Sample records for magnetic launch assist

  1. Magnetic Launch Assist System Demonstration

    NASA Technical Reports Server (NTRS)

    1999-01-01

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

  2. Magnetic Launch Assist Demonstration Test

    NASA Technical Reports Server (NTRS)

    2001-01-01

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

  3. Magnetic Launch Assist System-Artist's Concept

    NASA Technical Reports Server (NTRS)

    1999-01-01

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

  4. Magnetic Launch Assist Experimental Track

    NASA Technical Reports Server (NTRS)

    1999-01-01

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

  5. Magnetic Launch Assist Vehicle-Artist's Concept

    NASA Technical Reports Server (NTRS)

    1999-01-01

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

  6. Magnetic Launch Assist System Demonstration Test

    NASA Technical Reports Server (NTRS)

    2001-01-01

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

  7. Tabletop Experimental Track for Magnetic Launch Assist

    NASA Technical Reports Server (NTRS)

    2000-01-01

    Marshall Space Flight Center's (MSFC's) Advanced Space Transportation Program has developed the Magnetic Launch Assist System, formerly known as the Magnetic Levitation (MagLev) technology that could give a space vehicle a running start to break free from Earth's gravity. A Magnetic Launch Assist system would use magnetic fields to levitate and accelerate a vehicle along a track at speeds up to 600 mph. The vehicle would shift to rocket engines for launch into orbit. Similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway, a Magnetic Launch Assist system would electromagnetically propel a space vehicle along the track. The tabletop experimental track for the system shown in this photograph is 44-feet long, with 22-feet of powered acceleration and 22-feet of passive braking. A 10-pound carrier with permanent magnets on its sides swiftly glides by copper coils, producing a levitation force. The track uses a linear synchronous motor, which means the track is synchronized to turn the coils on just before the carrier comes in contact with them, and off once the carrier passes. Sensors are positioned on the side of the track to determine the carrier's position so the appropriate drive coils can be energized. MSFC engineers have conducted tests on the indoor track and a 50-foot outdoor track. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  8. Artist's Concept of Magnetic Launch Assisted Air-Breathing Rocket

    NASA Technical Reports Server (NTRS)

    1999-01-01

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

  9. Magnetic Launch Assist

    NASA Technical Reports Server (NTRS)

    Jacobs, W. A.

    2000-01-01

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

  10. Magnetic Launch Assist: NASA's Vision for the Future

    NASA Technical Reports Server (NTRS)

    Jacobs, William A.; Montenegro, Justino (Technical Monitor)

    2000-01-01

    With the ever-increasing cost of getting to space and the need for safe, reliable, and inexpensive ways to access space. The National Aeronautics and Space Administration (NASA) is taking a look at technologies that will get us there. One of these technologies is Magnetic Launch Assist (MagLev). This is the concept of using both magnetic levitation and magnetic propulsion to provide an initial velocity by using electrical power from ground sources. The use of ground generated electricity can significantly reduce operational costs over the consumables necessary to attain the same velocity. The technologies to accomplish this are both old and new. The concept of MagLev has been around for a long time and several MagLev Trains have been developed. Where NASA's MagLev diverges from the traditional train is in the immense amount of power required to propel this vehicle to 183 meters per second in less than 10 seconds. New technologies or the upgrade of existing technologies will need to be investigated in the areas of energy storage and power switching. An added difficulty is the separation of a very large mass (the space vehicle) from the track and the aerodynamics of that vehicle while on the track. These are of great concern and require considerable study and testing. NASA's plan is to mature these technologies in the next 25 years to achieve our goal of launching a full sized space vehicle for under $300 a kilogram.

  11. Developments in Understanding Stability as Applied to Magnetic Levitated Launch Assist

    NASA Technical Reports Server (NTRS)

    Gering, James A.

    2002-01-01

    Magnetic levitation is a promising technology, with the potential of constituting the first stage of a third generation space transportation system. Today, the Space Shuttle burns on the order of one million pounds of solid rocket propellant to bring the orbiter and external tank to nearly Mach 1 (1,000 kph). Imagine the reductions in launch vehicle weight, complexity and risk if an aerospace vehicle could be accelerated to the same speed utilizing about $1,000 of off-board electrical energy stored in flywheels. After over two decades of development, maglev trains travel on full-scale demonstration tracks in Germany and Japan reaching speeds approaching 500 kph. Encouraging as this may appear, the energy and power required to accelerate a 1 million pound launch vehicle to 1,000 kph would radically redefine the state-of-the-art in electrical energy storage and delivery. Reaching such a goal will require levitation with sufficient stability to withstand an operating environment fundamentally different from that of a high-speed train. Recently NASA let contracts for the construction of three maglev demonstration tracks. This construction and several associated trade studies represent a first-order investigation into the feasibility of maglev launch assist. This report provides a review of these efforts, other government sponsored maglev projects and additional technical literature pertinent to maglev stability. This review brings to light details and dimensions of the maglev stability problem which are not found in previous NASA-sponsored trade studies and which must be addressed in order to realize magnetic levitation as a launch assist technology.

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

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

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

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

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

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

  14. Aero-Assisted Pre-Stage for Ballistic and Aero-Assisted Launch Vehicles

    NASA Technical Reports Server (NTRS)

    Ustinov, Eugene A.

    2012-01-01

    A concept of an aero-assisted pre-stage is proposed, which enables launch of both ballistic and aero-assisted launch vehicles from conventional runways. The pre-stage can be implemented as a delta-wing with a suitable undercarriage, which is mated with the launch vehicle, so that their flight directions are coaligned. The ample wing area of the pre-stage combined with the thrust of the launch vehicle ensure prompt roll-out and take-off of the stack at airspeeds typical for a conventional jet airliner. The launch vehicle is separated from the pre-stage as soon as safe altitude is achieved, and the desired ascent trajectory is reached. Nominally, the pre-stage is non-powered. As an option, to save the propellant of the launch vehicle, the pre-stage may have its own short-burn propulsion system, whereas the propulsion system of the launch vehicle is activated at the separation point. A general non-dimensional analysis of performance of the pre-stage from roll-out to separation is carried out and applications to existing ballistic launch vehicle and hypothetical aero-assisted vehicles (spaceplanes) are considered.

  15. Closed End Launch Tube (CELT)

    NASA Technical Reports Server (NTRS)

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

    2000-01-01

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

  16. Hot Water Propulsion for Horizontal Rocket Assisted Take-Off Systems for Future Reusable Launch Vehicles

    NASA Astrophysics Data System (ADS)

    Pilz, N.; Adirim, H.; Lo, R.; Schildknecht, A.

    2004-10-01

    Among other concepts, reusable space transportation systems that comprise winged reusable launch vehicles (RLV) with horizontal take-off and horizontal landing (HTHL) are under worldwide investigation, e.g. the respective concepts within ESA's FESTIP-Study (Future European Space Transportation Integration Program) or the HOPPER concept by EADS-ST. The payload of these RLVs could be significantly increased by means of a ground-based take-off assistance system that would accelerate the vehicle along a horizontal track until it reaches the desired speed to ignite its onboard engines for leaving the ground and launching into orbit. This paper illustrates the advantages of horizontal take-off for winged RLVs and provides an overview of launch-assist options for HTHL RLVs. It presents hot water propulsion for ground-based take-off assistance systems for future RLVs as an attractive choice besides magnetic levitation and acceleration (maglev) technology. Finally, preliminary design concepts are presented for a rocket assisted take-off system (RATOS) with hot water propulsion followed by an analysis of its improvement potential.

  17. The Feasibility of Railgun Horizontal-Launch Assist

    NASA Technical Reports Server (NTRS)

    Youngquist, Robert C.; Cox, Robert B.

    2011-01-01

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

  18. Preliminary Design of a Ramjet for Integration with Ground-Based Launch Assist

    NASA Technical Reports Server (NTRS)

    Sayles, Emily L.

    2008-01-01

    This viewgraph presentation reviews the preliminary design of a ramjet for integration with a ground based launch assist. The reasons for the use of ground-based launch assist and the proposed mechanism for a system are reviewed. The use of a Optimal Trajectory by Implicit Simulation (OTIS), to model the flight and comparison with an actual rocket trajectory is given. The OTIS system is reviewed, The benefits of a launch assist system are analyzed concluding that a launch assist can provide supersonic speeds thus allowing ignition of ramjet without an onboard compressor. This means a further reduction in total launch weight. The Ramjet study is reviewed next. This included a review of the ONX simulations, the verification of the ONX results with the use of Holloman Sled experiment data as derived from the Feasibility of Ramjet Engine Test Capability on The Holloman AFB Sled Track. The conclusion was that the ONX system was not sufficient to meet the needs for the modeling required. The GECAT (Graphical Engine Cycle Analysis Tool) is examined. The results of the GECAT simulations was verified with data from Stataltex and D21 flights. The Next steps are: to create a GECAT Model of a launch assist ramjet, to adjust the geometry to produce the desired thrust, and to survey the ramjet's performance over a range of Mach numbers. The assumptions and requirements of a launch assist ramjet are given, and the acceptable flight regimes are reviewed.

  19. Throttleable GOX/ABS launch assist hybrid rocket motor for small scale air launch platform

    NASA Astrophysics Data System (ADS)

    Spurrier, Zachary S.

    Aircraft-based space-launch platforms allow operational flexibility and offer the potential for significant propellant savings for small-to-medium orbital payloads. The NASA Armstrong Flight Research Center's Towed Glider Air-Launch System (TGALS) is a small-scale flight research project investigating the feasibility for a remotely-piloted, towed, glider system to act as a versatile air launch platform for nano-scale satellites. Removing the crew from the launch vehicle means that the system does not have to be human rated, and offers a potential for considerable cost savings. Utah State University is developing a small throttled launch-assist system for the TGALS platform. This "stage zero" design allows the TGALS platform to achieve the required flight path angle for the launch point, a condition that the TGALS cannot achieve without external propulsion. Throttling is required in order to achieve and sustain the proper launch attitude without structurally overloading the airframe. The hybrid rocket system employs gaseous-oxygen and acrylonitrile butadiene styrene (ABS) as propellants. This thesis summarizes the development and testing campaign, and presents results from the clean-sheet design through ground-based static fire testing. Development of the closed-loop throttle control system is presented.

  20. 3-D MHD modeling and stability analysis of jet and spheromak plasmas launched into a magnetized plasma

    NASA Astrophysics Data System (ADS)

    Fisher, Dustin; Zhang, Yue; Wallace, Ben; Gilmore, Mark; Manchester, Ward; Arge, C. Nick

    2016-10-01

    The Plasma Bubble Expansion Experiment (PBEX) at the University of New Mexico uses a coaxial plasma gun to launch jet and spheromak magnetic plasma configurations into the Helicon-Cathode (HelCat) plasma device. Plasma structures launched from the gun drag frozen-in magnetic flux into the background magnetic field of the chamber providing a rich set of dynamics to study magnetic turbulence, force-free magnetic spheromaks, and shocks. Preliminary modeling is presented using the highly-developed 3-D, MHD, BATS-R-US code developed at the University of Michigan. BATS-R-US employs an adaptive mesh refinement grid that enables the capture and resolution of shock structures and current sheets, and is particularly suited to model the parameter regime under investigation. CCD images and magnetic field data from the experiment suggest the stabilization of an m =1 kink mode trailing a plasma jet launched into a background magnetic field. Results from a linear stability code investigating the effect of shear-flow as a cause of this stabilization from magnetic tension forces on the jet will be presented. Initial analyses of a possible magnetic Rayleigh Taylor instability seen at the interface between launched spheromaks and their entraining background magnetic field will also be presented. Work supported by the Army Research Office Award No. W911NF1510480.

  1. Geostationary orbits from mid-latitude launch sites via lunar gravity assist

    NASA Astrophysics Data System (ADS)

    Graziani, F.; Castronuovo, M. M.; Teofilatto, P.

    The out-of-plane maneuver, necessary to acquire a geostationary orbit from launch sites that are at some degrees of latitude, makes the cost of such a mission very high. In this paper, we present a trajectory design for reaching a geostationary orbit from a mid-latitude launch base, with a consistent saving of propellant. This has been obtained using a lunar gravity assist (g.a.) to change the high inclination of the satellite orbit and, at the same time, to raise the perigee to the geosynchronous height. The Moon g.a. has been designed, describing the physical process by means of Opik's method. This is an analytical approximation technique which allows computation of outcome of planetary close encounters in a simple, but accurate, way. The trajectory resulting from this preliminary study has been used as a starting point for a numerical integration, using Everhart's integrator RADAU. We considered also the launch from Cape Canaveral (28.5 deg North), finding a small saving of V. The mission sequences are described and compared to other traditional trajectory designs.

  2. Dynamics of Magnetized Plasma Jets and Bubbles Launched into a Background Magnetized Plasma

    NASA Astrophysics Data System (ADS)

    Wallace, B.; Zhang, Y.; Fisher, D. M.; Gilmore, M.

    2016-10-01

    The propagation of dense magnetized plasma, either collimated with mainly azimuthal B-field (jet) or toroidal with closed B-field (bubble), in a background plasma occurs in a number of solar and astrophysical cases. Such cases include coronal mass ejections moving in the background solar wind and extragalactic radio lobes expanding into the extragalactic medium. Understanding the detailed MHD behavior is crucial for correctly modeling these events. In order to further the understanding of such systems, we are investigating the injection of dense magnetized jets and bubbles into a lower density background magnetized plasma using a coaxial plasma gun and a background helicon or cathode plasma. In both jet and bubble cases, the MHD dynamics are found to be very different when launched into background plasma or magnetic field, as compared to vacuum. In the jet case, it is found that the inherent kink instability is stabilized by velocity shear developed due to added magnetic tension from the background field. In the bubble case, rather than directly relaxing to a minimum energy Taylor state (spheromak) as in vacuum, there is an expansion asymmetry and the bubble becomes Rayleigh-Taylor unstable on one side. Recent results will be presented. Work supported by the Army Research Office Award No. W911NF1510480.

  3. Observations and modeling of magnetized plasma jets and bubbles launched into a transverse B-field

    NASA Astrophysics Data System (ADS)

    Fisher, Dustin M.; Zhang, Yue; Wallace, Ben; Gilmore, Mark; Manchester, Ward B., IV; van der Holst, Bart; Rogers, Barrett N.; Hsu, Scott C.

    2017-10-01

    Hot, dense, plasma structures launched from a coaxial plasma gun on the HelCat dual-source plasma device at the University of New Mexico drag frozen-in magnetic flux into the chamber's background magnetic field providing a rich set of dynamics to study magnetic turbulence, force-free magnetic spheromaks, shocks, as well as CME-like dynamics possibly relevant to the solar corona. Vector magnetic field data from an eleven-tipped B-dot rake probe and images from an ultra-fast camera will be presented in comparison with ongoing MHD modeling using the 3-D MHD BATS-R-US code developed at the University of Michigan. BATS-R-US employs an adaptive mesh refinement grid (AMR) that enables the capture and resolution of shock structures and current sheets and is uniquely suited for flux-rope expansion modeling. Recent experiments show a possible magnetic Rayleigh-Taylor (MRT) instability that appears asymmetrically at the interface between launched spheromaks (bubbles) and their entraining background magnetic field. Efforts to understand this instability using in situ measurements, new chamber boundary conditions, and ultra-fast camera data will be presented. Work supported by the Army Research Office Award No. W911NF1510480.

  4. Blazar Variability from Turbulence in Jets Launched by Magnetically Arrested Accretion Flows

    NASA Astrophysics Data System (ADS)

    O' Riordan, Michael; Pe'er, Asaf; McKinney, Jonathan C.

    2017-07-01

    Blazars show variability on timescales ranging from minutes to years, the former being comparable to and in some cases even shorter than the light-crossing time of the central black hole. The observed γ-ray light curves can be described by a power-law power density spectrum (PDS), with a similar index for both BL Lacs and flat-spectrum radio quasars. We show that this variability can be produced by turbulence in relativistic jets launched by magnetically arrested accretion flows (MADs). We perform radiative transport calculations on the turbulent, highly magnetized jet launching region of a MAD with a rapidly rotating supermassive black hole. The resulting synchrotron and synchrotron self-Compton emission, originating from close to the black hole horizon, is highly variable. This variability is characterized by PDS, which is remarkably similar to the observed power-law spectrum at frequencies less than a few per day. Furthermore, turbulence in the jet launching region naturally produces fluctuations in the plasma on scales much smaller than the horizon radius. We speculate that similar turbulent processes, operating in the jet at large radii (and therefore a high bulk Lorentz factor), are responsible for blazar variability over many decades in frequency, including on minute timescales.

  5. Blazar Variability from Turbulence in Jets Launched by Magnetically Arrested Accretion Flows

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

    Riordan, Michael O’; Pe’er, Asaf; McKinney, Jonathan C., E-mail: michael_oriordan@umail.ucc.ie

    2017-07-10

    Blazars show variability on timescales ranging from minutes to years, the former being comparable to and in some cases even shorter than the light-crossing time of the central black hole. The observed γ -ray light curves can be described by a power-law power density spectrum (PDS), with a similar index for both BL Lacs and flat-spectrum radio quasars. We show that this variability can be produced by turbulence in relativistic jets launched by magnetically arrested accretion flows (MADs). We perform radiative transport calculations on the turbulent, highly magnetized jet launching region of a MAD with a rapidly rotating supermassive blackmore » hole. The resulting synchrotron and synchrotron self-Compton emission, originating from close to the black hole horizon, is highly variable. This variability is characterized by PDS, which is remarkably similar to the observed power-law spectrum at frequencies less than a few per day. Furthermore, turbulence in the jet launching region naturally produces fluctuations in the plasma on scales much smaller than the horizon radius. We speculate that similar turbulent processes, operating in the jet at large radii (and therefore a high bulk Lorentz factor), are responsible for blazar variability over many decades in frequency, including on minute timescales.« less

  6. Measuring temperature and field profiles in heat assisted magnetic recording

    NASA Astrophysics Data System (ADS)

    Hohlfeld, J.; Zheng, X.; Benakli, M.

    2015-08-01

    We introduce a theoretical and experimental framework that enables quantitative measurements of the temperature and magnetic field profiles governing the thermo-magnetic write process in heat assisted magnetic recording. Since our approach allows the identification of the correct temperature dependence of the magneto-crystalline anisotropy field in the vicinity of the Curie point as well, it provides an unprecedented experimental foundation to assess our understanding of heat assisted magnetic recording.

  7. Effects of head field and AC field on magnetization reversal for microwave assisted magnetic recording

    NASA Astrophysics Data System (ADS)

    Kase, Aina; Akagi, Fumiko; Yoshida, Kazuetsu

    2018-05-01

    Microwave assisted magnetic recording (MAMR) is a promising recording method for achieving high recording densities in hard disk drives. In MAMR, the AC field from a spin-torque oscillator (STO) assists the head field with magnetization reversal in a medium. Therefore, the relationship between the head field and the AC field is very important. In this study, the effects of the head field and the AC field on magnetization reversal were analyzed using a micromagnetic simulator that takes the magnetic interactions between a single-pole type (SPT) write-head, an exchange coupled composite (ECC) medium, and the STO into account. As a result, the magnetization reversal was assisted not just by the y-component of the AC field (Hstoy) but also by the y-component of the head field (Hhy) in the medium. The Hhy over 100 kA/m with a frequency of about 15.5 GHz induced the magnetic resonance. The large Hhy was produced by the field from the STO to the SPT head.

  8. Space Shuttle Discovery Launch

    NASA Image and Video Library

    2008-05-31

    NASA Shuttle Launch Director Michael Leinbach, left, STS-124 Assistant Launch Director Ed Mango, center, and Flow Director for Space Shuttle Discovery Stephanie Stilson clap in the the Launch Control Center after the main engine cut off and successful launch of the Space Shuttle Discovery (STS-124) Saturday, May 31, 2008, at the Kennedy Space Center in Cape Canaveral, Fla. The Shuttle lifted off from launch pad 39A at 5:02 p.m. EDT. Photo Credit: (NASA/Bill Ingalls)

  9. Zero field reversal probability in thermally assisted magnetization reversal

    NASA Astrophysics Data System (ADS)

    Prasetya, E. B.; Utari; Purnama, B.

    2017-11-01

    This paper discussed about zero field reversal probability in thermally assisted magnetization reversal (TAMR). Appearance of reversal probability in zero field investigated through micromagnetic simulation by solving stochastic Landau-Lifshitz-Gibert (LLG). The perpendicularly anisotropy magnetic dot of 50×50×20 nm3 is considered as single cell magnetic storage of magnetic random acces memory (MRAM). Thermally assisted magnetization reversal was performed by cooling writing process from near/almost Curie point to room temperature on 20 times runs for different randomly magnetized state. The results show that the probability reversal under zero magnetic field decreased with the increase of the energy barrier. The zero-field probability switching of 55% attained for energy barrier of 60 k B T and the reversal probability become zero noted at energy barrier of 2348 k B T. The higest zero-field switching probability of 55% attained for energy barrier of 60 k B T which corespond to magnetif field of 150 Oe for switching.

  10. Launch and capture of a single particle in a pulse-laser-assisted dual-beam fiber-optic trap

    NASA Astrophysics Data System (ADS)

    Fu, Zhenhai; She, Xuan; Li, Nan; Hu, Huizhu

    2018-06-01

    The rapid loading and manipulation of microspheres in optical trap is important for its applications in optomechanics and precision force sensing. We investigate the microsphere behavior under coaction of a dual-beam fiber-optic trap and a pulse laser beam, which reveals a launched microsphere can be effectively captured in a spatial region. A suitable order of pulse duration for launch is derived according to the calculated detachment energy threshold of pulse laser. Furthermore, we illustrate the effect of structural parameters on the launching process, including the spot size of pulse laser, the vertical displacement of beam waist and the initial position of microsphere. Our result will be instructive in the optimal design of the pulse-laser-assisted optical tweezers for controllable loading mechanism of optical trap.

  11. STS-87 Mission Specialist Chawla is assisted with her launch and entry spacesuit at LC 39B during TC

    NASA Technical Reports Server (NTRS)

    1997-01-01

    STS-87 Mission Specialist Kalpana Chawla, Ph.D., is assisted with her orange launch and entry spacesuit by NASA suit technicians at Launch Pad 39B during Terminal Countdown Demonstration Test (TCDT) activities. The crew of the STS-87 mission is scheduled for launch Nov. 19 aboard the Space Shuttle Columbia. The TCDT is held at KSC prior to each Space Shuttle flight providing the crew of each mission opportunities to participate in simulated countdown activities. The TCDT ends with a mock launch countdown culminating in a simulated main engine cut-off. The crew also spends time undergoing emergency egress training exercises at the pad and has an opportunity to view and inspect the payloads in the orbiter's payload bay.

  12. Magnetically Assisted Bilayer Composites for Soft Bending Actuators.

    PubMed

    Jang, Sung-Hwan; Na, Seon-Hong; Park, Yong-Lae

    2017-06-12

    This article presents a soft pneumatic bending actuator using a magnetically assisted bilayer composite composed of silicone polymer and ferromagnetic particles. Bilayer composites were fabricated by mixing ferromagnetic particles to a prepolymer state of silicone in a mold and asymmetrically distributed them by applying a strong non-uniform magnetic field to one side of the mold during the curing process. The biased magnetic field induces sedimentation of the ferromagnetic particles toward one side of the structure. The nonhomogeneous distribution of the particles induces bending of the structure when inflated, as a result of asymmetric stiffness of the composite. The bilayer composites were then characterized with a scanning electron microscopy and thermogravimetric analysis. The bending performance and the axial expansion of the actuator were discussed for manipulation applications in soft robotics and bioengineering. The magnetically assisted manufacturing process for the soft bending actuator is a promising technique for various applications in soft robotics.

  13. Magnetically Assisted Bilayer Composites for Soft Bending Actuators

    PubMed Central

    Jang, Sung-Hwan; Na, Seon-Hong; Park, Yong-Lae

    2017-01-01

    This article presents a soft pneumatic bending actuator using a magnetically assisted bilayer composite composed of silicone polymer and ferromagnetic particles. Bilayer composites were fabricated by mixing ferromagnetic particles to a prepolymer state of silicone in a mold and asymmetrically distributed them by applying a strong non-uniform magnetic field to one side of the mold during the curing process. The biased magnetic field induces sedimentation of the ferromagnetic particles toward one side of the structure. The nonhomogeneous distribution of the particles induces bending of the structure when inflated, as a result of asymmetric stiffness of the composite. The bilayer composites were then characterized with a scanning electron microscopy and thermogravimetric analysis. The bending performance and the axial expansion of the actuator were discussed for manipulation applications in soft robotics and bioengineering. The magnetically assisted manufacturing process for the soft bending actuator is a promising technique for various applications in soft robotics. PMID:28773007

  14. Vibration measurements and analyses for a magnet superconductor levitated system

    NASA Astrophysics Data System (ADS)

    Wen, Zheng; Liu, Yu; Yang, Wenjiang; Qiu, Ming

    2007-12-01

    Magnetic levitation technology, having the characteristics of low cost and high quality, has been considered a preferable option for the next generation of launcher systems. A world-wide research design on the conceptual level has been carried out on the highly reusable space transportation systems by applying magnetic levitation to the launch assistance. Recently, a research plan has been implemented in our laboratory by constructing a scale-model suspension system with high temperature superconductor (HTS henceforth) bulks over a 7 m Nd-Fe-B permanent-magnet (PM henceforth) track for the launch assistance. An experimental platform was built to investigate the dynamic responses of the PM-HTS interaction at different field-cooled positions. The critical frequencies and amplitudes which lead to the instability of levitation drift were investigated. The stiffness and the vibration damping were also discussed at the zero-field-cooled position.

  15. Unidirectional edge modes launched by surface fluctuation in magnetic metamaterials

    NASA Astrophysics Data System (ADS)

    Chen, Huajin; Luo, Youzhu; Liang, Chenghua; Li, Zhenglin; Liu, Shiyang; Lin, Zhifang

    2018-03-01

    We demonstrate theoretically that the surface fluctuation can be used to launch the unidirectional electromagnetic edge mode for a Gaussian beam incident normal to the magnetic metamaterials (MMs) composed of an array of ferrite rods with the uppermost layer introduced position or size fluctuation in the coupling region. Such an edge mode is solely allowed to propagate in one direction due to the time-reversal symmetry breaking in MMs under the exertion of an external magnetic field, and it is substantially enhanced by the magnetic surface plasmon resonance. The nonreciprocal excitation of the edge states can also be understood by examining the scattering amplitudes of different partial waves, which indicate that the 1st order of the angular momentum channel plays a crucial role in realizing the nonreciprocity. The present research might be significant for the implementation of unidirectional absorption and the reexamination of bound states in the continuum in the context of MMs. In addition, the unique optical property can be exploited to design electromagnetic waveguide devices, such as one-way waveguide and wave bender, which are strongly robust against the obstacles placed in the channel of designed devices, facilitating to realize optical integrated circuits.

  16. Launch Services Safety Overview

    NASA Technical Reports Server (NTRS)

    Loftin, Charles E.

    2008-01-01

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

  17. Noncollinear magnetic order induced by Dzyaloshinskii-Moriya interaction in oxygen-assisted Pt nanojunctions

    NASA Astrophysics Data System (ADS)

    Yuan, J. R.; Yan, X. H.; Xiao, Y.; Guo, Y. D.; Dai, C. J.

    2016-11-01

    Motivated by recent measurement of the magnetism and conductance of the oxygen-assisted Pt nanojunctions, we performed first principle calculations of the magnetic order and electronic transport by explicitly including fully relativistic effects. Our results show that the spin alignment is a cycloidal spiral feature attributed to the Dzyaloshinskii-Moriya interaction, which indicates that the observed magnetism in experiments is of noncollinear nature. The oxygen concentration is the responsible for the switching of the rotational sense of the spiral magnetic order found in oxygen-assisted Pt nanojunctions. Furthermore, the magnetic moments and magnetoresistances vary with oxygen concentration in the chain, which can be used to tune the magnetism and magnetotransport. The oxygen-assisted Pt nanojunctions offer a possibility for spintronic applications in magnetic memory and quantum devices.

  18. Magnetic-Field-Assisted Assembly of Ordered Multifunctional Ceramic Nanocomposites for Extreme Environments

    DTIC Science & Technology

    2016-04-01

    SUBJECT TERMS carbon nanotubes, composite, electromagnetic shielding , extreme environments, magnetism , fibers, woven composite, boron nitride...AFRL-AFOSR-VA-TR-2016-0158 Magnetic -Field-Assisted Assembly of Ordered Multifunctional Ceramic Nanocomposites for Extreme Environments Konstantin...From - To) 15 Sep 2012 to 14 Nov 2017 4. TITLE AND SUBTITLE Magnetic -Field-Assisted Assembly of Ordered Multifunctional Ceramic Nanocomposites for

  19. 34 CFR 280.1 - What is the Magnet Schools Assistance Program?

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... 34 Education 1 2011-07-01 2011-07-01 false What is the Magnet Schools Assistance Program? 280.1 Section 280.1 Education Regulations of the Offices of the Department of Education OFFICE OF ELEMENTARY AND SECONDARY EDUCATION, DEPARTMENT OF EDUCATION MAGNET SCHOOLS ASSISTANCE PROGRAM General § 280.1 What is the...

  20. 34 CFR 280.1 - What is the Magnet Schools Assistance Program?

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... 34 Education 1 2010-07-01 2010-07-01 false What is the Magnet Schools Assistance Program? 280.1 Section 280.1 Education Regulations of the Offices of the Department of Education OFFICE OF ELEMENTARY AND SECONDARY EDUCATION, DEPARTMENT OF EDUCATION MAGNET SCHOOLS ASSISTANCE PROGRAM General § 280.1 What is the...

  1. Assisted Writing in Spin Transfer Torque Magnetic Tunnel Junctions

    NASA Astrophysics Data System (ADS)

    Ganguly, Samiran; Ahmed, Zeeshan; Datta, Supriyo; Marinero, Ernesto E.

    2015-03-01

    Spin transfer torque driven MRAM devices are now in an advanced state of development, and the importance of reducing the current requirement for writing information is well recognized. Different approaches to assist the writing process have been proposed such as spin orbit torque, spin Hall effect, voltage controlled magnetic anisotropy and thermal excitation. In this work,we report on our comparative study using the Spin-Circuit Approach regarding the total energy, the switching speed and energy-delay products for different assisted writing approaches in STT-MTJ devices using PMA magnets.

  2. ARES I-X Launch

    NASA Image and Video Library

    2009-10-27

    NASA Ares I-X Launch Director Ed Mango, left, laughs as NASA Ares I-X Assistant Launch Director Pete Nickolenko looks out the window of Firing Room One of the Launch Control Center (LCC) at the Kennedy Space Center prior to the launch of the Ares I-X rocket from pad 39b at the Kennedy Space Center in Cape Canaveral, Fla., Wednesday, Oct. 28, 2009. The flight test of Ares I-X will provide NASA with an early opportunity to test and prove flight characteristics, hardware, facilities and ground operations associated with the Ares I. Photo Credit: (NASA/Bill Ingalls)

  3. Effect of magnetic polarity on surface roughness during magnetic field assisted EDM of tool steel

    NASA Astrophysics Data System (ADS)

    Efendee, A. M.; Saifuldin, M.; Gebremariam, MA; Azhari, A.

    2018-04-01

    Electrical discharge machining (EDM) is one of the non-traditional machining techniques where the process offers wide range of parameters manipulation and machining applications. However, surface roughness, material removal rate, electrode wear and operation costs were among the topmost issue within this technique. Alteration of magnetic device around machining area offers exciting output to be investigated and the effects of magnetic polarity on EDM remain unacquainted. The aim of this research is to investigate the effect of magnetic polarity on surface roughness during magnetic field assisted electrical discharge machining (MFAEDM) on tool steel material (AISI 420 mod.) using graphite electrode. A Magnet with a force of 18 Tesla was applied to the EDM process at selected parameters. The sparks under magnetic field assisted EDM produced better surface finish than the normal conventional EDM process. At the presence of high magnetic field, the spark produced was squeezed and discharge craters generated on the machined surface was tiny and shallow. Correct magnetic polarity combination of MFAEDM process is highly useful to attain a high efficiency machining and improved quality of surface finish to meet the demand of modern industrial applications.

  4. Patient burden and patient preference: comparing magnetic resonance enteroclysis, capsule endoscopy and balloon-assisted enteroscopy.

    PubMed

    Wiarda, Bart M; Stolk, Mark; Heine, Dimitri G N; Mensink, Peter; Thieme, Mai E; Kuipers, Ernst J; Stoker, Jaap

    2013-03-01

    We aimed to prospectively determine patient burden and patient preference for magnetic resonance enteroclysis, capsule endoscopy and balloon-assisted enteroscopy in patients with suspected or known Crohn's disease (CD) or occult gastrointestinal bleeding (OGIB).  Consecutive consenting patients with CD or OGIB underwent magnetic resonance enteroclysis, capsule endoscopy and balloon-assisted enteroscopy. Capsule endoscopy was only performed if magnetic resonance enteroclysis showed no high-grade small bowel stenosis. Patient preference and burden was evaluated by means of standardized questionnaires at five moments in time. From January 2007 until March 2009, 76 patients were included (M/F 31/45; mean age 46.9 years; range 20.0-78.4 years): 38 patients with OGIB and 38 with suspected or known CD. Seventeen patients did not undergo capsule endoscopy because of high-grade stenosis. Ninety-five percent (344/363) of the questionnaires were suitable for evaluation. Capsule endoscopy was significantly favored over magnetic resonance enteroclysis and balloon-assisted enteroscopy with respect to bowel preparation, swallowing of the capsule (compared to insertion of the tube/scope), burden of the entire examination, duration and accordance with the pre-study information. Capsule endoscopy and magnetic resonance enteroclysis were significantly preferred over balloon-assisted enteroscopy for clarity of explanation of the examination, and magnetic resonance enteroclysis was significantly preferred over balloon-assisted enteroscopy for bowel preparation, painfulness and burden of the entire examination. Balloon-assisted enteroscopy was significantly favored over magnetic resonance enteroclysis for insertion of the scope and procedure duration. Pre- and post-study the order of preference was capsule endoscopy, magnetic resonance enteroclysis and balloon-assisted enteroscopy. Capsule endoscopy was preferred to magnetic resonance enteroclysis and balloon-assisted enteroscopy

  5. Current induced perpendicular-magnetic-anisotropy racetrack memory with magnetic field assistance

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

    Zhang, Y.; Klein, J.-O.; Chappert, C.

    2014-01-20

    High current density is indispensable to shift domain walls (DWs) in magnetic nanowires, which limits the using of racetrack memory (RM) for low power and high density purposes. In this paper, we present perpendicular-magnetic-anisotropy (PMA) Co/Ni RM with global magnetic field assistance, which lowers the current density for DW motion. By using a compact model of PMA RM and 40 nm design kit, we perform mixed simulation to validate the functionality of this structure and analyze its density potential. Stochastic DW motion behavior has been taken into account and statistical Monte-Carlo simulations are carried out to evaluate its reliability performance.

  6. ARES I-X Launch Prep

    NASA Image and Video Library

    2009-10-26

    NASA Ares I-X Assistant Launch Director Pete Nickolenko, left, and NASA Ares I-X Launch Director Ed Mango monitor the launch countdown from Firing Room One of the Launch Control Center (LCC) at the Kennedy Space Center during the planned launch of the Ares I-X rocket from pad 39b at the Kennedy Space Center in Cape Canaveral, Fla., Tuesday, Oct. 27, 2009. The flight test of Ares I-X will provide NASA with an early opportunity to test and prove flight characteristics, hardware, facilities and ground operations associated with the Ares I. Photo Credit: (NASA/Bill Ingalls)

  7. Automated Assistance for Designing Active Magnetic Bearings

    NASA Technical Reports Server (NTRS)

    Imlach, Joseph

    2008-01-01

    MagBear12 is a computer code that assists in the design of radial, heteropolar active magnetic bearings (AMBs). MagBear12 was developed to help in designing the system described in "Advanced Active-Magnetic-Bearing Thrust-Measurement System". Beyond this initial application, MagBear12 is expected to be useful for designing AMBs for a variety of rotating machinery. This program incorporates design rules and governing equations that are also implemented in other, proprietary design software used by AMB manufacturers. In addition, this program incorporates an advanced unpublished fringing-magnetic-field model that increases accuracy beyond that offered by the other AMB-design software.

  8. 42GHz ECRH assisted Plasma Breakdown in tokamak SST-1

    NASA Astrophysics Data System (ADS)

    Shukla, B. K.; Pradhan, S.; Patel, Paresh; Babu, Rajan; Patel, Jatin; Patel, Harshida; Dhorajia, Pragnesh; Tanna, V.; Atrey, P. K.; Manchanda, R.; Gupta, Manoj; Joisa, Shankar; Gupta, C. N.; Danial, Raju; Singh, Prashant; Jha, R.; Bora, D.

    2015-03-01

    In SST-1, 42GHz ECRH system has been commissioned to carry out breakdown and heating experiments at 0.75T and 1.5T operating toroidal magnetic fields. The 42GHz ECRH system consists of high power microwave source Gyrotron capable to deliver 500kW microwave power for 500ms duration, approximately 20 meter long transmission line and a mirror based launcher. The ECRH power in fundamental O-mode & second harmonic X-mode is launched from low field side (radial port) of the tokamak. At 0.75T operation, approximately 300 kW ECH power is launched in second harmonic X-mode and successful ECRH assisted breakdown is achieved at low loop_voltage ~ 3V. The ECRH power is launched around 45ms prior to loop voltage. The hydrogen pressure in tokamak is maintained ~ 1×10-5mbar and the pre-ionized density is ~ 4×1012/cc. At 1.5T operating toroidal magnetic field, the ECH power is launched in fundamental O-mode. The ECH power at fundamental harmonic is varied from 100 kW to 250 kW and successful breakdown is achieved in all ECRH shots. In fundamental harmonic there is no delay in breakdown while at second harmonic ~ 40ms delay is observed, which is normal in case of second harmonic ECRH assisted breakdown.

  9. A study: Effect of Students Peer Assisted Learning on Magnetic Field Achievement

    NASA Astrophysics Data System (ADS)

    Mueanploy, Wannapa

    2016-04-01

    This study is the case study of Physic II Course for students of Pathumwan Institute of Technology. The purpose of this study is: 1) to develop cooperative learning method of peer assisted learning (PAL), 2) to compare the learning achievement before and after studied magnetic field lesson by cooperative learning method of peer assisted learning. The population was engineering students of Pathumwan Institute of Technology (PIT’s students) who registered Physic II Course during year 2014. The sample used in this study was selected from the 72 students who passed in Physic I Course. The control groups learning magnetic fields by Traditional Method (TM) and experimental groups learning magnetic field by method of peers assisted learning. The students do pretest before the lesson and do post-test after the lesson by 20 items achievement tests of magnetic field. The post-test higher than pretest achievement significantly at 0.01 level.

  10. Launch of Space Shuttle Atlantis / STS-129 Mission

    NASA Image and Video Library

    2009-11-16

    STS129-S-058 (16 Nov. 2009) --- In Firing Room 4 of NASA Kennedy Space Center's Launch Control Center, shuttle launch director Michael Leinbach (standing), assistant launch director Peter Nickolenko and Atlantis flow director Angie Brewer (both seated), applaud the launch team upon the successful launch of Space Shuttle Atlantis. Liftoff of Atlantis from Launch Pad 39A on its STS-129 mission to the International Space Station came at 2:28 p.m. (EST) Nov. 16, 2009.

  11. Electrical detection of microwave assisted magnetization reversal by spin pumping

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

    Rao, Siddharth; Subhra Mukherjee, Sankha; Elyasi, Mehrdad

    2014-03-24

    Microwave assisted magnetization reversal has been investigated in a bilayer system of Pt/ferromagnet by detecting a change in the polarity of the spin pumping signal. The reversal process is studied in two material systems, Pt/CoFeB and Pt/NiFe, for different aspect ratios. The onset of the switching behavior is indicated by a sharp transition in the spin pumping voltage. At a threshold value of the external field, the switching process changes from partial to full reversal with increasing microwave power. The proposed method provides a simple way to detect microwave assisted magnetization reversal.

  12. In vitro characterization of a magnetically suspended continuous flow ventricular assist device.

    PubMed

    Kim, H C; Bearnson, G B; Khanwilkar, P S; Olsen, D B; Maslen, E H; Allaire, P E

    1995-01-01

    A magnetically suspended continuous flow ventricular assist device using magnetic bearings was developed aiming at an implantable ventricular assist device. The main advantage of this device includes no mechanical wear and minimal chance of blood trauma such, as thrombosis and hemolysis, because there is no mechanical contact between the stationary and rotating parts. The total system consists of two subsystems: the centrifugal pump and the magnetic bearing. The centrifugal pump is comprised of a 4 vane logarithmic spiral radial flow impeller and a brushless DC motor with slotless stator, driven by the back emf commutation scheme. Two radial and one thrust magnetic bearing that dynamically controls the position of the rotor in a radial and axial direction, respectively, contains magnetic coils, the rotor's position sensors, and feedback electronic control system. The magnetic bearing system was able to successfully suspend a 365.5g rotating part in space and sustain it for up to 5000 rpm of rotation. Average force-current square factor of the magnetic bearing was measured as 0.48 and 0.44 (kg-f/Amp2) for radial and thrust bearing, respectively. The integrated system demonstrated adequate performance in mock circulation tests by providing a 6 L/min flow rate against 100 mmHg differential pressure at 2300 rpm. Based on these in vitro performance test results, long-term clinical application of the magnetically suspended continuous flow ventricular assist device is very promising after system optimization with a hybrid system using both active (electromagnet) and passive (permanent magnets) magnet bearings.

  13. ARES I-X Launch Prep

    NASA Image and Video Library

    2009-10-26

    Mission managers, from left, NASA Ares I-X Assistant Launch Director Pete Nickolenko, Ground Operations Manager Philip "Pepper" Phillips, Ares I-X Launch Director Ed Mango, and Constellation Program manager Jeff Hanley review the latest weather radar from Firing Room One of the Launch Control Center (LCC) at the Kennedy Space Center during the launch countdown of the Ares I-X rocket in Cape Canaveral, Fla., Tuesday, Oct. 27, 2009. The flight test of Ares I-X will provide NASA with an early opportunity to test and prove flight characteristics, hardware, facilities and ground operations associated with the Ares I. Photo Credit: (NASA/Bill Ingalls)

  14. First Stage of a Highly Reliable Reusable Launch System

    NASA Technical Reports Server (NTRS)

    Kloesel, Kurt J.; Pickrel, Jonathan B.; Sayles, Emily L.; Wright, Michael; Marriott, Darin; Holland, Leo; Kuznetsov, Stephen

    2009-01-01

    Electromagnetic launch assist has the potential to provide a highly reliable reusable first stage to a space access system infrastructure at a lower overall cost. This paper explores the benefits of a smaller system that adds the advantages of a high specific impulse air-breathing stage and supersonic launch speeds. The method of virtual specific impulse is introduced as a tool to emphasize the gains afforded by launch assist. Analysis shows launch assist can provide a 278-s virtual specific impulse for a first-stage solid rocket. Additional trajectory analysis demonstrates that a system composed of a launch-assisted first-stage ramjet plus a bipropellant second stage can provide a 48-percent gross lift-off weight reduction versus an all-rocket system. The combination of high-speed linear induction motors and ramjets is identified, as the enabling technologies and benchtop prototypes are investigated. The high-speed response of a standard 60 Hz linear induction motor was tested with a pulse width modulated variable frequency drive to 150 Hz using a 10-lb load, achieving 150 mph. A 300-Hz stator-compensated linear induction motor was constructed and static-tested to 1900 lbf average. A matching ramjet design was developed for use on the 300-Hz linear induction motor.

  15. Magnetic carbon nanostructures: microwave energy-assisted pyrolysis vs. conventional pyrolysis.

    PubMed

    Zhu, Jiahua; Pallavkar, Sameer; Chen, Minjiao; Yerra, Narendranath; Luo, Zhiping; Colorado, Henry A; Lin, Hongfei; Haldolaarachchige, Neel; Khasanov, Airat; Ho, Thomas C; Young, David P; Wei, Suying; Guo, Zhanhu

    2013-01-11

    Magnetic carbon nanostructures from microwave assisted- and conventional-pyrolysis processes are compared. Unlike graphitized carbon shells from conventional heating, different carbon shell morphologies including nanotubes, nanoflakes and amorphous carbon were observed. Crystalline iron and cementite were observed in the magnetic core, different from a single cementite phase from the conventional process.

  16. Low launch-energy trajectories to the outer solar system via Venus and earth gravity-assist flybys

    NASA Technical Reports Server (NTRS)

    Diehl, Roger; Belbruno, Edward; Bender, David; Myers, Mark; Stetson, Douglas

    1988-01-01

    Recent cancellation of the program to develop a Centaur upper stage for use in the Space Transportation System (STS) has motivated considerable interest in trajectory modes with low launch-energy requirements to the outer solar system. Flyby encounters of the inner planets, especially Venus and earth, may be used to enable missions to Jupiter, Saturn, and a restricted class of comets. An examination of mission opportunities to these targets is presented through the end of this century using gravity-assist trajectories.

  17. Spin torque oscillator for microwave assisted magnetization reversal

    NASA Astrophysics Data System (ADS)

    Taniguchi, Tomohiro; Kubota, Hitoshi

    2018-05-01

    A theoretical study is given for the self-oscillation excited in a spin torque oscillator (STO) consisting of an in-plane magnetized free layer and a perpendicularly magnetized pinned layer in the presence of a perpendicular magnetic field. This type of STO is a potential candidate for a microwave source of microwave assisted magnetization reversal (MAMR). It is, however, found that the self-oscillation applicable to MAMR disappears when the perpendicular field is larger than a critical value, which is much smaller than a demagnetization field. This result provides a condition that the reversal field of a magnetic recording bit by MAMR in nanopillar structure should be smaller than the critical value. The analytical formulas of currents determining the critical field are obtained, which indicate that a material with a small damping is not preferable to acheive a wide range of the self-oscillation applicable to MAMR, although such a material is preferable from the viewpoint of the reduction of the power consumption.

  18. Magnetically assisted intraperitoneal drug delivery for cancer chemotherapy.

    PubMed

    Shamsi, Milad; Sedaghatkish, Amir; Dejam, Morteza; Saghafian, Mohsen; Mohammadi, Mehdi; Sanati-Nezhad, Amir

    2018-11-01

    Intraperitoneal (IP) chemotherapy has revived hopes during the past few years for the management of peritoneal disseminations of digestive and gynecological cancers. Nevertheless, a poor drug penetration is one key drawback of IP chemotherapy since peritoneal neoplasms are notoriously resistant to drug penetration. Recent preclinical studies have focused on targeting the aberrant tumor microenvironment to improve intratumoral drug transport. However, tumor stroma targeting therapies have limited therapeutic windows and show variable outcomes across different cohort of patients. Therefore, the development of new strategies for improving the efficacy of IP chemotherapy is a certain need. In this work, we propose a new magnetically assisted strategy to elevate drug penetration into peritoneal tumor nodules and improve IP chemotherapy. A computational model was developed to assess the feasibility and predictability of the proposed active drug delivery method. The key tumor pathophysiology, including a spatially heterogeneous construct of leaky vasculature, nonfunctional lymphatics, and dense extracellular matrix (ECM), was reconstructed in silico. The transport of intraperitoneally injected magnetic nanoparticles (MNPs) inside tumors was simulated and compared with the transport of free cytotoxic agents. Our results on magnetically assisted delivery showed an order of magnitude increase in the final intratumoral concentration of drug-coated MNPs with respect to free cytotoxic agents. The intermediate MNPs with the radius range of 200-300 nm yield optimal magnetic drug targeting (MDT) performance in 5-10 mm tumors while the MDT performance remains essentially the same over a large particle radius range of 100-500 nm for a 1 mm radius small tumor. The success of MDT in larger tumors (5-10 mm in radius) was found to be markedly dependent on the choice of magnet strength and tumor-magnet distance while these two parameters were less of a concern in small tumors

  19. Strain-assisted current-induced magnetization reversal in magnetic tunnel junctions: A micromagnetic study with phase-field microelasticity

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

    Huang, H. B., E-mail: houbinghuang@gmail.com; Department of Physics, University of Science and Technology Beijing, Beijing 100083; Hu, J. M.

    2014-09-22

    Effect of substrate misfit strain on current-induced in-plane magnetization reversal in CoFeB-MgO based magnetic tunnel junctions is investigated by combining micromagnetic simulations with phase-field microelasticity theory. It is found that the critical current density for in-plane magnetization reversal decreases dramatically with an increasing substrate strain, since the effective elastic field can drag the magnetization to one of the four in-plane diagonal directions. A potential strain-assisted multilevel bit spin transfer magnetization switching device using substrate misfit strain is also proposed.

