.; Kunath, R. R.; Sharp, G. R.

    1990-01-01

    Four technology development tasks were chosen to reduce (or at least better understand) the technology risks associated with proposed approaches to Advanced Tracking and Data Relay Satellite (ATDRS). The four tasks relate to a Tri-Band Antenna feed system, a Digital Beamforming System for the S Band Multiple Access System (SMA), an SMA Phased Array Antenna, and a Configuration Thermal/Mechanical Analysis task. The objective, approach, and status of each are discussed.

  9. CROSSCUTTING TECHNOLOGY DEVELOPMENT AT THE CENTER FOR ADVANCED SEPARATION TECHNOLOGIES

    SciTech Connect

    Christopher E. Hull

    2005-01-20

    The U.S. is the largest producer of mining products in the world. In 2003, U.S. mining operations produced $57 billion worth of raw materials that contributed a total of $564 billion to the nation's wealth. Despite these contributions, the mining industry has not been well supported with research and development funds as compared to mining industries in other countries. To overcome this problem, the Center for Advanced Separation Technologies (CAST) was established to develop technologies that can be used by the U.S. mining industry to create new products, reduce production costs, and meet environmental regulations. Much of the research to be conducted with Cooperative Agreement funds will be longer-term, high-risk, basic research and will be carried out in five broad areas: (1) Solid-solid separation; (2) Solid-liquid separation; (3) Chemical/Biological Extraction; (4) Modeling and Control; and (5) Environmental Control.

  10. Mobile display technologies: Past developments, present technologies, and future opportunities

    NASA Astrophysics Data System (ADS)

    Ohshima, Hiroyuki

    2014-01-01

    It has been thirty years since the first active matrix (AM) flat panel display (FPD) was industrialized for portable televisions (TVs) in 1984. The AM FPD has become a dominant electronic display technology widely used from mobile displays to large TVs. The development of AM FPDs for mobile displays has significantly changed our lives by enabling new applications, such as notebook personal computers (PCs), smartphones and tablet PCs. In the future, the role of mobile displays will become even more important, since mobile displays are the live interface for the world of mobile communications in the era of ubiquitous networks. Various developments are being conducted to improve visual performance, reduce power consumption and add new functionality. At the same time, innovative display concepts and novel manufacturing technologies are being investigated to create new values.

  11. AFCI Safeguards Enhancement Study: Technology Development Roadmap

    SciTech Connect

    Smith, Leon E.; Dougan, A.; Tobin, Stephen; Cipiti, B.; Ehinger, Michael H.; Bakel, A. J.; Bean, Robert; Grate, Jay W.; Santi, P.; Bryan, Steven; Kinlaw, M. T.; Schwantes, Jon M.; Burr, Tom; Lehn, Scott A.; Tolk, K.; Chichester, David; Menlove, H.; Vo, D.; Duckworth, Douglas C.; Merkle, P.; Wang, T. F.; Duran, F.; Nakae, L.; Warren, Glen A.; Friedrich, S.; Rabin, M.

    2008-12-31

    The Advanced Fuel Cycle Initiative (AFCI) Safeguards Campaign aims to develop safeguards technologies and processes that will significantly reduce the risk of proliferation in the U.S. nuclear fuel cycle of tomorrow. The Safeguards Enhancement Study was chartered with identifying promising research and development (R&D) directions over timescales both near-term and long-term, and under safeguards oversight both domestic and international. This technology development roadmap documents recognized gaps and needs in the safeguarding of nuclear fuel cycles, and outlines corresponding performance targets for each of those needs. Drawing on the collective expertise of technologists and user-representatives, a list of over 30 technologies that have the potential to meet those needs was developed, along with brief summaries of each candidate technology. Each summary describes the potential impact of that technology, key research questions to be addressed, and prospective development milestones that could lead to a definitive viability or performance assessment. Important programmatic linkages between U.S. agencies and offices are also described, reflecting the emergence of several safeguards R&D programs in the U.S. and the reinvigoration of nuclear fuel cycles across the globe.

  12. Crosscutting Technology Development at the Center for Advanced Separation Technologies

    SciTech Connect

    Christopher Hull

    2009-10-31

    The U.S. is the largest producer of mining products in the world. In 2003, U.S. mining operations produced $57 billion worth of raw materials that contributed a total of $564 billion to the nation's wealth. Despite these contributions, the mining industry has not been well supported with research and development funds as compared to mining industries in other countries. To overcome this problem, the Center for Advanced Separation Technologies (CAST) was established to develop technologies that can be used by the U.S. mining industry to create new products, reduce production costs, and meet environmental regulations. Originally set up by Virginia Tech and West Virginia University, this endeavor has been expanded into a seven-university consortium -- Virginia Tech, West Virginia University, University of Kentucky, University of Utah, Montana Tech, New Mexico Tech and University of Nevada, Reno - that is supported through U.S. DOE Cooperative Agreement No. DE-FC26-02NT41607: Crosscutting Technology Development at the Center for Advanced Separation Technologies. Much of the research to be conducted with Cooperative Agreement funds will be longer-term, high-risk, basic research and will be carried out in five broad areas: (1) Solid-solid separation; (2) Solid-liquid separation; (3) Chemical/biological extraction; (4) Modeling and control; and (5) Environmental control. Distribution of funds is handled via competitive solicitation of research proposals through Site Coordinators at the seven member universities. These were first reviewed and ranked by a group of technical reviewers (selected primarily from industry). Based on these reviews, and an assessment of overall program requirements, the CAST Technical Committee made an initial selection/ranking of proposals and forwarded these to the DOE/NETL Project Officer for final review and approval. The successful projects are listed by category, along with brief abstracts of their aims and objectives.

  13. Microsystem technology development at Sandia National Laboratories

    SciTech Connect

    Smith, J.H.

    1995-11-01

    An overview of the major sensor and actuator projects using the micromachining capabilities of the Microelectronics Development Laboratory at Sandia National Laboratories is presented. Development efforts are underway for a variety of surface micromachined sensors and actuators. A technology that embeds micromechanical devices below the surface of the wafer prior to microelectronics fabrication has also been developed for integrating microelectronics with surface micromachined micromechanical devices.

  14. Making technological innovation work for sustainable development

    PubMed Central

    Anadon, Laura Diaz; Harley, Alicia G.; Matus, Kira; Moon, Suerie; Murthy, Sharmila L.

    2016-01-01

    This paper presents insights and action proposals to better harness technological innovation for sustainable development. We begin with three key insights from scholarship and practice. First, technological innovation processes do not follow a set sequence but rather emerge from complex adaptive systems involving many actors and institutions operating simultaneously from local to global scales. Barriers arise at all stages of innovation, from the invention of a technology through its selection, production, adaptation, adoption, and retirement. Second, learning from past efforts to mobilize innovation for sustainable development can be greatly improved through structured cross-sectoral comparisons that recognize the socio-technical nature of innovation systems. Third, current institutions (rules, norms, and incentives) shaping technological innovation are often not aligned toward the goals of sustainable development because impoverished, marginalized, and unborn populations too often lack the economic and political power to shape innovation systems to meet their needs. However, these institutions can be reformed, and many actors have the power to do so through research, advocacy, training, convening, policymaking, and financing. We conclude with three practice-oriented recommendations to further realize the potential of innovation for sustainable development: (i) channels for regularized learning across domains of practice should be established; (ii) measures that systematically take into account the interests of underserved populations throughout the innovation process should be developed; and (iii) institutions should be reformed to reorient innovation systems toward sustainable development and ensure that all innovation stages and scales are considered at the outset. PMID:27519800

  15. Making technological innovation work for sustainable development.

    PubMed

    Anadon, Laura Diaz; Chan, Gabriel; Harley, Alicia G; Matus, Kira; Moon, Suerie; Murthy, Sharmila L; Clark, William C

    2016-08-30

    This paper presents insights and action proposals to better harness technological innovation for sustainable development. We begin with three key insights from scholarship and practice. First, technological innovation processes do not follow a set sequence but rather emerge from complex adaptive systems involving many actors and institutions operating simultaneously from local to global scales. Barriers arise at all stages of innovation, from the invention of a technology through its selection, production, adaptation, adoption, and retirement. Second, learning from past efforts to mobilize innovation for sustainable development can be greatly improved through structured cross-sectoral comparisons that recognize the socio-technical nature of innovation systems. Third, current institutions (rules, norms, and incentives) shaping technological innovation are often not aligned toward the goals of sustainable development because impoverished, marginalized, and unborn populations too often lack the economic and political power to shape innovation systems to meet their needs. However, these institutions can be reformed, and many actors have the power to do so through research, advocacy, training, convening, policymaking, and financing. We conclude with three practice-oriented recommendations to further realize the potential of innovation for sustainable development: (i) channels for regularized learning across domains of practice should be established; (ii) measures that systematically take into account the interests of underserved populations throughout the innovation process should be developed; and (iii) institutions should be reformed to reorient innovation systems toward sustainable development and ensure that all innovation stages and scales are considered at the outset.

  16. Incorporating Geospatial Technology into Teacher Professional Development

    NASA Astrophysics Data System (ADS)

    Sproles, E. A.; Songer, L.

    2009-12-01

    The need for students to think spatially and use geospatial technologies is becoming more critical as these tools and concepts are increasingly incorporated into a broad range of occupations and academic disciplines. Geospatial Teaching Across the Curriculum (Geo-STAC) is a collaborative program that provides high school teachers with mentored professional development workshops in geospatial thought and technology. The seminars, led by community college faculty, give high school teachers the ability to incorporate geospatial technology into coursework across the curriculum — in Science, Technology, Engineering, and Math (STEM) and non-STEM disciplines. Students participating in the hands-on lessons gain experience in web-based and desktop Geographic Information Systems (GIS). The goals of the workshop are for teachers to: (1) understand the importance of geospatial thinking; (2) learn how to employ geospatial thinking in each discipline; (3) learn about geospatial technologies; (4) develop a Web-based GIS lesson; and, (5) implement a Web-based GIS lesson. Additionally, Geo-STAC works with high school students so that they: (1) understand the importance of geospatial technologies and careers in future job markets; (2) learn how to use Web-based GIS to solve problems; and, (3) visit the community college GIS lab and experience using desktop GIS. Geo-STAC actively disseminates this collaborative model to colleges to community colleges and high schools across the country.

  17. An Overview of NASA's Current Materials Development Efforts for Mars EDL

    NASA Technical Reports Server (NTRS)

    Beck, Robin A.; Gasch, Matthew; Calomino, Anthony

    2011-01-01

    Current roadmaps point to landing heavy masses (cargo, followed by manned vehicles) on Mars in the 2030's and the existing entry, descent and landing (EDL) technology will not be sufficient to facilitate such missions. In 2009 the Exploration Technology Development Program (ETDP) established the Entry, Descent and Landing Technology Development Project (EDL TDP), to be managed programmatically at Langley Research Center (LaRC) and technically a Ames Research Center (ARC). The purpose of the project is to further the technologies required to land heavy (approximately 40 metric ton) masses on Mars to facilitate exploration. The EDL TDP contains three technical elements. They are: 1) Thermal Protection Systems (TPS) development 2) Modeling and Tools (MAT) development 3) Supersonic Retropropulsion (SRP) development The primary goals of the EDL TDP TPS element is to design and develop TPS materials capable of withstanding the severe aerothermal loads associated with aerocapture and entry into the Martian atmosphere while significantly decreasing the TPS mass fraction contribution to the entry system. Significant advancements in TPS materials technology are needed in order to enable heavy mass payloads to be successfully landed on the Martian surface for robotic precursors and subsequent human exploration missions. The EDL TDP TPS element is further divided into two different TPS concepts for Mars EDL those being: 1) Rigid TPS for a mid L/D aeroshell with the capability to withstand dual pulsed heating environments as high as 500 W/square cm for aerocapture and 130 W/square cm for entry 2) Flexible TPS for a deployable aerodynamic decelerator with the capability to withstand dual pulsed heating environments as high as 120 W/square cm for aerocapture and 30 W/square cm for entry NASA, along with its vendors, has begun developing and testing materials for each of the deceleration approaches. These include multi-layer rigid ablators and flexible ablative materials. In order

  18. Development of fluidized bed cement sintering technology

    SciTech Connect

    Mukai, Katsuji

    1994-12-31

    In the new system presented in this paper, the cement clinker is sintered, not in a rotary kiln, but in two different furnaces: a spouted bed kiln and a fluidized bed kiln. The heat generated in the process of cooling the cement clinker is recovered by a fluidized bed cooler and a packed bed cooler, which are more efficient than the conventional coolers. Compared with the rotary kiln system, the new technology significantly reduces NO{sub x} emissions, appreciably cuts energy consumption, and reduces CO{sub 2} emissions as well. Thus, the new system is an efficient cement sintering system that is friendly to the global environment. In this paper, we describe this new technology as one of the applied technologies at an industrial level that is being developed in the Clean Coal Technology Project, and we present the results from test operations at our pilot plant.

  19. A Proposal to Develop Interactive Classification Technology

    NASA Technical Reports Server (NTRS)

    deBessonet, Cary

    1998-01-01

    Research for the first year was oriented towards: 1) the design of an interactive classification tool (ICT); and 2) the development of an appropriate theory of inference for use in ICT technology. The general objective was to develop a theory of classification that could accommodate a diverse array of objects, including events and their constituent objects. Throughout this report, the term "object" is to be interpreted in a broad sense to cover any kind of object, including living beings, non-living physical things, events, even ideas and concepts. The idea was to produce a theory that could serve as the uniting fabric of a base technology capable of being implemented in a variety of automated systems. The decision was made to employ two technologies under development by the principal investigator, namely, SMS (Symbolic Manipulation System) and SL (Symbolic Language) [see debessonet, 1991, for detailed descriptions of SMS and SL]. The plan was to enhance and modify these technologies for use in an ICT environment. As a means of giving focus and direction to the proposed research, the investigators decided to design an interactive, classificatory tool for use in building accessible knowledge bases for selected domains. Accordingly, the proposed research was divisible into tasks that included: 1) the design of technology for classifying domain objects and for building knowledge bases from the results automatically; 2) the development of a scheme of inference capable of drawing upon previously processed classificatory schemes and knowledge bases; and 3) the design of a query/ search module for accessing the knowledge bases built by the inclusive system. The interactive tool for classifying domain objects was to be designed initially for textual corpora with a view to having the technology eventually be used in robots to build sentential knowledge bases that would be supported by inference engines specially designed for the natural or man-made environments in which the

  20. Technical Colleges, Technology Deployment, and Regional Development.

    ERIC Educational Resources Information Center

    Rosenfeld, Stuart

    In this document, the Organization for Economic Cooperation and Development (OECD) reports on the state of technical education in Europe, the United States, and Canada. It states that technical colleges are emerging as key institutions in technology-based education to fill industry requirement for more highly skilled and technically proficient…

  1. Recommendations for Radiologic Technology Workforce Development.

    ERIC Educational Resources Information Center

    Collins, Dale E.

    A literature review was conducted to establish criteria for the development and establishment of an associate degree program in radiologic technology in Alaska, where traditional education programs had been slow to respond to the current personnel shortage. The information was obtained from a variety of state, regional, and national organizations…

  2. Human Support Technology Research, Development and Demonstration

    NASA Technical Reports Server (NTRS)

    Joshi, Jitendra; Trinh, Eugene

    2004-01-01

    The Human Support Technology research, development, and demonstration program address es the following areas at TRL: Advanced Power and Propulsion. Cryogenic fluid management. Closed-loop life support and Habitability. Extravehicular activity systems. Scientific data collection and analysis. and Planetary in-situ resource utilization.

  3. Thermoelectric Development at Hi-Z Technology

    SciTech Connect

    Kushch, Aleksandr S.; Bass, John C.; Ghamaty, Saeid; Elsner, Norbert B.; Bergstrand, Richard A.; Furrow, David; Melvin, Mike

    2002-08-25

    An improved Thermoelectric Generator (TEG) for the Heavy Duty Class Eight Diesel Trucks is under development at Hi-Z Technology. The current TEG is equipped with the improved HZ-14 Thermoelectric module, which features better mechanical properties as well as higher electric power output. Also, the modules are held in place more securely.

  4. Implementing Information Technology Projects in Developing Countries.

    ERIC Educational Resources Information Center

    Kanamugire, Athanase B.

    1993-01-01

    Reviews the problems of implementing information technology in developing countries and cites examples from African projects. The use of CD-ROM for access to information is examined, and experiences at the King Fahd University of Petroleum and Minerals in Saudi Arabia in introducing CD-ROM search services are described. (Contains five references.)…

  5. Vaccine development using recombinant DNA technology

    Technology Transfer Automated Retrieval System (TEKTRAN)

    Vaccines induce an immune response in the host that subsequently recognizes infectious agents and helps fight off the disease; vaccines must do this without causing the disease. This paper reviews the development of recombinant DNA technologies as a means of providing new ways for attenuating diseas...

  6. Cryogenic Technology Development for Exploration Missions

    NASA Technical Reports Server (NTRS)

    Chato, David J.

    2007-01-01

    This paper reports the status and findings of different cryogenic technology research projects in support of the President s Vision for Space Exploration. The exploration systems architecture study is reviewed for cryogenic fluid management needs. It is shown that the exploration architecture is reliant on the cryogenic propellants of liquid hydrogen, liquid oxygen and liquid methane. Needs identified include: the key technologies of liquid acquisition devices, passive thermal and pressure control, low gravity mass gauging, prototype pressure vessel demonstration, active thermal control; as well as feed system testing, and Cryogenic Fluid Management integrated system demonstration. Then five NASA technology projects are reviewed to show how these needs are being addressed by technology research. Projects reviewed include: In-Space Cryogenic Propellant Depot; Experimentation for the Maturation of Deep Space Cryogenic Refueling Technology; Cryogenic Propellant Operations Demonstrator; Zero Boil-Off Technology Experiment; and Propulsion and Cryogenic Advanced Development. Advances are found in the areas of liquid acquisition of liquid oxygen, mass gauging of liquid oxygen via radio frequency techniques, computational modeling of thermal and pressure control, broad area cooling thermal control strategies, flight experiments for resolving low gravity issues of cryogenic fluid management. Promising results are also seen for Joule-Thomson pressure control devices in liquid oxygen and liquid methane and liquid acquisition of methane, although these findings are still preliminary.

  7. Cosmic Origins (COR) Technology Development Program Overview

    NASA Astrophysics Data System (ADS)

    Werneth, Russell; Pham, B.; Clampin, M.

    2014-01-01

    The Cosmic Origins (COR) Program Office was established in FY11 and resides at the NASA Goddard Space Flight Center (GSFC). The office serves as the implementation arm for the Astrophysics Division at NASA Headquarters for COR Program related matters. We present an overview of the Program’s technology management activities and the Program’s technology development portfolio. We discuss the process for addressing community-provided technology needs and the Technology Management Board (TMB)-vetted prioritization and investment recommendations. This process improves the transparency and relevance of technology investments, provides the community a voice in the process, and leverages the technology investments of external organizations by defining a need and a customer. Goals for the COR Program envisioned by the National Research Council’s (NRC) “New Worlds, New Horizons in Astronomy and Astrophysics” (NWNH) Decadal Survey report includes a 4m-class UV/optical telescope that would conduct imaging and spectroscopy as a post-Hubble observatory with significantly improved sensitivity and capability, a near-term investigation of NASA participation in the Japanese Aerospace Exploration Agency/Institute of Space and Astronautical Science (JAXA/ISAS) Space Infrared Telescope for Cosmology and Astrophysics (SPICA) mission, and future Explorers.

  8. NASA Astrophysics Funds Strategic Technology Development

    NASA Astrophysics Data System (ADS)

    Seery, Bernard D.; Ganel, Opher; Pham, Bruce

    2016-01-01

    The COR and PCOS Program Offices (POs) reside at the NASA Goddard Space Flight Center (GSFC), serving as the NASA Astrophysics Division's implementation arm for matters relating to the two programs. One aspect of the PO's activities is managing the COR and PCOS Strategic Astrophysics Technology (SAT) program, helping mature technologies to enable and enhance future astrophysics missions. For example, the SAT program is expected to fund key technology developments needed to close gaps identified by Science and Technology Definition Teams (STDTs) planned to study several large mission concept studies in preparation for the 2020 Decadal Survey.The POs are guided by the National Research Council's "New Worlds, New Horizons in Astronomy and Astrophysics" Decadal Survey report, NASA's Astrophysics Implementation Plan, and the visionary Astrophysics Roadmap, "Enduring Quests, Daring Visions." Strategic goals include dark energy, gravitational waves, and X-ray observatories. Future missions pursuing these goals include, e.g., US participation in ESA's Euclid, Athena, and L3 missions; Inflation probe; and a large UV/Optical/IR (LUVOIR) telescope.To date, 65 COR and 71 PCOS SAT proposals have been received, of which 15 COR and 22 PCOS projects were funded. Notable successes include maturation of a new far-IR detector, later adopted by the SOFIA HAWC instrument; maturation of the H4RG near-IR detector, adopted by WFIRST; development of an antenna-coupled transition-edge superconducting bolometer, a technology deployed by BICEP2/BICEP3/Keck to measure polarization in the CMB signal; advanced UV reflective coatings implemented on the optics of GOLD and ICON, two heliophysics Explorers; and finally, the REXIS instrument on OSIRIS-REx is incorporating CCDs with directly deposited optical blocking filters developed by another SAT-funded project.We discuss our technology development process, with community input and strategic prioritization informing calls for SAT proposals and

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

    NASA Technical Reports Server (NTRS)

    Steele, Gynelle C.

    2001-01-01

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

  10. Extended Temperature Solar Cell Technology Development

    NASA Technical Reports Server (NTRS)

    Landis, Geoffrey A.; Jenkins, Phillip; Scheiman, David; Rafaelle, Ryne

    2004-01-01

    Future NASA missions will require solar cells to operate both in regimes closer to the sun, and farther from the sun, where the operating temperatures will be higher and lower than standard operational conditions. NASA Glenn is engaged in testing solar cells under extended temperature ranges, developing theoretical models of cell operation as a function of temperature, and in developing technology for improving the performance of solar cells for both high and low temperature operation.

  11. ICPP Waste Management Technology Development Program

    SciTech Connect

    Hogg, G.W.; Olson, A.L.; Knecht, D.A.; Bonkoski, M.J.

    1993-01-01

    As a result of the decision to curtail reprocessing at the Idaho Chemical Processing Plant (ICPP), a Spent fuel and Waste Management Technology Development plan has been implemented to identify acceptable options for disposing of the (1) sodium-bearing liquid radioactive waste, (2) radioactive calcine, and (3) irradiated spent fuel stored at the Idaho National Engineering Laboratory (INEL). The plan was developed jointly by DOE and WINCO.

  12. [Recent development of microfluidic diagnostic technologies].

    PubMed

    Li, Haifang; Zhang, Qianyun; Lin, Jin-Ming

    2011-04-01

    Microfluidic devices exhibit a great promising development in clinical diagnosis and disease screening due to their advantages of precise controlling of fluid flow, requirement of miniamount sample, rapid reaction speed and convenient integration. In this paper, the improvements of microfluidic diagnostic technologies in recent years are reviewed. The applications and developments of on-chip disease marker detection, microfluidic cell selection and cell drug metabolism, and diagnostic micro-devices are discussed.

  13. In-Space Propulsion Technology Products for NASA's Future Science and Exploration Missions

    NASA Technical Reports Server (NTRS)

    Anderson, David J.; Pencil, Eric; Peterson, Todd; Dankanich, John; Munk, Michelle M.

    2011-01-01

    Since 2001, the In-Space Propulsion Technology (ISPT) project has been developing and delivering in-space propulsion technologies that will enable or enhance NASA robotic science missions. These in-space propulsion technologies are applicable, and potentially enabling, for future NASA flagship and sample return missions currently being considered, as well as having broad applicability to future competed mission solicitations. The high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance for lower cost was completed in 2009. Two other ISPT technologies are nearing completion of their technology development phase: 1) NASA's Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system; and 2) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures; guidance, navigation, and control (GN&C) models of blunt-body rigid aeroshells; aerothermal effect models: and atmospheric models for Earth, Titan, Mars and Venus. This paper provides status of the technology development, applicability, and availability of in-space propulsion technologies that have recently completed their technology development and will be ready for infusion into NASA s Discovery, New Frontiers, Science Mission Directorate (SMD) Flagship, and Exploration technology demonstration missions

  14. In-Space Propulsion Technology Products Ready for Infusion on NASA's Future Science Missions

    NASA Technical Reports Server (NTRS)

    Anderson, David J.; Pencil, Eric; Peterson, Todd; Dankanich, John; Munk, Michele M.

    2012-01-01

    Since 2001, the In-Space Propulsion Technology (ISPT) program has been developing and delivering in-space propulsion technologies that will enable or enhance NASA robotic science missions. These in-space propulsion technologies are applicable, and potentially enabling, for future NASA flagship and sample return missions currently being considered. They have a broad applicability to future competed mission solicitations. The high-temperature Advanced Material Bipropellant Rocket (AMBR) engine, providing higher performance for lower cost, was completed in 2009. Two other ISPT technologies are nearing completion of their technology development phase: 1) NASA s Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system; and 2) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures; guidance, navigation, and control (GN&C) models of blunt-body rigid aeroshells; aerothermal effect models; and atmospheric models for Earth, Titan, Mars and Venus. This paper provides status of the technology development, applicability, and availability of in-space propulsion technologies that have recently completed their technology development and will be ready for infusion into NASA s Discovery, New Frontiers, SMD Flagship, or technology demonstration missions.

  15. Survey and analysis of federally developed technology

    SciTech Connect

    Reed, J.E.; Conrad, J.L.

    1983-02-01

    The methodology and results of a test effort to determine whether there exist unexpected opportunities for the direct transfer of technologies from federal laboratories to industry are presented. Specifically, the latest results of six federal laboratories with potential application in the pulp and paper industry, particularly those results applicable to improving energy productivity, were evaluated, cataloged, and distributed to industry representatives to gauge their reaction. The principal methodological steps in this effort were the development of a taxonomy of the pulp and paper industry, identification of industry needs and laboratory capabilities, laboratory visits, review of technology findings with industry, and evaluation and compilation of industry responses.

  16. Continuation of Crosscutting Technology Development at Cast

    SciTech Connect

    Yoon, Roe-Hoan

    2012-03-31

    This Final Technical Report describes progress made on the sub-projects awarded in the Cooperative Agreement DE-FC26-05NT42457: Continuation of Crosscutting Technology Development at Center for Advanced Separation Technologies (CAST). The final reports for each sub-project are attached in the appendix. Much of the research to be conducted with Cooperative Agreement funds will be longer-term, high-risk, basic research and will be carried out in five broad areas: a) Solid-solid separation b) Solid-liquid separation c) Chemical/Biological Extraction d) Modeling and Control, and e) Environmental Control.

  17. Advanced Gas Turbine (AGT) technology development project

    NASA Technical Reports Server (NTRS)

    1987-01-01

    This report is the final in a series of Technical Summary Reports for the Advanced Gas Turbine (AGT) Technology Development Project, authorizrd under NASA Contract DEN3-167 and sponsored by the DOE. The project was administered by NASA-Lewis Research Center of Cleveland, Ohio. Plans and progress are summarized for the period October 1979 through June 1987. This program aims to provide the US automotive industry the high risk, long range technology necessary to produce gas turbine engines for automobiles that will reduce fuel consumption and reduce environmental impact. The intent is that this technology will reach the marketplace by the 1990s. The Garrett/Ford automotive AGT was designated AGT101. The AGT101 is a 74.5 kW (100 shp) engine, capable of speeds to 100,000 rpm, and operates at turbine inlet temperatures to 1370 C (2500 F) with a specific fuel consumption level of 0.18 kg/kW-hr (0.3 lbs/hp-hr) over most of the operating range. This final report summarizes the powertrain design, power section development and component/ceramic technology development.

  18. TECHNOLOGY DEVELOPMENT ON THE DUPIC SAFEGUARDS SYSTEM

    SciTech Connect

    H. KIM; H. CHA; ET AL

    2001-02-01

    A safeguards system has been developed since 1993 in the course of supporting a fuel cycle process to fabricate CANDU fuel with spent PWR fuel (known as Direct Use of PWR spent fuel In CANDU, DUPIC). The major safeguards technology involved here was to design and fabricate a neutron coincidence counting system for process accountability, and also an unattended continuous monitoring system in association with independent verification by the IAEA. This combined technology was to produce information of nuclear material content and to maintain knowledge of the continuity of nuclear material flow. In addition to hardware development, diagnosis software is being developed to assist data acquisition, data review, and data evaluation based on a neural network system on the IAEA C/S system.

  19. Gas cooled fuel cell systems technology development

    NASA Astrophysics Data System (ADS)

    Canton, M. H.; Chepanoske, W. A.; Feret, J. M.; France, L. L.; Haines, N. L.; Heberling, C. F.; Holman, R. R.; Kelly, J. L.; Kochka, E. L.

    1992-03-01

    The development is reported of a Phosphoric Acid Fuel Cell (PAFC) for electric utility or industrial power plant applications. Results of this effort include: (1) development of a baseline rolled electrode technology; (2) advancement of fuel cell technology through improvements in the areas of acid management, catalyst selection, electrode and plate materials and processes, components designs, and quality assurance programs; (3) demonstration of improved fuel cell and stack performance and endurance; (4) successful scaleup of cell and stack design features into fun height 100 kill stacks; and (5) demonstration of combining stacks into a 400 kill module that will be the building block for power plants, including the development of testing facilities and operating procedures applicable to plant operations.

  20. Gas cooled fuel cell systems technology development

    NASA Astrophysics Data System (ADS)

    1992-03-01

    This report documents in detail the work performed by Westinghouse Electric Corporation and the Energy Research Corporation during the fourth phase of a planned multiphase program to develop a Phosphoric Acid Fuel Cell (PAFC) for electric utility or industrial power plant applications. The results of this effort include (1) development of a baseline rolled electrode technology; (2) advancement of fuel cell technology through innovative improvements in the areas of acid management, catalyst selection, electrode and plate materials and processes, component designs, and quality assurance programs; (3) demonstration of improved fuel cell and stack performance and endurance; (4) successful scaleup of cell and stack design features into full height 100 kW stacks; and (5) demonstration of combining stacks into a 400 kW module that will be the building block for power plants, including the development of testing facilities and operating procedures applicable to plant operations.

  1. Latest Developments in Nuclear Emulsion Technology

    NASA Astrophysics Data System (ADS)

    Morishima, Kunihiro

    Nuclear emulsion is high sensitive photographic film used for detection of three-dimensional trajectory of charged particles. These trajectories are recorded as tracks consist of a lot of silver grains. The size of silver grain is about 1 μm, so that nuclear emulsion has submicron three-dimensional spatial resolution, which gives us a few mrad three-dimensional angular resolution. The important technical progress was speed-up of the read-out technique of nuclear emulsions built with optical microscope system. We succeeded in developing a high-speed three-dimensional read-out system named Super Ultra Track Selector (S-UTS) with the operating read-out speed of approximately 50 cm2/h. Nowadays we are developing the nuclear emulsion gel independently in Nagoya University by introducing emulsion gel production machine. Moreover, we are developing nuclear emulsion production technologies (gel production, poring and mass production). In this paper, development of nuclear emulsion technologies for the OPERA experiment, applications by the technologies and current development are described.

  2. Technology transfer of military space microprocessor developments

    NASA Astrophysics Data System (ADS)

    Gorden, C.; King, D.; Byington, L.; Lanza, D.

    1999-01-01

    Over the past 13 years the Air Force Research Laboratory (AFRL) has led the development of microprocessors and computers for USAF space and strategic missile applications. As a result of these Air Force development programs, advanced computer technology is available for use by civil and commercial space customers as well. The Generic VHSIC Spaceborne Computer (GVSC) program began in 1985 at AFRL to fulfill a deficiency in the availability of space-qualified data and control processors. GVSC developed a radiation hardened multi-chip version of the 16-bit, Mil-Std 1750A microprocessor. The follow-on to GVSC, the Advanced Spaceborne Computer Module (ASCM) program, was initiated by AFRL to establish two industrial sources for complete, radiation-hardened 16-bit and 32-bit computers and microelectronic components. Development of the Control Processor Module (CPM), the first of two ASCM contract phases, concluded in 1994 with the availability of two sources for space-qualified, 16-bit Mil-Std-1750A computers, cards, multi-chip modules, and integrated circuits. The second phase of the program, the Advanced Technology Insertion Module (ATIM), was completed in December 1997. ATIM developed two single board computers based on 32-bit reduced instruction set computer (RISC) processors. GVSC, CPM, and ATIM technologies are flying or baselined into the majority of today's DoD, NASA, and commercial satellite systems.

  3. Extravehicular Activity Technology Development Status and Forecast

    NASA Technical Reports Server (NTRS)

    Chullen, Cinda; Westheimer, David T.

    2011-01-01

    The goal of NASA s current EVA technology effort is to further develop technologies that will be used to demonstrate a robust EVA system that has application for a variety of future missions including microgravity and surface EVA. Overall the objectives will be to reduce system mass, reduce consumables and maintenance, increase EVA hardware robustness and life, increase crew member efficiency and autonomy, and enable rapid vehicle egress and ingress. Over the past several years, NASA realized a tremendous increase in EVA system development as part of the Exploration Technology Development Program and the Constellation Program. The evident demand for efficient and reliable EVA technologies, particularly regenerable technologies was apparent under these former programs and will continue to be needed as future mission opportunities arise. The technological need for EVA in space has been realized over the last several decades by the Gemini, Apollo, Skylab, Space Shuttle, and the International Space Station (ISS) programs. EVAs were critical to the success of these programs. Now with the ISS extension to 2028 in conjunction with a current forecasted need of at least eight EVAs per year, the EVA hardware life and limited availability of the Extravehicular Mobility Units (EMUs) will eventually become a critical issue. The current EMU has successfully served EVA demands by performing critical operations to assemble the ISS and provide repairs of satellites such as the Hubble Space Telescope. However, as the life of ISS and the vision for future mission opportunities are realized, a new EVA systems capability will be needed and the current architectures and technologies under development offer significant improvements over the current flight systems. In addition to ISS, potential mission applications include EVAs for missions to Near Earth Objects (NEO), Phobos, or future surface missions. Surface missions could include either exploration of the Moon or Mars. Providing an

  4. Recent developments in terahertz sensing technology

    NASA Astrophysics Data System (ADS)

    Shur, Michael

    2016-05-01

    Terahertz technology has found numerous applications for the detection of biological and chemical hazardous agents, medical diagnostics, detection of explosives, providing security in buildings, airports, and other public spaces, shortrange covert communications (in the THz and sub-THz windows), and applications in radio astronomy and space research. The expansion of these applications will depend on the development of efficient electronic terahertz sources and sensitive low-noise terahertz detectors. Schottky diode frequency multipliers have emerged as a viable THz source technology reaching a few THz. High speed three terminal electronic devices (FETs and HBTs) have entered the THz range (with cutoff frequencies and maximum frequencies of operation above 1 THz). A new approach called plasma wave electronics recently demonstrated an efficient terahertz detection in GaAs-based and GaN-based HEMTs and in Si MOS, SOI, FINFETs and in FET arrays. This progress in THz electronic technology has promise for a significant expansion of THz applications.

  5. Space solar cell technology development - A perspective

    NASA Technical Reports Server (NTRS)

    Scott-Monck, J.

    1982-01-01

    The developmental history of photovoltaics is examined as a basis for predicting further advances to the year 2000. Transistor technology was the precursor of solar cell development. Terrestrial cells were modified for space through changes in geometry and size, as well as the use of Ag-Ti contacts and manufacture of a p-type base. The violet cell was produced for Comsat, and involved shallow junctions, new contacts, and an enhanced antireflection coating for better radiation tolerance. The driving force was the desire by private companies to reduce cost and weight for commercial satellite power supplies. Liquid phase epitaxial (LPE) GaAs cells are the latest advancement, having a 4 sq cm area and increased efficiency. GaAs cells are expected to be flight ready in the 1980s. Testing is still necessary to verify production techniques and the resistance to electron and photon damage. Research will continue in CVD cell technology, new panel technology, and ultrathin Si cells.

  6. NASA GRC Stirling Technology Development Overview

    NASA Technical Reports Server (NTRS)

    Thieme, Lanny G.; Schreiber, Jeffrey G.

    2003-01-01

    The Department of Energy, Lockheed Martin (LM), Stirling Technology Company, and NASA Glenn Research Center (GRC) are developing a high-efficiency Stirling Radioisotope Generator (SRG) for potential NASA Space Science missions. The SRG is being developed for multimission use, including providing spacecraft onboard electric power for NASA deep space missions and power for unmanned Mars rovers. NASA GRC is conducting an in- house supporting technology project to assist in developing the Stirling convertor for space qualification and mission implementation. Preparations are underway for a thermalhacuum system demonstration and unattended operation during endurance testing of the 55-We Technology Demonstration Convertors. Heater head life assessment efforts continue, including verification of the heater head brazing and heat treatment schedules and evaluation of any potential regenerator oxidation. Long-term magnet aging tests are continuing to characterize any possible aging in the strength or demagnetization resistance of the permanent magnets used in the linear alternator. Testing of the magnet/lamination epoxy bond for performance and lifetime characteristics is now underway. These efforts are expected to provide key inputs as the system integrator, LM, begins system development of the SRG. GRC is also developing advanced technology for Stirling convertors. Cleveland State University (CSU) is progressing toward a multi-dimensional Stirling computational fluid dynamics code, capable of modeling complete convertors. Validation efforts at both CSU and the University of Minnesota are complementing the code development. New efforts have been started this year on a lightweight convertor, advanced controllers, high-temperature materials, and an end-to-end system dynamics model. Performance and mass improvement goals have been established for second- and third-generation Stirling radioisotope power systems.

  7. NASA GRC Stirling Technology Development Overview

    NASA Astrophysics Data System (ADS)

    Thieme, Lanny G.; Schreiber, Jeffrey G.

    2003-01-01

    The Department of Energy, Lockheed Martin (LM), Stirling Technology Company, and NASA Glenn Research Center (GRC) are developing a high-efficiency Stirling Radioisotope Generator (SRG) for potential NASA Space Science missions. The SRG is being developed for multimission use, including providing spacecraft onboard electric power for NASA deep space missions and power for unmanned Mars rovers. NASA GRC is conducting an in-house supporting technology project to assist in developing the Stirling convertor for space qualification and mission implementation. Preparations are underway for a thermal/vacuum system demonstration and unattended operation during endurance testing of the 55-We Technology Demonstration Convertors. Heater head life assessment efforts continue, including verification of the heater head brazing and heat treatment schedules and evaluation of any potential regenerator oxidation. Long-term magnet aging tests are continuing to characterize any possible aging in the strength or demagnetization resistance of the permanent magnets used in the linear alternator. Testing of the magnet/lamination epoxy bond for performance and lifetime characteristics is now underway. These efforts are expected to provide key inputs as the system integrator, LM, begins system development of the SRG. GRC is also developing advanced technology for Stirling convertors. Cleveland State University (CSU) is progressing toward a multi-dimensional Stirling computational fluid dynamics code, capable of modeling complete convertors. Validation efforts at both CSU and the University of Minnesota are complementing the code development. New efforts have been started this year on a lightweight convertor, advanced controllers, high-temperature materials, and an end-to-end system dynamics model. Performance and mass improvement goals have been established for second- and third-generation Stirling radioisotope power systems.

  8. Technology Transfer and the Product Development Process

    SciTech Connect

    Mock, John E.

    1989-03-21

    It is my pleasure this morning to address a topic that is much talked about in passing but rarely examined from a first person point of view. That topic is Technology Transfer. Over the next 30 minutes I'd like to approach Technology Transfer within the context of the Product Development Process looking at it from the perspectives of the federal government researcher and the industry manufacturer/user. Fist let us recognize that we are living in an ''Information Age'', where global economic and military competition is determined as much by technology as it is by natural resource assets. It is estimated that technical/scientific information is presently growing at a rate of l3 percent per year; this is expected to increase to 30 percent per year by the turn of the century. In fact, something like 90 percent of all scientific knowledge has been generated in the last 30 years; this pool will double again in the next 10-15 years (Exhibit 1). Of all the scientists and engineers throughout history, 90% live and work in the present time. Successfully managing this technical information/knowledge--i.e., transforming the results of R&D to practical applications--will be an important measure of national strength. A little over a dozen years ago, the United States with only 5 percent of the world's population was generating approximately 75 percent of the world's technology. The US. share is now 50 percent and may decline to 30 percent by the turn of the century. This decline won't be because of downturn in U.S. technological advances but because the other 95 percent of the world's population will be increasing its contribution. Economic and military strength then, will be determined by how quickly and successfully companies, industries, and nations can apply new technological information to practical applications--i.e., how they manage technology transfer within the context of the product development process. Much discussion and pronouncements are ongoing in public forums

  9. Modular, Reconfigurable, High-Energy Technology Development

    NASA Technical Reports Server (NTRS)

    Carrington, Connie; Howell, Joe

    2006-01-01

    The Modular, Reconfigurable High-Energy (MRHE) Technology Demonstrator project was to have been a series of ground-based demonstrations to mature critical technologies needed for in-space assembly of a highpower high-voltage modular spacecraft in low Earth orbit, enabling the development of future modular solar-powered exploration cargo-transport vehicles and infrastructure. MRHE was a project in the High Energy Space Systems (HESS) Program, within NASA's Exploration Systems Research and Technology (ESR&T) Program. NASA participants included Marshall Space Flight Center (MSFC), the Jet Propulsion Laboratory (JPL), and Glenn Research Center (GRC). Contractor participants were the Boeing Phantom Works in Huntsville, AL, Lockheed Martin Advanced Technology Center in Palo Alto, CA, ENTECH, Inc. in Keller, TX, and the University of AL Huntsville (UAH). MRHE's technical objectives were to mature: (a) lightweight, efficient, high-voltage, radiation-resistant solar power generation (SPG) technologies; (b) innovative, lightweight, efficient thermal management systems; (c) efficient, 100kW-class, high-voltage power delivery systems from an SPG to an electric thruster system; (d) autonomous rendezvous and docking technology for in-space assembly of modular, reconfigurable spacecraft; (e) robotic assembly of modular space systems; and (f) modular, reconfigurable distributed avionics technologies. Maturation of these technologies was to be implemented through a series of increasingly-inclusive laboratory demonstrations that would have integrated and demonstrated two systems-of-systems: (a) the autonomous rendezvous and docking of modular spacecraft with deployable structures, robotic assembly, reconfiguration both during assembly and (b) the development and integration of an advanced thermal heat pipe and a high-voltage power delivery system with a representative lightweight high-voltage SPG array. In addition, an integrated simulation testbed would have been developed

  10. The Advanced Technology Development Center (ATDC)

    NASA Technical Reports Server (NTRS)

    Clements, G. R.; Willcoxon, R. (Technical Monitor)

    2001-01-01

    NASA is building the Advanced Technology Development Center (ATDC) to provide a 'national resource' for the research, development, demonstration, testing, and qualification of Spaceport and Range Technologies. The ATDC will be located at Space Launch Complex 20 (SLC-20) at Cape Canaveral Air Force Station (CCAFS) in Florida. SLC-20 currently provides a processing and launch capability for small-scale rockets; this capability will be augmented with additional ATDC facilities to provide a comprehensive and integrated in situ environment. Examples of Spaceport Technologies that will be supported by ATDC infrastructure include densified cryogenic systems, intelligent automated umbilicals, integrated vehicle health management systems, next-generation safety systems, and advanced range systems. The ATDC can be thought of as a prototype spaceport where industry, government, and academia, in partnership, can work together to improve safety of future space initiatives. The ATDC is being deployed in five separate phases. Major ATDC facilities will include a Liquid Oxygen Area; a Liquid Hydrogen Area, a Liquid Nitrogen Area, and a multipurpose Launch Mount; 'Iron Rocket' Test Demonstrator; a Processing Facility with a Checkout and Control System; and Future Infrastructure Developments. Initial ATDC development will be completed in 2006.

  11. Advanced Gas Turbine (AGT) Technology Development Project, ceramic component developments

    NASA Technical Reports Server (NTRS)

    Teneyck, M. O.; Macbeth, J. W.; Sweeting, T. B.

    1987-01-01

    The ceramic component technology development activity conducted by Standard Oil Engineered Materials Company while performing as a principal subcontractor to the Garrett Auxiliary Power Division for the Advanced Gas Turbine (AGT) Technology Development Project (NASA Contract DEN3-167) is summarized. The report covers the period October 1979 through July 1987, and includes information concerning ceramic technology work categorized as common and unique. The former pertains to ceramic development applicable to two parallel AGT projects established by NASA contracts DEN3-168 (AGT100) and DEN3-167 (AGT101), whereas the unique work solely pertains to Garrett directed activity under the latter contract. The AGT101 Technology Development Project is sponsored by DOE and administered by NASA-Lewis. Standard Oil directed its efforts toward the development of ceramic materials in the silicon-carbide family. Various shape forming and fabrication methods, and nondestructive evaluation techniques were explored to produce the static structural components for the ceramic engine. This permitted engine testing to proceed without program slippage.

  12. Ultrashort pulsed laser technology development program

    NASA Astrophysics Data System (ADS)

    Manke, Gerald C.

    2014-10-01

    The Department of Navy has been pursuing a technology development program for advanced, all-fiber, Ultra Short Pulsed Laser (USPL) systems via Small Business Innovative Research (SBIR) programs. Multiple topics have been published to promote and fund research that encompasses every critical component of a standard USPL system and enable the demonstration of mJ/pulse class systems with an all fiber architecture. This presentation will summarize published topics and funded programs.

  13. Gas cooled fuel cell systems technology development

    NASA Technical Reports Server (NTRS)

    Feret, J. M.

    1986-01-01

    The work performed during the Second Logical Unit of Work of a multi-year program designed to develop a phosphoric acid fuel cell (PAFC) for electric utility power plant application is discussed. The Second Logical Unit of Work, which covers the period May 14, 1983 through May 13, 1984, was funded by the U.S. Department of Energy, Office of Fossil Energy, Morgantown Energy Technology Center, and managed by the NASA Lewis Research Center.

  14. Wave Rotor Research and Technology Development

    NASA Technical Reports Server (NTRS)

    Welch, Gerard E.

    1998-01-01

    Wave rotor technology offers the potential to increase the performance of gas turbine engines significantly, within the constraints imposed by current material temperature limits. The wave rotor research at the NASA Lewis Research Center is a three-element effort: 1) Development of design and analysis tools to accurately predict the performance of wave rotor components; 2) Experiments to characterize component performance; 3) System integration studies to evaluate the effect of wave rotor topping on the gas turbine engine system.

  15. Technology development for DOE SNF management

    SciTech Connect

    Hale, D.L.; Einziger, R.E.; Murphy, J.R.

    1995-12-31

    This paper describes the process used to identify technology development needs for the same management of spent nuclear fuel (SNF) in the US Department of Energy (DOE) inventory. Needs were assessed for each of the over 250 fuel types stores at DOE sites around the country for each stage of SNF management--existing storage, transportation, interim storage, and disposal. The needs were then placed into functional groupings to facilitate integration and collaboration among the sites.

  16. Radar Technology Development at NASA/JPL

    NASA Technical Reports Server (NTRS)

    Rosen, Paul A.

    2011-01-01

    Radar at JPL and worldwide is enjoying a period of unprecedented development. JPL's science-driven program focuses on exploiting commercially available components to build new technologies to meet NASA's science goals. Investments in onboard-processing, advanced digital systems, and efficient high-power devices, point to a new generation of high-performance scientific SAR systems in the US. Partnerships are a key strategy for US missions in the coming decade

  17. Recent developments in PET detector technology

    PubMed Central

    Lewellen, Tom K

    2010-01-01

    Positron emission tomography (PET) is a tool for metabolic imaging that has been utilized since the earliest days of nuclear medicine. A key component of such imaging systems is the detector modules—an area of research and development with a long, rich history. Development of detectors for PET has often seen the migration of technologies, originally developed for high energy physics experiments, into prototype PET detectors. Of the many areas explored, some detector designs go on to be incorporated into prototype scanner systems and a few of these may go on to be seen in commercial scanners. There has been a steady, often very diverse development of prototype detectors, and the pace has accelerated with the increased use of PET in clinical studies (currently driven by PET/CT scanners) and the rapid proliferation of pre-clinical PET scanners for academic and commercial research applications. Most of these efforts are focused on scintillator-based detectors, although various alternatives continue to be considered. For example, wire chambers have been investigated many times over the years and more recently various solid-state devices have appeared in PET detector designs for very high spatial resolution applications. But even with scintillators, there have been a wide variety of designs and solutions investigated as developers search for solutions that offer very high spatial resolution, fast timing, high sensitivity and are yet cost effective. In this review, we will explore some of the recent developments in the quest for better PET detector technology. PMID:18695301

  18. Developing Technology Products - A Physicist's Perspective

    NASA Astrophysics Data System (ADS)

    Burka, Michael

    2014-03-01

    There are many physicists working in the industrial sector. We rarely have the word physicist in our job title; we are far more commonly called engineers or scientists. But, we are physicists, and we succeed because our training in physics has given us the habits of mind and the technical skills that one needs to solve complex technical challenges. This talk will explore the transition from physics research to technology product development using examples from my own career, first as a postdoctoral fellow and research scientist on the LIGO project, and then developing products in the spectroscopy, telecommunications, and medical device industries. Approaches to identifying and pursuing opportunities in industry will be discussed.

  19. An overview: Challenges in wind technology development

    SciTech Connect

    Thresher, R.W.; Hock, S.M.

    1991-12-01

    Developing innovative wind turbine components and advanced turbine configurations is a primary focus for wind technology researchers. In their rush to bring these new components and systems to the marketplace, designers and developers should consider the lessons learned in the wind farms over the past 10 years. Experience has shown that a disciplined design approach is required that realistically accounts for the turbulence-induced loads, unsteady stall loading, and fatigue effects. This paper reviews past experiences and compares current modelling capabilities with experimental measurements in order to identify some of the knowledge gaps that challenge designers of advanced components and systems. 7 refs., 11 figs.

  20. An overview: Challenges in wind technology development

    NASA Astrophysics Data System (ADS)

    Thresher, R. W.; Hock, S. M.

    1991-12-01

    Developing innovative wind turbine components and advanced turbine configurations is a primary focus for wind technology researchers. In their rush to bring these new components and systems to the marketplace, designers and developers should consider the lessons learned in the wind farms over the past 10 years. Experience has shown that a disciplined design approach is required that realistically accounts for the turbulence-induced loads, unsteady stall loading, and fatigue effects. This paper reviews past experiences and compares current modeling capabilities with experimental measurements in order to identify some of the knowledge gaps that challenge designers of advanced components and systems.

  1. Medically relevant ElectroNeedle technology development.

    SciTech Connect

    Schmidt, Carrie Frances; Thomas, Michael Loren; McClain, Jaime L.; Harper, Jason C.; Achyuthan, Komandoor E.; Ten Eyck, Gregory A.

    2008-11-01

    ElectroNeedles technology was developed as part of an earlier Grand Challenge effort on Bio-Micro Fuel Cell project. During this earlier work, the fabrication of the ElectroNeedles was accomplished along with proof-of-concept work on several electrochemically active analytes such as glucose, quinone and ferricyanide. Additionally, earlier work demonstrated technology potential in the field of immunosensors by specifically detecting Troponin, a cardiac biomarker. The current work focused upon fabrication process reproducibility of the ElectroNeedles and then using the devices to sensitively detect p-cresol, a biomarker for kidney failure or nephrotoxicity. Valuable lessons were learned regarding fabrication assurance and quality. The detection of p-cresol was accomplished by electrochemistry as well as using fluorescence to benchmark ElectroNeedles performance. Results from these studies will serve as a guide for the future fabrication processes involving ElectroNeedles as well as provide the groundwork necessary to expand technology applications. One paper has been accepted for publication acknowledging LDRD funding (K. E. Achyuthan et al, Comb. Chem. & HTS, 2008). We are exploring the scope for a second paper describing the applications potential of this technology.

  2. Adapting communication technology for rural development.

    PubMed

    Fraser, C

    1983-01-01

    The experience in most Third World countries is that communication technology is not being applied to rural development. Originally, communications programs were advanced to meet the need for better participation in development programs by rural people and to facilitate the transfer of technical know-how. However, there has been so systematic use of this approach. Rural broadcasting rarely receives more than a fraction of total air time, and programs that do exist are uninspiring and ineffective. There is a shortage of portable recording equipment and transport, meaning that very little field recording can be done. Totally unexplored has been the potential of portable closed-circuit video for use in rural areas. The mere availability of cheap and appropriate communication technology such as videotaping does not ensure its use for rural development. The real obstacles are linked to rural development policies and politics. Within most governments, rural and agricultural development are not priorities in terms of budgetary and staff allocations. Morever, within that sector, communication is viewed as a peripheral activity. Governments have found it easier in many cases to issue 1-way commands than to communicate and plan with the rural population. A final factor of great importance is training people to use the tools of communication.

  3. Tracing Impacts of Science and Technology Development

    NASA Astrophysics Data System (ADS)

    Powell, Jeanne

    2003-03-01

    ATP's Mission and Operations. The ATP partners with industry to accelerate the development of innovative technologies for broad national economic benefit. The program's focus is on co-funding collaborative, multi-disciplinary technologies and enabling technology platforms that appear likely to be commercialized, with private sector funding, once the high technical risks are reduced. Industry-led projects are selected for funding in rigorous competitions on the basis of technical and economic merit. Since 1990, ATP has co-funded 642 projects, with 1,329 participants and another 1,300 subcontractors. Measuring to Mission: Overview of ATP's Evaluation Program. ATP's multi-component evaluation strategy provides measures of progress and performance matched to the stage of project evolution; i.e., for the short-term, from the time of project selection and over the course of the R for the mid-term, as commercial applications are pursued, early products reach the market, and dissemination of knowledge created in the R projects occurs; and for the longer-term, as more fully-developed technologies diffuse across multiple products and industries. The approach is applicable to all public S programs and adaptable to private or university projects ranging from basic research to applied industrial R. Examples of Results. ATP's composite performance rating system assesses ATP's completed projects against multi-faceted performance criteria of Knowledge Creation and Dissemination and Commercialization Progress 2-3 years after the end of ATP-funded R. It generates scores ranging from zero to four stars. Results for ATP's first 50 completed projects show that 16are in the bottom group of zero or one stars. 60the middle group. It is understood that not all ATP projects will be successful given the program's emphasis on funding high-risk technology development that the private sector is unwilling and unable to fund alone. Different technologies have different timelines for

  4. Fission Surface Power Technology Development Update

    NASA Technical Reports Server (NTRS)

    Palac, Donald T.; Mason, Lee S.; Houts, Michael G.; Harlow, Scott

    2011-01-01

    Power is a critical consideration in planning exploration of the surfaces of the Moon, Mars, and places beyond. Nuclear power is an important option, especially for locations in the solar system where sunlight is limited or environmental conditions are challenging (e.g., extreme cold, dust storms). NASA and the Department of Energy are maintaining the option for fission surface power for the Moon and Mars by developing and demonstrating technology for a fission surface power system. The Fission Surface Power Systems project has focused on subscale component and subsystem demonstrations to address the feasibility of a low-risk, low-cost approach to space nuclear power for surface missions. Laboratory demonstrations of the liquid metal pump, reactor control drum drive, power conversion, heat rejection, and power management and distribution technologies have validated that the fundamental characteristics and performance of these components and subsystems are consistent with a Fission Surface Power preliminary reference concept. In addition, subscale versions of a non-nuclear reactor simulator, using electric resistance heating in place of the reactor fuel, have been built and operated with liquid metal sodium-potassium and helium/xenon gas heat transfer loops, demonstrating the viability of establishing system-level performance and characteristics of fission surface power technologies without requiring a nuclear reactor. While some component and subsystem testing will continue through 2011 and beyond, the results to date provide sufficient confidence to proceed with system level technology readiness demonstration. To demonstrate the system level readiness of fission surface power in an operationally relevant environment (the primary goal of the Fission Surface Power Systems project), a full scale, 1/4 power Technology Demonstration Unit (TDU) is under development. The TDU will consist of a non-nuclear reactor simulator, a sodium-potassium heat transfer loop, a power

  5. NASA Solar Sail Propulsion Technology Development

    NASA Technical Reports Server (NTRS)

    Johnson, Les; Montgomery, Edward E.; Young, Roy; Adams, Charles

    2007-01-01

    NASA's In-Space Propulsion Technology Program has developed the first generation of solar sail propulsion systems sufficient to accomplish inner solar system science and exploration missions. These first generation solar sails, when operational, will range in size from 40 meters to well over 100 meters in diameter and have an areal density of less than 13 grams per square meter. A rigorous, multi-year technology development effort culminated in 2005 with the testing of two different 20-m solar sail systems under thermal vacuum conditions. The first system, developed by ATK Space Systems of Goleta, California, uses rigid booms to deploy and stabilize the sail. In the second approach, L'Garde, Inc. of Tustin, California uses inflatable booms that rigidize in the coldness of space to accomplish sail deployment. This effort provided a number of significant insights into the optimal design and expected performance of solar sails as well as an understanding of the methods and costs of building and using them. In a separate effort, solar sail orbital analysis tools for mission design were developed and tested. Laboratory simulations of the effects of long-term space radiation exposure were also conducted on two candidate solar sail materials. Detailed radiation and charging environments were defined for mission trajectories outside the protection of the earth's magnetosphere, in the solar wind environment. These were used in other analytical tools to prove the adequacy of sail design features for accommodating the harsh space environment. Preceding and in conjunction with these technology efforts, NASA sponsored several mission application studies for solar sails. Potential missions include those that would be flown in the near term to study the sun and be used in space weather prediction to one that would use an evolved sail capability to support humanity's first mission into nearby interstellar space. This paper will describe the status of solar sail propulsion within

  6. Technology developments for a compound cycle engine

    NASA Technical Reports Server (NTRS)

    Bobula, George A.; Wintucky, William T.; Castor, J. G.

    1988-01-01

    The Compound Cycle Engine (CCE) is a highly turbocharged, power compounded power plant which combines the light weight pressure rise capability of a gas turbine with the high efficiency of a diesel. When optimized for a rotorcraft, the CCE will reduce fuel burned for a typical 2 hour (plus 30 min reserve) mission by 30 to 40 percent when compared to a conventional advanced technology gas turbine. The CCE can provide a 50 percent increase in range-payload product on this mission. Results of recent activities in a program to establish the technology base for a CCE are presented. The objective of this program is to research and develop those critical technologies which are necessary for the demonstration of a multicylinder diesel core in the early 1990s. A major accomplishment was the initial screening and identification of a lubricant which has potential for meeting the material wear rate limits of the application. An in-situ wear measurement system also was developed to provide accurate, readily obtainable, real time measurements of ring and liner wear. Wear data, from early single cylinder engine tests, are presented to show correlation of the in-situ measurements and the system's utility in determining parametric wear trends. A plan to demonstrate a compound cycle engine by the mid 1990s is included.

  7. Small Hydropower Research and Development Technology Project

    SciTech Connect

    Blackmore, Mo

    2013-12-06

    The objective of this work was to investigate, develop, and validate the next generation of small hydroturbine generator designs that maximize the energy transfer from flowing water to electrical power generation. What resulted from this effort was the design of a new technology hydroturbine that Near Space Systems (NSS) has named the Star*Stream© Hydroturbine. Using a design that eliminates nearly all of the shortfalls of conventional hydroturbines, the Star*Stream© Hydroturbine employs a new mechanical-to-electrical energy transfer hydro design that operates without lubrication of any kind, and does not introduce foreign chemicals or particulate matter from oil or drive shaft seal degradation into the hydro ecology. In its unique configuration, the Star*Stream© Hydroturbine is nearly environmentally inert, without the negative aspects caused by interrupting the ecological continuity, i.e., disruptions to sedimentation, water quality, habitat changes, human displacement, fish migration, etc., - while it ensures dramatically reduced timeframes to project completion. While a remarkable reduction in LCOE resulting from application of the Star*Stream© Hydroturbine technology has been the core achievement of the this effort, there have been numerous technological breakthroughs from the development effort.