  20. 34 CFR 280.1 - What is the Magnet Schools Assistance Program?

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... schools; (e) Improvement of the capacity of LEAs, including through professional development, to continue... terminated; and (f) Ensuring that all students enrolled in the magnet school programs have equitable access... 34 Education 1 2012-07-01 2012-07-01 false What is the Magnet Schools Assistance Program? 280.1...

  1. 34 CFR 280.1 - What is the Magnet Schools Assistance Program?

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... schools; (e) Improvement of the capacity of LEAs, including through professional development, to continue... terminated; and (f) Ensuring that all students enrolled in the magnet school programs have equitable access... 34 Education 1 2014-07-01 2014-07-01 false What is the Magnet Schools Assistance Program? 280.1...

  2. 34 CFR 280.1 - What is the Magnet Schools Assistance Program?

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... schools; (e) Improvement of the capacity of LEAs, including through professional development, to continue... terminated; and (f) Ensuring that all students enrolled in the magnet school programs have equitable access... 34 Education 1 2013-07-01 2013-07-01 false What is the Magnet Schools Assistance Program? 280.1...

  3. A novel magnet focusing plate for matrix-assisted laser desorption/ionization analysis of magnetic bead-bound analytes.

    PubMed

    Gode, David; Volmer, Dietrich A

    2013-05-15

    Magnetic beads are often used for serum profiling of peptide and protein biomarkers. In these assays, the bead-bound analytes are eluted from the beads prior to mass spectrometric analysis. This study describes a novel matrix-assisted laser desorption/ionization (MALDI) technique for direct application and focusing of magnetic beads to MALDI plates by means of dedicated micro-magnets as sample spots. Custom-made MALDI plates with magnetic focusing spots were made using small nickel-coated neodymium micro-magnets integrated into a stainless steel plate in a 16 × 24 (384) pattern. For demonstrating the proof-of-concept, commercial C-18 magnetic beads were used for the extraction of a test compound (reserpine) from aqueous solution. Experiments were conducted to study focusing abilities, the required laser energies, the influence of a matrix compound, dispensing techniques, solvent choice and the amount of magnetic beads. Dispensing the magnetic beads onto the micro-magnet sample spots resulted in immediate and strong binding to the magnetic surface. Light microscope images illustrated the homogeneous distribution of beads across the surfaces of the magnets, when the entire sample volume containing the beads was pipetted onto the surface. Subsequent MALDI analysis of the bead-bound analyte demonstrated excellent and reproducible ionization yields. The surface-assisted laser desorption/ionization (SALDI) properties of the strongly light-absorbing γ-Fe2O3-based beads resulted in similar ionization efficiencies to those obtained from experiments with an additional MALDI matrix compound. This feasibility study successfully demonstrated the magnetic focusing abilities for magnetic bead-bound analytes on a novel MALDI plate containing small micro-magnets as sample spots. One of the key advantages of this integrated approach is that no elution steps from magnetic beads were required during analyses compared with conventional bead experiments. Copyright © 2013 John Wiley

  4. Dynamics of Plasma Jets and Bubbles Launched into a Transverse Background Magnetic Field

    NASA Astrophysics Data System (ADS)

    Zhang, Yue

    2017-10-01

    A coaxial magnetized plasma gun has been utilized to launch both plasma jets (open B-field) and plasma bubbles (closed B-field) into a transverse background magnetic field in the HelCat (Helicon-Cathode) linear device at the University of New Mexico. These situations may have bearing on fusion plasmas (e.g. plasma injection for tokamak fueling, ELM pacing, or disruption mitigation) and astrophysical settings (e.g. astrophysical jet stability, coronal mass ejections, etc.). The magnetic Reynolds number of the gun plasma is 100 , so that magnetic advection dominates over magnetic diffusion. The gun plasma ram pressure, ρjetVjet2 >B02 / 2μ0 , the background magnetic pressure, so that the jet or bubble can easily penetrate the background B-field, B0. When the gun axial B-field is weak compared to the gun azimuthal field, a current-driven jet is formed with a global helical magnetic configuration. Applying the transverse background magnetic field, it is observed that the n = 1 kink mode is stabilized, while magnetic probe measurements show contrarily that the safety factor q(a) drops below unity. At the same time, a sheared axial jet velocity is measured. We conclude that the tension force arising from increasing curvature of the background magnetic field induces the measured sheared flow gradient above the theoretical kink-stabilization threshold, resulting in the emergent kink stabilization of the injected plasma jet. In the case of injected bubbles, spheromak-like plasma formation is verified. However, when the spheromak plasma propagates into the transverse background magnetic field, the typical self-closed global symmetry magnetic configuration does not hold any more. In the region where the bubble toroidal field opposed the background B-field, the magneto-Rayleigh-Taylor (MRT) instability has been observed. Details of the experiment setup, diagnostics, experimental results and theoretical analysis will be presented. Supported by the National Science Foundation

  5. The influence of assist gas on magnetic properties of electrotechnical steel sheets cut with laser

    NASA Astrophysics Data System (ADS)

    Gaworska-Koniarek, Dominika; Szubzda, Bronisław; Wilczyński, Wiesław; Drosik, Jerzy; Karaś, Kazimierz

    2011-07-01

    The paper presents the influence of assist gas (air and nitrogen) during laser cutting on magnetization, magnetic permeability and loss characteristics of non-oriented electrical steels. The research was made on an non-oriented M330-50A grade electrical steels by means of single sheet tester. In order to enhance the effect of cutting and the same degradation zone on magnetic properties, strips with different width were achieved. Measurements results indicate that application of air as assist gas has more destructive effect on magnetic properties of electrical steels than nitrogen one.

  6. Spin–orbit torque-assisted switching in magnetic insulator thin films with perpendicular magnetic anisotropy

    DOE PAGES

    Li, Peng; Liu, Tao; Chang, Houchen; ...

    2016-09-01

    As an in-plane charge current flows in a heavy metal film with spin-orbit coupling, it produces a torque on and thereby switches the magnetization in a neighbouring ferromagnetic metal film. Such spin-orbit torque (SOT)-induced switching has been studied extensively in recent years and has shown higher efficiency than switching using conventional spin-transfer torque. Here we report the SOT-assisted switching in heavy metal/magnetic insulator systems. The experiments used a Pt/BaFe 12O 19 bilayer where the BaFe 12O 19 layer exhibits perpendicular magnetic anisotropy. As a charge current is passed through the Pt film, it produces a SOT that can control themore » up and down states of the remnant magnetization in the BaFe 12O 19 film when the film is magnetized by an in-plane magnetic field. Furthermore, it can reduce or increase the switching field of the BaFe 12O 19 film by as much as about 500 Oe when the film is switched with an out-of-plane field.« less

  7. Spin-orbit torque-assisted switching in magnetic insulator thin films with perpendicular magnetic anisotropy

    NASA Astrophysics Data System (ADS)

    Li, Peng; Liu, Tao; Chang, Houchen; Kalitsov, Alan; Zhang, Wei; Csaba, Gyorgy; Li, Wei; Richardson, Daniel; Demann, August; Rimal, Gaurab; Dey, Himadri; Jiang, J. S.; Porod, Wolfgang; Field, Stuart B.; Tang, Jinke; Marconi, Mario C.; Hoffmann, Axel; Mryasov, Oleg; Wu, Mingzhong

    2016-09-01

    As an in-plane charge current flows in a heavy metal film with spin-orbit coupling, it produces a torque on and thereby switches the magnetization in a neighbouring ferromagnetic metal film. Such spin-orbit torque (SOT)-induced switching has been studied extensively in recent years and has shown higher efficiency than switching using conventional spin-transfer torque. Here we report the SOT-assisted switching in heavy metal/magnetic insulator systems. The experiments used a Pt/BaFe12O19 bilayer where the BaFe12O19 layer exhibits perpendicular magnetic anisotropy. As a charge current is passed through the Pt film, it produces a SOT that can control the up and down states of the remnant magnetization in the BaFe12O19 film when the film is magnetized by an in-plane magnetic field. It can reduce or increase the switching field of the BaFe12O19 film by as much as about 500 Oe when the film is switched with an out-of-plane field.

  8. Advanced Concept

    NASA Image and Video Library

    1999-10-21

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

  9. Segmented media and medium damping in microwave assisted magnetic recording

    NASA Astrophysics Data System (ADS)

    Bai, Xiaoyu; Zhu, Jian-Gang

    2018-05-01

    In this paper, we present a methodology of segmented media stack design for microwave assisted magnetic recording. Through micro-magnetic modeling, it is demonstrated that an optimized media segmentation is able to yield high signal-to-noise ratio even with limited ac field power. With proper segmentation, the ac field power could be utilized more efficiently and this can alleviate the requirement for medium damping which has been previously considered a critical limitation. The micro-magnetic modeling also shows that with segmentation optimization, recording signal-to-noise ratio can have very little dependence on damping for different recording linear densities.

  10. Renormalized anisotropic exchange for representing heat assisted magnetic recording media

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

    Jiao, Yipeng; Liu, Zengyuan; Victora, R. H., E-mail: victora@umn.edu

    2015-05-07

    Anisotropic exchange has been incorporated in a description of magnetic recording media near the Curie temperature, as would be found during heat assisted magnetic recording. The new parameters were found using a cost function that minimized the difference between atomistic properties and those of renormalized spin blocks. Interestingly, the anisotropic exchange description at 1.5 nm discretization yields very similar switching and magnetization behavior to that found at 1.2 nm (and below) discretization for the previous isotropic exchange. This suggests that the increased accuracy of anisotropic exchange may also reduce the computational cost during simulation.

  11. Gap-mode-assisted light-induced switching of sub-wavelength magnetic domains

    NASA Astrophysics Data System (ADS)

    Scheunert, G.; McCarron, R.; Kullock, R.; Cohen, S. R.; Rechav, K.; Kaplan-Ashiri, I.; Bitton, O.; Hecht, B.; Oron, D.

    2018-04-01

    Creating sub-micron hotspots for applications such as heat-assisted magnetic recording (HAMR) is a challenging task. The most common approach relies on a surface-plasmon resonator (SPR), whose design dictates the size of the hotspot to always be larger than its critical dimension. Here, we present an approach which circumvents known geometrical restrictions by resorting to electric field confinement via excitation of a gap-mode (GM) between a comparatively large Gold (Au) nano-sphere (radius of 100 nm) and the magnetic medium in a grazing-incidence configuration. Operating a λ=785 nm laser, sub-200 nm hot spots have been generated and successfully used for GM-assisted magnetic switching on commercial CoCrPt perpendicular magnetic recording media at laser powers and pulse durations comparable to SPR-based HAMR. Lumerical electric field modelling confirmed that operating in the near-infrared regime presents a suitable working point where most of the light's energy is deposited in the magnetic layer, rather than in the nano-particle. Further, modelling is used for predicting the limits of our method which, in theory, can yield sub-30 nm hotspots for Au nano-sphere radii of 25-50 nm for efficient heating of FePt recording media with a gap of 5 nm.

  12. Correlative Magnetic Imaging of Heat-Assisted Magnetic Recording Media in Cross Section Using Lorentz TEM and MFM

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

    Kim, Taeho Roy; Phatak, Charudatta; Petford-Long, Amanda K.

    In order to increase the storage density of hard disk drives, a detailed understanding of the magnetic structure of the granular magnetic layer is essential. Here, we demonstrate an experimental procedure of imaging recorded bits on heat-assisted magnetic recording (HAMR) media in cross section using Lorentz transmission electron microscopy (TEM). With magnetic force microscopy and focused ion beam (FIB), we successfully targeted a single track to prepare cross-sectional TEM specimens. Then, we characterized the magnetic structure of bits with their precise location and orientation using Fresnel mode of Lorentz TEM. Here, this method can promote understanding of the correlation betweenmore » bits and their material structure in HAMR media to design better the magnetic layer.« less

  13. Correlative Magnetic Imaging of Heat-Assisted Magnetic Recording Media in Cross Section Using Lorentz TEM and MFM

    DOE PAGES

    Kim, Taeho Roy; Phatak, Charudatta; Petford-Long, Amanda K.; ...

    2017-10-23

    In order to increase the storage density of hard disk drives, a detailed understanding of the magnetic structure of the granular magnetic layer is essential. Here, we demonstrate an experimental procedure of imaging recorded bits on heat-assisted magnetic recording (HAMR) media in cross section using Lorentz transmission electron microscopy (TEM). With magnetic force microscopy and focused ion beam (FIB), we successfully targeted a single track to prepare cross-sectional TEM specimens. Then, we characterized the magnetic structure of bits with their precise location and orientation using Fresnel mode of Lorentz TEM. Here, this method can promote understanding of the correlation betweenmore » bits and their material structure in HAMR media to design better the magnetic layer.« less

  14. Advanced Concept

    NASA Image and Video Library

    1999-01-01

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

  15. Vehicle Dynamics due to Magnetic Launch Propulsion

    NASA Technical Reports Server (NTRS)

    Galaboff, Zachary J.; Jacobs, William; West, Mark E.; Montenegro, Justino (Technical Monitor)

    2000-01-01

    The field of Magnetic Levitation Lind Propulsion (MagLev) has been around for over 30 years, primarily in high-speed rail service. In recent years, however, NASA has been looking closely at MagLev as a possible first stage propulsion system for spacecraft. This approach creates a variety of new problems that don't currently exist with the present MagLev trains around the world. NASA requires that a spacecraft of approximately 120,000 lbs be accelerated at two times the acceleration of gravity (2g's). This produces a greater demand on power over the normal MagLev trains that accelerate at around 0.1g. To be able to store and distribute up to 3,000 Mega Joules of energy in less than 10 seconds is a technical challenge. Another problem never addressed by the train industry and, peculiar only to NASA, is the control of a lifting body through the acceleration of and separation from the MagLev track. Very little is understood about how a lifting body will react with external forces, Such as wind gusts and ground effects, while being propelled along on soft springs such as magnetic levitators. Much study needs to be done to determine spacecraft control requirements as well as what control mechanisms and aero-surfaces should be placed on the carrier. Once the spacecraft has been propelled down the track another significant event takes place, the separation of the spacecraft from the carrier. The dynamics involved for both the carrier and the spacecraft are complex and coupled. Analysis of the reaction of the carrier after losing, a majority of its mass must be performed to insure control of the carrier is maintained and a safe separation of the spacecraft is achieved. The spacecraft angle of attack required for lift and how it will affect the carriage just prior to separation, along with the impacts of around effect and aerodynamic forces at ground level must be modeled and analyzed to define requirements on the launch vehicle design. Mechanisms, which can withstand the

  16. Launch Period Development for the Juno Mission to Jupiter

    NASA Technical Reports Server (NTRS)

    Kowalkowski, Theresa D.; Johannesen, Jennie R.; Lam, Try

    2008-01-01

    The Juno mission to Jupiter is targeted to launch in 2011 and would reach the giant planet about five years later. The interplanetary trajectory is planned to include two large deep space maneuvers and an Earth gravity assist a little more than two years after launch. In this paper, we describe the development of a 21-day launch period for Juno with the objective of keeping overall launch energy and delta-V low while meeting constraints imposed on Earth departure, the deep space maneuvers' timing and geometry, and Jupiter arrival.

  17. Review: magnetically assisted resistance spot welding

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

    Li, Y. B.; Li, D. L.; Lin, Z. Q.

    2016-02-25

    Currently, the use of advanced high strength steels (AHSSs) is the most cost effective means of reducing vehicle body weight and maintaining structural integrity at the same time. However, AHSSs present a big challenge to the traditional resistance spot welding (RSW) widely applied in automotive industries because the rapid heating and cooling procedures during RSW produce hardened weld microstructures, which lower the ductility and fatigue properties of welded joints and raise the probability of interfacial failure under external loads. Changing process parameters or post-weld heat treatment may reduce the weld brittleness, but those traditional quality control methods also increase energymore » consumption and prolong cycle time. In recent years, a magnetically assisted RSW (MA-RSW) method was proposed, in which an externally applied magnetic field would interact with the conduction current to produce a Lorentz force that would affect weld nugget formation. This paper is a review of an experimental MA-RSW platform, the mode of the external magnetic field and the mechanism that controls nugget shape, weld microstructures and joint performance. In conclusion, the advantages of the MA-RSW method in improving the weldability of AHSSs are given, a recent application of the MA-RSW process to light metals is described and the outlook for the MA-RSW process is presented.« less

  18. Astronaut Jean-Francois Clervoy in white room on launch pad 39B

    NASA Technical Reports Server (NTRS)

    1994-01-01

    In the white room at Launch Pad 39B, STS-66 mission specialist Jean-Francois Clervoy is assisted with his partial pressure launch/entry suit by close-out crew members Travis Thompson and Danny Wyatt (background) before entering the Space Shuttle Atlantis for its November 3 launch.

  19. Magnetic-assisted triboelectric nanogenerators as self-powered visualized omnidirectional tilt sensing system

    NASA Astrophysics Data System (ADS)

    Han, Mengdi; Zhang, Xiao-Sheng; Sun, Xuming; Meng, Bo; Liu, Wen; Zhang, Haixia

    2014-04-01

    The triboelectric nanogenerator (TENG) is a promising device in energy harvesting and self-powered sensing. In this work, we demonstrate a magnetic-assisted TENG, utilizing the magnetic force for electric generation. Maximum power density of 541.1 mW/m2 is obtained at 16.67 MΩ for the triboelectric part, while the electromagnetic part can provide power density of 649.4 mW/m2 at 16 Ω. Through theoretical calculation and experimental measurement, linear relationship between the tilt angle and output voltage at large angles is observed. On this basis, a self-powered omnidirectional tilt sensor is realized by two magnetic-assisted TENGs, which can measure the magnitude and direction of the tilt angle at the same time. For visualized sensing of the tilt angle, a sensing system is established, which is portable, intuitive, and self-powered. This visualized system greatly simplifies the measure process, and promotes the development of self-powered systems.

  20. Magnetic-assisted triboelectric nanogenerators as self-powered visualized omnidirectional tilt sensing system

    PubMed Central

    Han, Mengdi; Zhang, Xiao-Sheng; Sun, Xuming; Meng, Bo; Liu, Wen; Zhang, Haixia

    2014-01-01

    The triboelectric nanogenerator (TENG) is a promising device in energy harvesting and self-powered sensing. In this work, we demonstrate a magnetic-assisted TENG, utilizing the magnetic force for electric generation. Maximum power density of 541.1 mW/m2 is obtained at 16.67 MΩ for the triboelectric part, while the electromagnetic part can provide power density of 649.4 mW/m2 at 16 Ω. Through theoretical calculation and experimental measurement, linear relationship between the tilt angle and output voltage at large angles is observed. On this basis, a self-powered omnidirectional tilt sensor is realized by two magnetic-assisted TENGs, which can measure the magnitude and direction of the tilt angle at the same time. For visualized sensing of the tilt angle, a sensing system is established, which is portable, intuitive, and self-powered. This visualized system greatly simplifies the measure process, and promotes the development of self-powered systems. PMID:24770490

  1. New vibration-assisted magnetic abrasive polishing (VAMAP) method for microstructured surface finishing.

    PubMed

    Guo, Jiang; Kum, Chun Wai; Au, Ka Hing; Tan, Zhi'En Eddie; Wu, Hu; Liu, Kui

    2016-06-13

    In order to polish microstructured surface without deteriorating its profile, we propose a new vibration-assisted magnetic abrasive polishing (VAMAP) method. In this method, magnetic force guarantees that the magnetic abrasives can well contact the microstructured surface and access the corners of microstructures while vibration produces a relative movement between microstructures and magnetic abrasives. As the vibration direction is parallel to the microstructures, the profile of the microstructures will not be deteriorated. The relation between vibration and magnetic force was analyzed and the feasibility of this method was experimentally verified. The results show that after polishing, the surface finish around microstructures was significantly improved while the profile of microstructures was well maintained.

  2. Thermally assisted magnetization reversal in sub-micron sized magnetic thin films

    NASA Astrophysics Data System (ADS)

    Koch, Roger H.

    2000-03-01

    We have measured the rate of thermally assisted magnetization reversal of sub-micron sized magnetic thin film elements. For fields H just less than the zero-temperature coercive field H_C, the probability of reversal, P^exps (t), increases for short times, t, achieves a maximum value, and then decreases exponentially. The temperature dependence of the reversal is consistent with a temperature independent barrier height. Micromagnetic simulations exhibit the same behavior, and show that the reversal for a film without disorder proceeds through the annihilation of two domain walls that move from opposite sides of the sample. The behavior of P^exps (t) can be understood using a simple ``energy-ladder" model of thermal activation. In this model, the film reverses its magnetization direction by thermally activating (reversibly) through a ladder of intermediate metastable states. The measured data are consistent with there being a handful of these states in the energy landscape of the film. These states are a result of the disorder in the film and we will show micromagnetic simulation movies depicting this behavior. In collaboration with G. Grinstein, G.A. Keefe, Yu Lu, P.L. Trouilloud, W. J. Gallagher, S.S.P. Parkin, S. Ingvarson, and G. Xaio

  3. Delta II THEMIS Pre-Launch

    NASA Image and Video Library

    2002-01-01

    The Delta II rocket with the THEMIS spacecraft atop sits ready for launch on Pad 17-B at Cape Canaveral Air Force Station in this aerial view of the launch complex area as the mobile service tower begins to move away. THEMIS, an acronym for Time History of Events and Macroscale Interactions during Substorms, consists of five identical probes that will track violent, colorful eruptions near the North Pole. This will be the largest number of scientific satellites NASA has ever launched into orbit aboard a single rocket. The THEMIS mission aims to unravel the mystery behind auroral substorms, an avalanche of magnetic energy powered by the solar wind that intensifies the northern and southern lights. The mission will investigate what causes auroras in the Earth’s atmosphere to dramatically change from slowly shimmering waves of light to wildly shifting streaks of bright color. Launch is scheduled for 6:05 p.m.

  4. Highly Reusable Space Transportation System Concept Evaluation (The Argus Launch Vehicle)

    NASA Technical Reports Server (NTRS)

    Olds, John R.; Bellini, Peter X.

    1998-01-01

    This paper summarizes the results of a conceptual design study that was performed in support of NASA's recent Highly Reusable Space Transportation study. The Argus concept uses a Maglifter magnetic-levitation sled launch assist system to accelerate it to a takeoff ground speed of 800 fps on its way to delivering a payload of 20,000 lb. to low earth orbit. Main propulsion is provided by two supercharged ejector rocket engines. The vehicle is autonomous and is fully reusable. A conceptual design exercise determined the vehicle gross weight to be approximately 597,250 lb. and the dry weight to be 75,500 lb. Aggressive weight and operations cost assumptions were used throughout the design process consistent with a second-generation reusable system that might be deployed in 10-15 years. Drawings, geometry, and weight of the concept are included. Preliminary development, production, and operations costs along with a business scenario assuming a price-elastic payload market are also included. A fleet of three Argus launch vehicles flying a total of 149 flights per year is shown to have a financial internal rate of return of 28%. At $169/lb., the recurring cost of Argus is shown to meet the study goal of $100/lb.-$200/lb., but optimum market price results in only a factor of two to five reduction compared to today's launch systems.

  5. Atomic hydrogen as a launch vehicle propellant

    NASA Technical Reports Server (NTRS)

    Palaszewski, Bryan A.

    1990-01-01

    An analysis of several atomic hydrogen launch vehicles was conducted. A discussion of the facilities and the technologies that would be needed for these vehicles is also presented. The Gross Liftoff Weights (GLOW) for two systems were estimated; their specific impulses (I sub sp) were 750 and 1500 lb(sub f)/s/lb(sub m). The atomic hydrogen launch vehicles were also compared to the currently planned Advanced Launch System design concepts. Very significant GLOW reductions of 52 to 58 percent are possible over the Advanced Launch System designs. Applying atomic hydrogen propellants to upper stages was also considered. Very high I(sub sp) (greater than 750 lb(sub f)/s/lb(sub m)) is needed to enable a mass savings over advanced oxygen/hydrogen propulsion. Associated with the potential benefits of high I(sub sp) atomic hydrogen are several challenging problems. Very high magnetic fields are required to maintain the atomic hydrogen in a solid hydrogen matrix. The magnetic field strength was estimated to be 30 kilogauss (3 Tesla). Also the storage temperature of the propellant is 4 K. This very low temperature will require a large refrigeration facility for the launch vehicle. The design considerations for a very high recombination rate for the propellant are also discussed. A recombination rate of 210 cm/s is predicted for atomic hydrogen. This high recombination rate can produce very high acceleration for the launch vehicle. Unique insulation or segmentation to inhibit the propellant may be needed to reduce its recombination rate.

  6. RICK BURT AND ANDY SCHORR WITH LAUNCH VEHICLE STAGE ADAPTER

    NASA Image and Video Library

    2016-09-23

    RICK BURT, RIGHT, DIRECTOR OF SAFETY AND MISSION ASSURANCE TALKS WITH ANDY SCHORR, ASSISTANT MANAGER OF THE SPACE LAUNCH SYSTEM'S SPACECRAFT PAYLOAD INTEGRATION AND EVOLUTION OFFICE. BEHIND THEM IS THE LAUNCH VEHICLE STAGE ADAPTOR, WHICH WAS DESIGNED AND MANUFACTURED AT MARSHALL AND WILL CONNECT TWO MAJOR SLS UPPER SECTIONS

  7. NASA Launches Rocket Into Active Auroras

    NASA Image and Video Library

    2017-12-08

    A test rocket is launched the night of Feb. 17 from the Poker Flat Research Range in Alaska. Test rockets are launched as part of the countdown to test out the radar tracking systems. NASA is launching five sounding rockets from the Poker Range into active auroras to explore the Earth's magnetic environment and its impact on Earth’s upper atmosphere and ionosphere. The launch window for the four remaining rockets runs through March 3. Credit: NASA/Terry Zaperach NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

  8. Magnetic-Field-Assisted Terahertz Quantum Cascade Laser Operating up to 225 K

    NASA Technical Reports Server (NTRS)

    Wade, A.; Fedorov, G.; Smirnov, D.; Kumar, S.; Williams, B. S.; Hu, Q.; Reno, J. L.

    2008-01-01

    Advances in semiconductor bandgap engineering have resulted in the recent development of the terahertz quantum cascade laser1. These compact optoelectronic devices now operate in the frequency range 1.2-5 THz, although cryogenic cooling is still required2.3. Further progress towards the realization of devices operating at higher temperatures and emitting at longer wavelengths (sub-terahertz quantum cascade lasers) is difficult because it requires maintaining a population inversion between closely spaced electronic sub-bands (1 THz approx. equals 4 meV). Here, we demonstrate a magnetic-field-assisted quantum cascade laser based on the resonant-phonon design. By applying appropriate electrical bias and strong magnetic fields above 16 T, it is possible to achieve laser emission from a single device over a wide range of frequencies (0.68-3.33 THz). Owing to the suppression of inter-landau-level non-radiative scattering, the device shows magnetic field assisted laser action at 1 THz at temperatures up to 215 K, and 3 THz lasing up to 225 K.

  9. Research Technology

    NASA Image and Video Library

    2001-03-01

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

  10. Multimaterial magnetically assisted 3D printing of composite materials.

    PubMed

    Kokkinis, Dimitri; Schaffner, Manuel; Studart, André R

    2015-10-23

    3D printing has become commonplace for the manufacturing of objects with unusual geometries. Recent developments that enabled printing of multiple materials indicate that the technology can potentially offer a much wider design space beyond unusual shaping. Here we show that a new dimension in this design space can be exploited through the control of the orientation of anisotropic particles used as building blocks during a direct ink-writing process. Particle orientation control is demonstrated by applying low magnetic fields on deposited inks pre-loaded with magnetized stiff platelets. Multimaterial dispensers and a two-component mixing unit provide additional control over the local composition of the printed material. The five-dimensional design space covered by the proposed multimaterial magnetically assisted 3D printing platform (MM-3D printing) opens the way towards the manufacturing of functional heterogeneous materials with exquisite microstructural features thus far only accessible by biological materials grown in nature.

  11. Experimental and theoretical studies of implant assisted magnetic drug targeting

    NASA Astrophysics Data System (ADS)

    Aviles, Misael O.

    One way to achieve drug targeting in the body is to incorporate magnetic nanoparticles into drug carriers and then retain them at the site using an externally applied magnetic field. This process is referred to as magnetic drug targeting (MDT). However, the main limitation of MDT is that an externally applied magnetic field alone may not be able to retain a sufficient number of magnetic drug carrier particles (MDCPs) to justify its use. Such a limitation might not exist when high gradient magnetic separation (HGMS) principles are applied to assist MDT by means of ferromagnetic implants. It was hypothesized that an Implant Assisted -- MDT (IA-MDT) system would increase the retention of the MDCPs at a target site where an implant had been previously located, since the magnetic forces are produced internally. With this in mind, the overall objective of this work was to demonstrate the feasibility of an IA-MDT system through mathematical modeling and in vitro experimentation. The mathematical models were developed and used to demonstrate the behavior and limitations of IA-MDT, and the in vitro experiments were designed and used to validate the models and to further elucidate the important parameters that affect the performance of the system. IA-MDT was studied with three plausible implants, ferromagnetic stents, seed particles, and wires. All implants were studied theoretically and experimentally using flow through systems with polymer particles containing magnetite nanoparticles as MDCPs. In the stent studies, a wire coil or mesh was simply placed in a flow field and the capture of the MDCPs was studied. In the other cases, a porous polymer matrix was used as a surrogate capillary tissue scaffold to study the capture of the MDCPs using wires or particle seeds as the implant, with the seeds either fixed within the polymer matrix or captured prior to capturing the MDCPs. An in vitro heart tissue perfusion model was also used to study the use of stents. In general, all

  12. Multimaterial magnetically assisted 3D printing of composite materials

    NASA Astrophysics Data System (ADS)

    Kokkinis, Dimitri; Schaffner, Manuel; Studart, André R.

    2015-10-01

    3D printing has become commonplace for the manufacturing of objects with unusual geometries. Recent developments that enabled printing of multiple materials indicate that the technology can potentially offer a much wider design space beyond unusual shaping. Here we show that a new dimension in this design space can be exploited through the control of the orientation of anisotropic particles used as building blocks during a direct ink-writing process. Particle orientation control is demonstrated by applying low magnetic fields on deposited inks pre-loaded with magnetized stiff platelets. Multimaterial dispensers and a two-component mixing unit provide additional control over the local composition of the printed material. The five-dimensional design space covered by the proposed multimaterial magnetically assisted 3D printing platform (MM-3D printing) opens the way towards the manufacturing of functional heterogeneous materials with exquisite microstructural features thus far only accessible by biological materials grown in nature.

  13. Delta II THEMIS Pre-Launch

    NASA Image and Video Library

    2002-01-01

    In this close-up aerial view, the Delta II rocket with the THEMIS spacecraft atop sits ready for launch on Pad 17-B at Cape Canaveral Air Force Station. THEMIS, an acronym for Time History of Events and Macroscale Interactions during Substorms, consists of five identical probes that will track violent, colorful eruptions near the North Pole. This will be the largest number of scientific satellites NASA has ever launched into orbit aboard a single rocket. The THEMIS mission aims to unravel the mystery behind auroral substorms, an avalanche of magnetic energy powered by the solar wind that intensifies the northern and southern lights. The mission will investigate what causes auroras in the Earth’s atmosphere to dramatically change from slowly shimmering waves of light to wildly shifting streaks of bright color. Launch is scheduled for 6:05 p.m.

  14. Animal trials of a Magnetically Levitated Left-Ventricular Assist Device

    NASA Technical Reports Server (NTRS)

    Paden, Brad; Antaki, James; Groom, Nelson

    2000-01-01

    The University of Pittsburgh/Magnetic Moments mag-lev left-ventricular assist devices (LVADs), the Streamliner HG3b and HG3c, have successfully been implanted in calves. The first was implanted for 4 hours on July 10, 1998 and the second for 34 days on August 24, 1999 respectively. The tests confirmed the feasibility of low power levitation (1.5 watts coil power) and very low blood damage in a mag-lev ventricular assist device. In this paper, we describe the unique geometry of this pump and its design. Key features of this LVAD concept are the passive radial suspension and active voice-coil thrust bearing.

  15. Method And Apparatus For Launching Microwave Energy Into A Plasma Processing Chamber

    DOEpatents

    DOUGHTY, FRANK C.; [et al

    2001-05-01

    A method and apparatus for launching microwave energy to a plasma processing chamber in which the required magnetic field is generated by a permanent magnet structure and the permanent magnet material effectively comprises one or more surfaces of the waveguide structure. The waveguide structure functions as an impedance matching device and controls the field pattern of the launched microwave field to create a uniform plasma. The waveguide launcher may comprise a rectangular waveguide, a circular waveguide, or a coaxial waveguide with permanent magnet material forming the sidewalls of the guide and a magnetization pattern which produces the required microwave electron cyclotron resonance magnetic field, a uniform field absorption pattern, and a rapid decay of the fields away from the resonance zone. In addition, the incorporation of permanent magnet material as a portion of the waveguide structure places the magnetic material in close proximity to the vacuum chamber, allowing for a precisely controlled magnetic field configuration, and a reduction of the amount of permanent magnet material required.

  16. Launch Control Network Engineer

    NASA Technical Reports Server (NTRS)

    Medeiros, Samantha

    2017-01-01

    The Spaceport Command and Control System (SCCS) is being built at the Kennedy Space Center in order to successfully launch NASA’s revolutionary vehicle that allows humans to explore further into space than ever before. During my internship, I worked with the Network, Firewall, and Hardware teams that are all contributing to the huge SCCS network project effort. I learned the SCCS network design and the several concepts that are running in the background. I also updated and designed documentation for physical networks that are part of SCCS. This includes being able to assist and build physical installations as well as configurations. I worked with the network design for vehicle telemetry interfaces to the Launch Control System (LCS); this allows the interface to interact with other systems at other NASA locations. This network design includes the Space Launch System (SLS), Interim Cryogenic Propulsion Stage (ICPS), and the Orion Multipurpose Crew Vehicle (MPCV). I worked on the network design and implementation in the Customer Avionics Interface Development and Analysis (CAIDA) lab.

  17. Year 3 Magnet Schools Assistance Program Annual Progress Report, 2009-10. E&R Report No. 10.09

    ERIC Educational Resources Information Center

    Brasfield, Jon; Cárdenas, Virginia

    2010-01-01

    The three Magnet Schools Assistance Program (MSAP) schools: East Garner International Baccalaureate Magnet Middle School (EGMMS), Garner International Baccalaureate Magnet High School (GMHS), and Southeast Raleigh Leadership and Technology Magnet High School (SRMHS) have shown progress on MSAP performance measures during the 3rd year of the grant.…

  18. Design of permanent magnet eddy current brake for a small scaled electromagnetic launch model

    NASA Astrophysics Data System (ADS)

    Zhou, Shigui; Yu, Haitao; Hu, Minqiang; Huang, Lei

    2012-04-01

    A variable pole-pitch double-sided permanent magnet (PM) linear eddy current brake (LECB) is proposed for a small scaled electromagnetic launch model. A two-dimensional (2D) analytical steady state model is presented for the double-sided PM-LECB, and the expression for the braking force is derived. Based on the analytical model, the material and eddy current skin effect of the conducting plate are analyzed. Moreover, a variable pole-pitch double-sided PM-LECB is proposed for the effective braking of the moving plate. In addition, the braking force is predicted by finite element (FE) analysis, and the simulated results are in good agreement with the analytical model. Finally, a prototype is presented to test the braking profile for validation of the proposed design.

  19. Advanced Concept

    NASA Image and Video Library

    1999-01-01

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

  20. Electric-field assisted switching of magnetization in perpendicularly magnetized (Ga,Mn)As films at high temperatures

    NASA Astrophysics Data System (ADS)

    Wang, Hailong; Ma, Jialin; Yu, Xueze; Yu, Zhifeng; Zhao, Jianhua

    2017-01-01

    The electric-field effects on the magnetism in perpendicularly magnetized (Ga,Mn)As films at high temperatures have been investigated. An electric-field as high as 0.6 V nm-1 is applied by utilizing a solid-state dielectric Al2O3 film as a gate insulator. The coercive field, saturation magnetization and magnetic anisotropy have been clearly changed by the gate electric-field, which are detected via the anomalous Hall effect. In terms of the Curie temperature, a variation of about 3 K is observed as determined by the temperature derivative of the sheet resistance. In addition, electrical switching of the magnetization assisted by a fixed external magnetic field at 120 K is demonstrated, employing the gate-controlled coercive field. The above experimental results have been attributed to the gate voltage modulation of the hole density in (Ga,Mn)As films, since the ferromagnetism in (Ga,Mn)As is carrier-mediated. The limited modulation magnitude of magnetism is found to result from the strong charge screening effect introduced by the high hole concentration up to 1.10  ×  1021 cm-3, while the variation of the hole density is only about 1.16  ×  1020 cm-3.

  1. Motion of Solid Grains During Magnetic Field-Assisted Directional Solidification

    NASA Astrophysics Data System (ADS)

    Wang, Jiang; Lin, Xin; Fautrelle, Yves; Nguyen-Thi, Henri; Ren, Zhongming

    2018-06-01

    In this paper, we report the visible evidence for thermoelectric magnetic forces (TEMFs) during magnetic field-assisted directional solidification, and their potential to control the motion of solid grains (dendrite fragments or equiaxed grains). These motions are observed by means of synchrotron X-ray radiography and compared with analytic calculations for a spherical particle's motion driven only by TEMFs, which confirms that the observed solid grain motions are the combined result of the TEMFs and gravity. We also carried out corresponding 3D numerical simulations to validate the calculations and further prove our conclusion that TEMF acts on the solid grain and affects its motion trajectory.

  2. A Launch Requirements Trade Study for Active Space Radiation Shielding for Long Duration Human Missions

    NASA Technical Reports Server (NTRS)

    Singleterry, Robert C., Jr.; Bollweg, Ken; Martin, Trent; Westover, Shayne; Battiston, Roberto; Burger, William J.; Meinke, Rainer

    2015-01-01

    A trade study for an active shielding concept based on magnetic fields in a solenoid configuration versus mass based shielding was developed. Monte Carlo simulations were used to estimate the radiation exposure for two values of the magnetic field strength and the mass of the magnetic shield configuration. For each field strength, results were reported for the magnetic region shielding (end caps ignored) and total region shielding (end caps included but no magnetic field protection) configurations. A value of 15 cSv was chosen to be the maximum exposure for an astronaut. The radiation dose estimate over the total shield region configuration cannot be used at this time without a better understanding of the material and mass present in the end cap regions through a detailed vehicle design. The magnetic shield region configuration, assuming the end cap regions contribute zero exposure, can be launched on a single Space Launch System rocket and up to a two year mission can be supported. The magnetic shield region configuration results in two versus nine launches for a comparable mass based shielding configuration. The active shielding approach is clearly more mass efficient because of the reduced number of launches than the mass based shielding for long duration missions.

  3. Controlled morphology and optical properties of n-type porous silicon: effect of magnetic field and electrode-assisted LEF.

    PubMed

    Antunez, Edgar E; Campos, Jose; Basurto, Miguel A; Agarwal, Vivechana

    2014-01-01

    Fabrication of photoluminescent n-type porous silicon (nPS), using electrode-assisted lateral electric field accompanied with a perpendicular magnetic field, is reported. The results have been compared with the porous structures fabricated by means of conventional anodization and electrode-assisted lateral electric field without magnetic field. The lateral electric field (LEF) applied across the silicon substrate leads to the formation of structural gradient in terms of density, dimension, and depth of the etched pores. Apart from the pore shape tunability, the simultaneous application of LEF and magnetic field (MF) contributes to a reduction of the dimension of the pores and promotes relatively more defined pore tips as well as a decreased side-branching in the pore walls of the macroporous structure. Additionally, when using magnetic field-assisted etching, within a certain range of LEF, an enhancement of the photoluminescence (PL) response was obtained.

  4. Controlled morphology and optical properties of n-type porous silicon: effect of magnetic field and electrode-assisted LEF

    PubMed Central

    2014-01-01

    Fabrication of photoluminescent n-type porous silicon (nPS), using electrode-assisted lateral electric field accompanied with a perpendicular magnetic field, is reported. The results have been compared with the porous structures fabricated by means of conventional anodization and electrode-assisted lateral electric field without magnetic field. The lateral electric field (LEF) applied across the silicon substrate leads to the formation of structural gradient in terms of density, dimension, and depth of the etched pores. Apart from the pore shape tunability, the simultaneous application of LEF and magnetic field (MF) contributes to a reduction of the dimension of the pores and promotes relatively more defined pore tips as well as a decreased side-branching in the pore walls of the macroporous structure. Additionally, when using magnetic field-assisted etching, within a certain range of LEF, an enhancement of the photoluminescence (PL) response was obtained. PMID:25313298

  5. Reversible Control of Interfacial Magnetism through Ionic-Liquid-Assisted Polarization Switching

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

    Herklotz, Andreas; Guo, Er-Jia; Wong, Anthony T.

    The ability to control magnetism of materials via electric field enables a myriad of technological innovations in information storage, sensing, and computing. In this paper, we use ionic-liquid-assisted ferroelectric switching to demonstrate reversible modulation of interfacial magnetism in a multiferroic heterostructure composed of ferromagnetic (FM) La 0.8Sr 0.2MnO 3 and ferroelectric (FE) PbZr 0.2Ti 0.8O 3. It is shown that ionic liquids can be used to persistently and reversibly switch a large area of a FE film. Finally, this is a prerequisite for polarized neutron reflectometry (PNR) studies that are conducted to directly probe magnetoelectric coupling of the FE polarizationmore » to the interfacial magnetization.« less

  6. Reversible Control of Interfacial Magnetism through Ionic-Liquid-Assisted Polarization Switching

    DOE PAGES

    Herklotz, Andreas; Guo, Er-Jia; Wong, Anthony T.; ...

    2017-02-06

    The ability to control magnetism of materials via electric field enables a myriad of technological innovations in information storage, sensing, and computing. In this paper, we use ionic-liquid-assisted ferroelectric switching to demonstrate reversible modulation of interfacial magnetism in a multiferroic heterostructure composed of ferromagnetic (FM) La 0.8Sr 0.2MnO 3 and ferroelectric (FE) PbZr 0.2Ti 0.8O 3. It is shown that ionic liquids can be used to persistently and reversibly switch a large area of a FE film. Finally, this is a prerequisite for polarized neutron reflectometry (PNR) studies that are conducted to directly probe magnetoelectric coupling of the FE polarizationmore » to the interfacial magnetization.« less

  7. Delta II THEMIS Pre-Launch

    NASA Image and Video Library

    2002-01-01

    In this aerial view, the Delta II rocket with the THEMIS spacecraft sits ready for launch on Pad 17-B at Cape Canaveral Air Force Station, as the mobile service tower moves away from the pad. THEMIS, an acronym for Time History of Events and Macroscale Interactions during Substorms, consists of five identical probes that will track violent, colorful eruptions near the North Pole. This will be the largest number of scientific satellites NASA has ever launched into orbit aboard a single rocket. The THEMIS mission aims to unravel the mystery behind auroral substorms, an avalanche of magnetic energy powered by the solar wind that intensifies the northern and southern lights. The mission will investigate what causes auroras in the Earth’s atmosphere to dramatically change from slowly shimmering waves of light to wildly shifting streaks of bright color. Launch is scheduled for 6:05 p.m.

  8. Delta II THEMIS Pre-Launch

    NASA Image and Video Library

    2002-01-01

    In this close-up aerial view, the Delta II rocket with the THEMIS spacecraft atop sits ready for launch on Pad 17-B at Cape Canaveral Air Force Station as the mobile service tower moves away from the pad. THEMIS, an acronym for Time History of Events and Macroscale Interactions during Substorms, consists of five identical probes that will track violent, colorful eruptions near the North Pole. This will be the largest number of scientific satellites NASA has ever launched into orbit aboard a single rocket. The THEMIS mission aims to unravel the mystery behind auroral substorms, an avalanche of magnetic energy powered by the solar wind that intensifies the northern and southern lights. The mission will investigate what causes auroras in the Earth’s atmosphere to dramatically change from slowly shimmering waves of light to wildly shifting streaks of bright color. Launch is scheduled for 6:05 p.m.

  9. Delta II THEMIS Pre-Launch

    NASA Image and Video Library

    2002-01-01

    In this close-up aerial view, the Delta II rocket with the THEMIS spacecraft atop sits ready for launch on Pad 17-B at Cape Canaveral Air Force Station as the mobile service tower begins to move away. THEMIS, an acronym for Time History of Events and Macroscale Interactions during Substorms, consists of five identical probes that will track violent, colorful eruptions near the North Pole. This will be the largest number of scientific satellites NASA has ever launched into orbit aboard a single rocket. The THEMIS mission aims to unravel the mystery behind auroral substorms, an avalanche of magnetic energy powered by the solar wind that intensifies the northern and southern lights. The mission will investigate what causes auroras in the Earth’s atmosphere to dramatically change from slowly shimmering waves of light to wildly shifting streaks of bright color. Launch is scheduled for 6:05 p.m.

  10. Forces in magnetospheric launching of micro-ejections

    NASA Astrophysics Data System (ADS)

    Cemeljic, Miljenko

    2013-07-01

    In 2D-axisymmetric simulations with our resistive MHD code Zeus-347 we show that micro-ejections, a quasi-stationary fast ejecta of matter of small mass and angular momentum fluxes, can be launched from a purely resistive magnetosphere above the disk gap. They are produced by a combination of pressure gradient and magnetic forces, in presence of ongoing magnetic reconnection along the boundary layer between the star and the disk, where a current sheet is formed. Mass flux of micro-ejections increases with increasing magnetic field strength and stellar rotation rate.

  11. Magnetic Assisted Colloidal Pattern Formation

    NASA Astrophysics Data System (ADS)

    Yang, Ye

    photoacids, which stabilized the structures after the external field was removed. This approach has potential applications in the fabrication of advanced materials. My thesis is arranged as follows. In Chapter 1, I present a brief background of general pattern formation and why I chose to investigate patterns formed in colloidal systems. I also provide a brief review of field-assisted manipulation techniques in order to motivate why I selected magnetic and acoustic field to study colloidal patterns. In chapter 2, I present the theoretical background of magnetic manipulation, which is the main technique used in my research. In this chapter, I will introduce the basic knowledge on magnetic materials and theories behind magnetic manipulation. The underlining thermodynamic mechanisms and theoretical/computational approaches in colloidal pattern formation are also briefly reviewed. In Chapter 3, I focus on using these concepts to study adhesion forces between particle and surfaces. In Chapter 4, I focus on exploring the ground states of colloidal patterns formed from the anti-ferromagnetic interactions of mixtures of particles, as a function of the particle volume fractions. In Chapter 5, I discuss my research on phase transformations of the well-ordered checkerboard phase formed from the equimolar mixture of magnetic and non-magnetic beads in ferrofluid, and I focus mainly on phase transformations in a slowly varying magnetic field. In Chapter 6, I discuss my work on the superimposed magnetic and acoustic field to study patterns formed from monocomponent colloidal suspensions under vertical confinement. Finally, I conclude my thesis in Chapter 7 and discuss future directions and open questions that can be explored in magnetic field directed self-organization in colloidal systems.