  8. Environmental technology development through industry partnership

    SciTech Connect

    Sebastion, R.L.

    1995-12-31

    The Coherent Laser Vision System (CLVS) is being developed to provide precision real-time 3D world views to support site characterization and robotic operations and during facilities Decontamination and Decommissioning. Autonomous or semiautonomous robotic operations requires an accurate, up-to-date 3D world view. Existing technologies for real-time 3D imaging, such as AM laser radar, have limited accuracy at significant ranges and have variability in range estimates caused by lighting or surface shading. Recent advances in fiber optic component technology and digital processing components have enabled the development of a new 3D vision system based upon a fiber optic FMCW coherent laser radar. The approach includes a compact scanner with no-moving parts capable of randomly addressing all pixels. The system maintains the immunity to lighting and surface shading conditions which is characteristic to coherent laser radar. The random pixel addressability allows concentration of scanning and processing on the active areas of a scene, as is done by the human eye-brain system. The precision measurement capability of the coherent laser radar (CLR) technology has already been demonstrated in the form of the CLR 3D Mapper, of which several copies have been delivered or are under order. The CLVS system, in contrast to the CLR 3D Mapper, will have substantially greater imaging speed with a compact no-moving parts scanner, more suitable for real-time robotic operations.

  9. Hydraulic hammer drilling technology: Developments and capabilities

    SciTech Connect

    Melamed, Y.; Kiselev, A.; Gelfgat, M.; Dreesen, D.; Blacic, J.

    1996-12-31

    Percussion drilling technology was considered many years ago as one of the best approaches for hard rock drilling. Unfortunately the efficiency of most hydraulic hammer (HH) designs was very low (8% maximum), so they were successfully used in shallow boreholes only. Thirty years of research and field drilling experience with HH application in Former Soviet Union (FSU) countries led to the development of a new generation of HH designs with a proven efficiency of 40%. That advance achieved good operational results in hard rock at depths up to 2,000 m and more. The most recent research has shown that there are opportunities to increase HH efficiency up to 70%. This paper presents HH basic design principles and operational features. The advantages of HH technology for coiled-tubing drilling is shown on the basis of test results recently conducted in the US.

  10. Terrestrial Planet Finder: Technology Development Plans

    NASA Technical Reports Server (NTRS)

    Lindensmith, Chris

    2004-01-01

    One of humanity's oldest questions is whether life exists elsewhere in the universe. The Terrestrial Planet Finder (TPF) mission will survey stars in our stellar neighborhood to search for planets and perform spectroscopic measurements to identify potential biomarkers in their atmospheres. In response to the recently published President's Plan for Space Exploration, TPF has plans to launch a visible-light coronagraph in 2014, and a separated-spacecraft infrared interferometer in 2016. Substantial funding has been committed to the development of the key technologies that are required to meet these goals for launch in the next decade. Efforts underway through industry and university contracts and at JPL include a number of system and subsystem testbeds, as well as components and numerical modeling capabilities. The science, technology, and design efforts are closely coupled to ensure that requirements and capabilities will be consistent and meet the science goals.

  11. Aluminate solution decomposition new technology development

    SciTech Connect

    Abramov, V.Ya.; Stelmakova, G.D.

    1996-10-01

    Scientific Technical Centre Reactor together with SC Aluminy carried out the number of investigations in the field of aluminum solution decomposition new technology development. It was based on large prime ratio on one hand, and liquid-solid countercurrent flow movement on the other hand. Practically the suggested technology was considered to be the result of unstationary, mass-transfer theory, which had been checked up at 100 m3 plot scale plant. Hydrate washing was accomplished at the first stage under the condition of countercurrent flow and less than 1 m3 water discharge. The experiments of 3.2--3.3 caustic module aluminate solution decomposition were carried out at the second stage. While full reactor 20 hour regime operation the caustic module increased till 4.1. Usually it accounts 3.7 under the analogous conditions and time.

  12. Fission Surface Power Technology Development Status

    NASA Technical Reports Server (NTRS)

    Palac, Donald T.; Mason, Lee S.; Harlow, Scott

    2009-01-01

    With the potential future deployment of a lunar outpost there is expected to be a clear need for a high-power, lunar surface power source to support lunar surface operations independent of the day-night cycle, and Fission Surface Power (FSP) is a very effective solution for power levels above a couple 10 s of kWe. FSP is similarly enabling for the poorly illuminated surface of Mars. The power levels/requirements for a lunar outpost option are currently being studied, but it is known that cost is clearly a predominant concern to decision makers. This paper describes the plans of NASA and the DOE to execute an affordable fission surface power system technology development project to demonstrate sufficient technology readiness of an affordable FSP system so viable and cost-effective FSP system options will be available when high power lunar surface system choices are expected to be made in the early 2010s.

  13. Photonics technology development for optical fuzing.

    SciTech Connect

    Liu, J.J.; Geib, Kent Martin; von der Lippe, C.M.; Peake, Gregory Merwin; Serkland, Darwin Keith; Keeler, Gordon Arthur; Mar, Alan

    2005-07-01

    This paper describes the photonic component development, which exploits pioneering work and unique expertise at Sandia National Laboratories, ARDEC and the Army Research Laboratory by combining key optoelectronic technologies to design and demonstrate components for this fuzing application. The technologies under investigation for the optical fuze design covered in this paper are vertical cavity surface emitting lasers (VECSELs), integrated resonant cavity photodetectors (RCPD), and diffractive micro-optics. The culmination of this work will be low cost, robust, fully integrated, g-hardened components designed suitable for proximity fuzing applications. The use of advanced photonic components will enable replacement of costly assemblies that employ discrete lasers, photodetectors, and bulk optics. The integrated devices will be mass produced and impart huge savings for a variety of Army applications.

  14. Development of Interconnect Technologies for Particle Detectors

    SciTech Connect

    Tripathi, Mani

    2015-01-29

    This final report covers the three years of this grant, for the funding period 9/1/2010 - 8/31/2013. The project consisted of generic detector R&D work at UC Davis, with an emphasis on developing interconnect technologies for applications in HEP. Much of the work is done at our Facility for Interconnect Technologies (FIT) at UC Davis. FIT was established using ARRA funds, with further studies supported by this grant. Besides generic R&D work at UC Davis, FIT is engaged in providing bump bonding help to several DOE supported detector R&D efforts. Some of the developmental work was also supported by funding from other sources: continuing CMS project funds and the Linear Collider R&D funds. The latter program is now terminated. The three year program saw a good deal of progress on several fronts, which are reported here.

  15. Overview of NASA GRC Stirling Technology Development

    NASA Technical Reports Server (NTRS)

    Schreiber, Jeffrey; Thieme, Lanny

    2003-01-01

    The Stirling Radioisotope Generator (SRG) is currently being developed by Lockheed Martin Astronautics (LMA) under contract to the Depar1ment of Energy (DOE). The generator will be a high efficiency electric power source for NASA Space Science missions with the capability to operate in the vacuum of deep space or in an atmosphere such as on the surface of Mars. High system efficiency is obtained through the use of free-piston Stirling power conversion technology. Power output of the generator will be greater than 100 watts at the beginning of life with the decline in power being largely due to the decay of the plutonium heat source. In suppOl1 of the DOE SRG project, the NASA Glenn Research Center (GRC) has established a near-term technology effort to provide some of the critical data to ensure a successful transition to flight for what will be the first dynamic power system used in space. Initially, a limited number of technical areas were selected for the GRC effort, however this is now being expanded to more thoroughly cover a range of technical issues. The tasks include in-house testing of Stirling convertors and controllers, materials evaluation and heater head life assessment, structural dynamics, electromagnetic interference, organics evaluation, and reliability analysis. Most of these high-level tasks have several subtasks within. There is also an advanced technology effort that is complementary near-term technology effort. Many of the tests make use of the 55-We Technology Demonstration Convel10r (TDC). There have been multiple controller tests to support the LMA flight controller design effort. Preparation is continuing for a thermal/vacuum system demonstration. A pair of flight prototype TDC's have recently been placed on an extended test with unattended, continuous operation. Heater head life assessment efforts continue, with the material data being refined and the analysis moving toward the system perspective. Long-term magnet aging tests are

  16. Engineering research, development and technology FY99

    SciTech Connect

    Langland, R T

    2000-02-01

    The growth of computer power and connectivity, together with advances in wireless sensing and communication technologies, is transforming the field of complex distributed systems. The ability to deploy large numbers of sensors with a rapid, broadband communication system will enable high-fidelity, near real-time monitoring of complex systems. These technological developments will provide unprecedented insight into the actual performance of engineered and natural environment systems, enable the evolution of many new types of engineered systems for monitoring and detection, and enhance our ability to perform improved and validated large-scale simulations of complex systems. One of the challenges facing engineering is to develop methodologies to exploit the emerging information technologies. Particularly important will be the ability to assimilate measured data into the simulation process in a way which is much more sophisticated than current, primarily ad hoc procedures. The reports contained in this section on the Center for Complex Distributed Systems describe activities related to the integrated engineering of large complex systems. The first three papers describe recent developments for each link of the integrated engineering process for large structural systems. These include (1) the development of model-based signal processing algorithms which will formalize the process of coupling measurements and simulation and provide a rigorous methodology for validation and update of computational models; (2) collaborative efforts with faculty at the University of California at Berkeley on the development of massive simulation models for the earth and large bridge structures; and (3) the development of wireless data acquisition systems which provide a practical means of monitoring large systems like the National Ignition Facility (NIF) optical support structures. These successful developments are coming to a confluence in the next year with applications to NIF structural

  17. Overview of NASA GRC Stirling Technology Development

    NASA Technical Reports Server (NTRS)

    Schreiber, Jeffrey G.; Thieme, Lanny G.

    2004-01-01

    The Stirling Radioisotope Generator (SRG) is currently being developed by Lockheed Martin Astronautics (LMA) under contract to the Department of Energy (DOE). The generator will be a high efficiency electric power source for NASA Space Science missions with the ability to operate in vacuum or in an atmosphere such as on Mars. High efficiency is obtained through the use of free-piston Stirling power conversion. Power output will be greater than 100 watts at the beginning of life with the decline in power largely due to the decay of the plutonium heat source. In support of the DOE SRG project, the NASA Glenn Research Center (GRC) has established a technology effort to provide data to ensure a successful transition to flight for what will be the first dynamic power system in space. Initially, a limited number of areas were selected for the effort, however this is now being expanded to more thoroughly cover key technical issues. There is also an advanced technology effort that is complementary to the near-term technology effort. Many of the tests use the 55-We Technology Demonstration Convertor (TDC). There have been multiple controller tests to support the LMA flight controller design effort. Preparation is continuing for a thermal/vacuum system demonstration. A pair of flight prototype TDC s have been placed on continuous operation. Heater head life assessment continues, with the material data being refined and the analysis moving toward the system perspective. Magnet aging tests continue to characterize any possible aging in the strength or demagnetization resistance of the magnets in the linear alternator. A reliability effort has been initiated to help guide the development activities with focus on the key components and subsystems. This paper will provide an overview of some of the GRC technical efforts, including the status, and a description of future efforts.

  18. Small Orbital Stereo Tracking Camera Technology Development

    NASA Technical Reports Server (NTRS)

    Bryan, Tom; MacLeod, Todd; Gagliano, Larry

    2016-01-01

    On-Orbit Small Debris Tracking and Characterization is a technical gap in the current National Space Situational Awareness necessary to safeguard orbital assets and crew. This poses a major risk of MOD damage to ISS and Exploration vehicles. In 2015 this technology was added to NASA's Office of Chief Technologist roadmap. For missions flying in or assembled in or staging from LEO, the physical threat to vehicle and crew is needed in order to properly design the proper level of MOD impact shielding and proper mission design restrictions. Need to verify debris flux and size population versus ground RADAR tracking. Use of ISS for In-Situ Orbital Debris Tracking development provides attitude, power, data and orbital access without a dedicated spacecraft or restricted operations on-board a host vehicle as a secondary payload. Sensor Applicable to in-situ measuring orbital debris in flux and population in other orbits or on other vehicles. Could enhance safety on and around ISS. Some technologies extensible to monitoring of extraterrestrial debris as well To help accomplish this, new technologies must be developed quickly. The Small Orbital Stereo Tracking Camera is one such up and coming technology. It consists of flying a pair of intensified megapixel telephoto cameras to evaluate Orbital Debris (OD) monitoring in proximity of International Space Station. It will demonstrate on-orbit optical tracking (in situ) of various sized objects versus ground RADAR tracking and small OD models. The cameras are based on Flight Proven Advanced Video Guidance Sensor pixel to spot algorithms (Orbital Express) and military targeting cameras. And by using twin cameras we can provide Stereo images for ranging & mission redundancy. When pointed into the orbital velocity vector (RAM), objects approaching or near the stereo camera set can be differentiated from the stars moving upward in background.

  19. Small Orbital Stereo Tracking Camera Technology Development

    NASA Technical Reports Server (NTRS)

    Bryan, Tom; Macleod, Todd; Gagliano, Larry

    2015-01-01

    On-Orbit Small Debris Tracking and Characterization is a technical gap in the current National Space Situational Awareness necessary to safeguard orbital assets and crew. This poses a major risk of MOD damage to ISS and Exploration vehicles. In 2015 this technology was added to NASA's Office of Chief Technologist roadmap. For missions flying in or assembled in or staging from LEO, the physical threat to vehicle and crew is needed in order to properly design the proper level of MOD impact shielding and proper mission design restrictions. Need to verify debris flux and size population versus ground RADAR tracking. Use of ISS for In-Situ Orbital Debris Tracking development provides attitude, power, data and orbital access without a dedicated spacecraft or restricted operations on-board a host vehicle as a secondary payload. Sensor Applicable to in-situ measuring orbital debris in flux and population in other orbits or on other vehicles. Could enhance safety on and around ISS. Some technologies extensible to monitoring of extraterrestrial debris as well to help accomplish this, new technologies must be developed quickly. The Small Orbital Stereo Tracking Camera is one such up and coming technology. It consists of flying a pair of intensified megapixel telephoto cameras to evaluate Orbital Debris (OD) monitoring in proximity of International Space Station. It will demonstrate on-orbit optical tracking (in situ) of various sized objects versus ground RADAR tracking and small OD models. The cameras are based on Flight Proven Advanced Video Guidance Sensor pixel to spot algorithms (Orbital Express) and military targeting cameras. And by using twin cameras we can provide Stereo images for ranging & mission redundancy. When pointed into the orbital velocity vector (RAM), objects approaching or near the stereo camera set can be differentiated from the stars moving upward in background.

  20. Small Orbital Stereo Tracking Camera Technology Development

    NASA Astrophysics Data System (ADS)

    Gagliano, L.; Bryan, T.; MacLeod, T.

    On-Orbit Small Debris Tracking and Characterization is a technical gap in the current National Space Situational Awareness necessary to safeguard orbital assets and crew. This poses a major risk of MOD damage to ISS and Exploration vehicles. In 2015 this technology was added to NASAs Office of Chief Technologist roadmap. For missions flying in or assembled in or staging from LEO, the physical threat to vehicle and crew is needed in order to properly design the proper level of MOD impact shielding and proper mission design restrictions. Need to verify debris flux and size population versus ground RADAR tracking. Use of ISS for In-Situ Orbital Debris Tracking development provides attitude, power, data and orbital access without a dedicated spacecraft or restricted operations on-board a host vehicle as a secondary payload. Sensor Applicable to in-situ measuring orbital debris in flux and population in other orbits or on other vehicles. Could enhance safety on and around ISS. Some technologies extensible to monitoring of extraterrestrial debris as well To help accomplish this, new technologies must be developed quickly. The Small Orbital Stereo Tracking Camera is one such up and coming technology. It consists of flying a pair of intensified megapixel telephoto cameras to evaluate Orbital Debris (OD) monitoring in proximity of International Space Station. It will demonstrate on-orbit optical tracking (in situ) of various sized objects versus ground RADAR tracking and small OD models. The cameras are based on Flight Proven Advanced Video Guidance Sensor pixel to spot algorithms (Orbital Express) and military targeting cameras. And by using twin cameras we can provide Stereo images for ranging & mission redundancy. When pointed into the orbital velocity vector (RAM), objects approaching or near the stereo camera set can be differentiated from the stars moving upward in background.

  1. Stirling technology development at NASA GRC

    NASA Astrophysics Data System (ADS)

    Thieme, Lanny G.; Schreiber, Jeffrey G.; Mason, Lee S.

    2002-01-01

    The Department of Energy, Stirling Technology Company (STC), and NASA Glenn Research Center (GRC) are developing a free-piston Stirling convertor for a high-efficiency Stirling Radioisotope Generator (SRG) for NASA Space Science missions. The SRG is being developed for multimission use, including providing electric power for unmanned Mars rovers and deep space missions. NASA GRC is conducting an in-house technology project to assist in developing the convertor for space qualification and mission implementation. Recent testing of 55-We Technology Demonstration Convertors (TDC's) built by STC includes mapping of a second pair of TDC's, single TDC testing, and TDC electromagnetic interference and electromagnetic compatibility characterization on a non-magnetic test stand. Launch environment tests of a single TDC without its pressure vessel to better understand the convertor internal structural dynamics and of dual-opposed TDC's with several engineering mounting structures with different natural frequencies have recently been completed. A preliminary life assessment has been completed for the TDC heater head, and creep testing of the IN718 material to be used for the flight convertors is underway. Long-term magnet aging tests are continuing to characterize any potential aging in the strength or demagnetization resistance of the magnets used in the linear alternator (LA). Evaluations are now beginning on key organic materials used in the LA and piston/rod surface coatings. GRC is also conducting finite element analyses for the LA, in part to look at the demagnetization margin on the permanent magnets. The world's first known integrated test of a dynamic power system with electric propulsion was achieved at GRC when a Hall-effect thruster was successfully operated with a free-piston Stirling power source. Cleveland State University is developing a multi-dimensional Stirling computational fluid dynamics code to significantly improve Stirling loss predictions and assist in

  2. Stirling Technology Development at NASA GRC. Revised

    NASA Technical Reports Server (NTRS)

    Thieme, Lanny G.; Schreiber, Jeffrey G.; Mason, Lee S.

    2002-01-01

    The Department of Energy, Stirling Technology Company (STC), and NASA Glenn Research Center (NASA Glenn) are developing a free-piston Stirling convertor for a high-efficiency Stirling Radioisotope Generator (SRG) for NASA Space Science missions. The SRG is being developed for multimission use, including providing electric power for unmanned Mars rovers and deep space missions. NASA Glenn is conducting an in-house technology project to assist in developing the convertor for space qualification and mission implementation. Recent testing, of 55-We Technology Demonstration Convertors (TDC's) built by STC includes mapping, of a second pair of TDC's, single TDC testing, and TDC electromagnetic interference and electromagnetic compatibility characterization on a nonmagnetic test stand. Launch environment tests of a single TDC without its pressure vessel to better understand the convertor internal structural dynamics and of dual-opposed TDC's with several engineering mounting structures with different natural frequencies have recently been completed. A preliminary life assessment has been completed for the TDC heater head, and creep testing of the IN718 material to be used for the flight convertors is underway. Long-term magnet aging tests are continuing to characterize any potential aging in the strength or demagnetization resistance of the magnets used in the linear alternator (LA). Evaluations are now beginning on key organic materials used in the LA and piston/rod surface coatings. NASA Glenn is also conducting finite element analyses for the LA, in part to look at the demagnetization margin on the permanent magnets. The world's first known integrated test of a dynamic power system with electric propulsion was achieved at NASA Glenn when a Hall-effect thruster was successfully operated with a free-piston Stirling power source. Cleveland State University is developing a multidimensional Stirling computational fluid dynamics code to significantly improve Stirling loss

  3. Stirling Technology Development at NASA GRC

    NASA Technical Reports Server (NTRS)

    Thieme, Lanny G.; Schreiber, Jeffrey G.; Mason, Lee S.

    2001-01-01

    The Department of Energy, Stirling Technology Company (STC), and NASA Glenn Research Center (NASA Glenn) are developing a free-piston Stirling convertor for a high efficiency Stirling Radioisotope Generator (SRG) for NASA Space Science missions. The SRG is being developed for multimission use, including providing electric power for unmanned Mars rovers and deep space missions. NASA Glenn is conducting an in-house technology project to assist in developing the convertor for space qualification and mission implementation. Recent testing of 55-We Technology Demonstration Convertors (TDCs) built by STC includes mapping of a second pair of TDCs, single TDC testing, and TDC electromagnetic interference and electromagnetic compatibility characterization on a nonmagnetic test stand. Launch environment tests of a single TDC without its pressure vessel to better understand the convertor internal structural dynamics and of dual-opposed TDCs with several engineering mounting structures with different natural frequencies have recently been completed. A preliminary life assessment has been completed for the TDC heater head, and creep testing of the IN718 material to be used for the flight convertors is underway. Long-term magnet aging tests are continuing to characterize any potential aging in the strength or demagnetization resistance of the magnets used in the linear alternator (LA). Evaluations are now beginning on key organic materials used in the LA and piston/rod surface coatings. NASA Glenn is also conducting finite element analyses for the LA, in part to look at the demagnetization margin on the permanent magnets. The world's first known integrated test of a dynamic power system with electric propulsion was achieved at NASA Glenn when a Hall-effect thruster was successfully operated with a free-piston Stirling power source. Cleveland State University is developing a multidimensional Stirling computational fluid dynamics code to significantly improve Stirling loss

  4. Advanced Technology Development for Stirling Convertors

    NASA Astrophysics Data System (ADS)

    Thieme, Lanny G.; Schreiber, Jeffrey G.

    2004-02-01

    A high-efficiency Stirling Radioisotope Generator (SRG) for use on potential NASA Space Science missions is being developed by the Department of Energy, Lockheed Martin, Stirling Technology Company, and NASA Glenn Research Center (GRC). These missions may include providing spacecraft onboard electric power for deep space missions or power for unmanned Mars rovers. GRC is also developing advanced technology for Stirling convertors, aimed at substantially improving the specific power and efficiency of the convertor and the overall power system. Performance and mass improvement goals have been established for second- and third-generation Stirling radioisotope power systems. Multiple efforts are underway to achieve these goals, both in-house at GRC and under various grants and contracts. The status and results to date for these efforts will be discussed in this paper. Cleveland State University (CSU) is developing a multi-dimensional Stirling computational fluid dynamics code, capable of modeling complete convertors. A 2-D version of the code is now operational, and validation efforts at both CSU and the University of Minnesota are complementing the code development. A screening of advanced superalloy, refractory metal alloy, and ceramic materials has been completed, and materials have been selected for creep and joining characterization as part of developing a high-temperature heater head. A breadboard characterization is underway for an advanced controller using power electronics for active power factor control with a goal of eliminating the heavy tuning capacitors that are typically needed to achieve near unity power factors. Key Stirling developments just initiated under recent NRA (NASA Research Announcement) awards will also be discussed. These include a lightweight convertor to be developed by Sunpower Inc. and an advanced microfabricated regenerator to be done by CSU.

  5. Advanced Technology Development for Stirling Convertors

    NASA Technical Reports Server (NTRS)

    Thieme, Lanny G.; Schreiber, Jeffrey G.

    2004-01-01

    A high-efficiency Stirling Radioisotope Generator (SRG) for use on potential NASA Space Science missions is being developed by the Department of Energy, Lockheed Martin, Stirling Technology Company, and NASA Glenn Research Center (GRC). These missions may include providing spacecraft onboard electric power for deep space missions or power for unmanned Mars rovers. GRC is also developing advanced technology for Stirling convertors, aimed at substantially improving the specific power and efficiency of the convertor and the overall power system. Performance and mass improvement goals have been established for second- and thirdgeneration Stirling radioisotope power systems. Multiple efforts are underway to achieve these goals, both in-house at GRC and under various grants and contracts. The status and results to date for these efforts will be discussed in this paper. Cleveland State University (CSU) is developing a multi-dimensional Stirling computational fluid dynamics code, capable of modeling complete convertors. A 2-D version of the code is now operational, and validation efforts at both CSU and the University of Minnesota are complementing the code development. A screening of advanced superalloy, refractory metal alloy, and ceramic materials has been completed, and materials have been selected for creep and joining characterization as part of developing a high-temperature heater head. A breadboard characterization is underway for an advanced controller using power electronics for active power factor control with a goal of eliminating the heavy tuning capacitors that are typically needed to achieve near unity power factors. Key Stirling developments just initiated under recent NRA (NASA Research Announcement) awards will also be discussed. These include a lightweight convertor to be developed by Sunpower Inc. and an advanced microfabricated regenerator to be done by CSU.

  6. CROSSCUTTING TECHNOLOGY DEVELOPMENT AT THE CENTER FOR ADVANCED SEPARATION TECHNOLOGIES

    SciTech Connect

    Hugh W. Rimmer

    2003-11-15

    The U.S. is the largest producer of mining products in the world. In 1999, U.S. mining operations produced $66.7 billion worth of raw materials that contributed a total of $533 billion to the nation's wealth. Despite these contributions, the mining industry has not been well supported with research and development funds as compared to mining industries in other countries. To overcome this problem, the Center for Advanced Separation Technologies (CAST) was established to develop technologies that can be used by the U.S. mining industry to create new products, reduce production costs, and meet environmental regulations. Much of the research to be conducted with Cooperative Agreement funds will be longer-term, high-risk, basic research and will be carried out in five broad areas: (a) Solid-solid separation (b) Solid-liquid separation (c) Chemical/Biological Extraction (d) Modeling and Control, and (e) Environmental Control. Distribution of funds is being handled via competitive solicitation of research proposals through Site Coordinators at the seven member universities. The first of these solicitations, referred to as the CAST II-Round 1 RFP, was issued on October 28, 2002. Thirty-eight proposals were received by the December 10, 2002 deadline for this RFP-eleven (11) Solid-Solid Separation, seven (7) Solid-Liquid Separation, ten (10) Chemical/Biological Extraction, six (6) Modeling & Control and four (4) Environmental Control. These were first reviewed and ranked by a group of technical reviewers (selected primarily from industry). Based on these reviews, and an assessment of overall program requirements, the CAST Technical Committee made an initial selection/ranking of proposals and forwarded these to the DOE/NETL Project Officer for final review and approval. This process took some 7 months to complete but 17 projects (one joint) were in place at the constituent universities (three at Virginia Tech, two at West Virginia University, three at University of Kentucky

  7. Status of SOFCo SOFC technology development

    SciTech Connect

    Privette, R.; Perna, M.A.; Kneidel, K.

    1996-12-31

    SOFCo, a Babcock & Wilcox/Ceramatec Research & Development Limited Partnership, is a collaborative research and development venture to develop technologies related to planar, solid-oxide fuel cells (SOFCs). SOFCo has successfully demonstrated a kW-class, solid-oxide fuel cell module operating on pipeline natural gas. The SOFC system design integrates the air preheater and the fuel processor with the fuel cell stacks into a compact test unit; this is the platform for multi-kW modules. The cells, made of tape-cast zirconia electrolyte and conventional electrode materials, exhibit excel lent stability in single-cell tests approaching 40,000 hours of operation. Stack tests using 10-cm and 15-cm cells with ceramic interconnects also show good performance and stability in tests for many thousands of hours.

  8. Developments in precision optical grinding technology

    NASA Astrophysics Data System (ADS)

    Fess, Edward; Bechtold, Mike; Wolfs, Frank; Bechtold, Rob

    2013-09-01

    Optical systems that utilize complex optical geometries such as aspheres and freeform optics require precise control through the manufacturing process. As the preparatory stage for polishing, this is especially true for grinding. The quality of the grinding process can greatly influence the polishing process and the resultant finished product. OptiPro has performed extensive development work in evaluating components of a precision grinding machine to determine how they influence the overall manufacturing process. For example, spindle technology has a strong effect on how a grinding machine will perform. Through metrology techniques that measure the vibration characteristics of a machine and measurements of grinding forces with a dynamometer, OptiPro has also developed a detailed knowledge of how the machine can influence the grinding process. One of the outcomes of this work has led OptiPro to develop an ultrasonic head for their grinding platform to aid in reducing grinding forces. Initial results show a reduction in force by ~50%.

  9. 78 FR 17418 - Rural Health Information Technology Network Development Grant

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-03-21

    ... HUMAN SERVICES Health Resources and Services Administration Rural Health Information Technology Network... award under the Rural Health Information Technology Network Development Grant (RHITND) to Grace... relinquishing its fiduciary responsibilities for the Rural Health Information Technology Network...

  10. Development of Advanced Ceramic Manufacturing Technology

    SciTech Connect

    Pujari, V.K.

    2001-04-05

    Advanced structural ceramics are enabling materials for new transportation engine systems that have the potential for significantly reducing energy consumption and pollution in automobiles and heavy vehicles. Ceramic component reliability and performance have been demonstrated in previous U.S. DOE initiatives, but high manufacturing cost was recognized as a major barrier to commercialization. Norton Advanced Ceramics (NAC), a division of Saint-Gobain Industrial Ceramics, Inc. (SGIC), was selected to perform a major Advanced Ceramics Manufacturing Technology (ACMT) Program. The overall objectives of NAC's program were to design, develop, and demonstrate advanced manufacturing technology for the production of ceramic exhaust valves for diesel engines. The specific objectives were (1) to reduce the manufacturing cost by an order of magnitude, (2) to develop and demonstrate process capability and reproducibility, and (3) to validate ceramic valve performance, durability, and reliability. The program was divided into four major tasks: Component Design and Specification, Component Manufacturing Technology Development, Inspection and Testing, and Process Demonstration. A high-power diesel engine valve for the DDC Series 149 engine was chosen as the demonstration part for this program. This was determined to be an ideal component type to demonstrate cost-effective process enhancements, the beneficial impact of advanced ceramics on transportation systems, and near-term commercialization potential. The baseline valve material was NAC's NT451 SiAION. It was replaced, later in the program, by an alternate silicon nitride composition (NT551), which utilized a lower cost raw material and a simplified powder-processing approach. The material specifications were defined based on DDC's engine requirements, and the initial and final component design tasks were completed.

  11. Chemical sensors technology development planning workshop

    SciTech Connect

    Bastiaans, G.J.; Haas, W.J. Jr.; Junk, G.A.

    1993-03-01

    The workshop participants were asked to: (1) Assess the current capabilities of chemical sensor technologies for addressing US Department of Energy (DOE) Environmental Restoration and Waste Management (EM) needs; (2) Estimate potential near term (one to two years) and intermediate term (three to five years) capabilities for addressing those needs; and (3) Generate a ranked list of specific recommendations on what research and development (R&D) should be funded to provide the necessary capabilities. The needs were described in terms of two pervasive EM problems, the in situ determination of chlorinated volatile organic compounds (VOCs), and selected metals in various matrices at DOE sites. The R&D recommendations were to be ranked according to the estimated likelihood that the product technology will be ready for application within the time frame it is needed and the estimated return on investment. The principal conclusions and recommendations of the workshop are as follows: Chemical sensors capable of in situ determinations can significantly reduce analytical costs; Chemical sensors have been developed for certain VOCs in gases and water but none are currently capable of in situ determination of VOCs in soils; The DOE need for in situ determination of metals in soils cannot be addressed with existing chemical sensors and the prospects for their availability in three to five years are uncertain; Adaptation, if necessary, and field application of laboratory analytical instruments and those few chemical sensors that are already in field testing is the best approach for the near term; The chemical sensor technology development plan should include balanced support for near- and intermediate-term efforts.

  12. Status and Mission Applicability of NASA's In-Space Propulsion Technology Project

    NASA Technical Reports Server (NTRS)

    Anderson, David J.; Munk, Michelle M.; Dankanich, John; Pencil, Eric; Liou, Larry

    2009-01-01

    The In-Space Propulsion Technology (ISPT) project develops propulsion technologies that will enable or enhance NASA robotic science missions. Since 2001, the ISPT project developed and delivered products to assist technology infusion and quantify mission applicability and benefits through mission analysis and tools. These in-space propulsion technologies are applicable, and potentially enabling for flagship destinations currently under evaluation, as well as having broad applicability to future Discovery and New Frontiers mission solicitations. This paper provides status of the technology development, near-term mission benefits, applicability, and availability of in-space propulsion technologies in the areas of advanced chemical thrusters, electric propulsion, aerocapture, and systems analysis tools. The current chemical propulsion investment is on the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance for lower cost. Investments in electric propulsion technologies focused on completing NASA's Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system, and the High Voltage Hall Accelerator (HiVHAC) thruster, which is a mid-term product specifically designed for a low-cost electric propulsion option. Aerocapture investments developed a family of thermal protections system materials and structures; guidance, navigation, and control models of blunt-body rigid aeroshells; atmospheric models for Earth, Titan, Mars and Venus; and models for aerothermal effects. In 2009 ISPT started the development of propulsion technologies that would enable future sample return missions. The paper describes the ISPT project's future focus on propulsion for sample return missions. The future technology development areas for ISPT is: Planetary Ascent Vehicles (PAV), with a Mars Ascent Vehicle (MAV) being the initial development focus; multi-mission technologies for Earth Entry Vehicles (MMEEV) needed

  13. Application of radiation technology in vaccines development

    PubMed Central

    2015-01-01

    One of the earliest methods used in the manufacture of stable and safe vaccines is the use of chemical and physical treatments to produce inactivated forms of pathogens. Although these types of vaccines have been successful in eliciting specific humoral immune responses to pathogen-associated immunogens, there is a large demand for the development of fast, safe, and effective vaccine manufacturing strategies. Radiation sterilization has been used to develop a variety of vaccine types, because it can eradicate chemical contaminants and penetrate pathogens to destroy nucleic acids without damaging the pathogen surface antigens. Nevertheless, irradiated vaccines have not widely been used at an industrial level because of difficulties obtaining the necessary equipment. Recent successful clinical trials of irradiated vaccines against pathogens and tumors have led to a reevaluation of radiation technology as an alternative method to produce vaccines. In the present article, we review the challenges associated with creating irradiated vaccines and discuss potential strategies for developing vaccines using radiation technology. PMID:26273573

  14. Alternative technological development for RF hybridization

    NASA Astrophysics Data System (ADS)

    Antônio Finardi, Célio; da Fontoura Ponchet, André; Battesini Adamo, Cristina; Flacker, Alexander; Cotrin Teixeira, Ricardo; Panepucci, Roberto Ricardo

    2017-03-01

    The paper presents a technological solution for high frequency packaging platform evaluated up to 40 GHz. The main purpose of this development was to define an alternative hybrid technology that is more flexible and faster to prototype compared with thin film or multi chip module (MCM-D). The alternative technology also shows adequate performance for high bit rate solutions integrating optical and electronics blocks. This approach consists of a soft substrate (laminate material), plating processes (electroless Ni–P/Au, electrolytic Au) and lithography patterning. Ground coplanar waveguide was used for microwave structures with excellent ground planes connections due to easy via holes implementation. We present results of high frequency packaging of important RF blocks, such as integrated broadband bias-T, transimpedance amplifier ICs and silicon photonics optical modulators. The paper demonstrates a solution for high frequency hybridization that can be implemented with standard substrates, designed with any shape and with large numbers of metalized via holes and compatible with usual assembling techniques.

  15. Coordinated development of leading biomass pretreatment technologies.

    PubMed

    Wyman, Charles E; Dale, Bruce E; Elander, Richard T; Holtzapple, Mark; Ladisch, Michael R; Lee, Y Y

    2005-12-01

    For the first time, a single source of cellulosic biomass was pretreated by leading technologies using identical analytical methods to provide comparative performance data. In particular, ammonia explosion, aqueous ammonia recycle, controlled pH, dilute acid, flowthrough, and lime approaches were applied to prepare corn stover for subsequent biological conversion to sugars through a Biomass Refining Consortium for Applied Fundamentals and Innovation (CAFI) among Auburn University, Dartmouth College, Michigan State University, the National Renewable Energy Laboratory, Purdue University, and Texas A&M University. An Agricultural and Industrial Advisory Board provided guidance to the project. Pretreatment conditions were selected based on the extensive experience of the team with each of the technologies, and the resulting fluid and solid streams were characterized using standard methods. The data were used to close material balances, and energy balances were estimated for all processes. The digestibilities of the solids by a controlled supply of cellulase enzyme and the fermentability of the liquids were also assessed and used to guide selection of optimum pretreatment conditions. Economic assessments were applied based on the performance data to estimate each pretreatment cost on a consistent basis. Through this approach, comparative data were developed on sugar recovery from hemicellulose and cellulose by the combined pretreatment and enzymatic hydrolysis operations when applied to corn stover. This paper introduces the project and summarizes the shared methods for papers reporting results of this research in this special edition of Bioresource Technology.

  16. Commercial development of advanced PFBC technology

    SciTech Connect

    McClung, J.D.

    1995-12-31

    In the 1970s, the coal-fired power generation industry recognized that the declining price of electricity over the previous five decades was coming to an end. Maximum use had been made of existing cycle efficiencies and scale-up. As researchers looked for a new approach, the focus shifted from the fully developed Rankine cycle to a new array of coal-fired plants using combined-cycle technology. Now, coal-fired combined-cycle plants are being introduced that shift power production to the Brayton cycle. Integrated Gasification Combined Cycle (IGCC) and Pressurized Fluidized Bed Combustion (PFBC) are two technologies at the forefront of this approach. The PFBC approach burns coal in a fluidized bed combustor at elevated pressure. The plant generates electricity from a gas turbine (expanding the hot, pressurized products of combustion) in addition to the conventional steam (bottoming) cycle. Such a plant can achieve thermal efficiencies of about 40 percent and have a levelized busbar cost below any competing coal-based technology. In addition to the economic benefits, the {open_quotes}built-in{close_quotes} feature of environmental control (SO{sub 2} and NO{sub x}) in the combustion process eliminates the need for external gas cleanup such as scrubbers. A PFBC can burn a wider range of coals than a pulverized-coal-fired (PCF) boiler and is simpler to operate and maintain than an IGCC power plant.

  17. Thin Film Technology Development for the Powersphere

    NASA Technical Reports Server (NTRS)

    Simburger, Edward J.; Matsumoto, James H.; Giants, Thomas W.; Garcia, Alexander, III; Liu, Simon; Rawal, Suraj P.; Perry, Alan R.; Marshall, Craig H.; Lin, John K.; Scarborough, Stephen; Curtis, Henry B.

    2003-01-01

    The Aerospace Corporation, NASA Glenn Research Center, Lockheed-Martin, and ILC Dover over the past two years have been engaged in developing a Multifunctional Inflatable Structure for the Powersphere Concept under contract with NASA (NAS3-01115). The Powersphere concept consists of a relatively large spherical solar array, which would be deployed from a microsatellite. The Powersphere structure and the deployment method was patented by the Aerospace Corporation (U.S. Patent Numbers 6,284,966 B 1 and 6,3 18,675). The work on this project has resulted in a number of technological innovations in the state of the art for integrating flexible thin-film solar cells with flex circuit harness technology and inflatable ultraviolet-light-rigidizable structures. The specific power, specific volume, for the Powersphere are presented in Figures 1 and 2 as a function of solar cell technology and efficiency. The Powersphere will enable microsatellite missions across NASA enterprises and DoD missions by providing ample electric power at an affordable cost. The Powersphere design provides attitude-independent electric power and thermal control for an enclosed microsatellite payload. The design is scalable, robust in high radiation environments and provides sufficient electric power to allow the use of electric propulsion. Electric propulsion enables precise positioning of microsatellites which is required for inspectors that would be deployed to inspect the International Space Station, Space Shuttle or large unmanned spacecraft. The Powersphere allows for efficient launch packaging versus deployed volume as shown in Figure 3.

  18. Mucosal Vaccine Development Based on Liposome Technology

    PubMed Central

    Norling, Karin; Bally, Marta; Höök, Fredrik

    2016-01-01

    Immune protection against infectious diseases is most effective if located at the portal of entry of the pathogen. Hence, there is an increasing demand for vaccine formulations that can induce strong protective immunity following oral, respiratory, or genital tract administration. At present, only few mucosal vaccines are found on the market, but recent technological advancements and a better understanding of the principles that govern priming of mucosal immune responses have contributed to a more optimistic view on the future of mucosal vaccines. Compared to live attenuated vaccines, subcomponent vaccines, most often protein-based, are considered safer, more stable, and less complicated to manufacture, but they require the addition of nontoxic and clinically safe adjuvants to be effective. In addition, another limiting factor is the large antigen dose that usually is required for mucosal vaccines. Therefore, the combination of mucosal adjuvants with the recent progress in nanoparticle technology provides an attractive solution to these problems. In particular, the liposome technology is ideal for combining protein antigen and adjuvant into an effective mucosal vaccine. Here, we describe and discuss recent progress in nanoparticle formulations using various types of liposomes that convey strong promise for the successful development of the next generation of mucosal vaccines. PMID:28127567

  19. Wind Energy Workforce Development: Engineering, Science, & Technology

    SciTech Connect

    Lesieutre, George A.; Stewart, Susan W.; Bridgen, Marc

    2013-03-29

    Broadly, this project involved the development and delivery of a new curriculum in wind energy engineering at the Pennsylvania State University; this includes enhancement of the Renewable Energy program at the Pennsylvania College of Technology. The new curricula at Penn State includes addition of wind energy-focused material in more than five existing courses in aerospace engineering, mechanical engineering, engineering science and mechanics and energy engineering, as well as three new online graduate courses. The online graduate courses represent a stand-alone Graduate Certificate in Wind Energy, and provide the core of a Wind Energy Option in an online intercollege professional Masters degree in Renewable Energy and Sustainability Systems. The Pennsylvania College of Technology erected a 10 kilowatt Xzeres wind turbine that is dedicated to educating the renewable energy workforce. The entire construction process was incorporated into the Renewable Energy A.A.S. degree program, the Building Science and Sustainable Design B.S. program, and other construction-related coursework throughout the School of Construction and Design Technologies. Follow-on outcomes include additional non-credit opportunities as well as secondary school career readiness events, community outreach activities, and public awareness postings.

  20. NASA's Exploration Technology Development Program Energy Storage Project Battery Technology Development

    NASA Technical Reports Server (NTRS)

    Reid, Concha M.; Miller, Thomas B.; Mercer, Carolyn R.; Jankovsky, Amy L.

    2010-01-01

    Technical Interchange Meeting was held at Saft America s Research and Development facility in Cockeysville, Maryland on Sept 28th-29th, 2010. The meeting was attended by Saft, contractors who are developing battery component materials under contracts awarded through a NASA Research Announcement (NRA), and NASA. This briefing presents an overview of the components being developed by the contractor attendees for the NASA s High Energy (HE) and Ultra High Energy (UHE) cells. The transition of the advanced lithium-ion cell development project at NASA from the Exploration Technology Development Program Energy Storage Project to the Enabling Technology Development and Demonstration High Efficiency Space Power Systems Project, changes to deliverable hardware and schedule due to a reduced budget, and our roadmap to develop cells and provide periodic off-ramps for cell technology for demonstrations are discussed. This meeting gave the materials and cell developers the opportunity to discuss the intricacies of their materials and determine strategies to address any particulars of the technology.

  1. The development of health technology assessment.

    PubMed

    Banta, David

    2003-02-01

    The field of health technology assessment (HTA) is still relatively new, but it has shown remarkable growth over the last decade, having spread first from the United States to Europe, and now to the entire world. HTA seeks to couple evidence with decision-making, and thus has similarities to evidence-based health care and evidence-based policy-making. The early history of HTA, beginning around 1975, reveals a first period of synthesising available evidence-principally that dealing with efficacy and cost-effectiveness of health care interventions-so as to put it in a format helpful to health policy-makers, especially those in national governments. From 1985 or so, the focus of the second period was on seeking more effective links with these policy-makers, particularly in Europe. The most recent period, beginning in the late 1990s, has been increasingly devoted to more effective dissemination and implementation in order to influence administrators and clinicians. While early assessments tended to focus on large, expensive, machine-based technologies, the scope has gradually widened to include smaller technologies, 'softer' technologies (such as counselling), and health care needs. Actual assessments have also taken on broader issues, such as organisational, social, and ethical implications. In the Member States of the European Union (EU), HTA activities are increasingly visible, and almost all now have a national focus for HTA associated with the Ministry of Health or its equivalent. Central and Eastern European countries are also developing HTA activities. Most recently, HTA has been highlighted by health policy documents from the European Commission. It seems likely that HTA will in the future be institutionalised in some form as part of EU activities.

  2. Reprocessing technology development for irradiated beryllium

    SciTech Connect

    Kawamura, H.; Sakamoto, N.; Tatenuma, K.

    1995-09-01

    At present, beryllium is under consideration as a main candidate material for neutron multiplier and plasma facing material in a fusion reactor. Therefore, it is necessary to develop the beryllium reprocessing technology for effective resource use. And, we have proposed reprocessing technology development on irradiated beryllium used in a fusion reactor. The preliminary reprocessing tests were performed using un-irradiated and irradiated beryllium. At first, we performed beryllium separation tests using un-irradiated beryllium specimens. Un-irradiated beryllium with beryllium oxide which is a main impurity and some other impurities were heat-treated under chlorine gas flow diluted with Ar gas. As the results high purity beryllium chloride was obtained in high yield. And it appeared that beryllium oxide and some other impurities were removed as the unreactive matter, and the other chloride impurities were separated by the difference of sublimation temperature on beryllium chloride. Next, we performed some kinds of beryllium purification tests from beryllium chloride. And, metallic beryllium could be recovered from beryllium chloride by the reduction with dry process. In addition, as the results of separation and purification tests using irradiated beryllium specimens, it appeared that separation efficiency of Co-60 from beryllium was above 96%. It is considered that about 4% Co-60 was carried from irradiated beryllium specimen in the form of cobalt chloride. And removal efficiency of tritium from irradiated beryllium was above 95%.

  3. Current Status of VHTR Technology Development

    SciTech Connect

    David Petti; Hans Gougar; Richard Wright; William Windes; Steve Herring; Richard Schultz; Paul Humrickhouse

    2010-10-01

    Abstract – High Temperature Gas-cooled Reactors (HTGRs) featuring particle fuel reached the stage of commercial deployment in the mid-1980s with the Fort St.Vrain and Thorium HochTemperatur Reaktor feeding electricity to the grids in the United States and West Germany, respectively. The technology was then adopted by Japan and China with the operation of the High Temperature Test Reactor in Oarai, Japan and the High Temperature Reactor (HTR-10) in China. Increasing the outlet temperature of the HTGR to even higher temperatures above 900°C will improve the thermodynamic efficiency of the system and enable application of a new class of gas reactor, the very high temperature reactor, to provide process heat, electricity, and hydrogen to chemical industries with the attendant benefits of improved energy security and reduced CO2 emissions. However, the increase in coolant outlet temperature presents a number of technical challenges associated with fuel, materials, power conversion, and analysis methods for the reactor and hydrogen production. The U.S. Department of Energy is sponsoring a broad program of research and development with a goal of addressing the technical challenges over a broad range of outlet temperatures as part of the Next Generation Nuclear Plant Project. This paper describes the research and development activities that are currently underway to realize the technologies needed for an HTGR that features outlet temperatures of 750 to 950°C.

  4. Technology development needs summary, FY 1995

    SciTech Connect

    Not Available

    1994-03-01

    Historic activities of DOE during the period of nuclear weapons development, and disposal practices of that time, resulted in the discharge of chemical and radioactive materials to the environment at many DOE facilities and sites. DOE has now focused a major technical effort on mitigating the effects of those discharges through an environmental restoration program. Since this could lead to prohibitive costs if conventional technology is applied for remedial action, a national program will be initiated to develop and demonstrate faster, better, cheaper, and safer means of restoring the DOE sites to conditions that will meet state and federal environment regulations. Key elements of the initiative are the Integrated Programs and Integrated Demonstrations, which work together to identify possible solutions to major environmental problems. Needed statements are given for the following programs: mixed waste landfill, uranium in soils, VOC-arid, decontamination and decommissioning of facilities, buried waste, characterization/monitoring/sensor technology, mixed waste, in situ remediation, efficient separations/processing, minimum additive waste stabilization, supercritical water oxidation. A section on how to get involved is included.

  5. Photonics technology development for optical fuzing

    NASA Astrophysics Data System (ADS)

    Geib, K. M.; Serkland, D. K.; Keeler, G. A.; Peake, G. M.; Mar, A.; von der Lippe, C. M.; Liu, J. J.

    2005-09-01

    This paper describes the photonic component development taking place at Sandia National Laboratories, ARDEC and the Army Research Laboratory in support of an effort to develop a robust, compact, and affordable photonic proximity sensor for munitions fuzing applications. Successful implementation of this sensor will provide a new capability for direct fire applications. The technologies under investigation for the optical fuze design covered in this paper are vertical-cavity surface-emitting lasers (VCSELs), vertical-external-cavity surface-emitting lasers (VECSELs), integrated resonant-cavity photodetectors (RCPDs), and refractive micro-optics. The culmination of this work will be low cost, robust, fully integrated, g-hardened components suitable for proximity fuzing applications. The use of advanced photonic components will enable replacement of costly assemblies that employ discrete lasers, photodetectors, and bulk optics. The integrated devices will be mass produced and impart huge savings for a variety of Army applications. The specific application under investigation is for gun-fired munitions. Nevertheless, numerous civilian uses exist for this proximity sensor in automotive, robotics and aerospace applications. This technology is also applicable to robotic ladar and short-range 3-D imaging.

  6. Development of element technologies for EUVL

    NASA Astrophysics Data System (ADS)

    Kinoshita, Hiroo; Watanabe, Takeo; Harada, Tetsuo

    2015-08-01

    Thirty years have passed since the first report on extreme ultraviolet lithography (EUVL) was presented at the annual meeting of the Japanese Society of Applied Physics in 1986. This technology is now in the manufacturing development stage. The high-volume manufacturing of dynamic-random-access-memory (DRAM) chips with a line width of 15 nm is expected in 2016. However, there are critical development issues that remain: generating a stand-alone EUV source with a higher power and producing a mask inspection tool for obtaining zero-defect masks. The Center for EUVL at the University of Hyogo was established in 2010. At present, it utilizes various types of equipment, such as an EUV mask defect inspection tool, an interference-lithography system, a device for measuring the thickness of carbon contamination film deposited by resist outgassing, and reflectivity measurement systems.

  7. Risk Management for Human Support Technology Development

    NASA Technical Reports Server (NTRS)

    jones, Harry

    2005-01-01

    NASA requires continuous risk management for all programs and projects. The risk management process identifies risks, analyzes their impact, prioritizes them, develops and carries out plans to mitigate or accept them, tracks risks and mitigation plans, and communicates and documents risk information. Project risk management is driven by the project goal and is performed by the entire team. Risk management begins early in the formulation phase with initial risk identification and development of a risk management plan and continues throughout the project life cycle. This paper describes the risk management approach that is suggested for use in NASA's Human Support Technology Development. The first step in risk management is to identify the detailed technical and programmatic risks specific to a project. Each individual risk should be described in detail. The identified risks are summarized in a complete risk list. Risk analysis provides estimates of the likelihood and the qualitative impact of a risk. The likelihood and impact of the risk are used to define its priority location in the risk matrix. The approaches for responding to risk are either to mitigate it by eliminating or reducing the effect or likelihood of a risk, to accept it with a documented rationale and contingency plan, or to research or monitor the risk, The Human Support Technology Development program includes many projects with independently achievable goals. Each project must do independent risk management, considering all its risks together and trading them against performance, budget, and schedule. Since the program can succeed even if some projects fail, the program risk has a complex dependence on the individual project risks.

  8. Energy Storage Technology Development for Space Exploration

    NASA Technical Reports Server (NTRS)

    Mercer, Carolyn R.; Jankovsky, Amy L.; Reid, Concha M.; Miller, Thomas B.; Hoberecht, Mark A.

    2011-01-01

    The National Aeronautics and Space Administration is developing battery and fuel cell technology to meet the expected energy storage needs of human exploration systems. Improving battery performance and safety for human missions enhances a number of exploration systems, including un-tethered extravehicular activity suits and transportation systems including landers and rovers. Similarly, improved fuel cell and electrolyzer systems can reduce mass and increase the reliability of electrical power, oxygen, and water generation for crewed vehicles, depots and outposts. To achieve this, NASA is developing non-flow-through proton-exchange-membrane fuel cell stacks, and electrolyzers coupled with low permeability membranes for high pressure operation. The primary advantage of this technology set is the reduction of ancillary parts in the balance-of-plant fewer pumps, separators and related components should result in fewer failure modes and hence a higher probability of achieving very reliable operation, and reduced parasitic power losses enable smaller reactant tanks and therefore systems with lower mass and volume. Key accomplishments over the past year include the fabrication and testing of several robust, small-scale non-flow-through fuel cell stacks that have demonstrated proof-of-concept. NASA is also developing advanced lithium-ion battery cells, targeting cell-level safety and very high specific energy and energy density. Key accomplishments include the development of silicon composite anodes, lithiatedmixed- metal-oxide cathodes, low-flammability electrolytes, and cell-incorporated safety devices that promise to substantially improve battery performance while providing a high level of safety.

  9. Development of an Instrument to Measure Preservice Teachers' Technology Skills, Technology Beliefs, and Technology Barriers

    ERIC Educational Resources Information Center

    Brush, Thomas; Glazewski, Krista D.; Hew, Khe Foon

    2008-01-01

    The purpose of this study was to develop and field-test the Technology Skills, Beliefs, and Barriers scale and to determine its validity and reliability for use with preservice teachers. Data were collected from 176 preservice teachers enrolled in a field-based teacher education program located at a major Southwestern university in the United…

  10. Technology platforms: opportunities and development perspectives

    NASA Astrophysics Data System (ADS)

    Belyakov, G. P.; Avramchikova, N. T.; Belyakova, G. Y.; Chuvashova, M. N.

    2016-11-01

    The term “technology platform” is used to define thematic scopes in terms of which technological priorities are formed concerning state, business, science and education cooperation that are aimed to solve the problem of state technological independence. The authors have examined the implementation of this tool so that to concentrate essential resources in priority-driven vectors of science and technological advancement of a guiding cluster of innovative technologies in the field of space applications.

  11. Advanced Electric Traction System Technology Development

    SciTech Connect

    Anderson, Iver

    2011-01-14

    As a subcontractor to General Motors (GM), Ames Laboratory provided the technical expertise and supplied experimental materials needed to assess the technology of high energy bonded permanent magnets that are injection or compression molded for use in the Advanced Electric Traction System motor. This support was a sustained (Phase 1: 6/07 to 3/08) engineering effort that builds on the research achievements of the primary FreedomCAR project at Ames Laboratory on development of high temperature magnet alloy particulate in both flake and spherical powder forms. Ames Lab also provide guidance and direction in selection of magnet materials and supported the fabrication of experimental magnet materials for development of injection molding and magnetization processes by Arnold Magnetics, another project partner. The work with Arnold Magnetics involved a close collaboration on particulate material design and processing to achieve enhanced particulate properties and magnetic performance in the resulting bonded magnets. The overall project direction was provided by GM Program Management and two design reviews were held at GM-ATC in Torrance, CA. Ames Lab utilized current expertise in magnet powder alloy design and processing, along with on-going research advances being achieved under the existing FreedomCAR Program project to help guide and direct work during Phase 1 for the Advanced Electric Traction System Technology Development Program. The technical tasks included review of previous GM and Arnold Magnets work and identification of improvements to the benchmark magnet material, Magnequench MQP-14-12. Other benchmark characteristics of the desired magnet material include 64% volumetric loading with PPS polymer and a recommended maximum use temperature of 200C. A collaborative relationship was maintained with Arnold Magnets on the specification and processing of the bonded magnet material required by GM-ATC.

  12. User Interface Technology for Formal Specification Development

    NASA Technical Reports Server (NTRS)

    Lowry, Michael; Philpot, Andrew; Pressburger, Thomas; Underwood, Ian; Lum, Henry, Jr. (Technical Monitor)

    1994-01-01

    Formal specification development and modification are an essential component of the knowledge-based software life cycle. User interface technology is needed to empower end-users to create their own formal specifications. This paper describes the advanced user interface for AMPHION1 a knowledge-based software engineering system that targets scientific subroutine libraries. AMPHION is a generic, domain-independent architecture that is specialized to an application domain through a declarative domain theory. Formal specification development and reuse is made accessible to end-users through an intuitive graphical interface that provides semantic guidance in creating diagrams denoting formal specifications in an application domain. The diagrams also serve to document the specifications. Automatic deductive program synthesis ensures that end-user specifications are correctly implemented. The tables that drive AMPHION's user interface are automatically compiled from a domain theory; portions of the interface can be customized by the end-user. The user interface facilitates formal specification development by hiding syntactic details, such as logical notation. It also turns some of the barriers for end-user specification development associated with strongly typed formal languages into active sources of guidance, without restricting advanced users. The interface is especially suited for specification modification. AMPHION has been applied to the domain of solar system kinematics through the development of a declarative domain theory. Testing over six months with planetary scientists indicates that AMPHION's interactive specification acquisition paradigm enables users to develop, modify, and reuse specifications at least an order of magnitude more rapidly than manual program development.

  13. Next stages in HDR technology development

    SciTech Connect

    Duchane, D.V.

    1993-03-01

    Twenty years of research and development have brought HDR heat mining technology from the purely conceptual stage to the establishment of an engineering-scale heat mine at Fenton Hill, NM. In April 1992, a long-term flow test (LTFT) of the HDR reservoir at Fenton Hill was begun. The test was carried out under steady-state conditions on a continuous basis for four months, but a major equipment failure in late July forced a temporary suspension of operations. Even this short test provided valuable information and extremely encouraging results as summarized below: There was no indication of thermal drawdown of the reservoir. There was evidence of increasing access to hot rock with time. Water consumption was in the rangki of 10--12%. Measured pumping costs were $0.003 per kilowatt of energy produced. Temperature logs conducted in the reservoir production zone during and after the flow test confirmed the fact that there was no decline in the average temperature of the fluid being produced from the reservoir. In fact, tracer testing showed that the fluid was taking more indirect pathways and thus contacting a greater amount of hot rock as the test progressed. Water usage quickly dropped to a level of 10--15 gallons per minute, an amount equivalent to about 10--12% of the injected fluid volume. At a conversion rate of 10--15%, these would translate to effective ``fuel costs`` of 2--3{cents} per kilowatt hour of electricity production potential. The completion of the LTFT will set the stage for commercialization of HDR but will not bring HDR technology to maturity. Relatively samples extensions of the current technology may bring significant improvements in efficiency, and these should be rapidly investigated. In the longer run, advanced operational concepts could further improve the efficiency of HDR energy extraction and may even offer the possibility of cogeneration schemes which solve both energy and water problems throughout the world.

  14. Development of conformal respirator monitoring technology

    SciTech Connect

    Shonka, J.J.; Weismann, J.J.; Logan, R.J.

    1997-04-01

    This report summarizes the results of a Small Business Innovative Research Phase II project to develop a modular, surface conforming respirator monitor to improve upon the manual survey techniques presently used by the nuclear industry. Research was performed with plastic scintillator and gas proportional modules in an effort to find the most conducive geometry for a surface conformal, position sensitive monitor. The respirator monitor prototype developed is a computer controlled, position-sensitive detection system employing 56 modular proportional counters mounted in molds conforming to the inner and outer surfaces of a commonly used respirator (Scott Model 801450-40). The molds are housed in separate enclosures and hinged to create a {open_quotes}waffle-iron{close_quotes} effect so that the closed monitor will simultaneously survey both surfaces of the respirator. The proportional counter prototype was also designed to incorporate Shonka Research Associates previously developed charge-division electronics. This research provided valuable experience into pixellated position sensitive detection systems. The technology developed can be adapted to other monitoring applications where there is a need for deployment of many traditional radiation detectors.