  12. Thermal effects on transducer material for heat assisted magnetic recording application

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

    Ji, Rong, E-mail: Ji-Rong@dsi.a-star.edu.sg; Xu, Baoxi; Cen, Zhanhong

    2015-05-07

    Heat Assisted Magnetic Recording (HAMR) is a promising technology for next generation hard disk drives with significantly increased data recording capacities. In HAMR, an optical near-field transducer (NFT) is used to concentrate laser energy on a magnetic recording medium to fulfill the heat assist function. The key components of a NFT are transducer material, cladding material, and adhesion material between the cladding and the transducer materials. Since transducer materials and cladding materials have been widely reported, this paper focuses on the adhesion materials between the Au transducer and the Al{sub 2}O{sub 3} cladding material. A comparative study for two kindsmore » of adhesion material, Ta and Cr, has been conducted. We found that Ta provides better thermal stability to the whole transducer than Cr. This is because after thermal annealing, chromium forms oxide material at interfaces and chromium atoms diffuse remarkably into the Au layer and react with Au to form Au alloy. This study also provides insights on the selection of adhesion material for HAMR transducer.« less

  13. Magnetically Assisted Remote-controlled Endovascular Catheter for Interventional MR Imaging: In Vitro Navigation at 1.5 T versus X-ray Fluoroscopy

    PubMed Central

    Losey, Aaron D.; Lillaney, Prasheel; Martin, Alastair J.; Cooke, Daniel L.; Wilson, Mark W.; Thorne, Bradford R. H.; Sincic, Ryan S.; Arenson, Ronald L.; Saeed, Maythem

    2014-01-01

    Purpose To compare in vitro navigation of a magnetically assisted remote-controlled (MARC) catheter under real-time magnetic resonance (MR) imaging with manual navigation under MR imaging and standard x-ray guidance in endovascular catheterization procedures in an abdominal aortic phantom. Materials and Methods The 2-mm-diameter custom clinical-grade microcatheter prototype with a solenoid coil at the distal tip was deflected with a foot pedal actuator used to deliver 300 mA of positive or negative current. Investigators navigated the catheter into branch vessels in a custom cryogel abdominal aortic phantom. This was repeated under MR imaging guidance without magnetic assistance and under conventional x-ray fluoroscopy. MR experiments were performed at 1.5 T by using a balanced steady-state free precession sequence. The mean procedure times and percentage success data were determined and analyzed with a linear mixed-effects regression analysis. Results The catheter was clearly visible under real-time MR imaging. One hundred ninety-two (80%) of 240 turns were successfully completed with magnetically assisted guidance versus 144 (60%) of 240 turns with nonassisted guidance (P < .001) and 119 (74%) of 160 turns with standard x-ray guidance (P = .028). Overall mean procedure time was shorter with magnetically assisted than with nonassisted guidance under MR imaging (37 seconds ± 6 [standard error of the mean] vs 55 seconds ± 3, P < .001), and time was comparable between magnetically assisted and standard x-ray guidance (37 seconds ± 6 vs 44 seconds ± 3, P = .045). When stratified by angle of branch vessel, magnetic assistance was faster than nonassisted MR guidance at turns of 45°, 60°, and 75°. Conclusion In this study, a MARC catheter for endovascular navigation under real-time MR imaging guidance was developed and tested. For catheterization of branch vessels arising at large angles, magnetically assisted catheterization was faster than manual catheterization

  14. Magnetically assisted remote-controlled endovascular catheter for interventional MR imaging: in vitro navigation at 1.5 T versus X-ray fluoroscopy.

    PubMed

    Losey, Aaron D; Lillaney, Prasheel; Martin, Alastair J; Cooke, Daniel L; Wilson, Mark W; Thorne, Bradford R H; Sincic, Ryan S; Arenson, Ronald L; Saeed, Maythem; Hetts, Steven W

    2014-06-01

    To compare in vitro navigation of a magnetically assisted remote-controlled (MARC) catheter under real-time magnetic resonance (MR) imaging with manual navigation under MR imaging and standard x-ray guidance in endovascular catheterization procedures in an abdominal aortic phantom. The 2-mm-diameter custom clinical-grade microcatheter prototype with a solenoid coil at the distal tip was deflected with a foot pedal actuator used to deliver 300 mA of positive or negative current. Investigators navigated the catheter into branch vessels in a custom cryogel abdominal aortic phantom. This was repeated under MR imaging guidance without magnetic assistance and under conventional x-ray fluoroscopy. MR experiments were performed at 1.5 T by using a balanced steady-state free precession sequence. The mean procedure times and percentage success data were determined and analyzed with a linear mixed-effects regression analysis. The catheter was clearly visible under real-time MR imaging. One hundred ninety-two (80%) of 240 turns were successfully completed with magnetically assisted guidance versus 144 (60%) of 240 turns with nonassisted guidance (P < .001) and 119 (74%) of 160 turns with standard x-ray guidance (P = .028). Overall mean procedure time was shorter with magnetically assisted than with nonassisted guidance under MR imaging (37 seconds ± 6 [standard error of the mean] vs 55 seconds ± 3, P < .001), and time was comparable between magnetically assisted and standard x-ray guidance (37 seconds ± 6 vs 44 seconds ± 3, P = .045). When stratified by angle of branch vessel, magnetic assistance was faster than nonassisted MR guidance at turns of 45°, 60°, and 75°. In this study, a MARC catheter for endovascular navigation under real-time MR imaging guidance was developed and tested. For catheterization of branch vessels arising at large angles, magnetically assisted catheterization was faster than manual catheterization under MR imaging guidance and was comparable to

  15. Research Technology

    NASA Image and Video Library

    1999-10-01

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

  16. STS-131 Launch from Firing Room 4

    NASA Image and Video Library

    2010-04-05

    STS131-S-055 (5 April 2010) --- Assistant Launch Director Mike Leinbach (right) speaks with NASA commentator Mike Curie in Firing Room 4 in the Launch Control Center at NASA's Kennedy Space Center in Florida prior to the launch of space shuttle Discovery's STS-131 mission. The seven-member STS-131 crew will deliver the multi-purpose logistics module Leonardo, filled with supplies, a new crew sleeping quarters and science racks that will be transferred to the International Space Station's laboratories. The crew also will switch out a gyroscope on the station’s truss structure, install a spare ammonia storage tank and retrieve a Japanese experiment from the station’s exterior. STS-131 is the 33rd shuttle mission to the station and the 131st shuttle mission overall.

  17. Launching of Jets and the Vertical Structure of Accretion Disks

    NASA Astrophysics Data System (ADS)

    Ogilvie, Gordon I.; Livio, Mario

    2001-05-01

    The launching of magnetohydrodynamic outflows from accretion disks is considered. We formulate a model for the local vertical structure of a thin disk threaded by a poloidal magnetic field of dipolar symmetry. The model consists of an optically thick disk matched to an isothermal atmosphere. The disk is supposed to be turbulent and possesses an effective viscosity and an effective magnetic diffusivity. In the atmosphere, if the magnetic field lines are inclined sufficiently to the vertical, a magnetocentrifugal outflow is driven and passes through a slow magnetosonic point close to the surface. We determine how the rate of mass loss varies with the strength and inclination of the magnetic field. In particular, we find that for disks in which the mean poloidal field is sufficiently strong to stabilize the disk against the magnetorotational instability, the mass-loss rate decreases extremely rapidly with increasing field strength and is maximal at an inclination angle of 40°-50°. For turbulent disks with weaker mean fields, the mass-loss rate increases monotonically with increasing strength and inclination of the field, but the solution branch terminates before achieving excessive mass-loss rates. Our results suggest that efficient jet launching occurs for a limited range of field strengths and a limited range of inclination angles in excess of 30°. In addition, we determine the direction and rate of radial migration of the poloidal magnetic flux and discuss whether configurations suitable for jet launching can be maintained against dissipation.

  18. Research Technology

    NASA Image and Video Library

    2001-03-01

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

  19. Magnetic-Nanoflocculant-Assisted Water-Nonpolar Solvent Interface Sieve for Microalgae Harvesting.

    PubMed

    Lee, Kyubock; Na, Jeong-Geol; Seo, Jung Yoon; Shim, Tae Soup; Kim, Bohwa; Praveenkumar, Ramasamy; Park, Ji-Yeon; Oh, You-Kwan; Jeon, Sang Goo

    2015-08-26

    Exploitation of magnetic flocculants is regarded as a very promising energy-saving approach to microalgae harvesting. However, its practical applicability remains limited, mainly because of the problem of the postharvest separation of magnetic flocculants from microalgal flocs, which is crucial both for magnetic-flocculant recycling and high-purity microalgal biomasses, but which is also a very challenging and energy-consuming step. In the present study, we designed magnetic nanoflocculants dually functionalizable by two different organosilane compounds, (3-aminopropyl)triethoxysilane (APTES) and octyltriethoxysilane (OTES), which flocculate negatively charged microalgae and are readily detachable at the water-nonpolar organic solvent (NOS) interface only by application of an external magnetic field. APTES functionalization imparts a positive zeta potential charge (29.6 mV) to magnetic nanoflocculants, thereby enabling microalgae flocculation with 98.5% harvesting efficiency (with a dosage of 1.6 g of dMNF/g of cells). OTES functionalization imparts lipophilicity to magnetic nanoflocculants to make them compatible with NOS, thus effecting efficient separation of magnetic flocculants passing through the water-NOS interface sieve from hydrophilic microalgae. Our new energy-saving approach to microalgae harvesting concentrates microalgal cultures (∼1.5 g/L) up to 60 g/L, which can be directly connected to the following process of NOS-assisted wet lipid extraction or biodiesel production, and therefore provides, by simplifying multiple downstream processes, a great potential cost reduction in microalgae-based biorefinement.

  20. Magnetic levitation assisted aircraft take-off and landing (feasibility study - GABRIEL concept)

    NASA Astrophysics Data System (ADS)

    Rohacs, Daniel; Rohacs, Jozsef

    2016-08-01

    The Technology Roadmap 2013 developed by the International Air Transport Association envisions the option of flying without an undercarriage to be in operation by 2032. Preliminary investigations clearly indicate that magnetic levitation technology (MagLev) might be an appealing solution to assist the aircraft take-off and landing. The EU supported research project, abbreviated as GABRIEL, was dealing with (i) the concept development, (ii) the identification, evaluation and selection of the deployable magnetic levitation technology, (iii) the definition of the core system elements (including the required aircraft modifications, the ground-based system and airport elements, and the rendezvous control system), (iv) the analysis of the safety and security aspects, (v) the concept validation and (vi) the estimation of the proposed concept impact in terms of aircraft weight, noise, emission, cost-benefit). All results introduced here are compared to a medium size hypothetic passenger aircraft (identical with an Airbus A320). This paper gives a systematic overview of (i) the applied methods, (ii) the investigation of the possible use of magnetic levitation technology to assist the commercial aircraft take-off and landing processes and (iii) the demonstrations, validations showing the feasibility of the radically new concept. All major results are outlined.

  1. Simulation Assisted Risk Assessment Applied to Launch Vehicle Conceptual Design

    NASA Technical Reports Server (NTRS)

    Mathias, Donovan L.; Go, Susie; Gee, Ken; Lawrence, Scott

    2008-01-01

    A simulation-based risk assessment approach is presented and is applied to the analysis of abort during the ascent phase of a space exploration mission. The approach utilizes groupings of launch vehicle failures, referred to as failure bins, which are mapped to corresponding failure environments. Physical models are used to characterize the failure environments in terms of the risk due to blast overpressure, resulting debris field, and the thermal radiation due to a fireball. The resulting risk to the crew is dynamically modeled by combining the likelihood of each failure, the severity of the failure environments as a function of initiator and time of the failure, the robustness of the crew module, and the warning time available due to early detection. The approach is shown to support the launch vehicle design process by characterizing the risk drivers and identifying regions where failure detection would significantly reduce the risk to the crew.

  2. Wiggler magnetic field assisted third harmonic generation in expanding clusters

    NASA Astrophysics Data System (ADS)

    Vij, Shivani

    2018-04-01

    A simple theoretical model is constructed to study the wiggler magnetic field assisted third harmonic generation of intense short pulse laser in a cluster in its expanding phase. The ponderomotive force of laser causes density perturbations in cluster electron density which couples with wiggler magnetic field to produce a nonlinear current that generates transverse third harmonic. An intense short pulse laser propagating through a gas embedded with atomic clusters, converts it into hot plasma balls via tunnel ionization. Initially, the electron plasma frequency inside the clusters ω pe > \\sqrt{3}{ω }1 (with ω 1 being the frequency of the laser). As the cluster expands under Coulomb force and hydrodynamic pressure, ω pe decreases to \\sqrt{3}{ω }1. At this time, there is resonant enhancement in the efficiency of the third harmonic generation. The efficiency of third harmonic generation is enhanced due to cluster plasmon resonance and by phase matching due to wiggler magnetic field. The effect of cluster size on the expansion rate is studied to observe that the clusters of different radii would expand differently. The impact of laser intensity and wiggler magnetic field on the efficiency of third harmonic generation is also explored.

  3. Magnetisation switching of ECC grains in microwave-assisted magnetic recording

    NASA Astrophysics Data System (ADS)

    Greaves, Simon John; Muraoka, Hiroaki; Kanai, Yasushi

    2018-05-01

    Microwave-assisted magnetic recording was investigated using a planar write head and exchange-coupled composite (ECC) media. When recording on ECC media using a planar head field distribution and the high frequency field generated by a spin torque oscillator it was possible to switch the media magnetisation into the opposite direction to the head field, i.e. the media effectively had a negative coercive field. The conditions for this effect to occur are discussed.

  4. Magnetic design for the PediaFlow ventricular assist device.

    PubMed

    Noh, Myounggyu D; Antaki, James F; Ricci, Michael; Gardiner, Jeff; Paden, Dave; Wu, Jingchun; Prem, Ed; Borovetz, Harvey; Paden, Bradley E

    2008-02-01

    This article describes a design process for a new pediatric ventricular assist device, the PediaFlow. The pump is embodied in a magnetically levitated turbodynamic design that was developed explicitly based on the requirements for chronic support of infants and small children. The procedure entailed the consideration of multiple pump topologies, from which an axial mixed-flow configuration was chosen for further development. The magnetic design includes permanent-magnet (PM) passive bearings for radial support of the rotor, an actively controlled thrust actuator for axial support, and a brushless direct current (DC) motor for rotation. These components are closely coupled both geometrically and magnetically, and were therefore optimized in parallel, using electromagnetic, rotordynamic models and fluid models, and in consideration of hydrodynamic requirements. Multiple design objectives were considered, including efficiency, size, and margin between critical speeds to operating speed. The former depends upon the radial and yaw stiffnesses of the PM bearings. Analytical expressions for the stiffnesses were derived and verified through finite element analysis (FEA). A toroidally wound motor was designed for high efficiency and minimal additional negative radial stiffness. The design process relies heavily on optimization at the component level and system level. The results of this preliminary design optimization yielded a pump design with an overall stability margin of 15%, based on a pressure rise of 100 mm Hg at 0.5 lpm running at 16,000 rpm.

  5. Research Technology

    NASA Image and Video Library

    2000-01-01

    Marshall Space Flight Center’s (MSFC’s) Advanced Space Transportation Program has developed the Magnetic Launch Assist System, formerly known as the Magnetic Levitation (MagLev) technology that could give a space vehicle a running start to break free from Earth’s gravity. A Magnetic Launch Assist system would use magnetic fields to levitate and accelerate a vehicle along a track at speeds up to 600 mph. The vehicle would shift to rocket engines for launch into orbit. Similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway, a Magnetic Launch Assist system would electromagnetically propel a space vehicle along the track. The tabletop experimental track for the system shown in this photograph is 44-feet long, with 22-feet of powered acceleration and 22-feet of passive braking. A 10-pound carrier with permanent magnets on its sides swiftly glides by copper coils, producing a levitation force. The track uses a linear synchronous motor, which means the track is synchronized to turn the coils on just before the carrier comes in contact with them, and off once the carrier passes. Sensors are positioned on the side of the track to determine the carrier’s position so the appropriate drive coils can be energized. MSFC engineers have conducted tests on the indoor track and a 50-foot outdoor track. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  6. San Marco D/L Post Launch Report No. 2

    NASA Technical Reports Server (NTRS)

    1988-01-01

    The San Marco D/L spacecraft, utilizing a NASA supplied Scout expendable launch vehicle, was launched fran the San Marco Range, located off the coast of Kenya, Africa, on March 25, 1988 at 19:50 GMT. The launch was conducted by an Italian crew assisted by LaRC and LTV personnel. The San Marco D/L was the fifth in a series of Italian and United States satellites. The purpose of the mission is to explore the relationship between solar activity and the physics of the equatorial thermosphere and ionosphere. Information now being collected will augment, and be used in correlation with, data and information obtained from ground based facilities and other satellites.

  7. Bit patterned media with composite structure for microwave assisted magnetic recording

    NASA Astrophysics Data System (ADS)

    Eibagi, Nasim

    Patterned magnetic nano-structures are under extensive research due to their interesting emergent physics and promising applications in high-density magnetic data storage, through magnetic logic to bio-magnetic functionality. Bit-patterned media is an example of such structures which is a leading candidate to reach magnetic densities which cannot be achieved by conventional magnetic media. Patterned arrays of complex heterostructures such as exchange-coupled composites are studied in this thesis as a potential for next generation of magnetic recording media. Exchange-coupled composites have shown new functionality and performance advantages in magnetic recording and bit patterned media provide unique capability to implement such architectures. Due to unique resonant properties of such structures, their possible application in spin transfer torque memory and microwave assisted switching is also studied. This dissertation is divided into seven chapters. The first chapter covers the history of magnetic recording, the need to increase magnetic storage density, and the challenges in the field. The second chapter introduces basic concepts of magnetism. The third chapter explains the fabrication methods for thin films and various lithographic techniques that were used to pattern the devices under study for this thesis. The fourth chapter introduces the exchanged coupled system with the structure of [Co/Pd] / Fe / [Co/Pd], where the thickness of Fe is varied, and presents the magnetic properties of such structures using conventional magnetometers. The fifth chapter goes beyond what is learned in the fourth chapter and utilizes polarized neutron reflectometry to study the vertical exchange coupling and reversal mechanism in patterned structures with such structure. The sixth chapter explores the dynamic properties of the patterned samples, and their reversal mechanism under microwave field. The final chapter summarizes the results and describes the prospects for future

  8. MSFC Advanced Concepts Office and the Iterative Launch Vehicle Concept Method

    NASA Technical Reports Server (NTRS)

    Creech, Dennis

    2011-01-01

    This slide presentation reviews the work of the Advanced Concepts Office (ACO) at Marshall Space Flight Center (MSFC) with particular emphasis on the method used to model launch vehicles using INTegrated ROcket Sizing (INTROS), a modeling system that assists in establishing the launch concept design, and stage sizing, and facilitates the integration of exterior analytic efforts, vehicle architecture studies, and technology and system trades and parameter sensitivities.

  9. Lubricant reflow after laser heating in heat assisted magnetic recording

    NASA Astrophysics Data System (ADS)

    Wu, Haoyu; Mendez, Alejandro Rodriguez; Xiong, Shaomin; Bogy, David B.

    2015-05-01

    In heat assisted magnetic recording (HAMR) technology for hard disk drives, the media will be heated to about 500 °C during the writing process in order to reduce its magnetic coercivity and thus allow data writing with the magnetic head transducers. The traditional lubricants such as Z-dol and Z-tetraol may not be able to perform in such harsh heating conditions due to evaporation, decomposition and thermal depletion. However, some of the lubricant depletion can be recovered due to reflow after a period of time, which can help to reduce the chance of head disk interface failure. In this study, experiments of lubricant thermal depletion and reflow were performed using a HAMR test stage for a Z-tetraol type lubricant. Various lubricant depletion profiles were generated using different laser heating conditions. The lubricant reflow process after thermal depletion was monitored by use of an optical surface analyzer. In addition, a continuum based lubrication model was developed to simulate the lubricant reflow process. Reasonably good agreement between simulations and experiments was achieved.

  10. Galileo 1989 VEEGA trajectory design. [Venus-Earth-Earth-Gravity-Assist

    NASA Technical Reports Server (NTRS)

    D'Amario, Louis A.; Byrnes, Dennis V.; Johannesen, Jennie R.; Nolan, Brian G.

    1989-01-01

    The new baseline for the Galileo Mission is a 1989 Venus-earth-earth gravity-assist (VEEGA) trajectory, which utilizes three gravity-assist planetary flybys in order to reduce launch energy requirements significantly compared to other earth-Jupiter transfer modes. The launch period occurs during October-November 1989. The total flight time is about 6 years, with November 1995 as the most likely choice for arrival at Jupiter. Optimal 1989 VEEGA trajectories have been generated for a wide range of earth launch dates and Jupiter arrival dates. Launch/arrival space contour plots are presented for various trajectory parameters, including propellant margin, which is used to measure mission performance. The accessible region of the launch/arrival space is defined by propellant margin and launch energy constraints; the available launch period is approximately 1.5 months long.

  11. Flat super-oscillatory lens for heat-assisted magnetic recording with sub-50 nm resolution.

    PubMed

    Yuan, Guanghui; Rogers, Edward T F; Roy, Tapashree; Shen, Zexiang; Zheludev, Nikolay I

    2014-03-24

    Heat-assisted magnetic recording (HAMR) is a future roadmap technology to overcome the superparamagnetic limit in high density magnetic recording. Existing HAMR schemes depend on a simultaneous magnetic stimulation and light-induced local heating of the information carrier. To achieve high-density recorded data, near-field plasmonic transducers have been proposed as light concentrators. Here we suggest and investigate in detail an alternative approach exploiting a far-field focusing device that can focus light into sub-50 nm hot-spots in the magnetic recording layer using a laser source operating at 473 nm. It is based on a recently introduced super-oscillatory flat lens improved with the use of solid immersion, giving an effective numerical aperture as high as 4.17. The proposed solution is robust and easy to integrate with the magnetic recording head thus offering a competitive advantage over plasmonic technology.

  12. Interfering lipoproteins in magnetic field-assisted agglutination of superparamagnetic particles immunoassay.

    PubMed

    Cauet, Gilles; Daynès, Aurélien; Temurok, Nevzat

    2016-04-01

    The technology of magnetic field-assisted immuno-agglutination of superparamagnetic particles allows sensitive detection of biomarkers in whole blood. However, we observed non-specific agglutination (NSA), due to interfering plasma proteins, that negatively affects C-reactive protein immunoassay. The objective of the study was to identify the plasma proteins involved and to eliminate these interferences. Plasma was fractionated by size exclusion HPLC and each fraction was tested for non-specific agglutination. In addition, plasma proteins bound to magnetic particles were analyzed by SDS-gel electrophoresis and identified by mass spectrometry. We found that NSA was due to the binding of some lipoproteins to the particles. NSA was observed in the presence of purified LDL and VLDL but not HDL. NSA was mediated by the binding of ApoB100 to magnetic particles through its heparin binding sites. These interferences could be eliminated by addition of heparin or other polyanions like dextran sulfate to the assay buffer. NSA results from the binding of some plasma lipoproteins to magnetic particles. The use of a polyanion to eliminate these interferences allows the formulation of a stable reagent.

  13. Single axis controlled hybrid magnetic bearing for left ventricular assist device: hybrid core and closed magnetic circuit.

    PubMed

    da Silva, Isaias; Horikawa, Oswaldo; Cardoso, Jose R; Camargo, Fernando A; Andrade, Aron J P; Bock, Eduardo G P

    2011-05-01

    In previous studies, we presented main strategies for suspending the rotor of a mixed-flow type (centrifugal and axial) ventricular assist device (VAD), originally presented by the Institute Dante Pazzanese of Cardiology (IDPC), Brazil. Magnetic suspension is achieved by the use of a magnetic bearing architecture in which the active control is executed in only one degree of freedom, in the axial direction of the rotor. Remaining degrees of freedom, excepting the rotation, are restricted only by the attraction force between pairs of permanent magnets. This study is part of a joint project in development by IDPC and Escola Politecnica of São Paulo University, Brazil. This article shows advances in that project, presenting two promising solutions for magnetic bearings. One solution uses hybrid cores as electromagnetic actuators, that is, cores that combine iron and permanent magnets. The other solution uses actuators, also of hybrid type, but with the magnetic circuit closed by an iron core. After preliminary analysis, a pump prototype has been developed for each solution and has been tested. For each prototype, a brushless DC motor has been developed as the rotor driver. Each solution was evaluated by in vitro experiments and guidelines are extracted for future improvements. Tests have shown good results and demonstrated that one solution is not isolated from the other. One complements the other for the development of a single-axis-controlled, hybrid-type magnetic bearing for a mixed-flow type VAD. © 2011, Copyright the Authors. Artificial Organs © 2011, International Center for Artificial Organs and Transplantation and Wiley Periodicals, Inc.

  14. XMCD and XMCD-PEEM Studies on Magnetic-Field-Assisted Self-Assembled 1D Nanochains of Spherical Ferrite Particles

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

    Zhang, Wen; Wong, Ping Kwan Johnny; Zhang, Dong

    Quasi-1D nanochains of spherical magnetic ferrite particles with a homogeneous particle size of ≈200 nm and a micrometer-sized chain length are fabricated in this paper via a self-assembly method under an external magnetic field. This assisting magnetic field (H assist), applied during synthesis, significantly modifies the distribution of the Fe 2+O h, Fe 3+T d, and Fe 3+O h cations in the chains, as demonstrated by X-ray magnetic circular dichroism (XMCD) combined with theoretical analysis. This provides direct evidence of the nontrivial role of external synthetic conditions for defining the crystal chemistry of nanoscale ferrites and in turn their magneticmore » properties, providing an extra degree of freedom for intentional control over the performances of 1D magnetic nanodevices for various applications. Magnetic imaging, performed via XMCD in photoemission electron microscopy, further shows the possibility of creating and trapping a series of adjacent magnetic domain walls in a single chain, suggesting that there is great application potential for these nanochains in 1D magnetic nanodevices, as determined by field- or current-driven domain wall motions. Finally, practical control over the magnetic properties of the nanochains is also achieved by extrinsic dopants of cobalt and zinc, which are observed to occupy the ferrite ionic sites in a selective manner.« less

  15. XMCD and XMCD-PEEM Studies on Magnetic-Field-Assisted Self-Assembled 1D Nanochains of Spherical Ferrite Particles

    DOE PAGES

    Zhang, Wen; Wong, Ping Kwan Johnny; Zhang, Dong; ...

    2017-05-30

    Quasi-1D nanochains of spherical magnetic ferrite particles with a homogeneous particle size of ≈200 nm and a micrometer-sized chain length are fabricated in this paper via a self-assembly method under an external magnetic field. This assisting magnetic field (H assist), applied during synthesis, significantly modifies the distribution of the Fe 2+O h, Fe 3+T d, and Fe 3+O h cations in the chains, as demonstrated by X-ray magnetic circular dichroism (XMCD) combined with theoretical analysis. This provides direct evidence of the nontrivial role of external synthetic conditions for defining the crystal chemistry of nanoscale ferrites and in turn their magneticmore » properties, providing an extra degree of freedom for intentional control over the performances of 1D magnetic nanodevices for various applications. Magnetic imaging, performed via XMCD in photoemission electron microscopy, further shows the possibility of creating and trapping a series of adjacent magnetic domain walls in a single chain, suggesting that there is great application potential for these nanochains in 1D magnetic nanodevices, as determined by field- or current-driven domain wall motions. Finally, practical control over the magnetic properties of the nanochains is also achieved by extrinsic dopants of cobalt and zinc, which are observed to occupy the ferrite ionic sites in a selective manner.« less

  16. Large Diameter Shuttle Launched-AEM (LDSL-AEM) study

    NASA Technical Reports Server (NTRS)

    1976-01-01

    A technical description of a Large Diameter Shuttle Launched-AEM (LDSL-AEM), an AEM base module adapted to carry 5 ft diameter payloads in the shuttle with propulsion for carrying payloads to higher altitude orbits from a 150 NM shuttle orbit, is described. The AEM is designed for launch on the scout launch vehicle. Onboard equipment provides capability to despin, acquire the earth, and control the vehicle in an earth pointing mode using reaction wheels for torque with magnets for all attitude acquisition, wheel desaturation, and nutation damping. Earth sensors in the wheels provide pitch and roll attitude. This system provides autonomous control capability to 1 degree in pitch and roll and 2 degrees in yaw. The attitude can be determined to .5 degrees in pitch and roll and 2 degrees in yaw.

  17. A two-stage heating scheme for heat assisted magnetic recording

    NASA Astrophysics Data System (ADS)

    Xiong, Shaomin; Kim, Jeongmin; Wang, Yuan; Zhang, Xiang; Bogy, David

    2014-05-01

    Heat Assisted Magnetic Recording (HAMR) has been proposed to extend the storage areal density beyond 1 Tb/in.2 for the next generation magnetic storage. A near field transducer (NFT) is widely used in HAMR systems to locally heat the magnetic disk during the writing process. However, much of the laser power is absorbed around the NFT, which causes overheating of the NFT and reduces its reliability. In this work, a two-stage heating scheme is proposed to reduce the thermal load by separating the NFT heating process into two individual heating stages from an optical waveguide and a NFT, respectively. As the first stage, the optical waveguide is placed in front of the NFT and delivers part of laser energy directly onto the disk surface to heat it up to a peak temperature somewhat lower than the Curie temperature of the magnetic material. Then, the NFT works as the second heating stage to heat a smaller area inside the waveguide heated area further to reach the Curie point. The energy applied to the NFT in the second heating stage is reduced compared with a typical single stage NFT heating system. With this reduced thermal load to the NFT by the two-stage heating scheme, the lifetime of the NFT can be extended orders longer under the cyclic load condition.

  18. Performance of a continuous flow ventricular assist device: magnetic bearing design, construction, and testing.

    PubMed

    Allaire, P; Hilton, E; Baloh, M; Maslen, E; Bearnson, G; Noh, D; Khanwilkar, P; Olsen, D

    1998-06-01

    A new centrifugal continuous flow ventricular assist device, the CFVAD III, which is fully magnetic bearing suspended, has been developed. It has only one moving part (the impeller), has no contact (magnetic suspension), is compact, and has minimal heating. A centrifugal impeller of 2 inch outer diameter is driven by a permanent magnet brushless DC motor. This paper discusses the design, construction, testing, and performance of the magnetic bearings in the unit. The magnetic suspension consists of an inlet side magnetic bearing and an outlet side magnetic bearing, each divided into 8 pole segments to control axial and radial displacements as well as angular displacements. The magnetic actuators are composed of several different materials to minimize size and weight while having sufficient load capacity to support the forces on the impeller. Flux levels in the range of 0.1 T are employed in the magnetic bearings. Self sensing electronic circuits (without physical sensors) are employed to determine the impellar position and provide the feedback control signal needed for the magnetic bearing control loops. The sensors provide position sensitivity of approximately 0.025 mm. A decentralized 5 axis controller has been developed using modal control techniques. Proportional integral derivative controls are used for each axis to levitate the magnetically supported impeller.

  19. GOLD Mission Launches to Study Near-Space Environment

    NASA Image and Video Library

    2018-01-25

    On Jan. 25, NASA’s Global-scale Observations of the Limb and Disk, or GOLD mission, launched from French Guiana. GOLD is an instrument launching on a commercial satellite to inspect, from geostationary orbit, the dynamic intermingling of space and Earth’s uppermost atmosphere. GOLD will seek to understand what drives change in this region where terrestrial weather in the lower atmosphere interacts with the tumult of solar activity from above and Earth’s magnetic field. Resulting data will improve forecasting models of space weather events that can impact life on Earth, as well as satellites and astronauts in space.

  20. Aerodynamic flight control to increase payload capability of future launch vehicles

    NASA Technical Reports Server (NTRS)

    Cochran, John E., Jr.

    1995-01-01

    The development of new launch vehicles will require that designers use innovative approaches to achieve greater performance in terms of pay load capability. The objective of the work performed under this delivery order was to provide technical assistance to the Contract Officer's Technical Representative (COTR) in the development of ideas and concepts for increasing the payload capability of launch vehicles by incorporating aerodynamic controls. Although aerodynamic controls, such as moveable fins, are currently used on relatively small missiles, the evolution of large launch vehicles has been moving away from aerodynamic control. The COTR reasoned that a closer investigation of the use of aerodynamic controls on large vehicles was warranted.

  1. Ultrasound-assisted fabrication of a biocompatible magnetic hydroxyapatite.

    PubMed

    Zhou, Gang; Song, Wei; Hou, Yongzhao; Li, Qing; Deng, Xuliang; Fan, Yubo

    2014-10-01

    This work describes the fabrication and characterization of a biocompatible magnetic hydroxyapatite (HA) using an ultrasound-assisted co-precipitation method. X-ray diffraction (XRD), Fourier transform infrared spectroscopy (FT-IR), and transmission electron microscopy (TEM) were used to characterize the structure and chemical composition of the produced samples. The M-H loops of synthesized materials were traced using a vibrating sample magnetometer (VSM) and the biocompatibility was evaluated by cell culture and MTT (3-(4,5-dimethylthiazol-2-yl)-2,5-diphenyltetrazolium bromide) assay. Furthermore, in vivo histopathological examinations were used to evaluate the potential toxicological effects of Fe₃O₄-HA composites on kidney of SD rats injected intraperitoneally with Fe₃O₄-HA particles. The results showed that magnetic iron oxide particles first replace OH ions of HA, which are parallel to the c axis, and then enter the HA crystal lattice which produces changes in the crystal surface of HA. Chemical bond interaction was observed between PO₄³⁻ groups of HA and iron ions of Fe₃O₄. The saturation magnetization (MS ) of Fe₃O₄-HA composites was 46.36 emu/g obtained from VSM data. Cell culture and MTT assays indicated that HA could affect the growth and proliferation of HEK-293 cells. This Fe₃O₄-HA composite produced no negative effects on cell morphology, viability, and proliferation and exhibited remarkable biocompatibility. Moreover, no inflammatory cell infiltration was observed in kidney histopathology slices. Therefore, this study succeeds to develop a Fe₃O₄-HA composite as a prospective biomagnetic material for future applications. © 2013 Wiley Periodicals, Inc.

  2. Atomic hydrogen as a launch vehicle propellant

    NASA Technical Reports Server (NTRS)

    Palaszewski, Bryan A.

    1990-01-01

    An analysis of several atomic hydrogen launch vehicles was conducted. A discussion of the facilities and the technologies that would be needed for these vehicles is also presented. The Gross Liftoff Weights (GLOW) for two systems were estimated; their specific impulses (I sub sp) were 750 and 1500 lb (sub f)/s/lb(sub m). The atomic hydrogen launch vehicles were also compared to the currently planned Advanced Launch System design concepts. Very significant GLOW reductions of 52 to 58 percent are possible over the Advanced Launch System designs. Applying atomic hydrogen propellants to upper stages was also considered. Very high I(sub sp) (greater than 750 1b(sub f)/s/lb(sub m) is needed to enable a mass savings over advanced oxygen/hydrogen propulsion. Associated with the potential benefits of high I(sub sp) atomic hydrogen are several challenging problems. Very high magnetic fields are required to maintain the atomic hydrogen in a solid kilogauss (3 Tesla). Also the storage temperature of the propellant is 4 K. This very low temperature will require a large refrigeration facility for the launch vehicle. The design considerations for a very high recombination rate for the propellant are also discussed. A recombination rate of 210 cm/s is predicted for atomic hydrogen. This high recombination rate can produce very high acceleration for the launch vehicle. Unique insulation or segmentation to inhibit the propellant may be needed to reduce its recombination rate.

  3. Bipolar Jets Launched by a Mean-field Accretion Disk Dynamo

    NASA Astrophysics Data System (ADS)

    Fendt, Christian; Gaßmann, Dennis

    2018-03-01

    By applying magnetohydrodynamic simulations, we investigate the launching of jets driven by a disk magnetic field generated by a mean-field disk dynamo. Extending our earlier studies, we explore the bipolar evolution of the disk α 2Ω-dynamo and the outflow. We confirm that a negative dynamo-α leads to a dipolar field geometry, whereas positive values generate quadrupolar fields. The latter remain mainly confined to the disk and cannot launch outflows. We investigate a parameter range for the dynamo-α ranging from a critical value below which field generation is negligible, {α }0,{crit}=-0.0005, to α 0 = ‑1.0. For weak | {α }0| ≤slant 0.07, two magnetic loop structures with opposite polarity may arise, which leads to reconnection and disturbs the field evolution and accretion-ejection process. For a strong dynamo-α, a higher poloidal magnetic energy is reached, roughly scaling with {E}mag}∼ | {α }0| , which also leads to higher accretion and ejection rates. The terminal jet speed is governed by the available magnetic energy and increases with the dynamo-α. We find jet velocities on the order of the inner disk Keplerian velocity. For a strong dynamo-α, oscillating dynamo modes may occur that can lead to a pulsed ejection. This is triggered by an oscillating mode in the toroidal field component. The oscillation period is comparable to the Keplerian timescale in the launching region, thus too short to be associated with the knots in observed jets. We find a hemispherically asymmetric evolution for the jet and counter-jet in the mass flux and field structure.

  4. Vertical Si nanowire arrays fabricated by magnetically guided metal-assisted chemical etching

    NASA Astrophysics Data System (ADS)

    Chun, Dong Won; Kim, Tae Kyoung; Choi, Duyoung; Caldwell, Elizabeth; Kim, Young Jin; Paik, Jae Cheol; Jin, Sungho; Chen, Renkun

    2016-11-01

    In this work, vertically aligned Si nanowire arrays were fabricated by magnetically guided metal-assisted directional chemical etching. Using an anodized aluminum oxide template as a shadow mask, nanoscale Ni dot arrays were fabricated on an Si wafer to serve as a mask to protect the Si during the etching. For the magnetically guided chemical etching, we deposited a tri-layer metal catalyst (Au/Fe/Au) in a Swiss-cheese configuration and etched the sample under the magnetic field to improve the directionality of the Si nanowire etching and increase the etching rate along the vertical direction. After the etching, the nanowires were dried with minimal surface-tension-induced aggregation by utilizing a supercritical CO2 drying procedure. High-resolution transmission electron microscopy (HR-TEM) analysis confirmed the formation of single-crystal Si nanowires. The method developed here for producing vertically aligned Si nanowire arrays could find a wide range of applications in electrochemical and electronic devices.

  5. Heat assisted magnetic recording with patterned FePt recording media using a lollipop near field transducer

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

    Ghoreyshi, Ali; Victora, R. H., E-mail: victora@umn.edu

    In heat-assisted magnetic recording, optical energy is transferred to a small optical spot on the recording media using a near field transducer. In this study, a scattered field finite difference time domain simulation is used to analyze the performance of a lollipop transducer in heat assisted magnetic recording on both a patterned FePt media and a continuous thin film. To represent wear, sharp corners of the peg are approximated with curved ones, which are found to narrow the track width without excessive loss of intensity. Compared with continuous media, the patterned media exhibits higher energy efficiency and a better concentratedmore » optical beam spot. This effect is due to the near field effects of patterned media on the performance of the transducer.« less

  6. Lubricant depletion under various laser heating conditions in Heat Assisted Magnetic Recording (HAMR)

    NASA Astrophysics Data System (ADS)

    Xiong, Shaomin; Wu, Haoyu; Bogy, David

    2014-09-01

    Heat assisted magnetic recording (HAMR) is expected to increase the storage areal density to more than 1 Tb/in2 in hard disk drives (HDDs). In this technology, a laser is used to heat the magnetic media to the Curie point (~400-600 °C) during the writing process. The lubricant on the top of a magnetic disk could evaporate and be depleted under the laser heating. The change of the lubricant can lead to instability of the flying slider and failure of the head-disk interface (HDI). In this study, a HAMR test stage is developed to study the lubricant thermal behavior. Various heating conditions are controlled for the study of the lubricant thermal depletion. The effects of laser heating repetitions and power levels on the lubricant depletion are investigated experimentally. The lubricant reflow behavior is discussed as well.

  7. Crew Launch Vehicle Mobile Launcher Solid Rocket Motor Plume Induced Environment

    NASA Technical Reports Server (NTRS)

    Vu, Bruce T.; Sulyma, Peter

    2008-01-01

    The plume-induced environment created by the Ares 1 first stage, five-segment reusable solid rocket motor (RSRMV) will impose high heating rates and impact pressures on Launch Complex 39. The extremes of these environments pose a potential threat to weaken or even cause structural components to fail if insufficiently designed. Therefore the ability to accurately predict these environments is critical to assist in specifying structural design requirements to insure overall structural integrity and flight safety. This paper presents the predicted thermal and pressure environments induced by the launch of the Crew Launch Vehicle (CLV) from Launch Complex (LC) 39. Once the environments are predicted, a follow-on thermal analysis is required to determine the surface temperature response and the degradation rate of the materials. An example of structures responding to the plume-induced environment will be provided.

  8. eLaunch Hypersonics: An Advanced Launch System

    NASA Technical Reports Server (NTRS)

    Starr, Stanley

    2010-01-01

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

  9. Spin-Orbit Torque-Assisted Switching in Magnetic Insulator Thin Films with Perpendicular Magnetic Anisotropy

    NASA Astrophysics Data System (ADS)

    Wu, Mingzhong

    As an in-plane charge current flows in a heavy metal film with spin-orbit coupling, it produces a torque that can induce magnetization switching in a neighboring ferromagnetic metal film. Such spin-orbit torque (SOT)-induced switching has been studied extensively in recent years and has shown higher efficiency than switching using conventional spin-transfer torque. This presentation reports the SOT-assisted switching in heavy metal/magnetic insulator systems.1 The experiments made use of Pt/BaFe12O19 bi-layered structures. Thanks to its strong spin-orbit coupling, Pt has been widely used to produce pure spin currents in previous studies. BaFe12O19 is an M-type barium hexagonal ferrite and is often referred as BaM. It is one of the few magnetic insulators with strong magneto-crystalline anisotropy and shows an effective uniaxial anisotropy field of about 17 kOe. It's found that the switching response in the BaM film strongly depends on the charge current applied to the Pt film. When a constant magnetic field is applied in the film plane, the charge current in the Pt film can switch the normal component of the magnetization (M⊥) in the BaM film between the up and down states. The current also dictates the up and down states of the remnant magnetization when the in-plane field is reduced to zero. When M⊥ is measured by sweeping an in-plane field, the response manifests itself as a hysteresis loop, which evolves in a completely opposite manner if the sign of the charge current is flipped. When the coercivity is measured by sweeping an out-of-plane field, its value can be reduced or increased by as much as about 500 Oe if an appropriate charge current is applied. 1. P. Li, T. Liu, H. Chang, A. Kalitsov, W. Zhang, G. Csaba, W. Li, D. Richardson, A. Demann, G. Rimal, H. Dey, J. S. Jiang, W. Porod, S. Field, J. Tang, M. C. Marconi, A. Hoffmann, O. Mryasov, and M. Wu, Nature Commun. 7:12688 doi: 10.1038/ncomms12688 (2016).

  10. Automated design of gravity-assist trajectories to Mars and the outer planets

    NASA Technical Reports Server (NTRS)

    Longuski, James M.; Williams, Steve N.

    1991-01-01

    In this paper, a new approach to planetary mission design is described which automates the search for gravity-assist trajectories. This method finds all conic solutions given a range of launch dates, a range of launch energies and a set of target planets. The new design tool is applied to the problems of finding multiple encounter trajectories to the outer planets and Venus gravity-assist trajectories to Mars. The last four-planet grand tour opportunity (until the year 2153) is identified. It requires an earth launch in 1996 and encounters Jupiter, Uranus, Neptune, and Pluto. Venus gravity-assist trajectories to Mars for the 30 year period 1995-2024 are examined. It is shown that in many cases these trajectories require less launch energy to reach Mars than direct ballistic trajectories.

  11. Polymer-assisted iron oxide magnetic nanoparticle immobilized keratinase

    NASA Astrophysics Data System (ADS)

    Konwarh, Rocktotpal; Karak, Niranjan; Rai, Sudhir Kumar; Mukherjee, Ashis Kumar

    2009-06-01

    Nanotechnology holds the prospect for avant-garde changes to improve the performance of materials in various sectors. The domain of enzyme biotechnology is no exception. Immobilization of industrially important enzymes onto nanomaterials, with improved performance, would pave the way to myriad application-based commercialization. Keratinase produced by Bacillus subtilis was immobilized onto poly(ethylene glycol)-supported Fe3O4 superparamagnetic nanoparticles. The optimization process showed that the highest enzyme activity was noted when immobilized onto cyanamide-activated PEG-assisted MNP prepared under conditions of 25 °C and pH 7.2 of the reaction mixture before addition of H2O2 (3% w/w), 2% (w/v) PEG6000 and 0.062:1 molar ratio of PEG to FeCl2·4H2O. Further statistical optimization using response surface methodology yielded an R2 value that could explain more than 94% of the sample variations. Along with the magnetization studies, the immobilization of the enzyme onto the PEG-assisted MNP was characterized by UV, XRD, FTIR and TEM. The immobilization process had resulted in an almost fourfold increase in the enzyme activity over the free enzyme. Furthermore, the immobilized enzyme exhibited a significant thermostability, storage stability and recyclability. The leather-industry-oriented application of the immobilized enzyme was tested for the dehairing of goat-skin.

  12. Astronaut Story Musgrave in launch/landing suit during STS-33 training

    NASA Image and Video Library

    1989-10-20

    S89-48009 (29 Oct. 1996) --- About to embark on his sixth shuttle flight, astronaut Story Musgrave receives assistance with his launch and entry suit during a training session in the Johnson Space Center's (JSC) Shuttle Mockup and Integration Laboratory (SMIL).

  13. Study on Alternative Cargo Launch Options from the Lunar Surface

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

    Cheryl A. Blomberg; Zamir A. Zulkefli; Spencer W. Rich

    In the future, there will be a need for constant cargo launches from Earth to Mars in order to build, and then sustain, a Martian base. Currently, chemical rockets are used for space launches. These are expensive and heavy due to the amount of necessary propellant. Nuclear thermal rockets (NTRs) are the next step in rocket design. Another alternative is to create a launcher on the lunar surface that uses magnetic levitation to launch cargo to Mars in order to minimize the amount of necessary propellant per mission. This paper investigates using nuclear power for six different cargo launching alternatives,more » as well as the orbital mechanics involved in launching cargo to a Martian base from the moon. Each alternative is compared to the other alternative launchers, as well as compared to using an NTR instead. This comparison is done on the basis of mass that must be shipped from Earth, the amount of necessary propellant, and the number of equivalent NTR launches. Of the options, a lunar coil launcher had a ship mass that is 12.7% less than the next best option and 17 NTR equivalent launches, making it the best of the presented six options.« less

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

    NASA Technical Reports Server (NTRS)

    Stromgren, Chel; Cates, Grant; Cirillo, William

    2009-01-01

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

  15. Maglev Launch: Ultra-low Cost, Ultra-high Volume Access to Space for Cargo and Humans

    NASA Astrophysics Data System (ADS)

    Powell, James; Maise, George; Rather, John

    2010-01-01

    Despite decades of efforts to reduce rocket launch costs, improvements are marginal. Launch cost to LEO for cargo is ~$10,000 per kg of payload, and to higher orbit and beyond much greater. Human access to the ISS costs $20 million for a single passenger. Unless launch costs are greatly reduced, large scale commercial use and human exploration of the solar system will not occur. A new approach for ultra low cost access to space-Maglev Launch-magnetically accelerates levitated spacecraft to orbital speeds, 8 km/sec or more, in evacuated tunnels on the surface, using Maglev technology like that operating in Japan for high speed passenger transport. The cost of electric energy to reach orbital speed is less than $1 per kilogram of payload. Two Maglev launch systems are described, the Gen-1System for unmanned cargo craft to orbit and Gen-2, for large-scale access of human to space. Magnetically levitated and propelled Gen-1 cargo craft accelerate in a 100 kilometer long evacuated tunnel, entering the atmosphere at the tunnel exit, which is located in high altitude terrain (~5000 meters) through an electrically powered ``MHD Window'' that prevents outside air from flowing into the tunnel. The Gen-1 cargo craft then coasts upwards to space where a small rocket burn, ~0.5 km/sec establishes, the final orbit. The Gen-1 reference design launches a 40 ton, 2 meter diameter spacecraft with 35 tons of payload. At 12 launches per day, a single Gen-1 facility could launch 150,000 tons annually. Using present costs for tunneling, superconductors, cryogenic equipment, materials, etc., the projected construction cost for the Gen-1 facility is 20 billion dollars. Amortization cost, plus Spacecraft and O&M costs, total $43 per kg of payload. For polar orbit launches, sites exist in Alaska, Russia, and China. For equatorial orbit launches, sites exist in the Andes and Africa. With funding, the Gen-1 system could operate by 2020 AD. The Gen-2 system requires more advanced technology

  16. Rapid Design of Gravity Assist Trajectories

    NASA Technical Reports Server (NTRS)

    Carrico, J.; Hooper, H. L.; Roszman, L.; Gramling, C.

    1991-01-01

    Several International Solar Terrestrial Physics (ISTP) missions require the design of complex gravity assisted trajectories in order to investigate the interaction of the solar wind with the Earth's magnetic field. These trajectories present a formidable trajectory design and optimization problem. The philosophy and methodology that enable an analyst to design and analyse such trajectories are discussed. The so called 'floating end point' targeting, which allows the inherently nonlinear multiple body problem to be solved with simple linear techniques, is described. The combination of floating end point targeting with analytic approximations with a Newton method targeter to achieve trajectory design goals quickly, even for the very sensitive double lunar swingby trajectories used by the ISTP missions, is demonstrated. A multiconic orbit integration scheme allows fast and accurate orbit propagation. A prototype software tool, Swingby, built for trajectory design and launch window analysis, is described.