  15. Integrated diesel engine NOx reduction technology development

    SciTech Connect

    Hoelzer, J.; Zhu, J.; Savonen, C.L.; Kharas, K.C.C.; Bailey, O.H.; Miller, M.; Vuichard, J.

    1997-12-31

    The effectiveness of catalyst performance is a function of the inlet exhaust gas temperature, gas flow rate, concentration of NO{sub x} and oxygen, and reductant quantity and species. Given this interrelationship, it becomes immediately clear that an integrated development approach is necessary. Such an approach is taken in this project. As such, the system development path is directed by an engine-catalyst engineering team. Of the tools at the engine engineer`s disposal the real-time aspects of computer assisted subsystem modeling is valuable. It will continue to be the case as ever more subtle improvements are needed to meet competitive performance, durability, and emission challenges. A review of recent prototype engines has shown that considerable improvements to base diesel engine technology are being made. For example, HSDI NO{sub x} has been reduced by a factor of two within the past ten years. However, additional substantial NO{sub x}/PM reduction is still required for the future. A viable lean NO{sub x} catalyst would be an attractive solution to this end. The results of recent high and low temperature catalyst developments were presented. High temperature base metal catalysts have been formulated to produce very good conversion efficiency and good thermal stability, albeit at temperatures near the upper range of diesel engine operation. Low temperature noble metal catalysts have been developed to provide performance of promising 4-way control but need increased NO{sub x} reduction efficiency.

  16. An Information Technology Architecture for Pharmaceutical Research and Development

    PubMed Central

    Klingler, Daniel E.; Jaffe, Marvin E.

    1990-01-01

    Rationale for and development of an information technology architecture are presented. The architectural approach described produces a technology environment that is integrating, flexible, robust, productive, and future-oriented. Issues accompanying architecture development and potential impediments to success are discussed.

  17. Scientific and Technological Development of Hadrontherapy

    NASA Astrophysics Data System (ADS)

    Braccini, Saverio

    2010-04-01

    Hadrontherapy is a novel technique of cancer radiation therapy which employs beams of charged hadrons, protons and carbon ions in particular. Due to their physical and radiobiological properties, they allow one to obtain a more conformal treatment with respect to photons used in conventional radiation therapy, sparing better the healthy tissues located in proximity of the tumour and allowing a higher control of the disease. Hadrontherapy is the direct application of research in high energy physics, making use of specifically conceived particle accelerators and detectors. Protons can be considered today a very important tool in clinical practice due to the several hospital-based centres in operation and to the continuously increasing number of facilities proposed worldwide. Very promising results have been obtained with carbon ion beams, especially in the treatment of specific radio resistant tumours. To optimize the use of charged hadron beams in cancer therapy, a continuous technological challenge is leading to the conception and to the development of innovative methods and instruments. The present status of hadrontherapy is reviewed together with the future scientific and technological perspectives of this discipline.

  18. SEP Mission to Titan NEXT Aerocapture In-Space Propulsion (Quicktime Movie)

    NASA Technical Reports Server (NTRS)

    Baggett, Randy

    2004-01-01

    The ion thruster is one of the most promising solar electric propulsion (SEP) technologies to support future Outer Planet missions (place provided link below here) for NASA's Office of Space Science. Typically, ion thrusters are used in high Isp- low thrust applications that require long lifetimes, as well as, higher efficiency over state-of-the-art chemical propulsion systems.Today, the standard for ion thrusters is the SEP Technology Application Readiness (NSTAR) thruster. Jet Propulsion Laboratory's (JPL's) extended life test (ELT) of the DS 1 flight spare NSTAR thruster began in October 1998. This test successfully demonstrated lifetime of the NSTAR flight spare thruster, which will provide a solid basis for selection of ion thrusters for future Code S missions. The NSTAR ELT was concluded on June 30,2003 after 30,352 hours. The purpose of the Next Generation Ion (NGI) activities is to advance Ion propulsion system technologies through the development of NASA's Evolutionary Xenon Thruster (NEXT). The goal of NEXT is to more than double the power capability and lifetime throughput (the total amount of propellant which can be processed) while increasing the Isp by 30% and the thrust by 120%.

  19. Free-piston Sirling engine technology development

    NASA Astrophysics Data System (ADS)

    Dochat, G. R.

    1982-03-01

    The program will utilize the Technology Demonstrator Engine system as a test bed to evaluate specific loss mechanisms within the engine during operation. This will provide meaningful information and test data to increase understanding of free-piston operation, and will be of benefit to application development programs for heat-activated heat pumps, fluid pumps, engine generators, etc. The evaluation will include the current analytical procedures for calculating the specific losses, perform a series of tests designed to isolate each loss, comparison of actual changes in engine performance with predicted change, and in engine performance with predicted change, and to determine the adequacy of present analytical methods. Recommendations to improve overall engine/system performance and/or analytical methods will be made.

  20. Laser light scattering instrument advanced technology development

    NASA Technical Reports Server (NTRS)

    Wallace, J. F.

    1993-01-01

    The objective of this advanced technology development (ATD) project has been to provide sturdy, miniaturized laser light scattering (LLS) instrumentation for use in microgravity experiments. To do this, we assessed user requirements, explored the capabilities of existing and prospective laser light scattering hardware, and both coordinated and participated in the hardware and software advances needed for a flight hardware instrument. We have successfully breadboarded and evaluated an engineering version of a single-angle glove-box instrument which uses solid state detectors and lasers, along with fiber optics, for beam delivery and detection. Additionally, we have provided the specifications and written verification procedures necessary for procuring a miniature multi-angle LLS instrument which will be used by the flight hardware project which resulted from this work and from this project's interaction with the laser light scattering community.

  1. Development of micropatterning technology for cultured cells.

    PubMed

    Matsuda, T; Inoue, K; Sugawara, T

    1990-01-01

    The manipulation of regional cell adhesiveness by surface design could provide micropatterned cell culturing. Based on the photoreactive chemistry of a phenylazide group, a novel surface micropatterning technology for cultured cells was successfully developed. The principle is as follows: 1) a photoreactive hydrophilic co-polymer with phenylazide was cast on a hydrophobic matrix surface, 2) a photoreactive hydrophobic co-polymer was cast on a hydrophilic matrix; 3) a photomask with a given pattern was tightly placed on the cast film; and 4) after UV irradiation and subsequent washing, bovine endothelial cells (ECs) were seeded and cultured. ECs adhered and grew only on nonhydrophilic regions, eventually resulting in micropatterning of ECs. The micropatterns of cultured ECs prepared by 1) and 2) were negative- and positive-type patterns to that of the photomask used, respectively.

  2. Molten nitrate salt technology development status report

    SciTech Connect

    Carling, R.W.; Kramer, C.M.; Bradshaw, R.W.; Nissen, D.A.; Goods, S.H.; Mar, R.W.; Munford, J.W.; Karnowsky, M.M.; Biefeld, R.N.; Norem, N.J.

    1981-03-01

    Recognizing thermal energy storage as potentially critical to the successful commercialization of solar thermal power systems, the Department of Energy (DOE) has established a comprehensive and aggressive thermal energy storage technology development program. Of the fluids proposed for heat transfer and energy storage molten nitrate salts offer significant economic advantages. The nitrate salt of most interest is a binary mixture of NaNO/sub 3/ and KNO/sub 3/. Although nitrate/nitrite mixtures have been used for decades as heat transfer and heat treatment fluids the use has been at temperatures of about 450/sup 0/C and lower. In solar thermal power systems the salts will experience a temperature range of 350 to 600/sup 0/C. Because central receiver applications place more rigorous demands and higher temperatures on nitrate salts a comprehensive experimental program has been developed to examine what effects, if any, the new demands and temperatures have on the salts. The experiments include corrosion testing, environmental cracking of containment materials, and determinations of physical properties and decomposition mechanisms. This report details the work done at Sandia National Laboratories in each area listed. In addition, summaries of the experimental programs at Oak Ridge National Laboratory, the University of New York, EIC Laboratories, Inc., and the Norwegian Institute of Technology on molten nitrate salts are given. Also discussed is how the experimental programs will influence the near-term central receiver programs such as utility repowering/industrial retrofit and cogeneration. The report is designed to provide easy access to the latest information and data on molten NaNO/sub 3//KNO/sub 3/ for the designers and engineers of future central receiver projects.

  3. Concept and technology development for HOPE spaceplane

    NASA Astrophysics Data System (ADS)

    Ito, Testsuichi; Akimoto, Toshio; Miyaba, Hiroshi; Kano, Yasuomi; Suzuki, Norio

    1990-10-01

    HOPE spaceplane has been studied for several years in NASDA. The purpose of the current study is to establish the feasible concept of HOPE and to prepare the technical bases. The primary mission of HOPE is the Space Station Freedom/JEM logistics transportation complementing with U.S. Space Shuttle fleet. Besides previous concept of ten ton class orbiter launched by H-II rocket, extended size orbiter concept has been studied along with enhancement of H-II rocket, which is called H-IID (derivative) rocket. An orbiter derived from this study weighs 20t at lift off and has three to five tons of payload capability, based on the H-IID configuration of H-II first stage with six solid boosters strapped on. Subsystems design and technology development in such field as aerodynamics, structure and materials, guidance-navigation and control, and Space Station interface are in progress. In order to acquire the reentry flight data, orbital reentry experiment is planned and under development utilizing orbital flight opportunity of H-II test flight in 1993. These concepts are under review and trade off in NASDA for establishing HOPE development scenario.

  4. Advanced Gas Turbine (AGT) Technology Development Project

    NASA Technical Reports Server (NTRS)

    1987-01-01

    This report is the eleventh in the series of Technical Summary reports for the Advanced Gas Turbine (AGT) Technology Development Project, authorized under NASA Contract DEN3-167, and sponsored by the Department of Energy (DOE). This report was prepared by Garrett Turbine Engine Company, A Division of the Garrett Corporation, and includes information provided by Ford Motor Company, the Standard Oil Company, and AiResearch Casting Company. This report covers plans and progress for the period July 1, 1985 through June 30, 1986. Technical progress during the reported period was highlighted by the 85-hour endurance run of an all-ceramic engine operating in the 2000 to 2250 F temperature regime. Component development continued in the areas of the combustion/fuel injection system, regenerator and seals system, and ceramic turbine rotor attachment design. Component rig testing saw further refinements. Ceramic materials showed continued improvements in required properties for gas turbine applications; however, continued development is needed before performance and reliability goals can be set.

  5. Pyro-processing Technology Development in Japan

    SciTech Connect

    Inoue, Tadashi; Koyama, Tadafumi; Myochin, Munetaka; Arai, Yasuo

    2007-07-01

    Metal fuel cycle with pyro-processing technology has another potential different from oxide fuel cycle with aqueous process. In addition to the advantage of metal fuel fast reactor, such as achieving a high breeding ratio over 1.3, the pyro-processing with metal electrorefining expects that no additional process is required to separate minor actinides and no organic solvent that degrades by radiation and acid is utilized. 'Feasibility Study on Commercialized Fast Reactor (FR) Cycle Systems' in Japan selected the metal fuel fast reactor fuel cycle with metal-electrorefining as the sub-system for future development. CRIEPI has been involving on R and D of pyro-processing technology with metal-electrorefining since 1980's and followed JAERI, that orients to apply on the treatment of spent target with nitride fuel for ADS, and JNC, currently merged to JAEA, and, then, wider collaboration started among CRIEPI/JAERI/JNC. The series verification of process starting with MOX pellets have produced U-Pu alloy after distillation through reduction and electrorefining at the facility installed in Tokai, JAEA. The metal fuel fabrication has started from the stage of U-Pu alloy fabrication from UO{sub 2} and PuO{sub 2} mixture by electrochemical reduction, and currently succeeds to produce a fuel slag of U-Pu-Zr of 30 cm by injection casting in Oarai, JAEA. The alloys are scheduled to irradiate in JOYO fast reactor core. The development of engineering model of electro-refiner and electrochemical reduction device has successfully conducted by use of UO{sub 2} with kg scale. In addition to domestic R and Ds, pyro-processing verification with genuine material is proceeding in the joint study of CRIEPI/ITU. TRU is extracted into cadmium from chloride prepared from HLLW through denitration by reductive extraction in a caisson installed in a hot cell, and, then, electrorefining by use of PHENIX-irradiated metal fuel with minor actinides is scheduled. Thus, the R and D on pyro

  6. Airbreathing Hypersonic Technology Vision Vehicles and Development Dreams

    NASA Technical Reports Server (NTRS)

    McClinton, C. R.; Hunt, J. L.; Ricketts, R. H.; Reukauf, P.; Peddie, C. L.

    1999-01-01

    Significant advancements in hypersonic airbreathing vehicle technology have been made in the country's research centers and industry over the past 40 years. Some of that technology is being validated with the X-43 flight tests. This paper presents an overview of hypersonic airbreathing technology status within the US, and a hypersonic technology development plan. This plan builds on the nation's large investment in hypersonics. This affordable, incremental plan focuses technology development on hypersonic systems, which could be operating by the 2020's.

  7. Advancing Technology Education: The Role of Professional Development.

    ERIC Educational Resources Information Center

    Loucks-Horsley, Susan; Bybee, Rodger W.

    2000-01-01

    The technology literacy standards will necessitate increased professional development for those required to implement them. Four areas to guide professional development plans are as follows:(1) learning about technology; (2) learning to teach technology; (3) self-assessment and continuous improvement; and (4) sustained professional development.…

  8. 30 CFR 402.11 - Technology-development project applications.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... RESEARCH PROGRAM AND THE WATER-RESOURCES TECHNOLOGY DEVELOPMENT PROGRAM Application, Evaluation, and Management Procedures § 402.11 Technology-development project applications. (a) Grant awards will be used to... 30 Mineral Resources 2 2014-07-01 2014-07-01 false Technology-development project...

  9. 30 CFR 402.11 - Technology-development project applications.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... RESEARCH PROGRAM AND THE WATER-RESOURCES TECHNOLOGY DEVELOPMENT PROGRAM Application, Evaluation, and Management Procedures § 402.11 Technology-development project applications. (a) Grant awards will be used to... 30 Mineral Resources 2 2012-07-01 2012-07-01 false Technology-development project...

  10. 30 CFR 402.11 - Technology-development project applications.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... RESEARCH PROGRAM AND THE WATER-RESOURCES TECHNOLOGY DEVELOPMENT PROGRAM Application, Evaluation, and Management Procedures § 402.11 Technology-development project applications. (a) Grant awards will be used to... 30 Mineral Resources 2 2010-07-01 2010-07-01 false Technology-development project...

  11. 30 CFR 402.11 - Technology-development project applications.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... RESEARCH PROGRAM AND THE WATER-RESOURCES TECHNOLOGY DEVELOPMENT PROGRAM Application, Evaluation, and Management Procedures § 402.11 Technology-development project applications. (a) Grant awards will be used to... 30 Mineral Resources 2 2013-07-01 2013-07-01 false Technology-development project...

  12. 30 CFR 402.11 - Technology-development project applications.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... RESEARCH PROGRAM AND THE WATER-RESOURCES TECHNOLOGY DEVELOPMENT PROGRAM Application, Evaluation, and Management Procedures § 402.11 Technology-development project applications. (a) Grant awards will be used to... 30 Mineral Resources 2 2011-07-01 2011-07-01 false Technology-development project...

  13. Technology Development: Imperatives for Higher Education.

    ERIC Educational Resources Information Center

    Broere, I.; Geyser, H. C.; Kruger, M.

    2002-01-01

    Discusses the enhancement of higher education in South Africa through technology, exploring some relevant aspects through learner-centered and managerial perspectives. Outlines some critical conditions to integrate technologies into teaching and learning. (SLD)

  14. Developing Technological Fluency through Creative Robotics

    ERIC Educational Resources Information Center

    Bernstein, Debra Lynn

    2010-01-01

    Children have frequent access to technologies such as computers, game systems, and mobile phones (Sefton-Green, 2006). But it is useful to distinguish between engaging with technology as a "consumer" and engaging as a "creator" or designer (Resnick & Rusk, 1996). Children who engage as the former can use technology efficiently, while those who…

  15. Using Assistive Technology for Literacy Development

    ERIC Educational Resources Information Center

    Wepner, Shelley B.; Bowes, Kathleen A.

    2004-01-01

    Assistive Technology--as defined by the ?"Tech Act?" (Technology-Related Assistance for Individuals with Disabilities Act, Public Law 100-407)?is any item, piece of equipment, or product system that is used to increase, maintain, or improve functional capabilities of individuals with disabilities. While the term assistive technology is new, the…

  16. Wikipedia use: Risk for developing technology addiction

    PubMed Central

    Sharma, Manoj Kumar

    2016-01-01

    The present case highlights the addictive potential of Wikipedia usage. The users approached a technology addiction clinic for the management of excessive use of technology. A clinical interview was used to elicit information about usages. It indicates the addictive use of Wikipedia and associated dysfunction in lifestyle. It has implication for promotion of healthy use of technology. PMID:28163416

  17. Digital Technology and Student Cognitive Development

    ERIC Educational Resources Information Center

    Cavanaugh, J. Michael; Giapponi, Catherine C.; Golden, Timothy D.

    2016-01-01

    Digital technology has proven a beguiling, some even venture addictive, presence in the lives of our 21st century (millennial) students. And while screen technology may offer select cognitive benefits, there is mounting evidence in the cognitive neuroscience literature that digital technology is restructuring the way our students read and think,…

  18. Space Station Engineering and Technology Development

    NASA Technical Reports Server (NTRS)

    1985-01-01

    The evolving space station program will be examined through a series of more specific studies: maintainability; research and technology in space; solar thermodynamics research and technology; program performance; onboard command and control; and research and technology road maps. The purpose is to provide comments on approaches to long-term, reliable operation at low cost in terms of funds and crew time.

  19. Technology Development Risk Assessment for Space Transportation Systems

    NASA Technical Reports Server (NTRS)

    Mathias, Donovan L.; Godsell, Aga M.; Go, Susie

    2006-01-01

    A new approach for assessing development risk associated with technology development projects is presented. The method represents technology evolution in terms of sector-specific discrete development stages. A Monte Carlo simulation is used to generate development probability distributions based on statistical models of the discrete transitions. Development risk is derived from the resulting probability distributions and specific program requirements. Two sample cases are discussed to illustrate the approach, a single rocket engine development and a three-technology space transportation portfolio.

  20. Personnel Implications of New Technological Developments: Undersea Technologies.

    ERIC Educational Resources Information Center

    Wilson, David A.

    During the next two decades, changes in underseas technology will profoundly affect Navy personnel and training requirements. Both Navy and national programs in ocean science and engineering will require operational commitments from the Navy which are far beyond present personnel capabilities. In the near future, Navy personnel will routinely work…

  1. Developments in Science and Technology. Fiscal Year 1974.

    DTIC Science & Technology

    The document covers developments in space science and technology, space communication, urban transportation, vessel traffic system, environmental engineering, biomedical engineering and research in supporting development.

  2. Some implications of in situ uranium mining technology development

    SciTech Connect

    Cowan, C.E.; Parkhurst, M.A.; Cole, R.J.; Keller, D.; Mellinger, P.J.; Wallace, R.W.

    1980-09-01

    A technology assessment was initiated in March 1979 of the in-situ uranium mining technology. This report explores the impediments to development and deployment of this technology and evaluates the environmental impacts of a generic in-situ facility. The report is divided into the following sections: introduction, technology description, physical environment, institutional and socioeconomic environment, impact assessment, impediments, and conclusions. (DLC)

  3. Development of Survey of Technological Pedagogical and Content Knowledge (TPACK)

    ERIC Educational Resources Information Center

    Sahin, Ismail

    2011-01-01

    The purpose of this study is to develop a survey of technological pedagogical and content knowledge (TPACK). The survey consists of seven subscales forming the TPACK model: 1) technology knowledge (TK), 2) pedagogy knowledge (PK), 3) content knowledge (CK), 4) technological pedagogical knowledge (TPK), 5) technological content knowledge (TCK), 6)…

  4. Westinghouse gasification technology development and projects status

    SciTech Connect

    Daugherty, D. P.; Schmidt, D. K.

    1982-01-01

    A joint program between Westinghouse, the Department of Energy, and the Gas Research Institute has shown, through the use of a 35 ton-per-day coal feed process development unit (PDU), that the fluidized bed gasifier is technically feasible and economically attractive. The process has been shown to be simple, controllable, and safe in converting many types of coals, including reactive western coals, caking eastern coals, high ash coals, and run-of-mine coals. The process is efficient because it utilizes many coals at high conversion efficiency with relatively low use of oxidant and steam. Because of its simplicity, its use of available hardware technology, and the absence of tars in the product gas, the system has low capital and operating costs. It can be employed with little adverse environmental impact because of its efficiency, low pollutant output, low water usage, and disposal ash product. Process advantages have been confirmed by independent conceptual designs and cost estimates for commercial-scale applications, including substitute natural gas (SNG), industrial fuel gas, liquid synfuels, and combined cycle power generation. The development program includes unique cost-effective integration of hot and cold small-scale experimental models, a commercial-scale cold flow model, and analytical modeling, together with the PDU, to provide commercial design procedures. Westinghouse commercial designs are utilizing these design tools and the process is now being scaled-up for a commercial-scale demonstration facility.

  5. HAN-Based Monopropellant Technology Development

    NASA Technical Reports Server (NTRS)

    Reed, Brian

    2002-01-01

    NASA Glenn Research Center is sponsoring efforts to develop technology for high-performance, high-density, low-freezing point, low-hazards monopropellant systems. The program is focused on a family of monopropellant formulations composed of an aqueous solution of hydroxylammonium nitrate (HAN) and a fuel component. HAN-based monopropellants offer significant mass and volume savings to small (less than 100 kg) satellite for orbit raising and on-orbit propulsion applications. The low-hazards characteristics of HAN-based monopropellants make them attractive for applications where ground processing costs are a significant concern. A 1-lbf thruster has been demonstrated to a 20-kg satellite orbit insertion duty cycle, using a formulation compatible with currently available catalysts. To achieve specific impulse levels above those of hydrazine, catalyst materials that can withstand the high-temperature, corrosive combustion environment of HAN-based monopropellants have to be developed. There also needs to be work done to characterize propellant properties, burning behavior, and material compatibility. NASA is coordinating their monopropellant efforts with those of the United States Air Force.

  6. Decision Gate Process for Assessment of a Technology Development Portfolio

    NASA Technical Reports Server (NTRS)

    Kohli, Rajiv; Fishman, Julianna; Hyatt, Mark

    2012-01-01

    The NASA Dust Management Project (DMP) was established to provide technologies (to TRL 6 development level) required to address adverse effects of lunar dust to humans and to exploration systems and equipment, which will reduce life cycle cost and risk, and will increase the probability of sustainable and successful lunar missions. The technology portfolio of DMP consisted of different categories of technologies whose final product is either a technology solution in itself, or one that contributes toward a dust mitigation strategy for a particular application. A Decision Gate Process (DGP) was developed to assess and validate the achievement and priority of the dust mitigation technologies as the technologies progress through the development cycle. The DGP was part of continuous technology assessment and was a critical element of DMP risk management. At the core of the process were technology-specific criteria developed to measure the success of each DMP technology in attaining the technology readiness levels assigned to each decision gate. The DGP accounts for both categories of technologies and qualifies the technology progression from technology development tasks to application areas. The process provided opportunities to validate performance, as well as to identify non-performance in time to adjust resources and direction. This paper describes the overall philosophy of the DGP and the methodology for implementation for DMP, and describes the method for defining the technology evaluation criteria. The process is illustrated by example of an application to a specific DMP technology.

  7. Hypersonic Inflatable Aerodynamic Decelerator (HIAD) Technology Development Overview

    NASA Technical Reports Server (NTRS)

    Hughes, Stephen J.; Cheatwood, F. McNeil; Calomino, Anthony M.; Wright, Henry S.; Wusk, Mary E.; Hughes, Monica F.

    2013-01-01

    The successful flight of the Inflatable Reentry Vehicle Experiment (IRVE)-3 has further demonstrated the potential value of Hypersonic Inflatable Aerodynamic Decelerator (HIAD) technology. This technology development effort is funded by NASA's Space Technology Mission Directorate (STMD) Game Changing Development Program (GCDP). This paper provides an overview of a multi-year HIAD technology development effort, detailing the projects completed to date and the additional testing planned for the future.

  8. Elementary Teachers' Experiences with Technology Professional Development and Using Technology in the Classroom: A Case Study

    ERIC Educational Resources Information Center

    Grizzle, Pamela Lavon

    2016-01-01

    In order for educators to prepare students for technology-enhanced learning educators must first be prepared. The digital divide and technology professional development are two factors impacting the depth at which technology is integrated into the classroom. The local problem addressed in this study was that the impact of technology professional…

  9. Planetary Science Technology Infusion Study: Findings and Recommendations Status

    NASA Technical Reports Server (NTRS)

    Anderson, David J.; Sandifer, Carl E., II; Sarver-Verhey, Timothy R.; Vento, Daniel M.; Zakrajsek, June F.

    2014-01-01

    The Planetary Science Division (PSD) within the National Aeronautics and Space Administrations (NASA) Science Mission Directorate (SMD) at NASA Headquarters sought to understand how to better realize a scientific return on spacecraft system technology investments currently being funded. In order to achieve this objective, a team at NASA Glenn Research Center was tasked with surveying the science and mission communities to collect their insight on technology infusion and additionally sought inputs from industry, universities, and other organizations involved with proposing for future PSD missions. This survey was undertaken by issuing a Request for Information (RFI) activity that requested input from the proposing community on present technology infusion efforts. The Technology Infusion Study was initiated in March 2013 with the release of the RFI request. The evaluation team compiled and assessed this input in order to provide PSD with recommendations on how to effectively infuse new spacecraft systems technologies that it develops into future competed missions enabling increased scientific discoveries, lower mission cost, or both. This team is comprised of personnel from the Radioisotope Power Systems (RPS) Program and the In-Space Propulsion Technology (ISPT) Program staff.The RFI survey covered two aspects of technology infusion: 1) General Insight, including: their assessment of barriers to technology infusion as related to infusion approach; technology readiness; information and documentation products; communication; integration considerations; interaction with technology development areas; cost-capped mission areas; risk considerations; system level impacts and implementation; and mission pull. 2) Specific technologies from the most recent PSD Announcements of Opportunities (AOs): The Advanced Stirling Radioisotope Generator (ASRG), aerocapture and aeroshell hardware technologies, the NASA Evolutionary Xenon Thruster (NEXT) ion propulsion system, and the

  10. High speed technology development and evaluation

    NASA Astrophysics Data System (ADS)

    Parker, D. R.; Brown, E. R.; Dickson, J. F.

    1986-10-01

    Semiconductor technology suited to high on-board data handling rates was investigated. Very high speed discrete logic and high speed gate arrays; single chip digital signal processors and single chip floating point processing peripherals; and analog CCD technologies and custom designed CCD chips for synthetic aperture radar applications were assessed. The 2 micron CMOS technology is highly reliable, supporting semicustom design techniques. Process JGC, the CCD technology, is highly reliable except for tolerance to ionizing radiation. Reliability of the ECL 16-bit serial-parallel parallel-serial converter junction isolated bipolar process, process WZA, is compromised by a design error and oxide contamination contributing to high leakage levels. The bipolar circuit is tolerant to an ionizing radiation of 20kRad. Step stress environmental testing to 200 C produces no failures in CMOS and CCD technologies, but accelerates the degradation of the oxide contaminated bipolar process. All technologies are susceptible to single event upsets.

  11. Technology Development Roadmap: A Technology Development Roadmap for a Future Gravitational Wave Mission

    NASA Technical Reports Server (NTRS)

    Camp, Jordan; Conklin, John; Livas, Jeffrey; Klipstein, William; McKenzie, Kirk; Mueller, Guido; Mueller, Juergen; Thorpe, James Ira; Arsenovic, Peter; Baker, John; Bender, Peter; Brinker, Edward; Crow, John; Spero, Robert; deVine Glenn; Ziemer, John

    2013-01-01

    Humankind will detect the first gravitational wave (GW) signals from the Universe in the current decade using ground-based detectors. But the richest trove of astrophysical information lies at lower frequencies in the spectrum only accessible from space. Signals are expected from merging massive black holes throughout cosmic history, from compact stellar remnants orbiting central galactic engines from thousands of close contact binary systems in the Milky Way, and possibly from exotic sources, some not yet imagined. These signals carry essential information not available from electromagnetic observations, and which can be extracted with extraordinary accuracy. For 20 years, NASA, the European Space Agency (ESA), and an international research community have put considerable effort into developing concepts and technologies for a GW mission. Both the 2000 and 2010 decadal surveys endorsed the science and mission concept of the Laser Interferometer Space Antenna (LISA). A partnership of the two agencies defined and analyzed the concept for a decade. The agencies partnered on LISA Pathfinder (LPF), and ESA-led technology demonstration mission, now preparing for a 2015 launch. Extensive technology development has been carried out on the ground. Currently, the evolved Laser Interferometer Space Antenna (eLISA) concept, a LISA-like concept with only two measurement arms, is competing for ESA's L2 opportunity. NASA's Astrophysics Division seeks to be a junior partner if eLISA is selected. If eLISA is not selected, then a LISA-like mission will be a strong contender in the 2020 decadal survey. This Technology Development Roadmap (TDR) builds on the LISA concept development, the LPF technology development, and the U.S. and European ground-based technology development. The eLISA architecture and the architecture of the Mid-sized Space-based Gravitational-wave Observatory (SGO Mid)-a competitive design with three measurement arms from the recent design study for a NASA

  12. Career Development and Counseling Strategies in an Age of Technology.

    ERIC Educational Resources Information Center

    Hu, Xiaolu; Toman, Sarah

    The technology revolution not only brings new channels of global communication, but also brings unprecedented changes that can impact America's workforce. This paper highlights the impact of technology and knowledge-based economies to career development and the new concept and strategies that need to be developed. The technology revolution brings…

  13. NASA's In-Space Propulsion Technology Program: A Step Toward Interstellar Exploration

    NASA Technical Reports Server (NTRS)

    Johnson, Les; James, Bonnie; Baggett, Randy; Montgomery, Sandy

    2005-01-01

    NASA's In-Space Propulsion Technology Program is investing in technologies that have the potential to revolutionize the robotic exploration of deep space. For robotic exploration and science missions, increased efficiencies of future propulsion systems are critical to reduce overall life-cycle costs and, in some cases, enable missions previously considered impossible. Continued reliance on conventional chemical propulsion alone will not enable the robust exploration of deep space. The maximum theoretical efficiencies have almost been reached and are insufficient to meet needs for many ambitious science missions currently being considered. By developing the capability to support mid-term robotic mission needs, the program is laying the technological foundation for travel to nearby interstellar space. The In-Space Propulsion Technology Program s technology portfolio includes many advanced propulsion systems. From the next-generation ion propulsion systems operating in the 5-10 kW range, to solar sail propulsion, substantial advances in spacecraft propulsion performance are anticipated. Some of the most promising technologies for achieving these goals use the environment of space itself for energy and propulsion and are generically called "propellantless" because they do not require onboard fuel to achieve thrust. Propellantless propulsion technologies include scientific innovations, such as solar sails, electrodynamic and momentum transfer tethers, and aerocapture. This paper will provide an overview of those propellantless and propellant-based advanced propulsion technologies that will most significantly advance our exploration of deep space.