  17. Microwave-Assisted Synthesis, Microstructure, and Magnetic Properties of Rare-Earth Cobaltites.

    PubMed

    Gutiérrez Seijas, Julia; Prado-Gonjal, Jesús; Ávila Brande, David; Terry, Ian; Morán, Emilio; Schmidt, Rainer

    2017-01-03

    The series of perovskite rare-earth (RE) doped cobaltites (RE)CoO 3 (RE = La-Dy) was prepared by microwave-assisted synthesis. The crystal structure undergoes a change of symmetry depending on the size of the RE cation. LaCoO 3 is rhombohedral, S.G. R3̅c (No. 167), while, for the rest of the RE series (Pr-Dy), the symmetry is orthorhombic, S.G. Pnma (No. 62). The crystal structure obtained by X-ray diffraction was confirmed by high-resolution transmission electron microscopy, which yielded a good match between experimental and simulated images. It is further shown that the well-known magnetism in LaCoO 3 , which involves a thermally induced Co 3+ (d 6 ) low spin to intermediate or high spin state transition, is strongly modified by the RE cation, and a rich variety of magnetic order has been detected across the series.

  18. NASA Social Briefing on Planet-Hunting Mission Launch

    NASA Image and Video Library

    2018-04-15

    NASA and industry leaders speak to NASA Social participants about the agency's Transiting Exoplanet Survey Satellite (TESS) in the Press Site auditorium at Kennedy Space Center in Florida. Speaking to the group is Zach Berta-Thompson, assistant professor, University of Colorado Boulder. TESS is the next step in the search for planets outside of our solar system. The mission will find exoplanets that periodically block part of the light from their host stars, events called transits. The satellite will survey the nearest and brightest stars for two years to search for transiting exoplanets. TESS will launch on a SpaceX Falcon 9 rocket from Space Launch Complex 40 at Cape Canaveral Air Force Station no earlier than 6:32 p.m. EDT on Monday, April 16.

  19. A study on dynamic heat assisted magnetization reversal mechanisms under insufficient reversal field conditions

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

    Chen, Y. J.; Yang, H. Z.; Leong, S. H.

    2014-10-20

    We report an experimental study on the dynamic thermomagnetic (TM) reversal mechanisms at around Curie temperature (Tc) for isolated 60 nm pitch single-domain [Co/Pd] islands heated by a 1.5 μm spot size laser pulse under an applied magnetic reversal field (Hr). Magnetic force microscopy (MFM) observations with high resolution MFM tips clearly showed randomly trapped non-switched islands within the laser irradiated spot after dynamic TM reversal process with insufficient Hr strength. This observation provides direct experimental evidence by MFM of a large magnetization switching variation due to increased thermal fluctuation/agitation over magnetization energy at the elevated temperature of around Tc. The averagemore » percentage of non-switched islands/magnetization was further found to be inversely proportional to the applied reversal field Hr for incomplete magnetization reversal when Hr is less than 13% of the island coercivity (Hc), showing an increased switching field distribution (SFD) at elevated temperature of around Tc (where main contributions to SFD broadening are from Tc distribution and stronger thermal fluctuations). Our experimental study and results provide better understanding and insight on practical heat assisted magnetic recording (HAMR) process and recording performance, including HAMR writing magnetization dynamics induced SFD as well as associated DC saturation noise that limits areal density, as were previously observed and investigated by theoretical simulations.« less

  20. Areal density optimizations for heat-assisted magnetic recording of high-density media

    NASA Astrophysics Data System (ADS)

    Vogler, Christoph; Abert, Claas; Bruckner, Florian; Suess, Dieter; Praetorius, Dirk

    2016-06-01

    Heat-assisted magnetic recording (HAMR) is hoped to be the future recording technique for high-density storage devices. Nevertheless, there exist several realization strategies. With a coarse-grained Landau-Lifshitz-Bloch model, we investigate in detail the benefits and disadvantages of a continuous and pulsed laser spot recording of shingled and conventional bit-patterned media. Additionally, we compare single-phase grains and bits having a bilayer structure with graded Curie temperature, consisting of a hard magnetic layer with high TC and a soft magnetic one with low TC, respectively. To describe the whole write process as realistically as possible, a distribution of the grain sizes and Curie temperatures, a displacement jitter of the head, and the bit positions are considered. For all these cases, we calculate bit error rates of various grain patterns, temperatures, and write head positions to optimize the achievable areal storage density. Within our analysis, shingled HAMR with a continuous laser pulse moving over the medium reaches the best results and thus has the highest potential to become the next-generation storage device.

  1. Analysis of self-heating of thermally assisted spin-transfer torque magnetic random access memory

    DOE PAGES

    Deschenes, Austin; Muneer, Sadid; Akbulut, Mustafa; ...

    2016-11-11

    Thermal assistance has been shown to significantly reduce the required operation power for spin torque transfer magnetic random access memory (STT-MRAM). Proposed heating methods include modified material stack compositions that result in increased self-heating or external heat sources. Here, we analyze the self-heating process of a standard perpendicular magnetic anisotropy STT-MRAM device through numerical simulations in order to understand the relative contributions of Joule, thermoelectric Peltier and Thomson, and tunneling junction heating. A 2D rotationally symmetric numerical model is used to solve the coupled electro-thermal equations including thermoelectric effects and heat absorbed or released at the tunneling junction. We comparemore » self-heating for different common passivation materials, positive and negative electrical current polarity, and different device thermal anchoring and boundaries resistance configurations. The variations considered are found to result in significant differences in maximum temperatures reached. Average increases of 3 K, 10 K, and 100 K for different passivation materials, positive and negative polarity, and different thermal anchoring configurations, respectively, are observed. Furthermore, the highest temperatures, up to 424 K, are obtained for silicon dioxide as the passivation material, positive polarity, and low thermal anchoring with thermal boundary resistance configurations. Interestingly it is also found that due to the tunneling heat, Peltier effect, device geometry, and numerous interfacial layers around the magnetic tunnel junction (MTJ), most of the heat is dissipated on the lower potential side of the magnetic junction. We have observed this asymmetry in heating and is important as thermally assisted switching requires heating of the free layer specifically and this will be significantly different for the two polarity operations, set and reset.« less

  2. GREECE Mission Launching Into Aurora

    NASA Image and Video Library

    2014-03-04

    Caption: A NASA-funded sounding rocket launches into an aurora in the early morning of March 3, 2014, over Venetie, Alaska. The GREECE mission studies how certain structures – classic curls like swirls of cream in coffee -- form in the aurora. Credit: NASA/Christopher Perry More info: On March 3, 2014, at 6:09 a.m. EST, a NASA-funded sounding rocket launched straight into an aurora over Venetie, Alaska. The Ground-to-Rocket Electrodynamics – Electron Correlative Experiment, or GREECE, sounding rocket mission, which launched from Poker Flat Research Range in Poker Flat, Alaska, will study classic curls in the aurora in the night sky. The GREECE instruments travel on a sounding rocket that launches for a ten-minute ride right through the heart of the aurora reaching its zenith over the native village of Venetie, Alaska. To study the curl structures, GREECE consists of two parts: ground-based imagers located in Venetie to track the aurora from the ground and the rocket to take measurements from the middle of the aurora itself. At their simplest, auroras are caused when particles from the sun funnel over to Earth's night side, generate electric currents, and trigger a shower of particles that strike oxygen and nitrogen some 60 to 200 miles up in Earth's atmosphere, releasing a flash of light. But the details are always more complicated, of course. Researchers wish to understand the aurora, and movement of plasma in general, at much smaller scales including such things as how different structures are formed there. This is a piece of information, which in turn, helps paint a picture of the sun-Earth connection and how energy and particles from the sun interact with Earth's own magnetic system, the magnetosphere. GREECE is a collaborative effort between SWRI, which developed particle instruments and the ground-based imaging, and the University of California, Berkeley, measuring the electric and magnetic fields. The launch is supported by a sounding rocket team from

  3. Simulation of Magnetic Field Assisted Finishing (MFAF) Process Utilizing Smart MR Polishing Tool

    NASA Astrophysics Data System (ADS)

    Barman, Anwesa; Das, Manas

    2017-02-01

    Magnetic field assisted finishing process is an advanced finishing process. This process is capable of producing nanometer level surface finish. In this process magnetic field is applied to control the finishing forces using magnetorheological polishing medium. In the current study, permanent magnet is used to provide the required magnetic field in the finishing zone. The working gap between the workpiece and the magnet is filled with MR fluid which is used as the polishing brush to remove surface undulations from the top surface of the workpiece. In this paper, the distribution of magnetic flux density on the workpiece surface and behaviour of MR polishing medium during finishing are analyzed using commercial finite element packages (Ansys Maxwell® and Comsol®). The role of magnetic force in the indentation of abrasive particles on the workpiece surface is studied. A two-dimensional simulation study of the steady, laminar, and incompressible MR fluid flow behaviour during finishing process is carried out. The material removal and surface roughness modelling of the finishing process are also presented. The indentation force by a single active abrasive particle on the workpiece surface is modelled during simulation. The velocity profile of MR fluid with and without application of magnetic field is plotted. It shows non-Newtonian property without application of magnetic field. After that the total material displacement due to one abrasive particle is plotted. The simulated roughness profile is in a good agreement with the experimental results. The conducted study will help in understanding the fluid behavior and the mechanism of finishing during finishing process. Also, the modelling and simulation of the process will help in achieving better finishing performance.

  4. Canadian Space Launch: Exploiting Northern Latitudes For Efficient Space Launch

    DTIC Science & Technology

    2015-04-01

    9  Peoples’ Republic of China .........................................................................................11  USA Launch... taxation and legislation that make Canada an attractive destination for commercial space companies.3 General Definitions Highly Inclined Orbit...launches from sites north of the 35th parallel.33 USA Launch Facilities There are 3 US based launch facilities that conduct launch operations north

  5. Analysis of Particulate Contamination During Launch of MMS Mission

    NASA Technical Reports Server (NTRS)

    Brieda, Lubos; Barrie, Alexander; Hughes, David; Errigo, Therese

    2010-01-01

    NASA's Magnetospheric MultiScale (MMS) is an unmanned constellation of four identical spacecraft designed to investigate magnetic reconnection by obtaining detailed measurements of plasma properties in Earth's magnetopause and magnetotail. Each of the four identical satellites carries a suite of instruments which characterize the ambient ion and electron energy spectrum and composition. Some of these instruments utilize microchannel plates and are sensitive to particulate contamination. In this paper, we analyze the transport of particulates during pre-launch, launch and ascent events, and use the analysis to obtain quantitative predictions of contamination impact on the instruments. Viewfactor calculation is performed by considering the gravitational and aerodynamic forces acting on the particles.

  6. Comparison between the Juno Earth flyby magnetic measurements and the magnetometer package on the IRIS solar observatory

    NASA Astrophysics Data System (ADS)

    Merayo, J. M.; Connerney, J. E.; Joergensen, J. L.; Dougherty, B.

    2013-12-01

    In October 2013 the NASA's Juno New Frontier spacecraft will perform an Earth Flyby Gravity Assist. During this flyby, Juno will reach an altitude of about 600 km and the magnetometer experiment will measure the magnetic field with very high precision. In June 2013 the NASA's IRIS solar observatory was successfully launched. IRIS uses a very fine guiding telescope in order to maintain a high pointing accuracy, assisted by a very high accuracy star tracker and a science grade vector magnetometer. IRIS was placed into a Sun-synchronous orbit at about 600 km altitude by a Pegasus rocket from the Vandenberg Air Force Base in California. This platform will also allow to performing measurements of the Earth's magnetic field with very high precision, since it carries similar instrumentation as on the Swarm satellites (star trackers and magnetometer). The data recorded by the Juno magnetic experiment and the IRIS magnetometer will bring a very exciting opportunity for comparing the two experiments as well as for determining current structures during the flyby.

  7. Launch Vehicles

    NASA Image and Video Library

    2007-09-09

    Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. Launch Pad 39B of the Kennedy Space Flight Center (KSC), currently used for Space Shuttle launches, will be revised to host the Ares launch vehicles. The fixed and rotating service structures standing at the pad will be dismantled sometime after the Ares I-X test flight. A new launch tower for Ares I will be built onto a new mobile launch platform. The gantry for the shuttle doesn't reach much higher than the top of the four segments of the solid rocket booster. Pad access above the current shuttle launch pad structure will not be required for Ares I-X because the stages above the solid rocket booster are inert. For the test scheduled in 2012 or for the crewed flights, workers and astronauts will need access to the highest levels of the rocket and capsule. When the Ares I rocket rolls out to the launch pad on the back of the same crawler-transporters used now, its launch gantry will be with it. The mobile launchers will nestle under three lightning protection towers to be erected around the pad area. Ares time at the launch pad will be significantly less than the three weeks or more the shuttle requires. This “clean pad” approach minimizes equipment and servicing at the launch pad. It is the same plan NASA used with the Saturn V rockets and industry employs it with more modern launchers. The launch pad will also get a new emergency escape system for astronauts, one that looks very much like a roller coaster. Cars riding on a rail will replace the familiar baskets hanging from steel cables. This artist's concept illustrates the Ares I on launch pad 39B.

  8. Radio emission from the X-ray pulsar Her X-1: a jet launched by a strong magnetic field neutron star?

    NASA Astrophysics Data System (ADS)

    van den Eijnden, J.; Degenaar, N.; Russell, T. D.; Miller-Jones, J. C. A.; Wijnands, R.; Miller, J. M.; King, A. L.; Rupen, M. P.

    2018-01-01

    Her X-1 is an accreting neutron star (NS) in an intermediate-mass X-ray binary. Like low-mass X-ray binaries (LMXBs), it accretes via Roche lobe overflow, but similar to many high-mass X-ray binaries containing a NS; Her X-1 has a strong magnetic field and slow spin. Here, we present the discovery of radio emission from Her X-1 with the Very Large Array. During the radio observation, the central X-ray source was partially obscured by a warped disc. We measure a radio flux density of 38.7 ± 4.8 μJy at 9 GHz but cannot constrain the spectral shape. We discuss possible origins of the radio emission, and conclude that coherent emission, a stellar wind, shocks and a propeller outflow are all unlikely explanations. A jet, as seen in LMXBs, is consistent with the observed radio properties. We consider the implications of the presence of a jet in Her X-1 on jet formation mechanisms and on the launching of jets by NSs with strong magnetic fields.

  9. ESA to launch six scientific satellites

    NASA Astrophysics Data System (ADS)

    1995-09-01

    The Infrared Space Observatory, ISO, will lead the trio into space. It will be launched on an Ariane 4 rocket in early November from the European launch site at Kourou, French Guiana. It will be followed in mid-December by SOHO, the Solar and Heliospheric Observatory, which will be launched by an Atlas IIAS rocket from Cape Canaveral, USA. Finally, in mid-January the four Cluster probes will be carried into space on the inaugural flight of Ariane 5. ISO is the world's only orbiting infrared observatory and is the most sophisticated ever. Its sensitive detectors will be cooled to below -270 degrees C, allowing it to observe cool objects in space, invisible through ordinary telescopes. ISO's many scientific goals include studying newly formed stars and planets, investigating the aging process of galaxies and search for the universe's elusive 'dark matter' that is believed to outweigh visible stars and galaxies. The SOHO observatory will provide scientists with a comprehensive study of the sun, the nuclear powerhouse in the centre of our solar system. Its twelve experiments, developed by scientists from Europe and the United States, will investigate the sun from its core outwards -from the very inner workings of the star, to the solar wind which blows through the solar system. The four identical Cluster spacecraft will focus on studying the interaction of the sun with plasmas of the Earth and the magnetic field in a region known as the magnetosphere. The four probes, flying in formation, will allow scientists to build up a three-dimensional picture of the battle between the sun's streams of wind and the Earth's protective magnetic field. These missions represent years of work by scientists across Europe and around the world. The data they gather will provide us with a greater understanding of our own solar neighbourhood and deep space. SPACECRAFT STATUS AS AT 1 SEPTEMBER 95 ISO The ISO satellite, together with all the associated equipment, was transported in June by

  10. First night launch of a Saturn I launch vehicle

    NASA Image and Video Library

    1965-05-25

    First night time launching of a Saturn I launch vehicle took place at 2:35 a.m., May 25, 1965, with the launch of the second Pegasus meteoroid detection satellite from Complex 37, Cape Kennedy, Florida.

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

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

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

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

    NASA Technical Reports Server (NTRS)

    1998-01-01

    Some of Florida's natural foliage stands silent sentinel to the lift off of the Space Shuttle Discovery from Launch Pad 39A at 6:06:24 p.m. EDT June 2. On board Discovery are Mission Commander Charles J. Precourt; Pilot Dominic L. Gorie; and Mission Specialists Wendy B. Lawrence, Franklin R. Chang-Diaz, Janet Lynn Kavandi and Valery Victorovitch Ryumin. The nearly 10-day mission will feature the ninth and final Shuttle docking with the Russian space station Mir, the first Mir docking for the Space Shuttle orbiter Discovery, the first on-orbit test of the Alpha Magnetic Spectrometer (AMS), and the first flight of the new Space Shuttle super lightweight external tank. Astronaut Andrew S. W. Thomas will be returning to Earth as an STS-91 crew member after living more than four months aboard Mir.

  13. Heat-assisted magnetic recording of bit-patterned media beyond 10 Tb/in2

    NASA Astrophysics Data System (ADS)

    Vogler, Christoph; Abert, Claas; Bruckner, Florian; Suess, Dieter; Praetorius, Dirk

    2016-03-01

    The limits of areal storage density that is achievable with heat-assisted magnetic recording are unknown. We addressed this central question and investigated the areal density of bit-patterned media. We analyzed the detailed switching behavior of a recording bit under various external conditions, allowing us to compute the bit error rate of a write process (shingled and conventional) for various grain spacings, write head positions, and write temperatures. Hence, we were able to optimize the areal density yielding values beyond 10 Tb/in2. Our model is based on the Landau-Lifshitz-Bloch equation and uses hard magnetic recording grains with a 5-nm diameter and 10-nm height. It assumes a realistic distribution of the Curie temperature of the underlying material, grain size, as well as grain and head position.

  14. StarTram: An Ultra Low Cost Launch System to Enable Large Scale Exploration of the Solar System

    NASA Astrophysics Data System (ADS)

    Powell, James; Maise, George; Paniagua, John

    2006-01-01

    StarTram is a new approach for low launch to space using Maglev technology. Spacecraft are magnetically levitated and accelerated without propellants to orbital speeds in an evacuated tunnel at ground level using only electrical energy. The cost of the electric energy for acceleration to 8 kilometers per second is only 60 cents per kilogram of payload. After reaching orbital speed, the StarTram spacecraft coast upwards inside an evacuated levitated launch tube to an altitude, of 10 kilometers or more, where they enter the low-pressure ambient atmosphere. The launch tube is magnetically levitated by the repulsive force between a set of high current superconducting cables on it and oppositely directed currents in a set of superconducting cables on the ground beneath. High strength Kevlar tethers anchor the launch tube against crosswinds and prevent it from moving laterally or vertically. A Magneto Hydro Dynamic (MHD) pump at the exit of the evacuated launch tube prevents air from entering the tube. Two StarTram systems are described, a high G (30G) system for cargo only launch and a moderate G (2.5 G) system for passenger/cargo spacecraft. StarTram's projected unit cost is $30 per kilogram of payload launched, including operating and amortization costs. A single StarTram facility could launch more than 100,000 tons of cargo per year and many thousands of passengers. StarTram would use existing superconductors and materials, together with Maglev technology similar to that now operating. The StarTram cargo launch system could be implemented by 2020 AD and the passenger system by 2030 AD.

  15. Space Technology 5 Post-Launch Ground Attitude Estimation Experience

    NASA Technical Reports Server (NTRS)

    Harman, Richard R.

    2007-01-01

    The Space Technology (ST)-5 satellites were launched March 22, 2006 on a Pegasus XL launch vehicle into a Sun-synchronous orbit. The three micro-satellites which constituted the ST-5 mission were kept in a formation which allowed three successive measurements taken of the Earth s magnetic field in order to study short term fluctuations of the field. The attitude of each satellite was computed on the ground using data from the science grade magnetometer as well as the miniature spinning Sun sensor (MSSS) which was the primary attitude sensor. Attitude and orbit maneuvers were performed using a single axial cold gas thruster. This paper describes the ground attitude estimation process and performance as well as anomaly resolutions.

  16. Microwave-assisted RAFT polymerization of well-constructed magnetic surface molecularly imprinted polymers for specific recognition of benzimidazole residues

    NASA Astrophysics Data System (ADS)

    Chen, Fangfang; Wang, Jiayu; Chen, Huiru; Lu, Ruicong; Xie, Xiaoyu

    2018-03-01

    Magnetic nanoparticles have been widely used as support core for fast separation, which could be directly separated from complicated matrices using an external magnet in few minutes. Surface imprinting based on magnetic core has shown favorable adsorption and separation performance, including good adsorption capacity, fast adsorption kinetics and special selectivity adsorption. Reversible addition-fragmentation chain transfer (RAFT) is an ideal choice for producing well-defined complex architecture with mild reaction conditions. We herein describe the preparation of well-constructed magnetic molecularly imprinted polymers (MMIPs) for the recognition of benzimidazole (BMZ) residues via the microwave-assisted RAFT polymerization. The merits of RAFT polymerization assisting with microwave heating allowed successful and more efficient preparation of well-constructed imprinted coats. Moreover, the polymerization time dramatically shortened and was just 1/24th of the time taken by conventional heating. The results indicated that a uniform nanoscale imprinted layer was formed on the Fe3O4 core successfully, and enough saturation magnetization of MMIPs (16.53 emu g-1) was got for magnetic separation. The desirable adsorption capacity (30.18 μmol g-1) and high selectivity toward template molecule with a selectivity coefficient (k) of 13.85 of MMIPs were exhibited by the adsorption isothermal assay and competitive binding assay, respectively. A solid phase extraction enrichment approach was successfully established for the determination of four BMZ residues from apple samples using MMIPs coupled to HPLC. Overall, this study provides a versatile approach for highly efficient fabrication of well-constructed MMIPs for enrichment and determination of target molecules from complicated samples.

  17. Solar system 'fast mission' trajectories using aerogravity assist

    NASA Technical Reports Server (NTRS)

    Randolph, James E.; Mcronald, Angus D.

    1992-01-01

    Initial analyses of the aerogravity assist (AGA) delivery technique to solar system targets (and beyond) has been encouraging. Mission opportunities are introduced that do not exist with typical gravity assist trajectories and current launch capabilities. The technique has the most payoff for high-energy missions such as outer planet orbiters and flybys. The goal of this technique is to reduce the flight duration significantly and to eliminate propulsion for orbit insertion. The paper will discuss detailed analyses and parametric studies that consider launch opportunities for missions to the sun, Saturn, Uranus, Neptune, and Pluto using AGA at Venus and Mars.

  18. Launch Preparation and Rocket Launching

    DTIC Science & Technology

    1991-05-23

    which do not exceed several hundred kilometers. In the USA MBR and heavy rocket carriers to distant distances are transported predominantly on air or...Balloon for transportation of MBR "Minuteman" (drawing): - balloon; 2 - rocket. DOC = 91032701 PAGE 34 Page 20. Thus, for the protection from the axial g...launching is suitable for rockets, launched from surface of the earth (water), or from silo (submarine in submerged state). The selection of

  19. NASA to launch second business communications satellite

    NASA Technical Reports Server (NTRS)

    1981-01-01

    The two stage Delta 3910 launch vehicle was chosen to place the second small business satellite (SBS-B) into a transfer orbit with an apogee of 36,619 kilometers and a perigee of 167 km, at an inclination of 27.7 degrees to Earth's equator. The firing and separation sequence and the inertial guidance system are described as well as the payload assist module. Facilities and services for tracking and control by NASA, COMSAT, Intelsat, and SBS are outlined and prelaunch operations are summarized.

  20. The Launch of an Atlas/Centaur Launch Vehicle

    NASA Technical Reports Server (NTRS)

    1978-01-01

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

  1. COSMOS Launch Services

    NASA Astrophysics Data System (ADS)

    Kalnins, Indulis

    2002-01-01

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

  2. Porous cobalt spheres for high temperature gradient magnetically assisted fluidized beds

    NASA Technical Reports Server (NTRS)

    Atwater, James E.; Akse, James R.; Jovanovic, Goran N.; Wheeler, Richard R Jr; Sornchamni, Thana

    2003-01-01

    Porous metallic cobalt spheres have been prepared as high temperature capable media for employment in gradient magnetically assisted fluidization and filtration technologies. Cobalt impregnated alginate beads are first formed by extrusion of an aqueous suspension of Co3O4 into a Co(II) chloride solution. The organic polymer is thermally decomposed yielding cobalt oxide spheres, followed by reduction to the metallic state, and densification. Cobalt beads have been produced with porosities ranging between 10 and 50%, depending upon sintering conditions. The product media have been characterized by scanning electron microscopy (SEM), nitrogen adsorption porosimetry, and vibrating sample magnetometry. c2003 Elsevier Science Ltd. All rights reserved.

  3. Influence of cooling rate in planar thermally assisted magnetic random access memory: Improved writeability due to spin-transfer-torque influence

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

    Chavent, A.; CNRS, INAC-SPINTEC, F-38000 Grenoble; CEA, INAC-SPINTEC, F-38000 Grenoble

    This paper investigates the effect of a controlled cooling rate on magnetic field reversal assisted by spin transfer torque (STT) in thermally assisted magnetic random access memory. By using a gradual linear decrease of the voltage at the end of the write pulse, the STT decays more slowly or at least at the same rate as the temperature. This condition is necessary to make sure that the storage layer magnetization remains in the desired written direction during cooling of the cell. The influence of the write current pulse decay rate was investigated on two exchange biased synthetic ferrimagnet (SyF) electrodes.more » For a NiFe based electrode, a significant improvement in writing reproducibility was observed using a gradual linear voltage transition. The write error rate decreases by a factor of 10 when increasing the write pulse fall-time from ∼3 ns to 70 ns. For comparison, a second CoFe/NiFe based electrode was also reversed by magnetic field assisted by STT. In this case, no difference between sharp and linear write pulse fall shape was observed. We attribute this observation to the higher thermal stability of the CoFe/NiFe electrode during cooling. In real-time measurements of the magnetization reversal, it was found that Ruderman-Kittel-Kasuya-Yosida (RKKY) coupling in the SyF electrode vanishes for the highest pulse voltages that were used due to the high temperature reached during write. As a result, during the cooling phase, the final state is reached through a spin-flop transition of the SyF storage layer.« less

  4. The Launch Systems Operations Cost Model

    NASA Technical Reports Server (NTRS)

    Prince, Frank A.; Hamaker, Joseph W. (Technical Monitor)

    2001-01-01

    One of NASA's primary missions is to reduce the cost of access to space while simultaneously increasing safety. A key component, and one of the least understood, is the recurring operations and support cost for reusable launch systems. In order to predict these costs, NASA, under the leadership of the Independent Program Assessment Office (IPAO), has commissioned the development of a Launch Systems Operations Cost Model (LSOCM). LSOCM is a tool to predict the operations & support (O&S) cost of new and modified reusable (and partially reusable) launch systems. The requirements are to predict the non-recurring cost for the ground infrastructure and the recurring cost of maintaining that infrastructure, performing vehicle logistics, and performing the O&S actions to return the vehicle to flight. In addition, the model must estimate the time required to cycle the vehicle through all of the ground processing activities. The current version of LSOCM is an amalgamation of existing tools, leveraging our understanding of shuttle operations cost with a means of predicting how the maintenance burden will change as the vehicle becomes more aircraft like. The use of the Conceptual Operations Manpower Estimating Tool/Operations Cost Model (COMET/OCM) provides a solid point of departure based on shuttle and expendable launch vehicle (ELV) experience. The incorporation of the Reliability and Maintainability Analysis Tool (RMAT) as expressed by a set of response surface model equations gives a method for estimating how changing launch system characteristics affects cost and cycle time as compared to today's shuttle system. Plans are being made to improve the model. The development team will be spending the next few months devising a structured methodology that will enable verified and validated algorithms to give accurate cost estimates. To assist in this endeavor the LSOCM team is part of an Agency wide effort to combine resources with other cost and operations professionals to

  5. Morpheus Launch Pad Move

    NASA Image and Video Library

    2014-03-14

    CAPE CANAVERAL, Fla. – Construction workers assist as a crane lowers a portion of the launch pad for the Project Morpheus prototype lander onto a transporter at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The launch pad is being moved to a different location at the landing facility to support the next phase of flight testing. Morpheus completed its seventh free flight test on March 11. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Dimitri Gerondidakis

  6. Morpheus Launch Pad Move

    NASA Image and Video Library

    2014-03-14

    CAPE CANAVERAL, Fla. – Construction workers assist as a crane lowers a large portion of the launch pad for the Project Morpheus prototype lander onto a transporter at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The launch pad is being moved to a different location at the landing facility to support the next phase of flight testing. Morpheus completed its seventh free flight test on March 11. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Dimitri Gerondidakis

  7. Morpheus Launch Pad Move

    NASA Image and Video Library

    2014-03-14

    CAPE CANAVERAL, Fla. – Construction workers assist as a crane is used to lift a large portion of the launch pad for the Project Morpheus prototype lander onto a transporter at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The launch pad is being moved to a different location at the landing facility to support the next phase of flight testing. Morpheus completed its seventh free flight test on March 11. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Dimitri Gerondidakis

  8. U.S. & international small launch vehicles : Quarterly Launch Report : special report

    DOT National Transportation Integrated Search

    1998-01-01

    Since the 1980s, there have been expectations that a substantial commercial market for launch services using small launch vehicles would develop. In fact, commercial launches of small launch vehicles have, in theory, been available since the mid-1980...

  9. Jet Launching in Resistive GR-MHD Black Hole–Accretion Disk Systems

    NASA Astrophysics Data System (ADS)

    Qian, Qian; Fendt, Christian; Vourellis, Christos

    2018-05-01

    We investigate the launching mechanism of relativistic jets from black hole sources, in particular the strong winds from the surrounding accretion disk. Numerical investigations of the disk wind launching—the simulation of the accretion–ejection transition—have so far almost only been done for nonrelativistic systems. From these simulations we know that resistivity, or magnetic diffusivity, plays an important role for the launching process. Here we extend this treatment to general relativistic magnetohydrodynamics (GR-MHD), applying the resistive GR-MHD code rHARM. Our model setup considers a thin accretion disk threaded by a large-scale open magnetic field. We run a series of simulations with different Kerr parameter, field strength, and diffusivity level. Indeed, we find strong disk winds with, however, mildly relativistic speed, the latter most probably due to our limited computational domain. Further, we find that magnetic diffusivity lowers the efficiency of accretion and ejection, as it weakens the efficiency of the magnetic lever arm of the disk wind. As a major driving force of the disk wind we disentangle the toroidal magnetic field pressure gradient; however, magnetocentrifugal driving may also contribute. Black hole rotation in our simulations suppresses the accretion rate owing to an enhanced toroidal magnetic field pressure that seems to be induced by frame dragging. Comparing the energy fluxes from the Blandford–Znajek-driven central spine and the surrounding disk wind, we find that the total electromagnetic energy flux is dominated by the total matter energy flux of the disk wind (by a factor of 20). The kinetic energy flux of the matter outflow is comparatively small and comparable to the Blandford–Znajek electromagnetic energy flux.

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

    NASA Technical Reports Server (NTRS)

    1998-01-01

    Searing the early evening sky with its near sun-like rocket exhaust, the Space Shuttle Discovery lifts off from Launch Pad 39A at 6:06:24 p.m. EDT June 2 on its way to the Mir space station. On board Discovery are Mission Commander Charles J. Precourt; Pilot Dominic L. Gorie; and Mission Specialists Wendy B. Lawrence, Franklin R. Chang-Diaz, Janet Lynn Kavandi and Valery Victorovitch Ryumin. The nearly 10-day mission will feature the ninth and final Shuttle docking with the Russian space station Mir, the first Mir docking for the Space Shuttle orbiter Discovery, the first on-orbit test of the Alpha Magnetic Spectrometer (AMS), and the first flight of the new Space Shuttle super lightweight external tank. Astronaut Andrew S. W. Thomas will be returning to Earth as a STS-91 crew member after living more than four months aboard Mir.

  11. 4. GENERAL VIEW OF LAUNCH PAD B FROM LAUNCH PAD ...

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

    4. GENERAL VIEW OF LAUNCH PAD B FROM LAUNCH PAD A MOBILE SERVICE STRUCTURE; VIEW TO SOUTH. - Cape Canaveral Air Station, Launch Complex 17, Facility 28402, East end of Lighthouse Road, Cape Canaveral, Brevard County, FL

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

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

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

  13. 14 CFR 420.29 - Launch site location review for unproven launch vehicles.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LICENSE TO OPERATE A LAUNCH SITE Criteria and Information Requirements for Obtaining a License § 420.29 Launch site location review for unproven launch vehicles. An applicant for a license to operate a launch site for an unproven launch vehicle shall...

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

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LICENSE TO OPERATE A LAUNCH SITE Criteria and Information Requirements for Obtaining a License § 420.29 Launch site location review for unproven launch vehicles. An applicant for a license to operate a launch site for an unproven launch vehicle shall...

  15. Low energy trajectories to Mars via gravity assist from Venus to earth

    NASA Technical Reports Server (NTRS)

    Williams, S. N.; Longuski, J. M.

    1991-01-01

    The analytical determination of launch dates and proposed trajectories is reviewed with respect to the search for a low-energy trajectory to Mars with gravitational assist from Venus for the years 1995-2024. Both Ballistic and Venus-Earth gravity assist (VEGA) trajectories are calculated with an automated design tool by the authors (1990). The trajectories are modeled as conic sections from one gravitating body to the next, and gravity assist is considered to act impulsively. VEGA trajectories to Mars require similar launch energies for 6 years listed and have moderate arrival C3s, with the lowest C3 requirement in 2015. The flight time and arrival energies of the trajectories are found to be larger than those of ballistic trajectories, but the low-energy launch window makes them desirable for unmanned Mars missions, in particular.

  16. Licensing of commercial launch sites : Quarterly Launch Report : special report :

    DOT National Transportation Integrated Search

    2000-01-01

    The Commercial Space Launch Act of 1984 as recodified at 49 U.S.C. Subtitle IX--Commercial Space Transportation, ch. 701, Commercial Space Launch Activities, 49 U.S.C. '' 70101- authorizes the Secretary of Transportation to license launches or the op...

  17. U.S. small launch vehicles : Quarterly Launch Report : special report

    DOT National Transportation Integrated Search

    1996-01-01

    1995 was an ambitious and difficult year for the United States small launch vehicle market. A total of five small launch vehicles were launched from the United States, two of which were successful (Atlas : E and Pegasus 1) and three of which resulted...

  18. Launch of Agena Target Docking Vehicle atop Atlas launch vehicle

    NASA Technical Reports Server (NTRS)

    1966-01-01

    An Agena Target Docking Vehicle atop its Atlas launch vehicle was launched fromt the Kennedy Space Center's Launch Complex 14 at 6:05 a.m., September 12, 1966. The Agena served as a rendezvous and docking vehicle for the Gemini 11 spacecraft.

  19. STS-120 launch

    NASA Image and Video Library

    2007-10-23

    STS120-S-026 (23 Oct. 2007) --- In the firing room of the Kennedy Space Center in Florida, NASA Shuttle Launch Director Michael Leinbach (second right) and launch managers watch the 11:38 a.m. (EDT) launch of Space Shuttle Discovery. Discovery launched Oct. 23 on a 14-day construction mission to the International Space Station. Photo credit: NASA/Bill Ingalls

  20. Computer-Assisted Monitoring Of A Complex System

    NASA Technical Reports Server (NTRS)

    Beil, Bob J.; Mickelson, Eric M.; Sterritt, John M.; Costantino, Rob W.; Houvener, Bob C.; Super, Mike A.

    1995-01-01

    Propulsion System Advisor (PSA) computer-based system assists engineers and technicians in analyzing masses of sensory data indicative of operating conditions of space shuttle propulsion system during pre-launch and launch activities. Designed solely for monitoring; does not perform any control functions. Although PSA developed for highly specialized application, serves as prototype of noncontrolling, computer-based subsystems for monitoring other complex systems like electric-power-distribution networks and factories.

  1. Morphology and magnetic properties of CeCo5 submicron flakes prepared by surfactant-assisted high-energy ball milling

    NASA Astrophysics Data System (ADS)

    Zhang, J. J.; Gao, H. M.; Yan, Y.; Bai, X.; Su, F.; Wang, W. Q.; Du, X. B.

    2012-10-01

    CeCo5 permanent magnetic alloy has been processed by surfactant assisted high energy ball milling. Heptane and oleic acid were used as the solvent and surfactant, respectively. The amount of surfactant used was 50% by weight of the starting powder. The produced particles were deposited on a piece of copper (4 mm in length and width) under a magnetic field of 27 kOe applied along the copper surface and immobilized by ethyl α-cyanoacrylate. Scanning electron microscope pictures show that the particles are flakes, several μm in length and width and tens of nm in thickness. X-ray diffraction patterns and magnetic measurements prove that the flakes are crystalline with c-axes magnetic anisotropy. The easy magnetization axis is oriented perpendicular to the surface of the flake. A maximum coercivity of 3.3 kOe was obtained for the sample milled for 40 min.

  2. Magnetic suspension of the rotor of a ventricular assist device of mixed flow type.

    PubMed

    Horikawa, Oswaldo; de Andrade, Aron José Pazin; da Silva, Isaías; Bock, Eduardo Guy Perpetuo

    2008-04-01

    This work presents results of preliminary studies concerning application of magnetic bearing in a ventricular assist device (VAD) being developed by Dante Pazzanese Institute of Cardiology-IDPC (São Paulo, Brazil). The VAD-IDPC has a novel architecture that distinguishes from other known VADs. In this, the rotor has a conical geometry with spiral impellers, showing characteristics that are intermediate between a centrifugal VAD and an axial VAD. The effectiveness of this new type of blood pumping principle was showed by tests and by using it in heart surgery for external blood circulation. However, the developed VAD uses a combination of ball bearings and mechanical seals, limiting the life for some 10 h, making impossible its long-term use or its use as an implantable VAD. As a part of development of an implantable VAD, this work aims at the replacement of ball bearings by a magnetic bearing. The most important magnetic bearing principles are studied and the magnetic bearing developed by Escola Politécnica of São Paulo University (EPUSP-MB) is elected because of its very simple architecture. Besides presenting the principle of the EPUSP-MB, this work presents one possible alternative for applying the EPUSP-MB in the IDPC-VAD.

  3. Magnet-assisted device-level alignment for the fabrication of membrane-sandwiched polydimethylsiloxane microfluidic devices

    NASA Astrophysics Data System (ADS)

    Lu, J.-C.; Liao, W.-H.; Tung, Y.-C.

    2012-07-01

    Polydimethylsiloxane (PDMS) microfluidic device is one of the most essential techniques that advance microfluidics research in recent decades. PDMS is broadly exploited to construct microfluidic devices due to its unique and advantageous material properties. To realize more functionalities, PDMS microfluidic devices with multi-layer architectures, especially those with sandwiched membranes, have been developed for various applications. However, existing alignment methods for device fabrication are mainly based on manual observations, which are time consuming, inaccurate and inconsistent. This paper develops a magnet-assisted alignment method to enhance device-level alignment accuracy and precision without complicated fabrication processes. In the developed alignment method, magnets are embedded into PDMS layers at the corners of the device. The paired magnets are arranged in symmetric positions at each PDMS layer, and the magnetic attraction force automatically pulls the PDMS layers into the aligned position during assembly. This paper also applies the method to construct a practical microfluidic device, a tunable chaotic micromixer. The results demonstrate the successful operation of the device without failure, which suggests the accurate alignment and reliable bonding achieved by the method. Consequently, the fabrication method developed in this paper is promising to be exploited to construct various membrane-sandwiched PDMS microfluidic devices with more integrated functionalities to advance microfluidics research.

  4. High-Altitude Balloon Launches for Effective Education, Inspiration and Research

    NASA Astrophysics Data System (ADS)

    Voss, H. D.; Dailey, J.; Patterson, D.; Krueger, J.

    2006-12-01

    Over a three-year period the Taylor University Science Research Training Program (SRTP) has successfully launched and recovered 33 sophisticated payloads to altitudes between 20-33 km (100% success with rapid recovery). All of the payloads included two GPS tracking systems, cameras and monitors, a 110 kbit down link, and uplink command capability for educational experiments (K-12 and undergrad) and nanosatellite subsystem testing. Launches were conducted both day and night, with multiple balloons, with up to 10 experiment boxes, and under varying weather and upper atmospheric conditions. The many launches in a short period of time allowed the payload bus design to evolve toward increased performance, reliability, standardization, simplicity, and modularity for low-cost launch services. The current design uses a Zigbee wireless connection (50 kbaud rate) for each of the payload experiment boxes for rapid assembly and checkout with a common interface board for gathering analog and digital data and for commanding. Common data from each box is processed and displayed using modular LabView software. The use of balloons for active research (ozone, aerosols, cosmic rays. UV, IR, remote sensing, energy, propulsion) significantly invigorates and motivates student development, drives team schedule, uncovers unexpected problems, permits end-to-end closure, and forces calibration and validation of real data. The SRTP has helped to spin off a student company called StratoStar Systems for providing an affordable low-cost balloon launch service capability, insurance plan, and other technical assistance for scientific, industrial and STEM educational use.

  5. Mixing of nanosize particles by magnetically assisted impaction techniques

    NASA Astrophysics Data System (ADS)

    Scicolone, James V.

    approach based on use of small magnetic particles as mixing media is introduced that achieves a high-degree of mixing at scales of about a micron. The method is tested for binary mixture of alumina/silica and silica/titania. Various parameters such as processing time, size of the magnets, and magnetic particle to powder mixed ratio are considered. Experiments are carried out in batch containers in liquid and dry mediums, as well as a fluidized bed set-up. Homogeneity of Mixing (HoM), defined as the compliment of the Intensity of Segregation, was evaluated at the micron scale through field-emission scanning electron microscopy (FESEM) and the energy dispersive x-ray spectroscopy (EDS). Secondary electron images, along with elemental mappings, were used to visualize the change in agglomerate sizes. Compositional percent data of each element were obtained through an EDS spatial distribution point analysis and used to obtain quantitative analysis on the homogeneity of the mixture. The effect of magnet impaction on mixing quality was examined on the HoM of binary mixtures. The research shows that HoM improved with magnetically assisted impaction mixing techniques indicating that the HoM depends on the product of processing time with the number of magnets. In a fluidized bed set-up, MAIM not only improved dispersion, but it was also found that the magnetic particles served to break down the larger agglomerates, to reduce the minimum fluidization velocity, to delay the onset of bubbling, and to convert the fluidization behavior of ABF powder to APF. Thus MAIM techniques may be used to achieve mixing of nanopowders at a desired HoM through adjusting the number of magnets and processing time; and its inherent advantages are its simplicity, an environmentally benign operation, and reduced cost as compared with wet mixing techniques.

  6. Validation of the GOES-16 magnetometer using multipoint measurements and magnetic field models

    NASA Astrophysics Data System (ADS)

    Califf, S.; Loto'aniu, P. T. M.; Redmon, R. J.; Sarris, T. E.; Brito, T.

    2017-12-01

    The Geostationary Operational Environmental Satellites (GOES) have been providing continuous geomagnetic field measurements for over 40 years. While the primary purpose of GOES is operational, the magnetometer data are also widely used in the scientific community. In an effort to validate the recently launched GOES-16 magnetometer, we compare the measurements to existing magnetic field models and other GOES spacecraft currently on orbit. There are four concurrent measurements from GOES-13, 14, 15 and 16 spanning 75W to 135W longitude. Also, GOES-13 is being replaced by GOES-16 in the GOES-East location, and during the transition, GOES-13 and GOES-16 will be parked nearby in order to assist with calibration of the new operational satellite. This work explores techniques to quantify the performance of the GOES-16 magnetometer by comparison to data from nearby spacecraft. We also build on previous work to assimilate in situ measurements with existing magnetic field models to assist in comparing data from different spatial locations. Finally, we use this unique dataset from four simultaneous geosynchronous magnetometer measurements and the close separation between GOES-13 and GOES-16 to study the spatial characteristics of ULF waves and other magnetospheric processes.

  7. Agena Target Vehicle atop Atlas Launch vehicle launched from KSC

    NASA Technical Reports Server (NTRS)

    1966-01-01

    An Agena Target Vehicle atop its Atlas Launch vehicle is launched from the Kennedy Space Center (KSC) Launch Complex 14 at 10:15 am.m., May 17, 1966. The Agena was intended as a rendezvous and docking vehicle for the Gemini 9 spacecraft. However, since the Agena failed to achieve orbit, the Gemini 9 mission was postponed.

  8. Launch Vehicles

    NASA Image and Video Library

    1990-06-01

    The Delta II expendable launch vehicle with the ROSAT (Roentgen Satellite), cooperative space X-ray astronomy mission between NASA, Germany and United Kingdom, was launched from the Cape Canaveral Air Force Station on June 1, 1990.

  9. Employee and family assistance video counseling program: a post launch retrospective comparison with in-person counseling outcomes.

    PubMed

    Veder, Barbara; Pope, Stan; Mani, Michèle; Beaudoin, Kelly; Ritchie, Janice

    2014-01-01

    Access to technologically mediated information and services under the umbrella of mental and physical health has become increasingly available to clients via Internet modalities, according to a recent study. In May 2010, video counseling was added to the counseling services offered through the Employee and Family Assistance Program at Shepell·fgi as a pilot project with a full operational launch in September 2011. The objective of this study was to conduct a retrospective post launch examination of the video counseling service through an analysis of the reported clinical outcomes of video and in-person counseling modalities. A chronological sample of 68 video counseling (VC) cases and 68 in-person (IP) cases were collected from a pool of client clinical files closed in 2012. To minimize the variables impacting the study and maintain as much clinical continuity as possible, the IP and the VC clients must have attended clinical sessions with any one of six counselors who provided both the VC and the IP services. The study compared the two counseling modalities along the following data points (see glossary of terms): (1) client demographic profiles (eg, age, gender, whether the sessions involved individuals or conjoint sessions with couples or families, etc), (2) presenting issue, (3) average session hours, (4) client rating of session helpfulness, (5) rates of goal completion, (6) client withdrawal rates, (7) no show and late cancellation rates, and (8) pre/post client self-assessment. Specific to VC, we examined client geographic location. Data analysis demonstrates that the VC and the IP showed a similar representation of presenting issues with nearly identical outcomes for client ratings of session helpfulness, rates of goal completion, pre/post client self-assessment, average session duration, and client geographic location. There were no statistically significant differences in the rates of withdrawal from counseling, no shows, and late cancellations between

  10. Vented Launch Vehicle Adaptor for a Manned Spacecraft with "Pusher" Launch Abort System

    NASA Technical Reports Server (NTRS)

    Vandervort, Robert E. (Inventor)

    2017-01-01

    A system, method, and apparatus for a vented launch vehicle adaptor (LVA) for a manned spacecraft with a "pusher" launch abort system are disclosed. The disclosed LVA provides a structural interface between a commercial crew vehicle (CCV) crew module/service module (CM/SM) spacecraft and an expendable launch vehicle. The LVA provides structural attachment of the module to the launch vehicle. It also provides a means to control the exhaust plume from a pusher-type launch abort system that is integrated into the module. In case of an on-pad or ascent abort, which requires the module to jettison away from the launch vehicle, the launch abort system exhaust plume must be safely directed away from critical and dangerous portions of the launch vehicle in order to achieve a safe and successful jettison.

  11. Preparation and characterization of magnetic carboxylated nanodiamonds for vortex-assisted magnetic solid-phase extraction of ziram in food and water samples.

    PubMed

    Yılmaz, Erkan; Soylak, Mustafa

    2016-09-01

    A simple and rapid vortex-assisted magnetic solid phase extraction (VA-MSPE) method for the separation and preconcentration of ziram (zinc dimethyldithiocarbamate), subsequent detection of the zinc in complex structure of ziram by flame atomic absorption spectrometry (AAS) has been developed. The ziram content was calculated by using stoichiometric relationship between the zinc and ziram. Magnetic carboxylated nanodiamonds (MCNDs) as solid-phase extraction adsorbent was prepared and characterized by Fourier transform infrared (FT-IR) spectra, X-ray diffraction (XRD) spectrometry and scanning electron microscopy (SEM). These magnetic carboxylated nanodiamonds carrying the ziram could be easily separated from the aqueous solution by applying an external magnetic field; no filtration or centrifugation was necessary. Some important factors influencing the extraction efficiency of ziram such as pH of sample solution, amount of adsorbent, type and volume of eluent, extraction and desorption time and sample volume were studied and optimized. The total extraction and detection time was lower than 10min The preconcentration factor (PF), the precision (RSD, n=7), the limit of detection (LOD) and limit of quantification (LOQ) were 160, 7.0%, 5.3µgL(-1) and 17.5µgL(-1), respectively. The interference of various ions has been examined and the method has been applied for the determination of ziram in various waters, foodstuffs samples and synthetic mixtures. Copyright © 2016 Elsevier B.V. All rights reserved.