  14. New developments in surface technology and prototyping

    NASA Astrophysics Data System (ADS)

    Himmer, Thomas; Beyer, Eckhard

    2003-03-01

    Novel lightweight applications in the automotive and aircraft industries require advanced materials and techniques for surface protection as well as direct and rapid manufacturing of the related components and tools. The manufacturing processes presented in this paper are based on multiple additive and subtractive technologies such as laser cutting, laser welding, direct laser metal deposition, laser/plasma hybrid spraying technique or CNC milling. The process chain is similar to layer-based Rapid Prototyping Techniques. In the first step, the 3D CAD geometry is sliced into layers by a specially developed software. These slices are cut by high speed laser cutting and then joined together. In this way laminated tools or parts are built. To improve surface quality and to increase wear resistance a CNC machining center is used. The system consists of a CNC milling machine, in which a 3 kW Nd:YAG laser, a coaxial powder nozzle and a digitizing system are integrated. Using a new laser/plasma hybrid spraying technique, coatings can be deposited onto parts for surface protection. The layers show a low porosity and high adhesion strength, the thickness is up to 0.3 mm, and the lower effort for preliminary surface preparation reduces time and costs of the whole process.

  15. High temperature dynamic engine seal technology development

    NASA Technical Reports Server (NTRS)

    Steinetz, Bruce M.; Dellacorte, Christopher; Machinchick, Michael; Mutharasan, Rajakkannu; Du, Guang-Wu; Ko, Frank; Sirocky, Paul J.; Miller, Jeffrey H.

    1992-01-01

    Combined cycle ramjet/scramjet engines being designed for advanced hypersonic vehicles, including the National Aerospace Plane (NASP), require innovative high temperature dynamic seals to seal the sliding interfaces of the articulated engine panels. New seals are required that will operate hot (1200 to 2000 F), seal pressures ranging from 0 to 100 psi, remain flexible to accommodate significant sidewall distortions, and resist abrasion over the engine's operational life. This report reviews the recent high temperature durability screening assessments of a new braided rope seal concept, braided of emerging high temperature materials, that shows promise of meeting many of the seal demands of hypersonic engines. The paper presents durability data for: (1) the fundamental seal building blocks, a range of candidate ceramic fiber tows; and for (2) braided rope seal subelements scrubbed under engine simulated sliding, temperature, and preload conditions. Seal material/architecture attributes and limitations are identified through the investigations performed. The paper summarizes the current seal technology development status and presents areas in which future work will be performed.

  16. Recent NASA aerospace medicine technology developments

    NASA Technical Reports Server (NTRS)

    Jones, W. L.

    1973-01-01

    Areas of life science are being studied to obtain baseline data, strategies, and technology to permit life research in the space environment. The reactions of the cardiovascular system to prolonged weightlessness are also being investigated. Particle deposition in the human lung, independent respiratory support system, food technology, and remotely controlled manipulators are mentioned briefly.

  17. Definition of Technology Readiness Levels for Transmutation Fuel Development

    SciTech Connect

    Jon Carmack; Kemal O. Pasamehmetoglu

    2008-01-01

    To quantitatively assess the maturity of a given technology, the Technology Readiness Level (TRL) process is used. The TRL process has been developed and successfully used by the Department of Defense (DOD) for development and deployment of new technology and systems for defense applications. In addition, NASA has also successfully used the TRL process to develop and deploy new systems for space applications. Transmutation fuel development is a critical technology needed for closing the nuclear fuel cycle. Because the deployment of a new nuclear fuel forms requires a lengthy and expensive research, development, and demonstration program, applying the TRL concept to the transmutation fuel development program is very useful as a management and tracking tool. This report provides definition of the technology readiness level assessment process as defined for use in assessing nuclear fuel technology development for the Transuranic Fuel Development Campaign.

  18. Development of a Virtual Technology Coach to Support Technology Integration for K-12 Educators

    ERIC Educational Resources Information Center

    Sugar, William; van Tryon, Patricia J. Slagter

    2014-01-01

    In an effort to develop a virtual technology coach for K-12 educators, this article analyzed survey results from sixty teachers with regards to specific resources that a technology coach could provide within a virtual environment. A virtual technology coach was proposed as a possible solution to provide continual professional development for…

  19. Hanford Technology Development (Tank Farms) - 12509

    SciTech Connect

    Fletcher, Thomas; Charboneau, Stacy; Olds, Erik

    2012-07-01

    soil between the ground surface and the water table 200-to-300 feet below. The project tracks and monitors contamination in the soil. Technologies are being developed and deployed to detect and monitor contaminants. Interim surface barriers, which are barriers put over the single-shell tanks, prevent rain and snow from soaking into the ground and spreading contamination. The impermeable barrier placed over T Farm, which was the site of the largest tank waste leak in Hanford's history, is 60,000 square feet and sloped to drain moisture outside the tank farm. The barrier over TY Farm is constructed of asphalt and drains moisture to a nearby evaporation basin. Our discussion of technology will address the incredible challenge of removing waste from Hanford's single-shell tanks. Under the terms of the Tri-Party Agreement, ORP is required to remove 99 percent of the tank waste, or until the limits of technology have been reached. All pumpable liquids have been removed from the single-shell tanks, and work now focuses on removing the non-pumpable liquids. Waste retrieval was completed from the first single-shell tank in late 2003. Since then, another six single-shell tanks have been retrieved to regulatory standards. (authors)

  20. Development of Technology Readiness Level (TRL) Metrics and Risk Measures

    SciTech Connect

    Engel, David W.; Dalton, Angela C.; Anderson, K. K.; Sivaramakrishnan, Chandrika; Lansing, Carina

    2012-10-01

    This is an internal project milestone report to document the CCSI Element 7 team's progress on developing Technology Readiness Level (TRL) metrics and risk measures. In this report, we provide a brief overview of the current technology readiness assessment research, document the development of technology readiness levels (TRLs) specific to carbon capture technologies, describe the risk measures and uncertainty quantification approaches used in our research, and conclude by discussing the next steps that the CCSI Task 7 team aims to accomplish.

  1. Turnaround Operations Analysis for OTV. Volume 3: Technology Development Plan

    NASA Technical Reports Server (NTRS)

    1988-01-01

    An integrated technology development plan for the technologies required to process both GBOTVs and SBOTVs are described. The plan includes definition of the tests and experiments to be accomplished on the ground, in a Space Shuttle Sortie Mission, on an Expendable Launch Vehicle, or at the Space Station as a Technology Development Mission (TDM). The plan reflects and accommodates current and projected research and technology programs where appropriate.

  2. Center for development technology and program in technology and human affairs. [emphasizing technology-based networks

    NASA Technical Reports Server (NTRS)

    Wong, M. D.

    1974-01-01

    The role of technology in nontraditional higher education with particular emphasis on technology-based networks is analyzed nontraditional programs, institutions, and consortia are briefly reviewed. Nontraditional programs which utilize technology are studied. Technology-based networks are surveyed and analyzed with regard to kinds of students, learning locations, technology utilization, interinstitutional relationships, cost aspects, problems, and future outlook.

  3. Technology Readiness Levels for Advanced Nuclear Fuels and Materials Development

    SciTech Connect

    Jon Carmack

    2014-01-01

    The Technology Readiness Level (TRL) process is used to quantitatively assess the maturity of a given technology. The TRL process has been developed and successfully used by the Department of Defense (DOD) for development and deployment of new technology and systems for defense applications. In addition, NASA has also successfully used the TRL process to develop and deploy new systems for space applications. Advanced nuclear fuels and materials development is a critical technology needed for closing the nuclear fuel cycle. Because the deployment of a new nuclear fuel forms requires a lengthy and expensive research, development, and demonstration program, applying the TRL concept to the advanced fuel development program is very useful as a management and tracking tool. This report provides definition of the technology readiness level assessment process as defined for use in assessing nuclear fuel technology development for the Advanced Fuel Campaign (AFC).

  4. Technological Innovation of Thin-Film Transistors: Technology Development, History, and Future

    NASA Astrophysics Data System (ADS)

    Yamamoto, Yoshitaka

    2012-06-01

    The scale of the liquid crystal display industry has expanded rapidly, driven by technological innovations for thin-film transistors (TFTs). The TFT technology, which started from amorphous silicon (a-Si), has produced large TVs, and low-temperature polycrystalline silicon (poly-Si) has become a core technology for small displays, such as mobile phones. Recently, various TFT technological seeds have been realized, indicating that new information appliances that match new lifestyles and information infrastructures will be available in the near future. In this article, I review the history of TFT technology and discuss the future of TFT technological development from the technological innovation viewpoint.

  5. Fuel Cell/Reformers Technology Development

    NASA Technical Reports Server (NTRS)

    2004-01-01

    NASA Glenn Research Center is interested in developing Solid Oxide Fuel Cell for use in aerospace applications. Solid oxide fuel cell requires hydrogen rich feed stream by converting commercial aviation jet fuel in a fuel processing process. The grantee's primary research activities center on designing and constructing a test facility for evaluating injector concepts to provide optimum feeds to fuel processor; collecting and analyzing literature information on fuel processing and desulfurization technologies; establishing industry and academic contacts in related areas; providing technical support to in-house SOFC-based system studies. Fuel processing is a chemical reaction process that requires efficient delivery of reactants to reactor beds for optimum performance, i.e., high conversion efficiency and maximum hydrogen production, and reliable continuous operation. Feed delivery and vaporization quality can be improved by applying NASA's expertise in combustor injector design. A 10 KWe injector rig has been designed, procured, and constructed to provide a tool to employ laser diagnostic capability to evaluate various injector concepts for fuel processing reactor feed delivery application. This injector rig facility is now undergoing mechanical and system check-out with an anticipated actual operation in July 2004. Multiple injector concepts including impinging jet, venturi mixing, discrete jet, will be tested and evaluated with actual fuel mixture compatible with reforming catalyst requirement. Research activities from September 2002 to the closing of this collaborative agreement have been in the following areas: compiling literature information on jet fuel reforming; conducting autothermal reforming catalyst screening; establishing contacts with other government agencies for collaborative research in jet fuel reforming and desulfurization; providing process design basis for the build-up of injector rig facility and individual injector design.

  6. Development of Technology Transfer Economic Growth Metrics

    NASA Technical Reports Server (NTRS)

    Mastrangelo, Christina M.

    1998-01-01

    The primary objective of this project is to determine the feasibility of producing technology transfer metrics that answer the question: Do NASA/MSFC technical assistance activities impact economic growth? The data for this project resides in a 7800-record database maintained by Tec-Masters, Incorporated. The technology assistance data results from survey responses from companies and individuals who have interacted with NASA via a Technology Transfer Agreement, or TTA. The goal of this project was to determine if the existing data could provide indications of increased wealth. This work demonstrates that there is evidence that companies that used NASA technology transfer have a higher job growth rate than the rest of the economy. It also shows that the jobs being supported are jobs in higher wage SIC codes, and this indicates improvements in personal wealth. Finally, this work suggests that with correct data, the wealth issue may be addressed.

  7. Technology Development for Millimeter Wave Phased Arrays.

    DTIC Science & Technology

    1987-05-01

    design would use the technology of integration-the same technology that has brought us computing power at such a low cost. The integrated phased array ...circuitry and/or the feed network, which can degrade sidelobe levels or polarization. A Two Layer Substrate Figure 2.8 shows a possible two-layer design ...feed substrates. Coupling is again through aper- tures in the ground plane of the antenna substrate. This design also allows the use of a low dielectric

  8. Thermoelectric Development at Hi-Z Technology

    SciTech Connect

    Kushch, Aleksandr

    2001-08-05

    An improved Thermoelectric Generator (TEG) for the Heavy Duty Class Eight Diesel Trucks is under development at Hi-Z Technology. The current TEG is equipped with the improved HZ-14 Thermoelectric module, which features better mechanical properties as well as higher electric power output. Also, the modules are held in place more securely. The TEG is comprised of 72 TE modules, which are capable of producing 1kW of electrical power at 30 V DC during nominal engine operation. Currently the upgraded generator has completed testing in a test cell and starting from August 2001 will be tested on a Diesel truck under typical road and environmental conditions. It is expected that the TEG will be able to supplement the existing shaft driven alternator, resulting in significant fuel saving, generating additional power required by the truck's accessories. The electronic and thermal properties of bulk materials are altered when they are incorporated into quantum wells. Two-dimensional quantum wells have been synthesized by alternating layers of B4C and B9C in one system and alternating layers of Si and Si0.8Ge0.2 in another system. Such nanostructures are being investigated as candidate thermoelectric materials with high figures of merit (Z). The predicted enhancement is attributed to the confined motion of charge carriers and phonons in the two dimensions and separating them from the ion scattering centers. Multilayer quantum well materials development continues with the fabrication of thicker films, evaluation of various substrates to minimize bypass heat loss, and bonding techniques to minimize high contact resistance. Quantum well thermoelectric devices with N-type Si/Si0.8Ge0.2 and P-type B4C/B9C have been fabricated from these films. The test results generated continue to indicate that much higher thermoelectric efficiencies can be achieved in the quantum wells compared to the bulk

  9. Engineering research, development and technology report

    SciTech Connect

    Langland, R T

    1999-02-01

    Nineteen ninety-eight has been a transition year for Engineering, as we have moved from our traditional focus on thrust areas to a more focused approach with research centers. These five new centers of excellence collectively comprise Engineering's Science and Technology program. This publication summarizes our formative year under this new structure. Let me start by talking about the differences between a thrust area and a research center. The thrust area is more informal, combining an important technology with programmatic priorities. In contrast, a research center is directly linked to an Engineering core technology. It is the purer model, for it is more enduring yet has the scope to be able to adapt quickly to evolving programmatic priorities. To put it another way, the mission of a thrust area was often to grow the programs in conjunction with a technology, whereas the task of a research center is to vigorously grow our core technologies. By cultivating each core technology, we in turn enable long-term growth of new programs.

  10. Selection and Prioritization of Advanced Propulsion Technologies for Future Space Missions

    NASA Technical Reports Server (NTRS)

    Eberle, Bill; Farris, Bob; Johnson, Les; Jones, Jonathan; Kos, Larry; Woodcock, Gordon; Brady, Hugh J. (Technical Monitor)

    2002-01-01

    The exploration of our solar system will require spacecraft with much greater capability than spacecraft which have been launched in the past. This is particularly true for exploration of the outer planets. Outer planet exploration requires shorter trip times, increased payload mass, and ability to orbit or land on outer planets. Increased capability requires better propulsion systems, including increased specific impulse. Chemical propulsion systems are not capable of delivering the performance required for exploration of the solar system. Future propulsion systems will be applied to a wide variety of missions with a diverse set of mission requirements. Many candidate propulsion technologies have been proposed but NASA resources do not permit development of a] of them. Therefore, we need to rationally select a few propulsion technologies for advancement, for application to future space missions. An effort was initiated to select and prioritize candidate propulsion technologies for development investment. The results of the study identified Aerocapture, 5 - 10 KW Solar Electric Ion, and Nuclear Electric Propulsion as high priority technologies. Solar Sails, 100 Kw Solar Electric Hall Thrusters, Electric Propulsion, and Advanced Chemical were identified as medium priority technologies. Plasma sails, momentum exchange tethers, and low density solar sails were identified as high risk/high payoff technologies.

  11. Evaluation Criteria for Solid Waste Processing Research and Technology Development

    NASA Technical Reports Server (NTRS)

    Levri, Julie A.; Hogan, J. A.; Alazraki, M. P.

    2001-01-01

    A preliminary list of criteria is proposed for evaluation of solid waste processing technologies for research and technology development (R&TD) in the Advanced Life Support (ALS) Program. Completion of the proposed list by current and prospective ALS technology developers, with regard to specific missions of interest, may enable identification of appropriate technologies (or lack thereof) and guide future development efforts for the ALS Program solid waste processing area. An attempt is made to include criteria that capture information about the technology of interest as well as its system-wide impacts. Some of the criteria in the list are mission-independent, while the majority are mission-specific. In order for technology developers to respond to mission-specific criteria, critical information must be available on the quantity, composition and state of the waste stream, the wast processing requirements, as well as top-level mission scenario information (e.g. safety, resource recovery, planetary protection issues, and ESM equivalencies). The technology readiness level (TRL) determines the degree to which a technology developer is able to accurately report on the list of criteria. Thus, a criteria-specific minimum TRL for mandatory reporting has been identified for each criterion in the list. Although this list has been developed to define criteria that are needed to direct funding of solid waste processing technologies, this list processes significant overlap in criteria required for technology selection for inclusion in specific tests or missions. Additionally, this approach to technology evaluation may be adapted to other ALS subsystems.

  12. Fuel cell development at McDermott Technology, Inc.

    SciTech Connect

    Tharp, M.R.; Privette, R.M.; Rowley, D.R.; Khandkar, A.

    1999-07-01

    McDermott Technology, Inc. (MTI) has been involved with the development of a wide variety of fuel cell technologies since 1990. Current programs include the development of planar solid fuel cell (pSOFC) stacks and systems and fuel processing and balance of plant development for proton exchange membrane (PEM) systems. These programs are described.

  13. Developing an Educational Technology Group for Pre-Service Teachers

    ERIC Educational Resources Information Center

    Wilson, Jay

    2012-01-01

    The College of Education Technology Group is a pilot program that supports teacher candidates in developing an understanding of the integration of technology. By engaging teacher candidates with local schools the program is enhancing technology-based learning in the classroom for high school students, especially those from First Nations and other…

  14. Development of Technology Teacher Certification Examination in Taiwan.

    ERIC Educational Resources Information Center

    Lee, Lung-Sheng Steven

    A project was conducted to develop assessment instruments for the living technology (LT) teacher certification examination in Taiwan. Living technology is a secondary-level comprehensive experiential program that addresses technology, its evolution, applications, and impacts. During the project, LT teacher competencies were identified and…

  15. Safeguards and Security Technology Development Directory. FY 1993

    SciTech Connect

    Not Available

    1993-06-01

    The Safeguards and Security Technology Development Directory is published annually by the Office of Safeguards and Security (OSS) of the US Department of Energy (DOE), and is Intended to inform recipients of the full scope of the OSS R&D program. It is distributed for use by DOE headquarters personnel, DOE program offices, DOE field offices, DOE operating contractors, national laboratories, other federal agencies, and foreign governments. Chapters 1 through 7 of the Directory provide general information regarding the Technology Development Program, including the mission, program description, organizational roles and responsibilities, technology development lifecycle, requirements analysis, program formulation, the task selection process, technology development infrastructure, technology transfer activities, and current research and development tasks. These chapters are followed by a series of appendices which contain more specific information on aspects of the Program. Appendix A is a summary of major technology development accomplishments made during FY 1992. Appendix B lists S&S technology development reports issued during FY 1992 which reflect work accomplished through the OSS Technology Development Program and other relevant activities outside the Program. Finally, Appendix C summarizes the individual task statements which comprise the FY 1993 Technology Development Program.

  16. Controlling Complex Systems and Developing Dynamic Technology

    NASA Astrophysics Data System (ADS)

    Avizienis, Audrius Victor

    In complex systems, control and understanding become intertwined. Following Ilya Prigogine, we define complex systems as having control parameters which mediate transitions between distinct modes of dynamical behavior. From this perspective, determining the nature of control parameters and demonstrating the associated dynamical phase transitions are practically equivalent and fundamental to engaging with complexity. In the first part of this work, a control parameter is determined for a non-equilibrium electrochemical system by studying a transition in the morphology of structures produced by an electroless deposition reaction. Specifically, changing the size of copper posts used as the substrate for growing metallic silver structures by the reduction of Ag+ from solution under diffusion-limited reaction conditions causes a dynamical phase transition in the crystal growth process. For Cu posts with edge lengths on the order of one micron, local forces promoting anisotropic growth predominate, and the reaction produces interconnected networks of Ag nanowires. As the post size is increased above 10 microns, the local interfacial growth reaction dynamics couple with the macroscopic diffusion field, leading to spatially propagating instabilities in the electrochemical potential which induce periodic branching during crystal growth, producing dendritic deposits. This result is interesting both as an example of control and understanding in a complex system, and as a useful combination of top-down lithography with bottom-up electrochemical self-assembly. The second part of this work focuses on the technological development of devices fabricated using this non-equilibrium electrochemical process, towards a goal of integrating a complex network as a dynamic functional component in a neuromorphic computing device. Self-assembled networks of silver nanowires were reacted with sulfur to produce interfacial "atomic switches": silver-silver sulfide junctions, which exhibit

  17. [Development of real-world haptic technology].

    PubMed

    Ohnishi, Kouhei; Shimono, Tomoyuki; Natori, Kenji

    2012-07-01

    This paper introduces the principle of real-world haptic and its technology applied to high-grade surgery and/or welfare areas. The existing technology has depended on force sensors, which leads to a trade-off issue between stability and performance. The implementation and realization of a better system has been an unsolved problem for a long time. The authors invented a novel technology that works without force sensors. Modal decomposition and acceleration-based bilateral control(ABC method)are its key concepts. This idea has been actualized with three dof robotic forceps. Several experimental results found by the application of haptic forceps mounted on a 6 dof industrial robot are shown.

  18. Recent Developments in BMW's Diesel Technology

    SciTech Connect

    Steinparzer, F

    2003-08-24

    The image of BMW is very strongly associated to high power, sports biased, luxury cars in the premium car segment, however, particularly in the United States and some parts of Asia, the combination of a car in this segment with a diesel engine was up until now almost unthinkable. I feel sure that many people in the USA are not even aware that BMW produces diesel-powered cars. In Europe there is a completely contrary situation which, driven by the relative high fuel price, and the noticeable difference between gasoline and diesel prices, there has been a continuous growth in the diesel market since the early eighties. During this time BMW has accumulated more then 20 years experience in developing and producing powerful diesel engines for sports and luxury cars. BMW started the production of its 1st generation diesel engine in 1983 with a 2,4 l, turbocharged IDI engine in the 5 series model range. With a specific power of 35 kW/l, this was the most powerful diesel engine on the market at this time. In 1991 BMW introduced the 2nd generation diesel engine, beginning with a 2,5 l inline six, followed in 1994 by a 1,7 l inline four. All engines of this 2nd BMW diesel engine family were turbocharged and utilized an indirect injection combustion system. With the availability of high-pressure injection systems such as the common rail system, BMW developed its 3rd diesel engine family which consists of four different engines. The first was the 4-cylinder for the 3 series car in the spring of 1998, followed by the 6-cylinder in the fall of 1998 and then in mid 1999 by the worlds first V8 passenger car diesel with direct injection. Beginning in the fall of 2001 with the 4-cylinder, BMW reworked this DI engine family fundamentally. Key elements are an improved core engine design, the use of the common rail system of the 2nd generation and a new engine control unit with even better performance. Step by step, these technological improvements were introduce d to production for

  19. Technology Estimating: A Process to Determine the Cost and Schedule of Space Technology Research and Development

    NASA Technical Reports Server (NTRS)

    Cole, Stuart K.; Reeves, John D.; Williams-Byrd, Julie A.; Greenberg, Marc; Comstock, Doug; Olds, John R.; Wallace, Jon; DePasquale, Dominic; Schaffer, Mark

    2013-01-01

    NASA is investing in new technologies that include 14 primary technology roadmap areas, and aeronautics. Understanding the cost for research and development of these technologies and the time it takes to increase the maturity of the technology is important to the support of the ongoing and future NASA missions. Overall, technology estimating may help provide guidance to technology investment strategies to help improve evaluation of technology affordability, and aid in decision support. The research provides a summary of the framework development of a Technology Estimating process where four technology roadmap areas were selected to be studied. The framework includes definition of terms, discussion for narrowing the focus from 14 NASA Technology Roadmap areas to four, and further refinement to include technologies, TRL range of 2 to 6. Included in this paper is a discussion to address the evaluation of 20 unique technology parameters that were initially identified, evaluated and then subsequently reduced for use in characterizing these technologies. A discussion of data acquisition effort and criteria established for data quality are provided. The findings obtained during the research included gaps identified, and a description of a spreadsheet-based estimating tool initiated as a part of the Technology Estimating process.

  20. Technology Transfer vs. Technological Learning: IT-Infrastructure and Health Care in Developing Countries.

    ERIC Educational Resources Information Center

    Braa, Jorn; And Others

    1995-01-01

    Analyzes the conditions and possibilities for technological learning about information technology infrastructure in developing countries; distinguishes between local, contextual learning and institutional or technological infrastructure for learning. Provides examples from Mongolian and South African health care to illustrate the need for learning…

  1. McREL Technology Initiative: The Development of a Technology Intervention Program.

    ERIC Educational Resources Information Center

    Pitler, Howard; Barley, Zoe

    2004-01-01

    The initiative seeks to create and test a comprehensive, research-based model of professional development that helps teachers integrate technology into their classroom instruction, and ultimately, help students achieve high, challenging standards. McREL defines technology integration as using technology, including computers, digital cameras,…

  2. Nature of Technology: Implications for Design, Development, and Enactment of Technological Tools in School Science Classrooms

    ERIC Educational Resources Information Center

    Waight, Noemi; Abd-El-Khalick, Fouad

    2012-01-01

    This position paper provides a theory-based explanation informed by philosophy of technology (PoT) of the recurrent documented patterns often associated with attempts to enact technology-supported, inquiry-based approaches in precollege science classrooms. Understandings derived from the history of technological development in other domains (e.g.…

  3. Composite Technology Personnel Development. Final Report.

    ERIC Educational Resources Information Center

    Massuda, Rachel; Fink, Edwin

    A project was conducted at Delaware County Community College, Media, Pennsylvania, to train two instructional staff members in the area of composite materials technology. A 1-year training program was set up for the two technical instructional specialists at the Boeing Helicopter Training Center, Eddystone, Pennsylvania. The program consisted of…

  4. Vocabulary Development in Technology and Engineering Education

    ERIC Educational Resources Information Center

    Klink, Pamela; Loveland, Thomas

    2015-01-01

    Some students have trouble performing well on summative tests in technology and engineering education. This is largely due to the students' inability to apply the terms to real-world scenarios (Baker, Simmons, & Kameenui, 1995). Exams often provide situational questions and, with these, critical-thinking skills are required. Students may lack…

  5. Communication Technology To Develop Collaborative Skills.

    ERIC Educational Resources Information Center

    Lawrence, Carolena Lyons

    2003-01-01

    Explores communication technology as an instructional tool in relationship to quality of interaction, individual productivity, group productivity, and satisfaction with the learning environment. Discusses collaborative learning skills and examines differences in graduate students' perception using groupware versus face-to-face learning.…

  6. A Lunar Surface System Supportability Technology Development Roadmap

    NASA Technical Reports Server (NTRS)

    Oeftering, Richard C.; Struk, Peter M.; Taleghani, barmac K.

    2011-01-01

    This paper discusses the establishment of a Supportability Technology Development Roadmap as a guide for developing capabilities intended to allow NASA s Constellation program to enable a supportable, sustainable and affordable exploration of the Moon and Mars. Presented is a discussion of supportability, in terms of space facility maintenance, repair and related logistics and a comparison of how lunar outpost supportability differs from the International Space Station. Supportability lessons learned from NASA and Department of Defense experience and their impact on a future lunar outpost is discussed. A supportability concept for future missions to the Moon and Mars that involves a transition from a highly logistics dependent to a logistically independent operation is discussed. Lunar outpost supportability capability needs are summarized and a supportability technology development strategy is established. The resulting Lunar Surface Systems Supportability Strategy defines general criteria that will be used to select technologies that will enable future flight crews to act effectively to respond to problems and exploit opportunities in an environment of extreme resource scarcity and isolation. This strategy also introduces the concept of exploiting flight hardware as a supportability resource. The technology roadmap involves development of three mutually supporting technology categories, Diagnostics Test and Verification, Maintenance and Repair, and Scavenging and Recycling. The technology roadmap establishes two distinct technology types, "Embedded" and "Process" technologies, with different implementation and thus different criteria and development approaches. The supportability technology roadmap addresses the technology readiness level, and estimated development schedule for technology groups that includes down-selection decision gates that correlate with the lunar program milestones. The resulting supportability technology roadmap is intended to develop a set

  7. A Lunar Surface System Supportability Technology Development Roadmap

    NASA Technical Reports Server (NTRS)

    Oeftering, Richard C.; Struk, Peter M.; Taleghani, Barmac K.

    2009-01-01

    This paper discusses the establishment of a Supportability Technology Development Roadmap as a guide for developing capabilities intended to allow NASA's Constellation program to enable a supportable, sustainable and affordable exploration of the Moon and Mars. Presented is a discussion of "supportability", in terms of space facility maintenance, repair and related logistics and a comparison of how lunar outpost supportability differs from the International Space Station. Supportability lessons learned from NASA and Department of Defense experience and their impact on a future lunar outpost is discussed. A supportability concept for future missions to the Moon and Mars that involves a transition from a highly logistics dependent to a logistically independent operation is discussed. Lunar outpost supportability capability needs are summarized and a supportability technology development strategy is established. The resulting Lunar Surface Systems Supportability Strategy defines general criteria that will be used to select technologies that will enable future flight crews to act effectively to respond to problems and exploit opportunities in a environment of extreme resource scarcity and isolation. This strategy also introduces the concept of exploiting flight hardware as a supportability resource. The technology roadmap involves development of three mutually supporting technology categories, Diagnostics Test & Verification, Maintenance & Repair, and Scavenging & Recycling. The technology roadmap establishes two distinct technology types, "Embedded" and "Process" technologies, with different implementation and thus different criteria and development approaches. The supportability technology roadmap addresses the technology readiness level, and estimated development schedule for technology groups that includes down-selection decision gates that correlate with the lunar program milestones. The resulting supportability technology roadmap is intended to develop a set of

  8. Technology for the future - Long range planning for space technology development

    NASA Technical Reports Server (NTRS)

    Collier, Lisa D.; Breckenridge, Roger A.; Llewellyn, Charles P.

    1992-01-01

    NASA's Office of Aeronautics and Space Technology (OAST) has begun the definition of an Integrated Technology Plan for the civilian space program which guides long-term technology development for space platforms, in light of continuing marker research and other planning data. OAST has conferred particular responsibility for future candidate space mission evaluations and platform performance requirement projections to NASA-Langley. An implementation plan is devised which is amenable to periodic space-platform technology updates.

  9. Status of NASA In-Space Propulsion Technologies and Their Infusion Potential

    NASA Technical Reports Server (NTRS)

    Anderson, David; Pencil, Eric; Vento, Dan; Peterson, Todd; Dankanich, John; Hahne, David; Munk, Michelle

    2011-01-01

    Since 2001, the In-Space Propulsion Technology (ISPT) program has been developing in-space propulsion technologies that will enable or enhance NASA robotic science missions. These in-space propulsion technologies have broad applicability to future competed Discovery and New Frontiers mission solicitations, and are potentially enabling for future NASA flagship and sample return missions currently being considered. This paper provides status of the technology development of several in-space propulsion technologies that are ready for infusion into future missions. The technologies that are ready for flight infusion are: 1) the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance; 2) NASA s Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system; and 3) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures; guidance, navigation, and control (GN&C) models of blunt-body rigid aeroshells; and aerothermal effect models. Two component technologies that will be ready for flight infusion in FY12/13 are 1) Advanced Xenon Flow Control System, and 2) ultra-lightweight propellant tank technology advancements and their infusion potential will be also discussed. The paper will also describe the ISPT project s future focus on propulsion for sample return missions: 1) Mars Ascent Vehicles (MAV); 2) multi-mission technologies for Earth Entry Vehicles (MMEEV) needed for sample return missions from many different destinations; and 3) electric propulsion for sample return and low cost missions. These technologies are more vehicle-focused, and present a different set of technology infusion challenges. Systems/Mission Analysis focused on developing tools and assessing the application of propulsion technologies to a wide variety of mission concepts.

  10. NASA'S Changing Role in Technology Development and Transfer

    NASA Technical Reports Server (NTRS)

    Griner, Carolyn S.; Craft, Harry G., Jr.

    1997-01-01

    National Aeronautics and Space Administration NASA has historically had to develop new technology to meet its mission objectives. The newly developed technologies have then been transferred to the private sector to assist US industry's worldwide competitiveness and thereby spur the US economy. The renewed emphasis by the US Government on a proactive technology transfer approach has produced a number of contractual vehicles that assist technology transfer to industrial, aerospace and research firms. NASA's focus has also been on leveraging the shrinking space budget to accomplish "more with less." NASA's cooperative agreements and resource sharing agreements are measures taken to achieve this goal, and typify the changing role of government technology development and transfer with industry. Large commercial partnerships with aerospace firms, as typified by the X-33 and X-34 Programs, are evolving. A new emphasis on commercialization in the Small Business Innovative Research and Dual Use programs paves the way for more rapid commercial application of new technologies developed for NASA.

  11. Development of advanced technologies for biomass pyrolysis

    NASA Astrophysics Data System (ADS)

    Xu, Ran

    the entering vapors and gases to spin, providing good heat transfer and driving the condensed droplets to the wall through cyclonic action. This condenser design has been successfully demonstrated for the application on the pilot fluidized bed pyrolysis unit. After condensation, a stable aerosol is also typically formed which is difficult to be efficiently captured with conventional technologies. A pilot scale helicoidal rotary demister, a novel technology for removing persistent fine bio-oil droplets from gases using dynamic centrifugal forces, has been developed. The demister uses a helicoidal element, which consists of a metal sheet wound as a spiral, designed to rotate at high speeds within a cyclone body. Larger droplets are separated as they enter the cyclone housing, while the smaller droplets are carried by the gas into the helicoidal path of the rotating element, where they are centrifuged towards the outer collecting walls and, as a result of a specially designed baffle, may flow counter-currently to the gas and are drained out from the bottom of the rotating element. The mist-free gas leaves through a channel located at the center of the spiral. This unique demister design has demonstrated a high separation efficiency when tested offline with artificial submicron mist and tested online for demisting bio-oil aerosol on the pyrolysis unit. Bio-oil Upgrading: Very often, phase separation of bio-oil occurs naturally upon condensation of the bio-oil vapors, typically through the use of cyclonic condensers. The bio-oil is separated into an organic phase and an aqueous phase. Research has been conducted on the possibility to enhance the fuel properties and energy performance of the organic phase by reducing its water content, enhancing its heating value and improving its stability. Through the use of drying agents, a remarkable reduction of water content and an increase of heating value can be achieved. Moreover, the volumetric energy density can be greatly

  12. Digital technology and human development: a charter for nature conservation.

    PubMed

    Maffey, Georgina; Homans, Hilary; Banks, Ken; Arts, Koen

    2015-11-01

    The application of digital technology in conservation holds much potential for advancing the understanding of, and facilitating interaction with, the natural world. In other sectors, digital technology has long been used to engage communities and share information. Human development-which holds parallels with the nature conservation sector-has seen a proliferation of innovation in technological development. Throughout this Perspective, we consider what nature conservation can learn from the introduction of digital technology in human development. From this, we derive a charter to be used before and throughout project development, in order to help reduce replication and failure of digital innovation in nature conservation projects. We argue that the proposed charter will promote collaboration with the development of digital tools and ensure that nature conservation projects progress appropriately with the development of new digital technologies.

  13. Duct injection technology prototype development: Evaluation of engineering data

    SciTech Connect

    Not Available

    1990-07-01

    The objective of the Duct Injection Technology Prototype Development Project is to develop a sound design basis for applying duct injection technology as a post-combustion SO{sub 2}emissions control method to existing coal-fired power plants. The necessary engineering design and scale-up criteria will be developed for the commercialization of duct injection technology for the control of SO{sub 2} emissions from coal-fired boilers in the utility industry. The primary focus of the analyses summarized in this Topical Report is the review of the known technical and economic information associated with duct injection technology. (VC)

  14. Development of Thermal Protection Materials for Future Mars Entry, Descent and Landing Systems

    NASA Technical Reports Server (NTRS)

    Cassell, Alan M.; Beck, Robin A. S.; Arnold, James O.; Hwang, Helen; Wright, Michael J.; Szalai, Christine E.; Blosser, Max; Poteet, Carl C.

    2010-01-01

    Entry Systems will play a crucial role as NASA develops the technologies required for Human Mars Exploration. The Exploration Technology Development Program Office established the Entry, Descent and Landing (EDL) Technology Development Project to develop Thermal Protection System (TPS) materials for insertion into future Mars Entry Systems. An assessment of current entry system technologies identified significant opportunity to improve the current state of the art in thermal protection materials in order to enable landing of heavy mass (40 mT) payloads. To accomplish this goal, the EDL Project has outlined a framework to define, develop and model the thermal protection system material concepts required to allow for the human exploration of Mars via aerocapture followed by entry. Two primary classes of ablative materials are being developed: rigid and flexible. The rigid ablatives will be applied to the acreage of a 10x30 m rigid mid L/D Aeroshell to endure the dual pulse heating (peak approx.500 W/sq cm). Likewise, flexible ablative materials are being developed for 20-30 m diameter deployable aerodynamic decelerator entry systems that could endure dual pulse heating (peak aprrox.120 W/sq cm). A technology Roadmap is presented that will be used for facilitating the maturation of both the rigid and flexible ablative materials through application of decision metrics (requirements, key performance parameters, TRL definitions, and evaluation criteria) used to assess and advance the various candidate TPS material technologies.

  15. Developing a Strategic Plan for NASA JSC's Technology Investments

    NASA Technical Reports Server (NTRS)

    Stecklein, Jonette M.

    2012-01-01

    Human space exploration has always been heavily influenced by goals to achieve a specific mission on a specific schedule. This approach drove rapid technology development, the rapidity of which adds risks as well as provides a major driver for costs. The National Aeronautics and Space Administration (NASA) is now approaching the extension of human presence throughout the solar system by balancing a proactive yet less schedule-driven development of technology with opportunistic scheduling of missions as the needed technologies are realized. This approach should provide cost effective, low risk technology development that will enable efficient and effective manned spaceflight missions. As a first step, the NASA Human Spaceflight Architecture Team (HAT) has identified a suite of critical technologies needed to support future manned missions across a range of destinations, including in cislunar space, near earth asteroid visits, lunar exploration, Mars space, and Mars exploration. The challenge now is to develop a strategy and plan for technology development that efficiently enables these missions over a reasonable time period, without increasing technology development costs unnecessarily due to schedule pressure, and subsequently mitigating development and mission risks. NASA fs Johnson Space Center (JSC), as the nation's primary center for human exploration, is addressing this challenge through an innovative approach allocating Internal Research and Development funding to projects that have been prioritized using four focus criteria, with appropriate importance weighting. These four focus criteria are the Human Space Flight Technology Needs, JSC Core Technology Competencies, Commercialization Potential, and Partnership Potential. The inherent coupling in these focus criteria have been captured in a database and have provided an initial prioritization for allocation of technology development research funding. This paper will describe this process and this database

  16. The Development of Space Science and Technology in China,

    DTIC Science & Technology

    1986-05-22

    TESI ’.V-i . (0 00 FTD-ID (RS) T-0282-86 ~/ 4: FOREIGN TECHNOLOGY DIVISION THE DEVELOPMENT OF SPACE SCIENCE AND TECHNOLOGY IN CHINA by Yung-An Liu...TRANSLATION FTD-ID(RS)T-0282-86 22 May 1986 MICROFICHE NR: FTD-86-C-001864 THE DEVELOPMENT OF SPACE SCIENCE AND TECHNOLOGY IN CHINA By: Yung-An Liu English

  17. Impact of developing technology on indirect liquefaction

    SciTech Connect

    Gray, D.; Lytton, M.; Neuworth, M.; Tomlinson, G.

    1980-11-01

    The status of commercial technology for indirect liquefaction, as exemplified by SASOL facilities in South Africa, is reviewed. The impact of substituting more advanced gasifiers and synthesis systems is then investigated. Slagging BGC/Lurgi, Texaco and Shell-Koppers gasifiers were substituted for the Dry Ash Lurgi units used at SASOL. SASOL SYNTHOL synthesis units were replaced by slurry phase Fischer-Tropsch units employing technology pioneered by Kolbel. The advanced systems were found to have a highly favorable impact on plant efficiency, product distribution and gasoline cost. If all the projected technical improvements can be realized for indirect liquefaction, the yields of refined transportation fuels per ton of coal will approach those anticipated for direct liquefaction processes.

  18. Factors Influencing Technology Planning in Developing Countries: A Literature Review

    ERIC Educational Resources Information Center

    Keengwe, Jared; Malapile, Sandy

    2014-01-01

    This article is a literature review concerning the factors that play an important role in the development of educational technology plans in the educational system of developing countries (DCs). Largely, the technology plans are influenced by factors that emanates from within the country (internal) and those outside of their borders (external).…

  19. Computed Tomography Technology: Development and Applications for Defence

    SciTech Connect

    Baheti, G. L.; Saxena, Nisheet; Tripathi, D. K.; Songara, K. C.; Meghwal, L. R.; Meena, V. L.

    2008-09-26

    Computed Tomography(CT) has revolutionized the field of Non-Destructive Testing and Evaluation (NDT and E). Tomography for industrial applications warrants design and development of customized solutions catering to specific visualization requirements. Present paper highlights Tomography Technology Solutions implemented at Defence Laboratory, Jodhpur (DLJ). Details on the technological developments carried out and their utilization for various Defence applications has been covered.

  20. The Los Alamos nuclear safeguards and nonproliferation technology development program

    SciTech Connect

    Smith, H.A. Jr.; Menlove, H.O.; Reilly, T.D.; Bosler, G.E.; Hakkila, E.A.; Eccleston, G.W.

    1994-04-01

    For nearly three decades, Los Alamos National Laboratory has developed and implemented nuclear measurement technology and training in support of national and international nuclear safeguards. This paper outlines the major elements of those technologies and highlights some of the latest developments.

  1. Sustaining Innovation: Developing an Instructional Technology Assessment Process

    ERIC Educational Resources Information Center

    Carmo, Monica Cristina

    2013-01-01

    This case study developed an instructional technology assessment process for the Gevirtz Graduate School of Education (GGSE). The theoretical framework of Adelman and Taylor (2001) guided the development of this instructional technology assessment process and the tools to aid in its facilitation. GGSE faculty, staff, and graduate students…

  2. ECLSS instrumentation technology development for the Space Exploration Initiative

    NASA Astrophysics Data System (ADS)

    Diamant, Bryce L.; Bao, Jinjun; Wieland, Paul; Humphries, William R.

    1991-07-01

    A study of ECLSS instrumentation technologies and an evaluation of SEI ECLSS mission requirements have identified several areas where instrumentation enhancements are required. Attention is given to the ECLSS instrument database fields including development potential, accuracy, cycle time, reliability, resolution, and selectivity. An initial list of instrumentation technologies is recommended for further development to correct each of the deficiencies identified.

  3. Extension Youth Educators' Technology Use in Youth Development Programming

    ERIC Educational Resources Information Center

    McClure, Carli; Buquoi, Brittany; Kotrlik, Joe W.; Machtmes, Krisanna; Bunch, J. C.

    2014-01-01

    The purpose of this descriptive-correlational study was to determine the use of technology in youth programming by Extension youth development educators in Louisiana, Mississippi, and Tennessee. Data were collected via e-mail and a SurveyMonkey© questionnaire. Extension educators are using some technology in youth development programming. More…

  4. Development of Nano Processing Technology for Shape Memory Alloy Fibers

    DTIC Science & Technology

    2011-01-30

    Final Report AOARD-09-4037 (FA2386-09-1-4037) Title: Development of nano processing technology for shape memory alloy fibers PI: Hiroyuki...4. TITLE AND SUBTITLE Development of nano processing technology for shape memory alloy fibers 5a. CONTRACT NUMBER FA23860914037 5b. GRANT NUMBER

  5. Computed Tomography Technology: Development and Applications for Defence

    NASA Astrophysics Data System (ADS)

    Baheti, G. L.; Saxena, Nisheet; Tripathi, D. K.; Songara, K. C.; Meghwal, L. R.; Meena, V. L.

    2008-09-01

    Computed Tomography(CT) has revolutionized the field of Non-Destructive Testing and Evaluation (NDT&E). Tomography for industrial applications warrants design and development of customized solutions catering to specific visualization requirements. Present paper highlights Tomography Technology Solutions implemented at Defence Laboratory, Jodhpur (DLJ). Details on the technological developments carried out and their utilization for various Defence applications has been covered.

  6. Words, Science and Learning. Developing Science and Technology Series.

    ERIC Educational Resources Information Center

    Sutton, Clive Remer

    Science and technology are often presented and taught as two separate essences. When this is done, students as well as teachers are forced to attempt to develop the appropriate linkages. This book is one of a series designed to help teachers develop their science and technological education in ways that are both satisfying to themselves and…

  7. The Implementation of Technology-Based SME Management Development Programmes

    ERIC Educational Resources Information Center

    Carr, James

    2005-01-01

    Learning technology is seen as one solution to the problem of delivering management training in Small and Medium-sized Enterprises (SMEs). This paper investigates how the Higher Education (HE) sector can use its growing expertise in learning technology implementation to develop effective SME management development solutions. It is found that there…

  8. Development of Composite Technologies for the European Next Generation Launcher

    NASA Astrophysics Data System (ADS)

    Fatemi, Javad; van der Bas, Finn

    2014-06-01

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

  9. [Research development on disinfection technology for viruses in drinking water].

    PubMed

    Zhang, Yun; Zhang, Qiang; Liu, Yan; Dai, Ruihua; Liu, Xiang

    2010-09-01

    With the deterioration of water source pollution, the quality requirements for drinking water of countries will become stricter and stricter, and the microbe index has been one of the important aspects. The introduction of the virus index and the development of disinfection technology focusing on virus have significant importance for the improvement of the drinking water standards and for the protection of people health in every country. To be familiar with the domestic and abroad research development of the disinfection control technology focusing on virus provides certain theory guidance and technological support for continuously improving drinking water standard in our country and for establishing safer drinking water processing technologies. So, this article will comprehensively describes 4 aspects: resistance comparison of virus over every disinfection technology, influential factors of disinfection, research development of new technology, and the mechanisms.

  10. World Market Development and Consumer Acceptance of Irradiation Technology

    PubMed Central

    Maherani, Behnoush; Hossain, Farah; Criado, Paula; Ben-Fadhel, Yosra; Salmieri, Stephane; Lacroix, Monique

    2016-01-01

    Food irradiation is an efficient technology that can be used to ensure food safety by eliminating insects and pathogens to prolong the shelf life. The process could be applied to fresh or frozen products without affecting the nutritional value. Presently more than 60 countries have adopted the technology. However, the technology adaptation differs from one country to another and, in some cases, consumers’ misunderstanding and lack of acceptance may hinder the technology adaptation process. This review summarizes the development of irradiation treatment worldwide and consumer attitudes towards the introduction of this technology. Also, the wholesomeness, beneficial effects, and regulation of irradiation are assessed. PMID:28231173

  11. World Market Development and Consumer Acceptance of Irradiation Technology.

    PubMed

    Maherani, Behnoush; Hossain, Farah; Criado, Paula; Ben-Fadhel, Yosra; Salmieri, Stephane; Lacroix, Monique

    2016-11-24

    Food irradiation is an efficient technology that can be used to ensure food safety by eliminating insects and pathogens to prolong the shelf life. The process could be applied to fresh or frozen products without affecting the nutritional value. Presently more than 60 countries have adopted the technology. However, the technology adaptation differs from one country to another and, in some cases, consumers' misunderstanding and lack of acceptance may hinder the technology adaptation process. This review summarizes the development of irradiation treatment worldwide and consumer attitudes towards the introduction of this technology. Also, the wholesomeness, beneficial effects, and regulation of irradiation are assessed.

  12. Airframe Technology Development for Next Generation Launch Vehicles

    NASA Technical Reports Server (NTRS)

    Glass, David E.

    2004-01-01

    The Airframe subproject within NASA's Next Generation Launch Technology (NGLT) program has the responsibility to develop airframe technology for both rocket and airbreathing vehicles for access to space. The Airframe sub-project pushes the state-of-the-art in airframe technology for low-cost, reliable, and safe space transportation. Both low and medium technology readiness level (TRL) activities are being pursued. The key technical areas being addressed include design and integration, hot and integrated structures, cryogenic tanks, and thermal protection systems. Each of the technologies in these areas are discussed in this paper.

  13. Supplement to energy for rural development: Renewable resources and alternative technologies for developing countries

    NASA Astrophysics Data System (ADS)

    The publication energy for rural development: renewable resources and alternative technologies for developing countries, which presented information on a variety of subjects, including direct uses of solar energy (heating, cooling, distillation, crop drying, photovoltaics), indirect uses of solar energy (wind power, hydropower, photosynthesis, biomass), geothermal energy, and energy storage is reviewed. New technologies developed and advances made in technologies are discussed.

  14. Photovoltaic technology development for synchronous orbit

    NASA Technical Reports Server (NTRS)

    Brandhorst, H. W.

    1980-01-01

    Accomplishments and expected benefits are summarized for the following efforts: (1) achieving silicon solar cell efficiency of 18% at 200 micron m to 250 micron m thickness; (2) reducing silicon cell radiation damage in geosynchronous orbit after 10 years to less than 15%; (3) demonstrating coplanar back contact 50 micron m thick silicon solar cells with efficiency of 14%; (4) demonstrating the feasibility of a radiation tolerant GaAs concentrator cell; (5) achieving 30% efficient photo conversion in the laboratory; (6) defining candidate concepts for 50% efficient electromagnetic conversion; and (7) demonstrating the technology for protecting arrays capable of 300W/kg after 10 years in geosynchronous orbit.

  15. Technology development for high power induction accelerators

    SciTech Connect

    Birx, D.L.; Reginato, L.L.

    1985-06-11

    The marriage of Induction Linac technology with Nonlinear Magnetic Modulators has produced some unique capabilities. It appears possible to produce electron beams with average currents measured in amperes, at gradients exceeding 1 MeV/meter, and with power efficiencies approaching 50%. A 2 MeV, 5 kA electron accelerator has been constructed at the Lawrence Livermore National Laboratory (LLNL) to demonstrate these concepts and to provide a test facility for high brightness sources. The pulse drive for the accelerator is based on state-of-the-art magnetic pulse compressors with very high peak power capability, repetition rates exceeding a kilohertz and excellent reliability.

  16. Enhancing Teachers' Technological Pedagogical Knowledge and Practices: A Professional Development Model for Technology Teachers in Malawi

    ERIC Educational Resources Information Center

    Chikasanda, Vanwyk Khobidi Mbubzi; Otrel-Cass, Kathrin; Williams, John; Jones, Alister

    2013-01-01

    This paper reports on a professional development that was designed and implemented in an attempt to broaden teachers' knowledge of the nature of technology and also enhance their technological pedagogical practices. The professional development was organised in four phases with each phase providing themes for reflection and teacher learning in…

  17. Teaching Science with Technology: Case Studies of Science Teachers' Development of Technology, Pedagogy, and Content Knowledge

    ERIC Educational Resources Information Center

    Guzey, S. Selcen; Roehrig, Gillian H.

    2009-01-01

    This study examines the development of technology, pedagogy, and content knowledge (TPACK) in four in-service secondary science teachers as they participated in a professional development program focusing on technology integration into K-12 classrooms to support science as inquiry teaching. In the program, probeware, mind-mapping tools (CMaps),…

  18. Teachers' Perceptions of the Barriers to Technology Integration and Practices with Technology under Situated Professional Development

    ERIC Educational Resources Information Center

    Kopcha, Theodore J.

    2012-01-01

    This case study examines 18 elementary school teachers' perceptions of the barriers to technology integration (access, vision, professional development, time, and beliefs) and instructional practices with technology after two years of situated professional development. Months after transitioning from mentoring to teacher-led communities of…

  19. Nature of Technology: Implications for design, development, and enactment of technological tools in school science classrooms

    NASA Astrophysics Data System (ADS)

    Waight, Noemi; Abd-El-Khalick, Fouad

    2012-12-01

    This position paper provides a theory-based explanation informed by philosophy of technology (PoT) of the recurrent documented patterns often associated with attempts to enact technology-supported, inquiry-based approaches in precollege science classrooms. Understandings derived from the history of technological development in other domains (e.g. medicine, transportation, and warfare) reveal numerous parallels that help to explain these recurrent patterns. Historical analyses of major technologies reveal a conglomerate of factors that interact to produce benefits, as well as intended and unintended consequences. On a macro-scale, PoT facilitates understandings of how technologies interact and are impacted by individuals, society, institutions, economy, politics, and culture. At the micro-level, and most relevant to science education, PoT engages the inherent nature of technology along a number of key dimensions: role of culture and values, notions of technological progression, technology as part of systems, technological diffusion, technology as a fix, and the notions of expertise. Overall, the present analysis has implications for the design, development, implementation, and adoption of technological tools for use in precollege science education, and highlights the role of technology as both artifact and process.

  20. ZERO EMISSION POWER GENERATION TECHNOLOGY DEVELOPMENT

    SciTech Connect

    Ronald Bischoff; Stephen Doyle

    2005-01-20

    Clean Energy Systems (CES) was previously funded by DOE's ''Vision 21'' program. This program provided a proof-of-concept demonstration that CES' novel gas generator (combustor) enabled production of electrical power from fossil fuels without pollution. CES has used current DOE funding for additional design study exercises which established the utility of the CES-cycle for retrofitting existing power plants for zero-emission operations and for incorporation in zero-emission, ''green field'' power plant concepts. DOE funding also helped define the suitability of existing steam turbine designs for use in the CES-cycle and explored the use of aero-derivative turbines for advanced power plant designs. This work is of interest to the California Energy Commission (CEC) and the Norwegian Ministry of Petroleum & Energy. California's air quality districts have significant non-attainment areas in which CES technology can help. CEC is currently funding a CES-cycle technology demonstration near Bakersfield, CA. The Norwegian government is supporting conceptual studies for a proposed 40 MW zero-emission power plant in Stavager, Norway which would use the CES-cycle. The latter project is called Zero-Emission Norwegian Gas (ZENG). In summary, current engineering studies: (1) supported engineering design of plant subsystems applicable for use with CES-cycle zero-emission power plants, and (2) documented the suitability and availability of steam turbines for use in CES-cycle power plants, with particular relevance to the Norwegian ZENG Project.

  1. IVHM for the 3rd Generation RLV Program: Technology Development

    NASA Technical Reports Server (NTRS)

    Kahle, Bill

    2000-01-01

    The objective behind the Integrated Vehicle Health Management (IVHM) project is to develop and integrate the technologies which can provide a continuous, intelligent, and adaptive health state of a vehicle and use this information to improve safety and reduce costs of operations. Technological areas discussed include: developing, validating, and transfering next generation IVHM technologies to near term industry and government reusable launch systems; focus NASA on the next generation and highly advanced sensor and software technologies; and validating IVHM systems engineering design process for future programs.

  2. Cryogenic Fluid Management Technology Development for Nuclear Thermal Propulsion

    NASA Technical Reports Server (NTRS)

    Taylor, B. D.; Caffrey, J.; Hedayat, A.; Stephens, J.; Polsgrove, R.

    2015-01-01

    Cryogenic fluid management technology is critical to the success of future nuclear thermal propulsion powered vehicles and long duration missions. This paper discusses current capabilities in key technologies and their development path. The thermal environment, complicated from the radiation escaping a reactor of a nuclear thermal propulsion system, is examined and analysis presented. The technology development path required for maintaining cryogenic propellants in this environment is reviewed. This paper is intended to encourage and bring attention to the cryogenic fluid management technologies needed to enable nuclear thermal propulsion powered deep space missions.

  3. The NASA In-Space Propulsion Technology Project's Current Products and Future Directions

    NASA Technical Reports Server (NTRS)

    Anderson, David J.; Dankanich, John; Munk, Michelle M.; Pencil, Eric; Liou, Larry

    2010-01-01

    Since its inception in 2001, the objective of the In-Space Propulsion Technology (ISPT) project has been developing and delivering in-space propulsion technologies that enable or enhance NASA robotic science missions. These in-space propulsion technologies are applicable, and potentially enabling for future NASA flagship and sample return missions currently under consideration, as well as having broad applicability to future Discovery and New Frontiers mission solicitations. This paper provides status of the technology development, applicability, and availability of in-space propulsion technologies that recently completed, or will be completing within the next year, their technology development and are ready for infusion into missions. The paper also describes the ISPT project s future focus on propulsion for sample return missions. The ISPT technologies completing their development are: 1) the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance for lower cost; 2) NASA s Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system; and 3) aerocapture technologies which include thermal protection system (TPS) materials and structures, guidance, navigation, and control (GN&C) models of blunt-body rigid aeroshells; and atmospheric and aerothermal effect models. The future technology development areas for ISPT are: 1) Planetary Ascent Vehicles (PAV); 2) multi-mission technologies for Earth Entry Vehicles (MMEEV) needed for sample return missions from many different destinations; 3) propulsion for Earth Return Vehicles (ERV) and transfer stages, and electric propulsion for sample return and low cost missions; 4) advanced propulsion technologies for sample return; and 5) Systems/Mission Analysis focused on sample return propulsion.

  4. Overview of NASA's Thermal Control Technology Development Project

    NASA Technical Reports Server (NTRS)

    Stephan, Ryan A.

    2010-01-01

    NASA?s Constellation Program included the Orion, Altair, and Lunar Surface Systems project offices. The first two elements, Orion and Altair, were planned to be manned space vehicles while the third element was much broader and included several sub-elements including Rovers and a Lunar Habitat. The planned missions involving these systems and vehicles included several risks and design challenges. Due to the unique thermal operating environment, many of these risks and challenges were associated with the vehicles? thermal control system. NASA?s Exploration Technology Development Program (ETDP) consisted of several technology development projects. The project chartered with mitigating the aforementioned thermal risks and design challenges was the Thermal Control System Development for Exploration Project. These risks and design challenges were being addressed through a rigorous technology development process that was planned to culminate with an integrated thermal control system test. Although these Constellation elements have been cancelled or significantly changed, the thermal technology development process is being continued within a new program entitled Enabling Technology Development and Demonstration (ETDD). The current paper summarizes the development efforts being performed by the technology development project. The development efforts involve heat acquisition and heat rejection hardware including radiators, heat exchangers, and evaporators. The project has also been developing advanced phase change material heat sinks and performing a material compatibility assessment for a promising thermal control system working fluid. The to-date progress and lessons-learned from these development efforts will be discussed throughout the paper.