  12. Magnetization Switching of a Co /Pt Multilayered Perpendicular Nanomagnet Assisted by a Microwave Field with Time-Varying Frequency

    NASA Astrophysics Data System (ADS)

    Suto, Hirofumi; Kanao, Taro; Nagasawa, Tazumi; Mizushima, Koichi; Sato, Rie

    2018-05-01

    Microwave-assisted magnetization switching (MAS) is attracting attention as a method for reversing nanomagnets with a high magnetic anisotropy by using a small-amplitude magnetic field. We experimentally study MAS of a perpendicularly magnetized nanomagnet by applying a microwave magnetic field with a time-varying frequency. Because the microwave field frequency can follow the nonlinear decrease of the resonance frequency, larger magnetization excitation than that in a constant-frequency microwave field is induced, which enhances the MAS effect. The switching field decreases almost linearly as the start value of the time-varying microwave field frequency increases, and it becomes smaller than the minimum switching field in a constant-frequency microwave field. To obtain this enhancement of the MAS effect, the end value of the time-varying microwave field frequency needs to be almost the same as or lower than the critical frequency for MAS in a constant-frequency microwave field. In addition, the frequency change typically needs to take 1 ns or longer to make the rate of change slow enough for the magnetization to follow the frequency change. This switching behavior is qualitatively explained by the theory based on the macrospin model.

  13. Launch Collision Probability

    NASA Technical Reports Server (NTRS)

    Bollenbacher, Gary; Guptill, James D.

    1999-01-01

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

  14. Electron launching voltage monitor

    DOEpatents

    Mendel, Clifford W.; Savage, Mark E.

    1992-01-01

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

  15. Electron launching voltage monitor

    DOEpatents

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

    1992-03-17

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

  16. Design of an airborne launch vehicle for an air launched space booster

    NASA Technical Reports Server (NTRS)

    Chao, Chin; Choi, Rich; Cohen, Scott; Dumont, Brian; Gibin, Mauricius; Jorden, Rob; Poth, Stefan

    1993-01-01

    A conceptual design is presented for a carrier vehicle for an air launched space booster. This airplane is capable of carrying a 500,000 pound satellite launch system to an altitude over 40,000 feet for launch. The airplane features a twin fuselage configuration for improved payload and landing gear integration, a high aspect ratio wing for maneuverability at altitude, and is powered by six General Electric GE-90 engines. The analysis methods used and the systems employed in the airplane are discussed. Launch costs are expected to be competitive with existing launch systems.

  17. Design of an airborne launch vehicle for an air launched space booster

    NASA Astrophysics Data System (ADS)

    Chao, Chin; Choi, Rich; Cohen, Scott; Dumont, Brian; Gibin, Mauricius; Jorden, Rob; Poth, Stefan

    1993-12-01

    A conceptual design is presented for a carrier vehicle for an air launched space booster. This airplane is capable of carrying a 500,000 pound satellite launch system to an altitude over 40,000 feet for launch. The airplane features a twin fuselage configuration for improved payload and landing gear integration, a high aspect ratio wing for maneuverability at altitude, and is powered by six General Electric GE-90 engines. The analysis methods used and the systems employed in the airplane are discussed. Launch costs are expected to be competitive with existing launch systems.

  18. Launch Vehicle Assessment for Space Solar Power

    NASA Technical Reports Server (NTRS)

    Olds, John R.

    1998-01-01

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

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

    NASA Technical Reports Server (NTRS)

    May, Todd; Lyles, Garry

    2014-01-01

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

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

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Launch site location review-launch site boundary. 420.21 Section 420.21 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... the debris dispersion radius of the largest launch vehicle type and weight class proposed for the...

  1. 14 CFR 420.21 - Launch site location review-launch site boundary.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Launch site location review-launch site boundary. 420.21 Section 420.21 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... the debris dispersion radius of the largest launch vehicle type and weight class proposed for the...

  2. 14 CFR 420.21 - Launch site location review-launch site boundary.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Launch site location review-launch site boundary. 420.21 Section 420.21 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... the debris dispersion radius of the largest launch vehicle type and weight class proposed for the...

  3. 14 CFR 420.21 - Launch site location review-launch site boundary.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Launch site location review-launch site boundary. 420.21 Section 420.21 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... the debris dispersion radius of the largest launch vehicle type and weight class proposed for the...

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

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Launch site location review-launch site boundary. 420.21 Section 420.21 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... the debris dispersion radius of the largest launch vehicle type and weight class proposed for the...

  5. 14 CFR 417.17 - Launch reporting requirements and launch specific updates.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... by the terms of the launch operator's license. A launch operator must file any change to the... information: (i) Payload information required by § 415.59 of this chapter; and (ii) Flight information, including the launch vehicle, planned flight path, staging and impact locations, and any on-orbit activity...

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

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... by the terms of the launch operator's license. A launch operator must file any change to the... information: (i) Payload information required by § 415.59 of this chapter; and (ii) Flight information, including the launch vehicle, planned flight path, staging and impact locations, and any on-orbit activity...

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

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... by the terms of the launch operator's license. A launch operator must file any change to the... information: (i) Payload information required by § 415.59 of this chapter; and (ii) Flight information, including the launch vehicle, planned flight path, staging and impact locations, and any on-orbit activity...

  8. 14 CFR 417.17 - Launch reporting requirements and launch specific updates.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... by the terms of the launch operator's license. A launch operator must file any change to the... information: (i) Payload information required by § 415.59 of this chapter; and (ii) Flight information, including the launch vehicle, planned flight path, staging and impact locations, and any on-orbit activity...

  9. 14 CFR 417.17 - Launch reporting requirements and launch specific updates.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... by the terms of the launch operator's license. A launch operator must file any change to the... information: (i) Payload information required by § 415.59 of this chapter; and (ii) Flight information, including the launch vehicle, planned flight path, staging and impact locations, and any on-orbit activity...

  10. Technicians assist STS-47 MS Jemison prior to JSC bailout training

    NASA Technical Reports Server (NTRS)

    1992-01-01

    STS-47 Endeavour, Orbiter Vehicle (OV) 105, Mission Specialist (MS) Mae C. Jemison, assisted by technicians, adjusts a strap on her launch and entry suit (LES) prior to launch emergency egress (bailout) exercises in JSC's Mockup and Integration Laboratory Bldg 9A. Jemison is making her first flight in space.

  11. Using hybrid magnetic bearings to completely suspend the impeller of a ventricular assist device.

    PubMed

    Khanwilkar, P; Olsen, D; Bearnson, G; Allaire, P; Maslen, E; Flack, R; Long, J

    1996-06-01

    Clinically available blood pumps and those under development suffer from poor mechanical reliability and poor biocompatibility related to anatomic fit, hemolysis, and thrombosis. To alleviate these problems concurrently in a long-term device is a substantial challenge. Based on testing the performance of a prototype, and on our judgment of desired characteristics, we have configured an innovative ventricular assist device, the CFVAD4, for long-term use. The design process and its outcome, the CFVAD4 system configuration, is described. To provide unprecedented reliability and biocompatibility, magnetic bearings completely suspend the rotating pump impeller. The CFVAD4 uses a combination of passive (permanent) and active (electric) magnetic bearings, a mixed flow impeller, and a slotless 3-phase brushless DC motor. These components are shaped, oriented, and integrated to provide a compact, implantable, pancake-shaped unit for placement in the left upper abdominal quadrant of adult humans.

  12. LAUNCH Health Forum

    NASA Image and Video Library

    2010-10-30

    Tom Kalil, Deputy Director of the White House Office of Science and Technology Policy, opens the LAUNCH: Health forum at NASA's Kennedy Space Center in Florida on Saturday, Oct. 30, 2010. LAUNCH: Health provides a forum to discuss accelerating innovation for a sustainable future. LAUNCH: Health partners include NASA, USAID and Nike. Photo Credit: (NASA/Bill Ingalls)

  13. Learning to Lead: The Professional Development Needs of Assistant Principals

    ERIC Educational Resources Information Center

    Allen, James G.; Weaver, Rosa L.

    2014-01-01

    The purpose of this study was to investigate the professional development needs of assistant principals in the northern Kentucky region in preparation for the launch of the Northern Kentucky Assistant Principals' Network, a unique and innovative program to support their leadership development. Using the Educational Leadership Policy Standards:…

  14. Magnet Assisted Composite Manufacturing: A Flexible New Technique for Achieving High Consolidation Pressure in Vacuum Bag/Lay-Up Processes.

    PubMed

    Pishvar, Maya; Amirkhosravi, Mehrad; Altan, M Cengiz

    2018-05-17

    This work demonstrates a protocol to improve the quality of composite laminates fabricated by wet lay-up vacuum bag processes using the recently developed magnet assisted composite manufacturing (MACM) technique. In this technique, permanent magnets are utilized to apply a sufficiently high consolidation pressure during the curing stage. To enhance the intensity of the magnetic field, and thus, to increase the magnetic compaction pressure, the magnets are placed on a magnetic top plate. First, the entire procedure of preparing the composite lay-up on a magnetic bottom steel plate using the conventional wet lay-up vacuum bag process is described. Second, placement of a set of Neodymium-Iron-Boron permanent magnets, arranged in alternating polarity, on the vacuum bag is illustrated. Next, the experimental procedures to measure the magnetic compaction pressure and volume fractions of the composite constituents are presented. Finally, methods used to characterize microstructure and mechanical properties of composite laminates are discussed in detail. The results prove the effectiveness of the MACM method in improving the quality of wet lay-up vacuum bag laminates. This method does not require large capital investment for tooling or equipment and can also be used to consolidate geometrically complex composite parts by placing the magnets on a matching top mold positioned on the vacuum bag.

  15. Detection of IL-6 by magnetic nanoparticles grown with the assistance of mid-infrared lighting.

    PubMed

    Jiang, Xiufeng; Zhang, Ye; Miao, Xiaofei; Li, Zenghui; Bao, Zengtao; Wang, Tong

    2013-01-01

    Nanomedical systems have attracted considerable attention primarily due to suitability in applications for specific cell selection through biomolecular targeting and rare cell detection enhancement in a diverse, multicellular population. In the present study, magnetic nanoparticles were prepared for use in high accuracy cell sensing. Magnetic nanoparticle growth was assisted by mid-infrared lighting. By this mechanism, a narrow window, estimated to be 2%, was achieved for the dimension distribution of grown nanoparticles. Combined with silicon nanowire (SiNW) transistors, a sensor with ultra high sensitivity for the detection of specific potential low abundance biomarkers has been achieved, which has been specifically used to detect interleukin-6 (IL-6) at extremely low concentrations. A novel biosensor with high sensitivity has been fabricated and utilized in the detection of IL-6 at 75 fM to 50 pM. The system consists of an SiNW transistor and magnetic nanoparticles with even dimension distribution. The novel sensor system is suitable for quantifying IL-6 at low concentrations in protein samples.

  16. 14 CFR 1214.117 - Launch and orbit parameters for a standard launch.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ...) Launch at a time, selected by NASA, from a launch window of not less than 1 hour (a more restrictive launch window may be provided as an optional service). (b) For shared flights from KSC to the standard...

  17. Magnetic navigation system assisted percutaneous coronary intervention: a comparison to the conventional approach in daily practice.

    PubMed

    Li, Chun-Jian; Wang, Hui; Yang, Zhi-Jian; Cao, Ke-Jiang

    2011-01-01

    The benefits of the magnetic navigation system (MNS) for percutaneous coronary intervention (PCI) remain unclear, and a comparison of the MNS assisted approach to the conventional approach for PCI, when used in daily practice, is little studied. This study aimed to investigate the benefits of an MNS assisted technique as compared to the conventional technique for PCI. Forty-eight consecutive patients scheduled for PCI were recruited between December 2009 and April 2010. MNS assisted PCIs were performed on 54 target vessels. Another 45 patients with 54 target vessels undergoing conventional PCIs were selected from a historical population of patients to match the MNS group according to the coronary lesion type (ACC/AHA classification). Emergency PCIs and chronic total occlusions were excluded from both groups. Analyses were performed using Stata 9.2 statistical software. There were no significant differences between the baseline characteristics of the MNS group and the control group. The success rates were 100.0% for the MNS assisted PCI and 98.1% for the conventional PCI, which did not reach a significant difference (P = 1.000); there were also no significant differences in terms of guide wire crossing time ((51.7 ± 30.5) seconds vs. (57.5 ± 49.4) seconds, P = 0.448), operation time ((28.4 ± 15.9) minutes vs. (28.0 ± 24.7) minutes, P = 0.935), X-ray exposure ((458.1 ± 350.1) µGym(2) vs. (558.7 ± 451.7) µGym(2), P = 0.197; and (94.2 ± 80.9) mGy vs. (96.2 ± 77.3) mGy, P = 0.895) or contrast usage ((7.3 ± 4.0) ml vs. (6.1 ± 3.7) ml, P = 0.121) between the two groups. However, a trend toward shorter guide wire crossing time and less X-ray exposure were observed for the magnetic group. In daily practice, MNS assisted PCI resulted in a similar procedural success rate, operation time, and contrast usage, with a trend toward shorter guide wire crossing time and less X-ray exposure when compared to the conventional PCI.

  18. Fifth FLTSATCOM to be launched

    NASA Technical Reports Server (NTRS)

    1981-01-01

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

  19. Size dependence of magnetization switching and its dispersion of Co/Pt nanodots under the assistance of radio frequency fields

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

    Furuta, Masaki, E-mail: furutam@mail.tagen.tohoku.ac.jp; Okamoto, Satoshi; Kikuchi, Nobuaki

    2014-04-07

    We have studied the dot size dependence of microwave assisted magnetization switching (MAS) on perpendicular magnetic Co/Pt multilayer dot array. The significant microwave assistance effect has been observed over the entire dot size D ranging from 50 nm to 330 nm examined in the present study. The MAS behavior, however, critically depends on D. The excitation frequency dependence of the switching field is well consistent with the spin wave theory, indicating that the magnetization precession in MAS is in accordance with the well defined eigenmodes depending on the dot diameter. The lowest order spin wave is only excited for D ≤ 100 nm, and thenmore » the MAS effect is well consistent with that of the single macrospin prediction. On the other hand, higher order spin waves are excited for D > 100 nm, giving rise to the significant enhancement of the MAS effect. The dispersion of MAS effect also depends on D and is significantly reduced for the region of D > 100 nm. This significant reduction of the dispersion is attributed to the essential feature of the MAS effect which is insensitive to the local fluctuation of anisotropy field, such as defect, damaged layer, and so on.« less

  20. 12 CFR 1807.900 - Assistance agreement.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 12 Banks and Banking 9 2012-01-01 2012-01-01 false Assistance agreement. 1807.900 Section 1807.900... MAGNET FUND Terms and Conditions of Assistance § 1807.900 Assistance agreement. (a) Each Applicant that is selected to receive a CMF award must enter into an Assistance Agreement with the CDFI Fund. The...

  1. 12 CFR 1807.900 - Assistance agreement.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 12 Banks and Banking 7 2011-01-01 2011-01-01 false Assistance agreement. 1807.900 Section 1807.900... MAGNET FUND Terms and Conditions of Assistance § 1807.900 Assistance agreement. (a) Each Applicant that is selected to receive a CMF award must enter into an Assistance Agreement with the CDFI Fund. The...

  2. Launch summary for 1978

    NASA Technical Reports Server (NTRS)

    Vostreys, R. W.

    1978-01-01

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

  3. Noise reduction in heat-assisted magnetic recording of bit-patterned media by optimizing a high/low Tc bilayer structure

    NASA Astrophysics Data System (ADS)

    Muthsam, O.; Vogler, C.; Suess, D.

    2017-12-01

    It is assumed that heat-assisted magnetic recording is the recording technique of the future. For pure hard magnetic grains in high density media with an average diameter of 5 nm and a height of 10 nm, the switching probability is not sufficiently high for the use in bit-patterned media. Using a bilayer structure with 50% hard magnetic material with low Curie temperature and 50% soft magnetic material with high Curie temperature to obtain more than 99.2% switching probability leads to very large jitter. We propose an optimized material composition to reach a switching probability of Pswitch > 99.2% and simultaneously achieve the narrow transition jitter of pure hard magnetic material. Simulations with a continuous laser spot were performed with the atomistic simulation program VAMPIRE for a single cylindrical recording grain with a diameter of 5 nm and a height of 10 nm. Different configurations of soft magnetic material and different amounts of hard and soft magnetic material were tested and discussed. Within our analysis, a composition with 20% soft magnetic and 80% hard magnetic material reaches the best results with a switching probability Pswitch > 99.2%, an off-track jitter parameter σoff,80/20 = 0.46 nm and a down-track jitter parameter σdown,80/20 = 0.49 nm.

  4. Launch Vehicle Control Center Architectures

    NASA Technical Reports Server (NTRS)

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

    2014-01-01

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

  5. Impact of radius and skew angle on areal density in heat assisted magnetic recording hard disk drives

    NASA Astrophysics Data System (ADS)

    Cordle, Michael; Rea, Chris; Jury, Jason; Rausch, Tim; Hardie, Cal; Gage, Edward; Victora, R. H.

    2018-05-01

    This study aims to investigate the impact that factors such as skew, radius, and transition curvature have on areal density capability in heat-assisted magnetic recording hard disk drives. We explore a "ballistic seek" approach for capturing in-situ scan line images of the magnetization footprint on the recording media, and extract parametric results of recording characteristics such as transition curvature. We take full advantage of the significantly improved cycle time to apply a statistical treatment to relatively large samples of experimental curvature data to evaluate measurement capability. Quantitative analysis of factors that impact transition curvature reveals an asymmetry in the curvature profile that is strongly correlated to skew angle. Another less obvious skew-related effect is an overall decrease in curvature as skew angle increases. Using conventional perpendicular magnetic recording as the reference case, we characterize areal density capability as a function of recording position.

  6. Using Hybrid Magnetic Bearings to Completely Suspend the Impeller of a Ventricular Assist Device.

    PubMed

    Khanwilkar, Pratap; Olsen, Don; Bearnson, Gill; Allaire, Paul; Maslen, Eric; Flack, Ron; Long, James

    1996-05-01

    Clinically available blood pumps and those under development suffer from poor mechanical reliability and poor biocompatibility related to anatomic fit, hemolysis, and thrombosis. To alleviate these problems concurrently in a long-term device is a substantial challenge. Based on testing the performance of a prototype, and on our judgment of desired characteristics, we have configured an innovative ventricular assist device, the CF-VAD4, for long-term use. The design process and its outcome, the CFVAD4 system configuration, is described. To provide unprecedented reliability and biocompatibility, magnetic bearings completely suspend the rotating pump impeller. The CFVAD4 uses a combination of passive (permanent) and active (electric) magnetic bearings, a mixed flow impeller, and a slotless 3-phase brushless DC motor. These components are shaped, oriented, and integrated to provide a compact, implantable, pancake-shaped unit for placement in the left upper abdominal quadrant of adult humans. © 1996 International Society for Artificial Organs.

  7. Launch summary for 1980

    NASA Technical Reports Server (NTRS)

    Vostreys, R. W.

    1981-01-01

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

  8. STS-135 Atlantis Launch

    NASA Image and Video Library

    2011-07-07

    NASA Administrator Charles Bolden, right, participates in the post launch traditional beans and cornbread at the NASA Kennedy Space Center, Launch Control Center (LCC) shortly after the space shuttle Atlantis, STS-135, launched on Friday, July 8, 2011, in Cape Canaveral, Fla. The launch of Atlantis is the final flight of the shuttle program, a 12-day mission to the International Space Station. Photo Credit: (NASA/Bill Ingalls)

  9. Strain-assisted magnetization reversal in Co/Ni multilayers with perpendicular magnetic anisotropy

    PubMed Central

    Gopman, D. B.; Dennis, C. L.; Chen, P. J.; Iunin, Y. L.; Finkel, P.; Staruch, M.; Shull, R. D.

    2016-01-01

    Multifunctional materials composed of ultrathin magnetic films with perpendicular magnetic anisotropy combined with ferroelectric substrates represent a new approach toward low power, fast, high density spintronics. Here we demonstrate Co/Ni multilayered films with tunable saturation magnetization and perpendicular anisotropy grown directly on ferroelectric PZT [Pb(Zr0.52Ti0.48)O3] substrate plates. Electric fields up to ±2 MV/m expand the PZT by 0.1% and generate at least 0.02% in-plane compression in the Co/Ni multilayered film. Modifying the strain with a voltage can reduce the coercive field by over 30%. We also demonstrate that alternating in-plane tensile and compressive strains (less than 0.01%) can be used to propagate magnetic domain walls. This ability to manipulate high anisotropy magnetic thin films could prove useful for lowering the switching energy for magnetic elements in future voltage-controlled spintronic devices. PMID:27297638

  10. 14 CFR 1214.117 - Launch and orbit parameters for a standard launch.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ...) Launch from Kennedy Space Center (KSC) into the customer's choice of two standard mission orbits: 160 NM... 14 Aeronautics and Space 5 2013-01-01 2013-01-01 false Launch and orbit parameters for a standard launch. 1214.117 Section 1214.117 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION...

  11. 14 CFR 1214.117 - Launch and orbit parameters for a standard launch.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ...) Launch from Kennedy Space Center (KSC) into the customer's choice of two standard mission orbits: 160 NM... 14 Aeronautics and Space 5 2012-01-01 2012-01-01 false Launch and orbit parameters for a standard launch. 1214.117 Section 1214.117 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION...

  12. 14 CFR 1214.117 - Launch and orbit parameters for a standard launch.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ...) Launch from Kennedy Space Center (KSC) into the customer's choice of two standard mission orbits: 160 NM... 14 Aeronautics and Space 5 2011-01-01 2010-01-01 true Launch and orbit parameters for a standard launch. 1214.117 Section 1214.117 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION...

  13. Venture Class Launch Services

    NASA Technical Reports Server (NTRS)

    Wiese, Mark

    2016-01-01

    Provide an introduction to the Launch Services Program, and specifically the strategic initiative that drove the Venture Class Launch Services contracts. Provide information from the VCLS request for proposals, as well as the Agency's CubeSat Launch Initiative.

  14. Foreign launch competition growing

    NASA Astrophysics Data System (ADS)

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

    1986-07-01

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

  15. Magnetic space-based field measurements

    NASA Technical Reports Server (NTRS)

    Langel, R. A.

    1981-01-01

    Satellite measurements of the geomagnetic field began with the launch of Sputnik 3 in May 1958 and have continued sporadically in the intervening years. A list of spacecraft that have made significant contributions to an understanding of the near-earth geomagnetic field is presented. A new era in near-earth magnetic field measurements began with NASA's launch of Magsat in October 1979. Attention is given to geomagnetic field modeling, crustal magnetic anomaly studies, and investigations of the inner earth. It is concluded that satellite-based magnetic field measurements make global surveys practical for both field modeling and for the mapping of large-scale crustal anomalies. They are the only practical method of accurately modeling the global secular variation. Magsat is providing a significant contribution, both because of the timeliness of the survey and because its vector measurement capability represents an advance in the technology of such measurements.

  16. Launch Vehicle Operations Simulator

    NASA Technical Reports Server (NTRS)

    Blackledge, J. W.

    1974-01-01

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

  17. STS-135 Atlantis Launch

    NASA Image and Video Library

    2011-07-07

    NASA Photographer Kim Shiflett, left, and Videographer Glenn Benson capture a group photo of the launch team in Firing Room Four of the NASA Kennedy Space Center Launch Control Center (LCC) shortly after the space shuttle Atlantis, STS-135, launched on Friday, July 8, 2011, in Cape Canaveral, Fla. The launch of Atlantis is the final flight of the shuttle program, a 12-day mission to the International Space Station. Photo Credit: (NASA/Bill Ingalls)

  18. Pegasus air-launched space booster

    NASA Astrophysics Data System (ADS)

    Lindberg, Robert E.; Mosier, Marty R.

    The launching of small satellites with the mother- aircraft-launched Pegasus booster yields substantial cost improvements over ground launching and enhances operational flexibility, since it allows launches to be conducted into any orbital inclination. The Pegasus launch vehicle is a three-stage solid-rocket-propelled system with delta-winged first stage. The major components of airborne support equipment, located on the mother aircraft, encompass a launch panel operator console, an electronic pallet, and a pylon adapter. Alternatives to the currently employed B-52 launch platform aircraft have been identified for future use. Attention is given to the dynamic, thermal, and acoustic environments experienced by the payload.

  19. Launching a Weather Balloon to check conditions for the THEMIS L

    NASA Image and Video Library

    2002-01-01

    A worker releases a weather balloon at the Cape Canaveral Air Force Station weather station. The balloon is equipped with a radiosonde, an instrument that transmits measurements on atmospheric pressure, humidity, temperature and winds as it ascends. The data will be used to determine if conditions are acceptable for the launch of NASA's THEMIS mission. THEMIS, an acronym for Time History of Events and Macroscale Interactions during Substorms, consists of five identical probes that will track violent, colorful eruptions near the North Pole. This will be the largest number of scientific satellites NASA has ever launched into orbit aboard a single rocket. The THEMIS mission aims to unravel the mystery behind auroral substorms, an avalanche of magnetic energy powered by the solar wind that intensifies the northern and southern lights. The mission will investigate what causes auroras in the Earth’s atmosphere to dramatically change from slowly shimmering waves of light to wildly shifting streaks of bright color. Launch is planned from Pad 17-B in a window that extends from 6:01 to 6:19 p.m. EST.

  20. Launching a Weather Balloon to check conditions for the THEMIS L

    NASA Image and Video Library

    2002-01-01

    A radiosonde, an instrument that transmits measurements on atmospheric pressure, humidity, temperature and winds, is prepared for use on a weather balloon at the Cape Canaveral Air Force Station weather station. The data it returns will be used to determine if conditions are acceptable for the launch of NASA's THEMIS mission. THEMIS, an acronym for Time History of Events and Macroscale Interactions during Substorms, consists of five identical probes that will track violent, colorful eruptions near the North Pole. This will be the largest number of scientific satellites NASA has ever launched into orbit aboard a single rocket. The THEMIS mission aims to unravel the mystery behind auroral substorms, an avalanche of magnetic energy powered by the solar wind that intensifies the northern and southern lights. The mission will investigate what causes auroras in the Earth’s atmosphere to dramatically change from slowly shimmering waves of light to wildly shifting streaks of bright color. Launch is planned from Pad 17-B in a window that extends from 6:01 to 6:19 p.m. EST.

  1. Launching a Weather Balloon to check conditions for the THEMIS L

    NASA Image and Video Library

    2002-01-01

    A weather balloon takes flight from the Cape Canaveral Air Force Station weather station. The balloon is equipped with a radiosonde, an instrument that transmits measurements on atmospheric pressure, humidity, temperature and winds as it ascends. The data will be used to determine if conditions are acceptable for the launch of NASA's THEMIS mission. THEMIS, an acronym for Time History of Events and Macroscale Interactions during Substorms, consists of five identical probes that will track violent, colorful eruptions near the North Pole. This will be the largest number of scientific satellites NASA has ever launched into orbit aboard a single rocket. The THEMIS mission aims to unravel the mystery behind auroral substorms, an avalanche of magnetic energy powered by the solar wind that intensifies the northern and southern lights. The mission will investigate what causes auroras in the Earth’s atmosphere to dramatically change from slowly shimmering waves of light to wildly shifting streaks of bright color. Launch is planned from Pad 17-B in a window that extends from 6:01 to 6:19 p.m. EST.

  2. Launching a Weather Balloon to check conditions for the THEMIS L

    NASA Image and Video Library

    2002-01-01

    A weather balloon is prepared for release at the Cape Canaveral Air Force Station weather station. The balloon is equipped with a radiosonde, an instrument that transmits measurements on atmospheric pressure, humidity, temperature and winds as it ascends. The data will be used to determine if conditions are acceptable for the launch of NASA's THEMIS mission. THEMIS, an acronym for Time History of Events and Macroscale Interactions during Substorms, consists of five identical probes that will track violent, colorful eruptions near the North Pole. This will be the largest number of scientific satellites NASA has ever launched into orbit aboard a single rocket. The THEMIS mission aims to unravel the mystery behind auroral substorms, an avalanche of magnetic energy powered by the solar wind that intensifies the northern and southern lights. The mission will investigate what causes auroras in the Earth’s atmosphere to dramatically change from slowly shimmering waves of light to wildly shifting streaks of bright color. Launch is planned from Pad 17-B in a window that extends from 6:01 to 6:19 p.m. EST.

  3. Proposal of New Triggered Lightning Launch Commit Criteria for Japan's Safety Rocket Launch

    NASA Astrophysics Data System (ADS)

    Saito, Yasuhiro; Saito, Toshiya; Okita, Koichi

    2013-09-01

    Triggered lightning for rocket launch can cause the failure.The current Japanese criteria to postpone the launch opportunity is the thickness of cloud 1.8km with 0 -20 degrees Celsius. Of all H2A launches during these ten years, slipping launches have occurred over half of its flights. So, we have initiated a research on Triggered Lightning Launch Commit Criteria, two years ago.We present the overall activities with the observation campaign (RAIJIN*) in Feb/2012 and Jan-Feb/2013, by means of air-born field mill with airplane, X-band dual polarization radar, ground based field mill and Videosonde. Also, the analytical results and proposal of the new criteria will be shown.*) Raijin is originally a name for Thunder god in Japanese and here it stands for Rocket launch Atmospheric electricity Investigation by Jaxa IN cooperation with academia.

  4. Advanced transportation system studies technical area 2(TA-2): Heavy lift launch vehicle development. volume 1; Executive summary

    NASA Technical Reports Server (NTRS)

    McCurry, J.

    1995-01-01

    The purpose of the TA-2 contract was to provide advanced launch vehicle concept definition and analysis to assist NASA in the identification of future launch vehicle requirements. Contracted analysis activities included vehicle sizing and performance analysis, subsystem concept definition, propulsion subsystem definition (foreign and domestic), ground operations and facilities analysis, and life cycle cost estimation. This document is part of the final report for the TA-2 contract. The final report consists of three volumes: Volume 1 is the Executive Summary, Volume 2 is Technical Results, and Volume 3 is Program Cost Estimates. The document-at-hand, Volume 1, provides a summary description of the technical activities that were performed over the entire contract duration, covering three distinct launch vehicle definition activities: heavy-lift (300,000 pounds injected mass to low Earth orbit) launch vehicles for the First Lunar Outpost (FLO), medium-lift (50,000-80,000 pounds injected mass to low Earth orbit) launch vehicles, and single-stage-to-orbit (SSTO) launch vehicles (25,000 pounds injected mass to a Space Station orbit).

  5. Overview of C/C-SiC Composite Development for the Orion Launch Abort System

    NASA Technical Reports Server (NTRS)

    Allen, Lee R.; Valentine, Peter G.; Schofield, Elizabeth S.; Beshears, Ronald D.; Coston, James E.

    2012-01-01

    Past and present efforts by the authors to further understanding of the ceramic matrix composite (CMC) material used in the valve components of the Orion Launch Abort System (LAS) Attitude Control Motor (ACM) will be presented. The LAS is designed to quickly lift the Orion Crew Exploration Vehicle (CEV) away from its launch vehicle in emergency abort scenarios. The ACM is a solid rocket motor which utilizes eight throttleable nozzles to maintain proper orientation of the CEV during abort operations. Launch abort systems have not been available for use by NASA on manned launches since the last Apollo ]Saturn launch in 1975. The CMC material, carbon-carbon/silicon-carbide (C/C-SiC), is manufactured by Fiber Materials, Inc. and consists of a rigid 4-directional carbon-fiber tow weave reinforced with a mixed carbon plus SiC matrix. Several valve and full system (8-valve) static motor tests have been conducted by the motor vendor. The culmination of these tests was the successful flight test of the Orion LAS Pad Abort One (PA ]1) vehicle on May 6, 2010. Due to the fast pace of the LAS development program, NASA Marshall Space Flight Center assisted the LAS community by performing a series of material and component evaluations using fired hardware from valve and full ]system development motor tests, and from the PA-1 flight ACM motor. Information will be presented on the structure of the C/C-SiC material, as well as the efficacy of various non ]destructive evaluation (NDE) techniques, including but not limited to: radiography, computed tomography, nanofocus computed tomography, and X-ray transmission microscopy. Examinations of the microstructure of the material via scanning electron microscopy and energy dispersive spectroscopy will also be discussed. The findings resulting from the subject effort are assisting the LAS Project in risk assessments and in possible modifications to the final ACM operational design.

  6. Project Centaur. [for earth dayside magnetic cleft investigation

    NASA Technical Reports Server (NTRS)

    Brence, W. A.; Hardin, J. W.; Crook, E. D.; Roberts, H.

    1982-01-01

    The National Aeronautics and Space Administration (NASA) and the Canada Centre for Space Science, National Research Council of Canada (NRCC), conducted a cooperative sounding rocket campaign in the Canadian Arctic during November/December 1981. The objective of the campaign was to investigate the earth's dayside magnetic cleft region. The project was named CENTAUR for Cleft Energetics Transport and Ultraviolet Radiation. Remote launch support facilities were established at Cape Parry, NWT, Canada (70 deg 10 min N latitude, 124 deg 40 min W longitude). The cleft region is accessible from this location when launched poleward during reasonably quiet magnetic activity. Five large sounding rockets were launched (3 NASA, 2 NRCC). About 30 scientific experiments were launched, and an extensive array of ground based experiments was established at Cape Parry and at Sachs Harbour, Banks Island, 130 miles poleward. This paper discusses the unique organization, planning, facilities, instrumentation, and operation required to support the campaign, and looks briefly at the results.

  7. Gravity-Assist Mechanical Simulator for Outreach

    NASA Technical Reports Server (NTRS)

    Doody, David F.; White, Victor E.; Schaff, Mitch D.

    2012-01-01

    There is no convenient way to demonstrate mechanically, as an outreach (or inreach) topic, the angular momentum trade-offs and the conservation of angular momentum associated with gravityassist interplanetary trajectories. The mechanical concepts that underlie gravity assist are often misunderstood or confused, possibly because there is no mechanical analog to it in everyday experience. The Gravity Assist Mech - anical Simulator is a hands-on solution to this longstanding technical communications challenge. Users intuitively grasp the concepts, meeting specific educational objectives. A manually spun wheel with high angular mass and low-friction bearings supplies momentum to an attached spherical neodymium magnet that represents a planet orbiting the Sun. A steel bearing ball following a trajectory across a glass plate above the wheel and magnet undergoes an elastic collision with the revolving magnet, illustrating the gravitational elastic collision between spacecraft and planet on a gravity-assist interplanetary trajectory. Manually supplying the angular momentum for the elastic collision, rather than observing an animation, intuitively conveys the concepts, meeting nine specific educational objectives. Many NASA and JPL interplanetary missions are enabled by the gravity-assist technique.

  8. Launch Vehicle Control Center Architectures

    NASA Technical Reports Server (NTRS)

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

    2014-01-01

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

  9. Transcranial magnetic stimulation assisted by neuronavigation of magnetic resonance images

    NASA Astrophysics Data System (ADS)

    Viesca, N. Angeline; Alcauter, S. Sarael; Barrios, A. Fernando; González, O. Jorge J.; Márquez, F. Jorge A.

    2012-10-01

    Technological advance has improved the way scientists and doctors can learn about the brain and treat different disorders. A non-invasive method used for this is Transcranial Magnetic Stimulation (TMS) based on neuron excitation by electromagnetic induction. Combining this method with functional Magnetic Resonance Images (fMRI), it is intended to improve the localization technique of cortical brain structures by designing an extracranial localization system, based on Alcauter et al. work.

  10. NASA’s BARREL Mission Launches 20 Balloons

    NASA Image and Video Library

    2017-12-08

    Pumping helium into the first BARREL balloon to launch from Halley Research Satation. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science

  11. NASA’s BARREL Mission Launches 20 Balloons

    NASA Image and Video Library

    2017-12-08

    The BARREL team at the SANAE IV research station celebrates their final launch in the Antarctica sun. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors

  12. SKYLAB IV - LAUNCH

    NASA Image and Video Library

    1973-11-27

    S73-37285 (16 Nov. 1973) --- The Skylab 4/Saturn 1B space vehicle is launched from Pad B, Launch Complex 39, Kennedy Space Center, Florida, at 9:01:23 a.m. (EST), Friday, Nov. 16, 1973. Skylab 4 is the third and last of three scheduled manned Skylab missions. Aboard the Skylab 4 Command/Service Module were astronauts Gerald P. Carr, Edward G. Gibson and William R. Pogue. In addition to the CSM and its launch escape system, the Skylab 4 space vehicle consisted of the Saturn 1B first (S-1B) stage and the Saturn 1B second (S-IVB) stage. (The Skylab 1/Saturn V unmanned space vehicle with the space station payload was launched from Pad A on May 14, 1973). Photo credit: NASA

  13. SKYLAB IV - LAUNCH

    NASA Image and Video Library

    1973-11-27

    S73-37286 (16 Nov. 1973) --- The Skylab 4/Saturn 1B space vehicle is launched from Pad B, Launch Complex 39, Kennedy Space Center, Florida, at 9:01:23 a.m. (EST), Friday, Nov. 16, 1973. Skylab 4 is the third and last of three scheduled manned Skylab missions. Aboard the Skylab 4 Command/Service Module were astronauts Gerald P. Carr, Edward G. Gibson and William R. Pogue. In addition to the CSM and its launch escape system, the Skylab 4 space vehicle consisted of the Saturn 1B first (S-1B) stage and the Saturn 1B second (S-IVB) stage. (The Skylab 1/Saturn V unmanned space vehicle with the space station payload was launched from Pad A on May 14, 1973). Photo credit: NASA

  14. Robot-assisted real-time magnetic resonance image-guided transcatheter aortic valve replacement.

    PubMed

    Miller, Justin G; Li, Ming; Mazilu, Dumitru; Hunt, Tim; Horvath, Keith A

    2016-05-01

    Real-time magnetic resonance imaging (rtMRI)-guided transcatheter aortic valve replacement (TAVR) offers improved visualization, real-time imaging, and pinpoint accuracy with device delivery. Unfortunately, performing a TAVR in a MRI scanner can be a difficult task owing to limited space and an awkward working environment. Our solution was to design a MRI-compatible robot-assisted device to insert and deploy a self-expanding valve from a remote computer console. We present our preliminary results in a swine model. We used an MRI-compatible robotic arm and developed a valve delivery module. A 12-mm trocar was inserted in the apex of the heart via a subxiphoid incision. The delivery device and nitinol stented prosthesis were mounted on the robot. Two continuous real-time imaging planes provided a virtual real-time 3-dimensional reconstruction. The valve was deployed remotely by the surgeon via a graphic user interface. In this acute nonsurvival study, 8 swine underwent robot-assisted rtMRI TAVR for evaluation of feasibility. Device deployment took a mean of 61 ± 5 seconds. Postdeployment necropsy was performed to confirm correlations between imaging and actual valve positions. These results demonstrate the feasibility of robotic-assisted TAVR using rtMRI guidance. This approach may eliminate some of the challenges of performing a procedure while working inside of an MRI scanner, and may improve the success of TAVR. It provides superior visualization during the insertion process, pinpoint accuracy of deployment, and, potentially, communication between the imaging device and the robotic module to prevent incorrect or misaligned deployment. Copyright © 2016 The American Association for Thoracic Surgery. Published by Elsevier Inc. All rights reserved.

  15. Magnetic field amplification via protostellar disc dynamos

    NASA Astrophysics Data System (ADS)

    Dyda, S.; Lovelace, R. V. E.; Ustyugova, G. V.; Koldoba, A. V.; Wasserman, I.

    2018-06-01

    We numerically investigate the generation of a magnetic field in a protostellar disc via an αΩ-dynamo and the resulting magnetohydrodynamic (MHD) driven outflows. We find that for small values of the dimensionless dynamo parameter αd, the poloidal field grows exponentially at a rate σ ∝ Ω _K √{α _d}, before saturating to a value ∝ √{α _d}. The dynamo excites dipole and octupole modes, but quadrupole modes are suppressed, because of the symmetries of the seed field. Initial seed fields too weak to launch MHD outflows are found to grow sufficiently to launch winds with observationally relevant mass fluxes of the order of 10^{-9} M_{⊙} yr^{-1} for T Tauri stars. This suggests that αΩ-dynamos may be responsible for generating magnetic fields strong enough to launch observed outflows.

  16. Launch Summary for 1979

    NASA Technical Reports Server (NTRS)

    Vostreys, R. W.

    1980-01-01

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

  17. APOLLO VIII - LAUNCH - KSC

    NASA Image and Video Library

    1968-12-21

    S68-56002 (21 Dec. 1968) --- The Apollo 8 (Spacecraft 103/Saturn 503) space vehicle is launched from Pad A, Launch Complex 39, Kennedy Space Center (KSC), at 7:51 a.m. (EST), Dec. 21, 1968. The crew of the Apollo 8 lunar orbit mission is astronauts Frank Borman, commander; James A. Lovell Jr., command module pilot; and William A. Anders, lunar module pilot. Apollo 8 was the first manned Saturn V launch. (F-ls 1/3 way from top of mobile launch tower.)

  18. Russian Soyuz in Launch Position

    NASA Technical Reports Server (NTRS)

    2000-01-01

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

  19. STS-111/Endeavour/ISS UF2 Pre-Launch Activities: Launch with Playbacks

    NASA Technical Reports Server (NTRS)

    2002-01-01

    This video of the preflight preparations for and launch of Space Shuttle Endeavour on STS-111 begins with a view of Endeavour on the launch pad. Additional launch pad views leading up to liftoff are interspersed with footage from the Firing Room at Kennedy Space Center, the crew's prelaunch activities, and inspection of the crew members in the White Room before boarding Endeavour. The crew is introduced by a narrator during the preflight banquet and suiting up, and a later clip shows them departing to the launch site. The crew consists of Commander Kenneth Cockrell, Pilot Paul Lockhart, Mission Specialists Philippe Perrin and Franklin Chang-Diaz, and the Expedition 5 crew of the International Space Station (ISS) (Commander Valery Korzun and Flight Engineers Peggy Whitsun and Sergei Treschev). The nozzles on Endeavour's Space Shuttle Main Engine (SSME) are swiveled before liftoff, and the launch is shown past the separation of the solid rocket boosters. After a brief clip from the Mission Control Center at Johnson Space Center, the following launch replays are shown: Beach Tracker, VAB, Pad A, Tower 1, UCS-15, Grandstand, Cocoa Beach DOAMS, Playalinda DOAMS, UCS-23, and OTV-070.

  20. The use of magnetite nanoparticles for implant-assisted magnetic drug targeting in thrombolytic therapy.

    PubMed

    Kempe, Maria; Kempe, Henrik; Snowball, Ian; Wallén, Rita; Arza, Carlos Rodriguez; Götberg, Matthias; Olsson, Tommy

    2010-12-01

    Implant-assisted targeting of magnetic particles under the influence of an external magnetic field has previously been verified through mathematical modeling, in vitro studies, and in vivo studies on rat carotid arteries as a feasible method for localized drug delivery. The present study focuses on the development of nanoparticles for the treatment of in-stent thrombosis. Magnetic nanoparticles in the size-range 10-30 nm were synthesized in a one-pot procedure by precipitation of ferrous hydroxide followed by oxidation to magnetite. The nanoparticles were silanized with tetraethyl orthosilicate in the presence of triethylene glycol and/or polyethylene glycol. The surface coated magnetite nanoparticles were activated with either N-hydroxysulfosuccinimide or tresyl chloride for covalent immobilization of tissue plasminogen activator (tPA). Hysteresis loops showed saturation magnetizations of 55.8, 44.1, and 43.0 emu/g for the naked nanoparticles, the surface coated nanoparticles, and the tPA-nanoparticle conjugates, respectively. The hemolytic activity of the nanoparticles in blood was negligible. An initial in vivo biocompatibility test in pig, carried out by intravascular injection of the nanoparticles in a stented brachial artery, showed no short-term adverse effects. In vitro evaluation in a flow-through model proved that the nanoparticles were captured efficiently to the surface of a ferromagnetic coiled wire at the fluid velocities typical for human arteries. A preliminary test of the tPA-nanoparticle conjugates in a pig model suggested that the conjugates may be used for treatment of in-stent thrombosis in coronary arteries. Copyright © 2010 Elsevier Ltd. All rights reserved.

  1. Evolution of the Florida Launch Site Architecture: Embracing Multiple Customers, Enhancing Launch Opportunities

    NASA Technical Reports Server (NTRS)

    Colloredo, Scott; Gray, James A.

    2011-01-01

    The impending conclusion of the Space Shuttle Program and the Constellation Program cancellation unveiled in the FY2011 President's budget created a large void for human spaceflight capability and specifically launch activity from the Florida launch Site (FlS). This void created an opportunity to re-architect the launch site to be more accommodating to the future NASA heavy lift and commercial space industry. The goal is to evolve the heritage capabilities into a more affordable and flexible launch complex. This case study will discuss the FlS architecture evolution from the trade studies to select primary launch site locations for future customers, to improving infrastructure; promoting environmental remediation/compliance; improving offline processing, manufacturing, & recovery; developing range interface and control services with the US Air Force, and developing modernization efforts for the launch Pad, Vehicle Assembly Building, Mobile launcher, and supporting infrastructure. The architecture studies will steer how to best invest limited modernization funding from initiatives like the 21 st elSe and other potential funding.

  2. Vandenberg Air Force Base Upper Level Wind Launch Weather Constraints

    NASA Technical Reports Server (NTRS)

    Shafer, Jaclyn A.; Wheeler, Mark M.

    2012-01-01

    Microsoft Excel using Visual Basic for Applications. The GUI displays the critical sounding data easily and quickly for the LWOs on day of launch. This tool will replace the existing one used by the 30 OSSWF, assist the LWOs in determining the probability of exceeding specific wind threshold values, and help to improve the overall upper winds forecast for the launch customer.

  3. Orion Launch

    NASA Image and Video Library

    2014-12-05

    A Delta IV Heavy rocket lifts off from Space Launch Complex 37 at Cape Canaveral Air Force Station in Florida carrying NASA's Orion spacecraft on an unpiloted flight test to Earth orbit. Liftoff was at 7:05 a.m. EST. During the two-orbit, four-and-a-half hour mission, engineers will evaluate the systems critical to crew safety, the launch abort system, the heat shield and the parachute system.

  4. Space Shuttle Discovery Launch

    NASA Image and Video Library

    2008-05-31

    NASA Administrator, Michael Griffin watches the launch of the Space Shuttle Discovery (STS-124) from the Launch Control Center Saturday, May 31, 2008, at the Kennedy Space Center in Cape Canaveral, Fla. The Shuttle lifted off from launch pad 39A at 5:02 p.m. EDT. Photo Credit: (NASA/Bill Ingalls)

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

    NASA Technical Reports Server (NTRS)

    May, Todd A.; Lyles, Garry M.

    2014-01-01

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

  6. Peak Wind Forecasts for the Launch-Critical Wind Towers on Kennedy Space Center/Cape Canaveral Air Force Station, Phase IV

    NASA Technical Reports Server (NTRS)

    Crawford, Winifred

    2011-01-01

    This final report describes the development of a peak wind forecast tool to assist forecasters in determining the probability of violating launch commit criteria (LCC) at Kennedy Space Center (KSC) and Cape Canaveral Air Force Station (CCAFS). The peak winds arc an important forecast clement for both the Space Shuttle and Expendable Launch Vehicle (ELV) programs. The LCC define specific peak wind thresholds for each launch operation that cannot be exceeded in order to ensure the safety of the vehicle. The 45th Weather Squadron (45 WS) has found that peak winds are a challenging parameter to forecast, particularly in the cool season months of October through April. Based on the importance of forecasting peak winds, the 45 WS tasked the Applied Meteorology Unit (AMU) to update the statistics in the current peak-wind forecast tool to assist in forecasting LCC violations. The tool includes onshore and offshore flow climatologies of the 5-minute mean and peak winds and probability distributions of the peak winds as a function of the 5-minute mean wind speeds.

  7. KSC Vertical Launch Site Evaluation

    NASA Technical Reports Server (NTRS)

    Phillips, Lynne V.

    2007-01-01

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

  8. Voyager 1's Launch Vehicle

    NASA Image and Video Library

    1977-09-05

    The Titan/Centaur-6 launch vehicle was moved to Launch Complex 41 at Kennedy Space Center in Florida to complete checkout procedures in preparation for launch. The photo is dated January 1977. This launch vehicle carried Voyager 1 into space on September 5, 1977. https://photojournal.jpl.nasa.gov/catalog/PIA21739

  9. Game Changing: NASA's Space Launch System and Science Mission Design

    NASA Technical Reports Server (NTRS)

    Creech, Stephen D.

    2013-01-01

    NASA s Marshall Space Flight Center (MSFC) is directing efforts to build the Space Launch System (SLS), a heavy-lift rocket that will carry the Orion Multi-Purpose Crew Vehicle (MPCV) and other important payloads far beyond Earth orbit (BEO). Its evolvable architecture will allow NASA to begin with Moon fly-bys and then go on to transport humans or robots to distant places such as asteroids and Mars. Designed to simplify spacecraft complexity, the SLS rocket will provide improved mass margins and radiation mitigation, and reduced mission durations. These capabilities offer attractive advantages for ambitious missions such as a Mars sample return, by reducing infrastructure requirements, cost, and schedule. For example, if an evolved expendable launch vehicle (EELV) were used for a proposed mission to investigate the Saturn system, a complicated trajectory would be required - with several gravity-assist planetary fly-bys - to achieve the necessary outbound velocity. The SLS rocket, using significantly higher C3 energies, can more quickly and effectively take the mission directly to its destination, reducing trip time and cost. As this paper will report, the SLS rocket will launch payloads of unprecedented mass and volume, such as "monolithic" telescopes and in-space infrastructure. Thanks to its ability to co-manifest large payloads, it also can accomplish complex missions in fewer launches. Future analyses will include reviews of alternate mission concepts and detailed evaluations of SLS figures of merit, helping the new rocket revolutionize science mission planning and design for years to come.

  10. Game changing: NASA's space launch system and science mission design

    NASA Astrophysics Data System (ADS)

    Creech, S. D.

    NASA's Marshall Space Flight Center (MSFC) is directing efforts to build the Space Launch System (SLS), a heavy-lift rocket that will carry the Orion Multi-Purpose Crew Vehicle (MPCV) and other important payloads far beyond Earth orbit (BEO). Its evolvable architecture will allow NASA to begin with Moon fly-bys and then go on to transport humans or robots to distant places such as asteroids and Mars. Designed to simplify spacecraft complexity, the SLS rocket will provide improved mass margins and radiation mitigation, and reduced mission durations. These capabilities offer attractive advantages for ambitious missions such as a Mars sample return, by reducing infrastructure requirements, cost, and schedule. For example, if an evolved expendable launch vehicle (EELV) were used for a proposed mission to investigate the Saturn system, a complicated trajectory would be required - with several gravity-assist planetary fly-bys - to achieve the necessary outbound velocity. The SLS rocket, using significantly higher characteristic energy (C3) energies, can more quickly and effectively take the mission directly to its destination, reducing trip time and cost. As this paper will report, the SLS rocket will launch payloads of unprecedented mass and volume, such as “ monolithic” telescopes and in-space infrastructure. Thanks to its ability to co-manifest large payloads, it also can accomplish complex missions in fewer launches. Future analyses will include reviews of alternate mission concepts and detailed evaluations of SLS figures of merit, helping the new rocket revolutionize science mission planning and design for years to come.

  11. 14 CFR § 1214.117 - Launch and orbit parameters for a standard launch.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... flights: (1) Launch from Kennedy Space Center (KSC) into the customer's choice of two standard mission... 14 Aeronautics and Space 5 2014-01-01 2014-01-01 false Launch and orbit parameters for a standard launch. § 1214.117 Section § 1214.117 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE...

  12. Small Space Launch: Origins & Challenges

    NASA Astrophysics Data System (ADS)

    Freeman, T.; Delarosa, J.

    2010-09-01

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

  13. 14 CFR 420.30 - Launch site location review for permitted launch vehicles.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LICENSE TO OPERATE A LAUNCH SITE Criteria and Information Requirements for Obtaining a License § 420.30 Launch site location review for...

  14. 14 CFR 420.30 - Launch site location review for permitted launch vehicles.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LICENSE TO OPERATE A LAUNCH SITE Criteria and Information Requirements for Obtaining a License § 420.30 Launch site location review for...

  15. Magnetic levitation systems for future aeronautics and space research and missions

    NASA Technical Reports Server (NTRS)

    Blankson, Isaiah M.; Mankins, John C.

    1996-01-01

    The objectives, advantages, and research needs for several applications of superconducting magnetic levitation to aerodynamics research, testing, and space-launch are discussed. Applications include very large-scale magnetic balance and suspension systems for high alpha testing, support interference-free testing of slender hypersonic propulsion/airframe integrated vehicles, and hypersonic maglev. Current practice and concepts are outlined as part of a unified effort in high magnetic fields R&D within NASA. Recent advances in the design and construction of the proposed ground-based Holloman test track (rocket sled) that uses magnetic levitation are presented. It is protected that ground speeds of up to Mach 8 to 11 at sea-level are possible with such a system. This capability may enable supersonic combustor tests as well as ramjet-to-scramjet transition simulation to be performed in clean air. Finally a novel space launch concept (Maglifter) which uses magnetic levitation and propulsion for a re-usable 'first stage' and rocket or air-breathing combined-cycle propulsion for its second stage is discussed in detail. Performance of this concept is compared with conventional advanced launch systems and a preliminary concept for a subscale system demonstration is presented.

  16. Launch Pad Activities

    NASA Image and Video Library

    1959-09-08

    Big Joe Capsule Launch Pad Activities: This film covers both the Big Joe and a Little Joe Project Mercury flight test with a research and development version of the Mercury capsule. Big Joe was an Atlas missile that successfully launched a boilerplate model of the Mercury capsule on September 9, 1959. The lower half of the capsule was created at NASA Lewis. The scenes include coverage of the assembly and erection of the boosters, delivery of the capsules, mating of the capsules to the boosters, prelaunch views of the capsule and boosters on launchers, mission control, the launches, and recovery.

  17. Powering Exploration: The Ares I Crew Launch Vehicle and Ares V Cargo Launch Vehicle

    NASA Technical Reports Server (NTRS)

    Cook, Stephen A.

    2008-01-01

    The National Aeronautics and Space Administration (NASA)'s Constellation Program is depending on the Ares Projects to deliver the crew and cargo launch capabilities needed to send human explorers to the Moon and beyond. The Ares Projects continue to make progress toward design, component testing, and early flight testing of the Ares I crew launch vehicle, as well as early design work for Ares V cargo launch vehicle. Ares I and Ares V will form the core space launch capabilities the United States needs to continue its pioneering tradition as a spacefaring nation. This paper will discuss programmatic, design, fabrication, and testing progress toward building these new launch vehicles.

  18. STS-41 MS Akers assisted by technician on SMS middeck at JSC

    NASA Technical Reports Server (NTRS)

    1990-01-01

    STS-41 Mission Specialist (MS) Thomas D. Akers, wearing launch and entry suit (LES) and launch and entry helmet (LEH), is assisted by a technician on the middeck of JSC's Shuttle Mission Simulator (SMS). Akers seated in the mission specialists chairis participating in a simulation of mission events. The SMS is located in JSC's Mission Simulation and Training Facility Bldg 5.

  19. Local Magnetoelectric Effect in La-Doped BiFeO3 Multiferroic Thin Films Revealed by Magnetic-Field-Assisted Scanning Probe Microscopy

    NASA Astrophysics Data System (ADS)

    Pan, Dan-Feng; Zhou, Ming-Xiu; Lu, Zeng-Xing; Zhang, Hao; Liu, Jun-Ming; Wang, Guang-Hou; Wan, Jian-Guo

    2016-06-01

    Multiferroic La-doped BiFeO3 thin films have been prepared by a sol-gel plus spin-coating process, and the local magnetoelectric coupling effect has been investigated by the magnetic-field-assisted scanning probe microscopy connected with a ferroelectric analyzer. The local ferroelectric polarization response to external magnetic fields is observed and a so-called optimized magnetic field of ~40 Oe is obtained, at which the ferroelectric polarization reaches the maximum. Moreover, we carry out the magnetic-field-dependent surface conductivity measurements and illustrate the origin of local magnetoresistance in the La-doped BiFeO3 thin films, which is closely related to the local ferroelectric polarization response to external magnetic fields. This work not only provides a useful technique to characterize the local magnetoelectric coupling for a wide range of multiferroic materials but also is significant for deeply understanding the local multiferroic behaviors in the BiFeO3-based systems.

  20. NASA Launch Services Program Overview

    NASA Technical Reports Server (NTRS)

    Higginbotham, Scott

    2016-01-01

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

  1. 34 CFR 280.10 - What types of projects does the Secretary assist?

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... ELEMENTARY AND SECONDARY EDUCATION, DEPARTMENT OF EDUCATION MAGNET SCHOOLS ASSISTANCE PROGRAM What Types of... assist? (a) The Secretary funds applications proposing projects in magnet schools that are part of an...

  2. Launch of the space experiment PAMELA

    NASA Astrophysics Data System (ADS)

    Casolino, M.; Picozza, P.; Altamura, F.; Basili, A.; De Simone, N.; Di Felice, V.; De Pascale, M. P.; Marcelli, L.; Minori, M.; Nagni, M.; Sparvoli, R.; Galper, A. M.; Mikhailov, V. V.; Runtso, M. F.; Voronov, S. A.; Yurkin, Y. T.; Zverev, V. G.; Castellini, G.; Adriani, O.; Bonechi, L.; Bongi, M.; Taddei, E.; Vannuccini, E.; Fedele, D.; Papini, P.; Ricciarini, S. B.; Spillantini, P.; Ambriola, M.; Cafagna, F.; De Marzo, C.; Barbarino, G. C.; Campana, D.; De Rosa, G.; Osteria, G.; Russo, S.; Bazilevskaja, G. A.; Kvashnin, A. N.; Maksumov, O.; Misin, S.; Stozhkov, Yu. I.; Bogomolov, E. A.; Krutkov, S. Yu.; Nikonov, N. N.; Bonvicini, V.; Boezio, M.; Lundquist, J.; Mocchiutti, E.; Vacchi, A.; Zampa, G.; Zampa, N.; Bongiorno, L.; Ricci, M.; Carlson, P.; Hofverberg, P.; Lund, J.; Orsi, S.; Pearce, M.; Menn, W.; Simon, M.

    2008-08-01

    PAMELA is a satellite borne experiment designed to study with great accuracy cosmic rays of galactic, solar, and trapped nature in a wide energy range (protons 80 MeV-700 GeV, electrons 50 MeV-400 GeV). Main objective is the study of the antimatter component: antiprotons (80 MeV-190 GeV), positrons (50 MeV-270 GeV) and search for antimatter with a precision of the order of 10 -8. The experiment, housed on board the Russian Resurs-DK1 satellite, was launched on June 15th, 2006 in a 350 × 600 km orbit with an inclination of 70°. The detector is composed of a series of scintillator counters arranged at the extremities of a permanent magnet spectrometer to provide charge, time-of-flight, and rigidity information. Lepton/hadron identification is performed by a silicon-tungsten calorimeter and a neutron detector placed at the bottom of the device. An anticounter system is used offline to reject false triggers coming from the satellite. In self-trigger mode the calorimeter, the neutron detector, and a shower tail catcher are capable of an independent measure of the lepton component up to 2 TeV. In this work we describe the experiment, its scientific objectives, and the performance in the first months after launch.

  3. Synthesis and application of magnetic deep eutectic solvents: Novel solvents for ultrasound assisted liquid-liquid microextraction of thiophene.

    PubMed

    Khezeli, Tahere; Daneshfar, Ali

    2017-09-01

    Two novel magnetic deep eutectic solvents (MDESs), comprised of cheap and simple components named [choline chloride/phenol] [FeCl 4 ] and [choline chloride/ethylene glycol] [FeCl 4 ] were prepared and characterized by CHN elemental analysis, proton nuclear magnetic resonance ( 1 H NMR), vibrating sample magnetometery (VSM), Raman, Fourier transform-infrared (FT-IR) and UV-Vis spectrometery. The extraction efficiency of the prepared MDESs has been investigated in ultrasound assisted liquid-liquid microextraction based MDES (UALLME-MDES). Briefly, MDESs were added to n-heptan containing thiophene. Then, MDESs were dispersed in n-heptane by sonication. After that, microdroplets of MDESs were collected by a magnet and the remained concentration of thiophene in n-heptane phase was analyzed by GC-FID. The results indicated that [choline chloride/phenol] [FeCl 4 ] has higher extraction efficiency than [choline chloride/ethylene glycol] [FeCl 4 ]. This work opens a new way to the application of MDESs. Copyright © 2016 Elsevier B.V. All rights reserved.

  4. Launch Condition Deviations of Reusable Launch Vehicle Simulations in Exo-Atmospheric Zoom Climbs

    NASA Technical Reports Server (NTRS)

    Urschel, Peter H.; Cox, Timothy H.

    2003-01-01

    The Defense Advanced Research Projects Agency has proposed a two-stage system to deliver a small payload to orbit. The proposal calls for an airplane to perform an exo-atmospheric zoom climb maneuver, from which a second-stage rocket is launched carrying the payload into orbit. The NASA Dryden Flight Research Center has conducted an in-house generic simulation study to determine how accurately a human-piloted airplane can deliver a second-stage rocket to a desired exo-atmospheric launch condition. A high-performance, fighter-type, fixed-base, real-time, pilot-in-the-loop airplane simulation has been modified to perform exo-atmospheric zoom climb maneuvers. Four research pilots tracked a reference trajectory in the presence of winds, initial offsets, and degraded engine thrust to a second-stage launch condition. These launch conditions have been compared to the reference launch condition to characterize the expected deviation. At each launch condition, a speed change was applied to the second-stage rocket to insert the payload onto a transfer orbit to the desired operational orbit. The most sensitive of the test cases was the degraded thrust case, yielding second-stage launch energies that were too low to achieve the radius of the desired operational orbit. The handling qualities of the airplane, as a first-stage vehicle, have also been investigated.

  5. Launch - STS-6 - KSC

    NASA Image and Video Library

    1983-04-12

    S83-30222 (4 April 1983) --- The second reusable spacecraft in history successfully launches from Launch Pad 39A at 1:30:00:88 p.m. (EST) on April 4, 1983, and heads for its history making five-day mission in Earth orbit. The space shuttle Challenger, its two solid rocket boosters (SRB), and a new lightweight?external fuel tank were captured on film by an automatically-tripped camera in a protected station nearer to the launch pad than human beings are able to be at launch time. Onboard the spacecraft are astronauts Paul J. Wietz, Karol J. Bobko, Dr. Story Musgrave and Donald H. Peterson. Photo credit: NASA

  6. Magnetic-Force-Assisted Straightening of Bent Mild Steel Strip by Laser Irradiation

    NASA Astrophysics Data System (ADS)

    Dutta, Polash P.; Kalita, Karuna; Dixit, Uday S.; Liao, Hengcheng

    2017-12-01

    This study proposes a technique to straighten bent metallic strips with magnetic-force-assisted laser irradiation. Experiments were conducted for three different types of mechanically-bent mild strips. The first type was bent strips without any heat treatment. The second type was stress-relieved and third type was subcritical-annealed bent strips. These strips were straightened following different schemes of laser irradiation sequence to understand the performance of straightening. A parametric study was conducted by varying laser power and scanning speed. Micro-hardness, tensile test, Charpy impact test and microstructure after straightening were also studied. Different scanning schemes provided different microstructures and mechanical properties. Any serious deterioration in the quality of straightened strips was not noticed. Overall, subcritical-annealed bent strips provided the best performance in straightening. The proposed straightening scheme has potential of becoming an industrial practice.

  7. Synthesis of Bifunctional Fe3O4@SiO2-Ag Magnetic-Plasmonic Nanoparticles by an Ultrasound Assisted Chemical Method

    NASA Astrophysics Data System (ADS)

    Chu, Dung Tien; Sai, Doanh Cong; Luu, Quynh Manh; Tran, Hong Thi; Quach, Truong Duy; Kim, Dong Hyun; Nguyen, Nam Hoang

    2017-06-01

    Bifunctional magnetic-plasmonic nanoparticles (NPs)—Fe3O4@SiO2-Ag were successfully synthesized by an ultrasound assisted chemical method. Silver ions were absorbed and then reduced by sodium borohydride on the surface of 3-aminopropyltriethoxysilane (APTES) functionalized silica-coated magnetic NPs, then they were reduced under the influence of a 200 W ultrasonic wave for 60 min. When the amount of precursor silver ions increased, the relative intensity of diffraction peaks of silver crystals in all samples increased with the atomic ratio of silver/iron increasing from 0.208 to 0.455 and saturation magnetization ( M s) decreasing from 44.68 emu/g to 34.74 emu/g. The NPs have superparamagnetic properties and strong surface plasmon absorption at 420 nm, which make these particles promising for biomedical applications.

  8. 14 CFR 417.25 - Post launch report.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

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

  9. 14 CFR 417.25 - Post launch report.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

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

  10. 14 CFR 417.25 - Post launch report.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Post launch report. 417.25 Section 417.25... TRANSPORTATION LICENSING LAUNCH SAFETY General and License Terms and Conditions § 417.25 Post launch report. (a) For a launch operator launching from a Federal launch range, a launch operator must file a post launch...

  11. 14 CFR 417.25 - Post launch report.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

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

  12. 14 CFR 417.25 - Post launch report.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

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

  13. Evolved Expendable Launch Vehicle (EELV)

    DTIC Science & Technology

    2015-12-15

    FY13+ Phase I Buy Contractor: United Launch Services, LLC Contractor Location: 9501 East Panorama Circle Centennial , CO 80112 Contract Number...Contract Name: FY13+ Phase I Buy Contractor: United Launch Services, LLC Contractor Location: 9501 East Panorama Circle Centennial , CO 80112 Contract...FY12 EELV Launch Services (ELS5) Contractor: United Launch Services, LLC. Contractor Location: 9501 East Panorama Circle Centennial , CO 80112

  14. 76 FR 52694 - National Environmental Policy Act: Launch of NASA Routine Payloads on Expendable Launch Vehicles

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-08-23

    ...: Launch of NASA Routine Payloads on Expendable Launch Vehicles AGENCY: National Aeronautics and Space Administration (NASA). ACTION: Notice of availability and request for comments on the draft environmental assessment (``Draft EA'') for launch of NASA routine payloads on expendable launch vehicles. SUMMARY...

  15. Is There a Magnet-School Effect? A Multisite Study of MSAP-Funded Magnet Schools

    ERIC Educational Resources Information Center

    Wang, Jia; Schweig, Jonathan D.; Herman, Joan L.

    2017-01-01

    Magnet schools are one of the largest sectors of choice schools in the United States. In this study, we explored the heterogeneity in magnet-school effects on student achievement by examining 24 magnet schools, funded under the Magnet Schools Assistance Program (MSAP), in 5 school districts across 4 states. The magnet effects were synthesized…

  16. Launch, Jupiter-C, Explorer 1

    NASA Technical Reports Server (NTRS)

    1958-01-01

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

  17. Advanced small launch vehicle study

    NASA Technical Reports Server (NTRS)

    Reins, G. E.; Alvis, J. F.

    1972-01-01

    A conceptual design study was conducted to determine the most economical (lowest cost/launch) approach for the development of an advanced small launch vehicle (ASLV) for use over the next decade. The ASLV design objective was to place a 340 kg (750 lb) payload into a 556 km (300 n.mi.) circular orbit when launched due east from Wallops Island, Virginia. The investigation encompassed improvements to the current Scout launch vehicle; use of existing military and NASA launch vehicle stages; and new, optionally staged vehicles. Staging analyses included use of liquid, solid, and hybrid propellants. Improvements in guidance, controls, interstages, telemetry, and payload shroud were also considered. It was concluded that the most economical approach is to progressively improve the Scout launch vehicle in three phased steps which are discussed.

  18. Apollo 4 launch

    NASA Image and Video Library

    1967-09-11

    S67-50903 (9 Nov. 1967) --- The Apollo 4 (Spacecraft 017/Saturn 501) space mission was launched from Pad A, Launch Complex 39, Kennedy Space Center, Florida. The liftoff of the huge 363-feet tall Apollo/Saturn V space vehicle was at 7:00:01 a.m. (EST), Nov. 9, 1967. The successful objectives of the Apollo 4 Earth-orbital unmanned space mission obtained included (1) flight information on launch vehicle and spacecraft structural integrity and compatibility, flight loads, stage separation, subsystem operation, emergency detection subsystem, and (2) evaluation of the Apollo Command Module heat shield under conditions encountered on return from a moon mission.

  19. One-step microwave-assisted synthesis of water-dispersible Fe3O4 magnetic nanoclusters for hyperthermia applications

    NASA Astrophysics Data System (ADS)

    Sathya, Ayyappan; Kalyani, S.; Ranoo, Surojit; Philip, John

    2017-10-01

    To realize magnetic hyperthermia as an alternate stand-alone therapeutic procedure for cancer treatment, magnetic nanoparticles with optimal performance, within the biologically safe limits, are to be produced using simple, reproducible and scalable techniques. Herein, we present a simple, one-step approach for synthesis of water-dispersible magnetic nanoclusters (MNCs) of superparamagnetic iron oxide by reducing of Fe2(SO4)3 in sodium acetate (alkali), poly ethylene glycol (capping ligand), and ethylene glycol (solvent and reductant) in a microwave reactor. The average size and saturation magnetization of the MNC's are tuned from 27 to 52 nm and 32 to 58 emu/g by increasing the reaction time from 10 to 600 s. Transmission electron microscopy images reveal that each MNC composed of large number of primary Fe3O4 nanoparticles. The synthesised MNCs show excellent colloidal stability in aqueous phase due to the adsorbed PEG layer. The highest SAR value of 215 ± 10 W/gFe observed in 52 nm size MNC at a frequency of 126 kHz and field of 63 kA/m suggest the potential use of these MNC in hyperthermia applications. This study further opens up the possibilities to develop metal ion-doped MNCs with tunable sizes suitable for various biomedical applications using microwave assisted synthesis.

  20. Impedance spectroscopy assisted by magnetic nanoparticles as a potential biosensor principle for breast cancer cells in suspension.

    PubMed

    Silva, Jesús G; Cárdenas, Rey A; Quiróz, Alan R; Sánchez, Virginia; Lozano, Lucila M; Pérez, Nadia M; López, Jaime; Villanueva, Cleva; González, César A

    2014-06-01

    Breast cancer (BC) is the leading cause of cancer death in women worldwide, with a higher mortality reported in undeveloped countries. Ideal adjuvant therapeutic strategies require the continuous monitoring of patients by regular blood tests to detect circulating cancer cells, in order to determine whether additional treatment is necessary to prevent cancer dissemination. This circumstance requires a non-complex design of tumor cell biosensor in whole blood with feasibility for use in poor regions. In this work we have evaluated an inexpensive and simple technique of relative bioimpedance measurement, assisted by magnetic nanoparticles, as a potential biosensor of BC cells in suspension. Measurements represent the relative impedance changes caused by the magnetic holding of an interphase of tumor cells versus a homogenous condition in the frequency range of 10-100 kHz. The results indicate that use of a magnet to separate tumor cells in suspension, coupled to magnetic nanoparticles, is a feasible technique to fix an interphase of tumor cells in close proximity to gold electrodes. Relative impedance changes were shown to have potential value as a biosensor method for BC cells in whole blood, at frequencies around 20 kHz. Additional studies are warranted with respect to electrode design and sensitivity at micro-scale levels, according to the proposed technique.

  1. Traveling waves in a magnetized Taylor-Couette flow.

    PubMed

    Liu, Wei; Goodman, Jeremy; Ji, Hantao

    2007-07-01

    We investigate numerically a traveling wave pattern observed in experimental magnetized Taylor-Couette flow at low magnetic Reynolds number. By accurately modeling viscous and magnetic boundaries in all directions, we reproduce the experimentally measured wave patterns and their amplitudes. Contrary to previous claims, the waves are shown to be transiently amplified disturbances launched by viscous boundary layers, rather than globally unstable magnetorotational modes.

  2. MAVEN Atlas V Launch

    NASA Image and Video Library

    2013-11-18

    The United Launch Alliance Atlas V rocket with NASA’s Mars Atmosphere and Volatile EvolutioN (MAVEN) spacecraft launches from the Cape Canaveral Air Force Station Space Launch Complex 41, Monday, Nov. 18, 2013, Cape Canaveral, Florida. NASA’s Mars-bound spacecraft, the Mars Atmosphere and Volatile EvolutioN, or MAVEN, is the first spacecraft devoted to exploring and understanding the Martian upper atmosphere. Photo Credit: (NASA/Bill Ingalls)

  3. NASA’s BARREL Mission Launches 20 Balloons

    NASA Image and Video Library

    2017-12-08

    Some of the BARREL balloon launches took place at the South African National Antarctic Expedition Research base, called SANAE IV, the others at Halley Research Station. This balloon is taking flight at SANAE IV. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014. NASA

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

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... elevation angle setting that ensures the rocket will not fly uprange. A launch operator must set the... throughout each stage of powered flight. A caliber, for a rocket configuration, is defined as the distance... rocket configuration. (f) Tracking. A launch operator must track the flight of an unguided suborbital...

  5. 14 CFR 417.125 - Launch of an unguided suborbital launch vehicle.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... elevation angle setting that ensures the rocket will not fly uprange. A launch operator must set the... throughout each stage of powered flight. A caliber, for a rocket configuration, is defined as the distance... rocket configuration. (f) Tracking. A launch operator must track the flight of an unguided suborbital...

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

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... elevation angle setting that ensures the rocket will not fly uprange. A launch operator must set the... throughout each stage of powered flight. A caliber, for a rocket configuration, is defined as the distance... rocket configuration. (f) Tracking. A launch operator must track the flight of an unguided suborbital...

  7. 14 CFR 417.125 - Launch of an unguided suborbital launch vehicle.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... elevation angle setting that ensures the rocket will not fly uprange. A launch operator must set the... throughout each stage of powered flight. A caliber, for a rocket configuration, is defined as the distance... rocket configuration. (f) Tracking. A launch operator must track the flight of an unguided suborbital...

  8. 14 CFR 417.125 - Launch of an unguided suborbital launch vehicle.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... elevation angle setting that ensures the rocket will not fly uprange. A launch operator must set the... throughout each stage of powered flight. A caliber, for a rocket configuration, is defined as the distance... rocket configuration. (f) Tracking. A launch operator must track the flight of an unguided suborbital...

  9. Space 2035: Technology, Transparency, and Trusted Immunity

    DTIC Science & Technology

    2010-02-17

    12 Figure 2: Maglev -Assisted RLV Concepts .................................................................................. 14...reusable launch vehicles (RLVs). 12, 13 14 Figure 2: Maglev -Assisted RLV Concepts 14 By 2035, several innovative concepts for space...transportation may emerge. These include magnetically-levitated and assisted ( maglev ) RLVs; a novel Space Pier concept, which comprises a series of

  10. New Air-Launched Small Missile (ALSM) Flight Testbed for Hypersonic Systems

    NASA Technical Reports Server (NTRS)

    Bui, Trong T.; Lux, David P.; Stenger, Michael T.; Munson, Michael J.; Teate, George F.

    2007-01-01

    The Phoenix Air-Launched Small Missile (ALSM) flight testbed was conceived and is proposed to help address the lack of quick-turnaround and cost-effective hypersonic flight research capabilities. The Phoenix ALSM testbed results from utilization of the United States Navy Phoenix AIM-54 (Hughes Aircraft Company, now Raytheon Company, Waltham, Massachusetts) long-range, guided air-to-air missile and the National Aeronautics and Space Administration (NASA) Dryden Flight Research Center (Edwards, California) F-15B (McDonnell Douglas, now the Boeing Company, Chicago, Illinois) testbed airplane. The retirement of the Phoenix AIM-54 missiles from fleet operation has presented an opportunity for converting this flight asset into a new flight testbed. This cost-effective new platform will fill the gap in the test and evaluation of hypersonic systems for flight Mach numbers ranging from 3 to 5. Preliminary studies indicate that the Phoenix missile is a highly capable platform; when launched from a high-performance airplane, the guided Phoenix missile can boost research payloads to low hypersonic Mach numbers, enabling flight research in the supersonic-to-hypersonic transitional flight envelope. Experience gained from developing and operating the Phoenix ALSM testbed will assist the development and operation of future higher-performance ALSM flight testbeds as well as responsive microsatellite-small-payload air-launched space boosters.

  11. Magnetic Flux Rope Shredding By a Hyperbolic Flux Tube: The Detrimental Effects of Magnetic Topology on Solar Eruptions

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

    Chintzoglou, Georgios; Vourlidas, Angelos; Savcheva, Antonia

    We present the analysis of an unusual failed eruption captured in high cadence and in many wavelengths during the observing campaign in support of the Very high Angular resolution Ultraviolet Telescope ( VAULT2.0 ) sounding rocket launch. The refurbished VAULT2.0 is a Ly α ( λ 1216 Å) spectroheliograph launched on 2014 September 30. The campaign targeted active region NOAA AR 12172 and was closely coordinated with the Hinode and IRIS missions and several ground-based observatories (NSO/IBIS, SOLIS, and BBSO). A filament eruption accompanied by a low-level flaring event (at the GOES C-class level) occurred around the VAULT2.0 launch. Nomore » coronal mass ejection was observed. The eruption and its source region, however, were recorded by the campaign instruments in many atmospheric heights ranging from the photosphere to the corona in high cadence and spatial resolution. This is a rare occasion that enabled us to perform a comprehensive investigation on a failed eruption. We find that a rising Magnetic Flux Rope (MFR)-like structure was destroyed during its interaction with the ambient magnetic field, creating downflows of cool plasma and diffuse hot coronal structures reminiscent of “cusps.” We employ magnetofrictional simulations to show that the magnetic topology of the ambient field is responsible for the destruction of the MFR. Our unique observations suggest that the magnetic topology of the corona is a key ingredient for a successful eruption.« less

  12. Gravity-Assist Trajectories to the Ice Giants: An Automated Method to Catalog Mass- Or Time-Optimal Solutions

    NASA Technical Reports Server (NTRS)

    Hughes, Kyle M.; Knittel, Jeremy M.; Englander, Jacob A.

    2017-01-01

    This work presents an automated method of calculating mass (or time) optimal gravity-assist trajectories without a priori knowledge of the flyby-body combination. Since gravity assists are particularly crucial for reaching the outer Solar System, we use the Ice Giants, Uranus and Neptune, as example destinations for this work. Catalogs are also provided that list the most attractive trajectories found over launch dates ranging from 2024 to 2038. The tool developed to implement this method, called the Python EMTG Automated Trade Study Application (PEATSA), iteratively runs the Evolutionary Mission Trajectory Generator (EMTG), a NASA Goddard Space Flight Center in-house trajectory optimization tool. EMTG finds gravity-assist trajectories with impulsive maneuvers using a multiple-shooting structure along with stochastic methods (such as monotonic basin hopping) and may be run with or without an initial guess provided. PEATSA runs instances of EMTG in parallel over a grid of launch dates. After each set of runs completes, the best results within a neighborhood of launch dates are used to seed all other cases in that neighborhood-allowing the solutions across the range of launch dates to improve over each iteration. The results here are compared against trajectories found using a grid-search technique, and PEATSA is found to outperform the grid-search results for most launch years considered.

  13. Gravity-Assist Trajectories to the Ice Giants: An Automated Method to Catalog Mass-or Time-Optimal Solutions

    NASA Technical Reports Server (NTRS)

    Hughes, Kyle M.; Knittel, Jeremy M.; Englander, Jacob A.

    2017-01-01

    This work presents an automated method of calculating mass (or time) optimal gravity-assist trajectories without a priori knowledge of the flyby-body combination. Since gravity assists are particularly crucial for reaching the outer Solar System, we use the Ice Giants, Uranus and Neptune, as example destinations for this work. Catalogs are also provided that list the most attractive trajectories found over launch dates ranging from 2024 to 2038. The tool developed to implement this method, called the Python EMTG Automated Trade Study Application (PEATSA), iteratively runs the Evolutionary Mission Trajectory Generator (EMTG), a NASA Goddard Space Flight Center in-house trajectory optimization tool. EMTG finds gravity-assist trajectories with impulsive maneuvers using a multiple-shooting structure along with stochastic methods (such as monotonic basin hopping) and may be run with or without an initial guess provided. PEATSA runs instances of EMTG in parallel over a grid of launch dates. After each set of runs completes, the best results within a neighborhood of launch dates are used to seed all other cases in that neighborhood---allowing the solutions across the range of launch dates to improve over each iteration. The results here are compared against trajectories found using a grid-search technique, and PEATSA is found to outperform the grid-search results for most launch years considered.

  14. Manager's assistant systems for space system planning

    NASA Technical Reports Server (NTRS)

    Bewley, William L.; Burnard, Robert; Edwards, Gary E.; Shoop, James

    1992-01-01

    This paper describes a class of knowledge-based 'assistant' systems for space system planning. Derived from technology produced for the DARPA/USAF Pilot's Associate program, these assistant systems help the human planner by doing the bookkeeping to maintain plan data and executing the procedures and heuristics currently used by the human planner to define, assess, diagnose, and revise plans. Intelligent systems for Space Station Freedom assembly sequence planning and Advanced Launch System modeling will be presented as examples. Ongoing NASA-funded work on a framework supporting the development of such tools will also be described.

  15. Exchange coupled CoPt/FePtC media for heat assisted magnetic recording

    NASA Astrophysics Data System (ADS)

    Dutta, Tanmay; Piramanayagam, S. N.; Ru, Tan Hui; Saifullah, M. S. M.; Bhatia, C. S.; Yang, Hyunsoo

    2018-04-01

    L10 FePtC granular media are being studied as potential future magnetic recording media and are set to be used in conjunction with heat assisted magnetic recording (HAMR) to enable recording at write fields within the range of current day recording heads. Media structures based on a FePtC storage layer and a capping layer can alleviate the switching field distribution (SFD) requirements of HAMR and reduce the noise originating from the writing process. However, the current designs suffer from SFD issues due to high temperature writing. To overcome this problem, we study a CoPt/FePtC exchange coupled composite structure, where FePtC serves as the storage layer and CoPt (with higher Curie temperature, Tc) as the capping layer. CoPt remains ferromagnetic at near Tc of FePtC. Consequently, the counter exchange energy from CoPt would reduce the noise resulting from the adjacent grain interactions during the writing process. CoPt/FePtC bilayer samples with different thicknesses of CoPt were investigated. Our studies found that CoPt forms a continuous layer at a thickness of 6 nm and leads to considerable reduction in the saturation field and its distribution.

  16. U.S. advanced launch vehicle technology programs : Quarterly Launch Report : special report

    DOT National Transportation Integrated Search

    1996-01-01

    U.S. firms and U.S. government agencies are jointly investing in advanced launch vehicle technology. This Special Report summarizes U.S. launch vehicle technology programs and highlights the changing : roles of government and industry players in pick...

  17. Online nutrition and T2DM continuing medical education course launched on state-level medical association.

    PubMed

    Hicks, Kristen K; Murano, Peter S

    2017-01-01

    The purpose of this research study was to determine whether a 1-hour online continuing medical education (CME) course focused on nutrition for type 2 diabetes would result in a gain in nutrition knowledge by practicing physicians. A practicing physician and dietitian collaborated to develop an online CME course (both webinar and self-study versions) on type 2 diabetes. This 1-hour accredited course was launched through the state-level medical association's education library, available to all physicians. Physicians (n=43) registered for the course, and of those, 31 completed the course in its entirety. A gain in knowledge was found when comparing pre- versus post-test scores related to the online nutrition CME ( P <0.0001). Online CME courses launched via state-level medical associations offer convenient continuing education to assist practicing physicians in addressing patient nutrition and lifestyle concerns related to chronic disease. The present diabetes CME one-credit course allowed physicians to develop basic nutrition care concepts on this topic to assist patients in a better way.

  18. Progress of the European Assistive Technology Information Network.

    PubMed

    Gower, Valerio; Andrich, Renzo

    2015-01-01

    The European Assistive Technology Information Network (EASTIN), launched in 2005 as the result of a collaborative EU project, provides information on Assistive Technology products and related material through the website www.eastin.eu. In the past few years several advancements have been implemented on the EASTIN website thanks to the contribution of EU funded projects, including a multilingual query processing component for supporting non expert users, a user rating and comment facility, and a detailed taxonomy for the description of ICT based assistive products. Recently, within the framework of the EU funded project Cloud4All, the EASTIN information system has also been federated with the Unified Listing of assistive products, one of the building blocks of the Global Public Inclusive Infrastructure initiative.

  19. New Horizons Launch Contingency Effort

    NASA Astrophysics Data System (ADS)

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

    2007-01-01

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

  20. Intelsat satellite scheduled for launch

    NASA Technical Reports Server (NTRS)

    1981-01-01

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

  1. Launch Vehicles

    NASA Image and Video Library

    1961-01-01

    This is a comparison illustration of the Redstone, Jupiter-C, and Mercury Redstone launch vehicles. The Redstone ballistic missile was a high-accuracy, liquid-propelled, surface-to-surface missile. Originally developed as a nose cone re-entry test vehicle for the Jupiter intermediate range ballistic missile, the Jupiter-C was a modification of the Redstone missile and successfully launched the first American Satellite, Explorer-1, in orbit on January 31, 1958. The Mercury Redstone lifted off carrying the first American, astronaut Alan Shepard, in his Mercury spacecraft Freedom 7, on May 5, 1961.

  2. Bulk-buy practices by satellite operators foster further commercialization of launch services industry : Quarterly Launch Report : special report

    DOT National Transportation Integrated Search

    1997-01-01

    The satellite launch industry has steadily grown and matured to take on the features of a truly commercial industry. This year, commercial launches outnumber government launches for the first time. New launch systems, such as the Delta 3, Sea Launch,...

  3. STS-135 Atlantis Launch

    NASA Image and Video Library

    2011-07-07

    NASA Administrator Charles Bolden speaks to visitors at the NASA Kennedy Space Center Banana Creek viewing site prior to going to the Launch Control Center (LCC) for the planned launch of the space shuttle Atlantis from pad 39A on Friday, July 8, 2011, in Cape Canaveral, Fla. The launch of Atlantis, STS-135, is the final flight of the shuttle program, a 12-day mission to the International Space Station. Photo Credit: (NASA/Bill Ingalls)

  4. Antares Rocket Test Launch

    NASA Image and Video Library

    2013-04-21

    The Orbital Sciences Corporation Antares rocket is seen as it launches from Pad-0A of the Mid-Atlantic Regional Spaceport (MARS) at the NASA Wallops Flight Facility in Virginia, Sunday, April 21, 2013. The test launch marked the first flight of Antares and the first rocket launch from Pad-0A. The Antares rocket delivered the equivalent mass of a spacecraft, a so-called mass simulated payload, into Earth's orbit. Photo Credit: (NASA/Bill Ingalls)

  5. Launching Garbage-Bag Balloons.

    ERIC Educational Resources Information Center

    Kim, Hy

    1997-01-01

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

  6. Ultrasound-assisted magnetic solid-phase extraction based ionic liquid-coated Fe3O4@graphene for the determination of nitrobenzene compounds in environmental water samples.

    PubMed

    Cao, Xiaoji; Shen, Lingxiao; Ye, Xuemin; Zhang, Feifei; Chen, Jiaoyu; Mo, Weimin

    2014-04-21

    An ultrasound-assisted magnetic solid-phase extraction procedure with the [C7MIM][PF6] ionic liquid-coated Fe3O4-grafted graphene nanocomposite as the magnetic adsorbent has been developed for the determination of five nitrobenzene compounds (NBs) in environmental water samples, in combination with high performance liquid chromatography-photodiode array detector (HPLC-PDA). Several significant factors that affect the extraction efficiency, such as the types of magnetic nanoparticle and ionic liquid, the volume of ionic liquid and the amount of magnetic nanoparticles, extraction time, ionic strength, and solution pH, were investigated. With the assistance of ultrasound, adsorbing nitrobenzene compounds by ionic liquid and self-aggregating ionic liquid onto the surface of the Fe3O4-grafted graphene proceeded synchronously, which made the extraction achieved the maximum within 20 min using only 144 μL [C7MIM][PF6] and 3 mg Fe3O4-grafted graphene. Under the optimized conditions, satisfactory linearities were obtained for all NBs with correlation coefficients larger than 0.9990. The mean recoveries at two spiked levels ranged from 80.35 to 102.77%. Attributed to the convenient magnetic separation, the Fe3O4-grafted graphene could be recycled many times. The proposed method was demonstrated to be feasible, simple, solvent-saving and easy to operate for the trace analysis of NBs in environmental water samples.

  7. Microgravity and Hypogravity Compatible Methods for the Destruction of Solid Wastes by Magnetically Assisted Gasification

    NASA Technical Reports Server (NTRS)

    Atwater, James E.; Akse, James R.; Wheeler, Richard R., Jr.; Jovanovic, Goran N.; Pinto-Espinoza, Joaquin; Reed, Brian; Sornchamni, Thana

    2003-01-01

    This report summarizes a three-year collaborative effort between researchers at UMPQUA Research Company (URC) and the Chemical Engineering Department at Oregon State University (OSU). The Magnetically Assisted Gasification (MAG) concept was originally conceived as a microgravity and hypogravity compatible means for the decomposition of solid waste materials generated aboard spacecraft, lunar and planetary habitations, and for the recovery of potentially valuable resources. While a number of methods such as supercritical water oxidation (SCW0), fluidized bed incineration, pyrolysis , composting and related biological processes have been demonstrated for the decomposition of solid wastes, none of these methods are particularly well- suited for employment under microgravity or hypogravity conditions. For example, fluidized bed incineration relies upon a balance between drag forces which the flowing gas stream exerts upon the fluidization particles and the opposing force of gravity. In the absence of gravity, conventional fluidization cannot take place. Hypogravity operation can also be problematic for conventional fluidized bed reactors, because the various factors which govern fluidization phenomena do not all scale linearly with gravity. For this reason it may be difficult to design and test fluidized bed reactors in lg, which are intended to operate under different gravitational conditions. However, fluidization can be achieved in microgravity (and hypogravity) if a suitable replacement force to counteract the forces between fluid and particles can be found. Possible alternatives include: centripetal force, electric fields, or magnetic fields. Of these, magnetic forces created by the action of magnetic fields and magnetic field gradients upon ferromagnetic media offer the most practical approach. The goal of this URC-OSU collaborative effort was to develop magnetic hardware and methods to control the degree of fluidization (or conversely consolidation) of granular

  8. Pathological and 3 Tesla Volumetric Magnetic Resonance Imaging Predictors of Biochemical Recurrence after Robotic Assisted Radical Prostatectomy: Correlation with Whole Mount Histopathology.

    PubMed

    Tan, Nelly; Shen, Luyao; Khoshnoodi, Pooria; Alcalá, Héctor E; Yu, Weixia; Hsu, William; Reiter, Robert E; Lu, David Y; Raman, Steven S

    2018-05-01

    We sought to identify the clinical and magnetic resonance imaging variables predictive of biochemical recurrence after robotic assisted radical prostatectomy in patients who underwent multiparametric 3 Tesla prostate magnetic resonance imaging. We performed an institutional review board approved, HIPAA (Health Insurance Portability and Accountability Act) compliant, single arm observational study of 3 Tesla multiparametric magnetic resonance imaging prior to robotic assisted radical prostatectomy from December 2009 to March 2016. Clinical, magnetic resonance imaging and pathological information, and clinical outcomes were compiled. Biochemical recurrence was defined as prostate specific antigen 0.2 ng/cc or greater. Univariate and multivariate regression analysis was performed. Biochemical recurrence had developed in 62 of the 255 men (24.3%) included in the study at a median followup of 23.5 months. Compared to the subcohort without biochemical recurrence the subcohort with biochemical recurrence had a greater proportion of patients with a high grade biopsy Gleason score, higher preoperative prostate specific antigen (7.4 vs 5.6 ng/ml), intermediate and high D'Amico classifications, larger tumor volume on magnetic resonance imaging (0.66 vs 0.30 ml), higher PI-RADS® (Prostate Imaging-Reporting and Data System) version 2 category lesions, a greater proportion of intermediate and high grade radical prostatectomy Gleason score lesions, higher pathological T3 stage (all p <0.01) and a higher positive surgical margin rate (19.3% vs 7.8%, p = 0.016). On multivariable analysis only tumor volume on magnetic resonance imaging (adjusted OR 1.57, p = 0.016), pathological T stage (adjusted OR 2.26, p = 0.02), positive surgical margin (adjusted OR 5.0, p = 0.004) and radical prostatectomy Gleason score (adjusted OR 2.29, p = 0.004) predicted biochemical recurrence. In this cohort tumor volume on magnetic resonance imaging and pathological variables, including Gleason score

  9. Development of a Common User Interface for the Launch Decision Support System

    NASA Technical Reports Server (NTRS)

    Scholtz, Jean C.

    1991-01-01

    The Launch Decision Support System (LDSS) is software to be used by the NASA Test Director (NTD) in the firing room during countdown. This software is designed to assist the NTD with time management, that is, when to resume from a hold condition. This software will assist the NTD in making and evaluating alternate plans and will keep him advised of the existing situation. As such, the interface to this software must be designed to provide the maximum amount of information in the clearest fashion and in a timely manner. This research involves applying user interface guidelines to a mature prototype of LDSS and developing displays that will enable the users to easily and efficiently obtain information from the LDSS displays. This research also extends previous work on organizing and prioritizing human-computer interaction knowledge.

  10. Russian Soyuz Moves to Launch Pad

    NASA Technical Reports Server (NTRS)

    2000-01-01

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

  11. SLI Artist `s Launch Concept

    NASA Technical Reports Server (NTRS)

    2002-01-01

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

  12. Room Temperature Magnetic Behavior In Nanocrystalline Ni-Doped Zro2 By Microwave-Assisted Polyol Synthesis

    NASA Astrophysics Data System (ADS)

    Parimita Rath, Pragyan; Parhi, Pankaj Kumar; Ranjan Panda, Sirish; Priyadarshini, Barsharani; Ranjan Sahoo, Tapas

    2017-08-01

    This article, deals with a microwave-assisted polyol method to demonstrate a low temperature route < 250°C, to prepare a high temperature cubic zirconia phase. Powder XRD pattern shows broad diffraction peaks suggesting nanometric size of the particles. Magnetic behavior of 1-5 at% Ni doped samples show a threshold for substitutional induced room temperature ferromagnetism up to 3 at% of Ni. TGA data reveals that Ni-doped ZrO2 polyol precursors decompose exothermically below 300°C. IR data confirms the reduction of Zr(OH)4 precipitates to ZrO2, in agreement with the conclusions drawn from the TGA analysis.

  13. Enrichment of peptides in serum by C(8)-functionalized magnetic nanoparticles for direct matrix-assisted laser desorption/ionization time-of-flight mass spectrometry analysis.

    PubMed

    Yao, Ning; Chen, Hemei; Lin, Huaqing; Deng, Chunhui; Zhang, Xiangmin

    2008-03-21

    Human serum contains a complex array of proteolytically derived peptides (serum peptidome), which contain biomarkers of preclinical screening and disease diagnosis. Recently, commercial C(8)-functionalized magnetic beads (1-10 microm) were widely applied to the separation and enrichment of peptides in human serum, prior to matrix-assisted laser desorption/ionization time-of-flight mass spectrometry (MALDI-TOF-MS) analysis. In this work, laboratory-prepared C(8)-functionalized magnetic nanoparticles (about 50 nm) were prepared and applied to the fast separation and the enrichment of peptides from serum. At first, the C(8)-magnetic nanoparticles were synthesized by modifying amine-functionalized magnetic nanoparticles with chlorodimethyloctylsilane. These synthesized C(8)-amine-functionalized magnetic particles have excellent magnetic responsibility, high dispersibility and large surface area. Finally, the C(8)-magnetic nanoparticles were successfully applied to fast and efficient enrichment of low-abundance peptides from protein tryptic digestion and human serum followed by MALDI-TOF-MS analysis.