  5. Status of Propulsion Technology Development Under the NASA In-space Propulsion Technology Program

    NASA Technical Reports Server (NTRS)

    Anderson, David; Kamhawi, Hani; Patterson, Mike; Dankanich, John; Pencil, Eric; Pinero, Luis

    2014-01-01

    Since 2001, the In-Space Propulsion Technology (ISPT) program has been developing and delivering in-space propulsion technologies for NASA's Science Mission Directorate (SMD). These in-space propulsion technologies are applicable, and potentially enabling for future NASA Discovery, New Frontiers, Flagship and sample return missions currently under consideration. The ISPT program is currently developing technology in three areas that include Propulsion System Technologies, Entry Vehicle Technologies, and Systems Mission Analysis. ISPT's propulsion technologies include: 1) the 0.6-7 kW NASA's Evolutionary Xenon Thruster (NEXT) gridded ion propulsion system; 2) a 0.3-3.9kW Hall-effect electric propulsion (HEP) system for low cost and sample return missions; 3) the Xenon Flow Control Module (XFCM); 4) ultra-lightweight propellant tank technologies (ULTT); and 5) propulsion technologies for a Mars Ascent Vehicle (MAV). The HEP system is composed of the High Voltage Hall Accelerator (HiVHAc) thruster, a power processing unit (PPU), and the XFCM. NEXT and the HiVHAc are throttle-able electric propulsion systems for planetary science missions. The XFCM and ULTT are two component technologies which being developed with nearer-term flight infusion in mind. Several of the ISPT technologies are related to sample return missions needs like: MAV propulsion and electric propulsion. And finally, one focus of the SystemsMission Analysis area is developing tools that aid the application or operation of these technologies on wide variety of mission concepts. This paper provides a brief overview of the ISPT program, describing the development status and technology infusion readiness.

  6. Status of Propulsion Technology Development Under the NASA In-Space Propulsion Technology Program

    NASA Technical Reports Server (NTRS)

    Anderson, David; Kamhawi, Hani; Patterson, Mike; Pencil, Eric; Pinero, Luis; Falck, Robert; Dankanich, John

    2014-01-01

    Since 2001, the In-Space Propulsion Technology (ISPT) program has been developing and delivering in-space propulsion technologies for NASA's Science Mission Directorate (SMD). These in-space propulsion technologies are applicable, and potentially enabling for future NASA Discovery, New Frontiers, Flagship and sample return missions currently under consideration. The ISPT program is currently developing technology in three areas that include Propulsion System Technologies, Entry Vehicle Technologies, and Systems/Mission Analysis. ISPT's propulsion technologies include: 1) the 0.6-7 kW NASA's Evolutionary Xenon Thruster (NEXT) gridded ion propulsion system; 2) a 0.3-3.9kW Halleffect electric propulsion (HEP) system for low cost and sample return missions; 3) the Xenon Flow Control Module (XFCM); 4) ultra-lightweight propellant tank technologies (ULTT); and 5) propulsion technologies for a Mars Ascent Vehicle (MAV). The NEXT Long Duration Test (LDT) recently exceeded 50,000 hours of operation and 900 kg throughput, corresponding to 34.8 MN-s of total impulse delivered. The HEP system is composed of the High Voltage Hall Accelerator (HIVHAC) thruster, a power processing unit (PPU), and the XFCM. NEXT and the HIVHAC are throttle-able electric propulsion systems for planetary science missions. The XFCM and ULTT are two component technologies which being developed with nearer-term flight infusion in mind. Several of the ISPT technologies are related to sample return missions needs: MAV propulsion and electric propulsion. And finally, one focus of the Systems/Mission Analysis area is developing tools that aid the application or operation of these technologies on wide variety of mission concepts. This paper provides a brief overview of the ISPT program, describing the development status and technology infusion readiness.

  7. The development and technology transfer of software engineering technology at NASA. Johnson Space Center

    NASA Technical Reports Server (NTRS)

    Pitman, C. L.; Erb, D. M.; Izygon, M. E.; Fridge, E. M., III; Roush, G. B.; Braley, D. M.; Savely, R. T.

    1992-01-01

    The United State's big space projects of the next decades, such as Space Station and the Human Exploration Initiative, will need the development of many millions of lines of mission critical software. NASA-Johnson (JSC) is identifying and developing some of the Computer Aided Software Engineering (CASE) technology that NASA will need to build these future software systems. The goal is to improve the quality and the productivity of large software development projects. New trends are outlined in CASE technology and how the Software Technology Branch (STB) at JSC is endeavoring to provide some of these CASE solutions for NASA is described. Key software technology components include knowledge-based systems, software reusability, user interface technology, reengineering environments, management systems for the software development process, software cost models, repository technology, and open, integrated CASE environment frameworks. The paper presents the status and long-term expectations for CASE products. The STB's Reengineering Application Project (REAP), Advanced Software Development Workstation (ASDW) project, and software development cost model (COSTMODL) project are then discussed. Some of the general difficulties of technology transfer are introduced, and a process developed by STB for CASE technology insertion is described.

  8. Configurable technology development for reusable control and monitor ground systems

    NASA Technical Reports Server (NTRS)

    Uhrlaub, David R.

    1994-01-01

    The control monitor unit (CMU) uses configurable software technology for real-time mission command and control, telemetry processing, simulation, data acquisition, data archiving, and ground operations automation. The base technology is currently planned for the following control and monitor systems: portable Space Station checkout systems; ecological life support systems; Space Station logistics carrier system; and the ground system of the Delta Clipper (SX-2) in the Single-Stage Rocket Technology program. The CMU makes extensive use of commercial technology to increase capability and reduce development and life-cycle costs. The concepts and technology are being developed by McDonnell Douglas Space and Defense Systems for the Real-Time Systems Laboratory at NASA's Kennedy Space Center under the Payload Ground Operations Contract. A second function of the Real-Time Systems Laboratory is development and utilization of advanced software development practices.

  9. Recent Developments in Smart Freezing Technology Applied to Fresh Foods.

    PubMed

    Xu, Ji-Cheng; Zhang, Min; Mujumdar, Arun S; Adhikari, Benu

    2015-10-13

    Due to the increased awareness of consumers in sensorial and nutritional quality of frozen foods, the freezing technology has to seek new and innovative technologies for better retaining the fresh-like quality. In this article, we reviewed the recent developments in smart freezing technology applied to fresh foods. The application of these intelligent technologies and the associated underpinning concepts has greatly improved the quality of frozen foods and the freezing efficiency. These technologies are able to automatically collect the information in-line during freezing and help control the freezing process better. Smart freezing technology includes new and intelligent technologies and concepts applied to the pretreatment of the frozen product, freezing processes, cold chain logistics as well as warehouse management. These technologies enable real-time monitoring of quality during freezing process and help improve product quality and freezing efficiency. We also provided a brief overview of several sensing technologies used to achieve automatic control of individual steps of freezing process. These sensing technologies included computer vision, electronic nose, electronic tongue, digital simulation, confocal laser, near infrared spectroscopy, nuclear magnetic resonance technology and ultrasound. Understanding of the mechanism of these new technologies will be helpful for applying them to improve the quality of frozen foods.

  10. Principles for fostering the transdisciplinary development of assistive technologies.

    PubMed

    Boger, Jennifer; Jackson, Piper; Mulvenna, Maurice; Sixsmith, Judith; Sixsmith, Andrew; Mihailidis, Alex; Kontos, Pia; Miller Polgar, Janice; Grigorovich, Alisa; Martin, Suzanne

    2016-04-07

    Developing useful and usable assistive technologies often presents complex (or "wicked") challenges that require input from multiple disciplines and sectors. Transdisciplinary collaboration can enable holistic understanding of challenges that may lead to innovative, impactful and transformative solutions. This paper presents generalised principles that are intended to foster transdisciplinary assistive technology development. The paper introduces the area of assistive technology design before discussing general aspects of transdisciplinary collaboration followed by an overview of relevant concepts, including approaches, methodologies and frameworks for conducting and evaluating transdisciplinary working and assistive technology design. The principles for transdisciplinary development of assistive technologies are presented and applied post hoc to the COACH project, an ambient-assisted living technology for guiding completion of activities of daily living by older adults with dementia as an illustrative example. Future work includes the refinement and validation of these principles through their application to real-world transdisciplinary assistive technology projects. Implications for rehabilitation Transdisciplinarity encourages a focus on real world 'wicked' problems. A transdisciplinary approach involves transcending disciplinary boundaries and collaborating with interprofessional and community partners (including the technology's intended users) on a shared problem. Transdisciplinarity fosters new ways of thinking about and doing research, development, and implementation, expanding the scope, applicability, and commercial viability of assistive technologies.

  11. Traditional Field Crops. Appropriate Technologies for Development.

    ERIC Educational Resources Information Center

    Leonard, David

    This manual, primarily designed to help Peace Corps volunteers develop and strengthen their agricultural skills, deals with traditional field crops. The focus of the manual is on surveying and interpreting local agricultural environment and individual farm units, developing agricultural extension techniques and practices, and providing basic…

  12. The development of ion mobility technology

    NASA Astrophysics Data System (ADS)

    Beliakov, V. V.; Golovin, A. V.; Vasilev, V. K.; Malkin, E. K.; Gromov, E. A.; Ivanov, I. A.; Matusko, M. A.; Lipatov, D. Y.

    2016-10-01

    Increased terrorist threat in recent years makes it especially important to improve the custom equipment including the development of ion mobility spectrometers for reliable, realtime and sensitive identification of illicit substances. The paper summarizes different approaches used in recent developments in the last years: statistical analysis, sampling automation and construction materials study.

  13. Technology development for lunar base water recycling

    NASA Technical Reports Server (NTRS)

    Schultz, John R.; Sauer, Richard L.

    1992-01-01

    This paper will review previous and ongoing work in aerospace water recycling and identify research activities required to support development of a lunar base. The development of a water recycle system for use in the life support systems envisioned for a lunar base will require considerable research work. A review of previous work on aerospace water recycle systems indicates that more efficient physical and chemical processes are needed to reduce expendable and power requirements. Development work on biological processes that can be applied to microgravity and lunar environments also needs to be initiated. Biological processes are inherently more efficient than physical and chemical processes and may be used to minimize resupply and waste disposal requirements. Processes for recovering and recycling nutrients such as nitrogen, phosphorus, and sulfur also need to be developed to support plant growth units. The development of efficient water quality monitors to be used for process control and environmental monitoring also needs to be initiated.

  14. Research and development of fish passage technology

    SciTech Connect

    Hackney, P.A.

    1986-12-01

    Any fish passage provided at TVA's John Sevier Fossil Plant (JSF) would involve only warmwater species. Although some anadromous (marine) warmwater species (e.g., American shad, blueback herring) are currently passed upstream and downstream through structures deliberately built for that purpose, effectiveness of this technology for passage of adults and young of potential target species (e.g., paddlefish and sauger/walleye) in Cherokee Reservoir is unproven. Downstream passage is by far the larger and more poorly understood subject of fish migration and should be investigated first. Currently, the Electric Power Research Institute (EPRI) is conducting research on downstream fish passage (Project RP 2694). It will ultimately be necessary to adapt this information to the target species and site specificity at JSF.

  15. New developments in blown flap noise technology

    NASA Technical Reports Server (NTRS)

    Gibson, J. S.

    1976-01-01

    The noise technology relating to blown-flap systems is reviewed. There are three general sources of noise: turbomachinery, airframe, and the interaction noise of the jet blowing on the flaps. The latter noise-source area is the most critical and the main subject dicussed. Characteristics of lower surface blown and upper surface blown systems are described, including noise spectra, directivity, jet velocity characteristics, aircraft geometric variation effects, and aircraft forward speed effects. Noise reduction concepts are described, including slowing down the jet flow field by devices and engine cycle modifications, structural geometry and shielding modifications, local flow field modifications of the passive and active type, and the absorption of noise. It is concluded that, while there has been considerable progress in the past several years, low noise characteristics in blown flap aircraft must be largely built in by better application of low noise principles during the design.

  16. Stretched Lens Array Photovoltaic Concentrator Technology Developed

    NASA Technical Reports Server (NTRS)

    Piszczor, Michael F., Jr.; O'Neill, Mark J.

    2004-01-01

    Solar arrays have been and continue to be the mainstay in providing power to nearly all commercial and government spacecraft. Light from the Sun is directly converted into electrical energy using solar cells. One way to reduce the cost of future space power systems is by minimizing the size and number of expensive solar cells by focusing the sunlight onto smaller cells using concentrator optics. The stretched lens array (SLA) is a unique concept that uses arched Fresnel lens concentrators to focus sunlight onto a line of high-efficiency solar cells located directly beneath. The SLA concept is based on the Solar Concentrator Array with Refractive Linear Element Technology (SCARLET) design that was used on NASA's New Millennium Deep Space 1 mission. The highly successful asteroid/comet rendezvous mission (1998 to 2001) demonstrated the performance and long-term durability of the SCARLET/SLA solar array design and set the foundation for further improvements to optimize its performance.

  17. Technology Development Benefits and the Economics Breakdown Structure

    NASA Technical Reports Server (NTRS)

    Shaw, Eric J.

    1998-01-01

    This paper describes the construction and application of the EBS (Economics Breakdown Structure) in evaluating technology investments across multiple systems and organizations, illustrated with examples in space transportation technology. The United States Government (USG) has a long history of investing in technology to enable its missions. Agencies such as the National Aeronautics and Space Administration (NASA) and the Department of Defense (DoD) have evaluated their technology development programs primarily on their effects on mission performance and cost. More and more, though, USG agencies are being evaluated on their technology transfer to the commercial sector. In addition, an increasing number of USG missions are being accomplished by industry-led or joint efforts, where the USG provides technology and funding but tasks industry with development and operation of the mission systems.

  18. Recent Developments in NASA Piezocomposite Actuator Technology

    NASA Technical Reports Server (NTRS)

    Wilkie, William K.; Inman, Daniel J.; High, James W.; Williams, R. Brett

    2004-01-01

    In this paper, we present an overview of recent progress in the development of the NASA Macro-Fiber Composite (MFC) piezocomposite actuator device. This will include a brief history of the development of the MFC, a description of the standard manufacturing process used to fabricate MFC actuators, and a summary of ongoing MFC electromechanical characterization testing. In addition, we describe the development of a prototype single-crystal piezoelectric MFC device, and compare its performance with MFC actuator specimens utilizing conventional piezoceramic materials.

  19. Advanced Technology Development for Active Acoustic Liners

    NASA Technical Reports Server (NTRS)

    Sheplak, Mark; Cattafesta, Louis N., III; Nishida, Toshikazu; Kurdila, Andrew J.

    2001-01-01

    Objectives include: (1) Develop electro-mechanical/acoustic models of a Helmholtz resonator possessing a compliant diaphragm coupled to a piezoelectric device; (2) Design and fabricate the energy reclamation module and active Helmholtz resonator; (3) Develop and build appropriate energy reclamation/storage circuit; (4) Develop and fabricate appropriate piezoelectric shunt circuit to tune the compliance of the active Helmholtz resonator via a variable capacitor; (5) Quantify energy reclamation module efficiency in a grazing-flow plane wave tube possessing known acoustic energy input; and (6) Quantify actively tuned Helmholtz resonator performance in grazing-flow plane wave tube for a white-noise input

  20. Invention Development Program Helps Nurture NCI at Frederick Technologies | Poster

    Cancer.gov

    The Invention Development Fund (IDF) was piloted by the Technology Transfer Center (TTC) in 2014 to facilitate the commercial development of NCI technologies. The IDF received a second round of funding from the NCI Office of the Director and the Office of Budget and Management to establish the Invention Development Program (IDP) for fiscal year 2016. The IDP is using these funds to help advance a second set of inventions.

  1. New media, old media: The technologies of international development

    NASA Astrophysics Data System (ADS)

    Ingle, Henry T.

    1986-09-01

    The research, theory and practice of educational technology over the past 75 years provide convincing evidence that this process offers a comprehensive and integrated approach to solving educational and social problems. The use of media and technology in development has shifted from an emphasis on mass media to personal media. A variety of electronic delivery systems are being used and are usually coordinated by centralized governmental agencies. There are no patterns of use since the problems vary and the medium used is responsive to the problem. Computers are used most frequently and satellite telecommunication networks follow. The effective use of these and other technologies requires a long-term commitment to financial support and training of personnel. The extension model of face-to-face contact still prevails in developing nations whether in agriculture, education or rural development. Low-cost technologies are being used in local projects while major regional and national companies use radio, film and related video technologies. The use of all available and cost-effective media and technologies make possible appropriate communications for specific goals with specific audiences. There appears to be no conflict among proponents of various media formats. Development in education and other sectors has much to gain from old and new communication technologies and has hardly been tapped. Several new educational technology developments are discussed as potential contributors to formal and nonformal education.

  2. Science and Technology Education: Developments Under Review.

    ERIC Educational Resources Information Center

    Lockard, David J.

    1985-01-01

    Summarizes what has been learned from recent major studies of the status of science teaching in developed countries and makes recommendations about appropriate future directions for science education. (JDH)

  3. Development of space technology for ecological habitats

    NASA Technical Reports Server (NTRS)

    Martello, N. V.

    1986-01-01

    The development of closed ecological systems for space stations is discussed. Growth chambers, control systems, microgravity, ecosystem stability, lighting equipment, and waste processing systems are among the topics discussed.

  4. Mars 2018: Planetary Protection and Sample Integrity Focused Technology Development

    NASA Technical Reports Server (NTRS)

    Lin, Ying

    2011-01-01

    Mars 2018 is a Category V and IVb mission with corresponding PP (Planetary Protection) requirements center; MSR (Mars Sample Return) PP requirements are sufficiently different from all previous Mars missions that new technology and capabilities are needed; Technology gaps for Mars 2018 have been identified and an investment portfolio developed; Mars Focused Technology program will invest in four critical areas: Contamination risk assessment, Surface sterilization and precision cleaning, Cross contamination prevention, Sample containment, sealing, sample integrity.

  5. Development of a nationwide network for technology transfer

    NASA Technical Reports Server (NTRS)

    Fong, Louis B. C.; Brockman, Paul R.

    1987-01-01

    The winter and spring of 1987 saw the cooperative nationwide network for technology transfer translated from concept to reality. The most obvious of the network relationships which were developed or which are anticipated are summarized. The objective was to help assure that every U.S. business which has the capacity to exploit, or the need to obtain new technology in any form, has access to the technology it needs or can use.

  6. Integrated life sciences technology utilization development program

    NASA Technical Reports Server (NTRS)

    1975-01-01

    The goal of the TU program was to maximize the development of operable hardware and systems which will be of substantial benefit to the public. Five working prototypes were developed, and a meal system for the elderly is now undergoing evaluation. Manpower utilization is shown relative to the volume of requests in work for each month. The ASTP mobile laboratories and post Skylab bedrest study are also described.

  7. RESEARCH, DEVELOPMENT, AND EXPERIMENTAL TELECOMMUNICATIONS TECHNOLOGY

    SciTech Connect

    Zvi H. Meiksin

    2002-07-01

    A temporary installation of Transtek's in-mine communications system in the Lake Lynn mine was used in the mine rescue training programs offered by NIOSH in April and May 2002. We developed and implemented a software program that permits point-to-point data transmission through our in-mine system. We also developed a wireless data transceiver for use in a PLC (programmed logic controller) to remotely control long-wall mining equipment.

  8. Long life Regenerative Fuel Cell technology development plan

    NASA Technical Reports Server (NTRS)

    Littman, Franklin D.; Cataldo, Robert L.; Mcelroy, James F.; Stedman, Jay K.

    1992-01-01

    This paper summarizes a technology roadmap for completing advanced development of a Proton Exchange Membrane (PEM) Regenerative Fuel Cell (RFC) to meet long life (20,000 hrs at 50 percent duty cycle) mobile or portable power system applications on the surface of the moon and Mars. Development of two different sized RFC power system modules is included in this plan (3 and 7.5 kWe). A conservative approach was taken which includes the development of a Ground Engineering System, Qualification Unit, and Flight Unit. This paper includes a concept description, technology assessment, development issues, development tasks, and development schedule.

  9. Developing operational requirements for the design of law enforcement technologies

    NASA Astrophysics Data System (ADS)

    Overlin, Trudy K.; Marts, Donna J.

    1995-05-01

    The Idaho National Engineering Laboratory (INEL) was awarded a two-year project to design and develop an air bag restraint for use in law enforcement patrol vehicles. The work has successfully proven the concept and is in the final stages of prototype development. The end product will be the design and delivery of one prototype unit to the National Institute of Justice for evaluation. The INEL also assessed possible technologies that could be used to halt suspects in fleeing vehicles and safely put an end to high-speed pursuits. During the assessment of these technologies, a set of operational requirements were developed that were useful in determining the appropriateness of the technologies for the law enforcement application. This paper discusses the importance of operational requirements in their application to the technologies assessment conducted in the laboratory. The paper discusses the law enforcement and pursuit environment in terms of liability, safety of operation, social acceptance, and effectiveness of technology.

  10. Schedule Risks Due to Delays in Advanced Technology Development

    NASA Technical Reports Server (NTRS)

    Reeves, John D. Jr.; Kayat, Kamal A.; Lim, Evan

    2008-01-01

    This paper discusses a methodology and modeling capability that probabilistically evaluates the likelihood and impacts of delays in advanced technology development prior to the start of design, development, test, and evaluation (DDT&E) of complex space systems. The challenges of understanding and modeling advanced technology development considerations are first outlined, followed by a discussion of the problem in the context of lunar surface architecture analysis. The current and planned methodologies to address the problem are then presented along with sample analyses and results. The methodology discussed herein provides decision-makers a thorough understanding of the schedule impacts resulting from the inclusion of various enabling advanced technology assumptions within system design.

  11. Solar Electric Propulsion Technology Development for Electric Propulsion

    NASA Technical Reports Server (NTRS)

    Mercer, Carolyn R.; Kerslake, Thomas W.; Scheidegger, Robert J.; Woodworth, Andrew A.; Lauenstein, Jean-Marie

    2015-01-01

    NASA is developing technologies to prepare for human exploration missions to Mars. Solar electric propulsion (SEP) systems are expected to enable a new cost effective means to deliver cargo to the Mars surface. Nearer term missions to Mars moons or near-Earth asteroids can be used to both develop and demonstrate the needed technology for these future Mars missions while demonstrating new capabilities in their own right. This presentation discusses recent technology development accomplishments for high power, high voltage solar arrays and power management that enable a new class of SEP missions.

  12. Large Deployable Reflector (LDR) system concept and technology definition study. Volume 2: Technology assessment and technology development plan

    NASA Astrophysics Data System (ADS)

    Agnew, Donald L.; Jones, Peter A.

    1989-04-01

    A study was conducted to define reasonable and representative LDR system concepts for the purpose of defining a technology development program aimed at providing the requisite technological capability necessary to start LDR development by the end of 1991. This volume presents thirteen technology assessments and technology development plans, as well as an overview and summary of the LDR concepts. Twenty-two proposed augmentation projects are described (selected from more than 30 candidates). The five LDR technology areas most in need of supplementary support are: cryogenic cooling; astronaut assembly of the optically precise LDR in space; active segmented primary mirror; dynamic structural control; and primary mirror contamination control. Three broad, time-phased, five-year programs were synthesized from the 22 projects, scheduled, and funding requirements estimated.

  13. Large Deployable Reflector (LDR) system concept and technology definition study. Volume 2: Technology assessment and technology development plan

    NASA Technical Reports Server (NTRS)

    Agnew, Donald L.; Jones, Peter A.

    1989-01-01

    A study was conducted to define reasonable and representative LDR system concepts for the purpose of defining a technology development program aimed at providing the requisite technological capability necessary to start LDR development by the end of 1991. This volume presents thirteen technology assessments and technology development plans, as well as an overview and summary of the LDR concepts. Twenty-two proposed augmentation projects are described (selected from more than 30 candidates). The five LDR technology areas most in need of supplementary support are: cryogenic cooling; astronaut assembly of the optically precise LDR in space; active segmented primary mirror; dynamic structural control; and primary mirror contamination control. Three broad, time-phased, five-year programs were synthesized from the 22 projects, scheduled, and funding requirements estimated.

  14. Trajectory and Aeroheating Environment Development and Sensitivity Analysis for Capsule-shaped Vehicles

    NASA Technical Reports Server (NTRS)

    Robinson, Jeffrey S.; Wurster, Kathryn E.

    2006-01-01

    Recently, NASA's Exploration Systems Research and Technology Project funded several tasks that endeavored to develop and evaluate various thermal protection systems and high temperature material concepts for potential use on the crew exploration vehicle. In support of these tasks, NASA Langley's Vehicle Analysis Branch generated trajectory information and associated aeroheating environments for more than 60 unique entry cases. Using the Apollo Command Module as the baseline entry system because of its relevance to the favored crew exploration vehicle design, trajectories for a range of lunar and Mars return, direct and aerocapture Earth-entry scenarios were developed. For direct entry, a matrix of cases was created that reflects reasonably expected minimum and maximum values of vehicle ballistic coefficient, inertial velocity at entry interface, and inertial flight path angle at entry interface. For aerocapture, trajectories were generated for a range of values of initial velocity and ballistic coefficient that, when combined with proper initial flight path angles, resulted in achieving a low Earth orbit either by employing a full lift vector up or full lift vector down attitude. For each trajectory generated, aeroheating environments were generated which were intended to bound the thermal protection system requirements for likely crew exploration vehicle concepts. The trades examined clearly pointed to a range of missions / concepts that will require ablative systems as well as a range for which reusable systems may be feasible. In addition, the results clearly indicated those entry conditions and modes suitable for manned flight, considering vehicle deceleration levels experienced during entry. This paper presents an overview of the analysis performed, including the assumptions, methods, and general approach used, as well as a summary of the trajectory and aerothermal environment information that was generated.

  15. Development of cooling technologies for SMES

    NASA Astrophysics Data System (ADS)

    Hirano, Naoki; Watanabe, Tomonori; Nagaya, Shigeo

    2016-12-01

    A Superconducting Magnetic Energy Storage (SMES) system has good characteristics as energy storage equipment in electric power systems such as high efficiency, quick response and no deterioration in repetition operation. Since 1991, the Agency for National Resources and Energy Japan has carried out a national project to develop an SMES for power control in power systems. Moreover, SMES has been developed to bridge for instantaneous voltage dips since 2003. A field test of 5 MVA SMES for bridging instantaneous voltage dips was carried out on an advanced large liquid crystal TV plant in Kameyama from July 2003. Before that, a 10 MVA SMES system was working there. After the field test, the commercial SMES for instantaneous voltage dips is working there. In 2015, three commercial SMES units for bridging instantaneous voltage dips are operating in Japan. These SMESs are all equipped with metal superconducting coils. When considering cost-reduction, size-reduction, and maintenance of the SMES in the future, it is necessary to develop a SMES with a high-temperature superconductor and improve the efficiency of its cooling system. We have also developed and conducted operation tests of SMES with a Bi2212 oxide superconductor and high performance cryocooler which enable energy conservation operation by inverter control. In this paper, developed results on cooling systems and cryocooler for SMES are presented.

  16. Status of molten carbonate fuel cell technology development

    NASA Astrophysics Data System (ADS)

    Parsons, E. L., Jr.; Williams, M. C.; George, T. J.

    The MCFC technology has been identified by the DOE as a promising product for commercialization. Development of the MCFC technology supports the National Energy Strategy. Review of the status of the MCFC technology indicates that the MCFC technology developers are making rapid and significant progress. Manufacturing facility development and extensive testing is occurring. Improvements in performance (power density), lower costs, improved packaging, and scale up to full height are planned. MCFC developers need to continue to be responsive to end-users in potential markets. It will be market demands for the correct product definition which will ultimately determine the character of MCFC power plants. There is a need for continued MCFC product improvement and multiple product development tests.

  17. Tank waste processing and disposal technology development data summary

    SciTech Connect

    Cruse, J.M.; McGinnis, C.P.

    1994-01-01

    The US Department of Energy`s Waste Management and Technology Development Programs are engaged in a number of projects to develop, demonstrate, test, and evaluate new technologies to support the clean-up and site remediation of more than 300 underground storage tanks containing over 381,000 cubic meters (100 million gallons) of radioactive mixed waste. Significant development is needed within primary processing functions and in determining an overall bounding strategy. This document is a first attempt to summarize the overall strategy and show technology development activities within the strategy. It is intended to serve as an information resource to support understanding, decision making and integration of multiple program technology development activities. Recipients are encouraged to provide comments and input to the authors for incorporation in future revisions.

  18. Flywheel Energy Storage Technology Being Developed

    NASA Technical Reports Server (NTRS)

    Wolff, Frederick J.

    2001-01-01

    A flywheel energy storage system was spun to 60,000 rpm while levitated on magnetic bearings. This system is being developed as an energy-efficient replacement for chemical battery systems. Used in groups, the flywheels can have two functions providing attitude control for a spacecraft in orbit as well as providing energy storage. The first application for which the NASA Glenn Research Center is developing the flywheel is the International Space Station, where a two-flywheel system will replace one of the nickel-hydrogen battery strings in the space station's power system. The 60,000-rpm development rotor is about one-eighth the size that will be needed for the space station (0.395 versus 3.07 kWhr).

  19. Extravehicular Space Suit Bearing Technology Development Research

    NASA Astrophysics Data System (ADS)

    Pang, Yan; Liu, Xiangyang; Guanghui, Xie

    2017-03-01

    Pressure bearing has been acting an important role in the EVA (extravehicular activity) suit as a main mobility component. EVA suit bearing has its unique traits on the material, dustproof design, seal, interface, lubrication, load and performance. This paper states the peculiarity and development of the pressure bearing on the construction design element, load and failure mode, and performance and test from the point view of structure design. The status and effect of EVA suit pressure bearing is introduced in the paper. This analysis method can provide reference value for our country’s EVA suit pressure bearing design and development.

  20. Advanced Space Radiation Detector Technology Development

    NASA Technical Reports Server (NTRS)

    Wrbanek, John D.; Wrbanek, Susan Y.; Fralick, Gustave C.

    2013-01-01

    The advanced space radiation detector development team at NASA Glenn Research Center (GRC) has the goal of developing unique, more compact radiation detectors that provide improved real-time data on space radiation. The team has performed studies of different detector designs using a variety of combinations of solid-state detectors, which allow higher sensitivity to radiation in a smaller package and operate at lower voltage than traditional detectors. Integration of multiple solid-state detectors will result in an improved detector system in comparison to existing state-of-the-art (SOA) instruments for the detection and monitoring of the space radiation field for deep space and aerospace applications.