  14. Antares Rocket Test Launch

    NASA Image and Video Library

    2013-04-21

    NASA Deputy Administrator Lori Garver and other guests react after having watched the successful launch of the Orbital Sciences Corporation Antares rocket from the Mid-Atlantic Regional Spaceport (MARS) at the NASA Wallops Flight Facility in Virginia, Sunday, April 21, 2013. The test launch marked the first flight of Antares and the first rocket launch from Pad-0A. The Antares rocket delivered the equivalent mass of a spacecraft, a so-called mass simulated payload, into Earth's orbit. Photo Credit: (NASA/Bill Ingalls)

  15. Aquarius SAC-D Launch

    NASA Image and Video Library

    2011-06-10

    A Delta II rocket launches with the Aquarius/SAC-D spacecraft payload from Space Launch Complex 2 at Vandenberg Air Force Base, Calif. on Friday, June 10, 2011. The joint U.S./Argentinian Aquarius/Satélite de Aplicaciones Científicas (SAC)-D mission, set to launch June 10, will map the salinity at the ocean surface, information critical to improving our understanding of two major components of Earth's climate system: the water cycle and ocean circulation. Photo Credit: (NASA/Bill Ingalls)

  16. InSight Launch

    NASA Image and Video Library

    2018-05-05

    The NASA InSight spacecraft launches onboard a United Launch Alliance Atlas-V rocket, Saturday, May 5, 2018, from Vandenberg Air Force Base in California. InSight, short for Interior Exploration using Seismic Investigations, Geodesy and Heat Transport, is a Mars lander designed to study the "inner space" of Mars: its crust, mantle, and core. Photo Credit: (NASA/Bill Ingalls)

  17. Thermally assisted interlayer magnetic coupling through Ba{sub 0.05}Sr{sub 0.95}TiO{sub 3} barriers

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

    Carreira, Santiago J.; Steren, Laura B.; Consejo Nacional de Investigaciones Científicas y Técnicas, Ciudad Autonoma de Buenos Aires C1425FQB

    2016-08-08

    We report on the interlayer exchange coupling across insulating barriers observed on Ni{sub 80}Fe{sub 20}/Ba{sub 0.05}Sr{sub 0.95}TiO{sub 3}/La{sub 0.66}Sr{sub 0.33}MnO{sub 3} (Py/BST{sub 0.05}/LSMO) trilayers. The coupling mechanism has been analyzed in terms of the barrier thickness, samples' substrate, and temperature. We examined the effect of MgO (MGO) and SrTiO{sub 3} (STO) (001) single-crystalline substrates on the magnetic coupling and also on the magnetic anisotropies of the samples in order to get a deeper understanding of the magnetism of the structures. We measured a weak coupling mediated by spin-dependent tunneling phenomena whose sign and strength depend on barrier thickness and substrate.more » An antiferromagnetic (AF) exchange prevails for most of the samples and smoothly increases with the barrier thicknesses as a consequence of the screening effects of the BST{sub 0.05}. The coupling monotonically increases with temperature in all the samples and this behavior is attributed to thermally assisted mechanisms. The magnetic anisotropy of both magnetic components has a cubic symmetry that in the case of permalloy is added to a small uniaxial component.« less

  18. Heat-Assisted Magnetic Recording: Fundamental Limits to Inverse Electromagnetic Design

    NASA Astrophysics Data System (ADS)

    Bhargava, Samarth

    In this dissertation, we address the burgeoning fields of diffractive optics, metals-optics and plasmonics, and computational inverse problems in the engineering design of electromagnetic structures. We focus on the application of the optical nano-focusing system that will enable Heat-Assisted Magnetic Recording (HAMR), a higher density magnetic recording technology that will fulfill the exploding worldwide demand of digital data storage. The heart of HAMR is a system that focuses light to a nano- sub-diffraction-limit spot with an extremely high power density via an optical antenna. We approach this engineering problem by first discussing the fundamental limits of nano-focusing and the material limits for metal-optics and plasmonics. Then, we use efficient gradient-based optimization algorithms to computationally design shapes of 3D nanostructures that outperform human designs on the basis of mass-market product requirements. In 2014, the world manufactured ˜1 zettabyte (ZB), ie. 1 Billion terabytes (TBs), of data storage devices, including ˜560 million magnetic hard disk drives (HDDs). Global demand of storage will likely increase by 10x in the next 5-10 years, and manufacturing capacity cannot keep up with demand alone. We discuss the state-of-art HDD and why industry invented Heat-Assisted Magnetic Recording (HAMR) to overcome the data density limitations. HAMR leverages the temperature sensitivity of magnets, in which the coercivity suddenly and non-linearly falls at the Curie temperature. Data recording to high-density hard disks can be achieved by locally heating one bit of information while co-applying a magnetic field. The heating can be achieved by focusing 100 microW of light to a 30nm diameter spot on the hard disk. This is an enormous light intensity, roughly ˜100,000,000x the intensity of sunlight on the earth's surface! This power density is ˜1,000x the output of gold-coated tapered optical fibers used in Near-field Scanning Optical Microscopes

  19. Constellation Ground Systems Launch Availability Analysis: Enhancing Highly Reliable Launch Systems Design

    NASA Technical Reports Server (NTRS)

    Gernand, Jeffrey L.; Gillespie, Amanda M.; Monaghan, Mark W.; Cummings, Nicholas H.

    2010-01-01

    Success of the Constellation Program's lunar architecture requires successfully launching two vehicles, Ares I/Orion and Ares V/Altair, in a very limited time period. The reliability and maintainability of flight vehicles and ground systems must deliver a high probability of successfully launching the second vehicle in order to avoid wasting the on-orbit asset launched by the first vehicle. The Ground Operations Project determined which ground subsystems had the potential to affect the probability of the second launch and allocated quantitative availability requirements to these subsystems. The Ground Operations Project also developed a methodology to estimate subsystem reliability, availability and maintainability to ensure that ground subsystems complied with allocated launch availability and maintainability requirements. The verification analysis developed quantitative estimates of subsystem availability based on design documentation; testing results, and other information. Where appropriate, actual performance history was used for legacy subsystems or comparative components that will support Constellation. The results of the verification analysis will be used to verify compliance with requirements and to highlight design or performance shortcomings for further decision-making. This case study will discuss the subsystem requirements allocation process, describe the ground systems methodology for completing quantitative reliability, availability and maintainability analysis, and present findings and observation based on analysis leading to the Ground Systems Preliminary Design Review milestone.

  20. ARES I-X Launch

    NASA Image and Video Library

    2009-10-27

    NASA Ares I-X Launch Director Ed Mango, 3rd from left, along with other mission managers watches the launch of the Ares I-X rocket from Firing Room One of the Launch Control Center (LCC) at the Kennedy Space Center in Cape Canaveral, Fla., Wednesday, Oct. 28, 2009. The flight test of Ares I-X will provide NASA with an early opportunity to test and prove flight characteristics, hardware, facilities and ground operations associated with the Ares I. Photo Credit: (NASA/Bill Ingalls)

  1. ARES I-X Launch Prep

    NASA Image and Video Library

    2009-10-26

    NASA Ares I-X Launch Director Ed Mango monitors the launch countdown from Firing Room One of the Launch Control Center (LCC) at the Kennedy Space Center during the planned launch of the Ares I-X rocket from pad 39b at the Kennedy Space Center in Cape Canaveral, Fla., Tuesday, Oct. 27, 2009. The flight test of Ares I-X will provide NASA with an early opportunity to test and prove flight characteristics, hardware, facilities and ground operations associated with the Ares I. Photo Credit: (NASA/Bill Ingalls)

  2. Evolved Expendable Launch Vehicle: DOD Is Assessing Data on Worldwide Launch Market to Inform New Acquisition Strategy

    DTIC Science & Technology

    2016-07-22

    Launch Services (ILS) of a Proton M launch vehicle and one provided by Space Exploration Technologies ( SpaceX ) of a Falcon 9 launch vehicle — and...U.S. based providers are United Launch Alliance (ULA), Space Exploration Technologies Corporation ( SpaceX ), and Orbital ATK. Countries we reviewed

  3. STS Derived Exploration Launch Operations

    NASA Technical Reports Server (NTRS)

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

    2004-01-01

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

  4. NASA’s BARREL Mission Launches 20 Balloons

    NASA Image and Video Library

    2017-12-08

    BARREL team members run under the payload as the balloon first takes flight at the SANAE IV research station in Antarctica. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four

  5. NASA’s BARREL Mission Launches 20 Balloons

    NASA Image and Video Library

    2017-12-08

    A crane lowers two BARREL balloon payloads onto the platform at Halley Research Station in Antarctica. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors

  6. NASA’s BARREL Mission Launches 20 Balloons

    NASA Image and Video Library

    2017-12-08

    The BARREL cargo on its four-hour journey from the supply ship to the research station. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science

  7. NASA’s BARREL Mission Launches 20 Balloons

    NASA Image and Video Library

    2017-12-08

    An emperor penguin waddles away on Christmas morning in Antarctica. On Christmas day, the BARREL team visited a penguin colony. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through

  8. NASA’s BARREL Mission Launches 20 Balloons

    NASA Image and Video Library

    2017-12-08

    Liftoff! A balloon begins to rise over the brand new Halley VI Research Station, which had its grand opening in February 2013. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through

  9. NASA’s BARREL Mission Launches 20 Balloons

    NASA Image and Video Library

    2017-12-08

    Watching a BARREL balloon – and the instruments dangling below – float up over the SANAE IV research base in Antarctica. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four

  10. Performance benefits from pulsed laser heating in heat assisted magnetic recording

    NASA Astrophysics Data System (ADS)

    Xu, B. X.; Cen, Z. H.; Goh, J. H.; Li, J. M.; Toh, Y. T.; Zhang, J.; Ye, K. D.; Quan, C. G.

    2014-05-01

    Smaller cross track thermal spot size and larger down track thermal gradient are desired for increasing the density of heat assisted magnetic recording. Both parameters are affected significantly by the thermal energy accumulation and diffusion in the recording media. Pulsed laser heating is one of the ways to reduce the thermal diffusion. In this paper, we describe the benefits from the pulsed laser heating such as the dependences of the cross track thermal width, down track thermal gradient, the required laser pulse/average powers, and the transducer temperature rise on the laser pulse width at different media thermal properties. The results indicate that as the pulse width decreases, the thermal width decreases, the thermal gradient increases, the required pulse power increases and the average power decreases. For shorter pulse heating, the effects of the medium thermal properties on the thermal performances become weaker. This can greatly relax the required thermal properties of the media. The results also show that the pulsed laser heating can effectively reduce the transducer temperature rise and allow the transducer to reach its "dynamically" stable temperature more quickly.

  11. The Impact of New Trends in Satellite Launches on the Orbital Debris Environment

    NASA Technical Reports Server (NTRS)

    Karacalioglu, Arif Goektug; Stupl, Jan

    2016-01-01

    The main goal of this study is to examine the impact of new trends in satellite launch activities on the orbital debris environment and collision risk. As a foundation for the study, we developed a deployment scenario for satellites and associated rocket bodies based on publicly announced future missions. The upcoming orbital injection technologies, such as the new launch vehicles dedicated for small spacecraft and propulsive interstages, are also considered in this scenario. We then used a simulation tool developed in-house to propagate the objects within this scenario using variable-sized time-steps as small as one second to detect conjunctions between objects. The simulation makes it possible to follow the short- and long-term effects of a particular satellite or constellation in the space environment. Likewise, the effects of changes in the debris environment on a particular satellite or constellation can be evaluated. It is our hope that the results of this paper and further utilization of the developed simulation tool will assist in the investigation of more accurate deorbiting metrics to replace the generic 25-year disposal guidelines, as well as to guide future launches toward more sustainable and safe orbits.

  12. Magnetic navigation system assisted stenting of coronary bifurcation lesions.

    PubMed

    Simsek, Cihan; Magro, Michael; Patterson, Mark S; Onuma, Yoshinobu; Ciampichetti, Isabella; van Weenen, Sander; van Domburg, Ron T; Serruys, Patrick W; Boersma, Eric; van Geuns, Robert-Jan

    2011-03-01

    Magnetic guidewire assisted percutaneous coronary interventions (MPCI) could have certain advantages in coronary bifurcation lesions. We aimed to report the angiographic characteristics of the bifurcation lesions, as well as the procedural and clinical outcomes of the MPCI patients. The lesion characteristics and the treatment effect were assessed by performing diagnostic and quantitative coronary angiography with dedicated bifurcation software. A total of 76 patients (age 65 years, 78% male) were assigned to undergo MPCI, in which two-thirds of the lesions were located in LAD/D1. Fifty-seven out of 78 lesions (73%) had a diseased side branch and complex stenting techniques were used in the majority of the lesions (64%). All 59/78 (76%) fenestration attempts were successfully performed and only 13 dedicated bifurcation stents were implanted. The average acute gain in minimal luminal diameter was 1.08±0.81 mm, 0.80±0.70 mm and 0.59±0.56 mm for the proximal, distal and side branch, respectively. The procedural success was 69% with a procedure time of 107±43 minutes, fluoroscopy time of 34±24 minutes and contrast use of 338±136 ml. At a mean of 1.8-years follow-up, 15 patients (20%) had a cardiac event. MPCI is associated with good angiographic, fenestration and procedural success rates in the treatment of coronary bifurcation lesions.

  13. Antares Rocket Test Launch

    NASA Image and Video Library

    2013-04-21

    NASA Administrator Charles Bolden and NASA Deputy Administrator Lori Garver and other guests react after having watched the successful launch of the Orbital Sciences Corporation Antares rocket from the Mid-Atlantic Regional Spaceport (MARS) at the NASA Wallops Flight Facility in Virginia, Sunday, April 21, 2013. The test launch marked the first flight of Antares and the first rocket launch from Pad-0A. The Antares rocket delivered the equivalent mass of a spacecraft, a so-called mass simulated payload, into Earth's orbit. Photo Credit: (NASA/Bill Ingalls)

  14. M-V launch vehicle

    NASA Astrophysics Data System (ADS)

    Matsuo, Hiroki; Kawaguchi, Jun'ichiro

    1995-01-01

    M-V is the next generation satellite launcher of the Institute of Space and Astronautical Science (IS AS) expected to be a work horse for Japanese scientific missions beyond late 1990s. It is a three staged, solid propellant rocket with 2ton class launch capability into LEO. Its development is underway toward the revised first launch date in 1996. This paper describes the back ground and the design philosophy of M-V along with vehicle characteristics featuring new technology to be introduced. Also given are the development status and the launch schedule.

  15. Head-disk Interface Study for Heat Assisted Magnetic Recording (HAMR) and Plasmonic Nanolithography for Patterned Media

    NASA Astrophysics Data System (ADS)

    Xiong, Shaomin

    The magnetic storage areal density keeps increasing every year, and magnetic recording-based hard disk drives provide a very cheap and effective solution to the ever increasing demand for data storage. Heat assisted magnetic recording (HAMR) and bit patterned media have been proposed to increase the magnetic storage density beyond 1 Tb/in2. In HAMR systems, high magnetic anisotropy materials are recommended to break the superparamagnetic limit for further scaling down the size of magnetic bits. However, the current magnetic transducers are not able to generate strong enough field to switch the magnetic orientations of the high magnetic anisotropy material so the data writing is not able to be achieved. So thermal heating has to be applied to reduce the coercivity for the magnetic writing. To provide the heating, a laser is focused using a near field transducer (NFT) to locally heat a ~(25 nm)2 spot on the magnetic disk to the Curie temperature, which is ~ 400 C-600°C, to assist in the data writing process. But this high temperature working condition is a great challenge for the traditional head-disk interface (HDI). The disk lubricant can be depleted by evaporation or decomposition. The protective carbon overcoat can be graphitized or oxidized. The surface quality, such as its roughness, can be changed as well. The NFT structure is also vulnerable to degradation under the large number of thermal load cycles. The changes of the HDI under the thermal conditions could significantly reduce the robustness and reliability of the HAMR products. In bit patterned media systems, instead of using the continuous magnetic granular material, physically isolated magnetic islands are used to store data. The size of the magnetic islands should be about or less than 25 nm in order to achieve the storage areal density beyond 1 Tb/in2. However, the manufacture of the patterned media disks is a great challenge for the current optical lithography technology. Alternative lithography

  16. Constellation Ground Systems Launch Availability Analysis: Enhancing Highly Reliable Launch Systems Design

    NASA Technical Reports Server (NTRS)

    Gernand, Jeffrey L.; Gillespie, Amanda M.; Monaghan, Mark W.; Cummings, Nicholas H.

    2010-01-01

    Success of the Constellation Program's lunar architecture requires successfully launching two vehicles, Ares I/Orion and Ares V/Altair, within a very limited time period. The reliability and maintainability of flight vehicles and ground systems must deliver a high probability of successfully launching the second vehicle in order to avoid wasting the on-orbit asset launched by the first vehicle. The Ground Operations Project determined which ground subsystems had the potential to affect the probability of the second launch and allocated quantitative availability requirements to these subsystems. The Ground Operations Project also developed a methodology to estimate subsystem reliability, availability, and maintainability to ensure that ground subsystems complied with allocated launch availability and maintainability requirements. The verification analysis developed quantitative estimates of subsystem availability based on design documentation, testing results, and other information. Where appropriate, actual performance history was used to calculate failure rates for legacy subsystems or comparative components that will support Constellation. The results of the verification analysis will be used to assess compliance with requirements and to highlight design or performance shortcomings for further decision making. This case study will discuss the subsystem requirements allocation process, describe the ground systems methodology for completing quantitative reliability, availability, and maintainability analysis, and present findings and observation based on analysis leading to the Ground Operations Project Preliminary Design Review milestone.

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

    NASA Technical Reports Server (NTRS)

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

    2012-01-01

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

  18. The Interplanetary Magnetic Field Observed by Juno Enroute to Jupiter

    NASA Technical Reports Server (NTRS)

    Gruesbeck, Jacob R.; Gershman, Daniel J.; Espley, Jared R.; Connerney, John E. P.

    2017-01-01

    The Juno spacecraft was launched on 5 August 2011 and spent nearly 5 years traveling through the inner heliosphere on its way to Jupiter. The Magnetic Field Investigation was powered on shortly after launch and obtained vector measurements of the interplanetary magnetic field (IMF) at sample rates from 1 to 64 samples/second. The evolution of the magnetic field with radial distance from the Sun is compared to similar observations obtained by Voyager 1 and 2 and the Ulysses spacecraft, allowing a comparison of the radial evolution between prior solar cycles and the current depressed one. During the current solar cycle, the strength of the IMF has decreased throughout the inner heliosphere. A comparison of the variance of the normal component of the magnetic field shows that near Earth the variability of the IMF is similar during all three solar cycles but may be less at greater radial distances.

  19. Commercial space and launch insurance : current market and future outlook : fourth quarter 2002 Quarterly Launch Report

    DOT National Transportation Integrated Search

    2002-01-01

    Since the last review of the space and launch insurance industry (see "Update of the Space and Launch Insurance Industry," 4th quarter, : 1998 Quarterly Launch Report), many changes have occurred in the market. This report endeavors to examine the cu...

  20. NASA’s BARREL Mission Launches 20 Balloons

    NASA Image and Video Library

    2017-12-08

    A BARREL balloon floats into the sky as it is partially filled. When fully inflated, each balloon is 90 feet in diameter and carries an instrument suite that weighs 50 pounds. This is small for an Antarctica balloon launch, which can have balloons Typical balloons l the size of a football field with payloads of some 3,000 pounds. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in

  1. Intelsat communications satellite scheduled for launch

    NASA Technical Reports Server (NTRS)

    1983-01-01

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

  2. Alien crop circle? No, that’s just NASA’s newest balloon launch pad

    NASA Image and Video Library

    2017-12-08

    Aviators, skydivers and other altitude-seeking enthusiasts flying out of Wanaka Airport, New Zealand, are double taking at a new topographical feature reminiscent of an alien crop circle. Rest assured, the nearly 2,000-foot (600-meter) diameter circle with a pie-shaped wedge on one side and spokes on the other is no extraterrestrial footprint and it’s definitely no hoax. It’s NASA’s newest launch pad for launching the agency’s most advanced high-altitude, heavy-lift scientific balloon: the super pressure balloon. The four spokes emanating from the center and toward the west, each nearly 1,000 feet (300 meters) long, align with magnetic compass directions at 240, 260, 290 and 320 degrees. On launch day, balloon flight experts from NASA’s Columbia Scientific Balloon Facility will assess meteorological data and determine if the conditions are suitable to support a launch opportunity. The new pad is the first major project in developing a long-term super pressure balloon launch site in Wanaka. Earlier in 2017, NASA signed a 10-year lease with the Queenstown Airport Corporation to conduct balloon operations from a newly acquired piece of land adjacent to the Wanaka Airport. Credit: NASA/Dave Webb NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

  3. NASA's Space Launch System: An Enabling Capability for Discovery

    NASA Technical Reports Server (NTRS)

    Creech, Stephen D.

    2014-01-01

    infrastructure requirements, cost, and schedule. A traditional baseline approach for a mission to investigate the Jovian system would require a complicated trajectory with several gravity-assist planetary fly-bys to achieve the necessary outbound velocity. The SLS rocket, offering significantly higher C3 energies, can more quickly and effectively take the mission directly to its destination, providing scientific results sooner and at lower operational cost. The SLS rocket will launch payloads of unprecedented mass and volume, such as "monolithic" telescopes and in-space infrastructure, and will revolutionize science mission planning and design for years to come. As this paper will explain, SLS is making measurable progress toward becoming a global infrastructure asset for robotic and human scouts of all nations by harnessing business and technological innovations to deliver sustainable solutions for space exploration.

  4. Athena: Advanced air launched space booster

    NASA Astrophysics Data System (ADS)

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

    1994-06-01

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

  5. Athena: Advanced air launched space booster

    NASA Technical Reports Server (NTRS)

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

    1994-01-01

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

  6. IMP-I spacecraft final magnetic tests

    NASA Technical Reports Server (NTRS)

    Harris, C. A.

    1972-01-01

    The increased IMP-I spacecraft spin axis moment resulting from excessive field exposures during environmental testing substantiated the need for a final pre-launch magnetic deperm and measurement. By performing a dc rotation deperm it was possible to reduce this moment below the previous initial test post deperm magnitude. In addition, the magnetic field disturbance at the flight magnetometer diminished to below 0.1 nanotesla (gamma) in all directions.

  7. Launch Vehicle Communications

    NASA Technical Reports Server (NTRS)

    Welch, Bryan; Greenfeld, Israel

    2005-01-01

    As the National Aeronautics and Space Administration's (NASA) planning for updated launch vehicle operations progresses, there is a need to consider improved methods. This study considers the use of phased array antennas mounted on launch vehicles and transmitting data to either NASA's Tracking and Data Relay Satellite System (TDRSS) satellites or to the commercial Iridium, Intelsat, or Inmarsat communications satellites. Different data rate requirements are analyzed to determine size and weight of resulting antennas.

  8. Taking the Next Steps: The Ares I Crew Launch Vehicle and Ares V Cargo Launch Vehicle

    NASA Technical Reports Server (NTRS)

    Cook, Stephen A.; Vanhooser, Teresa

    2008-01-01

    The National Aeronautics and Space Administration (NASA)'s Constellation Program is depending on the Ares Projects Office (APO) to deliver the crew and cargo launch capabilities needed to send human explorers to the Moon, Mars, and beyond. The APO continues to make progress toward design, component testing, and early flight testing of the Ares I crew launch vehicle, as well as early design work for the Ares V cargo launch vehicle. Ares I and Ares V will form the core space launch capabilities that the United States needs to continue its pioneering tradition as a spacefaring nation (Figure 1). This paper will discuss design, fabrication, and testing progress toward building these new launch vehicles.

  9. No Launch Before Its Time

    NASA Technical Reports Server (NTRS)

    Townsend, Bill

    2004-01-01

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

  10. Magnetically Assisted Surface-Enhanced Raman Spectroscopy for the Detection of Staphylococcus aureus Based on Aptamer Recognition.

    PubMed

    Wang, Junfeng; Wu, Xuezhong; Wang, Chongwen; Shao, Ningsheng; Dong, Peitao; Xiao, Rui; Wang, Shengqi

    2015-09-23

    A magnetically assisted surface-enhanced Raman scattering (SERS) biosensor for single-cell detection of S. aureus on the basis of aptamer recognition is reported for the first time. The biosensor consists of two basic elements including a SERS substrate (Ag-coated magnetic nanoparticles, AgMNPs) and a novel SERS tag (AuNR-DTNB@Ag-DTNB core-shell plasmonic NPs or DTNB-labeled inside-and-outside plasmonic NPs, DioPNPs). Uniform, monodisperse, and superparamagnetic AgMNPs with favorable SERS activity and magnetic responsiveness are synthesized by using polymer polyethylenimine. AgMNPs use magnetic enrichment instead of repeated centrifugation to prevent sample sedimentation. DioPNPs are designed and synthesized as a novel SERS tag. The Raman signal of DioPNPs is 10 times stronger than that of the commonly used SERS tag AuNR-DTNB because of the double-layer DTNB and the LSPR position adjustment to match the given laser excitation wavelength. Consequently, a strong SERS enhancement is achieved. Under the optimized aptamer density and linker length, capture by aptamer-modified AgMNPs can achieve favorable bacteria arrest (up to 75%). With the conventional Raman spectroscopy, the limit of detection (LOD) is 10 cells/mL for S. aureus detection, and a good linear relationship is also observed between the SERS intensity at Raman peak 1331 cm(-1) and the logarithm of bacteria concentrations ranging from 10(1) to 10(5) cells/mL. With the help of the newly developed SERS mapping technique, single-cell detection of S. aureus is easily achieved.

  11. High Altitude Launch for a Practical SSTO

    NASA Technical Reports Server (NTRS)

    Landis, Geoffrey A.; Denis, Vincent

    2003-01-01

    Existing engineering materials allow the construction of towers to heights of many kilometers. Orbital launch from a high altitude has significant advantages over sea-level launch due to the reduced atmospheric pressure, resulting in lower atmospheric drag on the vehicle and allowing higher rocket engine performance. High-altitude launch sites are particularly advantageous for single-stage to orbit (SSTO) vehicles, where the payload is typically 2 percent of the initial launch mass. An earlier paper enumerated some of the advantages of high altitude launch of SSTO vehicles. In this paper, we calculate launch trajectories for a candidate SSTO vehicle, and calculate the advantage of launch at launch altitudes 5 to 25 kilometer altitudes above sea level. The performance increase can be directly translated into increased payload capability to orbit, ranging from 5 to 20 percent increase in the mass to orbit. For a candidate vehicle with an initial payload fraction of 2 percent of gross lift-off weight, this corresponds to 31 percent increase in payload (for 5-kilometer launch altitude) to 122 percent additional payload (for 25-kilometer launch altitude).

  12. High Altitude Launch for a Practical SSTO

    NASA Technical Reports Server (NTRS)

    Landis, Geoffrey A.; Denis, Vincent

    2003-01-01

    Existing engineering materials allow the construction of towers to heights of many kilometers. Orbital launch from a high altitude has significant advantages over sea-level launch due to the reduced atmospheric pressure, resulting in lower atmospheric drag on the vehicle and allowing higher rocket engine performance. high-altitude launch sites are particularly advantageous for single-stage to orbit (SSTO) vehicles, where the payload is typically 2% of the initial launch mass. An earlier paper enumerated some of the advantages of high altitude launch of SSTO vehicles. In this paper, we calculate launch trajectories for a candidate SSTO vehicle, and calculate the advantage of launch at launch altitudes 5 to 25 kilometer altitudes above sea level. The performance increase can be directly translated in to increased payload capability to orbit, ranging from 5 to 20% increase in the mass to orbit. For a candidate vehicle with an initial payload fraction of 2% of gross lift-off weight, this corresponds to 31 % increase in payload (for 5-km launch altitude) to 122% additional payload (for 25-km launch altitude).

  13. High Altitude Launch for a Practical SSTO

    NASA Technical Reports Server (NTRS)

    Landis, Geoffrey A.; Denis, Vincent; Lyons, Valerie (Technical Monitor)

    2003-01-01

    Existing engineering materials allow the construction of towers to heights of many kilometers. Orbital launch from a high altitude has significant advantages over sea-level launch due to the reduced atmospheric pressure, resulting in lower atmospheric drag on the vehicle and allowing higher rocket engine performance. High-altitude launch sites are particularly advantageous for single-stage to orbit (SSTO) vehicles, where the payload is typically 2% of the initial launch mass. An earlier paper enumerated some of the advantages of high altitude launch of SSTO vehicles. In this paper, we calculate launch trajectories for a candidate SSTO vehicle, and calculate the advantage of launch at launch altitudes 5 to 25 kilometer altitudes above sea level. The performance increase can be directly translated into increased payload capability to orbit, ranging from 5 to 20% increase in the mass to orbit. For a candidate vehicle with an initial payload fraction of 2% of gross lift-off weight, this corresponds to 31% increase in payload (for 5-km launch altitude) to 122% additional payload (for 25-km launch altitude).

  14. High Altitude Launch for a Practical SSTO

    NASA Astrophysics Data System (ADS)

    Landis, Geoffrey A.; Denis, Vincent

    2003-01-01

    Existing engineering materials allow the constuction of towers to heights of many kilometers. Orbital launch from a high altitude has significant advantages over sea-level launch due to the reduced atmospheric pressure, resulting in lower atmospheric drag on the vehicle and allowing higher rocket engine performance. High-altitude launch sites are particularly advantageous for single-stage to orbit (SSTO) vehicles, where the payload is typically 2% of the initial launch mass. An earlier paper enumerated some of the advantages of high altitude launch of SSTO vehicles. In this paper, we calculate launch trajectories for a candidate SSTO vehicle, and calculate the advantage of launch at launch altitudes 5 to 25 kilometer altitudes above sea level. The performance increase can be directly translated into increased payload capability to orbit, ranging from 5 to 20% increase in the mass to orbit. For a candidate vehicle with an initial payload fraction of 2% of gross lift-off weight, this corresponds to 31% increase in payload (for 5-km launch altitude) to 122% additional payload (for 25-km launch altitude).

  15. Rocket Launch Trajectory Simulations Mechanism

    NASA Technical Reports Server (NTRS)

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

    2002-01-01

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

  16. Using NASA's Space Launch System to Enable Game Changing Science Mission Designs

    NASA Technical Reports Server (NTRS)

    Creech, Stephen D.

    2013-01-01

    NASA's Marshall Space Flight Center is directing efforts to build the Space Launch System (SLS), a heavy-lift rocket that will help restore U.S. leadership in space by carrying the Orion Multi-Purpose Crew Vehicle and other important payloads far beyond Earth orbit. Its evolvable architecture will allow NASA to begin with Moon fly-bys and then go on to transport humans or robots to distant places such as asteroids, Mars, and the outer solar system. Designed to simplify spacecraft complexity, the SLS rocket will provide improved mass margins and radiation mitigation, and reduced mission durations. These capabilities offer attractive advantages for ambitious missions such as a Mars sample return, by reducing infrastructure requirements, cost, and schedule. For example, if an evolved expendable launch vehicle (EELV) were used for a proposed mission to investigate the Saturn system, a complicated trajectory would be required with several gravity-assist planetary fly-bys to achieve the necessary outbound velocity. The SLS rocket, using significantly higher C3 energies, can more quickly and effectively take the mission directly to its destination, reducing trip times and cost. As this paper will report, the SLS rocket will launch payloads of unprecedented mass and volume, such as monolithic telescopes and in-space infrastructure. Thanks to its ability to co-manifest large payloads, it also can accomplish complex missions in fewer launches. Future analyses will include reviews of alternate mission concepts and detailed evaluations of SLS figures of merit, helping the new rocket revolutionize science mission planning and design for years to come.

  17. Launch of Jupiter-C/Explorer 1

    NASA Technical Reports Server (NTRS)

    1958-01-01

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

  18. Environmentally-Preferable Launch Coatings

    NASA Technical Reports Server (NTRS)

    Kessel, Kurt R.

    2015-01-01

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

  19. Launch Vehicles

    NASA Image and Video Library

    2007-09-09

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

  20. Functional Fe3O4@ZnO magnetic nanoparticle-assisted enrichment and enzymatic digestion of phosphoproteins from saliva.

    PubMed

    Chen, Wei-Yu; Chen, Yu-Chie

    2010-11-01

    Saliva contains various proteins, particularly abundant are phosphoproteins, that may be related to disease occurrences and that play significant roles in a biological system. Thus, medical diagnostics will benefit tremendously if disease-related protein biomarkers are discovered from saliva. In this paper, we propose and demonstrate an approach using functional zinc oxide coated iron oxide magnetic nanoparticles (Fe(3)O(4)@ZnO MNPs) as affinity probes to selectively enrich phosphoproteins from complex saliva samples and as microwave absorbers to assist the enrichment and subsequent tryptic digestion of trapped proteins under microwave heating. The target species trapped by MNPs were characterized by matrix-assisted laser desorption/ionization mass spectrometry (MALDI MS) combined with protein database search. Entire analysis time was shortened to less than 20 min. The detection limit of this approach for a monophosphopeptide was as low as 250 pM (10 μL).

  1. Nanopatterning reconfigurable magnetic landscapes via thermally assisted scanning probe lithography

    NASA Astrophysics Data System (ADS)

    Albisetti, E.; Petti, D.; Pancaldi, M.; Madami, M.; Tacchi, S.; Curtis, J.; King, W. P.; Papp, A.; Csaba, G.; Porod, W.; Vavassori, P.; Riedo, E.; Bertacco, R.

    2016-06-01

    The search for novel tools to control magnetism at the nanoscale is crucial for the development of new paradigms in optics, electronics and spintronics. So far, the fabrication of magnetic nanostructures has been achieved mainly through irreversible structural or chemical modifications. Here, we propose a new concept for creating reconfigurable magnetic nanopatterns by crafting, at the nanoscale, the magnetic anisotropy landscape of a ferromagnetic layer exchange-coupled to an antiferromagnetic layer. By performing localized field cooling with the hot tip of a scanning probe microscope, magnetic structures, with arbitrarily oriented magnetization and tunable unidirectional anisotropy, are reversibly patterned without modifying the film chemistry and topography. This opens unforeseen possibilities for the development of novel metamaterials with finely tuned magnetic properties, such as reconfigurable magneto-plasmonic and magnonic crystals. In this context, we experimentally demonstrate spatially controlled spin wave excitation and propagation in magnetic structures patterned with the proposed method.

  2. Nanopatterning reconfigurable magnetic landscapes via thermally assisted scanning probe lithography.

    PubMed

    Albisetti, E; Petti, D; Pancaldi, M; Madami, M; Tacchi, S; Curtis, J; King, W P; Papp, A; Csaba, G; Porod, W; Vavassori, P; Riedo, E; Bertacco, R

    2016-06-01

    The search for novel tools to control magnetism at the nanoscale is crucial for the development of new paradigms in optics, electronics and spintronics. So far, the fabrication of magnetic nanostructures has been achieved mainly through irreversible structural or chemical modifications. Here, we propose a new concept for creating reconfigurable magnetic nanopatterns by crafting, at the nanoscale, the magnetic anisotropy landscape of a ferromagnetic layer exchange-coupled to an antiferromagnetic layer. By performing localized field cooling with the hot tip of a scanning probe microscope, magnetic structures, with arbitrarily oriented magnetization and tunable unidirectional anisotropy, are reversibly patterned without modifying the film chemistry and topography. This opens unforeseen possibilities for the development of novel metamaterials with finely tuned magnetic properties, such as reconfigurable magneto-plasmonic and magnonic crystals. In this context, we experimentally demonstrate spatially controlled spin wave excitation and propagation in magnetic structures patterned with the proposed method.

  3. Mobile, high-wind, balloon-launching apparatus

    NASA Technical Reports Server (NTRS)

    Rust, W. David; Marshall, Thomas C.

    1989-01-01

    In order to place instruments for measuring meteorological and electrical parameters into thunderstorms, an inexpensive apparatus has been developed which makes it possible to inflate, transport, and launch balloons in high winds. The launching apparatus is a cylinder of bubble plastic that is made by joining the sides of the cylinder together with a velcro rip strip. A balloon is launched by pulling the rip strip rapidly. This allows the balloon to pop upward into the ambient low-level wind and carry its instrumentation aloft. Different-sized launch tubes are constructed to accommodate particular sizes of balloons. Balloons have been launched in winds of about 20 m/s.

  4. STS-135 Launch Day

    NASA Image and Video Library

    2011-07-07

    NASA Chief, Astronaut Office, Johnson Space Center Peggy Whitson deals cards during a traditional game that is played at the NASA Kennedy Space Center Operations and Checkout Building with the shuttle crew prior to them leaving for the launch pad, on Friday, July 8, 2011 in Cape Canaveral, Fla. The point of the game is that the commander must use up all his or her bad luck before launch, so the crew can only leave for the pad after the commander loses. The launch of Atlantis, STS-135, is the final flight of the shuttle program, a 12-day mission to the International Space Station. Photo Credit: (NASA/Jerry Ross)

  5. Launch Commit Criteria Monitoring Agent

    NASA Technical Reports Server (NTRS)

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

    2005-01-01

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

  6. Intellectual Disability and Assistive Technology: Opening the GATE Wider.

    PubMed

    Boot, Fleur Heleen; Dinsmore, John; Khasnabis, Chapal; MacLachlan, Malcolm

    2017-01-01

    The World Health Organization has launched a program to promote Global Cooperation on Assistive Technology (GATE). The objective of the GATE program is to improve access to high quality, affordable assistive technology for people with varying disabilities, diseases, and age-related conditions. As a first step, GATE has developed the assistive products list, a list of priority assistive products based on addressing the greatest need at population level. A specific group of people who can benefit from user appropriate assistive technology are people with intellectual disabilities. However, the use of assistive products by people with intellectual disabilities is a neglected area of research and practice, and offers considerable opportunities for the advancement of population health and the realization of basic human rights. It is unknown how many people with intellectual disabilities globally have access to appropriate assistive products and which factors influence their access. We call for a much greater focus on people with intellectual disabilities within the GATE program. We present a framework for understanding the complex interaction between intellectual disability, health and wellbeing, and assistive technology.

  7. Trends in space launch services : globalization and commercial development : Quarterly Launch Report : special report

    DOT National Transportation Integrated Search

    1996-01-01

    Launch service providers are leading the globalization of the space industry by forming international partnerships. The end of the Cold : War has created an environment that favors cooperation between manufacturers of high technology launch systems, ...

  8. Fifth International Symposium on Magnetic Suspension Technology

    NASA Technical Reports Server (NTRS)

    Groom, Nelson J. (Editor); Britcher, Colin P.

    2000-01-01

    In order to examine the state of technology of all areas of magnetic suspension and to review recent developments in sensors, controls, superconducting magnet technology, and design/implementation practices, the Fifth International Symposium on Magnetic Suspension Technology was held at the Radisson Hotel Santa Barbara, Santa Barbara, California, on December 1-3, 1999. The symposium included 18 sessions in which a total of 53 papers were presented. The technical sessions covered the areas of bearings, controls, modeling, electromagnetic launch, magnetic suspension in wind tunnels, applications flywheel energy storage, rotating machinery, vibration isolation, and maglev. A list of attendees is included in the document.

  9. EELV Booster Assist Options for CEV

    NASA Technical Reports Server (NTRS)

    McNeal, Curtis, Jr.

    2005-01-01

    Medium lift EELVs may still play a role in manned space flight. To be considered for manned flight, medium lift EELVs must address the short comings in their current boost assist motors. Two options exist: redesign and requalify the solid rocket motors. Replace solid rocket motors (SRMs) with hybrid rocket motors. Hybrid rocket motors are an attractive alternative. They are safer than SRMs. The TRL's Lockheed Martin Small Launch Vehicle booster development substantially lowers the development risk, cost risk, and the schedule risk for developing hybrid boost assist for EELVs. Hybrid boosters testability offsets SRMs higher inherent reliability.Hybrid booster development and recurring costs are lower than SRMs. Performance gains are readily achieved.

  10. Little Joe Launch

    NASA Image and Video Library

    1959-10-04

    Launching of the LJ6 Little Joe on Oct. 4, 1959 took place at Wallops Island, Va. This was the first attempt to launch an instrumented capsule with a Little Joe booster. Only the LJ1A and the LJ6 used the space metal chevron plates as heat reflector shields, as they kept shattering. Caption title ...and ascending skyward on a plume of exhaust. Photograph published in Winds of Change, 75th Anniversary NASA publication, page 77, by James Schultz

  11. Launch of STS-63 Discovery

    NASA Technical Reports Server (NTRS)

    1995-01-01

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

  12. Peer Review of Launch Environments

    NASA Technical Reports Server (NTRS)

    Wilson, Timmy R.

    2011-01-01

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

  13. Reusable Launch Vehicle Technology Program

    NASA Technical Reports Server (NTRS)

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

    1996-01-01

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

  14. The U.S. Evolved Expendable Launch Vehicle (EELV) programs : Quarterly Launch Report : special report

    DOT National Transportation Integrated Search

    1997-01-01

    The Evolved Expendable Launch Vehicle (EELV) Program is a Department of Defense technology-development program managed by the Air Force. The program is intended to produce an improved launch vehicle family for government use. The EELV will replace th...

  15. ISS Service Module Pre-Launch

    NASA Technical Reports Server (NTRS)

    2000-01-01

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

  16. Antares Rocket Test Launch

    NASA Image and Video Library

    2013-04-21

    NASA Deputy Administrator Lori Garver talks with CEO and President of Orbital Sciences Corporation David Thompson, left, Executive Vice President and Chief Technical Officer, Orbital Sciences Corporation Antonio Elias, second from left, and Executive Director, Va. Commercial Space Flight Authority Dale Nash, background, in the Range Control Center at the NASA Wallops Flight Facility after the successful launch of the Orbital Sciences Antares rocket from the Mid-Atlantic Regional Spaceport (MARS) in Virginia, Sunday, April 21, 2013. The test launch marked the first flight of Antares and the first rocket launch from Pad-0A. The Antares rocket delivered the equivalent mass of a spacecraft, a so-called mass simulated payload, into Earth's orbit. Photo Credit: (NASA/Bill Ingalls)

  17. LAUNCH - STS-1 - KSC

    NASA Image and Video Library

    1981-04-12

    S81-30498 (12 April 1981) --- After six years of silence, the thunder of manned spaceflight is heard again, as the successful launch of the first space shuttle ushers in a new concept in utilization of space. The April 12, 1981 launch, at Pad 39A, just seconds past 7 a.m., carries astronaut John Young and Robert Crippen into an Earth-orbital mission scheduled to last for 54 hours, ending with unpowered landing at Edwards Air Force Base in California. STS-1, the first in a series of shuttle vehicles planned for the Space Transportation System, utilizes reusable launch and return components. Photo credit: NASA or National Aeronautics and Space Administration

  18. STS-135 Launch Day

    NASA Image and Video Library

    2011-07-07

    NASA Chief, Astronaut Office, Johnson Space Center Peggy Whitson, center, STS-135 Astronauts, Rex Walheim, left, and Commander Chris Ferguson are seen as the entire crew plays a traditional card game at the NASA Kennedy Space Center Operations and Checkout Building prior to them leaving for the launch pad, on Friday, July 8, 2011 in Cape Canaveral, Fla. The point of the game is that the commander must use up all his or her bad luck before launch, so the crew can only leave for the pad after the commander loses. The launch of Atlantis, STS-135, is the final flight of the shuttle program, a 12-day mission to the International Space Station. Photo Credit: (NASA/Jerry Ross)

  19. 14 CFR 415.109 - Launch description.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ...) Identification of any facilities at the launch site that will be used for launch processing and flight. (b... dimensions and weight; (iii) Location of all safety critical systems, including any flight termination hardware, tracking aids, or telemetry systems; (iv) Location of all major launch vehicle control systems...

  20. 14 CFR 415.109 - Launch description.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ...) Identification of any facilities at the launch site that will be used for launch processing and flight. (b... dimensions and weight; (iii) Location of all safety critical systems, including any flight termination hardware, tracking aids, or telemetry systems; (iv) Location of all major launch vehicle control systems...

  1. 14 CFR 415.109 - Launch description.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ...) Identification of any facilities at the launch site that will be used for launch processing and flight. (b... dimensions and weight; (iii) Location of all safety critical systems, including any flight termination hardware, tracking aids, or telemetry systems; (iv) Location of all major launch vehicle control systems...

  2. Launch Pad Flame Trench Refractory Materials

    NASA Technical Reports Server (NTRS)

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

    2010-01-01

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

  3. Advanced Transportation System Studies Technical Area 2 (TA-2) Heavy Lift Launch Vehicle Development Contract. Volume 2; Technical Results

    NASA Technical Reports Server (NTRS)

    1995-01-01

    The purpose of the Advanced Transportation System Studies (ATSS) Technical Area 2 (TA-2) Heavy Lift Launch Vehicle Development contract was to provide advanced launch vehicle concept definition and analysis to assist NASA in the identification of future launch vehicle requirements. Contracted analysis activities included vehicle sizing and performance analysis, subsystem concept definition, propulsion subsystem definition (foreign and domestic), ground operations and facilities analysis, and life cycle cost estimation. This document is Volume 2 of the final report for the contract. It provides documentation of selected technical results from various TA-2 analysis activities, including a detailed narrative description of the SSTO concept assessment results, a user's guide for the associated SSTO sizing tools, an SSTO turnaround assessment report, an executive summary of the ground operations assessments performed during the first year of the contract, a configuration-independent vehicle health management system requirements report, a copy of all major TA-2 contract presentations, a copy of the FLO launch vehicle final report, and references to Pratt & Whitney's TA-2 sponsored final reports regarding the identification of Russian main propulsion technologies.

  4. WESTAR-V launch on delta

    NASA Technical Reports Server (NTRS)

    1982-01-01

    The WESTAR-V, the second in a series of second-generation, large, 24-transponder communications satellites developed for the Space Communications Company is discussed. It is scheduled to be launched on a Delta vehicle from the Eastern Space and Missile Center no earlier than June 8, 1982. The launch support for this mission will be provided by NASA, on a reimbursable basis, to the Space Communications Company for a fixed price of $25.OM. The launch vehicle for the WESTAR-V mission will be the Delta 3910 configuration which incorporates an extended long tank Thor booster, nine Castor IV strap-on motors, a TR-201 second stage, and an 8-foot fairing. The Delta launch vehicle will place the spacecraft along a suborbital trajectory. The PAM-D stage will then thrust it to a synchronous transfer orbit. Three days after launch, the spacecraft apogee kick motor will be fired to circularize its orbit at geosynchronous altitude of 19,300 NM above the equator at approxmately 75 degrees west longitude.

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

    NASA Technical Reports Server (NTRS)

    Creech, Stephen D.; May, Todd A.

    2013-01-01

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

  6. Space Launch System Spacecraft and Payload Elements: Making Progress Toward First Launch

    NASA Technical Reports Server (NTRS)

    Schorr, Andrew A.; Creech, Stephen D.; Ogles, Michael; Hitt, David

    2016-01-01

    Significant and substantial progress continues to be accomplished in the design, development, and testing of the Space Launch System (SLS), the most powerful human-rated launch vehicle the United States has ever undertaken. Designed to support human missions into deep space, SLS is one of three programs being managed by the National Aeronautics and Space Administration's (NASA's) Exploration Systems Development directorate. The Orion spacecraft program is developing a new crew vehicle that will support human missions beyond low Earth orbit, and the Ground Systems Development and Operations (GSDO) program is transforming Kennedy Space Center (KSC) into next-generation spaceport capable of supporting not only SLS but also multiple commercial users. Together, these systems will support human exploration missions into the proving ground of cislunar space and ultimately to Mars. SLS will deliver a near-term heavy-lift capability for the nation with its 70 metric ton Block 1 configuration, and will then evolve to an ultimate capability of 130 metric tons. The SLS program marked a major milestone with the successful completion of the Critical Design Review in which detailed designs were reviewed and subsequently approved for proceeding with full-scale production. This marks the first time an exploration class vehicle has passed that major milestone since the Saturn V vehicle launched astronauts in the 1960s during the Apollo program. Each element of the vehicle now has flight hardware in production in support of the initial flight of the SLS - Exploration Mission-1 (EM-1), an uncrewed mission to orbit the moon and return, and progress in on track to meet the initial targeted launch date in 2018. In Utah and Mississippi, booster and engine testing are verifying upgrades made to proven shuttle hardware. At Michoud Assembly Facility (MAF) in Louisiana, the world's largest spacecraft welding tool is producing tanks for the SLS core stage. This paper will particularly focus on

  7. Synthesis of magnetic nickel spinel ferrite nanospheres by a reverse emulsion-assisted hydrothermal process

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

    Zhang Jilin; Shi Jianxin, E-mail: chemshijx@163.co; Gong Menglian

    2009-08-15

    Nickel ferrite nanospheres were successfully synthesized by a reverse emulsion-assisted hydrothermal method. The reverse emulsion was composed of water, cetyltrimethyl ammonium bromide, polyoxyethylene(10)nonyl phenyl ether, iso-amyl alcohol and hexane. During the hydrothermal process, beta-FeO(OH) and Ni{sub 0.75}Fe{sub 0.25}(CO{sub 3}){sub 0.125}(OH){sub 2}.0.38H{sub 2}O (INCHH) nanorods formed first and then transformed into nickel spinel ferrite nanospheres. The phase transformation mechanism is proposed based on the results of X-ray powder diffraction, transmission electron microscopy and energy-dispersive X-ray spectroscopy, etc. Nickel ferrite may form at the end of the INCHH nanorods or from the solution accompanied by the dissolution of beta-FeO(OH) and INCHH nanorods.more » The X-ray photoelectron spectroscopy analysis shows that a few Fe{sup 3+} ions have been reduced to Fe{sup 2+} ions during the formation of nickel ferrite. The maximum magnetization of the nickel ferrite nanospheres obtained after hydrothermal reaction for 30 h is 55.01 emu/g, which is close to that of bulk NiFe{sub 2}O{sub 4}. - Graphical abstract: Nickel ferrite nanospheres were obtained through a reverse emulsion-assisted hydrothermal process. The phase transformation as a function of reaction time was studied based on the XRD, TEM and EDS analyses.« less

  8. 46 CFR 133.120 - Launching stations.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 46 Shipping 4 2012-10-01 2012-10-01 false Launching stations. 133.120 Section 133.120 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) OFFSHORE SUPPLY VESSELS LIFESAVING SYSTEMS Requirements for All OSVs § 133.120 Launching stations. (a) Each launching station must be positioned to ensure...

  9. 46 CFR 133.120 - Launching stations.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 46 Shipping 4 2014-10-01 2014-10-01 false Launching stations. 133.120 Section 133.120 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) OFFSHORE SUPPLY VESSELS LIFESAVING SYSTEMS Requirements for All OSVs § 133.120 Launching stations. (a) Each launching station must be positioned to ensure...

  10. Interpretation of long- and short-wavelength magnetic anomalies

    USGS Publications Warehouse

    DeNoyer, John M.; Barringer, Anthony R.

    1980-01-01

    Magset was launched on October 30, 1979. More than a decade of examining existing data, devising appropriate models of the global magnetic field, and extending methods for interpreting long-wavelength magnetic anomalies preceded this launch Magnetic data collected by satellite can be interrupted by using a method of analysis that quantitively describes the magnetic field resulting from three-dimensional geologic structures that are bounded by an arbitrary number of polygonal faces, Each face my have any orientation and three or more sides. At each point of the external field, the component normal to each face is obtained by using an expression for the solid angle subtended by a generalized polygon. The "cross" of tangential components are relatively easy to obtain for the same polygons. No approximations have been made related to orbit height that restrict the dimensions of the polygons relative to the distance from the external field points. This permits the method to be used to model shorter wavelength anomalies obtained from aircraft or ground surveys. The magnetic fields for all the structures considered are determine in the same rectangular coordinate system. The coordinate system is in depended from the orientation of geologic trends and permits multiple structures or bodies to be included in the same magnetic field calculations. This single reference system also simplified adjustments in position and direction to account for earth curvature in regional interpretation.

  11. NASA’s BARREL Mission Launches 20 Balloons

    NASA Image and Video Library

    2017-12-08

    An iceberg as viewed from the bow of the RRS Ernest Shackleton a few days before the BARREL team reached Halley Research Station in Antarctica. This research vessel regularly carries scientists and supplies to Halley. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014

  12. NASA’s BARREL Mission Launches 20 Balloons

    NASA Image and Video Library

    2017-12-08

    Arrival of the RRS Ernest Shackleton near Halley Research Station in Antarctica. The Shackleton is the regular resupply ship for the station and it also brought in some of the BARREL team scientists. The long tether is for the ship’s mooring. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch

  13. Launch of STS-63 Discovery

    NASA Technical Reports Server (NTRS)

    1995-01-01

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

  14. Launch of STS-63 Discovery

    NASA Technical Reports Server (NTRS)

    1995-01-01

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

  15. The Aquila launch service for small satellites

    NASA Astrophysics Data System (ADS)

    Whittinghill, George R.; McKinney, Bevin C.

    1992-07-01

    The Aquila launch vehicle is described emphasizing its use in the deployment of small satellites for the commercial sector. The Aquila is designed to use a guidance, navigation, and control system, and the rocket is based on hybrid propulsion incorporating a liquid oxidizer with a solid polybutadiene fuel. The launch vehicle for the system is a ground-launched four-stage vehicle that can deliver 3,200 lbs of payload into a 185-km circular orbit at 90-deg inclination. Aquila avionics include inertial navigation, radar transponder, and an S-band telemetry transmitter. The payload environment minimizes in-flight acoustic levels, and the launch-ascent profile is characterized by low acceleration. The launch vehicle uses low-cost rocket motors, a high-performance LO(x) feed system, and erector launch capability which contribute to efficient launches for commercial payloads for low polar earth orbits.

  16. NPP Satellite Launch

    NASA Image and Video Library

    2011-10-28

    The Satellite Operations Facility of the National Oceanic and Atmospheric Administration (NOAA) is seen here minutes before the launch of the National Polar-orbiting Operational Environmental Satellite System Preparatory Project (NPP) on Friday, Oct. 28, 2011 in Suitland, Md. NPP is a joint venture between NASA and NOAA, and is the nation's newest Earth-observing satellite, which will provide data on climate change science, allow for accurate weather forecasts and advance warning for severe weather. NPP was launched from Vandenberg Air Force Base in California. Photo Credit: (NASA/Carla Cioffi)

  17. Operation of magnetically assisted fluidized beds in microgravity and variable gravity: experiment and theory

    NASA Technical Reports Server (NTRS)

    Sornchamni, T.; Jovanovic, G. N.; Reed, B. P.; Atwater, J. E.; Akse, J. R.; Wheeler, R. R.

    2004-01-01

    The conversion of solid waste into useful resources in support of long duration manned missions in space presents serious technological challenges. Several technologies, including supercritical water oxidation, microwave powered combustion and fluidized bed incineration, have been tested for the conversion of solid waste. However, none of these technologies are compatible with microgravity or hypogravity operating conditions. In this paper, we present the gradient magnetically assisted fluidized bed (G-MAFB) as a promising operating platform for fluidized bed operations in the space environment. Our experimental and theoretical work has resulted in both the development of a theoretical model based on fundamental principles for the design of the G-MAFB, and also the practical implementation of the G-MAFB in the filtration and destruction of solid biomass waste particles from liquid streams. c2004 COSPAR. Published by Elsevier Ltd. All rights reserved.

  18. Experimental investigation of coaxial-gun-formed plasmas injected into a background transverse magnetic field or plasma

    NASA Astrophysics Data System (ADS)

    Zhang, Yue; Fisher, Dustin M.; Gilmore, Mark; Hsu, Scott C.; Lynn, Alan G.

    2018-05-01

    Injection of coaxial-gun-formed magnetized plasmas into a background transverse vacuum magnetic field or into a background magnetized plasma has been studied in the helicon-cathode (HelCat) linear plasma device at the University of New Mexico [M. Gilmore et al., J. Plasma Phys. 81, 345810104 (2015)]. A magnetized plasma jet launched into a background transverse magnetic field shows emergent kink stabilization of the jet due to the formation of a sheared flow in the jet above the kink stabilization threshold 0.1kVA [Y. Zhang et al., Phys. Plasmas 24, 110702 (2017)]. Injection of a spheromak-like plasma into a transverse background magnetic field led to the observation of finger-like structures on the side with a stronger magnetic field null between the spheromak and the background field. The finger-like structures are consistent with magneto-Rayleigh-Taylor instability. Jets or spheromaks launched into a background, low-β magnetized plasma show similar behavior as above, respectively, in both cases.

  19. STS-112 M.S. Magnus in white room before launch

    NASA Technical Reports Server (NTRS)

    2002-01-01

    KENNEDY SPACE CENTER, FLA. - -- In the White Room at Launch Pad 39B, STS-112 Mission Specialist Sandra H. Magnus, Ph.D., receives assistance with her spacesuit before boarding Space Shuttle Atlantis. Liftoff is schedued for 3:46 p.m. EDT. Along with a crew of six, Atlantis will carry the S1 Integrated Truss Structure and the Crew and Equipment Translation Aid (CETA) Cart A to the International Space Station (ISS). The CETA is the first of two human-powered carts that will ride along the ISS railway, providing mobile work platforms for future spacewalking astronauts. On the 11-day mission, three spacewalks are planned to attach the S1 truss.

  20. STS-112 M.S. Sellers in white room before launch

    NASA Technical Reports Server (NTRS)

    2002-01-01

    KENNEDY SPACE CENTER, FLA. - -- In the White Room at Launch Pad 39B, STS-112 Mission Specialist Piers J. Sellers, Ph.D., receives assistance with his spacesuit before boarding Space Shuttle Atlantis. Liftoff is schedued for 3:46 p.m. EDT. Along with a crew of six, Atlantis will carry the S1 Integrated Truss Structure and the Crew and Equipment Translation Aid (CETA) Cart A to the International Space Station (ISS). The CETA is the first of two human-powered carts that will ride along the ISS railway, providing mobile work platforms for future spacewalking astronauts. On the 11-day mission, three spacewalks are planned to attach the S1 truss.

  1. STS-112 M.S. Wolf in white room before launch

    NASA Technical Reports Server (NTRS)

    2002-01-01

    KENNEDY SPACE CENTER, FLA. - -- In the White Room at Launch Pad 39B, STS-112 Mission Specialist David A. Wolf, M.D., receives assistance with his spacesuit before boarding Space Shuttle Atlantis. Liftoff is schedued for 3:46 p.m. EDT. Along with a crew of six, Atlantis will carry the S1 Integrated Truss Structure and the Crew and Equipment Translation Aid (CETA) Cart A to the International Space Station (ISS). The CETA is the first of two human-powered carts that will ride along the ISS railway, providing mobile work platforms for future spacewalking astronauts. On the 11-day mission, three spacewalks are planned to attach the S1 truss.

  2. Technicians assist STS-41 Pilot Cabana his parachute prior to egress training

    NASA Technical Reports Server (NTRS)

    1990-01-01

    Technicians (training personnel) assist STS-41 Discovery, Orbiter Vehicle (OV) 103, Pilot Robert D. Cabana with his launch and entry suit (LES) parachute prior to emergency egress training exercises in JSC's Mockup and Integration Laboratory (MAIL) Bldg 9A.

  3. Performance characterization of a rotary centrifugal left ventricular assist device with magnetic suspension.

    PubMed

    Jahanmir, Said; Hunsberger, Andrew Z; Heshmat, Hooshang; Tomaszewski, Michael J; Walton, James F; Weiss, William J; Lukic, Branka; Pae, William E; Zapanta, Conrad M; Khalapyan, Tigran Z

    2008-05-01

    The MiTiHeart (MiTiHeart Corporation, Gaithersburg, MD, USA) left ventricular assist device (LVAD), a third-generation blood pump, is being developed for destination therapy for adult heart failure patients of small to medium frame that are not being served by present pulsatile devices. The pump design is based on a novel, patented, hybrid passive/active magnetic bearing system with backup hydrodynamic thrust bearing and exhibits low power loss, low vibration, and low hemolysis. Performance of the titanium alloy prototype was evaluated in a series of in vitro tests with blood analogue to map out the performance envelop of the pump. The LVAD prototype was implanted in a calf animal model, and the in vivo pump performance was evaluated. The animal's native heart imparted a strong pulsatility to the flow rate. These tests confirmed the efficacy of the MiTiHeart LVAD design and confirmed that the pulsatility does not adversely affect the pump performance.

  4. Benefits to the Europa Clipper Mission Provided by the Space Launch System

    NASA Technical Reports Server (NTRS)

    Creech, Stephen D.; Patel, Keyur

    2013-01-01

    The National Aeronautics and Space Administration's (NASA's) proposed Europa Clipper mission would provide an unprecedented look at the icy Jovian moon, and investigate its environment to determine the possibility that it hosts life. Focused on exploring the water, chemistry, and energy conditions on the moon, the spacecraft would examine Europa's ocean, ice shell, composition and geology by performing 32 low-altitude flybys of Europa from Jupiter orbit over 2.3 years, allowing detailed investigations of globally distributed regions of Europa. In hopes of expediting the scientific program, mission planners at NASA's Jet Propulsion Laboratory are working with the Space Launch System (SLS) program, managed at Marshall Space Flight Center. Designed to be the most powerful launch vehicle ever flown, SLS is making progress toward delivering a new capability for exploration beyond Earth orbit. The SLS rocket will offer an initial low-Earth-orbit lift capability of 70 metric tons (t) beginning with a first launch in 2017 and will then evolve into a 130 t Block 2 version. While the primary focus of the development of the initial version of SLS is on enabling human exploration missions beyond low Earth orbit using the Orion Multi-Purpose Crew Vehicle, the rocket offers unique benefits to robotic planetary exploration missions, thanks to the high characteristic energy it provides. This paper will provide an overview of both the proposed Europa Clipper mission and the Space Launch System vehicle, and explore options provided to the Europa Clipper mission for a launch within a decade by a 70 t version of SLS with a commercially available 5-meter payload fairing, through comparison with a baseline of current Evolved Expendable Launch Vehicle (EELV) capabilities. Compared to that baseline, a mission to the Jovian system could reduce transit times to less than half, or increase mass to more than double, among other benefits. In addition to these primary benefits, the paper will

  5. Design of a sensitive aptasensor based on magnetic microbeads-assisted strand displacement amplification and target recycling.

    PubMed

    Li, Ying; Ji, Xiaoting; Song, Weiling; Guo, Yingshu

    2013-04-03

    A cross-circular amplification system for sensitive detection of adenosine triphosphate (ATP) in cancer cells was developed based on aptamer-target interaction, magnetic microbeads (MBs)-assisted strand displacement amplification and target recycling. Here we described a new recognition probe possessing two parts, the ATP aptamer and the extension part. The recognition probe was firstly immobilized on the surface of MBs and hybridized with its complementary sequence to form a duplex. When combined with ATP, the probe changed its conformation, revealing the extension part in single-strand form, which further served as a toehold for subsequent target recycling. The released complementary sequence of the probe acted as the catalyst of the MB-assisted strand displacement reaction. Incorporated with target recycling, a large amount of biotin-tagged MB complexes were formed to stimulate the generation of chemiluminescence (CL) signal in the presence of luminol and H2O2 by incorporating with streptavidin-HRP, reaching a detection limit of ATP as low as 6.1×10(-10)M. Moreover, sample assays of ATP in Ramos Burkitt's lymphoma B cells were performed, which confirmed the reliability and practicality of the protocol. Copyright © 2013 Elsevier B.V. All rights reserved.

  6. The Application of the NASA Advanced Concepts Office, Launch Vehicle Team Design Process and Tools for Modeling Small Responsive Launch Vehicles

    NASA Technical Reports Server (NTRS)

    Threet, Grady E.; Waters, Eric D.; Creech, Dennis M.

    2012-01-01

    The Advanced Concepts Office (ACO) Launch Vehicle Team at the NASA Marshall Space Flight Center (MSFC) is recognized throughout NASA for launch vehicle conceptual definition and pre-phase A concept design evaluation. The Launch Vehicle Team has been instrumental in defining the vehicle trade space for many of NASA s high level launch system studies from the Exploration Systems Architecture Study (ESAS) through the Augustine Report, Constellation, and now Space Launch System (SLS). The Launch Vehicle Team s approach to rapid turn-around and comparative analysis of multiple launch vehicle architectures has played a large role in narrowing the design options for future vehicle development. Recently the Launch Vehicle Team has been developing versions of their vetted tools used on large launch vehicles and repackaged the process and capability to apply to smaller more responsive launch vehicles. Along this development path the LV Team has evaluated trajectory tools and assumptions against sounding rocket trajectories and air launch systems, begun altering subsystem mass estimating relationships to handle smaller vehicle components, and as an additional development driver, have begun an in-house small launch vehicle study. With the recent interest in small responsive launch systems and the known capability and response time of the ACO LV Team, ACO s launch vehicle assessment capability can be utilized to rapidly evaluate the vast and opportune trade space that small launch vehicles currently encompass. This would provide a great benefit to the customer in order to reduce that large trade space to a select few alternatives that should best fit the customer s payload needs.

  7. Integrated simulation of magnetic-field-assist fast ignition laser fusion

    NASA Astrophysics Data System (ADS)

    Johzaki, T.; Nagatomo, H.; Sunahara, A.; Sentoku, Y.; Sakagami, H.; Hata, M.; Taguchi, T.; Mima, K.; Kai, Y.; Ajimi, D.; Isoda, T.; Endo, T.; Yogo, A.; Arikawa, Y.; Fujioka, S.; Shiraga, H.; Azechi, H.

    2017-01-01

    To enhance the core heating efficiency in fast ignition laser fusion, the concept of relativistic electron beam guiding by external magnetic fields was evaluated by integrated simulations for FIREX class targets. For the cone-attached shell target case, the core heating performance deteriorates by applying magnetic fields since the core is considerably deformed and most of the fast electrons are reflected due to the magnetic mirror formed through the implosion. On the other hand, in the case of a cone-attached solid ball target, the implosion is more stable under the kilo-tesla-class magnetic field. In addition, feasible magnetic field configuration is formed through the implosion. As a result, the core heating efficiency doubles by magnetic guiding. The dependence of core heating properties on the heating pulse shot timing was also investigated for the solid ball target.

  8. AST Launch Vehicle Acoustics

    NASA Technical Reports Server (NTRS)

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

    2015-01-01

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

  9. Study of launch site processing and facilities for future launch vehicles

    NASA Astrophysics Data System (ADS)

    Shaffer, Rex

    1995-03-01

    The purpose of this research is to provide innovative and creative approaches to assess the impact to the Kennedy Space Center and other launch sites for a range of candidate manned and unmanned space transportation systems. The general scope of the research includes the engineering activities, analyses, and evaluations defined in the four tasks below: (1) development of innovative approaches and computer aided tools; (2) operations analyses of launch vehicle concepts and designs; (3) assessment of ground operations impacts; and (4) development of methodologies to identify promising technologies.

  10. Study of launch site processing and facilities for future launch vehicles

    NASA Technical Reports Server (NTRS)

    Shaffer, Rex

    1995-01-01

    The purpose of this research is to provide innovative and creative approaches to assess the impact to the Kennedy Space Center and other launch sites for a range of candidate manned and unmanned space transportation systems. The general scope of the research includes the engineering activities, analyses, and evaluations defined in the four tasks below: (1) development of innovative approaches and computer aided tools; (2) operations analyses of launch vehicle concepts and designs; (3) assessment of ground operations impacts; and (4) development of methodologies to identify promising technologies.

  11. Space Launch System Spacecraft and Payload Elements: Making Progress Toward First Launch

    NASA Technical Reports Server (NTRS)

    Schorr, Andrew A.; Creech, Stephen D.

    2016-01-01

    Significant and substantial progress continues to be accomplished in the design, development, and testing of the Space Launch System (SLS), the most powerful human-rated launch vehicle the United States has ever undertaken. Designed to support human missions into deep space, SLS is one of three programs being managed by the National Aeronautics and Space Administration's (NASA's) Exploration Systems Development directorate. The Orion spacecraft program is developing a new crew vehicle that will support human missions beyond low Earth orbit, and the Ground Systems Development and Operations program is transforming Kennedy Space Center into next-generation spaceport capable of supporting not only SLS but also multiple commercial users. Together, these systems will support human exploration missions into the proving ground of cislunar space and ultimately to Mars. SLS will deliver a near-term heavy-lift capability for the nation with its 70 metric ton (t) Block 1 configuration, and will then evolve to an ultimate capability of 130 t. The SLS program marked a major milestone with the successful completion of the Critical Design Review in which detailed designs were reviewed and subsequently approved for proceeding with full-scale production. This marks the first time an exploration class vehicle has passed that major milestone since the Saturn V vehicle launched astronauts in the 1960s during the Apollo program. Each element of the vehicle now has flight hardware in production in support of the initial flight of the SLS -- Exploration Mission-1 (EM-1), an un-crewed mission to orbit the moon and return. Encompassing hardware qualification, structural testing to validate hardware compliance and analytical modeling, progress in on track to meet the initial targeted launch date in 2018. In Utah and Mississippi, booster and engine testing are verifying upgrades made to proven shuttle hardware. At Michoud Assembly Facility in Louisiana, the world's largest spacecraft welding

  12. 14 CFR 415.119 - Launch plans.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

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

  13. SKYLAB (SL)-III - LAUNCH - KSC

    NASA Image and Video Library

    1973-08-17

    S73-32570 (28 July 1973) --- The Skylab 3/Saturn 1B space vehicle is launched from Pad B, Launch Complex 39, Kennedy Space Center, Florida, at 7:11 a.m. (EDT), Saturday, July 28, 1973. Skylab 3 is the second of three scheduled Skylab manned missions. Aboard the Skylab 3 Command/Service Module were astronauts Alan L. Bean, Owen K. Garriott and Jack R. Lousma. The Skylab 3 CSM later docked with the Skylab space station cluster in Earth orbit. In addition to the CSM and its launch escape system, the Skylab 3 space vehicle consisted of the Saturn 1B first (S-1B) stage and the Saturn 1B second (S-1VB) stage. (The Skylab 1/Saturn V space vehicle with the space station payload was launched from Pad A on May 14, 1973). Photo credit: NASA

  14. 14 CFR 420.19 - Launch site location review-general.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... site, at least one type of expendable or reusable launch vehicle can be flown from the launch point... × 10−6). (2) Types of launch vehicles include orbital expendable launch vehicles, guided sub-orbital expendable launch vehicles, unguided sub-orbital expendable launch vehicles, and reusable launch vehicles...

  15. An overview of the U.S. commercial space launch infrastructure : Quarterly Launch Report : special report

    DOT National Transportation Integrated Search

    1998-01-01

    The commercial space transportation industry has witnessed unparalleled growth in the number of commercial launches over the past few years. Last year witnessed the largest number yet, 35 commercial launches worldwide, nearly twice the 21 commercial ...

  16. OSIRIS-REx Rollout for Launch

    NASA Image and Video Library

    2016-09-07

    The United Launch Alliance Atlas V rocket arrives at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The launch vehicle will boost NASA’s Origins, Spectral Interpretation, Resource Identification, Security-Regolith Explorer, or OSIRIS-REx spacecraft. This will be the first U.S. mission to sample an asteroid, retrieve at least two ounces of surface material and return it to Earth for study. The asteroid, Bennu, may hold clues to the origin of the solar system and the source of water and organic molecules found on Earth.

  17. Scout Launch Lift off on Wallops Island

    NASA Image and Video Library

    1965-08-10

    Scout launch vehicle lift off on Wallops Island in 1965. The Scout launch vehicle was used for unmanned small satellite missions, high altitude probes, and reentry experiments. Scout, the smallest of the basic launch vehicles, is the only United States launch vehicle fueled exclusively with solid propellants. Published in the book " A Century at Langley" by Joseph Chambers pg. 92

  18. STS-132 Launch Tweetup

    NASA Image and Video Library

    2010-05-12

    NASA Astronaut Janet Voss speaks to participants at the two-day STS-132 Launch Tweetup at Kennedy Space Center, Thursday, May 13, 2010, in Cape Canaveral, Fla. NASA Twitter followers in attendance will have the opportunity to take a tour of NASA's Kennedy Space Center, view the space shuttle launch and speak with shuttle technicians, engineers, astronauts and managers. Photo Credit: (NASA/Paul E. Alers)

  19. Orion Launch from Helicopter - Aerials

    NASA Image and Video Library

    2014-12-05

    This helicopter view of Space Launch Complex 37 at Cape Canaveral Air Force Station in Florida shows the United Launch Alliance Delta IV Heavy rocket as it stands ready to boost NASA's Orion spacecraft on a 4.5-hour mission.

  20. Launch Pad in a Box

    NASA Technical Reports Server (NTRS)

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

    2016-01-01

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

  1. Launch Pad in a Box

    NASA Technical Reports Server (NTRS)

    Mantovani, James; Tamasy, Gabor; Mueller, Rob; Townsend, Van; Sampson, Jeff; Lane, Mike

    2016-01-01

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

  2. Space Shuttle Day-of-Launch Trajectory Design Operations

    NASA Technical Reports Server (NTRS)

    Harrington, Brian E.

    2011-01-01

    A top priority of any launch vehicle is to insert as much mass into the desired orbit as possible. This requirement must be traded against vehicle capability in terms of dynamic control, thermal constraints, and structural margins. The vehicle is certified to specific structural limits which will yield certain performance characteristics of mass to orbit. Some limits cannot be certified generically and must be checked with each mission design. The most sensitive limits require an assessment on the day-of-launch. To further minimize vehicle loads while maximizing vehicle performance, a day-of-launch trajectory can be designed. This design is optimized according to that day s wind and atmospheric conditions, which increase the probability of launch. The day-of-launch trajectory design and verification process is critical to the vehicle s safety. The Day-Of-Launch I-Load Update (DOLILU) is the process by which the National Aeronautics and Space Administration's (NASA) Space Shuttle Program tailors the vehicle steering commands to fit that day s environmental conditions and then rigorously verifies the integrated vehicle trajectory s loads, controls, and performance. This process has been successfully used for almost twenty years and shares many of the same elements with other launch vehicles that execute a day-of-launch trajectory design or day-of-launch trajectory verification. Weather balloon data is gathered at the launch site and transmitted to the Johnson Space Center s Mission Control. The vehicle s first stage trajectory is then adjusted to the measured wind and atmosphere data. The resultant trajectory must satisfy loads and controls constraints. Additionally, these assessments statistically protect for non-observed dispersions. One such dispersion is the change in the wind from the last measured balloon to launch time. This process is started in the hours before launch and is repeated several times as the launch count proceeds. Should the trajectory design

  3. Using Discrete Event Simulation to Model Integrated Commodities Consumption for a Launch Campaign of the Space Launch System

    NASA Technical Reports Server (NTRS)

    Leonard, Daniel; Parsons, Jeremy W.; Cates, Grant

    2014-01-01

    In May 2013, NASA's GSDO Program requested a study to develop a discrete event simulation (DES) model that analyzes the launch campaign process of the Space Launch System (SLS) from an integrated commodities perspective. The scope of the study includes launch countdown and scrub turnaround and focuses on four core launch commodities: hydrogen, oxygen, nitrogen, and helium. Previously, the commodities were only analyzed individually and deterministically for their launch support capability, but this study was the first to integrate them to examine the impact of their interactions on a launch campaign as well as the effects of process variability on commodity availability. The study produced a validated DES model with Rockwell Arena that showed that Kennedy Space Center's ground systems were capable of supporting a 48-hour scrub turnaround for the SLS. The model will be maintained and updated to provide commodity consumption analysis of future ground system and SLS configurations.

  4. NPP Satellite Launch

    NASA Image and Video Library

    2011-10-28

    NASA Deputy Administrator Lori Garver, left, watches the launch of the National Polar-orbiting Operational Environmental Satellite System Preparatory Project (NPP) at the National Oceanic and Atmospheric Administration (NOAA) Satellite Operations Center on Friday, Oct. 28, 2011 in Suitland, Md. U.S Congresswoman Donna Edwards, D-Md., is seen next to Garver. NPP is a joint venture between NASA and NOAA, and is the nation's newest Earth-observing satellite, which will provide data on climate change science, allow for accurate weather forecasts and advance warning for severe weather. NPP was launched from Vandenberg Air Force Base in California. Photo Credit: (NASA/Carla Cioffi)

  5. Zvezda Launch Coverage

    NASA Technical Reports Server (NTRS)

    2000-01-01

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

  6. Recommended Screening Practices for Launch Collision Aviodance

    NASA Technical Reports Server (NTRS)

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

    2015-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Creech, Stephen D.; May, Todd

    2013-01-01

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

  8. Controlling the size and magnetic properties of nano CoFe2O4 by microwave assisted co-precipitation method

    NASA Astrophysics Data System (ADS)

    Prabhakaran, T.; Mangalaraja, R. V.; Denardin, Juliano C.

    2018-02-01

    In this report, cobalt ferrite nanoparticles synthesized using microwave assisted co-precipitation method was reported. Efforts have been made to control the particles size, distribution, morphology and magnetic properties of cobalt ferrite nanoparticles by varying the concentration of NaOH solution and microwave irradiation time. It was observed that the rate of nucleation and crystal growth was influenced by the tuning parameters. In that way, the average crystallite size of single phase cobalt ferrite nanoparticles was controlled within 9-11 and 10-12 nm with an increase of base concentration and microwave irradiation time, respectively. A narrow size distribution of nearly spherical nanoparticles was achieved through the present procedure. A soft ferromagnetism at room temperature with the considerable saturation magnetization of 58.4 emu g-1 and coercivity of 262.7 Oe was obtained for the cobalt ferrites synthesized with 2.25 M of NaOH solution for 3 and 7 min of microwave irradiation time, respectively. The cobalt ferrite nanoparticles synthesized with a shorter reaction time of 3-7 min was found to be advantageous over other methods that involved conventional heating procedures and longer reaction time to achieve the better magnetic properties for the technological applications.

  9. KSC Launch Pad Flame Trench Environment Assessment

    NASA Technical Reports Server (NTRS)

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

    2010-01-01

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

  10. The development of a containment vessel and Dewar for the particle astrophysics magnet facility (ASTROMAG)

    NASA Technical Reports Server (NTRS)

    1985-01-01

    The ASTROMAG facility is the heart of a large charged particle detection and resolution system. ASTROMAG utilizes a superconducting magnet consisting of a large superconducting magnet coil with a stored magnetic energy of approximately 15 MJ. The active coil will have a mass of 1200 kg. This magnet will be cooled by a cryostat using a liquid helium Dewar for storage. The cryostat will have a series of gas-cooled shields with an external guard vacuum shield and an internal Dewar. The magnet and cryostat will be designed for shuttle or Delta launch and will be designed to withstand the internal pressure of expanded helium under full quench conditions when venting is prevented. The external guard vacuum shell is required to maintain a vacuum for Earth based testing and for cold launch of the cryostat and magnet. The magnet is designed to operate at 4.4 K with a peak field of 7.0 tesla. The superconducting material within the magnet is niobium titanium in a conductive matrix.

  11. STS-129 Launch Count Down

    NASA Image and Video Library

    2009-11-16

    A launch countdown sign is seen along the road at NASA's Kennedy Space Center on Monday, Nov. 16, 2009, Cape Canaveral, FL. The space shuttle Atlantis is scheduled to launch at 2:28 p.m. EST Nov. 16. Photo Credit: (NASA/Bill Ingalls)

  12. Achieving a Launch on Demand Capability

    NASA Astrophysics Data System (ADS)

    Greenberg, Joel S.

    2002-01-01

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

  13. NATO-3C/Delta launch

    NASA Technical Reports Server (NTRS)

    1978-01-01

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

  14. Launch Vehicles

    NASA Image and Video Library

    2007-09-09

    Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. In this HD video image, the first stage reentry 1/2% model is undergoing pressure measurements inside the wind tunnel testing facility at MSFC. (Highest resolution available)

  15. Environmental Assessment: Construction and Operation of an Alternate Drone Launch System at Tyndall Air Force Base

    DTIC Science & Technology

    2008-05-01

    matter less than or equal to 2.5 microns in aerodynamic diameter POL petroleum, oil , and lubricant RATO Rocket Assisted Take Off RCRA Resource... southeast of the Base airfield. The 325th Fighter Wing, Tyndall AFB, with the support of the Air Education and Training Command (AETC), has prepared this...segments. The drone launch facility is located just off U.S. Highway 98 southeast of the Base airfield (Figure 1-2). The proposed alternate drone

  16. Expedition 23 Launch Day

    NASA Image and Video Library

    2010-04-01

    Russian cosmonaut Expedition 23 Flight Engineer Mikhail Kornienko smiles as he awaits to have his Sokol suit pressure checked prior to launch, Friday, April 2, 2010, in Baikonur, Kazakhstan. Kornienko and fellow Expedition 23 crew members Soyuz Commander Alexander Skvortsov and NASA Flight Engineer Tracy Caldwell Dyson launched in their Soyuz TMA-18 rocket from the Baikonur Cosmodrome in Kazakhstan on Friday, April 2, 2010. Photo Credit: (NASA/Bill Ingalls)

  17. Expedition 23 Launch Day

    NASA Image and Video Library

    2010-04-01

    Expedition 23 NASA Flight Engineer Tracy Caldwell Dyson, left, talks with Soyuz Commander Alexander Skvortsov of Russia, while Flight Engineer Mikhail Kornienko of Russia has his Russian Sokol suit prepared for launch at the Baikonur Cosmodrome in Baikonur, Kazakhstan, Friday, April 2, 2010. The Expedition 23 crew members launched in their Soyuz TMA-18 rocket from the Baikonur Cosmodrome in Kazakhstan on Friday, April 2, 2010. (Photo Credit: NASA/Bill Ingalls)

  18. STS-1 - LAUNCH - KSC

    NASA Image and Video Library

    1981-04-15

    The Space Shuttle Columbia begins a new era of space transportation when it lifts off from NASA Kennedy Space Center (KSC). The reusable Orbiter, its two (2) fuel tanks and two (2) Solid Rocket Boosters (SRB) has just cleared the launch tower. Aboard the spacecraft are Astronauts John W. Young, Commander, and Robert L. Crippen, Pilot . 1. STS-I - LAUNCH KSC, FL KSC, FL Also available in 4x5 BW

  19. ARES I-X Launch

    NASA Image and Video Library

    2009-10-27

    NASA's Ares I-X rocket is seen through the windows of Firing Room One of teh Launch Control Center (LCC) at the Kennedy Space Center as it launches from pad 39b in Cape Canaveral, Fla., Wednesday, Oct. 28, 2009. The flight test will provide NASA with an early opportunity to test and prove flight characteristics, hardware, facilities and ground operations associated with the Ares I. Photo Credit: (NASA/Bill Ingalls)

  20. STS-135 Launch Day

    NASA Image and Video Library

    2011-07-07

    Warren Hinson, a NASA Emergency Response Team (ERT) member, keeps an eye out while flying near the Vehicle Assembly Building (VAB) prior to the launch of space shuttle Atlantis, STS-135, Friday, July 8, 2011, at Kennedy Space Center in Cape Canaveral, Fla. The launch of Atlantis, is the final flight of the shuttle program, a 12-day mission to the International Space Station. Photo Credit: (NASA/Bill Ingalls)

  1. The Crossbow Air Launch Trade Space

    NASA Technical Reports Server (NTRS)

    Bonometti, Joseph A.; Sorensen, Kirk F.

    2006-01-01

    Effective air launching of a rocket is approached from a broad systems engineering viewpoint. The elementary reasons for why and how a rocket might be launched from a carrier aircraft are examined. From this, a carefully crafted set of guiding principles is presented. Rules are generated from a fundamental foundation, derived from NASA systems study analyses and from an academic vantage point. The Appendix includes the derivation of a revised Mass Multiplier Equation, useful in understanding the rocket equation as it applies to real vehicles, without the need of complicated weight and sizing programs. The rationale for air launching, being an enormously advantageous Earth-To-Orbit (ETO) methodology, is presented along with the realization that the appropriate air launch solution may lie in a very large class of carrier aircraft; the pod-hauler. Finally, a unique area of the system trade space is defined and branded Crossbow. Crossbow is not a specific hardware design for air launch, but represents a comprehensive vision for commercial, military and space transportation. This document serves as a starting point for future technical papers that evaluate the air launch hypotheses and assertions produced during the past several years of study on the subject.

  2. Students Participate in Rocket Launch Project

    NASA Technical Reports Server (NTRS)

    2002-01-01

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

  3. Contributions of the NASA Langley Transonic Dynamics Tunnel to Launch Vehicle and Spacecraft Development

    NASA Technical Reports Server (NTRS)

    Cole, Stanley R.; Keller, Donald F.; Piatak, David J.

    2000-01-01

    The NASA Langley Transonic Dynamics Tunnel (TDT) has provided wind-tunnel experimental validation and research data for numerous launch vehicles and spacecraft throughout its forty year history. Most of these tests have dealt with some aspect of aeroelastic or unsteady-response testing, which is the primary purpose of the TDT facility. However, some space-related test programs that have not involved aeroelasticity have used the TDT to take advantage of specific characteristics of the wind-tunnel facility. In general. the heavy gas test medium, variable pressure, relatively high Reynolds number and large size of the TDT test section have made it the preferred facility for these tests. The space-related tests conducted in the TDT have been divided into five categories. These categories are ground wind loads, launch vehicle dynamics, atmospheric flight of space vehicles, atmospheric reentry. and planetary-probe testing. All known TDT tests of launch vehicles and spacecraft are discussed in this report. An attempt has been made to succinctly summarize each wind-tunnel test, or in the case of multiple. related tests, each wind-tunnel program. Most summaries include model program discussion, description of the physical wind-tunnel model, and some typical or significant test results. When available, references are presented to assist the reader in further pursuing information on the tests.

  4. 3850:..At the Cosmonaut Hotel crew quarters in Baikonur, Kazakhstan, Expedition 44 prime crewmember Kjell Lindgren of NASA (right) plants a tree in his name in a traditional pre-launch ceremony July 15. Assisting are crewmates Kimiya Yui of the Japan Aerospace Exploration Agency (left) and Oleg Kononenko of the Russian Federal Space Agency (Roscosmos, center), Yui, Kononenko and Lindgren will launch July 23, Kazakh time on the Soyuz TMA-17M spacecraft from the Baikonur Cosmodrome for a five-month mission on the International Space Station...Credit: Gagarin Cosmonaut Training Center.

    NASA Image and Video Library

    2015-07-15

    3850: At the Cosmonaut Hotel crew quarters in Baikonur, Kazakhstan, Expedition 44 prime crewmember Kjell Lindgren of NASA (right) plants a tree in his name in a traditional pre-launch ceremony July 15. Assisting are crewmates Kimiya Yui of the Japan Aerospace Exploration Agency (left) and Oleg Kononenko of the Russian Federal Space Agency (Roscosmos, center), Yui, Kononenko and Lindgren will launch July 23, Kazakh time on the Soyuz TMA-17M spacecraft from the Baikonur Cosmodrome for a five-month mission on the International Space Station. Credit: Gagarin Cosmonaut Training Center

  5. Ten-year space launch technology plan

    NASA Technical Reports Server (NTRS)

    1992-01-01

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

  6. Fabrication of Au nanoparticles supported on CoFe2O4 nanotubes by polyaniline assisted self-assembly strategy and their magnetically recoverable catalytic properties

    NASA Astrophysics Data System (ADS)

    Zhang, Zhen; Jiang, Yanzhou; Chi, Maoqiang; Yang, Zezhou; Nie, Guangdi; Lu, Xiaofeng; Wang, Ce

    2016-02-01

    This article reports the fabrication of magnetically responsive Au nanoparticles supported on CoFe2O4 nanotubes through polyaniline (PANI) assisted self-assembly strategy which can be used as an efficient magnetically recoverable nanocatalyst. The central magnetic CoFe2O4 nanotubes possess a strong magnetic response under an externally magnetic field, enabling an easy and efficient separation from the reaction system for reuse. The thorn-like PANI layer on the surface of CoFe2O4 nanotubes provides large surface area for supporting Au nanocatalysts due to the electrostatic interactions. The as-prepared CoFe2O4/PANI/Au nanotube assemblies exhibit a high catalytic activity for the hydrogenation of 4-nitrophenol by sodium borohydride (NaBH4) at room temperature, with an apparent kinetic rate constant (Kapp) of about 7.8 × 10-3 s-1. Furthermore, the composite nanocatalyst shows a good recoverable property during the catalytic process. This work affords a reliable way in developing multifunctional nanocomposite for catalysis and other potential applications in many fields.

  7. OSIRIS-REx Rollout for Launch

    NASA Image and Video Library

    2016-09-07

    A United Launch Alliance Atlas V rocket begins to roll out of the Vertical Integration Facility to Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The launch vehicle will boost NASA’s Origins, Spectral Interpretation, Resource Identification, Security-Regolith Explorer, or OSIRIS-REx spacecraft. This will be the first U.S. mission to sample an asteroid, retrieve at least two ounces of surface material and return it to Earth for study. The asteroid, Bennu, may hold clues to the origin of the solar system and the source of water and organic molecules found on Earth.

  8. OSIRIS-REx Rollout for Launch

    NASA Image and Video Library

    2016-09-07

    After leaving the Vertical Integration Facility, a United Launch Alliance Atlas V rocket is on its way to Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The launch vehicle will boost NASA’s Origins, Spectral Interpretation, Resource Identification, Security-Regolith Explorer, or OSIRIS-REx spacecraft. This will be the first U.S. mission to sample an asteroid, retrieve at least two ounces of surface material and return it to Earth for study. The asteroid, Bennu, may hold clues to the origin of the solar system and the source of water and organic molecules found on Earth.

  9. OSIRIS-REx Rollout for Launch

    NASA Image and Video Library

    2016-09-07

    After leaving the Vertical Integration Facility, a United Launch Alliance Atlas V rocket arrives at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The launch vehicle will boost NASA’s Origins, Spectral Interpretation, Resource Identification, Security-Regolith Explorer, or OSIRIS-REx spacecraft. This will be the first U.S. mission to sample an asteroid, retrieve at least two ounces of surface material and return it to Earth for study. The asteroid, Bennu, may hold clues to the origin of the solar system and the source of water and organic molecules found on Earth.

  10. OSIRIS-REx Rollout for Launch

    NASA Image and Video Library

    2016-09-07

    The United Launch Alliance Atlas V rocket arrives at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The launch vehicle will boost NASA’s Origins, Spectral Interpretation, Resource Identification, Security-Regolith Explorer, or OSIRIS-REx spacecraft. This will be the first U.S. mission to sample an asteroid, retrieve at least two ounces of surface material and return it to Earth for study. The asteroid, Bennu, may hold clues to the origin of the solar system and the source of water and organic molecules found on Earth. Photo credit: NASA/Kim Shiflett

  11. OSIRIS-REx Rollout for Launch

    NASA Image and Video Library

    2016-09-07

    A United Launch Alliance Atlas V rocket rolls out of the Vertical Integration Facility on its way to Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The launch vehicle will boost NASA’s Origins, Spectral Interpretation, Resource Identification, Security-Regolith Explorer, or OSIRIS-REx spacecraft. This will be the first U.S. mission to sample an asteroid, retrieve at least two ounces of surface material and return it to Earth for study. The asteroid, Bennu, may hold clues to the origin of the solar system and the source of water and organic molecules found on Earth.

  12. OSIRIS-REx Rollout for Launch

    NASA Image and Video Library

    2016-09-07

    A United Launch Alliance Atlas V rocket has left the Vertical Integration Facility and is on its way to Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The launch vehicle will boost NASA’s Origins, Spectral Interpretation, Resource Identification, Security-Regolith Explorer, or OSIRIS-REx spacecraft. This will be the first U.S. mission to sample an asteroid, retrieve at least two ounces of surface material and return it to Earth for study. The asteroid, Bennu, may hold clues to the origin of the solar system and the source of water and organic molecules found on Earth.

  13. OSIRIS-REx Rollout for Launch

    NASA Image and Video Library

    2016-09-07

    The United Launch Alliance Atlas V rocket has made the trek from the Vertical Integration Facility to Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The launch vehicle will boost NASA’s Origins, Spectral Interpretation, Resource Identification, Security-Regolith Explorer, or OSIRIS-REx spacecraft. This will be the first U.S. mission to sample an asteroid, retrieve at least two ounces of surface material and return it to Earth for study. The asteroid, Bennu, may hold clues to the origin of the solar system and the source of water and organic molecules found on Earth.

  14. OSIRIS-REx Rollout for Launch

    NASA Image and Video Library

    2016-09-07

    A United Launch Alliance Atlas V rocket rolled out of the Vertical Integration Facility and is on its way to Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The launch vehicle will boost NASA’s Origins, Spectral Interpretation, Resource Identification, Security-Regolith Explorer, or OSIRIS-REx spacecraft. This will be the first U.S. mission to sample an asteroid, retrieve at least two ounces of surface material and return it to Earth for study. The asteroid, Bennu, may hold clues to the origin of the solar system and the source of water and organic molecules found on Earth.

  15. ARES I-X Launch Prep

    NASA Image and Video Library

    2009-10-26

    Mission managers, from left, NASA Constellation Program manager Jeff Hanley, Ares I-X Launch Director Ed Mango, Ares I-X mission manager Bob Ess, Ground Operations Manager Philip "Pepper" Phillips, review the latest data in Firing Room One of the Launch Control Center (LCC) at the Kennedy Space Center during the launch countdown of the Ares I-X rocket in Cape Canaveral, Fla., Tuesday, Oct. 27, 2009. The flight test of Ares I-X will provide NASA with an early opportunity to test and prove flight characteristics, hardware, facilities and ground operations associated with the Ares I. Photo Credit: (NASA/Bill Ingalls)

  16. Japan's launch vehicle program update

    NASA Astrophysics Data System (ADS)

    Tadakawa, Tsuguo

    1987-06-01

    NASDA is actively engaged in the development of H-I and H-II launch vehicle performance capabilities in anticipation of future mission requirements. The H-I has both two-stage and three-stage versions for medium-altitude and geosynchronous orbits, respectively; the restart capability of the second stage affords considerable mission planning flexibility. The H-II vehicle is a two-stage liquid rocket primary propulsion design employing two solid rocket boosters for secondary power; it is capable of launching two-ton satellites into geosynchronous orbit, and reduces manufacture and launch costs by extensively employing off-the-shelf technology.

  17. Mars Pathfinder Status at Launch

    NASA Technical Reports Server (NTRS)

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

    1996-01-01

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

  18. 47 CFR 51.217 - Nondiscriminatory access: Telephone numbers, operator services, directory assistance services...

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... to have access to its directory assistance services, including directory assistance databases, so... provider, including transfer of the LECs' directory assistance databases in readily accessible magnetic.... Updates to the directory assistance database shall be made in the same format as the initial transfer...

  19. Magnetic field-assisted gene delivery: achievements and therapeutic potential.

    PubMed

    Schwerdt, Jose I; Goya, Gerardo F; Calatayud, M Pilar; Hereñú, Claudia B; Reggiani, Paula C; Goya, Rodolfo G

    2012-04-01

    The discovery in the early 2000's that magnetic nanoparticles (MNPs) complexed to nonviral or viral vectors can, in the presence of an external magnetic field, greatly enhance gene transfer into cells has raised much interest. This technique, called magnetofection, was initially developed mainly to improve gene transfer in cell cultures, a simpler and more easily controllable scenario than in vivo models. These studies provided evidence for some unique capabilities of magnetofection. Progressively, the interest in magnetofection expanded to its application in animal models and led to the association of this technique with another technology, magnetic drug targeting (MDT). This combination offers the possibility to develop more efficient and less invasive gene therapy strategies for a number of major pathologies like cancer, neurodegeneration and myocardial infarction. The goal of MDT is to concentrate MNPs functionalized with therapeutic drugs, in target areas of the body by means of properly focused external magnetic fields. The availability of stable, nontoxic MNP-gene vector complexes now offers the opportunity to develop magnetic gene targeting (MGT), a variant of MDT in which the gene coding for a therapeutic molecule, rather than the molecule itself, is delivered to a therapeutic target area in the body. This article will first outline the principle of magnetofection, subsequently describing the properties of the magnetic fields and MNPs used in this technique. Next, it will review the results achieved by magnetofection in cell cultures. Last, the potential of MGT for implementing minimally invasive gene therapy will be discussed.

  20. Small, Low Cost, Launch Capability Development

    NASA Technical Reports Server (NTRS)

    Brown, Thomas

    2014-01-01

    A recent explosion in nano-sat, small-sat, and university class payloads has been driven by low cost electronics and sensors, wide component availability, as well as low cost, miniature computational capability and open source code. Increasing numbers of these very small spacecraft are being launched as secondary payloads, dramatically decreasing costs, and allowing greater access to operations and experimentation using actual space flight systems. While manifesting as a secondary payload provides inexpensive rides to orbit, these arrangements also have certain limitations. Small, secondary payloads are typically included with very limited payload accommodations, supported on a non interference basis (to the prime payload), and are delivered to orbital conditions driven by the primary launch customer. Integration of propulsion systems or other hazardous capabilities will further complicate secondary launch arrangements, and accommodation requirements. The National Aeronautics and Space Administration's Marshall Space Flight Center has begun work on the development of small, low cost launch system concepts that could provide dedicated, affordable launch alternatives to small, high risk university type payloads and spacecraft. These efforts include development of small propulsion systems and highly optimized structural efficiency, utilizing modern advanced manufacturing techniques. This paper outlines the plans and accomplishments of these efforts and investigates opportunities for truly revolutionary reductions in launch and operations costs. Both evolution of existing sounding rocket systems to orbital delivery, and the development of clean sheet, optimized small launch systems are addressed.

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